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0.01

72

GENERAL

OCT 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

R The boxed items correspond to actions performed by memory by the

crew 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 with

an 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.

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EMERGENCY 1.01

72 SEP 13 001

1 - EMERGENCY PROCEDURESContent 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

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 1.09RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL.. 1.10

UNRELIABLE AIRSPEED INDICATION. 1.10/11 R

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EMERGENCY 1.02

72 SEP 13 500

IN FLIGHT ENG FIREOR SEVERE MECHANICAL DAMAGE

PL affected side .................................................................................. FICL affected side .................................................. FTR THEN FUEL SOFIRE HANDLE affected side..........................................................PULL If condition persists after 10 seconds

AGENT 1 affected side .......................................................... DISCH If condition persists after 30 seconds

AGENT 2 affected side .......................................................... DISCH

LAND ASAPSINGLE ENG OPERATION procedure (2.04)............................APPLY

ON GROUND ENG FIREOR SEVERE MECHANICAL DAMAGE

PL 1 + 2............................................................GI / REVERSE AS RQD When aircraft stopped

PARKING BRAKE ............................................................. ENGAGECL 1 + 2 .......................................................... FTR THEN FUEL SOFIRE HANDLE affected side.....................................................PULL If condition persists

AGENT 1 affected side ...................................................... DISCH If condition persists after 30 seconds .......................................

AGENT 2 affected side ...................................................... DISCH

If evacuation requiredON GROUND EMER EVACUATION procedure (1.02)....APPLY

ON GROUND EMER EVACUATION

AIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGEAUTO PRESS.............................................................................. DUMPATC (VHF 1 / HF) ..................................................................... NOTIFYCL 1 + 2 ............................................................... FTR THEN FUEL SO

MIN CAB LIGHT ............................................................................... ONCABIN CREW (PA)................................................................... NOTIFYFIRE HANDLES 1 + 2....................................................................PULLAGENTS ...................................................................................AS RQDENG START ROTARY SELECTOR................... OFF / START ABORTFUEL PUMPS 1 + 2........................................................................ OFFEVACUATION (PA) .................................................................INITIATE Before leaving aircraft

BAT ............................................................................................ OFF

Model : 212A

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EMERGENCY 1.02A

72 SEP 13 500

ENG FIRE AT TAKE OFF

Note: Captain may decide to shut down affected engine before reachingacceleration altitude, but not before 400ft AGL.

When airborneLDG GEAR ...................................................................................UP

At Acceleration AltitudePWR MGT..................................................................................MCT

At VFTO If normal condition

FLAPS......................................................................................... 0 If icing condition

FLAPS.....................................................................MAINTAIN 15

PL affected side............................................................................. FICL affected side .............................................. FTR THEN FUEL SOFIRE HANDLE illuminated.. .............PULL If fire persist after 10 seconds

AGENT 1 affected side ...................................................... DISCH If fire persist after 30 secondsAGENT 2 affected side....................................................... DISCH

BLEED engine alive............................................... OFF if necessary

LAND ASAPSINGLE ENG OPERATION procedure (2.04) ...........................APPLY

Model : 212A

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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 ..................................................................... CHECKOPTIMUM SPEED.................................................................. VmHBCAPT EHSI................................................................................ OFFCOMMUNICATIONS .............................................................. VHF 1ENG START ROTARY SELECTOR............................START A & B

ENG 2 RELIGHTENG 2 START PB .................................................................. ONWhen NH above 10%

CL 2 ..................................................................................FTRENG 2 RELIGHT ....................................................MONITORCL 2 then PL 2...........................................................AS RQD

ENG 1 RELIGHTENG 1 START PB .................................................................. ONWhen NH above 10%

CL 1 ..................................................................................FTRENG 1 RELIGHT ....................................................MONITORCL 1 then PL 1...........................................................AS RQD

If neither engine startsCL 1 + 2 .......................................................... FTR THEN FUEL SOENG START ROTARY SELECTOR.............. OFF / START ABORTFUEL PUMPS 1 + 2................................................................... OFFFORCED LANDING (1.08A) or DITCHING (1.08) procedure ..........................................................................................................APPLY

CAUTION: Do not select AVIONICS VENT EXHAUST MODE toOVBD

If engine(s) recoveredCL / PL engine(s) recovered................................................AS RQDIf one engine not recovered

CL engine NON recovered ........................ FTR THEN FUEL SOSINGLE ENG OPERATION procedure (2.04)..................APPLY

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

Mod : 3973 or 4371 or 4457

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1.04

72

EMERGENCY

NOV 11 500

ENG FLAME OUT AT TAKE OFF

UPTRIM ..................................................................................... CHECK

AUTOFEATHER ........................................................................ CHECKIf no UPTRIM

PL 1 + 2 ................................................. ADVANCE TO THE RAMP

When airborneLDG GEAR ....................................................................................UPBLEED 1 + 2 .................................................... OFF, IF NOT FAULT

At Acceleration AltitudeALT .............................................................................................SET

At VFTOPL 1 + 2 ................................................................... IN THE NOTCHPWR MGT .................................................................................MCTIAS ..............................................................................................SET

If normal conditionFLAPS ........................................................................................ 0

If icing conditionFLAPS ....................................................................MAINTAIN 15

PL affected side ............................................................................. FICL affected side.............................................. FTR THEN FUEL SOBLEED engine alive............................................... OFF if necessary

If damage suspectedFIRE HANDLE affected side.....................................................PULLLAND ASAPSINGLE ENG OPERATION procedure (2.04).......................APPLY

If no damage suspected

ENG RESTART IN FLIGHT procedure (2.08).......................APPLYIf unsuccessful

LAND ASAPSINGLE ENG OPERATION procedure (2.04)..................APPLY

BOMB ON BOARD

AUTO PRESS - LANDING ELEVATION .................. CABIN ALTITUDEFLIGHT LEVEL ................................ DESCEND TO CABIN ALTITUDEAVOID LOAD FACTORSHANDLE BOMB CAREFULLY - AVOID SHOCKS

When Z aircraft = Z cabin

APPROACH CONFIG: FLAPS 15 GEAR DOWN ..........SELECTEDAUTO PRESS......................................................................... DUMPSERVICE DOOR ................................................................UNLOCK

PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAGATTACHED TO THE DOOR HANDLESURROUND IT WITH DAMPING MATERIAL

CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER........... ............................................................................ MOVE FORWARD

PAX................................... MOVE FORWARD / CRASH POSITIONLAND ASAP

Eng : PW127F / PW127M

R

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1.04A

72

EMERGENCY

SEP 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

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

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EMERGENCY 1.05

72 SEP 13 500

SMOKE

CREW OXY MASKS.............................................................ON / 100%GOGGLES .......................................................................................SETCREW COMMUNICATIONS ..............................................ESTABLISHRECIRC FANS 1 + 2 ...................................................................... OFFAP ..................................................................................................... ON

SMOKE SOURCE.................................................................. IDENTIFY If source not identified or electrical smoke suspected

Note: ELEC light may be activated by an air conditioning smokesource

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

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EMERGENCY 1.05A

72 SEP 13 500

ELECTRICAL SMOKE

SMOKE procedure (1.05) ...........................................................APPLYAVIONICS VENT EXHAUST MODE ........................................... OVBDAIR FLOW......................................................................................HIGHDC SVCE AND UTLY BUS............................................................. OFFDC BTC.......................................................................................... ISOLACW GEN 1 + 2.............................................................................. OFFSUSPECTED EQUIPMENTS ......................................................... OFF

If smoke origin not identifiedLAND ASAPACW TOTAL LOSS procedure (2.16A) .................................APPLY

If smoke origin identifiedNOT AFFECTED EQUIPMENTS .................................... RESTORE

When P below 1 PSIOVBD VALVE ................................................................FULL OPENAVIONICS VENT EXHAUST MODE ......................................NORM

AIR COND SMOKE

SMOKE procedure (1.05) ...........................................................APPLYPACK VALVE 1............................................................................... OFFMAX FL ..................................................................................200 / MEA

If smoke persists

PACK VALVE 1 ........................................................................... ONPACK VALVE 2 ......................................................................... OFFCAUTION: 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 abnormaloperation in order to avoid shutting down safe engine.

PL affected side ............................................................................. FICL affected side .............................................. FTR THEN FUEL SOLAND ASAPSINGLE ENG OPERATION procedure (2.04).......................APPLY

Model : 212A

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EMERGENCY 1.06

72 SEP 13 502

FWD SMK

SMOKE procedure (1.05) ...........................................................APPLY1) PASSENGERS VERSION

CABIN CREW (PA).............................................................. ADVISEAVIONICS VENT EXHAUST MODE ...................................... OVBDAIR FLOW ................................................................................HIGHEXTRACT AIR FLOW LEVER (RH MAINT PANEL)..........CLOSED

CABIN CREW W ITH PORTABLE EXTINGUISHER,LOCATE AND KILL SOURCE OF SMOKELAND ASAP

When

P below 1 PSIOVBD VALVE...........................................................FULL OPENAVIONICS VENT EXHAUST MODE.................................NORM

2) CARGO VERSIONCAB PRESS MODE SEL...........................................................MANCAB ALT ................................................................ MAX INCREASEENG 2 BLEED (Except when in single bleed operation)........... OFFPACK VALVE 2 (Except when in single pack operation) .......... OFFCAB VENT AIR FLOW .............................................................. OFFFLIGHT COMPT TEMP SEL .....................................................HOT

CAUTION: LAND ASAP. If a quick landing is not possible, climb andmaintain minimum FL160; FL200 is recommended. WhenExcess 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 VERSIONCABIN CREW (PA).......................................ADVISE FOR ACTIONAIR FLOW ................................................................................HIGH

2) CARGO VERSIONCAB PRESS MODE SEL...........................................................MANCAB ALT ................................................................ MAX INCREASE

ENG 2 BLEED (Except when in single bleed operation)........... OFFPACK VALVE 2 (Except when in single pack operation) .......... OFFCAB VENT AIR FLOW .............................................................. OFFFLIGHT COMPT TEMP SEL .....................................................HOT

CAUTION: LAND ASAP. If a quick landing is not possible, climb

and maintain minimum FL160; FL200 isrecommended. When Excess CAB ALT warning,maintain FL160, maintain CAB ALT maw increase.

Note: Smoke alert may be generated during smoke evacuationprocess.

AUX AFT COMPT SMK

(depending on models)

SMOKE procedure (1.05) ...........................................................APPLYAUX AFT COMPT AGENT ......................................................... DISCH

Model : 212A

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1.07

72

EMERGENCY

OCT 09 300

DUAL DC GEN LOSS

R

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

If no generator recoveredHYD GREEN PUMP.................................................................. OFFTRU.............................................................................................. ON

Make sure that TRU arrow illuminates, BAT arrows extinguishMAN RATE KNOB..........................................................9 O'CLOCKCAB PRESS MODE SEL...........................................................MANAVIONICS VENT EXHAUST MODE ...................................... OVBDBAT SW .................................................................................. OVRDATC (VHF 1 or HF or HF 2) ................................................. NOTIFYMIN CAB LIGHT ........................................................................ OFF

Note: NAV lights switch set to ON is necessary to provide IEPillumination

STICK PUSHER / SHAKER ...................................................... OFF STICK PUSHER / SHAKER FAULT procedure (2.21) ..........APPLY

SIDE WINDOWS ANTI-ICING................................................... OFFADC SW....................................................................SET TO ADC 1ATC SW.................................................................... SET TO ATC 1TLU ................................................................. MAN MODE LO SPD

When TLU LO SPD illuminatesTLU .....................................................................................AUTO

CAUTION: Avoid large rudder input if IAS above 180 kt

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

Before descentPAX INSTRUCTIONS .................................................... USE PAHYD X FEED .......................................................................... ONNote: Selecting HYD X FEED ON allows to recover green

hydraulic system

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

Mod : 1603 + 4116 + 4366

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EMERGENCY1.07A

72 SEP 13 100

EMERGENCY DESCENT

R

OXYGEN MASKS / CREW COMMUNICATIONS .................... AS RQD

GOGGLES ................................................................................ AS RQDDESCENT ................................................................................ INITIATEPL 1 + 2............................................................................................... FICL 1 + 2 ............................................................................. 100% OVRD

OXYGEN PAX SUPPLY ........................................................... AS RQDSPEED ........... MMO / VMO (or less if structural damage is suspected)SIGNS ............................................................................................... ONATC (VHF1 / HF) ...................................................................... NOTIFYMEA ........................................................................................... CHECK

Mod : 3973 or 4371 or 4457

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EMERGENCY 1.08

72 SEP 13 500

DITCHING

Preparation (time permitting)ATC (VHF1 or HF) ............................................................... NOTIFYXPDR ........................................................................ EMERGENCYCABIN CREW (PA).............................................................. NOTIFYSIGNS.......................................................................................... ONGPWS........................................................................................ OFFTERR (If TAWS installed) .......................................................... OFFCABIN AND COCKPIT .................................................... PREPARE

- Loose equipment secured- Survival equipment prepared- Belts and shoulder harnesses locked

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

Approach

AUTO PRESS......................................................................... DUMPPACKS 1 + 2.............................................................................. OFFOVBD VALVE ..............................................................FULL CLOSEHYD AUX PUMP pushbutton (pedestal) ......................... DEPRESSFLAPS (If available).......................................................................30LDG GEAR LEVER ......................................................................UP

30 seconds before impact or 1250 ft above sea levelDITCH PB .................................................................................... ONENG START ROTARY SELECTOR.............. OFF / START ABORTCABIN REPORT ............................................................. OBTAINED

Before ditching (200 ft)MINIMIZE IMPACT SLOPE

OPTIMAL PITCH ATTITUDE FOR IMPACT ................................. 9BRACE FOR IMPACT ..........................................................ORDER

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

CL 1 + 2 .......................................................... FTR THEN FUEL SOFIRE HANDLES 1 + 2 ..............................................................PULLFUEL PUMPS 1 + 2................................................................... OFF

After ditching

Note: After ditching, one aft door will be under the water line.

CABIN CREW (PA).............................................................. NOTIFYEVACUATION ....................................................................INITIATE

Before leaving aircraftBAT ........................................................................................ OFF

Model : 212A

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EMERGENCY 1.08A

72 SEP 13 500

FORCED LANDING

Preparation (time permitting)ATC (VHF1 or HF) ............................................................... NOTIFYXPDR ........................................................................ EMERGENCYCABIN CREW (PA).............................................................. NOTIFYSIGNS.......................................................................................... ONGPWS........................................................................................ OFFTERR (If TAWS installed) .......................................................... OFFCABIN AND COCKPIT .................................................... PREPARE

- loose equipment secured- survival equipment prepared- belts and shoulder harnesses locked

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

ApproachHYD AUX PUMP pushbutton (pedestal) ......................... DEPRESSFLAPS (If available).......................................................................30LDG GEAR LEVER .............................................................AS RQDAUTO PRESS......................................................................... DUMPENG START ROTARY SELECTOR.............. OFF / START ABORTCABIN REPORT ............................................................. OBTAINED

Before impact (200 ft)

BRACE FOR IMPACT ..........................................................ORDER

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

CL 1 + 2 .......................................................... FTR THEN FUEL SOFIRE HANDLES 1 + 2 ..............................................................PULLFUEL PUMPS 1 + 2................................................................... OFF

After impact, when aircraft stoppedCABIN CREW (PA).............................................................. NOTIFYAGENTS ................................................................................ DISCHEVACUATION ....................................................................INITIATE Before leaving aircraft

BAT ........................................................................................ OFF

Model : 212A

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EMERGENCY 1.09

72 SEP 13 500

SEVERE ICING

MINIMUM ICING SPEED .................................................... INCREASE 10 ktPWR MGT...............................................................................................MCTCL 1 + 2 ....................................................................................100% OVRDPL 1 + 2..............................................................................................NOTCHAP (if engaged) .......FIRMLY HOLD CONTROL WHEEL and DISENGAGESEVERE ICING CONDITIONS........................................................ESCAPEATC ................................................................................................... NOTIFY

If an unusual roll response or uncommanded roll controlmovement is observed :

Push firmly on the control wheelFLAPS..........................................................................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) ........................PROHIBITEDAPP/LDG CONF ..........................................MAINTAIN FLAPS 15APP SPEED ..... "REDUCED FLAPS 15 LDG icing speeds" + 5 ktMultiply landing distance FLAPS 30 by 2.12.

DETECTION

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

and / or

Unexpected decrease in speed or rate of climb

and / or

The following secondary indications :. Water splashing and streaming on the windshield. Unusually extensive ice accreted on the airframe in areas not 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-flighticing :. Visible rain at temperatures close to 0C ambient air temperature (SAT). Droplets that splash or splatter on impact at temperatures close to 0C

ambient air temperature (SAT)


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EMERGENCY 1.10

72 SEP 13 500

RECOVERY AFTER STALLor ABNORMAL ROLL CONTROL

RR

R

R

R

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

If flaps 0 configuration

FLAPS ........................................................................................... 15PWR MGT ...................................................................................MCTCL 1 + 2.........................................................................100 % OVRDPL 1 + 2..................................................................................NOTCHATC ....................................................................................... NOTIFY

If flaps are extendedPWR MGT ...................................................................................MCTCL 1 + 2.........................................................................100 % OVRD

PL 1 + 2..................................................................................NOTCHATC ....................................................................................... NOTIFY

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

UNRELIABLE AIRSPEED INDICATION

R AP/YD/FD .........................................................................OFF/OFF/STBYPITCH 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 ONAPM..................................................................................................... OFF

WARNING: respect STALL alarm.

Note: Use any GPS speed information if available.

Take off phase, at or above acceleration altitudeALTITUDE.................................... MAINTAIN AT LEAST 30 SECONDSFLAPS..................................................................................................0

PITCH .................................................................................................. 8Note: Use climb table here after to adjust pitch if required.

AFTER TAKE OFF normal procedure .........................................APPLYLAND AT THE NEAREST SUITABLE AIRPORT

ClimbTLU ............................................................................................ LO SPDPWR MGT........................................................................................ CLBPL 1 + 2.......................................................................................NOTCH

Altitude (ft) 5000 10000 15000 20000

Normal conditionspitch 7 5 4 3

Icing conditionspitch 6 4 3 2

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1.11

72

EMERGENCY

NOV 11 500

UNRELIABLE AIRSPEED INDICATION(CONTD)

CruiseALTITUDE ............................................................................... MAINTAINTLU............................................................................................... HI SPD

Note: Average pitch around 0at cruise speed

PWR MGT ......................................................................................... CRZPL 1 + 2 ........................................................................................NOTCH

DescentTLU............................................................................................... HI SPDPITCH........................................................................MAINTAIN AT -2.5PL 1 + 2 ........................................................................ ADJUST 30% TQDESCENT normal procedure........................................................APPLY

Initial ApproachTLU.............................................................................................. LO SPD

APPROACH normal procedure.....................................................APPLYCAUTION: Transition from clean configuration to LDG configuration is tobe performed in level flight - REFER TO ALTIMETER - (if possible 30seconds 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 .................................................................................... DOWNPWR MGT ........................................................................................... TOFLAPS ................................................................................................. 30

Flaps 30- 130 kt 45% 45% 50%

Final ApproachPL 1 + 2 ........................................................................ ADJUST 35% TQBEFORE LANDING normal procedure ......................................... APPLY

Note: Set an average pitch of -5for a 3slope approac h.

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FOLLOWING FAILURES 2.01

72 SEP 13 500

2 - PROCEDURES FOLLOWING FAILURESContent 1/3

POWER PLANTSINGLE ENG OPERATION. 2.04START FAULT... 2.04X START FAIL 2.04

ABNORMAL PARAMETERS DURING START 2.05EXCESSIVE ITT DURING START. 2.05NO ITT DURING START.. 2.05NO NH DURING START.. 2.05ENG NAC OVHT 2.06

ABNORMAL ENG PARAMETERS IN FLIGHT 2.06FIRE LOOP FAULT.. 2.06

ABNORMAL PROP BRK. 2.07ENG RESTART IN FLIGHT. 2.08ENG STALL 2.08

ONE EEC FAULT.. 2.09BOTH EEC FAULT 2.09ENG FLAME OUT. 2.10IDLE GATE FAIL 2.10SYNPHR FAIL (if applicable) . 2.10ACL PNEUMATIC ACTUATOR BLOCKING (if applicable) . 2.10AUNCOMMANDED100%NPONONEORTWOPROPELLERS(if applicable) 2.10APEC SGL CH (if applicable) 2.10APEC FAULT (if applicable) .. 2.10ALO PITCH IN FLIGHT... 2.11ENG OVER LIMIT. 2.11PROP OVER LIMIT.. 2.11ENG OIL TEMP BELOW 45C 2.12ENG OIL TEMP HIGH.. 2.12ENG OIL LO PR. 2.12

ENG BOOST FAULT (if applicable) .. 2.12A

FUEL

FUEL ABNORMAL TEMP 2.13FUEL CLOG 2.13FUEL FEED LO PR... 2.13FUEL LEAK ALERT CONDITION.. 2.14FUEL LO LVL. 2.14FUEL LEAK 2.14

ELEC

DC BUS 1 OFF . 2.15AC BUS 1 OFF . 2.15DC BUS 2 OFF . 2.15A

AC BUS 2 OFF . 2.15AACW BUS 1 OFF / ACW BUS 2 OFF 2.16ACW TOTAL LOSS.. 2.16ADC ESS BUS OFF 2.17DC EMER BUS OFF. 2.17DC GEN FAULT. 2.18INV FAULT. 2.18

ACW GEN FAULT. 2.18DC SVCE/UTLY BUS SHED 2.18BAT CHG FAULT.. 2.18DUAL BAT CHG LOSS. 2.18BAT DISCHARGE IN FLIGHT (if applicable) ... 2.18

STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS... 2.18A2.18B

ESS BUS AND EMER BUS LOST EQUIPMENT LISTS.

Cargo configuration only..

2.42

2.42A

Model : 212A

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2.02

72

FOLLOWING FAILURES

OCT 09 001


HYDRAULIC

R HYD LO LVL .. 2.19BOTH MAIN HYD PUMPS LOSS .. 2.19BOTH HYD SYS LOSS 2.20HYD LO PR / HYD OVHT 2.20

FLIGHT CONTROLFLAPS UNLK . 2.21FLAPS JAM / UNCOUPLED / ASYM 2.21REDUCED FLAPS LANDING . 2.21STICK PUSHER / SHAKER FAULT .. 2.21PITCH TRIM ASYM (LOCAL LIGHT) 2.22PITCH TRIM INOPERATIVE .. 2.22DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTER UNIT FAIL ....... 2.22PITCH DISCONNECT . 2.22PITCH RECONNECTION ON GROUND (If applicable) 2.22ATLU FAULT 2.22A

AIL LOCK LIT (if applicable) ... 2.22AELEVATOR JAM .. 2.23AILERON JAM / SPOILER JAM . 2.23RUDDER JAM ... 2.23

LANDING GEARLDG GEAR GRAVITY EXTENSION . 2.24LANDING WITH ABNORMAL LDG GEAR .. 2.24LDG GEAR UNSAFE INDICATION .. 2.25LDG GEAR RETRACTION IMPOSSIBLE 2.25ANTI-SKID FAULT 2.25BRK TEMP HOT ... 2.25

AIRBLEED VALVE FAULT 2.26

BLEED OVHT 2.26BLEED LEAK 2.26X VALVE OPEN 2.26PACK VALVE FAULT .. 2.26BOTH PACK VALVES FAULT 2.26RECIRC FAN FAULT ... 2.26DUCT OVHT .. 2.26AEXCESS CAB ALT ... 2.26AAUTO PRESS FAULT . 2.26AEXCESS CAB P . 2.26AAVIONICS VENT EXHAUST MODE FAULT ... 2.27OVBD VALVE FAULT .. 2.27

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2.03

72

FOLLOWING FAILURES

SEP 10 001


ANTI ICE

AFR AIR BLEED FAULT . 2.28DE-ICING AIR FRAME FAULT .. 2.28DE-ICING MODE SEL FAULT 2.28MODE SEL AUTO FAULT (if applicable) . 2.28ICE DETECT FAULT 2.29DE- / ANTI-ICING ENG FAULT . 2.29ANTI-ICING PROP FAULT . 2.29ANTI-ICING HORNS FAULT .. 2.29SIDE WINDOW / WINDSHIELD HTG FAULT . 2.29PROBES 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) . 2.30PITCH TRIM FAIL (ADU message) (if applicable) .. 2.30DADC DATA INVALID (ADU message) 2.30

MPCAPM FAULT .. 2.30ADEGRADED PERF .. 2.30AINCREASE SPEED . 2.30A

AVIONICSAUDIO SEL FAULT .. 2.31AHRS A / ERECT FAIL 2.31EFIS COMP ... 2.31ADC SW FAULT ... 2.31ADU FAILURE .. 2.32ADC FAULT .. 2.32

AHRS FAIL 2.32SGU FAIL .. 2.32CRT FAIL .. 2.32

MISCELLANEOUSCOCKPIT DOOR CONTROL PANEL FAULT (if installed) 2.32AVOLCANIC ASH ENCOUNTER . 2.32ALOSS OF RADIO ALTIMETER INFORMATION . 2.33

R SMK DET FANS FAULT . 2.33DOORS UNLK IN FLIGHT . 2.33COCKPIT WINDOW CRACKED 2.33OXYGEN LO PR .. 2.33

MFCMFC 1A FAULT 2.34

MFC 1B FAULT 2.34MFC 2A FAULT 2.35MFC 2B FAULT 2.35MFC 1A + 1B FAULT ... 2.36MFC 1A + 2A FAULT ... 2.37MFC 1A + 2B FAULT ... 2.38MFC 1B + 2A FAULT ... 2.39MFC 2A + 2B FAULT ... 2.40MFC 1B + 2B FAULT ... 2.41

ELEC Section for EMER & ESS BUS lost equipment lists.Cargo configuration only

2.422.42A

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2.04

72

FOLLOWING FAILURESPOWER PLANT

OCT 09 500

SINGLE ENG OPERATION

R

R

LAND ASAP

PWR MGT.................................................... TO if necessary then MCTFUEL PUMP affected side.............................................................. OFFDC GEN affected side .................................................................... OFFACW GEN affected side ................................................................. OFFPACK affected side......................................................................... OFFBLEED affected side....................................................................... OFFAPM (if installed)............................................................................. OFFTCAS (if installed)................................................................... TA ONLYOIL PRESSURE ON FAILED ENGINE .................................MONITORNote: 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 beinformed.Note: monitor fuel balance. Recommended operational maximum fuel

unbalance is 200 kg (440 lb).

When FUEL CROSS FEED is requiredFUEL PUMP affected side........................................................... ONFUEL X FEED.............................................................................. ONFUEL PUMP operating engine .................................................. OFF

For approachMAX APPROACH SLOPE for Steep Slope Approach ............... 5.5

BLEED NOT AFFECTED .......................................................... OFFCL live engine............................................................... 100% OVRD

APPROACH SPEED ........................... NOT LESS THAN 1.1VMCANote: Refer to page (4.64) to determine 1.1VMCA.

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

START FAULT

ENG START ROTARY SELECTOR................... OFF / START ABORTIf above 45 % NH

START ON LIGHT....................................CHECK EXTINGUISHEDSTART ............................................................. TO BE CONTINUED

X START FAIL

CONTINUE NORMAL ENGINE STARTINFORM MAINTENANCE

Mod : 3973 or 4371 or 4457

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FOLLOWING FAILURES

POWER PLANT2.04

72 JUL 15 500

SINGLE ENG OPERATION

LAND ASAPPWR MGT .................................................. TO if necessary then MCTFUEL PUMP affected side ............................................................ OFFDC GEN affected side .................................................................. OFFACW GEN affected side ............................................................... OFFPACK affected side ...................................................................... OFFBLEED affected side .................................................................... OFFAPM (if installed) .......................................................................... OFFTCAS (if installed) ................................................................ TA ONLYOIL PRESSURE ON FAILED ENGINE ............................... MONITORNote: 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 beinformed.

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

When FUEL CROSS FEED is requiredFUEL PUMP affected side ......................................................... ONFUEL X FEED ........................................................................... ONFUEL PUMP operating engine ................................................. OFF

For approachMAX APPROACH SLOPE for Steep Slope Approach ............... 5.5

BLEED NOT AFFECTED ........................................................ OFFCL live engine ............................................................ 100% OVRD

V APP ......................................................... NOT LESS THAN VGAIf affected engine NP above 10%

V APP ........................ NOT LESS THAN LDG SPEED + 10ktIf V APP is increased

LDG DISTANCE ..........................................MULTIPLY BY 1.13

Note: Refer to part 4 to determine VGA, and landing distance.

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

START FAULT

ENG START ROTARY SELECTOR .................. OFF / START ABORTIf above 45 % NH

START ON LIGHT ................................... CHECK EXTINGUISHEDSTART ........................................................... TO BE CONTINUED

X START FAIL

CONTINUE NORMAL ENGINE STARTINFORM MAINTENANCE

Mod : 3973 or 4371 or 4457

R

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2.05

72


OCT 08 001

ABNORMAL PARAMETERSDURING START

If ITT tends to exceed 900C, 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 950C, 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.

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2.06

72


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

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2.07

72


NOV 11 500

ABNORMAL PROP BRK (if applicable)

Ifon ground

If unexpected propeller rotation or If local UNLK and CCAS PROP BRK alert

CL 2 .............................................................................. FUEL SOMAINTENANCE ACTION REQUIRED

If CCAS PROP BRK alert only

If GUST LOCK ONCL 2 ......................................................................... FUEL SO

If DC and AC GPU are not availableENG 1.....................................................................STARTCL 1..........................................................................AUTO

When READY light illuminatesPROP BRK................................................................. OFFUNLK LIGHT ............................. CHECK EXTINGUISHEDPROP BRK PWR SPLY C/B .....................................PULL

If GUST LOCK OFFGUST LOCK...................................................................... ON

According to operational situationPROP BRK................................................................. OFFALL PROP BRK LIGHTS ..........CHECK EXTINGUISHED

Ifin flightCONTINUE NORMAL OPERATIONENG 2 PARAMETERS .....................................................MONITOR

After landingCL 2 .............................................................................. FUEL SOMAINTENANCE ACTION REQUIRED

Mod : 3973 or 4371 or 4457

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2.08

72


APR 08 500

ENG RESTART IN FLIGHT

FUEL SUPPLY...........................................................................CHECKCL ...........................................................................................FUEL SOPL........................................................................................................ FI

CAUTION: After ATPCS sequence, PWR MGT rotary selector mustbe set to MCT position before engine restart, in order tocancel propeller feathering.

ENG START ROTARY SELECTOR................................ START A & BEEC PB............. RESET if necessary or DESELECT if FAULT persistsSTART PB ........................................................................................ON

At 10 % NHCL ...............................................................................................FTRRELIGHT ..........................................................................MONITORCL ............................................................................................AUTOPL......................................................ADJUST TO OTHER ENGINEENG START ROTARY SELECTOR....................................AS RQDSYSTEMS AFFECTED....................................................RESTORE

ENG STALL

PL affected side .................................................................................. FIENG PARAMETERS .................................................................CHECK

If abnormal engine parametersCL affected side.............................................. FTR THEN FUEL SOSINGLE ENG OPERATION procedure (2.04).......................APPLY

If normal engine parametersDE-/ANTI-ICING ENG .................................................................ONPL affected side ...............................................SLOWLY ADVANCE

If stall recursReduce thrust and operate below the stall threshold

If stall does not recurContinue engine operation

Mod : 3973 or 4371 or 4457

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2.09

72


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 successful

ATPCS .................................................................................... 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 ............................................................................................ OFFCAUTION: 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 ............................................................................. OFF

PL 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 rain

MAN IGN ........................................................................... ON

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

After landingBRAKE HANDLE........................................... EMER AS RQD

CAUTION: Reverse power is reduced.Both main HYD pumps will be lost at low speed.TAXI ON BOTH ENGINES,HANDLE THROTTLES W ITH CARE

Mod : 3973 or 4371 or 4457

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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 suspectedFIRE HANDLE affected side ...............................................PULLSINGLE ENG OPERATION procedure (2.04)..................APPLY

If no damage suspectedENG RESTART IN FLIGHT procedure (2.08)..................APPLY

If unsuccessfulSINGLE ENG OPERATION procedure (2.04) ............APPLY

IDLE GATE FAIL

In flightIDLE GATE LEVER .................................................................PUSH

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

Mod : 4111

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2.10A

72


SEP 10 500

R

R

UNCOMMANDED 100% NP ON ONE ORTWO PROPELLERS

RR

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

PEC SGL CH

DO NOT RESET PEC IN FLIGHT - NO SPECIAL CREW ACTIONANTICIPATE A PEC FAULT AT LANDINGMAINTENANCE IS REQUIRED

PEC FAULT

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

Above 400 ft or when adequateCL affected side............................................................ 100% OVRDPEC affected side..................................................................RESETIf successful

CL affected side..................................................................AUTOIf unsuccessful

PEC affected side................................................................. OFFAvoid sudden PL movementsBefore landing

CL NON AFFECTED .......................................... 100% OVRDReverse is not available on affected side.

TAXI ON BOTH ENGINESNote: ACW BTC may be check closed in order to avoid the lossof ACW bus on ground

Mod : 3973 or 4371 or 4457

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2.11

72


SEP 10 500

LO PITCH IN FLIGHT


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

PROP OVER LIMIT

RRRRRRRRR

PL affected side .......................... RETARD TO SET NP BELOW 106%PEC affected side .............................................................OFF then ONPL affected side .......................................................................AS RQD

If NP decreases below 106%CONTINUE NORMAL FLIGHTNote: 106% allowed to complete a flight without overshooting 73%

TQ in CRZ and 75% in CLB

If NP remains above 106% and conditions permitPL affected side .............................................................................. FI

CL affected side ............................................... FTR THEN FUEL SOSINGLE ENG OPERATION procedure (2.04) ........................APPLY


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2.12

72


OCT 08 500

ENG OIL TEMP BELOW 45C

If icing conditions are expected or presentENG POWER ...............................................If possible, INCREASE

ENG OIL TEMP HIGH

OIL TEMP between 125C and 140COIL TEMP AND PRESS ...................................................MONITORNote: 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 OILtemperature.

OIL TEMP between 125C and 140C for more than 20 minutesPL affected side...........RETARD TO SET minimum possible powerCAUTION: Flight plan must be rescheduled to minimize engine

operating time in these abnormal conditions.

OIL TEMP above 140CPL affected side............................................................................. FICL affected side.............................................. FTR THEN FUEL SOSINGLE ENG OPERATION procedure (2.04).......................APPLY

ENG OIL LO PR

R


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

If local alert only is activatedCL affected side.............................................. FTR THEN FUEL SOOnce engine is shut offCL affected side..........................................................................FTR

If CCAS is activated after 30 seconds

CL affected side............................................................ FUEL SOENG RESTART IN FLIGHT procedure (2.08)..................APPLY

If notCL affected side ............................................................FUEL SOSINGLE ENG OPERATION procedure (2.04)..................APPLY

If OIL LO PR alert on CAP only is activatedDISREGARDINFORM MAINTENANCE

If sing le engine operation requiredNP of feathered engine.....................................................MONITORIf NP of feathered engine above 10%

APPROACH SPEED .................................INCREASE BY 10 KT


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FOLLOWING FAILURESFUEL

2.13

72 SEP 13 500

FUEL ABNORMAL TEMP

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

If too low (

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2.14

72

FOLLOWING FAILURESFUEL

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+FUsignificantly 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 ONLAND ASAP

If LO LVL light on one side onlyIf leak suspectedFUEL LEAK procedure (2.14)...........................................APPLY

If no leak suspectedIf FQI < 160 kg / 352 lb

X FEED.............................................................................. ONIf FQI 160 kg / 352 lb,

Feeder jet pump malfunction is suspectedX FEED is not necessaryFUEL CONSUMPTION ..........................................MONITOR

FUEL LEAK

When a leak is confirmedLAND ASAP

Leak from engine (excessive fuel flow or feed spray from engine)PL affected side........................................................................ FICL affected side......................................... FTR THEN FUEL SOPUMP affected side.............................................................. OFFFIRE HANDLE affected side ...............................................PULLSINGLE ENG OPERATION procedure (2.04)..................APPLY

If excessive fuel flow was identified before engine shutdownFUEL X FEED valve can be opened

In all other cases X FEED valve must remain closed

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

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

Before landingATC................................................................................. NOTIFY

Mod : 4686 or 8148

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2.15

72

FOLLOWING FAILURESELEC

OCT 09 550

DC BUS 1 OFF

DC GEN 1 ....................................................................................... OFFPF.................................................................................................... CM2MAN RATE KNOB ...............................................................9 O'CLOCKCAB PRESS MODE SEL................................................................MANDC SVCE AND UTLY BUS SHED..................................MAINTAIN ONAFFECTED EQUIPMENT............................................................... OFFDC BUS 1 EQUIPMENT LIST ................................................... CHECKAt touch down

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

DC BUS 1 LOST EQUIPMENT LIST

Instruments, Navigation & Com:Weather RadarRadio Altimeter (2.33)(E)GPWSDME #1

Air:Bleed LEAK IND 1 & 2AUTO PRESS(2.26A)Flight controls:Stick Pusher (2.21)CM1 Stick Shaker (2.21)

Ice & Rain protection:CM1 and STBY Static Ports anti-icingCM1 Side Window Anti-Icing (2.32)CM2 Windshield HTG INDEngines:FF/FU#1,Fuel TEMP#1 & Fuel CLOG #1Oil PRESS & Oil TEMP #1AUTO IDLE GATE (2.10)Light:CM1 Dome, chartholder & reading lightCM2 Flood panel lightStorm light, Annunciator light testNAV & BEACON lightMiscellaneous: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 ONIf 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)

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2.15A

72


OCT 09 150

DC BUS 2 OFF

DC GEN 2 ....................................................................................... OFFPF.................................................................................................... CM1ADC SW.........................................................................SET TO ADC 1VHF 1 / ATC 1...........................................................................SELECTAFFECTED EQUIPMENT............................................................... OFFDC BUS 2 EQUIPMENT LIST ................................................... CHECKBefore descent

PAX INSTRUCTIONS.......................................................... USE PAAfter touch down

TAXI ON BOTH ENGINES

DC BUS 2 LOST EQUIPMENT LIST

RR

RRRRRRRRRRRRRR

R

Instruments, Navigation & Com:CM2 EADI/EHSI & SGU#2 (2.32)VOR/ILS/DME#2, ADF#2, CM1 RMI

VHF#2ATC#2, TCAS or T2CAS (if installed)ADC #2 & ALT ALERT # 2 (2.32)CM2 ClockGPS (KLN90) (if installed)CCAS:CAP amber alert except MaintPNL, PRKG BRK & MFCAir:Landing elevation INDHydraulic:DC AUX HYD PUMP (In Automatic)Landing gear:Secondary INDFlight controls:Right stick shakerStandby pitch trim controlTLU auto control

Ice & Rain protection:CM2 Static Port anti-icingCM2 Probes IND

CM2 WiperCM2 Side window anti-icing (2.29)CM1 Windshield HTG INDEngines:FF/FU #2FUEL TEMP #2, FUEL CLOG #2OIL PRESS, TEMP #2IDLE GATE FAIL INDLight:CM2 Chartholder, Reading LIGHTSIntegrated Norm INST&PANEL LIGHTSTaxi / Take off LIGHT, Wing LIGHTSPassenger SignsDoors:Doors UNLK lightsCockpit door locking system

Fire:NAC OVHT

RR

RRRRRRRRRRRRRR

R

AC BUS 2 OFF

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

DC BTC......................................................................... ISOL THEN ONIf unsuccessful

PF .............................................................................................. CM1AC 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, ALTIHeading RMI#1Bearing VOR#2&ADF#2 to RMI/SGU 1/2Course#2 and Heading#2 Select

RRR


Mod : 4116 + 4366

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2.16

72


OCT 09 001

ACW BUS 1 OFF / ACW BUS 2 OFF

ACW GEN affected side ................................................................. OFF

LEAVE AND AVOID ICING CONDITIONSAS LONG AS ICING CONDITIONS EXIST

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

If ACW BUS 1 OFFPF .............................................................................................. CM2CM1 AIRSPEED INDICATOR ..........................................MONITOR

If ACW BUS 2 OFFPF .............................................................................................. CM1CM2 AIRSPEED INDICATOR ..........................................MONITOR

AFFECTED EQUIPMENT............................................................... OFFHYD X FEED .................................................................................... ONACW BUS 1 or 2 LOST EQUIPMENT LIST .............................. CHECK

If any IAS discrepancy occurs

DADC DATA INVALID (ADU message) procedure (2.30) ....APPLYAfter touch down

TAXI ON BOTH ENGINES

ACW BUS 1 LOST EQUIPMENT LIST

RRRRRR

Hydraulic:BLUE PUMPLights:

Integrated INST&PNL LightsLEFT LANDING LIGHTLEFT and REAR STROBES

Ice & Rain protection:CM1 PITOT / ALPHA / TAT HeatingANTI-ICING PROP 1ANTI-ICING HORNS (LH ELEV, RUD)CM1 WINDSHIELD HTGMiscellaneous:Toilet (If supplied by ACW)

RRRRRRR

ACW BUS 2 LOST EQUIPMENT LIST

RRRRRR

Hydraulic:GREEN PUMPLights:TAXI/TO LIGHTSRIGHT LANDING LIGHTRIGHT STROBE

Ice & Rain protection:CM2 PITOT / ALPHA / TAT HeatingANTI-ICING PROP 2ANTI-ICING HORNS (RH ELEV, AIL)CM2 Windshield HTGICE DETECTOR

RRRRRR

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2.16A

72


OCT 09 001

ACW TOTAL LOSS

ACW GEN 1 + 2.............................................................................. OFF

HYD X FEED .....................................................................CHECK OFFLEAVE AND AVOID ICING CONDITIONSAS LONG AS ICING CONDITIONS EXIST

ICE ACCRETION........................................... VISUALLY MONITORCM1 and CM2 AIRSPEED INDICATORS........................MONITOR

ACW TOTAL LOSS EQUIPMENT LIST .................................... CHECKAFFECTED EQUIPMENT............................................................... OFFMAIN HYD PUMPS......................................................................... OFFLDG GEAR EXTENSION/RETRACTION ..................................... LOSTNORMAL BRAKE ......................................................................... LOSTLDG DIST ................................................................. MULTIPLY BY 1.5Note: Refer to Part 4 to determine LDG DIST

Before landingLDG GEAR LEVER ............................................................... DOWN

BLUE PRESSURE................................................................ CHECKFLAPS..................................................................................AS RQDLDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLY

After touch downREVERSE............................................................................AS RQD

BRAKE HANDLE..................................................... EMER AS RQDTAXI ON BOTH ENGINES

ACW TOTAL LOST EQUIPMENT LIST

RRRR

RR

Hydraulic:BLUE & GREEN PUMPLights:

Integrated INST&PNL Lights

LEFT & RIGHT LANDING LIGHTTAXI/TO LIGHTS

Ice & Rain protection:CM 1&2 PITOT/ALPHA/TAT HeatingANTI-ICING PROP 1&2ANTI-ICING HORNS

CM1&2 WINDSHIELD HTGICE DETECTORMiscellaneous:Toilet (If supplied by ACW)

RRRR

RRRR


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2.17

72


OCT 08 001

DC ESS BUS OFF

DC ESS BUS EQUIPMENT LIST ..............................................CHECK If Cockpit Securized Door installed

COCKPIT 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

R

R

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)........................APPLY

ANTI-ICING HORNS FAULT procedure (2.29) .....................APPLYCM1 and STBY IAS............................................COMPARE to CM2Note: Use CM2 instruments in case of disagreement.

Before landing

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

DC EMER BUS OFF LOST EQUIPMENT LIST

R See QRH pages 2.42 (all configuration)

and 2.42A (for cargo configuration only)


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2.18A

72

FOLLOWING FAILURES

ELECAPR 08 550

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116 + 4366

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2.18B

72

FOLLOWING FAILURES

ELECAPR 08 500

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116

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2.19

72

FOLLOWING FAILURESHYDRAULIC

OCT 08 001

HYD LO LVL

If blue system affectedBLUE PUMP.............................................................................. OFF

AUX PUMP.......................................................OFF (CONFIRMED)REDUCED FLAPS LANDING procedure (2.21)....................APPLY

Af ter touch downUSE NORMAL BRAKE FOR STEERINGTAXI ON BOTH ENGINES

If green system affectedGREEN PUMP........................................................................... OFFLDG DIST ............................................................MULTIPLY BY 1.5Note:Refer to Part 4 to determine landing distanceLDG GRAVITY EXTENSION procedure (2.24).....................APPLY

Af ter touch downTAXI ON BOTH ENGINESREVERSE.......................................................................AS RQDBRK HANDLE..................................................... EMER AS RQD

HYD SYS LOST EQUIPMENT LIST

BLUE GREEN

FLAPS / SPOILERS / N/W STEERINGPROP BRK (if applicable)EMER AND PARKING BRK (on accuonly)

LDG GEAR EXT / RETNORM BRK

BOTH MAIN HYD PUMPS LOSS

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

Before landingLDG GEAR LEVER ...............................................................DOWNBLUE PRESSURE................................................................CHECKFLAPS 15 ............................................................................AS RQDLDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLY

FLAPS 30 ............................................................................AS RQDAf ter touch down

TAXI ON BOTH ENGINESREVERSE............................................................................AS RQDBRK HANDLE.......................................................... EMER AS RQD

BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST

RR

BLUErecovered when

LDG GEAR lever is DOWNGREEN

RRR

FLAPS / SPOILERS / N/W STEERINGPROP BRK (if applicable)

EMER AND PARKING BRK (on accuonly)


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2.20

72

FOLLOWING FAILURESHYDRAULIC

OCT 08 500

BOTH HYD SYS LOSS

R

RRR

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

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

CAUTION: Tail strike may occur if pitch attitude exceeds 8duringthe flare depending upon vertical speed at touchdown.

After touch downREVERSE............................................................................AS RQDBRK HANDLE.......................................................... EMER AS RQDTAXI ON BOTH ENGINES

BOTH HYD SYS LOST EQUIPMENT LIST

R BLUE GREEN

RRR

FLAPS / SPOILERS / N/W STEERINGPROP BRK (if applicable)EMER AND PARKING BRK (on accuonly)


HYD LO PR / HYD OVHT

PUMP affected side ........................................................................ OFFX FEED ............................................................................................. ON

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

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2.21

72

FOLLOWING FAILURESFLIGHT CONTROL

APR 08 500

FLAPS UNLK

If before V1TAKE OFF ............................................................................ABORT

If after V1VR, V2.............................................................INCREASE BY 10 KT

If alarm occurs during approachGO AROUND procedure .......................................................APPLYVGA ................................................................INCREASE BY 10 KT

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

FLAPS JAM / UNCOUPLED / ASYM

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

When applicableREDUCED FLAPS LANDING procedure (2.21)....................APPLY

REDUCED FLAPS LANDING

GPWS.............. GPWS OVRD or FLAP OVRD (depending on version)

STEEP SLOPE APPROACH (4.5)............................... PROHIBITED

FLAPSLDG DISTFLAPS 30

MULTIPLY BYAPP/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 theflare depending upon vertical speed at touch down.

STICK PUSHER / SHAKER FAULT

STICK PUSHER / SHAKER ........................................................... OFFTCAS (if installed)................................................................... TA ONLYVmHB / VmLB FOR ALL CONFIGURATION ......INCREASE BY 10 KTLDG DIST ...............................................................MULTIPLY BY 1.13Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

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

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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)...........................PROHIBITEDFLAPS................ EXTEND AT VFE FOR EACH CONFIGURATIONLDG SPEED ...................................................INCREASE BY 10 KTLDG 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 availableYD ...................................................................................... ENGAGE

If YD is not availableLOCK THE RUDDER PEDALS WITH THE FEET TO PREVENTUNEXPECTED RUDDER PEDAL MOVEMENT

PITCH DISCONNECT

BOTH CONTROL COLUMNS ........................................ CHECK FREEIAS ....................................................................................... 180 kt MAXLOAD FACTOR ............................................................................... 2 g MAXBANK ANGLE............................ 30MAX UNTIL FLAPS EXTENSION

AVOID ICING CONDITIONS

For approach

STEEP SLOPE APPROACH (4.5)...........................PROHIBITEDLAND AT AIRPORT WITH MINIMUM CROSSWINDLDG SPEED ...................................................INCREASE BY 10 KTLDG DIST .......................................................... MULTIPLY BY 1.13

PL 1 + 2 ..................................... REDUCE SMOOTHLY TO FLARENote: Refer to Part 4 to determine LDG DATA

When on ground and ELEV CLUTCH GUARDED PB installedPITCH RECONNECTION ON GROUND procedure (2.22A)............

...............................................................................................APPLY

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FOLLOWING FAILURES

FLIGHT CONTROL2.22

72 JUL 15 100

PITCH TRIM ASYM (LOCAL LIGHT)

AP DISCONNECTION ..................................... CONFIRM MANUALLYPITCH 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) .......................... PROHIBITEDFLAPS ............... EXTEND AT VFE FOR EACH CONFIGURATION

LDG SPEED................................................. INCREASE BY 10 KTLDG DIST ........................................................MULTIPLY BY 1.13

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

DUTCH ROLL TENDENCY /RUDDER RELEASABLE CENTERING

UNIT FAIL

If YD is availableYD .................................................................................. ENGAGE

If YD is not available

LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENTUNEXPECTED RUDDER PEDAL MOVEMENT

PITCH DISCONNECT

BOTH CONTROL COLUMNS ...................................... CHECK FREEIAS .................................................................................... 180 kt MAXLOAD FACTOR............................................................................2 g MAXBANK ANGLE ........................... 30MAX UNTI L FLAPS EXTENSION

AVOID ICING CONDITIONS

For approachSTEEP SLOPE APPROACH (4.5) .......................... PROHIBITED

LAND AT AIRPORT WITH MINIMUM CROSSWINDLDG SPEED................................................. INCREASE BY 10 KTLDG DIST ........................................................MULTIPLY BY 1.13PL 1 + 2 .................................... REDUCE SMOOTHLY TO FLARE

Note: Refer to Part 4 to determine LDG DATA

At parkingIf pitch disconnect occurred in flight

MAINTENANCE ACTION REQUIRED

If pitch disconnect occurred on ground

PITCH RECONNECTION ON GROUND procedure (2.22A) ................. APPLY

Mod 3529 or 3530

R

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2.22A

72


APR 08 500

PITCH RECONNECTION ON GROUND(if applicable)

GUST LOCK ...........................................................................ENGAGEBOTH COLUMNS......................................................CHECK LOCKEDELEV CLUTCH GUARDED PB.........................DEPRESS AND HOLD

When PITCH DISCONNECT flashes red on CAPELEV CLUTCH GUARDED PB ........................................RELEASEPITCH DISCONNECT ON CAP ...............CHECK EXTINGUISHEDBOTH COLUMNS.............................................. CHECK COUPLED

TLU FAULT

If ADC 1 + 2 are lost

If IAS above 185 ktTLU...................................................................................HI SPD

If IAS below 185 ktTLU................................................................................. LO SPD

DISREGARD TLU FAULT ALERT

If at least one ADC operates

If IAS above 185 ktTLU...................................................................................HI SPD

If TLU FAULT alarm persistsSPEED ...............................................................180 KT MAXTLU............................................................................ LO SPD

If IAS below 185 ktSPEED.....................................................................180 KT MAXTLU................................................................................. LO SPDDISREGARD TLU FAULT ALERT

If TLU green light is not litVAPP....................................................INCREASE BY 10 KTLDG DIST ................................................MULTIPLY BY 1.13

LAND AT AIRPORT WITH MINIMUM CROSSWIND

Note: Maximum demonstrated crosswind (dry runway) with TLU HI SPDmode : 15 kt.

AIL LOCK LIT

If before take offRETURN TO PARKINGREFER TO MMEL ATA 27 ITEM 70-1 GUST LOCK SYSTEM

If after landingTAKE SPECIAL CARE FOR TAXI (WIND EFFECTS)USE STANDBY SYSTEM FOR AILERON LOCK AT PARKINGINFORM MAINTENANCE

Mod : 4373 or 8167

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2.23

72


APR 08 001

ELEVATOR JAM

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

AVOID ICING CONDITIONSIAS .....................................................................................180 KT MAX

If one elevator is stuck to ful l down positionIAS ................................................................................154 KT MAX

If left elevator is jammedMINIMUM MANEUVER OPERATING SPEEDS..........INCREASE BY 10 KT

If elevator jamming occurs at take offIAS ................................................................................161 KT MAX

PITCH DISCONNECT procedure (2.22).....................................APPLY

AILERON JAM / SPOILER JAM

BANK ANGLE LIMIT................................................................ 25 MAXBLUE AND AUX HYD PUMPS....................................................... OFFLAND AT AIRPORT WITH MINIMUM CROSSWIND

For approach

STEEP SLOPE APPROACH (4.5).......................... PROHIBITEDBLUE AND AUX HYD PUMPS.................................................... ON

CAUTION: Do not extend FLAPS in turn

When in landing configuration

BLUE AND AUX HYD PUMPS.................................................. OFFImmediately after touch down

BLUE AND AUX HYD PUMPS.................................................... ON

RUDDER JAM

STEEP SLOPE APPROACH (4.5)............................... PROHIBITEDLANDING...............................................................................FLAPS 30USE DIFFERENTIAL POWER SO AS TO MINIMIZE SIDESLIPLAND AT AIRPORT WITH MINIMUM CROSSWIND

At touch down

NOSE DOWN BEFORE REDUCTION BELOW FI

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2.24

72

FOLLOWING FAILURESLANDING

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