FCOM ATR42-500

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ATR 42 Model : 400/500

LIST OF NORMAL REVISIONS

FLIGHT CREW OPERATING MANUAL

L . N . R .P 1

DEC 10

001

0.05.00

N° REV DATE IN INSERTION DATE NAME

00 MAY 95 PRELIMINARY

01 DEC 95 TOTALE

02 MAR 96

03 NOV 96

04 MAY 97

05 NOV 97

06 MAY 98

07 NOV 98

08 NOV 99

09 NOV 00

10 NOV 01

11 NOV 02

12 DEC 03

13 DEC 04

14 DEC 05

15 DEC 06

16 DEC 07

17 APR 08

18 OCT 08

19 DEC 09

20 DEC 10

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ATR 42 Model : 400/500

REASON OF NORMAL REVISION


R . N . R .P 11

DEC 05

001

0.06.00

DATE REASON FOR ISSUE CHAP INVOLVED

DEC 05 Yellow pages to be turned to white

- ATPCS Test 2.03.06 -- 2.03.19

-- OEB 3.12

* NEW MODIFICATIONS

-- MPC Multi Purpose Computer 2.02.21

-- ACARS Aircraft Communication Addressing and Reporting System 2.02.22

* ACTION ON PART 0

-- New layout for manual presentation 0.40.00

* ACTION ON PART I

-- Seat Position Sight Gauge 1.00.20

-- MFC Maintenance Memory Reading : see Job Instruction Card 1.01.10

-- Stick Pusher/Shaker YES TEST Improvement 1.02.10

-- GNSS2 (if installed) electrical supply is on CD Bus 1 1.15.60

* ACTION ON PART II

-- Updating for JP4 prohibiited 2.01.04

-- Braking Failure on one Side Procedure Introduction 2.05.00 -- 2.05.07

-- ELEV JAM procedure : same as in QRH 2.05.06

* ACTION ON PART III

-- New layout for OEB chapter and OEB updating 3.12

* WORDING 2.03.04 -- 3.10.01

* TYPING CORRECTION 1.01.10 -- 1.16.402.05.00

AA

ATR 42 Model : 400/500

REASON OF THE REVISION


R . N . R .P 12

DEC 06

001

0.06.00

DATE REASON FOR ISSUE (MAJOR EVENTS) CHAP INVOLVED


- VHF and HF communication systems- FUEL LO LVL Procedure Updating -- MOD 4650

1.05.102.05.03

* NEW MODIFICATIONS

-- MOD 4650 : Add LOW Level Detection System 2.05.03

* ACTION ON PART 0

-- None

* ACTION ON PART I

-- Graph Correction for Cabin PRESS Indicator 1.03.40

-- BLUE and GREEN PUMP PWR ACW Electrical Distribution-- TOILET SYS ACW Electrical Distribution

1.06.60

-- EFIS Control Panel : impact of MOD 5506 1.10.30 -- 1.15.60

-- Flight Recorders : impact of MOD 5567 1.10.50

-- Correction multidisc brakes 1.14.40

-- HT1000 Controls : impact of MOD 5506 1.15.60

* ACTION ON PART II

-- Use of Jet B is prohibited 2.01.04

-- TCAS TA wording improvement 2.01.06

-- 2.02 Part Content Updating 2.02.00

-- AHRS Caution linked with attitudes and heading errors 2.02.14

-- AHRS and Weather Radar Layout 2.02.14

-- High Latitudes Operations new section 2.02.19

-- EMERGENCY DESCENT procedure Improvement 2.04.05

-- DITCHING and FORCED LANDING procedures Improvement 2.04.05

-- MFC Module Equipment List : see QRH 2.05.10

-- ADC DISAGREEMENT procedure editorial improvement 2.05.12


-- Typing error 3.03.02

-- Holding : Flight Level 15 Correction 3.06.02

AA

ATR 42 Model : 400/500



R . N . R .P 13

DEC 07

001

0.06.00



- Cockpit Voice Recorder MOD 5736 3.12.20 & 3.12.29

* NEW MODIFICATIONS

-- MOD 5840 : Completion for 100% Oxygen installation (50pax)

-- MOD 5736 : Cockpit voice recorder

2.01.05

3.12.29

* ACTION ON PART 0

-- None

* ACTION ON PART I

-- Hydraulic System -- General : indent correction for green system 1.12.10

-- AIRFRAME AIR BLEED FAULT light activation time correction 1.13.30

* ACTION ON PART II

-- Operational parameters improvements 2.01.03

-- Fuel Feeding wording correction 2.01.04

-- TCAS title and content update 2.01.062.02.15

-- Flight characteristics content : narrow runways and steep slopeapproach informations update

2.02.12

-- MPC wording and graph improvement 2.02.21

-- Part 2.04 EMERGENCY PROCEDURES improvement 2.04.002.04.022.04.032.04.042.04.05

-- Loading and fuel chart -- WBM link update for cargo loading 2.06.02


-- Special operations : harmonization with supplements andappendix located in AFM. Links towards AFM added

3.11.003.11.12 to .19

AA

ATR 42 Model : 400/500



R . N . R .P 14

APR 08

001

0.06.00


APR 08 Yellow pages to be turned to white

- FWD SMK and AFT SMK procedure wording correction 2.04.03

* NEW MODIFICATIONS

-- New engine PW127M

-- GNSS HT1000 RNAV, MOD 5768

Whole Manual2.01.07

* ACTION ON PART 0

-- None

* ACTION ON PART I

-- None 1.12.10

* ACTION ON PART II

-- Normal procedures re--writing 2.03

-- Procedures following failures re--writing 2.05


-- None except PW127M impact

AA

ATR 42 Model : 400/500



R . N . R .P 15

OCT 08

001

0.06.00


OCT 08

* ACTION ON PART 0-- None-- None

* ACTION ON PART I-- Wording and contents correction / improvements

1.05.101.15.60-- Wording and contents correction / improvements

-- PW127M mention added1.15.601.16.10

* ACTION ON PART II-- RTO and MCT rating comments precisedand Fuel RT and TS1 added

2.01.04-- RTO and MCT rating comments precisedand Fuel RT and TS1 added-- TAWS wording-- Normal Procedures :

2.01.04

2.01.092.03.05-- Normal Procedures :

Exterior inspection action corrections : pitot probes, nav andstrobe lights

2.03.05

-- Procedures following failure :contents pages updatedSINGLE ENG OPERATION :-- precision added for item fuel pump affected sideNO NH DURING START : item added :-- engine start rotary selector for start A or start BABNORMAL ENG PARAMETERS IN FLIGHT : item added :-- PL to be retarded in green sectorPEC FAULT : “Before landing” items reorganizedPROP OVER LIMIT : 101% NP condition according to AFMDC EMER BUS OFF : “use of CM2 instruments in case ofdisagreement “ note addedDC SVCE/UTLY BUS SHED : page reference in commentsparagraph correctionBOTH MAIN HYD PUMPS LOSS :-- FLAPS 35 instead of FLAPS 30Lost equipment list correction in the following procedures :-- DC BUS 1 OFF & DC BUS 2 OFF :-- AC BUS 1 OFF & AC BUS 2 OFF-- ACW BUS 1 OFF & ACW BUS 2 OFF & ACW TOTAL LOSS-- BOTH HYD SYS LOSSTitles correction in the following procedures :-- BOTH HYD SYS LOSS-- DE--/ANTI--ICING ENG FAULTDE--ICING MODE SEL FAULT : wording correction in commentsparagraphAll MFC FAULT procedures amended :-- Module precised on procedure items

2.05.002.05.02

2.05.04

2.05.05

2.05.04

2.05.05

2.05.092.05.09

2.05.14

-- Part 3:Wording correction following translation error.NL Charts graphs updated: runway slope correctionNet celing in normal conditions graph replacement for page 3

3.03.003.03.023.09.02

AA

ATR 42 Model : 400/500



R . N . R .P 16

DEC 09

001

0.06.00


DEC 09 * NEW MODIFICATIONS:-- Mod 6336--6337: Video cabin entertainement system 2.02.21 & 2.02.23

* ACTION ON PART III:--Time values removed, source of confusion for pilots--Wording correction : “...gear NOT down...”--Maximum demonstrated crosswind reviewed-- Volcanic Ash: content description and procedure-- Reverse phases informations added and Operations out of thenotch informations added-- APM procedure wording improvements

1.13.30&2.05.091.15.402.01.032.02.082.02.11

2.02.21notch informations added-- APM procedure wording improvements-- Hot Environment Start procedure--PL1+2 .... to be checked at Ground Idle--APM item to be set and checked before take off, 2enginesrunning--Fuel saving informations added (reduced power setting in cruise)--CCAS alerts non--inhibited added--ENG FLAME OUT AT TAKE OFF: Autofeather item moved

2.02.212.03.062.03.06

2.03.08&2.03.10

2.03.132.04.01&2.05.01

2.04.02--ENG FLAME OUT AT TAKE OFF: Autofeather item moved--Reminder to apply “SMOKE” procedure first added in all relevantsmoke procedures.--AIR COND SMOKE : warning changed to caution--DITCHING and FORCED LANDING : “TAWS” wording--EMERGENCY EVACUATION ON GROUND: dump function tobe used after aircraft stops and wording improvements--New: “RECOVERY AFTER STALL OR ABNORMAL ROLLCONTROL”

2.04.022.04.03

2.04.05

--New: “RECOVERY AFTER STALL OR ABNORMAL ROLLCONTROL”--SINGLE ENG OPER.: “1+2” deleted, and APM turned to OFFadded--ABNORMAL ENG ...IN FLIGHT: wording correction--FIRE LOOP FAULT:Memory item added--ONE EEC and PEC FAULT: noteadded: ACW BTC to bechecked closed to avoid ACW loose on ground--ENG FLAME OUT: memory item extended

2.05.02

--ENG FLAME OUT: memory item extended--ENG OVER LIMIT: note: bleed valve to be selected off to reduceexcessive ITT in flight.--Lost equipment lists reviewed with some corrected alertsconditions--Title changed into DUTCH ROLL TENDENCY / RUDDERCENTERING UNIT FAIL and procedure improved-- EFIS COMP: memory item, procedure improved and comments

2.05.04

2.05.06

2.05.12

* ACTION ON PART III:--Fuel saving information added--Take Off methodology reviewed

3.04.013.03.02&3.03.05

AA



R . N . R .P 17

DEC 10

001

0.06.00


DEC 10 *NEWMODIFICATION(S):-- Mod6477:ColdSoak(--45°). 2.01.03&2.02.20

*ACTIONONPART I-- GlossarycompletedwithCDLS.--Wordingcorrection.-- ELT(EmergencyBeacon)moredetailed.-- Oxygenpressure informationssimplified.-- Steepapppushbutton infoadded.(mod4404+5357)

0.50.001.03.301.05.101.07.201.15.40

* ACTION ON PART II-- Crosswind reviewed.-- CAT 2 informations updated.-- Fuel crossfeed procedure : note updated.-- Wording corrected for de--/anti icing and control columns.

2.01.032.02.042.02.072.02.08

-- Fuel crossfeed procedure : note updated.-- Wording corrected for de--/anti icing and control columns.-- Start--up sequence: informations updated and.-- Push back and Power back operations addedNormal Procedures :--Recorder test informations improved.

2.02.072.02.082.02.11

2.03.06Normal Procedures :--Recorder test informations improved.-- Preliminary cockpit preparation: slight improvements.-- ATPCS test (dynamic and static) informations improved.-- Afterlanding procedure: engine/ATPCS test...

2.03.06

2.03.19

Emergency procedures:-- CCAS alert corrected.-- BOTH ENGINES FLAMEOUT procedure: improvements.-- AIR CONDSMOKE: amber engine caution.-- FWDSMOKE: Smoke preliminary procedure to be reminded in first.-- RECOVERYAFTERSTALLORUNCOMMANDEDROLLCONTROLprocedure reviewed.Following failures procedure:-- CCAS alert corrected.-- ENGNACOVHT : title and wording improvement.-- ABNORMAL ENG PARAMETERS IN FLIGHT: procedure reviewed.-- ONEEEC FAULT: wording correction-- PROPOVER LIMIT: procedure reviewed-- UNCOMMANDED 100%NPONONEOR TWOPROPELLERS;procedure title and content changed instead of “ONEPROPELLERREMAINING AT NP 100%AFTERCLBPOWERSELECTION”-- Page header corrected (variant page)-- TLU FAULT procedure: correction-- ELEVATOR JAM: comments reviewed-- ANTI SKID FAULT: anti skid set to OFF itemadded.-- PACKVALVE FAULT : condition corrected.-- DUCT OVHT: temperature alert correction.-- SMKDET FANSFAULT: procedure title changed to generalize.-- DOORSUNLK IN FLIGHT: wording improvement.-- MFC 2A+2B FAULT: item added for correctio n.

2.04.012.04.022.04.03

2.04.05

2.05.012.05.02

2.05.042.05.06

2.05.072.05.08

2.05.13

2.05.14

* ACTION ON PART III :-- NL chart: graph improved and slightly corrected.--Take Off methodology : wording correction.

3.03.023.03.05

FCOM FLIGHT CREW OPERATING MANUAL 0-08 page 1-062

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N 1 16 00 001 001 DEC 95ALL

N 1 16 10 001 001 OCT 08 500ALL

N 1 16 20 001 001 DEC 95N 1 16 20 002 001 DEC 95 500

ALL

N 1 16 20 003 001 NOV 98 500N 1 16 20 004 001 NOV 99 500

ALL

N 1 16 20 005 001 DEC 95N 1 16 20 006 100 MAY 97 500 MOD 4601

ALL

N 1 16 20 007-008001 DEC 95ALL

N 1 16 20 009-010001 DEC 95 500ALL

N 1 16 20 011-012001 DEC 95 500ALL

N 1 16 20 013-014100 NOV 96 500 MOD 4601ALL

N 1 16 30 001 001 DEC 95N 1 16 30 002 001 NOV 98

ALL

N 1 16 30 003 100 NOV 98 500 MOD 4601N 1 16 30 004 001 NOV 98

ALL

N 1 16 30 005 100 NOV 96 500 MOD 4601N 1 16 30 006 100 NOV 96 500 MOD 4601

ALL

N 1 16 30 007 001 DEC 95N 1 16 30 008 001 DEC 95

ALL

N 1 16 30 009 001 DEC 95N 1 16 30 010 001 DEC 95

ALL

N 1 16 40 001 001 DEC 95 500N 1 16 40 002 001 MAY 98

ALL


ATR42-400/500


DEC 10


Turn EQ

N 1 16 40 003 001 DEC 95 500N 1 16 40 004 001 DEC 05

ALL

N 1 16 40 005 001 DEC 95N 1 16 40 006 001 DEC 95

ALL

N 1 16 40 007 001 NOV 97 500N 1 16 40 008 001 DEC 95 500

ALL

N 1 16 40 009 001 NOV 98 500N 1 16 40 010 001 NOV 97 500

ALL

N 1 16 40 011 001 DEC 95N 1 16 40 012 001 DEC 95

ALL

N 1 16 40 013 001 MAR 96N 1 16 40 014 001 DEC 95

ALL

N 1 16 40 015 100 NOV 96 500 MOD 4601N 1 16 40 016 001 DEC 95

ALL

N 1 16 50 001 001 DEC 95 500N 1 16 50 002 001 DEC 95

ALL

N 1 16 60 001 001 DEC 95N 1 16 60 002 001 DEC 95

ALL

N 1 16 60 003 001 DEC 95N 1 16 60 004 001 DEC 95

ALL

N 2 01 00 001 001 OCT 08ALL

N 2 01 01 001 001 MAY 97N 2 01 01 002 001 NOV 99

ALL

N 2 01 02 001 050 NOV 99 500 MOD 5150ALL

N 2 01 03 001 100 NOV 02 500 MOD 4462N 2 01 03 002 200 MAY 97 500 MOD 4372 +4540

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 01 03 003 001 APR 08 500N 2 01 03 004 001 APR 08 500

ALL

N 2 01 03 005 001 DEC 10 500ALL

N 2 01 04 001 001 OCT 08 500N 2 01 04 002 001 APR 08 500

ALL

N 2 01 04 003 001 APR 08 500N 2 01 04 004 001 APR 08 500

ALL

N 2 01 04 005 001 OCT 08N 2 01 04 006 001 DEC 07

ALL

N 2 01 05 001 001 DEC 04 500N 2 01 05 002 100 DEC 07 MOD 4292 or 5840

ALL

N 2 01 05 003 001 MAY 97ALL

N 2 01 06 001 050 DEC 07N 2 01 06 002 050 DEC 07

ALL

N 2 01 06 003 050 DEC 07N 2 01 06 004 050 DEC 07

ALL

N 2 01 06 005 080 DEC 07 MOD 5205ALL

N 2 01 07 001 700 APR 08 MOD 5768ALL

N 2 01 07 001A 700 APR 08 MOD 5768ALL

N 2 01 07 001B 700 APR 08 MOD 5768ALL

N 2 01 08 001 100 NOV 99 MOD 5067 or 5171ALL

N 2 01 09 001 110 OCT 08 MOD 5313 or 5467ALL

N 2 02 00 001 001 DEC 10ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 02 01 001 001 DEC 95N 2 02 01 002 001 MAY 98

ALL

N 2 02 01 003 001 NOV 99 500N 2 02 01 004 001 NOV 97

ALL

N 2 02 02 001 001 MAR 96ALL

N 2 02 03 001 001 DEC 95N 2 02 03 002 001 NOV 96

ALL

N 2 02 03 003 001 NOV 96N 2 02 03 004 001 DEC 95

ALL

N 2 02 04 001 001 NOV 96N 2 02 04 002 001 DEC 95

ALL

N 2 02 04 003 001 NOV 96N 2 02 04 004 001 NOV 96

ALL

N 2 02 04 005 001 DEC 95N 2 02 04 006 001 DEC 95

ALL

N 2 02 04 007 001 MAY 98N 2 02 04 008 020 DEC 10 MOD 1112

ALL

N 2 02 04 009 210 DEC 10 MOD 1112 +4583N 2 02 04 010 020 DEC 10 MOD 1112

ALL

N 2 02 04 011 020 DEC 10 MOD 1112N 2 02 04 012 020 DEC 10 500 MOD 1112

ALL

N 2 02 05 001 001 DEC 95 500N 2 02 05 002 001 NOV 96 500

ALL

N 2 02 05 003 001 DEC 95ALL

N 2 02 06 001 001 NOV 96N 2 02 06 002 001 NOV 97

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 02 06 003 100 MAY 98 500 MOD 4372N 2 02 06 004 001 NOV 96

ALL

N 2 02 06 005 001 NOV 02ALL

N 2 02 07 001 001 DEC 10ALL

N 2 02 08 001 001 DEC 09N 2 02 08 002 001 DEC 95

ALL

N 2 02 08 003 001 DEC 95N 2 02 08 004 300 NOV 02 500 MOD 4372 +(4450 or 4580) +4540

ALL

N 2 02 08 005 001 DEC 95N 2 02 08 006 100 NOV 00 500 MOD 4601

ALL

N 2 02 08 007 050 NOV 00 MOD 5008N 2 02 08 008 001 NOV 00

ALL

N 2 02 08 009 001 MAY 98N 2 02 08 010 001 DEC 09

ALL

N 2 02 08 011 001 MAY 97N 2 02 08 012 001 NOV 99

ALL

N 2 02 08 013 001 DEC 04N 2 02 08 014 001 MAY 97

ALL

N 2 02 08 015 001 NOV 99N 2 02 08 016 001 DEC 95

ALL

N 2 02 08 017 001 DEC 10N 2 02 08 018 001 NOV 96

ALL

N 2 02 08 019 001 NOV 00N 2 02 08 020 001 NOV 00

ALL

N 2 02 08 021 001 NOV 98N 2 02 08 022 001 NOV 98

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 02 08 023 001 DEC 09N 2 02 08 024 001 DEC 09

ALL

N 2 02 08 025 001 DEC 09ALL

N 2 02 09 001 001 NOV 97N 2 02 09 002 001 MAY 97

ALL

N 2 02 09 003 001 MAY 97ALL

N 2 02 10 001 001 MAY 98N 2 02 10 002 001 MAY 98

ALL

N 2 02 10 003 001 MAY 98N 2 02 10 004 001 MAY 98

ALL

N 2 02 10 005 001 MAY 98N 2 02 10 006 001 MAY 98

ALL

N 2 02 10 007 001 NOV 96N 2 02 10 008 001 NOV 97

ALL

N 2 02 10 009 001 DEC 95ALL

N 2 02 11 001 001 DEC 10N 2 02 11 002 001 NOV 02

ALL

N 2 02 11 002A 001 DEC 10ALL

N 2 02 11 003 001 NOV 96N 2 02 11 004 001 DEC 95

ALL

N 2 02 11 005 001 MAY 97N 2 02 11 006 001 APR 08 500

ALL

N 2 02 11 007 001 APR 08 500N 2 02 11 008 001 DEC 09

ALL

N 2 02 12 001 001 DEC 07N 2 02 12 002 001 DEC 95

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 02 12 003 001 NOV 99N 2 02 12 004 001 DEC 07

ALL

N 2 02 12 005 001 NOV 01ALL

N 2 02 13 001 110 NOV 00 MOD 5176N 2 02 13 002 110 NOV 00 MOD 5176

ALL

N 2 02 14 001 001 DEC 06N 2 02 14 002 001 DEC 06

ALL

N 2 02 15 001 060 DEC 07N 2 02 15 002 060 DEC 07

ALL

N 2 02 16 001 001 DEC 03ALL

N 2 02 19 001 001 DEC 06ALL

N 2 02 21 001 100 DEC 05N 2 02 21 002 100 DEC 05

ALL

N 2 02 21 003 100 DEC 05N 2 02 21 004 100 DEC 05

ALL

N 2 02 21 005 100 DEC 05N 2 02 21 006 100 DEC 05

ALL

N 2 02 21 007 100 DEC 07N 2 02 21 008 100 DEC 05

ALL

N 2 02 21 009 100 DEC 07N 2 02 21 010 100 DEC 05

ALL

N 2 02 21 011 100 DEC 09N 2 02 21 012 100 DEC 05

ALL

N 2 02 21 013 100 DEC 05N 2 02 21 014 100 DEC 05

ALL

N 2 02 21 015 100 DEC 05N 2 02 21 016 100 DEC 05

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 02 21 017 100 DEC 05N 2 02 21 018 100 DEC 05

ALL

N 2 02 21 018A 100 DEC 05ALL

N 2 02 22 001 100 DEC 05 MOD 5506N 2 02 22 002 100 DEC 05 MOD 5506

ALL

N 2 02 22 003 100 DEC 05 MOD 5506N 2 02 22 004 100 DEC 05 MOD 5506

ALL

N 2 02 22 005 100 DEC 05 MOD 5506N 2 02 22 006 100 DEC 05 MOD 5506

ALL

N 2 02 22 007 100 DEC 05 MOD 5506N 2 02 22 008 100 DEC 05 MOD 5506

ALL

N 2 03 00 001 001 APR 08ALL

N 2 03 01 001 001 APR 08ALL

N 2 03 02 001 001 APR 08ALL

N 2 03 03 001 001 APR 08N 2 03 03 002 001 APR 08

ALL

N 2 03 03 003 001 APR 08ALL

N 2 03 04 001 001 APR 08ALL

N 2 03 05 001 001 APR 08N 2 03 05 002 001 APR 08

ALL

N 2 03 05 003 001 APR 08N 2 03 05 004 001 OCT 08

ALL

N 2 03 05 005 001 APR 08N 2 03 05 006 001 OCT 08

ALL

N 2 03 05 007 001 APR 08ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 03 06 001 001 DEC 10N 2 03 06 002 001 DEC 10

ALL

N 2 03 06 003 001 DEC 10N 2 03 06 004 001 DEC 09

ALL

N 2 03 06 005 001 APR 08N 2 03 06 006 001 DEC 10

ALL

N 2 03 06 007 001 APR 08N 2 03 06 008 001 DEC 09

ALL

N 2 03 06 009 001 DEC 10ALL

N 2 03 07 001 001 APR 08N 2 03 07 002 001 APR 08

ALL

N 2 03 07 003 001 APR 08N 2 03 07 004 001 APR 08

ALL

N 2 03 07 005 001 APR 08N 2 03 07 006 001 APR 08

ALL

N 2 03 07 007 001 APR 08ALL

N 2 03 08 001 001 DEC 09ALL

N 2 03 09 001 001 APR 08ALL

N 2 03 10 001 001 DEC 09ALL

N 2 03 11 001 001 APR 08ALL

N 2 03 12 001 001 APR 08ALL

N 2 03 13 001 001 DEC 09N 2 03 13 002 001 DEC 09

ALL

N 2 03 14 001 001 APR 08ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 03 15 001 001 APR 08ALL

N 2 03 16 001 001 APR 08N 2 03 16 002 110 APR 08 500 MOD (4450 or 4580)

ALL

N 2 03 17 001 001 APR 08ALL

N 2 03 18 001 001 APR 08ALL

N 2 03 19 001 001 DEC 10ALL

N 2 03 20 001 001 APR 08ALL

N 2 03 21 001 001 APR 08ALL

N 2 04 00 001 001 DEC 09ALL

N 2 04 01 001 001 DEC 95N 2 04 01 002 001 DEC 09

ALL

N 2 04 02 001 001 DEC 07N 2 04 02 002 001 DEC 07

ALL

N 2 04 02 003 001 DEC 10N 2 04 02 004 001 DEC 95

ALL

N 2 04 02 005 001 DEC 09ALL

N 2 04 03 001 001 DEC 07N 2 04 03 002 001 DEC 09

ALL

N 2 04 03 003 001 DEC 10N 2 04 03 004 001 DEC 10

ALL

N 2 04 03 005 001 APR 08N 2 04 03 006 001 DEC 09

ALL

N 2 04 04 001 001 DEC 07N 2 04 04 002 001 NOV 99

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 04 05 001 001 DEC 07N 2 04 05 002 001 DEC 09

ALL

N 2 04 05 003 001 DEC 95N 2 04 05 004 001 DEC 95

ALL

N 2 04 05 005 001 DEC 09N 2 04 05 006 001 DEC 95

ALL

N 2 04 05 007 001 DEC 09N 2 04 05 008 001 NOV 98

ALL

N 2 04 05 009 001 DEC 03N 2 04 05 010 001 NOV 99

ALL

N 2 04 05 011 001 DEC 10ALL

N 2 05 00 001 001 DEC 10N 2 05 00 002 001 DEC 09

ALL

N 2 05 00 003 001 OCT 08N 2 05 00 004 001 DEC 10

ALL

N 2 05 01 001 001 APR 08N 2 05 01 002 001 DEC 09

ALL

N 2 05 02 001 001 DEC 09N 2 05 02 002 001 APR 08

ALL

N 2 05 02 003 001 APR 08N 2 05 02 004 001 OCT 08

ALL

N 2 05 02 005 001 DEC 10N 2 05 02 006 001 DEC 10

ALL

N 2 05 02 007 001 APR 08N 2 05 02 008 001 APR 08

ALL

N 2 05 02 009 001 APR 08N 2 05 02 010 001 DEC 10

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 05 02 011 001 APR 08N 2 05 02 012 001 APR 08

ALL

N 2 05 02 013 001 DEC 09N 2 05 02 014 001 APR 08

ALL

N 2 05 02 015 001 APR 08N 2 05 02 016 001 DEC 10

ALL

N 2 05 02 017 001 DEC 09N 2 05 02 018 001 APR 08

ALL

N 2 05 02 019 001 DEC 09N 2 05 02 020 001 DEC 10 PW127E-127M

ALL

N 2 05 02 021 001 APR 08 PW127E-127MN 2 05 02 022 001 APR 08

ALL

N 2 05 02 023 001 APR 08ALL

N 2 05 03 001 001 APR 08N 2 05 03 002 001 APR 08

ALL

N 2 05 03 003 500 APR 08 MOD 4650N 2 05 03 004 001 APR 08

ALL

N 2 05 04 001 001 DEC 09N 2 05 04 002 001 DEC 09

ALL

N 2 05 04 003 001 DEC 09N 2 05 04 004 001 DEC 09

ALL

N 2 05 04 005 001 DEC 09N 2 05 04 006 001 APR 08

ALL

N 2 05 04 007 001 APR 08N 2 05 04 008 001 OCT 08

ALL

N 2 05 04 009 001 APR 08N 2 05 04 010 001 OCT 08

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 05 04 011 001 APR 08N 2 05 04 012 001 DEC 10

ALL

N 2 05 04 013 001 APR 08N 2 05 04 014 001 APR 08

ALL

N 2 05 05 001 001 APR 08N 2 05 05 002 001 OCT 08

ALL

N 2 05 05 003 001 OCT 08N 2 05 05 004 001 APR 08

ALL

N 2 05 06 001 001 APR 08N 2 05 06 002 001 APR 08

ALL

N 2 05 06 003 001 APR 08N 2 05 06 004 001 APR 08

ALL

N 2 05 06 005 001 APR 08N 2 05 06 006 001 DEC 09

ALL

N 2 05 06 007 001 APR 08N 2 05 06 008 001 DEC 10

ALL

N 2 05 06 009 500 APR 08 500 MOD 4372N 2 05 06 010 001 DEC 10

ALL

N 2 05 06 011 001 APR 08N 2 05 06 012 001 APR 08

ALL

N 2 05 07 001 001 APR 08N 2 05 07 002 001 APR 08

ALL

N 2 05 07 003 001 APR 08N 2 05 07 004 001 APR 08

ALL

N 2 05 07 005 001 APR 08N 2 05 07 006 001 APR 08

ALL

N 2 05 07 007 001 DEC 10ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 05 08 001 001 APR 08N 2 05 08 002 001 APR 08

ALL

N 2 05 08 003 001 APR 08N 2 05 08 004 001 DEC 10

ALL

N 2 05 08 005 001 APR 08N 2 05 08 006 001 DEC 10

ALL

N 2 05 08 007 001 APR 08N 2 05 08 008 001 APR 08

ALL

N 2 05 08 009 001 APR 08ALL

N 2 05 09 001 001 DEC 09N 2 05 09 002 001 APR 08

ALL

N 2 05 09 003 001 OCT 08N 2 05 09 004 001 APR 08

ALL

N 2 05 09 005 001 OCT 08N 2 05 09 006 001 APR 08

ALL

N 2 05 09 007 001 APR 08ALL

N 2 05 10 001 001 APR 08N 2 05 10 002 001 APR 08

ALL

N 2 05 11 001 001 APR 08ALL

N 2 05 12 001 001 APR 08N 2 05 12 002 001 DEC 09

ALL

N 2 05 12 003 001 APR 08N 2 05 12 004 050 APR 08 MOD 5205

ALL

N 2 05 12 005 001 APR 08ALL

N 2 05 13 001 001 DEC 10N 2 05 13 002 001 DEC 10

ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 05 13 003 001 APR 08ALL

N 2 05 14 001 001 OCT 08N 2 05 14 002 001 OCT 08

ALL

N 2 05 14 003 001 OCT 08N 2 05 14 004 001 OCT 08

ALL

N 2 05 14 005 001 OCT 08N 2 05 14 006 001 OCT 08

ALL

N 2 05 14 007 001 OCT 08N 2 05 14 008 001 OCT 08

ALL

N 2 05 14 009 001 DEC 10N 2 05 14 010 001 OCT 08

ALL

N 2 06 00 001 001 DEC 95ALL

N 2 06 01 001 001 DEC 95ALL

N 2 06 02 001 001 DEC 07ALL

N 2 06 03 001 001 DEC 95N 2 06 03 002 001 DEC 95

ALL

N 2 06 03 003 001 DEC 95N 2 06 03 004 001 DEC 95

ALL

N 2 06 03 005 001 DEC 95N 2 06 03 006 001 DEC 95

ALL

N 2 06 03 007 001 DEC 95N 2 06 03 008 001 DEC 95

ALL

N 2 06 03 009 001 DEC 95N 2 06 03 010 001 DEC 95

ALL

N 2 06 03 011 001 DEC 95ALL


ATR42-400/500


DEC 10


Turn EQ

N 2 06 04 001 001 DEC 95N 2 06 04 002 001 DEC 95

ALL

N 2 06 04 003 001 DEC 95N 2 06 04 004 001 NOV 99 500

ALL

N 3 01 00 001 001 DEC 95ALL

N 3 01 01 001 001 DEC 95N 3 01 01 002 001 DEC 95

ALL

N 3 01 01 003 001 DEC 95ALL

N 3 01 02 001 001 DEC 95ALL

N 3 01 03 001 001 DEC 95ALL

N 3 01 04 001 001 DEC 95N 3 01 04 002 001 DEC 95

ALL

N 3 01 05 001 001 DEC 95ALL

N 3 02 00 001 100 NOV 98 MOD 3761 or 4601 or (4372 +4540)ALL

N 3 02 01 001 001 NOV 99N 3 02 01 002 001 DEC 95

ALL

N 3 02 02 001 001 APR 08 500 - PW127E-127MN 3 02 02 002 001 APR 08 500 - PW127E-127M

ALL


ALL


ALL


ALL


ATR42-400/500


DEC 10


Turn EQ


ALL

N 3 02 02 011 001 APR 08 500 - PW127E-127MN 3 02 02 012 100 APR 08 MOD 4601 or (4372 +4540)

ALL

N 3 02 02 013 100 APR 08 MOD 4601 or (4372 +4540)N 3 02 02 014 100 APR 08 MOD 4601 or (4372 +4540)

ALL

N 3 02 02 015 100 APR 08 MOD 4601 or (4372 +4540)ALL

N 3 03 00 001 001 OCT 08ALL

N 3 03 01 001 001 NOV 99N 3 03 01 002 200 APR 08 MOD 4372 +4540

ALL

N 3 03 02 001 001 DEC 95N 3 03 02 002 001 NOV 00

ALL

N 3 03 02 003 001 DEC 09N 3 03 02 004 200 APR 08 MOD 4372 +4540

ALL

N 3 03 02 005 200 DEC 10 500 MOD 4372 +4540N 3 03 02 006 200 APR 08 500 MOD 4372 +4540

ALL

N 3 03 03 001 001 APR 08N 3 03 03 002 300 APR 08 MOD 4372 +4540 +4971

ALL

N 3 03 03 002A 200 APR 08 MOD 4372 +4540ALL

N 3 03 03 003 200 APR 08 MOD 4372 +4540N 3 03 03 004 001 APR 08

ALL

N 3 03 03 004A 001 APR 08ALL

N 3 03 03 005 200 APR 08 MOD 4372 +4540ALL

N 3 03 03 005A 200 APR 08 MOD 4372 +4540ALL

N 3 03 03 006 200 APR 08 MOD 4372 +4540ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 03 03 007 200 APR 08 MOD 4372 +4540ALL

N 3 03 04 001 200 APR 08 MOD 4372 +4540N 3 03 04 002 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 003 200 APR 08 MOD 4372 +4540N 3 03 04 004 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 005 200 APR 08 MOD 4372 +4540N 3 03 04 006 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 007 200 APR 08 MOD 4372 +4540N 3 03 04 008 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 009 200 APR 08 MOD 4372 +4540N 3 03 04 010 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 011 200 APR 08 MOD 4372 +4540N 3 03 04 012 200 APR 08 MOD 4372 +4540

ALL

N 3 03 04 013 200 APR 08 MOD 4372 +4540ALL

N 3 03 05 001 001 DEC 10N 3 03 05 002 200 APR 08 MOD 4372 +4540

ALL

N 3 03 06 001 001 NOV 01ALL

N 3 04 00 001 001 DEC 03ALL

N 3 04 01 001 001 DEC 09ALL

N 3 04 02 001 200 APR 08 MOD 4372 +4540N 3 04 02 002 001 APR 08

ALL

N 3 04 02 003 001 APR 08ALL

N 3 04 03 001 200 APR 08 MOD 4372 +4540N 3 04 03 002 001 APR 08

ALL

N 3 04 03 003 001 APR 08ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 04 04 001 001 APR 08N 3 04 04 002 001 APR 08

ALL

N 3 04 04 003 001 APR 08N 3 04 04 004 001 APR 08

ALL

N 3 04 04 005 001 APR 08N 3 04 04 006 001 APR 08

ALL

N 3 04 04 007 001 APR 08N 3 04 04 008 001 APR 08

ALL

N 3 04 04 009 001 APR 08N 3 04 04 010 001 APR 08

ALL

N 3 04 04 011 200 APR 08 MOD 4372 +4540ALL

N 3 04 05 001 001 DEC 03N 3 04 05 002 001 DEC 03

ALL

N 3 04 05 003 001 DEC 03 500 - PW127EN 3 04 05 004 001 APR 08

ALL

N 3 04 05 005 001 APR 08ALL

N 3 05 00 001 001 DEC 95ALL

N 3 05 01 001 100 APR 08 MOD 4601 or (4372 +4540)ALL


ALL


ALL


ALL


ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 05 03 001 001 APR 08N 3 05 03 002 001 APR 08

ALL

N 3 05 03 003 001 APR 08N 3 05 03 004 001 APR 08

ALL

N 3 05 03 005 001 APR 08N 3 05 03 006 001 APR 08

ALL

N 3 05 03 007 001 APR 08N 3 05 03 008 001 APR 08

ALL

N 3 05 03 009 001 APR 08ALL

N 3 06 00 001 001 DEC 95ALL

N 3 06 01 001 100 APR 08 MOD 4601 or (4372 +4540)ALL

N 3 06 02 001 200 APR 08 MOD 4372 +4540N 3 06 02 002 200 APR 08 MOD 4372 +4540

ALL

N 3 06 03 001 200 APR 08 MOD 4372 +4540N 3 06 03 002 200 APR 08 MOD 4372 +4540

ALL

N 3 07 00 001 001 DEC 95ALL

N 3 07 01 001 100 NOV 99 500 MOD 4601 or (4372 +4540)ALL

N 3 07 02 001 001 APR 08N 3 07 02 002 001 APR 08

ALL

N 3 07 03 001 001 APR 08 500 - PW127E-127MN 3 07 03 002 001 APR 08

ALL

N 3 08 00 001 001 NOV 01ALL

N 3 08 01 001 120 NOV 02 500 MOD 1112 +(4450 or 4580)N 3 08 01 002 200 APR 08 MOD 4372 +4540

ALL

N 3 08 01 002A 220 MAY 97 500 - PW127E MOD 1112 +4372 +4540ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 08 01 003 300 APR 08 500 MOD 4372 +(4450 or 4580) +4540ALL

N 3 08 01 003A 420 APR 08 500 MOD 1112 +4372 +(4450 or 4580) +4540ALL

N 3 08 01 004 300 APR 08 MOD 4372 +(4450 or 4580) +4540ALL

N 3 08 01 004A 410 APR 08 MOD 1112 +4372 +(4450 or 4580) +4540ALL

N 3 08 02 001 300 NOV 02 500 - PW127 EMOD 4372+(4450 or 4580)+4540ALL

N 3 08 03 001 001 MAY 97N 3 08 03 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 08 03 002A 210 APR 08 500 MOD (4450 or 4580) +(4372 +4540 )ALL

N 3 08 03 003 100 NOV 00 500 MOD 4971N 3 08 03 004 001 DEC 95

ALL

N 3 08 04 001 001 NOV 01ALL

N 3 09 00 001 001 DEC 95ALL

N 3 09 01 001 001 MAY 98ALL

N 3 09 02 001 001 DEC 95N 3 09 02 002 001 NOV 00

ALL

N 3 09 02 003 001 OCT 08 500N 3 09 02 004 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 02 005 200 NOV 00 500 MOD 4372 +4540N 3 09 02 006 001 APR 08 500

ALL

N 3 09 02 007 001 APR 08 500N 3 09 02 008 001 APR 08 500

ALL

N 3 09 02 009 001 APR 08 500ALL

N 3 09 03 001 001 MAY 98N 3 09 03 002 001 MAY 98

ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 09 03 003 001 NOV 98ALL

N 3 09 10 001 200 APR 08 500 MOD 4372 +4540N 3 09 10 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 10 003 200 APR 08 500 MOD 4372 +4540N 3 09 10 004 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 15 001 200 APR 08 500 MOD 4372 +4540N 3 09 15 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 15 003 200 APR 08 500 MOD 4372 +4540N 3 09 15 004 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 16 001 001 APR 08 500N 3 09 16 002 001 APR 08 500

ALL

N 3 09 16 003 001 APR 08 500N 3 09 16 004 001 APR 08 500

ALL

N 3 09 17 001 001 APR 08 500N 3 09 17 002 001 APR 08 500

ALL

N 3 09 17 003 001 APR 08 500N 3 09 17 004 001 APR 08 500

ALL

N 3 09 20 001 001 APR 08 500N 3 09 20 002 001 APR 08 500

ALL

N 3 09 20 003 001 APR 08 500N 3 09 20 004 001 APR 08 500

ALL

N 3 09 20 005 001 APR 08 500N 3 09 20 006 001 APR 08 500

ALL

N 3 09 20 007 001 APR 08 500N 3 09 20 008 001 APR 08 500

ALL

N 3 09 25 001 001 APR 08 500N 3 09 25 002 001 APR 08 500

ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 09 25 003 001 APR 08 500N 3 09 25 004 001 APR 08 500

ALL

N 3 09 25 005 001 APR 08 500N 3 09 25 006 001 APR 08 500

ALL

N 3 09 25 007 001 APR 08 500ALL

N 3 09 30 001 200 APR 08 500 MOD 4372 +4540N 3 09 30 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 09 35 001 200 APR 08 500 MOD 4372 +4540N 3 09 35 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 10 00 001 001 DEC 95ALL

N 3 10 01 001 001 DEC 05N 3 10 01 002 001 DEC 95

ALL

N 3 10 02 001 001 APR 08 500N 3 10 02 002 001 APR 08 500

ALL

N 3 10 03 001 001 APR 08 500ALL

N 3 10 04 001 001 APR 08 500N 3 10 04 002 001 APR 08 500

ALL

N 3 10 04 003 001 APR 08 500N 3 10 04 004 001 APR 08 500

ALL

N 3 11 00 001 001 DEC 07N 3 11 00 002 001 NOV 00

ALL

N 3 11 01 001 001 APR 08 500N 3 11 01 002 200 APR 08 500 MOD 4372 +4540

ALL

N 3 11 01 003 200 APR 08 500 MOD 4372 +4540N 3 11 01 004 200 APR 08 500 MOD 4372 +4540

ALL

N 3 11 01 005 200 APR 08 500 MOD 4372 +4540N 3 11 01 006 001 APR 08 500

ALL


ATR42-400/500


DEC 10


Turn EQ

N 3 11 01 007 001 APR 08 500N 3 11 01 008 001 APR 08 500

ALL

N 3 11 01 009 001 APR 08 500N 3 11 01 010 200 APR 08 500 MOD 4372 +4540

ALL

N 3 11 01 011 001 APR 08 500ALL

N 3 11 02 001 001 MAY 98ALL

N 3 11 03 001 001 NOV 96ALL

N 3 11 04 001 001 APR 08 500ALL

N 3 11 05 001 001 APR 08 500ALL

N 3 11 06 001 001 NOV 96ALL

N 3 11 07 001 001 NOV 98ALL

N 3 11 08 001 001 APR 08 500ALL

N 3 11 09 001 001 MAY 97ALL

N 3 11 10 001 001 NOV 97ALL

N 3 11 11 001 001 NOV 96ALL

N 3 11 12 001 001 DEC 07ALL

N 3 11 13 001 001 DEC 07ALL

N 3 11 14 001 001 DEC 07ALL

N 3 11 15 001 001 DEC 07ALL

N 3 11 16 001 001 DEC 07ALL

N 3 11 17 001 001 DEC 07ALL


ATR42-400/500


DEC 10


End EQ

N 3 11 18 001 001 DEC 07ALL

N 3 11 19 001 001 DEC 07ALL

N 3 12 00 001 001 DEC 05ALL

N 3 12 10 001 001 DEC 05ALL

N 3 12 20 001 001 DEC 07ALL

N 3 12 21 001 001 SEP 95 500ALL

N 3 12 27 001 001 DEC 05 500ALL

N 3 12 28 001 001 DEC 05ALL

N 3 12 29 001 001 DEC 07 500 MOD 5736ALL


ATR42-400/500

L.O.M.List of Modifications

DEC 10

MODIF PARTS TITLEVALIDITY

Turn EQ

0043 1.3 REPLACE KING RADIO NAV-RADIO COMMEQUIPMENT BY COLLINS

ALL

1112 2.3 AUTO FLIGHT - RETROFIT CAT. 2CAPABILITY TO A/C DELIVERED WITHCAT. 1 CAPABILITY

ALL

3713 2.3 POWER PLANT - INSTALL PW127EENGINES

ALL

3832 1.2 NAVIGATION- TCAS - REPLACE COLLINSTCAS-COMPUTER

ALL

4019 1 DOORS - PASSENGER/CREW DOOR -REPLACE A 2ND HANDRAIL BY A SEMIAUTOMATIC HANDRAIL

ALL

4292 1.2 OXYGEN - INSTALL A 100% PAX OXYGENDISTRIBUTION SYSTEM

ALL

4358 1 DOORS - SERVICE DOOR - REPLACE THEOLD OPENING DEVICE BY A NEW RIGIDMECHANISM

ALL

4372 1.2.3 FLIGHT CONTROLS - AIRLERONSCONTROLS - INSTALL SPRING TAB

ALL

4403 1.2 NAVIGATION - INSTALL SUNDSTRANDMK7 GPWS

ALL

4439 2 FUSELAGE - SECT. 18 - INSTALLVERTICAL FIN WITH CARBON EPOXY BOX

ALL

4462 1.2 GENERAL - INCREASE ATR 42-500 VFE 15FROM 170 TO 180 KTS

ALL

4497 1 NAVIGATION - ATC - INSTALL 2NDCOLLINS ATC FEATURING MODES A ANDC

ALL


ATR42-400/500


DEC 10


Turn EQ

4540 2.3 WINGS - INB. & OUTB.FLAPS - DELETEDEFLECTORS

ALL

4568 1 INDICATING/RECORDING SYSTEMS -MODIFY FLAP EXTINTION LOGIC ON ST4& ST5

ALL

4580 2.3 INDICATING/RECORDING SYSTEMS -PROVIDE LANDING WITH FLAPS AT 25°

ALL

4583 2 AUTO FLIGHT - AUTOPILOT - IMPROVEGLIDE GUIDANCE LAW

ALL

4584 1.2 PNEUMATIC - AIR LEAK DETECTIONSYSTEM - REPLACE SENSING ELEMENTS

ALL

4601 1.2.3 PROPELLERS - PROPELLER CONTROL -DELETE 77 % NP

ALL

4650 2 FUEL - QUANTITY INDICATION - ADD LOWLEVEL DETECTION SYSTEM

ALL

4656 1 NAVIGATION - GNSS - PROVIDE DME'SCOUPLING

ALL

4971 3 GENERAL - RUNWAYS : OPERATION ONRUNWAY SLOPES BETWEEN 2 % & 4,5 %(42-500)

ALL

5008 1.2 ICE AND RAIN PROTECTION - MODIFYFLASHING LOGIC OF "ICING" LIGHTLOGIC OF "ICING" LIGHT(ASSOCIATED TOICE DETECT. SYSTEM)

ALL

5016 1 NAVIGATION - INSTALL NEW PRIMUS 660WEATHER RADAR

ALL

5017 1 COMMUNICATIONS - CABIN & FLIGHTCREW CALL SYSTEMS - ADD "EMERCALL" ON A NEW-LOOK CONFIG.ATTENDANT HANDSET

ALL


ATR42-400/500


DEC 10


Turn EQ

5020 2 NAVIGATION - INSTALL HT1000GNSS/GPS BUS WIRING PROVISION

ALL

5067 1.2 LIGHTS - PAX COMPARTMENT EXT;LIGHTING - REPLACE ESCAPE PATHMARKING SYSTEM

ALL

5146 1 NAVIGATION - TCAS - TCAS COLLINS TTR921 INSTALLATION

ALL

5150 2 STRUCTURE - EXTENSION OF THE FWDCG LIMITS

ALL

5176 1 NAVIGATION - GNSS - LOAD SOFTWAREFINAL BASELINE

ALL

5205 2 NAVIGATION - ATC/ATS - ACQUIREALTITUDE VIA BUS ARINC 429

ALL

5313 1.2 NAVIGATION - EGPWS MKVIII -ENHANCED PART ACTIVATON

ALL

5403 2 NAVIGATION - CERTIFICATION OF GNSSP-RNAV

ALL

5467 1 NAVIGATION - EGPWS - INSTALL EGPWSMKVIII P/N 965-1206-011

ALL

5487 1 NAVIGATION - ELEMENTARYSURVEILLANCE FID TRANSMISSION

ALL

5506 2 COMMUNICATIONS - INSTALL ACARSCOLLINS CMU 4000 AND VDL2

ALL

5567 1 INDICATING/RECORDING SYSTEMS -INSTALL AND ACTIVATE MPC

ALL

5570 NAVIGATION - ACTIVATE ENHANCEDSURVEILLANCE CAPABILITY

ALL


ATR42-400/500


DEC 10


End EQ

5736 3 COMMUNICATIONS - COCKPIT VOICERECORDER

ALL

5768 2 NAVIGATION - RNAV GNSS SINGLE ORDUAL NON-PRECISION APPROACHCAPABILITY

ALL

6135 2 - 3 NAVIGATION - T2CAS

ALL


ATR42-400/500

C.R.T.Cross Reference Table

DEC 10

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

End EQ

EQ0501 0844 HT-CLT

ATR 42 Model : 400/500

ORGANIZATION OF THE MANUAL


PRELIMINARY PAGESP 1

DEC 05

001

0.40.00

The Flight Crew Operating Manual (FCOM) provides operating crew members and flightoperations engineers with information on the ATR 42--400/500 technical description,procedures and performances characteristics. It may be used as a crew manual fortraining purposes and flight preparation.

FCOM mainly comprises :-- manuel management in Part 0-- systems description in Part 1-- limitations with comments in Part 2-- procedures : normal, following failure and emergency, in Part 2 with comments-- procedures and techniques in Part 2.02-- performances (conservative and simplified compared with AFM) in Part 3-- Special Operations in Part 3--OEB (Operations Engineering Bulletin) : validated by the ATRChief Test Pilot, their aimis to cover temporary equipment discrepancy. They are printed on pale green paper andare situated at the very end of FCOM.

For any question, comment or suggestion regarding this manual, or technicaldocumentation in general, we recommend to use following e--mail :

[email protected] at the minimum :-- aircraft model(s)-- manual(s) concerned-- precise page(s) if applicable

DEFINITION OF THE PAGE

A page is defined by :-- a reference : Part / Chapter / Section / page number -- Example : 2.05.10 page 20.-- an effectivity criterion determining the page sequence

example : Equipment, Modification, Engine...A page with a given reference may have several sequences :

example : 2.05.10 page 20No criterion Sequence 001. . . . . . . . . . .Mod XXXX Sequence 002. . . . . . . . . . . .Mod XXXX + YYYY Sequence 003. . . . . .

All the sequences cover, for a given reference, all technical solution or variant for aircrafttypes covered by the manual.Airlines receive a part of these sequences to cover their fleet.A sequence can be valid for several aircraft but an aircraft can not have severalsequences: an aircraft receives the page with the highest sequence among all pages forwhich it has a validity.

AA

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ATR 42 Model : 400/500




DEC 05

001

0.40.00

(1) GIE ATR logo, with aircraft type and manual type(2) Title of Chapter(3) Part, chapter and section in the manual(4) Page Numbering -- Particular case : a page followed by an alphabetic letter must beinserted between 2 pages. Example : page 11A must be inserted between pages 11 and 12.(5) Sequence number(6) If 2 letters (XX) are indicated on the page, this one is customized to airline XX(7) Date of revision (date of page issue)(8) Zone for standard(9) Zone for unit(10) Title of section

(1) Modification zone : contains expression of modifications characterizing the content ofthis page.

(2) Indication of engine type installed on aircraft ; if there is “ALL” or if there is no Engreference, the content of the page does not depend on a particular engine.

(3) Indication of aircraft type ; if there is “ALL” or if there is no Model reference, thecontent of the page does not depend on a particular model.

AAR

ATR 42 Model : 400/500




DEC 05

001

0.40.00

RECTO-VERSO

The FCOM is published in recto--verso paper AT5 format customized for each airline.

In theLENP (0.08.00)List ofEffective Normal Pages, when recto and verso are printed,each sheet is represented by 2 lines :-- the first line concerns the recto.-- the second line concerns the verso.If only recto sheet is printed, it is represented by only one line.Then for each sheet, we find the validity line with an expression containing one or severalnumbers which represent FSN (Fleet Serial Number) of aircraft for which this sheet isapplicable.

To understand the effectivity of the sheets, you must read :Example : XX0001--0003 = XX FSN0001 to FSN003 -- --> 3 aircraft valid

XX0001 XX0003 = XX FSN0001 and FSN0003 -- --> only 2 aircraft valid

In CRT (0.10.00), we find the list of fleet aircraft with FSN, MSN (Manufacturer SerialNumber) and registration number.

MANUAL UPDATING

Your manual comprises 2 types of pages :-- white pages or NORMAL pages-- yellow pages or TEMPORARY pagesThese 2 families of pages have a separated management.

NORMAL PAGES (white)

For its first issue FCOM was published in “white” normal pages.

Then on a yearly basis at theminimum, a normal revision is performed amending previousissue by revising pages (sheet replacement), creating new pages (sheet insertion) ordeleting pages (sheet deletion).

Detailed and exhaustive information for manual normal revision updating is in SNNP(0.07.00), Shipping Note for Normal Pages.

Operator must refer to SNNP and new LENP to update properly its manual.

SNNP lists all revised, created or deleted white sheets.LENP gives aircraft validity information for all concerned white sheets.It is important to note that the action given in SNNP is valid for the sheet (recto--verso) notfor one page.

Normal Revisions are listed in LNR (0.05.00) List of Normal Revisions.

Reasons of revision are highlighted in RNR (0.06.00) Reason of Normal Revisions.

AAR

ATR 42 Model : 400/500




DEC 05

001

0.40.00

MANUAL UPDATING (cont’d)

TEMPORARY PAGES (yellow)

Between two normal revisions some subjects may present a particular urgency. In thosecases we perform a Temporary Revision. It may concern only one customer or the wholefleet.All temporary pages at a given moment are listed in LETP (0.04.00), List of EffectiveTemporary Pages. Temporary pages are recto--only pages.When a white page exists with the same reference, a yellow page is inserted in face orbefore corresponding white page and its content amends the content of white page. Ifthere is no white page with the same reference, yellow page(s) is(are) inserted just afterthe last adapted white page or chapter.

Detailed and exhaustive information for manual temporary revision updating is in SNTP(0.03.00), Shipping Note for Temporary Pages.

Operator must refer to SNTP and new LETP to update properly its manual.

SNTP lists all revised, created or deleted yellow pages.LETP gives aircraft validity information for all concerned yellow pages.It is important to note that the action given inSNTP is valid for the yellow page (no verso onyellow page).

Temporary Revisions are listed in LTR (0.01.00) List of Temporary Revisions. Eachoperator has its own LTR as Temporary Revision does not necessarily concern allcustomer : TR01 for an operatormay be equivalent to TR10 for another operator andTR20for ENV.

Reasons of revision are highlighted in RTR (0.02.00) Reason of Temporary Revisions.

AIRCRAFT CONFIGURATION

All ATRmodifications having an impact on FCOMcontent are listed inLOM (0.09.00),ListOf Modifications.As forLENP orLETP, aircraft validity are given under FSN values.Wemay consult CRT tohave correspondence between FSN and MSN.

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ATR 42 Model : 400/500

STANDARD NOMENCLATURE



DEC 10

001

0.50.00

ATC Air Traffic ControlATE Automatic Test EquipmentATPCS Automatic Take off Power Control SystemATT AttitudeATTND AttendantAUTO AutomaticAUX AuxiliaryAVAIL AvailableAZ Azimuth

BARO BarometricBAT BatteryBC Back CourseBITE Built in Test EquipmentBPCU Bus Power Control UnitBPU Battery Protection UnitBRG BearingBRK BrakeBRNAV Basic Area NavigationBRT BrightBSC Battery Start ContactorBTC Bus Tie ContactorBTR Bus Tie RelayBXR Battery Transfer RelayCAB CabinCAC Crew Alerting ComputerCAP Crew Alerting PanelCAPT CaptainCAT CategoryC/B Circuit BreakerCCAS Centralized Crew Alerting SystemCCW Counter ClockwiseCD Coefficient of DragCDI Course Deviation IndicatorCDLS Cockpit Dorr Locking SystemCFC Constant Frequency ContactorCG Center of GravityCHAN ChannelCHC Charge ContactorCHG ChargeC/L Check ListCL Condition LeverCL Coefficient of LiftCLA Condition Lever AngleCLB Climb

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COCKPIT PHILOSOPHY

AIRCRAFT GENERAL

P 2A

DEC 05

001

1.00.20

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Seat position sight gaugemay be used for proper setting seat height and fore/aft position.It assures to the crew a correct view of instrument panels as well as runway environment,especially when flying low visibility instrument approaches.

This indicator is composed of three colored balls. Center ball is red and is horizontallyshifted compared with the other two white balls.For proper seat position, respective white ball is obscured by the red one.

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P 12

DEC 05

001

1.01.10

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ATR 42 Model : 400/500

GENERAL

MFC

P 13

DEC 05

001

1.01.10

LEFT INTENTIONALLY BLANK

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ATR 42 Model : 400/500

GENERAL

MFC

P 14

DEC 05

001

1.01.10


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ATR 42 Model : 400/500

GENERAL

MFC

P 15

DEC 05

001

1.01.10


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ATR 42 Model : 400/500

GENERAL

MFC

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DEC 05

001

1.01.10


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GENERAL

CCAS

P 12

DEC 05

001

1.02.10

10.5 LATERAL MAINTENANCE PANEL

On LH maintenance panel, a “WARN” section allows testing, on ground, of severalwarnings which cannot be tested on their own system.This section includes :-- a rotary selector to select the system to be tested ;-- a Push To Test (PTT) pushbutton to activate the selected test.

Note : The rotary selector must be replaced in NORM FLT position before flight.

WARN SECTION

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ATR 42 Model : 400/500

GENERAL

CCAS

P 13

DEC 05

001

1.02.10

ROTARY selectorSystem which can be tested :-- EXCESS CAB ∆P : MW, CRC, “EXCESS CAB ∆P” red light on CAP-- LDGGEARNOTDOWN : MW, CRC, “LDGGEARNOTDOWN” red light onCAP,

red light in landing gear lever.-- PITCH DISCONNECT : MW, CRC, “PITCH DISCONNECT” red light on CAP-- EXCESS CAB ALT : MW, CRC, “EXCESS CAB ALT” red light on CAP-- SMK : MW, CRC, “FWD SMK”, “AFT SMK”, and “ELEC SMK” red lights on CAP-- VMO: clacker-- STICK PUSHER SHAKER -- YES :

S Stall cricket and both stick shakers are activatedS After 5 seconds, GPWS FAULT illuminates amber on CAP *S After 10 seconds : -- CHAN 1, CHAN 2 illluminate

-- Stick pusher is activated-- Stick pusher indicators illuminate green

S Select WARN rotary selector to NORM FLTS Monitor : -- STICK PUSHER lights OFF

-- C/B 14 FU FLT CTL / STICK PUSHER / PWR SUPPLY in.

-- STICK PUSHER SHAKER -- TEST 1 :S Stall cricket and left stick shaker are activatedS After 5 seconds :-- GPWS FAULT illuminates amber on CAP *-- MC, FLT CTL on CAP and stick pusher FAULT pb illuminate amber

-- STICK PUSHER SHAKER -- TEST 2 :S Stall cricket and right stick shaker are activatedS After 5 seconds :-- GPWS FAULT illuminates amber on CAP *-- MC, FLT CTL on CAP and stick pusher FAULT pb illuminate amber

-- STICK PUSHER SHAKER -- TEST 3 :S CHAN 1, CHAN 2 illuminateS Stall cricket and both stick shakers are activatedS After 5 seconds, GPWS FAULT illuminates amber on CAP *

* only when Enhanced GPWS not installed

Note : If ICING AOA is illuminated :-- YES procedure is the same.-- Test 1 procedure is the same except that CHAN 1, CHAN2 illuminate-- Test 2 procedure is the same except that CHAN 1, CHAN 2 illuminate-- Test 3 procedure is the same except that stick pusher is activated in thesame time as shakers.

“CHAN” lightsIlluminate green to check the two angle of attack channels for correct operation.

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RAD PTT SW on NOSE WHEEL STEERING CONTROLHANDWHEEL

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GENERAL

COMMUNICATIONS

P 10

DEC 10

001

1.05.10

EMERGENCY BEACON

The transmitter is located in the ceiling of the cabin between the passengers entrydoor and the toilet door. The antenna is located in the fairing ahead of the stabilizerfin. This system includes its own battery.AUTO transmission is made automatically on 121.5 MHz, 243 MHz and

406 MHz when deceleration exceeds 5 g (X MIT ALERT Itilluminates amber).

MAN allows commanded operation (X MIT ALERT It illuminates amber)AUTO TEST RST Is used in case of undue alert (resert), or to test the emergency

beacon. Two cases are possible for the test :

ELT96A / ELT97A ELT ADT 406

Correct = X MIT ALERT Continuous during 2 Sec Continuous during 10 Sec

Failure = X MIT ALERT Blinking during 10 Sec Blinking during 10 Sec

CAUTION : The test must not be performed in MAN mode.

Aircraft on ground (and electrically supplied), when the emergency beacon is triggeredafter 30 seconds, the mechanical horn is triggered too.

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DISTRIBUTION EQUIPMENT LIST

ELECTRICAL SYSTEM

P 22

DEC 06

001

1.06.60

115 ACW BUS 1

ATA SYSTEM FUNCTION

29 HYDRAULIC -- BLUE PUMP PWR

30 ICE AND RAINPROTECTION

-- CAPT PITOT-- CAPT ALPHA-- CAPT TAT-- STBY PITOT (Normal)

33 LIGHTS -- EMER INSTRUMENTS SPLY INTEGRATED LT(Primary)-- NORMAL INSTRUMENTS SPLY AND LABELSINTEGRATED LT PWR-- LEFT LANDING PWR-- LEFT AND REAR STROBES-- PASSENGERS READING PWR (LEFT SIDE) *

38 WATER / WASTE -- TOILET SYS

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ATR 42 Model : 400/500

DISTRIBUTION EQUIPMENT LIST

ELECTRICAL SYSTEM

P 23

DEC 06

001

1.06.60

115 ACW BUS 2

ATA SYSTEM FUNCTION

24 ELECTRICAL POWER -- TRU CTL

29 HYDRAULIC -- GREEN PUMP PWR

30 ICE AND RAINPROTECTION

-- F/O PITOT-- F/O ALPHA-- F/O TAT-- ICE DETECTOR

33 LIGHTS -- TAXI AND TAKE OFF PWR-- RIGHT LANDING PWR-- RIGHT STROBE-- PASSENGERS READING PWR (RIGHT SIDE) *

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OXYGEN SYSTEM

EMERGENCY EQUIPMENT

P 2

DEC 10

100

1.07.20

20.2 CONTROLS

OXYGEN PANEL

HP ind.Oxygen bottle pressure is displayed in PSI X 1000.

MAIN SUPPLY pbControls the low pressure supply solenoïd valve.pb pressed in : The valve is open, low pressure oxygen is supplied to the cockpit

crew oxygen masks.OFF : (pb released) the valve is closed. OFF illuminates white.LO PR : illuminates amber and theCCAS is activatedwhena lowpressure

(below 50 PSI) is detected in the low pressure distribution circuit.

PAX SUPPLY SWMAN OVRD Controls manually the oxygenmasks unfolding and PAXSUPPLY

Valve opening at cabin altitude between 10000 ft and 25000 ft..AUTO : Oxygen masks unfolding in case of depressurization. The PAX

SUPPLY Valve is connected to the ALT PRESS switch whichengage when cabin altitude is above 13250 ft (+/-- 250 ft).

OFF : Passengers oxygen supply is closed. This position stops the paxoxygen supply and then the oxygen is dedicated to the crew.

PAX SUPPLY “ON” LtA light indicator “ON” illuminates white when the pax supply valve is open.

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EFIS

FLIGHT INSTRUMENTS

P 9

DEC 06

100

1.10.30

EFIS CONTROL PANEL (ECP)

FULL/ARC pbRepetitive action on this pb alternately selects FULL mode and ARCmode on EHSI.At power up, FULL mode is automatically displayed.GSPD/TTG pbRepetitive actions on this pb alternately selects Groundspeed (GSPD) and Time togo (TTG) on EHSI display. At power up, Groundspeed is displayed.This pb is inoperative in composite mode.ADI/DIM/DH/TST knobs-- Outer knob (ADI DIM) is used to select EADI ON/OFF and to set brightness.Automatic setting is also performed when ambient brighness changes.

-- Inner knob (DH TST) is used to set decision height from -- 10 to 990 ft.Depressing it enables a test of the EFIS system and radio altimeter :. Test of the EFIS is only functional on ground, all failure messages appear onEFIS.

. Radio altimeter test is performed in flight as well as on ground. RA indicationdisplays 100 ft on EADI.

CAUTION : In flight, the RA test provides the radar with altitude informationwhich trigger undue GPWS alerts.

HSI/DIM/WX/DIM knobs-- Outer knob (HSI DIM) is used to select EHSI ON/OFF and to set brightness.Automatic setting is also performed when ambient brighness changes.

-- Inner knob (WX DIM) is used to select ON/OFF weather radar traces, and to setaverage brightness in relation to other traces.

N° 1 BRG (0) selectorTo select blue bearing pointer to VOR 1 or to ADF 1 or to GPS active waypoint.On OFF position, blue pointer disappears from EHSI.Note : RNV1 position is inoperative when MAP display is active.N° 2 BRG (◊) selectorTo select green bearing pointer to VOR 2 or to ADF 2 or to GPS active waypoint.On OFF position, green pointer disappears from EHSI.Note : RNV2 position is inoperative when MAP display is active.Refer to 1.15.60.

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Mod : 5567

FLIGHT RECORDERS

FLIGHT INSTRUMENTS

P 1

DEC 06

100

1.10.50

50.1 DESCRIPTION

The aircraft is equipped with :-- a Cockpit Voice Recorder, CVR, and-- a Digital Flight Data Recorder, DFDR.The recorders are automatically energized as soon as the aircraft is on its own electricalsupply and are switched OFF automatically TeN minutes after engines cut. When theaircraft is on external power, recorders are OFF until one engine is started. They can beenergized by selecting ON the RCDR pushbutton, and deenergized by pushing the RESETpushbutton.Each recorder is equipped with an underwater acoustic beacon which is used to locate therecorder in the event of an aircraft accident over the sea. The beacons actuate immediatelyafter immersion. They should transmit a signal on 37.5 kHz for 30 days. The detection rangeis 3.5 km (4,000 yards).

CVR

All crew communications transmitted through the RCAU are recorded.In addition, a CVR microphone, located below the overhead panel, acquires cockpitconversation and aural alerts for recording. Cabin crew announcements are also recorded.Only the last 30 minutes (or 120 minutes, depending on version) are retained. All recordingmay be erased by pressing ERASE pushbutton provided the aircraft is on ground and theparking break is set.

DFDR

Various aircraft parameters are sent to aFlight DataAcquisition Unit (FDAU)whichconvertsthem into digital data.

The data are recorded by the DFDR which stores them on a magnetic tape. The 25 lasthours of flight are retained.

AA

Mod : 5567

FLIGHT RECORDERS

FLIGHT INSTRUMENTS

P 2

DEC 06

100

1.10.50

50.2 CONTROLS

FLIGHT DATA ENTRY PANEL (FDEP)

NOT APPLICABLE

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ATR 42 Model :400/500

FUEL SYSTEM

GENERALP 3

DEC 05

001

1.11.10

ENGINE FEED (See schematic p 13/14)

In normal conditions, each engine is supplied from its associated wing tank. Fuel flow/fuelused ind. allow the crew to monitor fuel consumption for each engine.Each tank is fittedwith a 200 l feeder compartment always full of fuel protecting the enginefeed system against negative or lateral load factors. In the feeder compartment, anelectrical pump and a jet pump are installed. The jet pump is activated by HP fuel from theengine HMU and is controlled by a motive flow valve.

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

In normal operation, the electrical pump is only used to start the engine. After start , jetpump takes over automatically.If jet pump pressure drops below 350 mbar (5PSI), the electrical pump is automaticallyactivated to supply the engine.A crossfeed valve, controlled by an electrically operated actuator, allows both engines tobe fed from one side or one engine to be fed by either tank, allowing control of anunbalance situation.When the crossfeed valve is open, a blue “FUEL X FEED” light comes onmemo panel. Inthis case, the two electrical pumps are automatically actuated. It’s possible to use onlyone fuel tank by switching off the opposite pump pb.At the fuel outlet of each tank a fuel LP valve, controlled by the associated fire handle, isinstalled.

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ENGINE AND WING PROTECTION

ICE AND RAIN PROTECTION

P 3

DEC 09

001

1.13.30

30.2 CONTROLS

ENGINE/WING DE ICING PANEL

AIRFRAME AIR BLEED pb

Controls both de ice and isolation valves.Pb pressed in Normal operation.Both DE ICE and ISOLATION VALVES are open.

OFF (pb released) OFF light comes on white.Both DE ICE and isolation valves are closed.However engine de--icing may be used (engine de--icing selected ONwill open de--ice valve).

But airframe de--icing is never available.

FAULT The light illuminates amber and the CCAS is activated when :-- Air pressure downstream of the de--ice valves stays below 14 PSI.

-- Air temperature upstream of the de--ice valves exceeds 230°C.The alert is inhibited when pb is released.

AIRFRAME pb

Controls the outputs A and B of both wings and stabilizers distribution valves.

ON (pb pressed in) Signal is sent to the MFC in order to initiate ade--icing cycle depending on MODE SEL pb.ON light illuminates blue.

Pb released In normal operation. Associated boots stay deflated.

FAULT The light illuminates amber and the CCAS is activated when inflationsequencing of airframe boots A and B is not correct :-- Associated distribution valve output has been controlled open butno downstream pressure has been detected, or

-- Associated distribution valve output has been controlled closedbut a downstream pressure is detected.

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This mode is active during cruise and approach with gear not in landingconfiguration.When the aircraft penetrates the envelope at a speed higher than 190 kts with gearnot down and locked, the “TOO LOW TERRAIN” voice alert is generated and the red“GPWS” warning lights illuminate.Note that the “TOOLOWTERRAIN”warning area upper limit is reduced to 500 feet ifGeometric Altitude is valid.

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GNSS

NAVIGATION SYSTEM

GLOBAL NAVIGATION SATELLITE SYSTEM P 1

OCT 08

120

1.15.60

60.1 DESCRIPTION

(See schematic p11/12)

Using information provided by a constellation of 24 satellites (the HT 1000 isable to track up to 12 satellites at a time), GNSS is an automatic tridimensional(latitude, longitude, altitude) location and navigation means. It also uses datarecorded in a data base.

The data base is stored in the NPU and is updated every 28 days on the groundusing a specific data loader. The effective date periods are displayed on theMCDU IDENT page.

The navigation is normally performed using the GPS sensor (GPS mode). In thecase of the GPS position becomes unavailable, the HT1000 reverts to DME--DME mode(if installed) and radio coverage allows it. If not, the dead reckoning mode (DR)is used as a back--up using true airspeed, heading and the lastcomputed wind data.

FUNCTIONS

HT 1000 is capable of performing all the functions associated with the great circlenavigation.

It mainly allows to perform:-- ”Direct To” navigation-- Flight plan navigation-- Navigation to nearest airport (or nearest VOR, NDB...)-- Vertical navigation (non coupled to auto pilot)-- Non precision approach

To know all the functions available, refer to the table of contents of the HT 1000pilot’s guide.

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Mod : (4885 or 5020 or 5176) + 5506

GNSS

NAVIGATION SYSTEM

GLOBAL NAVIGATION SATELLITE SYSTEMP 2

DEC 06

190

1.15.60

60.2 CONTROLS

HT 1000 CONTROLS

The MCDU is the pilot interface for operation and data entry of the HT 1000 andalso displays routes and advisory data on a color 5.5” liquid crystal display. Thedisplay has 14 lines of data with 24 characters per line. The MCDU keyboardsprovides for data input and display selection and control.

Two MCDU are installed. Each MCDU is interfaced with its on--side instrumentation.

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Mod : 5506 +(4885 or 5020 or 5176) ATR 42 Model 400/500

GNSS

NAVIGATION SYSTEM


DEC 06

190

1.15.60

EFIS CONTROL PANEL

Map pbRepetitive action on this pb selects alternately MAP display and ARC display onEHSI.In MAP selection, waypoints of the flight plan are displayed in white except theactive waypoint which is magenta.V/L pbAction on this pushbutton causes selection of the VOR/LOC mode.RNV pbAction on this pushbutton causes selection of the GNSS mode.Refer to 1.10.30.

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OCT 08

210

1.15.60

EADI

Alerting messages and displays related to the HT 1000 operation.

(1) RNV MSG is triggered by one of the following messages displayed on the MCDU:-- UNABLE RNP: message annunciated when ANP exceeds RNP or integrity is greaterthan twice the selected RNP (Once the value for approach). The conditions fordisplaying this message are flight phase dependent as follows:

PHASE OF FLIGHT DEFAULT RNP (NM) Unable RNP Time to Alarm (s)

OCEANIC 12 80

EN ROUTE 2 80

TERMINAL 1 60

APPROACH 0.3 10

-- DEAD RECKONING: message annunciated when NAV source becomes dead reckoning(GPS and DME modes are lost).

-- VERIFY RNP ENTRY: message annunciated when the pilot entered RNP is greater thandefault current RNP.

-- VERIFY RNP--POS REF: message annunciated when flight phase changes and currentpilot entered RNP is greater than the default RNP for new flight mode.

-- UNABLE APPROACH: message annunciated when within 2 NM from the FAF, and RAIMprediction at FAF/MAP fails, or navigation source is not GPS.

-- VERTICAL TRACK CHANGE ALERTThis message and annunciator is displayed prior reaching a vertical track change.

-- END OF DESCENTThismessage appearswhenever the aircraft reaches the last altitude constraint on thedescent path.

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GENERAL

POWER PLANT

P 1

OCT 08

001

1.16.10

The engine is a PW127E or PW127M certified for a 2400 SHP max take off rating.However, in normal operation, take off rating will be 2160 SHP with an automatic powerincrease to 2400 SHP (Reserve Take Off rating RTO) in case of other engine failure.

Power setting is characterized by constant power lever and condition lever positions. Thepower adapted to the flight phase is selected by the pilot through a power managementselector.

The engine comprises two spool gas generators driving a six blade propeller via a freeturbine/concentric shaft/reduction gear box assembly. Propeller regulation iselectronically controlled.

The propeller is a HS 568 F.-- Diameter : 3.93 m (12.9 ft)-- Rotation : clockwise (looking forward)-- 100% NP : 1200 RPM-- Weight : 180 kg.

The engine accessories are mounted on two accessory gear boxes, one driven by the HPspool, and one by the propeller reduction gear box.

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ATR 42 Model : 400/500

CONTENTS

LIMITATIONS

P 1

OCT 08

001

2.01.00

2.01.00 CONTENTS

2.01.01 GENERAL

2.01.02 WEIGHT AND LOADING

2.01.03 AIRSPEED AND OPERATIONAL PARAMETERS

2.01.04 POWER PLANT

2.01.05 SYSTEMS

2.01.06 TCAS (if installed)

2.01.07 GPS (if installed)

2.01.08 CABIN LIGHTING

2.01.09 TAWS (if installed)

2.01.10 COCKPIT DOOR SECURITY SYSTEM (if installed)

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CAUTION : Rapidly alternating large rudder applica-tions in combination with large sideslipangles may result in structural failure atany speed.

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AIRSPEED AND OPERATIONAL PARAMETERS

LIMITATIONS

P 3

APR 08

001

2.01.03

V1 limited by VMCG (FLAPS 15)

CAUTION : INCREASE BY 1.5 KT FOR TAKE--OFF BLEED ON

--40 --30 --20 0 10 20 30 40 50

OUTSIDE AIR TEMPERATURE (DG.C)

80

84

88

92

96

100

104

AA

APR 08

R

ATR 42 Model : 500

AIRSPEED AND OPERATIONAL PARAMETERS

LIMITATIONS

P 5

DEC 10

001

2.01.03

OPERATIONAL PARAMETERS

ENVIRONMENTAL ENVELOPE

Altitude Zp (ft)

TAKE--OFF AND LANDING

TAIL WIND LIMIT : 15 KT

MAXIMUM MEAN RUNWAY SLOPE : ± 2 %

CROSS WIND

The maximum demonstrated cross wind is :-- Take off: 45 kt. . . . . . . . . . . . . . . . . . . . . . . . . . .-- Landing Flaps 25�: 45 kt. . . . . . . . . . . . . . . . . . .

Flaps 35�: (*) 44 kt. . . . . . . . . . . . . . . . . . .

Braking Action TO LDG Maximum Crosswind

(TO and LDG)

GOOD 1 1 (*) 45 kt

GOOD/MEDIUM 2 2 37 kt

MEDIUM 3 -- 6 5 / 6 30 kt

MEDIUM/POOR 4 5 22 kt

POOR 7 7 15 kt

Runway status: 1: dry runway, 2:wet up to 3mm depth, 3 (TO only): slush or water from 3 to6mm depth, 4 (TO only):slush or water from 6 to 12.7mm depth,5: slush or water from 3 to 12.7mm depth, 6: compact snow, 7: ice

AA

R

R


POWER PLANT

LIMITATIONS

P 1

OCT 08

001

2.01.04

ENGINES

ENGINE PARAMETERS

Operating limits with no unscheduled maintenance action required.

Beyond these limits, refer to maintenance manual.

OPERATINGCONDITION

TIMELIMIT

TQ(%)

ITT(C)

NH(%)

NL(%)

NP(%)

OIL PRESS(PSI)

OIL TEMP(C) (2)

RESERVETAKE OFF

10 mn(6)

100 (1) 800 103.2 104.2 101 55 to 65 0 to 125

NORMALTAKE OFF

5 mn 90 (1) (5) 101.9 101.4 101 55 to 65 0 to 125

MAXIMUMCONTINUOUS

NONE(6)

100 (1) 800 103.2 104.2 101 55 to 65 0 to 125

GROUNDIDLE

66mini

40 mini(4)

-- 40 to 125

HOTEL (7)

MODE715 55 to 65 125

TRANSIENT 20 s 137.5 840 104.3 106.5 106 (3) 40 to 100

5 s 120

20 mn 140

STARTING 5 s 950 -- 54 mini

1) Value linked to 100 % NP.

2) Oil temperature must be maintained above 45 C to ensure protection for theengine air inlet against ice accumulation.

3) Permissible for completion of flight provided TQ does not exceed 85 % duringclimb and 84 % during cruise.

4) Up to 75 % NH only.

5) ITT limits depend on outside air temperature. Refer to 2.01.04 p 3.

6) --RTO : Time beyond 5 mn is linked to actual single engine operations only.--MCT rating is the max power certified for continuous use. In--flight

emergencies are the only conditions for which MCT use is authorized.

7) A qualified person is required to use engine 2 in HOTEL mode.

Note : Flight with an engine running and the propeller feathered is not permitted.

AA

RRR

R


POWER PLANT

LIMITATIONS

P 2

APR 08

001

2.01.04

AA

R

APR 08

R

APR 08

POWER PLANT

LIMITATIONS

P 5

OCT 08

001

2.01.04

STARTER

3 STARTS WITH A 1 MINUTE 30 SECONDS MAXIMUM COMBINED STARTERRUNNING TIME, FOLLOWED BY 4 MINUTES OFF

OIL SYSTEM

Approved lubricating oils

-- Aero Shell Turbine oil 500-- Aero Shell Turbine oil 560-- Royco Turbine oil 500-- Royco Turbine oil 560-- Mobil Jet oil II-- Mobil Jet oil 254-- Castrol 4000-- Castrol 5000-- Exxon Turbo oil 2380

Mixing of different brands of oil or viscosities of oil is not recommended.

FUEL SYSTEM

-- Use of JP 4 or JET B is prohibited.

-- Acceptable fuels (refer to PWC Documentation to determine equivalent approved fuels).

FUELS FREEZING POINT

MINIMUM FUEL TEMP (∞C) MAXIMUMFUEL TEMPFUELS FREEZING POINT

(∞C) Starting OperationFUEL TEMP

(∞C)

JET A -- 40 -- 34 -- 38 + 57JET A

JET A1

RT, TS1

-- 40

-- 50

-- 60

-- 34

-- 34

-- 34

-- 38

-- 48

-- 60

+ 57

+ 57

+ 57

JET A1

RT, TS1

JP 5

-- 50

-- 60

-- 46

-- 34

-- 34

-- 26

-- 48

-- 60

-- 33

+ 57

+ 57

+ 57

RT, TS1

JP 5

-- 60

-- 46

-- 34

-- 26

-- 60

-- 33

+ 57

+ 57

-- Approved anti icing additives (maximum concentration allowed : 0.15 % per volume) :

-- Philips PFA 55 MB

-- MIL--I --27 686 D

-- Ethylene Glycol Monomethyl Ether as defined in MIL--I --27 686 E.

AA

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DEC 07

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SYSTEMS

LIMITATIONS

P 2

DEC 07

100

2.01.05

OXYGENMinimum flight crew oxygen pressurewith andwithout observer and capacitywith full pax(50 cabin occupants).

TOFA--02--01--05--002--A

100AA

MINIMUM BOTTLE PRESS(STANDARD CONDITION 21°C)

(PSI)

MIN

BOTTLEPRESS

INDICATION(PSI)

AVAILABLE TIME AFTERDECOMPRESSION

HOLDING ALTITUDE

This graph gives the minimum bottle pressure required after loss of cabin pressure toprovide crew members and 100 % of passengers protection with diluted oxygen duringdescent from FL 250 to holding level followed by descent to FL100 (rate 3000 ft/minutes).

Reference Temperature = Cabin Temperature or OAT whichever is higher, on ground.= Cabin Temperature, in flight.

Note : -- At dispatch the computed flight time after decompression should be at least1/2 of estimated flight time to destination or flight time to the longest en routealternate which ever is higher.Provision is made to cover :

-- unusuable quantity-- normal system leakage-- Ref. Temp errors

AA

R

ATR 42 Model : 400/500

TCAS

LIMITATIONS

P1

DEC 07

050

2.01.06

TCAS

Applicable only when a ATR TCAS solution is installed. In case of TCAS STC(Supplier Type Certificate) solution installed, operator must consider STC

provider documentation.

LIMITATIONS

The limitations in Part 2.01 are applicable with the addition of the following:

1-- TCAS operation is approved for use in VFR meteorological conditions (VMC) andIFR meteorological conditions (IMC).

2-- The pilot must not initiate evasive maneuvers using information from the trafficdisplay only or from a traffic advisory (TCAS TA) only.These displays and advisories are intended only for assistance in visually locatingthe traffic and lack the resolution necessary for use in evasive maneuvering.

3-- Compliance with TCAS resolution advisory is required unless the pilot considers itunsafe to do so.

However, maneuvers which are in the opposite direction of the resolution advisory(TCAS RA) are extremely hazardous and are prohibited unless it is visuallydetermined they are the only means to assure safe separation.

CAUTION : Once a non crossing RA has been issued the vertical speed should beaccurately adjusted to comply with the RA, in order to avoid negatingthe effectiveness of a co--ordinated maneuvre by the intruder.

WARNING : Non compliance with a crossing RA by one airplane may result inreduced vertical separation. Therefore, safe horizontal separationmust also be assured by visual means.

4-- Evasive maneuvring should be made with the autopilot disengaged, and limited tothe minimum required to comply with the RA. The pilot must promptly return to theprevious ATC clearance when the TCAS “CLEAROF CONFLICT” voice message isannounced.

5-- Prior to perform RA’s climb or increase climb, the crew should select the appropriateengine power setting on the power MGT rotary selector and, if necessary, manuallyadjust 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--around shouldbe followed including the appropriate power increase and configuration changes.

AA

R

RRR

R

R ATR 42 Model : 400/500

TCAS

LIMITATIONS

P 2

DEC 07

050

2.01.06

TCAS (CONT’D)



7-- Because of the limited number of inputs to TCAS for determination of aircraftperformance inhibits, there are instances where inhibiting RAs would beappropriate, however it is not possible to do so. In these cases, TCASmay commandmaneuvers which may significantly reduce stall margins or result in stall warning.Conditionswhere thismay occur include operationswith a bank angle (wings level isassumed), weight, altitude and temperature combinations outside those notedbelow, leaving aircraft in landing configuration during climb RAon approach, engineout operations, and abnormal configurations such as landing gear not retracted orstick pusher/shaker failure.

The table below entitled “Flight Envelope in which climb resolution advisory can beaccomplished without stick pusher/shaker activation” outlines the parameters usedin the development of the performance inhibits. This table does not consider worstturboprop flight conditions especially operations using minimum operatingairspeeds as are sometimes required (e.g. obstacle clearance, ATC constraints). Inall cases, stall warning must be given precedence over climb RA commands.

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

WARNING : Priority must be granted to increasing airspeed when reaching stallwarning even when this requires deviation from an RA commandissued by the TCAS.

AA

R

RRR

R ATR 42 Model : 400/500

TCAS

LIMITATIONS

P 3

DEC 07

050

2.01.06

TCAS (CONT’D)



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

FLIGHTG

WEIGHTALTITUDE POWER FLAPS GEAR

AIRSPEED

REGIME ALTITUDETEMP.

POWER FLAPS GEARINITIAL MIN.

Take off FAR25/JAR25

Climb limit

Take off 15 Up V2 + 20 1.13 VSR

Approach FAR25/JAR25

Climb limit

Spin up to go aroundpower duringmaneuver from

power for level flight

15 UP 1.51VSR

1.13 VSR

LandingTransitioningto go around

at RA

FAR25/JAR25

Climb limit

Spin up to go aroundpower during maneuverfrom power required for

3° Glide Slope

Transitionfrom

35 to 15

DNtoUp

VAPP+10 1.13 VSR

Enroute Critical Wt/Alt

giving 1.3Gto

buffet onset

Power for level flightincrease to MaxContinuous

Up Up LongRangeCruise

Higher of1.13 VSR ifdefinedor buffetonset

Temperature range up to ISA + 27°

-- Enroute 0 25000 ftAltitude range -- Take off 0 6000 ft

-- Approach and landing 0 7000 ftWings Level Assumed

AA

R

RRR

R ATR 42 Model : 400/500

TCAS

LIMITATIONS

P 4

DEC 07

050

2.01.06

TCAS (CONT’D)



8-- Inhibition schemes

8.1-- Non icing conditions

CONFIGURATION RA CLIMB RA INCREASE CLIMB

FLAPS 0FLAPS 15 TOFLAPS 25 TOFLAPS 15 ApproachFLAPS 25 ApproachFLAPS 25 LandingFLAPS 35 Landing

AUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZED

AUTHORIZEDINHIBITEDINHIBITEDINHIBITEDINHIBITEDINHIBITEDINHIBITED

8.1-- Icing conditions

CONFIGURATION RA CLIMB RA INCREASE CLIMB

FLAPS 0FLAPS 15 TOFLAPS 25 TOFLAPS 15 ApproachFLAPS 25 ApproachFLAPS 25 LandingFLAPS 35 Landing

AUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZEDAUTHORIZED

AUTHORIZEDINHIBITEDINHIBITEDINHIBITEDINHIBITEDINHIBITEDINHIBITED

NOTE 1 : Pilots are authorized to deviate from their current ATC clearance tothe extent necessary to comply with a TCAS resolution advisory.

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

AA

R

RRR

R Mod : 5205 ATR 42 Model : 400/500

TCAS

LIMITATIONS

P 5

DEC 07

080

2.01.06

TCAS (CONT’D)



NORMAL PROCEDURES

The normal procedures in Part 2.03 are applicable.

EMERGENCY PROCEDURES

The emergency procedures in Part 2.04 are applicable.

PROCEDURES FOLLOWING FAILURES

The procedures following failures in Part 2.05 are applicable with the addition of thefollowing:

The TCAS must be turned TA ONLY in the following cases:

--Engine out operations

--Stick pusher/shaker failure

--Flight with landing gear down

The TCAS must be turned STBY in the following cases:

--ATC request

--LOSS OF RADIO ALTIMETER INFORMATION

--Errors or differences between independant air data sources

PERFORMANCES

The performances in Part 3 are applicable.

AA

R

RRR

Mod : 5768 ATR 42 Model : 400/500

GPS

LIMITATIONS

GLOBAL POSITIONING SYSTEM P 1

APR 08

700

2.01.07

GPS

1 - GENERAL

The Honeywell/Trimble GNSS HT1000 :

- complieswithTSOC129andTSOC115B,- is installed incompliancewith, AC20--130Aand AC20--138 fornavigationuse- is installed incompliancewithFAAAC20--129 for theadvisoryBaro--VNAVuse- hasbeendemonstrated tomeet primarymeansofnavigation inoceanic/remoteareasinaccordancewithFAANotice8110--60orequivalent indualHT1000configuration.

- hasbeendemonstratedtomeet theEn--routecontinental B--RNAVrequirementsofJAATGLno2,REV1orequivalent in singleordualHT1000configuration.

- hasbeendemonstrated tomeet theP--RNAVrequirementsof JAATGLno10.- hasbeendemonstratedtomeettheRNAV(GNSS)non--precisionapproachrequirementofAC20--138andRNPAPCHspecificationboth insingleordualHT1000configuration.

2 - LIMITATIONS

Compliance with the above regulations does not constitute an operationalapproval/authorization to conduct operations. Aircraft operators must apply to theirAuthority for such an approval/authorization.

- The HT1000pilot’sguidemust beavailableonboard.- The system must operate with HT1000--060 software version or any later approvedversion.

- Theapprovalof thesystem isbasedontheassumptionthat thenavigationdatabasehasbeenvalidated for intendeduse.

- Thissystem isapproved indual configuration for use for oceanicand remoteoperationsasaprimarynavigationmeans.

- In single HT1000 configuration, the system is approved for use for oceanic and remoteoperationswhenonlyone long rangenavigationsystem is required.

- This system is approved forRNAVEn--route continental (B--RNAV) and RNAV terminalareaoperations likeRNAVSID/STAR(P--RNAV).NOTE : This system is approved in any of the following configurations: AP coupling,

FD only or raw data (HSI information).

.../...

AA

Mod : 5768 ATR 42 Model : 400/500

GPS

LIMITATIONS

GLOBAL POSITIONING SYSTEM P 1A

APR 08

700

2.01.07

GPS (CONT’D)- This system is also approved as a supplemental navigation means for conventionalEn--route continental operations, conventional terminal operations (SID/STAR) andconventional non--precision approach (e.g. NDB, VOR/DME, LOC,...) provided :SApproved navigation equipments, other than GNSS, required for the

route to be flown are installed and operational.SWhen thesystem isused to flynon--precisionapproachnot promulgatedasRNAV(GNSS)approachorwhenprocedurecoordinates(SID/STAR,Approach)cannot beguaranteedas WGS84, rawdata(conventional navigation information)aredisplayed toverify thecorrectRNAV(GNSS)guidance.

- Both single and Dual HT1000 configurations are approved for RNAV (GNSS)non--precision approach provided:SThe crew respects the published MDA (without VNAV credit)SThe published approach procedure is referenced to WGS84 coordinatesor equivalent.SBefore starting the approach, crew checks that for dual configuration atleast one GNSS is operating without DGR annunciation or for singleconfiguration GNSS is operating without DGR annunciation.SAPP annunciation must be displayed in cyan on EHSI for final approach.NOTE : Pilots intending to conduct an RNP APCH procedure must fly the full leg

starting from IAF otherwise the system will not switch to APP mode (RNPand EHSI scale will remain at 1NM)

SRNAV(GNSS)non--precisionapproachesareperformedonly if anon--GNSS approachprocedure isavailableat destinationorat alternatedestination.SRNAV(GNSS)non--precisionapproachesmust beaborted incaseofDGRannunciationonEHSI and/orUNABLERNPmessageonMCDUaffecting theRNAV(GNSS)used forguidance.SApproved navigation equipments, other than RNAV(GNSS), required forthe approach to be flown (at destination and at any required alternateairport) are installed and operational.NOTE : ILS, LOC, LOC BC, LDA, SDF and MLS approaches are not covered.

- The RNAV (GNSS) system is approved for use as advisory Baro--VNAV system.NOTE : VDEV functionmust be permanently cross--checked by conventional means

(primary altimeters displays)- If GNSS must be used in oceanic/remote area, B--RNAV (if DME are not available),P--RNAV or for approach phases, the availability of the GPS integrity (RAIM or FDEfunctions)must be checked by the operator using prediction tool available in theGNSSduring the pre--flight planning phase or any other approved tool.

.../...

AA

Mod : 5768 ATR 42 Model : 400/500

GPS

LIMITATIONS

GLOBAL POSITIONING SYSTEM P 1B

APR 08

700

2.01.07

GPS (CONT’D)

3 - PROCEDURES FOLLOWING FAILURE

- DUAL GNSS :

SFor RNAV (GNSS) non--precision approach : in the event of both DGRalarm illuminations or if “VERIFY POSITION” message occurs, performa go around unless suitable visual reference is available.

SIn case of loss of navigation or navigation degradation leading to the lossof the required navigation performance crew must inform ATC and revert toalternate navigation means.

- SINGLE GNSS :

SFor RNAV (GNSS) non--precision approach, in the event of DGR alarmillumination or if “UNABLE RNP” message occurs, perform a go aroundunless suitable visual reference is available.

SIn case of loss of navigation or navigation degradation leading to the lossof the required navigation performance crew must inform ATC and revert toalternate navigation means.

AA

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R

R Mod : 5313 or 5467 ATR 42 Model : 400/500

TAWS

LIMITATIONS

P 1

OCT 08

110

2.01.09

TAWS

1 -- Navigation is not to be predicated on the use of the terrain display.

Note :The Terrain Display is intended to serve as a situational awareness tool only. It doesnot have the integrity, accuracy or fidelity on which to solely base decisions for terrainor obstacle avoidance.

2 -- To avoid giving nuisance alerts, the predictive TAWS functions must be inhibited whenlanding at an airport that is not included in the airport database.

AA

ATR 42 Model : 400/500

CONTENTS

PROCEDURES AND TECHNIQUES

P 1

DEC 10

001

2.02.00

2.02.00 CONTENTS

2.02.01 OPERATING SPEEDS

2.02.02 DATA CARD

2.02.03 AIR

2.02.04 AFCS

2.02.05 ELECTRICAL SYSTEM

2.02.06 FLIGHT CONTROLS

2.02.07 FUEL SYSTEM

2.02.08 ADVERSE WEATHER

2.02.09 LANDING GEAR/BRAKES

2.02.10 FLIGHT PATTERNS

2.02.11 POWER PLANT

2.02.12 FLIGHT CHARACTERISTICS

2.02.13 GPS/GNSS (*)

2.02.14 FLIGHT INSTRUMENTS

2.02.15 TCAS (*)

2.02.16 GPWS

2.02.18 Reserved

2.02.19 HIGH LATITUDE OPERATIONS

2.02.20 Operations below - 35°°°° C ground temperature (*)

2.02.21 MPC Multi Purpose Computer (*)

2.02.22 ACARS Aircraft Communication Addressing and Reporting System(*)

2.02.23 Video cabin system (In Flight Entertainement) (*)

(*) : if installed / if applicable

AA

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Mod. : 1112 ATR 42 Model : 400/500

AFCS


P 8

DEC 10

020

2.02.04

CAT 2 OPERATIONS

� GENERAL

CAT 2 approaches are flown with AP + FD ON.

� EQUIPEMENT REQUIRED

Approach with AP

Autopilot 1

FD bars 1 (PF side)

AP quick disconnect 1 (PF side)

AP OFF warning (lightand aural)

1

ADU 1

ILS receiver 2

AHRS 2

Standby Horizon 1

CRT 3 (2 PF side)

SGU 2

Radio altimeter 1 (with 2 displays)

DH indicator 2

GA pushbutton 1 (PF side)

Windshield wipers 1 (PF side)

Yaw damper 1

Airspeed indicators2: -- CM2 side must be operative (*)

-- If CM1 is PF, CM1 side must be operative

Altimeters 3

Hydraulic system Blue + Green

Electrical systemDC: BUS1 / BUS2 / EMER / STBY / ESS ;

AC: BUS1 / BUS2 / STBY ; ACW: BUS1 / BUS2

MFC modules 3

(*): The standby airspeed instrument can be easily monitored only from the CM1position (Captain position).

AA

R

Mod. : 1112 + 4583 ATR 42 Model : 400/500

AFCS


P 9

DEC 10

210

2.02.04

Maximum demonstrated crosswind:

AutoPilot

Headwind 30 kt

Tailwind 13 kt

Crosswind 25 kt

� TASK SHARINGThe philosophy of the task sharing is based on the following considerations:

- PF(�) task is aircraft flying during all the approach, he is in charge of speedcontrol. Approaching DH + 100ft, he looks outside to acquire external visualreferences.He makes decision for landing or go--around.

- PNF(�) task is approach monitoring with permanent reference to the instruments.

(�)PF, pilot flying,-- Monitors the A/C position, the flight path parameters and the AP.-- Controls the speed.-- Requests checklist, flaps setting and gear extension.-- Selects the modes and announces changes.

(�)PNF, pilot non flying,-- Is in charge of radio communications.-- Monitors the flight path, the speed, themode changes, the systemsand

the engines.-- Reads the checklist.-- Selects flaps setting and gear extension.

� NORMAL APPROACH AND LANDING SEQUENCE

� Prior to approach

� DESCENT procedure (PF / PNF):-- Last weather information reviewed (destination and alternate).-- Landing data collecting and ASI and TQ bugs setting(refer to 2.03.14 p1 for bugs setting description).-- Approach briefing stating runway in use, MSA, DH,missed approachprocedure, radio aids setting...

� APPROACH procedure (PF / PNF):-- AP/FD coupled PF side.-- Speed references set (VAPP, VGA, VmLB).-- Markers volume set.-- DH setting confirmed.

... / ...

AA

R

Mod. : 1112 ATR 42 Model : 400/500

AFCS


P 10

DEC 10

020

2.02.04

� Before capture� PF has to perform the following tasks:

-- NAV set to ILS frequency, ADF set as required.-- CRS set to final approach course.-- APP armed.-- IAS as required.

� PNF has to perform the following task:-- NAV and ADF set as required

� From capture to decision height

Note: The call --outs are written in bold with “ ...”.

CAT 2 eventsTasks and call- outs

CAT 2 eventsPF PNF

Localizer capture “LOC STAR”-- Set runway HDG-- Set ILS on NAV & CRS-- Check CAT 2 on ADU

Glide slope capture “GS STAR”Set GA altitude

Glide slope capture “GS STAR”

Check GA altitude

Set GA altitude

Check GA altitude

Set GA altitude

Request normal sequence for LDG config-uration

Set LDG configuration in sequence

(�): Outer marker orequivalent position (not

lower than 1000ft)Check altitude on RA and altimeter, and ifaircraft is stabilized

“WE CONTINUE”

“OUTER (�) ALTITUDECHECKED, STABILIZED(�)”

Check altitude on RA and altimeterand if aircraft stabilized

800 ft RA (�)

Check dual coupling and no star on LOCand G/S modes

“CHECK”

“800 FT, DUAL CPL, NO STAR“

Check dual coupling and no star on LOCand G/S modes

500 ft RA “500”

DH + 100 ft RA

Looks outside for visual references

“100 ABOVE”

Monitors the instruments

DH / auto call--out “DECISION”

(�): Stabilized means:-- On the final approach segment flight path.-- Landing flaps selected, VAPP reached.-- Final checklist completed.

(�):Anyfailure that isnotcompletely treatedbefore800ftAGL,or thatoccursbelow800ftAGLshall always lead toamissedapproach.

AA

R

Mod. : 1112 ATR 42 Model : 400/500

AFCS


P 11

DEC 10

020

2.02.04

� If visual references sufficient


CAT 2 eventsPF PNF

Visual at DH “LANDING”

80 ft RADisconnect AP

“80”80 ft RADisconnect AP

“80”

50 ft RA “50”

20 ft RA

Reduce PL and flare visually

“20”

� If visual references insufficient


CAT 2 eventsPF PNF

No visual at DH “GO AROUND, SET POWER,FLAPS ONE NOTCH”

-- Press GA pb-- Advance PL to the ramp-- Follow FD bars

-- Retract flaps one notch-- Adjust power

Positive rate of climb-- Request gear retraction

“POSITIVE CLIMB”-- Request gear retraction-- Request HDG, low bank, IAS, VGA-- Request AP engagement

“POSITIVE CLIMB”

-- Retract gear-- Select HDG, low bank, IAS, VGA-- Request AP engagement -- Select HDG, low bank, IAS, VGA-- Engage AP

AA

R

12

DEC 10

PF

PF

PF

PNF

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PNF

PNF

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FUEL SYSTEM


P 1

DEC 10

001

2.02.07

FUEL CROSSFEEDAllows feeding of 1 or 2 engines from either side tank, especially for fuel balancing.

PROCEDURE :

Intended tank to be used :

PUMP RUN and OFF LT extinguished. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

X FEED IN LINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Opposite tank :

PUMP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

When asymmetrical feeding is completed:

PUMPS both ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

X FEED X LINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note: Each electrical pump is able to supply one engine in the whole flightenvelope.One electrical pump and associated jet pump are able to supply both engines inthe whole flight envelope.When X FEED is selected « in line », both electrical pumps are forced to run(both RUN lights illuminate green) as long as associated PUMP pb is selectedON.

CAUTION : When X FEED procedure is applied, some fuel transfer from the wing tankwhere the pump is running to the other wing tank (where the pump is OFF)may occur. This transfer is particularly noticeable at low power settings (XFEED in Hotel mode is the worst case).

FUEL QUANTITY INDICATIONS

IN FLIGHTAccurate readings require aircraft levelledwithout side slip and pitch attitude close tozerodegree.

ON GROUNDAccurate readings should bemadewith aircraft static (not taxiing) and fuel pumps runningfor more than 4 minutes.

This procedure should be applied each time a comparative reading before and after flightis intended with correlation to fuel used.

COMMENTS-- Fuel quantity indications are affected by excessive longitudinal and lateral attitudes

and accelerations.

-- Fuel quantity indications are affected by the level of fuel in the feed tank. With pumpsrunning, the feed tanks are filled within a few minutes. This is the normal flight case.

AA

RRRRRRR

ATR 42 Model : 400/500

ADVERSE WEATHER


P 1

DEC 09

001

2.02.08

This chapter is divided in four parts :

-- Icing,-- Cold weather operations,-- Operations in wind conditions

-- Volcanic Ash encounter

ICING

I - GENERAL

Icing conditions are defined as follows :

� Atmospheric icing conditions.

Atmospheric icing conditions exist when OAT on ground and take--off is at orbelow 5°C or when TAT in flight is at or below 7°C and visible moisture in the airin any form is present (such as clouds, fog with visibility of one mile or less, rain,snow sleet and ice cristals).

� Ground icing conditions

Ground icing conditions exist when the OAT is at or below 5°C when operating onramps, taxiways and runways where surface snow, standing water or slush ispresent.

� Regulatory requirements

Certification requirements defined in JAR/FAR 25 appendix C consider droplet sizesup to 50 microns in diameter. No aircraft is certified for flight in conditions withdroplets larger than this diameter.

However, dedicated flight tests have linked unique ice accretion patterns toconditions of droplet sizes up to 400 microns. Procedures have been defined incase of inadvertent encounter of severe icing.

� Organization of this subchapter

It will address the following areas :

� Operations within the certified envelope.

� Information about severe icing beyond the certified envelope.

� Good operating practices.

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ATR 42 Model : 400/500

ADVERSE WEATHER


P 17

DEC 10

001

2.02.08

CAUTION : Wing, tailplane, vertical and horizontal stabilizers, all control surfaces andflaps should be clear of snow, frost and ice before take off.

PARTICULAR CASE : limited frost accretion on lower wing surfaces due to cold fuelremaining and high ambient humidity.

As stated in the operational requirements, no person may take off an aircraft whenfrost snow or ice is adhering to thewing, control surfaces or propeller of the aircraft.

FROST : frost is a light, powdery, crystalline ice which forms on the exposedsurfaces of a parked aircraft when the temperature of the exposedsurfaces is below freezing (while the free air temperaturemay be abovefreezing).

Frost degrades the airfoil aerodynamic characteristics. However, should the takeoff be conducted with frost adhering to the lower surface of the wing, check thefollowing :

-- The frost is located on the lower surface of the wing only.

-- Frost thickness is limited to 2 mm.

-- A visual check of the leading edge, upper surface of the wing, control surfacesand propellers is performed to make certain that those surfaces are totallycleared of ice.

-- Performance decrement and procedures defined for take off in atmosphericicing conditions are applied.

� DE ICING / ANTI ICING PROCEDURE

-- External de--/anti --icing will be performed as close as possible from take--off time inorder not to exceed the hold over time.Type 1 (low viscosity) or type 2/4 (high viscosity) fluids are used for these operations.The type 2/4 fluids are used for their anti icingqualities. As airflow increases the fluid isspread through the elevator gap and over the lower surface of the elevator.Depending on the brand of the fluid and the OAT, this phenomenon may temporarilychange the trim characteristics of the elevator by partially obstructing the elevator gap.This may lead to a considerable increase in control forces necessary to rotate. Thiseffect is most pronounced when center of gravity is forward.

-- To ensure the best possible tailplane de--/anti --icing, all along the fluid spraying, thepitchwheelmust be firmlymaintained on the forward stop togetherwith the aileron gustlock engaged.

-- De--/anti --icing may be performed in Hotel mode provided BLEEDS are selected OFF.If a de icing gantry is used, both engines must be shut down. For manual propeller deicing, the enginesmust be shut down and air intake blanked or precaution taken not tohave de icing fluid in the air intake. No propeller blade should be located at 6 o’clockposition during this procedure.

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ATR 42 Model : 400/500

ADVERSE WEATHER


P 23

DEC 09

001

2.02.08

VOLCANIC ASH ENCOUNTER

1- VOLCANIC ASH DESCRIPTION

Volcanic ash is, essentially, extremely fine particles of glass shards and pulverized rock,the composition of which reflects the composition of the magma inside the volcano.It is composed predominantly of siliceous materials (> 50%) that are both very hard andvery abrasive. The melting point of glassy silicates is around 1100�C that is close to theoperating temperature of the engine at cruise thrust.The ash is accompanied by gaseous solutions of sulphur dioxide (sulphuric acid) andchlorine (hydrochloric acid).

2- AVOIDANCE

Flight operations in volcanic ash are extremely hazardous andmust be avoided. Flights inareas of known volcanic activity must be avoided.When a flight is planned into an area with known potential for volcanic activity:

-- All NOTAMSand air traffic advisories have to be checked for current status of volcanicactivity.-- The planned route has to well avoid the area of volcanic activity.-- If possible, stay upwind of volcanic ash.

The first two or three days following an explosive eruption are especially critical becausehigh concentration of gas with hazardous concentration could be encountered at cruiselevels some considerable distance from the volcano. Beyond three days, it is assume thatif the ash is still visible by eye or from a satellite data, it still presents a hazard to aircraft.

3- DETECTION

Volcanic ash cloud does not produce ”return” or ”echoes” on the airborne weather radar.Volcanic ash may be difficult to detect visually, especially at night or on instrumentalmeteorological conditions. However, the following have been reported by flight crew:

-- Acrid odor, similar to electrical smell, burned dust or sulfur.-- Smoke or dust appearing in the cabin and cockpit, leaving a coating on cabin andcockpit surfaces.-- Multiple engine malfunctions, such as stall, increase ITT, flameout.-- Airspeed fluctuating erratically.-- At night, static electric discharges (St. Elmo’s fire) visible around the cockpitwindshields.-- At night, landing lights cast sharp, distinct shadows on the volcanic ash clouds asopposed to the normally fuzzy, indistinct shadows cast on water / ice clouds.

4- EFFECTS ON POWERPLANT

The melting point of volcanic ash is close to the operating temperature of the engine atcruise power. This can cause serious damage in hot section of the engine that could resultin engine thrust loss and possible flame out. (.../...)

AA

ATR 42 Model : 400/500

ADVERSE WEATHER


P 24

DEC 09

001

2.02.08

4- EFFECTS ON POWERPLANT (CONT’D)

Pilots are therefore asked to reduce engine power settings to flight idle when possible tolower the engine operating temperature below the melting point of volcanic ash.

The volcanic ash, being abrasive, also damage engine components causing loss ofengine thrust. The erosion also results in a decrease in the engine stall margin. Althoughthis abrasion effect takes longer than the melting fusion of volcanic ash to shut down theengine, the abrasion damage is permanent and irreversible. Reduction of engine thrust toidle slows the rate of erosion by the compressor blades but can not eliminate it entirelywhile the engine is still ingesting air contaminated by volcanic ash.

Propeller blades may also be degraded by erosion inducing loss of traction efficiency.

Oil cooler efficiency may also be decreased either due to excessive erosion of the cooleror due to blockage of the air intake by ashes.

5 - EFFECTS ON THE AIRFRAME AND EQUIPMENT

Volcanic ash abrades cockpit windows, airframe and flight surfaces. Any parts protrudingfrom airframe such as antennas, probes, ice detectors can be damaged and may berendered inoperable.

-- The abrasion of the cockpit window reduces the pilot’s forward visibility. This can leadto serious problems during landing phase.-- The abrasion damage of the wing or horizontal stabilizer leading edges can eitherprevent the correct operation of the de--icing boots or even detached parts of the bootswith subsequent drag increase.-- The abrasion damage of the landing lights can significantly reduce landing lighteffectiveness.-- Damage to the antennas can lead to a complete loss of HF communications and adegradation of VHF communications.-- Damage to the various sensors can seriously degrade the information available to thepilot through the instrument.

Volcanic ash can obstruct probes and penetrate into air conditioning and equipmentcooling system. It can contaminates electrical and avionic units, fuel and hydraulicsystem and smoke detection system.

-- Pitot probe can be blocked by volcanic ash resulting in unreliable airspeed indicationsor complete loss of airspeed indication in the cockpit.

Volcanic ash columns are highly charged electrically. The static charge on the aircraftcreates a ”cocoon” effect which may cause a temporary defection, or even complete lossof VHF or HF communication with ground stations.

(.../...)

AA

ATR 42 Model : 400/500

ADVERSE WEATHER


P 25

DEC 09

001

2.02.08

6 - PROCEDURE

VOLCANIC ASH ENCOUNTER

FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180 DEGREESTURN AND STARTING DESCENT (IF MSA PERMITS)

ATC NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 (if conditions permit) RETARD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPEED BUG TO VmHB SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HDG MODE HIGH BANK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CREW OXY MASKS ON / 100%. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN CREW NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PASSENGER OXYGEN AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIR FLOW HIGH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIRPEED INDICATORS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note: Reducing TQ reduces ash ingestion, maximizes engine surge margin andlowers engine turbine temperature. Monitor particularly ITT; it may becomenecessary to set PL to Flight Idle, if conditions permit.

Note: In extreme case, it may be necessary to consider precautionary engine shutdown and engine restart in flight. If both engines flame out, refer toBOTH ENGINE FLAME OUT procedure (2.04.02)

Note: Volcanicashmayclog thepitot probesresulting inunreliablespeedindications.If airspeed isunreliableor lost, adjust airplaneattitudeand torque.

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POWER PLANT


P 1

DEC 10

001

2.02.11

START UP PROCEDURE

ADC switching should be alternated every other day (ADC 1 odd days, ADC 2 evendays). Prior to initiating start sequence EEC FAULT light must be extinguished, if EECFAULT is lit try to reset ; if unsuccessful, deselect EEC.

During engine start or relighting, the following items must be monitored.

-- Correct NH increase when starting the sequence.-- Starter disconnection at 45 % NH.-- Maximum ITT : during a battery start one or two ITT peaks not exceeding 800°C may

usually be observed. ITT peaks are of lower value if a suitable GPU is used.

This example shows the start sequence of engine N° 1 on ground (engine 2 running) :

ENG OIL LO PR CCAS alarm is 30 seconds time delayed to avoid untimely ENGOIL LO PRduring engine start. Refer to 2.02.08 p18 for specific cold weather behaviour.

Note : This alert is inhibited when affected CL is in FUEL SO position.

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POWER PLANT


P 2A

DEC 10

001

2.02.11

PUSH BACK AND POWER BACK OPERATIONS

Push- back (with towbar)

Note: NAC OVHT and ENG FIRE can be triggered during push--back in hotel mode, with atail wind greater than 10kts, including aircraft direction changes throughout theprocedure.If the tail wind is above this limit, the push-- --back has to be done, with the propeller(s)running and unfeathered, and respecting ground safety rules and airport local rules.

-- Push--back is done after ATC clearance.-- Specific phraseology is used.-- Ground staff remains connected with the aircraft by using conventional signs and/orheadphones with several persons according to airline policy-- Parking brake released and steering OFF.-- Each crew member keeps his feet on the floor. NEVER USE BRAKES during push back(to avoid tail strike and/or strain on towing system). Wait for disconnection of the tow barby the ground staff before switching the steering ON.-- Set nose wheel steering to ON. Caution: neverset the hydraulicof thesteering beforethedisconnection of the tow bar.

Power back

Note: NAC OVHT and ENG FIRE can be triggered, if a prolonged power--back ismaintained with a tail wind greater than 10kts, including aircraft direction changesthroughout the procedureNote: In Ground Idle, after parking brake release, the aircraft moves forward. The powerlever has to be retarded slightly to power back just before releasing the brake.Note: Safety glasses have to be used by the ground staff, because of the possibility ofprojection during power back operation.

-- Before power back, both propellers are running and are unfeathered.-- Power back is done after ATC clearance.-- Ground staff area checked cleared before and during power back, by using conventionalsigns and/or headphones with several people, as per prevailing airlines policy.-- Nose wheel steering remains ON.-- To avoid moving forward, apply slight power back just before releasing brake.-- Each crew member keeps his feet on the floor. NEVER USE BRAKES during power back(to avoid tail strike).-- Power back is performed at low speed.-- Use Ground Idle or positive power to decrease speed or stop.

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ATR 42 Model : 400/500

POWER PLANT


P 8

DEC 09

001

2.02.11

REVERSE PHASES

NP is the parameter to be monitored during reverse phases. (NP is the only regulatedparameter in these phases)

OPERATIONS OUT OF THE NOTCH

WhenPLare retarded, during descent and approach, trim efficiency is reduced (referencepoint being notch), and cannot correct built --in discrepencies between engines and theirassociated controls. Tolerances due to PL rigging cannot be compensated in that area.TQ split up to 8% (8 counts) can be evidenced between engines in stabilised conditions.This is built --in and results from requirement of TQ accuracy in notch, which is the powersetting used for about 90% of flight time.TQ differences are allowable and can be eventually compensated manually by crew withPL adjustment.

AA

ATR 42 Model : 400/500

FLIGHT CHARACTERISTICS


P 1

DEC 07

001

2.02.12

TAKE OFF AND LANDING RUNS

-- Proper crew coordination is required in order to hold the control column at all timesand prevent excessive elevator or aileron deflections due to wind and/or reversed airflow from propellers.

The control column is initially held :

F in pitch : fully nose down, then slowly relaxed as speed increases.

F in roll : neutral or deflected TOWARD the wind in case of crosswindcomponent, as appropriate to maintain wings essentially level.

Note : Excessive aileron deflections should be avoided as they affect directionalcontrol.

-- For take--off, use of nose wheel steering guidance is only recommended for the veryfirst portion of the take--off run as rudder becomes very rapidly efficient when airspeedincreases (~ 40 Kts) and aircraft exhibits a natural tendency to go straight.

-- Action on NWS should be smooth and progressive, particularly as ground speedincreases.

-- Rudder must not be cycled during take--off, particularly the first portion where NWSis used : combination of unnecessary rudder cycling (with an increasingly efficientrudder) and NWS control would then lead to uncomfortable oscillations.

-- Rolling take--off technique.In order not to increase the take--off distances, power must be set quickly during thelast phase of the line up turn.

-- For landing or aborted take off, control column holding must be transfered to theco--pilot when the captain takes the NWS.If reverse is used, at low speeds and with high power, the reversed air flow mayshake violently the flight controls, particularly with no crosswind : the control columnmust be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged.

Narrow Runways :When the aircraft is operated on a narrow runway (width < 30 m (98 ft)), whoeveris the PF (CM1 or CM2), the CM1 should be ready to use NoseWheel Steering as soonas the nose wheel is on the ground.If reverse is used, at low speeds and with high power, the reversed air flow mayshake violently the flight controls, particularly with no crosswind : the control columnmust be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged.

Refer to 3.11.10

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R ATR 42 Model : 500/400

FLIGHT CHARACTERISTICS


P 4

DEC 07

001

2.02.12

APPROACH

-- The deceleration capabilities of the aircraft provide a good operational advantagewhich should be used extensively : decelerated approaches reduce noise, minimizetime and fuel burn and allow better integration in big airports. This is why they havebeen described as the “standard approaches” in section 2.02.10 (flight patterns).

-- Initial approach speed will vary with ATC constraints and turbulence, but may be up to240 Kts.

-- Initial approach speed may be maintained on a typical 3° glide slope to the followingheight above runway :

NP DECLARATION HEIGHT

82 % (IAS x 10) ft

Configuration changes should be made at VLE VFE when decelerating. This procedureallows to reach VAPP speed at 500 ft above runway.

Note : If deceleration rate on approach appears unsufficient, it is always possible toincrease it by setting NPs on 100 OVRD, but at the expense of an increasedinterior noise.

STEEP SLOPE APPROACH

Refer to 3.11.17

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AHRS


FLIGHT INSTRUMENTS P 1

DEC 06

001

2.02.14

AHRS

AHRS alignment sequence takes place as soon as the battery is switched ON, and it takesnominally 3 MINUTES DURING WHICH AIRCRAFT MUST NOT BE MOVED.

To know the remaining time for AHRS alignment, depress AHRS FAST ERECTpushbutton.The heading which can be read on the associated EHSI indicate the time remaining (inseconds) for AHRS alignment (example : heading 090 = 1 minute and 30 seconds). Thenrelease AHRS FAST ERECT pushbutton.

AHRS normally survive to electrical transients asociated with engine start.

ON GROUND ONLY, if needed, AHRS reset may be performed by cycling all relevant C/BOFF--ON.

Note : the beginning of the 3 minutes alignment period may be observed as it is associatedwith a brief display of horizon tilted 30� to the right without flag.

CAUTION : resetting AHRS C/B in flight is not recommended as in flight reailgnmentrequires 3 minutes of very stable flight (which may be impossible to get inturbulence) and possibility of pulling the wrong C/B could lead to completeAHRS failure unrecoverable for the rest of the flight.

Note : some of the AHRS failures observed in flight may be “self recoverable” when theyare associated to a temporary failure of the SPERRY DIGITAL BUS.

CAUTION : Pilots must be aware of possible induced attitudes and heading errors in caseof continuous turns, specially in high latitudes countries; therefore racetrackholding patterns are to be flown rather than circles.

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ATR 42 Model : 400/500

WEATHER RADAR


FLIGHT INSTRUMENTS P 2

DEC 06

001

2.02.14

WEATHER RADAR

The weather radar radiates power when operating in any mode other than STBY. Use ofweather radar on ground in a mode other than STBY requires special care :

-- make certain that no personnel is working in front of aircraft within a sector of 3 metersradius and 130� left or right of the aircraft axis.

-- direct aircraft nose so that no large size metal object (hangar, aircraft ...) is locatedwithin a 30 meters radius.

-- avoid operating radar during refueling operation of radiating aircraft or any otheraircraft within a 30 meters radius.

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R ATR 42 Model : 400/500

TCAS


P 1

DEC 07

060

2.02.15

TCAS



GENERAL

TCAS is an airborne Traffic alert and Collision Avoidance System that interrogates ATCtransponders in nearby aircraft and generates appropriate aural and visual advisories tothe flight crew to provide adequate separation.

Air to Air communications for coordinatingmaneuvers between TCASequipped aircraft isprovided by mode S ATC transponder.

Note 1 : TCAS system can only generate resolution advisories for intruders equippedwith operative mode S or mode C transponders (providing valid intrudersaltitude information).

Note 2 : Traffic advisories can only be generated for intruders equipped with operativemode S, C or A transponders (TCAS system provides no indication of aircraftwithout operative transponders).

CAUTION

The TCAS equipment is viewed as a supplement to the pilot who, with the aid ofq p pp p ,the Air Traffic Control, has the primary responsability for avoiding mid--air collisions.

START UP AND TEST

-- TURN rotary selector of the relevant ATC Control box to the STBY position.-- TURN rotary selector of TCAS control box to the STBY position.-- PRESS <<TEST>> button on the TCAS Control box and check proper aural messageand visual display.

GROUND OPERATION

TCAS test should be carried out during cockpit preparation.Unless otherwise instructed by ATC:-- KEEP selecting STBY mode on the TCAS Control box while taxiing for take off.-- Just prior to take off, select ”ALT” mode and check ATC1 selected on ATC transpondercontrol box; then select “AUTO” Mode on TCAS Control box.

-- Select STBY mode on TCAS Control box immediately after clearing the runwayfollowing landing.

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R ATR 42 Model : 400/500

TCAS


P 2

DEC 07

060

2.02.15

TCAS (CONT’D)



FLIGHT PROCEDURESProcedure is initiated by a TCAS Traffic Advisory : TA.

“TRAFFIC - TRAFFIC”

CPT -- Decide task sharing and announce : “TCAS, I (you) have the controls.”.

PF -- Be minded for maneuver. Follow traffic evolution on the TCAS indicator.

PNF -- Recall minimum safety altitude. Try to visually acquire the intruding aircraft.

Then may occur a Resolution Advisory : RA. Some RA will only advise to monitor verticalspeed (preventive RA). Others will advise to maneuver the aircraft.

The following procedures should then apply :

Sense of Resolution Advisory asking to maneuver

DESCEND CLIMB

CPT -- Confirm “We descend.”. CPT -- Confirm “We climb.”.

PF -- Disconnect Auto Pilot PNF -- Select proper rating on PWR MGT-- Descent at a rate in the green rotary selector (MCTen route or TO in(fly to) arc on TCAS VSI. other phases e.g. take off, approach

-- Ask for eventual configuration and landing) and adjust CL if requiredchanges. PF -- Disconnect Auto Pilot

PNF -- Advise ATC -- Apply roughly the bugged power-- Monitor IAS compared to VLE, -- Climb at a rate in the green (fly to)VFE, VMO pointer arc on TCAS VSI.

-- Monitor Aircraft altitude -- Ask for eventual configurationcompared to minimum changes.safety altitude. PNF -- Adjust power to TQ objectives

-- Advise ATC-- Monitor IAS compared VS.

Note : 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 configurationchanges.

After separation has becomeadequate (range increasing), TCASwill issue followingRA.

“CLEAR OF CONFLICT”Return promptly to last assigned ATC clearance.

AA

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ATR 42 Model : 400/500

HIGH LATITUDE OPERATIONS


P 1

DEC 06

001

2.02.19

CONDITIONS

Anomalous heading errors may occur on aircraft equipped with the Honeywell AH--600AHRS during high latitude operations, where the earth’s magnetic lines of force haveinclinations of greater than 75 degrees.

PROCEDURES

-- Take special care to keep the slip indicator centered in order to minimize headingerrors.

-- Crosscheck AHRS heading information with that of standby compass and/orGPS/GNSS.

-- Continous turn of more than 360�must be avoided; for holding, it is recommended tofly racetrack patterns with straight flight legs of at least one minute between the Uturns.

AA

ATR 42 Model : 400/500

MULTI PURPOSE COMPUTER


MPCP 1

DEC 05

100

2.02.21

APPLICABLE ONLY TO AIRCRAFT FITTED WITH MODIFICATION 5567

CONTENT

1 -- GENERAL 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 -- AFDAU PART DESCRIPTION 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.1 -- FDAU FUNCTION 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.2 -- APM FUNCTION DESCRIPTION 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.2.1 -- APIU 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.2.2 -- APM LIGHTS ON 13 VU 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.2.3 -- APM FAULT/OFF LIGHT ON 5 VU 6. . . . . . . . . . . . . . . . . . . . . . .2.2.4 -- APM TEST PUSHBUTTON ON 5 VU 7. . . . . . . . . . . . . . . . . . . . .2.2.5 -- APM WEIGHT ROTARY SELECTOR ON 5 VU 7. . . . . . . . . . . . . .2.2.6 -- CIRCUIT BREAKERS 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.2.7 -- ASSOCIATED CAUTION ALARMS 7. . . . . . . . . . . . . . . . . . . . . . .2.2.8 -- APM ARCHITECTURE 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.2.9 -- COCKPIT APM INTEGRATION 9. . . . . . . . . . . . . . . . . . . . . . . . .

2.3 -- APM FUNCTION LIMITATIONS/PROCEDURES 10. . . . . . . . . . . . . . . .2.3.1 -- LIMITATIONS 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.3.2 -- OPERATIONS AND TECHNIQUES 10. . . . . . . . . . . . . . . . . . . . .2.3.2.1 -- APM PRINCIPLE 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.3.2.2 -- APM INTERFACES 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2.3.2.3 -- APM TEST 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.3.3 -- NORMAL PROCEDURES 11. . . . . . . . . . . . . . . . . . . . . . . . . . . .2.3.3.1 -- WEIGHT SELECTION AND COMPUTATION 11. . . . . . . . . . . .2.3.3.2 -- CRUISE SPEED LOW PROCEDURE 12. . . . . . . . . . . . . . . . .

2.3.4 -- EMERGENCY PROCEDURES 12. . . . . . . . . . . . . . . . . . . . . . . . .2.3.5 -- ABNORMAL AND FOLLOWING FAILURES PROCEDURES 12. . .2.3.5.1 -- APM FAULT PROCEDURE 12. . . . . . . . . . . . . . . . . . . . . . . . .2.3.5.2 -- DEGRADED PERF PROCEDURE 13. . . . . . . . . . . . . . . . . . . .2.3.5.3 -- INCREASE SPEED PROCEDURE 13. . . . . . . . . . . . . . . . . . .

2.4 -- EHS FUNCTION 14--15--16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3 -- DMU PART 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 -- ABBREVIATIONS 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500



MPCP 2

DEC 05

100

2.02.21


LEFT INTENTIONALY BLANK

AA

ATR 4 Model : 400/500



MPCP 3

DEC 05

100

2.02.21


1- GENERAL

The scope of this section is to describe the MPC (Multi Purpose Computer) functions.TheMPC is composed of two independent parts, which are AFDAU part and DMU part.

-- AFDAU part performs the following functions (developed in software level ”C”regarding DO178B requirements) :

-- FDAU to transmit data to the FDR-- APM to monitor aircraft drag in icing conditions,-- EHS to transmit to the Ground via ATC, aircraft data.

--DMU part performs the following functions (developed in software level ”D” regardingDO178B requirements) :

-- Record on PCMCIA a copy of the FDR data frame for QAR function,-- Drive the 2 APM level discrete outputs,-- Manage a G--Meter report,-- Manage themaintenance of AFCS,MFC, TCAS*, PEC/EEC*, RadioCOM--NAV,-- Replacement of FDEP,-- Provide ACMS capacity, for customisation through a GSE

For more information, in particular regarding DMU part, please consult DO AMM.

You will find a list of abbreviations at the end of this section.

* : depending on version

AA

ATR 42 Model : 400/500



MPCP 4

DEC 05

100

2.02.21


2 - AFDAU (AUXILIARY FLIGHT DATA ACQUISITION UNIT) PART DESCRIPTION

2- 1 FDAU FUNCTION

Its main functions are :

-- Aircraft configuration identification through a dedicated pin--programming,-- Acquisition of anArinc 573 data stream from anotherdata acquisitionunit at differentinput speed rate (64w/s, 128w/s),

-- Acquisition of a secondArinc 573 data stream from aircraft SSFDR, for playback andSSFDR monitoring function,

-- Acquisition of new data and parameters through analog ports, discrete ports, Arinc429 ports, CSDB & ASCB ports,

-- Generation and transmission of a new data stream) to the aircraft FDR andQAR if installed.-- Transmission of data to the DMU via two internal lines,-- Transmission of a GMT signal on the Synchro CVR output..

AA

TR 42 Model : 400/500



MPCP 5

DEC 05

100

2.02.21


2- 2 APM (AIRCRAFT PERFORMANCE MONITORING) FUNCTION DESCRIPTION

TheAPM function is tomonitor the aircraft drag in icing conditions in order to alert the crewof a risk of severe icing conditions. The speed in cruise will be also monitored to alert thecrew of an abnormal speed decrease in icing conditions. The APMwill check also that theMSIS (Minimum Severe Icing Speed) is respected.

AA

ATR 42 Model : 400/500



MPCP 6

DEC 05

100

2.02.21


2.2 APM FUNCTION DESCRIPTION (cont’d)

2.2.1 -- APIU (AIRCRAFT PERFORMANCE INTERFACE UNIT)

The APIU is an electronic equipment installed in the cockpit, on the floor left side nearflight control Captain pedals.The function of this equipment is to realize interface between MPC and cockpitindicator lights and caution. It receives 2 information fromMPC (APM level 1 and APMlevel 2) and following dedicated logic manages cockpit signalisation by illuminatingthe corresponding indicator lights and cockpit caution signalisation (Caution light andSingle Chime).

2.2.2 -- APM LIGHTS ON FRONT INSTRUMENT PANEL (13 VU)

-- CRUISE SPEED LOW blue light-- DEGRADED PERF amber light-- INCREASE SPEED amber flashing lightThere are 2 groups of these 3 indicator lights, one on Captain side and one on FirstOfficer side.

2.2.3 -- APM FAULT/OFF LIGHT ON CM2 INSTRUMENT PANEL (5 VU)

This indicator light installed on the 5 VU panel is used to inform crew of a failure in theAPM function computation. In case of a FAULT indication, the APM shall be selectedOFF through this pushbutton, and in this case the OFF indication shall be illuminated.In normal utilization, without FAULT indication, theAPM function shall always be inONposition.

AA

ATR 42 Model : 400/500



MPCP 7

DEC 07

100

2.02.21


2.2 APM FUNCTION DESCRIPTION (Cont’d)

2.2.4 -- APM TEST PUSHBUTTON ON CM2 INSTRUMENT PANEL (5 VU)

This test pushbutton, shall be used to test the APM function.This test shall be performed daily by the crew, to determine whether the APMcomponents are operational.

2.2.5 -- APM WEIGHT ROTARY SELECTOR ON CM2 INSTRUMENT PANEL (5 VU)

The WEIGHT rotary selector is installed on the 5 VU panel, and is used by the crew toselect the aircraft weight. This weight information is used in the MPC for the APMperformance computation.This rotary switch has 12 positions to select the TO weight (depending on weight unit):-- In Tons : 12/13/14/14.5/15/15.5/16/16.5/17/17.5/18/18.5-- In pounds : 26.5/28.7/30.9/32/33.1/34.2/35.3/36.4/37.5/38.6/39.7/40.8

Note :To take into account the new value, position has to be changed (even ifactual weight is the same as precedent flight one).

2.2.6 -- CIRCUIT BREAKERS

The MPC and the APIU are powered in parallel through circuit breakers 4 TU and 159TU installed on 21 VU.TheAPMFAULT light is powered througha dedicatedcircuit breaker214TU, in order tohave APM FAULT signalisation in case of MPC and/or APIU power supply loss.

2.2.7 -- ASSOCIATED CAUTION ALARMSCRUISE SPEED LOW : blue lightDEGRADED PERF : amber light with CAUTION light + SCIINCREASE SPEED : amber flashing light with CAUTION light + SCFAULT : amber light with CAUTION light +SC +ANTI--ICING onCAPOFF : white light(SC = Single Chime)Note : The WEIGHT rotary selector position, the status of CRUISE SPEED LOW /

DEGRADEDPERF / INCREASESPEED indicator lights, and the OFFpositionof the APM pushbutton are recorded in the SSFDR.

AA

RR

ATR 42 Model : 400/500



MPCP 8

DEC 05

100

2.02.21



2.2.8 -- APM ARCHITECTURE

AA

ATR 42 Model : 400/500



MPC P 9

DEC 07

100

2.02.21



2.2.9 -- COCKPIT APM INTEGRATION

AA

R

ATR 42 Model 400/500



MPCP 10

DEC 05

100

2.02.21


2.3 - APM FUNCTION LIMITATIONS/PROCEDURES

2.3.1 -- LIMITATIONSAPM does not induce any specific limitation.

2.3.2 -- OPERATIONS AND TECHNIQUES2.3.2.1 -- APM principleTheAPManalysis is conducted if the aircraft is in icing conditions, that is tosay if theICINGAOA is illuminated and/or if the airframede--icing is selected ONand/or if iceaccretion has been detected at least once during the flight.The APM analysis principle is to compare the aircraft theoretical drag with an”in--flight drag” computed with measured parameters available.Measured parameters used by the APM are acquired each second and aresmoothed over a rolling average of 30 seconds to limit noise and errormeasurements. Then, the drag is calculated over a rolling average of 60 seconds.This means that the drag analysis alert would start after at least 90 seconds ofparameter acquisition.The drag analysis starts as soon as the aircraft entered in icing conditions withlanding gears and flaps retracted. The APM analysis will only be done with bothengines operating.A cruise speedmonitoringwill also be conducted by comparing themeasured IAS tothe theoretical maximum cruise IASth.Different alarm messages will be delivered to the crew depending on the dragdifference between computed drag and theoretical drag, and the speed differencebetween measured IAS and theoretical IASth.The alarm messages will not be delivered if the static air temperature is above 10Celsius degree.2.3.2.2. -- APM InterfacesThe APM electrical input / output interface is made of :-- one ASCB bus input-- one PCM FDAU input-- four discrete inputs for weight rotary selector positions-- one discrete output for alarm message : level 1-- one discrete output for alarm message : level 2-- one discrete input to monitor discrete output level 1-- one discrete input to monitor discrete output level 2-- one discrete output for APM FAULT-- one discrete input for APM TEST

AA

ATR 42 Model : 400/500



MPCP 11

DEC 09

100

2.02.21


2.3 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)

2.3.2.3 -- APM testThe APM test is activated by the crew daily, to check if all the APM components workproperly.When the crew activated APM test, 2 discrete signals are sent, one to the MPC andone to the APIU, to test the APM functions and its interfaces.The APM test shall be performed by pushing and maintaining, for all test duration(maximum 5 seconds), the APM PTT TEST pushbutton on the 5 VU and the testresult shall be as follows :

-- CRUISE SPEED LOW lights on 13 VU (both sides) illuminate-- over 1 second later, DEGRADED PERF lights on 13 VU (both sides) illuminate,

with CAUTION light and SC, with CRUISE SPEED LOW lights still illuminated-- over 1 second later, INCREASE SPEED lights on 13 VU (both sides) illuminate

flashing, with CAUTION light and SC, with CRUISE SPEED LOW andDEGRADED PERF lights still illuminated

-- over 1 second later, FAULT light on the 5VU illuminates, with CAUTION light,SC and ANTI--ICING (on CAP), with CRUISE SPEED LOW, DEGRADEDPERF and INCREASE SPEED lights still illuminated

-- end of test, the crew stop action on APM PTT TEST pushbutton, all lights shallextinguish.

2.3.3 -- NORMAL PROCEDURES

2.3.3.1 -- Weight Selection and Computation

SelectionTo determine the aircraft theoretical and ”in--flight” performances the aircraft weightmust be known. As the weight is not available, the crew must enter the take offweight value in the system with a twelve--position rotary selector.This rotary selector can be moved after MPC is powered on, and after starting up ofthe two engines.On ground just before flight and as soon as the crew has computed the take offweight on the load sheet, the crew must select the corresponding weight by movingthe rotary selector.It should be set to minimum weight then to take off weight nearest position.The takeoff weight will be taken into account by the system only if rotary selector has beenchanged.

Note : Any change of rotary selector in flight will have no effect.

ComputationIf the crew doesn’t select the take off weight before take off with the rotator, then theAPM will perform a take off weight computation.This computation is performedduring the first minutes of the flight and before the APM starts the drag analysis.The actual weight is then updated in flight by internal computation.

AA

RR

ATR 42 Model : 400/500



MPCP 12

DEC 05

100

2.02.21



2.3.3.2 -- CRUISE SPEED LOW PROCEDURE

CRUISE SPEED LOW light illuminated-- Appears in cruise only, to inform the crew that an abnormal drag increase inducesa speed decrease of more than 10kt compared with the expected speed.

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

2.3.4 -- EMERGENCY PROCEDURESNo specific Emergency Procedures when APM installed.

2.3.5 -- ABNORMAL AND FOLLOWING FAILURE PROCEDURES

2.3.5.1 -- APM FAULT PROCEDUREThe APM FAULT light function (5 VU) is to inform the crew that there is a problem inthe APM computation, either in the MPC or in the APIU or in the aircraft wiring.The FAULT can be triggered by :-- MPC in the following conditions :-- loss of ASCB acquisition-- loss of PCM acquisition-- MPC internal failure-- disagree between outputs level 1 and level 2 status and control

-- APIU in the following conditions :-- fault coming from MPC-- APIU internal failure-- disagree between outputs status and control

For trouble shooting aid associated to the APM FAULT light, it is necessary tomonitor the ”system” light on FDAU :-- if FDAU light is extinguished, the problem is on APIU side-- if FDAU light is illuminated flashing, the problem is on MPC side

In case of APM FAULT light illumination, the crew has to select the APM OFF bypushing on the FAULT light button on the 5 VU.

AA

ATR 42 Model : 400/500



MPCP 13

DEC 05

100

2.02.21



2.3.5.2 -- DEGRADED PERF PROCEDURE

DEGRADED PERF light illuminated with CAUTION light and Single Chime

-- Mainly appears in level flight after CRUISE SPEED LOW or in climb to inform thecrew that an abnormal drag increase induces a speed decrease or a loss of rate ofclimb.

-- The most probable reason 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 SEVERE ICING Conditions confirmed(unexpected decrease in speed or rate of climb, visual cues)OrH Impossibility to maintain IAS > RED BUG + 10 KT in level flightOrH Abnormal aircraft handling feelingSEVERE ICING procedure (2.04.05) APPLY. . . . . . . . . . . . . . . . . . . .H If notSCHEDULED FLIGHT. CONTINUE. . . . . . . . . . . . . . . . . . . . . . . . . . . .ICING CONDITIONS and SPEED. MONITOR. . . . . . . . . . . . . . . . . . .

2.3.5.3 -- INCREASE SPEED PROCEDURE

INCREASE SPEED light illuminated flashing with CAUTION and Single chime-- Appears after DEGRADED PERF to inform the crew that the drag is abnormallyhigh and IAS is lower than RED BUG + 10 KT

H If abnormal conditions confirmedIMMEDIATELY PUSH THE STICK TO INCREASE SPEEDTO RECOVER MINIMUM IAS = RED BUG + 10 KTSEVERE ICING procedure (2.04.05) APPLY. . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500



MPCP 14

DEC 05

100

2.02.21


2.4 - EHS (ENHANCED SURVEILLANCE) FUNCTION

In accordance with the European Air Traffic Management Plan, the implementation ofEHS requires aircraft to have capability to downlink aircraft derived data via a mode Stransponder.

This function allows to answer European regulation : NPA 20--12a.

The EHS function of MPC, allows acquiring flight parameters from aircraft computers, todownlink these data to Air Traffic Control through aircraft Transponder Mode S.

The flight parameters are acquired from different aircraft computers (ADC1/2, AHRS1/2,GNSS), in different acquisition format (ASCB, ARINC 429). They are computed in MPCand send to aircraft transponders through a dedicated ARINC 429 output.

Parameter Aircraft computer Acquisition format

Magnetic heading AHRS 1 or 2 ASCB

Indicated airspeed ADC 1 or 2 ASCB

True airspeed ADC 1 or 2 ASCB

Mach number ADC 1 or 2 ASCB

Vertical rate ADC 1 or 2 ASCB

Selected altitude AFCS ASCB

Roll angle AHRS 1 or 2 ASCB

True track angle GNSS ARINC 429

Ground speed GNSS ARINC 429

AA

ATR 42 Model : 400/500



MPCP 15

DEC 05

100

2.02.21


2.4 - EHS FUNCTION (cond’t)The EHS aircraft architecture is as follows :

AA

ATR 42 Model : 400/500



MPCP 16

DEC 05

100

2.02.21


2.4 - EHS FUNCTION (cond’t)In addition to theEHS, theMPC has capability provision to acquire, compute and transmitto aircraft transponders, following the same above architecture, parameters for ADS--B(Automatic Dependent Surveillance -- Broadcast) purpose.

The flight parameters acquired from aircraft computers are :

Parameter Aircraft computer Acquisition format

Latitude GNSS ARINC 429

Longitude GNSS ARINC 429

Baro--altitude GNSS ARINC 429

HIL GNSS ARINC 429

HFOM GNSS ARINC 429

HIL : Horizontal Integrity Limit

HFOM : Horizontal Figure Of Merit

AA

ATR 42 Model : 400/500



MPCP 17

DEC 05

100

2.02.21


3 - DMU (DATA MANAGEMENT UNIT) PART

The DMU system is dedicated to the aircraft maintenance.

The DMU has been designed to allow the user to customize the system according to hisspecific application, requirements, operating environment and logistics. Programmingcapabilities are provided, to allowmodification of monitoring functions or implementationof additional monitoring functions.

Most of the functions are configurable or programmable by an ”on--ground” equipmentcalled Ground Support Equipment (GSE), based on a Laptop. The GSE generates acustomized DMU database, which determines the detailed functions of the DMU and issupplied to the DMU system via a PCMCIA interface.

The DMU definition will be able to include two different ”customizations”:

1 -- the customization basically performed by the supplier for answering ATRspecification.

2 -- the customization developped by the user through the GSE.

The customization that are basically performed for ATR aircraft, activates the followingfunctions:

-- ARINC 429 aircraft parameters acquisition.-- Operational software and database upload from the PCMCIA interface.-- Management of two APM discrete.-- Management of PCMCIA QAR/DAR recording on a PCMCIA card.-- Dialogue with a MCDU.-- Management of a G--Meter report.-- Management of maintenance functions for various aircraft equipment.

AA

ATR 42 Model : 400/500



MPCP 18

DEC 05

100

2.02.21


3 - DMU PART(cond’t)

MPC MAIN MENU

After an MPC selection on the MCDU, the following initial menu is displayed.

AA



MPCP 18A

DEC 05

100

2.02.21


LIST OF SPECIFIC ABBREVIATIONS (see also 0.50.00) :

AFDAU Auxiliary Flight Data Acquisition UnitAPIU Aircraft Performance Interface UnitAPM :Aircraft Performance MonitoringARINC Aeronautical Radio IncASCB Avionics Standard Communication BusCSDB Commercial Standard Digital BusDAR Digital ACMS RecorderDMU Data Management UnitEHS Enhanced SurveillanceGSE Ground Support EquipmentMPC Multi Purpose ComputerMSIS Minimum Severe Icing SpeedPCMCIA Personal Computer Memory Card International AssociationQAR Quick Access Recorder(SS)FDR (Solid State) Flight Data Recorder

AA

Mod : 5506 ATR 42 Model : 400/500

Aircraft Communication Addressing and Reporting System


ACARSP 1

DEC 05

100

2.02.22

CONTENT

1 -- GENERAL 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2 -- LIMITATIONS 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3 -- DESCRIPTION 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3.1 -- SYSTEM DESCRIPTION 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3.2 -- FUNCTIONS 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 -- OPERATIONS 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4.1 -- COMMON FEATURES FOR USE 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . .4.2 -- DEPARTURE CLEARANCE DCL 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . .4.3 -- DIGITAL ATIS D--ATIS 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5 -- ABBREVIATIONS 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 2

DEC 05

100

2.02.22

LEFT INTENTIONALY BLANK

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 3

DEC 05

100

2.02.22

1- GENERAL

The ACARS system is optional.It may be customized by the operator to meet their requirements.This chapter provides a generic description of system.Refer to Collins Operator’s Guide for detailed description of all features.

The ACARS (Aircraft Communication Addressing and Reporting System) is a data linksystemwhich enables exchange of data between an aircraft and a ground based stationover an ARINC or SITA network.

2- LIMITATIONS

ACARS is approved as a ”non essential” system for the transmission of DepartureClearance (DCL) and Digital Automatic Terminal Information Service (D--ATIS) inaccordance with ED--85 and ED--89A.

This approval does not constitute an operational approval. DCLand D--ATISmessagescan be transmitted and received over ACARS if they are verified per approvedoperational procedures.

Terminal Weather Information for Pilots (TWIP) and Oceanic Clearance (OCL)functions are not certified and must not be used for flight management.

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 4

DEC 05

100

2.02.22

3- DESCRIPTIONThe ACARS system is optional. It may be customized by the operator to meet theirrequirements. This chapter provides a generic description of system.Refer to Collins Operator’s Guide for detailed description of all features.3- 1 SYSTEM DESCRIPTIONThe airborn ACARS system consists of :-- a CMU (Communication Management Unit) installed in one 80VU avionics shelf,-- a MCDU (Multifunction Control Display Unit) installed on the pedestal ; the MCDU is themain interface for preparing, sending downlink messages and reading uplink messages;MCDUs are shared between GNSS and ACARS

Note :-- in case of singleGNSS,GNSSandACARScan be accessed from eachMCDU-- in case of dual GNSS:

-- MCDU1 gives access to GNSS1 and ACARS-- MCDU2 gives access to GNSS2 and ACARS

-- a printer for printing out, if necessary, messages received and displayed on MCDU,-- a VHF (VHF3) is dedicated to ACARS and cannot be used for voice communications,-- two ACARS MSG attention getter lights which illuminates upon reception of ATS messages,-- aircraft discretes for OOOI (Out of gate, take Off, a/c On ground, a/c In gate) information.

The system is interfaced with:-- FDAU for engine parameters and Fuel On Board,-- GNSS for position and time,-- ATC control panel for Flight Identification.

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 5

DEC 05

100

2.02.22

3- DESCRIPTION (cont’d)

3- 2 SYSTEM FUNCTIONS

The ACARS system main pages are the following:-- AOC STD (Airline Operation Control Standard) pages : these pages are identified byDL in page header; they give access to predefined report pages and free text page.-- ATS (Air Traffic Services) pages : these pages are identified by ATS in page header;ATS Departure Clearances and D--ATIS are available in ATS MENU page.-- TECHNICAL pages : these pages are used for system initialisation and identified byACARS in header.

All functions are detailled in Collins Operator’s Guide.

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 6

DEC 05

100

2.02.22

4- OPERATIONS

4- 1 COMMON FEATURES FOR USE

TheDepartureClearance andD--ATIS requests are to beprepared onMCDU in relevantATS pages.

In case of loss of data link capability, usual voice procedures will be used.

When the crew is notified that there is no link with the ground station, ”NOCOMM”message, or in case of system failure, he must revert to voice procedures.

Upon illumination of ”ACARS MSG” attention getter lights, the crew should checkmessages on MCDUs.

The crew may have to send a new request or revert to voice procedures as required byATS.

4- 2 DEPARTURE CLEARANCE DCL

This service provides pilot with a data link departure clearance (DCL) within the scopeof preset operational procedures.

The DCL service should be initiated by the aircrew between 10 min and 3 min (orotherwise specified) before the clearance is needed.If DCL is not completed 3 min (or otherwise specified) before departure, the crewmustrevert to voice procedure.

The Reclearance capability must not be performed by the DCL service. In the event ofdatalink reclearance being received, the Aircrewmust ignore it andmust revert to voiceprocedures.

If the Aircrew is not able to accept the operational contents of the DCL message, hemust revert to voice procedures otherwise he must send the Clearance Echobackmessage.

A negative message may be sent back; in that case, the crew has to revert to voiceprocedure.

Message content consistency

The aircrew before take--off must check the consistency of the SID delivered in theDCL message with departure runway and flight plan information. Hemust revert tovoice procedures in case of inconsistency.

Departure Clearance frequency has to be monitored in case a voice DCL back--upprocedure is necessary.

All Departure Clearance delivered by voice supersede any datalink DepartureClearance message.

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 7

DEC 05

100

2.02.22

4- OPERATIONS (cont’d)

4- 3 DIGITAL ATIS D- ATIS

Where a D--ATIS is available, it supplements the existing Voice--ATIS, the informationare identical in both content and format and are updated simultaneously.

The crew, after sending an ATIS request, must complete the ATIS service (reception)within 4 minutes or otherwise indicated.Otherwise, the crew must resubmit his ATIS request or revert to voice procedures.

The crew must acknowledge receipt of the D--ATIS answer at contact with ATC.

For the crew, the voice procedures will be the back up of the D--ATIS service.

Message content consistency

The crew must cross check the global consistency between D--ATIS informationparameters.In particular, the crewmust check thenameof theATCairfield in theD--ATIS requestand in the ATIS message received

The crew must check that radio communication and radio navigation meansfrequencies required by D--ATIS are operational.

The following data must be cross--checked with Voice--ATIS:-- bird presence and presence of artificial obstacle on selected runway,-- meteorological and wind data for landing,-- type of approach,-- active runway,-- dew point temperature,-- altimeter setting.

AA

Mod : 5506 ATR 42 Model : 400/500



ACARSP 8

DEC 05

100

2.02.22

LIST OF SPECIFIC ABBREVIATIONS (see also 0.50.00) :

ACARS Aircraft Communication Addressing and Reporting SystemAOC STD Airline Operation Control StandardARINC Aeronautical Radio Inc(D--)ATIS (Digital--) Automatic Terminal Information ServiceATC Air Traffic ControlATS Air Traffic ServicesCMU Communication Management UnitDCL Departure ClearanceMCDU Multifunction Control Display UnitOCL Oceanic ClearanceOOOI Out of gate, Take Off, A/C O Ground, A/C In GateSID Standard Instrument DepartureTWIP Terminal Weather Information for Pilots

AA

ATR 42 Model : 400/500

CONTENT

NORMAL PROCEDURES

P 1

APR 08

001

2.03.00

2.03.00 CONTENT

2.03.01 FOREWORD

2.03.02 PRELIMINARY

2.03.03 PANEL SCAN SEQUENCE

2.03.04 FLIGHT PREPARATION

2.03.05 EXTERIOR INSPECTION

2.03.06 PRELIMINARY COCKPIT PREPARATION

2.03.07 COCKPIT PREPARATION

2.03.08 BEFORE PROPELLER ROTATION / BEFORE TAXI

2.03.09 TAXI

2.03.10 BEFORE TAKE OFF

2.03.11 TAKE OFF / TAKE OFF 100%

2.03.12 AFTER TAKE OFF

2.03.13 CRUISE

2.03.14 DESCENT

2.03.15 APPROACH

2.03.16 BEFORE LANDING

2.03.17 GO AROUND

2.03.18 LANDING

2.03.19 AFTER LANDING

2.03.20 PARKING

2.03.21 LEAVING THE AIRCRAFT

AA

ATR 42 Model : 400/500

FOREWORD

NORMAL PROCEDURES

P 1

APR 08

001

2.03.01

FOREWORD

Procedures contained in this chapter are recommended by the manufacturer. They areconsistent with the other chapters of this manual, in particular 2.02 PROCEDURES ANDTECHNIQUE.

Normal procedures are not certified by the Authorities, and in the judgment of theManufacturers, are presented here in, as the best way to proceed from a technical andoperational stand point.They are continuously updated, taking into account inputs from all operators andlessons of the Manufacturer’s own experience.

In the same manner, they may be amended as needed by the Operator.

However if the FCOM is used as the on board Operational Manual, the Manufacturerrecommends channeling any suggested amendment through him for earlypublicationso as to maintain the consistency of the Manual.

The Operator should be aware that a complete rewriting of this chapter may be doneunder his own responsability but could lead to difficulties in updaing and maintainingthe necessary homogeneity with the other chapters of this manual.

AA

ATR 42 Model : 400/500

PRELIMINARY

NORMAL PROCEDURES

P 1

APR 08

001

2.03.02

PRELIMINARY

The following sections provide expanded information related to normal procedures.

Normal procedures consist of inspections, preparations and normal check lists. All items arelisted in a sequence following a standardized scan of the cockpit panels (see section 2.03.03)except when required by the logic of actions priority, to ensure that all actions are performedthe most efficient way.

Normal procedures are divided into phases of flight and accomplish by recall.

In the following assignation :-- CM1 refers to the Crew Member in the left hand seat-- CM2 refers to the Crew Member in the right hand seat-- PF refers to the Pilot Flying-- PNF refers to the Pilot Non Flying

After completion of a given procedure, the related normal check list is used. Thenormal check list developed by the manufacturers includes only the items that mayhave a direct impact on safety and efficiency if not correctly accomplished. All normalcheck lists are initiated at the Pilot’s flying command. Somenormal procedureswhichare non routinewill be found in chapter 2.02PROCEDURESANDTECHNIQUEand inchapter 3.11 SPECIAL OPERATIONS.

All steps have to be performed before the first flight of the day or following a crewchange ormaintenance action. Transit steps are the only ones to be completed after atransit stop. They are grouped inthe COCKPIT FINAL PREPARATION.If there is any doubt as to whether the application of transit procedures coversall safety aspects, the complete preparation must be accomplished.

AA

ATR 42 Model : 400/500

PANEL SCAN SEQUENCE

NORMAL PROCEDURES

P 1

APR 08

001

2.03.03

OVERHEAD PANEL SCAN SEQUENCEAA

ATR 42 Model : 400/500

PANEL SCAN SEQUENCE

NORMAL PROCEDURES

P 2

APR 08

001

2.03.03

INSTRUMENTS PANELS SCAN SEQUENCEAA

ATR 42 Model : 400/500

PANEL SCAN SEQUENCE

NORMAL PROCEDURES

P 3

APR 08

001

2.03.03

PEDESTAL SCAN SEQUENCEAA

ATR 42 Model : 400/500

FLIGHT PREPARATION

NORMAL PROCEDURES

P 1

APR 08

001

2.03.04

FLIGHT PREPARATION

TECHNICAL CONDITION OF THE AIRCRAFT

The crew will verify the technical status of the aircraft in respect to airworthiness acceptability ofmalfunction and influence in the flight plan, using all necessary operator’s documents, inparticular MEL (Minimum Equipment List).

WEATHER BRIEFING

The crew will receive a weather briefing which should include :-- actual and expected weather conditions for take off and climb out including

runway conditions,-- en route significant weather : winds and temperatures,-- terminal forecasts for destination and alternate airports,-- actual weather for destination and aletrnates for short range flights and recent

past weather if available,-- survey of the meteorological conditions at airports along the planned route.

NAV / COM FACILITIES EN ROUTE

The crew will study the latest relevant NOTAMs (NOtice To AirMen) and will check that allrequired facilities at departure, destination and alternate airports are operational and that theyfulfill the appropriate requirements.

FLIGHT PLANS / OPERATIONAL REQUIREMENTS

The crew will check the company flight plan, in respect to routing, altitudes and flight time.

The crew will check theestimated load figures and will calculate maximum allowed take off andlanding weights.

The captain will decide the amount of fuel necessary for a safe conduct of the flight, taking intoconsideration possible economic fuel transportation.

The captain will check ATC flight plan and ensure it is filed according to the prescribedprocedures.

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 1

APR 08

001

2.03.05

INTRODUCTION

The exterior inspection is primarily a visuel check to ensure that the overall conditionof the aircraft, the visible components and equipments are safe for the flight.It is normally performed by maintenance or in the absence of maintenance by the firstofficer before each originating flight.During exterior walk around, observe that the FLIGHT CONTROL SURFACES andFLAPS are clear and memorize surfaces position.

Section content :

EXTERIOR WALK AROUND DRAWING PAGE 2. . . . . . . . . . . . . . . . . . . . . . . .MAIN LEFT LANDING GEAR AND FAIRING PAGE 3. . . . . . . . . . . . . . . . . . . . .LEFT WING TRAILING EDGE PAGE 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT WING LEADING EDGE PAGE 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT ENGINE PAGE 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT FORWARD FUSELAGE PAGE 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NOSE PAGE 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT FORWARD FUSELAGE PAGE 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT ENGINE PAGE 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT WING LEADING EDGE PAGE 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT WING TRAILING EDGE PAGE 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAIN RIGHT LANDING GEAR AND FAIRING PAGE 6. . . . . . . . . . . . . . . . . . . .RIGHT AFT FUSELAGE PAGE 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAIL PAGE 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT AFT FUSELAGE PAGE 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 2

APR 08

001

2.03.05

EXTERIOR INSPECTION DRAWING

... / ...

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 3

APR 08

001

2.03.05

EXTERIOR INSPECTION ACTIONS

MAIN LEFT LANDING GEAR AND FAIRING

PARKING BRAKE ACCU PRESSURE CHECK 1500 PSI MINIMUM. . . . . . . . . . . .MAINTENANCE DOORS CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GEAR DOORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WHEELS AND TIRES CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE TEMPERATURE SENSORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE WEAR DETECTORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING GEAR STRUCTURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYDRAULIC LINES CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WHEEL WELL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UPLOCK OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : On ground, the landing gear uplock box in closedposition leads to red local

UNLK alarm in the cockpit.The uplock box can be open by pulling the landing gear emergencyextension handle. Then, replace it in its initial position.

FREE FALL ASSISTER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SAFETY PIN REMOVED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BEACON LIGHT CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIR CONDITIONING PANEL LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PACK RAM AIR INLET CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAT PROBE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAGNETIC FUEL LEVEL IN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 4

OCT 08

001

2.03.05

EXTERIOR INSPECTION ACTIONS (CONT’D)

LEFT WING TRAILING EDGE

BANANA SEAL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXHAUST NOZZLE CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS POSITION CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AILERON AND TAB CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STATIC DISCHARGERS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HORN CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LEFT WING LEADING EDGE

R NAV AND STROBE LIGHTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .WING DE--ICING BOOTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL VENT NACA INLET CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAGNETIC FUEL LEVEL IN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ICE DETECTOR CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LEFT ENGINE

LEFT COWLINGS ALL FOUR CLOSED AND LATCHED. . . . . . . . . . . . . . . . . . .OIL COOLING FLAPS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINE AIR INTAKE CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINE DE--ICING BOOTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPINNER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROPELLER FEATHERED / CONDITION / FREE ROTATION. . . . . . . . . . . . . . . .RIGHT COWLINGS ALL FOUR CLOSED AND LATCHED. . . . . . . . . . . . . . . . . .INNER WING LEADING EDGE AND FAIRING CONDITION. . . . . . . . . . . . . . . . .

LEFT FORWARD FUSELAGE

WING AND EMERGENCY LIGHTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . .EMERGENCY EXIT CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT OVBD VALVE OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CARGO DOOR OPERATING PANEL DOOR CLOSED. . . . . . . . . . . . . . . . . . . .CARGO DOOR CLOSED AND LATCHED. . . . . . . . . . . . . . . . . . . . . . . . . . . . .O2 BOTTLE OVERLOAD DISCHARGE INDICATION GREEN. . . . . . . . . . . . . . . .ANGLE OF ATTACK PROBE CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .COCKPIT COMMUNICATION HATCH CHECK. . . . . . . . . . . . . . . . . . . . . . . . . .ICE EVIDENCE PROBE CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STATIC PORTS CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

R PITOT PROBES AND COVERS CHECK / REMOVED. . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 5

APR 08

001

2.03.05


NOSE

WIPERS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADOME AND LATCHES CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NOSE GEAR WHEELS AND TIRES CONDITION. . . . . . . . . . . . . . . . . . . . . . . .NOSE GEAR STRUCTURE CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAXI LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WHEEL WELL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FREE FALL ASSISTER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SAFETY PIN REMOVED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NOSE WHEEL STERRING CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYDRAULIC LINES CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NOSE GEAR DOORS CONDITION, 2 CLOSED. . . . . . . . . . . . . . . . . . . . . . . . .

RIGHT FORWARD FUSELAGE

PITOT PROBE AND COVER CHECK / REMOVED. . . . . . . . . . . . . . . . . . . . . . .STATIC PORTS CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ICE EVIDENCE PROBE CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANGLE OF ATTACK PROBE CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTERNAL DC AND AC ELECTRICAL POWER ACCESS DOORS CHECK. . . . . .EMERGENCY EXIT CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMERGENCY LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTENNAE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WING LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

RIGHT ENGINE

INNER WING LEADING EDGE AND FAIRING CONDITION. . . . . . . . . . . . . . . . .LEFT COWLINGS ALL FOUR CLOSED AND LATCHED. . . . . . . . . . . . . . . . . . .ENGINE AIR INTAKE CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINE DE--ICING BOOTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPINNER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROPELLER FEATHERED / CONDITION / FREE ROTATION. . . . . . . . . . . . . . . .Note : If propeller brake not set or not installed.RIGHT COWLINGS ALL FOUR CLOSED AND LATCHED. . . . . . . . . . . . . . . . . .OIL COOLING FLAPS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 6

OCT 08

001

2.03.05


RIGHT WING LEADING EDGE

R NAV AND STROBE LIGHTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . .R WING DE--ICING BOOTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R FUEL VENT NACA INLET CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R MAGNETIC FUEL LEVEL IN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R ICE DETECTOR CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

RIGHT WING TRAILING EDGE

R BANANA SEAL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R FLAPS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R EXHAUST NOZZLE CLEAR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R FLAPS POSITION CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R AILERON AND TAB CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R STATIC DISCHARGERS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .R HORN CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MAIN RIGHT LANDING GEAR AND FAIRING

MAGNETIC FUEL LEVEL IN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAT PROBE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIR CONDITIONING GROUND CONNECTION LOCKED. . . . . . . . . . . . . . . . . . .PACK RAM AIR INLET CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .REFUELING CONTROL PANEL ACCESS DOOR CLOSED AND LATCHED. . . . . .GEAR DOORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING GEAR STRUCTURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYDRAULIC LINES CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WHEEL WELL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UPLOCK OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FREE FALL ASSISTER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SAFETY PIN REMOVED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .WHEELS AND TIRES CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE WEAR DETECTORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE TEMPERATURE SENSORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . .REFUELING POINT ACCESS DOOR CHECK. . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

EXTERIOR INSPECTION

NORMAL PROCEDURES

P 7

APR 08

001

2.03.05


RIGHT AFT FUSELAGE

VHF ANTENNA CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SERVICE DOOR CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAIL PROP AND TAIL SKID CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OUTFLOW VALVES CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TAIL

FLIGHT CONTROLS ACCESS DOOR LOCKED. . . . . . . . . . . . . . . . . . . . . . . . .VOR ANTENNAE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STABILIZER DE--ICING BOOTS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . .LOGO LIGHTS (if installed) CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HORNS CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STABILIZER, ELEVATORS AND TABS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . .STATIC DISCHARGERS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIN, RUDDER AND TAB CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAIL CONE, NAV AND STROBE LIGHTS CHECK. . . . . . . . . . . . . . . . . . . . . . .VORTEX GENERATORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LEFT AFT FUSELAGE

WATER SERVICE PANEL ACCESS DOOR CLOSED. . . . . . . . . . . . . . . . . . . . .TOILET SERVICE PANEL ACCESS DOOR CLOSED. . . . . . . . . . . . . . . . . . . . .CABIN DOOR CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENTRY EMER LIGHT CONDITION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

PRELIMINARY COCKPIT PREPARATION

NORMAL PROCEDURES

P 1

DEC 10

001

2.03.06


The following procedures will be performed prior to the powering of the aircraft either bymaintenance staff or the first officer, as appropriate.

Completion ensures there will be no danger to aircraft and staff when powering the systems.

PROCEDURES WHEN USING A GPU pages 2 and 3. . . . . . . . . . . . . . . . . . . . . .

PROCEDURES WHEN USING ENG 2 IN HOTEL MODE pages 4 and 5. . . . . . . . .

ENGINE FIRE TEST page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATPCS TEST page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OXYGEN MASK TEST page 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRIMS TEST page 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENGINE START page 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .including HOT ENVIRONMENT START page 8

Note : APM has to be tested daily; refer to APM test, 2.02.21 page 11.

RECORDERS TEST page 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

R

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 2

DEC 10

001

2.03.06

PRELIMINARY COCKPIT PREPARATION (CONT’D)

PROCEDURES TO BE USED WHEN USING A GPUFOR HOTEL MODE SEE 2.03.06 PAGES 4 and 5.

CM2 CARGO DOOR CTL panel cover (if installed) CLOSED. . . . . . . . . . . . . . . . . . . . .EMERGENCY EQUIPMENT CHECK FOLLOWING LIST : page 6. . . . . . . . . . .GEAR PINS ON BOARD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LATERAL AND OVERHEAD PANELS C/B CHECK SET, RESET AS APPLICABLE. .BAT TOGGLE SW ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC FAULT LIGHTS CHECK FOLLOWING SEQUENCE. . . . . . . . . . . . . . . . . . .

MFC 1A AND MFC 2A FAULT LIGHTS CHECK FLASH. . . . . . . . . . . . . . . . .MFC 1A AND MFC 2A FAULT LIGHTS CHECK EXTINGUISH. . . . . . . . . . . . .MFC 1B AND MFC 2B FAULT LIGHTS CHECK FLASH. . . . . . . . . . . . . . . . .MFC 1B AND MFC 2B FAULT LIGHTS CHECK EXTINGUISH. . . . . . . . . . . . .

EMER AND ESS BUS SUPPLY IND CHECK ARROWS ILLUMINATED. . . . . . . . . .UNDV LIGHT CHECK EXTINGUUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . . . .PARKING BRAKE ACCU CHECK PRESSURE. . . . . . . . . . . . . . . . . . . . . . . . .

AUX HYD PUMP PB USE AS NECESSARY. . . . . . . . . . . . . . . . . . . . . . . . .PARKING BRAKE HANDLE SET TO PARKING. . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 CHECK AT G.I.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GUST LOCK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 + 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EEC 1 + 2 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS CONTROL LEVER CHECK ACCORDING TO ACTUAL FLAPS POSITION. .

SET AS NECESSARY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR CONTROL LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BOTH WIPERS ROTARY SELECTORS CHECK ON OFF POSITION. . . . . . . . . . .DC EXT PWR PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVERHEAD PANEL SCAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANY WHITE LIGHT EXTINGUISH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANN LT SW TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LIGHTS CHECK ALL ILLUMINATED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANN LT SW RETURN TO BRT OR DIM AS RQD. . . . . . . . . . . . . . . . . . . . . .

ENG 1 FIRE TEST : page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROP BRK (if installed) ON / LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CVR TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SIGNS PANEL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXIT LIGHT ARM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER LOCK XMTR AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

R

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 3

DEC 10

001

2.03.06


PROCEDURES TO BE USED WHEN USING A GPUFOR HOTEL MODE SEE 2.03.06 PAGES 4 AND 5.

CM2 COMPT SMK (if installed) TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXHAUST MODE RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 2 FIRE TEST : page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEDESTALFDEP CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRIMS CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

R ATPCS TEST : page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) STBY / TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VHF / NAV ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .XPDR STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE GATE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER AUDIO CANCEL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIL LOCK LIGHT (if installed) CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .EFIS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADAR STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTRAL PANELPWR MGT ROTARY SELECTOR TO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEC 1 + 2 (if installed) ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT LATERAL CONSOLE

CM1 N/W STEERING ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN MASK (ONCE A DAY) CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . .MKR TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT LATERAL CONSOLE

CM2 OXYGEN MASK (ONCE A DAY) CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . .LEFT AND RIGHT INSTRUMENT PANELS

ALL NO FLAG CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CLOCK SET TIME. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RMI / EHSI CROSSCHECK HEADING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 ADC SW SET TO ADEQUATE ADC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 4

DEC 09

001

2.03.06


PROCEDURES FOR HOTEL MODEFOR GPU USE SEE 2.03.06 PAGES 2 AND 3.

CM2 CARGO DOOR CTL panel cover (if installed) CLOSED. . . . . . . . . . . . . . . . . . . . .EMERGENCY EQUIPMENT CHECK FOLLOWING LIST : page 6. . . . . . . . . . .GEAR PINS ON BOARD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LATERAL AND OVERHEAD PANELS C/B CHECK SET, RESET AS APPLICABLE. .BAT TOGGLE SW ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC FAULT LIGHTS CHECK FOLLOWING SEQUENCE. . . . . . . . . . . . . . . . . . .

MFC 1A AND MFC 2A FAULT LIGHTS CHECK FLASH. . . . . . . . . . . . . . . . .MFC 1A AND MFC 2A FAULT LIGHTS CHECK EXTINGUISH. . . . . . . . . . . . .MFC 1B AND MFC 2B FAULT LIGHTS CHECK FLASH. . . . . . . . . . . . . . . . .MFC 1B AND MFC 2B FAULT LIGHTS CHECK EXTINGUISH. . . . . . . . . . . . .

EMER AND ESS BUS SUPPLY IND CHECK ARROWS ILLUMINATED. . . . . . . . . .UNDV LIGHT CHECK EXTINGUUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . . . .PARKING BRAKE ACCU CHECK PRESSURE. . . . . . . . . . . . . . . . . . . . . . . . .

AUX HYD PUMP PB USE AS NECESSARY. . . . . . . . . . . . . . . . . . . . . . . . .PARKING BRAKE HANDLE SET TO PARKING. . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 CHECK AT G.I.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GUST LOCK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 + 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EEC 1 + 2 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS CONTROL LEVER CHECK ACCORDING TO ACTUAL FLAPS POSITION. .

SET AS NECESSARY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR CONTROL LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BOTH WIPERS ROTARY SELECTORS CHECK ON OFF POSITION. . . . . . . . . . .ENG 2 FIRE TEST : page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROP BRK ON / LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATPCS TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVERHEAD PANEL SCAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANY WHITE LIGHT EXTINGUISH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANN LT SW TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LIGHTS CHECK ALL ILLUMINATED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANN LT SW RETURN TO BRT OR DIM AS RQD. . . . . . . . . . . . . . . . . . . . . .

PROP BRAKE LIGHT ON MEMO PANEL CHECK ILLUMINATED. . . . . . . . . . . . .ENG 2 START IN HOTEL MODE : page 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 1 FIRE TEST : page 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROP BRK (if installed) ON / LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CVR TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SIGNS PANEL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXIT LIGHT ARM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER LOCK XMTR AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

R

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 5

APR 08

001

2.03.06


PROCEDURES FOR HOTEL MODEFOR GPU USE SEE 2.03.06 PAGES 2 AND 3.

CM2 ENG 1 BLEED FAULT LIGHT CHECK ILLUMINATED. . . . . . . . . . . . . . . . . . . . . .AIR BLEED X VALVE OPEN LIGHT CHECK ILLUMINATED. . . . . . . . . . . . . . . . .COMPT SMK (if installed) TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXHAUST MODE RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEDESTALFDEP CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRIMS CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) STBY / TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VHF / NAV ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .XPDR STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE GATE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER AUDIO CANCEL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIL LOCK LIGHT (if installed) CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .EFIS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADAR STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTRAL PANELPWR MGT ROTARY SELECTOR TO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEC 1 + 2 (if installed) ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEFT LATERAL CONSOLE

CM1 N/W STEERING ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN MASK (ONCE A DAY) CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . .MKR TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RIGHT LATERAL CONSOLE

CM2 OXYGEN MASK (ONCE A DAY) CHECK : page 7. . . . . . . . . . . . . . . . . . . . . . .LEFT AND RIGHT INSTRUMENT PANELS

ALL NO FLAG CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CLOCK SET TIME. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RMI / EHSI CROSSCHECK HEADING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 ADC SW SET TO ADEQUATE ADC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 6

DEC 10

001

2.03.06


EMERGENCY EQUIPMENT LIST

-- exit hatch closed, handle locked and safetied, escape rope stowed-- life jackets (if applicable) stowed-- axe, flash lights, smoke goggles and oxygen masks stowed-- portable fire extinguisher safetied and pressure within the green area-- landing gear emergency extension handle stowed, cover closed-- protective glove

ENGINE FIRE TEST

ENG 1(2) FIRE HANDLE CHECK IN AND LATCHED. . . . . . . . . . . . . . . . . . . . . .ANY WHITE LIGHT EXTINGUISH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SQUIB TEST PB DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BOTH AGENT SQUIB LIGHT CHECK ILLUMINATE. . . . . . . . . . . . . . . . . . . .TEST SW SELECT ON FIRE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG FIRE RED LIGHT CHECK ILLUMINATES. . . . . . . . . . . . . . . . . . . . . . .

INTO ASSOCIATED FIRE HANDLE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CCAS CHECK ACTIVATES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : CRC + MW light flashing red + ENG 2 FIRE red light on CAP.FUEL SO RED LIGHT CHECK ILLUMINATES IN CL 1(2). . . . . . . . . . . . . . . . .

IF TEMPORARILY SELECTED OUT OF FUEL SO. . . . . . . . . . . . . . . . . . . .TEST SW SELECT ON FAULT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LOOP A AND LOOP B LIGHTS CHECK ILLUMINATE. . . . . . . . . . . . . . . . . .

ATPCS TEST

Static Test: has to be performed before each flight. The PL must be set at G.I. whenever a testis performed in hotel mode.

ATPCS TURN TO THE LEFT AND SELECT ARM. . . . . . . . . . . . . . . . . . . . . . . .ATPCS ARM LIGHT CHECK ILLUMINATES. . . . . . . . . . . . . . . . . . . . . . . . . . . .ATPCS SELECTOR SET TO ENG 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG 2 UPTRIM LIGHT CHECK ILLUMINATES. . . . . . . . . . . . . . . . . . . . . . .ARM LIGHT CHECK EXTINGUISHES AFTER 2 SECONDS. . . . . . . . . . . . . . .

ATPCS SELECTOR SET TO ENG 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 1 UPTRIM LIGHT CHECK ILLUMINATES. . . . . . . . . . . . . . . . . . . . . . .ARM LIGHT CHECK EXTINGUISHES AFTER 2 SECONDS. . . . . . . . . . . . . . .

Dynamic test: has to be done once a day, after landing of the last flight of the day.Refer to page 2.03.19 for developped procedure and informations.Note: a time delay of 10 minutes has to be observed after a test in order to not damagethe feathering pump, before take off.

... / ...

AA

RRR

RRRR

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 7

APR 08

001

2.03.06


OXYGEN MASK TEST without removing the mask (once a day)

On AUDIO CONTROL PANEL :INT / RAD SELECTOR SET TO INT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PRESS TO TEST AND RESET PB DEPRESS AND HOLD. . . . . . . . . . . . . . .Note : Hose and mask charged with oxygen.Observe blinker momentarily turns yellow and must turn dark if there is no leak.PRESS TO TEST AND RESET PB HOLD. . . . . . . . . . . . . . . . . . . . . . . . . .RED GRIPS ON EACH SIDE OF THE HOSE PRESS. . . . . . . . . . . . . . . . . . .Note : Oxygen pressure inflates the harness.Observe blinker momentarily turns yellow and must turn dark if there is no leak.PRESS TO TEST AND RESET PB HOLD. . . . . . . . . . . . . . . . . . . . . . . . . .EMERGENCY KNOB SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Emergency flow is tested.Observe blinker momentarily turns yellow during the oxygen flow and must turn darkwhen the knob is released.

Note : In this 3 cases, check that oxygen flow sounds through loudspeakers.OXY LO PR LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . .N/100% ROCKER LEVER SET TO 100%S. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TRIMS TEST

TRIMS DAILY CHECK FOR FIRST FLIGHT OF THE DAYPITCH, ROLL AND YAW TRIM OPERATION CHECK. . . . . . . . . . . . . . . . . .

-- Check the normal trim activation in both directions by depressingsimultaneously both control rocker switches

-- For few seconds depress independantly each single control rockerswitch and check the non--activation of the corresponding TRIM inboth possible directions

-- Reset TRIMS as required for take off

TRIMS CHECK BEFORE EACH FLIGHTPITCH, ROLL AND YAW TRIM OPERATION CHECK. . . . . . . . . . . . . . . . . .STBY PITCH TRIM OPERATION CHECK. . . . . . . . . . . . . . . . . . . . . . . . . .

STBY PITCH TRIM SW CHECK GUARDED IN OFF POSITION. . . . . .

... / ...

AA

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 8

DEC 09

001

2.03.06


ENGINE START

EEC FAULT LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . . .PEC FAULT LIGHT (if installed) CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR SET TO START. . . . . . . . . . . . . . . . . . . . . . .ENGINE AND PROPELLER AREA CHECK CLEAR. . . . . . . . . . . . . . . . . . . . . . .START 1(2) PB DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ON LIGHT CHECK ILLUMINATES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Starter electrically supplied.ENG ROTATION, NH MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� When passing 10% NH

CL 1(2) ADVANCE TO FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TIMING START. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Passing from FUEL SO to FTR is possible between 10% and 19% NH if

ITT > 200�C.LIGHT UP MONITOR WITHIN 10 SECONDS. . . . . . . . . . . . . . . . . . . . .� If 840��C < ITT < 950��C

EXCESSIVE ITT RECORD IN LOG BOOK. . . . . . . . . . . . . . . . . . . .� If ITT > 840��C more then 20 seconds, or if ITT > 950��C

CL 1(2) FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� When passing about 45% NH

START 1(2) PB ON LIGHT MONITOR EXTINGUISHES. . . . . . . . . . . . . . .� When passing about 61.5% NH

DC GEN 1(2) FAULT LIGHT MONITOR EXTINGUISHES. . . . . . . . . . . . . .ENGINE PARAMETERS CHECK STABILIZED AT IDLE VALUES. . . . . . . . . . .Note : NH 67% ± 2%, ITT 580�C ± 50�C, FF 110 kg/h (243 lb/h).Note : TQ indications are unreliable when CL in FTR position.

ENG START ROTARY SELECTOR OFF & START ABORT. . . . . . . . . . . . . . .PL 1(2) ADJUST AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : If Z ≥ 5000 ft and SAT ≥ ISA + 25�C, advance PL 1(2) up to GUST LOCK

stop.

HOT ENVIRONMENT START

In hot environments to prevent an engine starting from a “hot start” : High OAT or High residual ITT,it is recommended to delay the fuel opening up to 20% NH.

For residual ITT below 100°C, open fuel up to 10% NH.From 100°C to 200°C delay fuel opening by 1% NH per 10°C of residual ITT, up to 200°C (20% NH)Do not exceed 20% NH for fuel opening.

AA

R

ATR 42 Model : 400/500


NORMAL PROCEDURES

P 9

DEC 10

001

2.03.06


RECORDERS TEST

- On BATTERY MODE or HOTEL MODE:

CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green arc.DFDR: the status SYST light (on the FDEP or RCDR panel) has to be extinguished.Note: it can take over 1 minute to be extinguished after aircraft power up.

- On GPU:

Press on the RCDR PB (on the RCDR panel) and check ON light is illuminated.

CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green arc.DFDR: the status SYST light (on the FDEP or RCDR panel) has to be extinguished.Note: it can take over 1 minute to be extinguished after aircraft power up.

Press on the RESET PB (on the RCDR panel) and check ON light is extinguished.The status SYST light (on the FDEP or RCDR panel) has to be illuminated.Note: it can take over 1 minute to be illuminated after RESET PB action.

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 1

APR 08

001

2.03.07

INTRODUCTION

Cockpit preparation is plit between :-- system preparation : performed by first officer CM2 only-- cockpit final preparation : performed by captain CM1 and CM2 at their stations

All steps have to be performed before each flight except when specifically indicated.

Section content :

SYSTEM PREPARATION PAGES 2 TO 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVERHEAD PANEL PAGES 2 TO 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEDESTAL PAGE 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CENTER INSTRUMENT PANEL -- CAPTAIN PAGE 5. . . . . . . . . . . . . . . . . . .CAPTAIN LATERAL CONSOLE PAGE 5. . . . . . . . . . . . . . . . . . . . . . . . . . . .CAPTAIN INSTRUMENT PANEL PAGE 5. . . . . . . . . . . . . . . . . . . . . . . . . . .CENTER INSTRUMENT PANEL -- FIRST OFFICER PAGE 6. . . . . . . . . . . . . .FIRST OFFICER LATERAL CONSOLE PAGE 6. . . . . . . . . . . . . . . . . . . . . .FIRST OFFICER INSTRUMENT PANEL PAGE 6. . . . . . . . . . . . . . . . . . . . . .

FINAL COCKPIT PREPARATION PAGE 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 2

APR 08

001

2.03.07

SYSTEM PREPARATION

INTERNAL LIGHTING SET AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OVERHEAD PANEL

CALLS / SELCAL (if installed) CHECK LIGHT EXTINGUISHED. . . . . . . . . . . . .RESET AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG 1 PUMP ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RUN LIGHT CHECK ILLUMINATED. . . . . . . . . . . . . . . . . . . . . . . . . . . .FEED LO PR LIGHT CHECK EXTINGUISHES. . . . . . . . . . . . . . . . . . . . .LP VALVE CHECK IN LINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .X FEED VALVE CHECK X LINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If GPU is used (no HOTEL mode)ENG 2 APPLY SAME PROCEDURE. . . . . . . . . . . . . . . . . . . . . . . . . . .

DOORS SW TEST PB DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB OK / SVCE OK LIGHTS CHECK ILLUMINATED. . . . . . . . . . . . . . . .

PROVIDED ASSOCIATED DOORS ARE OPEN. . . . . . . . . . . . . . . . . . .

For all models

DOORS LIGHTS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPLR LIGHTS CHECK BOTH ILLUMINATED. . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR INDICATION CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR INDICATION CROSSCHECK with center instrument panel. . . . . . . .MFC PANEL SCAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : no amber light may be illuminated.

... / ...

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 3

APR 08

001

2.03.07

SYSTEM PREPARATION (CONT’D)

OVERHEAD PANEL (CONT’D)

EXT LIGHTS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COCKPIT VOICE RECORDER TEST PB DEPRESS. . . . . . . . . . . . . . . . . . .

POINTER MOVES BETWEEN GRADUATION 8 AND 10 CHECK. . . . . . . .FEED LO PR LIGHT CHECK EXTINGUISHES. . . . . . . . . . . . . . . . . . . . . . . .J If GPU is not used

EMER EXIT LIGHT ARM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI-- / DE--ICING LIGHTS CHECK ALL EXTINGUISHED. . . . . . . . . . . . . . .PROBES / WINDSHIELD HTG EXTINGUISH ANY WHITE LIGHT. . . . . . . . . .AC WILD ELEC POWER EXTINGUISH ANY WHITE LIGHT. . . . . . . . . . . . . .HYD PWR EXTINGUISH ANY WHITE LIGHT. . . . . . . . . . . . . . . . . . . . . . . .BLUE / GREEN PUMPS LO PR LIGHTS CHECK BOTH ILLUMINATED. . . . . .Note : any other HYD PWR lights has to be extinguished.EMER LOC XMTR (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CHECK TO AUTO, GUARDED AND LOCKWIRED. . . . . . . . . . . . . . . . . . . .SELCAL CODE SELECTION PANEL (if installed) AS RQD. . . . . . . . . . . . . . . .J If GPU is used

AIR BLEED / COMPT TEMP PANEL EXTINGUISH ANY WHITE LIGHT. . .COMPT TEMP SELECTORS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . .

J If GPU is not usedCOMPT AND DUCT INDICATIONS CHECK. . . . . . . . . . . . . . . . . . . . . .Note : Check that indications show realistic values with COMPT selectors on

flight COMPT and CABIN.OXYGEN HIGH PRESSURE INDICATION CHECK. . . . . . . . . . . . . . . . . . . .OXYGEN DURATION CHART (FCOM 2.01.05) CHECK. . . . . . . . . . . . . . . . .Note : To determine that quantity is sufficient for the scheduled flight.OXYGEN MAIN SUPPLY SELECT ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PB LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PAX SUPPLY CHECK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPT SMK TEST PB DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SMOKE DETECTORS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : When test is finished, reset AVIONICS VENT EXHAUST MODE

pushbutton to restart extract fan.

... / ...

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 4

APR 08

001

2.03.07


PEDESTAL

FDEP OR MCDU -- FDAU TIME BASE CHECK, ADJUST IF NECESSARY. . . .FDEP OR MCDU -- FLIGHT NUMBER CHECK, ADJUST IF NECESSARY. . . . .Note : numbers between 0000 and 7999 only.

RADIOS CHECK TRANSMISSION AND RECEPTION. . . . . . . . . . . . . . . . . .ADF SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .XPDR -- FID (if applicable) SELECT, INSERT FLIGHT ID. . . . . . . . . . . . . . . . .

STBY SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADIOS CHECK TRANSMISSION AND RECEPTION. . . . . . . . . . . . . . . . . .IDLE GATE LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . .

AND AMBER BAND VISIBLE ON THE LEVER. . . . . . . . . . . . . . . . . . . . . . .EMER AUDIO CANCEL SW CHECK GUARDED AND LOCKWIRED. . . . . . . .RADAR SELECT STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EFIS CTL PANELS -- EADI ON THEN CHECK COMPOSITE MODE. . . . . . . .EFIS CTL PANELS -- EHSI ON THEN CHECK NORMAL DISPLAY. . . . . . . . .

EADI AND EHSI BRIGHTNESS AS RQD. . . . . . . . . . . . . . . . . . . . . . . .BRGs AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

IF TCAS installedATC 1 STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS STBY / TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 5

APR 08

001

2.03.07


CENTER INTRUMENT PANEL - CAPTAIN

ADC SW SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Odd days : ADC 1 -- Even days : ADC 2.TAT CROSSCHECK WITH CONTROL TOWER INFORMATION. . . . . . . . . . .STBY INSTRUMENTS CHECK NO FLAG. . . . . . . . . . . . . . . . . . . . . . . . . . .STBY HORIZON PULL KNOB TO ERECT IF NECESSARY. . . . . . . . . . . . . .PWR MGT ROTARY SELECTOR CHECK TO. . . . . . . . . . . . . . . . . . . . . . . .ENG 1 INSTRUMENTS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OIL PRESS, FF, FU, NH, NP, TQ 0. . . . . . . . . . . . . . . . . . . . . . . . . . . .OIL / FUEL TEMP, ITT REALISTIC INFORMATION. . . . . . . . . . . . . . . . . .TQ TARGET BUG REALISTIC INFORMATION. . . . . . . . . . . . . . . . . . . . .

CROSSCHECK WITH ENG 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINE CONTROLS EXTINGUISH ANY WHITE LIGHT. . . . . . . . . . . . . . . .

CAPTAIN LATERAL CONSOLE

N/W STEERING SW CHECK GUARDED IN N/W STEERING POSITION. . . . . .J With NAV receivers ON

MKR SW TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Check 3 white boxes appear on bottom right of EADIs displaying O, M and Imarkers side by side.

MKR SW LO ??? except with 0043 ???. . . . . . . . . . . . . . . . . . . . . . . . . . . .AHRS 1 LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . .ATT / HDG, VOR / ILS, EFIS SG LIGHTS CHECK EXTINGUISHED. . . . . . . . .AUDIO SEL 1 LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . .GPWS SW CHECK GUARDED IN NORM POSITION. . . . . . . . . . . . . . . . . .GPWS FAULT LIGHT CHECK NOT ILLUMINATED ON CAP. . . . . . . . . . . . . .

CAPTAIN INTRUMENT PANEL

RMI / EHSI CROSSCHECK HEADING INFORMATION. . . . . . . . . . . . . . . . . .VSI CHECK NO FLAG AND POINTER INDICATES ZERO. . . . . . . . . . . . . . . .CLOCK CHECK TIME, ADJUST IF NECESSARY. . . . . . . . . . . . . . . . . . . . . .ASI CHECK NO FLAG, AIRSPEED POINTER INDICATES ZERO. . . . . . . . . . .

AND VMO POINTER INDICATES 250 kt. . . . . . . . . . . . . . . . . . . . . . . . . . .EADI CHECK NO FLAG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS TEST AS RQD (see FCOM 1.15.40). . . . . . . . . . . . . . . . . . . . . . . . .ALTIMETER CHECK NO FLAG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 6

APR 08

001

2.03.07


CENTER INTRUMENT PANEL - FIRST OFFICER

PRESSURIZATION LIGHTS CHECK ALL EXTINGUISHED. . . . . . . . . . . . . . .MAN RATE KNOB CHECK AT NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN PRESS IND CHECK DIFF AT ZERO, RATE AT ZERO. . . . . . . . . . . . . .

AND ALT AT PRESSURE ALTITUDE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STICK PUSHER / SHAKER FAULT LIGHT CHECK EXTINGUISHED. . . . . . . . .ANTI--SKID LIGHTS CHECK ALL EXTINGUISHED. . . . . . . . . . . . . . . . . . . .

FIRST OFFICER LATERAL CONSOLE

AHRS 2 LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . . . .ATT / HDG, VOR / ILS, EFIS SG LIGHTS CHECK EXTINGUISHED. . . . . . . . .AUDIO 2 SEL LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . .

FIRST OFFICER INTRUMENT PANEL

RMI / EHSI CROSSCHECK HEADING INFORMATION. . . . . . . . . . . . . . . . . .VSI CHECK NO FLAG AND POINTER INDICATES ZERO. . . . . . . . . . . . . . . .CLOCK CHECK TIME, ADJUST IF NECESSARY. . . . . . . . . . . . . . . . . . . . . .ASI CHECK NO FLAG, AIRSPEED POINTER INDICATES ZERO. . . . . . . . . . .

AND VMO POINTER INDICATES 250 kt. . . . . . . . . . . . . . . . . . . . . . . . . . .EADI CHECK NO FLAG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALTIMETER CHECK NO FLAG. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

... / ...

AA

ATR 42 Model : 400/500

COCKPIT PREPARATION

NORMAL PROCEDURES

P 7

APR 08

001

2.03.07

FINAL COCKPIT PREPARATION

CM1 PARKING BRAKE ON / PRESS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL ALTIMETERS SET BARO REFERENCE AND CHECK INDICATIONS. . . . . . . .

CM2 ATIS OBTAIN ATIS INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING ELEVATION SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Landing field elevation if QNH is used, ZERO if QFE is used.

ALL COM / NAV / GPS SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 FUEL QTY CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LO LVL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BOTH TANKS CHECK LOADED SYMETRICALLY. . . . . . . . . . . . . . . . . . . . .TOTAL FUEL QTY CHECK CORRESPONDS TO FLIGHT PLAN FUEL. . . . . . .MEMO PANEL CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PWR MGT ROTARY SELECTOR TO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 ENG F/U RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKE OFF DATA CARD (SEE xxx) 1ST PART FILLED. . . . . . . . . . . . . . . . . .

CM1 LOAD AND TRIM SHEET CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKE OFF WEIGHT .... -- TRIM SETTING ... ANNOUNCE. . . . . . . . . . . . . . .

ALL SPEED BUGS SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

-- External bugsS Lower value : V1S Intermediate valueFINAL TAKE OFF SPEED

VmLB0 normal conditiond orVmLB15 icing conditions and not less than V2

S Higher value : Minimum ICING SPEEDVmLB 0 icing conditions

-- Set internal bug to V2

CM1 TQ MANUAL BUGS SET TO TAKE OFF TORQUE. . . . . . . . . . . . . . . . . . . .Note : As a cross check procedure, TO torques should be computed by using power

setting torque tables with a tmperature not measured through aircraftsystems.

ALL SEATS, SEATS BELTS, HARNESSES AND RUDDER PEDALS ADJUST. . . . . .Note : Should be performed when rudder is in neutral position.

ALL FINAL COCKPIT PREPARATION CHECK LIST COMPLETED. . . . . . . . . .

AA

ATR 42 Model : 400/500

NORMAL PROCEDURES

BEFORE PROPELLER ROTATION/ BEFORE TAXI

P 1

DEC 09

001

2.03.08

BEFORE PROPELLER ROTATION

CM1 LOAD AND TRIM SHEET CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

START UP CLEARANCECM1 GROUND CREW CLEARANCE OBTAIN. . . . . . . . . . . . . . . . . . . . . . . . . . .CM2 ATC START UP CREW CLEARANCE OBTAIN. . . . . . . . . . . . . . . . . . . . . . .

CM1ALL DOORS CHECK CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL TAKE OFF BUGS SET AND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 ROLL AND YAW TRIMS RESET TO ZERO. . . . . . . . . . . . . . . . . . . . . . . . .PITCH TRIM SET FOR TAKE OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAKE OFF DATA CARD PREPARE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CDLS (if installed) ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 SEAT BELTS SW SEAT BELTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BEACON ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXIT LT ARM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL BEFORE PROPELLER ROTATION COMPLETED. . . . . . . . . . . . . . . . . . . . .

BEFORE TAXI

If propeller brake installed and if applicable :

CM1 PROP BRAKE OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 PROP BRK BLUE LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .Note : On PROP BRAKE control panel and on MEMO panel.

UNLK LIGHT CHECK FLASHES THEN EXTINGUISHES. . . . . . . . . . . . . . . . .

Then :

CM1 COCKPIT COM HATCH CHECK CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 CL 1 + 2 AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--SKID TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL BEFORE TAXI CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . . . . . .

AA

R

R

ATR 42 Model : 400/500

TAXI

NORMAL PROCEDURES

P 1

APR 08

001

2.03.09

TAXINote : when taxiing with tail wind component, use of reverse requires special care as wind

created by propeller reversion combined with tail wind will induce an exhaust gazreturn flow which may damage the nacelle. It is consequently recommended not toleave PL in reverse position for any period of time exceeding 10 seconds.

CM1 TAXI CLEARANCE OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAXI AND TO LIGHTS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL BRAKES CHECK NORMAL AND EMER. . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 AFCS SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Select assigned altitude, HDG LO BANK with runway heading, IAS with

V2+5kt and CPL on PF side.

CM1 RUDDER RELEASABLE CENTERING UNIT CHECK CENTERED. . . . . . . . . . .Note : Pedals centered, brief action on rudder trim switches.

ALL SPEED BUGS CROSSCHECK SETTINGS. . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 TO CONFIG TEST AND CHECK NO ALERT. . . . . . . . . . . . . . . . . . . . . . . .ATC CLEARANCE OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL INSTRUMENTS PANELS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Check no unnecessary flag on instruments.HORIZONS, HEADING / BEARING, BALL CHECK IN TURN. . . . . . . . . . . . . .

CM2 BLEED CHECK ALL LIGHTS EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . .COMPT TEMP SELECTOR AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ACW POWER CHECK ALL LIGHTS EXTINGUISHED. . . . . . . . . . . . . . . . . .

ALL AFCS SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Select assigned altitude, HDG LO BANK with runway heading, IAS with

V2+5kt and CPL on PF side.

CM1 TAKE OFF BRIEFING COMPLETE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-- Standard calls-- For significant failure before V1, CAPTAIN will call “STOP” and will take anynecessary stop actions

-- Above V1 take off will continue and no action will be taken except on CAPTAINcommand

-- Single engine procedure is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-- Acceleration altitude is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-- Departure clearance is . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 CABIN REPORT OBTAIN FROM CABIN ATTENDANT. . . . . . . . . . . . . . . . . . .

ALL TAXI CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

BEFORE TAKE OFF

NORMAL PROCEDURES

P 1

DEC 09

001

2.03.10

BEFORE TAKE OFF

CM2 TAKE OFF CLEARANCE OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIR FLOW NORM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVES AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GUST LOCK RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL FLIGHT CONTROLS CHECK FULL TRAVEL AND FREEDOM OF. . . . . . . . . .MOVEMENT IN PITCH, ROLL AND YAW. . . . . . . . . . . . . . . . . . . . . . . . . .

Note : For ROLL check SPOILER light.

Note : If BLEED ON, select both bleed valves on NORM FLOW.

Note : for aircraft fitted with CONT RELIGHT, set ENG START ROTARYSELECTOR to CONT RELIGHT in case of icing conditions, heavyprecipitations or contaminated runway.

CM1 CCAS TO INHI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXT LIGHTS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 XPDR / TCAS ALT / AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADAR AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL APM SET AND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL � When lined upFD BAR CENTER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL BEFORE TAKE OFF CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . .

AA

R

ATR 42 Model : 400/500

TAKE OFF

NORMAL PROCEDURES

P 1

APR 08

001

2.03.11

TAKE OFF

PF TAKE OFF ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKES RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL TIMING START. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF PL 1 + 2 ADVANCE TO POWER LEVER NOTCH. . . . . . . . . . . . . . . . . . . . .

PNF Note : Check actual torque matches take off torque (manual bug). Adjust ifnecessary by moving PL out of the notch as required.

F When reaching 60 ktNP CHECK 100%. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : NP 100% -- 0.6% / +0.8%.ATPCS ARM LIGHT CHECK ILLUMINATED. . . . . . . . . . . . . . . . . . . . .FDAU BUG CHECK DISPLAYS RTO VALUE. . . . . . . . . . . . . . . . . . . . .POWER SET CALL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AIRSPEED / ENGINE INSTRUMENTS SCAN THROUGHOUT TAKE OFF. . . .SEVENTY KNOTS ANNOUNCE WHEN READ ON PNF ASI. . . . . . . . . . . . .STBY ASI CROSSCHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF SPEED CROSSCHECK ON PF ASI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .I HAVE CONTROL ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF V1 ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F At VR

PNF ROTATE ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF AIRCRAFT HANDLING ROTATE SMOOTHLY. . . . . . . . . . . . . . . . . . .Note : Rotate smoothly to average single engine climb pitch attitude.SPEED ACCELERATE PROGRESSIVELY TO VmLB0. . . . . . . . . . . . . . .

F After lift offPNF POSITIVE CLIMB ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF GEAR UP ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PNF LDG GEAR LEVER UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LDG GEAR LIGHTS CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .AFCS YD ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

AFTER TAKE OFF

NORMAL PROCEDURES

P 1

APR 08

001

2.03.12

AFTER TAKE OFF

F When passing acceleration altitude

PF CLIMB SEQUENCE ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AFCS SELECTED SPEED INCREASE WITH PTW. . . . . . . . . . . . . . . . . .Note : In case of manual flight, this action will be performed by PNF.

PNF PL 1 + 2 CHECK IN THE NOTCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . .PWR MGT CLB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NP CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BLEED VALVES (if not already selected) ON. . . . . . . . . . . . . . . . . . . . . .Note : Pack 2 valve FAULT will illuminate during 10 seconds. A 10 seconds

delay is used for pack 2 valve to avoid pressure shocks.

TAXI AND TO LIGHTS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NO SMOKING SW OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Check actual torque matches climb torque. Adjust if necessary.Note : If the airline has chosen to reduce power in climb, set PLs

according to the airline derated tables.

PF F When passing VmLB0FLAPS 0 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 0 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS 0 ANNOUNCE WHEN INDICATED. . . . . . . . . . . . . . . . . . . .

PF AFCS ADU TARGET IAS SET DESIRED CLIMB SPEED. . . . . . . . . . . . . .

ALL F When passing transition altitudeALTIMETERS SET AND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Set standard pressure, 1013.2hPa / 29.92 in Hg.

ALL AFTER TAKE OFF CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

CRUISE

NORMAL PROCEDURES

P 1

DEC 09

001

2.03.13

CRUISE

PF � After acceleration to cruise speedPWR MGT ROTARY SELECTOR CRZ. . . . . . . . . . . . . . . . . . . . . . . . . .Note : when installed select CRZ1 or CRZ2.

Note : Check that the actual engine torque indication matches the cruiseobjective torque. Adjust if necessary.

PNF SEAT BELTS SW AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CRUISE SPEED LOW

ALERT

CONDITION VISUAL AURAL

Cruise speeddecrease

-- CRUISE SPEED LOW blue light on frontpanel

NIL

PROCEDURE

CRUISE SPEED LOW

Appears in cruise only, to inform the crew that an abnormal drag increase induces aspeed decrease of more than 10 kt compared with the expected speed

ICING CONDITIONS AND SPEED MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . .

REDUCED POWER SETTING IN CRUISE

The airline, according to its cost policy, can choose to cruise at reduced power, e.g. atlong--range power or given IAS. The associated cruise derated tables need to be availableon board for the flight crew. Those tables can be published with the FOS Module 2,In--flight performance, as shown in example in Figure 1.The PLs are set according to the torque given in the tables. This requires a PL adjustmentout of the notch.

Limitations:

The reduced power cruise is not allowed in case of icing conditions, as the IAS mayalready be decreased due to ice accretion on the airframe.In case of an engine failure, the PLs need to be immediately moved back into the notch,power management to MCT.

From a maintenance point of view, reduced power operations may achieve lower engineoverhaul costs as a result of the reduced power settings.

AA

R

R

ATR 42 Model : 400/500

CRUISE

NORMAL PROCEDURES

P 2

DEC 09

001

2.03.13

REDUCED POWER SETTING IN CRUISE (CONT’D)

Example:

Figure1: Long Range cruise performance table ) ATR 42--500 (PW127E)This is an example of a long--range cruise performance table generated with the FOSModule 2. In the case the cruise weight is 16t, the cruise FL 190, the torque is set to50.5% and the cruise IAS will be 174kts.

AA

ATR 42 Model : 400/500

DESCENT

NORMAL PROCEDURES

P 1

APR 08

001

2.03.14

DESCENT

PF CCAS RCL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIRCRAFT STATUS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF WEATHER AND LANDING INFORMATION OBTAIN. . . . . . . . . . . . . . . . . . . .LANDING WEIGHT, CONFIGURATION AND SPEEDS DETERMINE. . . . . . . . .DATA CARD FILL IN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING ELEVATION SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Landing field elevation if QNH is used, 0 if QFE is used.

ALL ASI BUGS SET AND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

-- External bugsSLower value : VGAS Intermediate valueSINGLE ENGINE : VmLB0 normal condiotions orCLIMB SPEED : VmLB15 icing conditions, and

not less than V2S Higher value : VmLB0 icing conditions

-- Set internal bug to VAPP

PNF TQ MANUAL BUGS SET TO GA TORQUE. . . . . . . . . . . . . . . . . . . . . . . . .

ALL ARRIVAL BRIEFING COMPLETEMain points are : -- minimum safe altitude

-- weather at destination-- approach procedures-- decision height-- go around procedures-- alternate and extra fuel

PNF DESCENT CLEARANCE OBTAIN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF AFCSASSIGNED ALTITUDE SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IAS OR VS MODE ENGAGE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .PTW AND PL USE AS RQD FOR DESCENT. . . . . . . . . . . . . . . . . . . . . . . .

ALL DESCENT CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

APPROACH

NORMAL PROCEDURES

P 1

APR 08

001

2.03.15

APPROACH

PNF SEAT BELTS SW SEAT BELTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NO SMKG SW NO SMOKING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL ALTIMETERS SET AND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF CABIN ALTITUDE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION : Max ∆P authorized at landing : 0.35 PSI.

CABIN REPORT FROM CABIN ATTEDANT OBTAIN. . . . . . . . . . . . . . . . . . .

ALL APPROACH CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 500

BEFORE LANDING

NORMAL PROCEDURES

P 1

APR 08

001

2.03.16

BEFORE LANDING - FLAPS 35 LANDING

F When passing deceleration altitude

ALL ALTITUDE CROSSCHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF PL 1 + 2 RETARD DOWN TO FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPEED REDUCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F When passing 170 kt

FLAPS 15 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 15 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF F When passing 160 ktGEAR DOWN ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS 25 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 25 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF LDG GEAR LEVER DN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PWR MGT TO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : NP remains unchanged.F When the three green lights are illuminated

FLAPS 15 -- LANDING GEAR DOWN ANNOUNCE. . . . . . . . . . . .TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF F When passing 150 ktFLAPS 35 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 35 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS 35 ANNOUNCE WHEN INDICATED. . . . . . . . . . . . . . . . . . .

PF PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADJUST TO MAINTAIN VAPP AND NOT LESS THAN VMCL. . . . . . .

ALL SPEED VERSUS ICING AOA CHECK AND SET. . . . . . . . . . . . . . . .

PF TAXI, TO and LAND EXT LIGHTS ON. . . . . . . . . . . . . . . . . . . . . . .

ALL BEFORE LANDING CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . .

AA

Mod : 4450 or 4580 ATR 42 Model : 500

BEFORE LANDING

NORMAL PROCEDURES

P 2

APR 08

110

2.03.16

BEFORE LANDING - FLAPS 25 LANDING

F When passing deceleration altitude

ALL ALTITUDE CROSSCHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF PL 1 + 2 RETARD DOWN TO FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPEED REDUCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F When passing 170 kt

FLAPS 15 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 15 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF GEAR DOWN ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF LDG GEAR LEVER DN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PWR MGT TO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : NP remains unchanged.F When the three green lights are illuminated

FLAPS 15 -- LANDING GEAR DOWN ANNOUNCE. . . . . . . . . . . .TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 LDG FLAP 25 PB SET TO ON. . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF F When passing 160 ktFLAPS 25 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLAPS 25 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS 25 ANNOUNCE WHEN INDICATED. . . . . . . . . . . . . . . . . . .

PF PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADJUST TO MAINTAIN VAPP AND NOT LESS THAN VMCL. . . . . . .

ALL SPEED VERSUS ICING AOA CHECK AND SET. . . . . . . . . . . . . . . .

PF TAXI, TO and LAND EXT LIGHTS ON. . . . . . . . . . . . . . . . . . . . . . .

ALL BEFORE LANDING CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

GO AROUND

NORMAL PROCEDURES

P 1

APR 08

001

2.03.17

GO AROUND

PF Simultaneously :GO AROUND ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GO AROUND PB ON PL 1 + 2 DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 ADVANCE TO RAMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS ONE NOTCH CALL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PITCH ATTITUDE ROTATE TO GO AROUND PITCH ATTITUDE. . . . . . . . . . .

PNF FLAPS RETRACT ONE NOTCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NP CHECK NP = 100%, ADJUST AS NECESSARY. . . . . . . . . . . . . . . . . . . .

PF FD BARS FOLLOW. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP DISCONNECT ALARM CANCEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPEED ACCELERATE TO OR MAINTAIN VGA (FCOM 2.02.01 page 4). . . . . . .

PNF F When positive rate of climb is achievedPOSITIVE CLIMB ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF GEAR UP COMMAND. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF F When climb is establishedLDG GEAR LEVER UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HDG/IAS SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS X ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : FLAPS X is one notch less than final approach FLAPS setting.GEAR UP ANNOUNCE WHEN INDICATED. . . . . . . . . . . . . . . . . . .PITCH / BANK ATTITUDES MONITOR. . . . . . . . . . . . . . . . . . . . . . .SPEED / FLIGHT PATH MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . .ENGINES PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

LANDING

NORMAL PROCEDURES

P 1

APR 08

001

2.03.18

LANDING

PNF 500 FEET ABOVE MINIMUM ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . .100 FEET ABOVE ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MINIMUM, DECIDE ANNOUNCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PF LAND or GO AROUND ANNOUNCE AS APPROPRIATE. . . . . . . . . . . . . . . .AP DISCONNECT PB PRESS TWICE. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF FLIGHT PARAMETERS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F After touch downIDLE GATE AUTOMATIC RETRACTION CHECK. . . . . . . . . . . . . . .

PF PL GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PNF BOTH LOW PITCH LIGHTS ILLUMINATED CHECK AND ANNOUNCE. . . .

PF REVERSE USE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 NOSE WHEEL STEERING CONTROL. . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 CONTROL WHEEL HOLD AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

AFTER LANDING

NORMAL PROCEDURES

P 1

DEC 10

001

2.03.19

AFTER LANDING

CM1 FLAPS 0 ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 FLAPS 0 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRIMS RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GUST LOCK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLIGHT CONTROLS CHECK LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . .XPDR / TCAS / RADAR STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LAND LIGHTS / STROBES OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--/DE--ICING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR OFF. . . . . . . . . . . . . . . . . . . . . . . . .ENG TEST : last flight of the day (Dynamic ATPCS Test)

CAUTION : Do not perform ENG TEST while taxiing as ACW is temporarily lostand, consequently, both main HYD pumps are temporarily lost as well.

Conditions :-- CL 1 + 2 on AUTO-- PL 1 + 2 at GI-- ATPCS pushbutton depressed; OFF extinguished-- PWR MGT on TO position

ARM positions :-- ARM light illuminates green-- Torque indications increase, NP and NH indications decrease

ENG position :-- PW121A : selected engine torque decreases below 18%-- PW127E/PW127M : selected engine torque decreases below 21%-- Opposite engine :-- UPTRIM light illuminates-- Torque does not change, NP and NH increase slightly

-- 2.15 seconds later :-- concerned propeller is automatically feathered-- ARM green light extinguishes

Note : If ENG TEST must be repeated, wait 10 minutes before setting ATPCSselector in ENG position in order not to damage feathering pump (windingheating).

CM1 � After at least one minuteCL 1 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FU 1 NOTE THEN RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note : Keep engine running at least oneminute at Gl power before shut downto assist in reducing residual heat build up in the engine and nacelle.

Note : Maintain feather position for 20 seconds before selecting FUEL SO(required for oil capacity check by maintenance and for properfeathering).

ALL AFTER LANDING CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . .

AA

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RR

ATR 42 Model : 400/500

PARKING

NORMAL PROCEDURES

P 1

APR 08

001

2.03.20

PARKING

Note : as often as possible, park the aircraft with wind relative to the nose at 10 o’clockto minimize noise and exhaust gaz interference when in hotel mode.

CM1 PARKING BRK ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAXI & TO LIGHTS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : If propeller brake is used, be sure propeller brake area is clear and

protected.

Last flight of the dayGUST LOCK RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CONTROL COLUMN PUSH IN NOSE DOWN POSITION. . . . . . . . . . .STICK PUSHER/SHAKER YES TEST procedure (FCOM 1.02.10)APPLYGUST LOCK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PITCH AN ROLL CONTROLS CHECK LOCKED. . . . . . . . . . . . . . . . .

CL 2 FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : If propeller brake is not available and provided propeller brake is

removed, activate PROP BRK switch and check AIR BLEED XVALVE OPEN light illuminates.

J If PROP BRAKE is used for MODE HOTELREADY LIGHT CHECK ILLUMINATED. . . . . . . . . . . . . . . . . . . . . . . .PROP BRK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UNLK LIGHT CHECK ILLUMINATED THEN EXTINGUISHED. . . . . . .PROP BRK LIGHTS CHECK ILLUMINATED. . . . . . . . . . . . . . . . . . . .

FU NOTE THEN RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SEAT BELTS SW OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM2 GROUND CONTACT AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CM1 TAIL PROP AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALL PARKING CHECK LIST COMPLETED. . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

LEAVING THE AIRCRAFT

NORMAL PROCEDURES

P 1

APR 08

001

2.03.21

LEAVING THE AIRCRAFT

OXYGEN MAIN SUPPLY OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ICE AND RAIN PROTECTION OFF. . . . . . . . . . . . . . . . . . . . . . . . . . .EXT LIGHTS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXIT LIGHT DISARM. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EFIS / RADAR / COM / NAV OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CDLS (if installed) OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BAT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

CONTENTS


P 1

DEC 09

001

2.04.00

2.04.00 CONTENTS

2.04.01 INTRODUCTION

2.04.02 POWER PLANTIN FLT ENG FIRE OR SEVERE MECHANICAL DAMAGEON GND ENG FIRE OR SEVERE MECHANICAL DAMAGEBOTH ENGINES FLAME OUTENG FLAME OUT AT TAKE OFF

2.04.03 SMOKESMOKEELECTRICAL SMOKEAIR COND SMOKEFWD SMOKEAFT SMOKEAUX AFT COMPT SMOKE

2.04.04 ELECTRICAL SYSTEMDUAL DC GEN LOSS

2.04.05 MISCELLANEOUSEMERGENCY DESCENTDITCHINGFORCED LANDINGON GROUND EMERGENCY EVACUATIONBOMB ON BOARDSEVERE ICINGRECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL

AA

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ATR 42 Model: 400/500

INTRODUCTION


P 2

DEC 09

001

2.04.01

PROCEDURES INITIATION

-- No action will be taken (apart from depressing MW pb):. Until flight path is stabilized.. Under 400 ft above runway (except for propeller feathering after engine failureduring approach at reduced power if go around is considered).

-- Before performing a procedure, the crew must assess the situation as a whole, takinginto consideration the failures, when fully identified, and the constraintsimposed.

ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT

Basic airmanship calls for a management review of the remaining aircraft capabilitiesunder the responsability of CM1.

CCAS

When TO INHI has been selected, until the first leg of landing gear unlocks, all alerts areinhibited except:

WARNING-- ENG 1 FIRE-- ENG 2 FIRE-- CONFIG-- FLAPS UNLK-- LDG GEAR NOT DN-- EXCESS ALT-- EXCESS CAB ∆P-- PITCH DISCONNECT-- PROP BRK (if applicable)

CAUTION-- EFIS COMP

ADVISORY-- PRKG BRK-- GPWS-- MAINT PANEL

AA

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ATR 42 Model : 400/500

POWER PLANT


P 1

DEC 07

001

2.04.02

IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE

ALERT


Fire signal -- MW light flashing red-- Associated ENG FIRE redlight on CAP-- red light in associated FIREhandle

-- FUEL SO red light inassociated CL

CRC

PROCEDURE

IN FLIGHT ENG FIRE OR SEVEREMECHANICAL DAMAGE

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F After 10 seconds

FIRST AGENT affected side DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If fire after further 30 seconds

SECOND AGENT affected side DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LAND ASAPSINGLE ENG OPERATION procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- Fire handle remains illuminated as long as a fire is detected.-- The 10 seconds delay allows to reduce nacelle ventilation in order to increase the agenteffect.

-- CRC stops when depressing MW. May be cancelled by use of EMER AUDIO CANCELSW.

-- Do not attempt to restart engine.-- Refer to SINGLE ENG OPERATION procedure.

AA

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ATR 42 Model : 400/500

POWER PLANT


P 2

DEC 07

001

2.04.02

ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE

PROCEDURE

ON GROUND ENG FIRE OR SEVEREMECHANICAL DAMAGE

PL 1+2 GI / REVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F When aircraft stopped

PARKING BRAKE ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1+2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRST AGENT affected side DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If fire after further 30 secondsSECOND AGENT affected side DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . .

J If evacuation requiredON GROUND EMER EVACUATION procedure APPLY. . . . . . . . . . . . . . .

COMMENTS

-- Same comments as in flight

-- The aircraft may be stopped using full reverse

Notify ATC the nature of the emergency and state intentions. Only VHF1 is available onbattery

-- Battery is left ON until leaving the aircraft to ensure cabin communication. Only PA isavailable on battery.

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ATR 42 Model : 400/500

POWER PLANT


P 3

DEC 10

001

2.04.02

BOTH ENGINES FLAME OUT

ALERTAn engine flame out may be recognized by a rapid decrease in ITT and in NH.

PROCEDURE

BOTH ENGINES FLAME OUT

PL 1 + 2 FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If NH drops below 30 % (no automatic relight)

CL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FUEL SUPPLY CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OPTIMUM SPEED Vm HB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAPT EHSI OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COMMUNICATIONS VHF 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR START A & B. . . . . . . . . . . . . . . . . . . . .

ENG 2 RELIGHTENG 2 START pb ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .�When NH above 10%

CL 2 FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 2 RELIGHT MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 2 then PL 2 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG 1 RELIGHTENG 1 START pb ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .�When NH above 10%

CL 1 FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 1 RELIGHT MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 then PL 1 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If neither engine startsCL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START rotary selector OFF/START ABORT. . . . . . . . . . . . . . . . . . . . . .FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FORCED LANDING or DITCHING PROCEDURE APPLY. . . . . . . . . . . . . . .

CAUTION : Do not select AVIONICS VENT EXHAUST MODE to OVBD.

� If engine(s) recoveredCL / PL engine(s) recovered AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If one engine not recovered

CL engine NON recovered FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure APPLY. . . . . . . . . . . . . . . . . . . . .

SYSTEMS affected RESTORE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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ATR 42 Model : 400/500

POWER PLANT


P 5

DEC 09

001

2.04.02

ENG FLAME OUT AT TAKE OFF

ALERT

An engine flame out may be recognized by:

-- Sudden dissymmetry-- TQ decrease-- Rapid ITT decrease

PROCEDURE

ENG FLAME OUT AT TAKE OFF

UPTRIM CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AUTOFEATHER CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If no uptrim

PL 1 + 2 ADVANCE TO THE RAMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BLEEDS and PACKS FAULT lights CHECK LIT. . . . . . . . . . . . . . . . . . . . . . . . . . .

� Above 400ft AGL

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BLEED engine alive OFF if necessary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If damage suspected

FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SINGLE ENG OPERATION PROCEDURE APPLY. . . . . . . . . . . . . . . . . . . .

� If no damage suspected

ENG RESTART IN FLIGHT PROCEDURE APPLY. . . . . . . . . . . . . . . . . . . . .

� If unsuccessful :

SINGLE ENG OPERATION PROCEDURE APPLY. . . . . . . . . . . . . . . . .

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ATR 42 Model : 400/500

SMOKE


P 1

DEC 07

001

2.04.03

SMOKE

PROCEDURE

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 APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . .

J If air conditioning smoke identifiedAIR COND SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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

J If AFT SMK illuminated or smoke in AFT zone of aircraftAFT SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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ATR 42 Model 400/500

SMOKE


P 2

DEC 09

001

2.04.03

ELECTRICAL SMOKE

ALERT


Smoke detected in the

avionics ventilation circuit

-- MW light flashing red

-- ELEC SMK red light on CAP

CRC

PROCEDURE

ELECTRICAL SMOKE

SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AIR FLOW HIGH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DC SVCE AND UTLY BUS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DC BTC ISOL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ACW GEN 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SUSPECTED EQUIPMENTS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If smoke origin not identifiedLAND ASAP

ACW TOTAL LOSS procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If smoke origin identified

NOT AFFECTED EQUIPMENTS RESTORE. . . . . . . . . . . . . . . . . . . . . . . . .

�When �P < 1 PSI

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

AVIONICS VENT EXHAUST MODE NORM. . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- Avionics compartment ventilation without cabin contamination is ensured by :-- selecting AVIONICS VENT EXHAUST mode OVBD-- shuting off the recirculation fans-- selecting the PACKS AIR FLOW HIGH.

-- Auto isolation is prepared on the main electrical system by opening the BTC.-- Suspected equipment may be shut off contingently by pulling out associated circuit

breaker.-- When �P < 1 PSI, OVBD VALVE is selected FULL OPEN and AVIONICS VENT

EXHAUST mode NORM in order to recover air evacuation capability through theEXTRACT FAN without any pressurization problem.

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ATR 42 Model : 400/500

SMOKE


P 3

DEC 10

001

2.04.03

AIR COND SMOKE

PROCEDURE

AIR COND SMOKE

SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PACK VALVE 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If smoke persists

PACK VALVE 1 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PACK VALVE 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : Evacuation of air conditioning smoke may trigger electrical smokewarning. Disregard it.

ENGINES PARAMETERS CAREFULLY MONITOR. . . . . . . . . . . . . . . . . . . . . . . .

� If any anomaly occurs such as :

-- amber engine caution illumination associated to local ITT alert

-- total loss of NL indication

-- engine abnormality clearly identified (NH, NL, ITT indications, noise, surge...)

CAUTION : Confirm which engine is showing signs of abnormal operation inorder to avoid shutting down the safe engine.

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SINGLE ENG OPERATION procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- Ensure crew communication is established. Avoid the use of interphone position tominimize interference from oxygene mask breathing noise. Check oxygen mask at100%.

-- Recirculation fans are switched off to limit cabin contamination.

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ATR 42 Model : 400/500

SMOKE


P 4

DEC 10

001

2.04.03

FWD SMOKE

ALERT


Smoke detected in theforward cargo compartment

-- MW lt flashing red-- FWD SMK red lt on CAP

CRC

Smoke detected in the cargo bay(CARGO VERSION ONLY)

-- MW It flashing red-- FWD SMK red It on CAP, or AFTSMK red It on CAP, or FWD SMKred lt on CAP and at least 1 CNTNRSMK redlt illuminated on overheadpanel, or AFT SMK red lt on CAPand at least 1 CNTNR SMK red ltilluminated on overhead panel.

PROCEDURE

FWD SMK

1) PASSENGERS VERSIONSMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN CREW (PA) ADVISE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AIR FLOW HIGH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EXTRACT AIR FLOW LEVER (RH MAINT PANEL) CLOSED. . . . . . . . . . . . . . . . .CABIN CREW WITH PORTABLE EXTINGUISHER LOCATE and KILL SOURCE OFSMOKE

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

2) CARGO VERSIONSMOKE porcedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB ALT MAX INCREASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG 2 BLEED (except when in single bleed operation) OFF. . . . . . . . . . . . . . . . . . .PACK VALVE 2 (except when in single pack operation) OFF. . . . . . . . . . . . . . . . . . .CAB VENT AIR FLOW OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLIGHT COMPT TEMP SEL HOT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain minimum

FL160, FL 200 is recommended.

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

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ATR 42 Model : 400/500

SMOKE


P 5

APR 08

001

2.04.03

COMMENTS-- Ensure crew communication is established. Avoid the use of interphone position tominimize interference from oxygen mask breathing noise. Check oxygen mask at100 %.

-- Cargo ventilation without cabin or cockpit contamination is ensured by :. selecting AVIONICS VENT EXHAUST mode OVBD. shuting off the recirculation fans. selecting HIGH the PACKS AIR FLOW. isolating the cockpit panels ventilation by selecting EXTRACT AIR FLOW toCLOSED.

-- Cabin crew is in charge to locate and kill source of smoke with his extinguisher.-- Cabin crew uses the portable oxygen bottle with the full face mask on 100 % positionwith full pressure. A fire extinguisher (3 kg -- 7 Lbs) is available at the left frontLocker).

-- When ∆P < 1 PSI, OVBD VALVE is selected full open and avionics VENT NORM inorder to recover air evacuation capability through the extract fan without anypressurization problem.

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ATR 42 Model : 400/500

SMOKE


P 6

DEC 09

001

2.04.03

AFT SMOKE

ALERT


Smoke detected in the aftcargo compartment or in thelavatory

-- MW lt flashing red-- AFT SMK red lt on CAP

CRC

Smoke detected in the cargo bay(CARGO VERSION ONLY)

-- MW It flashing red-- FWD SMK red It on CAP, orAFT SMK red It on CAP, orFWD or AFT SMK red lt on CAPand at least 1 CNTNR SMK redlt illuminated on overhead panel.

PROCEDURE

AFT SMK

1) PASSENGERS VERSION

SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CABIN CREW ADVISE FOR ACTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AIR FLOW HIGH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2) CARGO VERSION

SMOKE procedure APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAB ALT MAX INCREASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG 2 BLEED (Except when in single bleed operation) OFF. . . . . . . . . . . . . . . . . .

PACK VALVE 2 (Except when in single pack operation) OFF. . . . . . . . . . . . . . . . . . .

CAB VENT AIR FLOW OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIGHT COMPT TEMP SEL HOT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain minimum FL 160, FL 200 is recommended.

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

COMMENTS (PASSENGERS VERSION ONLY)

-- The cabin crew is in charge to locate and kill the source of smoke, if possible, usingthe portable fire extinguisher located in the cabin. Before entering the aft cargo area,the cabin attendant must wear an oxygen mask. To leave the aft cargo door open mayinduce some cabin contamination therefore it must be avoided.

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ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 1

DEC 07

001

2.04.04

DUAL DC GEN LOSS

PROCEDURE

DUAL DC GEN LOSS

DC GEN 1 + 2 OFF then ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If no generator recovered

HYD GREEN PUMP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TRU ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Make sure that TRU arrow illuminates, BAT arrows extinguish.MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . .BAT SW OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC (VHF 1 or HF or HF 2) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MIN CAB LIGHT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : NAV lights switch set to ON position is necessary to provide IEP

illumination.STICK PUSHER / SHAKER OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STICK PUSHER/SHAKER FAULT PROCEDURE APPLY. . . . . . . . . . . . . . . .SIDE WINDOWS ANTI--ICING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADC SW SET to ADC 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC SW SET to ATC 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU MAN MODE LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F When TLU LO SPD illuminates

TLU AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION : Avoid large rudder input if IAS above 180 kt.BUS EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F Before descent

PAX INSTRUCTIONS USE PA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : Selecting HYD X FEED to open position allows to recover green

hydraulic system.F At touch down

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

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ATR 42 Model : 400/500

MISCELLANEOUS


P 1

DEC 07

001

2.04.05

EMERGENCY DESCENT

PROCEDURE

EMERGENCY DESCENT

OXYGEN MASKS / CREW COMMUNICATIONS AS RQD. . . . . . . . . . . . . . . . . .GOOGLES AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DESCENT INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 + 2 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OXYGEN PAX SUPPLY AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SPEED MMO / VMO (or less if structural damage is suspected). . . . . . . . . . . . . .SIGNS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MEA CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- Oxygen may be used with N/100 % rocker in N position if air in the cabin is notcontaminated.

-- Maximum airspeed is MMO/VMO. But if structural damage is suspected, use the flightcontrols with care and reduce speed as appropriate. Landing gear may be extended inorder to increase rate of descent.

-- Notify ATC of the nature of the emergency encountered and state intentions. In theevent ATC cannot be contacted, select code A77 or transmit the distress message onone of the following frequencies (VHF) 121,5 MHz or (HF) 8364 KHz. Only VHF 1 isavailable on battery.

-- CL are selected 100%OVRD to increase drag and consequently to increase the rate ofdescent.

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ATR 42 Model : 400/500

MISCELLANEOUS


P 2

DEC 09

001

2.04.05

DITCHING

PROCEDURE

DITCHING

� Preparation (time permitting)ATC (VHF1 or HF or HF 2) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN CREW (PA) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SIGNS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TERR (if TAWS installed) OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN and COCKPIT PREPARE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

. Loose equipment secured

. Survival equipment prepared

. Belts and shoulder harness locked.AUTO PRESS -- LDG ELEVATION SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Approach

� If�P≠0AUTO PRESS DUMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PACKS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE FULL CLOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS (if available) 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR LEVER UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� 30 secondes before impact or 1250 ft above sea levelDITCH pb ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . .CABIN REPORT OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� Before ditching (200 ft)MINIMIZE IMPACT SLOPEOPTIMUM PITCH ATTITUDE FOR IMPACT 9�. . . . . . . . . . . . . . . . . . . . . . . .BRACE FOR IMPACT ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRE HANDLES 1 + 2 PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : in case of night ditching, shutting down both engines may be performed, at

captain discretion, immediately after the impact (to avoid loss of landing lightsduring flare out).

� After ditchingNote : After ditching, one aft door will be under the water line.CABIN CREW (PA) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EVACUATION INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before leaving aircraft

BAT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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ATR 42 Model : 400/500

MISCELLANEOUS


P 5

DEC 09

001

2.04.05

FORCED LANDING

PROCEDURE

FORCED LANDING

� Preparation (time permitting)

ATC (VHF1 or HF or HF 2) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CABIN CREW (PA) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SIGNS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TERR (if TAWS installed) OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CABIN and COCKPIT PREPARE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

. Loose equipment secured

. Survival equipment prepared

. Belts and shoulder harness locked.

AUTO PRESS -- LDG ELEVATION SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� Approach

FLAPS (if available) 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LDG GEAR LEVER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AUTO PRESS DUMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . . .

CABIN REPORT OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� Before impact (200 ft)

BRACE FOR IMPACT ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FIRE HANDLES 1 + 2 PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note : in case of night forced landing, shutting down both engines may beperformed, at captain discretinh, immediately after the impact (to avoid loss oflanding lights during flare out).

� After impact, when A/C stopped


AGENTS DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EVACUATION INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before leaving aircraft

BAT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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ATR 42 Model : 400/500

MISCELLANEOUS


P 7

DEC 09

001

2.04.05

ON GROUND EMER EVACUATION

PROCEDURE

ON GROUND EMER EVACUATION

AIRCRAFT / PARKING BRAKE STOP / ENGAGE. . . . . . . . . . . . . . . . . . . . . . . .

AUTO PRESS DUMP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ATC (VHF1) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MIN CAB LIGHT ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


FIRE HANDLES 1 + 2 PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AGENTS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . . .

FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EVACUATION (PA) INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before leaving aircraft

BAT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- Careful analysis is required to decide passenger evacuation, however useful timeshould not be wasted.

-- Notify ATCon the nature of theemergency andstate intentions.Only VHF1 isavailableon battery.

On battery, only PA is available to communicate with cabin crew.

R

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MISCELLANEOUS


P 11

DEC 10

001

2.04.05

RECOVERY AFTER STALL ORABNORMAL ROLL CONTROL

CONTROL WHEEL PUSH FIRMLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If flaps 0� configurationFLAPS 15�. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PWR MGT MCT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL / PL 100% / MCT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If flaps are extendedPWR MGT MCT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL / PL 100% / MCT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note: This procedure is applicable whatever the LDG GEAR position is ( DOWN orUP).

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ATR 42 Model : 400/500

CONTENTS

PROCEDURES FOLLOWING FAILURE

P 1

DEC 10

001

2.05.00

2.05.00 CONTENTS

2.05.01 INTRODUCTION

2.05.02 POWER PLANTSINGLE ENG OPERATIONSTART FAULTX START FAILABNORMAL PARAMETERS DURING STARTEXCESSIVE ITT DURING STARTNO ITT IND DURING STARTNO NH DURING STARTENG NAC OVHTABNORMAL ENG PARAMETERS IN FLIGHTFIRE LOOP FAULTABNORMAL PROP BRK (If applicable)ENG RESTART IN FLIGHTENG STALLONE EEC FAULTBOTH EEC FAULTENGINE FLAME OUTIDLE GATE FAILUNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS (if applicable)PEC SGL CHPEC FAULTLO PITCH IN FLIGHTENG OVER LIMITPROP OVER LIMITENG OIL TEMP BELOW 45�CENG OIL TEMP HIGHENG OIL LO PR

2.05.03 FUELFUEL ABNORMAL TEMPFUEL CLOGFEED LO PRFUEL LO LVLFUEL LEAK

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R

ATR 42 Model : 400/500

CONTENTS


P 2

DEC 09

001

2.05.00

2.05.04 ELECTRICAL SYSTEMDC BUS 1 OFFDC BUS 2 OFFAC BUS 1 OFF / AC BUS 2 OFFACW BUS 1 OFF / ACW BUS 2 OFFACW TOTAL LOSSDC ESS BUS OFFDC EMER BUS OFFDC GEN FAULTINV FAULTACW GEN FAULTDC SVCE/UTLY BUS SHEDBAT CHG FAULTDUAL BAT CHG LOSSBAT DISCHARGE IN FLIGHTSTBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS

2.05.05 HYDRAULICHYD LO LVLBOTH MAIN HYD PUMPS LOSSBOTH HYD SYS LOSSHYD LO PR / HYD OVHT

2.05.06 FLIGHT CONTROLSFLAPS UNLKFLAPS JAM / UNCOUPLED / ASYMREDUCED FLAPS LANDINGSTICK PUSHER / SHAKER FAULTPITCH TRIM ASYM (LOCAL LIGHT)PITCH TRIM INOPERATIVEDUTCHROLL TENDENCY / RUDDERRELEASABLE CENTERINGUNIT FAILPITCH DISCONNECTPITCH RECONNECTION ON GROUNDTLU FAULTAIL LOCK LIT (if applicable)ELEVATOR JAMAILERON JAM / SPOILER JAMRUDDER JAM

2.05.07 LANDING GEARLDG GEAR GRAVITY EXTENSIONLANDING WITH ABNORMAL LDG GEARLDG GEAR UNSAFE INDICATIONLDG GEAR RETRACTION IMPOSSIBLEANTI--SKID FAULTBRK TEMP HOT

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ATR 42 Model : 400/500

CONTENTS


P 3

OCT 08

001

2.05.00

2.05.08 AIRBLEED VALVE FAULTBLEED OVHTBLEED LEAKX VALVE OPENPACK VALVE FAULTBOTH PACK VALVES FAULTRECIRC FAN FAULTDUCT OVHTEXCESS CAB ALTAUTO PRESS FAULTEXCESS CAB nPAVIONICS VENT EXHAUST MODE FAULTOVBD VALVE FAULT

2.05.09 DE/ANTI ICEAFR AIR BLEED FAULTDE--ICING AIR FRAME FAULTDE--ICING MODE SEL FAULTMODE SEL AUTO FAULTICE DETECT FAULTDE-- / ANTI-- ICING ENG FAULTANTI--ICING PROP FAULTANTI--ICING HORNS FAULTSIDE WINDOW / WINDSHIELD HTG FAULTPROBES HTG FAULT

2.05.10 AUTOPILOTAILERON MISTRIM (ADU MESSAGE)or EXCESSIVE LATERAL TRIM REQUIREDor ABNORMAL FLIGHT CHARACTERISTICSPITCH MISTRIM (ADU MESSAGE)PITCH TRIM FAIL (ADU MESSAGE) (If applicable)DADC DATA INVALID (ADU message)

2.05.11 AIRCRAFT PERFORMANCE MONITORINGRefer to 2.02.21

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ATR 42 Model : 400/500

CONTENTS


P 4

DEC 10

001

2.05.00

2.05.12 AVIONICSAUDIO SEL FAULTAHRS A/ERECT FAILEFIS COMPADC SW FAULTADU FAILUREADC FAULTAHRS FAILSGU FAILCRT FAIL

2.05.13 MISCELLANEOUSCOCKPIT DOOR CONTROL PANEL FAULT (if installed)LOSS OF RADIO ALTIMETER INFORMATIONSMK DET FANS FAULTDOORS UNLK IN FLIGHTCOCKPIT WINDOW CRACKEDOXYGEN LO PR

2.05.14 MFCMFC 1A FAULTMFC 1B FAULTMFC 2A FAULTMFC 2B FAULTMFC 1A+1B FAULTMFC 1A+2A FAULTMFC 1A+2B FAULTMFC 1B+2A FAULTMFC 2A+2B FAULTMFC 1B+2B FAULT

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ATR 42 Model : 400/500

INTRODUCTION


P 1

APR 08

001

2.05.01

GENERAL

The procedures following failures represent the actions applicableafter a failure toensureadequate dafety and to ease the further conduct of the flight. They are applied accordingto the “Read and Do” principle except for the memory items.

PRESENTATION

The procedures are presented in the basic check list format with an adjacent expandedsection which provides:-- indication of the particular failure, alert condition-- explanation for actions where the reason is not self evident-- additional background information

The abbreviations used are identical with the nomenclature on the cockpit panels. Allactions are printed in CAPITAL letters.

: a preceding black square is used to identify a pre--condition (in bold) for givenaction(s).

: a preceding black dot is used to indicate the moment (in bold) when given action(s)have to be applied.

TASK SHARING

For all procedures, the general task sharing stated below is applicable.

The pilot flying remains pilot flying throughout the procedure.

PF, Pilot Flying, responsible for:-- PL-- flight path and airspeed control-- aircraft configuration-- navigation

PNF, Pilot Non Flying, responsible for:-- check list reading-- execution of required actions-- actions on overhead panel-- CL-- communications

The AFCS is always coupled to the PF side (CPL selection).

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ATR 42 Model : 400/500

INTRODUCTION


P 2

DEC 09

001

2.05.01

PROCEDURE INITIATION

-- No action will be taken apart from depressing MC / MW pushbuttons:

. until flight path is stabilized

. under 400 ft above runway except propeller feathering after engine failure duringapproach at reduced power if go around is considered

-- At flight crew discretion, oneRESETof a system failure associated to an amber cautionmay be performed by selecting OFF then ON related pushbutton. If the failure alertdisappears, continue normal operation and RECORD the event in the maintenancelog. If not, APPLY the associated following failure procedure.

-- Before performing a procedure, the crewmust assess the situations as a whole, takinginto consideration the failures, when fully identified, and the constraints imposed.

ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT

Basic airmanship calls for a management review of the remaining aircraft capabilitiesunder the responsability of CM1.

CCAS

When TO INHI has been selected, until the first leg of landing gear unlocks, all alerts areinhibited except:

WARNING-- ENG 1 FIRE-- ENG 2 FIRE-- CONFIG-- FLAPS UNLK-- LDG GEAR NOT DN-- EXCESS ALT

-- EXCESS CAB ∆P-- PITCH DISCONNECT-- PROP BRK (if applicable)CAUTION-- EFIS COMPADVISORY-- PRKG BRK-- GPWS-- MAINT PANEL

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ATR 42 Model : 400/500

POWER PLANT


P 1

DEC 09

001

2.05.02

SINGLE ENG OPERATION

PROCEDURE

SINGLE ENG OPERATION

LAND ASAPPWR MGT TO if necessary then MCT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL PUMP affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DC GEN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ACW GEN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PACK affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APM (if installed) OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (If installed) TA ONLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OIL PRESSURE ON FAILED ENGINE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . .

Note: In icing conditions, FLAPS 15 will be selected to improve drift downperformancesand single engine ceiling.

Note: Refer toQRHpages (4.61) and (4.62) to determine singleengine grossceiling.

Note: If during the flight, a positive oil pressure has been noted on the failed engine fora noticeable period of time, maintenance must be informed.

Note: monitor fuel balance. Recommended operational maximum fuel unbalance is200 kg (440 lb).

● When FUEL CROSS FEED is required

FUEL PUMP affected side ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL PUMP on operating ENG OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

● For approach

MAX APPROACH SLOPE for Steep Slope Approach 5.5�BLEED NOT AFFECTED OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL live engine 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .APPROACH SPEED NOT LESS THAN 1.1VMCA. . . . . . . . . . . . . . . . . . . . . . . .

Note: Refer to QRH page 4.64 to determine 1.1VMCA.

Note: At touch down, do not reduce below FI before nose wheel is on the ground.

COMMENTS

-- Refer to section Procedures and Techniques for fuel unbalance.-- For approach and landing, comply with Procedures and Techniques, Flight Patterns

sub--section 2.02.10.

AA

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ATR 42 Model : 400/500

POWER PLANT


P 2

APR 08

001

2.05.02

START FAULT

ALERT


Start sequence incident -- MC light flashing amber-- ENG amber light on CAP-- associated START FAULT-- amber light on overhead panel

SC

START FAULTENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . . . . .

If above 45 % NH

START ON LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . . . . . .START TO BE CONTINUED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

X START FAIL

ALERT


On ground, during secondengine start, operative DCGEN does not come on line tosupply the START BUSbetween 10 % and 45 % NH

-- MC light flashing amber-- ELEC amber light on CAP-- X START FAIL amber light on-- overhead panel

SC

PROCEDURE

X START FAIL

CONTINUE NORMAL ENGINE STARTINFORM MAINTENANCE

AA

ATR 42 Model : 400/500

POWER PLANT


P 3

APR 08

001

2.05.02

ABNORMAL PARAMETERS DURING START

PROCEDURE

ABNORMAL PARAMETERS DURING START

If ITT tends to exceed 900_C, or no ITT, or no NH

CL affected side FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . .

Then refer to the relevant procedure:EXCESSIVE ITT DURING START procedure (2.05.02 page 3)NO ITT DURING START procedure (2.05.02 page 4)NO NH DURING START procedure (2.05.02 page 4)

EXCESSIVE ITT DURING START

ALERTA hot start may be recognized by :-- Rapid ITT increase,-- NH slow increase,-- Exhaust flames may be reported by ground crew.The maximum authorized temperature during engine start is 950_C(refer to 2.01.04 page 2 for detailed limitation).

PROCEDURE

EXCESSIVE ITT DURING STARTWhen NH below 30 %

ENG START ROTARY SELECTOR CRANK. . . . . . . . . . . . . . . . . . . . . . . . . . .START PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

After 15 seconds

ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . .

CAUTION: If ITT exceeds 950_C, maintenance action is due.Note: BLEED VALVE may be selected OFF in order to reduce ITT.

AA

ATR 42 Model : 400/500

POWER PLANT


P 4

OCT 08

001

2.05.02

NO ITT DURING START

PROCEDURE

NO ITT DURING START

● After 30 seconds, to allow fuel draining

ENG START ROTARY SELECTOR CRANK. . . . . . . . . . . . . . . . . . . . . . . . . . .START PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

● After 15 seconds

ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . .

NO NH DURING START

PROCEDURE

NO NH DURING START

Note : On BAT only, OIL PRESS IND is not available.

ENG START ROTARY SELECTOR START A or START B. . . . . . . . . . . . . . . . . . . .START PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

● After 10 seconds

■ If OIL pressure increases

CL FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Continue START procedure, being informed NH indicator is inoperative.

■ If OIL pressure does not increase

ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . .Suspect starter motor failure. Maintenance action is due.

AA

R

ATR 42 Model : 400/500

POWER PLANT


P 5

DEC 10

001

2.05.02

NAC OVHT

ALERT


Nacelle temperature exceeds170�C (338�F) when aircraft ison ground

-- MW flashing red-- NAC OVHT red light on CAP

CRC

PROCEDURE

ENG NAC OVHT

■ If during hotel mode operation (when applicable)

PL affected side GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

■ If during taxi

AIRCRAFT STOP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL affected side SLIGHTLY INCREASE POWER. . . . . . . . . . . . . . . . . . . . . . .

■ If unsuccessful within 30 seconds

PL affected side GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- In case of tailwind component greater than 10 kt and just after engine start, propellermust be unfeathered rapidly to take advantage of the wind created by propellerrotation and consequently to avoid exhaust gas return flow in the nacelle.

-- When taxiing with tail wind component, use of reverse requires special care as air flowcreated by propeller reversing combined with tail wind will induce an exhaust gasreturn flowwhichmay damage the nacelle. It is consequently recommended not leavePL in reverse position for any period of time exceeding 10 seconds.

-- NAC OVHT alert is inhibited when both wow systems detect aircraft airborne.

AA

R

RR

R

RR

ATR 42 Model : 400/500

POWER PLANT


P 6

DEC 10

001

2.05.02

ABNORMAL ENG PARAMETERS IN FLIGHT

PROCEDURE

ABNORMAL ENG PARAMETERS IN FLIGHT

� If Intermittent fluctuations or unrealistic steady indication

ATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� When adequate flight situation

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EEC affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If successful

ONE EEC FAULT procedure (2.05.02 page10) APPLY. . . . . . . . . . . . . . .� If unsuccessful- or - � If TQ = 0% and NP < 77%

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATIONS procedure (2.05.02 page1) APPLY. . . . . . .

� If “---” indication on the torque digital counter (only for PW127E - PW127M)

AVOID SUDDEN PL MOVEMENTS

COMMENTS-- AFU provides TQ indication to the cockpit intruments. (needle).-- Untimely TQ indication drop lasting more than 2.15 seconds will induce an ATPCS

sequence if ATPCS was already armed.-- With engine at high power, a spurious ATPCS sequence would provoke an automatic

feathering and a very significant overtorque deselecting ATPCS will avoid such apossibility.

-- With no reliable TQ indication, engine power monitoring is assured on the affectedengine through NH / NP indications.

-- Refer to 2.02.11 page 2.

FIRE LOOP FAULT

PROCEDURE

FIRE LOOP FAULT

LOOP AFFECTED OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

R

ATR 42 Model : 400/500

POWER PLANT


P 7

APR 08

001

2.05.02

ABNORMAL PROP BRK (If applicable)ALERT


Propeller brake not locked infull locked or in full releasedposition --or--P ll b k d d

-- UNLK red light on overhead panel-- MW + PROP BRK red light on CAP--or-- with action on PROP BRK SW :

CRC

pPropeller brake engaged andGUST LOCK released(depending on models)

-- UNLK red light on overhead panel thenafter 30 seconds

-- MW + PROP BRK red light on CAP

PROCEDURE

ABNORMAL PROP BRK (If applicable)

J If on groundJ If unexpected propeller rotation- or - J If local UNLK and CCAS PROP BRK alert

CL 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAINTENANCE ACTION REQUIRED

J If CCAS PROP BRK alert onlyJ If GUST LOCK ON

CL 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If DC and AC GPU are not available

ENG 1 START. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F When READY light illuminatesPROP BRK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .UNLK LIGHT CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . . .PROP BRK PWR SPLY C/B PULL. . . . . . . . . . . . . . . . . . . . . . . . .

J If GUST LOCK OFFGUST LOCK ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F According to operational situation

PROP BRK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ALL PROP BRK LIGHTS CHECK EXTINGUISHED. . . . . . . . . . . . .

J If in flightCONTINUE NORMAL OPERATIONENG 2 PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F After landing

CL 2 FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAINTENANCE ACTION REQUIRED

AA

ATR 42 Model : 400/500

POWER PLANT


P 8

APR 08

001

2.05.02

ENG RESTART IN FLIGHT

PROCEDURE

ENG RESTART IN FLIGHT

FUEL SUPPLY CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION: After ATPCS sequence PWR MGT rotary selector must be set to MCT-

position before engine restart in order to cancel propeller feathering.ENG START ROTARY SELECTOR START A & B. . . . . . . . . . . . . . . . . . . . . . . . .EEC PB RESET if necessary or DESELECT if FAULT persists. . . . . . . . . . . . . . . .START PB ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F At 10 % NH

CL FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .RELIGHT MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL ADJUST TO OTHER ENGINE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . .SYSTEMS AFFECTED RESTORE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Engine relighting in flight is only guaranteed within the envelope and always

necessitate starter assistance.-- The power may be restored immediately after relighting provided OIL TEMP > 0°C.-- Should the engine fail to light up within 10 seconds, select fuel to shut off, the ignition

OFF and allow engine to be ventilated for 30 seconds minimum prior to makinganother attempt.

AA

ATR 42 Model : 400/500

POWER PLANT


P 9

APR 08

001

2.05.02

ENG STALL

ALERTAn engine stall may be recognized by :-- varying degrees of abnormal engine noise (rumbling bangs)-- fluctuating engine parameters-- abnormal PL response-- rapid ITT increase

PROCEDURE

ENG STALLPL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG PARAMETERS CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If abnormal engine parameters

CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . . .

J If normal engine parametersDE-- / ANTI--ICING ENG ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL affected side SLOWLY ADVANCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If stall recurs

Reduce thrust and operate below the stall thresholdJ If stall does not recur

Continue engine operation

AA

ATR 42 Model : 400/500

POWER PLANT


P 10

DEC 10

001

2.05.02

ONE EEC FAULT

ALERT


EEC failure -- MC light flashing amber-- ENG amber light on CAP-- associated EEC FAULT amber light on central

panel

SC

PROCEDURE

ONE EEC FAULT

ATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION: DO NOT DESELECT EEC FLASHING.

� When adequate flight situation

PL affected side RETARD IN GREEN SECTOR. . . . . . . . . . . . . . . . . . . . . . . .EEC affected side RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If successful

ATPCS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL affected side RESTORE POWER. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If unsuccessful

EEC affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL affected side RESTORE POWER. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HANDLING THROTTLE WITH CARE. . . . . . . . . . . . . . . . . . . . . . . . . . . .

� In the following cases : icing conditions, engine(s) flame out,emergency descent, severe turbulence, heavy rain

MAN IGN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� In final approach

CL 1 + 2 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After landing

TAXI WITH THE AFFECTED ENGINE FEATHEREDNote: ACW BTC must be check closed in order to avoid the loss of ACWbus on ground

COMMENTSRefer to 2.05.02 page 12.

AA

R

ATR 42 Model : 400/500

POWER PLANT


P 11

APR 08

001

2.05.02

BOTH EEC FAULT

ALERT


Both EEC failure -- MC light flashing amber-- ENG amber light on CAP-- EEC FAULT amber light(s) on central panel

SC

PROCEDURE

BOTH EEC FAULTATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION: DO NOT DESELECT EEC FLASHING.F When adequate flight situation

PL 1 + 2 RETARD IN GREEN SECTOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . .EEC 1 + 2 OFF THEN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If EEC 1 + 2 recovered

ATPCS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 RESTORE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If only one EEC recoveredONE EEC FAULT procedure (2.05.02 page 10) APPLY. . . . . . . . . . . . . . . . .

J If no EEC recoveredEEC 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 ADVANCE TO RESTORE POWER,. . . . . . . . . . . . . . . . . . . . . . .HANDLING THROTTLES WITH CARETQ IND ENG 1 + 2 MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F In the following cases : icing conditions, engine(s) flame out,

emergency descent, severe turbulence, heavy rainMAN IGN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F In final approachCL 1 + 2 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F After landingBRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . .CAUTION: Reverse power is reduced.

Both main HYD pumps will be at low speed.TAXI ON BOTH ENGINES,HANDLE THROTTLES WITH CARE


ATR 42 Model : 400/500

POWER PLANT


P 12

APR 08

001

2.05.02

ONE EEC FAULT / BOTH EEC FAULT (CONT’D)COMMENTS in common for both procedures-- With EEC OFF, the automatic relight is not available on affected engine(s).-- For PW121A only : EEC OFF operation, combined with BLEED OFF operation, may lead to

engine stall which may be prevented through slow power movements, especially whenadvancing PLs.

-- For PW121A only : an engine stall is indicated by mild surge(s). This will normally stops withoutcrew action, however a slight power reduction may be considered to restore normal operation.

ONE EEC FAULT (CONT’D)COMMENTS specific for ONE EEC FAULT-- When EEC fails, two cases must be considered :

High PowerPL set forward 52_

Low PowerPL set aft of 52_ in green sector

EEC FAULT light flashes, NH isautomatically frozen to its prior value (FAIL

FIX)

EEC FAULT comes on steady, EEC isautomatically deselected (Automatic

reversion)-- Feathering the engine with EEC failed for taxi and static operation will avoid prolonged

time in NP restricted band (propeller limitation).

BOTH EEC FAULT (CONT’D)COMMENTS specific for BOTH EEC FAULT-- During reduction at touch down, both ACW GEN may be lost and therefore both main

HYD pumps.-- Both digital torque indications are lost when TQ are below 20%.-- To avoid operating propellers in the NP restricted band, it is recommended to taxi with one

engine with NP > 63%.

ATR 42 Model : 400/500

POWER PLANT


P 13

DEC 09

001

2.05.02

ENG FLAME OUT

ALERTAn engine flame out may be recognized by :-- sudden dissymmetry-- TQ decrease-- rapid ITT decrease

PROCEDURE

ENG FLAME OUT

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If NH drops below 30% (no immediate relight)

CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If damage suspected

FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . .

� If no damage suspected

ENG RESTART IN FLIGHT procedure (2.05.02 page 8) APPLY. . . . . . . . . .� If unsuccessful

SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . .

COMMENTS

-- Shut down the engine if no immediate relight.-- The causes of engine flame out can generally be divided into two categories :. External causes such as icing, very heavy turbulence, fuel mismanagement. These

causes, which may affect both engines can generally be easily determined and animmediate relight can be attempted.

. Internal causes which as engine stalls or failures usually affect a single engine and arenot so easily determined. In these cases, the engine isshut down then thecause of theflame out investigated. If it cannot be positively determined what caused the flameout, the need for engine restart should be evaluated against the risk or further enginedamage or fire that may result from a restart attempt.

-- If damage is suspected, as precautionary measure, the FIRE handle is pulled.

AA

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ATR 42 Model : 400/500

POWER PLANT


P 14

APR 08

001

2.05.02

IDLE GATE FAIL

ALERT


Automatic idle gate systemfailure

-- MC light flashing red-- IDLE GATE amber light onCAP-- IDLE GATE FAIL amber lighton pedestal

SC

PROCEDURE

IDLE GATE FAILF In flight

IDLE GATE LEVER PUSH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F At touch down

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

COMMENTS-- In flight, pushing idle gate lever sets the stop at FI.-- On ground, pulling the lever removes the stop and allows reduction below FI (GI and

reverse).-- One reason for IDLE GATE FAIL alert may be a problem in the WOW (Weight On Wheel)

system. Other systems may be affected. Report to maintenance.

AA

ATR 42 Model : 400/500

POWER PLANT


P 15

APR 08

001

2.05.02


AA

ATR 42 Model : 400/500

POWER PLANT


P 16

DEC 10

001

2.05.02

UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS

PROCEDURE

UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS

CL 1 + 2 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PEC SGL CH

ALERT


Anomaly detection on eitherPEC channel

-- SGL amber light on centralpanel

NIL

PROCEDURE

PEC SGL CH

DO NOT RESET PEC IN FLIGHT -- NO SPECIAL CREW ACTIONANTICIPATE A PEC FAULT AT LANDINGMAINTENANCE IS REQUIRED

COMMENTS-- In case of PEC FAULT at landing :

. do not set PLs below FI before nose wheel is on the ground

. do not use reverse on affected engine

AA

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R

R

ATR 42 Model : 400/500

POWER PLANT


P 17

DEC 09

001

2.05.02

PEC FAULT

ALERT


Anomaly detection on both PECchannels

-- MC light flashing amber-- ENG amber light on CAP-- Associated FAULT light oncentral panel

SC

PROCEDURE

PEC FAULT

� If in short final approach (below 400 ft RA)GO AROUND procedure (2.03.17) APPLY. . . . . . . . . . . . . . . . . . . . . . . . . .

� Above 400 ft or when adequateCL affected side 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PEC affected side RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If successful

CL affected side AUTO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If unsuccessful

PEC affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID sudden PL movements� Before landing

CL NON AFFECTED 100% OVRD. . . . . . . . . . . . . . . . . . . . . . . . .Reverse is not available on affected side.TAXI ON BOTH ENGINESNote: ACW BTC may be check closed in order to avoid the loss of ACWbus on ground.

COMMENTS

-- Expect NP blocked at 102.5% (overspeed stop)-- Do not set PLs below FI before nose wheel is on ground.-- Reverse is not available because the secondary low pitch stop retraction solenoïd isdisabled that forbids the blades to go below the low pitch protection.

-- When the PEC is deenergized a NP cancel signal is sent to the EEC to cancel the EECNP governing mode (that controls the NP speed at 850 rpm) on ground.

-- ACW may be lost if NP drops below 65.5% on the affected engine.-- CL is set to OVRD to minimize NP transient when PEC is switched OFF/RESET.

AA

R

R

ATR 42 Model : 400/500

POWER PLANT


P 18

APR 08

001

2.05.02

LO PITCH IN FLIGHT

ALERT


Low pitch detection in flight -- MC light flashing amber-- ENG amber light on CAP-- Associated LO PITCH amber

light on central panel

SC

PROCEDURE

LO PITCH IN FLIGHT

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . .

COMMENTS-- If a low pitch is detected, pitch increases and returns to values which do not generate

alert. If failure still persists, pitch will decrease againwhich causes a cycling situation.

AA

ATR 42 Model : 400/500

POWER PLANT


P 19

DEC 09

001

2.05.02

ENG OVER LIMIT

ALERT


ITT above limit in flight or onground except at start

-- MC light flashing amber-- ENG amber light on CAP-- associated ITT caution light

on engine panel

SC

PROCEDURE

ENG OVER LIMIT

PL affected side RETARD TO RESTORE NORMAL VALUES. . . . . . . . . . . . . . . . . .

Note: BLEED VALVE may be selected OFF in order to reduce ITT

� If TQ, NH, and/or ITT still over limit and if conditions permitPL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . . .

COMMENTS

-- Red limits must not be deliberately exceeded.-- Check pointer and counter to determine limit exceedance and proceed accordingly.-- Over limit conditions and primary engine(s) parameters must be recorded for

maintenance purposes.-- If conditions do not permit engine shut down, land as soon as possible using the

minimum power required to sustain safe flight.

AA

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Eng : PW127E / PW127M ATR 42 Model :500

POWER PLANT


P 20

DEC 10

001

2.05.02

PROP OVER LIMIT

PROCEDURE

PROP OVER LIMIT

PL affected side RETARD TO SET NP BELOW 106%. . . . . . . . . . . . . . . . . . . . . . .PEC affected side OFF then ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL affected side AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If NP decreases below 106%

CONTINUE NORMAL FLIGHTNote : 106% allowed to complete a flight without overshooting 84% TQ in CRZ

and 85% in CLB.

� If NP remains above 106% and conditions permitPL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . .

COMMENTS

-- Red limits must not be deliberately exceeded.-- Transients in amber sector are normal during engine acceleration.-- Check pointer and counter to determine limit exceedance and proceed accordingly.-- Over limit conditions and primary engine(s) parameters must be recorded for

maintenance purposes.-- If conditions do not permit engine shut down, land as soon as possible using the

minimum power required to sustain safe flight. Nevertheless NP 106% is allowed tocomplete a flight

AA

R

Eng. : PW127E / PW127M ATR 42 Model : 500

POWER PLANT


P 21

APR 08

001

2.05.02

ENG OIL TEMP BELOW 45_C

PROCEDURE

ENG OIL TEMP BELOW 45_CJ If icing conditions are expected or present

ENG POWER If possible, INCREASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENG OIL TEMP HIGH

PROCEDURE

ENG OIL TEMP HIGHJ OIL TEMP between 125_C and 140_C

OIL TEMP AND PRESS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : If OIL TEMP rise follows PL reduction, advancing PL may reduce OIL TEMP.Note : If OIL TEMP rise occurs in steady state conditions, a power reduction should

permit a reduction in OIL TEMP.J OIL TEMP between 125_C and 140_C more than 20 minutes

PL affected side RETARD TO SET MINIMUM POSSIBLE POWER. . . . . . . . . .CAUTION : Flight plan must be rescheduled to minimize engine operating time in

these abnormal conditions.J OIL TEMP above 140_C

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . . .

COMMENTS-- Normal steady oil temperature is in the range 71/99_C.-- Increased power setting may reduce the OIL TEMP due to the increase of fuel flow

across the fuel/oil heat exchanger.-- If anOIL TEMP rise occurs in steadystate conditiona failureof theoil cooler flapmaybe

suspected, if no other engine malfunction is noted. In this case reducing power maylimit temperature excursion.

AA

ATR 42 Model : 400/500

POWER PLANT


P 22

APR 08

001

2.05.02

ENG OIL LO PR

ALERT


Oil pressure drops below 40PSI

-- MW light flashing red-- ENG OIL red light on CAP-- OIL warning light on engine panel

CRC

PROCEDURE

ENG OIL LO PRPL FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If both OIL LO PR alert on CAP and local alert are activated

CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . . .

J If local alert only is activatedCL FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Once engine is shut offCL FTR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If CCAS is activated after 30 seconds (normal warning delay)CL affected side FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENG RESTART IN FLIGHT procedure (2.05.02 page 8) APPLY. . . . . . . . . . .

J If notCL affected side FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . .

J If OIL LO PR alert only on CAP is activatedDISREGARD -- INFORM MAINTENANCE

J If single engine operation requiredNP of feathered engine MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If NP of feathered engine above 10%APPROACH SPEED INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . .


AA

ATR 42 Model : 400/500

POWER PLANT


P 23

APR 08

001

2.05.02

ENG OIL LO PR (CONT’D)

COMMENTS-- Engine oil low pressure is identified thanks to two low pressure detectors :

. the first one is connected to the CCAS (MW+CRC+ENG OIL red light on CAP)

. the second one is connected to the local alert (analogic oil low pressure indication +associated red light)

-- If the CONTRELIGHT (if installed) is ON when the CL is moved from FUEL SO toFTR,the combination of a fuel flow and active ignitersmay lead to an unintentional relight orto an overtemperature (ITT) condition.

-- If CCAS only is activated, alert must be disregarded, oil press local alert indicationmust be constantly monitored during flight.

-- If local alert only is activated and provided ENG OIL low pressure alert on CCAS ischecked operative, twin engine operation should be resumed.

-- NP>10%after a shut off proceduremay indicate an incomplete feathering. In this case,the approach speed is increased to compensate the extra drag of the incompletelyfeathered propeller, and, on aircraft not fitted with PEC, IAS is limited in order not toexceed the maximum allowed NP.

AA

ATR 42 Model : 400/500

FUEL


P 1

APR 08

001

2.05.03

FUEL ABNORMAL TEMPPROCEDURE

FUEL ABNORMAL TEMPJ If too high (>50_C)

Note : AVOID rapid throttle movement.OIL TEMP AND OTHER ENGINES PARAMETERS MONITOR. . . . . . . . . . . . .

J If too low (<0_C)Note : Use anti--icing additive for next refueling if repair can’t be done

COMMENTS-- Fuel is heated through a FUEL/OIL heat exchanger. Increasing fuel flow may reduce fuel

temperature.-- Rapide throttle movement with high temperature fuel may cause surge or flame out.-- In case of too low temperature, anti icing additive is needed to prevent ice formation in

the fuel supply system. Record it in the maintenance book.

FUEL CLOGALERT


Clogging of the filter asso-ciated with HP pump

-- MC light flashing amber-- ENG amber light on CAP-- FUEL CLOG amber light(s) on

main panel

SC

PROCEDURE

FUEL CLOGJ If both lights are illuminated

ENGINES PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If abnormal engines parameters

LAND ASAPNote : fuel contamination may be suspected.

MAINTENANCE ACTION REQUIREDJ If only one light is illuminated

ENGINE PARAMETERS affected side MONITOR. . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- If only one light illuminates, the crew may continue the flight or series of flight monitoring

associated engine parameters. Maintenance will perform action on the filter at themaintenance base.

-- If both lights are illuminated, the maintenance action has to be performed at the next stop.

AA

ATR 42 Model : 400/500

FUEL


P 2

APR 08

001

2.05.03

FEED LO PRALERT


Engine feed low pressure -- MC light flashing amber-- FUEL amber light on CAP-- FEED LO PR amber light on

overhead panel.

SC

PROCEDURE

FEED LO PRPUMP affected side CONFIRM ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINE affected side MONITOR FOR POSSIBLE RUNDOWN. . . . . . . . . . . . . .J If engine runs down or if fuel quantity decreases significantly

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PUMP affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . . . . .

CAUTION : Do not open X FEED valve.

COMMENTS-- The illumination of FEED LO PR light associated with PUMP RUN light identifies a

LEAK in the fuel line which may lead to engine rundown.-- If engine runs down or if fuel quantity decreases significantly, affected line must be

isolated by selecting the pump OFF and by closing the fuel shut--off valve.-- If PUMP RUN does not illuminate, pump system may be defective and a X FEED

attemptmay be performed in order to restoreengine supply.Max fuel unbalance has tobe considered.

AA

Mod : 4650 ATR 42 Model : 400/500

FUEL


P 3

APR 08

500

2.05.03

FUEL LO LVLALERT


Fuel quantity indicationbelow 160 kg / 352 lb-- or --Feeder tank not full

-- MC light flashing amber-- FUEL amber light on CAP-- LO LVL amber light on FUEL QTY

indicator

SC

PROCEDURE

FUEL LO LVLAVOID EXCESSIVE AIRCRAFT ATTITUDESJ If both LO LVL lights ON

LAND ASAPJ If LO LVL light on one side only

FUEL LEAK procedure (2.05.03 page 4) APPLY. . . . . . . . . . . . . . . . . . . . . . . .J If no leakJ If FQI < 160 kg / 352 lb

X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If FQI ≥ 160 kg / 352 lb, feeder jet pump malfunction is suspected

X FEED is not necessaryFUEL COMSUMPTION MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- After fuel pump is selected ON, feeder tank is full within 10 minutes.-- The LO LVL alert for each side will be triggered by :

. the fuel remaining indicated on FQI, when it is less than 160 kg / 352 lb.

. the secondary low level detection system, when feeder tank is not completely full.-- In case of feeder jet pumpmalfunction, fuel quantity unusable in each fuel tank is raised

from 20 kg / 44 lb to 130 kg / 287 lb.

AA

ATR 42 Model : 400/500

FUEL


P 4

APR 08

001

2.05.03

FUEL LEAKALERT


A fuel leak may be detected by either :-- sum of fuel on board (FOB), read in steady flight at cruise level,

and fuel used (FU), FOB+FU significantly less than fuel at depar-ture, or

-- passenger observation (fuel spray from engine or wing tip), or-- total fuel quantity decreasing at an abnormal rate, or-- fuel imbalance, or-- a tank emptying too fast (leak from engine or a hole in a tank), or-- excessive fuel flow (leak from engine), or-- fuel smell in the cabin

NIL NIL

PROCEDURE

FUEL LEAKF When a leak is confirmed

LAND ASAPJ If leak from engine (excessive fuel flow or feed spray from engine)

PL affected side FI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL affected side FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . .PUMP affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FIRE HANDLE affected side PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .SINGLE ENG OPERATION procedure (2.05.02 page 1) APPLY. . . . . . . . . .J If excessive fuel flow was identified before engine shutdown

FUEL X FEED valve can be openedJ In all other cases, X FEED valve MUST REMAIN CLOSED

J If leak not locatedFUEL X FEED MAINTAIN CLOSED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : the X feed must remain closed to prevent the leak affecting both sides.

F Before landingATC NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 1

DEC 09

001

2.05.04

DC BUS 1 OFF

ALERT


DC BUS 1 notsupplied (shortcircuit protection)

-- MC light flashing amber-- ELEC amber light on CAP-- DC GEN 1 FAULT, DC BUS (1) OFF, INV 1

FAULT and DC SVCE/UTLY BUS SHEDamber lights on overhead panel

SC

PROCEDURE

DC BUS 1 OFF

DC GEN 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PF CM2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DC SVCE/UTLY BUS PB MAINTAIN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AFFECTED EQUIPMENT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DC BUS 1 LOST EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . .� At touch down

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

DC BUS 1 LOST EQUIPMENT LIST

Instruments, Navigation & Com:Weather RadarRadio Altimeter(E)GPWSDME #1Air:Bleed LEAK IND 1 & 2AUTO PRESSFlight controls:Stick PusherCM1 Stick Shaker

Ice & Rain protection:CM1 and STBY Static Ports anti--icingCM1 Side Window Anti--IcingCM2 Windshield HTG INDEngines:FF/FU#1,Fuel TEMP#1 & Fuel CLOG #1Oil PRESS & Oil TEMP #1AUTO IDLE GATELight:CM1 Dome, chartholder & reading lightCM2 Flood panel lightStorm light, Annunciator light testNAV & BEACON lightMiscellaneous:Toilet flushing (If supplied by DC)

For more information on BUS EQUIPMENT LISTS see 1.06.60

COMMENTS-- DCSVCE/UTLYBUSpushbuttonmay bemaintainedONwith SHED illuminated in order to

keep DC UTLY BUS 2 on line.-- Stick pusher is lost.

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 2

DEC 09

001

2.05.04

DC BUS 2 OFF

ALERT


DC BUS 2 notsupplied (shortcircuit protection)

-- MC light flashing amber-- DC GEN 2 FAULT, DC BUS (2) OFF, INV 2

FAULT and DC SVCE/UTLY BUS SHEDamber lights on overhead panel

NIL

PROCEDURE

DC BUS 2 OFF

DC GEN 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PF CM1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADC SW SET TO ADC 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VHF 1 / ATC 1 SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AFFECTED EQUIPMENT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DC BUS 2 LOST EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before descent

PAX INSTRUCTIONS USE PA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� After touch down

TAXI ON BOTH ENGINES

DC BUS 2 LOST EQUIPMENT LIST

Instruments, Navigation & Com:CM2 EADI/EHSI & SGU#2VOR/ILS/DME#2, ADF#2, CM1 RMIVHF#2ATC#2, TCAS or T2CAS (if installed)ADC #2 & ALT ALERT # 2CM2 ClockGPS (KLN90) (if installed)CCAS:CAP amber alert except Maint PNL,PRKG BRK & MFCAir: Landing elevation INDHydraulic:DC AUX HYD PUMP (In Automatic)Landing gear:Secondary INDFlight controls:Right stick shakerStandby pitch trim controlTLU auto control

Ice & Rain protection:CM2 Static Port anti--icingCM2 Probes INDCM2 WiperCM2 Side window anti--icingCM1 Windshield HTG INDEngines:FF/FU #2FUEL TEMP #2, FUEL CLOG #2OIL PRESS, TEMP #2IDLE GATE FAIL INDLight:CM2 Chartholder, Reading LIGHTSIntegrated Norm INST&PANEL LIGHTSTaxi / Take off LIGHT, Wing LIGHTSPassenger SignsDoors:Doors UNLK lightsCockpit door locking systemFire: NAC OVHT

COMMENTS-- CM1 is pilot flying due to complete loss of CM2 panel.

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 3

DEC 09

001

2.05.04

AC BUS 1 OFF / AC BUS 2 OFF

ALERT


AC BUS notsupplied (shortcircuit protection)

-- MC light flashing amber-- ELEC amber light on CAP-- associated INV FAULT and BUS OFF

amber lights on overhead panel

SC

PROCEDURE

AC BUS 1 OFF / AC BUS 2 OFF

Note : Wait for 10 seconds in order to confirm the failure.

DC BTC ISOL THEN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If unsuccessful� If AC BUS 2 OFF

PF CM1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AC BUS 1 or 2 LOST EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . . . .

AC BUS 1 LOST EQUIPMENT LIST

115 AC BUS 1 26 AC BUS 1

BLEED LEAK DET 1 & 2 TRIMS IND

AC BUS 2 LOST EQUIPMENT LIST

115 AC BUS 1 26 AC BUS 1

GPWS CM2 ASI, VSI, ALTIHeading RMI#1Bearing VOR#2 & ADF#2 to RMI/SGU 1/2Course#2 and Heading#2 Select

COMMENTS-- The DC BTC pushbutton controls also the AC BTC. The reset of this pushbutton may

help to recover the affected AC BUS.-- In case of inverter failure, the AC BUSOFF light illuminates during 10 seconds through

the BTR temporizing, then extinguishes. The AC BUS is then available. An AC BUSfailure is effective as soon as the light stays on after 10 seconds.

-- In case of AC BUS 2 failure, CM1 is pilot flying due to loss of ASI, VSI and altimeter onCM2 panel.

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 4

DEC 09

001

2.05.04

ACW BUS 1 OFF / ACW BUS 2 OFFALERT


ACW BUS notsupplied (shortcircuit protection)

-- MC light flashing amber-- ELEC amber light on CAP-- associated ACW GEN FAULT and ACW

BUS OFF amber lights on overhead panel

SC

PROCEDURE

ACW BUS 1 OFF / ACW BUS 2 OFF

ACW GEN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEAVE AND AVOID ICING CONDITIONS

AS LONG AS ICING CONDITIONS EXISTICE ACCRETION VISUALLY MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . .

� If ACW BUS 1 OFFPF CM2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CM1 AIRSPEED INDICATOR MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If ACW BUS 2 OFFPF CM1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CM2 AIRSPEED INDICATOR MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AFFECTED EQUIPMENT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ACW BUS 1 or 2 LOST EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . . . .� If any IAS discrepancy occurs

DADC DATA INVALID (ADU message) procedure (2.05.10 page 2) APPLY. . . . .� After touch down

TAXI ON BOTH ENGINES

ACW BUS 1 LOST EQUIPMENT LIST

Hydraulic:

BLUE PUMP

Lights:

Integrated INST&PNL Lights

LEFT LANDING LIGHT,

LEFT and REAR STROBES

Ice & Rain protection:

CM1 PITOT / ALPHA / TAT Heating

ANTI--ICING PROP 1

ANTI--ICING HORNS (LH ELEV, RUD)

CM1 WINDSHIELD HTG

Miscellaneous: Toilet (If supplied by ACW)

ACW BUS 2 LOST EQUIPMENT LIST

Hydraulic:

GREEN PUMP

Lights:

TAXI/TO LIGHTS, RIGHT LANDING LIGHT

RIGHT STROBE

Ice & Rain protection:

CM2 PITOT / ALPHA / TAT Heating

ANTI--ICING PROP 2

ANTI--ICING HORNS (RH ELEV, AIL)

CM2 Windshield HTG, ICE DETECTOR

COMMENTS-- Monitor airspeed on non affected side due to loss of affected side pitot heating.

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 5

DEC 09

001

2.05.04

ACW TOTAL LOSS

ALERT


ACW total loss -- MC light flashing amber-- ELEC amber light on CAP-- both ACW GEN FAULT and ACW BUS

OFF amber lights on overhead panel

SC

PROCEDURE

ACW TOTAL LOSS

ACW GEN 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED CHECK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEAVE AND AVOID ICING CONDITIONS

AS LONG AS ICING CONDITIONS EXISTICE ACCRETION VISUALLY MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . .CM1 and CM2 AIRSPEED INDICATORS MONITOR. . . . . . . . . . . . . . . . . .

ACW TOTAL LOSS LOST EQUIPMENT LIST CHECK. . . . . . . . . . . . . . . . . . . . .AFFECTED EQUIPMENT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAIN HYD PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR EXTENSION/RETRACTION LOST. . . . . . . . . . . . . . . . . . . . . . . . . . .NORMAL BRAKE LOST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before landing

LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLUE PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) APPLY. . . . . . .

� After touch down

REVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAXI ON BOTH ENGINES

ACW TOTAL LOSS LOST EQUIPMENT LIST

Hydraulic:BLUE & GREEN PUMPLights:Integrated INST&PNL LightsLEFT & RIGHT LANDING LIGHTTAXI/TO LIGHTS

Ice & Rain protection:CM 1&2 PITOT/ALPHA/TAT HeatingANTI--ICING PROP 1&2ANTI--ICING HORNSCM1&2 WINDSHIELD HTGICE DETECTORMiscellaneous:Toilet (If supplied by ACW)


AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 6

APR 08

001

2.05.04

ACW TOTAL LOSS (CONT’D)COMMENTS-- Monitor airspeed indicators on non affected side due to loss of both sides pitot heating.

STBY instruments will be used as a reference.-- The HYD DC AUX PUMP allows flaps extension, maintains the nosewheel steering

and powers the emergency brake accumulator.-- If a go around has to be performed :

. landing gear will not retract

. flaps will retract with a lower speed than normal normal due to DC AUX PUMP size.-- Landing distance is multiplied by 1.5 due to loss of normal braking.

AA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 7

APR 08

001

2.05.04

DC ESS BUS OFFPROCEDURE

DC ESS BUS OFFJ If Cockpit Securized Doord installed

COCKPIT DOOR MANUAL BOLT(S) MOVE TO CLOSE POSITION. . . . . . . . . .Note : Cockpit Doord Control Panel FAULT light is inoperative.Note : When the door is locked with the manual bolt(s), the emergency access to

the cockpit is unavailable. It is recommended that at least two crewmembersremain in the cockpit during that time.

COMMENTS-- For DC ESS BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 9 and 10.

AA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 8

OCT 08

001

2.05.04

DC EMER BUS OFF

ALERT


DC EMER BUS nolonger supplied

-- MC light flashing amber-- CAP alerts-- TQ indications loss-- VHF1 loss-- ADC FAULT light loss

SC

PROCEDURE

DC EMER BUS OFF

LEAVE AND AVOID ICING CONDITIONSDESCEND TOWARD FL 100/MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STBY PITCH TRIM USE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADC SW (ADC FAULT lights lost) SET TO ADC 2. . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If ice accretion builds up on airframe

DE--ICING MODE SEL FAULT procedure (2.05.09 page 3) APPLY. . . . . . . . . . .ANTI--ICING PROP FAULT procedure (2.05.09 page 6) APPLY. . . . . . . . . . . . .ANTI--ICING HORNS FAULT procedure (2.05.09 page 6) APPLY. . . . . . . . . . . .CM1 and STBY IAS INDICATIONS COMPARE TO CM2. . . . . . . . . . . . . . . . . .

Note : Use CM2 instruments in case of disagreement.

� Before landing

ANTI--SKID OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .N/W STEERING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--SKID FAULT procedure (2.05.07 page 7) APPLY. . . . . . . . . . . . . . . . . . .

COMMENTS-- For DC EMER BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 7 and 8.-- ACW powered blue hydraulic pump is lost. HYD X FEED must be selected to open

position to pressurize blue hydraulic circuit.-- TQ indications are lost: PLs must be set in the notch and engines monitoring must be

performed with fuel flow indications.-- Normal pitch trim is lost use stand by pitch trim.

AA

R

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 9

APR 08

001

2.05.04

DC GEN FAULTALERT


One DC generationchannel inoperative

-- MC light flashing amber-- ELEC amber light on CAP-- associated DC GEN FAULT amber light

on overhead panel

SC

PROCEDURE

DC GEN FAULTDC GEN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If OAT exceeds ISA + 25

FL 200 MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TAXI ON BOTH ENGINES

COMMENTS-- If OAT exceeds ISA+25, the maximum allowed flight level is FL 200 due to ventilation

problem of the remaining DC generator.

INV FAULTALERT


Under/Over voltageat INV output

-- MC light flashing amber-- ELEC amber light on CAP-- associated INV FAULT amber light on

overhead panel

SC

PROCEDURE

INV FAULTNO SPECIFIC ACTION IN FLIGHT

COMMENTS-- After 10 seconds following INV FAULT, the AC BTC is automatically closed causing

affected AC BUS and AC STBY BUS to be supplied from the remaining inverter.

AA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 10

OCT 08

001

2.05.04

ACW GEN FAULTALERT


One ACWgeneration channelinoperative

-- MC light flashing amber-- ELEC amber light on CAP-- associated ACW GEN FAULT amber

light on overhead panel

SC

PROCEDURE

ACW GEN FAULTACW GEN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LEAVE AND AVOID ICING CONDITIONSTAXI ON BOTH ENGINES

DC SVCE/UTLY BUS SHEDALERT


One DC UTLY BUSautomatically shedafter a sourceoverload

-- MC light flashing amber-- ELEC amber light on CAP-- DC SVCE/UTLY BUS SHED amber light

on overhead panel

SC

PROCEDURE

DC SVCE/UTLY BUS SHEDDC SVCE/UTLY BUS AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- For DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST refer to 1.06.60 pages 12

to 14.-- It is crew decision to select DC SVCE/UTLY BUS pushbutton OFF or not. In case this

pushbutton is selected OFF, it will :. confirm automatic shedding of affected DC UTLY BUS. shut off the non affected DC UTLY BUS and the DC SVCE BUS

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 11

APR 08

001

2.05.04

BAT CHG FAULTALERT


Incipient batterythermal runaway otrchange contactorfailure

-- MC light flashing amber-- ELEC amber light on CAP-- associated CHG FAULT amber light on

overhead panel

SC

PROCEDURE

BAT CHG FAULTCHG associated OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DUAL BAT CHG LOSSALERT


MFC failure leadingto dual batterycharge contactorsloss

-- MC light flashing amber-- ELEC amber light on CAP-- both amber arrows illuminated on

overhead panel

NIL

PROCEDURE

DUAL BAT CHG LOSSMFC MODULES, one at a time OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . .J If RESET unsuccessful

LAND ASAPNote : Minimize use of VHF 1 if conditions permit.

COMMENTS-- This case should only occur following a MFC software failure.

AA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 12

DEC 10

001

2.05.04

BAT DISCHARGE IN FLIGHT

ALERT


Battery(ies)discharge in flight(but DC mainsources available)

-- MC light flashing amber-- ELEC amber light on CAP-- Left and/or Right amber arrow(s)

illuminated on overhead panel

SC

PROCEDURE

BAT DISCHARGE IN FLIGHT

ENG START ROTARY SELECTOR OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� If battery(ies) still discharging

LAND ASAP

COMMENTS-- Alarm (MC + SC + ELEC on CAP) is controlled by MFC 1B or 2B and is inhibited :

. on ground

. on BAT OVRD position

. in case of DUAL DC GEN LOSS

AA

R

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 13

APR 08

001

2.05.04

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTSAA

ATR 42 Model : 400/500

ELECTRICAL SYSTEM


P 14

APR 08

001

2.05.04

STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS (CONT’D)AA

ATR 42 Model : 400/500

HYDRAULIC


P 1

APR 08

001

2.05.05

HYD LO LVLALERT


Tank compartmentfluid quantitybelow 2,5 l (0,67 USgal)

-- MC light flashing amber-- HYD amber light on CAP-- associated LO LVL amber light and LO PR

amber Iight on MAIN PUMP pushbutton,on overhead panel

SC

PROCEDURE

HYD LO LVLJ If blue system affected

BLUE PUMP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUX PUMP OFF (CONFIRMED). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .REDUCED FLAPS LANDING procedure (2.05.06 page 3) APPLY. . . . . . . . . . . .F After touch down

USE NORMAL BRAKE FOR STEERINGTAXI ON BOTH ENGINES

J If green system affectedGREEN PUMP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) APPLY. . . . . . .F After touch down

TAXI ON BOTH ENGINESREVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HYD SYS LOST EQUIPMENT LIST

BLUE GREEN

FLAPS / SPOILERS / N/W STEERINGPROP BRAKE (if installed)EMER and PARKING BRAKE (on accuonly)

LDG GEAR EXT / RETNORMAL BRAKE

COMMENTS-- In case of LO LVL, X FEEDremains closedandXFEED valveoperation isautomatically

inhibited.-- For emergency/parking brake, the brake accumulator allows at least six applications of

braking force at full braking pressure.-- If green system affected, landing distance is increased due to loss of normal braking. If

a go around has to be performed, landing gear will not retract.

AA

ATR 42 Model : 400/500

HYDRAULIC


P 2

OCT 08

001

2.05.05

BOTH MAIN HYD PUMPS LOSS

PROCEDURE

BOTH MAIN HYD PUMPS LOSS

MAIN BLUE AND GREEN PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .X FEED CHECK OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before landing

LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLUE PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FLAPS 15 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) APPLY. . . . . . .FLAPS 35 AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


TAXI ON BOTH ENGINESREVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BOTH MAIN HYD PUMPS LOSS LOST EQUIPMENT LIST

BLUErecovered when LDG GEAR lever is down

GREEN

FLAPS / SPOILERS / N/W STEERINGPROP BRK (if applicable)EMER AND PARKING BRK (on accuonly)

LDG GEAR EXT / RETNORM BRAKE

COMMENTS-- For emergency/parking brake, the brake accumulator allows at least six applications of

braking force at full braking pressure.-- Landing distance is increased due to loss of normal braking. If a go around has to be

performed, landing gear will not retract.

R

R

ATR 42 Model : 400/500

HYDRAULIC


P 3

OCT 08

001

2.05.05

BOTH HYD SYS LOSS

PROCEDURE

BOTH HYD SYS LOSS

MAIN AND AUX PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .� Before approach

GPWS GPWS OVRD or FLAP OVRD (depending on version). . . . . . . . . . . . . .LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) APPLY. . . . . . .APP/LDG SPEED VmHB 0 + WIND EFFECT. . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY LDG DIST FLAPS 35 BY 2.1. . . . . . . . . . . . . . . . . . . . .

CAUTION : Tail strike may occur if pitch attitude exceeds 10�C during the flaredepending upon vertical speed at touch down.


TAXI ON BOTH ENGINESREVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BOTH HYD SYS LOSS LOST EQUIPMENT LIST

BLUE GREEN

FLAPS / SPOILERS / N/W STEERINGPROP BRK (if applicable)EMER AND PARKING BRK (on accuonly)

LDG GEAR EXT / RETNORMAL BRAKE

COMMENTS-- The landing distance is increased due to loss of flaps and of normal braking.-- For emergency/parking brake, the brake accumulator allows at least six applications of

braking force at full braking pressure.-- If a go around has to be performed, landing gear will not retract.

AA

R

RRR

RRR

R

R

RR

R

ATR 42 Model : 400/500

HYDRAULIC


P 4

APR 08

001

2.05.05

HYD LO PR / HYD OVHTALERT


Pump deliverypressure below 1500PSI (103.5 bar)

-- MC light flashing amber-- HYD amber light on CAP-- associated pump LO PR amber light on

overhead panel

SC

Pump case drainline temperatureabove 121_C

-- MC light flashing amber-- HYD amber light on CAP-- associated OVHT amber light on overhead

panel

SC

PROCEDURE

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

COMMENTS-- Failed system users are supplied by the non affected pump when opening the cross

feed.-- In case of overheat, an attempt to restore the system may be performed after OVHT

alert has extinguished.

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 1

APR 08

001

2.05.06

FLAPS UNLKALERT


Flaps untimelyretraction of morethan 3_ when flapsextended

-- MW light flashing red-- FLAPS UNLK red light on CAP

CRC

PROCEDURE

FLAPS UNLK

J If before V1TAKE OFF ABORT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If after V1VR, V2 INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If alarm occurs during approachGO AROUND procedure (2.03.17) APPLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . .VGA INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F When possibleFLAPS 0. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .REDUCED FLAPS LANDING procedure (2.05.06 page 3) APPLY. . . . . . . . . . . .

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 2

APR 08

001

2.05.06

FLAPS JAM / UNCOUPLED / ASYMALERTFLAPS JAM / UNCOUPLED : No specific alert.FLAPS ASYM :


Flaps asymmetry ofmore than 6.7_during flapsactuation

-- MC light flashing amber-- FLT CTL amber light on CAP-- FLAP ASYM amber light on flight panel

SC

PROCEDURE

FLAPS JAM / UNCOUPLED / ASYM

FLAPS CONTROL LEVER NEAR FLAPS PRESENT POSITION. . . . . . . . . . . . . .

F When applicableREDUCED FLAPS LANDING procedure (2.05.06 page 3) APPLY. . . . . . . . . . . .

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 3

APR 08

001

2.05.06

REDUCED FLAPS LANDINGPROCEDURE

REDUCED FLAPS LANDING

GPWS GPWS OVRD or FLAP OVRD (depending on version). . . . . . . . . . . . . .STEEP SLOPE APPROACH (≥4.5_) PROHIBITED. . . . . . . . . . . . . . . . . . . . .

FLAPS

LDGFLAPS 35

MULTIPLY BYAPP/LDG SPD

0

15

25

1.35

1.15

1.1

Vm HB 0 + wind effect



CAUTION : Tail strike may occur if pitch attitude exceeds 10_ during the flaredepending upon vertical speed at touch downdepending upon vertical speed at touch down.

COMMENTS-- GPWS must be selected GPWS OVRD / FLAP OVRD to prevent nuisance alerts on

final approach.-- Normal landing flaps 25 is possible with aircraft fitted with mod 4450 or 4580.

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 4

APR 08

001

2.05.06

STICK PUSHER / SHAKER FAULTALERT


Stick pusher /shaker fault

-- MC light flashing amber-- FLT CTL amber light on CAP-- FAULT amber light in STICK PUSHER /

SHAKER pushbutton

SC

PROCEDURE

STICK PUSHER / SHAKER FAULT

STICK PUSHER / SHAKER OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) TA ONLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VmHB / VmLB FOR ALL CONFIGURATION INCREASE BY 10 KT. . . . . . . . . . . .LDG DIST MULTIPLY BY 1.13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- The minimum maneuvering speeds are increased by 10 kt in order to increase stall

margin.-- If ALPHA probes are not heated, ice accretion may modify alpha probes indication. If

angle of attack information offsets 4_, STICK PUSHER / SHAKER FAULT lightilluminates. When living icing conditions, as soon as alpha probes are cleared of ice,STICK PUSHER / SHAKER may be recovered by selecting it ON.

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 5

APR 08

001

2.05.06

PITCH TRIM ASYM (LOCAL LIGHT)ALERT


Pitch tabsdesynchronisation

-- MC light flashing amber-- FLT CTL amber light on CAP-- PITCH TRIM ASYM amber light on flight

deck

SC

PROCEDURE

PITCH TRIM ASYM (LOCAL LIGHT)

AP DISCONNECTION CONFIRM MANUALLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . .PITCH TRIM INOPERATIVE procedure (2.05.06 page 5) APPLY. . . . . . . . . . . . . . . .

COMMENTS-- When a PITCH TRIM ASYM alert is generated, AP automatically disconnects and

cannot be reengaged. However, it is recommended to manually confirm APdisconnection.

-- Don’t use the trims anymore and apply PITCH TRIM INOPERATIVE procedure.

PITCH TRIM INOPERATIVEALERTBoth normal and standby pitch trim controls are inoperative.

PROCEDURE

PITCH TRIM INOPERATIVE

EXISTING CONFIGURATION AND SPEED MAINTAIN AS LONG AS POSSIBLE. . . . . .F For approach

STEEP SLOPE APPROACH (≥4.5_) PROHIBITED. . . . . . . . . . . . . . . . . . . . . .FLAPS EXTEND AT VFE FOR EACH CONFIGURATION. . . . . . . . . . . . . . . . .LDG SPEED INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Maintain existing configuration and speed as long as possible to avoid high forces on

the columns.-- The landing distance is increased due to landing speed increase.

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 6

DEC 09

001

2.05.06

RUDDER RELEASABLE CENTERING UNIT FAIL

ALERT

There is no indication of a rudder releasable centering unit failure other than a dutch rolloscillation tendency.

PROCEDURE

DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERINGUNIT FAIL

� If YD is available

YD ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If YD is not available

LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTEDRUDDER PEDAL MOVEMENT

PITCH DISCONNECT

ALERT


Pitch couplingmechanismdisconnected

-- MW light flashing red-- PITCH DISCONNECT red light on CAP

CRC

PROCEDURE

PITCH DISCONNECT

BOTH CONTROL COLUMNS CHECK FREE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IAS 180 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LOAD FACTOR 2 g MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BANK ANGLE 30� MAX UNITL FLAPS EXTENSION. . . . . . . . . . . . . . . . . . . . . . . .

AVOID ICING CONDITIONS

� For approach

STEEP SLOPE APPROACH (≥4.5�) PROHIBITED. . . . . . . . . . . . . . . . . . . . . .LAND AT AIRPORT WITH MINIMUM CROSSWINDLDG SPEED INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PL 1 + 2 REDUCE SMOOTHLY TO FLARE. . . . . . . . . . . . . . . . . . . . . . . . . . .

� When on ground

PITCH RECONNECTION ON GROUND procedure (2.05.06 page 7) APPLY. . . .

COMMENTS-- As both elevator channels are disconnected, pitch control efficiency is reduced.

AA

RR

R

R

ATR 42 Model : 400/500

FLIGHT CONTROL


P 7

APR 08

001

2.05.06

PITCH RECONNECTION ON GROUNDThis procedure may be applied on ground after a PITCH DISCONNECT.PROCEDURE

PITCH RECONNECTION ON GROUND

GUST LOCK ENGAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BOTH COLUMNS CHECK LOCKED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ELEV CLUTCH GUARDED PB DEPRESS AND HOLD. . . . . . . . . . . . . . . . . . . . . . .F When PITCH DISCONNECT flashes red on CAP

ELEV CLUTCH GUARDED PB RELEASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PITCH DISCONNECT ON CAP CHECK EXTINGUISHED. . . . . . . . . . . . . . . . . . . .BOTH COLUMNS CHECK COUPLED. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 8

DEC 10

001

2.05.06

TLU FAULT

ALERT


Both ADC are lost, ordisagree between actual andtheoretical TLU position, orTLU synchro position failure

-- MC light flashing amber-- FLT CTL amber light on CAP-- TLU FAULT amber light on

overhead panel

SC

PROCEDURE

TLU FAULT

� If ADC 1 + 2 are lost

� If IAS above 195 kt

TLU HI SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If IAS below 195 kt

TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DISREGARD TLU FAULT ALERT

� If at least one ADC operates

� If IAS above 195 kt

TLU HI SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If TLU FAULT alarm persists

IAS 190 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If IAS below 195 kt

IAS 190 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU LO SPD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DISREGARD TLU FAULT ALERT

� If TLU green light is not lit

VAPP INCREASE BY 10 KT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LAND AT AIRPORT WITH MINIMUM CROSSWIND

Note : Maximum demonstrated crosswind (dry runway) with TLU HI SPD mode : 15 kt.

COMMENTS-- If both ADC are lost, TLU automatic functioning is lost. TLU must be set manually

according to IAS read on the STBY ASI.

AA

R

Mod : 4372 ATR 42 Model : 500

FLIGHT CONTROL


P 9

APR 08

500

2.05.06

AIL LOCK LITALERT


Disagree between aileronlocking actuators and gustlock control (temporizedalert 8 seconds)

-- MC light flashing amber-- FLT CTL amber light on CAP-- AIL LOCK amber light on pedestal

SC

Aileron locking actuators notfully retracted and PL on TOposition, orDisagree between aileronlocking actuators and gustlock control during the TOCONFIG test

-- MW light flashing red-- CONFIG red light on CAP-- FLT CTL amber light on CAP

CRC

PROCEDURE

AIL LOCK LIT

J If before take offRETURN TO PARKINGREFER TO MMEL 27 ITEM 70--1 GUST LOCK SYSTEM

J If after landingTAKE SPECIAL CARE FOR TAXI (WIND EFFECT)USE STANDBY SYSTEM FOR AILERON LOCK AT PARKINGINFORM MAINTENANCE

COMMENTS-- A malfunction of an aileron locking actuators is pointed out according two levels of

protection:. an amber alarm, before take off, with a 8 seconds temporization. a red alarm if either TO CONFIG test is performed or both PL are on TO position

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 10

DEC 10

001

2.05.06

ELEV JAM

ALERT

There is no indication of an elevator jam other than an inability to operate the controlcolumn.

PROCEDURE

ELEVATOR JAM

CONTROL COLUMNS UNCOUPLE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AVOID ICING CONDITIONSIAS 180 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If one elevator is stuck to full down position

IAS 154 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If left elevator is jammed

MINIMUM MANEUVER OPERATING SPEEDS INCREASE BY 10 KT. . . . . . . . .

� If elevator jamming occurs at take off

IAS 161 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PITCH DISCONNECT procedure (2.05.06 page 6) APPLY. . . . . . . . . . . . . . . . . . .

COMMENTS-- Both pilots accomplish a firm action on their own column IN THEWAY REQUIRED BY

THE JAMMING CONDITION.One of the two channels must yield; force required 52 daN (115 lb).

-- If uncoupling is unsuccessful, when trajectory under control and above safety altitude,apply opposite efforts on both control columns.

-- Stick pusher acts on left hand elevator. If left hand control column is jammed, stickpusher must be considered inoperative.

-- The maximum speed authorized if elevator jamming occurs at take off is linked to theelevator take off position.

-- If right hand control column is jammed, AutoPilot is no more available.-- After uncoupling, only one pilot has control and actuates one elevator only.

AA

RR

R

ATR 42 Model : 400/500

FLIGHT CONTROL


P 11

APR 08

001

2.05.06

AILERON JAM / SPOILER JAMALERTThere is no indication of an aileron jam other than an inability to operate the control wheellaterally.Spoiler jammay be detected when a SPLR light is illuminated on the overhead panel withcontrol wheel at neutral position.PROCEDURE

AILERON JAM / SPOILER JAM

BANK ANGLE LIMIT 25_ MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLUE AND AUX HYD PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LAND AT AIRPORT WITH MINIMUM CROSSWINDF For approach

STEEP SLOPE APPROACH (≥4.5_) PROHIBITED. . . . . . . . . . . . . . . . . . . . . .BLUE AND AUX HYD PUMPS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : Do not extend flaps in turn.F When in landing configuration

BLUE AND AUX HYD PUMPS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F Immediately after touch down

BLUE AND AUX HYD PUMPS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Bank angle is limited to 25_ due to reduced roll control efficiency.-- Blue pump and AUX pump are selected OFF in order to decrease drag from associated

extended spiler. These pumps are selected ON again when necessary then selectedOFF. They must be reselected ON immediately after touch down in order to recovernose wheel steering.

AA

ATR 42 Model : 400/500

FLIGHT CONTROL


P 12

APR 08

001

2.05.06

RUDDER JAMALERTThere is no indication of a rudder jam other than an inability to operate the rudder pedals.PROCEDURE

RUDDER JAM

STEEP SLOPE APPROACH (≥4.5_) PROHIBITED. . . . . . . . . . . . . . . . . . . . . . .LANDING FLAPS 35. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .USE DIFFERENTIAL POWER SO AS TO MINIMIZE SIDESLIPLAND AT AIRPORT WIT MINIMUM CROSSWINDF At touch down

NOSE DOWN BEFORE REDUCTION BELOW FI

AA

ATR 42 Model : 400/500

LANDING GEAR


P 1

APR 08

001

2.05.07

LDG GEAR GRAVITY EXTENSIONPROCEDURE

LDG GEAR GRAVITY EXTENSION

LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXTENSION HANDLE PULL ABOVE PEDESTAL LEVEL. . . . . . . . . . . . .

AND MAINTAIN UP TO GREEN LIGHTS ILLUMINATED. . . . . . . . . . . . . . . . . . . .

CAUTION : Do not twist handle when operating.

TCAS (if installed) TA ONLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If unsuccessful

LANDING WITH ABNORMAL LDG GEAR procedure (2.05.07 page 2) APPLY. . .

COMMENTS-- Although gravity extension is possible up to VLO, it is recommended to perform it at a

lower speed compatible with flight conditions.-- Pulling the handle mechanically releases the up locks. Pushing the handle back resets

the uplocking system.TRAINING-- After gravity extension for training purposes, reset the emergency extension handle

before normal retraction. If handle is maintained pulled, hydraulic configuration willinhibit gear retraction.

AA

ATR 42 Model : 400/500

LANDING GEAR


P 2

APR 08

001

2.05.07

LANDING WITH ABNORMAL LDG GEARPROCEDURE

LANDING WITH ABNORMAL LDG GEAR

F PreparationCABIN CREW (PA) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC / TRANSPONDER NOTIFY / AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . .SEAT BELTS / NO SMOKING ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN AND COCKPIT PREPARE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LOOSE AND SURVIVAL EQUIPMENT CHECK SECURED. . . . . . . . . . . . . . .BELTS AND SHOULDER HARNESS CHECK LOCKED. . . . . . . . . . . . . . . . . .FUEL WEIGHT IF POSSIBLE, REDUCE. . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If abnormal nose LDG GEAR

CG LOCATION IF POSSIBLE, AFT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If abnormal main LDG GEAR

FUEL UNBALANCE IF POSSIBLE, ESTABLISH. . . . . . . . . . . . . . . . . . . . .Note: Reduced fuel on side with failed LDG GEAR.

F ApproachLDG GEAR LEVER CONFIRM DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR EMER EXT HANDLE CONFIRM PULLED. . . . . . . . . . . . . . . . . . .ENG START ROTARY SELECTOR OFF / START ABORT. . . . . . . . . . . . . . . . .CABIN REPORT CONFIRM OBTAINED. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F Before landingBLEEDS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRACE FOR IMPACT ORDER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F At touch downPL 1 + 2 GI. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CL 1 + 2 FTR THEN FUEL SO. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F After touch downFIRE HANDLES 1 + 2 PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F When aircraft stoppedPARKING BRAKE SET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CABIN CREW (PA) NOTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FUEL PUMPS 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AGENTS 1 + 2 DISCH. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EVACUATION INITIATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F Before leaving aircraftBAT OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

LANDING GEAR


P 3

APR 08

001

2.05.07

LANDING WITH ABNORMAL LDG GEAR (CONT’D)COMMENTS-- The procedure is intended for use when one or more landing gear fail to extend and/or

lockdown following the application of either normal or gravity extension procedure.It is considered preferable to use all available gear locked down rather than carry out abelly landing. Under these circumstances, a hard surface runway landing is to berecommended.Full advantage should be taken from foam spread on the runway.

-- Notify ATC of the nature of emergency encountered and state intentions.-- Notify the cabin crew of the nature of emergency encountered and state intentions.

Specify the available time.-- GPWS is selected OFF to avoid nuisance warnings.-- Burn fuel off down to theminimumpossible impact weight. This reduces VAPPand as a

consequence the load factor for impact and the energy which must be dissipated.

AA

ATR 42 Model : 400/500

LANDING GEAR


P 4

APR 08

001

2.05.07

LDG GEAR UNSAFE INDICATIONALERT


Any gear not seen downlocked, andFlaps 35 (or 25*), andZRA < 500 ft

-- MW light flashing red-- LDG GEAR NOT DN red light on

CAP-- Red light in landing gear lever-- Any green ∇ light not illuminated

oon either panel

CRCwhich may not besilenced by

depressing MW PB

Any gear not seen downlocked, andAt least one PL at FI,andZRA < 500 ft

oon either panelCRC

which may besilenced by

depressing MW PB

Note : The second condition is inhibited during 150 seconds after the retraction of at leastone landing gear leg, to cover the case of the one engine go around.Note : In both cases, ZRA condition is inhibited in case of radio altimeter failure.*: Normal landing with flaps 25 is possible with aircraft fitted with mod 4450 or 4580.

PROCEDURE

LDG GEAR UNSAFE INDICATION

J If LDG GEAR selected DOWN

J If GREEN light OFF on one panel onlyUNSAFE INDICATION DISREGARD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If GREEN light OFF on both panelsLDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) APPLY. . . .

J If LDG GEAR selected UP

J If RED light ON on one panel onlyUNSAFE INDICATION DISREGARD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If RED or GREEN light ON on both panelsLEAVE AND AVOID ICING CONDITIONSIAS 160 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) TA ONLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

LANDING GEAR


P 5

APR 08

001

2.05.07

LDG GEAR UNSAFE INDICATION (CONT’D)COMMENTSLanding gear selected DOWN-- If all green lights are illuminted on one panel, the unsafe indication is false.-- If overhead panel (detection system 2) gives false indication, use of emergency audio

cancel will be requested to cancel aural warning CRCas soon as flapswill be selected35 (or 25).

-- If one gear remains unlocked, perform turns to increase load factor and performalternating side slips in an attempt to lock the gear.

Landing gear selected UP-- If light illuminated on one indicator but indications are normal on the other panel, the

unsafe indication is false.-- Flight with landing gear extended has a significant effect on fuel consumption and

climb gradient : see 3.11 -- SPECIAL OPERATIONS.-- Landing gear down selection may be delayed if peformance requires.

AA

ATR 42 Model : 400/500

LANDING GEAR


P 6

APR 08

001

2.05.07

LDG GEAR RETRACTION IMPOSSIBLE

PROCEDURE

LDG GEAR RETRACTION IMPOSSIBLE

LEAVE AND AVOID ICING CONDITIONSLDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IAS 180 KT MAX. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CCAS RECALL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) TA ONLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

LANDING GEAR


P 7

DEC 10

001

2.05.07

ANTI- SKID FAULT

ALERT


Anti--skid channelloss (power loss orloss of transducer orvalve continuity)

-- MC light flashing amber-- WHEEL amber light on CAP-- Associated F amber light on central

panel

SC

PROCEDURE

ANTI- SKID FAULT

ANTI--SKID OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG DIST MULTIPLY BY 1.4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� At touch down

REVERSE AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .NORMAL BRAKE USE WITH CARE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BRAKE HANDLE EMER AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS

-- landing distance is increased due to reduced braking efficiency.

BRK TEMP HOT

ALERT


Brake temperatureover 160�C

-- MC light flashing amber-- WHEEL amber light on CAP-- HOT amber light on central panel

SC

PROCEDURE

BRK TEMP HOT

� If BRK TEMP HOT occurs before take off

TAKE OFF DELAY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If BRK TEMP HOT occurs in flight

LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF FOR COOLINGEXCEPT IN CASE OF EMERGENCY

AA

R

ATR 42 Model : 400/500

AIR


P 1

APR 08

001

2.05.08

BLEED VALVE FAULTALERT


Bleed valve positionin disagree withcommand

-- MC light flashing amber-- AIR amber light on CAP-- Associated BLEED and PACK FAULT

amber lights on overhead panel

SC

PROCEDURE

BLEED VALVE FAULT

PACK VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

COMMENTS-- Following the detection of a FAULT, the affectedBLEEDVALVEwill closeautomatically

and the associated PACK VALVE will close due to lack of air supply. The associatedactions confirm automatic operation and extinguish related alerts, allowing flight to becontinued with one pack supplied.

-- Pack should be confirmed closed first due to PACK FAULT inhibition (as soon asBLEED is selected OFF, PACK FAULT light extinguishes).

-- For ATR 42--500 only, a failure of Handling Bleed Valve combined with BLEED OFFoperationmay lead to engine stall. Engine stall may be prevented through slow powerlevers movements, especially when advancing the power levers.

-- An engine stall is indicated by one or a series of mild surges. These will normally stopwithout crew action, however a slight power reduction, if appropriate, will restorenormal operation.

AA

ATR 42 Model : 400/500

AIR


P 2

APR 08

001

2.05.08

BLEED OVHTALERT


Overheat in bleedduct :T duct > 274_C /525_F

-- MC light flashing amber-- AIR amber light on CAP-- Associated OVHT, BLEED and PACK

FAULT amber lights on overheadpanel

SC

PROCEDURE

BLEED OVHT

PACK VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

COMMENTS-- Following the detection of an overheat, the affected BLEED VALVE will close

automatically and the associatedPACK VALVEwill close due to lack of air supply. Theassociated actions confirm automatic operation and extinguish related alerts,allowing flight to be continued with one pack supplied.


-- System may be restored in flight after OVHT alert has extinguished.

AA

ATR 42 Model : 400/500

AIR


P 3

APR 08

001

2.05.08

BLEED LEAKALERT


Bleed air leakLoop > 124_C / 255_F -- or --

-- MC light flashing amber-- AIR amber light on CAPA i t d LEAK BLEED d

SC

For aircraft fitted with mod4584: Bleed air leakLoop > 153_C / 307_F

g-- Associated LEAK, BLEED and

PACK FAULT amber lights onoverhead panel

PROCEDURE

BLEED LEAK

PACK VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDESCAUTION : System must not be restored in flight.Note : If a bleed leak occurs on ground during taxi, go back to parking.

COMMENTS-- Following the detection of a leak, the affected BLEED VALVE will close automatically

and the associated PACK VALVE will close due to lack of air supply. The associatedactions confirm automatic operation and extinguish related alerts, allowing flight to becontinued with one pack supplied.


-- System must not be restored in flight because it may create hazards.

AA

ATR 42 Model : 400/500

AIR


P 4

DEC 10

001

2.05.08

X VALVE OPEN

ALERT


X valve open with itshould be closed

-- MC light flashing amber-- AIR amber light on CAP-- X VALVE OPEN amber light on

overhead panel

SC

PROCEDURE

X VALVE OPEN

CAUTION : Do not supply both packs from one single bleed.

COMMENTS-- If both bleeds are available, no special procedure has to be applied. In case of bleed

failure, associated pack must be selected OFF.

PACK VALVE FAULT

ALERT


Pack valve position disagreeswith command or overheatdownstream of the compressor(T > 204�C / 393�F)

-- MC light flashing amber-- AIR amber light on CAP-- Associated PACK FAULT amber


SC

PROCEDURE

PACK VALVE FAULT

PACK VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

COMMENTS-- If both bleeds are available, no special procedure has to be applied. In case of bleed

failure, associated pack must be selected OFF.

AA

RR

ATR 42 Model : 400/500

AIR


P 5

APR 08

001

2.05.08

BOTH PACK VALVES FAULTPROCEDURE

BOTH PACK VALVES FAULT

MAX FL 100 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

F When ΔP < 1PSI

OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB MAX INCREASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- No air is entering in the cabin. Leaks will increase cabin altitude.

RECIRC FAN FAULTALERT


Recirculation fan low RPM < 900RPM) more than 20 secondsafter start or electrical motoroverheat

-- MC light flashing amber-- AIR amber light on CAP-- associated RECIRC FAN FAULT

amber light on overhead panel

SC

PROCEDURE

RECIRC FAN FAULT

RECIRC FAN affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

AIR


P 6

DEC 10

001

2.05.08

DUCT OVHT

ALERT


Overheat in the duct (T duct >92�C / 200�F)

-- MC light flashing amber-- AIR amber light on CAP-- associated TEMP SEL OVHT


SC

PROCEDURE

DUCT OVHT

TEMP SEL affected side MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .COMPT TEMP SELECTOR affected side COLD. . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : Monitor DUCT TEMP and make sure it remains positive to avoid possiblepack turbine damage due to freezing.

� If alert persists

PACK VALVE affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 200 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

COMMENTS-- TheOVHTalert light will remain as long as overtemperature is detected in the duct. It is

not inhibited when in MAN mode.-- When alert disappears, control COMPT TEMP manually is required.-- If alert does not disappear, the temperature control valve is jammed open. Pack valve

has to be closed.

AA

R

ATR 42 Model : 400/500

AIR


P 7

APR 08

001

2.05.08

EXCESS CAB ALTALERT


Cabin altitude above 10000 ft. -- MW light flashing red-- EXCESS CAB ALT red light on

CAP

CRC

PROCEDURE

EXCESS CAB ALT

CAB PRESS IND CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If rapid decompression

EMERGENCY DESCENT procedure (2.04.05 page 1) APPLY. . . . . . . . . . . . . .J If Z cabin > 10 000 ft confirmed

MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB DECREASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If unsuccessfulCREW OXYGEN MASKS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CREW COMMUNICATIONS ESTABLISH. . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PAX SUPPLY AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PRESSURE CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DESCENT AS RQD / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Check first for pressurization system fault. If system fault, apply appropriate procedure

(manual regulation). If no abnormal indication, start descent.

AA

ATR 42 Model : 400/500

AIR


P 8

APR 08

001

2.05.08

AUTO PRESS FAULTALERT


Digital controller failure -- MC light flashing amber-- AIR amber light on CAP-- FAULT amber light on MAN

pushbutton

SC

PROCEDURE

AUTO PRESS FAULT

MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB AS RQD TO SET CABIN RATE. . . . . . . . . . . . . . . . . . . . . . . .

Note : Minimum TARGET CAB ALT is landing elevation.

COMMENTS-- The table FL vs CAB ALT gives the relationship required to obtain ΔP = 6 PSI..

EXCESS CAB ΔPALERT


Differential pressure exceeds 6.35PSI

-- MW light flashing red-- EXCESS CAB ΔP light on CAP-- DIFF PRESS local IND exceeds

6.35 PSI

CRC

PROCEDURE

EXCESS CAB ΔP

MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB AS RQD TO SET CABIN RATE. . . . . . . . . . . . . . . . . . . . . . . .J If unsuccessful

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

AA

ATR 42 Model : 400/500

AIR


P 9

APR 08

001

2.05.08

AVIONICS VENT EXHAUST MODE FAULTALERT


Underspeed or overheat ofextract fan (T > 90_C / 194_F)

-- MC light flashing amber-- AIR amber light on CAP-- EXHAUST MODE FAULT amber


SC

PROCEDURE

AVIONICS VENT EXHAUST MODE FAULT

EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- EXHAUST MODE to OVBD position controls the OVBD valve to partially open and

stops the extract fan; ventilation air is then discharged overboard instead of beingdirected to the underfloor valve. Ventilation is ensured by ΔP between cabin andoutside air.

OVBD VALVE FAULTALERT


OVBD valve position notcorresponding with aircraftcondition

-- MC light flashing amber-- AIR amber light on CAP-- FAULT amber light on overhead

panel

SC

PROCEDURE

OVBD VALVE FAULT

CAUTION : DO NOT SELECT OVBD VALVE FULL OPEN IF ΔP > 1 PSI.J If engine 1 running, in flight or on ground

OVBD VALVE FULL CLOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If engine 1 not running, on ground

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

COMMENTS-- The OVBD VALVE should automatically close 2 minutes after engine 1 start (OIL LO

PRESSsignal). If it remains open after FULLCLOSEselection, maintenance action isrequired.

-- FULL CLOSE / FULL OPEN selection overrides OVBD selection.

AA

ATR 42 Model : 400/500

DE/ANTI ICE


P 1

DEC 09

001

2.05.09

AFR AIR BLEED FAULT

ALERT


Low pressure in thede--icing common airmanifold (P < 14 PSI)

-- or --Overtemperature (T >230�C) upstream thepressure regulatingvalve

-- MC light flashing amber-- ANTI ICING amber light on CAP-- AFR AIR BLEED FAULT amber light

on overhead panel

SC

PROCEDURE

AFR AIR BLEED FAULT

LEAVE AND AVOID ICING CONDITIONSAFR AIR BLEED OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If DE- ICING ENG FAULT light illuminates after 10 seconds

DE--ICING ENG affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AFR AIR BLEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AFR AIR BLEED light CHECK EXTINGUISH. . . . . . . . . . . . . . . . . . . . . . . . . .

� If DE- ICING ENG FAULT light does not illuminates on any side

DE--ICING AIR FRAME FAULT procedure (2.05.09 page 2) APPLY. . . . . . . . . . .

AA

R

ATR 42 Model : 400/500

DE/ANTI ICE


P 2

APR 08

001

2.05.09

DE- ICING AIR FRAME FAULTALERT


Distribution valve outputcontrolled open but nodownstream pressure detected-- or --Distribution valve outputcontrolled closed butdownstream pressure detected

-- MC light flashing amber-- ANTI ICING amber light on CAP-- Associated FAULT amber light on

overhead panel

SC

PROCEDURE

DE- ICING AIR FRAME FAULT

LEAVE AND AVOID ICING CONDITIONSDE--ICING AIR FRAME OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MINIMUM ICING SPEEDS INCREASE BY 15 KT. . . . . . . . . . . . . . . . . . . . . . . . .J If in icing condition

LDG DIST MULTIPLY BY 1.2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If ice accretion

STEEP SLOPE APPROACH (≥4.5_) PROHIBITED. . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

DE/ANTI ICE


P 3

OCT 08

001

2.05.09

DE- ICING MODE SEL FAULTALERT


Boots do not operate followingMFC failure-- or --Both boots A and B of the sameengine are supplied 200seconds after engine cyclebeginning-- or --Boots A(B) of both engines aresupplied while boots B(A) arenot supplied 20 seconds afterengines cycle beginning

-- MC light flashing amber-- ANTI ICING amber light on CAP-- DE--ICING MODE SEL FAULT


SC

PROCEDURE

DE- ICING MODE SEL FAULT

OVRD SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DE--ICING MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J In case of engine flame out

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

COMMENTS-- The OVRD mode allows to operate engines and airframe dual distribution valves in

case of engine boots primary control failure.-- DE--ICING MODE SEL OVRD must be used if there is evidence of boots cycling

malfunctionning even if DE--ICING MODE SEL FAULT is not illuminated.-- WhenDE--ICINGMODESEL is selected toOVRD, ENGand AIRFRAME FAULT lights

are inhibited and boots cycling operated only according to FAST mode.-- In case of DE--/ANTI--ICINGENGFAULTand after a prolonged flight with considerable

accretion, it is possible that when setting the DE--ICING MODE SEL to OVRD, theengine may ingest the build up ice and a flame out could occur. As the functionning ofthis device is sequential (i.e. the two engines are not concerned at the same time), it issuggested to release the DE--ICING MODE SEL pushbutton before the samephenomenon occurs on the second engine.

AA

R

ATR 42 Model : 400/500

DE/ANTI ICE


P 4

APR 08

001

2.05.09

MODE SEL AUTO FAULTALERT


MFC 1B or 2B and/or ADCfailure-- or --Discrepancy between outputs

-- MC light flashing amber-- ANTI ICING amber light on CAP-- FAULT amber light on overhead

panel

SC

PROCEDURE

MODE SEL AUTO FAULT

MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DE--ICING AND ANTI--ICING MANUAL MODE PBS . . . . . . . . . . . . . . . . . . . . . . .ACCORDING TO SAT SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- In case of FAULT or discrepancy between ADCs information and until pitlot’s action:

. High speed boots activation is selected (airframe + engines)

. High power cycle (20/60) is selected (propellers)-- OVRD gaurded pushbutton has to be used in case of cycle anomaly, indicated by its

own FAULT light.

ICE DETECT FAULTALERT


Ice detector failure -- MC light flashing amber-- ANTI ICING amber light on CAP-- FAULT ICING amber light on

control panel

SC

PROCEDURE

ICE DETECT FAULT

ICE ACCRETION VISUALLY MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

ATR 42 Model : 400/500

DE/ANTI ICE


P 5

OCT 08

001

2.05.09

DE- /ANTI- ICING ENG FAULT

ALERT


Distribution valve outputcontrolled open but nodownstream pressure detected-- or --Distribution valve outputcontrolled closed butdownstream pressure detected


overhead panel

SC

PROCEDURE

DE- /ANTI- ICING ENG FAULT

LEAVE AND AVOID ICING CONDITIONSENG PARAMETERS affected side MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Very large ice accretion on the engine air intake may generate an engine flame out

when the ice breaks free.-- Several cases of MFC failure may generate an engine DE--ICING FAULT alert prior

DE--ICING MODE SEL FAULT. Engine DE--ICING may be recovered when selectingDE--ICING MODE SEL OVRD.

AA

R

R

ATR 42 Model : 400/500

DE/ANTI ICE


P 6

APR 08

001

2.05.09

ANTI- ICING PROP FAULTALERT


One or more blade heating unitsinoperative


overhead panel

SC

PROCEDURE

ANTI- ICING PROP FAULT

LEAVE AND AVOID ICING CONDITIONSANTI--ICING PROP affected side OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If propeller unbalance due to ice becomes excessive

CL 1 + 2 MOVE TO 100% OVRD FOR 5 MINUTES. . . . . . . . . . . . . . . . . . . . .

COMMENTS-- If propeller unbalance due to ice becomes significant periodically moving both CL to

100% OVRD will modify centrifugal forces allowing ice elimination.

ANTI- ICING HORNS FAULTALERT


Power loss on a horn anti--icingunit

-- MC light flashing amber-- ANTI ICING amber light on CAP-- AssociatedFAULT amber light on

overhead panel

SC

PROCEDURE

ANTI- ICING HORNS FAULT

LEAVE AND AVOID ICING CONDITIONSJ If in icing conditions, every 5 minutes

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

COMMENTS-- One unit controls rudder and left elevator hornswhen the other controls ailerons and

right elevator horns.-- Checking of flight controlswill prevent ice accretion between flight controls and related

fixed parts of aircraft structure which couls generate flight control jamming.

AA

ATR 42 Model : 400/500

DE/ANTI ICE


P 7

APR 08

001

2.05.09

SIDE WINDOW / WINDSHIELD HTG FAULTALERT


Loss of window / windshieldheating


overhead panel

SC

PROCEDURE

SIDE WINDOW / WINDSHIELD HTG FAULT

SIDE WINDOW / WINDSHIELD HTG affected side OFF. . . . . . . . . . . . . . . . . . . .

PROBES HTG FAULTALERT


Power loss on a horn anti--icingunit

-- MC light flashing amber-- ANTI ICING amber light on CAP-- AssociatedFAULT amber light on

overhead panel

SC

PROCEDURE

PROBES HTG FAULT

J If one PROBE HTG ALPHA illuminatedSTICK PUSHER / SHAKER MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If two PROBE HTG ALPHA illuminatedSTICK PUSHER / SHAKER OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .STICK PUSHER / SHAKER FAULT procedure (2.05.06 page 4) APPLY. . . . . . .

J If PROBE HTG other than ALPHA illuminatedADC non affected side SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ASSOCIATED INDICATION MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Erroneous indicationsmay be displayed on associated equipment (CM1, CM2orSTBY

IND, TAT/SAT) due to loss of probe heating.

AA

ATR 42 Model : 400/500

AUTOPILOT


P 1

APR 08

001

2.05.10

AILERON MISTRIM (ADU message)or EXCESSIVE LATERAL TRIM REQUIREDor ABNORMAL FLIGHT CHARACTERISTICS

PROCEDURE

AILERON MISTRIM (ADU message)or EXCESSIVE LATERAL TRIM REQUIREDor ABNORMAL FLIGHT CHARACTERISTICS

FLIGHT CONTROLS HOLD FIRMLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP DISCONNECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : FLY MANUALLY PRIOR TO ADJUSTING THE LATERAL TRIMS.Note : The autopilot may be reengaged following adjustment of the lateral trims.

COMMENTS-- Ailerons forces may be affected by external conditions such as

. prolonged exposure to severe icing

. de--/anti --icing hold over time exceeded

PITCH MISTRIM (ADU message)ALERTAP trim threshold limit is exceededPROCEDURE

PITCH MISTRIM (ADU message)

FLIGHT CONTROLS HOLD FIRMLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP DISCONNECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS.

COMMENTS-- Elevator hinge moment may be affected by external conditions.-- From experience, themost likeky causeappears to be take off with ice remaining on the

tail plane (de--/anti --icing hold overtime exceeded).Severe icing may also be a factor.

AA

ATR 42 Model : 400/500

AUTOPILOT


P 2

APR 08

001

2.05.10

PITCH TRIM FAIL (ADU message)ALERTAP trim threshold limit is exceeded.PROCEDURE

PITCH TRIM FAIL (ADU message)

FLIGHT CONTROLS HOLD FIRMLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP DISCONNECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS.

DADC DATA INVALID (ADU message)ALERTIn case of disagreement between both ADC, AP (if engaged) disconnects being unable toidentify the valid ADC. APMSG is displayed on both EADI; DADCDATA INVALID is displayedon ADU.PROCEDURE

DADC DATA INVALID (ADU message)

INSTRUMENTS CROSSCHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .FAULTY ADC IDENTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ADC SW SELECT TO VALID ADC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If ADC 1 is wrong

C/B ADC 1 EMER SPLY PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C/B MFC 1A AUX / ADC 1 HOT SPLY PULL. . . . . . . . . . . . . . . . . . . . . . . . . .

J If ADC 2 is wrongC/B ADC 2 PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ADC FAULT procedure (2.05.12 page 4) APPLY. . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Drift between both ADC information may occur if pitots are partially obstructed. Check

pitots.

AA

ATR 42 Model : 400/500

AIRCRAFT PERFORMANCE MONITORING


P 1

APR 08

001

2.05.11

For APM PROCEDURES, refer to FCOM 2.02.21.

AA

ATR 42 Model : 400/500

AVIONICS


P 1

APR 08

001

2.05.12

AUDIO SEL FAULTALERT


RCAU processingboard failure orpower loss

-- MC light flashing amber-- AUDIO amber light on CAP-- AUDIO SEL FAULT amber light on

associated side panel

SC

PROCEDURE

AUDIO SEL FAULT

AUDIO SEL affected side ALTN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- In ALTN mode, affected crew station is connected directly and only to :

. VHF 1 if CM1 station is affected

. VHF 2 if CM2 station is affected

AHRS A/ERECT FAILALERT


One AHRS losesTAS input from bothADC

-- associated A/ERECT FAIL amber lightilluminates on associated side panel

NIL

PROCEDURE

AHRS A/ERECT FAIL

ATT / HDG PB affected side DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F When possible

AIRCRAFT STABILIZE SPEED AND LEVEL. . . . . . . . . . . . . . . . . . . . . . . . . .AHRS affected side, PUSH TO ERECT PB DEPRESS FOR 15 SECONDS. . . .

COMMENTS-- When the aircraft is stabilized (unaccelerated level flight), a gyro fast erection is

performed by depressing the associated pushbutton for 15 seconds.-- AHRS A/ERECT FAIL remains illuminated as long as TAS signal is lost.

AA

ATR 42 Model : 400/500

AVIONICS


P 2

DEC 09

001

2.05.12

EFIS COMP

ALERT


AHRS disagree -- MC light flashing amber-- EFIS COMP amber light on CAP-- *-- AP OFF red light on flight deck **-- AP MSG on both EADI **-- AHRS DATA INVALID on ADU **

SC

CRC **

* When the two AHRS disagree (6 degrees or more) on :. pitch information, amber PIT message is displayed on both EADI. roll information, amber ROL message is displayed on both EADI. both pitch and roll information, amber ATT message is displayed on both EADI. heading information, amber HDG message is displayed on both EADIIn these cases, AP (if engaged) disconnects being unable to identify the right AHRS.

** Only if AP is engaged.

PROCEDURE

EFIS COMP

�� If ROL, PIT, ATT, HDG cautions appears on EFI

BOTH EADI, STBY HORIZON CROSSCHECK. . . . . . . . . . . . . . . . . . . . . . . .WRONG INSTRUMENTS IDENTIFY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATT / HDG PB affected side DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

�� If AHRS 1 is wrong

C/B AHRS 1 “NORM SPLY” PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C/B AHRS 1 “AUX SPLY” PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

�� If AHRS 2 is wrong

C/B AHRS 2 “NORM SPLY“ PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C/B AHRS 2 “AUX SPLY FLT” PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note: C/Bs deselection allows AP reconnection

�� If LOC / GS / ILS caution appears on EFIS

NAV SOURCES CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .VOR / ILS PB affected side DEPRESS AS RQD. . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- The standby horizon is used as a reference to identify the wrong EADI.-- The pilot on the affected side selects the non affected AHRS to supply its SGU.-- The wrong AHRS is selected OFF to recover AP (pitch or roll AHRS disagree) or HDG

HOLD and GA mode (heading AHRS disagree).-- EFIS COMP can be triggered on ground by local magnetic perturbations. When the

aircraft moves away from magnetic perturbations source, the fault should disappearquickly

AA

R

R

ATR 42 Model : 400/500

AVIONICS


P 3

APR 08

001

2.05.12

ADC SW FAULTALERT


Incorrect ADCswitching

-- MC light flashing amber-- ENG amber light on CAP-- ADC SW FAULT amber light on flight

deck panel

SC

PROCEDURE

ADC SW FAULT

ADC SW SET TO OPPOSITE ADC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- ADC SW FAULT illuminates when ADC switch position does not correspond to ADC

actual selection (relays defect).-- ADC is set back to the previous selection in order to have an agreement between ADC

switch position and ADC selection.

ADU FAILURE

PROCEDURE

ADU FAILURE

IAS / VS MODE USE TCS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Note : ALT SEL mode is lost.J If amber AP MSG appears on EADI- or - J If in composite mode

FLIGHT CONTROLS HOLD FIRMLY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP DISCONNECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- As crew is no longer informed on anomaly message, AP must be disconnected.

AA

Mod : 5205 ATR 42 Model : 400/500

AVIONICS


P 4

APR 08

050

2.05.12

ADC FAULTALERT


Loss of ADC

Selected ADC isconnected to AP

-- Red flag on speed indicators-- TAT/SAT/TAS information are lost-- AP MSG on both EADI-- CPL DATA INVALID on ADU

NIL

PROCEDURE

ADC FAULT

VALID ADC SELECT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PF NON affected side. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AP COUPLING NON affected side. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ATC NON affected equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If ADC 1 is lost

LANDING ELEVATION PRESSURE ALTITUDE SET. . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

J If ADC 1 + 2 are wrongSTBY INST USE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAN RATE KNOB 9 O’CLOCK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CAB PRESS MODE SEL MAN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ENGINES PARAMETERS MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU MAN MODE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU FAULT procedure (2.05.06 page 8) APPLY. . . . . . . . . . . . . . . . . . . . . . . . .

Note : If both ADC are lost, de--/anti--icing MODE SEL AUTO is lost.

COMMENTS-- WhenADC1 is lost, ADC2 is automatically selected to supply the pressurizationdigital

controller. Then baro correction is no longer available (ref 1013 mb) and landing fieldelevation must be set in terms of pressure altitude.

-- If both ADC are lost, only standby instruments are available: air data instruments havea red flag and AHRS have lost their TAS inputs. Pressurization has to be performedmanually.

-- If the selected ADC is lost, FDAU does not receive inputs; bugs are not available onTQindicators. Each engine uses their own source (if ADC 1 is the faulty selected ADC).

-- Ten seconds are necessary to recover bugs on TQ indicator after selection of the validADC.

AA

ATR 42 Model : 400/500

AVIONICS


P 5

APR 08

001

2.05.12

AHRS FAILALERT


Loss of AHRS -- ATT FAIL red message on associated EADI-- HDG FAIL red message on associated EHSI-- Flag on opposite RMI

NIL

PROCEDURE

AHRS FAIL

ATT / HDG PB affected side DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .REMAINING AHRS OUTPUTS PERIODICALLY COMPARE TO STBY INST. . . . . .

COMMENTS-- The pilot on the affected side selects the non affected AHRS to supply its SGU.-- AP (if engaged) identifies the valid AHRS and remains engaged.

SGU FAILALERT-- Refer to 1.10.30 page 14 for SGU failure alerts.

PROCEDURE

SGU FAIL

EFIS SG PB affected side DEPRESS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- If AP is engaged and coupled to the wrong SGU, uppermodes are lost. When selecting

valid SGU, AP recovers upper modes.-- Do not confuse with CRT failure; in case of a SGU failure, both CRT on one side are

affected.

CRT FAIL

PROCEDURE

CRT FAIL

CRT affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COMMENTS-- Affected CRT must be switched OFF to obtain composite mode on the non affected

one. In composite mode, the background brightness (brown and blue colors) iscontrolled by the WX DIM rheostat.

AA

ATR 42 Model : 400/500

MISCELLANEOUS


P 1

DEC 10

001

2.05.13

COCKPIT DOOR CONTROL PANEL FAULT

PROCEDURE

COCKPIT DOOR CONTROL PANEL FAULT (if installed)

COCKPIT DOOR MANUAL LOCK BOLT(S) MOVE TO CLOSE POSITION. . . . . . .

Note : When the door is locked with the manual bolts, the emergency access to thecockpit is unavailable. It is recommended that at least two crewmembersremain in the cockpit during that time.

LOSS OF RADIO ALTIMETER INFORMATION

ALERT


Loss ofradioaltimeter

-- amber dashes on EADI-- GPWS FAULT amber light on CAP

NIL

PROCEDURE

LOSS OF RADIOALTIMETER INFORMATION

GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TCAS (if installed) STBY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : LDG GEAR NOT DOWN undue warning may be generated whenreducing PL.This alarm may be cancelled by using EMER AUDIO CANCEL.

SMK DET FANS FAULT

ALERT


Smoke detectorsfans failure

-- MC light flashing amber-- AIR amber light on CAP-- FANS FAULT amber light on overhead

panel

SC

PROCEDURE

SMK DET FANS FAULT

FAN ALTN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

R

R

ATR 42 Model : 400/500

MISCELLANEOUS


P 2

DEC 10

001

2.05.13

DOORS UNLK IN FLIGHT

ALERT


Door UNLK in flight -- MC light flashing amber-- DOOR amber light on CAP-- associated door amber light on

overhead panel

SC

PROCEDURE

DOORS UNLK IN FLIGHT

� If any door except FWD COMPT

SIGNS ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DOOR affected VISUALLY CHECK. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If unlocked or check not feasible

LANDING ELEVATION 9000 ft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 100 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� If FWD COMPT

NO ACTION

COMMENTS-- As the doors (except FWD COMPT) open outwards, when one is not locked, the ∆P

must be reduced by aircraft descent and landing elevation selection.

COCKPIT WINDOW CRACKED

PROCEDURE

COCKPIT WINDOW CRACKED

WINDOW HEAT affected OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LANDING ELEVATION 9000 ft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAX FL 100 / MEA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AA

R

ATR 42 Model : 400/500

MISCELLANEOUS


P 3

APR 08

001

2.05.13

OXYGEN LO PRALERT


Low pressure (below50 PSI) in the LPdistribution circuit

-- MC light flashing amber-- OXY amber light on CAP-- MAIN SUPPLY LO PR amber light on

overhead panel

SC

PROCEDURE

OXYGEN LO PR

OXY MAIN SUPPLY OFF THEN ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .J If oxygen LO PR light remains lit

MAIN SUPPLY OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OXYGEN PORTABLE UNIT INSTALL IN COCKPIT AS RQD. . . . . . . . . . . . . .

COMMENTS-- The 120 l portable oxygen bottle permits a continuous diluted flow to one crewmember

at 13 000 ft for a duration of 30 mn.Oxygen low pressure supply valve position may disagree with actual oxygen MAINSUPPLY pushbutton position if this pushbutton is activated by very close consecutiveactions.Interval betweenOFF andONactions on oxygenMAINSUPPLYmust be greater thanone second to be sure that low pressure supply valve position is in accordance withactual pushbutton position.

-- This bottle can be placed in the cockpit.

AA

ATR 42 Model : 400/500

MFC


P 1

OCT 08

001

2.05.14

MFC 1A FAULT

ALERT


MFC 1A FAULT -- MC light flashing amber-- MFC amber light on CAP-- Associated MFC FAULT amber light on

overhead panel

SC

PROCEDURE

MFC 1A FAULT

MODULE 1A OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1A MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . . . . . .

COMMENTS-- As HP valve 1 is lost, air is bled only from the LP stage. Applicable pack performance is

affected at low engine power.-- Landing gear primary RED UNLK indications are lost.

AA

RR

ATR 42 Model : 400/500

MFC


P 2

OCT 08

001

2.05.14

MFC 1B FAULT

ALERT


MFC 1B FAULT -- MC light flashing amber-- MFC amber light on CAP-- Associated MFC FAULT amber light on

overhead panel

SC

PROCEDURE

MFC 1B FAULT

MODULE 1B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1B MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . . . . . .

� If failure during taxi out

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

� Prior take off

PACK 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After take off

PACK 1 + 2 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE FULL CLOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR LEAVE DOWN FOR COOLING FOR 1 MINUTE. . . . . . . . . . . .

AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY. . . . . . . . . . . . . .

� After landing


CAUTION : Before opening any door, packs 1 and 2 must be selected OFF andcockpit communication hatch must be opened.

COMMENTS-- AsWOW signal is lost, OVBD valvemust be selected FULLOPENmanually on ground

to improve racks cooling.-- Hot brakes indication is lost; LDG GEAR must remain down during 1 minute after take

off for cooling.-- Ground turbofan 1 being lost, PACK 1 must be switched OFF on ground to avoid any

overheat problem.-- ENG 1 OIL LO PRESS light remains ON when engine 1 is shut down.-- After landing, as outflow valves do not fully open, selecting OVBD valve FULL OPEN

relieves the ∆P between cabin and outside.-- On ground, pressurization digital controller test capability is lost.

AA

RR

ATR 42 Model : 400/500

MFC


P 3

OCT 08

001

2.05.14

MFC 2A FAULT

ALERT


MFC 2A FAULT -- MC light flashing amber-- MFC amber light on CAP-- Associated MFC FAULT amber light on

overhead panel

SC

PROCEDURE

MFC 2A FAULT

MODULE 2A OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 2A MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . . . . . .



� After take off

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

� At touch down

IDLE GATE MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After landing


COMMENTS-- EXHAUST MODE to OVBD position controls the OVBD valve to partially open:

ventilatin air is then discharged overboard instead of being directed to the underfloorvalve. Ventilatin is ensured by ∆P between cabin and outside.

-- AsWOW signal is lost, OVBD valvemust be selected FULLOPENmanually on groundto improve racks cooling.

-- IDLE GATE FAIL amber alert is lost.-- As HP valve 2 is lost, air is bled only from the LP stage. Pack 2 performance is affected

at low engine power.-- Right hand side window anti--icing is lost.-- As extract fan is lost, avoid leaving avionics selected ON on ground for a long period of

time with high OAT.-- Landing gear secondary green arrows and RED UNLK indications are lost.

AA

R

R

ATR 42 Model : 400/500

MFC


P 4

OCT 08

001

2.05.14

MFC 2B FAULT

ALERT


MFC 2B FAULT -- MC light flashing amber-- MFC amber light on CAP-- Associated MFC FAULT amber light on

overhead panel

SC

PROCEDURE

MFC 2B FAULT

MODULE 2B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 2B MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . . . . . .



� Prior take off

PACK 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After take off

PACK 1 + 2 ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE FULL CLOSE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .LDG GEAR LEAVE DOWN FOR COOLING FOR 1 MINUTE. . . . . . . . . . . .

AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY. . . . . . . . . . . . . .

� After landing



COMMENTS-- AsWOW signal is lost, OVBD valvemust be selected FULLOPENmanually on ground

to improve racks cooling.-- Hot brakes indication is lost; LDG GEAR must remain down during 1 minute after take

off for cooling.-- Ground turbofan 2 being lost, PACK 2 must be switched OFF on ground to avoid any

overheat problem.-- ENG 2 OIL LO PRESS light remains ON when engine 2 is shut down.-- Landing gear secondary green arrows and RED UNLK indications are lost.-- After landing, selecting the OVBD valve fully open relieves the∆P between cabin and

outside.-- Right hand side window anti--icing is lost without FAULT indication.

AA

RR

ATR 42 Model : 400/500

MFC


P 5

OCT 08

001

2.05.14

MFC 1A + 1B FAULT

ALERT


MFC 1A + 1BFAULT

-- MC light flashing amber-- MFC amber light on CAP-- Associated MFC FAULT amber light on

overhead panel

SC

PROCEDURE

MFC 1A + 1B FAULT

MODULES 1A + 1B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING PROP 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING PROP FAULT procedure (2.05.09 page 6) APPLY. . . . . . . . . . . . . . .DE--ICING MODE SEL OVRD AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PACK 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED 1 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVE FAULT procedure (2.05.08 page 1) APPLY. . . . . . . . . . . . . . . . . . .RADAR OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1A + 1B MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . .

� Before landing

ATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After landing



COMMENTS-- Landing gear primary green arrows and RED UNLK indications are lost.-- PACK 1, BLEED 1, left hand side window anti--icing and stick pusher are lost without

FAULT indications.-- AC BUS 1 is lost leading to loss of trim indicator, GPWS and weather radar.-- ATPCS must be selected OFF before landing due to loss of autofeather on engine 1.

Check go around performances ATPCS OFF.See also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 1B FAULT

(2.05.14 page 2).

AA

R

R

ATR 42 Model : 400/500

MFC


P 6

OCT 08

001

2.05.14

MFC 1A + 2A FAULT

ALERT


MFC 1A + 2AFAULT


overhead panel

SC

PROCEDURE

MFC 1A + 2A FAULT

MODULES 1A + 2A OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .TLU MAN MODE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .RADAR OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GPWS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1A + 2A MODULES LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . .Note : Airframe FAULT amber alert is lost.Note : When airframe de--icing is used, monitor boots inflation.Note : As AP OFF alert is lost, use of AP below 1000 ft AGL is prohibited.Note : VOR 2, ADF 2, CRS 2 information are lost. ADC 2 outputs are not available.

� Before landing

LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : LDG GEAR cannot be retracted.

� At touch down


� After landing


COMMENTS-- AC BUS 1 + 2 are lost leading to loss of trim indicator, GPWS and weather radar.-- DC BUS 1 + 2 OFF warnings on overhead panel are lost.-- Mechanical, crew and hostess call are lost.-- Stick pusher FAULT indication is lost but stick pusher is still available.See also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 2A FAULT

(2.05.14 page 3).

AA

R

R

R

ATR 42 Model : 400/500

MFC


P 7

OCT 08

001

2.05.14

MFC 1A + 2B FAULT

ALERT


MFC 1A + 2BFAULT


overhead panel

SC

PROCEDURE

MFC 1A + 2B FAULT

MODULES 1A + 2B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MAIN BLUE HYD PUMP OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HYD X FEED ON. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DE--ICING MODE SEL OVRD AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1A + 2B MODULE LOST EQUIPMENT LIST (QRH pages 2.39--40--41) CHECKNote : AP does not disconnect after STBY PITCH TRIM activation.

� Before landing

Note : Flaps control is lost.REDUCED FLAPS LANDING procedure (2.05.06 page 3) APPLY. . . . . . . . . . . .LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


� After landing



COMMENTS-- Selecting de--icing mode to OVRD position allows to recover all pneumatic de--icers

operations.-- Main blue HYD pump control is lost as well as flaps control. Slecting HYD X FEED open

allows to recover blue HYD pressure but flaps control remains lostSee also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 2B FAULT

(2.05.14 page 4).

AA

R

R

R

ATR 42 Model : 400/500

MFC


P 8

OCT 08

001

2.05.14

MFC 1B + 2A FAULT

ALERT


MFC 1B + 2AFAULT


overhead panel

SC

PROCEDURE

MFC 1B + 2A FAULT

MODULES 1B + 2A OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DE--ICING MODE SEL OVRD AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1B + 2A MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . .Note : VOR 2, ADF 2, CRS 2 information are lost. CM2 IAS is not available.

� Before landing

Note : Flaps control is lost.REDUCED FLAPS LANDING procedure (2.05.06 page 3) APPLY. . . . . . . . . . . .LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


� At touch down


� After landing



COMMENTS-- Selecting de--icing mode to OVRD position allows to recover all pneumatic de--icers

operations.-- DC BUS 2 OFF warning on overhead panel is lost.-- Hostess and crew indications calls are lost.-- Hot brakes indicating system test is lost.-- Landing gear controls, secondary RED UNLK and green arrows indications are lost.See also COMMENTS for MFC 1B FAULT (2.05.14 page 2) and for MFC 2A FAULT

(2.05.14 page 3).

AA

RR

R

ATR 42 Model : 400/500

MFC


P 9

DEC 10

001

2.05.14

MFC 2A + 2B FAULT

ALERT


MFC 2A + 2BFAULT


overhead panel

SC

PROCEDURE

MFC 2A + 2B FAULT

MODULES 2A + 2B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AVIONICS VENT EXHAUST MODE OVBD. . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING PROP 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING PROP FAULT procedure (2.05.09 page 6) APPLY. . . . . . . . . . . . . . .DE--ICING MODE SEL OVRD AS RQD. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PACK 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .BLEED VALVE FAULT procedure (2.05.08 page 1) APPLY. . . . . . . . . . . . . . . . . . .MFC 2A + 2B MODULES LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . .

� Before landing

ATPCS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� At touch down


� After landing



COMMENTS-- STICK PUSHER, PACK 2, BLEED 2 are lost without FAULT indications.-- ATPCS must be selected OFF before landing due to loss of autofeather on engine 1.

Check go around performances ATPCS OFF.-- Hostess and crew indications calls are lost.See also COMMENTS for MFC 2A FAULT (2.05.14 page 3) and for MFC 2B FAULT

(2.05.14 page 4).

AA

R

ATR 42 Model : 400/500

MFC


P 10

OCT 08

001

2.05.14

MFC 1B + 2B FAULT

ALERT


MFC 1B + 2BFAULT


overhead panel

SC

PROCEDURE

MFC 1B + 2B FAULT

MODULES 1B + 2B OFF / RESET. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVERHEAD PANEL MONITOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .MFC 1B + 2B MODULE LOST EQUIPMENT LIST (QRH) CHECK. . . . . . . . . . . . .� Before landing

NOSE WHEEL STEERING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--SKID OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--SKID FAULT procedure (2.05.07 page 7) APPLY. . . . . . . . . . . . . . . . . . .LDG GEAR LEVER DOWN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .EMER EXTENSION HANDLE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CAUTION : LDG GEAR cannot be retracted.� At touch down

IDLE GATE PULL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DIFFERENTIAL BRAKING USE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

� After landingPACK 1 + 2 OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ANTI--ICING HORNS OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PROBES HEATING OFF. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OVBD VALVE FULL OPEN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Note : ATPCS ARM light is not available.Note : External power cannot be used.


COMMENTS-- MC, MW and most of centralized alerts are lost : monitor averhead panel.-- Braking is lost below 35 kt if anti --skid is ON.-- IDLE GATE automatic function is not availablet.-- TAT heating FAULT light is lost.-- No whooler is heard during trim activation.-- Stall Warning and Stick Shaker are lost without FAULT indication. Stick Pusher is

available.See also COMMENTS for MFC 1B FAULT (2.05.14 page 2) and for MFC 2B FAULT

(2.05.14 page 4).

AAAA

R

R

R

ATR 42 Model : 400/500

CARGO LOADING

LOADING FUEL BALANCE CHART

P 001

DEC 07

001

2.06.02

FORWARD AND REAR CARGO COMPARTMENTS

-- Refer to “Weight and Balance Manual” : 1--60--03R

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R Eng. : PW127E / PW127M ATR 42 Model : 500

TORQUE TABLES

POWER SETTING

P 1

APR 08

001

3.02.02

PW127E/M TAKE OFF TORQUE COMPUTED FOR VC = 50. KT

SAT (c) PROPELLER SPEED 100.0 %AIRCOND.

NORMALAIR

PRESSURE ALTITUDE (FT)COND.OFF

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

- 40. --63. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0- 10. --27. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0- 8. --24. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0- 6. --22. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0- 4. --19. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0

- 2. --17. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.00. --14. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.02. --12. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.04. --10. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.06. --7. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0

8. --5. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0

10. --2. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 89.612. 0. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 88.514. 3. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 89.1 87.216. 5. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 87.8 85.9

18. 8. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 86.4 84.5

20. 10. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 88.4 84.8 83.022. 13. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 90.0 86.8 83.2 81.4

24. 15. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 88.8 85.1 81.6 79.9

26. 18. 90.0 90.0 90.0 90.0 90.0 90.0 90.0 87.0 83.5 80.0 78.3

28. 20. 90.0 90.0 90.0 90.0 90.0 90.0 89.0 85.4 81.9 78.5 76.8

30. 23. 90.0 90.0 90.0 90.0 90.0 90.0 87.3 83.7 80.3 77.0 75.4

32. 25. 90.0 90.0 90.0 90.0 90.0 89.2 85.6 82.1 78.7 75.5 73.9

34. 28. 90.0 90.0 90.0 90.0 90.0 87.5 83.9 80.5 77.2 74.0 72.4

36. 30. 90.0 90.0 90.0 90.0 89.3 85.7 82.2 78.9 75.6 72.5 71.0

38. 33. 90.0 90.0 90.0 90.0 87.5 84.0 80.6 77.3 74.1 71.0 69.5

40. 36. 90.0 90.0 90.0 89.3 85.7 82.2 78.9 75.7 72.642. 38. 90.0 90.0 90.0 87.4 83.9 80.5 77.3 74.1

44. 41. 90.0 90.0 89.1 86.6 82.1 78.8 75.646. 43. 90.0 90.0 87.2 83.7 80.3 77.1

48. 46. 90.0 88.8 85.3 81.8 78.650. 48. 90.0 86.8 83.3 80.052. 51. 88.3 84.8 81.454. 53. 86.2 82.855. 54. 85.1 81.8

Applicable for 0 Vc 60 kt.

The part above the reinforced line is the flat rated area; engine mechanical limit.

The part below the reinforced line is the area where the thermodynamical limit is reachedfirst.

AAAA

R Eng. : PW127E / PW127M ATR 42 Model : 500

TORQUE TABLES

POWER SETTING

P 2

APR 08

001

3.02.02

PW127E/M RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT

SAT (c) PROPELLER SPEED 100.0 %AIRCOND.

NORMALAIR

PRESSURE ALTITUDE (FT)COND.OFF

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

- 40. --63. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0- 10. --27. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0- 8. --24. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0- 6. --22. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0- 4. --19. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0

- 2. --17. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.00. --14. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.02. --12. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.04. --10. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.06. --7. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0

8. --5. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0

10. --2. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 99.612. 0. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 98.314. 3. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 99.0 96.916. 5. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 97.5 95.5

18. 8. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 96.0 93.9

20. 10. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 98.2 94.2 92.222. 13. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 100.0 96.4 92.4 90.5

24. 15. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 98.6 94.6 90.7 88.8

26. 18. 100.0 100.0 100.0 100.0 100.0 100.0 100.0 96.7 92.7 88.9 87.0

28. 20. 100.0 100.0 100.0 100.0 100.0 100.0 98.9 94.8 90.9 87.2 85.4

30. 23. 100.0 100.0 100.0 100.0 100.0 100.0 97.0 93.0 89.2 85.5 83.7

32. 25. 100.0 100.0 100.0 100.0 100.0 99.2 95.1 91.2 87.5 83.9 82.1

34. 28. 100.0 100.0 100.0 100.0 100.0 97.2 93.2 89.4 85.8 82.2 80.5

36. 30. 100.0 100.0 100.0 100.0 99.2 95.2 91.4 87.6 84.0 80.6 78.9

38. 33. 100.0 100.0 100.0 100.0 97.2 93.3 89.5 85.8 82.3 78.9 77.3

40. 36. 100.0 100.0 100.0 99.2 95.2 91.4 87.7 84.1 80.642. 38. 100.0 100.0 100.0 97.2 93.2 89.5 85.8 82.3

44. 41. 100.0 100.0 99.0 95.1 91.3 87.6 84.046. 43. 100.0 100.0 96.9 93.0 89.3 85.7

48. 46. 100.0 98.7 94.7 90.9 87.350. 48. 100.0 96.4 92.6 88.952. 51. 98.1 94.2 90.454. 53. 95.7 92.055. 54. 94.6 90.8

Applicable for 0 Vc 60 kt.

The part above the reinforced line is the flat rated area; engine mechanical limit.

The part below the reinforced line is the area where the thermodynamical limit is reachedfirst.

AAAA

APR 08

PW127E/M

Eng. : PW127E / PW127M

APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

PW127E/M


APR 08

APR 08

APR 08

APR 08

ATR 42 Model : 400/500

CONTENTS

TAKE-OFF

P 1

OCT 08

001

3.03.00

3.03.00 CONTENTS

3.03.01 GENERALTAKE--OFF CONDITIONSTAKE--OFF SPEEDS

3.03.02 METHODOLOGYGENERALDETERMINATION OF THE TOWNL RUNWAYS

3.03.03 CORRECTIONSAIR CONDITIONINGRUNWAY CONTAMINATIONRUNWAY SLOPEWINDQNHWAT (WEIGHT -- ALTITUDE -- TEMPERATURE)OBSTACLESBRAKES ENERGY

3.03.04 QUICK REFERENCE TABLES (QRT)

3.03.05 TAKE-OFF SPEEDS VALUES

3.03.06 EXAMPLE OF TAKE-OFF CHART COMPUTED WITH FOS

AA

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ATR 42 Model : 400/500

METHODOLOGY

TAKE-OFF

P 3

DEC 09

001

3.03.02

DETERMINATION OF THE TOWFOR SPEED CALCULATION : REFER TO 3.03.05 PAGE 1

AA

R

APR 08

Mod : 4372 + 4540 ATR 42 Model : 500

METHODOLOGY

TAKE-OFF

P 5

DEC 10

200

3.03.02

NORMAL CONDITIONSNL CHART - ASSOCIATED TO MTOW = 18600 Kg

R

APR 08

ATR 42 Model : 500

CORRECTIONS

TAKE-OFF

P 1

APR 08

001

3.03.03

AIR CONDITIONING

Take off performances are computed with AIR CONDITIONING ON.

To take into account the effect of AIR CONDITIONING OFF add to the runway length the∆L correction given in the following table :

LENGTHAIR COND. ON

∆LAIR COND. OFF

750 m (2460 ft) 0 m (0 ft)

1000 m (3280 ft) 10 m (30 ft)

1500 m (4920 ft) 25 m (80 ft)

2000 m (6560 ft) 45 m (140 ft)

2500 m (8200 ft) 65 m (210 ft)

3000 m (9840 ft) 85 m (270 ft)

Note : The FOS, in accordance with AFM, takes into account a conservativeperformance decrement linked to the thermodynamical limitation of the engine.If the day conditions authorize a mechanical limit operation of the engine (i.etorque bleed ON = 90% for TO and 100% for RTO), the take off may be performedair conditioning ON without performance penalty.

AA

Mod : 4372 + 4540 + 4971 ATR 42 Model : 500

CORRECTIONS

TAKE-OFF

P 2

APR 08

300

3.03.03

RUNWAY SLOPE¯ Runway slope between -- 2 % and + 2 %Decrease the runway length by 700 m (2300 ft) for 1 % uphill slope.For a better accuracy, use the chart given in 3.03.02 page 5 or 6.¯ Runway slope beyond 2 %Refer to AFM and apply the given correction.

WINDDecrease the runway length by 500 m (1640 ft) for 10 kt tailwind.

QNHTo use a chart computed at the standard pressure when the actual QNH is not standard,follow the hereafter procedure :

1) With the actual wind and temperature, if necessary corrected by air conditioninginfluence, enter the chart and read the take--off weight and the associated limitation.

2) Apply the QNH correction :¯ QNH > 1013.25 HPa or 29.92 in HgNo credit in case of brakes energy limitation, keep the values of the chart.For all other limitations, add 70 kg (155 lb) to the TOW for each 10 HPa (0.29 in Hg)above the standard pressure.For QNH 1050 Hpa, keep the values of 1050 HPa.¯ QNH < 1013.25 HPa or 29.92 in HgSubstract 265 kg (585 lb) to the TOW for each 10 HPa (0.29 in Hg) below thestandard pressure.

3) With the new TOW, enter again the chart to interpolate the take off speeds.

AA

Mod : 4372 + 4540 ATR 42 Model : 500

CORRECTIONS

TAKE-OFF

P 2A

APR 08

200

3.03.03

NON DRY RUNWAYS

A non dry runway may be :-- wet,-- contaminated by water or slush, loose snow*, compacted snow, ice.

*Loose snow : must be considered as slush. To determine the equivalent slush depth,multiply the loose snow depth by : 1.25 x (actual loose snow density)

1 - Contaminated runway

At take off, the aircraft lateral controllability depends on :-- the exact contaminant characteristics,-- the cross wind component,-- the runway width and visual references.

Since these factors do not allow sufficient accuracy for predicting the effect ofasymmetrical reverse thrust, it is therefore not recommended to usesingle engine reversethrust for take off on contaminated runway.

Performances without reverser only are to be used for flight preparation.

2 - Wet runways

In this particular condition, the single reverser use is perfectly controllable and leads to theminimum stop distance in case of rejected take off.

3 - Non dry runways corrections for FCOM computation

According to the previous assumptions, decrease the runway length by the followingvalues to take into account the runway contamination :

RUNWAY CONTAMINATION CORRECTION

Wet 150 m (490 ft)

Water or slush between 3 mm (1/8 in) and6.3 mm (1/4 in) 350 m (1150 ft)

Water or slush between 6.3 mm (1/4 in)and 12.7 mm (1/2 in) 450 m (1480 ft)

Compact snow 200 m (660 ft)

Ice 500 m (1640 ft)

AA

Mod : 4372 + 4540 ATR 42 Model : 500

CORRECTIONS

TAKE-OFF

P 6

APR 08

200

3.03.03

BRAKES ENERGY LIMITATIONNORMAL CONDITIONSUSE FOR ANY TAILWIND UP TO 15 KT

TAKE OFF WEIGHT (KG) -- LIMITATIONSV1(IAS.KT)--VR(IAS.KT)--V2(IAS.KT)

ZP FT 0 1000 2000

0 18651 6--6 18318 6--6 17996 6--6.0 18651 6 6108 108 115

18318 6 6107 107 114

17996 6 6106 106 112

10 0 18311 6--6 17995 6--6 17689 6--610.0 18311 6 6107 107 114

17995 6 6106 106 112

17689 6 6105 105 111

20 0 17991 6--6 17691 6--6 17400 6--620.0 17991 6 6106 106 112

17691 6 6105 105 111

17400 6 6104 104 110

30 0 17711 6--6 17423 6--6 17136 6--630.0 17711 6 6105 105 111

17423 6 6104 104 110

17136 6 6103 103 109

40 0 17442 6--6 17156 6--6 16865 6--640.0 17442 6 6104 104 110

17156 6 6103 103 109

16865 6 6103 103 108

50 0 17181 6--6 16886 6--6 16596 6--650.0 17181 6 6104 104 109

16886 6 6103 103 108

16596 6 6102 102 107


ZP FT 4000 6000 8000

10 0 17695 6--6 17102 6--6 16517 6--6---10.0 17695 6 6105 105 111

17102 6 6103 103 109

16517 6 6101 101 107

0 17399 6--6 16805 6--6 16211 6--6.0 17399 6 6104 104 110

16805 6 6102 102 108

16211 6 6100 100 106

5 0 17247 6--6 16656 6--6 16064 6--65.0 17247 6 6104 104 110

16656 6 6102 102 107

16064 6 6100 100 105

10 0 17098 6--6 16511 6--6 15915 6--610.0 17098 6 6103 103 109

16511 6 6101 101 107

15915 6 6100 100 105

15 0 16955 6--6 16363 6--6 15775 6--615.0 16955 6 6103 103 109

16363 6 6101 101 106

15775 6 699 99 104

20 0 16822 6--6 16212 6--6 15635 6--620.0 16822 6 6102 102 108

16212 6 6100 100 106

15635 6 699 99 103

25 0 16691 6--6 16099 6--6 15497 6--625.0 16691 6 6102 102 108

16099 6 6100 100 105

15497 6 699 99 103

30 0 16558 6--6 15962 6--6 15361 6--630.0 16558 6 6102 102 107

15962 6 6100 100 105

15361 6 698 98 102

35 0 16422 6--6 15827 6--6 15224 6--635.0 16422 6 6101 101 107

15827 6 6100 100 104

15224 6 698 98 102

40 0 16284 6--6 15691 6--6 14765 3--340.0 16284 6 6101 101 106

15691 6 6100 100 104

14765 3 397 97 100

AA

Mod : 4372 + 4540 ATR 42 Model : 500

CORRECTIONS

TAKE-OFF

P 7

APR 08

200

3.03.03

BRAKES ENERGY LIMITATIONICING CONDITIONSUSE FOR ANY TAILWIND UP TO 15 KT


ZP FT 0 1000 2000 3000

BELOW 17552 6--6112 112 119

17260 6--6111 111 118

16969 6--6110 110 116

16687 6--6109 109 115

BELOW5˚C 112 112 119 111 111 118 110 110 116 109 109 115

BELOW 17400 6--6111 111 118

17110 6--6111 111 117

16825 6--6110 110 116

16544 6--6109 109 115

BELOW10˚C 111 111 118 111 111 117 110 110 116 109 109 115


ZP FT 4000 5000 6000 8000

BELOW 16404 6--6108 108 114

16121 6--6107 107 113

15839 6--6107 107 112

15275 6--6105 105 110

BELOW5˚C 108 108 114 107 107 113 107 107 112 105 105 110

BELOW 16263 6--6108 108 114

15985 6--6107 107 113

15700 6--6106 106 111

15132 6--6104 104 109

BELOW10˚C 108 108 114 107 107 113 106 106 111 104 104 109

TAKE OFF WEIGHT (LB) -- LIMITATIONSV1(IAS.KT)--VR(IAS.KT)--V2(IAS.KT)

ZP FT 0 1000 2000 3000

BELOW 38697 6--6112 112 119

38052 6--6111 111 118

37412 6--6110 110 116

36789 6--6109 109 115

BELOW5˚C 112 112 119 111 111 118 110 110 116 109 109 115

BELOW 38361 6--6111 111 118

37722 6--6111 111 117

37092 6--6110 110 116

36473 6--6109 109 115

BELOW10˚C 111 111 118 111 111 117 110 110 116 109 109 115

TAKE OFF WEIGHT (LB) -- LIMITATIONSV1(IAS.KT)--VR(IAS.KT)--V2(IAS.KT)

ZP FT 4000 5000 6000 8000

BELOW 36165 6--6108 108 114

35542 6--6107 107 113

34920 6--6107 107 112

33676 6--6105 105 110

BELOW5˚C 108 108 114 107 107 113 107 107 112 105 105 110

BELOW 35854 6--6108 108 114

35242 6--6107 107 113

34614 6--6106 106 111

33361 6--6104 104 109

BELOW10˚C 108 108 114 107 107 113 106 106 111 104 104 109

AA

Mod : 4372 + 4540 ATR 42 Model : 500

QUICK REFERENCE TABLES

TAKE-OFF

P 1

APR 08

200

3.03.04

The QRT are computed at standard pressure, with air conditioning ON, no wind, noobstacle, a dry runway and no slope.

Entry parameters must be determined as indicated in 3.03.02 page 3.

NORMAL CONDITIONS

The QRT are computed with V2/VSR = 1,143 and V1/VR = 1.

ICING CONDITIONS

The QRT are computed with V2/VSR = 1,222 and V1/VR = 1.

In case of ground icing conditions, if atmospheric icing conditions do not exist, the V2/VSspeed ratio may be the same as in normal conditions.

Note : All regulatory limitations are taken into account in the QRT, except the structurallimitation.When the QRT indicates a weight value above the certified structural value, thatmeans that the runway is NL in the conditions of computation of the QRT.In any cases, the actual TOW must always be less than the certified MTOWassociated to the operated ATR version.

AA

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

ATR 42 Model: 400/500

TAKE--OFF SPEEDS VALUES

TAKE-OFF

P 1

DEC 10

001

3.03.05

The determination of the take--off speeds is done in relation with the TOW determinedin 3.03.02 page 3.

� If RTOW maxi = structural MTOW (NL), speeds are read in the table 3.03.05 p 2 or inQRH. Read the speeds corresponding to the actual TOW.

� If NL limitation:If the runway is « NL », you can take off at the structural MTOW. Check the associatedspeeds in the table 3.03.05 p2or QRH, using the actual TOW

� If Wa limitation: speeds are read in the QRT3.03.04, with the day conditions (Zp, OAT,corrected runway length). Take the speeds corresponding to the take--off weightindicated in the tables, even if the actual TOW is lower.

� If Wb limitation: speeds are read in the brakes energy tables 3.03.03 p 6/7, with theday conditions (Zp, OAT).Take the speeds corresponding to the take--off weightindicated in the tables, even if the actual TOW is lower.

� If Wc &Wd limitation:-- Without tailwind, speeds are read in the table 3.03.05 p 2 or in QRH. Read thespeeds corresponding to the actual TOW.-- In case of tailwind, compare the previous speeds with the brake energy limitationspeeds 3.03.03 p 6/7 and take the lowest ones.

R

R Mod : 4372 + 4540 ATR 42 Model : 500

TAKE--OFF SPEEDS VALUES

TAKE-OFF

P 2

APR 08

200

3.03.05

NON LIMITING RUNWAY TAKE-OFF SPEEDS

When a runway has been determined NL, the following speeds may be used associatedto the actual TOW.

NEVER EXCEED THE CERTIFIED STRUCTURAL MTOW.

NORMAL CONDITIONS

WEIGHT SPEEDS (KT IAS)

KG (LB) V1 = VR * V2

18600 (41005) 110 115

18000 (39700) 108 113

17500 (38590) 106 112

17000 (37485)105 112

( )

and below105 112

ICING CONDITIONS

WEIGHT SPEEDS (KT IAS)

KG (LB) V1 = VR V2

18600 (41005) 118 122

18000 (39700) 115 120

17500 (38590) 114 118

17000 (37485) 112 116

16500 (36380) 110 115

16000 (35270) 109 113

15000 (33070)105 112

( )

and below105 112

* Because of a longer time between VR and VLOF due to water or slush runwaycontamination increase VR by :

F 1 kt between 6.3 mm (1/4 inch) and 12.7 mm (1/2 inch) in normalconditions only.

F no correction below 6.3 mm (1/4 inch).

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INTRODUCTION

CLIMB

P 1

DEC 09

001

3.04.01

Climb charts are established for two indicated speeds (160 kt, 190 kt) and forstandard temperature (ISA) at Climb Power with Air conditioning in normal mode.Corrections are given to take into account the temperature effect.

When using air conditioning in high mode, increase fuel consumption by 6.5 % (160 kt)or 8.5 % (190 kt).

All charts are established with a center of gravity location corresponding to 25%.

OPERATIONAL CEILING

The operational ceiling is the maximum altitude which can be reached with a minimumrate of climb of 300 ft/mn (see 3.04.02 p 1). This is the recommended cruise altitude tominimize the fuel consumption.

CLIMB IN ICING CONDITIONS

Atmospheric icing conditions exist when TAT in flight is at or below 7°C and visiblemoisture in any form is present (clouds, fog with visibility of less than one mile, rain,snow, sleet and ice crystals).

Climb charts in icing conditions are established for 160 kt at climb Power with Airconditioning in normal mode.

Performance are computed taking into account a degradation of aircraftaerodynamic at altitudes where icing conditions may be encountered.That is why tables are given for different temperatures (ISA--20, ISA--10, ISA,ISA + 10, ISA + 20).

The icing operational ceiling is computed for a minimum rate of climb of 100 ft/mn andcan be read directly on the tables (3.04.04 pages 1 to 10) just below a blank division.

The maximum operational ceiling (twin engine) which is accessible when flying atVMLBO = 1.45 VSR is given in 3.04.04 p.11.

Since computed with a lower residual rate of climb in icing conditions than in normalconditions, the operational ceiling may sometimes be greater in icing conditions. IN THISCASE DO NOT EXCEED THE CEILING COMPUTED FOR NORMAL CONDITIONS.

Note : All performance data given for ICING CONDITIONS derive from flight testsmeasurements performed with ICE SHAPES representative of the worst icingcases considered by certification and applicable losses of propeller efficiency.Because of the variability of REAL ICING, climb performance published for icingconditions MUST BE regarded as operational information only.

AA

RR

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

Mod : 4372 + 4540 ATR 42 Model : 500

ICING CONDITIONS

CLIMB

P 11

APR 08

200

3.04.04

MAXIMUM OPERATIONAL CEILING (Twin engine)ICING CONDITIONS -- FLAPS 0-- VMLB0 = 1.45 VSRMINIMUM RATE = 100 FT/MN

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INTRODUCTION

CRUISE

P 1

APR 08

100

3.05.01

Cruise charts are established from FL 60 to FL 250 for different ISA conditions with airconditioning in normal mode.

As soon as flight level is reached, select PWR MGT on CRZ position.

When using air conditioning in high mode increase fuel consumption by 3 % andsubtract 5 kt on True Airspeed.

All charts are established with a center of gravity location corresponding to 25 %.

Max cruise tables are given with NP = 82 %.

CRUISE IN ICING CONDITIONS


Tables are established only for the altitudes where icing conditions may be encounteredand for different temperatures (ISA -- 20, ISA -- 10, ISA, ISA + 10, ISA + 20).Note : All performance data given for ICING CONDITIONS derive from flight tests

measurements performed with ICE SHAPES representative of the worst icingcases considered by certification and applicable losses of propeller efficiency.Because of the variability of REAL ICING, cruise performance published for icingconditions MUST BE regarded as operational information only.

AA

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

Mod : 4601 or (4372 + 4540) ATR 42 Model : 500

INTRODUCTION

HOLDING

P 1

APR 08

100

3.06.01

Holding charts are established :

-- in clean configuration-- with air conditioning in normal mode.-- with NP = 82 % propeller speed-- at VmHBO of icing conditions.

This minimum manoeuvring speed covers the whole flight envelope in normalconditions and in icing conditions without appreciable increasing of consumption.

When using air conditioning in high mode, fuel consumption is increased by 3 %.

All charts are established with a center of gravity location corresponding to 25 %.

The temperature effect is negligible.

ICING CONDITIONS


AA

APR 08

15R

FCOATO--03.06.02.002.200

APR 08

APR 08

FCOATO--03.06.03.002.200

APR 08

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APPROACH CLIMB LIMITING WEIGHT

APPROACH - LANDING

P 4

APR 08

300

3.08.01

AA

R Mod : 1112 + 4372 + (4450 or 4580) + 4540 ATR 42 Model : 500

APPROACH CLIMB LIMITING WEIGHT

APPROACH - LANDING

P 4A

APR 08

410

3.08.01

CAT II - ICING CONDITIONS

In icing conditions, decrease the approach climb gradient limiting weight determined onparagraph 3.08.01 p 2A or 3A by the following values.

FLAPS 25 - V = 1.29 VSR

WEIGHT KG / LB CORRECTION KG / LB

21 000 / 46 300 -- 350 / -- 775

19 000 / 41 900 -- 250 / -- 550

17 000 / 37 480 -- 200 / -- 440

15 000 / 33 070 -- 150 / -- 330

and below

FLAPS 15 - V = 1.29 VSR

WEIGHT KG / LB CORRECTION KG / LB

21 000 / 46 300 -- 950 / -- 2 095

19 000 / 41 900 -- 750 / -- 1 655

17 000 / 37 500 -- 500 / -- 1 100

15 000 / 33 100 -- 250 / -- 550

14 000 / 30 865 -- 150 / -- 330

and below

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Mod : (4450 or 4580) + (4372 + 4540) ATR 42 Model : 500

LANDING DISTANCES

APPROACH - LANDING

P 2A

APR 08

210

3.08.03

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FLIGHT PREPARATION

ONE ENGINE INOPERATIVE

P 3

OCT 08

001

3.09.02

NET CEILING

Considering the atmospheric conditions of the day, read your net ceiling on one of thetwo following graphs :

� NORMAL CONDITIONS - FLAPS 0

12 13 14 15 16 17 18 19

6

8

10

12

14

16

18

20

22

24

OAT = -- 40oC

OAT = -- 30oC

OAT = -- 20oC

OAT = -- 10oC

OAT = 0oC

OAT = + 10oC

OAT = + 20oC

OAT = + 30oC

ISA + 10

ISA + 20

ISA + 30

ISA + 40

Zp(

nc)(1

000

FT)

ISA -- 10 ISA -- 20ISA

AIR CONDITIONING ON

AIR CONDITIONING OFF

FCOM42--500--3--09--02--002--001

TO USE THIS GRAPH, REFER TO THE

EXAMPLE GIVEN IN PAGE 4

ISA (oC) in DASHED LINE

OAT (oC) in CONTINUOUS LINE

WEIGHT (x 1000 KG)

Examples :

Weight = 15000 kg ; ISA + 20 ⇒ Net Ceiling : Zp(nc) = 16600 ft

Weight = 16500 kg ; OAT = 30°C ⇒ Net Ceiling : Zp(nc) = 18100 ft

1

2

Mod : 4372 + 4540 ATR 42 Model : 500

FLIGHT PREPARATION


P 4

APR 08

200

3.09.02

D NET CEILING IN ICING CONDITIONS - FLAPS 15

12 13 14 15 16 17 186

8

10

12

14

16

18

20

22

24

OAT = -- 40oC

OAT = -- 30oC

OAT = -- 20oC

OAT = -- 10oC

OAT = 0oC

OAT = + 15oC

OAT = + 25oC

OAT = + 5oCAIR CONDITIONING ON

AIR CONDITIONING OFF

ISA -- 10 ISA -- 20

ISA

Zp(ic)(1000FT)

ISA + 10

ISA + 20

ISA + 30

ISA + 40

FCOM42--500--3--09--02--003--200

Zp(OAT 5)

TO USE THIS GRAPH, REFER TO THEEXAMPLE GIVEN IN PAGE 4

ISA (oC) in DASHED LINEOAT (oC) in CONTINUOUS LINE

WEIGHT (x 1000 KG)

Examples :Weight = 16500 kg ; OAT = -- 30°C⇒ Net Ceiling : Zp(ic) = 16800 ftWeight = 16500 kg ; ISA + 20°C⇒ The corresponding OAT is greater than 5°C, sorefer to the Normal Conditions graph (page 2). For 16500 kg and ISA + 20°C, the NetCeiling is : Zp(nc) = 13600 ft.

Transition altitude from Icing to Normal Conditions for ISA + 20°C (intersection betweenISA + 20°C line and OAT = 5°C line) : Zp(OAT 5) = 15200 ft.

AA

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ATR 42 Model : 500

FLIGHT PREPARATION


P 6

APR 08

001

3.09.02

DOWN HILL RULE - NORMAL CONDITIONS - FLAPS 0

Examples :Height above ceiling = 5000 ftNo windDistance to reach the ceiling = 220 -- 55 = 165 Nm

Height above ceiling = 8000 ftWind = -- 80 kt (headwind)Distance to reach the ceiling = 120 -- 20 = 100 Nm.

AA

ATR 42 Model : 500

FLIGHT PREPARATION


P 7

APR 08

001

3.09.02

DOWN HILL RULE - ICING CONDITIONS - FLAPS 15

Examples :Height above ceiling = 5500 ftNo windDistance to reach the ceiling = 220 -- 65 = 155 Nm

Height above ceiling = 4500 ftWind = 80 kt (tailwind)Distance to reach the ceiling = 330 -- 110 = 220 Nm

AA

P 8

P 8

APR 08

APR 08

P 9

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APR 08

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APR 08

APR 08

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APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

ATR 42 Model : 500

IN FLIGHT


ICING 200 KT IAS DESCENT P 3

APR 08

001

3.09.17

DESCENT 1 ENGINE

200KT(IAS) THEN VZ = 500 FT/MNAIR COND FLOW NORM1 ENGINE AT MCT (NP=100%) ICING CONDITIONSFLAPS 0 ISA + 10

WEIGHT (1000KG)

FL 12 13 14 15 16 17 18 18.5

25024 175 24 180 25 183 25 184 25 185 25 185 25 184 25 184

250 100 65 103 65 106 65 107 65 107 65 107 65 107 65 107 65

23022 168 23 172 23 175 23 176 24 176 24 176 23 176 23 175

230 94 69 97 69 99 69 99 69 100 69 100 69 99 69 99 69

21021 160 21 163 22 166 22 166 22 166 22 166 22 165 22 165

210 87 72 89 72 91 72 91 72 92 72 91 72 91 72 91 72

19019 149 20 152 20 154 20 154 20 154 20 154 20 153 20 153

190 79 76 81 76 82 76 83 76 83 76 82 76 82 76 82 76

17017 136 17 138 18 140 18 140 18 140 18 139 17 138 17 138

170 71 80 72 80 73 80 73 80 73 80 72 80 72 80 72 80

15015 120 15 121 15 122 15 122 15 122 15 121 15 120 15 120

150 61 85 61 85 62 85 62 85 62 85 61 85 61 85 61 85

13012 98 12 98 12 99 12 99 12 98 12 98 12 98 12 97

130 48 90 48 90 49 90 49 90 48 90 48 90 48 90 48 90

1108 68 8 68 8 68 8 68 8 68 8 68 8 68 8 68

110 33 95 33 95 33 95 33 95 33 95 33 95 32 95 32 95

904 34 4 34 4 34 4 34 4 34 4 34 4 34 4 34

90 16 100 16 100 16 100 16 100 16 100 16 100 16 100 16 100

802 17 2 17 2 17 2 17 2 17 2 17 2 17 2 17

80 8 100 8 100 8 100 8 100 8 100 8 100 8 100 8 100

700 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0

70 0 100 0 100 0 100 0 100 0 100 0 100 0 100 0 100

FROM START OF DESCENT TIME FUEL(MIN) (KG)

FROM START OF DESCENT DIST TORQUE(NM) (%)

AA

ATR 42 Model : 500

IN FLIGHT


ICING 200 KT IAS DESCENT P 4

APR 08

001

3.09.17

DESCENT 1 ENGINE

200KT(IAS) THEN VZ = 500 FT/MNAIR COND FLOW NORM1 ENGINE AT MCT (NP=100%) ICING CONDITIONSFLAPS 0 ISA + 20

WEIGHT (1000KG)

FL 12 13 14 15 16 17 18 18.5

25023 164 24 168 24 172 25 173 25 174 25 175 25 175 25 175

250 99 61 102 61 104 61 106 61 106 61 107 61 107 61 107 61

23022 158 22 161 23 164 23 166 23 166 23 167 23 167 23 167

230 93 64 95 64 98 64 99 64 99 64 99 64 99 64 99 64

21020 150 21 153 21 156 22 157 22 158 22 158 22 157 22 157

210 86 68 88 68 90 68 91 68 91 68 91 68 91 68 91 68

19019 141 19 144 20 146 20 147 20 147 20 147 20 146 20 146

190 79 72 81 72 82 72 83 72 83 72 83 72 82 72 82 72

17017 130 17 132 18 134 18 134 18 134 18 134 18 133 18 133

170 71 76 72 76 73 76 74 76 74 76 73 76 73 76 73 76

15015 116 15 117 15 118 15 118 15 118 15 118 15 117 15 117

150 62 80 63 80 63 80 63 80 63 80 63 80 62 80 62 80

13012 94 12 94 12 94 12 94 12 94 12 94 12 94 12 94

130 48 84 49 84 49 84 49 84 49 84 49 84 48 84 48 84

1108 64 8 64 8 64 8 64 8 64 8 64 8 64 8 64

110 32 88 32 88 32 88 32 88 32 88 32 88 32 88 32 88

904 33 4 33 4 33 4 33 4 33 4 33 4 33 4 33

90 16 92 16 92 16 92 16 92 16 92 16 92 16 92 16 92

802 17 2 17 2 17 2 17 2 17 2 17 2 17 2 17

80 8 94 8 94 8 94 8 94 8 94 8 94 8 94 8 94

700 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0

70 0 95 0 96 0 96 0 96 0 96 0 96 0 95 0 95FROM START OF DESCENT TIME FUEL

(MIN) (KG)FROM START OF DESCENT DIST TORQUE

(NM) (%)

AA

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

APR 08

Mod. : 4372 + 4540 ATR 42 Model : 500

IN FLIGHT


NORMAL HOLDING 1 ENGINE P 1

APR 08

200

3.09.30

HOLDING 1 ENGINEVMHB0 ICINGISAFLAPS 0AIR COND FLOW: NORMANTI/DE ICING: OFF MCT (NP=100%)

WEIGHT FLIGHT LEVELWEIGHT(1000KG) 20 40 60 80 120

42.6 43.1 43.7 44.6 46.4

12 042.6319132

43.1310132

43.7301132

44.6293132

46.428213312.0 132 132 132 132 133

46.9 47.7 48.6 49.5 51.4

13 046.9336138

47.7327138

48.6318138

49.5311138

51.430213813.0 138 138 138 138 138

51.5 52.5 53.5 54.5 56.4

14 051.5352143

52.5344143

53.5336143

54.5331143

56.432214314.0 143 143 143 143 143

56.4 57.5 58.5 59.5 62.0

15 056.4370148

57.5361148

58.5356148

59.5351148

62.034414815.0 148 148 148 148 148

61.4 62.5 63.5 64.7 67.6

16 061.4387153

62.5381153

63.5376153

64.7372153

67.636615316.0 153 153 153 153 153

66.4 67.5 68.7 70.2 73.7

17 066.4407158

67.5401158

68.7397158

70.2394158

73.738915817.0 158 158 158 158 158

69.0 70.0 71.5 73.1 77.0

17 569.0417160

70.0412160

71.5408160

73.1405160

77.040216017.5 160 160 160 160 160

71.4 72.7 74.3 75.9 80.2

18 071.4427162

72.7423162

74.3419162

75.9416162

80.241616218.0 162 162 162 162 162

74.4 76.0 77.7 79.4 84.2

18 674.4439165

76.0436165

77.7433165

79.4430165

84.243216518.6 165 165 165 165 165

TQKG/H/ENG

IAS

AA

Mod. : 4372 + 4540 ATR 42 Model : 500

IN FLIGHT


NORMAL HOLDING 1 ENGINE P 2

APR 08

200

3.09.30

HOLDING 1 ENGINEVMHB0 ICINGISAFLAPS 0AIR COND FLOW: NORMANTI/DE ICING: OFF MCT (NP=100%)


47.2 47.6 48.0 49.1 50.3

12 047.2278133

47.6276133

48.0274133

49.1271133

50.326813312.0 133 133 133 133 133

52.2 52.8 53.4 54.7 56.2

13 052.2298138

52.8296138

53.4295138

54.7292138

56.229113813.0 138 138 138 138 138

57.7 58.4 59.1 60.7 62.8

14 057.7319144

58.4318144

59.1317144

60.7316144

62.832014414.0 144 144 144 144 144

63.4 64.2 65.1 67.3 69.6

15 063.4341149

64.2340149

65.1340149

67.3344149

69.635114915.0 149 149 149 149 149

69.5 70.6 71.7 74.1

16 069.5364154

70.6366154

71.7368154

74.137515416.0 154 154 154 154

76.0 77.3 78.5

17 076.0391158

77.3394158

78.539815817.0 158 158 158

79.4 80.7 82.0

17 579.4406161

80.7410161

82.041516117.5 161 161 161

82.8 84.2

18 082.8421163

84.242716318.0 163 163

87.0

18 687.044116618.6 166

TQKG/H/ENG

IAS

AA

Mod. : 4372 + 4540 ATR 42 Model : 500

IN FLIGHT


ICING HOLDING 1 ENGINE P 1

APR 08

200

3.09.35

HOLDING 1 ENGINEVMHB0 ICINGISAFLAPS 0AIR COND FLOW: NORMANTI/DE ICING: ON MCT (NP=100%)


42.6 43.1 48.2 49.1 50.9

12 042.6319132

43.1310132

48.2316132

49.1309132

50.929913312.0 132 132 132 132 133

46.9 47.7 53.4 54.4 56.6

13 046.9336138

47.7327138

53.4336138

54.4330138

56.632213813.0 138 138 138 138 138

51.5 52.5 58.8 59.9 62.4

14 051.5352143

52.5344143

58.8356143

59.9351143

62.434514314.0 143 143 143 143 143

56.4 57.5 64.3 65.7 68.5

15 056.4370148

57.5361148

64.3378148

65.7375148

68.536914815.0 148 148 148 148 148

61.4 62.5 70.1 71.6 75.1

16 061.4387153

62.5381153

70.1402153

71.6398153

75.139515316.0 153 153 153 153 153

66.4 67.5 76.0 77.6 82.2

17 066.4407158

67.5401158

76.0425158

77.6423158

82.242415817.0 158 158 158 158 158

69.0 70.0 79.1 80.8 86.0

17 569.0417160

70.0412160

79.1437160

80.8435160

86.044116017.5 160 160 160 160 160

71.4 72.7 82.1 84.1 89.7

18 071.4427162

72.7423162

82.1450162

84.1448162

89.745716218.0 162 162 162 162 162

74.4439

76.0436

85.9465

88.4465

18 6439165

436165

465165

46516518.6 165 165 165 165

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Mod. : 4372 + 4540 ATR 42 Model : 500

IN FLIGHT


ICING HOLDING 1 ENGINE P 2

APR 08

200

3.09.35

HOLDING 1 ENGINEVMHB0 ICINGISAFLAPS 0AIR COND FLOW: NORMANTI/DE ICING: ON MCT (NP=100%)


51.9 52.5 53.1 54.3 55.6

12 051.9296133

52.5294133

53.1293133

54.3291133

55.629013312.0 133 133 133 133 133

57.8 58.4 59.1 60.6 62.8

13 057.8319138

58.4318138

59.1316138

60.6316138

62.832013813.0 138 138 138 138 138

63.8 64.6 65.5 67.8 70.2

14 063.8343144

64.6341144

65.5342144

67.8346144

70.235514414.0 144 144 144 144 144

70.3 71.5 72.8 75.3

15 070.3369149

71.5370149

72.8373149

75.338114915.0 149 149 149 149

77.6 78.9 80.2

16 077.6399154

78.9402154

80.240715416.0 154 154 154

85.0

17 085.043215817.0 158

17 517.5

18 018.0

18 618.6TQ

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AA

ATR 42 Model : 400/500

CONTENTS


P 1

DEC 07

001

3.11.00

3.11.00 CONTENTS

3.11.01 FLIGHT WITH LANDING GEAR DOWN

3.11.02 DISPATCH WITH FLAPS RETRACTED

3.11.03 DISPATCH WITH ANTI SKID INOPERATIVE

3.11.04 DISPATCH WITH AUTOFEATHER SYSTEM INOPERATIVE

3.11.05 DISPATCH WITH EEC OFF

3.11.06 DISPATCH WITH ONE AFU INOPERATIVE

3.11.07 DISPATCH WITH ONE TQ INDICATOR INOPERATIVE

3.11.08 DISPATCH WITH ATPCS OFF

3.11.09 ETOPS

3.11.10 OPERATIONS ON NARROW RUNWAYS

3.11.11 DRY UNPAVED RUNWAYS

3.11.12 DISPATCH WITH ONE ACW GENERATOR CHANNEL INOPERATIVE

3.11.13 DISPATCH WITH SPOILERS CONTROL SYSTEM INOPERATIVE

3.11.14 DISPATCH WITH ONE WEEL BRAKE DEACTIVATED

3.11.15 FERRY FLIGHT WITH PITCH ELEVATORS DISCONNECTED

3.11.16 HIGH LATITUDES OPERATIONS

3.11.17 STEEP SLOPE APPROACH

3.11.18 RUNWAYS SLOPE BEYOND 2%

3.11.19 OPERATIONS IN CIS COUNTRIES

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FLIGHT WITH LANDING GEAR DOWN

SPECIAL OPERATIONS

P 1

APR 08

001

3.11.01

GENERAL

Extended overwater flight is not allowed. It is necessary to take into account theincreased drag to determine the take--off weight and fuel consumption.

FLIGHT IN ICING CONDITIONS IS PROHIBITED WITH GEAR DOWN

The propeller speed used is 82 %.

Refer to the MMEL for the operating procedures.

DETERMINATION OF MAX TAKE OFF WEIGHT

Penalties on performance affect the WAT ; Enter in the quick reference tables withWeight reduction 15 %.

APPROACH CLIMB PERFORMANCE

Decrease the basic limiting weight by 11 %.

FLIGHT PLANNING

Climb

Climb at VmHB0 icing (1.5 VSR) with both engines at maximum climb power setting. Thetables in 3.11.01 p 2 to 5 give the time, distance and fuel consumption according totake--off weight.

CruiseThe maximum recommended altitude is 16000 ft.The maximum cruise speed is 165 kt.

Pages 3.11.01 p 6 to 9 give cruise tables at this maximum speed.Obviously, the ceiling on one engine may be a limiting factor, and the choice of the routeshould reflect this concern.

Engine failure

The weight penalty on single engine ceiling computation is 15 %, consequentlydecrease the single engine ceiling by :

ACTUAL WEIGHT KG (lb) ISA -- 10 ISA ISA + 10 ISA + 20

18 600 (41005) -- 22 % -- 23 % -- 27 % -- 31 %

17 500 (38580) -- 18 % -- 20 % -- 22 % -- 24 %

16 500 (36375) and below -- 17 % -- 19 % -- 21 % -- 22 %

Holding

Page 3.11.01 p. 10 gives the holding parameters.

AA

R Mod : 4372 + 4540 ATR 42 Model : 500

FLIGHT WITH LANDING GEAR DOWN

SPECIAL OPERATIONS

P 2

APR 08

200

3.11.01

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CHANNEL INOPERATIVE

SPECIAL OPERATIONS

DISPATCH WITH ONE ACW GENERATOR P 1

DEC 07

001

3.11.12

D Refer to AFM 7_02.01

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SYSTEM INOPERATIVE

SPECIAL OPERATIONS

DISPATCH WITH SPOILERS CONTROL P 1

DEC 07

001

3.11.13


AA

DEACTIVATED OR REMOVED

SPECIAL OPERATIONS

DISPATCH WITH ONE WEEL BRAKE P 1

DEC 07

001

3.11.14


AA

DISCONNECTED

SPECIAL OPERATIONS

FERRY FLIGHT WITH PITCH ELEVATORS P 1

DEC 07

001

3.11.15


AA

HIGH LATITUDES OPERATIONS

SPECIAL OPERATIONS

P 1

DEC 07

001

3.11.16


AA

STEEP SLOPE APPROACH

SPECIAL OPERATIONS

P 1

DEC 07

001

3.11.17


AA

RUNWAYS SLOPE BEYOND 2%

SPECIAL OPERATIONS

P 1

DEC 07

001

3.11.18


AA

OPERATIONS IN CIS COUNTRIES

SPECIAL OPERATIONS

P 1

DEC 07

001

3.11.19

D Refer to AFM 7_09

AA

ATR 42 Model : 400/500

CONTENTS

OPERATIONS ENGINEERING BULLETINS

P 1

DEC 05

001

3.12.00

3.12.00 C0NTENTS

3.12.10 GENERAL DESCRIPTION

3.12.20 LIST OF O.E.B.

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ATR 42 Model : 400/500

GENERAL DESCRIPTION


P 1

DEC 05

001

3.12.10

Operations Engineering Bulletins, OEB, are issued by ATR, under supervision of FlightTest Department, as the need arises to transmit in advance technical or proceduralinformation before technical solutions is developped and implemented.ALL OEB aredistributed to ALL FCOM holders.Information in OEB is responsibility of ATR in the samemanner as the whole FCOM, andmay not be approved by AirworthinessAuthorities at thetime of release.In case of conflict with the certified Flight Manual, the latter willsupersede.When an operator implements amodification cancelling anOEB, thisoperatormay not take into account this OEB anymore for the concerned aircraft.

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LIST OF EFFECTIVE O.E.B.


P 1

DEC 07

001

3.12.20

O.E.B.No/ISSUE DATE SUBJECT VALIDITY

01/01 21 SEP95

(on ground) propeller brakeand engine shut off procedure

CANCELLED by Mod 4506

02/01 DEC 95 ICE SHED selection on PWRMGT rotactor

ATR 42--400 487 and 491CANCELLED by mod 4489

03/01 JUN 97 GNSS HT 1000 operation CANCELLED by mod 4885

04/01 OCT 97 VHF INTERFERENCESON GNSS HT 1000

CANCELLED by mod 4885

05/01 DEC 98 KLN 90B GPS operation All aircraft fitted withmod 4890 or 5022

07/01 MAR 05 PEC OFF Operations Pending Modification 4883application(or SB ATR42--73--0007)

08/01 MAR 05 STATIC INVERTER DOUBLELOSS

Pending Modification 5544application

09/01 JAN 07 COCKPIT VOICERECORDER

All aircraft fitted withmod 5736

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Eng : PW127E ATR42 Model : 500

O.E.B. N° 7 DESCRIPTION


P 1

DEC 05

001

3.12.27

Issued byDO/TV

SUBJECT : PEC OFF operations

1. REASON FOR ISSUE

In thePECOFF condition, if the NPbecomes inferior to 77%at idle power, the engineeventually will not spool up when advancing the power lever.

2. BACKGROUND

Np < 77% at idle power is never reached at normal operating speeds, therefore thisproblem could only be met in training flights during stall exercices or touch and gomaneuvers.

3. ATR ACTION

Implementation of modification 4883 or SB ATR42--73--0007 cancels this OEB.

4. PROCEDURES

-- Flight at airspeeds inferior to 90kt is prohibited in the PEC OFF condition

-- Training : In the PEC OFF condition touch and go and stall maneuvers areprohibited.

Validity : For model 42--500

AA

ATR 42 Model : 400/500



P 1

DEC 05

001

3.12.28

Issued byDO/TV

SUBJECT : STATIC INVERTER DOUBLE LOSS

1 - Reason for issue

Warning to crew before modification application.

2 - Applicability

All aircraft not fitted with modification 5544.

3 - Background information

In flight it is difficult to identify which bus is in short--circuit.Considering also the particular pilot workload following system failure and thatseveral circuit breakers must be opened for the faulty unit isolation.

4 - ATR action

A modification is already defined and must be applied for OEB cancellation.

5 - Procedures

Note : ATR recommend application of SB ATR42--24--0055 (mod 5546) whichfacilitates identification of involved C/B by means of orange caps.

STATIC INVERTER DOUBLE LOSS

BTC ISOL (light ON). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C/B 3XA INV1 127VU position AB3 RESET. . . . . . . . . . . .C/B 10XA INV2 124VU position AB4 RESET. . . . . . . . . . . .KEEP FLYING WITH BTC ISOL (light ON). . . . . . . . . . . . . . . . . . . . . . . . . . .If no static inverter recoveredC/B 3XD 26VAC STBY BUS 122VU position Q39 OFF. . . . . . . . . . .C/B 4XD 115VAC STBY BUS 122VU position Q40 OFF. . . . . . . . . . .C/B 3XA INV1 127VU position AB3 RESET. . . . . . . . .C/B 10XA INV2 124VU position AB4 RESET. . . . . . . . .BTC ON (ISOL light OFF). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Validity : pending application of modification 5544 or SB ATR42--24--0056

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Mod : 5736 ATR 42 Model : 500



P 1

DEC 07

001

3.12.29

Issued byDO/TV

SUBJECT : COCKPIT VOICE RECORDER

1 - Reason for issue

In some phases, the voices recorded in the cockpit by the area microphone are lackingclearness.

2 - ATR action

An improvement in the cockpit area microphone has been requested to the manufacturer,and is expected not later than 2008.

3 - Procedures

In the meanwhile boomsets should be used by the crew on ground and in flight below FL100.

Validity : All aircraft fitted with Mod 5736

AA

Documents

FCOM ATR42-500