ATR 72-500 QRH
January 2, 2017 | Author: gianninipilot | Category: N/A
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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 NOV 11 001
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 ……………………………………… R 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………. R UNRELIABLE AIRSPEED INDICATION……….
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 1.11
1.02
EMERGENCY 72
JUN 12
500
IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE PL affected side .................................................................................. FI CL affected side .................................................. FTR THEN FUEL SO FIRE HANDLE affected side..........................................................PULL If condition persist after 10 seconds AGENT 1 affected side .......................................................... DISCH If condition persist after 30 seconds AGENT 2 affected side .......................................................... DISCH LAND ASAP SINGLE ENG OPERATION procedure (2.04) ............................ APPLY
ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE PL 1 + 2............................................................GI / REVERSE AS RQD When aircraft stopped PARKING BRAKE ............................................................. ENGAGE CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLE affected side.....................................................PULL If condition persist AGENT 1 affected side ...................................................... DISCH If condition persist after 30 seconds ......................................... AGENT 2 affected side ...................................................... DISCH If evacuation required ON GROUND EMER EVACUATION procedure (1.02).... APPLY
ON GROUND EMER EVACUATION AIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGE AUTO PRESS.............................................................................. DUMP ATC (VHF 1 / HF) ..................................................................... NOTIFY CL 1 + 2 ............................................................... FTR THEN FUEL SO MIN CAB LIGHT ............................................................................... ON CABIN CREW (PA)................................................................... NOTIFY FIRE HANDLES 1 + 2....................................................................PULL AGENTS ...................................................................................AS RQD ENG START ROTARY SELECTOR................... OFF / START ABORT FUEL PUMPS 1 + 2........................................................................ OFF EVACUATION (PA) .................................................................INITIATE Before leaving aircraft BAT ............................................................................................ OFF
Model : 212A
EMERGENCY 72
1.02A JUN 12
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
1.03 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
1
EMERGENCY 72
1.05 JUN 12
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 JUN 12
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
JUN 12
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 07
100
EMERGENCY DESCENT OXYGEN MASKS / CREW COMMUNICATIONS ....................AS RQD GOOGLES ................................................................................AS RQD DESCENT................................................................................INITIATE PL 1 + 2............................................................................................... FI CL 1 + 2 ............................................................................. 100% OVRD OXYGEN PAX SUPPLY ...........................................................AS RQD SPEED........... MMO / VMO (or less if structural damage is suspected) SIGNS............................................................................................... ON ATC........................................................................................... NOTIFY MEA ........................................................................................... CHECK
Mod : 3973 or 4371 or 4457
EMERGENCY 72
1.08 JUN 12
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 ......................................... 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 JUN 12
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 ......................................... 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 JUN 12
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
JUN 12
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 AP/YD/FD BARS ...............................................................OFF/OFF/STBY PITCH AND TQ......................................................................... MAINTAIN If at take off or GA below 1500 ft: PITCH IMMEDIATELY ........................................................................ 8° ICING / VOLCANIC ASHES CONDITIONS.................................ESCAPE PROBE HEATING, DE-/ANTI-ICING ...................................... CHECK ON APM..................................................................................................... OFF WARNING: respect STALL alarm. Note: Use any GPS speed information if available. Take off phase, at or above acceleration altitude ALTITUDE.................................... MAINTAIN AT LEAST 30 SECONDS FLAPS.................................................................................................. 0° PITCH .................................................................................................. 8° Note: Use climb table here after to adjust pitch if required. AFTER TAKE OFF normal procedure .........................................APPLY LAND AT THE NEAREST SUITABLE AIRPORT Climb TLU ............................................................................................ LO SPD PWR MGT........................................................................................ CLB PL 1 + 2.......................................................................................NOTCH Altitude (ft)
5000
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 JUN 12
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
2.05 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 NP50°C) Note: Avoid rapid throttle movement OIL TEMP AND OTHER ENGINES PARAMETERS .......MONITOR If too low ( 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 APR 08 500
AFR AIR BLEED FAULT LEAVE AND AVOID ICING CONDITIONS AFR AIR BLEED ............................................................................. OFF If DE-ICING ENG FAULT light illuminates after 10 s DE-ICING ENG affected side .................................................... OFF AFR AIR BLEED.......................................................................... ON AFR AIR BLEED light ....................................CHECK EXTINGUISH If DE-ICING ENG FAULT light does not illuminate on any side DE-ICING AIR FRAME FAULT procedure (2.28).................. APPLY
DE-ICING AIR FRAME FAULT DE-ICING AIR FRAME ................................................................... OFF LEAVE AND AVOID ICING CONDITIONS MINIMUM ICING SPEEDS ................................... INCREASE BY 10 kt If in icing conditions LDG DIST .......................................................... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine SPEEDS and LDG DIST If ice accretion STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED
DE-ICING MODE SEL FAULT OVRD........................................................................................SELECT MONITOR DE-ICING In case of engine flame out OVRD................................................................................ RELEASE
MODE SEL AUTO FAULT MODE SEL .....................................................................................MAN DE-ICING and ANTI-ICING MANUAL MODE PBs: ACCORDING TO CURRENT SAT ...........................................SELECT
Model : 212A
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 OCT 09 001
AUDIO SEL FAULT AUDIO SEL affected side ............................................................. ALTN
AHRS A / ERECT FAIL ATT / HDG PB affected side................................................. DEPRESS When possible AIRCRAFT .................................... STABILIZE SPEED AND LEVEL AHRS affected side, PUSH TO ERECT PB ...................................... .................................................DEPRESS FOR 15 SECONDS
EFIS COMP R R R R R R R R R R R R R R R R R 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 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
NOV 11 100
BEFORE PROPELLER ROTATION CM1
CM2
LOADSHEET ……...……………..CHECK GNSS WEIGHT & FUEL........…UPDATE SPEED BUGS ................. SET & CHECK TRIMS ........................................ CHECK 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 .............................................. AUTO SGL CH……………….………..…CHECK 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
COCKPIT COM HATCH… ....... CLOSED NWS……………….……...………….…ON
CL 1. ............................................. AUTO SGL CH………………..……….…CHECK LO PITCH ………………...………CHECK ACW GEN 1……………………..ON LINE ACW BTC .....................................OPEN XPDR……………………...AS REQUEST
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: 3973 or 4371 or 4457
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
NOV 11 001
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
PL ........................................................GI REVERSE.......................USE AS RQRD
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
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 NOV 11 160
ATPCS - DYNAMIC TEST (last flight of the day) Conditions: - PL 1 + 2 .................................................................................................................. GI - CL 1 + 2 ........................................................................................................... AUTO - ATPCS P/B depressed in, OFF light extinguished - PWR MGT on TO position Check the following results : Turn the ATPCS knob to the left to the arm position and check - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION.............................................................................DECREASE Turn the ATPCS knob to ENG 1 position and check : - ENG 2 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 2 ...................................................................................................... NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 1 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED Turn the ATPCS knob to the right to the arm position and check : - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION.............................................................................DECREASE Turn the ATPCS knob to ENG 2 position and check : - ENG 1 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 1 ...................................................................................................... NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 2 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED Note: If ENG TEST must be repeated, wait 10 minutes before setting ATPCS.selector in ENG position in order not to damage feathering pumps. (Winding heating).
ENG BOOST TEST Conditions: - PL 1 + 2 .................................................................................................................. GI - EEC 1 + 2 ...............................................................................ON. OFF extinguished. Test: ENG BOOST PB ..................................................................................... PRESSED-IN - ON ..............................................................................................ILLUMINATED - FAULT light ............................................................................ EXTINGUISHED ENG BOOST PB ............................................................................... RELEASED-OUT - ON .......................................................................................... EXTINGUISHED - FAULT light ............................................................................ EXTINGUISHED Note: Test can be performed disregarding engine running condition (both engines running, one engine running, or both engines shut-off)
Mod: 5908
Eng: PW127M
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 72
OCT 08 500
13 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
104 110
110 (Flaps 0)
110 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
105 (Flaps 0)
VmHB (Flaps 30)
95
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
99 (Flaps 15) 126 (Flaps 0) 95
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
85.6 409 235 289 80.6 386 227 289
83.0 398 231 287 78.1 375 224 287
79.9 384 227 285 75.5 363 220 285
76.7 372 223 282 72.6 351 216 283
73.2 359 218 279 69.5 340 212 280
69.8 347 213 276 66.3 327 207 276
66.0 333 208 271 63.0 316 202 272
200
75.1 361 219 287
72.8 350 216 286
70.5 340 212 284
68.1 329 209 282
65.5 319 205 279
62.6 308 200 276
59.7 298 195 272
220
69.7 336 211 286
67.7 326 208 284
65.6 317 204 283
63.5 308 201 281
61.3 298 197 278
58.9 289 193 275
56.2 279 188 271
240
64.6 312 203 284
62.8 303 199 282
60.9 295 196 281
59.0 287 192 278
57.1 278 189 276
55.0 270 185 273
52.8 262 180 269
250
62.1 300 199 283
60.3 292 195 281
58.6 284 192 279
56.8 276 188 277
54.9 268 184 274
53.0 260 181 271
51.0 253 176 268
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.32
OPS DATA 72
OCT 08 500
14 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
104 110
110 (Flaps 0)
110 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
109 (Flaps 0)
VmHB (Flaps 30)
95
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
103 (Flaps 15) 131 (Flaps 0) 95
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
85.6 409 234 288 80.5 386 227 288
82.9 397 231 287 78.0 375 223 286
79.8 384 226 284 75.4 363 220 285
76.6 372 222 282 72.5 351 215 282
73.2 359 217 278 69.4 339 211 279
69.7 346 212 275 66.3 327 206 275
66.0 333 207 270 63.0 316 201 271
200
75.0 361 219 287
72.7 350 215 285
70.4 340 212 283
68.0 329 208 281
65.4 319 204 278
62.5 308 199 275
59.6 297 194 270
220
69.6 335 210 285
67.6 326 207 283
65.5 317 203 281
63.4 308 200 279
61.1 298 196 277
58.7 289 191 273
56.1 279 187 269
240
64.4 311 202 282
62.6 303 198 281
60.8 294 195 279
58.8 286 191 277
56.9 278 187 274
54.8 269 183 270
52.6 261 179 267
250
62.0 300 197 281
60.2 291 194 279
58.4 283 190 277
56.6 275 187 275
54.7 267 183 272
52.9 260 179 269
50.8 252 175 265
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.33
OPS DATA 72
OCT 08 500
15 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
104 110
114 (Flaps 0)
110 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
114 (Flaps 0)
VmHB (Flaps 30)
95
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
107 (Flaps 15) 136 (Flaps 0) 97
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
85.5 409 234 288 80.5 386 226 287
82.9 397 230 286 77.9 374 223 286
79.8 383 226 284 75.3 363 219 284
76.6 372 222 281 72.4 351 215 281
73.1 358 217 278 69.4 339 210 278
69.7 346 212 274 66.2 327 205 274
65.9 333 206 269 62.9 316 200 269
200
74.9 360 218 286
72.6 349 214 284
70.3 339 211 282
67.9 329 207 280
65.2 319 203 277
62.4 308 198 273
59.5 297 193 269
220
69.5 335 209 283
67.5 325 206 282
65.4 316 202 280
63.3 307 199 278
61.0 297 194 275
58.6 289 190 271
56.0 278 185 267
240
64.3 310 201 281
62.4 302 197 279
60.6 294 193 277
58.6 285 190 274
56.7 277 186 271
54.6 269 181 268
52.5 261 177 264
250
61.8 299 196 279
60.0 290 192 277
58.2 282 189 275
56.4 275 185 272
54.5 267 181 269
52.7 259 177 266
50.6 252 173 262
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.34
OPS DATA 72
OCT 08 500
16 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
104 110
118 (Flaps 0)
110 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
118 (Flaps 0)
VmHB (Flaps 30)
95
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
111 (Flaps 15) 140 (Flaps 0) 100
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
85.5 409 233 287 80.3 385 226 286
82.8 397 230 285 77.8 374 222 285
79.7 383 225 283 75.2 363 218 283
76.5 371 221 280 72.3 350 214 280
73.1 358 216 276 69.3 339 209 276
69.6 346 211 272 66.1 327 204 272
65.9 333 205 268 62.8 315 198 268
200
74.8 360 217 285
72.5 349 213 283
70.2 339 210 281
67.7 328 206 278
65.1 318 201 275
62.3 307 196 271
59.4 297 191 266
220
69.3 334 208 282
67.3 325 205 280
65.2 316 201 278
63.1 306 197 276
60.8 297 193 273
58.4 288 188 269
55.9 278 183 264
240
64.1 310 199 279
62.2 301 196 277
60.4 293 192 274
58.4 285 188 272
56.5 276 184 269
54.5 268 180 265
52.3 260 175 261
250
61.6 298 195 277
59.7 290 191 275
58.0 282 187 272
56.2 274 183 270
54.3 266 179 267
52.5 259 175 263
50.4 251 170 259
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.35
OPS DATA 72
OCT 08 500
17 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
104 110
121 (Flaps 0)
111 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
121 (Flaps 0)
VmHB (Flaps 30)
96
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
115 (Flaps 15) 145 (Flaps 0) 104
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
85.4 408 233 286 80.2 385 225 285
82.7 397 229 285 77.7 374 221 283
79.6 383 224 282 75.1 362 217 281
76.4 371 220 279 72.2 350 213 278
73.0 358 215 275 69.1 338 208 275
69.5 346 210 271 65.9 326 203 271
65.8 333 204 266 62.7 315 197 266
200
74.6 359 216 283
72.3 348 212 281
70.0 338 208 279
67.6 328 204 276
64.9 318 200 273
62.1 307 195 269
59.2 296 190 264
220
69.1 333 207 280
67.1 324 203 278
65.0 315 199 276
62.9 306 195 273
60.7 296 191 270
58.3 288 187 266
55.7 278 181 262
240
63.8 309 197 277
62.0 300 194 274
60.2 292 190 272
58.2 284 186 269
56.3 275 182 266
54.2 268 177 262
52.1 260 172 257
250
61.3 297 193 275
59.5 289 189 272
57.7 281 185 269
55.9 273 181 266
54.1 265 177 263
52.2 258 172 259
50.1 250 167 254
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.36
OPS DATA 72
OCT 09 500
18 t R
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
107 111
125 (Flaps 0)
115 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
125 (Flaps 0)
VmHB (Flaps 30)
99
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
118 (Flaps 15) 149 (Flaps 0) 107
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
85.3 408 232 285 80.1 384 224 284
82.6 397 228 284 77.5 373 220 282
79.5 383 224 281 74.9 362 216 280
76.3 371 219 278 72.0 349 211 277
72.9 358 214 274 69.0 338 206 273
69.4 346 208 269 65.8 326 201 269
65.7 333 203 264 62.6 315 196 264
200
74.4 358 215 282
72.1 348 211 279
69.8 338 207 277
67.4 327 203 274
64.8 317 198 271
62.0 307 193 267
59.1 296 188 262
220
68.9 333 205 278
66.9 323 202 276
64.8 314 198 274
62.7 305 194 271
60.5 296 189 268
58.1 287 184 263
55.5 277 179 258
240
63.6 308 196 274
61.7 299 192 272
59.9 291 188 269
57.9 283 184 266
56.0 275 179 262
54.0 267 174 258
51.8 259 169 252
250
61.1 296 191 272
59.2 288 187 269
57.4 280 183 266
55.6 272 178 263
53.8 264 174 259
51.9 257 169 254
49.8 249 163 248
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.37
OPS DATA 72
OCT 08 500
19 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
104 110
110 114
129 (Flaps 0)
119 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
129 (Flaps 0)
VmHB (Flaps 30)
102
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
121 (Flaps 15) 153 (Flaps 0) 110
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
85.1 408 231 284 79.9 384 223 283
82.5 396 227 282 77.3 372 219 281
79.4 382 223 279 74.8 361 214 278
76.2 371 218 276 71.9 349 210 275
72.8 357 212 272 68.8 338 205 271
69.4 346 207 268 65.7 326 200 267
65.6 333 201 263 62.4 315 194 262
200
74.2 358 213 280
71.9 347 209 278
69.6 337 205 275
67.2 327 201 272
64.6 317 196 269
61.8 306 191 264
58.9 296 185 259
220
68.7 332 204 276
66.7 323 200 274
64.6 313 196 271
62.4 304 192 268
60.2 295 187 265
57.8 286 182 260
55.2 276 176 254
240
63.3 307 194 271
61.4 298 190 269
59.6 290 186 266
57.7 282 181 262
55.7 273 176 258
53.6 266 171 253
51.4 258 165 246
250
60.8 295 189 269
58.9 286 184 266
57.1 279 180 262
55.3 271 175 258
53.4 263 170 253
51.5 256 164 248
49.4 248 158 240
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.38
OPS DATA 72
OCT 09 500
20 t R
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
105 110
114 118
132 (Flaps 0)
122 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
132 (Flaps 0)
VmHB (Flaps 30)
105
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
125 (Flaps 15) 157 (Flaps 0) 114
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
85.0 407 230 283 79.7 383 221 281
82.3 396 226 281 77.1 372 217 279
79.2 382 221 278 74.6 361 213 276
76.1 370 216 275 71.7 348 208 273
72.6 357 211 270 68.7 337 203 269
69.3 345 206 266 65.5 325 198 264
65.5 332 199 261 62.3 314 192 259
200
74.0 357 212 278
71.7 346 208 276
69.4 336 204 273
67.0 326 199 270
64.4 316 194 266
61.6 305 189 261
58.7 295 183 255
220
68.4 331 202 274
66.4 322 198 271
64.3 313 194 268
62.2 303 189 265
60.0 294 185 261
57.5 285 179 256
54.9 276 172 249
240
63.0 306 191 268
61.1 297 187 265
59.3 289 183 262
57.3 281 178 257
55.3 272 172 252
53.2 265 166 246
50.9 256 159 238
250
60.4 294 186 265
58.5 285 181 261
56.7 277 176 257
54.8 269 171 252
52.9 261 165 246
50.9 254 158 238
48.7 246 149 227
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.39
OPS DATA 72
OCT 08 500
21 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
108 111
117 121
136 (Flaps 0)
125 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
136 (Flaps 0)
VmHB (Flaps 30)
108
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
128 (Flaps 15) 161 (Flaps 0) 117
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
84.8 407 229 282 79.5 382 220 279
82.2 395 225 279 76.9 371 216 277
79.1 381 220 276 74.4 360 212 274
76.0 370 215 273 71.5 348 207 271
72.5 357 210 269 68.5 337 202 267
69.2 345 204 264 65.3 325 196 262
65.4 332 198 258 62.1 314 190 256
200
73.8 356 210 276
71.5 346 206 273
69.1 336 202 270
66.8 325 197 267
64.1 315 192 263
61.4 305 186 257
58.4 294 180 251
220
68.1 330 200 271
66.1 320 196 268
64.0 312 191 265
61.8 302 187 261
59.6 293 181 256
57.2 284 175 250
54.6 275 167 242
240
62.6 304 189 265
60.7 296 184 261
58.8 288 179 257
56.8 279 173 251
54.8 270 167 245
52.6 263 159 236
50.1 254 148 222
250
60.0 292 182 260
58.0 283 177 256
56.1 275 172 250
54.2 267 165 244
52.1 258 157 234
49.8 251 145 219
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.40
OPS DATA 72
OCT 09 500
21.5 t R
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
109 113
119 122
138 (Flaps 0)
126 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
138 (Flaps 0)
VmHB (Flaps 30)
109
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
129 (Flaps 15) 163 (Flaps 0) 119
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
84.8 406 228 281 79.4 382 219 278
82.1 395 224 279 76.8 371 215 276
79.0 381 219 275 74.3 360 211 273
75.9 370 214 272 71.4 348 206 270
72.5 357 209 268 68.4 337 201 266
69.1 345 203 263 65.2 324 195 260
65.3 332 197 257 62.0 314 188 254
200
73.6 355 209 275
71.3 345 205 272
69.0 335 201 269
66.7 325 196 266
64.0 315 191 261
61.2 304 185 255
58.3 294 178 248
220
68.0 329 199 269
65.9 320 195 267
63.8 311 190 263
61.7 302 185 259
59.4 293 179 254
56.9 284 172 247
54.3 274 164 237
240
62.4 303 187 262
60.5 295 182 258
58.6 287 177 254
56.5 278 171 248
54.4 269 163 239
52.2 262 154 228
250
59.8 291 181 258
57.7 282 175 252
55.8 274 169 246
53.8 266 161 237
51.5 256 150 224
160 180
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.41
OPS DATA 72
OCT 09 500
22 t
PW127F / PW127M
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
111 114
120 123
139 (Flaps 0)
128 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
139 (Flaps 0)
VmHB (Flaps 30)
111
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
131 (Flaps 15) 165 (Flaps 0) 120
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
84.7 406 228 280 79.3 381 219 278
82.0 395 223 278 76.7 370 214 275
78.9 381 219 275 74.2 359 210 272
75.8 370 214 271 71.3 347 205 268
72.4 357 208 267 68.3 336 200 264
69.0 345 202 262 65.1 324 193 259
65.2 332 195 255 61.9 313 187 252
73.5 355 208 273
71.2 345 204 271
68.9 335 200 268
66.5 324 195 264
63.9 314 189 259
61.1 304 183 253
58.1 293 175 245
220
67.8 328 197 268
65.8 319 193 265
63.6 310 188 261
61.4 301 183 256
59.2 292 177 251
56.7 283 170 243
54.0 273 160 231
240
62.2 303 185 260
60.2 294 180 255
58.3 286 174 250
56.2 277 167 243
53.9 268 158 232
51.1 258 141 209
250
59.5 290 178 254
57.4 281 172 248
55.3 272 164 240
53.2 264 155 228
160 180 R
200 R
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED
Model : 212A
4.42
OPS DATA 72
OCT 09 500
22.5 t
PW127F / PW127M
Never exceed certified weight limitations
R
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
112 115
122 125
140 (Flaps 0)
130 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
140 (Flaps 0)
VmHB (Flaps 30)
113
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
133 (Flaps 15) 167 (Flaps 0) 122
MAX CRUISE 2 ENGINES ∆ ISA -10
-5
0
+5
+10
+15
+20
80
94.5 459 248 271
94.5 461 247 272
94.5 464 246 274
89.3 446 239 269
84.2 428 233 263
79.7 412 226 258
75.2 396 220 253
100
94.5 453 246 276
94.5 456 245 278
90.2 440 239 274
85.6 424 232 269
80.8 408 226 264
76.3 392 219 258
72.1 377 213 253
120
93.5 446 242 280
89.9 433 237 277
86.0 418 232 273
82.1 404 226 269
77.9 390 220 265
73.7 375 213 259
69.6 361 207 254
140
89.2 427 235 280
86.0 412 230 277
82.7 401 225 274
79.0 387 219 270
75.4 374 214 266
71.4 360 208 260
67.5 346 201 254
160
84.6 406 227 279
81.9 394 223 277
78.8 381 218 274
75.7 369 213 270
72.3 356 207 265
68.9 345 201 260
65.1 331 194 254
180
79.2 381 218 277
76.6 370 213 274
74.1 359 209 271
71.2 347 204 267
68.2 336 198 263
65.0 324 192 257
61.8 313 185 250
200
73.4 354 207 272
71.0 344 203 269
68.7 334 199 266
66.4 324 194 262
63.7 314 188 257
60.9 304 181 250
57.9 293 173 241
220
67.6 328 196 266
65.6 318 192 263
63.4 310 186 258
61.2 300 181 253
59.0 291 174 247
56.4 282 166 237
53.6 272 154 223
240
61.9 302 183 257
59.9 293 178 252
57.9 284 171 246
55.7 275 162 236
53.1 265 149 219
250
59.2 289 176 251
57.0 279 168 243
54.7 270 158 232
TQ % NP = 82 % KG/H/ENG IAS TAS
NOT THERMO LIMITED Model : 212A
4.43
OPS DATA 72
OCT 09 500
23 t
PW127F / PW127M Never exceed certified weight limitations
R R
NON LIMITING RWY TAKE-OFF FLAPS 15
Speeds
Normal
Icing
V1 = VR V2
114 117
123 126
141 (Flaps 0)
132 (Flaps 15)
FINAL TAKE OFF DRIFT DOWN VmLB
141 (Flaps 0)
VmHB (Flaps 30)
115
MINI EN ROUTE FINAL APPROACH
FLIGHT LEVEL
135 (Flaps 15) 169 (Flaps 0) 124
MAX CRUISE 2 ENGINES ∆ ISA -10
-5
0
+5
+10
+15
+20
80
94.5 459 248 271
94.5 461 247 272
94.5 464 246 274
89.3 446 239 269
84.2 428 233 263
79.7 412 226 258
75.2 396 220 253
100
94.5 453 246 276
94.5 456 245 278
90.2 440 239 274
85.6 424 232 269
80.8 408 226 264
76.3 392 219 258
72.1 377 213 253
120
93.5 446 242 280
89.9 433 237 277
86.0 418 232 273
82.1 404 226 269
77.9 390 220 265
73.7 375 213 259
69.6 361 207 254
140
89.2 427 235 280
86.0 412 230 277
82.7 401 225 274
79.0 387 219 270
75.4 374 214 266
71.4 360 208 260
67.5 346 201 254
160
84.6 406 227 279
81.9 394 223 277
78.8 381 218 274
75.7 369 213 270
72.3 356 207 265
68.9 345 201 260
65.1 331 194 254
180
79.2 381 218 277
76.6 370 213 274
74.1 359 209 271
71.2 347 204 267
68.2 336 198 263
65.0 324 192 257
61.8 313 185 250
200
73.4 354 207 272
71.0 344 203 269
68.7 334 199 266
66.4 324 194 262
63.7 314 188 257
60.9 304 181 250
57.9 293 173 241
220
67.6 328 196 266
65.6 318 192 263
63.4 310 186 258
61.2 300 181 253
59.0 291 174 247
56.4 282 166 237
53.6 272 154 223
240
61.9 302 183 257
59.9 293 178 252
57.9 284 171 246
55.7 275 162 236
53.1 265 149 219
250
59.2 289 176 251
57.0 279 168 243
54.7 270 158 232
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
4.65
OPS DATA 72
SEP 10
700
PW127F / PW127M ACTUAL LANDING DISTANCE (M) - SEA LEVEL
NORMAL CONDITIONS - FLAPS 30
RUNWAY CONDITION
CONTAMINATED BY
WEIGHT (1000 KG) 13
14
15
16
17
18
19
20
21
22
22.5
23
530
530
530
530
530
550
570
590
610
630
640
660
690
690
690
690
700
730
760
780
810
840
850
860
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
DRY WET WATER OR SLUSH
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