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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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EMERGENCY
OCT 09 001
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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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
OCT 09 160
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
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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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OCT 09 001
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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EMERGENCY
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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EMERGENCY
APR 08 001
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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FOLLOWING FAILURES
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2 - PROCEDURES FOLLOWING FAILURES
Content 2/3
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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FOLLOWING FAILURES
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2 - PROCEDURES FOLLOWING FAILURES
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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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FOLLOWING FAILURESPOWER PLANT
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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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2.10A
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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2.19
42
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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2.20
42
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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2.21
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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2.22
42
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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2.23
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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2.24
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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2.25
42
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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2.26
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