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    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

    RThe 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 withan amber caution may be performed by selecting OFF then ONrelated 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 SHARINGFor all procedures, the general task sharing stated below is

    applicable. 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

    JUN 10 001

    1 - EMERGENCY PROCEDURES

    Content 1/1

    R 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

    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 SMK ................................................................................... 1.05A

    AIR COND SMOKE................................................................................... 1.05A

    FWD SMK ................................................................................................. 1.06

    AFT SMK................................................................................................... 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 UNCOMMANDED ROLL CONTROL....................................................1.10

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    EMERGENCY

    OCT 09 001

    IN FLIGHT ENG FIREOR SEVERE MECHANICAL DAMAGE

    PL affected side .................................................................................. FICL affected side .................................................. FTR THEN FUEL SOFIRE HANDLE affected side..........................................................PULL After 10 seconds

    FIRST AGENT affected side.................................................. DISCH If fire after further 30 seconds

    SECOND AGENT 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.....................................................PULLFIRST AGENT affected side.................................................. DISCH If fire after further 30 seconds

    SECOND AGENT affected side ........................................ DISCH

    If evacuation required

    ON GROUND EMER EVACUATION procedure (1.02)....APPLY

    ON GROUND EMERGENCYEVACUATION

    RAIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGEAUTO PRESS.............................................................................. DUMPATC (VHF 1) ............................................................................. 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

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    EMERGENCY

    JUN 10 100

    BOTH ENGINES FLAME OUT

    R

    R

    R

    ENG START ROTARY SELECTOR............................CONT RELIGHT

    PL 1 + 2............................................................................................... FIIf 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 .................................................................. ON When NH above 10 %

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

    ENG 1 RELIGHTENG 1 START PB .................................................................. ON When 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.......................................................... RESTOREENG START ROTARY SELECTOR.......................CONT RELIGHT

    Mod : 0332 or 3420

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    ENG FLAME OUT AT TAKE OFF

    R

    R

    ENG START ROTARY SELECTOR............................CONT RELIGHTUPTRIM ..................................................................................... CHECKAUTOFEATHER ........................................................................CHECK If no UPTRIM

    PL 1 + 2 ....................................................................... SET AT RTO

    Above 400 ft AGLPL affected side ............................................................................. FICL affected side .............................................. FTR THEN FUEL SO

    If damage suspected

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

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

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

    BOMB ON BOARD

    AUTO PRESS - LANDING ELEVATION .................. CABIN ALTITUDEFLIGHT LEVEL................................ DESCEND TO CABIN ALTITUDEAVOID LOAD FACTORS

    HANDLE BOMB CAREFULLY - AVOID SHOCKS

    When Z aircraft = Z cabinAPPROACH 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

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    APR 08 001

    SMOKE

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

    SMOKE SOURCE..................................................................IDENTIFYIf source not identified or electrical smoke suspected

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

    ELECTRICAL SMOKE procedure (1.05A) ............................APPLYIf air conditioning smoke identified

    AIR COND SMOKE procedure (1.05A).................................APPLYIf FWD SMK illuminated or smoke in FWD zone of aircraft

    FWD SMOKE procedure (1.06).............................................APPLYIf AFT SMK illuminated or smoke in AFT zone of aircraft

    AFT SMOKE procedure (1.06) ..............................................APPLY

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    FWD SMK

    R SMOKE procedures (1.05) .........................................................APPLY

    1) PASSENGERS VERSIONCABIN CREW (PA).............................................................. ADVISEDC SVCE AND UTLY BUS........................................................ OFFAVIONICS VENT EXHAUST MODE ...................................... OVBDAIR FLOW ................................................................................HIGHEXTRACT AIR FLOW LEVER (RH MAINT PANEL)..........CLOSED

    CABIN CREW WITH PORTABLE EXTINGUISHER,LOCATE AND KILL SOURCE OF SMOKE

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

    2) CARGO VERSIONSMOKE procedures (1.05) ....................................................APPLY

    CAB 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, climband maintain minimum FL160; FL200 isrecommended.

    Note: Smoke alert may be generated during smoke evacuationprocess.

    AFT SMK

    R SMOKE procedures (1.05) .........................................................APPLY

    1) PASSENGERS VERSIONSMOKE procedures (1.05) ....................................................APPLYCABIN CREW (PA)....................................... ADVISE FOR ACTIONAIR FLOW ................................................................................HIGH

    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, climband maintain minimum FL160; FL200 isrecommended.

    Note: Smoke alert may be generated during smoke evacuationprocess.

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    EMERGENCY

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    DUAL DC GEN LOSS

    R

    R

    R

    R

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

    If no generator recoveredLAND ASAP, flight under IMC must be limited to 30 minutesBAT SW .................................................................................. OVRDNote: If after a restart, a DC GEN becomes operative, set BAT SW

    to ONCAPT EHSI................................................................................ OFFATC (VHF 1 or HF or HF 2) ................................................. NOTIFYPAX INSTRUCTIONS.......................................................... USE PADESCENT TOWARDS FL 100 / MEA ................................INITIATEAVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDE

    MIN CAB LIGHT ........................................................................ OFF

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

    STICK PUSHER / SHAKER ...................................................... OFFSTICK PUSHER / SHAKER FAULT procedure (2.21) ..........APPLYCAUTION: Do not select AVIONICS VENT EXHAUST MODE to

    OVBDMAIN BATTERY CHARGE (on LH maintenance panel) ...... CHECKBUS EQUIPMENT LIST (2.18A 2.18B) ............................. CHECK

    When P < 1 PSI

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

    If STBY BUS UNDV light illuminates

    STBY BUS...............For approach, OVRD only when necessary

    Before descent

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

    hydraulic system

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

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    EMERGENCY

    APR 08 001

    EMERGENCY DESCENT

    OXYGEN MASKS / CREW COMMUNICATIONS ....................AS RQDGOGGLES ................................................................................AS RQDDESCENT................................................................................INITIATEPL 1 + 2............................................................................................... FICL 1 + 2 .................................................................................MAX RPMENG START ROTARY SELECTOR............................CONT RELIGHT

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

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    DITCHING

    R

    R

    R

    Preparation (time permitting)ATC (VHF1 or HF or HF2) ................................................... NOTIFYCABIN 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

    IfP0AUTO PRESS..................................................................... DUMP

    PACKS 1 + 2.............................................................................. OFFOVBD VALVE ..............................................................FULL CLOSEFLAPS.......................................................................................... 30

    Note: if A/C is clear of ice, flaps can be extended to 45 (if available)

    LDG GEAR LEVER ......................................................................UP

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

    Before ditching (200 ft)MINIMIZE IMPACT SLOPE

    OPTIMAL PITCH ATTITUDE FOR IMPACT ................................. 9BRACE FOR IMPACT ..........................................................ORDERCL 1 + 2 .......................................................... FTR THEN FUEL SOFIRE HANDLES 1 + 2 ..............................................................PULLFUEL PUMPS 1 + 2................................................................... OFF

    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).

    After ditching

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

    CABIN CREW (PA).............................................................. NOTIFYEVACUATION ....................................................................INITIATE Before leaving aircraft

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

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    OCT 09 001

    FORCED LANDING

    R

    R

    R

    Preparation (time permitting)ATC (VHF1 or HF or HF2) ................................................... NOTIFYCABIN 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

    FLAPS.......................................................................................... 30Note: if A/C is clear of ice, flaps can be extended to 45 (If available)

    LDG GEAR LEVER .............................................................AS RQDAUTO PRESS......................................................................... DUMPENG START ROTARY SELECTOR.............. OFF / START ABORTCABIN REPORT ............................................................. OBTAINED

    Before impact (200 ft)BRACE FOR IMPACT ..........................................................ORDERCL 1 + 2 .......................................................... FTR THEN FUEL SOFIRE HANDLES 1 + 2 ..............................................................PULLFUEL PUMPS 1 + 2................................................................... OFF

    Note: In case of night forced landing, shutting down both engines

    may be performed at captain discretion, immediately afterthe impact (avoiding loss of landing lights during flare out).

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

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

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    SEVERE ICING

    R

    MINIMUM ICING SPEED..............................INCREASE RED BUG by 10 ktPWR MGT...............................................................................................MCTCL / PL .......................................................................................100% / MCTAP (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.........................................................................................15

    If the flaps are extended, do not retract them unti l the airframe isclear of ice.

    If the aircraft is not clear of ice :GPWS ............................................................FLAP/GPWS OVRD

    STEEP SLOPE APPROACH (4.5) ....................... PROHIBITEDAPP/LDG CONF ..........................................MAINTAIN FLAPS 15

    with "REDUCED FLAPS APP/LDG icing speeds" + 5 ktLDG DIST FLAPS 30......................................MULTIPLY BY 1.22

    DETECTION

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

    and / orUnexpected 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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    R

    RECOVERY AFTER STALLor UNCOMMANDED ROLL CONTROL

    R

    CONTROL WHEEL........................................................ PUSH FIRMLYIf flaps 0configuration

    FLAPS........................................................................................... 15PWR MGT...................................................................................MCTCL / PL ............................................................................100% / MCTATC ....................................................................................... NOTIFY

    If flaps are extendedPWR MGT...................................................................................MCTCL/PL ................................................................................100%/MCTATC ....................................................................................... NOTIFY

    Note: This procedure is applicable whatever the LDG GEAR position is(DOWN or UP)

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    FOLLOWING FAILURES

    JUN 10 001

    2 - PROCEDURES FOLLOWING FAILURES

    Content 1/3

    R POWER PLANT

    SINGLE ENG OPERATION............................................................................. 2.04START FAULT................................................................................................. 2.04X START FAIL ................................................................................................. 2.04ABNORMAL PARAMETERS DURING START................................................ 2.05EXCESSIVE ITT DURING START................................................................... 2.05NO ITT DURING START.................................................................................. 2.05NO NH DURING START.................................................................................. 2.05NAC OVHT....................................................................................................... 2.06ABNORMAL ENG PARAMETERS IN FLIGHT ................................................ 2.06FIRE LOOP FAULT.......................................................................................... 2.06ABNORMAL PROP BRK.................................................................................. 2.07ENG RESTART IN FLIGHT ............................................................................. 2.08ENG STALL ..................................................................................................... 2.08ONE ECU FAULT ............................................................................................ 2.09BOTH ECU FAULT.......................................................................................... 2.09ENG FLAME OUT............................................................................................ 2.10

    IDLE GATE FAIL.............................................................................................. 2.10SYNPHR FAIL.................................................................................................. 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

    FUEL

    FUEL ABNORMAL TEMP................................................................................ 2.13FUEL CLOG..................................................................................................... 2.13FEED 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 ................................................................................................ 2.15AAC 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....................................................................................................... 2.18ACW GEN FAULT............................................................................................ 2.18DC SVCE/UTLY BUS SHED............................................................................ 2.18BAT CHG FAULT............................................................................................. 2.18

    BAT 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..................................For cargo configuration only... ....

    For aircraft fiited with mod 4116 only.......

    2.422.42A2.42B

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    2 - PROCEDURES FOLLOWING FAILURES

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    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 CONTROL

    FLAPS UNLK ................................................................................................... 2.21FLAPS JAM / UNCOUPLED ............................................................................ 2.21REDUCED FLAPS LANDING .......................................................................... 2.21STICK PUSHER / SHAKER FAULT................................................................. 2.21PITCH TRIM FAIL / ASYM (depending on version) ......................................... 2.22PITCH TRIM INOPERATIVE............................................................................ 2.22DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTER UNIT FAIL.. 2.22PITCH DISCONNECT...................................................................................... 2.22ELEVATOR JAM.............................................................................................. 2.23AILERON JAM / SPOILER JAM....................................................................... 2.23

    RUDDER JAM.................................................................................................. 2.23

    LANDING GEAR

    LDG 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

    AIR

    BLEED VALVE FAULT..................................................................................... 2.26BLEED OVHT .................................................................................................. 2.26BLEED LEAK ................................................................................................... 2.26X VALVE OPEN............................................................................................... 2.26

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

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    ANTI ICE

    R AFR AIR BLEED FAULT .................................................................................. 2.28DE-ICING AIR FRAME FAULT ........................................................................ 2.28DE-ICING MODE SEL 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 / NOSE UP (DN) (ADU message) (depending on version)... 2.30

    DADC DATA INVALID (ADU message) ........................................................... 2.30

    MPC

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

    AVIONICS

    AUDIO SEL FAULT.......................................................................................... 2.31AHRS A / ERECT FAIL .................................................................................... 2.31EFIS COMP ..................................................................................................... 2.31CCAS FAULT................................................................................................... 2.31ADU FAILURE ................................................................................................. 2.32ADC FAULT ..................................................................................................... 2.32AHRS FAIL....................................................................................................... 2.32SGU FAIL......................................................................................................... 2.32

    CRT FAIL ......................................................................................................... 2.32

    MISCELLANEOUS

    COCKPIT DOOR CONTROL PANEL FAULT (if installed)............................... 2.32AVOLCANIC ASH ENCOUNTER....................................................................... 2.32ALOSS OF RADIO ALTIMETER INFORMATION .............................................. 2.33AFT COMPT / LAV DET FANS FAULT............................................................ 2.33DOORS UNLK IN FLT...................................................................................... 2.33COCKPIT WINDOW CRACKED ...................................................................... 2.33OXYGEN LO PR.............................................................................................. 2.33

    MFC

    NOT APPLICABLE........................................................................................... 2.34

    See ELEC Section ...........................................................................................

    2.42

    2.42A2.42B

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    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

    SINGLE ENG OPERATION

    R

    LAND ASAP

    CL operating side...................................................................MAX RPMPWR MGT.................................................... TO if necessary then MCTSYNPHR ......................................................................................... OFFFUEL PUMP affected side.............................................................. OFFDC GEN affected side .................................................................... OFFACW GEN affected side ................................................................. OFFPACK affected side......................................................................... OFFBLEED affected side....................................................................... OFFAPM ................................................................................................ 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 thefailed 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 on operating ENG ................................................ OFF

    For approachMAX APPROACH SLOPE for Steep Slope Approach ............... 5.5BLEED NOT AFFECTED .......................................................... OFFAPPROACH SPEED ........................... NOT LESS THAN 1.1VMCA

    Note: Refer to page (4.64) to determine 1.1VMCA.If landing is performed FLAPS 45 (emergency or if permitted)

    FLAPS 30 ..................... MAINTAIN UNTIL COMMITTED TO LAND

    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

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    2.06

    42

    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

    NAC OVHT

    R

    R

    R

    RR

    Ifduring Hotel mode operationPL affected side ............................................................................. GI

    CL affected side.............................................. FTR THEN FUEL SO Ifduring taxi

    AIRCRAFT...............................................................................STOPPL affected side ............................. SLIGHTLY INCREASE POWER

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

    ABNORMAL ENG PARAMETERSIN FLIGHT

    R

    If Intermittent fluctuations or unrealistic steady indication

    ATPCS....................................................................................... OFF When adequate flight situation

    ECU affected side ............................................................. OFF If fluctuations stop or indication are realistic

    ONE ECU FAULT procedure (2.09) .........................APPLY If unsuccessful

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

    FIRE LOOP FAULT

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

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    2.07

    42

    FOLLOWING FAILURES

    POWER PLANTOCT 08 001

    ABNORMAL PROP BRK (if applicable)

    R

    Ifon 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 ONCL 2 ......................................................................... FUEL SO

    If DC and AC GPU are not availableENG 1.....................................................................START

    CL 1 ...................................................................MAX RPM

    When READY light illuminatesPROP BRK................................................................. OFF

    UNLK LIGHT .............................CHECK EXTINGUISHED

    PROP BRK PWR SPLY C/B .....................................PULL

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

    According to operational situationPROP BRK................................................................. OFF

    ALL PROP BRK LIGHTS ..........CHECK EXTINGUISHED

    Ifin flightCONTINUE NORMAL OPERATION

    ENG 2 PARAMETERS .....................................................MONITOR

    After landingCL 2 .............................................................................. FUEL SO

    MAINTENANCE ACTION REQUIRED

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    2.08

    42

    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

    ENG RESTART IN FLIGHT

    R

    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.

    ECU ............................................................................................RESETENG START ROTARY SELECTOR..................START / START A & BSTART PB ........................................................................................ ON

    At 10 % NHCL ...............................................................................................FTRRELIGHT ..........................................................................MONITOR

    ECU .............................................. DESELECT IF FAULT PERSISTCL THEN PL ..................................... ADJUST TO OTHER ENGINEENG START ROTARY SELECTOR....................................AS RQDSYSTEMS AFFECTED.................................................... RESTORE

    ENG STALL

    PL affected side .................................................................................. FIENG START ROTARY SELECTOR............................CONT RELIGHTENG 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

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    2.09

    42

    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

    ONE ECU FAULT

    R

    RR

    ECU affected side ........................................................................... OFFPL affected side............................. ADVANCE TO RESTORE POWER

    When adequate flight situationPL affected side ............................................ RETARD BELOW 60ECU affected side..................................................................RESET If successful

    PL affected side...................ADVANCE TO RESTORE POWER If unsuccessful

    ECU affected side ................................................................ OFFPL affected side.................. ADVANCE TO RESTORE POWER

    In case of flame outENG RESTART IN FLIGHT procedure (2.08).......................APPLY

    If unsuccessfulENG affected side C/B ECU / PWR SPLY (2 C/Bs)............PULL

    ENG RESTART IN FLIGHT procedure (2.08)..................APPLY

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

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

    BOTH ECU FAULT

    R

    ECU 1 + 2 ....................................................................................... OFFPL 1 + 2..........................................ADVANCE TO RESTORE POWER When adequate flight situation

    PL 1 + 2 ........................................................ RETARD BELOW 60ECU 1 + 2 ..............................................................................RESET If ECU 1 + 2 recovered

    PL 1 + 2 ............................... ADVANCE TO RESTORE POWER If only one ECU recovered

    ONE ECU FAULT procedure (2.09) .................................APPLY If no ECU recovered

    ECU 1 + 2 ............................................................................ OFFPL 1 + 2 .............................. ADVANCE TO RESTORE POWER

    In case of flame outENG RESTART IN FLIGHT procedure (2.08).......................APPLY

    If unsuccessfulENG affected side C/B ECU / PWR SPLY (2 C/Bs)............PULL

    ENG RESTART IN FLIGHT procedure (2.08)..................APPLY

    For approachSTEEP SLOPE APPROACH (4.5).................PROHIBITEDLDG DIST .................................................. MULTIPLY BY 1.4Note: Refer to Part 4 to determine landing distance

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

    CAUTION: Braking will be performed by first depressing the pedalsto use the remaining green hydraulic pressure. Reverse power isreduced. Both main HYD pumps will be lost at low speed.

    TAXI ON BOTH ENGINES

    Note: Minimize time spent in this condition to minimum ( NP restricted band)

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    2.10

    42

    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

    ENG FLAME OUT

    RR

    ENG START ROTARY SELECTOR............................CONT RELIGHT

    PL affected side .................................................................................. FIIf 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

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    2.10A

    42

    FOLLOWING FAILURES

    POWER PLANTAPR 08 001

    SYNPHR FAIL

    SYNPHR......................................................................................... OFF

    NP 1 + 2.......................................................................................ALIGN

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    42

    FOLLOWING FAILURES

    POWER PLANTAPR 08 050

    SYNPHR FAIL

    SYNPHR ......................................................................................... OFF

    NP 1 + 2.......................................................................................ALIGN

    SYNPHR ...........................................................................................ON

    If failure persistsSYNPHR....................................................................................OFF

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    2.11

    42

    FOLLOWING FAILURESPOWER PLANT

    JUN 10 001

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

    If TQ, NH, and/or ITT still in amber sectorEngine operation may be continued until next landing

    PROP OVER LIMIT

    RRR

    PL and CL affected side . RETARD TO RESTORE NORMAL VALUESNote: If conditions do not permit engine shut down, 110% is allowed to

    complete the flight. An engine removal has to be done formaintenance action on arrival.

    If NP decreases below 101%CONTINUE NORMAL FLIGHT

    If NP remains above 101% and conditions permitPL affected side ............................................................................. FICL affected side.............................................. FTR THEN FUEL SOSINGLE ENG OPERATION procedure (2.04).......................APPLY

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    2.12

    42

    FOLLOWING FAILURESPOWER PLANT

    OCT 09 001

    ENG OIL TEMP BELOW 45C

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

    ENG OIL TEMP HIGH

    OIL TEMP between 115C and 125COIL 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 115C and 125C 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 125C

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

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

    If CONT RELIGHT is required by current flight conditions,maintain ON as long as necessary and keep the affected engineshut off. Apply SINGLE ENG OPERATION procedure (2.04)

    When CONT RELIGHT is not required by flight conditions

    CONT RELIGHT................................................................... OFF

    CL affected side .....................................................................FTR

    If CCAS is activated after 30 secondsCL 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 single engine operation required

    NP of feathered engine.....................................................MONITOR If NP of feathered engine above 10%

    IAS ........................................LIMIT NOT TO EXCEED NP 101%APPROACH SPEED INCREASE BY 10 KT

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    2.13

    42

    FOLLOWING FAILURESFUEL

    APR 08 001

    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

    42

    FOLLOWING FAILURESFUEL

    APR 08 001

    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, andfuel 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

    AVOID EXCESSIVE AIRCRAFT ATTITUDES

    If both LO LVL lights ONLAND ASAP

    If LO LVL light on one side onlyFUEL LEAK procedure (2.14)................................................APPLY

    FUEL LEAK

    zWhen a leak is confirmed LAND 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 CLOSEDNote: the X FEED must remain closed to prevent the leak

    affecting both sides.

    zBefore landingATC.................................................................................NOTIFY

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    2.15

    42

    FOLLOWING FAILURESELEC

    JUN 10 070

    DC BUS 1 OFF

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

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

    DC BUS 1 LOST EQUIPMENT LIST

    (*) = Items lost if TRU not installed

    Instruments, Nav and Comm:Weather Radar, Radio Altimeter,(E)GPWS/TAWS, TCAS, CM1 EHSI, DME#1

    (*) ADC#1, ALT ALERT#1(*) ADF#1, HF#1, CM2 RMICCAS:MC light, CAP caution lightExcept CCAS, GPWS, MAINT PNL, PRK BRKAir:AUTO PRESS(*)BLEED 1 & BLEED 1 FAULT, OVHT 1(*)LEAK Ind 1 + 2(*) PACK 1 & PACK 1 IndAutopilot:AFCS ComputerFlight controls :Stick Pusher, CM2 Stick shaker

    Ice and Rain protection:CM1 & STBY Static ports anti-icingCM1 Side windows anti-icingCM1 Windshield HTG Ind(*) CM1 WiperEngine:FF/FU #1, FUEL TEMP #1, FUEL CLOG #1,OIL PRESS, TEMP #1AUTO IDLE GATELights:CM1 Dome, Chartholder, Reading LightsCM2 Flood panels,Storms Lights, ANNUNCIATOR LT TEST,NAV, BEACON, TAXI/TO Lights(*) LH LDG LightsPAX reading light,Misc: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 LOST EQUIPMENT LIST.................................... CHECK

    AC BUS 1 LOST EQUIPMENT LIST

    R 115 AC BUS 1 26 AC BUS 1 R

    R

    (*) = Items lost if TRU not installed

    Weather Radar

    BLEED LEAK Detector

    TRIMS IND(*) CM1 ASI/VSI/ALTI

    (*) TAS/TEMP IND(*) ALT REF for ADC1 & FDAU

    For more information on BUS EQUIPMENT LISTS see FCOM 1.06.80

    Mod : 2973 + 1977

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    2.15A

    42

    FOLLOWING FAILURESELEC

    JUN 10 070

    DC BUS 2 OFF

    RRR

    DC GEN 2 ....................................................................................... OFFPF.................................................................................................... CM1

    VHF 1 / ATC 1...........................................................................SELECTHYD X FEED .................................................................................... ONAFFECTED EQUIPMENT............................................................... OFFDC BUS 2 EQUIPMENT LIST ................................................... CHECKBefore descent

    PAX INSTRUCTIONS.......................................................... USE PA

    CAUTION: In case of go around, gear retraction is not available, except ifthere is a LDG GEAR RET OVRD Pushbutton installed. In thiscase the PB must be depressed to retract the landing gears.

    After touch downTAXI ON BOTH ENGINES

    DC BUS 2 LOST EQUIPMENT LIST

    (*) = Items lost if TRU not installed

    Instruments, Nav and Comm:CM2 EADI/EHSI, SGU#2, VOR/ILS/DME#2,ADF#2 , CM1 RMI, VHF#2 HF#2, ATC#2ADC #2 , ALT ALERT# 2, CM2 Clock, TCAS,GPS/GNSS, GPWS Fault IndAir:Landing Elevation IND(*) BLEED 2 & BLEED FAULT#2, OVHT Ind #2(*) PACK & PACK VALVE Ind #2Autopilot:ADUHydraulic:Green pump, DC AUX HYD PUMP CTL & Ind(in automatic)

    Landing Gear:Secondary IndFlight controls :STBY PITCH TRIM CTL,LEFT STICK SHAKER

    Ice and Rain protection:CM2 Static ports anti-icingCM2 Side windows anti-icingCM2 Windshield HTG Ind and Probes INDCM2 WiperEngine:FF/FU #2, FUEL TEMP #2, FUEL CLOG #2,OIL PRESS, TEMP #2IDLE GATE FAIL IndLights:CM2 Chartholder, Reading LightsIntegrated Normal INST & PANELS LightsRH LDG Light, Wing Lights, Passenger SignsDoor:

    Doors UNLK lights,Cockpit door locking systemCCAS:GPWS FAULT on CAP

    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

    RR GPWS, CM2 ASI/VSI/ALTI

    HDG RMI#1, Bearing VOR#2 andADF#2 to RMI/SGU 1/2,Course#2 and HDG#2 select

    For more information on BUS EQUIPMENT LISTS see FCOM 1.06.80

    Mod : 2973+1977

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    2.16

    42

    FOLLOWING FAILURESELEC

    OCT 09 001

    ACW BUS 1 OFF / ACW BUS 2 OFF

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

    PF ..............................................................................................CM1CM2 AIRSPEED INDICATOR ..........................................MONITOR

    AFFECTED EQUIPMENT............................................................... OFFHYD 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 downTAXI ON BOTH ENGINES

    ACW BUS 1 LOST EQUIPMENT LIST

    R Hydraulic:BLUE PUMP PWRLights:Integrated Normal INST& PANELSLights

    LH LDG LightLH and REAR STROBE LightsCabin:TOILET SYS and LH PAX ReadingLights

    Ice and Rain Protection:CM1 PITOT/ALPHA/TAT andWINDSHIELD HTG

    ANTI-ICING HORNS (Rud&LH Elev)ANTI-ICING PROP 1

    ACW BUS 2 LOST EQUIPMENT LIST

    R Hydraulic:GREEN PUMP PWRLights:TAXI/TO LightsRH LDG LightRH STROBE LightCabin:GalleyRH PAX Reading Lights

    Ice and Rain Protection:CM2 PITOT/ALPHA/TAT andWINDSHIELD HTG

    ANTI-ICING HORNS (AIL&RH Elev)ANTI-ICING PROP 2ICE DETECTOR

    For more information on BUS EQUIPMENT LISTS see FCOM 1.06.80

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    2.16A

    42

    FOLLOWING FAILURESELEC

    OCT 09 001

    ACW TOTAL LOSS

    ACW GEN 1 + 2.............................................................................. OFFHYD X FEED .....................................................................CHECK OFFLEAVE AND AVOID ICING CONDITIONS

    AS 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 1.4Note: Refer to Part 4 to determine LDG DIST

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

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

    ACW TOTAL LOST EQUIPMENT LIST

    R Hydraulic:GREEN and BLUE PUMP PWRLights:Integrated Normal INST& PANELSLightsTAXI/TO, LDG, STROBE LightsCabin:TOILET SYS, GalleyPAX Reading Lights

    Ice and Rain Protection:CM 1+2 PITOT/ALPHA/TAT andWINDSHIELD HTG

    ANTI-ICING HORNSANTI-ICING PROP 1+2ICE DETECTOR

    For more information on BUS EQUIPMENT LISTS see FCOM 1.06.80

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    2.17

    42

    FOLLOWING FAILURESELEC

    OCT 08 050

    DC ESS BUS OFF

    R DC ESS BUS OFF LOST 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 OFF LOST EQUIPMENT LIST

    RRR

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

    and 2.42B (for aircraft fitted with mod 4116 only)

    DC EMER BUS OFF

    R

    R

    R

    LEAVE AND AVOID ICING CONDITIONSDESCEND TOWARD ........................................................FL100 / MEASTBY PITCH TRIM.......................................................... USE AS RQDHYD X FEED .................................................................................... ONDC EMER BUS OFF LOST EQUIPMENT LIST ........................ CHECK

    If ice accretion builds up on airframeDE-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 CM2

    Note: 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

    RR

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

    For more information on BUS EQUIPMENT LISTS see FCOM 1.06.80

    Mod : 3059

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    2.18

    42

    FOLLOWING FAILURESELEC

    OCT 08 020

    DC GEN FAULT

    DC GEN affected side..................................................................... OFFTAXI ON BOTH ENGINES

    INV FAULT

    NO SPECIFIC ACTION IN FLIGHT

    ACW GEN FAULT

    RACW GEN affected side ................................................................. OFFFL...........................................................................................200 / MEALEAVE AND AVOID ICING CONDITIONSTAXI 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 1.06.80 page 12 to 14

    BAT CHG FAULT

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

    BAT DISCHARGE IN FLIGHT

    ENG START ROTARY SELECTOR............................................... OFFENG START ROTARY SELECTOR.............CONT RELIGHT AS RQDIf battery(ies) still discharging

    LAND ASAP

    Mod : 3245

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    2.18A

    42

    FOLLOWING FAILURES

    ELECAPR 08 001

    STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

    BAT ONLY

    (ACW available)

    STBY

    BUS

    (AC +

    DC)

    BASIC

    STBY

    BUS

    UNDV

    STBY

    BUS

    OVRD

    AHRS#2 *

    LOST

    #2 *

    LOST

    #2 *

    LOST

    ASI, VSI, ALTIBOTH

    LOST

    BOTH

    LOST

    BOTH

    LOST

    ADCBOTH

    LOST

    BOTH

    LOST

    BOTH

    LOST

    EHSIBOTH

    LOST

    BOTH

    LOST

    BOTH

    LOST

    VOR/ILS

    EADI/SGU

    #1

    LOST

    #2

    LOST

    BOTH

    LOST

    #2

    LOST

    DME BOTHLOST

    BOTHLOST

    BOTHLOST

    ADFBOTH

    LOST

    BOTH

    LOST

    BOTH

    LOST

    GPWS LOST LOST LOST

    RADAR LOST LOST LOST

    RADIO ALTI LOST LOST LOST

    TAS/TAT/SAT LOST LOST

    RMI#2

    LOST

    BOTH

    LOST

    BOTH

    LOST

    BOTH

    LOST

    AFCS COMPTR LOST LOST LOST

    AFCS ADU LOST LOST LOST

    CCAS

    AMBER

    ALERTS

    LOST

    RED+

    AMBER

    ALERTS

    LOST

    RED+

    AMBER

    ALERTS

    LOST

    VHF#2

    LOST

    #2

    LOST

    #2

    LOST

    HF LOST LOST

    ATC#2

    LOST

    #2

    LOST

    #2

    LOST

    MAIN PUMPSGREEN

    LOST

    GREEN

    LOST

    GREEN

    LOST

    AUX PUMP LOST LOST LOST

    PRESS IND LOST LOST

    FLAPS LOST LOST

    X FEEDVALVE LOST LOST

    * AUTO ERECT LOST ON AHRS 1; IF INSTALLED #3 IS LOST.

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    2.18B

    42

    FOLLOWING FAILURESELEC

    APR 08 030

    STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS (CONTD)

    BAT ONLY(ACW available)

    STBYBUS(AC +

    DC

    BASICSTBYBUS

    UNDV

    STBYBUS

    OVRD

    L/G RET LOST * LOST *

    L/G EXTEMERONLY

    EMERONLY

    L/G POS INDMAIN

    PANELLOST

    OVHDPANELLOST

    BOTHLOST

    OVHDPANELLOST

    ANTI-SKID INB LOST INB LOSTLANDING LIGHTSTAXI AND T.O.

    LightsLOST LOST LOST

    FF / FU / OIL TEMPAND PRESS

    BOTHLOST

    BOTHLOST

    BOTHLOST

    SYNPHR LOST LOST LOST

    AUTO IDLE GATE LOST LOST LOSTPROP BRK

    (if applicable)LOST LOST

    BLEED/PACKRECIRC / FAN

    BOTHLOST

    BOTHLOST

    BOTHLOST

    PRESSUAUTOLOST

    AUTOLOST

    AUTOLOST

    HORNS ANTI ICEPROP ANTI ICE

    WIPERSBOTHLOST

    BOTHLOST

    BOTHLOST

    MAIN WINDOW HTG

    SIDE WINDOW HTGBOTHLOST

    BOTHLOST

    BOTHLOST

    PROBE HTG

    STATICS PORTSALL

    LOSTALL

    LOSTALL

    LOST

    * HYD GREEN PUMP LOST / USE THE CROSS FEED

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    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

    After touch downUSE NORMAL BRAKE FOR STEERINGTAXI ON BOTH ENGINES

    If green system affected

    GREEN PUMP........................................................................... OFFLDG DIST ............................................................MULTIPLY BY 1.4Note: Refer to Part 4 to determine landing distanceLDG GRAVITY EXTENSION procedure (2.24) .....................APPLY

    After 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 1.4Note: Refer to Part 4 to determine landing distance

    Before landing

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

    FLAPS 30 ............................................................................AS RQD After 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)

    LDG GEAR EXT / RETNORM BRK

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    FOLLOWING FAILURESHYDRAULIC

    JUN 10 001

    BOTH HYD SYS LOSS

    RRR

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

    Before approachGPWS......... GPWS OVRD or FLAP OVRD (depending on version)LDG GEAR GRAVITY EXTENSION procedure (2.24)..........APPLYAPP SPEED ........................................... VmHB 0 + WIND EFFECTLDG SPEED ............................................VmLB 0 + WIND EFFECTLDG DIST ........................MULTIPLY LDG DIST FLAPS 30 BY 1.8Note: Refer to Part 4 to determine VmHB and LDG DIST

    CAUTION: Tail strike may occur if pitch attitude exceeds 10during the flare depending upon vertical speed attouch down.

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

    BOTH 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

    HYD LO PR / HYD OVHT

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

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    42

    FOLLOWING FAILURESFLIGHT CONTROL

    APR 08 001

    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

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

    FLAPS JAM / UNCOUPLED / ASYM

    FLAPS CONTROL LEVER ..........NEAR FLAPS PRESENT POSITION

    zWhen 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 SPEED LDG SPEED

    0 1.30VmHB 0 +

    WIND EFFECTVmLB 0 +

    WIND EFFECT

    15 1.15VmHB 15 +

    WIND EFFECTVmLB 15 +

    WIND EFFECT

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

    CAUTION: Tail strike may occur if pitch attitude exceeds 10 during

    the flare 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

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    FOLLOWING FAILURESFLIGHT CONTROL

    OCT 09 001

    PITCH TRIM FAIL / ASYM(LOCAL LIGHT depending on version)

    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)...........................PROHIBITED

    FLAPS................ 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 available

    YD ...................................................................................... 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 ............................ 30 MAX 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 1.13PL 1 + 2 ..................................... REDUCE SMOOTHLY TO FLARE

    Note: Refer to Part 4 to determine LDG DATA

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    42

    FOLLOWING FAILURESFLIGHT CONTROL

    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

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

    CAUTION: Do not extend FLAPS in turn

    zWhen in landing configuration

    BLUE AND AUX HYD PUMPS.................................................. OFFzImmediately 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

    zAt touch down

    NOSE DOWN BEFORE REDUCTION BELOW FI

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    42

    FOLLOWING FAILURESLANDING GEAR

    APR 08 001

    LDG GEAR GRAVITY EXTENSION

    LDG GEAR LEVER.....................................................................DOWNEMER 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 unsuccessfulLANDING WITH ABNORMAL LDG GEARprocedure (2.24)............APPLY

    LANDING WITH ABNORMAL LDG GEAR

    zPreparationCABIN CREW (PA).............................................................. NOTIFYATC / TRANSPONDER...................................... NOTIFY / AS RQDSEAT BELTS / NO SMOKING ....................................................ONGPWS........................................................................................OFFCABIN AND COCKPIT ....................................................PREPARELOOSE AND SURVIVAL EQUIPMENT ............CHECK SECUREDBELTS AND SHOULDER HARNESS ..................CHECK LOCKEDFUEL WEIGHT ..........................................IF POSSIBLE, REDUCEIf abnormal nose LDG GEAR

    CG LOCATION..............................................IF POSSIBLE, AFTIf abnormal main LDG GEAR

    FUEL UNBALANCE .........................IF POSSIBLE, ESTABLISH

    Note: Reduced fuel on side with failed LDG GEAR.zApproach

    LDG GEAR LEVER .............................................CONFIRM DOWNLDG GEAR EMER EXT HANDLE .....................CONFIRM PULLEDENG START ROTARY SELECTOR..............OFF / START ABORTCABIN REPORT...........................................CONFIRM OBTAINED

    zBefore landingBLEEDS 1 + 2............................................................................ OFFBRACE FOR IMPACT ..........................................................ORDER

    zAt touch downPL 1 + 2 .........................................................................................GICL 1 + 2.......................................................... FTR THEN FUEL SO

    zAf ter touch down

    FIRE HANDLES 1 + 2 ..............................................................PULLzWhen aircraft stopped

    PARKING BRAKE ......................................................................SETCABIN CREW (PA).............................................................. NOTIFYFUEL PUMPS 1 + 2...................................................................OFFAGENTS 1 + 2....................................................................... DISCHEVACUATION ....................................................................INITIATE

    zBefore leaving aircraftBAT ............................................................................................OFF

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    FOLLOWING FAILURESLANDING GEAR

    JUN 10 150

    LDG GEAR UNSAFE INDICATION

    If LDG GEAR selected DOWN

    If GREEN LIGHT OFF on one panel onlyUNSAFE INDICATION ...........................................DISREGARDIf GREEN LIGHT OFF on both panels

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

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

    UNSAFE INDICATION ...........................................DISREGARDIf 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

    L/G LEVER ................................................................ DOWN THEN UP

    If no retraction occursLDG GEAR RET OVRD PB.............................. OVRD THEN HOLD

    If unsuccessfulL/G LEVER ............................................................................ DOWNMAX SPEED............................................................................170 ktCCAS......................................................................................... RCLTCAS (if installed).............................................................. TA ONLYIDLE GATE .......................................................................MONITOR

    Note: LDG GEAR RET OVRD PB must be held until red UNLK lights are

    extinguished.

    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

    Mod : 1694 + 1790

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    42

    FOLLOWING FAILURESAIR

    APR 08 001

    BLEED VALVE FAULT

    PACK VALVE affected side............................................................OFFBLEED VALVE affected side.......................................................... OFFMAX FL ..................................................................................200 / MEAAVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

    BLEED OVHT

    PACK VAL