0.01
GENERAL
72
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
The boxed items correspond to actions performed by memory by the
R
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
R
R
R
R
R
No action will be taken (apart from depressing MC/MW pushbutton) :
- until flight path is stabilized
- under 400 ft above runway, except propeller feathering after engine
failure during approach at reduced power if go around is considered
At flight crew discretion, one reset of a system failure associated with
an amber caution (except PEC SGL CH) may be performed by
selecting OFF then ON related pushbutton.
Flight Crew may reengage a tripped circuit breaker only if he/she
judges it necessary for a safe continuation of the flight. In this case
only one reengagement should be attempted.
If the failure alert disappears, continue normal operation and record
the event in the maintenance log. If not, apply the associated failure
procedure.
Before performing a procedure, the crew must assess the situation as
a whole, taking into consideration the failures, when fully identified,
and the flight constraints imposed.
TASK SHARING
For all procedures, the general task sharing stated below is
applicable. The pilot flying remains pilot flying throughout the
procedure.
PF, Pilot Flying, responsible for : PNF, Pilot Non Flying, responsible
- PL
for :
- flight path and airspeed control
- Check List reading
- aircraft configuration
- execution of required actions
- navigation
- 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 remaining
aircraft capabilities under the responsibility of CM1.
EMERGENCY
72
1.01
SEP 13
001
1 - EMERGENCY PROCEDURES
Content 1/1
IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE
………..
ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE ….
ON GROUND EMER EVACUATION ……………………………………
ENG FIRE AT TAKE OFF ………………………………………………..
BOTH ENGINES FLAME OUT …………………………………………..
ENG FLAME OUT AT TAKE OFF ……………………………………….
BOMB ON BOARD ………………………………………………………..
COCKPIT DOOR SECURITY SYSTEM ………………………………..
SMOKE ……………………………………………………………………….
ELECTRICAL SMOKE…………………………………………………….
AIR COND SMOKE ……………………………………………………….
FWD SMOKE…………………...………………………………………….
AFT SMOKE……………………………………………………………..
AUX AFT COMPT SMOKE………………………………………………..
DUAL DC GEN LOSS …………………………………………………….
EMERGENCY DESCENT ………………………………………………..
DITCHING ………………………………………………………………….
FORCED LANDING ……………………………………………………….
SEVERE ICING ……………………………………………………………
RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL……………..
1.02
1.02
1.02
1.02A
1.03
1.04
1.04
1.04A
1.05
1.05A
1.05A
1.06
1.06
1.06
1.07
1.07A
1.08
1.08A
1.09
1.10
UNRELIABLE AIRSPEED INDICATION…………………………………. 1.10/11 R
1.02
EMERGENCY
72
SEP 13
500
IN FLIGHT ENG FIRE
OR SEVERE MECHANICAL DAMAGE
PL affected side .................................................................................. FI
CL affected side .................................................. FTR THEN FUEL SO
FIRE HANDLE affected side..........................................................PULL
 If condition persists after 10 seconds
AGENT 1 affected side .......................................................... DISCH
 If condition persists after 30 seconds
AGENT 2 affected side .......................................................... DISCH
LAND ASAP
SINGLE ENG OPERATION procedure (2.04) ............................ APPLY
ON GROUND ENG FIRE
OR SEVERE MECHANICAL DAMAGE
PL 1 + 2............................................................GI / REVERSE AS RQD
 When aircraft stopped
PARKING BRAKE ............................................................. ENGAGE
CL 1 + 2 .......................................................... FTR THEN FUEL SO
FIRE HANDLE affected side.....................................................PULL
 If condition persists
AGENT 1 affected side ...................................................... DISCH
 If condition persists after 30 seconds .......................................
AGENT 2 affected side ...................................................... DISCH
 If evacuation required
ON GROUND EMER EVACUATION procedure (1.02).... APPLY
ON GROUND EMER EVACUATION
AIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGE
AUTO PRESS.............................................................................. DUMP
ATC (VHF 1 / HF) ..................................................................... NOTIFY
CL 1 + 2 ............................................................... FTR THEN FUEL SO
MIN CAB LIGHT ............................................................................... ON
CABIN CREW (PA)................................................................... NOTIFY
FIRE HANDLES 1 + 2....................................................................PULL
AGENTS ...................................................................................AS RQD
ENG START ROTARY SELECTOR................... OFF / START ABORT
FUEL PUMPS 1 + 2........................................................................ OFF
EVACUATION (PA) .................................................................INITIATE
 Before leaving aircraft
BAT ............................................................................................ OFF
Model : 212A
EMERGENCY
72
1.02A
SEP 13
500
ENG FIRE AT TAKE OFF
Note: Captain may decide to shut down affected engine before reaching
acceleration altitude, but not before 400ft AGL.
 When airborne
LDG GEAR ...................................................................................UP
 At Acceleration Altitude
PWR MGT..................................................................................MCT
 At VFTO
 If normal condition
FLAPS......................................................................................... 0°
 If icing condition
FLAPS.....................................................................MAINTAIN 15°
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
FIRE HANDLE illuminated…………………………….. .............PULL
 If fire persist after 10 seconds
AGENT 1 affected side ...................................................... DISCH
 If fire persist after 30 seconds
AGENT 2 affected side....................................................... DISCH
BLEED engine alive ............................................... OFF if necessary
LAND ASAP
SINGLE ENG OPERATION procedure (2.04) ........................... APPLY
Model : 212A
EMERGENCY
72
1.03
OCT 09 100
BOTH ENGINES FLAME OUT
PL 1 + 2............................................................................................... FI
If NH drops below 30 % (no automatic relight)
CL 1 + 2 .......................................................... FTR THEN FUEL SO
FUEL SUPPLY ..................................................................... CHECK
OPTIMUM SPEED.................................................................. VmHB
CAPT EHSI ................................................................................ OFF
COMMUNICATIONS .............................................................. VHF 1
ENG START ROTARY SELECTOR............................START A & B
ENG 2 RELIGHT
ENG 2 START PB .................................................................. ON
When NH above 10%
CL 2 ..................................................................................FTR
ENG 2 RELIGHT ....................................................MONITOR
CL 2 then PL 2...........................................................AS RQD
ENG 1 RELIGHT
ENG 1 START PB .................................................................. ON
When NH above 10%
CL 1 ..................................................................................FTR
ENG 1 RELIGHT ....................................................MONITOR
CL 1 then PL 1...........................................................AS RQD
If neither engine starts
CL 1 + 2 .......................................................... FTR THEN FUEL SO
ENG START ROTARY SELECTOR.............. OFF / START ABORT
FUEL PUMPS 1 + 2................................................................... OFF
FORCED LANDING (1.08A) or DITCHING (1.08) procedure ...........
............................................................................................... APPLY
CAUTION: Do not select AVIONICS VENT EXHAUST MODE to
OVBD
R
If engine(s) recovered
CL / PL engine(s) recovered................................................AS RQD
If one engine not recovered
CL engine NON recovered ........................ FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04).................. APPLY
SYSTEMS affected.......................................................... RESTORE
Mod : 3973 or 4371 or 4457
EMERGENCY
72
1.04
NOV 11 500
ENG FLAME OUT AT TAKE OFF
R
UPTRIM ..................................................................................... CHECK
AUTOFEATHER ........................................................................ CHECK
If no UPTRIM
PL 1 + 2 ................................................. ADVANCE TO THE RAMP
When airborne
LDG GEAR ....................................................................................UP
BLEED 1 + 2 .................................................... OFF, IF NOT FAULT
At Acceleration Altitude
ALT .............................................................................................SET
At VFTO
PL 1 + 2 ................................................................... IN THE NOTCH
PWR MGT .................................................................................MCT
IAS ..............................................................................................SET
If normal condition
FLAPS ........................................................................................ 0°
If icing condition
FLAPS .................................................................... MAINTAIN 15°
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
BLEED engine alive............................................... OFF if necessary
If damage suspected
FIRE HANDLE affected side.....................................................PULL
LAND ASAP
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
If no damage suspected
ENG RESTART IN FLIGHT procedure (2.08) ....................... APPLY
If unsuccessful
LAND ASAP
SINGLE ENG OPERATION procedure (2.04).................. APPLY
BOMB ON BOARD
AUTO PRESS - LANDING ELEVATION .................. CABIN ALTITUDE
FLIGHT LEVEL ................................ DESCEND TO CABIN ALTITUDE
AVOID LOAD FACTORS
HANDLE BOMB CAREFULLY - AVOID SHOCKS
When Z aircraft = Z cabin
APPROACH CONFIG: FLAPS 15 GEAR DOWN ..........SELECTED
AUTO PRESS......................................................................... DUMP
SERVICE DOOR ................................................................UNLOCK
PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAG
ATTACHED TO THE DOOR HANDLE
SURROUND IT WITH DAMPING MATERIAL
CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER...........
............................................................................ MOVE FORWARD
PAX................................... MOVE FORWARD / CRASH POSITION
LAND ASAP
Eng : PW127F / PW127M
EMERGENCY
72
1.04A
SEP 04 400
COCKPIT DOOR SECURITY SYSTEM
Electrical Power Lost
Move the manual lock bolt to CLOSE position
Note : When the door is locked with the manual bolt, the
emergency access to the cockpit is unavailable. It is
recommended that at least two crew members remain in
the cockpit during that time.
Cockpit Door Jammed
l When cockpit exit required
COCKPIT DOOR LOCKING SYSTEM ............................... OFF
Disconnect PLUG on top of the door
Remove the safety pins from the door
Push and remove corresponding door panel
Mod : 5465
EMERGENCY
72
1.05
SEP 13
500
SMOKE
CREW OXY MASKS............................................................. ON / 100%
GOGGLES .......................................................................................SET
CREW COMMUNICATIONS ..............................................ESTABLISH
RECIRC FANS 1 + 2 ...................................................................... OFF
AP ..................................................................................................... ON
SMOKE SOURCE.................................................................. IDENTIFY
 If source not identified or electrical smoke suspected
Note: ELEC light may be activated by an air conditioning smoke
source
ELECTRICAL SMOKE procedure (1.05A) ............................ APPLY
 If air conditioning smoke identified
AIR COND SMOKE procedure (1.05A) ................................. APPLY
 If FWD SMK illuminated or smoke in FWD zone of aircraft
FWD SMOKE procedure (1.06) ............................................. APPLY
 If AFT SMK illuminated or smoke in AFT zone of aircraft
AFT SMOKE procedure (1.06) .............................................. APPLY
 If AUX AFT COMPT SMK illuminated (depending on models)
AUX AFT COMPT SMK procedure (1.06) ............................. APPLY
Model : 212A
EMERGENCY
72
1.05A
SEP 13
500
ELECTRICAL SMOKE
SMOKE procedure (1.05) ........................................................... APPLY
AVIONICS VENT EXHAUST MODE ........................................... OVBD
AIR FLOW......................................................................................HIGH
DC SVCE AND UTLY BUS............................................................. OFF
DC BTC.......................................................................................... ISOL
ACW GEN 1 + 2.............................................................................. OFF
SUSPECTED EQUIPMENTS ......................................................... OFF
 If smoke origin not identified
LAND ASAP
ACW TOTAL LOSS procedure (2.16A) ................................. APPLY
 If smoke origin identified
NOT AFFECTED EQUIPMENTS .................................... RESTORE
 When P below 1 PSI
OVBD VALVE ................................................................FULL OPEN
AVIONICS VENT EXHAUST MODE ......................................NORM
AIR COND SMOKE
SMOKE procedure (1.05) ........................................................... APPLY
PACK VALVE 1............................................................................... OFF
MAX FL ..................................................................................200 / MEA
 If smoke persists
PACK VALVE 1 ........................................................................... ON
PACK VALVE 2 ......................................................................... OFF
CAUTION: Evacuation of air conditioning smoke may trigger
electrical smoke warning. Disregard it.
ENGINES PARAMETERS......................... CAREFULLY MONITOR
 If any anomaly occurs, such as:
- amber engine caution illumination associated to local ITT alert
- total loss of NL indication
- engine abnormality clearly identified (NH, NL, ITT indications,
noise, surge…)
CAUTION: Confirm which engine is showing signs of abnormal
operation in order to avoid shutting down safe engine.
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
Model : 212A
1.06
EMERGENCY
72
SEP 13
502
FWD SMK
SMOKE procedure (1.05) ........................................................... APPLY
1) PASSENGERS VERSION
CABIN CREW (PA).............................................................. ADVISE
AVIONICS VENT EXHAUST MODE ...................................... OVBD
AIR FLOW ................................................................................HIGH
EXTRACT AIR FLOW LEVER (RH MAINT PANEL) ..........CLOSED
CABIN CREW WITH PORTABLE EXTINGUISHER,
LOCATE AND KILL SOURCE OF SMOKE
LAND ASAP
 When P below 1 PSI
OVBD VALVE ...........................................................FULL OPEN
AVIONICS VENT EXHAUST MODE.................................NORM
2) CARGO VERSION
CAB PRESS MODE SEL...........................................................MAN
CAB ALT ................................................................ MAX INCREASE
ENG 2 BLEED (Except when in single bleed operation)........... OFF
PACK VALVE 2 (Except when in single pack operation) .......... OFF
CAB VENT AIR FLOW .............................................................. OFF
FLIGHT COMPT TEMP SEL ..................................................... HOT
CAUTION: LAND ASAP. If a quick landing is not possible, climb and
maintain minimum FL160; FL200 is recommended. When
“Excess CAB ALT” warning, maintain FL160, maintain CAB
ALT maw increase.
Note: Smoke alert may be generated during smoke evacuation
process.
AFT SMK
SMOKE procedure (1.05) ........................................................... APPLY
1) PASSENGERS VERSION
CABIN CREW (PA)....................................... ADVISE FOR ACTION
AIR FLOW ................................................................................HIGH
2) CARGO VERSION
CAB PRESS MODE SEL...........................................................MAN
CAB ALT ................................................................ MAX INCREASE
ENG 2 BLEED (Except when in single bleed operation)........... OFF
PACK VALVE 2 (Except when in single pack operation) .......... OFF
CAB VENT AIR FLOW .............................................................. OFF
FLIGHT COMPT TEMP SEL ..................................................... HOT
CAUTION: LAND ASAP. If a quick landing is not possible, climb
and
maintain
minimum
FL160;
FL200
is
recommended. When “Excess CAB ALT” warning,
maintain FL160, maintain CAB ALT maw increase.
Note: Smoke alert may be generated during smoke evacuation
process.
AUX AFT COMPT SMK
(depending on models)
SMOKE procedure (1.05) ........................................................... APPLY
AUX AFT COMPT AGENT ......................................................... DISCH
Model : 212A
EMERGENCY
72
1.07
OCT 09 300
DUAL DC GEN LOSS
DC GEN 1 + 2 ................................................................... OFF then ON
If no generator recovered
HYD GREEN PUMP .................................................................. OFF
TRU.............................................................................................. ON
R
Make sure that TRU arrow illuminates, BAT arrows extinguish
MAN RATE KNOB ..........................................................9 O'CLOCK
CAB PRESS MODE SEL...........................................................MAN
AVIONICS VENT EXHAUST MODE ...................................... OVBD
BAT SW .................................................................................. OVRD
ATC (VHF 1 or HF or HF 2) ................................................. NOTIFY
MIN CAB LIGHT ........................................................................ OFF
Note: NAV lights switch set to ON is necessary to provide IEP
illumination
STICK PUSHER / SHAKER ...................................................... OFF
STICK PUSHER / SHAKER FAULT procedure (2.21) .......... APPLY
SIDE WINDOWS ANTI-ICING................................................... OFF
ADC SW.................................................................... SET TO ADC 1
ATC SW .................................................................... SET TO ATC 1
TLU ................................................................. MAN MODE LO SPD
When TLU LO SPD illuminates
TLU .....................................................................................AUTO
CAUTION: Avoid large rudder input if IAS above 180 kt
BUS EQUIPMENT LISTS (2.18 A – 2.18 B)......................... CHECK
Before descent
PAX INSTRUCTIONS .................................................... USE PA
HYD X FEED .......................................................................... ON
Note: Selecting HYD X FEED ON allows to recover green
hydraulic system
At touch down
IDLE GATE LEVER .............................................................PULL
Mod : 1603 + 4116 + 4366
EMERGENCY
72
1.07A
SEP 13
100
EMERGENCY DESCENT
OXYGEN MASKS / CREW COMMUNICATIONS .................... AS RQD
GOGGLES ................................................................................ AS RQD
DESCENT ................................................................................ INITIATE
PL 1 + 2............................................................................................... FI
CL 1 + 2 ............................................................................. 100% OVRD
R
OXYGEN PAX SUPPLY ........................................................... AS RQD
SPEED ........... MMO / VMO (or less if structural damage is suspected)
SIGNS ............................................................................................... ON
ATC (VHF1 / HF) ...................................................................... NOTIFY
MEA ........................................................................................... CHECK
Mod : 3973 or 4371 or 4457
EMERGENCY
72
1.08
SEP 13
500
DITCHING
 Preparation (time permitting)
ATC (VHF1 or HF) ............................................................... NOTIFY
XPDR ........................................................................ EMERGENCY
CABIN CREW (PA).............................................................. NOTIFY
SIGNS.......................................................................................... ON
GPWS........................................................................................ OFF
TERR (If TAWS installed) .......................................................... OFF
CABIN AND COCKPIT .................................................... PREPARE
- Loose equipment secured
- Survival equipment prepared
- Belts and shoulder harnesses locked
AUTO PRESS - LDG ELEVATION.............................................SET
 Approach
AUTO PRESS......................................................................... DUMP
PACKS 1 + 2.............................................................................. OFF
OVBD VALVE ..............................................................FULL CLOSE
HYD AUX PUMP pushbutton (pedestal) ......................... DEPRESS
FLAPS (If available).......................................................................30
LDG GEAR LEVER ......................................................................UP
 30 seconds before impact or 1250 ft above sea level
DITCH PB .................................................................................... ON
ENG START ROTARY SELECTOR.............. OFF / START ABORT
CABIN REPORT ............................................................. OBTAINED
 Before ditching (200 ft)
MINIMIZE IMPACT SLOPE
OPTIMAL PITCH ATTITUDE FOR IMPACT ................................. 9°
BRACE FOR IMPACT ..........................................................ORDER
Note: In case of night ditching, shutting down both engines may be
performed at captain discretion, immediately after the
impact (avoiding loss of landing lights during flare out).
CL 1 + 2 .......................................................... FTR THEN FUEL SO
FIRE HANDLES 1 + 2 ..............................................................PULL
FUEL PUMPS 1 + 2................................................................... OFF
 After ditching
Note: After ditching, one aft door will be under the water line.
CABIN CREW (PA).............................................................. NOTIFY
EVACUATION ....................................................................INITIATE
 Before leaving aircraft
BAT ........................................................................................ OFF
Model : 212A
EMERGENCY
72
1.08A
SEP 13
500
FORCED LANDING
 Preparation (time permitting)
ATC (VHF1 or HF) ............................................................... NOTIFY
XPDR ........................................................................ EMERGENCY
CABIN CREW (PA).............................................................. NOTIFY
SIGNS.......................................................................................... ON
GPWS........................................................................................ OFF
TERR (If TAWS installed) .......................................................... OFF
CABIN AND COCKPIT .................................................... PREPARE
- loose equipment secured
- survival equipment prepared
- belts and shoulder harnesses locked
AUTO PRESS - LDG ELEVATION.............................................SET
 Approach
HYD AUX PUMP pushbutton (pedestal) ......................... DEPRESS
FLAPS (If available).......................................................................30
LDG GEAR LEVER .............................................................AS RQD
AUTO PRESS......................................................................... DUMP
ENG START ROTARY SELECTOR.............. OFF / START ABORT
CABIN REPORT ............................................................. OBTAINED
 Before impact (200 ft)
BRACE FOR IMPACT ..........................................................ORDER
Note: In case of night forced landing, shutting down both engines
may be performed at captain discretion, immediately after
the impact (avoiding loss of landing lights during flare out).
CL 1 + 2 .......................................................... FTR THEN FUEL SO
FIRE HANDLES 1 + 2 ..............................................................PULL
FUEL PUMPS 1 + 2................................................................... OFF
 After impact, when aircraft stopped
CABIN CREW (PA).............................................................. NOTIFY
AGENTS ................................................................................ DISCH
EVACUATION ....................................................................INITIATE
 Before leaving aircraft
BAT ........................................................................................ OFF
Model : 212A
EMERGENCY
72
1.09
SEP 13
500
SEVERE ICING
MINIMUM ICING SPEED .................................................... INCREASE 10 kt
PWR MGT...............................................................................................MCT
CL 1 + 2 ....................................................................................100% OVRD
PL 1 + 2..............................................................................................NOTCH
AP (if engaged) ....... FIRMLY HOLD CONTROL WHEEL and DISENGAGE
SEVERE ICING CONDITIONS........................................................ESCAPE
ATC ................................................................................................... NOTIFY
 If an unusual roll response or uncommanded roll control
movement is observed :
Push firmly on the control wheel
FLAPS..........................................................................EXTEND 15
 If the flaps are extended, do not retract them until the airframe is
clear of ice.
 For approach, if the aircraft is not clear of ice:
GPWS ............................................................ FLAP/GPWS OVRD
STEEP SLOPE APPROACH (4.5°) ........................PROHIBITED
APP/LDG CONF ..........................................MAINTAIN FLAPS 15
APP SPEED ..... "REDUCED FLAPS 15 LDG icing speeds" + 5 kt
Multiply landing distance FLAPS 30 by 2.12.
DETECTION
Visual cue identifying severe icing is characterized by ice covering all or a
substantial part of the unheated portion of either side window
and / or
Unexpected decrease in speed or rate of climb
and / or
The following secondary indications :
. Water splashing and streaming on the windshield
. Unusually extensive ice accreted on the airframe in areas not normally
observed to collect ice
. Accumulation of ice on the lower surface of the wing aft of the protected
areas
. Accumulation of ice on propeller spinner farther aft than normally
observed
The following weather conditions may be conducive to severe in-flight
icing :
. Visible rain at temperatures close to 0°C ambient air temperature (SAT)
. Droplets that splash or splatter on impact at temperatures close to 0°C
ambient air temperature (SAT)
Eng : PW127F / PW127M
1.10
EMERGENCY
72
SEP 13
500
RECOVERY AFTER STALL
or ABNORMAL ROLL CONTROL
R
R
R
R
R
CONTROL WHEEL........................................................ PUSH FIRMLY
 If flaps 0° configuration
FLAPS ........................................................................................... 15°
PWR MGT ...................................................................................MCT
CL 1 + 2......................................................................... 100 % OVRD
PL 1 + 2 ..................................................................................NOTCH
ATC ....................................................................................... NOTIFY
 If flaps are extended
PWR MGT ...................................................................................MCT
CL 1 + 2......................................................................... 100 % OVRD
PL 1 + 2 ..................................................................................NOTCH
ATC ....................................................................................... NOTIFY
Note: this procedure is applicable regardless the LDG GEAR position
is (DOWN or UP)
UNRELIABLE AIRSPEED INDICATION
R
AP/YD/FD .........................................................................OFF/OFF/STBY
PITCH AND TQ......................................................................... MAINTAIN
 If at take off or GA below 1500 ft:
PITCH IMMEDIATELY ........................................................................ 8°
ICING / VOLCANIC ASHES CONDITIONS.................................ESCAPE
PROBE HEATING, DE-/ANTI-ICING...................................... CHECK ON
APM..................................................................................................... OFF
WARNING: respect STALL alarm.
Note: Use any GPS speed information if available.
 Take off phase, at or above acceleration altitude
ALTITUDE.................................... MAINTAIN AT LEAST 30 SECONDS
FLAPS.................................................................................................. 0°
PITCH .................................................................................................. 8°
Note: Use climb table here after to adjust pitch if required.
AFTER TAKE OFF normal procedure .........................................APPLY
LAND AT THE NEAREST SUITABLE AIRPORT
 Climb
TLU ............................................................................................ LO SPD
PWR MGT........................................................................................ CLB
PL 1 + 2.......................................................................................NOTCH
Altitude (ft)
5000
Normal conditions pitch
Icing conditions pitch
7°
6°
10000
15000
20000
5°
4°
4°
3°
3°
2°
Continuing next page …/…
Eng : PW127F / PW127M
1.11
EMERGENCY
72
NOV 11 500
UNRELIABLE AIRSPEED INDICATION
(CONT’D)
Cruise
ALTITUDE ............................................................................... MAINTAIN
TLU ............................................................................................... HI SPD
Note: Average pitch around 0° at cruise speed
PWR MGT ......................................................................................... CRZ
PL 1 + 2 ........................................................................................NOTCH
Descent
TLU ............................................................................................... HI SPD
PITCH ........................................................................MAINTAIN AT -2.5°
PL 1 + 2 ........................................................................ ADJUST 30% TQ
DESCENT normal procedure ........................................................APPLY
Initial Approach
TLU .............................................................................................. LO SPD
APPROACH normal procedure .....................................................APPLY
CAUTION: Transition from clean configuration to LDG configuration is to
be performed in level flight - REFER TO ALTIMETER - (if possible 30
seconds between each step).
Note: Refer to following tables to adjust TQ:
Aircraft configuration
- Average speed
14 T
Flaps 0° - 180 kt
35%
TQ (Altitude of 3000ft)
18 T
22 T
45%
50%
FLAPS ................................................................................................. 15°
Flaps 15° - 150 kt
35%
40%
45%
LDG GEAR .................................................................................... DOWN
PWR MGT ........................................................................................... TO
FLAPS ................................................................................................. 30°
Flaps 30° - 130 kt
45%
45%
50%
Final Approach
PL 1 + 2 ........................................................................ ADJUST 35% TQ
BEFORE LANDING normal procedure .........................................APPLY
Note: Set an average pitch of -5° for a 3° slope approac h.
Eng : PW127F / PW127M
FOLLOWING FAILURES
72
2.01
SEP 13
500
2 - PROCEDURES FOLLOWING FAILURES
Content 1/3
POWER PLANT
SINGLE ENG OPERATION……………………………………………………….
START FAULT……………………………………………………………………...
X START FAIL………………………………………………………………………
ABNORMAL PARAMETERS DURING START…………………………………
EXCESSIVE ITT DURING START……………………………………………….
NO ITT DURING START…………………………………………………………..
NO NH DURING START…………………………………………………………..
ENG NAC OVHT
ABNORMAL ENG PARAMETERS IN FLIGHT…………………………………
FIRE LOOP FAULT………………………………………………………………..
ABNORMAL PROP BRK………………………………………………………….
ENG RESTART IN FLIGHT……………………………………………………….
ENG STALL…………………………………………………………………………
ONE EEC FAULT…………………………………………………………………..
BOTH EEC FAULT…………………………………………………………………
ENG FLAME OUT………………………………………………………………….
IDLE GATE FAIL……………………………………………………………………
SYNPHR FAIL (if applicable) …………………………………………………….
CL PNEUMATIC ACTUATOR BLOCKING (if applicable) …………………….
UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS (if applicable) ……………
PEC SGL CH (if applicable) ………………………………………………………
PEC FAULT (if applicable) ………………………………………………………..
LO PITCH IN FLIGHT……………………………………………………………...
ENG OVER LIMIT………………………………………………………………….
PROP OVER LIMIT………………………………………………………………..
ENG OIL TEMP BELOW 45°C……………………………………………………
ENG OIL TEMP HIGH……………………………………………………………..
ENG OIL LO PR…………………………………………………………………….
ENG BOOST FAULT (if applicable) ……………………………………………..
2.04
2.04
2.04
2.05
2.05
2.05
2.05
2.06
2.06
2.06
2.07
2.08
2.08
2.09
2.09
2.10
2.10
2.10A
2.10A
2.10A
2.10A
2.10A
2.11
2.11
2.11
2.12
2.12
2.12
2.12A
FUEL
FUEL ABNORMAL TEMP…………………………………………………………
FUEL CLOG…………………………………………………………………………
FUEL FEED LO PR……….………………………………………………………..
FUEL LEAK ALERT CONDITION………………………………………………..
FUEL LO LVL……………………………………………………………………….
FUEL LEAK…………………………………………………………………………
2.13
2.13
2.13
2.14
2.14
2.14
ELEC
DC BUS 1 OFF …………………………………………………………………….
AC BUS 1 OFF …………………………………………………………………….
DC BUS 2 OFF …………………………………………………………………….
AC BUS 2 OFF …………………………………………………………………….
ACW BUS 1 OFF / ACW BUS 2 OFF……………………………………………
ACW TOTAL LOSS………………………………………………………………..
DC ESS BUS OFF…………………………………………………………………
DC EMER BUS OFF……………………………………………………………….
DC GEN FAULT…………………………………………………………………….
INV FAULT………………………………………………………………………….
ACW GEN FAULT………………………………………………………………….
DC SVCE/UTLY BUS SHED………………………………………………………
BAT CHG FAULT…………………………………………………………………..
DUAL BAT CHG LOSS…………………………………………………………….
BAT DISCHARGE IN FLIGHT (if applicable) …………………………………...
2.15
2.15
2.15A
2.15A
2.16
2.16A
2.17
2.17
2.18
2.18
2.18
2.18
2.18
2.18
2.18
2.18A
STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS………………... 2.18B
ESS BUS AND EMER BUS LOST EQUIPMENT LISTS………………………. 2.42
Cargo configuration only….. 2.42A
Model : 212A
FOLLOWING FAILURES
72
2.02
OCT 09 001
2 - PROCEDURES FOLLOWING FAILURES
Content 2/3
HYDRAULIC
R
HYD LO LVL ………………………………………………………………………..
BOTH MAIN HYD PUMPS LOSS ………………………………………………..
BOTH HYD SYS LOSS ……………………………………………………………
HYD LO PR / HYD OVHT …………………………………………………………
2.19
2.19
2.20
2.20
FLIGHT CONTROL
FLAPS UNLK ……………………………………………………………………….
FLAPS JAM / UNCOUPLED / ASYM ……………………………………………
REDUCED FLAPS LANDING …………………………………………………….
STICK PUSHER / SHAKER FAULT ……………………………………………..
PITCH TRIM ASYM (LOCAL LIGHT) ……………………………………………
PITCH TRIM INOPERATIVE ……………………………………………………..
DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTER UNIT FAIL ….......
PITCH DISCONNECT …………………………………………………………….
PITCH RECONNECTION ON GROUND (If applicable) ………………………
TLU FAULT …………………………………………………………………………
AIL LOCK LIT (if applicable) ……………………………………………………...
ELEVATOR JAM …………………………………………………………………..
AILERON JAM / SPOILER JAM ………………………………………………….
RUDDER JAM ……………………………………………………………………...
2.21
2.21
2.21
2.21
2.22
2.22
2.22
2.22
2.22A
2.22A
2.22A
2.23
2.23
2.23
LANDING GEAR
LDG GEAR GRAVITY EXTENSION …………………………………………….
LANDING WITH ABNORMAL LDG GEAR ……………………………………..
LDG GEAR UNSAFE INDICATION ……………………………………………..
LDG GEAR RETRACTION IMPOSSIBLE ………………………………………
ANTI-SKID FAULT …………………………………………………………………
BRK TEMP HOT …………………………………………………………………...
2.24
2.24
2.25
2.25
2.25
2.25
AIR
BLEED VALVE FAULT ……………………………………………………………
BLEED OVHT ………………………………………………………………………
BLEED LEAK ………………………………………………………………………
X VALVE OPEN ……………………………………………………………………
PACK VALVE FAULT ……………………………………………………………..
BOTH PACK VALVES FAULT ……………………………………………………
RECIRC FAN FAULT ……………………………………………………………...
DUCT OVHT ………………………………………………………………………..
EXCESS CAB ALT ………………………………………………………………...
AUTO PRESS FAULT …………………………………………………………….
EXCESS CAB ∆P ………………………………………………………………….
AVIONICS VENT EXHAUST MODE FAULT …………………………………...
OVBD VALVE FAULT ……………………………………………………………..
2.26
2.26
2.26
2.26
2.26
2.26
2.26
2.26A
2.26A
2.26A
2.26A
2.27
2.27
FOLLOWING FAILURES
72
2.03
SEP 10
001
2 - PROCEDURES FOLLOWING FAILURES
Content 3/3
ANTI ICE
AFR AIR BLEED FAULT ………………………………………………………….
DE-ICING AIR FRAME FAULT …………………………………………………..
DE-ICING MODE SEL FAULT ……………………………………………………
MODE SEL AUTO FAULT (if applicable) ……………………………………….
ICE DETECT FAULT ………………………………………………………………
DE- / ANTI-ICING ENG FAULT ………………………………………………….
ANTI-ICING PROP FAULT ……………………………………………………….
ANTI-ICING HORNS FAULT ……………………………………………………..
SIDE WINDOW / WINDSHIELD HTG FAULT ………………………………….
PROBES HTG FAULT …………………………………………………………….
2.28
2.28
2.28
2.28
2.29
2.29
2.29
2.29
2.29
2.29
AUTO PILOT
AILERON MISTRIM (ADU message)
or EXCESSIVE LATERAL TRIM REQUIRED …………………………………..
or ABNORMAL FLIGHT CHARACTERISTICS
PITCH MISTRIM (ADU message) ……………………………………………….
PITCH TRIM FAIL (ADU message) (if applicable) ……………………………..
DADC DATA INVALID (ADU message) …………………………………………
2.30
2.30
2.30
2.30
MPC
APM FAULT ……………………………………………………………………….. 2.30A
DEGRADED PERF ……………………………………………………………….. 2.30A
INCREASE SPEED ………………………………………………………………. 2.30A
AVIONICS
AUDIO SEL FAULT ………………………………………………………………..
AHRS A / ERECT FAIL ……………………………………………………………
EFIS COMP ………………………………………………………………………...
ADC SW FAULT …………………………………………………………………...
ADU FAILURE ……………………………………………………………………..
ADC FAULT ………………………………………………………………………..
AHRS FAIL …………………………………………………………………………
SGU FAIL …………………………………………………………………………..
CRT FAIL …………………………………………………………………………..
2.31
2.31
2.31
2.31
2.32
2.32
2.32
2.32
2.32
MISCELLANEOUS
R
COCKPIT DOOR CONTROL PANEL FAULT (if installed) ……………………
VOLCANIC ASH ENCOUNTER………………… ……………………………….
LOSS OF RADIO ALTIMETER INFORMATION ……………………………….
SMK DET FANS FAULT ………………………………………………………….
DOORS UNLK IN FLIGHT ……………………………………………………….
COCKPIT WINDOW CRACKED …………………………………………………
OXYGEN LO PR …………………………………………………………………..
2.32A
2.32A
2.33
2.33
2.33
2.33
2.33
MFC
MFC 1A FAULT ……………………………………………………………………
MFC 1B FAULT ……………………………………………………………………
MFC 2A FAULT ……………………………………………………………………
MFC 2B FAULT ……………………………………………………………………
MFC 1A + 1B FAULT ……………………………………………………………...
MFC 1A + 2A FAULT ……………………………………………………………...
MFC 1A + 2B FAULT ……………………………………………………………...
MFC 1B + 2A FAULT ……………………………………………………………...
MFC 2A + 2B FAULT ……………………………………………………………...
MFC 1B + 2B FAULT ……………………………………………………………...
2.34
2.34
2.35
2.35
2.36
2.37
2.38
2.39
2.40
2.41
ELEC Section for EMER & ESS BUS lost equipment lists…………….……… 2.42
Cargo configuration only…… 2.42A
72
FOLLOWING FAILURES
POWER PLANT
2.04
OCT 09 500
SINGLE ENG OPERATION
R
R
LAND ASAP
PWR MGT.................................................... TO if necessary then MCT
FUEL PUMP affected side.............................................................. OFF
DC GEN affected side .................................................................... OFF
ACW GEN affected side ................................................................. OFF
PACK affected side......................................................................... OFF
BLEED affected side....................................................................... OFF
APM (if installed)............................................................................. OFF
TCAS (if installed) ................................................................... TA ONLY
OIL PRESSURE ON FAILED ENGINE .................................MONITOR
Note: In icing conditions, FLAPS 15 will be selected to improve drift down
performances and single engine ceiling.
Note: Refer to pages (4.61) and (4.62) to determine single engine gross
ceiling.
Note: If during the flight, a positive oil pressure has been noted on the
failed engine for a noticeable period of time, maintenance must be
informed.
Note: monitor fuel balance. Recommended operational maximum fuel
unbalance is 200 kg (440 lb).
When FUEL CROSS FEED is required
FUEL PUMP affected side........................................................... ON
FUEL X FEED.............................................................................. ON
FUEL PUMP operating engine .................................................. OFF
For approach
MAX APPROACH SLOPE for Steep Slope Approach ............... 5.5°
BLEED NOT AFFECTED .......................................................... OFF
CL live engine............................................................... 100% OVRD
APPROACH SPEED ........................... NOT LESS THAN 1.1VMCA
Note: Refer to page (4.64) to determine 1.1VMCA.
Note: At touch down, do not reduce below FI before nose wheel is on
the ground.
START FAULT
ENG START ROTARY SELECTOR................... OFF / START ABORT
If above 45 % NH
START ON LIGHT ....................................CHECK EXTINGUISHED
START ............................................................. TO BE CONTINUED
X START FAIL
CONTINUE NORMAL ENGINE START
INFORM MAINTENANCE
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.04
JUL 15
500
SINGLE ENG OPERATION
R
LAND ASAP
PWR MGT.................................................. TO if necessary then MCT
FUEL PUMP affected side ............................................................ OFF
DC GEN affected side .................................................................. OFF
ACW GEN affected side ............................................................... OFF
PACK affected side ...................................................................... OFF
BLEED affected side .................................................................... OFF
APM (if installed) .......................................................................... OFF
TCAS (if installed) ................................................................ TA ONLY
OIL PRESSURE ON FAILED ENGINE ............................... MONITOR
Note: In icing conditions, FLAPS 15 will be selected to improve drift down
performances and single engine ceiling.
Note: Refer to pages (4.61) and (4.62) to determine single engine gross
ceiling.
Note: If during the flight, a positive oil pressure has been noted on the
failed engine for a noticeable period of time, maintenance must be
informed.
Note: monitor fuel balance. Recommended operational maximum fuel
unbalance is 200 kg (440 lb).
When FUEL CROSS FEED is required
FUEL PUMP affected side ......................................................... ON
FUEL X FEED ........................................................................... ON
FUEL PUMP operating engine................................................. OFF
For approach
MAX APPROACH SLOPE for Steep Slope Approach ............... 5.5°
BLEED NOT AFFECTED ........................................................ OFF
CL live engine ............................................................ 100% OVRD
V APP......................................................... NOT LESS THAN VGA
■ If affected engine NP above 10%
V APP ........................ NOT LESS THAN LDG SPEED + 10kt
■ If V APP is increased
LDG DISTANCE ..........................................MULTIPLY BY 1.13
Note: Refer to part 4 to determine VGA, and landing distance.
Note: At touch down, do not reduce below FI before nose wheel is
on the ground.
START FAULT
ENG START ROTARY SELECTOR .................. OFF / START ABORT
If above 45 % NH
START ON LIGHT................................... CHECK EXTINGUISHED
START ........................................................... TO BE CONTINUED
X START FAIL
CONTINUE NORMAL ENGINE START
INFORM MAINTENANCE
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.05
OCT 08 001
ABNORMAL PARAMETERS
DURING START
 If ITT tends to exceed 900°C, or no ITT, or no NH
CL affected side ................................................................ FUEL SO
ENG START ROTARY SELECTOR.............. OFF / START ABORT
Then refer to relevant procedure:
 EXCESSIVE ITT DURING START procedure (2.05)
 NO ITT DURING START procedure (2.05)
 NO NH DURING START procedure (2.05)
EXCESSIVE ITT DURING START
 When NH below 30 %
ENG START ROTARY SELECTOR..................................... CRANK
START PB ................................................................................... ON
 After 15 seconds
ENG START ROTARY SELECTOR ........ OFF / START ABORT
CAUTION: If ITT exceeds 950°C, maintenance action is due.
Note: BLEED VALVE may be selected OFF in order to reduce ITT.
NO ITT DURING START
 After 30 seconds, to allow fuel draining
ENG START ROTARY SELECTOR..................................... CRANK
START PB ................................................................................... ON
 After 15 seconds
ENG START ROTARY SELECTOR ........ OFF / START ABORT
NO NH DURING START
Note: On BAT only, OIL PRESS IND is not available.
R
ENG START ROTARY SELECTOR...................START A or START B
START PB ........................................................................................ ON
 After 10 seconds
 If OIL pressure increases
CL ..........................................................................................FTR
Continue START procedure, being informed NH indicator is
inoperative.
 If OIL pressure does not increases
ENG START ROTARY SELECTOR ........ OFF / START ABORT
Suspect starter motor failure. Maintenance action is due.
72
R
R
R
R
R
R
FOLLOWING FAILURES
POWER PLANT
2.06
SEP 10
001
ENG NAC OVHT
 If during Hotel mode operation
PL affected side .............................................................................GI
CL affected side.............................................. FTR THEN FUEL SO
 If during taxi
AIRCRAFT ...............................................................................STOP
PL affected side .............................SLIGHTLY INCREASE POWER
 If unsuccessful within 30 seconds
PL affected side ........................................................................GI
CL affected side......................................... FTR THEN FUEL SO
ABNORMAL ENG PARAMETERS
IN FLIGHT
R
R
R
R
R
R
R
R
R
R
 If Intermittent fluctuations or unrealistic steady indication
ATPCS ....................................................................................... OFF
 When adequate flight situation
PL affected side…………………………………………………… FI
EEC affected side ................................................................. OFF
 If successful
ONE EEC FAULT procedure (2.09) .............................. APPLY
 If unsuccessful
- or -  If TQ = 0% and NP<77%
PL affected side..................................................................... FI
CL affected side......................................................... FUEL SO
SINGLE ENG OPERATION procedure (2.04) .............. APPLY
 If "- - -" indication on torque digital counter (only for PW127 PW127F - PW127M)
AVOID SUDDEN PL MOVEMENTS
FIRE LOOP FAULT
LOOP affected ................................................................................ OFF
72
FOLLOWING FAILURES
POWER PLANT
2.07
NOV 11 500
ABNORMAL PROP BRK (if applicable)
If on ground
If unexpected propeller rotation
– or – If local UNLK and CCAS PROP BRK alert
CL 2 .............................................................................. FUEL SO
MAINTENANCE ACTION REQUIRED
If CCAS PROP BRK alert only
If GUST LOCK ON
CL 2 ......................................................................... FUEL SO
If DC and AC GPU are not available
ENG 1.....................................................................START
CL 1 ..........................................................................AUTO
When READY light illuminates
PROP BRK ................................................................. OFF
UNLK LIGHT .............................CHECK EXTINGUISHED
PROP BRK PWR SPLY C/B .....................................PULL
If GUST LOCK OFF
GUST LOCK...................................................................... ON
According to operational situation
PROP BRK ................................................................. OFF
ALL PROP BRK LIGHTS ..........CHECK EXTINGUISHED
If in flight
CONTINUE NORMAL OPERATION
ENG 2 PARAMETERS .....................................................MONITOR
After landing
CL 2 .............................................................................. FUEL SO
MAINTENANCE ACTION REQUIRED
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.08
APR 08 500
ENG RESTART IN FLIGHT
FUEL SUPPLY........................................................................... CHECK
CL ........................................................................................... FUEL SO
PL........................................................................................................ FI
CAUTION: After ATPCS sequence, PWR MGT rotary selector must
be set to MCT position before engine restart, in order to
cancel propeller feathering.
ENG START ROTARY SELECTOR................................ START A & B
EEC PB............. RESET if necessary or DESELECT if FAULT persists
START PB ........................................................................................ ON
z At 10 % NH
CL ...............................................................................................FTR
RELIGHT ..........................................................................MONITOR
CL ............................................................................................AUTO
PL...................................................... ADJUST TO OTHER ENGINE
ENG START ROTARY SELECTOR....................................AS RQD
SYSTEMS AFFECTED.................................................... RESTORE
ENG STALL
PL affected side .................................................................................. FI
ENG PARAMETERS ................................................................. CHECK
„ If abnormal engine parameters
CL affected side.............................................. FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
„ If normal engine parameters
DE-/ANTI-ICING ENG ................................................................. ON
PL affected side ............................................... SLOWLY ADVANCE
„ If stall recurs
Reduce thrust and operate below the stall threshold
„ If stall does not recur
Continue engine operation
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.09
SEP 10
500
ONE EEC FAULT
R
R
ATPCS ............................................................................................ OFF
CAUTION: DO NOT DESELECT EEC FLASHING
 When adequate flight situation
PL affected side ............................... RETARD IN GREEN SECTOR
EEC affected side ..................................................................RESET
 If successful
ATPCS.................................................................................... ON
PL affected side ........................................... RESTORE POWER
 If unsuccessful
EEC affected side ................................................................. OFF
PL affected side .......................................... RESTORE POWER
......................................... HANDLING THROTTLE WITH CARE
 In the following cases: icing conditions, engine(s) flame out,
emergency descent, severe turbulence, heavy rain
MAN IGN ........................................................................... ON
 In final approach
CL 1 + 2 .............................................................. 100% OVRD
 After landing
TAXI WITH THE AFFECTED ENGINE FEATHERED
Note: ACW BTC must be check closed in order to avoid the loss
of ACW bus on ground
BOTH EEC FAULT
ATPCS ............................................................................................ OFF
CAUTION: DO NOT DESELECT EEC FLASHING
 When adequate flight situation
PL 1 + 2 ........................................... RETARD IN GREEN SECTOR
EEC 1 + 2 ................................................................. OFF THEN ON
 If EEC 1+2 recovered
ATPCS.................................................................................... ON
PL 1 + 2 ....................................................... RESTORE POWER
 If only one EEC recovered
ONE EEC FAULT procedure (2.09) ................................. APPLY
 If no EEC recovered
EEC 1 + 2 ............................................................................. OFF
PL 1 + 2 ....................................................... RESTORE POWER
....................................... HANDLING THROTTLES WITH CARE
TQ IND ENG 1 + 2.......................................................MONITOR
LDG DIST ....................................................... MULTIPLY BY 1.5
Note: Refer to Part 4 to determine landing distance
 In the following cases: icing conditions, engine(s) flame out,
emergency descent, severe turbulence, heavy rain
MAN IGN ........................................................................... ON
 In final approach
CL 1 + 2 .............................................................. 100% OVRD
 After landing
BRAKE HANDLE........................................... EMER AS RQD
CAUTION: Reverse power is reduced.
Both main HYD pumps will be lost at low speed.
TAXI ON BOTH ENGINES,
HANDLE THROTTLES WITH CARE
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.10
OCT 09 050
ENG FLAME OUT
PL affected side .................................................................................. FI
R
R
R
If NH drops below 30 % (no immediate relight)
CL affected side.............................................. FTR THEN FUEL SO
If damage suspected
FIRE HANDLE affected side ...............................................PULL
SINGLE ENG OPERATION procedure (2.04).................. APPLY
If no damage suspected
ENG RESTART IN FLIGHT procedure (2.08).................. APPLY
If unsuccessful
SINGLE ENG OPERATION procedure (2.04) ............ APPLY
IDLE GATE FAIL
In flight
IDLE GATE LEVER .................................................................PUSH
At touch down
IDLE GATE LEVER ..................................................................PULL
Mod : 4111
72
R
R
R
R
FOLLOWING FAILURES
POWER PLANT
2.10A
SEP 10
500
UNCOMMANDED 100% NP ON ONE OR
TWO PROPELLERS
CL 1 + 2 ............................................................................. 100% OVRD
PEC SGL CH
DO NOT RESET PEC IN FLIGHT - NO SPECIAL CREW ACTION
ANTICIPATE A PEC FAULT AT LANDING
MAINTENANCE IS REQUIRED
PEC FAULT
If in short final approach (below 400 ft RA)
GO AROUND procedure ....................................................... APPLY
Above 400 ft or when adequate
CL affected side............................................................ 100% OVRD
PEC affected side ..................................................................RESET
If successful
CL affected side..................................................................AUTO
If unsuccessful
PEC affected side................................................................. OFF
Avoid sudden PL movements
Before landing
CL NON AFFECTED .......................................... 100% OVRD
Reverse is not available on affected side.
TAXI ON BOTH ENGINES
Note: ACW BTC may be check closed in order to avoid the loss
of ACW bus on ground
Mod : 3973 or 4371 or 4457
72
FOLLOWING FAILURES
POWER PLANT
2.11
SEP 10
500
LO PITCH IN FLIGHT
PL affected side .................................................................................. FI
CL affected side ................................................... FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04) ............................ APPLY
ENG OVER LIMIT
PL affected side .............. RETARD TO RESTORE NORMAL VALUES
Note: BLEED VALVE may be selected OFF in order to reduce ITT
If TQ, NH, and/or ITT still over limit and if conditions permit
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
PROP OVER LIMIT
R
R
R
R
R
R
R
R
R
PL affected side .......................... RETARD TO SET NP BELOW 106%
PEC affected side ............................................................. OFF then ON
PL affected side .......................................................................AS RQD
If NP decreases below 106%
CONTINUE NORMAL FLIGHT
Note: 106% allowed to complete a flight without overshooting 73%
TQ in CRZ and 75% in CLB
If NP remains above 106% and conditions permit
PL affected side .............................................................................. FI
CL affected side ............................................... FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04) ........................ APPLY
Eng : PW127F / PW127M
72
FOLLOWING FAILURES
POWER PLANT
2.12
OCT 08 500
ENG OIL TEMP BELOW 45°C
„ If icing conditions are expected or present
ENG POWER ...............................................If possible, INCREASE
ENG OIL TEMP HIGH
„ OIL TEMP between 125°C and 140°C
OIL TEMP AND PRESS ...................................................MONITOR
Note: If OIL temperature rise follows PL reduction, advancing PL
may reduce OIL temperature.
Note: If OIL temperature rise occurs in steady state conditions, a
power reduction should permit a reduction in OIL
temperature.
„ OIL TEMP between 125°C and 140°C for more than 20 minutes
PL affected side ...........RETARD TO SET minimum possible power
CAUTION: Flight plan must be rescheduled to minimize engine
operating time in these abnormal conditions.
„ OIL TEMP above 140°C
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
ENG OIL LO PR
R
PL affected side .................................................................................. FI
„ If both OIL LO PR on CAP and local alert are activated
CL affected side.............................................. FTR THEN FUEL SO
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
„ If local alert only is activated
CL affected side.............................................. FTR THEN FUEL SO
Once engine is shut off
CL affected side..........................................................................FTR
„ If CCAS is activated after 30 seconds
CL affected side............................................................ FUEL SO
ENG RESTART IN FLIGHT procedure (2.08).................. APPLY
„ If not
CL affected side ............................................................ FUEL SO
SINGLE ENG OPERATION procedure (2.04).................. APPLY
„ If OIL LO PR alert on CAP only is activated
DISREGARD
INFORM MAINTENANCE
„ If single engine operation required
NP of feathered engine.....................................................MONITOR
„ If NP of feathered engine above 10%
APPROACH SPEED .................................INCREASE BY 10 KT
Eng : PW127F / PW127M
72
FOLLOWING FAILURES
FUEL
2.13
SEP 13
500
FUEL ABNORMAL TEMP
 If too high (>50°C)
Note: Avoid rapid throttle movement
OIL TEMP AND OTHER ENGINES PARAMETERS .......MONITOR
 If too low (<0°C)
Note: Use anti-icing additive for next refueling if repair can't be done
FUEL CLOG
 If both lights are illuminated
ENGINES PARAMETERS................................................MONITOR
 If abnormal engines parameters
LAND ASAP
Note: Fuel contamination may be suspected
MAINTENANCE ACTION REQUIRED
 If only one light is illuminated
ENGINE PARAMETERS affected side.............................MONITOR
FUEL FEED LO PR
PUMP affected side ........................................................ CONFIRM ON
ENGINE affected side...........MONITOR FOR POSSIBLE RUN DOWN
 If engine runs down or if fuel quantity decreases significantly
PL affected side ............................................................................. FI
CL affected side.............................................. FTR THEN FUEL SO
PUMP affected side ................................................................... OFF
FIRE HANDLE affected side.....................................................PULL
LAND ASAP
SINGLE ENG OPERATION procedure (2.04)....................... APPLY
CAUTION: Do not open X FEED valve
Model : 212A
72
FOLLOWING FAILURES
FUEL
2.14
OCT 09 500
FUEL LEAK ALERT CONDITION
A fuel leak may be detected by either:
- sum of fuel on board (FOB), read in steady flight at cruise level, and
fuel used (FU), FOB+FU significantly less than fuel at departure, or
- total fuel quantity decreasing (fuel spray from engine or wing tip), or
- fuel imbalance, or
- a tank emptying too fast (leak from engine or a hole in a tank), or
- excessive fuel flow (leak from engine), or
- fuel smell in the cabin
FUEL LO LVL
R
AVOID EXCESSIVE AIRCRAFT ATTITUDES
If both LO LVL lights ON
LAND ASAP
If LO LVL light on one side only
If leak suspected
FUEL LEAK procedure (2.14)........................................... APPLY
If no leak suspected
If FQI < 160 kg / 352 lb
X FEED.............................................................................. ON
If FQI ≥ 160 kg / 352 lb,
Feeder jet pump malfunction is suspected
X FEED is not necessary
FUEL CONSUMPTION ..........................................MONITOR
FUEL LEAK
When a leak is confirmed
LAND ASAP
Leak from engine (excessive fuel flow or feed spray from engine)
PL affected side ........................................................................ FI
CL affected side......................................... FTR THEN FUEL SO
PUMP affected side.............................................................. OFF
FIRE HANDLE affected side ...............................................PULL
SINGLE ENG OPERATION procedure (2.04).................. APPLY
If excessive fuel flow was identified before engine shutdown
FUEL X FEED valve can be opened
In all other cases X FEED valve must remain closed
Leak not located
FUEL X FEED............................................. MAINTAIN CLOSED
Note: the X FEED must remain closed to prevent the leak
affecting both sides.
Before landing
ATC................................................................................. NOTIFY
Mod : 4686 or 8148
72
FOLLOWING FAILURES
ELEC
2.15
OCT 09 550
DC BUS 1 OFF
DC GEN 1 ....................................................................................... OFF
PF.................................................................................................... CM2
MAN RATE KNOB ...............................................................9 O'CLOCK
CAB PRESS MODE SEL................................................................MAN
DC SVCE AND UTLY BUS SHED.................................. MAINTAIN ON
AFFECTED EQUIPMENT............................................................... OFF
DC BUS 1 EQUIPMENT LIST ................................................... CHECK
At touch down
IDLE GATE LEVER ..................................................................PULL
DC BUS 1 LOST EQUIPMENT LIST
Instruments, Navigation & Com:
Weather Radar
Radio Altimeter (2.33)
(E)GPWS
DME #1
Air:
Bleed LEAK IND 1 & 2
AUTO PRESS (2.26A)
Flight controls:
Stick Pusher (2.21)
CM1 Stick Shaker (2.21)
Ice & Rain protection:
CM1 and STBY Static Ports anti-icing
CM1 Side Window Anti-Icing (2.32)
CM2 Windshield HTG IND
Engines:
FF/FU#1,
Fuel TEMP#1 & Fuel CLOG #1
Oil PRESS & Oil TEMP #1
AUTO IDLE GATE (2.10)
Light:
CM1 Dome, chartholder & reading light
CM2 Flood panel light
Storm light, Annunciator light test
NAV & BEACON light
Miscellaneous:
Toilet flushing (If supplied by DC)
AC BUS 1 OFF
Note: Wait for 10 seconds in order to confirm the failure.
DC BTC......................................................................... ISOL THEN ON
If unsuccessful
AC BUS 1 EQUIPMENT LIST .............................................. CHECK
AC BUS 1 LOST EQUIPMENT LIST
115 AC BUS 1
BLEED LEAK DET 1 & 2
26 AC BUS 1
TRIMS IND
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
Mod : 4366 and (3973 or 4371 or 4457)
FOLLOWING FAILURES
ELEC
72
2.15A
OCT 09 150
DC BUS 2 OFF
DC GEN 2 ....................................................................................... OFF
PF.................................................................................................... CM1
ADC SW......................................................................... SET TO ADC 1
VHF 1 / ATC 1...........................................................................SELECT
AFFECTED EQUIPMENT............................................................... OFF
DC BUS 2 EQUIPMENT LIST ................................................... CHECK
Before descent
PAX INSTRUCTIONS.......................................................... USE PA
After touch down
TAXI ON BOTH ENGINES
DC BUS 2 LOST EQUIPMENT LIST
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
Instruments, Navigation & Com:
CM2 EADI/EHSI & SGU#2 (2.32)
VOR/ILS/DME#2, ADF#2, CM1 RMI
VHF#2
ATC#2, TCAS or T2CAS (if installed)
ADC #2 & ALT ALERT # 2 (2.32)
CM2 Clock
GPS (KLN90) (if installed)
CCAS: CAP amber alert except Maint
PNL, PRKG BRK & MFC
Air: Landing elevation IND
Hydraulic:
DC AUX HYD PUMP (In Automatic)
Landing gear: Secondary IND
Flight controls:
Right stick shaker
Standby pitch trim control
TLU auto control
Ice & Rain protection:
CM2 Static Port anti-icing
CM2 Probes IND
CM2 Wiper
CM2 Side window anti-icing (2.29)
CM1 Windshield HTG IND
Engines:
FF/FU #2
FUEL TEMP #2, FUEL CLOG #2
OIL PRESS, TEMP #2
IDLE GATE FAIL IND
Light:
CM2 Chartholder, Reading LIGHTS
Integrated Norm INST&PANEL LIGHTS
Taxi / Take off LIGHT, Wing LIGHTS
Passenger Signs
Doors:
Doors UNLK lights
Cockpit door locking system
Fire: NAC OVHT
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
R
AC BUS 2 OFF
Note: Wait for 10 seconds in order to confirm the failure.
DC BTC......................................................................... ISOL THEN ON
If unsuccessful
PF .............................................................................................. CM1
AC BUS 2 EQUIPMENT LIST .............................................. CHECK
AC BUS 2 LOST EQUIPMENT LIST
115 AC BUS 2
R
R GPWS
26 AC BUS 2
CM2 ASI, VSI, ALTI
Heading RMI#1
Bearing VOR#2&ADF#2 to RMI/SGU 1/2
Course#2 and Heading#2 Select
For more information on BUS EQUIPMENT LISTS see F
COM 1.06.60
Mod : 4116 + 4366
R
R
R
72
FOLLOWING FAILURES
ELEC
2.16
OCT 09 001
ACW BUS 1 OFF / ACW BUS 2 OFF
ACW GEN affected side ................................................................. OFF
LEAVE AND AVOID ICING CONDITIONS
AS LONG AS ICING CONDITIONS EXIST
ICE ACCRETION ..................................... VISUALLY MONITOR
If ACW BUS 1 OFF
PF .............................................................................................. CM2
CM1 AIRSPEED INDICATOR ..........................................MONITOR
If ACW BUS 2 OFF
PF .............................................................................................. CM1
CM2 AIRSPEED INDICATOR ..........................................MONITOR
AFFECTED EQUIPMENT............................................................... OFF
HYD X FEED .................................................................................... ON
ACW BUS 1 or 2 LOST EQUIPMENT LIST .............................. CHECK
If any IAS discrepancy occurs
DADC DATA INVALID (ADU message) procedure (2.30) .... APPLY
After touch down
TAXI ON BOTH ENGINES
ACW BUS 1 LOST EQUIPMENT LIST
R
R
R
R
R
R
Hydraulic:
BLUE PUMP
Lights:
Integrated INST&PNL Lights
LEFT LANDING LIGHT
LEFT and REAR STROBES
Ice & Rain protection:
CM1 PITOT / ALPHA / TAT Heating
ANTI-ICING PROP 1
ANTI-ICING HORNS (LH ELEV, RUD)
CM1 WINDSHIELD HTG
Miscellaneous:
Toilet (If supplied by ACW)
R
R
R
R
R
R
R
ACW BUS 2 LOST EQUIPMENT LIST
R
R
R
R
R
R
Hydraulic:
GREEN PUMP
Lights:
TAXI/TO LIGHTS
RIGHT LANDING LIGHT
RIGHT STROBE
Ice & Rain protection:
CM2 PITOT / ALPHA / TAT Heating
ANTI-ICING PROP 2
ANTI-ICING HORNS (RH ELEV, AIL)
CM2 Windshield HTG
ICE DETECTOR
R
R
R
R
R
R
72
FOLLOWING FAILURES
ELEC
2.16A
OCT 09 001
ACW TOTAL LOSS
ACW GEN 1 + 2.............................................................................. OFF
HYD X FEED .....................................................................CHECK OFF
LEAVE AND AVOID ICING CONDITIONS
AS LONG AS ICING CONDITIONS EXIST
ICE ACCRETION........................................... VISUALLY MONITOR
CM1 and CM2 AIRSPEED INDICATORS ........................MONITOR
ACW TOTAL LOSS EQUIPMENT LIST .................................... CHECK
AFFECTED EQUIPMENT............................................................... OFF
MAIN HYD PUMPS......................................................................... OFF
LDG GEAR EXTENSION/RETRACTION ..................................... LOST
NORMAL BRAKE ......................................................................... LOST
LDG DIST ................................................................. MULTIPLY BY 1.5
Note: Refer to Part 4 to determine LDG DIST
Before landing
LDG GEAR LEVER ............................................................... DOWN
BLUE PRESSURE................................................................ CHECK
FLAPS..................................................................................AS RQD
LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY
After touch down
REVERSE............................................................................AS RQD
BRAKE HANDLE ..................................................... EMER AS RQD
TAXI ON BOTH ENGINES
ACW TOTAL LOST EQUIPMENT LIST
R
R
R
R
R
R
Hydraulic:
BLUE & GREEN PUMP
Lights:
Integrated INST&PNL Lights
LEFT & RIGHT LANDING LIGHT
TAXI/TO LIGHTS
Ice & Rain protection:
CM 1&2 PITOT/ALPHA/TAT Heating
ANTI-ICING PROP 1&2
ANTI-ICING HORNS
CM1&2 WINDSHIELD HTG
ICE DETECTOR
Miscellaneous:
Toilet (If supplied by ACW)
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
R
R
R
R
R
R
R
R
72
FOLLOWING FAILURES
ELEC
2.17
OCT 08 001
DC ESS BUS OFF
DC ESS BUS EQUIPMENT LIST .............................................. CHECK
 If Cockpit Securized Door installed
COCKPIT DOOR MANUAL LOCK BOLT(S).....................................
.......................................................... MOVE TO CLOSE POSITION
Note: Cockpit Door Control Panel FAULT LIGHT is inoperative.
Note: When the door is locked with the manual bolt(s), the
emergency access to the cockpit is unavailable. It is
recommended that at least two crewmembers remain in the
cockpit during that time.
R
R
DC ESS BUS LOST EQUIPMENT LIST
See QRH pages 2.42 (all configuration)
and 2.42A (for cargo configuration only)
DC EMER BUS OFF
R
R
LEAVE AND AVOID ICING CONDITIONS
DESCEND TOWARD ........................................................FL100 / MEA
STBY PITCH TRIM .......................................................... USE AS RQD
ADC SW (ADC FAULT lights lost) ................................. SET TO ADC 2
HYD X FEED .................................................................................... ON
 If ice accretion builds up on airframe
DE-ICING MODE SEL FAULT procedure (2.28)................... APPLY
ANTI-ICING PROP FAULT procedure (2.29) ........................ APPLY
ANTI-ICING HORNS FAULT procedure (2.29) ..................... APPLY
CM1 and STBY IAS ............................................COMPARE to CM2
Note: Use CM2 instruments in case of disagreement.
 Before landing
ANTI-SKID ................................................................................. OFF
N/W STEERING ........................................................................ OFF
ANTI-SKID FAULT procedure (2.25)..................................... APPLY
DC EMER BUS OFF LOST EQUIPMENT LIST
R
See QRH pages 2.42 (all configuration)
and 2.42A (for cargo configuration only)
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
FOLLOWING FAILURES
ELEC
72
2.18
OCT 08 500
DC GEN FAULT
DC GEN affected side..................................................................... OFF
„ If OAT exceeds ISA + 25
FL........................................................................................200 MAX
TAXI ON BOTH ENGINES
INV FAULT
NO SPECIFIC ACTION IN FLIGHT
ACW GEN FAULT
ACW GEN affected side ................................................................. OFF
LEAVE AND AVOID ICING CONDITIONS
TAXI ON BOTH ENGINES
DC SVCE/UTLY BUS SHED
DC SVCE/UTLY BUS PB..........................................................AS RQD
DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST
R
See FCOM 1.06.60 pages 12 to 14
BAT CHG FAULT
CHG associated.............................................................................. OFF
DUAL BAT CHG LOSS
MFC MODULES, one at a time ....................................... OFF / RESET
„ If RESET unsuccessful
LAND ASAP
Note: minimize use of VHF 1 if conditions permit.
BAT DISCHARGE IN FLIGHT
ENG START ROTARY SELECTOR............................................... OFF
„ If battery(ies) still discharging
LAND ASAP
Mod : 3246 + 4111
FOLLOWING FAILURES
ELEC
72
2.18A
APR 08 550
STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS
Mod : 4116 + 4366
72
FOLLOWING FAILURES
ELEC
2.18B
APR 08 500
STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS
Mod : 4116
72
FOLLOWING FAILURES
HYDRAULIC
2.19
OCT 08 001
HYD LO LVL
„ If blue system affected
BLUE PUMP .............................................................................. OFF
AUX PUMP ....................................................... OFF (CONFIRMED)
REDUCED FLAPS LANDING procedure (2.21).................... APPLY
z After touch down
USE NORMAL BRAKE FOR STEERING
TAXI ON BOTH ENGINES
„ If green system affected
GREEN PUMP........................................................................... OFF
LDG DIST ............................................................ MULTIPLY BY 1.5
Note: Refer to Part 4 to determine landing distance
LDG GRAVITY EXTENSION procedure (2.24) ..................... APPLY
z After touch down
TAXI ON BOTH ENGINES
REVERSE.......................................................................AS RQD
BRK HANDLE..................................................... EMER AS RQD
HYD SYS LOST EQUIPMENT LIST
BLUE
FLAPS / SPOILERS / N/W STEERING
PROP BRK (if applicable)
EMER AND PARKING BRK (on accu
only)
GREEN
LDG GEAR EXT / RET
NORM BRK
BOTH MAIN HYD PUMPS LOSS
MAIN BLUE AND GREEN PUMPS ................................................ OFF
X FEED ..............................................................................CHECK OFF
LDG DIST ................................................................. MULTIPLY BY 1.5
Note: Refer to Part 4 to determine landing distance
z Before landing
LDG GEAR LEVER ............................................................... DOWN
BLUE PRESSURE................................................................ CHECK
FLAPS 15 ............................................................................AS RQD
LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY
FLAPS 30 ............................................................................AS RQD
z After touch down
TAXI ON BOTH ENGINES
REVERSE............................................................................AS RQD
BRK HANDLE.......................................................... EMER AS RQD
R
R
R
R
R
BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST
BLUE
recovered when
GREEN
LDG GEAR lever is DOWN
FLAPS / SPOILERS / N/W STEERING
PROP BRK (if applicable)
EMER AND PARKING BRK (on accu
only)
LDG GEAR EXT / RET
NORM BRK
72
FOLLOWING FAILURES
HYDRAULIC
2.20
OCT 08 500
BOTH HYD SYS LOSS
R
R
R
R
MAIN AND AUX PUMPS ................................................................ OFF
Before approach
GPWS......... GPWS OVRD or FLAP OVRD (depending on version)
LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY
APP/LDG SPEED ........................VmHB 0 + 5 KT + WIND EFFECT
LDG DIST ........................MULTIPLY LDG DIST FLAPS 30 BY 2.9
Note: Refer to Part 4 to determine VmHB and LDG DIST
CAUTION: Tail strike may occur if pitch attitude exceeds 8° during
the flare depending upon vertical speed at touch
down.
After touch down
REVERSE............................................................................AS RQD
BRK HANDLE .......................................................... EMER AS RQD
TAXI ON BOTH ENGINES
BOTH HYD SYS LOST EQUIPMENT LIST
R
R
R
R
BLUE
FLAPS / SPOILERS / N/W STEERING
PROP BRK (if applicable)
EMER AND PARKING BRK (on accu
only)
GREEN
LDG GEAR EXT / RET
NORM BRK
HYD LO PR / HYD OVHT
PUMP affected side ........................................................................ OFF
X FEED ............................................................................................. ON
Mod : 3973 or 4371 or 4457
Eng : PW127 / PW127F / PW127M
FOLLOWING FAILURES
FLIGHT CONTROL
72
2.21
APR 08 500
FLAPS UNLK
„ If before V1
TAKE OFF ............................................................................ ABORT
„ If after V1
VR, V2.............................................................INCREASE BY 10 KT
„ If alarm occurs during approach
GO AROUND procedure ....................................................... APPLY
VGA ................................................................INCREASE BY 10 KT
z When possible
FLAPS..............................................................................................0
REDUCED FLAPS LANDING procedure (2.21).................... APPLY
FLAPS JAM / UNCOUPLED / ASYM
FLAPS CTL LEVER .....................NEAR FLAPS PRESENT POSITION
z When applicable
REDUCED FLAPS LANDING procedure (2.21).................... APPLY
REDUCED FLAPS LANDING
GPWS .............. GPWS OVRD or FLAP OVRD (depending on version)
STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED
FLAPS
LDG DIST
FLAPS 30
MULTIPLY BY
APP/LDG SPEED
0
2.2
VmHB 0 + WIND EFFECT + 5 KT
15
2
VmHB 15 + WIND EFFECT
Note: Refer to Part 4 to determine VmHB and LDG DIST
CAUTION: Tail strike may occur if pitch attitude exceeds 8° during the
flare depending upon vertical speed at touch down.
STICK PUSHER / SHAKER FAULT
STICK PUSHER / SHAKER ........................................................... OFF
TCAS (if installed) ................................................................... TA ONLY
VmHB / VmLB FOR ALL CONFIGURATION ......INCREASE BY 10 KT
LDG DIST ............................................................... MULTIPLY BY 1.13
Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST
Mod : 3973 or 4371 or 4457
Eng : PW127 / PW127F / PW127M
72
FOLLOWING FAILURES
FLIGHT CONTROL
2.22
OCT 09 001
PITCH TRIM ASYM (LOCAL LIGHT)
AP DISCONNECTION ...................................... CONFIRM MANUALLY
PITCH TRIM INOPERATIVE procedure (2.22) .......................... APPLY
PITCH TRIM INOPERATIVE
EXISTING CONFIGURATION AND SPEED ..........................................
.................................................... MAINTAIN AS LONG AS POSSIBLE
For approach
STEEP SLOPE APPROACH (≥4.5°)...........................PROHIBITED
FLAPS................ EXTEND AT VFE FOR EACH CONFIGURATION
LDG SPEED ...................................................INCREASE BY 10 KT
LDG DIST .......................................................... MULTIPLY BY 1.13
Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST
R
R
R
R
R
DUTCH ROLL TENDENCY /
RUDDER RELEASABLE CENTERING
UNIT FAIL
If YD is available
YD ...................................................................................... ENGAGE
If YD is not available
LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT
UNEXPECTED RUDDER PEDAL MOVEMENT
PITCH DISCONNECT
BOTH CONTROL COLUMNS ........................................ CHECK FREE
IAS ....................................................................................... 180 kt MAX
LOAD FACTOR ............................................................................... 2 g MAX
BANK ANGLE ............................ 30° MAX UNTIL FLAPS EXTENSION
AVOID ICING CONDITIONS
For approach
STEEP SLOPE APPROACH (≥4.5°)...........................PROHIBITED
LAND AT AIRPORT WITH MINIMUM CROSSWIND
LDG SPEED ...................................................INCREASE BY 10 KT
LDG DIST .......................................................... MULTIPLY BY 1.13
PL 1 + 2 ..................................... REDUCE SMOOTHLY TO FLARE
Note: Refer to Part 4 to determine LDG DATA
When on ground and ELEV CLUTCH GUARDED PB installed
PITCH RECONNECTION ON GROUND procedure (2.22A) ............
............................................................................................... APPLY
FOLLOWING FAILURES
FLIGHT CONTROL
72
2.22
JUL 15
100
PITCH TRIM ASYM (LOCAL LIGHT)
AP DISCONNECTION..................................... CONFIRM MANUALLY
PITCH TRIM INOPERATIVE procedure (2.22).......................... APPLY
PITCH TRIM INOPERATIVE
EXISTING CONFIGURATION AND SPEED ........................................
.................................................. MAINTAIN AS LONG AS POSSIBLE
For approach
STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED
FLAPS ............... EXTEND AT VFE FOR EACH CONFIGURATION
LDG SPEED................................................. INCREASE BY 10 KT
LDG DIST ........................................................MULTIPLY BY 1.13
Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST
DUTCH ROLL TENDENCY /
RUDDER RELEASABLE CENTERING
UNIT FAIL
If YD is available
YD .................................................................................. ENGAGE
If YD is not available
LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT
UNEXPECTED RUDDER PEDAL MOVEMENT
PITCH DISCONNECT
BOTH CONTROL COLUMNS ...................................... CHECK FREE
IAS .................................................................................... 180 kt MAX
LOAD FACTOR ............................................................................ 2 g MAX
BANK ANGLE ........................... 30° MAX UNTI L FLAPS EXTENSION
R
AVOID ICING CONDITIONS
For approach
STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED
LAND AT AIRPORT WITH MINIMUM CROSSWIND
LDG SPEED................................................. INCREASE BY 10 KT
LDG DIST ........................................................MULTIPLY BY 1.13
PL 1 + 2 .................................... REDUCE SMOOTHLY TO FLARE
Note: Refer to Part 4 to determine LDG DATA
At parking
If pitch disconnect occurred in flight
MAINTENANCE ACTION REQUIRED
If pitch disconnect occurred on ground
PITCH RECONNECTION ON GROUND procedure (2.22A)................. APPLY
Mod 3529 or 3530
FOLLOWING FAILURES
FLIGHT CONTROL
72
2.22A
APR 08 500
PITCH RECONNECTION ON GROUND
(if applicable)
GUST LOCK ........................................................................... ENGAGE
BOTH COLUMNS ...................................................... CHECK LOCKED
ELEV CLUTCH GUARDED PB .........................DEPRESS AND HOLD
z When PITCH DISCONNECT flashes red on CAP
ELEV CLUTCH GUARDED PB ........................................ RELEASE
PITCH DISCONNECT ON CAP ...............CHECK EXTINGUISHED
BOTH COLUMNS.............................................. CHECK COUPLED
TLU FAULT
„ If ADC 1 + 2 are lost
„ If IAS above 185 kt
TLU ...................................................................................HI SPD
„ If IAS below 185 kt
TLU ................................................................................. LO SPD
DISREGARD TLU FAULT ALERT
„ If at least one ADC operates
„ If IAS above 185 kt
TLU ...................................................................................HI SPD
„ If TLU FAULT alarm persists
SPEED ............................................................... 180 KT MAX
TLU............................................................................ LO SPD
„ If IAS below 185 kt
SPEED..................................................................... 180 KT MAX
TLU ................................................................................. LO SPD
DISREGARD TLU FAULT ALERT
„ If TLU green light is not lit
VAPP ....................................................INCREASE BY 10 KT
LDG DIST ................................................ MULTIPLY BY 1.13
LAND AT AIRPORT WITH MINIMUM CROSSWIND
Note: Maximum demonstrated crosswind (dry runway) with TLU HI SPD
mode : 15 kt.
AIL LOCK LIT
„ If before take off
RETURN TO PARKING
REFER TO MMEL ATA 27 ITEM 70-1 GUST LOCK SYSTEM
„ If after landing
TAKE SPECIAL CARE FOR TAXI (WIND EFFECTS)
USE STANDBY SYSTEM FOR AILERON LOCK AT PARKING
INFORM MAINTENANCE
Mod : 4373 or 8167
72
FOLLOWING FAILURES
FLIGHT CONTROL
2.23
APR 08 001
ELEVATOR JAM
CONTROL COLUMNS ...................................................... UNCOUPLE
AVOID ICING CONDITIONS
IAS ..................................................................................... 180 KT MAX
„ If one elevator is stuck to full down position
IAS ................................................................................ 154 KT MAX
„ If left elevator is jammed
MINIMUM MANEUVER OPERATING SPEEDS..........INCREASE BY 10 KT
„ If elevator jamming occurs at take off
IAS ................................................................................ 161 KT MAX
PITCH DISCONNECT procedure (2.22)..................................... APPLY
AILERON JAM / SPOILER JAM
BANK ANGLE LIMIT................................................................ 25° MAX
BLUE AND AUX HYD PUMPS ....................................................... OFF
LAND AT AIRPORT WITH MINIMUM CROSSWIND
z For approach
STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED
BLUE AND AUX HYD PUMPS.................................................... ON
CAUTION: Do not extend FLAPS in turn
z When in landing configuration
BLUE AND AUX HYD PUMPS.................................................. OFF
z Immediately after touch down
BLUE AND AUX HYD PUMPS.................................................... ON
RUDDER JAM
STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED
LANDING ............................................................................... FLAPS 30
USE DIFFERENTIAL POWER SO AS TO MINIMIZE SIDESLIP
LAND AT AIRPORT WITH MINIMUM CROSSWIND
z At touch down
NOSE DOWN BEFORE REDUCTION BELOW FI
72
FOLLOWING FAILURES
LANDING GEAR
2.24
APR 08 001
LDG GEAR GRAVITY EXTENSION
LDG GEAR LEVER..................................................................... DOWN
EMER EXTENSION HANDLE .........PULL ABOVE PEDESTAL LEVEL
.....................AND MAINTAIN UP TO GREEN LIGHTS ILLUMINATED
CAUTION: Do not twist the handle when operating
TCAS (if installed) ................................................................... TA ONLY
„ If unsuccessful
LANDING WITH ABNORMAL LDG GEAR procedure (2.24) ............ APPLY
LANDING WITH ABNORMAL LDG GEAR
z Preparation
CABIN CREW (PA).............................................................. NOTIFY
ATC / TRANSPONDER ...................................... NOTIFY / AS RQD
SEAT BELTS / NO SMOKING .................................................... ON
GPWS ........................................................................................ OFF
CABIN AND COCKPIT .................................................... PREPARE
LOOSE AND SURVIVAL EQUIPMENT ............ CHECK SECURED
BELTS AND SHOULDER HARNESS .................. CHECK LOCKED
FUEL WEIGHT .......................................... IF POSSIBLE, REDUCE
„ If abnormal nose LDG GEAR
CG LOCATION ..............................................IF POSSIBLE, AFT
„ If abnormal main LDG GEAR
FUEL UNBALANCE .........................IF POSSIBLE, ESTABLISH
Note: Reduced fuel on side with failed LDG GEAR.
z Approach
LDG GEAR LEVER ............................................. CONFIRM DOWN
LDG GEAR EMER EXT HANDLE .....................CONFIRM PULLED
ENG START ROTARY SELECTOR.............. OFF / START ABORT
CABIN REPORT........................................... CONFIRM OBTAINED
z Before landing
BLEEDS 1 + 2............................................................................ OFF
BRACE FOR IMPACT ..........................................................ORDER
z At touch down
PL 1 + 2 .........................................................................................GI
CL 1 + 2 .......................................................... FTR THEN FUEL SO
z After touch down
FIRE HANDLES 1 + 2 ..............................................................PULL
z When aircraft stopped
PARKING BRAKE ......................................................................SET
CABIN CREW (PA).............................................................. NOTIFY
FUEL PUMPS 1 + 2................................................................... OFF
AGENTS 1 + 2 ....................................................................... DISCH
EVACUATION ....................................................................INITIATE
z Before leaving aircraft
BAT ............................................................................................ OFF
72
FOLLOWING FAILURES
LANDING GEAR
2.25
SEP 10
001
LDG GEAR UNSAFE INDICATION
 If LDG GEAR selected DOWN
 If GREEN LIGHT OFF on one panel only
UNSAFE INDICATION ........................................... DISREGARD
 If GREEN LIGHT OFF on both panels
LDG GEAR GRAVITY EXTENSION procedure (2.24) .... APPLY
 If LDG GEAR selected UP
 If RED LIGHT ON on one panel only
UNSAFE INDICATION ........................................... DISREGARD
 If RED or GREEN LIGHT ON on both panels
LEAVE AND AVOID ICING CONDITIONS
IAS ........................................................................... 160 KT MAX
LDG GEAR ....................................................................... DOWN
TCAS (if installed)......................................................... TA ONLY
LDG GEAR RETRACTION IMPOSSIBLE
LEAVE AND AVOID ICING CONDITIONS
LDG GEAR LEVER..................................................................... DOWN
IAS ..................................................................................... 185 KT MAX
CCAS .............................................................................................. RCL
TCAS (if installed) ................................................................... TA ONLY
IDLE GATE ............................................................................MONITOR
ANTI-SKID FAULT
R
ANTI SKID ...................................................................................... OFF
LDG DIST ................................................................. MULTIPLY BY 1.4
Note: Refer to Part 4 to determine LDG DIST
 At touch down
REVERSE............................................................................AS RQD
NORMAL BRAKE ................................................. USE WITH CARE
BRAKE HANDLE ..................................................... EMER AS RQD
BRK TEMP HOT
 If BRK TEMP HOT occurs before take off
TAKE OFF .............................................................................DELAY
 If BRK TEMP HOT occurs in flight
LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF
FOR COOLING EXCEPT IN CASE OF EMERGENCY
72
FOLLOWING FAILURES
AIR
2.26
APR 08 001
BLEED VALVE FAULT
PACK VALVE affected side ............................................................ OFF
BLEED VALVE affected side .......................................................... OFF
MAX FL ..................................................................................200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
BLEED OVHT
PACK VALVE affected side ............................................................ OFF
BLEED VALVE affected side .......................................................... OFF
MAX FL ..................................................................................200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
BLEED LEAK
PACK VALVE affected side ............................................................ OFF
BLEED VALVE affected side .......................................................... OFF
MAX FL ..................................................................................200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
CAUTION: System must not be restored in flight.
Note: If a bleed leak occurs on ground during taxi, go back to parking.
X VALVE OPEN
CAUTION: Do not supply both packs from one single bleed.
PACK VALVE FAULT
PACK VALVE affected side ............................................................ OFF
MAX FL ..................................................................................200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
BOTH PACK VALVES FAULT
MAX FL ..................................................................................100 / MEA
z When ΔP < 1 PSI
OVBD VALVE ............................................................... FULL OPEN
MAN RATE KNOB ..........................................................9 O'CLOCK
CAB PRESS MODE SEL...........................................................MAN
MAN RATE KNOB ................................................. MAX INCREASE
RECIRC FAN FAULT
RECIRC FAN affected side ............................................................ OFF
FOLLOWING FAILURES
AIR
72
2.26A
OCT 08 001
DUCT OVHT
TEMP SEL affected side.................................................................MAN
COMPT TEMP SELECTOR affected side ....................................COLD
CAUTION: Monitor DUCT TEMP and make sure it remains positive to
avoid possible pack turbine damage due to freezing.
„ If alert persists
PACK VALVE affected side ....................................................... OFF
MAX FL .............................................................................200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
EXCESS CAB ALT
R
CABIN PRESS IND.................................................................... CHECK
„ If rapid decompression
EMERGENCY DESCENT procedure (1.07A) ....................... APPLY
„ If Z cabin > 10000 ft confirmed
MAN RATE KNOB ..........................................................9 O'CLOCK
CAB PRESS MODE SEL...........................................................MAN
MAN RATE KNOB .........................................................DECREASE
„ If unsuccessful
CREW OXYGEN MASKS............................................................ ON
CREW COMMUNICATIONS .........................................ESTABLISH
OXYGEN PAX SUPPLY ......................................................AS RQD
OXYGEN PRESSURE.......................................................... CHECK
DESCENT.................................................................AS RQD / MEA
AUTO PRESS FAULT
MAN RATE KNOB ...............................................................9 O'CLOCK
CAB PRESS MODE SEL................................................................MAN
MAN RATE KNOB ............................... AS RQD TO SET CABIN RATE
FL
140
170
200
250
TARGET
CAB ALT (ft)
0
2000
4000
6750
Note: Minimum TARGET CAB ALT is landing elevation
EXCESS CAB ΔP
MAN RATE KNOB ...............................................................9 O'CLOCK
CAB PRESS MODE SEL................................................................MAN
MAN RATE KNOB ...................................................... MAX INCREASE
„ If unsuccessful
DESCENT TO A COMPATIBLE FL....................................INITIATE
72
FOLLOWING FAILURES
AIR
2.27
APR 08 001
AVIONICS VENT EXHAUST MODE FAULT
EXHAUST MODE ........................................................................ OVBD
OVBD VALVE FAULT
CAUTION: Do not select OVBD valve FULL OPEN if ΔP > 1 PSI.
„ If engine 1 running, in flight or on ground
OVBD VALVE ............................................................. FULL CLOSE
„ If engine 1 not running, on ground
OVBD VALVE ............................................................... FULL OPEN
72
FOLLOWING FAILURES
DE/ANTI ICE
2.28
SEP 13
500
AFR AIR BLEED FAULT
R
LEAVE AND AVOID ICING CONDITIONS
AFR AIR BLEED ............................................................................. OFF
 If DE-ICING ENG FAULT light illuminates after 6 s
DE-ICING ENG affected side .................................................... OFF
AFR AIR BLEED.......................................................................... ON
AFR AIR BLEED light ....................................CHECK EXTINGUISH
 If DE-ICING ENG FAULT light does not illuminate on any side
DE-ICING AIR FRAME FAULT procedure (2.28).................. APPLY
DE-ICING AIR FRAME FAULT
DE-ICING AIR FRAME ................................................................... OFF
LEAVE AND AVOID ICING CONDITIONS
MINIMUM ICING SPEEDS ................................... INCREASE BY 10 kt
 If in icing conditions
LDG DIST .......................................................... MULTIPLY BY 1.13
Note: Refer to Part 4 to determine SPEEDS and LDG DIST
 If ice accretion
STEEP SLOPE APPROACH (4.5°)...........................PROHIBITED
DE-ICING MODE SEL FAULT
OVRD........................................................................................SELECT
MONITOR DE-ICING
 In case of engine flame out
OVRD................................................................................ RELEASE
MODE SEL AUTO FAULT
MODE SEL .....................................................................................MAN
DE-ICING and ANTI-ICING MANUAL MODE PBs:
ACCORDING TO CURRENT SAT ...........................................SELECT
Model : 212A
72
FOLLOWING FAILURES
DE/ANTI ICE
2.29
OCT 09 500
ICE DETECT FAULT
ICE ACCRETION................................................ VISUALLY MONITOR
DE-/ANTI-ICING ENG FAULT
LEAVE AND AVOID ICING CONDITIONS
ENGINE PARAMETERS affected side..................................MONITOR
ANTI-ICING PROP FAULT
LEAVE AND AVOID ICING CONDITIONS
ANTI-ICING PROP affected side.................................................... OFF
If propeller unbalance due to ice becomes excessive
CL 1 + 2 ......................... MOVE TO 100% OVRD FOR 5 MINUTES
ANTI-ICING HORNS FAULT
LEAVE AND AVOID ICING CONDITIONS
If in icing conditions, every 5 minutes
FLIGHT CONTROLS ............. CHECK FREEDOM OF MOVEMENT
R
SIDE WINDOW / WINDSHIELD HTG
FAULT
SIDE WINDOW / WINDSHIELD HTG affected side....................... OFF
PROBES HTG FAULT
If One PROBE HTG ALPHA illuminated
STICK PUSHER / SHAKER .............................................MONITOR
If Two PROBE HTG ALPHA illuminated
STICK PUSHER / SHAKER ...................................................... OFF
STICK PUSHER / SHAKER procedure (2.21)....................... APPLY
If PROBE HTG other than ALPHA illuminated
ADC non affected side....................................................SELECTED
Associated INDICATION ..................................................MONITOR
Mod : 3973 or 4371 or 4457
FOLLOWING FAILURES
AUTO PILOT
72
2.30
OCT 08 550
AILERON MISTRIM (ADU message)
– or – EXCESSIVE LATERAL TRIM REQUIRED
– or – ABNORMAL FLIGHT CHARACTERISTICS
FLIGHT CONTROLS ...............................................HOLDING FIRMLY
AP ...................................................................................DISCONNECT
Note: FLY MANUALLY PRIOR TO ADJUSTING THE LATERAL TRIMS
Note: The autopilot may be reengaged following adjustment of the lateral
trims
PITCH MISTRIM (ADU message)
FLIGHT CONTROLS ...............................................HOLDING FIRMLY
AP ...................................................................................DISCONNECT
Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS
PITCH TRIM FAIL (ADU message)
FLIGHT CONTROLS ...............................................HOLDING FIRMLY
AP ...................................................................................DISCONNECT
Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS
DADC DATA INVALID (ADU Message)
INSTRUMENTS ............................................................ CROSSCHECK
FAULTY ADC......................................................................... IDENTIFY
ADC SW............................................................... SELECT VALID ADC
„ If ADC 1 is wrong
C/B ADC 1 EMER SPLY...........................................................PULL
C/B MFC 1A AUX / ADC 1 HOT SPLY.....................................PULL
„ If ADC 2 is wrong
C/B ADC 2 ................................................................................PULL
ADC FAULT procedure (2.32) ................................................... APPLY
Mod : 3168 + 4366
72
FOLLOWING FAILURES
AND ABNORMAL
MPC
2.30A
APR 08 100
APPLICABLE TO AIRCRAFT
FITTED WITH MODIFICATION 5567 or 8392 or 8442
APM FAULT
APM ..................................................................................................OFF
For troubleshooting see FCOM 2.02.21.
DEGRADED PERF
Mainly appears in level flight after CRUISE SPEED LOW or in climb, to
inform the crew that an abnormal drag increase induces a speed
decrease or a loss of rate of climb
The most probable reason is an abnormal ice accretion
AIRFRAME DE-ICING ON......................................................... CHECK
IAS > RED BUG + 10 KT .......................................................MONITOR
AP (if engaged) ................HOLD FIRMLY CONTROL WHEEL and DISENGAGE
„ If SEVERE ICING conditions confirmed
– or –
„ If impossibility to maintain IAS > RED BUG + 10 KT in level flight
– or –
„ If abnormal aircraft handling feeling
SEVERE ICING procedure (1.09) ......................................... APPLY
„ If not
SCHEDULED FLIGHT....................................................CONTINUE
ICING CONDITIONS and SPEED....................................MONITOR
INCREASE SPEED
Appears after DEGRADED PERF to inform the crew that the drag is
abnormally high and IAS is lower than RED BUG + 10 KT
„ If abnormal conditions confirmed
IMMEDIATELY PUSH THE STICK TO INCREASE SPEED
TO RECOVER MINIMUM IAS = RED BUG + 10 KT
SEVERE ICING procedure (1.09) ......................................... APPLY
72
FOLLOWING FAILURES
AVIONICS
2.31
SEP 13
001
AUDIO SEL FAULT
AUDIO SEL affected side ............................................................. ALTN
AHRS A / ERECT FAIL
ATT / HDG PB affected side................................................. DEPRESS
 When possible
AIRCRAFT .................................... STABILIZE SPEED AND LEVEL
AHRS affected side, PUSH TO ERECT PB ......................................
.................................................DEPRESS FOR 15 SECONDS
EFIS COMP
R
 If ROL, PIT, ATT, HDG cautions appears on EFIS
BOTH EADI, STBY HORIZON ................................ CROSSCHECK
WRONG INSTRUMENT ................................................... IDENTIFY
ATT / HDG PB affected side............................................ DEPRESS
 If HDG cautions appears on EFIS
HDG/TK/GPS/ STBY COMPASS ............................ CROSSCHECK
WRONG INSTRUMENT ................................................... IDENTIFY
ATT / HDG PB affected side............................................ DEPRESS
 If AHRS 1 is wrong
C/B AHRS 1 NORM SPLY ..................................................PULL
C/B AHRS 1 AUX SPLY ......................................................PULL
 If AHRS 2 is wrong
C/B AHRS 2 NORM SPLY ..................................................PULL
C/B AHRS 2 AUX SPLY FLT...............................................PULL
Note: C/Bs deselection allows AP reconnection
 If LOC / GS / ILS caution appears on EFIS
NAV SOURCES.................................................................... CHECK
VOR / ILS PB affected side .............................. DEPRESS AS RQD
ADC SW FAULT
ADC SW........................................................ SET TO OPPOSITE ADC
72
FOLLOWING FAILURES
AVIONICS
2.32
APR 08 550
ADU FAILURE
IAS / VS MODE....................................................................... USE TCS
Note: ALT SEL mode is lost
„ If amber "AP MSG" appears on EADI or
„ If in composite mode
FLIGHT CONTROLS ................................................ HOLD FIRMLY
AP ..............................................................................DISCONNECT
ADC FAULT
VALID ADC ...............................................................................SELECT
PF.............................................................................. NON affected side
AP COUPLING ......................................................... NON affected side
ATC .................................................................NON affected equipment
„ If ADC 1 is lost
LANDING ELEVATION ...................... PRESSURE ALTITUDE SET
GPWS ........................................................................................ OFF
„ If ADC 1 + 2 are lost
STBY INST ................................................................................ USE
MAN RATE KNOB ..........................................................9 O'CLOCK
CAB PRESS MODE SEL...........................................................MAN
ENGINE PARAMETERS ..................................................MONITOR
TCAS (if installed).................................................................... STBY
GPWS ........................................................................................ OFF
TLU ................................................................................MAN MODE
TLU FAULT procedure (2.22A) ............................................. APPLY
Note: If both ADC are lost, De-/Anti-Icing AUTO Mode Selection is lost.
AHRS FAIL
ATT / HDG PB affected side................................................. DEPRESS
Periodically compare remaining AHRS outputs to STBY INST
SGU FAIL
EFIS SG PB affected side .................................................... DEPRESS
CRT FAIL
CRT affected................................................................................... OFF
Mod : 5205
Model : 212A
72
FOLLOWING FAILURES
MISCELLANEOUS
2.32A
OCT 09 200
COCKPIT DOOR CONTROL PANEL FAULT
(if installed)
COCKPIT DOOR MANUAL LOCK BOLT(S) ..........................................
............................................................... MOVE TO CLOSE POSITION
Note: when the door is locked with the manual bolt(s), the emergency
access to the cockpit is unavailable. It is recommended that at
least two crewmembers remain in the cockpit during that time.
VOLCANIC ASH ENCOUNTER
FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180°
TURN AND STARTING DESCENT (IF MSA PERMITS)
ATC ........................................................................................... NOTIFY
PL 1 + 2 (If conditions permit) ..................................................RETARD
SPEED BUG TO VmHB...................................................................SET
HDG MODE ........................................................................HIGH BANK
CREW OXY MASKS ............................................................. ON / 100%
CABIN CREW ........................................................................... NOTIFY
PASSENGER OXYGEN ...........................................................AS RQD
AIR FLOW ......................................................................................HIGH
ENG PARAMETERS .............................................................MONITOR
AIRSPEED INDICATORS......................................................MONITOR
Note: Reducing TQ reduces ash ingestion, maximizes engine surge
margin and lowers engine turbine temperature. Monitor particularly ITT;
it may become necessary to set PL to Flight Idle, if conditions permit.
Note: In extreme case, it may be necessary to consider precautionary
engine shut down and engine restart in flight. If both engines flame out,
refer to BOTH ENGINE FLAME OUT procedure (1.03)
Note: Volcanic ash may clog the pitot probes resulting in unreliable
speed indications. If airspeed is unreliable or lost, adjust airplane
attitude and torque.
Mod: 4111
72
FOLLOWING FAILURES
MISCELLANEOUS
2.33
SEP 10
001
LOSS OF RADIO ALTIMETER INFORMATION
GPWS ............................................................................................. OFF
TCAS (if installed) ......................................................................... STBY
CAUTION: LDG GEAR NOT DOWN undue warning may be
generated when reducing PL; this alarm may be
cancelled by using EMER AUDIO CANCEL.
R
SMK DET FANS FAULT
FAN............................................................................................... ALTN
DOORS UNLK IN FLIGHT
 If any door except FWD COMPT
SIGNS.......................................................................................... ON
ASSOCIATED DOOR.........................................VISUALLY CHECK
 If unlocked or check not feasible
LANDING ELEVATION .....................................................9000 ft
MAX FL........................................................................100 / MEA
 If FWD COMPT
NO ACTION
COCKPIT WINDOW CRACKED
WINDOW HEAT affected................................................................ OFF
LANDING ELEVATION................................................................9000 ft
MAX FL ..................................................................................100 / MEA
OXYGEN LO PR
OXY MAIN SUPPLY ...................................................... OFF THEN ON
 If OXYGEN LO PR light remains illuminated
MAIN SUPPLY........................................................................... OFF
OXYGEN PORTABLE UNIT.......... INSTALL IN COCKPIT AS RQD
72
FOLLOWING FAILURES
MFC
2.34
OCT 08 001
MFC 1A FAULT
R
R
MODULE 1A .................................................................... OFF / RESET
MFC 1A MODULE LOST EQUIPMENT LIST............................ CHECK
R
MFC 1A MODULE LOST EQUIPMENT LIST
MECHANIC CALL IND
DC BUS 1 OFF WARNING
AC BUS 1 SPLY
INV 1 FAULT LIGHT
LDG GEAR PRIMARY UNLK IND
BLEED HP VALVE 1
FWD COMPT DOOR UNLK IND
EMER HATCH UNLK IND
RIGHT AFT DOOR UNLK IND, if
applicable
MFC 1B FAULT
R
R
MODULE 1B .................................................................... OFF / RESET
MFC 1B MODULE LOST EQUIPMENT LIST............................ CHECK
„ If failure during take off
PACK 1 ...................................................................................... OFF
OVBD VALVE ............................................................... FULL OPEN
z Prior take off
PACK 2 ................................................................................. OFF
z After take off
PACKS.................................................................................... ON
OVBD VALVE ........................................................ FULL CLOSE
LDG GEAR ......LEAVE DOWN FOR COOLING FOR 1 MINUTE
..........AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY
z After landing
PACK 1 ...................................................................................... OFF
OVBD VALVE ............................................................... FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 1B MODULE LOST EQUIPMENT LIST
GROUND FAN 1
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTO
FUNCTIONING
CVR ERASE
DC STBY BUS UNDV DETECT
INV 1 FAULT LIGHT
GREEN PUMP LO PR IND
BRAKE OVERTEMP ALERTS LH / RH
BLEED VALVE 1 FAULT IND
72
FOLLOWING FAILURES
MFC
2.35
OCT 08 001
MFC 2A FAULT
R
R
R
MODULE 2A .................................................................... OFF / RESET
AVIONICS VENT EXHAUST MODE ........................................... OVBD
MFC 2A MODULE LOST EQUIPMENT LIST............................ CHECK
„ If failure during taxi out
OVBD VALVE ............................................................... FULL OPEN
z After take off
IDLE GATE ...................................................................... CHECK
OVBD VALVE .....................................................................AUTO
z At touch down
IDLE GATE .......................................................................MONITOR
z After landing
OVBD VALVE ............................................................... FULL OPEN
MFC 2A MODULE LOST EQUIPMENT LIST
AIR X VALVE
OVBD VALVE AUTO FUNCTIONING
EXTRACT FAN
HOSTESS CALL IND
CREW CALL IND
DC BUS 2 OFF WARNING
AC BUS 2 SPLY
INV 2 FAULT LIGHT
RH SIDE WINDOW ANTI-ICING
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
BLEED HP VALVE 2
LEFT DOORS UNLK IND
IDLE GATE AMBER WARNING
MFC 2B FAULT
R
R
MODULE 2B .................................................................... OFF / RESET
MFC 2B MODULE LOST EQUIPMENT LIST............................ CHECK
„ Failure during take off
PACK 2 ...................................................................................... OFF
OVBD VALVE ............................................................... FULL OPEN
z Prior take off
PACK 1 ................................................................................. OFF
z After take off
PACK 1 + 2............................................................................. ON
OVBD VALVE ........................................................ FULL CLOSE
LDG GEAR ......LEAVE DOWN FOR COOLING FOR 1 MINUTE
..........AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY
z After landing
PACK 2 ...................................................................................... OFF
OVBD VALVE ............................................................... FULL OPEN
CAUTION: Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 2B MODULE LOST EQUIPMENT LIST
GROUND FAN 2
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTO FUNCTIONING
INV 2 FAULT LIGHT
RH SIDE WINDOW ANTI-ICING and
associated FAULT IND
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
RH BRAKE OVERTEMP ALERTS
BLEED VALVE 2 FAULT IND
72
FOLLOWING FAILURES
MFC
2.36
OCT 08 001
MFC 1A+1B FAULT
R
R
MODULES 1A+1B ........................................................... OFF / RESET
PROP 1 ANTI-ICING ...................................................................... OFF
PROP ANTI-ICING FAULT procedure (2.29) ............................. APPLY
DE-ICING MODE SEL .................................................. OVRD AS RQD
PACK 1 ........................................................................................... OFF
BLEED 1 ......................................................................................... OFF
BLEED VALVE FAULT procedure (2.26) ................................... APPLY
RADAR ........................................................................................... OFF
GPWS ............................................................................................. OFF
MFC 1A+1B MODULES LOST EQUIPMENT LIST................... CHECK
z Before landing
ATPCS ....................................................................................... OFF
z After landing
OVBD VALVE ............................................................... FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 1A+1B MODULES LOST EQUIPMENT LIST
PACK 1 / PACK 1 FAULT IND
GROUND FAN 1
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTOFUNCTIONING
MECHANIC CALL IND
CVR ERASE
DC STBY BUS UNDV DETECT
DC BUS 1 OFF WARNING
AC BUS 1 SPLY
INV 1 FAULT LIGHT
LEFT PFTS
STICK PUSHER
TRIPLE TRIM IND
GREEN PUMP LO PR INDICATION
ANTI-ICING PROP 1 and associated
FAULT IND
DE-ICING AIRFRAME (BOOTS A)
DE-ICING AIRFRAME (BOOTS B)
LH SIDE WINDOW ANTI-ICING and
associated FAULT IND
PRIMARY UNLK IND
PRIMARY GREEN ARROWS
BRAKE OVERTEMP ALERTS LH / RH
BLEED HP VALVE 1
BLEED VALVE 1 and associated
FAULT IND
FWD COMPT DOOR UNLK IND
EMER HATCH UNLK IND
RIGHT AFT DOOR UNLK IND, if
applicable
ENG 1 UPTRIM
ENG 1 AUTO FEATHER
LEFT AUTO CL
72
FOLLOWING FAILURES
MFC
2.37
OCT 08 001
MFC 1A+2A FAULT
R
R
R
MODULES 1A+2A ........................................................... OFF / RESET
TLU .....................................................................................MAN MODE
AVIONICS VENT EXHAUST MODE ........................................... OVBD
RADAR ........................................................................................... OFF
GPWS ............................................................................................. OFF
MFC 1A+2A MODULES EQUIPMENT LIST ............................. CHECK
Note : Airframe FAULT amber alert is lost.
Note : When airframe de-icing is used, monitor boots inflation.
Note : As AP OFF alert is lost, use of AP below 1000 ft AGL is prohibited.
Note : VOR 2, ADF 2, CRS 2 information are lost. ADC 2 outputs are not
available.
 Before landing
LDG GEAR LEVER ............................................................... DOWN
EMER EXTENSION HANDLE ..................................................PULL
CAUTION : LDG GEAR cannot be retracted.
 At touch down
IDLE GATE .......................................................................MONITOR
 After landing
OVBD VALVE ................................................................FULL OPEN
R
MFC 1A+2A MODULES LOST EQUIPMENT LIST
AIR X VALVE
OVBD VALVE AUTOFUNCTIONING
EXTRACT FAN
AP OFF WARNING LIGHT
ALTITUDE ALERT LIGHT
GUIDANCE LIGHT
MECHANIC CALL IND
HOSTESS CALL IND
CREW CALL IND
RECORDERS (START/STOP)
DC BUS 1 + 2 OFF WARNING
AC BUS 1 + 2 SPLY
INV 1 + 2 FAULT LIGHT
EMER BAT CHG CTL
FLAPS UNLK WARNING
STICK PUSHER / SHAKER FAULT
Releasable Centering Unit AUTO
DISCONNECT after YAW TRIM
action or YD engagement
TLU FAULT LIGHT
TRIPLE TRIM IND
AIL LOCK LIGHT (if installed)
DE-ICING AIRFRAME FAULT
RH SIDE WINDOW ANTI-ICING
CCAS WARNING ALERT (FLAP
UNLK)
LDG GEAR CONTROL
LDG GEAR PRIMARY UNLK IND
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
LIGHT TEST
BLEED HP VALVE 1 + 2
LEFT DOORS UNLK IND
FWD COMPT DOOR UNLK IND
EMER HATCH UNLK IND
RIGHT AFT DOOR UNLK IND, if
applicable
RIGHT FWD DOOR UNLK IND
IDLE GATE and associated AMBER
WARNING
72
FOLLOWING FAILURES
MFC
2.38
OCT 08 001
MFC 1A+2B FAULT
R
R
R
MODULES 1A+2B ........................................................... OFF / RESET
MAIN BLUE HYD PUMP................................................................. OFF
HYD X FEED .................................................................................... ON
DE-ICING MODE SEL .................................................. OVRD AS RQD
MFC 1A+2B MODULES EQUIPMENT LIST ............................. CHECK
Note : AP does not disconnect after STBY PITCH TRIM activation.
 Before landing
Note : Flaps control is lost.
REDUCED FLAPS LANDING procedure (2.21).................... APPLY
LDG GEAR LEVER ............................................................... DOWN
EMER EXTENSION HANDLE ..................................................PULL
CAUTION : LDG GEAR cannot be retracted.
 After landing
PACK 2 ...................................................................................... OFF
OVBD VALVE ................................................................FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 1A+2B MODULES LOST EQUIPMENT LIST
GROUND FAN 2
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTOFUNCTIONING
MECHANIC CALL IND
DC BUS 1 OFF WARNING
AC BUS 1 SPLY
INV 1 + 2 FAULT LIGHT
FLAPS CONTROL
BLUE HYD PUMP CTL
DE-/ANTI-ICING ENG 1
DE-/ANTI-ICING ENG 2 FAULT
RH SIDE WINDOW ANTI-ICING and
associated FAULT IND
LDG GEAR CONTROL
LDG GEAR PRIMARY UNLK IND
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
BRAKE OVERTEMP ALERT RH
BLEED HP VALVE 1
BLEED VALVE 2 FAULT IND
FWD COMPT DOOR UNLK IND
EMER HATCH UNLK IND
RIGHT AFT DOOR UNLK IND, if
applicable
72
FOLLOWING FAILURES
MFC
2.39
OCT 08 001
MFC 1B+2A FAULT
R
R
R
MODULES 1B+2A ........................................................... OFF / RESET
DE-ICING MODE SEL .................................................. OVRD AS RQD
AVIONICS VENT EXHAUST MODE ........................................... OVBD
MFC 1B+2A MODULES EQUIPMENT LIST ............................. CHECK
Note : VOR 2, ADF 2, CRS 2 information are lost. CM2 IAS is not
available.
 Before landing
Note : Flaps control is lost.
REDUCED FLAPS LANDING procedure (2.21).................... APPLY
LDG GEAR LEVER ............................................................... DOWN
EMER EXTENSION HANDLE ..................................................PULL
CAUTION : LDG GEAR cannot be retracted.
 At touch down
IDLE GATE .......................................................................MONITOR
 After landing
PACK 1 ...................................................................................... OFF
OVBD VALVE ................................................................FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 1B+2A MODULES LOST EQUIPMENT LIST
GROUND FAN 1
AIR X VALVE
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTOFUNCTIONING
EXTRACT FAN
HOSTESS CALL IND
CREW CALL IND
CVR ERASE
DC STBY BUS UNDV DETECT
DC BUS 2 OFF WARNING
AC BUS 2 SPLY
INV 1 FAULT LIGHT
INV 2 FAULT LIGHT
FLAPS CONTROL
GREEN PUMP LO PR INDICATION
DE-/ANTI-ICING ENG 1 FAULT
DE-/ANTI-ICING ENG 2
RH SIDE WINDOW ANTI-ICING
LDG GEAR CONTROL
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
BRAKE OVERTEMP ALERTS LH / RH
BLEED HP VALVE 2
BLEED VALVE 1 FAULT IND
LEFT DOORS UNLK IND
IDLE GATE AMBER WARNING
72
FOLLOWING FAILURES
MFC
2.40
OCT 08 001
MFC 2A+2B FAULT
R
R
MODULES 2A+2B ........................................................... OFF / RESET
AVIONICS VENT EXHAUST MODE ........................................... OVBD
ANTI-ICING PROP 2 ...................................................................... OFF
ANTI-ICING PROP FAULT procedure (2.29) ............................. APPLY
DE-ICING MODE SEL .................................................. OVRD AS RQD
PACK 2 ........................................................................................... OFF
BLEED 2 ......................................................................................... OFF
BLEED VALVE FAULT procedure (2.26) ................................... APPLY
MFC 2A+2B MODULES EQUIPMENT LIST ............................. CHECK
z Before landing
ATPCS ....................................................................................... OFF
z At touch down
IDLE GATE .......................................................................MONITOR
z After landing
OVBD VALVE ............................................................... FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 2A+2B MODULES LOST EQUIPMENT LIST
PACK 2
PACK 2 FAULT IND
GROUND FAN 2
AIR X VALVE
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTOFUNCTIONING
EXTRACT FAN
HOSTESS CALL IND
CREW CALL IND
DC BUS 2 OFF WARNING
AC BUS 2 SPLY
INV 2 FAULT LIGHT
STICK PUSHER
ANTI-ICING PROP 2
ANTI-ICING PROP 2 FAULT
DE-ICING AIRFRAME (BOOTS B)
RH SIDE WINDOW ANTI-ICING and
associated FAULT IND
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
BRAKE OVERTEMP ALERT RH
BLEED HP VALVE 2
BLEED VALVE 2
BLEED VALVE 2 FAULT IND
LEFT DOORS UNLK IND
ENG 2 UPTRIM
ENG 2 AUTO FEATHER
PROP BRAKE BRAKING if applicable
PROP BRAKE RELEASING if
applicable
IDLE GATE AMBER WARNING
RIGHT AUTO CL
72
FOLLOWING FAILURES
MFC
2.41
OCT 08 001
MFC 1B+2B FAULT
R
R
MODULES 1B+2B ........................................................... OFF / RESET
OVERHEAD PANEL ..............................................................MONITOR
MFC 1B+2B MODULES EQUIPMENT LIST ............................. CHECK
z Before landing
NOSE WHEEL STEERING ....................................................... OFF
ANTI-SKID ................................................................................. OFF
ANTI-SKID FAULT procedure (2.25)..................................... APPLY
LDG GEAR LEVER ............................................................... DOWN
EMER EXTENSION HANDLE..................................................PULL
CAUTION : LDG GEAR cannot be retracted.
z At touch down
IDLE GATE ...............................................................................PULL
DIFFERENTIAL BRAKING ........................................................ USE
z After landing
PACK 1 + 2 ................................................................................ OFF
ANTI-ICING HORNS ................................................................. OFF
PROBES HTG ........................................................................... OFF
OVBD VALVE ............................................................... FULL OPEN
Note : ATPCS ARM light is not available. Autofeather light is lost.
Note : External power cannot be used.
CAUTION : Before opening any door, PACKS 1 and 2 must be selected
OFF and cockpit communication hatch must be open.
R
MFC 1B+2B MODULES LOST EQUIPMENT LIST
GROUND FAN 1
GROUND FAN 2
AIR X VALVE
OUTFLOW VALVE OPENING AFTER
LANDING
OVBD VALVE AUTOFUNCTIONING
CVR ERASE
DC STBY BUS UNDV DETECT
INV 1 FAULT LIGHT
INV 2 FAULT LIGHT
MAIN BAT CHG CTL
BAT DISCHARGE IN FLIGHT
FLAPS ASYMMETRY DETECTION
STICK PUSHER INHIBITION
STICK SHAKER
STALL WARNING
PITCH TRIM WHOOLER
PITCH TRIM ASYMWARNING
AIL LOCK LIGHT if applicable
GREEN PUMP LO PR INDICATION
RH SIDE WINDOW ANTI-ICING and
associated FAULT IND
INHIBITION OF HORNS ANTI-ICING
ON GROUND
CCAS MASTER WARNING
CCAS MASTER CAUTION
CCAS AURAL ALERTS
CCAS AMBER ALERTS ON CAP
CCAS WARNING ALERTS (CONFIG,
PROP BRK, ENG OIL)
LDG GEAR CONTROL
LDG GEAR Secondary UNLK IND
LDG GEAR Secondary GREEN
ARROWS
BRAKE OVERTEMP ALERTS LH / RH
LDG GEAR LEVER LOCKED DOWN
ON GROUND
NOSE WHEEL STEERING
ANTI-SKID
"LANDING GEAR NOT DOWN"
WARNING
BLEED VALVE 1 FAULT IND
BLEED VALVE 2 FAULT IND
ARM LIGHT IND
PROP BRAKE RED UNLK LT if
applicable
LEFT and RIGHT AUTO CL
72
FOLLOWING FAILURES
ELEC
DC EMER BUS
LOST EQUIPMENT LIST
AIR CONDITIONING
OVBD and Underfloor Valves CTL
OVBD and Underfloor Valves IND
AIR COOLING high flow IND
PRESS IND / EXCESS ALT IND
Pneumatic Outflow Valves
FWD COMPT Ventilation Valve (*)
AUTO PILOT
AP/FD Computer
GUIDANCE IND
COMMUNICATIONS
VHF / RCAU
CM2 Cockpit Amplifier
ELECTRICAL POWER
AC BUS OFF 1 + 2 IND
ACW BUS OFF 1 + 2 IND
INV 1 FAULT IND
DC BUS OFF 1 + 2 IND
DC STBY BUS IND (UNDV/OVRD)
EMER BAT CHG IND
FIRE PROTECTION
FIRE HANDLE IND ENG 1 + 2
FIRE DETECTION ENG 1 + 2
FLIGHT CONTROLS
PITCH TRIM NORMAL COMMAND
RUDDER TRIM
AILERON TRIM
HYDRAULIC POWER
BLUE PUMP CTL and IND
GREEN PUMP IND
ICE AND RAIN PROTECTION
AAS CTL, IND and ALERTS
WING, EMPENNAGE BOOTS A
ENG 1 BOOTS A and B
PROP 1 + 2 ANTI-ICING CTL
PROP 1 + 2 ANTI-ICING IND
HORNS ANTI-ICING IND and CTL
INDICATING / RECORDING
CM1 CLOCK
FDAU on ground
LANDING GEAR
ANTI-SKID Outboard
NOSE WHEEL STEERING
WOW 1 CTL
LIGHTS
CM1 PANELS
PYLON
STBY COMPASS
LAVATORY (EMER)
NAVIGATION
ATC 1
PROPELLERS
A/F AUX PUMPS CTL
TQ IND 1 + 2
ENGINES
CL FIRE IND 1 + 2
(*): if applicable
Mod : 4116 + 4366
2.42
APR 08 150
DC ESS BUS
LOST EQUIPMENT LIST
AIR CONDITIONING
PACK and RECIRC FAN 1 + 2 IND
PACK 1 + 2 Valve
EXTRACT FAN CTL
Landing Elevation IND
Cockpit and Cabin Automatic and
Manual TEMP CTL and IND
AUTO PILOT
AP OFF IND and DISC by Quick
Disconnect
COMMUNICATIONS
CM1+2 Flight Interphones
CM1+2 Audio Control Panels
CM1 Cockpit Amplifier
CVR / Passenger Address
Mechanical CALL
Cockpit and Cabin Crew CALL
ELECTRICAL POWER
DC SVCE/UTLY BUS 1 + 2 CTL
MAIN BAT CHG IND
INV 2 FAULT IND
FIRE PROTECTION
Avionics / Toilets SMK DET
FWD and AFT COMPT SMK DET
AFT COMPT and FWD COMPT
/Toilets DET FANS CTL and IND
FWD COMPT Fire Extinguishing
CTL, IND and TEST (*)
AUX AFT COMPT (*)
See 2.42A for Cargo Operations
FLIGHT CONTROLS
Clutch Reengagement System (*)
AILERON Locking CTL
FUEL
FQI 1 + 2
X FEED Valve
Starting Pumps 1 + 2
Motive Flow Valves 1 + 2
HYDRAULIC
GREEN PUMP CTL
ICE AND RAIN PROTECTION
DE-ICING ISOL Valves
Side Windows ANTI-ICING IND
CAPT/STBY/TAT PROBES IND
CM1 Wiper
INDICATING / RECORDING
FDAU in flight
LIGHTS
Landing CTL
NAVIGATION
TAS TEMP IND
OXYGEN
PRESS IND
Pilots and Pax Valves CTL
Pax Masks DROP CTL
PNEUMATIC
BLEED Valves PWR and IND 1 + 2
PROPELLERS
NP IND 1 + 2
PROP BRK PWR, CTL and IND
ENGINES
IGNITION and STARTING 1 + 2
NH/NL, ITT IND 1 + 2
NORMAL PROCEDURES
72
3.01
NOV 11 001
3 - NORMAL PROCEDURES
All steps have to be performed before the first flight of the day or
following a crew change or maintenance action. In other cases, start at
FINAL COCKPIT PREPARATION.
With the USE OF GPU (DC)
(Refer to page 3.04 to 3.06 for HOTEL MODE)
EXTERIOR INSPECTION
CM1
CM2
Exterior walk around performed
PRELIMINARY COCKPIT PREPARATION (On GPU)
CM1
CM2
EMER EQPT...............................CHECK
GEAR PINS & COVERS ...... ON BOARD
C/Bs ............................................CHECK
PL 1 + 2 .............................................. GI
GUST LOCK ............................ ENGAGE
CL 1 + 2 ................................... FUEL SO
FLAPS LEVER............................CHECK
LDG GEAR ..................................DOWN
EEC 1+2.............................................ON
WIPERS ................................... ……OFF
STBY HORIZON ERECT……….…PULL
BAT....................................................ON
MFC AUTO TEST.......................CHECK
EMER & BUS SUPPL IND ……..CHECK
UNDV LT……………………….....CHECK
DC EXT PWR P/B..............................ON
ANN LT………………………………TEST
OVERHEAD PANEL
DOME LT………………………AS RQRD
STBY COMPASS LT.........CHECK&OFF
STORM LT…………………CHECK&OFF
CALL & SELCAL(If installed) LT…...OFF
MIN CAB LT…………………………..OFF
FUEL PUMPS & XFEED………..…TEST
DOORS .…………………………….TEST
SPOILERS LTs…………………........OFF
LDG GEAR IND…3 GREEN/NO RED LT
TLU ..………………………………..AUTO
SELCAL (If installed)…….CHECK CODE
ENG 1 FIRE ................................... TEST
EXT LT…….…………………...AS RQRD
PROP BRK…................... ON / LOCKED
ENG START….......OFF/START ABORT
MAIN ELEC PWR…..……………CHECK
CVR & DFDR................................. TEST
SIGNS ........................................CHECK
EMER EXIT LT ............................... ARM
DE / ANTI ICING LT…..EXTINGUISHED
PROBES HTG ……………………....OFF
WINDSHIELD HTG…………………..ON
AC WILD ELEC PWR……………CHECK
HYD PWR………………………...CHECK
EMER LOC XMTR........................ AUTO
NORMAL PROCEDURES
72
3.02
NOV 11 100
PRELIMINARY COCKPIT PREPARATION (On GPU)
(CONT'D)
CM1
CM2
ANN LT SW………………… .AS RQRD
AIR BLEED / COMPT TEMP…...CHECK
AVIONICS VENT ……………..…CHECK
OVBD VALVE ............................... AUTO
OXYGEN PRESS .......................CHECK
OXYGEN MAIN SUPPLY…………….ON
PAX SUPPLY…………………NO LIGHT
COMPT SMK ................................ TEST
EXHAUST MODE ....................... RESET
ENG 2 FIRE…………………………TEST
PEDESTAL
ATPCS.......... ……………………….TEST
TCAS ……...………...……..STBY / TEST
TRIMS .......................................CHECK
(A full test has to be perform for the first
flight of the day)
STBY PITCH TRIM……………...CHECK
STBY PITCH TRIM…….GUARDED/OFF
RCDR…CHECK DATA FDEP or MCDU
COM / ADF …………...……….ON /TEST
XPDR (ATC)……………… STBY / TEST
IDLE GATE .................................CHECK
EMER AUDIO CANCEL .............CHECK
PARKING BRK………………………...ON
GUST LOCK…………………………...ON
AIL LOCK LT…………. EXTINGUISHED
EFIS CTRL PANEL ............... TEST/SET
RADAR .......................................... STBY
COCKPIT DOOR LK SYS…...….CHECK
CENTRAL PANEL
FUEL QUANTITY ………TEST / CHECK
ICE DETECT PANEL…..TEST / CHECK
CAP………………………………..CLEAR
PEC 1 + 2 ..........................................ON
BOOST (if installed) ……...…..…CHECK
(A full test has to be perform daily)
PWR MGT ......................................... TO
STBY INSTR…………CHECK NO FLAG
ENG FUEL USED……………..…RESET
ENG INSTR & PANEL ………….CHECK
MEMO PANEL ……………...…...CHECK
CAB PRESS MODE SEL............. NORM
AUTO PRESS………...…TEST / CHECK
CAB PRESS IND ………...……...CHECK
STICK PUSHER…..……………..CHECK
RUD TLU ………LO SPD ILLUMINATED
FLAPS IND ……………...……….CHECK
FLAPS ASYM LT……...EXTINGUISHED
PITCH TRIM ASYM LT.EXTINGUISHED
BRK TEMP HOT LT…..EXTINGUISHED
ANTI SKID…….DEPRESSED IN/NO LT
HYD GAUGES……………………CHECK
Mod: 3973 or 4371 or 4457
NORMAL PROCEDURES
72
3.03
NOV 11 100
PRELIMINARY COCKPIT PREPARATION (On GPU)
(CONT'D)
CM1
CM2
GLARESHIELD
FD BARS………………………BOTH ON
VOR/ILS 1&2…………………..TEST/ON
ADU BRT......................................... SET
LEFT LATERAL CONSOLE
COCKPIT COM HATCH…………..OPEN
STICK PUSHER/SHAKER(once a day)…..
………………………………………..TEST
WARN ROT SEL…………….NORM FLT
N/W STEERING………...GUARDED/ON
OXYGEN MASK (once a day) ....... CHECK
RIGHT LATERAL CONSOLE
EXTR AIRFLOW........OPEN/ GUARDED
OXYGEN MASK (once a day) ........CHECK
LEFT SWITCHING PANEL
MKR …………………………………….LO
AUDIO 1SEL .......................... ..CHECK
AHRS1 ……………………………CHECK
CAPT SWITCHING PANEL….....CHECK
EGPWS / TAWS........GUARDED/NORM
TERR…………………GUARDED/NO LT
STEEP APP(if installed)…………CHECK
LEFT SWITCHING PANEL
F/O SWITCHING PANEL……….CHECK
AUDIO 2 SEL..............................CHECK
AHRS 2 …………………………..CHECK
LEFT INSTRUMENT PANEL
CLOCK TIME ................. ……………SET
AIRSPEED…............CHECK / NO FLAG
RMI / EHSI …………...…X CHECK HDG
EADI…………………………CHECK ATT
EGPWS TEST …………….…PERFORM
GPWS G/S P/B……..CHECK NO LIGHT
ALTIMETER.............CHECK / NO FLAG
VSI…………………………………CHECK
TAT/SAT IND……………………..CHECK
ADC SWITCH……………………….1 or 2
DSP SEL………………………….CHECK
RIGHT INSTRUMENT PANEL
APM TEST……………………PERFORM
GPWS G/S P/B……..CHECK NO LIGHT
ALTIMETER.............CHECK / NO FLAG
VSI…………………………………CHECK
DSP SEL………………………….CHECK
RMI / EHSI …………...…X CHECK HDG
EADI…………………………CHECK ATT
AIRSPEED…............CHECK / NO FLAG
CLOCK TIME................. ……………SET
Mod: 3973 or 4371 or 4457
NORMAL PROCEDURES
72
3.04
NOV 11 001
3 - NORMAL PROCEDURES
All steps have to be performed before the first flight of the day or
following a crew change or maintenance action. In other cases, start at
FINAL COCKPIT PREPARATION.
With the USE of HOTEL MODE
(Refer to page 3.01 to 3.03 for EXTERIOR INSPECTION and for GPU)
PRELIMINARY COCKPIT PREPARATION (Hotel mode)
CM1
CM2
EMER EQPT...............................CHECK
GEAR PINS & COVERS ...... ON BOARD
C/Bs ............................................CHECK
PL 1 + 2 .............................................. GI
GUST LOCK ............................ ENGAGE
CL 1 + 2 ................................... FUEL SO
FLAPS LEVER............................CHECK
LDG GEAR ..................................DOWN
EEC 1+2.............................................ON
WIPERS ................................... ……OFF
STBY HORIZON ERECT……….…PULL
BAT....................................................ON
MFC AUTO TEST.......................CHECK
EMER & BUS SUPPL IND ……..CHECK
UNDV LT……………………….....CHECK
ENG 2 FIRE ……………………….. TEST
ATPCS TEST…………...…....PERFORM
SERVICE DOOR ………...…….CLOSED
FUEL PUMP 2…………………………ON
WING LT………………………………..ON
PROP BRK………………....ON/LOCKED
ENG 2 …….....START IN HOTEL MODE
ANN LIGHT.................................... TEST
OVERHEAD PANEL
DOME LT………………………AS RQRD
STBY COMPASS LT.........CHECK&OFF
STORM LT…………………CHECK&OFF
CALL & SELCAL(If installed) LT…...OFF
MIN CAB LT…………………………..OFF
FUEL PUMPS & XFEED………..…TEST
DOORS .…………………………….TEST
SPOILERS LTs…………………........OFF
LDG GEAR IND…3 GREEN/NO RED LT
TLU ..………………………………..AUTO
SELCAL (If installed)…….CHECK CODE
ENG 1 FIRE ................................... TEST
EXT LT…….…………………...AS RQRD
PROP BRK…................... ON / LOCKED
ENG START….......OFF/START ABORT
MAIN ELEC PWR…..……………CHECK
CVR & DFDR................................. TEST
SIGNS ........................................CHECK
EMER EXIT LT ............................... ARM
DE / ANTI ICING LT…..EXTINGUISHED
PROBES HTG ……………………....OFF
WINDSHIELD HTG…………………..ON
AC WILD ELEC PWR……………CHECK
HYD PWR………………………...CHECK
EMER LOC XMTR........................ AUTO
NORMAL PROCEDURES
72
3.05
NOV 11 100
PRELIMINARY COCKPIT PREPARATION (Hotel mode)
(CONT'D)
CM1
CM2
ANN LT SW………………… .AS RQRD
AIR BLEED / COMPT TEMP…...CHECK
AVIONICS VENT ……………..…CHECK
OVBD VALVE ............................... AUTO
OXYGEN PRESS .......................CHECK
OXYGEN MAIN SUPPLY…………….ON
PAX SUPPLY…………………NO LIGHT
COMPT SMK ................................ TEST
EXHAUST MODE ....................... RESET
PEDESTAL
TCAS ……...………...……..STBY / TEST
TRIMS…………………………….CHECK
(A full test has to be perform for the first
flight of the day)
STBY PITCH TRIM……………...CHECK
STBY PITCH TRIM…….GUARDED/OFF
RCDR…CHECK DATA FDEP or MCDU
COM / ADF …………...……….ON /TEST
XPDR (ATC)……………… STBY / TEST
IDLE GATE .................................CHECK
EMER AUDIO CANCEL .............CHECK
PARKING BRK………………………...ON
GUST LOCK…………………………...ON
AIL LOCK LT…………. EXTINGUISHED
EFIS CTRL PANEL ............... TEST/SET
RADAR .......................................... STBY
COCKPIT DOOR LK SYS…...….CHECK
CENTRAL PANEL
FUEL QUANTITY ………TEST / CHECK
ICE DETECT PANEL…..TEST / CHECK
CAP………………………………..CLEAR
PEC 1 + 2 ..........................................ON
BOOST (if installed) ……...…..…CHECK
(A full test has to be perform daily)
PWR MGT ......................................... TO
STBY INSTR…………CHECK NO FLAG
ENG FUEL USED……………..…RESET
ENG INSTR & PANEL ………….CHECK
MEMO PANEL ……………...…...CHECK
CAB PRESS MODE SEL............. NORM
AUTO PRESS………...…TEST / CHECK
CAB PRESS IND ………...……...CHECK
STICK PUSHER…..……………..CHECK
RUD TLU ………LO SPD ILLUMINATED
FLAPS IND ……………...……….CHECK
FLAPS ASYM LT……...EXTINGUISHED
PITCH TRIM ASYM LT.EXTINGUISHED
BRK TEMP HOT LT…..EXTINGUISHED
ANTI SKID…….DEPRESSED IN/NO LT
HYD GAUGES……………………CHECK
R
Mod: 3973 or 4371 or 4457
NORMAL PROCEDURES
72
3.06
NOV 11 100
PRELIMINARY COCKPIT PREPARATION (Hotel mode)
(CONT'D)
CM1
CM2
GLARESHIELD
FD BARS………………………BOTH ON
VOR/ILS 1&2…………………..TEST/ON
ADU BRT ......................................... SET
LEFT LATERAL CONSOLE
COCKPIT COM HATCH…………..OPEN
STICK PUSHER/SHAKER(once a day)…..
………………………………………..TEST
WARN ROT SEL…………….NORM FLT
N/W STEERING………...GUARDED/ON
OXYGEN MASK (once a day) ....... CHECK
RIGHT LATERAL CONSOLE
EXTR AIRFLOW........OPEN/ GUARDED
OXYGEN MASK (once a day) ........CHECK
LEFT SWITCHING PANEL
MKR …………………………………….LO
AUDIO 1SEL .......................... ..CHECK
AHRS1 ……………………………CHECK
CAPT SWITCHING PANEL….....CHECK
EGPWS / TAWS........GUARDED/NORM
TERR…………………GUARDED/NO LT
STEEP APP(if installed)…………CHECK
LEFT SWITCHING PANEL
F/O SWITCHING PANEL……….CHECK
AUDIO 2 SEL..............................CHECK
AHRS 2 …………………………..CHECK
LEFT INSTRUMENT PANEL
CLOCK TIME ................. ……………SET
AIRSPEED…............CHECK / NO FLAG
RMI / EHSI …………...…X CHECK HDG
EADI…………………………CHECK ATT
EGPWS TEST …………….…PERFORM
GPWS G/S P/B……..CHECK NO LIGHT
ALTIMETER.............CHECK / NO FLAG
VSI…………………………………CHECK
TAT/SAT IND……………………..CHECK
ADC SWITCH……………………….1 or 2
DSP SEL………………………….CHECK
RIGHT INSTRUMENT PANEL
APM TEST……………………PERFORM
GPWS G/S P/B……..CHECK NO LIGHT
ALTIMETER.............CHECK / NO FLAG
VSI…………………………………CHECK
DSP SEL………………………….CHECK
RMI / EHSI …………...…X CHECK HDG
EADI…………………………CHECK ATT
AIRSPEED…............CHECK / NO FLAG
CLOCK TIME................. ……………SET
Mod: 3973 or 4371 or 4457
NORMAL PROCEDURES
72
3.07
NOV 11 001
FINAL COCKPIT PREPARATION
CM1
CM2
AIRFIELD DATA ……………..…OBTAIN
LANDING ELEVATION. ................... SET
PF
PNF
GNSS HT1000 Programming
(if applicable)
INIT………………………………..CHECK
NAV …………………………….…… SET
NAV ………………...…………… CHECK
PERF…….........................................SET
PERF ……….…..........................CHECK
NAVAIDS / NAV SOURCES ........ …SET
COM …………………………………..SET
NAVAIDS / NAV SOURCES ............ SET
COM……………………...……………SET
CM1
CM2
PARKING BRK........ ON/PRESS CHECK
SIGNS….……….………………..…….ON
MEMO PANEL ........................... CHECK
FUEL QTY / FOB ...........………..CHECK
FUEL USED……………………….RESET
ALTIMETERS................................... SET
TQ BUGS…………………SET & CHECK
SEATS, SEATS BELT, HARNESS,
RUDDER PEDALS.....................ADJUST
DEPART BRIEFING............ COMPLETE
ALTIMETERS .................................. SET
TQ BUGS…………………SET & CHECK
SEATS, SEATS BELT, HARNESS,
RUDDER PEDALS.....................ADJUST
DEPART BRIEFING ............COMPLETE
FINAL COCKPIT PREPARATION C/L
NORMAL PROCEDURES
72
3.08
NOV 11 001
HOTEL MODE START UP
CM1
CM2
SERVICE DOOR ………...…….CLOSED
FUEL PUMP 2 …………………….…..ON
WING LIGHTS …………………..…….ON
PROP BRK.......................ON / LOCKED
ENGINE 2 .………………………..START
- ENGINE & PROP AREA ………CLEAR
- ENG START………………..START A/B
- START 2 P/B………DEPRESSED / ON
- ENG ROTATION (NH) ……..MONITOR
When passing 10 % NH
(maximum 19% NH if ITT > 200°c)
- CL 2 …..……………….……..........FTR
- ITT rises within 10s…...…….…CHECK
- Oil Pressure…………………….CHECK
When passing 45 % NH
- START P/B ON LT…..EXTINGUISHED
When engine parameters stabilized
- ENG START….OFF & START ABORT
- GPU……........................................OFF
- DC GEN 2 ……………..……..ON LINE
- DC BTC .…………...CHECK CLOSED
- BLEED / PACK XVALVE………………
……………………………CHECK OPEN
- PL 1 + 2…………..ADJUST AS RQRD
3.09
NORMAL PROCEDURES
72
SEP 13
160
BEFORE PROPELLER ROTATION
CM1
CM2
LOADSHEET ……...……………..CHECK
GNSS WEIGHT & FUEL........…UPDATE
SPEED BUGS ................. SET & CHECK
TRIMS ........................................ CHECK
BOOST ....................... ON(if necessary)
The BOOST is effective only when the
engine is thermally limited. Select ON,
only when a gain in payload is
necessary.
TAIL PROP ..........................ON BOARD
DOORS .................................... CLOSED
SEAT BELTS......................................ON
BEACON………………………….. ......ON
NWS (if push back)………………..…OFF
GNSS WEIGHT & FUEL........…UPDATE
SPEED BUGS................. SET & CHECK
TRIMS.............................................. SET
START UP CLEARANCE………OBTAIN
CDLS .................................................ON
BEFORE PROPELLER ROTATION C/L
BEFORE TAXI
CM1
CM2
PROP BRK RDY LT....................CHECK
PROP BRK SW ................................OFF
When NP stabilized
CL 2 ........................................MAX RPM
LO PITCH ………………………...CHECK
ACW GEN 2……………………..ON LINE
ACW BTC……………………….CLOSED
HYD……………………………….CHECK
ANTI-ICING............................... AS RQD
ANTI-SKID ..................................... TEST
FLAPS .......................................... ….15°
ENGINE 1 …………………...……START
When NP stabilized
CL 1. .......................................MAX RPM
LO PITCH ………………...………CHECK
ACW GEN 1……………………..ON LINE
ACW BTC .....................................OPEN
XPDR……………………...AS REQUEST
COCKPIT COM HATCH… ....... CLOSED
NWS……………….……...………….…ON
BEFORE TAXI C/L
TAXI
CM1
CM2
TAXI CLEARANCE ……………..OBTAIN
TAXI & TO LIGHTS ........................... ON
BRAKES…………………………..CHECK
INSTRUMENTS………………… CHECK
BRAKES .....................................CHECK
INSTRUMENTS………………… CHECK
AFCS ......................................... CHECK
AFCS .............................................. SET
TO CONFIG ................................... TEST
TO DATA …………………………CHECK
TAKE OFF BRIEFING......... COMPLETE
CABIN REPORT …………….OBTAINED
ATC CLEARANCE ……………...OBTAIN
TO DATA …………………………CHECK
TAKE OFF BRIEFING .........COMPLETE
TAXI C/L
Mod: 5908
Eng: PW127M
3.10
NORMAL PROCEDURES
72
NOV 11 030
BEFORE TAKE OFF
CM1
CM2
FLIGHT CONTROLS……..………CHECK
CCAS ………………………….………RCL
CCAS…………………….………TO INHIB
OVERHEAD PANEL ………...........SCAN
GUST LOCK…………………...RELEASE
FLIGHT CONTROLS ……………CHECK
TCAS……… ……….......................AUTO
XPDR…………………………….........ALT
APM ROT SEL …SELECT T/O WEIGHT
AIR FLOW …………………………NORM
----------------EXT LIGHTS……………………………ON
----------------BLEED VALVES…………………AS RQD
When lined up
When lined up
FD BAR ….…………………...CENTERED
RUDDER CAM ………………CENTERED
FD BAR ……………………..CENTERED
BEFORE TAKE OFF C/L
TAKE OFF
CM1
CM2
BRAKES ........................... RELEASED
PL1+2....................................... NOTCH
“ATPCS ARM”……...CHECK & ANNOUNCE
ENGINE PARAMETERS...................CHECK
“POWER SET”...........................ANNOUNCE
When reaching 70 Kt
“SEVENTY KNOTS”………...….ANNOUNCE
Mod : 4111
3.11
NORMAL PROCEDURES
72
NOV 11 100
TAKE OFF (CONT’D)
PF
PNF
When reaching 70 Kt
“I HAVE CONTROL”….....ANNOUNCE
“V1”.........................................ANNOUNCE
When reaching VR
“ROTATE”..............................ANNOUNCE
ROTATION ........................ PERFORM
After LIFT OFF
“ POSITIVE RATE”..............ANNOUNCE
“GEAR UP” ............................ORDER
LDG GEAR LEVER.............. SELECT UP
YD……………........................... ENGAGE
TAXI & TAKE OFF LIGHT ……….....OFF
LDG GEAR LT……………………………
………………..CHECK EXTINGUISHED
When passing ACCELERATION
ALTITUDE
“ACCELERATION ALTITUDE”…………..
……………………………..….ANNOUNCE
“CLIMB SEQUENCE” .............ORDER
- PL 1 + 2…………………………………
………….SET/CHECK IN THE NOTCH
- IAS ......INCREASE ABOVE WHITE BUG
- PL 1 + 2.............CHECK IN THE NOTCH
- PWR MGT ....................................CLIMB
- NP................................................CHECK
- BLEEDs .............................................ON
- SPEED TARGET…….…... SET to 170 kt
“CLIMB SEQUENCE COMPLETE”……….
…………………………………ANNOUNCE
When passing WHITE BUG
(ICING BUG in Icing condition)
“FLAPS ZERO” ....................... ORDER
FLAPS ZERO ............................ SELECT
When cleared to a FL
“SET STD”........................ANNOUNCE
ALTIMETERS 1 + 2……………………
………..…SET STD & CROSS CHECK
ALTIMETERS 1 + 2………………………
…………….SET STD & CROSS CHECK
AFTER TO CHECK LIST
Mod: 3973 or 4371 or 4457
3.12
NORMAL PROCEDURES
72
NOV 11 100
CLIMB
CM1
PNF
Crossing FL 100 climbing
SEAT BELTS........................AS RQRD
LANDING LIGHTS ..............................OFF
PRESSURIZATION………………..CHECK
CRUISE
PF
PNF
At Cruise FL
SAT ..............................................CHECK
CRUISE PARAMETER…...…..COMPUTE
Reaching Cruise Speed
CRUISE TQ & SPEEDS….….…CHECK
PWR MGT..........................................CRZ
CRUISE PARAMETER…………...CHECK
ALL SYSTEM…PERIODICALLY..CHECK
FUEL.............................................CHECK
DESCENT PREPARATION
PF
PNF
CCAS.…………………..………...…..RCL
STBY QNH (CM1)…………………...SET
LANDING DATA …………………..OBTAIN
LDG ELEVATION…..……………...CHECK
GNSS PREPARATION…….. …...…SET
NAVAIDS / NAV SOURCES………..SET
ASI BUGS..……………………..……SET
DH /MDA….………………SET/CHECK
ARRIVAL BRIEFING............COMPLETE
NAVAIDS / NAV SOURCES……….…SET
ASI BUGS ………………………………SET
TQ BUGS ……………………………….SET
DH /MDA….………………..…SET/CHECK
ARRIVAL BRIEFING…………COMPLETE
DESCENT C/L
DESCENT
PF
PNF
DESCENT ……………….…INITIATE
When passing FL 100
SEAT BELTS (CM1)…….……….ON
Mod: 3973 or 4371 or 4457
ALL SYSTEMS……………………CHECK
LANDING LIGHTS ………………..….ON
PRESSURIZATION………………CHECK
NORMAL PROCEDURES
72
3.13
NOV 11 100
APPROACH
PF
PNF
When cleared to Altitude
When cleared to Altitude
ALTIMETERS.................. SET & CHECK
ALTIMETERS…...............SET & CHECK
CABIN ALTITUDE ..................... .CHECK
CABIN REPORT (CM1)...............OBTAIN
APPROACH C/L
BEFORE LANDING
PF
PNF
When Cleared for Approach
NAV SOURCES …………………CHECK
NAV SOURCES …………………CHECK
At appropriate speed
“FLAPS 15” ...............................ORDER
FLAPS 15 ..................................SELECT
At appropriate speed
“GEAR DOWN”..........................ORDER
GEAR DOWN.............................SELECT
PWR MGT.......................................... TO
EXT LIGHTS ......................................ON
At appropriate speed
“FLAPS 30” …............................ORDER
SPEED VERSUS AOA ………….CHECK
FLAPS 30 ..................................SELECT
TLU ...............................CHECK LO SPD
ICING AOA LIGHT......................CHECK
SPEED VERSUS AOA ………….CHECK
BEFORE LDG C/L
Mod: 3973 or 4371 or 4457
3.14
NORMAL PROCEDURES
72
SEP 13
001
LANDING
PF
PNF
At DH +500 ft (Or MDA + 500ft)
“CHECK”..............................ANNOUNCE
“500 ”………MONITOR or ANNOUNCE
At DH +100 ft (Or MDA + 100ft)
“100”............. MONITOR or ANNOUNCE
“CHECK”..............................ANNOUNCE
At DH (Or MDA)
“MINIMUM”..........................ANNOUNCE
“CONTINUE”.......................ANNOUNCE
or
“GO AROUND, SET PWR, FLAPS”…….
……ANNOUNCE (Check GA Procedure)
FLIGHT PARAMETERS .............CHECK
AP …………………………DISCONNECT
After touch down
R
PL ........................................................GI
REVERSE........................USE AS RQD
After touch down
IDLE GATE……… AUTO RETRACTION
BOTH LOW PITCH LIGHT..........CHECK
“2 LOW PITCH”..................ANNOUNCE
When reaching 70 Kt
“SEVENTY KNOTS”……….ANNOUNCE
CM1
CM2
When reaching 70 Kt
“I HAVE CONTROL”….....ANNOUNCE
NOSE WHEEL STEERING ...CONTROL
CONTROL WHEEL......HOLD AS RQD
R
NORMAL PROCEDURES
72
3.15
NOV 11 100
GO AROUND
PF
PNF
“GO AROUND, SET PWR, FLAPS ONE
NOTCH”……………………...ANNOUNCE
GO AROUND P/B on PL..........DEPRESS
PL 1+2....................ADVANCE TO RAMP
PITCH ATT ..........ROTATE to GA PITCH
PWR……………………………..CHECK
FLAPS ONE NOTCH...............SELECT
When positive rate
When positive rate
“POSITIVE RATE”…………ANNOUNCE
“GEAR UP,HDG,LO BANK, IAS VGA”…..
……………………………………...ORDER
LDG GEAR LEVER............ SELECT UP
YD……………........................ ENGAGE
TAXI & TAKE OFF LIGHT …..........OFF
HDG LO BANK …………….……….SET
IAS VGA……………..………..……..SET
When passing ACCELERATION
ALTITUDE
When passing ACCELERATION
ALTITUDE
“CLIMB SEQUENCE” .................ORDER
- PL 1 + 2...SET/CHECK IN THE NOTCH
- IAS...INCREASE ABOVE WHITE BUG
- PL 1 + 2..........CHECK IN THE NOTCH
- PWR MGT .................................CLIMB
- NP............................................CHECK
- BLEEDs ..........................................ON
- SPEED TARGET………. SET to 170 kt
“CLIMB SEQUENCE COMPLETE”……..
……………………………….ANNOUNCE
When passing WHITE BUG
(ICING BUG in Icing condition)
When passing WHITE BUG
(ICING BUG in Icing condition)
“FLAPS ZERO” ......................... ORDER
FLAPS ZERO .......................... SELECT
When cleared to a FL
When cleared to a FL
“SET STD”...........................ANNOUNCE
ALTIMETERS 1 + 2…………………….
……………..SET STD & CROSS CHECK
ALTIMETERS 1 + 2……………….....
……………SET STD & CROSS CHECK
AFTER TAKE OFF C/L
Mod: 3973 or 4371 or 4457
NORMAL PROCEDURES
72
3.16
NOV 11 001
AFTER LANDING
CM1
CM2
When runway is vacated
“AFTER LANDING PROCEDURE”.... ORDER
TRIMS ......................................... RESET
TCAS ………………………………. STBY
FLAPS......……………………………….0°
GUST LOCK……………………ENGAGE
FLIGHT CONTROLS.….LOCKED XPDR
XPDR / TCAS …………………AS RQRD
RADAR...........................................STBY
LAND LIGHTS / STROBES..............OFF
PROB HTG / ANTI / DE-ICING……..OFF
ATPCS DYNAMIC TEST (Last flight of
the day)………………………..PERFORM
After at least one minute
CL 1.......................FTR THEN FUEL SO
AFTER LANDING C/L
PARKING
CM1
CM2
Marshaller in sight (last turn)
TAXI & TO LIGHTS ......................... OFF
HYD SYST ………...CHECK 3X3000
AT the stand
PARKING BRK .................................. ON
CL 2…………………………... ...........FTR
READY LIGHT....CHECK ILLUMINATED
When NP Stabilized
PROP BRK .............................. ENGAGE
PROP BRK LT ...CHECK ILLUMINATED
PROP 2………………CHECK STOPPED
BEACON ......................................... OFF
If GPU is used for disembarking
- DC EXT PWR PB.........................ON
- CL 2 ...................................FUEL SO
TAIL PROP........................ IN POSITION
SEAT BELTS................................... OFF
XPDR………………………………...STBY
PARKING C/L
NORMAL PROCEDURES
72
3.17
NOV 11 001
LEAVING THE AIRCRAFT
CM1
CM2
OXYGEN MAIN SUPPLY ..............OFF
ICE & RAIN PROT.........................OFF
EXT LIGHTS..................................OFF
EMER EXIT LIGHT................. DISARM
RADAR ..........................................OFF
CL 2.......................................FUEL SO
FUEL PUMPS 1 + 2.......................OFF
CDLS.............................................OFF
EXT PWR (if used)…………………OFF
BAT ...............................................OFF
LEAVING THE AIRCRAFT C/L
72
NORMAL PROCEDURES
DAILY CHECKS
3.18
SEP 13
150
ATPCS – dynamic test (last flight of the day)
Conditions:
- PL 1 + 2 .................................................................................................................. GI
- CL 1 + 2 ........................................................................................................... AUTO
- ATPCS P/B depressed in, OFF light extinguished
- PWR MGT on TO position
Check the following results :
Turn the ATPCS knob to the left to the arm position and check
- ARM light .............................................................................................ILLUMINATES
- TQ INDICATION ....................................................................................... INCREASE
- NP & NH INDICATION ............................................................................ DECREASE
Turn the ATPCS knob to ENG 1 position and check :
- ENG 2 UPTRIM LIGHT ........................................................................ILLUMINATES
- TQ 2 .......................................................................................................NO CHANGE
- NP, NH....................................................................................INCREASE SLIGHTLY
- TQ 1 needles indication ................................................... DECREASE BELOW 18 %
- After 2.15 s : associated propeller is automatically feathered :
- ARM light ................................................................................. EXTINGUISHED
Turn the ATPCS knob to the right to the arm position and check :
- ARM light .............................................................................................ILLUMINATES
- TQ INDICATION ....................................................................................... INCREASE
- NP & NH INDICATION ............................................................................ DECREASE
Turn the ATPCS knob to ENG 2 position and check :
- ENG 1 UPTRIM LIGHT ........................................................................ILLUMINATES
- TQ 1 .......................................................................................................NO CHANGE
- NP, NH....................................................................................INCREASE SLIGHTLY
- TQ 2 needles indication ................................................... DECREASE BELOW 18 %
- After 2.15 s : associated propeller is automatically feathered :
- ARM light ................................................................................. EXTINGUISHED
R
CAUTION: Do not perform ENG TEST while taxiing as ACW is temporarily lost and
consequently, both main HYD pumps are temporarily lost as well.
Note: If ENG TEST must be repeated, wait 10 minutes before setting ATPCS.selector
in ENG position in order not to damage feathering pumps. (Winding heating).
Mod: 3973 or 4371 or 4457
Eng: PW127 – PW127F – PW127M
72
NORMAL PROCEDURES
DAILY CHECKS
3.19
NOV 11 001
CVR / DFDR
CVR:
TEST PB ................................................................................................ DEPRESS
Check pointer moves to the green arc.
DFDR:
Check status SYST light (on the FDEP or RCDR panel) has to be extinguished..
STICK PUSHER / SHAKER
- Release gust lock
- Push Control column in nose down position
- Select WARN rotary selector (LH maintenance panel) to STICK PUSHER
YES
- depress and maintain PTT
- monitor stall cricket and stick shaker
- after ten seconds delay, monitor
. CHAN 1 and CHAN 2 illuminate green on LH maintenance panel
. STICK PUSHER lights illuminate green on both pilots panel
. Stick pusher actuator operates.
- select WARN rotary selector to NORM FLT
- reengage the gust lock
TRIMS
First Flight of the Day:
Check PITCH, ROLL, and YAW TRIM operation as follows:
- Check the normal TRIM activation in both directions by depressing simultaneously
both control rocker switches.
- For few seconds depress independently each single control rocker switch and check
the non-activation of the corresponding TRIM in both possible directions.
- Reset TRIMS as required for take off.
Before each flight::
- Check PITCH, ROLL, and YAW TRIM operation.
- Check STBY PITCH TRIM operation, check GUARDED switch in OFF position.
72
NORMAL PROCEDURES
DAILY CHECKS
3.20
NOV 11 001
COCKPIT DOOR DAILY CHECK (if applicable)
COCKPIT DOOR LOCKING SYSTEM SW ..............................................................ON
In the cargo compartment, on the DOOR CALL panel:
EMER PB ............................................................................................... DEPRESS
CHECK OPEN LIGHT flashes
In the cockpit:
CHECK BUZZER
CHECK OPEN LIGHT flashes
 If correct
In the cockpit:
TOGGLE SW ON COCKPIT DOOR CTL panel....................................... DENY
CHECK BUZZER stops
CHECK OPEN LIGHT extinguishes
In the cargo compartment, on the DOOR CALL panel:
CHECK OPEN LIGHT extinguishes and DENIED LIGHT illuminates
 If correct
In the cockpit:
TOGGLE SW ..................................................................................... OPEN
COCKPIT DOOR LOCKING SYSTEM SW ........................................... OFF
COCKPIT DOOR CTL panel FAULT LIGHT ....................................CHECK
FUNCTIONAL CHECK OF THE MANUAL LOCK BOLT(S)
APM TEST (if installed)
DAILY CHECK MUST BE PERFORMED
APM PTT PB .................................. PUSH and MAINTAIN for test duration
- CRUISE SPEED LOW lights on 13 VU (both sides) illuminate
- over 1 second later, DEGRADED PERF lights on 13 VU (both sides) illuminate, with
CAUTION light and SC, with CRUISE SPEED LOW lights still illuminated
- over 1 second later, INCREASE SPEED lights on 13 VU (both sides) illuminate flashing,
with CAUTION light and SC, with CRUISE SPEED LOW and DEGRADED PERF
lights still illuminated
- over 1 second later, FAULT light on the 5VU illuminates, with CAUTION light, SC and
ANTI-ICING (on CAP), with CRUISE SPEED LOW, DEGRADED PERF and
INCREASE SPEED lights still illuminated
- end of test, the crew stop action on APM PTT TEST pushbutton, all lights shall
extinguish.
3.21
NORMAL PROCEDURES
72
NOV 11 500
CRUISE SPEED LOW
Appears in cruise only, to inform the crew that an abnormal drag increase
induces a speed decrease of more than 10 KT compared with the
expected speed
ICING CONDITIONS and SPEED .........................................MONITOR
ENTERING ICING CONDITIONS
ANTI-ICING (PROP - HORNS - SIDE WINDOWS) .....................................ON
MODE SEL.............................................................................................. AUTO
MINIMUM MANEUVER/OPERATING ICING SPEEDS .................BUGGED AND OBSERVED
ICE ACCRETION .............................................................................MONITOR
AT FIRST VISUAL INDICATION OF
ICE ACCRETION AND
AS LONG AS ICING CONDITIONS EXIST
ANTI-ICING (PROP - HORNS - SIDE WINDOWS) ...................CONFIRM ON
MODE SEL............................................................................ CONFIRM AUTO
ENG DE-ICING ............................................................................................ON
AIRFRAME DE-ICING .................................................................................ON
MINIMUM MANEUVER/OPERATING ICING SPEEDS .................BUGGED AND OBSERVED
BE ALERT TO SEVERE ICING DETECTION
In case of severe icing, refer to 1.09
 If significant vibrations occur
BOTH CL ........................................ 100 OVRD for not less than 5 minutes
LEAVING ICING CONDITIONS
DE-ICING AND ANTI-ICING MAY BE SWITCHED OFF
WHEN THE AIRCRAFT IS VISUALLY
VERIFIED CLEAR OF ICE
ICING AOA CAPTION MAY BE CANCELLED AND NORMAL SPEEDS MAY
BE USED
Model : 212A
4.01
OPS DATA
72
APR 08 500
4 – OPS DATA
COMMENTS:
- T/O SPEEDS COMPUTATION
Valid for non limiting runways only
- VR COMPUTATION (normal or icing conditions)
For runway contaminated by water or slush, increase VR by:
• 0 kt up to 1/4 inch
• 1 kt between 1/4 and 1/2 inch
- LANDING SPEEDS COMPUTATION
The approach speeds have been computed with 1.23 VSR of landing
configuration or VMCL, whichever is higher
- GROSS CEILING COMPUTATION
For operational reasons, gross ceilings have been established with
CG position: 25%
R
Model : 212A
4.11
OPS DATA
72
APR 08 500
PW127F / PW127M - BOOST OFF
TAKE OFF TORQUE COMPUTED FOR VC = 50. KT
o
SAT ( C)
AIR
COND
OFF
NORMAL HIGH
AIR
AIR
COND COND
ON
ON
PROPELLER SPEED 100 %
PRESSURE ALTITUDE (FT)
-1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
89.7
88.7
90.0
89.7
88.7
87.8
86.8
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
89.3
88.3
87.2
87.7
86.7
85.7
84.7
83.6
85.8
84.9
83.9
82.9
81.9
8.
10.
12.
14.
16.
- 5.
- 2.
0.
3.
5.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
88.9
89.9
88.8
87.7
86.5
85.2
86.2
85.2
84.1
83.0
81.7
82.6
81.7
80.7
79.5
78.4
80.9
79.9
79.0
77.9
76.7
18.
20.
22.
24.
26.
8.
10.
13.
15.
18.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
88.5
90.0
89.6
88.1
86.5
85.0
87.5
86.0
84.5
83.0
81.5
83.9
82.5
81.0
79.6
78.2
80.5
79.1
77.7
76.3
75.0
77.1
75.8
74.5
73.2
71.9
75.5
74.2
72.9
71.7
70.4
28.
30.
32.
34.
36.
20.
23.
25.
28.
30.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
88.9
87.1
90.0
88.8
87.1
85.4
83.7
86.9
85.2
83.6
81.9
80.3
83.4
81.8
80.2
78.6
77.0
80.0
78.5
77.0
75.4
73.9
76.7
75.3
73.8
72.4
70.9
73.6
72.2
70.8
69.4
68.0
70.5
69.2
67.9
66.5
65.2
69.1
67.7
66.4
65.1
63.8
38.
40.
42.
44.
46.
33.
36.
38.
41.
43.
90.0
90.0
88.8
86.9
85.0
88.9
87.1
85.3
83.5
81.6
85.4
83.6
81.9
80.1
78.4
82.0
80.3
78.6
76.9
75.3
78.7
77.1
75.4
73.8
72.2
75.5
73.9
72.4
70.8
69.3
72.4
70.9
69.4
68.0
69.5
68.0
66.6
66.6
65.2
63.8
62.5
48.
50.
52.
54.
55.
46.
48.
51.
53.
54.
83.1
81.2
79.3
77.5
76.5
79.8
78.0
76.2
74.4
73.5
76.6
74.9
73.2
73.6
71.9
70.6
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Applicable for 0 < VC < 60 kt
Model : 212A
4.11A
OPS DATA
72
OCT 08 500
PW127M – BOOST ON
TAKE OFF TORQUE COMPUTED FOR VC = 50. KT
SAT (oC)
PROPELLER SPEED 100 %
NORMAL HIGH
AIR
AIR
AIR
COND
COND COND
OFF
ON
ON
PRESSURE ALTITUDE (FT)
-1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
89.1
88.1
87.0
89.3
88.3
87.3
86.2
85.2
8.
10.
12.
14.
16.
- 5.
- 2.
0.
3.
5.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
88.7
89.7
88.6
87.5
86.3
85.0
86.0
84.9
83.9
82.7
81.5
84.2
83.2
82.1
81.0
79.8
18.
20.
22.
24.
26.
8.
10.
13.
15.
18.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
88.8
90.0
89.5
87.9
86.4
84.8
87.3
85.8
84.3
82.8
81.3
83.7
82.3
80.9
79.4
78.0
80.3
78.9
77.5
76.1
74.8
78.6
77.2
75.9
74.6
73.2
28.
30.
32.
34.
36.
20.
23.
25.
28.
30.
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
90.0
89.2
87.4
90.0
89.1
87.4
85.6
83.9
87.2
85.5
83.8
82.2
80.5
83.2
81.7
80.1
78.5
76.9
79.8
78.3
76.8
75.3
73.8
76.6
75.1
73.6
72.2
70.7
73.4
72.0
70.6
69.2
67.8
71.9
70.5
69.1
67.8
66.4
38.
40.
42.
44.
46.
33.
36.
38.
41.
43.
90.0
90.0
90.0
90.0
88.8
90.0
90.0
89.1
87.2
85.3
89.2
87.4
85.6
83.8
81.9
85.7
83.9
82.2
80.4
78.7
82.2
80.5
78.9
77.2
75.5
78.9
77.3
75.7
74.0
72.4
75.3
73.8
72.3
70.7
72.3
70.8
69.3
69.3
67.9
66.4
65.0
48.
50.
52.
54.
55.
46.
48.
51.
53.
54.
86.9
84.9
82.9
81.0
80.0
83.4
81.5
79.6
77.8
76.8
80.1
78.3
76.5
76.9
75.2
73.8
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Applicable for 0 < VC < 60 kt
Eng : PW127M
Model : 212A
4.12
OPS DATA
72
APR 08 500
PW127F / PW127M - BOOST OFF
RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT
o
SAT ( C)
AIR
COND
OFF
PROPELLER SPEED 100 %
NORMAL HIGH
AIR
AIR
COND COND
ON
ON
PRESSURE ALTITUDE (FT)
-1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
- 71.
- 35.
- 32.
- 30.
- 27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.6
98.5
100.
99.7
98.6
97.5
96.5
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
- 25.
- 22.
- 19.
- 17.
- 14.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.3
98.1
96.9
97.4
96.3
95.2
94.1
92.9
95.4
94.3
93.2
92.1
91.0
8.
10.
12.
14.
16.
- 5.
- 2.
0.
3.
5.
- 12.
- 9.
- 7.
- 4.
- 1
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
98.7
99.9
98.7
97.5
96.1
94.7
95.8
94.6
93.5
92.2
90.8
91.8
90.7
89.6
88.4
87.1
89.9
88.8
87.8
86.5
85.3
18.
20.
22.
24.
26.
8.
10.
13.
15.
18.
2.
4.
7.
10.
13.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
98.4
100.
99.6
97.9
96.1
94.4
97.2
95.5
93.9
92.2
90.6
93.2
91.6
90.0
88.5
86.9
89.4
87.9
86.4
84.8
83.3
85.7
84.3
82.8
81.3
79.9
83.9
82.5
81.1
79.6
78.2
28.
30.
32.
34.
36.
20.
23.
25.
28.
30.
16.
18.
21.
24.
27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
98.8
96.8
100.
98.7
96.8
94.9
93.0
96.6
94.7
92.9
91.1
89.2
92.7
90.9
89.1
87.4
85.6
88.9
87.2
85.5
83.8
82.1
85.3
83.6
82.0
80.4
78.8
81.8
80.2
78.6
77.1
75.5
78.4
76.9
75.4
73.9
72.4
76.7
75.3
73.8
72.4
70.9
38.
40.
42.
44.
46.
33.
36.
38.
41.
43.
30.
32.
35.
38.
41.
100.
100.
98.7
96.6
94.4
98.8
96.8
94.8
92.7
90.7
94.9
92.9
91.0
89.0
87.1
91.1
89.2
87.3
85.5
83.6
87.4
85.6
83.8
82.0
80.2
83.9
82.2
80.4
78.7
77.0
80.5
78.8
77.2
75.5
77.2
75.6
74.0
74.0
72.5
70.9
69.5
48.
50.
52.
54.
55.
46.
48.
51.
53.
54.
43.
46.
49.
52.
53.
92.3
90.3
88.2
86.1
85.0
88.7
86.7
84.7
82.7
81.7
85.2
83.2
81.3
81.8
79.9
78.5
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Applicable for 0 < VC < 60 kt
Model : 212A
4.12A
OPS DATA
72
OCT 08 500
PW127M - BOOST ON
RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT
SAT (oC)
PROPELLER SPEED 100 %
NORMAL HIGH
AIR
AIR
AIR
COND
COND COND
OFF
ON
ON
PRESSURE ALTITUDE (FT)
-1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
- 71.
- 35.
- 32.
- 30.
- 27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
- 25.
- 22.
- 19.
- 17.
- 14.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.0
97.9
96.7
99.3
98.1
97.0
95.8
94.7
8.
10.
12.
14.
16.
- 5.
- 2.
0.
3.
5.
- 12.
- 9.
- 7.
- 4.
- 1
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.9
98.5
99.6
98.4
97.2
95.9
94.5
95.5
94.4
93.2
91.9
90.6
93.5
92.4
91.3
90.0
88.7
18.
20.
22.
24.
26.
8.
10.
13.
15.
18.
2.
4.
7.
10.
13.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
98.7
100.
99.4
97.7
96.0
94.2
97.0
95.4
93.7
92.0
90.4
93.0
91.4
89.8
88.3
86.7
89.2
87.7
86.1
84.6
83.1
87.3
85.8
84.3
82.8
81.3
28.
30.
32.
34.
36.
20.
23.
25.
28.
30.
16.
18.
21.
24.
27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.1
97.2
100.
99.0
97.1
95.2
93.2
96.8
95.0
93.2
91.3
89.5
92.5
90.7
89.0
87.2
85.5
88.7
87.0
85.3
83.6
82.0
85.1
83.4
81.8
80.2
78.6
81.5
80.0
78.4
76.9
75.3
79.8
78.3
76.8
75.3
73.8
38.
40.
42.
44.
46.
33.
36.
38.
41.
43.
30.
32.
35.
38.
41.
100.
100.
100.
100.
98.7
100.
100.
99.0
97.0
94.8
99.1
97.1
95.1
93.1
91.0
95.2
93.2
91.3
89.3
87.4
91.4
89.5
87.6
85.7
83.9
87.7
85.9
84.0
82.3
80.5
83.7
82.0
80.3
78.6
80.3
78.6
77.0
77.0
75.4
73.8
72.3
48.
50.
52.
54.
55.
46.
48.
51.
53.
54.
43.
46.
49.
52.
53.
96.5
94.3
92.1
90.0
88.9
92.7
90.6
88.5
86.4
85.3
89.0
87.0
85.0
85.4
83.5
82.0
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Applicable for 0 < VC < 60 kt
Eng : PW127M
Model : 212A
4.13
OPS DATA
72
APR 08 500
PW127F / PW127M - BOOST OFF
GO AROUND TORQUE APPLICABLE FOR 0 ≤ VC ≤ 125 kt
o
TAT ( C)
PROPELLER SPEED 100. %
NORMAL HIGH
AIR
AIR
AIR
COND.
COND. COND.
-100.0.
OFF
ON
ON
PRESSURE ALTITUDE (FT)
0.
100.0.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
- 71.
- 35.
- 32.
- 30.
- 27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.8
98.7
100.
99.9
98.8
97.8
96.7
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
- 25.
- 22.
- 19.
- 17.
- 14.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.5
98.3
97.2
97.6
96.5
95.4
94.3
93.2
95.6
94.5
93.4
92.3
91.2
8.
10.
12.
14.
16.
- 5.
- 2.
0.
3.
5.
- 12.
- 9.
- 7.
- 4.
- 1.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.0
100.
98.9
97.7
96.4
95.0
96.0
94.9
93.7
92.5
91.1
92.1
91.0
89.9
88.7
87.4
90.1
89.1
88.0
86.8
85.5
18.
20.
22.
24.
26.
8.
10.
13.
15.
18.
2.
4.
7.
10.
13.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
98.7
100.
99.9
98.2
96.5
94.7
97.5
95.9
94.2
92.6
90.9
93.6
92.0
90.4
88.8
87.2
89.7
88.2
86.7
85.2
83.6
86.0
84.6
83.1
81.7
80.2
84.3
82.8
81.4
79.9
78.5
28.
30.
32.
34.
36.
20.
23.
25.
28.
30.
16.
18.
21.
24.
27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.2
97.2
100.
99.0
97.1
95.2
93.3
96.9
95.1
93.2
91.4
89.6
93.0
91.2
89.5
87.7
86.0
89.2
87.5
85.9
84.2
82.5
85.6
84.0
82.4
80.7
79.1
82.1
80.5
79.0
77.4
75.9
78.7
77.2
75.7
74.3
72.8
77.1
75.6
74.2
72.7
71.2
38.
40.
42.
44.
46.
33.
36.
38.
41.
43.
30.
32.
35.
38.
41.
100.
100.
99.0
96.9
94.8
99.2
97.1
95.1
93.1
91.1
95.2
93.3
91.3
89.4
87.5
91.4
89.6
87.7
85.8
84.0
87.8
86.0
84.2
82.4
80.6
84.2
82.5
80.8
79.1
77.4
80.8
79.2
77.5
75.9
74.2
77.5
75.9
74.4
72.8
74.3
72.8
71.3
71.3
69.8
69.8
68.4
48.
50.
52.
54.
56.
46.
48.
51.
53.
54.
43.
46.
49.
52.
54.
92.7
90.6
88.5
86.4
84.4
89.1
87.1
85.0
83.0
81.0
85.5
83.6
81.7
79.7
82.1
80.3
78.4
78.8
77.0
75.7
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Add 0.8% for each 10 kt above 125 kt without exceeding 100% torque
Model : 212A
4.13A
OPS DATA
72
OCT 08 500
PW127M - BOOST ON
GO AROUND TORQUE COMPUTED FOR VC = 100. KT
TAT (oC)
PROPELLER SPEED 100 %
NORMAL HIGH
AIR
AIR
AIR
COND
COND COND
OFF
ON
ON
PRESSURE ALTITUDE (FT)
-1000.
0.
1000.
2000.
3000.
4000.
5000.
6000.
7000.
8000.
8500.
- 40.
- 10.
- 8.
- 6.
- 4.
- 63.
- 27.
- 24.
- 22.
- 19.
- 71.
- 35.
- 32.
- 30.
- 27.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
- 2.
0.
2.
4.
6.
- 17.
- 14.
- 12.
- 10.
- 7.
- 25.
- 22.
- 19.
- 17.
- 14.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.3
98.1
96.9
99.5
98.3
97.2
96.1
94.9
8.
10.
12.
14.
16.
18.
20.
22.
24.
26.
28.
30.
32.
34.
36.
38.
40.
42.
44.
46.
48.
50.
52.
54.
56.
- 5. - 12.
- 2. - 9.
0. - 7.
3. - 4.
5. - 1
8.
2.
10.
4.
13.
7.
15.
10.
18.
13.
20.
16.
23.
18.
25.
21.
28.
24.
30.
27.
33.
30.
36.
32.
38.
35.
41.
38.
43.
41.
46.
43.
48.
46.
51.
49.
53.
52.
55.
54.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.1
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.4
97.3
95.2
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.4
97.5
95.5
93.6
91.7
89.9
88.0
86.1
84.3
82.4
80.5
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.0
97.2
95.4
93.5
91.7
89.9
88.0
86.2
84.4
82.6
80.9
79.1
100.
100.
100.
100.
98.8
97.4
95.7
94.0
92.4
90.7
89.1
87.4
85.7
84.0
82.3
80.7
79.0
77.4
75.7
99.9
98.7
97.5
96.1
94.8
93.4
91.8
90.2
88.6
87.0
85.4
83.8
82.2
80.6
79.0
77.4
75.8
74.2
95.8
94.6
93.5
92.2
90.9
89.5
88.0
86.5
85.0
83.4
81.9
80.4
78.8
77.3
75.7
74.2
72.7
93.8
92.6
91.5
90.3
89.0
87.7
86.2
84.7
83.2
81.7
80.2
78.7
77.2
75.6
74.1
72.6
71.1
93.1
91.0
88.9
86.8
84.7
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.5
97.5
95.6
93.6
91.7
89.7
87.8
85.8
83.9
82.0
100.
100.
100.
100.
100.
100.
99.8
98.0
96.3
94.6
92.8
91.1
89.3
87.6
85.8
84.1
82.4
80.7
78.9
77.2
96.9
94.7
92.5
90.4
88.2
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
100.
99.5
97.5
95.5
93.4
91.4
89.4
87.4
85.4
83.3
The part in bolt is the flat rated zone; engine mechanical limit.
The part below is the area where the thermodynamical limit is reached first.
Note: Add 0.8% for each 10 kt above 125 kt without exceeding 100% torque
Eng : PW127M
Model : 212A
4.31
OPS DATA
13 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
110
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
105
(Flaps 0)
99
(Flaps 15)
126
(Flaps 0)
95
95
93
94
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.2
457
252
275
94.5
461
251
277
94.5
463
250
279
89.8
447
245
275
84.8
430
239
270
80.2
413
233
267
75.7
397
228
262
100
94.5
452
250
281
94.5
455
249
283
90.8
442
245
280
86.2
426
239
276
81.4
409
233
272
76.9
393
227
268
72.7
378
222
264
120
94.2
448
248
287
90.6
434
243
284
86.7
420
238
281
82.8
406
233
278
78.5
391
228
274
74.2
376
222
270
70.2
362
217
266
140
90.1
430
241
288
86.8
415
237
286
83.5
403
233
284
79.8
388
228
280
76.1
376
223
277
72.1
362
218
273
68.1
347
212
269
160
85.6
409
235
289
83.0
398
231
287
79.9
384
227
285
76.7
372
223
282
73.2
359
218
279
69.8
347
213
276
66.0
333
208
271
80.6
386
227
289
75.1
361
219
287
78.1
375
224
287
72.8
350
216
286
75.5
363
220
285
70.5
340
212
284
72.6
351
216
283
68.1
329
209
282
69.5
340
212
280
65.5
319
205
279
66.3
327
207
276
62.6
308
200
276
63.0
316
202
272
59.7
298
195
272
220
69.7
336
211
286
67.7
326
208
284
65.6
317
204
283
63.5
308
201
281
61.3
298
197
278
58.9
289
193
275
56.2
279
188
271
240
64.6
312
203
284
62.8
303
199
282
60.9
295
196
281
59.0
287
192
278
57.1
278
189
276
55.0
270
185
273
52.8
262
180
269
250
62.1
300
199
283
60.3
292
195
281
58.6
284
192
279
56.8
276
188
277
54.9
268
184
274
53.0
260
181
271
51.0
253
176
268
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.31
OPS DATA
R
13 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
110
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
105
(Flaps 0)
99
(Flaps 15)
126
(Flaps 0)
VmHB
95
95
(Flaps 30)
VGA
GO AROUND
93*
94*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.2
457
252
275
94.5
461
251
277
94.5
463
250
279
89.8
447
245
275
84.8
430
239
270
80.2
413
233
267
75.7
397
228
262
100
94.5
452
250
281
94.5
455
249
283
90.8
442
245
280
86.2
426
239
276
81.4
409
233
272
76.9
393
227
268
72.7
378
222
264
120
94.2
448
248
287
90.6
434
243
284
86.7
420
238
281
82.8
406
233
278
78.5
391
228
274
74.2
376
222
270
70.2
362
217
266
140
90.1
430
241
288
86.8
415
237
286
83.5
403
233
284
79.8
388
228
280
76.1
376
223
277
72.1
362
218
273
68.1
347
212
269
160
85.6
409
235
289
83.0
398
231
287
79.9
384
227
285
76.7
372
223
282
73.2
359
218
279
69.8
347
213
276
66.0
333
208
271
80.6
386
227
289
75.1
361
219
287
78.1
375
224
287
72.8
350
216
286
75.5
363
220
285
70.5
340
212
284
72.6
351
216
283
68.1
329
209
282
69.5
340
212
280
65.5
319
205
279
66.3
327
207
276
62.6
308
200
276
63.0
316
202
272
59.7
298
195
272
220
69.7
336
211
286
67.7
326
208
284
65.6
317
204
283
63.5
308
201
281
61.3
298
197
278
58.9
289
193
275
56.2
279
188
271
240
64.6
312
203
284
62.8
303
199
282
60.9
295
196
281
59.0
287
192
278
57.1
278
189
276
55.0
270
185
273
52.8
262
180
269
250
62.1
300
199
283
60.3
292
195
281
58.6
284
192
279
56.8
276
188
277
54.9
268
184
274
53.0
260
181
271
51.0
253
176
268
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.32
OPS DATA
14 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
110
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
109
(Flaps 0)
103
(Flaps 15)
131
(Flaps 0)
95
95
97
97
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
252
275
94.5
461
251
277
94.5
463
250
278
89.8
447
244
274
84.7
429
238
270
80.2
413
233
266
75.7
397
227
262
100
94.5
452
250
281
94.5
455
249
283
90.8
442
244
280
86.1
426
239
276
81.3
409
233
272
76.8
393
227
267
72.7
378
222
263
120
94.1
447
247
286
90.6
434
243
284
86.6
420
238
281
82.7
406
233
278
78.5
391
227
274
74.2
376
222
269
70.2
362
217
265
140
90.1
429
241
288
86.8
415
237
285
83.5
403
233
283
79.8
388
228
280
76.1
376
223
277
72.0
361
217
272
68.1
347
212
268
160
85.6
409
234
288
82.9
397
231
287
79.8
384
226
284
76.6
372
222
282
73.2
359
217
278
69.7
346
212
275
66.0
333
207
270
80.5
386
227
288
75.0
361
219
287
78.0
375
223
286
72.7
350
215
285
75.4
363
220
285
70.4
340
212
283
72.5
351
215
282
68.0
329
208
281
69.4
339
211
279
65.4
319
204
278
66.3
327
206
275
62.5
308
199
275
63.0
316
201
271
59.6
297
194
270
220
69.6
335
210
285
67.6
326
207
283
65.5
317
203
281
63.4
308
200
279
61.1
298
196
277
58.7
289
191
273
56.1
279
187
269
240
64.4
311
202
282
62.6
303
198
281
60.8
294
195
279
58.8
286
191
277
56.9
278
187
274
54.8
269
183
270
52.6
261
179
267
250
62.0
300
197
281
60.2
291
194
279
58.4
283
190
277
56.6
275
187
275
54.7
267
183
272
52.9
260
179
269
50.8
252
175
265
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.32
OPS DATA
R
14 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
110
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
109
(Flaps 0)
103
(Flaps 15)
131
(Flaps 0)
VmHB
95
95
(Flaps 30)
VGA
GO AROUND
97*
97*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
252
275
94.5
461
251
277
94.5
463
250
278
89.8
447
244
274
84.7
429
238
270
80.2
413
233
266
75.7
397
227
262
100
94.5
452
250
281
94.5
455
249
283
90.8
442
244
280
86.1
426
239
276
81.3
409
233
272
76.8
393
227
267
72.7
378
222
263
120
94.1
447
247
286
90.6
434
243
284
86.6
420
238
281
82.7
406
233
278
78.5
391
227
274
74.2
376
222
269
70.2
362
217
265
140
90.1
429
241
288
86.8
415
237
285
83.5
403
233
283
79.8
388
228
280
76.1
376
223
277
72.0
361
217
272
68.1
347
212
268
160
85.6
409
234
288
82.9
397
231
287
79.8
384
226
284
76.6
372
222
282
73.2
359
217
278
69.7
346
212
275
66.0
333
207
270
80.5
386
227
288
75.0
361
219
287
78.0
375
223
286
72.7
350
215
285
75.4
363
220
285
70.4
340
212
283
72.5
351
215
282
68.0
329
208
281
69.4
339
211
279
65.4
319
204
278
66.3
327
206
275
62.5
308
199
275
63.0
316
201
271
59.6
297
194
270
220
69.6
335
210
285
67.6
326
207
283
65.5
317
203
281
63.4
308
200
279
61.1
298
196
277
58.7
289
191
273
56.1
279
187
269
240
64.4
311
202
282
62.6
303
198
281
60.8
294
195
279
58.8
286
191
277
56.9
278
187
274
54.8
269
183
270
52.6
261
179
267
250
62.0
300
197
281
60.2
291
194
279
58.4
283
190
277
56.6
275
187
275
54.7
267
183
272
52.9
260
179
269
50.8
252
175
265
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.33
OPS DATA
15 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
114
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
114
(Flaps 0)
107
(Flaps 15)
136
(Flaps 0)
95
97
100
101
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
252
275
94.5
461
251
276
94.5
463
250
278
89.7
447
244
274
84.7
429
238
270
80.1
413
232
266
75.7
397
227
261
100
94.5
453
250
281
94.5
455
249
282
90.7
441
244
279
86.1
426
238
276
81.3
409
232
271
76.8
393
227
267
72.6
378
221
263
120
94.1
447
247
286
90.6
434
243
284
86.6
419
238
281
82.7
406
233
277
78.4
391
227
273
74.1
376
221
269
70.1
362
216
265
140
90.0
429
241
287
86.8
415
236
285
83.4
402
232
283
79.7
388
227
279
76.1
375
222
276
72.0
361
217
271
68.0
347
211
267
160
85.5
409
234
288
82.9
397
230
286
79.8
383
226
284
76.6
372
222
281
73.1
358
217
278
69.7
346
212
274
65.9
333
206
269
80.5
386
226
287
74.9
360
218
286
77.9
374
223
286
72.6
349
214
284
75.3
363
219
284
70.3
339
211
282
72.4
351
215
281
67.9
329
207
280
69.4
339
210
278
65.2
319
203
277
66.2
327
205
274
62.4
308
198
273
62.9
316
200
269
59.5
297
193
269
220
69.5
335
209
283
67.5
325
206
282
65.4
316
202
280
63.3
307
199
278
61.0
297
194
275
58.6
289
190
271
56.0
278
185
267
240
64.3
310
201
281
62.4
302
197
279
60.6
294
193
277
58.6
285
190
274
56.7
277
186
271
54.6
269
181
268
52.5
261
177
264
250
61.8
299
196
279
60.0
290
192
277
58.2
282
189
275
56.4
275
185
272
54.5
267
181
269
52.7
259
177
266
50.6
252
173
262
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.33
OPS DATA
R
15 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
114
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
114
(Flaps 0)
107
(Flaps 15)
136
(Flaps 0)
VmHB
95
97
(Flaps 30)
VGA
GO AROUND
100*
101*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
252
275
94.5
461
251
276
94.5
463
250
278
89.7
447
244
274
84.7
429
238
270
80.1
413
232
266
75.7
397
227
261
100
94.5
453
250
281
94.5
455
249
282
90.7
441
244
279
86.1
426
238
276
81.3
409
232
271
76.8
393
227
267
72.6
378
221
263
120
94.1
447
247
286
90.6
434
243
284
86.6
419
238
281
82.7
406
233
277
78.4
391
227
273
74.1
376
221
269
70.1
362
216
265
140
90.0
429
241
287
86.8
415
236
285
83.4
402
232
283
79.7
388
227
279
76.1
375
222
276
72.0
361
217
271
68.0
347
211
267
160
85.5
409
234
288
82.9
397
230
286
79.8
383
226
284
76.6
372
222
281
73.1
358
217
278
69.7
346
212
274
65.9
333
206
269
80.5
386
226
287
74.9
360
218
286
77.9
374
223
286
72.6
349
214
284
75.3
363
219
284
70.3
339
211
282
72.4
351
215
281
67.9
329
207
280
69.4
339
210
278
65.2
319
203
277
66.2
327
205
274
62.4
308
198
273
62.9
316
200
269
59.5
297
193
269
220
69.5
335
209
283
67.5
325
206
282
65.4
316
202
280
63.3
307
199
278
61.0
297
194
275
58.6
289
190
271
56.0
278
185
267
240
64.3
310
201
281
62.4
302
197
279
60.6
294
193
277
58.6
285
190
274
56.7
277
186
271
54.6
269
181
268
52.5
261
177
264
250
61.8
299
196
279
60.0
290
192
277
58.2
282
189
275
56.4
275
185
272
54.5
267
181
269
52.7
259
177
266
50.6
252
173
262
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.34
OPS DATA
16 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
118
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
118
(Flaps 0)
111
(Flaps 15)
140
(Flaps 0)
95
100
103
104
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
275
94.5
461
250
276
94.5
463
249
278
89.7
447
244
274
84.7
429
238
269
80.1
413
232
265
75.6
397
226
261
100
94.5
453
249
280
94.5
455
248
282
90.7
441
243
279
86.1
426
238
275
81.3
409
232
271
76.8
393
226
266
72.6
378
220
262
120
94.1
447
247
285
90.5
434
242
283
86.6
419
237
280
82.6
406
232
277
78.4
391
226
272
74.1
376
221
268
70.1
362
215
264
140
90.0
429
240
287
86.7
414
236
284
83.4
402
232
282
79.6
388
227
279
76.0
375
221
275
72.0
361
216
270
68.0
347
210
266
160
85.5
409
233
287
82.8
397
230
285
79.7
383
225
283
76.5
371
221
280
73.1
358
216
276
69.6
346
211
272
65.9
333
205
268
80.3
385
226
286
74.8
360
217
285
77.8
374
222
285
72.5
349
213
283
75.2
363
218
283
70.2
339
210
281
72.3
350
214
280
67.7
328
206
278
69.3
339
209
276
65.1
318
201
275
66.1
327
204
272
62.3
307
196
271
62.8
315
198
268
59.4
297
191
266
220
69.3
334
208
282
67.3
325
205
280
65.2
316
201
278
63.1
306
197
276
60.8
297
193
273
58.4
288
188
269
55.9
278
183
264
240
64.1
310
199
279
62.2
301
196
277
60.4
293
192
274
58.4
285
188
272
56.5
276
184
269
54.5
268
180
265
52.3
260
175
261
250
61.6
298
195
277
59.7
290
191
275
58.0
282
187
272
56.2
274
183
270
54.3
266
179
267
52.5
259
175
263
50.4
251
170
259
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.34
OPS DATA
R
16 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
118
(Flaps 0)
110
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
118
(Flaps 0)
111
(Flaps 15)
140
(Flaps 0)
VmHB
95
100
(Flaps 30)
VGA
GO AROUND
103*
104*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
275
94.5
461
250
276
94.5
463
249
278
89.7
447
244
274
84.7
429
238
269
80.1
413
232
265
75.6
397
226
261
100
94.5
453
249
280
94.5
455
248
282
90.7
441
243
279
86.1
426
238
275
81.3
409
232
271
76.8
393
226
266
72.6
378
220
262
120
94.1
447
247
285
90.5
434
242
283
86.6
419
237
280
82.6
406
232
277
78.4
391
226
272
74.1
376
221
268
70.1
362
215
264
140
90.0
429
240
287
86.7
414
236
284
83.4
402
232
282
79.6
388
227
279
76.0
375
221
275
72.0
361
216
270
68.0
347
210
266
160
85.5
409
233
287
82.8
397
230
285
79.7
383
225
283
76.5
371
221
280
73.1
358
216
276
69.6
346
211
272
65.9
333
205
268
80.3
385
226
286
74.8
360
217
285
77.8
374
222
285
72.5
349
213
283
75.2
363
218
283
70.2
339
210
281
72.3
350
214
280
67.7
328
206
278
69.3
339
209
276
65.1
318
201
275
66.1
327
204
272
62.3
307
196
271
62.8
315
198
268
59.4
297
191
266
220
69.3
334
208
282
67.3
325
205
280
65.2
316
201
278
63.1
306
197
276
60.8
297
193
273
58.4
288
188
269
55.9
278
183
264
240
64.1
310
199
279
62.2
301
196
277
60.4
293
192
274
58.4
285
188
272
56.5
276
184
269
54.5
268
180
265
52.3
260
175
261
250
61.6
298
195
277
59.7
290
191
275
58.0
282
187
272
56.2
274
183
270
54.3
266
179
267
52.5
259
175
263
50.4
251
170
259
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.35
OPS DATA
17 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
121
(Flaps 0)
111
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
121
(Flaps 0)
115
(Flaps 15)
145
(Flaps 0)
96
104
107
108
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
274
94.5
461
250
276
94.5
463
249
277
89.7
447
243
273
84.6
429
237
269
80.0
413
231
264
75.6
397
225
260
100
94.5
453
249
280
94.5
455
248
281
90.7
441
243
279
86.0
425
237
274
81.2
409
231
270
76.7
393
225
265
72.5
378
220
261
120
94.0
447
246
285
90.5
434
242
283
86.5
419
237
279
82.6
405
231
276
78.3
391
226
272
74.0
376
220
267
70.0
362
214
262
140
89.9
429
240
286
86.6
414
235
284
83.3
402
231
281
79.6
388
226
278
75.9
375
221
274
71.9
361
215
269
67.9
347
209
264
160
85.4
408
233
286
82.7
397
229
285
79.6
383
224
282
76.4
371
220
279
73.0
358
215
275
69.5
346
210
271
65.8
333
204
266
80.2
385
225
285
74.6
359
216
283
77.7
374
221
283
72.3
348
212
281
75.1
362
217
281
70.0
338
208
279
72.2
350
213
278
67.6
328
204
276
69.1
338
208
275
64.9
318
200
273
65.9
326
203
271
62.1
307
195
269
62.7
315
197
266
59.2
296
190
264
220
69.1
333
207
280
67.1
324
203
278
65.0
315
199
276
62.9
306
195
273
60.7
296
191
270
58.3
288
187
266
55.7
278
181
262
240
63.8
309
197
277
62.0
300
194
274
60.2
292
190
272
58.2
284
186
269
56.3
275
182
266
54.2
268
177
262
52.1
260
172
257
250
61.3
297
193
275
59.5
289
189
272
57.7
281
185
269
55.9
273
181
266
54.1
265
177
263
52.2
258
172
259
50.1
250
167
254
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.35
OPS DATA
R
17 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
104
110
FINAL TAKE OFF
VFTO
121
(Flaps 0)
111
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
121
(Flaps 0)
115
(Flaps 15)
145
(Flaps 0)
VmHB
96
104
(Flaps 30)
VGA
GO AROUND
107*
108*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
274
94.5
461
250
276
94.5
463
249
277
89.7
447
243
273
84.6
429
237
269
80.0
413
231
264
75.6
397
225
260
100
94.5
453
249
280
94.5
455
248
281
90.7
441
243
279
86.0
425
237
274
81.2
409
231
270
76.7
393
225
265
72.5
378
220
261
120
94.0
447
246
285
90.5
434
242
283
86.5
419
237
279
82.6
405
231
276
78.3
391
226
272
74.0
376
220
267
70.0
362
214
262
140
89.9
429
240
286
86.6
414
235
284
83.3
402
231
281
79.6
388
226
278
75.9
375
221
274
71.9
361
215
269
67.9
347
209
264
160
85.4
408
233
286
82.7
397
229
285
79.6
383
224
282
76.4
371
220
279
73.0
358
215
275
69.5
346
210
271
65.8
333
204
266
80.2
385
225
285
74.6
359
216
283
77.7
374
221
283
72.3
348
212
281
75.1
362
217
281
70.0
338
208
279
72.2
350
213
278
67.6
328
204
276
69.1
338
208
275
64.9
318
200
273
65.9
326
203
271
62.1
307
195
269
62.7
315
197
266
59.2
296
190
264
220
69.1
333
207
280
67.1
324
203
278
65.0
315
199
276
62.9
306
195
273
60.7
296
191
270
58.3
288
187
266
55.7
278
181
262
240
63.8
309
197
277
62.0
300
194
274
60.2
292
190
272
58.2
284
186
269
56.3
275
182
266
54.2
268
177
262
52.1
260
172
257
250
61.3
297
193
275
59.5
289
189
272
57.7
281
185
269
55.9
273
181
266
54.1
265
177
263
52.2
258
172
259
50.1
250
167
254
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.36
OPS DATA
18 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
107
111
FINAL TAKE OFF
VFTO
125
(Flaps 0)
115
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
125
(Flaps 0)
118
(Flaps 15)
149
(Flaps 0)
99
107
110
111
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
274
94.5
461
250
275
94.5
463
249
277
89.6
447
243
273
84.6
429
236
268
80.0
413
231
264
75.5
397
225
259
100
94.5
453
249
279
94.5
455
248
281
90.6
441
243
278
86.0
425
237
274
81.2
409
230
269
76.6
393
224
264
72.5
378
219
260
120
93.9
447
246
284
90.4
434
241
282
86.5
419
236
279
82.5
405
231
275
78.3
391
225
271
74.0
376
219
266
70.0
361
213
261
140
89.8
429
239
285
86.5
414
235
283
83.2
402
230
280
79.5
388
225
277
75.8
375
220
273
71.8
361
214
268
67.8
347
208
263
160
85.3
408
232
285
82.6
397
228
284
79.5
383
224
281
76.3
371
219
278
72.9
358
214
274
69.4
346
208
269
65.7
333
203
264
80.1
384
224
284
74.4
358
215
282
77.5
373
220
282
72.1
348
211
279
74.9
362
216
280
69.8
338
207
277
72.0
349
211
277
67.4
327
203
274
69.0
338
206
273
64.8
317
198
271
65.8
326
201
269
62.0
307
193
267
62.6
315
196
264
59.1
296
188
262
220
68.9
333
205
278
66.9
323
202
276
64.8
314
198
274
62.7
305
194
271
60.5
296
189
268
58.1
287
184
263
55.5
277
179
258
240
63.6
308
196
274
61.7
299
192
272
59.9
291
188
269
57.9
283
184
266
56.0
275
179
262
54.0
267
174
258
51.8
259
169
252
250
61.1
296
191
272
59.2
288
187
269
57.4
280
183
266
55.6
272
178
263
53.8
264
174
259
51.9
257
169
254
49.8
249
163
248
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.36
OPS DATA
R
18 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
107
111
FINAL TAKE OFF
VFTO
125
(Flaps 0)
115
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
125
(Flaps 0)
118
(Flaps 15)
149
(Flaps 0)
VmHB
99
107
(Flaps 30)
VGA
GO AROUND
110*
111*
(Flaps 15)
* VGA must not be less than 1.1 VMCA IAS (refer to page 4.64)
FINAL APPROACH
FLIGHT
LEVEL
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
251
274
94.5
461
250
275
94.5
463
249
277
89.6
447
243
273
84.6
429
236
268
80.0
413
231
264
75.5
397
225
259
100
94.5
453
249
279
94.5
455
248
281
90.6
441
243
278
86.0
425
237
274
81.2
409
230
269
76.6
393
224
264
72.5
378
219
260
120
93.9
447
246
284
90.4
434
241
282
86.5
419
236
279
82.5
405
231
275
78.3
391
225
271
74.0
376
219
266
70.0
361
213
261
140
89.8
429
239
285
86.5
414
235
283
83.2
402
230
280
79.5
388
225
277
75.8
375
220
273
71.8
361
214
268
67.8
347
208
263
160
85.3
408
232
285
82.6
397
228
284
79.5
383
224
281
76.3
371
219
278
72.9
358
214
274
69.4
346
208
269
65.7
333
203
264
80.1
384
224
284
74.4
358
215
282
77.5
373
220
282
72.1
348
211
279
74.9
362
216
280
69.8
338
207
277
72.0
349
211
277
67.4
327
203
274
69.0
338
206
273
64.8
317
198
271
65.8
326
201
269
62.0
307
193
267
62.6
315
196
264
59.1
296
188
262
220
68.9
333
205
278
66.9
323
202
276
64.8
314
198
274
62.7
305
194
271
60.5
296
189
268
58.1
287
184
263
55.5
277
179
258
240
63.6
308
196
274
61.7
299
192
272
59.9
291
188
269
57.9
283
184
266
56.0
275
179
262
54.0
267
174
258
51.8
259
169
252
250
61.1
296
191
272
59.2
288
187
269
57.4
280
183
266
55.6
272
178
263
53.8
264
174
259
51.9
257
169
254
49.8
249
163
248
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.37
OPS DATA
19 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
110
114
FINAL TAKE OFF
VFTO
129
(Flaps 0)
119
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
129
(Flaps 0)
121
(Flaps 15)
153
(Flaps 0)
102
109
113
114
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
250
273
94.5
461
249
275
94.5
464
248
276
89.6
447
242
272
84.5
429
236
267
79.9
413
230
263
75.5
397
224
258
100
94.5
453
248
279
94.5
455
247
280
90.5
441
242
277
85.9
425
236
273
81.1
409
230
268
76.6
393
224
263
72.4
377
218
259
120
93.9
447
245
284
90.3
434
240
281
86.4
419
235
278
82.4
405
230
274
78.2
391
224
269
73.9
376
218
265
69.9
361
212
260
140
89.7
428
238
284
86.5
414
234
282
83.1
402
229
279
79.4
388
224
275
75.8
375
219
271
71.7
361
213
266
67.8
347
207
261
160
85.1
408
231
284
82.5
396
227
282
79.4
382
223
279
76.2
371
218
276
72.8
357
212
272
69.4
346
207
268
65.6
333
201
263
79.9
384
223
283
74.2
358
213
280
77.3
372
219
281
71.9
347
209
278
74.8
361
214
278
69.6
337
205
275
71.9
349
210
275
67.2
327
201
272
68.8
338
205
271
64.6
317
196
269
65.7
326
200
267
61.8
306
191
264
62.4
315
194
262
58.9
296
185
259
220
68.7
332
204
276
66.7
323
200
274
64.6
313
196
271
62.4
304
192
268
60.2
295
187
265
57.8
286
182
260
55.2
276
176
254
240
63.3
307
194
271
61.4
298
190
269
59.6
290
186
266
57.7
282
181
262
55.7
273
176
258
53.6
266
171
253
51.4
258
165
246
250
60.8
295
189
269
58.9
286
184
266
57.1
279
180
262
55.3
271
175
258
53.4
263
170
253
51.5
256
164
248
49.4
248
158
240
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.37
OPS DATA
R
19 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
104
110
110
114
FINAL TAKE OFF
VFTO
129
(Flaps 0)
119
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
129
(Flaps 0)
121
(Flaps 15)
153
(Flaps 0)
102
109
113
114
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
458
250
273
94.5
461
249
275
94.5
464
248
276
89.6
447
242
272
84.5
429
236
267
79.9
413
230
263
75.5
397
224
258
100
94.5
453
248
279
94.5
455
247
280
90.5
441
242
277
85.9
425
236
273
81.1
409
230
268
76.6
393
224
263
72.4
377
218
259
120
93.9
447
245
284
90.3
434
240
281
86.4
419
235
278
82.4
405
230
274
78.2
391
224
269
73.9
376
218
265
69.9
361
212
260
140
89.7
428
238
284
86.5
414
234
282
83.1
402
229
279
79.4
388
224
275
75.8
375
219
271
71.7
361
213
266
67.8
347
207
261
160
85.1
408
231
284
82.5
396
227
282
79.4
382
223
279
76.2
371
218
276
72.8
357
212
272
69.4
346
207
268
65.6
333
201
263
79.9
384
223
283
74.2
358
213
280
77.3
372
219
281
71.9
347
209
278
74.8
361
214
278
69.6
337
205
275
71.9
349
210
275
67.2
327
201
272
68.8
338
205
271
64.6
317
196
269
65.7
326
200
267
61.8
306
191
264
62.4
315
194
262
58.9
296
185
259
220
68.7
332
204
276
66.7
323
200
274
64.6
313
196
271
62.4
304
192
268
60.2
295
187
265
57.8
286
182
260
55.2
276
176
254
240
63.3
307
194
271
61.4
298
190
269
59.6
290
186
266
57.7
282
181
262
55.7
273
176
258
53.6
266
171
253
51.4
258
165
246
250
60.8
295
189
269
58.9
286
184
266
57.1
279
180
262
55.3
271
175
258
53.4
263
170
253
51.5
256
164
248
49.4
248
158
240
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.38
OPS DATA
20 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
105
110
114
118
FINAL TAKE OFF
VFTO
132
(Flaps 0)
122
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
132
(Flaps 0)
125
(Flaps 15)
157
(Flaps 0)
105
114
117
118
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
250
273
94.5
461
249
274
94.5
464
248
276
89.5
447
241
271
84.4
429
235
266
79.9
412
229
262
75.4
396
223
257
100
94.5
453
247
278
94.5
455
246
280
90.4
441
241
276
85.8
425
235
272
81.0
409
229
267
76.5
392
222
262
72.3
377
216
257
120
93.8
446
244
283
90.2
433
240
280
86.3
419
234
277
82.4
405
229
273
78.1
390
223
268
73.9
376
217
263
69.8
361
211
258
140
89.6
428
237
283
86.3
413
233
281
83.0
401
228
278
79.3
387
223
274
75.7
374
217
270
71.7
361
211
265
67.7
347
205
260
160
85.0
407
230
283
82.3
396
226
281
79.2
382
221
278
76.1
370
216
275
72.6
357
211
270
69.3
345
206
266
65.5
332
199
261
79.7
383
221
281
74.0
357
212
278
77.1
372
217
279
71.7
346
208
276
74.6
361
213
276
69.4
336
204
273
71.7
348
208
273
67.0
326
199
270
68.7
337
203
269
64.4
316
194
266
65.5
325
198
264
61.6
305
189
261
62.3
314
192
259
58.7
295
183
255
220
68.4
331
202
274
66.4
322
198
271
64.3
313
194
268
62.2
303
189
265
60.0
294
185
261
57.5
285
179
256
54.9
276
172
249
240
63.0
306
191
268
61.1
297
187
265
59.3
289
183
262
57.3
281
178
257
55.3
272
172
252
53.2
265
166
246
50.9
256
159
238
250
60.4
294
186
265
58.5
285
181
261
56.7
277
176
257
54.8
269
171
252
52.9
261
165
246
50.9
254
158
238
48.7
246
149
227
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.38
OPS DATA
R
20 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
105
110
114
118
FINAL TAKE OFF
VFTO
132
(Flaps 0)
122
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
132
(Flaps 0)
125
(Flaps 15)
157
(Flaps 0)
105
114
117
118
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
250
273
94.5
461
249
274
94.5
464
248
276
89.5
447
241
271
84.4
429
235
266
79.9
412
229
262
75.4
396
223
257
100
94.5
453
247
278
94.5
455
246
280
90.4
441
241
276
85.8
425
235
272
81.0
409
229
267
76.5
392
222
262
72.3
377
216
257
120
93.8
446
244
283
90.2
433
240
280
86.3
419
234
277
82.4
405
229
273
78.1
390
223
268
73.9
376
217
263
69.8
361
211
258
140
89.6
428
237
283
86.3
413
233
281
83.0
401
228
278
79.3
387
223
274
75.7
374
217
270
71.7
361
211
265
67.7
347
205
260
160
85.0
407
230
283
82.3
396
226
281
79.2
382
221
278
76.1
370
216
275
72.6
357
211
270
69.3
345
206
266
65.5
332
199
261
79.7
383
221
281
74.0
357
212
278
77.1
372
217
279
71.7
346
208
276
74.6
361
213
276
69.4
336
204
273
71.7
348
208
273
67.0
326
199
270
68.7
337
203
269
64.4
316
194
266
65.5
325
198
264
61.6
305
189
261
62.3
314
192
259
58.7
295
183
255
220
68.4
331
202
274
66.4
322
198
271
64.3
313
194
268
62.2
303
189
265
60.0
294
185
261
57.5
285
179
256
54.9
276
172
249
240
63.0
306
191
268
61.1
297
187
265
59.3
289
183
262
57.3
281
178
257
55.3
272
172
252
53.2
265
166
246
50.9
256
159
238
250
60.4
294
186
265
58.5
285
181
261
56.7
277
176
257
54.8
269
171
252
52.9
261
165
246
50.9
254
158
238
48.7
246
149
227
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.39
OPS DATA
21 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
108
111
117
121
FINAL TAKE OFF
VFTO
136
(Flaps 0)
125
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
136
(Flaps 0)
128
(Flaps 15)
161
(Flaps 0)
108
117
120
121
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
249
272
94.5
461
248
273
94.5
464
247
275
89.4
446
241
270
84.4
429
234
265
79.8
412
228
260
75.3
396
222
255
100
94.5
453
247
277
94.5
456
246
279
90.3
440
240
275
85.7
425
234
271
80.9
408
228
266
76.4
392
221
261
72.2
377
215
256
120
93.7
446
243
282
90.1
433
239
279
86.2
418
233
276
82.3
405
228
271
78.1
390
222
267
73.8
376
215
262
69.8
361
209
257
140
89.5
428
237
282
86.2
413
232
280
82.9
401
227
277
79.2
387
222
272
75.5
374
216
268
71.6
361
210
263
67.6
347
204
258
160
84.8
407
229
282
82.2
395
225
279
79.1
381
220
276
76.0
370
215
273
72.5
357
210
269
69.2
345
204
264
65.4
332
198
258
79.5
382
220
279
73.8
356
210
276
76.9
371
216
277
71.5
346
206
273
74.4
360
212
274
69.1
336
202
270
71.5
348
207
271
66.8
325
197
267
68.5
337
202
267
64.1
315
192
263
65.3
325
196
262
61.4
305
186
257
62.1
314
190
256
58.4
294
180
251
220
68.1
330
200
271
66.1
320
196
268
64.0
312
191
265
61.8
302
187
261
59.6
293
181
256
57.2
284
175
250
54.6
275
167
242
240
62.6
304
189
265
60.7
296
184
261
58.8
288
179
257
56.8
279
173
251
54.8
270
167
245
52.6
263
159
236
50.1
254
148
222
250
60.0
292
182
260
58.0
283
177
256
56.1
275
172
250
54.2
267
165
244
52.1
258
157
234
49.8
251
145
219
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.39
OPS DATA
R
21 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
108
111
117
121
FINAL TAKE OFF
VFTO
136
(Flaps 0)
125
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
136
(Flaps 0)
128
(Flaps 15)
161
(Flaps 0)
108
117
120
121
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
249
272
94.5
461
248
273
94.5
464
247
275
89.4
446
241
270
84.4
429
234
265
79.8
412
228
260
75.3
396
222
255
100
94.5
453
247
277
94.5
456
246
279
90.3
440
240
275
85.7
425
234
271
80.9
408
228
266
76.4
392
221
261
72.2
377
215
256
120
93.7
446
243
282
90.1
433
239
279
86.2
418
233
276
82.3
405
228
271
78.1
390
222
267
73.8
376
215
262
69.8
361
209
257
140
89.5
428
237
282
86.2
413
232
280
82.9
401
227
277
79.2
387
222
272
75.5
374
216
268
71.6
361
210
263
67.6
347
204
258
160
84.8
407
229
282
82.2
395
225
279
79.1
381
220
276
76.0
370
215
273
72.5
357
210
269
69.2
345
204
264
65.4
332
198
258
79.5
382
220
279
73.8
356
210
276
76.9
371
216
277
71.5
346
206
273
74.4
360
212
274
69.1
336
202
270
71.5
348
207
271
66.8
325
197
267
68.5
337
202
267
64.1
315
192
263
65.3
325
196
262
61.4
305
186
257
62.1
314
190
256
58.4
294
180
251
220
68.1
330
200
271
66.1
320
196
268
64.0
312
191
265
61.8
302
187
261
59.6
293
181
256
57.2
284
175
250
54.6
275
167
242
240
62.6
304
189
265
60.7
296
184
261
58.8
288
179
257
56.8
279
173
251
54.8
270
167
245
52.6
263
159
236
50.1
254
148
222
250
60.0
292
182
260
58.0
283
177
256
56.1
275
172
250
54.2
267
165
244
52.1
258
157
234
49.8
251
145
219
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.40
OPS DATA
21.5 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
109
113
119
122
FINAL TAKE OFF
VFTO
138
(Flaps 0)
126
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
138
(Flaps 0)
129
(Flaps 15)
163
(Flaps 0)
109
119
121
122
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
249
272
94.5
461
248
273
94.5
464
247
274
89.4
446
240
270
84.3
429
234
265
79.8
412
227
260
75.3
396
221
255
100
94.5
453
246
277
94.5
456
245
279
90.3
440
240
275
85.7
425
234
270
80.9
408
227
265
76.4
392
221
260
72.2
377
214
255
120
93.6
446
243
281
90.1
433
238
279
86.1
418
233
275
82.2
405
227
271
78.0
390
221
266
73.7
375
215
261
69.7
361
209
256
140
89.4
427
236
282
86.2
413
231
279
82.8
401
226
276
79.1
387
221
272
75.5
374
215
267
71.5
361
209
262
67.6
346
203
257
160
84.8
406
228
281
82.1
395
224
279
79.0
381
219
275
75.9
370
214
272
72.5
357
209
268
69.1
345
203
263
65.3
332
197
257
79.4
382
219
278
73.6
355
209
275
76.8
371
215
276
71.3
345
205
272
74.3
360
211
273
69.0
335
201
269
71.4
348
206
270
66.7
325
196
266
68.4
337
201
266
64.0
315
191
261
65.2
324
195
260
61.2
304
185
255
62.0
314
188
254
58.3
294
178
248
220
68.0
329
199
269
65.9
320
195
267
63.8
311
190
263
61.7
302
185
259
59.4
293
179
254
56.9
284
172
247
54.3
274
164
237
240
62.4
303
187
262
60.5
295
182
258
58.6
287
177
254
56.5
278
171
248
54.4
269
163
239
52.2
262
154
228
250
59.8
291
181
258
57.7
282
175
252
55.8
274
169
246
53.8
266
161
237
51.5
256
150
224
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.40
OPS DATA
R
21.5 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
109
113
119
122
FINAL TAKE OFF
VFTO
138
(Flaps 0)
126
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
138
(Flaps 0)
129
(Flaps 15)
163
(Flaps 0)
109
119
121
122
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
249
272
94.5
461
248
273
94.5
464
247
274
89.4
446
240
270
84.3
429
234
265
79.8
412
227
260
75.3
396
221
255
100
94.5
453
246
277
94.5
456
245
279
90.3
440
240
275
85.7
425
234
270
80.9
408
227
265
76.4
392
221
260
72.2
377
214
255
120
93.6
446
243
281
90.1
433
238
279
86.1
418
233
275
82.2
405
227
271
78.0
390
221
266
73.7
375
215
261
69.7
361
209
256
140
89.4
427
236
282
86.2
413
231
279
82.8
401
226
276
79.1
387
221
272
75.5
374
215
267
71.5
361
209
262
67.6
346
203
257
160
84.8
406
228
281
82.1
395
224
279
79.0
381
219
275
75.9
370
214
272
72.5
357
209
268
69.1
345
203
263
65.3
332
197
257
79.4
382
219
278
73.6
355
209
275
76.8
371
215
276
71.3
345
205
272
74.3
360
211
273
69.0
335
201
269
71.4
348
206
270
66.7
325
196
266
68.4
337
201
266
64.0
315
191
261
65.2
324
195
260
61.2
304
185
255
62.0
314
188
254
58.3
294
178
248
220
68.0
329
199
269
65.9
320
195
267
63.8
311
190
263
61.7
302
185
259
59.4
293
179
254
56.9
284
172
247
54.3
274
164
237
240
62.4
303
187
262
60.5
295
182
258
58.6
287
177
254
56.5
278
171
248
54.4
269
163
239
52.2
262
154
228
250
59.8
291
181
258
57.7
282
175
252
55.8
274
169
246
53.8
266
161
237
51.5
256
150
224
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.41
OPS DATA
22 t
72
DEC 14 500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
111
114
120
123
FINAL TAKE OFF
VFTO
139
(Flaps 0)
128
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
139
(Flaps 0)
131
(Flaps 15)
165
(Flaps 0)
111
120
123
124
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
248
271
94.5
461
247
273
94.5
464
246
274
89.3
446
240
269
84.3
429
233
264
79.7
412
227
259
75.3
396
220
254
100
94.5
453
246
277
94.5
456
245
278
90.2
440
239
274
85.6
425
233
269
80.9
408
226
264
76.3
392
220
259
72.2
377
214
254
120
93.6
446
243
281
90.0
433
238
278
86.1
418
232
274
82.2
404
226
270
78.0
390
220
265
73.7
375
214
260
69.7
361
208
255
140
89.3
427
235
281
86.1
413
231
278
82.8
401
226
275
79.1
387
220
271
75.4
374
215
267
71.5
360
208
261
67.5
346
202
255
160
84.7
406
228
280
82.0
395
223
278
78.9
381
219
275
75.8
370
214
271
72.4
357
208
267
69.0
345
202
262
65.2
332
195
255
79.3
381
219
278
73.5
355
208
273
76.7
370
214
275
71.2
345
204
271
74.2
359
210
272
68.9
335
200
268
71.3
347
205
268
66.5
324
195
264
68.3
336
200
264
63.9
314
189
259
65.1
324
193
259
61.1
304
183
253
61.9
313
187
252
58.1
293
175
245
220
67.8
328
197
268
65.8
319
193
265
63.6
310
188
261
61.4
301
183
256
59.2
292
177
251
56.7
283
170
243
54.0
273
160
231
240
62.2
303
185
260
60.2
294
180
255
58.3
286
174
250
56.2
277
167
243
53.9
268
158
232
51.1
258
141
209
250
59.5
290
178
254
57.4
281
172
248
55.3
272
164
240
53.2
264
155
228
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.41
OPS DATA
R
22 t
72
JUL 15
500
Speeds
Normal
Icing
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
111
114
120
123
FINAL TAKE OFF
VFTO
139
(Flaps 0)
128
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
139
(Flaps 0)
131
(Flaps 15)
165
(Flaps 0)
111
120
123
124
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
80
94.5
459
248
271
94.5
461
247
273
94.5
464
246
274
89.3
446
240
269
84.3
429
233
264
79.7
412
227
259
75.3
396
220
254
100
94.5
453
246
277
94.5
456
245
278
90.2
440
239
274
85.6
425
233
269
80.9
408
226
264
76.3
392
220
259
72.2
377
214
254
120
93.6
446
243
281
90.0
433
238
278
86.1
418
232
274
82.2
404
226
270
78.0
390
220
265
73.7
375
214
260
69.7
361
208
255
140
89.3
427
235
281
86.1
413
231
278
82.8
401
226
275
79.1
387
220
271
75.4
374
215
267
71.5
360
208
261
67.5
346
202
255
160
84.7
406
228
280
82.0
395
223
278
78.9
381
219
275
75.8
370
214
271
72.4
357
208
267
69.0
345
202
262
65.2
332
195
255
79.3
381
219
278
73.5
355
208
273
76.7
370
214
275
71.2
345
204
271
74.2
359
210
272
68.9
335
200
268
71.3
347
205
268
66.5
324
195
264
68.3
336
200
264
63.9
314
189
259
65.1
324
193
259
61.1
304
183
253
61.9
313
187
252
58.1
293
175
245
220
67.8
328
197
268
65.8
319
193
265
63.6
310
188
261
61.4
301
183
256
59.2
292
177
251
56.7
283
170
243
54.0
273
160
231
240
62.2
303
185
260
60.2
294
180
255
58.3
286
174
250
56.2
277
167
243
53.9
268
158
232
51.1
258
141
209
250
59.5
290
178
254
57.4
281
172
248
55.3
272
164
240
53.2
264
155
228
180
200
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.42
OPS DATA
22.5 t
72
Speeds
DEC 14 500
Normal
Icing
Never exceed certified weight limitations
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
112
115
122
125
FINAL TAKE OFF
VFTO
140
(Flaps 0)
130
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
140
(Flaps 0)
133
(Flaps 15)
167
(Flaps 0)
113
122
124
125
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
94.5
459
248
271
94.5
453
246
276
94.5
461
247
272
94.5
456
245
278
94.5
464
246
274
90.2
440
239
274
89.3
446
239
269
85.6
424
232
269
84.2
428
233
263
80.8
408
226
264
79.7
412
226
258
76.3
392
219
258
75.2
396
220
253
72.1
377
213
253
120
93.5
446
242
280
89.9
433
237
277
86.0
418
232
273
82.1
404
226
269
77.9
390
220
265
73.7
375
213
259
69.6
361
207
254
140
89.2
427
235
280
86.0
412
230
277
82.7
401
225
274
79.0
387
219
270
75.4
374
214
266
71.4
360
208
260
67.5
346
201
254
160
84.6
406
227
279
81.9
394
223
277
78.8
381
218
274
75.7
369
213
270
72.3
356
207
265
68.9
345
201
260
65.1
331
194
254
180
79.2
381
218
277
76.6
370
213
274
74.1
359
209
271
71.2
347
204
267
68.2
336
198
263
65.0
324
192
257
61.8
313
185
250
200
73.4
354
207
272
71.0
344
203
269
68.7
334
199
266
66.4
324
194
262
63.7
314
188
257
60.9
304
181
250
57.9
293
173
241
67.6
328
196
266
61.9
302
183
257
65.6
318
192
263
59.9
293
178
252
63.4
310
186
258
57.9
284
171
246
61.2
300
181
253
55.7
275
162
236
59.0
291
174
247
53.1
265
149
219
56.4
282
166
237
53.6
272
154
223
59.2
289
176
251
57.0
279
168
243
54.7
270
158
232
80
100
220
240
250
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.42
OPS DATA
R
22.5 t
72
Speeds
JUL 15
Normal
500
Icing
Never exceed certified weight limitations
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
112
115
122
125
FINAL TAKE OFF
VFTO
140
(Flaps 0)
130
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
140
(Flaps 0)
133
(Flaps 15)
167
(Flaps 0)
113
122
124
125
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
94.5
459
248
271
94.5
453
246
276
94.5
461
247
272
94.5
456
245
278
94.5
464
246
274
90.2
440
239
274
89.3
446
239
269
85.6
424
232
269
84.2
428
233
263
80.8
408
226
264
79.7
412
226
258
76.3
392
219
258
75.2
396
220
253
72.1
377
213
253
120
93.5
446
242
280
89.9
433
237
277
86.0
418
232
273
82.1
404
226
269
77.9
390
220
265
73.7
375
213
259
69.6
361
207
254
140
89.2
427
235
280
86.0
412
230
277
82.7
401
225
274
79.0
387
219
270
75.4
374
214
266
71.4
360
208
260
67.5
346
201
254
160
84.6
406
227
279
81.9
394
223
277
78.8
381
218
274
75.7
369
213
270
72.3
356
207
265
68.9
345
201
260
65.1
331
194
254
180
79.2
381
218
277
76.6
370
213
274
74.1
359
209
271
71.2
347
204
267
68.2
336
198
263
65.0
324
192
257
61.8
313
185
250
200
73.4
354
207
272
71.0
344
203
269
68.7
334
199
266
66.4
324
194
262
63.7
314
188
257
60.9
304
181
250
57.9
293
173
241
67.6
328
196
266
61.9
302
183
257
65.6
318
192
263
59.9
293
178
252
63.4
310
186
258
57.9
284
171
246
61.2
300
181
253
55.7
275
162
236
59.0
291
174
247
53.1
265
149
219
56.4
282
166
237
53.6
272
154
223
59.2
289
176
251
57.0
279
168
243
54.7
270
158
232
80
100
220
240
250
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.43
OPS DATA
23 t
72
DEC 14 500
Speeds
Normal
Icing
Never exceed certified weight limitations
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
114
117
123
126
FINAL TAKE OFF
VFTO
141
(Flaps 0)
132
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
141
(Flaps 0)
135
(Flaps 15)
169
(Flaps 0)
115
124
126
127
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
94.5
459
248
271
94.5
453
246
276
94.5
461
247
272
94.5
456
245
278
94.5
464
246
274
90.2
440
239
274
89.3
446
239
269
85.6
424
232
269
84.2
428
233
263
80.8
408
226
264
79.7
412
226
258
76.3
392
219
258
75.2
396
220
253
72.1
377
213
253
120
93.5
446
242
280
89.9
433
237
277
86.0
418
232
273
82.1
404
226
269
77.9
390
220
265
73.7
375
213
259
69.6
361
207
254
140
89.2
427
235
280
86.0
412
230
277
82.7
401
225
274
79.0
387
219
270
75.4
374
214
266
71.4
360
208
260
67.5
346
201
254
160
84.6
406
227
279
81.9
394
223
277
78.8
381
218
274
75.7
369
213
270
72.3
356
207
265
68.9
345
201
260
65.1
331
194
254
180
79.2
381
218
277
76.6
370
213
274
74.1
359
209
271
71.2
347
204
267
68.2
336
198
263
65.0
324
192
257
61.8
313
185
250
200
73.4
354
207
272
71.0
344
203
269
68.7
334
199
266
66.4
324
194
262
63.7
314
188
257
60.9
304
181
250
57.9
293
173
241
67.6
328
196
266
61.9
302
183
257
65.6
318
192
263
59.9
293
178
252
63.4
310
186
258
57.9
284
171
246
61.2
300
181
253
55.7
275
162
236
59.0
291
174
247
53.1
265
149
219
56.4
282
166
237
53.6
272
154
223
59.2
289
176
251
57.0
279
168
243
54.7
270
158
232
80
100
220
240
250
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.43
OPS DATA
R
23 t
72
JUL 15
Speeds
Normal
500
Icing
Never exceed certified weight limitations
NON LIMITING RWY
TAKE-OFF
(Flaps 15)
V1 = VR
V2
114
117
123
126
FINAL TAKE OFF
VFTO
141
(Flaps 0)
132
(Flaps 15)
DRIFT DOWN
VmLB
MINI EN ROUTE
FINAL APPROACH
GO AROUND
FLIGHT
LEVEL
VmHB
(Flaps 30)
VGA
(Flaps 15)
141
(Flaps 0)
135
(Flaps 15)
169
(Flaps 0)
115
124
126
127
MAX CRUISE 2 ENGINES
∆ ISA
-10
-5
0
+5
+10
+15
+20
94.5
459
248
271
94.5
453
246
276
94.5
461
247
272
94.5
456
245
278
94.5
464
246
274
90.2
440
239
274
89.3
446
239
269
85.6
424
232
269
84.2
428
233
263
80.8
408
226
264
79.7
412
226
258
76.3
392
219
258
75.2
396
220
253
72.1
377
213
253
120
93.5
446
242
280
89.9
433
237
277
86.0
418
232
273
82.1
404
226
269
77.9
390
220
265
73.7
375
213
259
69.6
361
207
254
140
89.2
427
235
280
86.0
412
230
277
82.7
401
225
274
79.0
387
219
270
75.4
374
214
266
71.4
360
208
260
67.5
346
201
254
160
84.6
406
227
279
81.9
394
223
277
78.8
381
218
274
75.7
369
213
270
72.3
356
207
265
68.9
345
201
260
65.1
331
194
254
180
79.2
381
218
277
76.6
370
213
274
74.1
359
209
271
71.2
347
204
267
68.2
336
198
263
65.0
324
192
257
61.8
313
185
250
200
73.4
354
207
272
71.0
344
203
269
68.7
334
199
266
66.4
324
194
262
63.7
314
188
257
60.9
304
181
250
57.9
293
173
241
67.6
328
196
266
61.9
302
183
257
65.6
318
192
263
59.9
293
178
252
63.4
310
186
258
57.9
284
171
246
61.2
300
181
253
55.7
275
162
236
59.0
291
174
247
53.1
265
149
219
56.4
282
166
237
53.6
272
154
223
59.2
289
176
251
57.0
279
168
243
54.7
270
158
232
80
100
220
240
250
TQ % NP = 82 %
KG/H/ENG
IAS
TAS
NOT THERMO LIMITED
Model : 212A
4.61
OPS DATA
72
APR 08 500
For weight in KG, use white boxes.
For weight in LB, use shaded boxes.
PW127F / PW127M – BOOST OFF
SINGLE ENGINE GROSS CEILING (FT)
NORMAL CONDITIONS (FLAPS 0)
WEIGHT
x 1000 kg
ISA - 10
ISA
ISA + 10
ISA + 15
ISA + 20
WEIGHT
x 1000 lb
13.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
29
14.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 24900
31
15.0
25000 25000 25000 25000 24300 24400 23700 23700 23100 23100
33
16.0
25000 25000 23700 23900 22400 22700 21800 22000 21100 21400
35
17.0
23300 23700 22000 22300 20700 21000 20000 20400 19100 19500
37
18.0
21600 22100 20300 20800 18900 19400 18100 18700 17300 17800
39
19.0
20000 20600 18600 19300 17300 17900 16400 17000 15700 16300
41
20.0
18500 19200 17100 17900 15700 16500 14900 15600 14200 14900
43
21.0
17100 17600 15700 16500 14100 15100 13400 14300 12700 13600
45
22.0
15700 16600 14400 15300 12800 13700 12000 13000 11300 12300
47
22.5
15100 15400 13700 14100 12100 12400 11300 11700 10500 11000
49
-
-
15100
-
13700
-
12100
-
11300
-
10500
49.6
Model : 212A
4.61A
OPS DATA
72
OCT 08 500
For weight in KG, use white boxes.
For weight in LB, use shaded boxes.
PW127M – BOOST ON
SINGLE ENGINE GROSS CEILING (FT)
NORMAL CONDITIONS (FLAPS 0)
WEIGHT
x 1000 kg
ISA - 10
ISA
ISA + 10
ISA + 15
ISA + 20
WEIGHT
x 1000 lb
13.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
29
14.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
31
15.0
25000 25000 25000 25000 25000 25000 24400 24500 23800 23900
33
16.0
25000 25000 24500 24700 23200 23400 22500 22800 21900 22200
35
17.0
24100 24500 22700 23100 21400 21800 20800 21200 19900 20400
37
18.0
22400 22900 21000 21500 19700 20200 19000 19600 18100 18600
39
19.0
20800 21400 19400 20100 18100 18700 17200 17900 16500 17100
41
20.0
19300 20000 17900 18700 16500 17300 15700 16400 15000 15700
43
21.0
17800 18700 16500 17300 15000 15900 14200 15100 13500 14400
45
22.0
16500 17400 15100 16100 13600 14500 12900 13800 12100 13100
47
22.8
15500 16200 14100 14800 12500 13200 11800 12500 11000 11800
49
-
-
15600
-
14300
-
12600
Eng : PW127M
-
11900
-
11200
50
Model : 212A
4.62
OPS DATA
72
APR 08 500
For weight in KG, use white boxes.
For weight in LB, use shaded boxes.
PW127F / PW127M – BOOST OFF
SINGLE ENGINE GROSS CEILING (FT)
ICING CONDITIONS (FLAPS 15)
WEIGHT
x 1000 kg
ISA - 10
ISA
ISA + 10
ISA + 15
ISA + 20
WEIGHT
x 1000 lb
13.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
29
14.0
25000 25000 25000 25000 25000 25000 24800 24700 24200 24100
31
15.0
25000 25000 24700 24800 23500 23500 22800 22900 22200 22300
33
16.0
24300 24500 22900 23100 21600 21800 21000 21200 20200 20400
35
17.0
22500 22800 21100 21500 19800 20200 19100 19500 18200 18600
37
18.0
20700 21300 19400 19900 18000 18500 17200 17700 16400 17000
39
19.0
19000 19700 17700 18300 16300 17000 15400 16100 15100 15400
41
20.0
17400 18200 16100 16900 14600 15400 13900 14600
-
-
43
21.0
16000 16800 14600 15500 13100 13900 12600 13200
-
-
45
22.0
14600 15600 13300 14200 11700 12600
-
12600
-
-
47
22.5
14000 14300 12600 13000 11000 11300
-
-
-
-
47
-
-
-
-
48.5
-
-
14000
-
12600
-
11000
Note : When bolt-underlined figures, icing conditions do not exist.
Model : 212A
4.62A
OPS DATA
72
OCT 08 500
For weight in KG, use white boxes.
For weight in LB, use shaded boxes.
PW127M – BOOST ON
SINGLE ENGINE GROSS CEILING (FT)
ICING CONDITIONS (FLAPS 15)
WEIGHT
x 1000 kg
ISA - 10
ISA
ISA + 10
ISA + 15
ISA + 20
WEIGHT
x 1000 lb
13.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
29
14.0
25000 25000 25000 25000 25000 25000 25000 25000 25000 25000
31
15.0
25000 25000 25000 25000 24200 24300 23600 23600 22900 23000
33
16.0
25000 25000 23600 23800 22300 22600 21700 21900 21000 21200
35
17.0
23200 23600 21800 22200 20500 20900 19900 20300 19000 19400
37
18.0
21500 22000 20100 20700 18800 19300 18000 18600 17200 17700
39
19.0
19800 20500 18400 19100 17100 17800 16200 16900 15500 16200
41
20.0
18200 19000 16800 17600 15400 16300 14600 15400 15000 15100
43
21.0
16700 17600 15400 16200 13800 14800 13100 14000
-
-
45
22.0
15400 16300 14000 15000 12400 13400 12600 12700
-
-
47
22.8
14400 15100 13000 13700 11400 12100
-
-
14500
-
13100
-
11500
-
12500
-
-
49
-
-
-
-
50
Note : When bolt-underlined figures, icing conditions do not exist.
Eng : PW127M
Model : 212A
4.63
OPS DATA
72
SEP 10
500
PW127F / PW127M
REDUCED FLAPS
LANDING CONFIGURATION – VAPP (kt)
NOTE: For a go around flaps 15 configuration increase speed up to VmLB0
before selecting flaps 0
FLAPS 0
VmHB0 + 5 kt
FLAPS 15
VmHB15
KG
WEIGHT
(x 1000kg)
Normal
Icing
Normal
Icing
13
14
15
16
17
18
19
20
21
22
22.5 *
23 *
115
119
123
127
131
135
139
142
146
149
151
152
136
141
146
151
155
160
164
168
172
176
178
180
97
97
100
103
107
110
113
116
120
123
124
126
102
106
110
114
118
122
125
129
132
135
137
139
FLAPS 0
VmHB0 + 5 kt
FLAPS 15
VmHB15
Lb
WEIGHT
(x 1000Lb)
Normal
Icing
Normal
Icing
29
31
33
35
37
39
41
43
45
47
49
49.6 *
50.7 *
115
119
123
127
130
134
137
141
144
147
150
151
152
137
142
146
150
154
158
162
166
170
173
177
178
180
97
97
100
103
106
109
112
115
118
121
123
124
126
103
107
110
114
117
121
124
127
130
133
136
137
139
* Never exceed the certified Maximum Landing Weight
: PW127E
Eng :Eng
PW127F-PW127M
4.64
OPS DATA
72
OCT 08 500
PW127F / PW127M
1.1 VMCA IAS *
OAT °C
-30
-20
-10
0
+ 10
+ 20
+30
+ 40
+ 50
0
111
110
109
108
108
107
106
104
100
2000
109
108
108
107
106
105
104
101
97
4000
108
107
106
105
105
104
100
97
94
6000
106
106
105
104
103
100
97
94
91
8500
104
104
103
100
98
96
93
90
88
ZP (ft)
* Conservative values calculated for the maximum landing weight.
Model : 212A
4.64
OPS DATA
72
JUL 15
500
R
PW127F / PW127M
1.1 VMCA IAS *
OAT
°C
-50
-40
-30
-20
-10
0
+ 10
+ 20
+30
+ 40
+ 50
-1000
112
111
111
110
109
109
108
107
106
106
102
0
111
111
110
109
109
108
107
106
106
104
100
2000
110
110
109
108
107
106
106
105
104
100
97
4000
108
108
107
107
106
105
104
103
100
97
94
6000
107
107
106
105
104
103
102
99
97
94
91
8500
105
105
104
103
102
100
98
95
93
90
87
ZP (ft)
* Conservative values calculated for the maximum landing weight.
Legend :
Grey background = Out of operational envelope
Grey text color = Below Vmcl
Model : 212A
4.65
OPS DATA
72
SEP 10
600
PW127F / PW127M
ACTUAL LANDING DISTANCE (M) - SEA LEVEL
NORMAL CONDITIONS - FLAPS 30
15
16
17
18
19
20
21
22
22.5
23
570
570
570
570
570
590
610
630
650
670
680
700
WET
690
690
690
690
700
730
760
780
810
840
850
860
WATER
OR
SLUSH
<1/2 in
640
680
710
750
780
820
860
900
940
980 1000 1020
COMPACT
690
SNOW
720
760
790
830
860
900
930
970 1000 1020 1030
RUNWAY CONDITION
14
DRY
CONTAMINATED BY
R WEIGHT (1000 KG)
13
ICE
1010 1070 1120 1170 1230 1280 1340 1390 1450 1500 1530 1560
ICING CONDITIONS – FLAPS 30
RUNWAY CONDITION
CONTAMINATED BY
WEIGHT (1000 KG) 13
14
15
16
17
18
19
20
21
22
22.5
23
DRY
610
610
620
620
620
640
670
690
710
740
750
770
WET
760
760
760
760
770
800
830
860
890
920
940
950
WATER
OR
SLUSH
<1/2 in
700
740
780
820
860
900
950
990 1040 1080 1100 1130
COMPACT
760
SNOW
800
840
880
920
960 1000 1040 1080 1120 1140 1160
ICE
1140 1200 1260 1320 1390 1450 1520 1580 1640 1710 1740 1770
CORRECTION ON LANDING DISTANCES
-Wind
: • dry or wet runway
add 10% per 5 kt tailwind.
subtract 2% per 5 kt headwind.
• contaminated runway
add 16% per 5 kt tailwind.
subtract 2% per 5 kt headwind.
-Airport elevation : • dry or wet runway
add 3% per 1000 ft above sea level.
• contaminated runway
add 5% per 1000 ft above sea level.
-Effect of reverse : landing distances are decreased by :
• 2% on dry runway.
R
• 4% on wet runway.
• 8% on runway contaminated by water or slush.
• 10% on runway contaminated by compact snow.
• 30 % on runway contaminated by ice.
CAUTION: On contaminated runway, performances without reverser only are to
be used for flight preparation.
NOTE: Landing on damp runway.
A runway is damp when it is not perfectly dry, but when the water which is on it
does not give it a shiny appearance.
For damp runway, we consider no performance limitation.
Mod : 5561
Model : 212A
OPS DATA
72
4.66
DEC 14 001
LEFT INTENTIONALLY BLANK
4.67
OPS DATA
72
DEC 14 500
Maximum Landing Weight (Kg) limited by
maximum Brake Energy (8.3 MJ)
NORMAL CONDITIONS FLAPS 30°- Vref – Dry or Wet Run way – no wind
( * never exceed certified MLW)
Landing
ISA-30°C ISA-20°C ISA-10°C ISA
elevation
ISA+10°C ISA+20°C ISA+30°C ISA+40°C
8500 ft
23 100
22 600
22 200
21 800
21 400
21 000
20 700
20 300
7000 ft
23 700
23 200
22 700
22 300
21 900
21 600
21 200
20 800
5000 ft
24 400
24 000
23 500
23 100
22 700
22 300
21 900
21 500
3000 ft
25 200
24 800
24 300
23 900
23 500
23 100
22 600
22 300
1000 ft
26 100
25 600
25 100
24 700
24 300
23 800
23 400
23 000
0 ft
26 500
26 000
25 500
25 100
24 700
24 200
23 800
23 400
-1000 ft
26 900
26 400
26 000
25 600
25 100
24 600
24 200
23 800
Corrections on Weight limited by maximum brake energy at landing:
• Head wind: increase weight by 3% per 10kt
• Tail wind: decrease weight by 11% per 10kt
• Vref +10kt: decrease weight by 6%
• Icing conditions: decrease weight by 6%
• One brake inoperative: decrease weight by 13%
• Effect of reverse: increase weight by 2%
• Runway slope: - increase weight by 1% per 1% uphill slope
- decrease weight by 1% per 1% downhill slope
NORMAL CONDITIONS FLAPS 15°- Vref – Dry or Wet Run way – no wind
Landing
ISA-30°C ISA-20°C ISA-10°C ISA
elevation
ISA+10°C ISA+20°C ISA+30°C ISA+40°C
8500 ft
20 800
20 400
20 000
19 700
19 300
19 000
18 700
18 400
7000 ft
21 400
20 900
20 500
20 200
19 800
19 500
19 200
18 800
5000 ft
22 000
21 600
21 200
20 900
20 500
20 100
19 800
19 500
3000 ft
22 800
22 300
21 900
21 600
21 200
20 800
20 500
20 100
1000 ft
23 500
23 100
22 700
22 300
21 900
21 500
21 100
20 800
0 ft
23 900
23 400
23 000
22 600
22 200
21 900
21 500
21 100
-1000 ft
24 300
23 800
23 400
23 000
22 600
22 200
21 800
21 500
Corrections on Weight limited by maximum brake energy at landing:
• Head wind: increase weight by 4% per 10kt
• Tail wind: decrease weight by 13% per 10kt
• Vref +10kt: decrease weight by 7%
• Icing conditions: decrease weight by 7%
• Effect of reverse: increase weight by 3%
• Runway slope: - increase weight by 1% per 1% uphill slope
- decrease weight by 1% per 1% downhill slope
Model : 212A
4.68
OPS DATA
72
DEC 14 500
Maximum Landing Weight (Kg) limited by
maximum Brake Energy (8.3 MJ)
NORMAL CONDITIONS FLAPS 0°- Vref + 5kt – Dry or We t Runway – no wind
Landing
ISA-30°C ISA-20°C ISA-10°C ISA
elevation
ISA+10°C ISA+20°C ISA+30°C ISA+40°C
8500 ft
17 600
17 200
16 900
16 600
16 400
16 100
15 900
15 600
7000 ft
18 000
17 700
17 400
17 100
16 800
16 500
16 300
16 000
5000 ft
18 600
18 300
17 900
17 600
17 300
17 100
16 800
16 500
3000 ft
19 200
18 800
18 500
18 200
17 900
17 600
17 300
17 000
1000 ft
19 800
19 400
19 100
18 800
18 500
18 200
17 900
17 600
0 ft
20 100
19 700
19 400
19 100
18 800
18 500
18 100
17 900
-1000 ft
20 400
20 000
19 700
19 400
19 100
18 800
18 400
18 100
Corrections on Weight limited by maximum brake energy at landing:
• Head wind: increase weight by 4% per 10kt
• Tail wind: decrease weight by 15% per 10kt
• Vref +10kt: prohibited
• Icing conditions: decrease weight by 13%
• Effect of reverse: increase weight by 2%
• Runway slope: - increase weight by 1% per 1% uphill slope
- decrease weight by 1% per 1% downhill slope
Model : 212A
CHECK LIST
L.T.R.
72
List of Temporary Revisions
5.01
JUL 15
RO
TR
EDITION
DATE
DESTROYED
INSERTION
DATE
01
MAY 11
AT REV 32
DATED NOV 11
TR 16 ENV
02
JUN 12
AT REV 33
DATED SEP 13
TR 18 ENV
03
JUL 15
REASON
SEE RTR
104
CHECK LIST
R.T.R.
72
Reason of Temporary Revisions
5.02
JUL 15
001
ENV
TEMPORARY REVISION N°1 TO 18 ARE NO LONGER AVAILABL E
TR
EDITION
DATE
REASON
FOLLOWING FAILURES/ POWER
PLANT : SINGLE ENG OPERATION,
Procedure “V APP” reviewed
19
JUL 15
FOLLOWING FAILURES/ FLIGHT
CONTROL: Pitch disconnect, procedure
“At parking “reviewed
OPS DATA : Entirely Reviewed with go
Around Speed
AFFECTED PAGES
2.04
2.22
From 4.31 to 4.43
and 4.64
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S.N.T.P.
JUL 15
Please find below the list of the temporary pages created, suppressed or revised
Temporary revision N° 03 (JUL 15).
"F"=Facing
"A" = After
"ADD"=Add
"……" = Revised
Action
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** **
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** **
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4
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4
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4
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4
** **
064 500 JUL 15
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ADD
5 01 **
001 104 JUL 15
L.T.R.
ADD
5 02 **
001 001 JUL 15
R.T.R.
ADD
5 04 **
001 104 JUL 15
L.E.T.P.
End
Label
"DESTROY" = Destroy
"SEE VAL" = See Validation
Modification expression
MOD 3973 or 4371 or 4457
MOD 3529 or 3530
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L.E.T.P.
JUL 15
You must hold in your manual the following temporary pages
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P CH SE Page Seq Date
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TR03
2
**
**
004 500 JUL 15
ALL
MOD 3973 or 4371 or 4457
TR03
2
**
**
022 100 JUL 15
ALL
MOD 3529 or 3530
TR03
4
**
**
031 500 JUL 15
ALL
212A
TR03
4
**
**
032 500 JUL 15
ALL
212A
TR03
4
**
**
033 500 JUL 15
ALL
212A
TR03
4
**
**
034 500 JUL 15
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TR03
4
**
**
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TR03
4
**
**
036 500 JUL 15
ALL
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TR03
4
**
**
037 500 JUL 15
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TR03
4
**
**
038 500 JUL 15
ALL
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TR03
4
**
**
039 500 JUL 15
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TR03
4
**
**
040 500 JUL 15
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TR03
4
**
**
041 500 JUL 15
ALL
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TR03
4
**
**
042 500 JUL 15
ALL
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TR03
4
**
**
043 500 JUL 15
ALL
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TR03
4
**
**
064 500 JUL 15
ALL
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TR03
5 01 **
001 104 JUL 15
ALL
L.T.R.
TR19
5 02 **
001 001 JUL 15
ALL
R.T.R.
TR03
5 04 **
001 104 JUL 15
ALL
L.E.T.P.
End
RO
Modification expression
RO
RO
CHECK LIST
5.05
L.N.R.
72
DEC 14 001
List of Normal Revisions
REV
EDITION
DATE
INSERTION
DATE
00
OCT 89
01
DEC 89
02
MAR 90
03
NOV 90
04
MAY 91
05
NOV 91
06
MAY 92
07
NOV 92
TOTAL EDITION
08
MAY 93
TOTAL EDITION
09
NOV 93
TOTAL EDITION
10
JUN 94
11
DEC 94
12
JUN 95
13
DEC 95
14
JUN 96
15
DEC 96
16
JUN 97
17
DEC 97
18
JUL 98
19
JUL 99
20
JUL 00
21
JUL 01
22
SEP 02
23
SEP 03
24
SEP 04
25
SEP 05
26
SEP 06
27
SEP 07
28
APR 08
29
OCT 08
30
OCT 09
31
SEP 10
32
NOV 11
(Edited in MAR 12)
33
SEP 13
(Edited in JAN 14)
34
DEC 14
(Edited in MAR 15)
REMARKS
TOTAL WORD EDITION
CHECK LIST
R.N.R.
72
REV
EDITION
DATE
33
SEP 13
Reason of Normal Revisions
DEC 14 001
REASON FOR ISSUE
CHAP
INVOLVED
TR n°18: Banking:
- Some Emergency procedure update for 72-212A 1.02-1.02A-1.051.05A-1.06-1.08following AFM 72-212A revision.
1.08A-1.09-1.10
2.01.5002.13.500
- Fuel feed lo pr procedure updated
for 72-212A
2.13
EMERGENCY PROCEDURES ;
-Content page : Updated
- IN FLIGHT ENG FIRE OR SEVERE
MECHANICAL DAMAGE: Procedure improved
-ON GROUND ENG FIRE OR SEVERE
MECHANICAL DAMAGE : Procedure improved
- EMERGENCY DESCENT: Procedure updated
- DITCHING: Procedure reviewed( New variant)
- FORCED LANDING: Procedure reviewed( New
variant)
- SEVERE ICING: Procedure reviewed
- RECOVERY AFTER STALL and UNRELIABLE
AIRSPEED INDICATION: Procedure reviewed
PROCEDURES FOLLOWING FAILURES :
- AFR AIR BLEED FAULT : All variants reviewed
- EFIS COMP : Procedure updated
NORMAL PROCEDURES :
- BEFORE PROPELLER ROTATION : New variant
for the boost (Mod 5908)
- BEFORE LANDING: Procedure reviewed
- LANDING: Procedure reviewed
- ATPCS- Dynamic test : All variants reviewed
- CHECK LIST : All variants updated
34
DEC 14
5.06
OPS DATA : Reviewed with Go Around Speeds
Mod : 7055 Brake Energy – High Altitude runways
Operations
Brake Energy – Normal Altitude runways
1.01
1.02
1.02
1.07A
1.08
1.08A
1.09
1.10
2.28
2.31
3.09 & 3.11
3.13
3.14
3.18
6.01
From 4.31 to
4.43
4.66
4.67- 4.68
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" ADD " = Add
"DESTROY" = Destroy "
DEC 14
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"SEE VAL" = See Validation
Action
P CH SE Page Seq Date
Validation Criteria
......
4
4
31
32
500 DEC 14
500 DEC 14
212A
212A
......
4
4
33
34
500 DEC 14
500 DEC 14
212A
212A
......
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4
35
36
500 DEC 14
500 DEC 14
212A
212A
......
4
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500 DEC 14
500 DEC 14
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212A
......
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4
39
40
500 DEC 14
500 DEC 14
212A
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......
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4
41
42
500 DEC 14
500 DEC 14
212A
212A
......
4
43
500 DEC 14
212A
ADD
4
4
65
66
600 SEP 10
001 DEC 14
212A
ADD
4
4
67
68
500 DEC 14
500 DEC 14
212A
212A
......
5 01
01
104 DEC 14
L.T.R.
......
5 02
01
001 DEC 14
R.T.R.
......
5 04
01
104 DEC 14
L.E.T.P.
......
5 05
01
001 DEC 14
L.N.R.
......
5 06
01
001 DEC 14
R.N.R.
......
5 08
01
104 DEC 14
L.E.N.P.
Turn
RO
MOD 5561
RO
RO
RO
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S.N.N.P.
" ADD " = Add
"DESTROY" = Destroy "
DEC 14
…….." = Revised
"SEE VAL" = See Validation
Action
P CH SE Page Seq Date
Validation Criteria
......
5 09
01
104 DEC 14
L.O.M.
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......
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01
104 DEC 14
C.R.T.
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L.E.N.P.
DEC 14
You must hold in your manual the following normal pages
M
P CH SE Page Seq Date
Label
Validity expression
NORMAL REVISION N° 34
0
01
001 OCT 08
ALL
1
1
01
02
001 SEP 13
500 SEP 13
ALL
1
1
1
1
1
1
03
04
100 OCT 09
500 NOV 11
ALL
212A
MOD 3973 or 4371 or 4457
PW127F-127M
04A 400 SEP 04
ALL
05
MOD 5465
500 SEP 13
ALL
212A
05A 500 SEP 13
ALL
212A
1
06
502 SEP 13
ALL
1
07
300 OCT 09
ALL
MOD 1603 +4116 +4366
07A 100 SEP 13
ALL
MOD 3973 or 4371 or 4457
1
1
1
Turn
02A 500 SEP 13
ALL
212A
08
212A
500 SEP 13
ALL
212A
08A 500 SEP 13
ALL
212A
1
1
09
10
500 SEP 13
500 SEP 13
ALL
PW127F-PW127M
PW127F-PW127M
1
11
500 NOV 11
ALL
PW127F-PW127M
2
2
01
02
500 SEP 13
001 OCT 09
ALL
212A
2
2
03
04
001 SEP 10
500 OCT 09
ALL
MOD 3973 or 4371 or 4457
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M
L.E.N.P.
DEC 14
P CH SE Page Seq Date
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2
2
05
06
001 OCT 08
001 SEP 10
ALL
2
2
07
08
500 NOV 11
500 APR 08
ALL
MOD 3973 or 4371 or 4457
MOD 3973 or 4371 or 4457
2
2
09
10
500 SEP 10
050 OCT 09
ALL
MOD 3973 or 4371 or 4457
MOD 4111
10A 500 SEP 10
ALL
MOD 3973 or 4371 or 4457
2
2
2
11
12
500 SEP 10
500 OCT 08
ALL
PW127F-127M
PW127F-127M
2
2
13
14
500 SEP 13
500 OCT 09
ALL
212A
2
15
550 OCT 09
ALL
MOD 4366 +(3973 or 4371 or 4457)
15A 150 OCT 09
ALL
MOD 4116 +4366
2
2
2
2
2
16
MOD 4686 or 8148
001 OCT 09
ALL
16A 001 OCT 09
ALL
17
18
001 OCT 08
500 OCT 08
ALL
MOD 3246 +4111
2
18A 550 APR 08
ALL
MOD 4116 +4366
2
18B 500 APR 08
ALL
MOD 4116
2
2
19
20
001 OCT 08
500 OCT 08
ALL
2
2
21
22
500 APR 08
001 OCT 09
ALL
2
Turn
5-08 page 2-104
PW127-127F-127M
MOD (3973 or 4371 or 4457)
PW127-127F-127M
MOD (3973 or 4371 or 4457)
22A 500 APR 08
ALL
MOD 4373 or 8167
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DEC 14
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23
24
001 APR 08
001 APR 08
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2
25
26
001 SEP 10
001 APR 08
ALL
2
26A 001 OCT 08
ALL
2
2
27
28
001 APR 08
500 SEP 13
ALL
2
2
29
30
500 OCT 09
550 OCT 08
ALL
2
2
2
2
Turn
5-08 page 3-104
212A
MOD 3973 or 4371 or 4457
MOD 3168 +4366
30A 100 APR 08
ALL
31
32
001 SEP 13
550 APR 08
ALL
212A
32A 200 OCT 09
ALL
MOD 5205
MOD 4111
2
2
33
34
001 SEP 10
001 OCT 08
ALL
2
2
35
36
001 OCT 08
001 OCT 08
ALL
2
2
37
38
001 OCT 08
001 OCT 08
ALL
2
2
39
40
001 OCT 08
001 OCT 08
ALL
2
2
41
42
001 OCT 08
150 APR 08
ALL
MOD 4116 +4366
3
3
01
02
001 NOV 11
100 NOV 11
ALL
MOD 3973 or 4371 or 4457
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DEC 14
P CH SE Page Seq Date
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3
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03
04
100 NOV 11
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ALL
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3
05
06
100 NOV 11
100 NOV 11
ALL
MOD 3973 or 4371 or 4457
MOD 3973 or 4371 or 4457
3
3
07
08
001 NOV 11
001 NOV 11
ALL
3
3
09
10
160 SEP 13
030 NOV 11
ALL
3
3
11
12
100 NOV 11
100 NOV 11
ALL
MOD 3973 or 4371 or 4457
MOD 3973 or 4371 or 4457
3
3
13
14
100 NOV 11
001 SEP 13
ALL
MOD 3973 or 4371 or 4457
3
3
15
16
100 NOV 11
001 NOV 11
ALL
MOD 3973 or 4371 or 4457
3
3
17
18
001 NOV 11
150 SEP 13
ALL
3
3
19
20
001 NOV 11
001 NOV 11
ALL
3
21
500 NOV 11
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4
01
500 APR 08
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4
11
500 APR 08
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4
4
4
Turn
5-08 page 4-104
PW127M
MOD 4111
PW127-PW127F-PW127M MOD (3973 or 4371 or 4457)
11A 500 OCT 08
ALL
12
500 APR 08
ALL
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12A 500 OCT 08
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4
13
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13A 500 OCT 08
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DEC 14
P CH SE Page Seq Date
Label
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4
N
5-08 page 5-104
61A 500 OCT 08
ALL
62
500 APR 08
ALL
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ALL
PW127M
212A
PW127
4
4
63
64
500 SEP 10
500 OCT 08
ALL
PW127F-127M
212A
4
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66
600 SEP 10
001 DEC 14
ALL
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5-08 page 6-104
DEC 14
M
P CH SE Page Seq Date
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67
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104 DEC 14
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ALL
L.E.T.P.
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01
001 DEC 14
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104 DEC 14
ALL
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5 09
01
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ALL
L.O.M.
RO
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5 10
01
104 DEC 14
ALL
C.R.T.
RO
6
01
100 SEP 13
ALL
End
RO
RO
MOD 3973 or 4371 or 4457
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List of Modifications
5-09 page 1-104
L.O.M.
DEC 14
MODIF
PARTS
TITLE
VALIDITY
1368
2.4
ICE AND RAIN PROTECTION - INSTALL
INNER WING DE-ICING SYSTEM
1603
1
ELECTRICAL POWER - INSTALL TRU ON
PROVISION
2735
4
ENGINE INDICATING - CHANGE
SOFTWARE AS 06 IN E.E.C
3168
2
AUTO FLIGHT - REPLACE AFC
COMPUTER
3246
2
ELECTRICAL POWER - ADD BATTERIES
DISCHARGE INDICATION IN FLIGHT
3530
1.2
FLIGHT CONTROLS - ELEVATORS INSTALL CLUTCH RECONDITIONING
DEVICE ON EXISTING PROVISION
(PRODUCTION SCHEME)
3827
2
PROPELLERS - ADD FAILURE INDICATION
OF SYNCHROPHASER
4111
1.2.3.6
CONTINUOUS IGNITION TRANSFORMATION IN "MAN IGNITION"
4116
1.2
HYDRAULIC POWER - RELOCATE GREEN
PUMP CONTROL CIRCUIT BREAKER
4237
2
INDICATING & RECORDING SYSTEMS INSTALL STANDARD L52 MFC
4238
2
INDICATING & RECORDING SYSTEMS INSTALL STANDARD L23 MFC
4366
1
AUTOFLIGHT - MODIFY ELECTRICAL
POWER SUPPLIES
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
Turn
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List of Modifications
5-09 page 2-104
L.O.M.
DEC 14
MODIF
PARTS
TITLE
VALIDITY
4371
1.2.3
PROPELLERS 14SF - 11E -PROPELLER
CONTROL INSTALL ELECTRONIC
REGULATION ON ATR 72-200
4373
2
FLIGHT CONTROLS - AILERONS
CONTROLS - INSTALL SPRING TAB
4457
1.2.3
PROPELLERS - INSTALL 568F
PROPELLERS ON ATR 72-210
4686
2
CARBURANT - INDIC. QUANTITY
INDICATION - ADD LOW LEVEL
DETECTION SYSTEM
5205
2
NAVIGATION - ATC/TCAS - ACQUIRE
ALTITUDE VIA BUS ARINC 429
5377
1.2.3.6
EQUIPMENT/FURNISHINGS - WIRING FOR
COCKPIT ENTRANCE SECURISED
5434
1.2.3.6
EQUIPMENT/FURNISHINGS - INSTALL
DOOR ON ELECTRICAL PROVISION
5465
2.3.6
EQUIPMENT/FURNISHINGS - SECURISED
DOOR INSTALLATION ON ELECTRICAL
SUPPLY
5561
4
LANDING GEAR-MLG-REPLACE DUNLOP
WHEELS & BRAKES BY MESSIERBUGATTI ONES
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
ALL
End
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Cross Reference Table
5-10 page 1-104
C.R.T.
DEC 14
This table shows, for each delivered aircraft, the cross reference between :
- the fleet serial number (F.S.N.)
- the manufacturing serial number (M.S.N.)
- the registration number
It is the F.S.N. which appears in the L.E.N.P. or L.E.T.P.
End
F.S.N.
M.S.N.
REGISTRATION
RO0051
0861
YR-ATH
RO0052
0867
YR-ATI
RO
6.01
NORMAL PROCEDURES
72
R
SEP 13
100
IN CASE OF ICING CONDITIONS REFER TO 3.21
IN CASE OF SEVERE ICING REFER TO 1.09
FINAL COCKPIT PREPARATION
DESCENT
ALTIMETERS ........................................... SET
PARKING BRK ...............ON / PRESS CHECK
LANDING ELEVATION............................. SET
COM / NAV / GPS..................................... SET
FUEL QTY ........................................... CHECK
ENG F/U ...............................................RESET
MEMO PANEL..................................... CHECK
PWR MGT .................................................. TO
CCAS.........................................................RCL
LDG ELEVATION................................. CHECK
GNSS * ...................................... SET / CHECK
LDG BUGS ................................ SET / CHECK
ARRIVAL BREIFING..................... COMPLETE
BEFORE PROPELLER ROTATION
CDLS *........................................................ ON
T/O BUGS ...........................SET AND CHECK
TRIMS ...................................................... SET
TAIL PROP................................... ON BOARD
DOORS .............................................CLOSED
SEAT BELTS .............................................. ON
BEACON .................................................... ON
BEFORE TAXI
PROP BRK *............................................. OFF
COCKPIT COM HATCH ....................CLOSED
CL 1 + 2................................................. AUTO
ANTI-ICING ........................................AS RQD
ANTI-SKID.............................................. TEST
FLAPS ...................................................... SET
NWS ........................................................... ON
TAXI
TAXI & T.O LIGHTS.................................... ON
BRAKES .............................................. CHECK
AFCS......................................... SET / CHECK
TO CONFIG............................................ TEST
TAKE OFF BRIEFING................... COMPLETE
BEFORE TAKE OFF
GUST LOCK .................................... RELEASE
FLIGHT CONTROLS ........................... CHECK
XPDR / TCAS *.................................... CHECK
AIR FLOW ............................................ NORM
CCAS ............................... RCL then TO INHIB
APM* ...................................SET AND CHECK
BLEED VALVES .................................AS RQD
EXT LIGHTS............................................... ON
FD BAR (When lined up)....................CENTER
RUDDER CAM ..................................CENTER
AFTER TAKE OFF
LDG GEAR ................................................. UP
FLAPS ..........................................................0°
PWR MGT / NP ......................... CLB / CHECK
BLEED VALVES ......................................... ON
TAXI & T.O LIGHTS.................................. OFF
ALTIMETERS ............................ SET / CHECK
APPROACH
SEAT BELTS .............................................. ON
LDG LIGHTS .............................................. ON
ALTIMETERS ...................... SET AND CHECK
CABIN ALTITUDE................................ CHECK
BEFORE LANDING
LDG GEAR ....................................... 3 GREEN
FLAPS ................................................. CHECK
PWR MGT ...................................................TO
TLU......................................................LO SPD
ICING AOA LIGHT............................... CHECK
EXT LIGHTS............................................... ON
AFTER LANDING
RADAR ....................................................STBY
FLIGHT CONTROLS ......................... LOCKED
FLAPS .......................................................... 0°
TRIMS ....................................................... SET
LAND LIGHTS / STROBES........................OFF
ANTI-/DE-ICING ........................................OFF
 After at least one minute
CL 1........................... FTR THEN FUEL SO
PARKING
PARKING BRK ........................................... ON
TAXI & T.O LIGHTS.................................. OFF
CL 2 ......................................................... FTR
PROP BRK *............................................... ON
BEACON .................................................. OFF
TAIL PROP ............................... ON POSITION
SEAT BELTS ............................................ OFF
 When leaving aircraft
OXYGEN MAIN SUPPLY ................... OFF
ICE AND RAIN PROTECTION ........... OFF
EXT LIGHTS....................................... OFF
EMER EXIT LIGHT.......................DISARM
EFIS / RADAR / COM / NAV............... OFF
CL 2............................................ FUEL SO
FUEL PUMPS 1 + 2............................ OFF
CDLS * ............................................... OFF
EXT PWR ........................................... OFF
BAT .................................................... OFF
* : if applicable / if installed
ON GROUND EMER EVACUATION
AIRCRAFT / PARKING BRAKE ...........................................................STOP / ENGAGE
AUTO PRESS....................................................................................................... DUMP
ATC (VHF 1)...................................................................................................... NOTIFY
CL 1 + 2......................................................................................... FTR THEN FUEL SO
MIN CAB LIGHT ........................................................................................................ ON
CABIN CREW (PA)............................................................................................ NOTIFY
FIRE HANDLES 1 + 2.............................................................................................PULL
AGENTS............................................................................................................AS RQD
ENG START ROTARY SELECTOR..............................................OFF / START ABORT
FUEL PUMPS 1 + 2................................................................................................. OFF
EVACUATION .................................................................................................. INITIATE
 Before leaving aircraft, BAT............................................................................... OFF
Mod : 3973 or 4371 or 4457