AFM 72 202

(1)

(2)

P1

TQ

AUG 07

--LIST OF TEMPORARY REVISIONS

L. T. R.

AFM

0

01

082

EASA APPROVED

AIRPLANE FLIGHT MANUAL

No

TR EDITIONDATE DESTROYED INSERTIONDATE NAME OR REMARKS

(3)

PAGE :

001

MAY 92

–

AFM

0

02

DATE REASON FOR TEMPORARY REVISION CHAP INVOLVED

1 AIRPLANE FLIGHT MANUAL

R . T . R .

_DGAC

APPROVED

OCT 89 Introduction of modification 1742 2.04 – 3.04 Limitations – Power plant – 2.04 Limitations updating

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

Procedure following failure : 5.02 Modification of the procedure EEC FAULT

Graph add 6.05

JAN 90 Flight with pitch elevators disconnected 5.04 – 7.02 Modification 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 – 6.02

Introduction of modification 2595 2.02 – 3.00 – 3.06 Change of modification number 4.00 – 4.03 – 7.00

concerning mod 2059 7.02

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

7.02 Mod 2464 : wording improvement 2.03 Addition of landing distances associated to 5.04 increased 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 – 2.05 5.02 – 5.04 – 7.00

(4)

PAGE :

001 --AFM

0

02

2

DEC 92 MAR 93 JUL 93 OCT 93 DEC 93 FEB 94 APR 94 R NOV 94 JAN 95 24 JAN 95 MAR 95

AIRPLANE FLIGHT MANUAL

R . T . R .

DGAC

APPROVED

MAR 95

NOV 92 Introduction of models 211--212 2.00 -- 2.01

2.02 -- 2.03 2.04 -- 2.05 -- 3.02 3.03 -- 3.04 -- 3.06 4.03 -- 5.02 -- 5.04 6.01 -- 6.02 -- 6.03 6.04 -- 6.05 -- 6.06 7.01 -- 7.02

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 2.04

temporary limitation

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

DEC 93 Introduction of Mod 3849 (MZ FW increase) 2.02

Single DC GEN electrical limitation 2.05

Acceptable 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) 7.02

Introduction 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 -- 3.04} Enforcement 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 2.06

conditions

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 -- 5.02 MAN IGN for aircraft fitted with automatic 7.02 relight)

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

MAR 95 Improvement of Mod 3952 (GPS Bendix/King 2.05

(5)

PAGE :

001 --AFM

0

02

3

FEB 99

R

AIRPLANE FLIGHT MANUAL

R . T . R .

DGAC

APPROVED

FEB 99

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

JUN 95 Improvement of procedures 2.01 -- 2.06 -- 3.04

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

change)

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 -- 7.01

7.02 15 SEP 95 Introduction of Operations on Narrow runways 7.02

Mod 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 7.01

beyond 2%)

DEC 97 Improvement of Missed Approach procedure 3.05

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

APR 98 Introduction of Mod 4890 : 2.05

GPS KLN90B/BRNAV

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

PEC FAULT procedure improvement 5.04

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

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

(6)

PAGE :

001 --AFM

0

02

4 AIRPLANE FLIGHT MANUAL

R . T . R .

EASA

APPROVED AUG 07

MAR 01 Introduction of Mod 8259 : 2.05 -- 7.01

TCAS Collins on King avionics

FEB 03 Introduction of modifications 5377+5434 : 7.01

Cockpit Door Locking System for Models 102--202--212

OCT 03 Introduction of modifications 5377+8333 : 7.01

Cockpit Door Locking System for Models 101--201--211

and amendment of Cockpit Door Jammed procedure for all models

MAR06 Introduction of modification 5561 : 5.04 -- 6.05

Messier--Bugatti Wheels and Brakes

SEP 06 FUEL Feeding Limitations Harmonization 2.04

EMER DESCENT procedure amendment 4.05

(7)

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

(8)

(9)

(10)

(11)

(12)

PAGE :

001

AUG 07

--AFM

0

05

5

EASA APPROVED

AIRPLANE FLIGHT MANUAL

L . N . R .

LIST OF NORMAL REVISIONS

N0

REV INSERTEDDATE EASA APPROVED

19 JUL 05 EASA A.A. 01029

20 JUL 06 EASA A.A. 01205

(13)

PAGE :

001

FEB 91

–

AFM

0

06

DATE REASON FOR NORMAL REVISION CHAP INVOLVED

1 AIRPLANE FLIGHT MANUAL

R . N . R .

DGAC

APPROVED

DEC 89 Cancellation of the temporary revision of Oct 89

Introduction of modification 2495 2.04 Introduction of modification 2464 2.03 Introduction of auxiliary aft cargo 4.03 smoke procedure (Mod : 2059)

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

Modification of the “pitch disconnect” 5.04 – 7.02 procedure

MAY 90 Introduction of mod 2456 2.05

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

Modification of the OXYGEN LO PR procedure 5.04 Flight in icing conditions. Effect on approach 6.06 climb gradient weight. Graph modification.

Introduction of the brake energy limitation for 7.02 dispatch flaps 00

Introduction of the dispatch with one AFU

inoperative 7.02

Introduction of the dispatch with ATPCS OFF 7.02 Introduction of the supplement “Ferry flight with

pitch elevators disconnected” 7.02 FEB 91 Environmental correct extension (T/O and

landing) 2.03

Explanations or figures improved 4.03 – 7.01 – 6.02 2.04 – 1.02 – 2.02

(14)

06

0 PAGE :

MAY 92

–

AFM

2

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

001

FEB 91 Procedure changes 2.04 – 2.05

Introduction 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 – 0.05 and N0 6, JUL91) 3.00 – 3.06 – 4.00 4.03 – 5.02 – 5.04 6.02 – 7.00 – 7.01 7.02 Procedure improvement 4.03 – 4.05 – 5.02 7.02 – 5.04 Lay out and wording 1.02 – 2.01 – 2.05

5.04 – 6.02 – 5.02 6.03 – 6.06 – 4.04

5.04 – 7.00 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 – 3.00 3.06 – 4.00 – 4.03 6.00 – 7.00 – 7.01 7.02 Procedure improvement 2.04 – 3.02 – 3.05 4.03 – 5.02 – 5.03 5.04 – 7.01 – 7.02 Graphes improvement 2.02 – 6.01 – 6.02 6.03 – 6.04 – 6.05 6.06 – 7.01 – 7.02

(15)

06

0 PAGE :

001

FEB 94

–

AFM

3

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED MAY 92 Yellow pages to be turned to white 2.01 – 2.05 – 4.03

5.02 – 5.04– 7.01 7.02 Lay out and wording 1.02 – 5.04 – 6.01

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

2.05 – 3.00 – 4.00 7.00 APR 93 Yellow pages to be turned to white 2.00 – 2.01 – 2.02

2.03 – 2.04 – 2.05 3.02 – 3.03 – 3.04 3.06 – 4.03 – 5.02 5.04 – 6.01 – 6.02 6.03 – 6.04 – 6.05 6.06 – 7.01 – 7.02 Pages to be deleted 2.03

Modification of TCAS number 2.00 – 2.05 – 5.02 5.04 – 7.00 – 7.01

7.02 Procedure improvement 2.04 – 3.04 – 3.05

4.05 – 5.02 – 5.03 5.04 – 7.01 – 7.02 Wording and lay out improvement 1.02 – 2.01 – 2.04 6.01 – 6.02 – 6.03 6.05 – 6.06 – 7.01 FEB 94 Yellow pages to be turned to white 2.02 – 2.04 – 2.05 7.00 – 7.01 – 7.02 Pages to be deleted 2.04 – 6.01 247F propeller retrofit 2.04 – 6.03 – 6.04 6.05 – 6.06 – 7.01 Procedure improvement 2.04 –3.04 – 3.07 5.02 – 5.04 – 6.05 7.02 Wording and lay out improvement 1.02 – 2.00 – 2.06

3.04 – 5.01 – 5.04 6.00 – 6.03 – 6.04 7.00 – 7.01 – 7.02 Graph improvement 6.03 – 6.05 – 6.06

(16)

06

0 PAGE :

001

OCT 96

–

AFM

4 AIRPLANE FLIGHT MANUAL

R . N . R .

DGAC

APPROVED

DATE REASON FOR NORMAL REVISION CHAP INVOLVED AUG 95 Yellow pages to be turned to white 1.02 – 2.00 – 2.01

2.05 – 2.06 – 3.00 3.03 – 3.04 – 3.05 4.00 – 4.02 – 4.04 4.05 – 5.00 – 5.02 5.04 – 7.02 Pages to be deleted 1.02 – 2.00 – 2.01 2.05 – 2.06 – 3.04 4.00 – 5.00 – 5.04 7.02 Procedure improvement 2.04 – 3.04 – 3.05 4.04 – 5.02 – 5.04 7.01 – 7.02 Wording and lay out improvement, typing errors 1.02 – 1.03 – 3.02

4.00 – 4.02 – 5.02 5.03 – 5.04 – 6.02

6.03 Graph improvement or correction 7.02 OCT 96 Yellow pages to be turned to white 2.03 – 2.05 – 3.02

3.03 – 4.05 – 5.00 5.02 – 5.04 – 7.02 Pages to be deleted 1.02 – 2.04 – 3.03 3.04 – 4.05 – 5.02 5.04 – 6.03 – 6.04 6.05 – 6.06 – 7.01 7.02 Procedure improvement 2.04 – 2.05 – 3.01 3.02 – 3.03 – 3.05 5.02 – 5.04 – 7.02 Wording and lay out improvement, typing errors 1.02 – 2.05 – 3.04 4.05 – 5.02 – 5.03 5.04 – 6.01 – 6.03 6.06 – 7.00 – 7.01

7.02 Graph improvement or correction 6.01 – 6.02 – 6.03

6.04 – 6.05 – 6.06 7.01 – 7.02

(17)

06

0 PAGE :

001

SEP 97

–

AFM

5

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED OCT 96 KVS1G extension at take off 6.03

Enforcement of “Consigne de navigabilité no _{2.01 – 2.05 – 2.06} 96 – 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 – 5.02

7.02 Limitation – Procedure Improvement 1.02 – 2.04 – 3.04

4.04 – 4.05 – 5.04 6.02 – 7.02 Wording and layout improvement, typing errors 3.05 – 6.00 – 6.01

6.03 Graph improvement or correction 6.01 – 6.03 – 6.05

7.01 Part 2.05 presentation improvement 2.00 – 2.05 Part 5.02 presentation improvement 5.02 Container transportation presentation improvement 2.02 – 3.00 –3.06

4.00 – 4.03 – 7.02 Mod 4295 introduction – Mod 4111 anti–mod 3.00 – 3.03 – 3.04 3.05 – 4.02 – 4.05

5.02 – 7.02 Mod 4654 introduction – Installation of 2.05 HT1000 GNSS

(18)

06

0 PAGE :

001

SEP 99

–

AFM

6

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED SEP 98 Yellow pages to be turned to white 2.05 – 3.05 – 4.03

5.04

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 7.02 inoperative

Graph improvement or correction 6.06 – 7.01 Introduction of wet and contaminated runways 7.03 advisory materials

Wording and layout improvement, typing errors 1.02 – 1.03 – 2.05 3.07 – 5.04 – 6.03

7.00 – 7.02 MAY 99 Severe Icing: TR 37 to be turned to white 2.06 – 3.04 – 4.05 SEP 99 TR36 to be turned to white 2.05

Introduction of Mod 4511 (New look for 3.06 – 4.03 – 7.02 transport container)

Introduction of Mod 8233 (Power plant) 7.01

Engine limitation change 2.04

Procedures improvement 2.05 – 3.06 – 4.05 5.02 – 5.04 – 7.01 Effect of Mod 4371 (Electronic propeller control 7.03 regulation) on wet and contaminated runways

performances.

V1 limited by VMCG on wet and contaminated 7.03 runways

Wording and layout , typing errors 1.02 – 4.04 – 5.04 6.03 – 6.06 – 7.00 7.00 – 7.02 – 7.03

(19)

06

0 PAGE :

001

JUL 02

–

AFM

7

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED SEP 00 Introduction of Mod 5176 : GNSS, 2.05

Load 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 – 3.05

4.05 – 7.02

Graph improvement 2.02

Wording and layout improvement 1.01 – 4.00 –5.04

Typing 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 7.01.05 as 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 – 2.05

MK VIII 3.00 – 3.07 – 4.05

Use of rudder in case of large sideslip angles 2.03 Procedure improvement : at normal landing with 3.05 PW124 with electronic regulation it is not

necessary to have NP

≥

86%

(20)

06

0 PAGE :

001

SEP 03

–

AFM

8

DGAC APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED 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 4.03

DC SVCE & UTLY BUS ... OFF item

Severe Icing Procedure Improvement 4.05 FWD and AFT SMK Procedures Improvement 4.03

for cargo version

Steep Slope Approach prohibited for : 4.05 – 5.04 Severe 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 7.02.07 dispatch ONE EEC OFF : reduce both TQ

before PWR MGT on CLB for engines with electronic regulation

LBA supplement creation 7.04

(21)

06

0 PAGE :

001

JUL 05

–

AFM

9

EASA APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

DATE REASON FOR NORMAL REVISION CHAP INVOLVED JUL 04 Yellow pages to be turned white

TR40 : Cockpit Door Security System ST2 7.01 Securized Cockpit Door Jammed Procedure 7.01 improvement

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 : 2.04 to ensure adequate relight

Steep Slope Approach :

≥

4.5_ (not

>

) 5.04 – 7.00 – 7.01 Introduction of modification 5465 7.01 New 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

(22)

06

0 PAGE :

001

AUG 07

--AFM

EASA

10

APPROVED

AIRPLANE FLIGHT MANUAL

R . N . R .

JUL 06 Use of Jet B is prohibited 2.04

Cockpit Checks Preparation Trims’ Title 3.00

Introduction of modification 5561 : 6.05

Messier--Bugatti Wheels and Brakes

TCAS new wording for Traffic Advisory case 7.01 Introduction of modification 5567 : MPC 7.00 -- 7.01 Multi Purpose Computer -- APM :

Aircraft Performance Monitoring

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

Introduction of modification 5506 : 7.00 -- 7.01 ACARS

AUG 07 Blanking of TR24:

FUEL Feeding Limitations Harmonization 2.04

EMER DESCENT procedure amendment 4.05

ONE 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 -- 7.02 Numbering of Appendices and Supplements

Introduction of modification 8442 : MPC 7.01.15

New High Latitudes Operations 7.01.18

(23)

0-07 page 1-082

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

(24)

0-07 page 2-082

ATR

72

S.N.N.P.

... 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

(25)

0-07 page 3-082

ATR

72

S.N.N.P.

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

NEW PAGES ARE LISTED IN LIST OF EFFECTIVE NORMAL PAGES ( LENP)

(26)

0-08 page 1-082

ATR

72

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. ALL R 0 04 001 082 AUG 07 L.E.T.P. TQ ALL 0 05 001 001 MAY 92 L.N.R. ALL 0 05 002 001 SEP 97 L.N.R. ALL 0 05 003 001 SEP 01 L.N.R. ALL 0 05 004 001 JUL 04 L.N.R. ALL R 0 05 005 001 AUG 07 L.N.R. ALL 0 06 001 001 FEB 91 R.N.R. 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. ALL

Turn

TQ

(27)

0-08 page 2-082

0-09 page 1-082

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

(45)

0-09 page 2-082

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

(46)

0-10 page 1-082

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

(47)

00

1 GENERAL

PAGE :

001

SEP 89 Eng : ALL DGAC APPROVED

–

Model : ALL Mod : –

AFM

1

1 . 00 – CONTENTS 1 . 01 – INTRODUCTION 1 . 02 – PARTICULAR EXPLANATIONS DEFINITION OF WORDING UNIT CONVERSION

GLOSSARY OF STANDARD NOMENCLATURE

(48)

01 INTRODUCTION

1 GENERAL

PAGE :

001

EASA APPROVED

–

AFM

1

SEP 89 JUL 05 R R SEP 00

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

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

ORGANIZATION OF THE MANUAL

The AFM contents are divided into seven chapters : 1 – General

2 – Limitations 3 – Normal procedures 4 – Emergency procedures 5 – Procedures following failure 6 – Performance

7 – Appendices and supplements

Preliminary pages include all approval references and define the updating status of the list of effective pages :

– for the airlines manual

– for the envelope manual (covering all the airlines manuals). The pages are numbered per chapter and section

Applicability of each page is identifed at the bottom of the page by : – engine

– model

– modification number (if any)

NOTE : Unless otherwise specified at the bottom of the page its content is valid for all models mentioned on the heading page (0.00 page 1).

(49)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001

SEP 98 DGAC APPROVED

–

AFM

1

_{SEP 89} R R 1 . 02 . 01 – DEFINITION OF WORDING

Note : An operating procedure, technique etc... considered essential to emphasize

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

result in injury or loss of life if not carefully followed.

1 . 02 . 02 – UNIT CONVERSION

Weight 1 kg = 2.2046 lb 1 lb = 0.4536 kg Length – Altitude

Distance 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

(50)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

2 R

MAY 92

APR 93

1 . 02 . 03 – GLOSSARY OF STANDARD NOMENCLATURE

AAS Anti–icing Advisory System

A/C Aircraft

AC Alternating Current

ACW Alternating Current Wild Frequency ADC Air Data Computer

ADF Automatic Direction Finding ADI Attitude Director Indicator ADU Advisory Display Unit

AFCS Automatic Flight Control System A/FEATH Automatic Feathering

AFM Airplane Flight Manual

AFT Rear Part

AFU Auto Feathering Unit AGL Above Ground Level

AH Ampere – Hours

AHRS Attitude and Heading Reference System AHRU Attitude and Heading Reference Unit AIR COND Air Conditioning

ALT Altitude

ANN Annunciator

AP 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 Unit B–RNAV Basic Area Navigation

BRK Brake

BRT Bright

BTC Bus Tie Contactor BTR Bus Tie Relay

(51)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

3

R AUG 91 SEP 97 R

BXR Battery Transfer Relay

CAB Cabin

CAP Crew Alerting Panel

CAPT Captain

CAS Calibrated Air Speed

CAT Category

C/B Circuit Breaker

CCAS Centralized Crew Alerting System CDI Course Deviation Indicator CFC Constant Frequency Contactor

CG Center of Gravity

CHC Charge Contactor

CH Charge

CHG Charger

CL Condition Lever

CLA Condition Lever Angle

CLB Climb CLR Clear CM Crew Member COM Communication COMPT Compartment CONFIG Configuration CONT Continuous CORRECT Correction

CPL Auto Pilot Coupling

CR Cruise

CRC Continuous Repetitive Chime

CRS Course

CRT Cathodic ray tube

CRZ Cruise

CTL Control

CVR Cockpit Voice Recorder

dB Decibel

DC Direct Current

DEC Declination Decrease

DELTA P Differential Pressure

DEV Deviation

DFDR Digital Flight Data Recorder

DG.C Celsius Degree

DGR Degraded

DH Decision Height

DIFF Differential

DIM Light Dimmer

DIST Distance

(52)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001

JUL 04 DGAC APPROVED

–

AFM

4

SEP 89 R MAY 95 AUG 95 OCT 96 DN Down DSPL Display

EADI Electronic Attitude Director Indicator EEC Electronic Engine Control

EFIS Electronic Flight Instrument System EGHR External Ground Handling Relay EHSI Electronic Horizontal Situation Indicator

ELEC Electrical

ELV Elevation

EMER Emergency

ENG Engine

EPC External Power Contactor

ET Elapsed Time

ETOPS Extended Twin Operations

EXT Exterior, External

EXC External Power/Service Bus Contactor

FAIL Failed, Failure

FD Flight Director

FDAU Flight Data Acquisition Unit FDEP Flight Data Entry Panel FEATH or FTR Feather, Feathering

FF Fuel Flow

FI Flight Idle

FL Flight Level

FLT Flight

F/O First Officier

FQI Fuel Quantity Indication

FT, ft Foot, Feet FU Fuel Used FWD Forward GA Go around GAL Galley GC Generator Contactor

GCU Generator Control Unit

GD Gear Down

GEN Generator

GI Ground Idle

GMT Greenwitch Mean Time

GND Ground

GPS Global Positioning System

GPU Ground Power Unit

(E)GPWS (Enhanced) Ground Proximity Warning System

G/S Glide Slope

(53)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

5

SEP 89 R R SEP 97 R HD Head Down HDG Heading HF High Frequency HI High HLD Hold

HMU Hydromechanical Unit

HP High Pressure

HPa Hecto Pascal

HSI Horizontal Situation Indicator

HYD Hydraulic

IAF Initial Approach Fix

IAS Indicated Air Speed

IDT Ident

IFR Instrument Flight Rules ILS Instrument Landing System

INC Increase

IND Indicator

IN, in Inch(es)

IN/HG Inches of Mercury

INHI Inhibit

INST Instrument

INT Interphone

INV Inverter

ISOL Isolation

ITT Inter Turbine Temperature

Kg, KG Kilogramme

KHZ Kilo – Hertz

KT, kt Knot

LB Pound

LBA Lowest Blade Angle

LDG Landing

L/G Landing Gear

LH Left Hand

LIM Limitation

L–NAV Lateral Navigation

LO Low LOC Localiser LO PR Low Pressure LT Light LVL Level M, m Meter

MAC Mean Aerodynamic Chord

MAN Manual

MAP Ground Mapping

(54)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

6

SEP 89 R AUG 95 SEP 99

MBE Maximum Brake Energy

MC Master Caution

MCT Maximum Continuous

MEA Minimum en Route Altitude MFC Multi Function Computer

MGT Management MHZ Megahertz MIC Microphone MIN Minimum MKR Marker MM Millimeter

MMO Maximum Operating Mach

mn Minute

MW Master Warning

MTOW Maximum Take–off Weight

NAV Navigation

NDB Non Directional Bearing

NEG Negative

NH High Pressure Spool Rotation Speed

NIL Nothing, No object

NM Nautical Mile

NORM Normal

NP Propeller Rotation Speed

N/W Nose Wheel

OAT Outside Air Temperature OBS Omni Bearing Selector OCL Obstacle Clearance Limit

OUTB Outboard OVBD Overboard OVHT Overheat OVRD Override OXY Oxygen PA Passenger Adress PAX Passenger PB Push Button

PCU Propeller control Unit PEC Propeller electronic control

PF Pilot Flying

PIT Pitch

PL Power Lever

PLA Power Lever Angle

PNF Pilot Non Flying

PNL Panel

POS Position

P–RNAV Precision Area Navigation

PR Pressure

(55)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

7

SEP 89 R R AUG 95 SEP 98 PRKG Parking PROP Propeller

PSI Pound per Square Inch

PT Point

PTT Push to Talk, Push to Test

PWR Power

QFU Runway Heading

QTY Quantity

RA Radio Altitude

RAD/INT Radio/Interphone

RAIM Receiver Autonomous Integrity Monitoring RCAU Remote Control Audio Unit

RCDR Recorder

RCL Recall

RCU Rudder releasable Centering Unit

RECIRC Recirculation

REF Reference

REV Reverse

RH Right Hand

RMI Radio Magnetic Indicator RPM Revolution Per Minute

RQD Required

RTO Reserve Take–off

RUD Rudder

RWY Runway

SAT Static Air Temperature

SBY Stand By

SC Single Chime, Starter Contactor

SEL Selector

SGL Single

SGU Symbol Generator Unit SID Standard Instrument Departure S/O or SO Shut Off

SPD Speed

SSR Service Bus Select Relay

STAB Stabilizer

STAR Standard Arrival

STBY Stand By

STR Service Bus Transfer Relay

STRG Steering

SVCE Service

SW Switch

SYS System

TAD Terrain Awareness Display

TAS True Air Speed

TAT Total Air Temperature

TAWS Terrain Awareness Warning System

(56)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

8

R MAY 92 SEP 98

TCAS Traffic alert and collision avoidance system TCAS RA TCAS resolution advisory

TCAS TA TCAS traffic advisory TCF Terrain Clearance Floor TCS Touch Control Steering

TEMP Temperature

TGT Target

TK Tank

TLU Travel Limitation Unit

TO Take–off

TOD Take–off Distance

TOR Take–off Run

TOW Take–off Weight

TQ Torque

UBC Utility Bus Contactor

U/F Underfloor

UHF Ultra High Frequency UNDV Undervoltage

UNLK Unlock

UTLY Utility

VA Design Maneuvering Speed VAPP Approach Speed

VC Calibrated Airspeed VENT Ventilation

VERT Vertical

VFE Flaps Extended Speed VFR Visual Flight Rules VFTO Final Take–off Speed VGA Go around speed VHF Very High Frequency

VLE Landing Gear Extended Speed VLO Landing Gear Operating Speed VLOF Lift Off Speed

VMCA Minimum Control Speed in flight VMCG Minimum Control Speed on Ground

VMCL Minimum Control Speed in Flight (Landing config). VMO Maximum Operating Speed

VMU Minimum Unstick Speed VOR VHF Omni Directional Range

VR Rotation Speed

VRA Rough Air Speed VS1G Stall Speed

VS Vertical Speed

VSI Vertical Speed Indicator

VU Visual Unit

(57)

02 PARTICULAR EXPLANATIONS

1 GENERAL

PAGE :

001 –

AFM

9

R FEB 94

XFEED Cross Feed

XFR Transfer

YD Yaw Damper

Z Altitude

ZA Aircraft Altitude

ZCTH Theoretical Cabin Altitude

ZFW Zero Fuel Weight

ZP Pressure Altitude

ZPI Indicated Pressure Altitude ZRA Radio Altimeter Altitude

(58)

03 3 VIEW DRAWING

1 GENERAL

PAGE :

001 –

AFM

1

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 REFERENCE

CHORD LEADING EDGE . . . 13.604 m ( 535.591 in)

HORIZONTAL TAIL

REFERENCE AREA . . . 11.73 m2 ( 18182 in2) REFERENCE CHORD LH . . . 1.636 m ( 64.409 in) ASPECT RATIO . . . 4.555 DISTANCE FROM 25 % OF LA

TO 25 % OF LH . . . 13.654 m ( 537.559 in)

VERTICAL TAIL

REFERENCE AREA _{. . .}12.48 m2 ( 19344 in2) REF CHORD LV . . . 2.851 m ( 112.244 in) ASPECT RATIO . . . 1.6 DISTANCE FROM 25 % OF LA

(59)

00

2 LIMITATIONS

PAGE :

001 –

AFM

1

NOV 92 APR 93 FEB 94 APR 94 R JAN 95 AUG 95 SEP 97 2 . 00 – CONTENTS 2 . 01 – GENERAL INTRODUCTION KINDS OF OPERATION MINIMUM FLIGHT CREW

PERFORMANCE CONFIGURATION MAXIMUM OPERATING ALTITUDE MANEUVERING LIMIT LOAD FACTORS CONFIGURATION DEVIATION LIST NOISE CHARACTERISTICS

MAXIMUM NUMBER OF PASSENGER SEATS

2 . 02 – WEIGHT AND LOADING

WEIGHTS

CENTER OF GRAVITY ENVELOPE LOADING

2 . 03 – AIRSPEED AND OPERATIONAL PARAMETERS

AIRSPEEDS OPERATIONAL PARAMETERS 2 . 04 – POWER PLANT ENGINES PROPELLERS OIL SYSTEM STARTER FUEL SYSTEM 2 . 05 – SYSTEMS AIR - PRESSURIZATION HYDRAULIC SYSTEM LANDING GEAR FLAPS AFCS INSTRUMENTS MARKING CARGO DOOR OPERATION MFC COMMUNICATIONS ELECTRICAL TCAS GPS EGPWS 2 . 06 – ICING CONDITIONS

(60)

01 GENERAL

2 LIMITATIONS

PAGE :

001

OCT 96 Eng : ALL DGAC APPROVED

–

Model : ALL Mod : –

AFM

1

MAY 92 APR 93 JUN 95 AUG 95 R 2 . 01 . 01 – INTRODUCTION

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

2 . 01 . 02 – KINDS OF OPERATION

The airplane is certified in the Transport Category, JAR 25 and ICAO annex 16 for day and night operations, in the following conditions when the appropriate equipment and instruments required by the airworthiness and operating regulations are approved, installed and in an operable condition :

- VFR and IFR

- Flight in icing conditions.

- Reverse thrust taxi (single or twin engine)

2 . 01 . 03 – MINIMUM FLIGHT CREW

2 pilots

2 . 01 . 04 – PERFORMANCE CONFIGURATION

Refer to 6.01.03 for airplane configuration associated with certified performances.

2 . 01 . 05 – MAXIMUM OPERATING ALTITUDE

25000 ft

2 . 01 . 06 – MANEUVERING LIMIT LOAD FACTORS

Gear and flaps retracted : + 2.5 to – 1 g Gear and/or flaps extended : + 2 to 0 g

2 . 01 . 07 – CONFIGURATION DEVIATION LIST

Refer to 7.01.02

2 . 01 . 08 – NOISE CHARACTERISTICS

The aircraft meets the requirements of ICAO annex 16, Chapter 3 with no weight restriction.

Refer to noise characteristics in Appendix 7.01.01 of this manual for noise levels.

2 . 01 . 09 – MAXIMUM NUMBER OF PASSENGER SEATS

(61)

02 WEIGHT AND LOADING

2 LIMITATIONS

PAGE :

002

APR 93 Eng : ALL DGAC APPROVED

–

Model : 201 – 202 – 211 – 212 Mod : –

AFM

1

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 by performance requirements related to the following (see chapter 6) :

– climb performance (first and second segment, final take–off and en route, approach and landing climb)

– available runway length (take–off and landing) – tyre limit speed

– brake energy limit, observe BRK TEMP light extinguished for take–off

– obstacle clearance (take–off and en route) – en route and landing weight

(62)

02 WEIGHT AND LOADING

2 LIMITATIONS

PAGE :

070

FEB 94 Eng : ALL DGAC APPROVED

–

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

AFM

1

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

SEP 89 R 2 . 03 . 01 – AIRSPEEDS

•MAXIMUM OPERATING SPEED VMO / MMO

This limit must not be intentionally exceeded in any flight regime VMO = 250 kt CAS MMO = 0.55

•MAXIMUM DESIGN MANEUVERING SPEED VA

Full application of roll and yaw controls, as well as maneuvers that involve angles of attack near the stall should be confined to speeds below VA.

VA = 175 kt CAS

CAUTION : Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed.

•MAXIMUM FLAPS EXTENDED OR OPERATING SPEEDS VFE FLAPS 15 185 kt CAS

FLAPS 30 150 kt CAS

•MAXIMUM LANDING GEAR EXTENDED OR OPERATING SPEEDS VLE = 185 kt CAS

VLO lowering = 170 kt CAS retracting = 160 kt CAS

(66)

03 AIRSPEED AND OPERATIONAL

PARAMETERS

2 LIMITATIONS

PAGE :

230 –

Model : ALL Mod : 3037+ (8044 or 3522)

AFM

2

R NOV 92 2 . 03 . 02 – OPERATIONAL PARAMETERS ENVIRONMENTAL ENVELOPE

Note : Refer to 2.04.05 for fuel temperature limitation. TAKE–OFF AND LANDING

– Tail wind limit : 15 kt

(67)

04 POWER PLANT

2 LIMITATIONS

PAGE :

120

SEP 00 Eng : PW124 DGAC APPROVED

–

Mod : 2735

AFM

1

R NOV 92 APR 93 FEB 94 AUG 95 SEP 99

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

Beyond these limits refer to maintenance manual

POWER SETTING TIME LIMIT TQ (%) ITT (o_C) NH_(%) _(%)NL _(%)NP _PRESSOIL (PSI) OIL TEMP (o_C) RESERVE TAKE OFF 10 mn (4) 106.3 (5) 800 102.7 104 101 55 to 65 0 to 125 (3) TAKE OFF 5 mn 90 (1) 101 101.7 101 55 to 65 0 to 125 (3) MAXIMUM CONTINUOUS NONE 102.5 800 102.7 104 101 55 to 65 0 to 125 (3) GROUND IDLE 66 mini 40 mini –40 to 125 (3) HOTEL MODE 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 115o_{C (120}o_{C in hotel mode) is authorized without time}

limitation.

20 mn are authorized between 115o_{C (120}o_{C in hotel mode) and 125}o_C. NOTE : Oil temperature must be maintained above 45oC to ensure intake strut

de–icing.

Oil temperature must be maintained above 71o_{C 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 is not permitted.

(68)

04 POWER PLANT

2 LIMITATIONS

PAGE :

001 –

AFM

2

TAKE OFF

(69)

04 POWER PLANT

2 LIMITATIONS

PAGE :

001 –

AFM

3

NOV 92 APR 93 R AUG 95 OCT 96 2 . 04 . 02 – PROPELLERS

TWO HAMILTON STANDARD 14 SF 11

GROUND OPERATION

H Avoid static operation between 41 % and 65 % Np

H Avoid use of feather position above 47 % TQ.

H Engine run up must be performed into the wind.

H Do not exceed 91.7 % TQ below 30 kt except for transients of engine run up at start of take off and for brief service checks of 2 minutes or less each.

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

GROUND OR FLIGHT OPERATION

H If a propeller is involved in an overspeed or in an engine overtorque refer to the propeller maintenance manual.

FLIGHT OPERATION

H ATR airplanes are protected against a positioning of power levers below the flight idle stop in flight by an IDLE GATE device.

It is reminded that any attempt to override this protection is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power.

(70)

04 POWER PLANT

2 LIMITATIONS

PAGE :

001

AUG 07 EASA APPROVED

--AFM

4

APR 93 NOV 92 DEC 93 FEB 94 AUG 95 JUL 04 JUL 05 R JUL 06 SEP 06 R R R 2 . 04 . 03 -- OIL SYSTEM SPECIFICATION

Refer to specification PWA 521 type II

2 . 04 . 04 -- STARTER

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

2 . 04 . 05 -- FUEL SYSTEM

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 taken into account to ensure adequate relight :

--34o_{C for fuel types JET A, JET A1 and RT, TS1.} --26o_{C for fuel type JP5.}

• Maximum temperature :

57o_{C for fuel types JET A, JET A1, JP 5 and RT, TS1.} REFUELING

Maximum pressure 3.5 bars (50 PSI) USABLE FUEL

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

NOTE :Fuel remaining in the tanks when quantity indicators show zero is not usable in flight.

UNBALANCE

Maximum fuel unbalance : 730 kg (1609 lbs) FEEDING

• Each electrical pump is able to supply one engine in the whole flight envelope.

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

(71)

05 SYSTEMS

2 LIMITATIONS

PAGE :

001 –

AFM

1

APR 93 NOV 92 DEC 93 FEB 94 NOV 94 JAN 95 AUG 95 R OCT 96 SEP 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 VALVE

full 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 GEAR

Towing with TOWBARLESS system is prohibited.

Do not perform pivoting (sharp turns) upon a landing gear with fully braked wheels except in case of emergency.

2 . 05 . 04 – FLAPS

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

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

– Minimum height for autopilot engagement on take off : 100 ft

– NAV mode for VOR approach, using either autopilot or flight director is authorized only if :

– a co–located DME is available, and – DME HOLD is not selected

– Minimum height for use of either autopilot or flight director :

– Except during take off or executing an approach : 1000 ft – VS or IAS mode during approach : 160 ft

– CAT 1 APP mode : 160 ft

Refer to 7.01.03 for CAT II operation (if applicable).

2 . 05 . 06 – INSTRUMENTS MARKING

Red arc or radial line : minimum and maximum limits Yellow arc : caution area