AFM 72 202

P1 TQ

AUG 07

--

LIST OF TEMPORARY REVISIONS

L. T. R.AFM

0 01

082EASA

APPROVED

AIRPLANE FLIGHT MANUAL

NoTR

EDITIONDATE DESTROYED INSERTION

DATE NAME OR REMARKS

01 SEP 06 AT REV 21DATED AUG 07 TR 42 EASA

PAGE : 001

MAY 92

–

AFM

0 02

DATE REASON FOR TEMPORARY REVISION CHAP INVOLVED

1AIRPLANE FLIGHT MANUAL

R . T . R . DGACAPPROVED

OCT 89 Introduction of modification 1742 2.04 – 3.04

Limitations – Power plant – 2.04Limitations updating

Reduced flaps landing procedure : 5.04 – 7.02add landing distance coefficient

Procedure following failure : 5.02Modification of the procedure EEC FAULT

Graph add 6.05

JAN 90 Flight with pitch elevators disconnected 5.04 – 7.02Modification of the procedure following failure

JUN 90 Introduction of the Modification 1603 4.04

JAN 91 Introduction of modification 2803 4.03

MAY 91 Mod 2735, additional data 2.04 – 6.02Introduction of modification 2595 2.02 – 3.00 – 3.06Change of modification number 4.00 – 4.03 – 7.00concerning mod 2059 7.02

JUL 91 Mod 2813 + 3156 + 3074 2.00 – 2.05 – 5.02Introduction of TCAS 5.04 – 7.00 – 7.01

7.02

Mod 2464 : wording improvement 2.03

Addition of landing distances associated to 5.04increased speeds and introduction of Mod 1742(Engine anti–icing instead of Engine de–icing)Minor change (wording)

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 2.05 – 7.01

MAR 92 Change of TCAS modification number 1.02 – 2.00 – 2.055.02 – 5.04 – 7.00

7.01 – 7.02

PAGE : 001

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AFM

0 02


2

DEC 92MAR 93JUL 93OCT 93DEC 93FEB 94APR 94

R

NOV 94JAN 95

24 JAN 95

MAR 95



MAR 95NOV 92 Introduction of models 211--212 2.00 -- 2.012.02 -- 2.03

2.04 -- 2.05 -- 3.023.03 -- 3.04 -- 3.064.03 -- 5.02 -- 5.046.01 -- 6.02 -- 6.036.04 -- 6.05 -- 6.06

7.01 -- 7.02

DEC 92 Introduction of Mod 3560 2.04 -- 6.03(PW127 with propeller 14 SFL--11) 6.04 -- 6.05

6.06 -- 7.01

MAR 93 Introduction of Mod 3644 7.00(dry unpaved runways)

Introduction of Mod 3651 2.02 -- 7.01(MTOW increase)

JUL 93 PW 127 Power Plant : Introduction of 2.04temporary limitation

OCT 93 Introduction of Mod 3792 (steep slope approach) 7.00 -- 7.01associated to Mod 3793 (GPWS MK VII)

DEC 93 Introduction of Mod 3849 (MZ FW increase) 2.02Single DC GEN electrical limitation 2.05Acceptable fuels 2.04

FEB 94 Changes in validity of mods 3651 + 3849 2.02 -- 7.01(Design weights)

APR 94 Use of grass runways (Mod 3644) 7.02Introduction of Mod 3952 2.00 -- 2.05(GPS B / K KLN 90 A)

NOV 94 Enforcement of AD no T 94--245 R1 2.05

JAN 95 Cancellation of AD no T 94--245 R1 and 2.00 -- 2.05 -- 3.04Enforcement of AD no T 95 008 025 2.06 -- 4.00 -- 4.05

5.00 -- 5.04

24 JAN 95 Change in the limitations chapter, about icing 2.06conditions

FEB 95 -- Introduction of Mods 4111 and 4230 3.03 -- 3.04 -- 3.05(Deletion of CONT RELIGHT and addition of 4.02 -- 4.05 -- 5.02MAN IGN for aircraft fitted with automatic 7.02relight)

-- Introduction of Mod 4116 (Relocation of 4.04hydraulic green pump control circuit--breaker)

MAR 95 Improvement of Mod 3952 (GPS Bendix/King 2.05KLN 90A)

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0 02


3

FEB 99

R



FEB 99

MAY 95 Introduction of ETOPS 1.02 -- 7.00 -- 7.02

JUN 95 Improvement of procedures 2.01 -- 2.06 -- 3.044.05

JUL 95 Introduction of Mod 4384 (Flight envelope 2.03 -- 2.05change)

SEP 95 Introduction of Mod 3973 1.02 -- 3.02 -- 3.03(Propeller electronic regulation for PW127) 3.04 -- 4.05 -- 5.00

5.02 -- 5.04 -- 7.017.02

15 SEP 95 Introduction of Operations on Narrow runways 7.02Mod 4406

DEC 95 Introduction of Mod 8125 2.05 -- 5.02 -- 5.04(Propeller brake removal)

FEB 96 Introduction of Mod 4371 3.02 -- 3.03 -- 3.04(Propeller electronic regulation for PW124) 4.05 -- 5.00 -- 5.02

5.04 -- 7.01 -- 7.02

DEC 96 Introduction of Mod 4710 (RUNWAY SLOPE 7.01beyond 2%)

DEC 97 Improvement of Missed Approach procedure 3.05

Introduction of Mod 4885 and introduction of 2.05BRNAV capacity for GNSS HT 1000

APR 98 Introduction of Mod 4890 : 2.05GPS KLN90B/BRNAV

JUN 98 Smoke procedures improvement (cargo version 4.03mod 2595)

PEC FAULT procedure improvement 5.04

NOV 98 Introduction of Mod 5022 : new version of GPS 2.05KLN90B/BRNAV

FEB 99 Severe Icing: improvement of detection and 2.06 -- 3.04 -- 4.05procedures

PAGE : 001

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AFM

0 02



R . T . R . EASAAPPROVED AUG 07

MAR 01 Introduction of Mod 8259 : 2.05 -- 7.01TCAS Collins on King avionics

FEB 03 Introduction of modifications 5377+5434 : 7.01Cockpit Door Locking Systemfor Models 102--202--212

OCT 03 Introduction of modifications 5377+8333 : 7.01Cockpit Door Locking Systemfor Models 101--201--211and amendment of Cockpit Door Jammedprocedure for all models

MAR06 Introduction of modification 5561 : 5.04 -- 6.05Messier--Bugatti Wheels and Brakes

SEP 06 FUEL Feeding Limitations Harmonization 2.04EMER DESCENT procedure amendment 4.05ONE EEC OFF procedure harmonization 5.02

AFM AIRPLANE FLIGHT MANUAL 0-04 page 1-082

ATR 72

L.E.T.P. List of EffectiveTemporary Pages EASA AUG 07

You must hold in your manual the following pages Issue P CH SE Page Seq Date Label Modification expression Validity expression

REV21 0 01 001 082 AUG 07 L.T.R. TQ ALL REV21 0 02 001 001 MAY 92 R.T.R. ALL REV21 0 02 002 001 AUG 95 R.T.R. ALL REV21 0 02 003 001 SEP 99 R.T.R. ALL REV21 0 02 004 001 AUG 07 R.T.R. ALL REV21 0 04 001 082 AUG 07 L.E.T.P. TQ ALL

End TQ

PAGE : 001

AUG 07

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AFM

0 05

5EASA

APPROVED


L . N . R .

LIST OF NORMAL REVISIONS

N0REV

INSERTEDDATE

EASA APPROVED

19 JUL 05 EASA A.A. 01029

20 JUL 06 EASA A.A. 01205

21 AUG 07 EASA A.A. 01555

PAGE : 001

FEB 91

–

AFM

0 06

DATE REASON FOR NORMAL REVISION CHAP INVOLVED


R . N . R . DGACAPPROVED

DEC 89 Cancellation of the temporary revisionof Oct 89

Introduction of modification 2495 2.04

Introduction of modification 2464 2.03

Introduction of auxiliary aft cargo 4.03smoke procedure (Mod : 2059)

Introduction of the forward cargo 4.03smoke procedure (Mod : 1861)

Modification of the “pitch disconnect” 5.04 – 7.02procedure

MAY 90 Introduction of mod 2456 2.05

Landing flaps 00 : modification of landing 5.04 – 7.02distance correction coefficient

Modification of the OXYGEN LO PR procedure 5.04

Flight in icing conditions. Effect on approach 6.06climb gradient weight. Graph modification.

Introduction of the brake energy limitation for 7.02dispatch flaps 00

Introduction of the dispatch with one AFUinoperative 7.02

Introduction of the dispatch with ATPCS OFF 7.02

Introduction of the supplement “Ferry flight withpitch elevators disconnected” 7.02

FEB 91 Environmental correct extension (T/O andlanding) 2.03

Explanations or figures improved 4.03 – 7.01 – 6.022.04 – 1.02 – 2.02

6.03 – 5.02

060

PAGE :

MAY 92

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AFM2

DGACAPPROVED


R . N . R .

001


FEB 91 Procedure changes 2.04 – 2.05Introduction of modification 2735 2.04 – 6.03 – 6.04

6.06

Non valid pages (delivery error) 5.04

Non valid page to be deleted 3.03(All planes embody modif 2403).

Yellow page changes to white (mod 1603) 4.04

CDL improvement (Jacking point covers) 7.01

Introduction of modif 2803 4.03

AUG 91 Yellow pages to be turned white 1.02 – 2.00 – 2.02(from temporary revision N0 5, MAY 91 2.03 – 2.04 – 0.05and N0 6, JUL91) 3.00 – 3.06 – 4.00

4.03 – 5.02 – 5.046.02 – 7.00 – 7.01

7.02

Procedure improvement 4.03 – 4.05 – 5.027.02 – 5.04

Lay out and wording 1.02 – 2.01 – 2.055.04 – 6.02 – 5.026.03 – 6.06 – 4.04

5.04 – 7.00

MAY 92 Introduction of mod 8044 2.03 – 6.03(tail wind limit up to 15 kt)

Remodelling of title pages 2.00 – 2.05 – 3.003.06 – 4.00 – 4.036.00 – 7.00 – 7.01

7.02

Procedure improvement 2.04 – 3.02 – 3.054.03 – 5.02 – 5.035.04 – 7.01 – 7.02

Graphes improvement 2.02 – 6.01 – 6.026.03 – 6.04 – 6.056.06 – 7.01 – 7.02

060

PAGE : 001

FEB 94

–

AFM3

DGACAPPROVED


R . N . R .


MAY 92 Yellow pages to be turned to white 2.01 – 2.05 – 4.035.02 – 5.04– 7.01

7.02Lay out and wording 1.02 – 5.04 – 6.01

6.03 – 7.02Pages to be deleted 1.02 – 2.00 – 2.04

2.05 – 3.00 – 4.007.00

APR 93 Yellow pages to be turned to white 2.00 – 2.01 – 2.022.03 – 2.04 – 2.053.02 – 3.03 – 3.043.06 – 4.03 – 5.025.04 – 6.01 – 6.026.03 – 6.04 – 6.056.06 – 7.01 – 7.02

Pages to be deleted 2.03Modification of TCAS number 2.00 – 2.05 – 5.02

5.04 – 7.00 – 7.017.02


Wording and lay out improvement 1.02 – 2.01 – 2.046.01 – 6.02 – 6.036.05 – 6.06 – 7.01

FEB 94 Yellow pages to be turned to white 2.02 – 2.04 – 2.057.00 – 7.01 – 7.02

Pages to be deleted 2.04 – 6.01247F propeller retrofit 2.04 – 6.03 – 6.04

6.05 – 6.06 – 7.01Procedure improvement 2.04 –3.04 – 3.07

5.02 – 5.04 – 6.057.02

Wording and lay out improvement 1.02 – 2.00 – 2.063.04 – 5.01 – 5.046.00 – 6.03 – 6.047.00 – 7.01 – 7.02

Graph improvement 6.03 – 6.05 – 6.067.02

060

PAGE : 001

OCT 96

–

AFM4


R . N . R . DGACAPPROVED


AUG 95 Yellow pages to be turned to white 1.02 – 2.00 – 2.012.05 – 2.06 – 3.003.03 – 3.04 – 3.054.00 – 4.02 – 4.044.05 – 5.00 – 5.02

5.04 – 7.02

Pages to be deleted 1.02 – 2.00 – 2.012.05 – 2.06 – 3.044.00 – 5.00 – 5.04

7.02

Procedure improvement 2.04 – 3.04 – 3.054.04 – 5.02 – 5.04

7.01 – 7.02

Wording and lay out improvement, typing errors 1.02 – 1.03 – 3.024.00 – 4.02 – 5.025.03 – 5.04 – 6.02

6.03

Graph improvement or correction 7.02

OCT 96 Yellow pages to be turned to white 2.03 – 2.05 – 3.023.03 – 4.05 – 5.005.02 – 5.04 – 7.02

Pages to be deleted 1.02 – 2.04 – 3.033.04 – 4.05 – 5.025.04 – 6.03 – 6.046.05 – 6.06 – 7.01

7.02


Wording and lay out improvement, typing errors 1.02 – 2.05 – 3.044.05 – 5.02 – 5.035.04 – 6.01 – 6.036.06 – 7.00 – 7.01

7.02

Graph improvement or correction 6.01 – 6.02 – 6.036.04 – 6.05 – 6.06

7.01 – 7.02

060

PAGE : 001

SEP 97

–

AFM5

DGACAPPROVED


R . N . R .


OCT 96 KVS1G extension at take off 6.03

Enforcement of “Consigne de navigabilité no 2.01 – 2.05 – 2.0696 – 207 – 031 (B)” 3.04 – 4.00 – 4.05

SEP 97 Yellow pages to be turned to white 7.00 – 7.01

Pages to be deleted 2.05 – 4.03 – 5.027.02

Limitation – Procedure Improvement 1.02 – 2.04 – 3.044.04 – 4.05 – 5.04

6.02 – 7.02

Wording and layout improvement, typing errors 3.05 – 6.00 – 6.016.03

Graph improvement or correction 6.01 – 6.03 – 6.057.01

Part 2.05 presentation improvement 2.00 – 2.05Part 5.02 presentation improvement 5.02

Container transportation presentation improvement 2.02 – 3.00 –3.064.00 – 4.03 – 7.02

Mod 4295 introduction – Mod 4111 anti–mod 3.00 – 3.03 – 3.043.05 – 4.02 – 4.05

5.02 – 7.02

Mod 4654 introduction – Installation of 2.05HT1000 GNSS

Flaps retracted dispatch 7.02

060

PAGE : 001

SEP 99

–

AFM6

DGACAPPROVED


R . N . R .


SEP 98 Yellow pages to be turned to white 2.05 – 3.05 – 4.035.04

Pages to be deleted 7.02

Mod 4597 introduction – Mod 3952 anti–mod 2.05

Procedure improvement 3.04 – 4.04 – 7.02

Introduction of dispatch with one torque indicator 7.02inoperative

Graph improvement or correction 6.06 – 7.01

Introduction of wet and contaminated runways 7.03advisory materials

Wording and layout improvement, typing errors 1.02 – 1.03 – 2.053.07 – 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 2.05

Introduction of Mod 4511 (New look for 3.06 – 4.03 – 7.02transport container)Introduction of Mod 8233 (Power plant) 7.01

Engine limitation change 2.04

Procedures improvement 2.05 – 3.06 – 4.055.02 – 5.04 – 7.01

Effect of Mod 4371 (Electronic propeller control 7.03regulation) on wet and contaminated runwaysperformances.V1 limited by VMCG on wet and contaminated 7.03 runways

Wording and layout , typing errors 1.02 – 4.04 – 5.046.03 – 6.06 – 7.007.00 – 7.02 – 7.03

060

PAGE : 001

JUL 02

–

AFM7

DGACAPPROVED


R . N . R .


SEP 00 Introduction of Mod 5176 : GNSS, 2.05Load software final baseline.

Manual management about the TCAS 7.01

Introduction of a new appendix 7.00 – 7.01

Pages to be deleted 2.05 – 5.02 – 5.04 7.01 – 7.02

Procedure improvement 2.04 – 3.04 – 3.054.05 – 7.02

Graph improvement 2.02

Wording and layout improvement 1.01 – 4.00 –5.04Typing error 7.01

SEP 01 Yellow pages to be turned to white 2.05 – 7.01

Procedure Improvement 4.05

Steep Slope Approach : add a tail wind limitation 7.01.05as for model 42–500

Take Off after use of fluids type II or IV 7.01.08

JUL 02 5313 : Enhanced GPWS activation with GPWS 2.00 – 2.05MK VIII 3.00 – 3.07 – 4.05

Use of rudder in case of large sideslip angles 2.03

Procedure improvement : at normal landing with 3.05PW124 with electronic regulation it is not necessary to have NP ≥ 86%

Typing error 4.02

060

PAGE : 001

SEP 03

–

AFM8

DGACAPPROVED


R . N . R .


SEP 03 Temporary revisions to be turned to white TR39 Introduction of modifications 5377+5434 : 7.01

Cockpit Door Locking System

Introduction of modifications :5403 : GNSS HT1000 P–RNAV 2.05

Trims checks updating 3.01 – 3.02

ELEC SMK procedure : adding of 4.03DC SVCE & UTLY BUS ... OFF item

Severe Icing Procedure Improvement 4.05

FWD and AFT SMK Procedures Improvement 4.03for cargo version

Steep Slope Approach prohibited for : 4.05 – 5.04Severe Icing, Reduced Flaps Landing,Pitch Disconnect

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 7.02.04

deactivated or removed– Dispatch with anti skid system inoperative 7.02.05

Improvement of CLIMB sequence in case of 7.02.07dispatch ONE EEC OFF : reduce both TQbefore PWR MGT on CLB for engines withelectronic regulation

LBA supplement creation 7.04

Various 7.00.00

060

PAGE : 001

JUL 05

–

AFM9

EASAAPPROVED


R . N . R .


JUL 04 Yellow pages to be turned whiteTR40 : Cockpit Door Security System ST2 7.01

Securized Cockpit Door Jammed Procedure 7.01improvement

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

JUL 05 EASA/DGAC Approval 1.01

Limitations of minimum fuel temperature : 2.04to ensure adequate relight

Steep Slope Approach : ≥4.5� (not >) 5.04 – 7.00 – 7.01

Introduction of modification 5465 7.01New Securized Cockpit Door Fittings

Complement for EGPWS Mod 5467 2.05 – 3.00 – 4.05

Dispâtch with wheel brake removed is not possible 7.00 – 7.02

060

PAGE : 001

AUG 07

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AFM10

EASAAPPROVED


R . N . R .


JUL 06 Use of Jet B is prohibited 2.04

Cockpit Checks Preparation Trims’ Title 3.00

Introduction of modification 5561 : 6.05Messier--Bugatti Wheels and Brakes

TCAS new wording for Traffic Advisory case 7.01

Introduction of modification 5567 : MPC 7.00 -- 7.01Multi Purpose Computer -- APM :Aircraft Performance Monitoring

Introduction of modification 5570 and 8431 : 7.00 -- 7.01Enhanced Surveillance

Introduction of modification 5506 : 7.00 -- 7.01ACARS

AUG 07 Blanking of TR24:FUEL Feeding Limitations Harmonization 2.04EMER DESCENT procedure amendment 4.05ONE EEC OFF procedure harmonization 5.02

Fuels RT and TS1 acceptable 2.04

Part 4 Emergency Procedures Improvement 4

7.01 and 7.02 parts wholly revised 7.00 -- 7.01 -- 7.02Numbering of Appendices and Supplements

Introduction of modification 8442 : MPC 7.01.15

New High Latitudes Operations 7.01.18

IAC Supplement for Operations in CIS countries 7.09


ATR 72

S.N.N.P. Shipping Note Normal Pages EASA AUG 07

Action P CH SE Page Seq Date Validation Criteria

" ADD " = Add "DESTROY" = Destroy " …….." = Revised

"SEE VAL" = See Validation

ADD 0 01 001 082 AUG 07 L.T.R. TQ ...... 0 02 004 001 AUG 07 R.T.R. ...... 0 04 001 082 AUG 07 L.E.T.P. TQ ...... 0 05 005 001 AUG 07 L.N.R. ...... 0 06 010 001 AUG 07 R.N.R. ...... 0 08 001 082 AUG 07 L.E.N.P. TQ ...... 0 09 001 082 AUG 07 L.O.M. TQ ...... 0 10 001 082 AUG 07 C.R.T. TQ ADD 2 02 001 002 APR 93 201-202-211-212 ADD 2 02 002 002 APR 93 201-202-211-212 ...... 2 04 004 001 AUG 07 ADD 2 05 004 050 SEP 01 MOD 3074 or 3113 or 3625 or 3832 or 8259 ...... 4 00 001 001 AUG 07 ...... 4 02 001 001 AUG 07 ...... 4 02 002 001 AUG 07

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...... 4 03 001 001 AUG 07 ...... 4 03 002 001 AUG 07 ...... 4 03 003 002 AUG 07 102-202-212 ...... 4 03 004 001 AUG 07 ...... 4 03 005 001 AUG 07 ADD 4 04 001 001 AUG 07 ...... 4 04 001 160 AUG 07 MOD 1603 ...... 4 05 001 001 AUG 07 ...... 4 05 002 001 AUG 07 DESTROY 4 05 002 020 JUL 05 MOD 5313 or 5467 ...... 4 05 003 001 AUG 07 DESTROY 4 05 003 020 JUL 05 MOD 5313 or 5467 ...... 4 05 004 001 AUG 07 ...... 5 02 001 001 AUG 07 ...... 7 00 001 001 AUG 07 ...... 7 00 002 001 AUG 07

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CANCEL AND REPLACE ALL PAGES OF 7-01 AND 7-02 CHAPTERS.

NEW PAGES ARE LISTED IN LIST OF EFFECTIVE NORMAL PAGES

( LENP)

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L.E.N.P. List of Effective Normal Pages EASA AUG 07

You must hold in your manual the following normal pages M P CH SE Page Seq Date Label Validity expression

NORMAL REVISION N° 21 0 00 001 001 FEB 94 COVER PAGE

ALL N 0 01 001 082 AUG 07 L.T.R. TQ

ALL 0 02 001 001 MAY 92 R.T.R.

ALL 0 02 002 001 AUG 95 R.T.R.

ALL 0 02 003 001 SEP 99 R.T.R.

ALL R 0 02 004 001 AUG 07 R.T.R.

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ALL R 0 05 005 001 AUG 07 L.N.R.

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ALL 0 06 002 001 MAY 92 R.N.R.

ALL 0 06 003 001 FEB 94 R.N.R.

ALL 0 06 004 001 OCT 96 R.N.R.

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6 01 005 001 SEP 89 ALL

6 01 006 001 OCT 96 ALL

6 01 007 001 OCT 96 ALL

6 01 008 001 SEP 97 ALL

6 01 009 001 SEP 97 ALL

6 01 010 001 OCT 96 ALL

6 01 011 001 OCT 96 ALL

6 01 012 001 SEP 97 ALL

Turn TQ


ATR 72



6 01 013 001 SEP 97 ALL

6 02 001 001 OCT 96 PW124 ALL

6 02 002 050 OCT 96 PW124 MOD 2735 ALL

6 02 003 001 OCT 96 PW124 ALL

6 03 001 001 SEP 97 ALL

6 03 002 001 OCT 96 PW124 ALL

6 03 003 001 OCT 96 PW124 ALL

6 03 004 001 MAY 92 ALL

6 03 005 001 SEP 98 ALL

6 03 005A 001 APR 93 PW124 ALL

6 03 006 001 APR 93 ALL

6 03 007 001 OCT 96 PW124 ALL

6 03 008 120 OCT 96 PW124 MOD 2735 ALL

6 03 009 001 OCT 96 PW124 ALL

6 03 010 001 OCT 96 PW124 ALL

6 03 011 080 OCT 96 MOD 8044 or 3522 ALL

6 03 012 001 OCT 96 PW124 ALL

6 03 013 001 OCT 96 PW124 ALL

Turn TQ


ATR 72



6 03 014 080 OCT 96 MOD 8044 or 3522 ALL

6 03 015 001 SEP 99 PW124 ALL

6 03 016 080 OCT 96 MOD 8044 or 3522 ALL

6 03 017 001 OCT 96 PW124 ALL

6 03 018 001 OCT 96 PW124 ALL

6 03 019 001 OCT 96 PW124 ALL

6 03 020 001 OCT 96 ALL

6 03 021 001 OCT 96 PW124 ALL

6 03 022 001 OCT 96 PW124 ALL

6 03 023 001 OCT 96 PW124 ALL

6 03 024 001 OCT 96 PW124 ALL

6 03 025 001 OCT 96 PW124 ALL

6 03 026 001 OCT 96 PW124 ALL

6 03 027 001 OCT 96 PW124 ALL

6 03 031 001 OCT 96 ALL

6 03 032 001 OCT 96 ALL

6 04 001 001 APR 93 ALL

6 04 002 120 OCT 96 PW124 MOD 2735 ALL

Turn TQ


ATR 72



6 05 001 001 FEB 94 PW124 ALL

6 05 002 001 OCT 96 PW124 ALL

6 05 003 001 OCT 96 PW124 ALL

6 05 004 001 SEP 97 PW124 ALL

6 06 001 001 JUL 04 ALL

6 06 002 130 OCT 96 PW124 MOD 1368 ALL

6 06 003 001 APR 93 PW124 ALL

6 06 004 001 SEP 99 PW124 ALL

6 06 005 220 OCT 96 PW124 MOD 1368 +2735 ALL

6 06 006 001 SEP 99 PW124 ALL

6 06 007 001 SEP 99 PW124 ALL

6 06 008 001 SEP 99 PW124 ALL

6 06 008A 001 JUL 04 ALL

6 06 009 001 JUL 04 PW124 ALL

6 06 009A 001 JUL 04 ALL

6 06 010 001 JUL 04 PW124 ALL

6 06 011 220 OCT 96 PW124 MOD 1368 +2735 ALL

6 06 012 130 SEP 98 PW124 MOD 1368 ALL

Turn TQ


ATR 72



6 06 013 130 SEP 98 PW124 MOD 1368 ALL

R 7 00 001 001 AUG 07 ALL

R 7 00 002 001 AUG 07 ALL

N 7 01 01 001 002 AUG 07 201-202 - PW124 TQ0002

N 7 01 01 001 110 AUG 07 201-202 - PW124 MOD 3651 TQ0001

N 7 01 02 001 001 AUG 07 ALL

N 7 01 02 002 001 AUG 07 ALL

N 7 01 02 003 001 AUG 07 ALL

N 7 01 02 004 001 AUG 07 ALL

N 7 01 02 005 001 AUG 07 ALL

N 7 01 02 006 001 AUG 07 ALL

N 7 01 03 001 150 AUG 07 MOD 0069 +1112 ALL

N 7 01 03 002 100 AUG 07 MOD 1112 ALL

N 7 01 03 003 100 AUG 07 MOD 1112 ALL

N 7 01 03 004 100 AUG 07 MOD 1112 ALL

N 7 01 03 005 150 AUG 07 MOD 0069 +1112 ALL

N 7 01 03 006 100 AUG 07 MOD 1112 ALL

N 7 01 03 007 100 AUG 07 PW124 MOD 1112 ALL

Turn TQ


ATR 72



N 7 01 03 008 100 AUG 07 MOD 1112 ALL

N 7 01 03 009 100 AUG 07 MOD 1112 ALL

N 7 01 03 010 100 AUG 07 MOD 1112 ALL

N 7 01 03 011 100 AUG 07 MOD 1112 ALL

N 7 01 03 012 100 AUG 07 PW124 MOD 1112 ALL

N 7 01 03 013 230 AUG 07 PW124 MOD 1112 +1368 ALL

N 7 01 04 001 001 AUG 07 ALL

N 7 01 04 002 001 AUG 07 ALL

N 7 01 04 003 001 AUG 07 ALL

N 7 01 04 004 001 AUG 07 ALL

N 7 01 04 005 110 AUG 07 MOD 5205 ALL

N 7 01 05 001 001 AUG 07 ALL

N 7 01 06 001 001 AUG 07 ALL

N 7 01 08 001 100 AUG 07 PW124 ALL

N 7 01 08 002 150 AUG 07 PW124 MOD 2735 ALL

N 7 01 08 003 170 AUG 07 PW124 MOD 1368 +2735 ALL

N 7 01 09 001 001 AUG 07 ALL

N 7 01 10 001 001 AUG 07 ALL

Turn TQ


ATR 72



N 7 01 11 001 001 AUG 07 ALL

N 7 01 12 001 001 AUG 07 ALL

N 7 01 12 001A 001 AUG 07 ALL

N 7 01 12 001B 001 AUG 07 ALL

N 7 01 13 001 100 AUG 07 MOD 5434 or 5465 or 8330 or 8333 ALL

N 7 01 13 002 100 AUG 07 MOD 5434 or 8330 ALL

N 7 01 15 001 001 AUG 07 ALL

N 7 01 15 002 001 AUG 07 ALL

N 7 01 16 001 001 AUG 07 ALL

N 7 01 17 001 001 AUG 07 ALL

N 7 01 18 001 001 AUG 07 ALL

N 7 01 19 001 001 AUG 07 ALL

N 7 02 00 001 001 AUG 07 ALL

N 7 02 01 001 001 AUG 07 ALL

N 7 02 01 002 001 AUG 07 ALL

N 7 02 01 003 001 AUG 07 ALL

N 7 02 01 004 001 AUG 07 ALL

N 7 02 02 001 001 AUG 07 PW124 ALL

Turn TQ


ATR 72



N 7 02 03 001 001 AUG 07 PW124 ALL

N 7 02 03 002 001 AUG 07 PW124 ALL

N 7 02 03 003 001 AUG 07 PW124 ALL

N 7 02 03 004 001 AUG 07 PW124 ALL

N 7 02 04 001 001 AUG 07 ALL

N 7 02 05 001 001 AUG 07 ALL

N 7 02 05 002 001 AUG 07 ALL

N 7 02 06 001 001 AUG 07 PW124 ALL

N 7 02 06 002 001 AUG 07 PW124 ALL

N 7 02 06 003 001 AUG 07 PW124 ALL

N 7 02 06 004 001 AUG 07 PW124 ALL

N 7 02 07 001 001 AUG 07 PW124 ALL

N 7 02 07 002 001 AUG 07 PW124 ALL

N 7 02 07 003 001 AUG 07 PW124 ALL

N 7 02 07 004 001 AUG 07 PW124 ALL

N 7 02 07 005 001 AUG 07 PW124 ALL

N 7 02 08 001 001 AUG 07 ALL

N 7 02 09 001 001 AUG 07 ALL

Turn TQ


ATR 72



N 7 02 09 002 001 AUG 07 ALL

N 7 02 09 003 001 AUG 07 ALL

N 7 02 09 004 001 AUG 07 ALL

N 7 02 09 005 001 AUG 07 ALL

N 7 02 09 006 001 AUG 07 PW124 ALL

N 7 02 09 007 001 AUG 07 PW124 ALL

N 7 02 09 008 001 AUG 07 PW124 ALL

N 7 02 09 009 001 AUG 07 PW124 ALL

N 7 02 09 010 001 AUG 07 PW124 ALL

N 7 02 09 011 001 AUG 07 PW124 ALL

N 7 02 10 001 001 AUG 07 PW124 ALL

N 7 02 10 002 001 AUG 07 PW124 ALL

N 7 02 10 003 001 AUG 07 PW124 ALL

N 7 02 10 004 001 AUG 07 PW124 ALL

N 7 02 11 001 001 AUG 07 ALL

N 7 02 11 002 001 AUG 07 ALL

N 7 02 11 003 001 AUG 07 ALL

N 7 02 12 001 001 AUG 07 ALL

Turn TQ


ATR 72



7 03 001 001 SEP 99 ALL

7 03 001A 001 SEP 99 ALL

7 03 002 001 SEP 99 ALL

7 03 003 001 SEP 98 PW124 ALL

7 03 004 001 SEP 98 PW124 ALL

7 03 005 001 SEP 98 PW124 ALL

7 03 006 001 SEP 98 PW124 ALL

7 03 007 001 SEP 98 PW124 ALL

7 03 008 001 SEP 98 PW124 ALL

7 03 009 001 SEP 98 PW124 ALL

7 03 010 001 SEP 99 PW124 ALL

7 03 011 001 SEP 98 PW124 ALL

7 03 012 001 SEP 98 PW124 ALL

7 03 013 001 SEP 98 PW124 ALL

7 03 014 001 SEP 98 PW124 ALL

7 03 015 001 SEP 99 PW124 ALL

7 03 016 001 JUL 03 PW124 ALL

7 03 017 001 SEP 98 PW124 ALL

Turn TQ


ATR 72



7 03 018 001 SEP 98 PW124 ALL

7 03 019 001 SEP 98 PW124 ALL

7 03 020 001 SEP 99 PW124 ALL

7 03 021 001 SEP 98 PW124 ALL

7 03 022 001 SEP 98 PW124 ALL

7 03 023 001 SEP 98 PW124 ALL

7 03 024 001 SEP 98 PW124 ALL

7 03 025 001 SEP 99 PW124 ALL

7 03 026 001 SEP 98 PW124 ALL

7 03 026A 001 SEP 98 PW124 ALL

7 03 026B 001 SEP 98 PW124 ALL

7 03 027 001 SEP 99 ALL

7 03 028 001 SEP 98 PW124 ALL

7 03 029 001 SEP 98 PW124 ALL

7 03 030 001 SEP 98 PW124 ALL

7 03 031 001 SEP 98 PW124 ALL

7 03 032 001 SEP 98 PW124 ALL

7 03 033 001 SEP 98 PW124 ALL

Turn TQ


ATR 72



7 03 034 001 SEP 98 PW124 ALL

7 03 035 001 SEP 98 PW124 ALL

7 03 036 001 SEP 98 PW124 ALL

End TQ


ATR 72

L.O.M. List of Modifications EASA AUG 07

MODIF PARTS TITLE VALIDITY

0069 7 AFCS. USE OF A CAT.II APPROVED AP/FD

DOWN TO 50 FT. ALL 1112 7 AUTO FLIGHT - RETROFIT CAT 2

CAPABILITY TO A/C DELIVERED CAT 1 CAPABILITY

ALL 1368 5 - 6 - 7 ICE AND RAIN PROTECTION - INSTALL

INNER WING DE-ICING SYSTEM ALL 1603 4 ELECTRICAL POWER - INSTALL TRU ON

PROVISION TQ0001 2456 2 COMMUNICATIONS - RELOCATE VHF2

ANTENNA ON UPPER FUSELAGE ALL 2735 2 - 6 - 7 ENGINE INDICATING - CHANGE

SOFTWARE ES 06 IN E.E.C ALL 3037 2 PNEUMATIC - ECS - MODIFY ISOLATING

VALVE OPENING CONTROL IN TAXYING ALL 3168 5 AUTO FLIGHT - REPLACE AFC

COMPUTER ALL 3522 2 - 6 GENERAL - CERTIFY ATR 72 FOR 15 KT

TAILWIND LANDING ALL 3625 2 - 5 NAVIGATION - INSTALL A SFE TCAS

COMPUTER ALL 3651 2 - 7 GENERAL - INCREASE MTOW AT

22,000KGS (48,500LBS) TQ0001

Turn TQ


ATR 72

L.O.M. List of Modifications EASA AUG 07

MODIF PARTS TITLE VALIDITY

3832 2 - 7 NAVIGATION - REPLACE COLLINS TCAS - COMPUTER

ALL 4654 2 NAVIGATION - INSTALL HT1000 GNSS ON

FULL PROVISION ALL 4885 2 NAVIGATION - GNSS - REPLACE NPU BY

A NEW ONE ALL 5176 2 NAVIGATION - GNSS - LOAD SOFTWARE

FINAL BASELINE ALL 5205 7 NAVIGATION - ATC/TCAS - ACQUIRE

ALTITUDE VIA BUS ARINC 429 ALL 5313 2 - 3 - 4 NAVIGATION - EGPWS MKVIII -

ENHANCED PART ACTIVATION ALL 5377 7 EQUIPMENT/FURNISHINGS - WIRING FOR

COCKPIT ENTRANCE SECURISED ALL 5403 2 NAVIGATION - CERTIFICATION OF GNSS

P-RNAV ALL 5434 7 EQUIPMENT/FURNISHINGS - INSTALL

DOOR ON ELECTRICAL PROVISION ALL 5467 3 NAVIGATION - EGPWS - INSTALLATION

EGPWS MKVIII P/N 965-1206-011 ALL 8044 2 - 6 GENERAL - CERTIFY ATR 72 FOR 15 KT

TAILWIND LANDING TQ0002

End TQ


ATR 72

C.R.T. Cross Reference Table EASA AUG 07

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. M.S.N. REGISTRATION

TQ0001 0365 PP-PTH TQ0002 0352

End TQ

00

CONTENTS

1GENERAL

PAGE : 001

SEP 89

Eng : ALL

DGACAPPROVED

–

Model : ALLMod : –

AFM1

1 . 00 – CONTENTS

1 . 01 – INTRODUCTION

1 . 02 – PARTICULAR EXPLANATIONS

DEFINITION OF WORDINGUNIT CONVERSIONGLOSSARY OF STANDARD NOMENCLATURE

1 . 03 – 3 VIEW DRAWING

01

INTRODUCTION

1GENERAL

PAGE : 001EASA

APPROVED

–

AFM1

SEP 89

JUL 05

R

R

SEP 00

The Airplane Flight Manual (AFM) is related to a specific airplane whosemodel is specified on the heading page. It is approved by : EASA.

NOTE : “DGAC APPROVED” is kept on pages created/revised before EASAcreation. This mention is changed to “EASA APPROVED” for all new orrevised pages.

ORGANIZATION OF THE MANUAL

The AFM contents are divided into seven chapters :

1 – General2 – Limitations3 – Normal procedures4 – Emergency procedures5 – Procedures following failure6 – Performance7 – Appendices and supplements

Preliminary pages include all approval references and define the updatingstatus 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 contentis valid for all models mentioned on the heading page(0.00 page 1).

02

PARTICULAR EXPLANATIONS

1GENERAL

PAGE : 001

SEP 98DGAC

APPROVED

–

AFM1 SEP 89

RR

1 . 02 . 01 – DEFINITION OF WORDING

Note : An operating procedure, technique etc... consideredessential to emphasize

CAUTION : An operating procedure, technique etc... which mayresult in damage to equipment if not carefully followed

WARNING : An operating procedure, technique etc... which mayresult in injury or loss of life if not carefully followed.

1 . 02 . 02 – UNIT CONVERSION

Weight 1 kg = 2.2046 lb 1 lb = 0.4536 kg

Length – AltitudeDistance 1 m = 3.2808 ft 1 ft = 0.3048 m

1 m = 39.3701 in 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

02


1GENERAL

PAGE : 001

SEP 98DGACAPPROVED

–

AFM2

R

MAY 92

APR 93

1 . 02 . 03 – GLOSSARY OF STANDARD NOMENCLATURE

AAS Anti–icing Advisory SystemA/C AircraftAC Alternating CurrentACW Alternating Current Wild FrequencyADC Air Data ComputerADF Automatic Direction FindingADI Attitude Director IndicatorADU Advisory Display UnitAFCS Automatic Flight Control SystemA/FEATH Automatic FeatheringAFM Airplane Flight ManualAFT Rear PartAFU Auto Feathering UnitAGL Above Ground LevelAH Ampere – HoursAHRS Attitude and Heading Reference SystemAHRU Attitude and Heading Reference UnitAIR COND Air ConditioningALT Altitude ANN AnnunciatorAP Auto–Pilot APP Approach ARM Armed ASCB Avionics Standard Communications Bus ASD Acceleration Stop Distance ASI Air Speed Indicator ATC Air Traffic Control ATE Automatic Test Equipment ATPCS Automatic Take off Power Control System ATT Attitude ATTND Attendant AUTO Automatic AUX Auxiliary BARO Barometric BAT Battery BC Back Course BPCU Bus Power Control Unit BPU Battery Protection UnitB–RNAV Basic Area NavigationBRK BrakeBRT BrightBTC Bus Tie ContactorBTR Bus Tie Relay

02


1GENERAL

PAGE : 001

SEP 98DGAC

APPROVED

–

AFM3

R

AUG 91SEP 97

R

BXR Battery Transfer RelayCAB CabinCAP Crew Alerting PanelCAPT CaptainCAS Calibrated Air SpeedCAT CategoryC/B Circuit BreakerCCAS Centralized Crew Alerting SystemCDI Course Deviation IndicatorCFC Constant Frequency ContactorCG Center of GravityCHC Charge ContactorCH ChargeCHG ChargerCL Condition LeverCLA Condition Lever AngleCLB ClimbCLR ClearCM Crew MemberCOM CommunicationCOMPT CompartmentCONFIG ConfigurationCONT ContinuousCORRECT CorrectionCPL Auto Pilot CouplingCR CruiseCRC Continuous Repetitive ChimeCRS CourseCRT Cathodic ray tubeCRZ CruiseCTL ControlCVR Cockpit Voice RecorderdB DecibelDC Direct CurrentDEC Declination DecreaseDELTA P Differential PressureDEV DeviationDFDR Digital Flight Data RecorderDG.C Celsius DegreeDGR DegradedDH Decision HeightDIFF DifferentialDIM Light DimmerDIST DistanceDME Distance Measuring Equipment

02


1GENERAL

PAGE : 001

JUL 04DGACAPPROVED

–

AFM4

SEP 89

R

MAY 95AUG 95OCT 96

DN DownDSPL DisplayEADI Electronic Attitude Director IndicatorEEC Electronic Engine ControlEFIS Electronic Flight Instrument SystemEGHR External Ground Handling RelayEHSI Electronic Horizontal Situation IndicatorELEC ElectricalELV ElevationEMER EmergencyENG EngineEPC External Power ContactorET Elapsed TimeETOPS Extended Twin OperationsEXT Exterior, ExternalEXC External Power/Service Bus ContactorFAIL Failed, FailureFD Flight DirectorFDAU Flight Data Acquisition UnitFDEP Flight Data Entry PanelFEATH or FTR Feather, FeatheringFF Fuel FlowFI Flight IdleFL Flight LevelFLT FlightF/O First OfficierFQI Fuel Quantity IndicationFT, ft Foot, FeetFU Fuel UsedFWD ForwardGA Go aroundGAL GalleyGC Generator ContactorGCU Generator Control UnitGD Gear DownGEN GeneratorGI Ground IdleGMT Greenwitch Mean TimeGND GroundGPS Global Positioning SystemGPU Ground Power Unit(E)GPWS (Enhanced) Ground Proximity Warning SystemG/S Glide SlopeGU Gear Up

02


1GENERAL

PAGE : 001

SEP 98DGACAPPROVED

–

AFM5

SEP 89

R

R

SEP 97

R

HD Head DownHDG HeadingHF High FrequencyHI HighHLD HoldHMU Hydromechanical UnitHP High PressureHPa Hecto PascalHSI Horizontal Situation IndicatorHYD HydraulicIAF Initial Approach FixIAS Indicated Air SpeedIDT IdentIFR Instrument Flight RulesILS Instrument Landing SystemINC IncreaseIND IndicatorIN, in Inch(es)IN/HG Inches of MercuryINHI InhibitINST InstrumentINT InterphoneINV InverterISOL IsolationITT Inter Turbine TemperatureKg, KG KilogrammeKHZ Kilo – HertzKT, kt KnotLB PoundLBA Lowest Blade AngleLDG LandingL/G Landing GearLH Left HandLIM LimitationL–NAV Lateral NavigationLO LowLOC LocaliserLO PR Low PressureLT LightLVL LevelM, m MeterMAC Mean Aerodynamic ChordMAN ManualMAP Ground MappingMAX Maximum

02


1GENERAL

PAGE : 001

JUL 04DGACAPPROVED

–

AFM6

SEP 89

R

AUG 95SEP 99

MBE Maximum Brake EnergyMC Master CautionMCT Maximum ContinuousMEA Minimum en Route AltitudeMFC Multi Function ComputerMGT ManagementMHZ MegahertzMIC MicrophoneMIN MinimumMKR MarkerMM MillimeterMMO Maximum Operating Machmn MinuteMW Master WarningMTOW Maximum Take–off WeightNAV NavigationNDB Non Directional BearingNEG NegativeNH High Pressure Spool Rotation SpeedNIL Nothing, No objectNM Nautical MileNORM NormalNP Propeller Rotation SpeedN/W Nose WheelOAT Outside Air TemperatureOBS Omni Bearing SelectorOCL Obstacle Clearance LimitOUTB OutboardOVBD OverboardOVHT OverheatOVRD OverrideOXY OxygenPA Passenger AdressPAX PassengerPB Push ButtonPCU Propeller control UnitPEC Propeller electronic controlPF Pilot FlyingPIT PitchPL Power LeverPLA Power Lever AnglePNF Pilot Non FlyingPNL PanelPOS PositionP–RNAV Precision Area NavigationPR PressurePRESS Pressurization, Pressure

02


1GENERAL

PAGE : 001

JUL 04DGACAPPROVED

–

AFM7

SEP 89

R

R

AUG 95SEP 98

PRKG ParkingPROP PropellerPSI Pound per Square InchPT PointPTT Push to Talk, Push to TestPWR PowerQFU Runway HeadingQTY QuantityRA Radio AltitudeRAD/INT Radio/InterphoneRAIM Receiver Autonomous Integrity MonitoringRCAU Remote Control Audio UnitRCDR RecorderRCL RecallRCU Rudder releasable Centering UnitRECIRC RecirculationREF ReferenceREV ReverseRH Right HandRMI Radio Magnetic IndicatorRPM Revolution Per MinuteRQD RequiredRTO Reserve Take–offRUD RudderRWY RunwaySAT Static Air TemperatureSBY Stand BySC Single Chime, Starter ContactorSEL SelectorSGL SingleSGU Symbol Generator UnitSID Standard Instrument DepartureS/O or SO Shut OffSPD SpeedSSR Service Bus Select RelaySTAB StabilizerSTAR Standard ArrivalSTBY Stand BySTR Service Bus Transfer RelaySTRG SteeringSVCE ServiceSW SwitchSYS SystemTAD Terrain Awareness DisplayTAS True Air SpeedTAT Total Air TemperatureTAWS Terrain Awareness Warning SystemTBD To be Determinated

02


1GENERAL

PAGE : 001

JUL 04DGAC

APPROVED

–

AFM8

R

MAY 92SEP 98

TCAS Traffic alert and collision avoidance systemTCAS RA TCAS resolution advisoryTCAS TA TCAS traffic advisoryTCF Terrain Clearance FloorTCS Touch Control SteeringTEMP TemperatureTGT TargetTK TankTLU Travel Limitation UnitTO Take–offTOD Take–off DistanceTOR Take–off RunTOW Take–off WeightTQ TorqueUBC Utility Bus ContactorU/F UnderfloorUHF Ultra High FrequencyUNDV UndervoltageUNLK UnlockUTLY UtilityVA Design Maneuvering SpeedVAPP Approach SpeedVC Calibrated AirspeedVENT VentilationVERT VerticalVFE Flaps Extended SpeedVFR Visual Flight RulesVFTO Final Take–off SpeedVGA Go around speedVHF Very High FrequencyVLE Landing Gear Extended SpeedVLO Landing Gear Operating SpeedVLOF Lift Off SpeedVMCA Minimum Control Speed in flightVMCG Minimum Control Speed on GroundVMCL Minimum Control Speed in Flight (Landing config).VMO Maximum Operating SpeedVMU Minimum Unstick SpeedVOR VHF Omni Directional RangeVR Rotation SpeedVRA Rough Air SpeedVS1G Stall SpeedVS Vertical SpeedVSI Vertical Speed IndicatorVU Visual UnitWARN Warning

02


1GENERAL

PAGE : 001

SEP 98DGACAPPROVED

–

AFM9

R

FEB 94

XFEED Cross FeedXFR TransferYD Yaw DamperZ AltitudeZA Aircraft AltitudeZCTH Theoretical Cabin AltitudeZFW Zero Fuel WeightZP Pressure AltitudeZPI Indicated Pressure AltitudeZRA Radio Altimeter Altitude�P Differential Pressure

03

3 VIEW DRAWING

1GENERAL

PAGE : 001

SEP 98DGACAPPROVED

–

AFM1

SEP 89

AUG 95

10.772 m (424.095 in)

27.149 m (1068.859 in)

27.166 m (1069.528 in)

3.962 m (155.984 in)

4.10 m

8.10 m (318.898 in)

27.05 m (1064.961 in)

2.362 m (92.992 in)

7.65

m (

301.

181

in)

7.31

m (

287.

795

in)

(161.417 in)

R

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 REFERENCECHORD 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 LATO 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 LATO 25 % OF LV 12.484 m ( 491.496 in). . . . . . . . . . . . . . . . . . . . . . . .

00

CONTENTS

2LIMITATIONS

PAGE : 001

JUL 02DGAC

APPROVED

–

AFM1

NOV 92APR 93

FEB 94

APR 94

R

JAN 95

AUG 95SEP 97

2 . 00 – CONTENTS

2 . 01 – GENERAL

INTRODUCTIONKINDS OF OPERATIONMINIMUM FLIGHT CREWPERFORMANCE CONFIGURATIONMAXIMUM OPERATING ALTITUDEMANEUVERING LIMIT LOAD FACTORSCONFIGURATION DEVIATION LISTNOISE CHARACTERISTICSMAXIMUM NUMBER OF PASSENGER SEATS

2 . 02 – WEIGHT AND LOADING

WEIGHTSCENTER OF GRAVITY ENVELOPELOADING

2 . 03 – AIRSPEED AND OPERATIONAL PARAMETERS

AIRSPEEDSOPERATIONAL PARAMETERS

2 . 04 – POWER PLANT

ENGINESPROPELLERSOIL SYSTEMSTARTERFUEL SYSTEM

2 . 05 – SYSTEMS

AIR - PRESSURIZATIONHYDRAULIC SYSTEMLANDING GEARFLAPSAFCSINSTRUMENTS MARKINGCARGO DOOR OPERATIONMFCCOMMUNICATIONSELECTRICALTCASGPSEGPWS

2 . 06 – ICING CONDITIONS

01

GENERAL

2LIMITATIONS

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM1

MAY 92APR 93

JUN 95

AUG 95

R

2 . 01 . 01 – INTRODUCTIONObservance of the limitations contained in this chapter is required by law.When operating in accordance with an approved appendix or supplement tothis manual, the limitations of this basic Airplane Flight Manual section apply,except as altered by such an appendix or supplement.

2 . 01 . 02 – KINDS OF OPERATIONThe airplane is certified in the Transport Category, JAR 25 and ICAO annex 16for day and night operations, in the following conditions when the appropriateequipment and instruments required by the airworthiness and operatingregulations 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 CREW2 pilots

2 . 01 . 04 – PERFORMANCE CONFIGURATIONRefer to 6.01.03 for airplane configuration associated with certifiedperformances.

2 . 01 . 05 – MAXIMUM OPERATING ALTITUDE25000 ft

2 . 01 . 06 – MANEUVERING LIMIT LOAD FACTORSGear and flaps retracted : + 2.5 to – 1 gGear and/or flaps extended : + 2 to 0 g

2 . 01 . 07 – CONFIGURATION DEVIATION LISTRefer to 7.01.02

2 . 01 . 08 – NOISE CHARACTERISTICSThe aircraft meets the requirements of ICAO annex 16, Chapter 3 with noweight restriction.Refer to noise characteristics in Appendix 7.01.01 of this manual for noiselevels.

2 . 01 . 09 – MAXIMUM NUMBER OF PASSENGER SEATS74 as limited by emergency exits configuration.

02

WEIGHT AND LOADING

2LIMITATIONS

PAGE : 002

APR 93

Eng : ALL

DGACAPPROVED

–

Model : 201 – 202 – 211 – 212Mod : –

AFM1

NOV 92

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 byperformance 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

02

WEIGHT AND LOADING

2LIMITATIONS

PAGE : 070

FEB 94

Eng : ALL

DGAC APPROVED

–

Model : 201 – 202 – 211 – 212Mod : 3651

AFM1

MAR 93

R

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 byperformance 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

02

WEIGHT AND LOADING

2LIMITATIONS

PAGE : 002

APR 93

Eng : ALL

DGACAPPROVED

–

Model : 201 – 202 – 211 – 212Mod : –

AFM2

NOV 92

2 . 02 . 02 – CENTER OF GRAVITY ENVELOPE

For definition of reference (Mean Aerodynamic Chord (MAC) and momentsorigin) : see chapter 1

2 . 02 . 03 – LOADING

The airplane must be loaded in accordance with the loading instructions givenin the WEIGHT AND BALANCE manual.

02

WEIGHT AND LOADING

2LIMITATIONS

PAGE : 070

SEP 00DGAC

APPROVED

–

Model : 201 – 202 – 211 – 212Mod : 3651

AFM2

MAR 93

R

FEB 94

2 . 02 . 02 – CENTER OF GRAVITY ENVELOPE

For definition of reference (Mean Aerodynamic Chord (MAC) and momentsorigin) : see chapter 1

2 . 02 . 03 – LOADING

The airplane must be loaded in accordance with the loading instructions givenin the WEIGHT AND BALANCE manual.

03

AIRSPEED AND OPERATIONALPARAMETERS

2LIMITATIONS

PAGE : 001

JUL 02DGACAPPROVED

–

AFM1

SEP 89

�

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 thatinvolve angles of attack near the stall should be confined to speedsbelow VA.

VA = 175 kt CAS

CAUTION : Rapidly alternating large rudder applications incombination with large sideslip angles may result instructural failure at any speed.

• MAXIMUM FLAPS EXTENDED OR OPERATING SPEEDS VFE

FLAPS 15 185 kt CASFLAPS 30 150 kt CAS

• MAXIMUM LANDING GEAR EXTENDED OR OPERATING SPEEDS

VLE = 185 kt CASVLO lowering = 170 kt CAS

retracting = 160 kt CAS

03

AIRSPEED AND OPERATIONALPARAMETERS

2LIMITATIONS

PAGE : 230

APR 93

Eng : ALL

DGACAPPROVED

–

Model : ALLMod : 3037+ (8044 or 3522)

AFM2

R

NOV 92

2 . 03 . 02 – OPERATIONAL PARAMETERSENVIRONMENTAL 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 %

04

POWER PLANT

2LIMITATIONS

PAGE : 120

SEP 00

Eng : PW124

DGACAPPROVED

–

Mod : 2735

AFM1

R

NOV 92APR 93FEB 94AUG 95SEP 99

2 . 04 . 01 – ENGINES PRATT AND WHITNEY OF CANADA PW 124 – BOperating limits with no unscheduled maintenance action required

Beyond these limits refer to maintenance manual

POWERSETTING

TIME LIMIT TQ(%)

ITT(oC)

NH(%)

NL(%)

NP(%)

OILPRESS(PSI)

OIL TEMP(oC)

RESERVETAKE 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)

MAXIMUMCONTINUOUS

NONE 102.5 800 102.7 104 101 55 to 65 0 to 125 (3)

GROUNDIDLE

66mini

40 mini –40 to 125(3)

HOTELMODE

715 55 to 65 125 (3)

STARTING 5 s 950 –54 mini

OTHER 102.3 (2) 800

TRANSIENT 20 s 124.5 840 103.7 104.3 115 40 to 100

10 mn 106.3

(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 timelimitation.20 mn are authorized between 115oC (120oC in hotel mode) and 125oC.

NOTE : Oil temperature must be maintained above 45oC to ensure intake strutde–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.

NOTE : Flight with an engine running and the propeller feathered isnot permitted.

04

POWER PLANT

2LIMITATIONS

PAGE : 001

SEP 89

Eng : PW124

DGACAPPROVED

–

AFM2

TAKE OFF

ITT LIMITS AT TAKE OFF POWER

04

POWER PLANT

2LIMITATIONS

PAGE : 001

SEP 97

Eng : PW124

DGACAPPROVED

–

AFM3

NOV 92APR 93

R

AUG 95

OCT 96

2 . 04 . 02 – PROPELLERS

TWO HAMILTON STANDARD 14 SF 11

GROUND OPERATION

� Avoid static operation between 41 % and 65 % Np

� Avoid use of feather position above 47 % TQ.

� Engine run up must be performed into the wind.

� Do not exceed 91.7 % TQ below 30 kt except for transients of enginerun up at start of take off and for brief service checks of 2 minutes orless each.

� Do not exceed 91.6% NP below 30 kt except for transients , at the startof take off and for brief service checks of 2 minutes or less each.

GROUND OR FLIGHT OPERATION

� If a propeller is involved in an overspeed or in an engine overtorquerefer to the propeller maintenance manual.

FLIGHT OPERATION

� ATR airplanes are protected against a positioning of power leversbelow 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 inan engine overspeed condition and consequent loss of engine power.

04

POWER PLANT

2LIMITATIONS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM4

APR 93NOV 92

DEC 93

FEB 94AUG 95JUL 04JUL 05

R

JUL 06SEP 06

R

R

R

2 . 04 . 03 -- OIL SYSTEM

SPECIFICATIONRefer to specification PWA 521 type II

2 . 04 . 04 -- STARTER

3 starts with a 1 minute 30 seconds maximum combined starter running timefollowed by 4 minutes OFF.

2 . 04 . 05 -- FUEL SYSTEM

Acceptable fuels : Jet A, Jet A1, JP5 and RT, TS1.Use of JP4 and Jet B is prohibited.

TEMPERATURE• For flight preparation, a minimum fuel temperature must be takeninto 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.

REFUELINGMaximum pressure 3.5 bars (50 PSI)

USABLE FUELThe total quantity of fuel usable in each tank is : 2500 kg (5510 lbs)

NOTE :Fuel remaining in the tankswhenquantity indicators showzero is notusable in flight.

UNBALANCEMaximum fuel unbalance : 730 kg (1609 lbs)

FEEDING• Each electrical pump is able to supply one engine in the wholeflight envelope.

• One electrical pump and associated jet pump are able to supplyboth engines in the whole flight envelope.

05

SYSTEMS

2LIMITATIONS

PAGE : 001

JUL 04DGACAPPROVED

–

AFM1

APR 93NOV 92

DEC 93FEB 94NOV 94JAN 95

AUG 95

R

OCT 96SEP 97

R

2 . 05 . 01 – AIR PRESSURIZATION

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 VALVEfull open selection 1 PSI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum altitude for one bleed off operation 20000 ft. . . . . . . . . . . . . . . . . .

2 . 05 . 02 – HYDRAULIC SYSTEM

Specification : Hyjet IV or Skydrol LD 4

2 . 05 . 03 – LANDING GEARTowing with TOWBARLESS system is prohibited.Do not perform pivoting (sharp turns) upon a landing gear with fully brakedwheels except in case of emergency.

2 . 05 . 04 – FLAPS

Holding with any flaps extended is prohibited in icing conditions (except forsingle engine operations).

2 . 05 . 05 – AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)

– 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 limitsYellow arc : caution areaGreen arc : normal area

05

SYSTEMS

2LIMITATIONS

PAGE : 150

SEP 97DGAC

APPROVED

–

Model :102 or 202 or 212Mod : 2456

AFM2

R

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 prohibited2 . 05 . 09 – COMMUNICATIONS

Not applicable

05

SYSTEMS

2LIMITATIONS

PAGE : 001

SEP 97DGAC

APPROVED

–

AFM3

Date de révisionantérieure

APR 94

R

JAN 95

AUG 952 . 05 . 10 – ELECTRICAL

Single DC GEN operation :– In flight, if OAT exceeds ISA + 25, flight level must be limited to FL200

05

SYSTEMS

2LIMITATIONS

PAGE : 050

SEP 00

DGACAPPROVED

–

Mod : 3074 or 3113 or 3625 or 3832 or 8259

AFM4

MAY 92

APR 93

JAN 95

AUG 95

SEP 97

SEP 99

SEP 01

R

MAR 01

2.05.11 – TCAS.

REFER TO APPENDIX 7.01.04

05

SYSTEMS

2LIMITATIONS

PAGE : 500

SEP 03DGAC

APPROVED

–

AFM5


Mod : 5403

2 . 05 . 11 – GPS

1 – GENERALThe 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 operationalapproval/authorization to conduct operations. Aircraft operators must applyto 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 onlyone long range navigation system is required.

- supplemental navigation means, en route, in terminal area and for nonprecision approach operations until the missed approach point withrespect 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 alternativemeans of navigation.

- In addition, where the coupled DME option is not installed or if the coupled DME isnot 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). Dispatchmust not be made in the event of predicted continuous loss of RAIM of morethan 5 minutes for any part of the intended flight.(b) Traditional navigation equipment must be selected to available aids so asto allow immediate cross–checking or reversion in the event of loss of GPSnavigation capability.

05

SYSTEMS

2LIMITATIONS

PAGE : 020EASA

APPROVED

–

AFM6

JUL 05

Mod : 5313 or 5467R

JUL 02

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 awarenesstool only. It does not have the integrity, accuracy or fidelity on whichto solely base decisions for terrain or obstacle avoidance.

2.To avoid giving nuisance alerts, the predictive TAWS functions must beinhibited when landing at an airport that is not included in the airportdatabase.

06

ICING CONDITIONS

2LIMITATIONS

PAGE : 001

MAY 99DGACAPPROVED

–

AFM1

DEC 89

R

FEB 94JAN 95

24 JAN 95JUN 95AUG 95OCT 96FEB 99

R

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.

� 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 forperformance data.

� Operation in ground icing conditions :Refer to 3.04.01 for associated procedures and to FCOM part 3 and toAFM section 7.03 for advisory information on contaminated runwayspenalties.

.../...

06

ICING CONDITIONS

2LIMITATIONS

PAGE : 001

JUL 04DGACAPPROVED

–

AFM2

R

DEC 96

FEB 99

2 . 06 . 01 – ICING CONDITIONS (cont’d)� Severe icing :

WARNING :Severe icing may result from environmental conditions outside of those forwhich the airplane is certificated. Flight in freezing rain, freezing drizzle, ormixed icing conditions (supercooled liquid water and ice crystals) may resultin ice build–up on protected surfaces exceeding the capability of the iceprotection system, or may result in ice forming aft of the protected surfaces.This ice may not be shed using the ice protection systems, and mayseriously 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 :

Visual cue identifying severe icing is characterized by ice covering all or asubstantial 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 priorityhandling from Air Traffic Control to facilitate a route or an altitude change toexit the icing conditions. Apply procedure specified in the EmergencyProcedures chapter.

– Since the autopilot may mask tactile cues that indicate adverse changes inhandling characteristics, use of the autopilot is prohibited when the severeicing defined above exists, or when unusual lateral trim requirements orautopilot trim warnings are encountered while the airplane is in icingconditions.

00

CONTENTS

3NORMAL PROCEDURES

PAGE : 001

JUL 06EASAAPPROVED

--

AFM1

MAY 92FEB 94

R

R

SEP 97

3 . 00 -- CONTENTS

3 . 01 -- COCKPIT PREPARATION CHECKS

ENGINE FIRE PROTECTION

TRIMS

ENGINE

CVR / DFDR

3 . 02 -- DAILY CHECKS

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

3 . 07 -- GPWS OR EGPWS

01

COCKPIT PREPARATION CHECKS

3NORMAL PROCEDURES

PAGE : 001 OCT 96

DGACAPPROVED

–

AFM1

DEC 89

R

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

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 illuminatesTurn 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.

02

DAILY CHECKS

3NORMAL PROCEDURES

PAGE : 001AUG 95

Eng : PW124

DGACAPPROVED

–

AFM1

NOV 92APR 93

R

SEP 03

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 lostand consequently, both main hyd. pumps are temporarily lost aswell.

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

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

03

TAKE OFF

3NORMAL PROCEDURES

PAGE : 001

APR 93

Eng : ALL

DGACAPPROVED

–


AFM1

NOV 92

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

04

FLIGHT CONDITIONS

3NORMAL PROCEDURES

PAGE : 001

SEP 00DGACAPPROVED

–

AFM1

SEP 89APR 93FEB 94JAN 95

R

JUN 95AUG 95OCT 96FEB 99MAY 99

R

3 . 04 . 01 – ICING CONDITIONS

• DEFINITIONRefer to 2 .06 .01

� Procedure for operation in atmospheric icing conditions :

• As soon as and as long as atmospheric icing conditions exist, thefollowing procedures must be applied :ANTI–ICING (propellers, horns, side–windows) ON. . . . . . . . . . . . . . . . PROP MODE SEL According to SAT. . . . . . . . . . . . . . . . . . . . . . . . . . . . NP set � 86 %. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Minimum maneuver/operatingicing speed BUGGED AND OBSERVED. . . . . . . . . . . . . . . . . . . . . . . . . . ICE ACCRETION MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE :horns anti icing selection triggers the illumination of the ”ICINGAOA” green light, and lowers the AOA stall warning threshold.

• At first visual indication of ice accretion and as long as atmospheric icingconditions 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.

• When leaving icing conditions, CONT RELIGHT, DE ICING and ANTIICING may be switched OFF.

• When the aircraft is visually verified clear of ice, ICING AOA caption maybe cancelled and normal speeds may be used.

NOTE :Experience has shown that the last part to clear is the iceevidence probe. As long as this condition is not reached the icingspeeds must be observed and the ICING AOA caption must notbe cancelled.

04

FLIGHT CONDITIONS

3NORMAL PROCEDURES

PAGE : 130

SEP 98

Eng : PW124

DGACAPPROVED

–

Mod : 1368

AFM2

R

NOV 92APR 93

FEB 94

OCT 96

0

• MINIMUM MANEUVER / OPERATING ICING SPEEDS :

Whenever ICING AOA light is lit, the following minimum icing speeds mustbe observed :

FLAPS MINIMUM MANEUVER / OPERATINGICING SPEED

MAXIMUM BANK ANGLE

0 1.43 VS1G 15o

1.21 VS1G T/O, 2nd segment 15o

1.38 VS1G En route 15o

15 1.44 VS1G APPROACH 30o

1.23 VS1G GO AROUND 15o

30 1.30 VS1G 30o

CAUTION :For obstacle clearance, the en–route configuration with enginefailure is FLAPS 150 at a minimum speed of 1.38 VS1G if iceaccretion is observed.

� Procedure for take–off with ground icing conditions but no atmosphericicing 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 takeoff.

• Minimum maneuver/operating speeds :The normal minimum maneuver/operating speeds are applicable.

Refer to FCOM part 3 and AFM section 3 for information on contaminatedrunways penalties.

NOTE :Horns anti icing must not be selected ON to avoid lowering AOA ofthe stall warning threshold.

04

FLIGHT CONDITIONS

3NORMAL PROCEDURES

PAGE : 001

SEP 89

Eng : ALL

DGACAPPROVED

–


AFM3

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. . . . . . . . . . . . . . . . . . . . . .

05

APPROACH AND LANDING

3NORMAL PROCEDURES

PAGE : 001

Eng : PW124

DGACAPPROVED

–

AFM1

R

NOV 92APR 93

AUG 95OCT 96SEP 97DEC 97SEP 98

SEP 00

R

3 . 05 . 01 – NORMAL LANDING

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). . . . . . . . . . .

� Before landingNP � 86 %. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After nose wheel touch downBoth PL GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Both LO PITCH lights Check illuminated. . . . . . . . . . . . . . . . . . . .

CAUTION :If a thrust dissymmetry occurs or if one LO PITCH light isnot 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

06

CONTAINER TRANSPORTATION

3NORMAL PROCEDURES

PAGE : 001

SEP 97DGACAPPROVED

–

AFM1

MAY 92

R 3 . 06 . 01 – CONTAINER TRANSPORTATION

NOT APPLICABLE

07

GPWS

3NORMAL PROCEDURES

PAGE : 040

JUL 04DGAC

APPROVED

–

AFM1

Mod : 5467

3 . 07 . 01 GROUND PROXIMITY WARNING SYSTEM : EGPWS

1. General

Following a EGPWS warning, the crew must immediately focus theirattention on terrain proximity.Positive action to alter the flight path or / and to change the configurationshould 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”

07

GPWS

3NORMAL PROCEDURES

PAGE : 040

JUL 04DGAC

APPROVED

–

AFM2

Mod : 5467

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 turnedon ”OFF” position. Refer to chapter 4.05, Ditching and forced landing.

- In case of landing in abnormal flaps conditions GPWS sw may be turnedon ”OVRD” position, refer to chapter 5.04, flight controls.

- Terrain/Obstacle Awareness Caution. When a terrain awarenessCAUTION occurs, verify the aeroplane flight path and correct it ifrequired. If in doubt, perform a climb until the CAUTION alert ceases.

- Terrain/Obstacle Awareness Warning. If a terrain awareness WARNINGoccurs, immediately initiate and continue a climb that will providemaximum terrain clearance until all alerts cease. Only verticalmanoeuvres are recommended, unless operating in visualmeteorological conditions (VMC), and/or the pilot determines, based onavailable information, that turning in addition to the vertical escapemanoeuvre 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 andtaken into account.

- If the WX radar control is selected OFF, no terrain information will bedisplayed on the EHSI and TERR FAULT amber light will beilluminated.Even in case of a radar failure, select the STBY position.

00

CONTENTS

4EMERGENCY PROCEDURES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

R

R

4 . 00 -- CONTENTS

4 . 01 -- INTRODUCTION

4 . 02 -- POWER PLANT

ENG FIRE OR SEVERE MECHANICAL DAMAGEBOTH ENGINES FLAME OUT

4 . 03 -- SMOKE

SMOKEELECTRICAL SMOKEAIR COND SMOKEFWD SMOKEAFT SMOKEAUX AFT COMPT SMOKE

4 . 04 -- ELECTRICAL SYSTEM

DUAL DC GEN LOSS

4 . 05 -- MISCELLANEOUS

EMERGENCY DESCENTDITCHINGFORCED LANDINGON GROUND EMERGENCY EVACUATIONSEVERE ICING

01

INTRODUCTION


PAGE : 001

SEP 89

Eng : ALL

DGACAPPROVED

–


AFM1

– The following procedures have been established and recommended by theaircraft manufacturer and approved by the Airworthiness Authorities forapplication in the event of a serious failure.

– The framed items correspond to actions performed by memory by the crewwithin a minimum period of time.

– It is assumed that in general, all failures are indicated by the operation ofspecific system warnings and/or by direct observation.

– The actions recommended may result in the loss of certain systems notassociated with the failure.

– If actions depend on a precondition, a preceding black square � is used toidentify the precondition.

– Whenever a procedure calls for LAND AS SOON AS POSSIBLE, theseriousness of the situation as well as use of the nearest suitable airportshould be taken into consideration.

– However, whenever fire is encountered on the airplane, landing at the nearestsuitable airport is recommended.After conducting any fire suppression/smoke evacuation procedure, eventhough smoke has been dissipated, if it has not or cannot be visibly verifiedthat 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 goto 100 % oxygen.

02

POWER PLANT


PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

R

4 . 02 . 01 -- ENGINE FIRE OR SEVERE MECHANICAL DAMAGE

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 secondsSECOND AGENT DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LAND AS SOON AS POSSIBLE

02

POWER PLANT


PAGE : 001

AUG 07EASAAPPROVED

--

AFM2

R

4 . 02 . 02 -- BOTH ENGINES FLAME OUT

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 startsFORCED LANDING or DITCHING PREPARE. . . . . . . . . . . . . . . . . . . . . . . .

03

SMOKE


PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

R 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 sourceELECTRICAL SMOKE procedure (4.03.01) APPLY. . . . . . . . . . . . . . . . . .

J If air conditioning smoke identifiedAIR CONDITIONING SMOKE procedure (4.03.02) APPLY. . . . . . . . . . . .

J If FWD SMK illuminated or smoke in FWD zone of aircraftFWD SMOKE procedure (4.03.03) APPLY. . . . . . . . . . . . . . . . . . . . . . . . . .

J If AFT SMK illuminated or smoke in AFT zone of aircraftAFT 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 identifedLAND AS SOON AS POSSIBLE

• When ∆ P < 1 PSIOVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE NORM. . . . . . . . . . . . . . . . . . . . . . . . .

03

SMOKE


PAGE : 001

AUG 07EASAAPPROVED

--

AFM2

R

4 . 03 . 02 -- AIR CONDITIONING SMOKE

PACK VALVE 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If smoke persistsPACK 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 abnormaloperation in order to avoid shutting down the safeengine.

PL afffected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL afffected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPER PROCEDURE APPLY. . . . . . . . . . . . . . . . . . . . . . . . .

03

SMOKE


PAGE : 002

AUG 07EASAAPPROVED

--

Model : 102 -- 202 -- 212

AFM3

R4 . 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 ANDKILL SOURCE OF SMOKE

• When ∆ P < 1 PSIOVBD 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 : LANDASAP -- If a quick landing is not possible : climb andmaintainminimum FL 160, FL 200 is recommended.

NOTE : Smoke alert may be generated during smoke evacuation process.

03

SMOKE


PAGE : 001

EASAAPPROVED

--

AFM4

R

R

AUG 07

4 . 03 . 04 -- AFT SMOKE

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 : LANDASAP -- If a quick landing is not possible : climb andmaintainminimum FL 160, FL 200 is recommended.

NOTE : Smoke alert may be generated during smoke evacuation process.

03

SMOKE


PAGE : 001

AUG 07EASAAPPROVED

--

AFM5

R 4 . 03 . 05 -- AUX AFT COMPT SMOKE (IF APPLICABLE)

AUX AFT COMPT AGENT DISCHARGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

ELECTRICAL SYSTEM


PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

R

4 . 04 . 01 -- DUAL DC GEN LOSS

DC GEN 1 + 2 OFF then ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If no generator recoveredLAND ASAPMAN 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 illuminationSTICK 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FWhen 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 illuminatesSTBY BUS For approach, OVRD only when necessary. . . . . . . . . . . .

F Before descentPAX INSTRUCTIONS USE PA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F At touch downIDLE GATE LEVER PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

ELECTRICAL SYSTEM


PAGE : 160

AUG 07EASAAPPROVED

--

Mod : 1603

AFM1

R

4 . 04 . 01 -- DUAL DC GEN LOSS

DC GEN 1 + 2 OFF then ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If no generator recoveredTRU 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 illuminationSTICK 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FWhen 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 downIDLE GATE LEVER PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

05

MISCELLANEOUS


PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

R

4 . 05 . 01 -- EMERGENCY DESCENT

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

05

MISCELLANEOUS


PAGE : 001

AUG 07EASAAPPROVED

--

AFM2

R

4 . 05 . 02 -- DITCHING

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 ApproachJ 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 levelDITCH PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . .CABIN REPORT OBTAIN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F Before ditching (200 ft)

MINIMIZE IMPACT SLOPEOPTIMUM 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 beperformed 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

05

MISCELLANEOUS


PAGE : 001

AUG 07EASAAPPROVED

--

AFM3

R

4 . 05 . 03 -- FORCED LANDING

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 ApproachFLAPS (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 enginesmay beperformed 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

05

MISCELLANEOUS


PAGE : 001

AUG 07EASAAPPROVED

--

AFM4

R

4 . 05 . 04 -- ON GROUND EMERGENCY EVACUATION

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

05

MISCELLANEOUS


PAGE : 001

SEP 03

Eng : PW124

DGACAPPROVED

–

AFM5

R

JAN 95JUN 95AUG 95FEB 99MAY 99

4 . 05 . 05 – SEVERE ICING

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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If an unusual roll response or uncommanded roll control movement isobserved��

Push firmly on the control wheelFLAPS 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If the flaps are extended, do not retract them until the airframe is clear ofice

� ��

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

.../...

05

MISCELLANEOUS


PAGE : 001

SEP 03DGACAPPROVED

–

AFM6

R

OCT 96FEB 99MAY 99SEP 99

4 . 05 . 05 – SEVERE ICING (CONT’D)

DETECTION

Visual cue identifying severe icing is characterized by ice covering all or asubstantial 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 normallyobserved to collect ice

. Accumulation of ice on the lower surface of the wing aft of the protectedareas

. Accumulation of ice on propeller spinner farther aft than normallyobserved

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�Cambient air temperature (SAT)

00

CONTENTS

5PROCEDURES FOLLOWING FAILURES

PAGE : 001

AUG 95

Eng : ALL

DGACAPPROVED

–


AFM1 AUG 91

R

JAN 95

5 . 00 – CONTENTS

5 . 01 – INTRODUCTION

5 . 02 – ENGINE

ENGINE FLAME OUTENG OIL LO PREEC FAULTENG RELIGHT ENVELOPEENG RESTART IN FLTENG NAC OVHT

5 . 03 – FLYING WITH ONE ENGINE INOPERATIVE

TAKE OFFAPPROACH AND LANDINGMISSED APPROACH

5 . 04 – SYSTEMS

FUELELECTRICAL SYSTEMHYDRAULIC SYSTEMFLIGHT CONTROLSLANDING GEARAIRICE AND RAIN PROTECTIONMFCAUTOPILOTMISCELLANEOUS

01

INTRODUCTION


PAGE : 001

FEB 94

Eng : ALL

DGACAPPROVED

–


AFM1

SEP 89

R

– The procedures contained in this chapter have been established andrecommended by the aircraft manufacturer and approved by theAirworthiness Authorities as acceptable procedures for a proper use of theaircraft.

– They give information related to system and operational requirements andcover the actions to be followed in case of failures which are not considered asemergency cases (these cases are covered in chapter 4).

– If actions depend on a precondition, a preceding black square � is used toidentify the precondition.

– Only particular operations, which are considered useful to highlight arepresented. Those procedures which are considered to be “basic airmanship”are therefore not covered.

02

ENGINE


PAGE : 001

AUG 07EASAAPPROVED

--

Mod : 3074 or 3113 or 3625

AFM1

MAY 92APR 93

AUG 95OCT 96SEP 97

R

SEP 99SEP 065 . 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 suspectedFIRE HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 . 02 . 02 -- ENG OIL LO PRPL FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .H If both OIL LO PR alert on CAP and local alert are activatedCL FTR then FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

H If local alert only is activatedCL FTR then FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Once engine is shut offH If CONT RELIGHT is required by current flight conditionsmaintain it ONas long as necessary and keep the affected engine shut off.Apply SINGLE ENG OPER PROC

HWhen 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 notCL FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPER PROC APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . .

H If CCAS only is activatedDISREGARDINFORM MAINTENANCENOTE : TCAS must be set on TA only when one engine inoperative.

5 . 02 . 03 -- EEC FAULTATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .H If PL is out of green sectorDo not deselect affected EECWhen adequate, retard PL to green sector

H If PL is within green sectorAffected EEC RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

H If unsuccessfulEEC OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Advance PL to restore power, handling throttle with care.• In final approachCL MAX RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• After landingTaxi with the affected engine feathered

02

ENGINE


PAGE : 001

DGACAPPROVED

–

AFM2

SEP 97

R

FEB 94

5 . 02 . 04 – ENG RELIGHT ENVELOPE

5 . 02 . 05 – ENG RESTART IN FLT

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 % NHCL 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 toMCT position before engine restart in order to cancel propellerfeathering.

5 . 02 . 06 – ENG NAC OVHT

• DURING HOTEL MODE OPERATIONPL GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CL FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

02

ENGINE


PAGE : 001

SEP 97DGACAPPROVED

–

AFM3

SEP 89

• DURING TAXIAircraft STOP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Increase slightly power

�If unsuccessfull within 30 sPL GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CL FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

03

FLYING WITH ONE ENGINEINOPERATIVE


PAGE : 001

Eng : ALL

DGACAPPROVED

–


AFM1

SEP 89APR 93

R

AUG 95OCT 96

5 . 03 . 01 – TAKE–OFF

� 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 isrecommended to maintain the speed reached without exceeding V2 + 10 Kt.In any case the minimum speed must be equal to V2.

03

FLYING WITH ONE ENGINEINOPERATIVE


PAGE : 001

AUG 95

Eng : ALL

DGACAPPROVED

–


AFM2

R

MAY 92APR 93

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 theground.

5 . 03 . 03 – MISSED APPROACH

Apply normal missed approach procedure (3.05.02).

At acceleration altitude proceed as for a take off with engine flame out betweenV1 and V2 (5.03 p 1).

04

SYSTEMS


PAGE : 001

JUL 04DGACAPPROVED

–

AFM1

SEP 89

R

SEP 97

5 . 04 . 01 – FUEL

� FEED LO PRPUMP associated CONFIRM ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE associated Monitor for possible run down.. . . . . . . . . . . . . . . . . . . . �If engine runs down or if fuel quantity decreases significantly

CL FTR then FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUMP associated OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FIRE HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� LO LVLAVOID EXCESSIVE AIRCRAFT ATTITUDES

� FUEL LEAK

��

�� !"#$%�� &��'��%��

!"($%��& � �� )��)�� &��'�� ! ��)�� &� ��*� &��)$�� +�� &�� %�� %�� )�� &�� !�� &� �� $%��,��'�� *�!�� &� �$%��

�When a leak is confirmed

LAND ASAP

�Leak 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. . . . . . . . . . . . . . . .

�If excessive fuel flow was identified before engine shutdown,FUEL X FEED valve can be opened

�In all other cases,FUEL X FEED valve must remain closed

�Leak not locatedFUEL X FEED MAINTAIN CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE :FUEL X FEED valve must remain closed to prevent the leakaffecting both sides

BEFORE LANDING, NOTIFY ATC

04

SYSTEMS


PAGE : 001

SEP 97DGACAPPROVED

–

AFM2

R

SEP 89

APR 93

R

AUG 95

5 . 04 . 02 – ELECTRICAL SYSTEM

� DC GEN FAULTDC GEN affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Taxi on both engines

� If OAT exceeds ISA + 25 MAX FL FL 200. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� DC BUS 1 OFFDC GEN 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PF CM2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • At touch down

IDLE GATE LEVER PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� DC BUS 2 OFFDC 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 OFFLEAVE AND AVOID ICING CONDITIONSDESCENT TOWARD FL 100 / MEASTBY PITCH TRIM USED AS REQUIRED. . . . . . . . . . . . . . . . . . . . . . . . . . ADC SW Set to ADC 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If ice accretion builds up on airframeDE–ICING MODE SEL OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� In case of engine flame outOVRD RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PROPELLERS ANTI ICING FAULT PROC APPLY. . . . . . . . . . . . . . . . HORNS ANTI ICING FAULT PROC APPLY. . . . . . . . . . . . . . . . . . . . . .

• Before landingNOSE WHEEL STEERING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANTI–SKID OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANTI–SKID FAULT PROC APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• After landingDIFFERENTIAL BRAKING USE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM3

SEP 89

R

R

AUG 95

� CHG FAULTCHG OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� DUAL CHG LOSSMFC modules ONE AT A TIME OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . .

� If unsuccessfulLAND ASAPIf conditions permit, minimize use of VHF1.

� SVCE & UTLY BUS SHEDSVC & UTLY BUS AS REQUIRED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� AC BUS 2 OFFPF CM1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� ACW GEN FAULTACW GEN affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Taxi on both enginesLEAVE AND AVOID ICING CONDITIONS

� ACW BUS OFFACW GEN affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Associated AIRSPEED IND MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE AND AVOID ICING CONDITIONSTaxi on both engines

� ACW TOTAL LOSSACW GEN both OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HYD X FEED CHECK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE AND AVOID ICING CONDITIONSAffected 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 landingL/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BLUE PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAPS As required. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L/G GRAVITY EXTENSION PROCEDURE APPLY. . . . . . . . . . . . . .

Taxi on both engines

04

SYSTEMS


PAGE : 001

SEP 89

Eng : ALL

DGAC APPROVED

–


AFM4

5 . 04 . 03 – HYDRAULIC SYSTEM

� HYD TK COMPT LO LEVELPUMP (S) associated OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE : � 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.

� If green system is affected– normal braking– landing gear normal extension/retraction

are lost.

� HYD LO PR / HYD OVHTPUMP affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� BOTH MAIN HYD PUMPS LOSSMAIN PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE : Spoilers and landing gear extension and retraction are lost.

LGD DIST FLAPS 300 Multiply by 1.5. . . . . . . . . . . . . . . . . . . . . . . . . . . .

• Before landingL/G lever DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BLUE PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAPS 150 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LDG GEAR GRAVITY EXT PROC APPLY. . . . . . . . . . . . . . . . . . . . . . . . . FLAPS 300 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• After touch downFULL REVERSE IF NECESSARY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAXI ON BOTH ENGINES

04

SYSTEMS


PAGE : 001

Eng : PW124

EASAAPPROVED

–

AFM5

SEP 97

NOV 92

APR 93

R

JUL 05 SEP 03

5 . 04 . 04 – FLIGHT CONTROLS� REDUCED FLAPS LANDING

GPWS FLAP OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STEEP SLOPE APPROACH (≥4.5�) PROHIBITED. . . . . . . . . . . . . . . . . .

FLAPSLDG DISTFLAPS 30

MULTIPLY BYAPP SPD

015

1.91.8

1.23 VS1G (0) + 5 kt + wind effect1.23 VS1G (15) + wind effect

� FLAPS UNLOCKED� During TO

� Before V1TAKE OFF ABORT INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After V1VR, V2 INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� During approachGA 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If one elevator is stuck to full down position

MAX SPEED 154 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If left elevator is jammed :

MINIMUM MANEUVER OPERATING SPEED INC BY 10 KT. . . . . . . . � 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

� For approachEXTEND FLAPS AT VFE FOR EACH CONFIGURATIONLANDING 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. . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 001

EASAAPPROVED

–

AFM6

SEP 98

R

AUG 91FEB 94

JUL 05 SEP 03

� PITCH DISCONNECTAVOID ICING CONDITIONSCHECK BOTH CONTROL COLUMNS FREEMAX SPEED 180 kt . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX LOAD FACTOR : 2 gBANK ANGLE MUST BE RESTRICTED TO 30� until flaps extensionSTEEP SLOPE APPROACH (≥4.5�) PROHIBITED. . . . . . . . . . . . . . . . . . . . VAPP INC BY 10 kt. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING DISTANCE FLAPS 30 MULTIPLY BY 1.13. . . . . . . . . . . . . . . . . . . . LAND AT AIRPORT WITH MINIMUM CROSSWINDREDUCE SMOOTHLY TO FLARE

� TLU FAULT� If both ADC are lost

� IAS above 185 ktTLU HI SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� IAS below 185 ktTLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DISREGARD TLU FAULT ALERT� If at least one ADC operates

� IAS above 185 ktTLU HI SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If TLU FAULT alarm persists

MAX SPEED 180 kt. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� IAS below 185 ktMAX SPEED 180 kt. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � 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 highspeed position : 15 kt

� AILERON JAMMINGBANK ANGLE LIMIT 25�. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . BLUE HYD PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LAND AT AIRPORT WITH MINIMUM CROSSWINDSELECT BLUE HYD PUMP ON BEFORE FLAPS EXTENSION THENSELECT IT OFF AS WELL AS HYD AUX PUMPDO NOT EXTEND FLAPS IN TURN

• After touch downBLUE HYD PUMP and HYD AUX PUMP ON. . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 001

DGACAPPROVED

–

AFM7

SEP 98

MAY 92

R

R

� SPOILER JAMMINGBLUE HYD PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LAND AT AIRPORT WITH MINIMUM CROSSWINDSELECT BLUE HYD PUMP ON BEFORE FLAPS EXTENSION THENSELECT IT OFF AS WELL AS HYD AUX PUMP

• After touch downBLUE HYD PUMP and HYD AUX PUMP ON. . . . . . . . . . . . . . . . . . . . .

� RUDDER JAMMINGUse differential power to minimize side slip.Land at airport with minimum crosswind.

• At touch downNOSE DOWN BEFORE REDUCTION BELOW FI

� RUDDER RELEASABLE CENTERING UNIT FAILURE� If YD is available

YD ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If YD is not available

KEEP THE FEET ON THE PEDALS

� PITCH TRIM ASYMPITCH TRIM INOPERATIVE PROCEDURE APPLY. . . . . . . . . . . . . . . . . . .

NOTE : AP automatically disengages and cannot be reengaged.

04

SYSTEMS


PAGE : 001

Eng : ALL

DGACAPPROVED

–


AFM8

MAY 92

R

RR

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 EXTL/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER EXT HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� L/G RETRACTION IMPOSSIBLEL/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX SPEED 185 kt. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� ANTI SKID FAULTLANDING DISTANCE MULTIPLY BY 1.4. . . . . . . . . . . . . . . . . . . . . . . . . . .

• At touch downUSE 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 COOLINGEXCEPT IN CASE OF EMERGENCY

04

SYSTEMS


PAGE : 001

DGACAPPROVED

–

AFM9

SEP 00

AUG 91

R

SEP 98

5 . 04 . 06 – AIR

� BLEED VALVE FAULT / BLEED VALVE OVHTPACK 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. . . . . . . . . . . . . . . . . . . . . .

� EXCESS CAB ALT OXY MASKS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CREW COMMUNICATIONS ESTABLISH. . . . . . . . . . . . . . . . . . . . . . . . . . DESCENT AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If unsuccessful

DESCENT TO COMPATIBLE FL INITIATE. . . . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 130

DGACAPPROVED

–

AFM10

SEP 98

MAY 92APR 93

R

JAN 95

AUG 95OCT 96

R

R

R

R

Mod : 1368

5 . 04 . 07 – ICE AND RAIN PROTECTION

� PROP ANTI ICING FAULTPROP ANTI ICING affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE AND AVOID ICING CONDITIONS� If propeller unbalance due to ice becomes excessive

CL (both) MOVE TO MAX RPM for 5 mn. . . . . . . . . . . . . . . . . . . . . . . . .

� HORNS ANTI ICING FAULTLEAVE AND AVOID ICING CONDITIONS� If icing conditions, every 5 mn

FLIGHT CONTROLS associated CHECK FREEDOM OF MOVEMENT. . . . . . .

� ENG DE ICING FAULTLEAVE AND AVOID ICING CONDITIONSAssociated ENGINE PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . .

� AIRFRAME AIR BLEED FAULTLEAVE AND AVOID ICING CONDITIONSAIRFRAME AIR BLEED OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . � If ENG DE ICING FAULT illuminates after 10 s

ENG DE ICING (affected) OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME AIR BLEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME FAULT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .

� If ENG DE ICING FAULT does not illuminate after 10 sMINIMUM ICING SPEED INC BY 10 kt. . . . . . . . . . . . . . . . . . . . . . . . . . WHEN REACHING VAPPCL MAX RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING DISTANCE (icing conditions, flaps 30) Multiply by 1.13. . . . . . . . . . . .

� AIRFRAME DE ICING FAULTAIRFRAME DE ICING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE AND AVOID ICING CONDITIONSMINIMUM ICING SPEEDS INC BY 10 kt. . . . . . . . . . . . . . . . . . . . . . . . . . . LANDING DISTANCE (icing conditions, flaps 30) Multiply by 1.13. . . . . . . .

� DE ICING MODE SEL FAULTDE ICING MODE SEL OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

NOTE : monitor de–icing :� In case of engine flame out

OVRD RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 001

SEP 98DGACAPPROVED

–

AFM11

DEC 89

R

FEB 94

5 . 04 . 08 – MFC

� MFC 1A FAULTAFFECTED MODULE OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� MFC 1B FAULTAFFECTED MODULE OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . �If failure during taxi out

PACK 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• Prior take offPACK 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• After take offPACKS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE FULL CLOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LEAVE L/G DOWN FOR COOLING FOR 1 mn AFTERTAKE OFF EXCEPT IN CASE OF EMERGENCY

• After landingPACK 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

�If failure in flight or after landing


CAUTION : Before opening any door, Packs 1 and 2 must be selected OFFand cockpit communication hatch must be opened.

04

SYSTEMS


PAGE : 001

SEP 98DGACAPPROVED

–

AFM12

DEC 89

R

� MFC 2A FAULTAFFECTED MODULE OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . �If failure during taxi out

OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • After take off

IDLE GATE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• At touchdownIDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• After landingOVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

�If failure in flight or after landing• At touchdown

IDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • After landing

OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� MFC 2B FAULTAFFECTED MODULE OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . �If 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 OFFEXCEPT IN CASE OF EMERGENCY


�If failure in flight or after landing• After landing

PACK 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


04

SYSTEMS


PAGE : 001

APR 93

Eng : ALL

DGACAPPROVED

–


AFM13

R

AUG 91

� MFC 1A + 1B FAULTAFFECTED 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 landingATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CL BOTH MAX RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



� MFC 1A + 2A FAULTAFFECTED MODULES OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . TLU MAN MODE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RADAR OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME FAULT AMBER ALERT IS LOSTWHEN AIRFRAME DE-ICING IS USED, MONITOR BOOTS INFLATIONAS AP OFF ALERT IS LOST, USE OF AP BELOW 1000 ft AGL ISPROHIBITED

• Before landingL/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . .

• At touch downIDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


04

SYSTEMS


PAGE : 001

APR 93

Eng : ALL

DGAC APPROVED

–


AFM14

R

R

AUG 91

� MFC 1A + 2B FAULTAFFECTED MODULES OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . DE-ICING MODE SEL OVRD (AS RQD). . . . . . . . . . . . . . . . . . . . . . . . . . .

• Before landingFLAPS CONTROL IS LOSTREDUCED FLAP LDG PROC APPLY. . . . . . . . . . . . . . . . . . . . . . . . . L/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . .



� MFC 1B + 2A FAULTAFFECTED MODULES OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . DE-ICING MODE SEL OVRD (AS RQD). . . . . . . . . . . . . . . . . . . . . . . . . . . AVIONIC VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . .

• Before landingFLAPS CONTROL IS LOSTREDUCE FLAP LDG PROC APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . L/G LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : GEAR CANNOT BE RETRACTED

• At touch downIDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



04

SYSTEMS


PAGE : 001

APR 93

Eng : ALL

DGAC APPROVED

–


AFM15

R

AUG 91

� MFC 2A + 2B FAULTAFFECTED 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 landingATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CL BOTH MAX RPM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• At touch-downIDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



� MFC 1B + 2B FAULTAFFECTED MODULES OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVERHEAD PANEL MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

• Before landingNOSE 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 landingPACK 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PACK 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HORNS ANTI-ICING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PROBES HEATING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


04

SYSTEMS


PAGE : 090

AUG 95

Eng : ALL

DGACAPPROVED

–

Model : ALLMod : 3168

AFM16

R

JAN 95

5 . 04 . 09 – AUTOPILOT

� PITCH MISTRIMAP DISCONNECT HOLDING FIRMLY THE CONTROLS. . . . . . . . . . . . . FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS.

� PITCH TRIM FAILAP 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.

04

SYSTEMS


PAGE : 001

SEP 98DGACAPPROVED

–

AFM17

MAY 90

R

JAN 95

AUG 95

OCT 96

R

5 . 04 . 10 – MISCELLANEOUS

� ADC FAULTADC SW non affected side. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PF non affected side. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If both ADC’s are lostTLU MAN MODE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY INST USE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENG PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� ADC DISAGREEMENTINSTRUMENTS CROSS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VALID ADC SELECTED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FAULTY ADC OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� ADC SW FAULTADC sw Set to opposite ADC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� AHRS FAULTATT / HDG SWITCHING affected side ON. . . . . . . . . . . . . . . . . . . . . . . . . . Compare periodically remaining AHRS outputs to STBY INST.

� FIRE LOOP FAULTLOOP affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� OXYGEN LO PRMAIN SUPPLY OFF then ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If oxygen LO PR light remains litMAIN SUPPLY OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oxygen portable unit Use if required. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� ADU FAULTAP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

04

SYSTEMS


PAGE : 001

SEP 99DGACAPPROVED

–

AFM18

R

DEC 89FEB 94

R

JAN 95

AUG 95

� EFIS COMPARISONBOTH EADI, STBY HORIZON CROSS CHECK. . . . . . . . . . . . . . . . . . . . . WRONG IDENTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AHRS non affected SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . WRONG AHRS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If AHRS 1 is WRONG, pull C/B ATT/HDG AHRS 1 “NORM SPLY” and“AUX SPLY”

� If AHRS 2 is WRONG, pull C/B ATT/HDG AHRS 2 “NORM SPLY” and“AUX SPLY FLT”

00

CONTENTS

6PERFORMANCE

PAGE : 001

SEP 97DGACAPPROVED

–

AFM1

R

MAY 92

FEB 94

6 . 00 – CONTENTS

6 . 01 – GENERAL

INTRODUCTIONSTALL SPEEDS – VS1GAIRPLANE CONFIGURATIONCROSS WINDDETERMINATION OF WIND COMPONENTSCALIBRATION SPEED AND ALTITUDE

6 . 02 – ENGINE MANAGEMENT

6 . 03 – TAKE OFF

DEFINITIONPERFORMANCE DETERMINATIONDETERMINATION OF MAXIMUM TAKE OFF WEIGHT FOR AGIVEN RUNWAYALTITUDE – SPEED – BANK ANGLETURN RADIUS : RELATIONSHIPS

6 . 04 – SINGLE ENGINE CRUISE

DEFINITIONEN ROUTE NET GRADIENT

6 . 05 – LANDING

DEFINITIONPERFORMANCE DETERMINATION

6 . 06 – ATMOSPHERIC ICING CONDITIONS

INTRODUCTIONFLIGHT IN ATMOSPHERIC ICING CONDITIONS

01

GENERAL

6PERFORMANCE

PAGE : 001

FEB 94

Eng : ALL

DGAC APPROVED

–


AFM1

SEP 89

R

6 . 01 . 01 – INTRODUCTION

In compliance with Airworthiness regulations, an aircraft is cleared to take offfrom any airport if the weight allows it to achieve the take off, “en route” andlanding performance included in this chapter.

The curves or tables approved by Airworthiness Authority must not beextrapolated.

Performance is related to VS1G (see page 2)

Wind speed is measured at the height of 10 meters.

All weight, altitude, temperature and speed limits presented on section 2 – LIMITATIONS – must be observed for the utilization of the performancecharts.

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 97

Eng : PW124

DGACAPPROVED

–

AFM2

NOV 92

APR 93

R

OCT 96

6 . 01 . 02 – STALL SPEEDS – VS1G

01

GENERAL

6PERFORMANCE

PAGE : 001

FEB 94

Eng : ALL

DGAC APPROVED

–


AFM3

APR 93

R

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 AIRCOND

ENG POWER

REMARKS

TAKE OFF 150 ON / OFF TO / RTO

ATPCS ONAccelerate stop distanceestablished using only

wheel normal braking sys-tem, antiskid ON, PL at GI.

FINAL TAKE OFF 00 OFF MCT

EN ROUTE 00 OFF / ON MCT

APPROACH 150 OFF For go aroundRTO

LANDING 300 OFFLanding distances

established with antiskidON, PL at GI

6 . 01 . 04 – CROSS WIND

The maximum demonstrated cross wind is 35 kt.

01

GENERAL

6PERFORMANCE

PAGE : 001

MAY 92DGACAPPROVED

–

AFM4

6 . 01 . 05 – DETERMINATION OF WIND COMPONENTS

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 89

Eng : ALL

DGACAPPROVED

–


AFM5

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.

01

GENERAL

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM6

SEP 89

R

R

SPEED CORRECTION (FLAPS 15)PILOT & COPILOT ADC OUTPUT

ERROR IN GROUND EFFECTΔ V = IAS – CAS

SPEED CORRECTION (FLAPS 15)STAND BY STATIC SOURCEERROR IN GROUND EFFECT

Δ V = IAS – CAS

01

GENERAL

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM7

SEP 89

R

R

TAKE-OFF – GO AROUND (FLAPS 15)SPEED CORRECTION

PILOT & COPILOT ADCOUTPUT ERRORΔ V = IAS – CAS

TAKE-OFF – GO AROUND (FLAPS 15)SPEED CORRECTION

STAND BY SOURCE ERRORΔ V = IAS – CAS

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 97DGACAPPROVED

–

AFM8

R

OCT 96

FINAL APPROACH – LANDING (FLAPS 30)SPEED CORRECTION

PILOT & COPILOT ADC OUTPUT ERRORΔ V = IAS – CAS

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 97DGACAPPROVED

–

AFM9

SEP 89

R

OCT 96

FINAL APPROACH – LANDING (FLAPS 30)SPEED CORRECTION

STAND BY STATIC SOURCE ERRORΔ V = IAS – CAS

01

GENERAL

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM10

SEP 89

R

R

TAKE-OFF – GO AROUND (FLAPS 15)ALTITUDE CORRECTION

PILOT & COPILOT OUTPUT ERRORΔ Zp = Zpi – Zp

01

GENERAL

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM11

R

SEP 89

R

TAKE-OFF – GO AROUND (FLAPS 15)ALTITUDE CORRECTION

STAND BY STATIC SOURCE ERRORΔ Zp = Zpi – Zp

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 97DGAC

APPROVED

–

AFM12

SEP 89

R

OCT 96

FINAL APPROACH – LANDING (FLAPS 30)ALTITUDE CORRECTION

PILOT & COPILOT OUTPUT ERRORΔ Zp = Zpi – Zp

01

GENERAL

6PERFORMANCE

PAGE : 001

SEP 97DGACAPPROVED

–

AFM13

SEP 89

R

OCT 96

FINAL APPROACH – LANDING (FLAPS 30)ALTITUDE CORRECTION

STAND BY SOURCE ERRORΔ Zp = Zpi – Zp

02

ENGINE MANAGEMENT

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW 124

DGACAPPROVED

–


AFM1 DATE

REVISIONANTERIEURE

R

R

R

MAY 92

TAKE OFF TORQUE COMPUTED FOR VC = 50. KT

SAT (oC) PROPELLER SPEED 100 %

AIRCOND

NORMALAIR

HIGHAIR

PRESSURE ALTITUDE (FT)AIRCONDOFF

AIRCOND

ON

AIRCOND

ON –1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

– 40.– 10.– 8.– 6.– 4.

– 63.– 27.– 24.– 22.– 19.

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.089.0

90.090.089.288.287.2

– 2. 0. 2. 4. 6.

– 17.– 14.– 12.– 10.– 7.

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.089.688.587.4

88.087.085.984.983.8

86.285.184.183.182.1

8. 10. 12. 14. 16.

– 5.– 2. 0. 3. 5.

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.088.9

90.088.987.886.585.2

86.385.384.283.081.7

82.881.780.779.578.4

81.180.079.077.976.7

18. 20. 22. 24. 26.

8. 10. 13. 15.

18.

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.089.888.0

90.089.587.886.184.5

87.485.884.282.681.0

83.982.380.879.377.7

80.478.977.576.074.5

77.175.774.372.971.4

75.574.172.771.369.9

28.30.32.34.36.

20. 23. 25. 28. 30.

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.088.386.6

89.988.286.584.883.1

86.384.783.081.479.8

82.881.279.778.176.5

79.577.976.474.973.4

76.274.873.371.970.4

73.171.770.368.967.5

70.168.767.466.164.7

68.667.366.064.763.4

38.40. 42. 44. 46.

33. 36.38

41. 43.

90.090.088.286.384.4

88.386.584.782.981.1

84.883.181.379.677.9

81.479.778.176.474.7

78.176.574.973.371.7

75.073.471.970.468.8

71.970.469.067.5

69.067.666.2

66.164.8

63.4 62.1

48.50. 52. 54. 55.

46. 48. 51. 53. 54.

82.680.778.876.976.0

79.377.575.773.973.0

76.174.472.7

73.171.4

70.1

Note : Applicable for 0 � Vc � 60 kt

02

ENGINE MANAGEMENT

6PERFORMANCE

PAGE : 050

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM2 DATE

REVISIONANTERIEURE

R

R

R

APR 93

AUG 95MAXIMUM CONTINUOUS TORQUE COMPUTED FOR VC = 120. KT

TAT (oC) PROPELLER SPEED 100 %

AIRCOND

NORMALAIR

COND

HIGHAIR

COND

PRESSURE ALTITUDE (FT)CONDOFF

AIRCOND

ON

AIRCOND

ON 0. 2000. 4000. 6000. 8000. 10000. 12000. 14000. 16000. 18000. 20000. 22000. 24000. 25000.

– 43.– 40.– 37.– 33.– 29.

– 56.– 52.– 48.– 44.– 40.

– 67.– 63.– 59.– 55.– 50.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.099.697.996.0

94.993.391.890.288.5

87.385.984.483.081.4

80.479.077.776.474.9

74.273.071.770.569.2

68.267.166.064.963.6

62.661.660.659.558.4

60.059.058.057.055.9

– 25.– 21.– 17.– 13.– 10.

– 36.– 32.– 28.– 24.– 20.

– 46.– 42.– 38.– 33.– 29.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.099.797.996.194.3

94.091.990.288.686.9

86.684.783.181.680.1

79.777.976.575.173.7

73.371.770.469.167.8

67.766.265.063.862.6

62.360.959.858.757.6

57.155.954.953.952.9

54.753.552.651.650.6

– 5.– 2. 1. 4. 8.

– 16.– 12.– 8.– 4. 0.

– 24.– 20.– 16.– 11.– 7.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.099.2

100.098.296.494.491.8

92.590.789.087.184.7

85.383.682.180.378.1

78.677.075.674.072.0

72.370.969.668.166.2

66.565.264.062.761.0

61.460.259.157.956.3

56.555.454.453.251.8

51.850.849.948.947.5

49.748.747.846.845.5

11. 15. 18. 22. 25.

4. 8. 12. 16.

20.

– 2. 2. 7. 12. 16.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.098.094.7

97.095.092.990.987.8

89.787.886.084.181.2

82.981.179.477.675.0

76.474.873.271.669.1

70.468.967.466.063.7

64.863.462.060.758.6

59.658.457.155.953.9

55.053.952.751.6

50.649.648.5

46.545.544.5

44.543.6

29.33.37.41.44.

24. 28. 32. 36. 40.

21. 25. 29. 33. 38.

100.0100.097.494.691.7

98.094.190.687.985.3

91.087.584.281.779.2

84.481.178.075.873.5

78.175.072.270.168.0

72.169.366.664.7

66.563.961.5

61.358.8

56.4

48. 52. 56. 60. 64.

44. 48. 52. 56. 60.

42. 46. 50. 54. 58.

88.986.083.281.6

82.680.077.3

76.874.3

71.2

Note : Applicable for Vc � 125 kt. Add 0.8 % for each 10 kt above 125 kt without exceeding 100.0 % torque.

02

ENGINE MANAGEMENT

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW 124

DGACAPPROVED

–


AFM3 DATE

REVISIONANTERIEURE

R

R

R

MAY 92

GO AROUND TORQUE COMPUTED FOR VC = 100. KT

TAT (oC) PROPELLER SPEED 100 %

AIRCOND

NORMALAIR

HIGHAIR

PRESSURE ALTITUDE (FT)AIRCONDOFF

AIRCOND

ON

AIRCOND

ON –1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

– 40.– 10.– 8.– 6.– 4.

– 63.– 27.– 24.– 22.– 19.

– 71.– 35.– 32.– 30.– 27.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.099.2

100.0100.099.398.297.1

– 2. 0. 2. 4. 6.

– 17.– 14.– 12.– 10.– 7.

– 25.– 22.– 19.– 17.– 14.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.099.898.697.4

98.096.995.794.693.4

96.094.893.792.691.4

8. 10. 12. 14. 16.

– 5.– 2. 0. 3. 5.

– 12.– 9.– 7.– 4.– 1.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.099.0

100.099.097.896.495.0

96.295.093.892.591.1

92.291.189.988.787.4

90.389.288.086.885.5

18. 20. 22. 24. 26.

8. 10. 13. 15.

18.

2. 4. 7. 10. 13.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.0100.098.2

100.099.897.996.194.2

97.595.794.092.290.4

93.591.890.188.486.7

89.788.186.484.883.2

86.084.582.981.379.7

84.282.781.279.678.1

28.30.32.34.36.

20. 23. 25. 28. 30.

16. 18. 21. 24. 27.

100.0100.0100.0100.0100.0

100.0100.0100.0100.0100.0

100.0100.0100.098.596.5

100.098.496.594.692.7

96.394.492.690.889.0

92.490.688.987.185.4

88.687.085.383.681.9

85.083.481.880.278.6

81.580.078.576.975.4

78.276.775.273.872.3

76.675.173.772.270.8

38.40. 42. 44. 46.

33. 36.38

41. 43.

30. 32. 35. 38. 41.

100.0100.098.396.394.2

98.596.594.592.590.5

94.692.690.788.886.9

90.889.087.185.383.4

87.285.483.681.880.1

83.781.980.278.576.8

80.378.677.075.473.7

77.075.473.972.3

73.872.370.8

70.869.4

69.367.9

48.50. 52. 54. 56.

46. 48. 51. 53. 54.

43. 46. 49. 52. 54.

92.190.087.985.983.8

88.586.584.582.580.5

84.983.081.179.2

81.679.777.9

78.376.5

75.1

Note : Applicable for Vc � 125 ktAdd 0.8 % for each 10 kt above 125 kt without exceeding 100 % torque.

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

SEP 97DGACAPPROVED

–

AFM1

R

NOV 92APR 93

FEB 94

OCT 96

6 . 03 . 01 – DEFINITION

SPEEDS– VMCG : Minimum control speed on ground from which a sudden

failure of the critical engine can be controlled by use ofprimary flight controls only. The other engine being set atRTO power.

– V1 : Speed at which the pilot must make the decision followingfailure 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 ftheight.

– V2 : Take off safety speed reached before 35 ft height with oneengine 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 criticalengine the other being set at RTO power (take off flapssetting 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.

DISTANCESAVAILABLE RUNWAY LENGTH

Length of the paved runway surface, able to accept aircraft weight in allnormal operating conditions.

STOPWAYExtension of runway, occasionally used for taxiing but adequate fordeceleration of the aircraft in case of aborted take–off.

CLEARWAYClear area at the end of the runway which can be taken into account fortake–off distance calculation.

AVAILABLE ACCELERATION STOP LENGTHSum 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 orless than the sum of available runway length and allowable clearway (ifany).

TAKE OFF RUN (TOR)Distance between brakes release point and half of the segmentbetween VLOF and 35 ft height.It has to be equal to or less than the available runway length.

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM2

MAY 92

APR 93

R

R

V1 LIMITED BY VMCG (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM3

MAY 92

APR 93

R

FEB 94

MINIMUM CONTROL SPEED IN FLIGHT – VMCA (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

MAY 92

Eng : ALL

DGACAPPROVED

–


AFM4

TAKE OFF FLIGHT PATH IN CASE OF ENGINE FAILURE

Note : Point zero indicates the 35 ft height point on the flight path.

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

SEP 98DGACAPPROVED

–

AFM5

NOV 92

APR 93

R

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

The following table defines the meaning of the distances and length taken intoaccount for take off.Performance is related to T� ISA – 300CIf T < ISA – 300C, calculate as follows : T = ISA – 300C .

RUNWAY WITH THE FOLLOWING CHARACTERISTICS

without clearwaywithout stopway

without clearwaywith stopway

with clearwaywithout stopway

with clearwaywith stopway

length TOR runway length runway length

to beused

TOD runway length runway length runway length+ clearway

runway length+ clearway

to enterthe manual

ASD runway length runway length+ stopway

runway length runway length+ stopway

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

APR 93

Eng : PW124

DGACAPPROVED

–


AFM5A

NOV 92

TAKE OFF WITH AIR CONDITIONING

Take-off performances are determined with AIR CONDITIONING OFF. For take-offcomputations with AIR CONDITIONING ON (normal flow), the following graph must beused to calculate a fictitious OAT. This fictitious OAT has to be entered in the followingpages to take into account the performance decrement. (Fictitious OAT = actual OAT + Δ T)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

APR 93DGACAPPROVED

–

AFM6

NOV 92

6 . 03 . 03 – DETERMINATION OF MAXIMUM TAKE OFF WEIGHT FOR AGIVEN RUNWAY

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM7

MAY 92

R

R

SECOND SEGMENTMAXIMUM WEIGHT AT BRAKES RELEASE

TAKE OFF GRADIENT (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWERAIR CONDITIONING OFF – ANTI/DE ICING OFF– GEAR UP

03

TAKE–OFF

6PERFORMANCE

PAGE : 120

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM8

NOV 92

APR 93

R

R

R

FINAL TAKE OFF (FLAPS 0)EQUIVALENT WEIGHT AT BRAKES RELEASE

ONE ENGINE MAX. CONTINUOUS POWER – ONE PROPELLER FEATHEREDAIR CONDITIONING OFF – ANTI/DE ICING OFF – GEAR UP

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW 124

DGACAPPROVED

–


AFM9

MAY 92

R

R

R

TAKE OFF RUN (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R. T. O. POWER AFTER CRITICALENGINE FAILURE – AIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAYSLOPE – NO WIND

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM10

MAY 92

R

R

R

REQUIRED TAKE OFF RUN (FLAPS 15)ALL ENGINES OPERATING

TWO ENGINES AT T/O POWERAIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

TAKE–OFF

6PERFORMANCE

PAGE : 080

OCT 96

Eng : ALL

DGACAPPROVED

–

Model : ALLMod : 8044 or 3522

AFM11

NOV 92

APR 93

R

R

TAKE OFF RUN CORRECTIONS (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

Eng : PW 124

DGACAPPROVED

–


AFM12

OCT 96

MAY 92

R

R

R

TAKE OFF DISTANCE (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER AFTER CRITICALENGINE FAILURE – AIR CONDITIONING OFF – ANTI/DE ICING OFFNO RUNWAY SLOPE – NO WIND

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

Eng : PW124

DGACAPPROVED

–


AFM13

MAY 92

OCT 96

R

R

R

REQUIRED TAKE OFF DISTANCE (FLAPS 15)ALL ENGINES OPERATING

TWO ENGINES AT T/O POWERAIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

TAKE–OFF

6PERFORMANCE

PAGE : 080

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM14

NOV 92

APR 93

R

R

TAKE – OFF DISTANCE CORRECTIONS (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

SEP 99

Eng : PW 124

DGACAPPROVED

–

AFM15

MAY 92

R

OCT 96

ACCELERATE STOP DISTANCE (FLAPS 15)

TWO ENGINES OPERATING OR ONE ENGINE FAILEDAIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

TAKE–OFF

6PERFORMANCE

PAGE : 080

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM16

NOV 92

APR 93

R

R

ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW 124

DGACAPPROVED

–


AFM17

MAY 92

R

R

PERFORMANCE – TAKE OFF – DECISION SPEEDLIMITED BY MAXIMUM BRAKE ENERGY (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

Eng : PW 124

DGACAPPROVED

–


AFM18

OCT 96

AUG 91

R

R

ROTATION SPEED – VR (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWEREFFECT OF AIR BLEED ON VR IS NEGLIGIBLE

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM19

MAY 92

R

R

TAKE OFF SPEED – V2 (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O. POWER

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM20

R

MAY 92

FEB 94

AUG 95

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 mustbe determined. In the flight manual charts reference zero is thepoint 35 ft below the end of the TOD and the flight paths showninclude the 35 ft operational clearance. Where the TOD is greater(less) than the runway length the obstacle distance from end of therunway must be decreased (increased) by the difference betweenTOD and runway length.

1. Place the obstacle (point A). In this example the TOD is initially assumedequal to runway length.

2. Replace the obstacle according to the wind (point C) drawing a parallel tothe gross height lines.

3. The path intersects the obstacle in B.

4. Determine the gradient allowing the clearance taking into account thedecrease 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 determinesmaximum weight allowing clearance of the obstacle.

7. To be precise, the take–off distance corresponding to this new maximumweight must be calculated.

8. Using this distance, replace the obstacle and check that it will be cleared, ifnot restart the calculation.

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM21

AUG 91

R OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES)V2 / VS1G = 1.13 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM22

MAY 92

R OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES)V2 / VS1G = 1.13 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

Eng : PW124

DGACAPPROVED

–


AFM23

R

OCT 96

MAY 92

OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES)V2 / VS1G = 1.20 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM24

MAY 92

R OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES)V2 / VS1G = 1.20 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM25

MAY 92

ROBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES)

V2 / VS1G = 1.25 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM26

MAY 92

ROBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES)

V2 / VS1G = 1.25 (FLAPS 15)

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM27

R

MAY 92APR 93

R

R

NOT APPLICABLE

Consequently pages from 28 to 30 –001 are intentionaly missing in thismanual.

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM31

6 . 03 . 04 – ALTITUDE – SPEED – BANK ANGLE – TURN RADIUS :

RELATIONSHIPS

03

TAKE–OFF

6PERFORMANCE

PAGE : 001

OCT 96

Eng : ALL

DGACAPPROVED

–


AFM32

MAY 92

APR 93

BANK ANGLE EFFECT ON SINGLE ENGINE CLIMB GRADIENT (FLAPS 15)

04

SINGLE ENGINE CRUISE

6PERFORMANCE

PAGE : 001

APR 93

Eng : ALL

DGAC APPROVED

–


AFM1

NOV 92

6 . 04 . 01 – DEFINITIONS

The “En route” gradient given in this chapter are established by decreasing theavailable 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.

04

SINGLE ENGINE CRUISE

6PERFORMANCE

PAGE : 120

OCT 96

Eng : PW 124

DGACAPPROVED

–


AFM2 DATE

REVISIONANTERIEURE

APR 93

NOV 92

R

FEB 94

R

6 . 04 . 02 – EN ROUTE NET GRADIENT

V / VS1G = 1.18 (FLAPS 0)

ONE PROPELLER FEATHERED – ONE ENGINE : MCT POWERAIR CONDITIONING OFF BELOW 10000 ft – ANTI/DE ICING OFF

05

LANDING

6PERFORMANCE

PAGE : 001

FEB 94

Eng : PW124

DGAC APPROVED

–


AFM1

R

NOV 92APR 93

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 atGA power (landing flaps setting, gear extended)and whichprovides rolling capability specified by regulations.

FLAPS VMCL (CAS)

300

15090 kt94 kt

6 . 05 . 02 – PERFORMANCE DETERMINATION

– Landing climb performance (two engines at GA power, landing flaps setting) isnever limiting.

– The landing distance represents the distance from the 50 ft to complete stopon a level, smooth, dry, hard surfaced runway.Antiskid is operative.Engines are at GI.

– To determine the required runway length for landing, apply national operational regulations.

05

LANDING

6PERFORMANCE

PAGE : 001

Eng : PW124

DGACAPPROVED

–


AFM2

OCT 96

R

NOV 92APR 93

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 intoaccount for landing distance computation.It is equal to 1.23 VS1G in the landing configuration or VMCL, whichever ishigher.

05

LANDING

6PERFORMANCE

PAGE : 001

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM3 MAY 92

R

R

APPROACH CLIMB GRADIENTAPPROACH CLIMB LIMITING WEIGHT (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE : GO AROUND POWERAIR CONDITIONING OFF – ANTI/DE ICING OFF – GEAR UP

05

LANDING

6PERFORMANCE

PAGE : 001

SEP 97

Eng : PW124

DGACAPPROVED

–

AFM4

MAY 92

R

FEB 94

LANDING DISTANCE (FLAPS 30)

INCREASE BY 15% ON FORESEEN WET RUNWAY

06

ATMOSPHERIC ICING CONDITIONS

6PERFORMANCE

PAGE : 001

JUL 04DGACAPPROVED

–

AFM1

SEP 89

6 . 06 . 01 – INTRODUCTION

The following sub sections provide data for flight in atmospheric icingconditions.

Refer to chapter 3 . 04 for definition of the minimum maneuver/operating icingspeeds.

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 (closeobstacles).

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.

06


6PERFORMANCE

PAGE : 130

OCT 96

Eng : PW124

DGACAPPROVED

–


AFM2

NOV 92

APR 93

FEB 94

R

6 . 06 . 02 – FLIGHT IN ATMOSPHERIC ICING CONDITIONS

MINIMUM MANEUVER / OPERATING SPEED

06


6PERFORMANCE

PAGE : 001

APR 93

Eng : PW124

DGACAPPROVED

–

AFM3

NOV 92

TAKE OFF FLIGHT PATH IN CASE OF ENGINE FAILURE

Note : Point zero indicates the 35 ft height point on the flight path.

06


6PERFORMANCE

PAGE : 001

SEP 99

Eng : PW124

DGACAPPROVED

–

AFM4

NOV 92

APR 93

R

OCT 96

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S

TAKE OFFEFFECT ON SECOND SEGMENT WEIGHT

V2 / VS1G = 1.21 (FLAPS 15)

Note : Performance decrement applies to the maximum second segmentweight computed in normal conditions with V2 = 1.21 VS1G (flaps 15)

06


6PERFORMANCE

PAGE : 220

OCT 96

Eng : PW124

DGACAPPROVED

–

Model : ALLMod : 1368 + 2735

AFM5

NOV 92

APR 93

R

R

FINAL TAKE-OFFEQUIVALENT WEIGHT AT BRAKES RELEASE

V / VS1G = 1.38 (FLAPS 15)

ONE ENGINE MAX. CONTINUOUS POWER – ONE PROPELLER FEATHEREDAIR CONDITIONING OFF – DE ICING ON – GEAR UP

06


6PERFORMANCE

PAGE : 001

Eng : PW124

DGACAPPROVED

–

AFM6

NOV 92

APR 93

SEP 99

R

OCT 96

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S

TAKE OFFEFFECT ON TAKE OFF RUNV2 / VS1G = 1.21 (FLAPS 15)

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.

06


6PERFORMANCE

PAGE : 001

SEP 99

Eng : PW124

DGACAPPROVED

–

AFM7

NOV 92

APR 93

R

OCT 96

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S

TAKE OFFEFFECT ON TAKE OFF DISTANCE

V2 / VS1G = 1.21 (FLAPS 15)

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.

06


6PERFORMANCE

PAGE : 001

SEP 99

Eng : PW124

DGACAPPROVED

–

AFM8

NOV 92

APR 93

R

OCT 96

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S

TAKE OFFEFFECT ON ACCELERATE STOP DISTANCE

V2 / VS1G = 1.21 (FLAPS 15)

NOTE : Performance decrement applies to the acceleration stop distance lengthcomputed in normal conditions withV2 = 1.21 VS1G (flaps 15).

06


6PERFORMANCE

PAGE : 001

JUL 04DGAC APPROVED

–

AFM8A

RESEARCH OF WEIGHT LIMITED BYOBSTACLE 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 bedetermined. In the flight manual charts reference zero is the point 35 ft belowthe end of the TOD and the flight paths shown include the 35 ft operationalclearance. Where the TOD is greater (less) than the runway length the obstacledistance from end of the runway must be decreased (increased) by thedifference between TOD and runway length.


2. Replace the obstacle according to the wind (point C) drawing a parallel tothe gross height lines.





7. To be precise, the take–off distance corresponding to this new maximumweight must be calculated.

8. Using this distance, replace the obstacle and check that it will be cleared.If not, restart the calculation.

06


6PERFORMANCE

PAGE : 001

JUL 04

Eng : PW124

DGAC APPROVED

–

AFM9

OBSTACLE CLEARANCE T.O. FLIGHT PATH (CLOSE OBSTACLES)V2 / VS1G = 1.21 (FLAPS 15)

06


6PERFORMANCE

PAGE : 001

JUL 04DGAC APPROVED

–

AFM9A

RESEARCH OF WEIGHT LIMITED BYOBSTACLE 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 bedetermined. In the flight manual charts reference zero is the point 35 ft belowthe end of the TOD and the flight paths shown include the 35 ft operationalclearance. Where the TOD is greater (less) than the runway length the obstacledistance from end of the runway must be decreased (increased) by thedifference between TOD and runway length.


2. Replace the obstacle according to the wind (point C) drawing a parallelto the gross height lines.





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 becleared. If not, restart the calculation.

06


6PERFORMANCE

PAGE : 001

JUL 04

Eng : PW124

DGAC APPROVED

–

AFM10

OBSTACLE CLEARANCE T.O. FLIGHT PATH (REMOTE OBSTACLES)V2 / VS1G = 1.21 (FLAPS 15)

06


6PERFORMANCE

PAGE : 220

OCT 96

Eng : PW124

DGACAPPROVED

–

Model : ALLMod : 1368 + 2735

AFM11

FEB 91

APR 93

R

R

EN ROUTE NET GRADIENTV/VS1G = 1.38 (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE : MAX CONTINUOUS POWERAIR CONDITIONING : OFF BELOW 10 000 ft – DE ICING ON.

06


6PERFORMANCE

PAGE : 130

SEP 98

Eng : PW124

DGACAPPROVED

–

Mod : 1368

AFM12

NOV 92

APR 93

R

OCT 96

NO

RM

AL

CO

ND

ITIO

NS

AN

D A

IRC

RA

FT

FR

EE

OF

ICE

(IC

ING

AO

A O

FF

)

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S O

R R

ES

IDU

AL

ICE

ON

TH

E A

IRC

RA

FT

(IC

ING

AO

A L

IT)

EFFECT ON APPROACHCLIMB GRADIENT WEIGHTV / VS1G = 1.23 (FLAPS 15)

NOTE : Performance decrement applies to the maximum approach climb gradientlimiting weight computed in normal conditions withV = 1.23 VS1G (flaps 15).

06


6PERFORMANCE

PAGE : 130

SEP 98

Eng : PW124

DGACAPPROVED

–

Mod : 1368

AFM13

NOV 92

APR 93

R

OCT 96

NO

RM

AL

CO

ND

ITIO

NS

AN

D A

IRC

RA

FT

FR

EE

OF

ICE

(IC

ING

AO

A O

FF

)

AT

MO

SP

HE

RIC

ICIN

G C

ON

DIT

ION

S O

R R

ES

IDU

AL

ICE

ON

TH

E A

IRC

RA

FT

(IC

ING

AO

A L

IT)

EFFECT ON LANDING DISTANCEV / VS1G = 1.30 (FLAPS 30)

NOTE : Performance decrement applies to the landing distance computed innormal conditions.

00

CONTENTS

7APPENDICES & SUPPLEMENTS

PAGE : 001EASA

APPROVED

--

AFM1

R

AUG 07

01 APPENDICES

01 EXTERNAL NOISE. .02 CONFIGURATION DEVIATION LIST. .03 CAT II OPERATION. .04 TCAS. .05 STEEP SLOPE MANUAL APPROACH. .06 CONTAINER TRANSPORT. .07 Reserved. .08 ETOPS. .09 OPERATIONS ON NARROW RUNWAYS. .10 RUNWAYS SLOPE BEYOND 2 %. .11 POWER PLANT. . .12 TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV. .13 COCKPIT DOOR SECURITY SYTEM (if installed). .14 Reserved. .15 Aircraft Performance Monitoring APM16 SSR Mode S Enhanced Surveillance17 ACARS18 HIGH LATITUDES OPERATIONS. .19 DRY UNPAVED RUNWAYS. .

.../...

00

CONTENTS


PAGE : 001EASA

APPROVED

--

AFM2

AUG 07

02 -- SUPPLEMENTS

00 INTRODUCTION. . .

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 EEC OFF. . .08 DISPATCH WITH ONE AFU INOPERATIVE. . .09 DISPATCH WITH ONE TQ INDICATOR INOPERATIVE. . .10 DISPATCH WITH ATPCS OFF. . .11 FLIGHT WITH LANDING GEAR DOWN. . .12 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

01.01

APPENDIX No 01

7APPENDICES

PAGE : 002

AUG 07EASAAPPROVED

--

AFM1

Eng : PW124 Model : 201 -- 202

EXTERNAL NOISE

NOISE CHARACTERISTICS

No determination has been made by the DGAC that the noise procedures andlevels in this manual are, or should be, acceptable or unacceptable foroperation at, into, or out of any airport.

NOISE LEVELS

Noise levels shown here after comply with ICAO annex 16 Chapter 3 noiserequirements and were obtained by analysis of approved data from approvednoise tests.See section 2.02.01 for identification of the maximum take off and landingweights 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 constantclimb speed equal to V2 + 10 kt with all engines operating, air conditioningOFF, and gear retracted, with cutback.

- Landingapproachat FLAPS30configurationona three degreeglide slope, ata speed of at least 1.23 VS1G was used with air conditioning ON and gearextended.

CONFIGURATION

Engines : Pratt & Whitney of Canada Ltd ; PW 124Propeller : Hamilton Standard ; HS 14 SF-11 with spinner

CERTIFICATED NOISE LEVELS

TAKE-OFF 86.5 EPNdBSIDE LINE 84.7 EPNdBAPPROACH 94.1 EPNdB

01.01

APPENDIX No 01

7APPENDICES

PAGE : 110

AUG 07EASAAPPROVED

--

AFM1

Eng : PW124 Model : 201 -- 202Mod : 3651

EXTERNAL NOISE

NOISE CHARACTERISTICS

No determination has been made by the DGAC that the noise procedures andlevels in this manual are, or should be, acceptable or unacceptable foroperation at, into, or out of any airport.

NOISE LEVELS

Noise levels shown here after comply with ICAO annex 16 Chapter 3 noiserequirements and were obtained by analysis of approved data from approvednoise tests.See section 2.02.01 for identification of the maximum take off and landingweights 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 constantclimb speed equal to V2 + 10 kt with all engines operating, air conditioningOFF, and gear retracted, with cutback.

- Landingapproachat FLAPS30configurationona three degreeglide slope, ata speed of at least 1.23 VS1G was used with air conditioning ON and gearextended.

CONFIGURATION

Engines : Pratt & Whitney of Canada Ltd ; PW 124Propeller : Hamilton Standard ; HS 14 SF-11 with spinner

CERTIFICATED NOISE LEVELS

TAKE-OFF 86.9 EPNdBSIDE LINE 84.7 EPNdBAPPROACH 94.1 EPNdB

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

CONFIGURATION DEVIATION LIST

GENERAL

The configuration deviation list belongs to chapter 2 limitations of this airplaneflight manual. Flight with certain secondary airframe missing parts is possibleas indicated in this list. Any part not included in this list must be considered asnecessary.

Repairs or replacements must be done at the first station where appropriatefacilities are available, and in any case at the main base.

The sign ( -- ) in NUMBER INSTALLED or NUMBER REQUIRED FORDISPATCH columns indicates that the quantity is variable.

Letter ( m ) against an item indicates that some maintenance action isnecessary to permit flight with these parts missing. Refer to the related sectionof the Maintenance Manual for this information.

LIMITATIONS

Nomore than one part for any one sub-system in this appendixmay bemissingunless specifically designated combinations are indicated herein.Unless otherwise specified herein, parts from different sub-systems may bemissing.

Whenmissing part introduces additional limitation(s), this limitation is indicatedin “REMARKS or CONDITIONS“ column. This limitation comes in addition tolimitations of chapter 2 of Flight Manual. It must be clearly indicated by aplacard on the captain’s instrument panel.

PERFORMANCE

Performance penalties are indicated in “REMARKS or CONDITIONS” column.Performance penalties are cumulative unless specific penalties for particularcombinations of missing parts are indicated.

These take-off, en route and landing penalties apply to the most limitingcorresponding weight.

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

ATA CHAPTER 1

ITEM

2 -- NUMBER INSTALLED

3 -- NUMBER REQUIRED FOR DISPATCH

4 -- REMARKS OR CONDITIONS

2

23 -- COMMUNICATIONS

1 -- Static dischargers 25 17 Provided :a) each aileron is equipped with at least4 operative static dischargers, and

b) rudder is equipped with at least 4operative static dischargers and

c) each elevator is equipped with atleast 2 operative static dischargers

d) tail cone is equipped with at least oneoperative static discharger.

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

ATA CHAPTER 1

ITEM




3

27 -- FLIGHT CONTROLS

1 -- Flap hinge fairing 8 6 Provided aircraft is not operated intoknown or forecast icing conditions

2 -- Flap lower surface 4 3trailing edge

3 -- Inner / outer flaps coupling 2 0 Provided flaps are retracted, placardedsystem and considered inoperative.

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

ATA CHAPTER 1

ITEM




4

32 -- LANDING GEAR

1 -- Main gear door 2 1 Provided aircraft is not operated intoknown or forecast icing conditionsMaximum speed : 200 kt

1 bis -- Main gear 4 2 Provided missing parts are on thefoldable doors 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

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

ATA CHAPTER 1

ITEM




5

52 -- DOORS

1 -- Access door to GPU 2 0connector (DC or ACW)

2 -- Access door to refueling 1 0panel

3 -- Access door to hydraulic 1 0bay

4 -- Access door to water 1 0service panel

5 -- Access door to toilet 1 0service panel

6 -- Access door to tail cone 1 0 Maximum speed : 200 ktbay

7 -- Access door to air 1 0 Maximum speed : 200 ktconditioning externalconnector

8 -- Access door to refueling 1 0point

9 -- Jacking point covers -- 0

01.02

APPENDIX No 02

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

ATA CHAPTER 1

ITEM




6

61 -- PROPELLER

1 -- Propeller spinner 2 1 Provided aircraft is not operated intoknown or forecast icing conditions

79 -- OIL

1 -- Engine oil cooler flap 2 0 Provided flap is removed

01.03

APPENDIX No 03

7APPENDICES

PAGE : 150

AUG 07EASAAPPROVED

--

Mod : 0069 + 1112

AFM

1

CAT II OPERATION

LIMITATIONS

This appendix is intended to provide necessary information to allow the use ofthe aircraft in category II.

Limitations, procedures and performance included in the appendix replace orcomplete the corresponding information of the basic Flight Manual.

The automatic flight control system (AFCS) with the associated equipment hasbeen 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 constituteapproval to conduct category II operations.Such authorization must be obtained by the operator from theappropriate 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 : 30 ktTailwind : 10 ktCrosswind : 15 kt

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

2

CAT II OPERATION (CONT’D)

NORMAL PROCEDURES

NOTA : Failures have been demonstrated using the procedures described inthis chapter.

A -- Approved configurations

• Approach : AP is approved with use of approach mode for CAT IIprecision ILS approaches. The CAT II capability must be displayed onADU.

• 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 ftVc ≤ 180 kt at 1500 ft

• Approach speed :

When the aircraft is stabilized on GLIDE slope the selected approachspeedVAPP is 1.23VSR (flaps 30) +wind correction and not less thanVMCL.

The wind correction is equal to the highest of 1/3 of the reportedheadwind or the gust in full, with a maximum correction of 15 kt.

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM3


C -- Minimum equipment required to meet CAT II approach criteria.

Approach withAP

Autopilot 1FD bars sw 1 CM1 sideAP quick disconnect 1 CM1 sideADU 1ILS receiver 2AHRS 2Standby Horizon 1CRT 3

SGU 2Radio altimeter 1 (with 2 displays)DH indicator 2GA pushbutton 1 CM1 sideWindshield wipers 1 CM1 sideYaw damper 1Airspeed indicators 2

ADC 2 must be operativeHydraulic system Blue + GreenElectrical system 1 DC generator

1 AC generatorMFC modules 3

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

4


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 glideslope interception.

NOTA : GLIDE capture is inhibited as long as localizer capture is notinitiated (LOC*).

- The approach speed (VAPP) is 1.23 VS1G (FLAPS 30) + windcorrection and not less than VMCL.

- The approach configuration is FLAPS 30.

-- Mode phases

LOC* At localizer capture the white LOC extinguishes and thegreen LOC* illuminates on both EADI and on ADU.LOC phase engages when the A/C is stabilized on the LOCbeam axis.LOC illuminates on both EADI and on ADU.

GS* At glide slope capture the white GS extinguishes and thegreen GS* illuminates on both EADI and on ADU.GS phase engages when the A/C is stabilized on the GLIDESLOPE.Green GS illuminates on both EADI and on ADU.

1200 > ZRA > 800 ft Before 800 ft (radio altimeter), dual couplingmust 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 radioaltimeter value.

DH Amber DH symbol illuminates in the white box.

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 150

AUG 07EASAAPPROVED

--

Mod : 0069 + 1112

AFM

5


E -- Normal approach and landing sequence.

Final Approach

-- CM2 (pilot flying) monitors the A/C position and the trajectoryparameters. He announces mode changes. He asks PNFfor flaps setting and gear extension.

-- CM1 (pilot non flying) monitors the flight path and controlsspeed.

-- 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 lowerthan 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 bedone if :- Speed becomes lower than V APP -- 5 kt or greater thanV APP + 10 kt (V APP is the selected approach speed).

- Pitch attitude becomes lower than 4o nose down or greater than4o 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/Sdeviation occurs.

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

6


F -- GO around sequence (configuration flaps 30)

-- CM1 announces “GO AROUND, flaps 15presses the GO AROUND push button, follows the FDbars and advances PL to the ramp.

-- CM2 retracts flaps one step, adjusts and monitors engineparameters

As soon as rate of climb is positive :-- CM2 announces it.-- CM1 asks for gear retraction-- CM2 retracts the gear

EMERGENCY PROCEDURENO CHANGE

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

7

Eng : PW124

CAT II OPERATION (CONT’D)PROCEDURES FOLLOWING FAILURE

DEMONSTRATED ALTITUDE LOSS WITH(AP/FD) SYSTEM MALFUNCTION

Maximumpath deviationwith take over occuring 1 second after failurerecognition : 30 ft.

DEVIATION PROFILE -- CAT II

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

8


FAILURES AND ASSOCIATED ACTIONS DURING APPROACH

If external visual references are insufficient, failures not completely treatedbefore 800 ft should lead to a missed approach.

Nota 1 : ENGINE FAILURE

Provided lateral trimming is properly achieved before 800 ft, singleengine approachmay be performedwith autopilot engaged, but mustbe restricted to CAT I.

Nota 2 : AFCS failure and trajectory deviation

In case of CAT II INVALID, excess deviations or AFCS failure, goaround must be performed with STBY HORIZON : initial missedapproach attitude : 10o.

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

9


FAILURES AND ASSOCIATED ACTIONS DURING A CAT II APPROACH

A/C SYSTEMS

Warnings Actions at the time of failure detection> 800 ft < 800 ft

Complementaryactions

Flap failure,jammed between 0and 15 position

Revert toCat I minima

Notapplicable

Flap failure,jammed above 15position

ContinueIncrease VAPP

(flaps 30)by 10 kt

Multiply landingdistance flaps 30 by

1.13

Engine failure Revert to Cat Iminima

Discontinuethe approach

Hydraulic failure(without fluid loss)

TransferNo capability loss

First MFCmodule failure

Apply associatedprocedurecontinue theapproach


Second MFCmodule failure

Apply associatedprocedureRevert to

CAT 1 minima


.. / ..

01.03

APPENDIX No 03

7

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

10APPENDICES


FAILURES AND ASSOCIATED ACTIONS DURING A CAT II APPROACH

FLIGHT INSTRUMENTS

Warnings Actions at the time of failure detection> 800 ft < 800 ft

Complementaryactions

Standby horizonflag

Revert to Cat Iminima

Radio altimeterwarningon CM2 EFIS

Revert to Cat Iminima


ATT / PIT / ROLLwarning on anyEFIS

Switch to valid AHRSReengage APRevert to Cat I

minima

First action beforeswitching AHRS isto refer to standbyhorizon to determine

HDG warningon any EFIS

Switch to valid AHRSRevert to CAT I

minima

horizon to determinethe wrong AHRS

LOC / GS / ILS /warning on anyEFIS

Revert toCat I minima

Loss of one CRT Switch affectedCRT OFF

Loss of bothCRT on one side

Switch to validSGU. Revertto Cat I minima

Loss of ADC 2 Revert toCat I minima

.. / ..

01.03

APPENDIX No 03

7APPENDICES

PAGE : 100

AUG 07EASAAPPROVED

--

Mod : 1112

AFM

11


FAILURES AND ASSOCIATED ACTIONSDURING A CAT II APPROACH

AFCS and ADU

Warnings Actions at the time of failure detectionZ RA : 800 ft 500 ft

Complementaryaction

AP disengage Try to recoverIf impossible

revertto Cat I

FD approach

discontinuethe approach

LOC or G/Sexcess deviation

Not applicable discontinuethe approach

Loss of ADU Perform a Cat Iminima manual

approach


Loss of Cat IIcapability(Triple click)

Try to recoverIf impossiblerevert to

Cat I minima


.. / ..

AUG 07APPENDIX No 03

APPENDICESPAGE : 100

Eng : PW124

EASAAPPROVED

Mod : 1112

AFM12

01.037--

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 POWERAIR CONDITIONING ON -- ANTI/DE ICING OFF -- GEAR UP -- V = 1.14 VS1G

.. / ..



EASAAPPROVED

Mod : 1112 + 1368

AFM13

01.037--

Eng : PW124

CAT II OPERATION (CONT’D)ICING CONDITIONS

LANDING CAT II -- APPROACH CLIMB GRADIENTAPPROACH CLIMB LIMITING WEIGHT (FLAPS 15)

ONE PROPELLER FEATHERED -- ONE ENGINE : GO AROUND POWERAIR CONDITIONING ON -- DE ICING ON -- GEAR UP -- V = 1.23 VS1G

NORMALCONDITIONSANDAIRCRAFTFREEOFICE(ICINGAOAOFF)

ATMOSPHERIC

ICINGCONDITIONSORRESIDUALICEONTHEAIRCRAFT(ICINGAOALIT)

01.04

APPENDIX No 04

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

TCASThis 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 -- GENERALThe general information in Section 1 are applicable.

2 -- LIMITATIONSThe 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 thetraffic display only or from a traffic advisory (TCAS) only.These displays and advisory are intended only for assistance in visuallylocating the traffic and lack the resolution necessary for use in evasivemaneuvering.

3. Compliance with TCAS resolution advisory is required unless the pilotconsiders it unsafe to do so.However maneuvers which are in the opposite direction of the resolutionadvisory (TCAS) are extremely hazardous and are prohibited unless it isvisually determinated they are the only means to assure safe separation.

CAUTION : Once a non crossing RA has been issued the vertical speedshould be accurately adjusted to comply with the RA, in orderto avoid negating the effectiveness of a co--ordinatedmaneuvre by the intruder.

WARNING : Non compliancewith a crossingRAby oneairplanemay resultin reduced vertical separation. Therefore, safe horizontalseparation must also be assured by visual means.

4. Evasive maneuvring should be made with the autopilot disengaged, andlimited to the minimum required to comply with the RA. The pilot mustpromptly return to the previous ATC clearancewhen the TCAS “CLEAROFCONFLICT” voice message is announced.

5. Prior to perform RA’s climb or increase climb, the crew should select theappropriate engine power setting on the power MGT rotary selector and, ifnecessary, manually adjust CLs.

6. When a climb or increase climb RA occurs with the airplane in the landingconfiguration or in the go--around phase, a normal procedure of go--aroundshould be followed including the appropriate power increase andconfiguration changes.

.. / ..

01.04

APPENDIX No 04

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

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 aircraftperformance inhibits, there are instances where inhibiting RA’s would beappropriate, however it is not possible to do so. In these cases, TCAS maycommandmaneuvers which may significantly reduce stall margins or resultin stall warning. Conditions where this may occur include operations with abank angle (wings level is assumed), weight altitude and temperaturecombinations outside those noted below, leaving aircraft in landingconfiguration during climb RA on approach, engine out operations, andabnormal configurations such as landing gear not retracted or stickpusher/shaker failure.

The table below entitled “Flight envelope in which climb resolution advisorycan be accomplished without stick pusher/shaker activation” outlines theparameters used in the development of the performance inhibits. This tabledoes not consider worst turboprop flight conditions especially operationsusing minimum operating airspeeds as are sometimes required (e.g.obstacle clearance, ATC constraints). In all cases, stall warning must begiven precedence over climb RA commands.

NOTE : TCAS is viewed as a supplement to the pilot who, with the aid of theATC system, has the primary responsibility for avoiding mid--aircollisions.

WARNING : Priority must be granted to increasing airspeed when reachingstall warningevenwhen this requires deviation fromanRAcommand issued by the TCAS.

.. / ..

01.04

APPENDIX No 04

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

AIRSPEED


FLIGHT ENVELOPE IN WHICH CLIMB RESOLUTION ADVISORY CANBE ACHIEVED WITHOUT STICK PUSHER / SHAKER ACTIVATION

FLIGHTREGIME

WEIGHTALTITUDETEMP

POWER FLAPS GEARINITIAL MIN.

Take off FAR25/JAR25Climb limit

Take off 15 Up V2 + 20 1.13 Vsr

Approach FAR25/JAR25Climb limit

Spin up to goaround powerduring maneuver

from power for levelflight

15 Up 1.51 Vsr 1.13 Vsr

LandingTransitioningto go around

at RA

FAR25/JAR25Climb limit

Spin up to goaround power

during maneuverfrom power requiredfor 30 Glide Slope

Transi-tionfrom

30 to 15

DntoUp

Vapp + 10 1.13 Vsr

En route

CriticalWt / Alt giving1.3 G to Buffet

onset

Power for levelflight

increased to MaxContinuous

Up UpLongRangeCruise

Higher of1.13 Vsrif Definedor buffetonset

• Temperature range up to ISA + 270

• Altitude range -- En route 0 25 000 ft-- Take off 0 6 000 ft-- Approach and landing 0 7 000 ft

* Wings level assumed

.. / ..

01.04

APPENDIX No 04

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4


8. Inhibition schemes

8.1 NON ICING CONDITIONS

CONFIGURATION RA CLIMB RA INCREASE CLIMB

FLAPS 0FLAPS 15 TOFLAPS 15 ApproachFLAPS 30

AUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZED

AUTHORIZEDINHIBITED

AUTHORIZEDINHIBITED

8.2 ICING CONDITIONS

CONFIGURATION RA CLIMB RA INCREASE CLIMB

FLAPS 0 Z < 20000 ftZ > 20000 ft

FLAPS 15 TOFLAPS 15 ApproachFLAPS 30

AUTHORIZEDINHIBITED

AUTHORIZEDAUTHORIZEDINHIBITED

INHIBITEDINHIBITEDINHIBITEDINHIBITEDINHIBITED

NOTE 1 : Pilots are authorized to deviate from their current ATCclearance to the extent necessary to comply with a TCASresolution advisory.

NOTE 2 : Maneuvers based solely on information displayed on the trafficdisplay are not authorized.

.. / ..

01.04

APPENDIX No 04

7APPENDICES

PAGE : 110

AUG 07DGACAPPROVED

--

Mod : 5205

AFM

5


3 -- NORMAL PROCEDURESThe normal procedures in Section 3 are applicable.

4 -- EMERGENCY PROCEDURESThe emergency procedures in Section 4 are applicable.

5 -- PROCEDURES FOLLOWING FAILURESThe procedures following failures are applicable with the addition ofthe 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 -- PERFORMANCESThe performances in Section 6 are applicable.

01.05

APPENDIX No 05

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

STEEP SLOPE APPROACH(APPROACH SLOPE > 4.5_)

NOT APPLICABLE

01.06

APPENDIX No 06

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

CONTAINER TRANSPORT

NOT APPLICABLE

01.08

APPENDIX No 08

7APPENDICES

PAGE : 100

EASAAPPROVED

--

AFM1

Eng : PW124

AUG 07

ETOPS

1 -- GENERAL

APPLICABILITY

This supplement applies to airplanes operated according to the provisionsof 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/enginecombination has been evaluated and found to comply with the criteria ofCTC 20 according to DGAC interpretation of FAA Advisory Circular AC120--42A chapter 8, 9 (a) and appendix 1when configured,maintained andoperated in accordance with provisions of CMP standards for ETOPS atthe latest approved revision.

This Statement of Capability does not constitute approval to conductETOPS flights.

2 -- LIMITATIONSThe limitations of section 2 of this Flight Manual must be completed by thefollowing :

Maximum diversion time may not exceed 120 minutes at one enginecruising speed.

3 -- FLIGHT MANUAL SUPPLEMENT EXCLUSIONTransport of Containers and dispatch with one AFU inoperative are notpermitted in conjunction with this supplement.

4 -- PROCEDURESTheprocedures of sections 3and 4of this FlightManual remain applicable.

A special attention should be paid to the fuel unbalance (refer to chapter2.04.05).

5 -- PERFORMANCE

- Refer to chapter 6.04 (normal conditions) and 6.06 (icing conditions) ofthismanual 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 netgradient at 200 kt IAS.

.. / ..



EASAAPPROVED

Eng : PW124

AFM2

01.087--

Mod : 2735... / ...

ETOPS (CONT’D)DESCENT 1 ENGINE WITHOUT OBSTACLE -- NET GRADIENT -- 200 KT IASFLAPS 0 -- NORMAL CONDITIONS -- AIR CONDITIONING OFF BELOW 10000 FT

AIR CONDITIONING OFF below 10000 ft



EASAAPPROVED

Eng : PW124

AFM3

01.087--

Mod : 1368 + 2735

ETOPS (CONT’D)DESCENT 1 ENGINE WITHOUT OBSTACLE -- NET GRADIENT -- 200 KT IASFLAPS 0 -- ICING CONDITIONS -- AIR CONDITIONING OFF BELOW 10000 FT

AIR CONDITIONING OFF below 10000 ft

01.09

APPENDIX No 09

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM1

OPERATIONS ON NARROW RUNWAYS

NOT APPLICABLE

01.10

APPENDIX No 10

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

RUNWAY SLOPE BEYOND 2%

NOT APPLICABLE

APPENDIX N_ 11


EASAAPPROVED

7 -- 01.11

AFM

1

AUG 07

POWER PLANT

NOT APPLICABLE

APPENDIX N_ 12


AUG 07EASAAPPROVED

7 -- 01.12

AFM

1

TAKE OFF AFTER USE OF FLUIDS TYPE II OR IV

This appendix applies only to aircraft de/anti iced before take off, using fluidstype II or type IV.

These types of fluids may lead to an increase in control forces necessary torotate, and then to a modification of take off performances.

Therefore this Flight Manual must be modified in compliance with one of thefollowing 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

APPENDIX N_ 1


EASAAPPROVED

AFM

1A

AUG 07

7 -- 01.12


COMPLIANCE METHOD 1

1. GENERALThe general information in Section 1 are applicable.

2. LIMITATIONSThe limitations in Section 2 are applicable.

3. NORMAL PROCEDURESThe normal procedures in Section 3 are applicable.

4. EMERGENCY PROCEDURESThe emergency procedures in Section 4 are applicable.

5. PROCEDURES FOLLOWING FAILURESThe procedures following failures in Section 5 are applicable.

6. PERFORMANCESTheperformances inSection6 for dry runwaysand inSection 7.03 for nondryrunways (advisory materials) are applicable with the addition of the followingfor take off computations :Determine VR for the lowest available V2Assume V1 = VRIncrease TOR, TOD, ASD by 25 %

7. APPENDICES AND SUPPLEMENTSData 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 disconnectedTake off with flaps retracted.

APPENDIX N_ 12


EASAAPPROVED

AFM

1B

AUG 07

7 -- 01.12


COMPLIANCE METHOD 2CREW TRAINING REQUIRED

1. GENERALThe general information in Section 1 are applicable.

2. LIMITATIONSThe limitations in Section 2 are applicable.

3. NORMAL PROCEDURESThe normal procedures in Section 3 are applicable with the addition of thefollowing :TheCaptainmust be the pilot flying and the pre--take off briefingmust includethe following take off procedure (point 5).

4. EMERGENCY PROCEDURESThe emergency procedures in Section 4 are applicable.

5. PROCEDURES FOLLOWING FAILURESThe procedures following failures in Section 5 are applicable with the additionof the following :TAKE OFF SEQUENCEIn case of difficulties to rotate, the Captain should require the non flying pilotassistance.In that case, onCPT order, PNF pulls the control column until 5_ pitch attitudeis reached, then PNF releases the controls.

6. PERFORMANCESThe performances in Section 6 for dry runways and in section 7.03 for non dryrunways (advisorymaterials) are applicablewith the addition of the following :

Increase the TOD by 70m.

7. APPENDICES AND SUPPLEMENTSData 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 flightTake off with flaps retracted.

APPENDIX N_ 13


EASAAPPROVED

7 -- 01.13

AFM

1

Mod : 5434 or 5465 or 8330 or 8333

AUG 07

COCKPIT DOOR SECURITY SYSTEMLIMITATIONS

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 PROCEDURESDaily 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 BOLTSBefore Taxi

- COCKPIT DOOR LOCKING SYSTEM SW ON. . . . . . . . . . . . . . . . . . . . .Before leaving the aircraft

- COCKPIT DOOR LOCKING SYSTEM SW OFF. . . . . . . . . . . . . . . . . . . .

.. / ..

APPENDIX N_ 13


EASAAPPROVED

7 -- 01.13

AFM

2

Model : 102--202--212Mod : 5434 or 8330

AUG 07

COCKPIT DOOR SECURITY SYSTEM (CONT’D)

EMERGENCY PROCEDURESElectrical Power Lost

- Move the manual lock bolts to CLOSE position

- Note : when the door is locked with the manual bolts, the emergencyaccess to the cockpit is unavailable. It is recommended that at leasttwo crew members remain in the cockpit during that time.

Cockpit Door Jammed

DWhen 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 FAILURESCockpit 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 emergencyaccess to the cockpit is unavailable. It is recommended that at leasttwo crew members remain in the cockpit during that time.

DC ESS BUS Lost

- ApplyCockpit DoorControl Panel FAULTLIGHT illuminatesprocedure

- Note : Cockpit Door Control Panel FAULT LIGHT is inoperative.

PERFORMANCE NO CHANGE

APPENDIX N_ 15


EASAAPPROVED

7 -- 01.15

AFM

1

AUG 07

Aircraft Performance Monitoring -- APMThis Appendix is applicable only for aircraft fitted with mod 5567 or 8442.

LIMITATIONSInstallation 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 illuminationand single chime

In Flight, Climb, Cruise and Descent

APM LIGHTS and CAUTION MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

H CRUISE SPEED LOW light illuminatedAppears in cruise only, to inform the crew that an abnormal dragincrease induces a speed decrease of more than 10 kt comparedwith the expected speed

ICING CONDITIONS and SPEED MONITOR. . . . . . . . . . . . . . . . .

.. / ..

APPENDIX N_ 15


EASAAPPROVED

7 -- 01.15

AFM

2

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 illuminatedAPM OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

"DEGRADED PERF light illuminated with CAUTION and SINGLE CHIME

Mainly appears in level flight after CRUISESPEEDLOWor in climb to informthe crew that an abnormal drag increase induces a speed decrease or a lossof 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 inspeed or rate of climb, visual cues)

orH If impossibility to maintain IAS > RED BUG + 10 kt in level flight

orH If abnormal aircraft handling feeling

SEVERE ICING procedure (4--05) APPLY. . . . . . . . . . . . . . . . . . . . .

H If notSCHEDULED FLIGHT CONTINUE. . . . . . . . . . . . . . . . . . . . . . . . . . . .ICING CONDITIONS and SPEED MONITOR. . . . . . . . . . . . . . . . . . .

" INCREASE SPEED light illuminated flashing with CAUTION andSINGLE CHIME

Appears after DEGRADED PERF to inform the crew that the drag isabnormally high and IAS is lower than RED BUG + 10 KT.

H If abnormal conditions confirmedIMMEDIATELY PUSH THE STICK TO INCREASE SPEED

TO RECOVER MINIMUM IAS = RED BUG + 10 KTSEVERE ICING procedure (4--05) APPLY. . . . . . . . . . . . . . . . . . . . .

APPENDIX N_ 16


EASAAPPROVED

7 -- 01.16

AFM

1

AUG 07

SSR Mode S Enhanced SurveillanceThis Appendix is applicable only for aircraft fitted with

mod 5570 (GNSS) or mod 8431 (KLN90B).

LIMITATIONSThe installed Mode S system satisfies the data requirements of ICAO Doc7030/4, Regional Supplementary Procedures for SSR Mode S EnhancedSurveillance in designated European airspace. The capability to transmit dataparameters is shown in column 2:

Parameter Available/Not available

Magnetic Heading

Indicated Airspeed

Available

Mach No Available

Vertical Rate Available

Roll Angle Available

True Air Speed Available

True Track Angle Available only on aircraft fittedwih GNSS or GPS KLN90B

Groundspeed Available only on aircraft fittedwih GNSS or GPS KLN90B

Selected Altitude Available

Barometric Pressure Setting Available

To be inserted in the flight manual and record sheet amended accordingly

APPENDIX N_ 17


EASAAPPROVED

7 -- 01.17

AFM

1

AUG 07

ACARSModification 5506 not applied.

APPENDIX N_ 18


EASAAPPROVED

7 -- 01.18

AFM

1

AUG 07

HIGH LATITUDES OPERATIONS

CONDITIONSAnomalous heading errors may occur on aircraft equipped with the HoneywellAH--600AHRSduringhigh latitudeoperations, where the earth’smagnetic lines offorce have inclinations of greater than 75 degrees.

PROCEDURES

--Take special care to keep the slip indicator centered in order tominimize headingerrors.--Crosscheck AHRS heading information with that of standby compass.

01.19

APPENDIX No 19

7APPENDICES

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

DRY UNPAVED RUNWAYS

NOT APPLICABLE

02.00

INTRODUCTION

7SUPPLEMENTS

PAGE : 001EASA

APPROVED

--

AFM

1

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

02.01

SUPPLEMENT No 01

7SUPPLEMENTS

PAGE : 001EASA

APPROVED

--

AFM

1

AUG 07

DISPATCH WITH ONE ACW GENERATOR CHANNELINOPERATIVE

- 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

... / ...

02.01

SUPPLEMENT No 01

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

DISPATCH WITH ONE ACW GENERATOR CHANNELINOPERATIVE (CONT’D)

EMERGENCY BRAKINGEFFECT ON ACCELERATE STOP DISTANCE

... / ...

02.01

SUPPLEMENT No 01

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3


EFFECT OF GEAR DOWNON 2ND SEGMENT CLIMB AND APPROACH CLIMB

... / ...

02.01

SUPPLEMENT No 01

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4


EFFECT OF GEAR DOWN ON FINAL TAKE OFF CLIMB ANDWEIGHT PENALTY ON SINGLE ENGINE CEILING COMPUTATION

02.02

SUPPLEMENT No 02

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

Eng : PW124

DISPATCH WITH SPOILERS CONTROL SYSTEMINOPERATIVE

Increase VMCA by 2 ktVMCL FLAPS 30 = 101 ktMaximum crosswind on dry runway : 20 ktTake off with fuel unbalance must be avoided

02.03

SUPPLEMENT No 03

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

Eng : PW124

DISPATCH WITH FLAPS RETRACTED

- Authorized only if aircraft is not operated into known or forecast icingconditions.

- 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 previouslydetermined CAS values.

- DecreaseV1 limited bymaxbrake energy by 5 kt and checkV1V1 limitedbymax 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 onthe 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° 2.5 2 1.5 1 0.4NOSE UP UP UP UP UP

... / ...

02.03

SUPPLEMENT No 03

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

Eng : PW124

DISPATCH WITH FLAPS RETRACTED (CONT’D)TAKE OFF WITH FLAPS RETRACTED

TAKE OFF RUN CORRECTIONS

... / ...

02.03

SUPPLEMENT No 03

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

Eng : PW124

DISPATCH WITH FLAPS RETRACTED (CONT’D)TAKE OFF WITH FLAPS RETRACTEDTAKE OFF DISTANCE CORRECTIONS

... / ...

02.03

SUPPLEMENT No 03

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4

Eng : PW124

DISPATCH WITH FLAPS RETRACTED (CONT’D)TAKE OFF WITH FLAPS RETRACTED

ACCELERATE STOP DISTANCE CORRECTIONS

02.04

SUPPLEMENT No 04

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

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)

02.05

SUPPLEMENT No 05

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

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)

... / ...

02.05

SUPPLEMENT No 05

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

DISPATCH WITH ANTI--SKID SYSTEM INOPERATIVE (CONT’D)

ANTI--SKID OFF EFFECT ON ACCELERATE STOP DISTANCE (FLAPS 15)

02.06

SUPPLEMENT No 06

7SUPPLEMENTS

PAGE : 001

EASAAPPROVED

--

AFM

1

Eng : PW124

AUG 07

DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE

Uptrim and AFU are considered operative. If not, refer to the connectedprocedure.

-- 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 PLAbefore feathering.

NOTE: Readjust RTO power upon reaching acceleration height.

... / ...

02.06

SUPPLEMENT No 06

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

Eng : PW124

DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE(CONT’D)

EFFECT ON TAKE OFF RUN (FLAPS 15)

... / ...

02.06

SUPPLEMENT No 06

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

Eng : PW124


EFFECT ON TAKE OFF DISTANCE (FLAPS 15)

... / ...

02.06

SUPPLEMENT No 06

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4

Eng : PW124


EFFECT ON 2nd SEGMENT

02.07

SUPPLEMENT No 07

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

Eng : PW124

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 ATPCSOFF.

• 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 bypushing PL up to the ramp.

• Engine(s) with inoperative EEC must be set to RTO power (¦ 2 %) byadjusting 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. . . . . . . . . . . . . . .

... / ...

02.07

SUPPLEMENT No 07

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

Eng : PW124

DISPATCH WITH ONE OR BOTH EEC OFF (CONT’D)


... / ...

02.07

SUPPLEMENT No 07

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

Eng : PW124



... / ...

02.07

SUPPLEMENT No 07

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4

Eng : PW124


EFFECT ON ACCELERATE STOP DISTANCE (FLAPS 15)

... / ...

02.07

SUPPLEMENT No 07

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

5

Eng : PW124


EFFECT ON SECOND SEGMENT WEIGHT

02.08

SUPPLEMENT No 08

7SUPPLEMENTS

PAGE : 001

EASAAPPROVED

--

AFM

1

AUG 07

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.

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE

J If only the FDAU bug is inoperativeConsider 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 withATPCS 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 Supplement07 : Dispatch with EEC inoperative.

J If both pointer and counter are inoperative on one side :

ATPCS and both EEC must be operative• Take offCheck effect on performances (pages 2 to 5)Increase VR by 1 ktUse minimum fuel flow tables (pages 6 to 11)

CAUTION: NoteRTOandMCTmin fuel flow to be applied in case of engineflame 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 islower than anticipated by take off min fuel flow table.Observe ITT limitation.

• Climb / CruiseBLEED 1+2 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Check engine fuel flow on inoperative side and maintain it within ¦ 5 %band of opposite engine one.

• Go aroundPL 1+2 UP TO THE RAMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Check and adjust fuel flow if the inoperative side indication is lower thananticipated by go around min fuel flow table.Observe ITT limitation.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)EFFECT ON TAKE OFF RUN (FLAPS 15)

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)EFFECT ON TAKE OFF DISTANCE (FLAPS 15)

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)ACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

5

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 andapproach climb weights.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

6

Eng : PW124

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)TAKE OFF MIN. FUEL FLOW (KG/H) NP 100% VC=50 KT

SAT (C)PRESSURE ALTITUDE (FT)

SAT (C)--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.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

7

Eng : PW124

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)RESERVE TAKE OFF MIN. FUEL FLOW (KG/H) NP 100% VC=50 KT


SAT (C)--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.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

8

Eng : PW124

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)GO AROUND MIN. FUEL FLOW (KG/H) NP 100% VC=100 KT


SAT (C)--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.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

9

Eng : PW124

DISPATCH WITH ONE TQ INDICATOR INOPERATIVE (CONT’D)

MAXI CONTINUOUS MIN. FUEL FLOW (KG/H) NP 100% VC = 120. KT

PRESSURE ALTITUDE (FT)TAT


PRESSURE ALTITUDE (FT)TAT(C)

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.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

10

Eng : PW124






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.

... / ...

02.09

SUPPLEMENT No 09

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

11

Eng : PW124






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.

02.10

SUPPLEMENT No 10

7SUPPLEMENTS

PAGE : 001

EASAAPPROVED

--

AFM

1

Eng : PW124

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.

... / ...

02.10

SUPPLEMENT No 10

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

Eng : PW124

DISPATCH WITH ATPCS OFF (CONT’D)


... / ...

02.10

SUPPLEMENT No 10

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

Eng : PW124



... / ...

02.10

SUPPLEMENT No 10

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

4

Eng : PW124


EFFECT ON SECOND SEGMENT WEIGHT (FLAPS 15)

02.11

SUPPLEMENT No 11

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

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 pressingRCL pb.

- Limit maximum speed to 160 kt.

... / ...

02.11

SUPPLEMENT No 11

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

2

FLIGHT WITH LANDING GEAR DOWN (CONT’D)EFFECT ON SECOND SEGMENT CLIMB

AND APPROACH CLIMB

... / ...

02.11

SUPPLEMENT No 11

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

3

FLIGHT WITH LANDING GEAR DOWN (CONT’D)

EFFECT ON FINAL TAKE OFFWEIGHT PENALTY ON SINGLE ENGINE CEILING COMPUTATION

Valid for all configurations

02.12

SUPPLEMENT No 12

7SUPPLEMENTS

PAGE : 001

AUG 07EASAAPPROVED

--

AFM

1

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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99DGACAPPROVED

–

AFM1

Date révision antérieure

SEP 98

R

R

7 . 03 . 01 – GENERAL

This information has been prepared by the manufacturer and approved by theAuthority in the form of guidance material, to assist operators in developingsuitable guidance, recommandations or instructions for use by their flightcrews when operating on wet/contaminated runway surface conditions.Unless otherwise stated, this information does not in any way replace or amendthe operating limitations and performance information listed in other parts ofthis approved aeroplane flight manual.

A non dry runway may be :- wet : well soaked but without significant areas of standing water.

NOTE : a runway is considered well soaked when there is sufficientmoisture on the runway surface to cause it to appear reflective.

- contaminated, if more than 25 % of the required area are covered by thecontaminant.

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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99DGACAPPROVED

–

AFM1A


R

SEP 98

R

7 . 03 . 02 – TAKE OFF

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

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 tothe 15 ft computation, for water covered runways.

- accelerate stop distance. They are basically computed with the use ofboth reversers. Additional pages are provided to supply data in case ofno reverser and are to be used for flight preparation.Since the effect of asymmetrical reverse thrust is not predictable with asufficient accuracy on contaminated runways, it is therefore notrecommended 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 ofatmospheric icing conditions, refer to 6.06 to combine both effects (runwayconditions + 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 inexcess of that permitted on an equivalent dry runway is notallowed.

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99DGACAPPROVED

–

AFM2


SEP 98

R V1 LIMITED BY VMCG :

Refer to 6.03 p 2:

V1 limited by VMCG on DRY RUNWAYS

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM3 DATE

REVISIONANTERIEURE

WET RUNWAYTAKE 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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM4 DATE

REVISIONANTERIEURE

WET RUNWAYTAKE 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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM5 DATE

REVISIONANTERIEURE

JAN 93

R

WET RUNWAYACCELERATE STOP DISTANCE (FLAPS 15)

TWO ENGINES OPERATING OR ONE ENGINE FAILEDAIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM6


AC

TU

AL

DIS

TAN

CE

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

WET RUNWAYACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM7 DATE

REVISIONANTERIEURE

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 POWERAIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM8 DATE

REVISIONANTERIEURE

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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM9 DATE

REVISIONANTERIEURE

R

WATER COVERED RUNWAY : 6.3 mm : (1/4 in)ACCELERATE STOP DISTANCE (FLAPS 15)

TWO ENGINES OPERATING OR ONE ENGINE FAILEDAIR CONDITIONING OFF – ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99

Eng : PW 124

DGACAPPROVED

–

AFM10


SEP 98

TH

EO

RE

TIC

AL

DIS

TAN

CE

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

R

WATER COVERED RUNWAY : 6.3 mm : (1/4 in)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM11 DATE

REVISIONANTERIEURE

WATER COVERED RUNWAY : 6.3 mm (1/4 in)ROTATION SPEED VR (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWERAIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM12 DATE

REVISIONANTERIEURE

WATER COVERED RUNWAY : 12.7 mm (1/2 in)TAKE OFF RUN (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM13 DATE

REVISIONANTERIEURE

WATER COVERED RUNWAY : 12.7 mm (1/2 in)TAKE OFF DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM14 DATE

REVISIONANTERIEURE

R

WATER COVERED RUNWAY : 12.7 mm (1/2 in)ACCELERATE STOP DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99

Eng : PW 124

DGACAPPROVED

–

AFM15


SEP 98

TH

EO

RE

TIC

AL

DIS

TAN

CE

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

R

WATER COVERED RUNWAY : 12.7 mm : (1/2 in)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM16 DATE

REVISIONANTERIEUREJUL 03

R

WATER COVERED RUNWAY : 12.7 mm (1/2 in)ROTATION SPEED VR (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWERAIR CONDITIONING OFF– ANTI DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM17 DATE

REVISIONANTERIEURE

COMPACTED SNOW COVERED RUNWAYTAKE 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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM18 DATE

REVISIONANTERIEURE

COMPACTED SNOW COVERED RUNWAYTAKE OFF DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM19 DATE

REVISIONANTERIEURE

COMPACTED SNOW COVERED RUNWAYACCELERATE STOP DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99

Eng : PW 124

DGACAPPROVED

–

AFM20


TH

EO

RE

TIC

AL

DIS

TAN

CE

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

SEP 98

R

COMPACTED SNOW COVERED RUNWAYACCELERATE STOP DISTANCE CORRECTIONS (FLAPS 15)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM21 DATE

REVISIONANTERIEURE

COMPACTED SNOW COVERED RUNWAYROTATION 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

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM22 DATE

REVISIONANTERIEURE

ICE COVERED RUNWAYTAKE OFF RUN (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM23 DATE

REVISIONANTERIEURE

ICE COVERED RUNWAYTAKE OFF DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM24 DATE

REVISIONANTERIEURE

R

ICE COVERED RUNWAYACCELERATE STOP DISTANCE (FLAPS 15)


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99

Eng : PW 124

DGACAPPROVED

–

AFM25


SEP 98

R

1000

3000

5000

7000

9000

11000

13000

500

1000

1500

2000

2500

3000

3500

4000

1000

3000

5000

7000

9000

11000

13000

500

1000

1500

2000

2500

3000

3500

4000(FT) (METERS)

(FT)(METERS)

TH

EO

RE

TIC

AL

DIS

TAN

CE

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

ICE COVERED RUNWAY


03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM26 DATE

REVISIONANTERIEURE

ICE COVERED RUNWAYROTATION SPEED – VR (FLAPS 15)

ONE PROPELLER FEATHERED – ONE ENGINE AT R.T.O POWERAIR CONDITIONING OFF– ANTI/DE ICING OFF – NO RUNWAY SLOPE – NO WIND

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM26A DATE

REVISIONANTERIEURE

0

2000

4000

6000

8000

10000

12000

250

750

1250

1750

2250

2750

3250

0

2000

4000

6000

8000

10000

12000

250

750

1250

1750

2250

2750

3250

15 F

EE

T H

EIG

HT

35 F

EE

T H

EIG

HT

(FT

)

(FT

)

(ME

TE

RS

)

(ME

TE

RS

)

TAKE OFF RUN CORRECTIONS (FLAPS 15)

WATER COVERED RUNWAY : 6.3 or 12.7 mm (1/4 or 1/2 inch)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM26B DATE

REVISIONANTERIEURE

0

2000

4000

6000

8000

10000

12000

250

750

1250

1750

2250

2750

3250

0

2000

4000

6000

8000

10000

12000

250

750

1250

1750

2250

2750

3250

15 F

EE

T H

EIG

HT

35 F

EE

T H

EIG

HT

(FT

)

(ME

TE

RS

)

(FT

)

(ME

TE

RS

)

TAKE OFF DISTANCE CORRECTIONS (FLAPS 15)

WATER COVERED RUNWAY : 6.3 or 12.7 mm (1/4 or 1/2 inch)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 99DGACAPPROVED

–

AFM27


SEP 98

R

7 . 03 . 03 – LANDING

Three cases of contaminated runways have been considered :

- water : applicable for depths between 3mm (1/ 8 in) and 12.7 mm (1 / 2 in) ofwater, or less than 12.7 mm (1 / 2 in) of slush or equivalent depth of loosesnow.

- 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 sufficientaccuracy on contaminated runways, it is therefore not recommended to use singleengine reverse thrust. The actual landing distances without reversers, only, are tobe 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).

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM28 DATE

REVISIONANTERIEURE

TH

EO

RE

TIC

AL

DIS

TAN

CE

WIT

H T

WO

RE

VE

RS

ER

S

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH DEPTH

LANDING DISTANCE (FLAPS 30)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM29


OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH.

LANDING DISTANCE CORRECTIONS

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM30


OPERATION ON WATER COVERED RUNWAY VALID UP TO 1/2 INCH.

LANDING DISTANCE CORRECTIONS

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM31 DATE

REVISIONANTERIEURE

TH

EO

RE

TIC

AL

DIS

TAN

CE

WIT

H T

WO

RE

VE

RS

ER

S

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

OPERATION ON RUNWAY COVERED WITH COMPACTED SNOW LANDING DISTANCE (FLAPS 30)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM32


OPERATION ON RUNWAY COVERED WITH COMPACTED SNOWLANDING DISTANCE CORRECTION

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM33


OPERATION ON RUNWAYS COVERED WITH COMPACTED SNOWLANDING DISTANCE CORRECTIONS

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM34 DATE

REVISIONANTERIEURE

TH

EO

RE

TIC

AL

DIS

TAN

CE

WIT

H T

WO

RE

VE

RS

ER

S

AC

TU

AL

DIS

TAN

CE

WIT

HO

UT

RE

VE

RS

ER

OPERATION ON ICY RUNWAYLANDING DISTANCE ( FLAPS 30)

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM35

OPERATION ON ICY RUNWAY LANDING DISTANCE CORRECTION

03

NON DRY RUNWAYS

ADVISORY MATERIALS


PAGE : 001

SEP 98

Eng : PW 124

DGACAPPROVED

–

AFM36

OPERATION ON ICY RUNWAY LANDING DISTANCE CORRECTIONS

AFM 72 202

Documents

Transcript of AFM 72 202