ATR 72-500 QRH

0.0172

GENERALOCT 08 001

TABLE OF CONTENTS

0 GENERAL

1 EMERGENCY PROCEDURES

2 PROCEDURES FOLLOWING FAILURES

3 NORMAL PROCEDURES

4 OPS DATA

5 MANAGEMENT PAGES

6 NORMAL CHECK LIST

COMMENTS ON PARTS 1 AND 2

LAYOUT

RThe boxed items correspond to actions performed by memory by thecrew within a minimum period of time

: highlights a precondition to apply an action

: highlights the moment when an action is to be applied

PROCEDURES INITIATION

No action will be taken (apart from depressing MC/MW pushbutton) :

RR

- until flight path is stabilized- under 400 ft above runway, except propeller feathering after enginefailure during approach at reduced power if go around is considered

RRR

At flight crew discretion, one reset of a system failure associated withan amber caution (except PEC SGL CH) may be performed byselecting OFF then ON related pushbutton.

Flight Crew may reengage a tripped circuit breaker only if he/shejudges it necessary for a safe continuation of the flight. In this caseonly one reengagement should be attempted.

If the failure alert disappears, continue normal operation and recordthe event in the maintenance log. If not, apply the associated failureprocedure.

Before performing a procedure, the crew must assess the situation asa whole, taking into consideration the failures, when fully identified,and the flight constraints imposed.

TASK SHARING

For all procedures, the general task sharing stated below isapplicable. The pilot flying remains pilot flying throughout theprocedure.

PF, Pilot Flying, responsible for :- PL- flight path and airspeed control- aircraft configuration- navigation

PNF, Pilot Non Flying, responsiblefor :

- Check List reading- execution of required actions- actions on OVHD panel- CL- communications

The AFCS is always coupled to the PF side (CPL selection)

ANALYSIS OF CONSEQUENCES OF A FAILURE ON FLIGHT

Basic airmanship calls for a management review of the remainingaircraft capabilities under the responsibility of CM1.

1.01

72

EMERGENCY NOV 11 001

1 - EMERGENCY PROCEDURES Content 1/1 IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE ………... 1.02 ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE ……. 1.02 ON GROUND EMER EVACUATION ……………………………………… 1.02

R ENG FIRE AT TAKE OFF …………………………………………….. 1.02A BOTH ENGINES FLAME OUT …………………………………………….. 1.03 ENG FLAME OUT AT TAKE OFF …………………………………………. 1.04

BOMB ON BOARD ………………………………………………………….. 1.04 COCKPIT DOOR SECURITY SYSTEM ………………………………….. 1.04A SMOKE ………………………………………………………………………. 1.05 ELECTRICAL SMOKE………………………………………………………. 1.05A AIR COND SMOKE …………………………………………………………. 1.05A FWD SMOKE……………………...………………………………………. 1.06 AFT SMOKE………………………………………………………………….. 1.06 AUX AFT COMPT SMOKE………………………………………………….. 1.06 DUAL DC GEN LOSS ………………………………………………………. 1.07 EMERGENCY DESCENT ………………………………………………….. 1.07A DITCHING ……………………………………………………………………. 1.08 FORCED LANDING …………………………………………………………. 1.08A SEVERE ICING ……………………………………………………………… 1.09 RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL………. 1.10

R

UNRELIABLE AIRSPEED INDICATION………. 1.11

1.02

72

EMERGENCY JUN 12 500

IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE

PL affected side .................................................................................. FI CL affected side .................................................. FTR THEN FUEL SO FIRE HANDLE affected side..........................................................PULL � If condition persist after 10 seconds AGENT 1 affected side .......................................................... DISCH � If condition persist after 30 seconds AGENT 2 affected side .......................................................... DISCH LAND ASAP SINGLE ENG OPERATION procedure (2.04)............................APPLY

ON GROUND ENG FIRE

OR SEVERE MECHANICAL DAMAGE

PL 1 + 2............................................................GI / REVERSE AS RQD � When aircraft stopped PARKING BRAKE ............................................................. ENGAGE CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLE affected side.....................................................PULL � If condition persist AGENT 1 affected side ...................................................... DISCH � If condition persist after 30 seconds ......................................... AGENT 2 affected side ...................................................... DISCH � If evacuation required ON GROUND EMER EVACUATION procedure (1.02)....APPLY

ON GROUND EMER EVACUATION

AIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGE AUTO PRESS.............................................................................. DUMP ATC (VHF 1 / HF) ..................................................................... NOTIFY CL 1 + 2 ............................................................... FTR THEN FUEL SO MIN CAB LIGHT ............................................................................... ON CABIN CREW (PA)................................................................... NOTIFY FIRE HANDLES 1 + 2....................................................................PULL AGENTS ...................................................................................AS RQD ENG START ROTARY SELECTOR................... OFF / START ABORT FUEL PUMPS 1 + 2........................................................................ OFF EVACUATION (PA) .................................................................INITIATE � Before leaving aircraft BAT ............................................................................................ OFF

Model : 212A

1.02A

72


ENG FIRE AT TAKE OFF

Note: Captain may decide to shut down affected engine before reaching acceleration altitude, but not before 400ft AGL. �� When airborne LDG GEAR ...................................................................................UP � At Acceleration Altitude PWR MGT..................................................................................MCT � At VFTO � If normal condition FLAPS......................................................................................... 0° � If icing condition FLAPS.....................................................................MAINTAIN 15° PL affected side............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO FIRE HANDLE illuminated…………………………….. .............PULL

� If fire persist after 10 seconds AGENT 1 affected side ...................................................... DISCH � If fire persist after 30 seconds AGENT 2 affected side....................................................... DISCH BLEED engine alive............................................... OFF if necessary

LAND ASAP SINGLE ENG OPERATION procedure (2.04) ...........................APPLY

Model : 212A

1.03

72

EMERGENCY OCT 09 100

BOTH ENGINES FLAME OUT

R

PL 1 + 2............................................................................................... FI � If NH drops below 30 % (no automatic relight) CL 1 + 2 .......................................................... FTR THEN FUEL SO FUEL SUPPLY .....................................................................CHECK OPTIMUM SPEED.................................................................. VmHB CAPT EHSI................................................................................ OFF COMMUNICATIONS .............................................................. VHF 1 ENG START ROTARY SELECTOR............................START A & B

ENG 2 RELIGHT ENG 2 START PB .................................................................. ON � When NH above 10% CL 2 ..................................................................................FTR ENG 2 RELIGHT ....................................................MONITOR CL 2 then PL 2...........................................................AS RQD


� If neither engine starts CL 1 + 2 .......................................................... FTR THEN FUEL SO ENG START ROTARY SELECTOR.............. OFF / START ABORT FUEL PUMPS 1 + 2................................................................... OFF FORCED LANDING (1.08A) or DITCHING (1.08) procedure ........... ...............................................................................................APPLY

CAUTION: Do not select AVIONICS VENT EXHAUST MODE to OVBD

� If engine(s) recovered CL / PL engine(s) recovered................................................AS RQD � If one engine not recovered CL engine NON recovered ........................ FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)..................APPLY

SYSTEMS affected.......................................................... RESTORE

Mod : 3973 or 4371 or 4457

1.03

72


BOTH ENGINES FLAME OUT

R

PL 1 + 2............................................................................................... FI � If NH drops below 30 % (no automatic relight) CL 1 + 2 .......................................................... FTR THEN FUEL SO FUEL SUPPLY .....................................................................CHECK OPTIMUM SPEED.................................................................. VmHB CAPT EHSI................................................................................ OFF COMMUNICATIONS .............................................................. VHF 1 ENG START ROTARY SELECTOR............................START A & B



� If neither engine starts CL 1 + 2 .......................................................... FTR THEN FUEL SO ENG START ROTARY SELECTOR.............. OFF / START ABORT FUEL PUMPS 1 + 2................................................................... OFF FORCED LANDING (1.08A) or DITCHING (1.08) procedure ........... ...............................................................................................APPLY

CAUTION: Do not select AVIONICS VENT EXHAUST MODE to OVBD

� If engine(s) recovered CL / PL engine(s) recovered................................................AS RQD � If one engine not recovered CL engine NON recovered ........................ FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)..................APPLY

SYSTEMS affected.......................................................... RESTORE

Mod : 3973 or 4371 or 4457

1.04

72


ENG FLAME OUT AT TAKE OFF

UPTRIM .....................................................................................CHECK AUTOFEATHER ........................................................................CHECK � If no UPTRIM PL 1 + 2 ................................................. ADVANCE TO THE RAMP � When airborne LDG GEAR ....................................................................................UP BLEED 1 + 2 .................................................... OFF, IF NOT FAULT

� At Acceleration Altitude ALT .............................................................................................SET

� At VFTO PL 1 + 2 ................................................................... IN THE NOTCH PWR MGT .................................................................................MCT IAS ..............................................................................................SET � If normal condition FLAPS ........................................................................................ 0° � If icing condition FLAPS ....................................................................MAINTAIN 15°

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 LAND ASAP SINGLE ENG OPERATION procedure (2.04).......................APPLY � If no damage suspected ENG RESTART IN FLIGHT procedure (2.08) .......................APPLY � If unsuccessful LAND ASAP SINGLE ENG OPERATION procedure (2.04)..................APPLY

BOMB ON BOARD

AUTO PRESS - LANDING ELEVATION .................. CABIN ALTITUDE FLIGHT LEVEL ................................ DESCEND TO CABIN ALTITUDE AVOID LOAD FACTORS HANDLE BOMB CAREFULLY - AVOID SHOCKS � When Z aircraft = Z cabin APPROACH CONFIG: FLAPS 15 GEAR DOWN ..........SELECTED AUTO PRESS......................................................................... DUMP SERVICE DOOR ................................................................UNLOCK PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAG ATTACHED TO THE DOOR HANDLE SURROUND IT WITH DAMPING MATERIAL CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER........... ............................................................................ MOVE FORWARD PAX................................... MOVE FORWARD / CRASH POSITION LAND ASAP

Eng : PW127F / PW127M

R

1.04A72

EMERGENCYSEP 04 400

COCKPIT DOOR SECURITY SYSTEM

Electrical Power LostMove the manual lock bolt to CLOSE positionNote : When the door is locked with the manual bolt, the

emergency access to the cockpit is unavailable. It isrecommended that at least two crew members remain inthe cockpit during that time.

Cockpit Door Jammed

l When cockpit exit requiredCOCKPIT DOOR LOCKING SYSTEM ............................... OFFDisconnect PLUG on top of the doorRemove the safety pins from the doorPush and remove corresponding door panel

Mod : 5465

1

1.05

72


SMOKE

CREW OXY MASKS.............................................................ON / 100% GOGGLES .......................................................................................SET CREW COMMUNICATIONS ..............................................ESTABLISH RECIRC FANS 1 + 2 ...................................................................... OFF AP ..................................................................................................... ON SMOKE SOURCE.................................................................. IDENTIFY � If source not identified or electrical smoke suspected Note: ELEC light may be activated by an air conditioning smoke source ELECTRICAL SMOKE procedure (1.05A) ............................APPLY � If air conditioning smoke identified AIR COND SMOKE procedure (1.05A) .................................APPLY � If FWD SMK illuminated or smoke in FWD zone of aircraft FWD SMOKE procedure (1.06).............................................APPLY � If AFT SMK illuminated or smoke in AFT zone of aircraft AFT SMOKE procedure (1.06) ..............................................APPLY � If AUX AFT COMPT SMK illuminated (depending on models) AUX AFT COMPT SMK procedure (1.06) .............................APPLY

Model : 212A

1.05A

72


ELECTRICAL SMOKE

SMOKE procedure (1.05) ...........................................................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 identified LAND ASAP ACW TOTAL LOSS procedure (2.16A) .................................APPLY

� If smoke origin identified NOT AFFECTED EQUIPMENTS .................................... RESTORE

� When ∆∆∆∆P below 1 PSI OVBD VALVE ................................................................FULL OPEN AVIONICS VENT EXHAUST MODE ......................................NORM

AIR COND SMOKE

SMOKE procedure (1.05) ...........................................................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 smoke warning. 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 in order to avoid shutting down safe engine.

PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.04).......................APPLY

Model : 212A

1.06

72


FWD SMK

SMOKE procedure (1.05) ...........................................................APPLY

1) PASSENGERS VERSION 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 OF SMOKE LAND ASAP

� When ∆∆∆∆P below 1 PSI OVBD VALVE...........................................................FULL OPEN AVIONICS VENT EXHAUST MODE.................................NORM

2) CARGO VERSION CAB PRESS MODE SEL...........................................................MAN CAB ALT................................................................ MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)........... OFF PACK VALVE 2 (Except when in single pack operation) .......... OFF CAB VENT AIR FLOW .............................................................. OFF FLIGHT COMPT TEMP SEL ..................................................... HOT

CAUTION: LAND ASAP. If a quick landing is not possible, climb and maintain minimum FL160; FL200 is recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

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

AFT SMK

SMOKE procedure (1.05)...........................................................APPLY

1) PASSENGERS VERSION CABIN CREW (PA)....................................... ADVISE FOR ACTION AIR FLOW ................................................................................HIGH

2) CARGO VERSION CAB PRESS MODE SEL...........................................................MAN CAB ALT................................................................ MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)........... OFF PACK VALVE 2 (Except when in single pack operation) .......... OFF CAB VENT AIR FLOW .............................................................. OFF FLIGHT COMPT TEMP SEL ..................................................... HOT

CAUTION: LAND ASAP. If a quick landing is not possible, climb and maintain minimum FL160; FL200 is recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

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

AUX AFT COMPT SMK (depending on models)

SMOKE procedure (1.05) ...........................................................APPLY AUX AFT COMPT AGENT ......................................................... DISCH

Model : 212A

1.07

72


DUAL DC GEN LOSS

R

DC GEN 1 + 2...................................................................OFF then ON � 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 is necessary to provide IEP illumination

STICK PUSHER / SHAKER ...................................................... OFF STICK PUSHER / SHAKER FAULT procedure (2.21) ..........APPLY SIDE WINDOWS ANTI-ICING................................................... OFF ADC SW....................................................................SET TO ADC 1 ATC SW .................................................................... SET TO ATC 1 TLU ................................................................. MAN MODE LO SPD

� When TLU LO SPD illuminates TLU .....................................................................................AUTO

CAUTION: Avoid large rudder input if IAS above 180 kt

BUS EQUIPMENT LISTS (2.18 A – 2.18 B).........................CHECK

� Before descent PAX INSTRUCTIONS .................................................... USE PA HYD X FEED .......................................................................... ON

Note: Selecting HYD X FEED ON allows to recover green hydraulic system

� At touch down IDLE GATE LEVER .............................................................PULL

Mod : 1603 + 4116 + 4366

1.07A

72

EMERGENCY SEP 07 100

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

Mod : 3973 or 4371 or 4457

1.08

72


DITCHING

� Preparation (time permitting) ATC (VHF1 or HF) ............................................................... NOTIFY XPDR ........................................................................ EMERGENCY 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 harnesses locked

AUTO PRESS - LDG ELEVATION.............................................SET

� Approach AUTO PRESS......................................................................... DUMP PACKS 1 + 2.............................................................................. OFF OVBD VALVE ..............................................................FULL CLOSE HYD AUX PUMP pushbutton ......................................... DEPRESS FLAPS (If available).......................................................................30 LDG GEAR LEVER ......................................................................UP

� 30 seconds before impact or 1250 ft above sea level DITCH PB .................................................................................... ON ENG START ROTARY SELECTOR.............. OFF / START ABORT CABIN REPORT............................................................. OBTAINED

� Before ditching (200 ft) MINIMIZE IMPACT SLOPE OPTIMAL PITCH ATTITUDE FOR IMPACT ................................. 9° BRACE FOR IMPACT ..........................................................ORDER

Note: In case of night ditching, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out).

CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ..............................................................PULL FUEL PUMPS 1 + 2................................................................... OFF � After ditching Note: After ditching, one aft door will be under the water line.

CABIN CREW (PA).............................................................. NOTIFY EVACUATION ....................................................................INITIATE � Before leaving aircraft BAT........................................................................................ OFF

Model : 212A

1.08A

72


FORCED LANDING

� Preparation (time permitting) ATC (VHF1 or HF) ............................................................... NOTIFY XPDR ........................................................................ EMERGENCY 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 harnesses locked

AUTO PRESS - LDG ELEVATION.............................................SET

� Approach HYD AUX PUMP pushbutton ......................................... DEPRESS FLAPS (If available).......................................................................30 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

Note: In case of night forced landing, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out).

CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ..............................................................PULL FUEL PUMPS 1 + 2................................................................... OFF

� After impact, when aircraft stopped CABIN CREW (PA).............................................................. NOTIFY AGENTS ................................................................................ DISCH EVACUATION ....................................................................INITIATE � Before leaving aircraft BAT........................................................................................ OFF

Model : 212A

1.09

72


SEVERE ICING

MINIMUM ICING SPEED.................................................... INCREASE 10 kt PWR MGT...............................................................................................MCT CL 1 + 2 ....................................................................................100% OVRD PL 1 + 2..............................................................................................NOTCH AP (if engaged) .......FIRMLY HOLD CONTROL WHEEL and DISENGAGE SEVERE ICING CONDITIONS........................................................ESCAPE ATC ................................................................................................... NOTIFY

� If an unusual roll response or uncommanded roll control movement is observed :

Push firmly on the control wheel FLAPS..........................................................................EXTEND 15

� If the flaps are extended, do not retract them until the airframe is clear of ice.

� For approach, if the aircraft is not clear of ice: GPWS ............................................................ FLAP/GPWS OVRD STEEP SLOPE APPROACH (≥4.5°) ........................PROHIBITED

APP/LDG CONF ..........................................MAINTAIN FLAPS 15 APP SPEED ..... "REDUCED FLAPS 15 LDG icing speeds" + 5 kt Multiply landing distance FLAPS 30 by 2.12.

DETECTION

Visual cue identifying severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window

and / or

Unexpected decrease in speed or rate of climb

and / or

The following secondary indications : . Water splashing and streaming on the windshield . Unusually extensive ice accreted on the airframe in areas not normally

observed to collect ice . Accumulation of ice on the lower surface of the wing aft of the protected

areas . Accumulation of ice on propeller spinner farther aft than normally

observed

The following weather conditions may be conducive to severe in-flight icing : . Visible rain at temperatures close to 0°C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0°C

ambient air temperature (SAT)



1.10

72


RECOVERY AFTER STALL

or ABNORMAL ROLL CONTROL

R R R R

R

CONTROL WHEEL........................................................ PUSH FIRMLY

� If flaps 0° configuration FLAPS ........................................................................................... 15° PWR MGT...................................................................................MCT CL 1 + 2 .........................................................................100% OVRD PL 1 + 2..................................................................................NOTCH ATC ....................................................................................... NOTIFY

� If flaps are extended PWR MGT...................................................................................MCT CL 1 + 2 .........................................................................100% OVRD PL 1 + 2..................................................................................NOTCH ATC ....................................................................................... NOTIFY

Note: this procedure is applicable regardless the LDG GEAR position is (DOWN or UP)

UNRELIABLE AIRSPEED INDICATION

AP/YD/FD BARS ...............................................................OFF/OFF/STBY

PITCH AND TQ......................................................................... MAINTAIN � If at take off or GA below 1500 ft: PITCH IMMEDIATELY........................................................................ 8°

ICING / VOLCANIC ASHES CONDITIONS.................................ESCAPE PROBE HEATING, DE-/ANTI-ICING...................................... CHECK ON APM..................................................................................................... OFF

WARNING: respect STALL alarm.

Note: Use any GPS speed information if available.

� Take off phase, at or above acceleration altitude ALTITUDE.................................... MAINTAIN AT LEAST 30 SECONDS FLAPS.................................................................................................. 0° PITCH .................................................................................................. 8° Note: Use climb table here after to adjust pitch if required. AFTER TAKE OFF normal procedure .........................................APPLY LAND AT THE NEAREST SUITABLE AIRPORT

� Climb TLU ............................................................................................ LO SPD PWR MGT........................................................................................ CLB PL 1 + 2.......................................................................................NOTCH

Altitude (ft) 5000 10000 15000 20000

Normal conditions pitch 7° 5° 4° 3°

Icing conditions pitch 6° 4° 3° 2°

Continuing next page …/…


1.11

72


UNRELIABLE AIRSPEED INDICATION

(CONT’D)

� Cruise

ALTITUDE ............................................................................... MAINTAIN TLU............................................................................................... HI SPD Note: Average pitch around 0° at cruise speed PWR MGT ......................................................................................... CRZ PL 1 + 2 ........................................................................................NOTCH

� Descent TLU............................................................................................... HI SPD PITCH........................................................................MAINTAIN AT -2.5° PL 1 + 2 ........................................................................ ADJUST 30% TQ DESCENT normal procedure ........................................................APPLY

� Initial Approach TLU.............................................................................................. LO SPD APPROACH normal procedure .....................................................APPLY CAUTION: Transition from clean configuration to LDG configuration is to be performed in level flight - REFER TO ALTIMETER - (if possible 30 seconds between each step). Note: Refer to following tables to adjust TQ:

TQ (Altitude of 3000ft) Aircraft configuration

- Average speed 14 T

18 T

22 T

Flaps 0 ° - 180 kt 35% 45% 50%

FLAPS ................................................................................................. 15° Flaps 15 ° - 150 kt 35% 40% 45%

LDG GEAR ....................................................................................DOWN PWR MGT ........................................................................................... TO FLAPS ................................................................................................. 30°

Flaps 30 ° - 130 kt 45% 45% 50%

� Final Approach PL 1 + 2 ........................................................................ ADJUST 35% TQ BEFORE LANDING normal procedure .........................................APPLY Note: Set an average pitch of -5° for a 3° slope approac h.

2.01

72

FOLLOWING FAILURES JUN 12 500

2 - PROCEDURES FOLLOWING FAILURES

Content 1/3 POWER PLANT SINGLE ENG OPERATION………………………………………………………. 2.04 START FAULT……………………………………………………………………... 2.04 X START FAIL……………………………………………………………………… 2.04 ABNORMAL PARAMETERS DURING START………………………………… 2.05 EXCESSIVE ITT DURING START………………………………………………. 2.05 NO ITT DURING START………………………………………………………….. 2.05 NO NH DURING START………………………………………………………….. 2.05 ENG NAC OVHT 2.06 ABNORMAL ENG PARAMETERS IN FLIGHT………………………………… 2.06 FIRE LOOP FAULT……………………………………………………………….. 2.06 ABNORMAL PROP BRK…………………………………………………………. 2.07 ENG RESTART IN FLIGHT………………………………………………………. 2.08 ENG STALL………………………………………………………………………… 2.08 ONE EEC FAULT………………………………………………………………….. 2.09 BOTH EEC FAULT………………………………………………………………… 2.09 ENG FLAME OUT…………………………………………………………………. 2.10 IDLE GATE FAIL…………………………………………………………………… 2.10 SYNPHR FAIL (if applicable) ……………………………………………………. 2.10A CL PNEUMATIC ACTUATOR BLOCKING (if applicable) ……………………. 2.10A UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS (if applicable) …………… 2.10A PEC SGL CH (if applicable) ……………………………………………………… 2.10A PEC FAULT (if applicable) ……………………………………………………….. 2.10A LO PITCH IN FLIGHT……………………………………………………………... 2.11 ENG OVER LIMIT…………………………………………………………………. 2.11 PROP OVER LIMIT……………………………………………………………….. 2.11 ENG OIL TEMP BELOW 45°C …………………………………………………… 2.12 ENG OIL TEMP HIGH…………………………………………………………….. 2.12 ENG OIL LO PR……………………………………………………………………. 2.12 ENG BOOST FAULT (if applicable) …………………………………………….. 2.12A FUEL FUEL ABNORMAL TEMP………………………………………………………… 2.13 FUEL CLOG………………………………………………………………………… 2.13 FUEL FEED LO PR……….……………………………………………………….. 2.13 FUEL LEAK ALERT CONDITION……………………………………………….. 2.14 FUEL LO LVL………………………………………………………………………. 2.14 FUEL LEAK………………………………………………………………………… 2.14 ELEC DC BUS 1 OFF ……………………………………………………………………. 2.15 AC BUS 1 OFF ……………………………………………………………………. 2.15 DC BUS 2 OFF ……………………………………………………………………. 2.15A AC BUS 2 OFF ……………………………………………………………………. 2.15A ACW BUS 1 OFF / ACW BUS 2 OFF…………………………………………… 2.16 ACW TOTAL LOSS……………………………………………………………….. 2.16A DC ESS BUS OFF………………………………………………………………… 2.17 DC EMER BUS OFF………………………………………………………………. 2.17 DC GEN FAULT……………………………………………………………………. 2.18 INV FAULT…………………………………………………………………………. 2.18 ACW GEN FAULT…………………………………………………………………. 2.18 DC SVCE/UTLY BUS SHED……………………………………………………… 2.18 BAT CHG FAULT………………………………………………………………….. 2.18 DUAL BAT CHG LOSS……………………………………………………………. 2.18 BAT DISCHARGE IN FLIGHT (if applicable) …………………………………... 2.18

STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS………………... 2.18A 2.18B

ESS BUS AND EMER BUS LOST EQUIPMENT LISTS………………………. Cargo configuration only…..

2.42 2.42A

Model : 212A

2.02

72

FOLLOWING FAILURES OCT 09 001

2 - PROCEDURES FOLLOWING FAILURES Content 2/3 HYDRAULIC

R HYD LO LVL ……………………………………………………………………….. 2.19 BOTH MAIN HYD PUMPS LOSS ……………………………………………….. 2.19 BOTH HYD SYS LOSS …………………………………………………………… 2.20 HYD LO PR / HYD OVHT ………………………………………………………… 2.20 FLIGHT CONTROL FLAPS UNLK ………………………………………………………………………. 2.21 FLAPS JAM / UNCOUPLED / ASYM …………………………………………… 2.21 REDUCED FLAPS LANDING ……………………………………………………. 2.21 STICK PUSHER / SHAKER FAULT …………………………………………….. 2.21 PITCH TRIM ASYM (LOCAL LIGHT) …………………………………………… 2.22 PITCH TRIM INOPERATIVE …………………………………………………….. 2.22 DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTER UNIT FAIL …....... 2.22 PITCH DISCONNECT ……………………………………………………………. 2.22 PITCH RECONNECTION ON GROUND (If applicable) ……………………… 2.22A TLU FAULT ………………………………………………………………………… 2.22A AIL LOCK LIT (if applicable) ……………………………………………………... 2.22A ELEVATOR JAM ………………………………………………………………….. 2.23 AILERON JAM / SPOILER JAM …………………………………………………. 2.23 RUDDER JAM ……………………………………………………………………... 2.23 LANDING GEAR LDG GEAR GRAVITY EXTENSION ……………………………………………. 2.24 LANDING WITH ABNORMAL LDG GEAR …………………………………….. 2.24 LDG GEAR UNSAFE INDICATION …………………………………………….. 2.25 LDG GEAR RETRACTION IMPOSSIBLE ……………………………………… 2.25 ANTI-SKID FAULT ………………………………………………………………… 2.25 BRK TEMP HOT …………………………………………………………………... 2.25 AIR BLEED VALVE FAULT …………………………………………………………… 2.26 BLEED OVHT ……………………………………………………………………… 2.26 BLEED LEAK ……………………………………………………………………… 2.26 X VALVE OPEN …………………………………………………………………… 2.26 PACK VALVE FAULT …………………………………………………………….. 2.26 BOTH PACK VALVES FAULT …………………………………………………… 2.26 RECIRC FAN FAULT ……………………………………………………………... 2.26 DUCT OVHT ……………………………………………………………………….. 2.26A EXCESS CAB ALT ………………………………………………………………... 2.26A AUTO PRESS FAULT ……………………………………………………………. 2.26A EXCESS CAB ∆P …………………………………………………………………. 2.26A AVIONICS VENT EXHAUST MODE FAULT …………………………………... 2.27 OVBD VALVE FAULT …………………………………………………………….. 2.27

2.03

72

FOLLOWING FAILURES SEP 10 001

2 - PROCEDURES FOLLOWING FAILURES Content 3/3 ANTI ICE AFR AIR BLEED FAULT …………………………………………………………. 2.28 DE-ICING AIR FRAME FAULT ………………………………………………….. 2.28 DE-ICING MODE SEL FAULT …………………………………………………… 2.28 MODE SEL AUTO FAULT (if applicable) ………………………………………. 2.28 ICE DETECT FAULT ……………………………………………………………… 2.29 DE- / ANTI-ICING ENG FAULT …………………………………………………. 2.29 ANTI-ICING PROP FAULT ………………………………………………………. 2.29 ANTI-ICING HORNS FAULT …………………………………………………….. 2.29 SIDE WINDOW / WINDSHIELD HTG FAULT …………………………………. 2.29 PROBES HTG FAULT ……………………………………………………………. 2.29 AUTO PILOT

AILERON MISTRIM (ADU message)

or EXCESSIVE LATERAL TRIM REQUIRED ………………………………….. or ABNORMAL FLIGHT CHARACTERISTICS

2.30

PITCH MISTRIM (ADU message) ………………………………………………. 2.30 PITCH TRIM FAIL (ADU message) (if applicable) …………………………….. 2.30 DADC DATA INVALID (ADU message) ………………………………………… 2.30 MPC APM FAULT ……………………………………………………………………….. 2.30A DEGRADED PERF ……………………………………………………………….. 2.30A INCREASE SPEED ………………………………………………………………. 2.30A AVIONICS AUDIO SEL FAULT ……………………………………………………………….. 2.31 AHRS A / ERECT FAIL …………………………………………………………… 2.31 EFIS COMP ………………………………………………………………………... 2.31 ADC SW FAULT …………………………………………………………………... 2.31 ADU FAILURE …………………………………………………………………….. 2.32 ADC FAULT ……………………………………………………………………….. 2.32 AHRS FAIL ………………………………………………………………………… 2.32 SGU FAIL ………………………………………………………………………….. 2.32 CRT FAIL ………………………………………………………………………….. 2.32 MISCELLANEOUS COCKPIT DOOR CONTROL PANEL FAULT (if installed) …………………… 2.32A VOLCANIC ASH ENCOUNTER………………… ………………………………. 2.32A LOSS OF RADIO ALTIMETER INFORMATION ………………………………. 2.33

R SMK DET FANS FAULT …………………………………………………………. 2.33 DOORS UNLK IN FLIGHT ………………………………………………………. 2.33 COCKPIT WINDOW CRACKED ………………………………………………… 2.33 OXYGEN LO PR ………………………………………………………………….. 2.33 MFC MFC 1A FAULT …………………………………………………………………… 2.34 MFC 1B FAULT …………………………………………………………………… 2.34 MFC 2A FAULT …………………………………………………………………… 2.35 MFC 2B FAULT …………………………………………………………………… 2.35 MFC 1A + 1B FAULT ……………………………………………………………... 2.36 MFC 1A + 2A FAULT ……………………………………………………………... 2.37 MFC 1A + 2B FAULT ……………………………………………………………... 2.38 MFC 1B + 2A FAULT ……………………………………………………………... 2.39 MFC 2A + 2B FAULT ……………………………………………………………... 2.40 MFC 1B + 2B FAULT ……………………………………………………………... 2.41

ELEC Section for EMER & ESS BUS lost equipment lists…………….………

Cargo configuration only…… 2.42 2.42A

2.04

72

FOLLOWING FAILURES POWER PLANT

OCT 09 500

SINGLE ENG OPERATION

R

R

LAND ASAP

PWR 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 down

performances and single engine ceiling. Note: Refer to pages (4.61) and (4.62) to determine single engine gross

ceiling. Note: If during the flight, a positive oil pressure has been noted on the

failed engine for a noticeable period of time, maintenance must be informed.

Note: monitor fuel balance. Recommended operational maximum fuel unbalance is 200 kg (440 lb).

� When FUEL CROSS FEED is required FUEL PUMP affected side........................................................... ON FUEL X FEED.............................................................................. ON FUEL PUMP operating engine .................................................. 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 page (4.64) to determine 1.1VMCA.

Note: At touch down, do not reduce below FI before nose wheel is on the ground.

START FAULT

ENG START ROTARY SELECTOR................... OFF / START ABORT � If above 45 % NH START ON LIGHT....................................CHECK EXTINGUISHED START ............................................................. TO BE CONTINUED

X START FAIL

CONTINUE NORMAL ENGINE START INFORM MAINTENANCE

Mod : 3973 or 4371 or 4457

2.0572

FOLLOWING FAILURESPOWER PLANT

OCT 08 001

ABNORMAL PARAMETERSDURING START

If ITT tends to exceed 900°C, or no ITT, or no NHCL affected side ................................................................ FUEL SOENG START ROTARY SELECTOR..............OFF / START ABORT

Then refer to relevant procedure:

EXCESSIVE ITT DURING START procedure (2.05)

NO ITT DURING START procedure (2.05)

NO NH DURING START procedure (2.05)

EXCESSIVE ITT DURING START

When NH below 30 %ENG START ROTARY SELECTOR.....................................CRANKSTART PB ................................................................................... ON

After 15 secondsENG 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.

NO ITT DURING START

After 30 seconds, to allow fuel drainingENG START ROTARY SELECTOR.....................................CRANKSTART PB ................................................................................... ON

After 15 secondsENG START ROTARY SELECTOR ........OFF / START ABORT

NO NH DURING START

R

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 increasesCL ..........................................................................................FTRContinue START procedure, being informed NH indicator isinoperative.

If OIL pressure does not increasesENG START ROTARY SELECTOR ........OFF / START ABORTSuspect starter motor failure. Maintenance action is due.

2.0672


SEP 10 001

R ENG NAC OVHT

RR

R

RR

If during Hotel mode operationPL affected side .............................................................................GICL affected side.............................................. FTR THEN FUEL SO

If during taxiAIRCRAFT...............................................................................STOPPL affected side .............................SLIGHTLY INCREASE POWER

If unsuccessful within 30 secondsPL affected side........................................................................GICL affected side......................................... FTR THEN FUEL SO

ABNORMAL ENG PARAMETERSIN FLIGHT

RRRRRRRRRR

If Intermittent fluctuations or unrealistic steady indicationATPCS....................................................................................... OFF

When adequate flight situationPL affected side…………………………………………………… FIEEC affected side................................................................. OFF If successful

ONE EEC FAULT procedure (2.09) ..............................APPLY If unsuccessful- or - If TQ = 0% and NP<77%

PL affected side..................................................................... FICL affected side......................................................... FUEL SOSINGLE ENG OPERATION procedure (2.04) ..............APPLY

If "- - -" indication on torque digital counter (only for PW127 -PW127F - PW127M)

AVOID SUDDEN PL MOVEMENTS

FIRE LOOP FAULT

LOOP affected ................................................................................ OFF

2.07

72


NOV 11 500

ABNORMAL PROP BRK (if applicable)

� If on ground � If unexpected propeller rotation – or – � If local UNLK and CCAS PROP BRK alert CL 2 .............................................................................. FUEL SO MAINTENANCE ACTION REQUIRED

� If CCAS PROP BRK alert only � If GUST LOCK ON CL 2 ......................................................................... FUEL SO

� If DC and AC GPU are not available ENG 1.....................................................................START CL 1 ..........................................................................AUTO

� When READY light illuminates PROP BRK................................................................. OFF UNLK LIGHT .............................CHECK EXTINGUISHED PROP BRK PWR SPLY C/B .....................................PULL

� If GUST LOCK OFF GUST LOCK...................................................................... ON

� According to operational situation PROP BRK................................................................. OFF ALL PROP BRK LIGHTS ..........CHECK EXTINGUISHED

� If in flight CONTINUE NORMAL OPERATION ENG 2 PARAMETERS .....................................................MONITOR

� After landing CL 2 .............................................................................. FUEL SO MAINTENANCE ACTION REQUIRED

Mod : 3973 or 4371 or 4457

2.08

72


APR 08 500

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

At 10 % NH CL ...............................................................................................FTR RELIGHT ..........................................................................MONITOR CL ............................................................................................AUTO PL......................................................ADJUST TO OTHER ENGINE ENG START ROTARY SELECTOR....................................AS RQD SYSTEMS AFFECTED.................................................... RESTORE

ENG STALL

PL affected side .................................................................................. FI ENG PARAMETERS .................................................................CHECK

If abnormal engine parameters CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04).......................APPLY

If normal engine parameters DE-/ANTI-ICING ENG ................................................................. ON PL affected side ...............................................SLOWLY ADVANCE If stall recurs Reduce thrust and operate below the stall threshold If stall does not recur Continue engine operation

Mod : 3973 or 4371 or 4457

2.0972


SEP 10 500

ONE EEC FAULT

RR

ATPCS ............................................................................................ OFF

CAUTION: DO NOT DESELECT EEC FLASHING

When adequate flight situationPL affected side ............................... RETARD IN GREEN SECTOREEC affected side ..................................................................RESET

If successfulATPCS.................................................................................... ONPL affected side........................................... RESTORE POWER

If unsuccessfulEEC affected side................................................................. OFFPL affected side .......................................... RESTORE POWER......................................... HANDLING THROTTLE WITH CARE

In the following cases: icing conditions, engine(s) flame out,emergency descent, severe turbulence, heavy rainMAN IGN ........................................................................... ON

In final approachCL 1 + 2 ..............................................................100% OVRD

After landingTAXI WITH THE AFFECTED ENGINE FEATHEREDNote: ACW BTC must be check closed in order to avoid the lossof ACW bus on ground

BOTH EEC FAULT

ATPCS ............................................................................................ OFF

CAUTION: DO NOT DESELECT EEC FLASHING

When adequate flight situationPL 1 + 2 ........................................... RETARD IN GREEN SECTOREEC 1 + 2 ................................................................. OFF THEN ON

If EEC 1+2 recoveredATPCS.................................................................................... ONPL 1 + 2 ....................................................... RESTORE POWER

If only one EEC recoveredONE EEC FAULT procedure (2.09) .................................APPLY

If no EEC recoveredEEC 1 + 2 ............................................................................. OFFPL 1 + 2 ....................................................... RESTORE POWER....................................... HANDLING THROTTLES WITH CARETQ IND ENG 1 + 2.......................................................MONITORLDG DIST ....................................................... MULTIPLY BY 1.5Note: Refer to Part 4 to determine landing distance

In the following cases: icing conditions, engine(s) flame out,emergency descent, severe turbulence, heavy rainMAN IGN ........................................................................... ON

In final approachCL 1 + 2 ..............................................................100% OVRD

After landingBRAKE HANDLE........................................... EMER AS RQDCAUTION: Reverse power is reduced.Both main HYD pumps will be lost at low speed.TAXI ON BOTH ENGINES,HANDLE THROTTLES WITH CARE

Mod : 3973 or 4371 or 4457

2.10

72


OCT 09 050

ENG FLAME OUT

RRR

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 (2.04)..................APPLY

� If no damage suspected ENG RESTART IN FLIGHT procedure (2.08)..................APPLY

� If unsuccessful SINGLE ENG OPERATION procedure (2.04) ............APPLY

IDLE GATE FAIL

� In flight IDLE GATE LEVER .................................................................PUSH � At touch down IDLE GATE LEVER ..................................................................PULL

Mod : 4111

2.10A

72


SEP 10 500

R

R

UNCOMMANDED 100% NP ON ONE OR

TWO PROPELLERS

RR

CL 1 + 2 .............................................................................100% OVRD

PEC SGL CH

DO NOT RESET PEC IN FLIGHT - NO SPECIAL CREW ACTION ANTICIPATE A PEC FAULT AT LANDING MAINTENANCE IS REQUIRED

PEC FAULT

� If in short final approach (below 400 ft RA) GO AROUND procedure .......................................................APPLY

� Above 400 ft or when adequate CL 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 ENGINES Note: ACW BTC may be check closed in order to avoid the loss of ACW bus on ground

Mod : 3973 or 4371 or 4457

2.11

72


SEP 10 500

LO PITCH IN FLIGHT

PL affected side .................................................................................. FI CL affected side ................................................... FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04) ............................APPLY

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 permit PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04).......................APPLY

PROP OVER LIMIT

R R R RRRRRR

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 FLIGHT Note: 106% allowed to complete a flight without overshooting 73% TQ in CRZ and 75% in CLB

� If NP remains above 106% and conditions permit PL affected side .............................................................................. FI CL affected side ............................................... FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04) ........................APPLY


2.12

72


OCT 08 500

ENG OIL TEMP BELOW 45°C

If icing conditions are expected or present

ENG POWER ...............................................If possible, INCREASE

ENG OIL TEMP HIGH

OIL TEMP between 125°C and 140°C

OIL TEMP AND PRESS ...................................................MONITOR Note: If OIL temperature rise follows PL reduction, advancing PL

may reduce OIL temperature. Note: If OIL temperature rise occurs in steady state conditions, a

power reduction should permit a reduction in OIL temperature.

OIL TEMP between 125°C and 140°C for 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.

OIL TEMP above 140°C PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04).......................APPLY

ENG OIL LO PR

R

PL affected side .................................................................................. FI

If both OIL LO PR on CAP and local alert are activated CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04).......................APPLY

If local alert only is activated CL affected side.............................................. FTR THEN FUEL SO Once engine is shut off CL affected side..........................................................................FTR If CCAS is activated after 30 seconds CL affected side............................................................ FUEL SO ENG RESTART IN FLIGHT procedure (2.08)..................APPLY If not CL affected side ............................................................ FUEL SO SINGLE ENG OPERATION procedure (2.04)..................APPLY

If OIL LO PR alert on CAP only is activated DISREGARD INFORM MAINTENANCE

If single engine operation required NP of feathered engine.....................................................MONITOR If NP of feathered engine above 10% APPROACH SPEED .................................INCREASE BY 10 KT


2.13

72

FOLLOWING FAILURES FUEL

JUN 12 500

FUEL ABNORMAL TEMP

� If too high (>50°C) Note: Avoid rapid throttle movement OIL TEMP AND OTHER ENGINES PARAMETERS .......MONITOR

� If too low (<0°C) Note: Use anti-icing additive for next refueling if repair can't be done

FUEL CLOG

� If both lights are illuminated

ENGINES PARAMETERS................................................MONITOR � If abnormal engines parameters LAND ASAP Note: Fuel contamination may be suspected

MAINTENANCE ACTION REQUIRED

� If only one light is illuminated ENGINE PARAMETERS affected side.............................MONITOR

FUEL FEED LO PR

PUMP affected side ........................................................ CONFIRM ON ENGINE affected side...........MONITOR FOR POSSIBLE RUN DOWN

� If engine runs down or if fuel quantity decreases s ignificantly PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO PUMP affected side ................................................................... OFF FIRE HANDLE affected side.....................................................PULL LAND ASAP SINGLE ENG OPERATION procedure (2.04).......................APPLY

CAUTION: Do not open X FEED valve

Model : 212A

2.14

72

FOLLOWING FAILURES FUEL

OCT 09 500

FUEL LEAK ALERT CONDITION

A fuel leak may be detected by either: - sum of fuel on board (FOB), read in steady flight at cruise level, and

fuel used (FU), FOB+FU significantly less than fuel at departure, or - total fuel quantity decreasing (fuel spray from engine or wing tip), 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

FUEL LO LVL

R

AVOID EXCESSIVE AIRCRAFT ATTITUDES

� If both LO LVL lights ON LAND ASAP

� If LO LVL light on one side only � If leak suspected FUEL LEAK procedure (2.14)...........................................APPLY � If no leak suspected � If FQI < 160 kg / 352 lb X FEED.............................................................................. ON � If FQI ≥ 160 kg / 352 lb, Feeder jet pump malfunction is suspected X FEED is not necessary FUEL CONSUMPTION ..........................................MONITOR

FUEL LEAK

� When a leak is confirmed LAND ASAP

� 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 (2.04)..................APPLY

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

� In all other cases X FEED valve must remain closed

� Leak not located FUEL X FEED............................................. MAINTAIN CLOSED

Note: the X FEED must remain closed to prevent the leak affecting both sides.

� Before landing ATC................................................................................. NOTIFY

Mod : 4686 or 8148

2.15

72

FOLLOWING FAILURES ELEC

OCT 09 550

DC BUS 1 OFF

DC GEN 1 ....................................................................................... OFF PF.................................................................................................... CM2 MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN DC SVCE AND UTLY BUS SHED..................................MAINTAIN ON AFFECTED EQUIPMENT............................................................... OFF DC BUS 1 EQUIPMENT LIST ...................................................CHECK � At touch down IDLE GATE LEVER ..................................................................PULL

DC BUS 1 LOST EQUIPMENT LIST

Instruments, Navigation & Com: Weather Radar Radio Altimeter (2.33) (E)GPWS DME #1 Air: Bleed LEAK IND 1 & 2 AUTO PRESS (2.26A) Flight controls: Stick Pusher (2.21) CM1 Stick Shaker (2.21)

Ice & Rain protection: CM1 and STBY Static Ports anti-icing CM1 Side Window Anti-Icing (2.32) CM2 Windshield HTG IND Engines: FF/FU#1, Fuel TEMP#1 & Fuel CLOG #1 Oil PRESS & Oil TEMP #1 AUTO IDLE GATE (2.10) Light: CM1 Dome, chartholder & reading light CM2 Flood panel light Storm light, Annunciator light test NAV & BEACON light Miscellaneous: Toilet flushing (If supplied by DC)

AC BUS 1 OFF

Note: Wait for 10 seconds in order to confirm the failure.

DC BTC......................................................................... ISOL THEN ON � If unsuccessful AC BUS 1 EQUIPMENT LIST ..............................................CHECK

AC BUS 1 LOST EQUIPMENT LIST

115 AC BUS 1 26 AC BUS 1

BLEED LEAK DET 1 & 2 TRIMS IND

For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60

Mod : 4366 and (3973 or 4371 or 4457)

2.15A

72


OCT 09 150

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 EQUIPMENT LIST ...................................................CHECK � Before descent PAX INSTRUCTIONS.......................................................... USE PA � After touch down TAXI ON BOTH ENGINES

DC BUS 2 LOST EQUIPMENT LIST

RRRRRRRRRRRRRRRRR

Instruments, Navigation & Com: CM2 EADI/EHSI & SGU#2 (2.32) VOR/ILS/DME#2, ADF#2, CM1 RMI VHF#2 ATC#2, TCAS or T2CAS (if installed) ADC #2 & ALT ALERT # 2 (2.32) CM2 Clock GPS (KLN90) (if installed) CCAS: CAP amber alert except Maint PNL, PRKG BRK & MFC Air: Landing elevation IND Hydraulic: DC AUX HYD PUMP (In Automatic) Landing gear: Secondary IND Flight controls: Right stick shaker Standby pitch trim control TLU auto control

Ice & Rain protection: CM2 Static Port anti-icing CM2 Probes IND CM2 Wiper CM2 Side window anti-icing (2.29) CM1 Windshield HTG IND Engines: FF/FU #2 FUEL TEMP #2, FUEL CLOG #2 OIL PRESS, TEMP #2 IDLE GATE FAIL IND Light: CM2 Chartholder, Reading LIGHTS Integrated Norm INST&PANEL LIGHTS Taxi / Take off LIGHT, Wing LIGHTS Passenger Signs Doors: Doors UNLK lights Cockpit door locking system Fire: NAC OVHT

RRRRRRRRRRRRRRRRR

AC BUS 2 OFF

Note: Wait for 10 seconds in order to confirm the failure.

DC BTC......................................................................... ISOL THEN ON � If unsuccessful PF .............................................................................................. CM1 AC BUS 2 EQUIPMENT LIST ..............................................CHECK

AC BUS 2 LOST EQUIPMENT LIST

R 115 AC BUS 2 26 AC BUS 2

R GPWS CM2 ASI, VSI, ALTI Heading RMI#1 Bearing VOR#2&ADF#2 to RMI/SGU 1/2 Course#2 and Heading#2 Select

RRR

For more information on BUS EQUIPMENT LISTS see F COM 1.06.60

Mod : 4116 + 4366

2.16

72


OCT 09 001

ACW BUS 1 OFF / ACW BUS 2 OFF

ACW GEN affected side ................................................................. OFF LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION ..................................... VISUALLY MONITOR

� If ACW BUS 1 OFF PF .............................................................................................. CM2 CM1 AIRSPEED INDICATOR ..........................................MONITOR

� If ACW BUS 2 OFF PF .............................................................................................. 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 (2.30) ....APPLY

� After touch down TAXI ON BOTH ENGINES

ACW BUS 1 LOST EQUIPMENT LIST

RRRRR R

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)

RRRRRRR

ACW BUS 2 LOST EQUIPMENT LIST

RRRRRR

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

RRRRR R

2.16A

72


OCT 09 001

ACW TOTAL LOSS

ACW GEN 1 + 2.............................................................................. OFF HYD X FEED .....................................................................CHECK OFF LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION........................................... VISUALLY MONITOR CM1 and CM2 AIRSPEED INDICATORS........................MONITOR ACW TOTAL LOSS EQUIPMENT LIST ....................................CHECK AFFECTED EQUIPMENT............................................................... OFF MAIN HYD PUMPS......................................................................... OFF LDG GEAR EXTENSION/RETRACTION..................................... LOST NORMAL BRAKE ......................................................................... LOST LDG DIST ................................................................. MULTIPLY BY 1.5 Note: Refer to Part 4 to determine LDG DIST

� Before landing LDG GEAR LEVER ............................................................... DOWN BLUE PRESSURE................................................................CHECK FLAPS..................................................................................AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLY

� After touch down REVERSE............................................................................AS RQD BRAKE HANDLE ..................................................... EMER AS RQD TAXI ON BOTH ENGINES

ACW TOTAL LOST EQUIPMENT LIST

RRRRRR

Hydraulic: BLUE & GREEN PUMP Lights: Integrated INST&PNL Lights LEFT & RIGHT LANDING LIGHT TAXI/TO LIGHTS

Ice & Rain protection: CM 1&2 PITOT/ALPHA/TAT Heating ANTI-ICING PROP 1&2 ANTI-ICING HORNS CM1&2 WINDSHIELD HTG ICE DETECTOR Miscellaneous: Toilet (If supplied by ACW)

RRRRRRRR


2.1772

FOLLOWING FAILURESELEC

OCT 08 001

DC ESS BUS OFF

DC ESS BUS EQUIPMENT LIST ..............................................CHECK

If Cockpit Securized Door installedCOCKPIT DOOR MANUAL LOCK BOLT(S).....................................

.......................................................... MOVE TO CLOSE POSITION

Note: Cockpit Door Control Panel FAULT LIGHT is inoperative.

Note: When the door is locked with the manual bolt(s), theemergency access to the cockpit is unavailable. It isrecommended that at least two crewmembers remain in thecockpit during that time.

DC ESS BUS LOST EQUIPMENT LIST

RR

See QRH pages 2.42 (all configuration)and 2.42A (for cargo configuration only)

DC EMER BUS OFF

RR

LEAVE AND AVOID ICING CONDITIONSDESCEND TOWARD ........................................................FL100 / MEASTBY PITCH TRIM.......................................................... USE AS RQDADC SW (ADC FAULT lights lost) .................................SET TO ADC 2HYD X FEED .................................................................................... ON If ice accretion builds up on airframe

DE-ICING MODE SEL FAULT procedure (2.28)...................APPLYANTI-ICING PROP FAULT procedure (2.29) ........................APPLYANTI-ICING HORNS FAULT procedure (2.29) .....................APPLYCM1 and STBY IAS ............................................COMPARE to CM2Note: Use CM2 instruments in case of disagreement.

Before landingANTI-SKID ................................................................................. OFFN/W STEERING ........................................................................ OFFANTI-SKID FAULT procedure (2.25).....................................APPLY

DC EMER BUS OFF LOST EQUIPMENT LIST

RSee QRH pages 2.42 (all configuration)and 2.42A (for cargo configuration only)


2.18

72


OCT 08 500

DC GEN FAULT

DC GEN affected side..................................................................... OFF If OAT exceeds ISA + 25

FL........................................................................................200 MAX TAXI ON BOTH ENGINES

INV FAULT

NO SPECIFIC ACTION IN FLIGHT

ACW GEN FAULT

ACW GEN affected side ................................................................. OFF LEAVE AND AVOID ICING CONDITIONS TAXI ON BOTH ENGINES

DC SVCE/UTLY BUS SHED

DC SVCE/UTLY BUS PB..........................................................AS RQD

DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST

R See FCOM 1.06.60 pages 12 to 14

BAT CHG FAULT

CHG associated.............................................................................. OFF

DUAL BAT CHG LOSS

MFC MODULES, one at a time ....................................... OFF / RESET If RESET unsuccessful

LAND ASAP Note: minimize use of VHF 1 if conditions permit.

BAT DISCHARGE IN FLIGHT

ENG START ROTARY SELECTOR............................................... OFF

If battery(ies) still discharging LAND ASAP

Mod : 3246 + 4111

2.18A

72


APR 08 550

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116 + 4366

2.18B

72


APR 08 500

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116

2.19

72

FOLLOWING FAILURES HYDRAULIC

OCT 08 001

HYD LO LVL

If blue system affected BLUE PUMP .............................................................................. OFF AUX PUMP ....................................................... OFF (CONFIRMED) REDUCED FLAPS LANDING procedure (2.21)....................APPLY After touch down USE NORMAL BRAKE FOR STEERING TAXI ON BOTH ENGINES

If green system affected GREEN PUMP........................................................................... OFF LDG DIST ............................................................ MULTIPLY BY 1.5 Note: Refer to Part 4 to determine landing distance LDG GRAVITY EXTENSION procedure (2.24) .....................APPLY After touch down TAXI ON BOTH ENGINES REVERSE.......................................................................AS RQD BRK HANDLE..................................................... EMER AS RQD

HYD SYS LOST EQUIPMENT LIST

BLUE GREEN

FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on accu only)

LDG GEAR EXT / RET NORM BRK

BOTH MAIN HYD PUMPS LOSS

MAIN BLUE AND GREEN PUMPS ................................................ OFF X FEED ..............................................................................CHECK OFF LDG DIST .................................................................MULTIPLY BY 1.5 Note: Refer to Part 4 to determine landing distance

Before landing LDG GEAR LEVER ............................................................... DOWN BLUE PRESSURE................................................................CHECK FLAPS 15 ............................................................................AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLY FLAPS 30 ............................................................................AS RQD

After touch down TAXI ON BOTH ENGINES REVERSE............................................................................AS RQD BRK HANDLE.......................................................... EMER AS RQD

BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST

R R

BLUE

recovered when LDG GEAR lever is DOWN

GREEN

R R R



2.20

72

FOLLOWING FAILURES HYDRAULIC

OCT 08 500

BOTH HYD SYS LOSS

R

RRR

MAIN AND AUX PUMPS ................................................................ OFF

� Before approach GPWS......... GPWS OVRD or FLAP OVRD (depending on version) LDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLY APP/LDG SPEED........................VmHB 0 + 5 KT + WIND EFFECT LDG DIST ........................MULTIPLY LDG DIST FLAPS 30 BY 2.9 Note: Refer to Part 4 to determine VmHB and LDG DIST

CAUTION: Tail strike may occur if pitch attitude exceeds 8° during the flare depending upon vertical speed at touch down.

� After touch down REVERSE............................................................................AS RQD BRK HANDLE.......................................................... EMER AS RQD TAXI ON BOTH ENGINES

BOTH HYD SYS LOST EQUIPMENT LIST

R BLUE GREEN

R R R



HYD LO PR / HYD OVHT

PUMP affected side ........................................................................ OFF X FEED ............................................................................................. ON

Mod : 3973 or 4371 or 4457 Eng : PW127 / PW127F / PW127M

2.21

72

FOLLOWING FAILURES FLIGHT CONTROL

APR 08 500

FLAPS UNLK

If before V1

TAKE OFF ............................................................................ ABORT If after V1

VR, V2.............................................................INCREASE BY 10 KT If alarm occurs during approach

GO AROUND procedure .......................................................APPLY VGA ................................................................INCREASE BY 10 KT

When possible FLAPS..............................................................................................0 REDUCED FLAPS LANDING procedure (2.21)....................APPLY

FLAPS JAM / UNCOUPLED / ASYM

FLAPS CTL LEVER.....................NEAR FLAPS PRESENT POSITION

When applicable REDUCED FLAPS LANDING procedure (2.21)....................APPLY

REDUCED FLAPS LANDING

GPWS .............. GPWS OVRD or FLAP OVRD (depending on version) STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED

FLAPS LDG DIST FLAPS 30

MULTIPLY BY APP/LDG SPEED

0 2.2 VmHB 0 + WIND EFFECT + 5 KT

15 2 VmHB 15 + WIND EFFECT

Note: Refer to Part 4 to determine VmHB and LDG DIST CAUTION: Tail strike may occur if pitch attitude exceeds 8° during the

flare depending upon vertical speed at touch down.

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 Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

Mod : 3973 or 4371 or 4457 Eng : PW127 / PW127F / PW127M

2.22

72


OCT 09 001

PITCH TRIM ASYM (LOCAL LIGHT)

AP DISCONNECTION...................................... CONFIRM MANUALLY PITCH TRIM INOPERATIVE procedure (2.22) ..........................APPLY

PITCH TRIM INOPERATIVE

EXISTING CONFIGURATION AND SPEED.......................................... .................................................... MAINTAIN AS LONG AS POSSIBLE

� 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 Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

RRR

DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING

UNIT FAIL

RR

� If YD is available YD ...................................................................................... ENGAGE � If YD is not available LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTED RUDDER PEDAL MOVEMENT

PITCH DISCONNECT

BOTH CONTROL COLUMNS ........................................ CHECK FREE IAS .......................................................................................180 kt MAX LOAD FACTOR ............................................................................... 2 g MAX BANK ANGLE ............................ 30° MAX UNTIL FLAPS EXTENSION

AVOID ICING CONDITIONS � For approach STEEP SLOPE APPROACH (≥4.5°)...........................PROHIBITED LAND AT AIRPORT WITH MINIMUM CROSSWIND LDG SPEED ...................................................INCREASE BY 10 KT LDG DIST .......................................................... MULTIPLY BY 1.13 PL 1 + 2 ..................................... REDUCE SMOOTHLY TO FLARE Note: Refer to Part 4 to determine LDG DATA

� When on ground and ELEV CLUTCH GUARDED PB installed PITCH RECONNECTION ON GROUND procedure (2.22A) ............ ...............................................................................................APPLY

2.22A

72


APR 08 500

PITCH RECONNECTION ON GROUND

(if applicable)

GUST LOCK ........................................................................... ENGAGE BOTH COLUMNS...................................................... CHECK LOCKED ELEV CLUTCH GUARDED PB .........................DEPRESS AND HOLD

When PITCH DISCONNECT flashes red on CAP ELEV CLUTCH GUARDED PB ........................................RELEASE PITCH DISCONNECT ON CAP ...............CHECK EXTINGUISHED BOTH COLUMNS.............................................. CHECK COUPLED

TLU FAULT

If ADC 1 + 2 are lost

If IAS above 185 kt TLU ...................................................................................HI SPD If IAS below 185 kt TLU ................................................................................. LO SPD DISREGARD TLU FAULT ALERT

If at least one ADC operates If IAS above 185 kt TLU ...................................................................................HI SPD If TLU FAULT alarm persists SPEED ............................................................... 180 KT MAX TLU............................................................................ LO SPD If IAS below 185 kt SPEED..................................................................... 180 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.

AIL LOCK LIT

If before take off

RETURN TO PARKING REFER TO MMEL ATA 27 ITEM 70-1 GUST LOCK SYSTEM

If after landing TAKE SPECIAL CARE FOR TAXI (WIND EFFECTS) USE STANDBY SYSTEM FOR AILERON LOCK AT PARKING INFORM MAINTENANCE

Mod : 4373 or 8167

2.23

72


APR 08 001

ELEVATOR JAM

CONTROL COLUMNS ...................................................... UNCOUPLE

AVOID ICING CONDITIONS IAS ..................................................................................... 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 (2.22).....................................APPLY

AILERON JAM / SPOILER JAM

BANK ANGLE LIMIT................................................................ 25° MAX BLUE AND AUX HYD PUMPS ....................................................... OFF LAND AT AIRPORT WITH MINIMUM CROSSWIND

For approach STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED BLUE AND AUX HYD PUMPS.................................................... ON CAUTION: Do not extend FLAPS in turn

When in landing configuration BLUE AND AUX HYD PUMPS.................................................. OFF

Immediately after touch down BLUE AND AUX HYD PUMPS.................................................... ON

RUDDER JAM

STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED LANDING............................................................................... FLAPS 30 USE DIFFERENTIAL POWER SO AS TO MINIMIZE SIDESLIP LAND AT AIRPORT WITH MINIMUM CROSSWIND

At touch down NOSE DOWN BEFORE REDUCTION BELOW FI

2.24

72

FOLLOWING FAILURES LANDING GEAR

APR 08 001

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 the handle when operating TCAS (if installed) ................................................................... TA ONLY If unsuccessful

LANDING WITH ABNORMAL LDG GEAR procedure (2.24)............APPLY

LANDING WITH ABNORMAL LDG GEAR

Preparation CABIN 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 If abnormal nose LDG GEAR CG LOCATION..............................................IF POSSIBLE, AFT If abnormal main LDG GEAR FUEL UNBALANCE .........................IF POSSIBLE, ESTABLISH Note: Reduced fuel on side with failed LDG GEAR.

Approach LDG GEAR LEVER ............................................. CONFIRM DOWN LDG GEAR EMER EXT HANDLE .....................CONFIRM PULLED ENG START ROTARY SELECTOR..............OFF / START ABORT CABIN REPORT........................................... CONFIRM OBTAINED

Before landing BLEEDS 1 + 2............................................................................ OFF BRACE FOR IMPACT ..........................................................ORDER

At touch down PL 1 + 2 .........................................................................................GI CL 1 + 2 .......................................................... FTR THEN FUEL SO

After touch down FIRE HANDLES 1 + 2 ..............................................................PULL

When aircraft stopped PARKING BRAKE ......................................................................SET CABIN CREW (PA).............................................................. NOTIFY FUEL PUMPS 1 + 2................................................................... OFF AGENTS 1 + 2 ....................................................................... DISCH EVACUATION ....................................................................INITIATE

Before leaving aircraft BAT ............................................................................................ OFF

2.2572

FOLLOWING FAILURESLANDING GEAR

SEP 10 001

LDG GEAR UNSAFE INDICATION

If LDG GEAR selected DOWN If GREEN LIGHT OFF on one panel only

UNSAFE INDICATION ........................................... DISREGARD If GREEN LIGHT OFF on both panels

LDG GEAR GRAVITY EXTENSION procedure (2.24) ....APPLY

If LDG GEAR selected UP If RED LIGHT ON on one panel only

UNSAFE INDICATION ........................................... DISREGARD If RED or GREEN LIGHT ON on both panels

LEAVE AND AVOID ICING CONDITIONSIAS ........................................................................... 160 KT MAXLDG GEAR ....................................................................... DOWNTCAS (if installed)......................................................... TA ONLY

LDG GEAR RETRACTION IMPOSSIBLE

LEAVE AND AVOID ICING CONDITIONSLDG GEAR LEVER..................................................................... DOWNIAS ..................................................................................... 185 KT MAXCCAS .............................................................................................. RCLTCAS (if installed) ................................................................... TA ONLYIDLE GATE ............................................................................MONITOR

ANTI-SKID FAULT

R ANTI SKID ...................................................................................... OFFLDG DIST ................................................................. MULTIPLY BY 1.4Note: Refer to Part 4 to determine LDG DIST

At touch downREVERSE............................................................................AS RQDNORMAL BRAKE .................................................USE WITH CAREBRAKE HANDLE ..................................................... EMER AS RQD

BRK TEMP HOT

If BRK TEMP HOT occurs before take offTAKE OFF .............................................................................DELAY

If BRK TEMP HOT occurs in flightLEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFFFOR COOLING EXCEPT IN CASE OF EMERGENCY

2.26

72

FOLLOWING FAILURES AIR

APR 08 001

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

BLEED OVHT

PACK VALVE affected side ............................................................ OFF BLEED VALVE affected side .......................................................... OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

BLEED LEAK

PACK VALVE affected side ............................................................ OFF BLEED VALVE affected side .......................................................... OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES CAUTION: System must not be restored in flight. Note: If a bleed leak occurs on ground during taxi, go back to parking.

X VALVE OPEN

CAUTION: Do not supply both packs from one single bleed.

PACK VALVE FAULT

PACK VALVE affected side ............................................................ OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

BOTH PACK VALVES FAULT

MAX FL ..................................................................................100 / MEA When ΔP < 1 PSI

OVBD VALVE ............................................................... FULL OPEN MAN RATE KNOB..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN MAN RATE KNOB................................................. MAX INCREASE

RECIRC FAN FAULT

RECIRC FAN affected side ............................................................ OFF

2.26A

72


OCT 08 001

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 possible pack 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

EXCESS CAB ALT

R

CABIN PRESS IND....................................................................CHECK

If rapid decompression EMERGENCY DESCENT procedure (1.07A) .......................APPLY

If Z cabin > 10000 ft confirmed MAN RATE KNOB..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN MAN RATE KNOB.........................................................DECREASE

If unsuccessful CREW OXYGEN MASKS............................................................ ON CREW COMMUNICATIONS .........................................ESTABLISH OXYGEN PAX SUPPLY......................................................AS RQD OXYGEN PRESSURE..........................................................CHECK DESCENT.................................................................AS RQD / MEA

AUTO PRESS FAULT

MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN MAN RATE KNOB ...............................AS RQD TO SET CABIN RATE

FL 140 170 200 250

TARGET CAB ALT (ft) 0 2000 4000 6750

Note: Minimum TARGET CAB ALT is landing elevation

EXCESS CAB ΔP

MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN MAN RATE KNOB ...................................................... MAX INCREASE

If unsuccessful DESCENT TO A COMPATIBLE FL....................................INITIATE

2.27

72


APR 08 001

AVIONICS VENT EXHAUST MODE FAULT

EXHAUST MODE ........................................................................ OVBD

OVBD VALVE FAULT

CAUTION: Do not select OVBD valve FULL OPEN if ΔP > 1 PSI.

If engine 1 running, in flight or on ground OVBD VALVE ............................................................. FULL CLOSE

If engine 1 not running, on ground OVBD VALVE ............................................................... FULL OPEN

2.28

72

FOLLOWING FAILURES DE/ANTI ICE

APR 08 500

AFR AIR BLEED FAULT

LEAVE AND AVOID ICING CONDITIONS AFR AIR BLEED............................................................................. OFF

If DE-ICING ENG FAULT light illuminates after 10 s DE-ICING ENG affected side .................................................... OFF AFR AIR BLEED.......................................................................... ON AFR AIR BLEED light ....................................CHECK EXTINGUISH

If DE-ICING ENG FAULT light does not illuminate on any side DE-ICING AIR FRAME FAULT procedure (2.28)..................APPLY

DE-ICING AIR FRAME FAULT

DE-ICING AIR FRAME ................................................................... OFF LEAVE AND AVOID ICING CONDITIONS MINIMUM ICING SPEEDS ................................... INCREASE BY 10 kt

If in icing conditions LDG DIST .......................................................... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine SPEEDS and LDG DIST

If ice accretion STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED

DE-ICING MODE SEL FAULT

OVRD........................................................................................SELECT MONITOR DE-ICING

In case of engine flame out OVRD................................................................................RELEASE

MODE SEL AUTO FAULT

MODE SEL .....................................................................................MAN DE-ICING and ANTI-ICING MANUAL MODE PBs: ACCORDING TO CURRENT SAT ...........................................SELECT

Model : 212A

2.29

72

FOLLOWING FAILURES DE/ANTI ICE

OCT 09 500

ICE DETECT FAULT

ICE ACCRETION................................................ VISUALLY MONITOR

DE-/ANTI-ICING ENG FAULT

LEAVE AND AVOID ICING CONDITIONS ENGINE PARAMETERS affected side..................................MONITOR

ANTI-ICING PROP FAULT

LEAVE AND AVOID ICING CONDITIONS ANTI-ICING PROP affected side.................................................... OFF

� If propeller unbalance due to ice becomes excessive CL 1 + 2 ......................... MOVE TO 100% OVRD FOR 5 MINUTES

ANTI-ICING HORNS FAULT

LEAVE AND AVOID ICING CONDITIONS

� If in icing conditions, every 5 minutes FLIGHT CONTROLS.............CHECK FREEDOM OF MOVEMENT

R

SIDE WINDOW / WINDSHIELD HTG

FAULT

SIDE WINDOW / WINDSHIELD HTG affected side....................... OFF

PROBES HTG FAULT

� If One PROBE HTG ALPHA illuminated STICK PUSHER / SHAKER .............................................MONITOR

� If Two PROBE HTG ALPHA illuminated STICK PUSHER / SHAKER ...................................................... OFF STICK PUSHER / SHAKER procedure (2.21).......................APPLY

� If PROBE HTG other than ALPHA illuminated ADC non affected side....................................................SELECTED Associated INDICATION ..................................................MONITOR

Mod : 3973 or 4371 or 4457

2.30

72

FOLLOWING FAILURES AUTO PILOT

OCT 08 550

AILERON MISTRIM (ADU message)

– or – EXCESSIVE LATERAL TRIM REQUIRED

– or – ABNORMAL FLIGHT CHARACTERISTICS

FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT

Note: FLY MANUALLY PRIOR TO ADJUSTING THE LATERAL TRIMS Note: The autopilot may be reengaged following adjustment of the lateral

trims

PITCH MISTRIM (ADU message)

FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS

PITCH TRIM FAIL (ADU message)

FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS

DADC DATA INVALID (ADU Message)

INSTRUMENTS............................................................CROSSCHECK FAULTY ADC......................................................................... IDENTIFY ADC SW............................................................... SELECT VALID ADC

If ADC 1 is wrong C/B ADC 1 EMER SPLY...........................................................PULL C/B MFC 1A AUX / ADC 1 HOT SPLY.....................................PULL

If ADC 2 is wrong C/B ADC 2 ................................................................................PULL ADC FAULT procedure (2.32) ...................................................APPLY

Mod : 3168 + 4366

2.30A

72

FOLLOWING FAILURES AND ABNORMAL

MPC APR 08 100

APPLICABLE TO AIRCRAFT FITTED WITH MODIFICATION 5567 or 8392 or 8442

APM FAULT

APM ..................................................................................................OFF

For troubleshooting see FCOM 2.02.21.

DEGRADED PERF

Mainly appears in level flight after CRUISE SPEED LOW or in climb, to inform the crew that an abnormal drag increase induces a speed decrease or a loss of rate of climb

The most probable reason is an abnormal ice accretion

AIRFRAME DE-ICING ON.........................................................CHECK IAS > RED BUG + 10 KT.......................................................MONITOR AP (if engaged) ................HOLD FIRMLY CONTROL WHEEL and DISENGAGE

If SEVERE ICING conditions confirmed – or – If impossibility to maintain IAS > RED BUG + 10 KT in level flight – or – If abnormal aircraft handling feeling

SEVERE ICING procedure (1.09) .........................................APPLY

If not

SCHEDULED FLIGHT....................................................CONTINUE ICING CONDITIONS and SPEED....................................MONITOR

INCREASE SPEED

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

If abnormal conditions confirmed

IMMEDIATELY PUSH THE STICK TO INCREASE SPEED TO RECOVER MINIMUM IAS = RED BUG + 10 KT

SEVERE ICING procedure (1.09) .........................................APPLY

2.31

72

FOLLOWING FAILURES AVIONICS

OCT 09 001

AUDIO SEL FAULT

AUDIO SEL affected side ............................................................. ALTN

AHRS A / ERECT FAIL

ATT / HDG PB affected side................................................. DEPRESS

� When possible AIRCRAFT.................................... STABILIZE SPEED AND LEVEL AHRS affected side, PUSH TO ERECT PB ......................................

.................................................DEPRESS FOR 15 SECONDS

EFIS COMP

RRRRRRRRRRRRRRRRRR

� If ROL, PIT, ATT, HDG cautions appears on EFIS BOTH EADI, STBY HORIZON ................................ CROSSCHECK WRONG INSTRUMENT................................................... 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

ADC SW FAULT

ADC SW........................................................ SET TO OPPOSITE ADC

2.32

72

FOLLOWING FAILURES AVIONICS

APR 08 550

ADU FAILURE

IAS / VS MODE.......................................................................USE TCS Note: ALT SEL mode is lost

If amber "AP MSG" appears on EADI or If in composite mode

FLIGHT CONTROLS................................................ HOLD FIRMLY AP ..............................................................................DISCONNECT

ADC FAULT

VALID ADC ...............................................................................SELECT PF..............................................................................NON affected side AP COUPLING .........................................................NON affected side ATC.................................................................NON affected equipment

If ADC 1 is lost LANDING ELEVATION ...................... PRESSURE ALTITUDE SET GPWS........................................................................................ OFF

If ADC 1 + 2 are lost STBY INST ................................................................................ USE MAN RATE KNOB..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN ENGINE PARAMETERS ..................................................MONITOR TCAS (if installed).................................................................... STBY GPWS........................................................................................ OFF TLU ................................................................................MAN MODE TLU FAULT procedure (2.22A) .............................................APPLY Note: If both ADC are lost, De-/Anti-Icing AUTO Mode Selection is lost.

AHRS FAIL

ATT / HDG PB affected side................................................. DEPRESS Periodically compare remaining AHRS outputs to STBY INST

SGU FAIL

EFIS SG PB affected side .................................................... DEPRESS

CRT FAIL

CRT affected................................................................................... OFF

Mod : 5205 Model : 212A

2.32A

72

FOLLOWING FAILURES MISCELLANEOUS

OCT 09 200

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 bolt(s), the emergency access to the cockpit is unavailable. It is recommended that at least two crewmembers remain in the cockpit during that time.

VOLCANIC ASH ENCOUNTER

FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180° TURN 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 AIRSPEED INDICATORS......................................................MONITOR

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

Note: In extreme case, it may be necessary to consider precautionary engine shut down and engine restart in flight. If both engines flame out, refer to BOTH ENGINE FLAME OUT procedure (1.03)

Note: Volcanic ash may clog the pitot probes resulting in unreliable speed indications. If airspeed is unreliable or lost, adjust airplane attitude and torque.

Mod: 4111

2.3372

FOLLOWING FAILURESMISCELLANEOUS

SEP 10 001

LOSS OF RADIO ALTIMETER INFORMATION

GPWS ............................................................................................. OFFTCAS (if installed) ......................................................................... STBY

CAUTION: LDG GEAR NOT DOWN undue warning may begenerated when reducing PL; this alarm may becancelled by using EMER AUDIO CANCEL.

R SMK DET FANS FAULT

FAN............................................................................................... ALTN

DOORS UNLK IN FLIGHT

If any door except FWD COMPTSIGNS.......................................................................................... ONASSOCIATED DOOR.........................................VISUALLY CHECK

If unlocked or check not feasibleLANDING ELEVATION .....................................................9000 ftMAX FL........................................................................100 / MEA

If FWD COMPTNO ACTION

COCKPIT WINDOW CRACKED

WINDOW HEAT affected................................................................ OFFLANDING ELEVATION................................................................9000 ftMAX FL ..................................................................................100 / MEA

OXYGEN LO PR

OXY MAIN SUPPLY ...................................................... OFF THEN ON

If OXYGEN LO PR light remains illuminatedMAIN SUPPLY........................................................................... OFFOXYGEN PORTABLE UNIT.......... INSTALL IN COCKPIT AS RQD

2.34

72

FOLLOWING FAILURES MFC

OCT 08 001

MFC 1A FAULT

R R

MODULE 1A .................................................................... OFF / RESET MFC 1A MODULE LOST EQUIPMENT LIST............................CHECK

R MFC 1A MODULE LOST EQUIPMENT LIST

MECHANIC CALL IND DC BUS 1 OFF WARNING AC BUS 1 SPLY INV 1 FAULT LIGHT

LDG GEAR PRIMARY UNLK IND BLEED HP VALVE 1 FWD COMPT DOOR UNLK IND EMER HATCH UNLK IND RIGHT AFT DOOR UNLK IND, if

applicable

MFC 1B FAULT

R R

MODULE 1B .................................................................... OFF / RESET MFC 1B MODULE LOST EQUIPMENT LIST............................CHECK

If failure during take off PACK 1 ...................................................................................... OFF OVBD VALVE ............................................................... FULL OPEN Prior take off PACK 2 ................................................................................. OFF After take off PACKS.................................................................................... ON OVBD VALVE........................................................ FULL CLOSE LDG GEAR ......LEAVE DOWN FOR COOLING FOR 1 MINUTE ..........AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY

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

CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and cockpit communication hatch must be open.

R MFC 1B MODULE LOST EQUIPMENT LIST

GROUND FAN 1 OUTFLOW VALVE OPENING AFTER

LANDING OVBD VALVE AUTO

FUNCTIONING CVR ERASE

DC STBY BUS UNDV DETECT INV 1 FAULT LIGHT GREEN PUMP LO PR IND BRAKE OVERTEMP ALERTS LH / RH BLEED VALVE 1 FAULT IND

2.35

72


OCT 08 001

MFC 2A FAULT

R R

MODULE 2A .................................................................... OFF / RESET AVIONICS VENT EXHAUST MODE ........................................... OVBD MFC 2A MODULE LOST EQUIPMENT LIST............................CHECK

If failure during taxi out OVBD VALVE ............................................................... FULL OPEN After take off IDLE GATE......................................................................CHECK OVBD VALVE.....................................................................AUTO

At touch down IDLE GATE .......................................................................MONITOR

After landing OVBD VALVE ............................................................... FULL OPEN

R MFC 2A MODULE LOST EQUIPMENT LIST

AIR X VALVE OVBD VALVE AUTO FUNCTIONING EXTRACT FAN HOSTESS CALL IND CREW CALL IND DC BUS 2 OFF WARNING AC BUS 2 SPLY INV 2 FAULT LIGHT

RH SIDE WINDOW ANTI-ICING LDG GEAR Secondary UNLK IND LDG GEAR Secondary GREEN

ARROWS BLEED HP VALVE 2 LEFT DOORS UNLK IND IDLE GATE AMBER WARNING

MFC 2B FAULT

R R

MODULE 2B .................................................................... OFF / RESET MFC 2B MODULE LOST EQUIPMENT LIST............................CHECK

Failure during take off PACK 2 ...................................................................................... OFF OVBD VALVE ............................................................... FULL OPEN 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 PACK 2 ...................................................................................... OFF OVBD VALVE ............................................................... FULL OPEN

CAUTION: Before opening any door, PACKS 1 and 2 must be selected OFF and cockpit communication hatch must be open.

R MFC 2B MODULE LOST EQUIPMENT LIST

GROUND FAN 2 OUTFLOW VALVE OPENING AFTER

LANDING OVBD VALVE AUTO FUNCTIONING INV 2 FAULT LIGHT RH SIDE WINDOW ANTI-ICING and

associated FAULT IND

LDG GEAR Secondary UNLK IND LDG GEAR Secondary GREEN

ARROWS RH BRAKE OVERTEMP ALERTS BLEED VALVE 2 FAULT IND

2.36

72


OCT 08 001

MFC 1A+1B FAULT

R R

MODULES 1A+1B ........................................................... OFF / RESET PROP 1 ANTI-ICING ...................................................................... OFF PROP ANTI-ICING FAULT procedure (2.29) .............................APPLY DE-ICING MODE SEL .................................................. OVRD AS RQD PACK 1 ........................................................................................... OFF BLEED 1 ......................................................................................... OFF BLEED VALVE FAULT procedure (2.26) ...................................APPLY RADAR ........................................................................................... OFF GPWS ............................................................................................. OFF MFC 1A+1B MODULES LOST EQUIPMENT LIST...................CHECK

Before landing ATPCS....................................................................................... OFF



R MFC 1A+1B MODULES LOST EQUIPMENT LIST

PACK 1 / PACK 1 FAULT IND GROUND FAN 1 OUTFLOW VALVE OPENING AFTER

LANDING OVBD VALVE AUTOFUNCTIONING MECHANIC CALL IND CVR ERASE DC STBY BUS UNDV DETECT DC BUS 1 OFF WARNING AC BUS 1 SPLY INV 1 FAULT LIGHT LEFT PFTS STICK PUSHER TRIPLE TRIM IND GREEN PUMP LO PR INDICATION ANTI-ICING PROP 1 and associated

FAULT IND

DE-ICING AIRFRAME (BOOTS A) DE-ICING AIRFRAME (BOOTS B) LH SIDE WINDOW ANTI-ICING and

associated FAULT IND PRIMARY UNLK IND PRIMARY GREEN ARROWS BRAKE OVERTEMP ALERTS LH / RH BLEED HP VALVE 1 BLEED VALVE 1 and associated

FAULT IND FWD COMPT DOOR UNLK IND EMER HATCH UNLK IND RIGHT AFT DOOR UNLK IND, if

applicable ENG 1 UPTRIM ENG 1 AUTO FEATHER LEFT AUTO CL

2.3772

FOLLOWING FAILURESMFC

OCT 08 001

MFC 1A+2A FAULT

R

R

R

MODULES 1A+2A ........................................................... OFF / RESETTLU .....................................................................................MAN MODEAVIONICS VENT EXHAUST MODE ........................................... OVBDRADAR ........................................................................................... OFFGPWS ............................................................................................. OFFMFC 1A+2A MODULES EQUIPMENT LIST .............................CHECKNote : 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 landingLDG GEAR LEVER ............................................................... DOWNEMER EXTENSION HANDLE..................................................PULL

CAUTION : LDG GEAR cannot be retracted.

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

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

R MFC 1A+2A MODULES LOST EQUIPMENT LIST

AIR X VALVEOVBD VALVE AUTOFUNCTIONINGEXTRACT FANAP OFF WARNING LIGHTALTITUDE ALERT LIGHTGUIDANCE LIGHTMECHANIC CALL INDHOSTESS CALL INDCREW CALL INDRECORDERS (START/STOP)DC BUS 1 + 2 OFF WARNINGAC BUS 1 + 2 SPLYINV 1 + 2 FAULT LIGHTEMER BAT CHG CTLFLAPS UNLK WARNINGSTICK PUSHER / SHAKER FAULTReleasable Centering Unit AUTO

DISCONNECT after YAW TRIMaction or YD engagement

TLU FAULT LIGHT

TRIPLE TRIM INDAIL LOCK LIGHT (if installed)DE-ICING AIRFRAME FAULTRH SIDE WINDOW ANTI-ICINGCCAS WARNING ALERT (FLAP

UNLK)LDG GEAR CONTROLLDG GEAR PRIMARY UNLK INDLDG GEAR Secondary UNLK INDLDG GEAR Secondary GREEN

ARROWSLIGHT TESTBLEED HP VALVE 1 + 2LEFT DOORS UNLK INDFWD COMPT DOOR UNLK INDEMER HATCH UNLK INDRIGHT AFT DOOR UNLK IND, if

applicableRIGHT FWD DOOR UNLK INDIDLE GATE and associated AMBER

WARNING

2.3872


OCT 08 001

MFC 1A+2B FAULT

R

R

R

MODULES 1A+2B ........................................................... OFF / RESETMAIN BLUE HYD PUMP................................................................. OFFHYD X FEED .................................................................................... ONDE-ICING MODE SEL .................................................. OVRD AS RQDMFC 1A+2B MODULES EQUIPMENT LIST .............................CHECKNote : AP does not disconnect after STBY PITCH TRIM activation.

Before landingNote : Flaps control is lost.REDUCED FLAPS LANDING procedure (2.21)....................APPLYLDG GEAR LEVER ............................................................... DOWNEMER EXTENSION HANDLE..................................................PULL


After landingPACK 2 ...................................................................................... OFFOVBD VALVE ................................................................FULL OPEN

CAUTION : Before opening any door, PACKS 1 and 2 must be selectedOFF and cockpit communication hatch must be open.


GROUND FAN 2OUTFLOW VALVE OPENING AFTER

LANDINGOVBD VALVE AUTOFUNCTIONINGMECHANIC CALL INDDC BUS 1 OFF WARNINGAC BUS 1 SPLYINV 1 + 2 FAULT LIGHTFLAPS CONTROLBLUE HYD PUMP CTLDE-/ANTI-ICING ENG 1DE-/ANTI-ICING ENG 2 FAULT

RH SIDE WINDOW ANTI-ICING andassociated FAULT IND

LDG GEAR CONTROLLDG GEAR PRIMARY UNLK INDLDG GEAR Secondary UNLK INDLDG GEAR Secondary GREEN

ARROWSBRAKE OVERTEMP ALERT RHBLEED HP VALVE 1BLEED VALVE 2 FAULT INDFWD COMPT DOOR UNLK INDEMER HATCH UNLK INDRIGHT AFT DOOR UNLK IND, if

applicable

2.3972


OCT 08 001

MFC 1B+2A FAULT

R

RR

MODULES 1B+2A ........................................................... OFF / RESETDE-ICING MODE SEL .................................................. OVRD AS RQDAVIONICS VENT EXHAUST MODE ........................................... OVBDMFC 1B+2A MODULES EQUIPMENT LIST .............................CHECKNote : VOR 2, ADF 2, CRS 2 information are lost. CM2 IAS is not

available.

Before landingNote : Flaps control is lost.REDUCED FLAPS LANDING procedure (2.21)....................APPLYLDG GEAR LEVER ............................................................... DOWNEMER EXTENSION HANDLE..................................................PULL


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

After landingPACK 1 ...................................................................................... OFFOVBD VALVE ................................................................FULL OPEN

CAUTION : Before opening any door, PACKS 1 and 2 must be selectedOFF and cockpit communication hatch must be open.

R MFC 1B+2A MODULES LOST EQUIPMENT LIST

GROUND FAN 1AIR X VALVEOUTFLOW VALVE OPENING AFTER

LANDINGOVBD VALVE AUTOFUNCTIONINGEXTRACT FANHOSTESS CALL INDCREW CALL INDCVR ERASEDC STBY BUS UNDV DETECTDC BUS 2 OFF WARNINGAC BUS 2 SPLYINV 1 FAULT LIGHTINV 2 FAULT LIGHT

FLAPS CONTROLGREEN PUMP LO PR INDICATIONDE-/ANTI-ICING ENG 1 FAULTDE-/ANTI-ICING ENG 2RH SIDE WINDOW ANTI-ICINGLDG GEAR CONTROLLDG GEAR Secondary UNLK INDLDG GEAR Secondary GREEN

ARROWSBRAKE OVERTEMP ALERTS LH / RHBLEED HP VALVE 2BLEED VALVE 1 FAULT INDLEFT DOORS UNLK INDIDLE GATE AMBER WARNING

2.40

72


OCT 08 001

MFC 2A+2B FAULT

R R

MODULES 2A+2B ........................................................... OFF / RESET AVIONICS VENT EXHAUST MODE ........................................... OVBD ANTI-ICING PROP 2 ...................................................................... OFF ANTI-ICING PROP FAULT procedure (2.29) .............................APPLY DE-ICING MODE SEL .................................................. OVRD AS RQD PACK 2 ........................................................................................... OFF BLEED 2 ......................................................................................... OFF BLEED VALVE FAULT procedure (2.26) ...................................APPLY MFC 2A+2B MODULES EQUIPMENT LIST .............................CHECK

Before landing ATPCS....................................................................................... OFF

At touch down IDLE GATE .......................................................................MONITOR




PACK 2 PACK 2 FAULT IND GROUND FAN 2 AIR X VALVE OUTFLOW VALVE OPENING AFTER

LANDING OVBD VALVE AUTOFUNCTIONING EXTRACT FAN HOSTESS CALL IND CREW CALL IND DC BUS 2 OFF WARNING AC BUS 2 SPLY INV 2 FAULT LIGHT STICK PUSHER ANTI-ICING PROP 2 ANTI-ICING PROP 2 FAULT DE-ICING AIRFRAME (BOOTS B)

RH SIDE WINDOW ANTI-ICING and associated FAULT IND

LDG GEAR Secondary UNLK IND LDG GEAR Secondary GREEN

ARROWS BRAKE OVERTEMP ALERT RH BLEED HP VALVE 2 BLEED VALVE 2 BLEED VALVE 2 FAULT IND LEFT DOORS UNLK IND ENG 2 UPTRIM ENG 2 AUTO FEATHER PROP BRAKE BRAKING if applicable PROP BRAKE RELEASING if

applicable IDLE GATE AMBER WARNING RIGHT AUTO CL

2.41

72


OCT 08 001

MFC 1B+2B FAULT

R R

MODULES 1B+2B ........................................................... OFF / RESET OVERHEAD PANEL..............................................................MONITOR MFC 1B+2B MODULES EQUIPMENT LIST .............................CHECK

Before landing NOSE WHEEL STEERING ....................................................... OFF ANTI-SKID ................................................................................. OFF ANTI-SKID FAULT procedure (2.25).....................................APPLY LDG GEAR LEVER ............................................................... DOWN EMER EXTENSION HANDLE..................................................PULL


At touch down IDLE GATE ...............................................................................PULL DIFFERENTIAL BRAKING........................................................ USE

After landing PACK 1 + 2 ................................................................................ OFF ANTI-ICING HORNS ................................................................. OFF PROBES HTG ........................................................................... OFF OVBD VALVE ............................................................... FULL OPEN Note : ATPCS ARM light is not available. Autofeather light is lost. Note : External power cannot be used.


R MFC 1B+2B MODULES LOST EQUIPMENT LIST

GROUND FAN 1 GROUND FAN 2 AIR X VALVE OUTFLOW VALVE OPENING AFTER

LANDING OVBD VALVE AUTOFUNCTIONING CVR ERASE DC STBY BUS UNDV DETECT INV 1 FAULT LIGHT INV 2 FAULT LIGHT MAIN BAT CHG CTL BAT DISCHARGE IN FLIGHT FLAPS ASYMMETRY DETECTION STICK PUSHER INHIBITION STICK SHAKER STALL WARNING PITCH TRIM WHOOLER PITCH TRIM ASYMWARNING AIL LOCK LIGHT if applicable GREEN PUMP LO PR INDICATION RH SIDE WINDOW ANTI-ICING and

associated FAULT IND INHIBITION OF HORNS ANTI-ICING

ON GROUND

CCAS MASTER WARNING CCAS MASTER CAUTION CCAS AURAL ALERTS CCAS AMBER ALERTS ON CAP CCAS WARNING ALERTS (CONFIG,

PROP BRK, ENG OIL) LDG GEAR CONTROL LDG GEAR Secondary UNLK IND LDG GEAR Secondary GREEN

ARROWS BRAKE OVERTEMP ALERTS LH / RH LDG GEAR LEVER LOCKED DOWN

ON GROUND NOSE WHEEL STEERING ANTI-SKID "LANDING GEAR NOT DOWN"

WARNING BLEED VALVE 1 FAULT IND BLEED VALVE 2 FAULT IND ARM LIGHT IND PROP BRAKE RED UNLK LT if

applicable LEFT and RIGHT AUTO CL

2.42

72


APR 08 150

DC EMER BUS LOST EQUIPMENT LIST

DC ESS BUS LOST EQUIPMENT LIST

AIR CONDITIONING OVBD and Underfloor Valves CTL OVBD and Underfloor Valves IND AIR COOLING high flow IND PRESS IND / EXCESS ALT IND Pneumatic Outflow Valves FWD COMPT Ventilation Valve (*) AUTO PILOT AP/FD Computer GUIDANCE IND COMMUNICATIONS VHF / RCAU CM2 Cockpit Amplifier ELECTRICAL POWER AC BUS OFF 1 + 2 IND ACW BUS OFF 1 + 2 IND INV 1 FAULT IND DC BUS OFF 1 + 2 IND DC STBY BUS IND (UNDV/OVRD) EMER BAT CHG IND FIRE PROTECTION FIRE HANDLE IND ENG 1 + 2 FIRE DETECTION ENG 1 + 2 FLIGHT CONTROLS PITCH TRIM NORMAL COMMAND RUDDER TRIM AILERON TRIM HYDRAULIC POWER BLUE PUMP CTL and IND GREEN PUMP IND ICE AND RAIN PROTECTION AAS CTL, IND and ALERTS WING, EMPENNAGE BOOTS A ENG 1 BOOTS A and B PROP 1 + 2 ANTI-ICING CTL PROP 1 + 2 ANTI-ICING IND HORNS ANTI-ICING IND and CTL INDICATING / RECORDING CM1 CLOCK FDAU on ground LANDING GEAR ANTI-SKID Outboard NOSE WHEEL STEERING WOW 1 CTL LIGHTS CM1 PANELS PYLON STBY COMPASS LAVATORY (EMER) NAVIGATION ATC 1 PROPELLERS A/F AUX PUMPS CTL TQ IND 1 + 2 ENGINES CL FIRE IND 1 + 2 (*): if applicable

AIR CONDITIONING PACK and RECIRC FAN 1 + 2 IND PACK 1 + 2 Valve EXTRACT FAN CTL Landing Elevation IND Cockpit and Cabin Automatic and Manual TEMP CTL and IND AUTO PILOT AP OFF IND and DISC by Quick Disconnect COMMUNICATIONS CM1+2 Flight Interphones CM1+2 Audio Control Panels CM1 Cockpit Amplifier CVR / Passenger Address Mechanical CALL Cockpit and Cabin Crew CALL ELECTRICAL POWER DC SVCE/UTLY BUS 1 + 2 CTL MAIN BAT CHG IND INV 2 FAULT IND FIRE PROTECTION Avionics / Toilets SMK DET FWD and AFT COMPT SMK DET AFT COMPT and FWD COMPT /Toilets DET FANS CTL and IND FWD COMPT Fire Extinguishing CTL, IND and TEST (*) AUX AFT COMPT (*) See 2.42A for Cargo Operations FLIGHT CONTROLS Clutch Reengagement System (*) AILERON Locking CTL FUEL FQI 1 + 2 X FEED Valve Starting Pumps 1 + 2 Motive Flow Valves 1 + 2 HYDRAULIC GREEN PUMP CTL ICE AND RAIN PROTECTION DE-ICING ISOL Valves Side Windows ANTI-ICING IND CAPT/STBY/TAT PROBES IND CM1 Wiper INDICATING / RECORDING FDAU in flight LIGHTS Landing CTL NAVIGATION TAS TEMP IND OXYGEN PRESS IND Pilots and Pax Valves CTL Pax Masks DROP CTL PNEUMATIC BLEED Valves PWR and IND 1 + 2 PROPELLERS NP IND 1 + 2 PROP BRK PWR, CTL and IND ENGINES IGNITION and STARTING 1 + 2 NH/NL, ITT IND 1 + 2

Mod : 4116 + 4366

3.0172

NORMAL PROCEDURESNOV 11 001

3 - NORMAL PROCEDURESAll steps have to be performed before the first flight of the day orfollowing a crew change or maintenance action. In other cases, start atFINAL COCKPIT PREPARATION.

With the USE OF GPU (DC)(Refer to page 3.04 to 3.06 for HOTEL MODE)

EXTERIOR INSPECTION

CM1 CM2

Exterior walk around performed

PRELIMINARY COCKPIT PREPARATION (On GPU)

CM1 CM2EMER EQPT...............................CHECKGEAR PINS & COVERS...... ON BOARDC/Bs ............................................CHECKPL 1 + 2 .............................................. GIGUST LOCK............................ENGAGECL 1 + 2...................................FUEL SOFLAPS LEVER............................CHECKLDG GEAR ..................................DOWNEEC 1+2.............................................ONWIPERS ...................................……OFFSTBY HORIZON ERECT……….…PULLBAT....................................................ONMFC AUTO TEST.......................CHECKEMER & BUS SUPPL IND ……..CHECKUNDV LT……………………….....CHECKDC EXT PWR P/B..............................ON

ANN LT………………………………TEST

OVERHEAD PANELDOME LT………………………AS RQRDSTBY COMPASS LT.........CHECK&OFFSTORM LT…………………CHECK&OFFCALL & SELCAL(If installed) LT…...OFFMIN CAB LT…………………………..OFFFUEL PUMPS & XFEED………..…TESTDOORS .…………………………….TESTSPOILERS LTs…………………........OFFLDG GEAR IND…3 GREEN/NO RED LTTLU ..………………………………..AUTOSELCAL (If installed)…….CHECK CODEENG 1 FIRE................................... TESTEXT LT…….…………………...AS RQRDPROP BRK…................... ON / LOCKEDENG START….......OFF/START ABORTMAIN ELEC PWR…..……………CHECKCVR & DFDR................................. TESTSIGNS ........................................CHECKEMER EXIT LT ............................... ARMDE / ANTI ICING LT…..EXTINGUISHEDPROBES HTG ……………………....OFFWINDSHIELD HTG…………………..ONAC WILD ELEC PWR……………CHECKHYD PWR………………………...CHECKEMER LOC XMTR........................ AUTO

3.0272


PRELIMINARY COCKPIT PREPARATION (On GPU)(CONT'D)

CM1 CM2ANN LT SW………………… .AS RQRDAIR BLEED / COMPT TEMP…...CHECKAVIONICS VENT ……………..…CHECKOVBD VALVE............................... AUTOOXYGEN PRESS .......................CHECKOXYGEN MAIN SUPPLY…………….ONPAX SUPPLY…………………NO LIGHTCOMPT SMK ................................ TESTEXHAUST MODE ....................... RESETENG 2 FIRE…………………………TEST

PEDESTALATPCS..........……………………….TESTTCAS ……...………...……..STBY / TESTTRIMS .......................................CHECK(A full test has to be perform for the firstflight of the day)STBY PITCH TRIM……………...CHECKSTBY PITCH TRIM…….GUARDED/OFFRCDR…CHECK DATA FDEP or MCDUCOM / ADF …………...……….ON /TESTXPDR (ATC)……………… STBY / TESTIDLE GATE.................................CHECKEMER AUDIO CANCEL .............CHECKPARKING BRK………………………...ONGUST LOCK…………………………...ONAIL LOCK LT…………. EXTINGUISHEDEFIS CTRL PANEL ............... TEST/SETRADAR ..........................................STBYCOCKPIT DOOR LK SYS…...….CHECK

CENTRAL PANELFUEL QUANTITY ………TEST / CHECKICE DETECT PANEL…..TEST / CHECKCAP………………………………..CLEARPEC 1 + 2 ..........................................ONBOOST (if installed) ……...…..…CHECK(A full test has to be perform daily)PWR MGT ......................................... TOSTBY INSTR…………CHECK NO FLAGENG FUEL USED……………..…RESETENG INSTR & PANEL ………….CHECKMEMO PANEL ……………...…...CHECKCAB PRESS MODE SEL............. NORMAUTO PRESS………...…TEST / CHECKCAB PRESS IND ………...……...CHECKSTICK PUSHER…..……………..CHECKRUD TLU ………LO SPD ILLUMINATEDFLAPS IND ……………...……….CHECKFLAPS ASYM LT……...EXTINGUISHEDPITCH TRIM ASYM LT.EXTINGUISHEDBRK TEMP HOT LT…..EXTINGUISHEDANTI SKID…….DEPRESSED IN/NO LTHYD GAUGES……………………CHECK

Mod: 3973 or 4371 or 4457

3.03

72

NORMAL PROCEDURES NOV 11 100

PRELIMINARY COCKPIT PREPARATION (On GPU)

(CONT'D)

CM1 CM2

GLARESHIELD FD BARS………………………BOTH ON VOR/ILS 1&2…………………..TEST/ON ADU BRT......................................... SET

LEFT LATERAL CONSOLE COCKPIT COM HATCH…………..OPEN STICK PUSHER/SHAKER(once a day)….. ………………………………………..TEST WARN ROT SEL…………….NORM FLT N/W STEERING………...GUARDED/ON OXYGEN MASK (once a day) ....... CHECK

RIGHT LATERAL CONSOLE EXTR AIRFLOW........OPEN/ GUARDED OXYGEN MASK (once a day) ........CHECK

LEFT SWITCHING PANEL MKR …………………………………….LO AUDIO 1SEL .......................... ..CHECK AHRS1 ……………………………CHECK CAPT SWITCHING PANEL….....CHECK EGPWS / TAWS........GUARDED/NORM TERR…………………GUARDED/NO LT STEEP APP(if installed)…………CHECK

LEFT SWITCHING PANEL F/O SWITCHING PANEL……….CHECK AUDIO 2 SEL..............................CHECK AHRS 2 …………………………..CHECK

LEFT INSTRUMENT PANEL CLOCK TIME .................……………SET AIRSPEED…............CHECK / NO FLAG RMI / EHSI …………...…X CHECK HDG EADI…………………………CHECK ATT EGPWS TEST …………….…PERFORM GPWS G/S P/B……..CHECK NO LIGHT ALTIMETER.............CHECK / NO FLAG VSI…………………………………CHECK TAT/SAT IND……………………..CHECK ADC SWITCH……………………….1 or 2 DSP SEL………………………….CHECK

RIGHT INSTRUMENT PANEL APM TEST……………………PERFORM GPWS G/S P/B……..CHECK NO LIGHT ALTIMETER.............CHECK / NO FLAG VSI…………………………………CHECK DSP SEL………………………….CHECK RMI / EHSI …………...…X CHECK HDG EADI…………………………CHECK ATT AIRSPEED…............CHECK / NO FLAG CLOCK TIME................. ……………SET

Mod: 3973 or 4371 or 4457

3.0472


3 - NORMAL PROCEDURESAll steps have to be performed before the first flight of the day orfollowing a crew change or maintenance action. In other cases, start atFINAL COCKPIT PREPARATION.

With the USE of HOTEL MODE

(Refer to page 3.01 to 3.03 for EXTERIOR INSPECTION and for GPU)

PRELIMINARY COCKPIT PREPARATION (Hotel mode)

CM1 CM2EMER EQPT...............................CHECKGEAR PINS & COVERS...... ON BOARDC/Bs ............................................CHECKPL 1 + 2 .............................................. GIGUST LOCK............................ENGAGECL 1 + 2...................................FUEL SOFLAPS LEVER............................CHECKLDG GEAR ..................................DOWNEEC 1+2.............................................ONWIPERS ...................................……OFFSTBY HORIZON ERECT……….…PULLBAT....................................................ONMFC AUTO TEST.......................CHECKEMER & BUS SUPPL IND ……..CHECKUNDV LT……………………….....CHECKENG 2 FIRE ……………………….. TESTATPCS TEST…………...…....PERFORMSERVICE DOOR ………...…….CLOSEDFUEL PUMP 2…………………………ONWING LT………………………………..ONPROP BRK………………....ON/LOCKEDENG 2 …….....START IN HOTEL MODE

ANN LIGHT.................................... TEST

OVERHEAD PANELDOME LT………………………AS RQRDSTBY COMPASS LT.........CHECK&OFFSTORM LT…………………CHECK&OFFCALL & SELCAL(If installed) LT…...OFFMIN CAB LT…………………………..OFFFUEL PUMPS & XFEED………..…TESTDOORS .…………………………….TESTSPOILERS LTs…………………........OFFLDG GEAR IND…3 GREEN/NO RED LTTLU ..………………………………..AUTOSELCAL (If installed)…….CHECK CODEENG 1 FIRE................................... TESTEXT LT…….…………………...AS RQRDPROP BRK…................... ON / LOCKEDENG START….......OFF/START ABORTMAIN ELEC PWR…..……………CHECKCVR & DFDR................................. TESTSIGNS ........................................CHECKEMER EXIT LT ............................... ARMDE / ANTI ICING LT…..EXTINGUISHEDPROBES HTG ……………………....OFFWINDSHIELD HTG…………………..ONAC WILD ELEC PWR……………CHECKHYD PWR………………………...CHECKEMER LOC XMTR........................ AUTO

3.0572


PRELIMINARY COCKPIT PREPARATION (Hotel mode)(CONT'D)

CM1 CM2ANN LT SW………………… .AS RQRDAIR BLEED / COMPT TEMP…...CHECKAVIONICS VENT ……………..…CHECKOVBD VALVE............................... AUTOOXYGEN PRESS .......................CHECKOXYGEN MAIN SUPPLY…………….ONPAX SUPPLY…………………NO LIGHTCOMPT SMK ................................ TESTEXHAUST MODE ....................... RESET

PEDESTALTCAS ……...………...……..STBY / TESTTRIMS…………………………….CHECK(A full test has to be perform for the firstflight of the day)STBY PITCH TRIM……………...CHECKSTBY PITCH TRIM…….GUARDED/OFFRCDR…CHECK DATA FDEP or MCDUCOM / ADF …………...……….ON /TESTXPDR (ATC)……………… STBY / TESTIDLE GATE.................................CHECKEMER AUDIO CANCEL .............CHECKPARKING BRK………………………...ONGUST LOCK…………………………...ONAIL LOCK LT…………. EXTINGUISHEDEFIS CTRL PANEL ............... TEST/SETRADAR ..........................................STBYCOCKPIT DOOR LK SYS…...….CHECK

CENTRAL PANELFUEL QUANTITY ………TEST / CHECKICE DETECT PANEL…..TEST / CHECKCAP………………………………..CLEARPEC 1 + 2 ..........................................ONBOOST (if installed) ……...…..…CHECK(A full test has to be perform daily)PWR MGT ......................................... TOSTBY INSTR…………CHECK NO FLAGENG FUEL USED……………..…RESETENG INSTR & PANEL ………….CHECKMEMO PANEL ……………...…...CHECKCAB PRESS MODE SEL............. NORMAUTO PRESS………...…TEST / CHECKCAB PRESS IND ………...……...CHECKSTICK PUSHER…..……………..CHECKRUD TLU ………LO SPD ILLUMINATEDFLAPS IND ……………...……….CHECKFLAPS ASYM LT……...EXTINGUISHEDPITCH TRIM ASYM LT.EXTINGUISHEDBRK TEMP HOT LT…..EXTINGUISHEDANTI SKID…….DEPRESSED IN/NO LTHYD GAUGES……………………CHECK

R
Mod: 3973 or 4371 or 4457

3.0672


PRELIMINARY COCKPIT PREPARATION (Hotel mode)(CONT'D)

CM1 CM2

GLARESHIELDFD BARS………………………BOTH ONVOR/ILS 1&2…………………..TEST/ONADU BRT......................................... SET

LEFT LATERAL CONSOLECOCKPIT COM HATCH…………..OPENSTICK PUSHER/SHAKER(once a day)…..………………………………………..TESTWARN ROT SEL…………….NORM FLTN/W STEERING………...GUARDED/ONOXYGEN MASK (once a day) ....... CHECK

RIGHT LATERAL CONSOLEEXTR AIRFLOW........OPEN/ GUARDEDOXYGEN MASK (once a day) ........CHECK

LEFT SWITCHING PANELMKR …………………………………….LOAUDIO 1SEL .......................... ..CHECKAHRS1 ……………………………CHECKCAPT SWITCHING PANEL….....CHECKEGPWS / TAWS........GUARDED/NORMTERR…………………GUARDED/NO LTSTEEP APP(if installed)…………CHECK

LEFT SWITCHING PANELF/O SWITCHING PANEL……….CHECKAUDIO 2 SEL..............................CHECKAHRS 2 …………………………..CHECK

LEFT INSTRUMENT PANELCLOCK TIME ................. ……………SETAIRSPEED…............CHECK / NO FLAGRMI / EHSI …………...…X CHECK HDGEADI…………………………CHECK ATTEGPWS TEST …………….…PERFORMGPWS G/S P/B……..CHECK NO LIGHTALTIMETER.............CHECK / NO FLAGVSI…………………………………CHECKTAT/SAT IND……………………..CHECKADC SWITCH……………………….1 or 2DSP SEL………………………….CHECK

RIGHT INSTRUMENT PANELAPM TEST……………………PERFORMGPWS G/S P/B……..CHECK NO LIGHTALTIMETER.............CHECK / NO FLAGVSI…………………………………CHECKDSP SEL………………………….CHECKRMI / EHSI …………...…X CHECK HDGEADI…………………………CHECK ATTAIRSPEED…............CHECK / NO FLAGCLOCK TIME................. ……………SET

Mod: 3973 or 4371 or 4457

3.0772


FINAL COCKPIT PREPARATION

CM1 CM2

AIRFIELD DATA ……………..…OBTAINLANDING ELEVATION. ................... SET

PF PNF

GNSS HT1000 Programming(if applicable)

INIT………………………………..CHECK

NAV …………………………….…… SET

PERF…….........................................SET

NAVAIDS / NAV SOURCES ........ …SETCOM …………………………………..SET

NAV ………………...…………… CHECK

PERF ……….…..........................CHECK

NAVAIDS / NAV SOURCES ............ SETCOM……………………...……………SET

CM1 CM2

PARKING BRK........ON/PRESS CHECKSIGNS….……….………………..…….ONMEMO PANEL ........................... CHECKFUEL QTY / FOB ...........………..CHECKFUEL USED……………………….RESETALTIMETERS...................................SETTQ BUGS…………………SET & CHECKSEATS, SEATS BELT, HARNESS,RUDDER PEDALS.....................ADJUSTDEPART BRIEFING............ COMPLETE

ALTIMETERS .................................. SETTQ BUGS…………………SET & CHECKSEATS, SEATS BELT, HARNESS,RUDDER PEDALS.....................ADJUSTDEPART BRIEFING ............COMPLETE

FINAL COCKPIT PREPARATION C/L

3.0872


HOTEL MODE START UPCM1 CM2

SERVICE DOOR ………...…….CLOSEDFUEL PUMP 2 …………………….…..ONWING LIGHTS …………………..…….ONPROP BRK.......................ON / LOCKEDENGINE 2 .………………………..START- ENGINE & PROP AREA ………CLEAR- ENG START………………..START A/B- START 2 P/B………DEPRESSED / ON- ENG ROTATION (NH) ……..MONITOR

When passing 10 % NH(maximum 19% NH if ITT > 200°c)

- CL 2 …..……………….……..........FTR- ITT rises within 10s…...…….…CHECK- Oil Pressure…………………….CHECK

When passing 45 % NH

- START P/B ON LT…..EXTINGUISHED

When engine parameters stabilized

- ENG START….OFF & START ABORT- GPU……........................................OFF- DC GEN 2 ……………..……..ON LINE- DC BTC .…………...CHECK CLOSED- BLEED / PACK XVALVE……………………………………………CHECK OPEN- PL 1 + 2…………..ADJUST AS RQRD

3.0972


BEFORE PROPELLER ROTATION

CM1 CM2

LOADSHEET ……...……………..CHECKGNSS WEIGHT & FUEL........…UPDATESPEED BUGS................. SET & CHECKTRIMS ........................................ CHECK

TAIL PROP ..........................ON BOARDDOORS .................................... CLOSEDSEAT BELTS......................................ONBEACON………………………….. ......ONNWS (if push back)………………..…OFF

GNSS WEIGHT & FUEL........…UPDATESPEED BUGS................. SET & CHECKTRIMS.............................................. SETSTART UP CLEARANCE………OBTAIN

CDLS .................................................ON

BEFORE PROPELLER ROTATION C/L

BEFORE TAXI

CM1 CM2

PROP BRK RDY LT....................CHECKPROP BRK SW ................................OFF

COCKPIT COM HATCH… ....... CLOSEDNWS……………….……...………….…ON

When NP stabilized

CL 2 .............................................. AUTOSGL CH……………….………..…CHECKLO PITCH ………………………...CHECKACW GEN 2……………………..ON LINEACW BTC……………………….CLOSEDHYD……………………………….CHECKANTI-ICING................................AS RQDANTI-SKID ..................................... TESTFLAPS .......................................... ….15°

ENGINE 1 …………………...……START

When NP stabilized

CL 1. ............................................. AUTOSGL CH………………..……….…CHECKLO PITCH ………………...………CHECKACW GEN 1……………………..ON LINEACW BTC .....................................OPENXPDR……………………...AS REQUEST

BEFORE TAXI C/L

TAXI

CM1 CM2

TAXI & TO LIGHTS ............................ONBRAKES…………………………..CHECKINSTRUMENTS………………… CHECK

AFCS ......................................... CHECK

TO DATA …………………………CHECK

TAKE OFF BRIEFING......... COMPLETECABIN REPORT …………….OBTAINED

TAXI CLEARANCE ……………..OBTAIN

BRAKES .....................................CHECKINSTRUMENTS………………… CHECK

AFCS .............................................. SETTO CONFIG................................... TEST

ATC CLEARANCE ……………...OBTAINTO DATA …………………………CHECKTAKE OFF BRIEFING .........COMPLETE

TAXI C/L

Mod: 3973 or 4371 or 4457

3.10

72


BEFORE TAKE OFF CM1 CM2

FLIGHT CONTROLS……..………CHECK CCAS ………………………….………RCL CCAS…………………….………TO INHIB OVERHEAD PANEL ………...........SCAN

----------------- EXT LIGHTS……………………………ON

When lined up

FD BAR ….…………………...CENTERED RUDDER CAM ………………CENTERED

GUST LOCK…………………...RELEASE FLIGHT CONTROLS ……………CHECK TCAS……… ……….......................AUTO XPDR…………………………….........ALT APM ROT SEL …SELECT T/O WEIGHT AIR FLOW …………………………NORM

----------------- BLEED VALVES…………………AS RQD

When lined up

FD BAR ……………………..CENTERED

BEFORE TAKE OFF C/L

TAKE OFF

CM1 CM2

BRAKES ........................... RELEASED PL1+2....................................... NOTCH

“ATPCS ARM”……...CHECK & ANNOUNCE ENGINE PARAMETERS...................CHECK “POWER SET”...........................ANNOUNCE

When reaching 70 Kt

“SEVENTY KNOTS”………...….ANNOUNCE

Mod : 4111

3.1172


TAKE OFF (CONT’D)

PF PNF

When reaching 70 Kt

“I HAVE CONTROL”….....ANNOUNCE

ROTATION ........................ PERFORM

“GEAR UP” ............................ORDER

“CLIMB SEQUENCE” .............ORDER- PL 1 + 2…………………………………………….SET/CHECK IN THE NOTCH

When passing WHITE BUG(ICING BUG in Icing condition)

“FLAPS ZERO” ....................... ORDER

When cleared to a FL

“SET STD”........................ANNOUNCEALTIMETERS 1 + 2……………………………..…SET STD & CROSS CHECK

“V1”.........................................ANNOUNCE

When reaching VR

“ROTATE”..............................ANNOUNCE

After LIFT OFF

“ POSITIVE RATE”..............ANNOUNCE

LDG GEAR LEVER.............. SELECT UPYD……………........................... ENGAGETAXI & TAKE OFF LIGHT ……….....OFFLDG GEAR LT……………………………………………..CHECK EXTINGUISHED

When passing ACCELERATIONALTITUDE

“ACCELERATION ALTITUDE”…………..……………………………..….ANNOUNCE

- IAS ......INCREASE ABOVE WHITE BUG- PL 1 + 2.............CHECK IN THE NOTCH- PWR MGT ....................................CLIMB- NP................................................CHECK- BLEEDs .............................................ON- SPEED TARGET…….…... SET to 170 kt

“CLIMB SEQUENCE COMPLETE”……….…………………………………ANNOUNCE

FLAPS ZERO ............................ SELECT

ALTIMETERS 1 + 2…………………………………….SET STD & CROSS CHECK

AFTER TO CHECK LIST

Mod: 3973 or 4371 or 4457

3.1272


CLIMB

CM1 PNF

SEAT BELTS........................AS RQRD

Crossing FL 100 climbing

LANDING LIGHTS ..............................OFFPRESSURIZATION………………..CHECK

CRUISE

PF PNF

CRUISE TQ & SPEEDS….….…CHECK

At Cruise FL

SAT ..............................................CHECKCRUISE PARAMETER…...…..COMPUTE

Reaching Cruise Speed

PWR MGT..........................................CRZCRUISE PARAMETER…………...CHECKALL SYSTEM…PERIODICALLY..CHECKFUEL.............................................CHECK

DESCENT PREPARATION

PF PNF

CCAS.…………………..………...…..RCLSTBY QNH (CM1)…………………...SET

GNSS PREPARATION…….. …...…SET

NAVAIDS / NAV SOURCES………..SETASI BUGS..……………………..……SET

DH /MDA….………………SET/CHECKARRIVAL BRIEFING............COMPLETE

LANDING DATA …………………..OBTAINLDG ELEVATION…..……………...CHECK

NAVAIDS / NAV SOURCES……….…SETASI BUGS ………………………………SETTQ BUGS ……………………………….SET

DH /MDA….………………..…SET/CHECKARRIVAL BRIEFING…………COMPLETE

DESCENT C/L

DESCENT

PF PNF

DESCENT ……………….…INITIATE

When passing FL 100

SEAT BELTS (CM1)…….……….ON

ALL SYSTEMS……………………CHECK

LANDING LIGHTS ………………..….ONPRESSURIZATION………………CHECK

Mod: 3973 or 4371 or 4457

3.1372


BEFORE LANDING

PF PNF

When Cleared for Approach

NAV SOURCES …………………CHECK

At appropriate speed

“FLAPS 15” ...............................ORDER


“GEAR DOWN”..........................ORDER


“FLAPS 30” …............................ORDER

SPEED VERSUS AOA ………….CHECK

NAV SOURCES …………………CHECK

FLAPS 15 ..................................SELECT

GEAR DOWN.............................SELECTPWR MGT.......................................... TOEXT LIGHTS......................................ON

FLAPS 30 ..................................SELECTTLU ...............................CHECK LO SPDICING AOA LIGHT......................CHECKSPEED VERSUS AOA ………….CHECK

BEFORE LDG C/L

APPROACH

PF PNF

When cleared to Altitude

ALTIMETERS.................. SET & CHECK

CABIN REPORT (CM1)...............OBTAIN

When cleared to Altitude

ALTIMETERS…...............SET & CHECKCABIN ALTITUDE ..................... .CHECK

APPROACH C/L

Mod: 3973 or 4371 or 4457

3.1472


LANDING

PF PNF

“CHECK”..............................ANNOUNCE

“CHECK”..............................ANNOUNCE

“CONTINUE”.......................ANNOUNCE

or

“GO AROUND, SET PWR, FLAPS”…….……ANNOUNCE (Check GA Procedure)

AP …………………………DISCONNECT

After touch down

PL ........................................................GI

REVERSE.......................USE AS RQRD

At DH +500 ft (Or MDA + 500ft)

“500 ”………MONITOR or ANNOUNCE

At DH +100 ft (Or MDA + 100ft)

“100”............. MONITOR or ANNOUNCE

At DH (Or MDA)

“MINIMUM”..........................ANNOUNCE

FLIGHT PARAMETERS .............CHECK

After touch down

IDLE GATE……… AUTO RETRACTIONBOTH LOW PITCH LIGHT..........CHECK“2 LOW PITCH”..................ANNOUNCE

When reaching 70 Kt

“SEVENTY KNOTS”……….ANNOUNCE

CM1 CM2

When reaching 70 Kt

“I HAVE CONTROL”….....ANNOUNCE

NOSE WHEEL STEERING ...CONTROL CONTROL WHEEL......HOLD AS RQD

GO AROUND

PF PNF

“GO AROUND, SET PWR, FLAPS ONENOTCH”……………………...ANNOUNCEGO AROUND P/B on PL..........DEPRESSPL 1+2....................ADVANCE TO RAMPPITCH ATT ..........ROTATE to GA PITCH

PWR……………………………..CHECKFLAPS ONE NOTCH...............SELECT

When positive rate

“GEAR UP,HDG,LO BANK, IAS VGA”…..……………………………………...ORDER

When positive rate

“POSITIVE RATE”…………ANNOUNCE

LDG GEAR LEVER............ SELECT UPYD……………........................ ENGAGETAXI & TAKE OFF LIGHT …..........OFFHDG LO BANK …………….……….SETIAS VGA……………..………..……..SET


“CLIMB SEQUENCE” .................ORDER- PL 1 + 2...SET/CHECK IN THE NOTCH


- IAS...INCREASE ABOVE WHITE BUG- PL 1 + 2..........CHECK IN THE NOTCH- PWR MGT .................................CLIMB- NP............................................CHECK- BLEEDs ..........................................ON- SPEED TARGET………. SET to 170 kt

“CLIMB SEQUENCE COMPLETE”……..……………………………….ANNOUNCE


“FLAPS ZERO” ......................... ORDER


FLAPS ZERO .......................... SELECT


“SET STD”...........................ANNOUNCEALTIMETERS 1 + 2…………………….……………..SET STD & CROSS CHECK


ALTIMETERS 1 + 2……………….....……………SET STD & CROSS CHECK

AFTER TAKE OFF C/L

3.1572


Mod: 3973 or 4371 or 4457

AFTER LANDING

CM1 CM2

When runway is vacated

“AFTER LANDING PROCEDURE”.... ORDER

After at least one minute

CL 1.......................FTR THEN FUEL SO

TRIMS......................................... RESETTCAS ………………………………. STBYFLAPS......……………………………….0°GUST LOCK……………………ENGAGEFLIGHT CONTROLS.….LOCKED XPDRXPDR / TCAS …………………AS RQRDRADAR...........................................STBYLAND LIGHTS / STROBES..............OFFPROB HTG / ANTI / DE-ICING……..OFFATPCS DYNAMIC TEST (Last flight ofthe day)………………………..PERFORM

AFTER LANDING C/L

PARKING

CM1 CM2

Marshaller in sight (last turn)

TAXI & TO LIGHTS ......................... OFF

AT the standPARKING BRK.................................. ONCL 2…………………………... ...........FTRREADY LIGHT....CHECK ILLUMINATED

When NP Stabilized

PROP BRK.............................. ENGAGEPROP BRK LT ...CHECK ILLUMINATEDPROP 2………………CHECK STOPPEDBEACON ......................................... OFF

If GPU is used for disembarking- DC EXT PWR PB.........................ON- CL 2 ...................................FUEL SO

TAIL PROP........................ IN POSITIONSEAT BELTS................................... OFFXPDR………………………………...STBY

HYD SYST ………...CHECK 3X3000

PARKING C/L

3.1672


LEAVING THE AIRCRAFT

CM1 CM2

OXYGEN MAIN SUPPLY ..............OFFICE & RAIN PROT.........................OFFEXT LIGHTS..................................OFFEMER EXIT LIGHT................. DISARMRADAR..........................................OFFCL 2.......................................FUEL SOFUEL PUMPS 1 + 2.......................OFFCDLS.............................................OFFEXT PWR (if used)…………………OFFBAT ...............................................OFF

LEAVING THE AIRCRAFT C/L

3.1772


3.18

72

NORMAL PROCEDURES DAILY CHECKS

NOV 11 160

ATPCS - DYNAMIC TEST (last flight of the day)

Conditions: - PL 1 + 2 .................................................................................................................. GI - CL 1 + 2 ........................................................................................................... AUTO - ATPCS P/B depressed in, OFF light extinguished - PWR MGT on TO position

Check the following results : Turn the ATPCS knob to the left to the arm position and check - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION.............................................................................DECREASE Turn the ATPCS knob to ENG 1 position and check : - ENG 2 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 2 ...................................................................................................... NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 1 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED Turn the ATPCS knob to the right to the arm position and check : - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION.............................................................................DECREASE Turn the ATPCS knob to ENG 2 position and check : - ENG 1 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 1 ...................................................................................................... NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 2 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED

Note: If ENG TEST must be repeated, wait 10 minutes before setting ATPCS.selector in ENG position in order not to damage feathering pumps. (Winding heating).

ENG BOOST TEST

Conditions: - PL 1 + 2 .................................................................................................................. GI - EEC 1 + 2 ...............................................................................ON. OFF extinguished.

Test: ENG BOOST PB ..................................................................................... PRESSED-IN - ON ..............................................................................................ILLUMINATED - FAULT light ............................................................................ EXTINGUISHED ENG BOOST PB ............................................................................... RELEASED-OUT - ON .......................................................................................... EXTINGUISHED - FAULT light ............................................................................ EXTINGUISHED

Note: Test can be performed disregarding engine running condition (both engines running, one engine running, or both engines shut-off)

Mod: 5908 Eng: PW127M

3.19

72

NORMAL PROCEDURES DAILY CHECKS

NOV 11 001

CVR / DFDR

CVR: TEST PB ................................................................................................ DEPRESS Check pointer moves to the green arc. DFDR: Check status SYST light (on the FDEP or RCDR panel) has to be extinguished..

STICK PUSHER / SHAKER

- Release gust lock - Push Control column in nose down position - Select WARN rotary selector (LH maintenance panel) to STICK PUSHER YES - depress and maintain PTT - monitor stall cricket and stick shaker - after ten seconds delay, monitor . CHAN 1 and CHAN 2 illuminate green on LH maintenance panel . STICK PUSHER lights illuminate green on both pilots panel . Stick pusher actuator operates.

- select WARN rotary selector to NORM FLT

- reengage the gust lock

TRIMS

First Flight of the Day: Check PITCH, ROLL, and YAW TRIM operation as follows: - Check the normal TRIM activation in both directions by depressing simultaneously both control rocker switches. - For few seconds depress independently each single control rocker switch and check the non-activation of the corresponding TRIM in both possible directions. - Reset TRIMS as required for take off. Before each flight:: - Check PITCH, ROLL, and YAW TRIM operation. - Check STBY PITCH TRIM operation, check GUARDED switch in OFF position.

3.2072

NORMAL PROCEDURESDAILY CHECKS

NOV 11 001

COCKPIT DOOR DAILY CHECK (if applicable)

COCKPIT DOOR LOCKING SYSTEM SW ..............................................................ONIn the cargo compartment, on the DOOR CALL panel:

EMER PB ............................................................................................... DEPRESSCHECK OPEN LIGHT flashesIn the cockpit:CHECK BUZZERCHECK OPEN LIGHT flashes If correct

In the cockpit:TOGGLE SW ON COCKPIT DOOR CTL panel....................................... DENYCHECK BUZZER stopsCHECK OPEN LIGHT extinguishesIn the cargo compartment, on the DOOR CALL panel:CHECK OPEN LIGHT extinguishes and DENIED LIGHT illuminates If correct

In the cockpit:TOGGLE SW ..................................................................................... OPENCOCKPIT DOOR LOCKING SYSTEM SW...........................................OFFCOCKPIT DOOR CTL panel FAULT LIGHT ....................................CHECKFUNCTIONAL CHECK OF THE MANUAL LOCK BOLT(S)

APM TEST (if installed)

DAILY CHECK MUST BE PERFORMED

APM PTT PB.................................. PUSH and MAINTAIN for test duration

- 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 and DEGRADED PERFlights still illuminated

- over 1 second later, FAULT light on the 5VU illuminates, with CAUTION light, SC andANTI-ICING (on CAP), with CRUISE SPEED LOW, DEGRADED PERF andINCREASE SPEED lights still illuminated

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

3.2172


CRUISE SPEED LOW

Appears in cruise only, to inform the crew that an abnormal drag increaseinduces a speed decrease of more than 10 KT compared with theexpected speed

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

ENTERING ICING CONDITIONS

ANTI-ICING (PROP - HORNS - SIDE WINDOWS) .....................................ON

MODE SEL..............................................................................................AUTO

MINIMUM MANEUVER/OPERATING ICING SPEEDS .................BUGGED AND OBSERVED

ICE ACCRETION .............................................................................MONITOR

AT FIRST VISUAL INDICATION OFICE ACCRETION AND

AS LONG AS ICING CONDITIONS EXIST

ANTI-ICING (PROP - HORNS - SIDE WINDOWS) ...................CONFIRM ON

MODE SEL............................................................................CONFIRM AUTOENG DE-ICING ............................................................................................ONAIRFRAME DE-ICING .................................................................................ON

MINIMUM MANEUVER/OPERATING ICING SPEEDS .................BUGGED AND OBSERVED

BE ALERT TO SEVERE ICING DETECTIONIn case of severe icing, refer to 1.09

If significant vibrations occurBOTH CL ........................................ 100 OVRD for not less than 5 minutes

LEAVING ICING CONDITIONS

DE-ICING AND ANTI-ICING MAY BE SWITCHED OFF

WHEN THE AIRCRAFT IS VISUALLYVERIFIED CLEAR OF ICE

ICING AOA CAPTION MAY BE CANCELLED AND NORMAL SPEEDS MAYBE USED

Model : 212A

4.01

72

OPS DATA APR 08 500

4 – OPS DATA

COMMENTS:

- T/O SPEEDS COMPUTATION Valid for non limiting runways only

- VR COMPUTATION (normal or icing conditions) For runway contaminated by water or slush, increase VR by:

• 0 kt up to 1/4 inch • 1 kt between 1/4 and 1/2 inch

- LANDING SPEEDS COMPUTATION

The approach speeds have been computed with 1.23 VSR of landing configuration or VMCL, whichever is higher

- GROSS CEILING COMPUTATION

For operational reasons, gross ceilings have been established with CG position: 25%

R Model : 212A

4.11

72

OPS DATA APR 08 500

PW127F / PW127M - BOOST OFF

TAKE OFF TORQUE COMPUTED FOR VC = 50. KT

SAT (oC) PROPELLER SPEED 100 %

PRESSURE ALTITUDE (FT) AIR COND OFF

NORMAL AIR

COND ON

HIGH AIR

COND ON

-1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.0 90.0 90.0 89.7 88.7

90.0 89.7 88.7 87.8 86.8

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.089.388.387.2

87.7 86.7 85.7 84.7 83.6

85.8 84.9 83.9 82.9 81.9

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.088.9

89.988.887.786.585.2

86.285.284.183.081.7

82.6 81.7 80.779.5 78.4

80.9 79.9 79.0 77.9 76.7

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.090.090.090.090.0

90.090.090.090.090.0

90.090.090.090.088.5

90.089.688.186.585.0

87.586.084.583.081.5

83.982.581.079.678.2

80.579.177.776.375.0

77.1 75.8 74.5 73.2 71.9

75.5 74.2 72.9 71.7 70.4

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.090.090.088.987.1

90.088.887.185.483.7

86.985.283.681.980.3

83.481.880.278.677.0

80.078.577.075.473.9

76.775.373.872.470.9

73.672.270.869.468.0

70.5 69.2 67.9 66.5 65.2

69.1 67.7 66.4 65.1 63.8

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

90.0 90.0 88.8 86.9 85.0

88.9 87.1 85.3 83.5 81.6

85.483.681.980.178.4

82.080.378.676.975.3

78.777.175.473.872.2

75.573.972.470.869.3

72.470.969.468.0

69.568.066.6

66.665.2

63.8

62.5

48. 50. 52. 54. 55.

46. 48. 51. 53. 54.

83.1 81.2 79.3 77.5 76.5

79.8 78.0 76.2 74.4 73.5

76.674.973.2

73.671.9

70.6

The part in bolt is the flat rated zone; engine mechanical limit.

The part below is the area where the thermodynamical limit is reached first. Note: Applicable for 0 < VC < 60 kt

Model : 212A

4.11A

72

OPS DATA OCT 08 500

PW127M – BOOST ON

TAKE OFF TORQUE COMPUTED FOR VC = 50. KT



NORMAL AIR

COND ON

HIGH AIR

COND ON

-1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 89.1 88.1 87.0

89.3 88.3 87.3 86.2 85.2

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 88.7

89.7 88.6 87.5 86.3 85.0

86.0 84.9 83.982.7 81.5

84.2 83.2 82.1 81.0 79.8

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 88.8

90.0 89.5 87.9 86.4 84.8

87.3 85.8 84.3 82.8 81.3

83.7 82.3 80.9 79.4 78.0

80.3 78.9 77.5 76.1 74.8

78.6 77.2 75.9 74.6 73.2

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 90.0 90.0

90.0 90.0 90.0 89.2 87.4

90.0 89.1 87.4 85.6 83.9

87.2 85.5 83.8 82.2 80.5

83.2 81.7 80.1 78.5 76.9

79.8 78.3 76.8 75.3 73.8

76.6 75.1 73.6 72.2 70.7

73.4 72.0 70.6 69.2 67.8

71.9 70.5 69.1 67.8 66.4

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

90.0 90.0 90.0 90.0 88.8

90.0 90.0 89.1 87.2 85.3

89.2 87.4 85.6 83.8 81.9

85.7 83.9 82.2 80.4 78.7

82.2 80.5 78.9 77.2 75.5

78.9 77.3 75.7 74.0 72.4

75.3 73.8 72.3 70.7

72.3 70.8 69.3

69.3 67.9

66.4

65.0

48. 50. 52. 54. 55.

46. 48. 51. 53. 54.

86.9 84.9 82.9 81.0 80.0

83.4 81.5 79.6 77.8 76.8

80.1 78.3 76.5

76.9 75.2

73.8



Eng : PW127M Model : 212A

4.12

72

OPS DATA APR 08 500


RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT



NORMAL AIR

COND ON

HIGH AIR

COND ON

-1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

- 71. - 35. - 32. - 30. - 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100. 100. 100. 99.6 98.5

100. 99.7 98.6 97.5 96.5

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

- 25. - 22. - 19. - 17. - 14.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.99.398.196.9

97.4 96.3 95.2 94.1 92.9

95.4 94.3 93.2 92.1 91.0

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

- 12. - 9. - 7. - 4. - 1

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.98.7

99.998.797.596.194.7

95.894.693.592.290.8

91.8 90.7 89.6 88.4 87.1

89.9 88.8 87.8 86.5 85.3

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

2. 4. 7.

10. 13.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.98.4

100.99.697.996.194.4

97.295.593.992.290.6

93.291.690.088.586.9

89.487.986.484.883.3

85.7 84.3 82.8 81.3 79.9

83.9 82.5 81.1 79.6 78.2

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

16. 18. 21. 24. 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.98.896.8

100.98.796.894.993.0

96.694.792.991.189.2

92.790.989.187.485.6

88.987.285.583.882.1

85.383.682.080.478.8

81.880.278.677.175.5

78.4 76.9 75.4 73.9 72.4

76.7 75.3 73.8 72.4 70.9

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

30. 32. 35. 38. 41.

100. 100. 98.7 96.6 94.4

98.8 96.8 94.8 92.7 90.7

94.992.991.089.087.1

91.189.287.385.583.6

87.485.683.882.080.2

83.982.280.478.777.0

80.578.877.275.5

77.275.674.0

74.072.5

70.9

69.5

48. 50. 52. 54. 55.

46. 48. 51. 53. 54.

43. 46. 49. 52. 53.

92.3 90.3 88.2 86.1 85.0

88.7 86.7 84.7 82.7 81.7

85.283.281.3

81.879.9

78.5



Model : 212A

4.12A

72

OPS DATA OCT 08 500

PW127M - BOOST ON

RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT



NORMAL AIR

COND ON

HIGH AIR

COND ON

-1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

- 71. - 35. - 32. - 30. - 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

- 25. - 22. - 19. - 17. - 14.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 99.0 97.9 96.7

99.3 98.1 97.0 95.8 94.7

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

- 12. - 9. - 7. - 4. - 1

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 99.9 98.5

99.6 98.4 97.2 95.9 94.5

95.5 94.4 93.2 91.9 90.6

93.5 92.4 91.3 90.0 88.7

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

2. 4. 7. 10. 13.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 98.7

100. 99.4 97.7 96.0 94.2

97.0 95.4 93.7 92.0 90.4

93.0 91.4 89.8 88.3 86.7

89.2 87.7 86.1 84.6 83.1

87.3 85.8 84.3 82.8 81.3

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

16. 18. 21. 24. 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 99.1 97.2

100. 99.0 97.1 95.2 93.2

96.8 95.0 93.2 91.3 89.5

92.5 90.7 89.0 87.2 85.5

88.7 87.0 85.3 83.6 82.0

85.1 83.4 81.8 80.2 78.6

81.5 80.0 78.4 76.9 75.3

79.8 78.3 76.8 75.3 73.8

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

30. 32. 35. 38. 41.

100. 100. 100. 100. 98.7

100. 100. 99.0 97.0 94.8

99.1 97.1 95.1 93.1 91.0

95.2 93.2 91.3 89.3 87.4

91.4 89.5 87.6 85.7 83.9

87.7 85.9 84.0 82.3 80.5

83.7 82.0 80.3 78.6

80.3 78.6 77.0

77.0 75.4

73.8

72.3

48. 50. 52. 54. 55.

46. 48. 51. 53. 54.

43. 46. 49. 52. 53.

96.5 94.3 92.1 90.0 88.9

92.7 90.6 88.5 86.4 85.3

89.0 87.0 85.0

85.4 83.5

82.0




4.13

72

OPS DATA APR 08 500


GO AROUND TORQUE APPLICABLE FOR 0 ≤ VC ≤ 125 kt

TAT (oC) PROPELLER SPEED 100. %

PRESSURE ALTITUDE (FT) AIR COND.

OFF

NORMAL AIR

COND. ON

HIGH AIR

COND. ON

-100.0. 0. 100.0. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

- 71. - 35. - 32. - 30. - 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100. 100. 100. 99.8 98.7

100. 99.9 98.8 97.8 96.7

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

- 25. - 22. - 19. - 17. - 14.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.99.598.397.2

97.6 96.5 95.4 94.3 93.2

95.6 94.5 93.4 92.3 91.2

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

- 12. - 9. - 7. - 4. - 1.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.99.0

100.98.997.796.495.0

96.094.993.792.591.1

92.1 91.0 89.9 88.7 87.4

90.1 89.1 88.0 86.8 85.5

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

2. 4. 7. 10. 13.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.100.100.

100.100.100.100.100.

100.100.100.100.98.7

100.99.998.296.594.7

97.595.994.292.690.9

93.692.090.488.887.2

89.788.286.785.283.6

86.0 84.6 83.1 81.7 80.2

84.3 82.8 81.4 79.9 78.5

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

16. 18. 21. 24. 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100.100.100.99.297.2

100.99.097.195.293.3

96.995.193.291.489.6

93.091.289.587.786.0

89.287.585.984.282.5

85.684.082.480.779.1

82.180.579.077.475.9

78.7 77.2 75.7 74.3 72.8

77.1 75.6 74.2 72.7 71.2

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

30. 32. 35. 38. 41.

100. 100. 99.0 96.9 94.8

99.2 97.1 95.1 93.1 91.1

95.293.391.389.487.5

91.489.687.785.884.0

87.886.084.282.480.6

84.282.580.879.177.4

80.879.277.575.974.2

77.575.974.472.8

74.372.871.3

71.3 69.8

69.8 68.4

48. 50. 52. 54. 56.

46. 48. 51. 53. 54.

43. 46. 49. 52. 54.

92.7 90.6 88.5 86.4 84.4

89.1 87.1 85.0 83.0 81.0

85.583.681.779.7

82.180.378.4

78.877.0

75.7


The part below is the area where the thermodynamical limit is reached first. Note: Add 0.8% for each 10 kt above 125 kt without exceeding 100% torque

Model : 212A

4.13A

72

OPS DATA OCT 08 500

PW127M - BOOST ON

GO AROUND TORQUE COMPUTED FOR VC = 100. KT

TAT (oC) PROPELLER SPEED 100 %


NORMAL AIR

COND ON

HIGH AIR

COND ON

-1000. 0. 1000. 2000. 3000. 4000. 5000. 6000. 7000. 8000. 8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

- 71. - 35. - 32. - 30. - 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100.

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

- 25. - 22. - 19. - 17. - 14.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

99.3 98.1 96.9

99.5 98.3 97.2 96.1 94.9

100. 100. 100. 100.

8. 10. 12. 14. 16.

- 5. - 2. 0. 3. 5.

- 12. - 9. - 7. - 4. - 1

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100. 98.8

99.9 98.7 97.5 96.1 94.8

95.8 94.6 93.5 92.2 90.9

93.8 92.6 91.5 90.3 89.0

100. 100. 100. 100. 100. 99.8 100. 100. 98.0 100. 100. 96.3

18. 20. 22. 24. 26.

8. 10. 13. 15. 18.

2. 4. 7. 10. 13.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100. 100. 99.0 94.6

97.4 95.7 94.0 92.4 90.7

93.4 91.8 90.2 88.6 87.0

89.5 88.0 86.5 85.0 83.4

87.7 86.2 84.7 83.2 81.7

100. 100. 100. 99.4 100. 97.5 99.5 95.5

28. 30. 32. 34. 36.

20. 23. 25. 28. 30.

16. 18. 21. 24. 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100. 97.5 93.6

97.2 95.4 93.5 91.7 89.9

92.8 91.1 89.3 87.6 85.8

89.1 87.4 85.7 84.0 82.3

85.4 83.8 82.2 80.6 79.0

81.9 80.4 78.8 77.3 75.7

80.2 78.7 77.2 75.6 74.1

100. 100. 100. 100. 100. 99.4 100. 97.3

38. 40. 42. 44. 46.

33. 36. 38. 41. 43.

30. 32. 35. 38. 41. 99.1 95.2

99.5 97.5 95.5 93.4 91.4

95.6 93.6 91.7 89.7 87.8

91.7 89.9 88.0 86.1 84.3

88.0 86.2 84.4 82.6 80.9

84.1 82.4 80.7 78.9 77.2

80.7 79.0 77.4 75.7

77.4 75.8 74.2

74.2 72.7

72.6 71.1

48. 50. 52. 54. 56.

46. 48. 51. 53. 55.

43. 46. 49. 52. 54.

96.9 94.7 92.5 90.4 88.2

93.1 91.0 88.9 86.8 84.7

89.4 87.4 85.4 83.3

85.8 83.9 82.0

82.4 80.5

79.1


The part below is the area where the thermodynamical limit is reached first. Note: Add 0.8% for each 10 kt above 125 kt without exceeding 100% torque


4.31

72

OPS DATA OCT 08 500

13 t PW127F / PW127M

Speeds Normal Icing

NON LIMITING RWY TAKE-OFF FLAPS 15

V1 = VR V2

104 110

104 110

FINAL TAKE OFF 110 (Flaps 0)

110 (Flaps 15)

DRIFT DOWN 99 (Flaps 15)

MINI EN ROUTE VmLB 105

(Flaps 0) 126 (Flaps 0)

FINAL APPROACH

VmHB (Flaps 30) 95 95

MAX CRUISE 2 ENGINES

∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.2 457 252 275

94.5 461 251 277

94.5 463 250 279

89.8 447 245 275

84.8 430 239 270

80.2 413 233 267

75.7 397 228 262

100 94.5 452 250 281

94.5 455 249 283

90.8 442 245 280

86.2 426 239 276

81.4 409 233 272

76.9 393 227 268

72.7 378 222 264

120 94.2 448 248 287

90.6 434 243 284

86.7 420 238 281

82.8 406 233 278

78.5 391 228 274

74.2 376 222 270

70.2 362 217 266

140 90.1 430 241 288

86.8 415 237 286

83.5 403 233 284

79.8 388 228 280

76.1 376 223 277

72.1 362 218 273

68.1 347 212 269

160 85.6 409 235 289

83.0 398 231 287

79.9 384 227 285

76.7 372 223 282

73.2 359 218 279

69.8 347 213 276

66.0 333 208 271

180 80.6 386 227 289

78.1 375 224 287

75.5 363 220 285

72.6 351 216 283

69.5 340 212 280

66.3 327 207 276

63.0 316 202 272

200 75.1 361 219 287

72.8 350 216 286

70.5 340 212 284

68.1 329 209 282

65.5 319 205 279

62.6 308 200 276

59.7 298 195 272

220 69.7 336 211 286

67.7 326 208 284

65.6 317 204 283

63.5 308 201 281

61.3 298 197 278

58.9 289 193 275

56.2 279 188 271

240 64.6 312 203 284

62.8 303 199 282

60.9 295 196 281

59.0 287 192 278

57.1 278 189 276

55.0 270 185 273

52.8 262 180 269

250 62.1 300 199 283

60.3 292 195 281

58.6 284 192 279

56.8 276 188 277

54.9 268 184 274

53.0 260 181 271

51.0 253 176 268

TQ % NP = 82 % KG/H/ENG IAS TAS

NOT THERMO LIMITED

Model : 212A

4.32

72

OPS DATA OCT 08 500

14 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

104 110


110 (Flaps 15)




FINAL APPROACH



∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 252 275

94.5 461 251 277

94.5 463 250 278

89.8 447 244 274

84.7 429 238 270

80.2 413 233 266

75.7 397 227 262

100 94.5 452 250 281

94.5 455 249 283

90.8 442 244 280

86.1 426 239 276

81.3 409 233 272

76.8 393 227 267

72.7 378 222 263

120 94.1 447 247 286

90.6 434 243 284

86.6 420 238 281

82.7 406 233 278

78.5 391 227 274

74.2 376 222 269

70.2 362 217 265

140 90.1 429 241 288

86.8 415 237 285

83.5 403 233 283

79.8 388 228 280

76.1 376 223 277

72.0 361 217 272

68.1 347 212 268

160 85.6 409 234 288

82.9 397 231 287

79.8 384 226 284

76.6 372 222 282

73.2 359 217 278

69.7 346 212 275

66.0 333 207 270

180 80.5 386 227 288

78.0 375 223 286

75.4 363 220 285

72.5 351 215 282

69.4 339 211 279

66.3 327 206 275

63.0 316 201 271

200 75.0 361 219 287

72.7 350 215 285

70.4 340 212 283

68.0 329 208 281

65.4 319 204 278

62.5 308 199 275

59.6 297 194 270

220 69.6 335 210 285

67.6 326 207 283

65.5 317 203 281

63.4 308 200 279

61.1 298 196 277

58.7 289 191 273

56.1 279 187 269

240 64.4 311 202 282

62.6 303 198 281

60.8 294 195 279

58.8 286 191 277

56.9 278 187 274

54.8 269 183 270

52.6 261 179 267

250 62.0 300 197 281

60.2 291 194 279

58.4 283 190 277

56.6 275 187 275

54.7 267 183 272

52.9 260 179 269

50.8 252 175 265


NOT THERMO LIMITED

Model : 212A

4.33

72

OPS DATA OCT 08 500

15 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

104 110


110 (Flaps 15)




FINAL APPROACH



∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 252 275

94.5 461 251 276

94.5 463 250 278

89.7 447 244 274

84.7 429 238 270

80.1 413 232 266

75.7 397 227 261

100 94.5 453 250 281

94.5 455 249 282

90.7 441 244 279

86.1 426 238 276

81.3 409 232 271

76.8 393 227 267

72.6 378 221 263

120 94.1 447 247 286

90.6 434 243 284

86.6 419 238 281

82.7 406 233 277

78.4 391 227 273

74.1 376 221 269

70.1 362 216 265

140 90.0 429 241 287

86.8 415 236 285

83.4 402 232 283

79.7 388 227 279

76.1 375 222 276

72.0 361 217 271

68.0 347 211 267

160 85.5 409 234 288

82.9 397 230 286

79.8 383 226 284

76.6 372 222 281

73.1 358 217 278

69.7 346 212 274

65.9 333 206 269

180 80.5 386 226 287

77.9 374 223 286

75.3 363 219 284

72.4 351 215 281

69.4 339 210 278

66.2 327 205 274

62.9 316 200 269

200 74.9 360 218 286

72.6 349 214 284

70.3 339 211 282

67.9 329 207 280

65.2 319 203 277

62.4 308 198 273

59.5 297 193 269

220 69.5 335 209 283

67.5 325 206 282

65.4 316 202 280

63.3 307 199 278

61.0 297 194 275

58.6 289 190 271

56.0 278 185 267

240 64.3 310 201 281

62.4 302 197 279

60.6 294 193 277

58.6 285 190 274

56.7 277 186 271

54.6 269 181 268

52.5 261 177 264

250 61.8 299 196 279

60.0 290 192 277

58.2 282 189 275

56.4 275 185 272

54.5 267 181 269

52.7 259 177 266

50.6 252 173 262


NOT THERMO LIMITED

Model : 212A

4.34

72

OPS DATA OCT 08 500

16 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

104 110


110 (Flaps 15)




FINAL APPROACH



∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 251 275

94.5 461 250 276

94.5 463 249 278

89.7 447 244 274

84.7 429 238 269

80.1 413 232 265

75.6 397 226 261

100 94.5 453 249 280

94.5 455 248 282

90.7 441 243 279

86.1 426 238 275

81.3 409 232 271

76.8 393 226 266

72.6 378 220 262

120 94.1 447 247 285

90.5 434 242 283

86.6 419 237 280

82.6 406 232 277

78.4 391 226 272

74.1 376 221 268

70.1 362 215 264

140 90.0 429 240 287

86.7 414 236 284

83.4 402 232 282

79.6 388 227 279

76.0 375 221 275

72.0 361 216 270

68.0 347 210 266

160 85.5 409 233 287

82.8 397 230 285

79.7 383 225 283

76.5 371 221 280

73.1 358 216 276

69.6 346 211 272

65.9 333 205 268

180 80.3 385 226 286

77.8 374 222 285

75.2 363 218 283

72.3 350 214 280

69.3 339 209 276

66.1 327 204 272

62.8 315 198 268

200 74.8 360 217 285

72.5 349 213 283

70.2 339 210 281

67.7 328 206 278

65.1 318 201 275

62.3 307 196 271

59.4 297 191 266

220 69.3 334 208 282

67.3 325 205 280

65.2 316 201 278

63.1 306 197 276

60.8 297 193 273

58.4 288 188 269

55.9 278 183 264

240 64.1 310 199 279

62.2 301 196 277

60.4 293 192 274

58.4 285 188 272

56.5 276 184 269

54.5 268 180 265

52.3 260 175 261

250 61.6 298 195 277

59.7 290 191 275

58.0 282 187 272

56.2 274 183 270

54.3 266 179 267

52.5 259 175 263

50.4 251 170 259


NOT THERMO LIMITED

Model : 212A

4.35

72

OPS DATA OCT 08 500

17 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

104 110


111 (Flaps 15)




FINAL APPROACH



∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 251 274

94.5 461 250 276

94.5 463 249 277

89.7 447 243 273

84.6 429 237 269

80.0 413 231 264

75.6 397 225 260

100 94.5 453 249 280

94.5 455 248 281

90.7 441 243 279

86.0 425 237 274

81.2 409 231 270

76.7 393 225 265

72.5 378 220 261

120 94.0 447 246 285

90.5 434 242 283

86.5 419 237 279

82.6 405 231 276

78.3 391 226 272

74.0 376 220 267

70.0 362 214 262

140 89.9 429 240 286

86.6 414 235 284

83.3 402 231 281

79.6 388 226 278

75.9 375 221 274

71.9 361 215 269

67.9 347 209 264

160 85.4 408 233 286

82.7 397 229 285

79.6 383 224 282

76.4 371 220 279

73.0 358 215 275

69.5 346 210 271

65.8 333 204 266

180 80.2 385 225 285

77.7 374 221 283

75.1 362 217 281

72.2 350 213 278

69.1 338 208 275

65.9 326 203 271

62.7 315 197 266

200 74.6 359 216 283

72.3 348 212 281

70.0 338 208 279

67.6 328 204 276

64.9 318 200 273

62.1 307 195 269

59.2 296 190 264

220 69.1 333 207 280

67.1 324 203 278

65.0 315 199 276

62.9 306 195 273

60.7 296 191 270

58.3 288 187 266

55.7 278 181 262

240 63.8 309 197 277

62.0 300 194 274

60.2 292 190 272

58.2 284 186 269

56.3 275 182 266

54.2 268 177 262

52.1 260 172 257

250 61.3 297 193 275

59.5 289 189 272

57.7 281 185 269

55.9 273 181 266

54.1 265 177 263

52.2 258 172 259

50.1 250 167 254


NOT THERMO LIMITED

Model : 212A

4.36

72

OPS DATA OCT 09 500

18 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

107 111


115 (Flaps 15)




FINAL APPROACH



∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 251 274

94.5 461 250 275

94.5 463 249 277

89.6 447 243 273

84.6 429 236 268

80.0 413 231 264

75.5 397 225 259

100 94.5 453 249 279

94.5 455 248 281

90.6 441 243 278

86.0 425 237 274

81.2 409 230 269

76.6 393 224 264

72.5 378 219 260

120 93.9 447 246 284

90.4 434 241 282

86.5 419 236 279

82.5 405 231 275

78.3 391 225 271

74.0 376 219 266

70.0 361 213 261

140 89.8 429 239 285

86.5 414 235 283

83.2 402 230 280

79.5 388 225 277

75.8 375 220 273

71.8 361 214 268

67.8 347 208 263

160 85.3 408 232 285

82.6 397 228 284

79.5 383 224 281

76.3 371 219 278

72.9 358 214 274

69.4 346 208 269

65.7 333 203 264

180 80.1 384 224 284

77.5 373 220 282

74.9 362 216 280

72.0 349 211 277

69.0 338 206 273

65.8 326 201 269

62.6 315 196 264

200 74.4 358 215 282

72.1 348 211 279

69.8 338 207 277

67.4 327 203 274

64.8 317 198 271

62.0 307 193 267

59.1 296 188 262

220 68.9 333 205 278

66.9 323 202 276

64.8 314 198 274

62.7 305 194 271

60.5 296 189 268

58.1 287 184 263

55.5 277 179 258

240 63.6 308 196 274

61.7 299 192 272

59.9 291 188 269

57.9 283 184 266

56.0 275 179 262

54.0 267 174 258

51.8 259 169 252

250 61.1 296 191 272

59.2 288 187 269

57.4 280 183 266

55.6 272 178 263

53.8 264 174 259

51.9 257 169 254

49.8 249 163 248


NOT THERMO LIMITED

Model : 212A

R

4.37

72

OPS DATA OCT 08 500

19 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

104 110

110 114


119 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 102 110


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 458 250 273

94.5 461 249 275

94.5 464 248 276

89.6 447 242 272

84.5 429 236 267

79.9 413 230 263

75.5 397 224 258

100 94.5 453 248 279

94.5 455 247 280

90.5 441 242 277

85.9 425 236 273

81.1 409 230 268

76.6 393 224 263

72.4 377 218 259

120 93.9 447 245 284

90.3 434 240 281

86.4 419 235 278

82.4 405 230 274

78.2 391 224 269

73.9 376 218 265

69.9 361 212 260

140 89.7 428 238 284

86.5 414 234 282

83.1 402 229 279

79.4 388 224 275

75.8 375 219 271

71.7 361 213 266

67.8 347 207 261

160 85.1 408 231 284

82.5 396 227 282

79.4 382 223 279

76.2 371 218 276

72.8 357 212 272

69.4 346 207 268

65.6 333 201 263

180 79.9 384 223 283

77.3 372 219 281

74.8 361 214 278

71.9 349 210 275

68.8 338 205 271

65.7 326 200 267

62.4 315 194 262

200 74.2 358 213 280

71.9 347 209 278

69.6 337 205 275

67.2 327 201 272

64.6 317 196 269

61.8 306 191 264

58.9 296 185 259

220 68.7 332 204 276

66.7 323 200 274

64.6 313 196 271

62.4 304 192 268

60.2 295 187 265

57.8 286 182 260

55.2 276 176 254

240 63.3 307 194 271

61.4 298 190 269

59.6 290 186 266

57.7 282 181 262

55.7 273 176 258

53.6 266 171 253

51.4 258 165 246

250 60.8 295 189 269

58.9 286 184 266

57.1 279 180 262

55.3 271 175 258

53.4 263 170 253

51.5 256 164 248

49.4 248 158 240


NOT THERMO LIMITED

Model : 212A

4.38

72

OPS DATA OCT 09 500

20 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

105 110

114 118


122 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 105 114


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 250 273

94.5 461 249 274

94.5 464 248 276

89.5 447 241 271

84.4 429 235 266

79.9 412 229 262

75.4 396 223 257

100 94.5 453 247 278

94.5 455 246 280

90.4 441 241 276

85.8 425 235 272

81.0 409 229 267

76.5 392 222 262

72.3 377 216 257

120 93.8 446 244 283

90.2 433 240 280

86.3 419 234 277

82.4 405 229 273

78.1 390 223 268

73.9 376 217 263

69.8 361 211 258

140 89.6 428 237 283

86.3 413 233 281

83.0 401 228 278

79.3 387 223 274

75.7 374 217 270

71.7 361 211 265

67.7 347 205 260

160 85.0 407 230 283

82.3 396 226 281

79.2 382 221 278

76.1 370 216 275

72.6 357 211 270

69.3 345 206 266

65.5 332 199 261

180 79.7 383 221 281

77.1 372 217 279

74.6 361 213 276

71.7 348 208 273

68.7 337 203 269

65.5 325 198 264

62.3 314 192 259

200 74.0 357 212 278

71.7 346 208 276

69.4 336 204 273

67.0 326 199 270

64.4 316 194 266

61.6 305 189 261

58.7 295 183 255

220 68.4 331 202 274

66.4 322 198 271

64.3 313 194 268

62.2 303 189 265

60.0 294 185 261

57.5 285 179 256

54.9 276 172 249

240 63.0 306 191 268

61.1 297 187 265

59.3 289 183 262

57.3 281 178 257

55.3 272 172 252

53.2 265 166 246

50.9 256 159 238

250 60.4 294 186 265

58.5 285 181 261

56.7 277 176 257

54.8 269 171 252

52.9 261 165 246

50.9 254 158 238

48.7 246 149 227


NOT THERMO LIMITED

Model : 212A

R

4.39

72

OPS DATA OCT 08 500

21 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

108 111

117 121


125 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 108 117


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 249 272

94.5 461 248 273

94.5 464 247 275

89.4 446 241 270

84.4 429 234 265

79.8 412 228 260

75.3 396 222 255

100 94.5 453 247 277

94.5 456 246 279

90.3 440 240 275

85.7 425 234 271

80.9 408 228 266

76.4 392 221 261

72.2 377 215 256

120 93.7 446 243 282

90.1 433 239 279

86.2 418 233 276

82.3 405 228 271

78.1 390 222 267

73.8 376 215 262

69.8 361 209 257

140 89.5 428 237 282

86.2 413 232 280

82.9 401 227 277

79.2 387 222 272

75.5 374 216 268

71.6 361 210 263

67.6 347 204 258

160 84.8 407 229 282

82.2 395 225 279

79.1 381 220 276

76.0 370 215 273

72.5 357 210 269

69.2 345 204 264

65.4 332 198 258

180 79.5 382 220 279

76.9 371 216 277

74.4 360 212 274

71.5 348 207 271

68.5 337 202 267

65.3 325 196 262

62.1 314 190 256

200 73.8 356 210 276

71.5 346 206 273

69.1 336 202 270

66.8 325 197 267

64.1 315 192 263

61.4 305 186 257

58.4 294 180 251

220 68.1 330 200 271

66.1 320 196 268

64.0 312 191 265

61.8 302 187 261

59.6 293 181 256

57.2 284 175 250

54.6 275 167 242

240 62.6 304 189 265

60.7 296 184 261

58.8 288 179 257

56.8 279 173 251

54.8 270 167 245

52.6 263 159 236

50.1 254 148 222

250 60.0 292 182 260

58.0 283 177 256

56.1 275 172 250

54.2 267 165 244

52.1 258 157 234

49.8 251 145 219


NOT THERMO LIMITED

Model : 212A

4.40

72

OPS DATA OCT 09 500

21.5 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

109 113

119 122


126 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 109 119


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 249 272

94.5 461 248 273

94.5 464 247 274

89.4 446 240 270

84.3 429 234 265

79.8 412 227 260

75.3 396 221 255

100 94.5 453 246 277

94.5 456 245 279

90.3 440 240 275

85.7 425 234 270

80.9 408 227 265

76.4 392 221 260

72.2 377 214 255

120 93.6 446 243 281

90.1 433 238 279

86.1 418 233 275

82.2 405 227 271

78.0 390 221 266

73.7 375 215 261

69.7 361 209 256

140 89.4 427 236 282

86.2 413 231 279

82.8 401 226 276

79.1 387 221 272

75.5 374 215 267

71.5 361 209 262

67.6 346 203 257

160 84.8 406 228 281

82.1 395 224 279

79.0 381 219 275

75.9 370 214 272

72.5 357 209 268

69.1 345 203 263

65.3 332 197 257

180 79.4 382 219 278

76.8 371 215 276

74.3 360 211 273

71.4 348 206 270

68.4 337 201 266

65.2 324 195 260

62.0 314 188 254

200 73.6 355 209 275

71.3 345 205 272

69.0 335 201 269

66.7 325 196 266

64.0 315 191 261

61.2 304 185 255

58.3 294 178 248

220 68.0 329 199 269

65.9 320 195 267

63.8 311 190 263

61.7 302 185 259

59.4 293 179 254

56.9 284 172 247

54.3 274 164 237

240 62.4 303 187 262

60.5 295 182 258

58.6 287 177 254

56.5 278 171 248

54.4 269 163 239

52.2 262 154 228

250 59.8 291 181 258

57.7 282 175 252

55.8 274 169 246

53.8 266 161 237

51.5 256 150 224


NOT THERMO LIMITED

Model : 212A

R

4.41

72

OPS DATA OCT 09 500

22 t PW127F / PW127M

Speeds Normal Icing


V1 = VR V2

111 114

120 123


128 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 111 120


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 248 271

94.5 461 247 273

94.5 464 246 274

89.3 446 240 269

84.3 429 233 264

79.7 412 227 259

75.3 396 220 254

100 94.5 453 246 277

94.5 456 245 278

90.2 440 239 274

85.6 425 233 269

80.9 408 226 264

76.3 392 220 259

72.2 377 214 254

120 93.6 446 243 281

90.0 433 238 278

86.1 418 232 274

82.2 404 226 270

78.0 390 220 265

73.7 375 214 260

69.7 361 208 255

140 89.3 427 235 281

86.1 413 231 278

82.8 401 226 275

79.1 387 220 271

75.4 374 215 267

71.5 360 208 261

67.5 346 202 255

160 84.7 406 228 280

82.0 395 223 278

78.9 381 219 275

75.8 370 214 271

72.4 357 208 267

69.0 345 202 262

65.2 332 195 255

180 79.3 381 219 278

76.7 370 214 275

74.2 359 210 272

71.3 347 205 268

68.3 336 200 264

65.1 324 193 259

61.9 313 187 252

200 73.5 355 208 273

71.2 345 204 271

68.9 335 200 268

66.5 324 195 264

63.9 314 189 259

61.1 304 183 253

58.1 293 175 245

220 67.8 328 197 268

65.8 319 193 265

63.6 310 188 261

61.4 301 183 256

59.2 292 177 251

56.7 283 170 243

54.0 273 160 231

240 62.2 303 185 260

60.2 294 180 255

58.3 286 174 250

56.2 277 167 243

53.9 268 158 232

51.1 258 141 209

250 59.5 290 178 254

57.4 281 172 248

55.3 272 164 240

53.2 264 155 228


NOT THERMO LIMITED

Model : 212A

R

R

4.42

72

OPS DATA OCT 09 500

22.5 t PW127F / PW127M Never exceed certified weight limitations

Speeds Normal Icing


V1 = VR V2

112 115

122 125


130 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 113 122


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 248 271

94.5 461 247 272

94.5 464 246 274

89.3 446 239 269

84.2 428 233 263

79.7 412 226 258

75.2 396 220 253

100 94.5 453 246 276

94.5 456 245 278

90.2 440 239 274

85.6 424 232 269

80.8 408 226 264

76.3 392 219 258

72.1 377 213 253

120 93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140 89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160 84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180 79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200 73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

220 67.6 328 196 266

65.6 318 192 263

63.4 310 186 258

61.2 300 181 253

59.0 291 174 247

56.4 282 166 237

53.6 272 154 223

240 61.9 302 183 257

59.9 293 178 252

57.9 284 171 246

55.7 275 162 236

53.1 265 149 219

250 59.2 289 176 251

57.0 279 168 243

54.7 270 158 232


NOT THERMO LIMITED

Model : 212A

R

4.43

72

OPS DATA OCT 09 500

23 t PW127F / PW127M Never exceed certified weight limitations

Speeds Normal Icing


V1 = VR V2

114 117

123 126


132 (Flaps 15)




FINAL APPROACH

VmHB (Flaps 30) 115 124


∆ ISA FLIGHT LEVEL -10 -5 0 +5 +10 +15 +20

80 94.5 459 248 271

94.5 461 247 272

94.5 464 246 274

89.3 446 239 269

84.2 428 233 263

79.7 412 226 258

75.2 396 220 253

100 94.5 453 246 276

94.5 456 245 278

90.2 440 239 274

85.6 424 232 269

80.8 408 226 264

76.3 392 219 258

72.1 377 213 253

120 93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140 89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160 84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180 79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200 73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

220 67.6 328 196 266

65.6 318 192 263

63.4 310 186 258

61.2 300 181 253

59.0 291 174 247

56.4 282 166 237

53.6 272 154 223

240 61.9 302 183 257

59.9 293 178 252

57.9 284 171 246

55.7 275 162 236

53.1 265 149 219

250 59.2 289 176 251

57.0 279 168 243

54.7 270 158 232


NOT THERMO LIMITED

Model : 212A

R R

4.61

72

OPS DATA APR 08 500

For weight in KG, use white boxes. For weight in LB, use shaded boxes.

PW127F / PW127M – BOOST OFF

SINGLE ENGINE GROSS CEILING (FT) NORMAL CONDITIONS (FLAPS 0)

WEIGHT x 1000 kg ISA - 10 ISA ISA + 10 ISA + 15 ISA + 20 WEIGHT

x 1000 lb

13.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 29

14.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 24900 31

15.0 25000 25000 25000 25000 24300 24400 23700 23700 23100 23100 33

16.0 25000 25000 23700 23900 22400 22700 21800 22000 21100 21400 35

17.0 23300 23700 22000 22300 20700 21000 20000 20400 19100 19500 37

18.0 21600 22100 20300 20800 18900 19400 18100 18700 17300 17800 39

19.0 20000 20600 18600 19300 17300 17900 16400 17000 15700 16300 41

20.0 18500 19200 17100 17900 15700 16500 14900 15600 14200 14900 43

21.0 17100 17600 15700 16500 14100 15100 13400 14300 12700 13600 45

22.0 15700 16600 14400 15300 12800 13700 12000 13000 11300 12300 47

22.5 15100 15400 13700 14100 12100 12400 11300 11700 10500 11000 49

- - 15100 - 13700 - 12100 - 11300 - 10500 49.6

Model : 212A

4.61A

72

OPS DATA OCT 08 500


PW127M – BOOST ON

SINGLE ENGINE GROSS CEILING (FT)

NORMAL CONDITIONS (FLAPS 0)

WEIGHT x 1000 kg

ISA - 10 ISA ISA + 10 ISA + 15 ISA + 20 WEIGHT x 1000 lb

13.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 29

14.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 31

15.0 25000 25000 25000 25000 25000 25000 24400 24500 23800 23900 33

16.0 25000 25000 24500 24700 23200 23400 22500 22800 21900 22200 35

17.0 24100 24500 22700 23100 21400 21800 20800 21200 19900 20400 37

18.0 22400 22900 21000 21500 19700 20200 19000 19600 18100 18600 39

19.0 20800 21400 19400 20100 18100 18700 17200 17900 16500 17100 41

20.0 19300 20000 17900 18700 16500 17300 15700 16400 15000 15700 43

21.0 17800 18700 16500 17300 15000 15900 14200 15100 13500 14400 45

22.0 16500 17400 15100 16100 13600 14500 12900 13800 12100 13100 47

22.8 15500 16200 14100 14800 12500 13200 11800 12500 11000 11800 49

- - 15600 - 14300 - 12600 - 11900 - 11200 50


4.62

72

OPS DATA APR 08 500


PW127F / PW127M – BOOST OFF

SINGLE ENGINE GROSS CEILING (FT) ICING CONDITIONS (FLAPS 15)

WEIGHT x 1000 kg ISA - 10 ISA ISA + 10 ISA + 15 ISA + 20 WEIGHT

x 1000 lb

13.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 29

14.0 25000 25000 25000 25000 25000 25000 24800 24700 24200 24100 31

15.0 25000 25000 24700 24800 23500 23500 22800 22900 22200 22300 33

16.0 24300 24500 22900 23100 21600 21800 21000 21200 20200 20400 35

17.0 22500 22800 21100 21500 19800 20200 19100 19500 18200 18600 37

18.0 20700 21300 19400 19900 18000 18500 17200 17700 16400 17000 39

19.0 19000 19700 17700 18300 16300 17000 15400 16100 15100 15400 41

20.0 17400 18200 16100 16900 14600 15400 13900 14600 - - 43

21.0 16000 16800 14600 15500 13100 13900 12600 13200 - - 45

22.0 14600 15600 13300 14200 11700 12600 - 12600 - - 47

22.5 14000 14300 12600 13000 11000 11300 - - - - 47

- - 14000 - 12600 - 11000 - - - - 48.5

Note : When bolt-underlined figures, icing conditions do not exist.

Model : 212A

4.62A

72

OPS DATA OCT 08 500


PW127M – BOOST ON

SINGLE ENGINE GROSS CEILING (FT)

ICING CONDITIONS (FLAPS 15)

WEIGHT x 1000 kg

ISA - 10 ISA ISA + 10 ISA + 15 ISA + 20 WEIGHT x 1000 lb

13.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 29

14.0 25000 25000 25000 25000 25000 25000 25000 25000 25000 25000 31

15.0 25000 25000 25000 25000 24200 24300 23600 23600 22900 23000 33

16.0 25000 25000 23600 23800 22300 22600 21700 21900 21000 21200 35

17.0 23200 23600 21800 22200 20500 20900 19900 20300 19000 19400 37

18.0 21500 22000 20100 20700 18800 19300 18000 18600 17200 17700 39

19.0 19800 20500 18400 19100 17100 17800 16200 16900 15500 16200 41

20.0 18200 19000 16800 17600 15400 16300 14600 15400 15000 15100 43

21.0 16700 17600 15400 16200 13800 14800 13100 14000 - - 45

22.0 15400 16300 14000 15000 12400 13400 12600 12700 - - 47

22.8 14400 15100 13000 13700 11400 12100 - 12500 - - 49

- - 14500 - 13100 - 11500 - - - - 50

Note : When bolt-underlined figures, icing conditions do not exist.


4.63

72

OPS DATA SEP 10 500

PW127F / PW127M

REDUCED FLAPS LANDING CONFIGURATION – V APP (kt)

NOTE: For a go around flaps 15 configuration increase speed up to VmLB0 before selecting flaps 0

FLAPS 0 VmHB0 + 5 kt

FLAPS 15 VmHB15

KG

WEIGHT (x 1000kg) Normal Icing Normal Icing

13 115 136 97 102 14 119 141 97 106 15 123 146 100 110 16 127 151 103 114 17 131 155 107 118 18 135 160 110 122 19 139 164 113 125 20 142 168 116 129 21 146 172 120 132 22 149 176 123 135

22.5 * 151 178 124 137 23 * 152 180 126 139

FLAPS 0 VmHB0 + 5 kt

FLAPS 15 VmHB15

Lb

WEIGHT (x 1000Lb) Normal Icing Normal Icing

29 115 137 97 103 31 119 142 97 107 33 123 146 100 110 35 127 150 103 114 37 130 154 106 117 39 134 158 109 121 41 137 162 112 124 43 141 166 115 127 45 144 170 118 130 47 147 173 121 133 49 150 177 123 136

49.6 * 151 178 124 137 50.7 * 152 180 126 139

* Never exceed the certified Maximum Landing Weight Eng : PW127E Eng : PW127F-PW127M

4.64

72

OPS DATA OCT 08 500

PW127F / PW127M

1.1 VMCA IAS * OAT °C

ZP (ft) -30 -20 -10 0 + 10 + 20 +30 + 40 + 50

0 111 110 109 108 108 107 106 104 100

2000 109 108 108 107 106 105 104 101 97

4000 108 107 106 105 105 104 100 97 94

6000 106 106 105 104 103 100 97 94 91

8500 104 104 103 100 98 96 93 90 88

* Conservative values calculated for the maximum landing weight.

Model : 212A

4.65

72

OPS DATA SEP 10 700

PW127F / PW127M ACTUAL LANDING DISTANCE (M) - SEA LEVEL

NORMAL CONDITIONS - FLAPS 30

WEIGHT (1000 KG) 13 14 15 16 17 18 19 20 21 22 22.5 23

DRY 530 530 530 530 530 550 570 590 610 630 640 660

WET 690 690 690 690 700 730 760 780 810 840 850 860

WATER OR

SLUSH <1/2 in

640 680 710 750 780 820 860 900 940 980 1000 1020

COMPACT SNOW 690 720 760 790 830 860 900 930 970 1000 1020 1030 R

UN

WA

Y C

ON

DIT

ION

CO

NT

AM

INA

TE

D B

Y

ICE 1010 1070 1120 1170 1230 1280 1340 1390 1450 1500 1530 1560

ICING CONDITIONS – FLAPS 30

WEIGHT (1000 KG) 13 14 15 16 17 18 19 20 21 22 22.5 23

DRY 570 570 570 570 570 600 620 640 670 690 710 720

WET 760 760 760 760 770 800 830 860 890 920 940 950

WATER OR

SLUSH <1/2 in

700 740 780 820 860 900 950 990 1040 1080 1100 1130

COMPACT SNOW 760 800 840 880 920 960 1000 1040 1080 1120 1140 1160 R

UN

WA

Y C

ON

DIT

ION

CO

NT

AM

INA

TE

D B

Y

ICE 1140 1200 1260 1320 1390 1450 1520 1580 1640 1710 1740 1770

CORRECTION ON LANDING DISTANCES

-Wind: • dry or wet runway add 10% per 5 kt tailwind. subtract 2% per 5 kt headwind. • contaminated runway add 16% per 5 kt tailwind. subtract 2% per 5 kt headwind.

-Airport elevation: • dry or wet runway add 3% per 1000 ft above sea level. • contaminated runway add 5% per 1000 ft above sea level.

-Effect of reverse : landing distances are decreased by : • 2% on dry runway. • 4% on wet runway. • 8% on runway contaminated by water or slush. • 10 % on runway contaminated by compact snow. • 30 % on runway contaminated by ice.

CAUTION: On contaminated runway, performances without reverser only are to be used for flight preparation.

NOTE: Landing on damp runway. A runway is damp when it is not perfectly dry, but when the water which is on it does not give it a shiny appearance. For damp runway, we consider no performance limitation.

Mod : 6055 Model : 212A

5.0172

CHECK LIST

L.T.R.List of Temporary Revisions JUN 12 108

LZ

TREDITION

DATEDESTROYED

INSERTIONDATE

REASON

01 MAY 11AT REV 32

DATED NOV 11TR 16 ENV

02 JUN 12 TR 18 ENV

5.02

72

CHECK LIST

R.T.R. Reason of Temporary Revisions JUN 12 001

ENV

TR EDITION DATE REASON AFFECTED PAGES

01 OCT 98 Single engine gross ceiling 4.61 - 4.62

02 FEB 99 DUAL DC GEN LOSS 1.06

03 MAR 99 SEVERE ICING : improvement of detection

and procedure 1.09 - 3.04

04 NOV 99 Spring tab MOD 4373 or 8167 ENG FLAME OUT AT TO

2.03 - 2.20 - 2.21

05 NOV 00 Introduction of FAA AD Missing page for 212A

Various

3.05 - 3.06 - 3.07 4.64 2.37

06 FEB 02 Introduction of modification 5313 EGPWS 1.07 - 1.08

07 FEB 03 Introduction of modifications 5377+5434

CDLS Models 102-202-212-212A 1 - 2 - 3 - 6

08 OCT 03 Introduction of modifications 5377+5434 CDLS Models 101-201-211 1 - 2 - 3 - 6

09 FEB 05

Correction of content 2.02 Introduction of BOTH ELEVATORS RECONNECTION ON GROUND

Correction of Cockpit Door Daily Check Single Eng Gross Ceiling Flaps 15 for Icing

Conditions

2.02 2.22A

3.02A 4.62

10 APR 06 FUEL LO LVL Procedure Updating

Introduction of Mod 5561 : Messier--Bugatti Wheels and Brakes

2.13 4.65

11 MAR 07 DITCHING and FORCED LANDING

Procedure Updating MISSING PAGE 2.14

1.08 – 1.08A 2.14

12 MAY 07 MPC : indicating/recording system, install

MPC with QAR Thales 2.29A

13 JUN 08

Contents page correction (deletion of EEC SELECT IN FLIGHT and ATPCS FAIL)

ENG OIL LO PR : (Only for Aircraft with Man Ignition), Procedure updating

2.01

2.12 (sequences 050, 150

and 500 only)

14 JUL 08 PW127M impact including BOOST function Part 4

15 AUG 08 ENG BOOST FAULT procedure introduction 2.01 – 2.12A

16 MAY 11 UNRELIEABLE AIRSPEED INDICATION Emergency procedure introduction

1.10 – 1.11

17 JUL 11 UNRELIEABLE AIRSPEED INDICATION :

Corrections for 72-200/210 series only : missing pages (pec and/or non pec)

1.10 – 1.11

18 JUN 12

- Some Emergency procedure update for 72-212A following AFM 72-212A revision.

- Fuel feed lo pr procedure updated for 72-212A

1.02-1.02A-1.05-1.05A-1.06-1.08-1.08A-1.09-1.10

2.13

QRH QUICK REFERENCE HANDBOOK 5-03 page 1-108

ATR72

S.N.T.P.Shipping Note Temporary Pages

JUN 12

Please find below the list of the temporary pages created, suppressed or revised

Temporary revision N° 02 (JUN 12).

Action P CH SE Page Seq Date Label Modification expression

End LZ

"F"=Facing "ADD"=Add "DESTROY" = Destroy"A" = After "……" = Revised "SEE VAL" = See Validation

ADD 1 ** ** 002 500 JUN 12 212A

ADD 1 ** ** 002A 500 JUN 12 212A

ADD 1 ** ** 005 500 JUN 12 212A

ADD 1 ** ** 005A 500 JUN 12 212A

ADD 1 ** ** 006 502 JUN 12 212A

ADD 1 ** ** 008 500 JUN 12 212A

ADD 1 ** ** 008A 500 JUN 12 212A

ADD 1 ** ** 009 500 JUN 12 PW127F-PW127M

ADD 1 ** ** 010 500 JUN 12 PW127F-PW127M

ADD 2 ** ** 001 500 JUN 12 212A

ADD 2 ** ** 013 500 JUN 12 212A

ADD 5 01 ** 001 108 JUN 12 L.T.R. LZ

ADD 5 02 ** 001 001 JUN 12 R.T.R.

ADD 5 04 ** 001 108 JUN 12 L.E.T.P, LZ


ATR72

L.E.T.P.List of EffectiveTemporary Pages

JUN 12

You must hold in your manual the following temporary pages

Issue P CH SE Page Seq Date Label Modification expressionValidity expression

End LZ

TR02 1 ** ** 002 500 JUN 12 212AALL

TR02 1 ** ** 002A 500 JUN 12 212AALL

TR02 1 ** ** 005 500 JUN 12 212AALL

TR02 1 ** ** 005A 500 JUN 12 212AALL

TR02 1 ** ** 006 502 JUN 12 212AALL

TR02 1 ** ** 008 500 JUN 12 212AALL

TR02 1 ** ** 008A 500 JUN 12 212AALL

TR02 1 ** ** 009 500 JUN 12 PW127F-PW127MALL

TR02 1 ** ** 010 500 JUN 12 PW127F-PW127MALL

TR02 2 ** ** 001 500 JUN 12 212AALL

TR02 2 ** ** 013 500 JUN 12 212AALL

TR02 5 01 ** 001 001 JUN 12 L.T.R. LZALL

TR18 5 02 ** 001 001 JUN 12 R.T.R.ALL

TR02 5 04 ** 001 001 JUN 12 L.E.T.P, LZALL

5.05

72

CHECK LIST

L.N.R. List of Normal Revisions NOV 11 001

REV EDITION DATE

INSERTION DATE REMARKS

00 OCT 89

01 DEC 89

02 MAR 90

03 NOV 90

04 MAY 91

05 NOV 91

06 MAY 92

07 NOV 92 TOTAL EDITION

08 MAY 93 TOTAL EDITION

09 NOV 93 TOTAL EDITION

10 JUN 94

11 DEC 94

12 JUN 95

13 DEC 95

14 JUN 96

15 DEC 96

16 JUN 97

17 DEC 97

18 JUL 98

19 JUL 99

20 JUL 00

21 JUL 01

22 SEP 02

23 SEP 03

24 SEP 04 TOTAL WORD EDITION

25 SEP 05

26 SEP 06

27 SEP 07

28 APR 08

29 OCT 08

30 OCT 09

31 SEP 10

32 NOV 11 (Edited in MAR 12)

5.06

72

CHECK LIST

R.N.R. Reason of Normal Revisions NOV 11 001

REV EDITION DATE REASON FOR ISSUE CHAP

INVOLVED

32 NOV 11 TR n°16 & n°17: Banking: - Unreliable airspeed indication EMERGENCY PROCEDURES ; -Content page : Updated - IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE: Procedure improved -ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE : Procedure improved - ENG FIRE AT TAKE OFF: New procedure - ENG FLAME OUT AT TAKE OFF: reviewed PROCEDURES FOLLOWING FAILURES : - ABNORMAL PROP BRK : Reviewed - DC BUS 1 OFF : Lost equipment updated NORMAL PROCEDURES : Entirely reviewed

1.10 & 1.11

1.01

1.02

1.02 1.02A 1.04

2.07

2.15 3.01 to 3.21 6.01


ATR72

S.N.N.P.Shipping Note Normal Pages

NOV 11

Action P CH SE Page Seq Date Validation Criteria

Turn LZ

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

"SEE VAL" = See Validation

DESTROY TR 001

...... 1 01 001 NOV 111 02 001 NOV 11

ADD 1 02A 001 NOV 11

...... 1 03 100 OCT 09 MOD 3973 or 4371 or 44571 04 500 NOV 11 PW127F-127M

ADD 1 09 100 APR 08 PW127-127F-127M1 10 500 NOV 11 PW127F-PW127M

ADD 1 11 500 NOV 11 PW127F-PW127M

ADD 2 07 500 NOV 11 MOD 3973 or 4371 or 44572 08 500 APR 08 MOD 3973 or 4371 or 4457

ADD 3 01 001 NOV 113 02 100 NOV 11 MOD 3973 or 4371 or 4457

DESTROY 3 01A 001 APR 08

DESTROY 3 02 500 APR 08 MOD 3973 or 4371 or 4457


ADD 3 03 100 NOV 11 MOD 3973 or 4371 or 44573 04 001 NOV 11

DESTROY 3 03 500 OCT 09 MOD 3973 or 4371 or 4457

DESTROY 3 04 050 OCT 09 MOD 4111

ADD 3 05 100 NOV 11 MOD 3973 or 4371 or 44573 06 100 NOV 11 MOD 3973 or 4371 or 4457

DESTROY 3 05 500 OCT 08 212A


ATR72


NOV 11


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ADD 3 07 001 NOV 113 08 001 NOV 11

ADD 3 09 100 NOV 11 MOD 3973 or 4371 or 44573 10 030 NOV 11 MOD 4111

ADD 3 11 100 NOV 11 MOD 3973 or 4371 or 44573 12 100 NOV 11 MOD 3973 or 4371 or 4457



ADD 3 17 001 NOV 113 18 160 NOV 11 PW127M MOD 5908

ADD 3 19 001 NOV 113 20 001 NOV 11

ADD 3 21 500 NOV 11 212A

...... 5 01 01 108 NOV 11 L.T.R. LZ

...... 5 02 01 001 NOV 11 R.T.R.

...... 5 04 01 108 NOV 11 L.E.T.P. LZ

...... 5 05 01 001 NOV 11 L.N.R.

...... 5 06 01 001 NOV 11 R.N.R.

...... 5 08 01 108 NOV 11 L.E.N.P. LZ

...... 5 09 01 108 NOV 11 L.O.M. LZ


ATR72


NOV 11


End LZ



...... 5 10 01 108 NOV 11 C.R.T. LZ

...... 6 01 100 NOV 11 MOD 3973 or 4371 or 4457


ATR72

L.E.N.P.List of Effective Normal Pages

NOV 11

You must hold in your manual the following normal pages

M P CH SE Page Seq Date LabelValidity expression

Turn LZ

NORMAL REVISION N° 32

0 01 001 OCT 08ALL

R 1 01 001 NOV 11R 1 02 001 NOV 11

ALL

N 1 02A 001 NOV 11ALL

1 03 100 OCT 09 MOD 3973 or 4371 or 4457R 1 04 500 NOV 11 PW127F-127M

ALL

1 04A 400 SEP 04 MOD 5465ALL

1 05 001 SEP 07ALL

1 05A 001 SEP 10ALL

1 06 002 OCT 09 102-202-212-212AALL

1 07 300 OCT 09 MOD 1603 +4116 +4366ALL

1 07A 100 SEP 07 MOD 3973 or 4371 or 4457ALL

1 08 001 OCT 09ALL

1 08A 001 OCT 09ALL

1 09 100 APR 08 PW127-127F-127MN 1 10 500 NOV 11 PW127F-PW127M

ALL

N 1 11 500 NOV 11 PW127F-PW127MALL

2 01 001 SEP 102 02 001 OCT 09

ALL

2 03 001 SEP 102 04 500 OCT 09 MOD 3973 or 4371 or 4457

ALL


ATR72


NOV 11


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2 05 001 OCT 082 06 001 SEP 10

ALL

N 2 07 500 NOV 11 MOD 3973 or 4371 or 44572 08 500 APR 08 MOD 3973 or 4371 or 4457

ALL

2 09 500 SEP 10 MOD 3973 or 4371 or 44572 10 050 OCT 09 MOD 4111

ALL

2 10A 500 SEP 10 MOD 3973 or 4371 or 4457ALL

2 11 500 SEP 10 PW127F-127M2 12 500 OCT 08 PW127F-127M

ALL

2 13 001 APR 082 14 500 OCT 09 MOD 4686 or 8148

ALL

2 15 550 OCT 09 MOD 4366 +(3973 or 4371 or 4457)ALL

2 15A 150 OCT 09 MOD 4116 +4366ALL

2 16 001 OCT 09ALL

2 16A 001 OCT 09ALL

2 17 001 OCT 082 18 500 OCT 08 MOD 3246 +4111

ALL

2 18A 550 APR 08 MOD 4116 +4366ALL

2 18B 500 APR 08 MOD 4116ALL

2 19 001 OCT 082 20 500 OCT 08 PW127-127F-127M MOD (3973 or 4371 or 4457)

ALL

2 21 500 APR 08 PW127-127F-127M MOD (3973 or 4371 or 4457)2 22 001 OCT 09

ALL

2 22A 500 APR 08 MOD 4373 or 8167ALL


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NOV 11


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2 23 001 APR 082 24 001 APR 08

ALL

2 25 001 SEP 102 26 001 APR 08

ALL

2 26A 001 OCT 08ALL

2 27 001 APR 082 28 500 APR 08 212A

ALL

2 29 500 OCT 09 MOD 3973 or 4371 or 44572 30 550 OCT 08 MOD 3168 +4366

ALL

2 30A 100 APR 08ALL

2 31 001 OCT 092 32 550 APR 08 212A MOD 5205

ALL

2 32A 200 OCT 09 MOD 4111ALL

2 33 001 SEP 102 34 001 OCT 08

ALL

2 35 001 OCT 082 36 001 OCT 08

ALL

2 37 001 OCT 082 38 001 OCT 08

ALL

2 39 001 OCT 082 40 001 OCT 08

ALL

2 41 001 OCT 082 42 150 APR 08 MOD 4116 +4366

ALL

R 3 01 001 NOV 11N 3 02 100 NOV 11 MOD 3973 or 4371 or 4457

ALL

N 3 03 100 NOV 11 MOD 3973 or 4371 or 4457R 3 04 001 NOV 11

ALL


ATR72


NOV 11


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R 3 05 100 NOV 11 MOD 3973 or 4371 or 4457N 3 06 100 NOV 11 MOD 3973 or 4371 or 4457

ALL

N 3 07 001 NOV 11N 3 08 001 NOV 11

ALL

N 3 09 100 NOV 11 MOD 3973 or 4371 or 4457N 3 10 030 NOV 11 MOD 4111

ALL

N 3 11 100 NOV 11 MOD 3973 or 4371 or 4457N 3 12 100 NOV 11 MOD 3973 or 4371 or 4457

ALL

N 3 13 100 NOV 11 MOD 3973 or 4371 or 4457N 3 14 001 NOV 11

ALL

N 3 15 100 NOV 11 MOD 3973 or 4371 or 4457N 3 16 001 NOV 11

ALL

N 3 17 001 NOV 11N 3 18 160 NOV 11 PW127M MOD 5908

ALL

N 3 19 001 NOV 11N 3 20 001 NOV 11

ALL

N 3 21 500 NOV 11 212AALL

4 01 500 APR 08 212AALL

4 11 500 APR 08 212AALL

4 11A 500 OCT 08ALL

4 12 500 APR 08 212AALL

4 12A 500 OCT 08ALL

4 13 500 APR 08 212AALL

4 13A 500 OCT 08ALL


ATR72


NOV 11


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4 31 500 OCT 08 212A4 32 500 OCT 08 212A

ALL

4 33 500 OCT 08 212A4 34 500 OCT 08 212A

ALL

4 35 500 OCT 08 212A4 36 500 OCT 09 212A

ALL

4 37 500 OCT 08 212A4 38 500 OCT 09 212A

ALL

4 39 500 OCT 08 212A4 40 500 OCT 09 212A

ALL

4 41 500 OCT 09 212A4 42 500 OCT 09 212A

ALL

4 43 500 OCT 09 212AALL

4 61 500 APR 08 212AALL

4 61A 500 OCT 08ALL

4 62 500 APR 08 212AALL

4 62A 500 OCT 08ALL

4 63 500 SEP 10 PW127F-127M4 64 500 OCT 08 212A

ALL

4 65 700 SEP 10 212A MOD 6055ALL

R 5 01 01 108 NOV 11 L.T.R. LZALL

R 5 02 01 001 NOV 11 R.T.R.ALL

R 5 04 01 108 NOV 11 L.E.T.P. LZALL

R 5 05 01 001 NOV 11 L.N.R.ALL


ATR72


NOV 11


End LZ

R 5 06 01 001 NOV 11 R.N.R.ALL

R 5 08 01 108 NOV 11 L.E.N.P. LZALL

R 5 09 01 108 NOV 11 L.O.M. LZALL

R 5 10 01 108 NOV 11 C.R.T. LZALL

R 6 01 100 NOV 11 MOD 3973 or 4371 or 4457ALL


ATR72

L.O.M.List of Modifications

NOV 11

MODIF PARTS TITLEVALIDITY

Turn LZ

1368 2.4 ICE AND RAIN PROTECTION - INSTALLINNER WING DE-ICING SYSTEM

ALL

1603 1 ELECTRICAL POWER - INSTALL TRU ONPROVISION

ALL

2735 4 ENGINE INDICATING - CHANGESOFTWARE AS 06 IN E.E.C

ALL

3168 2 AUTO FLIGHT - REPLACE AFCCOMPUTER

ALL

3246 2 ELECTRICAL POWER - ADD BATTERIESDISCHARGE INDICATION IN FLIGHT

ALL

3530 1.2 FLIGHT CONTROLS - ELEVATORS -INSTALL CLUTCH RECONDITIONINGDEVICE ON EXISTING PROVISION(PRODUCTION SCHEME)

ALL

3827 2 PROPELLERS - ADD FAILURE INDICATIONOF SYNCHROPHASER

ALL

4111 1.2.3.6 CONTINUOUS IGNITION -TRANSFORMATION IN "MAN IGNITION"

ALL

4116 1.2 HYDRAULIC POWER - RELOCATE GREENPUMP CONTROL CIRCUIT BREAKER

ALL

4237 2 INDICATING & RECORDING SYSTEMS -INSTALL STANDARD L52 MFC

ALL

4238 2 INDICATING & RECORDING SYSTEMS -INSTALL STANDARD L23 MFC

ALL

4366 1 AUTOFLIGHT - MODIFY ELECTRICALPOWER SUPPLIES

ALL


ATR72

L.O.M.List of Modifications

NOV 11

MODIF PARTS TITLEVALIDITY

End LZ

4371 1.2.3 PROPELLERS 14SF - 11E -PROPELLERCONTROL INSTALL ELECTRONICREGULATION ON ATR 72-200

ALL

4373 2 FLIGHT CONTROLS - AILERONSCONTROLS - INSTALL SPRING TAB

ALL

4457 1.2.3 PROPELLERS - INSTALL 568FPROPELLERS ON ATR 72-210

ALL

4686 2 CARBURANT - INDIC. QUANTITYINDICATION - ADD LOW LEVELDETECTION SYSTEM

ALL

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

ALL

5377 1.2.3.6 EQUIPMENT/FURNISHINGS - WIRING FORCOCKPIT ENTRANCE SECURISED

ALL

5434 1.2.3.6 EQUIPMENT/FURNISHINGS - INSTALLDOOR ON ELECTRICAL PROVISION

ALL

5465 2.3.6 EQUIPMENT/FURNISHINGS - SECURISEDDOOR INSTALLATION ON ELECTRICALSUPPLY

ALL

5561 4 LANDING GEAR-MLG-REPLACE DUNLOPWHEELS & BRAKES BY MESSIER-BUGATTI ONES

ALL

6055 LANDING GEAR - BRAKE ASSEMBLY -INSTALLATION OF NEW MESSIER-BUGATTI (MB) BRAKES

ALL


ATR72

C.R.T.Cross Reference Table

NOV 11

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 LZ

LZ0051 0879 F-ORAA

GUST LOCK....................................RELEASE FLIGHT CONTROLS ...........................CHECK

XPDR / TCAS *....................................CHECK AIR FLOW ............................................ NORM CCAS ............................... RCL then TO INHIB APM* ...................................SET AND CHECK BLEED VALVES .................................AS RQD EXT LIGHTS...............................................ON FD BAR (When lined up)....................CENTER RUDDER CAM ..................................CENTER

LDG GEAR ................................................. UP FLAPS ..........................................................0° PWR MGT / NP ......................... CLB / CHECK BLEED VALVES .........................................ON

TAXI & T.O LIGHTS.................................. OFF ALTIMETERS ............................ SET / CHECK

6.01

72


* : if applicable / if installed

Mod : 3973 or 4371 or 4457

FINAL COCKPIT PREPARATION

ALTIMETERS ........................................... SET PARKING BRK ...............ON / PRESS CHECK LANDING ELEVATION............................. SET COM / NAV / GPS..................................... SET

FUEL QTY ...........................................CHECK ENG F/U.............................................. RESET MEMO PANEL.....................................CHECK PWR MGT .................................................. TO

DESCENT

CCAS.........................................................RCL LDG ELEVATION................................. CHECK GNSS * ...................................... SET / CHECK LDG BUGS ................................ SET / CHECK ARRIVAL BREIFING..................... COMPLETE

CDLS *........................................................ON T/O BUGS ...........................SET AND CHECK TRIMS ...................................................... SET

TAIL PROP................................... ON BOARD DOORS .............................................CLOSED SEAT BELTS..............................................ON BEACON ....................................................ON

BEFORE TAXI

PROP BRK *............................................. OFF COCKPIT COM HATCH ....................CLOSED CL 1 + 2................................................. AUTO ANTI-ICING ........................................AS RQD

ANTI-SKID.............................................. TEST FLAPS ...................................................... SET NWS...........................................................ON

TAXI & T.O LIGHTS....................................ON BRAKES..............................................CHECK AFCS......................................... SET / CHECK TO CONFIG............................................ TEST TAKE OFF BRIEFING...................COMPLETE

BEFORE TAKE OFF

AFTER TAKE OFF

APPROACH

SEAT BELTS.............................................. ON LDG LIGHTS .............................................. ON ALTIMETERS ...................... SET AND CHECK CABIN ALTITUDE................................ CHECK

BEFORE LANDING

LDG GEAR ....................................... 3 GREEN FLAPS ................................................. CHECK PWR MGT ...................................................TO TLU......................................................LO SPD ICING AOA LIGHT............................... CHECK EXT LIGHTS............................................... ON

AFTER LANDING

RADAR....................................................STBY FLIGHT CONTROLS ......................... LOCKED FLAPS .......................................................... 0° TRIMS .......................................................SET LAND LIGHTS / STROBES........................OFF ANTI-/DE-ICING ........................................OFF � After at least one minute CL 1........................... FTR THEN FUEL SO

PARKING

PARKING BRK ...........................................ON TAXI & T.O LIGHTS.................................. OFF CL 2 ......................................................... FTR PROP BRK *...............................................ON BEACON .................................................. OFF TAIL PROP............................... ON POSITION SEAT BELTS............................................ OFF � When leaving 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 * ............................................... OFF

EXT PWR........................................... OFF BAT .................................................... OFF

IN CASE OF ICING CONDITIONS REFER TO 3.05 IN CASE OF SEVERE ICING REFER TO 1.09

ON GROUND EMER EVACUATION

AIRCRAFT / PARKING BRAKE...........................................................STOP / ENGAGE AUTO PRESS.......................................................................................................DUMP ATC (VHF 1).......................................................................................................NOTIFY CL 1 + 2......................................................................................... FTR THEN FUEL SO MIN CAB LIGHT ........................................................................................................ ON CABIN CREW (PA).............................................................................................NOTIFY FIRE HANDLES 1 + 2.............................................................................................PULL AGENTS............................................................................................................AS RQD ENG START ROTARY SELECTOR..............................................OFF / START ABORT FUEL PUMPS 1 + 2................................................................................................. OFF EVACUATION .................................................................................................. INITIATE � Before leaving aircraft, BAT............................................................................... OFF

TAXI

R

R

R

R

R BEFORE PROPELLER ROTATION

ATR 72-500 QRH

flight eng

flight constraints

pl flight path

pilot flying

aft smoke

ground eng

electrical smoke

fwd smoke

Text of ATR 72-500 QRH

AFM ATR 72-500

ATR 72 VS Q400

QEC_Atr_42_Rev15 Motor PW ATR 72

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ATR 72-600 Brochure 72-600 Brochure

EUROPEAN AVIATION SAFETY AGENCY - easa.europa.eu OEB ATR... · EASA Operational Evaluation Board ATR 42/72 – Fli ght Crew Qualifications ATR 42/72 OEB, Revision 03 page 3 Contents

ATR 42-72 CAPABILITY LIST - SPAREWAYSspareways.net/gallery/atr-capa list-spareways.pdf · 2019-07-12 · atr 42-72 capability list ... 1012974-4-002 eec-electronic engine control

PC/Mac - aerosoft-shop.com · 6.6 Electrical System ... 6.11 Fuel System ... The ATR 72 is the stretched version of the ATR 42 (which has capacity . ATR 72-500. ATR 72-500

Aircraft Part Number Manufacturer Nomenclature Aerospace ... · ATR-72 64050-663-1 Thales Airspeed Indicator Avions de Transport Régional ATR-72 C14129BA Thales Altimeter Avions

TRANSPORT CANADA MMEL SUPPLEMENT TO ATR 42 / ATR 72 … · 2015. 8. 12. · DRAFT TRANSPORT CANADA Master Minimum Equipment List Supplement ATR 42 / ATR 72 Page: II Revision: 04 13

Atr 72-500 Pilot Handbook

Ramp & Transit ATR 72

QRH ATR 42-300

Qrh Atr 72-Pec (m116 v13).PDF

ATR FAMILYUPDATEFOR RAAA NATIONAL CONVENTION 2014 · atr familyupdatefor raaa national convention 2014 1. ... first 72-500 delivery 2011 ... atr 72-200 1992 atr 72-210 1997 atr 72-500

Flight1 â€“ ATR 72-500

SERIOUS INCIDENT - AAIU UK ATR72-202 EI-SLG 07-12... · serious incident was conducted in conjunction with the ... were operating before setting ... ATR 72 QRH Section 2.22 A - TLU

ATR 72 - 500 Checklist / Flow-Procedure · ATR 72-500 Flight 1 ATR72-500 Created by Carsten Rau () Page 1 DO NOT USE FOR FLIGHT ATR 72 - 500 Checklist / Flow-Procedure including basic

ATR LIMITATIONS · 2010. 3. 11. · Design Weight Limitation ATR 42-500 Design Weight Limitation ATR 72-500 CG ENVELOPE 42-500. CG ENVELOPE 72-500. Airspeeds 42-500. Airspeeds 72-500

foreword · 2020. 11. 1. · review of the ATR operational documentation (AFM, FCOM & QRH). NB: ... 72 PEC refers to 72-500 42 PEC refers to 42-500 72 not PEC refers to 72-200/210

ATR 72-500 682 MAY 13

AERONAUTICS ATR 42-500 and 72-500 WSIMULATOR 7 ATR 42-500 and 72-500 6 Planet AeroSpace 1 | 2007 AERONAUTICS ATR TRAINING ORGANISATION Designing, building and selling aircraft is only

ATR 42/72 - 2013 - Thales Group · PDF fileATR THALES AVIONICS ELECTRICAL SYSTEMS TECHNICAL PUBLICATION ATR 42/72 - 2013 - ... Landing Gear Control Lever E 1 All ATR F0296 B3893-000

Atr 72 Normal Procedures

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ATR 72-500 QRH

Text of ATR 72-500 QRH