AFM 72 202
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0 -- 01
AIRPLANE FLIGHT MANUAL AFM
P1
L. T. R.
082
EASA APPROVED
TQ AUG 07
LIST OF TEMPORARY REVISIONS
No TR
EDITION DATE
DESTROYED
01
SEP 06
AT REV 21 DATED AUG 07
INSERTION
DATE
NAME OR REMARKS TR 42 EASA
AIRPLANE FLIGHT MANUAL
0
– 02
PAGE : 1 AFM
R.T.R.
DGAC APPROVED
DATE OCT 89
REASON FOR TEMPORARY REVISION Introduction of modification 1742 Limitations – Power plant – Limitations updating Reduced flaps landing procedure : add landing distance coefficient
001 MAY 92
CHAP INVOLVED 2.04 – 3.04 2.04 5.04 – 7.02
Procedure following failure : Modification of the procedure EEC FAULT
5.02
Graph add
6.05
JAN 90
Flight with pitch elevators disconnected Modification of the procedure following failure
5.04 – 7.02
JUN 90
Introduction of the Modification 1603
4.04
JAN 91
Introduction of modification 2803
4.03
MAY 91
Mod 2735, additional data Introduction of modification 2595 Change of modification number concerning mod 2059
2.04 – 6.02 2.02 – 3.00 – 3.06 4.00 – 4.03 – 7.00 7.02
JUL 91
Mod 2813 + 3156 + 3074 Introduction of TCAS
2.00 – 2.05 – 5.02 5.04 – 7.00 – 7.01 7.02
Mod 2464 : wording improvement
2.03
Addition of landing distances associated to increased speeds and introduction of Mod 1742 (Engine anti–icing instead of Engine de–icing) Minor change (wording)
5.04
SEP 91
Following DGAC request
2.01
OCT 91
Procedures following DGAC A.D.
4.03
15 Oct 91
Introduction of modification 3168
5.04
15 Dec 91
TCAS procedure improvement
MAR 92
Change of TCAS modification number
2.05 – 7.01 1.02 – 2.00 – 2.05 5.02 – 5.04 – 7.00 7.01 – 7.02
AIRPLANE FLIGHT MANUAL AFM
DATE
REASON FOR TEMPORARY REVISION
NOV 92
Introduction of models 211--212
DEC 92
Introduction of Mod 3560 (PW127 with propeller 14 SFL--11)
MAR 93
Introduction of Mod 3644 (dry unpaved runways) Introduction of Mod 3651 (MTOW increase) PW 127 Power Plant : Introduction of temporary limitation Introduction of Mod 3792 (steep slope approach) associated to Mod 3793 (GPWS MK VII) Introduction of Mod 3849 (MZ FW increase) Single DC GEN electrical limitation Acceptable fuels Changes in validity of mods 3651 + 3849 (Design weights) Use of grass runways (Mod 3644) Introduction of Mod 3952 (GPS B / K KLN 90 A) Enforcement of AD no T 94--245 R1 Cancellation of AD no T 94--245 R1 and Enforcement of AD no T 95 008 025
JUL 93 OCT 93 DEC 93 FEB 94 APR 94 NOV 94 JAN 95 24 JAN 95 FEB 95
R
R.T.R.
MAR 95
Change in the limitations chapter, about icing conditions -- Introduction of Mods 4111 and 4230 (Deletion of CONT RELIGHT and addition of MAN IGN for aircraft fitted with automatic relight) -- Introduction of Mod 4116 (Relocation of hydraulic green pump control circuit--breaker) Improvement of Mod 3952 (GPS Bendix/King KLN 90A)
0 -- 02 PAGE : 2 DGAC
APPROVED
DEC 92
001 MAR 95
CHAP INVOLVED 2.00 -- 2.01 2.02 -- 2.03 2.04 -- 2.05 -- 3.02 3.03 -- 3.04 -- 3.06 4.03 -- 5.02 -- 5.04 6.01 -- 6.02 -- 6.03 6.04 -- 6.05 -- 6.06 7.01 -- 7.02 2.04 -- 6.03 6.04 -- 6.05 6.06 -- 7.01 7.00 2.02 -- 7.01 2.04 7.00 -- 7.01 2.02 2.05 2.04 2.02 -- 7.01 7.02 2.00 -- 2.05 2.05 2.00 -- 2.05 -- 3.04 2.06 -- 4.00 -- 4.05 5.00 -- 5.04 2.06 3.03 -- 3.04 -- 3.05 4.02 -- 4.05 -- 5.02 7.02 4.04 2.05
MAR 93 JUL 93 OCT 93 DEC 93 FEB 94 APR 94 NOV 94 JAN 95
24 JAN 95
MAR 95
AIRPLANE FLIGHT MANUAL AFM
R.T.R.
0 -- 02 PAGE : 3 DGAC
APPROVED
DATE
REASON FOR TEMPORARY REVISION
001 FEB 99
CHAP INVOLVED
MAY 95
Introduction of ETOPS
1.02 -- 7.00 -- 7.02
JUN 95
Improvement of procedures
2.01 -- 2.06 -- 3.04 4.05
JUL 95
Introduction of Mod 4384 (Flight envelope change)
2.03 -- 2.05
SEP 95
Introduction of Mod 3973 (Propeller electronic regulation for PW127)
1.02 -- 3.02 -- 3.03 3.04 -- 4.05 -- 5.00 5.02 -- 5.04 -- 7.01 7.02
15 SEP 95
Introduction of Operations on Narrow runways Mod 4406
DEC 95
Introduction of Mod 8125 (Propeller brake removal)
2.05 -- 5.02 -- 5.04
FEB 96
Introduction of Mod 4371 (Propeller electronic regulation for PW124)
3.02 -- 3.03 -- 3.04 4.05 -- 5.00 -- 5.02 5.04 -- 7.01 -- 7.02
DEC 96
Introduction of Mod 4710 (RUNWAY SLOPE beyond 2%)
7.01
DEC 97
Improvement of Missed Approach procedure
3.05
Introduction of Mod 4885 and introduction of BRNAV capacity for GNSS HT 1000
2.05
APR 98
Introduction of Mod 4890 : GPS KLN90B/BRNAV
2.05
JUN 98
Smoke procedures improvement (cargo version mod 2595)
4.03
PEC FAULT procedure improvement
5.04
Introduction of Mod 5022 : new version of GPS KLN90B/BRNAV
2.05
NOV 98 R FEB 99
Severe Icing: improvement of detection and procedures
7.02
2.06 -- 3.04 -- 4.05
FEB 99
AIRPLANE FLIGHT MANUAL AFM
R.T.R.
0 -- 02 PAGE : 4 EASA
APPROVED
DATE
REASON FOR TEMPORARY REVISION
001 AUG 07
CHAP INVOLVED
MAR 01
Introduction of Mod 8259 : TCAS Collins on King avionics
2.05 -- 7.01
FEB 03
Introduction of modifications 5377+5434 : Cockpit Door Locking System for Models 102--202--212
7.01
OCT 03
Introduction of modifications 5377+8333 : Cockpit Door Locking System for Models 101--201--211 and amendment of Cockpit Door Jammed procedure for all models
7.01
MAR06
Introduction of modification 5561 : Messier--Bugatti Wheels and Brakes
SEP 06
FUEL Feeding Limitations Harmonization EMER DESCENT procedure amendment ONE EEC OFF procedure harmonization
5.04 -- 6.05
2.04 4.05 5.02
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
List of EffectiveTemporary Pages
L.E.T.P.
0-04 page 1-082 EASA
AUG 07
You must hold in your manual the following pages Issue
P CH SE Page Seq Date Label Validity expression
REV21
0 01
001 082 AUG 07 ALL
L.T.R.
REV21
0 02
001 001 MAY 92 ALL
R.T.R.
REV21
0 02
002 001 AUG 95 ALL
R.T.R.
REV21
0 02
003 001 SEP 99 ALL
R.T.R.
REV21
0 02
004 001 AUG 07 ALL
R.T.R.
REV21
0 04
001 082 AUG 07 ALL
L.E.T.P.
End
TQ
Modification expression
TQ
TQ
AIRPLANE FLIGHT MANUAL
0 -- 05 PAGE : 5
AFM
L.N.R.
EASA APPROVED
LIST OF NORMAL REVISIONS N0 REV
INSERTED DATE
EASA APPROVED
19
JUL 05
EASA A.A. 01029
20
JUL 06
EASA A.A. 01205
21
AUG 07
EASA A.A. 01555
001 AUG 07
AIRPLANE FLIGHT MANUAL
0
– 06
PAGE : 1 AFM
DATE DEC 89
R.N.R.
REASON FOR NORMAL REVISION
FEB 91
CHAP INVOLVED
Introduction of modification 2495
2.04
Introduction of modification 2464
2.03
Introduction of auxiliary aft cargo smoke procedure (Mod : 2059)
4.03
Introduction of the forward cargo smoke procedure (Mod : 1861)
4.03
Introduction of mod 2456 Landing flaps 00 : modification of landing distance correction coefficient
FEB 91
001
Cancellation of the temporary revision of Oct 89
Modification of the “pitch disconnect” procedure MAY 90
DGAC APPROVED
5.04 – 7.02 2.05 5.04 – 7.02
Modification of the OXYGEN LO PR procedure
5.04
Flight in icing conditions. Effect on approach climb gradient weight. Graph modification.
6.06
Introduction of the brake energy limitation for dispatch flaps 00
7.02
Introduction of the dispatch with one AFU inoperative
7.02
Introduction of the dispatch with ATPCS OFF
7.02
Introduction of the supplement “Ferry flight with pitch elevators disconnected”
7.02
Environmental correct extension (T/O and landing)
2.03
Explanations or figures improved
4.03 – 7.01 – 6.02 2.04 – 1.02 – 2.02 6.03 – 5.02
AIRPLANE FLIGHT MANUAL AFM
DATE FEB 91
AUG 91
MAY 92
R.N.R. REASON FOR NORMAL REVISION
0 –06 PAGE : 2 DGAC APPROVED
001 MAY 92
CHAP INVOLVED
Procedure changes Introduction of modification 2735
2.04 – 2.05 2.04 – 6.03 – 6.04 6.06
Non valid pages (delivery error)
5.04
Non valid page to be deleted (All planes embody modif 2403).
3.03
Yellow page changes to white (mod 1603)
4.04
CDL improvement (Jacking point covers)
7.01
Introduction of modif 2803
4.03
Yellow pages to be turned white (from temporary revision N0 5, MAY 91 and N0 6, JUL91)
1.02 – 2.00 – 2.02 2.03 – 2.04 – 0.05 3.00 – 3.06 – 4.00 4.03 – 5.02 – 5.04 6.02 – 7.00 – 7.01 7.02
Procedure improvement
4.03 – 4.05 – 5.02 7.02 – 5.04
Lay out and wording
1.02 – 2.01 – 2.05 5.04 – 6.02 – 5.02 6.03 – 6.06 – 4.04 5.04 – 7.00
Introduction of mod 8044 (tail wind limit up to 15 kt)
2.03 – 6.03
Remodelling of title pages
2.00 – 2.05 – 3.00 3.06 – 4.00 – 4.03 6.00 – 7.00 – 7.01 7.02
Procedure improvement
2.04 – 3.02 – 3.05 4.03 – 5.02 – 5.03 5.04 – 7.01 – 7.02
Graphes improvement
2.02 – 6.01 – 6.02 6.03 – 6.04 – 6.05 6.06 – 7.01 – 7.02
AIRPLANE FLIGHT MANUAL
0 –06 PAGE : 3
AFM
DATE MAY 92
R.N.R.
REASON FOR NORMAL REVISION Yellow pages to be turned to white Lay out and wording Pages to be deleted
APR 93
Yellow pages to be turned to white
Pages to be deleted Modification of TCAS number Procedure improvement Wording and lay out improvement
FEB 94
Yellow pages to be turned to white Pages to be deleted 247F propeller retrofit Procedure improvement Wording and lay out improvement
Graph improvement
DGAC APPROVED
001 FEB 94
CHAP INVOLVED 2.01 – 2.05 – 4.03 5.02 – 5.04– 7.01 7.02 1.02 – 5.04 – 6.01 6.03 – 7.02 1.02 – 2.00 – 2.04 2.05 – 3.00 – 4.00 7.00 2.00 – 2.01 – 2.02 2.03 – 2.04 – 2.05 3.02 – 3.03 – 3.04 3.06 – 4.03 – 5.02 5.04 – 6.01 – 6.02 6.03 – 6.04 – 6.05 6.06 – 7.01 – 7.02 2.03 2.00 – 2.05 – 5.02 5.04 – 7.00 – 7.01 7.02 2.04 – 3.04 – 3.05 4.05 – 5.02 – 5.03 5.04 – 7.01 – 7.02 1.02 – 2.01 – 2.04 6.01 – 6.02 – 6.03 6.05 – 6.06 – 7.01 2.02 – 2.04 – 2.05 7.00 – 7.01 – 7.02 2.04 – 6.01 2.04 – 6.03 – 6.04 6.05 – 6.06 – 7.01 2.04 –3.04 – 3.07 5.02 – 5.04 – 6.05 7.02 1.02 – 2.00 – 2.06 3.04 – 5.01 – 5.04 6.00 – 6.03 – 6.04 7.00 – 7.01 – 7.02 6.03 – 6.05 – 6.06 7.02
AIRPLANE FLIGHT MANUAL
0 –06 PAGE : 4
AFM
DATE AUG 95
OCT 96
R.N.R.
REASON FOR NORMAL REVISION
DGAC APPROVED
001 OCT 96
CHAP INVOLVED
Yellow pages to be turned to white
1.02 – 2.00 – 2.01 2.05 – 2.06 – 3.00 3.03 – 3.04 – 3.05 4.00 – 4.02 – 4.04 4.05 – 5.00 – 5.02 5.04 – 7.02
Pages to be deleted
1.02 – 2.00 – 2.01 2.05 – 2.06 – 3.04 4.00 – 5.00 – 5.04 7.02
Procedure improvement
2.04 – 3.04 – 3.05 4.04 – 5.02 – 5.04 7.01 – 7.02
Wording and lay out improvement, typing errors
1.02 – 1.03 – 3.02 4.00 – 4.02 – 5.02 5.03 – 5.04 – 6.02 6.03
Graph improvement or correction
7.02
Yellow pages to be turned to white
2.03 – 2.05 – 3.02 3.03 – 4.05 – 5.00 5.02 – 5.04 – 7.02
Pages to be deleted
1.02 – 2.04 – 3.03 3.04 – 4.05 – 5.02 5.04 – 6.03 – 6.04 6.05 – 6.06 – 7.01 7.02
Procedure improvement
2.04 – 2.05 – 3.01 3.02 – 3.03 – 3.05 5.02 – 5.04 – 7.02
Wording and lay out improvement, typing errors
1.02 – 2.05 – 3.04 4.05 – 5.02 – 5.03 5.04 – 6.01 – 6.03 6.06 – 7.00 – 7.01 7.02
Graph improvement or correction
6.01 – 6.02 – 6.03 6.04 – 6.05 – 6.06 7.01 – 7.02
AIRPLANE FLIGHT MANUAL
0 –06 PAGE : 5
AFM
DATE OCT 96
R.N.R.
REASON FOR NORMAL REVISION KVS1G extension at take off Enforcement of “Consigne de navigabilité no 96 – 207 – 031 (B)”
SEP 97
Yellow pages to be turned to white
DGAC APPROVED
001 SEP 97
CHAP INVOLVED 6.03 2.01 – 2.05 – 2.06 3.04 – 4.00 – 4.05
7.00 – 7.01
Pages to be deleted
2.05 – 4.03 – 5.02 7.02
Limitation – Procedure Improvement
1.02 – 2.04 – 3.04 4.04 – 4.05 – 5.04 6.02 – 7.02
Wording and layout improvement, typing errors
3.05 – 6.00 – 6.01 6.03
Graph improvement or correction
6.01 – 6.03 – 6.05 7.01
Part 2.05 presentation improvement Part 5.02 presentation improvement
2.00 – 2.05 5.02
Container transportation presentation improvement
2.02 – 3.00 –3.06 4.00 – 4.03 – 7.02
Mod 4295 introduction – Mod 4111 anti–mod
3.00 – 3.03 – 3.04 3.05 – 4.02 – 4.05 5.02 – 7.02
Mod 4654 introduction – Installation of HT1000 GNSS
2.05
Flaps retracted dispatch
7.02
AIRPLANE FLIGHT MANUAL
0 –06 PAGE : 6
AFM
DATE SEP 98
R.N.R. REASON FOR NORMAL REVISION Yellow pages to be turned to white
DGAC APPROVED
2.05 – 3.05 – 4.03 5.04 7.02
Mod 4597 introduction – Mod 3952 anti–mod
2.05
Introduction of dispatch with one torque indicator inoperative Graph improvement or correction Introduction of wet and contaminated runways advisory materials
SEP 99
CHAP INVOLVED
Pages to be deleted
Procedure improvement
001
3.04 – 4.04 – 7.02 7.02 6.06 – 7.01 7.03
Wording and layout improvement, typing errors
1.02 – 1.03 – 2.05 3.07 – 5.04 – 6.03 7.00 – 7.02
MAY 99
Severe Icing: TR 37 to be turned to white
2.06 – 3.04 – 4.05
SEP 99
TR36 to be turned to white Introduction of Mod 4511 (New look for transport container) Introduction of Mod 8233 (Power plant)
2.05 3.06 – 4.03 – 7.02 7.01
Engine limitation change
2.04
Procedures improvement
2.05 – 3.06 – 4.05 5.02 – 5.04 – 7.01
Effect of Mod 4371 (Electronic propeller control regulation) on wet and contaminated runways performances. V1 limited by VMCG on wet and contaminated runways Wording and layout , typing errors
7.03 7.03 1.02 – 4.04 – 5.04 6.03 – 6.06 – 7.00 7.00 – 7.02 – 7.03
AIRPLANE FLIGHT MANUAL
0 –06 001
PAGE : 7 AFM
DATE SEP 00
R.N.R. REASON FOR NORMAL REVISION
JUL 02
CHAP INVOLVED 2.05
Manual management about the TCAS
7.01 7.00 – 7.01
Pages to be deleted
2.05 – 5.02 – 5.04 7.01 – 7.02
Procedure improvement
2.04 – 3.04 – 3.05 4.05 – 7.02
Graph improvement
2.02
Wording and layout improvement Typing error
1.01 – 4.00 –5.04 7.01
Yellow pages to be turned to white
2.05 – 7.01
Procedure Improvement
JUL 02
APPROVED
Introduction of Mod 5176 : GNSS, Load software final baseline.
Introduction of a new appendix
SEP 01
DGAC
4.05
Steep Slope Approach : add a tail wind limitation as for model 42–500
7.01.05
Take Off after use of fluids type II or IV
7.01.08
5313 : Enhanced GPWS activation with GPWS MK VIII
2.00 – 2.05 3.00 – 3.07 – 4.05
Use of rudder in case of large sideslip angles
2.03
Procedure improvement : at normal landing with PW124 with electronic regulation it is not necessary to have NP ≥ 86%
3.05
Typing error
4.02
AIRPLANE FLIGHT MANUAL
0 –06 001
PAGE : 8 AFM
DATE SEP 03
R.N.R. REASON FOR NORMAL REVISION Temporary revisions to be turned to white TR39 Introduction of modifications 5377+5434 : Cockpit Door Locking System Introduction of modifications : 5403 : GNSS HT1000 P–RNAV Trims checks updating
DGAC APPROVED
SEP 03
CHAP INVOLVED 7.01
2.05 3.01 – 3.02
ELEC SMK procedure : adding of DC SVCE & UTLY BUS ... OFF item
4.03
Severe Icing Procedure Improvement
4.05
FWD and AFT SMK Procedures Improvement for cargo version
4.03
Steep Slope Approach prohibited for : Severe Icing, Reduced Flaps Landing, Pitch Disconnect
4.05 – 5.04
Flaps failure during CAT II approach : wording
7.01.03
Limitations regarding TCAS Resolution Advisory
7.01.04
Harmonization with FAA for supplements : – Dispatch with one wheel brake deactivated or removed – Dispatch with anti skid system inoperative Improvement of CLIMB sequence in case of dispatch ONE EEC OFF : reduce both TQ before PWR MGT on CLB for engines with electronic regulation LBA supplement creation Various
7.02.04 7.02.05 7.02.07
7.04 7.00.00
AIRPLANE FLIGHT MANUAL
0 –06 PAGE : 9
AFM
DATE JUL 04
JUL 05
R.N.R. REASON FOR NORMAL REVISION Yellow pages to be turned white TR40 : Cockpit Door Security System ST2
EASA APPROVED
001 JUL 05
CHAP INVOLVED 7.01
Securized Cockpit Door Jammed Procedure improvement
7.01
Use of JP4 is prohibited (SFAR88)
2.04
Towing with TOWBARLESS system is prohibited
2.05
Severe Icing Limitations Updating
2.06
Introduction of modification 5467 EGPWS
3.07
Introduction of FUEL LEAK procedure
5.04
Examples for Obstacles Calculations
6.06
Wording improvement for dispatch
7.02
CAA supplement
7.08
Abbreviations updating
1.02
Management of the manual
7.01
EASA/DGAC Approval
1.01
Limitations of minimum fuel temperature : to ensure adequate relight
2.04
Steep Slope Approach : ≥4.5_ (not >)
5.04 – 7.00 – 7.01
Introduction of modification 5465 New Securized Cockpit Door Fittings
7.01
Complement for EGPWS Mod 5467
2.05 – 3.00 – 4.05
Dispâtch with wheel brake removed is not possible
7.00 – 7.02
AIRPLANE FLIGHT MANUAL AFM
DATE JUL 06
AUG 07
R.N.R. REASON FOR NORMAL REVISION
0 -- 06 001
PAGE : 10 EASA APPROVED
AUG 07
CHAP INVOLVED
Use of Jet B is prohibited
2.04
Cockpit Checks Preparation Trims’ Title
3.00
Introduction of modification 5561 : Messier--Bugatti Wheels and Brakes
6.05
TCAS new wording for Traffic Advisory case
7.01
Introduction of modification 5567 : MPC Multi Purpose Computer -- APM : Aircraft Performance Monitoring
7.00 -- 7.01
Introduction of modification 5570 and 8431 : Enhanced Surveillance
7.00 -- 7.01
Introduction of modification 5506 : ACARS
7.00 -- 7.01
Blanking of TR24: FUEL Feeding Limitations Harmonization EMER DESCENT procedure amendment ONE EEC OFF procedure harmonization
2.04 4.05 5.02
Fuels RT and TS1 acceptable
2.04
Part 4 Emergency Procedures Improvement 7.01 and 7.02 parts wholly revised Numbering of Appendices and Supplements
4 7.00 -- 7.01 -- 7.02
Introduction of modification 8442 : MPC
7.01.15
New High Latitudes Operations
7.01.18
IAC Supplement for Operations in CIS countries
7.09
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
Shipping Note Normal Pages
0-07 page 1-082
S.N.N.P.
" ADD " = Add
"DESTROY" = Destroy "
EASA
AUG 07
…….." = Revised
"SEE VAL" = See Validation
Action
P CH SE Page Seq Date
Validation Criteria
ADD
0 01
001 082 AUG 07
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001 002 APR 93
201-202-211-212
ADD
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002 002 APR 93
201-202-211-212
......
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ADD
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004 050 SEP 01
......
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001 001 AUG 07
......
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Turn
TQ
TQ
MOD 3074 or 3113 or 3625 or 3832 or 8259
TQ
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
Shipping Note Normal Pages
0-07 page 2-082
S.N.N.P.
" ADD " = Add
"DESTROY" = Destroy "
EASA
AUG 07
…….." = Revised
"SEE VAL" = See Validation
Action
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Turn
Validation Criteria
102-202-212
MOD 1603
MOD 5313 or 5467
MOD 5313 or 5467
TQ
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
Shipping Note Normal Pages
0-07 page 3-082
S.N.N.P.
" ADD " = Add
"DESTROY" = Destroy "
EASA
AUG 07
…….." = Revised
"SEE VAL" = See Validation
Action
P CH SE Page Seq Date
Validation Criteria
CANCEL AND REPLACE ALL PAGES OF 7-01 AND 7-02 CHAPTERS. NEW PAGES ARE LISTED IN LIST OF EFFECTIVE NORMAL PAGES ( LENP)
End
TQ
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
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ATR 72
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0-08 page 15-082 EASA
AUG 07
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
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P CH SE Page Seq Date Label Validity expression 7 03
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AUG 07
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ATR 72
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AUG 07
AFM
AIRPLANE FLIGHT MANUAL
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AUG 07
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
List of Modifications
L.O.M.
0-09 page 1-082 EASA
AUG 07
MODIF
PARTS
TITLE VALIDITY
0069
7
AFCS. USE OF A CAT.II APPROVED AP/FD DOWN TO 50 FT.
1112
7
AUTO FLIGHT - RETROFIT CAT 2 CAPABILITY TO A/C DELIVERED CAT 1 CAPABILITY
1368
5-6-7
ALL
ALL ICE AND RAIN PROTECTION - INSTALL INNER WING DE-ICING SYSTEM ALL 1603
4
ELECTRICAL POWER - INSTALL TRU ON PROVISION
2456
2
COMMUNICATIONS - RELOCATE VHF2 ANTENNA ON UPPER FUSELAGE
2735
2-6-7
ENGINE INDICATING - CHANGE SOFTWARE ES 06 IN E.E.C
3037
2
PNEUMATIC - ECS - MODIFY ISOLATING VALVE OPENING CONTROL IN TAXYING
3168
5
AUTO FLIGHT - REPLACE AFC COMPUTER
TQ0001
ALL
ALL
ALL
ALL 3522
2-6
3625
2-5
3651
2-7
GENERAL - CERTIFY ATR 72 FOR 15 KT TAILWIND LANDING ALL NAVIGATION - INSTALL A SFE TCAS COMPUTER ALL GENERAL - INCREASE MTOW AT 22,000KGS (48,500LBS) TQ0001
Turn
TQ
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
List of Modifications
L.O.M.
0-09 page 2-082 EASA
AUG 07
MODIF
PARTS
TITLE VALIDITY
3832
2-7
NAVIGATION - REPLACE COLLINS TCAS COMPUTER
4654
2
NAVIGATION - INSTALL HT1000 GNSS ON FULL PROVISION
4885
2
NAVIGATION - GNSS - REPLACE NPU BY A NEW ONE
5176
2
NAVIGATION - GNSS - LOAD SOFTWARE FINAL BASELINE
5205
7
NAVIGATION - ATC/TCAS - ACQUIRE ALTITUDE VIA BUS ARINC 429
5313
2-3-4
NAVIGATION - EGPWS MKVIII ENHANCED PART ACTIVATION
5377
7
EQUIPMENT/FURNISHINGS - WIRING FOR COCKPIT ENTRANCE SECURISED
5403
2
NAVIGATION - CERTIFICATION OF GNSS P-RNAV
5434
7
EQUIPMENT/FURNISHINGS - INSTALL DOOR ON ELECTRICAL PROVISION
5467
3
NAVIGATION - EGPWS - INSTALLATION EGPWS MKVIII P/N 965-1206-011
8044
2-6
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL GENERAL - CERTIFY ATR 72 FOR 15 KT TAILWIND LANDING TQ0002
End
TQ
AFM
AIRPLANE FLIGHT MANUAL
ATR 72
Cross Reference Table
C.R.T.
0-10 page 1-082 EASA
This table shows, for each delivered aircraft, the cross reference between : - the fleet serial number (F.S.N.) - the manufacturing serial number (M.S.N.) - the registration number It is the F.S.N. which appears in the L.E.N.P. or L.E.T.P. F.S.N.
End
M.S.N.
REGISTRATION
TQ0001
0365
PP-PTH
TQ0002
0352
TQ
AUG 07
1 –00
GENERAL
PAGE : 1 CONTENTS
AFM
1 . 00 – CONTENTS 1 . 01 – INTRODUCTION 1 . 02 – PARTICULAR EXPLANATIONS DEFINITION OF WORDING UNIT CONVERSION GLOSSARY OF STANDARD NOMENCLATURE 1 . 03 – 3 VIEW DRAWING
Mod : –
Eng : ALL
001
DGAC SEP 89 APPROVED
Model : ALL
GENERAL
1 –01 PAGE : 1
AFM
INTRODUCTION
EASA APPROVED
R
SEP 89 SEP 00
001 JUL 05
The Airplane Flight Manual (AFM) is related to a specific airplane whose model is specified on the heading page. It is approved by : EASA. NOTE : “DGAC APPROVED” is kept on pages created/revised before EASA creation. This mention is changed to “EASA APPROVED” for all new or revised pages. ORGANIZATION OF THE MANUAL The AFM contents are divided into seven chapters : 1 – General 2 – Limitations 3 – Normal procedures 4 – Emergency procedures 5 – Procedures following failure 6 – Performance 7 – Appendices and supplements
R
Preliminary pages include all approval references and define the updating status of the list of effective pages : – for the airlines manual – for the envelope manual (covering all the airlines manuals). The pages are numbered per chapter and section Applicability of each page is identifed at the bottom of the page by : – engine – model – modification number (if any) NOTE :
Unless otherwise specified at the bottom of the page its content is valid for all models mentioned on the heading page (0.00 page 1).
GENERAL
1 –02 001
PAGE : 1 AFM
PARTICULAR EXPLANATIONS
DGAC APPROVED
SEP 98
1 . 02 . 01 – DEFINITION OF WORDING Note
: An operating procedure, technique etc... considered essential to emphasize
CAUTION
: An operating procedure, technique etc... which may result in damage to equipment if not carefully followed
WARNING
: An operating procedure, technique etc... which may result in injury or loss of life if not carefully followed.
1 . 02 . 02 – UNIT CONVERSION Weight R R
1 kg = 2.2046 lb
1 lb = 0.4536 kg
1 m = 3.2808 ft 1 m = 39.3701 in
1 ft = 0.3048 m 1 in = 0.0254 m
Pressure
1 HPa = 0.0145 psi
1 psi = 69 HPa
Temperature
1° C = ( 1° F – 32 ) x .555
1° F = 1° C x 1.8 + 32
Length – Altitude Distance
SEP 89
GENERAL
1 –02 PAGE : 2
AFM
PARTICULAR EXPLANATIONS
DGAC APPROVED
1 . 02 . 03 – GLOSSARY OF STANDARD NOMENCLATURE
R
AAS A/C AC ACW ADC ADF ADI ADU AFCS A/FEATH AFM AFT AFU AGL AH AHRS AHRU AIR COND ALT ANN AP APP ARM ASCB ASD ASI ATC ATE ATPCS ATT ATTND AUTO AUX BARO BAT BC BPCU BPU B–RNAV BRK BRT BTC BTR
Anti–icing Advisory System Aircraft Alternating Current Alternating Current Wild Frequency Air Data Computer Automatic Direction Finding Attitude Director Indicator Advisory Display Unit Automatic Flight Control System Automatic Feathering Airplane Flight Manual Rear Part Auto Feathering Unit Above Ground Level Ampere – Hours Attitude and Heading Reference System Attitude and Heading Reference Unit Air Conditioning Altitude Annunciator Auto–Pilot Approach Armed Avionics Standard Communications Bus Acceleration Stop Distance Air Speed Indicator Air Traffic Control Automatic Test Equipment Automatic Take off Power Control System Attitude Attendant Automatic Auxiliary Barometric Battery Back Course Bus Power Control Unit Battery Protection Unit Basic Area Navigation Brake Bright Bus Tie Contactor Bus Tie Relay
MAY 92 001 SEP 98
APR 93
GENERAL
1 –02 PAGE : 3
AFM
R
R
BXR CAB CAP CAPT CAS CAT C/B CCAS CDI CFC CG CHC CH CHG CL CLA CLB CLR CM COM COMPT CONFIG CONT CORRECT CPL CR CRC CRS CRT CRZ CTL CVR dB DC DEC DELTA P DEV DFDR DG.C DGR DH DIFF DIM DIST DME
PARTICULAR EXPLANATIONS
DGAC APPROVED
Battery Transfer Relay Cabin Crew Alerting Panel Captain Calibrated Air Speed Category Circuit Breaker Centralized Crew Alerting System Course Deviation Indicator Constant Frequency Contactor Center of Gravity Charge Contactor Charge Charger Condition Lever Condition Lever Angle Climb Clear Crew Member Communication Compartment Configuration Continuous Correction Auto Pilot Coupling Cruise Continuous Repetitive Chime Course Cathodic ray tube Cruise Control Cockpit Voice Recorder Decibel Direct Current Declination Decrease Differential Pressure Deviation Digital Flight Data Recorder Celsius Degree Degraded Decision Height Differential Light Dimmer Distance Distance Measuring Equipment
001 SEP 98
AUG 91 SEP 97
GENERAL
1 –02 PAGE : 4
AFM
R
DN DSPL EADI EEC EFIS EGHR EHSI ELEC ELV EMER ENG EPC ET ETOPS EXT EXC FAIL FD FDAU FDEP FEATH or FTR FF FI FL FLT F/O FQI FT, ft FU FWD GA GAL GC GCU GD GEN GI GMT GND GPS GPU (E)GPWS G/S GU
PARTICULAR EXPLANATIONS
DGAC APPROVED
001 JUL 04
Down Display Electronic Attitude Director Indicator Electronic Engine Control Electronic Flight Instrument System External Ground Handling Relay Electronic Horizontal Situation Indicator Electrical Elevation Emergency Engine External Power Contactor Elapsed Time Extended Twin Operations Exterior, External External Power/Service Bus Contactor Failed, Failure Flight Director Flight Data Acquisition Unit Flight Data Entry Panel Feather, Feathering Fuel Flow Flight Idle Flight Level Flight First Officier Fuel Quantity Indication Foot, Feet Fuel Used Forward Go around Galley Generator Contactor Generator Control Unit Gear Down Generator Ground Idle Greenwitch Mean Time Ground Global Positioning System Ground Power Unit (Enhanced) Ground Proximity Warning System Glide Slope Gear Up
SEP 89 MAY 95 AUG 95 OCT 96
1 –02
GENERAL
PAGE : 5 AFM
R
R
R
HD HDG HF HI HLD HMU HP HPa HSI HYD IAF IAS IDT IFR ILS INC IND IN, in IN/HG INHI INST INT INV ISOL ITT Kg, KG KHZ KT, kt LB LBA LDG L/G LH LIM L–NAV LO LOC LO PR LT LVL M, m MAC MAN MAP MAX
PARTICULAR EXPLANATIONS
DGAC APPROVED
Head Down Heading High Frequency High Hold Hydromechanical Unit High Pressure Hecto Pascal Horizontal Situation Indicator Hydraulic Initial Approach Fix Indicated Air Speed Ident Instrument Flight Rules Instrument Landing System Increase Indicator Inch(es) Inches of Mercury Inhibit Instrument Interphone Inverter Isolation Inter Turbine Temperature Kilogramme Kilo – Hertz Knot Pound Lowest Blade Angle Landing Landing Gear Left Hand Limitation Lateral Navigation Low Localiser Low Pressure Light Level Meter Mean Aerodynamic Chord Manual Ground Mapping Maximum
SEP 89
001 SEP 98
SEP 97
GENERAL
1 –02 PAGE : 6
AFM
PARTICULAR EXPLANATIONS
DGAC APPROVED
R
MBE MC MCT MEA MFC MGT MHZ MIC MIN MKR MM MMO mn MW MTOW NAV NDB NEG NH NIL NM NORM NP N/W OAT OBS OCL OUTB OVBD OVHT OVRD OXY PA PAX PB PCU PEC PF PIT PL PLA PNF PNL POS P–RNAV PR PRESS
Maximum Brake Energy Master Caution Maximum Continuous Minimum en Route Altitude Multi Function Computer Management Megahertz Microphone Minimum Marker Millimeter Maximum Operating Mach Minute Master Warning Maximum Take–off Weight Navigation Non Directional Bearing Negative High Pressure Spool Rotation Speed Nothing, No object Nautical Mile Normal Propeller Rotation Speed Nose Wheel Outside Air Temperature Omni Bearing Selector Obstacle Clearance Limit Outboard Overboard Overheat Override Oxygen Passenger Adress Passenger Push Button Propeller control Unit Propeller electronic control Pilot Flying Pitch Power Lever Power Lever Angle Pilot Non Flying Panel Position Precision Area Navigation Pressure Pressurization, Pressure
001 JUL 04
SEP 89 AUG 95 SEP 99
GENERAL
1 –02 001
PAGE : 7 AFM
R R
PRKG PROP PSI PT PTT PWR QFU QTY RA RAD/INT RAIM RCAU RCDR RCL RCU RECIRC REF REV RH RMI RPM RQD RTO RUD RWY SAT SBY SC SEL SGL SGU SID S/O or SO SPD SSR STAB STAR STBY STR STRG SVCE SW SYS TAD TAS TAT TAWS TBD
PARTICULAR EXPLANATIONS
DGAC APPROVED
JUL 04
Parking Propeller Pound per Square Inch Point Push to Talk, Push to Test Power Runway Heading Quantity Radio Altitude Radio/Interphone Receiver Autonomous Integrity Monitoring Remote Control Audio Unit Recorder Recall Rudder releasable Centering Unit Recirculation Reference Reverse Right Hand Radio Magnetic Indicator Revolution Per Minute Required Reserve Take–off Rudder Runway Static Air Temperature Stand By Single Chime, Starter Contactor Selector Single Symbol Generator Unit Standard Instrument Departure Shut Off Speed Service Bus Select Relay Stabilizer Standard Arrival Stand By Service Bus Transfer Relay Steering Service Switch System Terrain Awareness Display True Air Speed Total Air Temperature Terrain Awareness Warning System To be Determinated
SEP 89 AUG 95 SEP 98
GENERAL
PAGE : 8 AFM
R
TCAS TCAS RA TCAS TA TCF TCS TEMP TGT TK TLU TO TOD TOR TOW TQ UBC U/F UHF UNDV UNLK UTLY VA VAPP VC VENT VERT VFE VFR VFTO VGA VHF VLE VLO VLOF VMCA VMCG VMCL VMO VMU VOR VR VRA VS1G VS VSI VU WARN
PARTICULAR EXPLANATIONS
MAY 92 SEP 98
1 –02 DGAC APPROVED
Traffic alert and collision avoidance system TCAS resolution advisory TCAS traffic advisory Terrain Clearance Floor Touch Control Steering Temperature Target Tank Travel Limitation Unit Take–off Take–off Distance Take–off Run Take–off Weight Torque Utility Bus Contactor Underfloor Ultra High Frequency Undervoltage Unlock Utility Design Maneuvering Speed Approach Speed Calibrated Airspeed Ventilation Vertical Flaps Extended Speed Visual Flight Rules Final Take–off Speed Go around speed Very High Frequency Landing Gear Extended Speed Landing Gear Operating Speed Lift Off Speed Minimum Control Speed in flight Minimum Control Speed on Ground Minimum Control Speed in Flight (Landing config). Maximum Operating Speed Minimum Unstick Speed VHF Omni Directional Range Rotation Speed Rough Air Speed Stall Speed Vertical Speed Vertical Speed Indicator Visual Unit Warning
001 JUL 04
GENERAL
1 –02 PAGE : 9
AFM
R
XFEED XFR YD Z ZA ZCTH ZFW ZP ZPI ZRA nP
PARTICULAR EXPLANATIONS
Cross Feed Transfer Yaw Damper Altitude Aircraft Altitude Theoretical Cabin Altitude Zero Fuel Weight Pressure Altitude Indicated Pressure Altitude Radio Altimeter Altitude Differential Pressure
DGAC APPROVED
001 SEP 98
FEB 94
1 –03
GENERAL
SEP 89
001
PAGE : 1 3 VIEW DRAWING
AFM
DGAC
7.65 m (301.181 in)
APPROVED
R
10.772 m (424.095 in)
SEP 98
3.962 m (155.984 in)
4.10 m (161.417 in)
27.149 m (1068.859 in)
8.10 m (318.898 in)
27.166 m (1069.528 in)
7.31 m (287.795 in)
27.05 m (1064.961 in)
2.362 m (92.992 in)
WING REFERENCE AREA . . . . . . . . . . . . . . . . . . . . . . . 61 m2 ( 94550 in2 ) ROOT CHORD . . . . . . . . . . . . . . . . . . . . . . . . . 2.574 m ( 101.339 in) ASPECT RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.995 REFERENCE CHORD LA ( = MAC ) . . . . . . . . 2.303 m ( 90.669 in) DISTANCE FROM MOMENT ORIGIN TO REFERENCE CHORD LEADING EDGE . . . . . . . . . . . . . . . 13.604 m ( 535.591 in) HORIZONTAL TAIL REFERENCE AREA . . . . . . . . . . . . . . . . . . . . . 11.73 m2 ( 18182 in2) REFERENCE CHORD LH . . . . . . . . . . . . . . . . . 1.636 m ( 64.409 in) ASPECT RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.555 DISTANCE FROM 25 % OF LA TO 25 % OF LH . . . . . . . . . . . . . . . . . . . . . . . 13.654 m ( 537.559 in) VERTICAL TAIL REFERENCE AREA . . . . . . . . . . . . . . . . . . . . . 12.48 m2 ( 19344 in2) REF CHORD LV . . . . . . . . . . . . . . . . . . . . . . . . . 2.851 m ( 112.244 in) ASPECT RATIO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.6 DISTANCE FROM 25 % OF LA TO 25 % OF LV . . . . . . . . . . . . . . . . . . . . . . . . 12.484 m ( 491.496 in)
AUG 95
2 –00
LIMITATIONS CONTENTS
AFM
PAGE : 1
001
DGAC APPROVED
JUL 02
2 . 00 – CONTENTS 2 . 01 – GENERAL INTRODUCTION KINDS OF OPERATION MINIMUM FLIGHT CREW PERFORMANCE CONFIGURATION MAXIMUM OPERATING ALTITUDE MANEUVERING LIMIT LOAD FACTORS CONFIGURATION DEVIATION LIST NOISE CHARACTERISTICS MAXIMUM NUMBER OF PASSENGER SEATS 2 . 02 – WEIGHT AND LOADING WEIGHTS CENTER OF GRAVITY ENVELOPE LOADING 2 . 03 – AIRSPEED AND OPERATIONAL PARAMETERS AIRSPEEDS OPERATIONAL PARAMETERS 2 . 04 – POWER PLANT ENGINES PROPELLERS OIL SYSTEM STARTER FUEL SYSTEM 2 . 05 – SYSTEMS
R
AIR - PRESSURIZATION HYDRAULIC SYSTEM LANDING GEAR FLAPS AFCS INSTRUMENTS MARKING CARGO DOOR OPERATION MFC COMMUNICATIONS ELECTRICAL TCAS GPS EGPWS 2 . 06 – ICING CONDITIONS
NOV 92 APR 93 FEB 94 APR 94 JAN 95 AUG 95 SEP 97
2 –01
LIMITATIONS
PAGE : 1 AFM
GENERAL
MAY 92
001
DGAC OCT 96 APPROVED
2 . 01 . 01 – INTRODUCTION Observance of the limitations contained in this chapter is required by law. When operating in accordance with an approved appendix or supplement to this manual, the limitations of this basic Airplane Flight Manual section apply, except as altered by such an appendix or supplement.
R
2 . 01 . 02 – KINDS OF OPERATION The airplane is certified in the Transport Category, JAR 25 and ICAO annex 16 for day and night operations, in the following conditions when the appropriate equipment and instruments required by the airworthiness and operating regulations are approved, installed and in an operable condition : - VFR and IFR - Flight in icing conditions. - Reverse thrust taxi (single or twin engine) 2 . 01 . 03 – MINIMUM FLIGHT CREW 2 pilots 2 . 01 . 04 – PERFORMANCE CONFIGURATION Refer to 6.01.03 for airplane configuration associated with certified performances. 2 . 01 . 05 – MAXIMUM OPERATING ALTITUDE 25000 ft 2 . 01 . 06 – MANEUVERING LIMIT LOAD FACTORS Gear and flaps retracted : + 2.5 to – 1 g Gear and/or flaps extended : + 2 to 0 g 2 . 01 . 07 – CONFIGURATION DEVIATION LIST Refer to 7.01.02 2 . 01 . 08 – NOISE CHARACTERISTICS The aircraft meets the requirements of ICAO annex 16, Chapter 3 with no weight restriction. Refer to noise characteristics in Appendix 7.01.01 of this manual for noise levels. 2 . 01 . 09 – MAXIMUM NUMBER OF PASSENGER SEATS 74 as limited by emergency exits configuration.
Mod : –
Eng : ALL
Model : ALL
APR 93 JUN 95 AUG 95
2 –02
LIMITATIONS
PAGE : 1 WEIGHT AND LOADING
AFM
NOV 92
002
DGAC APR 93 APPROVED
2 . 02 . 01 – WEIGHTS STRUCTURAL LIMITATIONS MAXIMUM WEIGHT
KG
LB
TAXI
21530
47465
TAKE–OFF
21500
47400
LANDING
21350
47068
ZERO FUEL
19700
43430
PERFORMANCE LIMITATIONS Maximum take–off weight and maximum landing weight may be reduced by performance requirements related to the following (see chapter 6) : – climb performance (first and second segment, final take–off and en route, approach and landing climb) – available runway length (take–off and landing) – tyre limit speed – brake energy limit, observe BRK TEMP light extinguished for take–off – obstacle clearance (take–off and en route) – en route and landing weight
Mod : –
Eng : ALL
Model : 201 – 202 – 211 – 212
2 –02
LIMITATIONS
MAR 93
070
PAGE : 1 WEIGHT AND LOADING
AFM
DGAC APPROVED
FEB 94
2 . 02 . 01 – WEIGHTS STRUCTURAL LIMITATIONS MAXIMUM WEIGHT
KG
LB
TAXI
22030
48567
TAKE–OFF
22000
48501
LANDING
21350
47068
ZERO FUEL
19700
43430
PERFORMANCE LIMITATIONS Maximum take–off weight and maximum landing weight may be reduced by performance requirements related to the following (see chapter 6) : – climb performance (first and second segment, final take–off and en route, approach and landing climb) – available runway length (take–off and landing) – tyre limit speed – brake energy limit, observe BRK TEMP light extinguished for take–off – obstacle clearance (take–off and en route) – en route and landing weight
R
Mod : 3651
Eng : ALL
Model : 201 – 202 – 211 – 212
2 –02
LIMITATIONS
PAGE : 2 AFM
WEIGHT AND LOADING
DGAC APPROVED
NOV 92
002 APR 93
2 . 02 . 02 – CENTER OF GRAVITY ENVELOPE For definition of reference (Mean Aerodynamic Chord (MAC) and moments origin) : see chapter 1
2 . 02 . 03 – LOADING The airplane must be loaded in accordance with the loading instructions given in the WEIGHT AND BALANCE manual.
Mod : –
Eng : ALL
Model : 201 – 202 – 211 – 212
2 –02
LIMITATIONS
PAGE : 2 AFM
WEIGHT AND LOADING
DGAC APPROVED
MAR 93
070 SEP 00
2 . 02 . 02 – CENTER OF GRAVITY ENVELOPE For definition of reference (Mean Aerodynamic Chord (MAC) and moments origin) : see chapter 1
R
2 . 02 . 03 – LOADING The airplane must be loaded in accordance with the loading instructions given in the WEIGHT AND BALANCE manual.
Mod : 3651
Model : 201 – 202 – 211 – 212
FEB 94
LIMITATIONS
2 –03 PAGE : 1
AFM
AIRSPEED AND OPERATIONAL PARAMETERS
SEP 89
001
DGAC JUL 02 APPROVED
2 . 03 . 01 – AIRSPEEDS • MAXIMUM OPERATING SPEED VMO / MMO This limit must not be intentionally exceeded in any flight regime VMO = 250 kt CAS
MMO = 0.55
• MAXIMUM DESIGN MANEUVERING SPEED VA Full application of roll and yaw controls, as well as maneuvers that involve angles of attack near the stall should be confined to speeds below VA. VA = 175 kt CAS R
CAUTION : Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed. • MAXIMUM FLAPS EXTENDED OR OPERATING SPEEDS VFE FLAPS 15 FLAPS 30
185 kt CAS 150 kt CAS
• MAXIMUM LANDING GEAR EXTENDED OR OPERATING SPEEDS VLE = 185 kt CAS VLO lowering = 170 kt CAS retracting = 160 kt CAS
LIMITATIONS
2 –03 PAGE : 2
AFM
AIRSPEED AND OPERATIONAL PARAMETERS
DGAC APR 93 APPROVED
2 . 03 . 02 – OPERATIONAL PARAMETERS ENVIRONMENTAL ENVELOPE
Note : Refer to 2.04.05 for fuel temperature limitation. TAKE–OFF AND LANDING – Tail wind limit : 15 kt – Maximum mean runway slope : ± 2 %
R
Mod : 3037+ (8044 or 3522)
Eng : ALL
NOV 92
230
Model : ALL
2 –04
LIMITATIONS
PAGE : 1 POWER PLANT
AFM
DGAC APPROVED
120 SEP 00
2 . 04 . 01 – ENGINES PRATT AND WHITNEY OF CANADA PW 124 – B Operating limits with no unscheduled maintenance action required Beyond these limits refer to maintenance manual POWER SETTING
TIME LIMIT
TQ (%)
ITT (oC)
NH (%)
NL (%)
NP (%)
OIL PRESS (PSI)
OIL TEMP (oC)
RESERVE TAKE OFF
10 mn (4)
106.3 (5)
800
102.7
104
101
55 to 65
0 to 125 (3)
TAKE OFF
5 mn
90
(1)
101
101.7
101
55 to 65
0 to 125 (3)
MAXIMUM CONTINUOUS
NONE
102.5
800
102.7
104
101
55 to 65
0 to 125 (3)
40 mini
–40 to 125 (3)
55 to 65
125 (3)
GROUND IDLE
66 mini
HOTEL MODE STARTING
715 5s
TRANSIENT
950 102.3 (2)
800
20 s
124.5
840
10 mn
106.3
OTHER
–54 mini
103.7
104.3
115
40 to 100
(1) ITT limits depend on outside air temperature. Refer to 2.04 p2 for detailed information. (2) When NP is below 86 % NOTE : Using a reduced NP, TQ may exceed 100 % but not 102.3 % (3) Temperature up to 115oC (120oC in hotel mode) is authorized without time limitation. 20 mn are authorized between 115oC (120oC in hotel mode) and 125oC. NOTE : Oil temperature must be maintained above 45oC to ensure intake strut de–icing. Oil temperature must be maintained above 71oC to ensure fuel anti– icing protection in absence of the low fuel temperature indication. (4) Time beyond 5 mn is linked to actual single engine operations only. (5) This value must be considered as acceptable overtorque value. For day to day operation refer to chapter 6.02. R
NOTE : Flight with an engine running and the propeller feathered is not permitted.
Mod : 2735
Eng : PW124
NOV 92 APR 93 FEB 94 AUG 95 SEP 99
LIMITATIONS
2 –04 PAGE : 2
AFM
POWER PLANT
DGAC APPROVED
TAKE OFF ITT LIMITS AT TAKE OFF POWER
Eng : PW124
001 SEP 89
2 –04
LIMITATIONS
PAGE : 3 POWER PLANT
AFM
DGAC APPROVED
NOV 92
001
APR 93
SEP 97
AUG 95
2 . 04 . 02 – PROPELLERS TWO HAMILTON STANDARD 14 SF 11 GROUND OPERATION H Avoid static operation between 41 % and 65 % Np H Avoid use of feather position above 47 % TQ. H Engine run up must be performed into the wind. H Do not exceed 91.7 % TQ below 30 kt except for transients of engine run up at start of take off and for brief service checks of 2 minutes or less each. H Do not exceed 91.6% NP below 30 kt except for transients , at the start of take off and for brief service checks of 2 minutes or less each. GROUND OR FLIGHT OPERATION H If a propeller is involved in an overspeed or in an engine overtorque refer to the propeller maintenance manual. FLIGHT OPERATION R
H ATR airplanes are protected against a positioning of power levers below the flight idle stop in flight by an IDLE GATE device. It is reminded that any attempt to override this protection is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power.
Eng : PW124
OCT 96
LIMITATIONS AFM
POWER PLANT
NOV 92
2 -- 04 PAGE : 4 EASA APPROVED
001 AUG 07
2 . 04 . 03 -- OIL SYSTEM SPECIFICATION Refer to specification PWA 521 type II 2 . 04 . 04 -- STARTER 3 starts with a 1 minute 30 seconds maximum combined starter running time followed by 4 minutes OFF. 2 . 04 . 05 -- FUEL SYSTEM R
Acceptable fuels : Jet A, Jet A1, JP5 and RT, TS1. Use of JP4 and Jet B is prohibited.
R
TEMPERATURE • For flight preparation, a minimum fuel temperature must be taken into account to ensure adequate relight : --34oC for fuel types JET A, JET A1 and RT, TS1. --26oC for fuel type JP5. • Maximum temperature : 57oC for fuel types JET A, JET A1, JP 5 and RT, TS1.
R
REFUELING Maximum pressure 3.5 bars (50 PSI) USABLE FUEL The total quantity of fuel usable in each tank is : 2500 kg (5510 lbs) NOTE :Fuel remaining in the tanks when quantity indicators show zero is not usable in flight. UNBALANCE Maximum fuel unbalance : 730 kg (1609 lbs) FEEDING • Each electrical pump is able to supply one engine in the whole flight envelope. • One electrical pump and associated jet pump are able to supply both engines in the whole flight envelope.
R
APR 93 DEC 93 FEB 94 AUG 95 JUL 04 JUL 05 JUL 06 SEP 06
LIMITATIONS
PAGE : 1 AFM
SYSTEMS
NOV 92
2 –05 DGAC APPROVED
001 JUL 04
2 . 05 . 01 – AIR PRESSURIZATION
AUG 95
Maximum differential pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.35 PSI Maximum negative differential pressure . . . . . . . . . . . . . . . . . . . . . – 0.5 PSI Maximum differential pressure for landing . . . . . . . . . . . . . . . . . . . . 0.35 PSI Maximum differential pressure for OVBD VALVE full open selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 PSI Maximum altitude for one bleed off operation . . . . . . . . . . . . . . . . . . 20000 ft
OCT 96 SEP 97
2 . 05 . 02 – HYDRAULIC SYSTEM Specification : Hyjet IV or Skydrol LD 4
R
2 . 05 . 03 – LANDING GEAR Towing with TOWBARLESS system is prohibited. Do not perform pivoting (sharp turns) upon a landing gear with fully braked wheels except in case of emergency. 2 . 05 . 04 – FLAPS Holding with any flaps extended is prohibited in icing conditions (except for single engine operations). 2 . 05 . 05 – AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)
R
APR 93 DEC 93 FEB 94 NOV 94 JAN 95
– Minimum height for autopilot engagement on take off : 100 ft – NAV mode for VOR approach, using either autopilot or flight director is authorized only if : – a co–located DME is available, and – DME HOLD is not selected – Minimum height for use of either autopilot or flight director : – Except during take off or executing an approach : 1000 ft – VS or IAS mode during approach : 160 ft – CAT 1 APP mode : 160 ft Refer to 7.01.03 for CAT II operation (if applicable). 2 . 05 . 06 – INSTRUMENTS MARKING Red arc or radial line : minimum and maximum limits Yellow arc : caution area Green arc : normal area
2 –05
LIMITATIONS
PAGE : 2 AFM
SYSTEMS
DGAC APPROVED
150 SEP 97
2 . 05 . 07 – CARGO DOOR OPERATION Do not operate cargo door with a lateral wind component of more than 45 kt. 2 . 05 . 08 – MFC Take off with two or more failed MFC modules is prohibited 2 . 05 . 09 – COMMUNICATIONS Not applicable
Mod : 2456
Model :102 or 202 or 212
LIMITATIONS
2 –05 PAGE : 3
AFM R
SYSTEMS
DGAC APPROVED
Date de révision antérieure
001 SEP 97
2 . 05 . 10 – ELECTRICAL Single DC GEN operation : – In flight, if OAT exceeds ISA + 25, flight level must be limited to FL200
APR 94 JAN 95 AUG 95
LIMITATIONS
2 –05 PAGE : 4
AFM
SYSTEMS
DGAC APPROVED
MAY 92
050
APR 93
SEP 01
JAN 95 AUG 95
2.05.11 – TCAS. REFER TO APPENDIX 7.01.04
SEP 97 SEP 99 SEP 00 MAR 01
R
Mod : 3074 or 3113 or 3625 or 3832 or 8259
LIMITATIONS
2 –05 PAGE : 5
AFM
SYSTEMS
DGAC APPROVED
Date de révision antérieure
500 SEP 03
2 . 05 . 11 – GPS 1 – GENERAL The Honeywell/Trimble GNSS 1000 : - complies with TSO C 129 and TSO C115B, - is installed in compliance with FAA AC 20–129, AC 20–130A, AC 20–138 and DGAC CRI S–9902, - has been demonstrated to meet the requirements of JAA TGL no2,REV1 and FAA AC 20–138 and FAA Notice N8110–60. - has been demonstrated to meet the P–RNAV requirements of JAA TGL no10. 2 – LIMITATIONS Compliance with the above regulations does not constitute an operational approval/authorization to conduct operations. Aircraft operators must apply to their Authority for such an approval/authorization. - The HT1000 pilot’s guide must be available on board. - The system must operate with HT 1000–060 software version or any later approved version. - The approval of the system is based on the assumption that the navigation database has been validated for intended use. - This equipment is approved for use as : - primary navigation means for oceanic and remote operations when only one long range navigation system is required. - supplemental navigation means, en route, in terminal area and for non precision approach operations until the missed approach point with respect of the MDA. NOTE : Stand alone GPS approach is not approved. Conventional means must be permanently cross–checked during the approach. - advisory VNAV means NOTE : VDEV function must be permanently monitored. 3 – PROCEDURES - In the event of DGR alarm illumination the flight crew must cross–check the aircraft position using conventional means or must revert to an alternative means of navigation. - In addition, where the coupled DME option is not installed or if the coupled DME is not operative, the following procedures apply for B–RNAV operations : (a) during the pre–flight planning phase, the availability of GPS integrity (RAIM) must be confirmed for the intended flight (route and time). Dispatch must not be made in the event of predicted continuous loss of RAIM of more than 5 minutes for any part of the intended flight. (b) Traditional navigation equipment must be selected to available aids so as to allow immediate cross–checking or reversion in the event of loss of GPS navigation capability.
Mod : 5403
LIMITATIONS
2 –05 PAGE : 6
AFM
SYSTEMS
EASA APPROVED
JUL 02
020 JUL 05
2 . 05 . 13 – EGPWS 1. Navigation is not to be predicated on the use of the terrain display. NOTE : The Terrain display is intended to serve as a situational awareness tool only. It does not have the integrity, accuracy or fidelity on which to solely base decisions for terrain or obstacle avoidance. 2.To avoid giving nuisance alerts, the predictive TAWS functions must be inhibited when landing at an airport that is not included in the airport database.
R
Mod : 5313 or 5467
LIMITATIONS
2 –06 PAGE : 1
AFM
ICING CONDITIONS
DGAC APPROVED
001 MAY 99
2 . 06 . 01 – ICING CONDITIONS • Atmospheric icing conditions exist when – OAT on the ground and for take–off is at or below 5oC or when TAT in flight is at or below 7oC, – and visible moisture in any form is present (such as clouds, fog with visibility of less than one mile, rain, snow, sleet and ice crystals). • Ground icing conditions exist when – OAT on the ground is at or below 5oC, – and surface snow, standing water or slush is present on the ramps taxiways and runways. Take–off is prohibited when frost, snow or ice is adhering to the wings, control surfaces or propellers. R
R
Ć Operation in atmospheric icing conditions : NP setting below 86 % is prohibited. All icing detection lights must be operative prior to flight at night . NOTE :This supersedes any relief provided by the Master Minimum Equipment List (MMEL). The ice detector must be operative. Refer to 3.04.01 for associated procedures and 6.06.02 for performance data. Ć Operation in ground icing conditions : Refer to 3.04.01 for associated procedures and to FCOM part 3 and to AFM section 7.03 for advisory information on contaminated runways penalties.
.../...
DEC 89 FEB 94 JAN 95 24 JAN 95 JUN 95 AUG 95 OCT 96 FEB 99
LIMITATIONS
PAGE : 2 AFM
ICING CONDITIONS
DEC 96 FEB 99
2 –06 DGAC APPROVED
001 JUL 04
2 . 06 . 01 – ICING CONDITIONS (cont’d) Ć Severe icing : WARNING : Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build–up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane. – During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following : R
Visual cue identifying severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window and / or Unexpected decrease in speed or rate of climb. and / or The following secondary indications : . Water splashing and streaming on the windshield . Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. . Accumulation of ice on the lower surface of the wing aft of the protected area. . Accumulation of ice on the propeller spinner farther aft than normally observed. The following weather conditions may be conductive to severe in–flight icing: . Visible rain at temperatures close to 0_C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0_C ambient air temperature (SAT) If one of these phenomena is observed, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. Apply procedure specified in the Emergency Procedures chapter. – Since the autopilot may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when the severe icing defined above exists, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions.
NORMAL PROCEDURES CONTENTS
AFM
3 . 00 -- CONTENTS 3 . 01 -- COCKPIT PREPARATION CHECKS ENGINE FIRE PROTECTION TRIMS ENGINE CVR / DFDR 3 . 02 -- DAILY CHECKS
R
ATPCS TEST STICK PUSHER / SHAKER TEST TRIMS 3 . 03 -- TAKE OFF 3 . 04 -- FLIGHT CONDITIONS ICING CONDITIONS SEVERE TURBULENCE HEAVY RAIN 3 . 05 -- APPROACH AND LANDING NORMAL LANDING MISSED APPROACH 3 . 06 -- CONTAINER TRANSPORTATION
R
3 . 07 -- GPWS OR EGPWS
3 -- 00 PAGE : 1 EASA APPROVED
001 JUL 06
MAY 92 FEB 94 SEP 97
NORMAL PROCEDURES
3 –01 PAGE : 1
AFM
COCKPIT PREPARATION CHECKS
DGAC APPROVED
001 SEP 03
3 . 01 . 01 – ENGINE FIRE PROTECTION – Check ENG 2 (1) fire handle IN and latched – Extinguish any white lt – Depress SQUIB TEST pb and check both AGENT SQUIB lt illuminate – Select TEST sw on FIRE and check : . ENG FIRE red lt illuminates into associated fire handle . CCAS is activated (CRC + MW lt flashing red + ENG 2 (1) red lt on CAP)
– Select TEST sw on FAULT and check : . both LOOP A and LOOP B FAULT lt illuminate . CCAS is activated (sc + MC lt flashing + LOOP amber lt on CAP) 3 . 01 . 02 – TRIMS R
Before each flight : – Check PITCH, ROLL and YAW TRIM operation – Check STBY PITCH TRIM operation, check GUARDED SW in OFF position See Daily Check in 3–02 page 1 3 . 01 . 03 – ENGINE Turn ATPCS to ARM – CHECK ATPCS ARM green light illuminates Turn ATPCS to ENG position – CHECK associated ENG UPTRIM light illuminates – 2.15 s later check ATPCS ARM light extinguishes. 3 . 01 . 04 – CVR / DFDR – CVR Depress TEST pb : check pointer moves to a location between 8 and 10 – DFDR Check STATUS amber lights not lit.
DEC 89 OCT 96
3 –02
NORMAL PROCEDURES
PAGE : 1 DAILY CHECKS
AFM
NOV 92
001
DGAC SEP 03 APPROVED
3 . 02 . 01 – ATPCS TEST (autofeather and uptrim while engines run) Conditions : – Both CLs between MAX and MIN RPM – Both PLs at GI – ATPCS pb depressed. OFF extinguished. – PWR MGT selector on TO position ARM positions
– ARM light illuminates green – TORQUE indications increase – NP and NH indications decrease
ENG positions
– Selected engine torque decreases below 21 % – Opposite engine : – Torque doesn’t change – UPTRIM light illuminates – NP and NH increase slightly – 2.15 seconds later : – concerned propeller is automatically feathered – ARM green light extinguishes.
CAUTION :Do not perform ENG TEST while taxiing as ACW is temporarily lost and consequently, both main hyd. pumps are temporarily lost as well. 3 . 02 . 02 – STICK PUSHER / SHAKER TEST – Release gust lock – Push Control column in nose down position – Select WARN rotary selector (LH maintenance panel) to STICK PUSHER YES – depress and maintain PTT – monitor stall cricket and stick shaker – after ten seconds delay, monitor . CHAN 1 and CHAN 2 illuminate green on LH maintenance panel . STICK PUSHER lights illuminate green on both pilots panel . stick pusher actuator operates. 3 . 02 . 03 – TRIMS R
For the first flight of the day : – Check PITCH, ROLL and YAW TRIM operation as follows : –Check the normal TRIM activation in both directions by depressing –simultaneously both control rocker switches –For few seconds depress independently each single control rocker switch and check the non–activation of the corresponding TRIM in both possible directions – Reset TRIMS as required for take off Eng : PW124
APR 93 AUG 95
NORMAL PROCEDURES
3 –03 PAGE : 1
TAKE OFF
AFM
NOV 92
001
DGAC APR 93 APPROVED
3 . 03 . 01 – TAKE OFF – Anti–skid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . test – Set flaps 150 and pitch trim as required – ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . As required – PWR MGT selectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO – CL both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM
BOTH EEC’s ON – Advance PL to power lever notch. – At VR rotate to the required pitch attitude to maintain an airspeed at or above V2. – When a positive vertical speed is confirmed, select landing gear up. – At safe height : accelerate up to at least VFTO (flaps 0o) retract flaps
Mod :
–
Eng : ALL
Model : ALL
NORMAL PROCEDURES
3 –04 PAGE : 1
AFM
FLIGHT CONDITIONS
DGAC APPROVED
SEP 89
001 SEP 00
3 . 04 . 01 – ICING CONDITIONS • DEFINITION Refer to 2 .06 .01 J Procedure for operation in atmospheric icing conditions : • As soon as and as long as atmospheric icing conditions exist, the following procedures must be applied : ANTI–ICING (propellers, horns, side–windows) . . . . . . . . . . . . . . . . ON PROP MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . According to SAT NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set w 86 % Minimum maneuver/operating icing speed . . . . . . . . . . . . . . . . . . . . . . . . . . BUGGED AND OBSERVED ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR NOTE : horns anti icing selection triggers the illumination of the ”ICING AOA” green light, and lowers the AOA stall warning threshold. R
• At first visual indication of ice accretion and as long as atmospheric icing conditions exist, the following procedure must be applied : – ENG START rotary selector . . . . . . . . . . . . . . . . . . . . CONT RELIGHT – ANTI ICING (propellers, horns, side windows) . . . . . . CONFIRM ON – DE ICING ENG 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON – AIRFRAME DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON – Eng and airframe MODE SEL . . . . . . . . . . . . . ACCORDING TO SAT – Minimum maneuver/operating icing speed . . . . . . . . . . . . . . CONFIRM BUGGED AND OBSERVED NOTE : Be alert to severe icing detection. In case of severe icing refer to Emergency Procedures 4.05.05.
R
• When leaving icing conditions, CONT RELIGHT, DE ICING and ANTI ICING may be switched OFF. • When the aircraft is visually verified clear of ice, ICING AOA caption may be cancelled and normal speeds may be used. NOTE : Experience has shown that the last part to clear is the ice evidence probe. As long as this condition is not reached the icing speeds must be observed and the ICING AOA caption must not be cancelled.
APR 93 FEB 94 JAN 95 JUN 95 AUG 95 OCT 96 FEB 99 MAY 99
0
3 –04
NORMAL PROCEDURES
NOV 92
130
APR 93
SEP 98
FEB 94
PAGE : 2 FLIGHT CONDITIONS
AFM
DGAC APPROVED
• MINIMUM MANEUVER / OPERATING ICING SPEEDS : Whenever ICING AOA light is lit, the following minimum icing speeds must be observed :
FLAPS
MINIMUM MANEUVER / OPERATING ICING SPEED
MAXIMUM BANK ANGLE
0
1.43 VS1G
15o
15
1.21 VS1G
T/O, 2nd segment
15o
1.38 VS1G
En route
15o
1.44 VS1G
APPROACH
30o
1.23 VS1G
GO AROUND
15o
30
30o
1.30 VS1G
CAUTION :For obstacle clearance, the en–route configuration with engine failure is FLAPS 150 at a minimum speed of 1.38 VS1G if ice accretion is observed. J Procedure for take–off with ground icing conditions but no atmospheric icing conditions : • For take off the following procedure MUST BE APPLIED : ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . CONT RELIGHT PROP ANTI ICING ONLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON NOTE : It is recommended when possible to cycle landing gear after take off. • Minimum maneuver/operating speeds : The normal minimum maneuver/operating speeds are applicable. R
Refer to FCOM part 3 and AFM section 3 for information on contaminated runways penalties. NOTE :Horns anti icing must not be selected ON to avoid lowering AOA of the stall warning threshold.
Mod : 1368
Eng : PW124
OCT 96
NORMAL PROCEDURES
3 –04 PAGE : 3
FLIGHT CONDITIONS
AFM
001
DGAC SEP 89 APPROVED
3 . 04 . 02 – SEVERE TURBULENCE – ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . CONT RELIGHT – SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Maintain the speed at or below VRA : 180 kt CAS. 3 . 04 . 03 – HEAVY RAIN – ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . CONT RELIGHT
Mod :
–
Eng : ALL
Model : ALL
NORMAL PROCEDURES
3 –05 001
PAGE : 1 AFM
APPROACH AND LANDING
DGAC APPROVED
SEP 00
3 . 05 . 01 – NORMAL LANDING
R
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 LANDING gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN/3 GREEN TLU GREEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LIT FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO ENG START rotary selector . . . . . . . . . . . CONT RELIGHT (if required) D Before landing NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86 %
R
D After nose wheel touch down Both PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI Both LO PITCH lights . . . . . . . . . . . . . . . . . . . . Check illuminated CAUTION :If a thrust dissymmetry occurs or if one LO PITCH light is not illuminated the use of any reverser is not allowed. 3 . 05 . 02 – MISSED APPROACH (both power plants operating) – Depress Go around push button on PLs. – Set Go around power. – Simultaneously retract flaps one notch and rotate to the required pitch attitude. – Accelerate to or maintain Go around speed. – With positive rate of climb : – Retract landing gear
Eng : PW124
NOV 92 APR 93 AUG 95 OCT 96 SEP 97 DEC 97 SEP 98
NORMAL PROCEDURES
3 –06 PAGE : 1
AFM
R
CONTAINER TRANSPORTATION
3 . 06 . 01 – CONTAINER TRANSPORTATION NOT APPLICABLE
DGAC APPROVED
MAY 92
001 SEP 97
3 –07
NORMAL PROCEDURES
PAGE : 1 GPWS
AFM
DGAC APPROVED
040 JUL 04
3 . 07 . 01 GROUND PROXIMITY WARNING SYSTEM : EGPWS 1. General Following a EGPWS warning, the crew must immediately focus their attention on terrain proximity. Positive action to alter the flight path or / and to change the configuration should be initiated immediately. 2. Inputs EGPWS is associated with the following systems : • ADC 1 • Radio altimeter • ILS 2 • SGU 1 and 2 • Flaps position • Landing gear position • GNSS (if installed) or EGPWS internal GPS card • AHRS 1 • Weather radar 3. Outputs 3.1. Basic GPWS modes - For modes 1 – 2 – 3 and 4 • Visual warning : red ”GPWS” lights illuminate. • Aural warning : Mode 1”SINK RATE” “PULL UP” Mode 2 : ”TERRAIN” PULL UP” Mode 3 : ”DON’T SINK” Mode 4 : According to speed and / or flaps / gear setting : ”TOO LOW TERRAIN” or ”TOO LOW GEAR” or ”TOO LOW FLAPS” - For mode 5 • Visual warning : amber ”GS” lights illuminate. • Aural warning : ”GLIDE SLOPE” - For mode 6 • Aural warning : ”MINIMUMS” ”MINIMUMS”. • Aural warning : “FIVE HUNDRED” • Aural warning : “BANK ANGLE, BANK ANGLE”
Mod : 5467
3 –07
NORMAL PROCEDURES
PAGE : 2 AFM
GPWS
DGAC APPROVED
040 JUL 04
3 . 07 . 01 GROUND PROXIMITY WARNING SYSTEM : EGPWS (CONT’D) 3.2. Enhanced modes - For TCF mode (Terrain Clearance Floor) • Visual warning : red GPWS lights illuminate • Aural warning : “TOO LOW Terrain” - For TAD (Terrain Awareness & Display) mode • Visual warning : red GPWS lights illuminate • Aural caution : “Terrain ahead – terrain ahead” or “Obstacle ahead – Obstacle ahead” warning : “Terrain ahead – Pull Up” or “Obstacle ahead – Pull up” • EFIS display : conflicting terrain in red or yellow. 4 – Operation - During normal operations GPWS sw should be always set on ”NORM” position and TERR pb must be depressed in. - In case of emergency conditions GPWS sw and TERR pb may be turned on ”OFF” position. Refer to chapter 4.05, Ditching and forced landing. - In case of landing in abnormal flaps conditions GPWS sw may be turned on ”OVRD” position, refer to chapter 5.04, flight controls. - Terrain/Obstacle Awareness Caution. When a terrain awareness CAUTION occurs, verify the aeroplane flight path and correct it if required. If in doubt, perform a climb until the CAUTION alert ceases. - Terrain/Obstacle Awareness Warning. If a terrain awareness WARNING occurs, immediately initiate and continue a climb that will provide maximum terrain clearance until all alerts cease. Only vertical manoeuvres are recommended, unless operating in visual meteorological conditions (VMC), and/or the pilot determines, based on available information, that turning in addition to the vertical escape manoeuvre is a safer course of action. Notes - All modes are inhibited by stall warning. - Mode 5 is active only when ILS2 is tuned on the correct frequency and gear down. - GPWS or TERR FAULT illumination indicates that some or all basic or enhanced modes are lost. In that case, the remaining alerts must be considered as valid and taken into account. - If the WX radar control is selected OFF, no terrain information will be displayed on the EHSI and TERR FAULT amber light will be illuminated. Even in case of a radar failure, select the STBY position. Mod : 5467
EMERGENCY PROCEDURES CONTENTS
AFM
4 -- 00 PAGE : 1 EASA
APPROVED
4 . 00 -- CONTENTS 4 . 01 -- INTRODUCTION 4 . 02 -- POWER PLANT R
ENG FIRE OR SEVERE MECHANICAL DAMAGE BOTH ENGINES FLAME OUT 4 . 03 -- SMOKE
R
SMOKE ELECTRICAL SMOKE AIR COND SMOKE FWD SMOKE AFT SMOKE AUX AFT COMPT SMOKE 4 . 04 -- ELECTRICAL SYSTEM DUAL DC GEN LOSS 4 . 05 -- MISCELLANEOUS EMERGENCY DESCENT DITCHING FORCED LANDING ON GROUND EMERGENCY EVACUATION SEVERE ICING
001 AUG 07
EMERGENCY PROCEDURES
4 –01 PAGE : 1
AFM
INTRODUCTION
DGAC APPROVED
001 SEP 89
– The following procedures have been established and recommended by the aircraft manufacturer and approved by the Airworthiness Authorities for application in the event of a serious failure. – The framed items correspond to actions performed by memory by the crew within a minimum period of time. – It is assumed that in general, all failures are indicated by the operation of specific system warnings and/or by direct observation. – The actions recommended may result in the loss of certain systems not associated with the failure. – If actions depend on a precondition, a preceding black square J is used to identify the precondition. – Whenever a procedure calls for LAND AS SOON AS POSSIBLE, the seriousness of the situation as well as use of the nearest suitable airport should be taken into consideration. – However, whenever fire is encountered on the airplane, landing at the nearest suitable airport is recommended. After conducting any fire suppression/smoke evacuation procedure, even though smoke has been dissipated, if it has not or cannot be visibly verified that the fire has been put out, immediately land at the nearest suitable airport. – Whenever a fire extinguisher is discharged in the cockpit, the crew should go to 100 % oxygen.
Mod : –
Eng : ALL
Model : ALL
EMERGENCY PROCEDURES AFM
POWER PLANT
4 -- 02 PAGE : 1 EASA
APPROVED
001 AUG 07
4 . 02 . 01 -- ENGINE FIRE OR SEVERE MECHANICAL DAMAGE R
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL F After 10 seconds FIRST AGENT affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH NOTE : On ground, do not wait 10 seconds before discharging the agent J If fire after further 30 seconds SECOND AGENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH LAND AS SOON AS POSSIBLE
EMERGENCY PROCEDURES AFM
POWER PLANT
4 -- 02 PAGE : 2 EASA
APPROVED
001 AUG 07
4 . 02 . 02 -- BOTH ENGINES FLAME OUT R
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . CONT RELIGHT PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI J If NH drops below 30% (no automatic relight) CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO NOTE : See engine relight envelope (chapter 5) J If neither engine starts FORCED LANDING or DITCHING . . . . . . . . . . . . . . . . . . . . . . . . PREPARE
EMERGENCY PROCEDURES AFM
R
SMOKE
4 -- 03 PAGE : 1 EASA APPROVED
001 AUG 07
4 . 03 . 00 -- SMOKE CREW OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / 100% GOGGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH RECIRC FANS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON SMOKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY J If source not identified or electrical smoke suspected NOTE: ELEC light may be activated by an air conditioning smoke source ELECTRICAL SMOKE procedure (4.03.01) . . . . . . . . . . . . . . . . . . APPLY J If air conditioning smoke identified AIR CONDITIONING SMOKE procedure (4.03.02) . . . . . . . . . . . . APPLY J If FWD SMK illuminated or smoke in FWD zone of aircraft FWD SMOKE procedure (4.03.03) . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If AFT SMK illuminated or smoke in AFT zone of aircraft AFT SMOKE procedure (4.03.04) . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If AUX AFT COMPT SMK illuminated (depending on models) AUX AFT COMPT SMOKE procedure (4.03.05) . . . . . . . . . . . . . . APPLY 4 . 03 . 01 -- ELECTRICAL SMOKE AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH DC SVCE AND UTLY BUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL ACW GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF SUSPECTED EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF J If smoke origin not identifed LAND AS SOON AS POSSIBLE • When ∆ P < 1 PSI OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . NORM
EMERGENCY PROCEDURES AFM
SMOKE
4 -- 03 PAGE : 2 EASA
APPROVED
001 AUG 07
4 . 03 . 02 -- AIR CONDITIONING SMOKE R
PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA J If smoke persists PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PACK VALVE 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . . . . CAREFULLY MONITOR J If any anomaly occurs such as : -- amber engine warning illumination associated to local ITT alert -- total loss of NL indication -- engine abnormality clearly identified (NH, NL, ITT indications, noise, surge...) WARNING : Confirm which engine is showing signs of abnormal operation in order to avoid shutting down the safe engine. PL afffected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL afffected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO SINGLE ENG OPER PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
EMERGENCY PROCEDURES AFM
R
SMOKE
4 -- 03 PAGE : 3 EASA APPROVED
002 AUG 07
4 . 03 . 03 -- FWD SMOKE 1) PASSENGERS VERSION CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH EXTRACT AIR FLOW LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED CABIN CREW WITH PORTABLE EXTINGUISHER LOCATE AND KILL SOURCE OF SMOKE • When ∆ P < 1 PSI OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . NORM 2) CARGO VERSION CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE ENG 2 BLEED (except when in single bleed operation) . . . . . . . . . . . . . OFF PACK VALVE 2 (except when in single pack operation) . . . . . . . . . . . . . OFF CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT CAUTION : LAND ASAP -- If a quick landing is not possible : climb and maintain minimum FL 160, FL 200 is recommended. NOTE : Smoke alert may be generated during smoke evacuation process.
Model : 102 -- 202 -- 212
EMERGENCY PROCEDURES AFM
SMOKE
4 -- 03 PAGE : 4 EASA
APPROVED
001 AUG 07
4 . 03 . 04 -- AFT SMOKE R
1) PASSENGERS VERSION CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE FOR ACTION AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH 2) CARGO VERSION CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE ENG 2 BLEED (except when in single bleed operation) . . . . . . . . . . . . . OFF PACK VALVE 2 (except when in single pack operation) . . . . . . . . . . . . . OFF CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT CAUTION : LAND ASAP -- If a quick landing is not possible : climb and maintain minimum FL 160, FL 200 is recommended. NOTE : Smoke alert may be generated during smoke evacuation process.
R
EMERGENCY PROCEDURES AFM
R
SMOKE
4 -- 03 PAGE : 5 EASA APPROVED
001 AUG 07
4 . 03 . 05 -- AUX AFT COMPT SMOKE (IF APPLICABLE) AUX AFT COMPT AGENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCHARGE
EMERGENCY PROCEDURES AFM
ELECTRICAL SYSTEM
4 -- 04 PAGE : 1 EASA
APPROVED
001 AUG 07
4 . 04 . 01 -- DUAL DC GEN LOSS R
DC GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON J If no generator recovered LAND ASAP MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . OVBD BAT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD CAPT EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE :NAV lights switch set to ON is necessary to provide IEP illumination STICK PUSHER/SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF STICK PUSHER/SHAKER FAULT PROCEDURE . . . . . . . . . . . . APPLY SIDE WINDOWS ANTI--ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HF (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ADC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET TO ADC 1 ATC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET TO ATC 1 TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE LO SPD F When TLU LO SPD illuminates TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO CAUTION : Avoid large rudder input if IAS above 180 kt. MAIN BATTERY CHARGE (on LH maintenance panel) . . . . . . CHECK BUS EQPT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK J If STBY BUS UNDV light illuminates STBY BUS . . . . . . . . . . . . For approach, OVRD only when necessary F Before descent PAX INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
EMERGENCY PROCEDURES ELECTRICAL SYSTEM
AFM
4 -- 04 PAGE : 1 EASA
APPROVED
160 AUG 07
4 . 04 . 01 -- DUAL DC GEN LOSS R
DC GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON J If no generator recovered TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Make sure that TRU arrow illuminates and BAT arrows extinguish. MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . OVBD BAT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD CAPT EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE :NAV lights switch set to ON is necessary to provide IEP illumination STICK PUSHER/SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF STICK PUSHER/SHAKER FAULT PROCEDURE . . . . . . . . . . . . APPLY SIDE WINDOWS ANTI--ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ADC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET TO ADC 1 ATC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET TO ATC 1 TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE LO SPD F When TLU LO SPD illuminates TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO CAUTION : Avoid large rudder input if IAS above 180 kt. BUS EQPT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK F Before descent PAX INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
Mod : 1603
EMERGENCY PROCEDURES AFM
MISCELLANEOUS
4 -- 05 001
PAGE : 1 EASA
APPROVED
AUG 07
4 . 05 . 01 -- EMERGENCY DESCENT R
OXY MASKS / CREW COMMUNICATIONS . . . . . . . . . . . . . . . AS RQD GOOGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE PL 1+ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . CONT RELIGHT OXY PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD SPEED . . . . . . MMO / VMO (or less if structural damage is suspected) SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY MEA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
EMERGENCY PROCEDURES AFM
MISCELLANEOUS
4 -- 05 PAGE : 2 EASA APPROVED
001 AUG 07
4 . 05 . 02 -- DITCHING R
F Preparation ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TERR (If Enhanced GPWS installed) . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN and COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE AUTO PRESS -- LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . SET F Approach J If ∆P ≠ 0 AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP PACKS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE FLAPS (If available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP F 30 seconds before impact or 1250 ft above sea level DITCH PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG START ROTARY SELECTOR . . . . . . . . . . OFF / START ABORT CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN F Before ditching (200 ft) MINIMIZE IMPACT SLOPE OPTIMUM PITCH ATTITUDE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . 90 BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE : In case of night ditching, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). F After ditching NOTE : After ditching, one aft door will be under the water line. CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE F Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
EMERGENCY PROCEDURES AFM
MISCELLANEOUS
4 -- 05 PAGE : 3 EASA APPROVED
001 AUG 07
4 . 05 . 03 -- FORCED LANDING R
F Preparation ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TERR (If Enhanced GPWS installed) . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN and COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE AUTO PRESS -- LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . SET F Approach FLAPS (If available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP ENG START ROTARY SELECTOR . . . . . . . . . . OFF / START ABORT CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN F Before impact (200 ft) BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE : In case of night forced landing, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). F After impact, when aircraft stopped CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE F Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
EMERGENCY PROCEDURES AFM
MISCELLANEOUS
4 -- 05 PAGE : 4 EASA APPROVED
001 AUG 07
4 . 05 . 04 -- ON GROUND EMERGENCY EVACUATION R
AIRCRAFT / PARKING BRAKE . . . . . . . . . . . . . . . . . . . STOP / ENGAGE ATC (VHF 1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO MIN CAB LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD ENG START ROTARY SELECTOR . . . . . . . . . . . . OFF / START ABORT FUEL PUMPS 1+ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE F Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
EMERGENCY PROCEDURES
4 –05 PAGE : 5
AFM
MISCELLANEOUS
001
DGAC SEP 03 APPROVED
4 . 05 . 05 – SEVERE ICING R MINIMUM ICING SPEED . . . . . . . . . . . . . . . . . INCREASE RED BUG by 10 kt PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT CL / PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% / MCT AP (if engaged) . . . . . . FIRMLY HOLD CONTROL WHEEL and DISENGAGE SEVERE ICING CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESCAPE ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
H If an unusual roll response or uncommanded roll control movement is observed : Push firmly on the control wheel FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
H If the flaps are extended, do not retract them until the airframe is clear of ice
H If the aircraft is not clear of ice : GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD STEEP SLOPE APPROACH (4.5_) . . . . . . . . . . . . . . . . . . . PROHIBITED APP/LDG CONF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN FLAPS 15 . . . . . . . . . . . . . . . . . with “REDUCED FLAPS APP/LDG icing speeds” + 5 kt Multiply landing distance FLAPS 30 by 1.91
.../...
Eng : PW124
JAN 95 JUN 95 AUG 95 FEB 99 MAY 99
EMERGENCY PROCEDURES
4 –05 PAGE : 6
AFM
MISCELLANEOUS
001
DGAC SEP 03 APPROVED
4 . 05 . 05 – SEVERE ICING (CONT’D) R DETECTION Visual cue identifying severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window and / or Unexpected decrease in speed or rate of climb and / or The following secondary indications : . Water splashing and streaming on the windshield . Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice . Accumulation of ice on the lower surface of the wing aft of the protected areas . Accumulation of ice on propeller spinner farther aft than normally observed The following weather conditions may be conducive to severe in–flight icing : . Visible rain at temperatures close to 0_C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0_C ambient air temperature (SAT)
OCT 96 FEB 99 MAY 99 SEP 99
PROCEDURES FOLLOWING FAILURES
5 –00 PAGE : 1
CONTENTS
AFM
001
DGAC AUG 95 APPROVED
5 . 00 – CONTENTS 5 . 01 – INTRODUCTION 5 . 02 – ENGINE ENGINE FLAME OUT ENG OIL LO PR EEC FAULT ENG RELIGHT ENVELOPE ENG RESTART IN FLT ENG NAC OVHT 5 . 03 – FLYING WITH ONE ENGINE INOPERATIVE TAKE OFF APPROACH AND LANDING MISSED APPROACH 5 . 04 – SYSTEMS
R
FUEL ELECTRICAL SYSTEM HYDRAULIC SYSTEM FLIGHT CONTROLS LANDING GEAR AIR ICE AND RAIN PROTECTION MFC AUTOPILOT MISCELLANEOUS
Mod : –
Eng : ALL
Model : ALL
AUG 91 JAN 95
PROCEDURES FOLLOWING FAILURES
5 –01 PAGE : 1
AFM
INTRODUCTION
SEP 89
001
DGAC FEB 94 APPROVED
– The procedures contained in this chapter have been established and recommended by the aircraft manufacturer and approved by the Airworthiness Authorities as acceptable procedures for a proper use of the aircraft. – They give information related to system and operational requirements and cover the actions to be followed in case of failures which are not considered as emergency cases (these cases are covered in chapter 4). R
– If actions depend on a precondition, a preceding black square is used to identify the precondition. – Only particular operations, which are considered useful to highlight are presented. Those procedures which are considered to be “basic airmanship” are therefore not covered.
Mod : –
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
AFM
ENGINE
5 -- 02 PAGE : 1 EASA
APPROVED
MAY 92
001 AUG 07
5 . 02 . 01 -- ENGINE FLAME OUT ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . CONT RELIGHT PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI H If NH drops below 30 % (no immediate relight) CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR then FUEL SO H If damage suspected FIRE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL 5 . 02 . 02 -- ENG OIL LO PR PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI H If both OIL LO PR alert on CAP and local alert are activated CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR then FUEL SO H If local alert only is activated CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR then FUEL SO Once engine is shut off H If CONT RELIGHT is required by current flight conditions maintain it ON as long as necessary and keep the affected engine shut off. Apply SINGLE ENG OPER PROC H When CONT RELIGHT is not required by flight conditions. CONT RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR H If CCAS is activated after 30 s. CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO ENG RESTART IN FLIGHT PROC . . . . . . . . . . . . . . . . . . . . . . APPLY H If not CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO SINGLE ENG OPER PROC . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY H If CCAS only is activated DISREGARD INFORM MAINTENANCE NOTE : TCAS must be set on TA only when one engine inoperative.
R
5 . 02 . 03 -- EEC FAULT ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF H If PL is out of green sector Do not deselect affected EEC When adequate, retard PL to green sector H If PL is within green sector Affected EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET H If unsuccessful EEC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Advance PL to restore power, handling throttle with care. • In final approach CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM • After landing Taxi with the affected engine feathered Mod : 3074 or 3113 or 3625
APR 93 AUG 95 OCT 96 SEP 97 SEP 99 SEP 06
PROCEDURES FOLLOWING FAILURES
5 –02 PAGE : 2
AFM
ENGINE
DGAC APPROVED
FEB 94
001 SEP 97
5 . 02 . 04 – ENG RELIGHT ENVELOPE
5 . 02 . 05 – ENG RESTART IN FLT
R
FUEL SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI ENG START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START EEC . . . . . . . . . RESET IF NECESSARY OR DESELECT if FAULT persists. START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON At 10 % NH CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR CL then PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO OTHER ENGINE ENG START rotary selector . . . . . . . OFF START ABORT/CONT RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (as required) NOTE : After ATPCS sequence PWR MGT rotary selector must be set to MCT position before engine restart in order to cancel propeller feathering. 5 . 02 . 06 – ENG NAC OVHT • DURING HOTEL MODE OPERATION PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
PROCEDURES FOLLOWING FAILURES
5 –02 PAGE : 3
AFM
ENGINE
DGAC APPROVED
SEP 89
001 SEP 97
• DURING TAXI Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOP Increase slightly power JIf unsuccessfull within 30 s PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
PROCEDURES FOLLOWING FAILURES
5 –03 PAGE : 1
AFM
FLYING WITH ONE ENGINE INOPERATIVE
DGAC APPROVED
SEP 89
001 OCT 96
5 . 03 . 01 – TAKE–OFF R
" REJECTED TAKE OFF (engine flame out before V1) Immediately and simultaneously : BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAXIMUM PL both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI / REVERSE " TAKE OFF WITH ENGINE FLAME OUT BETWEEN V1 AND V2. – At VR rotate to the safe pitch attitude. – With a positive vertical speed . retract landing gear . use rudder and control wheel to control aircraft heading maintaining aircraft wings essentially levelled. – Climb at V2 – At acceleration altitude : . deselect both bleeds (if previously selected) . accelerate up to 1.18 VS1G (flaps 00) . retract the flaps . continue climb at this speed selecting MCT on the PWR MGT rotary selector on expiry of RTO power limiting time. CAUTION : RTO POWER IS ONLY ALLOWED FOR 10 MINUTES " ENGINE FLAME OUT DURING INITIAL CLIMB OUT – Proceed as above however, if the flame out occurs above V2 it is recommended to maintain the speed reached without exceeding V2 + 10 Kt. In any case the minimum speed must be equal to V2.
Mod : –
Eng : ALL
Model : ALL
APR 93 AUG 95
PROCEDURES FOLLOWING FAILURES
5 –03 PAGE : 2
AFM
FLYING WITH ONE ENGINE INOPERATIVE
MAY 92
001
DGAC AUG 95 APPROVED
5 . 03 . 02 – APPROACH AND LANDING BLEED both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Select normal approach and landing configurations. NOTE : At touch down, do not reduce below FI before nose wheel is on the ground. 5 . 03 . 03 – MISSED APPROACH Apply normal missed approach procedure (3.05.02). R
At acceleration altitude proceed as for a take off with engine flame out between V1 and V2 (5.03 p 1).
Mod : –
Eng : ALL
Model : ALL
APR 93
PROCEDURES FOLLOWING FAILURES
PAGE : 1 SYSTEMS
AFM
SEP 89 SEP 97
5 –04 DGAC APPROVED
001 JUL 04
5 . 04 . 01 – FUEL " FEED LO PR PUMP associated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ON ENGINE associated . . . . . . . . . . . . . . . . . . . . Monitor for possible run down. JIf engine runs down or if fuel quantity decreases significantly CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR then FUEL SO PUMP associated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FIRE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL " LO LVL AVOID EXCESSIVE AIRCRAFT ATTITUDES R
" FUEL LEAK
ALERT CONDITION A fuel leak may be detected by either : -sum of fuel on board (FOB), read in steady flight at cruise level, and fuel used (FU), FOB+FU significantly less than fuel at departure or -passenger observation (fuel spray from engine or wing tip) or -total fuel quantity decreasing at an abnormal rate, or -fuel imbalance, or -a tank emptying too fast (leak from engine or a hole in a tank),or -excessive fuel flow (leak from engine), or -fuel smell in the cabin DWhen a leak is confirmed LAND ASAP JLeak from engine (excessive fuel flow or feed spray from engine) PL (ON AFFECTED ENGINE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL (ON AFFECTED ENGINE) . . . . . . . . . . . . . . . FTR THEN FUEL SO PUMP ASSOCIATED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FIRE HANDLE (ON AFFECTED ENGINE) . . . . . . . . . . . . . . . . . . . PULL SINGLE ENG OPERATION PROCEDURE . . . . . . . . . . . . . . . . APPLY JIf excessive fuel flow was identified before engine shutdown, FUEL X FEED valve can be opened JIn all other cases, FUEL X FEED valve must remain closed JLeak not located FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN CLOSED NOTE :FUEL X FEED valve must remain closed to prevent the leak affecting both sides BEFORE LANDING, NOTIFY ATC
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 2
AFM
SYSTEMS
DGAC APPROVED
SEP 89
001 SEP 97
5 . 04 . 02 – ELECTRICAL SYSTEM " DC GEN FAULT DC GEN affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Taxi on both engines J If OAT exceeds ISA + 25 MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 200
R
" DC BUS 1 OFF DC GEN 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CM2 CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN • At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL " DC BUS 2 OFF DC GEN 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CM1 VHF1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ADC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET TO ADC 1 • Before descent PAX INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA Taxi on both engines " DC EMER BUS OFF LEAVE AND AVOID ICING CONDITIONS DESCENT TOWARD FL 100 / MEA STBY PITCH TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . USED AS REQUIRED ADC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Set to ADC 2 HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
R
J If ice accretion builds up on airframe DE–ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD J In case of engine flame out OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE PROPELLERS ANTI ICING FAULT PROC . . . . . . . . . . . . . . . . APPLY HORNS ANTI ICING FAULT PROC . . . . . . . . . . . . . . . . . . . . . . APPLY • Before landing NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI–SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI–SKID FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY • After landing DIFFERENTIAL BRAKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
APR 93 AUG 95
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 3
SYSTEMS
AFM
DGAC APPROVED
001 OCT 96
CHG FAULT CHG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF DUAL CHG LOSS MFC modules . . . . . . . . . . . . . . . . . . . . . . . . ONE AT A TIME OFF / RESET
If unsuccessful LAND ASAP If conditions permit, minimize use of VHF1.
SVCE & UTLY BUS SHED SVC & UTLY BUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED AC BUS 2 OFF PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CM1
R
ACW GEN FAULT ACW GEN affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Taxi on both engines LEAVE AND AVOID ICING CONDITIONS ACW BUS OFF ACW GEN affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Associated AIRSPEED IND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON LEAVE AND AVOID ICING CONDITIONS Taxi on both engines
R
ACW TOTAL LOSS ACW GEN both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF LEAVE AND AVOID ICING CONDITIONS Affected equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Capt and F/O AIRSPEED IND . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR MAIN HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Landing gear normal EXT and normal BRK . . . . . . . . . . . . . . . . . . . . LOST LDG DIST flaps 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Multiply by 1.5 Before landing L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . As required L/G GRAVITY EXTENSION PROCEDURE . . . . . . . . . . . . . . APPLY Taxi on both engines Mod : –
Eng : ALL
Model : ALL
SEP 89 AUG 95
PROCEDURES FOLLOWING FAILURES
5 –04 001
PAGE : 4 AFM
SYSTEMS
DGAC APPROVED
SEP 89
5 . 04 . 03 – HYDRAULIC SYSTEM " HYD TK COMPT LO LEVEL PUMP (S) associated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE :
J If blue system is affected – flaps – nose wheel steering – propeller brake – spoilers are lost. For emergency / parking brake, the brake accumulator allows at least six applications of braking force at full braking pressure. J If green system is affected – normal braking – landing gear normal extension/retraction are lost.
" HYD LO PR / HYD OVHT PUMP affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON " BOTH MAIN HYD PUMPS LOSS MAIN PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE : Spoilers and landing gear extension and retraction are lost. LGD DIST FLAPS 300 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Multiply by 1.5 • Before landing L/G lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS 150 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD LDG GEAR GRAVITY EXT PROC . . . . . . . . . . . . . . . . . . . . . . . . . APPLY FLAPS 300 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD • After touch down FULL REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IF NECESSARY BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD TAXI ON BOTH ENGINES
Mod : –
Eng : ALL
Model : ALL
5 –04
PROCEDURES FOLLOWING FAILURES
PAGE : 5 SYSTEMS
AFM
R
EASA APPROVED
NOV 92
001
APR 93
JUL 05
SEP 97 SEP 03
5 . 04 . 04 – FLIGHT CONTROLS " REDUCED FLAPS LANDING GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . PROHIBITED FLAPS
LDG DIST FLAPS 30 MULTIPLY BY
APP SPD
0 15
1.9 1.8
1.23 VS1G (0) + 5 kt + wind effect 1.23 VS1G (15) + wind effect
" FLAPS UNLOCKED J During TO D Before V1 TAKE OFF ABORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE D After V1 VR, V2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE BY 10 KT J During approach GA POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE BY 10 KT " FLAPS ASYM FLAPS CONTROL LEVER . . . . . . . NEAR FLAPS PRESENT POSITION REDUCED FLAP LANDING PROC . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY " ELEVATOR JAMMING CONTROL COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNCOUPLE AVOID ICING CONDITIONS MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT J If one elevator is stuck to full down position MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154 KT J If left elevator is jammed : MINIMUM MANEUVER OPERATING SPEED . . . . . . . . INC BY 10 KT J Elevator jamming on take off MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KT PITCH DISCONNECT PROCEDURE . . . . . . . . . . . . . . . . . . . . . . APPLY " PITCH TRIM INOPERATIVE MAINTAIN EXISTING CONFIGURATION AND SPEED AS LONG AS POSSIBLE D For approach EXTEND FLAPS AT VFE FOR EACH CONFIGURATION LANDING SPEED . . . . . . . . . . . . . . . . . . . . . INCREASE BY 10 kt LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.13 " STICK PUSHER / SHAKER FAULT STICK PUSHER/SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MINIMUM MANEUVER OPERATING SPEED . . . . INCREASE BY 10 KT LANDING DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.13 Eng : PW124
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 6
AFM
R
SYSTEMS
EASA APPROVED
001
AUG 91 FEB 94 SEP 98
JUL 05
" PITCH DISCONNECT AVOID ICING CONDITIONS CHECK BOTH CONTROL COLUMNS FREE MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 kt MAX LOAD FACTOR : 2 g BANK ANGLE MUST BE RESTRICTED TO 30_ until flaps extension STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . PROHIBITED VAPP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INC BY 10 kt LANDING DISTANCE FLAPS 30 . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.13 LAND AT AIRPORT WITH MINIMUM CROSSWIND REDUCE SMOOTHLY TO FLARE " TLU FAULT H If both ADC are lost H IAS above 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD H IAS below 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD DISREGARD TLU FAULT ALERT H If at least one ADC operates H IAS above 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD H If TLU FAULT alarm persists MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD H IAS below 185 kt MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD H If TLU green light is not lit VAPP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INC BY 10 kt Landing distance flaps 30 . . . . . . . . . . . . . . . . . multiply by 1.13 LAND AT AIRPORT WITH MINIMUM CROSSWIND NOTE : Maximum demonstrated cross wind on dry runway with TLU in high speed position : 15 kt " AILERON JAMMING BANK ANGLE LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25_ BLUE HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LAND AT AIRPORT WITH MINIMUM CROSSWIND SELECT BLUE HYD PUMP ON BEFORE FLAPS EXTENSION THEN SELECT IT OFF AS WELL AS HYD AUX PUMP DO NOT EXTEND FLAPS IN TURN • After touch down BLUE HYD PUMP and HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . ON
SEP 03
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 7
AFM
SYSTEMS
DGAC APPROVED
MAY 92
001 SEP 98
" SPOILER JAMMING BLUE HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LAND AT AIRPORT WITH MINIMUM CROSSWIND SELECT BLUE HYD PUMP ON BEFORE FLAPS EXTENSION THEN SELECT IT OFF AS WELL AS HYD AUX PUMP • After touch down BLUE HYD PUMP and HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . ON " RUDDER JAMMING Use differential power to minimize side slip. Land at airport with minimum crosswind. • At touch down NOSE DOWN BEFORE REDUCTION BELOW FI
R R
" RUDDER RELEASABLE CENTERING UNIT FAILURE H If YD is available YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE H If YD is not available KEEP THE FEET ON THE PEDALS " PITCH TRIM ASYM PITCH TRIM INOPERATIVE PROCEDURE . . . . . . . . . . . . . . . . . . . APPLY NOTE : AP automatically disengages and cannot be reengaged.
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 8
AFM
SYSTEMS
DGAC APPROVED
001 MAY 92
5 . 04 . 05 – LANDING GEAR " L/G UNSAFE INDICATION • L/G selected DOWN – GREEN LT OFF on one panel only UNSAFE INDICATION . . . . . . . . . . . . . . . . . DISREGARD – GREEN LT OFF on both panels L/G GRAVITY EXT . . . . . . . . . . . . . . . . . . . . . . . . . APPLY • L/G selected UP – RED LT ON on one panel only UNSAFE INDICATION . . . . . . . . . . . . . . . . . DISREGARD – RED or GREEN LT ON on both panels MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160 kt L/G . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN " L/G GRAVITY EXT L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXT HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL " L/G RETRACTION IMPOSSIBLE L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN MAX SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185 kt
R R R
" ANTI SKID FAULT LANDING DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.4 • At touch down USE FULL REVERSE if necessary. USE NORM BRK with care or BRK HANDLE . . . . . . . . . . . . . . EMER " BRK TEMP HOT • Before take off DELAY TAKE OFF • In flight LEAVE L/G DOWN FOR 1 mn AFTER TAKE–OFF FOR COOLING EXCEPT IN CASE OF EMERGENCY
Mod : –
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 9
AFM
SYSTEMS
DGAC APPROVED
001 SEP 00
5 . 04 . 06 – AIR " BLEED VALVE FAULT / BLEED VALVE OVHT PACK VALVE affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 200 AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDE " BLEED LEAK PACK VALVE affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 200 AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDE CAUTION : Do not restore the system in flight " PACK VALVE FAULT PACK VALVE affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 200 AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDE " DUCT OVHT TEMP SEL affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN COMPT TEMP SELECTOR associated . . . . . . . . . . . . . . . . . . . . . . COLD
R
" EXCESS CAB ALT OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD H If rapid decompression EMERGENCY DESCENT PROCEDURE . . . . . . . . . . . . . . . . . APPLY " AUTO PRESS FAULT CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN Adjust manually cabin pressure " EXCESS CAB Δ P CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INC H If unsuccessful DESCENT TO COMPATIBLE FL . . . . . . . . . . . . . . . . . . . . . . . INITIATE
AUG 91 SEP 98
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 10
SYSTEMS
AFM
DGAC APPROVED
MAY 92
130
APR 93 JAN 95
SEP 98
AUG 95 OCT 96
5 . 04 . 07 – ICE AND RAIN PROTECTION
R
R
" PROP ANTI ICING FAULT PROP ANTI ICING affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LEAVE AND AVOID ICING CONDITIONS H If propeller unbalance due to ice becomes excessive CL (both) . . . . . . . . . . . . . . . . . . . . . . . . . MOVE TO MAX RPM for 5 mn " HORNS ANTI ICING FAULT LEAVE AND AVOID ICING CONDITIONS H If icing conditions, every 5 mn FLIGHT CONTROLS associated . . . . . . . CHECK FREEDOM OF MOVEMENT
" ENG DE ICING FAULT LEAVE AND AVOID ICING CONDITIONS Associated ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . MONITOR
R
R
" AIRFRAME AIR BLEED FAULT LEAVE AND AVOID ICING CONDITIONS AIRFRAME AIR BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF H If ENG DE ICING FAULT illuminates after 10 s ENG DE ICING (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AIRFRAME AIR BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AIRFRAME FAULT . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED H If ENG DE ICING FAULT does not illuminate after 10 s MINIMUM ICING SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . INC BY 10 kt WHEN REACHING VAPP CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM LANDING DISTANCE (icing conditions, flaps 30) . . . . . . . . . . . . Multiply by 1.13
" AIRFRAME DE ICING FAULT AIRFRAME DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LEAVE AND AVOID ICING CONDITIONS MINIMUM ICING SPEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . INC BY 10 kt LANDING DISTANCE (icing conditions, flaps 30) . . . . . . . . Multiply by 1.13 " DE ICING MODE SEL FAULT DE ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD
R
NOTE : monitor de–icing : H In case of engine flame out OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE
Mod : 1368
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 11
SYSTEMS
AFM
DGAC APPROVED
DEC 89
001 SEP 98
5 . 04 . 08 – MFC " MFC 1A FAULT AFFECTED MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
R
" MFC 1B FAULT AFFECTED MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET HIf failure during taxi out PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN • Prior take off PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF • After take off PACKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE LEAVE L/G DOWN FOR COOLING FOR 1 mn AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY • After landing PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN HIf failure in flight or after landing • After landing PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened.
FEB 94
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 12
AFM
R
SYSTEMS
DGAC APPROVED
DEC 89
001 SEP 98
" MFC 2A FAULT AFFECTED MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . OVBD HIf failure during taxi out OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN • After take off IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO • At touchdown IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • After landing OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN HIf failure in flight or after landing • At touchdown IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • After landing OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN " MFC 2B FAULT AFFECTED MODULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET HIf failure during taxi out PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN • Prior take off PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF • After take off PACKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE LEAVE L/G DOWN FOR COOLING FOR 1 min AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY • After landing PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN HIf failure in flight or after landing • After landing PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened.
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 13
SYSTEMS
AFM
DGAC APPROVED
R
AUG 91
001 APR 93
" MFC 1A + 1B FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET PROP 1 ANTI–ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PROP ANTI–ICING FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . APPLY DE-ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD (AS RQD) PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF • Before landing ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CL BOTH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM • After landing OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened. " MFC 1A + 2A FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . OVBD GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AIRFRAME FAULT AMBER ALERT IS LOST WHEN AIRFRAME DE-ICING IS USED, MONITOR BOOTS INFLATION AS AP OFF ALERT IS LOST, USE OF AP BELOW 1000 ft AGL IS PROHIBITED • Before landing L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXTENSION HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL • At touch down IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • After landing OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
Mod : –
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 14
SYSTEMS
AFM
DGAC APPROVED
R
AUG 91
001 APR 93
" MFC 1A + 2B FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET DE-ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD (AS RQD) • Before landing FLAPS CONTROL IS LOST REDUCED FLAP LDG PROC . . . . . . . . . . . . . . . . . . . . . . . . . APPLY L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXTENSION HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL • After landing PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened.
R
" MFC 1B + 2A FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET DE-ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD (AS RQD) AVIONIC VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD • Before landing FLAPS CONTROL IS LOST REDUCE FLAP LDG PROC . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXTENSION HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL CAUTION : GEAR CANNOT BE RETRACTED • At touch down IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • After landing PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened.
Mod : –
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 15
SYSTEMS
AFM
DGAC APPROVED
R
AUG 91
001 APR 93
" MFC 2A + 2B FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET AVIONIC VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD PROP 2 ANTI-ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PROP ANTI-ICING FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY DE-ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD (AS RQD) PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY • Before landing ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CL BOTH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX RPM • At touch-down IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • After landing OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened. " MFC 1B + 2B FAULT AFFECTED MODULES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET OVERHEAD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR • Before landing NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI SKID FAULT PROC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY L/G LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXTENSION HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL CAUTION : GEAR CANNOT BE RETRACTED • At touch down IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL DIFFERENTIAL BRAKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE • After landing PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HORNS ANTI-ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN CAUTION : Before opening any door, Packs 1 and 2 must be selected OFF and cockpit communication hatch must be opened.
Mod : –
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 16
AFM
R
SYSTEMS
DGAC APPROVED
JAN 95
090 AUG 95
5 . 04 . 09 – AUTOPILOT " PITCH MISTRIM AP . . . . . . . . . . . . . DISCONNECT HOLDING FIRMLY THE CONTROLS FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS. " PITCH TRIM FAIL AP . . . . . . . . . . . . . DISCONNECT HOLDING FIRMLY THE CONTROLS FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS. " If any unusual situations are observed such as : • excessive lateral trim required • illumination of the AILERON MISTRIM message on the ADU • abnormal flight characteristics of the airplane AP . . . . . . . . . . . . . DISCONNECT HOLDING FIRMLY THE CONTROLS AND FLY MANUALLY PRIOR TO ADJUSTING THE LATERAL TRIMS. The autopilot may be reengaged following adjustment of the lateral trims.
Mod : 3168
Eng : ALL
Model : ALL
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 17
AFM
SYSTEMS
DGAC APPROVED
001 SEP 98
5 . 04 . 10 – MISCELLANEOUS " ADC FAULT ADC SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . non affected side PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . non affected side R
H If both ADC’s are lost TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE STBY INST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF " ADC DISAGREEMENT INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK VALID ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECTED FAULTY ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF " ADC SW FAULT ADC sw . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Set to opposite ADC " AHRS FAULT ATT / HDG SWITCHING affected side . . . . . . . . . . . . . . . . . . . . . . . . . . ON Compare periodically remaining AHRS outputs to STBY INST. " FIRE LOOP FAULT LOOP affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF " OXYGEN LO PR MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON
R
H If oxygen LO PR light remains lit MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Oxygen portable unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Use if required " ADU FAULT AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAY 90 JAN 95 AUG 95 OCT 96
PROCEDURES FOLLOWING FAILURES
5 –04 PAGE : 18
AFM
SYSTEMS
DGAC APPROVED
001 SEP 99
" EFIS COMPARISON BOTH EADI, STBY HORIZON . . . . . . . . . . . . . . . . . . . . . CROSS CHECK WRONG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY AHRS non affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT WRONG AHRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF R
H If AHRS 1 is WRONG, pull C/B ATT/HDG AHRS 1 “NORM SPLY” and “AUX SPLY”
R
H If AHRS 2 is WRONG, pull C/B ATT/HDG AHRS 2 “NORM SPLY” and “AUX SPLY FLT”
DEC 89 FEB 94 JAN 95 AUG 95
6 –00
PERFORMANCE
PAGE : 1 CONTENTS
AFM
DGAC APPROVED
MAY 92
001 SEP 97
6 . 00 – CONTENTS 6 . 01 – GENERAL R
INTRODUCTION STALL SPEEDS – VS1G AIRPLANE CONFIGURATION CROSS WIND DETERMINATION OF WIND COMPONENTS CALIBRATION SPEED AND ALTITUDE 6 . 02 – ENGINE MANAGEMENT 6 . 03 – TAKE OFF DEFINITION PERFORMANCE DETERMINATION DETERMINATION OF MAXIMUM TAKE OFF WEIGHT FOR A GIVEN RUNWAY ALTITUDE – SPEED – BANK ANGLE TURN RADIUS : RELATIONSHIPS 6 . 04 – SINGLE ENGINE CRUISE DEFINITION EN ROUTE NET GRADIENT 6 . 05 – LANDING DEFINITION PERFORMANCE DETERMINATION 6 . 06 – ATMOSPHERIC ICING CONDITIONS INTRODUCTION FLIGHT IN ATMOSPHERIC ICING CONDITIONS
FEB 94
PERFORMANCE
6 –01 PAGE : 1
AFM
GENERAL
DGAC APPROVED
SEP 89
001 FEB 94
6 . 01 . 01 – INTRODUCTION In compliance with Airworthiness regulations, an aircraft is cleared to take off from any airport if the weight allows it to achieve the take off, “en route” and landing performance included in this chapter. The curves or tables approved by Airworthiness Authority must not be extrapolated. Performance is related to VS1G (see page 2) Wind speed is measured at the height of 10 meters. R
All weight, altitude, temperature and speed limits presented on section 2 – LIMITATIONS – must be observed for the utilization of the performance charts.
Mod : –
Eng : ALL
Model : ALL
PERFORMANCE
PAGE : 2 AFM
R
GENERAL
6 . 01 . 02 – STALL SPEEDS – VS1G
Eng : PW124
NOV 92
6 –01 DGAC APPROVED
001 SEP 97
APR 93 OCT 96
PERFORMANCE
6 –01 001
PAGE : 3 GENERAL
AFM
DGAC APPROVED
FEB 94
6 . 01 .03 – AIRPLANE CONFIGURATION The take off and landing performances has been established on a smooth, dry, hard surfaced runway. The performances have been established in the following configuration. Single engine operation is considered. FLAPS
AIR COND
ENG POWER
REMARKS ATPCS ON
TAKE OFF
150
ON / OFF
TO / RTO
FINAL TAKE OFF
00
OFF
MCT
EN ROUTE
00
OFF / ON
MCT
APPROACH
150
OFF
For go around RTO
LANDING
300
OFF
Accelerate stop distance established using only wheel normal braking system, antiskid ON, PL at GI.
Landing distances established with antiskid ON, PL at GI
6 . 01 . 04 – CROSS WIND The maximum demonstrated cross wind is 35 kt.
R
Mod : –
Eng : ALL
Model : ALL
APR 93
6 –01
PERFORMANCE
PAGE : 4 AFM
GENERAL
DGAC APPROVED
6 . 01 . 05 – DETERMINATION OF WIND COMPONENTS
001 MAY 92
6 –01
PERFORMANCE
PAGE : 5 AFM
GENERAL
DGAC APPROVED
001 SEP 89
6 . 01 . 06 – CALIBRATION SPEED AND ALTITUDE CRUISE No correction to be applied on altitude. Correction to be applied on speed : Δ V = IAS – CAS = 2 kt TAKE OFF – APPROACH – LANDING The following graphs give the correction to be applied when flaps are extended.
Mod : –
Eng : ALL
Model : ALL
PERFORMANCE
6 –01 PAGE : 6
AFM
GENERAL
DGAC APPROVED
R
SPEED CORRECTION (FLAPS 15) PILOT & COPILOT ADC OUTPUT ERROR IN GROUND EFFECT Δ V = IAS – CAS
R
SPEED CORRECTION (FLAPS 15) STAND BY STATIC SOURCE ERROR IN GROUND EFFECT Δ V = IAS – CAS
Mod : –
Eng :
ALL
SEP 89
001 OCT 96
Model : ALL
6 –01
PERFORMANCE
PAGE : 7 AFM
GENERAL
DGAC APPROVED
R
TAKE-OFF – GO AROUND (FLAPS 15) SPEED CORRECTION PILOT & COPILOT ADC OUTPUT ERROR Δ V = IAS – CAS
R
TAKE-OFF – GO AROUND (FLAPS 15) SPEED CORRECTION STAND BY SOURCE ERROR Δ V = IAS – CAS
Mod : –
Eng : ALL
Model : ALL
SEP 89
001 OCT 96
PERFORMANCE
6 –01 PAGE : 8
AFM
R
GENERAL
FINAL APPROACH – LANDING (FLAPS 30) SPEED CORRECTION PILOT & COPILOT ADC OUTPUT ERROR Δ V = IAS – CAS
DGAC APPROVED
OCT 96
001 SEP 97
PERFORMANCE
6 –01 PAGE : 9
AFM R
GENERAL
FINAL APPROACH – LANDING (FLAPS 30) SPEED CORRECTION STAND BY STATIC SOURCE ERROR Δ V = IAS – CAS
DGAC APPROVED
SEP 89
001 SEP 97
OCT 96
6 –01
PERFORMANCE
PAGE : 10 AFM
GENERAL
DGAC APPROVED
TAKE-OFF – GO AROUND (FLAPS 15) ALTITUDE CORRECTION PILOT & COPILOT OUTPUT ERROR Δ Zp = Zpi – Zp
R
R
Mod : –
Eng : ALL
Model : ALL
SEP 89
001 OCT 96
6 –01
PERFORMANCE
PAGE : 11 AFM
R
GENERAL
DGAC APPROVED
TAKE-OFF – GO AROUND (FLAPS 15) ALTITUDE CORRECTION STAND BY STATIC SOURCE ERROR Δ Zp = Zpi – Zp
R
Mod : –
Eng :
ALL
Model : ALL
SEP 89
001 OCT 96
6 –01
PERFORMANCE
PAGE : 12 AFM
R
GENERAL
DGAC APPROVED
FINAL APPROACH – LANDING (FLAPS 30) ALTITUDE CORRECTION PILOT & COPILOT OUTPUT ERROR Δ Zp = Zpi – Zp
001 SEP 97
SEP 89 OCT 96
6 –01
PERFORMANCE
PAGE : 13 AFM
R
GENERAL
DGAC APPROVED
FINAL APPROACH – LANDING (FLAPS 30) ALTITUDE CORRECTION STAND BY SOURCE ERROR Δ Zp = Zpi – Zp
SEP 89
001 SEP 97
OCT 96
6 –02
PERFORMANCE
PAGE : 1 ENGINE MANAGEMENT
AFM
001
DATE REVISION ANTERIEURE
OCT 96
TAKE OFF TORQUE COMPUTED FOR VC = 50. KT
R
SAT (oC)
R
R
DGAC APPROVED
AIR COND OFF
NORMAL AIR COND ON
– 40. – 10. – 8. – 6. – 4.
PROPELLER SPEED 100 % HIGH AIR COND ON
MAY 92
PRESSURE ALTITUDE (FT) –1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
– 63. – 27. – 24. – 22. – 19.
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 89.0
90.0 90.0 89.2 88.2 87.2
– 2. 0. 2. 4. 6.
– 17. – 14. – 12. – 10. – 7.
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 89.6 88.5 87.4
88.0 87.0 85.9 84.9 83.8
86.2 85.1 84.1 83.1 82.1
8. 10. 12. 14. 16.
– 5. – 2. 0. 3. 5.
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 88.9
90.0 88.9 87.8 86.5 85.2
86.3 85.3 84.2 83.0 81.7
82.8 81.7 80.7 79.5 78.4
81.1 80.0 79.0 77.9 76.7
18. 20. 22. 24. 26.
8. 10. 13. 15. 18.
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 89.8 88.0
90.0 89.5 87.8 86.1 84.5
87.4 85.8 84.2 82.6 81.0
83.9 82.3 80.8 79.3 77.7
80.4 78.9 77.5 76.0 74.5
77.1 75.7 74.3 72.9 71.4
75.5 74.1 72.7 71.3 69.9
28. 30. 32. 34. 36.
20. 23. 25. 28. 30.
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 90.0 90.0
90.0 90.0 90.0 88.3 86.6
89.9 88.2 86.5 84.8 83.1
86.3 84.7 83.0 81.4 79.8
82.8 81.2 79.7 78.1 76.5
79.5 77.9 76.4 74.9 73.4
76.2 74.8 73.3 71.9 70.4
73.1 71.7 70.3 68.9 67.5
70.1 68.7 67.4 66.1 64.7
68.6 67.3 66.0 64.7 63.4
38. 40. 42. 44. 46.
33. 36. 38 41. 43.
90.0 90.0 88.2 86.3 84.4
88.3 86.5 84.7 82.9 81.1
84.8 83.1 81.3 79.6 77.9
81.4 79.7 78.1 76.4 74.7
78.1 76.5 74.9 73.3 71.7
75.0 73.4 71.9 70.4 68.8
71.9 70.4 69.0 67.5
69.0 67.6 66.2
66.1 64.8
63.4
62.1
48. 50. 52. 54. 55.
46. 48. 51. 53. 54.
82.6 80.7 78.8 76.9 76.0
79.3 77.5 75.7 73.9 73.0
76.1 74.4 72.7
73.1 71.4
70.1
Note : Applicable for 0 p Vc p 60 kt
Mod : –
Eng : PW 124
Model : ALL
6 –02
PERFORMANCE
050
PAGE : 2 ENGINE MANAGEMENT
AFM
DGAC APPROVED
DATE REVISION ANTERIEURE
OCT 96
APR 93
TAT (oC)
R
R
AUG 95
MAXIMUM CONTINUOUS TORQUE COMPUTED FOR VC = 120. KT
R
PROPELLER SPEED 100 %
AIR COND OFF
NORMAL AIR COND ON
HIGH AIR COND ON
– 43. – 40. – 37. – 33. – 29.
– 56. – 52. – 48. – 44. – 40.
– 67. – 63. – 59. – 55. – 50.
– 25. – 21. – 17. – 13. – 10.
– 36. – 32. – 28. – 24. – 20.
– 5. – 2. 1. 4. 8.
PRESSURE ALTITUDE (FT) 0.
2000.
4000.
6000.
8000.
10000.
12000.
14000.
16000.
18000.
20000.
22000.
24000.
25000.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 99.6 97.9 96.0
94.9 93.3 91.8 90.2 88.5
87.3 85.9 84.4 83.0 81.4
80.4 79.0 77.7 76.4 74.9
74.2 73.0 71.7 70.5 69.2
68.2 67.1 66.0 64.9 63.6
62.6 61.6 60.6 59.5 58.4
60.0 59.0 58.0 57.0 55.9
– 46. – 42. – 38. – 33. – 29.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 99.7 97.9 96.1 94.3
94.0 91.9 90.2 88.6 86.9
86.6 84.7 83.1 81.6 80.1
79.7 77.9 76.5 75.1 73.7
73.3 71.7 70.4 69.1 67.8
67.7 66.2 65.0 63.8 62.6
62.3 60.9 59.8 58.7 57.6
57.1 55.9 54.9 53.9 52.9
54.7 53.5 52.6 51.6 50.6
– 16. – 12. – 8. – 4. 0.
– 24. – 20. – 16. – 11. – 7.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 99.2
100.0 98.2 96.4 94.4 91.8
92.5 90.7 89.0 87.1 84.7
85.3 83.6 82.1 80.3 78.1
78.6 77.0 75.6 74.0 72.0
72.3 70.9 69.6 68.1 66.2
66.5 65.2 64.0 62.7 61.0
61.4 60.2 59.1 57.9 56.3
56.5 55.4 54.4 53.2 51.8
51.8 50.8 49.9 48.9 47.5
49.7 48.7 47.8 46.8 45.5
11. 15. 18. 22. 25.
4. 8. 12. 16. 20.
– 2. 2. 7. 12. 16.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 98.0 94.7
97.0 95.0 92.9 90.9 87.8
89.7 87.8 86.0 84.1 81.2
82.9 81.1 79.4 77.6 75.0
76.4 74.8 73.2 71.6 69.1
70.4 68.9 67.4 66.0 63.7
64.8 63.4 62.0 60.7 58.6
59.6 58.4 57.1 55.9 53.9
55.0 53.9 52.7 51.6
50.6 49.6 48.5
46.5 45.5 44.5
44.5 43.6
29. 33. 37. 41. 44.
24. 28. 32. 36. 40.
21. 25. 29. 33. 38.
100.0 100.0 97.4 94.6 91.7
98.0 94.1 90.6 87.9 85.3
91.0 87.5 84.2 81.7 79.2
84.4 81.1 78.0 75.8 73.5
78.1 75.0 72.2 70.1 68.0
72.1 69.3 66.6 64.7
66.5 63.9 61.5
61.3 58.8
56.4
48. 52. 56. 60. 64.
44. 48. 52. 56. 60.
42. 46. 50. 54. 58.
88.9 86.0 83.2 81.6
82.6 80.0 77.3
76.8 74.3
71.2
Note : Applicable for Vc p 125 kt. Add 0.8 % for each 10 kt above 125 kt without exceeding 100.0 % torque.
Mod : 2735
Eng : PW124
Model : ALL
6 –02
PERFORMANCE
PAGE : 3 ENGINE MANAGEMENT
AFM
001
DATE REVISION ANTERIEURE
OCT 96
GO AROUND TORQUE COMPUTED FOR VC = 100. KT
R
TAT (oC)
R
R
DGAC APPROVED
PROPELLER SPEED 100 %
AIR COND OFF
NORMAL AIR COND ON
HIGH AIR COND ON
–1000.
0.
1000.
2000.
3000.
– 40. – 10. – 8. – 6. – 4.
– 63. – 27. – 24. – 22. – 19.
– 71. – 35. – 32. – 30. – 27.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
– 2. 0. 2. 4. 6.
– 17. – 14. – 12. – 10. – 7.
– 25. – 22. – 19. – 17. – 14.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
8. 10. 12. 14. 16.
– 5. – 2. 0. 3. 5.
– 12. – 9. – 7. – 4. – 1.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
18. 20. 22. 24. 26.
8. 10. 13. 15. 18.
2. 4. 7. 10. 13.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
28. 30. 32. 34. 36.
20. 23. 25. 28. 30.
16. 18. 21. 24. 27.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
38. 40. 42. 44. 46.
33. 36. 38 41. 43.
30. 32. 35. 38. 41.
100.0 100.0 98.3 96.3 94.2
48. 50. 52. 54. 56.
46. 48. 51. 53. 54.
43. 46. 49. 52. 54.
92.1 90.0 87.9 85.9 83.8
PRESSURE ALTITUDE (FT) 6000.
7000.
8000.
8500.
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 99.2
100.0 100.0 99.3 98.2 97.1
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 99.8 98.6 97.4
98.0 96.9 95.7 94.6 93.4
96.0 94.8 93.7 92.6 91.4
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 99.0
100.0 99.0 97.8 96.4 95.0
96.2 95.0 93.8 92.5 91.1
92.2 91.1 89.9 88.7 87.4
90.3 89.2 88.0 86.8 85.5
100.0 100.0 100.0 100.0 100.0
100.0 100.0 100.0 100.0 98.2
100.0 99.8 97.9 96.1 94.2
97.5 95.7 94.0 92.2 90.4
93.5 91.8 90.1 88.4 86.7
89.7 88.1 86.4 84.8 83.2
86.0 84.5 82.9 81.3 79.7
84.2 82.7 81.2 79.6 78.1
100.0 100.0 100.0 98.5 96.5
100.0 98.4 96.5 94.6 92.7
96.3 94.4 92.6 90.8 89.0
92.4 90.6 88.9 87.1 85.4
88.6 87.0 85.3 83.6 81.9
85.0 83.4 81.8 80.2 78.6
81.5 80.0 78.5 76.9 75.4
78.2 76.7 75.2 73.8 72.3
76.6 75.1 73.7 72.2 70.8
98.5 96.5 94.5 92.5 90.5
94.6 92.6 90.7 88.8 86.9
90.8 89.0 87.1 85.3 83.4
87.2 85.4 83.6 81.8 80.1
83.7 81.9 80.2 78.5 76.8
80.3 78.6 77.0 75.4 73.7
77.0 75.4 73.9 72.3
73.8 72.3 70.8
70.8 69.4
69.3 67.9
88.5 86.5 84.5 82.5 80.5
84.9 83.0 81.1 79.2
81.6 79.7 77.9
78.3 76.5
75.1
Note : Applicable for Vc p 125 kt Add 0.8 % for each 10 kt above 125 kt without exceeding 100 % torque.
Mod : –
MAY 92
Eng : PW 124
Model : ALL
4000.
5000.
PERFORMANCE
6 –03 PAGE : 1
AFM
TAKE–OFF
DGAC APPROVED
NOV 92
001 SEP 97
APR 93 FEB 94 OCT 96
6 . 03 . 01 – DEFINITION
R
SPEEDS – VMCG : Minimum control speed on ground from which a sudden failure of the critical engine can be controlled by use of primary flight controls only. The other engine being set at RTO power. – V1 : Speed at which the pilot must make the decision following failure of critical engine : . either to continue take–off . or to stop the aircraft – VR : Speed at which rotation is initiated to reach V2 at 35 ft height. – V2 : Take off safety speed reached before 35 ft height with one engine failed and providing second segment climb gradient not less than the minimum (2.4 %). – VLOF : Lift off speed. – VMCA : Minimum control speed in flight at which aircraft can be controlled with 50 bank, in case of failure of the critical engine the other being set at RTO power (take off flaps setting and gear retracted). – VFTO : Speed at the end of the take off path in the en route configuration which is not less than 1.18 VS1G and provides the manoeuvring capability specified by regulations. DISTANCES AVAILABLE RUNWAY LENGTH Length of the paved runway surface, able to accept aircraft weight in all normal operating conditions. STOPWAY Extension of runway, occasionally used for taxiing but adequate for deceleration of the aircraft in case of aborted take–off. CLEARWAY Clear area at the end of the runway which can be taken into account for take–off distance calculation. AVAILABLE ACCELERATION STOP LENGTH Sum of the available runway length and the stopway (if any). TAKE OFF DISTANCE (TOD) Distance between brakes release and 35 ft height. It has to be equal or less than the sum of available runway length and allowable clearway (if any). TAKE OFF RUN (TOR) Distance between brakes release point and half of the segment between VLOF and 35 ft height. It has to be equal to or less than the available runway length.
PERFORMANCE
6 –03 PAGE : 2
TAKE–OFF
AFM R
DGAC APPROVED
V1 LIMITED BY VMCG (FLAPS 15)
R
Mod :
–
Eng : PW124
Model : ALL
MAY 92
001 OCT 96
APR 93
PERFORMANCE
PAGE : 3 TAKE–OFF
AFM R
DGAC APPROVED
MINIMUM CONTROL SPEED IN FLIGHT – VMCA (FLAPS 15)
Mod :
–
Eng : PW124
MAY 92
6 –03
Model : ALL
001 OCT 96
APR 93 FEB 94
PERFORMANCE
6 –03 001
PAGE : 4 TAKE–OFF
AFM
DGAC APPROVED
MAY 92
TAKE OFF FLIGHT PATH IN CASE OF ENGINE FAILURE
Note : Point zero indicates the 35 ft height point on the flight path.
Mod :
–
Eng : ALL
Model : ALL
6 –03
PERFORMANCE
PAGE : 5 TAKE–OFF
AFM
DGAC APPROVED
NOV 92
001 SEP 98
6 . 03 .02 – PERFORMANCE DETERMINATION Maximum take off weight is subordinated to the following conditions – at take-off : . maximum design weight . first, second and final TO segments limitations . runway limitation . tire speed limitation . brake energy limitation . obstacle clearance – single engine cruise . obstacle clearance – at landing . approach climb limitation . runway limitation The following conditions are never limiting : . first segment climb gradient . tire speed . VMU
R
The following table defines the meaning of the distances and length taken into account for take off. Performance is related to Tq ISA – 300C If T < ISA – 300C, calculate as follows : T = ISA – 300C .
RUNWAY WITH THE FOLLOWING CHARACTERISTICS without clearway without stopway
without clearway
with clearway
with stopway
without stopway
with clearway with stopway
length
TOR
runway length runway length
to be used
TOD runway length runway length runway length runway length + clearway + clearway
to enter the manual
ASD runway length runway length runway length runway length + stopway + stopway
APR 93
PERFORMANCE
6 –03 PAGE : 5A
AFM
TAKE–OFF
DGAC APPROVED
NOV 92
001 APR 93
TAKE OFF WITH AIR CONDITIONING Take-off performances are determined with AIR CONDITIONING OFF. For take-off computations with AIR CONDITIONING ON (normal flow), the following graph must be used to calculate a fictitious OAT. This fictitious OAT has to be entered in the following pages to take into account the performance decrement. (Fictitious OAT = actual OAT + Δ T)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03 PAGE : 6
AFM
TAKE–OFF
DGAC APPROVED
NOV 92
001 APR 93
6 . 03 . 03 – DETERMINATION OF MAXIMUM TAKE OFF WEIGHT FOR A GIVEN RUNWAY
6 –03
PERFORMANCE
PAGE : 7 AFM
DGAC APPROVED
SECOND SEGMENT MAXIMUM WEIGHT AT BRAKES RELEASE TAKE OFF GRADIENT (FLAPS 15)
R R
TAKE–OFF
ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER AIR CONDITIONING OFF – ANTI/DE ICING OFF– GEAR UP
Mod : –
Eng : PW124
Model : ALL
MAY 92
001 OCT 96
6 –03
PERFORMANCE
PAGE : 8 TAKE–OFF
AFM
R
R
DGAC APPROVED
FINAL TAKE OFF (FLAPS 0) EQUIVALENT WEIGHT AT BRAKES RELEASE ONE ENGINE MAX. CONTINUOUS POWER – ONE PROPELLER FEATHERED AIR CONDITIONING OFF – ANTI/DE ICING OFF – GEAR UP
R
Mod : 2735
Eng : PW124
Model : ALL
NOV 92
120 OCT 96
APR 93
PERFORMANCE
6 –03 PAGE : 9
AFM
R R
TAKE–OFF
DGAC APPROVED
MAY 92
001 OCT 96
TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT R. T. O. POWER AFTER CRITICAL ENGINE FAILURE – AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
R
Mod : –
Eng : PW 124
Model : ALL
6 –03
PERFORMANCE
PAGE : 10 AFM
R
R
TAKE–OFF
DGAC APPROVED
MAY 92
001 OCT 96
REQUIRED TAKE OFF RUN (FLAPS 15) ALL ENGINES OPERATING TWO ENGINES AT T/O POWER AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
R
Mod : –
Eng : PW124
Model : ALL
6 –03
PERFORMANCE
PAGE : 11 TAKE–OFF
AFM
R
DGAC APPROVED
TAKE OFF RUN CORRECTIONS (FLAPS 15)
R
Mod : 8044 or 3522
Eng :
ALL
Model : ALL
NOV 92
080 OCT 96
APR 93
PERFORMANCE
6 –03 PAGE : 12
AFM
DGAC APPROVED
001 OCT 96
TAKE OFF DISTANCE (FLAPS 15)
R R
TAKE–OFF
MAY 92
ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER AFTER CRITICAL ENGINE FAILURE – AIR CONDITIONING OFF – ANTI/DE ICING OFF NO RUNWAY SLOPE – NO WIND
R
Mod : –
Eng : PW 124
Model : ALL
6 –03
PERFORMANCE
PAGE : 13 AFM
DGAC APPROVED
OCT 96
REQUIRED TAKE OFF DISTANCE (FLAPS 15) ALL ENGINES OPERATING
R
R
TAKE–OFF
MAY 92
001
TWO ENGINES AT T/O POWER AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
R
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03 PAGE : 14
TAKE–OFF
AFM
DGAC APPROVED
TAKE – OFF DISTANCE CORRECTIONS (FLAPS 15)
R
R
Mod :
8044 or 3522
Eng :
ALL
Model : ALL
NOV 92
080 OCT 96
APR 93
6 –03
PERFORMANCE
PAGE : 15 AFM
TAKE–OFF
DGAC APPROVED
001 SEP 99
ACCELERATE STOP DISTANCE (FLAPS 15) R
TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
MAY 92 OCT 96
PERFORMANCE
6 –03 PAGE : 16
AFM
R
TAKE–OFF
DGAC APPROVED
ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
R
Mod : 8044 or 3522
Eng :
ALL
Model : ALL
NOV 92
080 OCT 96
APR 93
PERFORMANCE
6 –03 PAGE : 17
TAKE–OFF
AFM
DGAC APPROVED
PERFORMANCE – TAKE OFF – DECISION SPEED LIMITED BY MAXIMUM BRAKE ENERGY (FLAPS 15)
R
R
Mod :
–
Eng : PW 124
Model : ALL
MAY 92
001 OCT 96
6 –03
PERFORMANCE
PAGE : 18 TAKE–OFF
AFM
DGAC APPROVED
ROTATION SPEED – VR (FLAPS 15)
R
ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER EFFECT OF AIR BLEED ON VR IS NEGLIGIBLE
R
Mod :
–
Eng : PW 124
Model : ALL
AUG 91
001 OCT 96
6 –03
PERFORMANCE
PAGE : 19 AFM
TAKE–OFF
DGAC APPROVED
TAKE OFF SPEED – V2 (FLAPS 15)
R
ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER
R
Mod : –
Eng : PW124
Model : ALL
001 OCT 96
MAY 92
6 –03
PERFORMANCE
MAY 92
001
PAGE : 20 AFM
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE ON T/O (EXAMPLE) see chart page 22 Initial gradient : 3 % (associated to the weight limited by the runway condition) Obstacle : 4000 ft at 21 km of the end of the runway. 10 kt nose wind. NOTE : The obstacle height and distance with respect to reference zero must be determined. In the flight manual charts reference zero is the point 35 ft below the end of the TOD and the flight paths shown include the 35 ft operational clearance. Where the TOD is greater (less) than the runway length the obstacle distance from end of the runway must be decreased (increased) by the difference between TOD and runway length. 1. Place the obstacle (point A). In this example the TOD is initially assumed equal to runway length. 2. Replace the obstacle according to the wind (point C) drawing a parallel to the gross height lines. 3. The path intersects the obstacle in B. 4. Determine the gradient allowing the clearance taking into account the decrease in TOD associated to the decrease in weight. This gives point D. 5. Follow the path up to the end of the 2nd segment. 6. The point E gives the second segment gradient which determines maximum weight allowing clearance of the obstacle. 7. To be precise, the take–off distance corresponding to this new maximum weight must be calculated. R
8. Using this distance, replace the obstacle and check that it will be cleared, if not restart the calculation.
Mod : –
Eng : ALL
Model : ALL
FEB 94 AUG 95
PERFORMANCE
6 –03
AUG 91
001
PAGE : 21 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES) V2 / VS1G = 1.13 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03
MAY 92
001
PAGE : 22 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES) V2 / VS1G = 1.13 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03
MAY 92
001
PAGE : 23 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES) V2 / VS1G = 1.20 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03 001
PAGE : 24 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES) V2 / VS1G = 1.20 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
MAY 92
PERFORMANCE
6 –03
MAY 92
001
PAGE : 25 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES) V2 / VS1G = 1.25 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03
MAY 92
001
PAGE : 26 AFM
R
TAKE–OFF
DGAC APPROVED
OCT 96
OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES) V2 / VS1G = 1.25 (FLAPS 15)
Mod : –
Eng : PW124
Model : ALL
PERFORMANCE
6 –03
MAY 92
001
PAGE : 27 AFM
R
R
R
TAKE–OFF
DGAC APPROVED
OCT 96
NOT APPLICABLE Consequently pages from 28 to 30 –001 are intentionaly missing in this manual.
Mod : –
Eng : PW124
Model : ALL
APR 93
PERFORMANCE
6 –03 001
PAGE : 31 AFM
TAKE–OFF
DGAC APPROVED
OCT 96
6 . 03 . 04 – ALTITUDE – SPEED – BANK ANGLE – TURN RADIUS : RELATIONSHIPS
Mod : –
Eng : ALL
Model : ALL
PERFORMANCE
6 –03 PAGE : 32
AFM
TAKE–OFF
DGAC APPROVED
BANK ANGLE EFFECT ON SINGLE ENGINE CLIMB GRADIENT (FLAPS 15)
Mod : –
Eng : ALL
Model : ALL
MAY 92
001 OCT 96
APR 93
6 –04
PERFORMANCE
PAGE : 1 AFM
SINGLE ENGINE CRUISE
DGAC APPROVED
NOV 92
001 APR 93
6 . 04 . 01 – DEFINITIONS The “En route” gradient given in this chapter are established by decreasing the available gradient at each point with a margin of 1.1 %. The single engine cruise configuration is flaps 00. The speed to be maintained is 1.18 VS1G. The operative engine is set at MCT power. Air conditioning is ON when aircraft is above 10000 ft. Air conditioning is OFF when aircraft is below 10000 ft.
Mod : –
Eng : ALL
Model : ALL
6 –04
PERFORMANCE
PAGE : 2 AFM
SINGLE ENGINE CRUISE
DGAC APPROVED
ONE PROPELLER FEATHERED – ONE ENGINE : MCT POWER AIR CONDITIONING OFF BELOW 10000 ft – ANTI/DE ICING OFF
R
Eng : PW 124
DATE REVISION ANTERIEURE NOV 92 FEB 94
V / VS1G = 1.18 (FLAPS 0)
Mod : 2735
OCT 96
APR 93
6 . 04 . 02 – EN ROUTE NET GRADIENT
R
120
Model : ALL
PERFORMANCE
6 –05 PAGE : 1
LANDING
AFM
DGAC APPROVED
NOV 92
001 FEB 94
6 . 05 . 01 – DEFINITION VMCL : Minimum flight speed at which aircraft can be controlled with 50 bank in case of failure of the critical engine, the other being set at GA power (landing flaps setting, gear extended)and which provides rolling capability specified by regulations. FLAPS
VMCL (CAS)
300 150
90 kt 94 kt
6 . 05 . 02 – PERFORMANCE DETERMINATION – Landing climb performance (two engines at GA power, landing flaps setting) is never limiting. – The landing distance represents the distance from the 50 ft to complete stop on a level, smooth, dry, hard surfaced runway. Antiskid is operative. Engines are at GI. R
– To determine the required runway length for landing, apply national operational regulations.
Mod :
–
Eng : PW124
Model : ALL
APR 93
PERFORMANCE
6 –05 PAGE : 2
AFM
LANDING
DGAC APPROVED
NOV 92
001
APR 93
OCT 96
FEB 94
Approach speeds The approach speed is at least 1.23 VS1G in the configurations : – flaps 150 – flaps 300 or VMCL, whichever is higher. The regulations allows to take approach speed up to 1.4 VS1G. The minimum final approach speed is the speed at 50ft height taken into account for landing distance computation. It is equal to 1.23 VS1G in the landing configuration or VMCL, whichever is higher.
R
Mod : –
Eng : PW124
Model : ALL
6 –05
PERFORMANCE
PAGE : 3 AFM
DGAC APPROVED
APPROACH CLIMB GRADIENT APPROACH CLIMB LIMITING WEIGHT (FLAPS 15)
R R
LANDING
ONE PROPELLER FEATHERED – ONE ENGINE : GO AROUND POWER AIR CONDITIONING OFF – ANTI/DE ICING OFF – GEAR UP
Mod : –
Eng : PW124
Model : ALL
001 OCT 96
MAY 92
6 –05
PERFORMANCE
PAGE : 4 AFM
LANDING
DGAC APPROVED
LANDING DISTANCE (FLAPS 30) R
INCREASE BY 15% ON FORESEEN WET RUNWAY
Eng : PW124
MAY 92
001 SEP 97
FEB 94
SEP 89
6 –06
PERFORMANCE
001
PAGE : 1 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
JUL 04
6 . 06 . 01 – INTRODUCTION The following sub sections provide data for flight in atmospheric icing conditions. Refer to chapter 3 . 04 for definition of the minimum maneuver/operating icing speeds. 6.06 P2 – Minimum maneuver / operating speed in icing conditions 6.06 P3 – Take off flight path in case of engine failure. 6.06 P4 – Take off – Effect on second segment weight 6.06 P5 – Final take off maximum weight at brakes release. 6.06 P6 – Take off – Effect on take off run. 6.06 P7 – Take off – Effect on take off distance. 6.06 P8 – Take off – Effect on accelerate stop distance. 6.06 P8A – Research of weight limited by obstacle clearance (close obstacles). 6.06 P9 – Obstacle clearance take off flight path (close obstacles). 6.06 P9A – Research of weight limited by obstacle clearance (remote obstacles). 6.06 P10 – Obstacle clearance take off flight path (remote obstacles). 6.06 P11 – En route net gradient 6.06 P12 – Effect on approach climb gradient weight. 6.06 P13 – Effect on landing distance.
6 –06
PERFORMANCE
PAGE : 2 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
6 . 06 . 02 – FLIGHT IN ATMOSPHERIC ICING CONDITIONS MINIMUM MANEUVER / OPERATING SPEED
R
Mod : 1368
Eng : PW124
Model : ALL
NOV 92
130 OCT 96
APR 93 FEB 94
PERFORMANCE
6 –06 PAGE : 3
AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
TAKE OFF FLIGHT PATH IN CASE OF ENGINE FAILURE
Note : Point zero indicates the 35 ft height point on the flight path.
Eng : PW124
NOV 92
001 APR 93
6 –06
PERFORMANCE
PAGE : 4 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
NOV 92
001 SEP 99
TAKE OFF EFFECT ON SECOND SEGMENT WEIGHT V2 / VS1G = 1.21 (FLAPS 15)
ATMOSPHERIC ICING CONDITIONS
R
Note : Performance decrement applies to the maximum second segment weight computed in normal conditions with V2 = 1.21 VS1G (flaps 15) Eng : PW124
APR 93 OCT 96
6 –06
PERFORMANCE
PAGE : 5 AFM
R
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
FINAL TAKE-OFF EQUIVALENT WEIGHT AT BRAKES RELEASE V / VS1G = 1.38 (FLAPS 15) ONE ENGINE MAX. CONTINUOUS POWER – ONE PROPELLER FEATHERED AIR CONDITIONING OFF – DE ICING ON – GEAR UP
R
Mod : 1368 + 2735
Eng : PW124
Model : ALL
NOV 92
220 OCT 96
APR 93
6 –06
PERFORMANCE
NOV 92
001
PAGE : 6 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
SEP 99
TAKE OFF EFFECT ON TAKE OFF RUN V2 / VS1G = 1.21 (FLAPS 15)
ATMOSPHERIC ICING CONDITIONS
R
NOTE : Performance decrement applies to – Take off run length computed in normal conditions with V2 = 1.21 VS1G (flaps 15). – OR – – required take off run length computed in normal conditions with V2 = 1.21 VS1G (flaps 15) whichever is higher. Eng : PW124
APR 93 OCT 96
6 –06
PERFORMANCE
PAGE : 7 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
NOV 92
001 SEP 99
TAKE OFF EFFECT ON TAKE OFF DISTANCE V2 / VS1G = 1.21 (FLAPS 15)
ATMOSPHERIC ICING CONDITIONS
R
NOTE : Performance decrement applies to – Take off distance length computed in normal conditions with V2 = 1.21 VS1G (flaps 15). – OR – – required take off distance length computed in normal conditions with V2 = 1.21 VS1G (flaps 15) whichever is higher. Eng : PW124
APR 93 OCT 96
6 –06
PERFORMANCE
PAGE : 8 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
NOV 92
001 SEP 99
TAKE OFF EFFECT ON ACCELERATE STOP DISTANCE V2 / VS1G = 1.21 (FLAPS 15)
ATMOSPHERIC ICING CONDITIONS
R
NOTE : Performance decrement applies to the acceleration stop distance length computed in normal conditions with V2 = 1.21 VS1G (flaps 15). Eng : PW124
APR 93 OCT 96
PERFORMANCE
6 –06 PAGE : 8A
AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
001 JUL 04
RESEARCH OF WEIGHT LIMITED BY OBSTACLE CLEARANCE CLOSE OBSTACLE Initial gradient : 3% (associated to the weight limited by the runway condition). Obstacle
: 180 ft at 1700 m of the end of the runway, 18 kt nose wind. NOTE
The obstacle height and distance with respect to reference zero must be determined. In the flight manual charts reference zero is the point 35 ft below the end of the TOD and the flight paths shown include the 35 ft operational clearance. Where the TOD is greater (less) than the runway length the obstacle distance from end of the runway must be decreased (increased) by the difference between TOD and runway length. 1. Place the obstacle (point A). In this example the TOD is initially assumed equal to runway length. 2. Replace the obstacle according to the wind (point C) drawing a parallel to the gross height lines. 3. The path intersects the obstacle in B. 4. Determine the gradient allowing the clearance taking into account the decrease in TOD associated to the decrease in weight. This gives point D. 5. Follow the path up to the end of the 2nd segment. 6. The point E gives the second segment gradient which determines maximum weight allowing clearance of the obstacle. 7. To be precise, the take–off distance corresponding to this new maximum weight must be calculated. 8. Using this distance, replace the obstacle and check that it will be cleared. If not, restart the calculation.
PERFORMANCE
6 –06 001
PAGE : 9 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
JUL 04
OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES) V2 / VS1G = 1.21 (FLAPS 15)
Eng : PW124
PERFORMANCE
6 –06 PAGE : 9A
AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
001 JUL 04
RESEARCH OF WEIGHT LIMITED BY OBSTACLE CLEARANCE REMOTE OBSTACLE Initial gradient : 3% (associated to the weight limited by the runway condition). Obstacle
: 1800 ft at 17 km of the end of the runway, 18 kt nose wind. NOTE
The obstacle height and distance with respect to reference zero must be determined. In the flight manual charts reference zero is the point 35 ft below the end of the TOD and the flight paths shown include the 35 ft operational clearance. Where the TOD is greater (less) than the runway length the obstacle distance from end of the runway must be decreased (increased) by the difference between TOD and runway length. 1. Place the obstacle (point A). In this example the TOD is initially assumed equal to runway length. 2. Replace the obstacle according to the wind (point C) drawing a parallel to the gross height lines. 3. The path intersects the obstacle in B. 4. Determine the gradient allowing the clearance taking into account the decrease in TOD associated to the decrease in weight. This gives point D. 5. Follow the path up to the end of the 2nd segment. 6. The point E gives the second segment gradient which determines maximum weight allowing clearance of the obstacle. 7. To be precise, the take–off distance corresponding to this new maximum weight must be calculated. 8. Using this distance, replace the obstacle and check that it will be cleared. If not, restart the calculation.
PERFORMANCE
6 –06 001
PAGE : 10 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
JUL 04
OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES) V2 / VS1G = 1.21 (FLAPS 15)
Eng : PW124
PERFORMANCE
6 –06 PAGE : 11
AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
EN ROUTE NET GRADIENT V/VS1G = 1.38 (FLAPS 15)
R
ONE PROPELLER FEATHERED – ONE ENGINE : MAX CONTINUOUS POWER AIR CONDITIONING : OFF BELOW 10 000 ft – DE ICING ON.
R
Mod : 1368 + 2735
Eng : PW124
Model : ALL
FEB 91
220 OCT 96
APR 93
6 –06
PERFORMANCE
PAGE : 12 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
NOV 92
130 SEP 98
NORMAL CONDITIONS AND AIRCRAFT FREE OF ICE (ICING AOA OFF)
ATMOSPHERIC ICING CONDITIONS OR RESIDUAL ICE ON THE AIRCRAFT (ICING AOA LIT)
EFFECT ON APPROACH CLIMB GRADIENT WEIGHT V / VS1G = 1.23 (FLAPS 15)
R
NOTE : Performance decrement applies to the maximum approach climb gradient limiting weight computed in normal conditions with V = 1.23 VS1G (flaps 15). Mod : 1368
Eng : PW124
APR 93 OCT 96
6 –06
PERFORMANCE
PAGE : 13 AFM
ATMOSPHERIC ICING CONDITIONS
DGAC APPROVED
130
APR 93 SEP 98
NORMAL CONDITIONS AND AIRCRAFT FREE OF ICE (ICING AOA OFF)
ATMOSPHERIC ICING CONDITIONS OR RESIDUAL ICE ON THE AIRCRAFT (ICING AOA LIT)
EFFECT ON LANDING DISTANCE V / VS1G = 1.30 (FLAPS 30)
R
NOTE : Performance decrement applies to the landing distance computed in normal conditions.
Mod : 1368
Eng : PW124
NOV 92 OCT 96
7 -- 00
APPENDICES & SUPPLEMENTS CONTENTS
AFM
001
PAGE : 1 EASA
APPROVED
AUG 07
R 01 APPENDICES 01 . . 02 . . 03 . . 04 . . 05 . . 06 . . 07 . . 08 . . 09 . . 10 . . 11 . . . 12 . . 13 . . 14 . . 15 16 17 18 . . 19 . .
EXTERNAL NOISE CONFIGURATION DEVIATION LIST CAT II OPERATION TCAS STEEP SLOPE MANUAL APPROACH CONTAINER TRANSPORT Reserved ETOPS OPERATIONS ON NARROW RUNWAYS RUNWAYS SLOPE BEYOND 2 % POWER PLANT TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV COCKPIT DOOR SECURITY SYTEM (if installed) Reserved Aircraft Performance Monitoring APM SSR Mode S Enhanced Surveillance ACARS HIGH LATITUDES OPERATIONS DRY UNPAVED RUNWAYS
.../...
APPENDICES & SUPPLEMENTS CONTENTS
AFM
7 -- 00 PAGE : 2 EASA
APPROVED
001 AUG 07
02 -- SUPPLEMENTS 00 . . . INTRODUCTION 01 . . . 02 . . . 03 . . . 04 . . . 05 . . . 06 . . . 07 . . . 08 . . . 09 . . . 10 . . . 11 . . . 12 . . .
DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE DISPATCH WITH SPOILERS CONTROL SYSTEM INOPERATIVE DISPATCH WITH FLAPS RETRACTED DISPATCH WITH ONE WHEEL BRAKE DEACTIVATED DISPATCH WITH ANTI SKID SYSTEM INOPERATIVE DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE DISPATCH EEC OFF DISPATCH WITH ONE AFU INOPERATIVE DISPATCH WITH ONE TQ INDICATOR INOPERATIVE DISPATCH WITH ATPCS OFF FLIGHT WITH LANDING GEAR DOWN FERRY FLIGHT WITH PITCH ELEVATORS DISCONNECTED
03 -- NON DRY RUNWAYS (Advisory materials) 01 . . GENERAL 02 . . TAKE OFF 03 . . LANDING
08 -- CAA (UK) SUPPLEMENT 09 -- OPERATIONS IN CIS COUNTRIES
7 -- 01.01
APPENDICES
PAGE : 1
APPENDIX No 01
AFM
EASA APPROVED
002 AUG 07
EXTERNAL NOISE NOISE CHARACTERISTICS No determination has been made by the DGAC that the noise procedures and levels in this manual are, or should be, acceptable or unacceptable for operation at, into, or out of any airport. NOISE LEVELS Noise levels shown here after comply with ICAO annex 16 Chapter 3 noise requirements and were obtained by analysis of approved data from approved noise tests. See section 2.02.01 for identification of the maximum take off and landing weights applicable to a particular airplane. NOISE CERTIFICATION PROCEDURES Compliance with ICAO annex 16 included the following procedures : - An all-engine take off at FLAPS 15 configuration was used with a constant climb speed equal to V2 + 10 kt with all engines operating, air conditioning OFF, and gear retracted, with cutback. - Landing approach at FLAPS 30 configuration on a three degree glide slope, at a speed of at least 1.23 VS1G was used with air conditioning ON and gear extended. CONFIGURATION Engines : Pratt & Whitney of Canada Ltd ; PW 124 Propeller : Hamilton Standard ; HS 14 SF-11 with spinner CERTIFICATED NOISE LEVELS TAKE-OFF SIDE LINE APPROACH
86.5 84.7 94.1
EPNdB EPNdB EPNdB
Eng : PW124
Model : 201 -- 202
7 -- 01.01
APPENDICES
PAGE : 1
APPENDIX No 01
AFM
EASA APPROVED
110 AUG 07
EXTERNAL NOISE NOISE CHARACTERISTICS No determination has been made by the DGAC that the noise procedures and levels in this manual are, or should be, acceptable or unacceptable for operation at, into, or out of any airport. NOISE LEVELS Noise levels shown here after comply with ICAO annex 16 Chapter 3 noise requirements and were obtained by analysis of approved data from approved noise tests. See section 2.02.01 for identification of the maximum take off and landing weights applicable to a particular airplane. NOISE CERTIFICATION PROCEDURES Compliance with ICAO annex 16 included the following procedures : - An all-engine take off at FLAPS 15 configuration was used with a constant climb speed equal to V2 + 10 kt with all engines operating, air conditioning OFF, and gear retracted, with cutback. - Landing approach at FLAPS 30 configuration on a three degree glide slope, at a speed of at least 1.23 VS1G was used with air conditioning ON and gear extended. CONFIGURATION Engines : Pratt & Whitney of Canada Ltd ; PW 124 Propeller : Hamilton Standard ; HS 14 SF-11 with spinner CERTIFICATED NOISE LEVELS TAKE-OFF SIDE LINE APPROACH
Mod : 3651
86.9 84.7 94.1
Eng : PW124
EPNdB EPNdB EPNdB
Model : 201 -- 202
APPENDICES APPENDIX No 02
AFM
7 -- 01.02 PAGE : 1 EASA APPROVED
001 AUG 07
CONFIGURATION DEVIATION LIST GENERAL The configuration deviation list belongs to chapter 2 limitations of this airplane flight manual. Flight with certain secondary airframe missing parts is possible as indicated in this list. Any part not included in this list must be considered as necessary. Repairs or replacements must be done at the first station where appropriate facilities are available, and in any case at the main base. The sign ( -- ) in NUMBER INSTALLED or NUMBER REQUIRED FOR DISPATCH columns indicates that the quantity is variable. Letter ( m ) against an item indicates that some maintenance action is necessary to permit flight with these parts missing. Refer to the related section of the Maintenance Manual for this information. LIMITATIONS No more than one part for any one sub-system in this appendix may be missing unless specifically designated combinations are indicated herein. Unless otherwise specified herein, parts from different sub-systems may be missing. When missing part introduces additional limitation(s), this limitation is indicated in “REMARKS or CONDITIONS“ column. This limitation comes in addition to limitations of chapter 2 of Flight Manual. It must be clearly indicated by a placard on the captain’s instrument panel. PERFORMANCE Performance penalties are indicated in “REMARKS or CONDITIONS” column. Performance penalties are cumulative unless specific penalties for particular combinations of missing parts are indicated. These take-off, en route and landing penalties apply to the most limiting corresponding weight.
7 -- 01.02
APPENDICES APPENDIX No 02
AFM ATA CHAPTER
1
PAGE : 2 EASA APPROVED
001 AUG 07
2 -- NUMBER INSTALLED 3 -- NUMBER REQUIRED FOR DISPATCH
ITEM
4 -- REMARKS OR CONDITIONS
23 -- COMMUNICATIONS 1 -- Static dischargers
25
17
Provided : a) each aileron is equipped with at least 4 operative static dischargers, and b) rudder is equipped with at least 4 operative static dischargers and c) each elevator is equipped with at least 2 operative static dischargers d) tail cone is equipped with at least one operative static discharger.
7 -- 01.02
APPENDICES APPENDIX No 02
AFM ATA CHAPTER
1
PAGE : 3 EASA APPROVED
001 AUG 07
2 -- NUMBER INSTALLED 3 -- NUMBER REQUIRED FOR DISPATCH
ITEM
4 -- REMARKS OR CONDITIONS
27 -- FLIGHT CONTROLS 1 -- Flap hinge fairing
8
6
2 -- Flap lower surface trailing edge
4
3
3 -- Inner / outer flaps coupling system
2
0
Provided aircraft is not operated into known or forecast icing conditions
Provided flaps are retracted, placarded and considered inoperative.
7 -- 01.02
APPENDICES APPENDIX No 02
AFM ATA CHAPTER
1
001
PAGE : 4 EASA APPROVED
AUG 07
2 -- NUMBER INSTALLED 3 -- NUMBER REQUIRED FOR DISPATCH
ITEM
4 -- REMARKS OR CONDITIONS
32 -- LANDING GEAR 1 -- Main gear door
2
1
Provided aircraft is not operated into known or forecast icing conditions Maximum speed : 200 kt
1 bis -- Main gear foldable doors
4
2
Provided missing parts are on the same side
2 -- Nose gear forward door
2
0
Flight with gear down (refer to 7.02.11 )
3 -- Nose gear aft door
2
0
Maximum speed : 200 kt
4 -- Cover wheels
2
0
7 -- 01.02
APPENDICES APPENDIX No 02
AFM ATA CHAPTER
1
PAGE : 5 EASA APPROVED
2 -- NUMBER INSTALLED 3 -- NUMBER REQUIRED FOR DISPATCH
ITEM
4 -- REMARKS OR CONDITIONS
52 -- DOORS 1 -- Access door to GPU connector (DC or ACW)
2
0
2 -- Access door to refueling panel
1
0
3 -- Access door to hydraulic bay
1
0
4 -- Access door to water service panel
1
0
5 -- Access door to toilet service panel
1
0
6 -- Access door to tail cone bay
1
0
Maximum speed : 200 kt
7 -- Access door to air conditioning external connector
1
0
Maximum speed : 200 kt
8 -- Access door to refueling point
1
0
9 -- Jacking point covers
--
0
001 AUG 07
7 -- 01.02
APPENDICES APPENDIX No 02
AFM ATA CHAPTER
1
PAGE : 6 EASA APPROVED
001 AUG 07
2 -- NUMBER INSTALLED 3 -- NUMBER REQUIRED FOR DISPATCH
ITEM
4 -- REMARKS OR CONDITIONS
61 -- PROPELLER 1 -- Propeller spinner
2
1
Provided aircraft is not operated into known or forecast icing conditions
2
0
Provided flap is removed
79 -- OIL 1 -- Engine oil cooler flap
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 150
PAGE : 1 EASA APPROVED
AUG 07
CAT II OPERATION LIMITATIONS This appendix is intended to provide necessary information to allow the use of the aircraft in category II. Limitations, procedures and performance included in the appendix replace or complete the corresponding information of the basic Flight Manual. The automatic flight control system (AFCS) with the associated equipment has been found to meet the airworthiness and performance criteria of : - ACJ 25 - 1329 -- for the autopilot - Special condition F2 : AP engagement at take off - JAR AWO subpart 2 for category II NOTA : Compliance with the standards noted above does not constitute approval to conduct category II operations. Such authorization must be obtained by the operator from the appropriate authorities. - Minimum height for use of autopilot in approach mode : 50 ft - Minimum decision height : 100 ft - Certified configuration : flaps 30 - Maximum demonstrated wind : Headwind : Tailwind : Crosswind :
30 kt 10 kt 15 kt
.. / ..
Mod : 0069 + 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 PAGE : 2 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) NORMAL PROCEDURES NOTA : Failures have been demonstrated using the procedures described in this chapter. A --
Approved configurations • Approach : AP is approved with use of approach mode for CAT II precision ILS approaches. The CAT II capability must be displayed on ADU. • GO around : FD is approved with use of GA mode
B --
Performance envelope in approach • LOC capture : distance ≥ 6 NM -- Capture angle ≤ 90o • GLIDE capture : height ≥ 1500 ft Vc ≤ 180 kt at 1500 ft • Approach speed : When the aircraft is stabilized on GLIDE slope the selected approach speed VAPP is 1.23 VSR (flaps 30) + wind correction and not less than VMCL. The wind correction is equal to the highest of 1/3 of the reported headwind or the gust in full, with a maximum correction of 15 kt.
.. / ..
Mod : 1112
7 -- 01.03
APPENDICES
PAGE : 3
APPENDIX No 03
AFM
EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) C --
Minimum equipment required to meet CAT II approach criteria.
Approach with AP Autopilot FD bars sw AP quick disconnect ADU ILS receiver AHRS Standby Horizon CRT
1 1 CM1 side 1 CM1 side 1 2 2 1 3
SGU Radio altimeter DH indicator GA pushbutton Windshield wipers Yaw damper Airspeed indicators
2 1 (with 2 displays) 2 1 CM1 side 1 CM1 side 1 2 ADC 2 must be operative Blue + Green 1 DC generator 1 AC generator 3
Hydraulic system Electrical system MFC modules
.. / ..
Mod : 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 PAGE : 4 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) D --
Approach and landing preparation Approach preparation - Select decision height (DH). - Select ILS frequency and RWY HDG. - Engage the APP mode : GS and LOC illuminate white on both EADI and ADU. CAT II illuminates white on ADU (if this capability available). - The approach must be planned to capture the localizer prior to glide slope interception.
NOTA : GLIDE capture is inhibited as long as localizer capture is not initiated (LOC*). - The approach speed (VAPP) is 1.23 VS1G (FLAPS 30) + wind correction and not less than VMCL. - The approach configuration is FLAPS 30. -- Mode phases LOC*
At localizer capture the white LOC extinguishes and the green LOC* illuminates on both EADI and on ADU. LOC phase engages when the A/C is stabilized on the LOC beam axis. LOC illuminates on both EADI and on ADU.
GS*
At glide slope capture the white GS extinguishes and the green GS* illuminates on both EADI and on ADU. GS phase engages when the A/C is stabilized on the GLIDE SLOPE. Green GS illuminates on both EADI and on ADU.
1200 > ZRA > 800 ft
Before 800 ft (radio altimeter), dual coupling must illuminate on both EADI and on ADU (arrows) if correct capture conditions are met.
DH + 100 ft
A white box illuminates on the left of radio altimeter value.
DH
Amber DH symbol illuminates in the white box. .. / ..
Mod : 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 150
PAGE : 5 EASA APPROVED
AUG 07
CAT II OPERATION (CONT’D) E --
Normal approach and landing sequence. Final Approach
-- CM2
(pilot flying) monitors the A/C position and the trajectory parameters. He announces mode changes. He asks PNF for flaps setting and gear extension.
-- CM1
(pilot non flying) monitors the flight path and controls speed.
-- At 800 ft (radio altimeter) -- CM1 check, Dual coupling -- CM2 select FD bars OFF for AP approach DH + 100 ft -- CM1 looks for external visual reference. mini -- CM2 monitors the flight path and announces heights. DH
-- EXTERNAL VISUAL REFERENCES SUFFICIENT -- CM1 announces “VISUAL“, selects AP OFF not lower than 50 ft and performs the landing. -- CM2 announces “Minimum” and “50 ft“ -- EXTERNAL VISUAL REFERENCES INSUFFICIENT -- Perform a go around.
NOTA : A call out (indicating that a flight parameter is exceeded) must be done if : - Speed becomes lower than V APP -- 5 kt or greater than V APP + 10 kt (V APP is the selected approach speed). - Pitch attitude becomes lower than 4o nose down or greater than 4o nose up or bank angle becomes greater than 10o. - Excessive LOC or GLIDE deviation occurs. - Sustained AP / FD order NOT JUSTIFIED by LOC or G/S deviation occurs.
.. / ..
Mod : 0069 + 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 100
PAGE : 6 EASA APPROVED
AUG 07
CAT II OPERATION (CONT’D) F --
GO around sequence (configuration flaps 30) -- CM1 -- CM2
announces “GO AROUND, flaps 15 presses the GO AROUND push button, follows the FD bars and advances PL to the ramp. retracts flaps one step, adjusts and monitors engine parameters
As soon as rate of climb is positive : -- CM2 announces it. -- CM1 asks for gear retraction -- CM2 retracts the gear EMERGENCY PROCEDURE NO CHANGE
.. / ..
Mod : 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 PAGE : 7 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) PROCEDURES FOLLOWING FAILURE DEMONSTRATED ALTITUDE LOSS WITH (AP/FD) SYSTEM MALFUNCTION Maximum path deviation with take over occuring 1 second after failure recognition : 30 ft. DEVIATION PROFILE -- CAT II
.. / ..
Mod : 1112
Eng : PW124
APPENDICES AFM
APPENDIX No 03
7 -- 01.03 100
PAGE : 8 EASA APPROVED
AUG 07
CAT II OPERATION (CONT’D) FAILURES AND ASSOCIATED ACTIONS DURING APPROACH If external visual references are insufficient, failures not completely treated before 800 ft should lead to a missed approach. Nota 1 : ENGINE FAILURE Provided lateral trimming is properly achieved before 800 ft, single engine approach may be performed with autopilot engaged, but must be restricted to CAT I. Nota 2 : AFCS failure and trajectory deviation In case of CAT II INVALID, excess deviations or AFCS failure, go around must be performed with STBY HORIZON : initial missed approach attitude : 10o.
.. / ..
Mod : 1112
APPENDICES AFM
APPENDIX No 03
7 -- 01.03 PAGE : 9 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) FAILURES AND ASSOCIATED ACTIONS DURING A CAT II APPROACH A/C SYSTEMS Warnings
Actions at the time of failure detection > 800 ft < 800 ft
Flap failure, jammed between 0 and 15 position
Revert to Cat I minima
Flap failure, jammed above 15 position
Continue Increase VAPP (flaps 30) by 10 kt
Engine failure
Revert to Cat I minima
Complementary actions
Not applicable Multiply landing distance flaps 30 by 1.13 Discontinue the approach
Hydraulic failure (without fluid loss)
Transfer No capability loss
First MFC module failure
Apply associated procedure continue the approach
Discontinue the approach
Second MFC module failure
Apply associated procedure Revert to CAT 1 minima
Discontinue the approach
.. / ..
Mod : 1112
APPENDICES AFM
APPENDIX No 03
7 -- 01.03 PAGE : 10 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) FAILURES AND ASSOCIATED ACTIONS DURING A CAT II APPROACH FLIGHT INSTRUMENTS
Warnings
Actions at the time of failure detection > 800 ft < 800 ft
Standby horizon flag
Revert to Cat I minima
Radio altimeter warning on CM2 EFIS
Revert to Cat I minima
ATT / PIT / ROLL warning on any EFIS HDG warning on any EFIS
Switch to valid AHRS
Reengage AP Revert to Cat I minima
Switch to valid AHRS
Discontinue the approach
First action before switching AHRS is to refer to standby horizon to determine the wrong AHRS
Revert to CAT I minima
LOC / GS / ILS / warning on any EFIS
Revert to Cat I minima
Loss of one CRT
Switch affected CRT OFF
Loss of both CRT on one side
Switch to valid SGU. Revert to Cat I minima
Loss of ADC 2
Complementary actions
Revert to Cat I minima
.. / .. Mod : 1112
APPENDICES AFM
APPENDIX No 03
7 -- 01.03 PAGE : 11 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) FAILURES AND ASSOCIATED ACTIONS DURING A CAT II APPROACH AFCS and ADU Warnings
AP disengage
Actions at the time of failure detection Z RA : 800 ft 500 ft Try to recover If impossible revert to Cat I FD approach
LOC or G/S excess deviation
Not applicable
Loss of ADU
Perform a Cat I minima manual approach
Loss of Cat II capability (Triple click)
Try to recover If impossible revert to Cat I minima
Complementary action
discontinue the approach discontinue the approach discontinue the approach
discontinue the approach
.. / ..
Mod : 1112
APPENDICES APPENDIX No 03
AFM
7 -- 01.03 PAGE : 12 EASA APPROVED
100 AUG 07
CAT II OPERATION (CONT’D) NORMAL CONDITIONS
LANDING CAT II -- APPROACH CLIMB GRADIENT -- APPROACH CLIMB LIMITING WEIGHT (FLAPS 15) ONE PROPELLER FEATHERED -- ONE ENGINE : GO AROUND POWER AIR CONDITIONING ON -- ANTI/DE ICING OFF -- GEAR UP -- V = 1.14 VS1G
Mod : 1112
Eng : PW124
.. / ..
7 -- 01.03
APPENDICES
PAGE : 13
APPENDIX No 03
AFM
EASA APPROVED
CAT II OPERATION (CONT’D) ICING CONDITIONS
LANDING CAT II -- APPROACH CLIMB GRADIENT APPROACH CLIMB LIMITING WEIGHT (FLAPS 15)
NORMAL CONDITIONS AND AIRCRAFT FREE OF ICE (ICING AOA OFF)
ATMOSPHERIC ICING CONDITIONS OR RESIDUAL ICE ON THE AIRCRAFT (ICING AOA LIT)
ONE PROPELLER FEATHERED -- ONE ENGINE : GO AROUND POWER AIR CONDITIONING ON -- DE ICING ON -- GEAR UP -- V = 1.23 VS1G
Mod : 1112 + 1368
Eng : PW124
230 AUG 07
APPENDICES AFM
APPENDIX No 04
7 -- 01.04 PAGE : 1 EASA APPROVED
001 AUG 07
TCAS This appendix is applicable only when a ATR TCAS solution is installed. In case of TCAS STC (Supplier Type Certificate) solution installed, operator must consider STC provider appendix or supplement. 1 -- GENERAL The general information in Section 1 are applicable. 2 -- LIMITATIONS The limitations in Section 2 are applicable with addition of the following : 1. TCAS operation is approved for use in VFR meteorological conditions (VMC) and IFR meteorological conditions (IMC). 2. The pilot must not initiate evasive maneuvers using information from the traffic display only or from a traffic advisory (TCAS) only. These displays and advisory are intended only for assistance in visually locating the traffic and lack the resolution necessary for use in evasive maneuvering. 3. Compliance with TCAS resolution advisory is required unless the pilot considers it unsafe to do so. However maneuvers which are in the opposite direction of the resolution advisory (TCAS) are extremely hazardous and are prohibited unless it is visually determinated they are the only means to assure safe separation. CAUTION : Once a non crossing RA has been issued the vertical speed should be accurately adjusted to comply with the RA, in order to avoid negating the effectiveness of a co--ordinated maneuvre by the intruder. WARNING : Non compliance with a crossing RA by one airplane may result in reduced vertical separation. Therefore, safe horizontal separation must also be assured by visual means. 4. Evasive maneuvring should be made with the autopilot disengaged, and limited to the minimum required to comply with the RA. The pilot must promptly return to the previous ATC clearance when the TCAS “CLEAR OF CONFLICT” voice message is announced. 5. Prior to perform RA’s climb or increase climb, the crew should select the appropriate engine power setting on the power MGT rotary selector and, if necessary, manually adjust CLs. 6. When a climb or increase climb RA occurs with the airplane in the landing configuration or in the go--around phase, a normal procedure of go--around should be followed including the appropriate power increase and configuration changes. .. / ..
APPENDICES AFM
APPENDIX No 04
7 -- 01.04 PAGE : 2 EASA APPROVED
001 AUG 07
TCAS (CONT’D) This appendix is applicable only when a ATR TCAS solution is installed. In case of TCAS STC (Supplier Type Certificate) solution installed, operator must consider STC provider appendix or supplement. 7. Because of the limited number of inputs to TCAS for determination of aircraft performance inhibits, there are instances where inhibiting RA’s would be appropriate, however it is not possible to do so. In these cases, TCAS may command maneuvers which may significantly reduce stall margins or result in stall warning. Conditions where this may occur include operations with a bank angle (wings level is assumed), weight altitude and temperature combinations outside those noted below, leaving aircraft in landing configuration during climb RA on approach, engine out operations, and abnormal configurations such as landing gear not retracted or stick pusher/shaker failure. The table below entitled “Flight envelope in which climb resolution advisory can be accomplished without stick pusher/shaker activation” outlines the parameters used in the development of the performance inhibits. This table does not consider worst turboprop flight conditions especially operations using minimum operating airspeeds as are sometimes required (e.g. obstacle clearance, ATC constraints). In all cases, stall warning must be given precedence over climb RA commands. NOTE : TCAS is viewed as a supplement to the pilot who, with the aid of the ATC system, has the primary responsibility for avoiding mid--air collisions. WARNING : Priority must be granted to increasing airspeed when reaching stall warning even when this requires deviation from an RA command issued by the TCAS.
.. / ..
7 -- 01.04
APPENDICES
001
PAGE : 3
APPENDIX No 04
AFM
EASA APPROVED
AUG 07
TCAS (CONT’D) This appendix is applicable only when a ATR TCAS solution is installed. In case of TCAS STC (Supplier Type Certificate) solution installed, operator must consider STC provider appendix or supplement. FLIGHT ENVELOPE IN WHICH CLIMB RESOLUTION ADVISORY CAN BE ACHIEVED WITHOUT STICK PUSHER / SHAKER ACTIVATION FLIGHT REGIME
WEIGHT ALTITUDE TEMP
Take off
AIRSPEED
POWER
FLAPS
GEAR
FAR25/JAR25 Climb limit
Take off
15
Up
V2 + 20
1.13 Vsr
Approach
FAR25/JAR25 Climb limit
Spin up to go around power during maneuver from power for level flight
15
Up
1.51 Vsr
1.13 Vsr
Landing Transitioning to go around at RA
FAR25/JAR25 Climb limit
Spin up to go around power during maneuver from power required for 30 Glide Slope
Transition from 30 to 15
Dn to Up
Vapp + 10
1.13 Vsr
Up
Long Range Cruise
Higher of 1.13 Vsr if Defined or buffet onset
En route
Critical Wt / Alt giving 1.3 G to Buffet onset
Power for level flight increased to Max Continuous
Up
INITIAL
• Temperature range up to ISA + 270 • Altitude range
-- En route -- Take off -- Approach and landing
0 0 0
25 000 ft 6 000 ft 7 000 ft
* Wings level assumed
.. / ..
MIN.
APPENDICES AFM
APPENDIX No 04
7 -- 01.04 001
PAGE : 4 EASA APPROVED
AUG 07
TCAS (CONT’D) This appendix is applicable only when a ATR TCAS solution is installed. In case of TCAS STC (Supplier Type Certificate) solution installed, operator must consider STC provider appendix or supplement. 8. Inhibition schemes 8.1 NON ICING CONDITIONS CONFIGURATION FLAPS 0 FLAPS 15 TO FLAPS 15 Approach FLAPS 30
RA CLIMB
RA INCREASE CLIMB
AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED
AUTHORIZED INHIBITED AUTHORIZED INHIBITED
8.2 ICING CONDITIONS CONFIGURATION FLAPS 0 Z < 20000 ft Z > 20000 ft FLAPS 15 TO FLAPS 15 Approach FLAPS 30
RA CLIMB
RA INCREASE CLIMB
AUTHORIZED INHIBITED AUTHORIZED AUTHORIZED INHIBITED
INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED
NOTE 1 : Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with a TCAS resolution advisory. NOTE 2 : Maneuvers based solely on information displayed on the traffic display are not authorized.
.. / ..
APPENDICES APPENDIX No 04
AFM
7 -- 01.04 110
PAGE : 5 DGAC APPROVED
AUG 07
TCAS (CONT’D) This appendix is applicable only when a ATR TCAS solution is installed. In case of TCAS STC (Supplier Type Certificate) solution installed, operator must consider STC provider appendix or supplement. 3 -- NORMAL PROCEDURES The normal procedures in Section 3 are applicable. 4 -- EMERGENCY PROCEDURES The emergency procedures in Section 4 are applicable. 5 -- PROCEDURES FOLLOWING FAILURES The procedures following failures are applicable with the addition of the following : 5.1 The TCAS must be turned TA ONLY in the following cases • Engine out operations • Stick pusher/shaker failure • Flight with landing gear down 5.2 The TCAS must be turned STBY in the following cases • ATC request • Errors or differences between independant air data sources. 6 -- PERFORMANCES The performances in Section 6 are applicable.
Mod : 5205
APPENDICES APPENDIX No 05
AFM
STEEP SLOPE APPROACH (APPROACH SLOPE > 4.5_) NOT APPLICABLE
7 -- 01.05 PAGE : 1 EASA APPROVED
001 AUG 07
APPENDICES APPENDIX No 06
AFM
CONTAINER TRANSPORT NOT APPLICABLE
7 -- 01.06 PAGE : 1 EASA APPROVED
001 AUG 07
7 -- 01.08
APPENDICES APPENDIX No 08
AFM
PAGE : 1 EASA APPROVED
100 AUG 07
ETOPS 1 -- GENERAL APPLICABILITY This supplement applies to airplanes operated according to the provisions of the DGAC “Conditions Techniques Complèmentaires CTC 20 ETOPS” relative to eligibility and capability for ETOPS flights. STATEMENT OF CAPABILITY The type design reliability and performance of this airframe/engine combination has been evaluated and found to comply with the criteria of CTC 20 according to DGAC interpretation of FAA Advisory Circular AC 120--42A chapter 8, 9 (a) and appendix 1 when configured, maintained and operated in accordance with provisions of CMP standards for ETOPS at the latest approved revision. This Statement of Capability does not constitute approval to conduct ETOPS flights. 2 -- LIMITATIONS The limitations of section 2 of this Flight Manual must be completed by the following : Maximum diversion time may not exceed 120 minutes at one engine cruising speed. 3 -- FLIGHT MANUAL SUPPLEMENT EXCLUSION Transport of Containers and dispatch with one AFU inoperative are not permitted in conjunction with this supplement. 4 -- PROCEDURES The procedures of sections 3 and 4 of this Flight Manual remain applicable. A special attention should be paid to the fuel unbalance (refer to chapter 2.04.05). 5 -- PERFORMANCE - Refer to chapter 6.04 (normal conditions) and 6.06 (icing conditions) of this manual to determine the en route net gradient at the drift down speed. - Refer to pages 2 and 3 of this supplement to determine the en route net gradient at 200 kt IAS.
.. / ..
Eng : PW124
APPENDICES AFM
APPENDIX No 08
7 -- 01.08 PAGE : 2 EASA APPROVED
150 AUG 07
ETOPS (CONT’D) DESCENT 1 ENGINE WITHOUT OBSTACLE -- NET GRADIENT -- 200 KT IAS FLAPS 0 -- NORMAL CONDITIONS -- AIR CONDITIONING OFF BELOW 10000 FT
AIR CONDITIONING OFF below 10000 ft
Mod : 2735
Eng : PW124
... / ...
APPENDICES AFM
APPENDIX No 08
7 -- 01.08 PAGE : 3 EASA APPROVED
170 AUG 07
ETOPS (CONT’D) DESCENT 1 ENGINE WITHOUT OBSTACLE -- NET GRADIENT -- 200 KT IAS FLAPS 0 -- ICING CONDITIONS -- AIR CONDITIONING OFF BELOW 10000 FT
AIR CONDITIONING OFF below 10000 ft
Mod : 1368 + 2735
Eng : PW124
7 -- 01.09
APPENDICES APPENDIX No 09
AFM
PAGE : 1 EASA APPROVED
OPERATIONS ON NARROW RUNWAYS NOT APPLICABLE
001 AUG 07
7 -- 01.10
APPENDICES APPENDIX No 10
AFM
PAGE : 1 EASA APPROVED
RUNWAY SLOPE BEYOND 2% NOT APPLICABLE
001 AUG 07
APPENDICES AFM
APPENDIX N_ 11
POWER PLANT NOT APPLICABLE
7 -- 01.11 PAGE : 1 EASA APPROVED
001 AUG 07
APPENDICES AFM
APPENDIX N_ 12
7 -- 01.12 PAGE : 1 EASA APPROVED
001 AUG 07
TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV This appendix applies only to aircraft de/anti iced before take off, using fluids type II or type IV. These types of fluids may lead to an increase in control forces necessary to rotate, and then to a modification of take off performances. Therefore this Flight Manual must be modified in compliance with one of the following two methods :
COMPLIANCE METHOD 1 See 7.01.12 page 1A--001
COMPLIANCE METHOD 2 See 7.01.12 page 1B--001 NOTE: Compliance Method 2 requires dedicated crew training
7 -- 01.12
APPENDICES AFM
APPENDIX N_ 1
PAGE : 1A EASA APPROVED
001 AUG 07
TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV
COMPLIANCE METHOD 1 1. GENERAL The general information in Section 1 are applicable. 2. LIMITATIONS The limitations in Section 2 are applicable. 3. NORMAL PROCEDURES The normal procedures in Section 3 are applicable. 4. EMERGENCY PROCEDURES The emergency procedures in Section 4 are applicable. 5. PROCEDURES FOLLOWING FAILURES The procedures following failures in Section 5 are applicable. 6. PERFORMANCES The performances in Section 6 for dry runways and in Section 7.03 for non dry runways (advisory materials) are applicable with the addition of the following for take off computations : Determine VR for the lowest available V2 Assume V1 = VR Increase TOR, TOD, ASD by 25 % 7. APPENDICES AND SUPPLEMENTS Data contained in Section 7 are available with the addition of the following : For the dispatch cases : Apply take off penalties due to the system failure, Then apply take off penalties due to the use of fluids type II or IV. Dispatch is not authorized in the following cases : Ferry flight with pitch elevators disconnected Take off with flaps retracted.
7 -- 01.12
APPENDICES AFM
APPENDIX N_ 12
PAGE : 1B EASA APPROVED
001 AUG 07
TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV
COMPLIANCE METHOD 2 CREW TRAINING REQUIRED 1. GENERAL The general information in Section 1 are applicable. 2. LIMITATIONS The limitations in Section 2 are applicable. 3. NORMAL PROCEDURES The normal procedures in Section 3 are applicable with the addition of the following : The Captain must be the pilot flying and the pre--take off briefing must include the following take off procedure (point 5). 4. EMERGENCY PROCEDURES The emergency procedures in Section 4 are applicable. 5. PROCEDURES FOLLOWING FAILURES The procedures following failures in Section 5 are applicable with the addition of the following : TAKE OFF SEQUENCE In case of difficulties to rotate, the Captain should require the non flying pilot assistance. In that case, on CPT order, PNF pulls the control column until 5_ pitch attitude is reached, then PNF releases the controls. 6. PERFORMANCES The performances in Section 6 for dry runways and in section 7.03 for non dry runways (advisory materials) are applicable with the addition of the following : Increase the TOD by 70m. 7. APPENDICES AND SUPPLEMENTS Data contained in Section 7 are available with the addition of the following : For the dispatch cases : Apply take off penalties due to the system failure, Then apply the take off penalty due to the use of fluids type II or IV. Dispatch is not authorized in the following cases : Pitch elevators disconnected, even for ferry flight Take off with flaps retracted.
APPENDICES APPENDIX N_ 13
AFM
7 -- 01.13 PAGE : 1 EASA APPROVED
100 AUG 07
COCKPIT DOOR SECURITY SYSTEM LIMITATIONS Cockpit door must be checked closed and locked before taxi. Perform daily the functional test of the cockpit door locking system : See this appendix Normal Procedure part. NORMAL PROCEDURES Daily Check - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . ON In the cargo compartment, on the DOOR CALL PANEL - EMER PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH - Check OPEN LIGHT flashes In the cockpit : - Check buzzer - Check OPEN LIGHT flashes H If correct : In the cockpit : - TOGGLE SW on COCKPIT DOOR CONTROL PANEL . . . . . . DENY - Check buzzer stops - Check OPEN LIGHT extinguishes In the cargo compartment, on the DOOR CALL PANEL - Check OPEN LIGHT extinguishes and DENIED LIGHT illuminates H If correct : - TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . OFF - FUNCTIONAL CHECK OF THE MANUAL LOCK BOLTS Before Taxi - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . ON Before leaving the aircraft - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . OFF .. / .. Mod : 5434 or 5465 or 8330 or 8333
7 -- 01.13
APPENDICES
PAGE : 2
APPENDIX N_ 13
AFM
EASA APPROVED
100 AUG 07
COCKPIT DOOR SECURITY SYSTEM (CONT’D) EMERGENCY PROCEDURES Electrical Power Lost - Move the manual lock bolts to CLOSE position - Note : when the door is locked with the manual bolts, the emergency access to the cockpit is unavailable. It is recommended that at least two crew members remain in the cockpit during that time. Cockpit Door Jammed D When cockpit exit required - Remove the inspection seals from the two latches of the door left panel (facing the door) - Actuate the two corresponding latches as per placards - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . OFF - Disconnect PLUG from the door - Push and remove corresponding door panel PROCEDURES FOLLOWING FAILURES Cockpit Door Control Panel FAULT LIGHT illuminates - Move the manual lock bolts to CLOSE position - Note : when the door is locked with the manual bolts, the emergency access to the cockpit is unavailable. It is recommended that at least two crew members remain in the cockpit during that time. DC ESS BUS Lost - Apply Cockpit Door Control Panel FAULT LIGHT illuminates procedure - Note : Cockpit Door Control Panel FAULT LIGHT is inoperative. PERFORMANCE NO CHANGE
Mod : 5434 or 8330
Model : 102--202--212
APPENDICES APPENDIX N_ 15
AFM
7 -- 01.15 PAGE : 1 EASA APPROVED
001 AUG 07
Aircraft Performance Monitoring -- APM This Appendix is applicable only for aircraft fitted with mod 5567 or 8442. LIMITATIONS Installation of APM does not induce any specific limitations. NORMAL PROCEDURES Final Cockpit Preparation APM WEIGHT ROTARY SELECTOR . . . . SELECT MINIMUM WEIGHT APM WEIGHT ROTARY SELECTOR . . . . SELECT TAKE OFF WEIGHT Daily Check Press the PTT PB and check dedicated lights, master caution illumination and single chime In Flight, Climb, Cruise and Descent APM LIGHTS and CAUTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR H CRUISE SPEED LOW light illuminated Appears in cruise only, to inform the crew that an abnormal drag increase induces a speed decrease of more than 10 kt compared with the expected speed ICING CONDITIONS and SPEED . . . . . . . . . . . . . . . . . MONITOR
.. / ..
APPENDICES AFM
APPENDIX N_ 15
7 -- 01.15 PAGE : 2 EASA APPROVED
001 AUG 07
Aircraft Performance Monitoring -- APM (CONT’D) This Appendix is applicable only for aircraft fitted with mod 5567 or 8442. ABNORMAL PROCEDURES AND PROCEDURES FOLLOWING FAILURE " APM FAULT light illuminated APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF " DEGRADED PERF light illuminated with CAUTION and SINGLE CHIME Mainly appears in level flight after CRUISE SPEED LOW or in climb to inform the crew that an abnormal drag increase induces a speed decrease or a loss of rate of climb. The most probable cause is an abnormal ice accretion : AIRFRAME DE--ICING ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK IAS > RED BUG + 10 KT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR AP (if engaged) . . . FIRMLY HOLD CONTROL WHEEL and DISENGAGE H If SEVERE ICING conditions confirmed (unexpected decrease in speed or rate of climb, visual cues) or H If impossibility to maintain IAS > RED BUG + 10 kt in level flight or H If abnormal aircraft handling feeling SEVERE ICING procedure (4--05) . . . . . . . . . . . . . . . . . . . . . APPLY H If not SCHEDULED FLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE ICING CONDITIONS and SPEED . . . . . . . . . . . . . . . . . . . MONITOR " INCREASE SPEED light illuminated flashing with CAUTION and SINGLE CHIME Appears after DEGRADED PERF to inform the crew that the drag is abnormally high and IAS is lower than RED BUG + 10 KT. H If abnormal conditions confirmed IMMEDIATELY PUSH THE STICK TO INCREASE SPEED TO RECOVER MINIMUM IAS = RED BUG + 10 KT SEVERE ICING procedure (4--05) . . . . . . . . . . . . . . . . . . . . . APPLY
APPENDICES APPENDIX N_ 16
AFM
7 -- 01.16 001
PAGE : 1 EASA APPROVED
AUG 07
SSR Mode S Enhanced Surveillance This Appendix is applicable only for aircraft fitted with mod 5570 (GNSS) or mod 8431 (KLN90B). LIMITATIONS The installed Mode S system satisfies the data requirements of ICAO Doc 7030/4, Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. The capability to transmit data parameters is shown in column 2:
Parameter
Magnetic Heading
Available/Not available
Available
Indicated Airspeed Mach No
Available
Vertical Rate
Available
Roll Angle
Available
True Air Speed
Available
True Track Angle
Available only on aircraft fitted wih GNSS or GPS KLN90B
Groundspeed
Available only on aircraft fitted wih GNSS or GPS KLN90B
Selected Altitude
Available
Barometric Pressure Setting
Available
To be inserted in the flight manual and record sheet amended accordingly
APPENDICES AFM
APPENDIX N_ 17
ACARS Modification 5506 not applied.
7 -- 01.17 PAGE : 1 EASA APPROVED
001 AUG 07
APPENDICES AFM
APPENDIX N_ 18
7 -- 01.18 PAGE : 1 EASA APPROVED
001 AUG 07
HIGH LATITUDES OPERATIONS CONDITIONS Anomalous heading errors may occur on aircraft equipped with the Honeywell AH--600 AHRS during high latitude operations, where the earth’s magnetic lines of force have inclinations of greater than 75 degrees. PROCEDURES --Take special care to keep the slip indicator centered in order to minimize heading errors. --Crosscheck AHRS heading information with that of standby compass.
APPENDICES APPENDIX No 19
AFM
DRY UNPAVED RUNWAYS NOT APPLICABLE
7 -- 01.19 PAGE : 1 EASA APPROVED
001 AUG 07
SUPPLEMENTS INTRODUCTION
AFM
7 -- 02.00 PAGE : 1
001
EASA APPROVED
AUG 07
7 . 02 . 00 -- INTRODUCTION Following sections cover AFM amendments associated with MMEL dispatch. No combination of the hereafter considered cases is allowed for dispatch : 01
Dispatch with one ACW generator channel inoperative
02
Dispatch with spoilers control system inoperative
03
Dispatch with flaps retracted
04
Dispatch with one wheel brake deactivated
05
Dispatch with anti skid system inoperative
06
Dispatch with autofeather system inoperative
07
Dispatch with EEC OFF
08
Dispatch with one AFU inoperative
09
Dispatch with one TQ indicator inoperative
10
Dispatch with ATPCS OFF
11
Dispatch with landing gear down
12
Ferry flight with pitch elevators disconnected
7 -- 02.01
SUPPLEMENTS AFM
PAGE : 1
SUPPLEMENT No 01
EASA
APPROVED
001 AUG 07
DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE - If accelerate stop has to be performed, EMER BRAKING has to be used. - Check EMER BRAKING effect on ASD - Check GEAR DOWN effect on 2nd segment climb and approach climb (valid for all configurations) - Check GEAR DOWN effect on final take off climb - Check single engine ceiling by using a weight penalty - Avoid icing conditions - Taxi on both engines
... / ...
7 -- 02.01
SUPPLEMENTS AFM
PAGE : 2
SUPPLEMENT No 01
EASA APPROVED
DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE (CONT’D) EMERGENCY BRAKING EFFECT ON ACCELERATE STOP DISTANCE
... / ...
001 AUG 07
7 -- 02.01
SUPPLEMENTS AFM
PAGE : 3
SUPPLEMENT No 01
EASA
APPROVED
DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE (CONT’D) EFFECT OF GEAR DOWN ON 2ND SEGMENT CLIMB AND APPROACH CLIMB
... / ...
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 01
7 -- 02.01 PAGE : 4 EASA
APPROVED
001 AUG 07
DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE (CONT’D) EFFECT OF GEAR DOWN ON FINAL TAKE OFF CLIMB AND WEIGHT PENALTY ON SINGLE ENGINE CEILING COMPUTATION
SUPPLEMENTS AFM
SUPPLEMENT No 02
7 -- 02.02 PAGE : 1 EASA APPROVED
DISPATCH WITH SPOILERS CONTROL SYSTEM INOPERATIVE Increase VMCA by 2 kt VMCL FLAPS 30 = 101 kt Maximum crosswind on dry runway : 20 kt Take off with fuel unbalance must be avoided
Eng : PW124
001 AUG 07
7 -- 02.03
SUPPLEMENTS
PAGE : 1
SUPPLEMENT No 03
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH FLAPS RETRACTED - Authorized only if aircraft is not operated into known or forecast icing conditions. - Determine for V2=1.2VS1G (Chapter 6--03 FLAPS 15): - 2nd segment climb requirement - V1 limited by max brake energy, VR (assume V1=VR), V2 (CAS FLAPS 15) - TOR, TOD and ASD with V1/VR=1 - V1, VR and V2 IAS FLAPS 0 are obtained by adding 18 kt to the previously determined CAS values. - Decrease V1 limited by max brake energy by 5 kt and check V1 V1 limited by max brake energy - Check effect on TOR, TOD and ASD (pages 2 to 4) - Decrease 2nd segment and approach climb limiting weight by 300 kg (660 lb). - Inhibit config warning by depressing WARNING pb when applying power on the brakes (Note: CAP light will not extinguish). - Landing speed : 1.23 VS1G FLAPS 0+ 5 kt - Landing distance : multiply landing distance FLAPS 30 by 1.9 Pitch trim setting for FLAPS 0 take off : CG%
14
20
25
30
37
TRIM° NOSE
2.5 UP
2 UP
1.5 UP
1 UP
0.4 UP
... / ... Eng : PW124
7 -- 02.03
SUPPLEMENTS AFM
PAGE : 2
SUPPLEMENT No 03
EASA APPROVED
DISPATCH WITH FLAPS RETRACTED (CONT’D) TAKE OFF WITH FLAPS RETRACTED TAKE OFF RUN CORRECTIONS
... / ... Eng : PW124
001 AUG 07
7 -- 02.03
SUPPLEMENTS AFM
PAGE : 3
SUPPLEMENT No 03
EASA APPROVED
DISPATCH WITH FLAPS RETRACTED (CONT’D) TAKE OFF WITH FLAPS RETRACTED TAKE OFF DISTANCE CORRECTIONS
... / ... Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 03
7 -- 02.03 PAGE : 4 EASA APPROVED
DISPATCH WITH FLAPS RETRACTED (CONT’D) TAKE OFF WITH FLAPS RETRACTED ACCELERATE STOP DISTANCE CORRECTIONS
Eng : PW124
001 AUG 07
7 -- 02.04
SUPPLEMENTS AFM
SUPPLEMENT No 04
PAGE : 1 EASA APPROVED
DISPATCH WITH ONE WHEEL BRAKE DEACTIVATED
LIMITATIONS --Not allowed for operation from/to contaminated runway PROCEDURES --No change PERFORMANCE TAKE OFF --Multiply ASD BY 1.1 --Check V1 < 0.8 of V1 MAX BRK ENERGY LANDING --Multiply LDG DIST by 1.1 (valid for all configurations)
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 05
7 -- 02.05 PAGE : 1 EASA APPROVED
DISPATCH WITH ANTI--SKID SYSTEM INOPERATIVE LIMITATIONS -- Not allowed for operation from/to contaminated runway PROCEDURES -- No change PERFORMANCE TAKE OFF -- Check ANTI SKID OFF effect on ASD (page 2) LANDING -- Multiply LDG DIST by 1.4 (valid for all configurations)
... / ...
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 05
7 -- 02.05 PAGE : 2 EASA APPROVED
001 AUG 07
DISPATCH WITH ANTI--SKID SYSTEM INOPERATIVE (CONT’D) ANTI--SKID OFF EFFECT ON ACCELERATE STOP DISTANCE (FLAPS 15)
SUPPLEMENTS AFM
SUPPLEMENT No 06
7 -- 02.06 PAGE : 1 EASA APPROVED
001 AUG 07
DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE Uptrim and AFU are considered operative. If not, refer to the connected procedure. -- Increase V1 limited by VMCG by 4 kt -- Increase VR by 2 kt -- Increase VMCA by 3 kt, check VR, V2 -- Check effect on TOR, TOD, 2nd segment climb (pages 2 to 4) NOTE: In case of engine failure after V1, do not reduce PL below 48o of PLA before feathering. NOTE: Readjust RTO power upon reaching acceleration height.
... / ...
Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 06
7 -- 02.06 PAGE : 2 EASA APPROVED
001 AUG 07
DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE (CONT’D) EFFECT ON TAKE OFF RUN (FLAPS 15)
... / ... Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 06
7 -- 02.06 PAGE : 3 EASA APPROVED
001 AUG 07
DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE (CONT’D) EFFECT ON TAKE OFF DISTANCE (FLAPS 15)
... / ... Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 06
7 -- 02.06 PAGE : 4 EASA APPROVED
001 AUG 07
DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE (CONT’D) EFFECT ON 2nd SEGMENT
Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 07
7 -- 02.07 PAGE : 1 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE OR BOTH EEC OFF -- TAXIING: • Taxi on both engines • Set affected engine to GI and taxi using non affected engine -- TAKE OFF: • Take off must be performed with BLEED VALVES OFF and ATPCS OFF. • Increase V1 limited by VMCG by 4 kt. • Increase VR by 2 kt • Increase VMCA by 3 kt. Check VR and V2 • Check EEC OFF and ATPCS OFF effect on performances • If applicable, engine with operative EEC must be set to RTO power by pushing PL up to the ramp. • Engine(s) with inoperative EEC must be set to RTO power (¦ 2 %) by adjusting PL(s) • Release the brakes when both torques reach 40 % NOTE: If acceleration stop has to be performed, EMER BRAKE must be used. NOTE: In case of engine failure after V1: -- do not reduce PL below 48o of PLA before feathering -- readjust RTO power upon reaching acceleration height. -- CLIMB SEQUENCE: • Reduce both torques by 10 % average • PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB • BLEED VALVE 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON • Set PL 1+2 as to reach ENGINE TQ (automatic bug) -- FINAL APPROACH • CL 1+2 . . . . . . . . . . MAX RPM or 100% OVRD (depending on models) -- LANDING • If BOTH EEC OFF, Landing Distance . . . . . . . . . . . . . . . Multiply by 1.5
... / ... Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 07
7 -- 02.07 PAGE : 2 EASA APPROVED
DISPATCH WITH ONE OR BOTH EEC OFF (CONT’D) EFFECT ON TAKE OFF RUN (FLAPS 15)
... / ...
Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 07
7 -- 02.07 PAGE : 3 EASA APPROVED
DISPATCH WITH ONE OR BOTH EEC OFF (CONT’D) EFFECT ON TAKE OFF DISTANCE (FLAPS 15)
... / ...
Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 07
7 -- 02.07 PAGE : 4 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE OR BOTH EEC OFF (CONT’D) EFFECT ON ACCELERATE STOP DISTANCE (FLAPS 15)
... / ...
Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 07
7 -- 02.07 PAGE : 5 EASA APPROVED
DISPATCH WITH ONE OR BOTH EEC OFF (CONT’D) EFFECT ON SECOND SEGMENT WEIGHT
Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 08
7 -- 02.08 PAGE : 1 EASA APPROVED
DISPATCH WITH ONE AFU INOPERATIVE CAUTION: A maintenance procedure is required. Refer to MMEL 1--77 page 1 item 001. Apply dispatch with ATPCS OFF procedure : Supplement 10.
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 09
7 -- 02.09 001
PAGE : 1 EASA APPROVED
AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE J If only the FDAU bug is inoperative Consider FDAU bug value on operative side. J If TQ needle indication is inoperative, perform ATPCS test : J If ATPCS is operative : no penalties. J If ATPCS is inoperative, then refer to Supplment 10 : Dispatch with ATPCS inoperative. J If TQ digital counter is inoperative : J If associated EEC FAULT light is not illuminated : no penalties. J If associated EEC FAULT light is illuminated, then refer to Supplement 07 : Dispatch with EEC inoperative. J If both pointer and counter are inoperative on one side : ATPCS and both EEC must be operative • Take off Check effect on performances (pages 2 to 5) Increase VR by 1 kt Use minimum fuel flow tables (pages 6 to 11) CAUTION: Note RTO and MCT min fuel flow to be applied in case of engine flame out at take off. EEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BLEED 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN THE NOTCH Before 50 kt check and adjust fuel flow if the inoperative side indication is lower than anticipated by take off min fuel flow table. Observe ITT limitation. • Climb / Cruise BLEED 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check engine fuel flow on inoperative side and maintain it within ¦ 5 % band of opposite engine one. • Go around PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP TO THE RAMP Check and adjust fuel flow if the inoperative side indication is lower than anticipated by go around min fuel flow table. Observe ITT limitation. ... / ...
SUPPLEMENTS AFM
SUPPLEMENT No 09
7 -- 02.09 PAGE : 2 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) EFFECT ON TAKE OFF RUN (FLAPS 15)
... / ...
SUPPLEMENTS AFM
SUPPLEMENT No 09
7 -- 02.09 PAGE : 3 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) EFFECT ON TAKE OFF DISTANCE (FLAPS 15)
... / ...
SUPPLEMENTS AFM
SUPPLEMENT No 09
7 -- 02.09 PAGE : 4 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
... / ...
7 -- 02.09
SUPPLEMENTS AFM
SUPPLEMENT No 09
PAGE : 5 EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) EFFECT ON SECOND SEGMENT WEIGHT NOTE :This graph is also valid for Final Take Off, single engine ceiling and approach climb weights.
... / ...
7 -- 02.09
SUPPLEMENTS
PAGE : 6
SUPPLEMENT No 09
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) TAKE OFF MIN. FUEL FLOW (KG/H) SAT (C)
NP 100%
VC=50 KT
PRESSURE ALTITUDE (FT) --1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
-- 40. -- 30. -- 20. -- 16. -- 14.
450. 456. 462. 465. 466.
444. 451. 457. 459. 460.
439. 446. 452. 454. 455.
433. 440. 446. 449. 450.
429. 435. 441. 444. 445.
424. 430. 436. 439. 440.
422. 427. 432. 434. 435.
420. 425. 430. 431. 432.
418. 422. 427. 429. 430.
417. 422. 426. 427. 428.
417. 421. 425. 427. 428.
-- 12. -- 10. -- 8. -- 6. -- 4.
467. 468. 469. 470. 471.
461. 463. 464. 465. 466.
456. 457. 459. 460. 461.
451. 452. 454. 455. 456.
446. 447. 448. 450. 451.
441. 442. 443. 445. 446.
436. 438. 439. 440. 441.
433. 434. 435. 436. 437.
431. 432. 433. 434. 435.
429. 430. 431. 432. 428.
428. 429. 426. 423. 419.
-- 2. 0. 2. 4. 6.
472. 473. 474. 475. 476.
467. 468. 469. 470. 471.
462. 463. 464. 465. 466.
457. 458. 459. 460. 461.
452. 453. 454. 455. 457.
447. 448. 449. 450. 452.
442. 443. 444. 446. 447.
438. 439. 440. 441. 442.
436. 436. 436. 432. 428.
425. 421. 418. 414. 411.
416. 413. 409. 406. 402.
8. 10. 12. 14. 16.
477. 478. 479. 480. 481.
472. 473. 474. 475. 476.
467. 468. 469. 470. 471.
462. 463. 464. 465. 466.
458. 459. 460. 461. 462.
453. 454. 455. 456. 457.
448. 449. 450. 451. 448.
443. 440. 437. 434. 430.
425. 422. 420. 416. 413.
408. 405. 403. 399. 396.
400. 397. 394. 391. 388.
18. 20. 22. 24. 26.
482. 483. 484. 485. 485.
477. 478. 479. 480. 481.
472. 473. 474. 475. 476.
467. 468. 469. 470. 471.
463. 464. 465. 465. 459.
458. 457. 452. 446. 441.
444. 439. 434. 428. 423.
426. 421. 416. 411. 406.
409. 404. 399. 395. 390.
392. 388. 383. 379. 374.
384. 380. 376. 371. 366.
28. 30. 32. 34. 36.
486. 487. 488. 489. 490.
482. 483. 484. 484. 485.
477. 478. 479. 473. 466.
472. 466. 460. 454. 448.
453. 448. 442. 436. 430.
435. 430. 424. 419. 413.
418. 413. 407. 402. 396.
401. 396. 391. 386. 380.
385. 380. 375. 370. 365.
369. 365. 360. 355. 350.
362. 358. 353. 348. 343.
38. 40. 42. 44. 46.
490. 491. 484. 476. 469.
479. 472. 465. 457. 450.
460. 453. 446. 439. 432.
441. 435. 428. 421. 415.
424. 417. 411. 405. 398.
407. 401. 395. 389. 383.
390. 385. 379. 373.
375. 369. 364.
360. 354.
345.
338.
48. 50. 52. 54. 55.
462. 455. 448. 441. 438.
443. 437. 430. 424. 420.
426. 420. 413.
409. 403.
393.
... / ... Eng : PW124
7 -- 02.09
SUPPLEMENTS
PAGE : 7
SUPPLEMENT No 09
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) RESERVE TAKE OFF MIN. FUEL FLOW (KG/H) NP 100% VC=50 KT SAT (C)
PRESSURE ALTITUDE (FT) --1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
-- 40. -- 30. -- 20. -- 16. -- 14.
484. 492. 499. 501. 503.
479. 486. 492. 495. 497.
473. 480. 487. 490. 491.
471. 476. 482. 484. 486.
468. 473. 479. 481. 482.
466. 471. 476. 478. 479.
465. 469. 474. 476. 477.
464. 469. 473. 475. 476.
465. 468. 473. 474. 475.
466. 470. 473. 474. 475.
467. 470. 474. 475. 476.
-- 12. -- 10. -- 8. -- 6. -- 4.
504. 505. 507. 508. 509.
498. 499. 501. 502. 503.
492. 494. 495. 496. 497.
487. 488. 489. 491. 492.
483. 484. 485. 486. 487.
480. 481. 482. 483. 484.
478. 479. 480. 481. 482.
477. 477. 478. 479. 480.
476. 477. 478. 478. 479.
476. 476. 477. 478. 474.
476. 477. 473. 468. 464.
-- 2. 0. 2. 4. 6.
510. 511. 513. 514. 515.
505. 506. 507. 508. 510.
499. 500. 501. 502. 504.
493. 494. 496. 497. 498.
488. 489. 490. 492. 493.
485. 486. 487. 488. 489.
483. 484. 485. 486. 487.
481. 481. 482. 483. 484.
480. 481. 480. 475. 470.
469. 464. 460. 455. 450.
459. 455. 450. 445. 441.
8. 10. 12. 14. 16.
516. 517. 518. 520. 521.
511. 512. 513. 514. 515.
505. 506. 507. 509. 510.
499. 501. 502. 503. 504.
494. 495. 496. 498. 499.
490. 491. 492. 493. 494.
488. 489. 490. 491. 486.
485. 481. 476. 471. 466.
465. 461. 457. 452. 447.
446. 442. 438. 433. 429.
437. 433. 429. 424. 420.
18. 20. 22. 24. 26.
522. 523. 524. 525. 526.
516. 518. 519. 520. 521.
511. 512. 513. 515. 516.
505. 507. 508. 509. 510.
500. 501. 502. 503. 497.
495. 494. 488. 482. 477.
480. 474. 469. 463. 458.
460. 455. 450. 444. 439.
442. 437. 432. 427. 421.
424. 419. 414. 409. 404.
415. 410. 406. 401. 396.
28. 30. 32. 34. 36.
527. 528. 529. 530. 531.
522. 523. 524. 525. 526.
517. 518. 519. 513. 506.
511. 505. 499. 492. 485.
491. 485. 479. 472. 466.
471. 465. 459. 453. 447.
452. 447. 441. 435. 429.
434. 429. 423. 418. 412.
416. 411. 406. 401. 396.
400. 395. 390. 385. 380.
392. 387. 382. 377. 372.
38. 40. 42. 44. 46.
532. 533. 526. 518. 510.
520. 512. 505. 498. 490.
499. 492. 485. 478. 470.
479. 472. 466. 459. 451.
460. 453. 447. 440. 433.
441. 435. 429. 423. 416.
424. 418. 412. 406.
407. 401. 395.
390. 385.
375.
367.
48. 50. 52. 54. 55.
502. 493. 485. 476. 472.
482. 474. 465. 457. 453.
462. 455. 447.
444. 436.
426.
... / ... Eng : PW124
7 -- 02.09
SUPPLEMENTS
001
PAGE : 8
SUPPLEMENT No 09
AFM
EASA APPROVED
AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) GO AROUND MIN. FUEL FLOW (KG/H) SAT (C)
NP 100%
VC=100 KT
PRESSURE ALTITUDE (FT) --1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
-- 40. -- 30. -- 20. -- 16. -- 14.
483. 491. 498. 501. 502.
478. 485. 492. 495. 496.
472. 479. 486. 489. 490.
468. 474. 480. 483. 484.
465. 471. 477. 479. 480.
462. 468. 474. 476. 477.
461. 466. 471. 473. 474.
459. 464. 469. 471. 471.
459. 463. 468. 469. 470.
459. 463. 467. 468. 469.
460. 463. 467. 468. 469.
-- 12. -- 10. -- 8. -- 6. -- 4.
503. 504. 506. 507. 508.
497. 499. 500. 501. 503.
491. 493. 494. 495. 497.
486. 487. 488. 490. 491.
481. 482. 483. 484. 485.
478. 479. 480. 481. 482.
475. 476. 477. 478. 479.
472. 473. 474. 475. 476.
471. 472. 473. 474. 475.
470. 471. 472. 472. 469.
470. 470. 468. 464. 459.
-- 2. 0. 2. 4. 6.
509. 511. 512. 513. 514.
504. 505. 506. 507. 509.
498. 499. 500. 502. 503.
492. 493. 495. 496. 497.
487. 488. 489. 490. 492.
483. 484. 485. 486. 487.
480. 481. 482. 483. 484.
477. 478. 479. 480. 481.
475. 476. 476. 471. 467.
465. 461. 456. 452. 448.
455. 451. 447. 442. 439.
8. 10. 12. 14. 16.
515. 516. 517. 519. 520.
510. 511. 512. 513. 514.
504. 506. 507. 508. 509.
498. 500. 501. 502. 503.
493. 494. 495. 497. 498.
488. 489. 490. 491. 492.
485. 486. 487. 488. 485.
482. 479. 475. 470. 465.
463. 459. 455. 451. 446.
444. 440. 436. 432. 427.
435. 431. 427. 423. 419.
18. 20. 22. 24. 26.
521. 522. 523. 524. 525.
515. 516. 518. 519. 520.
510. 511. 513. 514. 515.
505. 506. 507. 508. 509.
499. 500. 501. 503. 497.
494. 494. 488. 483. 477.
479. 474. 469. 463. 458.
460. 455. 450. 445. 440.
441. 436. 432. 427. 422.
423. 419. 414. 410. 405.
415. 410. 406. 401. 397.
28. 30. 32. 34. 36.
526. 527. 528. 529. 530.
521. 522. 523. 524. 525.
516. 517. 518. 513. 506.
510. 506. 499. 492. 486.
491. 485. 479. 473. 466.
471. 466. 460. 454. 448.
453. 447. 441. 435. 430.
434. 429. 423. 418. 412.
417. 412. 406. 401. 396.
400. 395. 390. 385. 379.
392. 387. 382. 377. 372.
38. 40. 42. 44. 46.
531. 532. 526. 519. 511.
520. 513. 505. 498. 490.
499. 492. 485. 478. 471.
479. 472. 466. 459. 452.
460. 454. 447. 440. 434.
441. 435. 429. 423. 416.
424. 418. 412. 406. 399.
407. 401. 395. 389.
390. 385. 379.
374. 369.
367. 362.
48. 50. 52. 54. 55.
503. 494. 486. 477. 474.
482. 474. 466. 458. 455.
463. 455. 448. 440.
445. 437. 430.
427. 420.
410.
... / ... Eng : PW124
7 -- 02.09
SUPPLEMENTS
PAGE : 9
SUPPLEMENT No 09
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) MAXI CONTINUOUS MIN. FUEL FLOW (KG/H) TAT (C)
NP 100%
VC = 120. KT
PRESSURE ALTITUDE (FT) 0.
2000.
4000.
6000.
8000.
10000.
12000.
14000.
16000.
18000.
20000.
22000.
24000.
25000.
--56. --52. --48. --44. --40.
466. 469. 472. 475. 478.
458. 461. 463. 466. 468.
452. 455. 457. 459. 461.
449. 451. 453. 455. 457.
450. 452. 453. 455. 456.
452. 454. 455. 457. 458.
454. 455. 457. 458. 460.
450. 451. 444. 436. 429.
413. 414. 407. 400. 393.
378. 379. 373. 367. 360.
347. 348. 343. 337. 331.
325. 326. 321. 316. 310.
306. 307. 302. 297. 292.
298. 299. 294. 289. 283.
--36. --32. --28. --24. --20.
481. 484. 487. 490. 492.
470. 473. 475. 478. 481.
464. 466. 468. 470. 473.
459. 461. 463. 465. 467.
458. 459. 461. 462. 463.
460. 461. 462. 464. 461.
458. 451. 442. 433. 424.
421. 414. 406. 398. 390.
386. 380. 373. 365. 358.
354. 349. 342. 335. 328.
326. 321. 315. 308. 302.
305. 300. 294. 288. 282.
286. 282. 276. 270. 264.
278. 274. 268. 262. 256.
--16. --12. --8. --4. 0.
495. 498. 501. 503. 505.
483. 486. 488. 491. 494.
475. 477. 479. 481. 483.
468. 470. 472. 474. 476.
465. 467. 469. 467. 459.
453. 445. 438. 430. 423.
416. 409. 403. 396. 389.
383. 376. 371. 364. 358.
351. 346. 341. 335. 330.
322. 317. 313. 308. 303.
297. 292. 288. 283. 279.
277. 273. 269. 264. 260.
260. 255. 251. 247. 243.
252. 248. 244. 239. 235.
4. 8. 12. 16. 20.
508. 510. 512. 515. 517.
496. 499. 501. 504. 506.
485. 487. 490. 492. 491.
479. 477. 469. 461. 455.
451. 441. 433. 426. 420.
416. 406. 399. 393. 388.
383. 374. 368. 363. 358.
353. 345. 339. 334. 330.
325. 317. 312. 308. 304.
298. 292. 287. 283. 280.
275. 268. 264. 261.
256. 250. 246.
239. 233. 229.
231. 226.
24. 28. 32. 36. 40.
519. 521. 523. 517. 507.
508. 508. 493. 479. 469.
482. 470. 457. 444. 435.
446. 436. 423. 411. 403.
413. 403. 391. 381. 373.
381. 372. 361. 352.
352. 343. 334.
324. 316.
299.
44. 48. 52. 56. 60.
496. 484. 473. 462.
459. 449. 438.
426. 416.
394.
... / ...
Eng : PW124
7 -- 02.09
SUPPLEMENTS
PAGE : 10
SUPPLEMENT No 09
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) MAXI CONTINUOUS MIN. FUEL FLOW (KG/H) TAT (C)
NP 100% VC = 140. KT
PRESSURE ALTITUDE (FT) 0.
2000.
4000.
6000.
8000.
10000.
12000.
14000.
16000.
18000.
20000.
22000.
24000.
25000.
--56. --52. --48. --44. --40.
467. 470. 473. 476. 479.
458. 460. 463. 465. 468.
451. 453. 456. 458. 461.
448. 450. 452. 454. 456.
448. 450. 451. 453. 454.
449. 450. 452. 453. 455.
449. 450. 452. 453. 455.
449. 450. 447. 439. 432.
417. 418. 411. 405. 398.
386. 387. 381. 374. 368.
356. 358. 352. 346. 340.
333. 334. 328. 323. 317.
311. 312. 307. 301. 296.
301. 301. 296. 291. 286.
--36. --32. --28. --24. --20.
482. 484. 487. 490. 493.
470. 473. 476. 478. 481.
463. 465. 467. 470. 472.
458. 460. 462. 464. 465.
455. 457. 458. 460. 462.
456. 458. 459. 460. 462.
457. 454. 446. 436. 427.
424. 418. 410. 401. 393.
391. 385. 378. 370. 362.
361. 356. 349. 341. 334.
334. 329. 323. 316. 309.
312. 307. 301. 295. 288.
291. 286. 281. 275. 269.
281. 277. 271. 265. 260.
--16. --12. --8. --4. 0.
496. 499. 501. 504. 506.
484. 486. 489. 492. 494.
474. 476. 479. 481. 483.
467. 469. 471. 474. 476.
464. 465. 467. 469. 463.
457. 449. 441. 434. 427.
420. 412. 406. 399. 392.
386. 379. 373. 367. 361.
356. 349. 344. 338. 332.
328. 323. 318. 312. 306.
304. 298. 294. 288. 283.
283. 278. 274. 269. 264.
264. 259. 255. 250. 245.
255. 251. 246. 241. 237.
4. 8. 12. 16. 20.
508. 511. 513. 515. 517.
497. 499. 502. 504. 507.
485. 487. 490. 492. 495.
478. 480. 473. 465. 459.
455. 445. 437. 430. 424.
419. 410. 403. 397. 391.
386. 377. 371. 365. 360.
355. 347. 341. 336. 332.
327. 319. 314. 310. 305.
301. 294. 289. 285. 281.
279. 272. 268. 264. 260.
260. 254. 250. 246.
242. 237. 233.
234. 229. 225.
24. 28. 32. 36. 40.
519. 521. 523. 522. 511.
509. 511. 498. 484. 474.
487. 475. 462. 449. 440.
451. 440. 428. 416. 408.
417. 407. 396. 385. 377.
384. 375. 365. 355.
354. 345. 336.
326. 318.
300. 293.
276.
44. 48. 52. 56. 60.
500. 489. 478. 466.
464. 454. 443.
431. 421.
399.
... / ...
Eng : PW124
7 -- 02.09
SUPPLEMENTS
PAGE : 11
SUPPLEMENT No 09
AFM
EASA APPROVED
001 AUG 07
DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D) MAXI CONTINUOUS MIN. FUEL FLOW (KG/H) TAT (C)
NP 100%
VC = 160. KT
PRESSURE ALTITUDE (FT) 0.
2000.
4000.
6000.
8000.
10000.
12000.
14000.
16000.
18000.
20000.
22000.
24000.
25000.
--56. --52. --48. --44. --40.
468. 471. 474. 477. 480.
458. 460. 463. 465. 468.
449. 451. 454. 456. 459.
445. 447. 449. 451. 453.
445. 446. 447. 449. 450.
447. 449. 450. 452. 453.
451. 453. 454. 456. 457.
452. 453. 455. 455. 447.
431. 433. 426. 419. 411.
397. 398. 392. 385. 379.
367. 368. 362. 356. 350.
342. 343. 338. 332. 326.
319. 320. 314. 309. 303.
308. 309. 303. 298. 293.
--36. --32. --28. --24. --20.
483. 486. 489. 491. 494.
470. 473. 476. 479. 482.
461. 463. 466. 468. 470.
454. 456. 458. 460. 462.
452. 453. 455. 457. 459.
455. 456. 457. 459. 460.
459. 460. 460. 450. 440.
439. 432. 424. 415. 406.
404. 398. 391. 382. 374.
372. 367. 360. 352. 345.
344. 339. 333. 326. 319.
320. 315. 309. 302. 296.
298. 293. 287. 281. 274.
287. 282. 277. 270. 264.
--16. --12. --8. --4. 0.
497. 500. 502. 505. 507.
484. 487. 489. 492. 495.
472. 475. 477. 479. 481.
464. 466. 468. 471. 473.
460. 462. 464. 465. 467.
461. 458. 450. 442. 434.
432. 424. 416. 409. 401.
399. 391. 384. 377. 370.
368. 361. 355. 348. 341.
339. 333. 327. 321. 314.
313. 308. 302. 297. 291.
291. 285. 280. 275. 270.
269. 264. 259. 254. 249.
259. 254. 250. 245. 240.
4. 8. 12. 16. 20.
509. 512. 514. 516. 518.
497. 500. 502. 505. 507.
484. 486. 489. 491. 494.
475. 477. 478. 470. 463.
460. 450. 442. 434. 428.
425. 416. 408. 401. 396.
393. 384. 377. 371. 366.
363. 355. 349. 343. 338.
335. 328. 322. 317. 313.
309. 303. 298. 293. 289.
286. 280. 276. 272. 268.
265. 259. 255. 252.
245. 240. 236.
236. 231. 228.
24. 28. 32. 36. 40.
521. 523. 525. 527. 519.
509. 512. 505. 491. 481.
492. 480. 467. 454. 445.
455. 444. 432. 420. 412.
420. 410. 399. 389. 381.
388. 379. 369. 359. 352.
359. 350. 341. 332.
332. 324. 315.
307. 300.
284.
44. 48. 52. 56. 60.
509. 498. 486. 475.
472. 462. 451.
437. 428.
404.
374.
Eng : PW124
SUPPLEMENTS SUPPLEMENT No 10
AFM
7 -- 02.10 PAGE : 1 EASA APPROVED
001 AUG 07
DISPATCH WITH ATPCS OFF AFU must be checked operative prior to take off. If not, refer to the connected procedure. - Select ATPCS OFF and BLEED VALVES OFF - Increase V1 limited by VMCG by 4 kt - Increase VR by 2 kt - Increase VMCA by 3 kt. Check VR and V2 - Check ATPCS inoperative effect on TOR, TOD and 2nd segment - Apply RTO power by pushing both PLs up to the ramp - After take off set both PLs into the notches, then apply CLIMB SEQUENCE - BLEED VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON NOTE : In case of engine failure after V1: -- do not reduce PL below 48o of PLA before feathering -- readjust RTO power upon reaching acceleration height.
... / ...
Eng : PW124
SUPPLEMENTS AFM
SUPPLEMENT No 10
7 -- 02.10 PAGE : 2 EASA APPROVED
DISPATCH WITH ATPCS OFF (CONT’D) EFFECT ON TAKE OFF RUN (FLAPS 15)
... / ...
Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 10
7 -- 02.10 PAGE : 3 EASA APPROVED
DISPATCH WITH ATPCS OFF (CONT’D) EFFECT ON TAKE OFF DISTANCE (FLAPS 15)
... / ...
Eng : PW124
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 10
7 -- 02.10 001
PAGE : 4 EASA APPROVED
AUG 07
DISPATCH WITH ATPCS OFF (CONT’D) EFFECT ON SECOND SEGMENT WEIGHT (FLAPS 15)
Eng : PW124
7 -- 02.11
SUPPLEMENTS AFM
PAGE : 1
SUPPLEMENT No 11
EASA APPROVED
001 AUG 07
FLIGHT WITH LANDING GEAR DOWN - Flight in icing conditions is prohibited. - Check GEAR DOWN effect on 2nd segment climb and approach climb. - Check GEAR DOWN effect on final take--off climb. - Check weight penalty on single engine ceiling computation. - During the climb sequence after take off extinguish TO INHI light by pressing RCL pb. - Limit maximum speed to 160 kt.
... / ...
7 -- 02.11
SUPPLEMENTS AFM
PAGE : 2
SUPPLEMENT No 11
EASA APPROVED
FLIGHT WITH LANDING GEAR DOWN (CONT’D) EFFECT ON SECOND SEGMENT CLIMB AND APPROACH CLIMB
... / ...
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 11
7 -- 02.11 PAGE : 3 EASA APPROVED
FLIGHT WITH LANDING GEAR DOWN (CONT’D) EFFECT ON FINAL TAKE OFF WEIGHT PENALTY ON SINGLE ENGINE CEILING COMPUTATION Valid for all configurations
001 AUG 07
SUPPLEMENTS AFM
SUPPLEMENT No 12
7 -- 02.12 PAGE : 1 EASA APPROVED
001 AUG 07
FERRY FLIGHT WITH PITCH ELEVATORS DISCONNECTED - For ONE FLIGHT WITHOUT PAX - No operation into known or forecast icing conditions - Check both control columns free - Check CG is between 25 % and 32 % - Max take--off weight : 18 t (39600 lb) - Max crosswind at landing : 15 kt - Performance computed with V2 = 1.21 VS1G - Max load factor : 2 g - Max speed : 180 kt For approach and landing - Refer to FCOM 2.02.06 and AFM 5.04
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
Date révision antérieure
7 –03 001
PAGE : 1 DGAC APPROVED
SEP 99
7 . 03 . 01 – GENERAL This information has been prepared by the manufacturer and approved by the Authority in the form of guidance material, to assist operators in developing suitable guidance, recommandations or instructions for use by their flight crews when operating on wet/contaminated runway surface conditions. Unless otherwise stated, this information does not in any way replace or amend the operating limitations and performance information listed in other parts of this approved aeroplane flight manual. A non dry runway may be : - wet : well soaked but without significant areas of standing water.
R
R
NOTE : a runway is considered well soaked when there is sufficient moisture on the runway surface to cause it to appear reflective. - contaminated, if more than 25 % of the required area are covered by the contaminant. A runway may be contaminated by : - standing water : depth higher than 3 mm (1/8 in) - slush or loose snow, equivalent to more than 3 mm (1/8 in) of water - compacted snow - ice
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
Date révision antérieure
7 –03 PAGE : 1A
001
DGAC
SEP 99
APPROVED
7 . 03 . 02 – TAKE OFF R
Slush and water have the same impact on aircraft performances. Loose snow is considered as slush. To determine the equivalent slush depth, multiply the loose snow depth by the actual loose snow density divided by 0.8. Five cases have been considered : - wet - water 6.3 mm (1/4 in) applicable for depths between 3 and 6.3 mm of water or less than 6.3 mm of slush or equivalent depth of loose snow - water 12.7 mm (1/2 in) applicable for depths between 6.3 and 12.7 mm of water or slush or equivalent depth of loose snow - compacted snow - ice
R
The performance determination philosophy remains the same than in 6.03.02. Refer to 7–03 p.2 for V1 limited by VMCG data. For each runway condition are provided : - take off run - take off distance (between brakes release and 15 ft height with one engine inoperative). NOTE :If 35 ft is required at the end of TOD: –apply TOR, TOD calculated on a dry runway for wet, compacted snow and ice runways, –apply TOR, TOD corrections given pages 26A and 26B to the 15 ft computation, for water covered runways. - accelerate stop distance. They are basically computed with the use of both reversers. Additional pages are provided to supply data in case of no reverser and are to be used for flight preparation. Since the effect of asymmetrical reverse thrust is not predictable with a sufficient accuracy on contaminated runways, it is therefore not recommended to use single engine reverse thrust for accelerate stop. - VR (for contaminated runway only – No change for wet runway). These data are provided for atmospheric non icing conditions. In case of atmospheric icing conditions, refer to 6.06 to combine both effects (runway conditions + atmospheric icing conditions). NOTE 1. : Wind and slope corrections are the same as for dry runways. NOTE 2. : Operation on a wet or contaminated runway at a weight in excess of that permitted on an equivalent dry runway is not allowed.
SEP 98
APPENDICES & SUPPLEMENTS AFM
R
NON DRY RUNWAYS ADVISORY MATERIALS
V1 LIMITED BY VMCG : Refer to 6.03 p 2: V1 limited by VMCG on DRY RUNWAYS
Date révision antérieure
7 –03 PAGE : 2 DGAC APPROVED
001 SEP 99
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 3 DGAC APPROVED
001 SEP 98
WET RUNWAY TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O./R.T.O POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 4 DGAC APPROVED
001 SEP 98
WET RUNWAY TAKE OFF DISTANCE (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O./R.T.O POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 5 DGAC APPROVED
001 SEP 98
WET RUNWAY ACCELERATE STOP DISTANCE (FLAPS 15) R
TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE JAN 93
APPENDICES & SUPPLEMENTS AFM
7 –03
Date révision antérieure
001
PAGE : 6
NON DRY RUNWAYS ADVISORY MATERIALS
DGAC APPROVED
SEP 98
ACTUAL DISTANCE
DISTANCE WITHOUT REVERSER
WET RUNWAY ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
Eng : PW 124
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 7 DGAC APPROVED
001 SEP 98
WATER COVERED RUNWAY : 6.3 mm (1/4 in) TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 8 DGAC APPROVED
001 SEP 98
WATER COVERED RUNWAY : 6.3 mm : (1/4 in) TAKE OFF DISTANCE (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O. POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 9 DGAC APPROVED
001 SEP 98
WATER COVERED RUNWAY : 6.3 mm : (1/4 in) ACCELERATE STOP DISTANCE (FLAPS 15) R
TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
Date révision antérieure
7 –03 001
PAGE : 10
NON DRY RUNWAYS ADVISORY MATERIALS
DGAC APPROVED
SEP 99
WATER COVERED RUNWAY : 6.3 mm : (1/4 in)
ACTUAL DISTANCE WITHOUT REVERSER
ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
THEORETICAL DISTANCE
R
Eng : PW 124
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 11
001
DGAC APPROVED
SEP 98
WATER COVERED RUNWAY : 6.3 mm (1/4 in) ROTATION SPEED VR (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 12 DGAC APPROVED
001 SEP 98
WATER COVERED RUNWAY : 12.7 mm (1/2 in) TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 13
001
DGAC APPROVED
SEP 98
WATER COVERED RUNWAY : 12.7 mm (1/2 in) TAKE OFF DISTANCE (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 14 DGAC APPROVED
001 SEP 98
WATER COVERED RUNWAY : 12.7 mm (1/2 in) ACCELERATE STOP DISTANCE (FLAPS 15) R
TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
7 –03
Date révision antérieure
001
PAGE : 15
NON DRY RUNWAYS ADVISORY MATERIALS
DGAC APPROVED
SEP 99
WATER COVERED RUNWAY : 12.7 mm : (1/2 in)
ACTUAL DISTANCE WITHOUT REVERSER
ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
THEORETICAL DISTANCE
R
Eng :
PW 124
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 16 DGAC APPROVED
001 JUL 03
WATER COVERED RUNWAY : 12.7 mm (1/2 in) ROTATION SPEED VR (FLAPS 15) R
ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWER AIR CONDITIONING OFF– ANTI DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 17 DGAC APPROVED
001 SEP 98
COMPACTED SNOW COVERED RUNWAY TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 18 DGAC APPROVED
001 SEP 98
COMPACTED SNOW COVERED RUNWAY TAKE OFF DISTANCE (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 19 DGAC APPROVED
001 SEP 98
COMPACTED SNOW COVERED RUNWAY ACCELERATE STOP DISTANCE (FLAPS 15) TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
7 –03
Date révision antérieure
001
PAGE : 20
NON DRY RUNWAYS ADVISORY MATERIALS
DGAC APPROVED
SEP 99
COMPACTED SNOW COVERED RUNWAY ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)
THEORETICAL DISTANCE
ACTUAL DISTANCE WITHOUT REVERSER
R
Eng :
PW 124
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 21 DGAC APPROVED
001 SEP 98
COMPACTED SNOW COVERED RUNWAY ROTATION SPEED – VR (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 22 DGAC APPROVED
001 SEP 98
ICE COVERED RUNWAY TAKE OFF RUN (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 23 DGAC APPROVED
001 SEP 98
ICE COVERED RUNWAY TAKE OFF DISTANCE (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT T.O/R.T.O POWER – AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 24 DGAC APPROVED
001 SEP 98
ICE COVERED RUNWAY ACCELERATE STOP DISTANCE (FLAPS 15) R
TWO ENGINES OPERATING OR ONE ENGINE FAILED AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS
001
PAGE : 25
NON DRY RUNWAYS ADVISORY MATERIALS
AFM
Date révision antérieure
DGAC APPROVED
SEP 99
ICE COVERED RUNWAY ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15) (FT)
(METERS) 4000
(METERS) 4000
3500
3500
13000
(FT)
13000
3000
3000
R 11000
11000
2500
2500
9000
9000
2000
2000
7000 ACTUAL DISTANCE WITHOUT REVERSER
7000
1500
1000
3000
500
1000
THEORETICAL DISTANCE
5000
Eng : PW 124
1500
5000
1000
3000
500
1000
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 26 DGAC APPROVED
001 SEP 98
ICE COVERED RUNWAY ROTATION SPEED – VR (FLAPS 15) ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWER AIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND
Eng : PW 124
DATE REVISION ANTERIEURE
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 26A 001 DGAC APPROVED
DATE REVISION ANTERIEURE
SEP 98
TAKE OFF RUN CORRECTIONS (FLAPS 15)
3250
(FT)
(METERS)
(METERS)
(FT)
WATER COVERED RUNWAY : 6.3 or 12.7 mm (1/4 or 1/2 inch)
3250
12000
12000
2750
2750
10000
10000
2250
2250
8000
8000
1750
1750
6000
6000
1250
1250
750
2000
250
0
35 FEET HEIGHT
4000 15 FEET HEIGHT
4000
750
2000
250
0
Eng : PW 124
7 –03
APPENDICES & SUPPLEMENTS AFM
PAGE : 26B 001
NON DRY RUNWAYS ADVISORY MATERIALS
DGAC APPROVED
DATE REVISION ANTERIEURE
SEP 98
TAKE OFF DISTANCE CORRECTIONS (FLAPS 15)
3250
(FT)
(METERS)
(METERS)
(FT)
WATER COVERED RUNWAY : 6.3 or 12.7 mm (1/4 or 1/2 inch)
3250
12000
12000
2750
2750
10000
10000
2250
2250
8000
8000
1750
1750
6000
6000
750
2000
250
0
35 FEET HEIGHT
4000
1250 15 FEET HEIGHT
1250
4000
750
2000
250
0
Eng : PW 124
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 27 DGAC APPROVED
Date de révision antérieure
001 SEP 99
7 . 03 . 03 – LANDING Three cases of contaminated runways have been considered : R
- water : applicable for depths between 3mm (1/ 8 in) and 12.7 mm (1 / 2 in) of water, or less than 12.7 mm (1 / 2 in) of slush or equivalent depth of loose snow. - compacted snow - ice The landing distance is computed with and without the use of reversers. Since the effect of asymmetrical reverse thrust is not predictable with a sufficient accuracy on contaminated runways, it is therefore not recommended to use single engine reverse thrust. The actual landing distances without reversers, only, are to be used for flight preparation. The following data are provided for atmospheric non icing conditions. In case of atmospheric icing conditions, refer to 6.06 to combine both effects (runway conditions + atmospheric icing conditions).
SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 28 DGAC APPROVED
001
DATE REVISION ANTERIEURE
SEP 98
OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH DEPTH
Eng : PW 124
ACTUAL DISTANCE WITHOUT REVERSER
THEORETICAL DISTANCE WITH TWO REVERSERS
LANDING DISTANCE (FLAPS 30)
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 29 DGAC APPROVED
Date révision antérieure
001 SEP 98
OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH. LANDING DISTANCE CORRECTIONS
Eng :
PW 124
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 30 DGAC APPROVED
Date révision antérieure
001 SEP 98
OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH. LANDING DISTANCE CORRECTIONS
Eng :
PW 124
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 31 DGAC APPROVED
001
DATE REVISION ANTERIEURE
SEP 98
Eng : PW 124
ACTUAL DISTANCE WITHOUT REVERSER
THEORETICAL DISTANCE WITH TWO REVERSERS
OPERATION ON RUNWAY COVERED WITH COMPACTED SNOW LANDING DISTANCE (FLAPS 30)
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03 PAGE : 32 DGAC APPROVED
OPERATION ON RUNWAY COVERED WITH COMPACTED SNOW LANDING DISTANCE CORRECTION
Eng :
PW 124
Date révision antérieure
001 SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS
7 –03
Date révision antérieure
001
PAGE : 33 DGAC APPROVED
SEP 98
OPERATION ON RUNWAYS COVERED WITH COMPACTED SNOW LANDING DISTANCE CORRECTIONS
Eng :
PW 124
APPENDICES & SUPPLEMENTS NON DRY RUNWAYS ADVISORY MATERIALS
PAGE : 34 DGAC APPROVED
001
DATE REVISION ANTERIEURE
SEP 98
Eng : PW 124
ACTUAL DISTANCE WITHOUT REVERSER
OPERATION ON ICY RUNWAY LANDING DISTANCE ( FLAPS 30)
THEORETICAL DISTANCE WITH TWO REVERSERS
AFM
7 –03
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS OPERATION ON ICY RUNWAY LANDING DISTANCE CORRECTION
Eng : PW 124
7 –03 PAGE : 35 DGAC APPROVED
001 SEP 98
APPENDICES & SUPPLEMENTS AFM
NON DRY RUNWAYS ADVISORY MATERIALS OPERATION ON ICY RUNWAY LANDING DISTANCE CORRECTIONS
Eng : PW 124
7 –03 PAGE : 36 DGAC APPROVED
001 SEP 98
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