Descripción: PT6A-20 Maintenance Manual...
ATP INDEX COPYRIGHT
2006
COPYRIGHT IS NOT CLAIMED AS TO ANY PART OF AN ORIGINAL WORK PREPARED BY A UNITED STATES GOVERNMENT OFFICER OR EMPLOYEE AS PART OF THAT PERSONS OFFICIAL DUTIES OR BY ANY OTHER THIRD PARTY OFFICER OR EMPLOYEE AS PART OF THAT PERSONS DUTIES. "ATP" is a registered trademark of Aircraft Technical Publishers. All original authorship of ATP is protected under U.S. and foreign copyrights and is subject to written license agreements between ATP and its Subscribers. ALL RIGHTS RESERVED. NO PART OF THIS PUBLICATION MAY BE REPRODUCED, STORED IN A RETRIEVAL SYSTEM, OR TRANSMITTED IN ANY FORM BY ANY MEANS, ELECTRONIC, MECHANICAL, PHOTOCOPYING, RECORDING OR OTHERWISE, WITHOUT PRIOR WRITTEN PERMISSION OF THE PUBLISHER.
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ATP Grid Index to Manufacturer’s Publications:
Whitney Canada
Prat
PT6A-20 Series
PT6A-6
Engines
Maintendnce Manual Section
General
Topic Information
Title Page List of
Chapters (Table of Contents)
Record of Revisions Record of
Temporary
Revisions
(Highlights of Changes) Pages
Letter of Transmittal List of Effective
Service Bulletin List
Airworthiness Limitations
Part 1
Description
of
Engine
Introduction
Leading Particulars and Specifications General
Information
Detailed Information Air
Systems
Lubrication System
Ignition System Glow Plug Type (Pre-SB1429) Spark Igniter Type (Post-SB1429) Fuel System Introduction Fuel Fuel
Pump (Vane Type) Pump (Gear Type)
Fuel Control System
Fuel Control Unit Power Turbine Governor (PT6A-6 Series
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PT6A-20 Engines)
Publishers
Page
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5
Secti on
Topi c
Propeller Governor (PT6A-20A and -20B Engines) Temperature Compensator Fuel Control System Complete Operation (Typical) Fuel Dump Valve Fuel Manifold and Spray Nozzles Engine Controls and Instrumentation Propeller Non-Reversing Inst (PT6A-6 Engines) Propeller Reversing Inst (PT6A-6A Engines) PT6A-20 Engines) Propeller Reversing Inst (PT6A-6B PT6A-20B Engines) Propeller Reversing Inst (PT6A-20A Part 2
General Procedures
Engine Oil System Servicing Preparation for Service or Storage Introduction Removal /Installation
Engine Preservation/Depreservation Cleaning Introduction
Specific Parts Field Cleaning Internal Washes Fuel Nozzle
Engine
Cleaning
External Wash
Standard Practices Metal Particles-Identification
Marking of Parts Temporary Marking Methods Welding Standard Inspection Procedure Elbow Fittings
Touch-Up Solution Torque Recommendations Testing Introduction
Ground Safety Precautions Test Information
Extreme Weather Conditions Ground Testing
Checks After Idle
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Component Repair-Replacement Speed Adjustments Copyright
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Page
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5
Section
Topic
Engine Final Checkout Troubleshooting Consumable Materials
Part 3
Special
Line Maintenance
Tools
Removal and Installation
Propeller
Shaft Oil Seal
Power Section
Thermocouple Harness and Post-SB1246 Probes T5 Thermocouple. Harness. Bus-Bar Compressor Turbine Disk Turbine Inlet T4 Thermocouple Harness‘ T5
Post-SB1246
Engines, Post-SB1198) Glow Plugs and Cables (Pre-SB1429) T4 Trim Harness (PT6A-Series
Spark Igniters
and Igniter Cables (Post-SB 1429)
Gas Generator Case Drain Valves
Combustion Chamber Liner Power Turbine Governor and NF Tachometer-Generator
Governor (PT6A-20A and’-20B Engines)
Propeller
Air Inlet Screen
Inlet Fairing Winterized Heat Shield
Compressor Bleed Valve Fuel Control Unit Fuel
Pump Eng) Pump Outlet Filter (Vane-Type~Pump)(Pre-SB1071 Fuel Pump Init Scrn (Vane-Type Pump)(Pst-SB1071,-SB1112) Fuel Pmp Init Scrn (Gear Pump )(Post-SB1096, Pre-SB1155) Fuel PmpOutlt Filter (Gear Pump)(Pst-SB1155 PT6A-20A) Fuel Pmp Init Scrn (Gear Pump)(Post-SB1155 PT6A-20A) Temperature Compensator Fuel
Pneumatic Control Line (P3) and P3 Air Filter
Oil Filter
Oil´• Filter Housing (Post-SB1247) Oil Flter Check
Bypass Valve Assy (Post-SB1247)
Oil Pressure Relief Valve
Ignition System Ballast Tubes (Pre-SB1429) Ignition Current Regulator (Pre-SB1429) Ignition Exciter (Post-SB1429) Oil-to-Fuel Heater
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Section
Topic
Accessory Drive Seals
Propeller Reversing Inspection Control Linkage
Interconnect
Linkage
Corrosion
Tubing and’Hose Assemblies Accessories
In-Service
Inspection Inspection
Hot Section
Shaft Oil Seal
Propeller
Combustion Chamber Liner
Compressor Compressor Compresses Compressor Compressor
Turbine Blade Tip Clearance and Power Turbine Blades and Power Turbine Vanes Blades (First
Stage)
Turbine Vanes
Turbine Inlet-T4
Thermocouple
Harness
Thermocouple Harhess. Probes and Bus-Bay Intrstg Sealing Rings Compressor Trbn Shroud Housing Glow Plugs (Pre-SB1429)Spark Igniters and Spark Ignition System (Post-SB1429) Fuel Manifold Adapter Assemblies
T5
Oil Filter Element (Post-SB1038. Post-SB1118
Chip
PT6A-20A)
Dectector
Fuel
Pmp Init Screen Plclvance Revision No.
Otlt Fltr (Pst
SBi155
PT6A-20A)
67
Engine Unscheduled Inspection Part 4
Heavy Maintenance
Special
Tools
Removal
and Installation
Introduction
Engine Stands Power Turbine Vanes (Pre-SB1OG1
Post-SB1246)
Power Turbin Vane
Ring PT6A-20 (Post-SB1OG1- SB1246) Compressor Turbine Vanes a~nd Shroud Segments Large Exit Duct Starter-Gen Gearshaft Cntrfgl Breather Carbon Seal Scavenge Pump Inlet Screen
Inspection Repair 03/27/2006
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Page
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5
Section
Topic Introduction Helical Coil
Inserts
Reduction Gearbox
Assembly
Combustion Chamber Liner Exhaust Duct Turning Vane (Pre-SB1151 Engines) Exhaust Duct (Pre-SB1151
Compressor
Engines)
Inlet Case
Gas Generator Case Turbine Shroud
Grinding Assembly T5 Bus-Bar Terminal Straps or Lugs
Compressor
Accessory Gearbox T5 Terminal Block T5
Termocouple
Harness
Fireseals Inlet Fairing and
Support Ring
Insulated and Heated Pneumatic Tubes
Oil Filter Check Valve
Ignition Current Regulator Box Special Limits and Torque Recommendations Reduction Gearbox PT6A-6A Engines Reduction Gearbox
Pre-SB1124 PT6A-6,-6B and 20 Engines
Reduction Gearbox
Post-SB1124 PT6A-20 and PT6A-20A
Post-SB1046 PT6A-20
Eng, Post-SB1043/1046 PT6A-20A’ Eng
Eng
Pre/PostlSB1043 and Post-SB1046 PT6A-6 and PT6A-6B Eng PT6A-6A Engines eropeller Reversing Linkage Reversing Linkage T. PT6A-6B and PT6A-20 Engines PT6A-20A Engines Reversing Linkage Accessory Gearbox (All Eengines)’
End of Index
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Page
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NI FG,
INTRO
IMAINTENANCE IWANUAL TURBOPROP GAS TU RBINE ENGIN E
Nlodel(s) PT6A-6 SERIES AND -20 SERIES ENGINES
Manual Part No. 3015442 Issued 4
July
1973
The contents of this manual have been examined and found acceptable to the Minister in meeting the requirements of an Engine Maintenance Manual for the Pratt Whitney Canada PT6-6 Series and PT6A-20 Series engine models, as required by the Canadian Airworthiness Manual, Chapter 533.4 "lnstructions for Continued
Airworthiness".
PRATT 1000
WHITN’EY CANADA
Marie-Victorin, Longueuil, Quebec, Canada J4G 1Al
Jun 01/89 O (973 Pratt
Whitney Canada Corp.
PRINTED IN CANADA
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPRIETARY NOTICE
This document contains matter of proprietary nature and is delivered on the express condition that it is not to be disclosed or reproduced in whole or in part without the written consent of Pratt Whitney Canada Corp. This restriction does not limit the
obtained from other
right
sources.
to disclose
information
RECORD OF REVISIONS
MFG REV NO 20
DESCRIPTION See
Highlights
Correction to Revision No. 20 21
(See Highlights
ISSUEDATE
ATPREVDATE
INSERTEDBY
2112/99
4119/99
ATPIKS
2112/99
10115101
ATPIMT
211/02
5/29102
ATPIMG
22
See
Highlights
8/16102
10/30/02
ATPIRCL
23
See
Highlights
6/6/03
10/1/03
ATP/HW
24
See
Highlights
4/2/04
6/17/04
ATPIMG
25
See
Highlights
8/27/04
11/18/04
ATP/JSF
26
See
Highlights
11/26/04
2/18/05
ATP/MB
27
See
Highlights
6/1 0/05
7/22/05
ATP/VD R
28
See
Highlights
12/2/05
3/8/06
ATP/JSF
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
RECORD OF REVISIONS REV
ISSUE
NO.
DATE
DATE INSERTED
BY
1
Nov 15/73
P&WC
2
1 Jun 02/75
P&WC
3´•
Oct 04/76
P&WC
4
May 09/77
P&WC
5
1 Mar 15/78
P&WC
6
1 Jun 12/79
P&WC
7
1 Feb 01/80
P&WC
8
Sep
18/81
P&WC
9
Feb 14/83
P&WC
10
Oct 08/85
P&WC
11
I Sep
30/86
P&WC
12
1 Apr
11/88
P&WC
13
Jun 01/89
P&WC
14
May
01/91
P&WC
15
Jun 01/91
16
May
15/92
P&WC
17
May
15/93
P&WC
18
Nov 15/93
P&WC
19
Feb 27/98
P&WC
20
Feb 12/99
21
~un
2
24
25 2r,
4/03
Ar>r 2/04
1 ~ug 27/1)4 Nov-
26/04
2?
JLn~ ~0/05
28
n-e
2/05
ISSUE
DATE
NO.
DATE
INSERTED
BY
P&WC
1 Feb 01/2002 NUS
REV
Feb
12/99
P&WC
~r
01/02
P&WC
~f r230 Oa;l Oct Tun
1/03
ATP/HW
!?/04
ATP/MG
Oct
F25
ATP/JSF
1.8/05
Jul. 22/05 ~ar
8/n6
ATP!MB h~3R /~SP
RECORD OF REVISIONS
Jul
04/73
RECORD OF TEMPORARY REVISIONS
TEMP REV NO
DESCRIPTION
64
Part 2-Sec 2:2-16
65
Part 3-Sec 2:2-64
66
Part 3-Sec 2:2-66
67
Part 3-Sec 3:3-73
ATP REV
INSERT
DATE
REV
REMOVE
ISSUE DATE
DATE
BY
REMOVED
INCOR
BY
1/24/03
4/16/03
ATP/MG
10/1/03
23
ATP/HW
311106
4/5/06
ATPNP
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
RECORD OF ADVANCE REVISIONS
TR. NO.
CH/SE/SU
PAGE NO. 2-]. 6
h;2
i;l>art
45
Part
3
2-64
66
Part
3
2-66
67
Part
2
3
3-73
ISSUE
INSERTED
DATE
DATE
BY
REMOVED
1/24/03
ATP/MG
3/1./06
ATP \,IP
10/?/03
REMOVED BY
ATP/HW
RECORD OF ARs
Jul o4n3
Whitney Canada Corp.
Pratt
Pratt 1Whitney Canada
1000, Marie-Victorin
Longueuil, QuBbec, Canada J4G
1Al
A United
TBI. 450-677-9411
January 5,
Technologies Company
2006
REVISION TRANSMITTAL SHEET
TO:
Holders of the Pratt
Whitney
SUBJECT:
Canada Maintenance Manual for
Engines,
PT6A-6/-6A/-6B/-20/-20A/-20B
Manual Part No. 3015442.
Revision No. 28, dated Dec 02/2005
Please insert the attached Revision No. 28 pages into your copy of the PT6A-6/-6A/-6B/-20/-20A/-20B Maintenance Manual. Remove and destroy superseded pages.
page-block replacement (replacing an entire partial page-block replacement (replacing only the affected pages within
Revised data may be in the form of
page-block); or, page-block).
a
a
full
the
is most important that extreme care be exercised in updating your copy of the manual. To that you do not inadvertently discard pages that should be retained, the manual should updated in accordance with the Lists of Effective Pages.
tIeb with the new date but no visible change may contain and should be inserted as part of the revision.
Pages supplied the
user
ensure
coding changes transparent
to
Please add Revision No. 28 to the Record of Revisions.
Any discrepancies, problems or suggestions regarding this revision should be forwarded using the Pratt Whitney Canada Customer Feedback Sheet (RSVP), and directed to: Pratt
Whitney Canada 1000 Marie-Victorin
in
writing
Corp.
Longueuil, Quebec Canada J4G 1Al Attention: Email:
Fax:
Manager, Technical Publications (01PB4) publications pwc.ca (450) 647-2702
Customer Feedback Sheets are contained with new manuals and each may also submit your feedback via our on-line RSVP form available at: www. pwc .ca/e n/3_0/3_0_6/3_0_6_5_7 .as p.
subsequent revision. You
Page HIGHLIGHTS
1
Dec 02/2005
Pnrt
Whitney
Canada
Corp.
MAINTENANCE MANUAL PT6A-6/-6A/-6B/-20/-20A/-20B REVISION NO. 28 HIGHLIGHTS Location
Description of Change
Part 2 Section 1
OIL LEVEL CHECK Deleted CAUTION.
Engine
oil top up allowed
(Ref.
SB1001R24). Part 3 Section 3
INTRODUCTION Deleted CAUTION in Oil
System. Engine
oil
top up allowed
(Ref. SB1001R24).
Page HIGHLIGHTS
2
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART SECTION Title
FAG E
DATE Jun 01/89
Page
Record of Revisions
Jul 04/73
Record of Advance Revisions
Jul 04/73
LEP
1
Jun 10/2005
2 blank
Jun 10/2005
Part/Section
1
Feb 01/2002
List
2
Feb 01/2002
Advance
1
Jun 06/2003
Revision
2 blank
Jun 06/2003
1
Apr 02/2004
2
Apr 02/2004
3
Apr 02/2004 Apr 02/2004 Apr 02/2004 Apr 02/2004
Index
Service Bulletin List
4 5 6
FRONT MATTER LEP
Jun
10/20 5Page
1/2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART/SECTION LIST
PART/SECTION
TITLE
AIRWORTHINESS LIMITATIONS
Ain~vorthiness Limitations
1
GENERAL INFORMATION AND DESCRIPTION 1-1
Introduction
1-2
Leading
1-3
General Information
1-4
Detailed Information
1-5
Air
1-6
Lubrication
1-7
Ignition System
1-8
Fuel
1-9
Engine
1-10
Propeller Non-reversing
1-11
Propeller Non-reversing Installation (PT6A-6A Engines)
1-12
Propeller Non-reversing Installation (PT6A-6B PT6A-20 Engines)
1-13
Propeller Non-reversing Installation (PT6A-20A -20B Engines)
Particulars and
Specifications
Systems
System
System Controls and Instrumentation Installation
(PT6A-6 Engines)
and
and
GENERAL PROCEDURES
2
Oil
System Servicing
2-1
Engine
2-2
Preparation
2-3
Cleaning
2-4
Standard Practices
2-5
Torque Recommendations
2-6
Testing
2-7
Troubleshooting
2-8
Consumable Materials
for Service
or
Storage
PART/SECT LIST
Feb
01/2002Page
1
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART/SECTION
TITLE
3
LINE MAINTENANCE
Tools
3-1
Special
3-2
Removal and Installation
3-3
Inspection HEAVY MAINTENANCE
4
Tools
4-1
Special
4-2
Removal and Installation
4-3
Inspection
4-4
Repair
4-5
Spedial
Limits and
Torque
Recommendations
PART/SECT LIST
Feb
01/2002Page
2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
SERVICE BULLETIN LIST This list identifies all Service Bulletins (SB’s) for the PT6A-6 Series and PT6A-20 Series engine models. Bulletins considered to have no effect on manual have the words "No Effect" added; effective bulletins give the date incorporated in the manual. The
incorporation of Service
Bulletins
on
the
engine
is recorded in the
engine log
book and
related documents.
early PT6A-6 and PT6A-20 Series (Engine Model Group #01) engine ATA 72-Series Service Bulletins are prefixed with Part No. 3026521 in lieu of a specific model identifier. New and recently revised SBs have the prefix PTGA.
All
For a current set of PT6A-6 Series engine Service Bulletins only, use ordering number 3020771. For a current set of PT6A-20 Series engine Service Bulletins only, use ordering number 3020772. NOTE:
´•I
The noted Service Bulletins are being continually revised to reflect P&WC recommendations for oil, fuels, engine planned maintenance, etc., and are concurrent with incorporation of engine modifications. Effect/Date
P&WC SE No.
ATA
SE No.
Rev. No.
1001
72-1001
23
PT6A-6/-6A/-6B/-20/-20A/-20B
See NOTE
1002
72-1002
23
PT6A-6/-6A/-68/-20/-20A/-20B
See NOTE
1003
72-1003
28
PT6A-6/-6A/-6B
See NOTE
1024
72-1024
1
1038
72-1 038
1040
72-1 040
1043
72-1 043
1045
72-1 045
1046
72-1 046
1047
72-1 047
1056
72-1056
1061
72-1061
1067
72-1 067
1069
72-1 069
1071
72-1071
1073
72-1073
1078
72-1 078
1083
72-1083
1088
72-1 088
Engine
Model
Incorporated
Applicability
Feb 01/80 Jul 04/73
Orig. Orig. Orig. Orig. Orig. Orig.
Nov 15/73 Jul 04/73 Jul 04/73 Jul 04/73
Nov 15/73 Feb 01/80
2
Jul 04/73
Orig. Orig. Orig. 1
Jul 04/73 Jul 04/73
Cancelled
Superseded by
SB1112
2
Jul 04/73
Orig. 1
No Effect Oct 04/76
Cancelled
Superseded by SB1255
No Effect Nov 15/73
Orig. Orig. Orig.
Jul 04/73
1094
72-1 094
1095
72-1 095
1096
72-1096
1102
72-1102
1103
72-1103
2
Jul 04/73
1104
72-11 04
1
Jul 04/73
1
Jul 04/73
Cancelled
Superseded by SB1155
No Effect Jul 04/73
Orig.
SE LIST
Apr
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1
1
1
1
1
Effect/Date
P&WC SE No.
ATA
SE No.
Rev. No.
1105
72-1105
1109
72-1109
1111
72-1111
1112
72-1112
1114
72-1114
Orig. Orig. Orig. Orig. Orig.
Engine
Model
Incorporated
Applicability
No Effect No Effect No Effect Jul 04/73
No Effect
Never Issued
1118
72-1118
1
Jan 12/79
1124
72-1124
1
No Effect
1127
72-1127
1134
72-1134
Jul 04/73
1137
72-1137
Orig. Orig. Orig.
1138
72-1138
3
No Effect
1139
72-1139
Jul 04/73
1140
72-1140
1141
72-1141
1142
72-1142
1143
72-1143
Orig. Orig. Orig. Orig. Orig.
1144
72-1144
1
Oct 08/85
1146
72-1146
No Effect
1147
72-1147
Orig. Orig.
1148
72-1148
2
No Effect
1149
72-1149
4
No Effect
1150
72-11 50
Orig.
Nov 15/73
1151
72-1151
4
Jan 12/79
1155
72-1155
1
Oct 08/85
1156
72-1156
Orig.
No Effect
1157
72-1157
1
Oct 08/85
1165
72-1165
Orig.
Jul 04/73
Nov 15/73
Jul 04/73
No Effect No Effect No Effect
Jul 04/73
Jul 04/73
1166
72-1166
1
No Effect
1167
72-1167
3
No Effect
1168
72-1168
Orig.
No Effect
Cancelled
Superseded by
SB1287
Cancelled
Superseded by
SB1103
No Effect
1171
72-1171
1
1173
72-1173
Orig.
1174
72-1174
1
1176
72-1176
Orig.
No Effect
1177
72-1177
3
No Effect
1179
72-1179
1180
72-1180
Jul 04/73
1181
72-1181
Orig. Orig. Orig.
No Effect No Effect
No Effect
No Effect
1182
72-1182
1
Oct 04/76
1183
72-1183
1
Oct 04/76
1185
72-1185
Orig.
Oct 04/76
1188
72-1188
3
No Effect
1191
72-1191
3
No Effect
1194
72-1194
1
Mar 15/78
SE LIST
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Effect/Date
P&WC SE No.
ATA
SE No.
Rev. No.
1195
72-1195
Orig.
1198
72-1198
1200
72-1200
1203
72-1203
1206
72-1206
2
Jun 02/75
1207
72-1207
1
No Effect
1210
72-1210
2
Mar 15/78
1212
72-1212
2
Oct 08/85
1213
72-1213
3
Engine ModelApplicability
Incorporated No Effect 18/81
2
Sep
1
No Effect
No Effect
Orig.
Cancelled
Superseded by SB1234
No Effect
1217
72-1217
4
Jan 12/79
1218
72-1218
3
Oct 04/76
1221
72-1221
1223
72-1223
6
No Effect
1224
72-1224
2
No Effect
1226
72-1226
1
No Effect
1227
72-1227
3
Mar 15/78
1228
72-1228
2
No Effect
1232
72-1232
2
No Effect
1233
72-1233
2
No Effect
1234
72-1234
1
Oct 04/76
1236
72-1236
2
No Effect
1239
72-1239
1240
72-1240
3
1244
72-1 244
20
1245
72-1 245
3
1246
72-1 246
3
Sep Sep
1247
72-1 247
5
Feb 14/83
1248
72-1248
2
No Effect
1249
72-1249
No Effect
Orig.
No Effect
Orig.
No Effect PTGA- 6/-6PJ- 6 B/-2 0/-2 0A/-2 0 B
See NOTE
May
Orig. Orig.
18/81 18/81
09/77
No Effect
1254
72-1254
1255
72-1255
4
No Effect
1257
72-1257
3
No Effect
1258
72-1258
4
No Effect
1261
72-1261
2
No Effect
1262
72-1262
2
No Effect
1263
72-1263
2
No Effect
1267
72-1267
1268
72-1268
1270
72-1270
1272
72-1272
1273
72-1273
1275
72-1275
1
No Effect
1276
72-1 276
3
Sep
1277
72-1277
2
No Effect
No Effect
Orig. Orig.
No Effect No Effect
1 2
No Effect
Cancelled
No Effect
Orig.
SE LIST
18/81
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Effect/Date
P&WC SE No.
ATA
SE No.
Rev. No.
1281
72-1281
2
No Effect
1285
72-1285
1
No Effect
1287
72-1287
2
No Effect
1293
72-1293
1
No Effect
1294
72-1294
1
Sep
Engine
Model
Applicability
Incorporated
30/86
1297
72-1297
1
No Effect
1299
72-1299
Orig.
No Effect
1300
72-1300
1
No Effect
1316
72-1316
1
Feb 14/83
1318
72-1318
3
No Effect
1321
72-1321
2
No Effect
1322
72-1322
Orig.
No Effect
1323
1
No Effect
1324
72-1323 72-1324
3
Sep 30/86
1328
72-1328
Orig.
No Effect
1331
72-1331
1
No Effect
1332
72-1332
Orig.
No Effect
1338
72-1338
2
No Effect
1339
72-1339
2
No Effect
1354
72-1354
3
No Effect
1357
72-1357
2
No Effect
1359
72-1359
No Effect
1361
72-1361
Orig. Orig.
1367
72-1367
3
No Effect
1377
72-1377
3
No Effect
1379
72-1379
2
Jun 01/89
1381
72-1381
3
No Effect
1386
72-1386
3
No Effect
1389
72-1389
1
No Effect
1390
72-1390
6
1391
72-1391
2
Apr11/88 Sep 30/86
1395
72-1395
Orig.
1397
72-1397
3
1398
72-1398
2
1404
72-1404
7
No Effect
1409
72-1409
1
No Effect
1413
72-1413
1
No Effect
1414
72-1414
No Effect
No Effect No Effect No Effect
Cancelled
Sep
30/86
1415
72-1415
Orig. Orig.
1416
72-1416
1
No Effect
1417
72-1417
72-1419
Orig. Orig.
No Effect
1419 1423
72-1423
1
No Effect
1427
72-1427
2
No Effect
No Effect
No Effect
SE LIST
Apr
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Effect/Date
P&WC SE No.
ATA
1429
72-1429
2
No Effect
1430
72-1430
4
No Effect
1431
72-1431
1
No Effect
1439
72-1439
2
Jun 01/89
1441
72-1441
2
No Effect
1447
72-1447
2
No Effect
1457
72-1457
1
No Effect
1465
72-1465
1
No Effect
1466
72-1465
Orig.
No Effect
1470
72-1470
2
No Effect
1474
72-1474
72-1476
1478
72-1478
Orig. Orig. Orig.
No Effect
1476 1479
72-1479
1
No Effect
1481
72-1481
1
No Effect
1484
72-1484
1
No Effect
1485
72-1485
No Effect
1486
72-1486
Orig. Orig.
SE No.
Rev. No.
Engine ModelApplicability
Incorporated
No Effect No Effect
No Effect
1487
72-1487
1
No Effect
1488
72-1488
No Effect
1489
72-1489
1490
72-1490
Orig. Orig. Orig.
1492
72-1492
1
No Effect
1493
72-1493
No Effect
1498
72-1498
1501
72-1501
1503
72-1503
Orig. Orig. Orig. Orig.
1506
72-1506
1
No Effect
1508
72-1508 72-1509
1518
72-1518
1522
72-1522
1524
72-1524
1527
72-1527
Orig. Orig. Orig. Orig. Orig. Orig.
No Effect
1509
1534
72-1534
3
No Effect
1541
72-1541
Orig.
No Effect
1544
72-1544
1
No Effect
1553
72-1553
Orig. Orig.
No Effect No Effect
No Effect No Effect
No Effect
No Effect Feb 27/98
No Effect No Effect No Effect No Effect No Effect
No Effect
1554
72-1554
1561
72-1561
2
1563
72-1563
Orig.
No Effect
1564
72-1564
3
No Effect
1567
72-1567
2
No Effect
1568
72-1568
2
No Effect
SE LIST
Apr
PRATT
WHITNEY CANADA
IVIAINTENANCE MANUAL MANUAL PART NO. 3015442
Effect/Date
F~&WC SE No.
ATA SE No.
Rev. No.
1571
72-1571
2
No Effect
1578
72-1578
1
No Effect
1587
72-1587
1597
72-1597
Orig. Orig.
No Effect
1598
72-1598
1
No Effect
1599
72-1599
No Effect
No Effect
1606
72-1606
Orig. Orig.
1610
72-1610
2
1614
72-1614
1803
72-1803
Orig. Orig.
Engine ModelApplicability
Incorporated
No Effect
No Effect No Effect
PT6A-20/-20A/-20B
SE LIST
See NOTE
Apr
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS PAGE
SUBJECT AIRWORTHINESS LIMITATIONS 1.
General
1
AIRWORTHINESS CONTENTS
Feb
01/20 2Page
1/2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART
SECTION
PAGE
DATE
1
Feb 01/2002
2 blank
Feb 01/2002
1
Feb 01/2002
2 blank
Feb 01/2002
Airworthiness
1
Feb 01/2002
Limitations
2 blank
Feb 01/2002
LEP
Contents
AIRWORTHINESS LEP
Feb
01/20 2Page
1/2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AIRWORTHINESS LIMITATIONS
1.
General The Airworthiness Limitations section
specifies mandatory
Rotor
Component
Service Life
Intervals and approved Oils and Fuels required for Limits, Scheduled Inspection/Maintenance type certification. The Airworthiness Limitations section is approved by the Canadian
Minister of Transport and specifies maintenance required by any applicable airworthiness operational rule unless an alternative program has been approved by the Canadian Minister of Transport. For Rotor
Component
Service Life Limits refer to the latest revision of P&WC S.B. No.1002.
For Time Between Overhauls and Hot Section revision of P&WC S.B. No.1003.
Approved Oils
Approved
are
Fuels
Inspection Frequency
refer to the latest
listed in the latest revision of P&WC S.B. No.1001.
are
or
listed in the latest revision of Service Bulletin 1244.
AIRWORTHINESS
PA RT
DESCRIPTION OF ENGINE
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT
PAGE PART 1
SECTION 1
DESCRIPTION OF ENGINE
GENERAL INFORMATION AND DESCRIPTION
INTRODUCTION 1.
GENERAL
1-1-1
2.
MAINTENANCE CONCEPT
1-1-2
3.
CUSTOMER SUPPORT
1-1-2
4.
ACCESSORIES SUPPORT
1-1-2
5.
SUPPLEMENTARY PUBLICATION
1-1-2
6.
SERVICE BULLETINS
1-1-2
7.
DIRECTIONAL REFERENCES
1-1-3
3.
FITS AND CLEARANCES
1-1-3
9.
TOOL PROCUREMENT
1-1-3
10.
SUPPLIERS AND SUPPLIER SERVICES
1-1-3
11.
CONSUMABLE MATERIALS
1-1-3
SECTION 2
LEADING PARTICULARS AND SPECIFICATIONS
1.
GENERAL
1-2-1
2.
FRONT AND REAR ACCESSORY DRIVES
1-2-2
3.
FUEL AND LUBRICATION SYSTEMS
1-2-2
4.
METAL SHIPPING CONTAINER
1-2-4
5.
FIBERBOARD SHIPPING CONTAINER
1-2-4
SECTION 3 1.
GENERAL INFORMATION
GENERAL
SECTION 4
1-3-1
DETAILED INFORMATION
1.
GENERAL
1-4-1
2.
COMPRESSOR INLET CASE
1-4-1
PART 1
CONTENTS
Aug
PRA~T
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
PAGE
SUBJECT SECTION 4
DETAILED INFORMATION
(Cont’d)
3.
COMPRESSOR ROTOR AND STATOR ASSEMBLY
1-4-1
4.
GAS GENERATOR CASE
1-4-7
5.
COMBUSTION CHAMBER LINER
1-4-11
6.
TURBINE SECTION
1-4-11
7.
COMPRESSOR TURBINE VANES
1-4-11
8.
COMPRESSOR TURBINE
1-4-15
9.
INTERSTAGE BAFFLE
1-4-15
10.
POWER TURBINE VANES
1-4-15
11.
POWER TURBINE
1-4-15
12.
POWER TURBINE SUPPORT HOUSING
1-4-16
13.
NO. 3 AND 4 BEARINGS
1-4-16
14.
REDUCTION GEARBOX STAGE
(PTGA-SERIES ENGINES)- TWO 1-4-16
15.
TORQUEMETER
1-4-20
16.
EXHAUST DUCT
1-4-21
17.
ACCESSORY GEARBOX
1-4-21
18.
ENGINE LIFTING POINTS
1-4-23
SECTION 5 -AIR SYSTEMS 1.
GENERAL
1-5-1
2.
COMPRESSOR BLEED VALVE
1-5-1
3.
BEARING COMPARTMENT SEALS, TURBINE COOLING AND AIR BLEED SYSTEMS
1-5-1
SECTION 6
LUBRICATION SYSTEM
1.
GENERAL
1-6-1
2.
OIL TANK
1-6-1
3.
OIL PUMP
1-6-1
PART 1
CONTENTS
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS SUBJECT SECTION 6
PAGE LUBRICATION SYSTEM
(Cont’d)
4.
OIL FILTER ASSEMBLY
1-6-1
5.
OIL PRESSURE SYSTEM
1-6-3
6.
PITCH REVERSING VALVE SYSTEM
7.
SCAVENGE OIL SYSTEM
1-6-7
8.
BREATHER SYSTEM
1-6-8
9.
CENTRIFUGAL BREATHER
1-6-8
10.
OIL-TO-FUEL HEATER
1-6-9
11.
OIL SYSTEM INSTRUMENTATION
1-6-9
SECTION 7
(PT6A-6A ENGINES)
1-6-7
IGNITION SYSTEM
GLOW PLUG TYPE
(PRE-SB1429)
1.
GENERAL
1-7-1
2.
IGNITION CURRENT REGULATOR
1-7-1
3.
GLOW PLUGS
1-7-1
SPARK IGNITER TYPE
(POST-SB1429)
4.
GENERAL
1-7-4
5.
IGNITION EXCITER
1-7-4
6.
SPARK IGNITERS
1-7-4
SECTION 8
FUEL SYSTEM
INTRODUCTION 1.
GENERAL
FUEL PUMP 2.
(VANE TYPE)
GENERAL
FUEL PUMP 3.
1-8-1
1-8-1
(GEAR TYPE)
GENERAL
1-8-5
PART 1
CONTENTS
Aug
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT SECTION 8
PAGE FUEL SYSTEM
(Cont’d)
FUEL CONTROL SYSTEM 4.
GENERAL
1-8-5
FUEL CONTROL UNIT 5.
GENERAL
1-8-9
6.
FUEL SYSTEM
1-8-9
7.
POWER INPUT, SPEED GOVERNOR, AND ENRICHMENT SECTION
1-8-11
BELLOWS SECTION
1-8-13
8.
POWER TURBINE GOVERNOR 9.
(PT6A-6 SERIES AND PT6A-20 ENGINES)
GENERAL
1-8-16
PROPELLER GOVERNOR (PT6A-20A AND -208 ENGINES) 10.
GENERAL
1-8-17
TEMPERATURE COMPENSATOR 11.
GENERAL
FUEL CONTROL SYSTEM
1-8-17
COMPLETE OPERATION
(TYPICAL)
12.
ENGINE STARTING
1-8-17
13.
ACCELERATION
1-8-20
14.
GOVERNING
1-8-20
15.
ALTITUDE COMPENSATION
1-8-20
16.
DECELERATION
1-8-21
17.
REVERSE THRUST OPERATION
1-8-21
18.
STOPPING THE ENGINE
1-8-22
FUEL DUMP VALVE 19.
GENERAL
1-8-22
PART 1
CONTENTS
Plug
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS SUBJECT
PAGE
SECTION 8
FUEL SYSTEM
(Cont’d)
FUEL MANIFOLD AND SPRAY NOZZLES 20.
GENERAL
1-8-22
21.
FU EL MAN IFOLD ADAPTER ASSEMBLY
1 -8-24
SECTION 9
ENGINE CONTROLS AND INSTRUMENTATION
1.
GENERAL
1-9-1
2.
POWER CONTROL LEVER
1-9-1
3.
FUEL SHUT-OFF LEVER -208
4.
-20A AND
ENGINES)
1-9-1
PROPELLER CONTROL LEVER -20A AND -208
5.
(PT6A-6A, -68, -6/C20, -20,
(PT6A-6, -6A, -6B, -6/C20, -20,
ENGINES)
1-9-1
INTERTURBINE TEMPERATURE SENSING SYSTEM -20A AND -208 ENGINES)
(T5)
(PT6A-6/C20, -20, 6.
TURBINE TEMPERATURE SENSING SYSTEM AND -68 ENGINES)
(T4) (PT6A-6,
1-9-2
-6A 1-9-2
7.
OIL PRESSURE INDICATOR
1-9-2
8.
OIL TEMPERATURE INDICATOR
1-9-5
9.
TACHQM ETE R-G EN E RATOR
GAS G EN ERATOR
(Ng)
10.
TAC HOM ETE R-G EN E RATOR
POWE R TU RE I N E
(Nf)
11.
TORQUEMETER
1-9-5 1 -9-5
1-9-5
SECTION 10- PROPELLER NON-REVERSING INSTALLATION
(PT6A-6 ENGINES) 1.
GENERAL
1-10-1
2.
PROPELLER
1-10-1
3.
PROPELLER GOVERNOR
1-10-1
4.
PROPELLER GOVERNOR ON-SPEED CYCLE
1-10-3
5.
PROPELLER GOVERNOR OVERSPEED CYCLE
PART 1
1-10-3
1
CONTENTS
Aug
PRA~T
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT
FAG E
SECTION 10
PROPELLER NON-REVERSING INSTALLATION
(Cont’d) 6.
PROPELLER GOVERNOR UNDERSPEED CYCLE
1;10-3
7.
PROPELLER OVERSPEED GOVERNOR
1-10-5
8.
POWER TURBINE GOVERNOR
1-10-5
SECTION 11
PROPELLER REVERSING INSTALLATION
(PT6A-6A ENGINES) 1.
GENERAL
1-11-1
2.
PROPELLER
1-11-1
3.
PROPELLER GOVERNOR
1-11-3
4.
PROPELLER GOVERNOR ON-SPEED CYCLE
1-11-3
5.
PROPELLER GOVERNOR OVERSPEED CYCLE
1-11-5
6.
PROPELLER GOVERNOR UNDERSPEED CYCLE
1-11-5
7.
PROPELLER OVERSPEED GOVERNOR
1-11-6
8.
POWER TURBINE GOVERNOR
1-11-6
9.
PITCH REVERSING VALVE AND LINKAGE
1-11-6
10.
PROPELLER REVERSING INTERCONNECTING LINKAGE
1-11-7
11.
LOW PITCH CONTROL CYCLE
1-11-7
12.
HIGH PITCH CONTROL CYCLE
1-11-9
13.
REVERSE PITCH CONTROL CYCLE
1-11-9
14.
REVERSE TO LOW PITCH CONTROL CYCLE
SECTION 12
(PT6A-6B
1-11-10
PROPELLER REVERSING INSTALLATION
PT6A-20)
1.
GENERAL
1-12-1
2.
PROPELLER
1-12-1
3.
PROPELLER GOVERNOR
1-12-3
PART 1
CONTENTS
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SU BJ ECT SECTION 12
FAG E PROPELLER REVERSING INSTALLATION
(Cont’d)
4.
PROPELLER GOVERNOR ON-SPEED CYCLE
1-12-5
5.
PROPELLER GOVERNOR OVERSPEED CYCLE
1-12-5
6.
PROPELLER GOVERNOR UNDERSPEED CYCLE
1-12-5
7.
PROPELLER OVERSPEED GOVERNOR
1-12-6
8.
POWER TURBINE GOVERNOR
1-12-6
9.
FUEL CUT-OFF LEVER
1-12-6
10.
POWER CONTROL LEVER
1-12-9
11.
NON-STOL APPLICATIONS
1-12-10
SECTION 13
PROPELLER REVERSING INSTALLATION
(PT6A-20A AND PT6A-20B ENGINES) 1.
GENERAL
1-13-1
2.
PROPELLER
1-13-1
3.
PROPELLER GOVERNOR
1-13-5
4.
PROPELLER GOVERNOR ON-SPEED CYCLE
1-13-10
5.
PROPELLER GOVERNOR OVERSPEED CYCLE
1-13-10
6.
PROPELLER GOVERNOR UNDERSPEED CYCLE
1-13-11
7.
PROPELLER OVERSPEED GOVERNOR
1-13-11
8.
NON-STOL APPLICATIONS
1-13-11
PART 1
CONTENTS
PRA~
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART SECTION LEP
PART
PAGE 1 2
3 4 blank
Contents
1 2
3 4 5
6 7
8 blank
List of
1
Figures
2 3 4 blank
List of
1
Tables
2 blank
Section 1
1-1-1
1-1-2 1-1-3 1-1-4 blank
Section 2
Section 3
DATE
Aug Aug Aug Aug
SECTION
FAG E
DATE
27/2004
1-3-8 blank
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27/2004
1-3-9
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27/2004
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27/2004 1-4-1
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Section 4
27/2004
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1-4-10 blank
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Feb 01/2002
PART1
LEP
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART
PART DATE
FAG E
SECTION
DATE
SECTION
FAG E
Section 5
1-5-1
Feb 01/2002
1-8-21
Feb 01/2002
1-5-2
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1-8-22
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1-5-3
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Section 6
Section 7
Section 8
1-6-1
Feb 01/2002
1-6-2
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1-6-3
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1-9-1
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1-6-9
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Section 9
1-10-1
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1-10-2
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1-10-3
Feb 01/2002
1-7-2
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1-8-1
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1-8-9
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1-11-9
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1-8-10
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1-11-10
Feb 01/2002
1-7-1
Section 10
Section 11
1-8-11
Feb 01/2002
1-8-12
Feb 01/2002
1-12-1
Feb 01/2002
1-8-13
Feb 01/2002
1-12-2
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1-8-14
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1-12-3
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1-12-4
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Feb 01/2002
Section 12
PART1
LEP
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LIST OF EFFECTIVE PAGES
PART SECTION
Section 13
FAG E
DATE
1-12-10
Feb 01/2002
1-13-1
Feb 01/2002
1-13-2 blank
Feb 01/2002
1-13-3
Feb 01/2002
1-13-4 blank
Feb 01/2002
1-13-5
Feb 01/2002
1-13-6 blank
Feb 01/2002
1-13-7
Feb 01/2002
1-13-8 blank
Feb 01/2002
1-13-9
Feb 01/2002
1-13-10
Feb 01/2002
1-13-11
Feb 01/2002
1-13-12 blank
Feb 01/2002
PART1
LEP
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES FIGURE
PAGE
Front and Rear
Drives
Accessory
Particulars
Leading
PT6
Engine
-Cross Section
(Typical) Figure
PT6
Engine
-Airflow
1-3-2
Typical
PT6
Figure
Engine Figure
Figure
1-2-1
1-2-3
1-3-1
1-3-3 1-3-5
1-3-3
1-3-7
PT6A-6 Series
Engines
Right
Front View
Figure
1-3-4
1-3-9
PT6A-6 Series
Engines
Right
Rear View
Figure
1-3-5
1-3-10
PT6A-6 Series
Engines
Left Front View
Figure
1-3-6
1-3-11
PT6A-6 Series
Engines
Left Rear View
Figure
1-3-7
1-3-12
PT6A-20
Engine
Right
Front View
Figure
1-3-8
1-3-13
PT6A-20
Engine
Right
Rear View
Figure
1-3-9
1-3-14
PT6A-20
Engine
Left Front View
Figure
1-3-10
1-3-15
PT6A-20
Engine
Left Rear View
Figure
1-3-11
1-3-16
PT6A-20A
Engine
Right
Front View
Figure
1-3-12
1-3-17
PT6A-20A
Engine
Right
Rear View
Figure
1-3-13
1-3-18
PT6A-20A
Engine
Left Front View
Figure
1-3-14
1-3-19
PT6A-20A
Engine
Left Rear View
Figure
1-3-15
1-3-20
PT6
Engine
Exploded
View
Compressor
Inlet Case
Compressor
Rotor and Stater
Main
Bearing
Figure
Installation
1-4-1
1-4-3
1-4-2
1-4-5
and No.l
Assembly
(Typical) Figure
Combustion Chamber Liner
Compressor
(Typical) Figure
Figure
Area
Figure
1-4-3
1-4-6
1-4-4
1-4-9
1-4-5
and Power Turbine Area
Power Turbine No. 3 and No. 4
Bearing
1-4-12
Figure
Bearing
1-4-6
Areas
Figure
1-4-13 1-4-7
1-4-17
Two
Stage
Reduction Gearbox Cross Section
Figure
1-4-8
1-4-18
Two
Stage
Reduction Gearbox Cross Section
Figure
1-4-9
1-4-19
Torquemeter
Schematic
Figure
1-4-10
PART 1
1-4-22
LIST OF FIGURES
1
Aug
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES
FIGURE
PAGE
Twin Outlet Port Exhaust Duct
Accessory
Gearbox
Compressor
Cross Section
Bleed Valve
Engine
Gearbox
Lubrication
Figure
1-4-25 1-5-2
and Air Bleed
Systems (Typical) 1-5-3
Schematic
Installation
1-4-24
1-5-1
Cooling
Schematic PT6A-6/20
Ignition Current Regulator Plug
Turbine
1-4-11
1-4-12
Lubrication Schematic
Oil-to-Fuel Heater Flow
Glow
Figure
Schematic
Bearing Compartment Seals, Figure 1-5-2 Accessory
(Typical) Figure
Circuit
Figure
Figure
Figure
Figure
1-6-1
1-6-2
1-6-2
1-6-5
1-6-3
1-6-10
Diagram Figure
1-7-1
1-7-2
1-7-2
1-7-3
Fuel
System
Schematic
Figure
1-8-1
1-8-3
Fuel Control
System
Schematic
Figure
1-8-2
1-8-7
Engine
Fuel Control Unit Drive
Figure
Body Assembly
FCU Bellows Section Manual Override
1-8-3
Operation Figure Functional
System Figure
Temperature Compensator Fuel Ratio Curve for
1-8-10
Starting
1-8-4
1-8-12
Diagram Figure
1-8-5
1-8-14
1-8-6
1-8-15
Cross Section
Figure
1-8-7
and Acceleration Schedules
1-8-18
(Typical) Figure
1-8-8
1-8-19
Fuel Manifold
Adapter Assembly
Front Cross Section
Figure
1-8-9
1-8-23
Fuel Manifold
Adapter Assembly
Front Cross Section
Figure
1-8-10
1-8-25
Interturbine
Temperature (T5) Sensing System Figure
Turbine Inlet
1-9-1
Temperature (T4) Sensing System Figure
Typical Single-acting Propeller- Schematic Figure
Propeller Governor -Schematic Figure
1-9-2
1-10-1
Installation
Schematic
Reduction Gearbox
Propeller Reversing
Figure
Installation
1-9-4 1-10-2
1-10-2
Propeller Reversing
PART 1
1-9-3
1-10-4 1-11-1
Figure
1-11-2 1-11-2
LIST OF FIGURES
1-11-4
2
WHITNEY CANADA
PRA~T
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES
FIGURE
Propeller Control
PAGE Lever
Cam Slot
Terminology Figure
Propeller Reversing
Installation
Schematic
Propeller Reversing
Installation
Reduction Gearbox
Engine
Controls and
Propeller Reversing
Engine
Controls and
Reversing Installation
Reversing
Installation
Figure
Schematic Installation
PART 1
Figure
1-12-1
Figure
1-11-8 1-12-2
1-12-2
1-12-3
Figure
Figure
1-11-3
1-13-1 1-13-2
LIST OF FIGURES
1-12-4 1-12-7
1-13-3 1-13-7
WHITNEV CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF TABLES
PAGE
TITLE TABLE 1-2-1,
Engine Specifications
TABLE 1-2-2,
Engine Leading
TABLE 1-2-3,
Accessory
Drives
Particulars
Leading
TABLE 1-2-4, Fuel and Lubrication TABLE 1-2-5,
Metal
Shipping
1-2-1 1-2-1
Particulars
1-2-2
System Specifications
1-2-4
Container Data
TABLE 1-2-6, Fiberboard -Type PK562
Shipping Container
TABLE 1-2-7, Fiberboard
Shipping
1-2-4
Data
(PT6A-6, -6A,
-6B
Engines) 1-2-4
Container Data
(PT6A-20) -Type
PK1325
PART 1 LIST OF TABLES
1-2-5
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I GENERAL INFORMATION AND DESCRIPTION
SECTION 1
INTRODUCTION 1.
GENERAL A.
publication is compiled and issued by the Customer Support Department of Pratt Whitney Canada, Longueuil, Quebec, Canada. It includes approved and recommended maintenance procedures for turboprop engine models PT6A-6, -6A, -6B, -6/C20, -20, -20A and -20B. The PT6A-6/C20 is a -6 reworked by the manufacturer to -20 configuration. The PT6A-20A is similar to the -20 except for reversing linkage and exhaust duct. The PT6A-20B is modified from the -20 SB1206) to have reversing linkage similar to the -20A. All turboprop models except PT6A-6 have reversing pitch propeller
This
installations. B.
Because the PTGA-Series engines are under a continuing program of improvements in design and manufacture, it is anticipated that the appearance of certain parts or details may change as refinements are introduced. However, this publication will be revised as necessary to incorporate the latest approved data.
C.
Requests for pertinent information not covered in this publication and suggestions for modification or amplification of these instructions so as to increase their usefulness, will be welcomed by the Customer Support Department of Pratt Whitney Canada.
D.
Any discrepancies, problems or suggestions regarding this publication should be forwarded in writing, using the Pratt Whitney Canada Customer Feedback Sheet (RSVP), to: Pratt Whitney Canada 1000 Marie-Victorin Blvd
Longueuil, Canada Attention:
Corp.
Quebec J4G 1Al
Manager
Publications
Dept (01PB4)
Website: www.pwc.ca E-mail:
publications@ pwc.ca
E.
Customer Feedback Sheets are enclosed with new manuals and each subsequent revision. Additional forms may be obtained by contacting: The Supervisor, Publications Customer Services, at the above address.
F.
The on-line Customer Feedback Sheet
Whitney Canada
website
(RSVP form) (www.pwc.ca).
is also available
on
the Pratt
Page 1-1-1 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2.
MAINTENANCE CONCEPT A.
The maintenance functions for the PT6 engines described in this manual are divided into two basic levels; Line Maintenance and Heavy Maintenance. The scope of Line Maintenance consists of the removal and installation of external components, engine
accessories and Hot Section Inspection. Heavy Maintenance details repairs normally considered beyond the capabilities of the average line maintenance shop. The scope consists of the removal and installation of engine components and limited repairs to the hot section area, reduction gearbox and accessory gearbox. Repairs beyond this level are not recommended and should be accomplished by an approved overhaul facility. For Engine Condition Trend Monitoring System refer to Part 2, Section 6. 3.
CUSTOMER SUPPORT A.
Customer and
Support representatives
maintain contact with
operators and service activities or problem. Requests for
available for the investigation of any specific difficulty assistance and/or AOG support should be directed to: are
Pratt
Whitney
Canada
Corp.
1000 Marie-Victorin Blvd.
Longueuil,Quebec Canada
J4G1A1
Attention: Customer B.
Customer
Help
Support
Desk
(24-hour service):
US and Canada: 1-800-268-8000
International: 450-647-8000 Fax: 450-647-2888 Telex: DELETED Email: 4.
customerhelpdeskQ pwc.ca
ACCESSORIES SUPPORT Accessories may be sent for
repair
or
complete
overhaul to:
P&WC Accessories Services rue d’Auvergne (Area 2K) Longueuil, Quebec
333
Canada 5.
SUPPLEMENTARY PUBLICATION A.
6.
J4H 3Y3
Personnel concerned with the maintenance of these engines should familiarize themselves with the contents of the Parts Catalog (P/N 3015444), which lists and describes the saleable parts of the engines and illustrates their interrelationship.
SERVICE BULLETINS A.
Service Bulletins will be issued as required to provide information or instructions for modifying earlier production engines or parts to the latest configuration.
Page 1-1-2 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
DIRECTIONAL REFERENCES A.
8.
The terms right and left, clockwise and counterclockwise, upper and lower, and similar directional references will apply to the engine as viewed from the rear and the engine in a horizontal position.
FITS AND CLEARANCES A.
During
all
operations
which involve measurements, Clearances, Part 4.
frequent
reference should be made
to the Table of Fits and
9.
TOOL PROCUREMENT A.
Depending on the geographical special tools, should be sent to: (1)
location of the operator, requests for the
purchase of
United States: Kell-Strom Tool Co. 214 Church Street
Wethersfield, CT 06109 USA TEL: 860-529-6851 860-721-0658
(USA number)
1-800-851-6851
or
(24
hour service
Canada),
or
FAX: 860-257-9694
(2)
Canada and Elsewhere: Pratt
Whitney
Canada Inc.
1000 Marie-Victorin
Quebec J4G1A1
Longueuil, Canada
Attention: Sales 10.
Department
SUPPLIERS AND SUPPLIER SERVICES A.
of any companies provided in this publication as a possible source for services or supplies are furnished for information purposes only. Pratt Whitney required Canada does not endorse the work performed or supplies procured from these
The
names
companies. Further, Pratt degree, for the selection of 11.
Whitney Canada does not accept responsibility, to any companies for such work performed or supplies procured.
such
CONSUMABLE MATERIALS A.
Part 2, Section 8, Table 2-8-1, lists the consumable materials used in the maintenance of the engine.
B.
Material
Safety
Data Sheets
(MSDS) containing
information about Trade Name,
Safety
Hazards, Health Hazards, Reactivity, Spill or Leak Procedures, Special Protection Information, Special Precautions, and Transportation and Labelling are available from manufacturer. Read
prior
to
using
consumable materials.
Page 1-1-3/4 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
DESCRIPTION OF ENGINE
PART 1 SECTION 2
LEADING PARTICULARS AND SPECIFICATIONS
GENERAL
1.
A.
Leading particulars PT6A-20B engines
of the PT6A-6, PT6A-6A, PT6A-6B, PT6A-20, PT6A-20A and follows: (Refer to Tables 1-2-1 and 1-2-2)
are as
TABLE~1-2-1,
Engine Specifications JP-4 Fuel
Consumption
Takeoff
Max.
(59"F)
A-6
A-20
A-6
A-20A
A-6A
A-20B
A-20B
A-6A A-6B
A-20B
A-6B
A-20 A-20A A-20B
550
550
2200
2200
70
72
0.650
0.649
(2)
(2)
500
550
2200
2200
62
72
0.670
0.649
(1)
(2)
500
538
2200
2200
62
70
0.670
0.653
495
2200
2200
60
68
0.680
0.670
A-20 A-20A
A-6B
A-20B
578
579
579
566
(1)
Climb Max. Cruise
(Ib.) A-20
A-6
A-6A A-6B
525
(3) A-20A
A-20
A-20A
Cent Max.
LB/ESHP/HR AT 15"C
A-6 A-6A A-6B
A-6 A-6A
525
Jet Thrust
SHP
ESHP
Rating
Shaft RPM
495
471
522
(1)
Available to 18.3 "C
(65"F)
(2)
Available to 21.1 "C
(70 "F)
(3)
Rotor
Speed
Ambient ambient
Power Turbine 33,000 rpm
NOTE: Maximum Continuous is
an
emergency
TABLE 1-2-2,
rating only.
Engine Leading
Particulars
LEADING PARTICULARS
Engine Type
Free Turbine
Type of combustion chamber
Annular
Compression
ratio
6.3:1
Propeller shaft rotation (looking FWD)
Clockwise
Propeller shaft configuration (PT6A-6 and -20 Series)
Flanged
Page
1-2-1
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 1-2-2,
Engine Leading
Particulars
(Cont’d)
LEADING PARTICULARS
Propeller shaft gear ratio (PT6A-6 and -20 Series) Engine
diameter
Basic at Room
2.
0.0668:1
19.0 in.
Temperature
(482.6 mm)
Engine length
62.0 in.
Basic at Room Temperature (PT6A-6 and -20 Series)
(1575 mm)
Oil
Consumption (maximum) (10 hour period)
0.2 Ib/hr
Dry weight, (Approximate) (Standard equipment) (PT6A-6 and -20 Series)
275 Ib.
(0.091 kg/hr)
(125 kg)
FRONT AND REAR ACCESSORY DRIVES A.
For
leading particulars
of the front and
TABLE 1-2-3,
Accessory
rear
accessory drives, refer to Table 1-2-3.
Drives
Leading
Particulars Max.
Drive Pad
Torque
Rotation
Ratio
Continuous
Static
CW
0.293:1
170
1600
CCW
0.167:1
CCW
0.112:1
7
100
CCW
0.103:1
60
800
1
Starter-generator (1)
2
Fuel
3
Ng
4
Vacuum Air
5
OptionalAccessory
Drive
(1)
CW
0.321:1
135
800
6
OptionalAccessory
Drive
(1)
CCW
0.203:1
150
800
7
Propeller
CW
0.1273:1
50
850
8
Nf Tach Generator
CW
0.1273:1
7
100
9
Propeller OverspeedGovernor (2)
CW
0.1273:1
70
850
Pump/FCU (1)
Tach Generator
(1)
Pump (Optional) (1)
Governor
(2) (2)
NOTE: 1. Rear
Accessory
Drives
(100
Ng
37500
rpm).
NOTE: 2. Front
Accessory
Drives
(100
Nf 33000
rpm).
3.
FUEL AND LUBRICATION SYSTEMS A.
For
specifications
of the fuel and lubrication
systems, refer
to Table 1-2-4.
Page
1-2-2
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
6
AS VIEWED FROM REAR
AS VIEWED FROM FRONT
C7819B Front and Rear
Accessory Drives Figure 1-2-1
Leading
Particulars
Page
1-2-3
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 1-2-4, Fuel and Lubrication
System Specifications Specification
Nomenclature Fuel Oil
Refer to SE No. 1244
Specification
Refer to SE No. 1001
Specification
Oil Tank
2.3 US
Total Capacity
gallons (1.92 Imp. gallons,
8.70
gallons (0.58 Imp. gallons,
2.64
gallons (1.25 Imp. gallons,
5.68
liters) Oil Tank
0.7 US
Expansion Space
liters) Oil Tank
1.5 US
Usable Quantity
liters) 4.
METAL SHIPPING CONTAINER A.
For leading 1-2-5.
particulars
of the reusable
TABLE 1-2-5, Metal
engine metal shipping container, refer
Shipping
to Table
Container Data Data
Description Length
79 inches
(2001 mm)
Width
34 inches
(864 mm)
Height
38 inches
(965 mm)
Weight
400 Ib.
Pressure Tested at
10
Material
SAE 1010-1020
Specification
(181.4 kg)
psig
Paint Primer Coat
TT-P-664
Paint Finish Coat
MIL-E-7729
Semi-gloss 5.
FIBERBOARD SHIPPING CONTAINER A.
For
leading particulars
Table 1-2-6
or
of the non-reusable
engine
fiberboard
shipping container,
refer to
1-2-7.
TABLE 1-2-6, Fiberboard
Shipping Container
Data
(PT6A-6, -6A,
-6B
Engines) -Type
PK562
Data
Description Length
73.5 inches
(1867 mm)
Width
31.5 inches
(800 mm)
Height
37 inches
Weight (approximate)
160 Ibs
(940 mm)
(72.6 kg)
Page 1-2-4 Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 1-2-7, Fiberboard
Shipping
Container Data
(PT6A-20) -Type
PK1325
Data
Description
Length
68 inches
(1727 mm)
Width
26 inches
(660 mm)
Height
26 inches
(660 mm)
Weight (approximate)
210 Ibs
(95.3 kg)
Page
1-2-5/6
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
DESCRIPTION OF ENGINE
SECTION 3 1.
GENERAL INFORMATION
GENERAL
engines described throughout this publication are variants of the basic PT6 powerplant which is a lightweight free-turbine engine designed for use in fixed or rotary-wing aircraft. The PTGA series engines for use in fixed-wing aircraft are available in two configurations: the PT6A-6 which utilizes a non-reversing propeller and the PT6A-6A, -6B, -6/C20, -20, -20A and -208 which, though essentially similar, are equipped with additional features to provide control for reversing propeller applications.
A.
The
B.
All
C.
independent turbines; one driving a compressor in generator section, the second driving reduction gearing for propeller, operation. (See Figure 1-3-1)
engines
utilize two
the gas or
rotary-wing
Inlet air enters the engine through and annular plenum chamber formed by the compressor inlet case. From there it is directed to the compressor. The compressor consists of three axial stages and one centrifugal stage assembled as an integral unit, which
provides
a
compression
ratio of 6.3:1.
row of stater vanes, located between each stage of compression, diffuses the air, raises its static pressure and directs it to the next stage of compression. The compressed air is passed through diffuser pipes, turned ninety degrees in direction, then led through straightening vanes to the combustion chamber. (See Figure 1-3-2)
D.
A
E.
The combustion chamber liner located in the gas generator case consists of an annular reverse flow weldment with varying size perforations which provide an entry for the compressed air. The flow of air changes direction to enter the combustion chamber liner where it reverses direction and mixes with fuel. The location of the combustion
chamber liner eliminates the need for
a
long
shaft between the compressor and the
turbine, thus reducing the overall length and weight of the engine. F
into the combustion chamber liner by 14 simplex nozzles supplied by a manifold. The fuel/air mixture is ignited by two glow plugs (Pre-SB1429) or spark igniters (Post-SB1429) which protrude into the combustion chamber liner. The resultant gases expand from the combustion chamber liner, reverse direction and pass through the turbine guide vanes to the compressor turbine. The turbine guide vanes ensure that the expanding gases impinge on the turbine blades at the correct angle, with minimum loss of energy. The still expanding gases pass forward through a second set of stationary guide vanes to drive the power turbine. Fuel is
injected
common
G.
The compressor and power turbines are located in the approximate center of the engine with their shafts extending in opposite directions. This provides for simplified installation and inspection procedures. The exhaust gas from the power turbine is directed through an exhaust plenum to atmosphere via dual exhaust ports provided in the duct.
Page
1-3-1
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
H.
An accessory gearcase is located at the rear of the engine with the relevant accessory drives and mounting pads. The accessories are driven from the compressor by means of a coupling shaft which extends the drive through a conical tube in the oil tank
center-section. An integral oil tank with a capacity of 2.3 U.S. gallons: 8.70 liters) is provided in the compressor inlet case. i.
gallons (1.92 Imperial
A
planetary gearbox located in the front of the engine, provides the speed reduction between the power turbine and the propeller shaft (PTGA series engines). The PTGA series engines have a two stage planetary gearbox. Engine output is accurately indicated by
means
of
J.
Stations and
K.
For
an
integral torquemeter
flanges
specifications
are
of the
shown
on
device located in the
Figure
engine, refer
gearbox.
1-3-3.
to Table 1-2-1.
Page
1-3-2
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C5B PT6
Engine
-Cross Section
Figure
(Typical)
1-3-1
Page
1-3-3/4
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1
4i
L)
t 1)
C552A
PT6
Engine -Airflow Figure 1-3-2
Page 1-3-5/6 Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR TURBINE INLET
I
I I
I I
(5)
~4)
~31
INTERTURBINE
EXHAUST OUTLET
EXHAUST DUCT
--7
(7)
STATIONS
(6)
I
COMBUSTION CHAMBER INLET I
COMPRESSOR INLET
I
ENGINE INLET
(2)
~1
io
O
~ii
I....
I
C
FLANGES REDUCTION GEARBOX TO EXHAUST CASE
(A)
(B)
~C)
(D)
~E)
~F)
I
I
I
I
I
I
I
I
I
REDUCTION GEARBOX REAR CASE TO POWER TURBINE HOUSING SUPPORT
EXHAUST DUCT TO GAS GENERATOR CASE
I
C553B
Typical PT6 Engine Figure 1-3-3
Page
1-3-7/8
Feb 01/2002
INIIER EXIT DUCT TO COMPRESSOR TURBINE SHROUD HOUSING
EXHAUST DUCT TO POWER TURBINE VAWE HOUSING
OIL TANK TO ACCESSORY GEARBOX DIAPHRAGM GAS GENERATOR CASE TO COMPRESSOR INLET CASE
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
.ORIGINAL .;As iReceived
:By
TP C77465
PT6A-6 Series
Engines Right Front View Figure 1-3-4
Page
1-3-9
Feb 01/2002
PRATT
WHITNEY CANADA
MAINfEiNANCE MANUAL MANUAL PART NO. 3015442
ORIGINAL ~9s
Received:By aTP
It: Ll;n-l sr:~
~8-:
C77464 PT6A-6 Series
Engines Right Figure 1-3-5
Rear View
Page
1-3-10
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL´• PART
,N01
3015442
.ORIGINAL As
Received By ATP
C77463 PT6A-6 Series
Engines Left Figure 1-3-6
Front View
Page
1-3-11
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
ORIGINAL As;Received By ATP
C77466 PT6A-6 Series
Engines Left Figure 1-3-7
Rear View
Page
1-3-12
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MAINTENANCE MANUAL MANUAL PART:NO.
3b15442
.ORIGINAL As
Received’By ATP C77459 PT6A-20
Engine Right Figure 1-3-8
Front View
Page
1-3-13
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
.ORIGINAL As
Received BY AT:P C77460 PT6A-20
Engine Right Figure 1-3-9
Rear View
Page
1-3-14
Feb 01/2002
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
ORIGINAL ~s
Received:By ATP
C77461
PT6A-20
Engine Figure
Left Front View 1-3-10
Page
1-3-15
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
OR\G\NAIBY As Received .ATP C77462 PT6A-20
Engine Figure
Left Rear View 1-3-11
Page
1-3-16
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
:ORIGINAL As:Received By .AT P C77470 PT6A-20A
Engine Figure
Right Front
View
1-3-12
Page
1-3-17
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
ORIGINAL As ~Received BY ATP
C77468 PT6A-20A
Engine Figure
Right Rear
View
1-3-13
Page
1-3-18
Feb 01/2002
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
ORIGINAL As Received
´•By
ATP
C77467 PT6A-20A
Engine Left Front View Figure 1-3-14
Page
1-3-19
Feb 01/2002
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IVIAINTENANCE MANUAL MANUAL PART NO. 3015442
ORIGINAL As Received
By
ATP
C77471 PT6A-20A
Engine Left Rear Figure 1-3-15
View
Page
1-3-20
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART,1
DESCRIPTION,OF ENGINE
SECTION 4 1.
GENERAL A.
2.
DETAILED INFORMATION
This section describes in detail all
major
items of the
engine. (See Figure 1-4-1)
COMPRESSOR INLET CASE A.
The compressor inlet case (see Figure 1-4-2) consists of a circular casting, the front of which forms a plenum chamber for the passage of compressor inlet air. The rear portion, which consists of a hollow compartment, is used to form an integral oil tank. A large area circular wire mesh screen is bolted around the air intake and the rear of the gas
generator B.
case
to
preclude foreign object ingestion by
the compressor.
and labyrinth seal are contained within the The inlet centerbore. case bearing support is secured to the inlet case compressor centerbore flange by four bolts. A nut and shroud washer retains the No. 1 bearing outer race in its support housing. An oil nozzle, fitted at the end of a cored passage, provides lubrication to the rear of No. 1 bearing at approximately the 1 o’clock position.
The No. 1
bearing, bearing support
Other cored passages
are
provided
for pressure and scavenge oil
(see Figure
1-4-3). C.
3.
engine main oil filter, incorporating check and bypass valve assemblies, and a pressure relief valve are respectively located on the right hand side of the inlet case in 3 and 1 o’clock positions. A fabricated conical tube, complete with preformed packings, is located between the wall of the inlet case centerbore and centerbore of the accessory diaphragm, to form a passage for the coupling shaft driving the accessories. The oil pressure pump, connected to the oil filter housing, is driven by an accessory drive gear. The pump located in the bottom of the oil tank, is secured to the accessory diaphragm by four bolts.
The
COMPRESSOR ROTOR AND STATOR ASSEMBLY A.
The compressor rotor and stater assembly (see Figure 1-4-3) consists of three axial rotor stages, three interstage spacers, three Stater assemblies and a single-stage centrifugal impeller and housing. The blades fit into dove-tail grooves machined in the rotor disk
rims, and limited clearance between blade clicking heard during compressor
characteristic metallic
root and groove produces the rundown. Blade axial
by interstage spacers between the disks. The airfoil cross-section of differ from those of the second and third stages which are blades first-stage identical. The length of the blades differ in each stage, decreasing from first to third stage. The wide chord first stage blades provide increased impact resistance. movement is limited
the
Page
1-4-1/2
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
IB
~P
dl
I II
II
(12 13
~s
~2
/(14
10
7~
U\
15
4
LEGEND
16 17
2)
J~ 9)
~6
1
18)
19)
20) V
C555A PT6
Engine
1
Exploded View (Typical) Figure 1-4-1
Page
1-4-3/4
Feb 01/2002
1
I
1
1 1
1.2. 3. 4. 5. 6. 7. 8. 9.
PROPELLER REDUCTION GEARBOX POWER TURBINE SUPPORT HOUSING EXHAUST DUCT POWER TURBINE COMPRESSOR TURBINE COMBUSTION CHAMBER LINER FUEL MANIFOLD GAS GENERATOR CASE COMPRESSOR BLEED VALVE COMPRESSOR ASSEMBLY COMPRESSOR INLETCASE OIL-TO-FUEL HEATER DIP-STICKAND FILLER CAP ACCESSORY GEARBOX IGNITION CURRENTREGULATOR FUELCONTROL UNITANDPUMP
10. 11. 12. 13. 14. 15. 16. 17. AIR INLET SCREEN 18. IGNITION GLOW PLUG 19. COMPRESSOR TURBINE GUIDE VANES 20. POWER TURBINE GUIDE VANES
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
OIL INLET FROM FUEL HEATER AND OIL COOLER PRESSURE RELIEF VALVE HOUSING ,le
INLET CASE
O
1
FWD
1
PRESSURE OIL
DRAIN PLUG ORIFICE
OIL FILTER
HOUSING PORT
PRESSURE OIL BOSS
C562B
Compressor Inlet Case Figure 1-4-2
Page
1-4-5
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
SHORT SLEEVE AND SPACER ASSEMBLY (2)
COMPRESSOR INLET CASE
COMPRESSOR BLADE
COMPRESSOR INTERSTAGE AIR BLEED
NO. 1 BEARING OIL NOZZLE
IMPELLER
HOUSING OIL TANK CENTER TUBE
CENTRIFUGAL IMPELLER TIE ROD
(6)
COMPRESSOR FRONT STUB SHAFT LONG SPACER AND SLEEVE ASSEMBLY
ACCESSORIES GEARBOX COUPLING SHAFT
/I(
NO. 1 BEARING VANE AND SHROUD ASSEMBLY GAS GENERATOR CASE
-t
(3) COMPRESSOR REAR HUB
’i
NO. 1 BEARING OIL TRANSFER TUBE
C556A
Compressor
Rotor and Stater
Assembly Figure 1-4-3
and No.l
Bearing
Area
Page
1-4-6
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
The first and second stage stater assemblies each contain 44 vanes and the third stage contains 40 vanes. Each set of compressor stater vanes is held in position by a circular ring through which the vane ends protrude and to which they are brazed. The vane rings provide shrouds for the first, second and third stage rotor blades. Stater assemblies
impeller housing are retained to prevent rotation of the assembly, by lugs on vane rings engaging grooves on vane rings and impeller housing. Interstage pressure air (P2.5) is vented to the compressor bleed valve chamber in the gas generator case through slots in the third stage vane ring. and
impeller, and impeller housing are positioned in interstage spacer, a stater assembly and a rotor assembly. The rotating assembly is stacked and secured together by six tie-rods which are numbered during initial assembly. The impeller housing is secured in the gas generator case by eight eccentric bolts. The compressor stubshaft is a hollow forging, machined to accommodate the No. 2 bearing double labyrinth air seal rotor and the No. 2 bearing assembly. The No. 2 bearing, a roller type, supports the compressor stubshaft and the compressor rotor assembly in the gas generator case. (See Figure 1 -4-4).
C.
The compressor stubshaft, centrifugal that order, followed sequentially by an
D.
The compressor rear hub is an integral part of the first stage compressor rotor disk. The hub, a hollow forging, is machined to accommodate the No. 1 bearing labyrinth air seal rotor, a spacer, and the No. 1 bearing. The No. 1 bearing is a ball type, and supports the compressor rear hub and the compressor rotor assembly in the compressor inlet case. A short, hollow coupling, extemally splined at its protruding end, is secured within the
compressor E.
rear
hub
by
a
transverse
pin
which passes
through
the hub and
coupling.
complete compressor rotor and stater assembly is fitted into the center rear section generator case, which forms the compressor housing, and secured by the impeller housing at the front and the compressor inlet case at the rear.
The
of the gas
F
A short, hollow, coupling shaft, internally splined, locates on the splined hub coupling, to extend the compressor drive to the accessory gearbox input gearshaft. The coupling embodies a ball-lock at the front end to prevent end thrust on the input gearshaft roller
bearings. 4.
GAS GENERATOR CASE A.
The gas generator case is attached to the front flange of the compressor inlet case. It consists of two sections fabricated into a single structure. The rear inlet section provides a housing support for the compressor assembly. The No. 2 bearing with two air seals is located in the centerbore of the gas generator case. The bearing has a flanged outer race which is secured in the support housing by four bolts. The front and
spiral wound gaskets are each secured in the centerbore An oil nozzle with two jets, one in the front and the other in the bolts. case by eight 14 radial vanes brazed inside the double lubrication..The of the rear bearing, provides skin center section of the gas generator case, provide a pressure increase to the compressed air as it leaves the centrifugal impeller. The compressed air is then rear
stater air seals with their
of the
directed
through seventy straightening
vanes
diffuser and out to the combustion chamber
welded inside the gas
area
through
a
generator
case
slotted diffuser outlet baffle.
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1-4-7/8
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
SERIALNO. TO FRONT
~THRUST BEARING
r
SERIAL NO. TO FRONT
r
SECOND STAGE CARRIER BEARING
r
SPLIT INNER RACE- r PULLER GROOVE TO FRONT’X’ MARKS ALIGNED WITH MASTER SPLINE
INNER RACESERIAL NO. TO FRONT AND ALIGNED WITH MASTER SPLINE
OUTER RACESERIAL NO. TO FRONT
OUTER RACESERIAL NO. TO FRONT
r
INNER RACE SERIAL NO. TO FRONT AND ALIGNED WITH STUBSHAFT MASTER SPLINE
OUTER RACEFLANGE AND SERIAL NO. TO FRONT
r
SPLIT INNER RACEPULLER GROOVE TO REAR. ’X’ MARKS ALIGNED WITH OFFSET HOLES ON REAR HUB
OUTER RACESERIAL NO. TO REAR
CAGE AND BALLSSERIAL NO. TO REAR
CAGE AND BALLSSERIAL NO. TO FRONT
ACCESSORY INPUT DRIVE BEARINGS
MASTER SPLINE
I
OFFSET HOLE
rREAR HUB
STUBSHAFT
NO. 4
NO.3
MASTER NO.2 SPLINE
c;s
NOTE
CAUTION
ALL ACCESSORY DRIVE BEARINGS MUST BE REINSTALLED IN THEIR ORIGINAL LOCATIONS.
i. INNER RACES CAGE AND BALLS OF NO. 1 AND NO. 4 BEARING ARE ID IDENTICAL. 2. NO. 2 AND NO. 3 BEARINGS ARE IDENTICAL. 3. INTERMIXING OF BEARING COMPONENTS IS STRICTLY UNACCEPTABLE.
C1769A Main
Bearing Installation (Typical) Figure 1-4-4
Page
1-4-9/10
Feb 01/2002
NO. 1
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
The front section of the gas chamber liner. It consists of
generator
case
forms
an
outer
housing
for the combustion
circular structure provided with mounting bosses for the 14 fuel noule assemblies and common manifold. Mounting bosses are also provided at the six o’clock position for the fuel dump valve and combustion chamber front and rear drain valves. Two igniter plugs at the 4 and 8 o’clock positions, protrude into the a
combustion chamber liner to ignite the fuel/air mixture. Three equi-spaced pads on outer circumference of gas generator case, provide accommodation for flexible type engine mounts. The compressor bleed valve outlet port is located at the 8 o’clock position. 5.
COMBUSTION CHAMBER LINER A.
(see Figure 1-4-5) is of the reverse-flow type and annular heat-resistant liner open at one end. A series of straight, plunged and shielded perforations allow air to enter the liner in a manner designed to provide the best fuel/air ratios for starting and sustained combustion. Direction of air flow
The combustion chamber liner
consists
primarily of
an
located opposite the perforations. The perforations distribution at the compressor turbine inlet. The domed front end of the combustion chamber liner is supported inside the gas generator case seven of the fourteen fuel nozzles sheaths. The rear of the liner is supported by is controlled
by cooling rings temperature
ensure an even
by
sliding joints which fit into the inner and outer exit duct assemblies. The duct assemblies form an envelope which effectively changes the direction of the gas flow by providing an outlet in close proximity to the compressor turbine vanes. The outlet duct and heat assembly is attached to the gas generator case by seven equi-spaced support brackets in the case. The heat shield forms a passage through which compressor discharge air is routed for cooling purposes. A scalloped flange on the rear of the outer duct locks in the support brackets and secures the assembly. The center section of the assembly is bolted with the compressor turbine guide vane support to the centerbore
shield
of the gas generator 6.
(See Figure 1-4-6).
TURBINE SECTION A.
7.
case.
The turbine rotor section consists of two separate single-stage turbine slocated in the center of the gas generator case and completely enveloped by the annular combustion chamber liner. (See Figure 1-4-6).
COMPRESSOR TURBINE VANES A.
The compressor turbine vane assembly consists of 29 vanes located between the combustion chamber exit ducts and compressor turbine. The vanes, incorporating individual dowel pins on the inner platforms, are positioned in holes on the outer circumference of the inner support. Sealing is ensured by ceramic fiber cord packing on the outside diameter of the support which is secured to the centerbore of the gas generator by eight bolts. The outer platforms of the vanes, sealed with a chevron packing, fits into the shroud housing and small exit duct which are secured together with twelve
bolts. The shroud housing extends forward into two classified the power turbine stater housing, to form a seal between both compressor turbine shroud segments positioned in the shroud
provide
a
running
clearance for the compressor turbine
interstage sealing rings on housings. Fourteen housing act as a seal and assembly.
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1-4-11
Feb 01/2002
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
FUELNOZZLEPORT WITH SUPPORT BRACKET
(7)
~ai
i
:rj I‘ r
GLOW PLUG SLEEVE
FUEL NOZZLE PORT PLAIN (7)
(2)
C11
Combustion Chamber Liner
Figure
1-4-5
Page
1-4-12
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL MANIFOLD ADAPTER ASSEMBLY
TERMINAL BLOCK
COMBUSTION CHAMBER LINER ASSEMBLY
GAS GENERATOR CASE ASSEMBLY
Tt4 THERMOCOUPLE PROBE
T5 THERMOCOUPLE PROBE
COMBUSTION CHAMBER SMALL (INNER) EXIT DUCT ASSEMBLY
COMPRESSOR TURBINE GUIDE VANES
COMPRESSOR TURBINE VANE SUPPORT
EXHAUST DUCT ASSEMBLY
COMBUSTION CHAMBER LARGE (OUTER) EXIT DUCT ASSEMBLY
SINGLE BOLT ATTACHMENT MULTI-BOLT ATTACHMENT
SINGLE PLANE BALANCING DISK ASSEMBLY
INTERSTAGE BAFFLE ASSEMBLY
SINGLE BOLT ATTACHMENT MIO PLANE BALANCING DISK ASSEMBLY
POWER TURBINE GUIDE VANES
COMPRESSOR TURBINE POWER TURBINE
POWER TURBINE INTEGRAL VANE RING
C557C
Compressor
and Power Turbine Area
Figure
1-4-6
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Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
8.
COMPRESSOR TURBINE A.
The compressor turbine which consists of a classified weights, drives the compressor in
turbine disk, blades and counterclockwise direction. The two-plane balanced assembly is secured to the front stubshaft by a simplified center lock bolt (see Figure 1-4-6). A master spline is provided to ensure the disk assembly is always installed in a predetermined position to retain proper balance. The disk embodies a reference circumferential groove to enable
two-plane balanced
a
checking
of disk
growth
when
required.
The 58 blades in the compressor turbine disk are secured in fir-tree serrations machined in the outer circumference of the disk and held in position by individual rivets. The
that ensure a minimum amount of pick-up should the rotating into contact with the shroud segments. The required number of classified weights is determined during balancing procedures and riveted to the relevant flanges machined on the turbine disk. A small machined area on the rear face of the disk
blades blades
embody squealer tips come
provides 9.
a
sealing surface
to control the flow of turbine disk
cooling air.
INTERSTAGE BAFFLE A.
The compressor turbine is separated from the power turbine by an interstage baffle which prevents dissipation of turbine gases and consequent transmission of heat to the turbine disk faces. (See Figure 1-4-6). The baffle is secured to and supported by the power turbine vane ring. The center section of the baffle includes small circular lipped flanges on the front and rear faces. The flanges fit over mating rotor seals machined on the
respective turbine disk faces
to
provide
control of
cooling
air flow
through
the
perforated
center of the baffle. 10.
POWERTURBINEVANES A.
On PT6A-6 series, PT6A-6/C20, early PT6A-20 and PT6A-20B engines, the power turbine vane assembly consists of 19 cast vanes. The vanes are cast with dowel pin platforms which fit into the interstage baffle rim. The stater housing with the enclosed vane assembly is bolted to the exhaust duct and supports the two classified sealing rings at flange D. The rings are self-centering and held in position by retaining plates bolted to the rear face of the stater housing. On most PT6A-20, PT6A-20B and all PT6A-20A engines, the individual vanes are replaced by a power turbine vane ring with 19 integrally cast vanes.
11.
POWER TURBINE A.
The power turbine assembly consisting of a turbine disk, blades, and classified weights, drives the reduction gearing through the power turbine shaft in a clockwise direction. The disk is held to close tolerances and embodies a reference circumferential groove to permit disk growth check measurements when required. The turbine disk is splined to the turbine shaft and secured by a single center lockbolt and keywasher (See Figure 1-4-6). A master spline ensures the power turbine disk is always installed in a predetermined position to retain the original balance. The required number of classified is determined during balancing procedures and riveted to a flange on the face of the turbine disk. The power turbine blades differ from those of the compressor turbine in that they are cast complete with notched and shrouded tips. The 41 blades
weights rear
are
by fir-tree serrations in the turbine disk and held in position by individual rivets. tips rotate inside a double knife-edge shroud and form a continuous seal engine is running. This reduces tip leakage and increases turbine efficiency.
secured
The blade when the
Page
1-4-15
Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
12.
POWER TURBINE SUPPORT HOUSING A.
13.
The power turbine reduction gearbox
support housing consists of
a cylindrical housing attached to the by 12 studs. The housing provides support for the power turbine shaft assembly and two bearings (see Figure 1-4-7). A labyrinth type seal, secured at the rear of the housing, prevents oil leakage into the power turbine section. An internal oil transfer tube with four oil nozzles, provides front and rear lubrication to number three and four bearings. A scavenge tube inside the housing transfers bearing scavenge oil to the front of the engine.
rear case
NO. 3 AND 4 BEARINGS A.
The power turbine disk and shaft assembly is supported and secured in the power turbine shaft housing by two bearings, the No. 3 bearing which is a roller type and the No. 4
bearing which is a ball bearing (see Figures 1-4-7 and 1-4-4). The No. 3 bearing includes an inner race and a flanged outer race. The inner race is secured on the rear of the power turbine shaft together with the power turbine air seal and power turbine disk by the center lock bolt. The outer race is secured inside the power turbine shaft housing by four bolts and tabwashers. B.
bearing includes a split inner race and a flanged outer race. The split inner is secured on the front of the power turbine shaft, together with the first stage reduction gear coupling and a coupling positioning ring, by a keywasher and spanner nut. A puller groove is incorporated on the front half of the split inner race to facilitate
The No. 4 race
removal. The
flanged
outer race is secured inside the power turbine shaft
housing by
four bolts and
14.
REDUCTION GEARBOX
(PTGA-SERIES ENGINES)
TWO STAGE
A.
The reduction gearbox (see Figure 1-4-8 for PT6A-6 series engines, and Figure 1-4-9 for PT6A-20 series engines) is located at the front of the engine and consists of two castings bolted to the front flange of the exhaust duct. The first stage of reduction is contained in the rear case. Torque from the power turbine is transmitted through the power turbine shaft to the first stage sun gear.
B.
The first
stage
gear consists of a short hollow shaft which has an integral spur gear at the front end and externally splined at the rear. The external splines fit over the end of the power turbine shaft and engage the internal splines of a retainer coupling. The coupling is in turn splined to the turbine shaft and secured there by a retaining nut and keywasher. Two double coil retaining rings hold the sun gear in the retainer coupling. The spur gear end of the sun gear drives the three planetary gears in the first stage planet carrier.
C.
The first
stage ring gear
reduction
sun
is located in helical splines provided in the first stage reduction The gearbox torque developed by the power turbine is transmitted through the sun gear and planet gears to the ring gear which is opposed by the helical splines. This results in rotation of the planet carrier. The ring gear, though secured by the helical splines, is allowed to move axially between the case and three retaining plates. This rear case.
movement is used in the
torquemeter application (refer
to
Paragraph 15., following).
Page
1-4-16
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
THERMAL INSULATION BLANKET
EXHAUST DUCT
OIL NOZZLE ASSEMBLY
OIL STRAINER
TURBINE BLADES
(SHROUDED TIP)
FROM TORQUEMETER
FIRST STAGE
TURBINE DISK
CARRIER
CARRIER SLEEVE TURBINE LOCKING BOLT
PLAIN BEARING
POWER TURBINE AIR SEAL
REDUCTION GEARBOX REAR CASE
SCAVENGE OIL TUBE
RETAINER RING
TRANSFER TUBE NO. 3 BEARING NO. 4 BEARING
I
POWER TURBINE SHAFT HOUSING
POWER TURBINE SHAFT
C5588 Power Turbine No. 3 and No. 4 Figure 1-4-7
Bearing
Areas
Page
1-4-17
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
GOVERNOR DRIVE SHAFT GEAR FRONT CASE
ASSEMBLY
FLANGE
_J
OIL TRANSFER GALLERY
A
2NO STAGE SUN GEAR FLEXIBLE COUPLING REAR CASE ASSEMBLY
BEVEL GEAR
OIL SEAL
1STSTAGE PLANET GEAR
PROPELLER SHAFT
SPLINE ADAPTER
FLANGE
B
THRUST BEARING
TORQUEMETER CYLINDER AND PISTON
THRUST BEARING COVER
1ST STAGE RING GEAR
PROPELLER OIL TRANSFER HOUSING
2ND STAGE RING GEAR ROLLER BEARING 2ND STAGE PLANET GEAR
C419A
(PT6A-6 Series Engines) Two
Stage
Reduction Gearbox Cross Section Figure 1-4-8
Page
1-4-18
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FRONTCASEASSEMBLY
FLANGE
GOVERNOR DRIVE SHAFTGEAR
A
I
SECOND STAGE SUN GEAR OIL TRANSFER GALLERY
FLEXIBLE COUPLING REAR CASE
ASSEMBLY
~P
BEVEL GEAR
OIL SEAL
PROPELLER SHAFT
f=--
FIRST STAGE PLANET GEAR
~YB
Ij
SPLINE ADAPTER FLANGE
B
TORQUEMETER CYLINDER AND PISTON
THRUST BEARING THRUST BEARING COVER
FIRST STAGE RING GEAR
PROPELLER OIL TRANSFER HOUSING
I"
SECOND STAGE RING GEAR
ROLLER BEARING SECOND STAGE
CHIP DETECTOR
PLANETGEAR
(PT6A-20 Two
Stage
Series
Engines)
C1163A
Reduction Gearbox Cross Section
Figure
1-4-9
Page
1-4-19
Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
D.
stage reduction gearing is contained at the front of the reduction gearbox. stage planetary gears drive the second stage sun gear via a flexible coupling
The second The first
vibrations between the two rotating gear assemblies. The second five drives planet gears in the second stage carrier. A second stage gear ring gear is fixed by splines to the reduction gearbox front case and secured by three bolted retaining plates. The second stage carrier is in turn splined to the propeller shaft and secured by a retaining nut and shroud washer. A flanged roller bearing assembly, secured by four bolts to the case provides support for the second stage carrier and propeller shaft. An oil transfer tube and nozzle assembly fitted with preformed packings is secured within the propeller shaft by a retaining ring to provide lubrication to No. 4 which also
stage
dampens any
sun
bearing. E.
15.
gearbox front case are driven by a bevel gear mounted on the propeller shaft behind the thrust bearing assembly (see Figures 1-4-8 and 1-4-9). Propeller thrust loads are absorbed by a flanged ball bearing located in the front face of the reduction gearbox centerbore. The bevel drive gear, adjusting spacer, thrust bearing and seal runner are stacked and secured to the propeller shaft by a single spanner nut and keywasher. The thrust bearing cover is secured to the front of the reduction gearbox and incorporates a removable oil seal retaining ring to facilitate replacement of the oil seal. The accessories located
on
the reduction
TORQUEMETER A.
The
and B.
hydro-mechanical torque measuring device located inside, the first housing to provide an accurate indication of engine power output. mechanism consists of a torquemeter cylinder, torquemeter piston, valve plunger spring. (See Figure 1-4-10).
The torquemeter is a stage reduction gear
ring gear is resisted by the helical splines which impart an axial ring gear and therefore to the torquemeter piston. This in turn moves plunger against a spring, opening a metering orifice and allowing an increased
Rotation of the
movement to the
valve
a
torquemeter chamber. This movement will continue until the oil pressure in the torque chamber is proportional to the torque being absorbed by the ring gear. Any change in power control lever setting will re-cycle the sequence until a state of equilibrium is again reached.
flow of pressure oil to enter the
lock is prevented by chamber into the reduction gear of the torquemeter cylinder.
allowing oil to bleed continuously from the pressure casing through a small bleed hole provided in the top
C.
Hydrostatic
D.
Because the external pressure within the reduction gearbox may vary and affect the total pressure on the exterior face of the torquemeter piston, the internal pressure is measured. The difference between the torquemeter pressure and the reduction gearbox internal pressure accurately indicates the torqu’e being produced. The two pressures are
internally
routed to bosses located on the top of the reduction gearbox front case can be made to suit individual cockpit instrumentation requirements.
where connections
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1-4-20
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
16.
EXHAUST DUCT A.
The exhaust duct
(see Figure 1-4-11),
a
divergent
heat resistant duct has two outlet
ports, one on each side of the case. The duct is attached to the front flange of the gas generator case and consists of inner and outer sections. A reinforcing ring is provided at of the exhaust duct at flange D. This consists of a scalloped ring machined in coupled to form a circle by two equi-spaced clevis pin joints. The power turbine stater housing is secured to flange D by twelve bolts which screw into and also secure the reinforcing ring. The outer conical section which has two flanged exhaust outlet ports forms the outer gas path and also functions as~a structural member to support the reduction gearbox. The inner section forms the inner gas path and provides a compartment for the reduction gearbox rear case and the power turbine support housing. A removable sandwich-type heat shield insulates the power turbine support housing from the hot exhaust gases. A short No. 3 bearing cover and spacer are secured at the rear of the power turbine support housing by a retaining ring. A drain passage, located at the 6 o’clock position in the exhaust duct, enables residual fuel accumulating in the exhaust duct during engine shutdown to drain into the gas generator case where it is discharged overboard through the front drain plug. the
rear
two halves and
17.
ACCESSORY GEARBOX A.
The accessory gearbox housing, located at the rear of the engine, consists of two castings both of which are attached to the rear flange of the compressor inletcase by 16 studs. The front casting, which incorporates front and rear preformed packings, forms an oil-tight diaphragm between the oil tank compartment of the inlet case and the for the accessory drive gear whichis secured to the diaphragm by four bearings, seals, and main pressure oil pump bolts. The diaphragm is attached to the accessory gearbox rear casting by four countersunk screws and nuts located at the 4th, 8th, 14th and 18th positions in clockwise
accessory drives. The
diaphragm provides support
rotation, assuming the Ist B.
to be at the 12 o’clock
position. (See Figure 1-4-12).
forms an accessory gearbox cover and provides support bosses for the drive bearings and seals. The internal scavenge oil pump is secured inside accessory the housing and a second scavenge pump is externally mounted. Mounting pads and studs are provided on the rear face for the combined starter-generator, the fuel control unit with the sandwich mounted fuel pump, and the Ng tachometer-generator. A The
rear
casting
plug located below the starter-generator mounting pad provides passage tool which must be used to disengage and hold the ball-locked coupling shaft puller and input gearshaft during disassembly. Three additional pads are available for optional requirements. Accessory drives are supported on similar roller bearings fitted large
for
access
a
with garter-type oil seals. An oil tank filler cap and integral dipstick is located at the 11 o’clock position on the rear housing to facilitate servicing of the oil system. A centrifugal oil separator mounted on the starter-generator drive gearshaft separates the oil from the engine breather air in the accessory gearbox housing. A cored passage in the diaphragm connects the oil separator to an external mounting pad located at the
position on the rear housing. A carbon face seal located gearshaft in the diaphragm precludes pressure leakage through
12 o’clock
on
the
the
the front of
bearing assembly.
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Feb 01/2002
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
10
I) ~----1
1
ii
~9
121
(4
2
5
II
C14B
Torquemeter- Schematic Figure 1-4-10
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1-4-22
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
1-4-10
1.
Gearbox Pressure
2.
Torquemeter Pressure
3.
Oil Control Piston
4.
Control
5.
Spring Metering Orifice
6.
Piston
7.
12.
Torquemeter Chamber First Stage Planet Gear First Stage Ring Gear Helical Splines Casting Cylinder
13.
Bleed Hole
8.
9. 10. 11.
18.
to
ENGINE LIFTING POINTS A.
Engine installation or removal is facilitated by front and rear lifting sling suspension points. The front suspension point consists of a single metal bracket secured to the top of the exhaust duct at flange A for all engine models. The bracket embodies a special eye to accommodate the sling attachment and is identified for this use; a bolted service plate is incorporated to accommodate the front linkage swivel joint. On PT6A-6 and PT6A-6A engines there are two rear suspension points. These consist of two metal brackets located at the 3 and 9 o’clock positions on flange G. On PT6A-6B and PT6A-20 Series engines, the rear suspension point consists of a single metal bracket secured to the top of the accessory gearbox at flange G.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
A
FLANGE
C
FLANGE
D
C454B Twin Outlet Port Exhaust Duct
Figure
(Typical)
1-4-11
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Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
ACCESSORY GEARBOX HOUSING FLANGE
1
G
CENTRIFUGAL BREATHER IMPELLER ACCESSORY DIAPHRAGM
CARBON FACESEAL
~nr
I
ilAI
STARTER-GENERATOR DRIVE GEARSHAFT
BALL LOCK
ROLLER BEARING
CrvPlCAL)
INPUT GEARSHAFT OIL PUMP DRIVE GEARSHAFT
OIL FILTER AND NON-RETURN VALVE
OIL SEAL
(TYPICAL) MAIN PRESSURE PUMP BODY ASSEMBLY
INLET OIL SCREEN INTERNAL SCAVENGE PUMP GEARS
OIL TRAY
C554A
Accessory
Gearbox
Figure
Cross Section
1-4-12
Page
1-4-25/26
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
PART 1
DESCRIPTION OF ENGINE
SECTION 5 -AIR SYSTEMS 1.
GENERAL A.
2.
The
engine has three separate air bleed systems: a compressor air bleed control, a bearing compartment air seal and bleed system and a turbine disk cooling system. A fourth system is available as an optional source of high-pressure air for use in operating auxiliary airframe equipment. A blanked mounting flange located on the gas generator case is provided for external connections.
COMPRESSOR BLEED VALVE A.
The compressor bleed valve automatically opens a port in the gas generator case to spill interstage compressor air (P2.5), thereby providing antistall characteristics at low
engine speeds (less
than 80%
Ng).
The port closes
gradually
as
high engine speeds
are
attained.
3.
B.
The compressor bleed valve consisting of a piston type valve in a ported housing, is installed on the gas generator case at the 7 o’clock position, and is secured by two bolts. The piston assembly is supported in the bore of the housing and is guided by a seal support plate, guidepin and a guidepin bolt, which holds the piston assembly together. A rolling diaphragm permits the piston full travel in either direction, to open or close the port, while at the same time effectively sealing the compartment at the top of the piston. A port in the gas generator case provides a direct passage for the flow of compressor interstage air (P2.5) to the bottom of the bleed valve piston. (See Figure 1-5-1).
C.
Compressor delivery air (P3) is tapped off and applied to the bleed valve through a nozzle (fixed orifice) in the bleed valve cover, then passed through an intermediate passage and out to atmosphere through a metering plug (convergent-divergent orifice). The control pressure (Px) between the two orifices acts upon the upper side of the bleed valve piston, so that when Pr is greater than P2.5, the bleed valve closes. In the closed position, the interstage air port is sealed by the seal support plate which is forced against its seat by the action of Pr. Conversely, when Pr is less than P2.5, the bleed valve opens and allows interstage air (P2.5) to be discharged to atmosphere. The piston is prevented from closing off the Pr feed line to the upper section of the valve chamber and from damaging the piston assembly by the stop formed by the hexagon of the guidepin, which is screwed into the valve cover, and the hexagon of the piston guidepin bolt.
BEARING COMPARTMENT SEALS TURBINE COOLING AND AIR BLEED SYSTEMS A.
Engine air pressure is utilized to seal the Ist, 2nd and 3rd bearing compartments and also to cool both the compressor and the power turbines (see Figure 1-5-2). The air pressure is used in conjunction with air seals which establish and control the required gradients. The air seals used on the engine consist of a series of stationary expansion chambers (labyrinths) formed by deep annular~grooves machined in the bore of a circular seal. The clearance between the rotating and stationary parts is kept as small as possible consistent with mechanical safety. pressure
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
P3-COMPRESSOR DISCHARGE AIR
’t FIXED ORIFICE
Px-POTENTIOMETRIC PRESSURE TO TOP OF PISTON
ft PRESSUREAMBIENT FINAL ORIFICE CENTRAL GUIDE PIN ROLLING DIAPHRAGM:j:
t
Z~
BODY
PISTON DISCHARGE TO ATMOSPHERE
:j:
GAS GENERATOR CASE
OUTER GUIDE
INTERSTAGE AIR
(P2.5)
C829
Compressor
Bleed Valve
Figure
Schematic
1-5-1
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1-5-2
Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
I) A
SEALING AND COOLING
I) B
AIR BLEED SYSTEM
I,C
TURBINE COOLING
i’ Bh~lV
;I,
;1
C563A
Bearing Compartment Seals,
Turbine
Cooling Figure 1-5-2
and Air Bleed
Systems (Typical)
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1-5-3
Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
Compressor interstage located in front of No. 1
air is utilized to provide a pressure drop across the air seal bearing. The air is led through perforations in the rim of the
compressor long spacer and sleeve assembly into the center of the rotor. It then flows rearward through passages in the three compressor disks and out to an annulus machined in the center of the air seal via passages in the compressor rear hub. The pressure air is allowed to leak through the labyrinth and so provides the required pressure seal. C.
The No. 2
bearing
is
Pressure air for this on
protected by
an
air seal at the front and at the
rear
system is bled either from the centrifugal impeller tip
engine speed, from
the
labyrinth
seal
system. The air flows through passages pressure at the front and seal in the front and rear
rear
of the
connecting in the No. 2
of the or,
bearing. depending
it to the turbine
cooling air bearing support, equalizing
bearing compartment
and
ensures a
the air
pressure
labyrinths.
D.
The compressor and power turbine disks are both cooled by compressor discharge air bled from the slotted diffuser baffle area down the rear face of the outer exit duct assembly. It is then metered through holes in the compressor turbine vane support into the turbine baffle hub, where it divides into three paths. Some of the air is metered to cool the rear face of the compressor turbine disk, and some to pressurize the bearing seals. The balance is led forward through passages in the compressor turbine hub to cool the front face of the compressor turbine. A portion of this cooling air is also led through a passage in the center of the interstage baffle where the flow divides. One path flows up the rear face of the power turbine disk while the other is led through the center of the disk hub and out through drilled passages in the hub of the No. 3 bearing air seals and front face of the power turbine disk.
E.
The
cooling air from both turbine disks is dissipated into the main gas stream flow to atmosphere. The bearing cavity leakage air is scavenged with the scavenge oil into the accessory gearbox and vented to atmosphere through the centrifugal breather.
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1-5-4
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
DESCRIPTION OF ENGINE
SECTION 6 1.
LUBRICATION SYSTEM
GENERAL A.
to provide a constant supply of clean lubricating oil reduction gears, torquemeter, propeller and all accessory drive gears. The oil lubricates and cools the bearings, and conducts any foreign matter to the main oil filter where it is precluded from further circulation. Calibrated oil nozzles are
The lubrication to the
system is designed
engine bearings,
engine bearings to ensure that an optimum oil flow is maintained for all conditions. A main pressure pump located in the oil tank supplies oil to the accessory section and through an external transfer tube to the gas generator section and reduction gearbox. used
on
the main
operating
2.
3.
OIL TANK A.
The oil tank is
integral part of the compressor inlet case and is located in front of the accessory gearbox. The tank capacity is sufficient to meet all normal operating requirements, since the average oil consumption is less than 0.2 Ibs/hr. For tank capacities and other data, refer to Section 2, preceding.
B.
The oil tank is
an
provided with an oil filler neck and a quantity dipstick and cap which protrudes through the accessory gearbox at the 11 o’clock position. The markings on the dipstick correspond to U.S. quarts, and indicate the quantity of oil required to service the tank to the full mark. A drain plug provided in the bottom of the tank facilitates oil drainage. SB1506 introduces a check valve at the lower end of the Oil Filter Tube, restricting oil loss should the oil-filler-cap be improperly installed.
OIL PUMP A.
a gear type pump, in the lowest portion of the oil tank, is delivered under pressure to the engine lubricating system. The oil pump consists of two gears within a pump body and cover which are bolted together to the front face of the accessory diaphragm. Drive is imparted to the pump by an accessory gearshaft which also drives the internal double element scavenge pump. A removable screen is provided at the oil pump inlet. A circular mounting boss on the pump body accommodates a spring loaded check valve, and through which oil delivery pressure is pumped into the filter
011 supplied to
housing. 4.
OIL FILTER ASSEMBLY A.
assembly consists of either a disposable cartridge type filter element or an all-metal cleanable element, with a perforated flanged end, a spring-loaded bypass valve and check valve, (see Figure 1-6-1). These are secured in a alloy housing located in the compressor inlet case at the 3 o’clock position. A filter cover, secured to the inlet case by four nuts, holds the filter element and housing in position. Oil pressure flows through the check valve into the housing, through the filter element and out to the engine system via a cored passage, leaving any foreign matter deposited on the exterior of the element. The check valve, positioned in the end of the housing, prevents gravity flow into the engine after shutdown and permits the filter element to be changed or removed for cleaning without having to drain the oil tank. The oil filter
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1-6-1
Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO.´•3015442
OVERBOARD BREATHER-VENT RELIEF VALVE BODY OIL TANK FILLER CAP AND DIPSTICK
O ADJUSTING SPACER ACCESSORY GEARBOX HOUSING
OIL PRESSURE RELIEF VALVE
FILTER ELEMENT
OIL FILTER COVER TEFLON SPACER
STARTER GENERATOR CAVITY DRAIN
FILTER HOUSING
BYPASS VALVE
8 CHECK VALVE
REDUCTION GEARBOX AND POWER SECTION SCAVENGE OIL RETURN
7~r ’C
EXTERNAL DOUBLE ELEMENT SCAVENGE OIL PUMP
INTERNAL DOUBLE ELEMENT SCAVENGE OIL PUMP
PRESSURE OIL TO REDUCTION GEARBOX AND POWER SECTION
OIL TANK DRAIN PLUG
C308A
Accessory
Lubrication Schematic Figure 1-6-1
Gearbox
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1-6-2
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
bypass is provided by a spring-loaded bypass valve located in the downstream side of the check valve. The bypass valve is normally closed and sealed against leakage by a molded seal located on the front end of the disposable filter element, or by a preformed packing located on the front of the all-metal element. In the event of a blocked filter, the increased pressure overcomes the bypass valve spring, opens the bypass valve and provides an alternate passage for unfiltered oil flow through the engine. A filter
C.
5.
Engine oil pressure is regulated by a plunger type pressure relief valve located on the inlet case just above the oil filter assembly, (see Figure 1-6-1). Oil in excess of the regulated pressure is bypassed back to the tank through a cored passage inside the case. Oil pressure is adjusted at the factory by the addition or deletion of adjusting spacers and does not normally require any further adjustment.
OIL PRESSURE SYSTEM A.
Oil lubrication for the accessory drives and bearings is supplied from the oil filter through cored passages and transfer tubes in the accessory diaphragm and rear housing, (see Figure 1-6-1). The No. 1 bearing is lubricated by oil routed via an internal passage in the compressor inlet case, through a filter and nozzle assembly secured in the center section of the case at the rear of the bearing. The oil is sprayed by the nozzle into a collector ring mounted on the rear of the compressor hub and directed through passages in the split inner race to the bearing assembly by centrifugal force.
B.
A direct
supply of oil
is
provided
to lubricate the No. 2
bearing, reduction gearbox, front
accessories, and power turbine shaft bearings, (see Figure 1-6-2). From the filter, the oil is directed through a cored passage to an outlet boss located at the bottom of the compressor inlet case. An external transfer tube, connected to the boss, leads oil pressure forward to the reduction gearbox. Oil is tapped from the tube to lubricate No. 2 bearing via an internal transfer tube secured in the gas generator case. The tube passes through a diffuser vane to an oil gallery with two nozzles. A strainer protects the two nozzles which are positioned one in front and the other at the rear of the No. 2
bearing. C.
The main oil pressure is delivered at 70 psig to the reduction gearbox where it is divided into´•two branches. One branch leads to the first stage reduction gears, splines, torquemeter, Nos. 3 and 4 bearings. The second branch delivers oil to the second stage reduction gears and spray lubrication for the No. 4 bearing.
D.
Oil pressure to the torquemeter is directed through a metering valve which controls the flow into the torquemeter chamber. The position of the metering valve is dependent on the torquemeter piston which reacts in direct proportion to engine torque. (For torquemeter details, refer to Section 4, preceding.) The oil from the torquemeter supply is directed via an internal oil transfer tube and strainer in the power turbine support housing to four nozzles; two of the nozzles are positioned one in front and one in the rear of No. 3 bearing. The other two nozzles are located one in front and the other in the rear of No. 4 bearing to provide additional lubrication to the first stage sun gear coupling and the
bearing.
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1-6-314
Feb 01/2002
PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FROM OIL COOLER
OIL-TO-FUEL HEATER r------~
DEAERATOR PROPELLER GOVERNOR
SPLINES, BEARINGSAND
~q
INTEGRALOILTANK CAPACITY 2.3 GALLONS
-~re
OIL TANK BREATHER
i______j OIL FILLER AND DIP STICK
TORQUEMETER OIL CONTROLVALVE
CENTRIFUGAL BREATHER
REDUCTION GEARS NO. 4 BEARING
B
OILSVPPLY
N0.3
NO. 1 BEARING
NO. 2 BEARING
VALVETO
OIL COOLER
(30 PSI MAX.)
POWER TURBINE BEARINGS
OIL FILTER AND CHECK ASSEMBLY
COMPRESSOR BEARINGS
Nb. 2 BEARING SCAVENGE PUMP
FILTER BYPASS VALVE THRUST BEARING
POWER TURBINE BEARINGS VENGE PUMP
REDUCTION CASE SCAVENGE PUMP
PRESSURE RELIEF VALVE WITH RETURN TO OIL TANK
ACCESSORY CASE SCAVENGE PUMP
OIL PRESSURE PUMP PRESSURE TRANSMITTER
TO TORQUEMETER PRESSURE INDICATOR
3 OIL TANK DRAIN
If
GRAVITY DRAIN ACCESSORY GEARBOX
BYPASS VALVE
SCAVENGE OIL FROM PROPELLER AND REDUCTION GEARBOX
tj
TOCOCKPIT INS1’RUMENTS’
OIL SUPPLY TO PROPELLER AND REDUCTION GEARBOX 70 PSI TO REDUCTION GEARBOX OIL SUMP PROPELLER CONTROL OIL
n~ji
TO REDUCTION GEARBOX SUPPLY PRESSURE OIL
R’V’RS1NG VLLV~
SCIIVENGE OIL
DIVIDER BRAIN OIL
PT6A-6A ENGINES ONLY
C13815
Engine
Lubrication
Schematic PT6A-6/20
Figure
1-6-2
Page
1-6-5/6
Feb 01/2002
PEBa
BREP~TnER LINE
I
ITEMPERATURE BULB 1
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
The second branch oil pressure is directed to No. 4 bearing through an oil nozzle secured in the rear of the propeller oil transfer tube. Passages in the split inner races of the bearing line up with a drilled annulus on the power turbine shaft to provide access for
centrifugal
oil flow into the bearing assembly. The second branch also provides oil from the through cored passages to the propeller constant speed control unit,
internal annulus
the accessory drive gears and the the second stage carrier bearing. 6.
propeller
thrust
bearing.
Oil mist
provides lubrication
to
PITCH REVERSING VALVE SYSTEM (PT6A-6A ENGINES) A.
The
valve works in connection with
B.
The flow divider consists of
a flow divider to provide a hydraulic control medium for use on reversing propeller installations. The reversing valve serves as a variable pivot for the reversing valve lever; its position is therefore a function of reversing valve lever travel. It consists of a ported sleeve valve and housing secured in the propeller thrust bearing cover.
pitch reversing
ported sleeved valve which is spring-loaded to the closed separate housing, secured to the reduction gearbox and position. interconnects the reversing valve to the gearbox oil sump. It also provides an alternate oil passage through a check valve to the reduction gearbox main oil pressure inlet. During normal propeller operation, a high-pressure oil bleed opens the flow divider valve ports, allowing the oil dumped by the reversing valve to return directly to the reduction gearbox oil sump. However, during windmilling operations, with consequent low gas generator rpm, the flow divider valve spring tension overcomes the oil bleed pressure, closing the valve ports and directing the propeller control oil flow back to the main oil inlet where it is recirculated through various passages in the reduction It is contained in
a
a
gearbox.pressure 7.
SCAVENGE OIL SYSTEM A.
The scavenge oil system includes two double-element scavenge pumps connected by internal passages and lines to two main external transfer tubes. One pump is secured inside the accessory gearbox and the other is externally mounted. They are contained in separate housings and driven off accessory gearshafts.
B.
The oil from the No. 1 bearing compartment is returned by gravity through an internal cored passage to the bottom of the compressor inlet case and then through oil transfer tube in the oil tank and accessory diaphragm into the accessory gearbox. No. 2 bearing oil drains down from its compartment into an external transfer tube leading
rearward tothe bottom of the oil tank. It is then scavenged through a cored passage in the accessory diaphragm to the front element of the internal scavenge pump which forces oil into the accessory gearbox. The oil from the centrifugal breather and input gearshaft and bearings drains to the bottom of the accessory gearbox. It is scavenged from the gearbox together with the oil from Nos. 1 and 2 bearings and the scavenged oil from Nos. 3 and 4 bearings (see Paragraph 17, following). The double-element scavenge pump is connected by a quillshaft to the main oil pump in the oil tank and drives
an
externally
mounted
tachometer-generator.
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1-6-7
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C.
bearing compartment oil is scavenged through a transfer tube into the gearbox, and drains rearward through an external transfer tube to the front element of the external scavenge pump, where it is returned into the accessory gearbox. Oil from the propeller control, front thrust bearing, reduction gears and torquemeter bleed orifice drains into the reduction gearbox sump, and is scavenged by the rear element The Nos. 3 and 4 reduction
of the external scavenge pump via a separate external transfer tube. The oil from the pump is delivered through a tee connection into a tube to the airframe cooler, from where it is returned to the oil tank. Oil returned to the accessory gearbox from Nos. 1, 2, 3 and 4 bearings is scavenged by the rear element of the internal scavenge pump circulated through the airframe oil cooler and returned to the oil tank. 8.
BREATHER SYSTEM A.
Breather air from the
engine bearing compartments and the accessory gearbox is through a centrifugal breather located in the accessory gearbox. The various engine compartments are connected to the accessory gearbox by cored passages or existing scavenge oil transfer tubes. The No. 1 bearing vents rearward through the bearing rear housings and the oil tank center tube into the accessory gearbox via the input gearshaft bearing. The No. 2 bearing is vented to the accessory gearbox by an interconnecting vent tube in the compressor assembly and the hollow passages in the extension drive coupling and gearshaft. A bypass valve, immediately upstream of vented overboard
the front element of the internal scavenge pump, allows oil and air to be vented into the accessory gearbox under certain transient operating conditions to prevent overpressurizing the number 2 bearing area. Under normal operating conditions, the valve is closed to prevent oil flooding back into the tube assembly. The Nos. 3 and 4 bearings and the reduction gearbox are vented by utilizing the present large diameter internal and external scavenge tubes which lead back from the reduction gearbox to the external scavenge pump mounted on the accessory gearbox and dumped into the oil tank after passing the airframe cooler. The oil tank, in turn, vents into the accessory gearbox through a breather tube. 9.
CENTRIFUGAL BREATHER A.
breather consists of
a shrouded aluminum alloy impeller secured to the gearshaft by a retaining ring. Rotational torque is starter-generator transmitted from the gearshaft to the impeller by three equi-spaced alloy pins. Breather air flows radially inward through the rotating impeller housing where the oil particles are separated from the air mist by centrifugal force. The oil particles are thrown outward and drain freely to the bottom of the accessory gearbox. The relatively oil-free breather air passes forward through the hollow center section of the gearshaft to a cored passage in the accessory diaphragm. It is then routed through a transfer tube to a breather boss on the rear face of the accessory housing where a connection for an overboard vent line is provided.
The
centrifugal
rear
face of the
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
10.
OIL-TO-FUELHEATER
A.
The oil-to-fuel heater is
a self-contained engine option secured to flange G on the accessory gearbox. It functions as a heat exchanger when the engine is running, utilizing heat from the engine lubricating system to pre-heat fuel in the engine fuel system. The
a two-pass engine oil circuit and a two-pass fuel circuit, at right angles (see Figure 1-6-3). A temperature control valve regulates the fuel temperature by either permitting oil flow through the heater core, or bypassing it through the valve back to the engine oil tank through an external line.
system incorporates
to one another
11.
B.
Hot engine oil enters the oil circuit through the oil inlet port of the heater under engine pressure. If the outlet fuel temperature is less than the ball valve setting, the vernatherm plunger will be retracted and the ball will seal the bypass port, forcing the engine oil to circulate through the core of the heat exchanger. The heat from the engine oil is transferred through the walls of the heat exchanger to warm the engine fuel.
C.
If the fuel outlet temperature is above the ball valve setting, the vernatherm plunger will be in an extended position and the ball will be lifted off its seat by the plunger. This permits the hot engine oil to flow through the bypass port and oil outlet without circulating through the heat exchanger core. The fuel outlet temperature is accordingly reduced.
OIL SYSTEM INSTRUMENTATION A.
Main oil pressure is measured from the transmitter located at the 3 o’clock position on the accessory housing. Oil temperature is measured by a temperature bulb located at the 4 o’clock position on the accessory gearbox.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL IN
I::::::::
i5ii~
j:’
i FUEL OUT
t OIL IN
I
I
I
I
OIL OUT
O;L O;L IN
OUT
BY-PASS CONDITION
023 Oil-to-Fuel Heater Flow Schematic Figure 1-6-3
Page
1-6-10
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PARII
DESGRIPTION OF ENGINE
SECTION 7
IGNITION SYSTEM
GLOW PLUG TYPE 1.
(PRE-SB1429)
GENERAL A.
The glow plug type ignition system has been developed and adapted to provide the
engine with an ignition system capable of quick light-up at extremely low ambient temperatures. The basic system consists of an ignition current regulator with a selectable circuit to the two sets of ballast tubes, two shielded ignition cable and clamp assemblies and two glow plugs. 2.
IGNITION CURRENT REGULATOR A.
The ignition current regulator is secured by three bolts to the accessory gearbox
casting
G. The regulator may be airframe mounted if required. The regulator box has a removable cover and contains four ballast tubes (See Figure 1-7-1) Each tube consists of a pure iron filament surrounded by helium and hydrogen gases and enclosed in a glass envelope sealed to an octal base. The iron filament, having a positive coefficient of.resistance (resistance increased with temperature increase caused by current flow), provides a stabilizing effect on the current passing through it. At low temperatures ballast tube resistance is decreased to counteract power loss and as temperatures rise ballast tube resistance increases to maintain nearly constant glow-plug current. Each glow plug is wired in series with two parallel-connected ballast tubes and either or both glow plugs may be selected for light-up. Ballast tubes provide an initial current surge when switched on, and a lower stabilized current after approximately 30 seconds. This characteristic provides rapidly heated glow plugs for fast light-up. at
3.
flange
GLOW PLUGS A.
a helical heating element fitted into a short secured the to plug body. plugs gas generator case in threaded bosses and o’clock 8 4 the at provided positions. The heating element consists of a helically wound coil which lies slightly below the end of the plug body. Four holes, equi-spaced on the periphery of the plug body lead into an annulus provided below the coil. During
The glow plug (see Figure 1-7-2) consists of The
are
the fuel sprayed by the fuel nozzles traverses the lower wall of the combustion chamber liner into the annulus, The fuel is vaporized and ignited by the hot coil element which heats up (yellow hot) to approximately 1260"C (2300"F). The four air
starting procedure,
holes bleed compressor discharge air fr~m the gas generator case into the body then past the hot coil into the combustion chamber to produce a hot streak or torching effect which ignites the remainder of the fuel. The air also serves to cool the coils when the engine is running with the ignition system switched off.
Page
1-7-1
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
GLOV~ PLUGS
(9
RIGHT
LEFT O’CLOCK POSITION)
(40’CLOCK POSITION)
UPPER INPUT CONNECTOR
LOWER OUTPUT CONNECTOR
I
2
I
I B
I
4\
1 I
1
0\
II
1
Q
10
I A
CENTER OUTPUT I CONNECTOR
/4
5
/00 3
05
O
Os
06 7
O I
#1
I
I I
1
#3
BALLAST TUBE BASE 3 2
1 I
II
O
10
#2
4\
0\
1
e-~c\s
I
05
06/
I
2
11
I 1
4
/00
\10
Q
Os05
#4
2&3COMMON 7&8COMMON
C448D
Ignition
Current
Regulator Circuit Diagram Figure 1-7-1
Page
1-7-2
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXHAUST CASE INNER SECTION
COMBUSTION CHAMBER LINER
GLOW PLUG COOLINGAIRPPSSIGE
GAS GENERATOR CASE
I
_I
LEAD CONNECTOR FROM IGNITION REGULATOR BOX
C3735A Glow
Plug Installation Figure 1-7-2
Page
1-7-3
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
SPARK IGNITER TYPE 4.
GENERAL A.
5.
(POST-SB1429)
spark ignition system has been developed to provide the engine with an ignition system capable of quick light-ups over a wide temperature range. The system consists of an engine-mounted ignition exciter, two individual high tension cable assemblies and two spark igniters. The system is energized from the aircraft nominal 28-volt d.c. supply and will operate in the 9- to 30-volt range. The
IGNITION EXCITER
ignition exciter is a sealed unit containing electronic components encased in an epoxy resin. The unit is energized only during the engine starting sequence to initiate combustion in the combustion chamber. The exciter transforms the DC input to a pulsed high voltage output through solid-stage circuitry, a transformer and diodes.
A.
The
B.
When the unit is
energized, a capacitor on the high voltage side of the output transformer progressively charged, until the energy stored, approximately four joules, is sufficient to ionize a spark gap in the unit and discharge the capacitor across the two spark igniters through a dividing and step-up transformer network. The network is designed so that if one igniter is open or shorted, the remaining igniter will continue to function. The network also enables the capacitor to discharge automatically in the event of either or both igniters becoming inoperative, or input voltage is switched off. is
6.
SPARK IGNITERS A.
spark igniters, located at the 4 and 8 o’clock positions on the gas generator case adjacent to the fuel manifold, are in the form of a double-ended, threaded plug.with a central positive electrode, enclosed in an annular semi-conducting material. The electrical potential developed by the ignition exciter is applied across the gap between the central conductor and the igniter shell (ground). As this potential increases, a small current passes across the semi-conducting material. This current increases until the air between the central conductor and the shell ionizes. When ionization occurs, high energy discharges between the electrodes. The spark always occurs somewhere in the The and
annular space between the central conductor and shell.
Page
1-7-4
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
DESCRIPTION OF ENGINE
SECTION 8
FUEL SYSTEM
INTRODUCTION 1.
GENERAL A.
The basic fuel system (see Figure 1-8-1) consists of a single engine driven pump, a fuel control unit, a fuel manifold and 14 simplex fuel nozzles. A fuel dump valve and two drain valves are provided on the gas generator case to ensure drainage of residual fuel after engine shutdown.
FUEL PUMP 2.
(VANE TYPE)
GENERAL A.
The fuel pump is mounted on the accessory gearbox and is driven through a splined coupling. The coupling splines are lubricated by oil mist from the accessory gearbox through a hole in the gearshaft. Another splined coupling shaft extends the drive to the fuel control unit which is bolted to the rear face of the fuel pump. Fuel from the aircraft fuel boost pump enters the pump through a 74 micron (200 mesh) inlet screen. The filter screen is spring-loaded to lift and allow unfiltered fuel to flow in the event of the screen becoming blocked. The fuel is pumped by rotation of the slotted rotor´•which contains 10 vanes. The vanes move within their slots, following the inside contour of a cam
ring.
The
vanes are
held
against
the contour of the
ring by centrifugal
force and
system pressure. The moving vanes in the cam ring form opposing chambers connected to pump inlet and outlet ports. As each chamber, formed between the vanes, moves around in the cam ring, it changes in volume, drawing in fuel and then ejecting^it.
Page
1-8-1/2
Feb 01/2002
WHITNEY CANADA
PHATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LEGEND
BYPASS FUEL PRESSURE
Po
uNMETEREoFuELPREssuRE
P1 PZ
t-~ METERED FUEL PRESSURE
AMBIENT PRESSURE
TRANSFER TUBE
FUEL MANIFOLD ADAPTER ASSEMBLY NOULE
Pa
SHEATH
GOVERNOR SERVO PRESSURE
DRAIN
Py
ACCELERATION 6 SPEED ENRICHMENT PRESSURE COMPRESSOR DISCHARGEPRESSURE
I
COMBUSTIONCHAMBER LINER
Pr
GASGENERATOR CASE
Pc
ORII*YALVt TO ITMOSPWTRF
GRAIN TO ATMOSPHERE
MINIMUM
CUT-OFF VALVE
PRESSUR~ING
MIN. FLOW STOP
1
I
NOTE PROPELLERSPEED PROPELLER GOVERNOR ON MAX. STOP PT6A-6 SERIES AND PT6A-20 ENGINES IS AIRFRAME SUPPLY ~51 Ir~
FUEL CONTROL
vn~ve
METERING VALVE
I
I
IJ 5
1 ~49
AUTOMATIC FUEL DUMP VALVE
:UNIT SPECIFIC CRAVTTY ADJUSTMENT
OUTPUT FILTER
(BIMETAUIC) B.
BELLOWS STOP
(10 MICRON)
GEAR TYPE
DISK GROUP
a
FUEL PUMP
FILTER BYPASS VALVE
METERING HEAD REGULATOR
OIFFEREMIIC
PROP.GOVERNOA RESETARM OAl
X
PRESSURE REGULATING
BELLOWS
j
I
~--rmGY1U N
r
VALVE
O
MAXIMUM
I~
BLEED RETURN TO TANK
OR
STOP
iRm,
a.
RELIEF
I
I
VALVE
PUMP GEAR AND SHAFTGEAR
ACCELERATIDN BELLOWS
UNDERSPEEDFUEL GOVERNINGSPEED ADJUSTMENT
~VACUATED)
MAX. FLOW
L_
STOP 1
INLET SCREEN
PROPELLER GOVERNOR Nf SECTION
L
PT6A-20A OR 208 ENGINES ONLY
BYPASS PRESSURE REGULATING VALVE
CUT-OFF STOP
FUEL INLET BOOST PUMP)
(FROM
PRIMARY AND Pc NEEDLE VALVE IDLE RESET STOP
VIEW OF CUT-OFF IDLE RESET LINKAGE MAX. STOPrlN. STOP
POWER TURBINE GOVERNROR SCHEDULING CAM
DISK GROUP
NfGOVERNORGASSPEED~;
PT6A-6 SERIES AND PT6A-20 ENGINES ONLY
L. VIEW OF POWER TURBINE GOVERNOR LEVER
(BIMETALLIC)
DISCH*ROE PRESSURE
r-
SCHEDULING CAM
Ng GOVERNOR TEMPERATURE COMPENSATOR
IDLE SPEED STOP
C1854A
Engine
INPUTCOUPLING
System Schematic Figure 1-8-1
Fuel
Page 1-8-3/4 Feb 01/2002
(74 MICRON)
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL PUMP 3.
(GEAR TYPE)
GENERAL A.
positive displacement gear type pump which incorporates spring and pressure bushings and is driven off the accessory gearbox. A coupling is incorporated to transmit the drive to the pump gears. The coupling splines are lubricated by oil mist from the accessory gearbox, through a hole in the engine gearshaft. Another coupling is used to transmit a speed signal to the fuel control unit from the pump gears. Fuel from the aircraft boost pump enters the fuel pump through a 74 micron (200 mesh) inlet screen and flows into the pump gear chamber, from where the fuel is delivered at high pressure to the fuel control unit through a 10 micron pump outlet filter. The inlet screen is spring-loaded to lift and allow unfiltered fuel to flow into the pump in the event of the screen becoming blocked. A bypass valve, in parallel with the outlet filter and connected to the fuel control unit by cored passages in the pump casing, enables unfiltered high pressure fuel to pass from the pump to the fuel control unit when the outlet filter becomes blocked. An internal cored passage originating at the mating face with the fuel control unit mounting flange returns bypass fuel from the fuel control unit to the pump inlet downstream of the inlet screen. A pressure regulating valve in this line serves to pressurize the gear bearings. This is
a
loaded
FUEL CONTROL SYSTEM 4.
GENERAL A.
The fuel control system consists of three separate units with interdependent functions: The fuel control unit (FCU), the power turbine governor, or propeller governor package
(PT6A-20A
and PT6A-20B
engines)
and
temperature compensator, (see Figure 1-8-2).
The FCU determines the correct fuel schedule for the engine, to provide the power required as established by the power control lever. This is accomplished by controlling the speed of the compressor turbine (Ng). The power turbine governor, or power turbine
(Nf) of the propeller governor package (PT6A-20A and PT6A-20B engines), provides power turbine overspeed protection during normal operation. On propeller reversing installations, the propeller governor is inoperative during reverse thrust operation, and control of the power turbine speed is accomplished by the power turbine governor, or power turbine governor section (Nf) of the propeller governor package (PT6A-20A and -20B engines). The temperature compensator alters the acceleration fuel schedule of the fuel control unit, to compensate for variations in compressor inlet air temperature. Engine characteristics vary with changes in inlet air temperature and the acceleration fuel schedule must, in turn, be altered to prevent compressor stall and/or governor section
excessive turbine
temperatures.
Page
1-8-5/6
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
1 2 3 4 5 6 7 8
8’ 9 10
FUEL METERING VALVE MINIMUM PRESSURIZING VALVE HIGM-PRESSURE RELIEFVALVE TORQUE TUBE ASSEMBLY BYPASSVALVE NEEDLE VALVE ORIFICE ROD COMPRESSOR TURBINE GOVERNOR SPRING COMPRESSORTURBINE ENRICHMENTSPRING COMPRESSOR TURBINE SPEED SET LEVER LINK IDLE SPEEDADJUSTMENT POWER TURBINE SPEED SET LEVER POWER TURBINE GOVERNOR SPRING POWER TURBINE GOVERNOR PLATFORM NEEDLE VALVE ROD
r-
TEMPERATURE COMPENSATOR
11 12 13 14 15 16 MINIMUMNSCUT-BACK 17 CUT-OFFIIALVE 18 COMPRESSOR TURBINE GOVERNOR PLATFORM 19 MINIMUM Nf GOVERNING 20 SPEED SET LEVER 21 SPEEDER SPRING 22 PLATFORM 23 OVERSPEED ADJUSTMENT
FUEL CONTROL~OL UNIT
PNEUMATIC (COMPUTING) SECTION
~1
O
i
pv
~X i
Hn
i
111
jj po
i
i
Py 05 06 08 72
FUEL OUTLET TO NOULES
ei
FUEL PUMP FROM BOOSTER
LEUFPMUP
0,
23
nTB
II
a
o
Pa Pc P1 P2 Po Pr
I
17
~i= :li-
L_____J
YOKED BELLCRANK AMBIENTAIR COMPRESSOR DICHARGEAIR UMMETERED PUMP DELIVERY FUEL METEREDFUEL BYPASSFUEL ENRICHMENT PRESSURE GOVERNING ENRICHMENT ORIFICE GOVERNING ORIFICE GOVERNING ORIFICE AIR INLETTEMPERATURE
FUeL BLEEO TO TINK
15
IUNOIRSPeeO*OJUSTM.II~
25
METERING SECTIONNO/
I
O
o
I
ra
~Kls
i
16 22
PRESSUREiGOVERNOR Nf GOVERNOR SECTION
PROPELLER GOVERNOR Nf SECTION _J
PT6A-20A AND -208 ENGINES ONLY
C1852A Fuel Control
System Schematic Figure 1-8-2
Page 1-8-7/8 Feb 01/2002
1
1
PT6A-6 SERIES AND PT6A-20 ENGINES ONLY
PRATT
WHITNEY CANADA
N1AINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL CONTROL VNIT 5.
GENERAL A.
6.
The gas turbine fuel control unit (FCU) (see Figure 1-8-3) is mounted on the engine driven fuel pump and driven at a speed proportional to compressor turbine speed (Ng). The FCU determines the correct fuel schedule for the engine, to provide the power required by the power control lever setting. This is accomplished by controlling the speed of the compressor turbine (Ng). Engine power output is directly dependent upon compressor turbine speed. The FCU governs compressor turbine speed (Ng), thereby governing the actual power output of the engine. Control of Ng is accomplished by regulating the amount of fuel supplied to the combustion chamber.
FUEL SYSTEM A.
The FCU is supplied with fuel at pump pressure (P1), (see Figures 1-8-1 and 1-8-2). Fuel flow is established by a metering valve and bypass valve system. Fuel at P1 pressure is applied to the metering valve inlet. The fuel pressure at the metering valve outlet is referred to as metered fuel pressure (P2). The bypass valve maintains an
essentially
constant fuel pressure differential
area
of the
(P1
P2)
across
the
metering
valve. The
valve changes to meet specific engine requirements. Fuel pump output in excess of these requirements is returned to pump inlet, and is referred to as Po. The bypass valve consists of a sliding valve operating in a ported sleeve. The orifice
metering
valve is actuated by means of a diaphragm and spring. In operation, the spring force is balanced by the pressure differential (P1 P2) operating on the diaphragm. The bypass P1 P2 differential and to bypass fuel in valve is always positioned to maintain the excess
of
engine requirements.
B.
A relief valve is incorporated parallel to the bypass valve to prevent a buildup of excessive P1 pressure in the control body. The valve is spring loaded closed and remains closed until the inlet fuel pressure (P1) overcomes the spring force and opens the valve. As soon as the inlet pressure is reduced, the valve again closes.
C.
The metering valve consists of a contoured needle working in a sleeve. The metering valve regulates the flow of fuel by changing orifice area. Fuel flow is a function of metering valve position only, as the bypass valve maintains an essentially constant differential fuel pressure across the orifice regardless of variations in inlet or discharge fuel pressures. The pressurizing valve is located between the metering valve and the cut-off valve. Its function is to maintain adequate pressure within the control to assure correct fuel metering. The cut-off valve provides a positive means of stopping fuel flow to the engine. During normal operation, this valve is fully open and offers no restriction to the flow of fuel to the nozzles. On installations not incorporating a reversing propeller, the cut-off valve is actuated by the power control lever. On installations incorporating a reversing propeller, an additional linkage system is employed to operate the cut-off valve.
D.
An external adjustment is
provided on the bypass valve spring cover to match accelerations between engines on multi-engine installations. Compensation for variations in specific gravity resulting from changes in fuel temperature is accomplished by the bimetallic disks under the bypass valve spring.
Page
1-8-9
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
HI-IDLE STOP
CUT-OFF STOP
&I ACCELERATION ADJUSTMENT
FCU CONTROL ARM
MAX Ng SPEED ADJUSTMENT
~sS,
PART POWER
TRIM STOP
FUEL OUTLET
I-.J
’Lil
FUEL INLET
FUEL CUT-OFF VALVE LEVER
C27B
Fuel Control Unit
Figure
1-8-3
Page
1-8-10
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
POWER INPUT. SPEED GOVERNOR AND ENRICHMENT SECTION ----´•´•´•--´•´•I´•´•´•--
A.
For details of the governor and enrichment levers, see Figure 1-8-4. Views A and B the individual levers and their relationship to each other. Views C and D show these levers in operation. The power input shaft incorporates a cam which depresses internal lever when the power is increased. A spring connects this cam follower lever
identify
an
to the governor lever. The governor lever is pivoted and one end operates against an orifice to form the governor valve. The enrichment lever pivots at the same point as
the governor lever. It has two extensions which straddle a portion of the governor lever so that after a slight movement a gap will be closed and then both levers must move together. The enrichment lever actuates a fluted pin which operates against the enrichment hat valve. Another smaller spring connects the enrichment lever to the
governor lever. A roller governor spool. B.
on
the
arm
of the enrichment lever contacts the end of the
speed scheduling cam applies tension to the governor spring through the intermediate applies a force to close the governor valve. The enrichment spring, between the enrichment and governor levers, provides a force to open the enrichment valve. As the drive shaft revolves, it rotates a table on which the governor weights are mounted. Small levers on the inside of the weights contact the governor spool. As compressor turbine speed (Ng) increases, centrifugal force causes the weights to apply increasing force against the spool. This tends to move the spool outward on the shaft against the enrichment lever. As governor weight force overcomes opposing spring force, the governor valve is opened and the eririchment valve is closed. The
lever which
The enrichment valve will start to close whenever compressor turbine speed (Ng) increases enough to cause the weight force to overcome the force of the small spring. If Ng continues to increase, the enrichment lever will continue to move until it contacts the governor lever as shown in View C, at which time the enrichment valve will be fully closed. The governor valve will open if compressor turbine speed (Ng) increases sufficiently to cause the weight force to overcome the force of the larger spring. At this point the governor valve will be open and the enrichment valve closed, as shown in View
D.
body incorporates a vent port which vents the inner body cavity to atmospheric Modified compressor discharge pressure, Pr and Py, will be bled off to (Pa). pressure Pa when the respective enrichment and governor valves are open.
The main
Page
1-8-11
Feb 01/2002
WHITNEY CANADA
PRATT.
MAINTENANCE MANUAL MANUAL PART NO. 3015442
I
SPEED ENRICHMENT VALVE OPEN
L\
COVERNORLEVER
I
’;3 ENRICHMENT
C
GOVERNOR VALVE CLOSED
NOTE LOCATION OF GAP VIEW
VIEW
A
B
ENRICHMENT LEVER
GOVERNOR LEVER
SPEED ENRICHMENT AND GOVERNOR VALVES CLOSED
ii
ij
~sl
SPEED ENRICHMENT VALVE CLOSED GOVERNOR VALVE OPEN
1 i61~-=
NOTE
LOCATIONOF GAP
VIEW
,43~
C
VIEW
GOVERNOR WEIGHT FORCE OVERCOMES FORCE OF SMALL SPRING
D
GOVERNOR WEIGHT FORCE OVERCOMES FORCE OF LARGE SPRING
0451 Drive
Body Assembly Operation Figure 1-8-4
Page
1-8-12
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
8.
BELLOWSSECTION A.
assembly consists of an evacuated (acceleration) bellows and governor by a common rod. The end of the acceleration bellows opposite the rod is attached to the body casting. The acceleration bellows provides an absolute pressure reference. The governor bellows is secured in the body cavity and its function is similar to that of a diaphragm. Movement of the bellows is transmitted to the metering valve by the cross shaft and associated levers. The cross shaft moves within a torque tube which is attached to the shaft near the bellows lever. The tube is secured in the body casting at the opposite end by means of an adjustment bushing. Therefore, any rotational The bellows
bellows connected
movement of the cross shaft will result in
an
increase
or
decrease in the force of the
torque tube. The torque tube forms the seal between the air and fuel sections of the control. The torque tube is positioned during assembly to provide a force in a direction
tending to close the metering valve. The bellows act against this force to open the metering valve. Py pressure is applied to the outside of the governor bellows. Pr pressure is applied to the inside of the governor bellows and to the outside of the acceleration bellows. ;B.
For explanation purposes the governor bellows assembly is illustrated as a diaphragm (see Figure 1-8-5). Py pressure is applied to one side of the diaphragm and Pr is applied to the opposite side. Pr is also applied to the evacuated bellows attached to the diaphragm. The force of Pr applied against the evacuated bellows is cancelled by application of the same pressure on an equal area of the diaphragm, as the forces act in opposite directions. All pressure forces applied to the bellows section can be resolved into forces acting on the diaphragm only. These forces are: Py pressure acting on the entire surface of one side; the internal pressure of the evacuated bellows acting on a portion of the opposite side (within the area of pressure cancellation); and Pr acting on the remainder of that side. Any change in Py will have more effect on the diaphragm than an equal change in Pr, due to the difference in effective area.
C.
Pr and Py vary with changing engine operating conditions as well as inlet air temperature. When both pressures increase simultaneously, as during acceleration, the bellows cause the metering valve to move in an opening direction. When Py decreases as the
desired compressor turbine speed (Ng) is approached (for governing after acceleration), the bellows will travel to reduce the opening of the metering valve. When both pressures decrease simultaneously, the bellows will travel to reduce the metering valve opening because a change in Py is more effective than the same change in Pr. This occurs during deceleration and moves the metering valve to its minimum flow stop. D.
incorporating a manual override (see Figure 1-8-6), the cover containing stop (for governor bellows) and the retaining plate is removed and replaced by a mechanism which can manually move the end of the governor bellows. This, in turn, will move the metering valve in a direction to increase the fuel flow to the engine. The mechanism contains an operating pin with a driving pin passing through it and through the portion of the actuating shaft which is contoured (helix). Both ends of the driving pin engage in slots in the cover to prevent rotation. A special manual control in the cockpit connects to the actuating shaft lever and provides rotation of the actuating shaft. When the lever is in the OFF position, the operating pin acts as the bellows travel stop. This system is uni-directional in that it can only push on the governor bellows On installations,
the bellows travel
to increase fuel flow. It has
no
reduce fuel flow. This system bellows failure.
power to
provides
the bellows in the other direction to emergency control in the event of governor
move
an
Page
1-8-13
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AREAOFPRESSURE CANCELLATION
Pr Py
Pr
EVACUATED
DIAPHRAGM REPRESENTS GOVERNOR BELLOWS
(ACCELERATION) BELLOWS
C434 FCU Bellows Section
Figure
Functional
Diagram
1-8-5
Page
1-8-14
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO.’ 3015442
SHIMS
DRIVINGPIN
COVER
STOP
SHAFT
LEVER
OPERATING PIN BODY
C30A Manual Override
Figure
System
1-8-6
Page
1-8-15
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
POWER TURBINE GOVERNOR 9.
(PT6A-6
SERIES AND PT6A-20
ENGINES)
GENERAL A.
The power turbine govemor, mounted on the reduction gearbox of the engine, is driven at a speed proportional to power turbine speed (Nf). The function of the power turbine governor is to limit the maximum speed of the power turbine (Nf) as, during normal operation, Nf is controlled by the propeller governor. However, if a malfunction occurs the power turbine governor will prevent power turbine speed (Nf) from exceeding 105%. This is accomplished by reducing the fuel flow in the FCU.
B.
The power turbine governor employs a drive body similar to the drive body of the FCU, with the main difference being the elimination of the speed enrichment mechanism. The cover incorporates vent holes which maintain the inner cavity of the governor at atmospheric pressure (Pa). During normal operation, the governor throttle lever is
positioned against the locked in this position. C.
maximum
speed stop. On non-reversing applications,
Py pressure from the FCU (see Figure 1-8-1) is applied to the power turbine governor valve. If a power turbine overspeed occurs, the governor weight force overcomes the spring force which opens the valve to bleed off Py pressure. This, in turn, reduces Py pressure on the governor bellows on the FCU, and results in a reduction of fuel flow and
consequently,
compressor turbine
speed (Ng).
As the
overspeed
condition is
corrected, the governor weight force diminishes and the spring force again
weight force. This action closes the valve fuel flow to the FCU.
the reduced
engine D.
the lever is
On installations
during by the
using
restoring
control of
Py
overcomes
pressure and
reversing propeller, the propeller governor becomes ineffective operation, and power turbine speed (Nf) is then controlled governor to approximately 95%. a
REVERSE THRUST
power turbine
Page
1-8-16
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER GOVERNOR 10.
(PT6A-20A
AND -208
ENGINES)
GENERAL A.
propeller governor, mounted on the reduction gearbox of the engine contains a propeller governor (CSU) section, a reversing valve, and a power turbine governor section, driven at a speed proportional to power turbine speed (Nf). The Nf governor section provides power turbine overspeed protection during normal operation. During reverse thrust operation the propeller governor is inoperative and control of power turbine speed is accomplished by the Nf governor section. The Nf governor section of the propeller governor senses Py pressure through an external pneumatic line from the drive body adapter on the FCU to the governor. In the event of a power turbine overspeed condition, an airbleed orifice in the Nf governor section is opened by flyweight action (see Figure 1-8-1), to bleed off Py pressure through the governor. When this occurs, Py pressure acting on the FCU bellows decreases to move the FCU metering valve in a closing direction, thus reducing fuel flow. Reduction in fuel flow decreases Ng speed and consequently Nf speed. The speed at which the airbleed orifice opens is dependent on the setting of the propeller governor control lever and the setting of the Nf air bleed link. Normally the airbleed orifice is opened at approximately 6% above propeller governor speed setting with the Nf govemor air bleed link at maximum position, and approximately 4% under propeller governor speed setting at minimum position. In reverse thrust the propeller reversing interconnect linkage resets the Nf governor air bleed link to a setting below the propeller governor control lever setting. Power turbine speed (Nf) and hence propeller speed is then limited by the Nf governor; power supplied by the gas generator is reduced to allow a propeller speed approximately 5% under the speed set by the propeller governor. The
normal
TEMPERATURE COMPENSATOR 11.
GENERAL A.
on the compressor inlet into the inlet air stream. Compressor discharge pressure (Pc) is applied to the compensator. This pressure source is used to provide a Pr pressure signal to the FCU. The compensator changes the Pr pressure to provide an acceleration schedule biased by inlet temperature to prevent compressor stall or
The
temperature compensator (see Figure 1-8-7) is mounted
case
with the bimetallic disks
extending
excessive turbine temperature.
FUEL CONTROL SYSTEM 12.
COMPLETE OPERATION
(TYPICAL)
ENGINE STARTING A.
PT6A-6 engine starting cycle is initiated with the power control lever in the CUT-OFF position, while PT6A-6A, PT6A-68, PT6A-6/C20, PT6A-20, PT6A-20A and PT6A-20B engine starting cycle is initiated with the power control lever in the IDLE position and the fuel shut-off lever in the CUT-OFF position. The ignition and starter are switched on and when required compressor turbine speed (Ng) is attained, either the power control lever on the former engines or the fuel shut-off lever on the latter engines, is moved to the IDLE position to provide fuel. For the fuel ratio curve (see Figure 1-8-8).
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
NEEDLE VALVE
Q
HOT
BIMETALLIC DISK GROUP
P, COMPRESSOR AIR
C3
P
C31A
Temperature Compensator Cross Figure 1-8-7
Section
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
ACCELERATION
STARTING
105"F 59"F Wf Pc
-50"F
0
IDLE
IGNITION
Ng
SPEED ENRICHMENT
100
SPEED
C32B Fuel Ratio Curve for
Starting and Acceleration Figure 1-8-8
Schedules
(Typical)
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
B.
At the time of
ignition, the fuel control metering valve is in a low flow position. As the engine accelerates, the compressor discharge pressure (Pc) increases, causing an increase in Pr pressure. Pr and Py increase simultaneously as Pr Py during engine acceleration. The increase in pressure sensed by the bellows causes the metering valve to move in an opening direction. As compressor turbine speed (Ng) approaches idle, the centrifugal force of the drive body weights begins to overcome the governor spring force and opens the governor valve. This creates a Pr Py differential which causes the metering valve to move in a closing direction until the required-to-run idle fuel flow is obtained.
C.
13.
variation in engine speed from the selected (idle) speed will be sensed by the governor weights and will result in increased or decreased weight force. This change in weight force will cause movement of the governor valve which will then be reflected .a change in fuel flow necessary to re-establish the proper speed.
Any
by
ACCELERATION A.
As the power control lever is advanced above the IDLE position, the speed scheduling cam is repositioned, moving the cam follower lever to increase the governor spring
force. The governor spring then overcomes the weight force and moves the lever closing the governor valve. Pr and Py immediately increase and cause the metering valve to move in an opening direction. Acceleration is then a function of increasing Pr (Px Py). B.
With the increase in fuel flow, the compressor turbine will accelerate. When compressor turbine speed (Ng) reaches a predetermined point (above 80%), weight force overcomes the enrichment spring and starts to close the enrichment valve. When the enrichment valve starts to close, Py and Pr pressures increase causing an increase in the movement rate of the governor bellows and metering valve, thus providing speed enrichment to the acceleration fuel schedule. Continued movement of the enrichment will then be discontinued. Meanwhile, as compressor speed (Ng) and hence power turbine speed (Nf)
increase, the propeller governor increases the pitch of the propeller to prevent Nf from overspeeding and applies the increased power as additional thrust. Acceleration is completed when the centrifugal force of the weights again overcomes the governor spring and opens the governor valve. 14.
GOVERNING A.
15.
Once the acceleration cycle has been completed, any variation in engine speed from the selected speed will be sensed by the governor weights and will result in increased or decreased weight force. This change in weight force will cause the governor valve to either open or close, which will then be reflected by the change in fuel flow necessary to re-establish the proper speed. When the FCU is governing, the valve will be maintained in a regulating, or "floating" position.
ALTITUDE COMPENSATION A.
compensation is automatic with this fuel control system since the acceleration assembly is evacuated and affords an absolute pressure reference. Compressor discharge is a measurement of engine speed and air density. Pr is proportional to compressor discharge pressure, so it will decrease with a decrease in air density. This is sensed by the acceleration bellows which acts to reduce fuel flow.
Altitude bellows
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
18.
DECELERATION A.
When the power control lever is retarded, the speed scheduling cam is rotated to a lower point on the cam rise. This reduces the governor spring force and allows the governor valve to move in an opening direction. The resulting drop in Py moves the valve in a closing direction until it contacts the minimum flow stop. This stop sufficient fuel to the engine to prevent flameout. The engine will continue to decelerate until the governor weight force decreases to balance the governor spring force at the new governing position.
metering assures
17.
REVERSE THRUST OPERATION A.
On PT6A-6A engine installations, the FCU speed scheduling cam has two contoured robes. This permits scheduling full power at each end of the power control lever travel. When the power control lever is moved into the reverse thrust range, the propeller pitch control and the FCU are integrated. Power control lever movement toward full reverse will increase gas generator turbine speed (Ng) and propeller reverse pitch. The function of the propeller governor is eliminated in the reverse thrust range and the limiting of power turbine speed (Nf) is provided by the power turbine governor.
B.
On PT6A-6B, PT6A-6/C20, PT6A-20, PT6A-20A and PT6A-20B engine installations, the FCU has a single lobe cam. A cam type linkage on the engine provides forward movement of the fuel control lever at the fuel control when the power control lever is moved in either the reverse lobe cam in this control.
G
forward direction. This eliminates the
necessity
for the two
The idle reset has two settings, low (ground) idle and high (flight) idle. The high idle setting permits acceleration to maximum rpm to be accomplished in a reduced amount of time. The idle setting, as well as cut-off, is controlled by the cut-off lever in the
D.
or
cockpit.
The throttle
linkage
is used
only
to increase
or
decrease power.
When the power control lever is moved into the reverse thrust position, it integrates the propeller pitch control and the function of the propeller governor is eliminated. In the reverse thrust range limiting of power turbine speed (Nf) is provided by the power turbine
governor. E.
linkage moves the power turbine governor lever or, air bleed link on propeller governor (PT6A-20A and PT6A-20B engines) away from the maximum stop, so limiting will be on the idle adjustment which is set at approximately 95% power turbine speed (Nf).
F.
When power turbine speed (Nf) is reset during reverse thrust operation, the power turbine governor servo will be partially open, bleeding off some Py pressure. If
Coordinated
power turbine
speed drops off,
the
servo
valve will
move
toward its closed
position
increasing Py pressure and fuel flow to increase compressor turbine speed (Ng), thereby increasing power turbine speed. If power turbine speed exceeds the desired value, the servo valve will move further open to decrease Py pressure and fuel flow.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
18.
STOPPING THE ENGINE A.
The cut-off valve provides a positive means of stopping fuel flow to the engine. During normal operation, this valve is fully open and offers no restriction to the flow of fuel to the nozzles. On PT6A-6 engines the cut-off valve is operated by the power control lever. On PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20, -20A and -20B engines an additional linkage system is employed to operate the cut-off valve. PT6A-6 engines are stopped by placing the fuel shutoff lever in the CUT-OFF position. This action moves the FCU cut-off valve to its seated position stopping all fuel flow to the engine.
FUEL DUMP VALVE 19.
GENERAL A.
The fuel dump valve consists of a spring-loaded poppet valve which automatically dumps residual manifold and spray nozzle fuel overboard after engine shutdown. The valve is connected to the common fuel manifold adapter by a tube coupling at the 6 o’clock position. Pressure fuel is led from the fuel control unit directly to the fuel dump
through an external pipe. Fuel pressure in excess of 13 psig opens a port connecting the valve inlet with the manifold and directs the fuel flow through to the nozzles. Conversely, closing of the shut-off valve in the fuel control unit will stop the fuel flow, reduce the fuel pressure at the dump valve which will open and dump residual fuel overboard, thus preventing the fuel from being coked in the system due to heat absorption. (See Figure 1-8-9). valve
FUEL MANIFOLD AND SPRAY NOULES 20.
GENERAL A.
The fuel manifold delivers
a
constant
supply
of
high-pressure
fuel from the fuel
dump
valve to 14 simplex fuel nozzles. The common fuel manifold consists of 14 fuel manifold adapter assemblies interconnected by 14 short fuel transfer tubes. The transfer tubes incorporate preformed packings at each end to accomplish sealing. Lockplates maintain the transfer tube alignment and security in their respective manifold adapters. Each manifold, with its lockplate, is secured by two bolts to a mounting boss on the
circumference of the gas generator
adapter assemblies
can
case.
be removed and
Individual transfer tubes and fuel manifold
replaced
without
removing
the
remaining
assemblies and tubes.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
LOCKING PLATE
FUEL MANIFOLD ADAPTER ASSEMBLY
FUEL MANIFOLD TRANSFER TUBE
GASKET
GAS GENERATOR CASE ASSEMBLY
COMBUSTION CHAMBER LINER ASSEMBLY FUEL NOZZLE FUEL NOZZLE SHEATH
(Most
PT6A-20 and
Fuel Manifold
C1213
PT6A-20B, and all PT6A-20A Engines)
Adapter Assembly Front Cross Section Figure 1-8-9
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
21.
FUEL MANIFOLD ADAPTER ASSEMBLY A.
The fuel manifold
adapter assembly (see Figure 1-8-9 and 1-8-10) consists of 14 fuel adapters, each fitted with a simplex fuel nozzle assembly. The fuel nozzle assemblies provide a fine atomized fuel spray in the annular combustion chamber liner. Each fuel nozzle assembly consists of a sheath, a spray nozzle and tip all protected by a fine strainer. The sheath, which functions as a heat shield, fits over the fuel nozzle assembly and is located on the underside of the manifold adapter by a dowel pin. The sheath is perforated at the flanged end to permit entry of compressor discharge air, which cools the nozzle tips and assists fuel atomization. The fuel nozzles are positioned on the manifold adapter extension to produce a continuous tangential spray from one manifold
nozzle to the next in the combustion chamber liner. The combustion chamber liner is located and supported by alternate fuel nozzle sheaths. The sheaths act as spigots and pass through the suspension collars and support brackets welded on the outer wall of the liner. The spigot fit, between the sheaths and suspension collars, securely locates the front of the liner in the gas
generator
case.
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
FUEL MANIFOLD ADAPTER ASSEMBLY
LOCKING PLATE
FUEL MANIFOLD TRANSFER TUBE
GASKET~
GAS GENERATOR CASE ASSEMBLY
COMBUSTION CHAMBER LINER ASSEMBLY
FUEL NOZZLE
(PT6A-6, -6A, -6B, PT6A-6/C20, early Fuel Manifold
PT6A20 and PT6A-20B
Adapter Assembly
Figure
FUEL NOZZLE SHEATH
Engines)
C33A
Front Cross Section
1-8-10
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
SECTION 9 1.
DESCRIPTION OF ENGINE
ENGINE CONTROLS AND INSTRUMENTATION
GENERAL A.
following instrumentation and controls are available and considered necessary for operation of engine in flight, to ascertain its mechanical condition, and to ground check and adjust the power output when necessary.
The
normal
2.
POWER CONTROL LEVER A.
The power control lever controls the gas generator speed and thus modulates engine power output from Idle to Takeoff. The position for Idle represents the lowest permissible
level of power. B.
On
non-reversing propeller installations, positions below Idle.
fuel to the
engine
is
automatically
shut off at
lever C.
3.
reversing propeller installations, the lever is interconnected with the power turbine governor, or propeller governor on PT6A-20A and PT6A-20B engines only and modulates engine power from Full Reverse to Takeoff. On
FUEL SHUT-OFF LEVER (PT6A-6A, -6B, -6/C20, -20, -20A AND -20B ENGINES) The fuel shut-off lever opens and closes the cut-off valve, thus selecting CUT-OFF or IDLE positions, through external linkage. This lever also selects the HI-IDLE position where
4.
applicable.
PROPELLER CONTROL LEVER (PT6A-6, -6A, -6B, -6/C20, -20, -20A AND -20B ENGINES) A.
propeller lever positions the speed adjusting lever on the propeller governor to provide a means of selecting the desired propeller rpm. When placed in the maximum decrease rpm position, the propeller will automatically feather.
The
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
5
INTERTVRBINE TEMPERATURE SENSING SYSTEM (T5)
-20B A.
(PT6~-B/C20. -2~,
-20A FIND
ENGINES) temperature sensing system (Tt5) provides the pilot with an accurate engine operating temperatures. The system monitors the temperature at a
The interturbine indication of
point between the compressor and power turbines; it consists of 8 individual thermocouples connected in parallel by a bus-bar assembly. Earlier engines may include a wiring harness assembly in lieu of the bus-bar. Each thermocouple probe protrudes through a threaded boss on the power turbine stater housing into the area immediately in front of the leading edge of the power turbine vanes (see Figure 1-9-1). Each probe is secured to its boss by means of a floating, threaded fitting which is part of the probe assembly. The bus-bar assembly consists of two bus-bars with 8 terminal straps on each bar. Each bus-bar terminal strap is secured to its respective probe assembly terminal by special screws, the large diameter screws being for the alumel terminals and the smaller diameter screws for the chromel terminals. The bus-bar assembly is located on the power turbine stater housing by five mounting clamps. The assembly is secured together with five sealing ring retaining plates, by five bolts. The shielded leads which connect each bus-bar to the terminal block are supported by four brackets welded on the power turbine stater housing and two brackets on the exhaust duct. The terminal block is mounted at the 2 o’clock position on the gas generator case. The terminal block and gasket are secured on the inner wall of the gas generator case with the terminals protruding through the case to provide a connection point for external wiring to cockpit instrumentation. 6.
TURBINE TEMPERATURE SENSING SYSTEM (T4) (PT6A-6, -6A AND -6B ENGINES) A.
The turbine inlet temperature sensing system (T4) provides the pilot with an accurate indication of engine operating temperatures. The system monitors the temperature of the gases in the area immediately in front of the compressor turbine guide vanes and consists of 24 chromel/alumel
thermocouple probes,
and
a
chromel and
an
alumel bus-bar
a wiring harness. The thermocouple probes are mounted in pairs assembly brackets and connected in parallel to two bus-bars. Each bracket is secured to
on
12
E by a centrally located bolt. The probes extend through the small exit duct into the gas stream between the large and small exit ducts, through a locating ring mounted on the front face of the small exit duct (See Figure 1-9-2). The shielded wiring harness connected to the bus-bars incorporates an integral terminal block which is mounted at the 2 o’clock position on the gas generator case. The terminal block and gasket are secured to the inner wall of the gas generator case, with their terminal posts protruding
flange
through
a
port in the
for external bverhauled 7.
the connection point for the trim harness and instrumentation. The trim harness is provided on some cockpit to eliminate read out errors. case, to
provide
for
wiring engines
OIL PRESSURE INDICATOR A.
The oil pressure indicator shows the pressure in the lubricating system, taken from the delivery side of the oil pump. Provision has been made to install an oil pressure transmitter in a mounting boss located at the 3 o’clock position on the accessory gearbox
housing.
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MAINTENANCE MANUAL MANUAL PART NO. 3015492
a,,
TERMINAL BLOCK
SHIELDED LEADS
fERMINALLUC
ALUMEL
\i
CHROMEL SEAL
RETAININGPLATE\i\
TERMINAL STRAPS
BUS-BAR SCREW TERNIINALLUG
CONTAINMENT RING
TRIM THERMOCOUPLE
CHROMEL TERMINAL
~MEL:ERMINIL
ALUMELTERFIIINAL
CAP SCREW
WASHER
DETAIL
A
T5 TERMINAL BLOCK
THREADED COUPLING PROBE ASSEMBLY
O~
CHROMEL TERMINAL FLANGE
DETAIL OF
THERMOCOUPLE PROBE
(PT6A-20 Interturbine
C
(REF.)
Series
Engines)
C571D
Temperature (T5) Sensing System Figure 1-9-1
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
GAS GENERATOR CASE ASSEMBLY FUEL NOULE
COMBUSTION CHAMBER LINER ASSEMBLY COMBUSTION CHAMBER SMALL EXIT DUCT
WIRING
I
HARNESS
V
LARGE EXIT DUCT
TERMINAL BLOCK EXHAUST CASE ASSEMBLY POWER TURBINE
I POWER TURBINE GUIDE VANES
FLANGE
TURBINE
j
1
PROBE
COMPRESSOR TURBINE GUIDE VANES
WIRING HARNESS
INCONEL TWEE
PROBE
BRACKET
MOUNTING BOLT HOLE
1111
CHROMEL BUS-BAR
ALUMEL BUS-BAR
(PT6A-6 Turbine Inlet
Series
Engines)
C309B
Temperature (T4) Sensing System Figure 1-9-2
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
8.
OIL TEMPERATURE INDICATOR A.
temperature indicator shows the temperature of the lubricating oil as it leaves the delivery side of the pressure oil pump. A mounting boss is provided on the accessory gearbox housing just below the oil pressure transmitter mounting to accommodate an oil
The oil
temperature bulb. 9.
TACHOMETER-GENERATOR A.
GAS GENERATOR
(Ng)
tachometer-generator provides an electric current which is used in conjunction with tachometer to indicate gas generator rpm. The tachometer-generator is located at the 5 o’clock position on the accessory gearbox housing and is driven from the internal scavenge pump. Rotation is counterciockwise with a drive ratio of 0.112.1.
The a
10.
TACHOMETER-GENERATOR A.
11.
POWER TURBINE (Nf)
tachometer-generator operates in the same manner as that of the gas generator. However, the turbine tachometer-generator is installed on the reduction gearbox case and rotates clockwise with a drive ratio of 0.1273.1.
The power turbine
TORQUEMETER A.
The torquemeter indicating system is an integral hydro-mechanical torque measuring device which provides an accurate indication of the torque being produced by the power turbine. The torque pressure value is obtained by tapping the two outlets on top of the reduction gearbox. The pressure differential between the two outlets is then led to an instrument which indicates the correct torque pressure.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
SECTION 10
DESCRIPTION OF ENGINE
PROPELLER NON-REVERSING INSTALLATION
(PT6A-6 ENGINES) 1.
GENERAL A.
2.
engines non-reversing installation is designed to utilize a hydraulically operated propeller controlled by a propeller governor and an overspeed governor. A power turbine governor prevents turbine overspeed by controlling gas generator output through the FCU. The PT6A-6
PROPELLER A.
The engine is normally equipped with a three bladed metal propeller dowelled and bolted to the front face of the propeller shaft flange. The propeller consists of a hollow steel spider hub which supports three propeller blades and also houses an internal oil pilot tube and feather return springs (see Figure 1-10-1). Movement of the propeller blades is controlled by a hydraulic servo piston which is mounted on the front of the spider and is connected by individual linkage to the blade trailing roots. Centrifugal counterweights on each blade, combined with the feathering springs in the servo piston, tend to drive the piston into the feather or high pitch positions. This movement is opposed by the oil pressure generated and controlled by the propeller governor. The oil is routed to the Servo piston via an internal oil transfer housing and the oil pilot tube. An increase in the oil flow moves the servo piston forward, pulling the blades towards the low pitch position (increased rpm). A decrease in the oil flow allows the blades to move toward the high pitch position (decreased rpm) under the influence of the feathering springs and blade counterweights.
erusserprelleporp
3.
PROPELLER GOVERNOR A.
propeller governor consists of a constant speed single-acting centrifugal governor on the reduction gearbox front case at the 12 o’clock position. The propeller governor regulates power turbine speed by varying the pitch of the propeller to match the load torque to the engine torque in response to changing flight conditions. The propeller governor utilizes pressure oil to decrease blade pitch while the centrifugal force of the blade counterweights assisted by return springs tend to increase the pitch.
The
mounted
B.
The main parts of the~ propeller governor include a gear type oil pump with a pressure relief valve, a pair of pivoted flyweights mounted on a rotating flyweight head, a spring-loaded pilot valve and the necessary cored passages contained in the governor cover and base. The rotating flyweights determine the position of the spring-loaded pilot valve while the spring load adjusting control is varied by an externally mounted speed lever.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER CONTROL LEVER
GOVERNOR PUMP
SPEED SETTING SCREW
’R-
SPEEDER SPRING THRUST BEARING
U
7~
SPEEDER SPRING
THRVSTBEPIRING
Uc FLY-
7
PROPELLERWEIGHTS Y~ij
GOVERNOR
PROPELLER OVERSPEED GOVERNOR
RELIEF VALVE DRIVE
II
SPLINE OIL DUMP TO REDUCTION GEARBOX
DRIVE
SPLINE
ii
OIL DUMP TO REDUCTION GEARBOX
COUNTERWEIGHT
ENGINE OIL SUPPLY
FEATHER RETURN SPRINGS SERVO PISTON
ROTATION
t
PISTON SEAL
PROPELLER OIL TRANSFER HOUSING
SLIDING GUIDE ROD (3) HIGH PITCH STOP
PROPELLER
COUNTERWEIGHT FINE PITCH
C548A
Typical Single-acting Propeller Figure 1-10-1
Schematic
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
propeller governor incorporates two safety features. The first is the control lever spring attached to the speed adjusting lever. In the event of a propeller control linkage failure, the spring holds the speed adjusting lever in its last selected position or moves it toward the high speed setting. A high speed stop prevents the lever moving beyond the 100% position and enables the engine to operate at or near full rated speed and to develop maximum power. The second safety feather is a positive low speed setting. Moving the propeller control lever and thence the speed adjusting lever against the low speed stop, raises the pilot valve to a positive coarse pitch or feathering position regardless of flyweight force. This enables the pilot to feather the propeller and minimize propeller drag in the event of engine failure. The
D.
the propeller governor with a sensing element, the rotating pivoted flyweights mechanically to the engine by a hollow drive gearshaft (see Figure 1-10-2). The rotating flyweights, actuated by centrifugal force, position the pilot valve so as to cover or uncover ports in the drive gearshaft and regulate the oil flow to and from the propeller servo piston. The centrifugal force exerted by the flyweights is opposed by the force of the adjustable speeder spring. This determines the engine rpm required to develop sufficient centrifugal force on the flyweights to center the pilot valve. To
are
4.
During an on-speed condition, (see Figure 1-10-2) the forces acting on the combination are in a state of balance. With the propeller control engine/governor/propeller lever set to obtain the desired rpm, and the propeller blades in the correct pitch range to absorb the power developed by the engine, the centrifugal force of the rotating flyweights exactly balances the force of the speeder spring with the flyweights in the vertical position. This positions the pilot valve plungers so that the ports which control the oil flow from the propeller governor pump to the propeller servo piston are closed. The oil is therefore diverted through the open relief valve back to the inlet side of the pump.
PROPELLER GOVERNOR OVERSPEED CYCLE A.
6.
linked
PROPELLER GOVERNOR ON-SPEED CYCLE A.
5.
provide
In an overspeed condition, the rotating flyweights pivot outward, overcome the speeder spring tension and raise the pilot valve plunger. This uncovers the ports in the drive gearshaft and dumps the oil from the propeller servo piston to the reduction gearbox sump. As the propeller blades increase in pitch angle the load on the engine is increased with a consequent decrease in engine rpm. The centrifugal force exerted on the governor flyweights is reduced allowing the speeder spring tension to return the flyweights to a vertical position. The pilot valve plunger once again blocks the flow of control oil to or from the propeller servo piston.
PROPELLER GOVERNOR UNDERSPEED CYCLE A.
With the propeller control lever set to the desired rpm, a condition of underspeed when the engine rpm drops below the predetermined setting. The speeder spring
occurs
tension then overcomes the decreased centrifugal force on the flyweights and pivots them inward, forcing the pilot valve plunger downward and opening the ports. This directs a flow of pressure oil to the propeller servo piston which overcomes the combined forces of the propeller counterweights and return springs and decreases the pitch of the propeller blades. The load on the engine is reduced with a consequent increase in engine rpm. This is sensed by the propeller governor flyweights causing the pilot valve plunger again to be positioned to close the oil ports.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
SPEED ADJUSTING CONTROL LEVER HIGH SPEED STOP
CONTROL LEVER SPRING
LIFT ROD
FLYWEIGHT ADJUSTING WORM
SPEEDER
DRIVE GEAR SHAFT PILOT VALVE PLUNGER
n
RELIEF VALVE
EOTGNIRPS
FLYWEIGHT HEAD
DRAIN TO SUMP j
OIL PUMP
PROPELLER
CONTROL LINE
ENGINE OIL INLET
PRESSURE
"ON SPEED CONDITION"
C547
Propeller Governor -Schem~atic Figure 1-10-2
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
PROPELLER OVERSPEED GOVERNOR
A.
propeller overspeed governor is installed in parallel with the propeller governor and is mounted at approximately the 10 o’clock position on the reduction gearbox front case. It is provided to control power turbine/propeller overspeed condition by immediately dumping the oil from the propeller servo piston to the reduction gearbox sump (see Figure 1-10-1). The overspeed governor consists of conventional type flyweights mounted on
The
rotating hollow splined shaft. The hollow shaft embodies ports which are normally closed by a pilot valve and held in this position by a speeder spring. The spring tension acts in opposition to the centrifugal force produced by the rotating flyweights. When a power turbine/propeller overspeed condition occurs, the increased centrifugal force sensed by the flyweights overcomes the spring tension, lifts the pilot valve and dumps the propeller servo piston oil back to the reduction gearbox through the hollow splined shaft. This permits the combined forces of the counterweights and return springs to move the blades toward a coarse pitch position, absorbing the engine power and preventing further power turbine/propeller overspeed. a
8.
POWER TURBINE GOVERNOR A.
Th e powe r tu rb i n e gove m o r i s m o u nted on top of a san dw ich type tach om ete r-gene rater located at the 2 o’clock position on the reduction gearbox front case. It is driven by the propeller shaft through bevel gears. This governor provides additional overspeed protection by utilizing an overall fuel limiting control which becomes effective at approximately 105% power turbine (Nf) rpm. Further clarification is provided in Section
8, preceding.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
SECTION 11
DESCRIPTION OF ENGINE
PROPELLER REVERSING INSTALLATION
(PT6A-6A ENGINES) 1.
GENERAL A.
2.
reversing propeller installation consists of a reversing propeller, controlled by a propeller governor. An optional overspeed governor may be provided to limit engine speed in the event of a propeller governor failure. A propeller governor lever determines the limiting rpm range to which the governor will control the propeller in the normal range. The power delivered by the engine to the propeller shaft is controlled by a power control lever through the FCU. However, for reverse propeller operation the FCU works in conjunction with a power turbine governor to limit power output according to propeller requirements. An adjustable linkage, control levers and a slotted cam arrangement interconnect a reversing valve and lever with the power turbine governor and the FCU, thereby enabling all reverse pitch operations to be controlled by the cockpit power control lever (see Figure 1-11-1). The PT6A-6A
PROPELLER A.
engine is normally equipped with a three bladed metal propeller dowelled and bolted to the front face of the propeller shaft flange. The propeller consists of a hollow steel spider hub which supports three propeller blades and houses an internal oil pilot tube and feather return springs (see Figure 1-11-1). Movement of the propeller blades is controlled by a hydraulic servo piston which is mounted on the front of the propeller spider hub and connected by individual linkage to the blade trailing roots.
The
Centrifugal counterweights on each blade combined with the feathering springs in the servo piston, tend to drive the piston into the feather or high pitch position. This movement is opposed by the propeller governor. The pressure oil is routed to the servo piston via an internal oil transfer housing the oil pilot tube. An increase in the oil pressure moves the servo piston forward pulling the propeller blades towards the low pitch position (increased rpm). A decrease in the oil pressure allows the blades to move toward the high pitch position (decreased rpm) under the influence of the feathering springs and blade counterweights. B.
The
servo
piston
is also connected
by three spring loaded sliding rods to a feedback The three rods are actuated by the servo piston,
propeller. ring automatically repositioning the feedback ring. Movement of the feedback ring is transmitted by a carbon block through linkage to the reversing valve which opens progressively and diverts oil flow from the propeller to the reduction gearbox, precluding any further change in pitch. Conversely, closing of the valve will increase the oil flow and so decrease the pitch (increased rpm). mounted behind the
C.
The
reversing
maximum on
the
valve function is to schedule the blade angle between the low and pitch positions and also limit the low pitch. An internal sleeve located
reverse
pilot valve provides angle.
a
mechanical stop to limit blade
pitch
at the maximum
reverse
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER CONTROL LEVER
PROPELLER OVERSPEED GOVERNOR
PROPELLER GOVERNOR
g--
SPEEDER SPRING
THRUST BEARING FLYWEIGHTS
RELIEF VALVE
T
I)
II
DRIVE SPLINE
II
R
-i~-
II
I
GEARBOX
PROPELLER OIL TRANSFER HOUSING
TP~KEOFF POWER
COUNTERWEIGHT FEATHER RETURN SPRINGS SERVO PISTON
II
-I´•o
Il
FLOW DIVIDER V
II
t
I
POWER CONTROLLEVER
CARBONBLOCK REVERSINGVALVELEVER J
VALVE
FOLLOWEP
PISTON SEAL
REVERSE RETURN SPRINGS
TO REDUCTION GEARBOX SUMP
REAR
OILDUMPTO REDUCTION GEARBOX
.´•::.:-´•´•:´•1
CHECK VALVE
II
II
DRIVE SPLINE
r
RINGI/
IDLE
\1’
CJ
ii
OIL DUMP TO REDUCTION GEARBOX
FULL REVERSE
SPEEDER SPRING
~J
GOVERNORPUMP
MAIN OIL SUPPLY
SPEED SETTING SCREW
POWER TURBINE GOVERNOR
LEVER
MAX. STOP-SET AT U.A.C.L.
PROPELLER CONTROLLEVER
,C
FUEL CONTROL UNIT LEVER
9) ~YI
I
I CENTER FIRESEAL
CONTROL LEVER
REAR
MOUNTING BRACKET
FIRESEAL
ADJUSTABLE TURNBUCKLE GOVERNOR ACTUATING LEVER ASSEMBLY
C549A
(PT6A-6A Engines) Propeller Reversing Installation Figure 1-11-1
Schematic
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3
PROPELLERGOVERNOR A.
propeller governor consists of a constant speed single-acting centrifugal governor mounted at the 12 o’clock position on the reduction gearbox front case. The governor regulates power turbine speed by varying propeller blade pitch to match the load torque to the engine torque, in response to changing flight conditions. The governor utilizes pressure oil to decrease blade pitch while the centrifugal force of the blade The
counter-weights 1-11-1). B.
by
return
springs
tend to increase the
pitch. (See Figure
a gear-type oil pump with a pressure pair of pivoted flyweights mounted on a rotating flyweight head; a spring-loaded pilot valve and the necessary cored oil passages contained in the propeller governor housing and base. The rotating flyweights determine the position of the pilot valve while the spring load can be varied by an externally mounted propeller control lever.
The main
parts of the propeller governor include
relief valve;
C.
assisted
a
propeller governor incorporates two safety features. The first is a control lever spring which is attached to the speed adjusting lever. In the event of a propeller control linkage failure, the spring holds the speed adjusting lever in its last selected position, or tends to move it toward the high speed setting. The high speed stop prevents the lever moving The
position and enables the power turbine to operate at or near develop maximum power. The second safety feature is a positive speed low speed setting. Moving the speed adjusting control lever against the low speed stop raises the pilot valve to a positive coarse pitch or feathering position regardless of flyweight force. This enables the pilot to feather the propeller and minimize propeller drag in the event of engine failure.
beyond
the 100%
and
full-rated
D.
propeller governor with a sensing element, the rotating pivoted flyweights mechanically to the engine by a hollow drive gearshaft (see Figure 1-11-2). The rotating flyweights actuated by centrifugal force, position the pilot valve so as to cover or uncover ports in the drive gearshaft and regulate the oil flow to and from the propeller servo piston. The centrifugal force exerted by the flyweights is opposed by the force of the adjustable speeder spring. This determines the engine rpm required to develop sufficient centrifugal force on the flyweights to center the pilot valve.
To
provide
are
4.
the
linked
PROPELLER GOVERNOR ON-SPEED CYCLE A.
During an on-speed condition (see Figure 1-11-2) in forward thrust the forces acting on combination are in a state of balance with the propeller engine/governor/propeller control lever set to obtain the desired rpm and the propeller blades in the correct pitch range to absorb the power developed by the engine, the centrifugal force of the rotating flyweights exactly balances the force of the speeder spring with the flyweights in the vertical position. This positions the pilot valve plunger so that the ports which control the oil flow from the govemor pump to the propeller servo piston are closed. The oil is therefore diverted through the open relief valve back to the inlet side of the the
govemor pump.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
10 8
12
13
14
4
15
2
Ir
C342B
(PT6A-6A Engines) Reduction Gearbox
Propeller Reversing
Figure
Installation
1-11-2
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PRATT
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Key
1-11-2
Pressure Oil Transfer Tube
2.
Flow Divider Valve
3.
Cable Tensioner
4.
Low Pitch
Housing
6.
Stop Adjustment Reversing Valve Reversing Valve Lever
7.
Power Turbine Governor
8.
Governor
12.
Actuating Linkage Reversing Lever Guidepin Return Spring Sliding Rod (3) Feedback Ring
13.
Carbon Block
14.
Propeller Thrust Bearing Cover Scavenge Oil Transfer Tube
9. 10. 11.
15.
PROPELLER GOVERNOR OVERSPEED CYCLE A.
6.
Figure
1.
5.
5.
to
overspeed condition, the rotating flyweights pivot outward, overcomethe speeder spring tension and raise the pilot valve plunger. This uncovers the ports in the drive gearshaft and dumps the oil from the propeller servo piston to the reduction gearbox sump. As the propeller blades increase in pitch angle, the load on the engine is increased with a consequent decrease in engine rpm. The centrifugal force exerted on the governor flyweights is reduced allowing the speeder spring tension to return the flyweights to a vertical position. The pilot valve plunger once again blocks the flow of control oil to or from the propeller servo piston mechanism. In
an
PROPELLER GOVERNOR UNDERSPEED CYCLE A.
With the propeller control lever set to the desired rpm, a condition of underspeed occurs when the propeller rpm drops below the predetermined setting. The speeder spring tension then overcomes the decreased centrifugal force on the flyweights and pivots them inward, forcing the pilot valve plunger downward and opening the ports. This directs a flow of pressure oil to the propeller servo piston which overcomes the combined forces of
propeller counterweights and return springs and decreases the pitch of the propeller blades. The load on the propeller is reduced with a consequent increase in propeller rpm. This is sensed by the governor flyweights, causing the pilot valve plunger to again be positioned to close the oil ports. the
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
PROPELLER OVERSPEED GOVERNOR A.
The propeller overspeed governor is installed in parallel with the propeller governor and is mounted at approximately the 10 o’clock position on the reduction gearbox front case. It is provided to control a power turbine/propeller overspeed condition by immediately dumping the oil from the propeller servo piston to the reduction gearbox sump (see Figure
1-11-1). The governor consists of conventional type flyweights mounted on a rotating splined shaft. The hollow shaft embodies ports which are normally closed by a pilot valve and held in this position by a speeder spring. The spring tension acts in opposition to the centrifugal force of the rotating flyweights. When a power turbine/propeller overspeed condition occurs, the increased centrifugal force sensed by the flyweights overcomes the spring tension, lifts the pilot valve and dumps the propeller servo piston oil back tothe reduction gearbox through the hollow splined shaft. This permits the combined forces of the counterweights and return springs to move the blades toward a coarse pitch position, absorbing the engine power and preventing further power turbine/propeller overspeed. hollow
8.
POWER TURBINE GOVERNOR A.
The power turbine governor is mounted on the top of a sandwich type tachometer-generator (Nf). The generator is mounted at approximately the 2 o’clock position on the reduction gearbox and driven by the propeller shaft through bevel gears. The power turbine governor is set to approximately 106% (Nf) speed for normal pitch operation. Should the propeller stick in such a way as to prevent the propeller governor from governing in the normal pitch range, the power turbine governor will act as a power turbine/propeller overspeed limiter by cutting back fuel flow in the event the propeller shaft overspeed reaches 106% (Nf).
B.
During reverse operation, the power turbine governor is progressively reset to approximately 95% (Nf) before the propeller reaches a negative pitch angle. This ensures that the engine power is limited to maintain a propeller rpm somewhat less than that of the propeller governor setting. The propeller governor will, therefore, always sense an underspeed condition and direct pressure oil to the propeller servo piston. The power turbine governor lever is connected by adjustable linkage to the reversing valve lever system
9.
PITCH REVERSING VALVE AND LINKAGE A.
The
pitch reversing valve consists of a plug type sleeve valve located in the propeller thrust bearing cover at the 6 o’clock position (see Figure 1-11-2). The reversing valve oil inlet passage is connected by an external oil transfer tube to an internal transfer tube the reduction gearbox. The dump side of the reversing valve is connected to the reduction gearbox through an externally mounted oil flow divider and pressure check valve. These ensure an adequate supply of oil to the power section bearings during en~ine on
The propeller reversing valve accommodates a pivoted reversing lever at its center. One end of the reversing lever is attached to a push-pull control wire rope which is interconnected through propeller control and cam follower levers to the FCU, then to the cockpit power control lever. The opposite end of the reversing lever is attached to and positioned by a carbon block located in the propeller feedback ring.
windmilling.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
10.
PROPELLER REVERSING INTERCONNECTING LINKAGE
A.
propeller reversing interconnecting linkage provides the correct relationship between engine power and propeller blade pitch during reversing operations. The system (see Figure 1-11-1) comprises three major parts: a control lever mounting bracket bolted to the accessory gearbox at flange G; a rear control lever, with a circumferential and radial cam slot (see Figure 1-11-3), mounted on a pivot in the mounting bracket, and a rear follower lever. The rear follower and rear control levers are interconnected by a follower pin which rides in the contoured cam slot, transmitting movement of either lever. The cockpit power control lever is connected directly to the attaching lug on the rear follower lever, or through the lever pivot pin which is splined and has a special extension to accommodate an airframe supplied type lever. Two lugs are provided on the control lever mounting bracket for use by the airframe manufacturer. These enable attachment of flexible cable supports and provide a terminal point for the static cable casing. A ball bearing ended interconnecting rod completes the linkage from the rear follower lever to the The
FCU control B.
arm.
reversing valve lever on the reduction push-pull wire rope. Swivel joint telescopic units are used at each end of the cable to allow for angular variations between the rear control lever and the reverse lever relative to the wire rope outer casing. The telescopic unit at the rear control lever end includes an adjustment to enable varying the effective wire rope length. The clevis end of the wire rope is attached to the rear control lever by using one of a number of holes provided to effect the desired pitch change rate. The telescopic unit at the reversing valve lever end includes a wire rope tensioning spring which eliminates and an adjustable stop to limit the forward travel of the reversing valve lever. The is set to ensure that the reversing valve is in a "null" position for normal stop operation The
rear
control lever is connected forward to the
gearbox by
a
,hsalkcabrelleporp
C.
propeller operation (from IDLE to TAKEOFF), the follower pin moves in portion of the cam slot, but imparts no motion through the rear control lever to the reversing lever. However, on selection of reverse pitch, the follower pin moves up the radial portion of the slot, rotating the rear control lever and transmitting this motion forward through the cable to the reversing lever. During
normal
the circumferential
11.
LOW PITCH CONTROL CYCLE A.
cockpit power control lever is normally placed in the IDLE position prior to engine lightup. At this point, the follower pin is at the intersection between the radial and circumferential ports on the cam slot. The feedback ring and therefore the propeller end of the reversing lever is fixed by stops and return springs to its maximum rearmost position. The wire rope clevis end of the reversing lever is positioned by the wire rope spring stop so that the reversing valve is shut off. Both the propeller and power turbine governors are set for maximum rpm (100% propeller rpm and 100% Nf) respectively.
The
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER CONTROL
CAM,
n o o O O
CAM SLOT
RADIAL SECTION
CIRCUMFERENTIAL SECTION
C1212
Propeller
Control Lever
Figure
Cam Slot
Terminology
1-11-3
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1-11-8
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
s.
12.
engine lights up and the rpm increases, the propeller governor senses an underspeed and directs pressure oil to the propeller servo piston to effect a pitch change. At an angle somewhat above the low pitch setting, the propeller servo piston will pick up the low pitch adjustment stops on the guide rods. The feedback ring moves axially fbrward transmitting this motion through the carbon block to the reversing lever. The reversing lever pivots on the wire rope clevis end which is presently static and gradually opens the reversing valve. Oil from the propeller is dumped through the flow divider to the reduction gearbox. The process continues until the amount of oil dumped by the valve equals the amount being supplied by the propeller governor, at which point there will be no further change in pitch and the propeller will be in low pitch. As the
HIGH PITCH CONTROL CYCLE A.
engine operating
and the
in low
pitch thigh rpm), the power control lever is advanced from IDLE to the TAKEOFF position. The movement transmitted through the wire rope moves the follower pin in the circumferential position of the cam With the
propeller
altering the position of the rear control lever. Movement of the rear follower simultaneously advances the FCU control lever to full power position (100% rpm). As the propeller governing speed is reached, the propeller govemor will dump pressure oil from the propeller to increase pitch and maintain speed. The feedback ring returns to a rearward position shutting off the reversing valve and the propeller will operate in the conventional manner. slot without lever
13.
REVERSE PITCH CONTROL CYCLE A.
To go into reverse pitch from the low pitch position, the power control ever is pulled back through a gate into the REVERSE position. This moves the follower pin up the radial portion of the cam slot, rotating the rear control lever and transmitting a pulling force to the wire rope against the tension spring. This moves´•the end of the reversing lever which pivots on the feedback ring end, partially closing the reversing valve and reducing the amount of oil being dumped to an amount less than that supplied by the propeller governor. Since this condition is one of underspeed, the propeller will move through low pitch into the negative pitch range as long as the reversing lever continues to move. As the propeller moves into low pitch, the feedback ring changes position in an attempt to open the reversing valve and prevent a further change in pitch. This cannot occur while the
B.
reverse
lever continues to be moved.
propeller reaches the full reverse pitch position, movement at the wire rope clevis reversing lever will cease. The reversing lever will have travelled only far enough to move the reversing valve to a "null" position at which point the oil flow into the propeller is equal to the flow out. The power turbine governor is simultaneously reset from 106% to 95% (Nf). This final setting leads the propeller and will be reached before the propeller attains full reverse pitch. Selection of reverse pitch also repositions the FCU control lever increasing fuel flow and consequently power output. The chosen relationship of engine power to propeller pitch depends largely on operating requirements. Should the relationship selected be such as to require 95% (Nf), the power turbine governor will limit the engine power according to the ability of the propeller to absorb the power at that speed. As the
end of the
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
14.
REVERSE TO LOW PITCH CONTROL CYCLE A.
The process of returning to low pitch from full reverse is exactly opposite to going into reverse pitch. As the power control lever is moved towards the low pitch gate, the reversing valve is opened past its "null" position, dumping more oil into the reduction gearbox than is being supplied by the propeller governor. As the propeller pitch moves out of the reverse pitch range, the fuel flow is progressively reduced and the power turbine governor reset to 106% (Nf). The full stabilized low pitch position is obtained when the amount of oil dumped by the reversing valve equals the quantity supplied by the
propeller governor.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1 SECTION 12
DESCRIPTION OF ENGINE
PROPELLER REVERSING INSTALLATION
(PT6A-6B 1.
2.
PT6A-20)
GENERAL A.
The PT6A-6B and PT6A-20
reversing propeller installation utilizes a single-acting hydraulic reversing propeller controlled by a propeller governor. An optional propeller overspeed governor may be provided to limit power turbine speed in the event of failure of the propeller governor. A power turbine governor controls propeller speed in the Beta range and will also limit propeller speed in the remote event of the propeller overspeeding.
B.
The
propeller combination has three cockpit controls: a fuel cut-off lever, a power control lever and a propeller control lever. The fuel cut-off lever has two positions. CUT-OFF and IDLE. An additional HI-IDLE position is provided on certain installations. This lever controls the cut-off function of the fuel control unit (FCU) and resets the power control lever Idle Stop to provide 50% minimum Ng in the IDLE position and up to a minimum of 80% Ng in the HI-IDLE position, where applicable. The Ng selected by the power control lever is a maximum value which is reached only if the power turbine governor does not act to reduce Ng below the selected value. The power control lever also selects low blade angle (Beta) and resets the power turbine governor from over propeller selected speed at full forward power to under propeller selected speed in the Beta range. The propeller control lever is connected to the propeller governor through linkage. Movement of the linkage determines and limits the rpm range of the propeller governor and so governs the propeller. When the control lever is moved to the minimum rpm position, the propeller will automatically feather. integrated engine
and
PROPELLER A.
engine is normally equipped with a three bladed metal propeller dowelled and bolted to the front face of the propeller shaft flange. The propeller consists of a hollow steel spider hub which supports three propeller blades and also houses an internal oil pilot tube and the feather retum springs (see Figure 1-12-1). Movement of the propeller blades is controlled by a hydraulic servo piston mounted on the front of the The
propeller spider hub. The servo piston is connected by a link to each of the blade trailing edge roots. Centrifugal counterweights on each blade and feathering springs in the servo piston tend to drive the servo piston into the feather, or high pitch position. This movement is opposed by the oil pressure generated and controlled by the propeller governor. The pressure oil is transferred to the servo piston via an oil transfer housing and the hollow center of the propeller shaft. An increase in the oil pressure moves the propeller blades toward the low pitch position (increased rpm). A decrease in the oil pressure allows the blades to move toward the high pitch position (decreased rpm) under the influence of the feathering springs and blade counterweights.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
SPEED ADJUSTING LEVER
PROPELLER OVERSPEED GOVERNOR
BETA CONTROL
PROPELLER GOVERNOR
GOVERNOR PUMP
ENGINE OIL SUPPLY
j
v
SPRING STOP
STOP RELIEF VALVE
OIL DUMP TO II REDUCTION II GEARBOX II
OIL DUMP TO REDUCTION GEARBOX
I’
COUNTERWEIGHT
REVERSE RETURN SPRINGS
LOW STOP COLLAR FEEDBACK RING
f
_
n
I
SERVO PISTON
ROTATION
J
PISTON SEAL
PROPELLER OIL TRANSFER HOUSING
LOW STOP ROD
(3 OFF)
FEATHER RETURN SPRINGS CARBON BLOCK
(PT6A-6B
and
C37B
-P0Engines)
Propeller Reversing Installation Figure 1;12-1
Schematic
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
s.
3.
by three spring-loaded sliding rods to a feedback propeller. Movement of the feedback ring is transmitted by carbon blocks through a propeller reversing lever and linkages to the propeller governor override rod. The lever functions as a link between the push-pull wire rope and the override rod in the propeller governor and also functions as a feedback link in the reverse pitch and low pitch selections. is also connected
The
servo
ring
mounted behind the
piston
PROPELLER GOVERNOR A.
propeller governor performs two functions. Under normal flight conditions it acts as speed governing unit (CSU) to regulate power turbine speed (Nf) by varying the propeller blade pitch to match the load torque to the engine torque in response to changing flight conditions. During low airspeed operations, the propeller governor can be used to select the required blade angle (Beta control); while in the Beta control range, engine power is adjusted by the FCU and the power turbine governor to maintain power turbine speed (Nf) at a speed slightly less than the selected rpm. The a
B.
constant
propeller governor consists of a single-acting centrifugal governor mounted at the position on the reduction gearbox front case (see Figure 1-12-2). The propeller governor function in forward thrust is to boost engine oil pressure to decrease propeller blade pitch, while the centrifugal force of the blade counterweights, assisted by feathering springs, tend to increase the pitch.
The
12 o’clock
C.
propeller governor includes an integral gear type oil pump with a pressure relief a pair of pivoted flyweights mounted on a rotating flyweight head, a spring-loaded and the necessary cored oil passages contained in the governor housing and valve ’pilot base. The rotating flyweights determine the position of the pilot valve while the spring load can be varied by an externally mounted propeller control lever. The
valve,
D.
In the event of a propeller control linkage failure, a spring attached to the propeller speed adjusting lever holds the lever in its last selected position or moves it toward the high speed setting. The high speed stop prevents the lever moving beyond the 100% position and enables the engine to be operated at or near full rated speed and develop maximum power. Moving the propeller speed adjusting lever against the low speed stop raises the pilot valve to a positive coarse pitch or feathering position regardless of flyweight force. This enables the pilot to feather the propeller and minimize propeller drag in the event of engine failure.
E.
propeller governor with a sensing element, the rotating pivoted flyweights are mechanically to the engine by a hollow drive gearshaft. The rotating flyweights, actuated by centrifugal force, position the pilot valve so as to cover or uncover oil ports in the drive gearshaft and regulate the oil flow to and from the propeller servo piston. The centrifugal force exerted by the flyweights is opposed by the force of the adjustable speeder spring. This determines the engine rpm required to develop sufficient centrifugal force on the flyweights to center the pilot valve, thereby preventing To
provide
the
linked
oil flow.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
HIGH SPEED ADJUSTMENT STOP
I
PROPELLER GOVERNOR CABLE TERMINAL
LOW PITCH STOP ADJUSTER
PROPELLER REVERSING LEVER
O
jiP"
INTERCONNECTING ROD PROPELLER GOVERNOR
PROPELLER OVERSPEED GOVERNORTEST SOLENOID
Od
PROPELLER OVERSPEED GOVERNOR
a
lp
FEEDBACK
~ING
C38A
Propeller Reversing
Installation
Figure
Reduction Gearbox
1-12-2
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PRATT
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
An override rod is located inside the hollow center of the
propeller governor pilot valve and is connected through a linkage to the propeller reversing lever. The rod is ineffective when the engine is in the constant speed range as the rotating flyweights hold the pilot valve clear of the rod. However, when the propeller is running at a speed lower than that selected
on the propeller control lever, the flyweights allow the pilot valve to drop, causing the blade angle to decrease. As the propeller blades approach the angle selected by the power control lever, the feedback ring repositions the propeller reversing lever to move the pilot valve, through the override rod, to an on-speed or null position and so
prevent further blade 4.
PROPELLER GOVERNOR ON-SPEED CYCLE A.
5.
During an on-speed condition in forward thrust the forces acting on the engine/propeller governor/propeller combination are in a state of balance. With the propeller control lever set to obtain the desired rpm and the propeller blades in the correct pitch range to absorb the power developed by the engine, the centrifugal force of the rotating flyweights balances the force of the speeder spring with the flyweights in the vertical position. This positions the pilot valve plunger so that the ports which control the oil flow from the governor pump to the propeller servo piston are closed. The oil pressure is therefore diverted through the relief valve, back to the inlet side of the governor pump.
PROPELLER GOVERNOR OVERSPEED CYCLE A.
6.
movement.
In
overspeed condition, the rotating flyweights pivot outward, overcome the speeder spring tension and raise the pilot valve. This uncovers the ports in the drive gearshaft and dumps the oil from the propeller servo piston to the reduction gearbox sump. As the propeller blades increase in pitch angle, the load on the engine is increased with a consequent decrease in engine rpm. The centrifugal force exerted on the propeller governor flyweights is reduced allowing the~ speeder spring tension to return the flyweights to a vertical position. The pilot valve once again blocks the flow of control oil to or from the propeller servo piston. an
PROPELLER GOVERNOR UNDERSPEED CYCLE A.
With the propeller control lever set to the desired rpm, a condition of underspeed when the engine rpm drops below the predetermined setting. The speeder spring tension then
overcomes
the decreased
centrifugal
force
on
the
flyweights
and
occurs
pivots
them inward, forcing the pilot valve downward and opening the ports. This directs a flow of pressure oil to the propeller servo piston which overcomes the combined forces of the propeller counterweights and return springs and decreases the pitch of the propeller
blades. The load on the engine is reduced with a consequent increase in engine rpm. This is sensed by the propeller governor flyweights, which cause the pilot valve plunger to again be positioned to close the oil ports.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
PROPELLER OVERSPEED GOVERNOR A.
The
propeller overspeed governor is installed in parallel with the propeller governor and is mounted at approximately the 10 o’clock position on the reduction gearbox front case. It is provided to control any power turbine/propeller overspeed condition by immediately
the oil from the propeller servo piston to the reduction gearbox (see Figures 1-12-2). The propeller overspeed governor consists of conventional type flyweights mounted on a rotating hollow-splined shaft. The hollow shaft embodies ports which are normally closed by a pilot valve and held in this position by a speeder spring. The spring tension acts in opposition to the centrifugal force of the rotating
bypassing
1-12-1 and
flyweights. When an engine overspeed condition occurs, the increased centrifugal force sensed by the flyweights overcomes the spring tension, lifts the pilot valve and bypasses the propeller servo piston oil back to the reduction gearbox through the hollow splined shaft. This permits the combined forces of the counterweights and return springs to move the blades toward a coarse pitch position, absorbing the engine power and preventing further engine overspeed. A ground test solenoid valve in the governor is provided to permit testing the unit. The valve resets the governor to approximately 10% below its normal overspeed setting. 8.
POWER TURBINE GOVERNOR A.
The power turbine governor is mounted on the top of a sandwich type The generator is mounted at approximately the 2 o’clock tachometer-generator.(Nf). the reduction position on gearbox and is driven by the propeller shaft through bevel gears
(see Figure 1-12-3). The power turbine governor is set to approximately 106% (Nf) speed for normal pitch operation. Should the propeller stick in such a way as to prevent the propeller governor from governing in the normal pitch range, the power turbine governor will act as an overspeed limiter by bleeding FCU control air, thereby reducing the fuel flow to limit the power and so govern the propeller shaft speed. B.
The power turbine governor is progressively reset to below 100% Nf as the propeller control cam is pulled back into the Beta range, i.e. below the 90% position of the power control lever. If Nf exceeds the setting of the power turbine governor, the governor will reduce the fuel flow, through the FCU, and so reduce engine power by reduction of Ng. The power turbine governor can reduce Ng to a minimum of 50%. If with Ng at 50%, Nf still exceeds the governor setting, the propeller reverts to a constant-speed condition controlled by the propeller governor. This will occur under high airspeed conditions and under these conditions Beta control and reverse pitch selection are not
possible. 9.
FUEL CUT-OFF LEVER A.
The cockpit fuel cut-off lever is connected through a combined lever and stop on the top of the FCU to the cut-off valve lever. The lever and stop also function as an idle stop for the FCU control rod. With the cockpit fuel cut-off lever in the IDLE position, the FCU control rod stop is set to the 50% Ng position while with the cockpit fuel cut-off lever in the HI-IDLE position, (where applicable) the FCU control rod stop is reset to the 80% Ng position.
Page
1-12-6
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
PROPELLER CONTROL CAM( 1
NON-STOL CAM SLOT CONFIGURATION
)REAR FORK END
2
3 )LOCKNUT o
REAR WIRE ROPE TERMINAL
4
o
)CLAMPING BOLT
CLAMPING
OPICTUP~TING
BOLT(38) ,COUNTERWEIGHT
LEVER SUPWRT P~RM
POWER TURBINE GOVERNOR INTERCONNECT ROD (UPPER)
39
HARTZELL PROPELLER HC-B3TN-3 (IN FEATHERED POSITION)
PROPELLER GOVERNOR STOP
90"f1"
5
TAKE-OFF POSITION
IDLE DEADBAND ADJUSTING BOLT
IDLE POSITION
OPdoPELLERsPEEosELEET
REVERSE POSITION
I
24)FRONT FORK END!
ROD END PROPELLERRING, O
To COCKPIT CONTROLLEVER
SERVO PISTON
PROPELLER GOVERNOR IRM
(NON-STOL APPLICATION)
OPROPELLER
GOYERNMI
FEATHER RETURN SPRINGS
FRONT LIFTING BRACKET
O
DIM.Z
31
~FCU OPROPELLW ~CIM
FRONT SWIVEL JOINT
5WIYELJ~INT
*CTU~ITING LEYER
SPRING RETAINER CUP
25
26
MLUhllER LEYER
DETAIL
YA
PITCH STOP ADJUSTER
CONTROL CfiM
A
rC
SPRING STOP DIM. X------~
PROPELLER CONSTANT 21 )SPEED CONTROL UNIT STOP
WIRE ROPE CASING
HIGH PITCH AND FEATHER
PROPELLER GOVERNOR~ ACTUATING LEVER
LOW-STOP ROD
SPRING, REVERSE RETURN
POWER TURBINE GOVERNOR LINE
33 R
~aoJusnao
PUSH-PULL WIRE ROPE
SPPICER
PROPELLER FEEDBACK RING
40 )POWER TURBINE GOVERNOR MAXIMUM STOP
42)POWER
O
15
43
mRBINE GOVERNOR INTERCONNECT RW
(LOWERJ
POWER TURBINE GOVERNOR LEVER
POWER TURBINE GOVERNOR LINE (Py)
32)LOCK-BOLT
CAM FOLLOWER PIN
FCU REVERSING LEVER
14
PROPELLER REVERSING LEVER (CARBON BLOCKS (25) NOT SHOWN)
41 )pOWER TURBINE GOVERNOR ARM
r~carPnPowEa CONTROL LEIIER
STOL CAM SLOT CONFIGURATION
LOW PITCH AND REVERSE
16
FCU INTERCONNECT ROD
FRONT LIFTING 20 BRACKET
CENTER FIRESEAL
POWER CONTROL LEVER
LOW-PITCH ADJUSTER STOP
D
REAR FIRESEAL
13 )Ne
28
Mnx. STOP
44
12 )FCU
FUEL CONTROL UNIT (FCU)
~j)
ARM EXTENSION
FCU CONTROL nRM
DETAIL
10 )CUT-OFF VALVE LEVER
(PT6A-6B
Engine
and -20
Controls and
Figure
C1849A
Engines)
Reversing
C
POST-SB298
Installation
1-12-3
Page
1-12-7/8
Feb 01/2002
LOCKNUT
RETAINING PLATE
DETAIL
B
34) SPRING
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
10
POWER CONTROL LEVER
cockpit power control lever controls engine power through the full range from maximum Take-off power through to Full Reverse. It also selects the propeller pitch (Beta control) from the reverse selection up to the constant speed rpm as selected by the cockpit propeller control lever (Se;e Figure 1-12-3)
A.
The
B.
cam assembly, secured to the accessory gearbox is the connecting point for the cockpit power control lever and provides scheduled control movements to the FCU, power turbine governor and the low blade angle selection system. The cam assembly consists of an input lever, which is connected through a shaft to a cam follower assembly, and three cam type levers. The FCU reversing lever is free-mounted on the input lever shaft while the propeller control cam and FCU actuating lever are free-mounted on a second shaft. The FCU actuating lever is spring-loaded toward idle and is connected through an adjustable control rod to the FCU control arm. In operation, movement of the cockpit power control lever rotates the cam follower. The cam follower pin contacts one face of the FCU actuating lever and slides in the slotted propeller control cam.
C.
The
A
propeller control cam is coupled through a push-pull wire rope to the~ upper end of propeller reversing lever. The mid-point of the reversing lever is connected through linkage to the propeller governor interconnect rod. The upper end of the lever is also coupled through two adjustable control rods and a lever to the power turbine governor.
the
D.
a
When the upper end of the reversing lever is moved by the push-pull wire rope, both the power turbine governor and the propeller low blade angle selection mechanism are reset. If the propeller rpm is below constant speed rpm, movement of the reversing lever the propeller governor to change the propeller pitch. The resulting movement propeller feedback ring moves the lower end of the lever to return the propeller governor to a null position and prevent further blade movement when the selected blade angle is reached. causes
of the
E.
In the Beta control range, movement of the power control lever from IDLE up to the 90% position will select increasing propeller blade pitch angles. Movement of the lever from IDLE to REVERSE will select decreasing propeller pitch
approximately angles F
until the ~full
reverse
pitch
is obtained.
The FCU control arm is positioned by the cockpit power control lever through the cam follower and in the reverse selection through the FCU reversing lever. In the IDLE
position (see Figure 1-12-3), the cam follower pin is contacted by the adjuster on the FCU reversing lever and by the FCU actuating lever. When the power control lever is pushed toward the TAKEOFF position, the cam follower pin pushes the FCU actuating lever forward against the action of the spring and moves the FCU control arm until the required power is selected. In the TAKEOFF position, the controls will be in the positions shown (see Figure 1-12-3). G.
Moving the power control lever back from the IDLE to the REVERSE position, the cam follower pin contacts the adjuster on the FCU reversing lever and rotates the lever. The lug at the bottom of the FCU reversing lever contacts the underside of the FCU actuating lever, lifting it clear of the cam follower pin and rotating it toward the TAKEOFF position. When the power control lever is in the full REVERSE selection, the FCU actuating lever will be in the Takeoff position. (See Figure 1-12-3).
Page
1-12-9
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
11.
NON-STOL APPLICATIONS A.
The installation of Non-Stot applications is identical to the Stol reversing propeller installation except that a special propeller cam is used. This cam has a different curved slot configuration for the Lo-idle position up to the Take-Off position of the power control lever travel (refer to Figure 1-12-3 for a detail of the Non-Stol cam). The reverse position of the propeller control cam is the same as that for Stol applications except that the beta range of the Stol
application is limited to that part of the control range from Lo-ldle cockpit power control lever from Idle to Take-Off position, direct effect upon propeller pitch.
to Reverse. Movement of the
therefore, has B.
no
Reduced idle power may be obtained by selecting below idle at which point a 12" dead band allows selection of a flat, fine low without increasing the FCU power lever travel.
Page
1-12-10
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 1
SECTION 13
DESCRIPTION OF ENGINE
PROPELLER REVERSING INSTALLATION
(PT6A-20A 1.
AND PT6A-20B
ENGINES)
GENERAL A.
engine reversing propeller installation consists of a single-acting hydraulic propeller by a propeller governor, combining the functions of a normal propeller governor (CSU), a reversing valve and a power turbine governor (Nf).
The
controlled
B.
and propeller combination has three cockpit controls: a fuel cut-off power control lever and a propeller control lever. The fuel cut-off lever has two positions: CUT-OFF and IDLE. An additional HI-IDLE position is provided on certain installations. This lever controls the cut-off function of the fuel control unit (FCU) and resets the power control lever Idle Stop to provide 50% minimum Ng in the IDLE position and up to a minimum of 80% Ng in the HI-IDLE position, where applicable. The Ng selected by the power control lever is a maximum value which is reached only if the power turbine governor section of the propeller governor does not act to reduce Ng speed below the selected value. The power control lever also selects low blade angle (Beta) and resets the power turbine governor section of the propeller governor from over propeller selected speed at full forward power to under propeller selected speed in the Beta range. The propeller control lever is connected to the propeller governor through linkage. Movement of the linkage determines and limits the rpm range of the propeller governor and so governs the propeller. When the control lever is moved to the minimum rpm position, the propeller will automatically feather.
The
integrated engine
lever,
2.
a
PROPELLER A.
The
engine is normally equipped witha three bladed metal propeller dowelled and bolted to the front face of the propeller shaft flange. The propeller consists of a hollow steel spider hub which supports three propeller blades and also houses an internal oil pilot tube and the feather return springs (see Figure 1-13-1). Movement of the propeller blades is controlled by a hydraulic servo piston mounted on the front of the propeller spider hub. The servo piston is connected by a link to each of the blade trailing edge roots. Centrifugal counterweights on each blade and feathering springs in the servo piston tend to drive the servo piston into the feather, or high pitch position. This movement is opposed by the oil pressure generated and controlled by the propeller governor. The pressure oil is transferred to the servo piston via an oil transfer housing and the hollow center of the propeller shaft. An increase in the oil pressure moves the propeller blades toward the low pitch position (increased rpm). A decrease in the oil pressure allows the blades to move toward the high pitch position (decreased rpm) under the influence of the feathering springs and blade counterweights.
B.
The
servo piston is also connected by three spring-loaded sliding rods to a feedback mounted behind the propeller. Movement of the feedback ring is transmitted by a carbon block through the propeller reversing lever and thence to the Beta valve. This motion is used to control blade angle from normal forward fine pitch stop to full reverse blade angle. The motion is available only from approximately 20 degrees positive to 20 degrees reverse blade angle.
ring
Page 1-13-1/2 Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
STOL CAM
r PUSH-PULL CONTROL
l~j)
7
o
o
SPEED ADJUSTING LEVER O
o
SPEEDER SPRING FCU ARM
r PILOTVALVE
PY~
n
RESET POST BETA CONTROL VALVE AIR BLEED LINK
_
MINIMUM GOVERNING ADJUSTMENT
RETURN TO PUMP
TO SUMP PITCH LOCK SOLENOID VALVE
I
FROM PUMP
I I TEST SOLENOID
PROPELLER OVERSPEED GOVERNOR
ii:
J
PITCH LOCK SOLENOID ACTUATING SWITCH
and -208
C1353
Engines)
Propeller Reversing Installation Figure 1-13-1
Schematic
Page
HYDRAULIC LOW PITCH ADJUSTMENT
COUNTERWEIGHT
TO SUMP
(PT6A-20
1
BETA ROD
1-13-314
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
If
3.
PROPELLERGOVERNOR A.
propeller governor performs three functions. Under normal flight conditions it acts constant speed governing (CSU), maintaining the propeller speed selected by the pilot by varying the propeller blade pitch to match the load to the engine torque in response to changing flight conditions. During low airspeed operations, the propeller governor can be used to select the required blade angle (Beta control); while in the Beta control range, engine power is adjusted by the FCU and the power turbine section of the propeller governor to maintain power turbine speed (Nf) at slightly less than the selected rpm. The
as a
propeller governor is a single-acting centrifugal type mounted at thel2 o’clock position on the reduction gearbox front case (see Figure 1-13-2). in forward thrust operation, the function of the propeller govemor is to boost engine pressure oil to decrease propeller blade pitch, while the centrifugal force of the blade counterweights, assisted by feathering spring, tends to increase the pitch.
B.
The
C.
The
D.
A maximum
propeller governor consists of an integral gear type oil pump with a pressure relief valve, two pivoted flyweights mounted on a rotating flyweight head, a spring loaded pilot valve and necessary cored passages contained in an aluminum housing. The flyweight head is attached to a hollow drive shaft which protrudes below the housing flange. The shaft is externally splined to mate with the corresponding coupling shaft in the reduction gearbox. The spring loaded pilot valve is installed in the drive shaft centerbore. Ports in the drive shaft and the position of the pilot valve control the direction of oil flow within the housing. The rotating shaft speed and hence rotating flyweight determine the position of the pilot valve, while the opposing spring load on the valve is varied by the speed adjusting lever at top of the governor. The speed adjusting lever is connected through airframe linkage to the propeller control lever in the cockpit. stop prevents the speed adjusting
lever
moving beyond
100%
position
and
enables the propeller to be operating at or near, full rated speed, and the engine to develop maximum power. Movement of the adjusting lever towards the minimum preset (feathering) stop, raises the pilot valve and decreases oil pressure to propeller servo piston. This decrease in pressure allows the propeller piston to move under the influence of the
feathering
return
springs
and blade
counterweights,
to rotate the
propeller
blades to a positive coarse pitch or feathering position, regardless of governor flyweight force acting on the pilot valve. This enables the pilot to feather the propeller and minimize drag in the event of engine failure. E.
In the event of a malfunction in the linkage of the propeller control ever, a spring attached to the speed adjusting lever holds the lever in its last selected position or it against the maximum stop.
moves
Page 1-13-5/6 Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER CONTROL CAM
1)(2)REARFORKEND NON-STOL CAM SLOT CONFIGURATION
3
LOCKNUT
O
REARWIRE
ROPE RERMINAL
SPEED ADJUSTING LEVER
TO COCKPIT PROPELLER CONTROL LEVER
O
O
24 )FRONT FORK 4 )CLAMPING
/h~\P_
EXTENSION SPRING
BOLT
900~10
IDLE POSITION
CAM FOLLOWER LEVER
(NON-STOL APPLICATION)
REVERSE POSITION
TAKE-OFF POSITION
COUPLING WIRE ROPE CASIIIG
NUT( 40
(43~
~WIRE ROPE(46
LEVER( 6
‘r\
2
PROPELLER GOVERNOR AIR
18
CAM FOLLOWER LEVER
DETAIL
PROPELLER GOVERNOR INTERCONNECT ROD
9
PUSH-PULL WIRE ROPE
HI-IDLE
P~-´•
7
FOLLOWER PIN
15
25
r
47)\(36)
(38
26~
j
SPRING( 34
P~t
U\
301
IT.
Y~MAX.STOP
FUELCONTROL UNIT (FCU)
12 )FCU
39
48
)Ns
FRONTWIRE ROPE TERMINAL
SELF-LOCKING
FIRESEAL
24
39
36
MAX. STOP
33
32
MAx. STOP
ARM EXTENSION
1
\~c(33)
32
LOCKBOLT
41 GOVERNOR AIR BLEED
LINK( 35
(REF.) PROPELLER GOVERNOR( INTERCONNECTROD
26 PT6A-20A PUSH-PULL CONTROL RODARRANGEMENT
41
I
26 PT6A-20B PUSH-PULL CONTROL ROD ARRANGEMENT (TELESCOPIC UNIT)
Engine
BETA VALVE CLEVIS
CARBON BLOCK
10 )CUT-OFF VALVE
PT6A-20A and -208 Controls and
Figure
C1850B
Engines)
Reversing
Installation
1-13-2
Page
BOLT
PROPELLER REVERSING LEVER
l+p~
~tlpy
11 )FCU CONTROL ARM
31
FRONT FORK NED
REAR FIRESEAL
(i 4) FCU INTERCONNECT ROD 13
(26
LOCKNUT( 30
FRONT SWIVEL JOINT
24)
ADJUSTER STOP
NUT
INSULATION GASKET
/’i~
PROPELLER GOVERNOR INTERCONNECT ROD
38
LOW PITCH
LOCKNUT( 28
42)SELF-LOCKING
LEVER45m
FCU REVERSING LEVER
COMPRESSOR SPRING
PROPELLER FEEDB9~CI( RING
CLAMP
II
(16)POWER CqN]TqOL
CASTELLATED NUT
27
LOW PITCH STOP ADJUSTER
19 )LOCKNUT
COCKPIT POWER CONTROL LEVER
17
TELESCOPIC TERMINAL HOUSING
LOW STOP ROD
44)BRACKET
40
8
A
POST-SB298
2
SPRING, REVERSE RETURN
26
0
ADJUSTING SPACER
HIGH PITCH AND FEATHER i
CASING
1
PROPELLER CONTROL CAM
LOW PITCH AND REVERSE
WIRE ROPE
PRESSURETUBE(Py)
37) RETAINING PLATE
(25) LOW PITCH STOP ALUUSTER
REARSWIVEL JOINT
/’SPRINGRETAINERCUP
A
"i~
_>
o
REAR FORK END
FEATHER RETURN SPRINGS
i
i’
FRONT LIFTING BRACKET
SERVO PISTON
~:PI
D
FCU ACTUATING
PROPELLER-TYPICAL FEATHERED POSITION)
END~/’n"
I iC
LZ~g
20
FRONT LIFTING BRACKET
(088. ONLY)
RING,RODEND
21
SETTING MAX. STOP
~I
5 IDLE DEADBAND ADJUSTING BOLT
22
PROPELLER GOVERNOR
PROPELLER CUTAWAY
COUNTERWEIGHT
1-13-718
Feb 01/2002
iI
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
F.
The Beta valve, incorporated in the
valve, and mechanically connected
propeller governor pump output line to the pilot propeller reversing lever, is designed so will initially block off high pressure oil to the propeller
to the
that forward movement of the valve sewo piston; as forward movement continues, pressure oil in the
servo
will be
dumped
back to the reduction gearbox. Axial movement in reverse direction has no effect on normal propeller control. When the propeller is rotating at a speed lower than selected by the speed adjusting lever, the governor oil pump provides pressure oil to the
piston thereby producing finer propeller pitch, until the feedback ring pulls back the Beta valve to block off pressure oil to the servo piston, thus preventing further pitch change. The pitch angle will coarsen automatically to maintain selected propeller speed as higher engine power is selected. The Beta control does not forcibly select reverse blade angles and very fine pitch, reverse can only occur when conditions are such that the propeller is underspeeding relative to that selected. servo
G.
On
some installations, a lock pitch solenoid is mounted at the front of the propeller governor and connected by cored passages to the pump oil pressure line to the servo piston. The solenoid is energized automatically by a microswitch through movement of the feedback ring, at a predetermined propeller blade angle. When the solenoid is energized the valve will close to block oil flow to the servo piston; this action will lock oil in the piston chamber and prevent any further movement of blades. However, if the engine power lever is moved into the reverse position, a secondary microswitch installed
in the power lever quadrant, will deenergize the solenoid valve actuating switch, opening the valve. This enables the propeller governor, power turbine section, to return to its
valve H
governing role. operation.
A test switch is
incorporated
in the
system
to
functionally
test
To
provide the governor with a sensing element, the rotating pivoted flyweights are mechanically coupled to the engine by a hollow drive shaft and accessory drive shaft in the reduction gearbox. The flyweights, actuated by centrifugal force, position the pilot valve so as to cover or uncover ports in the drive gearshaft and regulate oil flow to and from the servo piston. The centrifugal force exerted by the flyweights is opposed by the force of the speeder spring, this determines the engine rpm required to develop sufficient centrifugal force on the flyweights to center the pilot valve, thereby preventing oil flow to the servo piston.
Page 1-13-9 Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
i.
during normal forward thrust possible power turbine overspeed in the event of a propeller governor failure. During reverse thrust operation, the propeller govemor power turbine section is set below the propeller governor selected speed. This acts to control propeller speed via the FCU servo system (Py), and thus reduce the power supplied by the gas generator to below that required to maintain approximately 5% less than the selected propeller speed. A yoked bellcrank, operating off the flyweight head, opens a pneumatic orifice as speed is increased. The orifice is -connected to the pneumatic servo system of the FCU and opening of the orifice reduces fuel metered to the engine. The speed at which the propeller governor power turbine section operates is dependent on the speed selected on the governor and the position of the air bleed link. This link is normally set so that the propeller governor power turbine section will control Nf at approximately 6% higher than the selected speed in its maximum position and approximately 4% lower in its minimum position. The propeller governor power turbine section "droop" is approximately 4%, thus in maximum position, the governor will commence governing at 102% and fully govern at 106%. It should be noted that repositioning the air bleed link to its minimum position brings the yoke into contact with the pilot valve and brings in a spring load in addition to the speeder spring which the flyweights must overcome to control propeller speed. This effect causes propeller governed speed to increase to about 1% higher than nominally selected. The function of the
operation, is
4.
to
propeller
governor Nf section,
protect the engine against
a
PROPELLER GOVERNOR ON-SPEED CYCLE A.
condition in forward thrust, the forces acting on the engine, and propeller governor propeller combination are in a state of balance. With the propeller set to obtain the desired rpm and the propeller blades in the lever speed adjusting absorb to the power developed by the engine, the centrifugal force of correct pitch range the rotating flyweights balances the force of the speeder spring with the flyweights in the vertical position. This positions the pilot valve plunger so that the ports which control the oil flow from the governor pump to the propeller servo piston are closed. The oil pressure is therefore diverted through the relief valve, back to the inlet side of the governor
During
an
on-speed
pump. 5.
PROPELLER GOVERNOR OVERSPEED CYCLE A.
In an overspeed condition, the rotating flyweights pivot outward, overcome the speeder spring tension and raise the pilot valve. This uncovers the ports in the drive gearshaft and dumps the oil from the propeller servo piston to the reduction gearbox sump. As the propeller blades increase in pitch angle, the load on the engine is increased with a consequent decrease in engine rpm. The centrifugal force exerted on the governor flyweights is reduced allowing the speeder spring tension to return the flyweights to a vertical position. The pilot valve once again blocks the flow of control oil to or from the propeller servo piston.
Page
1-13-10
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
6.
PROPELLER GOVERNOR UNDERSPEED CYCLE A.
propeller speed adjusting lever set to the desired rpm, a condition of underspeed when the engine rpm drops below the predetermined setting. The speeder spring tension then overcomes the decreased centrifugal force on the flyweights and pivots them inward, forcing the pilot valve downward and opening the ports. This directs a flow With the occurs
of pressure oil to the propeller servo piston which overcomes the combined forces of the propeller counterweights and return springs and decreases the pitch of the propeller blades. The load on the engine is reduced with a consequent increase in engine rpm. This is sensed
positioned 7.
the governor
flyweights,
which
cause
the
pilot
valve
plunger to again
be
port.
PROPELLER OVERSPEED GOVERNOR A.
8.
by
to close the oil
The propeller overspeed governor is installed in parallel with the propeller governor and is mounted at approximately the 10 o’clock position on the reduction gearbox front case. It is provided to control any propeller overspeed condition by immediately bypassing the oil from the propeller servo piston to the reduction gearbox (see Figure 1-13-1). The propeller overspeed governor consists of conventiona!type flyweights mounted on a rotating hollow splined shaft. The hollow shaft embodies ports which are normally closed by a pilot valve and held in this position by a speeder spring. The spring tension acts in opposition to the centrifugal force of the rotating flyweights. When an engine overspeed condition occurs, the increased centrifugal force sensed by the flyweights overcomes the spring tension, lifts the pilot valve and bypasses the propeller servo piston oil back to the reduction gearbox through the hollow splined shaft. This permits the combined forces of the counterweights and return springs to move the blades toward a coarse pitch position, absorbing the engine power and preventing further engine overspeed. A solenoid valve, which resets the governor to a value below its normal overspeed setting, is provided to permit ground testing of the unit.
NON-STOL APPLICATIONS A.
The installation for Non-Stol applications is identical to the Stol reversing propeller installation except that a special propeller cam is used. This cam has a different curved slot configuration for the Low-idle position up to the Take-Off position of the power control lever travel (refer to Figure 1-13-2 for a detail of the Non-Stot cam). The reversing position
of the propeller control cam is the same as that for Stol applications except that the Beta range of the Stol application is limited to that part of the control range from Lo-ldle to Reverse. Movement of the cockpit power control lever from Lo-ldle to Take-Off position, therefore, has no direct effect upon propeller pitch. B.
Reduced idle power may be obtained by selecting below idle at which point a 12" dead band allows selection of a flat, fine low without increasing the FCU power lever travel.
Page
1-13-11/12
Feb 01/2002
_
PA RT
GEN RA L PROCEDURES
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
PAGE
SUBJECT PART 2 SECTION 1 1.
2.
3.
4.
5.
6.
GENERAL PROCEDURES
ENGINE OIL SYSTEM SERVICING
LUBRICATING OIL
2-1-1
A.
General
2-1-1
B.
CHANGE OF OIL BRAND
2-1-1
OIL LEVEL CHECK
2-1-2
A.
General
2-1-2
B.
Procedure
2-1-2
OIL SYSTEM DRAINAGE
2-1-2
A.
2-1-2
Procedure
OIL SYSTEM FILLING
2-1-3
A.
2-1-3
Procedure
OIL SYSTEM FLUSHING
2-1-5
A.
General
2-1-5
B.
Procedure
2-1-5
PATCH MAKING PROCEDURE
2-1-6
A.
2-1-6
Procedure
SECTION 2
PREPARATION FOR SERVICE OR STORAGE
INTRODUCTION 1.
GENERAL
2-2-1
2.
HUMIDITY CONTROL
2-2-1
3.
REACTIVATION OF DESSICANT
2-2-1
A.
2-2-1
Procedure
4.
STORAGE OF ENGINE
2-2-2
5.
STACKING FOR STORAGE
2-2-3
PART2 CONTENTS
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TABLE OF CONTENTS
PAGE
SUBJECT SECTION 2
PREPARATION FOR SERVICE OR STORAGE
(Cont’d)
REMOVAVINSTALLATION 6.
7.
8.
GENERAL A.
Precautions
2-2-3
B.
Types
2-2-4
11.
A.
2-2-4
13.
Procedure
REMOVAL OF ENGINE FROM FIBERBOARD CONTAINER TYPE PK562
2-2-5
Procedure
2-2-5
REMOVAL OF ENGINE FROM FIBERBOARD CONTAINER TYPE PK1325
2-2-7
Procedure
2-2-7
INSTALLATION OF ENGINE IN METAL CONTAINER
2-2-9
A.
General
2-2-9
B.
Procedure
2-2-9
PREPARATION OF FIBERBOARD CONTAINER A.
12.
Engine Slings
2-2-4
A. 10.
Of
REMOVAL OF ENGINE FROM METAL CONTAINER
A. 9.
2-2-3
TYPE PK562
2-2-12
Procedure
2-2-12
INSTALLATION OF ENGINE IN FIBERBOARD CONTAINER TYPE PK562
2-2-13
A.
General
2-2-13
B.
Procedure
2-2-13
INSTALLATION OF ENGINE- IN FIBERBOARD CONTAINER TYPE PK1325 (PT6A-6/C20, -20, -20A and -208 ENGINES
ONLY)
2-2-14
A.
General
2-2-14
B.
Procedure
2-2-14
PART2 CONTENTS
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TABLE OF CONTENTS
SUBJECT SECTION 2
PAGE PREPARATION FOR SERVICE OR STORAGE
(Cont’d)
ENGINE PRESERVATION/DEPRESERVATION 14.
GENERAL B.
15.
17.
2-2-17
Procedure
2-2-17 2-2-17
A.
2-2-17
Procedure
ENGINE FUEL SYSTEM PRESERVATION
2-2-18
Procedure
2-2-18
ENGINE DEPRESERVATION SCHEDULE A.
19.
2-2-16
ENGINE OIL SYSTEM PRESERVATION
A.
18.
Fuel Control Unit
ENGINE PRESERVATION SCHEDULE A.
16.
2-2-16
2-2-19
Procedure
2-2-19
ENGINE DEPRESERVATION
2-2-20
A.
2-2-20
Procedure
SECTION 3
CLEANING
INTRODUCTION 1.
GENERAL
2-3-1
SPECIFIC PARTS 2.
FUEL AND OIL TUBES
3.
OIL FILTER ELEMENT A.
Conventional
B.
Electrosonic
2-3-1
(Post-SB1118 ENGINES)
Cleaning Cleaning
2-3-1
Procedure
2-3-1
Procedure
2-3-2
4.
AIR INLET SCREEN
2-3-2
5.
GLOW PLUGS
2-3-4
A.
(Pre-SB1429)
Cleaning
2-3-4
PART2 CONTENTS
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TABLE OF CONTENTS
PAGE
SUBJECT SECTION 3 6.
SPARK IGNITERS A.
7.
8.
11.
2-3-4
(Post-SB1429)
2-3-4
Cleaning
2-3-4
2-3-5
Cleaning
2-3-5 2-3-8
Cleaning
2-3-8
COMPRESSOR BLEED VALVE
2-3-8
A.
2-3-8
Cleaning
CHIP DETECTOR
2-3-10
Cleaning
2-3-10
A. 12.
Cleaning
FUEL PUMP INLET SCREEN A.
10.
2-3-4
FUELMANIFOLD ADAPTER ASSEMBLIES A.
9.
(Post-SB1429)
IGNITION EXCITER A.
(Cont’d)
CLEANING
P3 FILTER ELEMENT
(Post-SB1294)
A.
Conventional
B.
Electrosonic Cleaning Procedure
Cleaning
2-3-10
Procedure
2-3-10
2-3-10
FIELD CLEANING 13.
14.
GENERAL K.
Minimizing
L.
Borescope Inspection
16.
Attack
2-3-13 2-3-13
INTERNAL WASH A.
15.
2-3-12
2-3-14
General
2-3-14
INTERNAL WASH METHODS
2-3-14
A.
2-3-14
General
RECOMMENDED WASH SCHEDULE
PART2 CONTENTS
2-3-17
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TABLE OF CONTENTS
SUBJECT SECTION 3 17.
18.
PAGE CLEANING
(Cont’d)
EQUIPMENT REQUIRED
2-3-18
A.
2-3-18
General
PREPARATION OF SOLUTIONS
2-3-22
INTERNAL WASHES 19.
20.
ENGINE MOTORING WASH
2-3-22
A.
2-3-22
COMPRESSOR TURBINE DESALINATION WASH A.
21.
22.
Procedure
2-3-25
Procedure
2-3-25
PERFORMANCE RECOVERY WASH
2-3-28
A.
2-3-28
Procedure
ENGINE RUNNING WASH A.
2-3-29
Procedure
2-3-29
FUEL NOZZLE CLEANING 23.
Preparation
and
Cleaning
2-3-30
A.
Equipment
2-3-30
B.
Preparation
2-3-30
C.
Cleaning
2-3-31
D.
Post-cleaning
2-3-32
ENGINE EXTERNAL WASH 24.
General
SECTION 4
2-3-32
STANDARD PRACTICES
1,
GENERAL
2-4-1
2.
PREFORMED PACKINGS, PACKING RETAINERS AND GASKETS
2-4-1
3.
LUBRICATION OF PREFORMED PACKINGS
2-4-2
A.
2-4-2
Procedure
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TABLE OF CONTENTS SUBJECT
FAG E
SECTION 4 4.
STANDARD PRACTICES
(Cont’d)
ANTIGALLING AND ANTISEIZE COMPOUNDS
2-4-2
A.
2-4-2
Procedure
5.
LOCKING DEVICES
6.
KEYWASHERS A.
2-4-3
(TAB
AND CUP
TYPES)
2-4-3
Procedure
2-4-3
7.
RETAINING RINGS
8.
LOCKWIRE
2-4-5
9.
LOCKING PROCEDURES
2-4-5
HARDWARE IDENTIFICATION
2-4-6
10.
METAL PARTICLES
(SPIROLOX, ETC.)
2-4-5
IDENTIFICATION
11.
GENERAL
2-4-12
12.
PRE-REQUISITES
2-4-12
A.
2-4-12
13.
Equipment Required
TEST PROCEDURES A.
2-4-14
Procedure
2-4-14
MARKING OF PARTS 14.
GENERAL
2-4-15
15.
PERMANENT MARKING METHODS
2-4-16
A.
2-4-16
Procedure
TEMPORARY MARKING METHODS 16.
17.
PROCEDURE
2-4-16
A.
Definition
B.
Temporary Marking
of Cold Areas
C.
Temporary Marking
of Hot
2-4-16
2-4-16
Cold Sections
2-4-17
MARKING LOCATIONS
2-4-17
PART2 CONTENTS
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TABLE OF CONTENTS
SUBJECT SECTION 4 18.
PAGE STANDARD PRACTICES
(Cont’d)
MARKING SIZE
2-4-17
WELDING 19.
GENERAL
2-4-17
20.
CLEANING BEFORE WELDING
2-4-18
21.
WELDING PROCEDURE
2-4-18
A.
2-4-18
Procedure
22.
CLEANING AFTER WELDING
2-4-19
23.
LOCAL STRESS RELIEF
2-4-20
24.
INSPECTION OF WELDING
2-4-20
STANDARD INSPECTION PROCEDURE 25.
GENERAL
2-4-20
26.
INSPECTION GAGES
2-4-21
ELBOW FITTINGS 27.
28.
REMOVAL
2-4-21
A.
2-4-21
Procedure
INSTALLATION
2-4-22
A.
Procedure
2-4-22
B.
Fluid and Pneumatic Lines
2-4-22
TOUCH-UP SOLUTION 29.
CHROME PICKLE SOLUTION
RGB AND AGE 2-4-23
A.
2-4-23
Preparation
SECTION 5 1.
(MAGNESIUM
HOUSINGS)
TORQUE RECOMMENDATIONS
GENERAL
2-5-1
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TABLE OF CONTENTS PAGE
SUBJECT SECTION 5 2.
TORQUE RECOMMENDATIONS
(Cont’d)
TQRQUE WRENCH AND EXTENSIONS
2-5-1
A.
2-5-1
Usage of Extension
to
Torque
Wrench
3.
NUTS, BOLTS AND SCREWS
2-5-2
4.
SELF-LOCKING NUTS
2-5-2
A.
2-5-2
5.
Procedure
CASTELLATED NUTS
2-5-2
6.
SLOTTED, STEEL LOCKNUTS
2-5-2
7.
STANDARD AND STEPPED STUDS
2-5-2
8.
HOSE, TUBING AND THREADED CONNECTORS
2-5-2
SECTION 6
TESTING
INTRODUCTION 1.
GENERAL
2-6-1
2.
ENGINE CONDITION TREND MONITORING
2-6-1
3.
SYMBOLS
2-6-1
GROUND SAFETY PRECAUTIONS 4.
GENERAL
2-6-2
5.
AIR INTAKE
2-6-2
6.
PROPELLER WINDMILLING
2-6-2
7.
ENGINE EXHAUST
2-6-4
8.
EXHAUST GASES
2-6-4
9.
COOL-DOWN
2-6-4
JET FUEL AND LUBRICATING OIL
2-6-4
10.
TEST INFORMATION 11.
GENERAL
2-6-4
12.
PRECIPITATION
2-6-5
PART2 CONTENTS
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TABLE OF CONTENTS
SUBJECT
PAGE
SECTION 6 -TESTING 13.
(Cont’d)
FUEL
2-6-5
14.~ INSTRUMENTS
2-6-5
15.
GROUND OPERATING LIMITS
2-6-5
16.
INADVERTENT CUT-OFF AND RELIGHT DURING TAXI
2-6-8
17.
ENGINE OVERTEMPERATURE
2-6-8
18.
ENGINE OVERSPEED
2-6-8
19.
ENGINE OVERTORQUE
2-6-8
EXTREME WEATHER CONDITIONS 20. 21.
COLD WEATHER PROCEDURES
2-6-13
HOT-WEATHER PROCEDURES
2-6-14
GROUND TESTING 22.
GENERAL A.
23.
26.
27.
2-6-14
PRESTART
2-6-15
Procedure
CHECK NO. 2 A.
25.
and Definitions
CHECK NO. 1 A.
24.
Purpose
2-6-14
2-6-15
ENGINE START
2-6-15
Procedure
2-6-15
UNSATISFACTORY START
2-6-16
A.
2-6-16
Procedure
MOTORING RUN
2-6-16
A.
General
2-6-16
B.
Procedure
2-6-16
CHECK NO. 3 A.
Procedure
B.
Adjustment
SETTING MAXIMUM GENERATOR SPEED
2-6-17 2-6-17
of Gas Generator Control
PART2 CONTENTS
2-6-18
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PAGE
SUBJECT SECTION 6 28. 29.
TESTING
(Cont’d)
TRIM SPEED DATA PLATE
CHECK NO. 4
2-6-18
ENGINE PERFORMANCE AND DATA PLATE
TRIM SPEED
30.
A.
General
2-6-18
B.
Performance Check Procedure
2-6-18
CHECK NO. 5 A.
31.
32.
ACCELERATION CHECWADJUSTMENT
Procedure
2-6-19
2-6-23
A.
2-6-23
Procedure
CHECK NO. 6
ENGINE SHUT-DOWN
2-6-27
GENERAL
35.
PROPELLER GOVERNOR CHECKS ENGINES ONLY)
37.
38.
39.
REPLACEMENT 2-6-29
(PT6A-20A AND
PT6A-20B 2-6-31
Procedure
2-6-31
PROPELLER FEATHERING CHECK PT6A-20 ENGINES
PT6A-6 SERIES AND 2-6-33
Procedure
2-6-33
POWER TURBINE GOVERNOR CHECK PT6A-20 ENGINES A.
2-6-29 2-6-29
34.
A.
COMPONENTS
General
CHECKS AFTER COMPONENT REPAIR
A.
2-6-27
Procedure
PERMISSIBLE FIELD ADJUSTMENT A.
36.
2-6-19
TORQUEMETER FUNCTION TEST
A. 33.
2-6-18
PT6A-6 SERIES AND 2-6-34
Procedure
2-6-34
POWER TURBINE GOVERNOR CHECK ENGINES
PTGB SERIES 2-6-35
COMPRESSOR BLEED VALVE
2-6-35
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TABLE OF CONTENTS
SUBJECT SECTION 6 40.
TESTING
(Cont’d)
FUEL CONTROL UNIT CHECK A.
41.
FAG E
2-6-36
Procedure
2-6-36
FUEL PUMP CHECK
2-6-36
A.
2-6-36
Procedure
42.
CHECKS AFTER COMPONENT REPLACEMENT
2-6-36
43.
PRESSURE TESTING FUEL CONTROL PNEUMATIC SYSTEM
2-6-36
A.
2-6-36
Procedure
IDLE SPEED ADJUSTMENTS 44.
GENERAL
45.
MINIMUM GOVERNING A.
46.
2-6-37
SPEED CHECK
(IDLE)
2-6-40
Procedure
2-6-40
MINIMUM FUEL FLOW ADJUSTMENT ON FUEL CONTROL UNIT
(FCU) A.
2-6-40
Procedure
2-6-40
ENGINE FINAL CHECKOUT 47.
CHECKS AND ADJUSTMENTS
2-6-42
A.
2-6-42
Procedure
SECTION 7 1.
TROUBLESHOOTING
GENERAL
2-7-1
A.
2-7-1
Procedure
2.
ENGINE CONDITION TREND MONITORING SYSTEM
2-7-1
3.
TROUBLESHOOTING
2-7-2
A.
Procedure
2-7-2
B.
Engine
C.
Lubricating
Condition Trend
Monitoring (ECTM)
Shift
2-7-2
Oil Contamination
PART2 CONTENTS
2-7-39
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TABLE OF CONTENTS
PAGE
SUBJECT
SECTION 8
CONSUMABLE MATERIALS
1.
GENERAL
2-8-1
2.
SPECIFICATIONS
2-8-1
3.
TRADE NAME PRODUCTS
2-8-1
4.
SUPPLIER CODES AND ADDRESSES
2-8-9
PART2 CONTENTS
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FAG E
DATE
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FAG E
1
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Section 3
2-3-3
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Section 2
2-1-1
Dec 02/2005
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2-1-2
Dec 02/2005
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2-1-3
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Feb 01/2002
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Feb 01/2002
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2-3-22
Feb 01/2002
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Feb 01/2002
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Jun 06/2003
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Jun 06/2003
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LIST OF EFFECTIVE PAGES
PART
SECTION
PART FAG E
DATE
SECTION
FAG E
Section 6
2-6-1
2-3-25
Feb 01/2002
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Feb 01/2002
2-6-2
2-3-27
Feb 01/2002
2-6-3
2-3-28
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2-4-1
Aug Aug
27/2004
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2-4-2
27/2004
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2-4-3
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Feb 01/2002
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Section 5
2-5-1
Feb 01/2002
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2-5-2
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2-5-3
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SECTION
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DATE
SECTION
Apr 02/2004 Apr 02/2004 Apr 02/2004
FAG E 2-7-38 2-7-39 2-7-40 2-7-41
Section 7
2-7-1 2-7-2 2-7-3 2-7-4 2-7-5 2-7-6 2-7-7 2-7-8 2-7-9 2-7-10 2-7-11 2-7-12
2-7-13 2-7-14
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2-8-32
16/2002
2-8-33
PART2 LEP
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Dec
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02/2005Page
3
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART
SECTION
DATE
PAGE 2-8-34 blank
Aug
27/2004
PART2 LEP
Dec
02/2005Page
4
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES
PAGE
FIGURE
Dipstick Assembly Figure
2-1-1
Metal
Components Figure
Shipping
Container
Fiberboard Container Fiberboard
Shipping
2-1-4
Components
Container
Electrosonic Cleaner
Bleed Valve
Electrosonic Cleaner Pressure
Testing
Figure
Existing
of
Lockwire Procedures
2-3-3 2-3-6
(Typical) Figure
System Figure
Figure
2-3-4
2-3-11
2-3-5
2-3-15
2-3-6
2-3-19
2-3-7
Wash
Locking Type
2-3-1
2-3-9
2-3-20
Ring Figure
2-3-8
Removal/i nstallation of Turbine Wash Tube
Examples
2-2-8
2-3-3
Schematic
Figure
2-2-2
2-3-2
Fuel Control Pneumatic
Water Wash Wand
Figure
2-2-10
P3 Air Filter Element
Compressor Wash Rig
Modification to
Figure
2-2-6
2-2-3
Oil Filter Element
Flushing Fixture (Fuel Nozzles) Figure
Compressor
PK562
Type
Figure
2-2-1
Washers
Figure
Figure
2-3-21 2-3-9
2-3-26
2-4-1
2-4-4
Figure
2-4-2
Lockwiring Examples Figure
2-4-3
(Sheet
Lockwiring Examples Figure
2-4-3
(Sheet 2)
2-4-9
Lockwiring Examples Figure
2-4-3
(Sheet 3)
2-4-10
Hardware Code Identification
2-4-7
Figure
1 of
Torque
Fitting (Typical) Figure
Wrench and Extension
Exhaust
Figure
Danger Areas -Typical Figure
Inadvertent Cut-off and
Overtemperature
Limits
2-4-8
2-4-4
2-4-11
Identification of Reduced Pitch Diameter Bolt Installation of Elbow
3)
Relight During
Figure
2-4-5
2-4-13
2-4-6
2-4-24
2-5-1
2-5-3
2-6-1
Taxi
2-6-3
Figure
2-6-2
2-6-9
(All Conditions except Starting) Figure
Overtemperature limits (Starting Conditions Only) Figure
2-6-3
2-6-10
2-6-4
PART 2 LIST OF FIGURES
2-6-11
Dec
02/2005Page
1
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES
FIGURE
FAG E
Overtorque Limits
All
Engines Figure
2-6-5
2-6-12
Part Power Trim Check Curve
Figure
2-6-6
(Sheet
Part Power Trim Check Curve
Figure
2-6-6
(Sheet 2)
Fuel Control
Adjustment -Typical Figure
and Data Plate Trim
Engine Performance (Sheet 2)
and Data Plate Trim
Acceleration Time
Ambient
2-6-20 2-6-21 2-6-22
Speed Check
Curve
Figure
2-6-8 2-6-24
Speed Check
Curve
Figure
2-6-8 2-6-25
vs
Power Turbine Governor
Temperature Figure
Adjustments Figure
Propeller Governor Adjustments Figure
Testing
2)
2-6-7
Engine Performance (Sheet 1 of 2)
Pressure
1 of
2-6-9
2-6-26
2-6-10
2-6-30
2-6-11
Fuel Control Pneumatic
2-6-32
System Figure
2-6-12
2-6-38
Gas Generator Speed Range at Minimum Fuel Flow for Various Pressure Altitudes Figure 2-6-13
Typical
Gas Generator
Speed
Minimum Fuel Flow
for Pressure Altitude at Minimum Fuel Flow
Adjustment Figure
Figure
2-6-39 2-6-14
2-6-41
2-6-15
2-6-43
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet 2)
2-7-4
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet 3)
2-7-5
Engine Starting Fault Isolation Chart Figure
2-7-1
(Sheet 4)
2-7-6
1 of
7)
2-7-3
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet 5)
2-7-7
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet 6)
2-7-8
Engine Starting
Fault Isolation Chart
Figure
2-7-1
(Sheet 7)
2-7-9
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 2)
2-7-11
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 3)
2-7-12
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 4)
2-7-13
1 of
10)
PART 2 LIST OF FIGURES
2-7-10
Dec
02/2005Page
2
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES FIGURE
PAGE
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 5)
2-7-14
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 6)
2-7-15
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 7)
2-7-16
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 8)
2-7-17
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 9)
2-7-18
Engine Operating
Fault Isolation Chart
Figure
2-7-2
(Sheet 10)
2-7-19
Engine
Performance Fault Isolation Chart
Engine
Performance Fault Isolation Chart Figure 2-7-3
(Sheet 2)
2-7-21
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 3)
2-7-22
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 4)
2-7-23
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 5)
2-7-24
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 6)
2-7-25
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 7)
2-7-26
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 8)
2-7-27
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 9)
2-7-28
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 10)
2-7-29
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 2)
2-7-31
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 3)
2-7-32
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 4)
2-7-33
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 5)
2-7-34
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 6)
2-7-35
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 7)
2-7-36
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 8)
2-7-37
Engine
Oil Contamination Fault Isolation Chart
Figure
2-7-5
(Sheet
Engine
Oil Contamination Fault Isolation Chart
Figure
2-7-5
(Sheet 2)
Figure
2-7-3
(Sheet
1 of
1 of
10)
2-7-20
8)
2-7-30
1 of
4)
PART 2 LIST OF FIGURES
2-7-41
2-7-42
Dec
02/2005Page
3
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF
Flil;URES PAGE
FIGURE
Engine
Oil Contamination Fault Isolation Chart
Figure
2-7-5
(Sheet 3)
2-7-43
Fault Isolation Chart
Figure
2-7-5
(Sheet 4)
2-7-44
Engine Oil Contamination
PART 2 LIST OF FIGU RES
Dec
02/2005Page
4
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF TABLES PAGE
TITLE
TABLE 2-2-1, Preservation Schedule for
Engine
Stacking
TABLE 2-2-3,
Temperature/Pressu re Gradient
Rinse Solution Formulation
TABLE 2-3-3,
Cleaning
2-2-12
2-3-2 2-3-16
Solution Formulation
2-3-16
Wash Schedule Recommendations
TABLE 2-3-5, Rinse Mixture
Cleaning
TABLE 2-3-7,
Cleaning Agents
Mixture
Compressor
2-3-17
Quantity Requirements
TABLE 2-3-6,
TABLE 2-3-8,
2-2-3
Specifications
TABLE 2-3-2,
TABLE 2-3-4,
2-2-2
Metal and Fiberboard Containers
Limitations
TABLE 2-2-2,
TABLE 2-3-1, Electrosonic Cleaner
in Metal Container
2-3-22
Quantity Requirements
2-3-23
2-3-23
Turbine Wash Schedule Recommendations
2-3-28
TABLE 2-4-1, Chrome Pickle Solution
2-4-23
TABLE 2-6-1,
Engine Operating Limits (PT6A-20,
TABLE 2-6-2,
Engine Operating
Limits
TABLE 2-6-3, Ground Checks after
-20A and
-20B)
2-6-5
(PT6A-6, -6A, -6B)
2-6-7
Component Replacement
2-6-31
TABLE 2-7-1, ECTM Shift Fault Isolation
2-7-38
TABLE 2-8-1, Consumable Materials TABLE 2-8-2,
Supplier
2-8-1
Codes and Addresses
PART 2 LIST OF TABLES
2-8-9
Dec
02/20 5Page
1/2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
´•I
GENERAL PROCEDURES
PART 2
SECTION 1 1.
ENGINE OIL.SYSTEM SERVICING
LUBRICATING OIL A.
General
specified for use in lubricating oil system of the engines covered in this manual are listed in Pratt Whitney Canada (P&WC) Service Bulletin No. 1001 (SB1001). The oils listed are for use in commercially operated PT6 series engines and are the only oils approved for flight operations. Should it be desired to use an oil not listed, P&WC Customer Support Department must be consulted first. Oil
Pratt Whitney Canada Customer Support Services 1000 Marie-Victorin Longueuil, Quebec Canada J4G1Al B.
CHANGE OF OIL BRAND
(1)
Different formulations of various oil brands may have different detergent action. an oil brand change this may cause release of carbon particles into the oil system, resulting in clogging of the scavenge screen. After change of oil brand, the
After
main oil filter should be
inspected for carbon particles at 10-hour intervals up (5 inspections) and at routine oil filter checks thereafter up excess of normal is noted, proceed as follows:
to
total of 50-hours hours. If carbon in
to 500
(a)
plug
a
Remove drain
(b) Using (c)
mirror and
position
light, inspect scavenge
If carbon is in evidence, attempt to
(d) Flush
(e)
a
from 6 o’clock
on
accessory
screen
dislodge
it
gearbox.
through
by using
a
drain hole.
small stiff
paint brush.
out any removed carbon.
If carbon cannot be removed by this method, the accessory gearbox should be removed (Refer to Part 4, Heavy Maintenance) and the screen cleaned.
NOTE:
advised that the engine lubricating oil and newly delivered/overhauled engines, may exhibit signs of a blue dye. This condition may be ignored as the dye has no detrimental effect on engine components or on protective treatments and is completely soluble in oil. Maintenance
oil wetted
personnel
components,
are
on
Page
2-1-1
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2.
OIL LEVEL CHECK A.
General
overservicing of oil tank, and high oil consumption, an oil level recommended within 30 minutes after engine shutdown. Ideal interval is If more than 30 minutes has passed, and the dip stick indicates that oil start the engine and run at ground idle for five minutes, and recheck oil
To avoid
B.
is needed, level.
Procedure
(1)
Unlock filler cap and dipstick from filler neck at 11 o’clock position gearbox, and remove filler cap.
(2)
Wipe dipstick
(3)
Install
(4)
Remove
cap/dipstick
CAUTION:
(5)
accessory
LOCKED, NO
and lock.
cap/dipstick. DELETED.
Check oil tank contents against marking NOTE:
Normal oil level is
one
maximum level, with
(6)
on
with clean lint-free cloth.
WHEN FILLER CAP ASSEMBLY IS INSTALLED AND MOVEMENT IS ALLOWED.
CAUTION:
I
check is 15 to 20 minutes.
US
dipstick,
on
and service
quart (0.83 Imp. quart,
engine
0.95
as
required.
liter)
below
in horizontal attitude.
If oil level is too low to register on dipstick due to possible excessive consumption, if low or fluctuating pressures have been recorded, refer to Troubleshooting, Engine Lubrication, for action to be taken; then proceed as follows:
or
(a)
Fill oil tank to normal level, and record
CAUTION:
3.
quantity
of oil added.
WHEN FILLER CAP ASSEMBLY IS INSTALLED AND MOVEMENT IS ALLOWED.
(b)
Install filler cap and
(c)
Run
engine 6, Testing).
(d)
Check oil level
(e)
Check main oil filter
at
dipstick;
ground
make
idle for
cap is locked.
approximately
(Ref. steps (2) (Ref.
sure
thru
LOCKED, NO
five minutes
(Ref.
Part 2, Section
(6) preceding).
Part 3, Section 2, Para. Removal of Oil
Filter).
OIL SYSTEM DRAINAGE A.
Procedure NOTE:
(See Figure 2-1-1)
For ail
change recommendations,
refer to SB1001.
Page
2-1-2
Dec 02/2005´•
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
drip tray under engine.
Place
(2)
Remove cotterpin and lockpin (5) plug (6) using puller (7).
(3)
Remove drain plug reduction gearbox.
(4) 4.
suitable
(1)
a
Remove drain
from bottom of air inlet
case
(2) or chip detector (3) and cover (4) from Inspect chip detector as detailed in Part 3,
plug (8) from
6 o’clock
position
on rear
and
drain
remove
6 o’clock
position
on
Section 3.
face of accessory
gearbox.
OIL SYSTEM FILLING A.
Procedure
(See Figure 2-1-1)
(1)
plug
Install
(a)
or
reduction
on
Pr.e-SB1217: Install plug (2) with No. 184, Fits Clearances) and
CAUTION:
(b)
chip detector
gearbox
as
follows:
preformed packing. Tighten plug, torque (Ref. safety wire.
THE CHIP DETECTOR CAN BE QUITE EASILY OVERTIGHTENED BY MODERATE HAND PRESSURE. THEREFORE, THE USE OF A TORQUE WRENCH IS IMPORTANT TO AVOID OVERTORQUING WHICH COULD RESULT IN FRACTURE OF THE CHIP DETECTOR BODY.
Post-SB1217: Install
chip
detector
(3)
with
preformed packing, tighten
and
Clearances); install cover (4) on chip detector torque (Ref. No. 200, Fits and torque (Ref. No. 199, Fits Clearances). Safety wire cover and chip detector.
(2)
(Ref. (3)
plug (8)
Install
with
No. 580, Fits
preformed packing in accessory gearbox. Tighten plug, torque Clearances) and safety wire.
Install drain plug (6) with preformed packing in bottom of air inlet with lockpin (5) and cotterpin.
case.
Secure in
position
(4)
Ensure that drain plug and airframe oil cooler (refer to
(5)
Fill oil tank with
specified
interconnecting lines are fitted and safety wired appropriate Aircraft Maintenance Manual).
oil
(Ref. SB1001)
to level of maximum
graduation
to
on
dipstick. CAUTION:
WITH FILLER CAP AND DIPSTICK ASSEMBLY LOCKED INTO
POSITION,
NO MOVEMENT IS ALLOWED.
(6)
(7)
Install filler cap and locked.
Start
engine
and
dipstick assembly
run
at
idle,
two minutes to circulate oil
(8)
Feather
as
in oil tank and
ensure
described in Section 6,
that cap is
following,
for
securely
approximately
through system.
propeller.
Page
2-1-3
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
REDUCTION GEARBOX
2)
C
(5 AIR INLET CASE
PRE-SB1217
3
IMPERIAL QUARTS
LITERS
POST-SB1217 6
0.833--1-
1.66 --1
cu
"a
1--1.90
7
ACCESSORY GEARBOX
2.49 --1
c~
8
3.80
3.32 --1
4.15 --1
1--2.85
~n
1--4.75
DETAIL OF
DIPSTICK ASSEMBLY
C6226
Dipstick Assembly Figure 2-1-1
Page
2-1-4
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
3. 4. 5.
6. 7.
8.
(10)
Shut down
5.
2-1-1
as
described in Section 6,
following.
Check oil level in tank and replenish, as required, to normal level described in Paragraph 2.B., preceding.
on
dipstick
as
WITH FILLER CAP AND DIPSTICK ASSEMBLY LOCKED INTO POSITION, NO MOVEMENT IS ALLOWED.
CAUTION:
(11)
engine,
Figure
Dipstick Assembly Drain Plug (Pre-SB1217) Chip Detector (Post-SB1217) Cover (Post-SB1217) Lockpin Drain Plug Puller (PWC30077) Drain Plug
1. 2.
(9)
to
Install filler cap and locked.
dipstick assembly
in oil tank and
ensure
that cap is
securely
OIL SYSTEM FLUSHING General
If an engine operated, or
is to be if the oil
operated on system has
an
oil which differs from that
been contaminated
by
on
which it
other than metallic
previously particles, then
the oil system must be flushed B.
Procedure
Place suitable
(2)
plugs or chip detector from gearbox, accessory gearbox and airframe oil Remove oil drain
CAUTION:
O
drip pan
under
engine.
(1)
compressor inlet case, reduction cooler.
LIMIT ENGINE ROTATION TO THE MINIMUM TIME REQUIRED TO ACCOMPLISH COMPLETE DRAINING.
(3)
With drains open, place power control lever to CUT-OFF (PT6A-6 engines), or to IDLE position (PT6A-6A, -6B, -20 Series engines), and fuel cut-off lever to CUT-OFF (PT6A-6A, -6B, -20 Series engines). Motor engine with starter only (no ignition) to allow scavenge pumps to clear engine.
(4)
Reinstall all drain
(5)
Taking all normal ground safety precautions (refer engine oil tank with nevi~ oil.
(6)
Start
engine
and
plugs
run
in
engine
and airframe cooler. to Section
6, following), refill
at IDLE for a minimum of two minutes.
Page
2-1-5
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Feather
(8)
Shut down
(9)
Repeat steps (1) (2)
propeller,
applicable.
engine. and
(3)preceding.
(10)
Remove engine oil filter; install disposable type (Pre-SB1118) or reinstall all-metal type (Post-SB1118) after cleaning as detailed in Section 3, following.
(11)
Reinstall and safety wire all drain airframe cooler.
(12)
Refill
(13)
Check oil level.
(14)
Start
(15)
Feather
(16)
Shut down
(17)
Check oil level and
engine
engine
CAUTION:
(18) 6.
if
(7)
oil tank with
and
run
new
plugs and magnetic chip
detector in
engine
and
oil.
at IDLE for a minimum of two minutes.
propeller, if applicable.
engine.
replenish
as
necessary.
WITH FILLER CAP AND DIPSTICK ASSEMBLY LOCKED INTO POSITION, NO MOVEMENT IS ALLOWED.
Reinstall filler cap and locked securely.
dipstick. Ensure
that filler cap is
correctly
installed and
PATCH MAKING PROCEDURE A.
Procedure
CAUTION:
DO NOT USE PATCH-MAKING PROCEDURE AS A CLEANING PROCEDURE FOR FILTER ELEMENTS.
(1)
Remove filter element from
(2)
Using
(3)
Place filter in
WARNING:
(4)
suitable
engine (Ref.
tapered plugs,
cylindrical
seal inner
Part 3, Section
cavity
2).
of filter element.
container.
REFER TO MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS, PHYSICAUCHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES.
Fill container with teksol (PWC11-048), enough to space for liquid movement when shaking. Secure
cover
filter element but
leaving
a
cover.
Page
2-1-6
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(5)
Shake container for about three minutes Remove
manually
or
30 seconds in
a
vibrator.
cover.
Ensure there are no deposits left and continue shaking.
NOTE.
on
filter. If there is,
secure
container
cover
(6)
Install
patch (PWC05-190) (2 liters or 1/2 gal, min.).
new
container
filter
in filter
(7)
Remove filter element from container.
(8)
Pour
(9)
liquid
contents of container into filter
Flush out all teksol
some
(10)
patch
holder and
place
over a
suitable
holder.
possible loose particles which may still be in container by pouring (PWC11-048) into it, shaking, then emptying into filter patch holder. patch from filter patch holder and place in patch receptacle. Identify type of filter, engine serial number and hours run.
Remove filter
sample (11)
patch
with
If any debris is found (particles large enough to be trapped sample to laboratory for material spectrographic analysis.
by filter patch), send
Some operators retain the filter patches to establish a visual coloration Operators doing this, need to build up their own experience for patch coloration trend evaluation because trends may vary from one engine to another and may be affected by the operating environment and maintenance practices.
NOTE:
trend.
(12)
plugs from the element).
Remove inside
WARNING:
filter element
(ensure
the
preformed packing
does not
drop
WHEN USING COMPRESSED AIR FOR DRYING, REGULATE TO 29 psig (200 kPa) OR LESS. WEAR GOGGLES OR FACE SHIELD TO PROTECT EYES.
(13)
Dry filter
(14)
Install filter element
element
using on
clean
compressed
engine (Ref.
air at 29
Part 3 Section
psig (200 kPa). 2).
Page
2-1-7/8
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
GENERAL PROCEDURES
PART 2
I SECTION 2
PREPARATION FOR SERVICE OR STORAGE
INTRODUCTION 1.
GENERAL A.
Procedures included in this section should be followed when removing the engine from, installing an engine in a storage container, and when carrying out engine depreservation or preservation. If available, Maintenance Stand (PWC30035) may be used for limited maintenance with engine in a horizontal position, or to support an engine after removal or prior to installation in airframe or storage container. However, if engine is to undergo heavy maintenance, it must be installed in Stand (PWC30800) as detailed in Part 4. or
B.
Two types of storage containers are in use. One type, of steel construction, is reusable and may be used for long periods of either indoor or outdoor storage provided the correct internal pressure is maintained, desiccant is replenished as required and the engine is preserved in accordance with the applicable schedule.
C.
The other
type, non-reusable, of which there are two configurations, is of fiberboard construction. These containers are intended primarily for domestic shipment (North American Continent) in closed conveyances, or for domestic and overseas air shipment. This type of container should not be used for shipment by sea. When properly sealed, these containers
for
storage, 2.
are
weather-resistant and
non-susceptible
to climatic conditions
up to one week. Fiberboard containers should not be used for outdoor but will withstand indoor storage in dry areas for periods up to six months.
periods
HUMIDITY CONTROL A.
To maintain internal moisture conditions at a safe level for storage, a specific quantity of dehydrating agent (desiccant) is stowed in each container. Desiccant is packed in individual bags, each containing eight units tone unit weighing one ounce). Each container is provided with a humidity indicator to show the moisture level within the container without disturbing the container or contents. At a safe moisture level (up to 40% relative humidity) the indicator color is blue. As intemal humidity increases, the color changes gradually to pink. An all pink color indicates that an unsafe moisture condition has been
reached, and desiccant should be replaced with freshly activated material. NOTE:
3.
Humidity indicators have a reversible element when reactivated, which may be reused provided the original all-blue color is evident. Indicators need not be replaced unless damaged.
REACTIVATION OF DESSICANT A.
Procedure
(1)
Place bags of used desiccant and pink humidity indicator in a suitable oven controlled at 121"C (250"F) for two hours (minimum). Humidity indicator must turn blue.
Page
2-2-1
Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(2)
Allow
bags
(3) 4.
oven to cool to and indicator.
room
temperature (approximately 22"C (72"F)), then
possible, after reactivation is complete, insert bags of polyethylene envelopes. Exclude all air and seal envelopes.
As
soon as
remove
desiccant into
STORAGE OF ENGINE A.
Long
term
storage (91 days
or
over) of engine
must be
accomplished
in
a
metal
container, when stored indoor or outdoor. All precautions must be observed to eliminate loss of pressure, and to prevent humidity from reaching an unsafe level. A periodic check must be carried out at least in accordance with Table 2-2-1.
once
every 30
TABLE 2-2-1, Preservation Schedule for
CONTAINER INTERNAL PRESSURE (psi) Normal for
prevailing
ambient
days
Engine
CONTAINER INTERNAL RELATIVE HUMIDITY Below 20
and any action necessary taken
in Metal Container
ACTION REQUIRED
No action all
required.
temperature in Table
(Indicator
Less than normal for ambient temperature in Table 2-2-3.
Below 20
Repressurize container (Ref. Para.lO.). If pressure has dropped after lapse of seven days, remove engine (Ref. Para. 7.), and reinstall in a serviceable container (Ref. Para.lO.).
20 to 40
Replace desiccant. Repressurize container and check for leakage using a
blue)
prevailing
(Indicator partially pink)
soapy water solution. Above 40
(Indicator
all
pink)
Remover container
engine from (Ref. Pam. 10.).
Inspect for corrosion; if condition is satisfactory, reinstall unit with shipping
freshly activated (Ref. Pam. 10.) and repressurize container. Check for leakage using soapy water solution. If necessary, rectify faulty container and repeat leakage check. If severe corrosion is present, engine should be shipped to an overhaul facility. covers,
desiccant
Page
2-2-2
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
is stored in a fiberboard container, a periodic check must be carried out at every 7 days, to prevent humidity from reaching an unsafe level. When indicator changes to a partially pink color, remove engine from container and protective envelope (refer to Paragraphs 3. and 9.). Replace desiccant with freshly activated bags of desiccant and reinstall engine in container (refer to Paragraphs 12. and 13.). If
engine
least
5.
once
STACKING FOR STORAGE A.
Instructions outlined in Table 2-2-2 must be followed when in containers.
stacking empty containers,
or
engines
TABLE 2-2-2,
Limitations
Metal and Fiberboard Containers
LIMITS
PRECAUTIONS
LIMITS ENGINE IN CONTAINER
Stacking
Ensure containers
(Three
are
sound and in undamaged condition.
high max.)
ACTION REQUIRED
Replace
ENGINE IN CONTAINER Two high maximum
with
used sleeve
new
sleeve and
cover.
(Static Storage) high maximum (Shipping)
One
EMPTY CONTAINER
Only static (no impact) and superimposed stacking is
(Four high max.)
EMPTY CONTAINER Four
Ensure wooden side
stiffeners, where
high (max.)
fitted,
are
sound and
undamaged. Only static (no impact) and superimposed stacking is
recommended. Avoid containers over each other.
dropping
recommended. Avoid dropping containers over
each other.
REMOVAL/INSTALLATION 6.
GENERAL A.
Precautions
(1)
engine is to be removed from, or installed container, the following precautions must be taken.
When
(a)
an
Ensure that hoist has sufficient follows:
capacity
and
in
a
safety
metal
or
fiberboard
factor to handle loads
1
A load of 350
pounds (159 kg)
when
lifting engine only.
2
A load of 800
pounds (363 kg)
when
lifting engine
as
loaded in fiberboard
container.
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Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
A load of 800
3
pounds (363 kg)
when
lifting engine
loaded in metal
container.
(2)
Ensure that container is
(3)
Ensure that free overhead space of available. NOTE:
B.
on
floor, directly beneath hoist.
approximately six feet (two metres)
This clearance is exclusive of the distance from the the hoist hook.
minimum is
top of the container
to
Types Of Engine Slings (1)
7.
positioned correctly
Two types of engine sling assemblies, (PWC30036) and (PWC32327), are used. Both slings have a single front extension. (PWC30036) has two rear extensions which attach at the 3 and 9 o’clock positions on PT6A-6 and -6A engines. (PWC32327) has a single rear extension which attaches to a bracket at the 12 o’clock position on PT6A-6B, -6/C20, -20, -20A and -208 engines.
REMOVAL OF ENGINE FROM METAL CONTAINER A.
Procedure
(See Figure 2-2-1)
(1)
Remove service
(2)
Depressurize
WARNING:
receptacle
container
cover
(1) by removing
two nuts and lockwashers.
air to escape
air fill valve
by allowing
through
(2).
A MINIMUM OF 10 MINUTES MUST BE ALLOWED FOR ALL PRESSURE TO BE RELIEVED BEFORE SEPARATING THE HALVES OF THE
CONTAINER. data papers from record
(3)
Remove all
(4)
Attach chain,
(5)
Remove 36 closure nuts and bolts which
(6)
Carefully raise top half of container from immediate work area.
CAUTION:
(7)
Attach
engine or
cable
sling,
to end
receptacle (5).
lifting points (8) provided secure
straight
on
top of container.
top and bottom halves of container.
up until clear of
engine,
then
remove
NEVER USE ENGINE SLING AND HOIST FITTINGS TO LIFT AN ENGINE THAT IS STILL ATTACHED TO LOWER HALF OF THE CONTAINER.
applicable Sling Assembly (PWC30036)
or
(PWC32327),
to
engine lifting
points.
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2-2-4
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(8)
weight of engine on sling and remove three quick release pins (9) securing engine to container mounting brackets. Lift engine slowly from container, simultaneously ensuring that engine remains level and is not permitted to swing.
Take
difficulty be experienced when removing any of the pins which engine to the container mounting brackets, remove bolts and washers which secure bracket in question. An alternative method of removing the engine from its container is to remove the eight bolts, washers and nuts which secure the mounting cradle (11) to the container. Lift out engine, together with mounting cradle, then separate engine from cradle.
NOTE:
Should secure
(9)
to a clear area and remove 11 bolts and washers securing forward brackets to engine. Reinstall container brackets on cradle and stow bolts and washers in cloth sacks provided on cradle.
Transfer and
8.
the
engine
rear
in
(10)
Install
(11)
Depreserve engine (refer
engine
stand.
appropriate
to
Paragraph 19.).
REMOVAL OF ENGINE FROM FIBERBOARD CONTAINER A.
Procedure
(See Figure 2-2-2)
(1)
Cut steel support straps
(2)
Cut
sealing tape
(3)
Cut
protective envelope (9)
(4)
Attach
CAUTION:
TYPE PK562
(15) and discard.
and fold back
sling (PWC30036)
flaps
on
and expose
or
Retain
corners
(16).
top of container.
top of engine.
(PWC32327)
to
engine lifting points.
NEVER USE ENGINE HOIST FITTINGS TO LIFT AN ENGINE AND CRADLE ASSEMBLY THAT IS STILL ATTACHED 10 SKID BASE.
weight of engine on sling and remove eight bolts (18) and lockwashers (19) securing cradle (13) to mounting brackets (14). Slowly lift out engine and cradle assembly ensuring that engine remains level and is not permitted to swing.
(5)
Take
(6)
Transfer engine to quick release pins rear bracket (12).
a
clear
area
and
(21) from engine
remove
cradle from
engine by removing three (11) and engine mount
mount front brackets
(7)
Remove 11 bolts and washers securing engine mount front and rear brackets to engine. Remove brackets and reassemble on cradle. Stow bolts and washers with cradle.
(8)
Remove
(9)
Remove all
protective envelope (9)
engine in
engine. Discard
non-reusable items.
data papers from bottom of container.
appropriate stand.
(10)
Install
(11)
Depreserve engine. (Refer
engine
from
to
Paragraph 19.).
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Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Q
I
6) 5
4~ 15
C1186C Metal
Shipping Container Components Figure 2-2-1
Page
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Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key 1.
Service
Air Fill Valve
2-2-1
Receptacle
Cover
Receptacle
3.
Service
4.
Pressure Relief Valve
5.
Record
8.
Receptacle Container Locating Pin Humidity Indicators Container Lifting Points
9.
Quick Release Pins
7.
10.
Container Gasket
11.
Mounting
Cradle
REMOVAL OF ENGINE FROM FIBERBOARD CONTAINER A.
1)
Figure
2.
6.
9.
to
(See Figure 2-2-3)
Procedure
(1)
Cut steel
(2)
Remove
(3)
Cut
(4)
Attach
support straps (10) and discard. Retain cover
(1)
from sleeve
protective envelope (7)
sling (PWC30036)
Take
(5)
(9).
and lift sleeve from skid base
and expose
or
corners
(17).
top of engine.
(PWC32327)
to
engine lifting points.
NEVER USE ENGINE HOIST FITTINGS TO LIFT AN ENGINE AND CRADLE ASSEMBLY THAT IS STILL A~TACHED TO SKID BASE.
CAUTION:
(5)
TYPE PK1325
weight of engine on sling engine to cradle.
and
remove
three
quick
release
pins (11)
that
secure
(6) (7)
lift
Slowly
engine
clear of cradle
(15), ensuring
that it does not
swing.
Remove 11 bolts and washers that secure brackets (12) and (14) to engine and bag; attach brackets (12) and (14) to cradle with quick release pins (11) and (13). stow in
(8)
Remove
(9)
Install
envelope (7)
engine
(10)
Remove all
(11)
On
in
and discard non-reusable items.
appropriate
engine
stand.
data papers from bottom of container.
with oil-to-fuel heater, remove two bolts and washers that heater to heater mounting bracket (13) and remove oil-to-fuel heater from cradle. Install heater on engine. (Refer to Part 3, Section 2).
engines equipped
secure
cradle, skid base and
(12)
Retain
(13)
Depreserve engine. (Refer
mount brackets to
(12)
for further
use.
Paragraph 19.).
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2-2-7
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Is _c----
~O
C1489B Fiberboard Container
Components Figure 2-2-2
Type
PK562
Page
2-2-8
Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key 1.
Inner Stiffener
2.
Bolt
3.
Plain Washer
4.
Outer Stiffener
5. 6.
Self-locking Reinforcing
7.
Shear Mount
8.
Pallet
9.
Protective
2-2-2
Nut Plate
Envelope
10.
Gaskets
11. 12.
Engine Engine
13.
Cradle
14.
16.
Mounting Bracket Steel Strapping Reinforcing Corner
17.
Screw
18.
Bolt
19.
Lockwasher
20.
Humidity
21.
Quick Release Pins
15.
10.
Figure
to
Mount Front Bracket Mount Rear Bracket
Indicator
INSTALLATION OF ENGINE IN METAL CONTAINER A.
General Prior to installation of engine in metal container, refer to for necessary preservation and schedule.
B.
Procedure CAUTION:
(1)
(2)
14. and 15.
following
(See Figure 2-2-1) ENSURE THAT OIL HAS BEEN COMPLETELY DRAINED BEFORE INSTALLING ENGINE IN CONTAINER.
For removal of
CAUTION:
Paragraphs
engine
from Stand
(PWC30800),
refer to Part 4.
DO NOT USE STANDARD COMMERCIAL HARDWARE TO FASTEN ENGINE SUPPORT BRACKETS TO THE ENGINE OR CONTAINER. USE OF HARDWARE OF LOWER STRENGTH THAN SPECIFIED COULD RESULT IN SERIOUS ENGINE DAMAGE DURING SHIPPING OR HANDLING.
Attach two container forward brackets and gaskets to lower mounting pads on engine gas generator case using eight bolts and lockwashers. Tighten bolts and
torque
to 225 to 250 Ib.in.
Page
2-2-9
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ai
S
oel/i/
a
6
to
a
4
a
~I
C38688
Shipping Container Figure 2-2-3
Fiberboard
Page
2-2-10
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
(3)
Attach container
to
1.
Cover
2.
Figure
2-2-3
Corners
3.
Reinforcing Steel Strap
4.
Pressure Sensitive
5.
Sleeve
6.
Humidity
7.
Protective
8.
Gaskets
9. 10.
Reinforcing Steel Strap
Tape
Indicator
Envelope Corners
11.
Quick-release Pin
12.
Front Mount Brackets
13.
Quick-release Pin
14.
Rear Mount Brackets
15.
Cradle
16.
Shear Mounts
17.
Skid Base
rear
bracket and
engine accessory gearbox, using
gasket
to
mounting pad
at 6 o’clock
three bolts and lockwashers.
Tighten
position
on
bolts and
to 50 to 70 Ib.in.
torque
shipping
and
plugs,
illustrated in Parts
Catalog
No. 3015444.
(4)
Install
(5)
Ensure that interior of container is free of dirt, water, oil, or other contaminants, and check mating faces of container flanges for distortion or other unserviceable conditions that may affect airtight sealing of flange joint.
(6)
Carefully
lower
covers
engine
holes and insert three
(7)
as
into bottom half of container, align brackets with mounting quick release pins (9) to secure engine to cradle.
the cradle may be removed from the container for engine installation. After assembling cradle to engine, lower into container and secure cradle with eight bolts, washers and nuts.
NOTE:
Alterplatively,
Remove
sling
from
engine.
CAUTION:
REMOVE DESICCANT BAGS FROM PROTECTIVE ENVELOPES BEFORE INSTALLATION.
CAUTION:
DO NOT PLACE DESICCANT BAGS ON OR NEAR THE COMPRESSOR INLET TO AVOID POSSIBLE INGESTION OF DESICCANT PARTICLES BY THE ENGINE.
(8)
(96 units 1 oz. per unit, total) freshly activated desiccant bags (PWC15-001) engine, evenly distributed over engine length, 6 on each side.
Tie 12 to
Page
2-2-11
Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(9)
lower top half of container over engine and on to bottom half of container, over locating pin (6) on forward end of flange of bottom half. Check container gasket (10) for correct seating.
Carefully guiding it
(10)
Secure top and bottom halves of container using 36 closure bolts, washers and nuts. Coat bolts with corrosion-preventive compound (PWC15-014) and torque nuts progressively to 270 to 300 Ib.in.
(11)
Introduce clean, dry air through air fill valve (2), until internal air pressure equals value indicated for prevailing ambient temperature (refer to Table 2-2-3). Replace valve cap.
Temperature/Pressure Gradient
TABLE 2-2-3,
Data
Description -29"C
-23"C
-18"C
-7"C
4"C
16"C
27"C
38"C
(-20"F)
(-10"F)
(O"F)
(20"F)
(40"F)
(60"F)
(80"F)
(100"F)
2.000
2.375
2.750
3.500
4.250
5.000
5.750
6.500
Ambient
Temperature Required psi gage pressure NOTE: 5
psig
(12)
is established at
a
standard
working temperature
Check container for pressure leaks
using
a
of 16"C
(60"F).
soap and water solution. Seal any leaks
immediately. NOTE:
(13)
Prior to shipping an engine in the container, check intemal pressure of container over a 48-hour period.
Install service
receptacle
cover
(1, Figure 2-2-1),
and
secure
using
two lockwashers
and nuts.
(14)
Wrap engine data papers in a waterproof envelope, pressure-sensitive adhesive tape (PWC05-070). NOTE:
(15)
11.
Place engine data papers in record lockwire bolt heads.
Procedure
(1) (2)
Open
secure
If the engine log book is the stiff cover type it must be with the log sheets, under separate cover.
receptacle (5).
PREPARATION OF FIBERBOARD CONTAINER A.
and
with
clean-stripping,
shipped, together
Install cover, secure, and
TYPE PK562
(See Figure 2-2-2) container and fold bottom end
flaps inward first, then side flaps.
reinforced filament tape (PWC05-070), seal middle seam and overlap 10 along sides, then tape bottom edges at each end and extend around sides approximately 12 inches. Use
nylon
to 12 inches
Page
2-2-12
Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
inner stiffener (1) resting at bottom inside of container six 7/16 inch diameter holes in container.
template,
drill
(3)
Using punch
(4)
Repeat step (3), preceding,
(5)
Install four bolts (2) and plain washers (3) in upper holes of outer stiffener (4) and attach to outside of container. Install inner stiffener (1) over bolts and secure with self-locking nuts (5) and washers (3). Do not tighten bolts at this stage.
(6)
In each lower pair of holes, install bolts through reinforcing plate (6), and attach to container. Secure shear mounts (7) to inside with self-locking nuts (5) and plain washers
(7)
(3).
opposite
on
as
or
side of container.
Do not torque nuts at this stage.
Repeat steps (5)
(6)
and
on
opposite
side of container.
Tighten
12 bolts and
torque
to 80 to 90 Ib.in.
12.
(8)
Install four
(9)
Place container
mounting on
brackets
(14)
on
shear mounts
(7)
(17).
TYPE PK562
General Prior to installation of
following, B.
screws
pallet (8).
INSTALLATION OF ENGINE IN FIBERBOARD CONTAINER A.
with
Procedure
(1)
engine in fiberboard container, preservation and schedule.
renew
any part found to be
(3)
Install engine in new protective envelope (9) aligned with respective engine mount pads.
CAUTION:
engine
from stand
(PWC30800)
For removal of
damaged.
so
refer to Part 4.
that
gaskets (10)
on
envelope
engine mount front brackets (11) to mount pads on gas generator bolts and washers. Tighten bolts and torque to 225 to 250 Ib.in.
eight
Attach engine mount rear bracket (12) to mount pad on accessory three bolts and washers. T~ghten bolts and torque to 50 to 70 Ib.in.
engine onto cradle (13) and secure front and cradle with three quick release pins (21).
Lower on
are
DO NOT USE STANDARD COMMERCIAL HARDWARE TO FASTEN THE ENGINE SUPPORT BRACKETS TO ENGINE OR CONTAINER. USE OF HARDWARE OF LOWER STRENGTH THEN SPECIFIED COULD CAUSE SERIOUS ENGINE DAMAGE DURING SHIPPING OR HANDLING.
Attach two with
(6)
14. and 15.,
ENSURE THAT OIL HAS BEEN COMPLETELY DRAINED BEFORE INSTALLING ENGINE IN CONTAINER.
(2)
(5)
Paragraphs
(See Figure 2-2-2)
Inspect pallet and cradle,
CAUTION:
(4)
refer to
for necessary
rear
gearbox
case
with
mount brackets to clevis
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Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
water or other contaminants.
(7)
Ensure that interior of container is free of
(8)
Secure
(9)
log book, log sheets and other relevant papers to be shipped with engine waterproof envelope and seal with pressure-sensitive tape.
humidity indicator (20)
to
dirt, oil,
protective envelope (9).
Place
(10)
engine and cradle assembly against any part of container.
(11)
Secure cradle to
(12)
Detach
Lower
sling
mounting
from
brackets
into container,
(14)
with
taking
bolts
eight
care
(18)
not to strike
in
a
engine
and lockwashers
(19).
engine.
CAUTION:
REMOVE DESICCANT BAGS FROM PROTECTIVE ENVELOPES BEFORE INSTALLATION.
CAUTION:
DO NOT PLACE DESICCANT BAGS ON OR NEAR THE COMPRESSOR INLET TO AVOID POSSIBLE INGESTION OF DESICCANT PARTICLES BY THE ENGINE.
(13)
(14)
(96 units engine, evenly
unit, total) freshly activated desiccant bags (PWC15-001)
Tie 12
1 oz. per
to
distributed
Heat-seal corner
along top
of
over
engine length,
envelope, using
open to evacuate air. Evacuate
envelope and align humidity indicator pressure-sensitive tape.
6
on
suitable hand
air, fold
corner
each side.
sealing iron, leaving
one
and heat-seal. Fold
with window in container.
Tape envelope end
folds with
(15) (16)
Fold end
flaps
of container inward, then side
flaps.
Using nylon reinforced filament tape(PWC05-070), tape middle seam and overlap by approximately eight inches. Tape edges at both ends and extend around sides approximately 12 inches. ends
(17)
Secure container to
strapping 13.
pallet (8) with five sets of (16) on each side.
steel
strapping (15), passing
over corners
INSTALLATION OF ENGINE
IIj
FIBERBOARD CONTAINER -TYPE PK1325 (PT6A-6/C20,
20, -20A and -20B ENGINES ONLY) A.
General Prior to installation of engine in fiberboard container, refer following, for necessary preservation and schedule.
B.
Procedure
(1)
to
Paragraphs
14. and 15.,
(See Figure 2-2-3)
Inspect
skid base and
cradle;
renew
any parts found to be
damaged.
Page
2-2-14
Jun 06/2003
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ENSURE THAT OIL HAS BEEN COMPLETELY DRAINED BEFORE INSTALLING ENGINE IN CONTAINER.
CAUTION:
(2)
On
engines
fitted with oil-to-fuel heater,
proceed
(a)
Disconnect all hoses from heater unit.
(b)
Remove two nuts
securing
heater
as
follows:
bracket to accessory
mounting
gearbox.
(c) Remove heater with bracket from engine. (d)
Blank off all
(e)
Install heater unit and washers.
openings
in heater and hoses with
mounting
on
bracket
(13)
plugs
or covers.
of cradle and
engine from Stand (PWC30800). (Refer
with two bolts
4.)
(3)
Remove
(4)
engine in new protective envelope (7) so that gaskets (8) aligned with respective engine mount pads on engine. Install
on
envelope
are
DO NOT USE STANDARD COMMERCIAL HARDWARE TO FASTEN THE ENGINE SUPPORT BRACKETS TO ENGINE OR CONTAINER. USE OF HARDWARE OF LOWER STRENGTH THAN SPECIFIED COULD CAUSE SERIOUS ENGINE DAMAGE DURING SHIPPING OR HANDLING.
CAUTION:
(5)
to Part
secure
Attach two container forward brackets (12) to lower mounting pads of engine gas generator case, with eight bolts and washers. Tighten bolts and torque 225 to 250 Ib.in.
(6)
Attach container
accessory 70 ib.in.
bracket (14) to mounting pad at 6 o’clock position on with three bolts and washers. Tighten bolts and torque 50 to
rear
gearbox
Lower
(8)
log book and other documents to be shipped with engine in a waterproof envelope, and seal with pressure sensitive tape. Glue envelope to skid base.
(9)
Detach
Place
(10)
Attach
(11)
Tie
sling new
from
engine.
humidity
indicator
(6)
to
envelope (7).
1? bags (96 units total) of freshly activated desiccant
NOTE:
(12)
engine
into cradle and attach with three
quick-release pins (11) and (13).
(7)
Desiccant
Heat-seal corner
bags
along top
of
should be
evenly
distributed
to
over
engine.
entire
engine length.
envelope, using suitable hand sealing iron, leaving
open to evacuate air. Evacuate
air, fold
one
and heat seal. Fold will align with window in container.
corner
envelope (7) and ensure that humidity indicator (6) Tape envelope and folds with pressure-sensitive tape (4). (13)
Place sleeve
(5)
over
engine
and fit in
position
on
skid base.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
flaps
of sleeve, and seal
(14)
Close
(15)
Place
(16)
Secure
(17)
Secure sleeve and
(1) on sleeve, pressure-sensitive tape (4). cover
cover
diagonally
fold
flaps
with steel strap and four cover
with
pressure-sensitive tape (4).
down and seal at each
corners
corner
with
(2).
to skid base with steel
straps (10) and
16
corners
(9).
ENGINE PRESERVATION/DEPRESERVATION 14.
GENERAL
procedure to be followed for preservation and depreservation of engines in service depends on the period of inactivity, type of preservative used, and whether or not the engine may be rotated during the inactive period. To establish procedure, reference shouldbe made to preservation records (tags) and to the engine service record (log book). The period of inactivity, or anticipated inactivity, should also be established.
A.
The
B.
Fuel Control Unit
(1)
Preservation of a fuel control unit depends on the period of not the FCU is operated during the inactive period.
inactivity
and whether
or
(a)
A FCU is considered active if an engine is involved in normal flight or if an engine is wet motored or run during preservation periods.
(b)
A FCU is not considered active if
aircraft inactive
(2)
engine
is not wet motored
or run
during
periods.
on inactive engines in long term container storage the time accumulated in the container begins at the time of packaging.
For fuel control units that remain
(off wing), (3)
an
operations
For units that have been removed from the engine and are in storage three years more, refer to Part 3, Section 2, Fuel Control Unit, Storage, Depreservation or
or
Reconditioning
of FCU, Three Year
Requirement.
(4)
For units that have been removed from the engine and are in storage more than six years, refer to Part 3, Section 2, Fuel Control Unit, Storage, Depreservation or Reconditioning of FCU, Six Year Requirement.
(5)
engines that are inactive for more than six months and that are not refer to Part 3, Section 2, Fuel Control Unit, Storage, Depreservation preserved, or Reconditioning of FCU, Six Year Requirement. For units
on
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
15.
ENGINE PRESERVATION SCHEDULE A.
Procedure CAUTION:
PROPELLER MUST BE RESTRAINED TO PREVENT WIND MILLING.
CAUTION:
UNDER NO CIRCUMSTANCES SHOULD PRESERVATIVE OIL BE SPRAYED INTO THE COMPRESSOR OR TURBINE END OF THE ENGINE. DIRT PARTICLES DEPOSITING ON BLADES AND VANES DURING ENGINE OPERATION WILL ALTER THE AIRFOIL SHAPE AND ADVERSELY AFFECT COMPRESSOR EFFICIENCY.
Days Engines may be left in an inactive state, with no preservation protection requirements, provided: engine is sheltered, humidity is not excessively high; engine is not subjected to extreme temperature changes which would produce condensation.
(1)
0 to 7
(2)
Days Engines inactive up to 28 days require no preservation providing all engine openings are sealed off and relative humidity in engine is maintained at less than 40%. Humidity control is maintained by placing desiccant bags in engine 8 to 28
exhaust duct. NOTE:
Ensure that desiccant bags are kept off all engine parts by placing on racks. Provide suitable windows in exhaust closures for observation of
humidity (3)
indicators.
29 to 90 Days Engines inactive for a period exceeding 28 days, but less than 90 days, need only have fuel system preserved (refer to Paragraph 17., following) engine intake and exhaust openings covered, and desicc8ht and humidity indicators
installed.
(4)
Engines inactive over 90 days, or removed for long term (refer to Paragraph 4.) must, in addition to 29 to 90 day storage have procedures, engine oil drained and unused accessory drive-ends sprayed. to (Refer Paragraph 16., following.) 91
Days
and Over
in container
16.
ENGINE OIL SYSTEM PRESERVATION A.
Procedure
(1)
Carry out preservation 90 days) as follows: CAUTION:
(a)
of
engine
oil
system (engines inactive for periods exceeding
OBSERVE STARTER MOTOR OPERATING LIMITS. STARTER MANUFACTURER’S MANUAL.)
(REFER TO
Close normal fuel supply shut-off valve and rotate engine with electric starter until oil pressure and compressor speed (Ng) are indicated. Disengage starter.
(b) ~Remove drain plugs gearbox.
from oil tank, accessory
gearbox
and
propeller reduction
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(c)
With drains open, motor engine with starter (no ignition) to permit scavenge pumps to clear engine, indicated by cessation of steady stream of oil from drains. To prevent excessive operation with limited lubrication, limit rotation to shortest possible time to accomplish complete drainage.
(d)
Remove oil filter element and allow to drain.
(e) Allow oil
to drain to a slow filter and close drains.
(f)
drip (approximately
one
half-hour),
then install oil
Remove cover plates from pads of accessory drives and spray exposed surfaces and gearshafts with engine lubricating oil (refer to P&WC Service Bulletin No. 1001 latest issue for list of approved oils). Replace cover
plates. (g)
Install plugs, caps and covers over all openings to prevent entry of foreign material accumulation of moisture. (Refer to Parts Catalog P/N 3015444.) NOTE:
(h) Tag (i)
If the engine is to remain in aircraft, and inlet ducts.
oil filler cap with date of
Install
humidity
place
desiccant
bags
in exhaust
preservation.
indicator in air inlet end and in exhaust end of
engine
compartment. Cover with suitable airtight moisture barrier. Provide inspection windows at each end for observation of
NOTE:
indicators.
Inspection of a preserved unit should be carried out every two weeks if the aircraft is stored outside, or every 30 days if the aircraft is stored inside. If the relative humidity, as indicated on the humidity indicator, is less than 40%,
no
further action is
exceeds 40%, the desiccant activated bags. 17.
humidity
bags
required. If humidity indicated replaced by freshly
must be
ENGINE FUEL SYSTEM PRESERVATION A.
Procedure
(1)
Carry as
out
preservation
CAUTION:
(a)
of
engine
fuel
system (engines inactive
more
than 28
days)
follows: EXTREME CARE MUST BE TAKEN TO PREVENT FOREIGN MATERIAL FROM BEING DRAWN INTO ENGINE FUEL SYSTEM. EQUIPMENT MUST BE FITTED WITH SUITABLE FILTERS OR STRAINERS, NO COARSER THAN 10-MICRON RATING.
Close normal fuel supply shut-off valve. Disconnect fuel inlet line to fuel pump oil-to-fuel heater and connect suitable oil supply line to fuel pump or oil-to-fuel heater. or
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CAUTION:
UNDER NO CIRCUMSTANCES PERMIT PRESERVATIVE OIL TO ENTER ENGINE WHERE IT MAY COME IN CONTACT WITH THERMOCOUPLE PROBE ASSEMBLY. OIL CONTAMINATION OF HARNESS MAY CAUSE COMPLETE FAILURE OF THERMOCOUPLE SYSTEM.
dump valve, to prevent flushing oil entering fuel required to permit drainage into a suitable container. Supply flushing oil (PWC05-077) at pressure of 5 to 25 psi at a temperature of at least 16"C (60"F). Disconnect fuel line at inlet of
(b)
manifold, and loosen line
CAUTION:
as
OBSERVE STARTER MOTOR OPERATING LIMITS. STARTER MANUFACTURER’S MANUAL.)
(REFER
TO
With ignition system off and power control lever to CUT-OFF, carry out normal 30 second motoring run. During motoring cycle power control lever should be
(c)
moved to TAKEOFF (PT6A-6 engines). On PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20A and PT6A-20B engines the power control lever should be moved to TAKEOFF and the cut-off lever to FULL OPEN, to displace fuel from system. After
(d)
If not,
18.
motoring run, check to repeat motoring cycle
see
until
if
flushing oil is coming from opened fuel flushing oil flows from opened fuel line.
line.
(e)
Return power control lever to CUT-OFF on PT6A-6 engines. Return power control lever to IDLE and cut-off lever to CUT-OFF on PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20, PT6A-20A and PT6A-20B engines. Reconnect fuel supply line to fuel pump or oil-to-fuel heater, and inlet of dump valve.
(f)
Install all plugs, caps and covers over all openings to prevent entry of foreign material and accumulation of moisture. (Refer to Parts Catalog P/N 3015444.)
ENGINE DEPRESERVATION SCHEDULE A.
Procedure
No
(1)
0 to 7
(2)
7 to 28
(3)
28 to 90
exhaust
and
fuel
(4)
Days
depreservation required.
Days Desiccant and moisture barriers must be removed. Ensure previously sealed engine openings are reopened and are unobstructed.
91
Days Remove engine intake and humidity indicators. Depreserve engine
Days
and Over
Engine
must be
covers
together
that all
with desiccant
system.
completely depreserved
and lubrication system
serviced
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
19.
ENGINE DEPRESERVATION A.
Procedure
(1)
engine oil tank with recommended oil. (Refer to P&WC Service Bulletin No. 1001 latest issue for list of approved oils.) Fill
NOTE:
CAUTION:
(2)
Oil system does not
require any depreservation procedures.
UNDER NO CIRCUMSTANCES PERMIT PRESERVATIVE OIL TO ENTER ENGINE WHERE IT MAY COME IN CONTACT WITH THERMOCOUPLE PROBE ASSEMBLY. OIL CONTAMINATION OF HARNESS MAY CAUSE COMPLETE FAILURE OF THERMOCOUPLE SYSTEM.
Disconnect fuel line at inlet of dump valve and loosen line drainage into a suitable container.
CAUTION:
Connect aircraft fuel
(4)
With
place power
engines
All
(d)
After
carry out normal 30 seconds
engines
motoring cycle,
oil from fuel
control lever to TAKEOFF
(b) PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20, place fuel cut-off lever to FULL OPEN. (c)
to
(REFER
permit
TO
supply.
ignition system OFF, displace preservative All
required
OBSERVE STARTER MOTOR OPERATING LIMITS. STARTER MANUFACTURER’S MANUAL.)
(3)
(a)
as
check if clean fuel
system
as
follows:
position.
PT6A-20A and PT6A-20B
engines
motoring cycle.
comes
from open fuel line. If not,
repeat motoring cycle until clean fuel appears. return power control lever to CUT-OFF.
(5)
PT6A-6
(6)
PT6A-6, PT6A-6B, PT6A-6/C20, PT6A-20, PT6A-20A and PT6A-20B engines
engines
return power control lever to IDLE and cut-off lever to CUT-OFF.
(7)
Reconnect fuel
(8)
Tighten
dump valve inlet line.
all connections, torque to 90 to 100 Ib.in., and lockwire.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
GENERAL PROCEDURES
PART 2
I
SECTION 3
CLEANING
INTRODUCTION 1.
GENERAL A.
Gas turbine engine cleaning prepares engine parts for detailed inspection,thus making it easier to detect flaws and other defects. Proper cleaning procedures remove engine deposits which can cause engine component malfunctioning and also prepares surfaces for the application of various types of repair processes. Gas turbine engine cleaning can be categorized in two broad areas, namely, parts cleaning and field cleaning.
SPECIFIC PARTS 2.
FUEL AND OIL TUBES A.
Clean the exterior surfaces of all tubes by spraying with petroleum solvent (PWC11-027), and using a soft-bristled brush as necessary. Observe all normal ventilation and fire
safety precautions. Install blanking caps on open tube ends at all times. When cleaning the internal bores of tubes, take particular care that no foreign matter remains inside the tubes. 3.
OIL FILTER ELEMENT (Post-SB1118 ENGINES) A.
Conventional Cleaning Procedure
(1)
Clean oil filter element
as
central tube
rubber
openings
Inspection
for filter
cleaning frequency.)
at both ends of oil filter element with suitable size
plugs.
(b) Agitate element for (PWC11-027).
Dry
to
(electrosonic) of cleaning filter element, refer to Paragraph B., following. If these methods prove ineffective, permanent type element only should be cleaned ultrasonically at an overhaul facility, and disposable type replaced.
(a) Seal
until
(Refer
For alternate method
NOTE:
(c)
follows:
five minutes in clean, unused
element with clean, dry, filtered dry in a clean environment.
NOTE:
Do not
use
petroleum solvent
compressed air,
or
allow element to stand
dry compressed air for drying disposable type
oil filter
elements.
(d) Visually inspect
element
as
indicated in
Inspection.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(e) Repeat cleaning serviceable. Use B.
Electrosonic
(1)
Cleaning
and visual inspection, if required, until element is deemed only clean and unused petroleum solvent each time.
Procedure
Clean oil filter element electrosonically as follows: Inspection for filter cleaning frequency.)
(See Figure 2-3-1,
at each end of filter element with suitable
(a)
Plug openings plugs.
(b)
Place element in
cleaning
tank
as
shown in
TABLE 2-3-1, Electrosonic Cleaner
Figure
plastic
and refer to
rubber
or
2-3-1.
Specifications SONAC S-2
Model
AC, 60 Hz, 25W, single phase
Rating
115V
Tank
24 U.S. fluid
oz.
Aerosupport
International Inc.
Capacity
Supplier
(700 mi)
75 de la Moselle
St. Lambert, Quebec Canada J4S1W3
(c)
Pour sufficient quantity of cleaning fluid (clean, unused petroleum solvent PWC11-027 or Trichloroethane PWC11-026) in tank to a level approximately 1/4-inch below top.
(d) Operate (e)
Rotate element 180 10 minutes.
NOTE:
4.
unit for 10 minutes.
degrees tend-to-end)
in tank and operate unit for
a
further
duration should be adjusted depending on condition of element; however, for optimum results, cleaning solvent should be replaced every 20 minutes.
Cleaning
element from tank and
(f)
Using clean, lint-free gloves,
(g)
Allow element to stand in clean environment until
(h)
Inspect
(i)
Store element in
element
as
remove
detailed in
remove
plugs.
dry.
Inspection. Repeat cleaning cycle
as
necessary.
polyethylene bag.
AIR INLET SCREEN
A.
is dirty, remove and clean in petroleum solvent (PWC11-027). After compressed air and dry screen thoroughly before reinstalling on engine.
If air inlet
screen
cleaning,
use
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FILTER ELEMENT ELECTROSONIC CLEANER PLUGS AT BOTH ENDS
O
Ii
5
CLEANING
SOLUTION
C6289A Electrosonic Cleaner
Figure
Oil Filter Element 2-3-1
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
5.
GLOW PLUGS (Pre-SB1429) A.
Cleaning (1)
Clean the exterior surfaces of the glow plugs with solvent (PWC11-027) (PWC11-031). Dry with clean low pressure compressed air.
(2)
Remove carbon
Immerse the element end of the glow (PWC11-021), for 10 to 30 minutes.
(a)
(b) Carefully
remove
plug
the loosened carbon
Rinse the element end of the
(c)
as
follows:
in Turco
Super
Carb
Compound
DO NOT USE ABRASIVE BLAST OR HIGH PRESSURE COMPRESSED AIR TO CLEAN THE ELEMENT. SUCH USE CAN CAUSE IRREPAIRABLE DAMAGE TO THE COIL.
CAUTION:
pressure
compressed
plug
using
a
soft
in hot water and
nylon
dry
brush.
with clean, low
air.
SPARK IGNITERS (Post-SB1429) A.
Cleaning
CAUTION:
7.
from the coil element
CARBON REMOVING COMPOUND IS TOXIC AND CAUSTIC. EXERCISE ALL PRECAUTIONS TO PREVENT CONTACT WITH SKIN AND EYES, AND INHALATION OF VAPORS.
WARNING:
6.
deposits
or
DO NOT CLEAN THE NOSE (FIRING) END OF IGNITERS. DO NOT REMOVE CARBON FROM ELECTRODES OR FROM ANNULAR GAP AREAS. CARBON DEPOSITS IN THE GAP AREA ACT AS AN AID IN IGNITER OPERATION.
(1)
Using a felt swab, soaked in isopropyl alcohol (PWC11-014) (PWC11-031), clean the terminal well and contact pin.
(2)
Dry using clean, dry compressed air.
or
engine
cleaner
IGNITION EXCITER (Post-SB1429) A.
Cleaning (1)
Remove all corrosion residue
(2)
Clean affected surfaces
a
stainless steel wire brush.
thoroughly using (PWC 11-022) methyl-ethyl-ketone
CAUTION:
(3)
using
a
clean lint-free cloth moistened with
DO NOT ALLOW ANY LUBRICANT TO COME IN CONTACT WITH CENTRAL CONDUCTORS OF EXCITER CONNECTORS. CONTACT WITH CONDUCTORS MAY RESULT IN A HIGH RESISTANCE PATH WHICH COULD GENERATE HEAT AND OXIDATION.
Apply light
film of fluorocarbon spray lubricant
(PWC06-005)
to cleaned areas.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
3.
FUEL MANIFOLD ADAPTER ASSEMBLIES A.
I
Cleaning WARNING:
CARBON REMOVING COMPOUND (MAGNUS AERO-DIP)(PWC11-O1 3) IS TOXIC AND CAUSTIC AND MUST BE HANDLED WITH EXTREME CARE. AVOID ALL DIRECT CONTACT WITH SKIN OR CLOTHING. PREVENT CONTACT WITH EYES AND AVOID INHALATION OF VAPOUR. COMPOUND CAN BE FATAL IF SWALLOWED. IF CONTACT WITH EYES OR SKIN OCCURS, WASH AFFECTED AREAS THOROUGHLY FOR 15 MINUTES WITH WATER AND RINSE WITH SATURATED BORIC ACID SOLUTION. IF ACCIDENTLY SWALLOWED, GET MEDICAL A~ENTION IMMEDIATELY. CONSULT WITH PHYSICIAN AS RAPIDLY AS POSSIBLE FOR ALL CONTACT CASES.
CAUTION:
ONLY USE RECOMMENDED (ALKALINE) SOLUTION (PH7). SOLUTIONS WITH A PH VALVE LOWER THAN 7 (ACIDIC) MAY CAUSE FUEL NOZZLE DAMAGE.
(1)
The
following equipment
is
required
to
thoroughly
clean
complete
or
partial
assemblies:
(a) Perforated Stainless step (b). CAUTION:
(b)
Steel Container
Local manufacture to suit
operation
with
OBSERVE FIRE SAFETY PRECAUTIONS AT ALL TIMES WHEN PROCEDURES INVOLVE USE OF FUELS OR SIMILAR COMBUSTIBLES. WEAR CLEAN, LINT-FREE COTTON GLOVES AT ALL TIMES WHEN HANDLING COMPONENTS, FINGERPRINTS ON ORIFICE OF NOZZLES AND SHEATHS MAY PRODUCE A POOR SPRAY PATTERN.
Ultrasonic cleaner, ModelT21
(Product Code 317)
or
Model T14
(Product
Code
311). NOTE:
It is not the intention of P&WC that individual operators actually purchase the ultrasonic cleaner listed, although it may be obtained from the following addresses if so desired. P&WC suggest that operators contact suitable maintenance facilities having this or similar equipment for most effective fuel nozzle cleaning.
L& R Manufacturing Co. 577 Elm Street
Kearny,
NJ 07032
USA L
R Ultrasonics Ltd.
45 Clairemont Rd.
Wealdstone, Harrow, Middlesex HA3 7AV
England (c)
Fuel Noule Flow Fixture
(d)
Test
(PWC30521).
Rig (PWC30506).
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL INLET FIT~NG SItE TO SUIT EXISTING EQUIPMENT
(STAINLESS STEEL)
0.50 IN. TO 0.625 IN. DIA. (TO SUIT FITTING)
71NCHES
I
___
DRILL AND TAP 0.250 IN. X 32 UNEF
DRILL 6.75 IN. DEEP
14 PLACES
TAP TO SUIT 1.50 IN. X1.50 IN. BAR STOCK, OR 1.50 IN. DIA. STOCK STAINLESS STEEL
FITTING
C3312A
Flushing
Fixture
(Fuel Noules)
Figure
2-3-2
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(e) Flushing (2)
Clean
Fixture
complete
Local manufacture
manifold
adapter
(see Figure 2-3-2).
assemblies in the
following
manner:
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Place as many container.
(b)
Heat solution of approximately two pints of carbon removing compound (PWC11-013, 2 Ibs per US gal, water) to approximately 95"C (200"F) and pour into tank of ultrasonic cleaner.
NOTE:
adapter
perforated stainless steel
(a)
assemblies
Subsequent operation (140"F).
as
possible
in
of cleaner will maintain solution at
approximately
60"C
(c)
Place container, with adapter assemblies in cleaner tank, completely immersed in compound.
ensuring
all
adapters
are
(d)
(e)
Cover tank and activate ultrasonic cleaner for
one
hour.
Remove container from tank and wash assemblies
thoroughly
in very hot
water.
FLUSHING MUST BE ACCOMPLISHED IMMEDIATELY FOLLOWING CONCLUSION OF CLEANING PROCESS TO AVOID DAMAGE TO ASSEMBLIES BY RESIDUAL CARBON REMOVER SOLUTION.
CAUTION:
(f)
To
ensure
as
follows:
1
Using
removal of residual solution from inside
adapter assemblies, proceed
Fixture (PWC30521) and appropriate blanking tube (refer to flow clean, very hot water through assembly at normal
,)noipsig, tcepsnI.noitarud for at least
pressure, up to 30
2
Remove
3
Dry
blanking plug
assemblies
from
one
Part, tap
minute
adapter.
thoroughly using clean,
filtered
compressed
air
or
nitrogen.
out leakage and functional checks of manifold adapter assemblies detailed in Part 3, Removal and Installation, and Inspection, respectively.
(g) Carry (3)
Clean fuel nozzles removed from manifold adapters in the
(a) (b)
Refer to
Subparagraph (1)
3
for list of
following
as
manner:
equipment.
Place nozzle in perforated stainless steel container and carry out cleaning detailed in Subparagraph (2), steps (b) to (e), inclusive.
procedure
FLUSHING MUST BE ACCOMPLISHED IMMEDIATELY FOLLOWING CONCLUSION OF CLEANING PROCESS TO AVOID DAMAGE TO NOZZLES BY RESIDUAL CARBON REMOVER SOLUTION.
CAUTION:
(c)
Install noules on flushing fixture all positions are not filled.
(d) Using water to 30
a
suitable
through psig.
adapter
(Figure 2-3-2).
Use suitable
blanking plugs
if
hose connected to flushing fixture, flow clean, ve~y hot one minute at normal tap water pressure up
nozzles for at least
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(e)
Disconnect water
supply
filtered, compressed air
from fixture and connect fixture to a supply of clean, nitrogen. Ensure nozzles are thoroughly dry.
or
(f)
With nozzles still installed on fixture, connect fixture to Test and flow fuel through nozzle for one ri~inute at 30 psig.
Rig (PWC30506),
(g)
Remove noule from
adapters. (Refer
Part 3, Removal and NOTE:
If nozzles
flushing fixture Installation).
are
container to
not
and install
on
manifold
required for immediate installation,
prevent exposure
to
store in covered
to dirt and dust.
out leakage and functional checks of fuel nozzles as detailed in Part 3, Sections Removal and Installation, and Inspection, respectively.
(h) Carry (4)
Clean manifold
(a)
(b)
Refer to
9.
for list of
manner:
stainless steel container and carry
Pressure wash parts thoroughly to remove residual compound under very hot running water for at least one minute. Ensure adequate water flow is maintained through intemal bores of adapters. Remove any loose carbon build-up from sheaths by scrubbing with non-metallic bristle brush. all parts
thoroughly
with clean filtered
compressed
air
or
nitrogen.
Assemble manifold adapters, nozzles and sheaths (refer to Part 3, Removal and Installation) and carry out leakage and functional checks as detailed in Part 3, Sections Removal and Installation, and Inspection, respectively.
FUEL PUMP INLET SCREEN A.
Cleaning (1) (2)
Agitate or rotate inlet screen compressed air jet regulated Inspect screen
NOTE:
petroleum solvent (PWC11-027). Dry using psig.
a
clean
at 15
particularly around thoroughly clean.
screen,
is not
in
the inside
diameter, and repeat Step (1) if
Replai~e screen with serviceable unit if screen repeating process, or if there is evidence looseness or corrosion on inspection.
after
10.
following
equipment.
adapters and sheaths in perforated cleaning time to 30 minutes.
(d) Dry (e)
Subparagraph (1)
Place out
(c)
in the
adapters and nozzle sheaths
is not thoroughly cleaned of broken screen strands,
COMPRESSOR BLEED VALVE A.
Cleaning (See Figure 2-3-3) (1)
Clean
metering plug
and nozzle orifices
as
follows:
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
NOULE
a
N1ETERING PLUG
rj
1
I
C937A
Compressor Bleed Valve Figure 2-3-3
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(a)
Cut lockwire and
(b)
Wash
plug
remove
and nozzle in
dowel to clear apertures.
(c)
Insert nozzle into valve
and nozzle.
metering plug
petroleum solvent (PWC11-027). Use a wooden Dry nozzle and plug in a compressed air jet.
body, tighten
and torque
(Ref.
No. 971, Fits
Clearances) metering plug, tighten
(d)
Install
and torque
(e)
When bleed valve is disassembled for
(Ref. 952,
Fits
Clearances).
diaphragm replacement,
components of valve in petroleum solvent (PWC11-027). Use clean apertures. Dry thoroughly with filtered compressed air. 11.
clean all
wooden dowel to
CHIP DETECTOR A.
Cleaning DO NOT IMMERSE CHIP DETECTOR IN SOLVENT.
CAUTION:
12.
a
(1)
Using
(2)
Ensure detector is free of metal
(3)
If not
a
stiff brush
Conventional
(1)
spray, clean
required immediately,
P3 FILTER ELEMENT A.
or
chip detector with petroleum solvent (PWC11-027).
particles
and
dry
with clean,
store detector in clean
dry compressed air.
plastic bag.
(Post-SB1294)
Cleaning
Procedure
Clean P3 air filter element
as
follows: (Refer to Inspection for filter cleaning
frequency) NOTE:
For alternate method
(electrosonic)
of
cleaning
refer to
Paragraph B.,
following. (a) Agitate element (PWC11-027).
(b)
Allow element to drain and
(c)
Inspect
element
(d) Repeat cleaning serviceable. Use B.
Electrosonic
(1)
for five minutes in clean, unused
as
dry
in
a
only
solvent
clean environment.
indicated in Part 3,
and visual
petroleum
inspection,
Inspection. if
clean and unused
required, until element is deemed petroleum solvent each time.
Cleaning Procedure
Clean air filter element electrosonically as follows: Inspection for filter cleaning frequency.)
(See Figure
2-3-4 and refer to
Page
2-3-10
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
P3 AIR FILTER
CLEANING SOLVENT
ELEMENTS
(TYP.)
5’a"
Id~a ab
oTF
a
I~
ELECTROSONIC CLEANER
C7140E P3 Air Filter Element Figure 2-3-4
Electrosonic Cleaner
(Typical)
Page
2-3-11
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(a)
Place element
in
vertically
cleaning
tank
or
suitable
low-frequency
sonic
cleaner, generating less than 10 kHz, with open end of element
at bottom
position.
(b)
Pour sufficient quantity of cleaning solvent (either petroleum solvent PWC11-027 Trichloroethane PWC11-026), into tank to a level approximately 1/4 inch below top. or
cleaner for ten
(c)
Operate
(d)
Turn element 180
(e) Operate cleaner (f)
NOTE:
(5)
end of element at
(5)
top).
minutes.
original position
cleaner for five
Cleaning
minutes.
degrees (open
for five
Turn element to
(g) Operate
(10)
(Refer step (a)).
in tank
minutes.
duration should be
adjusted
to suit condition of filter element.
However, for optimum results, cleaning solvent should be replaced every 20 minutes.
(h) Wear clean, lint-free gloves, and
(i)
Allow element to drain and
(j)
neces ary.Inspect
(k)
Store element in clean
element
as
dry
in
remove
a
element from tank.
clean environment.
detailed in Part 3,
Inspection. Repeat cleaning cycle
polyethylene bag
until
as
required for installation.
FIELD CLEANING 13.
GENERAL A.
Sulphidation
is
a common name
components of gas turbine
for
a
type of hot
corrosion which
can
affect turbine
area
engines.
B.
Sulphates form at engine operating temperatures with sodium and sulphur present. Most aviation turbine fuels contain sulphur in sufficient amounts for sulphidation. Common sources of sodium are seawater, atmospheric pollutants and volcanic discharges.
C.
Sulphidation attack most often affects the first-stage turbine blades, but, sulphidation of shroud segments and other non-rotating components is not uncommon.
D.
Degradation of the aluminide coating applied alloy. Post coating strip inspection may rejected
base
E.
Sulphidation
attack
can
generally
to CTT blades will involve some loss of the
reveal
a
be divided into four
majority
of components be
stages:
Page
2-3-12
Feb 01/2002
WHITNEY CANADA PRATT MAINT~NANCE MAkUAL MANUAL PART NO. 3015442
F.
Stage
by
some
Mechanical G.
Stage
Coating Deterioration (Sulphidation): Slight roughening of growth and localized breakdown of the oxide scale layer integrity is not affected.
Initial
1
caused
2
Initial Corrosion:
Roughness of surface is more marked integrity is not affected.
as
the surface
is evident.
oxide
layer
breakdown continues. Mechanical H.
Stage 3 Advanced Corrosion: Oxidation of the base material has penetrated to significant depth, with obvious build-up scale. Integrity seriously affected. Progression stage
i.
to
4 will accelerate.
Stage
4
Failure is
Severe Corrosion: Deep penetration of attack with likely due to loss of structural material.
large
"blister" of scale.
stages of attack may be encountered, although stages 3 and 4 will limited to those engines which are directly exposed to salt water.
J.
All
K.
Minimizing Attack Desalination wash attack.
using plain
During stages
water with
an
anti-freeze
normally
agent if required
1 and 2 the wash will dissolve and carry away
be
minimizes
sulphates
on
component surface.
washing must be free from contamination, in most Otherwise demineralized water should be used.
Water used for
acceptable.
is
Washfrequency depends on the amount acceptable. Maritime areas flight. the minimum
Recommended wash frequency is base refer to Table 2-3-3.
cases
drinking
water
Washing weekly is probably require washing daily or before each
of contamination. may
on
operators estimate of corrosion environment
or
L.
Borescope Inspection
establishing wash frequency is to monitor blade condition using borescope. Wash schedule should be adjusted according to results.
An alternative method of a
If sulphidated blades continue in service, a borescope inspection program should be started. This program should continue until a reliable progression rate for the particular circumstances can be established and a blade life limit determined. The recommended inspection interval is 200 hours. Blade lives established this way should be reviewed periodically to account for possible changes in the factors affecting
sulphidation. M.
Two
points
Stage
of
important
sulphidation
Estimate of N.
are
to consider when
evaluating sulphidated
blades.
attack.
progression
rate to
stage
3.
stage 3 mechanical integrity is jeopardized and blades should be removed from service. When estimating progression beyond stage 1 or 2 exposure to contamination and improvements in wash programs should be taken into account. At
Page
2-3-13
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
14.
INTERNALWASH A.
General
(1)
There
three
are
types
of internal wash:
(a) Compressor desalination is used to remove salt deposits, however light dirt deposits may also be removed. Wash medium is drinking water, provided minimum standards are met (Ref. Para. 19. following).
(b)
Turbine desalination wash is used to remove salt deposits from compressor turbine blades, wash medium same as for compressor wash. It is strongly recommended this environment. NOTE:
procedure
be carried out when
operating
in
a
salt laden
When desalination washes are performed in conjunction with each other it is essential that compressor wash is carried out first.
(c) Compressor performance recovery wash uses approved chemical additives remove more stubborn deposits which cannot be removed during normal
to
desalination washes. WARNING:
UNDER NO CIRCUMSTANCES MUST RUNNING WASHES BE PERFORMED WHEN USING A WAND OR A MODIFIED SPRAY RING WITH A FLOW RATE EXCEEDING 0.5 GPM (1.9 i/min). RUNNING WASHES MUST ONLY BE USED IN CONJUNCTION WITH A SPRAY RING NOT EXCEEDING A FLOW RATE OF 0.5 GPM
CAUTION:
BEFORE INTERNAL WASH, DISCONNECT P3 LINE AT CENTER FIRESEAL MOUNTING TESTING POINT (SEE FIGURE 2-3-5) AND CAP OPENINGS. AFTER WASH COMPLETED, CONNECT P3 LINE, REFER TO SECTION 6, TESTING, PARAGRAPH 49.
(d)
Internal washes performed while engine is motoring are described in Paragraph 19. 20. and 21. following, and washes performed while running in Paragraph 22.
(e) Washing
fluids
sprayed into the engine intake either through a low flow (0.5 I/min) spray ring if engine is running, or through a wash wand or gpm flow (2 to 3 gpm or 7.6 to 11.3 I/min) spray ring if motoring. When running, high is 60% approx.; this speed is chosen to ensure that emulsified fluid set at Ng hits the blades in liquid form. Too high a speed could vaporize the emulsion due to temperature rise and render it much less effective. Washing during a motoring cycle ensures that emulsion fluid remains in liquid form. or
15.
are
1.9
INTERNAL WASH METHODS A.
General
(1)
The two methods of
(a)
While
performing
motoring engine with
internal washes starter
are as
follows:
only.
Page
2-3-14
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ii
I
PT6A-20A AND PT6A-20B
OBT’
CONNECT AIR SUPPLY AT THIS POINT
C1851B Pressure
Testing
Fuel Control Pneumatic
Figure
System
2-3-5
Page
2-3-15
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Motoring wash is carried out at an Ng of 10% to 25% and the water or the cleaning mixture, depending on ambient temperature (Ref. Table 2-3-2, following), is injected at a pressure of 30 to 50 psig (207 to 345 kPa) through a high flowing wash ring or wand.
1
kPa
NOTE: While
(b)
kilo Pascal in SI Units
running engine.
wash is carried out at approximately 60% Ng (23,000 rpm) or IDLE if lower and the cleaning mixture and rinsing solution, depending on ambient temperature (Ref. Table 2-3-3, following), is injected at a pressure
Running
1
of 17
1
psig (117
7
kPa) through
a
low flow wash
ring.
TABLE 2-3-2, Rinse Solution Formulation
Water See NOTE)
Ambient Temperature
Methanol
"C
"F
by
+2 up
+36 up
100
-25 to +2
-12 to +36
50
50
Below -25
Below -12
40
60
NOTE: 1.
Drinking quality water only is recommended
is
vol.
by
vol.
permitted for motoring wash. However, demineralized water performing running wash. Refer to Equipment Required
when for acceptance criteria.
TABLE 2-3-3,
Ambient
+2
Cleaning Agent NOTE 1)
Temperature "F
"C
Up
by
+36
Cleaning
Up
vol.
Solution Formulation Aviation Kerosene
Methanol
Water
(NOTE 2)
(AMS 3004)
(NOTE 3)
by
vol.
by
vol.
by
vol.
25
Nil
Nil
75
-25 to +2
-12 to +36
25
15
20
40
Below -25
Below -12
25
15
40
20
Typical mixture proportions using B 8 B 3100 (PWC11-001C) or TC-100 (PWC11-003E), at amb. temp, of -25"C to +2"C: (Similar proportions for Magnus 1214 (PWC11-001B), R-MCS (PWC11-001D), R-MC G21 (PWC11-001E), ALMON AL-333 (PWC11-001A), TURCO 5884 (PWC11-001G) and CLIX (PWC11-001).
EXAMPLE:
B
B 3100 25%
Kerosene 15%
by
by
vol.
vol.
Methanol 20% by vol. Water 40%
by vol.
1250 mi in 5 liters
(1.33 US Gallons)
750 mi 1000 mi
2000 mi
Page
2-3-16
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-3-3,
Ambient
"F
Total 100%
by
vol.
Solution Formulation
Cleaning Agent NOTE 1)
Temperature
"C
Cleaning
by 5000 mi
or
5 liters
Aviation Kerosene
Methanol
Water
(NOTE 2)
(AMS 3004)
(NOTE 3)
vol.
(1.33
by US
(Cont’d)
vol.
by
vol.
by
vol.
Gallons)
NOTE: 1. Use any cleaning agent listed (Ref. CONSUMABLE MATERIALS). Solution strength must be in accordance with manufacturer/supplier’s recommendations. Where no specific instructions are provided, proportion of cleaning agent should be as indicated.
NOTE: 2. Use of emulsifying agent recommended to prevent NOTE: 3.
(PWC05-005A), 3% by vol. or 150 possibility of kerosene separation.
mi in 5 liters is
highly
permissible for motoring wash procedures. However, only is recommended when performing running wash. (Ref. Equipment required, for acceptance criteria.)
Drinking quality
water is
demineralized water
16.
RECOMMENDED WASH SCHEDULE on the operating environment, the nature and recommended to be in accordance with Table 2-3-4.
Depending
TABLE 2-3-4, Environment
frequency
of compressor wash is
Wash Schedule Recommendations
Wash
Frequency
Remarks
Continuously
salt laden
Desalination
Daily
Strongly recommended last flight of day.
Occasionally
salt laden
Desalination
Weekly
Strongly recommended. Adjust interval to suit engine condition
Performance
100 to
Recovery
200 hours
recommended. Performance recovery washes are required less
All
after
Strongly
frequently. Adjust frequency to suit engine operating conditions as indicated by ECTM. Motoring wash for light soiling and multiple motoring washes for heavy soiling is recommended. NOTE: 1.
Multiple motoring washes should be done to the extent permitted by operating limitations. Observe starter cooling period (Ref. Starter Manufacturer’s Manual).
starter
Page
2-3-17
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
17.
EQUIPMENT REQUIRED A.
General
(1)
The
following equipment for motoring wash or running (See Figures 2-3-6, 2-3-7 and 2-3-8)
wash is
required
as
indicated.
NOTE:
A wash cart, (PWC32677-300), is available. For further information, contact Customer Support Services (refer to 1-1-5).
(a) Spray 1
wash
Motoring
For
and wand:
rings
CAUTION:
Wash DO NOT USE ANY RESTRICTOR WHEN PERFORMING MOTORING WASH. HOWEVER, USE A RESTRICTOR TO REGULATE FLOW WHILE PERFORMING A RUNNING WASH.
Wash wand
a
(refer
to
Figure 2-3-7).
Flow rate 2 to 3 gpm
(7.6
to 11.3
I/min). Modified wash
b
to 11.3
1
Running
For
a
(b)
a
(7.6
(1.5
to 1.9
I/min)
gallon (19 liters) capacity each, capable of psig (345 kPa) working pressure.
Two stainless steel containers, 5 up to 50
Mechanical agitator, or recirculation agitation. (Refer to Figure 2-3-6).
(d) Compressed (e)
Flow rate 2 to 3 gpm
restrictor
withstanding (c)
Figure 2-3-8).
ring
Flow rate 0.4 to 0.5 gpm Use
to
restrictor.
Wash
wash
Optional
ring (refer
Use
I/min)
A
source
air
or
pump with relief valve, for moisture
nitrogen supply, regulated
up to 50
psig (345 kPa).
of demineralized water. Criteria for demineralized water should be
as
follows:
1
Appearance: free of suspended
2
Total solids: 10 ppm
3
Specific
4
Silica content: 3 ppm
5
pH
6
Intake filter not
(mg/l)
solids
max.
conductance: 11 micromhos/cm
(mg/l)
max.
max.
value: 5.0 to 7.5 inclusive. coarser
than 10 microns.
Page
2-3-18
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AGITATOR
CLEANING SOLUTIONSISTEEL TANK 5 U.S. GALS.
(19 LITERS)
CAPACITY WORKING PR. 50 P.S.I. AIR SUPPLY VALVE
PRESSURE
(345 kPa) SHUT-OFF VALVE
GAGE
I
XYALVE
XVALVE RELIEF VALVE TO SPRAY RING OR WASH WAND CONNECTION
AIRINITROGEN RECIRCULATION
PRESSURE SOURCE
PUMP
REGULATED UP TO 50
P.S.1.(345 kPa)
AIR SUPPLY VALVE
RINSE SOLUTION TANK 5 U.S,
SHUT-OFF VALVE
GALS.(l9 LITERS)
CAPACITY WORKING PR. 50 P.S.I.
(345 kPa) S/STEEL
C3974B
Compressor Wash Rig Schematic Figure 2-3-6
Page
2-3-19
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
17 HOLES 1/16 DIA.
DRILL, EQUALLYSPACED
LENGTH AND ANGLE OF THIS PORTION
TO BE DETERMINED BY AIRCRAFT INSTALLATION
10" SECTION
A-A
t,,,.
SOLDER/J
SOLDERsoLDER
STD. 112 DIA. FEMALE/ HOSE CONNECTION
DIMENSIONS ARE IN INCHES
3
A-
SOLDER
Io´•~:‘
12
DIRECTION OF SPRAY
ALL FITTINGS ARE STD. 112 DIA.
TEES, ELBOWS 6 CAPS
MATERIAL 1/2 DIA. HARD DRAWN COPPER PIPE
STANDARD 112 DIA.
B,
HOSE CONNECTION
17 HOLES 1M6 DIA. EQUALLY
STANDARD 112
CAP// C1B´•
SPACED TO SPRAY RADIALLY INWARD
8.5 R. TO FIT SCREEN
SECTION
ALTERNATE CONFIGURATION
B-B
DIMENSIONS ARE IN INCHES MATERIAL: 112 DIA. SOFT COPPER WATER PIPE
NOTE
THIS SKETCH IS INTENDED AS A GUIDE ONLY. ALL DIMENSIONS ARE APPROXIMATE AND
ALTERNATE MATERIALS MAY BE USED AS AVAILABLE.
C3972
Water Wash Wand
Figure
2-3-7
Page
2-3-20
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
MS 24402-6 TEE DO NOT USE RESTRICTOR
30" 40"
25"
Y 350
35
45
65"
40"
45"
K~\\
1
65"
8.640" R. 90´•
1A
85
(REF.)
A
I
70"
90"
95"
95
100"
100"
_C’9"" 1100
8.640" R.
(REF.)"""""""""""""""""""""""""""""""""""""""""""""""""‘~105 110"
115´;15~1 130"
135~
I
h’
\135"
130"
1’";J140" 1
150"
0.052-0.057 DIA.
50HOLESLOC. WITHIN 0.030 R. OF TRUE POS.
EXISTING 6 HOLES ADDITIONAL 44 HOLES DO NOT BREAK SHARP EDGES UNSCREW RING-HALVES AT TEE, FLUSH TO REMOVE SWARF, AND REASSEMBLE. SECTION
A-A C5383
Modification to
Existing Wash Ring Figure 2-3-8
Page
2-3-21
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(f)
Drinking
water
criteria
quality
(for Motoring
free of visible extraneous
1
Appearance:
2
Total solids: 175 ppm
3
pH
4
Chlorides: 15 ppm
5
Sulfates: 10 ppm
(mg/l)
Wash
ONLY)
should be
as
follows:
impurities.
max.
value: 6.0 to 8.0 inclusive.
NOTE:
Since
(mg/l)
(mg/l)
drinking
max.
max.
water
quality varies from place to place provided as a guide only.
and
season
to season, this criteria is
(g)
One pressure gage located in air
(h)
Two air
(i)
Two fluid shut-off valves.
(j)
Suitable
supply
tubing
to be 5/16-inch
(k)
delivery
line.
valves.
to interconnect
(8 mm)
components, valve and tubing connections
are
ID minimum.
Two flow control valves, for
use
with recirculation pump.
(Ref. Figure 2-3-6);
i,.
The
cleaning
and rinse solution formulation is
temperature and must be 2-3-7.
prepared
dependent upon the prevailing ambient in accordance with Tables 2-3-2, 2-3-3, 2-3-5,2-3-6 and
INTERNAL WASHES 19.
ENGINE MOTORING WASH A.
Procedure
(1)
(See Figure 2-3-6)
Depending on the ambient temperature, fill the wash tanks with appropriate mixture (refer to Tables 2-3-2 and 2-3-5). Alternatively, connect suitable hose to drinking water tap for ambient temperature above +2"C (+36"F). TABLE 2-3-5, Rinse Mixture
Quantity Requirements
Quantity
of Mixture
Wash Method
Liters
U.S. Gallons
Motoring
10
2.66
Running
15 to 19
4 to 5
Page
2-3-22
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-3-6,
Cleaning
Mixture
Quantity Requirements Quantity
of Mixture
Wash Method
Liters
U.S. Gallons
Motoring
5
1.33
Running
13 to 15
3.5 to 4
TABLE 2-3-7,
Cleaning Agents
TRADE NAME
SPECIFIC INSTRUCTIONS
Magnus
Refer to Table 2-3-3
1214
Refer to Table 2-3-3
B&B 3100
P&WC
W.C.T.
2
Developed
parts Witconate
P10-59B 4 1
R-MCS
R-MC G21
or
parts Carbitol part Triethanolamine
Refer to Table 2-3-3
Almon At-333
Refer to Table 2-3-3
Turco 4217
Mixture formulation
(Concentrate)
(5 liters)
Ambient
Temperature
(ml)
Turco
Kerosene
(ml)
Methanol
(ml)
Water Total
(ml)
(ml)
Below -25"
Above
-25 to
+2 C
+2"C
200
200
200
2000
2000
2000
1000
1800
2800
1800
1000
5000
5000
5000
Above +5 C
-5 to +5"C
-5 to +21"C
Below -21"C
1000
1000
1000
1000
0
1000
1600
2000
4000
3000
2500
2000
Add 150 mi Witconate and shake well. Ardrox 625
Same
as
for Turco.
(Concentrate) CLIX
Refer to Table 2-3-3
Zok27
Mixture formulation
(5 liters) Ambient Fluid
Temperature
(ml)
Methanol Water
(ml)
(ml)
Page
2-3-23
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-3-7,
Cleaning Agents (Cont’d)
TRADE NAME
SPECIFIC INSTRUCTIONS
Total
5000
(ml)
5000
Ardrox 6345/6367
Same
as
for Zok 27
Turboclean 2
Same
as
for Zok 27
(2)
5000
5000
Connect compressor air supply, regulated to 30 to 50 psig to wash tanks. In the tap water is used, connect through centrifugal pump if water pressure is below 30 psig.
event
(3)
engine cowlings, as applicable, (Ref. Aircraft Maintenance Manual) engine inlet screen and install wash wand or modified wash ring and 2-3-8). 2-3-7 (Ref. Figures Remove
or
open
to expose
CAUTION:
CONTAM I NATION/BLOCKAG E OF TH E FCU PN EUMATIC SECTION OR THE P3 FILTER WILL AFFECT ENGINE PERFORMANCE AND HANDLING. REMOVE AIR TUBE FROM ENGINE BEFORE MOTORING WASH.
CAUTION:
SPECIAL CARE SHOULD BE TAKEN WHEN PERFORMING A COMPRESSOR WASH TO ENSURE THAT THE P3 LINE IS COMPLETELY REMOVED TO AVOID BENDING STRESS OF ONE COUPLING.
(4)
Remove front air tube from engine´•to prevent distortion of tube Removal/installation of Electrical Connector).
(5)
Connect wash
ring
or
wand to
pressurized tanks,
or
to
drinking
(Ref.
water
tap,
as
applicable. prevent precipitation of deposits through inadvertent use of hard water, allow the engine to cool off to below 65"C (150"F). Minimum duration for cooling off to be 40 minutes since engine last operated.
NOTE:
(6)
To
Ensure
CAUTION:
and aircraft bleed air
ignition
are
OFF.
DO NOT MOTOR FOR MORE THAN 30 SECONDS, AND OBSERVE STARTER COOLING PERIOD (REFER TO STARTER MANUFACTURER’S MANUAL). WHEN USING WATEWALCOHOL SOLUTION, CARRY OUT AN ADDITIONAL 30-SECOND DRY MOTORING RUN BETWEEN STEPS (10) and (11), FOLLOWING, TO PURGE THE ENGINE OF VOLATILE FUMES. ENSURE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED FOLLOWING THIS ADDITIONAL STEP.
(7)
Motor
engine (starter only).
(8)
When
Ng
(9)
Stop motoring
reaches 5%,
inject
wash mixture
or
water into
engine,
as
applicable.
after 30 seconds.
(10)
Close tank valve
(11)
Observe starter
as soon as
Ng
falls to 5%.
cooling period (Ref.
Starter Manufacturer’s
Manual).
Page
2-3-24
Jun 06/2003
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(12)
Install front air tube NOTE:
(13)
Remove wash wand
(14)
Start
engine (Ref.
Connector).
or
ring
from inlet
screen.
Part 2, Section 6,
Engine Start), and run at 80% Ng for one completely dry engine. Check for zero air leaks at reinstalied coupling nuts during drying cycle. Check engine acceleration (Ref. Part 2, Section 6, Acceleration- Check/Adjustment). or more
to
(15)
Shut down
(16)
Install
(17)
Remove wash wand
(18)
Electrical
It is important to ensure that all solid P3 lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools (finger tight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.
minute
or
engine (Ref.
close
Maintenance
Start
engine (Ref.
Engine Shutdown).
or ring Manual).
from inlet
screen.
Reinstall
or
close
engine cowlings
Part 2, Section 6,
Engine Start), and run at 80% Ng for one completely dry engine. Check engine acceleration (Ref. Part 2, 6, Acceleration Check/Adjustment).
or more
Section
Part 2, Section 6,
engine cowlings (Ref. Aircraft Maintenance Manual).
(Ref.
minute
20.
(Ref. Removal/installation of
to
COMPRESSOR TURBINE DESALINATION WASH A.
Procedure
(1)
Depending on the ambient temperatures, fill the wash tank with appropriate mixture (Ref. Table 2-3-3). Alternately at temperatures above +2"C (+36"F) use suitable hose connected to drinking water supply.
(2)
Connect compressed air or nitrogen supply, regulated 30 to 50 psig, to wash tank(s). If drinking water supply is used, and water pressure is below 30 psig, connect through centrifugal pump.
WARNING:
(3)
(4)
RESIDUAL VOLTAGE IN IGNITION EXCITER (POST-SB1429) MAY BE DANGEROUSLY HIGH. ENSURE IGNITION IS SWITCHED OFF AND SYSTEM HAS BEEN INOPERATIVE FOR AT LEAST SIX MINUTES BEFORE REMOVING ANY IGNITION COMPONENTS. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER END FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE CABLE COUPLING NUTS. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.
Remove most accessible igniter (1, Fig. 2-3-9) and gasket (2) (Ref. Part 3, Section 2, Removal Spark Igniters and Ignition Cables) or glow plug and gasket (Ref. Part 3, Section 2, Removal Glow Plugs and Cables). Discard gasket. Install compressor turbine wash tube assembly (3, PWC32271) fingertight in igniter arrow and "RGB" on tang points towards reduction gearbox
port. Ensure inscribed and is
parallel
with
engine
center line
Page
2-3-25
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
:o´•´•
i;
i,
-X~7
I’
EBi
!jP
B´•~
I
(1
L´•~-
--er~s
i VIEW
A
C43005
Removal/lnstallation of Turbine Wash Tube
Figure
2-3-9
Page
2-3-26
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Connect
1.
Igniter/Glow Plug Gasket
3.
Wash Tube
Assembly
or
drinking
water
supply
to wash tube
assembly.
period or 40 minutes should be observed after engine Engine temperature must be below 65"C (150"F) to ensure inadvertent of hard water does not result in precipitation of deposits.
Minimum cool-down run.
use
Ensure aircraft
CAUTION:
2-3-9
2.
pressurized tank
NOTE:
(6)
Figure
DELIVERY HOSE SHOULD BE SUPPORTED TO PREVENT DAMAGE TO WASH TUBE.
CAUTION:
(5)
to
ignition
and bleed air
are
OFF.
DO NOT MOTOR ENGINE MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MAN UAL).
dry motoring
(Ref.
(7)
Carry
out
(8)
When
Ng reaches 5%, inject
(9)
Stop motoring
run
run
Part 2, Section 6,
water
or
Motoring Run).
water/methanol,
as
applicable,
into
engine.
after 30 seconds.
(10)
Shut off water dr water/methanol when
(11)
Repeat wash cycle (Ref. Table 2-3-8) as necessary to remove contaminants from compressor turbine and, if water/methanol used, carry out an additional 30 second dry motoring run. Observe same CAUTION as before.
(12)
Disconnect and
(13)
Ng
falls to 5%.
pressurized tank(s) or drinking water supply remove assembly (3) from igniter port.
from wash tube
assembly
igniter (1) with new gasket (2) (Ref. Part 3, Section 2, Installation Spark Igniters and Cables) or glow plug with new gasket (Ref. Part 3, Section 2, Installation Glow Plugs and Igniters) into igniter port.
Install
CAUTION:
OBSERVE STARTER COOLING MANUFACTURER’S MANUAL).
PERIOD
(REF STARTER
(14)
engine (Ref. Part 2, Section 6, Engine Start). Run engine approximately one minute to completely dry the engine.
(15)
Shut down
Start
engine (Ref.
Part 2, Section 6,
at 80%
Ng
for
Engine Shutdown).
Page
2-3-27
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE’ MANUAL MANUAL PART NO. 3015442
TABLE 2-3-8,
Compressor Turbine Wash Schedule Recommendations Nature of Wash
Recommended
Desalination and/or
As
environmental conditions
desulphidation
Operating
Environment
All salt water/air
Remarks
Frequency
Single wash for light contamination and multiple washing for heavy
required
contamination. 21.
PERFORMANCE RECOVERY WASH A.
Procedure
(1)
(See Figure 2-3-6)
Depending on the ambient temperature, fill the wash tanks with appropriate cleaning mixture (Ref. Table 2-3-3 and 2-3-6) and rinse solution (Ref. Tables and 2-3-5) in separate tanks.
(2)
Connect
(3)
Remove
or
Manual)
to expose
compressed open
air
supply,
30 to 50
psig
2-3-2
to wash tanks.
engine cowlings, as applicable, (Ref. Aircraft Maintenance engine inlet screen and install wash ring or wand.
CAUTION:
CONTAM INATION/BLOCKAGE OF THE FCU PNEUMATIC SECTION OR THE P3 FILTER WILL AFFECT ENGINE PERFORMANCE AND HANDLING. REMOVE AIR TUBE FROM ENGINE BEFORE MOTORING WASH.
CAUTION:
SPECIAL CARE SHOULD BE TAKEN WHEN PERFORMING A COMPRESSOR WASH TO ENSURE THAT THE P3 LINE IS COMPLETELY REMOVED TO AVOID BENDING STRESS OF ONE COUPLING.
(4)
Remove front air tube from
(5)
Connect wash
prevent distortion of tube (Ref. 3-2-70).
wand to pressure tanks.
To
Ensure
CAUTION:
or
to
prevent precipitation of deposits through inadvertent use of tiard water, allow the engine to cool off to below 65"C (150"F). Minimum duration for cooling off to be 40 minutes since engine last operated.
NOTE:
(6)
ring
engine
ignition and aircraft
bleed air
are
OFF.
DO NOT MOTOR FOR MORE THAN 30 SECONDS, AND OBSERVE STARTER COOLING PERIOD (REFER TO STARTER MANUFACTURER’S MANUAL). WHEN USING WATEWALCOHOL SOLUTION, CARRY OUT AN ADDITIONAL 30-SECOND DRY MOTORING RUN BETWEEN STEPS (11) and (12), FOLLOWING, TO PURGE THE ENGINE OF VOLATILE FUMES. ENSURE PRESCRIBED STARTER COOLING PERIOD IS ALLOWED FOLLOWING THIS ADDITIONAL STEP.
(7)
Motor
engine (starter only).
(8)
When
Ng
(9)
Stop motoring
reaches 5%,
inject
wash mixture
or
water into
engine.
after 30 seconds.
Page
2-3-28
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(10)
Close tank valve
(11)
Allow
cleaning
(12)
Motor
engine.
as soon as
Ng falls
to 5%.
solution to soak for 15 to 30 minutes. reaches 5%,
Ng
When
inject
rinse solution into
engine (half quantity
only) Observe starter
(14)
Repeat step (12),
(15)
Install front air tube
once
Starter Manufacturer’s
again observing
(Ref.
Manual).
limitations of starter.
Removal/installation of Electrical
Connector).
It is important to ensure that all solid P3 lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools (finger tight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.
NOTE:
(16)
Remove wash wand
(17)
Start
or
ring
from inlet
screen.
Engine Start), and run at 80% Ng for one completely dry engine. Check for zero air leaks at reinstalled coupling nuts during drying cycle. Check engine acceleration (Ref. Part 2, Section 6, Acceleration Check/Adjustment). Part 2, Section 6,
engine (Ref.
minute
22.
cooling period (Ref.
(13)
or more
(18)
Shut down
(19)
Install
or
to
engine (Ref.
close
Part 2, Section 6,
engine cowlings.(Ref.
Engine Shutdown).
Aircraft Maintenance
Manual).
ENGINE RUNNING WASH A.
Procedure
(1)
(See Figure 2-3-6)
Depending
on
the ambient temperature, fill wash tanks with appropriate cleaning
mixture (Ref. Tables 2-3-3 and 2-3-5) in separate tanks.
(2)
Connect
compressed
(3)
Remove
or
Manual)
to expose
open
air
2-3-6)
supply
and rinse solution
16 to 18
psig
(Ref.
to wash tanks.
engine cowlings, as applicable, (Ref. Aircraft engine inlet screen and install wash ring.
Connect wash
(5)
Ensure that aircraft bleed air is OFF.
to
pressurized
Maintenance
tanks.
(4)
ring
Tables 2-3-2 and
Page
2-3-29
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
TO ELIMINATE POSSIBILITY OF ENGINE OVER-TEMPERATURE OR OVERSPEEDING, THOROUGHLY AGITATE SOLUTION PRIOR TO INGESTION AND DURING WASH CYCLE, THUS PREVENTING SEPARATION OF KEROSENE. PREFERABLY, USE OF WITCO AS EMULSIFYING AGENT OR, ALTERNATIVELY, USE OF MECHANICAL AGITATOR OR RECIRCULATION PUMP WITH RELIEF VALVE (REFER TO FIGURE 2-3-6) IS STRONGLY RECOMMENDED.
engine (Ref. Part 2, Section 6, Engine Start, following). (23,000 rpm) or IDLE if lower.
(6)
Start
(7)
Inject cleaning solution. Flow of solution will be evidenced by decrease in Tt5 and a slight change in Ng for the mixture specified for an ambient temperature of +2"C (+36"F) up. However, flow of solution specified for ambient temperature below +2"C (+36"F) will be evidenced by a slight increase in Tt5 and a slight change in Ng. When solution supply is exhausted, Tt5 and Ng will return to prewash values.
CAUTION:
Ng
DO NOT INCREASE NG DURING RINSE CYCLE.
(8)
Inject rinse solution into engine.
(9)
On
(10)
Run at 60%
completion of rinse, increase Ng drying. Shut down
to 80% for one minute to ensure
complete
engine (Ref. Testing, following).
FUEL NOZZLE CLEANING 23.
Preparation and Cleaning A.
Equipment A wash cart
prepared NOTE:
B.
(Ref. PWC32677-100) is required. Prior to washing, the operated in accordance with the cleaning rig manual.
cart must be
and
Cleaning
should
only be initiated on new or recently cleaned nozzles as the will clear previous blockages. Clean every 200 hours. Adjust not procedure interval based on condition and experience.
Preparation CAUTION:
(1)
TURCO 5884 IS AN ALKALINE THAT CAN CAUSE SKIN IRRITATION. AVOID SKIN CONTACT.
Mixture ratios to be
as
follows:
(a)
At ambient temperatures of 2"C (35.5"F) and above, mix Turco 5884 to 4 parts demineralized water.
(b)
At ambient temperatures below 2"C (35.5"F) mix a 50% solution of methanol and demineralized water, then mix 4 parts of water/methanol (by volume) to 1 part Turco 5884.
by
volume: 1 part
Page
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Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
cnunohl:
BEFORE PROCEEDING FURTHER, MAKE SURE THAT AIR HAS BEEN RELEASED FROM RESERVOIRS. volume of
cleaning
solution
(Ref. step (1)).
(2)
Fill reservoir with
(3)
Fill rinse reservoir with appropriate volume of demineralized water or demineralized water/methanol mixture according to ambient temperature (Ref. step (1)).
(4)
Remove both gas generator drain valves from engine (Ref. Part 3, Section 2, Remove Gas Generator Case Drain Valves). Install suitable drain hoses.
(5)
fuel inlet line from flow divider and dump valve (Ref. Part 3, Section 2, Remove Fuel Dump Valve). Cap fuel inlet line and elbow on fuel dump valve.
(6)
Disconnect
Disconnect
engine
dump line from fuel dump valve outlet (Ref. Part 3, Section 2, Dump Valve).
Fuel
(7)
appropriate
Connect wash cart fluid
delivery
hose to valve outlet elbow
using adapter
"FUEL NOZZLE"
disconnect.
Remove
(0.4375-20 UNJF). (8)
Connect
rig fluid delivery
(9)
Connect
compressed air.
CAUTION:
C.
hose to
rig
quick
DO NOT EXCEED 120 PSIG.
(10)
Set wash
rig
(11)
Set
to 70
pulse
to 670
psig using
reservoir
regulator.
psig using pulse regulator.
Cleaning (1)
Let
engine
cool for
a
minimum of 40 minutes after
engine
shutdown before
cleaning
fuel nozzles.
(a)
(b)
Place valves A and B to AGITATE and valve C OFF and solution for 2 minutes. Place valves A and B to WASH and valve C to ON and
agitate detergent
detergent
wash for 3
detergent
wash for 3
minutes.
(c)
Places all valves to OFF and soak for 10 minutes.
(d)
Place valves A and B to WASH and valve C to ON and minutes.
(e)
Place all valves to OFF and soak for 10 minutes.
(f)
Places valves A and B to RINSE and valve C to ON and rinse for 6 minutes.
(g)
Places valves A and B to OFF and valve C to AIR DRY and
dry
for 5 minutes.
Page
2-3-31
Feb 01/2002
PRA~TT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(h)
Places all valves to OFF and reduce both reservoir and
pulse
pressures to
zero.
D.
Post-cleaning air
from wash cart.
(1)
Remove
(2)
Remove fluid
(3)
Reconnect
(4)
Remove
(5)
Reconnect fuel inlet line
(6)
Remove drain hose and reinstall gas generator case drain valve Section 2, Remove Gas Generator Case Drain Valves).
(7)
Perform
(8)
Clean wash cart, stow fluid
compressed
delivery hose from dump valve.
dump
blanking
an
supply
line
(Ref.
Part 3, Section 2, Install Fuel
cap at fuel inlet line and
(Ref.
engine ground
run
nipple
on
Dump Valve).
flow divider and
Part 3, Section 2, Install Fuel
check for leaks
delivery hoses,
dump
valve.
Dump Valve).
(Ref.
Part 3,
(Ref. Adjustmentl Test).
and bleed air pressure from reservoirs.
ENGINE EXTERNAL WASH 24.
General CAUTION:
DO NOT USE GASOLINE OR SIMILAR TOXIC SUBSTANCES FOR EXTERNAL CLEANING.
CAUTION:
DO NOT ATTEMPT TO WASH AN ENGINE WHICH IS STILL MOTOR RUNNING. ALLOW ENGINE TO COOL FOR A MINIMUM PERIOD OF 40 MINUTES AFTER SHUTDOWN.
A.
An external wash with fresh water is recommended when the engine is contaminated with salt, or corrosive chemicals from agricultural operations. Demineralized water is
not necessary. The engine should in a contaminated condition.
never
be left for
an
extended
period,
such
as
overnight,
B.
In the event water wash is not found effective, a petroleum solvent (varsol)/water emulsion may be used to remove oil and grime. Thoroughly rinse with water to remove all traces of cleaning fluid. Completely dry the engine using clean, dry, compressed air.
C.
External
cleaning
is found to be very effective in
tracing
the
origin
of
possible external
oil
leakage.
Page
2-3-32
Feb 01/2002
WHITNEY CANADA PRA~T MAINTENANC~ MA~UAL MANUAL PART NO. 3015442
´•I
PART 2
GENERAL PRACTICES
SECTION 4 1.
STANDARD PRACTICES
GENERAL
CAUTION:
DUST CAPS USED TO PROTECT OPEN LINES AGAINST CONTAMINATION SHOULD ALWAYS BE INSTALLED OVER THE TUBE ENDS AND NOT INSIDE. FLUID FLOW THROUGH THE LINES MAY BE BLOCKED OFF IF LINES ARE INADVERTENTLY INSTALLED WITH DUST CAPS INSIDE THE TUBE ENDS.
CAUTION:
MAKE CERTAIN THAT THERE IS SUFFICIENT PROTECTIVE MATERIAL PRESENT TO PRECLUDE THE POSSIBILITY OF DAMAGING ENGINE
PARTS. A.
The standard
B.
During the removal of tubes or engine parts, look for indications of scoring, burning or other undesirable conditions. To facilitate reinstallation, tag and mark all parts, clips and brackets to indicate their location. Route unserviceable parts and units to an overhaul facility for investigation and possible repair.
C.
Extreme
practices outlined in this section are approved by Pratt Whitney Canada. It is recommended that, when applicable, personnel engaged in the maintenance of engines make frequent reference to this section.
care must
be taken to
matter from
foreign disassembly even though or installing any part, sealing devices must
prevent dust, dirt, lockwire, nuts, washers
or
other
entering engine. If at any time such items are dropped, the or assembly process must stop until the dropped articles are located, this may require a considerable amount of time and labor. Before assembling the
ensure
that it is
be used to
thoroughly clean. Suitable caps, plugs and other protect all openings as soon as they are exposed.
D.
Use only a plastic or rawhide hammer when removing or installing engine parts. Cover critical engine parts or areas, e.g. compressor or turbine disks, with protective material to safeguard them from scratches, nicks or tool marks.
E.
Whenever adhesive tape has been-applied to any part, the tape must be removed and the part thoroughly cleaned of all tape residue with petroleum solvent (PWC11-027),
prior
being subjected to elevated temperatures during engine run. Test results indicate are capable of causing surface attack, and/or reduction in tensile ductility as temperature is increased. Do not, under any circumstances, leave tape or tape residue on engine parts. to
that all tapes
2.
PREFORMED PACKINGS, PACKING RETAINERS AND GASKETS A.
Discard all
preformed packings,-packing retainers (back-up rings) and gaskets, and replace with new parts during assembly. Ensure that correct parts are used by checking part numbers, alsoconfirm that replacement parts show no signs of damage or deterioration due to storage. Inspect all parts for burrs or sharp edges that may damage preformed packings and gaskets during subsequent assembly. Avoid the use of hardened, sharp-pointed or sharp-edged tools. Where packing retainers are to be fitted, ensure concave face of retainer faces toward preformed packing.
Page 2-4-1 Aug 27/2004
PRATT
WHITNEV CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3.
LUBRICATION OF PREFORMED PACKINGS A.
Procedure
(1)
Prior toinstallation, new O-ring type preformed packings should be coated with thin film of lubricant to the following specifications: CAUTION:
I
4.
APPLICATION OF LUBRICANT PLUS PROPER ASSEMBLY WILL PREVENT DAMAGE TO PACKINGS WHICH COULD CAUSE ENGINE MALFUNCTION.
(a) Packings
used in
engine
fuel system:
(b) Packings
used in
engine
oil
(c)
a
Lubricating
oil
(Refer
system: Lubricating oil (Refer
Packings used in engine pneumatic system, Lubricating oil (Refer to SB1001).
or
in water
or
to
to
SB1001).
SB1001).
alcohol assemblies:
ANTIGALLING AND ANTISEIZE COMPOUNDS CAUTION:
A.
ENSURE THAT ANTIGALLING AND ANTISEIZE COMPOUNDS ARE APPLIED IN A THIN EVEN COAT, AND THAT ALL EXCESS MATERIAL IS COMPLETELY REMOVED, TO AVOID CONTAMINATION OF PARTS, PASSAGES OR SURFACES WHERE THE COMPOUND MAY CAUSE MALFUNCTIONING, OR EVEN FAILURE OF THE ENGINE.
Procedure
(1)
The
following compounds
are
(a) Molykote (PWC06-036)
recommended for
specific applications:
lubricant should be used
on
all loose fit accessory
spline drives, which are external to the engine and have no other means of lubrication such as starter-generator gearshaft splines. Plastilube No. 3 lubricant may also be used if Molykote (PWC06-036) is not available.
(b) Molybdenum disulfide (PWC04-002) in either its paste form (Type G) or powdered form (Type Z) mixed with engine oil or grease may be used for turbine shaft splines and threads during assembly of these and other components which are not subjected to operating temperatures in excess of 427"C (800"F). (c)
Penetrating oil may be used to further facilitate disassembly of free turbines and other hot section parts at disassembly of these components.
Page 2-4-2 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
5.
LOCKING DEVICES CAUTION:
A.
6.
ONLY LOCKWIRE AND COTTERPINS MANUFACTURED FROM CORROSION-RESISTANT STEEL ARE TO BE USED.
Lockwire, lockwashers, tablocks, tabwashers, keywashers and cotterpins
must never be reused. All lockwire and cotterpins must fit snugly in the drilled holes provided in bolts and studs for locking purposes. Bushings and plugs must be lockwired to the boss or case. Do not lockwire the plug to the bushing. Install a cotterpin so that the head fits into the castellation of the nut and, unless otherwise specified, bend one end of the cotterpin back over the stud or bolt and the other end flat against the nut.
KEYWASHERS (TAB AND CUP TYPES) A.
Procedure
CAUTION:
NOTE:
(1)
THESE TYPES OF WASHERS MUST ONLY BE USED ONCE. NEW WASHERS MUST ALWAYS BE USED AT EACH ASSEMBLY. The terms keywasher, tabwasher and in this manual.
are
interchangeable,
used
as
Tabwashers When bending or setting the tabs on these washers (see Figure 2-4-1), do not use sharp-pointed tools. Use of such tools can lead to subsequent failure of the locking tabs which, on becoming detached, can pass through the engine
causing (2)
cupwasher
extensive
damage.
Cupwashers (a) Pre-Assembly: 1
Visually inspect cupwasher for freedom of deep drawing scoremarks (especially in the undercut adjacent to tangs) and for freedom of prior assembly/handling damage i.e. bent tangs or prior stake marks.
2
Visually inspect which may
3
(b)
contact surfaces for excessive
cause
the washer to bind
on
roughness, burrs
or scores
the nut.
Visually inspect the nut for burrs, nicks or the cupwasher which could cause the nut
scratches
on
pick
on
to
up
face which abuts the washer.
Assembly: 1
The
cupwasher
must be lubricated on the nut side
must be clean and
1
With
3
With
only,
cupwasher placed against shaft slots opposite tightening, screw nut finger-tight. a
silver
the
opposite
face
dry. to direction of nut
pencil, make an alignment mark on the cupwasher o.d. and immediately adjacent to the cupwasher not greater than
the component .020 in width.
Page
2-4-3
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C1189B
Examples
of
Locking Type Figure 2-4-1
Washers
Page
2-4-4
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
nut in the normal manner.
4
Torquethe
5
If the alignment mark has moved by an amount greater than width of the mark, remove and discard the cupwasher.
6
Repeat procedure with
Z
Stake
cupwasher, using or internal type
external NOTE:
7.
a new
equal
or
to the
cupwasher.
the proper tool, in the washer.
If nut is used to apply such torque without a foregoing instructions.
appropriate location for
seating torque to a rotor assembly, apply cupwasher installed, then proceed with the
RETAINING RINGS (SPIROLOX, ETC.) A.
Retaining rings must be installed using approved retaining ring pliers. Internal type rings compressed beyond the point where ends of the ring would meet. External type rings must be expanded only enough to allow installation without becoming bent. After installation, ensure each retaining ring is completely seated in its groove, must not be
without looseness 8.
or
distortion.
LOCKWIRE A.
Lockwire must be the same as that used during the original assembly of the engine; this part number MS9226-03, a heat and corrosion-resistant steel wire of 0.025 inch diameter to Specification AMS5687. Alternative MS9226-02 0.016 inch diameter wire is
wire, having limited application, will be specified 9.
as
required.
LOCKING PROCEDURES A.
There
are many combinations of These rules are as follows:
lockwiring
with certain basic rules
Lockwire must be vibration.
(2)
Lockwire must be installed in a manner that tends to tighten and keep in place, thus counteracting the natural tendency of the part to loosen.
(3)
installation to
prevent failure due
(1)
tight after
to all.
common
to
rubbing a
or
part
locked
Lockwire must never be overstressed. It will break under vibrations if twisted too The lockwire should be pulled taut when being twisted, but should have minimum tension (if any) when secured.
tightly. (4)
Lockwire ends must be
ends which
(5)
bent’toward
might present
Internal
wiring
method
can
a
safety
the engine or part, to avoid sharp hazard or vibrate in the air stream.
must not cross over, or
obstruct,
a
flow passage when
or
an
projecting alternate
be used.
Page
2-4-5
Feb 01/2002
PRATT
WHITN~Y CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
Check the units to be lockwired to make sure that they have been correctly torqued and that the wiring holes are properly positioned in relation to each other. When there are
units, it is desirable that the holes in the units be in the same relationship each other. Never overtorque or loosen units to obtain proper alignment of the holes.
two
or more
It should be
to
the wiring holes when the units are torqued within the if is it specified limits. However, impossible to obtain a proper alignment of the holes without either over or under-torquing, select another unit which will permit proper
alignment
10.
possible
within the
to
align
specified torque
limits.
C.
To prevent mutilation of the twisted section of wire when using pliers, grasp the wire at the ends or at a point that will not be twisted. Lockwire must not be nicked, kinked, or mutilated. Never twist the wire ends off with pliers, and, when cutting off ends, leave at least three complete turns after the loop, exercising extreme care to prevent the wire ends from falling into the engine. The strength of the material at lockwire holes is marginal; therefore, the wire should be cut, not pulled, during removal of wire.
D.
For
a typical lockwiring procedure, see Figure 2-4-2. Although there are numerous lockwiring operations performed on the engine, practically all are derived from the basic examples shown on Figure 2-4-3.
HARDWARE IDENTIFICATION A.
Correct engine reassembly procedures require that particular attention be paid to the material requirements for nuts and bolts used in the hot section of the engine. In those areas
where parts must be of material which is resistant to
high operating
temperatures, special heat-resistant alloys are employed. It is imperative that at reassembly of the engine or its components, the properly identified part (if serviceable) be reassembled in its
CAUTION:
B.
original
location.
NEVER ASSEMBLE A MATERIAL CODED PART WITH A C IDENTIFICATION IN A LOCATION WHICH REQUIRES AN H CODED PART AND VICE-VERSA.
Code systems, where used, employ the
use of the letter C for corrosion-resistant steel H and for heat-resistant application alloys in hot-section applications. The embossed letter will be followed or stamped by a number of one or more digits, e.g. C1, H3 and the the material C8, H12, digit signifying specification. Bolt code identification
for normal
usually appears on the top of the head, and nut identification on one side of the hexagon (see Figure 2-4-4). When the application is -an AN or MS six-digit part number, the code identification C or H will be preceded by the letter E, e.g. EC3 or EH10. NOTE:
All AN and MS
six-digit part numbers, when manufactured of material in the temperature range (such as cadmium plated, low-alloy, steel parts), also coded E, to indicate, in part, close material quality control.
common are
C.
adoption of this program will make it possible for service activities to avoid the assembly of parts with similar physical appearance in locations which require high heat-resistant parts. In this regard it is a requirement at time of disassembly to segregate all similarly coded parts so that two or more physically similar parts with different code numbers will not be scrambled. This will ensure that, at subsequent reassembly, the coded parts are replaced in their proper locations.
The
Page
2-4-6
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INSERT THE UPPERMOST WIRE,
WHICH POINTS TOWARDS THE SECOND 4:30 10:30
O’CLOCK
O’CLOCK
BOLT, THROUGH
THE
HOLE WHICH LIES BETWEEN THE POSITION THE HOLES.
NINE AND TWELVE O’CLOCK
POSITIONS. GRASP THE END OF THE WIRE WITH A PAIR OF PLIERS AND PULL THE WIRE
TIGHT.
BRING THE FREE END OF THE WIRE AROUND THE BOLT HEAD IN A COUNTERCLOCKWISE
INSERT PROPER GAGE WIRE.
DIRECTION AND UNDER THE END PROTRUDING FROM THE BOLT HOLE. TWIST THE WIRE IN A COUNTERCLOCKWISE DIRECTION.
GRASP UPPER END OF THE WIRE AND BEND IT AROUND THE
I
GRASP THE WIRE BEYOND THE
HEAD OF THE BOLT, THEN
I
TWISTED PORTION AND TWIST
UNDER THE OTHER END OF THE
I
THE WIRE ENDS COUNTER-
CLOCKWISE UNTIL TIGHT.
WIRE. BE SURE WIRE IS TIGHT AROUND HEAD.
TWIST WIRE UNTIL WIRE IS
DURING THE FINAL TWISTING
JUST SHORT OF HOLE IN THE
MOTION OF THE
PLIERS,
BEND
THE WIRE DOWN AND UNDER
SECOND BOLT.
THE HEAD OF THE BOLT.
KEEPING WIRE UNDER TENSION, TWIST IN A CLOCKWISE
I I
DIRECTION UNTIL THE WIRE IS TIGHT. WHEN TIGHTENED THE
CUT OFF EXCESS WIRE WITH
DIAGONAL CUTTERS.
WIRE SHALL HAVE APPROXIMATELY 7 TO 10 TWISTS PER INCH.
C194C Lockwire Procedures
Figure
2-4-2
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2-4-7
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXAMPLES
EXAMPLE1
EXAMPLES 1,2,3 AND 4 APPLY TO ALL TYPES OF
EXAMPLES
8XAMPLE4
BOLTS, FILLISTER HEAD SCREWS, SQUARE HEAD PLUGS,
AND
OTHER SIMILAR
PARTS WHICH ARE WIRED SO THAT THE LOOSENING TENDENCY OF EITHER PART IS COUNTERACTED BY TIGHTENING OF THE OTHER PART. THE DIRECTION OF
MIIST, FROM THE SECOND TO
THE THIRD
UNIT, IS COUNTER-CLOCKWISE TO KEEP THE LOOP IN POSITION AGAINST
THE HEAD OF THE BOLT. THE WIRE ENTERING THE HOLE IN THE THIRD UNIT WILL BE THE LOWER WIRE AND BY MAKING A
COUNTER-CLOCKWISE TWIST AFTER IT LEAVES THE HOLE, THE LOOP WILL BE SECURED IN PLACE AROUND THE HEAD OF THAT BOLT.
X EXAMPLE 5
~R EXAMPLE 6
EXAMPLE 8
EXAMPLE 7
EXAMPLES 5,6,7 AND 8 SHOW METHODS FOR WIRING VARIOUS STANDARD ITEMS. WIRE MAY BE WRAPPED OVER THE UNIT RATHER THAN AROUND IT WHEN WIRING CASTELLATED NUTS OR ON OTHER ITEMS WHEN THERE IS A CLEARANCE PROBLEM.
EXAMPLE 9
EXAMPLE 11
EXAMPLE 10
EXAMPLE 9 SHOWS THE METHOD
EXAMPLE 10 SHOWS HOLLOW
EXAMPLE 11 SHOWS CORRECT
FOR WIRING BOLTS IN DIFFERENT
HEAD PLUGS WIRED WITH THE
APPLICATION OF SINGLE WIRE
PLANES. NOTE THAT WIRE SHOULD
TAB BENT INSIDE THE HOLE
TO CLOSELY SPACED MULTIPLE
ALWAYS BE APPLIED SO THAT
TO AVOID SNAGS AND POSSIBLE
GROUP.
TENSION IS IN THE TIGHTENING
INJURY TO PERSONNEL WORKING
DIRECTION.
ON THE ENGINE.
C195 1
Lockwiring Examples Figure 2-4-3 (Sheet 1 of 3)
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Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
~a-o EXAMPLE13
EXAMPLE1Z
EXAMPLES 12 AND 13 SHOW METHODS FOR ATTACHING LEAD SEAL TO PROTECT CRITICAL ADJUSTMENTS.
EXAMPLE14
EXAMPLE1G
EXAMPLE15
EXAMPLE 14 SHOWS BOLT WIRED TO
EXAMPLE 15 SHOWS CORRECT METHOD
EXAMPLE 16 SHOWS CORRECT METHOD
A RIGHT ANGLE BRACKET WITH THE
FOR WIRING ADJUSTABLE CONNECTING
FOR WIRING THE COUPLING NUT ON
WIRE WRAPPED AROUND THE BRACKET.
ROD.
FLEXIBLE LINE TO THE STRAIGHT CONNECTOR BRAZED ON RIGID TUBE.
EXAMPLE 17
EXAMPLE 18
EXAMPLE 19
EXAMPLE 20
EXAMPLE 21
FITnNGS INCORPORATING WIRE LUGS SHALL BE WIRED AS SHOWN
SMALL SIZE COUPLING NUTS SHALL
IN EXAMPLES 17 AND 18. WHERE NO LOCKWIRE LUG IS
BE WIRED BY WRAPPING THE WIRE
PROVIDED,
WIRE SHOULD BE APPLIED AS SHOWN IN EXAMPLES 19 AND 20
AROUND THE NUT AND INSERTING
WITH CAUTION BEING EXERTED TO ENSURE THAT WIRE IS WRAPPED
IT THROUGH THE HOLES AS SHOWN.
TIGHTLY AROUND THE FITTING.
C195 2
Lockwiring Examples Figure 2-4-3 (Sheet 2)
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PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXAMPLE 22
EXAMPLE 23
COUPLING NUTS ATTACHED TO STRAIGHT CONNECTORS SHALL BE WIRED AS SHOWN WHEN HEX IS AN INTEGRAL PART OF THE CONNECTOR.
EXAMPLE 24 COUPLING NUTS ON A TEE SHALL BE WIRED AS SHOWN ABOVE SO THAT TENSION IS ALWAYS IN THE
TIGHTENING DIRECTION.
EXAMPLE 25 STRAIGHT CONNECTOR
(BULKHEAD PIPE)
EXAMPLE 26
EXAMPLE 27
EXAMPLE 28
EXAMPLES 26, 27 AND 28 SHOW THE VARIOUS STANDARD FITTINGS WITH CHECK NUT WIRED SO THAT IT NEED NOT BE DISTURBED WHEN REMOVING THE COUPLING NUT.
C195 3
Lockwiring Examples Figure 2-4-3 (Sheet 3)
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2-4-10
Feb 01/2002
PRATT
WHITNEY CANADA MANUAL:
MAINTENANCE
MANUAL PART NO. 3015442
C196 Hardware Code Identification
Figure
2-4-4
Page
2-4-11
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
D.
CARE MUST BE TAKEN DURING DISASSEMBLY PROCEDURES TO AVOID MIXING REDUCED PITCH DIAMETER (PD) BOLTS WITH SIMILAR SIZE STANDARD BOLTS.
engine manufacture it is the practice to use bolts with reduced pitch diameter in the hot section of the engine, to minimize the possibility of bolt and nut seizure. This practice is standard with regard to all applications where the parts are subjected to
At
elevated temperatures. To identify reduced PD bolts, check for a 120 degree depression in the threaded end of the bolt. This identifying mark must not be confused with a grinding center which is common with ground thread bolts. (See Figure 2-4-5)
METAL PARTICLES 11.
GENERAL A.
Should particles of metal be found in the fuel and/or oil strainers, they could be deposits of steel, tin, aluminum, magnesium, silver, titanium, bronze or cadmium. In some instances, the type of metal may be determined by the color and hardness of the pieces. However, when the particles cannot be positively identified by visual inspection, and knowledge of the exact character of the metal deposits is desired as an aid to
troubleshooting,
few simple tests will determine the kind deposits, refer to Paragraphs 12. and
a
unknown metal 12.
IDENTIFICATION
of metal present. To 13. following.
identify
PRE-REQUISITES A.
Equipment Required
(1)
Electric
(2)
Two
(3)
An open flame.
(4)
Permanent
(5)
Two
soldering
iron.
porcelain spot plates.
magnet.
ounces
of aqueous
(water)
solution
containing
10% ammonium nitrate
(NH,NO,). WARNING:
PERSONNEL MUST USE EXTREME CAUTION WHEN HANDLING ACIDS.
(6)
Two
(7)
Hydrofluoric acid (HF) (PWC05-004).
(8)
Sulfuric acid
(9)
Concentrated
(10)
ounces each of 50% by volume of hydrochloric acid concentrated nitric acid (PWC05-195)(HNO,).
(PWC05-004)(HC1)
and
(H,SO,) (PWC05-074). phosphoric
acid
(H,PO,) (PWC05-006).
Hydrogen peroxide (H,O,) (fresh) (3%
to 10%
solution) (PWC05-033).
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Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
120~ 0.109 0.079
REDUCED PITCH DIAMETER BOLT
STANDARD BOLT
C197B Identification of Reduced Pitch Diameter Bolt
Figure
2-4-5
Page
2-4-13
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
13.
(11)
Crystalline
(12)
Sodium
ammonium bifluoride
(NH,HF,) (PWC05-009).
Hydroxide (NaOH) (solid) (PWC05-058).
TEST PROCEDURES A.
Procedure
(1)
The following test procedures unknown metal particles: WARNING:
determining
the character of
A
test for these
simple
particles is burning. Magnesium will burn
white flash.
Particles
iron is attracted NOTE:
recommended for
NEVER ATTEMPT TO BURN MORE THAN A FEW PARTICLES OF METAL SUSPECTED TO BE MAGNESIUM. MAGNESIUM POWDER OR DUST 1S EXPLOSIVE.
(a) Magnesium with a bright (b) Steel
are
can
by
be isolated
the
by
means
of the permanent magnet. Steel
or
magnet.
Certain non-corrosive and stainless steels used in this engine are non-magnetic. Should steel colored particles, when checked with a magnet, prove to be non-magnetic, continue with the remaining tests. If the particles remain unidentified after all tests, it should be assumed that
they
are
non-magnetic
steel.
(c)
Cadmium Place the particles in aqueous (water) solution of ammonium nitrate. If all or any of the particles dissolve in this solution, they are cadmium. After completion of test, rinse and dry any remaining particles for additional tests and identification.
(d)
Tin
These
clean
particles can be distinguished by their low melting point. With a soldering iron, heated to 260"C (500"F), and tinned with 50-50 solder
(50% tin 50% the solder.
lead),
a
tin
particle dropped
on
the iron will melt and fuse with
(e)
Aluminum
(f)
Aluminum Paint Make a sodium hydroxide solution by adding one pellet of sodium hydroxide to three cubic centimeters of water on a watch glass. Drop
When a particle of aluminum is placed in 50% by volume hydrochloric acid, it will fizz with rapid emission of gas bubbles and gradually disintegrate and form a black residue (aluminum chloride). Silver and bronze do not noticeably react with hydrochloric acid.
suspected particles. Aluminum silicone paint will react mildly, forming gas bubbles and some visible gas, as the particles change to sodium aluminate. Aluminum chips will react much more actively with many more visible bubbles forming. Silver will not react. in the
(g)
Silver
When
producing
a
a
silver
particle is placed
whitish silver nitrate
fog
in nitric
acid, it
reacts rather
slowly,
in the acid.
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WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(h)
Titanium
The
following procedure should
be used for identification of titanium
particles: WARNING:
1
THE CHEMICALS USED IN THE FOLLOWING PROCEDURES ARE PARTICULARLY HAZARDOUS. THEY REQUIRE SPECIAL HANDLING AND THE TESTS ARE BEST PERFORMED BY QUALIFIED LABORATORY PERSONNEL.
particle of metal to be identified on white porcelain spot plate. A particle of known titanium should be placed alongside on second spot observe and verify results of tests on unknown. to plate Place
second
2
Add several
crystals
of ammonium bifluoride and 5 to 10
NOTE: 1. Solid ammonium bifluoride can be dry place and used as needed.
NOTE: 2. Two to three drops of 5% to 10% be used as an alternative. 3
4
Let particles stand for 20 to 30 minutes, discolored. Add two to three to one
6
Add three to four
drops of
If titanium is
become
(i)
(i.e.
stand another 20 to 30 minutes,
discol red.Let particles
Z
hydrofluoric
stored in
one
a
acid solution may
until solution becomes
or
1:1 sulfuric acid
conveniently
water
slightly
part concentrated acid
part water).
5
NOTE:
drops of
drops of
3% to 10% fresh
present,
or
until solution becomes
hydrogen peroxide.
yellowish color will develop which will darker with time if allowed to set.
a
progressively
drops of concentrated phosphoric acid, and stir gently to discharge any yellow color due to possible presence of iron. Any remaining light yellow to orange coloration indicates presence of titanium.
Add two to three
Bronze When a bronze oi copper green cloud is produced.
particle
is
placed
in nitric acid,
a
bright
MARKING OF PARTS 14.
GENERAL A.
When it is necessary to mark an engine part, weldment, or assembly, only the applicable Pratt Whitney Canada approved marking methods shall be used.
following
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Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
15.
PERMANENT MARKING METHODS A.
Procedure
(1)
Permanent methods of marking, in which the marking is service life of the part, are described as follows:
legible during
the entire
DO NOT CONFUSE ELECTROLYTIC ETCHING WITH ELECTRIC ARC SCRIBING WHICH IS PROHIBITED ON TURBINE ENGINES.
WARNING:
(a) Electrolytic Etching
Ordinarily, electrolytic etch markings may be applied to surface after which, assembly, does not move relative to a contacting any surface. Anodized parts, however, cannot be electrolytically etched. Characters are produced by electrolysis, confined to the area of the character by a stencil, or by an electrolytic marking pen. This technique is sometimes used a temporary method.
(b)
Vibration Peening This is a process whereby characters are produced by a vibrating radius-tipped conical tool. This method is not permitted if the hardness of the material at the time of marking is higher than Rockwell C45, equivalent.
as
or
TEMPORARY MARKING METHODS 16.
PROCEDURE CAUTION:
A.
ANY TEMPORARY MARKING METHOD WHICH LEAVES A CARBON DEPOSIT OR A DEPOSIT OF COPPER, ZINC, LEAD, OR SIMILAR RESIDUE MAY CAUSE SUBSEQUENT CARBURIZATION OR INTERGRANULAR ATTACK WHEN THE PART IS SUBJECTED TO INTENSE HEAT. AVOID THE USE OF SUCH A METHOD UNLESS THE MARKING IS COMPLETELY REMOVED BEFORE THE PART IS SUBJECTED TO INTENSE HEAT. DO NOT USE CHALK OR SOAPSTONE FOR MARKING.
Definition A method of
temporary marking is one which ensures identification during ordinary storage of items prior to final assembly.
handling
and
NOTE:
unqualified marking material is used, the mark must be in order to preclude any possible reduction in fatigue strength. The method of removal will be dictated by the material used and the particular part so marked.
In the event that
removed
B.
Temporary Marking
(1)
an
thoroughly
of Cold Areas
For
temporary marking of the cold
are
used:
(a) Volger Opaque (b) Dykem
Ink
Ink KX425
areas
of the
engine only,
the
following
materials
(Black) (PWC05-046B). (Black)
and KXX 122
(White) (PWC05-046C).
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Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Carter Ink No. 451
(c) C.
Temporary Marking (1)
of Hot
(Black) (PWC05-046). Cold Sections
For temporary marking of both the hot section and the cold following materials may be used:
(a)
Felt Wick Pen and
(b)
Marks-A-Lot
(c)
Cado Marker
Speedry
instant
engine, the
(PWC05-048B). (PWC05-178).
Supreme
No. 142
Tex-Rite instant
dry
ink: 400-1
(Black),
Purple Dye (PWC05-002).
(e)
Micro
(f)
Phano No. 71 Red Pencil
(g)
Colorbrite Silver No. 2101 Pencil
(PWC05-103). (PWC05-018A).
MARKING LOCATIONS WHEN USING A MARKING PENCIL, MARKS MUST NOT BE APPLIED TO THE MATING SURFACE OF FINISHED MACHINED PARTS OR TO CARBON SEAL PLATE SURFACES. HEAVY DEPOSITS OF THE MARKING MATERIAL COULD ADVERSELY AFFECT CLEARANCES AND RUNOUT
CAUTION:
A.
Except
where otherwise
manner
18.
of the
dry ink(PWC05-048A)
(d) Brushpen No. 57(PWC05-048) and 400-2 (Red) and 400-7 (Purple).
17.
areas
and
adjacent to,
specified, reidentification should or
in
a
be
accomplished in the original markings.
same
location similar to, that of the
MARKING SIZE A.
markings should be applied so as to ensure maximum legibility and durability of the produced without affecting the function or serviceability of the part. Permanent markings should not extend into any radius, chamfer, sharp edge or fillet adjoining the surface designated to be marked. Unless otherwise specified, marking characters should be 0.060 to 0.160 inch in height. In special cases, when the marking area is limited by size or configuration, characters not less than 0.016 inch and not more than 0.025 inch in height will be permitted. All
mark
WELDING 19.
GENERAL NOTE:
following procedures apply to components that are dispositioned for repair by welding and are removed from the engine. Weld repair of components still installed on an engine is not permitted.
The
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Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
WARNING:
A.
UNDER NORMAL CIRCUMSTANCES ONLY AN ARGON REGULATOR SHOULD BE USED WITH ARGON GAS, IF HOWEVER, AN OXYGEN REGULATOR IS USED, IT MUST NOT BE REINSTALLED ON AN OXYGEN CYLINDER. ARGON GAS IS NOT FREE FROM OIL AND THE POSSIBILITY EXISTS OF AN EXPLOSION CAUSED BY THE PRESENCE OF OIL IN THE OXYGEN REGULATOR. USE SAFE WELDING PRACTICES, ADEQUATE VENTILATION, AND PROTECTIVE EQUIPMENT. DO NOT WELD IN CONFINED AREAS WITHOUT EXHAUST VENTILATION.
An inert gas fusion welding process must be used when repairing cracks in engine parts. Argon or helium gas may be used in inert gas welding; however, argon is recommended because its greater density reduces its rate of diffusion with the
atmosphere. B.
Inert gas welding is a gas from the surrounding
welding process which uses inert gas to protect the weld atmosphere. The heat necessary for welding is provided by a intense is struck between a non-consumable thoriated tungsten electric which are very (tungsten and thorium alloy) electrode and the metal parts. On repairs where a filler material is required, a welding rod is fed into the weld area and melted with the base metal in the same manner as in conventional gas welding. are
area
C.
The inert gas
welding
process
(1)
An A.C.
(2)
A Linde HW-10 torch
D.C.
are
requires availability of the following equipment:
welder with
high frequency controls.
equivalent with circulating
or
water
equipment,
and ceramic
cups of suitable size.
(3) 20.
An argon gas
regulator
and two flowmeters.
CLEANING BEFORE WELDING A.
Surfaces to be welded must be free from objectionable protective coatings, dirt, grease, oil, and other foreign matter, and as free as praticable from oxides. Wire brushes and abrasives may be used to remove protective coatings and oxides, except that the final step in removing oxides from aluminum and aluminum alloys preferably should consist of chemical treatment taking place as close as practical to the time of welding. Wire brushes, if used for cleaning corrosion-resistant alloys, must have bristles of austenitic
corrosion-resistant steel. No undesirable be welded after cleaning operations. 21.
deposit
or
residue must remain
on
surface to
WELDING PROCEDURE A.
Procedure
NOTE:
(1)
Welding
Connect
one
behind crack
(2)
is to be carried out
only by qualified personnel.
argon gas flowmeter to torch. Install other flowmeter, if necessary, as a backup when ready to weld.
Connect torch to the
are
welder for
straight polarity.
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2-4-18
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(3)
tungsten electrode in the torch, allowing of the inch 5/16 to extend out of the ceramic cup. The point approximately ceramic cup must not be smaller than a No. 6 for the HW-10 torch, in order to provide a sufficient amount of inert gas to the weld area where cleanliness of the surface beads is important. Insert
a
NOTE:
1/16 inch diameter thoriated
A
practical,
on
the electrode must be
If it is necessary to
(4)
electrode may be used, but a needle point must be the electrode for more positive starting of the are. Where
plain tungsten
maintained
kept
clean of material
pickup.
protect underside of weld from contamination, possible weld
poor surface appearance, attach argon gas line behind crack to be welded. This may be done by fabricating small box-like fixtures having edges shaped to fit contours of part to be welded and using a suitable connection to secure line. Seal fixture to part in order to conserve as much of the gas as possible.
(5)
porosity,
or
NOTE:
The amount of pressure to provide sufficient backup must be determined. This pressure should not allow the gas to stir the puddle of the weld. Do not use flux when welding in an inert atmosphere.
When high frequency controls are used, it is not necessary to strike an are. Hold torch vertically to work so that the shielding gas (argon) will form a protective envelope around weld. It is preferable to have area to be welded in a horizontal
(flat) position. (6)
high frequency controls are not available, strike are and hold tip of electrode approximately 1/8 to 1/4 inch above surface to be welded until a puddle is formed. Add welding rod and proceed as in standard gas welding.
Where
NOTE:
Test welds using similar material of the same thickness and should be made to determine the proper gas pressures and
joint design are
welder
settings required. B.
Because a high percentage of steel parts used on the engine are fabricated from 12 percent chromium corrosion-resistant steels, which are characterized by their susceptibility to air hardening, field repair of cracks by fusion welding is a special problem. The high temperatures at which fusion weld repairs are made and the subsequent air cooling of the part, or parts, from these temperatures usually result in
an
which fusion weld repairs have been made have a tendency to crack because the steel structure becomes unstable, brittle and highly stressed. The structure of the material can be improved by
22.
loss in
increase in material hardness and
a
reheating
the
the
parts
and
controlling
ductility.
cooling
Parts
on
rate.
CLEANING AFTER WELDING A.
welding, flux must be removed as completely as practicable. If complete removal is not practical, the assemblies should be suitably treated to prevent corrosion by residual flux. After the welding is completed, clean out any holes with a rotary file and polish with No. 180 emery cloth (PWC05-021). After
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2,.
LOCALSTRESSREUEF A.
24.
Components which are not highly stressed may be repaired by fusion welding. It is possible partially to restore the original properties of such welded components through the use of local heat treatment. The localized heat may be applied by the neutral flame of an oxyacetylene torch. Extend the stress relief one inch minimum beyond the welded area. After the desired heat has been applied to the component for the proper length of time, reduce temperature gradually.
INSPECTION OF WELDING A.
the weld for
quality, uniformity, undercutting, cracking and flux removal. Welds adjacent metal in gradual, smooth curves. Welds must be sound, free from clean, foreign material, and from internal and external defects that would affect the strength of the weld. adversely
Inspect
must blend into the
STANDARD INSPECTION PROCEDURE 25.
GENERAL A.
Damage
to
engine parts
undesired movement.of
may result from improper ´•clearance, lack of lubrication, parts which are bolted or pressed together, uneven load
distribution, heat, shock, extension of minor scratches, tool marks, grinding cracks, nicks, etc. Damage to engine parts may also result from the presence of foreign matter such as grit, chips, moisture, chemicals, etc., or from improper technique during
assembly
or
disassembly.
B.
While it is
C.
Inspect parts for alignment, distortion, foreign matter, looseness, out-of-roundness, sharp edges, scratches, taper, warping and wear. In addition, check the following:
frequently possible to repair a damaged part so that it may be safety reinstalled, it is important that the cause of the damage be determined, and corrected if possible. Otherwise, more serious consequences may result.
(1)
Holes in cases, manifolds,
(2)
Gear teeth and
(3)
Magnesium parts
splines
pipes
and tubes for obstructions.
for contact patterns.
for corrosion.
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WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
(4)
ANY TEMPORARY MARKING METHOD WHICH LEAVES A CARBON DEPOSIT OR A DEPOSIT OF COPPER, ZINC, LEAD, OR SIMILAR RESIDUE MAY CAUSE SUBSEQUENT CARBURIZATION OF INTERGRANULAR ATTACK WHEN THE PART IS SUBJECTED TO INTENSE HEAT. AVOID THE USE OF SUCH A METHOD UNLESS THE MARKING IS COMPLETELY REMOVED BEFORE THE PART IS SUBJECTED TO INTENSE HEAT. DO NOT USE CHALK OR SOAPSTONE FOR MARKING.
Mounting pads NOTE:
Use
and
pencil
seating surfaces
carbon paper whenever
smoothness is
26.
for smoothness and flatness. a
smear-type indication of surface
required.
(5)
Plugs for tightness.
(6)
Studs, dowels, and similar protruding parts for alignment and projection length.
(7)
Protective surface
(8)
Threads for condition.
coatings for completeness.
INSPECTION GAGES A.
When a
B.
an
inspection procedure requires
a
very accurate measurement,
a
micrometer
or
dial indicator must be used.
micrometer is to be used, check it for accuracy before taking a measurement. Make that the contacting surfaces of the micrometer are clean, and that the contacting surfaces of the parts to be measured are clean and free from burrs. When using a depth micrometer, be sure to hold the anvil tightly ana squarely against the contacting surfaces. If
a
sure
C.
D.
If a dial indicator is used, make that any swivel connections are When
taking a measurement reasonably snug fit.
sure
that the indicator support is anchored
firmly and
tightened securely.
with
a
feeler gage, the final size of the feeler must be
a
ELBOW FITTINGS 27.
REMOVAL A.
Procedure
(1)
Note
(2)
Loosen
(3)
Remove preformed elbow fitting.
angular position jam
of elbow
fitting before
nut and remove elbow
removal.
fitting.
packing, packing
retainer
(back-up-ring),
and
jam
nut from
Page
2-4-21
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
28.
INSTALLATION A.
Procedure
(1)
(See Figure 2-4-6)
Lubricate
preformed packing and packing retainer (back-up ring), and threads fitting, with a light film of fluid to be used in system. If a dry assembly is required, use the lubricant/compound specified in assembly instructions. new
of elbow
(2)
Screw jam nut (2) on double-threaded end of elbow fitting (1), with counterbored face of nut outward. Turn nut on fitting until clear of non-threaded annulus.
(3)
Assemble packing retainer (3) nut:
on
elbow
fitting (1)
and press into counterbore of
jam
(2).
(4)
Assemble preformed packing annulus.
(5)
Turn
(6)
Install elbow fitting into boss on engine or accessory unit, allowing jam nut to rotate with fitting, until preformed packing contacts face of boss. This point will be
on
elbow
fitting (1)
and press into non-threaded
jam nut (2) outward until face of packing retainer (3) contacts preformed packing (4). Continue turning jam nut until preformed packing is pushed firmly against first thread on outer portion of elbow fitting.
recognized by (7)
(4)
increase in torque
required
to turn elbow
fitting.
With elbow fitting in this position, hold jam nut stationary and turn fitting into boss further 1-1/2 turns. If necessary, the elbow fitting may be turned into boss a maximum of one more complete turn to facilitate alignment to required angular
a
position. If elbow fitting tightens in jam nut before completing initial 1-112 turns, during final alignment, jam nut may be allowed to turn with fitting.
NOTE:
(8)
When elbow value
fitting is aligned in required position, tighten jam nut and torque specified in assembly instructions for engine or accessory unit.
to
Metal to metal contact between jam nut and boss must be obtained exceeding maximum recommended torque and there must be extrusion of preformed packing and/or packing retainer.
NOTE:
without
B.
or
no
Fluid and Pneumatic Lines NOTE:
Refer to
When
assembly
instructions.
fluid or pneumatic lines, whether solid tubes or flexible hoses, lines engage onto respective coupling adapters without tension or load.
installing
ensure
(2)
sections in Part 3 of this manual for
DO NOT USE FORCE TO POSITION LINE ONTO COUPLING ADAPTERS.
CAUTION:
(1)
specific
Alignment paragraph
must be obtained
28.
by adjusting the position of the adapters. Refer to preceding, for instructions pertaining to the installation of adapters.
Page
2-4-22
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TOUCH-UP SOLUTION 29.
CHROME PICKLE SOLUTION (MAGNESIUM RGB AND AGE HOUSINGS) A.
Preparation (Ref. Table 2-4-1)
WARNING:
(1)
Fill
REFER TO THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS FOR INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAUCHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES. SOME OF THESE MATERIALS CAN BE DANGEROUS. YOU CAN GET THE DATA SHEETS FROM THE MANUFACTURERS OR THE SUPPLIERS OF THESE MATERIALS. a
suitable container with tap water to
solution
no more
than ’/2 of the volume of the
required.
(2)
Slowly and carefully add the the sodium dichromate.
required
amount of sodium dichromate. Stir to dissolve
(3)
Slowly
required
amount of nitric acid. Stir to mix the solution.
(4)
Fill the remainder of the container with
carefully
and
add the
tap
water to the
specified
volume
required.
TABLE 2-4-1, Chrome Pickle Solution
PROPORTIONAL LIMITS
PROPORTION
MATERIAL Sodium Dichromate
1.0 to 1.5 Ibs.
1.5 Ibs.
(PWC05-055) Nitric Acid
1.5
1.0 to 1.5
pints
pints
(PWC05-1 95) NOTE: The
figures
that
are
given
are
per
gallon
of solution
required.
i Page 2-4-23 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ilJ~ 4)
(4
t-’-~S
C3146A Installation of Elbow
Figure
Fitting (Typical)
2-4-6
Page
2-4-24
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
2-4-6
Fitting
1.
Elbow
2.
Jam Nut
3.
Packing Retainer Preformed Packing
4.
Page 2-4-25/26 Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
GENERAL PROCEDURES
PART 2
SECTION 5 1.
TORQUE RECOMMENDATIONS
GENERAL A.
in the text of this manual are standard values for the size and thread of the item concerned (nut, bolt, screw, etc.). Reference to an item in Fits configuration Clearances indicates a specific torque value, and may also give special instructions not normally covered by standard practices. All torque limits have been established with
Torques specified
temperature prevails. If the parts involved are hot, sufficient time should be allowed for the temperature of the parts to reach that of the
the
that normal
understanding
surrounding area before tightening operation is attempted. Except where otherwise specified, torque values in this manual are based on the use of parts to which a thread lubricant, such as engine oil or equivalent, has been applied. Silver-plated
NOTE:
B.
All
tightening
must be
bolts do not
require
lubrication
accomplished slowly
and
prior
evenly
for
to
assembly.
consistency
and best
possible
accuracy.
C.
devices must be checked daily and calibrated by means of weights and a measured lever arm to ensure there are no inaccuracies; checking one torque wrench against another is not sufficient. Some wrenches are quite sensitive in the way they react to their support during a tightening operation; therefore, every effort must
Torque-indicating
be made to follow instructions furnished 2.
by
the wrench manufacturer.
TORQUE WRENCH AND EXTENSIONS A.
Usage (1)
of Extension to
Torque
Wrench
it is necessary to use a special extension, or adapter wrench together standard torque wrench (Ref. Fig. 2-5-1). In order to arrive at the resultant required torque limits, the following formula shall be used:
Occasionally, with
a
T
Desired torque
E
Effective
L
A R
on
the
part.
of
length special extension or adapter. Effective length of torque wrench. Distance through which force is applied to part. Reading on scale or dial of torque wrench. LTLT -A-L+E
Example:
torque of 1440 Ib.in. is desired on a part, using special extension having a length of three inches from center to center of its holes, and a torque wrench measuring 15 inches from center of handle or handle swivel pin to center of its square adapter. A
Then:
R
LT L
15X1440 5
15
3
12001b.in.
Page
2-5-1
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442´•
(2)
With the axis of the extension or adapter and the torque wrench in a straight line, to a wrench reading of 1200 Ib.in. will provide the desired torque of 1440 Ib.in. on the part.
tightening
3.
NUTS, BOLTS AND SCREWS A.
4.
Bolts and nuts on flanges with metal tubular gaskets must be initially torqued to the required limits and then retorqued until the recommended torque remains constant.
SELF-LOCKING NUTS A.
Procedure
(1)
For each item, note the torque necessary to turn the nut
on
the bolt before
seating
the nut.
(2)
5.
Add this torque to the value as the total applied torque.
Use this
new
value
tightening a castellated nut, alignment of the slot must be obtained without exceeding the maximum torque. If this is not possible, replace the nut. After tightening the nut to the recommended torque, it must not be loosened to permit insertion of lockwire or a cotterpin. If the slot in the nut or the lockwire hole in the bolt or screw is not properly aligned at the minimum torque limit, the nut, screw, or bolt should be further tightened to the next aligning position, but the maximum torque limit must not be exceeded. If alignment cannot be accomplished without exceeding the maximum limit, back off the or
bolt one-half turn and retorque.
SLOTTED STEEL LOCKNUTS A.
Effective locking of slotted, steel locknuts on bolts or studs requires full engagement of all locknut threads. The chamfered part of the locknut ID does not exert force on the bolt or stud; therefore, it is not necessary that the bolt or stud be flush with, or protrude from, the top face of the locknut.
STANDARD AND STEPPED STUDS A.
When the
torque required
minimum value, selected. 8.
application.
When
nut, screw,
7.
in the text for the
CASTELLATED NUTS A.
6.
given
or
to drive a stud to the correct
exceeds the maximum value of
protrusion does not provide the protrusion, another stud must be
HOSE TUBING AND THREADED CONNECTORS A.
If leakage occurs at a coupling, do not attempt to correct by the fitting and check for nicks, burrs, or foreign objects. Use
overtorquing. new
Disassemble
parts if necessary.
Page
2-5-2
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
E
-I-
L
C192A
Torque
Wrench and Extension
Figure
2-5-1
Page 2-5-314 Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
PART 2
GENERAL PROCEDURES
SECTION 6 -TESTING
INTRODUCTION 1.
GENERAL A.
2.
The
operating procedures contained in this section are based solely on items supplied Pratt by Whitney Canada; no attempt has been made to cover airframe supplied items for the many possible variations in installation. The powerplant section of the airframe manufacturer’s manual must be referred to for ground running, trim adjustments and performance checks. Before making any control adjustment/check, engine should be run for ten minutes minimum and all parameters stabilized.
ENGINE CONDITION TREND MONITORING A.
Gas
turbine/turboprop engine maintenance practices frequently include inflight engine performance monitoring, as a means of detecting mechanical deterioration in engine gas paths. A single system requiring almost no arithmetic calculation has been devised for the engine to aid in planning indicated rectifications early, and thus reduce primary and secondary damage costs resulting from fully developed failures, and risks of inflight shutdowns and flight cancellations. The turbine
engine characteristic of repeatedly producing its output at, or very close to, charted gas generator parameter values, provides the basis for the engine trend monitoring system. Thus, under known conditions of pressure altitude (PA) and indicated outside air temperature (IOAT), the gas generator parameter values of interturbine temperature (Tt5), compressor speed (Ng) and fuel flow (Wf) for particular propeller shaft speeds (Np) and torques are predictable within reasonable limits.
3.
e~gines
C.
New operate within a tolerance band either above or below charted parameter values, and tend to deviate more with time and deterioration of gas path components.
D.
Abrupt,
E.
The
or gradual changes of normal deviations from charted parameter values indicate critical changes in gas path component conditions, and as such changes are detectable before any drastic failure occurs.
system should be introduced when engines are new or newly overhauled. This enables establishing a base performance line before any deterioration takes place in the engine. For complete details, refer to P&WC Publication "Aircraft Gas Turbine Operation Information Letter No. 16 (AGTOIL #16)".
SYMBOLS A.
Symbols have been designated for the working testing. The symbols, referenced to the various meanings are as follows: Pamb
variables used in connection with engine stations within the engine, and their
Ambient Barometric Pressure
Page 2-6-1 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
compressor inlet
Pt2
Total pressure
Tamb
Ambient
Tt2
Total temperature
Tt4
Total temperature
compressor inlet screen compressor turbine inlet
Tt5
Total
interturbine temperature
Temperature
temperature Total temperature
Tt7
exhaust
Nf
Power Turbine rpm
Ng Np
Gas generator rpm
Propeller rpm Output shaft rpm
Ns
shp shp 6~8
shaft horse power
Wf
Fuel Flow
shaft horse power
S 8
(corrected)
(Ib/hr) Temperature
T
F
screen
P observed/P standard
(delta) (sigma) (theta)
Ratio of relative
density
T observedrr standard
GROUND SAFETY PRECAUTIONS 4.
GENERAL A.
5.
Turbine-powered aircraft make it necessary to improve ground safety precautions, to prevent injury to personnel and damage to property. When handling, or working on turbine-powered aircraft not only must the propeller area be avoided, but allowances must also be made for the hot, high velocity exhaust gases discharged from the exhaust nozzles. (See Figure 2-6-1)
AIR INTAKE A.
The compressor inlet case design is such that the air intake velocity is very low. Nevertheless, the immediate area of the engine inlet should be free of loose objects, sand, grit, rags and spilled fluids which could enter through the compressor inlet screen and contaminate
6.
or
damage
the compressor blades.
PROPELLER WINDMILLING A.
Propeller
must be restrained from
with
oil pressure,
zero
can cause
when aircraft is not in deterioration. section power
windmilling
use.
Windmilling,
Page
2-6-2
Apr 02/2004
WHITNEY CANADA
PRATT
WIAINTENANCE MANUAL MANUAL PART NO. 3015442
3 FT.
I
71"
(160"F)
18
:AREA´•ATTAKETOFF:
BLIAS~T): 50
KNOTS
\:::::::::::::::::::I:::::::::::::::::::I
79.50
121"
75-
(175"F)
(250"F)
15
~10
FEET
"C
150 _
250
655
232"
427"
(450"F)
5
(800"F)
593"(1100"F)
--~--1-
0
C231B Exhaust
Danger Areas -Typical Figure 2-6-1
Page 2-6-3 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
7.
ENGINE EXHAUST A.
At takeoff power settings the propeller may pick up and throw loose dirt, gravel, and other debris over a considerable distance. Precautionary measures must be taken
during the ground running of turbine engines to avoid injury to personnel and damage to property or other aircraft. Occasionally during the starting of a turbine engine, excess fuel accumulates in the exhaust ducting and when ignited causes long flames to be blown from the exhaust nozzles. Personnel must ensure that the runup inflammable materials and ground equipment. 8.
area
is clear of
EXHAUST GASES A.
The carbon monoxide content of exhaust gases is relatively low but other gases are present which have a disagreeable odor and are irritating. Exposure normally results in watering of the eyes, accompanied by a burning sensation. Less noticeable but equally
hazardous, is the possibility of respiratory irritation. For both these reasons, exposure should be avoided wherever possible, particularly in confined spaces. 9.
COOL-DOWN A.
After
engine operation,
allow sufficient coo-ldown time before
inspecting
or
working
on
the exhaust duct. 10.
JET FUEL AND LUBRICATING OIL A.
All
jet fuels and lubricating oils have an injurious effect taken to avoid contact as much as possible.
on
the skin. Precautions must be
TEST INFORMATION 11.
GENERAL A.
The performance of a turbine engine is greatly affected by surrounding atmospheric conditions. For this reason it is absolutely essential that accurate values of the actual barometric pressure (not corrected to sea level) and ambient temperature be obtained for the immediate area at the time of engine testing. Furthermore, it is highly desirable that engine trimming and performance checks be carried out at low wind velocity with the engine intake facing in the direction of the wind. Even this precaution will not prevent an unstable trim in certain aircraft at moderate-to-high wind velocities. Each type of aircraft must have special procedures and limits set up for trimming the engine, when the wind velocity and direction exceed those in which a stable trim can be obtained.
Page 2-6-4 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PRECIPITATION A.
13.
Performance and trim checks should not be attempted during moderate to heavy precipitation or fog. Water entering the engine inlet changes the power output of the engine, the change being proportional to the amount of water ingested. Any form of moisture in the air causes the engine to ingest water. This includes occasions when water or snow is blown into the air inlet by the propeller or sucked in by the compressor. Freezing rain or slushy snow has exactly the same effect on power output as water ingestion and in addition, may cling to inlet ducts or the inlet screen and upset the flow of air to the engine. If the engine must be performance checked or trimmed during adverse conditions, the inertial separation system (if fitted) should be selected and the applicable airframe power loss taken into consideration.
FUEL A.
14.
It is recommended that all trims be made
using
the
same
fuel
as
that used in service.
INSTRUMENTS A.
Due to the fact that even the best instrumentation available can vary with use, it is recommended that instrumentation used in trimming engines be calibrated every 30 days, or as dictated by experience. Instrument accuracy should be within the following
limits: Ambient temperature; ~tl"F
Ambient pressure; ~0.05 in.Hg Inlet air temperature
Probe range
(-65"
to
+75"C)
+1"C
lover full range)
Nf; ~0.5%
Ng;
~0.5%
1050"C) +15"C ton remainder of scale) Tt5; temperature (650" to 750"C) ~15"C ton remainder of scale) Oil temperature; Scale range (20" to 150"C) ~3"C lover full range) Torquemeter pressure; ~t26 Ib.ft., ~2% or 1 psig Tt4; +5"C (950"
to
+-5"C
15.
GROUND OPERATING LIMITS A.
The limits shown in Tables 2-6-1 and 2-6-2 are provided sea level and ambient temperatures as specified. TABLE 2-6-1,
Engine Operating Max.
Max. SHP
Setting
(OAT)
Takeoff and Max. Cent. En Route
Emergency
guide and
psig
(Tt5)
based
on
(PT6A-20, -20A and -20B)
Ng
Oil
Np
ITT"C Ib. ft.
are
Nom inal
Torque Power
Limits
as a
Oil
Temp. psig (3) 1 "C (9) Press.
(Tt5)
RPM
RPM
10 to
99"C
(50
550
21"C
(70"F)
to
210
1315
42.5
750
381001101.512200
100
65 to 85
"F)
Page 2-6-5 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Engine Operating
TABLE 2-6-1,
rved ITT"C
Torque Power
SHP
setting
(OAT)
Ib. ft.
Nom
Max.
Max.
psig
-20B) (Cont’d)
-20A and
(PT6A-20,
Limits
inal
Oil
Np
Ng
Oil
Press.
RPM
(Tt5)
(Tt5)
Temp. psig (3) 1 "C (9)
RPM
0 to
99"C
1
I
I
I
15"C I
I
I
I
538 Max.
Climb
(59"F)
1315
42.5
725
I
I
I
1
1(32
I
I
I
I
I
1
705 1
I
12200
100
to
210
"F)
65 to 85
0 to
99"C
1
I
I
I
I
I
I
I
1
I (59"F) 1
I
I
I
I
I
I
I
I
1
I
1
12200
495 Max.
15"C
Cruise
42.5
1315
705
100
65 to 85
1(32 to I ilo "F) -40 to 99 "C
(-40 19500 1
Idle
I
I
I
1
Starting
I
I
I
1
685
(6) 1
1090
52
500
I
I I
925 1
(5)(8)
I 1
I I
1 I
I I
I I
I I
40 Min.
210
"F) 1 -40 I Min. 0 to 99 "C
(32 1500
Acceleration
(5)
850
38500
(5)
(5)
48.5
2410 102.6
to
210
(5)
"F)
110
0 to 99 "C Max.
Reverse
500 21"C
1315
(70"F)
NOTE: 1.All limits NOTE: 2.
1
are
(7) based
Accessory drive
I
I
I
I
I
1
I
I
I
1
42.5 on sea
seal
750
level and ambient temperatures
leakage
should not exceed 3
NOTE: 3. Minimum oil pressure above 28,000
Ng
NOTE: 4. For rpm, ITT and torque limits refer to
NOTE: 5. These values NOTE: 6. Increase
Ng
are
to
is 65
c.c.
as
1
1(32
95 89
to
210 65 to 85
"F)
specified.
per hour.
psig.
Inspection
and
Figures 2-6-3,2-6-4
and 2-6-5.
time-limited to two seconds.
keep within this
limit.
NOTE: 7. If minimum torque is used, Np must be set power operation is limited to one minute. NOTE: 8.
I
12090 38100 1101.51 1960
Starting temperatures
above 925"C
so as
(1700"F)
not to exceed power limitations. Reverse
should be
investigated
for
cause.
NOTE: 9. For increased oil service life, an oil temperature between 74" and 80"C (+165" and +176"F) is recommended. A minimum oil temperature of +55"C (130"F) is recommended for fuel heater operation at Takeoff power.
Page 2-6-6 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-6-2,
Engine Operating
Max.
Max.
Nom
TIT"C
inal IT"C
(Tt4)
(Tt4)
Torque Power
SHP
Setting
(OAT) I I
Takeoff and Max. Cent. En
Ib. ft.
psig
Limits
(PT6A-6, -6A, -6B)
Np
Ng RPM
Oil
Oil
Press.
Temp.
psig (3) 1 "C (9)
RPM
I I
I I
I I
I I
I I
I I
I I
I I
I I
110 to I 99"C
1
I
I
I
I
I
I
I
1
1(50
Route
21"C I
I
I
I
I
I
I
I
I
1
Emergency
(70"F)
550
1315
42.5
38100 1101.51 2200
994
"F)
65 to 85
100
to
210
0 to
99"C
1
I
I
I
I
I
I
I
1 (32
18"C I
I
I
I
I
I
I
I
I
1
935 1
I
12200
500
Max.
Climb
(64"F)
1315
42.5
952
"F)
65 to 85
100
to
210
0 to
99"C 471 1 15"C I
Max. Cruise
(59"F)
I
I
I
I
1315
I
42.5
I 1
930
I
I I
I 1
I
1
1(32
I I 12200
I
1 210 65 to 85
100
to
"F) -40 to
99 "C
(-40 to
19500 1
I
Idle
I
I
1
700
(6) 1
1038
I
Starting
I
I
1
500
I
I I
870 1
(5)(8)
52
I
I
1
40
210
1
I
I
Min.
"F)
I I
I I
I I
r -40 I Min. 0 to 99 "C
(32 1500
Acceleration
(5)
994
38500
(5)
(5)
48.5
2420 102.6
to
210
(5)
"F)
110
0 to 99 "C
Max. Reverse
500 21"C
1315
(70"F)
NOTE: 1.All limits NOTE: 2.
1 (7)
are
Accessory
based
I
I
I
1
I
I
42.5 on sea
drive seal
994
leakage
NOTE: 4. For rpm, ITT and torque limits refer to are
12090
95
38100 1101.51 1960
89
should not exceed 3
Ng
is 65
I
1
level and ambient temperatures
NOTE: 3. Minimum oil pressure above 28,000
NOTE: 5. These values
I I
c.c.
as
1 (32
to
210 65 to 85
"F)
specified.
per hour.
psig.
Inspection
and
Figures 2-6-3,
2-6-4 and 2-6-5.
time-limited to two seconds.
NOTE: 6. Increase Ng to keep within this limit. NOTE: 7. If minimum torque is used, Np must be set power operation is limited to one minute.
so as
not to exceed power limitations. Reverse
Page 2-6-7 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-6-2,
Engine Operating Max.
Max.
SHP
Setting
(OAT)
NOTE: 8.
Ib. ft.
inal C
(Tt4)
(Tt4)
psig
Starting temperatures
above 870"C
(PT6A-6, -6A, -6B) (Cont’d)
Nom
TIT"C
ed
Torque Power
Limits
(1600"F)
Ng
Oil
Np
Oil
Temp. psig (3) 1 "C (9) Press.
RPM
should be
RPM
investigated for
cause.
NOTE: 9. For increased oil service life, an oil temperature between 74" and 80"C (+165" and +176"F) is recommended. A minimum oil temperature of +55"C (130"F) is recommended for fuel heater operation at Takeoff power.
INADVERTENT CUT-OFF AND RELIGHT DURING TAXI
relight happens when the operator moves the fuel condition lever from Low Idle to Cut-off and immediately back to Low Idle. This may result in a short-term sub-idle overtemperature.
An inadvertent cut-off and
NOTE:
A.
For operators WITH an engine monitor and have obtained a detailed recording of the overtemperature event: Refer to Chap. 71-00-00, ADJUSTMENTTTEST, Inadvertent
Cut-off and B.
Relight During
inspection
17.
B.
and
a
For inadvertent cut-off and
relight during taxi,
see
Figure
and
2-6-2.
excessively rapid rise in fuel flow, compressor speed, and turbine temperature. Several momentary high overtemperatures affect engine service life just as seriously as a single prolonged lower overtemperature condition. The higher the temperature, the sooner serious engine damage occurs and the more extensive is the inspection required. When an overtemperature condition is anticipated, or has occurred, perform a normal engine shutdown. Avoid an emergency shutdown unless it is obvious that continued operation will result in more than overtemperature damage.
Overtemperature
For
conditions
are
usually preceded by
an
overtemperature limits and the corresponding inspection procedures,
..61serugiF see
2-6-3 and 2-6-4.
C.
18.
19.
If
an
engine
was
subject
to
an
inadvertent cut-off and
relight during taxi,
refer to Para.
ENGINE OVERSPEED A.
I
engine monitor: Return the compressor turbine blade shop facility for stretch check, fluorescent penetrant metallurgical analysis (cut-up) of two blades.
ENGINE OVERTEMPERATURE A.
I
figure.
For operators WITHOUT an assembly to an overhaul
disk
C.
Taxi
engines subjected to overspeed, sudden stoppage, loss of oil or lightning strike conditions, refer to Engine Unscheduled Inspection for action required. For
ENGINE OVERTORQUE A.
For
engine
wnditions and conenivs actions
see
Figure
i)
2-6-5
Page 2-6-8 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AREA
A
RECORD OCCURRENCE IN ENGINE LOG BOOK.
AREA
B
1. DO HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE BLADE AND DISK ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH CHECK, FLUORESCENT PENETRANT INSPECTION AND A METALLURGICAL ANALYSIS (CUT-UP) OF TWO BLADES.
AREA
C
RETURN ENGINE TO AN OVERHAUL FACILITY. NOTE: INTERTURBINE TEMPERATURES SHOWN MAKE NO ALLOWANCE FOR INSTRUMENT ERRORS. BUT DO ALLOW FOR SOME TYPICAL INSTRUMENT LAG.
Tt4 1090
1040
00 980
1035
22 925
Y~ 980
AREA 870
ARE
A
925
0
L
5
15
10
20
25
30
TIME SECONDS
C94573 Inadvertent Cut-off and Relight Figure 2-6-2
During
Taxi
Page 2-6-9 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ACTION AREA
A
1. DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE. 2. VISUAL INSPECTION THROUGH EXHAUST PORTS OF POWER TURBINE BLADES AND EXHAUST DUCT TURNING VANES (16 FITTED). 3. RECORD IN ENGINE LOG BOOK.
AREA
B
i. PERFORM HOT SECTION INSPECTION.
AREA
C
1. PERFORM HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE DISK AND BLADE ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH CHECK AND FLOURESCENT PENETRANT
INSPECTION.~
a IF TEMPERATURE EXCEEDS THIS VALUE FOR 2 SECONDS RETURN
Tt4
Tt5
1050
850
1045
790
1040
780
1025
770
1015
765
ENGINE TO AN OVERHAUL FACILITY. COMPRESSOR TURBINE BLADES AND POWER TURBINE BLADES MUST BE DISCARDED AND BOTH THE TURBINE DISKS SUBJECTED TO STRETCH CHECK AND FLOURESCENT PENETRANTINSPECTION.
a
AREA
C] AREA
BJ
1AREA Aj 995
750
1´•´•~
NO ACTION REQUIRED
02
10
20
40
30
50
60
70
80
90
TIME- SECONDS
C763F
Overtemperature
(All Conditions ex~ept Starting) Figure~ 2-6-3
Limits
Page 2-6-10 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AREA
A
NOACTIONREQUIRED
AREA
B
DETERMINE AND CORRECT CAUSE OF OVERTEMPERATURE VISUAL INSPECTION THROUGH EXHAUST PORTS OF POWER TURBINE BLADES AND EXHAUST DUCT TURNING VANES (IF FITTED). RECORD IN ENGINE LOG BOOK.
AREA
C
i. PERFORM HOT SECTION INSPECTION. 2. RETURN COMPRESSOR TURBINE DISK AND BLADE ASSEMBLY TO AN OVERHAUL FACILITY FOR STRETCH CHECK AND FLOURESCENT PENETRANT
INSPECTION.
´•3E´• IF TEMPERATURE EXCEEDS THIS VALUE FOR 2 SECONDS RETURN
Tt4
Tt5
1050
1100
1040
1090
ENGINE TO AN OVERHAUL FACILITY. COMPRESSOR TURBINE BLADES AND POWER TURBINE BLADES MUST BE DISCARDED AND BOTH THE TURBINE DISKS SUBJECTED TO STRETCH CHECK AND FLOURESCENT PENETRANT INSPECTION.
ow g 980
w
NOTE TEMPERATURES SHOWN MAKE NO ALLOWAMCE FOR INSTRUMENT ERRORS
1035
IARI
Y
Y~a
P4
a
nREnC~ 925
960
j AREA 870
A
925 12
10
15
20
30
TIME- SECONDS
C764F
´•I
Overtemperature
limits
(Starting
Conditions
erugiF)ylnO 2-6-4
Page 2-6-11 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
48.5
~I
Uj
RECORD IN ENGINE LOG BOOK 42.5
NO ACTION REQUIRED
02 10 0
20
30
40
SECONDS
50
60 1
2
3
4
5
6
TIME- MINUTES
C765B
Overtorque Limits -All Engines Figure 2-6-5
Page 2-6-12 Apr 02/2004
PRA’IT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXTREME WEATHER CONDITIONS 20.
COLD WEATHER PROCEDURES
CAUTION:
A.
WHEN STARTING AN ENGINE WHICH HAS BEEN EXPOSED TO LOW AMBIENT TEMPERATURES OVERNIGHT, CAREFULLY OBSERVE FUEL AND OIL PRESSURES. THE LACK OF EITHER FUEL OR OIL PRESSURE INDICATION, OR PRESSURE INDICATION BELOW NORMAL OPERATING LIMITS, IS CAUSE FOR IMMEDIATE ENGINE SHUTDOWN. INSPECT FOR ICE IN THE SYSTEMS AND, IF ICE IS PRESENT, MOVE THE AIRCRAFT INDOORS AND/OR APPLY HOT AIR BEFORE ATTEMPTING ANOTHER START.
complete discourse on the effects of cold weather on turboprop engine operation is beyond the scope of this publication. However, the following procedures and summary of the more prevalent effects will aid in ground running and in troubleshooting some of the problems arising from cold weather operations.
A
cold soaked at temperatures below -18"C (O"F), it is recommended that 5 centistoke oil be used in place of 7.5 centistoke oil.
(1)
Where
(2)
engines are cold soaked at temperatures below -29"C (-20"F) preheat should applied evenly over accessory gearbox and reduction gearbox areas. Start engine with propeller lever in full increase position (fine pitch) to ensure oil flow to front annulus of propeller shaft transfer sleeve.
engines
are
frequently
When be
temperature decreases, water is thrown out of solution in the form of minute droplets. When the temperature is low enough, these droplets will freeze, forming tiny needle-shaped ice crystals. These crystals may collect on the filter surface, impeding fuel flow and, in extreme cases, cause clogging. Should this condition occur, it will be indicated by a drop in, or loss of fuel pressure to the engine. The only remedy is to apply heat to the engine and fuel system components. As fuel
C.
Under these conditions, it is most important that all sumps, strainers and filters be thoroughly inspected on all preflight checks. As long as fuel flows freely from the drains in the tanks and strainers, it can be assumed that the system is free of ice. Any indication that the flow is restricted is cause for the application of heat. If water has collected in the sumps and/or strainers and frozen there (indicated by a lack of flow from the drain) warm air must be applied liberally and the drain opened frequently. Collect all drainage in a clean container and inspect for the presence of water globules in the fuel.
Page 2-6-13 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
WARNING:
D.
FUEL DRAINING FROM THE AFFECTED COMPONENT AFTER SEVERAL MINUTES OF HEAT APPLICATION DOES NOT NECESSARILY INDICATE THAT ALL ICE HAS MELTED. LUMPS OF ICE MAY STILL REMAIN IN THE UNIT AND COULD BE A SERIOUS FLIGHT HAZARD. CONTINUE TO APPLY HEAT FOR A SHORT TIME AFTER FUEL BEGINS TO FLOW FROM THE DRAIN AND INSPECT THE DRAINAGE FREQUENTLY UNTIL IT IS EVIDENT THAT ALL WATER HAS BEEN REMOVED.
A similar condition may exist in the lubrication system, with the water coming from condensation of air in the tank or engine case area. When a hot engine is shut down under low ambient temperature conditions and allowed to stand for a period of time in the open, the chances of ice in the fuel and lubrication systems are much more prevalent.
Extra precautions should be taken to prevent formation of ice, and systems should be checked for the presence of any ice during preflight inspections. 21.
HOT-WEATHER PROCEDURES A.
Normal starting procedures are used in hot weather. However, it should be noted that with ambient temperature in excess of 21"C (70"F) the applicable power check curve must be consulted to prevent engine overtemperatures.
GROUND TESTING 22.
GENERAL A.
Purpose
(1)
and Definitions
Ground testing is intended to give an engine a thorough test for mechanical soundness and for correct indications of operating parameters. To avoid repeating the instructions, the following checks are based on reversing engines which utilize the fuel cut-off lever as a means of controlling starting and shutdown. On non-reversing engines this is accomplished by the initial movement of the power control lever to the IDLE detent. In cases of conflict between the instructions in this manual and those in the applicable aircraft manual, the latter will apply. To eliminate unnecessary ground running, ground testing is divided into ground test procedures or checks, as follows:
NOTE:
Although procedures for ground testing are described herein, the appropriate airframe manufacturer’s manual must be consulted for detailed procedures, curves or tables required to carry out the tests.
(a)
Check No. 1-
Prestart
(b)
Check No. 2
Engine Start
(c)
Check No. 3
Setting
Maximum Gas Generator
(d)
Check No. 4
Engine
Performance and Data Plate
(e)
Check No. 5 -Acceleration
(f)
Check No. 6
Engine
Speed Speed
Check/Adjustment
Shutdown
Page 2-6-14 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CHECK NO. 1 A.
PRESTART
Procedure ON ENGINES WITH FUEL CONTROL UNITS HAVING A MANUAL OVERRIDE SYSTEM INSTALLED, MAKE SURE THAT LEVER IS IN FULL OFF POSITION (FULLY COUNTERCLOCKWISE) OR AN OVERTEMPERATURE CONDITION WILL RESULT DURING START.
CAUTION:
(1)
Thoroughly inspect engine inlet and ensure that it is clear of loose nuts, bolts, tools, and other objects which could cause engine damage and possible subsequent engine failure.
(2)
Inspect run-up area in vicinity of engine inlet and exhaust, objects which might possibly be ingested by the engine or the velocity of exhaust gases and propeller blast.
(3)
Check level in oil tank. Refer to Part 2, Section 1.
(4)
Check for
(5)
Check fuel
Check
of oil in exhaust duct, and for evidence of oil
system for presence of
leaking
into intake.
water.
DO NOT SELECT REVERSE WITH PROPELLER WILL OCCUR TO THE REVERSING LINKAGE.
CAUTION:
(6)
signs
and remove any loose be blown rearward by
STATIC, AS DAMAGE
travel, freedom movement, propeller engine t ce rroc dn a controls for full
and
of
direction.
24.
CHECK NO. 2 A.
ENGINE START
Procedure
(1)
Power control lever
(2)
Propeller
(3)
Fuel cut-off lever- OFF.
(4)
Engine
(5)
Engine fuel shut-off
(6)
Fuel boost pump
(7)
Hold
(8)
INCREASE SPEED.
control lever
ON.
master switch
engine
CAUTION:
IDLE.
switch
ON
OPEN.
(engine
starter and
ignition
fuel inlet pressure 5 switches at ON
psig minimum).
position simultaneously.
BE PREPARED TO ABORT START IF TURBINE TEMPERATURE RISES AT AN ABNORMAL RATE, OR IF INDICATIONS ARE THAT THE MAXIMUM ALLOWABLE TURBINE TEMPERATURE MAY BE EXCEEDED. ENSURE THAT ENGINE ACCELERATES NORMALLY TO IDLE RPM.
As the gas generator speed passes through or has stabilized above the minimum light off speed, advance fuel cut-off lever to OPEN.
Page 2-6-15 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(9)
engine
Ensure
accelerates
normally
to idle rpm and oil pressure is not less than 40
psig.
(10)
NOTE:
Successful ignition normally takes place approximately ten seconds after moving fuel cut-off lever to OPEN and is indicated by a rise in TIT or ITT.
Release
engine
starter and
ignitions
switches when gas generator has reached idle
rpm. 25.
UNSATISFACTORY START A.
Procedure
(1)
unsatisfactory place:
An
conditions take
Hot Start Turbine temperature exceeds starting temperature limit. If greater than normal fuel flow is observed when fuel cut-off lever is moved to OPEN, a hot start may be anticipated and operator should be prepared to abort start before starting temperature limits are exceeded. Hot starts may also be caused
by (b)
following
IF TURBINE TEMPERATURE CONTINUES TO RISE, OPERATOR SHOULD BE PREPARED TO ABORT START BEFORE TEMPERATURE LIMITS ARE EXCEEDED.
CAUTION:
(a)
start will occur if one or more of the
False
False
or
or
Hung
Start.
Hung Start
After
lightup
has occurred, rpm remains at lower than Idle
rpm.
CAUTION:
(c)
26.
WHENEVER ENGINE FAILS TO LIGHT UP WITHIN 10 SECONDS AFTER MOVING FUEL CUT-OFF LEVER TO OPEN, SWITCH OFF FUEL AND IGNITION. ALLOW A 30 SECOND FUEL DRAINING PERIOD, FOLLOWED BY A MOTORING RUN, BEFORE ATTEMPTING ANOTHER START.
Engine does not light up within 10 seconds of moving fuel cut-off lever to OPEN, if turbine temperature gage does not indicate a rise in temperature, or if there is no increase in rpm, place fuel cut-off lever to OFF. No Start
MOTORING RUN A.
General
Following
an
unsatisfactory start,
clear
engine
of
trapped
fuel
or
vapors with
a
motoring
run.
B.
Procedure
(1)
Power control lever
(2)
Fuel cut-off lever- OFF.
(3)
Engine
master switch
IDLE.
ON
(to supply electrical power
to
starter).
Page 2-6-16 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(4) (5)
Engine
fuel shut-off switch
Fuel boost pump switch
ON.
(to provide lubrication
ON
for
engine
driven fuel
pumping
elements)
27.
(6)
Leave
(7)
Hold
(8)
Release
(9)
After
engine
switch in OFF
position.
starter switch ON for 10 seconds duration.
engine
starter switch.
engine rundown,
switch fuel boost pump
(10)
Engine
fuel shut-off switch
(11)
Engine
master switch
(12)
Allow the
CHECK NO. 3 A.
ignition
OFF.
OFF.
OFF.
required cooling period
for the starter before any further starter
operation.
SETTING MAXIMUM GENERATOR SPEED
Procedure
(1)
calibrated during bench test to provide maximum power and temperature rating on an 18"C (65"F) day. If engine inlet temperature is other than 18"C (65"F), it is impossible to set the maximum gas generator speed without exceeding either temperature or torque limits. To overcome this, a movable spacer is placed between the gas generator maximum speed (Ng) stop and the lever anvil. This spacer is called the part power trim stop and represents a constant Ng speed decrement. Permanently attached to the gas generator maximum speed stop, the part power trim stop may be removed from its stowed position as follows: Fuel control units
are
CAUTION:
THE MAXIMUM GOVERNING SPEED STOP IS PRESET ON ALL FUEL CONTROLS AND THE FOLLOWING PROCEDURE SHOULD NOT BE DONE UNLESS ABSOLUTELY ESSENTIAL. THIS PROCEDURE WILL ONLY BE POSSIBLE AT RELATIVELY HIGH AMBIENT TEMPERATURES.
CAUTION:
DURING CHECKS AND ADJUSTMENTS, IT MAY BE NECESSARY TO EXCEED 97.1% Ng TO ACHIEVE MAXIMUM Ng AT ALTITUDE (101.5%). CAUTION MUST BE USED; DURING ADJUSTMENT AND NORMAL OPERATION TO MAKE SURE ENGINE OPERATING LIMITS ARE NOT EXCEEDED (REF TABLES 2-6-1 and 2-6-2).
(a)
Loosen
screw
holding part power
trim
stop
to gas
generator maximum speed
stop.
(b)
Position part power trim stop between power lever anvil and maximum gas generator speed stop.
(c)
trimming, run engine operating temperatures. Prior to
for
approximately
two minutes to obtain normal
Page 2-6-17 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
Adjustment of Gas Generator Control
(1)
I
With power lever and propeller control lever full forward, adjust maximum gas generator control to obtain 97.1% gas generator (Ng) speed. One complete turn of gas generator speed control changes gas generator speed by approximately one percent. At completion, proceed as follows: (See Figure 2-6-7).
(a) Carry
28.
I
(b)
Stow and
(c)
Safety
engine safety
wire gas
shut-down check. wire
part power trim stop (9).
generator maximum speed adjustment (4).
TRIM SPEED DATA PLATE A.
29.
out
plate trim speed is gas generator speed (Ng) obtained with engine running at reference power on a standard day 15"C (59"F). This value is determined from final acceptance test, and each engine has its individual value stamped on trim speed data plate in rpm and as a percentage of maximum gas generator speed at a reference power of 476 shp/DELRTH. Data
CHECK NO. 4 A.
ENGINE PERFORMANCE AND DATA PLATE TRIM SPEED
General
(1)
Engine performance and data plate trim speed check curve enables engine performance to be checked over a wide range of ambient temperatures without overtorque or overtemperature of the engine.
(2)
engine performance checks should be carried out and changes in engine performance noted. All forms of engine deterioration are accompanied by an increase in turbine temperature and fuel flow at a given power. Compressor deterioration is, in most cases, due to dirt deposits and causes an increase in gas generator speed at a given power setting. This form of deterioration can be remedied by field cleaning (refer to Cleaning). Hot section deterioration results in decreased gas generator speed at a given power setting. Determine engine performance check parameters as follows: Periodic
(a)
Obtain ambient air temperature.
(b)
Obtain field barometric pressure
(c)
Obtain reference rpm from
(d)
From
(not
engine
corrected to
trim
speed
sea
data
level).
plate.
engine performance check curve, obtain fuel flow, torquemeter pressure, generator/data plate trim speed and turbine temperature for ambient
gas conditions. Record these values. B.
Performance Check Procedure NOTE:
This check should be carried out without bleed air operation of aircraft auxiliaries.
or
power extraction for
Page 2-6-18 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(1)
Determine the values of parameters
(2)
Carry
out
(3)
Effect
a
(4)
Run at idle rpm to
(5)
Advance power control lever to previously recorded torque setting with the applicable propeller shaft speed (Np) or output shaft speed (Ns).
(6)
pre-start check. (Refer
satisfactory engine warm
up
start.
as
to
detailed in
Paragraph 23., preceding).
(Refer
engine
Paragraph A., preceding.
to
Paragraph 24., preceding.)
and to stabilize instruments.
Compare observed fuel flow, gas generator speed and previously recorded.
turbine temperature with
values
(7)
Ensure that values observed during are within the following limits:
engine performance
and data
plate
trim
speed
check
15 Ib/hr fuel flow.
(a) (b)
rt 0.02 gas generator speed data plate trim speed ratio. (Ratio generator speed t data plate trim speed.)
(c)
30"C turbine temperature. If temperature is temperature, check instrumentation. NOTE:
(8) 30.
more
observed gas
than 30"C below chart
The above limits cover normal engine deterioration but deviations should not necessarily be cause for engine rejection until all possible troubleshooting has been completed (refer to Troubleshooting, following). Renewal or rework of hot section parts during hot section inspection can affect parameters, particularly gas generator speed ratio. Any increase in speed should be noted and recorded for future reference. The importance of monitoring the performance trend of an engine throughout its history cannot be overemphasized.
Carry out an engine shut-down check. (Refer Engine Shut Down, following.)
to
Paragraph 32.,
Check No. 6
CHECK NO. 5 -ACCELERATION CHECWADJUSTMENT A.
Procedure NOTE:
adjustment of acceleration time is considered necessary, an engine performance check should be carried out prior to making any adjustment. This will ensure the suspected acceleration problem is not due to engine When
deterioration
or
bleed valve malfunction.
(1)
Start
(2)
Set
(3)
Rapidly (less
(4)
Note and record time
engine
Ng
and
operate
at IDLE for five minutes to allow stabilization of
temperature.
to 64%.
than 1.0
second)
move
required for Ng
power control lever to maximum. to reach 97.5%.
Page 2-6-19 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION UNINSTALLED NO LOSS CONDITIONS. UNDER NO CIRCUMSTANCES MUST S.O.I. LIMITS BE EXCEEDED. TORQUE LIMIT
NOTES 1 FOR 2000 RPM (Np) OUT SPEED 2 1700 RPM (N9) PART POWER TRIM STOP 3 STATIC CONDITIONS 4 MAXIMUM OBSERVED
42
40
Ng=36400 (97.1%)
~U
i 5 TORQUE LB-FT= 30.87( PSI
´•p,
1
a
?b
~i
i~
38
~0O 34
~00
32
w rr
´•tf
30
700
~i
C-
28
650 26
"in I I
0
10
i
I
Ilnli
20
I
Ii
M
30
i
I I I i
i
I
I I
40
I
I
i
11
11111
50
1
1111111
1
I
I
60
I
I
1
111111’11’11:Tr
70
AMBIENT TEMPERATURE
PT6A20 Series
1
i
I
80
I
i
I
I 11rrr\l
90
I
i
I I i
I
100
I
;d:
I
110
120
F
Engines
C239C
Part Power Trim Check Curve Figure 2-6-6 (Sheet 1 of 2)
Page 2-6-20 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
~TORQUE ~L!M!T 1 FOR 2000 RPM (Np) OUTPUT SPEED 2 1700 RPM (Ng) PART POWER TRIM STOP 3 STATIC CONDITIONS 4 MAXIMUM OBSERVED
40
Ng=36400 (97.1%)
~PC:
5 TORQUE LB-FT
30.87< PSI
vi p: w
38
~3C: O
36
~49
34
~PO’ 32
;PO~ 1000
k 950
28
900
mY
26
CAUTION #FFFFFFFFFFFFfF##rFC 850 UNINSTALLED NO LOSS CONDITIONS. UNDER NO CIRCUMSTANCES MUST S.O.I. LIMITS BE EXCEEDED.
0
10
20
30
40
50
60
70
AMBIENT TEMPERATURE
PT6A6 Series
80
90
100
110
120
F
Engines
C756B
Part Power Trim Check Curve
Figure
2-6-6
(Sheet 2)
Page 2-6-21 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
2 3 4
)(5
i~ I
8 C
io
7)(6
9)(8
,´•I
’r
C2358
Adjustment -Typical Figure 2-6-7
Fuel Control
Page 2-6-22 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
Key Minimum Hi-idle
4.
5.
6. 7.
8. 9.
(5)
Figure
2-6-7
Governing Speed Adjustment (IDLE) Speed Adjustment Idle Cut-off Lever Stop Maximum Ng Speed Adjustment Fuel Pump Inlet Screen Fuel Pump Inlet Fuel Pump Outlet FCU Sensing Line Part Power Trim Stop
1. 2. 3.
to
10.
FCU Outlet
11.
Acceleration Dome
Immediately Ng
passes
through 97.5%,
retard power control lever to IDLE.
IF ACCELERATION CHECK IS DONE AFTER COMPRESSOR RUNNING
CAUTION:
WASH, CHECK P3 FILTER/FORWARD AIR TUBE FOR CONTAMINATION/ BLOCKAGE. DO NOT ADJUST FCU.
(6)
I
31.
Acceleration time must fall within the range specified in Figure 2-6-9. If not, rotate acceleration adjuster dome (11, Figure 2-6-7) one click at a time until requirement is met. Rotate dome clockwise to reduce acceleration time (faster acceleration), or counterclockwise to increase acceleration time (slower acceleration). If requirement cannot be met within a maximum of three clicks in either direction, replace fuel control unit.
TORQUEMETER FUNCTION TEST A.
Procedure
(1)
Determine and record field barometric pressure NOTE:
Pressure altitude may be obtained
(pressure altitude (ft)).
by setting
Kolsman window in altimeter
to 29.92 inches of mercury, position of needle will give value in feet or contacting the local flight service for an uncorrected pressure reading.
Do not
(2)
level pressure
normally supplied by
Determine and record indicated outside air temperature NOTE:
(3)
use sea
by
tower.
(IOAT)
in
degrees
celsius.
To make sure result of torquemeter function test is accurate, determine and record IOAT immediately before engine start. Use IOAT value recorded to determine take-off torque (Ref. step (3)).
Using flight manual chart, determine the take-off torque (target torque) at which to engine using pressure altitude (ft) and IOAT recorded at step (1) and step (2) respectively. Record the value.
set
(4)
Start
(5)
Switch off generator, bleed air and air
engine (Ref.
Para.
8.).
conditioning.
Page 2-6-23 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION UNINSTALLED NO LOSS CONDITIONS. UNDER NO CIRCUMSTANCES MUST S.O.I. LIMITS BE EXCEEDED.
42
W
38
a
36
e ~j
26.00 27.00
26.00
34 24.00
32
23.00
0
30 28
320 I
S
280 24.00
260 h
240 p C~ W ww
1.05
a~l w,0.95 C3a
a
0
700
Wo
ZW
NOTES
600 a
1. FOR 2000 RPM OUTPUT SPEED 2. STATIC CONDITIONS 3. REFERENCE POWER 476SHP 1 6
w
500
11 a
4. TORQUE LB-FT =30.87x PSI
-40 -30 -20-10
O
10
20
30
40
50
60
70
80
90
100 110 120
AMBIENT TEMPERATURE "F
PT6A20 Series
Engine
Engines
C240C
Performance and Data Plate Trim Speed Check Curve Figure 2-6-8 (Sheet 1 of 2)
Page 2-6-24 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FIELD BAROMETRIC PRESSURE
42
31100_IN.
g 38
g
27.00
36
~s 34 6
32 30 28
31 narc
340
~320 300
280 24.00
260
22.00
240
5) 1.05
P YW
CAUTION
UNINSTALLED NO LOSS CONDITIONS. UNDER NO
"d
CIRCUMSTANCES MUST S.O.I. LIMITS BE EXCEEDED. 1000
950
Wo
zu
900
I~ Be ~B
sso
NOTES 800
i 1. FOR 2000 RPM OUTPUT SPEED 2. STATIC CONDITIONS 3. REFERENCE POWER 476SHP 1 6 4. TORQUE LB-FT
750
-40
-30
-20
-10
0
10
20
30
40
50
~1 a
30.87X PSI
60
70
80
90
100
110
120
AMBIENT TEMPERATURE OF
PT6A6 Series
C341B
Engines
Engine Performance and Data Plate Trim Speed Figure 2-6-8 (Sheet 2)
Check Curve
Page 2-6-25 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
5.0
4.5
4.0
F
3.5
2.5
2.0
-20
0
60
40
20
Ttl AMBIENT TEMPERATURE
80
100
F
C1542A Ambient Figure 2-6-9
Acceleration Time
vs
Temperature
Page 2-6-26 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
control lever is in
(6)
Check
(7)
Check oil temperature is above 60"C.
(8)
Set
(9)
Record
(10)
propeller
Ng
500 rpm above
Ng, Np
Accelerate
and
Allow
engine slowly
(12)
Reduce
engine
idle
rpm.
(Ref. Operating Limitations).
engine torque (Tq).
target torque recorded
(11)
ground
high
and at
uniformly
at a rate of 2000 rpm per second until
step (3) is reached.
to stabilize for two minutes.
Ng slowly
and
uniformly
at
a
rate of 2000 rpm per second to
Ng
set at
step
(8).
(13)
Record
(14)
Repeat steps (10)
(15)
Reduce
(16)
Shut down
(17)
The
Ng, Np
Ng
to
and
Tq. to
(13).
ground-idle.
engine (Ref. Para. 9.).
engine torque indication system functions correctly when the difference Tq recorded in steps (12) (13) and (14) is equal to or less than 200
between
(18)
If the difference between the torque readings is in excess of 150 Ib.ft. check aircraft indication system. If the aircraft indicating system check is satisfactory, the power section is recommended to be removed and the torquemeter piston, cylinder and servo valve inspected at an authorized facility for excessive wear, scoring,
fretting, 32.
CHECK NO. 6 A.
Ib.ft.
etc.
ENGINE SHUT-DOWN
Procedure CAUTION:
WHILE THE AIRCRAFT IS UNATTENDED, ENSURE THAT THE PROPELLER IS TIED DOWN TO PREVENT WINDMILLING WITH ZERO OIL PRESSURE.
(1)
Retard power control lever to IDLE.
(2)
Allow
(3)
Propeller
(4)
Move fuel cut-off lever to OFF.
engine to stabilize for minimum of one minute (PT6A-20 series) or TIT (PT6A-6 series).
NOTE:
control lever to FEATHER
at minimum obtainable ITT
position.
change from normal gas generator (approximately 40 to 50 seconds).
Observe any
run-down time
Page 2-6-27 Apr 02/2004
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(5)
After rundown, switch fuel boost pump OFF. NOTE:
To
prevent possible bleeding of fuel lines and fuel pump cavitation, shut off
switching aircraft
fuel to engine by moving fuel cut-off lever OFF before boost pump OFF.
(6)
Engine
fuel shut-off switch
(7)
Engine
master switch
(8)
Listen for any unusual
(9)
Check fuel
(10)
dump
OFF.
OFF.
engine
noise such
valve and gas
as
generator
scraping, rubbing
case
grinding.
drain valves for correct
engine oil lines and connections for leaks. None normal seepage drains.
Check all
NOTE:
or
are
operation.
allowed, except
at
Allowable oil seepage is 3cc/hour at each accessory drive pad, and 5 cc/hour at the propeller shaft. All seal leakages shall be included in total oil
consumption. (11)
If engine is scheduled to remain inactive for an extended period, install and exhaust covers after engine has cooled down sufficiently.
(12)
Check the oil-to-fuel heater within 15 min. after engine shutdown for a high operating temperature (Ref. Section 3, Part 3, INSPECTION, Periodic Inspection). A heater fuel outlet or a fuel pump filter cover having a temperature above 140"F (60"C) after shutdown shows a heater that does not correctly operate. To measure the
temperature of the oil-to-fuel heater, do
NOTE:
The
WARNING:
inspection of
If the
the oil-to-fuel heater is
heater fuel outlet
or
a
following procedures:
minor
inspection requirement.
the fuel pump filter cover.
temperature of the heater fuel outlet
unusually hot, replace 2
of the
inlet
MAKE SURE PROTECTIVE CLOTHING IS PUT ON WHEN MANUALLY CHECKING THE TEMPERATURE OF THE HEATER FUEL OUTLET OR THE FUEL PUMP FILTER COVER. THE OIL-TO-FUEL HEATER CAN GET HOT. THIS WILL PREVENT POSSIBLE INJURY TO PERSONNEL.
(a) Carefully feel the 1
one
engine
or
the fuel pump filter
cover
feels
the oil-to-fuel heater.
If a high temperature is not felt, remove the protective clothing and carefully check the heater fuel outlet or the fuel pump filter cover again. the oil-to-fuel heater is operating correctly, the heater fuel outlet and the
pump filter
cover
If fuel
should be comfortable to touch.
Page 2-6-28 Apr 02/2004
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
A NEW TEMPERATURE RECORDER MUST BE USED FOR EACH
INSPECTION.
(b)
Put
a
cover.
temperature recorder on the heater fuel outlet or the fuel pump filter If the temperature recorder shows a temperature above 140"F
(60"C), replace NOTE: 33.
A
the oil-to-fuel heater.
Temp-Plate Temperature
PERMISSIBLE FIELD ADJUSTMENT A.
Recorder
(PWC05-329)
can
be used.
COMPONENTS
General CAUTION:
(1) (2)
ADJUSTING SCREWS MUST BE TURNED ONLY IN INCREMENTS OF 1/8 OF A TURN AT ANY ONE TIME. POWER TURBINE GOVERNOR MINIMUM SPEED ADJUSTMENT SHOULD BE TURNED IN EVEN FINER INCREMENTS.
Propeller governor maximum speed stop PT6A-20A and PT6A-20B engines only.
(refer to
Part 1,
Prop Reversing Installation).
Power turbine governor minimum and maximum governing speed adjustments Figure 2-6-10). All engines except PT6A-20A and PT6A-20B.
(1
and 2,
I
(3)
Propeller
governor, PT6A-20A and PT6A-20B
engines only. (See Figure 2-6-11)
(a) Feathering adjustment. (b) (4)
1
Maximum
speed stop.
Fuel control unit: All
(a)
Maximum
(b)
Minimum
engines. (See Figure 2-6-7)
Ng speed adjustment (4). governing speed adjustment (1).
CHECKS AFTER COMPONENT REPAIR 34.
REPLACEMENT
GENERAL A.
The checks to be carried out following the repair of replacement of various engine components are provided in Table 2-6-3. This table refers to the six test checks described
preceding paragraphs in addition to the following checks, the latter being more frequently associated with replacement of power section and certain engine components. in
Page 2-6-29 Apr 02/2004
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PT6A-6 and -20
Engines
C236C
Power Turbine Governor Adjustments Figure 2-6-10
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
Key Maximum
1.
to
Figure
2-6-10
Governing Speed Adjustment (Power
Turbine
Speed) Control Arm
2.
(Clockwise
to
Increase)
TABLE 2-6-3, Ground Checks after
Component Replacement Check
Req’d (Para. No.)
Component Power Turbine Governor
Compressor
1,2,4,6 and Paragraphs 37., 38.
Bleed Valve
1,2,3,4,5,6 and Paragraph 39.
Propeller Governor (PT6A-20A and -208 Engines only) (For other models refer to airframe manual requirements)
1,2,4,5,6 and Paragraph 35.
Starter-Generator
1,2,6
Ignition System Components
1,2,6
Fuel Nozzles
1,2,3,4,5,6
Fuel
Dump Valve,
Manifold
or
Fuel Lines
1,2,4,6
Fuel Control Unit Fuel
1,2,3,4,5,6 and Paragraph 40.
Pump
1,2,3,4,5,6 and Paragraph 1,2,3,4,6 and Checks in
Power Section
Paragraphs
41.
Paragraphs 35., 36., 37.,
are
required in addition
38..
to
checks 1 to 6.
Scavenge
Oil Tubes
22,23,31
Shaft Oil Seals NOTE:
35.
22,23,31 Table 2-6-3 intended to be used only after maintenance manual instructions on removal and installation of components and their subsequent depreservation (where applicable) have been fully complied with.
PROPELLER GOVERNOR CHECKS (PT6A-20A AND PT6A-20B ENGINES A.
Procedure
ONLY)
(See Figure 2-6-11)
(1)
Disconnect and cap governor air pressure tube at governor.
(2)
Perform
(3)
Start
engine. (Refer
(4)
Allow
engine
pre-start check. (Refer to
to
Paragraph 23., preceding.)
Paragraph 24., preceding.)
to stabilize at idle with oil
temperature in normal operating range.
Page 2-6-31 Apr 02/2004
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
6
4
II
jl
ii_
ii!
_1/
ii:
1111ia
r
C
i" r’´•
1
I;
PT6A-20A and -20B
Engines
C41511
Propeller Governor Adjustments Figure 2-6-11
Page 2-6-32 Apr 02/2004
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
Key
Figure
2-6-11
5.
Adjustment (NOT FOR Speed Adjustment Feathering Adjustment Pneumatic Minimum Eccentric Adjustment Air Bleed Link (Reset Arm)
6.
Interconnect Rod
7.
Push-pull Control Speed Adjusting Lever
Pneumatic Maximum
1.
FIELD
USE)
Governor Maximum
2. 3. 4.
8.
(5)
to
Ensure condition lever is set to LO-IDLE and
perform
two
feathering cycles
to purge
air from system.
If
NOTE:
feathering
time exceeds the airframe manufacturer’s
recommendations,
be decreased by turning the feathering adjusting screw (3) counterclockwise. Two turns from the nominal setting is the maximum adjustment permitted in the counterclockwise direction. it
can
(6)
With
(7)
Adjust propeller governor maximum speed adjustment (2) desired maximum propeller speed (Np).
(8)
control lever selected to full fine pitch position, advance power control lever to obtain sufficient power to allow the propeller to constant speed.
propeller
Np, torque, fuel flow and power Step (7) preceding.
Record
lever
as
position tangle
required
or
travel
to obtain
as
applicable)
obtained in
(9)
(10)
1
verify proper setting of pneumatic section of governor reconnect governor air pressure tube. Reset power lever to the position recorded in Step (8) preceding and check that Ng has not decreased. If a change in Ng occurs, recheck that propeller governor reset lever is locked hard against the stop. DO NOT ADJUST STOP. An Ng change of up to 100 rpm is acceptable. If change is greater than permissible limit of 100 rpm, propeller governor must be replaced.
To
To check
and
(11)
Re-run
power speed disconnect the interconnect rod the air bleed link (5) to the minimum stop.
reverse
secure
(6, Figure 2-6-11)
1% of to settings of Step (6), and check that Np governs at 95% speed set in Step (6), adjust pneumatic minimum eccentric adjustment required.
engine
the maximum
(4) (12)
as
Reconnect rod
(6)
to link
(5). Tighten nut, torque
to 24 to 36
Ib.in., and lock with
cotterpin. 36.
PROPELLER FEATHERING CHECK A.
PT6A-6 SERIES AND PT6A-20 ENGINES
Procedure
(1)
Perform
a
pre-start check. (Refer
to
Paragraph 23., preceding.)
Page 2-6-33 Apr 02/2004
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(2)
Accomplish
(3)
Allow
satisfactory engine
a
engine
to warm up to
start.
(Refer
Paragraph 24., preceding.)
to
operating temperature,
and
engine
instruments
to
stabilize at idle rpm.
(4)
With fuel cut-off lever at LO-IDLE, move propeller control lever to feathering position. A considerable reduction in power turbine speed should be observed
indicating
37.
has been
accomplished.
(5)
Return propeller control lever to the INCREASED position and observe that propeller shaft speed is regained.
(6)
Feather
two or three times to purge all air from
propeller
POWER TURBINE GOVERNOR CHECK A.
system.
PT6A-6 SERIES AND PT6A-20 ENGINES
Procedure
(1)
I
satisfactory feathering of propeller
that
If the power turbine governor has been follows: (See Figure 2-6-10)
replaced
or
its
operation suspect, proceed
as
(a)
Speed:
Minimum
1
Remove
2
Disconnect and
if 3
propeller overspeed governor and replace Manual).
with
a
blanking plate.
to Airframe Manufacturer’s
(Refer
secure
reversing linkage
from power turbine governor arm,
applicable.
Move governor control in this position.
arm
(2)
counterclockwise to minimum
speed
and
secure
pre-start check. (Refer
4
Perform
5
Accomplish
6
Warm
a
a
engine
satisfactory engine to
to
Paragraph 23., preceding.)
start.
operating temperature,
(Refer
to
Paragraph 24., preceding.)
and allow
engine
instruments to
stabilize at idle rpm.
Z
With
propeller
control lever in INCREASE position, advance power control governing action at 94% (+1%) propeller shaft speed
lever and observe
(Np).
governing point is reached when further movement of power produces no increase in propeller shaft speed. If propeller 1%, replace power turbine speed is not governed within 94%
The
control lever
shaft
governor. NOTE:
Adjust
in
extremely fine
increments
only.
Page 2-6-34 Apr 02/2004
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
8
Move power turbine governor control arm (2) clockwise to maximum and secure in this position.
governing speed stop,
If power turbine governor has been replaced, a reverse thrust check (refer to airframe manufacturer’s manual) must be carried out in addition to power turbine governor check. (Not
NOTE:
performance applicable (b)
Maximum
1
(c)
non-reversing PT6A-6.)
Speed:
On most aircraft installations, either the propeller fine pitch setting restricts the propeller speed (Np) at static conditions, or the travel of the maximum governor speed stop is limited, making it impossible to check the overspeed setting. However, if the governor maximum setting is suspected of limiting engine power, it may be checked as follows:
engine
stop with propeller in full fine pitch and record Ng.
a
Run
b
Disconnect governor air pressure tube from power turbine governor and install blanking plug in tube.
c
Re-run
Z!
If Ng has increased, reconnect tube. Adjust power turbine governor maximum speed adjustment counterclockwise in 1/8 turn increments to a maximum of one turn until power condition of Step c is obtained.
After checks
1
to
Reinstall
to trim
engine
as
in
Step
a
preceding,
ensure
Ng
has not increased.
completed:
propeller overspeed governor. (Refer
to Airframe Manufacturer’s
Manual). 2
38.
Reconnect
reversing linkage
POWER TURBINE GOVERNOR CHECK A.
to power turbine governor arm, if
applicable.
PTGB SERIES ENGINES
The power turbine governor is a droop-type governor with approximately S%droop from the no-load condition to the full-load condition. For the approved method of checking the power turbine governor refer to the aircraft manufacturers instructions. Provision is made for minimum and maximum speed (Nf) adjustment on the governor body. (See
Figure 2-6-10)
I 39.
COMPRESSOR BLEED VALVE CAUTION:
A.
ADJUSTMENTS ARE CARRIED OUT ONLY UNDER CONTROLLED CONDITIONS ATOVERHAUL.
Unsatisfactory part power and performance checks may indicate compressor bleed valve malfunction. For symptoms of compressor bleed valve malfunction, refer to Section Troubleshooting, following.
Page 2-6-35 Apr 02/2004
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
40.
FUEL CONTROL UNIT CHECK A.
Procedure
(1)
Carry
out
to OPEN
41.
(refer
check for
with another
(2)
Dry out engine preceding.
(3)
Perform checks Nos. 1
Paragraph 26., preceding), fuel system leaks. to
motoring
through
6
(refer
to
as
run
in accordance with
detailed in
Paragraphs
with fuel cut-off lever
Paragraph 26.,
23. to 32.,
preceding).
Procedure
(1)
Carry
motoring position, to
out a
to OPEN
run
Paragraph 26., preceding),
with fuel cut-off lever
check for fuel system leaks.
with another
(2)
Dry out engine preceding.
(3)
Perform checks Nos. 1
motoring
through
6
as
run
in accordance with
detailed in
Paragraphs
Paragraph 26.,
23. to 32.,
preceding).
CHECKS AFTER COMPONENT REPLACEMENT
fitting components
ground checks
referenced in Table 2-6-3.
A.
After
B.
The pneumatic portion of fuel control system must be pressure tested whenever leakage in any portion of the system is suspected. Any leakage will adversely affect operation of fuel control. For fuel control pneumatic system pressure testing refer to Paragraph 43.
43.
run
FUEL PUMP CHECK A.
42.
motoring position, to a
carry out
as
following.
PRESSURE TESTING FUEL CONTROL PNEUMATIC SYSTEM A.
Procedure
(1)
Disconnect compressor
delivery
tube
assembly
from 90" elbow
on
gas
generator
case.
front face of center
(2)
Remove two bolts which secure 90" elbow sealing sleeve fireseal mount ring. Remove sealing sleeve.
(3)
Remove bolts securing compressor air Remove elbow and gasket.
delivery
(4)
Connect AN832-4 union to compressor
delivery tube assembly.
(5)
Connect
supply
of clean,
dry
air
regulated
to 80
on
90" elbow to gas
(~5) psi
generator
case.
to union.
Page 2-6-36 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(6)
I
Apply suitable leak checking fluid (refer to Section 8, Consumable Materials, following) to entire surface of all connecting points throughout pneumatic control system (see Figure 2-6-12). Particular attention should be paid to that portion of system between temperature compensator and fuel control, and between fuel control and power turbine governor. No leaks are permitted other than bleed hole in base of FCU, from bleed to atmosphere in air inlet manifold, from window on side of FCU
body and from bleed hole in cover of P3 filter (if fitted). Slight sound of escaping coming from under side of power turbine governor can be disregarded.
air
(7)
all leak
Wipe
checking
found, affected parts pressure test of that
fluid from connections if
point is carried
(8)
Disconnect air
(9)
Remove AN832-4 union.
(10)
no
leaks
must be examined for defects and
are
found. If leaks
retorqued before
are
final
a
out.
supply.
Install compressor air delivery 90" elbow, together with gasket, in gas generator Secure elbow with two bolts, tighten bolts, and torque to 24 to 36 Ib.in.
case.
NOTE:
(11)
Install
Retaining bolts ground check.
sleeve over 90" elbow and
and lockwired after
completion
of
engine
hole provided in bottom half of sleeve fireseal mount ring with two to sealing ring. bolts and two self-locking nuts. Tighten nuts, and torque 32 to 36 Ib.in.
sealing
center fireseal mount
(12)
retorqued
must be
through
Secure
Assemble compressor air delivery tube to 90" elbow Tighten union, torque 90 to 100 Ib.in., and lockwire.
on
gas generator
case.
IDLE SPEED ADJUSTMENTS 44.
GENERAL A.
B.
At barometric pressures equivalent to altitudes less than 1500 feet above sea level, fuel flow is metered to maintain idle speed at a constant value, referred to as minimum governing speed. However, since the fuel flow required to maintain a constant idle speed decreases with increasing altitude, a point is reached where the fuel flow does not decrease further, this point being the minimum fuel flow setting. At altitudes higher than this point gas generator speed increases proportionally with altitude.
Usually
the minimum fuel flow
setting
will be lower than the minimum
governing speed. slightly higher than 28.0 in.Hg., the
However, under marginal conditions, that is, when altitude is close to
or
than 1500 feet and/or barometric pressure is close to or slightly less two speeds may coincide or Ng at minimum fuel flow may be higher than that at minimum governing.
C.
I
From the
speed adjustments should only be carried barometric high pressure. Figure 2-6-13 shows at minimum fuel flow for various barometric pressures.
preceding,
it will be
seen
that idle
out at conditions of low altitude and/or
typical Ng speeds
Page 2-6-37 Apr 02/2004
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
I’
I
PT6A-20A AND PT6A-20B
CONNECT AIR SUPPLY AT THIS POINT
C1851B Pressure
Testing
Fuel Control Pneumatic
Figure
System
2-6-12
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
63
62
i~ MAXIMUM Ng SPEED AT MINIMUM FUEL FLOW
59
58
57
MINIMUM Ng SPEED AT MINIMUM FUEL FLOW
56 z
P
55
CL:
54
w
53
z w
MINIMUM GOVERNING SPEED
52
50
49
48
47
46
30
29
28
27
26
25
24
23
BAROMETRIC PRESSURE
22
21
20
19
18
(INCHES H9)
C976A
Typical Gas
Generator
Speed Range
at Minimum Fuel Flow for Various Pressure Altitudes
Figure
2-6-13
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
45.
(IDLE) SPEED CHECK
MINIMUM GOVERNING A.
Procedure
DO NOT PERFORM CHECKS AT BAROMETRIC PRESSURES BELOW 28.0 IN.HG.OR ALTITUDES IN EXCESS OF 1500 FEET. CHECKS MUST BE PERFORMED WITH ZERO POWER EXTRACTION.
CAUTION:
(1)
Perform
(2)
Perform
(3)
Allow
prestart check. (Refer
a
a
satisfactory engine
engine
to
up to
warm
start.
to
Paragraph 23., preceding.)
(Refer
to
Paragraph 24., preceding.)
operating temperature
and instruments to stabilize at
idle rpm.
CAUTION:
IF INTERTURBINE TEMPERATURE (Tt5) OR TURBINE INLET TEMPERATURE (Tt4) RISES ABNORMALLY AT ANY TIME DURING IDLE SPEED CHECK, SHUT DOWN ENGINE IMMEDIATELY.
(4)
With propeller in fine idle Ng.
(5)
If
Ng
is 52%
(6)
If
Ng
is less than 51%,
direction,
1
46.
as
1%
pitch
no
required,
and oil temperature at 38"C
(100"F) minimum,
further action is necessary.
adjust speed adjustment (1, Figure 2-6-7)
to achieve 52%
in
a
(7)
If Ng is more than 53%, adjust speed adjustment (1, Figure 2-6-7) in 1%. counterclockwise direction, as required, to achieve 52%
(8)
If there is no response to unit must be replaced.
adjustments
clockwise
1%.
made in
(6)
or
(7), preceding,
MINIMUM FUEL FLOW ADJUSTMENT ON FUEL CONTROL UNIT A.
observe
a
the fuel control
(FCU)
Procedure NOTE:
(1)
(2)
The minimum fuel flow is pre-set on all fuel control units. This procedure should be accomplished during troubleshooting an individual engine starting problem where the minimum fuel flow setting is suspected.
Disconnect
Py
tube at FCU
or
Nf governor and leave open to atmosphere. Tube are not capped during this operation.
coupling
nuts and
Perform
prestart check (Refer
CAUTION:
component fittings to
Paragraph
23.
preceding).
CAREFULLY MONITOR T4 OR T5 LIMITS AS APPLICABLE. ENSURE LIMITS ARE NOT EXCEEDED.
(3)
engine (refer to Paragraph 24., preceding) operating temperature.
(4)
Check that indicated gas generator pressure (see Figure 2-6-14).
Start
speed (Ng)
and
run
at idle until stabilized at
is within +0.5
0.0% for altitude
Page 2-6-40 Apr 02/2004
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
63 62
60
58
54
Z
52
FT.
50
48
46
NOTE
NO POWER EXTRACTION NO CABIN AIR BLEED 44 -40
-30
-20
-10
0
AIR INLET TEMPERATURE
10
20
30
40
C
C13587
Gas Generator
Speed
for Pressure Altitude at Minimum Fuel Flow
Figure
2-6-14
Page 2-6-41 Apr 02/2004
WHITNEY CANADA
PRA~T
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(5)
1
ii fuel flow
is
ad~ustment
required, pmceed
as
follows.
DO NOT SLACKEN NUT A. ANY MOVEMENT WILL DISTURB MAIN METERINGVALVE AND NECESSITATE FCU RECALIBRATION AT AN OVERHAUL FACILITY.
CAUTION:
C and
(6)
Cut lockwire from nuts A and B and Alien
(7)
Hold nut A firmly with wrench and, using another wrench counterclockwise to loosen.
Using appropriate Alien wrench, adjust counterclockwise decreases Ng RPM.
screw
remove.
on
nut
B, carefully
turn
C, clockwise increases,
If there is no response to adjustment made in fuel control unit must be replaced.
NOTE:
(9)
screw
ADJUSTMENTS TO MINIMUM FUEL FLOW ARE EXTREMELY SENSITIVE ANDMUST BE MADE IN SMALL INCREMENTS.
CAUTION:
(8)
i)
(See Figure 2-6-15)
When correct 25 Ib.in.
Ng reached,
hold
screw
C and
preceding subparagraph,
tighten and torque
nut B 20 to
(10)
Shut down engine (refer to Paragraph 32. preceding) and connect Py tube to FCU or Nf governor as applicable. Tighten and torque Py tube coupling nuts 90 to 100 Ib.in. and lockwire.
(11)
Secure screw C and nuts A and B to lockwire.
mounting plate
attachment
screw
with
ENGINE FINAL CHECKOUT 47.
CHECKS AND ADJUSTMENTS A.
Procedure NOTE:
All
adjustments
must be made with the
Paragraph 23., preceding.)
(1)
Perform
(2)
Accomplish
(3)
Allow
(4)
On non-STOL aircraft, advance fuel cut-off lever slowly to HI-IDLE position and check that speed is within required range. If speed is incorrect, adjust HI-idle adjustment screw as required. (Turn clockwise to increase speed and
a
pre-start check. (Refer
engine stopped.
a
engine
satisfactory engine to
warm
up to
(5)
start.
(Refer
to
Paragraph 24., preceding.)
operating temperature
counterclockwise to decrease.
I
to
and stabilize at idle rpm.
(See Figure 2-6-7)
On STOL aircraft, with fuel cut-off lever at HI-IDLE position, slowly retard propeller control lever to between 85% and 90% Nf. If Hi-idle speed is incorrect, make necessary adjustment as outlined in Subparagraph (4) preceding.
Page 2-6-42 Apr 02/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
QI
V In~l
!I
a U
C -----clJllllllr
3)
~9-/ "5~
C9285 Minimum Fuel Flow Adjustment Figure 2-6-15
Page 2-6-43/44 Apr 02/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 2
I
GENERAL PROCEDVRES
SECTION 7 -TROUBLESHOOTING 1.
GENERAL A.
Procedure For details on recommended procedures for engine system troubleshooting, reference should be made to Tables 2-7-1 through 2-7-5. Each table comprises a series of diagnostic tests and rectification sequences which will assist an operator in discovering, isolating and correcting various troubles that may arise in the basic engine or any of its related
systems during service.
(1)
Discovering
the Trouble
hidden. If hidden troubles are not occur to the engine. Therefore, it is essential to have a thorough knowledge of correct turbine gas temperature and other important details of engine operation. Before attempting to locate a trouble or difficulty, or to work on an engine which has been malfunctioning during flight, consult flight log and any other available data which could help in diagnosing the
Engine
troubles
can
be either obvious
or
detected, serious and considerable damage may
trouble.
(2)
Isolating
the Trouble
it is necessary to have information of previous trouble, if any, and work which has been performed on the engine. Check each probable source of trouble, by use of relevant diagnostic test sequences, until defect has been isolated. Systematic checking is essential for thorough troubleshooting and will
To
correctly isolate trouble,
save
2.
time and extend
engine
life.
ENGINE CONDITION TREND MONITORING SYSTEM A.
turbine/turboprop engine maintenance practices frequently include in-flight engine performance monitoring as a means of detecting mechanical deterioration in engine gas paths. A simple system, requiring almost no arithmetic calculation, has been devised for the PTGA engine to aid in early planning of indicated rectifications, and thus reduce the potential costs of primary and secondary damage resulting from fully developed failures, or from the risks of in-flight shutdowns, and flight cancellations.
B.
The turbine
Gas
engine characteristic of repeatedly producing its output at, or very close to, generator parameter values, provides the basis for the engine trend monitoring system. Thus, under known conditions of pressure altitude (PA) and indicated outside air temperature (Tam), the gas generator parameter values of interturbine temperature (Tt5), gas generator speed (Ng) and fuel flow (Wf), for particular propeller speed (Np) and torques (T) are predictable within reasonable limits. charted gas
C.
New engines operate within a tolerance band, either above or below charted parameter values, and tend to deviate more than these values with time and deterioration of gas
path components.
Page 2-7-1 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
D.
Abrupt changes, charted
such, changes E.
or
gradual
parameter values are
increased rate of change, of the normal deviations from critical indicators of gas path component conditions. As
are
detectable before any
significant
deterioration
occurs.
The
monitoring system should be introduced when engines are new or newly overhauled. This enables the establishment of a performance baseline before any deterioration takes in the engine. For procedures, refer the appropriate P&WC Publication . oNL IS GEN-055.
place
I 3.
to
TROUBLESHOOTING A.
Procedure
(1)
To enable
systematic troubleshooting, engine troubles
categorized into four engine problems with rectification sequences. The classes of engine
basic classes. Each class consists of
common
appropriate diagnostic tests and problems and probable causes are detailed
as
are
related
follows:
(a) Troubleshooting, Engine Starting (Ref. Fig. 2-7-1).
(b) Troubleshooting, Engine Operating (Ref. Pig. 2-7-2). (c) Troubleshooting, Engine (d) Troubleshooting, ECTM (e) Troubleshooting, Engine
(f) B.
Engine (1)
Troubleshooting, Condition Trend
Performance Shift
(Ref.
Table
Lubrication
Oil Contamination
Monitoring (ECTM)
(Ref. Fig. 2-7-3). 2-7-1).
(Ref. Fig. 2-7-4). (Ref. Fig. 2-7-5).
Shift
To diagnose and rectify engine condition trend Fault Isolation Chart (Ref. Table .2-7-1)
monitoring shift,
refer to ECTM Shift
Page 2-7-2 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
NO INDICATION OF ENGINE RPM
on
Sheet 3
EXCESSIVE RPM
INSUFFICIENT RPM
NO
I IS STARTER-GENERATOR I OPERATION AUDIBLE
I
I
I I
CHECK ACCESSORY GEARBOXINPUTSHAFT COUPLING FOR PROPER ENGAGEMENT. INSPECT ACCESSORY GEAR DRIVES, BEARINGS AND COMPRESSOR REAR HUB SPLINES
I
ANY EVIDENCE OF DAMAGE, RETURN
CHECK ELECTRICAL POWER SUPPLIES AND STARTER-GENERATOR ELECTRICAL CONNECTIONS
YES
RECTIFY POWER SUPPLY
NO
FAULT
ARE ELECTRICAL POWER SUPPLIES I O.K.
YES
ENGINE TO APPROVED OVERHAUL FACILITY
REPLACE STARTER-GENERATOR (REF. AIRCRAFT MAINTENANCE MANUAL)
IF ANY STARTER-GENERATOR BEARING DISTRESS ANDIOR SHORTED ARMATURE TO THE STARTER-GENERATOR SHAFT IS SUSPECTED, PERFORM INSPECTION OF MAIN OIL FILTER AFTER STARTER-GENERATOR REPLACEMENT (REF. UNSCHEDULED INSPECTION, PART3 SECTION
DOES ENGINE ROTATE WITH STARTER-GENERATOR OPERATION
YES
3) REMOVE Ng TACHOMETER-GENERATOR AND ATTEMPT TO ROTATE COMPRESSOR AT TACHOMETER DRIVE
NO
Cont’d
on
Sheet 2
Cont’d
on
Sheet 2
C36866A
Engine Starting Fault Isolation Chart Figure 2-7-1 (Sheet 1 of 7)
Page 2-7-3 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 1
From Sheet 1
RECTIFY FAULT ON Ng TACHOMETER INDICATING SYSTEM
YES
I-
I
DOES COMPRESSOR ROTATE FREELY WITH NO SOUNDOFTURBINE BLADE SCRAPING
NO
REMOVE STARTER-GENERATOR. CHECK FOR SHEARED DRIVE SHAFT AND GEARSHAFT SPLINE DAMAGE
REMOVE POWER OUTPUT SECTION AND CHECK COMPRESSOR TURBINE TIP CLEARANCE
IS STARTER-GENERATOR DRIVE SHAFT SHEARED
IS TURBINE TIP CLEARANCE CORRECT
YES
ARE SPLINES ON GEARSHAFT O.K.
NO
NO
YES
NO
REMOVE COMPRESSOR TURBINE AND GRIND SEGMENTS
YES
REPLACE STARTER GENERATOR ANDIOR DRIVESHAFT (REF. AIRCRAFT MAINTENANCE
SHIP ENGINE TO APPROVED OVERHAUL FACILTTY
MANUAL)
IF ANY STARTER-GENERATOR BEARING DISTRESS ANDIOR SHORTED ARMATURE TO THE STARTER-GENERATOR SHAFT IS SUSPECTED, PERFORM INSPECTION OF MAIN OIL FILTER AFTER STARTER-GENERATOR REPLACEMENT
(REF. UNSCHEDULED INSPECTION, PART 3 SECTION 3)
C36867A
Engine Starting Fault Isolation Figure 2-7-1 (Sheet 2)
Chart
Page 2-7-4 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
From Sheet 1
on
Sheet 5
ENGINE FAILS TO LIGHT UP
HAS ENGINE STARTING PROCEDURE BEEN DONE
SET "FUEL CONDITION" LEVER TO "GROUND-IDLE" POSITION. ALLOW 30 SECONDS FUEL DRAINING PERIODANDCARRY OUT DRY MOTORING RUN
NO
YES
DO A DRY MOTORING RUN
REPEAT COMPLETE ENGINE START SEQUENCE
CAUTIQN:OBSERVE STARTER MOTOR LIMITS NOTE:
(PRE-SB1429)
ENGINES HAVE GLOW
PLUG IGNITION.
CAUTION: (POST SE-1429) RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING.
OPERATIONALLY CHECK IGNITION SYSTEM
IGNITION SYSTEM FOUND O.K.
NO
YES
Cont’d
on
CHECK POWER SUPPLIES TO IGNITION EXCITER. DO ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLES AND VISUALLY CHECK CABLES AND IGNITERS. RECTIFY AS NECESSARY.
Sheet 4
Cont’d
on
Sheet 4
C36868B
Engine Starting Fault Isolation Figure 2-7-1 (Sheet 3)
Chart
Page 2-7-5 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 3
From Sheet 3
ON AIRFRAME INSTALLATION CHECK OPERATION OF BOOSTER PUMP, IF FITTED, AND ENSURE FUEL SOURCE IS FREE OF ICE OR WATER CONTAMINATION
NO
IS AIRFRAME FUEL SUPPLY TO ENGINE O.K.
NO FAULTS FOUND ON IGNITERS OR CABLES. REPLACE IGNITION EXCITER (POST-SB1429) OR CURRENT REGULATOR
YES
(PRE-SB1429) FAULT POSSIBLE DUE TO AIR LOCK IN FUEL CONTROL UNIT. IF FUEL SYSTEM HAS BEEN DISCONNECTED, ENSURE BYPASS FUEL TO TANK IS UNRESTRICTED AND RESTART ENGINE TO CARRY OUT SELF-BLEEDING OPERATION
IF AIRFRAME FUEL SUPPLY IS O.K., CHECK BLEED AIR SYSTEM FROM FCU BYPASS. RECTIFY AS NECESSARY.
IF AIRFRAME FUEL SOURCE AND BLEED AIR SYSTEM ARE O.K.,
LOOSEN COUPLING NUT ON INLET TUBE OF FCU. CHECK FOR EVIDIENCE OF FLOW WHILE MOTORING
FUEL DRAINS FROM FLOW DIVIDER AND DUMP VALVE DURING MOTORING OF ENGINE
FUEL FLOW FOUND O.K.
YES
FAULT IN FLOW DIVIDER AND DUMP VALVE SYSTEM. RECTIFY OR REPLACE VALVES AS NECESSARY
NO YES REPLACE FUEL PUMP
IS EVIDENCE OF CONTAMINATION OR DAMAGE APPARENT ON FCU
NO
CHECK FUEL NOZZLES FOR RESTRICTION. FUNCTION CHECK NOULES
YES REPLACE FCU
C36869A
Engine Starting Fault Isolation Figure 2-7-1 (Sheet 4)
Chart
Page 2-7-6 Aug 16/2002
PRATT
WHITNEY CANADA MANUAL
MANUAL PART NO. 3015442
From Sheet 3
Cont’d
HOT START
on
Sheet 7
DELAYED LIGHT UP
HAS ENGINE STARTING PROCEDURE BEEN DONE
NO
NO
I
I
I
HAS ENGINE STARTING PROCEDURE BEEN DONE
YES
YES
CHECK FOR LOW POWER SUPPLIES AND POOR CONNECTIONS ON POWER INPUT LINES AND STARTER-GENERATOR CONNECTION ARE ELECTRICAL SUPPLIES O.K.
NO
SET "FUEGCONDITION" LEVER TO "GROUND-IDLE" POSITION. ALLOW 30 SECONDS FUEL DRAINING PERIOD AND CARRY OUT DRY MOTORING RUN
YES
RECTIFY POWER SUPPLY OR CABLE FAULT
REPEAT COMPLETE ENGINE START SEQUENCE CAUTION: OBSERVE STARTER MOTOR LIMITS
CHECK IGNITION SYSTEM
CHECK IGNITION SYSTEM
CAUTION: (POST-SB1429) RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE THAT IGNITION SYSTEM HAS BEEN SWITCHED OFF AT LEAST SIX MINUTES BEFORE DISCONNECTING Cont’d
on
NOTE: PRE-SB1429 ENGINES HAVE GLOW PLUG
IGNITION.
Cont’d
Sheet 6
on
Sheet 6
C61147A
Engine Starting Fault Isolation Figure 2-7-1 (Sheet 5)
Chart
Page 2-7-7 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 5
From Sheet 5
IGNITION
INO
NO
I
IGNITION SYSTEM FOUND O.K.
YES
YES
CHECK P3 BLEED AIR SYSTEM FOR AIRCRAFT SERVICES. MAKE SURE THAT ALL SERVICES ARE SELECTED OFF. RECTIFY AS NECESSARY
CHECK ENGINE CONTROL LINKAGE RIGGING
CHECK POWER SUPPLIES TO IGNITION EXCITER, DO ELECTRICAL INSULATION AND CONTINUITY CHECKS ON IGNITION CABLE AND VISUALLY CHECK CABLES AND IGNITERS. RECTIFY AS NECESSARY
NO FAULTS FOUND ON IGNITER OR CABLES. REPLACE IGNITION EXCITER
IS ENGINE CONTROL LINKAGE O.K.
NOI
CHECK DUMP VALVE. IS DUMP VALVE SECTION CLOSED
ADJUST CONTROL LINKAGE RIGGING AS REQUIRED YES
REPLACE DUMP VALVE
CHECK DUMPVALVE OPERATION. RECTIFY OR REPLACE AS NECESSARY
YES
NO
CHECK MINIMUM FUEL FLOW
CHECK FUEL NOZZLES FOR RESTRICTION. FUNCTION CHECK NOZZLES
C61148A
Engine Starting Fault Isolation Chart Figure 2-7-1 (Sheet 6)
Page 2-7-8 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d from Sheet 5
1 ENGINE FAILS OR IS SLOW TO ACCELERATETOIDLE SPEED (Ng)
CHECK P3 AIR BLEED DELIVERY TUBES FOR POSSIBLE LEAKS OR RESTRICTIONS FOR POST-SB1S11 OR 361362. REPLACE AIR FILTER IF NECESSARY
IF DELIVERY TUBES ARE O.K. CHECK PNEUMATIC SECTION OF (Nf) PROPELLER GOVERNER (PT6A-6 AND -20 ENGINES ONLY) AND (Ng) GOVER (ALL MODELS). RECTIFY AS NECESSARY
CHECK DUMP VALVE OPERATION. RECTIFY OR REPLACE AS NECESSARY.
IF PREVIOUS CHECKS ARE O.K. POSSIBLE FAULT DUE TO CONTAMINATION IN FCU. CHECK AND REPLACE FCU AS NECESSARY.
C61119B
Engine Starting Fault Isolation Figure 2-7-1 (Sheet 7)
Chart
Page 2-7-9 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
HOOTING OR HUMMING SOUND
CHECK PROPELLER GOVERNOR CONTROL SETTINGS. ADJUST AS NECESSARY
Sheet 2
EXCESSIVE MAX RPM
PROPELLER SLOW TO FEATHER AND UNFEATHER
CHECK OPERATION OF COMPRESSOR BLEED VALVE
on
(Np)
CHECK PROPELLER GOVERNOR CONTROL SETTINGS. ADJUST AS NECESSARY
BLEED VALVE OK IF GOVERNOR ADJUSTMENTS
ARE INEFFECTIVE, REPLACE GOVERNOR
NO
NO
HAVE NECESSARY GOVERNOR ADJUSTMENTS BEEN MADE
REPLACE BLEED VALVE YES
IF FAULT IS STILL APPARENT, POSSIBLE LEAK DUE TO WORN OR DAMAGED
YES
NO ACTION NECESSARY IF CONDITION OCCURS BELOW 60%
Ng P,NO
INTERMITTENTLY SUCH AS DURING ACCELERATION TO IDLE OR DURING A CHANGE OF SPEED. IF CONDITION PERSISTS, OR OCCURS ABOVE 60% Ng, DISASSEMBLE AND CHECK ClT DISK FOR BLADE SHIFT. REPAIR AS NECESSARY. IF NO BLADE SHIFT, REBALANCE OR REPLACE CTT DISK. IF CONDITION PERSISTS AFTER REPLACEMENT OF DISK. SHIP ENGINE TO AN APPROVED OVERHAUL FACILITY.
PREFORMED PACKING AT PROPELLER S~Pm OIL TRANSFER TUBE
PROPELLER BLADE ANGLE ADJUSTMENT INCORRECT. ADJUST AND REPLACE AS
MANUFACTURER’S
MANUAL)
REPLACE OIL TRANSFER TUBE PREFORMED PACKING
SHIP ENGINE OR POWER OUTPUT SECTION TO APPROVED OVERHAUL FACILITY
C61120A
Engine Operating Fault Isolation Chart Figure 2-7-2 (Sheet 1 of 10)
Page 2-7-10 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
From Sheet 1
FAILURE TO DECELERATE
on
Sheet 3
UNCONTROLLED ACCELERATION
OVERSPEED
(Ng)
CHECK FCU TO FUEL PUMP INTERFACE FOR POSSIBLE SHEARED OR WORN DRIVE SPLINE COUPLING
DRIVE SPLINE COUPLING SHEARED OR WORN YES
NO
REPLACE FCU ANDIOR COUPLING
CHECK FCU FOR CONTAMINATION ANDIOR CORROSION
REPLACE FCU
C61121A
Engine Operating Fault Isolation Chart Figure 2-7-2 (Sheet 2)
Page 2-7-11 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
From Sheet 2
on
Sheet 4
SLOW TO ACCELERATE
CHECK Py AIR BLEED TUBE AND P3 AIR DELIVERY TUBE FOR LEAKS OR RESTRICTIONS. FOR
POST-SB1294, REPLACE AIR FILTER IF NECESSARY
CHECK P3 AIR BLEED TUBES OK. REPLACE IF NECESSARY
NO
YES CHECK Nf PROPELLER GOVERNOR ENGINES ONL OR Nf POWER TURBINE GOVERNOR (PT6A-6 AND -20 ENGINES). RECTIFY AS NECESSARY.
RECTIFY OR REPLACE DEFECTIVE TUBE AS APPLICABLE
(PT6A-20A AND -208
YES
REPLACE FCU
C61122A
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 3)
Chart
Page 2-7-12 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
From Sheet 3
on
Sheet 5
I I
OVER TEMPERATURE (MAX. ALLOWABLE TEMP HAS BEEN
TEMPERATURE LIMITED
EXCEEDED)
CHECK OPERATION OF INDICATING SYSTEM AND MAKE SURE THAT DATA CURVES ARE CORRECT
INSPECT ENGINE FOR POSSIBLE TURBINE DAMAGE
TURBINE INSPECT O.K.
YES
CHECK ENGINE INSTALLATION FOR AIR LEAKAGES AT ENGINE FLANGES AND GAS GENERATOR DRAIN VALVES
~NO
I
RETURN ENGINE TO APPROVED OVERHAUL FACILITY
CHECK OPERATION OF TEMPERATURE INDICATING SYSTEM. RECTIFY AS NECESSARY
CHECK AIR INLET AND COMPRESSOR FOR CONTAMINATION BUILD UP
CHECK BLEED AIR VALVE OPERATION
I
YES _
I-
I
ARE BLEED VALVE OPERATIONS O.K.
NO
COMPRESSOR DIRTY YES I
REPLACE DEFECTIVE BLEED VALVE
NO
DO COMPRESSOR WASH PROCEDURE
CHECK FOR EXCESSIVE AIRFRAME ACCESSORY POWER LOADING (REF. AIRFRAME MANUFACTURER’S MANUAL)
CHECK ENGINE OVERTEMPERATURE CHART. INSPECT REMOVE ENGINE AS APPLICABLE
C61124
Engine Operating Fault Isolation Chart Figure 2-7-2 (Sheet 4)
Page 2-7-13 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FROM SHEET 4
CONT’D ON SHEET 7
FLAMEOUT
LOW POWER
SQUEAL NOISE AT
(ALL PARAMETERS LOW).
DECELERATION OR DURING MOTORING.
AIRFRAME FUEL Y. MAKE SURE
OF ICE OR WATER
CHECK OPERATION OF INDICATING SYSTEM AND MAKE SURE DATA CURVES ARE CORRECT. RECTIFY AS NECESSARY.
AMINATION
IF AIRFRAME FUEL SOURCE
IS SATISFACTORY, LOOSEN INLET TUBE AT FCU AND CHECK FOR FUEL FLOW WHILE MOTORING ENGINE.
IF NO FLOW, REPLACE FUEL PUMP.
CHECK AIR INLET AND COMPRRESSOR FOR ACCUMULATION OF DIRT. IF NECESSARY, DO A COMPRESSOR WASH
IF FUEL SUPPLY CHECKS
INSPECT ENGINE FOR TURBINE
ARE O.K., DEFECT DUE TO POSSIBLE AIR LOCK. RESTART ENGINE TO DO
DAMAGE. IF DAMAGED, RETURN APPROVED OVERHAUL FA CILITY
SELF-BLEEDING OPERATION.
CHECK FUEL PUMP. IF PUMP IS SOURCE CONTINUE IN SERVICE
’SUNDSTRAND FUEL PUMP PRESSURE PLATES NORMALLY SQUEAL AT LOW
Ng.
NAOT
CHECK FOR INCORRECT ADJUSTMENT OR DISCONNECTED CONTROL
CHECK ACCELERATION TIME OF ENGINE.
CONT’D ON SHEET 6
LINKAGES. (REF. AIRCRAFT MANUFACTURER’S MANUAL).
IF CONTROL LINKAGES ARE
SATISFACTORY, DO CHECKS ON PROPELLER GOVERNOR
(PNEUMATIC IF
SECTION
Nf).
DEFECTIVE, REPLACE
GOVERNOR.
CONT’D ON SHEET 6
C61125A
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 5)
Chart
Page 2-7-14 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL ~Aiit:’l;iij. 9015442
OPERATING PROBLEMS
from Sheet 5
from Sheet 5
CHECK FCU FOR CONTAMINATION OR CORROSION. FCU CONTAMINATION
YES
YES
ACCELERATION TIME O.K.
NO REPLACE FCU
IF CONTROL LINKAGES ARE SATISFACTORY CARRY OUT CHECKS ON Ng PROPELLER GOVERNOR (PT6A-20A AND -206 ENGINES) OR ON Nf GOVERNOR (PT6A-6 AND -20
ENGINES).
IF
DEFECTIVE,
REPLACE GOVERNOR.
INSPECT ENGINE FOR "FOD" OR TURBINE DAMAGE CHECK COMPRESSOR BLEED VALVE. RECTIFY OR REPLACE AS NECESSARY
IF FCU CHECKS ARE O.K. CHECK FUEL NOZZLES FOR
POSSIBLE RESTRICTIONS IF FUEL NOULES ARE O.K. POSSIBLE FAULT DUE TO CONTAMINATED FCU. CHECK AND REPLACE AS NECESSARY
CHECK P3 AIR BLEED DELIVERY TUBES FOR POSSIBLE LEAKS OR RESTRICTIONS FOR POST-SB1294. REPLACE AIR FILTER IF NECESSARY
C61126A
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 6)
Chart
Page 2-7-15 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d
From Sheet 5
VIBRATION
DO COMPRESSOR WASH PROCEDURE
MI\NUAL)
INSPECT ENGINE FOR LOOSE MOUNTING BRACKETS I
REMOVE FCU AND CHECK PREFORMED PACKING AT BY-PASS PORT. IS LEAKAGE VISIBLE NO
-I
CHECK THROUGH EXHAUST PORTS FOR POWER TURBINE DAMAGE
REMOVE AIR INLET SCREEN AND INSPECT 1ST STAGE COMPRESSOR FOR SIGNS OF DAMAGE
CHECK OPERATION OF COMPRESSOR BLEED VALVE
BLEED VALVE OPERATION O.K.
YES
Sheet 9
FUEL LEAKAGE AT FCUIFUELPUMP FLANGE
SURGE DURING ACCELERATION
PROPELLER DAMAGE OR BLADE ANGLE SLIPPED. ADJUST ANDIOR REPLACE AS NECESSARY (REF. TO AIRFRAME MANUFACTURER’S
on
YES
REPLACE PREFORMED PACKING AND FCU
LEAKAGE AT FUEL PUMP SHAFT SEAL. REPLACE FCU AND FUEL PUMP
NO REPLACE BLEED VALVE
NO TURBINE 8 COMPRESSOR O.K.
RETURN ENGINETO APPROVED OVERHAUL FACILITY
YES
CHANGE T2 TEMPERATURE I COMPENSATOR
CHECK COMPRESSOR BLEED AIR VALVE OPERATION
NOTE: THERE WILL BE A SMALL PUMP SEAL, THE ENGINE
ALWAYS
Cont’d
on
Sheet 8
LEAK AT THE EVEN WITH STOPPED.
C61128A
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 7)
Chart
Page 2-7-16 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
OPERATING PROBLEMS
From Sheet 7
REMOVE INLET SCREEN. EXAMINE 1ST STAGE COMPRESSOR BLADES FOR FOREIGN OBJECT DAMAGE
(FOD)
COMPRESSOR BLADES FOUND O.K.
NO
YES
RETURN ENGINE TO APPROVED OVERHAUL FACILITY
REPLACE FCU
C61129
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 8)
Chart
Page 2-7-17 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
OPERATING PROBLEMS FROM SHEET 7
CONT’D ON SHEET 10
UNUSUAL NOISES
ENGINE INTERNAL RUBBING OR SCRAPING NOISES. COMPRESSOR OR TURBINE ROTORS DO NOT ROTATE FREELY, DECELERATE OR RUN DOWN EASILY ON ENGINE SHUT DOWN.
75 TOO HIGH AT SHUT DOWN
I
I
AURALLY CHECK COMPRESSOR FOR SHORT AND ABRUPT DECELERATION OR RUN DOWN TIME.
I
RESTRAIN PROPELLER AND MOMENTARILY ROTATE COMPRESSOR WITH STARTER. CHECK FOR EVIDENCE OF COMPRESSOR TURBINE RUB, IF ONLY LIGHT RUBBING AUDIBLE, RESTART ENGINE AND ALLOW NORMAL PERIOD OF COOLING AT GROUND IDLE PRIOR TO SHUT DOWN.
ROTATE PROPELLER. CHECK FOR RUBS AND SCRAPING.
CHECK REAR MOUNTED ACCESSORIES FOR DRAG OR INTERFERENCE OF ROTATING COMPONENTS.
ON START UP, SLOW PROPELLER ACCELERATION, ABRUPT DECELERATION ON SHUT DOWN OR PROPELLER STIFF TO TURN.
I
I
I
INSPECT THROUGH EXHAUST
PORTS, EXHAUST AREAS AND INSPECT POWER TURBINE ROTOR AND EXHAUST AREAS FOR EVIDENCE OF DISTRESS
REMOVE POWER SECTION AND INSPECT FOR COMPRESSOR TURBINE BLADE TIP TO SHROUD RUB
I
I
I
I
I
I
I I
POWER TURBINE FOR EVIDENCE OF DISTRESS.
POSSIBLE PROPELLER SHAFT OIL TRANSFER HOUSING SEIZURE
LOOSE OR WORN NO. 3 BEARING COVER
RETURN TO OVERHAUL FACILITY FOR REPAIR
INSPECT AND REPLACE AS NECESSARY
C61149A
Engine Operating Fault Isolation Figure 2-7-2 (Sheet 9)
Chart
Page 2-7-18 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 9
SQUEAL AT RUN DOWN OR DURING MOTORING
CHECK IF SUNSTRAND FUEL PUMP INSTALLED
IF PUMP iS SOURCE OF NOISE, CONTINUE IN SERVICE
SUNSTRAND FUEL PUMP PRESSURE PLATED OFTEN SQUEAL AT LOW Ng
C61130
Engine Operating Fault Isolation Chart Figure 2-7-2 (Sheet 10)
Page 2-7-19 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
NO IS ENGINE ON ECTM PROGRAM
I
Cont’d
on
Sheet 7
YES
IS PARAMETER SHIFT CONSIDERED NORMAL FOR ENGINE RUNNING TIME (REF. NOTES 1 AND 6)
YES
DO PREVENTIVE MAINTENANCE (REF. NOTE 3)
NO
IF MULTI-ENGINE INSTALLATION, ANALYZE ECTM PLOTS FOR EACH ENGINE. ARE PARAMETER SHIFTS SIMILAR
YES
CHECK AIRCRAFT OAT, ALTITUDE AND AIR SPEED INDICATING SYSTEMS. A DEFECT IN THESE SYSTEMS WILL CAUSE SIMILAR ECTM SHIFT ON BOTH ENGINES
NO
rrr
(RAPID) SHIFT AND NO NSMlf SHIFT (REF. NOTES 2,5)
YES
NO
Ng (RAPID) SHIFT AND NO ITTMlf SHIFT (REF. NOTE 2)
YES
NO WF
(RAPID) SHIFT AND NO ITT~Ng SHIFT (REF. NOTE 2)
YES
CHECK ENGINE/AIRFRAME INDICATING SYSTEM
REPAIR
Cont’d on Sheet3
NO
Cont’d on Sheet 2
C36844A
Engine Performance Fault Figure 2-7-3 (Sheet
Isolation Chart 1 of
10)
Page 2-7-20 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 1
YES
ITT, Ng AND Wf
I NO
I
I
I
DECREASED?
CHECK ENGINEIAIRFRAME TORQUE AND Np INDICATING SYSTEMS. OK?
REPAIR
NO YES
NO
ITT, Ng, Wt INCREASED?
YES NO
CHECK ENGINE/AIRFRAME TORQUE AND Np INDICATING SYSTEMS. OK?
YES NO
INSPECT ENGINE INLET. CHECK BYPASS DOOWICE VANE RIGGING. OK? YES
INSPECT COMPRESSOR. FODIEROSIONIRUB?
YES
YES DMdAGE ACCEPTABLE/REPAIRABLE
REPAIR
Cdnt’d Sheet 3 "A"
NO
NO
COMPRESSOR DIRTY?
SHIP ENGINEIGGM TO AN APPROVED OVERHAUL FACILITY
YES
DO A COMPRESSOR WASH OR POWER RECOVERY WASH
NO Cont’d
on
Sheet 3
C36845
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 2)
Page 2-7-21 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
From Sheet 2 NO DO ENGINE BLEED VALVE CHECK. OK?
YES NO LEAK CHECK P2.5 AIRFRAME BLEED PIPE. OK? REPAIR
YES
CHECK HOT STARTS, A HOT START MAY CAUSE ALL
NO
PARAMETERSTOINCREASE SUDDENLY
INSPECT ENGINE HOT SECTION COMPONENTS AS REQUIRED
YES
From Sheets 1 and 2 "A"
YES
DO ENGINE PERFORMANCE CHECK. COMPARE WITH CHECK DONE AT ENGINE INSTALLATION OR LATER (AS AVAILABLE). RECORD DIFFERENCES (SHIFT) IN PARAMETERS
SIGNIFICANT DIFFERENCE BETWEEN ECTM AND ENGINE PERFORMANCE CHECK PARAMETERS RECORDED (REF. NOTE
4)
YES
IS THE INITIAL SHIFT REDUCEDIELIMINATED BY THE PREVIOUS MAINTENANCE ACTION
NO
YES
NO
SYSTEM NORMAL
Cont’d on Sheet 5
CHECK ENGINE FIREWALL AND INLET SEAL CONDITIONS. OK? (REF. NOTE 8)
I
YES
NO
REPAIR
Cont’d
on
Sheet 4
C36846A
Engine Performance Fault Isolation Figure 2-7-3 (Sheet 3)
Chart
Page 2-7-22 Aug 16/2632
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 3
AIR BLEED SYSTEM PRESSURE REGULATING VALVE OK? (REF. AIRCRAFT MAINTENANCE
NO
MANUAL) YES
AIR BLEED SYSTEM SHUTOFF VALVE OK? (REF. AIRCRAFT MAINTENANCE MANUAL)
NO
YES NO REPAIR
AIR BLEED SYSTEM DUCTING OK? (REF. AIRCRAFT MAINTENANCE MANUAL)
YES HOT SECTION COMPONENTS HAVE BEEN INSPECTED AND REPAIRED AS NECESSARY
YES CONTACT AIRCRAFT MANUFACTURER
REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED?
YES
SYSTEM
NORMAL
NO
Cont’d on Sheet 5
C61132
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 4)
Page 2-7-23 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheets 3 and 4
ITT AND Wt INCREASE AND Ng DECREASE? NO
YES
INSPECT CT STATOR, BLADES AND SHROUD SEGMENTS. DEFECTS FOUND?
YES
ARE DEFECTS UNACCEPTABLE OR COULD THEY CAUSE THE PERFORMANCE DETERIORATION?
NO
NO
DO AN HSI
DO A PERFORMANCE RECOVERY WASH
ITT AND Wt INCREASE WITH
YES
Ng CONSTANT?
YES
NO
CHECK GAS GENERATOR CASE DRAIN VALVES, FUEL NOULE GASKETS, "C" FLANGE AND T5 HARNESS SEAL FOR LEAKS. OK? YES
NO LEAK CHECK P3 BLEED
(AIRFRAME)
PIPE AND ADAPTER. OK?
YES NO INSPECT COMPRESSOR AND HOT SECTION. OK? (REF. NOTE 7)
1
I REPAIR
REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED?
YES
SYSTEM NORMAL
I
NO
Cont’don SheetG
C36848
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 5)
Page 2-7-24 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheets 5 and 9
NO
REPEAT ENGINE PERFORMANCE CHECK WITH BLEED AIR PORTS BLANKED OFF. HAS ENGINE PERFORMANCE IMPROVED (355. NOTE 10)
YES
NO
SYSTEM NORMAL
DO AN HSI
C36849
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 6)
Page 2-7-25 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 1 ENGINE PERFORMANCE .CHECK AFFECTED ENGINE IS SATISFACTORY (REF. NOTE 5)
YES
1
-I
CHECK ENGINE FIREWALL AND INLET SEAL CONDITION. OK? (888. NOTE 8)
NO
NO
YES
AIR BLEED SYSTEM PRESSURE REGULATING VALVE. OK? (REF. AIRCRAFT MAINTENANCE MANUAL)
COMPARE ENGINE PERFORMANCE CHECK WITH CHECK DONE AT ENGINE INSTALLATION OR LATER (AS AVAILABLE). RECORD DIFFERENCES IN PARAMETERS (REF. NOTE 3)
NO
YES
AIR BLEED SYSTEM SHUTOFF VALVE. OK? (REF. AIRCRAFT MAINTENANCE
NO
MANUAL) YES NO
CHECK AIR BLEED SYSTEM DUCTING (REF. AIRCRAFT MAINTENANCE MANUAL) ITTSHIFTANDNO NSSHIFT (REF. NOTES 8, 9)
YES
NO
YES
Ng
SHIFT AND NO ITT SHIFT? NO
CHECK ENGINEIAIRFRAME INDICATING SYSTEM
Cont’d
on
Sheet 8
REPAIR
Cont’d on Sheet 9 "C"
C36850
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 7)
Page 2-7-26 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 7
NO ITT AND Ng CHANGE
Cont’d
on
Sheet 9
YES
CHECK TORQUE AND Np INDICATING SYSTEMS (AIRFRAMEIENGINE). OK?
NO
YES INSPECT ENGINE INLET. CHECK BYPASS DOOWICE VANE RIGGING. OK?
NO
REPAIR
YES YES
INSPECT COMPRESSOR.
FODIEROSIONIRUB?
DAMAGE ACCEPTABLERREPARRABL
YES
REPAIR
NO
NO
SHIP ENGINE/GGM TO AN APPROVED OVERHAUL FACILITY
Contld on´•
Sheet 9
YES
DO A COMPRESSOR WASH OR POWER RECOVERY WASH
COMPRESSOR DIRTY?
I
L
"C"
NO CHECK ENGINE BLEED VALVE. OK?
NO
YES
REPAIR
LEAK CHECK P2.5 AIRFRAME BLEED PIPE. OK?
NO
YES CHECK FOR HOT STARTS. A HOT START MAY CAUSE ALL PARAMETERS TO INCREASE SUDDENLY
I
NO
INSPECT HOT SECTION COMPONENTS AS REQUIRED
YES Cont’d
on
Sheet 9 "C"
C36851A
Engine
Performance Fault Isolation Chart
Figure
2-7-3
(Sheet 8)
Page 2-7-27 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
From Sheet 8
ITT INCREASE AND
IFATIDLE CHECK FUEL HEATER OK?
Ng
DECREASE?
NO
_I
CHANGE FUELHEATER
YES
NO
INSPECT CT VANE, BLADES AND SHROUD SEGMENTS. DEFECTS FOUND? YES
ARE DEFECTS UNACCEPTABLE OR COULD THEY CAUSE THE PERFORMANCE DETERIORATION?
YES
NO
NO
DO AN DO A PERFORMANCE RECOVERY WASH
ITT AND Wt INCREASE WITH
HSI
Ng CONSTANT?
YES CHECK GAS GENERATOR CASE DRAIN VALVES, FUEL NO~LE GASKETS, "C" FLANGE AND T5 HARNESS SEAL FOR LEAKS. OK?
NO
YES NO LEAK CHECK P3 BLEED
(AIRFRAME)
PIPE AND ADAPTER. OK?
YES NO
INSPECT COMPRERSSOR AND HOT SECTION. OK? (REF. NOTE 7)
From Sheets 7 and 8 "C"
REPAIR
REPEAT ENGINE PERFORMANCE CHECK. HAS PERFORMANCE IMPROVED?
YES
SYSTEM NORMAL
NO
Cont’d on SheetG
C36852B
Engine Performance Fault Isolation Chart Figure 2-7-3 (Sheet 9)
Page 2-7-28 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
NOTE: 1.
Review ECTM data, pilot reports and maintenance log book entries and troubleshooting for the last 6 months. Hot section components and performance gradually deteriorate as running time accumulates. The deterioration rate varies according to operating conditions (environment and type of operation) and for different engine modification standards. If engine performance apparently
improves T5 fault).
decrease without maintenance action, check
indicating systems (usually T5 system
is at
NOTE: 2.
A
NOTE: 3.
To extend hot section life, the following preventive maintenance, based on the increase in T5 from the values established at engine installation (engine performancelground power check or ECTM), is
rapid
shift in
engine parameters
is
usually the
result of
an
indicating system
defect.
a 10"C (20"F) increase in T5, do a performance recovery wash. In addition, indicating system and engine performancelground power checks are recommended to ensure reliable engine performance data. Also, test spray pattern or refurbish fuel noules. For a 15"0 (270 Fl increase in T5 or a 1 to 1.5% decrease in Ng, do a borescope inspection of the
recommended: For
combustion chamber, small exit duct, CT stater vanes and CT blades. In addition, do the maintenance recommended above. NOTE: 4.
NOTE: 5.
A significant difference between ECTM and engine performance/ground power check parameters indicate that the defect is within the aircraft air bleed system on the affected engine lair bleed is off during an engine performancelground power check). An alternative method is to do an engine performancelground power check with air bleed ON then OFF. Compare the shift parameters for the engines on the same aircraft. A significant difference indicates bleed sharing problems. For single engine installations, contact p&WC for typical parameter shift recommendations.
When
an
check is
NOTE: 6.
NOTE: 7.
NOTE: 8.
engine is temperature limited on climb or cruise and the engine performance/ground satisfactory, the defect is within the aircraft bleed system of the affected engine.
An increase in temperature without other parameter shifts may be the result of defective fuel noules or a deteriorated combustion liner altering combustion profile and temperature distribution.
power
changing the
Compressor deterioration (which increases Ng) and hot section normal deterioration (which reduces Ng) may balance each other and the effect deterioration has on Ng will be very small or zero (i.e. Ng will remain constant). When the
engine is running on the ground, inlet plenum air pressure is lower than ambient air Therefore, if the inlet or firewall seals are damaged, hot air from around the engine may be ingested causing a temperature increase. Similarly, if the wind direction is from the rear, exhaust gas may be ingested and temperature increased. pressure.
NOTE: 9.
The relationship between T5 and the temperature in front of CT stater may change due to hot section component deterioration altering combustion profile andlor gas path temperature distribution. This may affect the T5 trim and the indicated T5 and the relationship between T5 and the temperature in front of the CT vane used for engine certification. A 75 trim verification will confirm a shift in the indicated temperature.
NOTE: 10.
To
remove
before
doubts,
doing
a
a
T5 system check
(including
individual
on
the
wing
thermocouple checks)
or
in the test cell
is recommended
complete HSI.
C65318
Engine Performance Fault Isolation Chart Figure 2-7-3 (Sheet 10)
Page 2-7-29 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LUBRICATION PROBLEMS CONT’D ON SHEET 3
LOW OIL PRESSURE
HIGH OIL PRESSURE
CHECK 011: PRESSURE INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE
INSUFFICIENT OIL. CHECK OIL LEVEL AND EXTERNAL OIL LINES AND COOLER FOR LEAKS. RECTIFY AS NECESSARY.
MANUAL)
OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSEM (REF. AIRCRAFT MAINTENANCE MANUAL
INDICATING SYSTEM O.K.
NO
I
NO
I
1
INDICATING SYSTEM O.K.
YES RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRCRAFT MAINTENANCE
MANUAL)
CONT’D ON SHEET 2
CONT’D ON SHEET 2
C29872A
Engine Lubrication Fault Isolation Chart Figure 2-7-4 (Sheet 1 of 8)
Page 2-7-30 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From
ADJUST
OIL
Sheet
1
PRESSURE
REGULATING VALVE AS NECESSARY
OIL PRESSURE REGULATING VALVE MALFUNCTION. CLEAN AND
REPLACE
OIL
REMOVE,
INSPECT VALVE
PRESSURE
REGULATING VALVE
NO PRESSURE REGULATING VALVE
O.K.
YES
PRESSURE RELIEF VALVE MALFUNCTION. AND
REPLACE PRESSURE
INO
RELIEF VALVE
I
REMOVE,
CLEAN
INSPECT VALVE
IPRESSURE RELIEF VALVE O.K.
SHIP
ENGINE TO APPROVED
OVERHAUL FACILITY
C23255
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 2)
Page 2-7-31 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LUBRICATION PROBLEMS CONT’D ON SHEET 4
FROM SHEET 1
OIL LEAK FROM COMPRESSOR INLET CASE OR INTO EXHAUST DUCT (ENGINE SIGNIFICANTLY NOSE DOWN)
SMOKE IN COCKPIT
CHECK FOR OIL LEAKAGE DUE TO DEFECTIVE PREFORMED PACKING AND PLASTIC RING ON OIL FILTER HOUSING
YES PREFORMED PACKING AND PLASTIC RING O.K. VERIFY CONDITION OF OIL FILTER HOUSING FRONT FACE (PRE-SB1247), REPAIR IF NECESSARY AND PERFORM STATIC LEAK TEST
NO
LAP CHECK VALVE (PRE-SB1247). RENEW PREFORMED PACKING (POST-SB1247). LAP CHECK VALVE AND SEAT (POST-SB1379). PERFORM STATIC LEAK TEST
REPLACE PREFORMED PACKING ANDIOR PLASTIC RING
LEAKAGE PERSISTS
CHECK FOR LEAKAGE AT PREFORMED PACKING ON ACCESSORY GEARBOX. RECTIFY AS NECESSARY
C29874A
Engine
Lubrication Fault Isolation Chart Figure 2-7-4 (Sheet 3)
Page 2-7-32 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LUBRICATION PROBLEMS CONT’D ON SHEET 5
FROM SHEET 3
OIL PRESSURE FOLLOWS POWER LEVER AND WILL NOT RESPOND TO ADDITION OF SHIMS
FLUCTUATING OIL PRESSURE
INSUFFICIENT OR EXCESS OIL. CHECK OIL LEVEL
OIL LEVEL O.K. CHECK OIL PRESSURE INDICATING SYSTEM (REF. AIRFRAME
MANUAL) RECTIFY FAULT ON INDICATING SYSTEM (REF. AIRFRAME
MANUAL)
NO
I-
I
INDICATING SYSTEM O.K.
I
I
OIL FILTER INSPECTION O.K. POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT
YES
INSPECT OIL FILTER. CLEAN OR REPLACE AS NECESSARY
OIL FILTER INSPECTION O.K. POSSIBLE PRESSURE RELIEF VALVE MALFUNCTION. CLEAN AND INSPECT
REPLACE PRESSURE RELIEF VALVE AS NECESSARY
REPLACE PRESSURE RELIEF VALVE AS NECESSARY
REMOVE ACCESSORY GEARBOX AND CHECK OIL PUMP HOUSING FOR CRACKS
REPLACE RELIEF VALVE HOUSING
C29876A
Engine Lubrication Fault Isolation Chart Figure 2-7-4 (Sheet 4)
Page 2-7-33 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From
Sheet
Cont’d
3
~k
HIGH
on
Sheet
d
OIL
TEMPERATURE
INSUFFICIENT OIL. CHECK
OIL
OIL
LEVEL
LEVEL
O.K.
CHECK OIL TEMPERATURE INDICATING SYSTEM
(REF.
AIRCRAFT
MAINTENANCE
ON
RECTIFY FAULT
INDICATING
(REF.
MANUAL)
SYSTEM
AIRCRAFT
INDICATING
NO
I i
SYSTEM O.K.
I
MAINTENANCE
MANUAL)
YES
IF HIGH
GROUND
OIL TEMP.
DURING
(AfRCRAFT
OPERATION,
STATIONARY)
VERIFY PROPELLER
RIGGING/ADJUSTMENT (PRIMARY BLADE
ANGLE)
MAINTENANCE
~k
(REF. AIRCRAFT MANUAL)
NOTE: IDLING
EXCESSIVE
FEATHER COULD
OVERHEATING RESTRICT
IN
CAUSE
INDICATION.
IDLING TIME
IN FEATHER
Cont’d
on
Sheet
5
C23257
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 5)
Page 2-7-34 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 4
CHECK AIRFRAME OIL COOLER-SYSTEM FOR RESTRICTIONS OR MALFUNCTIONS (REF. AIRCRAFT MAINTENANCE MANUAL)
RECTIFY FAULT ON OIL COOLER SYSTEM (REF. AIRCRAFT MAINTENANCE MANUAL)
NO
OIL COOLER SYSTEM O.K. YES
THERMOSTATIC BYPASS AND CHECK VALVE O.K. HEAT SHIELD FAILURE. SHIP ENGINE TO APPROVED OVERHAUL FACILITY.
C23258A
Engine
Lubrication Fault Isolation Chart Figure 2-7-4 (Sheet 6)
Page 2-7-35 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 6
EXCESSIVE OIL CONSUMPTION
Cont’d
EXCESSIVE DISCHARGE FROM OVERBOARD BREATHER
on
Sheet 7
EXTERNAL OIL LEAKS
CHECK OIL LEVEL FOR OVERSERVICED CONDITION
CHECK FOR EVIDENT OIL LEAKS AT TRANSFER TUBE PACKINGS. CHECK TRANSFER TUBES FOR BLOCKAGE. RECTIFY AS NECESSARY
CHECK PACKINGIBACKUP RING AT OIL FILTER HOUSING
CHECK CENTRIFUGAL BREATHER CARBON SEAL. RECTIFY AS NECESSARY
IF LEAKS PERSISTS, SHIP ENGINE TO AN APPROVED OVERHAUL FACILTTY
C61138A
Engine
Lubrication Fault Isolation Chart Figure 2-7-4 (Sheet 7)
Page 2-7-36 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
From Sheet 7
OIL AT EXHAUST DUCT AREA
OIL LEAK AT INLET CASE
CHECK OIL LEVEL FOR OVERSERVICED CONDITION
CHECK FOR RESTRICTIONS IN SCAVENGE TUBES, OR OIL TO FUEL HEATER TUBES
CHECK AIR BREATHER VALVE STICKING. RECTIFY AS NECESSARY
CHECK PACKINGIBACKUP RING AT OIL FILTER HOUSING
CHECK OIL TANK CENTER TUBE PREFORMED PACKINGS RECTIFY AS NECESSARY
-I
I
IF LEAK PERSISTS, SHIP ENGINE TO AN APPROVED OVERAHUL FACILITY
NO EXTERNAL OIL LEAKS
CHECK OIL TO FUEL HEATER FOR INTERNAL LEAKS. REPLACE.
C61139
Engine
Lubrication Fault Isolation Chart
Figure
2-7-4
(Sheet 8)
Page 2-7-37 Aug 16/2002
PRATT
WHITNEY CANADA
MAINIENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-7-1, ECTM Shift Fault Isolation
Engine
Parameters
Ail parameters UP
Probable Cause
Action
Remarks
Req’d
Engine/Airframe indicating systems.
Inspect.
Repair
as
req’d.
Air inlet door blocked.
Inspect.
Repair
as
req’d.
Bypass door or ice misrigged.
Inspect.
Repair
as
req’d.
Compressor FOD,
Inspect.
Remove
engine
damage
limits
vane
rub, erosion,
if
are
exceeded.
Compressor contaminated/dirty.
Wash compressor.
Bleed´•valve open.
Inspect.
Repair
as
req’d.
P2.5 air leaks from
Inspect.
Repair
as
req’d.
Repair
as
req’d.
engine/airframe system PT stater vanes burned/flow area increased. PT blade tip oxidation/rub. Hot start.
Inspect PT vanes
stater
and PT blades.
Inspect
hot section
and check
log
book.
Do
applicable
overtemperature
inspection. parameters DOWN
Engine/Airframe indicating system.
Inspect.
Repair
Engine/Airframe indicating system. (Note 1)
Inspect If applicable, do on-wing T5 system trim.
Repair as req’d. T5 usually decreases when probes are
(Note 2)
unserviceable.
Fuel nozzle deterioration.
Inspect.
Clean
Ng UP or DOWN, T5, WF Constant
Engine/Airframe indicating system.
Inspect.
Repair
as
req’d.
Wf UP or DOWN, T5, Ng Constant
Engine/Airframe indicating system.
Inspect.
Repair
as
req’d.
All
T5 UP or DOWN, Wf Constant
Wf,
T5 UP,
Ng,
Ng DOWN
CT stater vanes burned/flow area increased. CT blade tip oxidation/rub. Normal hot section deterioration,
Inspect
CT stater, and
CT blades.
as
as
req’d.
req’d.
If limits exceeded, do HSI.
an
Do an HSI if T5 limit exceeded.
Page 2-7-38 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-7-1, ECTM Shift Fault Isolation Parameters
Engine
Probable Cause
Action
(Cont’d) Remarks
Req’d
Inspect.
Repair
Gas generator case cracked at fuel nozzle or P3 bleed pads. Diffuser exit ducts cracked or loose.
Inspect.
Replace engine if defect confirmed.
Leaking gas generator drain valves, Cflange, fuel nozzle gasket, or T5
Inspect.
Wf, T5 UP, Ng
P3 leaks from
Constant
engine/airframe system.
as
req’d.
Replace engine
if
defect confirmed.
harness seal.
Concurrent hot section and compressor deterioration.
Inspect
CT stater and
CT blades, and
Do
an
engine
HSI or send for overhaul.
compressor.
NOTE: 1.An increase in T5 without other parameter shifts may be the result of defective fuel nozzles or a deteriorating combustion chamber liner altering combustion profile and
path temperature distribution.
gas
relationship between T5 and the temperature in front of the CT stater may change due to hot section component deterioration altering combustion profile and/or gas path temperature distribution. This may affect the T5 trim and the indicated T5, and the relationship between T5 and the temperature in front of the CT stater used for engine certification. A T5 trim verification on-wing or in a test cell will confirm a shift in
NOTE: 2. The
the indicated temperature. C.
Lubricating (1)
Oil Contamination
diagnose and rectify engine lubricating oil contamination, refer to Engine Lubricating Oil Contamination Fault Isolation Chart (Ref. Fig. 2-7-5).
To
Page 2-7-39 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(2)
The
following
NOTE: 1.
NOTES
are
referred to in
Figure
2-7-5:
Depending where the debris was found (i.e. strainer, main oil filter or chip detector) and the shape (i.e. tooth part, locking washer part etc.) a decision could be made concerning the removal of the affected module. Alternatively, remove engine.
NOTE: 2. If no debris is found at the 50-hour check, return the oil filter and detector inspections to operator’s standard maintenance program intervals. NOTE: 3. Results of
previous laboratory analysis and origin of debris original detection of debris.
chip
should be
determined within 50 hours of NOTE: 4. Results of last
sample
must be known
prior
to
continuing.
NOTE: 5. It should have
already been determined that the engine and not RGB mounted accessories are generating the debris. If propeller governor or O/S governor failure occurred prior to original debris detection and
the material could be identified as a propeller or O/S governor material then the engine may not be generating the debris.
NOTE: 6.
Bearing inner and outer rings steel AMS6440/6444 (52100)
well as rolling elements are made of AMS6490/6491 (M50). Bearing cages are made of steel AMS6414/6415 (4340) or bronze AMS4616, silver plated per AMS2412. When only bearing cage material is generated (major or minor filter contaminant), this may indicate cage wear due to lack of lubrication and/or bearing damage causing rolling element instability. as
or
Page 2-7-40 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CHIP DETECTOR
CIRCUIT COMPLETION
REMOVE AND INSPECT CHIP DETECTOR
TRANSFER DEBRIS AND SEND TO A LAB FOR ANALYSIS
REMOVE AND INSPECT ASSOCIATED STRAINER AND MAIN OIL FILTER
CARRY OUT PATCH MAKING AND SEND TO A LAB FOR ANALYSIS
Cont’d Sheet 4
I
on
Cont’d Sheet 4
on
Cont’d Sheet 4
CLASSIFY DEBRIS
on
CLEAN AND RE-INSTALL OIL FILTER, STRAINER AND CHIP DETECTOR. RETURN ENGINE TO SERVICE
YES
IS DEBRIS
ALLOWABLE?
RECORD CATEGORY, TYPE AND ORIGIN OF DEBRIS
Cont’d Sheet 4
on
NO
Is DEBIS NON-ALLOWABLE CATEGORY 1?
RECORD CATEGORY AND TYPE OF DEBRIS AND REMOVE MODULEI ENGINE
IYES
I
No
(RE~NOTE1)
IS MAGNETIC DEBRIS NON-ALLOWABLE CATEGORY 2 OR 3? NO RECORD ENGINE TIME CATEGORY, TYPE AND ORIGIN OF DEBRIS
IS DEBRIS CATEGORY 2 BRONZE (I.E., IT ORIGINATES IN RGB?) YES RECORD MODULE TIME CATEGORY. TYPE AND ORIGIN OF DEBRIS Cont’d
on
Sheet 2
t Cont’d
on
Sheet 3
C23263D
Engine
Oil Contamination Fault Isolation Chart Figure 2-7-5 (Sheet 1 of 4)
Page 2-7-41 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d from Sheet 1
NON-ALLOWABLE CATEGORY 2 BRONZE DEBRIS ORIGINATING IN RGB
HAS RGB GENERATED DEBRIS WITHIN LAST 400 HOURS
(555.
NOTE
NO
3) YES
CLEAN AND INSTALL OIL FILTER, CHIP DETECTOR AND STRAINERS
HAS QUANTITY OF CURRENT DEBRIS INCREASED OR IS GEARBOX CONSISTENTLY GENERATING DEBRIS? YES
NO
SCHEDULE RGB REMOVAL WITHIN 10 FLIGHT HOURS OF CURRENTLY REPORTED
RUN ENGINE AT 80% T.O. POWER FOR 10 MINUTES (555. ADJUSTMENTTTEST)
DEBRIS
CLEAN AND INSTALL CHIP
REMOVE AND INSPECT CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS DEBRIS CATEGORY 2 BRONZE FOUND? NO
I
DETECTOR, MAIN OIL FILTER AND STRAINERS
tYES DRAIN AND FLUSH OIL SYSTEM CLEAN AND INSTALL MAIN OIL FILTER, CHIP DETECTOR AND STRAINERS. FILL UP OIL SYSTEM
RUN ENGINE AT 80% FOR 10 MINUTES
REMOVE AND INSPECT OIL FILTER, CHIP DETECTOR AND STRAINERS. CATEGORY 2 BRONZE DEBRIS GENERATED?
YES
REMOVE RGB MODULE
NO CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS
RETURN ENGINE TO SERVICE AND CHECK CHIP DETECTOR AND MAIN OIL FILTER AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2). IF DEBRIS IS FOUND, SEND TO LABORATORY FOR ANALYSIS
Cont’d on Sheet 4
C36863
Engine
Oil Contamination Fault Isolation Chart Figure 2-7-5 (Sheet 2)
Page 2-7-42 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d from Sheet 1 NON-ALLOWABLE CATEGORY 2 OR 3 DEBRIS OTHER THAN BRONZE
HAS ENGINE GENERATED DEBRIS WITHIN 400 HOURS (REF. NOTE 3) NO CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS
YES
I
I
WERE THE RESULTS OF THE LAST LABORATORY ANALYSIS BEARING MATERIAL (REF. NOTE 4)
YES
NO
RUN ENGINE AT 80% FOR 10 MINUTES REMOVE ENGINE REMOVEAND INSPECTCHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS CATEGORY 2 OR 3 DEBRIS FOUND
NO
NO
I
I
I
IS THE OUANTITY OF DEBRIS SAME OR INCREASEDOR ISENGINE CONSISTENTLY GENERATING DEBRIS
YES YES DRAIN AND FLUSH OIL SYSTEM. CLEAN AND INSTALL CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. FILL UP OIL SYSTEM
REMOVE ENGINE AT FIRST OPPORTUNITY OR WITHIN 10 HOURS
RUN ENGINE AT 80% FOR 10 MINUTES CLEAN AND INSTALL CHIP DETECTOR. MAIN OIL FILTER AND STRAINERS REMOVE AND INSPECT CHIP DETECTOR, MAIN OIL FILTER AND STRAINERS. IS CATEGORY 2 OR 3 DEBRIS FOUND
YES REMOVE ENGINE
NO RETURN ENGINE TO SERVICE AND CHECK CHIP DETECTOR AND MAIN OIL FILTER AND STRAINERS AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (REF. NOTE 2). IF DEBRIS IS FOUND, SEND TO LABORATORY FOR ANALYSIS
Cont’d on Sheet 4
C36864B
Engine Oil Contamination Fault Isolation Chart Figure 2-7-5 (Sheet 3)
Page 2-7-43 Aug 16/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Cont’d from Sheets 1,2 and 3
DEBRIS ANALYSED AT LAB
WAS THE ENGINE GENERATING DEBRIS (REF. NOTE 5)
YES IS DEBRIS BEARING MATERIAL AMS6440/6444 (52100) OR AMS6490/6491 (M50) (366 NOTE 6)
NO YES
NO WAS DEBRIS ALLOWABLE
I
-I
CONTINUE IN SERVICE
NO
WAS DEBRIS GEAR MATERIAL?
ENGINE MAY REMAIN IN SERVICE. CARRY OUT A CHIP DETECTOR AND FILTER CHECK AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (666. NOTE 2)
1
I
REPLACE ENGINE
INSPECT MODULE AS REQUIRED USING
YES
BORESCOPE(LABORATORY ANALYSED DEBRIS)
NO WAS DEBRIS BRONZE
WAS MATERIAL AIR SEAL
AMS4117,AMS4127, AMS4150, I AMS5613, AMS5671, MOLY
1 CATEGORY 2 MATERIAL YES
)NO
I
I
IS MODULE IN ACCEPTABLE CONDITION
CONTINUEIN SERVICE
YES
CARRY OUT AN ADDITIONAL FILTER PATCH CHECK AFTER 10 HOURS AND PROVIDING NO DEBRIS IS FOUND, AFTER 50 HOURS (666. NOTE 2)
ENGINE MAY REMAIN IN SERVICE. CHECK CHIP DETECTOR AND MAIN OIL FILTER STRAINER AFTER 10 HOURS AND IF NO DEBRIS IS FOUND AFTER 50 HOURS (666. NOTE 2)
IS LAB SEAL OR BRONZE MATERIAL FOUND
(MAJOR
OR MINOR
NO
YES
REMOVE MODULE
CONTAMINANT)
NO REMOVE MODULE
RETURN TO SERVICE
C36865C
Engine Oil Contamination Fault Isolation Chart Figure 2-7-5 (Sheet 4)
Page 2-7-44 Aug 16/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 2
GENERAL PROCEDURES CONSUMABLE MATERIALS
SECTION 8 1.
GENERAL A.
This section contains a listing of consumable materials required for use in line and heavy maintenance. Materials are listed in major groups under applicable headings in Table 2-8-1. Material Safety Data Sheets (MSDS) containing information about Trade
Name, Safety Hazards, Health Hazards, Reactivity, Spill or Leak Procedures, Special Protection Information, Special Precautions, and Transportation and Labelling are available from manufacturer. Read B.
2.
to
using
consumable.
As used in this section, the term "Consumable Material" shall be defined as an expendable substance not separately obtainable from Pratt Whitney Canada and which may be applied to engines or engine parts during maintenance.
SPECIFICATIONS A.
3.
prior
Specification
numbers which
and shall be
interpreted
apply
to materials listed in Table 2-8-1
are
basic numbers
to include all revisions and amendments thereto.
TRADE NAME PRODUCTS A.
In
some
operator and their
instances, such
as for cleaning materials, product names are listed to assist identifying product types. These names are representative examples only listing does not exclude the use of equivalent products.
the
in
TABLE 2-8-1, Consumable Materials Item
Nomenclature/Specification
Supplier Code
PWC01-001
Fuel, Engine
(Ref. Approved
PWC03-001
Oil, Engine
A0001
Service
Bulletins)
Lubricating (Ref. Approved Service Bulletins) PWC03-002
Ref. Brayco 922 US MIL-PRF-7024 PMC 9041 PWC04-004
A0015
Fluid, Calibrating
Type
Grease
II
1
V074, 77163, A0022
High Temperature (Bentonite-type) Ref. Plastilube No. 3 PMC 9631
Page 2-8-1 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials Item
Nomenclature/Specification
PWC04-005
Grease Extreme Pressure Ref. Lubriplate 130A PMC 79919
PWC05-007
(Cont’d)
Supplier
Code
73219, A0032, A0033, A0034, A0035
03530
Fluid, Leak Check Ref. Leak Tec #372E
PMC 9569 PWC05-009
Ammonium Bifluoride Pet.
PWC05-011
Ammonium Nitrate Ref. Open Powder Form 1.725 Specific US MIL-A-175 PMC 1517
PWC05-019
A0001(s)
Crystalline
A0001(s)
Gravity
Compound, Lapping
731 65
Ref. Clover 2A No. 400 Grit PMC 3013
PWC05-021
Cloth, Abrasive Emery Ref. Open
A0001(s)
180 Grit
US ANSI B74.18
PWC05-027
Ink, Marking
S0089
Ref. Carter 21451 Black
PWC05-031
Flux, Resin
09185(m), 10178(m)
Ref. No. 1545
PMC 2000
PWC05-037
Enamel, Epoxy
A0097(s), S0098(s), ONYSS(m)
Aluminized Ref. 529K002 Base 910K021 Curing Solution PWA 569 LPMC1 746 PWC05-038
Hydrogen Peroxide Commercial Grade Ref. Open 32.5 to 35% US Fed. A-A-53707 PMC 1602
A0001(s),
08338
Page 2-8-2 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials
(Cont’d)
Item
Nomenclature/Specif ication
Supplier Code
PWC05-046A
Marker, Ink
S0036
Ref. Fast Drying No. 57 400-1 Black 400-2 Red 400-7
Purple
PWC05-046C
Ref. PWC05-229
PWC05-048
Pen, Marking Ref.
PWC05-048A
Brushpen
S0036 No. 57
A0013, 30133
Pen, Marking Ref. Felt Wick Pen
PWC05-048B
Ref. PWC05-331
PWC05-055
Sodium Dichromate
A0001(s)
Ref. Open Commercial Grade PMC 1300 PWC05-061
Cloth, Abrasive
A0001(s),
44197
(m), 61158(m)
Coated Crocus Ref. Open US ANSI B74.18 400 Grit PWC05-064
Solution, Anodize Touch-Up
84063
(for Aluminum Alloys) Ref. Alodine No. 1200S US. AMS 2473 PMC 71600 PWC05-070
Pressure Sensitive Adhesive Filament Reinforced Ref. 3M No. 898
Tape,
A0001(s), A0083, 76381(m)
Type II, 2 .0 in.
(50.8 mm)
Wide
US. ASTM D5330 PWC05-074
Acid, Sulfuric Ref. Commercial
A0001(s) or
Technical Grade 66 Degrees Baume PMC1 003
I´•
PWC05-077
Oil, Preservative
2R128
Ref. Grade 1010
Brayco
460
US MIL-PRF-6081
PMC 9852
Page 2-8-3 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials Item
Nomenclature/Specif ication
PWC05-089
Lockwire
or
Nickel Alloy Inconel 600
Safetywire (CRES)
(Cont’d)
Supplier Code A0001(s), 8W577(m)
Ref. MS9226-03 US. AMS5687
(0.64 mm) Dia. (for engine external applications only, PWC05-295 may be substituted).
0.025 in.
PWC05-101
A0001(s), 44197(m), 61158(m)
Cloth, Abrasive Aluminum Oxide Silicone Carbide Ref.
or
Open
US ANSI 874.18 No. 320 Grit PWC05-110
Lockwire or Nickel Alloy
Safetywire
A0001(s), 8W577(m)
or
Inconel 600 Ref. MS9226-01
US. AMS5687 0.016 in.
PWC05-1 47
(041 mm)
Dia.
A0001(s), 05838,
Electrode 2% Thoriated
Pet. Open PMC5052-3 Length: 7 in.
28835
Tungsten
(177.8 mm) (1.587 mm)
Diameter: 1/16 in. PWC05-1 90
A0084(s), 08071(m)
Patch, Filter Ref. P/N NY6004700
Millipore 60 Micron Nylon PWC05-1 95
Acid, Nitric Technical Grade
A0001(s)
Ref. Open US Fed A-A59105 5 to 10% Solution 42% Reagent Grade 45
Degrees
Baume
PMC1000 PWC05-229
Ink, Stamping Black
(For marking
on
surfaces with
a
98148(m)
non-porous rubber stamp)
Ref. Dykem Black KX-425 PMC 4021-1 or -3
Page 2-8-4 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials
(Cont’d)
Item
Nomenclature/Specification
Supplier
Code
PWC05-295
Wire, Safety, Steel
A0001(s),
1
A053(s)
Ref. Open AS 3214-02
PWC05-329
A0123
Temperature Recorder
Single
Position
0.56 in.
(14 mm.) dia. Ref. P/N 414-140F-060C
PWC05-331
Felt
Tip Marker (Rapid Drying) Temporary Marking
See NOTE
Ref. PMC 4050
NOTE: For tradenames andmanufacturers, refer to the SPM. Remove the part before heat treatment process and assembly per SPOP 209.
I
PWC06-005
PWC06-005D
SprayDiscontiued.
ink from the
Use PWC06-005D
Lubricant, Fluorocarbon PTFE Release Agent Ref. MS-122DF Aerosol
PWC06-023
marking
Compound, Antiseize Ref. Silver Goop
18598(m), A0103(s)
1
DD67(m),
1
E473(m),
02570(m), A0019(s), A0037(s), A0038(s), A0113(s)
PWA 36001 PMC 9940 PWC06-032
Compound, Antigalling (High Temperature)
and Anti-seize
A0104(s), 05972(m)
Ref. Loctite C-200.Solid Film US MIL-A-907 PWA586, PMC79912
(CPW37) PWC09-001
Sealant, Silicone Rubber
71984(m), K7750,
D8367
Ref. Silastic RTV 732 PMC 1836 (C PW51 9-1 1 PWC09-001A
Sealant, Silicone Rubber Ref. RTV 102, 103, 108, 109
01139(B)(m)
(CPW51 9-11) PWC09-002
Compound, Locking Retaining Anaerobii:
and
05972(m), A0104(s), A0018, D2617, U0406
Ref. Loctite Grade US. MIL-S-22473 PWA549-7, PMC79900
(CPW79-290)
Page 2-8-5 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials
(Cont’d) Code
Item
Nomenclature/Specif ication
Supplier
PWC09-002A
Compound, Locking and Retaining Anaerobic
05972(m), D2617,
AO 104(s), AOO 18,
U0406
Ref. Loctite Grade US. MIL-S-22473 PWA549-4, PMC79897
20913, 56444
Cleaner, Alkaline
PWC11-001
(Internal Engine Washing) Ref. CLIX PWC11-001A
A253
Cleaner, Alkaline
(Internal Engine Washing) Ref. Almon AL-333 PWC11-001B
02ERO(m),
Cleaner, Alkaline
85884
(Internal Engine Washing) Ref. Magnus 1214 PWC11-001C
21361
Cleaner, Alkaline
(Internal Engine Washing) Ref. B&B 3100 SPMC87-4 PWC11-001D
Cleaner, Alkaline
(Internal
.feECT RenignE R-MC
AOlll(s),
N1480
AOlll(s),
N1480
Washing)
Premixed P/N 4070 PWC11-001E
Cleaner, Alkaline
(Internal Engine Washing) Ref. ECT R-MC Concentrate P/N 4072
PWC11-btjlF
Cleaner, Alkaline
36325(m), 0BYN5(m)
(Internal Engine Washing) Ref. Turco 4217
Concentrate PWC 11-001H
Cleaner, Alkaline
(Internal Engine Washing)
A0052(s), 23373(s), 37127(s), A0121(m), 44389
Ref. Ardrox 624 Concentrate PWC11-001J
Cleaner, Alltalii~e
A0001(s)
(Internal Engine Washing) Ref. Triethanolamine PWC11-002
NOTE: Use use
Was Solvent trichloroethane 1-1-1 Ref. NOTE alcohol (PWC11-014) to replace the trichloroethane solvent. You SPOP 209, refer to the SPM, Chapter 70-21-00.
isopropyl
can
also
Page 2-8-6 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials
(Cont’d) Code
Item
Nomenclature/Specif ication
Supplier
PWC 11-003
Cleaner, Detergent
A0052(s), 2273(s), 37127(s), K6858(m), A0121(m),), 02CA7,
(Engine Washing)
PWC 11-003B
Ref. Ardrox 6345 SPMC 87-2
D1940
Cleaner, Detergent
A0052(s), A0121(m), 23373(s), 37127(s), 44389, K6858(m)
(Engine Washing) (Biodegradable) Ref. Ardrox 6367
(Turboclean 2) PWC 11-003C
A0052(s), 23373(s), 37127(s), K6858(m)
Cleaner, Detergent
(Engine Washing) (Biodegradable) Ref. Ardrox 6368
(Turboclean 2 RTU) (Ready to use) PWC 11-003D
U4628, 1 NCOO, 39052(s)
Cleaner, Detergent
(Engine Washing) (Biodegradable) Ref. ZOK 27 PWC 11-010
A0001(s)
Alcohol, Methyl US AMS3004
O-M-232 Grade A PMC 9089
PWC 11-012
A0001(s)
Acetone
Ref. Open PMC 9008
I
PWCI1-013
No
longer
availabe. Use
CMPSsevitanretla
PWC11-013A, PWC11-049
or
PWCI1-061
PWC 11-013A
Compound,
Carbon Ref. HDP 2888
Removing
02ERO
52
PWC 11-014
Alcohol, Isopropyl
A0001(s)
US Fed. TT-I-735 Grade A PMC 9094
I
PWC 11-016
DELETED
PWCII-021
Compound,
(Use PWC11-014) 0BYN5(m), 36325(m)
Cold Carbon Removing Ref. Turco Super Carb PMC 9047
Page 2-8-7 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
TABLE 2-8-1, Consumable Materials
(Cont’d)
Item
Nomenclature/Specif ication
Supplier
PWC11-021A
Compound,
Cold Carbon Removing Ref. Penetone, Formula #423 PMC 9031
56883
PWC11-021B
Compound,
88375
Code
Cold Carbon Removing Ref. Wyandotte P-1075 PMC 9084
PWCI 1-022
A0001(s),
Solvent, Cleaning
Methyl Ethyl Ref. Open
Ketone
36842
(MEK)
US ASTM D740
PMC9076, (CPW79908)´• Ref. NOTE NOTE: As an alternative, use the isopropyl alcohol (PWC11-014), acetone (PWC11-012), Ardrox Leeder 1064K (PWC11-023), Desoclean 45 (PWC11-025) or Envirosolv 655 (PWC11-005) to replace the MEK solvent. You can also use SPOP 209, refer to SPM, Chapter 70-21-00. PWC11-026
Was Solvent
Trichlorethylene NOTE: As
an
PWC 1 1 -027
alternative,
use
perchlorethylene
PWC11-016 to
Solvent, Petroleum
replace trichlorethylene solvent.
A000 1
(s),
361 31
Ref. Stoddard Petroleum Solvent US AMS 3160 US Fed. P-D-680 Type II
PMC 9001
PWC11-031
Cleaner, Engine
02ER0(m)
Ref. Tergit PMC 79783 PWC11-032
Solvent, Degreaser
02ERO(m)
Ref. Magkleen 4 PMC 79789
PWC11-033
Cleaner, Aqueous
02ER0(m)
Ref. Soliterj-304 PMC 71254
PWCll-048
Solvent, Cleaner
02ERO(m)
Ref. MAG-CHEM ITeksol
Spray-onANipe-off PWC11-049
Remover, Rust, All
C494B
Engine Front Linkage Figure 3-2-20
Page
3-2-54
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure.3-2-20 Control
1.
Push-pull
2.
Interconnect Rod
3.
Air Bleed Link
4.
6.
Propeller Governor Py Pneumatic Tube Governor Speed Adjusting
7.
Beta Control Valve
8.
Reversing
9.
Nf Tachometer-Generator
5.
43.
to
Linkage
Lever
Lever
INSTALLATION A.
Procedure
CAUTION:
NOTE:
KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS WHICH COULD BE INGESTED BY ENGINE AND CAUSE SERIOUS INTERNAL DAMAGE. If fine mesh halves
Apply
(2)
Before
(3)
(4)
installing Inspection.
Carefully position. Secure
torque
(5)
screen
is to be installed
compound (PWC09-003) screen,
install air inlet
flanges
(Pre-SB1056)
ensure
that inlet
fairing
not fitted.
thin film of
(1)
in
are
inspect
screen
inlet
area
to rubber rims of air inlet
and inlet
around inlet
area.
with three bolts, washers and
screen.
fairing sealing strips
Locate
self-locking
mating flanges
nuts.
Tighten
as
detailed
at 6 o’clock
nuts and
12 to 15 Ib.in.
If
installing new screen, check unstressed flange gap clearance (0.000 to 0.150 inch). If gap exceeds measurement, install spacers as required (Ref I.P.C., Post-SB11S1). NOTE:
Ensure ignition cable support bracket during assembly.
is installed at center bolt location
Page
3-2-55
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INLET FAIRING 44.
REMOVAL A.
Procedure CAUTION:
(1)
KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS WHICH COULD BE INGESTED BY ENGINE AND CAUSE SERIOUS INTERNAL DAMAGE.
On Post-SB1056 and all PT6A-20A
remove
inlet
fairing
halves
(a)
Remove air inlet
(b)
Remove six bolts and washers securing inlet fairing halves to assemblies attached to compressor inlet case.
(c)
Remove four inlet
45.
engines,
fairing
screen.
(Refer
to
as
follows:
Paragraph 42., preceding.) bracket
mounting
self-locking nuts, washers and bolts securing upper mating flanges. Remove fairing halves.
and lower
halves at
INSTALLATION A.
Procedure
Post-SB1056 and PT6A-20A
(1)
Install upper and lower inlet fairing approximate horizontal centerline.
(2)
Secure
mating flanges
nuts at this
Engines
halves in inlet area, with
with four bolts, washers and
mating flanges
self-locking
at the
nuts. Do not
tighten
stage.
(3)
Locate fairing halves on mounting bracket assemblies and washers. Tighten bolts and torque 32 to 36 Ib.in.
(4)
Tighten mating flange self-locking
(5)
Install air inlet
screen
(Refer
to
nuts and
torque
Paragraph
43.
secure
with six bolts and
36 to 40 Ib.in.
preceding).
WINTERIZED HEAT SHIELD 46.
REMOVAL A.
Procedure
CAUTION:
(1) (2)
KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS WHICH COULD BE INGESTED BY ENGINE AND CAUSE SERIOUS INTERNAL DAMAGE.
Remove fine mesh air inlet Rotate
pin
heat shield
fasteners 90
screen
degrees
(Refer
to
Paragraph 42., preceding).
to release upper heat shield
assembly
from lower
assembly.
Page
3-2-56
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(3)
Remove bolts and washers
generator
(4) 47.
securing
upper and lower heat shield assemblies to gas
case.
Remove heat shield assemblies and
remove
gaskets from lower assembly.
INSTALLATION A.
Procedure
(1) (2)
Install
new
gaskets
on
lower heat shield
assembly
horizontal
mating flanges.
Install upper and lower heat shield assemblies on gas generator case, with mating at approximate horizontal centerline. Align flanges of both assemblies and secure by engaging pin fasteners and turning through 90 degrees.
flanges
heat shield mating flange with gas generator mounting bosses and with bolts and washers. Tighten bolts and torque to 32 to 36 Ib.in.
(3)
Align
(4)
Install fine mesh air inlet
screen
(Refer
to
Paragraph
45.
secure
preceding).
COMPRESSOR BLEED VALVE 46.
REMOVAL A.
Procedure
CAUTION:
(See Figure 3-2-21)
KEEP COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS WHICH COULD BE INGESTED BY ENGINE AND CAUSE SERIOUS INTERNAL DAMAGE.
(1)
Remove air inlet
(2)
On PT6A-6A
(Refer
screen
to
Paragraph 42., preceding).
engines, incorporating winterized heat shield installation, assembly (Refer to Paragraph 46., preceding).
remove
upper heat shield
49.
(3)
Remove two hold-down bolts and
(4)
Remove two bolts and
plain
(5)
Withdraw bleed valve Remove gasket.
complete
(6)
Remove transfer tube and elbow. Remove of bleed valve.
plain
washers
washers at
securing
Procedure
(1)
elbow.
bleed valve to gas
with transfer tube and
flanged
generator
case.
elbow from
case.
preformed packings from tube and base
REPLACEMENT OF DIAPHRAGM (BLEED VALVE P/N A.
flanged
3022954) (Pre-SB1414)
(See Figure 3-2-22)
Disassemble bleed valve
as
follows:
Page
3-2-57
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
I ~33
i
)1
in
~II
C830B
Compressor Figure
Bleed Valve 3-2-21
Page
3-2-58
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(a) Remove four slotted screws (1) (3) from housing (14).
(2)
and washers
(2)
and
assembly
remove cover
complete assembly of piston (8) from housing.
(b)
Remove
(c)
cotterpin (13), castellated nut (12) and washers (11), and separate assembly. Discard diaphragm (7) and seal washer (5).
(d)
Clean bleed valve components
Remove
Assemble bleed valve in sequence
(a)
Install
new
(b) Lightly (c)
seal washer
coat
top
(5)
on
as
as
detailed in Part 2,
follows:
new
bolt
guide pin
outer circular surface of
Locate rubber side of
Cleaning.
(4)
followed
piston (8)
diaphragm (7)
with
by
retainer
(6).
compound (PWC09-003).
to contact retainer
(6)
on
guide pin
bolt, followed by piston (8). Ensure diaphragm is evenly contoured between retainer and
piston.
(d)
Install sleeve
(e)
Secure
assembly with two torque (Ref. No. 950, Fits
(f)
Lightly
(g)
While
coat
coat
mounting
on
bolt.
guide pin
(11) and castellated nut (12). Tighten nut, Clearances) and lock with cotterpin (13).
washers
face of
housing (14)
with
compound (PWC09-003).
mounting
face of
cover
assembly’(3)
with
down to
ensure
compound (PWC09-003).
assembly on housing, mate guide pin to bolt (4) on piston align mounting holes. Ensure diaphragm skirt is well seated and secure cover fingertight with four washers (2) and slotted screws (1). Insert bleed valve mounting bolts (15) in respective holes to ensure cover is centralized. Install
cover
assembly
(j)
support plate (10)
and
holding skirt firmly on housing, push piston up and diaphragm rolls correctly between piston and housing wall.
(h) Lightly (i)
(9)
and
Check movement of piston for full and free travel, then 16 to 20 Ib.in.
tighten
slotted
screws
(1).
Torque 50.
REPLACEMENT OF DIAPHRAGM A.
Procedure
(1)
(See Figure 3-2-23)
Disassemble bleed valve
(a)
(BLEED VALVE P/N 3027249) (Post-SB1414)
Remove four slotted from
as
follows:
screws
and washers
(2)
and
remove cover
assembly (3)
housing (15).
(b)
Remove
complete assembly of piston (8) from housing.
(c)
Remove cotterpin (13) and castellated nut Discard diaphragm (7).
(14),
and
separate assembly.
Page
3-2-59
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
o
U
3
RUBBER SURFACE
o
FABRIC SURFACE
DIAPHRAGM
10
12
e
o
C6227A
(Pre-SB1414) Compressor
Bleed Valve
Figure
P/N 3022954
3-2-22
Page
3-2-60
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
1.
Slotted Screw
2.
Washer
3.
Cover
4.
Guide Pin Bolt
5.
Seal Washer
6.
Retainer
7.
Diaphragm
Assembly
8.
Piston
9.
Sleeve
10.
Support
Plate
11.
Washers
12.
Castellated Nut
13.
Cotterpin Valve Housing Valve Mounting Bolt
14. 15.
(d) Clean bleed valve components
(2)
3-2-22
as
detailed in Part 2,
Assemble bleed valve, in sequence, with
(a)
Install retainer NOTE:
(b) Lightly (c)
(5)
on
new
diaphragm
Cleaning. as
follows:
guide pin bolt (4), followed by washer (6).
If dimension between shoulder and nearest full thread is greater than 1.525 inches, guide pin bolt must be replaced (Ref. Post-SB1413). coat outer circular surface of
piston (8) with compound, (PWC09-003).
Locate fabric side of new diaphragm (7) on piston (8), ensuring holes centrally aligned. Use washer (6) if necessary to achieve this. Press area to provide an even and smooth bond between diaphragm and piston.
(d) Exercising
care
to
provide
expose rubber surface
as
an even contour, fold shown in Detail A.
diaphragm
over
piston
are
to
(e)
Install assembly of diaphragm on guide pin bolt (4), with rubber side of diaphragm seated on retainer (5). Check for correct seating of washer (6).
(f)
Lightly
(g)
guide pin bolt, coated end to piston, followed by one washer (10), support plate (11), second washer (10) and spacer (12). Ensure spacer (12) is assembled with large diameter flange facing washer and support plate (11). Secure assembly with castellated nut (14). Tighten nut, torque (Ref. No. 950, Fits 8 Clearances) and lock with cotterpin (13).
coat flat end of sleeve
Install sleeve
(h) Lightly
coat
(9)
with
compound, (PWC09-003).
on
mounting face
of
housing (15)
with
compound, (PWC09-003).
Page
3-2-61
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1 2 1
I I
I
CY
n
/1C-~ 8
o
i
~3
RUBBER
RETAINER
10
SURFACE 11
j
;I PISTON
FABRIC SURFACE
L1
10
I
12
DIAPHRAGM
ii
6
8 7
O :i
.i i´•-´•:~´•:
i.ii.X, a..
C6223
(Post-SB1414) Compressor
Bleed Valve
Figure
P/N 3027249
3-2-23
Page
3-2-62
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
3-2-23
1.
Slotted Screw
2.
Washer
3.
Cover
4.
Guide Pin Bolt
5.
Retainer
6.
Washer
7.
Diaphragm
8.
Piston
Assembly
Sleeve
9. 10.
Washers
11.
13.
Support Plate Spacer Cotterpin
14.
Castellated Nut
12.
15.
Housing Mounting
Valve
16.
Bolt
(i)
piston assembly in housing. Carefully align mounting holes (diaphragm skirt to housing) and ensure complete seating of skirt on mounting face of housing.
(j)
While
Locate
holding skirt firmly diaphragm rolls correctly
on
housing, push piston up and down piston and housing wall.
to
ensure
between
face of
compound, (PWC09-003).
Lightly
coat
(I)
Install bolt in
cover
assembly on housing; mate guide pin on cover with guide pin piston assembly, and locating pin in housing with related hole in cover. Ensure diaphragm skirt is well seated and secure assembly fingertight with four washers (2) and slotted screws (1). Insert valve mounting slotted screws (16) in respective holes to ensure cover is centralized.
(m)
Check movement of (Ref. No. 967, Fits
mounting
cover
assembly (3)
with
(k)
piston for full and Clearances) and
free travel, then lockwire in
pairs.
tighten
bolts
(1). Torque (16).
Remove bolts
Page
3-2-63
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
51.
i)
INSTALLATION
A.
Procedure
CAUTION:
(See Figure 3-2-21)
KEEP THE COMPRESSOR INLET AREA CLEAR OF ALL FOREIGN OBJECTS THAT COULD BE INGESTED BY THE ENGINE AND CAUSE SERIOUS INTERNAL DAMAGE.
NOTE: 1.
Prior to installation, the bleed valve must be pressure checked Part 2, Troubleshooting.
as
detailed in
NOTE: 2. When the compressor bleed valve has been stored for a period exceeding 24 months, the valve must be returned to an approved service facility for retesting and calibration.
(1)
Install new preformed packings on base of bleed valve and both ends of transfer tube. Install tube and elbow in bleed valve port.
(2)
Install
(3)
Ensure that valve
new
generator
gasket
flanged
on
piston
elbow.
is free to travel, then install bleed valve
assembly
on
gas
case.
(4)
Secure bleed valve to at this stage.
(5)
Secure
case
with two bolts and
plain
washers. Do not
Tighten
elbow to gas generator case with two bolts and bolts, torque 32 to 36 Ib.in., and lockwire.
(6)
Tighten
bleed valve bolts, torque 35 to 45 Ib.in., and lockwire.
(7)
On PT6A-6A
(8)
Install air inlet
flanged
engines incorporating winterized heat shield, assembly (Refer to Paragraph 47., preceding.) screen.
(Refer
to
plain
tighten
bolts
washers.
install upper heat shield
Paragraph 43., preceding.)
FUEL CONTROL UNIT 52.
REMOVAL A.
Procedure
NOTE:
(See Figure 3-2-24)
If the FCU is to be stored off the engine, prepare the FCU for short storage (Ref. STORAGE) after removal is complete.
or
long
term
(1)
Disconnect fuel inlet and outlet at FCU.
(2)
Disconnect
(3)
Install dust caps
(4)
Disconnect FCU rod
Py
and Pr over
pneumatic tubes
at FCU.
ends of all tubes and
by removing
fittings.
castellated nut, washer and bolt.
Page
3-2-64
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL FILTER CAP NUT
PREFORMED PACKING
F.C.U.
FUEL PUMP
COUNTERBORE THIS END
DRIVE COUPLING
C618A Installation of Fuel Control Unit to Fuel Figure 3-2-24
Pump
Page
3-2-65
Nov 26/2004
PRATT
WHITNEV CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
53.
linkage
at FCU cut-off valve lever.
(5)
Disconnect control
(6)
Remove mounting nuts and washers which pump and retain coupling.
secure
FCU to fuel pump. Withdraw
INSTALLATION A.
Procedure NOTE:
(1)
(See Figure 3-2-24)
When a replacement FCU is being installed, check the do reconditioning after storage (Ref. STORAGE).
Install
preformed packing
new
If
in
bypass port
recess
length
of fuel pump
of storage and
mating flange.
contains a preformed packing which was not discarded at removal, or which was installed under the shipping plate on a new pump, such packing must be removed and a new preformed packing of correct part number installed.
NOTE:
recess
(2)
Clean FCU and fuel pump drive shafts thoroughly with petroleum solvent (PWC11-027). Ensure solvent does not enter FCU bearings.
(3)
Install FCU drive
coupling
as
follows:
(a)
For engines with fuel pump P/N 4V146R002, of the coupling is facing toward the FCU.
(b)
For engines with fuel pump P/N 4V146R100 or 4V146R101, ensure that the counterbored end of the coupling is facing toward the FCU. (See Figure
ensure
that the
deeper counterbore
3-2-24).
(c) (4)
For engines with fuel pump P/N 024800-101B, 024800-104 or 025323-101, the coupling has a male and female end and can only be installed in one position.
Install FCU
on
engagement
of
fuel pump. If necessary, rotate drive shaft to ensure proper coupling splines. Secure with self-locking nuts, tighten and torque 75
to 85 Ib.in.
CAUTION:
(5)
IF NECESSARY TO ALTER ANGULAR POSITION OF INLET ELBOW TO ALIGN WITH INLET HOSE, REFER TO INSTRUCTIONS IN PART 2, STANDARD PRACTICES TO AVOID DAMAGE TO PREFORMED PACKING.
Connect fuel inlet and outlet hose
couplings
at FCU.
Tighten coupling nuts, torque safety wire.
170 to 200 Ib.in. for inlet and 90 to 100 Ib.in. for outlet and
(6)
Connect
Py
75 Ib.in. and
and Pr
safety
pneumatic
tube
couplings
at FCU.
Torque coupling
nuts 65 to
wire.
(7)
On engines equipped with reversing mechanisms, connect FCU control rod to FCU control arm with bolt, washer and castellated nut. Torque 12 to 18 Ib.in. and secure with cotterpin.
(8)
Connect control
linkage
to FCU cut-off valve lever.
Page
3-2-66
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
54.
STORPIGE A.
Preservation of FCU
(1)
Short term
storage
CAUTION:
(a)
28
days
or
less:
DO NOT PERMIT FUEL OR OIL TO ENTER THE DRIVE BODY CAVITY OR ANY AIR PRESSURE PORTS.
Fill the fuel section of the FCU with a 10 micron filter.
calibrating fluid (PWC03-002)
filtered
through (b)
Install caps and
(c)
Check the security of all caps and plugs in all ports of the air section of the FCU to prevent the entrance of dirt or other contaminates.
(d)
Put
(e)
Refer to Para. C., contaminants.
(f)
Every
a
tag
on
ten
plugs
the unit
days,
in all
ports of the fuel section of the FCU.
indicating
Packaging
date of
and
storage.
Shipping,
for
protection from
dirt and other
check the fluid level in the fuel section of the unit and refill
as
necessary.
(2)
Long
term
storage
CAUTION:
more
than 28
clays:
DO NOT PERMIT FUEL OR OIL TO ENTER THE DRIVE BODY CAVITY OR ANY AIR PRESSURE PORTS.
(a) Drain all remaining fluid from the FCU.
(b)
Fill the fuel section of the FCU with
through NOTE:
a
Tip
the FCU
goes into all
(c)
preservative
oil
(PWC05-077)
filtered
10 micron filter. as
necessary to make
sure
that
a
complete
film of oil
ports and passages of the fuel section of the unit.
Drain the excess oil as fuel section of the unit.
required
and install caps and
plugs
in all
ports of the
(d) Check
the security of all caps and plugs in all openings of the air section of the FCU to prevent the entrance of dirt or other contaminates.
(e) (f)
Put
a
tag
on
the unit
Refer to Para. C.,
indicating
Packaging
date of
and
storage.
Shipping,
for
protection from
dirt and other
contaminants.
Page
3-2-67
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
Depreservation
or
Reconditioning
of FCU after
Storage
CAUTION:
DO NOT PERMIT FUEL OR OIL TO ENTER THE DRIVE BODY CAVITY OR ANY AIR PRESSURE PORTS.
CAUTION:
DO NOT ATTEMPT TO REPLACE ANY LOCKWIRE SEAL UNTIL THE FCU HAS BEEN CHECKED TO BE CERTAIN THAT CALIBRATION OR OPERATION HAS NOT BEEN EFFECTED.
(1)
Inspect
all lockwire and lockwire seals.
torque value of nuts, plugs, caps
(2)
Replace
or screws
that
broken lockwire after were
checking
the
lockwired.
Return the unit for recalibration if any lockwire seal indicates
tampering
or
if the
lockwire is broken.
(3)
For units in storage three years or less, remove the plugs and drain fluid prior to the return to service. No further action is required.
(4)
Three year
(a)
requirement:
For units in an
storage three years
approved
overhaul
2
Inspection of
3
A functional test of the FCU in accordance with the
all
remaining
drive
with the
Honeywell
body assembly bearings.
Honeywell Accessory
(ATA No. 73-20-54).
requirement:
For units in
facility (b)
facility (Ref.
Replacement of the drive shaft bearings in accordance Accessory Overhaul Manual (ATA No. 73-20-54).
Six year
(a)
but less than six years, ship the unit to Step (6)) for the following:
or more
1
Overhaul Manual
(5)
preservation
storage more reconditioning.
for
For units
than six years,
ship
the unit to
an
approved
overhaul
engines that are inactive for more than six months and that are preserved, remove the FCU from the engine (Ref. Removal/lnstallation) and ship the unit to an approved overhaul facility for reconditioning. on
not
(6)
Fuel control units may be
shipped
to:
Pratt Whitney Canada Corp. Plant 12, Accessories Business 2525, Fernand-Lafontaine
Longueuil, PQ Canada C.
Packaging (1)
J4N1N7
and
Shipping
of FCU
When the FCU is to be
(a) Make
sure
that all
(Ref. Fig. 3-2-25)
shipped
or
stored, prepare the unit
shipping plugs
and caps
as
follows:
are secure.
Page
3-2-68
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(b)
Place the FCU
movement
shipping
(6) in position during storage
Put the FCU and stand into and seal the
(2)
the
Put the power lever
prevent
(d)
on
base
(5) and
secure
with bolts
(4).
THE POWER LEVER MUST BE SECURED DURING STORAGE OR SHIPPING OR ELSE DAMAGE TO THE DRIVE SHAFT OR POWER LEVER CAN RESULT.
CAUTION:
(c)
(2)
opening.
(e)
Store the unit in
The
shipping
Air Parts and
an
a
Attach
and or
with lockwire
(3)
as
shown to
moisture and vapor proof container or plastic bag tag to the unit indicating the date of storage.
a
approved shipping
base P/N 2529654
secure
shipping.
can
be
carton or case.
purchased
from:
Supply Company
12840 SW 84th. Avenue
Rd.,
Miami, FL 33156 USA TEL: FAX:
(305) (305)
235-5401 235-8185
FUEL PUMP 55.
REMOVP~L A.
Procedure
(See Figure 3-2-24)
(1)
Remove FCU
(2)
Disconnect all fuel lines at fuel pump.
(3)
Install dust caps
(4)
(Ref. Paragraph 52., preceding).
over
ends of all lines and
Remove nuts and washers
fittings.
securing fuel pump
to accessory
gearbox housing.
Withdraw fuel pump.
(5)
Remove
gasket
and discard.
Page
3-2-69
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
FUEL OUT
12 FUEL OUT
FUELIN
3
4
6
C88316 Fuel Control Unit
Figure
(Typical)- Storage 3-2-25
Page
3-2-70
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
56.
to
Figure
3-2-25
Bypass Connector and Shipping Cap/Plug
1.
Fuel
2.
Fuel Control Unit
3.
Lockwire
4.
Bolt
5.
Shipping
6.
Power Lever
7.
P3 Air Port and
8.
Fuel Inlet Connector and
9.
Fuel Pressure
Stand
(P/N 2529654)
Shipping Cap/Plug Shipping Cap/Plug Connector and Shipping Cap/Plug
INSTALLATION A.
Procedure
CAUTION:
(See Figure 3-2-24) PRE-SB1316: ENSURE INPUT DRIVE COUPLING IS CORRECTLY SECURED ON PUMP INTERNAL SPLINES BY LIGHTLY PULLING AND PUSHING BY HAND. COUPLING SHOULD BE SLIGHTLY LOOSE, BUT SHOULD NOT MOVE IN OR OUT. DO NOT REMOVE COUPLING FROM PUMP. CHECK PROTRUSION OF COUPLING FROM MOUNTING FACE OF PUMP; MEASUREMENT SHOULD BE 1.00 TO 1.12 INCHES. ENSURE COUPLING IS NOT DISPLACED DURING ASSEMBLY TO GEARBOX. POST-SB1316 PUMP INPUT DRIVE COUPLING FEATURES A STOP FLANGE AND MORE POSITIVE RETENTION; THERE SHOULD BE NO AXIAL MOVEMENT. fuel pump
(1)
gasket housing.
(2)
Apply a thin film of engine oil to splines of fuel pump drive, ensuring that hole in gearshaft centerbore is clear, and teflon insert is installed. Ensure drive splines align and mesh correctly with intemally splined gearshaft. Secure assembly to accessory gearbox housing with three plain washers and self-locking nuts. Tighten
Install
nuts and
over
torque
studs
on
mounting pad
on
accessory
gearbox
75 to 85 Ib.in.
NOTE: 1. Some engines prior to serial number PCE20172 do not have the oil mist lubrication hole in gearshaft centerbore. For these engines, apply lubricant (Plastilube No. 3) sparingly to splines. For all other engines, all traces of grease should be removed from both the
of
gearshaft,
then lubricated with
a
thin film of
coupling engine oil.
and bore
NOTE: 2. On Post-SB1165 and all PT6A-20A
gearshaft
engines, oil mist lubrication hole larger in diameter and is countersunk on provide better spline lubrication.
in
centerbore is
upstream side
to
NOTE: 3. On Post-SB1409 engines, ensure oil mist lubrication hole in gearshaft centerbore is clear by manually inserting No. 55 drill (0.0520 inch) in hole and
(3)
turning by
hand.
Remove all dust caps from lines and
fittings.
Page
3-2-71
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(4)
Connect fuel inlet and outlet hose couplings to fuel pump. Tighten to 200 Ib.in. and lockwire to their respective adapters.
coupling nuts,
torque 170
(5)
Install fuel control unit.
(Refer
FUEL PUMP OUTLET FILTER 57.
(VANE-TYPE PUMP) (PRE-SB1071 ENGINES)
Procedure
filter
(1)
Unscrew and
(2)
Remove filter element and discard.
remove
housing
from fuel pump.
INSTALLATION A.
Procedure Before
(1)
installing new filter element, check for presence of preformed packing in internal diameter. The element must be installed so that the preformed packing slides over the spigot in the pump body.
(2)
Install filter element.
(3)
Install and
(4)
Lockwire
(5)
Check filter
handtighten
lugs
on
filter
housing
FUEL PUMP INLET SCREEN
59.
Paragraph 53., preceding).
REMOVAL A.
53.
to
filter
housing.
housing
to fuel pump
for leaks after
engine
body.
run.
(Refer
to Part
(VANE-TYPE PUMP) (POST-SB1071 ENGINES)
2, Testing)
AND POST-SB111P
REMOVAL A.
Procedure
(See Figure 3-2-26)
(1)
Cut lockwire
(2)
Unscrew and
vertically
to
securing fuel
screen
body.
together with screen, lifting assembly possible damage to screen body.
remove screen
prevent any
cap nut to fuel pump
cap nut
(3)
Disconnect fuel inlet line at pump end to drain off residual fuel.
(4)
Clean inlet
screen as
outlined in Part 2,
Cleaning.
Page
3-2-72
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
O
OO O O
i
O
I
,II
ii
FUEL FILTER CAP-NUT
(Post-SB1071
and Post-SB1112
Fuel
Pump Inlet Screen Figure 3-2-26
C751A
Engines)
Page
3-2-73
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
60.
INSTALLATION A.
Procedure
(See Figure 3-2-26)
(1)
preformed packing
(2)
Install Install
apply
screen
and cap nut
provided
assembly. Tighten
on screen
cap nut,
cap nut.
torque
75 to 100 Ib.in. and
lockwire.
(3)
Connect fuel inlet line, lockwire.
(4)
Check pump
body
tighten coupling nut, torque
for leaks after
FUEL PUMP INLET SCREEN
61.
in groove
engine ground
270 to 300 Ib.in. and
run.
(Refer
(GEAR-TYPE PUMP) (POST-SB1096 ENGINES)
to Part
apply
2, Testing).
AND PRE-SB1155
REMOVAL A.
Procedure
(1) (2)
(See Figure 3-2-27)
Remove
screws
securing fuel
inlet
screen cover
to fuel pump
body.
Insert Puller (PWC30443 or PWC30444) as applicable, in threaded removal hole in cover and extract inlet screen assembly.
provided
62.
(3)
Remove
(4)
Clean
long bolt, spring
screen as
and washers, and separate
detailed in Part 2,
screen
from
cover.
Cleaning.
INSTALLATION A.
Procedure
(1)
(2)
Attach filter to cover and secure with bolt and torque 20 to 23 Ib.in.
Install two cover
(3)
preformed packings assembly to pump body.
on
long bolt, spring
inlet
Secure cover with four washers and and lockwire.
screen cover
screws.
Tighten
and two washers.
and assemble
screws,
Tighten
screen
torque
and
40 to 46 Ib.in.,
Page
3-2-74
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
STEEL WASHER
"u
C835
(Pre-SB1155 Engines) Fuel
Pump Inlet Screen Removal Figure 3-2-27
Page
3-2-75
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL PUMP OUTLET FILTER
63.
Procedure
(See Figure 3-2-28) housing from fuel pump.
Unscrew and
(2)
Remove filter element and discard.
remove
Procedure
(See Figure 3-2-28)
(1)
Before installing new filter element, check for presence of preformed packing in intemal diameter. The element must be installed so that the preformed packing slides over the spigot in the pump body.
(2)
Install filter element.
(3)
Install
(4)
Install filter housing, tighten to compress metal-to-metal contact.
(5)
Lockwire filter
(6)
Check filter
preformed packing
housing
on
filter
to hole A
housing for
FUEL PUMP INLET SCREEN
housing.
on name
leaks after
engine
preformed packing
plate
and obtain
boss.
run.
(GEAR-TYPE PUMP) (POST-SB1155 ENGINES)
AND ALL PT6A-20A
REMOVAL A.
66.
filter
(1)
INSTALLATION A.
65.
AND ALL PT6A-20A
REMOVAL A.
64.
(GEAR-TYPE PUMP) (POST-SB1155 ENGINES)
Procedure
(See Figure 3-2-28)
(1)
Remove outlet filter
(2)
Unscrew inlet
(3)
Remove
(4)
Clean
as
detailed in
screen cover
Paragraph 63., preceding.
and withdraw
assembly.
long bolt, spring, washers and separate
screen as
detailed in Part 2,
screen
from
cover.
Cleaning.
INSTALLATION A.
Procedure
(1)
Attach
(See Figure 3-2-28) screen
washer.
to cover and
Tighten
secure
with
long bolt, spring,
steel washer and teflon
bolt, and torque 20 to 30 Ib.in.
Page
3-2-76
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
OUTLET PORT
PUMP DRIVE COUPLING
F.C.U. DRIVE COUPLING OUTLET FILTER HOUSING HOLE ’A’
FUEL HEATER OUTLET
INLET SCREEN COVER
I
HOLE ’B’
:h
INLET PORT
STRAIGHT ADAPTER
LEUF SPUMP OH
c~W ~!i
PUMPOUTLETI F.C.U. INLET HOSE
INLET
r9sa
FUEL PUMP OUTLET FILTER
ELBOW ADAPTER
(Post-SB11SS Fuel
and all PT6A-20A
C1214
Engines)
Pump and Filter Assembly Figure 3-2-28
Page
3-2-77
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(2)
Install two cover
preformed packings assembly to pump body. new
(3)
Tighten
(4)
Install outlet filter
cover to compress Lockwire to hole B.
as
on screen
preformed packing
detailed in
cover, and assemble
and
screen
and obtain metal-to-metal contact.
Paragraph 65., preceding.
TEMPERATURE COMPENSATOR 67.
REMOVAL A.
Procedure
(1)
(See Figure 3-2-29)
Disconnect
Py
tube at
coupling
nut
(1)
and P3 tube at
coupling
nut
(4) from
temperature compensator.
68.
(2)
Remove two bracket nuts (2) at
(3)
Loosen four bolts and nuts securing seal retaining
(4)
Remove temperature compensator complete with mounting bracket (3).
flange
G.
plate (5)
to
rear
fireseal
(6).
INSTALLATION A.
Procedure
(1)
If
(See Figure 3-2-29)
a new
at
(2)
is to be installed, transfer mounting bracket (3) plug and torque to 28 to 32 Ib.in.; tighten and torque nut Apply lockwire to both nuts.
temperature compensator
to new unit.
coupling
Tighten
nut at
38 to 42 Ib.in.
Position temperature compensator together with mounting bracket
on rear
fireseal
(6). (3)
Secure mounting bracket with two self-locking nuts (2) to flange G. Tighten nuts and
(4)
torque
Secure seal retaining plate (5) with four bolts and nuts. Tighten nuts and torque
(Ref. (5)
36 to 40 Ib.in.
No. 549, Fits
Reconnect tubes. lockwire.
Clearances).
Tighten coupling
nuts
(1
and
4), torque
40 to 65 Ib.in. and
apply
Page
3-2-78
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PNEUMATIC CONTROL LINE 69.
(P3)
AND P3 AIR FILTER
GENERAL A.
Should it be necessary to
replace the heated compressor discharge air pressure (P3)
tube, disconnect the heater electrical leads from the electrical bracket at
NOTE:
70.
flange
connector installed
on
G.
It is important to ensure that all solid pneumatic lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools, i.e., finger tight, before torquing. The installation of any pipe brackets should not distort the pipe in any way.
REMOVAUINSTALLATION OF ELECTRICAL CONNECTOR A.
Procedure
(See Figure 3-2-30) ENSURE CABLE HARNESS LEADS DO NOT TURN WHEN UNSCREWING BELL END FITTING FROM CONNECTOR SHELL.
CAUTION:
(1) (2)
(3)
Remove two
clamp
Unscrew bell end
screws
and cable sleeve
Slide
nylon
sleeve
B and D
(7)
(8)
clamp
(3)
halves from bell end
fitting (4).
and slide bell end
and rubber insulator (2) down heater harness to reveal of connector pins (7).
rear
Compressor discharge pressure (P3) A and B
(6)
remove
Using a suitable soldering iron, unsolder leads from connector pins (PT6A-6 Series, -6/C20, -20 and -20B) or B and D (PT6A-20A) compressor discharge air pressure (P3) tube heater leads. NOTE:
(5)
and
fitting (4) from flange mounted connector shell (1) (6) down electrical heater harness.
fitting
soldered terminals at
(4)
(5)
(PT6A-6 Series, PT6A-20 (PT6A-20A), Detail A.
A and B
for removal of
tube heater leads connect to
and
-20B),
Detail B
Carefully remove unsoldered tube heater leads by pulling through (2), bell end fitting (4) and cable sleeve (6).
rubber insulator
Insert relevant tube leads of
fitting (4)
and
insulator
(2).
nylon
sleeve
replacement unit through cable sleeve (6), bell (3). Pass leads through relevant holes in rubber
Using suitable soldering iron, solder leads to using Kester solder (PWC05-205)and Kester 3-2-30 for wire to pin location). Slide rubber insulator
(2)
and
nylon
sleeve
connector
resin flux
(3)
over
pins:
end
pins (7) solder buckets, (PWC05-031) (see Figure
soldered connections.
Page
3-2-79
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
910
O
I
5
I
C70
Temperature Compensator Figure 3-2-29
Page
3-2-80
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Slide bell end
1.
Coupling
Bracket Nut
3.
5.
Mounting Bracket Coupling Nut Seal Retaining Plate
6.
Rear Seal
REMOVAL A.
sleeve and over
screw
onto connector
cable sleeve
(6)
body; tighten fingertight.
and bell end
fitting
and
secure
(See Figure 3-2-31)
Disconnect
coupling
case
insulated tube
Remove two mount
(3)
over
clamp halves screws (5).
generator
(2)
Nut
(Pre-SB1294)
Procedure
(1)
fitting
Locate cable
with two 71.
3-2-29
DO NOT ALLOW LEADS TO TURN WHILE TIGHTENING BELL END FITTINGS.
CAUTION:
(10)
Figure
2.
4.
(9)
to
nuts of insulated tube
and tube
assembly (13)
at
assembly (11) rear
from elbow
fireseal mount
ring.
(9)
at gas
Remove
assembly.
self-locking
nuts that
secure
sealing
sleeve
(10)
to center fireseal
ring.
Remove two bolts that
secure
flanged
elbow
(9)
to gas
generator
case.
Remove
flanged elbow, gasket (8) and sealing sleeve. (4)
Release
self-locking nuts and bolts that secure seals (17) and seal retaining plates (16) (Post-SB1195) or seals (18) and seal retaining plates (19) (Pre-SB1195) to rear fireseal mount ring. NOTE:
Seals (17) and retaining plates (16) are common items shared with the fuel pressure line and, therefore, remain loosely attached to the mount
ring.
(5)
Disconnect
coupling
nut of tube
assembly (13)
at
straight nipple (14)
on
temperature
compensator. Remove tube assembly.
(6)
Disconnect electrical leads at connector
(12) secured to bracket (4) at flange G. (Refer to Paragraph 70., preceding.) Remove self-locking nuts that secure loop clamps, on electrical lead, to studs on flange G.
(7)
Disconnect
coupling (5)
coupling on
nuts of heated tube
assembly (1)
at elbow on FCU and tube
temperature compensator.
Page
3-2-’81
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2
1
3
4
5
6
KEY
O
O
I
Al o
o
O
O
7
FOR AIRFRAME USE
B
Ool
P3 HEATER LEAD
C5173 Electrical Connector
Figure
Wiring
Details
3-2-30
Page
3-2-82
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
72.
to
Figure
Mounted Connector Shell
1.
Flange
2.
Rubber Insulator Sleeve
3.
Nylon
4.
Bell End
Fitting
Screws
5.
Clamp
6.
Cable Sleeve
7.
Pin
REPLACEMENT OF P3 FILTER ELEMENT A.
Cut lockwire and
(34) (2)
(Post-SB1294)
(See Figure 3-2-32)
Procedure
(1)
3-2-30
and
Install
remove
new
and install
remove cover (32) from preformed packings (17
filter and
housing (14); withdraw 33) and discard.
preformed packing (17) in recess at inner end preformed packing (33) on cover (32).
of
new
filter element
filter element
(34)
new
(3)
Install filter element in filter housing spigot in centerbore of housing.
(4)
Apply engine oil to cover threads and screw filter cover (32) into tighten to compress preformed packing (33) and torque 60 to 70 to housing.
(14);
ensure
preformed packing (17) filter
slides
over
housing,
Ib.in.
revoceriwkcoL
73.
REMOVAL A.
(Post-SB1294)
Procedure
(1)
(See Figure 3-2-32)
Disconnect electrical leads at connector secured to bracket (26) at flange G. (Refer Paragraph 70., preceding.) Remove self-locking nut and bolt that secure loop clamps (30) to bracket (35) and remove loop clamps from electrical leads of heated tube assemblies (1 and 4). to
(2)
Disconnect
elbow
on
coupling
nuts of heated tube
assembly (4)
at elbow on FCU and at
top of P3 filter housing (14). Remove tube assembly.
(3)
Disconnect coupling nuts of heated tube assembly (1) at straight nipple (2) on the rear of filter housing (14) and tube coupling (25), and on the rear of temperature compensator (18); remove tube assembly.
(4)
Disconnect
generator
coupling
case
insulated tube
(5)
nuts of insulated tube
and tube
assembly (29)
assembly (28)
from elbow
at rear fireseal mount
ring;
(22)
at gas
remove
assembly.
Remove two bolts and fireseal mount ring.
self-locking
nuts that secure
sealing
sleeve
(23)
at center
Page
3-2-83
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
17
16 FCU
2
3
4
5
6
j POST-SB1195 REAR MOUNT
(D71
1´•9,
RING´•-I
(Cr
~00 PRE-SB1195
(8 10
CENTER FIRESEAL FIOUNT RING
C9169
(Pre-SB1294) Temperature ~ompensator and P3 Tube Figure 3-2-31
Page
3-2-84
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
1.
Heated Tube
2.
Jam Nut
3.
Jam Nut
3-2-31
Assembly
7.
Mounting Bracket Coupling Plug Preformed Packing
8.
Gasket
9.
Flanged Elbow Sealing Sleeve
4. 5.
Tube
6.
10. 11.
Insulated Tube
12.
Electrical Connector
13.
Tube
Assembly
Assembly Straight Nipple Preformed Packing Seal Retaining Plate (Post-SB1195) Seal (Post-SB1195) Seal (Pre-SB1195) Seal Retaining Plate (Pre-SB1195)
14. 15.
16. 17. 18. 19.
(6)
Remove two bolts that secure flanged elbow (22) at gas generator elbow, sealing sleeve and gasket (21); discard gasket.
(7)
Loosen
Remove
self-locking nuts and bolts that secure seals (8) and retaining plates (7) (Post-SB1195) or seal (6) and retaining plate (5) (Pre-SB1195) to rear fireseal mount ring. NOTE:
Seals
(8)
pressure
(8)
case.
Disconnect
and
retaining plates (7)
are common
items shared with the fuel
line, therefore, they should only be removed if found unserviceable.
coupling
nut of tube
assembly (29) from straight nipple (36) assembly.
at
temperature compensator. Remove tube
(9)
Remove
self-locking nuts, washers and bolts that secure housing assembly (14) (26). Remove housing assembly, spacers (13) and bracket (16).
to
filter bracket
(10)
If filter housing assembly is to be replaced with a serviceable unit, remove elbow fitting (9) and straight nipple (2) from assembly, and retain for reuse. Discard preformed packings (3 and 12), and packing retainer (11).
Page
3-2-85
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
F.C.U.
5J P0ST-SB1195
PRE-SBI 195 I VIEW
A
s
FLANGE
G
34
REAR FIRESEAL MOUNI.NC
116
7
15
20
19
18
27 I
35
j 31)
(26
25) 21
23)
Y~22
~-y´•a 28)
io~
CENTER FIRESEAL MOUNT RING
~2q
C8140
(Post-SB1294) Pneumatic Lines and P3 Filter Figure 3-2-32
Page
3-2-86
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key 1. 2.
3. 4. 5.
6. 7.
8. 9. 10.
to
Figure 3-2-32
Assembly Straight Nipple preformed Packing Heated Tube Assembly Seal Retaining Plate (Pre-SB1195) Seal (Post-SB1195) Seal Retaining Plate (Post-SB1195) Seal (Post-SB1195) Heated Tube
Elbow Jam Nut Retainer
11.
Packing
12.
Preformed
15.
Packing Spacer Filter Housing Assembly Loop Clamp (Fuel pressure)
16.
Angle
17.
Preformed Packing
18.
20.
Temperature Compensator Plug Preformed Packing
21.
Gasket
22.
25.
Flanged Elbow Sealing Sleeve Preformed Packing Tube Coupling
26.
Filter Bracket
27.
Jam Nut
13. 14.
19.
23. 24.
Bracket
28.
Insulated Air Pressure Tube
29.
Air Pressure Tube
30.
Loop Clamps
31.
Jam Nut
32.
Cover
33.
Preformed Packing
34.
Filter Element
35.
Bracket
36.
Straight Nipple
Page
3-2-87
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
74.
(Pre-SB1294)
INSTALLATION A.
(See Figure 3-2-31)
Procedure
It is important to ensure that all solid pneumatic lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools, i.e., finger tight, before torquing. The installation of any pipe brackets should not distort the pipe in any way.
NOTE:
(1)
sealing sleeve (10) on flanged elbow (9) then locate elbow and new gasket gas generator case, passing screwed end of elbow and boss of sealing sleeve through hole in center fireseal mount ring. Locate
(8)
(2)
on
Secure to 40
flanged
elbow to gas
generator
case
with two bolts.
Ib.in., and apply lockwire. Secure sealing sleeve
with bolts and
self-locking
nuts.
Tighten
nuts and
T~ghten bolts, torque 36 ring
to center fireseal mount
torque
36 to 40 Ib.in.
(3)
retaining plates were removed from rear fireseal mount ring during removal, proceed as follows. If seals and retaining plates were serviceable and remained attached to mount ring, proceed to Subparagraph (d). Locate seals (17) and seal retaining plates (16) on front and rear faces of rear fireseal mount ring (Post-SB1195) or single seal (18) and seal retaining plate (19) on front face of rear fireseal mount ring (Pre-SB1195) and secure with bolts and self-locking nuts (bolt heads to be on air inlet side of mount ring). Do not tighten nuts at this stage.
(4)
assembly (13) through rear fireseal mount ring and loosely mounted seals coupling nut of assembly to straight nipple (14) on temperature compensator. Tighten coupling nut, torque to 90 to 100 Ib.in., and apply lockwire. Tighten self-locking nuts and bolts that secure seals and seal retaining plates to mount ring and torque fingertight plus 180 degrees.
If seals and
Pass tube
and connect
(5)
Locate heated tube assembly (1) between elbow fitting on fuel control unit (FCU) and tube coupling (5) on temperature compensator. Tighten coupling nuts 90 to 100
(6)
Ib.in., and apply lockwire.
Route electrical lead of heated tube assembly forward and under mounting bracket (4) and connect leads to relevant pins of connector on bracket. (Refer to Paragraph
70.). (7)
assembly (11) between tube assembly (13) and flanged (9). Connect coupling nut of insulated tube to threaded fitting of tube assembly (13). Tighten nut and torque 90 to 100 Ib.in., and apply lockwire. Locate insulated tube
elbow
(8)
pressure
(9)
pneumatic pressure test (Refer to Part 2, Testing) connecting coupling nut at front end of insulated tube assembly.
Perform fuel system source
At conclusion of
assembly (11)
to
to
satisfactory pressure test, connect coupling nut of insulated flanged elbow (9). Tighten nut, torque 90 to 100 Ib.in., and
tube
lockwire.
Page
3-2-88
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INSTALLATION (Post-SB1294) A.
Procedure NOTE:
(1)
If
(See Figure 3-2-32)
It is important to ensure that all solid pneumatic lines are properly and correctly fitted before the coupling nuts are tightened. The coupling nuts should be seated without the use of tools (finger tight) before torquing. The installation of any pipe brackets should not distort the pipe in any way.
overhauled P3 air filter assembly is being installed, fit elbow nipple (2) prior to installation as follows:
new or
straight
Fit new preformed packing (3) on straight nipple (2) and install in boss at of filter housing (14). Tighten nipple and torque 38 to 42 Ib.in.
(a)
rear
Fit
and
(14)
tighten (Ref. 640,
Fits
Clearances).
Do not
torque
at this
stage.
Locate two bolts and washers in filter bracket, bolt heads on air inlet side of bracket. Fit two spacers (13) on bolts followed by filter housing (14). Secure filter housing with two self-locking nuts, positioning bracket (16) at outer location.
Tighten
(3)
and
jam nut (10) on double-threaded section of elbow followed by packing retainer (11) and preformed packing (12), locating preformed packing in non-threaded annulus. Assemble elbow fitting into boss at top of filter housing
(b)
(2)
fitting (9)
nuts and
torque
32 to 36 Ib.in.
assembly (4) and connect coupling nuts to elbow fitting on fuel (9) at top of filter housing (14). Tighten nuts, torque 90 to Ib.in., and apply lockwire.
Locate heated tube
control unit and to elbow 100
(4)
Locate heated tube on
assembly (1)
and connect
coupling
temperature compensator (18). Tighten nuts, torque
nuts to tube
90 to 100
coupling (25)
Ib.in., and apply
lockwire.
(5)
Route electrical leads of heated tube assemblies
(1 and 4) under bracket (26) and of electrical connector mounted on pins bracket. (Refer to Paragraph 70. for wiring details). Secure two leads to angle bracket (35) with two loop clamps (30), nuts and bolts. Tighten self-locking nuts and torque 36 to 40 Ib.in. connect leads to relevant connector
(6)
If seals and
were removed from rear fireseal mount ring during follows. If seals and retaining plates were serviceable and remained attached to mount ring, proceed to Subparagraph (7). Locate seals (8) and retaining plates (7) on front and rear faces of rear fireseal mount ring (Pre-SB1195)
retaining plates
removal, proceed
or
single
and
(7)
(6) and retaining plate (5) on front face of mount ring (Post-SB1195) with bolts and self-locking nuts (bolt heads to be on air inlet side of mount
seal
secure
ring).
as
Do not
tighten
nuts at this
stage.
Pass tube
assembly (29) through rear fireseal mount ring and loosely mounted coupling nut of assembly to straight nipple (36) on temperature compensator (18). Tighten coupling nut, torque 90 to 100 Ib.in., and apply lockwire. Tighten self-locking nuts and bolts that secure seals and seal retaining plates to rear fireseal mount ring and torque fingertight plus 180 degrees. seals and connect
Page
3-2-89
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(8)
(9)
Locate sealing sleeve (23) on flanged elbow (22), then locate elbow and new gasket (21) on gas generator case, passing screwed end of elbow and boss of sealing sleeve through hole in center fireseal mount ring. Secure
elbow to gas generator case with two bolts. T~ghten bolts, torque 36 Ib.in., apply lockwire. Secure sealing sleeve to center fireseal mount ring with two bolts and self-locking nuts (bolt heads to be on air inlet side of mount ring). Tighten nuts and torque 36 to 40 Ib.in.
flanged
to 40
(10)
and
Locate insulated tube
assembly (28) between tube assembly (29) and flanged (22). Connect coupling nut of assembly to threaded fitting of tube assembly (29). Tighten nut, torque 90 to 100 Ib.in. and apply lockwire.
elbow
(11)
Perform fuel system pressure
(12)
source
to
At conclusion of
assembly (28)
to
pneumatic pressure test (Refer to Part 2, Testing) connecting coupling nut at front end of insulated tube assembly (28).
satisfactory pressure test, connect coupling nut of insulated tube flanged elbow (22). Tighten nut, torque 90 to 100 Ib.in., and apply
lockwire.
OIL FILTER 76.
REMOVAL OF FILTER ELEMENT A.
Procedure
(1)
Remove four cover
(2)
(See Figures (1)
Remove
CAUTION:
77.
3-2-33 and
self-locking
nuts
3-2-34)
(20, Figure 3-2-33) and
washers
(19) securing
filter
to compressor inlet case. cover
from
case
and
preformed packing (17)
remove
from
cover.
EXERCISE CARE WHEN INSERTING PULLER FOR REMOVAL OF FILTER ELEMENT NOT 10 DAMAGE INNER SCREEN OF ELEMENT.
(3)
Remove filter element
(4)
Remove
(5)
Clean filter element
(15)
from filter
preformed packings (16 as
and
housing (5) using 21)
detailed in Part 2,
Puller
(PWC30556).
from filter element.
Cleaning.
INSTALLATION OF FILTER ELEMENT A.
Procedure
(See Figures
3-2-33 and
(1)
Install
(2)
Insert element into filter
(3)
Ensure teflon spacer
(4)
Install
preformed packings (16
3-2-34)
and 21,
Figure 3-2-33)
on
filter element
housing (5) perforated flange first,
(18)
is
firmly
preformed packing (17)
on
seated
on
filter
cover
filter cover, and install
(15).
in compressor inlet
case.
(1). cover on
compressor inlet
case.
Page
3-2-90
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(5)
Secure
cover
torque 36 78.
with four washers
REMOVAL OF FILTER HOUSING A.
Procedure
(1) (2)
(19)
and
self-locking
nuts
(20). Tighten
nuts and
to 40 Ib.in.
(See Figures
(Pre-SB1247)
3-2-33 and
Remove filter element.
(Refer
3-2-35) to
Paragraph 76., preceding.)
Place suitable container under compressor inlet case. Remove cotterpin and drain bottom of inlet case. Remove drain plug using Puller (PWC30077) oil tank to drain. Remove preformed packing from drain plug.
plug lockpin from and allow engine (3)
Remove filter
(4)
Remove
housing (3, Figure 3-2-35) from compressor inlet (4) (PWC30328).
preformed packings (3
and 9,
Figure 3-2-33)
and
case
using
plastic ring (4)
Puller
from
housing. 79.
INSTALLATION OF FILTER HOUSING A.
(Pre-SB1247)
Procedure
(See Figure 3-2-33)
(1)
Install
preformed packing (9)
Install
plastic ring (4) and preformed packing (3) positioning of ring and packing.)
(2)
on
housing. on
housing. (Refer
to
Figure
3-2-35 for
(3)
Insert filter Avoid
housing in compressor inlet case; push in by hand until firmly applying side loads on housing while pressing into position.
(4)
Install filter element.
(5)
Install drain Secure with
(6)
Fill oil tank with
(Refer
to
Paragraph 77., preceding.)
plug with preformed packing in bottom of compressor inlet lockpin and cotterpin. approved
seated.
oil and check oil level.
(Refer
to Part
case.
2, Engine Oil
System Servicing.) 80.
STATIC LEAK CHECK OF FILTER HOUSING A.
(Pre-SB1247) (Ref. Fig. 3-2-33)
Procedure
engine stand for two hours. Monitor oil leakage into filter housing; maximum leakage permitted is 0.5 ml/hr. If leakage exceeds limits, verify condition of preformed packing(s) (items 3 and 9).
(1)
Let
(2)
If necessary,
(3)
If leakage persists, replace part(s) if necessary and/or repeat lapping procedure applicable.
replace preformed packing(s) and repeat step (1).
Page
as
3-2-91
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
15
I;´•"--’;14~
1
I
a
i
22 20
4 14
2)
(10
12
13
11) (12) DETAIL
(13
A
INSTALLATION OF VEE PACKING
C1237D
Disassembly/Assembly of Figure 3-2-33
Oil Filter
Page 3-2-92 Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
3-2-33
1.
Oil Filter Cover
2.
Check Valve
3.
Preformed
12.
Packing Retaining Ring Filter Housing Check Valve Spring Spring Retainer Collar Lockpin Preformed Packing Bypass Valve Spring Packing Bypass Valve Piston
13.
Washer
14.
Cotterpin
15.
Oil Filter Element
16.
Prefdrmed
17.
Preformed
18.
Teflon
19.
Washer
20.
Nut
21.
Preformed
4.
5. 6. 7. 8.
9. 10. 11.
22. 81.
to
Plastic
Packing Packing Spacer
Repair
Packing (if fitted).
Washer
REMOVAL OF CHECWBYPASS VALVE ASSEMBLY (Pre-SB1247) A.
Procedure
(See Figure 3-2-33)
(1)
Remove oil filter element.
(2)
Remove oil filter
(3)
Compress
to
Paragraph 76., preceding.)
housing. (Refer
to
Paragraph 78., preceding.)
check valve check valve spring and and bypass valve from valve face. NOTE:
(4)
(Refer
spring (6) and remove lockpin (8) and collar (7). Remove repair washer (22) if fitted, and remove assembly of check housing (5). Care should be exercised not to damage
If repair washer is fitted and housing is serviceable, retain washer for reinstallation. If housing is to be replaced, discard repair washer.
If new check valve (2) or bypass seating requires lapping (refer to valve in the following manner:
(a) Compress bypass
valve
piston (12) is to be installed, or check valve Repair), disassemble check and bypass
Part 4,
valve piston from stem of check valve.
(12)
and
remove
cotterpin (14)
and washer
Page
(13)
3-2-93
Nov 26/2004
PRATT g, WHITNEy CANADA IMAINTENANCE MANUAL MANUAL PART
"I
i
NO. 3015442
F~
I bt~, fd, ~v
Oil Filter Cover and
Element
C660A
Figure 3-2-34
Page 3-2-94 Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
(b) Carefully
Figure
to
3-2-34
1.
Filter Element
2.
Teflon
3.
Oil Filter Cover
release and
remove
Spacer
piston, spring (10)
and
packing (11)
from
check valve. 82.
INSTALLATION OF CHECWBYPASS VALVE ASSEMBLY (Pre-SB1247) A.
Procedure
(1)
(See Figure 3-2-33)
Assemble check valve and
bypass
valve
piston
in the
following
(a)
Install
(b)
Install packing (11) in inner groove of bypass valve of packing facing outer groove of piston (Det. A).
(c)
Install
bypass
bypass
valve
valve
(d) Compress spring stem with washer
(2)
Slide check and
(3)
Hold valve
spring (10)
piston
over
until stem
(13)
bypass
and
valve
over
stem on check valve
spring (10)
(2).
piston (12)
with open end
and into centerbore of check valve
protrudes from end of piston cotterpin (14).
assembly
manner:
into filter
housing
assembly in position with suitable fiber drift spring (6), spring retaining collar (7) on protruding and
and
secure
piston
on
until seated.
and install check valve
section of check valve
stem
NOTE:
If a repaired filter housing is being reinstalled ensure repair washer installed between shoulder on housing and check valve spring.
(4)
Compress spring with collar and insert lockpin (8) through hole in valve stem. Release spring and allow collar to slip over lockpin. Ensure lockpin is completely covered by retaining collar.
(5)
Install oil filter
housing
and element
OIL FILTER HOUSING 83.
(22)
(Ref.
Para. 79. and
is
77.).
(POST-SB1247)
REMOVAL A.
Procedure
(1)
Place case.
(Ref. Figure 3-2-36) a suitable container directly under the oil drain Remove oil drain plug from bottom case using
plug of the compressor puller (PWC30077) and
inlet
drain
oil.
Page
3-2-95
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1iu, B
~W1 PREFORMED PACKING PLASTIC RING
025
Oil Filter
Figure
Housing 3-2-35
Page
3-2-96
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
84.
to
Figure
3-2-35
1.
Oil Filter Cover Mount Pad
2.
Check Valve Collar
3.
Filter
4.
Puller
(2)
Remove filter element
(3)
Remove filter
Housing (PWC30328)
(Ref. Para. 76.).
housing (9)
from compressor inlet
case
using puller (PWC30328).
INSTALLATION A.
Procedure
(See Figure 3-2-36)
(1)
Install
preformed packing (8)
Install
plastic ring (10) and preformed packing (11) positioning of ring and packing).
(2)
on
housing (9). on
housing (Refer
Figure
to
3-2-35 for
85.
(3)
Insert filter housing in compressor inlet case; push in by hand until Avoid applying side loads on housing while pressing into position.
(4)
Install filter element
(5)
Install drain Secure with
(6)
Fill oil tank with approved System Servicing).
(Refer
seated.
Paragraph 77., preceding).
plug with preformed packing lockpin and cotterpin.
STATIC LEAK CHECK (Ref. Fig. A.
to
firmly
in bottom of compressor inlet
oil and check oil level
(Refer
to Part
case.
2, Engine Oil
3-2-36)
Procedure
(1)
Let
(2)
If necessary,
(3)
engine stand for two hours. Monitor oil leakage into filter housing (maximum leakage permitted is 0.5 ml/hr). If leakage exceeds limits, verify condition of preformed packing(s) (items 8 and 11).
If
replace preformed packing(s)
leakage persists, replace applicable.
the necessary
and
repeat step (a).
part(s)
and/or repeat
lapping procedure,
as
OIL FILTER CHECK AND BYPASS VALVE ASSEMBLY 86.
(POST-SB1247)
REMOVAL A.
Procedure
(1)
(See Figure 3-2-36)
Remove oil filter and filter
housing (Refer
to
Paragraphs
76. and 83.,
preceding).
Page
3-2-97
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ITEM 14 ON PRE-SB1379 ENGINES ONL
e
6
o\:
3) i~
I:
P
INSTALL ITEM 20 IN THIS POSITION
12)
15 17
16
IX ~23
jQ
Post-SB1247, Pre-SB1379 Oil Filter Element,
Housing and Bypass/Check Figure 3-2-36
C621 8C Valve
Page
3-2-98
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
to
3-2-36
1.
Preformed
2.
Filter Element
3.
Preformed
4.
Preformed
5.
Teflon
6.
Cover
7.
14.
Retaining Ring Preformed Packing Filter Housing Plastic Ring Preformed Packing Preformed Packing Valve Housing Preformed Packing (Pre-SB1379)
15.
Check Valve
16.
21.
Spring Bypass Valve Guide Spring Retaining Ring Preformed Packing (V-type) Bypass Valve
22.
Washer
23.
Cotterpin
8. 9. 10.
11. 12. 13.
17. 18. 19. 20.
Packing
Packing Packing Spacer
of check and
(2)
Exercising care, remove retaining ring (7) bypass valve from filter housing (9).
(3)
Remove
(4)
retaining ring (19) and separate bypass valve guide (17) from valve housing (13). Exercise care when removing check valve (15) as it is spring loaded valve guide.
preformed packing (12)
and withdraw
from check valve
(15)
and
spring (16)
(6)
Remove
preformed packing (14, Pre-SB1379)
Exercise
care
bypass assembly.
to
Remove
during (21)
valve
spring (18)
this and
to
from valve seat.
Remove check valve
(8)
housing (13).
Remove
(5)
(7)
assembly
from valve
(15).
operation as parts are spring loaded. Apply light pressure remove cotterpin (23) and washer (22). Separate
from shaft of
guide
and
preformed packing (20) from valve
(21).
Page
3-2-99
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
87.
INSTALLATION A.
Procedure
NOTE:
(See Figure 3-2-36)
assembly, new check (Refer to Part 4, Repair) Prior to
packing (20)
valve and/or seat
bypass
valve
(Post-SB1379)
(21).
Ensure
must be
packing
lapped.
is installed
(1)
Install preformed shown
(2)
on internal shaft of bypass valve guide (17). Locate bypass valve shaft and compress spring so that shaft protrudes from end of valve. Secure assembly with washer (22) and cotterpin (23).
Install
(21)
(3)
on
as
spring (18)
over
Install
preformed packing (14, Pre-SB1379) Preformed
NOTE:
packing (14)
not
on
required
seating
on
face of check valve
reworked
(Post-SB1379)
(15). valve
ass~embly. (4)
Install spring (16) in recess in external shaft of bypass valve guide (17). Install complete assembly in valve housing (13) and secure with retaining ring (19).
(5)
Install
preformed packing (12)
Install
valve
housing (13).
PRIOR TO INSERTION OF VALVE ASSEMBLY INTO HOUSING, ENSURE PREFORMED PACKING (12) IS CORRECTLY SEATED ON VALVE SEAT AND IS NOT DISTORTED.
CAUTION:
(6)
on
complete assembly of check with retaining ring (7).
and
bypass valve
in oil filter
housing,
and
secure
housing (Refer
to
Paragraph 84., preceding).
(Refer
to
Paragraph 77., preceding).
(7)
Install oil filter
(8)
Install oil filter element
(9)
Fill oil tank with
approved
oil
(Refer
to Part
2, Engine Oil System Servicing).
OIL PRESSURE RELIEF VALVE 88.
REMOVAL A.
Procedure
(1)
(See Figure 3-2-37)
Remove two bolts
(4)
and
plain
washers
(3) securing relief
valve
cover
(2)
to inlet
case.
(2)
Remove
(3)
Withdraw relief valve
(4)
Wash valve
cover
using
Puller
(PWC30046-53).
assembly.
assembly
in
petroleum
solvent
(PWC11-027).
Page
3-2-100
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INSTALLATION A.
Procedure
(See Figure 3-2-37)
(1)
Install new preformed insert valve body into
(2)
Assemble
(3)
packing (7) on main oil pressure relief housing in compressor inlet case (6).
Insert
bypass valve (9), adjusting spacers (8; max. 4 required) assembly into main oil pressure relief valve body (10).
Install
new
preformed packing (1) assembly, secure with Ib.in. and apply lockwire.
relief valve 32 to 35
on
relief valve
washers
(3)
cover
body (10) and
and
spring (5).
(2) and place cover over (4). Tighten bolts, torque
and bolts
IGNITION SYSTEM BALLAST TUBES 90.
valve
(PRE-SB1429)
REMOVAL A.
Procedure
(See Figure 3-2-38)
(1)
Remove four spacers
(2)
Remove tubes
taking
care
securing
together
not to bend
cover
of
ignition
with tubular copper
current
spring
regulator, and detach
cover.
cushions. Slide out cushions
spring fingers.
INSTALLATION A.
Procedure CAUTION:
POST-SB1103 AND ALL PT6A-20A ENGINES: INSTALL RESISTOR TUBES IN POSITIONS INDICATED ON FIGURE 3-2-38.
(1)
Slide copper
(2)
Press tube
(3)
Install
spring spring fingers. firmly
ignition
cushion
into
glass
bulb end of tube
receptacle provided
regulator cover and apply safety wire.
current
10 to 11.5 Ib.in. and
over
in
ignition
secure
IGNITION CURRENT REGULATOR 92.
taking
current
retaining
care
not to bend
regulator.
screws.
Torque
screws
(PRE-SB1429)
REMOVAL A.
Procedure
(1) (2)
Disconnect power
input and ignition glow plug
Remove three bolts and washers securing Remove regulator.
cables from
ignition
current
receptacles regulator
on cover.
to accessory
gearbox housing.
Page
3-2-101
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2)
(4)
(3
5
II
Y
~s
io
C135A Main Oil Pressure Relief Valve
Figure
3-2-37
Page
3-2-102
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
1.
Preformed
Relief Valve Cover
Packing
3.
Plain Washer
4.
Relief Valve Cover Bolt
5.
Valve
7.
8. 9. 10.
Spring Compressor Inlet Case Preformed Packing Adjusting Spacers Bypass Valve Relief Valve Body
INSTALLATION A.
Procedure
(1)
Install ignition current regulator on three bosses provided on accessory gearbox housing with washers and bolts. Torque bolts 36 to 40 Ib.in. and apply safety wire.
(2)
Connect power input and ignition glow Torque cable nuts (Ref. No. 561, Fits
IGNITION EXCITER 94.
3-2-37
2.
6.
93.
to
plug cables to receptacles on regulator Clearances) and apply safety wire.
cover.
(POST-SB1429)
REMOVAL A.
Procedure
WARNING:
(See Figure 3-2-39)
RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. ENSURE THAT IGNITION IS SWITCHED OFF, AND SYSTEM HAS BEEN INOPERATIVE FOR AT LEAST SIX MINUTES BEFORE REMOVING ANY IGNITION COMPONENTS. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER END FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE CABLE COUPLING NUTS. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.
(1)
Isolate power from
(2)
Remove
CAUTION:
supply
cable from
Remove two
(4)
Remove four bolts
(5)
input
connector
on
ignition
exciter
(4).
DO NOT ALLOW IGNITION CABLE BRAIDING OR FERRULE TO ROTATE WHEN REMOVING COUPLING NUTS.
(3)
(7) and
ignition system.
ignition
remove
cable
couplings
(1), self-locking ignition exciter.
Remove three bolts
(5)
from output connectors
nuts
and washers
(3)
and washers
(6) securing
an
ignition
(2) securing
bracket
(7)
to
exciter.
unit to bracket
engine casing.
Page
3-2-103
Nov 26/2004
PRATT
WHITNEV CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1)
(2
A s
B
A
I (ilT~I ~lil a~
B
6)
15
C1327A
Ignition Current Regulator Figure 3-2-38
Page
3-2-104
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
95.
to
Figure
3-2-38
1.
Ignition
2.
Cover
Box
3.
Bolt
4.
Cables
5.
Resistor
6.
Cushion
7.
Spring
INSTALLATION A.
Procedure
(1)
(2)
(See Figure 3-2-39)
Secure bracket
(7)
bolts, torque 36
to 40
Secure
ignition
with four bolts 36 to 40 Ib.in. CAUTION:
(3)
Lightly
engine casing with three Ib.in., and safety wire.
bolts
(5) and washers (6). Tighten
exciter (4), with single input connector uppermost, to bracket (7) washers (2) and self-locking nuts (3). Tighten nuts and torque
(1),
DO NOT ALLOW ANY LUBRICANT TO COME IN CONTACT WITH CENTRALCONDUCTORS OF EXCITER CONNECTORS. CONTACT WITH CONDUCTORS MAY RESULT IN A HIGH RESISTANCE PATH WHICH COULD GENERATE HEAT AND OXIDATION. coat threads of
CAUTION:
(4)
to
ignition exciter
connectors with fluorocarbon spray lubricant.
DO NOT ALLOW IGNITION CABLE BRAIDING OR FERRULES TO ROTATE WHEN SCREWING ON COUPLING NUTS.
Connect
coupling nuts of supply cable and two high tension ignition cable couplings respective connectors on ignition exciter. Tighten nuts, torque fingertight plus 45 degrees and safety wire.
to
CAUTION:
(5)
DO NOT ALLOW BRAIDING OR FERRULES TO ROTATE WHEN SCREWING ON COUPLING NUTS.
Reconnect nuts and
coupling
nuts at other end of
torque fingertight plus
45
ignition degrees.
cables to
spark igniters. Tighten
OIL-TO-FUEL HEATER 96.
REMOVAL A.
Procedure
(1)
(See Figure 3-2-40)
Disconnect lines from oil-to-fuel heater assembly oil inlet (4) and oil outlet (7) connections.
(1)
at fuel inlet
(2), fuel
outlet
Page
(3),
3-2-105
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
7
P f
INpm
CONNECTOR
9
I:
d OUTPUT CONNECTORS
C41 498
(Post-SB1 429) Removal/installation of
Figure
Ignition
Exciter
3-2-39
Page 3-2-106 Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
(2)
to
Figure
3-2-39
1.
Bolt
2.
Washer
3. 4.
Self-locking Nut Ignition Exciter
5.
Bolt
6.
Washer
7.
Bolt
Remove self-locking nuts and washers G.
securing
heater
mounting
bracket to
flange
97.
(3)
Withdraw heater
(4)
Remove bolts
(5)
Withdraw heater,
(6)
Install dust caps
mounting bracket (6)
(5) securing together over
heater to
and heater from studs
mounting
flange
G.
bracket.
with two transfer tubes, from
ends of all lines and
on
mounting
bracket.
fittings.
INSTALLATION A.
Procedure
(See Figure 3-2-40)
(1)
new
Install
mounting
preformed packings (6).
on
two transfer tubes and insert transfer tubes into
bracket
(2)
Install heater (1) over transfer tubes and secure to mounting Tighten bolts, torque 32 to 36 Ib.in. and attach lockwire.
(3)
Install heater and with washers and
(4)
Remove all dust caps and reconnect fuel and oil lines to their Tighten nuts, and torque as follows:
bracket with bolts
mounting bracket assembly over studs on flange G and self-locking nuts. Tighten nuts and torque 32 to 36 Ib.in.
(a)
Fuel inlet hose
(b)
Fuel outlet hose
(c)
Oil inlet hose
(d)
Oil outlet hose
coupling nut, torque
secure
connections.
65 to 85 Ib.in.
coupling nut, torque
coupling nut, torque
respective
(5).
200 to 225 Ib.in.
110 to 120 Ib.in.
coupling nut, torque
110 to 120 Ib.in.
Page
3-2-107
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
0630 Oil-to-Fuel Heater
Figure
3-2-40
Page
3-2-108
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
3-2-40
1.
Oil-to-Fuel Heater
2.
Heater fuel Inlet Connection
Assembly
3.
Heater Fuel Outlet Line
4.
Heater Oil Inlet Connection
5.
6.
Retaining Bolts Heater Mounting
7.
Heater Oil Outlet Connection
Bracket
ACCESSORY DRIVE SEALS 98.
REMOVAL A.
Procedure
(1)
(See Figure 3-2-41)
Remove the accessory unit, if
applicable,
from the
mounting pad
on
the accessory
gearbox housing. (2)
gearshaft oil-seal carrier puller (PWC30046-57), and the starter-generator gearshaft oil-seal carrier puller (PWC30046-52) on Pre-SB1386 dry-spline starter-generator arrangements, or puller (PWC30046-54) on Post-SB1386 wet-spline starter-generator arrangements, to remove oil-seal and carrier from the gearbox housing. Use the
NOTE:
(3) 99.
When
removing seals at the fuel control unit (FCU) and the starter-generator mounting pads, make sure that the retaining rings are removed before attempting to withdraw the assembled seal and carrier.
Remove seal and
preformed packing from the
oil-seal carrier.
INSTALLATION A.
Procedure
(1)
(2)
(See Figure 3-2-41)
Moisten silicone element seal with
correctly
seated.
NOTE:
Use hand pressure
Install
only
engine
oil and
gently
press seal into carrier until
to install seal. Do not use bench press.
preformed packing on carrier and install seal and carrier assembly into respective using Drift (PWC30075 Pre-SB1386) or (PWC30675 Post-SB1386). new
boss
(3)
For starter-generator and FCU drive seal and carrier assemblies,
secure
with
retaining rings. NOTE:
(4)
Starter-generator gearshaft may be spline (Post-SB1386) configuration.
Check for oil
leakage (Ref.
of
dry spline (Pre-SB1386)
Part 2, Section 6, Para.
or
wet
31).
Page
3-2-109
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
I: ~3 :ic"’
/´•/Pa~
i,
Ii \i,
~a
NOTE: DETAIL
A
I;
i II1(
RETAINING RINGS AT FCU AND STARTER-GENERATOR GEARSHAFT NOT SHOWN
C502B
Accessory
Drive Seal
Figure
Replacement (Typical) 3-2-41
Page
3-2-110
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(5)
Check for oil
leakage
after 5 to 10 hours of
operation (Ref. Part 2, Section 6, Pam.
31).
PROPELLER REVERSING INTERCONNECT LINKAGE 100.
GENERAL
CAUTION:
A.
101.
THE FOLLOWING ASSEMBLY INSTRUCTIONS ARE GIVEN PRIMARILY TO SATISFY SHIPPING REQUIREMENTS AND THE RESULTANT RIGGING MAY DIFFER QUITE CONSIDERABLY FROM WHAT IT SHOULD BE WHEN THE ENGINE IS INSTALLED IN THE AIRFRAME. AT ENGINE INSTALLATION BY THE AIRFRAME MANUFACTURER THE LINKAGE IS ADJUSTED TO SUIT A PARTICULAR AIRFRAME REQUIREMENT. THIS ADJUSTMENT MAY INCLUDE ALTERING ROD LENGTHS, MOVING CLEVIS PINS TO DIFFERENT HOLES AND, IF NECESSARY, SELECTING A DIFFERENT CAM TO PROVIDE THE REQUIRED POWER RESPONSE CHARACTERISTICS. THE FINAL RIGGING ARRANGEMENT IS PART OF THE AIRCRAFT CERTIFICATION REQUIREMENT AND IS DETAILED IN THE APPROPRIATE AIRCRAFT MAINTENANCE MANUAL. THEREFORE, WHEN AN ENGINE IS REINSTALLED IN AN AIRCRAFT AFTER OVERHAUL OR REPAIR, THE ENGINE SHOULD BE RIGGED IN ACCORDANCE WITH THE RELEVANT AIRCRAFT MAINTENANCE MANUAL AND NOT IN ACCORDANCE WITH THE APPLICABLE P&WC MAINTENANCE OR OVERHAUL MANUAL.
adjustments in the following paragraphs are designed to provide the correct power relationship at all ambient temperatures. However, aircraft installations will differ and reference should be made to the power plant section of the applicable aircraft manual. It is assumed that all rigging will be accomplished with the propeller installed and blades in the full feather position.
The
REMOVAL OF REVERSING SYSTEM FLOW DIVIDER VALVE (PT6A-6A A.
Procedure
(1)
(2)
retaining ring (10) (8).
and
push
packing cover (39) from (23) and washers (24).
Remove
bolts
(3)
(See Figure 3-2-42)
Unlock cover
valve
Remove
preformed packings (38
(5)
Remove
retaining ring (25)
(6)
Remove
and
and
37) from
(26)
remove
valve
retaining ring (31) and 33) from sleeve (36).
remove
sealing
and
remove
into boss of thrust
divider valve.
sleeve
and
Compress spring (35) spring.
(11)
housing assembly (14) by removing
(PWC30267) on sleeve (36) of flow complete with valve and sealing sleeve.
(4)
(7)
oil transfer tube
Install Puller sleeve
(30
ENGINES)
two
withdraw
(36).
from sleeve
sleeve
retaining ring (29).
Carefully
bearing
(36).
(32), preformed packings Remove spacer
(34)
and
Page
3-2-111
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
I
?j, 13
8
10
14)
(12
15~
~32
16 17
18
27
25 39
C647B
(PT6A-6 Engines) Flow Divider Valve Assembly Figure 3-2-42
Page
3-2-112
Nov 26/2004
WHITNEY CANADA
PRATT
IVIAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
3-2-42
1.
Bolt
2.
Reduction Gearbox
3.
Preformed Packing
4.
Reversing
5.
Bolt
6.
Governor
Valve Tube
10.
Actuating Lever Bracket Preformed Packing Thrust Bearing Cover Preformed Packing Retaining Ring
11.
Transfer Tube
12.
Sleeve Strainer
7.
8. 9.
13.
Preformed Packing
14.
Valve
15.
Check Valve
16.
18.
Spring Spring Seat Retaining Ring
19.
Bolt
20.
Washer
21.
Preformed Packings
22.
Transfer Tube
23.
Bolt
24.
Washer
17.
Housing
25.
Retaining Ring
26.
Valve
27.
Retaining Ring Preformed Packing Retaining Ring Preformed Packing
28. 29.
30. 31. 32. 33.
Retaining Ring Sealing Sleeve Preformed Packing
35.
Spacer Spring
36.
Valve Sleeve
37.
Preformed Packing
38.
Preformed Packing
39.
Cover
34.
3-2-113 Nov 26/2004
Page
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(8)
Remove
(9)
Remove two bolts (19) and washers (20) securing flow divider valve housing (14) to reduction gearbox. Remove housing with transfer tube (22) and preformed packings
retaining ring (27)
from valve sleeve
(36).
(21). (10)
Remove valve
102.
retaining ring (18) (15) from housing.
and
remove
spring
(11)
Remove strainer
(12)
Remove transfer tube (11) with preformed (10) from boss in thrust bearing covet: (8).
(12)
seat
from open boss in reduction
(17), spring (16)
and check
gearbox.
packings (13
and
9),
and
retaining ring
INSTALLATION OF REVERSING SYSTEM FLOW DIVIDER VALVE (PT6A-6A A.
Procedure
(1) (2)
(See Figure 3-2-42)
Insert valve Install
ENGINES)
(26)
in valve sleeve
(36)
spring (35) in valve sleeve, retaining ring (29).
and
secure
with
retaining ring (25).
compress with spacer
(34).
Secure
spring
and
spacer with
(3)
Install
retaining ring (27)
(4)
Install
preformed packings (28,
(5)
Install
preformed packings (33
(6)
Install
sealing
(7)
sleeve
on
(32)
valve sleeve.
on
38 and
and
30)
sleeve
37) on
(36)
on
valve sleeve.
sealing
and
sleeve
secure
with
(32). retaining ring (31).
Install to
complete valve assembly in housing (14) and install cover (39). Secure cover housing with two washers (24) and bolts (23). Tighten and torque bolts 32 to
36 Ib.in., and attach lockwire.
(8)
Install check valve (15), spring (16) and spring seat (17) in housing (14). Compress with seat and secure with retaining ring (18). Insert strainer (12), fully bottomed, in boss in reduction gearbox.
spring
(9)
Install
preformed packings (13 and 9), and retaining ring (10) on transfer tube (11). fully bottomed, in boss in thrust bearing cover (8).
Insert tube,
(10)
(11)
Install preformed packings (21) on mounting flange of housing (14). Install
transfer tube
(22).
Insert tube into port in
complete assembly of valve housing on reduction gearbox and secure (20) and bolts (19). Tighten and torque bolts 32 to 36 Ib.in., and
two washers
with attach
lockwire.
(12)
Retract transfer tube (11), (refer to Subparagraph housing and secure in position with retaining ring
(9), preceding) (10).
into
port
in valve
I) Page
3-2-114
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
REMOVAL OF PROPELLER REVERSING REAR LINKAGE (PT6A-6A A.
Procedure
(1)
(See Figure 3-2-43)
Disconnect washer and
(2)
Loosen terminal
self-locking (32).
nut
clamping
on
bolt
Remove FCU interconnect rod (25) by bolts at follower lever (26) and at FCU
(4)
Remove
reversing
(6)
cotterpin,
(33).
Unscrew and
remove rear
wire rope
nuts and
cotterpin, washer and straight pin (27) securing follower lever (26) control lever (29).
(26) from linkage removing splined, grooved pin (36).
Remove
(29) by removing cotterpin,
control lever
removing cotterpins, castellated arm (42).
Remove follower lever
and
104.
clevis (30) from reversing straight pin (28).
rear
(3)
(5)
ENGINES)
reversing
bracket
(38) by loosening
to
lock bolt
(35)
(29) from linkage bracket (38) by removing straight pin (34).
control lever
washer and
INSTALLATION OF PROPELLER REVERSING REAR LINKAGE (PT6A-6A ENGINES) A.
Procedure
(1)
(2)
(See Figure 3-2-43)
Install rear wire rope terminal (32) by screwing onto wire rope until bottomed. Secure clamping bolt (33) by tightening self-locking nut and torquing (Ref. No. 581, Fits Clearances). Locate secure
(3)
(4)
reversing control lever (29) between front holes straight pin (34), washer and cotterpin.
Locate follower lever
between
rear
with
lock bolt
(35). Apply
(26) grooved pin (36) and
Connect follower lever washer and
NOTE:
in
linkage
bracket
(38)
and
with
(26)
to
reversing
holes in
linkage
bracket
(38)
and
secure
lockwire to the bolt.
control lever
(29)
with
straight pin (28),
cotterpin.
If lockwire at rod end connectors of interconnect rod (25) has been to 7-1/8 inches (between rod-end centers).
broken, check and, if necessary, adjust length
(5)
Connect rod (25) to lower hole on follower lever (26) and to FCU arm (42), with two bolts and castellated nuts. Tighten nuts, torque (Ref. No. 585, Fits 8 Clearances) and lock with-cotterpins.
(6)
Adjust length of rod (25) so that lever (26) Tighten locknuts, check rod-end for safety,
and and
arm
(42)
secure
are
approximately parallel.
with lockwire.
I) Page
3-2-115
Nov 26/2004
WHITNEY CANADA
PRATT
AIIAINTENANCE MANUAL MANUAL PART NO. 3015442
26
27
28
29
30
31
33
32
1234
24 25 34
37 2 38 42
41 7
\\\\8 9
11
15
21 16
20
19
14
13
10
1P
40
18
(Pf6A-6 Engines)
C596
Engine Controls and Reversing System Figure 3-2-43 Page 3-2-116 Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
3-2-43 22.
Swivel Joint
23.
Bracket
24.
Rod Ends
25.
FCU Interconnect Rod
26.
Follower Lever
Adjustment
27.
-Pin
28.
Straight Pin Straight Pin Reversing Control
1.
Rod Ends
2.
Maximum
3.
Nf Govemor Arm
4.
Maximum RPM
5.
Reverse Thrust
6. 7.
Carbon Block Pin
8.
Nf Govemor
9.
Pin
Stop Adjustment Speed
Actuating
29.
Lever
Valve
30.
Rear Clevis
31.
Jam Nut
32.
Wire
Lever
12.
Reversing Reversing Reversing
34.
Rope Terminal Clamping Bolt Straight Pin
13.
Bowelled Bolt
35.
Lock Bolt
14.
Clamping
36.
Splined Grooved
15.
Front Clevis
37.
Bracket
16.
38.
17.
Adjustable Stop Turnbuckle Assembly
18.
Locknut
40.
19.
Adjuster
41.
Linkage Bracket Maximum FCU Stop Part Power Stop Maximum Reverse Stop
20.
Internal
42.
FCU Arm
21.
Lock Bolt
10. 11.
Valve
Housing
Valve Lever
Bolt
Spring
33.
39.
Pin
Page
3-2-117
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(7)
rear clevis (30) at center hole on reversing control lever (29), and secure straight pin (28), washer and cotterpin. Ensure that lever (29) is approximately parallel to follower lever (26), and that pin (27) is in neutral position in cam slot in lever (29).
Connect with
(8)
Ensure that FCU
arm
slot in lever
(29).
cam
105.
(42)
makes contact with stops before
pin (27) reaches end of
REMOVAL OF PROPELLER REVERSING FRONT LINKAGE (PT6A-6A ENGINES) A.
Procedure
(1)
(2)
(See Figure 3-2-43)
Disconnect front clevis (15) from reversing valve lever (12) nut sleeve bushing, sleeve spacer and dowelled bolt (13). Remove turnbuckle
by removing
lever
guide,
assembly (17) by removing cotterpin, castellated nut, flanged arm (3), and cotterpin, castellated nut, two
washer and bolt at Nf governor washers and bolt at actuating lever (8).
sleeve,
(3)
Remove actuating lever (8) by removing cotterpin, washer and straight pin (6).
(4)
Remove reversing valve lever washer and straight pin (9).
(5)
Remove valve housing (11) complete with valve
removing
(6) (7)
(12)
from
reversing
valve
(10)
(10) by removing cotterpin,
from thrust
bearing
cover
by
two bolts.
Remove valve from housing by removing retaining ring. Remove one
one
packing
preformed packing from housing.
valve. Remove two
preformed packings and
retainer from
(8)
Disconnect rear clevis (30) from reversing control lever (29) washer and straight pin (28).
(9)
Loosen self-locking nut terminal (32).
on
clamping
bolt
(33).
Unscrew and
by removing cotterpin,
remove rear
wire rope
(10)
Disconnect wire rope front
(11)
Remove locknut and washer securing front swivel joint (22) to mounting bracket (23). Remove swivel joint complete with push-pull control linkage and wire rope. Exercise care to prevent damage to wire rope when extracting from casing.
(12)
Loosen self-locking nut from wire rope.
(13)
Remove lock bolt (21), and unscrew front swivel internal compression spring.
(14)
Remove front clevis (15) by sliding it rearward through adjustable stop (16).
(15)
Loosen locknut (18) and
on
casing
from front swivel
clamping
remove
bolt
(14),
and
adjustable stop
joint (22).
unscrew
joint
from
from
complete assembly
assembly.
Remove
adjuster (19).
Page
3-2-118
Nov 26/2004
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WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
106.
(16)
Disconnect
(17)
Remove locknut and washer and
(18)
Disconnect and
(19)
Remove
(20)
Disconnect and
(21)
Remove
rear
wire rope
casing
remove rear
self-locking
coupling
joint
renlove rear
wire rope
nut and bolt
remove
from swivel
from center fireseal
rear
fireseal.
joint from fireseal.
swivel
casing from coupling
securing clamp
front wire rope
at
casing
by removing
center fireseal.
front wire rope
on
from
on
coupling
on
casing
Procedure
(1)
locknut and two washers.
Install bulkhead
Clearances) Install
rear
coupling
on
center
swivel
joint
on rear
Install front swivel
(5)
one
fireseal and
secure
Clearances)
washer
on
each side of
torque (Ref. No. 586, Fits 8
with washer and locknut.
and
secure
Tighten
with lockwire.
joint (22) on mounting bracket (23) and secure torque (Ref. No. 583, Fits 8 Clearances)
locknut. Tighten locknut, lockwire.
(4)
fireseal, with
with locknut, r~ghten locknut, and secure with lockwire. secure
locknut, torque (Ref. No. 583, Fits
(3)
ENGINES)
(See Figure 3-2-43)
fireseal, and
(2)
flange
center fireseal.
INSTALLATION OF PROPELLER REVERSING FRONT LIN~AGE (PT6A-6A A.
to
with washer and
and
secure
with
Install rear wire rope casing, by connecting to swivel joint at rear fireseal and to coupling at center fireseal. Tighten casing coupling nuts, torque (Ref. No. 582, Fits 8 Clearances) and secure with lockwire. Install front wire rope
casing, by connecting to coupling at center fireseal and to joint on mounting bracket. Tighten casing coupling nuts, torque (Ref. No. 582, Fits 8 Clearances) and secure with lockwire.
front swivel
(6)
Screw
adjustable stop (16) into adjuster (19) followed by locknut (18). Finger-tighten leaving approximately six threads showing on adjustable stop.
locknut
(7)
Insert front clevis
(15) into stop followed by compression spring. Screw assembly joint (22), until holes in swivel joint and adjuster are aligned. Secure with lock bolt (21). Tighten bolt, torque (Ref. No. 585, Fits 8( Clearances) and secure onto swivel
with lockwire.
(8)
Ensure that wire rope is clean and free of foreign matter, and insert through casings from rear swivel joint. Screw wire rope counterclockwise through clamping bolt (14) in front swivel joint until fully bottomed. Tighten self-locking nut on clamping bolt and torque (Ref. No. 581, Fits 8 Clearances).
(9)
Install clamping bolt (33) on wire rope terminal (32). Screw assembly, clockwise, on end of wire rope until bottomed. Tighten self-locking nut on clamping bolt and torque (Ref. No. 581, Fits Clearances). rear
Page
3-2-119
Nov 26/2004
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(10)
Install
(11)
Install two preformed secure with retaining
(12)
Install bolts.
(13)
(14)
packings ring.
and on
retainer
packing valve
on
housing (11).
assembly of reversing valve on thrust bearing Tighten bolts and torque 36 to 40 Ib.in. (12) by securing
to
actuating lever (8) by securing straight pin (6), washer and cotterpin.
Secure short
arm
of
reversing
cover
and
housing
secure
valve with
to bracket
(10).
valve
Install valve in
reversing
Install Nf governor
(15) (16)
preformed packing
Install reversing valve lever washer and cotterpin.
with
(15)
one
on
and
with two
straight pin (9),
thrust
bearing
cover
actuating lever (8) and reversing valve lever (12) to front clevis (13) spacer, bushing, plain nut and lever guide.
with dowelled bolt
Tighten nut, torque NOTE:
32 to 36 Ib.in. and
secure
If lockwire at rod end connectors
(1)
with lockwire.
of turnbuckle assembly (17) has been to 3-318 inches and
broken, check and, if necessary, adjust length lockwire. Check rod ends for
(17)
Install turnbuckle
(a)
Connect
ton
one
assembly (17)
follows:
long arm of actuating lever (8) end), and castellated nut.
rod end to
each side of rod
(b) Connect
as
safety.
other rod end to governor
arm
(3)
with bolt, two washers
with bolt, washer,
flanged
sleeve
and castellated nut.
NOTE:
(c) Tighten (18)
107.
Assemble washer
on
side of rod end
opposite
to sleeve
both castellated nuts 24 to 36 Ib.in., and lock with
flange.
cotterpins.
Adjust stop (16) in adjuster (19) to obtain specified clearance (Ref. No. 86, Fits Clearances) between reversing valve (10) and reversing valve housing (11). Tighten locknut (18), torque (Ref. No. 584, Fits Clearances) and secure with lockwire.
REMOVAL OF PROPELLER REVERSING REAR LINKAGE (PT6A-6B, -6/C20, -20, -20A AND -20B ENGINES) A.
Procedure
(1~
(See Figures
Discdnnect airframe remove
(2) (3)
3-2-44 and
linkage
3-2-45)
from power
input
lever
(39, Figure 3-2-44),
and
lever.
Remove FCU control rod (6, Figure 3-2-45) from actuating lever (2) and FCU control arm (9) by removing two cotterpins, castellated nuts, washers and bolts. rear clevis rod end (3) from washer and straight pin.
Disconnect
cotterpin,
propeller
control
cam
(1) by removing
Page
3-2-120
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(4)
Loosen
self-locking nut on clamp bolt (4, Figure 3-2-44), by unscrewing from wire rope.
and
remove rear
wire
rope terminal
(5)
Remove mounting bracket (8, Figure 3-2-45), complete with flange G, by removing two self-locking nuts and one bolt.
(6)
Disassemble
(a)
rear
from
mounting
bracket
Remove extension
removing
two
spring (5) from actuating cotterpins and washers.
as
lever
(2)
Remove two cotterpins, washers, straight headed pin (16), and remove control cam (1) and actuating lever bracket (8).
(c)
Loosen lock bolt
(15),
and
on cam
actuating
linkage
from
follows:
(b)
lever 108.
linkage
rear
and
mounting
bracket
by
(17), cam follower pin (2) from mounting
follower lever (15). Remove grooved lever (13) from mounting bracket (8).
pin (7), follower
INSTALLATION OF PROPELLER REVERSING REAR LINKAGE (PT6A-6B, -6/C20, -20, -20A AND -208 ENGINES) A.
Procedure
(1)
(See Figures
3-2-45)
(2, Figure 3-2-45) and propeller control cam (1) to (8), and insert straight headed pin (17) through front lever (2), and secure pin with washer and cotterpin.
Assemble FCU actuating lever control lever mounting bracket holes of bracket,
(2)
3-2-44 and
cam
(1),
and
Assemble
actuating lever (13) and cam follower lever (15) to control lever mounting (8). Install grooved pin (7) through rear holes of bracket (8) and levers (13 and 15). T~ghten bolt on cam follower lever (15) and torque 32 to 36 Ib.in., securing with lockwire. bracket
(3)
Install fork end of cam follower lever (15) over propeller control cam cam follower pin (16) through holes in fork end of lever and through
propeller
(4)
(5)
cam.
Temporarily
Secure with washer and
and insert cam slot in
cotterpin.
secure angle bracket (12) to control lever bolt. Do not torque bolt at this stage.
mounting
bracket
(8)
with
mounting bracket assembly at flange G of accessory gearbox gearbox studs with two self-locking nuts. Tighten nuts and torque 36 to 40 Ib.in. Secure angle bracket (12) to accessory gearbox boss with two bolts. Tighten three angle bracket bolts 36 to 40 Ib.in., and secure with lockwire. Locate control lever
and
(6)
control
(1)
secure
to
spring (5) between post on control lever mounting bracket (8) actuating lever (2), and secure with washers and cotterpins.
Install extension
post
on
FCU
Page
and
3-2-121
Nov 26/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
~15
TO COCKPIT POWER CONTROL LEVER
(13~ ~i4
10
a
9 8 1
4 )118
i´•
(i
L~
C
8
34)\
51
5~’
j,~tq
35
50
7
1
48
25 18
23) 40
i
TO
COCKPIT~
33
PROPELLER
41
22
32
~;CONTROLLEVER
43
I
j
(19
20
21
FIRESEALCENTER
REAR FIRESEAL
42
46)(45)(44
1)(2
53
1"
15 REVERSE POSITION
TAKE-OFF POSITION IDLE POSITION DETAIL
A
DIM. ’Z’ 27
7 10 28
DETAIL
.’d
B
29
30
26
DETAIL
10
9
D
DIM. ’X’
31
(0.0101NCH)
DETAIL C 903’2-361185
DETAIL
(PT6A-6B Engine
and -20
Controls and
Figure
E
C1968A
Engines)
Reversing System
3-2-44
Page
3-2-122
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key 1.
Propeller
Control Cam
to
Figure 3-2-44 Adjuster Stop
28.
Low Pitch Locknut
33.
Spring Retaining Plate Wire Rope Wire Rope Casing
2.
Clevis Rod End
29.
3.
Locknut
30.
4.
Clamp
5.
32.
6.
Adjusting Bolt (NON-STOL APPLICATION) FCU Actuating Lever
34.
Locknut
7.
Front Swivel Joint
35.
Rear Swivel Joint
8.
Locknut
36.
Extension
9.
37.
Cam Follower Pin
38.
Grooved Pin
39. 40.
Input Lever (Airframe Supplied) Actuating Lever
41.
FCU Control Rod
15.
Spring Stop (Dimension X) Front Lifting Bracket Propeller Govemor Propeller Governor Arm Propeller Speed Adjusting Lever propeller Govemor Stop Actuating Lever Support Arm
42.
Ng Maximum Stop
16.
Governor Interconnect Rod
43,
FCU Arm Extension
17.
Clevis Rod End
44.
FCU Control Arm
18.
Propeller Reversing
45.
Cut-off Valve Lever
19.
Governor Maximum Stop
46.
Fuel Control Unit
20.
Governor Arm
47.
Hi-idle
21.
Governor Interconnect Rod
48.
(Lower)
49.
Stop Cut-off Stop Serrated Spacer
22.
Governor Lever
50.
Governor Air Pressure Line
23.
Govemor Air Pressure Line
51.
Cam Follower Lever
24.
Propeller Propeller
52.
Propeller Constant Speed Unit Stop
53.
Track Point
10. 11. 12. 13. 14.
25.
31.
Bolt
Idle Deadband
Feedback Governor
Lever
(Py) Ring Actuating
Lever 26.
Low Pitch
27.
Lockbolt
Spring
Power
(FCU)
(Py)
Control
Stop Adjuster
Page
3-2-123
Nov 26/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1
15
O O
o
ib 16
17
7
13
@I
r
5
I 12
8-
a
I
o
9
a o
7
10
(PT6A-6B, -20,
-20A and -208
C1969
Engines)
Engine Rear Linkage Figure 3-2-45
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Ke~ to 1.
2. 3. 4.
5. 6.
7. 8. 9. 10. 11.
12. 13. 14.
15.
16. 17. 109.
Figure
3-2-45
Propeller Control Cam Fuel ControlActuating Lever (6, Figure 3-2-44) Clevis Rod End (2, Figure 3-2-44) Locknut (3, Figure 3-2-44) Extension Spring (36, Figure 3-2-44) FCU Control Rod (41, Figure 3-2-44) Grooved Pin (38, Figure 3-2-44) Mounting Bracket FCU Control Arm (44, Figure 3-2-44) FCU Arm Extension (43, Figure 3-2-44) Serrated Spacer (49, Figure 3-2-44) Angle Bracket Actuating Lever (40, Figure 3-2-44) Idle Deadband Adjusting Bolt (NON-STOL APPLICATION) (5, Figure) Cam Follower Lever, (51, Figure 3-2-44) Cam Follower Pin (37, Figure 3-2-44) Straight Headed Pin
ADJUSTMENT OF PROPELLER REVERSING REAR LINKAGE
(PT6A-6B, -6/C20, -20, -20A
AND -20B ENGINES) A.
Procedure NOTE:
the rear linkage will vary considerably with various airframe installations and types of propeller control cam (STOL, NON-STOL, etc.) being used. The following adjustment procedure may be used as a general guide. For final adjustment trigging) of propeller reversing linkage in airframe, reference must be made to applicable airframe manufacturer’s manual. Adjust the propeller reversing rear linkage as follows: (See Figures 3-2-44 and
Adjustment trigging) of
3-2-45). (1)
Rotate FCU arm (44, Figure 3-2-44) fully counterclockwise. Holding the cut-off valve lever (45) against the cut-off stop (48) slowly rotate the FCU arm (44) clockwise until governor cam pick-up point is reached. NOTE:
Initial movement of the FCU
am7
(2)
fully counterclockwise position point will be recognized when a
from the
will be free of resistance. The pick-up small resistant force is encountered.
Slacken FCU arm extension (43) and adjust serrated spacer (49) until FCU arm (44) is approximately 16 degrees below horizontal as the pick-up point is reached. Clearances) and Tighten FCU arm extension (43), torque (Ref. No. 598, Fits secure
with lockwire.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(3)
adjust idle deadband adjusting bolt (5) in actuating lever (40) to suit airframe installation and propeller control cam (Refer to airframe manufacturer’s manual). Install and
specific (4)
Rotate power input lever (39) until cam follower pin (37) rests in track propeller control cam (1), (See IDLE POSITION, Figure 3-2-44).
(5)
With FCU
(6)
Rotate power input lever (39), if fitted, or grooved pin (38), fully clockwise, then fully counterclockwise, confirm that stop is contacted in both positions. Adjust length of
arm (44) set approximately two degrees counterclockwise from pick-up point and rear linkage in idle position and cam follower pin in track point, adjust length of FCU control rod (41) until holes in rod end connectors align with top hole of FCU actuating lever (6) and inner hole of FCU control arm (44). Tighten rod end connector locknuts and install FCU control rod (41). Temporarily secure with bolts, washers and castellated nuts.
FCU control rod
(7)
point (53) of
Tighten
locknuts
(41) on
as
necessary. Remove FCU control rod.
control rod, torque nuts 32 to 36 Ib.in., and
secure
with
lockwire.
(8)
110.
Apply light film of grease (PWC04-001) to ball end fittings on control rod. Install control rod and secure with bolts, washers and castellated nuts. Tighten nuts, Clearances) and lock with cotterpins. torque (Ref. No. 585, Fits
REMOVAL OF PROPELLER REVERSING FRONT LINKAGE (PT6A-6B, -6/C20 AND
)SENIGNE02-
A.
Procedure
(1)
(See Figure 3-2-44)
Disconnect
cotterpin, (2)
rear
(2) straight pin.
clevis rod end
washer and
from
propeller
control
cam
(1) by removing
self-locking nut on clamp bolt (4) and remove wire rope terminal by unscrewing from wire rope. Remove locknut (34) and washers, and unscrew joint (35) from wire rope casing nut. Loosen
swivel
(3)
Remove cotterpin, castellated nut, three washers and bolt securing power turbine govemor interconnect rod (16) to governor lever (22). Remove cotterpin, castellated nut and two washers securing interconnect rod to propeller reversing lever (18).
(4)
Disconnect clevis rod end (17) from reversing lever castellated nut, spacer and shouldered stud.
(5)
Disconnect front wire rope
(6)
On Pre-SB1185 engines, remove locknut (8) securing front swivel joint (7) to lifting bracket (10). Remove push-pull control linkage complete with wire rope, exercising care not to damage wire rope.
casing
(18) by removing cotterpin,
nut from front swivel
joint (7).
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(7)
On Post-SB1185 engines, remove innermost nut and bolt, and loosen remaining nut and bolt securing remaining plate (31), to lifting bracket. Loosen locknut (8) and
pivot retaining plate outward. Remove push-pull rope, exercising care not to damage wire rope. (8)
Remove bolts and as
(9)
self-locking nuts, securing
wire rope
linkage complete
with wire
casing
flange C,
bracket to
required.
Disconnect rear wire rope and remove casing.
casing
nut from bulkhead
(10)
Remove locknut and washers
(11)
Remove self-locking nut and washer from clamp assembly from wire rope. Remove clamp bolt.
(12)
Disassemble
(a)
control
push-pull
Remove lock bolt
securing
control
(27)
linkage
and
bulkhead
as
remove
coupling,
coupling bolt
(4)
on
center
fireseal,
to center fireseal.
and
unscrew
control
linkage
follows:
front swivel
joint (7) and spring (30) from
assembly. (b)
Loosen locknut and remove clevis rod end Remove wire rope terminal from assembly.
(c)
Remove locknut
(29)
and
remove
(17)
from front wire rope terminal.
adjuster stop (28)
from
low-pitch stop
adjuster (26). (13)
propeller reversing lever (18) from governor actuating lever (25) by removing cotterpin, castellated nut and bolt. Ensure that sleeve bushings on either side of reversing lever arm remain firmly in place.
(14)
Remove
Remove
removing fitted) (15) (16)
actuating lever (25) from governor arm (12) and’ support arm (15) by two cotterpins, castellated nuts and bolts, and governor arm shield (if
Remove
arms
Remove
spring stop (9),
(12
and
15) by removing if fitted, from
two
lifting
self-locking bracket
nuts and washers.
by removing
one
self-locking
nut, two bolts and washers.
(17)
Disconnect and remove interconnect rod (21) by removing cotterpin, castellated nut, washer and bolt and power turbine governor arm (20). Remove cotterpin, castellated nut, three washers and bolt at power turbine governor lever
(18)
Remove two self-locking nuts and lever (22), from flange A.
remove
(22).
support bracket, complete with govemor
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
111.
INSTALLATION OF PROPELLER REVERSING FRONT LINKAGE (PT6A-6B, -6C/20 AND -20
A.
ENGINES)
(See Figure 3-2-44)
Procedure
NOTE:
To obtain freedom of movement, lubricate all rod end connectors with grease
(PWC04-001). (1)
On Pre-SB1185
A, and
flange Clearances) (2)
on
engines, locate front swivel joint (7) in slot of lifting bracket, and retaining plate (31), bolt and self-locking nut. Tighten both nuts and 36 40 Ib.in. Install locknut (8) on swivel joint, tighten nut and torque (Ref. to torque No. 583, Fits 8 Clearances). with
Install
swivel joint (35) on rear fireseal and secure with two plain washers (34). Tighten nut and torque (Ref. No. 583, Fits 8 Clearances).
rear
locknut
(4)
secure
joint (7) in engine lifting bracket (10) (8). Tighten nut and torque (Ref. No. 583, Fits
insert front swivel
with locknut
On Post-SB1185 secure
(3)
engines,
and
Install bulkhead coupling and washer on center fireseal, inserting from rear, and secure with washers and locknut. Tighten nut, and torque (Ref. No. 586, Fits 8
Clearances) NOTE:
Two additional washers may be installed if necessary to compensate for discrepancy in length of wire rope casing.
(5)
Install front and rear section of wire rope casing. Tighten coupling nuts, torque (Ref. No. 582, Fits Clearances) and attach lockwire to adjacent locknuts. Secure front section of wire rope casing and bracket to flange C las applicable) with bolts and self-locking nuts. Tighten and torque nuts 36 to 40 Ib.in.
(6)
Assemble locknut
(7)
Insert front
(29) on adjuster stop (28) and screw assembly leaving approximately eight to twelve threads showing. (30).
adjuster (26)
push-pull control terminal from rear, into adjuster, followed by spring assembly over front of swivel joint and secure with lockbolt (27) on Tighten bolt, torque (Ref. No. 585, Fits Clearances) and secure with lockwire.
Slide
collar.
(8)
into
Install clevis rod end (17), complete with locknut, on push-pull control terminal. Ensure that threads are visible through inspection hole on clevis rod end. Check that travel of adjuster is approximately 1-114 inches.
NOTE:
Early engines may not incorporate inspection hole in rod end clevis; in this condition ensure that minimum of 3 threads are showing beyond locknut. Clevis must be drilled at next shop visit (Ref. Airworthiness Directive
CF-80-21). (9)
Suitably (52).
hold
propeller governor speed adjusting
lever
against maximum speed stop
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(10)
Insert feeler gage under pilot valve lifting rod on propeller governor, and hold dimension "Z" (see Detail B) at its low setting of 0.085 (~0.001) inch. Install arm (12) so that fork end is at 6 o’clock position or slightly forward.
NOTE:
(11)
When
installing the arm (12), the pilot valve lifting against upper flange of governor spool rod.
lever must be held
Move the arm (12) forward sufficiently to insert feeler gage beneath spool to set dimension "Z" at 0.210 inch. Screw in pilot valve maximum stop (14) on governor bracket to arm. Tighten nut on stop screw, and torque (Ref. no. 599, Fits
Clearances). CAUTION:
DO NOT FORCE THE ARM (12) TO GIVE A DIMENSION GREATER THAN 0.230 INCH OR DAMAGE TO THE GOVERNOR WILL RESULT.
(12)
Connect top end of actuating lever support arm (15) to forward hinge bolt on propeller governor bracket. Connect lower fork end of arm (15) and arm (12), to propeller actuating lever (25).
(13)
Assemble
(a)
propeller reversing lever (18)
For Pre-SB1067
reversing (b)
engines,
lever and
For Post-SB1067
reversing
as
follows:
insert
secure
spherical bearing into bore in propeller bearing in place with retaining ring.
engines, insert one retaining ring into bore in propeller spherical bearing and secure with second retaining ring.
lever. Install
(14)
Connect lever
(15)
While
(16)
Loosely
(17)
Assemble and install the upper power turbine governor interconnect rod (16) between levers (22 and 18). Adjust rod so that lower half of lever (15) is
(18)
to lever
(25) with spacer inserted
on
each side.
holding dimension "Z" to 0.085 inch, adjust clevis rod end (17) adjuster (28) in order to connect lever (1 8) ~to clevis rod end (17). install power turbine governor lever
approximately parallel
to
flange
(22)
and bracket
on
and/or
flange
A.
A.
(18)
Install power turbine governor arm (20) so that, with contact made to the power turbine governor maximum stop (19) i.e., fully clockwise, the arm points directly inward at right angles to engine axis.
(19)
Hold clevis rod end (17) fully forward, and install the lower power turbine governor interconnect rod (21) by adjusting its length until arm (20) is lightly touching stop (19). Shorten rod (21) by one complete tum on one end before installing rod.
(20)
Tighten all nuts on front linkage and controls, torque (Ref. No. 599, Fits Clearances) and lock with cotterpins. Recheck dimension "Z" with front terminal held fully forward.
control
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
(21)
112.
DO NOT TORQUE RETAINING NUTS THAT ATTACH ARMS (12 AND 15) TO PROPELLER CONSTANT SPEED CONTROL UNIT ABOVE SPECIFIED LIMITS.
Tighten power turbine governor lever mounting bracket hold down and torque 36 to 40 Ib.in. Ensure all rod ends are free to swivel.
nuts at
flange
A
SPRING STOP (OPTIONAL) (PT6A-6B AND -20 ENGINES) A.
Procedure
(See Figure 3-2-44)
(1)
stop shield
Install
Clearances) (2)
(4)
on arm
secure
(12). Tighten cotterpin.
bolt and nut,
torque (Ref. No. 599, Fits
with
Assemble
propeller reversing lever spring stop by inserting two springs into cylinder. Compress springs with piston and insert spiral retaining ring into groove provided in cylinder. Install adjuster screw into piston leaving approximately 318 inch threads showing. NOTE:
(3)
and
Use lubricant
(PWC06-036)
on
the
piston during assembly.
Install spring stop assembly in hole provided in lifting bracket at flange A, inserting from front. Secure with three bolts, plain washers and self-locking nuts. Tighten nuts and torque to 36 to 40 Ib.in.
Using feeler gage, control dimension "X" (between adjuster arm) to 0.010 inch, secure adjuster screw with cotterpin.
screw
and stop shield
on
NOTE:
113.
The adjuster screw may be turned clockwise up to 112 turn to facilitate installation of cotterpin.
INSTALLATION OF PROPELLER REVERSING INTERCONNECT FRONT AND REAR LINKAGE (PT6A-6B AND -20 ENGINES1 A.
Procedure
(1)
Secure bracket with on
(2)
(See Figure 3-2-44)
flange C, tighten
Install
self-locking nut and
nut and
torque 36
bolt,
at
approximately
the 3 o’clock
position
to 40 Ib.in.
clamp over front wire rope casing and secure Tighten nut and torque to 32 to 36 Ib.in.
to bracket on
flange
C with nut
and bolt.
(3)
clamp over front wire rope casing and another clamp over power turbine govemor pneumatic line front section. Secure two clamps together with bolt and nut, tighten nut and torque to 32 to 36 Ib.in.
(4)
Insert wire rope into rear swivel joint (35), through rear and front casings, into front adjuster assembly. Secure counterclockwise through clamping bolt (4) until wire
Install
rope end contacts bottom of blind hole in front terminal. NOTE:
As
casing
sections
are
internally lined,
no
lubrication is
required
on
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wire
3-2-130
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(5)
(6)
Check for safety of wire rope, by inserting a piece of wire into small hole in front terminal. Secure wire rope front end by tightening self-locking nut on clamping bolt (4), and torque (Ref. No. 599, Fits Clearances). Install
rear
threaded
(7)
(8)
terminal
clamping
on
bolt
wire rope,
allowing
wire rope to pass
through internally
(4).
Check for safety of wire rope, by inserting a piece of wire into small hole in terminal. Secure wire rope rear end by tightening self-locking nut on clamping bolt and torque (Ref. No. 581, Fits Clearances). Screw locknut to
align
(4),
and clevis rod end (2) on the rear push-pull terminal and adjust on the control cam (1). Extend clevis rod end by one half positive movement of control. Tighten locknut and torque 75 to
(3)
with middle hole
turn to ensure
85 Ib.in.
(9)
Insert
straight pin through
washer and
(10)
114.
clevis rod end
(2)
and control
cam
(1),
and
secure
with
cotterpin.
On
completion of all adjustments, carry out a thorough check of engine control and reversing system for correct torque loading of coupling and linkage nuts, and for securing with lockwire or cotterpins, as applicable.
REMOVAL OF PROPELLER REVERSING FRONT LINKAGE (PT6A-20A AND -208
ENGINES) A.
Procedure
(See Figure 3-2-46)
(1)
Disconnect
(2)
Loosen
(3)
rear clevis rod end (2) from propeller control cotterpin, washer and straight pin.
self-locking nut on clamping unscrewing from wire rope. Loosen and swivel
unscrew
coupling
nut
bolt
(7)
(4)
and
cam
remove rear
(1), by removing wire rope terminal,
at front end of wire rope
casing from
by
the
joint (19).
(4)
Remove
(5)
Remove cotterpin, washer and straight headed lever (29) to Beta control valve clevis (30).
(6)
Remove control lever and sleeve
(7)
Remove cotterpin, castellated nut, washer and bolt securing propeller governor interconnect rod (14) to propeller governor air bleed link.(31).
(8)
Remove cotterpin, castellated nut (25) and washer securing upper end of interconnect rod (14) to outer end of wire rope clamp bolt (27).
(9)
Remove interconnect rod
cotterpin, nut, spacer, propeller reversing lever (29).
sleeve and bolt
securing
clevis rod end
(12)
to
pin securing propeller reversing
bushing.
(14).
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
REAR FIRESEAL
6
58)
51
(2)
1
7
~Bs’k;
(35
26
1
DETAIL 17
A
POST-SB1185
48
~s 47’
(4Q 18 35
38T
40 37 42
TO COCKPIT POWER CONTROL LEVER
39
4443 46
45
12
TO COCKPIT PROPELLER CONTROL LEVER
1
s
ic
9
I
LOW PITCH 8 REVERSE
C
C
i
HIGH PITCH 8 FEATHER
PROPELLER FEEDBACK RING 13 14
(PT6A-20A
and -208
Engines)
C1967C_1
Engine Controls and Reversing System Figure 3-2-46 (Sheet 1 of 3)
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PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
CAM TRACK POINT 6
3~
90"+1"
(4
~5 REVERSE POSITION
TAKE-OFF POSITION
IDLE POSITION
DETAIL
B
~j"
25
20)
(22
28)
MAX. STOP
19
127
15 LOCK BOLT
29
25
21)! 21
14
30 r
!2~ GOVERNOIRAIR
CARBON BLOCK
BLEED LINK
(REF.)
14
MAX. STOP
54 28
19
15
29
DETAIL 30
31
DETAIL
C
jl;
C
PT6A-20A PUSH-PULL CONTROL ROD ARRANGEMENT (SOLID LINK)
CARBON BLOCK
(666.)
PT6A-20B PUSH-PULL CONTROL ROD ARRANGEMENT (TELESCOPIC LINK)
(PT6A-20A
and -20B
Engines)
c1967C_2
Engine Controls and Reversing System Figure 3-2-46 (Sheet 2)
Page 3-2-133 Nov 26/2004
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
PROPELLER GOVERNOR
’Aa\
BETAVALVE7
PROPELLER REVERSING LEVER
REVERSING LEVER GUIDE PIN BRACKET ASSEMBLY SEE DETAIL E FOR CORRECT INSTALLATION.
29
PROPELLER REVERSING LEVER MUST BE POSITIONED BEMIEEN GUIDE PIN AND PROPELLER SHAFT
THRUST BEARING COVER
cg DETAIL
’9
E
rg se
PT6A-20A and -208
Engine
Controls and
Figure
C80839
Engines
Reversing System (Sheet 3)
3-2-46
Page
3-2-134
Nov 26/2004
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key Control Cam
to
Figure
3-2-46
Lever
1.
Propeller
29.
Propeller Reversing
2.
Clevis Rod End
30.
Bata Valve Clevis
3.
Locknut
31.
Govemor Air Bleed Link
4.
Clamp
32.
Wire
5.
33.
Wire
34.
Locknut
35.
Rear Swivel Joint
7.
Adjusting Bolt (NON-STOL APPLICATION) Fuel Control Actuating Lever Coupling Nut
36.
Extension
8.
Locknut
37.
Cam Follower Pin
9.
Front
38.
Grooved Pin
39.
40.
Power Input Lever (Airframe Supplied) Actuating Lever
41.
FCU Control Rod
42.
Ng
Rod
43.
FCU Arm Extension
Lock Bolt
44.
FCU Control Arm
45.
Cut-off Valve Lever
46.
Fuel Control Unit
47.
6.
Bolt
Idle Deadband
11.
Lifting Bracket Propeller Govemor Propeller Speed Adjusting
12.
Clevis Rod End
13.
Propeller Propeller
10.
14. 15. 16.
Feedback
Lever
Ring
Governor Interconnect
~Bracket
Rope Rope Casing
Spring
Maximum
Stop
17.
Insulation Gasket
18.
Self-locking
19.
Front Swivel Joint
48.
20.
Locknut
49.
Stop Stop Serrated Spacer
21.
Low Pitch
50.
Govemor Air Pressure Line
22.
Spring
51.
Cam Follower Lever
23.
Locknut
52.
24.
Low Pitch
Telescopic Terminal Housing Compression Spring
25.
Castellated Nut
54.
Bolt
26.
Retaining Plate Clamp Bolt Self-locking Nut-
55.
Guide Pin Bracket
56.
Self-locking
27.
28.
Nut
Stop Adjuster
Adjuster Stop
53.
(FCU)
Hi-idle
Cut-off
(Py)
Assembly
Nut
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
(10)
Pre-SB1185: Remove locknut (20) securing front swivel joint (19) to lifting bracket (8) on flange A. Withdraw front swivel joint complete with push-pull control rod assembly and attached wire rope.
(11)
Post-SB1185: Remove innermost nut and bolt, and loosen remaining nut securing retaining plate (26) to lifting bracket (8). Loosen locknut (20) and pivot retaining plate outward. Remove front swivel joint (19) complete with push-pull control rod assembly and attached wire rope.
(12)
Remove
self-locking nut flange C.
and bolt
securing
wire rope
casing clamp
to bracket
attached at
casing (33)
(13)
Remove self-locking nut (18), washer and bolt bracket (16) attached to center fireseal.
(14)
Remove two self-locking nuts (18) and bolts securing retaining plates, seals, insulation gaskets (17) and angle bracket (16) to center fireseal. Split retaining plates and seals to enable wire rope casing (33) to be withdrawn through fireseal.
(15)
Loosen and remove wire rope casing coupling nut (7) from front end of rear swivel joint (35). Carefully remove clamp, seals, insulation gaskets and angle bracket from casing. Withdraw casing forward through center fireseal.
(16)
Remove
(34)
(17)
rear
located
swivel joint (35) from rear fireseal forward face of rear fireseal.
wire rope
by removing
swivel
joint
to
locknut
on
Disassemble
(a)
securing
push-pull
control rod
assembly
removed at
Step (10) or(ll)
Remove self-locking nut (28), and spacer from wire rope release tension on wire rope.
as
follows:
clamping bolt (27)
to
wire rope (32) from front linkage assembly by unscrewing wire rope in counterclockwise direction to disengage rope from clamping bolt (27) internal
(b) Remove a
threads. Withdraw wire rope.
(c)
PT6A-20A: Remove clamp bolt (27) from wire rope terminal and front clevis rod (12). Withdraw clevis rod from wire rope terminal.
(d)
PT6A-20B: Remove bolt
(54) securing front clevis (12) and withdraw clevis. bolt (27) from telescopic terminal housing (52), spring sleeve and wire rope terminal. Remove telescopic terminal housing (52) spring sleeve and compression spring (53) from wire rope terminal. Remove
clamp
(e)
Remove locknut
(f)
Unscrew low remove,
(g)
(23)
from low
pitch adjuster stop (24).
pitch adjuster stop (24) from low pitch stop adjuster (21) complete with wire rope terminal and spring.
and
(15) from low pitch stop adjuster (21) and front swivel joint (19). Slide low pitch stop adjuster from swivel joint flange. Remove lock bolt
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
115.
INSTALLATION OF PROPELLER REVERSING FRONT LINKAGE (PT6A-20A AND -20B
ENGINES) A.
Procedure NOTE:
(See Figure 3-2-46)
If rod end connectors have been or or
(1)
(2)
binding, turn equivalent.
washed,
or
if there is any evidence of
ball outward and lubricate surface
using
grease
sticking (PWC04-001)
Pre-SB1185: Insert front swivel joint (19) in forward engine lifting bracket (8) at flange A and secure with locknut (20). Tighten nut, torque (Ref. No. 960, Fits Clearances) and secure with lockwire.
Post-SB1185: Locate front swivel joint (19) in slot of lifting bracket (8) and secure retaining plate (26), bolt and self-locking nut. Tighten both nuts and torque 36 to 40 Ib.in. Install locknut (20) on swivel joint (19). Tighten nut and torque (Ref. No. 960, Fits Clearances) and secure with lockwire. with
(3)
Install
pitch stop adjuster (21) on front end of swivel joint (19) and lock in position (15). Tighten bolt, torque 24 to 36 Ib.in., and secure with lockwire.
with lockbolt
(4)
Install short helical NOTE:
compression spring (22)
over
front end of swivel
joint
stubshaft.
On Post-SB1129 engines, this spring has been removed permanently. Refer to appropriate aircraft manufacturer’s manual for information and instructions.
(5)
Install low
pitch adjuster stop (24) on wire rope terminal. Slide wire rope terminal swivel joint (19) stubshaft and screw adjuster stop (24) into stop adjuster (21), to obtain between 1.00 inch and 1.25 inch of travel on wire rope terminal. Screw plain locknut (23) onto adjuster stop (24) until fingertight. over
NOTE:
(6)
Locknut must not be
torqued until final adjustments have been made.
PT6A-20A
engines: Assemble clevis rod end (12) to wire rope terminal and insert (27) through holes in terminal and clevis rod end. Ensure that wire rope clamp screw hole in clamp bolt is lined up correctly, then screw wire rope into bolt, ensuring wire rope is visible when viewed through inspection hole in clevis rod end. Secure clamp bolt (27) with spacer and self-locking nut. Tighten nut and torque bolt
36 to 40 Ib.in.
(7)
PT6A-20B
engines: Install telescopic terminal housing (52) and compression spring (53) on front end of wire rope terminal. Install spring sleeve into telescopic terminal housing (52) and~ insert clamp bolt (27) into slot in telescopic terminal housing, hole in wire rope terminal and hole in spring sleeve. Ensure that wire rope screw hole in clamp bolt (27) is correctly aligned, then screw wire rope into bolt. Secure clamp bolt with spacer and self-locking nut. Secure clamp bolt with spacer and self-locking nut. Tighten nut and torque 36 to 40 Ib.in. Install clevis rod end (12) into telescopic terminal housing and secure with bolt and castellated nut. T~ghten nut, torque 12 to 18 Ib.in. and lock with cotterpin.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
THE LOWER END OF THE PROPELLER REVERSING LEVER (29) IS MACHINED WITH A STEPPED NOTCH. MAKE SURE THE STEPPED NOTCH AT THE END OF THE PROPELLER REVERSING LEVER (39) IS UNDER THE PIN IN THE REVERSING LEVER GUIDE PIN BRACKET ASSEMBLY (55) (REF FIG. 3-2-46, DETAIL E.
CAUTION:
(8)
Install upper end of propeller
reversing
lever
(29)
into clevis rod end
sleeve spacer and secure with bolt and castellated nut. 18 Ib.in., and lock with cotterpin.
(9)
(10)
Insert sleeve bushing in reversing lever (29) hole, clevis (30) slot, and secure with a straight headed
With
propeller feathered
pitch adjuster stop (24)
and carbon block
so
against
(12).
Install
Tighten nut, torque 12 to
place lever in Beta control pin, washer and cotterpin. rear
face of
slip ring,
valve
set low
that, with linkage pulled fully forward, Beta valve clevis
slot end is flush with front face of Beta valve captive nut. r~ghten nut (23), No. 584, Fits Clearances) and secure with lockwire to adjuster (21).
torque (Ref.
(11)
Secure lower end of
(12)
Adjust length of interconnect rod so that, with reversing linkage held fully forward against pitch adjuster stop (24), and reset arm against maximum stop, rod end connector at upper end of rod (14) aligns with wire rope clamp bolt (27).
(13)
Shorten govemor interconnect rod
propeller governor interconnecting rod (14) to lower hole of air bleed link (31) with bolt, washer and castellated nut. Tighten propeller governor nut, torque 12 to 18 Ib.in., and lock with cotterpin.
turn.
Tighten locknuts, torque
24
(14) by turning each rod end to 36 Ib.in., and apply lockwire
connector
to the
one
half
internally
threaded rod.
(14)
116.
Install upper end of rod end connector to clamp bolt (27), secure with two plain washers and castellated nut. Tighten nut, torque (Ref. No. 599, Fits Clearances) and lock with cotterpin.
INSTALLATION OF PROPELLER REVERSING INTERCONNECT FRONT AND REAR LINKAGE (PT6A-20A AND -20B ENGINES) A.
Procedure
(See Figure 3-2-46)
(1)
Install rear swivel joint (35) to rear fireseal using two plain hexagon locknuts (34). One locknut is installed forward of the fireseal and the other to the rear. Do not torque at this point.
(2)
Install insulation gaskets (17), seals and retaining plates on center fireseal mount ring at the 3 o’clock position. Install angle bracket (16) on front lower side of fireseal. Secure with two bolts and self-locking nuts (18). Do not torque at this point.
NOTE:
(3)
Seal
retaining bolt heads should be air inlet side of fireseal mount ring.
positioned
so
that bolt heads
are on
Install wire rope
casing (33) through seals and center fireseal mount ring and casing coupling nuts (7) to front swivel joint (19) and rear swivel joint (35). Adjust rear swivel joint position to compensate for variations in casing length.
connect
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(4)
Tighten locknut (34) Clearances).
(5)
Tighten coupling Clearances) and
on rear
swivel
joint (35), torque (Ref. No. 583,
nuts at each end of secure
casing (33), torque (Ref.
Fits
No. 582, Fits 8
with lockwire.
(6)
Tighten self-locking
(7)
Install
clamp on casing (33) and self-locking nut (18). Tighten nut
(8)
Insert wire rope (32) into rear swivel joint (35) and push forward into casing toward the front adjustable assembly. Check that internally threaded clamping bolt (27) is loose and screw wire rope (32) clockwise through clamp until rope bottoms. Check for
nuts
(18)
and
torque (Ref. No. 549, Fits
Clearances).
to angle bracket (16) with bolt, washer and and torque 24 to 36 Ib.in.
secure
safety by inserting a piece of wire into inspection hole in terminal. Tighten self-locking nut (28) on wire rope clamping bolt and torque (Ref. No. 581, Fits Clearances). (9)
Slip
safety nut
control terminal (complete with clevis rod end) over end of wire rope, and clockwise to engage wire rope into threaded hole of clamp bolt (4). Check for by inserting a piece of wire through small viewing hole in rod end. Tighten
rear
screw
on
clamping
NOTE:
bolt and
torque (Ref. No. 581, Fits
Clearances).
On Post-SB1170
engines, viewing hole is located on hexagon section of rod end adjacent to clamp bolt (4), while on Pre-SB1170 engines, viewing hole is located nearer clevis end of rod assembly.
(10)
Adjust length of clevis rod end (2) to align with center hole of propeller control (1). Extend clevis rod end by one half turn, to ensure positive movement of controls. Tighten locknut (3), torque 65 to 85 Ib.in. and secure with lockwire.
(11)
Attach clevis rod end
straight (12)
On
headed
(2) to center hole of propeller pin, plain washer and cotterpin.
completion of system to ensure applicable.
control
cam
(1)
and
secure
cam
with
adjustments, check through engine control and reversing that all fasteners are correctly installed and locked where
all
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´•I
PART 3
LINE MAINTENANCE
SECTION 3 1.
INSPECTION
INTRODUCTION A.
inspection procedures detailed are considered a normal function of operating organizations and are intended as a guide for minimum inspection and maintenance requirements. ROUTINE inspection coincides with the daily or preflight airframe inspection. MINOR coincides with a typical airframe zone inspection. The intervals at which these inspections are performed may be altered by the aircraft manufacturers maintenance program and approved by the local airworthiness authority. Engines maintained in compliance with the aircraft manufacturer’s approved maintenance program shall be as required by performance monitoring in accordance with the operator/regulator authority agreed plan. Engines operating in sandy or dusty environments or in smog or salt-laden atmospheres should be subjected to regular inspections for corrosion and compressor erosion (Ref. Table 3-3-1). Hot Section inspection intervals are outlined in the applicable service bulletin (Ref. AIRWORTHINESS LIMITATIONS), and will be updated periodically as dictated by service experience and time-between- overhauls (TBO). If, in the light of experience, it becomes necessary to modify procedures, these will be included in subsequent revisions to this manual. The
TABLE 3-3-1, Periodic
Inspection
Component
A.
Tubing, Wiring,
Inspection
(1)
All accessible
for
connections, clamps and brackets
Interval
MINOR
security.
Control
Linkages, Hose Assemblies
chafing,
cracks and
(2)
Evidence of wear, corrosion.
(3)
Evidence of fuel and old
(4)
Pay particular attention to rear linkage cam box, fuel control unit arm, telescopic rod and rod end fittings. Disconnect rod ends and clean using solvent (PWC11-027) or (PWC11-031). Examine rod end for corrosion, roughness in rotation, side play and radial play. Lubricate with light
leakage.
MINOR
ROUTINE
Every
100
hours
grease (PWC04-001)as necessary, making sure of free movement of linkage. After lubrication reinstall rod ends and torque to specified value Installation). (Ref. Part 3, Section 2, Removal
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TABLE 3-3-1,
Inspection (Cont’d)
Periodic
Interval
Inspection
Component NOTE: With the
exception
of rod end
fittings, linkages generally
will
operate satisfactorily without lubrication. While lubrication will be effective in
some
instances, it must be realized that
grease and oil attracts dirt and foreign matter. Depending local conditions, operators should take these facts into consideration before deciding to lubricate components. B.
Air Inlet
Screen C.
Gas Generator
Cleanliness. For screen edge rebonding instructions refer to Part 4, Section 4, Repair.
MINOR
Cracks, distortion and corrosion and evidence of
MINOR
on
overheating.
Case D.
Fireseals
E.
Exhaust Duct
Cracks and attachment of brackets and seals
MINOR
(1)
Cracks and distortion.
MINOR
(2)
Engines that (Ref. Part 4,
exhibit inferior welds Section 3, Inspection)
MINOR not
(SB1610).
to exceed
150 hours.
(3) F.
Engines that (Ref. Part 4,
exhibit cracks Section 3, Inspection)
25 hours
(SB1610). ROUTINE
Check for oil leaks.
Propeller
MINOR
Shaft Seal G.
Accessories
(1)
Security of installation, linkage
(2)
Evidence of fuel and oil leaks.
and
sense
lines.
MINOR ROUTINE
MINOR
(3)
Starter-generator gearshaft splines for wear. starter-generator removal/replacement only.
At 2.
ENGINE INTERNALS A.
Compressor Turbine Disk
Overhaul. Remove overhaul facility.
assembly
and
ship
to
an
approved
Refer to SE 1003 or SE 1803
Assembly
as
applicable. B.
Mot Section
Examine with
borescope (Ref. Para. 52.).
In
conjunction with
periodic fuel nozzle leak and function tests
(Ref.
4.H.).
I" A.OIL SYSTEMbil
Level
CAUTION: DELETED.
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TABLE 3-3-1, Periodic
Inspection (Cont’d) Interval
Inspection
Component (1)
ROUTINE MINOR
Check oil level.
NOTE: Do check within 10 minutes of engine shutdown Part 2, Section 1, Engine Oil System Servicing).
B.
Oil Filter Element Post-SB1118
(1)
Remove and
(2)
Filter elements must be cleaned (Ref. Part 2, Section 3, Cleaning) and inspected in accordance with Paragraph 45., normally at intervals coinciding with oil change periods recommended in SB1001.
(3)
(1)
(2)
matter.
MINOR
(See NOTE)
Inspect initially at 100 hours with extension to relevant airframe zone inspection based on inspection results but not to exceed 200 hours.
Filter element must be cleaned and inspected every 1500 hours at an overhaul facility using approved equipment prior to further use. Following this cleaning at an overhaul facility, the filter may be utilized for further 1500 hour period, maintaining the same inspection and
cleaning Reduction Gearbox Chip Detector
inspect for foreign
ROUTINE MINOR
oil filler cap.
Check condition and
NOTE:
C.
locking of
(3)
(Ref.
schedule.
Connect test set (Ref. Para. 36.B.) or utility volt-ohmmeter hours across the pins of chip detector. If a resistance of 100 ohms or less is indicated, remove and inspect chip detector in accordance with Paragraph 46., following. Remove magnetic chip detector (Ref. Pam. 46.). Bridge chip hours detector magnetic poles with suitable metallic jumper and using suitable ohmmeter check for continuity between connector pins. Replace chip detector if continuity does not exist.
NOTE: For aircraft
equipped
with
an
airframe
Every
100
hours
Every
600
hours
supplied
indicating device, the integrity of the complete indicating system can be checked by re-attaching the electrical connector to the removed chip detector and check for chip indication when magnetic poles are bridged. Closed circuit condition must exist (Ref. Aircraft Maintenance Manual).
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TABLE 3-3-1, Periodic
Inspection (Cont’d)
Component
Interval
Inspection (3)
Any foreign or
material found
on
the
chip detector
in the main oil filter should be identified
before further
inspection/operation (Ref. Practices).
Part 2,
Section 4, Standard 4.
FUEL SYSTEM A.
Fuel
Check fuel for water contamination.
MINOR
NOTE: On new aircraft, check for presence of water/ contamination after each flight until no contamination is found; also check after first flight or ground run whenever any component upstream of filter is
replaced. B.
Fuel
Check for attachment and leaks Section 6, Testing).
Pump
(Ref.
Part 2,
ROUTINE
NOTE: If airframe boost pump (either electrically or engine driven) fails or is inadvertently left off for a cumulative time in excess of 10 hours, the engine driven fuel pump must be removed and replaced. C.
Fuel Pump Inlet Screen
Check inlet screen for foreign matter or distortion. Clean and reinstall the screen install a new screen.
(74 micron)
Every or
D.
Fuel Pump Outlet Filter
Check for foreign matter or distortion. Install new filter as service conditions dictate. If fuel system contamination is suspected, flush system and replace filter.
E.
Fuel Pump Coupling
If Sundstrand fuel pump is installed, check fuel pump coupling in-situ for fretting corrosion (Ref. Para. 47.A. and B.).
F
Drain and Dump Valves
G.
Fuel Control Unit
Check for
(1) (2)
security
Attachment of unit, sense lines.
and
MINOR
Not to exceed 600
hours MINOR
and leaks.
linkage
500
hours
MINOR
pneumatic
wash-out indicated by effluent at FCU vent. Effluent dye is caused by mixture of bearing grease and fuel (Ref. Para 2, Troubleshooting Fuel Leakage at FCU Vent).
ROUTINE
Leak-test, function-test, and clean fuel manifold
See NOTE
Evidence of FCU
bearing
traces of blue
H.
Fuel Manifold
Adapter
and
Nozzle Assemblies
(1)
adapter and nozzle assemblies. Refurbish necessary (Ref. Para. 43. and 44.).
as
periodic borescope inspection of the hot section components in conjunction with these tests (Ref. 2.B.).
NOTE: Do the
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TABLE 3-3-1, Periodic
Component
Inspection (Cont’d) Interval
Inspection (2)
Engines ON
in-situ fuel nozzle
cleaning
program: Recommended initial interval for operators in where fuel quality may be questionable and for operators new to PTGA operation:
400 hours
Extension based
200 hours
(a)
areas
(b)
on
inspection
results.
Recommended initial interval for other
600 hours
operators. Extension based
(3)
Engines
on
inspection
results.
NOT ON in-situ fuel nozzle
200 hours
cleaning
program.
(a) Recommended initial interval for cleaning/inspection for operators in areas fuel quality may be questionable and for operators new to PTGA operation: Extension, if applicable, on
inspection
200 hours
where
to be determined based
results.
(b) Recommended initial interval for cleaning/inspection for other operators.
400 hours
Extension, if applicable,
200 hours
on
inspection
to be determined based
results.
NOTE 1: If one or more unacceptable nozzle(s) is tare) found the leak and function tests, it is highly recommended that the hot section be inspected for damage by a direct visual
during
inspection
or
borescope inspection.
NOTE 2: Regular fuel nozzle maintenance is important for hot section durability. Inspection is recommended at routine intervals according to either one of the above programs. J.
5.
Oil-to-Fuel Heater
Check oil-to-fuel heater installation (Ref. Part 2, Section 6).
MINOR
filter element based on service experience and environment, maximum interval 1000 hours (Refer to Part 3, Section 2, Removal/i nstallation, P3 Filter Element (Post-SB1294). The filter element may be cleaned electrosonically (Refer to Part. 2, Section 3, Cleaning, P3 Filter Element).
MINOR
PNEUMATIC SYSTEM A.
Compressor Delivery Air P3 Filter Element Post-SB1294
(1)
Install
new
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TABLE 3-3-1, Periodic
Inspection (Cont’d)
B.
Bleed Valve
Interval
Inspection
Component (1)
For
engines operating
in
salt laden environments conditions.
dusty, industrial/smog, high cyclic
or
Every
600
hours. Extension may be based on
operators
experience.
(2)
For other in
engines Step (1).
NOT
operating
in conditions
Inspect in conjunction with
a Hot Section
inspection.
6.
IGNITION SYSTEM A.
Ignition
Security
and condition.
MINOR
Current
Regulator Pre-SB1 429 E.
Cable Assemblies
C.
Glow Plugs Pre-SB1 429
D.
Ignition
Security of attachment. Chafing, twisting of braid.
wear
and
(1)
Cleanliness and condition of elements.
(2)
Functional check.
Security
(Refer
to
Paragraph 40.).
and condition.
MINOR
MINOR
MINOR
MINOR
Exciter Post-SE 1429 E.
Spark Igniters
Cleanliness, erosion and operation.
MINOR
Post-SB1 429
CONTROL LINKAGE 2.
GENERAL A.
Check all engine controls for correct operation, ensuring that the linkage from the cockpit controls to the engine units is connected to permit full and free movement. Make sure that the controls are adjusted to permit over-travel of the control lever, full operation of the engine unit and that the linkage can be operated without interference. and eliminate any slack in the control system. Lubricate and controls in accordance with the aircraft manufacturer’s instructions.
Also
investigate
adjust all
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CORROSION
3.
GENERAL A.
Corrosion may be identified as metal loss or pitting, but more usually appears as local swelling or buildup due to the greater volume occupied by nickel oxides. These corrosion products vary in color from black to green and in the advanced state there will
cracking, referred to as exfoliation. Care should be taken to distinguish between corrosion buildup and possible light brown or rust colored deposits which are essentially harmless combustion by products. The latter are usually more widespread over hot section components and while possibly affecting performance, will not directly affect compressor turbine and power turbine blade integrity. be associated
TUBING AND HOSE ASSEMBLIES 4.
TUBING A.
Procedure
(1)
Inspect all engine scavenge oil, pressure oil, pneumatic control and fuel supply tubing, except where special instructions apply, for the following: (a) Circumferential scratches in tubes are acceptable provided they do not exceed a 45 degree segment on circumference. Any number of scratches is permissible; these may be blended out provided depth of blend does not exceed one-quarter of the wall thickness of tube.
(b)
Longitudinal scratches in tubes must not exceed 1/2 inch in of scratches is permissible.
(c)
Nicks and chafing marks in tubes are acceptable provided three-quarters of the wall thickness remains after blending. Each blended area must not exceed on-half square inch.
(d)
length. Any
are of limited acceptability, provided there are no by sharp edges or corners. Dents are unacceptable inch of ferrule scarf-welds, or in a blended area.
Dents in tubes flow caused
(e)
Minor isolated
pitting
is
acceptable
number
restrictions to within one
if not greater than 0.003 inch in depth. a maximum depth of 0.005 inch.
Clusters of pits should be blended out to
(f)
Rust and stains on tubes are acceptable if with very mild abrasive.
they
can
be removed
by light
polishing 5.
INSULATED TUBES A.
Procedure
(1)
Examine silicone rubber sheathing for damage. Surface cuts up to three inches in length are rectified by use of cement filler (Ref. Repair).
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(a)
damage exceeds limits specified above (a), but depth is superficial, sheathing may be repaired by replacement of damaged portion (Ref. Repair).
(b)
Examine
(c)
Examine tubes for cracks,
If
flanged
end
fitting
for
elongated
especially
holes.
at brazed
(d) Check
tube assemblies for corrosion, dents, scratches.
(e)
Blend out minor
damage
joints. and
fretting, nicks, pitting
that does not exceed limits
specified
in
Inspection,
Tubing.
6.
for cracks
damaged
threads.
Examine
(g)
Check tube bores for obstructions.
(h)
Reject tube Tubing).
(i)
Examine insulation on pneumatic tube assemblies for cuts in outer rubber sheath. Cuts up to three inches long may be repaired. (Ref. Repair.)
couplings
and threaded
fittings
(f)
assemblies
damaged beyond specified
or
limits
(Ref. Inspection,
HEATED TUBES A.
Procedure
(1)
Check resistance value of heating element and lead of pneumatic tube assemblies using Turbine Temperature Indicating System Test Set (Barfield TT1000A) or equivalent. The resistance should be as follows: the resistance should be 20.0
(a)
Pre-SB1294 heated tube
(b)
Post-SB1294 heated tube assemblies, the resistance should be 19.0 3.0 ohms. NOTE:
Test Set
assembly,
(Barfield TT1000A)
(measured
in
1.4 ohms.
parallel)
obtainable from:
Barfield Instrument Corp. PO Box 527705 Miami, FL 33152-7705 USA TEL: 305-871-5629
NOTE:
Post-SB1294 heated tube assemblies, measured be
as
individually,
should
follows:
P/N’s 3030944 and 3030944A3 35.0 P/N’s 3030978 and 3030978A 40.0 P/N 30309448:39.0
2.0 ohms
P/N 30309788:41.2
2.0 ohms
3.5 ohms
4.0 ohms
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7.
HOSE ASSEMBLIES A.
Examine high and low pressure hose assemblies for crimps and buckling. High pressure hoses with such defects must be replaced, while low pressure hoses with such defects are acceptable. Flattening, caused by a permanent set at the bend of an assembly and not associated with a crimp or buckling, is acceptable. NOTE:
8.
crimp or buckle is an abrupt change in the hose teflon inner liner contour caused when the hose is bent at too small a radius. As a result, the liner will be partially or completely collapsed on one location. This condition, which can be detected through the outer hose covering, is similar to that which occurs when a cardboard tube is bent. When a hose assembly is straightened, the collapsed area will expand, but the inner liner contour may remain collapsed. A
METAL BRAID A.
Inspect metal braid sections of pneumatic tube assemblies for cuts in metal braid. Three broken wires per plait, or six broken wires per linear foot, are acceptable. Replace tubes on which wire braid is chafed or worn through to electrical conductors.
ACCESSORIES 9.
STARTER-GENERATOR GEARSHAFT A.
Procedure
(1)
Inspect starter-generator gearshaft internal splines for removal as follows: (Ref. Fig. 3-3-1).
(a)
wear, after
Set Gage (PWC30499-50) to 0.660 inch dimension ’A’ follows:
starter-generator
(View A, Figure 3-3-1)
as
(b)
1
Release gage clamp obtain dimension ’A’
2
Tighten
gage
clamp
screw (3) and adjust (0.660 inch).
screw
Insert gage into gearshaft, approximately 45 degrees.
(3)
ball and
screw
(4)
assemblies
to
and check dimension ’A’ has not altered.
tilting gage
so
that it enters
gearshaft splines
at
(c) Slowly allow gage to support itself in gearshaft splines. If gage supports itself, the gearshaft is serviceable. If gage does not support itself, gearshaft must be INSTALLATION. replaced as detailed in Part 4, REMOVAL
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MANUAL PART NO. 3015442
n
1
2
ALLOW GAGE TO SUPPORT ITSELF
3)
(4)
(1
tlrjDIM.
A
1 DETAIL
A
C1539B
Starter-Generator Gearshaft
Figure
Spline Wear Check
3-3-1
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key 1.
2.
3.
to
Figure
3-3-1
Gage (PWC30499-50) Starter-generator Gearshaft Spline Gage Clamp Screw
4.
Ball and Screw Assemblies
5.
Starter-Generator Mount Pad IN-SERVICE INSPECTION
10.
HOT SECTION COMPONENTS A.
Procedure
(1)
In-service inspection is a troubleshooting procedure used to find the reason for performance deterioration. Parts can be inspected using a borescope (Ref. Part 3, Section 3, Inspection) or by removing the power section. Refer to Part 2, Section 7, Troubleshooting, for areas to be inspected. a borescope is more practical for this inspection. Removal and installation of the power section components/assemblies could result in to parts and/or distortion of sealing surfaces causing gas leaks and performance loss.
(a) Using
damage
(b) Acceptable damage will have to be documented and the rate of progression monitored. Record engine module time and cycles, fuel nozzle port used, if found by borescope, component, description, location and dimensions of defect. (c)
(d)
are found with HSI must be done before the next
unacceptable damage during inspection, flight. If damaged non- rotating components are found, except when holes are burnt through the combustion chamber (Ref. Para. 12.A.(c)), or the CT vane ring trailing edge defects are beyond limits shown (Ref. Fig. 3-3-2), the HSI may be delayed, providing an engine ground power test (Ref. Aircraft Maintenance Manual) is done to check engine performance. If
rotating components
an
inspection of the affected area required, subsequent inspections and engine ground power test intervals will depend on the rate of progression and level of deterioration. Keeping an engine in service after components have deteriorated may substantially increase the cost of subsequent repai rs/refurbishments due to the effect on downstream components.
An additional
engine ground power
test and
must be done after 50 hours. If further extensions are
(e)
path components downstream of components having material missing must be inspected to check if secondary damage has occurred. Pay special attention to rotating components. Compressor turbine (CT) vane airfoils burnt through at the trailing edge (both pressure and suction sides) may mean replacement of the complete set of CT blades, depending on the area of the surface burnt through. Gas
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
NOTE: TRAILING EDGE DEFECTS EXCEEDING THESE LIMITS ARE NOT ACCEPTABLE. DIMENSIONS CANNOT BE ACCURATELY MEASURED WHEN USING A BORESCOPE THEREFORE THE EXTENT OF THE DAMAGE MAY BE ESTIMATED AS A PERCENTAGE OF AIRFOIL LEADING EDGE HEIGHT (1.130 APPROX.)
0.230
1.130 APPROX.
LEADING EDGE OPEN CRACK TRAILING EDGE SURFACE MISSING (BURNT MATERIAL) CRACKS IN THE OUTER RING EXTENDING INTO THE FILLET RADIUS OR ON THE AIRFOIL
BURNT AREA ON INNER/OUTER RING
C23013
Compressor Turbine
Vane
Ring Damage (HSI Recommended) Figure 3-3-2
Page
3-3-12
Dec 02/2005
WHITNEY CANADA
PRATT
RIIAINTENANCE MANUAL MANUAL PART NO. 3015442
(f)
ability of an engine to produce the TO power required by the flight manual for the actual Tam is the only engine power airworthiness requirement. However, on some installations the aircraft maintenance manual provides an engine ground power test. This test may be used to confirm TO power is produced within operating limits over the complete range of ambient temperature and altitude for which the engine/aircraft is certified. If, at an anticipated high ambient temperature and/or altitude, T5 and Ng will approach or exceed the maximum limits, an HSI is recommended before the actual The
conditions NOTE:
occur.
When T5 and Ng approach or are anticipated to approach or exceed the maximum limits, troubleshoot the engine/installation before doing an HSI.
(g)
Carbon accumulation inside fuel nozzle passages is the principle cause of spray pattern degradation which results in non-uniform combustion and local high temperature peaks. Exposure to these peaks contributes to premature hot section deterioration. Carbon accumulation is progressive and can affect all nozzles. Therefore, inspect all nozzles to minimize premature deterioration occurring at other locations.
(h)
component deterioration exceeds limits, either replace the individual component or do an HSI, depending on the general condition of the hot section
(i)
If
and
engine performance.
The
inspections
are
maintenance checks 11.
recommended concurrent with scheduled engine applicable to individual aircraft installations.
POWER SECTION MODULE A.
Procedure
(1)
As
an
alternative to
using
the
borescope, proceed as follows to remove/install inspection (heavy maintenance only):
the
power section module for visual
(a)
Removal
(Ref. Part 3, Section 2, Removal
1
Remove power section
2
Remove CT disk
3
Remove combustion chamber inner liner
assembly (Ref.
Installation).
Part 3, Section 2, Removal
(Ref.
Installation).
Part 3, Section 2, Removal
Installation). 4
Remove CT vane ring assembly, shroud housing and small exit duct Part 4, Section 2, Removal Installation). NOTE:
5
(b)
Do not limits.
Inspect hot
separate these parts unless CT
section
(Ref.
Para.
stater
damage
(Ref.
exceeds
18.).
Installation
Page
3-3-13
Dec´•02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
1
Install CT vane ring assembly, shroud housing and small exit duct Part 4, Section 2, Removal Installation).
1
Install CT disk
3
Install combustion chamber inner liner
assembly (Ref.
Part 3, Section 2, Removal
(Ref.
(Ref.
Installation).
Part 3, Section 2, Removal
Installation). 4
12.
Install power section
(Ref.
Part 3, Section 2, Removal
Installation).
COMBUSTION CHAMBER (SMALL EXIT DUCT, INNER AND OUTER COMBUSTION CHAMBER LINER ASSEMBLIES) A.
Procedure
(1)
Combustion chamber liner cracks may be repairable, and an HSI is recommended before they progress to such an extent that component replacement is required. Converging cracks in the inner and outer combustion chamber liner walls which do not meet are acceptable. Inspect affected area at 100 hours. Subsequent inspection intervals must not exceed 400 hours.
(a)
Plasma
top coating (ceramic) loss revealing undercoat (diffused aluminide) acceptable, providing base metal is not burnt or
on
outer and inner liners is
eroded.
(b)
(c)
Small areas (approx. 1 sq.in.) bulging and/or hot spots on inner or outer liner walls may be repairable and a HSI is recommended for economic reasons. However, the engine may remain in service, providing the associated fuel nozzle(s) are inspected and replaced if not within limits. Inspect the affected area at intervals not exceeding 400 hours. Holes in inner and outer liner walls are unacceptable. An HSI must be done to and then replace the affected component. Associated fuel nozzle(s) must be inspected and replaced if not within limits.
identify
(d) Cracked
or
distorted
cooling rings
on
liners may be
repairable.
For economic
reasons, a HSI is recommended before cooling rings are burnt through and pieces enter the gas stream. Bulging and/or burning in the dome area, associated or not with axial cracks, is acceptable provided the axial cracks (circumferentiar are unacceptable) do not exceed 1.0 inch in length or 0.030 inch in Alternatively, the engine may remain in service if it is understood that cooling air flow is changed, and the rate at which the combustion chamber
cracks
width.
the
deteriorates may increase. Thus, if a HSI is not done, combustion chamber liner having distorted cooling rings or converging cracks must have the associated fuel nozzle(s) inspected and replaced if not within specified limits. Inspect the damaged area at 100 hours. Subsequent inspection intervals must not exceed 400 hours.
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3-3-14
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(e)
Excessive carbon
deposits inside combustion chamber liners could be the result of poor fuel atomization by the fuel nozzles (indicated by deposits around fuel nozzle bosses). Distortion of combustion chamber liner cooling rings may produce carbon deposits in the dome area downstream of the affected cooling ring. If excessive carbon deposits are found, flow check the fuel nozzles. If the nozzles are serviceable, the combustion chamber liner is the probable cause. Inspect the CT blades, as erosion by carbon particles (some carbon particles remain in the gas stream and are not deposited in the combustion area) may damage and eventually cause CT blade replacement. If CT blades are eroded, refer to Para. 14. If CT blades are not eroded, the engine may remain in service and the CT blades and combustion chamber liners must be inspected within 100 hours. Subsequent inspection intervals must not exceed 400 hours.
(f)
As the structural
integrity of the small exit duct is not affected, cracks and open extending from the inner to the outer diameter are acceptable (length not limited), and an unlimited amount of coating loss is acceptable. Holes less than 0.500 in, in diameter in the outer wall are acceptable. If holes or open cracks are found, a HSI is recommended for economic reasons. The engine may remain in service, and HSI delayed, providing it is understood that the CT vane ring cooling air flow is affected, increasing the rate of deterioration. When damage is found, inspect the CT vane ring and associated fuel nozzle. Inspect the damaged area at 100 hours. Subsequent inspection intervals radial cracks
must not exceed 400 hours. If deterioration exceeds the above
limits,
an
HSI is
recommended.
(g)
along, or across, the dome to outer liner seam weld are acceptable provided the cracks do not intersect the fuel manifold support bracket. Inspect damage at 100 hours. Subsequent inspections are at the operators Cracks
discretion but must not exceed 400 hours. 13.
CT VANE RING A.
Procedure CAUTION:
IF ANY CT VANE HAS TRAILING EDGE BURN THROUGH AS SHOWN THE CT BLADES MUST BE DISCARDED.
(Ref. Fig. 3-3-2),
(1)
Burned
areas on vanes
increase flow
area
which accelerates downstream
component deterioration, deceases Ng and increases T5.
(a)
Fig. 3-3-3) are repairable. Keep the engine in service and monitor progression. Do an HSI before defects progress tosuch an extent that the CT vane ring becomes unrepairable. This will increase the cost of the subsequent HSI. Inspect CT vane ring having the defects shown within 100 hours. Subsequent inspection must not exceed 400 hours. Cracks (Ref. deterioration
Page
3-3-15
Dec 02/2005
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
AIRFOIL CRACKS ON PRESSURE AND SUCTION SIDES
LEADING EDG CRACK TRAILING EDGE PARALLEL CRACKS
INNEWOUTER RING CRACKS NOT EXTENDING INTO FILLET RADIUS
NOTE: THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE. THE EXTENT OF THE DEFECT(S) MUST BE RECORDED AND MONITORED BY ADDITIONAL INSPECTIONS. THE ASSOCIATED FUEL NOZZLE MUST BE INSPECTED AND REPLACED IF NOT WITHIN SPECIFIED LIMITS.
C23014
Compressor Turbine
Vane
Ring Acceptable and Repairable Damage Figure 3-3-3
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3-3-16
Dec 02/2005´•
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
If defects have progressed beyond repair limits shown, engine may remain in service, providing a ground power check (Ref. Aircraft Maintenance Manual) is done, and the airfoil trailing edge damage does not exceed limits shown
(b)
(Ref. Fig. 3-3-2). An HSI is recommended if the vane trailing edge defects are beyond the limits shown or downstream components are affected by the CT vane distress or engine performance is unacceptable. NOTE: 14.
Refer to Pam.
10. for additional
recommendations.
CT BLADES A.
While performing compression turbine blade inspection, operators might notice surface anomalies that could be mistaken for sulphidation. In fact, these surface anomalies are a result of the blade manufacturing process and do not affect turbine performance. The following points of inspection will help operators determine if the blades are sefl/iceable: No loss of No
change
coating. in color.
No evidence of
sulphidation
on
adjacent blades.
Geometrical deviations do not exceed 0.005 inches is no width limitation (Ref. Fig. 3-3-4). B.
deep
or
0.005 inches
high.
There
The condition of airfoils and tips is critical to obtain rated power. Most significant blade tip defects (rubs and oxidation) increase T5. Even if T5 is below maximum, an HSI may be recommended for economic reasons if distress is beyond the limits shown (Ref. Fig. 3-3-5). Defects shown are acceptable, providing their condition is monitored by
power checks. Subsequent inspection intervals long in the upper 1/3 of the trailing of blades is removed within 100 hours set the are complete edge acceptable providing and inspected in accordance with overhaul manual criteria. If defects are beyond those shown (Ref. Pig. 3-3-6), an HSI is recommended.
further
inspections
and
engine ground
must not exceed 400 hours. Cracks 0.050 in,
NOTE:
Refer to Para. 10.,
sSteps (c) and (d),
for additional HSI recommendations.
Page
3-3-17
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
0.005 IN
0.005 IN
C77352 CT Blade
Manufacturing Anomalies Figure 3-3-4
Page
3-3-18
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
BLADE TIP
EROSION
OPEN CRACK
ORIGINAL CONTOUR VIEW ON ARROW
i~ri: EROSION BURNT MATERIAL OR FOREIGN OBJECT DAMAGE (FOD)
A
BURNT OR MISSING MATERIAL
PA
TRAILING EDGE
I~li
SULFIDATION BLISTERING WITH SOME BLISTERS
(COATING
BURST)
~,c.´• LEADING EDGE
~v
c
i
C23067
Compressor Turbine Blade Unacceptable Damage Figure 3-3-5
Page
3-3-19
Dec 02/2005
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
HEAVY RUBBING AND BURNT MATERIAL IS ACCEPTABLE PROVIDING ENGINE PERFORMANCE IS WITHIN LIMITS. EROSION
CRACK
0.050 TYPICAL
0.050 TYPICAL
t
C,,,, 113 h 0.050 TYPICAL
COATINGI-.; LOSS
h
TRAILING EDGE
0.970
(REF.) LEADING EDGE COATING LOSS (CHANGE IN
COLOUR)
THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE. THE EXTENT OF THE DEFECT(S) MUST BE RECORDED AND MONITORED BY ADDITIONAL INSPECTIONS.
C23004
Compressor Turbine Blade Acceptable Damage Figure 3-3-6
Page
3-3-20
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C
Procedure
(1)
Check blades for axial shift. Normally, with components within assembly tolerances, the blade platforms are approximately in line. When a blade shifts, the blade moves axially and can be seen as having moved in relation to the adjacent platform. with a borescope, the CT blade TE platforms mismatch for each blade is quite difficult. The recommended method is to look at the leading edge (LE) mismatch while rotating the CT disk. When a mismatch is observed tone of the airfoils LE is shifted), check blade trailing edge platform. Maximum shift is 0.020 inch.
NOTE: 1.
Checking,
NOTE: 2. The amount of blade shift may be estimated by using a 0.020 in. thick wire The free end should be positioned within the field of view of the borescope. When estimating the amount of shift, position the free end of the wire adjacent to the platform being checked.
(2) 15.
If blade shift in
excess
of the limit is observed,
an
HSI is recommended.
CT SHROUD SEGMENTS A.
Heavy rubbing and oxidation are acceptable, providing T5 is within limits. Operating the engine with areas burnt on the shroud segments may cause damage to the CT shroud housing (cracking and burning of the attachment rim), and an HSI is recommended for economic reasons. A damaged shroud housing must be replaced at the next HSI or refurbishment.
NOTE: 16.
Refer to Para. 10.,
Steps (c)
and
(d),
for additional HSI recommendations.
POWER TURBINE (PT) VANE RING A.
Procedure
(1)
Damage on Ng and T5. NOTE:
the airfoils may
Inspection of the
produce
an
increase in flow
area
which will increase
PT stater and/or blades is recommended when upstream not explain performance loss or when secondary
component damage does
damage (a)
is
suspected.
on the inner and outer rings and airfoils are repairable. Keeping the in service, these defects will progress until the PT vane ring becomes engine unrepairable. This will increase the cost of the subsequent HSI. Inspect the damaged area within 100 hours. Subsequent inspection intervals must not
Cracks
exceed 400 hours.
(b)
An HSI is recommended when the defects
are
still
repairable.
Page
3-3-21
Dec 02/2005
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
If the defects are not repairable, replace PT vane ring at the next power section repair. Providing Ng and T5 are within limits, there is no need for power section repair and PT stater change, regardless of the amount of damage, unless structural integrity of the airfoils is affected (e.g. wide open cracks, excessive foreign object damage (FOD) and missing or burnt material are
(c)
unacceptable). 17.
PT BLADES A.
Increased tip clearance of PT stater blades increases T5. If T5 is within limits, there is no need to change the PT stater assembly, regardless of the amount of the damage, providing the structural integrity of the components is not affected. Cracks, missing material, excessive FOD, heavy sulphidation or blade distortion are unacceptable.
HOT SECTION INSPECTION 18.
GENERAL A.
Procedure
(1)
Hot section
inspection
is
normally
carried out under
one
of two sets of circumstances:
(a) Operators using Trend Monitoring, H.S.I. will be preformed when dictated by performance deterioration, in which case pre-inspection performance will be known and post-inspection improvement duly recorded. When performance has deteriorated sufficiently to warrant an H.S.I., some rework to the hot section may be expected. When H.S.I. is performed on a time basis, the object will be to avert component deterioration. Due to the fact that it may be necessary to rework or replace parts, it is recommended that a performance check be carried out both prior to and after the inspection, since components replaced during H.S.I. may affect engine performance.
(b)
NOTE: B.
For Hot Section
Inspection
interval
frequency
refer to SB1003.
General
(1)
inspection (H.S.I.) is inspection, proceed as follows:
The scope of the hot section to
accomplish
this
outlined in Table 3-3-2. In order
(a)
Remove power section (Ref. Section 2, Removal/lnstallation)
(b)
Remove compressor turbine disk assembly. (Ref. Section 2, Removal/lnstallation). Prior to disk removal, check tip clearances (Ref. Para. 25.).
(c)
Remove fuel manifold
adapter assemblies. (Ref.
Section 2, Removal/i nstallation).
Page
3-3-22
Dec 02/2005
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(d) Remove NOTE:
combustion chamber liner.
(Ref. Section 2, Removal/i nstallation).
Should it be necessary during H.S.I. to make a more detailed inspection of engine components listed in Table 3-3-2 which have not been disassembled (i.e. compressor turbine vane ring assembly and small and large exit duct), remove these parts as detailed in Part 4, Section 2, Removal/lnstallation.
TABLE 3-3-2, Hot Section
Inspection Nature of
Component
Inspection
Cracks, distortion, overheating and
Gas Generator Case
corrosion
(Ref. 72-30-04).
Combustion Chamber Liner
Cracks, distortion, burning, fretting hot spots.
Combustion Chamber
Large Exit Duct
Cracks, burning
or
distortion.
Combustion Chamber Small Exit Duct
Cracks, burning
or
distortion.
Combustion Turbine Vanes
Cracks, coating loss, erosion of parent metal or impact damage.
Compressor
Turbine Shroud
Segments
wear or
Cracks, distortion, erosion and metal
build-up. Compressor Turbine
Shroud
Compressor Turbine
Disk
Housing
Assembly
grooving in area of contact with interstage sealing rings. If wear is uneven and conducive to leakage, return shroud housing to an approved overhaul facility for incorporation of SB1157. Wear and
Measure radial
tip
clearance
(Ref.
Par.
25.). Inspect blades for tip rub, erosion, impact damage, coating loss, cracks, shift and circumferential movement, heat discoloration and corrosion (Ref. Table
3-3-3). Inspect blade retaining rivets for condition. If unacceptable, return bladed disk assembly to an overhaul facility for rectification and, if necessary, incorporation of SB1139. Examine disk for nicks, scratches and dents. Damage to 0.005 inch deep is acceptable in any area. Damage exceeding limit, ship disk to an approved overhaul
facility.
Page
3-3-23
Dec 02/2005
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-2, Hot Section
Inspection (Cont’d) Nature of
Component Interturbine or Turbine Inlet Temperature Sensing
Inspection
Security, wiring and functional check. Probes and bus-bar terminal straps or lugs for condition. For weld repair of straps or lugs, refer to Part 4, Section 4. OnPost-SB1102 and all PT6A-20A engines, inspect seal retaining plates for condition.
System
las applicable)
Interstage Sealing Rings
Wear, fretting and distortion (Two
ringsPre-SB1218 and one ring Post-SB1218 engines).
on
NOTE: To facilitate inspection of power turbine blade retaining rivets and inner exhaust duct, remove one airframe exhaust stub (if not already removed).
Power Turbine Disk
blades for impact damage, erosion cracks. or Inspect blade retaining rivets for condition. If unacceptable, return bladed disk assembly to an overhaul facility for rectification and, if necessary, incorporation
Assembly
Inspect
of SB1150.
Exhaust Duct
Cracks
Power Turbine Vane
or
distortion.
Cracks, erosion
Ring
or
impact damage.
Fuel Nozzles
Dissimilarity of carbon functional check.
Fuel Nozzle Sheaths
Fretting
Compressor
buildup.
Perform
wear, erosion and carbon
build-up.
Remove inlet screen and check compressor inlet area and first-stage compressor blades and vanes for dents, nicks, dirt deposits, corrosion and erosion.
Inlet
Reduction Gearbox Oil Strainer
Remove and
inspect
strainer for
foreign
matter.
PROPELLER SHAFT OIL SEAL 19.
INSPECTION A.
General
(1)
Inspect Propeller
Thrust
Bearing
Cover
as
follows:
(a) Inspect thrust bearing cover seal cavity for burrs, nicks and damage. Light stoning of damaged surfaces is acceptable. B.
other surface
Procedure
(1)
Inspect
Oil Seal
Retaining Ring
as
follows:
Page
3-3-24
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(a) Inspect retaining ring or ring halves for nicks, burrs stoning of damaged surfaces is acceptable.
(b)
C.
and surface
damage. Light
Check integrity of felt strip inserts (Ref. Fig. 3-3-7) in oil seal retaining ring halves (Post-SB1381 only). If worn or damaged, retaining ring halves must be shipped to an approved overhaul facility for felt strip insert replacement.
Inspection (1)
Inspect
oil seal
runner as
follows:
area of oil seal runner for nicks, burrs and other surface damage by tooling during removal of seal. No repair is acceptable. Ship power output section to an approved overhaul facility for replacement of defective
(a) Inspect
visible
caused
seal
runner
(b) Inspect propeller shaft oil seal contact surface on oil seal runner for evidence of wear (grooving). If concentrated wear exists, installation of alternate offset propeller shaft oil seal should be considered. The alternate oil seal contacts seal runner at a new location (Ref. I.P.C.).
COMBUSTION CHAMBER LINER 20.
GENERAL A.
Inspect the combustion chamber liner for cracks, buckling and/or burning. Cracks in the liner surfaces are usually of a stress-relieving nature and, as such, are not serious in that the rate of growth decreases as the crack lengthens. Thermal stresses, in effect, relieve original stress conditions. It is normal to observe a given type of deterioration repeated
from liner in the
consists of
adjacent 21.
buckling
and
to the dome.
ACCEPTABLE CONDITIONS A.
same engine or engines of the same model. Typical liner distress cracking of cooling rings and buckling at the inner wall
REPAIR UNNECESSARY
Procedure
(1)
Acceptable
conditions not
requiring repair
are as
follows:
(a) Localized buckling and/or burning of all cooling rings (except louvered type) accompanied by cracking is acceptable provided the cracks do not extend into the seam weld. (See Figure 3-3-9). in the louvered cooling ring (Ref. Fig. 3-3-10) are acceptable provided that circumferential cracks in the seain weld (see Figure 3-3-11) do not exceed 0.300 inch in length and are stop-drilled using a 1/10 inch drill.
(b) Cracks
(c) Straight
line cracks between two
adjacent cooling
holes.
Page
3-3-25
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3q 3 2
2
1)1
(4)
(1
56 v
c
FOR FIELD MAINTENANCE, CUT GASKET AT LOCATION SHOWN
FOR FIELD MAINTENANCE, CUT GASKET AT LOCATION SHOWN
I
GARTER SPRING
GARTER SPRING
885-581377
4(PRE-SB1390) VIEW
A
(ALTERNATE CONFIGURATIONS) GARTER SPRING
GARTER SPRING
4
P
F
8057-581377
1
2
8087-851381
1
Post-SB1227, Post-SB1390, Post-SB1381, excl. PT6A-6A Engines)
C41987
Propeller Shaft Oil Seal Figure 3-3-7
Page
3-3-26
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Key
3-3-7
Oil Seal Retaining Ring (Pre-SB1 377/Post-SB1390) Halves (Post-SB1 377/Post-SE 1381)
2.
Gasket
3.
Thrust
or
Ring
Cover
4.
Bearing Propeller Shaft
5.
Runner
6.
Bolt
7.
Washer
8.
Support Ring Halves (Post-SB1390) Felt Strip Inserts (Post-SB1381 only)
CAUTION:
Oil Seal
CRACKS RUNNING IN THE SAME DIRECTION, SO THAT THEY COULD JOIN, ARE NOT ACCEPTABLE UNLESS THEY ARE SEPARATED BY AT LEAST THREE INCHES OF SOUND METAL.
(d)
A maximum of seven cracks, each crack not exceeding one inch in acceptable in the inner liner adjacent to the dome end. (See Figure
(e)
Localized areas that have been heated to an extent as to cause bulging of the liner dome are considered acceptable (Ref. Fig. 3-3-12), provided there is no crack and the bulging is not associated with excessive burning, which would reduce the wall thickness and weaken the structure. The dome bulging is often associated with cooling ring buckling and reduction of cooling ring gap, and repair of the gap is necessary (Ref. Repair, Para. 22. A. (a)).
ACCEPTABLE CONDITIONS A.
Figure
1.
9.
22.
to
length, is 3-3-8).
REPAIR NECESSARY
Procedure
(1)
Acceptable (a)
conditions
requiring repair
are as
follows:
Buckled cooling rings, in which the gap has been eliminated, must be reworked. Use a suitable bar to restore a uniform gap to dimensions shown in
Figure
3-3-14. must be welded.
(b)
Cracks not exceeding two inches in Section 4, Repair).
(c)
Circumferential cracks adjacent to seam welds must be (Refer to Part 4, Section 4, Repair). NOTE:
(d)
Crack
openings
in
excess
length
of 0.030 inch
progressing from a free edge could allow a piece of metal to break (Refer to Part 4, Section 4, Repair). Cracks
are
(Refer
to Part
4,
repaired by welding.
not
repairable.
that their meeting is imminent and loose must be repaired by welding.
so
Page
3-3-27
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
t~3
d
C88A
Acceptable Cracks in Inner Figure 3-3-8
Liner
Page
3-3-28
Dec 02/2005´•
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CRACK MUST NOT EXTEND INTO SEAM WELD
(Except
Acceptable Buckling
Louvered
C223A
Type)
and Cracks in 3-3-9
erugiFsCooling gniR Page
3-3-29
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ACCEPTABLE, PROVIDED ANY CRACK IN COOLING RING SEAM WELD DOES NOT EXCEED 0.300 INCH IN LENGTH AND IS STOP-DRILLED USING 1/16 DRILL
------u
MULTIPLE CRACKS THROUGH COOLING RING ARE ACCEPTABLE, PROVIDED SEAM WELD CRACKS ARE WITHIN LIMITS
C224B
Acceptable
Cracks in Louvered Figure 3-3-10
Cooling Rings
Page
3-3-30
Dec 02/2005
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
d
d
d
d
d
’d
d
d
d
d d
d
3a
~citi
a~ a
888888888888888888
Q
(S
8
b
6
CRACKS OF THIS NATURE ARE ACCEPTABLE, PROVIDED THEY DO NOT EXCEED 0.300 INCH IN LENGTH AND ARE STOP-DRILLED USING 1116 DRILL.
C225B
Acceptable
Cracks in Louvered
Figure
Cooling Ring
Seam VVeld
3-3-11
Page
3-3-31
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
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C25837
Acceptable Bulging in Liner Dome Figure 3-3-12
Page
3-3-32
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
c-e c
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Acceptable Buckling in Figure 3-3-13
Liner
Page
3-3-33
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INNERLINE
L
#4
.0801N. .0601N.
#5
#7
#6
.0801N. .060 IN.
.0501N. .0301N.
.0801N. .0601N.
LINER DOME
B
.080 IN.
.0601N.
/;050 IN. .0301N.
-A
DOME TO OUTER LINER SEAM WELD
COOLING RINGS #1 #3
#1
.060 IN. .0401N.
.050 IN. .0301N.
i
ALL DIMENSIONS GIVEN ARE INTERNAL AS SHOWN IN THIS TYPICAL VIEW
DETAIL
#2 LOUVERED COOLING RING
#7
.010 IN. .000 IN.
VIEW ON ARROWS
B
A
C1057A Combustion Chamber Liner Cooling Figure 3-3-14
Ring Gaps
Page
3-3-34
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
UNACCEPTABLE CONDITIONS A.
NO REPAIR PERMITTED
Procedure
(1)
Unacceptable conditions necessitating rejection of are as
NOTE:
(a)
Rejected
Severe
liners must be returned to
buckling causing
(b) Multiple cracks (c)
the combustion chamber liner
follows:
Cracks
as
exceeding
shown
kinked metal. on
Figure
two inches in
(d) Circumferential cracks adjacent
an
overhaul
facility.
(Ref. Fig. 3-3-15).
3-3-16.
length. to seam welds which are
opened in
excess
of
0.030 inch. 24.
COMBUSTION CHAMBER SMALL AND LARGE EXIT DUCTS A.
Procedure
(1)
Inspect combustion 7).
chamber small and
large
exit ducts
as
follows:
(Ref. Fig.
3-3-1
small exit duct for fretting wear at duct flange which contacts the combustion chamber liner. Wear up to 0.015 inch is acceptable. If wear is in excess of 0.015 inch, duct should be returned to overhaul facility for possible
(a) Inspect
repair. long in small exit duct outer wall using a I~s (0.0625) inch drill.
acceptable
(b)
Radial cracks up to 1.00 inch provided they are stop drilled
(c)
Inspect large exit duct for fretting wear at surface which contacts the combustion chamber liner. Wear up to 50 percent of material thickness is acceptable. If wear is in excess of 50 percent, duct should be returned to overhaul facility for
are
possible repair. (d) Cracks up to 1.00 inch long in the large exit duct inner wall are acceptable provided they are stop-drilled using a ~s (0.0625) inch drill.
(e) Coating loss of any amount is acceptable on both small and large ducts provided there is no evidence of burning or erosion of parent metal.
Page
3-3-35
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
C
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C90A
Unacceptable Buckling in Liner Figure 3-3-15
Page
3-3-36
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C~9 t~is3
i
I
d ti;3
C91A
Unacceptable Multiple Cracks Figure 3-3-16
in Liner
Page
3-3-37
Dec 02/2005
PRAVT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMBUSTION CHAMBER LARGE EXIT DUCT
A
CRACKS OF THIS NATURE ARE ACCEPTABLE WITHOUT REPAIR
’iit tt DETAIL
A
C11OA
Inspection of Combustion Figure
Chamber
Large
Exit Duct
3-3-17
Page
3-3-38
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR TURBINE BLADE TIP CLEARANCE 25.
GENERAL A.
Measure and record the turbine tip clearance at several locations. Average tip clearance should be between 0.011 and 0.018 inch (REF. NO. 318, Fits Clearances). Clearances should be measured with wire or tapered feeler gages. Make sure that the shroud
assembly NOTE:
is centralized.
Tip clearance
at any
one
location should not exceed 0.019 inch
However, if clearance exceeds 0.018 inch
or
be less than
location, continue segments in service provided performance has been satisfactory and top 0.008 inch.
average clearance (0.018
inch)
at one
is not exceeded.
B.
If the tip clearances are below 0.008 inch due to a shroud high spot, a maximum of three segments may be ground locally over a length not exceeding one inch per segment. For localized grinding use an air drill (or equivalent) with abrasive wheel A54 IBF (or equivalent). When the total length of all high spots exceeds three inches, they must be ground using shroud Grinder (PWC30122) (Refer to Part 4, Section 4, Repair).
C.
Examine the compressor turbine shroud segments for evidence of metal cracks. Limits are shown on Figure 3-3-18.
buildup
and
COMPRESSOR AND POWER TURBINE BLADES GENERAL A.
For compressor turbine blade inspection requirements, refer to Table 3-3-3; for power turbine blade inspection requirements, refer to Table 3-3-4.
Page
3-3-39
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
HEAVY RUB WHERE FUSION OF METAL FROM COMPRESSOR TURBINE BLADE SQUEALER TIPS HAS OCCURRED, GRIND SEGMENT UNTIL FLUSH WITH CONTOUR. INSPECT COMPRESSOR TURBINE BLADES FOR 0.008 IN. MINIMUM SQUEALER TIP.
LIGHT TIP RUB OF THIS NATURE IS ACCEPTABLE
ONE CRACK (THROUGH) PERMITTED IN EACH COMPRESSOR TURBINE SHROUD SEGMENT
C226C
(Pre-SB1147 Engines) Metal Buildup and Cracks
Figure
on
Shroud
Segments
3-3-18
Page
3-3-40
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-3,
Inspection CORROSION
Compressor
Turbine Blade
Inspection
Maximum Serviceable
Maximum
Refer to
Not
repairable
Protrusion of blade root beyond disk rim must not exceed 0.005 inch on either side of disk. If blade shift is between 0.005 and 0.060 inch, further serviceability of the disk will be determined at an overhaul facility. Blade shift in excess of 0.060 inch will result in discarding of the disk.
Not
repairable.
See NOTE 1.
Max. 0.030 inch
Not
repairable.
See NOTE 1.
Not
repairable.
See NOTE 1.
Not
repairable.
See NOTE 1.
Not
repairable.
See NOTE 2.
Not
repairable.
Ref. NOTE 1
Not
repairable.
Ref. NOTE 2
Not
repairable.
Ref. NOTE 1
Not
repairable.
Ref. NOTE 2
Not
repairable
Ref. NOTE 1
Paragraphs
Repairable
Corrective Action
3. and 26.F.
BLADE SHIFT
CIRCUMFERENTIAL MOVEMENT
TIP
RUBSQUEALER
acceptable at blade tip Minimum
height
squealer tip
0.008 inch.
AREA A
Nicks, dents and pits
Three 0.005 inch
deep per blade. Not
Cracks AREA B
acceptable
(FILLET)
Nicks, dents and pits
One 0.005 inch per blade.
Cracks
Not
deep
acceptable
LEADING AND TRAILING
EDGES
Nicks, dents and pits
One 0.020 inch per blade.
Cracks
Not
deep
acceptable
LEADING EDGE TIP EROSION AND
BURNING Erosion
(Ref.Fig. 3-3-19)
Page
3-3-41
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-3,
Compressor
Turbine Blade
Inspection
Maximum Serviceable
Maximum
Burning
The entire set of Compressor Turbine blades must be
Not
scrapped if
Inspection (Cont’d) Corrective Action
Repairable
Ref. NOTE 1
repairable
a
compressor turbine vane
ring inspection
reveals that
vane
trailing edge burning has resulted in loss of airfoil area of 0.125
sq.in.
or
more,
any one vane and burnt area can be seen from the leading on
edge
of
vane
when viewed
engines longitudinal
ring parallel
to
NOTE: 1. Send bladed disk
axis.
assembly
to an
approved
NOTE: 2. If any blade is found cracked, return turbine for replacement of complete set of blades.
overhaul
facility.
assembly
TABLE 3-3-4, Power Turbine Blade
to an
approved
overhaul
facility
Inspection Repairable
Corrective Action
Inspection
Maximum Serviceable
Maximum
BLADE SHIFT
Protrusion of blade root beyond disk rim must not exceed 0.005
Not
repairable.
See NOTE 1.
0.030 inch
Not
repairable.
See NOTE 1.
Not
Not
repairable.
See NOTE 1.
Not
repairable.
None
Not
repairable.
See NOTE 1.
inch
on
either side of disk.
BLADE LOOSENESS
Circumferential movement
Axial
acceptable
movement
AREA A
Nicks, dents and pits
Three 0.003 inch
Cracks
Not
deep
acceptable
AREA B
Nicks, dents and pits
One 0.010 inch
Cracks
Not
acceptable
deep
One 0.020 inch Not
repairable
deep
Blend Ref. NOTE 1
Page
3-3-42
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
TABLE 3-3-4, Power Turbine Blade
Inspection
Inspection (Cont’d) Corrective Action
Maximum Serviceable
Maximum
One 0.010 inch
Not
repairable.
None
Not
repairable
Ref. NOTE 1
Repairable
LEADING AND TRAILING EDGES
Nicks,
dents and
pits
Cracks
Not
NOTE: 1. Send bladed disk
to an
approved overhaul facility.
1
Initial
Coating
Deterioration
(Sulfidation)
Evidenced by slight color change of part of coating area. May be rust colored or dark gray. If coating has deteriorated but is probably still intact, blades are considered acceptable for further service.
Stage D.
assembly
Examine compressor turbine airfoil surfaces, particularly concave surface, for loss of coating, up to 25 percent is permissible, and/or corrosion using 10-power magnification. Assess stage of deterioration and accept or reject bladed disk as follows:
Stage C.
acceptable
Cracks may not extend beyond coating depth. When after stripping coating, cracks do not extend into the base metal, blade may be considered serviceable. Other normal inspection criteria must be applied.
NOTE:
B.
deep
2
Initial Corrosion
Evidenced by apparent rise of sulfidated coating over surrounding surface, with small, scattered blisters appearing in coating. Corrosion of base material has started. Acceptance or rejection of disk is at discretion of operator based on previous experience. If blades are to remain in service, operators must increase existing desalination washes and schedule regular borescope inspection of blades every 200 hours.
Stage E.
Advanced Corrosion
Evidenced by clusters of ruptered blisters exposing bare material. Craters so formed progressively deepen and crater surfaces darken with glazed appearance. Ship disk assembly to an approved overhaul facility for blade replacement.
Stage F.
3
4
Severe Corrosion
Deep penetration with large ruptured blisters exposing large areas of bare metal. Failure is very likely due to structural loss. Ship disk assembly to an approved overhaul facility for blade replacement.
COMPRESSOR AND POWER TURBINE VANES 27.
GENERAL A.
For inspection requirements on compressor turbine and power turbine vanes, refer to Table 3-3-5 (PT6A-6, -6A, -6B and PT6A-20 (Pre-SB1OG1 engines) and Table 3-3-6
(PT6A-20 (Post-SB1OG1)
and all PT6A-20A
engines).
Page
3-3-43
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
0.100
0.100
0.200
rLEADINGEDGE
LEADING EDGE
0.100
~E PROVIDED ENGINE
PERFORMANCE IS SATISFACTORY FILLET AREA
B
TIP RADIUS EROSION LIMITS
BLADES HAVING THINNED OR FEATHERED LEADING EDGES DUE TO EROSION ARE NOT ACCEPTABLE
C3112E
Compressor
Turbine Blade Figure 3-3-19
Inspection
Page
3-3-44
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
UNACCEPTABLE CRACKED BEYOND LIMITS
ACCEPTABLE
C3348
(Pre-SB1OG1 Engines) Compressor Turbine
Vanes
(All Models) and Individual Figure 3-3-20
Power Turbine Vanes
Page
3-3-45
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-5,
Inspection of Compressor Turbine Vanes (All Engines) and Individual Power Turbine Vanes (Pre-SB1OG1 PT6A-20 Engines only) Max. Serviceable
Inspection
Max.
Action
Repairable
COMPRESSOR TURBINE VANES Loss of
coating
Parent metal erosion
0.300 inch square any airfoil surface 0.010 inch
deep
on
on
Not
Not
repairable
cracks
Multiple hairline cracks not exceeding 0.100 inch long Not more than five cracks per vane, which exceed 0.185 inch long.
Erosion and
burning
Replace vane
any airfoil surface
Trailing edge
Replace
repairable
at maintenance level
When a compressor turbine vane ring inspection reveals that vane trailing edge burning has resulted in loss of airfoil area, of 0.125 sq.in. (i.e., average length times average width equals or exceeds 0.125 sq.in.) or more, on any one vane and burnt area can be seen from the leading edge of the vane ring when viewed parallel to the engine longitudinal axis, the entire set of compressor turbine blades must be
Not
repairable
of
with
same
new
class
Replace
at maintenance level
Not
Replace
repairable
at maintenance level
Not
repairable
Replace vane
of
with
same
new
class
scrapped. Ship power section/turbine
disks to
an
approved
overhaul
facility.
POWER TURBINE VANES Erosion
or
chipping of leading or trailing edges
0.020 inch
0.020
Blend power turbine vanes to a smooth contour
Page
3-3-46
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-5,
Inspection of Compressor Turbine Vanes (All Engines) and Individual Power Turbine Vanes (Pre-SB1OG1 PT6A-20 Engines only) (Cont’d)
Inspection
Max. Serviceable
Max.
Airfoil surface
0.125 inch square by 0.010 inch deep on
Not
erosion
or
pitting
Action
Repairable
Replace
repairable
with
new
vane
of
any
same
class
vane
Cracks
Not
Not
repairable
Replace
repairable
with
new
vane
of
same
class
NOTE: 1. Cracks longer than 0.125 in. must be separated by at least 0.100 in. NOTE: 2. Cracks must not be open in
excess
of 0.020 in.
NOTE: 3. Classification, replace vane ring with same class within 0.03. If vane class unknown, refer to last test cell run matching figures in log book or contact P&WC Customer Support.
TABLE 3-3-6, Power Turbine Vane
Inspection
Ring Inspection (PT6A-20 Post-SB1OG1 Engines)
Max. Serviceable
Max.
and all PT6A-20A
Action
Repairable
CRACKS
Leading and/or trailing edges
0.400 inch
long
on
any number of vanes any airfoil surface.
Not
repairable
at maintenance level
Return power turbine vane
facility Outer ring
Not
long
0.600 inch
ring
to an
overhaul
repairable
at maintenance level
for possible repair.
Return power turbine vane
ring
to an
overhaul facility for possible
repair. Inner
ring
One crack entire
through
length is acceptable provided crack is not open
Not
repairable
at maintenance level
more
than
Return power turbine vane ring to an
overhaul facility for possible
repair.
0.020 inch
EROSION OR FITTING
Page
3-3-47
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-6, Power Turbine Vane
Ring Inspection (PT6A-20 Post-SB1OG1 Engines) (Cont’d)
Inspection
Max. Serviceable
Airfoil surfaces
0.010 inch
0.250 square inch
any
by
Not
Repairable
repairable
Action
Replace assembly with
on
one
vane
of
deep
Max.
and all PT6A-20A
Same
class
for any number
vanes
INTERSTAGE BAFFLE
Retaining
Replace rivets
rivets
for security
as
necessary
INTERSTAGE BAFFLE SEALING
RING(S) FRETTING WEAR Inside diameter
Acceptable provided
Not
repairable
Replace
end faces of
ring do not ring installed in seating
meet when
is
location over
compressor
turbine shroud
housing
Page
3-3-48
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-6, PowerTurbine Vane
Inspection
Sealing
face
Ring Inspection (PT6A-20 Engines) (Cont’d)
Max. Serviceable
Max.
Acceptable provided
Not
Post-SB1OG1 and all PT6A-20A
Action
Repairable
repairable
face shows witness of
Replace
with
new
vane
of
same
class
contact
around complete circumference when checked against true flat surface. Install original or new ring(s) individually in correct location and orientation on compressor turbine shroud
housing. Check gap between ring and
housing sealing diameter, maximum
acceptable gap in free state is 0.002 inch over not more than 120 degrees of are, remaining area to be light tight. Reject ring and/or housing if this
limit is exceeded POWER TURBINE STATOR HOUSING FRETTING WEAR
LUGS
Acceptable providing minimum lug width of
Not
repairable
Replace
Not
repairable
Replace
0.190 inch is
maintained
Sealing
face
Acceptable providing face shows witness of contact around
complete circumference when checked
against sealing ring
Page
3-3-49
Dec ´•02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 3-3-6, Power Turbine Vane
Light stoning surface to
NOTE: 2.
Max.
Max. Serviceable
Inspection NOTE: 1.
Ring Inspection (PT6A-20 Post-SB1OG1 Engines) (Cont’d)
of
Action
inside diameter and compressor turbine shroud localized high spots is acceptable
Replace vane ring and interstage ring classification, refer to IPC.
baffle
assembly
with
same
class
housing sealing
or
+0.1. For
vane
(FIRST STAGE)
GENERAL A.
29.
Repairable
ring
remove
COMPRESSOR BLADES 28.
and all PT6A-20A
inspect the first stage compressor blades, inspect them for acceptable or unacceptable blade damage as detailed in Paragraphs 29. and 31. Damage limits to first stage compressor blades are based primarily on structural integrity considerations. In assessing damage, it should be remembered that continued operation with a large percentage of blades damaged or eroded to maximum or near maximum acceptable limits may result in decreased compressor and engine efficiency. Due to restricted areas, and difficulty in accomplishing proper blending repairs, the damage and erosion limits in Paragraphs 30. to 32., are considered acceptable without repair. If, after troubleshooting, it is necessary
DAMAGE LIMITS A.
NARROW CHORD
to
(Pre-SB1094 ENGINES)
Procedure
(1)
Inspect compressor first stage, Fig. 3-3-21).
narrow
chord blades for
(a) Multiple superficial leading edge nicks,
damage
0.010 inch maximum
as
follows:
depth
on
(Ref.
any
number of blades.
(b) Leading
per blade
NOTE:
trailing edge dents 0.030 inch deep by 0.040 inch long. Four on either leading or trailing edge on any number of blades.
or
A dent is considered to be the parent metal has been
an
indentation caused
by impact
dents
in which
displaced.
or trailing edge tip curl without presence of tearing. Maximum allowable deformation 0.050 inch on one edge, six blades only.
(c) Leading (d) Leading nicks
on
NOTE:
or
trailing edge nicks 0.020 inch maximum depth. No more leading or trailing edge, on any number of blades.
than two
either
A nick is considered to be
impact, resulting
in
parent
a
sharp surface
indentation caused
metal loss. No cracks
by
permitted.
Page
3-3-50
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TIP CURL
DENT
(MATERIAL DISPLACED)
NICK
(MATERIAL LOSS)
MULTIPLE SUPERFICIAL NICKS
I
I
NARROW CHORD
0.050 INCH NO FOREIGN OBJECT DAMAGE ALLOWABLE IN ROOT FILLET RADIUS
C600B
Compressor
Blades
(First Stage
erugChord) iFstiDamage miL Narrow
3-3-21
Page
3-3-51
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
30.
NARROW CHORD (Pre-SB1094 ENGINES
EROSION LIMITS A.
Procedure
(1)
Inspect compressor (a)
Use Detail A for
first stage,
31.
as
follows
(Ref. Fig. 3-3-22).
erosion 0.200 inch maximum material loss
Unacceptable leading edge
and
adjacent airfoil surface
erosion
WIDE CHORD (Post-SB1094 AND ALL PT6A-20A
DAMAGE LIMITS A.
chord blades
comparison.
(b) Acceptable leading edge B).
(c)
narrow
(Ref.
(Ref.
Detail
Detail
C).
ENGINES)
Procedure
(1)
Inspect compressor
as
follows
(Ref. Fig. 3-3-23):
NICKS IN LEADING AND TRAILING EDGES BECOME INCREASINGLY CRITICAL TOWARD THE ROOT OF THE BLADE. DAMAGE IS NOT PERMITTED WITHIN 0.050 INCH OF THE BLADE ROOT FILLET RADIUS.
CAUTION:
(a)
first stage, wide chord blades
Multiple superficial leading edge nicks
0.050 inch maximum
depth
on
any
number of blades.
(b) Leading
per blade NOTE:
(c)
A dent is considered to be the parent metal has been
blade
on
NOTE:
EROSION LIMITS A.
an
indentation caused
by impact
dents
in which
displaced.
Leading or trailing edge tip curl without presence of tearing. Maximum allowable deformation 0.150 inch on one edge, four blades only.
(d) Leading
32.
trailing edge dents 0.100 inch deep by 0.100 inch long. Two on either leading or trailing edge on any number of blades.
or
trailing edge nicks 0.100 in, max, depth. Two dents leading or trailing edge on any number of blades.
or
maximum per
A nick is considered a sharp surface indentation caused resulting in parent metal loss. No cracks permitted.
WIDE CHORD
by impact,
(Post-SB1094 AND ALL PT6A-20A ENGINES)
Inspect compressor first stage, wide chord blades for leading edge erosion (Ref. Fig. 3-3-24). Eroded blades are considered acceptable without repair, provided maximum erosion from leading edge to apex of eroded area does not exceed 0.400 inch. NOTE:
If damage to the first stage compressor blades is acceptable and, following blending, engine performance remains within acceptable limits, inspection of the subsequent compressor rotors and stators is not required. Under these conditions, the engine is considered acceptable for service.
Page
3-3-52
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
0.200
DETAIL
A
DETAIL
B
DETAIL
C
NARROW CHORD
C613B
Compressor Blades (First Stage Figure
Narrow
Chord)
Erosion Limits
3-3-22
Page
3-3-53
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
LEADING EDGE TIP CURL
DENT
(MATERIAL DISPLACED)
NICK
I~-- (MATERIAL LOSS)
WIDE CHORD
0.050 INCH NO FOREIGN OBJECT
DAMAGE ALLOWABLE IN ROOT FILLET RADIUS
C935
Compressor Blades (First Stage Wide Chord)- Damage Limits Figure 3-3-23
Page
3-3-54
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
0.400 MAXIMUM MAIERIAL LOSS FROM EROSION
LEADING EDGE WIDE CHORD
C936A
Compressor
Blades
(First Stage Wide Chord) Figure 3-3-24
Erosion Limits
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR TURBINE VANES 33.
INSPECTION A.
Procedure
(1)
If any of the vanes exhibit evidence of impact damage, remove inner and outer exit duct assemblies and inspect the 14 blind rivets (if fitted) in gas generator case for security and condition (Ref. Fig. 3-3-25). Acceptable conditions without repair are as follows:
adjacent
(a)
Four
(b)
Six rivets
or
(c)
A total of
eight
(d)
A total of six
NOTE:
rivet
or
rivet heads
rivet heads
are
missing
loose rivets is
missing
missing.
are
from total of 14.
permissible provided
no
and two loose rivets is maximum
rivets
are
missing.
acceptable
condition.
(maximum) is acceptable between the rivet head and the sheet surface as shown on Figure 3-3-25, Detail A, provided that at least 40% of the rivet head circumference is in contact with the sheet surface. Should any of the above limiting conditions be exceeded, new rivets must be installed in accordance with the instructions contained in Part 4, Section 4, Repair. A gap of 0.005 inch
TURBINE INLET T4 THERMOCOUPLE HARNESS 34.
GENERAL A.
Since the harness is a single integral unit consisting of 24 thermocouples averaged by means of a bus-bar, the probes cannot be checked separately. The following method of checking will therefore only uncover circuit malfunctions such as an integral short
circuit, and 35.
an
open circuit in the harness lead.
FUNCTIONAL CHECK A.
Procedure
(1)
Check the harness at
(a)
major inspection
or
when
troubleshooting
as
follows:
Using Turbine Temperature Indicating System Test Set (Barfield TT1000A) equivalent, check resistance of internal harness at terminal block. When
or
measured from each of chromel and alumel posts of terminal block to gas generator case, the minimum acceptable resistance is 25,000 ohms. Barfield Instrument Corp. PO Box 527705 Miami, Florida 33152-7705 USA TEL: 305-871-5629
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
POST-SB1143
RIVET
MARK LETTER SR IN THIS AREA TO INDICATE COATED CASE HAS BEEN STRESS RELIEVED. VIBRO-PEEN MAXIMUM DEPTH 0.003 INCH.
(14)
C;
PRE-SB1143 PARTIAL VIEW OF GAS GENERATOR CASE
C1651B
Inspection
of Blind Rivets in Gas Generator Diffuser Area Figure 3-3-25
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(b) Check the continuity and loop resistance, measured across the chromel and alumel posts of the terminal block, using a Barfield TT1000A (or equivalent). Acceptable loop resistance is 1.26 to 1.54 ohms. Check the resistance of the harness extension (if fitted) using a Barfield TT1000A or equivalent. When measured from Pin A to Pin B of the connector to the metal overbraid, resistance must not be less than 25,000 ohms.
(c)
NOTE:
If several
probes are damaged or broken internally, the loop resistance necessarily fall outside the allowable tolerance. Erroneous temperature indication could occur because of the resultant would not
unbalance in the harness circuit. B.
Checking (1)
Check
suspected probes
NOTE:
This check
Section 2,
as
follows:
requires removal preceding).
of power section and T4 harness
(Refer
to
(a)
Attach Barfield TT1000A and alumel posts.
(b)
Heat each
(c)
Observe for a positive deflection of uniform polarity on the test set (or on the cockpit gage) from each probe. The harness should be replaced if it is found
or
equivalent
probe separately using
a
to the harness terminal block chromel
soldering
iron.
that: 1
Any probe
2
Four
T5 THERMOCOUPLE
36.
exhibits reversed
or more
probes
are
polarity.
otherwise defective.
HARNESS, PROBES AND BUS-BAR (PT6A-6/C20, -20, -20A AND -208 ENGINES)
GENERAL A.
The installed T5 temperature sensing system may be considered as a single unit. On Pre-SB1073 PT6A-6/C20, -20 and -208 engines, the assembly comprises a number of
thermocouple probes (SB1212, ten probes; Post-SBPost-SB1212, eight probes) and a wiring harness incorporating an integral terminal block. On Post-SB1073 and PT6A-20A engines, the assembly comprises a number of thermocouple probes (Pre-SB1212, ten probes; Post-SB1212, eight probes), a chromel and alumel bus-bar assembly and a wiring harness incorporating an integral terminal block. The assembly cannot be checked individually from the exterior. The following method of checking will only reveal circuit malfunctions. B.
To carry out inspection and functional checks use Turbine Temperature Indicating System Test Set, Model TT1000A. The inspection and heat response check of probes will be accomplished with power section removed. (Refer to Section 2, preceding.)
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Barfield Instrument
Corp.
PO Box 527705 Miami, Florida 33152-7705 USA 37.
INSPECTION A.
Procedure
(1)
Check harness, bus-bar and
general
condition
as
follows:
(a)
With power section removed, inspect harness lead terminals and terminal block for attachment and signs of damage. Block and terminals may be repaired as detailed in Part 4, Section 4, Repair.
(b)
Post-SB1073: Inspect bus-bar terminal straps for Section 4, Repair).
(c)
Inspect individual probes
in the
following
damage (Refer
to Part
4,
manner:
for attachment.
Reject probe if bar is loose.
1
Check terminal bar of
2
Disconnect either chromel or alumel terminal from probe using 9/32 inch open-end spanner and an Alien wrench (9/s4 inch wrench for alumel or 7/64 inch wrench for chromel). Isolate strap from terminal bar.
a
Using
4
5
probe
terminals. If resistance is to Section 2).
ohm, replace probe (Refer
Measure resistance between open terminal and stater housing. If resistance is less than 50,000 ohms, replace probe (Refer to Section Connect bus-bar strap (or harness lead) to probe. Torque No. 596, Fits 8 Clearances) and lockwire (MS9226-02).
(d) Carry Bus-bar
probes
test set, measure resistance across
not within 0.24 to 0.46
(2)
for
probes
out heat response check of each
probe (Ref.
Par.
screw
2).
(Ref.
38.).
inspection:
(a)
Bus-bar insulation resistance must not be less than 5000 ohms.
(b)
Check bus-bar for breaks, kinks,
(c)
Return defective bus-bar for Pratt
damage
or
possible repair
loose bracket. to the
following
P&WC
facility:
Whitney Canada (Plant 12)
2525 Fernand Lafontaine
Longueuil, Quebec Canada
J4N1N7
Attention: Accessories Overhaul
TEL: FAX:
(450) (450)
Shop
442-6800 442-6807
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
38.
FUNCTIONAL CHECK A.
Procedure
(1)
Check T5 temperature
sensing system
at
major inspection
and
troubleshooting
as
follows:
(a)
Insulation Resistance Check: Disconnect all leads from terminal block on gas generator case. Connect leads of test set to each terminal on block, in turn, and ground (Flange C), and measure harness insulation resistance. As measured from either chromel or alumel terminal to ground, resistance must not be less than 5000 ohms. and Loop Resistance Check: Using test set, measure resistance terminals of terminal block. Resistance must be 0.58 to 0.74 ohms for Post-SB1073, or 0.3 to 0.5 ohms for Pre-SB1073. If several probes are broken or damaged, the loop resistance may not necessarily fall out of the acceptable tolerance. However, erroneous temperature indications could occur due to resultant unbalance in the harness and bus-bar circuit.
(b) Continuity across
(c)
(d)
If thermocouple leads fail continuity proceed as follows:
or
resistance test,
1
Heat T5 terminal block for five minutes heat range of 538"C (1000"F).
2
Let terminal block cool to
3
Repeat
4
If
test in
room
using
or are
heat gun
found shorted,
having
maximum
temperature.
Step (l)(b).
problem persists, repeat Steps (l)(b)
and
(a).
Probe Heat Response Check: With power section removed, apply heat source, such as 100-watt soldering iron (to heat probes to 94"C (200"F), but not exceeding 540"C (1000"F)) to each probe and check for positive temperature deflection. After checking one probe allow heated temperature before proceeding with next probe.
NOTE:
probe
to cool to room
of one of the T5 probes is reversed in a T5 sensing the EMF of reversed polarity cancels out a portion of the total system, T5 signal. The amount of reduction depends on the total source When
polarity
impedances of the probes of each polarity. One probe with reversed polarity may produce a temperature change of 55.6"C (100"F). Therefore, when performing a heat response check on a probe, confirm that output signal is of same polarity with that of the other probes.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR TURBINE SHROUD HOUSING AND INTERSTAGE SEALING RINGS 39.
GENERAL A.
Procedure
(1)
Sealing area between compressor performance. Check as follows: (a)
Remove
engine
and power turbines is critical to
interstage sealing ring(s) from power section. Two rings required engines and one ring on Post-SB1218 engines.
on
Pre-SB1218
(b)
rings on compressor turbine shroud housing and check gap in sealing If rings. gap is less than 0.030 inch, sealing ring(s) should be replaced and shroud housing should be inspected for wear, fretting and distortion. If necessary, housing should be reworked or replaced (refer to Table 3-3-2).
(c)
Single ring configuration (Post-SB1218) rear of engine.
Install
GLOW PLUGS 40.
INSPECTION/FUNCTIONAL A.
must have
(PRESS) marking facing
(PRE-SB1429)
CHECK
Procedure
(1)
Inspect (a)
the
glow plugs
(2)
Inspect
the threads
Remove
on
body
glow plugs
glow plugs (Refer
ignition
to
of the
as
detailed in Part 2,
area.
The maximum fused area only. Plugs with fused
one area
as
for condition.
follows:
2).
ignition harness.
OFF.
Switch
(d)
glow plug elements approximately 8 seconds. Confirm that
(e) Switch ignition
plugs
to Section
(c)
Secure
Clean
than this limit must be discarded.
(b) Attach glow plugs
(f)
build-up.
Check the element for the presence of fused must be not more than ~s inch x 1/32 inch in
Perform functional check of
(a)
(Ref. Fig. 3-3-26):
Cleaning.
area(s) greater (c)
follows
Check the element for evidence of carbon
Section 3,
(b)
as
attain
an
acceptable orange-yellow color
in
OFF.
glow plugs
in gas
generator
case
(Refer
to Section
2).
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
C222 Glow
Plug Showing Fused Figure 3-3-26
Area-
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
SPARK IGNITERS AND SPARK IGNITION SYSTEM
(POST-SB1429)
INSPECTION
41.
A.
Procedure
(1)
Inspect spark igniters
and
ignition
exciter after
cleaning
as
detailed in Part 2,
CLEANING:
(a) Inspect
cylindrical area of firing acceptable to a depth of 0.015
exterior
Wear is
igniter
shell for
chafing
wear.
electrode for erosion (Ref. Fig. 3-3-27 and Table or exceeds amounts shown, reject spark igniter.
(b) Inspect igniter shell and 3-3-7). If erosion equals TABLE 3-3-7,
end of inch.
Spark Igniter
Erosion Limits
(IN)
P&WC PART NO.
VENDOR NAME AND PART NO.
DIM. A
3035102
Champion:
CH34055
0.3000
Not
Applicable
3031213
Bendix: 10-390667-1
0.3000
Not
Applicable
(c) Carry
acceptable
out functional test on
Para.
and
DIM. B
(IN)
replacement spark igniters (Ref.
42.).
(d) Inspect ignition
(e) Inspect input
exciter for
and
output
signs
of
damage
connectors for
and
general
condition.
damage, paying particular attention
to
connector threads for corrosion.
42.
FUNCTIONAL CHECK A.
Procedure
WARNING:
(1)
RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE IGNITION IS SWITCHED OFF AND SYSTEM HAS BEEN INOPERATIVE FOR AT LEAST SIX MINUTES BEFORE REMOVING ANY IGNITION COMPONENTS. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER END FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE CABLE COUPLING NUTS. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.
Perform functional check of
spark ignition system
as
follows:
(a) Switch ignition system OFF. CAUTION:
(b)
DO NOT ALLOW IGNITION CABLE BRAIDING OR FERRULES TO ROTATE WHEN RELEASING COUPLING NUTS.
Disconnect
coupling
nut of
one
ignition
cable from output connector
on
ignition
excite r.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION: SHOULD AN IGNITER PLUG BE DROPPED, INTERNAL DAMAGE, POSSIBLY NOT DETECTABLE BY TEST, CAN OCCUR. RECOMMENDATION IS TO REPLACE THE IGNITER PLUG.
DIM.
A
1 i
I~ NEW IGNITER
DIM.B
WORN OUT
ACCEPTABLE WEAR
NOTE: FOR DIMENSIONS A AND B REFER TO TABLE 201.
C174
Spark Igniter Erosion Figure 3-3-27
Limits
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAUTION:
BEFORE SWITCHING ON IGNITION TO PERFORM OPERATIONAL
CHECK, CARRY OUT A DRY MOTORING RUN (REFER TO PART 2, SECTION 6, TESTING) TO MAKE SURE THAT NO FUEL REMAINS IN GAS GENERATOR CASE. ON.
(c)
Switch
(d)
Listen at gas generator case for snapping sound with snap per second. Switch ignition OFF.
(e)
Reconnect coupling nut of ignition cable to ignition exciter and cable coupling nut. Repeat steps (c) and (d).
(f)
If
ignition
frequency
of at least
remove
one
other
not heard on either check, replace ignition exciter (Refer And Installation) and repeat steps (a) through Section Removal 2, 3,
snapping sound is
to Part
(e). (g)
If snapping sound is not heard on one check only, replace associated spark igniter and/or ignition cable (Refer to Part 3, Section 2, Removal And Installation), and repeat operational check. If spark igniter still fails, replace ignition exciter.
FUEL MANIFOLD ADAPTER ASSEMBLIES 43.
GENERAL A.
Procedure
CAUTION:
EXTREME CARE MUST BE EXERCISED WHEN HANDLING FUEL NOZZLES AND SHEATHS. WEAR CLEAN, LINT-FREE, COTTON GLOVES WHILE HANDLING COMPONENTS; FINGERPRINTS LEFT ON ORIFICE MAY PRODUCE A POOR SPRAY PATTERN.
CAUTION:
IF FUEL MANIFOLD ADAPTERS ARE REMOVED, AND ARE NOT TO BE REINSTALLED IMMEDIATELY, THEY MUST BE PLACED IN A COVERED CONTAINER TO PREVENT EXPOSURE TO DIRT AND DUST. IF FUEL NOZZLE TIPS EXHIBIT SIGNS OF CARBON BUILDUP, THEY SHOULD BE CLEANED. (REFER TO PART 2, CLEANING).
(1)
fuel manifold
Inspect
adapter assemblies
follows:
adapter assemblies (Refer
(a)
Remove fuel manifold
(b)
Remove sheath from each manifold
(c)
Inspect sheaths
for
as
fretting
to Section
2).
adapter assembly (Refer
wear to a
maximum
depth of
to Section
2).
0.010 inch.
(d) Inspect nozzle sheath for erosion and wear. Eroded areas provided final dome thickness is 0.040 inch minimum.
may be
lightly
buffed
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
44.
FUNCTIONAL CHECK A.
Procedure CAUTION:
CAUTION:
(1)
TO ELIMINATE DANGER OF ELECTROSTATIC CONNECTABLE (15) OF TEST RIG (PWC30506) GROUND POINT.
DISCHARGE,
(1)
TO SUITABLE
EXTREME CARE MUST BE EXERCISED WHEN HANDLING FUEL NOZZLES AND SHEATHS. WEAR CLEAN, LINT-FREE, COTTON GLOVES WHILE HANDLING COMPONENTS; FINGERPRINTS LEFT ON ORIFICE MAY PRODUCE A POOR SPRAY PATTERN.
Perform functional check
on
fuel manifold
adapter assemblies
as
follows:
(See
Figure 3-3-28). (a) Partially
fill container
(4)
of Test
Rig (PWC30506) (1),
or
equivalent,
with clean
fuel.
(b) Carefully insert blanking tube (13) and connecting tube (9) adapter(ll) and connect hose assembly (7) to connecting coupling nut securely. (c)
Locate and
secure
connecting
tube
in fuel manifold tube (9). Tighten
(11) with blanking tube (13) and (PWC30521) (12) and position drip tray
fuel manifold adapter
(9)
in Fixture
below
fixtu re.
adapter, blank off inlet connections equivalent, prior to locating adapter in
For the No. 8 fuel manifold inlet
NOTE:
using Plug (PWC30530) Fixture (PWC30521).
(d) Operate
pressure regulating valve indicates 20.0 psig.
or
(3) gradually
until pressure gage
(6)
(e)
A full conical spray, free of spitting or drooling, should appear at, or below 20.0 psig. An onion formation may or may not appear Ref. Fig. 3-3-29).
(f)
to increase the fuel pressure to 60 psig. The volume of spray should increase and be evenly spread about the center axis of the fuel nozzle orifice.
Adjust pressure regulating valve (3)
(g) Spitting reason
NOTE:
(h)
or
for
drooling at 20.0 psig, or more rejection of fuel nozzle (10).
than 20% streakiness at 60
psig,
is
Streakiness is defined as variations of spray quantity indifferent parts of the spray cone, showing up as darker streaks in the spray.
Remove external carbon deposits on the fuel nozzle by lightly brushing orifice a brush having either bronze or non-metallic bristles.
face, with NOTE:
Brush nozzle
only
while fuel is
flowing through
orifice.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(i)
Close off air
supply (2), by
means
of pressure
regulating
valve
(3),
and allow
pressure gage to decrease to zero.
(j)
(k)
Uncouple
hose
assembly (7)
from
connecting
tube
(9).
Remove fuel manifold adapter assembly (Il)from fixture tube (13) and connecting tube (9).
(12),
and withdraw
blanking (I)
Replacement
fuel nozzles must be pressure tested
as
detailed in Section 2.
OIL FILTER ELEMENT (POST-SB1033, POST-SB1118 AND ALL PT6A-20A ENGINES) 45.
GENERAL A.
Procedure
CAUTION:
(1)
IN INSTANCES OF ENGINE-GENERATED METAL CONTAMINATION, THE POSSIBILITY OF RESIDUAL MATTER REMAINING IN PROPELLER AND AIRFRAME OIL SYSTEMS COULD CONTRIBUTE TO CONTAMINATION OF NEWLY INSTALLED ENGINE. WHEN AN ENGINE IS REMOVED DUE TO METAL CONTAMINATION OF THE OIL SYSTEM, ALL AIRFRAME COMPONENTS ASSOCIATED WITH THE ENGINE OIL SYSTEM INCLUDING PROPELLER, PROPELLER GOVERNORS (WHEN AIRFRAME SUPPLIED), TUBES AND HOSES SHOULD BE FLUSHED ACCORDING TO AIRFRAME MANUFACTURER’S INSTRUCTIONS. AIRFRAME OIL COOLERS SHOULD BE REPLACED. ENGINE-SUPPLIED OIL-TO-FUEL HEATERS AND GOVERNORS SHOULD BE RETURNED WITH THE ENGINE.
found on the chip detector or in the main oil filter should be identified before further inspection/operation (Ref. Part 2, Section 4, Standard Practices). Inspect oil filter element as follows:
Any foreign material
(a)
Remove oil filter element
(b)
If
no
(Ref.
Part 3, Section 2, Removal And
visible metallic contaminant is evident, proceed Part 2, Section 3,
as
Installation).
follows:
Cleaning).
1
Clean oil filter element
2
Using
3
If dents and/or broken wires
4
than five percent of visible passages are found blocked after repeated cleaning, element must be sent to an overhaul facility for ultrasonic cleaning and bubble point testing.
(Ref.
a 10 power (minimum) magnifying blocked passages and broken wires.
If
are
glass, inspect
filter element for
found, the filter element
must be
replaced.
more
NOTE:
Operators requiring
further information should contact:
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
14
NOTE: MAXIMUM AIR INLET SUPPLY PRESSURE 100 P.S.I.G.
15
12
10 13
C993E Fuel Manifold
Adapter Assembly Figure 3-3-28
Functional Check
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
3-3-28
3.
Rig (PWC30506) Supply Pressure Regulating Valve
4.
Fuel Container
5.
Filter
6.
Pressure
1.
Test
2.
Air
Gage Assembly
7.
Hose
8.
Check Valve
9.
Connecting
Valve
10.
Fuel Nozzle
11.
Fuel Manifold
13.
Adapter Fixture (PWC30521) Blanking Tube
14.
Pressure Relief Valve
15.
Ground Cable
12.
Pratt Whitney Canada Customer Support Department 1000 Marie-Victorin Longueuil, Quebec Canada L4G 1Al
(c)
When a small amount of visible metallic contaminant is evident, follows: NOTE:
proceed
as
determining filter metal contamination, (Ref. Part 2, Section 4, Standard Practices, Paragraphs 19, 20 and 21) consideration must be given to particle/flake size, shape and engine operating history. A particle is a piece of metal with finite thickness large enough in area to become entrapped on the main oil filter surface. A flake is a metal chip having immeasurable thickness but large enough to become also entrapped on the main oil filter surface. The following should be used as a guide and not as a specification of engine serviceability. Examples of possible contaminants are: In
Small flakes of non-ferrous metal normally bearings or bushings of babbit, tin, bronze
originate or
from
plain
silver.
Small flakes of ferrous metal normally originate from spalled anti-friction bearings, gear teeth or fretting.
normally originate heavy scoring.
Slivers of steel
parts
or
from
from interference between steel
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
ACCEPTABLE
GOOD UNIFORM SPRAY QUALITY
LIGHT STREAKS MAX.
(20%)
NOT ACCEPTABLE
´•i"I: il [iI.:l’[i ONE OR MORE HEAVY STREAKS
ONE OR MORE VOIDS
SKEWNESS
DROOLING
SPITTING
25% 20%
FUEL NOZZLE
A
THE ADDITION OF THE STREAKS MUST NOT EXCEED 20% OF THE TOTAL FUEL SPRAY.
FUEL SPRAY UNDER VIEW
VIEW
A C67153A
Spray Conditions Figure 3-3-29
Fuel Nozzle
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
powdered material is cast iron and originates from the propeller shaft oil transfer sleeve.lt can be assumed that less than small particles of miscellaneous metal, largely non ferrous, can be Fuzz
or
40
cases the filter element should be cleaned and reinstalled. It must also be considered that new engines, or engines immediately after extensive shop work, may produce metal contamination at the oil filter. In such cases normal precautions apply.
discounted. In such
(d)
If Silver 1
Plating
Flakes
are
found, proceed
as
follows:
If the main oil filter contains a large quantity (15 or more) of silver flakes, engine oil system must be flushed (Ref. Part 2, Section 1).
the
(e)
(f)
2
if silver flakes greater than 0.080 inch are found in the main oil filter, the AGE internal scavenge pump screen must be cleaned (Ref. Part 4, Section 2). The engine oil system must be flushed (Ref. Part 2, Section 1).
3
In both cases after performing the above, the engine may be returned to service and the oil filter reinspected at the next scheduled inspection (Ref. Part 3, Table 3-3-1).
White Metal
(Ref.
Part 2, Section 3,
1
On first discovery, clean oil filter recheck after 10 hours.
2
discovery of similar amount of metal, change engine oil and recheck after 10 hours.
3
On third
On second
2
and
clean oil filter, drain and
inspection, if the same amount of white metal continues to generated, the engine should be shipped to an overhaul facility for inspection.
Bronze
1
Cleaning)
or
be
Steel
On first discovery, if there are less than 40 pieces of steel or bronze, clean filter (Ref. Part 2, Section 3, Cleaning) and recheck after 5 to 10 hours. On first
discovery,
if there
are more
than 40
pieces of steel
filter, drain and change engine oil. Perform ground
run
for
or
one
bronze, clean hour and
recheck. a
If
on
recheck after
b
If
on
recheck after
hour ground run, a greater quantity of steel or engine should be shipped to an overhaul facility
one
bronze is found, the for inspection.
one
hour
ground
run, a smaller
present, clean filter and recheck after five c
quantity of
metal is
to 10 hours.
If recheck after 5 to 10 hours reveals presence of similar quantity of steel or bronze metal, the engine should be shipped to an overhaul facility for inspection.
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
CHIP DETECTOR 46.
GENERAL A.
Procedure IN INSTANCES OF ENGINE-GENERATED METAL CONTAMINATION THE POSSIBILITY OF RESIDUAL MATTER REMAINING IN PROPELLER AND AIRFRAME OIL SYSTEMS COULD CONTRIBUTE TO CONTAMINATION OF NEWLY INSTALLED ENGINE. WHEN AN ENGINE IS REMOVED DUE TO METAL CONTAMINATION OF THE OIL SYSTEM, ALL AIRFRAME COMPONENTS ASSOCIATED WITH THE ENGINE OIL SYSTEM INCLUDING PROPELLER, PROPELLER GOVERNORS (WHEN SHOULD BE FLUSHED AIRFRAME SUPPLIED), TUBES AND HOSES ACCORDING TO AIRFRAME MANUFACTURER’S INSTRUCTIONS. AIRFRAME OIL COOLERS SHOULD BE REPLACED. ENGINE-SUPPLIED OIL-TO-FUEL HEATERS AND GOVERNORS SHOULD BE RETURNED WITH THE ENGINE.
CAUTION:
(1)
material found on the chip detector or in the main oil filter should be identified before further inspection/operation (Ref. Part 2, Standard Practices). Inspect reduction gearbox chip detector, which has indicated electrical continuity follows:
Any foreign
(a)
(b)
gearbox.
Remove
chip
NOTE:
Whenever the chip detector is removed for inspection, the oil filter should also be inspected as indicated in Paragraph 45.
If
detector from reduction
as
only a single chain of magnetic particles bridge the gap across the poles of chip detector and the particles consist of small slivers, clean and reinstall
the
detector.
NOTE:
(c)
Clean poles of after cleaning.
chip
detector
by wiping
with lint-free cloth; discard cloth
If more than 10 pieces of small, nugget shaped magnetic material are evident the engine should be shipped to an overhaul facility for inspection.
NOTE:
The chip detector can be is recommended to avoid detector body.
easily overtightened. Use of a torque wrench overtightening and possible fracture of chip
small amount of fuzz, made up of powdered material, is evident, clean detector, reinstall and recheck for continuity after 10 hours.
(d)
When
(e)
When
a
powdered fuzz is evident a second time, but the quantity has not increased, clean detector, reinstall and recheck for continuity after a further 10
hours.
(f)
When
engine
powdered fuzz is found a third time in similar or greater quantities the should be shipped to an overhaul facility for inspection.
Page
3-3-72
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ADVANCE REVISION NO. 67 (PT6A-6 SERIES INSERT Advance Revision
AND PT6A-20 SERIES
67 facing page-3-3-73, Part
ENGINES)
3 Section 3
FUEL PUMP INLET SCREEN AND OUTLET FILTER
(POST-SB1155 AND ALL PT6A-20A
ENGINES) PURPOSE:
To be done B.
Revised the fuel pump in-situ inspection procedure (Para. 47) and added figure 3-3-29A.
in.conjunction with P&WC S.B.
Sundstrand Fuel
(1)
No.1645.
Pump In-Situ Inspection
Remove the drain line and
fitting from
the fuel pump drain
port (Ref. Section 2).
CAUTION:;,IF COTTO~j SWAB OR SIMILAR DEVICE IS USED FOR THIS INSPECTION, CARE MUST BE TAKEN TO MAKE SURE THAT NO FOREIGN MATTER REMAINS IN DRAIN PORT OR ASSOCIATED FITTINGS AND LINES.
(2) :1
Insert´•
a
cotton
swab,
or
equivalent; 1.0
to 1.5 in,
deep into the drain port of the fuel
pump (RBf. Fig. 3-3-29A).
(3)
Angle the cotton swab towards the fuel pump outlet filter and roll it inside port to collect evid~ence of a possible reddish-brown ~deposit´•(iron oxide),
(4)
If no reddish-brown service
CAUTION:
(5)
(b)
stain is
ir
evident, the fuel pump may remain in
DO NOT REMOVE FUEL PUMP COUPLING, REMOVAL M~Y CAUSE CHIPPING OF SPLINES AND/OR LOSS OF CIRCLIP RETENTION. CIRCLIP ALLOWS VERY LIMITED MOVEMENT OF PUMP COUPLING.
If reddish-brown
(a)
(iron oxide)
the drain
(iron-oxide)
stain is evident,
remove
fuel pump
(Ref.
Section
2):´•
Examine input coupling side area of pump face (Se Fig. 3-3-30) for residue from fretting corrosion (iron-oxide deposit). If none present pump may remain in service. Evidence of corrosion residue indicates excessive approved overhaul facility.
spline
wear.
Ship
fuel pump
to
(c) (6)
Install
eheck for
a
replacement fuel pump (Ref. Section 2).
leakage
from seal drain port
as
follows:
(a) Coupling If limits Section
drive oil leaks from fuel pump drain should not exceed 3 cc per hour. exceeded, replace~plain seal on accessory gearbox pad (Ref. 2). If leaks are still present and exceed limits, ship unit for overhaul.
are
...5;´•"~
´•PART-3/SEC- 3
Page
1
of 4
Mar 01/2006 PRINTED IN CANADA
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AR 67
FUEL PUMP
OUTLET FILTER
~d ORIGINAL
i’B
As Received 8~
t,-´•6
ATP
CIVITY TO BE INSPECTED
DRAIN PORT
(DRAIN
FITTING
REMOVED)
C107468
Fuel
Pump In-situ Inspection Figure 3-3-29A
PART-3/SEC- 3
Page
2 of 4
Mar 01/2006
PRATT
WHITNEYCANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442 AR 67
DRIVE COUPLING
SEAL
DRAIN PORT
9 cs~ AREA TO BE INSPECTED
C41986 Fuel
Pump Coupling Area Figure 3-3-30
Inspection
PART-3/SEC- 3
Page
3 of 4
Mar 01/2006
PRATT.
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
AR 67
(b)
Fuel leaks should not exceed 20 pump for overhaul. NOTE:
If limit is
cc
per hour. If
leakage exceeds limit, ship fuel
exceeded, inspect FCU driveshaft bearing
area
for fuel
contamination.
PART-3/SEC- 3
Page
4
oi
4
Mar 01/2006
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
Inspection (1)
Perform detailed
(a)
inspection of chip
detector
as
follows:
Examine threads for damage. Chase threads detector if threads are damaged or crossed.
as
necessary.
Replace chip
(b) Examine lacquer witness stripes on detector housing/connector body (P/N 3019373 only). Misaligned stripes are an indication that rotation between the two parts of the detector has taken place with the possibility of short circuit between the two poles of the detector and therefore give rise to false indication. In this condition, reject chip detector. NOTE:
(c) Connect
Chip detector P/N 3029199 change letter B and subsequent incorporates a splined locking arrangement that prevents movement; therefore it does not require witness stripe identification. an
steel bar
ohmmeter
(keep)
detector output terminals and place a suitable the detector poles. Circuit continuity must exist.
across
across
(d) Check security of output terminal pins and condition of potting compound. pins are loose or compound is cracked reject detector.
(e) Connect
an
ohmmeter between shell of detector and each connector
pin,
If
in
turn. Insulation resistance must be not less than 5000 ohms.
FUEL PUMP INLET SCREEN AND OUTLET FILTER
(POST-SB1155
AND ALL PT6A-20A
ENGINES) 47.
GENERAL A.
Procedure
(1)
Inspect
fuel pump inlet
(a) Remove
(b)
inlet
Clean inlet
screen
screen
screen
and outlet filter
and outlet filter
(Ref.
(Ref.
Part 2, Section 3,
as
follows:
Section
2).
Cleaning).
10-power (minimum) magni~ying glass, inspect inlet screen for clogged passages and broken wires. Inspect outlet screen for contamination.
(c) Using
a
NOTE:
(d) B.
It is recommended that the fuel pump outlet filter (disposable replaced every 600 hours or as service conditions dictate.
If dents or broken wires be replaced.
are
found in fuel pump inlet screen, the
type)
screen
be
must
Inspection (1)
q
Inspect
fuel pump
NOTE: Please
see
coupling
as
follows:
the
TEIWPORARY REVISION
I
~thatrevisesthispage. I
I
Page
3-3-73
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
IF COTTON SWAB OR SIMILAR DEVICE IS USED FOR THIS INSPECTION, CARE MUST BE TAKEN TO MAKE SURE THAT NO FOREIGN MATTER REMAINS IN DRAIN PORT OR ASSOCIATED FITTINGS AND LINES.
CAUTION:
(a)
Remove drain line and
(b)
Inspect fuel drain port internal passage wall above drain port threads and inside diameter of drain port, drain fitting and drain line for evidence of reddish-brown (iron-oxide) stain. If none evident fuel pump may remain in service.
from pump drain
port (Ref. Section 2).
DO NOT REMOVE FUEL PUMP COUPLING, REMOVAL MAY CAUSE CHIPPING OF SPLINES AND/OR LOSS OF CIRCLIP RETENTION. CIRCLIP ALLOWS VERY LIMITED MOVEMENT OF PUMP COUPLING.
CAUTION:
(c)
fitting
(iron-oxide) stain is evident, remove fuel pump (Ref. Section precautionary measure and proceed as follows:
If reddish-brown
2) 1
as
Examine
input coupling side
of pump face (See Fig. 3-3-30) for (iron-oxide deposit). If none present pump
area
residue from fretting corrosion may remain in service. 2
Evidence of corrosion residue indicates excessive pump to approved overhaul facility.
3
Install
(d) Check L
for
original
or
leakage
replacement
fuel pump
from seal drain port
as
as
spline
Ship
wear.
fuel
applicable (Ref. Section 2).
follows:
drive oil leaks from fuel pump drain should not exceed 3 cc per hour. If limits are exceeded, replace plain seal on accessory gearbox pad (Ref. Section 2). If leaks are still present and exceed limits, ship unit for
Coupling
overhaul. 2
Fuel leaks should not exceed 20 fuel pump for overhaul. If limit is exceeded, contamination.
NOTE:
48.
CURRENT A.
REGULATOR_(Pre-S 429)
cc
per hour. If
inspect FCU
leakage
driveshaft
exceeds limit,
bearing
area
ship
for fuel
IGNITION BALLAST TUBES
Procedure
(1)
Inspect
(a)
current
Inspect
regulator ignition
ballast tubes
as
follows:
base of ballast tubes for cracks. If there is any reject tube.
suspicion of
air
leakage
into the tube,
NOTE: Please
A8~
see
the
TEMPORARY REVISION thatrevises
thispage. I I
Page
3-3-74
Dec 02/2005 ____.
_i
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
DRIVE COUPLING
j´•
1
SEAL DRAIN PORT
(9\) AREA TO BE INSPECTED
C41986 Fuel
Ae
NOTE: Please
see
Pump Coupling Area Figure 3-3-30
Inspection
the
TEMPORARY REVISION that revises this page.
I I
Page
I
Dec 02/2005
I
3-3-75
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MAINTENANCE MANUAL MANUAL PART NO. 3015442
(b) Using turbine temperature indicating test set (Ref. Barfield 2312G-8*) or equivalent, check for circuit continuity between Pins 2 and 8, and between Pins 3 and 7, of each ballast tube. If no continuity exists in either circuit, reject ballast tube. NOTE:
on ballast tubes may be identified by reference to the the base. No. 1 pin being the first pin clockwise from the key. all of Pins 1, 4, 5 and 6 may be missing.
Pin numbers
key on Any or
ENGINE UNSCHEDULED INSPECTION 49.
GENERAL A.
General Whenever unusual engine conditions (e.g, overspeed, sudden stoppage, or loss of oil) are experienced, perform unscheduled inspection.
8.
Performance Deterioration
(1) C.
Refer to Part 2, Section 7,
Troubleshooting.
Engine Overspeed (1)
When observed gas generator 102.6%:
(a) (2)
(3)
No action
Overhaul
(a) (4)
engine
When observed
NOTE:
speed (Ng) exceeds
101.5% but does not exceed
required.
When observed gas generator
(a)
for
speed (Ng)
exceeds 102.6%:
Light Overhaul, Engine Overspeed.
propeller speed (Np)
No action
Indicate
Ng
observed.
exceeds 100% but does not exceed 110%:
For transient conditions, refer to Table 6-2-1 Table 2-6-2 (PT6A-6, -6A, -68).
(PT6A-20, -20A, -208)
or
required.
When observed
propeller speed (Np) exceeds
(a) Overhaul engine or power Indicate Np observed. D.
strike
lightning
section for
110%:
Light Overhaul, Engine Overspeed.
Overtemperature (1)
Check engine/aircraft temperature indicating system. If 2-6-2 and 2-6-3 for required action.
satisfactory, refer
to
Fig.
Page
3-3-76
Dec 02/2005´•
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
E.
Overtorque
(1)
Check
engine/aircraft temperature indicating system. following steps for required action.
If
satisfactory,
refer to
Pig.
2-6-4 and the
(2)
Carry
out the
following
maintenance action.
If the overtorque is in the shaded area, remove and inspect the RGB chip detector, strainer and scavenge filter element. If no metallic debris is found, the power section module can remain in service without further unscheduled maintenance actions. If either is contaminated with metal, carry out procedure called up for debris in oil system (Ref. Part 2, Section 7,
(a)
Troubleshooting).
F.
(c)
Refer to Aircraft Maintenance Manual for related aircraft checks.
Overhaul
engine for Light Overhaul,
Immersion in Water.
Dropped Engine (1)
H.
If the overtorque is above shaded area in excess of transient, overhaul power section module for Light Overhaul, Overtorque
Immersion in Water
(1) G.
(b)
Overhaul
Material
(1)
for
engine
Light Overhaul, Dropped Engine.
Ingestion (e.g., ice, stones, etc.)
Check
first-stage
compressor rotor for
foreign object damage (FOD) (Ref.
Pam.
23.).
(2) i.
Carry
out
engine performance/ground power check (Ref. Part 2,
Bird Strike/Soft Material
(1)
Ingestion (e.g.,
soft rags,
Sec. 6, Para.
31).
plastic bags, etc.)
Remains on inlet screen and first-stage compressor airfoils confirm a bird or material has passed through the engine and possibly contaminated the gas path and CT vane cooling air passages. If contamination occurs, hot section components deteriorate rapidly, increasing the cost of refurbishment. Therefore, operators are recommended to carry out a hot section inspection (HSI) as soon as possible after bird strike or ingestion of soft material is confirmed.
(2)
However, if the engine remains in service, carry
(a)
out the
following procedure:
Check first-stage compressor airfoils for FOD and bird remains (Ref. Ref. Para. 23.).
(b) Carry
out a
(c) Carry
out an
Para.
performance recovery
wash
(Ref.
a
or
Part 2, Sec. 3, Pam.
engine performance/ ground power check (Ref.
soft material
17).
Part 2, Sec. 3,
17).
Page
3-3-77
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
J.
Chip
(1) K.
Detector Circuit
Refer to Part 2, Section 7,
Propeller (1)
Sudden
Stoppage
or
and/or Debris in Oil Filter
Troubleshooting. Impact
Propeller sudden stoppage occurs when propeller rotation stops a hard object (e.g., ground, ground service equipment, etc.) (a)
Overhaul power section module for
(b) Inspect
(2)
Completion
remainder of
due to contact with
Light Overhaul, Sudden Stoppage
engine:
I
Check exterior of gas generator case, engine mounts, inlet case, struts, accessories, accessory mountings and flanges for cracks and buckling.
2
Remove
starter-generator and check mounting pad
gearbox
for cracks.
area on
3
Rotate compressor turbine and check for unusual noises.
4
If damage is found, overhaul Sudden Stoppage.
5
Remove and overhaul
accessory
complete engine for Light Overhaul Propeller,
propeller governor for Propeller Sudden Stoppage.
Propeller strike causing blade structural damage propeller spar bent or metallic propeller blade tip bent lover 1.00 in.) or missing and blade bent).
blades:
NOTE:
Propeller strike occurs when (1) a rotating propeller hits a stationary object (2) a stationary propeller is hit by a moving object, causing blade damage. of
(a) Overhaul power
(b) Inspect
section for
remainder of
I
Check gas
2
Check
3
If any
engine:
generator
flanges
Light Overhaul, Overtorque.
case
for cracks
for surface
or
damage
or
distortion.
buckling
damage is found, overhaul complete engine for Light Overhaul, Propeller Strike.
Page
3-3-78
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
L.
Propeller strike causing slightly, etc.).
minor blade
damage (e.g., delamination, indentation,
blade
tip
bent
(1)
M.
Remove main oil filter, strainer and chip detector, and inspect for metallic debris. If metallic debris is found, refer to Part 2, Section 7, Troubleshooting. If no metallic debris is found, reinstall oil filter, strainer and chip detector. Then run engine at 80% torque for 10 minutes, recheck RGB chip detector, oil strainer and main oil filter. Return engine to service if no metallic debris is found. Check RGB chip detector daily for one week (approx. 65 hours). Return to standard inspection intervals if no chip indications occur. If chip detector circuit is completed or metallic debris is found, refer to Part 2, Section 7, Troubleshooting.
Propeller Lightning Strike
(1)
of arcing are found on the propeller blades, the propeller shaft and flange must be checked for magnetism. If the propeller shaft or flange is found magnetized, overhaul power section for Light Overhaul, Lightning Strike.
(2)
Remove and overhaul
(3)
Procedure:
If
signs
(a)
Check 1
propeller governor for Lightning Strike.
propeller shaft
and
flange
for
magnetism
with
one
of the
following:
propeller shaft, especially flange, using a magneto meter residual 3 gauss or 3 oersted or 2.38 A/cm. If sure magnetism is within oersted 3 3 is above or 2.38 A/cm., replace power section. reading gauss or
Check
to make
2
If
propeller shaft
or
flange
is not
magnetized,
remove
and
inspect
main oil
filter, RGB chip detector and oil strainer for metallic debris. If metallic debris is found, refer to Troubleshooting. 3
If no metallic debris is found, return engine to service. Monitor chip detector daily for 1 week. Remove main oil filter and inspect after 7 days (approx. 65 flight hours) (Ref. Part 3, Sec. 2, Para. 59).
4
If no metallic debris is found, engine may continue in service with subsequent inspections carried out as defined in the relevant maintenance
program. N.
Heavy Landing (1)
If
engine
NOTE:
(a)
was
2
heavy landing incident, carry
to a
out the
following
heavy landing is by structural damage to aircraft landing causing underwing skin buckling and rivet heads missing. A
Inspect 1
subjected
and if any of the
Cracks/distortion of
Damage
to
following
engine
defects
are
gear,
checks:
wing
span
evident, replace engine:
skin mounts.
engine structural housings (RGB, Exhaust, Housing).
Gas Generator,
AGE and Inlet
Page
3-3-79
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3
Check all
engine-mounted accessory adapters Pay special attention to:
and/or
bosses for
mounting
cracks and distortion.
4
a
Fuel pump, FCU and associated
adapter.
b
Starter-generator
and assodiated
adapter.
c
AC unit
2!
Fuel heater and external oil pump
Check the
or vacuum
engine
pump,
accessories
propeller
specified
control and
overspeed
governor.
packs. in
Step
3a for
security. Rectify
as
required. 5
Check the
following airframe/engine
connections for attachment:
fuel inlet oil cooler
indicating system ignition system air
system
fuel oil drains control 6
linkage
Remove main oil filter, strainer and chip detector and inspect for metallic debris. If metallic debris is found, refer to Part 2, Section 7, Troubleshooting. If no metallic debris is found, reinstall oil filter, strainer and chip detector. Then run engine at 80% torque for ten minutes, and recheck RGB chip detector, oil strainer and main oil filter. If no metallic debris is found, return the engine to service. Check chip detector daily for one week. Remove and inspect main oil filter after seven days (approx. 65 hours). If no metallic debris is found, the engine may remain in service with subsequent inspection carried out as defined in the relevant maintenance program.
O.
Sustained Running at
(1)
Check
an
Oil
Temperature
Outside Limits
oil temperature indicating system (Ref. Table 2-6-1 (PT6A-20, Table 2-6-2 (PT6A-6, -6A, -68). If satisfactory, do the following
aircraft/engine
-20A, -208)
or
maintenance
procedure: Part 2, Section. 1, Pam.
(a)
Drain and discard oil
(b)
Remove and check oil filter and strainer
(c)
Remove and check
(d)
Rectify cause 2-7-5).
of
(Ref.
(Ref.
chip detector(s) (Ref.
high
oil
3).
Part 3, Section 2, Para.
Part 3, Section 3, Pam.
59).
46.).
temperature (Ref. Part 2, Section 7, Troubleshooting,
Table
(e)
Fill oil
system (Ref. Part 2, Sec. 1, Pam. 4).
Page
3-3-80
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
P
Loss of Oil
NOTE:
or
Oil Pressure
or
Low Oil
Low oil pressure is defined as running the engine with the oil pressure below specified limits (Ref. Table 2-6-1 (PT6A-20, -20A, -208) or Table 2-62
the
(PT6A-6, -6A, -68). (1)
If the loss of oil is 6 qt. or more and the oil pressure or torquemeter indication fluctuated or oil pressure dropped below minimum value:
(a)
Check oil pressure and torque indicator system. If correct, and the engine did not run above 1315 Ib.ft., torque with pressure below 85 psi (minimum time running is permitted to allow flight crew to follow the emergency procedure), remove main filters, strainer, and chip detector and inspect for metallic debris. If metallic debris is found, refer to Troubleshooting.
(b) Turn the propeller by reduction gearbox or
(c)
If unusual noises
are
hand and listen for unusual noises PT bearings.
coming
from the
heard, overhaul power section for Light Overhaul,
Unusual Oil Conditions.
NOTE: 1. Oil pressures below 40 psig are unsafe and require the engine to be shut down (min. time running permitted to allow flight crew to follow
emergency NoTE:2.
procedure).
If oil pressure fluctuates or drops below the nominal value (i.e., 85 psi), reduce the engine power from the maximum of 1315 Ib.ft. torque. The engine may be kept running provided that the oil pressure does not fall lower than 40 psig; however, the torque indicating system will be unreliable at this low pressure (min. time running is permitted to allow flight crew to follow emergency procedure).
NOTE: 3. The PT blades may rub, immediately after not an indication of distress, providing the the
engine
engine shutdown which is rubbing disappears when
cools down. from
(d)
Turn the compressor rotor. Listen for unusual noises seals, gears, compressor and/or CT.
(e)
If unusual noises are heard, overhaul gas Unusual Oil Conditions.
(f)
Remove main oil filter, strainer and chip detector and inspect for metallic debris. If metallic debris is found, refer to Part 2, Section 7, Troubleshooting. If no metallic debris is found, reinstall oil filter, strainer and chip detector. Then run engine at 80% torque for 10 minutes; re check RG8 chip detector, oil strainer and
coming
bearings,
generator for Light Overhaul,
engine to service if no metallic debris is found. Check detector chip daily for one week (approx. 65 hours). Return to standard if no chip indications occur. If chip detector circuit is intervals inspection debris is found, refer to Part 2, Section 7, Troubleshooting. metallic or completed main oil filter. Return
RGB
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
If the engine was kept running above the maximum 1315 Ib.ft. torque with an oil pressure below 85 psi (Ref. Table 1-2-1), check oil pressure and torque indication systems; if correct, remove and overhaul the engine for low oil
(g)
pressure
If the loss of oil is 6 qt. or indication have fluctuated
(h)
NOTE:
Q.
more
and the
oil pressure
or
engine oil pressure or torquemeter dropped below 40 psi.
the oil pressure drops below 40 psi, an engine shut down is required. In single engine installation or emergency, use minimum power to sustain flight and prepare for emergency landing. In
case
(i)
Check oil pressure indicating system. If correct and the engine was kept running with oil pressure below 40 psi in excess of the time required to carry out the emergency engine shutdown procedure, overhaul engine for Light Overhaul, Unusual Oil Conditions.
(j)
Remove and overhaul
propeller governor
for Loss of Oil.
Oil Pressure Follows Throttle
(1)
R.
inspection.
In normal operation, oil pressure indication is stable. Malfunction of pressure relief valve or oil leakage can cause oil pressure indication to increase as throttle is advanced or to drop when throttle is retarded.
(a)
Check external lines for breaks and leakage. Remove pressure relief valve and check for scoring, sticking, etc. (Ref. Part 3, Sec. 2, Para. 71).
(b)
Remove accessory
(c)
Remove oil pressure relief valve and body. Examine body for wear resulting from relief valve rotation. Replace housing if necessary (Ref. Part 3, Sec. 2, Para. 71).
Contamination by Fire
(1)
In
case
~the
of
ground
Do a dry motoring deposits.
(b)
Wash
Halon fire
for cracks.
engine contamination by fire extinguishing agents (foam fire fighting equipment), do the following immediately: run
(Ref.
Part 2, Sec. 6, Para.
engine externally (Ref. out
extinguishing agent
26)
Part 2, Sec. 3, Para.
engine motoring performance recovery
17) omitting dry motoring
(2)
housing
Extinguishing Agents
(a)
(c) Carry
Check oil pump
gearbox.
powder from
to blow out residual
10) using
wash
or
(Ref.
fresh water
only.
Part 2, Sec. 3, Para.
run.
from aircraft
on
board fire
extinguishing
bottles
(system). (a)
No
engine
maintenance
required.
Page
3-3-82
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PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
S.
Audible
(1)
Rubbing, Binding
Any
unusual
or
Scraping and/or
(internal) engine noises (e.g. rubbing, scraping investigation. as follows:
squealing, etc.)
warrant immediate
Rotate compressor and/or turbine rotors and listen for any undesirable interference of rotating components with stationary parts.
(a)
(2)
Compressor
rotor audible
rubbing, scraping, rapid
or
abrupt
deceleration
on
shutdown.
(a) Check
for
(b) Check
for compressor turbine
accessory
case
mounted accessory
drag.
Part 3, Section 3, Para.
tip rub (Ref.
Indications of compressor rub or bearing distress. Overhaul Overhaul. Indicate Compressor Rotor Rub.
(c) (3)
rear
Power turbine rotor for rattles, rubbing or Abrupt deceleration on shutdown.
scraping.
Slow
15) for
engine
Light
propeller acceleration
on
start.
(a) Examine
power turbine disk for evidence of distress.
assembly
(b) If inspection reveals damage, carry
and exhaust
out
area
through exhaust ports
inspection
stiff propeller rotation. Overhaul power section for Indicate Audible Rubbing.
(c) Slow T.
or
Light Overhaul.
Propeller Windmilling after In-flight Shutdown
(1)
With stabilized
(a)
windmilling Np
less than oi
equal
If less than six quarts of oil are required to no further action is necessary
to 20 rpm.
bring
oil level up to MAX
on
dipstick,
six quarts of oil or more are required to refer to Loss of Oil/Oil Pressure.
(b) If
(2)
With
an
unknown
bring oil level up
to MAX on
(not recorded) Np or stabilized windmilling Np greater engine failure (serviceable engine).
dipstick,
than 20
rpm and related to
(a) Refer
(3)
With
to Loss of Oil/Oil Pressure.
in-flight
shutdown attributed to
approved overhaul facility. Indicate U.
Starter-Generator
(1)
a
confirmed engine problem, send engine to for removal.
an
reason
Replacement
If the starter-generator is replaced in order to rectify a reported engine starting electrical generation defect, that is suspected as an electrical fault or bearing distress of the starter-generator, inspect the main oil filter as follows:
Page
or
3-3-83
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(a) Do a main oil filter patch patch analysis should be
check (Ref. Part 2, Section 1). The results of the filter reviewed within the next 25 flight hours. If non allowable debris is found, follow the recommended maintenance actions (Ref. Part 2, Section 1).
(b) Regardless
of the results of the patch next 700 flight hours.
analysis, repeat step (a)
every 100
hours, for the
(c)
50.
ENGINE OVERTEMPERATURE A.
51.
For overtemperature limits and Section 6.
corresponding inspection procedures, refer
to Part
2,
ENGINE OVERTORQUE A.
52.
if bearing material (AMS 6440/6444 or AMS 6490/649, Ref. Part 2, Section 1) is found, remove the engine/gas generator module and send to an approved overhaul facility for repair.
For
overtorque limits and corrective action, refer
to Part
2, Section 6.
BORESCOPE A.
General
borescope is an optical device which enables an operator to perform visual inspection of hot section areas of PTGA series engines. Access is through ports or openings created by removal of engine components. Personnel performing borescope inspection must be fully qualified to do this check and analyze results.
The
B.
Description
(1)
(2)
borescope assembly comprises a pattern-controlled rigid Guide Tube (PWC34910-200), a direct viewing flexible 5 mm fiberscope (PWC34910-100), source, a side viewing adapter and other accessories. A still or video camera may be used to record engine areas.
The
the borescope, without removal of the engine power section, inspect the following:
Using
(a) Compressor
turbine blades and shroud
(b) Leading
trailing edges
(c)
and
Inner and outer
vane
(d) Cooling rings and NOTE:
rings
an
a
operator
light
can
segments.
of compressor turbine stater
assembly.
of the compressor turbine stater
assembly.
dome section of the combustion chamber liner.
using the borescope, study the following procedures, the borescope assembly and its accessories (Ref. Fig. 3-3-31). it is considered vulnerable to severe shocks, twisting and pinching. Care and attention must therefore be used when handling handling it to prolong Before
Page
3-3-84
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CAMERA AND LENS CAMERA ADAPTER
EYEPIECE
GUIDE TUBE FIBERSCOPE
HOLDING
FIXTURE
~J
rWRENCH
j
~-o
FLANGE
C
LIGHT SOURCE
C41524
Borescope
and Accessories Installed Figure 3-3-31
Page
3-3-85
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(3)
Light Source NOTE: A
(a)
Specify
requirements when purchasing borescope.
power
halogen lamp is used supply.
to
provide lighting from either
a
110V, 60-Hz
or a
220V,
50 Hz power
C.
(b) Remove top
cover
from
light
source
to
replace lamp.
(c)
Remove top
cover
from
light
source to
replace lamp.
(d)
Before
installing light
source
refer to manufacturer’s instructions.
Removal/installation
(1)
Side
(2)
An
Viewing Adapter (Ref. Fig. 3-3-32)
adapter (SL-4TP) is used to inspect components located at a nominal 90 degree angle to fiberscope distal tip. The use of side-viewing adapter will introduce a reduction in the field of view as compared to the direct viewing field. A ring is installed to protect distal end when side-viewing adapter is not fitted.
(a)
Installation
CAUTION:
I
Hold
INSTALL SIDE-VIEWING ADAPTER CAREFULLY. IF NOT INSTALLED AND TIGHTENED CORRECTLY, ADAPTER COULD FALL INTO THE ENGINE. OVERTIGHTENING ADAPTER COULD DAMAGE DISTAL END.
fiberscope
as
close
as
possible
to distal end and remove
protective
ring. 2
Hold fiberscope as close as possible to distal end. Install adapter indexing slot and lug aligned. Tighten adapter fingertight.
with
(b) Removal CAUTION:
1
(3)
INSTALL PROTECTIVE RING CAREFULLY. IF NOT INSTALLED AND TIGHTENED CORRECTLY, RING COULD FALL INTO THE ENGINE. OVERTIGHTENING RING COULD DAMAGE DISTAL END.
Hold fiberscope adapter.
as
close
as
possible
to distal end and remove
side-viewing
Camera
(a)
may be used with borescope to photograph internal engine components. It must be equipped with a 50 mm F1.8 lens. Refer to camera handbook for guidance A
1
camera
installation
Page
3-3-86
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
BORESCOPE DISTAL END
PROTECTIVE RING
DIRECTION OF ROTATION FOR RING REMOVAL
RING REMOVAL
PRISM BODY INDEXING LUG INDEXING SLOT
BORESCOPE DISTAL END
SIDE VIEWING ADAPTER THREADED RING DIRECTION OF ROTATION FOR RING REMOVAL
ADAPTER INSTALLATION
C12191
Side-viewing Adapter
Removal/i
erugiFnoital atsn 3-3-32
Page
3-3-87
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
DO NOT USE COMPRESSED AIR TO CLEAN CAMERA, BORESCOPE OR ASSOCIATED EQUIPMENT.
CAUTION:
a
Clean
camera
lens with lens b
Install
c
Install the 50
d
Install
e
Load
f
Set
g
endoscopic focusing
camera
adapter (CAII)
with film
speed to handbook).
Align bayonet slot eyepiece pins. NOTE:
(Ref.
film
camera
Make
screen
in
screen
and 50
mm
camera.
lens.
mm
camera
camera
(Ref.
view finder, reflex mirror, focusing cleaning tissue and cleaner.
of
sure
on
lens.
camera
handbook).
suit film and exposure
adapter
and
push-install
compensation
camera on
distal end is not moved when
to -2
borescope
taking photographs.
(b) Removal 1
Turn outer
ring
of
remove camera
(4)
disengage locking
mechanism and
Remove
3
Remove film from
4
Engine
5
Date and
6
Engine operating
Z
borescope inspection (suspected foreign object damage, power, etc.).
camera
adapter from
to
2
camera
lens.
and, using
a
label, add following data:
serial number. area
of component time
or
photographed.
cycles
since last overhaul.
Reason for
Guide Tube
(a)
adapter eyepiece.
camera
from
lower
(Ref. Pig. 3-3-33)
Installation 1
Remove
appropriate fuel manifold adapter(s) (Ref.
Part 3, Section 2, Pam.
24). NOTE:
The
rigid, pattern-controlled guide
tube must be inserted
freely,
no
force must be used. 2
Ease the Guide Tube (PWC34910-200) through manifold adapter port into the combustion chamber and exit duct zone turning the guide tube counterciockwise until it achieves a three-quarter t;m.
Page
3-3-88
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FUEL MANIFOLD ADAPTER PORT FLANGE
C7
C, ~i
RIGID GUIDE TUBE
C~ POINT OF ENTRY
(REF.)
FIBERSCOPE TIP
125"
VANE RING DISTAL
RELATION BETWEEN POINT OF ENTRY AND DISTAL TIP VIEW TOWARD AIR INLET CASE
C41525 Guide Tube Orientation
Figure
3-3-33
Page
3-3-89
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3
Installed, the guide tube end locates between stater, while its supporting flange rests
on
the
vanes
of compressor turbine
adapter boss. Secure flange
to boss.
(b)
(5)
Removal 1
Loosen knurled
2
Withdraw
3
Reinstall manifold
screw to
release
guide tube, turning
guide
tube
supporting flange.
clockwise.
adapter(s) (Ref.
Part 3, Section 2, Pam.
24).
Troubleshooting
(a) The possible sources of, and remedies for, problems borescope are shown in Table 3-3-8. TABLE 3-3-8,
Oil or
using
Borescope Troubleshooting
SOURCE
REMEDY
or dirt on distal tip, side viewing adapter
Clean using lens cleaner and tissue.
PROBLEM Poor illumination
encountered when
prism
Light
source
intensity
Set switch to HIGH.
switch set at LOW
Defective lamp
Replace lamp
Damaged borescope light tube
Return to manufacturer for repair.
Defective transformer
Return to manufacturer for repair.
Diopter ring correctly
Adjust
Poor definition
Fiberscope distal end does not move when control knob is turned NOTE:
Repairs
(6)
not
adjusted
to suit eyes.
Damaged fibers in fiberscope, (seen as black dots through viewer)
Return to manufacturer for repair.
Poor illumination
See
Damaged control
should be done
only by
wires
previous problem
Return to manufacturer for repair.
the manufacturer.
Inspection (a) Compressor Turbine (CT)
Blades
Page
3-3-90
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Install
guide
2
Clamp holding
3
Fasten
Para.
(Ref.
tube
C.(4).
fixture PWC34913 to
borescope
to
flange
C
(Ref. Fig. 3-3-31).
fixture and connect
holding
borescope
to
light
source
(Ref.Fig. 3-3-31). MAKE SURE ENGINE TEMPERATURE IS BELOW 60"C
CAUTION:
fl:
(140"F).
Slowly insert fiberscope into guide tube while looking through eyepiece. Stop inserting fiberscope immediately distal tip reaches end of guide tube.
NOTE:
Make
sure
installing
distal
or
tip actuating lever removing fiberscope.
is in neutral
position
when
5
Remove starter-generator from engine accessory gearbox (Ref. Aircraft Maintenance Manual).
6
Attach wrench
7
Loosen knurled knob
8
Examine CT blade tip, root and airfoil section 3-3-34 and Para. 26., for limits).
on
to
splined gearshaft.
holding
fixture.
(Ref.
Views A and
B, Fig.
MAKE SURE DISTAL TIP OF BORESCOPE IS NOT LOCATED BETWEEN COMPRESSOR TURBINE BLADES BEFORE TURNING COMPRESSOR.
cnu~:
9
(PWC34941)
Continue
inspection
of CT blades while
a
second operator,
using wrench,
rotates the compressor.
into
10
Retract
11
DELETED
12
Withdraw
13
Remove borescope and
14
Remove
15
Insert
fiberscope
tube.
fiberscope from guide
guide
tube
holding
(Ref.
fiberscope through
CAUTION:
16
guide
tube. fixture.
Para.
C.(4).
the exhaust duct port.
MAKE SURE THE PROPELLER AND THE POWER TURBINE DO NOT ROTATE WHILE FIBERSCOPE IS INSERTED THROUGH THE PT BLADES.
Examine the
trailing edge
of the CT blades while
a
second operator,
using
the wrench, rotates compressor. 17
Carefully
remove
the
fiberscope
from the exhaust duct.
Page
3-3-91
Dec 02/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
.i-
COMPRESSOR TURBINE BLADE TIP
COMPRESSOR TURBINE BLADE ROOT VIEW A
VIEW
B
8´•.~
VANE LEADING EDGE
VIEW
VANE TRAILING EDGE
C
VIEW
D
COMBUSTION CHAMBER LINER COOLING RING VIEW
E C27489
Borescope Views Figure 3-3-34
Page
3-3-92
Dec 02/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
18
Remove wrench from splined gearshaft, and install starter generator Aircraft Maintenance Manual).
(Ref.
(b) CT Stater Assembly tube
1
Install
2
Clamp holding
3
Install
guide
4
Insert
5
Examine
The
use
into
guide
(Ref. Fig. 3-3-31).
fixture and connect
light
source.
viewing adapter may C.(1).
(Ref. vane
leading
and
add to
inspection capability
trailing edges, inner and outer rings of vane ring Fig. 3-3-34, and Para. 27. for limits).
Views C and D,
photograph inspected
To
6
Remove
borescope and holding fixture.
Z
Remove
guide
(140"F)
tube.
NOTE:
tube
(Ref.
Combustion Chamber Liner CAUTION:
C
of side
Pam.
assembly (Ref.
(c)
holding
to
Flange
MAKE SURE ENGINE TEMPERATURE IS BELOW 60"C
fiberscope
NOTE:
C.(4).
fixture PWC34913 to
borescope
CAUTION:
Para.
(Ref.
area
Para.
refer to
paragraph C.(3).
C.(4).
Assembly
MAKE SURE ENGINE TEMPERATURE IS BELOW 60"C
(140"F).
1
Remove fuel manifold adapters as necessary (Ref. Part 3, Section 2, Fuel Dump Valve and Fuel Manifold Adapter Assemblies).
2
Clamp holding
3
fiberscope into a fuel manifold adapter port, holding fixture and connect light source.
4
fixture
(PWC34913)
to
flange
C.
Insert
Inspect combustion limits).
chamber liner
(Ref.
View E,
secure
Fig.
eyepiece
to
3-3-34 and Para. 20;
for
fiberscope, light
5
Remove
6
Install fuel manifold Fuel Manifold
source
and
holding
fixture.
adapters (Ref. Part 3, Section 2, Fuel Dump Valve and Adapter Assemblies).
Page 3-3-93/94 Dec 02/2005
PA RT
HEAVY
MAINTENANCE
PRATT
WHITNEY CANADA´•
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT
PAGE PART 4
SECTION 1 1.
HEAVY MAINTENANCE
SPECIAL TOOLS
GENERAL
SECTION 2
4-1-1
REMOVAL AND INSTALLATION
INTRODUCTION 1.
GENERAL
4-2-1
ENGINE STANDS 2.
3.
INSTALLATION OF ENGINE IN STAND
4-2-~1
A.
4-2-1
Procedure
REMOVAL OF ENGINE FROM STAND A.
4-2-2
Procedure
4-2-2
POWER TURBINE VANES (PRE-SB1OG1 AND POST-SB1246 ENGINES) 4.
REPLACEMENT
4-2-2
5.
REMOVAL
4-2-3
A. 6.
Procedure
4-2-3
INSTALLATION A.
4-2-3
Procedure
4-2-3
POWER TURBINE VANE RING PT6A-20 (POST-SB1OG1) ALL PT6A-20A ENGINES AND ALL POST-SB1246 7.
GENERAL
4-2-5
3.
REMOVAL
4-2-7
A.
4-2-7
9.
INSTALLATION A.
10.
Procedure
4-2-7
Procedure
4-2-7
REMOVAL (Pre-SB1046 ENGINES) A.
4-2-10
Procedure
4-2-10
PART4 CONTENTS
Jun
10/2005Page
1
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT SECTION 2 11.
(Pre-SB1046 ENGINES)
4-2-10 4-2-10
(Post-SB1046 ENGINES)
4-2-10
Procedure
INSTALLATION A.
(Cont’d)
Procedure
REMOVAL A.
13.
REMOVAL AND INSTALLATION
INSTALLATION A.
12.
PAGE
4-2-10
(Post-SB1046
AND ALL PT6A-20A
ENGINES)
4-2-13
Procedure
4-2-13
COMPRESSOR TURBINE VANES AND SHROUD SEGMENTS 14.
REPLACEMENT OF VANES
4-2-14
15.
REPLACEMENT OF SEGMENTS
4-2-14
16.
REMOVAL
4-2-14
A. 17.
Procedure
4-2-14
INSTALLATION
4-2-16
A.
4-2-16
Procedure
LARGE EXIT DUCT 18.
REMOVAL A.
19.
4-2-18
Procedure
4-2-18
INSTALLATION
4-2-19
A.
4-2-19
Procedure
STARTER-GENERATOR GEARSHAFT AND CENTRIFUGAL BREATHER CARBON SEAL 20.
21.
22.
REMOVAL
4-2-19
A.
4-2-19
Procedure
DISASSEMBLY/ASSEMBLY
4-2-23
A.
4-2-23
Procedure
INSTALLATION
4-2-25
A.
4-2-25
Procedure
PART4 CONTENTS
Jun
10/2005Page
2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
FAG E
SUBJECT SECTION 2
REMOVAL AND INSTALLATION
(Cont’d)
SCAVENGE PUMP INLET SCREEN 23.
CLEANING
4-2-29
A.
4-2-29
Procedure
SECTION 3
INSPECTION
1.
GENERAL
4-3-1
2.
EXHAUST DUCT
4-3-1
A. 3.
4-3-1
COMPRESSOR INLET CASE A.
4.
Procedure
4-3-3
Procedure
4-3-3
GAS GENERATOR CASE A.
4-3-3
Inspection of Gas Generator Case
SECTION 4
4-3-3
REPAIR
INTRODUCTION 1.
GENERAL
4-4-1
HELICAL COIL INSERTS 2.
REPLACEMENT A.
4-4-1
Repair
4-4-1
REDUCTION GEARBOX ASSEMBLY 3.
FRONT AND REAR REDUCTION GEARBOX HOUSING
4-4-1
A.
4-4-1
Repair
of Corrosion
COMBUSTION CHAMBER LINER 4.
CRACK REPAIR
4-4-3
A.
4-4-3
Procedure
PART4 CONTENTS
Jun
10/2005Page
3
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
PAGE
SUBJECT SECTION 4
REPAIR
(Cont’d)
EXHAUST DUCT TURNING VANE 5.
REPLACEMENT A.
6.
IPRE-SB1151 ENGINES) 4-4-3
Procedure
4-4-3
INSTALLATION A.
4-4-5
Procedure
4-4-5
EXHAUST DUCT (PRE-SB1151 ENGINES) 7.
REPAIR A.
4-4-5
Procedure
4-4-5
COMPRESSOR INLET CASE 8.
REPAIR OF CORROSION A.
4-4-7
Procedure
4-4-7
GAS GENERATOR CASE 9.
REMOVAL OF DEFECTIVE RIVETS
4-4-8
A.
4-4-8
Procedure
10.
SELECTION OF REPLACEMENT RIVET
11.
SELECTION OF REPLACEMENT RIVET (Post-SB1143 AND ALL PT6A-20A
12.
15.
ENGINES)
4-4-8 4-4-8
Procedure
4-4-8
REPAIR A.
14.
4-4-8
INSTALLATION A.
13.
(Pre-SB1143 ENGINES)
4-4-10
Procedure
4-4-10
CORROSION REMOVAL
4-4-10
A.
4-4-10
Procedure
SHANKNUT REPLACEMENT
4-4-12
A.
4-4-12
Procedure
PART4 CONTENTS
Jun
10/2005Page
4
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
SUBJECT SECTION 4 16.
17.
19.
REPAIR
(Cont’d)
DIFFUSER EXIT DUCTS
4-4-12
A.
4-4-12
Procedure
REPLACEMENT REPAIR A.
18.
PAGE
(REF FIG. 04-104-8)
4-4-13
Procedure
4-4-13
FUEL NOZZLE BOLT REMOVAL
4-4-13
A.
4-4-13
Procedure
REPAIR FUEL NOZZLE PAD FRONT DAMAGED THREADED
HOLE(S) A.
4-4-15
Procedure
4-4-15
COMPRESSOR TURBINE SHROUD GRINDING 20.
OPERATION BREAKDOWN
4-4-15
A.
4-4-15
Procedure
ACCESSORY GEARBOX ASSEMBLY 21.
ACCESSORY GEARBOX HOUSING A.
Repair
4-4-21
of Corrosion
4-4-21
T5 BUS-BAR TERMINAL STRAPS OR LUGS 22.
REPLACEMENT
4-4-23
A.
4-4-23
Procedure
T5 TERMINAL BLOCK 23.
REPAIR
4-4-23
A.
4-4-23
Procedure
T5 THERMOCOUPLE HARNESS 24.
LUG REPLACEMENT A.
25.
(SINGLE INSULATION CRIMPING)
4-4-26
Procedure
LUG REPLACEMENT
4-4-26
(DOUBLE
INSULATION
CRIMPING)
PART4 CONTENTS
4-4-28
Jun
10/2005Page
5
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WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE OF CONTENTS
PAGE
SU BJ ECT
SECTION 4- REPAIR A. 26.
(Cont’d)
Procedure
4-4-28
BRAIDING REPAIR
4-4-28
A.
4-4-28
Procedure
FIRESEALS 27.
28.
CHAFING STRIP REPLACEMENT
4-4-32
A.
4-4-32
Procedure
WIDE MESH AIR INLET SCREEN
4-4-32
A.
4-4-32
Procedure
INLET FAIRING AND SUPPORT RING 29.
SEALING STRIP BONDING
4-4-32
A.
4-4-32
Procedure
INSULATED AND HEATED PNEUMATIC TUBES 30.
REPAIR
4-4-33
A.
4-4-33
Procedure
OIL FILTER CHECK VALVE 31.
LAPPING
4-4-33
A.
4-4-33
Procedure
IGNITION CURRENT REGULATOR BOX 32.
BRACKET REPAIR
SECTION 5
(WELDED TYPE)
4-4-33
SPECIAL LIMITS AND TORQUE RECOMMENDATIONS
1.
GENERAL
4-5-1
2.
TERMS AND SYMBOLS
4-5-1
A.
4-5-1
3.
Procedure
TORQUE APPLICATION
4-5-1
PART4 CONTENTS
Jun
10/2005Page
6
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WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART
PART SECTION LEP
DATE
FAG E
SECTION
1
Jun 10/2005
4-2-13
2
Jun 10/2005
4-2-14
1
Jun 10/2005
4-2-16
2
Jun 10/2005
4-2-17
3
Jun 10/2005
4-2-18
4
Jun 10/2005
4-2-19
5
Jun 10/2005
4-2-20
6
Jun 10/2005
4-2-21
4-2-15
Contents
7 deleted
4-2-22
8 deleted
4-2-23 4-2-24
List of
1
Jun 10/2005
4-2-25
Figures
2
Jun 10/2005
4-2-26
4-2-27
List of
1
Jun 10/2005
4-2-28
Tables
2 blank
Jun 10/2005
4-2-29
4-2-30
Section 1
4-1-1 4-1-2
4-1-3 4-1-4 4-1-5 4-1-6 4-1-7 4-1-8 4-1-9 4-1-10
Section 2
4-2-1 4-2-2 4-2-3 4-2-4
4-2-5 4-2-6 4-2-7 4-2-8
4-2-9 4-2-10
4-2-11 4-2-12
Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug
DATE
FAG E
Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug
27/2004 27/2004 27/2004 27/2004 27/2004 27/2004 27/2004 27/2004 27/2004
27/2004 27/2004 27/2004 27/2004 27/2004
27/2004 27/2004 27/2004
27/2004
27/2004 4-3-1
Feb 01/2002
27/2004
4-3-2
Feb 01/2002
27/2004
4-3-3
Feb 01/2002
27/2004
4-3-4
Feb 01/2002
27/2004
4-3-5
Feb 01/2002
27/2004
4-3-6
Feb 01/2002
4-4-1
Jun 10/2005
4-4-2
Jun 10/2005
27/2004
Section 3
27/2004 27/2004 27/2004
Section 4
4-4-3
Jun 10/2005
27/2004
4-4-4
Jun 10/2005
27/2004
4-4-5
Jun 10/2005
27/2004
4-4-6
Jun 10/2005
27/2004
4-4-7
Jun 10/2005
27/2004
4-4-8
Jun 10/2005
27/2004
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Jun 10/2005
27/2004
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Jun 10/2005
27/2004
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Jun 10/2005
27/2004
4-4-12
Jun 10/2005
27/2004
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Jun 10/2005
27/2004
4-4-14
Jun 10/2005
27/2004
4-4-15
Jun 10/2005
PART4 LEP
Jun
10/2005Page
1
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF EFFECTIVE PAGES
PART
PART
SECTION
Section 5
FAG E
DATE
SECTION
4-4-16
Jun 10/2005
4-5-20
4-4-17
Jun 10/2005
4-5-21
4-4-18
Jun 10/2005
4-5-22
4-4-19
Jun 10/2005
4-5-23
4-4-20
Jun 10/2005
4-5-24
4-4-21
Jun 10/2005
4-5-25 deleted
4-4-22
Jun 10/2005
4-5-26 deleted
4-4-23
Jun 10/2005
4-4-24
Jun 10/2005
4-4-25
Jun 10/2005
4-4-26
Jun 10/2005
4-4-27
Jun 10/2005
4-4-28
Jun 10/2005
4-4-29
Jun 10/2005
4-4-30
Jun 10/2005
4-4-31
Jun 10/2005
4-4-32
Jun 10/2005
4-4-33
Jun 10/2005
4-4-34
Jun 10/2005
4-4-35
Jun 10/2005
4-4-36 blank
Jun 10/2005
4-5-1 4-5-2 4-5-3
4-5-4 4-5-5 4-5-6
4-5-7 4-5-8
4-5-9 4-5-10 4-5-11 4-5-12
4-5-13 4-5-14
4-5-15 4-5-16
4-5-17 4-5-18
4-5-19
DATE
PAGE
Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004
Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004 Aug 27/2004
PART4 LEP
Jun
10/2005Page
2
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES PAGE
FIGURE Power Turbine Vanes
Integral
Figure
Power Turbine Vane
Power Turbine and Vane
4-2-1
4-2-4
Ring Figure Area
Ring
4-2-2
Figure
4-2-6
4-2-3
4-2-8
Power Turbine
Figure
4-2-4
4-2-11
Power Turbine
Figure
4-2-5
4-2-12
Installation No. 2
Sequence
Turbine Vane and Shroud
Bearing Scavenge Gearbox
Accessory
Disassembly
Centrifugal
4r2-20
with Gears Installed
Figure
4-2-8
4-2-22
Inlet Screen
Figure
Locking Figure
Breather Gearshaft Carbon Seal
Diffuser Exit Tubes Fixture
4-2-7
Diaphragm
Installation of Exhaust Duct
4-2-10
Inspection Figure
Gas Generator Case
Shanknut
Turning
Figure
Replacement Figure
Vane
4-3-5
4-4-2
Figure
Figure
4-4-6 4-4-3
4-4-9
4-4-5
4-4-14
4-4-6
4-4-16 4-4-7
Compressor Turbine Shroud Grinding Figure
T5 Harness
4-3-2
4-4-11
Repair/Replacement Figure
Lugs
4-3-1
4-4-4
Diffuser Exit Duct
and
4-2-30
4-3-2
Figure
Repair (Typical) Figure
Straps
4-2-28
4-4-4
Diffuser Exit Tube
Terminal
4-2-11
4-4-1
Repair (Typical) Figure
Shroud Cross Section
4-2-26
4-2-12
Installation of Blind Rivets in Gas Generator Case Rivet Gun
4-2-24
Replacement Figure
(Typical Examples) Figure
(PWC30153) Figure
Modified.Cherry
4-2-9
Acceptable Crack Limits Figure
Exhaust Duct Vane
4-2-15
Figure
of Starter-Generator Gearshaft
Scavenge Pump
4-2-6
Oil Transfer Tube Removal
Gearbox Installation
Accessory
Figure
´•4-4-17
4-4-8
4-4-18
4-4-9
4-4-22
4-4-10
4-4-24
Replacement Figure
Lug Replacement
Single
Insulation
4-4-11
Crimping Figure
4-4-25
4-4-12
PART 4 LIST OF FIGURES
4-4-27
J,,
10/2005Page
1
PRA~T
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF FIGURES
FIGURE
PAGE
T5 Harness T5 harness T5
Lug Replacement
Lug Replacement, Crimping
Thermocouple
Lapping
Ignition
Double Insulation
Harness Braid
of Oil Filter Check Valve
Current
Regulator
Procedure
Repair Figure
Figure
Crimping Figure Figure
4-4-13
4-4-29
4-4-14
4-4-30
4-4-15
4-4-31
4-4-16
Riveting of Detached Bracket
4-4-34 to Box
Figure
4-4-17
4-4-35
Fits
Clearances
Figure
4-5-1
(Sheet
Fits
Clearances
Figure
4-5-1
(Sheet 2)
4-5-10
Fits
Clearances
Figure
4-5-1
(Sheet 3)
4-5-11
Fits 8 Clearances
Figure
4-5-1
(Sheet 4)
4-5-12
Fits
Clearances
Figure
4-5-1
(Sheet 5)
4-5-13
Fits
Clearances
Figure
4-5-1
(Sheet 6)
4-5-14
Fits
Clearances
Figure
4-5-1
(Sheet 7)
4-5-15
Fits
Clearances
Figure
4-5-1
(Sheet 8)
4-5-16
Fits
Clearances
Figure
4-5-1
(Sheet 9)
4-5-17
Fits
Clearances
Figure
4-5-1
(Sheet 10)
4-5-18
Fits
Clearances
Figure
4-5-1
(Sheet 11)
4-5-19
Fits
Clearances
Figure
4-5-1
(Sheet 12)
4-5-20
Fits
Clearances
Figure
4-5-1
(Sheet 13)
4-5-21
Fits
Clearances
Figure
4-5-1
(Sheet 14)
4-5-22
Fits
Clearances
Figure
4-5-1
(Sheet 15)
4-5-23
Fits
Clearances
Figure
4-5-1
(Sheet 16)
4-5-24
1 of
16)
PART 4 LIST OF FIGURES
4-5-9
Jun
10/2005Page
2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
LIST OF TABLES
PAGE
TITLE TABLE 4-1-1,
Special
Tools
TABLE 4-4-1, Filler Rod
Specification
4-1-2
Combustion Chamber Liner
Repair
PART 4 LIST OF TABLES
4-4-3
Jun
10/20 5Page
1/2
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
´•I
PART 4
HEAVY MAINTENANCE
SECTION 1 1.
SPECIAL TOOLS
GENERAL The
Special
tools necessary for overhaul, are listed at the front of each page block of every and are referred to by PWC number in the text. The special tool
Chapter/Section/Subject numbers
are
summarized below. Note that for tool
ordering purposes
the letters PWC
are a
component part of the tool number.
Depending
upon the
location of the operator,
geographical
requests for the purchase of tools
should be addressed to: USA: Kell-Strom Tool
Company
Inc.
Street, PO. Box 240 Wethersfield, CT 06109
214 Church
USA TEL: 860-529-6851
or
1-800-851-6851 (USA and FAX: 860-257-9694
Canada)
http:~www. kell-strom.com E-mail: Ipriest~ kell-strom.com
Website:
Pratt
Whitney,
Tool
Support
Services
411 Silver
Lane, Mail Stop 129-20 East Hartford, CT 06118
USA TEL: 860-565-0140
or
1-800-PWA-TOOL (USA and Canada) FAX: 860-610-2670
E-mail:
lemirejwQpweh.com
CANADA and all other locations:
Whitney Canada, Tooling d’Auvergne (02AN1) Longueuil,Quebec Pratt
Solutions
333 rue
Canada
J4H 3Y3
TEL: 450-442-5400
or
1-800-3-115-5122 (Canada, USA and FAX: 450-442-5420
International)
http:~www. pwctoolingsolutions .com E-mail:
[email protected] or
Website:
frank.caruso Q pwc.ca
Page 4-1-1 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
or
Rasakti Inc. 148 Sylvestre St-Germain-de-G rantham, Quebec Canada JOC1KO or (24 hour service 1-888-RASAKTI (727-2584) (Canada FAX: 819-395-1100
TEL: 819-395-1111
number) USA)
Website: www.rasakti.com E-mail: i.
poirier@ rasakti.com
The
special required for
tools and fixture necessary for Heavy Maintenance are in addition to those Line Maintenance and are listed in Table 4-1-1 and illustrated on Figure 4-1-1. TABLE 4-1-1,
Special
Tools Maintenance Level
Part No.
Name
PWC30030
Puller
Line
Heavy X
(Replaced by PWC30310) PWC30035
Maintenance Stand
X
PWC30046-57
Puller
X
PWC30051-01
Base
X
PWC30051-02
Drift
X
PWC30052
Puller
X
(Replaced by PWC30046-57) PWC30054
Drift
X
PWC30122
Grinder
(used with PWC32122-50) (Replaced by PWC37918)
X
PWC30128-04
Threaded Puller
X
PWC30153
Locating
Fixture
X
PWC30180
Radius
Gage (Replaced by PWC30417)
X
PWC30226
Jackscrews
X
(Replaced by PWC32396) PWC30266
Mount
Ring (Replaced by PWC32081)
X
PWC30271-1 00
Spreader (Replaced by
X
PWC30274
Base
PWC31 771-1 00) X
Page 4-1-2 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-1-1,
SpecialTools (Cont’d) Maintenance Level
Part No.
Name
PWC30275
Split (Replaced by PWC32275)
X
PWC30289
Bracket
X
Line
Plate
Heavy
(Replaced by PWC32389)
´•I
PWC30310
Puller
X
PWC30312
Adapter (Replaced by PWC30408)
X
PWC30332
Wrench
X
PWC30335
Adapter (Replaced by PWC30409)
X
PWC30373
Puller/Pusher
X
PWC30408
Adapter
X
PWC30409
Adapter (Replaced by PWC32209)
X
PWC30417
Radius
Gage (Replaced by PWC32417)
X
PWC30425
Pliers
X
PWC30675
Drift
X
PWC30712
Adapter
X
PWC30800
Engine Stand (Replaced by PWC34300)
X
PWC30854
Drift
X
PWC30855
Compressor (Replaced by PWC50502)
X
PWC31771-100
Spreader
X
PWC32122-50
Grinding
Wheel
(used
with
X
PWC301 22)
(Replaced by PWC32528)
PWC32081’
Mount
PWC32209
Adapter
PWC32275
Ring
X ´•X
Split Ring
X
PWC32380
Radius
X
PWC32389
Bracket
X
PWC32396
Jackscrews
X
I
Gage
Page 4-1-3 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-1-1,
SpecialTools (Cont’d) Maintenance Level
Line
Heavy
Part No.
Name
PWC32417
Radius
Gage (Replaced by PWC32380)
X
PWC32483
Cutter
X
PWC32484
Gage
X
PWC32528
Grinding
Wheel
PWC3791
(used
with
X
8) X
PWC34300
Engine Stand (Replaced by PWC51140)
PWC37918
Grinder
PWC50064-1 00
Kit, Drill Jig
X
PWC50064-200
Centre Drill
X
(used
with
PWC32528)
X
(Replacement Only; part’of PWC50064-100 kit) PWC50502
Compressor
X
PWC51140
Engine Stand
X
Page 4-1-4 Aug 27/2004
PRA~T
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MAINTENANCE MANUAL
MANUAL PART NO. 3015442
PWC30030
PWC30051-01
PVVC30054
PWC30051-02
PWC30122
TOOL NOT
ILLUSTRATED
PWC30035
TOOL
NOT ILLUSTRATED
a31: PVVC30046-57
PWC30052
PWC30128-04
I´•-´•~
Special Tool
Illustrations
Page 4-1-5 Aug 27/2004
PRA~T
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PWC30275
PWC30266
PWC30153
TOOL
TOOL
TOOL
NOT
NOT
NOT
ILLUSTRATED
ILLUSTRATED
ILLUSTRATED
PWC30289
PWC30271-100
PWC30180
TOOL
I
I
NOT
I
I
NOT
ILLUSTRATED
I
I
ILLUSTRATED
PWC30226
PWC30310
PWC30274
Special
TOOL
Tool Illustrations
Page 4-1-6 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PWC30312
PWC30373
PWC30417
PWC30332
PWC30408
PWC30425
PWC30335
PWC30409
PWC30675
TOOL NOT ILLUSTRATED
Special
Tool Illustrations
Page 4-1-7 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PWC30855
PWC32081
PWC30800
PWC31771-100
PWC32209
PWC30854
PWC32122-50
PWC32275
PWC30712
’3
3‘;
I
Special
Tool Illustrations
Page 4-1-8 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PWC32380
PWC32417
PWC32528
PWC32389
PWC32483
PWC34300
PWC32396
PWC32484
PWC37918
Special
Tool Illustrations
Page 4-1-9 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PWC50064-100
PWC51140
PWC50064-200
TOOL
NOT ILLUSTRATED
PWC50502
Special
Tool Illustrations
Page 4-1-10 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
HEAVY MAINTENANCE
PART 4
SECTION 2
REMOVAL AND INSTALLATION
INTRODUCTION 1.
GENERAL A.
removing and installing engine components during Having completed repairs described, ground testing should be carried out to check for mechanical soundness and correct operational parameters. These instructions are presented with the assumption that standard practices described in Part 2, Standard Practices, have been read and fully understood.
This section contains instructions for
heavy
B.
maintenance.
Refer to Section 1, preceding, for maintenance.
special
tools and fixtures which will be
required during
heavy C.
When the nature of work to be performed requires that an engine be supported in other than the horizontal position, Stand (PWC30800) or its equivalent must be employed. Used in conjunction with the stand are Mount Ring (PWC30266), Brackets (PWC30289) and
Adapters (PWC30712).
ENGINE STANDS INSTALLATION OF ENGINE IN STAND A.
Procedure
(1)
(2)
Attach
engine sling ~(PWC30036)
points.
Take up slack.
or
(PWC32327)
as
applicable,
to
Remove all drain plugs and No. 2 bearing scavenge oil line. Make completely drained (Refer to Part 2, Standard Practices).
engine lifting
sure
that the oil
is
(3)
(4)
Attach three brackets (PWC30289) to engine mounting pads on gas generator case. Secure each bracket with four bolts. Tighten bolts, torque 225 to 250 Ib.in. and lockwire heads using a single strand of wire. If mount
ring (PWC30266)
washers, and
(5)
Split
(6)
Attach
mount
remove
ring
larger
at
is installed in stand
mount
(PWC30800), ring (with adapters PWC30712)
four bolts and from stand.
remove
lockplates by removing four bolts from each lockplate.
mount
ring segment
to two brackets
(PWC30289)
on
engine,
with six
bolts and nuts. Use two washers
TOP is located
over
mounting
on each bolt. Make sure that the section marked pad at 12 o’clock position. Fingertighten the six
nuts.
Page 4-2-1 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Attach smaller mount
(7)
ring segment
to
bracket (PWC30289) on engine, each bolt. Fingertighten the three
remaining
with three bolts and nuts. Use two washers
on
nuts.
Tighten
washers.
3.
adapters (PWC30712) Tighten screws firmly.
Install two
(9)
and
ring segments and lockplates with eight bolts, nuts firmly on three bracket attachment bolts.
Secure
(8)
on
mount
(10)
Carefully lower engine into stand, and washers and nuts. Tighten nuts firmly.
(11)
Remove
with four machine
ring
secure
tighten
bolts
firmly.
screws
to stand with six
adapters
and
bolts,
engine sling.
REMOVAL OF ENGINE FROM STAND A.
Procedure Attach
(1)
applicable sling (PWC30036)
or
(PWC32327)
to
engine lifting points
and
take up slack.
(2)
Remove six nuts, washers and bolts securing adapters ring PWC30266) to stand (PWC30800).
(PWC30712) (attached
to
mount
clear of stand.
(3)
Raise
(4)
Remove
(5)
Detach mount
(6)
Remove nuts, bolts and washers securing mount attached to engine. Remove mount ring.
(7)
Remove 12 bolts
engine
adapters
from mount
ring segments by removing
securing
POWER TURBINE VANES 4.
ring by removing
screws
four bolts from each
three brackets to
(PRE-SB1OG1
four machine
ring
and washers.
lockplate.
to three brackets
mounting pads
on
AND POST-SB1246
(PWC30289),
gas generator
case.
ENGINES)
REPLACEMENT A.
Should power turbine vanes require replacement, it is desirable to replace them with new vanes of an identical class. However, if original class of a defective vane cannot be identified during disassembly, vanes of any class may be utilized provided that the total class average is within limits (Ref. No. 359, Fits Clearances). NOTE:
To arrive at class average, add together the class divide the total figure by the number of vanes.
markingsbf ail
Vanes
and
Page 4-2-2 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
5.
REMOVAL
A.
Procedure
(1) (2)
4-2-1 and
(See Figures
Remove power section PT6A-20
4-2-3) to Part
(Refer
3, Section 2, Removal
Installation).
(Pre-SB1073): Remove T5 thermocouple harness and probes, Installation). ring Refer to Part 3, Section 2, Removal
and
containment
(3)
Post-SB1246: Remove bolts at 1 and 7 o’clock positions and Figure 4-2-3) from top and bottom front face of Flange D.
(4)
Remove assembly of duct. Place assembly
(5) (6)
Lift stater Remove
housing
vanes on
clear of
packing (3)
and stater
(7, Figure 4-2-1)
bench, leading edge of
assembly of
from around outer
vanes
housing (9) facing down.
and baffle
vanes
platform of
half
remove
rings (1,
from exhaust
(6).
vanes.
Designate
adjacent
vane
to offset hole as No. 1, and number remaining vanes in clockwise sequence. This will make sure that the original relationship between vanes during reassembly.
(7)
Remove
vane
sealing strip
cover
(2)
and
sealing strip (1)
from outer
platform
of
vanes.
(8)
Remove suitable
6.
vanes
and
protective
remove vee
packings (4)
and
(5)
from baffle
(6).
Place
vanes
in
container.
INSTALLATION A.
Procedure
(1)
(See Figures
Open Vee interstage NOTE:
(2)
(3)
4-2-1 and
of packings baffle (6).
Packings engine.
4-2-3).
(4 and 5, Figure 4-2-1)
must be installed with Vee
and wrap around outer diameter of
openings facing
toward
rear
of
Install 19 vanes (7, Figure 4-2-1) over Vee packings on baffle (6), making sure that the vane pegs project through locating holes in baffle. Check vanes are in correct order with No. 1 adjacent to offset hole and remainder in clockwise sequence.
sealing strip (1) over outer platform Secure strip with cover (2).
Locate
of vanes,
mating
holes in
strip
with pegs
on vanes.
(4)
Install Vee section
(5)
packing (3) facing rear.
Lower turbine
vane
enters groove in
(6)
Install
as
stater
shown around outer
housing (9)
platform
over vanes
of vanes, open side of Vee
until outer
platform
rim of
vanes
housing.
complete assembly
on
exhaust duct,
Flange D,
with offset
holes aligned.
Page 4-2-3 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
10 7
7
4
3 2
1 6
5
10 1
2
Pre-SB1OG1
Engines
C1703A
Power Turbine Vanes
Figure
4-2-1
Page 4-2-4 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Key 1. 2.
3. 4. 5.
Cover
Baffle
7.
Vane
8.
Bolt
9.
Power Turbine Stater
(Post-SB1246): Use
4-2-1
6.
11.
NOTE:
Figure
Sealing Strip Sealing Strip Vee Packing Vee Packing Vee Packing
10.
(7)
to
(19 ea)
Housing Interstage Sealing Ring(s) (SB1218) Seal Ring Retaining Plate
Secure
Alignment
assembly
of turbine
vanes
to exhaust duct as follows:
(PWC32212) at several locations through the alignment of all mounting holes.
Pins
to make sure that
(a)
Install upper half ring (1, Figure 4-2-3) on front face of offset hole. Secure assembly with one bolt at 1 o’clock
(b)
Install lower half ring on front face of Flange D and align Secure assembly with one bolt at 7 o’clock position.
(c) Tighten bolts at alignment pins.
1 and 7 o’clock
positions
and
torque 32
(8)
Install T5 harness assembly and probes, and containment Section 2, Removal Installation).
(9)
Carry
out
loop
Flange D position.
half rings
and
mounting
align
holes.
to 36 Ib.in. Remove
ring (Refer
to Part
3,
and resistance checks of T5 sensing system and, if necessary, heat probes (Refer to Part 3, Section 2, Inspection).
response check of
(10)
install power section
(Refer
to Part
POWER TURBINE VANE RING PT6A-20
3, Section 2, Removal 8 Installation).
(POST-SB1OG1)
ALL PT6A-20A ENGINES AND ALL
POST-S B1 246 7.
GENERAL A.
ring is to be replaced, it is recommended that a complete stater assembly (vane interstage baffle), having vane ring of identical class, be used as replacement. In the unlikely event that original class of defective vane ring cannot be determined, a vane ring of any class may be fitted, providing class average is within limits specified (Ref. No. 359, Fits 8 Clearances). If
vane
ring
and
Page 4-2-5 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
3)
PT6A20
(Post-SB1061)
(4)
and all
Integral
(5
PT6A-?0A engines,
Power Turbine Vane
Figure
and Pre-SB1246
C5288
Ring
4-2-2
Page 4-2-6 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
4-2-2
1.
Exhaust Duct
2.
Power Turbine Shroud
Ring Reinforcing Ring Stater Housing Assembly T5 Probe Mounting Boss Interstage Seal Ring(s) (SB1218) Compressor Turbine Shroud Housing PT Vane and Baffle Assembly
3. 4. 5. 6. 7.
8. 8.
to
REMOVAL A.
Procedure
(1)
(See Figures
4-2-2 and
4-2-3)
With power section removed and suspended from appropriate sling, or supported on bench with wooden blocks, remove T5 harness assembly (Pre-SB1073) or thermocouple bus-bar and probes (Referto Part 3, Section 2, Removal Installation).
NOTE:
Pre-SB1246, Post-SB1177: The harness, bus-bar and probes need
not
lacing and release harness from clips on exhaust duct. Remove 12 bolts at Flange D and remove complete assembly; withdraw vane ring from stater housing. Exercise care not to damage probes. be removed. Cut
(2)
Remove containment
CAUTION:
9.
ring (2, Figure 4-2-3) by removing
ten bolts.
TO PREVENT POSSIBLE DAMAGE TO T5 HARNESS, FOLD LEADS AND TEMPORARILY TAPE TO END OF HARNESS.
(3)
Remove bolts at 1 and 7 o’clock positions, and remove half bottom of front face of Flange D of exhaust duct (8).
(4)
Remove stater
(5)
Remove stater assembly from housing. If difficulty is experienced tap gently on rim of stater using a soft faced hammer.
housing (3) complete
with stater
rings (1) from top and
assembly (6), by pulling
on vanes.
during removal,
INSTALLATION A.
Procedure NOTE:
(See Figures
4-2-2 and
4-2-3)
Pre-SB1246, Post-SB1177: Exercising care to prevent damage to probes, or undue pressure applied to bus-bar, or harness assembly (Pre-SB1073), install vane ring in stater housing and reinstall complete assembly on exhaust duct. Secure assembly with 12 bolts, torque 32 to 36 Ib.in. and lockwire. (See
Figure 4-2-2).
Secure harness to
clips
on
exhaust duct with lockwire
lacing.
Page 4-2-7 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1
3
Post-SB1OG1 and Post-SB1246
Power Turbine and Vane
Figure
Ring
Engines
4
C3800
Area
4-2-3
Page 4-2-8 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
CAUTION:
(1) (2)
Invert
4-2-3
1.
Half
Containment
3.
Stater
4.
T5
5.
Power Turbine Disk
Ring
Ring Housing Thermocouple Probe
6.
Vane
7.
Turbine Shroud
8.
Exhaust Duct
(Stator Assembly)
ON ENGINES INCORPORATING THE INTENT OF SERVICE BULLETINS SB1177 AND SB1212 THERE ARE ONLY EIGHT T5 PROBES IN THE STATOR HOUSING AND TEN SLOTS IN THE VANE RING. THE TWO CLOSELY SPACED SLOTS ARE NOT USED AND MUST NOT ALIGN WITH ANY OF THE EIGHT PROBES.
Figure 4-2-3) in housing (3) and align index marks. housing are fully mated with slots in vane ring.
assembly, making sure that the stater and housing do not separate. Holding (6) of stater, install complete assembly on Flange D of exhaust duct (8) and
align offset (3)
Figure
2.
Locate stater assembly (6, Make sure that the lugs on
vanes
to
Secure
holes.
assembly
NOTE:
Use
to exhaust duct in the
following
manner:
Alignment Pins (PWC32212) at several sure alignment of all mounting holes.
locations
through half rings
to
make
(a)
Install top half
assembly (b)
ring (1)
at 1 o’clock
on
front face of
position
with
Flange D and align offset holes. Secure silver-plated bolt, fingertight only.
one
Install bottom half ring on front face of Flange D and align mounting holes. Secure assembly at 7 o’clock position with one silver-plated bolt, fingertight
only. (4)
(5)
Make sure that the harness is clear of any residual tape adhesive solvent (PWC11-027)(AMS31 60). Route leads of harness
housing. Align silver-plated bolts. on
stater
12 bolts at
using petroleum
face of stater assembly and place containment ring offset holes, remove alignment pins and secure with ten
over
Flange D; torque
(2)
32 to 36 Ib.in., and lockwire.
(6)
Tighten
(7)
Install T5 thermocouple harness assembly and bus-bar (Refer to Part 3, Section 2, Removal
(8)
After installation of power section loop and resistance checks of T5
probes (Pre-SB1073), Installation).
(refer to Part 3, Removal sensing system ´•(Refer to
or
probes
and
Installation), carry out Part 3´•; !Section 3,
Inspection).
Page 4-2-9 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
10.
REMOVAL (Pre-SB1046 A.
Procedure
ENGINES)
(See Figures
4-2-1 and
4-2-3)
interstage baffle
Remove turbine
(2)
Unlock tabwasher and
remove
NOTE:
nuts are match-marked to bolts for
Disk
retaining
and
Remove power turbine shaft rotor air seal.
(4)
Remove power turbine disk and blade
NOTE:
bolts which is coat of
lubricant(PWC06-036)
Install power turbine disk and blade
on
(3)
Install power turbine shaft rotor air seal.
(4)
Install tabwasher and numbered nuts
that disk is
Install turbine
Procedure
(1)
(2) (3)
of
over
shroud is
on
portion
five bolts.
aligned
respective
of bolts.
with offset hole
turbine disk
one
mounting
properly seated, tighten nuts, torque (Ref.
bolts.
No. 539, Fits
baffle and
vane
assembly (Ref.
Paras. 6.
or
7.).
ENGINES)
(See Figure 4-2-5)
Remove turbine
Install wrench from
one
lock tabwashers.
interstage
REMOVAL (Post-SB1046
to threaded
assembly
Make sure that index mark exhaust duct.
sure
by
offset.
(2)
a
light
slightly
Apply
Clearances) and
A.
assembly using puller (PWC30310).
(See Figure 4-2-4)
NOTE:
12.
purposes and
balancing
ENGINES)
(1)
(6)
nuts.
Correct installation of turbine disk and seal rotor to shaft is done
Make
8.).
sure that the original location is maintained at reassembly, index mark power turbine shroud in line with offset hole on exhaust duct prior to removal of disk and blade assembly.
retaining
(5)
or
To make
INSTALLATION (Pre-SB1046 Procedure
retaining
Paras. 4.
original positions.
(3)
NOTE:
A.
vane
turbine disk
must be installed in their
11.
assembly (Ref.
(1)
interstage
baffle and
(6) (PWC30332)
at
vane
Flange
assembly (Ref.
Paras 4.
D of exhaust duct to
or
8.).
prevent turbine disk
rotating.
Insert
protector sleeve (7) (PWC30336) into centerbore of turbine disk.
Page 4-2-10 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C
_C
OFFSET HOLE
’X’ MARK
i
c~C, (Q 6
P~ES
Pre-SB1046
Engines
C212
Power Turbine Figure 4-2-4
Page 4-2-11 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
DIRECTION FOR TORQUING
9
’i
Post-SB1046 and all PT6A20A
Engines
C486C
Power Turbine
Figure
4-2-5
Page 4-2-12 Aug 27/2004
WHITNEY CANADA
PRA~T
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
4-2-5
Turbine
Bolt
3.
Retaining Cupwasher Dogs
4.
Threads
5.
Shoulder
6.
Wrench
7.
Protector Sleeve
8.
Socket and Extension
9.
Torque
1. 2.
tool
(PWC30332) (PWC30336)
Wrench
Using unlocking
(5)
Remove unlocking tool and break torque and extension.
(6)
Remove bolt and withdraw disk sleeve. NOTE:
To make
(PWC30335),
unlock
(4)
sure
of the
line with offset hole
keywasher
on
at
retaining
bolt
retaining
using
using puller (PWC30403).
bolt.
conventional socket
Remove the teflon
original location, index mark power turbine shroud exhaust duct prior to removal of disk and blade
in
on
assembly. INSTALLATION A.
Procedure
(1)
(Post-SB1046 AND ALL PT6A-20A ENGINES)
(See Figure 4-2-5)
Lightly disk
smear
on
NOTE:
lubricant
(PWC06-036).
Install bladed
Make sure that the index mark exhaust duct.
on
shroud is
aligned
with offset hole
one
(2)
Use new keywasher that is dry and free from burrs. Lightly smear inside of washer with lubricant (PWC06-036). Apply same lubricant to shoulder and threaded portion of bolt.
(3)
Insert
(4)
keywasher
Install wrench disk from
1
splines of turbine disk hub with master splines.
shaft, aligning
and
retaining
(PWC30332) rotating.
at
bolt into disk centerbore.
Flange
D of exhaust duct to
(5)
Tighten retaining bolt and double torque (Ref. using a conventional socket and extension.
(6)
Using locking tool (PWC30458), lock scratch disk centerbore.
(7)
install turbine
interstage baffle
and
No. 541
or
prevent power turbine
1283, Fits
Clearances)
keywasher. Withdraw tool, taking
vane
assembly (Ref.
Paras. 6.
or
care
not to
7.).
Page 4-2-13 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR TURBINE VANES AND SHROUD SEGMENTS 14.
REPLACEMENT OF VANES A.
In the event of compressor turbine vanes requiring replacement, it is desirable to them with new vanes of identical class. However, if original class of a defective vane cannot be identified, vanes of any class may be utilized provided that the total class average is equal to that determined at manufacture (first run engines) or last
replace
15.
(overhauled engines).
NOTE:
To arrive at a class average, add together class divide total figure by number of vanes.
markings
of all
vanes
and
REPLACEMENT OF SEGMENTS A.
16.
overhaul
For shroud segment classification guide and grinding when Part 4, Section 4, Repair, Table 4-4-2, following.
replacing segments,
refer to
REMOVAL A.
Procedure
NOTE:
(1)
(See Figure 4-2-6)
"X" Pre-SB1147) (3 segments), Post-SB1147 "Y"- Pre-SB1147/Post-SB1147 (1 segment)
Remove combustion chamber liner
(Refer
to Part
(13 segments)
3, Section 2, Removal
Installation). (2) (3)
Remove compressor turbine disk Remove
eight
bolts
(Refer
to Part
securing- compressor
3, Section 2, Removal
turbine
vane
assembly
to
no.
Installation). 2
bearing
cover.
(4)
Withdraw combustion chambersmall exit duct and compressor turbine
vane
assembly. (5)
securing -~compressor turbine shroud housing land T4 PT6A-6, -6A and -6B engines) to combustion chamber thermocouple small exit duct. Separate shroud housing from small exit duct and remove heat shield and four shroud segments. Remove and discard ceramic fiber cord from outer platforms of shroud segments. Pre-SB1147: Remove 12 bolts
harness
(6)
on
Post-SB1147: Remove 12 bolts securing compressor turbine shroud housing land thermocouple harness on PT6A-6, -6A and -6B engines) to combustion chamber small exit duct. Separate shroud~housing from small exit duct, remove heat shield and 14 shroud segments.
T4
(7)
Designate vane adjacent to offset hole at 12 o’clock position as No. 1, and number remaining vanes in a clockwise sequence. This will make sure correct relationship between vanes at reassembly. Pre-SB1172:
Page 4-2-14 Aug 27/2004
PRA~TT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
VANE SUPPORT
VEE PACKING
SLAVE PREFORMED PACKING COMPRESSOR TURBINE VANES (29) DETAIL A
SMALL EXIT DUCT DETAIL
INSTALLATION OF COMPRESSOR TURBINE VANES ON VANE SUPPORT
B
INSTALLATION OF VANE SUPPORT ASSEMBLY IN SMALL EXIT DUCT
CAUTION REMOVE SLAVE PREFORMED PACKING FROM VANE OUTER PLATFORM
j
SHORT SEGMENT ’X’ snRouD
LONG SEGMENT
IL
XJ
HOUSING
SMALL EXIT DUCT DETAIL
DETAIL
C
INSTALLATION OF SHROUD HOUSING IN SMALL EXIT DUCT
INSTALLATION OF COMPRESSOR TURBINE SHROUD SEGMENTS
Post-SB1144 and Pre-SB1172 Installation
D
Sequence Turbine Figure 4-2-6
Engines
C41510
Vane and Shroud
Page 4-2-15 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(8)
Separate compressor
turbine inner
support from combustion chamber small
vane
exit duct.
(9)
17.
Remove Vee packing
from
strip
vane
outer
platform.
store them in
suitable container.
(10)
Remove
(11)
Remove and discard all ceramic fiber cords
(12)
Post-SB1172: Remove support clamp from bore of inner
vanes
from
vane
support and
on vane
a
support. vane
support.
INSTALLATION A.
Procedure
(1)
Assemble and install compressor turbine shroud housing as follows:
vane
ring assembly,
small exit duct and
(a) Cut
three lengths of reinforced ceramic fiber cord slightly longer than circumference of front outer groove of vane support. Entwine cords to form a single length and install in front groove of support. make sure no gap exists
where cord ends meet.
(b)
Prior to
assembly of compressor turbine vane ring assembly, arrange number sequence and check each vane in turn as follows: I
Free fit of
vane
locating pin
2
Free fit of
vane
outer
NOTE:
to related hole in inner vane
platform
vanes
in
support.
to related groove and slots in small exit duct.
difficulty is experienced when checking recoated or refurbished coating may be removed from affected pins, lugs and/or platforms to provide free fit of vane. Coating must not be removed from airfoil surfaces. If dimensional discrepancies or distortion of any vane prevents proper fit, affected vane must be replaced with If
vanes,
a vane
(c)
of
same
Post-SB1172: Installsupport locates inside slotted flange.
class
clamp
area.
in
vane
inner support
so
that
clamp spigot
(d) Install 29 vanes of appropriate class average (Ref. Para. 14.) on vane support, locating vane pins in support holes. Start with No. 1 vane and proceed clockwise in numerical order. Temporarily retain installed vanes in position with a slave preformed packing. (e) Assemble i
vane
support assembly and small exit duct
as
follows:
Post-SB1144/Pre-SB1172: (Ref. Fig. 4-2-6) Locate vane packing around Vee opening facing vane leading edges. of with vanes, platforms Install vane assembly in small exit duct so that offset hole in vane support flange aligns with grooved lug on duct flange. Locate vane outer platform lugs in duct grooves. Remove slave preformed packing. outer
Page 4-2-16 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(f)
2
Post-SB1172: Insert vane outer support into small exit duct so that grooved lugs are aligned. Locate vane packing around outer platforms of vanes with Vee opening facing vane leading edges. Install inner support and vane assembly in outer support, mating small lugs on vane outer platforms with grooves in outer support. Remove slave preformed packing.
3
Check that a parallel gap of 0.002 and 0.005 inch exists between inner platforms of vanes. If gap exceeds 0.005 inch, rotate vanes, or if necessary, replace appropriate vanes. If gap is less than 0.002 inch, the platforms may be stoned to rectify.
Pre-SB1147: Install shroud segments, heat shield and shroud follows:
housing
as
1
Select appropriate class of shroud to match tip diameter of compressor turbine (Refer to Part 4, Section 4, Repair, Table 4-4-2).
2
Install four shroud segments tone long, three short) on vane outer platforms (Ref. Fig. 4-2-6), locating segment lugs between vane lugs. Make sure that one end of long segment aligns with top of vane support and that other end runs counterclockwise, when looking at trailing edges of vanes.
i!
Install heat shield over segments, place shroud bolt holes and press housing into position.
housing
over
assembly,
align (g)
Post-SB1147: Install shroud segments, heat shield and shroud follows:
housing
as
1
Select appropriate class of shroud to match tip diameter of compressor turbine (Refer to Part 4, Section 4, Repair, Table 4-4-2).
2
Install 14 shroud segments tone long, 13 short) on vane outer platforms, locating segment lugs between vane lugs. Make sure that one end of long segment aligns with grooved lug on outer support flange and that outer end runs counterclockwise when looking at trailing edges of vanes. Install short vanes in clockwise progression.
3
Install heat shield
on
lip of segments, straightening segments
to conform
with heat shield. 4
Using clean engine oil, lightly housing.
5
Install shroud
housing
over
lubricate groove in inner diameter of shroud
segments, lightly tapping it into position by
hand. Invert
and check that heat shield is
6
assembly housing lip.
positioned correctly
7
Using a small pick or screwdriver, adjust segments into position behind heat shield.
until shroud
on
lips drop
Page 4-2-17 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
8
Strike small exit duct
sharply by
hand to seat
flange fully
on
shroud
housing.
(h)
On PT6A-6, -6A and -6B CAUTION:
1
Install T4
engines,
install T4
thermocouple assembly
as
follows:
TO MINIMIZE THE POSSIBILITY OF DAMAGE, AVOID FLEXING THE BRAID BETWEEN FERRULES. WHEN TERMINAL BLOCK IS NOT ATTACHED TO GAS GENERATOR CASE, TEMPORARILY SECURE IT TO BUS-BAR.
thermocouple assembly
so
that when
grooved lug
of small exit
duct flange is at 12 o’clock (looking toward rear of engine), thermocouple bracket nearest cable connection is at 9 o’clock; this will make sure that cable is in correct position in relation to retaining clips on combustion chamber liner. Secure T4 bolts.
Specification (i)
thermocouple
Tighten bolts, torque 32
Install duct and
and shroud housing to small exit duct with 12 to 36 Ib.in. and lock with lockwire,
MS9226-03.
vane
assembly
in gas
generator
case as
follows:
L
Post-SBt 144/Pre-SB1172: Install assembly so that grooved lug on small exit duct flange is at 12 o’clock, and offset holes in vane support flange and No. 2 bearing cover are aligned. Secure assembly to bearing cover with eight silver-plated bolts. Tighten bolts, torque (Ref. No. 554, Fits Clearances), and lockwire in pairs. Using a 0.001 inch feeler gage, check for correct seating of vane support assembly.
2
assembly so that grooved or X-marked lugs of vane and small exit duct are at 12 o’clock position. Rotate support each direction until engagement of lugs on large exit duct with in assembly slots in inner vent support is felt. Observe through holes in clamp plate that lugs are engaged and inner support is correctly seated. There should be no clearance between clamp plate and large exit duct. Align offset hole in clamp plate with similar hole in No. 2 bearing cover flange and secure with eight silver-plated bolts. Tighten bolts, torque (Ref. No. 554, Fits Clearances) and lockwire in pairs.
Post-SB1172: Install
outer
LARGE EXIT DUCT 18.
REMOVAL A.
Procedure
(1)
Remove combustion chamber liner and compressor turbine disk Section 2, Removal
(Refer
to Part
3,
Installation).
(2)
Remove compressor turbine assembly (Ref. Para. 16.).
(3)
Apply hand pressure evenly on each side of centerbore of large exit duct and, simultaneously, rotate duct counterclockwise approximately 20 degrees to disengage duct from support brackets in gas generator case.
vane
ring,
shroud
housing
and small exit duct
Page 4-2-18 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(4)
19.
Withdraw duct from gas generator case. Remove and discard ceramic fiber cord from outer circumference of duct flange.
INSTALLATION A.
Procedure NOTE:
(1)
If SB1172 is embodied, then the
large
exit duct Post-SB1182 must be installed.
Position duct in gas generator case so that offset hole in duct is approximately degrees counterclockwise from offset hole in No. 2 bearing cover.
20
(2)
Rotate duct in
a clockwise direction to align offset holes; scallops be locked in position by brackets in gas generator case.
now
(3)
Install compressor turbine Para. 17.).
vane
ring,
shroud
housing
on
ducts should
assembly
and small exit duct
(Ref.
(4)
Install compressor turbine disk assembly and combustion chamber liner Part 3, Section 2, Removal Installation).
(Refer
to
STARTER-GENERATOR GEARSHAFT AND CENTRIFUGAL BREATHER CARBON SEAL 20.
REMOVAL A.
Procedure
NOTE:
(1) (2)
(See Figures 4-2-7,
4-2-8 and
4-2-9)
centrifugal breather gearshaft can only be obtained by removing accessory gearbox from compressor inlet case. Removal may be accomplished while the engine is installed in the aircraft. However, it is recommended that the engine be removed to obtain maximum accessibility. Access to
Drain oil tank Remove
(compressor inlet case) (Ref. Part 2,
engine
from airframe
(Ref.
General
Aircraft Maintenance
Procedures).
Manual),
and
secure
in
suitable stand.
(3)
Remove accessories, fuel heater oil lines, accessory pad covers and oil tubes, (Ref. Part 3, Section 2, Removal Installation). Install dust caps on all open ends of external lines and fittings.
(4)
Disconnect No. 2 bearing scavenge oil tube and remove short oil transfer tube from compressor inlet case using puller (PWC30128-04) (Ref. Fig. 4-2-7).
(5)
Remove filler tube
retaining ring
and withdraw filler tube from accessory
gearbox
housing. (6)
Withdraw oil filter
housing (Ref.
Part 3, Section 2, Removal
Installation).
Page 4-2-19 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C
g~i
I
C505D
No. 2
Bearing Scavenge Oil Transfer Figure 4-2-7
Tube Removal
Page 4-2-20 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
cnuTloN:
THE ACCESSORY GEARBOX DIAPHRAGM IS SECURED TO THE ACCESSORY HOUSING BY FOUR COUNTERSUNK SCREWS AND SELF-LOCKING NUTS. ASSUMING THE NUT AT THE 12 O’CLOCK POSITION TO BE NO. 1,THESE NUTS ARE 4TH, 8TH, 14TH AND 18TH IN CLOCKWISE ROTATION AND MUST NOT BE REMOVED AT THIS STAG E.
Remove
and accessory
(7)
self-locking nuts securing accessory gearbox housing diaphragm to compressor inlet case at Flange G.
(8)
Pre-SB1045 and engines with SB1104 embodied, separate accessory gearbox with attached diaphragm from compressor inlet case, holding the assembly in a horizontal position and withdrawing slowly rearward.
(9)
Post-SB1045, Post-SB1134 and all PT6A-20A engines, separate accessory gearbox with attached
(a)
diaphragm
from compressor inlet
Remove center boss hexagon Determine location of lock ball
case as
follows:
plug from accessory gearbox rear case. (8, Fig. 4-2-10) by viewing through center
boss
hole.
(b)
Rotate compressor by hand until notch on washer at rear hub (9) is at 3 o’clock position. This will make sure that the lock ball in the locking arrangement is at the
(c)
top of the compressor
rear
hub before
disengagement.
Insert pusher (PWC30373) through housing center boss into coupling shaft (2). Turn knurled body into center boss. Do not rotate pusher T handle once the tool is secured. Pull
(d) Handtighten
nut on
on
T handle until lock ball is
pusher enough
to
remove
fully disengaged.
all slackness
along coupling
shaft.
(e) Separate accessory gearbox with attached diaphragm from compressor inlet case using jackscrews (PWC30226). If, during removal of accessory gearbox the lock ball drops out of the locking arrangement, retrieve the lock ball from No. 1 bearing housing, or oil scavenge passage in compressor inlet case. (f)
and washer
(10)
(8) from locking arrangement on top of compressor rear hub retaining ring (3), washer (4), key (5), expander spring (6) (7) from inside of hub. Discard lock ball and expander spring.
Remove lock ball and
coupling (9),
Remove transfer tubes, oil tank center tube and
large preformed packing
from
diaphragm flange. (11)
Place accessory gearbox on bench, diaphragm facing downward. Remove four locknuts, washer and countersunk screws securing diaphragm to gearbox.
(12)
Separate diaphragm
(13)
Remove
assembly
Remove
flanged
(14)
from
of
roller
gearbox, using
a
soft faced hammer if necessary.
gearshaft (2, Fig. 4-2-8)
bearing
from
and
impeller (3) from diaphragm.
diaphragm by unlocking keywasher
and
removing
three bolts.
Page 4-2-21 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
9 9
DETAIL
A
8 6
C148C
Accessory Gearbox Diaphragm with Gears Figure 4-2-8
Installed
Page 4-2-22 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
Figure
4-2-8
1.
Flange G
2.
Starter-Generator Gearshaft
3. 4.
Centrifugal Breather Impeller Accessory Gearbox Drive Gearshaft
5.
Fuel Control Gearshaft
6.
Pressu re Oil
7.
Vacuum
Pump Pump and
and
Ng
Tachomete r-Generato r Gearshaft
Scavenge Pump Power Takeoff Gearshaft (Optional) Hydraulic Pump Gearshaft (Optional) Preformed Packing Preformed Packing Retaining Ring
8. 9. 10. 11. 12.
21.
to
External
(15)
Withdraw seal carrier from
(16)
Remove seal from carrier
Gearshaft
diaphragm using puller (PWC30052)or (PWC30046-57) (Ref. Fig. 4-2-11). using
drift
(PWC30051-02)
and base
(PWC30051-01).
DISASSEMBLY/ASSEMBLY A.
Procedure
(See Figure 4-2-9)
(1)
Locate
(2)
Position
(3)
split plate (3)
as
shown between
assembly
on
base
Install compressor
(1)
on
centrifugal impeller (5)
and
gearshaft (6).
(4).
impeller (5)
and mate
lugs
of compressor with slots in
impeller. CAUTION:
SEPARATION OF GEARSHAFT AND IMPELLER SHOULD NOT REQUIRE EXCESSIVE FORCE. IF DIFFICULTY IS EXPERIENCED, CHECK THAT RETAINING RING IS COMPLETELY CLEAR OF GROOVE IN IMPELLER. drift
(2)
inserted in compressor,
(4)
Using
(5)
Remove
(6)
Remove retaining ring (12, Figure 4-2-8) and from gearshaft and impeller respectively.
split plate
from
impeller
and
separate assembly.
gearshaft
from bottom of base.
preformed packings (10)
(a)
Install
preformed packing (10)
on
gearshaft (2).
(b)
Install
preformed packing (11)
on
impeller (3).
(c)
Install
retaining ring (12)
NOTE:
Check for
in groove in
security
and
(11)
gearshaft.
of shoulder
pins
before
mating parts.
Page 4-2-23 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR INSTALLATIONS
1
5)
j
(6)
1
o
IMPELLER AND GEARSHAFT SEPARATION
C3614
Disassembly
of Starter-Generator Gearshaft
Figure
4-2-9
Page 4-2-24 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
Key
4-2-9
5. 6.
Starter-Generator Gearshaft
3. 4.
22.
Figure
Compressor (PWC30855) Drift (PWC30854) Split Plate (PWC30275) Base (PWC30274) Centrifugal Impeller
1. 2.
(d)
to
Position impeller on gearshaft; align shoulder pins in impeller with holes in gearshaft and press parts firmly together by hand to engage retaining ring. Check parts are locked together.
INSTALLATION A.
Procedure
(See Figures 4-2-8,
CAUTION:
(1)
Heat
(175"
(2)
(4)
centrifugal to 195"F).
breather
gearshaft
Remove carrier from oil, press on
Install
preformed packing
Install
flanged bearing
torque 32
(5)
Install
CAUTION:
4-2-10)
PRIOR TO INSTALLATION, THE CARBON SEAL SHOULD BE IMMERSED IN ENGINE OIL AND WORKED IN AND OUT TO make sure THAT THE CARBON SEAL ELEMENT IS FREE TO TRAVEL WITHIN THE SEAL CASING.
cross-sectional views
(3)
4-2-11 and
Figure on
and
of
oil heated to 79" to 91"C
seal into carrier
4-2-11 for correct
secure
gearshaft
engine
using Drift (PWC30054). assembly.
seal carrier and press carrier into
to 35 Ib.in. and lock
assembly
new
seal carrier in
with three bolts and
See
diaphragm.
keywashers. Tighten bolts,
keywashers.
in
diaphragm
and mesh with related
gearshafts.
IF, FOR ANY REASON, OTHER ACCESSORY DRIVES WERE REMOVED DURING REMOVAL PROCEDURE ON ENGINES INCORPORATING OPTIONAL DRIVES, EXERCISE CARE NOT TO INTERCHANGE THE EXTERNAL SCAVENGE PUMP GEARSHAFT (7; FIGURE 4-2-8) WITH THE HYDRAULIC PUMP GEARSHAFT (9). THESE GEARSHAFTS ARE SIMILAR IN APPEARANCE AND MUST BE IDENTIFIED BY PART NUMBER.
(6)
Install preformed packing on rear flange of accessory gearbox diaphragm and. position housing over diaphragm. Lead in chamfer on gearshafts permits easy entry into seals in gearbox housing.
(7)
Secure assembly with four countersunk screws, washers and nuts, and torque 36 to 40 Ib.in.
(8)
O
Install
preformed packing on front spigot of diaphragm Flange G and insert oil (1) with preformed packing into diaphragm (See Figure 4-2-10).
tank
center tube
Page 4-2-25 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
L
ii
A
~1
VIEW
A
Post-SB1045
C221B
Engines
Accessory Gearbox Installation Figure 4-2-10
Locking
Page 4-2-26 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
(9)
(10)
Figure
to
4-2-10
1.
Oil Tank Center Tube
2. 3.
Coupling Shaft Retaining Ring
4.
Flat Washer
5.
Ball Thrust
6.
Lock Ball
7.
Flat Washer
8.
Lock Ball
9.
Compressor
Spring Key Expander Spring
Rear Hub
Coupling
Pre-SB1045: Install accessory gearbox assembly on inlet case studs, aligning transfer tubes. Make sure that index mark on coupling shaft is aligned with index mark on gearbox input shaft.
Pre-SB1045 and all PT6A-20A follows:
engines,
install accessory
gearbox assembly
inlet
on
case as
Install washer
(a)
compressor
(7),
rear
expander spring (6), key (5) and washer (4) into coupling (9) and secure with retaining ring (3).
new
hub
(b) Slowly rotate compressor until hole in splined end of rear hub is at 12 o’clock position. Coat new lock ball (8) with petrolatum jelly and place in hole. (See Figure 4-2-10). (c)
Install
(d)
Position hub.
pusher (PWC30373) through housing gearbox assembly
to
(f)
a
case
studs to
A visual check should show end of
(g)
input gearshaft.
align coupling
correctly engaged, end-float along coupling shaft slight fore-and-aft slackness.
forward of
On
inlet
If lock ball is
(e)
(11)
on
center boss into
shaft with
rear
will be reduced
coupling shaft approximately
0.250 inch
adapter.
Remove pusher and install hexagon plug complete with preformed packing. Torque plug (Ref. No. 92, Fits Clearances), and safety wire.
with Post-SB1104 embodied, install accessory gearbox assembly studs, aligning transfer tubes. Align coupling shaft with compressor
engines
inlet
case
on
rear
hub.
(12)
Install over
(13)
plain washers over short studs on compressor inlet case, and thick spacers long studs. Install nuts on studs, tighten and torque 32 to 36 Ib.in.
Install oil filter Removal&
housing together Installation).
with filter element and filter
cover
(Ref.
Part 3,
Page 4-2-27 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
\y)o
o´•
c,
G
G
C506C
Centrifugal
Breather Gearshaft Carbon Seal
Figure
Replacement
4-2-11
Page 4-2-28 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
new preformed packings on oil filler gearbox housing with retaining ring. accessory
(15)
Install new preformed packing on short internal oil transfer tube and insert into compressor inlet case at 6 o’clock position.
(16)
Install
Install two
tube and
in
(14)
secure
assembly
preformed packing on compressor inlet case end of No. 2 bearing flange with two bolts at 6 o’clock position and lockwire.
new
scavenge oil tube. Secure
removed accessories.
(17)
Install all
(18)
Connect all
(19)
Connect all electrical cables and lockwire electrical connectors if
(20)
Connect and lockwire all control rods
(21)
Install drain
(22)
previously
pneumatic,
plug
and
fuel and oil lines.
secure
Refill oil tank with oil of
with
as
lockpin
Tighten
connectors if
applicable. applicable.
required. and
cotterpin.
approved specification (Refer
to Part
2, Engine Oil System
Servicing)
SCAVENGE PUMP INLET SCREEN 23.
CLEANING A.
(Ref. Fig. 4-2-12)
Procedure
(1)
(2)
Drain the oil tank and AGE (Ref. Part 2, Section 1). With asuitable light source and mirror or borescope, check the scavenge pump inlet screen mesh for carbon or debris (Ref. Fig. 4-2-12). If the
(a)
mesh has carbon or debris, carefully remove it with scraper or brush. Do not deform the screen mesh.
screen
plastic
Flush
anycarbon
or
debris residue from the AGE
1
Remove the oil filler cap.
2
Remove the
3
suitable small
follows:
and oil filler tube.
suitable container under the AGE drain, and pour approximately 34 of new engine oil (PWC03-001) heated to 122"F (50"C) into the AGE filler tube opening. Make sure that the oil does not enter the oil tank. Place
fluid
4
retaining ring
as
a
a
ounces
Let the oil drain. Examine the inlet screen and surrounding area to make that the residue is removed. If not, repeat the cleaning and flushing
procedure
sure
above.
(b)
Install the oil filler tube and
(c)
Refill the oil tank
retaining ring.
Ref. Part 2, Section 1).
Page 4-2-29 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
OIL FILLER CAP AND CAGE ASSEMBLY
-t
I -tt
1
-I-
I-
DRAIN PLUG OR MAGNETIC CHIP DETECTOR
81)
PUMP INLET SCREEN
PUMP INLET SCREEN SECTION
A-A
(DRAIN PLUG REMOVED)
VIEW
(TYPICAL VIEW ON
B DRAIN
BOSS)
C41801
Scavenge Pump Inlet Screen Inspection Figure 4-2-12
Page 4-2-30 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 4
HEAVY MAINTENANCE
SECTION 3 1.
GENERAL A.
2.
INSPECTION
Compressor turbine blade stretch inspection is to be implemented at an approved overhaul facility only, and as such, compressor turbine disk and blade assemblies which have been subjected to an overtemperature condition (Ref. Part 2, Section 6, Testing) should be returned to an overhaul facility, together with records of total operating hours or flight cycles (Ref. PART 2, SECTION 4, STANDARD PRACTICES) since engine overhaul or installation of replacement port.
EXHAUST DUCT A.
Procedure
(1)
Inspect exhaust (a)
duct
as
follows:
Inspect case and flanges for nicks, dents, permitted in the outer case or flanges.
cracks
or
distortion. No cracks
are
(b) Inspect turning vanes (Pre-SB11S1) for security and cracks. Crack limits and acceptable stop drilling are shown on Figure 4-3-1. Vanes cracked beyond limits should be replaced. (Refer to Repair, following.) (c)
On Pre-SB1324 exhaust ducts, inspect outer surface of flange D, one inch below the flange, for circumferential cracks. If cracks or
evident,
(2)
return
engine
For engines that have inferior welds:
to overhaul
incorporated
facility
for
repair.
SB1610 since the last overhaul and that exhibit
(a) Inspect for cracks at each minor inspection Step (c)) at intervals not to exceed 150 (b)
approximately cracking are
and repeat the inspection hours of flight time.
(Ref.
If cracks are found, repeat the inspection (Ref. Step (c)) at intervals not to exceed 25 hours flight time. All cracks will be marked with a suitable metal marking pencil (PWC05-013), and the length, location, duct hours and Time Since Overhaul recorded.
(c)
Using
5x
magnification, visually inspect
the forward
area
of the exhaust duct for to 2 inches aft
cracks, from the propeller reduction gearbox mounting flange around the entire circumference of the duct.
1
Exhaust ducts
There
considered serviceable
are no more
The total No
are
one
length of
provided:
than 3 cracks. all cracks does not exceed 2 inches.
crack exceeds 1 inch.
Page
4-3-1
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
ANY LENGTH ACCEPTABLE WITHOUT REPAIR
1 INCH CRACK ACCEPTABLE
STOP DRILL 1/16 INCH
1 118 INCH CRACK ACCEPTABLE STOP DRILL 1/16 INCH
AIRFOIL CRACK FROM UE ANY LENGTH ACCEPTABLE STOP DRILL 1/16 INCH
(Pre-SB1151 Engines) Acceptable Figure 4-3-1
Exhaust Duct V~ne
C585A
Crack Limits
Page
4-3-2
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
´•I
When there are 2 or 3 cracks, they must be separated by a minimum of 6x the length of the longest crack or 3 inches, whichever is greater. The 3.
growth
rate of any crack does not exceed 0.015 inch/hour of
operation.
COMPRESSOR INLET CASE A.
Procedure
(1)
Inspect compressor (a)
inlet
case as
Examine compressor inlet
follows:
case
for
general condition.
crack tin one strut only) up to 0.700 inch is acceptable as is, provided crack is not open more than 0.020 inch and does not progress through the
(b) One
fiiet radius.
(c)
4.
Cracks exceeding 0.700 inch in inlet case struts will require removal of inlet case and forwarding to an approved overhaul facility for repair.
GAS GENERATOR CASE A.
Inspection
(1)
of Gas Generator Case
Missing
diffuser exit ducts:
(a)
Reject engine if two adjacent exit ?onadjacent ducts are missing.
(b)
An
ducts
are
missing,
or
if
more
than two
engine missing a maximum of two non-adjacent ducts may continue in service for 500 hours after discovery, if all other exit ducts are within allowable limits and engine performance remains acceptable. Remove debris and sharp
edges. NOTE:
with missing diffuser exit ducts may lead to accelerated hot section deterioration. If engine is kept in service, perform borescope inspection of hot section and combustion chamber at recommended interval (Ref. Periodic Inspection).
Operating
(2)
Examine gas generator case for evidence of overheating.
(3)
On engines installed in airframe, check engine mounts for attachment and conditions (Ref. Aircraft Maintenance Manual).
(4)
On engines which have been disassembled for HSI condition of mounting pads and threaded holes.
(5)
Examine shanknuts
damaged
on
nuts may be
general condition, including cracks, distortion,
(Ref.
Table
3-3-2),
flanges in area of No. 2 bearing for tightness. replaced (Ref. Repair).
and
examine
Loose
or
Page
4-3-3
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(6)
vanes for cracks and missing material. Up to seven vanes side broken off is acceptable provided no more than two are adjacent to another, and sharp material is blended to make sure no further detachment of
Inspect straightening with one
one
material
(7)
Examine diffuser exit ducts in gas
for
(a) Inspect
Between
fretting
adjacent
at
wear
generator
following
follows
(Ref. Fig. 4-3-2).
locations:
ducts.
Between ducts and
adjacent straightening
Between ducts and inner wall of gas NOTE:
case as
vanes.
generator
case.
Fretting wear on outer face and edge adjacent to acceptable. Blend repair sharp edges by removal
next ducts is
of
excessively
thinned metal. on inner or outer surfaces, which will not converge and allow metal detached, are acceptable (Ref. Details A, B and D, Fig. 4-3-2) provided they are stop drilled (Ref. Repair). A crack terminating at a seam weld requires no stop drilling. For cracks which could converge and allow metal to
(b) Any
cracks
to become
become detached
(8)
Loss of material
Detail
(Ref.
C)
refer to
Repair.
maximum of four diffuser exit ducts is
on a
acceptable provided:
(a)
Detached material is removed from
(b)
Size of detached material does not exceed 0.50 x 0.80 in. on the inner surface, 0.30 x 0.30 in, on the outer surfaces (Ref. Details A and B, Fig. 4-3-2).
(c)
A hole
on
engine.
the inner surface is smoothed to
remove uneven
edges (Ref.
Repai r).
(d)
Fretted
smoothed to
areas are
remove
excessively
thinned material
(Ref.
Repair). (e)
When any of the above limits
are
exceeded, the ducts
must be
replaced (Ref.
Repair).
(9)
Inspect gas generator NOTE:
For
engines
case
with
a
for corrosion: diffused aluminide conversion-coated gas generator Coloring will
case, the corrosion products may become visually apparent. be reddish brown to rust, which may give the impression that
attack has occurred
premature
Light brushing with a soft bristle brush will show that apparent rust is superficial. Appearance of coating may vary. Damaged coating should be touch-up repaired (Ref. Section 4, Approved Repairs). (a)
on
the base material.
Minor corrosion on the exposed surfaces of the gas removed (Ref. Section 4, Approved Repairs).
generator
case
may be
Page
4-3-4
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
DAMAGE ON INNER SURFACE
DAMAGE ON OUTER SURFACE
0.300 MAX.
PERMISSIBLE
I
Y
0.500 MAX. PERMISSIBLE
0.800
A
MAX.PERMISSIBLE
B
DAMAGE ON INNER SURFACE
DAMAGE ON OUTER SURFACE
FRETTED AREA
C
D
C347D Diffuser Exit Tubes
Figure
(Typical Examples) 4-3-2
Page
4-3-5
Feb 01/2002
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(b)
If the condition of the corrosion exhibited
generator
case
on
the
exposed surfaces of
the gas
indicates that further examination of the fuel manifold and
igniter bosses is required, remove the fuel manifold adapters and spark igniters (Ref. PART 3, SECTION 2, REMOVAL INSTALLATION). Examine mounting pads, fuel nozzle bosses and machined surfaces for corrosion and wear. Isolated corrosion pitting not closely grouped, less than 0.010 inch deep, not covering more than 75 percent of the surface is acceptable without repair.
Page
4-3-6
Feb 01/2002
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•I
HEAVY MAINTENANCE
PART 4
SECTION 4
REPAIR
INTRODUCTION 1.
GENERAL A.
This section contains the latest approved methods for repair at heavy maintenance level of the PT6 engine. It has been written with the understanding that all parts requiring repair have been thoroughly inspected and tagged to indicate necessary repairs. As more information concerning repairs becomes available, it will be included in subsequent
revisions to this manual.
HELICAL COIL INSERTS 2.
REPLACEMENT use of helical coil inserts permits repair of housings which might otherwise be scrapped because of damaged threads. The insert is located between tapped female thread and screw thread of stud or bolt, to restore a damaged thread to its original size. Refer to appropriate Illustrated Parts Catalog (IPC) for approved locations and part number of inserts.
The
Unauthorized helical coil, or similar inserts, repairs of damaged studholes, etc, is not Authorization for repairs of this type should be obtained from Pratt and Whitney Canada.
permitted. A.
Repair (1)
Replace inserts
(a) (b)
as
follows:
Remove unserviceable helical coil inserts commercial helical coil repair kits. Install thread
tang
new
using
tools contained in Standard
inserts of the same size as those removed, and drive to correct below surface of part in which they are installed. Cut off driving
pitch
at notch.
REDUCTION GEARBOX ASSEMBLY 3.
FRONT AND REAR REDUCTION GEARBOX HOUSING A.
I
Repair NOTE:
(1)
of Corrosion Corrosion must not be deeper than 0.010 in. and must not cover an area greater than 30 percent of the total surface of the front and rear RGB housing.
Apply
a
suitable
covering
material around the
area
to be
repaired.
Page
4-4-1
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(2) (3)
Clean the surface of the area to be repaired, using a swab soaked in alcohol (PWC11-014) and crocus cloth (PWC05-061).
isopropyl
Remove all traces of corrosion (magnesium oxide) using a suitable steel brush, cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner.
crocus
(4)
Flush the
(5)
Dry
the
(7)
area
with clean,
room
compressed air,
temperature. at 29
psig.
Prepare a chrome pickle solution (Ref. PART 2, SECTION 4, STANDARD PRACTICES, Touch-Up Solution). Using 29"C
a
swab
(55"
NOTE:
(8)
with clean water at
REFER TO THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS FOR INFORMATION, SUCH AS HAZARDOUS INGREDIENTS, PHYSICAVCHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES. SOME OF THESE MATERIALS CAN BE DANGEROUS. YOU CAN GET THE DATA SHEETS FROM THE MANUFACTURERS OR THE SUPPLIERS OF THESE MATERIALS.
WARNING:
(6)
area
to
or
brush, apply the chrome pickle solution, to the
85"F),
prepared
Repeat the application frequently continually wet with the solution.
Swab the
area
at a
temperature of 17"
to
surface for 30 to 45 seconds. to make sure that the affected surface is
with clean water until successive swabs
are no
longer stained
yellow. (9)
Dry
the
area
with local
(10)
Clean the affected
(11)
Dry
(12)
Apply
the
(14)
The
area
with clean,
two coats of
NOTE:
(13)
area
heating lair dry with
a
or a
heat gun at
a
low
setting).
rag soaked in clean water.
compressed air
at 29
psig.
primer (PWC13-001).
primer
can
Allow the
be diluted with 10% solvent.
primer to air dry compressed air at 29 psig
for
eight
hours before
to accelerate the
applying drying time.
enamel
paint. Use
three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. The final coat of enamel must dry for 24 hours before returning the engine to
Apply
service. NOTE:
primer and paint can be reduced with the use of setting. Refer to the manufacturer’s instructions.
Drying
time for the
gun at
a
low
´•a
Page
heat
4-4-2
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMBUSTION CHAMBER LINER 4.
CRACK REPAIR A.
Procedure
(1)
Repair acceptable combustion chamber INSPECTION, for repairable limits): CAUTION:
liner cracks
as
follows
(Ref.
PART 3,
ANY HOLES THAT ARE PLUGGED AS A RESULT OF WELDING MUST BE REDRILLED TO THE ORIGINAL SIZE, AND THEN DEBURRED. PARTICLES OF LOOSE WELD MUST BE REMOVED.
both ends of crack, using 1/16 (0.0625) inch drill. Vee-out crack suitable abrasive wheel. Wire brush thoroughly and swab with alcohol.
(a) Stop-drill (b)
using
Weld crack using inert gas fusion method (Ref. PART 2, preceding) and filler rod specified in Table 4-4-1. Use copper back-up plate to reduce distortion, with addition of argon gas back-up (if available). Stress relief after welding is not
required. NOTE:
Do not dress the weld.
TABLE 4-4-1, Filler Rod
Specification
Combustion Chamber Liner
SPECIFICATION
PART NO. Combustion Chamber Liner
Filler Rod
3007583
AMS5798
3009083
AMS5798
3d‘l 0083
AMS5798
3011083
AMS5798
3014142
AMS5798
3014769
AMS5798
3023774
AMS5837
EXHAUST DUCT TURNING VANE 5.
Repair
(PRE-SB11S1 ENGINES)
REPLACEMENT A.
Procedure
(1)
Before attempting to install replacement vanes, set up fixture (PWC30153) with reference to existing vanes in duct under repair, as follows (Ref. Fig. 4-4-1): and back off
setting
(2) by turning
counterclockwise.
(a)
Loosen locknut
(b)’
Rotate fixture arm (1) to line up with serviceable vane, when fixture is installed and located on the offset hole on flange D.
(3)
screw
Page
4-4-3
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
2
1
a
a
3
a
C112A
(PWC30153) Figure 4-4-1
Fixture
Page
4-4-4
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
6.
setting screw (2) Tighten locknut (3).
(c)
Turn
(d)
Shim
(e)
Remove fixture,
to contact, but not
pre-load, trailing edge
equally either side, as required, to take (PWC30153), and exhaust duct Flange D. taking
vane.
up any clearance between fixture
setting
not to disturb
care
of
of
(2).
screw
INSTALLATION A.
Procedure
(1)
Install
replacement vane(s)
as
follows
(Ref. Pig. 4-4-1, 4-4-2):
grinding
off rivet heads and
driving
(a)
Remove defective vane(s) by using a suitable pin punch.
(b)
Position and locate new vane in duct using the previously set vane locating fixture (PWC30153). The arm (1, Pig. 4-4-1) must be rotated to the desired radial location and the fixture reinstalled on the offset hole of Flange D to achieve
out stems
this.
(c)
Drill five holes in
(0.0635 inch)
No. 52
(d)
Remove fixture
(e)
Install
(f)
Prior to
new vane
and
Pilot-drill
using
drill followed
(PWC30153) secure
riveting, install plain
EXHAUST 7.
through the five holes in the duct. by No. 40 (0.098 inch) drill.
new vane
and
vane
and deburr the five holes.
with suitable sheet metal fasteners. washer
on
each of five rivets
(Ref. Pig. 4-4-2).
DUCT(PRE-SB1151 ENGINES)
REPAIR A.
Procedure
(1)
Inner exhaust duct walls that have cracks holes may be weld repaired as follows:
(a) Stop
drill 1/16
(b) Thoroughly (c)
(0.0625)
emanating
from the
turning
vane
rivet
inch end of crack.
wire brush the
Using tungsten inert-gas
area
to be welded.
method and filler rod
(PWC05-216A),
weld
prepared
areas.
(d)
Dress welds
as
required
and fluorescent
penetrant inspect
welded
areas.
Page
4-4-5
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXHAUST
DUCT(REF.)
RIVETS 5 PER VANE WASHERS 5 PER VANE
.A TRAILING EDGE
VANE
A
(REF.)
FWD B 111
1 B
RIVETS
RIVETS
LEADING EDGE
WASHERS
(2) 3 HOLES 0.098-0.100 DIA.
2 HOLES 0.098-0.100 DIA.
RIVETS
SECTION
(3)
B-8
SECTION
(Pre-SB11S1 Engines) Installation of Exhaust Duct
Figure
A-A
C113A
Turning Vane
4-4-2
Page
4-4-6
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
COMPRESSOR INLET CASE 8.
REPAIR OF CORROSION A.
Procedure
NOTE:
Corrosion must not be deeper than 0.010 in., and must not cover greater than 10 percent of the total surface of the inlet case. suitable
covering material
an area
the compressor section.
(1)
Apply
(2)
Clean the surface of the area to be repaired, using a swab soaked in alcohol (PWC11-014) and crocus cloth (PWC05-061).
(3)
Remove all traces of corrosion (aluminum oxide) using a suitable steel brush, crocus cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner.
(4)
Flush the
(5)
Locally clean the repaired surface and surrounding area, using perchlorethylene (PWC11-016) or acetone (PWC11-012) and a (PWC05-061). Remove all debris using a vacuum cleaner.
(6)
Apply
a
area
anodize
over
with clean water at
touch-up
solution
room
isopropyl
temperature.
(PWC05-064) using
a
swab
or
a
swab soaked in
crocus
cloth
brush for three to
four minutes.
NOTE: 1.
Repeat the application frequently to continually wet with the solution.
make
sure
that the affected surface
is
NOTE: 2. If the solution does not wet the surface, remove the solution with a clean cloth and repeat Step (3). Also, clean the first-stage compressor if the solution has been inadvertently applied.
(7)
Allow the surface to air
(8)
Examine the
(9)
coating
dry
or
wipe
and make
again,
off solution with
sure
that the
Reapply
the treatment
NOTE:
After the successful completion of service for the next 100 hours.
For
a more
(a)
Do
(b) Dry
durable
repair,
as
a
repair
cloth soaked in clean water.
surface is
completely
covered.
necessary.
do the
Step (8),
the
engine may
be returned to
following:
Steps (2) through (6) again. the affected
(c) Apply
area
two coats of
NOTE:
The
thoroughly.
primer (PWC13-001).
primer
can
be diluted with 10% solvent.
Page
4-4-7
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(d)
primer to air dry for eight hours before applying enamel paint. Use compressed air at 29 psig to accelerate the drying time. Allow the
three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. Allow a final coat of enamel paint to dry for 24 hours before returning the engine to service.
(e) Apply
NOTE:
(10)
Drying time can setting. Refer to
be reduced with the use of a heat gun at the manufacturers instructions.
a
low
repair is more than the maximum permitted limits, inspect the repaired again, at intervals not exceeding 10 flight hours. The engine must be returned to an approved overhaul facility within 50 flight hours for a repair to be If the corrosion area
done.
GAS GENERATOR CASE 9.
REMOVAL OF DEFECTIVE RIVETS A.
Procedure
(1)
Remove defective rivet
as
follows
(Ref. Fig. 4-4-3):
(a)
Drill rivet head only, using 1/8 (0.125) inch diameter drill, pry off weakened head and carefully punch out rivet stem using a suitable pin punch.
(b)
Make
sure
that all
punched out stems are removed from engine. If necessary, through straightening vanes by motoring engine.
stems may be blown out
10.
SELECTION OF REPLACEMENT RIVET (Pre-SB1143 ENGINES) A.
11.
SELECTION OF REPLACEMENT RIVET (Post-SB1143 AND ALL PT6A-20A ENGINES) A.
12.
Where possible, 1/8 (0.125) inch nominal diameter rivets P/N 3011178 (CR517-4-4) should be installed, provided hole diameter does not exceed 0.138 inch. If hole diameter exceeds 0.138 inch, open up hole using No. 20 (0.1610 inch) drill and install 5/32 (0.15625) inch diameter oversize rivet P/N 3012519 (CR517-5-4).
Where possible, 1/8 (0.125) inch nominal diameter rivets P/N 3018356 (CR517-4-6) should be installed, provided hole diameter does not exceed 0.138 inch. If hole diameter exceeds 0.138 inch, open up hole using No. 20 (0.16!0 inch) drill and install 5/32 (0.15625) inch diameter oversize rivet (CR517-5-6).
INSTALLATION A.
Procedure
(1)
Install
replacement
rivet
as
follows:
Page
4-4-8
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
POST-SB11 43
RIVET (14)
A PRE-SB1143 PARTIAL VIEW OF GAS GENERATOR CASE
W
C1651A Installation of Blind Rivets in Gas Generator Case
Figure
4-4-3
Page
4-4-9
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(a)
Install rivets using Cherry rivet gun 036 with pulling head G6H4B (1/8 dia. rivet) or G6H5B (5/32 dia. rivet). Care must be taken to keep rivet gun vertical to sheet metal to make sure rivet is properly installed. Use of modified rivet gun, as shown in Figure 4-4-4, is strongly recommended.
(b) Inspect 13.
installed rivets
(Ref.
SECTION 3,
INSPECTION).
REPAIR A.
Procedure
(1)
Repair bleed valve
(a) Open
mount
flange
threaded
hole(s)
damaged hole(s) using 0.332 5" included angle. x 90"
up
inch
as
follows:
(Q size)
drill. Chamfer 0.385 to
0.395 inch
(b) Tap
hole
0.375-16 UNF-2B
using
Install insert
(c)
("Keensert" surface, fingertight.
(d)
Drive
(e)
If
1
keys
P/N KN428
using locking
down
tap.
already installed, damaged
tool
(NAS 394C-4))
0.010 to 0.015 inch below
(P/N TD428L).
inserts may be
replaced
as
Drill out insert material between keys and thread to (3/16) inch using 0.281 (9/32) inch drill.
a
follows: maximum
depth
of
0.188
14.
2
Deflect keys inward, break off
3
Remove insert
4
Install
new
using
using
suitable
pin punch.
E-Z out tool.
insert, steps (c) and (d), preceding.
CORROSION REMOVAL A.
Procedure
(1)
Remove corrosion
as
follows:
(a) Manually remove all visible corrosion using coarse abrasive paper to the extent of exposing bare metal. Use abrasive cloth (PWC05-014) or a soft bristle brush to provide a clean surface. NOTE:
(b)
Do not
Restore coating coating loss:
use
on
power tools for corrosion removal.
gas
generator
case
that exhibits small localized
areas
Page
of
4-4-10
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
G36 HAND GUN CHERRY RIVET DIVISION TOWNSEND CDMPANY
318 DIA. NORI\IAL PIPE
A
6
REMOVE FINGER GUARD
CHERRY RIVET DIVISION TOWNSEND COMPANY
1RAD. PLUG
31/2C-´•-´•´•
O
3/32 THICK 12518
PLATE: MATERIAL- STEEL TUBE: MATERIAL- STEEL
17116
f 5/8 DIA.
9116 RAD.
15132
8112 RAD
SECTION
A-A
C2588
Cherry Rivet Gun Figure 4-4-4
Modified
Page
4-4-11
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
1
Remove all traces of oil
or
grease from touch-up if necessary, scrub
wipe (PWC11-033). spray non-metallic brush or pad. or
Casing
2
Mask all
exposed holes
3
Feather defective
4
Thoroughly agitate,
5
Apply
6
area
two or three
in fuel
using
on a
or
a
an
aqueous soft
igniter pads.
abrasive cloth
paint
shaker
brush, spray
Touch-up. Wipe
damp sponge coats of (PWC07-023) coating.
or
off
(PWC05-003).
equivalent, coating material.
or
excess
Allow each coat of touch-up conversion between coats.
coating
to air
dry for four
hours
of corrosion inhibitor:
(c) Application
15.
using with
is to be cool to the touch.
NOTE:
Sermetal 249
area area
1
Mask all holes that
2
Apply
are to
corrosion inhibitor instructions.
remain free of corrosion inhibitor.
(PWC15-013)
in accordance with manufacturer’s
SHANKNUT REPLACEMENT A.
Procedure
(1)
Replace shanknuts
as
follows
(Ref. Fig. 4-4-5, 4-4-6):
(a) Using a suitable drill, partially 4-4-5). NOTE:
Do not drill
through
(b) Remove shanknut using flare, and retrieve from
(c)
Install
new
a
remove
the flared end of shanknut
to contact
(2, Fig.
flange.
parallel pin punch
at drilled end to shear weakened
case.
shanknut and hold
against flange (Ref. Fig. 4-4-6).
(d) Lightly lubricate tapered portion of shanknut spreader (PWC30335) with engine oil (PWC03-001) and screw into shanknut until shank end is flared against flange. (e)
16.
Remove shanknut spreader and examine flared end of shanknut for correct forming with no evidence of deformation or cracks.
DIFFUSER EXIT DUCTS A.
Procedure
(1)
In-situ
repair (Ref. Fig. 4-4-7):
Page
4-4-12
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
drill cracks using a 1/16 (0.0625) inch drill (Ref. Details A, B and C). Cracks in the outer walls of ducts may be reached by drilling access holes in inner walls using a 1/4 (0.250) inch drill, then stop drill in outer wall using 1/16 (0.0625) inch drill (Ref. Detail D). Access holes are acceptable without
(a) Stop
a
repair.
(b)
Remove metal that would become detached due to
(c)
Blend out areas where metal has become detached, or has been removed (Ref. Details A, B and C), or where metal has been excessively thinned due
cracks.
fretting.
to
17.
converging
REPLACEMENT REPAIR (REF. FIG. 4-4-8) A.
Procedure BEFORE MACHINING, MASK OFF SURROUNDING HARDWARE TO PREVENTINGRESS OF METAL PARTICLES TO BEARING AREAS IN PARTICULAR AND TO ENGINE iN GENERAL.
CAUTION:
(1)
Insert
a
suitable shim
(brass
damaging surrounding part-off dimension (View B). area
NOTE:
steel) between ducts and case wall to avoid during machining. Cut off defective diffuser exit duct or
Replacement procedure (5) in Figure 4-4-8.
is not
applicable
to
to diffuser exit tubes at locations
(2)
Insert gage (item 64) into stub (3), using cutter (item 63) face to DIM. "A" Break sharp edges and chamfer as required (View B). Clean area.
(3)
Remove shim, coat OD of stub (3) with compound (PWC09-002). Open clamp (2) (View A-A) to permit insertion of small end of diffuser exit duct (1) and with clamp still open, as semble over stub (3) in diffuser ring.
(4)
Butt up duct to stub and progressively torque bolt shown. Torque bolt 28 to 32 Ib.in. and safety wire.
(4), maintaining
clearances
(5)
On
generator
before and after
completion, thoroughly masking tape.
clean and
vacuum
gas
case
(View B).
removal of 18.
FUEL NOZZLE BOLT REMOVAL A.
Procedure
(1)
Remove fuel manifold adapter and fuel nozzle assemblies broken bolt (Ref. PART 3, REMOVAVINSTALLATION).
CAUTION:
as
necessary to expose
MASK ENGINE, AS NECESSARY, TO PREVENT POSSIBLE INGESTION OF METAL PARTICLES.
(2)
Install drill
(3)
Drill
pilot
jig (PWC50064-100)
hole with center drill
on
fuel nozzle
pad, and
secure
with
jig
screw.
(PWC50064-200), using jig guide.
Page
4-4-13
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
n
s
c,
a
A
USE NO. 40 (0.098) DRILL TO CLEAN HOLE AFTER PAINTING OR RECOATING
n
2
p
i, a
REMOVE SHANKNU’TS WHERE NECESSARY
(POST-SBI1SO) s
lp
In,
1) a
rp n,
"rt’)
i
C1433D Gas Generator Case Repair Figure 4-4-5
(Typical)
Page
4-4-14
Jun 10/2005
PRATT
WHIINEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
19.
in
to
Figure
1.
Gas Generator Case
2.
Shanknut
Install
(5)
Drill bolt for
(6)
Remove bolt. Examine threads for
jig,
and
with lockscrew.
(4)
bushing
4-4-5
appropriate
secure
extractor.
damage,
and
repair
REPAIR FUEL NOZZLE PAD FRONT DAMAGED THREADED A.
if necessary.
HOLE(S)
Procedure
NOTE:
This procedure is to be used as a temporary measure to repair damaged thread in fuel nozzle pad front mounting hole(s). This repair is acceptable for continued operation until the next overhaul, when the hell-coil insert will be replaced by permanent TIG weld repair of the affected hole(s).
(1)
Mask gas generator
(2)
Drill
(3)
Chamfer 0.220-0.250 inch X 120
(4)
Tap
(5)
damaged
openings
to
front hole 13/64
keep
(0.203)
out debris.
inch to
original depth.
5" included
front hole 10-32 UNF-3B hell-coil
angle.
tap.
Install hell-coil insert (PWCO5-118) 10-32 UNF hell-coil insert tool.
(P/N
MS124655
or
equivalent
1191-
3CN0190) using (6)
Break and
(7)
Remove all
remove
driving tang.
masking
material.
COMPRESSOR TURBINE SHROUD GRINDING 20.
OPERATION BREAKDOWN A.
Procedure
(Ref. Fig. 4-4-9, 4-4-10)
(1)
out compressor turbine shroud
Carry
grinding operations
as
follows:
(a)
After grinding, the segments should be inspected. If a lip is present, which is either sharp edged or proud of the ground surface by more than 0.005 inch, remove by local grinding using a hand held rotary tool with flexible drive and grinding wheel attachment, or similar equipment.
(b)
Install radius gage 1
Zero
on
(PWC30417), (PWC32417)
or
(PWC32380):
master.
Page
4-4-15
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
SHANKNUT AFTER
SPREADER
INSTALLATION
I
SHANKNUT BEFORE INSTALLATION
TYPICAL CROSS-SECTION AREA AND APPLICATION
C1997A
Shanknut Replacement
Figure
4-4-6
Page
4-4-16
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
STOP-DRILL AND SMOOTH OUT HOLE
STOP-DRILL AND SMOOTH OUT HOLE
I b B
A
STOP-DRILL THROUGH WINDOW
STOP-DRILL, REMOVE METAL AND BLEND OUT HOLE
ON INNER WALL
0.800
1 Y" kl
i
0.400 MAX. 0.500 MAX.
0.250 MAX.
0.800 MAX.
D
C
C348C Diffuser Exit Tube
Figure
Repair (Typical) 4-4-7
Page
4-4-17
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
VIEW
A-A
si7 0.015 MIN. BOTH SIDES
A
A
0.080 0.020 BOTH SIDES
L
CHAMFER
2"~
DIM.A
DIM.B
1.290 1.280
1.370 1.320
X
VIEW
B
FERRULE AND CLAMP REMOVED FOR CLARITY
C10359B Diffuser Exit Duct
Repair/Replacement Figure 4-4-8
Page
4-4-18
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
2.
Replacement Diffuser Clamp
3.
Stub
4.
Bolt
5.
Diffuser Exit Duct
1.
Figure
4-4-8
Exit Duct
Assembly
Assembly (Repair
not
applicable
at these
locations) 2
adapter (PWC30408) preceding).
3
Indicate
use
(c) Centralize
on
(PWC30409)
or
on
stubshaft
(Ref.
Section 1,
heat shield.
vane
assembly:
loosen bolts
I
Slightly
2
Centralize.
3
Take four
readings
4
Retighten
bolts and
on vane
90
ring lockplate.
degree apart.
safety
wire.
(d) Remove shroud eccentricity: 1
Grind shroud to
remove
high spots
ID
on
following steps (f) through (j)
below.
(e) Determine amount of grinding or replacement of applicable (REF NO. 318, Fits and Clearances): NOTE:
(PWC32380) permits
Radius gage
using
1
Measure shroud ID
2
Measure bladed disk OD
radius gage
shroud
measurement of
(PWC30417)
(three places
segments,
and
or
as
taper.
(PWC32417).
average) using
8 to 9 inch
micrometer.
NOTE:
If measurements of bladed disk OD reveal differences in excess of an overhaul facility for tip
0.005 inch, disk must be returned to
grinding. ID
Average OD
Actual radial
4
If actual radial tip clearance is less than 0.013 inch, grind shrouds to obtain radial tip clearance of 0.013 inch (minimum) following procedure steps (f)
through (j) 5
tip
clearance
equals
3
2
below.
If actual radial
tip
clearance is
greater than 0.016 inch, replace shrouds
(minimum) grind below. (j) procedure steps (f) through
and
to obtain 0.013 inch
radial
tip clearance following
Page
4-4-19
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(f)
Install shroud
grinder (PWC30122)
or
(PWC37917),
as
applicable (Ref. Fig.
4-4-9):
(g)
1
On stubshaft.
2
Use
3
Align
Set
grinding
adapter (PWC30408)
(j)
(PWC30409) (Ref.
Section 1,
preceding).
offset hole. wheel
(PWC32122-50)
or
(PWC32528),
1
Wheel
freshly
2
Adjust
vertical vernier first.
3
Set wheel to bottom of shroud segments.
4
Adjustside
5
Set wheel to touch thickest segment.
6
Back off side vernier
as
applicable:
dressed.
vernier.
(h) Grinding Operation
(i)
or
one
turn.
1:
adjust side
vernier until wheel touches.
1
Start air and
2
Adjust vertical
3
Repeat until wheel touches top of shroud.
vernier
Grinding Operation
one
turn IN at each
completed
revolution of
grinder.
2:
side vernier until wheel touches.
1
Adjust
2
Adjust vertical vernier grinder.
3
Repeat until wheel
Grinding Operation
one
turn OUT at each
completed
revolution of
reaches bottom of shroud.
3.
side vernier until wheel touches.
1
Adjust
2
Repeat steps (h) and (i).
3
Repeat
this
procedure until
desired clearance is obtained.
Page
4-4-20
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
ACCESSORY GEARBOX ASSEMBLY 21.
ACCESSORY GEARBOX HOUSING A.
Repair
of Corrosion
NOTE:
(1)
Corrosion must not be deeper than 0.010 in. and must not cover greater than 10 percent of the total surface of the AGE housing.
Apply
a
suitable
(2)
(3)
material to be
covering
section and around the
area
over
all accessories,
linkages,
an area
the compressor
repaired.
Clean the surface of the area to be repaired with a swab soaked in alcohol (PWC11-014) and crocus cloth (PWC05-061).
isopropyl
Remove all traces of corrosion (magnesium oxide) using a suitable steel brush, cloth (PWC05-061), abrasive cloth (PWC05-101), file or grit paper. Remove all traces of debris using a vacuum cleaner.
crocus
(4)
Flush the
(5)
Dry
the
with clean water at
area
area
room
compressed
with clean
temperature.
air at 29
psig.
WARNING:
REFER TO THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS FOR INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAVCHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES. SOME OF THESE MATERIALS CAN BE DANGEROUS. YOU CAN GET THE DATA SHEETS FROM THE MANUFACTURERS OR THE SUPPLIERS OF THESE MATERIALS.
(6)
a
Prepare
chrome
pickle
solution
(Ref.
PART 2, SECTION 4, STANDARD
PRACTICES, Touch-Up Solution).
(7)
Using 29"C
a
NOTE:
(8)
swab
(55"
to
or
brush, apply the chrome pickle solution,
85"F),
to the
prepared
Repeat the application frequently continually wet with the solution.
Swab the
area
at
a
temperature of
17" to
surface for 30 to 45 seconds. to make
sure
with clean water until successive swabs
that the affected surface is
are no
longer
stained
yellow. (9)
Dry
the
area
with local
(10)
Clean the affected
(11)
Dry
(12)
Apply
the
area
The
area
with clean,
two coats of
NOTE:
heating lair dry with
a
or a
heat gun at
a
low
setting).
rag soaked in clean water.
compressed
air at 29
psig.
primer (PWC13-001).
primer
can
be diluted with 10% solvent.
Page
4-4-21
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
4
O
7
8
~ille
6
1
C1747
Compressor
Turbine Shroud 4-4-9
Grinding
Figure
Page
4-4-22
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
Key
to
Figure
4-4-9
3.
Blanking Material Grinding Wheel Shroud Grinding (PWC30122)
4.
Gas Generator Case
5.
Vertical Vernier
6.
Shroud
1. 2.
7.
Segment Adapter (PWC30408)
8.
Side Vernier
or
(PWC30409)
primer to air dry for eight hours before applying compressed air at 29 psig to accelerate the drying time.
(13)
Allow the
(14)
Apply
enamel
paint.
Use
three to four coats of enamel (PWC05-037) to the primed surface. Allow the surface of the enamel to become tacky (approximately 15 minutes) between each coat. The final coat of enamel must dry for 24 hours before returning the engine to
service. NOTE:
primer and paint can be reduced with the setting. Refer to the manufacturers instructions.
Drying
time for the
gun at
a
low
use
of
a
heat
T5 BUS-BAR TERMINAL STRAPS OR LUGS 22.
REPLACEMENT A.
Procedure
(1)
Replace damaged
terminal straps
or
lugs
Dress bus-bar to
(b)
Secure appropriate terminal strap to tungsten-inert gas (TIG) method. No
(c)
T5 bus-bar
as
follows
(Ref. Fig.
old weldment.
(a)
remove
on
bus-bar and fusion weld
filler rod
using
the
required.
lug to the bus-bar, making sure the large chamfer on threaded facing outward; fusion weld using the TIG method. Use chromel or alum’el welding rod (PWC05-164), as applicable.
Attach terminal
portion
NOTE:
is
Stress relief is not
required.
T5 TERMINAL BLOCK 23.
REPAIR A.
Procedure
(1)
Repair
loose T5 terminals in block
as
follows:
Page
4-4-23
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
EXAMPLE:
RECOMMENDED SHROUD SEGMENT
BLADED DISK OD
CLASS TO BE USED
MEASUREMENTS
CLASS
8.548
DIMENSION A (See
Illustration)
(INCHES)
1
GRIND SHROUD SEGMENT
0.042 to 0.043
ID TO
(INCHBS)
WINfHUn
MAKIMUM
8.570
8.584
REMARKS
tip 8.542
2
0.045 to 0.046
8.564
8.578
If
NOTE:
3
0.048 to 0.049
8.558
8.527
8.530
4
0.051
to 0.052
8.552
8.566
0.054 to 0.055
8.546
8.560
8.524
specified
exceeds
limits 8.536
blade
clearance after
removing eccentricity on shroud select segments, neat higher
(thicPrest) segments
class
and
8.518
6
0.057
to 0.058
8.540
8.554
grind as required.
8.512
7
0.060 to 0.061
8.534
8.548
bladed dish OD
8
0.069 to 0.072t
a
a
For
beloP~ 8.512
9
inches
use
class
8
or
f
Post-SEll47
a
Grind to suit
9.
0.079 to 0.083f
f
A SHROUD CROSS SECTION SHOWING DIMENSION "A"
C76140
Shroud Cross Section Figure 4-4-10
Page
4-4-24
Jun 10/2005
PRATT
WHITNEY CANADA
WIAINTENANCE MANUAL MANUAL PART NO. 3015442
WELD
0.200
0.685 0.565
o.oso~
ALUMEL TERMINAL LUG
WELD
45"fi
CHROMEL TERMINAL LUG
TERMINAL STRAP
n
C744A Terminal
Straps and Lugs Replacement Figure 4-4-11
Page
4-4-25
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
CARE MUST BE EXERCISED WHILE USING THERMOCOUPLE SEALING CEMENT (PWC08-009), OTHERWISE, SPLASHES MIGHT CAUSE DISCOMFORT OF THE EYES. IN THE EVENT OF CONTACT WITH EYES, IMMEDIATELY WASH WITH WATER AND CONSULT A PHYSICIAN (MEDICAL DOCTOR).
WARNING:
(a)
Secure terminals by applying a few drops of cement (PWC08-009). The terminal block is to be oven-dried at temperature of 65" to 93"C (149" to 199.4"F) for one-half hour, or air dried at room temperature for 24 hours. ceramic insulation
(b) Replace missing 1
Apply
cement
(PWC08-009),
as
as
follows:
required,
to surfaces.
Make sure that all surfaces coming into contact with the cement free from grease and dirt. Contamination by these impurities will adversely affect the physical and electrical insulating properties of the cement.
NOTE:
are
2
Dry assembly
3
Cure
at 38"C
(100"F)
for one-half hour to eliminate
assembly at a temperature of 65" to 93"C (149" or air dry at room temperature for 24 hours.
to
bubbling.
199.4"F) for
two
hours,
(c)
Perform
loop
resistance and
continuity
check
(Ref. PART 3, INSPECTION).
i)
THERMOCOUPLE.~RNESS 24.
LUG REPLACEMENT (SINGLE INSULATION CRIMPING) A.
Procedure
(1)
Replace
(a)
(b)
broken
or
damaged
close
terminal
lugs (Ref. Fig. 4-4-12).
Cut wire
as
NOTE:
Harness lead must not be shortened in order to maintain resistance within
as
possible
Work stainless steel braid back
damage insulation
weld, open
to
ears
approximately
and
remove
from lead.
lug
than absolutely necessary permissible limits.
more
1/2 inch. Exercise
care
not to
under braid.
(c) Wrap insulating tape (PWC05-191) two turns over exposed insulation, trim frayed insulation back to 3/16 (0.1875) inch from end of wire. (d)
Trim stainless steel braid to 5/16 two turns
(e)
(0.3125)
inch from end of wire and wrap
tape
braid.
chafing sleeve (tubing, class H-C-2) 7/16 (0.4375) inch long twisting motion, to 1/4 (0.250) inch from end of wire.
Slide with
over
over
tape,
Page
4-4-26
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
SLEEVE
O STEEL BRAID WIRE -/INSULATION
INSULATION TAPE
WELD 7
~r
CRIMP
O
C927B T5 Harness
Lug Replacement Single Figure 4-4-12
Insulation
Crimping
Page
4-4-27
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(f)
Secure
a
terminal lug of appropriate material (chromel or alumel) to the wire by small ear of lug around wire with approximately 1/16 (0.0625) inch of
crimping exposed.
wire
(g)
Fusion weld wire to terminal lug using TIG method. Use chromel or alumel welding rod (PWC05-164), as applicable. Inspect and test weld by gently pulling on lug with pliers. Clean both sides of lug with stainless steel wire brush or emery cloth (PWC05-003).
(h) Crimp large (i) 25.
lug
ears over
insulation sleeve.
Perform
loop resistance and continuity check (Ref. PART 3, SECTION 2, REMOVAUINSTALLATION).
LUG REPLACEMENT A.
terminal
(DOUBLE INSULATION CRIMPING)
Procedure
(1)
Replace broken (a)
or
damaged
terminal
lugs (Ref. Pig. 4-4-13):
Proceed as detailed in Paragraph 24., Steps (a) through (g). Use a sleeve 3/4 inch long and vary other dimensions slightly to allow for longer terminal
(0.750) lug.
(b) Crimp the two lug ears over Pig. 4-4-14, Steps 1 to 4). (c) 26.
Perform
the
chafing
sleeve
using pliers (PWC30425) (Ref.
loop resistance and continuity check (Ref. PART 3, INSPECTION).
BRAIDING REPAIR A.
Procedure
(1)
Lifted
or
broken stainless steel braiding may be cut away providing insulation Repair broken or deteriorated braiding on harness as follows:
remains intact.
(a)
Cut off all loose strands of
braiding
around
damaged
area.
(b) Wrap insulating tape (PWC05-191) around harness, covering damaged area (Ref. Pig. 4-4-15).
all of the
(c) Wrap repaired area with steel wire (PWC05-110) MS9226-01 (AMS5687). Hold wrapping wire snugly along length of harness braid beginning from the left. Starting at opposite end, wrap wire tightly and uniformly over harness braid and repaired area. NOTE:
(d)
When
end of
Make sure the wire end of the repair.
overlaps tape
and contacts harness braid at each
approximately two-thirds of wrapping length is completed, allow short loop to remain exposed. Continue wrapping wire to complete remaining
distance, shown
as
"113 X".
Page
4-4-28
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INSULATING TAPE
O WIRE
II;SULATION
STEEL BRAID
SLEEVE
W$D
CRIMP
C1184A T5 Harness
Lug Replacement Double Insulation Crimping Figure 4-4-13
Page
4-4-29
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
X STEPP
STEP1
STEP 4
STEP 3
C1185 T5 harness
Lug Replacement, Crimping Figure 4-4-14
Procedure
Page
4-4-30
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
INSULATING TAPE
B
:"i113
X
C4960C T5
Thermocouple
Harness Braid
Figure
Repair
4-4-15
Page
4-4-31
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(e)
After final turn of wrapping, insert wire "A" through loop. Cut off surplus end of wire "B", so that length is approximately one-third of repair lehgth. Pull loop end "C" until wire at "A" is snug and end "B" of wire has just disappeared underneath final turn of wrappings. Then, cut wire end "C" flush.
FIRESEALS 27.
CHAFING STRIP REPLACEMENT A.
Procedure
(1)
Detached
sealing strips,
if serviceable, may be rebonded
as
follows:
old cement and thoroughly clean surfaces to be bonded using inhibited trichloroethane (PWC11-014). Roughen surface of chafing strip with fine emery cloth and clean with inhibited trichloroethane.
(a) Remove
(b) Bond chafing strips to center fireseal (top and bottom) using silastic cement (PWC09-001), and allow to dry at room temperature for approximately 72 hours.
(c) 28.
Bond chafing strip to rear fireseal mount ring using cement allow to dry at room temperature for at least two hours.
(PWC08-009),
and
WIDE MESH AIR INLET SCREEN A.
Procedure
(1)
The
following repair is permissible provided there is unbonding of the chafing strips from the wire mesh.
(a)
Rebond
dry
chafing strips
at room
to
no
wire mesh
breakage
flanges using silastic cement (PWC09-001). approximately 72 hours.
or
Allow to
temperature for
INLET FAIRING AND SUPPORT RING 29.
SEALING STRIP BONDING A.
Procedure
(1)
Partially detached sealing strips,
(a)
if serviceable, may be rebonded
as
follows:
Remove old cement and thoroughly clean surfaces to be bonded using inhibited trichloroethane (PWC11-014). Roughen surface of sealing strip with fine emery cloth and clean with inhibited trichloroethane.
(b)
For Post-SB1056 engines: Bond sealing strip to top or bottom inlet fairing using silastic cement (PWC09-001), and allow to dry at room temperature for
approximately
72 hours.
Page
4-4-32
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
(c)
Bond to
support ring with silastic cement (PWC08-009), and allow temperature a minimum of 72 hours.
sealing strip
dry
at room
to
INSULATED AND HEATED PNEUMATIC TUBES 30.
REPAIR A.
Procedure
(1)
Cuts in rubber sheaths of insulated tubes may be
repaired
as
follows:
silastic cement (PWC08-009) to damaged area in accordance with manufacturer’s recommendations. If the cut is large, it may be necessary to bind the area lightly with plastic covered wire until the cement has cured.
(a) Apply
(b)
Allow cement to
(c)
Trim
excess
cure
24 hours at
room
temperature.
cement if necessary.
OIL FILTER CHECK VALVE 31.
LAPPING A.
Procedure
(1)
When
a new
lapped
in
oil filter check valve or housing is installed, the check valve may be in the filter housing as follows (Ref. Fig. 4-4-16):
position
Face A of valve in Post-SB1379 engines)
(a) Lap
housing, or sufficiently lapping compound (PWC05-019).
check valve in check valve seat (For to give 360-degree surface contact,
using
(b) After lapping, wash valve and housing thoroughly in petroleum solvent (PWC11-027). Make sure all traces of lapping compound are removed.
IGNITION CURRENT REGULATOR BOX 32.
BRACKET REPAIR (WELDED TYPE) A.
seams securing mounting brackets to box, become cracked, the bracket be reattached to the box by riveting. Drill three holes (using a No. 51 drill) in may locations shown on Figure 4-4-17 and install rivets MS20470B2-4 or equivalent.
Where weld
Page
4-4-33
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FILTER HOUSING
REPAIR WASHER MS9321-08 (IF FITTED)
FACE
A CHECK VALVE
C745A
Lapping
of Oil Filter Check Valve
Figure
4-4-16
Page
4-4-34
Jun 10/2005
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
O
lr
0.1 25
I+++I VIEW ON ARROW
6
A
116
C230A
Ignition
Current
Regulator Riveting of Figure 4-4-17
Detached Bracket to Box
Page
4-4-35/36
Jun 10/2005
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
PART 4
I SECTION 5 1.
HEAYY MAINTENANCE
SPECIAL LIMITS AND TORQUE RECOMMENDATIONS
GENERAL A.
Reference numbers on Figure 4-5-1 indicate the location of fits, clearances, and parts for which torque and spring pressures are specified. A description of, and limits for, these fits, clearances, backlashes, torques and spring pressures is located by referring reference number to Tables 601, 602, 603, 604 and 605 which
corresponds
a
to these
figures. 2.
TERMS AND SYMBOLS A.
Procedure
(1)
The terms and symbols used in Tables 4-5-1, 4-5-2, 4-5-3, 4-5-4 and 4-5-5 explained as follows:
are
DIMENSIONS FOR REF Column This column indicates the minimum and maximum manufacturing dimensions of two mating parts. These dimensions are provided for information only.
(a)
This column indicates the desired minimum and maximum fits and clearances between new parts, and also the allowable limit to which these parts may wear before replacement is necessary.
(b) LIMITS Column
The
(c)
symbol
T indicates
a
tight
fit and
a
fit without
a
T
symbol
denotes
a
loose
fit.
(d)
Unless otherwise
(e)
The
figures in interpreted as
specified,
all fits
are
diametrical.
the MINIMUM, MAXIMUM and REPLACE columns shall be follows: torque in pound-inches, spring pressures in pounds,
and all other limits in inches.
NOTE:
3.
Where the REPLACE column is left blank, the minimum limit applies, as required.
or
maximum
TORQUE APPLICATION A.
Where minimum and maximum figures are given for torque loads, they represent the intended tightening range. Where figures for castle nuts are provided in the minimum column only, these nuts should be tightened to the designated torque and then further
tightened,
if necessary, to
properly align
the
locking
slot. Where
figures
are
provided
columns, the alignment of the locking slot must be obtained without exceeding the maximum torque. If this is not possible, another nut should be used. After tightening nuts to the recommended torque, they shall not be loosened to in the minimum and maximum
permit
insertion of lockwire
or
cotterpins.
Page 4-5-1 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
B.
All nut, bolt and screw torques should be obtained using a thread lubricant. The lubricant should be engine oil or equivalent unless otherwise specified. Torque requirements for interference fit applications such as studs and pipe plugs may be obtained with
or
without lubrication, unless otherwise
specified.
TABLE 4-5-1, FITS AND CLEARANCES Dim. for Ref.
Name
88
Shaft, Propeller
0.4980
0.4990
Dowel
0.4995
0.5000
Adapter, Manifold, Fuel
0.5700
0.5710
243
Min.
Max.
Min. 0.0005T
Inlet
279
Limits
(inches)
REF NO.
0.0010T
Sheath, Manifold
0.5700
0.5720
Bolt, Compressor
0.6350
0.6370
0.6400
0.6420
Shroud, Power Turbine
10.2870
10.2890
Duct, Exhaust
10.2840
10.2870
0.8560
0.8580
0.8460
0.8480
0.1885
0.1890
0.1895
0.1915
Seal, Carbon Face
1.1885
1.1905
Carrier, Seal 1.186 in.
1.1865
1.1875
(inches)
Max.
Replace
0.0020T
0.0020
0.0030
Turbine Stubshaft Post-SB1043 and All PT6A-20A Engines
0.0030
0.0070
Disk, Turbine 307
0.0050T
0.0020
0.0080
0.0120
0.0150
0.0005
0.0030
0.0000
335
Case, Compressor Inlet
Body, Valve,
Pressure
Relief
456
PT6A-20A
Bolt, Machine
Lever, Propeller Governor
705
0.0010T
0.0040T
0.0008T
ID
Page 4-5-2 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-2,
Torque
and Stretch Limits
REF.
NO. 184
Name
Min.
Pre-SB1217
Max.
2151b.in.
2401b.in.
Plug 186
Nut, Propeller Gov. Mounting
170 Ib.in.
190 Ib.in.
187
Nut, Cover, Overspeed Gov. Dr.
170 Ib.in.
190 Ib.in.
188
Nut, Self-locking
145 Ib.in.
165 Ib.in.
199
Post-SB1217
Chip
200
Post-SB1217
Chip 318
451b.in.
551b.in.
Detector
Compressor Turbine Blade Radial Tip Clearance
NOTE:
318
Torque Fingertight Only
Detector Cover
0.0110
Dimensions 0.0110 and 0.0180 are inspection criteria for Section Inspection on engine with a good performance.
Compressor Turbine Blade Radial Tip Clearance
NOTE:
Dimensions 0.0130 and 0.0160 grinding under field conditions.
0.0180
(Run Segments) (Ref. NOTE) run
segments
0.0130
at Hot
0.0160
(New Segments) (Ref. NOTE) are
used when
a new
set of
segments require
359
For PT6A-6 Series Post-SB1OG1
12.0
12.4
359
For PT6A-20 Series Class Average
13.3
13.7
Page 4-5-3 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-2,
Torque and Stretch (Cont’d) Limits
REF. NO. 360
541
Name
Min.
For PT6A-6 Series Class Average (this value is the average of subclassification values marked on 29 vanes)
Max. 12.1
Pre-S B1 043
12.6
6001b.in.
6501b.in.
4201b.in.
4601b.in.
5001b.in.
5501b.in.
Bolt, Compressor Turbine (Molykote G lubrication. Tighten 650 Ib.in., release to zero, re-tighten to final limits.) to 600
541
Post-SB1043 and all PT6A-20A Bolt, Compressor Turbine
541
Post-SB1 439
Bolt, Compressor
I"’
Engines:
Turbine
Post-SB1 459 CANCELLED AND REPLACED BY FIT NO. 1283
549
Nut, Self-locking
550
Nozzle, Fuel
451b.in.
50lb.in.
554
Bolt
20lb.in.
251b.in.
561
Electrical Connectors
Fingertight, plus degrees.
562
Pre-SB1429 Glow Plug Post-S B1 429
Spark Igniter Tighten to 300 Ib.in.,
loosen to 0 Ib.in., minimum to 360 Ib.in. maximum.
Tighten until firm contact, plus 180 degrees.
3001b.in.
retighten
5
3601b.in.
to 300 Ib.in.
Page 4-5-4 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-2,
Torque and
Stretch
(Cont’d) Limits
REF. NO. 566
Name
Pre-SB1429
Lead, Ignition Output
Min.
Max.
Fingertight, plus degrees.
45
Post-SB1 429
Coupling Nut, Igniter Cable 576
580
Nut, Self-locking
12lb.in.
2151b.in.
Plug
15lb.in.
2401b.in.
or
Post-SB1985 and all PT6A-20A
Adapter, Straight
581
Nut, Self-locking
582
Casing,
583
PT6A-6 Series
Wire
Rope
351b.in.
40lb.in.
40lb.in.
60lb.in.
80 Ib.in.
100 Ib.in.
Nut
150lb.in.
2501b.in.
584
Nut
585
Nut, Castellated
20lb.in.
30lb.in.
586
Nut
60lb.in.
80lb.in.
587
PT6A-6 Series
8 Ib.in.
12 Ib.in.
Nut, Self-locking, (T4 Thermocouple Connection)
’588
PT6A-6 Series
10 Ib.in.
15 Ib.in.
Nut, Self-locking, (T4 Thermocouple Connection)
596
PT6A-20 Series
Slb.in.
12lb.in.
Screw, Cap
Page 4-5-5 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-2,
Torque
and Stretch
(Cont’d) Limits
REF. NO. 597
Name PT6A-20 Series
Min.
Max.
401b.in.
501b.in.
Nut, Coupling
598
PT6A-20 Series Extension, Fuel Control Arm
251b.in.
351b.in.
599
PT6A-20 Series
251b.in.
351b.in.
151b.in.
201b.in.
Nut, Castellated
600
PT6A-20 Series
Nut, Self-locking
902
Plug, Machine
903
Adapter,
950
Nut, Slot Hex
952
Metering Plug,
961
Pt6A-20 Series
I
Plug, Accessory Gearbox
Bleed Valve
Terminal Block
Connection)
PT6A-20 Series Bolt (T5 Terminal Block
Connection)
Bolt
962
Access
(T5
1501b.in.
2001b.in.
2001b.in.
2201b.in.
131b.in.
221b.in.
401b.in.
501b.in.
10 Ib.in.
15 Ib.in.
8 Ib.in.
12 Ib.in.
966
Bolt
351b.in.
451b.in.
967
Bolt
161b.in.
201b.in.
Nozzle, Bleed Valve
10 Ib.in.
15 Ib.in.
Page 4-5-6 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-2,
Torque
and Stretch
(Cont’d) Limits
REF NO. 1283
Name
Min.
Post-SB1 459
Max.
5001b.in.
550ib.in.
Turbine
Bolt, Compressor (Molykote G lubrication. Torque to 600 650 Ib.in., release to zero, re-torque to final limits.)
TABLE 4-5-3,
Spring
Pressure Limits
REF.
NO. 606
Name
Min.
Max.
Pre-SB1043
Spring,
Helical
Compression
1.500 inch
8 Ibs.
TABLE 4-5-4,
10 Ibs.
Special Assembly Limits
REF NO. 650
Name
Max.
Coating (1)
(2)
Coat
packing, packing retainer and external thread of fitting sparingly with petrolatum (PWC06-002), or fluid to be used in line, and assemble nut, packing retainer and packing onto fitting. Work packing retainer into counterbore of nut. Turn down until packing is pushed firmly against lower thread of fitting. Install
fitting
into boss, at the
contacts boss
turn
(3)
same
time, keep
nut
turning
with
fitting
until
packing
sudden torque increase). While holding nut stationary, in 1-1/2 turns. Position fitting by turning in, not over, one more turn.
fitting
(recognized by
While holding fitting stationary, turn nut down against boss, then lockwire. Obtain metal-to-metal contact between nut and boss without exceeding recommended
torque. Extrusion of packing
658
Min.
or
packing
retainer not
permissible.
Gaskets
(1)
When
gaskets are used, retorque bolts after acceptance run and before shipping. gasket changes made in service, retorque bolts after a minimum of half hour one running and before a maximum of five hours running iscdmpleted. new
For
Page 4-5-7 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
TABLE 4-5-5,
Compressor Turbine Stater
Backlash Limits
REF. NO.
Name
Min.
Max.
NOT APPLICABLE
Page 4-5-8 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
186
187
O
O
188 186
187
PT6A-6A
188
PT6A-6 NON-REVERSING
Reduction Gearbox
PT6A-6A
Clearances Fits 4-5-1 (Sheet 1 of Figure
Engines
c1223_1C
16)
Page 4-5-9 Aug 27/2004
PRATT
WHITNEV CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
200~ 199-
184
PRE-SB1217
POST-SB1217
Reduction Gearbox
PT6A-6A
Engines~
Fits 6 Clearances Figure 4-5-1 (Sheet 2)
Page 4-5-10 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
186
88 187
188
184
(PRE-SB1217)
200 199
(POST-SB1217)
Reduction Gearbox-Pre-SB1124 PT6A-6, PT6A-6B and PT6A-20 Fits
Figure
Engines
C1224B
Clearances 4-5-1
(Sheet 3)
Page 4-5-11 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
186
187
88
188
184
(PRE-SB1217)
200 199
(POST-SB1217)
Reduction Gearbox-Post-SB1124 PT6A-20 and PT6A-20A
Fits
Figure
Engines
C12258
Clearances 4-5-1
(Sheet 4)
Page 4-5-12 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
oli~ ~A
967
966
650 VIEW
V
A
Post-SB1046 PT6A-20
DETAIL
Engines, Fits
Figure
Post-SB1 043/1046 PT6A-20A
B
Engines C41698_1 A
Clearances 4-5-1
(Sheet 5)
Page 4-5-13 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
´•a o
o
o
561
Y
I((
576
580
REAR VIEW OF ENGINE
Post-SB1046 PT6A-20
Engines, Post-SB1043/1046 Fits
Figure
PT6A-20A
Engines C41698_2A
Clearances 4-5-1
(Sheet 6)
Page 4-5-14 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
C
318 307
597
554
541
264
278 277
359
360
211
Q-´•´• PRE-SB1043 ENGINES AND PRE-SB1046 ENGINES
Post-SB1046 PT6A-20
Engines, Fits
Figure
Post-SB1 043/1046 PT6A-20A
Engines C41699_1 A
Clearances 4-5-1
(Sheet 7)
Page 4-5-15 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
C 962-~
243
VIEW
FLANGE
C
C 318
550~
59!
554
541 541
562 -1
360
j 566
658
POST-SB1043 ENGINE AND POST-SB1046 ENGINES
Post-SB1046 PT6A-20
Engines, Fits
Figure
Post-SB1043/1046 PT6A-20A
Engines C41699_2A
Clearances 4-5-1
(Sheet 8)
Page 4-5-16 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
C
307
597
318 250
539
2642n 606
359
241
PRE-SB1043 ENGINES AND PRE-SB1046 ENGINES 588
587
359 307
318
554
967
952
Q50
~pe"
POST-SB1043 ENGINES AND POST-SB1OI ENGINES
Pre/Post-SB1043 and Post-SB1046 PT6A-6 and PT6A-6B Fits
Figure
Engines
C12288
Clearances 4-5-1
(Sheet 9)
Page 4-5-17 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
G
FLANGE 581
r
E
583 582
ri
I
585
I
582 549
L586L582
585
SECTION
G-G
Propeller Reversing Linkage Fits
Figure
PT6A-6A
Engines
C1230_1B
Clearances 4-5-1
(Sheet 10)
Page 4-5-18 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
583
FLANGE
C
FLANGE
7
585
7
r
584
r
581
A
SECTION
A-A
A
1
582
Propeller Reversing Linkage Fits
Figure
PT6A-6A
Engines
C1230_2B
Clearances 4-5-1
(Sheet 11)
Page 4-5-19 Ailg 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL
MANUAL PART NO. 3015442
583
582
\_H MI 11
M IIII
582
i Klj~i
i i
´•-C´•
ii
586
1582
REAR FIRESEAL
599
I
.X/
CENTER FIRESEAL
a
r
598
k SECTION
H-H
SECTION
N-N
SECTION
J
K-K‘
VIEW
L
SECTION
M-M
585
Reversing Linkage Fits
Figure
PT6A-6B and PT6A-20
Engines
C1231_1B
Clearances 4-5-1
(Sheet 12)
Page 4-5-20 Aug 27/2004
WHITNEY CANADA
PRATT
MAINTENANCE MANUAL MANUAL PART NO. 3015442
"O"hR
i~E
I !I! r-
VIEW LOOKING FROM REAR
F-F
SECTION
F
SECTION
lr
W"
GD-D
SECTION
C-C
SECTION
B-B
C16~LF D
SECTION
E-E
´•I~
599
S
B B 583
SECTION SECTION
~:F ~V
S-S
VIEW
A
R-R
Reversing Linkage Fits
Figure
PT6A-6B and PT6A-20
Engines
C1231_28
Clearances 4-5-1
(Sheet 13)
Page 4-5-21 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
FLANGE
583
C
FLANGE
A
582
B
D
r 582
A ´•C J
IYI
i
I
~B
582
I.i""i REAR FIRESEAL
586
CENTER FIRESEAL
598
585
VIEW
A
SECTION
Reversing Linkage Fits
Figure
B-B
PT6A-20A
SECTION
Engines
C-C
C1858_1A
Clearances 4-5-1
(Sheet 14)
Page 4-5-22 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
456 599
OYO
VIEW LOOKING FROM REAR
584
599
E
YIEW
O
L
i
581
Reversing Linkage
sEcTlaEl
PT6A-20A
Engines
E-E
C1858_2A
Fits 6 Clearances
Figure
4-5-1
(Sheet 15)
Page 4-5-23 Aug 27/2004
PRATT
WHITNEY CANADA
MAINTENANCE MANUAL MANUAL PART NO. 3015442
705
Accessory
Gearbox
Fits
Figure
(All Engines)
C1233B
Clearances 4-5-1
(Sheet 16)
Page 4-5-24 Aug 27/2004