Manual de Mantenimiento de Beechcraft - Bonanza 609
March 25, 2017 | Author: Abraham Said | Category: N/A
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Programas de Mantenimiento de la aeronave Bonanza 609 Orden de tarea por ATA's Ilustraciones Idioma inglés...
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ATP INDEX COPYRIGHT
2002
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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Customer Service
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(800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Raytheon Aircraft Co. Bonanza V35B; F33A;
F33C; A36; A36TC; B36TC
Maintenance Manual Section
Topic
General Information
Title Page Manufacturer’s Introduction Record of Revisions Record of
Temporary Revisions Letter of Transmittal (Highlights
of Changes)
Aircraft General
05.00.00
Time Limits/Maintenance Checks
05.00.00
List of Effective
05.10.00 05.10.00 05.20.00
Pages
Time Limits
Overhaul and
Replacement
Scheduled Maintenance Checks
06.00.00
Dimensions and Areas
06.00.00
List of Effective
06.00.00 07.00.00 07.00.00
07,00.00
Pages
General
Lifting and Shoring List of Effective Pages General
08.00.00
Leveling and Weighing
08.00.00
List of Effective
08.00.00
Pages
General
09.00.00
Towing and Taxiing
09.00.00
List of Effective
08/19/2002
Schedule
Pages
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
1 of
6
Section
09.00.00
10.00.00 10.00.00 10.00.00
Topic General
Parking, Mooring, Storage, and Return List of Effective Pages General
11.00,00
Placards and Markings
11.00.00
List of Effective Pages
11.00.00
General
11.20.00
Exterior Placards and
12.00.00
Servicing
12.00.00
List of Effective Pages
12.00.00
General
12.10.00
Replenishing
12.20.00
Scheduled Service
Airframe
Markings
Systems Airframe
20.00.00
Standard Practices
20.00.00
List of Effective Pages
20.00.00
to Service
General
20.01.00
Torque Wrenches
20.02.00
Electrostatic Discharge Sensitivity
20.03.00
Electrical Bonding
20.04.00
Control Cables and Pulleys
20.05.00
Bearings
20.06.00
Tube and Hose Assemblies and Fittings
20.07.00
Locking
20.08.00
Airplane
20.09.00
Corrosion
Devices
Finish Care
Conditioning
21.00.00
Air
21.00.00
List of Effective Pages
21.40.00 21.50.00
Heating and Ventilating System Cooling
23.00.00
Communications
23.00.00
List of Effective Pages
23.10.00 23.10.00
08/19/2002
Speech
Communication
Ground Communication System
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
2 of
6
Section
23.60.00
Topic Static Discharging
24.00.00
Electrical Power
24.00.00
List of Effective Pages
24.30.00
DC Generation
Standby Generator
24.31.00 24.40.00
External Power
24.50.00
AC Electrical Load Distribution
25.00.00
Equipment/Furnishings
25.00.00
List of Effective Pages
25.00.00
General
25.60.00
Emergency
27.00.00
Flight Controls Record of Temporary Revisions
27.00.00
List of Effective Pages
27.00.00
27.00.00
General
27.10.00
Aileron and Tab
CE-748,CE-772 and After;CJ´•149 and After;D-10097,D-10120
27.10.00
and After;E-I111,E-1241 Thru E-21111 Except E-1946 and
E-2104;EA-1 Thru EA-388 Except EA-320 After, EA-320, EA389 E-1946, E-2104, E-2111
27.11.00 27.20.00
Rudder and Tab
27.20.00
F33A, F33C, A36, A36TC AMD B36TC
27.21.00
V35B
27.30.00
Elevator and Tab
Stall Warning/Safe Flight System
27.31.00 27.50.00
Flaps
27.70.00
Gust Lock and
Dampener
28.00,00
Fuel
28.00.00
List of Effective Pages
28.00.00
General
28.10.00
Storage
28.20.00
Distribution
28.40.00
Indicating
30.00.00
Ice and Rain Protection
30.00.00
List of Effective Pages
30.00.00
08/19/2002
After
General
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
3 of
6
Section
Topic
Propellers/Rotors
30.60.00
32.00.00
Landing Gear
32.00.00
List of Effective
Pages
32.00.00
General
32.10.00
Main Gear and Doors
32.20.00
Nose Gear and Doors
32.30.00
Extension and Retraction
32.40.00
Wheels and Brakes
32.50.00
Steering
32.60.00
Position and Warning
33.00.00
Lights
33.00.00
List of Effective
Pages
33.20.00
Interior
33.40.00
Exterior
34.00.00
Navigation
34.00.00
List of Effective Pages
34.10.00
Flight Environmental
34.40.00
Independent
Position Determining
35.00.00
Oxygen
35.00.00
List of Effective
35.00.00
General
36.00.00
Pneumatic
36.00.00
List of Effective
36.00.00
Data
Pages
Pages
General
39.00.00
Electric Panels Parts and Instruments
39.00.00
List of Effective
Pages
39.00.00
General
39.10.00
Instrument and Control Panels
39.20.00
Electrical and Electronic Equipment Racks
Structures
51.00.00
Standard Practices
51.00.00
List of Effective
51.00.00
08/19/2002
Structures
Pages
General
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
4 of
6
Section
Topic
52.00.00
Doors
52.00.00
List of Effective Pages
52.00.00
General
52.10.00
Passenger/Crew Cargo
52.30.00
53.00.00
Fuselage
53.00.00
List of Effective Pages
Plates/Skin
53.30.00 55.00.00
Stabilizers
55.00.00
List of Effective Pages
55.00.00
General
55.10.00
Horizontal Stabilizer
55.20.00
Elevator and Rudder
55.30.00
Vertical Stabilizer
55.40.00
Rudder
56.00.00
Windows
56.00.00
List of Effective
General
56.10.00
Flight Compartment Passenger Compartment
57.00.00
Wings
57.00.00
List of Effective Pages
57.00.00
General
57.30.00
Plates/Skins
57.40.00
Attach Fittings
57.50.00
Flight Surfaces
Canard
Pages
56.00.00
56.20.00
or
Propeller/Rotor 61.00.00
Propellers/Propulsors
61.00.00
List of Effective Pages
61.10.00
Propeller Assembly
61.20.00
Controlling
Power Plant
08/19/2002
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
5 of
6
Section
Topic
71.00.00
Power Plant
71.00.00
List of Effective Pages
71.00.00
General
71.10.00
Cowling to Continental Aircraft
72.00.00
Engine (Refer
73.00.00 73.30.00
Engine Fuel and Control List of Effective Pages Fuel Flow Indicating
74.00.00
Ignition
74.00.00
List of Effective Pages
73.00.00
74.00.00
General
74.20.00
Distribution
77.00.00
Engine Indicating
77.00.00
List of Effective Pages
77.00.00
General
79.00.00
Oil
99.00.00
List of Effective Pages
99.00.00
General
80.00.00
Starting
80.00.00
List of Effective Pages
80.10.00
Cranking
81.00.00
Turbines
81.00.00
List of Effective Pages
81.00.00
Engine Manuals)
General
91.00.00
Charts
91.00.00
List of Effective Pages
91.00.00
Chart 1 Consumable Materials
91.00.00
Charts 2, 4 and 5
91.00.00
Installation of Flared Fittings
91.00.00
Chart 3 Thread Lubricants
End of Index
08/19/2002
Copyright
Aircraft Technical BC
0220
MM
Publishers
Page
6 of
6
NIFGI INTRO
Ral~heon Aircraft BEECH BONANZA SERIES
V35B F33A F33C A36
A36TC B36TC
(D-10097, D-10120 and After) (CE-748, CE-772 and After) (CJ-149 and After) (E-llll, E-1241 and After) (EA-I thru EA-272 Except EA-242) (EA-242, EA-273 and After)
Nlaintenance Manual
NOTE: This manual
was
formerly
called the Beechcraft Bonanza Series
Maintenance Manual.
Copyright P/N: 36-590001-9 Issued:
May
9, 1980
0
Raytheon
Aircraft
Company 2002 P/N: 36-590001-9A23 Revised: june 28, 2002
Published
By
RAVTH EO N AIRCRAFT COM PANY
P.O. Box 85
Wichita, Kansas 67201 U.S.A
NOTE Where Beech Aircraft
Corporation is referred to in this publication, Raytheon Aircraft Company.
it will be taken to read
EXPORT STATEMENT
Exported under the authority of license exception: TSU. ’7hese commodities, technology or software were exported from the United States in accordance with Export Administration Regulations. Diversion contrary to U.S. law
prohibited.
i
Raytheon Ai
rcraatRaytheon
Company
Member of GAMA General Aviation
CAIIA
Manufacturers Association
RECORD OF REVISIONS
MFG REV
DESCRIPTION
NO
ISSUEDATE
ATPREVDATE
INSERTEDBY
A22
See
Highlights
11/10/00
3/5/01
ATP/RCL
A23
See
Highlights
6/28/02
9/4/02
ATPNDR
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
LIST OF EFFECTIVE REVISIONS
Always destroy superseded pages when you
insert revised pages.
Title Page
June 28, 2002
"A"
Page
A23
"B"
Page
A23
PART NUMBER
DATE
CHAPTERS AFFECTED
36-590001-9A
May 9, 1980
Original
36-590001 -9A 1
October 10, 1980
Introduction, 5, 6, 11,24, 25, 30,34,36,73
36-590001-9A2
January 28,
36-590001 -9A3
March 12, 1981
36-590001-9A4
January 20,
1981
1982
Introduction, 12, 21, 25, 33, 35, 61,71,73, 77, 81 5, 11,32, 57
Introduction, 6, 12, 21, 23, 24, 25, 27, 28, 34, 39, 57, 61,81, 91
36-590001 -9A5
February 18,
36-590001-9A6
October 27, 1983
1983
Introduction, 5, 6, 27 Introduction, 5, 6, 12, 21, 24,
27,28,30,32,33,39,61,71, 72, 79, 91 36-590001-9A7
December 21, 1983
71
36-590001 -9A8
January 18, 1984
5, 12, 20, 28, 57, 91
36-590001-9A9
September 27, 1984
Introduction, 5, 12, 21,23, 25, 27, 33, 35, 36, 71, 74, 91
1985
36-590001-9A10
May 31,
36-590001-9A11
August 29,
36-590001-9A12
August 28, 1987
1985
Introduction, 27 12, 28
Introduction, 5, 11, 12, 25, 27, 28, 32, 36, 51, 55, 71,74
NOTE: A List of Effective pages will be in the front of each chapter. a part number which appears on the title page with the date of the issue. Subsequent revisions are identified by the addition of a part number Al after a part number denotes the first revision to the basic publication, A2 the second, etc Occasionally, it is necessary to reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto As these replacement reisstles are the code will also change to the next successive letter of the alphabet at each issues For example, B for the first reissue, C for the second, etc
publications
are
assigned
code after the
ordering a handbook, give the basic number, and the reissue code when applicable, if a complete up-to-date publication be required, give the basic number and revision code for the particular set of revision pages you desire
Is
desired Should only revision
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
Always destroy superseded pages when
A23
(Continued)
you insert revised pages.
PART NUMBER
DATE
CHAPTERS AFFECTED
36-590001-9A13
March 30, 1990
Introduction, 7, 32
36-590001-9A14
June 20, 1991
Introduction, 5, 12, 20, 27, 55, 71, 91
36-590001-9A15
December 20, 1991
Introduction, 52
36-590001 -9A 16
October 16, 1992
5, 9, 11,12, 21,25, 27, 28, 51, 55, 56, 91
36-590001 -9A 17
November 16, 1994
Introduction, 32, 74
36-590001 -9A 18
August 18,
36-590001-9A19
March 29, 1996
5, 27
36-590001 -9A20
February 26,
27
36-590001 -9A21
December 23, 1999
5, 32, 52
36-590001 -9A22
November 10, 2000
20, 25, 57
36-590001-9A23
June 28, 2002
5
1995
1999
Introduction, 12, 21, 23, 27, 32, 91
RECORD OF TEMPORARY REVISIONS
ia~b´• TEMP REV NO
DESCRIPTION
ATP REV
INSERT
DATE
REI
REMOVE
DATE
BY
REMOVED
INCOR
BY
ISSUE DATE
27-1
27-50-00:4
12/1 1/92
27-2
27-50-00:4
1 1
/1 5/93
12/1 5/97
ATP/M B
1
2/1 5/97
27-2
2/1 5/97
ATP/M B
8/09/99
A20
1
ATP/M B /JRS
Raytheon
Aircraft
BEECH BONANZA SERIES MAINTENANCE MANUAL
RECORD OF TEIIlIFORARY REVISIONS Affected
emporary Revision No.
Removed
Inserted
By Chapter
Page(s)
Date
By
Revision No.
Date
inserting or removing a temporary revision, the applicable revision number and the initials of the person(s) inserting and/or removing these revisions should be recorded on these pages.
When
NOTE: Insert the Record of
Temporary
Revisions after the
Log
of
Temporary Revisions page(s).
Pagel
Rayeheon
Aircraft
SEECH BONANZA SERIES MAINTENANCE MANUAL
RECORD OF TEMPORARY REVISIONS
No.
Page
2
Removed
I
Inserted
Affected
emporary Revision
By Chapter
Page(s)
By
Date
Revision No.
Date
Raytheon
Aircraft
BEECH BONANZA SERIES MAINTENANCE MANUAL
LOG OF TEMPORARY REVISIONS Revision No.
Date
27-1
Dec 11/92
27-2
Nov 15/93
Subject drive cable connection
Flap Flap drive cable connection
Incorporated TR 27-2 A20
Page 1 Feb 26/99 NOTE: Insert this
Log
of Temporary Revisions after the Record of Revisions page.
Ral~heMI Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
P/N 36-590001-9, REVISION A23, JUNE 28, 2002 HIGHLIGHTS The
chapters
which have been revised
are
listed below with the
Highlights
of each
change.
Remove the affected
pages and insert the A23 revision in accordance with the attached Instruction Page. Enter the revision number and the date inserted on the Record of Revisions page of this manual. The Highlights Page may be retained with the manual for future reference.
Description
Chapter/Section
5-10-00
Added data
5-20-00
data from 1000 hours to
Changed
references for Hartzell
Pressure
Pump
to
Magneto
Flap Motor
Added data
Changed
Change
Nose Gear Retract Rod Rod-ends from
on
Changed shimmy damper
Added
of
supplier
and
on
Chapter
5-20-00.
condition.
propellers, Woodward Propeller Governor
and Air
data.
Standby
Air Pressure
Brush check removed
System
replacing
motor
Check Valve data. on
condition
covers
the brushes.
the FACTS program.
on
references from FAR to 14 CFR.
Added data for
Standby Alternator/Generator,
Instrument Air
System
and
Standby
Instrument Air. Revised Added
Landing Gear Gearbox inspection.
inspection
of Fuel Strainer and Control Column. Revised Fuel Cell,
Caps
and
Vents data.
Added
Inspection
Revised Nose
of
Landing
Revised Cable and
Added
Flapper
inspection
Valve data.
Gear Retract Rod data.
Pulleys
data.
of Rudder Forward
Soar and other chages.
Page A23
1
Jun 28/02
Raytheon Aircraft REVISION 36-590001-9A23 to the
BEECH BONANZA SERIES MAINTENANCE MANUAL
P/N 36-590001-9
Title
MAV 9,
1980)
INSERT
REMOVE PAGE
(ISSUED:
CHAPTER
PAGE
Title
Page
CHAPTER
DATED
Jun 28/02
Page
Logo Page
Logo Page
"A"
Page
"A"
Page
A23
"B"
Page
"B"
Page
A23
All
5EFF
1
5-EFF
Jun 28/02
All
5-TOC
1 and 2
5-TOC
Jun 28/02
All
5-10-00
1 thru 6
5-10-00
Jun 28/02
All
5-20-00
1 thru 20
5-20-00
Jun 28/02
NOTE
These instruction pages may be discarded after the above revision has been properly incorporated into the Maintenance Manual.
Page
1 of 1
MAINTENANCE MANUAL INTRODUCTION LIST OF PAGE EFFECTIVIP/ CHA PTER-SECTION-SUBJECT
Introductian-Effectivity Introduction
PAGE
DATE
1
Aug 18/95
1
2
Sep 27/84 Sep 27/84
3
Jan 20/82
4
Jan 20/82
5
May 9/80
6
Oct7/83
7
Sep 27/84 Sep 27/84 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95
8 9 10 11 12 13 14 15 16 17
18 19 20 21
22 23 24 25
26 27
28 29
30 31 32
33
Introduction-Effectivity A18
Page 1 Aug 18/95
BEECHCRAFT BONAN;LA SERIES
MAINTENANCE MANUAL
WARNING
INTRODUCTION
only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources, in Use
NOTE Service Publication reissues
automatically provided
manual. For information reissues
or
revisions
or
revisions
connection with the maintenance and
are not
to the holders of this on
how
applicable
to
to this
Beech
Genuine BEECHCPAFT parts and inspected under rigorous
are produced procedures to insure airworthiness and suitability for use in Beech airplane applications. Parts purchased
Service Bulletin No. 2001.
from The BEECHCRAFT Bonanza Series Maintenance Manual is in accordance with GAMA (General Manufacturers Association) Specification No. 2 also meets the intent of the requirements of Specification 100 (Air Transport Association of
prepared
Aviation
format. It the ATA
America)
with respect to the arrangement and content of the SystemlChapters within the designated chapter´•numbering
system.
The Maintenance Manual is
of
obtain
manual,
refer to the latest revision of BEECHCRAFT
I
repair
airplanes.
supplemented by
the
sources
Salvaged airplane parts,
even
reworked
parts
obtained from non-BEECHCRAFT approved or parts, components, or structural assemblies, the service history of which is unknown or cannot be authenticated, may have
following publications: (1)
The BEECHCRAFT Bonanza 36 Series Parts Catalog, P/N 36-590001-1 (2) BEECHCRAFT Bonanza 35 Series Parts Catalog, P/N 35-590102-5 (3) BEECHCRAFT Bonanza 33 Series Parts Catalog, P/N 33-
sources,
(4) BEECHCRAFT Bonanza Wiring Diagram Manual, P/N 35-590102-9 (5) BEECHCRAFT Bonanza 33, 35, 36 Series Continuing Care Inspection Guide PIN 9836711 and (6) BEECHCRAFT Approved Model 33, 35 and 36 Inspection Guide P/N 98-32227.
temperatures
590010-7
other than BEECHCAAFT,
though outwardly identical in appearance, may not have had the required tests and inspections perfor~ed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane.
been
subjected or
unacceptable
stresses
have other hidden
damage,
to
or
not
through routine visual or usual nondestructive testing techniques. This may render the part, component or structural
discernible
assembly, even though originally manufactured by BEECHCAAFT, unsuitable and unsafe for ~airplane use.
NOTICE
BEEC)~1CRAFT expressly
Corporation expressly reserves supersede, cancel and/or declare
Seech Aircraft the
right
to
obsolete any part, part numbers, kits or publication that may be referenced in this manual without
prior
disclaims
any
respon!jibility for maifunctions, failures, damage or injury caused by use of non-BEECHCRAFT approved parts.
notice.
ASSIGNMENT OF SUBJECT MA TERIAL It
shall
be
owner/operator
the
responsibility
of
the
to ensure that the latest revision
publications referenced in this manual utilized during operation, servicing,
of
maintenance of the
are
and
publication is organized at four levels: Group, System/Chapter, Sub-System/Section, and Unit/Subject.
airplane.
CORRESPONDENCE
question should arise concerning the care of your airplane, it is important to include the airplane serial number in any correspondence. The serial number appears on the model designation placard (see Chapter 11 for placard If
The content of this
Identified by different colored divider tabs. Group are primary divisions of the manual that enable separation of content. Typical of this division separation between Airframe Systems and the Power
These
broad is the Plant.
a
location).
System/Chapter
The various groups
are
broken down into
major systems such as Environmental Systems, Electrical Power, Landing Gear, etc. The systems are arranged more or less alphabetically rather than by precedence or
INt~ODUCTION A9
Page 1 Sep 27/84
BEECHCRAFT BONANZA SEAIES MAINTENANCE MANUAL
importance. They the first element of
a
assigned
a
number, which becomes
standardized
numbering system. Thus,
are
the element "28" of the number 28-00-00 refers to the
chapter "Fuel". Everything concerning the fuel system be covered in this
CHAPTER SECTION SUBJECT
SUBJECT
FUEL
28
chapter.
Indicating
28-40
broken down into sub-systems. These sub-systems are identified by the second element of a standard numbering
Fuel
28-40-00
system. The number "40" of the number 28-40-00 is for the indicating portion of the fuel system.
The material is
Sub-System/Section
The
major systems of
The individual units within
Unit/Subject be identified
by
system, such
an
airplane
are
sub-system may numbering is assigned by the
a
the third element of the standard
as
28-40-01. This number
manufacturer and may,
or
PAGE
will
Uuantity Indicators arranged
within the
1
chapter
in
ascending
numerical sequence. The Chapter-Section Subject number and page number are found at the lower outside corner of each page.
may not, be used and will vary in
usage.
EFFECTI1~N LOG OF EFFECTIVE REVISIONS
APPLICATION The to the GAMA
or ATA format will
Any publication conforming use the same basic numbering system. Thus, whether manual be
the
Log of Effective
Revisions
the manual lists the revisions
following the title page of currently effective for the
manual.
BEECHCRAFT Bonanza Series Maintenance a BEECHCRAFT Bonanza Wiring Diagram
a
Manual, or Manual, the person wishing information concerning the
indicating portion of
the fuel
system, would refer
to the
Tab "28, Fuel". The table of contents in the front of this chapter will provide a list of sub-systems covered in this chapter.
AEROFICNE
System/Chapter
(GAMA) has specification for microfiche and registered the Aerofiche for use by all GAMA Members. Consult the
The General Aircraft Manufactures Association
developed For
example:
name
a
28-00
General
issue of the Publications Price List for an enumeration of the maintenance information available in
28-10
Storage
Aerofiche form for order from Seech Aircraft Corporation.
current
(Tanks, cells, necks, caps, instruments, etc.) 28-20
Distribution
(Fuel lines, pumps, valves, controls, etc.) 28-30
28-40
Dump (If in-flight dumping system is installed, it would appear here.) Indicating (Quantity, temperature, pressure, etc., does not include engine fuel flow
or
pressure.)
ALPHABETICAL INDEX An
alphabetical index,
page 9 of this assistance in
alphabetical
which may be found beginning on is also provided as an
Introduction,
locating the desired provides the chapter
index
information. and
The
sub-chapter
in
which any given information may be found. Reference to the Table of Contents in the front of the indicated chapter will
provide
the exact page
on
which the information
can
be found.
LIST Of EFFECTIVE PAGES this example further, by turning to the Table of Contents for Chapter 28, the following information might be
Carrying
found within the list:
Pages following each Chapter GividerTab, lists the issue date of each page that is effective for that chapter.
The list of Effective
INTRODUCTION
Page2 Sep 27/84
ASi
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL SVSTEM/CHAPTER INDEX GUIDE
following System/Chapter, Sub-System/Section Index Guide is prepared in Specification No. 100 and GAMA Specification No. 2 for use with Maintenance Manuals, Parts Catalogs and Wiring Diagram Manuals. The following chapters are not applicable to this Maintenance Manual: 4, 22, 26, 29, 31, 37, 38, 49, 60, The
accordance with both ATA
70, 75, 76, 77, 78, 83, and 95.
SYSTEMI
SUB-SYSTEMI
CHAPTER
SECTION
TITLE
INTRODUCTION 5
TIME LIMITS/MAINTENANCE CHECKS 10
Time Limits
20
Scheduled Maintenance Checks
6
DIMENSIONS AND AREAS
7
LIFTING AND SHORING General
00 8
LEVELING AND WEIGHING 00
j 9
TOWING AND TAXIING 00
10
12
00
General
20
Exterior Placards and
Markings
SERVICING General
10
Replenishing
20
Scheduled Servicing
STANDARD PRACTICES 20
21
General
REQUIRED PLACARDS
00
20
General
PARKING AND MOORING 00
11
General
AIRFRAME General
ENVIRONMENTAL SYSTEMS 40
Heating
60
Cooling
INTRODUCTION
Page A4
3
Jan 20182
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
23
COMMUNICATIONS 60
24
25
30
DC Generation
40
External Power
50
Electrical Load Distribution
EQUIPMENT/FURNISHINGS 00
General
10
Flight Compartment Passenger Compartment Emergency
60
FLIGHT CONTROLS
00
General
10
Aileron and Tab
20
Rudder and Tab
21
Ruddervator and Tab
30
Elevator and Tab
31
Warning/Safe Flight System Flaps Gust Lock and Damper
50 70
28
30
32
33
Discharging
ELECTRICAL POWER
20
27
Static
Stall
FUEL 00
General
10
Storage
20
Distribution
40
Indicating
ICE AND RAIN PROTECTION
00
General
60
Propellers
LANDING GEAR 00
General
10
Main Gear and Doors
20
Nose Gear and Doors
30
Extension and Retraction
40
Wheels and Brakes
50
Steering
60
Position and
Warning
LIGHTS 20
Interior
40
Exterior
INTRODUCTION
Page4 Jan 20/82
A4
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
34
NAVIGATION AND PITOT STATIC 10
35
OXVGEN 00
36
General
10
instrument 3 Control Panels Electrical 5 Electronic Equipment Racks
STRUCTURES
53
00
General
10
Passenger/Crew Cargo Doors
56
10
Horizontal Stabilizers
20
30
Elevator and Ruddervator Veriical Stabilizer
40
Rudder
WINDOWS
General
10
Flight Compartment
20
Cabin
WINGS
30
General Plates/Skin
40
Attach
Fittings
50
Flight
Surfaces
00
61
Plates/Skin
STABILIZERS
00
57
Doors
FUSELAGE 30
55
General
DOORS
30
j
MULTIPURPOSE PARTS
00
00
52
General
ELECTRICIELECTRONIC PANELS
20 51
General
PNEUMATIC 00
39
Flight Environmental Data/Pitot Static
PROPELLERS 10 20
Propeller Assembly Controlling
INTRODUCTION
Page 5 May 9180
BEECHCRAFI BONANZA SERIES MAINTENANCE MANUAL
71
POWER PLANT 00
General
10
Cowling
72
ENGINE
73
ENGINE FUEL AND CONTROL
Indicating
30 74
IGNITION 00
General
20
Distribution
77
ENGINE INDICATING
General
00
OIL
79
General
00 80
STARTING
Cranking
10
TURBINES
81
General
00
91
CHARTS
SUPPLEMENTARY PUBLICATIONS
Following
is
a
list
of
VENDOR PUBLICATIONS
publications providing servicing,
overhaul and parts information on various components of the BEECHCRAFT Bonanza which you may obtain to supplementthe Maintenance Manual. In most instances,
ENGINE
1
10-520
you should obtain the publications directly from the manufacturer or his distributor. Only a few, vendor manuals
Service Parts
supplementary publications, are available from Commercial Products Support, Beech Aircraft Corporation.
Mobile, Alabama 36601.
and Beech
Those
which
are
Publications Price
available List.
Since
are a
listed
wide
in the current
variety
of
radio
equipment is available and because radio manufacturers normally supply parts and a servicing manual with each set, radio publications have not been included in the list.
Motors
Catalog Form X-30040. Teledyne Continental
Aircraft
Maintenance
Teledyne
publications
on
additional
available, they will be added
components become
to this list of
and
Division, Post Office Box 90
Overhaul
Continental
Motors
Manual Aircraft
Form
X-30039.
Products
Division,
Post Office Box 90 Mobile, Alabama 36601.
Operators Handbook Motors Aircraft
As
Products
Form X-30041,
Products
Teledyne
Continental
Division, Post Office Box 90
Mobile, Alabama 36601.
publications.
INTRODUCTION
Page6 Oct7/83
A6
BEECHCRAFT BONANZA SEAIES NIAINTENANCE MANAUL
TSIO-520
Overhaul Manual with Parts List Bulletin No. 33080 for the 35-380088-1 Propeller Governor, Woodward Governor
Manual for TSIO-520 Series Aircraft Engines Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama
Company, Rockford,
36601.
MAGNETOS
Operators Manual for TSIO-520-U and -UB Engines Form No. X-30044, Teledyne Continental Motors Aircraft Products
Overhaul Instructions for Bendix S-1200 Series
Overhaul
Illinois.
Form No. X-30042,
Division, Post Office Box 90, Mobile, Alabama 36601.
Magnetos Corporation,
Form L-609, Scintilia Division, Bendix Aviation Sidney, New York.
10-550
Service Parts List for Bendix 8-1200 Series Magnetos, Form L-608, Scintilla Division, Bendix Aviation Corporation,
Illustrated Parts Catalog Form X-30569, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama 36601.
Sidney,
New York.
Installation, Maintenance and Operation Instructions, SGRNand S6AN-205 Magnetos, Form L-526, Scintilla
201
Overhaul Manual Form X-30568, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90,
Division, Bendix Aviation Corporation, Sidney, New York.
Mobile, Alabama 36601.
Ovemaul Instructions, S-600 Series Magnetos, Form L-551, Scintilla Division, Bendix Aviation Corporation, Sidney, New
Continued Airworthiness Maintenance and Operators Manual Form X-30565, Teledyne Continental Motors
York.
Aircraft
Division,
Products
Post Office Box 90, Mobile,
Alabama 36601.
Service Parts List, S-600 Series Scintilla Division, Bendix Aviation
Magnetos, Form L-552-1, Corporation, Sidney, New
York.
TURBOCHARGER Series Aircraft Magnetos Maintenance and Overhaul Instructions, Form No. 1037-A, Slick Electro, Inc., Rockford, Illinois 61101.
4200/6200
Overhaul Manual and Parts Catalog Fonn No. X-30055, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama 36601.
FUEL INJECTION
STARTING MOTOR
Overhaul Manual and Parts Catalog Form No. X-30052, Teledyne Continental Motors Corporation, Aircraft Products
Parts and
Division, Post Office Box 90, Mobile, Alabama 36601.
Ohio 43694.
Equipment List, Service Parts and Technical Data OE-A1, Equipment Section Service Department, Toledo,
PROPELLER ALTERNATOR Overhaul Manual and Parts
McCauley
Industrial
Catalog Manual No. 720415, Corporation, Dayton, Ohio.
Equipment List,
Service Parts and Technical Data OE-A1,
Prestolite Service Owner’s
Manual, 115H, or Overhaul Manual No. 1138, Hartzell Propeller, Inc., Piqua, Ohio. Hartzell
Propeller
Service
Manual
Service with
overhaul
and
parts for McCauley
propellers, Manual No. 761001 or McCauley propeller Operators Manual No. MPC-11, McCauley Accessory Division, Cessna Aircraft Company, 1840 Howell Ave., Dayton, Ohio 45417. 3A32C406-X
Department,
Parts
and
Equipment
Section, Toledo, Ohio 43601.
642056A1
Teledyne
and
Overhaul
Instructions for Continental
P/N
642051 Alternator, Publication No. X-30531, Continental Motors, Aircraft Products Division, or
Post Office Box 90, Mobile, Alabama 36601.
ELECTRIC PROPELLER DEICER
PROPELLER GOVERNOR
Report 70-04-700, Maintenance Report 68-04-7128, B.F. Goodrich Engineered Systems Company Division, B.F. Goodrich Company, Installation of Deicer Boots,
McCauley Service Manual No. 78041 for the 35-380088-3 Propeller Governor, 3535 McCauley Drive, Vandalia, Ohio
Manual
45377.
Akron, Ohio 44318. Introduction
A9
Pege7 Sep 27164
BEECHCRAFT BONAEnA SEAIES MAINTENANCE MANAUL
BATTERY
AUTOPILOT
King KFC-P00
Installation
Manual
No. 006-0203-00 for
Models F33C, M3A, A36, and A36TC or No. 006-0201-00 for Model V35B, King Radio Corporation, 400 N. Rogers
Service Manual, Publication Number: GSM-12n, Teledyne Battery Products, P.O. Box 431, 840 W. BrocMon Ave.,
Redlands, CA 92373.
Road, Olathe, Kansas 66061. Service Manual CB12-9, Edo-Aire Mitchell Service and Overhaul Manual for Century III PIN 68854 or Century IV P/N 68889, P.O. Box 610,
Concorde
Battery Corp.,
for Concorde
Aircraft
2009 San Bemadino
Battery,
Rd., West
Covina, CA 01790.
Mineral Wells, Texas 76067.
STROBE LIGHT RADAR Overhaul Power
Manual with
Supply),
Illustrated
Parts List
(60-1750-3
Publication Number: 33-40-58; Grimes Div. Corp., 515 North Russel Street, Urbana,
of Midland Ross
WeatherScout
description
Digital
Weather
Radar
and Installation Manual,
System, System
Publication Number:
188023100, R.C.A., Avionics Systems, 8500 Balboa Blvd.,
Ohio 43078.
Van
Nuys, CA
91409.
AIR CONDITIONER COMPRESSOR Model 508
Compressor, Abacus International,
P. O. Box
327, Dallas, Texas 75221.
SUPPLEMENTARY BEECHCRAFT PUBLICAT)ONS FLIGHT CONTROLS 98-35012
ELECTRIC ELEVATOR TRIM TA8
Brake
Edo-Aire Mitchell, Automatic Right Control Systems, AK563 Bulletin No. 686 or AK669 Bulletin No. 798, EDO-AIRE MITCHELL, P.O. Box 610, Mineral ~lells, Texas 76067.
Servicing
Maintenance Instructions and Illustrated
Parts Breakdown for the Main Wheel, Nose Wheel and
Assembly.
32-31-24 Maintenance Information and Breakdown for EM 27-8
Landing Gear
Illustrated
Parts
Motor.
Introduction
PageB Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
ACCESS OPENINGS, FUSELAGE AND A36TC ACCESS OPENINGS, FUSELAGE F33A AND F33C ACCESS OPENINGS, FUSELAGE V35B) ACRYLIC LACqUER (INTERIOR COLORS) ACT ASSY, ELEV TRIM TAB (E-llll) ACT BRUSH REPLACE SCHED, ELEC TRIM TAB ACT DISASSEMBLY, ELEV TRIM TAB (E-llll) ACT INST, ELEC TRIM TAB (F33A, F33C, V35B) ACT REM, ELEC TRIM TAB (F33A, F33C, V35B) ACTUATOR ASSEMBLY INSTL, LANDING GEAR ACTUATOR ASSEMBLY REMOVAL, LANDING GEAR ACTUATOR ASSEMBLY, ELEVATOR TRIM TAB ACTUATOR ASSEMBLY, LANDING GEAR RETRACT ACTUATOR CLEANING AND PARTS REP, LANDING GEAR RETRACT ACTUATOR DISASSEMBLY, ELEV TRIM TAB ACTUATOR DISASSEMBLY, LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST, LANDING GEAR RETRACT ACTUATOR INSTALLATION, FLAP ACTUATOR INSTALLATION TRIM TAB ACTUATOR INSTALLATION 33 and 36), ELEV TRIM TAB ACTUATOR INSTALLATION, AILERON TRIM TAB ACTUATOR REMOVAL, FLAP ACTUATOR REMOVAL V35B), TRIM TAB ACTUATOR REMOVAL 33 and 36), ELEV TRIM TAB ACTUATOR REMOVAL, AILERON TRIM TAB ACTUATOR REMOVAL (33 and 36), ELEV TRIM TAB ACTUATOR, FLAP DISASSEMBLY AND ASSEMBLY ADJUSTING THE WING AEROFICHE AILERON AND TAB-MAINTENANCE PRACTICES AILERON AND TAB-MAINTENANCE PRACTICES AILERON CONTROL CABLE INSTALLATION AILERON CONTROL CABLE REMOVAL AILERON CONTROL SYSTEM RIGGING AILERON CONTROL TRIMMER AILERON INSTALLATION AILERON INSTALLATION AILERON REMOVAL AILERON REMOVAL AILERON RIGGING AILERON TAB ACTUATOR INSTALLATION AILERON TAB ACTUATOR REMOVAL AILERON TAB AILERON TAB
jA36
IV35B),
I
PAGE
53-30-00 53-30-00 53-30-00 20-00-00 27-30-00 27-30-00 27-30-00 27-30-00 27-30-00 32-30-00 32-30-00 27-30-00 32-30-00 32-30-00 27-30-00 32-30-00 32-30-00 27-50-00 27-21-00 27-30-00 27-11-00 27-50-00 27-21-00 27-30-00 27-11-00 27-30-00 27-50-00 57-00-00 IN-TR-OD 27-10-00 27-11-00 27-11-00 27-11-00 27-11-00 27-10-00 27-10-00 27-11-00 27-10-00 27-11-00 27-10-00 27-11-00 27-11-00 27-10-00
3 1 2 3 8 13 7 12A 12A 1 1 6 6 6 6 6 9 4 8 12 6 4 7 11 6 11 5 4 2 1 1 3 3 4 6 4 3 4 2 4 8 8 6
27-11-00
7
INTRODUCTION Page 9 A18
Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAC INDEX
CHAPTER AND SUB CHAPTER
COMPONENT ITEM OR SUB SYSTEM
AILERON TRIM TAB CABLE INSTALLATION AILERON TRIM TAB CABLE REMOVAL AILERON TRIM TAB FREE PLAY INSPECTION AILERON TRIM TAB RIGGING AIR CONDITIONER BELT AIR CONDITIONER CONDENSER AIR CONDITIONER LEAK DETECTION AIR CONDITIONER MAINTENANCE AIR CONDITIONER TORQUES AIR CONDITIONER PRECAUTIONS AIR CONDITIONER TROUBLESHOOTING AIR CONDITIONING FUNCTIONAL TEST AIR CONDITIONING SYSTEM AIR CONDITIONING SYSTEM CHARGING AIR CONDITIONING SYSTEM DEPRESSURIZING AIR CONDITIONING SYSTEM PURGING AIR FILTER INSTALLATIONINLINE INTAKE AIR FILTER INSTALLATION AIR FILTER REMOVAL AIR FILTER REMOVAL INTAKE AIR PRESSURE PUMP INSTALLATION AIR PRESSURE PUMP REMOVAL AIR SYSTEM, INSTRUMENT AIRPLANE DIMENSIONS MODEL A36TC AIRPLANE DIMENSIONS MODEL A36 AIRPLANE DIMENSIONS MODEL B36TC AIRPLANE DIMENSIONS MODEL 33 AIRPLANE DIMENSIONS MODEL 35 AIRPLANE FINISH CARE AIRPLANE FINISH CLEANING ALCAL CALIBRATION UNIT ALPHABETICAL INDEX ALTERNATOR DRIVE GEAR AND COUPLING INSTL ALTERNATOR INSTALLATION ALTERNATOR REMOVAL ALUMINUM CORROSION REMOVAL ALUMINUM CORROSION TREATMENT
IINLINE
ALUMINUM ELECTRICAL BONDING ALUMINUM SURFACES ASSIGNMENT OF SUBJECT MATERIAL ATA APPLICATION AUXILIARY FUEL PUMP INSTALLATION AUXILIARY FUEL PUMP REMOVAL AUXILIARY OR FUEL BOOST PUMP AVIONICS/RADIO EQUIPMENT INSTALLATION AVIONICS/RADIO EQUIPMENT REMOVAL
27-11-00 27-11-00 27-11-00 27-11-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00
12-10-00 12-10-00 12-10-00 12-10-00 36-00-00 36-00-00 36-00-00 36-00-00 71-00-00 71-00-00 36-00-00
06-00-00 06-00-00 06-00-00 06-00-00 06-00-00 20-08-00 20-08-00 77-00-00 IN-TR-OD 24-30-00 24-30-00 24-30-00
20-09-00 20-09-00 20-03-00 20-03-00 IN-TR-OD IN-TR-OD 28-20-00 28-20-00 28-00-00 39-10-00 39-10-00
PAGE 7 7 8 7 7 8 7 5 7 5 4 5 2 3 3 3 5 5 5 5 6 6 1 4 3 5 1 2 2 3 1 2 6 6 6 3 4 7 2 1 2 1 1 1 1 1
INTRODUCTION
Page 10 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL ALPHABETICAL
COMPONENT OR SUB
INDEX
ITEM
SYSTEM
BAGGAGE DOOR INSTALLATION BAGGAGE DOOR REMOVAL BAGGAGE DOORS (MODELS F33A, F33C, AND V35B) BALANCING PROCEDURE BALANCING THE AILERON BALANCING THE ELEVATOR BALANCING THE RUDDER BALANCING THE RUDDERVATOR BATTERY BOX AND LID PAINTING BATTERY BOX CLEANING BATTERY CLEANING BATTERY INSTALLATION BATTERY MAINTENANCE PROGRAM BATTERY REMOVAL BATTERY REPLACEMENT, ELT BATTERY SERVICING BATTERY BEARING HOUSING INSPECTION BEARING INSTALLATION USING RETAINING COMPOUND BEARING INSTALLATION BY STAKING BELT TENSION ADJUSTMENT, COMPRESSOR BLEEDING THE BRAKE SYSTEM BLEEDING THE BRAKE SYSTEM, GRAVITY BLEEDING THE BRAKE SYSTEM, PRESSURE INSTALLATION BLOWER, FRESH AIR REMOVAL BLOWER, FRESH AIR BOLTS, TOR9UING COARSE THREAD IN SMEAR BOLTS, TORQUING FINE THREAD IN SMEAR BONDING JUMPER ACROSS TUBING CLAMP ELECTRICAL BONDING BOOST PUMP, AUXILIARY BRAKE ADJUSTMENT, PARKING BRAKE ASSEMBLY BRAKE ASSY AND MAIN WHEEL INSTALLATION BRAKE ASSY AND MAIN WHEEL REMOVAL BRAKE ASSY INSPECTION AND CLEANING BRAKE CLEANING AND PARTS REPLACE, PARKING BRAKE MASTER CYLINDER ASSEMBLY BRAKE MASTER CYLINDER CLEANING AND PARTS RPLACEMENT BRAKE MASTER CYLINDER DISASSEMBLY BRAKE MASTER CYLINDER INSTALLATION BRAKE MASTER CYLINDER LINKAGE ADJUSTMENT BRAKE MASTER CYLINDER REMOVAL BRAKE RELAY CHECK, DYNAMIC BRAKE RELINING
CHAPTER AND SUB CHAPTER
52-30-00 52-30-00 52-00-00 57-50-00 57-50-00 55-20-00 55-40-00 55-20-00 20-08-00 24-30-00 24-30-00 24-30-00 24-30-00 24-30-00 25-60-00 24-30-00 12-20-00 20-05-00 20-05-00 20-05-00 12-10-00 32-40-00 32-40-00 32-40-00 21-50-00 21-50-00 91-00-00 91-00-00 20-03-00 28-00-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-30-00 32-40-00
PAGE
1 1
1 1 1 1 1 3 7 9 8 8 7 8 1 9 1 2 2 3 7 8 10 9
11 11 11 11 8 1 7 1 1 3 4 8 7 6 6 6 6 6 3 6
INTRODUCTION A18
Page 11 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND
BRAKE SHUTTLE VALVE BRAKE SYSTEM BRAKE SYSTEM BLEEDING BRAKE SYSTEM BLEEDING, ELECTRIC BRAKE SYSTEM BLEEDING, GRAVITY BRAKE SYSTEM BLEEDING, PRESSURE POT BRAKE SYSTEM, HYDRAULIC BRAKE SYSTEM BRAKE SYSTEM TROUBLESHOOTING BRAKE VALVE ASSEMBLY, PARKING BRAKE VALVE DISASSEMBLY, PARKING BRAKE VALVE INSTALLATION, PARKING BRAKE VALVE REMOVAL, PARKING BRAKE WEAR AND WEAR LIMITS BRAKES, RELINING BREAK-IN ENGINE OIL BRUSH BLOCK CLEANING SLIP RING BRUSH BLOCK INSTALLATION BRUSH BLOCK REMOVAL BRUSH MODULE REPLACEMENT BRUSH MODULE RESISTANCE CHECK BRUSH REPLACEMENT BRUSH WEAR LIMITS
32-40-00 12-10-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 12-10-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 79-00-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00
1 6 1 13 13 13 9 10 11 11
CABIN DOOR ADJUSTMENT CABIN DOOR INSTALLATION (MODEL F33C) CABIN DOOR INSTL (F33A, V35B, A36, A36TC) CABIN DOOR LOCK, FITTING TUMBLER TO KEY CABIN DOOR QUICK RELEASE MECHANISM CABIN DOOR REMOVE (F33A, V35B, A36, A36TC) CABIN DOOR REMOVAL (MODEL F33C) CABIN DOOR TELEFLEX CABLE REMOVE AND INSTL CABIN DOOR WINDOW INSTALLATION CABIN DOOR WINDOW REMOVAL CABIN DOOR CABIN HEATING
52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 56-10-00 56-10-00 52-00-00 21-40-00 33-20-00 33-20-00 27-21-00 21-40-00 27-00-00 28-40-00 28-10-00 28-10-00
2 2 1 3 1 1 2 7 2 2 1 1 2 2 5 1 1 1 1 1
CABIN OVERHEAD LIGHT BULB INSTALLATION CABIN OVERHEAD LIGHT BULB REMOVAL CABIN REPL, ELEVATOR TAB INDICATOR CABIN VENTILATION CABLE TENSION, EFFECTS OF TEMPERATURE CALIBRATION OF FUEL QUANTITY INDICATOR CELL INSTALLATION, FUEL CELL REMOVAL, FUEL
SUB CHAPTER
PAGE 1 4 8 12 9 12 1 4 3 7 7 7
7
INTRODUCTION
Page 12 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
CHAPTER AND
OR SUB
SUB CHAPTER
ITEM SYSTEM
CHARGING THE AIR CONDITIONING SYSTEM CHART 1, SERVICING CHART 2, LUBRICATION SCHEDULE CHECKING BALANCE CHECKING BALANCE CLEANING AND PARTS REPL, MAIN LANDING GEAR CLEANING AND PARTS REPL, NOSE LANDING GEAR CLEANING AND WAXING THE AIRPLANE CLEANING AND WAXING THE AIRPLANE FINISH CLEANING FUEL STRAINERS CLEANING INTERIOR CABIN TRIM CLEANING PLASTIC WINDOWS CLEANING PLASTIC WINDOWS CLEANING THE STATIC AIR SYSTEM CLUTCH INSTALLATION, MAGNETIC CLUTCH REMOVAL, MAGNETIC CLUTCH TOROUE TEST, MAGNETIC COLUMN, CONTROL RIGGING CHAIN COLUMN, CONTROL RIGGING CHAIN COLUMN, CONTROL, ARM INSTALLATION COLUMN, CONTROL, ARM REMOVAL COLUMN, SINGLE CONTROL COMMUNICATION COMPASS LIGHT BULB INSTALLATION COMPASS LIGHT BULB REMOVAL COMPONENTS LOCATION ZONES, ELECTRICAL COMPRESSOR BELT INSTALLATION COMPRESSOR BELT PULLEY ALIGNMENT COMPRESSOR BELT REMOVAL COMPRESSOR BELT TENSION ADJUSTMENT COMPRESSOR INSTALLATION AND ALIGNMENT COMPRESSOR MOUNTING TORQUES COMPRESSOR OIL LEVEL CHECKING COMPRESSOR REMOVAL CONDENSER, AIR CONDITIONER CONDENSER CONTROL RIGGING CONSUMABLE MATERIALS CONTROL CABLE PULLEY INSPECTION CONTROL CABLE STORAGE CONTROL CABLE SYSTEM INSPECTION CONTROL COLUMN ARM INSTALLATION CONTROL COLUMN ARM REMOVAL CONTROL COLUMN CHAIN RIGGING CONTROL COLUMN CHAIN INSTALLATION CONTROL COLUMN CHAIN REMOVAL CONTROL COLUMN CHAIN RIGGING
12-10-00 12-20-00 12-20-00 55-20-00 57-50-00 32-10-00 32-20-00 20-00-00 12-20-00 28-00-00 12-20-00 56-00-00 12-20-00 34-10-00 27-30-00 27-30-00 27-30-00 27-10-00 27-11-00 27-10-00 27-10-00 27-10-00 23-10-00 33-20-00 33-20-00 39-20-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00
12-10-00 21-50-00 21-50-00 21-50-00 91-00-00 20-04-00 20-04-00 20-04-00 27-10-00 27-10-00 27-10-00 27-11-00 27-11-00 27-11-00
PAGE 3 6 7 1 1 2 2 2 4 2 5 1 4 2 12A 12A 13 1 1 1 1 1 1 1 1 1 7 7 7 7 9 7 3 9 8 8 1 3 3 2 1 1 1 1 1 1
INTRODUCTION A18
Page 13 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM
CHAPTER AND
OR SUB SYSTEM
SUB CHAPTER
CONTROL COLUMN ROLLER ADJUSTMENT CONTROL COLUMN SUPPORT ROLLER ADJUSTMENT CONTROL COLUMN, SINGLE CONTROL LOCKS CONTROL SYSTEM, AILERON, RIGGING CONTROL TRIMMER, AILERON CONTROLLING STATIC CHARGE BUILDUP COOLING DESCRIPTION AND OPERATION CORRESPONDENCE CORROSION CONTROL CORROSION PROTECTION CORROSION-RESISTANT (CRES) STEEL SURFACES COTTER PIN INSTALLATION COURTESY LIGHT BULB INSTALLATION COURTESY LIGHT BULB REMOVAL COWL FLAP RIGGING COWLING INSTALLATION COWLING LATCH RIGGING COWLING REMOVAL CRES STEEL OR TITANIUM ELECTRICAL BONDING CYLINDER ASSEMBLY, BRAKE MASTER CYLINDER CLEANING AND PARTS RPL, BRAKE MASTER CYLINDER DISASSEMBLY, BRAKE MASTER CYLINDER INSTALLATION, BRAKE MASTER CYLINDER LINKAGE ADJUSTMENT, BRAKE MASTER CYLINDER REMOVAL, BRAKE MASTER
27-11-00 27-11-00 27-10-00 10-00-00 27-10-00 27-10-00 20-02-00 21-50-00 IN-TR-OD 20-09-00 20-09-00 20-03-00 20-07-00 33-20-00 33-20-00 71-10-00 71-10-00 71-10-00 71-10-00 20-03-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00
2 2 1 1 1 4 6 1 1 1 3 6 4 2 2 1 1 1 1 6 7 7 7 7 7 6
DAMPENER ASSEMBLY, NOSE GEAR SHIMMY DAMPENER CLEANING/PARTS REP, NOSE GEAR SHIMMY DAMPENER DISASSEMBLY, NOSE GEAR SHIMMY DAMPENER INSTALLATION, NOSE GEAR SHIMMY DAMPENER OVERHAUL, NOSE GEAR SHIMMY DAMPENER REMOVAL, NOSE GEAR SHIMMY DEFUELING, AIRPLANE DEICER BOOT DEICER HEAT TEST DEICER TIMER CHECK DIMENSIONS AND AREAS DIRECT ELECTRICAL BONDING DOOR, UTILITY REMOVAL DRAINING THE FUEL SYSTEM DRAINS, FUEL SYSTEM DUAL CONTROL COLUMN DYNAMIC BRAKE RELAY CHECK
32-20-00 32-20-00
7 2 9 9 9 7 4 5 10 9 1 1 1 1 2 1 2
32-20-00 32-20-00
32-20-00 32-20-00 28-00-00 30-60-00 30-60-00 30-60-00 06-00-00 20-03-00 52-30-00 12-10-00 28-00-00 27-11-00 32-30-00
PAGE
INTRODUCTION
Page 14 Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
INDEX
CHAPTER AND
COMPONENT ITEM OR
SUB CHAPTER
SUB SYSTEM
DYNAMIC BRAKE RELAY DYNAMIC BRAKE RELAY
INSTL, LANDING GEAR REMOVAL, LANDING GEAR
EFFECT OF TEMPERATURE UPON CABLE TENSION ELECTRIC BLEEDING HR GUIDE ELECTRIC PROPELLER DEICER 100 HR GUIDE ELECTRIC PROPELLER DEICER 50 HR GUIDE) ELECTRIC PROPELLER DEICER ELECTRIC PROPELLER DEICING ELECTRICAL BONDING METHODS ELECTRICAL BONDING OF TUBES ELECTRICAL BONDING EXAMPLES ELECTRICAL BONDING OF GROUND TABS ELECTRICAL COMPONENTS LOCATION ZONES ELECTRICAL LOAD CONTINUOUS STANDARD ELECTRICAL LOAD CONTINUOUS ELECTRICAL LOAD INTERMITTENT OPTIONAL ELECTRICAL LOAD INTERMITTENT ELECTRICAL POWER RETURNS
j100
IOPTIONAL ISTANDARD
ELECTRICAL SYSTEM ELECTRICAL SYSTEM TROUBLESHOOTING ELECTRICAL UTILIZATION CHART
ELECTROLUMINESCENT PANEL INSTALLATION, LIGHTS ELECTROLUMINESCENT PANEL REMOVAL ELECTROSTATIC DISCHARGE SENSITIVITY CLASSIFICATION ELEV TAB FREE PLAY, CHECKING ELEV TRIM TAB SERVO INST, ELECTRIC ELEV TRIM TAB SERVO REMOVAL, ELECTRIC ELEVATOR AND TAB MAINTENANCE PRACTICES ELEVATOR AND TAB MODEL V35B ELEVATOR BALANCING ELEVATOR INSTALLATION ELEVATOR REMOVAL ELEVATOR RIGGING PROCEDURE ELEVATOR STABILIZER INSTALLATION, V35 ELEVATOR STABILIZER REMOVAL, V35 ELEVATOR TAB INDICATOR CABLE REPL ELEVATOR TAB INDICATOR CABLE REPL ELEVATOR TAB RIGGING ELEVATOR TAB RIGGING ELEVATOR TAB RIGGING, V35 ELEVATOR TAB RIGGING TO CORRECT FOR YAW, V35 ELEVATOR TABS, INSPECTION (V35B) ELEVATOR TRIM TAB ACTUATOR
PAGE
32-30-00 32-30-00
2 2
27-00-00 32-40-00 05-20-00 05-20-00 05-20-00 30-60-00 20-03-00 20-03-00 20-03-00 20-03-00 39-20-00 24-50-00 24-50-00 24-50-00 24-50-00 20-03-00 24-30-00 24-30-00 24-50-00 33-20-00 33-20-00 20-02-00 27-30-00 27-30-00 27-30-00 27-30-00 27-21-00 55-20-00 27-30-00 27-30-00 27-21-00 55-10-00 55-10-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-21-00 27-21-00 27-30-00
2 10 1 1 1 1 1 1 6 11 1 2 1 2 3 1 1 1 1 1 1 1 11 12 12 1 5 1 1 1
1,5 1 1 9 6 7 6B 7 9 7 6B
INTRODUCTION
Page 15 A18
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COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
ELEVATOR TRIM TAB ACTUATOR ASSEMBLY ELEVATOR TRIM TAB ACTUATOR INSTAL, V35 ELEVATOR TRIM TAB ACTUATOR REMOVAL, V35 ELEVATOR TRIM TAB ACTUATOR DISASSEMBLY ELEVATOR TRIM TAB INDICATOR CABLE REPL ELEVATOR TRIM TAB INDICATOR CABLE REPL ELEVATOR TRIM TAB HINGE INSPECTION ELECTRIC ELEVATOR TRIM,OPTIONAL OPTIONAL ELECTRIC ELEVATOR TRIM, ELEVATOR TRIM, ELEC GROUND CHECKS EMERGENCY LOCATOR TRANSMITTER BATTERY REPLACEMENT EMERGENCY LOCATOR TRANSMITTER MAINTENANCE EMERGENCY LOCATOR TRANSMITTER EMERGENCY LOCATOR TRANSMITTER TESTING EMPENNAGE SKIN THICK (F33A A36, A36TC) EMPENNAGE SKIN THICKNESS ENCLOSED AREAS SUBJECT TO HIGH HUMIDITY ENGINE AIR INDUCTION SYSTEM ENGINE AND FLIGHT INSTRUMENT INSTL ENGINE AND FLIGHT INSTRUMENT REMOVAL ENGINE BUILD-UP
27-30-00 27-21-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-30-00 25-60-00 25-60-00 25-60-00 25-60-00 55-00-00 55-00-00 20-08-00 71-00-00
(~358)
ENGINE CLEANING ENGINE DRIVEN FUEL PUMP INSTALLATION ENGINE DRIVEN FUEL PUMP REMOVAL ENGINE FUEL FILTERS AND SCREENS ENGINE INSTALLATION (TURBOCHARGED) ENGINE INSTL (NORMALLY ASPIRATED) ENGINE INSTRUMENT CLUSTER INSTALLATION
ENGINE INSTRUMENT CLUSTER REMOVAL ENGINE OIL, RECOMMENDED ENGINE REMOVA~NORMALCY ASPIRATED) ENGINE REMOVAL TURBOCHARGED) ENGINE TROUBLESHOOTING ENGINE ENVIRONMENTAL FALLOUT (ACID RAIN) EPOXY POLYAMIDE PRIMER FOR URETHANE EQUIP REQUIRED TO PERFORM CHECK BALANCE EVAPORATOR FILTER REPLACEMENT EVAPORATOR INSTALLATION EVAPORATOR REMOVAL EXTENDED STORAGE AND HIGH WIND EXTENSION SYSTEM, MANUAL LANDING GEAR EXTERIOR AND INTERIOR FINISHES EXTERIOR AND INTERIOR PRIMERS EXTERIOR LIGHTS, TROUBLESHOOTING EXTERIOR
39-10-00 39-10-00 71-00-00 12-20-00 71-00-00 71-00-00 12-10-00 71-00-00 71-00-00 39-10-00 39-10-00 79-00-00 71-00-00 71-00-00 71-00-00 72-00-00 20-08-00 20-00-00 57-50-00 21-50-00
21-50-00 21-50-00 10-00-00 32-30-00 20-00-00 20-00-00 33-40-00 11-20-00
PAGE
6C,8,9 12 11
6B,7,8 9 6A 10 12 7 12A 1 1 1 3 2 5 7 1 1 1 6 5 6 6 1 5 5 1 1 2 5 5 2 1 3 4 1 12 12 12 1 1 2 2 2 1
INTRODUCTION
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COMPONENT OR SUB
ITEM
SYSTEM
CHAPTER AND SUB CHAPTER
PAGE
EXTERNAL POWER EXTERNAL POWER
12-20-00 24-40-00
1 1
FAA REQUIRED PLACARDS AND MARKINGS FILLER CAPS AND VENT LINES INSP, FUEL CELL FILLING THE FUEL CELLS INLINE AIR FILTER INSTALLATION FILTER INSTALLATION INTAKE AIR FILTER REMOVAL INLINE), AIR AIR FILTER REMOVAL FITTING TORQUE, FLARE FITTINGS, FLARED FLAP ACTUATOR DISASSEMBLY FLAP ACTUATOR ASSEMBLY FLAP ACTUATOR INSTALLATION FLAP ACTUATOR REMOVAL FLAP INNER FLEX SHAFT INSTALLATION FLAP INNER FLEX SHAFT REMOVAL FLAP INSTALLATION FLAP LIMIT SWITCH ADJUSTMENT FLAP MOTOR INSTALLATION FLAP MOTOR REMOVAL FLAP POSITION INDICATOR AND ADJUSTMENT FLAP REMOVAL FLAP SHAFT INSTALLATION FLAP SHAFT REMOVAL FLAP TRACK WEAR LIMITS FLAPPER VALVE INSPECTION, FUEL CELL FLAPS DESCRIPTION AND OPERATION FLAPS MAINTENANCE PRACTICES FLAPS, THREE POSITION FLAPS, TWO POSITION FLARE FITTING TORQUE FLARED FITTINGS FLIGHT AND ENGINE INSTRUMENT INSTALLATION FLIGHT AND ENGINE INSTRUMENT REMOVAL FLIGHT ENVIRONMENT DATA FLUID LINE FITTING INSTALLATION FLYABLE STORAGE FUEL CELL FLAPPER VALVE, INSPECTION FUEL CELL INSTALLATION FUEL CELL LEAKAGE TEST FUEL CELL PRESERVATION (GOODYEAR) FUEL CELL PRESERVATION (UNIROYAL) FUEL CELL REMOVAL
11-00-00 28-20-00 12-10-00 36-00-00 36-00-00 36-00-00 36-00-00 91-00-00 28-20-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00
1 3 1 5 5 5 4 11 4 7 7 6 5 6 6 1 1 4 4 3 1 4 4 1 6 1 1 3 3 11 4 1 1 1 2 2 6 1 6 9 9 1
j tINTAKE)I
27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 28-10-00 27-50-00 27-50-00 27-50-00
27-50-00 91-00-00 28-20-00 39-10-00 39-10-00 34-10-00 20-06-00 10-00-00 28-10-00 28-10-00 28-10-00 28-10-00 28-10-00 28-10-00
INTRODUCTION Page 17 A18
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BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
CHAPTER AND SUB CHAPTER
COMPONENT ITEM OR SUB SYSTEM
FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL
CELL CELL CELL CELL FLOW FLOW FLOW
REPAI RGOODYEARUNIROYAL REPAIR
RESERVOIR (CJ-149 AND AFTER) VENT LINESAND FILLER CAPS, INSP INDICATING INDICATOR SYSTEM CALIBRTION AND CORRECTION FLOW TRANSMITTER INSTALLATION FLOW TRANSMITTER REMOVAL HANDLING PRACTICES PUMP ADJUSTMENT, ENGINE DRIVEN PUMP INSTALLATION, AUXILIARY PUMP INSTALLATION, ENGINE DRIVEN PUMP REMOVAL, AUXILIARY PUMP REMOVAL, ENGINE DRIVEN
QUANTITY QUANTITY FUEL QUANTITY FUEL QUANTITY FUEL QUANTITY
INDICATORS INDICATOR CALIBRATION SENSORS SENSOR INSTALLATION SENSOR REMOVAL
28-10-00 ’28-10-00 12-10-00 28-20-00 73-30-00 73-30-00 71-00-00 73-30-00 73-30-00 28-00-00 28-20-00 28-20-00 28-20-00 28-20-00 28-20-00 28-40-00 28-40-00 28-40-00 28-40-00
28-40-00
REMOVAL SELECTOR VALVE INSTALLATION SELECTOR VALVE REMOVAL STRAINER INSTL VALVE) FUEL STRAINER INSTL WING FUEL CELLS) SELECTOR VALVE) FUEL STRAINER REMOVAL FUEL CELL) FUEL STRAINER REMOVAL FUEL STRAINERS, CLEANING FUEL SYSTEM ADJUSTMENT (EA-l AND AFTER) FUEL SYSTEM ADJUSTMENT (TURBOCHARGED) FUEL SYSTEM DRAINS FUEL SYSTEM FULL THROTTLE ADJUSTMENT FUSELAGE ACCESS OPENINGS (A36 AND A36TC) FUSELAGE ACCESS OPENINGS (F33A AND F33C) FUSELAGE ACCESS OPENINGS (V35B) FUSELAGE SKIN THICKNESS (A36 AND A36TC) FUSELAGE SKIN THICKNESS (F33A AND F33C) FUSELAGE SKIN THICKNESS (V35B)
28-00-00 28-20-00 28-20-00 28-20-00
GALVANIC CORROSION
20-09-00 IN-TR-OD 32-10-00
FUEL FUEL FUEL FUEL
tSELECTOR IWING
GAMA APPLICATION GEAR ASSEMBLY, MAIN LANDING GEAR ASSEMBLY, NOSE LANDING
28-20-00 28-20-00 28-20-00 28-00-00 71-00-00 71-00-00 28-00-00 28-00-00 71-00-00 53-30-00 53-30-00 53-30-00 53-30-00 53-30-00 53-30-00
32-20-00
PAGE 9 9 1 3 1 1 11 1 1 2 1 1 1 1 1 1 1 1 1 1 4 2
2 2 3 2 3 2 12 12 2 1
7 3 1 1 8 4 6
1 2 5 7
INTRODUCTION
Page 18 Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
COMPONENT OR
SUB
INDEX
CHAPTER AND
ITEM
SUB CHAPTER
SYSTEM
32-10-00 32-20-00 32-10-00 32-20-00 32-60-00 32-10-00 32-20-00 32-00-00 32-10-00 32-20-00 33-20-00
PAGE
2 1 1
GEAR DISASSEMBLY, MAIN LANDING GEAR GEAR DISASSEMBLY, NOSE LANDING GEAR INSTALLATION, MAIN LANDING GEAR INSTALLATION, NOSE GEAR POSITION LIGHT ADJ, LANDING GEAR REMOVAL, MAIN LANDING GEAR REMOVAL, NOSE GEAR SYSTEM, LANDING GEAR WEAR TOLERANCE, MAIN GEAR WEAR TOLERANCE, NOSE GLARESHIELD FLOODLIGHT BULB REMOVAL GLARESHIELD FLOODLIGHT BULB INSTL GLARESHIELD INSTALLATION GLARESHIELD REMOVAL GRAVITY BLEEDING GROUND COMMUNICATION GROUND RUNNING AND WARM-UP GUST LOCK AND DAMPER
33-20-00 39-10-00 39-10-00 32-40-00 23-10-00 71-00-00 27-70-00
1 1 1 1 1 7 4 1 1 1 1 9 1 6 1
HANDLING OF ESDS COMPONENTS AND EQUIPMENT HANDLING PRACTICES, FUEL HEADLINER INSTALLATION HEADLINER REMOVAL HEAT AND VENT SYSTEM INSPECTION HEATER AND DEFROSTER OPERATION HEATER MUFF INSTALLATION HEATER MUFF PRESSURE TEST HEATER MUFF REMOVAL HEATING AND VENTILATION, INSPECTION OF HOISTING HORIZONTAL STABILIZER INSTALLATION HORIZONTAL STABILIZER REMOVAL HORN SYSTEM, THROTTLE WARNING HOSE ASSEMBLY INSTALLATION HUMIDITY AND DUST EFFECTS ON ESDS COMPONENTS AND HYDRAULIC BRAKE SYSTEM HYDRAULIC PRESS BEARING REMOVAL
20-02-00 28-00-00 25-00-00 25-00-00 21-40-00 21-40-00 21-40-00 21-40-00 21-40-00 21-40-00 07-00-00 55-10-00 55-10-00 32-60-00 20-06-00 20-02-00 32-40-00 20-05-00
3 2 5 5 7 1 7 7 7 7 1 1 1 1 1 8 1 1
30-00-00 71-00-00 71-00-00
1 7 8
ICE AND RAIN PROTECTION IDLE SPEED AND MIXTURE ADJUSTMENT IDLE SPEED AND MIXTURE ADJUSTMENT
EQUIPMENT
(EXCEPT 10-550 ENG) (10-550 ENG)
INTRODUCTION
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COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
IGNITION AND STARTER SWITCH IGNITION SYSTEM IGNITION TROUBLESHOOTING INDEFINITE STORAGE INDEX GUIDE INDICATOR CALIBRATION, FUEL QUANTITY INDICATORS, FUEL QUANTITY INDIRECT ELECTRICAL BONDING INDUCTION AIR FILTER INSP OF FUEL CELL VENT LINE/FILLER CAPS INSPECTING PITOT SYSTEM HOSES INSPECTION GUIDE 100-HOUR INSPECTION OF FUEL CELL FLAPPER VALVE INSPECTION OF HEATING AND VENTILATION INSPECTION OF THE HINGES INSPECTION OF THE OUTSIDE AIR TEMP GAGE INSPECTION, OUTBOARD WING MAIN SPAR CAP INSTRUMENT AIR PRESSURE, LOW INSTRUMENT AIR SYSTEM INSTRUMENT AIR SYSTEM SERVICING INSTRUMENT CLUSTER INSTt,
74-00-00 74-00-00 74-00-00 10-00-00 IN-TR-OD 28-40-00 28-40-00 20-03-00
INSTRUMENT CLUSTER
REMOVAL, ENGINE ENGINE AND FLIGHT POST LIGHT INSTALLATION POST LIGHT REMOVAL REMOVAL, ENGINE AND FLIGHT WEDGE LIGHT TRAY INSTL WEDGE LIGHT TRAY REMOVAL
INSTRUMENT INSTL, INSTRUMENT INSTRUMENT INSTRUMENT INSTRUMENT INSTRUMENT
JACKING
KEYWASHERS
LANDING LANDING LANDING LANDING LANDING LANDING LANDING
(TAB
GEAR GEAR GEAR GEAR GEAR GEAR GEAR
AND CUP
TYPES)
INSTALLATION
ACTUATOR ASSEMBLY INSTL ACTUATOR ASSEMBLY REMOVAL ASSEMBLY, MAIN ASSEMBLY, NOSE CLEANING AND PARTS REPL, MAIN CLEANING AND PARTS REPL, NOSE DISASSEMBLY, MAIN
PAGE
1 1 1 1 3 1 1 1 3
12-20-00 28-20-00 34-10-00 05-20-00 28-10-00 21-40-00 27-21-00 34-10-00 57-00-00 36-00-00 36-00-00 36-00-00 39-10-00 39-10-00 39-10-00 33-20-00 33-20-00 39-10-00 33-20-00 33-20-00
3 2 5 6 7 7 3 11 3 1 3 1 1 1 1 1 1 1 1
07-00-00
1
20-07-00
5
32-30-00
1 1 5 7 4 2 2
32-30-00 32-10-00 32-20-00 32-10-00 32-20-00 32-10-00
INTRODUCTION
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COMPONENT OR
CHAPTER AND
ITEM
SUB
SUB SYSTEM
LANDING GEAR DISASSEMBLY, NOSE LANDING GEAR DYNAMIC BRAKE RELAY CHECK LANDING GEAR DYNAMIC BRAKE RELAY INSTL LANDING GEAR DYNAMIC BRAKE RELAY REMVL LANDING GEAR ENGINE COMPARTMENT-LOCATED RETRACTAND PREVENT SWITCH ADJUSTMENT AFTER,AND CJ-180 AND LANDING GEAR ENGINE COMPARTMENT-LOCATED WARNING SWITCH ADJUSTMENT (CE-748,CE-772,iHRU CE-1300,CE-1302 THRU CE-1306,CJ-149 THRU CJ-179,D10097,D-10120 AND AFTER,E-1111,E-1241 THRU 2110,EXCEPT E-1946 AND E-2104,AND EA-1 THRU EA-388,
CHAPTER
PAGE
32-20-00 32-30-00 32-30-00 32-30-00 32-60-00
1 2 2 2 6
32-60-00
1
32-60-00
1
32-60-00
2
32-30-00 32-10-00 32-20-00 32-10-00 32-20-00 32-10-00 32-20-00 32-30-00 32-30-00 32-60-00
1 1 1 1 1 2 1 2 2 3
32-60-00
7
32-40-00 32-30-00 32-20-00 32-30-00 32-30-00
1 1 1 8 8
32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00
7 9 2 2 1 4 9 11
AFTERjCE1301.CE-1307
EXCEPT EA-320) LANDING GEAR ENGINE COMPARTMENT-LOCATED WARNING SWITCH ADJUSTMENT (CE-1301,CE-1307 AND AFTER,AND CJ-180 AND AFTER) LANDING GEAR EXTENSION SYSTEM, MANUAL LANDING GEAR INSTALLATION, MAIN LANDING GEAR INSTALLATION, NOSE LANDING GEAR LUBRICATION, MAIN LANDING GEAR LUBRICATION, NOSE LANDING GEAR OVERHAUL, MAIN LANDING GEAR OVERHAUL, NOSE LANDING GEAR MOTOR INSTALLATION LANDING GEAR MOTOR REMOVAL LANDING GEAR PEDESTAL-LOCATED WARNING SWITCH ADJUSTMENT (E-1946,E-2104,E-2111 AND AFTER,AND EA-320,EA-389 AND AFTER) LANDING GEAR PEDESTAL-LOCATED RETRACTPREVENT SWITCH ADJUSTMENT (E-2458,E-2468 AND AFTER, AND EA-320, EA-389 AND AFTER) LANDING GEAR POSITION LIGHT ADJUSTMENT LANDING GEAR REMOVAL, MAIN LANDING GEAR REMOVAL, NOSE LANDING GEAR RETRACT ACTUATOR ASSEMBLY LANDING GEAR RETRACT ACTUATOR CLEANING AND PARTS REPLACEMENT LANDING GEAR RETRACT ACTUATOR DISASSEMBLY LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST LANDING GEAR RETRACT ROD INSTL, MAIN LANDING GEAR RETRACT ROD REMOVAL, MAIN LANDING GEAR RETRACT SYSTEM LUBRICATION LANDING GEAR RIGGING LANDING GEAR SAFETY SYS MAIN AND ADJUST LANDING GEAR SAFETY SYS MICROSWITCH ADJUST
INTRODUCTION Page 21 A18
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BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
32-30-00 LANDING GEAR SAFETY SYS PRESS SWITCH ADJ 32-30-00 LANDING GEAR SAFETY SYS SAFETY SWITCH CHECK 32-30-00 LANDING GEAR SAFETY SYS SAFETY SWITCH CHECK 32-20-00 LANDING GEAR SHIMMY DAMPER 32-20-00 LANDING GEAR SHIMMY DAMPER OVERHAUL 32-20-00 LANDING GEAR SHIMMY DAMPER WEAR TOLERANCE 12-20-00 LANDING GEAR SHOCK STRUTS 32-00-00 LANDING GEAR SYSTEM 32-00-00 LANDING GEAR WEAR TOLERANCE, MAIN 32-00-00 LANDING GEAR WEAR TOLERANCE, NOSE 33-40-00 LANDING LIGHT INSTALLATION 33-40-00 LANDING LIGHT REMOVAL 28-10-00 LEAKAGE TEST, FUEL CELL 08-00-00 LEVELING 33-20-00 AND/OR POSITION) LIGHT BULB INSTL 33-20-00 LIGHT BULB REMVL WARNING AND/OR POSITION)LIGHTS 33-40-00 LIGHT BULB REPLACEMENT CHART-1 33-40-00 LIGHT, STEP 32-60-00 LNDG GR RETRACT-PREVENT SW-ENG COMPT-LOCATED (CE-1301, CE-1307 AND AFTER;CJ-180 AND AFTER) 32-60-00 LNDG GR WARN SW ADJUST-ENG COMPT-LOCATED (CE-748, CE-772 THRU CE-1300, CE-1302 THRU CE-1306; CJ-149 THRU C3-179, D-10097, D-10120, AND AFTER; E-llll, E-1241 THRU E-2110, EXCEPT E-1946 AND E-2104; EA-1 THRU EA-388, EXCEPT EA-320 32-60-00 LNDG GR WARN SW ADJUST-ENG COMPT-LOCATED (CE-1301 CE-1307 AND AFTER; CJ-180 AND AFTER) 33-40-00 LIGHT, STEP 20-07-00 LOCKWIRE AND COTTER PIN REQUIREMENTS 20-07-00 LOCKWIRE HOLE ALIGNMENT 20-07-00 LOCKWIRE INSTALLATION PROCEDURES 20-07-00 LOCKWIRE TWISTING IN-TR-OD LOG OF EFFECTIVE REVISIONS 33-40-00 LOWER ROTATING BEACON INSTALLATION 33-40-00 LOWER ROTATING BEACON REMOVAL 91-00-00 LUBRICANTS, THREAD 32-30-00 LUBRICATION LANDING GEAR RETRACT SYSTEM 12-20-00 LUBRICATION OF LANDING GEAR UPLOCK ROLLERS 32-10-00 LUBRICATION, MAIN LANDING GEAR 32-20-00 LUBR~CATION, NOSE LANDING GEAR 12-20-00 LUBRICATION
IWARN
MAGNESIUM CORROSION REMOVAL MAGNESIUM CORROSION TREATMENT MAGNETO DROP-OFF CHECK
20-09-00 20-09-00 74-00-00
PAGE 11 9 9 9 9 12 2 1
7 4 5 5 6 1 1 1 6 1 6 1
2
1 1 4 1 4 2 5 4 11 1 5 1 1 5
4 4
2
INTRODUCTION Page 22
Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT OR SUB
ITEM
SYSTEM
CHAPTER AND SUB CHAPTER
PAGE
MAGNETO INSTALLATION AND TIMING MAGNETO POINT GAP AND TIMING MAGNETO PREPARATION FOR INSTL MAGNETO PREPARATION MAGNETO PRESSURIZATION AIR FILTER MAGNETO REMOVAL MAGNETO TIMING MAIN LANDING GEAR ASSEMBLY MAIN LANDING GEAR CLEANING AND PARTS REPL MAIN LANDING GEAR DISASSEMBLY MAIN LANDING GEAR INSTALLATION MAIN LANDING GEAR LUBRICATION MAIN LANDING GEAR REMOVAL MAIN LANDING GEAR RETRACT ROD INSTALLATION MAIN LANDING GEAR RETRACT ROD REMOVAL MAIN LANDING GEAR SHOCK STRUTS SERVICING MAIN WHEEL AND BRAKE ASSY INSTALLATION MAIN WHEEL AND BRAKE ASSEMBLY REMOVAL MAIN WHEEL ASSEMBLIES MAIN WHEEL INSPECTION AND CLEANING MAIN WHEEL JACKING MANIFOLD PRESSURE ADJUSTMENT MANIFOLD PRESSURE ADJUSTMENT MAP LIGHT BULB INSTALLATION MAP LIGHT BULB REMOVAL MARKING OF ESDS COMPONENTS AND EQUIPMENT MASTER CYLINDER ASSEMBLY, BRAKE MASTER CYLINDER CLEANING AND PARTS RPL, BRAKE MASTER CYLINDER DISASSEMBLY, BRAKE MASTER CYLINDER INSTALLATION, BRAKE MASTER CYLINDER LINKAGE ADJUST, BRAKE MASTER CYLINDER REMOVAL, BRAKE MECHANICAL PRESS BEARING REMOVAL METAL SURFACE PREPARATION AND ELECTRICAL BONDING MODEL DESIGNATION PLACARD MOORING MOTOR INSTALLATION, FLAP MOTOR INSTALLATION, LANDING GEAR MOTOR REMOVAL, FLAP MOTOR REMOVAL, LANDING GEAR
74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 32-10-00 32-10-00 32-10-00 32-10-00 32-10-00 32-10-00 32-30-00 32-30-00 12-20-00 32-40-00 32-40-00 32-40-00 32-40-00 07-00-00 71-00-00 81-00-00 33-20-00 33-20-00 20-02-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 20-05-00 20-03-00 11-00-00 10-00-00 27-50-00 32-30-00 27-50-00 32-30-00
4 3 3 4 3 3 4 5 4 2 1 1 1 3 3 2 4 3 1 4 1 15 1 2 2 11 7 7 7 7 7 6 1 3 1 1 4 1 3 1
NONPOSITIONING TYPE FITTING INSTALLATION NOSE GEAR INSTALLATION NOSE GEAR LUBRICATION NOSE GEAR REMOVAL
20-06-00 32-20-00 32-20-00 32-20-00
2 1 1 1
INTRODUCTION
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COMPONENT ITEM OR SUB SYSTEM
NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE
NOSE
GEAR SHIMMY DAMPENER ASSEMBLY GEAR SHIMMY DAMPENER CLEANING/PARTS REPL GEAR SHIMMY DAMPENER DISASSEMBLY GEAR SHIMMY DAMPENER INSTALLATION GEAR SHIMMY DAMPENER MFG WEAR TOLERANCE GEAR SHIMMY DAMPENER REMOVAL LANDING GEAR ASSEMBLY LANDING GEAR CLEANING AND PARTS REPL LANDING GEAR DISASSEMBLY LANDING GEAR MFG WEAR TOLERANCE LANDING GEAR SHOCK STRUT WHEEL ASSEMBLY WHEEL INSPECTION AND CLEANING WHEEL INSTALLATION WHEEL REMOVAL WHEEL STEERING WHEEL TRAVEL STOP ADJUSTMENT
OIL BREAK-IN OIL COOLER INSTALLATION OIL COOLER REMOVAL OIL FILTER INSTALLATION OIL FILTER REMOVAL OIL GRADES OIL HIGH TEMPERATURE OIL PRESSURE ADJUSTMENT OIL SYSTEM OIL SYSTEM OPENABLE WINDOW INSTALLATION OPENABLE WINDOW REMOVAL OUTSIDE AIR TEMPERATURE GAGE REMOVAL OUTSIDE AIR TEMPERATURE GAGE OUTSIDE AIR TEMPERATURE GAGE INSTL OVERHAUL AND REPLACEMENT SCHEDULE OXYGEN CYLINDER INSTALLATION OXYGEN CONTROL CABLE ADJUSTMENT OXYGEN CYLINDER REMOVAL OXYGEN CYLINDER RETESTING OXYGEN HIGH PRESSURE TEST PROCEDURE OXYGEN LOW PRESSURE TEST PROCEDURE
OXYGEN SERVICING OXYGEN SYSTEM PURGING OXYGEN SYSTEM
CHAPTER AND SUB CHAPTER 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 12-20-00 32-40-00 32-40-00 32-40-00 32-40-00 32-50-00 32-50-00
79-00-00 79-00-00 79-00-00 12-10-00 12-10-00 79-00-00 79-00-00
71-00-00 12-10-00 79-00-00 56-20-00 56-20-00 34-10-00 34-10-00 34-10-00 05-10-00 35-00-00 35-00-00 35-00-00 35-00-00 35-00-00 35-00-00 12-10-00 35-00-00 12-10-00
PAGE
10 9 1 9
12 7 7 2 1 4 2 1 5 5 5 1 1
1 1 1 2 2 1 1 17 2 1 1 1 3 2 3 1 6 7 6 8
2 2 5 3 4
INTRODUCTION Page 24
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT
ITEM OR SUB SYSTEM
PACKAGING OF ESDS COMPONENTS AND EQUIPMENT PAINT FREE AREAS PAINT FREE AREAS PAINT REMOVAL FROM MAGNESIUM PAINT REMOVAL FROM MAGNESIUM SURFACES PAINTING AREAS OF HIGH HUMIDITY PAINTING BATTERY BOX AND LID PAINTING MAGNESIUM S.URFACES PAINTING MAGNESIUM PAINTING MUD AND SPRAY AREAS PAINTING PROCEDURES, SPECIAL PAINTING RUBBER SEALS PAINTING, PROPELLER BLADE PARKING BRAKE ADJUSTMENT PARKING BRAKE CLEANING AND PARTS REPLACEMENT PARKING BRAKE VALVE ASSEMBLY PARKING BRAKE VALVE DISASSEMBLY PARKING BRAKE VALVE INSTALLATION PARKING BRAKE VALVE REMOVAL PARKING PASSENGER READING LIGHT BULB INSTL PASSENGER READING LIGHT BULB REMOVAL PERMANENT STATIC CONTROL WORKSTATION PINS, TAPER PIPE THREAD FITTING INSTALLATION PITOT AND STATIC PRESSURE SYSTEM PITOT AND STATIC SYSTEM TROUBLESHOOTING PITOT SYSTEM PRESSURE TEST PITOT SYSTEM PLACARD REPLACEMENT
PLATES/SKIN PORTABLE STATIC CONTROL WORKSTATION POSITION LIGHT ADJ, LANDING GEAR POST LIGHTS POWER PLANT POWER SUPPLY UNIT INSTALLATION POWER SUPPLY UNIT REMOVAL PREPARATION FOR PRESERVATION OF FUEL CELL (GOODYEAR) PRESERVATION OF FUEL CELL (UNIROYAL) PRESSURE POT BLEEDING PRESSURE REGULATOR ADJUSTMENT PRESSURE REGULATOR INSTALLATION PRESSURE REGULATOR REMOVAL PRESSURE, LOW INSTRUMENT AIR
CHAPTER AND SUB CHAPTER
20-02-00 20-08-00 20-00-00 20-00-00 20-08-00 20-00-00 20-00-00 20-08-00 20-08-00 20-00-00 20-00-00 20-00-00 20-00-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 10-00-00 33-20-00 33-20-00 20-02-00 27-00-00 20-06-00 34-10-00 34-10-00 34-10-00 34-10-00 20-08-00 53-30-00 20-02-00 32-60-00 33-20-00 71-00-00 33-40-00 33-40-00 10-00-00 28-10-00 28-10-00 32-40-00 36-00-00 36-00-00 36-00-00 36-00-00
PAGE
10 7 6 3 5 5 6 6 5 5 5 5 5 7 7 7 7
7 7 1 1 1
4,6 2 2 1 1 1 1 3 1
5,8 1 1 1 2 2 4 9 9 10 7 6 6 2
INTRODUCTION
A18
Page 25 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
PRETREATMENT (WASH) PRIMER FOR URETHANE PAINT PRIMARY STRUCTURAL COMPONENTS PROPELLER ADJUSTMENT PROPELLER BLADE MAINTENANCE PROPELLER BLADES PAINTING PROPELLER DEICE BOOTS PROPELLER DEICER BOOT INSTALLATION PROPELLER DEICER BOOT REMOVAL PROPELLER DEICER TROUBLESHOOTING PROPELLER GOVERNOR ADJUSTMENT PROPELLER GOVERNOR INSTALLATION PROPELLER GOVERNOR REMOVAL PROPELLER INSTALLATION PROPELLER REMOVAL PROPELLER REPAIR, MINOR PROPELLERS PUMP INSTALLATION, AUXILIARY FUEL PUMP INSTALLATION, ENGINE DRIVEN FUEL PUMP REMOVAL, AUXILIARY FUEL
20-08-00 51-00-00 61-10-00 12-20-00
RADAR ANTENNA INSTALLATION RADAR ANTENNA REMOVAL
34-40-00 34-40-00 34-40-00 39-10-00 39-10-00 20-03-00 36-00-00 36-00-00 36-00-00 32-30-00 32-30-00 32-30-00 32-40-00 20-09-00 20-06-00 20-02-00 51-00-00 28-10-00
RADAR, WEATHER RADIO/AVIONICS EQUIPMENT INSTALLATION RADIO/AVIONICS EQUIPMENT REMOVAL RECOMMENDED MATERIALS REGULATOR ADJUSTMENT, PRESSURE REGULATOR INSTALLATION, PRESSURE REGULATOR REMOVAL, PRESSURE RELAY CHECK, DYNAMIC BRAKE RELAY INSTL, LANDING GEAR DYNAMIC BRAKE RELAY REMOVAL, LANDING GEAR DYNAMIC BRAKE RELINING THE BRAKES REMOVAL OF CORROSION FROM ALUMINUM SURFACES REMOVAL OF TUBE AND HOSE ASSEMBLIES REMOVAL/INSTALLATION OF ESDS EQUIPMENT REPAIR OF FIBERGLASS COMPONENTS REPAIR OF FUEL CELL (GOOOYEAR REPAIR OF FUEL CELL (UNIROYAL REPLACING ELEVATOR TRIM TAB RESERVOIR INSTL, FUEL (CJ-149 AND AFT) RETAINING RINGS (SPIROLOX, ETC.) INSTALLATION RETRACT ACTUATOR CLEANING AND PARTS REPL, LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST, LANDING GEAR
20-08-00 12-20-00 30-60-00 30-60-00 30-60-00 61-20-00 61-20-00 61-20-00 61-10-00 61-10-00 61-10-00 61-10-00
28-20-00 28-20-00 28-20-00
28-10-00 27-30-00 28-10-00 20-07-00 32-30-00 32-30-00
PACE 4 1 1 3 7 1 5
5 1 1 1 1 1 1 2 1 1 1 1
1 1 1 2 1 2 7 6 6 3 3 3 6 3 1 1 2 9 9 6 1 5 8 9
INTRODUCTION Page 26
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT OR SUB
ITEM
SYSTEM
RETRACT RETRACT RETRACT RETRACT RETRACT RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING
ACTUATOR ASSY, LANDING GEAR ACTUATOR DISASSY, LANDING GEAR ROD TNSTL, MAIN LANDING GEAR ROD REMOVAL, MAIN LANDING GEAR SYSTEM LUBRICATION, LANDING GEAR AILERON CONTROL SYSTEM AILERON CONTROL SYSTEM ELEV TAB, COMPENSATE YAW TO LEFT EtEV TAB, COMPENSATE YAW r0 RH ELEVATOR CONTROL SYSTEM ELEVATOR TAB ELEVATOR TRIM TAB RUDDER CONTROL SYSTEM THE CONTROL COLUMN CHAIN T~E LANDING GEAR RIGGING, ELEVATOR TAB, CORRECT FOR YAW ROTATING BEACON
CHAPTER AND SUB CHAPTER
32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 27-10-00 27-11-00 27-21-00 27-21-00 27-30-00 27-21-00 27-30-00 27-20-00 27-10-00 32-30-00 27-21-00 33-40-00 12-20-00
ROTCN LOCKS RUBBER SEALS RUDDER BALANCING RUDDER CONTROL SYSTEM RIGGING RUDDER INSTALLATION RUDDER REMOVAL RUDDER RIGGING PROCEDURE RUDDER-MAINTENANCE PRACTICES RUDDER, MODELS F33A, F33C, A36 AND A36TC RUDDER, V35B RUDDERVATOR BALANCING RUDOERVATOR INSTALLATION RUDDERVATOR REMOVAL RUDOERVATOR Rigging PRACTICES RUDDERVATOR-MAINTENANCE
27-20-00 27-21-00 55-20-00 27-21-00 27-21-00 27-21-00 27-21-00
SAFETY SWITCH CHECKING IN TEST POSITION, LANDING GEAR SAFETY SYS MAINT AND ADJ, LANDING GEAR SAFETY SYSTEM OPTIONAL LANDING GEAR SCHEDULED MAINTENANCE CHECKS SEAT INSTALLATION, PASSENGER SEAT INSTALLATION, PILOT AND COPILOT SEAT INSTL, FIFTH AND SIXTH, (A36 ANO A36SC) SEAT INSTL, FIFTH (MODEL F33A AND V35B) SEAT REMOVAL, FIFTH AND SIXTH (A36 AND A36TC) SEAT REMOVAL, FIFTH (MODELS F33A AND V35B) SEAT REMOVAL, PASSENGER
32-30-00 32-30-00 32-00-00 05-20-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00
20-08-00 55-40-00 27-20-00
27-20-00 27-20-00 27-21-00 27-20-00
PA
8 7 3 3
1 4
4
9 9
1
7 6 1 1 4 7 4 4 7 1 1 1 1 1 1 1 1 3 3 3 5 1
9 9 1 1 3 1 4 4 4 4
3
INTRODU
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT
ITEM OR SUB SYSTEM
CHAPTER AND
SEAT REMOVAL, PILOT AND COPILOT SEAT STOWAGE, FIFTH AND SIXTH (A36 AND A36TC) SEAT STOWAGE, FIFTH (F33A, F33C AND V35B) SEATING SECONDARY STRUCTURAL COMPONENTS SELECTOR VALVE INSTALLATION, FUEL SELECTOR VALVE REMOVAL, FUEL SELF-LOCKING NUTS SENSOR INSTALLATION, FUEL QUANTITY SENSOR REMOVAL, FUEL QUANTITY SHAFT INSTALLATION, FLAP SHAFT INSTALLATION, FLAP INNER FLEX SHAFT REMOVAL, FLAP SHAFT REMOVAL, FLAP INNER FLEX SHIMMY DAMPER SHIMMY DAMPER SHIMMY DAMPENER ASSEMBLY, NOSE GEAR SHIMMY DAMPENER CLEANING/PARTS REP NOSE GEAR SHIMMY DAMPENER DISASSEMBLY, NOSE GEAR SHIMMY DAMPENER INSTALLATION, NOSE GEAR SHIMMY DAMPENER OVERHAUL, NOSE GEAR SHIMMY DAMPENER REMOVAL, NOSE GEAR SHIMMY DAMPENER WEAR TOLERANCE SHOCK STRUT SHOCK STRUT, NOSE LANDING GEAR SHOCK STRUTS, MAIN LANDING GEAR SHUTTLE VALVE, BRAKE SKIN THICK, EMP (F33A, F33C, A36, A36TC) SKIN THICKNESS, EMPENNAGE (V35B) SKIN THICKNESS, FUSELAGE (A36 AND A36TC) SKIN THICKNESS, FUSELAGE (F33A AND F33C) SKIN THICKNESS, FUSELAGE (V35B) SLIP RING ALIGNMENT SLIP RING MACHINING SLIP RING SLOTTED, STEEL LOCKNUTS (PREVAILING TORQUE TYPE) SPARK PLUGS SPECIAL CONDITIONS CAUTIONARY NOTICE SPECIAL PAINT PROCEDURES SPECIAL TOOLS STABILIZER INSIALLATION, HORIZONTAL STABILIZER INSTALLATION, RUDDERVATOR STABILIZER INSTALLATION, VERTICAL STABILIZER REMOVAL, HORIZONTAL STABILIZER REMOVAL, V35 ELEVATOR STABILIZER REMOVAL, VERTICAL
25-00-00 25-00-00 25-00-00 25-00-00 51-00-00 28-20-00 28-20-00 20-07-00 28-40-00 28-40-00 27-50-00 27-50-00 27-50-00 27-50-00 12-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 12-20-00 32-20-00
SUB CHAPTER
32-10-00 32-40-00 55-00-00 55-00-00
53-30-00 53-30-00 53-30-00 30-60-00 30-60-00 30-60-00 20-07-00 12-20-00 05-10-00 20-08-00 12-20-00 55-10-00 55-10-00 55-30-00 55-10-00 55-10-00 55-30-00
PAGE 1 4 4 1 1 1 1 1 1 1 4 5 4 5 2 7 10 9 9 9 9 9 12 2 1 1 1 2 5 8 4 6 10 11 13 1 3 1 7 19 1 1 1 1 1 1
INTRODUCTION
Page 28 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES
MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
ITEM
CHAPTER AND
OR SUB SYSTEM
SUB CHAPTER
STAINLESS STEEL AND TITANIUM SURFACES STALL WARNING SYSTEM ADJUSTMENTS STALL WARNING SYSTEM DESC AND OPER STALL WARNING SYSTEM MAINT PRACTICES STALL WARNING/SAFE FLIGHT SYS DESC/OPER STALL WARNING STALL WARNING/SAFE FLIGHT SYS MAINT PRAC STANDBY AIR FILTER INSTL (INTAKE) STANDBY AIR FILTER REMOVAL (INTAKE) STANDBY AIR FILTER INSTL (INLINE) STANDBY AIR FILTER REMOVAL (INLINE) STANDBY GENERATOR-DESC AND OPER STANDBY GENERATOR-MAINTENANCE PRAC STANDBY INSTRUMENT AIR SYSTEM STARTER BRUSHES STARTER INSTALLATION STARTER LUBRICATION STARTER OVERHAUL STARTER REMOVAL STARTER TROUBLESHOOTING STARTING STATIC AIR SYSTEM-EMERGENCY STATIC AIR SYSTEM-NORMAL STATIC SYSTEM CHECKS STATIC WICK INSTALLATION STATIC WICK REMOVAL STATIC WICKS STATION DIAGRAMS (MODEL A36 AND A36TC) STATION DIAGRAMS (MODEL STATION DIAGRAMS (MODEL 35 STEEL CORROSION REMOVAL STEERING, NOSE WHEEL STEP LIGHT´•L STORAGE AND TRANSIT OF ESDS COMPONENTS AND STORAGE, EXTENDED STORAGE, TEMPORARY STORAGE STORM WINDOW INSTALLATION STORM WINDOW REMOVAL STRAINER INSTL (SELECTOR VALVE), FUEL STRAINER INSTL (WING FUEL CELLS), FUEL STRAINER REMOVAL (SELECTOR VALVE), FUEL STRAINER REMOVAL (WING FUEL CELLS), FUEL STRAINERS, CLEANING FUEL STRIPPING AND CLEANING URETHANE PAINT STROBE LIGHT POWER SUPPLY INSTL
20-03-00 27-31-00 27-31-00 27-31-00 27-31-00 27-31-00 27-31-00
36-00-00 36-00-00 36-00-00 36-00-00 24-31-00 24-31-00 36-00-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 34-10-00 34-10-00 34-10-00 23-60-00 23-60-00 23-60-00 06-00-00 06-00-00 06-00-00 20-09-00 32-50-00 33-40-00
33j
EQUIPMENT
20-02-00 10-00-00 10-00-00 10-00-00 56-10-00 56-10-00 28-20-00 28-20-00 28-20-00 28-20-00 28-00-00 20-08-00 33-40-00
PAGE 6 1 1 1 1 1 1 5 5 5 5 1 1 1 2 1 1 1 1 1 1 1 1 2 1 1 1 8 6 7 5 1 1
12 1 2 1 2 2 2 3 2 3 2 4
2
INTRODUCTION
A18
Page 29 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
STROBE LIGHT POWER SUPPLY REMOVAL STROBE LIGHT STRUCTURAL REPAIR SUBPANEL, RIGHT AND LEFT SUPPLEMENTARY PUBLICATIONS SURFACES SUSCEPTIBLE TO MUO AND SPRAY SURFACES, CONTROL
33-40-00 33-40-00 51-00-00 39-10-00 IN-TR-OD 20-08-00 27-00-00
2 1 1 2 6 7 1
TAB FREE PLAY, CHECKING ELEVATOR TAB HINGES, INSPECTION TAIL NAVIGATION LIGHT INSTALLATION TAIL NAVIGATION LIGHT REMOVAL TAIL STROBE/NAV LIGHT INSTALLATION TAIL STROBE/NAV LIGHT REMOVAL TAPER PINS, FLIGHT CONTROLS TAXI LIGHTINSTALLATION TAXI LIGHT REMOVAL TAXIING TEMPORARY STORAGE TEST FOR FUEL CELL LEAKAGE TESTING THE STATIC SYSTEM FOR LEAKS THREAD LUBRICANTS THROTTLE ADJUSTMENT THROTTLE WARNING HORN SYSTEM TIE-DOWN, NORMAL TIME LIMITS TIRE AND WHEEL MAINTENANCE TIRES TIRES TIT INDICATOR CALIBRATION TIT INDICATOR CALIBRATION
27-30-00 27-21-00 33-40-00 33-40-00 33-40-00 33-40-00 27-00-00 33-40-00 33-40-00 09-00-00 10-00-00 28-10-00 34-10-00 91-00-00 71-00-00 32-60-00 10-00-00 05-10-00 32-40-00 12-20-00 32-40-00 77-00-00 81-00-00 20-00-00 91-00-00 91-00-00 09-00-00 32-50-00 27-30-00 27-30-00 27-30-00 27-30-00 33-20-00 33-20-00 27-30-00 27-30-00
11 10
TORQUE WRENCHES TORQUING COARSE THREAD BOLTS IN SMEAR TORQUING FINE THREAD BOLTS IN SMEAR TOWING TRAVEL STOP ADJUSTMENT, NOSE WHEEL TRIM TAB ACTUATOR BRUSH REPLACE SCHED, ELEC TRIM TAB ACTUATOR INSTL, ELEC, (F33A, F33C, V35B) TRIM TAB ACTUATOR REMOVAL, ELEC, (F33A, F33C, V35B) TRIM TAB ACTUATOR, ELEVATOR TRIM TAB LIGHT BULB INSTALLATION TRIM TAB LIGHT BULB REMOVAL TRIM TAB SERVO INSTL, ELECTRIC ELEVATOR TRIM TAB SERVO REM, ELECTRIC ELEVATOR
PAGE
5 5 4 4 2
5 5 2 2 6
2 11 8 1 1 1 3 1 1 1 8 1 11 11 1 1’ 13 12 12 6 2 2 11 11
INTRODUCTION
Page 30 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT ITEM
CHAPTER AND
OR SUB
SUB
SYSTEM
TROUBLESHOOTING LANDING GEAR ELECTRICAL SYSTEM IROUBLESHOOTING-PITOT AND STATIC SYSTEM
CHAPTER
PAGE
TROUBLESHOOTING TUBE DAMAGE LIMITS TUBE INSTALLATION TUBING CLAMP TO BONDING JUMPER ELECTRICAL BONDING TURBOCHARGER ADJUSTMENT AND TEST TURBOCHARGER CONTROLLER INSTALLATION TURBOCHARGER CONTROLLER REMOVAL TURBOCHARGER INSPECTION TURBOCHARGER INSTALLATION TURBOCHARGER LEAK TEST TURBOCHARGER REMOVAL TURBOCHARGER SHAFT FREEING TURBOCHARGER SYSTEM TURBOCHARGER TROUBLESHOOTING TURNBUCKLE LOCK CLIP INSTALLATION TYPICAL BLIND GROUND STUD TYPICAL GROUND STUD ELECTRICAL BONDING
32-00-00 34-10-00 36-00-00 21-50-00 32-40-00 20-06-00 20-06-00 20-03-00 81-00-00 81-00-00 81-00-00 05-20-00 81-00-00 81-00-00 81-00-00 81-00-00 81-00-00 81-00-00 20-07-00 20-03-00 20-03-00
2 1 1 4 3 4 2 8 5 8 8 2 7 5 7 7 1 1 5 6 6
UPPER ROTATING BEACON INSTALLATION UPPER ROTATING BEACON REMOVAL URETHANE (EXTERIOR COLORS) URETHANE PAINT PROCEDURES (ALUMINUM) URETHANE PAINT REPAIR PROCEDURES URETHANE PAINTS URETHANE PRIMER URETHANE TOPCOATS URETHANE TOUCH-UP REPAIR UTILITY DOOR ADJUSTMENT UTILITY DOOR INSTL (MODEL A36 AND A36TC) UTILITY DOOR LATCH PIN ADJUSTMENT UTILITY DOOR REMOVAL (MODEL A36 AND A36TC) UTILITY DOOR WINDOW INSTALLATION UTILITY DOOR WINDOW REMOVAL UTILITY DOORS (MODEL A36 AND A36TC)
33-40-00 33-40-00 20-00-00 20-00-00 20-08-00 20-08-00 20-08-00 20-08-00 20-08-00 52-30-00 52-30-00 52-30-00 52-30-00 56-20-00 56-20-00 52-00-00
5 5 2 4 4 3 5 5 5 1 1 1 1 1 1 1
VALVE ASSEMBLY, PARKING BRAKE VALVE DISASSEMBLY, PARKING BRAKE VALVE INSTALLATION, PARKING
32-40-00 32-40-00 32-40-00
7 7 7
TROUBLESHOOTING, INSTRUMENT AIR SYSTEM TROUBLESHOOTING, AIR-CONDITIONING
INTRODUCTION
A18
Page 31 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
ITEM
OR SUB SYSTEM
VALVE VALVE VALVE VALVE VALVE
REMOVAL, PARKING
INSTALLATION,
FUEL SELECTOR INSTALLATION, PARKING BRAKE REMOVAL, FUEL SELECTOR REMOVAL, PARKING BRAKE VALVE, BRAKE SHUTTLE VENDOR PUBLICATIONS FILLER CAPS INSP, FUEL CELL VENT LINES VENTILATION BLOWER INSTALLATION VENTILATION BLOWER REMOVAL VERTICAL STABILIZER INSTALLATION VERTICAL STABILIZER REMOVAL VOLTAGE REGULATOR ADJUSTMENTS VOLTAGE REGULATOR INSTALLATION VOLTAGE REGULATOR REMOVAL
WARNING AND POSITION LIGHT BULB INSTL WARNING AND POSITION LIGHT BULB REMOVAL WARNING HORN SYSTEM, THROTTLE WAXING AIRPLANE FINISHES WEAR AND WEAR LIMITS, BRAKE WEATHER RADAR WHEEL AND TIRE MAINTENANCE WHEEL ASSEMBLIES, MAIN WHEEL ASSEMBLY AND BRAKE INSTALLATION WHEEL ASSEMBLY AND BRAKE REMOVAL WHEEL ASSEMBLY, NOSE WHEEL INSPECTION AND CLEANING MAIN WHEEL INSPECTION AND CLEANING, NOSE WHEEL INSTALLATION, NOSE WHEEL REMOVAL, NOSE WHEEL TRAVEL STOP ADJUSTMENT, NOSE WICKS, STATIC WINDOW CLEANING WINDOW INSTALLATION (FORWARD LEFT) WINDOW REMOVAL (FORWARD LEFT) WINDOWS AFT OF OPENABLE WINDOW INSTL WINDOWS AFT OF OPENABLE WINDOWS REMOVAL WINDSHIELD INSTALLATION WINDSHIELD REMOVAL WING ACCESS OPENINGS WING ADJUSTMENT WING ATTACH FITTINGS WING BOLT, NUT AND FITTING INSPECTION
CHAPTER AND SUB CHAPTER
32-40-00 ’28-20-00 32-40-00 28-20-00 32-40-00 32-40-00 IN-TR-OD 28-20-00 21-50-00 21-50-00 55-30-00 55-30-00 24-30-00 24-30-00 24-30-00
33-20-00 33-20-00 32-60-00 20-08-00 32-40-00 34-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00
32-40-00 32-40-00 32-40-00 32-40-00 32-50-00 23-60-00 56-00-00 56-10-00 56-10-00 56-20-00 56-20-00 56-10-00 56-10-00 57-30-00 57-00-00 57-40-00 57-00-00
PAGE 7 2 7 2 7 1 6 3 11 11 1 1 7 7 6
1 1 1 3 1 1 3 1 4 3 1 4 5 6 5 1 1 1 1 1 1 1 1 1 1 4 1 7
INTRODUCTION Page 32
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT OR SUB
WING WING WING WING WING WING WING WING WING WING WING WING
ITEM
CHAPTER AND
SYSTEM
SUB CHAPTER
INSTALLATION LEADING EDGE AND MAIN SPAR REMOVAL LEADING EDGE AND MAIN SPAR INSTL MAIN SPAR CAP INSPECTION, OUTBOARD NAVIGATION LIGHT INSTALLATION NAVIGATION LIGHT REMOVAL REMOVAL SKIN THICKNESS STROBE LIGHT INSTALLATION STROBE LIGHT REMOVAL TIP INSTALLATION TIP REMOVAL
57-00-00 57-00-00 57-00-00 57-00-00 33-40-00 33-40-00 57-00-00 57-30-00 33-40-00 33-40-00 57-00-00 57-00-00
PAGE 2 1 2 11 4 4 1 2 4 3 1 1
"END"
INTRODUCTION
A18
Page 33 Aug 18/95
CHAPTER
TIME LIMITS/
MAINTENANCE CH EC KS
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
TIME LIMITS/MAINTENANCE CHECKS
CHAPTER 5
TABLE OF CONTENTS
PAGE
SOBJECT
5-1 0-00
Special Landing
1
Replacement Schedule
Overhaul and
Conditions
Cautionary
1
Notice
2
Gear
3
Power Plant
Flaps Fuel
4
Controls
Flight
and
4
System
4
Instruments Electrical
5
System
5
Miscellaneous
5-20-00
Scheduled Maintenance Checks
1
Maintenance Practices
Electric
Propeller
Deicer
(EiO-Hour Guide)
1
Electric
Propeller
Deicer
(100-Hour Guide)
1
Turbocharger(EA-l
3
and After)
25 Hours
3
50 Hours
3
100 Hours
3 3
E33C, F33C Spin Inspection (Acrobatic Category) 100-Hour
or
Annual
Inspection
A36 and
Program (Models
Special
Conditions Cautionary Notice
A.
or
Annual
6
B36TC)
FACTS
1GO-Hour
6
Guide
7 9
Inspection
9
Operational Inspection
10
B. Power Plant
C. Cabin and D.
A23
Wings
and
Baggage Compartment
13
Carry-Through Structure
15
E. Nose Gear
16
F. Main Gear and Brakes
17
G. Main Gear
Operation
18
H. Nose Gear
Operation
19
5-CONTENTS
Jun
28/02Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
TABLE OF CONTENTS (CONTINUED)
SUBJECT
I. Rear
PAGE
Fuselage
and
Empennage
J. General
Jun
28/0Page
2
5-CONTENTS
19 20
A23
Ray~eon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
LIST OF PAGE EFFECTIVITY
CI-IAPTER-SECnON-SUBJECT
PAGE
DATE
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5-EFFECTIVITY
Jun
28/02Pagel
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE replacement must be performed not later than the recommended period. The condition period can be used as a criterion for determining subsequent periods applicable individual airplane or fleet operation, provided the operator has an approved monitoring system.
The first overhaul
or
item at the end of the first
The time
periods
for
inspections noted in
this manual
are
based
on
of the to the
average usage and average environmental
con-
ditions.
NOTE The recommended function
as
periods
do not constitute
a
guarantee the item will reach the period without malby the manufacturer.
the aforementioned factors cannot be controlled
SPECIAL CONDITIONS CAUTIONARY NOTICE
WARNING I WARNIEIO)
performing maintenance on an engine or the Airframe, ALWAYS pull the starter conLanding Gear circuit breaker. This will remove power to the control as well as the igniter power relay and Landing Gear Control relay.
Prior to
trol circuit breakers and the starter
for Air Taxi, or other than normal operation, and airplanes operated in humid tropics, or cold and damp climates, etc., may need more frequent inspections for wear, corrosion and/or lack of lubrication. In these areas, periodic inspections should be performed until the operator can set his own inspection periods based on ex-
Airplanes operated
perience. NOTE The date noted
on
the "STANDARD AIRWORTHINESS CERTIFICATE", FAA Form No. 8100-2,
which is issued with each
ponents listed in the An
engine cycle
new
following
is defined
as
airplane,
is to be used
as
the basis for all TBO
or
replacement
com-
schedule.
the
period
of time from the initial start to shutdown of the
engine. This
encompasses start-up, increase to full or partial power las required during a flight regime) and back to complete engine shutdown. Normal operation results in the number of landings being equivalent to
azs
engine cycles.
5-1 0-00
Jun
28/02Pagel
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE
OVERHAUL OR REPLACE
ITEM
NOTE All items not listed
are
to be overhauled or
replaced
"on condition". "On condition" items
are to
be overhauled
or
unserviceable condition, if they are worn, inoperative, potentially replaced inspection normal maintenance. Primarily items that are calender, cycle not intermittent and inaccurate, repairable through or hour limited are included in the following list. reveals
if
unsafe
a
or
LANDING GEAR Main Gear
On condition
(Leaking or collapsed struts that cannot be by replacement will constitute the "On condition" requirement. Any pitting, corrosion, cracking,
Assembly
corrected
distortion
seal
or
visible
replacement will overhaul.) Nose Gear
wear
noted
during the seal requirement for
also constitute the
an
On condition
(Leaking or collapsed struts that cannot be by seal replacement will constitute the "On condition" requirement. Any pitting, corrosion, cracking, distortion or visible wear noted during the seal replacement will also constitute the requirement for an overhaul.)
Assembly
corrected
Nose Gear Retract Rod Rod-Ends
(All)
2000 hours
Actuator
4000 hours
Retract Motor
2000 hours
Retract Motor Brushes
500 hours
Shimmy Damper
On condition
Wheels and Tires
On condition
or on
Brake
Assembly
On condition
Brake
Lining
On condition
Cylinder
On condition
Shuttle Valve Assembly
On condition
Master
Parking
Brake Valve
All Hoses
Jun
28/025-10-00
I
condition
I
On condition
On condition
als
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
POWER PLANT
NOTE A TBO
(time between overhaul) recommendation is in no way to be construed as a warranty or engine life proration basis. The TBO recommendation is based on the projected time for most advantageous initial overhaul. The individual operator’s experience may indicate a departure in either direction from the recommended TBO for the particular operation. Cabin Heater Muff
On condition
*Engine (Non-turbocharged)
1700 hours
*Engine (EA-I
1600 hours
*Reference
and
after)
Teledyne Continental Motors Corporation Service Bulletin M91-8,
Engine
Controls
On condition
Engine
Vibration Isolator Mounts
Engine
Exhaust
System
overhaul
dated
or on
July 10, 1991
or
subsequent.
condition
On condition
Starter
Inspect
at
engine overhaul,
overhaul
or
replace
on
condition
Standby Generator Standby Generator
1500 hours
Brushes
500 hours
Alternator
On condition
Oil Cooler
On condition,
Propeller (McCauley)
Refer to
Propeller (Hartzell)
replace
if contaminated
McCauley Service
Bulletin 1378
or
subsequent
Refer to the latest revision of Hartzell Service Letter 61 for TBO
Propeller Controls
On condition
Propeller Governor (McCauley)
At
engine
overhaul
condition but not to exceed
or on
1800 hours
Propeller Governor (Woodward)
At
engine overhaul
or on
condition. Refer to Woodward
I
Service Bulletin 3350. Air Pressure
Standby
Refer to
Pump
Air Pressure
All Hoses
Pump
Replacement Schedule
Every 600 hours Hoses
of pump
in Airborne SI 300-16
operation
carrying flammable liquids
at
engine
overhaul
or
every 5 years, whichever occurs first since the last replacement or delivery date of the airplane from the
factory; all other Engine
Air Filter
hoses
on
condition
Clean every 50 hours of operation (10 times max.). Replace every 500 hours or 1 year, whichever occurs first.
A23
5-1 0-00
Jun
28/02Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
POWER PLANT
Engine
(Continued)
Baffle Seals
Replace Teledyne Continental
Magneto (Bendix
(TCM))
Motors
as
necessary
or
every 10 years of service.
Engine overhaul or every four years, whichever first. Refer to TCM Service Bulletin 643.
comes
FLAPS AND FLIGHT CONTROLS Aileron Trim and
Flight
Linkage
On condition On condition
Controls
Elevator Tab Actuator
On condition
Flap Motor and Gearbox
Replace
Flap Actuators
2000 hours
Flap Flexible Shaft
2000 hours
on
condition
FUEL SYSTEM On condition
Fuel Cells
Wing
Fuel
Quantity
Transmitters
Fuel Cell Drain Valve
Fuel
System Check
Valves
On condition On condition On condition every 10 years
Fuel Selector Valve
Replace
Fuel Boost
Overhaul every 10 years
Pump
Hoses
All Hoses
carrying
flammable
liquids
at
engine overhaul
or
every 5 years, whichever occurs first since the last replacement or delivery of the airplane from the factory; all other hoses
Fuel Cell Reservoir Kit (If installed)
Replace
on
condition
foam insert every 10 years
INSTRUMENTS Turn Coordinator
On condition
Altimeter
Every 24 months calibrate)
Directional
Gyro
Horizon
Gyro
Pressure
nuJ4
28/02
(inspect and
On condition
On condition
Gyro
Page
per FAA directive
Gage
5-1 0-00
On condition
A23
I
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
INSTRUMENTS (Continued) Units
Engine Gage
On condition
Airspeed Indicator
On condition
Rate-Of-Climb
On condition
Fuel Flow/Manifold Pressure Indicator
On condition
Tachometer
On condition
Clock
On condition
Flap Position indicator
On condition
Free Air
On condition
Temperature Indicator
Pressure
System
Standby
Pressure
Air Pressure
Filter
(In-line
System
Regulator
and
Filters
Intake)
(In-line
and
300 hours of
Every
300 hours of pump operation
airplane operation
On condition
Valve
On condition
All Hoses
Standby
Intake)
Every
Air Pressure
System
Check Valve
Replace
every 10 years
ELECTRICAL SYSTEM
Battery Master Relay
On condition
All Other
On condition
Relays
Voltage Regulator
On condition
Starter
On condition
Relay
Battery (Emergency
Locator
Transmitter)
Replace
at 50% of useful life
las
any time transmitter is used cumulative hour or
stated
more
on
than
the
battery)
one
MISCELLANEOUS Hand Fire Cabin
Extinguisher
Heating
and
Ventilating
Ducts
Inspect
every 12 months,
Inspect
every 12 months
Oxygen Regulator
On condition
Air Conditioner Filter
On condition
Air Conditioner
On condition
Seat Belts
or
Compressor
Inspect every
Shoulder Harnesses
Oxygen Cylinder (Lightweight
3HT
Type)
12 months
Hydrostatically years
or
recharge
as
necessary
or on
condition
or on
condition
test every 3 years.
Replace every
4,380 refills (ICC regulation), whichever
24
occurs
first.
A23
5-1 0-00
Jun
28/02Page
5
Ray~hean Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE
(CONTINUED)
OVERHAUL OR REPLACE
ITEM
MISCELLANEOUS (Continued)
Oxygen Cylinder (Standard Weight Wing-Attach Bolts
3AA
Type)
Hydrostatically Replace Refer to
Jun
28/0Page
6
5-1 0-00
test every 5 years
10 years after initial Chapter 57.
inspection
or on
condition.
n?s
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
SCHEDULED MAINTENANCE CHECKS
ELECTRIC PROPELLER DNCER
MAINTENANCE PRACTICES
(50 HOUR GUIDE)
of the propeller deicer system should be inspected every 50 hours for the appearance of following inspections may provide means for detecting and correcting such defects before they render system inoperative:
The various
components
defects. The the deicer a.
Lock the brakes and
operate the engine
at near takeoff power. Turn the deicer
systems switch ON and observe
the ammeter for at least 3 minutes. If the ammeter needle does not indicate amperage (reference ELECTRIC PROPELLER DEICING in Chapter 30-60-00 for proper amperagej for 90 seconds at 90 second intervals, refer to the
troubleshooting
chart for the
probable
sources
of trouble.
WARNING IWdRNINO) Before moving propeller, make certain that ignition switch is OFF and that engine has cooled completely. There is always some danger of a cylinder firing when propeller is moved.
CAUTION I IcnuTloN While
following
the instructions of step b,
tween the brushes and
b.
With the
engine
move
the
forth to
propeller back and
prevent arcing be-
slip ring.
shut off, turn the deicer switch ON and feel the deicer boots
quence of heater operation. The presence of local hot spots indicates service should be repaired before more serious damage develops.
on
the
damage
propeller for
to the deicer
the proper
se-
heaters, which
Remove the spinner and open all access doors pertaining to the wiring and components of the deicer system. Turn the deicer switch ON and station an assistant in the cockpit to observe the system ammeter. Flex all accessible wiring, particularly the lead straps, leads from the slip ring assembly, and the firewall electrical connectors and their c.
wiring. Any short d.
or
movement of the ammeter, other than the
To extend the life of the lead
at least 1/2 inch from the e.
flicker that
occurs
at 90 second
intervals, indicates
Check for
damaged
existing
strap between the hub clamp and clip, reposition the bend in the strap
a
brush rods
Check for radio noise
or
at
a
point
location of the bend. or
springs
ELECTRIC PROPELLER DNCER a.
cycling
open circuit that must be located and corrected.
and for
worn or
damaged
brushes.
(100 HOUR GUIDE)
radio compass interference
at near takeoff power with the radio
by operating the engine
If, under these conditions, noise or interference occurs when the deicer switch is ON and disappears when the switch is OFF, refer to the troubleshooting chart for the probable source of trouble. gear turned
on.
WARNING IWARNINOI Before
moving propeller,
completely.
nza
There is
make certain that
always
some
ignition switch
is OFF and that
danger of a cylinder firing when
a
engine has cooled
propeller is moved.
5-20-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL b.
Check all
ness.
clamps, clips, mountings, electrical connections or missing safety wire.
and connectors for
tightness
and electrical sound-
Check also for loose, broken
Closely check the
deicer boots for wrinkles, loose or torn areas, particularly around the outboard end and at the the strap passes under the hub clamp. Look for abrasion or cuts along the leading edge of the flat or thrust face. If the heater wires are exposed in damaged areas or if the rubber is found to be tacky, swollen or detec.
point where riorated
d.
las
from contact with oil
or
solvent
fluids), replace
the
damaged
deicer boot.
Check that the hub
clamps are tight. Inspect for cracks or other damage. Check to see that the cushioning mamissing or damaged in the area under the hub clamp or on the edge of the spinner dome. Manually oppropeller from "high pitch" to "low pitch" while checking that the deicer lead straps do not come under
teria\ is not erate the
tension. e.
slip rings for gouges, roughened surfaces, cracks, burned or discolored areas, and for deposits of oil, dirt. Clean greasy or contaminated slip rings with CRC-2-26 solvent (23, Chart i, 91-00-00). After such a allow a run-in time of 5 hours of engine operation before turning on the deicer system.
Check the
grease
or
cleaning,
wobble is detected, check the alignment of the slip rings to the prop shaft with a dial indicator. the turning prop to check the slip ring alignment, push in on the prop to eliminate play in the propeller thrust If the out over 360" of rotation is over 0.005 inch or if over any 4-inch are it exceeds 0.002 inch, refer run bearing. to the paragraph on SLIP RING ALIGNMENT in Chapter 30-60-00. f.
If
uneven wear or
While
g.
Examine the brush
sure
that connections
mounting bracket and housing for cracks, deformation, tight and that the leads are not chafed or binding.
or
other indications of
damage. Make
are
fully on its slip ring over 360" of rotation. If the brush is not properly aligned, elongate the holes in the mounting bracket to raise or lower the brush block to the proper position. If the brushes ride BOTH high and low with respect to the slip rings in 360" of rotation, the slip ring assembly is eccentrically mounted and the spinner bulkhead must be replaced. For the correct angular location of the brushes to the slip ring, refer to the illustrations in Chapter 30-60-00. h.
Check to
that each brush rides
see
add shims under the brush block
or
Check for proper spacing between the brush block and slip rings as indicated in DEICER BRUSH REPLACEMENT, Chapter 30-60-00. If this distance is not within the specified limits, loosen the mounting screws and reposi-
i.
tion them in the
bearing plate
elongated holes until the block is properly positioned. If necessary, mounting bracket until the brush block is properly located.
add shims between the thrust
and
angle of the brush block in relation to the slip rings. If this angle is not approximately 2", as indicated in DEICER BRUSH REPLACEMENT, Chapter 30-60-00, loosen the mounting screws and reposition the brush block until the proper angle exists between the brush block and slip rings. The spacing established in Figure 3, Chapter 30-60-00 must also be maintained after the proper contact angle is established.
j.
Estimate the contact
CAUTION 1 [CAVTION While
following
the instructions of
tween the brushes and
k.
step k,
move
the
propeller back
and forth to
prevent arcing be-
slip ring.
With the deicer system operating and a man in the cockpit observing the ammeter, visually inspect and physifrom the brush blocks to each component of the deicer system and to the aircraft power supply.
cally flex the wiring
Movement of the ammeter needle indicate loose
wiring
in the
or
area
harness until the
Jun
28/0Page
2
(other than
the
cycling that occurs
when the timer switches at 90-second
intervals)
under examination at the moment. In such instances, continue to flex the that first indicated trouble while checking the continuity through the individual wires of the affected in the
broken
wiring
source
of trouble is located. Use the
5-20-00
area
wiring diagram
to trace the
circuitry
of the deicer
system.
Ray)heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
TURBOCHARGER
(EA-1
AND
AFTER)
25 HOURS a.
Visually inspect
oil leaks, exhaust system leaks and
general
condition.
oil leaks, exhaust system leaks and
general
condition.
50 HOURS a.
Visually inspect
100 HOURS
Inspect turbocharger system per a.
following method:
assembly. Inspect the compressor wheel for nicks, cracks or broken blades. Turn excess bearing drag or wheel rubbing against housing. Reinstall air inlet duct.
Remove compressor inlet duct
wheel b.
the
by hand and feel
for
Check the oil inlet and outlet ports in center
housing
for leaks, and the turbine heat blanket for condition and
security. Check for any interference with tion and security. c.
d.
Inspect
all exhaust system
linkage
between the
components for
worn or
bypass
valve
damaged
(wastegate)
areas, loose
clamps, cracks and
Inspect lubrication system components for worn or damaged areas, loose clamps and should be given to the ducts downstream (pressure side) of the compressor. e.
f.
Inspect
the fuel
injection
general
and actuator, its
leaks.
condi-
leaks.
Special
attention
nozzle pressure reference manifold, for deteriorated hose, loose connections, leaks
or
obstructions
g.
All fluid power lines should be checked for leaks and
security.
The compressor discharge reference line from the throttle air valve to the controller should be spected for oil leakage from the controller. Any leakage is cause for replacement of the controller. h.
opened
and in-
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) inspection is required on all E33C and F33C (CJ-1 and after) airplanes which are being acrobatically spun is (even if the spin time is only a small part of total time). This inspection is NOT required if an airplane performing acrobatic maneuvers other than spins (no spins at all). The regular 109-Hour Inspection (P/N 98-322276 or subseGuide (P/N quent), Intermediate 1 GO-Hour inspection (P/N 98-38999 or subsequent) or Continuing Care Inspection
This
98-36711D
n?s
or
subsequent)
MUST also be
complied
with.
5-20-00
JunPa2~egi:Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) FREQUENCY 1. 50 Hours
PART Rudder
INSPECTION
pedal
CORRECTIVE ACTION
Check for cracks.
If cracks
MECH
bellcrank
Technical
found, contact the Support Department of
support
Raytheon
Aircraft
INSP
are
Company.
assembly 2. 50 Hours
Elevator to
Check
Elevator
(4
torque fitting casting joint
proper hole diameter.
per
screw
holes
elevator)
If hole diameter is
for
inch,
ream
more
hole to 0.208
than 0.194 rt
0.002 inch
diameter and install NAS 2903-4
or
NAS 6203-4)( oversize bolt. If hole
diameter exceeds 0.210 inch for oversize bolts, contact the Technical
Support Department of Raytheon Company. Torque bolt or
Aircraft screw
to 30 to 40 inch-tbs.
Check hole size in
If hole diameter is greater than 0.251
elevator inboard
inch, replace elevator torque fitting.
hinge
mount hole in center of
elevator torque
fitting.
Check elevator rod end
mounting
3. 50 Hours
hole in the
If hole diameter is
inch,
ream
greater than 0.379
to 0.436
~t
elevator torque fitting for
install
proper diameter.
bushing.
Horizontaland
Horizontal stabilizer
If bolt holes
are more
vertical
in diameter
or
stabilizer
forward spar: Check diameter of 4 outboard
attachment
bolt holes
bolt holes
(2 upper and
on
each side 2
lower).
(stabilizer spars and
bulkheads)
one
bushings
0.001 inch and
BS 105740-X-XC-0500
than 0.253 inch
elongated,
to 0.270
ream
the
0.002 inch
diameter and install NAS 2904-14 oversize bolts. If hole diameter exceeds 0.272 inch for oversize
Horizontal stabilizer rear spar: Check diameter of 2 outboard bolt holes on
each side 1
(1
upper and
I bolts, contact the Technical Support Department of Raytheon Aircraft Company. Torque the nuts to 85 to 100 inch-lbs.
lower).
If any of these holes
are
oversize, check all other horizontal stabilizer holes and vertical stabilizer bolt holes for correct diameter.
Page
nu28102 J4
5-20-00
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) (CONTINUED) FREQUENCY
CORRECTIVE ACTION
INSPECTION
PART
Check torque
4. 50 Hours
on
all
nuts.
Inboard
Check for
elevatorhinge
and
straightness
Torque the pounds.
MECH
INSP
nuts to 85 to 100 inch
Replace
if bent
or worn.
Replace
if bent
or worn
wear.
bolts Elevator
push- I
rods to
Check for and
straightness
smaller than
0.370 inch diameter.
wear.
elevator
torque fitting bolt 5. 50 Hours
Upper
and
Inspect
tor
cracks,
middle rudder
corrosion andexcessive
hinges
wear.
cracks,
Lower rudder
Inspect
hinge
corrosion andexcessive
tor
Replace
if any of noted conditions
exist.
Replace
if any of noted conditions
exist.
wear.
6. 50 Hours
Elevatorhinge joint
Checkbearing for looseness and bearing bracket for cracks,
Replace
if noted conditions exist.
corrosion and excessive wear.
Check
If I.D. is
bushing
over
under 0.310
diameters.
Replace Check elevator
hinge
brackets hole diameter.
Check elevator
hinge
0.191 inch
or
O.D. is
inch, replace bushings.
if noted conditions exist.
If greater than 0.200 inch, replace
bracket.
Replace
if noted conditions exist.
Replace
if
bracket for cracks, corrosion and excessive wear.
Check bolts for
wear.
plating
is
worn or
corroded.
Check reassembled
joint 7. 50 Hours
straightness,
Elevator
Check for
pushrods
and cracks.
Check rod end
new
parts
as
bearing play.
Replace pushrod Replace
required.
excessive free
Check rod end
If
hole diameter.
more
I replace
if bent
or
cracked.
bearing if play is noted.
rod end
for excessive free
mounting
A23
Install
for looseness.
than 0.378 inch in diameter,
rod end.
5-20-00
Jun
28/02Page
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) (CONTINUED) FREQUENCY
PART
INSPECTION
CORRECTIVE ACTION
8. 50 Hours
Trim Tab
Check for cracks.
Replace if noted conditions
Check free indicated in
play as Chapter
Replace
tab
bushing
10. 50 Hours
Elevator
Trim tab
and/or trim tab
pushrod ends and/or trim excessive free
Check for cracks,
If cracks
especially between outboard hinge and
Technical
elevator balance horn.
repair.
Check
Replace
straightness.
are
play
INSP
exist.
tab
actuator shaft and/or trim tab
27-30-00.
9. 50 Hours
MECH
hinge
if
is noted.
found, contact the
Support Department of Raytheon Aircraft Company for if bent.
pushrod assemblies 11. 50 Hours
Trim tab
Check output shaft for
actuator
straightness.
Replace
if bent.
Check attach bolts for proper torque.
Check actuator installation for
looseness. 12. 50 Hours
Elevator
bellcrank
Check pushrod mounting hole for proper diameter.
If more than 0.379 inch, press out and press in one
existing bushing
BS105740X-XC0968 drill 0.377
hole 13. 50 Hours
14. 50 Hours
(elevator pushrod to bellcrank)
Check for
Inboard
Checkforcracks. Check
elevatorhinge casting
hinge bearingsfor
Bolt
and
straightness
rt
bushing
and
0.002-inch diameter
through bushing.
Replace
if bent
or worn
smaller than
0.370 inch.
wear.
Replace
if noted condition exists.
looseness.
100-HOUR ORANNUAL INSPECTION GUIDE operator is responsible for maintaining the airplane in an airworthy condition, including compliance applicable Airworthiness Directives as specified in Part 39 of Title 14 Code of Federal Regulations (14 CFR). It is further the responsibiiity of the owner or operator to ensure that the airplane is inspected in conformity with the I requirements covered in 14 CFR Parts 43 and S1.These 14 CFR Parts cover the requirements concerning the Inspection Guide. This Inspection Guide is not intended to be all inclusive, for no such guide can replace the good judgement of a certified airframe and power plant mechanic in the performance of his duties. As the one primarily responsible for the airworthiness of the airplane, the owner or operator should select only qualified personnel to maintain the airplane. The
owner or
with all
I
FACTS PROGRAIVI ~ODELS A36 AND
B36TC)
Airplanes delivered from the factory after August 1, 2001 will use the Factory Aircraft Comprehensive Tracking System (FACTS) which becomes the factory computerized maintenance tracking and forecasting system for the Model A36/B36TC series airplanes. The FACTS program for the Model A36/B36TC adheres to the guidelines es-
Jun 28/0 Page
:6
5-20-00
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL tablished in this
chapter of the
maintenance manual. The Raytheon Aircraft approved inspection program contained Raytheon factory computerized maintenance inspection program (FACTS), is specifically for the Model A36/B36TC series airplanes. Any variation to the inspection program must be approved in writing by the FAA Flight Standards District Office (FSDO), or Airworthiness Authority. The FACTS program meets the requirement of both 14 CFR 91 and 14 CFR 135. in this
and within the
chapter,
SPECIAL CONDITIONS CAUTIONARY NOTICE The time
periods for the inspections noted in this schedule are based on normal usage under average environmental Airplanes operated in humid tropics, or in cold, damp climates, etc., may need more frequent inspections for wear, corrosion, lubrication, and/or lack of maintenance. Under these adverse conditions, perform periodic inspections in compliance with this guide at more frequent intervals until the owner or operator can set his own inspection periods based on the contingencies of field experience. conditions.
NOTE The
required periods do not constitute a guarantee that the item will reach the period function, as the aforementioned factors cannot be controlled by the manufacturer.
without mal-
This inspection program, in accordance with 14 CFR Parts 43 and 91, consists of, but is not limited to, inspection items listed in this Inspection Guide, any applicable Airworthiness Directives issued
against Sheet
the airframe
as
or
any
equipment
installed therein and
conformity
to
Type Certificate Data
applicable.
Material contained in this
guide, including
the
inspection intervals, may
be
changed
at any time
by
the
owner/oper-
ator, with prior notification and approval of the local FAA General Aviation District Office, when warranted by service
experience or engineering recommendations. Information planes covered in this maintenance manual except where
contained herein is differences
are
applicable to all Bonanza by serial effectivity.
series air-
indicated
Inspection Guide may be used as an outline, detailed information of the many systems and components airplane will be found in the various sections of this maintenance manual and the pertinent supplier publications. It is also recommended that reference be made to the applicable maintenance handbooks, service instructions, Beech and Raytheon Aircraft service bulletins, applicable FAA regulations and publications, and supplier bulletins and specifications for torque values, clearances, settings, tolerances, and other requirements. In the final analysis, it is the responsibility of the owner/operator to ensure that the airframe and power plant mechanic inspecting the airplane has access to the previously noted documents as well as to this Inspection Guide. While the in the
NOTE
Any time are
an
airplane
not covered with
that have been
repainted or touched up, inspect all placards and decals to assure that they paint, are easily readable, and are securely attached. Replace any placards
is
inadvertently
defaced
or
removed.
In addition to the inspections prescribed by this schedule, the altimeter system and all ATC transponders MUST be tested and inspected at 24-month intervals in compliance with the requirements specified in 14 CFR Parts 91.411, and 91.70.
1
airplane must be accomplished within each 12-month period for compliance with the Regulations. The time periods for inspections stated in this inspection guide should NEVER be exceeded by more than 10 hours, and then only if the additional time is required to reach a place where the inspection can be satisfactorily accomplished. However, the additional time used must be deducted from the next inspection time. If 10 hours were used to reach the inspection facility, the next inspection would be due in 90 hours for the next 100-hour inspection with no extension allowed. A
complete inspection
of the
Title 14 Code of Federal
nu
5-20-00
JunPa2ggl~):Page
7
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
airplane must receive a complete (100-hour, annual, or complete continuing care inspection) inspection every 12 months regardless of the hours flown. The inspections completed during a 12-month period can be deleted from the items to be inspected. Rubber goods such as fuel lines are recommended to be changed at five year periods An
regardless
of
airplane time. NOTE
Additional
publications
For information
on
listed in the current Publications Price List CD ROM
are
these
1-800-796-2665, fax
publications (316) 676-4824,
(P/N 994-32808). (TMDC) at our web site at http:/l ray-
contact the Technical Manual Distribution Center
E-mail TMDC 8 rac.ray.con
or
visit
theonaircraft.com.
NOTE All electrical systems operational inspections are to be made using pable of delivering and maintaining 28.25 volts 0.25 volts DC.
I
Raytheon
Aircraft
Company issues
service information for the benefit of
classes of Service Bulletins. MANDATORY
(Red Border)
an
external power
source ca-
and operators in the form of two changes, inspections or modifica-
owners
Service Bulletins
are
factory considers compliance with these Service Bulletins mandatory. OPTIONAL Service Bulletins cover changes, modifications, improvements or inspections which may benefit the (No Border) of information covered by the OPTIONAL Service Bulletin, each owner or operator is the wide range owner. Due to responsible for conducting a thorough review of each OPTIONAL Service Bulletin to determine if compliance is required based on the applicability of the OPTIONAL Service Bulletin to his particular set of operating conditions. It is the responsibility of the owner or operator to ensure that all Beech and Raytheon Aircraft Service Bulletins which are pertinent to his particular operation are complied with. tions that could affect
safety.
The
NOTE Model E33C and F33C airplanes 50 hours.
being
spun MUST also have the AEROBATIC INSPECTION at
WARNING I I W~RNINO
During
I
the
Ensure the
Jun
28/0Page
8
performance landing gear
of this
inspection
the
airplane will be placed on three-point jacks. removing the airplane from the jacks.
is down and locked before
5-20-00
nns
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION A.
OPERATIONAL INSPECTION 1.
STARTER
energized
MECH
INSP
Check for proper operation, unusual noise and dragging. Check starter light (if installed) and/or load meter to ensure starter disengagement when
starter switch is released.
2.
3.
Check for proper fuel pressure limits and fluctuations.
FUEL FLOW
CYLINDER HEAD TEMPERATURE
I
I
I I
Check for proper operation, temperature and
fluctuations. Check for proper output and unusual noises.
4.
ALTERNATOR
5.
STANDBY ALTEWVATOR/ GENERATOR Perform
a
functional test
as
outlined in
Check for proper operation in test mode. 24-31-00 of P/N 36-590001-9A (or
Chapter
the Bonanza Series Maintenance Manual. Check
subsequent),
wiring
security
for
and
condition 6.
INSTRUMENT AIR SYSTEM
Check for proper
7.
STANDBY INSTRUMENT AIR
(If installed)
and
plumbing
wiring
for
operation
and output pressure.
Check far proper
and condition. Refer to AFM
security
operation. Check Supplement 36-590006-
23. 3.
PROPELLER OPERATION smoothness of
9.
Cycle propeller and
check for proper rpm
drop and
operation.
PROPELLER DEICER
Check for proper
operation
and amperage drawn
on
ammeter.
Check for proper pressure, temperature limits
10. OIL PRESSURE AND TEMPERATURE and unusual fluctuations. 11. MAGNETOS
Check the performance of the
NORMAL PROCEDURES in the 12. POWER CHECK
Operating
appropriate
Pilot’s
as
outlined under the
Operating
Refer to NORMAL PROCEDURES in the
heading
Handbook.
appropriate
Pilot’s
Handbook.
13. AMMETER
Check for proper indication and unusual fluctuations.
14. HEATING AND VENTILATING SYSTEM
15. FIREWALL SHUTOFF VALVE
Check for proper
16. IDLE RPM AND MIXTURE SETTINGS
Check controls for freedom of
17. IDLE CUT-OFF
Check for proper
18. IGNITION SWITCH
Rotate the
Check for proper operation, heat and airflow
of movement.
output. Check controls for freedom
settings.
magneto
operation
and freedom of movement.
Check for both proper rpm and mixture
operation.
operation
and freedom of movement.
ignition switch through
the OFF
position
to the extreme
limit of switch travel; if the engine stops firing, the switch is normal. If the engine continues to run with the switch held against the OFF stop, it is an indication that magneto is still "hot" or ungrounded. When the switch is released, it should
automatically
return to OFF and the
engine should stop running. However, replaced.
any
one
ignition
switch exhibiting this abnormal condition should be
ana
5-20-00
9
Ra~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION A. OPERATIONAL INSPECTION
(CONTINUED) MECH
(Continued)
INSP
With the engine running, check for proper operational limits, engine response and rigging. Check friction locks for proper operation.
19. ALL ENGINE CONTROLS
Check for proper operation and unusual fiuctuations.
20. FUEL QUANTITY GAGES 21. AUXILIARY FUEL PUMP
Check pump for proper
operation,
unusual noise and
fluctuations. 22. FUEL TANK SELECTOR
Check for proper placarding, proper
operation and
feel for
detent.
positive
Check for condition, attachment, cracked
23. ALL LIGHTS
switches, knobs and circuit breakers for looseness and 24. STALL WARNING SYSTEM
Check for proper
Check for proper
25. RADIO OPERATION
or
broken lenses. Check
operation.
operation
and
heating
of the unit.
operation, security of switches and
knobs.
Check for noisy operation, full travel and proper indication.
26. FLAPS
27. PITOT HEAT
Check for amperage drawn
on
ammeter and for proper
heating of
the
unit. 28. FLIGHT INSTRUMENTS
Check for condition and proper
operation.
Check for condition and wear, ease of operation and proper release of the brake. Check for unusual brake chatter.
29. BRAKES
parking
30. EMERGENCY LOCATOR TRANSMITTER Check for proper operation. Tune radio to 121.5 MHz on VHF or 243 MHz on UHF, then turn ELT switch to ON and monitor for
I
one
signal.
Turn ELT switch OFF, then place in ARM airplane is returned to service.
position.
Ensure that the ELT is
armed when the
31. AIR-CONDITIONER
condenser retracted
moves to
position
Operate the air conditioner and verify that the retractable ground extended position when turned on and returns to
the
when turned off. Check for proper
32. OXYGEN SYSTEM
operation
the
and unusual noise.
Functionally check the oxygen system for proper operation. Check operation.
the oxygen bottle shutoff valve for proper 33. SWITCHES, CIRCUIT BREAKERS
Check for proper operation.
CONTROLS, TRIM CONTROLS AND TRIM INDICATOR Check freedom movement and proper operation through full travel with and without flaps extended. Check electric trim controls for operation.
34. FLIGHT
B.
of
POWERPLANT 1.
NACELLE SKiN loose
2.
or
Page
cracks. Check for
COWL FLAPS
Open
the upper
for cracks.
Check for travel, deformation and
5-20-00
or
damage.
Check for condition, security and adjustment of latches.
cowling and clean. Inspect 4.
or
Check for cracks and deformation. Check for loose
rivets and concealed
COWLING
damage
rivets.
NACELLE STRUCTURE
missing 3.
missing
Check for deformation and obvious
security. Inspect for cracks.
Pi23
Ray~hean Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 1OO-HOUR OR ANNUAL INSPECTION B. POWER PLANT
5.
(CONTINUED)
(Continued)
MECH
INSP
Clean, inspect, regap, test and replace as necessary. Tighten spark torque and check ignition harness condition and for proper attachment.
SPARK PLUGS
plugs
to proper
6.
COMPRESSION
7.
BATTERY
Perform differential
compression
test.
tight connections and add distilled water to maintain a top of separators. Inspect the vents and overflow tube for obstructions. Check for security and proper attachment. Check for corrosion. Make certain the battery is clean. Water or dirt on battery surface can cause the battery to discharge. Inspect
for clean,
level of 3/8-inch above
8.
Inspect plumbing and associated accessories for condition (such as fraying) and attachment. Check plumbing clearance and secure against
PLUMBING cracks and
possible chafing. 9.
Check reservoir for
BRAKE FLUID RESERVOIR
security,
open vent, proper fluid level
and for leaks. 10. ENGINE OIL TANK OR SUMP and
Check for cracks, leaks, proper fluid level, deformation
security.
11. CRANKCASE
security
Check security of crankcase-thru bolts. inspect the
and that the tabs
are
dipstick tabs
for
not bent.
12. OIL SUMP DRAINS AND SCREENS
and for obstructions. Check for metal
Clean screens, check for holes in the screens particles or foreign matter on screens and filters.
Check for proper torque after installation. 13. OIL COOLER
Check oil cooler, lines and fittings for condition,
security, chafing
and
leaks. Check for condition and security. Check the lightning strikes. If there is evidence of lightning strikes, consult the propeller manufacturer, the engine manufacturer and Raytheon Aircraft Company. Inspect the blades for cracks, dents, nicks, scratches, erosion, corrosion, security and movement in the hub.
14. PROPELLER AND MOUNTING BOLTS
tip
of the blades for evidence of
15. PROPELLER SPINNER 16. PROPELLER HUB 17. ALTERNATOR
attachment and 18. ALTERNATOR
Check for deformation, security and cracks.
Check for cracks,
excessively leaking seals
Check for condition and attachment. Check
possible
and condition.
wiring
for proper
chafing. Check for unusual noise.
(Prestolite
or
Delco
Remy only) Remove and disassemble
the
necessary to inspect the rotor shaft bearings for condition and replace if necessary. Refer to Beech Service Instructions No. 0546-359 Rev II or subsequent.
alternator
as
19. STARTER
Check for condition, attachment and chafed
20. STANDBY GENERATOR/ALTERNATOR wires and for
n23
or
loose wires.
Check for condition, attachment, security of
chafing.
5-20-00
11
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION B. POWER PLANT
MECH
(Continued)
21. MAGNETOS
excessively
(CONTINUED) INSP
Check contact points for proper clearance. Points with deep pits or areas must be discarded. Inspect the cam follower felt pad for
burned
proper lubrication and clean the compartment with harness for proper connection,
security
and
22. MAGNETO PRESSURIZATION FILTER
a
fraying.
clean, dry cloth. Check ignition Check
timing.
Check for condition, cleanliness and
security.
Check cylinders and exhaust manifold for obvious leaks, security and cracks, check baffles for cracks and security. Check cylinders for broken cooling fins and loose or missing base nuts.
23. CYLINDERS AND BAFFLES
Check for deformation, security, cracks, leaks, loose or missing occur due to normal internal
24. EXHAUST SYSTEM
clamps. Check for thin wall condition which may erosion on stacks which have long service time. nuts and
25. FIREWALL access
Check for wrinkles, damage
holes for proper
or
cracks. Check all electrical and control
sealing.
Check all fuel, oil and air hose or duct for damage. Check fittings for security.
26. HOSE AND DUCTS
deterioration and
Check for condition,
27. ENGINE ACCESSORIES
and tubes for
chafing, security
28. ENGINE MOUNTS
security and leaks. Check wiring,
Check for cracks, corrosion and security. grounding straps for condition and
21-40-00.
Check for leaks and corrosion and control
30. PROPELLER GOVERNOR
31. ENGINE CONTROLS
attachment, alignment
Inspect rubber cushions, security.
Check for cracks, distortion, corrosion, leaks and
29. CABIN HEATER SYSTEM
Chapter
hoses
and leaks.
mount bolts and nuts, and
obstructions per
leakage, cracks,
Check controls and associated and
rigging.
equipment
arm
for
security.
for condition,
Remove cable connection bolts and check for wear
each 300 hours. 32. IGNITION HARNESS
Inspect
for
fraying and
attachment.
33. ELECTRICAL WIRING AND EQUIPMENT Inspect electrical equipment and accessories for fraying and attachment. Check for condition,
34. ALL DRAINS AND PLUGS leaks and correct
security
wiring
and associated
and obstructions. Check for
tightness.
35. PRESSURE PUMP INTAKE FILTER
Inspect
filter for
condition, cleanliness and
security. Check filter container for leaks. Replace filter every 300 hours
or more
often
as
necessary. 36. AIR-CONDITIONER COMPRESSOR
refrigerant level and for oil leaks. and worn or frayed condition.
security and attachment. Check Chapters 12 and 21. Check belt for tension
Check for
Refer to
Check for condition, cleanliness and security.
37. INDUCTION AIR FILTER
38. INDUCTION SYSTEM AND ALTERNATE AIR
delamination of the inner
cracks, operation and
dun
28/0Page
12
lining.
Check hot and cold flexible air ducts for
Check the alternate air valve for
blockage, security,
wear.
5-20-00
~23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION B. POWER PLANT
MECH
(Continued)
39. FUEL INJECTION CONTROL VALVE screen
(CONTINUED)
Clean the
screen
and check for
damage.
Install
and check for leaks.
Inspect all fuel injection components, lines and fittings for fuel leaks, fraying and cracking.
40. FUEL INJECTION SYSTEM
evidence of 41
FUEL RETURN LINE
(EA-I
drain line, particularly in the fitting of the fuel return line.
thru
EA-439) Check for chafing against the wastegate seal approximately six inches from the fire wall bulkhead
area
42. ELECTRIC PROPELLER DEICER a.
Check for service
damage
Check for attachment and
to the deicer
heaters, brush rods, springs and brushes.
security.
b.
Check the lead strap and all other clamps, connectors and wiring for electrical soundness, security and attachment.
c.
Check the
deposits d.
slip rings
for
of oil, grease
roughness, cracks, burned or discolored areas and for dirt. Check for security and attachment of all components.
or
Check deicer boots for wrinkles, loose
or
torn
areas.
43. TURBOCHARGER SYSTEM a.
Inspect the system
b.
Inspect the
for oil leaks, exhaust system
compressor wheel for nicks, cracks
leaks, cracks and attachment.
or
broken blades and freedom of
movement. c.
Inspect the bypass valve (wastegate) for proper operation and inspect all linkage for interference, condition, security and attachment.
d.
Inspect all
exhaust system components for
worn or
damaged
areas, loose
clamps,
worn or
damaged
areas, loose
clamps,
cracks and leaks. e.
Inspect
lubrication system components for
cracks and leaks.
injection
reference
f.
Inspect the upper deck pressure reference lines and the fuel manifold for loose connections, leaks and possible chafing.
g.
Check and calibrate the turbine inlet temperature indicator in accordance with Chapter 77-00-00.
h.
Check manifold pressure controller
44. ENGINE BAFFLE SEALS
annual
inspection. Replace
linkage
for
wear.
Inspect for security and condition as
necessary
or
at each 100-hour
or
every 10 years of service.
Inspect pressure system in-line filter for condition, cleanliness and security. Replace pressure system in-line filter in accordance with the Overhaul and Replacement Schedule in Chapter 5-10-00.
45. FILTERS
C.
CABIN AND BAGGAGE COMPARTMENT 1.
ana
SKIN Inspect skins for deformation, cracks and loose found, check adjacent structure.
or
missing
rivets. If
damage
is
5-20-00
INSP
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL IOO-HOUR OR ANNUAL INSPECTION C. CABIN AND BAGGAGE COMPARTMENT 2.
STRUCTURE concealed
3.
(CONTINUED)
I
(Continued)
Check for cracks and def ormation. Check for loose
or
missing
MECH
INSP
rivets and
damage.
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
cables and
proper
operation. Replace
length
of cable
important
pulleys
cables that have
than 3 broken strands in any 9-foot
more
evidence of corrosion. Check cables for proper tension. NOTE It is to operate controls through their full range so that the cables move away from
and all
or
portions
of the cables
are
exposed
for
inspection.
LANDING GEAR GEARBOX AND ACTUATING LINKAGE
4.
Check for
condition and attachment. Check for unusual noise. Remove oil filler
leakage, wear, plug and check oil
by engaging and turning the emergency hand crank 1/2 turn to determine that oil being picked up on the worm gear. The oil level should be maintained no more than necessary to cover 112 of the diameter of the worm gear. Install oil filler plug. level
is
I 5.
6.
security
and check
signs
of
chafing
security and wear at jam nuts for tightness.
Check for condition,
all
security
points. and leaks.
cracks.
or
BRAKE MASTER CYLINDER AND PARKING BRAKE VALVE
security 8.
housing
for
AUXILIARY FUEL PUMP AND FUEL LINES
Check lines for 7.
Check for condition,
FLAP MOTOR AND SHAFTS
Check drive shaft
and leaks. Check lines for
signs
of
chafing
or
Check for condition,
cracks.
Check for freedom of movement. Check cables, push/pull rods, bellcranks, pulleys, turnbuckles and fair leads for proper routing, condition and security. RUDDER PEDALS
Check rudder
positive
positions for wear. Check locks and pins to ensure important to operate controls through their full range so that away from pulleys and all portions of the cables are exposed for
pedal fore
lock. NOTE
the cables move
and aft
It is
inspection. 9.
CONTROL COLUMN, TRIM CONTROL AND INDICATOR (Electric and Manual) Check for freedom of movement. Inspect pulleys, sprockets, bearings, actuators, chains and turnbuckles for condition,
security
operation. Check trim indicator for proper
and
indication. 10. ENGINE CONTROLS locks for proper
Check for
ease
of
operation through full
travel. Check friction
operation.
11. ELECTRICAL WIRING AND EQUIPMENT
Check for condition,
security
and
signs
of
chafing. 12. PLUMBING
Check all plumbing and connections for security, leakage and
general
condition. 13. WINDOWS AND DOORS
Inspect windows for scratches, crazing and general Inspect doors for security of attachment. Check latching mechanism for proper engagement and ease of operation. Check that rotation of the interior door handle without depressing the handle lock release button does not unlatch the door. condition.
Jun
28/0Page
14
5-20-00
nns
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION C. CABIN AND BAGGAGE COMPARTMENT
(CONTINUED) MECH
(Continued)
INSP
14. INSTRUMENTS AND INSTRUMENT PANEL
Inspect instrument panel, sub panels, placards and instruments for condition and attachment. Check all knobs for security. Inspect shock mounts and ground straps for cracks and security.
15.
SEATS, SEAT BELTS AND SHOULDER HARNESSES Inspect cabin seats,
seat belts
and shoulder harnesses for proper operation, condition and security of attachment. Inspect floorboards for condition and seat attachment. Check for operation of the seat
stops. Check condition of the oxygen system and check the oxygen
16. OXYGEN SYSTEM
masks for cleanliness and stowage. 17. VENTILATING SYSTEM and
Check all fresh air and heat outlet vents for proper movement
operation.
18. FUEL SELECTOR VALVE
Inspect for leakage, security, freedom of movement, proper
detent feel and condition. Clean strainer and check for condition. Check for proper
placarding. Check emergency release handle and latch assembly for Check that the hatch moves out freely. Check the complete latch
19. EMERGENCY EXIT HATCH
operation. assembly for condition proper
and all moving parts for proper operation. With the hatch installed, check for proper latching and seal. Safety the emergency exit with 0.020
inch-diameter copper wire after 20. STATIC SYSTEM
opening.
Check and drain water from the static lines. Check for condition, mounting
21. CABIN AIR BLOWER
security
and
wear
at all
points.
Drain and clean. On fuel cells with foam inserts, check for brown foam material. Refer to Safety Communique No. 67 and Service Bulletin No. 2109.
22. FUEL STRAINER
23. CONTROL COLUMN
D.
(E-1946, E-2104, E-2111 and After; EA-320, EA-389 and After) U-joint roll pins and ensure they are not backing out.
I
control column
Inspect the
MECH
WINGS AND CARRY-THROUGH STRUCTURE
LH 1.
SKIN
Check for deformation and obvious damage. Check for cracks, loose
or
INSP
RH
missing
rivets. If damage is found, check adjacent structure. Check for indications of hard landing or excessive flight loading. 2.
STRUCTURE or
missing
Check for cracks, deformation and concealed damage. Check for loose
rivets. for cracks, proper fit and attachment.
3.
ACCESS DOORS AND PANELS
4.
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, cables and pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
Inspect
than 3 broken strands in any 3-foot length of cable or evidence of corrosion. Check cables for proper tension. NOTE It is important to operate controls through their full range so that the Gables move away from
proper
operation. Replace
pulleys and
nns
all
portions
cables that have
of the cables
are
more
exposed
for
inspection.
5-20-00
15
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL IOO-HOUR OR ANNUAL INSPECTION D. WINGS AND CARRY-THROUGH STRUCTURE
(CONTINUED) MECH
(Continued)
LH 5.
AILERONS
Check for condition and security. Check for cracks, loose
and freedom of movement. Check
rods for
security
hinge bearings
RH
missing rivets push/pull
and brackets for condition,
and rod ends for corrosion.
6.
FUEL CELLS, CAPS AND VENTS Inspect fuel cells, caps and Chapter 28. Refer to Service Instruction Number 0632-280.
7.
PLUMBING
8.
ELECTRICAL WIRING AND EQUIPMENT
I
or
INSP
Check for
leakage, chafing,
condition and
Inspect
for
vent lines. Refer to
security.
chafing, damage, security
and
attachment. 9.
FLAP LIMIT SWITCHES
Check for condition, security and freedom of operation. Check for condition, security, binding
10. FLAPS AN D ACTUATORS drive shafts. Check
roller
bearings
flap skin and
structure for
and tracks for condition. Check
11. FLAP POSITION TRANSMITTER
cracks, loose
stop
area
or
or
chafing of actuator
missing
are
Check the drain holes in the upper wing attach fittings to open and free of obstruction.
13. WING SPAR CAP
damage.
Check for security and operation.
12. DRAIN HOLES
they
rivets. Check
for condition and
Inspect the wing spar cap
for corrosion. Refer to
ensure
Chapter
that
57. See
Service Bulletin 2538. 14. WING BOLTS
wing bolts for proper torque at the first 1 GO-hour inspection and inspection after each reinstallation of the wing attach bolts. Refer to maintenance manual for wing bolt, nut and fitting inspection criterion
Check
at the first 1 GO-hour
Chapter 57 of this and frequency.
15. RADAR ANTENNA COVER
Check the fiberglass for security, attachment and cracks.
16. FUEL VENTS AND AIR INLETS, PITOT TUBE AND STALL WARNING VANE
Check
for condition and obstruction. 17. Perform the INSPECTION OF FUEL CELL FLAPPER VALVE
Refer
procedure. retpahC ot
I
28-10-00.
E.
MECH
NOSEGEAR WHEEL AND TIRE
1.
Check wheel for cracks and tire for wear, damage and proper
inflation. Check wheel
bearings
LANDING GEAR STRUT
2.
for condition and
Inspect
leakage.
Check for wear at attach
3.
ACTUATING LINKAGE
4.
GEAR DOORS AND LINKAGE
wear.
the shock strut and components for cracks,
attachment, proper inflation and evidence of
points. Check for cracks and security.
Check doors for damage and cracks to the structure and skins. Check linkage for wear and cracks at the attach points. Check for condition and
security.
NOSE GEAR STEERING LINKAGE
5.
security. Inspect linkage
Jun
INSP
28/02PagelG
Inspect linkage
for
tightness,
condition and
boots for condition.
5-20-00
A23
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION
(Continued)
E. NOSE GEAR 6.
(CONTINUED)
SHIMMY DAMPER
MECH
INSP
Check for condition and attachment. Check attach points for Chapter 12-20-00.
cracks. Check fluid level per 7.
in 8.
Check and maintain the proper fluid level in the strut as outlined
STRUT FLUID LEVEL
Chapter
12-20-00.
STRUT AND A-FRAME HINGE BOLTS
Inspect
for corrosion and
security of
attachment. 9.
STATIC CABLE
(If installed)
Inspect for condition, proper
clearances and attachment.
Check for condition.
10. VISUAL INDICATOR
11. NOSE LANDING GEAR DRAG BRACE
(P/N 002-820016-31, P/N 002-820018-3, or Installed) Check that the two drag brace bracket attachment bolts (Item 22, Figure 4, Chapter 32-20-00) are secure. Check drag brace assembly for shear stress, wear and corrosion. At 2,000 hours, remove and inspect the two bracket
with Kit 35-4012-1
attachment bolts.
Replace
all hardware with evidence of shear stress,
wear
and/or
corrosion. 12. NOSE LANDING GEAR RETRACT ROD ROD-ENDS
for F.
signs
of
cracking,
sheer stress,
wear
Check the retract rod rod-ends
I
and corrosion.
I MECH
MAIN GEAR AND BRAKES
LH 1.
BRAKES, LINES, LINING AND DISCS lines for
chafing
and
signs
of
leakage
or
Check for condition,
wear
and
cracks. Check discs for wear
or
I I INSP
RH
security. Check
warping.
Check
brake discs for cracks. 2.
Check wheels for cracks and tires for wear, damage, condition
WHEELS AND TIRES
and proper inflation. Check wheel 3.
bearings
for condition and
ACTUATOR GEARBOX, MOTOR AND SWITCHES
wear.
Check for
leakage, condition
and
security. 4.
LANDING GEAR STRUTS Inspect the shock struts and components for cracks, attachment, corrosion, proper inflation and evidence of leakage.
5.
ACTUATING LINKAGE condition and
6.
Check for
GEAR DOORS AND LINKAGE
linkage
for
STRUT FLUID LEVEL
8.
outlined in
points.
Check for
Chapter
Check doors for damage and cracks to the structure and cracks at the attach points. Check for condition
wear
security. Determine that all pins. and
as
and cracks at attach
security,
and skins. Check
7.
wear
clevis
retaining pins are
in
place and secured with
cotter
Check and maintain the proper hydraulic fluid level in the struts 12-20-00.
STRUT AND A-FRAME HINGE BOLTS
Inspect
for corrosion and
security of
attachment.
A23
5-20-00
17
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION G.
(CONTINUED)
MAIN GEAR OPERATION
MECH LH
INSP
RH
WARNING circumstances should the landing gear be operated electrically while the hand engaged. In the event of such an operation, a tear down and magnetic inspection should be performed to determine damage to the engagement slot in the worm shaft. Under
no
crank is
CAUTION
battery voltage is not sufficient to properly cycle the landing gear for this inspection, only an external power source capable of delivering and maintaining 28.25 0.25 VDC to the airplane’s electrical system throughout the extension and retraction cycles when performing the landing gear retraction inspection. Refer to Chapter 32 for more specific information on the following items. Since the use
fit and fair. Check for unusual noise.
1.
DOORS
2.
POSITION LIGHTS Check for security, adjustment and wiring for breaks, condition of insulation, loose connections and proper indication.
3.
WARNING HORN
4.
UPLOCK CABLE TENSION
Check
security. Check 5.
operation,
Check for proper operation.
uplock cable
Check
uplock
cable mechanism for condition and
for proper tension and for
EMERGENCY EXTENSION
possible fraying.
Check system for freedom of
operation. Check for engagement of the
unusual noise. With the spar cover installed, check for proper emergency extension handle and proper system operation. 6.
DOWNLOCI( TENSION
Check for proper deflection force
on
the main gear knee
joints. 7.
UPLOCK ROLLERS indicated in
Chapter
Check condition and clearance of 12-20-00. Check for
uplock
rollers and lubricate
as
binding.
8.
LIMIT SWITCH RIGGING Check for security and proper adjustment of the limit switches. Refer to RIGGING THE LANDING GEAR in Chapter 32-30-00 of this maintenance manual for correct landing gear gearbox internal clearance.
9.
SAFETY SWITCH
Check for security, proper
rigging
and
operation.
airplane on jacks and cycle the landing gear while position light switches operate in conjunction with the condition and operation of the complete landing gear the Check position.
10. GENERAL OPERATION
Place the
to ascertain that the
checking landing gear system.
11. DYNAMIC BRAKING ACTION 12.
of
dynamic
brake
relay.
(If Installed) Inspect the retractable step for cable and safety link condition, proper adjustment and operation. Check fixed link condition, proper adjustment and operation. Check fixed steps for security. ASSIST STEP
Page
nuJ81
Verify proper operation
28/02
5-20-00
nzs
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION H.
(CONTINUED) MECH
NOSE GEAR OPERATION
INSP
WARNING Under
circumstances should the landing gear be operated electrically while the hand engaged. In the event of such an operation, a tear down and magnetic inspection be performed to determine damage to the engagement slot in the worm shaft.
no
crank is should
CAUTION
I
I
II
voltage is not sufficient to properly cycle the landing gear for this inspection, 0.25 VDC to external power source capable of delivering and maintaining 28.25 the airplane ’s electrical system throughout the extension and retraction cycles when performing
Since the battery use
only an
Refer to
the landing gear retraction inspection. following items.
for
more
specific information
on
the
fit and fair. Check for unusual noise.
i.
DOORS
2.
NOSE GEAR UP TENSION
Check
Chapter 32
operation,
Check the up tension
on
the nose gear as indicated in
RIGGING THE LANDING GEAR in Chapter 32-30-00. 3.
DOWNLOCK TENSION Check the downlock tension RIGGING THE LANDING GEAR in 32-30-00.
4.
GENERAL OPERATION
on
the nose gear
as
indicated in
Place the airplane on jacks and cycle the landing gear while checking to ascertain that the position light switches operate in conjunction with the landing gear position. Check the condition and operation of the complete landing gear
system.
I.
Inspect for
5.
VISUAL INDICATOR
6.
NOSE GEAR STEERING
proper
adjustment
and operation.
Check for condition and security.
REAR FUSELAGE AND EMPENNAGE i.
Check for deformation, cracks and obvious damage. Check for loose damage is found, check adjacent structure.
SKIN
or
missing
rivets. If 2.
INTERNAL FUSELAGE STRUCTURE loose
or
missing
Check for cracks and deformation. Check for
rivets. Check bulkheads, door
posts, stringers and doublers for
corrosion, cracks and buckles. 3.
STRUCTURE other obvious
4.
Inspect the two damage.
most aft bulkheads for
cracks, distortion, loose rivets
or
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
cables and
have more than 3 broken strands in any 3foot Check cables for proper tension. NOTE It is of corrosion. evidence length their full range so that the cables move away from controls to through important operate for inspection. of the cables are and all exposed portions pulleys
proper
operation. Replace cables that
of cable
~123
or
5-20-00
Jun
28/02PagelS
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION (CONTINUED) I. REAR FUSELAGE AND EMPENNAGE
5.
CONTROL SURFACES or
missing
(Continued)
6.
Check for deformation, cracks and security. Check for loose security of hinges and
hinge casting ton
the aft
bulkhead)
for cracks
mounting bolt holes.
TRIM TABS AND ACTUATORS
Chapter
27-30-00. Check
hinges
Check for security and
Check free play per security and wear. Check
wear.
and trim tab actuators for
trim tabs for cracks and control rods for attachment. Lubricate trim tab
Chapter
hinges per
12-20-00.
7.
STATIC PORTS
8.
PLUMBING
9.
INSP
rivets. Check for freedom of movement. Check for
bond cables. Check the inboard elevator in
MECH
Check for obstruction and clean
Check for
leakage, cracks, chafing,
ELECTRICAL WIRING AND EQUIPMENT
as
necessary.
condition and
security.
Inspect for chafing, damage, security
and
attachment. 10. STATIC LINES 11. ANTENNAS
12.
Check condition of static lines and drain.
Check for condition and
ELEVATOR/RUDDER
security.
(Ruddervators)open and clean.
a.
Check that the drain holes
b.
Check that the ruddervator trim tab and ELEVATOR TRIM IAB
are
hinge pin are correctly INSTALLATION, Chapter 27-21-00.
the trim tab
c.
Check for cracks
d.
Check the stabilizer front and
on
hinge support
rear
mated. Refer to
channel.
spar attach points for cracks and looseness.
(CE-I thru CE-1425; CJ-I thru CJ-179; E-l airp\anes that have not installed Kit No. 33-6001-1 2333 every 500 flight hours or annually.
13. RUDDER FORWARD SPAR EA-1 thru EA-500 and
Service Bulletin No.
thru E-2518; S Refer to
(CE-1426 and After; CJ-180 and After; E-2519 and After; airplanes that have installed Kit No. 33-6001-1 S Open inspection covers adjacent to the upper and center hinges. Inspect ribs, spar, hinges and all rudder components in area of the hinges for attachment security, cracks and general condition using a flashlight and mirror. Install covers.
14. RUDDER FORWARD SPAR
EA-501 and After and
J.
GENERAL
Airplane
2.
Airplane lubricated,
3.
Inspect
4.
5.
Jun
28/0Page
20
all
placards
after
cleaning,
to ensure that
Ensure that all Airworthiness and
I
cleaned and serviced.
1.
previously
in accordance with
they
are
Chapter
easily readable
and
securely attached.
Directives, Beech and Raytheon Aircraft Service Bulletins are reviewed and complied with as required.
issued Service Instructions
complete or annual inspection of the airplane, all noted in this guide should be inspected. For
12-20-00.
a
5-20-00
items
on
the
airplane
that
are
nns
CHAPTER
DIMENSIONS AND AREAS
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 6
LIST OF PAGE EFFECTIVITY CHAPTER SECTION PAGE
SUBJECT 6-EFFECTIVITY/CONTENTS
DATE ........,,,.Oct 7/83
1
6-00-00
1
CHAPTER 6
.........,._
Feb 18/83
2
Oct 10/80
2A
Feb 18/83
3
................Oct 7/83
4
...............Jan 20/82
5
.........,.,..Oct 7/83
6
..............Jan 20/82
7
............,Jan 20/82
8
..............Jan 20/82
DIMENSIONS AND AREAS
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT
SUBJECT ..6-00-00
DIMENSIONS AND AREAS
(CE-748, CE-772 and after; CJ-149 thru CJ-155 Without Kit 33-4002-1) Airplane Dimensions (D-10097, D-10120 and after) Airplane Dimensions (CJ-156 and after, and CJ-149 thru CJ-155 with Kit 33-4002-1) Airplane
PAGE
Dimensions
........1
........2 ......2A
Airplane Dimensions (E-llll, E-1241 and after) Airplane Dimensions (EA-1 thru EA-272 except EA-242) Airplane Dimensions (EA-242, EA-273 and after) Stations Diagram (CE-748, CE-772 and after; CJ-149 and after) Stations Diagram (D-10097, D-10120 and after) Stations Diagram (E-llll, E-1241 and after; EA-1 and after)
i................
.......3 .......4 .......5 .......6
.......7 ............8
"END"
&EFFECTIVrTYICONTENTS
P~g´•l Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
26’8
i3
8’3" i
6’7"
7.5" MINIMUM CLEARANCE 33’6"
I
O
h\
o
’OPTIONAL RADAR
12’2"
7’ DIA
9’7"
1
113´•607.1(
Altplene Dimalmions (CE-748, CE´•772 and after; CJ-149 thru CJ-155 Without Kit 33-4002-1) Figure 1 6´•00-00
Pegei A5
Febi8/83
BEECHCRAFT BONANZA SERIES MAINtENANCE MANUAL
26’5"
T 6’7" c:r
i
I
7’7"
6´•8" MINIMUM CLEARANCE
33’6"
o
I
h\
o
´•OPTIONAL RADAR
10’6"
7’ DIA
9’7"----------1
Airplane
6-0090
Page2 Oct 10/80
Dimensions
(D-10097, P´•10120 Figure 2
v,r.~or.is
and
after)
BEECHCRAFF
BONANtA SERIES MAINTENANCE MANUAL
26’8
i3 8’3"
j
6’!"
7.5" MINIMVM CLEARANCE 33’6"
WING AREA: 181.0 SO.FT.
I
O
h\
lL111
o
12’2"
7’ ~DIA
9’7"
Airplane
Dimensions (CJ-150 and after, and CJ-149 thru CJ-155 With Kit 339002-1)
133-607.29
Figure 2A 6-00-00
Page 2 A A5
Feb18183
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
8’5"
6.6"
CI~
CLEARANCE, 9.5" E-1946, E-2104, E-2111 AND
7.5" MINIMUM
4FTER
~k
33’6"-
t
IQ
t
~Ck
*OPTIONAL RADAR
tAT SERIALS E´•1946, 6-2104, 6-2111 AND ~k AFTER, VORTEX GENERATORS WERE ADDED TO tHE WING LEADING EDGE. AT THE SAME SERIALS A CONTROLLABLE TAB REPLACED THE FIXED fAB ON THE LEFT AILERON.
12’2"
L~-
80" DIA 3 BLADE PROPELLER USED 6-1946,
6-2104, 6-2111 AND AFTER.
7’ DIA
t
t
j-9’7" A38-M)7- 33
Airptane
(8-1111, Figure 3
Dimensions
6-1241 and
atter)
6-00-00
Page3 A6
Oc17/83
YLL~)
ICI~ 1~,
BONANtA SERIES MAINTENANCE MANUAL
29.5
8 FT. 5 IN.
sFT:elN.
--W,L. I0oon
f-
9.5 IN. (MIN. CLEARANCE WITH TIRE AND SHOCK STRUT DEFLATED)
3"56 MIN.
2.5"
33 FT. 6 IN.
VERTICAL STABILIZER
’OPTIONAL RADAR
12 FT. 2 IN.
80 IN. DIA.
9 FT. 7 IN. A36TC-607-20
Airplane Dlmanalona (EA-l’thru Figure 4
EA-212
Except EA-242)
6-00-00
Page
4
Jan 20/82
A4
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
2.5’
L~pt
t t THE FIXED TAB IS REPLACED BY A CONTAOLLABLE TAB ON LEFT AILERON AT SERIALS EA-320, EA-389 AND AFTER
1
VERTICAL STABILIZER
12 FT. 2 IN.
078
~----9 FT. 7 IN.
29.5
Z> 6 FT. 6 IN.
~D ~D
(MIN. CLEARANCE WITH TIRE AND SHOCK STRUT DEFLATED)
10.5 IN.
8 FT. 5 IN.
-;-__1
--W.L. 100.00
r 3"56 MIN.
Airplane Dlmanaiona (EA-242, Figun, 5
EA-273 and
836TC-607-23
a’fter)
6-00-00
Page5 A6
Oct 7/83
BEECHCRA~ BONANZA SERIES MAINTENANCE MANUAL
14.96
’M
41.~72
..75
116.50
1I~qi
104.90
27200
292.00
257.649.00 19.812
174.50
151.00
33.345
ii om w.L111 I
82.53;1.W.L. 88.1
248.30
149~W
18.25 39.50 4.50 12125 29.25
68.00 58.50
83.090100.00
233.50
207.00
i
17.8;1 112138 131.00
256.90
170.00 179.00
291.00
FUSELAGE
152.250
HORIZONTAL STABILIZER
VERTICAL STABILIZER
272.000 257.806
3.500 1.245
15.250 38.403 25.500 35.750 ~CC----I
Y~-- 36.15 36.900
j
46.000
58.250 56.550 72.500
148.815
175.837
191.00
182563
123.1 82 39.375 86.000 113.172 59.000 135´•30 09.305 83.547 23.881 95.483 73.000
136.188
i~i
n WING
Ir 175.294
0.00
80.647 108.281 44.164 122.750
53.d00 I 45.000
131~
J3sow
36.030
Stations
Diagram (CE-748, CE-TIP Figura
and
after; CJ-149 and after)
8
6-00-00
Paga6 Jan 20/82
A4
BEECHCRAFT
BONIVJZASERIES MANmNANCE MANUAL,
82.960 94.75
116.25r
MIo4.so I ID1F~3.812 ~I IX(1B
41.172
14.96
27200
118´•50
I
33.545
257.609 151.M)
292.00
277.00
174.50
11_1
w.L. w.l
as.J-~--Clz(z
I
I
248.30 233.50
Mj.OO 18.25
\491W
39.50 12125 29,25
4.50
i
68.00 58.50
85.090100.00
LI
lir.87 131.00 112.138
256.90
297.00
FUSELAGE
170.00 1’19.00 152.250
CLOFAIRPLANE
:I
0.000
12500 56.250 35.750‘15.250 46.000
MLFRONT SPAR
STABIUZER
M REAR
38.15 3.900
39.315 66.000 135´•30 59.000
1 23.182
113.172
148.175136.1
175.837 191.00
162.563
rjg305 83.54173.0001. n~ rl
23.881
95.463
88
0.00
WING
175.294
80.b47 108.281 94.864 122=750
Stations Diagram
(0-10097, F~gure 7
53.d00 45.000 38.030
.i~´•7
I)-10120 and after)
6-00´•00
Page 7 Jan 20/82 A~
BEECHCRAFT BONAE~A SERIES MAINTENANCE MANUAL
58.00
1M).00
148.15
Ile.M
124.75 23.345 -10.00
174.00
48.50
I3~.!72
8.25
Iq.aol 155.00
20!.00
233.50
1257.606272.00
100.00
0.~00
’9´•25
170.00 39.00 29.50
83:00
58.00
112:138
131.00
12;.55
14j.00
FUSELAGE 495 .245
38.
39.375 83.547 66.00 122.75 103.641 146.875 73.M)S9 ~.091 113.1n (36.188 1gW83
175.281 181W
53:00 47.m
31.75
yu.se~
13.218~/
83.00
1
11~--23.06
VERTICAL STABIUZER
272.00
257.608
r
162563 7
136.168 i
108.261
MODELS F33A. F33C. V35B. A38. A36TC
3.M
I
BO.C17
25.50
45.00 23.at
35.75
WING
36.15 36.90
3’1.75
218.18
198.000
usloml iogsml~
122.7$ 148.875 175.281 136.188 162.563
103.641
83.541 66,00 73.M)
113.172IglpB(
580039.875123;881
56.25
47.00 66.55 .525
83.00
HORUOHTAL STABIUZER
162363 136.188 108.281
80.047
qjDD
MODEL B36TC
23.81
366038
Stations Diagram (E-llll. E-1241 and after; EA-1 and after) FIE(un, g 6QO-00
PegeB
"END"
3en ~0/82 A4
C H A PT E R
LIFTING AND
SHORING
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER I
LITTINC AND SHORING
TABLE OF CONTENTS SUBJECT
CHAPTER
CHAPTER
PACE
SECTION
7-00-00
Lifting and Shoring
Jacking Main
Maintenance Practices
SUBJECT ....7-00-00
1 I 2
Wheel ja;k:Ing
Hoisting "END"
7-CONTENTS Page 1 A13
Mar 30/90
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 7 LIST OF PAGE EFFECTIVITY
CHAPTER SECTION SUBJECT
PAGE
DATE
7-EFFECTIVITY
1
Mar 30/90
7-CONTENTS
1
Mar 30/90
7-00-00
1 2
Mar 30/90 Mar 30/90
"END"
7-EFFECT1V1TY A13
Page 1 Mar 30/90
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
LIFTING AND SHORING PRACTICES
MAINTENANCE
JACKING
WARN ING
The
landing
gear
struts
do
incorporate internal stops. the
aiplane
attempt
to
is
jacks,
on
remove
the
knees, the torque knee pins bolt connecting the torque
not
When do
not
torque or
the
knees the shock
without first aeflating absorber assembly and supporting the gear. The torque knees provide the extension stop for the lower shock absorber When assembly. they are disconnected, the cylinder is free to slide out of the upper
assembly. CAUTION
Jacking only
the
be
landing gear should accomplished within an or building hangar.
enclosed Should it become necessary to jack the airplane in the open, no more than one jack point should be utilized at a time. For safety of personnel and the airplane, wind
velocity in considered
any direction must be
prior
to
jacking
airplane.
the
35-590006 Main Wheel Jack Figure 2
Adapter
A three point jack (Figure 1) is used to ii ft the airplane off the ground. Each jack pad is identified and located on the underside of the fuselage. One jack pad is located on each of the lower wing-tofuselage attachment fittings along the front spar. The rear jack fitting consists of an eye bolt that is screwed completely into the airplane. WARNING
Be
sure
the
rear
jack point safety
place and safetied to prethe vent airplane from nosing over. As an additional precaution against nosing over, attach, but not suspend, a weight of approximately 200 pounds to the aft tiedown lug. is
in
When one wing is to be removed, a stand should be placed under the opposite wing and the tail to counteract the resulting unbalanced condition of the airplane. MAIN WHEEL JACKING
jack adapter (Figure 2) is optional equipment. Before raising the airplane, be sure the shock strut is properly inflated to the correct If the strut is not inflated to height. the recommended height, it will be impos-
The main wheel
supplied
Model 300 Service Jack
figure 1
as
sible to insert thejack adapter into the wheel axle. A scissor type jack is recommended for Individual wheel jacking.
main
7-00-00 A13
Page 1 Mar 30/90
BEECHCRAFT BONANZA SERIES MA1NTENANCE MANUAL
HOISTING
airplane
The
Install
a.
be
may
the
ting, P/N 35-590067, wing attach bolt. b. the c.
the
u
a
far
hoisting on
sling fiteach upper forward
Attach the hoisting 35-590064-1 shown
~n
hoisting sling fittings. Install the strap assembly aroung blade shanks.
propeller d.
Hoist the
airplane
ETON.ylhto ms
Adjust the strap assembly ai rp lane
the
slightly e.
may
mainte-
follows:
as
P/N
bly, to
hoisted
parts replacement
or
nance
be
nose
to
keep
level down attitude. in
or
a
As added precaution, an installed under the tail
a
stand the
of
airplane. 35-590064-1
Hoisting Sling Assembly Figure 3
If
the
airplane
must
be
hoisted
and
the
P/N 35-590064-1 When lowering the airplane, caution should be exercised to prevent the shock strut from becoming compressed and forcing the
landing
gear door
against the jack adapt-
er.
hoisting sling assembly available, remove the cabin door,
is not the left front window and the front seats. Attach a sling to the front wing spar in the fuselage and a line to the hoist fitting on the engine.
CAUTION
CAUTION
Do not walk on the wing walk with the airplane on the main wheel
A spreader must be used above the cabin to prevent damaging the door molding and window frame.
jack. "END"
1-00-00 Page 2 Mar 30/90
A13
CHAPTER
LEVELING AND VV EIGHING
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 8
LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
DATE
PAGE
8-EFFECTIVITY/CONTENTS
1
.........,,,May 9/80
8-00-00
1
...............May 9/80
CHAPTER 8
LEVELING AND WEIGHING
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
GENERAL
8-00-00
Maintenance Practices
PAGE
........1
Leveling
.......1
"END"
&EFFECTIVltYICONTENTS
Plg´•l Mly 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
GENERAL
MAINTENANCE PRACTICES
the center of
a
second
Suspending the plumb assist in stabilizing it.
LEVELING
a can
screw
below.
of
oil will
directly light engine
leveling is accomplished by removing the front seat(s) placing a bubble level on the spar carry thru structure. Deflate the tire or strut on the high side of the airplane to
To level the
Lateral
bob to the
and
airplane longitudinally, attach a cord and plumb phillips head screw, located beneath the rear window on the left side of the airplane. Inflate or deflate the nose gear shock strut as necessary to pass the cord through
phillips head bob in
center the bubble.
"END"
8-00QO
Page May
1
9/80
CHAPTER
TOVVING AND
TAXIING
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 9-TOWING AND TAXIING TABLF OF CONT~NTS CHAPTER
SUBJECT
PACE
9-00-00
Towing and Taxiing
1
Maintenance Practices
1
Towing One Person
Towing With Taxiing
i
Towing a
1
TractororTug
i
"END"
0-CONTENTS
Page 1 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 9 LIS T OF FACE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
9-EFFECTIVITY
1
Oct 16/92
9-CONTENTS
1
Oct 16/92
9-00-00
1
Oct 16/92
"END"
0-EFFECTIVITY
Page Ale
1
Oct 16192
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
TOWING AND PRACTICES
CAUTION
MAINTENANCE
TAXIING
After
moving
the tow bar.
TO WING
the
airplane, always remove propeller with
Never turn the
the tow bar attached to the the
WARNING
nose
gear
as
hit the tow bar.
engine is warm, and it is necessary the propeller to attach the tow bar,
If the to
propeller will
move
stand
clear of the
move
the
Make
of rotation.
direction
of rotation
area
propeller against
the
and
normal
certain
the
magneto switch is off. While the engine is warm, residual fuel in the intake ports and injectors may ignite and cause the engine to kick.
CAUTION When
airplane is being towed,
an
a
quali-
fied person must be in the pilot’s seat to operate the brakes in case of an emerWhen the
gency.
is
airplane
being
moved
backward, do not apply the brakes abrupt-
ly.
Hand Tow Bar
airplane slowly, avoiding sudor taxi the airplane strut. Even brief towing or taxi-
Tow the
den
stops.
with
a
flat
ing with damage
a
Figure
Never tow
deflated strut
can cause severe
used
as
a
handhold
tow bar
while
entering
closing
or
the door.
Always
to the care
Never leave the cabin
door open on the ramp damage the door.
as
wind
tractor
the tow
tug, attach the pins on the nose
or
Always observe the turn gear lower torque knee. Turns limits of the nose gear when making turns. geater than these limits can cause extensive damage
not be
open the storm window to relieve internal pressure when the cabin.
airplane with a ~P/N 45-590075) to
To tow the
top of the cabin door should
leaving
I
TOWING WITH A TRACTOR OR TUG
to the strut.
NOTE The
1
lower
gusts may
gear and shimmy damper. Also, exercise removing the tow bar from the nose gear torque knee to prevent damage to the lubrifittings on the torque knee.
nose
when
cation
NOTE ONE PERSON TOWING
attempt to tow the airplane backby the fitting in the tail skid. The tail skid was designed only to protect the tail in the tail-low landing and to provide Do not
ward
CAUTION The Hand Tow Bar used with
a
~Figure 1)
must not be
attachment for the tail tie-down.
tow vehicle.
TAXIING One
person smooth and
can
move
the
airplane easily
on
a
level surface with the tow bar (P/N 36-590015) furnished with the airplane. Attach the tow bar to the tow pins on the nose gear lower torque knee and push or pull gently to move the airplane.
airplane must be taxied with the wing flaps up, engine cowl flaps open. Turning may be accomplished by the use of the nose wheel steering
The
and the
mechanism.
"END"
9-00-00
Page A16
1
Oct 16/92
CHAPTER
PA RKING,
MOORING, STO RAG E, RTN TO SVC.
BEECHCRAFT
BONANZA SiRjES MAINTENANCE MANUAL
CHAPTER 10
LIST OF PAGE EFFECTIVITY CHAPTER SECTION DATE
PAGE
SUBJECT
10-EFFECTIVITY/CONTENTS
1
10-00-00
1
May 9/80 May ...............May ...............May ....May
2 3 4
CHAPTER 10
9/80
9/80 9/80 9/80
PARKING AND MOORING
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
GENERAL
10-00-00
.......1
Maintenance Practices
Parking. Mooring
........1 ........1
Normal Tie-Down
Extended
PAGE
Storage
and
High
........1
Wind
........1
Control Lock
Storage Flyable Storage 7 Temporary Storage Indefinite Storage
to 30
.........2
Days
30 to 90
.........2
Days
.........3
.........4
Preparation for Service
L’END"
1 O-EFFECtlVITYICONTENTS
p´•a´•1 Mly 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
surfaces must then be secured to prevent banging against the stops. The controls should be secured in position with
MAINTENANCE PRACTICES
GENERAL
control locks that
PARKING
mooring, parking by pulling out the parking brake control, then pressing the pilot’s brake pedals until firm. Do not attempt to lock the parking brake by applying force to the parking brake handle; it controls a valve only and cannot apply pressure to the brake master cylinders.
The brakes
for
are set
installed in the control column. When
properly.
Pitot-static tubes should be covered. EXTENDED STORAGE AND HIGH WIND
mooring the Bonanza, the following method is recommended: Place chocks fore and ah of each main wheel. Position a tail stand under the tail skid, adjusting the When
slightly compress the nose gear shock through each wing mooring lug, fastening each end to a ground point, one forward and one ah of the wing. Run a line through the hole in the tail skid and anchor at the sides of the airplane approximately 5 feet from the base of the stand. If a storm is anticipated, two lines may be secured to each main landing gear strut barrel near the
height of
CAUTION
are
be sure to fasten all doors and windows
the stand to
strut. Run a line
Do not set the brakes
are
parking
hot from
temperature when
brake control when the
severe use or
an
during
low
accumulation of moisture
may cause the brakes to freeze. An increase in outside air temperature can build up excessive pressure in the system. In addition, the parking brake should be left OFF and wheel chocks installed if the
airplane is
to be left unattended.
V-brace and also
a
line may be attached around the nose
gear strut near the lower torque knee. It is recommended that the airplane be tied down headed into the wind, with the control lock installed.
MOORING
CONTROL LOCK
designed to provide guidelines which can be mooring and securing Bonanza series airplanes. Mooring procedures for normal tie-down operations as well as mooring for extended storage and high
A control column lock pin is provided for the control column and the aileron control wheel. The lock pin secures both the aileron control wheel and the elevator control. A cover is
This section is
followed when
wind conditions follow:
on the control lock to cover the throttle control, boost pump, and the propeller control. Install the control lock assembly in the following sequence:
provided
NORMAL TIE-DOWN Rotate the control wheel to the right and move the so the hole in the bracket and the column
a.
On Bonanza series airplanes, a tie-down lug is installed.on each wing, and on the ah fuselage. The tie-downs should be nylon or dacron ropes or chains with sufficient strength to
column forward
gusty winds. Manila or high airplane hemp ropes should never be used. The tie-downs should allow very little or no movement when tightened, too much
provided
restrain the
in
or
slack will allow the airplane to jerk against the tie-downs. When securing the tail section of the airplane, the tie-down should have a slight slack so that the nose of the airplane will
align
to
accept the pin.
b.
pin through
and into the control
causes more pressure to be placed on the wing tie-down ropes and anchors. Adequate antislip knots such as bowlines or square knots should be used when securing the
guide
column. Ensure positive retention of the lock pin by placing assembly over the throttle control, boost pump, and propeller control. c.
the the
cover
not be raised off the ground. In a strong headwind, a tail tie-down that is too tight will increase the angle between the wing and the oncoming air. This creates an additional lifting
force, which
the hole
Push the control column lock in the control column
WARNING
Always completely remove the control lock assembly before engine start, taxiing, and flight.
lines.
STORAGE
Securing operations should be planned so the airplane is tied down facing the prevailing wind, if the ground attachment permits.
Once the
airplane
has been
positioned
into the wind,
the wheels should be checked fore and ah. The
flight
control
The storage procedures listed are intended to protect the airplane from deterioration while it is not in use. The primaly objectives of these measures are to prevent corrosion and
10-OMW)
Pagel May 9/80
BEECHCRAFT BONA~UA SERIES MAINTENANCE MANUAL
damage from exposure storage
are
to the elements. Three
f.
types of and
considered:
a.
FLYABLE STORAGE
b.
TEMPORARY STORAGE
c.
INDEFINITE STORAGE.
7 to 30
days.
up to 90
PITOT TUBE
h.
WINDSHIELD AND WINDOWS
days,
PREPARATION FOR SERVICE
line to the nose gear. ENGINE PREPARATiON FOR STORAGE a
Engines in airplanes that are flown only occasionally tend to exhibit cylinder wall corrosion much more than engines that flown
Iftheengine hasatotaltimeofmorethan25 consumption has stabilized, drain break-in oil after a ground warm-up and install oil Teledyne Continental Motors Specification MHS-24C. 2. Preflight the airplane. 1.
the per
30 to 90 DAYS
TEMPORARY STORAGE
frequently. 1.
Check for correct oil level and add oil if
2.
Run
engine
1500 rpm with oil and normal operating range.
at least five minutes at 1200 to
cylinder head temperatures
DURING FLYABLE STORAGE
Each
in the
seven
days
during fiyable storage, the propeller shall be rotated by hand. After rotating the engine six revolutions, stop the propeller 45" to 90" from the position it was in.
WARNING Before rotation of propeller blades, ascertain magnetoswitch is OFF, throttle in CLOSED position and mixture control is in the IDLE CUTOFF position. Always stand in the clear while turning propeller.
1.
airplane flown
Arrangements
should be made to have the
at least 30 minutes each week in order to
keep
the internal parts of the engine lubricated. Ground running of the engine will not provide proper heating of the oil without
possible damage
to other
cylinder/crankshaft
MOORING
b.
ENGINE PREPARATION FOR STORAGE
flyable storage. in
flight)
until oil
temperature
reaches normal range. Drain oil supplyfrom sump while engine is still warm and replace djain plug. 1. Fill the sump to the full mark on the dipstick lubricating oil meeting the requirements of MIL-C6529, Type 11 (3, Chart 1, 91-00-00), which will mix with normal oil and provide protection against conosion. 2. Removethetopsparkplug andatomizespray preservative oil MlL-L-46002, Grade 1 (4, Chart 1,9190-00) at room temperature, through the upper spark plug hole of each cylinder with piston in the down position. Rotate crankshaft as each pair of cylinders is sprayed. Stop crankshaft with no piston at top position, and thoroughly respray each cylinder. Reinstall spark plugs. 3. Apply preservative to engine interior by spraying the above specified oil (approximately two ounces) through the oil filler tube. Seal all engine openings exposed to the atmosphere using suitable plugs, or moisture resistant tape, and attach red streamen at each point. Affix a tag to the propeller in a conspicious place with the following
gage with
notation; DO NOT TURN PROPELLER, ENGINE PRESERVED. Seal the propeller blade spinner cutouts with
tape.
engine compartment components
due to lack of air flow, and will result in condensation of
moisture in the oil
See
a.
Operate engine (Preferably
necessary to bring level to full mark.
c.
Remove all
covers
hours and the oil
are
Close all
and tape, clean the airplane and give it a thorough inspection, particularly wheel wells, flaps, and control
7 to 30 DAYS
manila rope. It is recommended a tail support be used to compress the nose strut and reduce the angle of attack of the b.
cover.
be installed over windshield and windows.
openings.
Attach
Install
windows and window vents. It is recommended that covers
MOORING If the airplane cannot be placed in a a. hanger, install the control lock and tie the airplane down securely at the three points provided. Do not use hemp or
wings.
Static ground airplane securely
g.
i.
FLYABLE STORAGE
GROUNDING
effectively.
supply, increasing
the
possibility
of
rust.
c.
Fill to
FUEL CELLS
capacity
to minimize fuel
vapor and protect cell inner liners. FLIGHT CONTROL SURFACES d.
Lock with
internal and external locks. d.
FUEL CELLS
Fill to
capacity
to minimize fuel
vapor and protect cell inner linen, FLIGHT CONTROL SURFACES e. internal and extemal locks.
1040´•00
Page2 May 9/80
e.
and
Lock with
GROUNDING
Static
ground airplane securely
effectively. f.
PITOT TUBE
g.
WINDSHIELD AND WINDOWS
Install
cover.
Close all
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
windows and window vents. It is recommended
installed
over
h.
BATTERY
standard
cover
be
Remove and store
according
to
covers, tape, and
thorough inspection, particularly wheel wells, flaps, and control openings. With bottom spark plugs removed, hand turn propeller several revolutions to clear excess preservative oil, then reinstall plugs. Preflight the airplane and
flight
a
ENGINE PRESERVED.
NOT TURN PROPELLER
practices. Remove all PREPARATION FOR SERVICE and Clean the airplane give it a tags.
i.
propeller has not been removed, affix a conspicuous place with the following notation: DO if the
10.
tag in
windshield and windows.
The cylinder DURING INDEFINITE STORAGE c. protex plugs shall be inspected weekly. The plugs should be
changed
as soon as
their color indicates unsafe conditions of
storage. If the dehydrator plugs have changed color in half
engine
cylinders, replaced.
of the
or more
should be
all desiccant material
one-
on
the
test.
The cylinder bores should be resprayed with preventive mixture every six months or more frequently it bore inspection indicates corrosion has started. Replace all desiccant and protex plugs. Before spraying, the engine shall be inspected for corrosion as follows: Inspect the interior of at least one cylinder on the engine through a spark plug hole. If cylinder shows start of rust, spray cylinder corrosion preventive oil MIL-C6529, Type 11 (3, Chart 1, 91-00-00) and turn prop over five or six times, then respray. Remove the rocker box cover from the engine and inspect 1.
INDEFINITE STORAGE
corrosion
See FLYABLE STORAGE.
a.
MOORING
b.
ENGINE PREPARATION FOR INDEFINITE
Drain the engine oil and service with
STORAGE
lubricating
oil, MlL-C-6529, Type 11 (3, Chart 1, 91-00-00). 1. Immediately after servicing with the corrosion preventive mixture, fly the airplane for a period of time not to
exceed
a
the valve mechanism.
maximum of 30 minutes,
propeller be removed and the engine removed from the airplane. The propeller shaft should be coated with preservative oil and wrapped with moisture proof material and tape, 2.
It is recommended the
Coat blades with preservative oil
PROPELLER
d.
and wrap with moisture proof material and tape. If propeller has been removed, coat all paris with protective material to
exclude dust, and then tape. FUEL CELLS Drain fuel cells. e.
NOTE
engine is removed from the airplane, mooring stand must be used. If
a
tail
engine
oil
Remove the top spark plug from each’ and spray thoroughly with corrosion preventive
cylinder
mixture MlL-C-6529, Type 11 (3, Chart 1, 91-00-00), at a temperature range of 221" to 250"F. 4. install protex plugs in each of the top spark plug holes, making sure that each plug is blue in color when installed. Protect and support the spark plug leads with AN4060-1 protectors. 5. Place a bag of desiccant in the exhaust pipes and seel openings with moisture resistant tape. 6.
contained
gasoline.
according
to standard
by inserting a protex plug in the breather hose and damping in place. 8. Wrap engine with moisture proof material and tape after desiccant bags have been installed. 9. Attach a red streamer to each place on the engine where bags of desiccant are placed. Either attach red tape or to the with safety wire to prevent wicking of
streamers outside of the sealed area with
inside of sealed
area
moisture into sealed
area,
or
After 24 hours,
practices.
a
remove
Do not
fuel cells until 24 hours after oil has been f.
of
coating
light
cells and store remove or
handle
applied.
FLIGHT CONTROL SURFACES
Lubricate all
hinge pins, bearings, bell cranks, chains, control rods and quadrants and coat lightly with corrosion preventive compound MlL-C-16173 (5, Chart 1, 91-00-00). flight
control surface
1.
Seal cold air inlet to the heater muff with
moisture resistant tape, 7. Seal engine breather
thin
Flush, spray,
the inner liners of all fuel cells which have
2. 3.
rub
1. on
g. and
Lock with internal and external control locks.
GROUNDING
Static
ground airplane securely
effectively.
PITOT TUBE h. Apply a thin coating of grease, MlL-G-10924 (6, Chart 1, 91-000-00), and install cover. Close all WINDSHIELD AND WINDOWS i. windows and window vents and install covers over
windshield and windows. LANDING GEAR i’. the shock struts with k.
TIRES
periodically.
Inflate
Coat the extended portion of
light weight
Install as
oil.
covers.
Check air pressure
necessary.
10´•0090
Page3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
WING FLAP TRACKS AND ROLLERS
I.
corrosion
preventive compound.
Place
flaps
Coat with
PREPARATION FOR SERVICE
in retracted
position.
a.
standard
according
to
b.
INSTRUMENT PANEL
material and
secure
SEATS
p.
LANDING LIGHTS
c.
protective
according
with tape,
to standard
practices. Tape connections.
store in a
dry temperate AIRFRAME
s.
Remove and
room,
Cover static ports and all openings secure with tape to exclude rain,
foreign
matter.
propeller if it was removed. Rotate preservative oil from the cylinders. Install the spark plugs, battery, and rotate propeller a. by hand through all compressions of the engine to check for liquid lock. Reinstall cowling and start engine in the normal
Page 4 May 9/80
clear excess
manner.
f.
inspection
"END"
1090´•00
Reinstall the
propeller to
with barrier material and sun, and
lubricating oil, Per Teledyne Continental
Motors MHS-24C. d.
Remove and store
LOOSE TOOLS AND EQUIPMENT
r.
cylinder plugs and all paper, tape, and used to presen/e engine. Drain corrosion preventive mixture and reservice
with recommended
covers.
Cover with barrier material
STALL WARNING UNIT
q.
Remove all
dehydrating agent
with tape,
Install
o.
secure
Cover with barrier
Remove all covers, tape, and tags from the
airplane.
practices.
n.
and
Remove and store
BATTERY
m.
Give the airplane a thorough and test fly the airplane.
cleaning,
visual
C H A PT E R
PLACARDS AND MAR KI NGS
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER ~1-PLACARDS TABLE OF CONTENTS CHAPTER
SUBJECT
PAGE
11-00-00
Required FAA
Placards
Description and Operation
1
Required Placards and Markings Designation Placard
1
Model
1 11-20-00
Exterior Placards and
Markings
Description and Operation
1
"END"
11-CONTENTS
Page A16
1
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 11 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
11-EFFECTIVITY
1
Oct 16/92
11-CONTENTS
1
Oct 16/92
11-00-00
1
Oct 16/92
11-20-00
1
May
2
Oct 16/92
3
Oct 16/92
4
Oct 16/92
9/80
5
Oct 16/92
6
Oct 16/92
"END"
11-EFFECTIVIM
Page A16
1
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND
REQUIRED PLACARDS OPERATION
MOD~L D~SIGNA TION PLACARD
designation placard identifies the airplan by its model number and serial number. Should a question arise concerning the care of this airplane, i is important to include the airplane serial number in any correspondence to Beech Aircraft Corporation. Refer to Chapter 11-20-00 for illustration of the plac ard. On airplanes 0-10097, D-10120 and after; EA-1 The model
FAA REQUIRED MARKINGS
PLACARDS
AND
markings are listed Operating Handbook and FAA Approved Airplane Flight Manual. Refer to Section II of the applicable Pilot’s Operating Handbook for these placards and markings. For the acrobatic Bonanza (CJ-149 and after), also refer to the LOG OF SUPPLEMENTS in the Pilot’s Operating
All
required
interior
placards
and
in the Limitations of the Pilot’s
Handbook.
CAUTION Any time an airplane is repainted, inspect all placards to assure that they are not covered with paint, are easily readable, and are securely attached,
thru EA-272 except EA-242; CJ-149 and after; CE-748, CE-772 thru CE-1200; E-llll, E-1241 thiu E-2399; and
EA-242, EA-273 thru EA-472, the model designation
placard is located on the right side of adjacent to the inboard end of the flap. On
airplanes
the
fuselage
CE-1201 and after, E-2400 and after, and
EA-473 and after, the model designation placard is located on the right side of the fuselage under the
leading edge
of the horizontal stabilizer.
is mounted .50-inch below the skin
forward of the tail
lap
The
placard
and 12-inches
cone.
"END"
11-00-00
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
EXTERIOR PLACARDS AND DESCRIPTION AND OPERATION
Shown in this which
are
Chapter
are
essential for
r
markings, practices,
are
information for that model.
i
DOORIACK
IINSTALL
WITH
and
maintenance
r~ RTANT
by location/description of each. The placards which shown for location only and may or may not bear identical information to the placards installed on the various individual models. Note the specific information on the placards installed on each model to determine current
followed
follow
placards
exterior
good
ILINK
MARKINGS
BOLT;
ROD
HEAD
ATTACH POIN
-----------~1-I
AFTI
L_______11 LOCATED IN THE CENTER OF THE UNDERSIDE OF THE FUSELAGE AT APPROXIMATELY FS 131.00 LOCATED ON THE OUTBOARD SIDE OF THE ROOT RIB IN THE WHEEL WELL, VISIBLE ABOVE THE INBOARD DOOR
-CAVTIONTVRN LIMITS REACHED
WHEN RED LINES ALIGN
Do NOTEXCEED
I
TOW
r--
I
IJACK PADI L---_____J
LOCATED DIRECTLY ABOVE THE NOSE LANDING GEAR TORQUE KNEE
’c-~
I
iL__T_I
LOCATED ON THE LH SIDE OF THE FUSELAGE AT APPROXIMATELY FS 151.00 (2 PLACES)
LOCATED AT WING ROOT ON CENTER SECTION SPAR, FORWARD OF THE INBOARD WHEEL WELL DOOR
IMPORTANT INSTALL UPLOCK CABLE A~TACH BOLT WITH HEAD AFT
LOCATED AT APPROXIMATELY WS 60.00 IN EACH WHEEL WELL, DIRECTLY ABOVE THE UPLOCK ASSEMBLY
1I-2MK)
Page 1 May 9/80
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
I
(ilrechcralt
(I)cechfraft
OIL AIR STRUT
OIL AIR STRUT
FART NO. 36´•825(85 sEECH L~IRCR*FI UWIWRITK~N
.tKH *IIClln EOllollllON
I
I
I I
I I
(31cchcrzli OIL AIR STRUT ru~ a
s*IINO
I
*c*n* ulaui. u~u
I
Ib´•~10010
*rrl~
INSTRUCTIONS
r´•*w~
I.C* YCUII m*TUra
ul~
IrrsrRucnow
INSTRUCTIONS
TO CHECK FLUID AND Flu REMOVE VALVE C*P. DEPRESS VALVE CORE AND ALLOW STRUT TO FULLY COMPRESS. THEN RAISE AND BLOCK
STRUT n INCH FROM COMPRESSED POSITIDN- REMOVE VALVE BODY ASSEMBLY AND F11l WITH HYDRAULIC OIL CONFORMING TO INSTRUCTION MANUAL SPECIFICATIONS. SLOWLY EXTEND STRUT FROM BLOCKED POSITION AND REPLACE VALVE BODY ASSEMBLY. DEPRESS VALVE CORE AND COMPLETELY COMPRESS STRLIT TO RELEASE EXCESS AIR AND OIL. WITH AIRPLANE EMPTY EXCEPT FOR FUu FUEL AND OIL KEEP STRUT INFLATED TO3W INCHES OF PISTON SHOWING.
I
I
I
I
I
I
rO CHIEI ilUIO 1NO nit 1111811 VILYI C*). DHnI V*LVI COll LINO ALLOW IIIUT r0 IULL* CD*n~ll. ~nm I*lw ~No UOC* (IIUI INCH 11811 COMI(IIIYD ~OllnOH llMOVI V*LVI 11)81 UBMIL* ANO lII1 WIIH H*DI*ULIC 011 CONIOIUING 10 INIIIUCIION n*Null IICIrIC*lIlNr ~II oIIrl*ct lrsrAl UNrlL IDDlrlON IL 011 C*NNOI 11 10010 WIIH I1~Ur IXIINOID II)LICIV*LVIIODI 1III
CML~
~Onu. rlOY
*c* .011110*
COYIII´•(lrO
~uru* uo rli
nm
..Y01(
I1IYr
*muuc a mas ~o
IY~IIUCltO* YI*Y~L
ua´• rm*o
IM Al LrmD *Ma
I...Y1LI
V1LY(
IVYT mi
CORT
mnla mvr ro
1*o
CWCLTlr~r
111
uo a.na
I
I
1IU tym TIC~n U* rUlrUlwOOl U.r.M
I
I
´•TURLI m i car or Ala wrr.
I
I
DI~I(IIVLLVl(Olt
WARNING
I
LIULYU
IND COM)LIIIL’I CDMIIII~ I11UI ~O 11111I1 IXCIII *N 1NO O(L
I
I
I
IlaOW’NG
I
I I
WPH *lm*llI wm txcHI lot ruu lull IND 011 110 IIIUI INIUnD 10 I INCHIlOr nllOH
)(~’1
LOCATED ON THE RIGHT MAIN LANDING GEAR STRUT
WARNING RELEASE
AIR
IN
STRUT
BEFORE
I
DISASSEMBLINO BUILT UNDER ONE OR MORE OF THE FOLLOWING BEECH PATENTS: 2388137. 24708(61 OTHER P*TENTS
~lrll
CE-748 THRU CE-979;
CJ-143 THRU
WARNING III(~II*IIINI1)UI IKH~DI1*II(MILING
D-10397 AND AFTER;
CJ-156 AND AFTER;
E-1970 AND AFTER;
CE-980 AND AFTER.
(i)eechcrall OIL AIR STRUT a
~wlu,*
*Ic*uclulcoaula
EA-273 AND AFTER;
INSTRUCTIONS ~o wo; ato uo ru
CJ-155;
E-llll, E-1241 THRU 0.1969;
D-10097, D-10120 THRU D-10396;
LOCATED ON THE NOSE
LANDING GEAR STRUT
EA-1 THRU EA-272.
rloY
laYlalAn arru nr*nusr lo Im mn 1 r*
COYIl(llIO W)IIIIM
ITYOlr
11I1(
U)D’
uurUI 410 ru
*n* nouuc a moruc ro I*II(IUCII~* Y**UIL II´•rS´•UIO*S X~I. rma lIW rrY *arro *um uc´•ruu ao*
ISIIYI)LI
caarar
LOCATED ON THE NOSE LANDING GEAR STRUT
lo
Df~lr6r
IIM
uu~rr
*4111
r0 aLf*Y
Call flUII
111 CWILIIlL’ U UO a
I~*
unu rvn
SEE CHAPTER 12 OR 32 FOR CORRECT EXTENSION
I’U"D’O’ ´•rllll
LOCATED ON THE LEFT MAIN LANDING GEAR STRUT C9101542
11-20-00
Page
2
Oct 16/92
Ale
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
NOTICE WING BOLTS ARE LUBRICATED
SEE MAINTENANCE MANUAL FOR CORRECT TORQUE VALUES
ON AIRPLANES CE-950 AND AFTER, CJ-156 AND AFTER, D-10372 AND AFTER, E-1847 AND AFTER, EA-221 AND AFTER.
LOCATED ON THE LEFT WING NEAR THE FOUR WING ATTACH BOLTS AND ON THE RIGHT WING NEAR THE TWO´• LOWER ATTACH BOLTS. ALSO LOCATED ON THE RIGHT SIDE OF THE FUSELAGE NEAR THE TWO UPPER WING ATTACH BOLTS.
r EMERGENCY LOCATOR TRANSMITTER SWITCH
I
r
-I
EMERGENCY LOCATO~ TRANSMITTER
i
SWITCH
I
ON
OFF
ARM
REARM
XMIT
O
O FOR AVIATION EMERGENCY USE ONLY.
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
i
OPERATION IN VIOLATION OF FCC
I
OPERATION IN VIOLATION OF FCC
I
RULES SUBJECT TO FINE OR LICENSE
I
RULES SUBJECT TO FINE OR LICENSE
UNLICENSED OPERATION UNLAWFUL.
REVOCATION.
L
ARM
REVOCATION.
L_______________-_J _
_
_
_
_
_
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
FORWARD AND BELOW THE STABILIZER
FORWARD AND BELOW THE STABILIZER ON
ON AIRPLANES: EA-1 AND EA-2; CE-748, CE-772 THRU CE-828; E-llll, E-1241 THRU
AIRPLANES: D-10197 THRU D-10346; EA-3 THRU
E-1406, D-10097, D-10120 THRU D-10196 AND
EA-80; E-1407 THRU E-1686: CE-829 THRU CE-905 AND CJ-150 THRU CJ-155 EXCEPT
CJ-149 EXCEPT AIRPLANES WITH
AIRPLANES WITH KITS 101-3046 OR 101-3127 INSTALLED.
KITS 101-3046 OR 101-3127 INSTALLED.
r
--I
EMERGENCY LOCATOR TRANSMITTER
EMERGENCY LOCATOR TRANSMITTER
I
SWITCH XMIT
SWITCH
I
ARM
TEST
AUTO
XMIT
O FOR AVIATION EMERGENCY USE ONLY.
I
I
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
I
I
UNLICENSED OPERATION UNLAWFUL.
OPERATION IN VIOLATION OF FCC
I
OPERATION IN VIOLATION OF FCC
RULES SUBJECT TO FINE OR LICENSE
i
RULES SUBJECT TO FINE OR LICENSE
REVOCATION.
i
I J
_
_
_
_
I
L
REVOCATION. _
_
_
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE
FORWARD AND BELOW THE STABILIZER
FUSELAGE FORWARD AND BELOW THE STABILIZER
ON AIRPLANES D;10347 AND AFTER;
ON AIRPLANES: E-2148 THRU E-2423; EA-412
EA-81 THRU EA-411: E-1687 THRU E-2147;
THRU EA-479; CE-1033 THRU CE-1240 AND
CE-906 THRU CE-1032 AND AIRPLANES WITH
CJ-156 THRU CJ-179 EXCEPT AIRPLANES
KIT NO. 101-3046 EXCEPT AIRPLANES WITH
WITH KITS 101-3046 OR 101-3127 INSTALLED.
KIT NO. 101-3127 INSTALLED.
C9200973
11-20-00
Page A16
3
Oct 16192
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
r--------------------------~
EMERGENCY LOCATOR TRANSMITTER SWITCH
r----------------------------~ i EMERGENCY LOCATOR TRANSMITTER I
SWITCH ARMED/
TEST
ARM
XMIT
ON
RESET
1
O
i FOR AVIATION EMERGENCY USE ONLY.
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
UNLICENSED OPERATION UNLAWFUL.
I
OPERATION IN VIOLATION OF FCC
I
j
OPERATION IN VIOLATION OF FCC
RULES SUBJECT TO FINE OR LICENSE
I
I
RULES SUBJECT TO FINE OR LICENSE
REVOCATION.
REVOCATION.
L
L--______________~
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
FORWARD AND BELOW THE STABILIZER ON
FORWARD AND BELOW THE STABILIZER ON
AIRPLANES: CE-1241 THRU CE-)646; E-2424
AIRPLANES: CE-1647 AND AFTER; E-2694
THRU E-2693 AND EA-480 THRU EA-530
AND AFTER; EA-531 AND AFTER AND
EXCEPT AIRPLANES WITH KIT 101-3127
AIRPLANES WITH KIT 101-3127 INSTALLED.
INSTALLED.
r
r
AVGAS ONLY
AVGAS ONLY
s~B" ~I GRADE
GRADE
100LL
lIIS
1~9" ~a"
I
I
GRADE
GRADE
(M)LL
100
FOR ALTERNATE FUELS SEE
FOR ALTERNATE FUELS SEE
PILOTS OPERATING HANDBOOK
PILOTS OPERATING HANDBOOK
CAPACITY 40 US GALLONS tar USABLE) WITH WINGS LEVEL
DEPRESS FLAPPER CHECK QUANTITY
CAP. TO TAB BOTTOM 30 GAL (27 USABLE) CAP. TO TAB SLOT 35 GAL (32
USP~BLE)i
SECURE CAP
CAUTION DO NOT INSERT FUEL NOZZLE
i
MORE THAN 1%" INTO TANK
i
PLACE INBOARD OF FILLER CAP
rcnuTnow DO NOT INSERT
r------------------------1
FUEL NOZZLE
FUEL
MORE THAN 3"
L
INTO TANK
~1
1
54 US GAL CAPACITY
(51 US GAL USABLE) L__--_,-----~
80 GALLON FUEL SYSTEM ON AIRPLANES D-10303 AND AFTER; EA-33 THRU EA-272 EXCEPT EA-242;
PLACE DECAL AFT OF FILLER CAP 108 GALLON FUEL SYSTEM
CE-884 AND AFTER;
ON AIRPLANES EA-242,
CJ-156 AND AFTER; AND E-1594 AND AFTER
EA-273 AND AFTER C92M)97~
11-20-00
Page
4
Oct 16192
A16
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUEL AVIATION GASOLINE GRADE 100LL
or
100
FOR ALTERNATE FUELS SEE
PILOTS OPERATING MANUAL
CAPACITY 25 US GALLONS (22 USABLE)
CAUTION DO NOT INSERT FUEL NOZZLE MORE THAN 3" INTO TANK 50 GALLON FUEL SYSTEM ON AIRPLANES D-10097; 0-10120 THRU D-10302, EA-1 THRU EA-32, CE-748, CE-772 THRU CE-883;
CJ-149 THRU CJ-155; AND E-llll, E-1241 THRU E-1593
11-20-00
A16
Page
5
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
EXTERNAL
POWER 24 VOLT
THE MODEL DESIGNATION PLACARD IS LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE
ADJACENT TO THE INBOARD END OF THE FLAP ON AIRPLANES
ENGINE COMPARTMENT, JUST BELOW THE
D-10097,
COWLING DOOR
D-10120 AND AFTER; EA-1 THRU EA-272; CORPORATION
CJ-149 AND AFTER; CE-748, CE-772
MODEL
SERIAL
THRU CE-1200, E-llll, E-1241 THRU PC
~VSE ONLY MS20392-X25 OR ISHEAR PIN WITH THIS PLVNGER
E-2399; AND EA-273 THRU EA-472.
TC B
LOCATED ON THE NOSE LANDING
THE MODEL DESIGNATION
PLACARD IS LOCATED ON THE
GEAR RETRACT LINK ROD
RIGHT SIDE OF THE FUSELAGE UNDER THE LEADING EDGE r_-
OF THE HORIZONTAL STABILIZER
i STATIC AIR.
ON AIRPLANES
I KEEP CLEAN I
CE-1201 AND AFTER, E-2400 AND AFTER,
LOCATED ON THE LEFT SIDE OF THE FUSELAGE
AND EA-473 AND AFTER.
JUST AFT AND BELOW THE REAR WINDOW
USE SAE 50 ABOVE 40" F
I USE SAE 30 BELOW 40" F
L
I
rl~l
LOCATED ON THE INSIDE OF THE LEFT COWLING
DOOR, ON THE FORWARD SIDE. THE PLACARD IS r-
VISIBLE WHEN THE DOOR IS OPEN
PULL TO
I CHECK LATCH L ------I
r--------------------~
FUEL CELL SUMPI DRAIN DAILV I_ I
LOCATED NEAR THE FORWARD HANDLE OF EACH COWLING DOOR
rI I
__
_
_
_
_
_
_
LOCATED ON THE UNDERSIDE OF EACH WING NEAR THE FUSELAGE
CAUTION
MCAiNETO tS NOT INTERNALLY GROUNOEII. COHSULT OWNEAS BEFORE
.ONI-TCENNOCSID LMANUAL
_
I
.J
DRAIN DAILY _I
LOCATED ON THE INSIDE OF EACH COWLING DOOR, ON THE AFT SIDE, THIS PLACARD IS
LOCATED ON THE LEFT SIDE OF THE FUSELAGE
VISIBLE WHEN EITHER DOOR IS OPEN
JUST BELOW THE LEADING EDGE OF THE WING
r---~ NO HANDLE L,-,~J INBOARD END LEFT FLAP, JUST OUTBOARD
ON TOP SURFACE NEAR OUTBOARD
WALKWAY ON RIGHT FLAP, 4 INCHES
END OF EACH HORIZONTAL
OUTBOARD OF FUSELAGE NEAR WING LEADING EDGE.
STABILIZER. C92009;2
"END"
11-20-00
Page
6
Oct 16/92
A16
CHAPTER
SERVICING
c5deechcraft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 12-SERVICING TABLE OF CONTENTS PAGE
SUSJECT
12100-00 General
Description
And
1
Operation 12-1 0-00
Replenishing Maintenance Practices (Effectlvity: All) Filling The Fuel Cells (Effectivity: All) Draining The Fuel System (Effectivity: All) Fuel Cell Reservoir (Effectivity: CJ-149 And After) Engine Fuel Filters And Screens (Effectivity: All) Oil System (Effectivi~y: Ail) Oil Filter Removal (Effectivity: All) Oil Filter Installation (Effectivity: All) Air-Conditioning System (Effectivity: All) Depressurizing the Air-Conditioning System (Effectivity: All) Purging The Air-Conditioning System (Effectivity: All) Charging The Air-Conditioning System (Effectivi~: All) Checking Compressor Oil Level (Effectivity: All) Brake System (Effectivity: All) Oxygen System (Effectivity: All) Oxygen Servicing (Effectivity: All except E-1946, E-2104, E-2111 and after, EA-320, after) Oxygen Servicing (Effectivity: E-1946, E-2104, E-2111 and after, EA-389 thru EA-439) Oxygen Servicing (Effectivity: EA-320, EA-440 And After)
1
1 1 1
1 2 2 2 2
3 3 3 3 4 4
..........................................................................................1....,....................
EA-389 and 5 5
6
12120100 Scheduled
Servicing
Maintenance Practices
1 1
Tires
E>
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