ATR72_QRH

0.01

GENERAL 72

OCT 08 001

TABLE OF CONTENTS 0

GENERAL

1

EMERGENCY PROCEDURES

2

PROCEDURES FOLLOWING FAILURES

3

NORMAL PROCEDURES

4

OPS DATA

5

MANAGEMENT PAGES

6

NORMAL CHECK LIST

COMMENTS ON PARTS 1 AND 2 LAYOUT The boxed items correspond to actions performed by memory by the R crew within a minimum period of time  : highlights a precondition to apply an action  : highlights the moment when an action is to be applied PROCEDURES INITIATION

R R

R R R

No action will be taken (apart from depressing MC/MW pushbutton) : - until flight path is stabilized - under 400 ft above runway, except propeller feathering after engine failure during approach at reduced power if go around is considered At flight crew discretion, one reset of a system failure associated with an amber caution (except PEC SGL CH) may be performed by selecting OFF then ON related pushbutton. Flight Crew may reengage a tripped circuit breaker only if he/she judges it necessary for a safe continuation of the flight. In this case only one reengagement should be attempted. If the failure alert disappears, continue normal operation and record the event in the maintenance log. If not, apply the associated failure procedure. Before performing a procedure, the crew must assess the situation as a whole, taking into consideration the failures, when fully identified, and the flight constraints imposed. TASK SHARING For all procedures, the general task sharing stated below is applicable. The pilot flying remains pilot flying throughout the procedure. PF, Pilot Flying, responsible for : PNF, Pilot Non Flying, responsible - PL for : - flight path and airspeed control - Check List reading - aircraft configuration - execution of required actions - navigation - actions on OVHD panel - CL - communications The AFCS is always coupled to the PF side (CPL selection) ANALYSIS OF CONSEQUENCES OF A FAILURE ON FLIGHT Basic airmanship calls for a management review of the remaining aircraft capabilities under the responsibility of CM1.

EMERGENCY 72

1.01 SEP 13

001

1 - EMERGENCY PROCEDURES Content 1/1 IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE ……….. ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE …. ON GROUND EMER EVACUATION …………………………………… ENG FIRE AT TAKE OFF ……………………………………………….. BOTH ENGINES FLAME OUT ………………………………………….. ENG FLAME OUT AT TAKE OFF ………………………………………. BOMB ON BOARD ……………………………………………………….. COCKPIT DOOR SECURITY SYSTEM ……………………………….. SMOKE ………………………………………………………………………. ELECTRICAL SMOKE……………………………………………………. AIR COND SMOKE ………………………………………………………. FWD SMOKE…………………...…………………………………………. AFT SMOKE…………………………………………………………….. AUX AFT COMPT SMOKE……………………………………………….. DUAL DC GEN LOSS ……………………………………………………. EMERGENCY DESCENT ……………………………………………….. DITCHING …………………………………………………………………. FORCED LANDING ………………………………………………………. SEVERE ICING …………………………………………………………… RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL……………..

1.02 1.02 1.02 1.02A 1.03 1.04 1.04 1.04A 1.05 1.05A 1.05A 1.06 1.06 1.06 1.07 1.07A 1.08 1.08A 1.09 1.10

UNRELIABLE AIRSPEED INDICATION…………………………………. 1.10/11 R

1.02

EMERGENCY 72

SEP 13

500

IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE PL affected side .................................................................................. FI CL affected side .................................................. FTR THEN FUEL SO FIRE HANDLE affected side..........................................................PULL  If condition persists after 10 seconds AGENT 1 affected side .......................................................... DISCH  If condition persists after 30 seconds AGENT 2 affected side .......................................................... DISCH LAND ASAP SINGLE ENG OPERATION procedure (2.04) ............................ APPLY

ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE PL 1 + 2............................................................GI / REVERSE AS RQD  When aircraft stopped PARKING BRAKE ............................................................. ENGAGE CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLE affected side.....................................................PULL  If condition persists AGENT 1 affected side ...................................................... DISCH  If condition persists after 30 seconds ....................................... AGENT 2 affected side ...................................................... DISCH  If evacuation required ON GROUND EMER EVACUATION procedure (1.02).... APPLY

ON GROUND EMER EVACUATION AIRCRAFT / PARKING BRAKE ................................ STOP / ENGAGE AUTO PRESS.............................................................................. DUMP ATC (VHF 1 / HF) ..................................................................... NOTIFY CL 1 + 2 ............................................................... FTR THEN FUEL SO MIN CAB LIGHT ............................................................................... ON CABIN CREW (PA)................................................................... NOTIFY FIRE HANDLES 1 + 2....................................................................PULL AGENTS ...................................................................................AS RQD ENG START ROTARY SELECTOR................... OFF / START ABORT FUEL PUMPS 1 + 2........................................................................ OFF EVACUATION (PA) .................................................................INITIATE  Before leaving aircraft BAT ............................................................................................ OFF

Model : 212A

EMERGENCY 72

1.02A SEP 13

500

ENG FIRE AT TAKE OFF Note: Captain may decide to shut down affected engine before reaching acceleration altitude, but not before 400ft AGL.  When airborne LDG GEAR ...................................................................................UP  At Acceleration Altitude PWR MGT..................................................................................MCT  At VFTO  If normal condition FLAPS......................................................................................... 0°  If icing condition FLAPS.....................................................................MAINTAIN 15° PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO FIRE HANDLE illuminated…………………………….. .............PULL  If fire persist after 10 seconds AGENT 1 affected side ...................................................... DISCH  If fire persist after 30 seconds AGENT 2 affected side....................................................... DISCH BLEED engine alive ............................................... OFF if necessary LAND ASAP SINGLE ENG OPERATION procedure (2.04) ........................... APPLY

Model : 212A

EMERGENCY 72

1.03 OCT 09 100

BOTH ENGINES FLAME OUT PL 1 + 2............................................................................................... FI If NH drops below 30 % (no automatic relight) CL 1 + 2 .......................................................... FTR THEN FUEL SO FUEL SUPPLY ..................................................................... CHECK OPTIMUM SPEED.................................................................. VmHB CAPT EHSI ................................................................................ OFF COMMUNICATIONS .............................................................. VHF 1 ENG START ROTARY SELECTOR............................START A & B ENG 2 RELIGHT ENG 2 START PB .................................................................. ON When NH above 10% CL 2 ..................................................................................FTR ENG 2 RELIGHT ....................................................MONITOR CL 2 then PL 2...........................................................AS RQD ENG 1 RELIGHT ENG 1 START PB .................................................................. ON When NH above 10% CL 1 ..................................................................................FTR ENG 1 RELIGHT ....................................................MONITOR CL 1 then PL 1...........................................................AS RQD If neither engine starts CL 1 + 2 .......................................................... FTR THEN FUEL SO ENG START ROTARY SELECTOR.............. OFF / START ABORT FUEL PUMPS 1 + 2................................................................... OFF FORCED LANDING (1.08A) or DITCHING (1.08) procedure ........... ............................................................................................... APPLY CAUTION: Do not select AVIONICS VENT EXHAUST MODE to OVBD

R

If engine(s) recovered CL / PL engine(s) recovered................................................AS RQD If one engine not recovered CL engine NON recovered ........................ FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04).................. APPLY SYSTEMS affected.......................................................... RESTORE

Mod : 3973 or 4371 or 4457

EMERGENCY 72

1.04 NOV 11 500

ENG FLAME OUT AT TAKE OFF R

UPTRIM ..................................................................................... CHECK AUTOFEATHER ........................................................................ CHECK If no UPTRIM PL 1 + 2 ................................................. ADVANCE TO THE RAMP When airborne LDG GEAR ....................................................................................UP BLEED 1 + 2 .................................................... OFF, IF NOT FAULT At Acceleration Altitude ALT .............................................................................................SET At VFTO PL 1 + 2 ................................................................... IN THE NOTCH PWR MGT .................................................................................MCT IAS ..............................................................................................SET If normal condition FLAPS ........................................................................................ 0° If icing condition FLAPS .................................................................... MAINTAIN 15° PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO BLEED engine alive............................................... OFF if necessary If damage suspected FIRE HANDLE affected side.....................................................PULL LAND ASAP SINGLE ENG OPERATION procedure (2.04)....................... APPLY If no damage suspected ENG RESTART IN FLIGHT procedure (2.08) ....................... APPLY If unsuccessful LAND ASAP SINGLE ENG OPERATION procedure (2.04).................. APPLY

BOMB ON BOARD AUTO PRESS - LANDING ELEVATION .................. CABIN ALTITUDE FLIGHT LEVEL ................................ DESCEND TO CABIN ALTITUDE AVOID LOAD FACTORS HANDLE BOMB CAREFULLY - AVOID SHOCKS When Z aircraft = Z cabin APPROACH CONFIG: FLAPS 15 GEAR DOWN ..........SELECTED AUTO PRESS......................................................................... DUMP SERVICE DOOR ................................................................UNLOCK PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAG ATTACHED TO THE DOOR HANDLE SURROUND IT WITH DAMPING MATERIAL CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER........... ............................................................................ MOVE FORWARD PAX................................... MOVE FORWARD / CRASH POSITION LAND ASAP Eng : PW127F / PW127M

EMERGENCY 72

1.04A SEP 04 400

COCKPIT DOOR SECURITY SYSTEM Electrical Power Lost Move the manual lock bolt to CLOSE position Note : When the door is locked with the manual bolt, the emergency access to the cockpit is unavailable. It is recommended that at least two crew members remain in the cockpit during that time. Cockpit Door Jammed

l When cockpit exit required

COCKPIT DOOR LOCKING SYSTEM ............................... OFF Disconnect PLUG on top of the door Remove the safety pins from the door Push and remove corresponding door panel

Mod : 5465

EMERGENCY 72

1.05 SEP 13

500

SMOKE CREW OXY MASKS............................................................. ON / 100% GOGGLES .......................................................................................SET CREW COMMUNICATIONS ..............................................ESTABLISH RECIRC FANS 1 + 2 ...................................................................... OFF AP ..................................................................................................... ON SMOKE SOURCE.................................................................. IDENTIFY  If source not identified or electrical smoke suspected Note: ELEC light may be activated by an air conditioning smoke source ELECTRICAL SMOKE procedure (1.05A) ............................ APPLY  If air conditioning smoke identified AIR COND SMOKE procedure (1.05A) ................................. APPLY  If FWD SMK illuminated or smoke in FWD zone of aircraft FWD SMOKE procedure (1.06) ............................................. APPLY  If AFT SMK illuminated or smoke in AFT zone of aircraft AFT SMOKE procedure (1.06) .............................................. APPLY  If AUX AFT COMPT SMK illuminated (depending on models) AUX AFT COMPT SMK procedure (1.06) ............................. APPLY

Model : 212A

EMERGENCY 72

1.05A SEP 13

500

ELECTRICAL SMOKE SMOKE procedure (1.05) ........................................................... APPLY AVIONICS VENT EXHAUST MODE ........................................... OVBD AIR FLOW......................................................................................HIGH DC SVCE AND UTLY BUS............................................................. OFF DC BTC.......................................................................................... ISOL ACW GEN 1 + 2.............................................................................. OFF SUSPECTED EQUIPMENTS ......................................................... OFF  If smoke origin not identified LAND ASAP ACW TOTAL LOSS procedure (2.16A) ................................. APPLY  If smoke origin identified NOT AFFECTED EQUIPMENTS .................................... RESTORE  When P below 1 PSI OVBD VALVE ................................................................FULL OPEN AVIONICS VENT EXHAUST MODE ......................................NORM

AIR COND SMOKE SMOKE procedure (1.05) ........................................................... APPLY PACK VALVE 1............................................................................... OFF MAX FL ..................................................................................200 / MEA  If smoke persists PACK VALVE 1 ........................................................................... ON PACK VALVE 2 ......................................................................... OFF CAUTION: Evacuation of air conditioning smoke may trigger electrical smoke warning. Disregard it. ENGINES PARAMETERS......................... CAREFULLY MONITOR  If any anomaly occurs, such as: - amber engine caution illumination associated to local ITT alert - total loss of NL indication - engine abnormality clearly identified (NH, NL, ITT indications, noise, surge…) CAUTION: Confirm which engine is showing signs of abnormal operation in order to avoid shutting down safe engine. PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.04)....................... APPLY

Model : 212A

1.06

EMERGENCY 72

SEP 13

502

FWD SMK SMOKE procedure (1.05) ........................................................... APPLY 1) PASSENGERS VERSION CABIN CREW (PA).............................................................. ADVISE AVIONICS VENT EXHAUST MODE ...................................... OVBD AIR FLOW ................................................................................HIGH EXTRACT AIR FLOW LEVER (RH MAINT PANEL) ..........CLOSED CABIN CREW WITH PORTABLE EXTINGUISHER, LOCATE AND KILL SOURCE OF SMOKE LAND ASAP  When P below 1 PSI OVBD VALVE ...........................................................FULL OPEN AVIONICS VENT EXHAUST MODE.................................NORM 2) CARGO VERSION CAB PRESS MODE SEL...........................................................MAN CAB ALT ................................................................ MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)........... OFF PACK VALVE 2 (Except when in single pack operation) .......... OFF CAB VENT AIR FLOW .............................................................. OFF FLIGHT COMPT TEMP SEL ..................................................... HOT CAUTION: LAND ASAP. If a quick landing is not possible, climb and maintain minimum FL160; FL200 is recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

Note: Smoke alert may be generated during smoke evacuation process.

AFT SMK SMOKE procedure (1.05) ........................................................... APPLY 1) PASSENGERS VERSION CABIN CREW (PA)....................................... ADVISE FOR ACTION AIR FLOW ................................................................................HIGH 2) CARGO VERSION CAB PRESS MODE SEL...........................................................MAN CAB ALT ................................................................ MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)........... OFF PACK VALVE 2 (Except when in single pack operation) .......... OFF CAB VENT AIR FLOW .............................................................. OFF FLIGHT COMPT TEMP SEL ..................................................... HOT CAUTION: LAND ASAP. If a quick landing is not possible, climb and maintain minimum FL160; FL200 is recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

Note: Smoke alert may be generated during smoke evacuation process.

AUX AFT COMPT SMK (depending on models) SMOKE procedure (1.05) ........................................................... APPLY AUX AFT COMPT AGENT ......................................................... DISCH Model : 212A

EMERGENCY 72

1.07 OCT 09 300

DUAL DC GEN LOSS DC GEN 1 + 2 ................................................................... OFF then ON If no generator recovered HYD GREEN PUMP .................................................................. OFF TRU.............................................................................................. ON

R

Make sure that TRU arrow illuminates, BAT arrows extinguish MAN RATE KNOB ..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN AVIONICS VENT EXHAUST MODE ...................................... OVBD BAT SW .................................................................................. OVRD ATC (VHF 1 or HF or HF 2) ................................................. NOTIFY MIN CAB LIGHT ........................................................................ OFF Note: NAV lights switch set to ON is necessary to provide IEP illumination STICK PUSHER / SHAKER ...................................................... OFF STICK PUSHER / SHAKER FAULT procedure (2.21) .......... APPLY SIDE WINDOWS ANTI-ICING................................................... OFF ADC SW.................................................................... SET TO ADC 1 ATC SW .................................................................... SET TO ATC 1 TLU ................................................................. MAN MODE LO SPD When TLU LO SPD illuminates TLU .....................................................................................AUTO CAUTION: Avoid large rudder input if IAS above 180 kt BUS EQUIPMENT LISTS (2.18 A – 2.18 B)......................... CHECK Before descent PAX INSTRUCTIONS .................................................... USE PA HYD X FEED .......................................................................... ON Note: Selecting HYD X FEED ON allows to recover green hydraulic system At touch down IDLE GATE LEVER .............................................................PULL

Mod : 1603 + 4116 + 4366

EMERGENCY 72

1.07A SEP 13

100

EMERGENCY DESCENT OXYGEN MASKS / CREW COMMUNICATIONS .................... AS RQD GOGGLES ................................................................................ AS RQD DESCENT ................................................................................ INITIATE PL 1 + 2............................................................................................... FI CL 1 + 2 ............................................................................. 100% OVRD

R

OXYGEN PAX SUPPLY ........................................................... AS RQD SPEED ........... MMO / VMO (or less if structural damage is suspected) SIGNS ............................................................................................... ON ATC (VHF1 / HF) ...................................................................... NOTIFY MEA ........................................................................................... CHECK

Mod : 3973 or 4371 or 4457

EMERGENCY 72

1.08 SEP 13

500

DITCHING  Preparation (time permitting) ATC (VHF1 or HF) ............................................................... NOTIFY XPDR ........................................................................ EMERGENCY CABIN CREW (PA).............................................................. NOTIFY SIGNS.......................................................................................... ON GPWS........................................................................................ OFF TERR (If TAWS installed) .......................................................... OFF CABIN AND COCKPIT .................................................... PREPARE - Loose equipment secured - Survival equipment prepared - Belts and shoulder harnesses locked AUTO PRESS - LDG ELEVATION.............................................SET  Approach AUTO PRESS......................................................................... DUMP PACKS 1 + 2.............................................................................. OFF OVBD VALVE ..............................................................FULL CLOSE HYD AUX PUMP pushbutton (pedestal) ......................... DEPRESS FLAPS (If available).......................................................................30 LDG GEAR LEVER ......................................................................UP  30 seconds before impact or 1250 ft above sea level DITCH PB .................................................................................... ON ENG START ROTARY SELECTOR.............. OFF / START ABORT CABIN REPORT ............................................................. OBTAINED  Before ditching (200 ft) MINIMIZE IMPACT SLOPE OPTIMAL PITCH ATTITUDE FOR IMPACT ................................. 9° BRACE FOR IMPACT ..........................................................ORDER Note: In case of night ditching, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ..............................................................PULL FUEL PUMPS 1 + 2................................................................... OFF  After ditching Note: After ditching, one aft door will be under the water line. CABIN CREW (PA).............................................................. NOTIFY EVACUATION ....................................................................INITIATE  Before leaving aircraft BAT ........................................................................................ OFF

Model : 212A

EMERGENCY 72

1.08A SEP 13

500

FORCED LANDING  Preparation (time permitting) ATC (VHF1 or HF) ............................................................... NOTIFY XPDR ........................................................................ EMERGENCY CABIN CREW (PA).............................................................. NOTIFY SIGNS.......................................................................................... ON GPWS........................................................................................ OFF TERR (If TAWS installed) .......................................................... OFF CABIN AND COCKPIT .................................................... PREPARE - loose equipment secured - survival equipment prepared - belts and shoulder harnesses locked AUTO PRESS - LDG ELEVATION.............................................SET  Approach HYD AUX PUMP pushbutton (pedestal) ......................... DEPRESS FLAPS (If available).......................................................................30 LDG GEAR LEVER .............................................................AS RQD AUTO PRESS......................................................................... DUMP ENG START ROTARY SELECTOR.............. OFF / START ABORT CABIN REPORT ............................................................. OBTAINED  Before impact (200 ft) BRACE FOR IMPACT ..........................................................ORDER Note: In case of night forced landing, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). CL 1 + 2 .......................................................... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ..............................................................PULL FUEL PUMPS 1 + 2................................................................... OFF  After impact, when aircraft stopped CABIN CREW (PA).............................................................. NOTIFY AGENTS ................................................................................ DISCH EVACUATION ....................................................................INITIATE  Before leaving aircraft BAT ........................................................................................ OFF

Model : 212A

EMERGENCY 72

1.09 SEP 13

500

SEVERE ICING MINIMUM ICING SPEED .................................................... INCREASE 10 kt PWR MGT...............................................................................................MCT CL 1 + 2 ....................................................................................100% OVRD PL 1 + 2..............................................................................................NOTCH AP (if engaged) ....... FIRMLY HOLD CONTROL WHEEL and DISENGAGE SEVERE ICING CONDITIONS........................................................ESCAPE ATC ................................................................................................... NOTIFY  If an unusual roll response or uncommanded roll control movement is observed : Push firmly on the control wheel FLAPS..........................................................................EXTEND 15  If the flaps are extended, do not retract them until the airframe is clear of ice.  For approach, if the aircraft is not clear of ice: GPWS ............................................................ FLAP/GPWS OVRD STEEP SLOPE APPROACH (4.5°) ........................PROHIBITED APP/LDG CONF ..........................................MAINTAIN FLAPS 15 APP SPEED ..... "REDUCED FLAPS 15 LDG icing speeds" + 5 kt Multiply landing distance FLAPS 30 by 2.12.

DETECTION Visual cue identifying severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window and / or Unexpected decrease in speed or rate of climb and / or The following secondary indications : . Water splashing and streaming on the windshield . Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice . Accumulation of ice on the lower surface of the wing aft of the protected areas . Accumulation of ice on propeller spinner farther aft than normally observed

The following weather conditions may be conducive to severe in-flight icing : . Visible rain at temperatures close to 0°C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0°C ambient air temperature (SAT)

Eng : PW127F / PW127M

1.10

EMERGENCY 72

SEP 13

500

RECOVERY AFTER STALL or ABNORMAL ROLL CONTROL

R R

R R R

CONTROL WHEEL........................................................ PUSH FIRMLY  If flaps 0° configuration FLAPS ........................................................................................... 15° PWR MGT ...................................................................................MCT CL 1 + 2......................................................................... 100 % OVRD PL 1 + 2 ..................................................................................NOTCH ATC ....................................................................................... NOTIFY  If flaps are extended PWR MGT ...................................................................................MCT CL 1 + 2......................................................................... 100 % OVRD PL 1 + 2 ..................................................................................NOTCH ATC ....................................................................................... NOTIFY Note: this procedure is applicable regardless the LDG GEAR position is (DOWN or UP)

UNRELIABLE AIRSPEED INDICATION R

AP/YD/FD .........................................................................OFF/OFF/STBY PITCH AND TQ......................................................................... MAINTAIN  If at take off or GA below 1500 ft: PITCH IMMEDIATELY ........................................................................ 8° ICING / VOLCANIC ASHES CONDITIONS.................................ESCAPE PROBE HEATING, DE-/ANTI-ICING...................................... CHECK ON APM..................................................................................................... OFF WARNING: respect STALL alarm. Note: Use any GPS speed information if available.  Take off phase, at or above acceleration altitude ALTITUDE.................................... MAINTAIN AT LEAST 30 SECONDS FLAPS.................................................................................................. 0° PITCH .................................................................................................. 8° Note: Use climb table here after to adjust pitch if required. AFTER TAKE OFF normal procedure .........................................APPLY LAND AT THE NEAREST SUITABLE AIRPORT  Climb TLU ............................................................................................ LO SPD PWR MGT........................................................................................ CLB PL 1 + 2.......................................................................................NOTCH Altitude (ft)

5000

Normal conditions pitch Icing conditions pitch

7° 6°

10000

15000

20000

5° 4°

4° 3°

3° 2°

Continuing next page …/…


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.


FOLLOWING FAILURES 72

2.01 SEP 13

500

2 - PROCEDURES FOLLOWING FAILURES Content 1/3 POWER PLANT SINGLE ENG OPERATION………………………………………………………. START FAULT……………………………………………………………………... X START FAIL……………………………………………………………………… ABNORMAL PARAMETERS DURING START………………………………… EXCESSIVE ITT DURING START………………………………………………. NO ITT DURING START………………………………………………………….. NO NH DURING START………………………………………………………….. ENG NAC OVHT ABNORMAL ENG PARAMETERS IN FLIGHT………………………………… FIRE LOOP FAULT……………………………………………………………….. ABNORMAL PROP BRK…………………………………………………………. ENG RESTART IN FLIGHT………………………………………………………. ENG STALL………………………………………………………………………… ONE EEC FAULT………………………………………………………………….. BOTH EEC FAULT………………………………………………………………… ENG FLAME OUT…………………………………………………………………. IDLE GATE FAIL…………………………………………………………………… SYNPHR FAIL (if applicable) ……………………………………………………. CL PNEUMATIC ACTUATOR BLOCKING (if applicable) ……………………. UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS (if applicable) …………… PEC SGL CH (if applicable) ……………………………………………………… PEC FAULT (if applicable) ……………………………………………………….. LO PITCH IN FLIGHT……………………………………………………………... ENG OVER LIMIT…………………………………………………………………. PROP OVER LIMIT……………………………………………………………….. ENG OIL TEMP BELOW 45°C…………………………………………………… ENG OIL TEMP HIGH…………………………………………………………….. ENG OIL LO PR……………………………………………………………………. ENG BOOST FAULT (if applicable) ……………………………………………..

2.04 2.04 2.04 2.05 2.05 2.05 2.05 2.06 2.06 2.06 2.07 2.08 2.08 2.09 2.09 2.10 2.10 2.10A 2.10A 2.10A 2.10A 2.10A 2.11 2.11 2.11 2.12 2.12 2.12 2.12A

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

2.13 2.13 2.13 2.14 2.14 2.14

ELEC DC BUS 1 OFF ……………………………………………………………………. AC BUS 1 OFF ……………………………………………………………………. DC BUS 2 OFF ……………………………………………………………………. AC BUS 2 OFF ……………………………………………………………………. ACW BUS 1 OFF / ACW BUS 2 OFF…………………………………………… ACW TOTAL LOSS……………………………………………………………….. DC ESS BUS OFF………………………………………………………………… DC EMER BUS OFF………………………………………………………………. DC GEN FAULT……………………………………………………………………. INV FAULT…………………………………………………………………………. ACW GEN FAULT…………………………………………………………………. DC SVCE/UTLY BUS SHED……………………………………………………… BAT CHG FAULT………………………………………………………………….. DUAL BAT CHG LOSS……………………………………………………………. BAT DISCHARGE IN FLIGHT (if applicable) …………………………………...

2.15 2.15 2.15A 2.15A 2.16 2.16A 2.17 2.17 2.18 2.18 2.18 2.18 2.18 2.18 2.18 2.18A STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS………………... 2.18B ESS BUS AND EMER BUS LOST EQUIPMENT LISTS………………………. 2.42 Cargo configuration only….. 2.42A

Model : 212A


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


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


2.04 JUL 15

500

SINGLE ENG OPERATION

R

LAND ASAP PWR MGT.................................................. TO if necessary then MCT FUEL PUMP affected side ............................................................ OFF DC GEN affected side .................................................................. OFF ACW GEN affected side ............................................................... OFF PACK affected side ...................................................................... OFF BLEED affected side .................................................................... OFF APM (if installed) .......................................................................... OFF TCAS (if installed) ................................................................ TA ONLY OIL PRESSURE ON FAILED ENGINE ............................... MONITOR Note: In icing conditions, FLAPS 15 will be selected to improve drift down performances and single engine ceiling. Note: Refer to pages (4.61) and (4.62) to determine single engine gross ceiling. Note: If during the flight, a positive oil pressure has been noted on the failed engine for a noticeable period of time, maintenance must be informed. Note: monitor fuel balance. Recommended operational maximum fuel unbalance is 200 kg (440 lb). When FUEL CROSS FEED is required FUEL PUMP affected side ......................................................... ON FUEL X FEED ........................................................................... ON FUEL PUMP operating engine................................................. OFF For approach MAX APPROACH SLOPE for Steep Slope Approach ............... 5.5° BLEED NOT AFFECTED ........................................................ OFF CL live engine ............................................................ 100% OVRD V APP......................................................... NOT LESS THAN VGA ■ If affected engine NP above 10% V APP ........................ NOT LESS THAN LDG SPEED + 10kt ■ If V APP is increased LDG DISTANCE ..........................................MULTIPLY BY 1.13 Note: Refer to part 4 to determine VGA, and landing distance. Note: At touch down, do not reduce below FI before nose wheel is on the ground.

START FAULT ENG START ROTARY SELECTOR .................. OFF / START ABORT If above 45 % NH START ON LIGHT................................... CHECK EXTINGUISHED START ........................................................... TO BE CONTINUED

X START FAIL CONTINUE NORMAL ENGINE START INFORM MAINTENANCE

Mod : 3973 or 4371 or 4457

72


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


2.06 SEP 10

001

ENG NAC OVHT  If during Hotel mode operation PL affected side .............................................................................GI CL affected side.............................................. FTR THEN FUEL SO  If during taxi AIRCRAFT ...............................................................................STOP PL affected side .............................SLIGHTLY INCREASE POWER  If unsuccessful within 30 seconds PL affected side ........................................................................GI CL affected side......................................... FTR THEN FUEL SO

ABNORMAL ENG PARAMETERS IN FLIGHT

R R R R R R R R R R

 If Intermittent fluctuations or unrealistic steady indication ATPCS ....................................................................................... OFF  When adequate flight situation PL affected side…………………………………………………… FI EEC affected side ................................................................. OFF  If successful ONE EEC FAULT procedure (2.09) .............................. APPLY  If unsuccessful - or -  If TQ = 0% and NP<77% PL affected side..................................................................... FI CL affected side......................................................... FUEL SO SINGLE ENG OPERATION procedure (2.04) .............. APPLY  If "- - -" indication on torque digital counter (only for PW127 PW127F - PW127M) AVOID SUDDEN PL MOVEMENTS

FIRE LOOP FAULT LOOP affected ................................................................................ OFF

72


2.07 NOV 11 500

ABNORMAL PROP BRK (if applicable) If on ground If unexpected propeller rotation – or – If local UNLK and CCAS PROP BRK alert CL 2 .............................................................................. FUEL SO MAINTENANCE ACTION REQUIRED If CCAS PROP BRK alert only If GUST LOCK ON CL 2 ......................................................................... FUEL SO If DC and AC GPU are not available ENG 1.....................................................................START CL 1 ..........................................................................AUTO When READY light illuminates PROP BRK ................................................................. OFF UNLK LIGHT .............................CHECK EXTINGUISHED PROP BRK PWR SPLY C/B .....................................PULL If GUST LOCK OFF GUST LOCK...................................................................... ON According to operational situation PROP BRK ................................................................. OFF ALL PROP BRK LIGHTS ..........CHECK EXTINGUISHED If in flight CONTINUE NORMAL OPERATION ENG 2 PARAMETERS .....................................................MONITOR After landing CL 2 .............................................................................. FUEL SO MAINTENANCE ACTION REQUIRED

Mod : 3973 or 4371 or 4457

72


2.08 APR 08 500

ENG RESTART IN FLIGHT

FUEL SUPPLY........................................................................... CHECK CL ........................................................................................... FUEL SO PL........................................................................................................ FI CAUTION: After ATPCS sequence, PWR MGT rotary selector must be set to MCT position before engine restart, in order to cancel propeller feathering. ENG START ROTARY SELECTOR................................ START A & B EEC PB............. RESET if necessary or DESELECT if FAULT persists START PB ........................................................................................ ON z At 10 % NH CL ...............................................................................................FTR RELIGHT ..........................................................................MONITOR CL ............................................................................................AUTO PL...................................................... ADJUST TO OTHER ENGINE ENG START ROTARY SELECTOR....................................AS RQD SYSTEMS AFFECTED.................................................... RESTORE

ENG STALL PL affected side .................................................................................. FI ENG PARAMETERS ................................................................. CHECK If abnormal engine parameters CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)....................... APPLY If normal engine parameters DE-/ANTI-ICING ENG ................................................................. ON PL affected side ............................................... SLOWLY ADVANCE If stall recurs Reduce thrust and operate below the stall threshold If stall does not recur Continue engine operation

Mod : 3973 or 4371 or 4457

72


2.09 SEP 10

500

ONE EEC FAULT

R R

ATPCS ............................................................................................ OFF CAUTION: DO NOT DESELECT EEC FLASHING  When adequate flight situation PL affected side ............................... RETARD IN GREEN SECTOR EEC affected side ..................................................................RESET  If successful ATPCS.................................................................................... ON PL affected side ........................................... RESTORE POWER  If unsuccessful EEC affected side ................................................................. OFF PL affected side .......................................... RESTORE POWER ......................................... HANDLING THROTTLE WITH CARE  In the following cases: icing conditions, engine(s) flame out, emergency descent, severe turbulence, heavy rain MAN IGN ........................................................................... ON  In final approach CL 1 + 2 .............................................................. 100% OVRD  After landing TAXI WITH THE AFFECTED ENGINE FEATHERED Note: ACW BTC must be check closed in order to avoid the loss of ACW bus on ground

BOTH EEC FAULT ATPCS ............................................................................................ OFF CAUTION: DO NOT DESELECT EEC FLASHING  When adequate flight situation PL 1 + 2 ........................................... RETARD IN GREEN SECTOR EEC 1 + 2 ................................................................. OFF THEN ON  If EEC 1+2 recovered ATPCS.................................................................................... ON PL 1 + 2 ....................................................... RESTORE POWER  If only one EEC recovered ONE EEC FAULT procedure (2.09) ................................. APPLY  If no EEC recovered EEC 1 + 2 ............................................................................. OFF PL 1 + 2 ....................................................... RESTORE POWER ....................................... HANDLING THROTTLES WITH CARE TQ IND ENG 1 + 2.......................................................MONITOR LDG DIST ....................................................... MULTIPLY BY 1.5 Note: Refer to Part 4 to determine landing distance  In the following cases: icing conditions, engine(s) flame out, emergency descent, severe turbulence, heavy rain MAN IGN ........................................................................... ON  In final approach CL 1 + 2 .............................................................. 100% OVRD  After landing BRAKE HANDLE........................................... EMER AS RQD CAUTION: Reverse power is reduced. Both main HYD pumps will be lost at low speed. TAXI ON BOTH ENGINES, HANDLE THROTTLES WITH CARE Mod : 3973 or 4371 or 4457

72


2.10 OCT 09 050

ENG FLAME OUT PL affected side .................................................................................. FI R R R

If NH drops below 30 % (no immediate relight) CL affected side.............................................. FTR THEN FUEL SO If damage suspected FIRE HANDLE affected side ...............................................PULL SINGLE ENG OPERATION procedure (2.04).................. APPLY If no damage suspected ENG RESTART IN FLIGHT procedure (2.08).................. APPLY If unsuccessful SINGLE ENG OPERATION procedure (2.04) ............ APPLY

IDLE GATE FAIL In flight IDLE GATE LEVER .................................................................PUSH At touch down IDLE GATE LEVER ..................................................................PULL

Mod : 4111

72 R R

R R


2.10A SEP 10

500

UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS CL 1 + 2 ............................................................................. 100% OVRD

PEC SGL CH DO NOT RESET PEC IN FLIGHT - NO SPECIAL CREW ACTION ANTICIPATE A PEC FAULT AT LANDING MAINTENANCE IS REQUIRED

PEC FAULT If in short final approach (below 400 ft RA) GO AROUND procedure ....................................................... APPLY Above 400 ft or when adequate CL affected side............................................................ 100% OVRD PEC affected side ..................................................................RESET If successful CL affected side..................................................................AUTO If unsuccessful PEC affected side................................................................. OFF Avoid sudden PL movements Before landing CL NON AFFECTED .......................................... 100% OVRD Reverse is not available on affected side. TAXI ON BOTH ENGINES Note: ACW BTC may be check closed in order to avoid the loss of ACW bus on ground

Mod : 3973 or 4371 or 4457

72


2.11 SEP 10

500

LO PITCH IN FLIGHT PL affected side .................................................................................. FI CL affected side ................................................... FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04) ............................ APPLY

ENG OVER LIMIT PL affected side .............. RETARD TO RESTORE NORMAL VALUES Note: BLEED VALVE may be selected OFF in order to reduce ITT If TQ, NH, and/or ITT still over limit and if conditions permit PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)....................... APPLY

PROP OVER LIMIT R R R R R R R R R

PL affected side .......................... RETARD TO SET NP BELOW 106% PEC affected side ............................................................. OFF then ON PL affected side .......................................................................AS RQD If NP decreases below 106% CONTINUE NORMAL FLIGHT Note: 106% allowed to complete a flight without overshooting 73% TQ in CRZ and 75% in CLB If NP remains above 106% and conditions permit PL affected side .............................................................................. FI CL affected side ............................................... FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04) ........................ APPLY


72


2.12 OCT 08 500

ENG OIL TEMP BELOW 45°C If icing conditions are expected or present ENG POWER ...............................................If possible, INCREASE

ENG OIL TEMP HIGH OIL TEMP between 125°C and 140°C OIL TEMP AND PRESS ...................................................MONITOR Note: If OIL temperature rise follows PL reduction, advancing PL may reduce OIL temperature. Note: If OIL temperature rise occurs in steady state conditions, a power reduction should permit a reduction in OIL temperature. OIL TEMP between 125°C and 140°C for more than 20 minutes PL affected side ...........RETARD TO SET minimum possible power CAUTION: Flight plan must be rescheduled to minimize engine operating time in these abnormal conditions. OIL TEMP above 140°C PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)....................... APPLY

ENG OIL LO PR

R

PL affected side .................................................................................. FI If both OIL LO PR on CAP and local alert are activated CL affected side.............................................. FTR THEN FUEL SO SINGLE ENG OPERATION procedure (2.04)....................... APPLY If local alert only is activated CL affected side.............................................. FTR THEN FUEL SO Once engine is shut off CL affected side..........................................................................FTR If CCAS is activated after 30 seconds CL affected side............................................................ FUEL SO ENG RESTART IN FLIGHT procedure (2.08).................. APPLY If not CL affected side ............................................................ FUEL SO SINGLE ENG OPERATION procedure (2.04).................. APPLY If OIL LO PR alert on CAP only is activated DISREGARD INFORM MAINTENANCE If single engine operation required NP of feathered engine.....................................................MONITOR If NP of feathered engine above 10% APPROACH SPEED .................................INCREASE BY 10 KT


72

FOLLOWING FAILURES FUEL

2.13 SEP 13

500

FUEL ABNORMAL TEMP  If too high (>50°C) Note: Avoid rapid throttle movement OIL TEMP AND OTHER ENGINES PARAMETERS .......MONITOR  If too low (<0°C) Note: Use anti-icing additive for next refueling if repair can't be done

FUEL CLOG  If both lights are illuminated ENGINES PARAMETERS................................................MONITOR  If abnormal engines parameters LAND ASAP Note: Fuel contamination may be suspected MAINTENANCE ACTION REQUIRED  If only one light is illuminated ENGINE PARAMETERS affected side.............................MONITOR

FUEL FEED LO PR PUMP affected side ........................................................ CONFIRM ON ENGINE affected side...........MONITOR FOR POSSIBLE RUN DOWN  If engine runs down or if fuel quantity decreases significantly PL affected side ............................................................................. FI CL affected side.............................................. FTR THEN FUEL SO PUMP affected side ................................................................... OFF FIRE HANDLE affected side.....................................................PULL LAND ASAP SINGLE ENG OPERATION procedure (2.04)....................... APPLY CAUTION: Do not open X FEED valve

Model : 212A

72

FOLLOWING FAILURES FUEL

2.14 OCT 09 500

FUEL LEAK ALERT CONDITION A fuel leak may be detected by either: - sum of fuel on board (FOB), read in steady flight at cruise level, and fuel used (FU), FOB+FU significantly less than fuel at departure, or - total fuel quantity decreasing (fuel spray from engine or wing tip), or - fuel imbalance, or - a tank emptying too fast (leak from engine or a hole in a tank), or - excessive fuel flow (leak from engine), or - fuel smell in the cabin

FUEL LO LVL

R

AVOID EXCESSIVE AIRCRAFT ATTITUDES If both LO LVL lights ON LAND ASAP If LO LVL light on one side only If leak suspected FUEL LEAK procedure (2.14)........................................... APPLY If no leak suspected If FQI < 160 kg / 352 lb X FEED.............................................................................. ON If FQI ≥ 160 kg / 352 lb, Feeder jet pump malfunction is suspected X FEED is not necessary FUEL CONSUMPTION ..........................................MONITOR

FUEL LEAK When a leak is confirmed LAND ASAP Leak from engine (excessive fuel flow or feed spray from engine) PL affected side ........................................................................ FI CL affected side......................................... FTR THEN FUEL SO PUMP affected side.............................................................. OFF FIRE HANDLE affected side ...............................................PULL SINGLE ENG OPERATION procedure (2.04).................. APPLY If excessive fuel flow was identified before engine shutdown FUEL X FEED valve can be opened In all other cases X FEED valve must remain closed Leak not located FUEL X FEED............................................. MAINTAIN CLOSED Note: the X FEED must remain closed to prevent the leak affecting both sides. Before landing ATC................................................................................. NOTIFY

Mod : 4686 or 8148

72

FOLLOWING FAILURES ELEC

2.15 OCT 09 550

DC BUS 1 OFF DC GEN 1 ....................................................................................... OFF PF.................................................................................................... CM2 MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN DC SVCE AND UTLY BUS SHED.................................. MAINTAIN ON AFFECTED EQUIPMENT............................................................... OFF DC BUS 1 EQUIPMENT LIST ................................................... CHECK At touch down IDLE GATE LEVER ..................................................................PULL DC BUS 1 LOST EQUIPMENT LIST Instruments, Navigation & Com: Weather Radar Radio Altimeter (2.33) (E)GPWS DME #1 Air: Bleed LEAK IND 1 & 2 AUTO PRESS (2.26A) Flight controls: Stick Pusher (2.21) CM1 Stick Shaker (2.21)

Ice & Rain protection: CM1 and STBY Static Ports anti-icing CM1 Side Window Anti-Icing (2.32) CM2 Windshield HTG IND Engines: FF/FU#1, Fuel TEMP#1 & Fuel CLOG #1 Oil PRESS & Oil TEMP #1 AUTO IDLE GATE (2.10) Light: CM1 Dome, chartholder & reading light CM2 Flood panel light Storm light, Annunciator light test NAV & BEACON light Miscellaneous: Toilet flushing (If supplied by DC)

AC BUS 1 OFF Note: Wait for 10 seconds in order to confirm the failure. DC BTC......................................................................... ISOL THEN ON If unsuccessful AC BUS 1 EQUIPMENT LIST .............................................. CHECK AC BUS 1 LOST EQUIPMENT LIST 115 AC BUS 1 BLEED LEAK DET 1 & 2

26 AC BUS 1 TRIMS IND

For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60

Mod : 4366 and (3973 or 4371 or 4457)


72

2.15A OCT 09 150

DC BUS 2 OFF DC GEN 2 ....................................................................................... OFF PF.................................................................................................... CM1 ADC SW......................................................................... SET TO ADC 1 VHF 1 / ATC 1...........................................................................SELECT AFFECTED EQUIPMENT............................................................... OFF DC BUS 2 EQUIPMENT LIST ................................................... CHECK Before descent PAX INSTRUCTIONS.......................................................... USE PA After touch down TAXI ON BOTH ENGINES DC BUS 2 LOST EQUIPMENT LIST R R R R R R R R R R R R R R R R R

Instruments, Navigation & Com: CM2 EADI/EHSI & SGU#2 (2.32) VOR/ILS/DME#2, ADF#2, CM1 RMI VHF#2 ATC#2, TCAS or T2CAS (if installed) ADC #2 & ALT ALERT # 2 (2.32) CM2 Clock GPS (KLN90) (if installed) CCAS: CAP amber alert except Maint PNL, PRKG BRK & MFC Air: Landing elevation IND Hydraulic: DC AUX HYD PUMP (In Automatic) Landing gear: Secondary IND Flight controls: Right stick shaker Standby pitch trim control TLU auto control

Ice & Rain protection: CM2 Static Port anti-icing CM2 Probes IND CM2 Wiper CM2 Side window anti-icing (2.29) CM1 Windshield HTG IND Engines: FF/FU #2 FUEL TEMP #2, FUEL CLOG #2 OIL PRESS, TEMP #2 IDLE GATE FAIL IND Light: CM2 Chartholder, Reading LIGHTS Integrated Norm INST&PANEL LIGHTS Taxi / Take off LIGHT, Wing LIGHTS Passenger Signs Doors: Doors UNLK lights Cockpit door locking system Fire: NAC OVHT

R R R R R R R R R R R R R R R R R

AC BUS 2 OFF Note: Wait for 10 seconds in order to confirm the failure. DC BTC......................................................................... ISOL THEN ON If unsuccessful PF .............................................................................................. CM1 AC BUS 2 EQUIPMENT LIST .............................................. CHECK AC BUS 2 LOST EQUIPMENT LIST 115 AC BUS 2

R

R GPWS

26 AC BUS 2 CM2 ASI, VSI, ALTI Heading RMI#1 Bearing VOR#2&ADF#2 to RMI/SGU 1/2 Course#2 and Heading#2 Select

For more information on BUS EQUIPMENT LISTS see F COM 1.06.60

Mod : 4116 + 4366

R R R

72


2.16 OCT 09 001

ACW BUS 1 OFF / ACW BUS 2 OFF ACW GEN affected side ................................................................. OFF LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION ..................................... VISUALLY MONITOR If ACW BUS 1 OFF PF .............................................................................................. CM2 CM1 AIRSPEED INDICATOR ..........................................MONITOR If ACW BUS 2 OFF PF .............................................................................................. CM1 CM2 AIRSPEED INDICATOR ..........................................MONITOR AFFECTED EQUIPMENT............................................................... OFF HYD X FEED .................................................................................... ON ACW BUS 1 or 2 LOST EQUIPMENT LIST .............................. CHECK If any IAS discrepancy occurs DADC DATA INVALID (ADU message) procedure (2.30) .... APPLY After touch down TAXI ON BOTH ENGINES

ACW BUS 1 LOST EQUIPMENT LIST R R R R R R

Hydraulic: BLUE PUMP Lights:

Integrated INST&PNL Lights LEFT LANDING LIGHT LEFT and REAR STROBES

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

R R R R R R R

ACW BUS 2 LOST EQUIPMENT LIST R R R R R R

Hydraulic: GREEN PUMP Lights: TAXI/TO LIGHTS RIGHT LANDING LIGHT RIGHT STROBE

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

R R R R R R

72


2.16A OCT 09 001

ACW TOTAL LOSS ACW GEN 1 + 2.............................................................................. OFF HYD X FEED .....................................................................CHECK OFF LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION........................................... VISUALLY MONITOR CM1 and CM2 AIRSPEED INDICATORS ........................MONITOR ACW TOTAL LOSS EQUIPMENT LIST .................................... CHECK AFFECTED EQUIPMENT............................................................... OFF MAIN HYD PUMPS......................................................................... OFF LDG GEAR EXTENSION/RETRACTION ..................................... LOST NORMAL BRAKE ......................................................................... LOST LDG DIST ................................................................. MULTIPLY BY 1.5 Note: Refer to Part 4 to determine LDG DIST Before landing LDG GEAR LEVER ............................................................... DOWN BLUE PRESSURE................................................................ CHECK FLAPS..................................................................................AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY After touch down REVERSE............................................................................AS RQD BRAKE HANDLE ..................................................... EMER AS RQD TAXI ON BOTH ENGINES ACW TOTAL LOST EQUIPMENT LIST R R R R R R

Hydraulic: BLUE & GREEN PUMP Lights:

Integrated INST&PNL Lights LEFT & RIGHT LANDING LIGHT TAXI/TO LIGHTS

Ice & Rain protection: CM 1&2 PITOT/ALPHA/TAT Heating ANTI-ICING PROP 1&2 ANTI-ICING HORNS CM1&2 WINDSHIELD HTG ICE DETECTOR Miscellaneous: Toilet (If supplied by ACW)

For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60

R R R R R R R R

72


2.17 OCT 08 001

DC ESS BUS OFF DC ESS BUS EQUIPMENT LIST .............................................. CHECK  If Cockpit Securized Door installed COCKPIT DOOR MANUAL LOCK BOLT(S)..................................... .......................................................... MOVE TO CLOSE POSITION Note: Cockpit Door Control Panel FAULT LIGHT is inoperative. Note: When the door is locked with the manual bolt(s), the emergency access to the cockpit is unavailable. It is recommended that at least two crewmembers remain in the cockpit during that time.

R R

DC ESS BUS LOST EQUIPMENT LIST See QRH pages 2.42 (all configuration) and 2.42A (for cargo configuration only)

DC EMER BUS OFF

R R

LEAVE AND AVOID ICING CONDITIONS DESCEND TOWARD ........................................................FL100 / MEA STBY PITCH TRIM .......................................................... USE AS RQD ADC SW (ADC FAULT lights lost) ................................. SET TO ADC 2 HYD X FEED .................................................................................... ON  If ice accretion builds up on airframe DE-ICING MODE SEL FAULT procedure (2.28)................... APPLY ANTI-ICING PROP FAULT procedure (2.29) ........................ APPLY ANTI-ICING HORNS FAULT procedure (2.29) ..................... APPLY CM1 and STBY IAS ............................................COMPARE to CM2 Note: Use CM2 instruments in case of disagreement.  Before landing ANTI-SKID ................................................................................. OFF N/W STEERING ........................................................................ OFF ANTI-SKID FAULT procedure (2.25)..................................... APPLY DC EMER BUS OFF LOST EQUIPMENT LIST

R

See QRH pages 2.42 (all configuration) and 2.42A (for cargo configuration only) For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60


72

2.18 OCT 08 500

DC GEN FAULT DC GEN affected side..................................................................... OFF If OAT exceeds ISA + 25 FL........................................................................................200 MAX TAXI ON BOTH ENGINES

INV FAULT NO SPECIFIC ACTION IN FLIGHT

ACW GEN FAULT ACW GEN affected side ................................................................. OFF LEAVE AND AVOID ICING CONDITIONS TAXI ON BOTH ENGINES

DC SVCE/UTLY BUS SHED DC SVCE/UTLY BUS PB..........................................................AS RQD DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST R

See FCOM 1.06.60 pages 12 to 14

BAT CHG FAULT CHG associated.............................................................................. OFF

DUAL BAT CHG LOSS MFC MODULES, one at a time ....................................... OFF / RESET If RESET unsuccessful LAND ASAP Note: minimize use of VHF 1 if conditions permit.

BAT DISCHARGE IN FLIGHT ENG START ROTARY SELECTOR............................................... OFF If battery(ies) still discharging LAND ASAP

Mod : 3246 + 4111


72

2.18A APR 08 550

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116 + 4366

72


2.18B APR 08 500

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

Mod : 4116

72

FOLLOWING FAILURES HYDRAULIC

2.19 OCT 08 001

HYD LO LVL If blue system affected BLUE PUMP .............................................................................. OFF AUX PUMP ....................................................... OFF (CONFIRMED) REDUCED FLAPS LANDING procedure (2.21).................... APPLY z After touch down USE NORMAL BRAKE FOR STEERING TAXI ON BOTH ENGINES If green system affected GREEN PUMP........................................................................... OFF LDG DIST ............................................................ MULTIPLY BY 1.5 Note: Refer to Part 4 to determine landing distance LDG GRAVITY EXTENSION procedure (2.24) ..................... APPLY z After touch down TAXI ON BOTH ENGINES REVERSE.......................................................................AS RQD BRK HANDLE..................................................... EMER AS RQD HYD SYS LOST EQUIPMENT LIST BLUE FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on accu only)

GREEN LDG GEAR EXT / RET NORM BRK

BOTH MAIN HYD PUMPS LOSS MAIN BLUE AND GREEN PUMPS ................................................ OFF X FEED ..............................................................................CHECK OFF LDG DIST ................................................................. MULTIPLY BY 1.5 Note: Refer to Part 4 to determine landing distance z Before landing LDG GEAR LEVER ............................................................... DOWN BLUE PRESSURE................................................................ CHECK FLAPS 15 ............................................................................AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY FLAPS 30 ............................................................................AS RQD z After touch down TAXI ON BOTH ENGINES REVERSE............................................................................AS RQD BRK HANDLE.......................................................... EMER AS RQD

R R R R R

BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST BLUE recovered when GREEN LDG GEAR lever is DOWN FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on accu only)

LDG GEAR EXT / RET NORM BRK

72

FOLLOWING FAILURES HYDRAULIC

2.20 OCT 08 500

BOTH HYD SYS LOSS

R

R R R

MAIN AND AUX PUMPS ................................................................ OFF Before approach GPWS......... GPWS OVRD or FLAP OVRD (depending on version) LDG GEAR GRAVITY EXTENSION procedure (2.24).......... APPLY APP/LDG SPEED ........................VmHB 0 + 5 KT + WIND EFFECT LDG DIST ........................MULTIPLY LDG DIST FLAPS 30 BY 2.9 Note: Refer to Part 4 to determine VmHB and LDG DIST CAUTION: Tail strike may occur if pitch attitude exceeds 8° during the flare depending upon vertical speed at touch down. After touch down REVERSE............................................................................AS RQD BRK HANDLE .......................................................... EMER AS RQD TAXI ON BOTH ENGINES BOTH HYD SYS LOST EQUIPMENT LIST

R R R R

BLUE FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on accu only)

GREEN LDG GEAR EXT / RET NORM BRK

HYD LO PR / HYD OVHT PUMP affected side ........................................................................ OFF X FEED ............................................................................................. ON

Mod : 3973 or 4371 or 4457

Eng : PW127 / PW127F / PW127M

FOLLOWING FAILURES FLIGHT CONTROL

72

2.21 APR 08 500

FLAPS UNLK If before V1 TAKE OFF ............................................................................ ABORT If after V1 VR, V2.............................................................INCREASE BY 10 KT If alarm occurs during approach GO AROUND procedure ....................................................... APPLY VGA ................................................................INCREASE BY 10 KT z When possible FLAPS..............................................................................................0 REDUCED FLAPS LANDING procedure (2.21).................... APPLY

FLAPS JAM / UNCOUPLED / ASYM FLAPS CTL LEVER .....................NEAR FLAPS PRESENT POSITION z When applicable REDUCED FLAPS LANDING procedure (2.21).................... APPLY

REDUCED FLAPS LANDING GPWS .............. GPWS OVRD or FLAP OVRD (depending on version) STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED

FLAPS

LDG DIST FLAPS 30 MULTIPLY BY

APP/LDG SPEED

0

2.2

VmHB 0 + WIND EFFECT + 5 KT

15

2

VmHB 15 + WIND EFFECT

Note: Refer to Part 4 to determine VmHB and LDG DIST CAUTION: Tail strike may occur if pitch attitude exceeds 8° during the flare depending upon vertical speed at touch down.

STICK PUSHER / SHAKER FAULT STICK PUSHER / SHAKER ........................................................... OFF TCAS (if installed) ................................................................... TA ONLY VmHB / VmLB FOR ALL CONFIGURATION ......INCREASE BY 10 KT LDG DIST ............................................................... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

Mod : 3973 or 4371 or 4457

Eng : PW127 / PW127F / PW127M

72


2.22 OCT 09 001

PITCH TRIM ASYM (LOCAL LIGHT) AP DISCONNECTION ...................................... CONFIRM MANUALLY PITCH TRIM INOPERATIVE procedure (2.22) .......................... APPLY

PITCH TRIM INOPERATIVE EXISTING CONFIGURATION AND SPEED .......................................... .................................................... MAINTAIN AS LONG AS POSSIBLE For approach STEEP SLOPE APPROACH (≥4.5°)...........................PROHIBITED FLAPS................ EXTEND AT VFE FOR EACH CONFIGURATION LDG SPEED ...................................................INCREASE BY 10 KT LDG DIST .......................................................... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

R R R

R R

DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL If YD is available YD ...................................................................................... ENGAGE If YD is not available LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTED RUDDER PEDAL MOVEMENT

PITCH DISCONNECT BOTH CONTROL COLUMNS ........................................ CHECK FREE IAS ....................................................................................... 180 kt MAX LOAD FACTOR ............................................................................... 2 g MAX BANK ANGLE ............................ 30° MAX UNTIL FLAPS EXTENSION AVOID ICING CONDITIONS For approach STEEP SLOPE APPROACH (≥4.5°)...........................PROHIBITED LAND AT AIRPORT WITH MINIMUM CROSSWIND LDG SPEED ...................................................INCREASE BY 10 KT LDG DIST .......................................................... MULTIPLY BY 1.13 PL 1 + 2 ..................................... REDUCE SMOOTHLY TO FLARE Note: Refer to Part 4 to determine LDG DATA When on ground and ELEV CLUTCH GUARDED PB installed PITCH RECONNECTION ON GROUND procedure (2.22A) ............ ............................................................................................... APPLY


72

2.22 JUL 15

100

PITCH TRIM ASYM (LOCAL LIGHT) AP DISCONNECTION..................................... CONFIRM MANUALLY PITCH TRIM INOPERATIVE procedure (2.22).......................... APPLY

PITCH TRIM INOPERATIVE EXISTING CONFIGURATION AND SPEED ........................................ .................................................. MAINTAIN AS LONG AS POSSIBLE For approach STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED FLAPS ............... EXTEND AT VFE FOR EACH CONFIGURATION LDG SPEED................................................. INCREASE BY 10 KT LDG DIST ........................................................MULTIPLY BY 1.13 Note: Refer to Part 4 to determine VmHB / VmLB and LDG DIST

DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL If YD is available YD .................................................................................. ENGAGE If YD is not available LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTED RUDDER PEDAL MOVEMENT

PITCH DISCONNECT BOTH CONTROL COLUMNS ...................................... CHECK FREE IAS .................................................................................... 180 kt MAX LOAD FACTOR ............................................................................ 2 g MAX BANK ANGLE ........................... 30° MAX UNTI L FLAPS EXTENSION

R

AVOID ICING CONDITIONS For approach STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED LAND AT AIRPORT WITH MINIMUM CROSSWIND LDG SPEED................................................. INCREASE BY 10 KT LDG DIST ........................................................MULTIPLY BY 1.13 PL 1 + 2 .................................... REDUCE SMOOTHLY TO FLARE Note: Refer to Part 4 to determine LDG DATA At parking If pitch disconnect occurred in flight MAINTENANCE ACTION REQUIRED If pitch disconnect occurred on ground PITCH RECONNECTION ON GROUND procedure (2.22A)................. APPLY

Mod 3529 or 3530


72

2.22A APR 08 500

PITCH RECONNECTION ON GROUND (if applicable) GUST LOCK ........................................................................... ENGAGE BOTH COLUMNS ...................................................... CHECK LOCKED ELEV CLUTCH GUARDED PB .........................DEPRESS AND HOLD z When PITCH DISCONNECT flashes red on CAP ELEV CLUTCH GUARDED PB ........................................ RELEASE PITCH DISCONNECT ON CAP ...............CHECK EXTINGUISHED BOTH COLUMNS.............................................. CHECK COUPLED

TLU FAULT If ADC 1 + 2 are lost If IAS above 185 kt TLU ...................................................................................HI SPD If IAS below 185 kt TLU ................................................................................. LO SPD DISREGARD TLU FAULT ALERT If at least one ADC operates If IAS above 185 kt TLU ...................................................................................HI SPD If TLU FAULT alarm persists SPEED ............................................................... 180 KT MAX TLU............................................................................ LO SPD If IAS below 185 kt SPEED..................................................................... 180 KT MAX TLU ................................................................................. LO SPD DISREGARD TLU FAULT ALERT If TLU green light is not lit VAPP ....................................................INCREASE BY 10 KT LDG DIST ................................................ MULTIPLY BY 1.13 LAND AT AIRPORT WITH MINIMUM CROSSWIND Note: Maximum demonstrated crosswind (dry runway) with TLU HI SPD mode : 15 kt.

AIL LOCK LIT If before take off RETURN TO PARKING REFER TO MMEL ATA 27 ITEM 70-1 GUST LOCK SYSTEM If after landing TAKE SPECIAL CARE FOR TAXI (WIND EFFECTS) USE STANDBY SYSTEM FOR AILERON LOCK AT PARKING INFORM MAINTENANCE

Mod : 4373 or 8167

72


2.23 APR 08 001

ELEVATOR JAM CONTROL COLUMNS ...................................................... UNCOUPLE AVOID ICING CONDITIONS IAS ..................................................................................... 180 KT MAX If one elevator is stuck to full down position IAS ................................................................................ 154 KT MAX If left elevator is jammed MINIMUM MANEUVER OPERATING SPEEDS..........INCREASE BY 10 KT If elevator jamming occurs at take off IAS ................................................................................ 161 KT MAX PITCH DISCONNECT procedure (2.22)..................................... APPLY

AILERON JAM / SPOILER JAM BANK ANGLE LIMIT................................................................ 25° MAX BLUE AND AUX HYD PUMPS ....................................................... OFF LAND AT AIRPORT WITH MINIMUM CROSSWIND z For approach STEEP SLOPE APPROACH (≥4.5°).......................... PROHIBITED BLUE AND AUX HYD PUMPS.................................................... ON CAUTION: Do not extend FLAPS in turn z When in landing configuration BLUE AND AUX HYD PUMPS.................................................. OFF z Immediately after touch down BLUE AND AUX HYD PUMPS.................................................... ON

RUDDER JAM STEEP SLOPE APPROACH (≥4.5°) ............................... PROHIBITED LANDING ............................................................................... FLAPS 30 USE DIFFERENTIAL POWER SO AS TO MINIMIZE SIDESLIP LAND AT AIRPORT WITH MINIMUM CROSSWIND z At touch down NOSE DOWN BEFORE REDUCTION BELOW FI

72

FOLLOWING FAILURES LANDING GEAR

2.24 APR 08 001

LDG GEAR GRAVITY EXTENSION LDG GEAR LEVER..................................................................... DOWN EMER EXTENSION HANDLE .........PULL ABOVE PEDESTAL LEVEL .....................AND MAINTAIN UP TO GREEN LIGHTS ILLUMINATED CAUTION: Do not twist the handle when operating TCAS (if installed) ................................................................... TA ONLY If unsuccessful LANDING WITH ABNORMAL LDG GEAR procedure (2.24) ............ APPLY

LANDING WITH ABNORMAL LDG GEAR z Preparation CABIN CREW (PA).............................................................. NOTIFY ATC / TRANSPONDER ...................................... NOTIFY / AS RQD SEAT BELTS / NO SMOKING .................................................... ON GPWS ........................................................................................ OFF CABIN AND COCKPIT .................................................... PREPARE LOOSE AND SURVIVAL EQUIPMENT ............ CHECK SECURED BELTS AND SHOULDER HARNESS .................. CHECK LOCKED FUEL WEIGHT .......................................... IF POSSIBLE, REDUCE If abnormal nose LDG GEAR CG LOCATION ..............................................IF POSSIBLE, AFT If abnormal main LDG GEAR FUEL UNBALANCE .........................IF POSSIBLE, ESTABLISH Note: Reduced fuel on side with failed LDG GEAR. z Approach LDG GEAR LEVER ............................................. CONFIRM DOWN LDG GEAR EMER EXT HANDLE .....................CONFIRM PULLED ENG START ROTARY SELECTOR.............. OFF / START ABORT CABIN REPORT........................................... CONFIRM OBTAINED z Before landing BLEEDS 1 + 2............................................................................ OFF BRACE FOR IMPACT ..........................................................ORDER z At touch down PL 1 + 2 .........................................................................................GI CL 1 + 2 .......................................................... FTR THEN FUEL SO z After touch down FIRE HANDLES 1 + 2 ..............................................................PULL z When aircraft stopped PARKING BRAKE ......................................................................SET CABIN CREW (PA).............................................................. NOTIFY FUEL PUMPS 1 + 2................................................................... OFF AGENTS 1 + 2 ....................................................................... DISCH EVACUATION ....................................................................INITIATE z Before leaving aircraft BAT ............................................................................................ OFF

72

FOLLOWING FAILURES LANDING GEAR

2.25 SEP 10

001

LDG GEAR UNSAFE INDICATION  If LDG GEAR selected DOWN  If GREEN LIGHT OFF on one panel only UNSAFE INDICATION ........................................... DISREGARD  If GREEN LIGHT OFF on both panels LDG GEAR GRAVITY EXTENSION procedure (2.24) .... APPLY  If LDG GEAR selected UP  If RED LIGHT ON on one panel only UNSAFE INDICATION ........................................... DISREGARD  If RED or GREEN LIGHT ON on both panels LEAVE AND AVOID ICING CONDITIONS IAS ........................................................................... 160 KT MAX LDG GEAR ....................................................................... DOWN TCAS (if installed)......................................................... TA ONLY

LDG GEAR RETRACTION IMPOSSIBLE LEAVE AND AVOID ICING CONDITIONS LDG GEAR LEVER..................................................................... DOWN IAS ..................................................................................... 185 KT MAX CCAS .............................................................................................. RCL TCAS (if installed) ................................................................... TA ONLY IDLE GATE ............................................................................MONITOR

ANTI-SKID FAULT R

ANTI SKID ...................................................................................... OFF LDG DIST ................................................................. MULTIPLY BY 1.4 Note: Refer to Part 4 to determine LDG DIST  At touch down REVERSE............................................................................AS RQD NORMAL BRAKE ................................................. USE WITH CARE BRAKE HANDLE ..................................................... EMER AS RQD

BRK TEMP HOT  If BRK TEMP HOT occurs before take off TAKE OFF .............................................................................DELAY  If BRK TEMP HOT occurs in flight LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF FOR COOLING EXCEPT IN CASE OF EMERGENCY

72

FOLLOWING FAILURES AIR

2.26 APR 08 001

BLEED VALVE FAULT PACK VALVE affected side ............................................................ OFF BLEED VALVE affected side .......................................................... OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

BLEED OVHT PACK VALVE affected side ............................................................ OFF BLEED VALVE affected side .......................................................... OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

BLEED LEAK PACK VALVE affected side ............................................................ OFF BLEED VALVE affected side .......................................................... OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES CAUTION: System must not be restored in flight. Note: If a bleed leak occurs on ground during taxi, go back to parking.

X VALVE OPEN CAUTION: Do not supply both packs from one single bleed.

PACK VALVE FAULT PACK VALVE affected side ............................................................ OFF MAX FL ..................................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

BOTH PACK VALVES FAULT MAX FL ..................................................................................100 / MEA z When ΔP < 1 PSI OVBD VALVE ............................................................... FULL OPEN MAN RATE KNOB ..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN MAN RATE KNOB ................................................. MAX INCREASE

RECIRC FAN FAULT RECIRC FAN affected side ............................................................ OFF


72

2.26A OCT 08 001

DUCT OVHT TEMP SEL affected side.................................................................MAN COMPT TEMP SELECTOR affected side ....................................COLD CAUTION: Monitor DUCT TEMP and make sure it remains positive to avoid possible pack turbine damage due to freezing. If alert persists PACK VALVE affected side ....................................................... OFF MAX FL .............................................................................200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES

EXCESS CAB ALT

R

CABIN PRESS IND.................................................................... CHECK If rapid decompression EMERGENCY DESCENT procedure (1.07A) ....................... APPLY If Z cabin > 10000 ft confirmed MAN RATE KNOB ..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN MAN RATE KNOB .........................................................DECREASE If unsuccessful CREW OXYGEN MASKS............................................................ ON CREW COMMUNICATIONS .........................................ESTABLISH OXYGEN PAX SUPPLY ......................................................AS RQD OXYGEN PRESSURE.......................................................... CHECK DESCENT.................................................................AS RQD / MEA

AUTO PRESS FAULT MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN MAN RATE KNOB ............................... AS RQD TO SET CABIN RATE FL

140

170

200

250

TARGET CAB ALT (ft)

0

2000

4000

6750

Note: Minimum TARGET CAB ALT is landing elevation

EXCESS CAB ΔP MAN RATE KNOB ...............................................................9 O'CLOCK CAB PRESS MODE SEL................................................................MAN MAN RATE KNOB ...................................................... MAX INCREASE If unsuccessful DESCENT TO A COMPATIBLE FL....................................INITIATE

72


2.27 APR 08 001

AVIONICS VENT EXHAUST MODE FAULT EXHAUST MODE ........................................................................ OVBD

OVBD VALVE FAULT CAUTION: Do not select OVBD valve FULL OPEN if ΔP > 1 PSI. If engine 1 running, in flight or on ground OVBD VALVE ............................................................. FULL CLOSE If engine 1 not running, on ground OVBD VALVE ............................................................... FULL OPEN

72

FOLLOWING FAILURES DE/ANTI ICE

2.28 SEP 13

500

AFR AIR BLEED FAULT

R

LEAVE AND AVOID ICING CONDITIONS AFR AIR BLEED ............................................................................. OFF  If DE-ICING ENG FAULT light illuminates after 6 s DE-ICING ENG affected side .................................................... OFF AFR AIR BLEED.......................................................................... ON AFR AIR BLEED light ....................................CHECK EXTINGUISH  If DE-ICING ENG FAULT light does not illuminate on any side DE-ICING AIR FRAME FAULT procedure (2.28).................. APPLY

DE-ICING AIR FRAME FAULT DE-ICING AIR FRAME ................................................................... OFF LEAVE AND AVOID ICING CONDITIONS MINIMUM ICING SPEEDS ................................... INCREASE BY 10 kt  If in icing conditions LDG DIST .......................................................... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine SPEEDS and LDG DIST  If ice accretion STEEP SLOPE APPROACH (4.5°)...........................PROHIBITED

DE-ICING MODE SEL FAULT OVRD........................................................................................SELECT MONITOR DE-ICING  In case of engine flame out OVRD................................................................................ RELEASE

MODE SEL AUTO FAULT MODE SEL .....................................................................................MAN DE-ICING and ANTI-ICING MANUAL MODE PBs: ACCORDING TO CURRENT SAT ...........................................SELECT

Model : 212A

72

FOLLOWING FAILURES DE/ANTI ICE

2.29 OCT 09 500

ICE DETECT FAULT ICE ACCRETION................................................ VISUALLY MONITOR

DE-/ANTI-ICING ENG FAULT LEAVE AND AVOID ICING CONDITIONS ENGINE PARAMETERS affected side..................................MONITOR

ANTI-ICING PROP FAULT LEAVE AND AVOID ICING CONDITIONS ANTI-ICING PROP affected side.................................................... OFF If propeller unbalance due to ice becomes excessive CL 1 + 2 ......................... MOVE TO 100% OVRD FOR 5 MINUTES

ANTI-ICING HORNS FAULT LEAVE AND AVOID ICING CONDITIONS If in icing conditions, every 5 minutes FLIGHT CONTROLS ............. CHECK FREEDOM OF MOVEMENT

R

SIDE WINDOW / WINDSHIELD HTG FAULT SIDE WINDOW / WINDSHIELD HTG affected side....................... OFF

PROBES HTG FAULT If One PROBE HTG ALPHA illuminated STICK PUSHER / SHAKER .............................................MONITOR If Two PROBE HTG ALPHA illuminated STICK PUSHER / SHAKER ...................................................... OFF STICK PUSHER / SHAKER procedure (2.21)....................... APPLY If PROBE HTG other than ALPHA illuminated ADC non affected side....................................................SELECTED Associated INDICATION ..................................................MONITOR

Mod : 3973 or 4371 or 4457

FOLLOWING FAILURES AUTO PILOT

72

2.30 OCT 08 550

AILERON MISTRIM (ADU message) – or – EXCESSIVE LATERAL TRIM REQUIRED – or – ABNORMAL FLIGHT CHARACTERISTICS FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT Note: FLY MANUALLY PRIOR TO ADJUSTING THE LATERAL TRIMS Note: The autopilot may be reengaged following adjustment of the lateral trims

PITCH MISTRIM (ADU message) FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS

PITCH TRIM FAIL (ADU message) FLIGHT CONTROLS ...............................................HOLDING FIRMLY AP ...................................................................................DISCONNECT Note: FLY MANUALLY UNTIL RESUMING NORMAL CONDITIONS

DADC DATA INVALID (ADU Message) INSTRUMENTS ............................................................ CROSSCHECK FAULTY ADC......................................................................... IDENTIFY ADC SW............................................................... SELECT VALID ADC If ADC 1 is wrong C/B ADC 1 EMER SPLY...........................................................PULL C/B MFC 1A AUX / ADC 1 HOT SPLY.....................................PULL If ADC 2 is wrong C/B ADC 2 ................................................................................PULL ADC FAULT procedure (2.32) ................................................... APPLY

Mod : 3168 + 4366

72

FOLLOWING FAILURES AND ABNORMAL MPC

2.30A APR 08 100

APPLICABLE TO AIRCRAFT FITTED WITH MODIFICATION 5567 or 8392 or 8442

APM FAULT APM ..................................................................................................OFF For troubleshooting see FCOM 2.02.21.

DEGRADED PERF Mainly appears in level flight after CRUISE SPEED LOW or in climb, to inform the crew that an abnormal drag increase induces a speed decrease or a loss of rate of climb The most probable reason is an abnormal ice accretion AIRFRAME DE-ICING ON......................................................... CHECK IAS > RED BUG + 10 KT .......................................................MONITOR AP (if engaged) ................HOLD FIRMLY CONTROL WHEEL and DISENGAGE If SEVERE ICING conditions confirmed – or – If impossibility to maintain IAS > RED BUG + 10 KT in level flight – or – If abnormal aircraft handling feeling SEVERE ICING procedure (1.09) ......................................... APPLY If not SCHEDULED FLIGHT....................................................CONTINUE ICING CONDITIONS and SPEED....................................MONITOR

INCREASE SPEED Appears after DEGRADED PERF to inform the crew that the drag is abnormally high and IAS is lower than RED BUG + 10 KT If abnormal conditions confirmed IMMEDIATELY PUSH THE STICK TO INCREASE SPEED TO RECOVER MINIMUM IAS = RED BUG + 10 KT SEVERE ICING procedure (1.09) ......................................... APPLY

72

FOLLOWING FAILURES AVIONICS

2.31 SEP 13

001

AUDIO SEL FAULT AUDIO SEL affected side ............................................................. ALTN

AHRS A / ERECT FAIL ATT / HDG PB affected side................................................. DEPRESS  When possible AIRCRAFT .................................... STABILIZE SPEED AND LEVEL AHRS affected side, PUSH TO ERECT PB ...................................... .................................................DEPRESS FOR 15 SECONDS

EFIS COMP R

 If ROL, PIT, ATT, HDG cautions appears on EFIS BOTH EADI, STBY HORIZON ................................ CROSSCHECK WRONG INSTRUMENT ................................................... IDENTIFY ATT / HDG PB affected side............................................ DEPRESS  If HDG cautions appears on EFIS HDG/TK/GPS/ STBY COMPASS ............................ CROSSCHECK WRONG INSTRUMENT ................................................... IDENTIFY ATT / HDG PB affected side............................................ DEPRESS  If AHRS 1 is wrong C/B AHRS 1 NORM SPLY ..................................................PULL C/B AHRS 1 AUX SPLY ......................................................PULL  If AHRS 2 is wrong C/B AHRS 2 NORM SPLY ..................................................PULL C/B AHRS 2 AUX SPLY FLT...............................................PULL Note: C/Bs deselection allows AP reconnection  If LOC / GS / ILS caution appears on EFIS NAV SOURCES.................................................................... CHECK VOR / ILS PB affected side .............................. DEPRESS AS RQD

ADC SW FAULT ADC SW........................................................ SET TO OPPOSITE ADC

72

FOLLOWING FAILURES AVIONICS

2.32 APR 08 550

ADU FAILURE IAS / VS MODE....................................................................... USE TCS Note: ALT SEL mode is lost If amber "AP MSG" appears on EADI or If in composite mode FLIGHT CONTROLS ................................................ HOLD FIRMLY AP ..............................................................................DISCONNECT

ADC FAULT VALID ADC ...............................................................................SELECT PF.............................................................................. NON affected side AP COUPLING ......................................................... NON affected side ATC .................................................................NON affected equipment If ADC 1 is lost LANDING ELEVATION ...................... PRESSURE ALTITUDE SET GPWS ........................................................................................ OFF If ADC 1 + 2 are lost STBY INST ................................................................................ USE MAN RATE KNOB ..........................................................9 O'CLOCK CAB PRESS MODE SEL...........................................................MAN ENGINE PARAMETERS ..................................................MONITOR TCAS (if installed).................................................................... STBY GPWS ........................................................................................ OFF TLU ................................................................................MAN MODE TLU FAULT procedure (2.22A) ............................................. APPLY Note: If both ADC are lost, De-/Anti-Icing AUTO Mode Selection is lost.

AHRS FAIL ATT / HDG PB affected side................................................. DEPRESS Periodically compare remaining AHRS outputs to STBY INST

SGU FAIL EFIS SG PB affected side .................................................... DEPRESS

CRT FAIL CRT affected................................................................................... OFF

Mod : 5205

Model : 212A

72

FOLLOWING FAILURES MISCELLANEOUS

2.32A OCT 09 200

COCKPIT DOOR CONTROL PANEL FAULT (if installed) COCKPIT DOOR MANUAL LOCK BOLT(S) .......................................... ............................................................... MOVE TO CLOSE POSITION Note: when the door is locked with the manual bolt(s), the emergency access to the cockpit is unavailable. It is recommended that at least two crewmembers remain in the cockpit during that time.

VOLCANIC ASH ENCOUNTER FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180° TURN AND STARTING DESCENT (IF MSA PERMITS) ATC ........................................................................................... NOTIFY PL 1 + 2 (If conditions permit) ..................................................RETARD SPEED BUG TO VmHB...................................................................SET HDG MODE ........................................................................HIGH BANK CREW OXY MASKS ............................................................. ON / 100% CABIN CREW ........................................................................... NOTIFY PASSENGER OXYGEN ...........................................................AS RQD AIR FLOW ......................................................................................HIGH ENG PARAMETERS .............................................................MONITOR AIRSPEED INDICATORS......................................................MONITOR Note: Reducing TQ reduces ash ingestion, maximizes engine surge margin and lowers engine turbine temperature. Monitor particularly ITT; it may become necessary to set PL to Flight Idle, if conditions permit. Note: In extreme case, it may be necessary to consider precautionary engine shut down and engine restart in flight. If both engines flame out, refer to BOTH ENGINE FLAME OUT procedure (1.03) Note: Volcanic ash may clog the pitot probes resulting in unreliable speed indications. If airspeed is unreliable or lost, adjust airplane attitude and torque.

Mod: 4111

72

FOLLOWING FAILURES MISCELLANEOUS

2.33 SEP 10

001

LOSS OF RADIO ALTIMETER INFORMATION GPWS ............................................................................................. OFF TCAS (if installed) ......................................................................... STBY CAUTION: LDG GEAR NOT DOWN undue warning may be generated when reducing PL; this alarm may be cancelled by using EMER AUDIO CANCEL.

R

SMK DET FANS FAULT FAN............................................................................................... ALTN

DOORS UNLK IN FLIGHT  If any door except FWD COMPT SIGNS.......................................................................................... ON ASSOCIATED DOOR.........................................VISUALLY CHECK  If unlocked or check not feasible LANDING ELEVATION .....................................................9000 ft MAX FL........................................................................100 / MEA  If FWD COMPT NO ACTION

COCKPIT WINDOW CRACKED WINDOW HEAT affected................................................................ OFF LANDING ELEVATION................................................................9000 ft MAX FL ..................................................................................100 / MEA

OXYGEN LO PR OXY MAIN SUPPLY ...................................................... OFF THEN ON  If OXYGEN LO PR light remains illuminated MAIN SUPPLY........................................................................... OFF OXYGEN PORTABLE UNIT.......... INSTALL IN COCKPIT AS RQD

72

FOLLOWING FAILURES MFC

2.34 OCT 08 001

MFC 1A FAULT R R

MODULE 1A .................................................................... OFF / RESET MFC 1A MODULE LOST EQUIPMENT LIST............................ CHECK

R

MFC 1A MODULE LOST EQUIPMENT LIST MECHANIC CALL IND DC BUS 1 OFF WARNING AC BUS 1 SPLY INV 1 FAULT LIGHT

LDG GEAR PRIMARY UNLK IND BLEED HP VALVE 1 FWD COMPT DOOR UNLK IND EMER HATCH UNLK IND RIGHT AFT DOOR UNLK IND, if applicable

MFC 1B FAULT R R

MODULE 1B .................................................................... OFF / RESET MFC 1B MODULE LOST EQUIPMENT LIST............................ CHECK If failure during take off PACK 1 ...................................................................................... OFF OVBD VALVE ............................................................... FULL OPEN z Prior take off PACK 2 ................................................................................. OFF z After take off PACKS.................................................................................... ON OVBD VALVE ........................................................ FULL CLOSE LDG GEAR ......LEAVE DOWN FOR COOLING FOR 1 MINUTE ..........AFTER TAKE OFF EXCEPT IN CASE OF EMERGENCY z After landing PACK 1 ...................................................................................... OFF OVBD VALVE ............................................................... FULL OPEN CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and cockpit communication hatch must be open.

R

MFC 1B MODULE LOST EQUIPMENT LIST GROUND FAN 1 OUTFLOW VALVE OPENING AFTER LANDING OVBD VALVE AUTO FUNCTIONING CVR ERASE

DC STBY BUS UNDV DETECT INV 1 FAULT LIGHT GREEN PUMP LO PR IND BRAKE OVERTEMP ALERTS LH / RH BLEED VALVE 1 FAULT IND

72


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


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


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


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


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


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


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


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


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


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


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


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


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


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


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


SEP 13

160

BEFORE PROPELLER ROTATION CM1

CM2

LOADSHEET ……...……………..CHECK GNSS WEIGHT & FUEL........…UPDATE SPEED BUGS ................. SET & CHECK TRIMS ........................................ CHECK BOOST ....................... ON(if necessary) The BOOST is effective only when the engine is thermally limited. Select ON, only when a gain in payload is necessary. TAIL PROP ..........................ON BOARD DOORS .................................... CLOSED SEAT BELTS......................................ON BEACON………………………….. ......ON NWS (if push back)………………..…OFF

GNSS WEIGHT & FUEL........…UPDATE SPEED BUGS................. SET & CHECK TRIMS.............................................. SET START UP CLEARANCE………OBTAIN CDLS .................................................ON

BEFORE PROPELLER ROTATION C/L

BEFORE TAXI CM1

CM2

PROP BRK RDY LT....................CHECK PROP BRK SW ................................OFF

When NP stabilized

CL 2 ........................................MAX RPM LO PITCH ………………………...CHECK ACW GEN 2……………………..ON LINE ACW BTC……………………….CLOSED HYD……………………………….CHECK ANTI-ICING............................... AS RQD ANTI-SKID ..................................... TEST FLAPS .......................................... ….15° ENGINE 1 …………………...……START When NP stabilized

CL 1. .......................................MAX RPM LO PITCH ………………...………CHECK ACW GEN 1……………………..ON LINE ACW BTC .....................................OPEN XPDR……………………...AS REQUEST COCKPIT COM HATCH… ....... CLOSED NWS……………….……...………….…ON BEFORE TAXI C/L

TAXI CM1

CM2 TAXI CLEARANCE ……………..OBTAIN

TAXI & TO LIGHTS ........................... ON BRAKES…………………………..CHECK INSTRUMENTS………………… CHECK

BRAKES .....................................CHECK INSTRUMENTS………………… CHECK

AFCS ......................................... CHECK

AFCS .............................................. SET TO CONFIG ................................... TEST

TO DATA …………………………CHECK TAKE OFF BRIEFING......... COMPLETE CABIN REPORT …………….OBTAINED

ATC CLEARANCE ……………...OBTAIN TO DATA …………………………CHECK TAKE OFF BRIEFING .........COMPLETE

TAXI C/L Mod: 5908

Eng: PW127M

3.10


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


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


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


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


SEP 13

001

LANDING PF

PNF At DH +500 ft (Or MDA + 500ft)

“CHECK”..............................ANNOUNCE

“500 ”………MONITOR or ANNOUNCE At DH +100 ft (Or MDA + 100ft)

“100”............. MONITOR or ANNOUNCE “CHECK”..............................ANNOUNCE

At DH (Or MDA)

“MINIMUM”..........................ANNOUNCE “CONTINUE”.......................ANNOUNCE or

“GO AROUND, SET PWR, FLAPS”……. ……ANNOUNCE (Check GA Procedure) FLIGHT PARAMETERS .............CHECK AP …………………………DISCONNECT

After touch down

R

PL ........................................................GI REVERSE........................USE AS RQD

After touch down

IDLE GATE……… AUTO RETRACTION BOTH LOW PITCH LIGHT..........CHECK “2 LOW PITCH”..................ANNOUNCE When reaching 70 Kt

“SEVENTY KNOTS”……….ANNOUNCE

CM1

CM2

When reaching 70 Kt

“I HAVE CONTROL”….....ANNOUNCE NOSE WHEEL STEERING ...CONTROL

CONTROL WHEEL......HOLD AS RQD

R


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


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


3.17 NOV 11 001

LEAVING THE AIRCRAFT CM1

CM2 OXYGEN MAIN SUPPLY ..............OFF ICE & RAIN PROT.........................OFF EXT LIGHTS..................................OFF EMER EXIT LIGHT................. DISARM RADAR ..........................................OFF CL 2.......................................FUEL SO FUEL PUMPS 1 + 2.......................OFF CDLS.............................................OFF EXT PWR (if used)…………………OFF BAT ...............................................OFF LEAVING THE AIRCRAFT C/L

72

NORMAL PROCEDURES DAILY CHECKS

3.18 SEP 13

150

ATPCS – dynamic test (last flight of the day) Conditions: - PL 1 + 2 .................................................................................................................. GI - CL 1 + 2 ........................................................................................................... AUTO - ATPCS P/B depressed in, OFF light extinguished - PWR MGT on TO position Check the following results : Turn the ATPCS knob to the left to the arm position and check - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION ............................................................................ DECREASE Turn the ATPCS knob to ENG 1 position and check : - ENG 2 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 2 .......................................................................................................NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 1 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED Turn the ATPCS knob to the right to the arm position and check : - ARM light .............................................................................................ILLUMINATES - TQ INDICATION ....................................................................................... INCREASE - NP & NH INDICATION ............................................................................ DECREASE Turn the ATPCS knob to ENG 2 position and check : - ENG 1 UPTRIM LIGHT ........................................................................ILLUMINATES - TQ 1 .......................................................................................................NO CHANGE - NP, NH....................................................................................INCREASE SLIGHTLY - TQ 2 needles indication ................................................... DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered : - ARM light ................................................................................. EXTINGUISHED

R

CAUTION: Do not perform ENG TEST while taxiing as ACW is temporarily lost and consequently, both main HYD pumps are temporarily lost as well. Note: If ENG TEST must be repeated, wait 10 minutes before setting ATPCS.selector in ENG position in order not to damage feathering pumps. (Winding heating).

Mod: 3973 or 4371 or 4457

Eng: PW127 – PW127F – PW127M

72


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


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


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


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


NORMAL HIGH AIR AIR COND COND ON ON


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


Model : 212A

4.12A

OPS DATA 72

OCT 08 500 PW127M - BOOST ON RESERVE TAKE OFF TORQUE COMPUTED FOR VC = 50. KT

SAT (oC)




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


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)




0.

1000.

2000.

3000.

4000.

5000.

6000.

7000.

8000.

8500.

- 40. - 10. - 8. - 6. - 4.

- 63. - 27. - 24. - 22. - 19.

- 71. - 35. - 32. - 30. - 27.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

- 2. 0. 2. 4. 6.

- 17. - 14. - 12. - 10. - 7.

- 25. - 22. - 19. - 17. - 14.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 100. 100. 100.

100. 100. 99.3 98.1 96.9

99.5 98.3 97.2 96.1 94.9

8. 10. 12. 14. 16. 18. 20. 22. 24. 26. 28. 30. 32. 34. 36. 38. 40. 42. 44. 46. 48. 50. 52. 54. 56.

- 5. - 12. - 2. - 9. 0. - 7. 3. - 4. 5. - 1 8. 2. 10. 4. 13. 7. 15. 10. 18. 13. 20. 16. 23. 18. 25. 21. 28. 24. 30. 27. 33. 30. 36. 32. 38. 35. 41. 38. 43. 41. 46. 43. 48. 46. 51. 49. 53. 52. 55. 54.

100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 99.1

100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 99.4 97.3 95.2

100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 99.4 97.5 95.5 93.6 91.7 89.9 88.0 86.1 84.3 82.4 80.5

100. 100. 100. 100. 100. 100. 100. 100. 100. 99.0 97.2 95.4 93.5 91.7 89.9 88.0 86.2 84.4 82.6 80.9 79.1

100. 100. 100. 100. 98.8 97.4 95.7 94.0 92.4 90.7 89.1 87.4 85.7 84.0 82.3 80.7 79.0 77.4 75.7

99.9 98.7 97.5 96.1 94.8 93.4 91.8 90.2 88.6 87.0 85.4 83.8 82.2 80.6 79.0 77.4 75.8 74.2

95.8 94.6 93.5 92.2 90.9 89.5 88.0 86.5 85.0 83.4 81.9 80.4 78.8 77.3 75.7 74.2 72.7

93.8 92.6 91.5 90.3 89.0 87.7 86.2 84.7 83.2 81.7 80.2 78.7 77.2 75.6 74.1 72.6 71.1

93.1 91.0 88.9 86.8 84.7

100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 99.5 97.5 95.6 93.6 91.7 89.7 87.8 85.8 83.9 82.0

100. 100. 100. 100. 100. 100. 99.8 98.0 96.3 94.6 92.8 91.1 89.3 87.6 85.8 84.1 82.4 80.7 78.9 77.2

96.9 94.7 92.5 90.4 88.2

100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 100. 99.5 97.5 95.5 93.4 91.4 89.4 87.4 85.4 83.3

The part in bolt is the flat rated zone; engine mechanical limit. The part below is the area where the thermodynamical limit is reached first. Note: Add 0.8% for each 10 kt above 125 kt without exceeding 100% torque

Eng : PW127M

Model : 212A

4.31

OPS DATA

13 t

72

DEC 14 500

Speeds

Normal

Icing

NON LIMITING RWY TAKE-OFF (Flaps 15)

V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

110 (Flaps 0)

110 (Flaps 15)

DRIFT DOWN VmLB MINI EN ROUTE FINAL APPROACH GO AROUND

FLIGHT LEVEL

VmHB (Flaps 30) VGA (Flaps 15)

105 (Flaps 0)

99 (Flaps 15) 126 (Flaps 0)

95

95

93

94

MAX CRUISE 2 ENGINES ∆ ISA -10

-5

0

+5

+10

+15

+20

80

94.2 457 252 275

94.5 461 251 277

94.5 463 250 279

89.8 447 245 275

84.8 430 239 270

80.2 413 233 267

75.7 397 228 262

100

94.5 452 250 281

94.5 455 249 283

90.8 442 245 280

86.2 426 239 276

81.4 409 233 272

76.9 393 227 268

72.7 378 222 264

120

94.2 448 248 287

90.6 434 243 284

86.7 420 238 281

82.8 406 233 278

78.5 391 228 274

74.2 376 222 270

70.2 362 217 266

140

90.1 430 241 288

86.8 415 237 286

83.5 403 233 284

79.8 388 228 280

76.1 376 223 277

72.1 362 218 273

68.1 347 212 269

160

85.6 409 235 289

83.0 398 231 287

79.9 384 227 285

76.7 372 223 282

73.2 359 218 279

69.8 347 213 276

66.0 333 208 271

80.6 386 227 289 75.1 361 219 287

78.1 375 224 287 72.8 350 216 286

75.5 363 220 285 70.5 340 212 284

72.6 351 216 283 68.1 329 209 282

69.5 340 212 280 65.5 319 205 279

66.3 327 207 276 62.6 308 200 276

63.0 316 202 272 59.7 298 195 272

220

69.7 336 211 286

67.7 326 208 284

65.6 317 204 283

63.5 308 201 281

61.3 298 197 278

58.9 289 193 275

56.2 279 188 271

240

64.6 312 203 284

62.8 303 199 282

60.9 295 196 281

59.0 287 192 278

57.1 278 189 276

55.0 270 185 273

52.8 262 180 269

250

62.1 300 199 283

60.3 292 195 281

58.6 284 192 279

56.8 276 188 277

54.9 268 184 274

53.0 260 181 271

51.0 253 176 268

180 200

TQ % NP = 82 % KG/H/ENG IAS TAS

NOT THERMO LIMITED

Model : 212A

4.31

OPS DATA R

13 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

110 (Flaps 0)

110 (Flaps 15)

DRIFT DOWN VmLB MINI EN ROUTE

105 (Flaps 0)

99 (Flaps 15) 126 (Flaps 0)

VmHB 95 95 (Flaps 30) VGA GO AROUND 93* 94* (Flaps 15) * VGA must not be less than 1.1 VMCA IAS (refer to page 4.64) FINAL APPROACH

FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.2 457 252 275

94.5 461 251 277

94.5 463 250 279

89.8 447 245 275

84.8 430 239 270

80.2 413 233 267

75.7 397 228 262

100

94.5 452 250 281

94.5 455 249 283

90.8 442 245 280

86.2 426 239 276

81.4 409 233 272

76.9 393 227 268

72.7 378 222 264

120

94.2 448 248 287

90.6 434 243 284

86.7 420 238 281

82.8 406 233 278

78.5 391 228 274

74.2 376 222 270

70.2 362 217 266

140

90.1 430 241 288

86.8 415 237 286

83.5 403 233 284

79.8 388 228 280

76.1 376 223 277

72.1 362 218 273

68.1 347 212 269

160

85.6 409 235 289

83.0 398 231 287

79.9 384 227 285

76.7 372 223 282

73.2 359 218 279

69.8 347 213 276

66.0 333 208 271

80.6 386 227 289 75.1 361 219 287

78.1 375 224 287 72.8 350 216 286

75.5 363 220 285 70.5 340 212 284

72.6 351 216 283 68.1 329 209 282

69.5 340 212 280 65.5 319 205 279

66.3 327 207 276 62.6 308 200 276

63.0 316 202 272 59.7 298 195 272

220

69.7 336 211 286

67.7 326 208 284

65.6 317 204 283

63.5 308 201 281

61.3 298 197 278

58.9 289 193 275

56.2 279 188 271

240

64.6 312 203 284

62.8 303 199 282

60.9 295 196 281

59.0 287 192 278

57.1 278 189 276

55.0 270 185 273

52.8 262 180 269

250

62.1 300 199 283

60.3 292 195 281

58.6 284 192 279

56.8 276 188 277

54.9 268 184 274

53.0 260 181 271

51.0 253 176 268

180 200


NOT THERMO LIMITED

Model : 212A

4.32

OPS DATA

14 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

110 (Flaps 0)

110 (Flaps 15)


FLIGHT LEVEL


109 (Flaps 0)

103 (Flaps 15) 131 (Flaps 0)

95

95

97

97


-5

0

+5

+10

+15

+20

80

94.5 458 252 275

94.5 461 251 277

94.5 463 250 278

89.8 447 244 274

84.7 429 238 270

80.2 413 233 266

75.7 397 227 262

100

94.5 452 250 281

94.5 455 249 283

90.8 442 244 280

86.1 426 239 276

81.3 409 233 272

76.8 393 227 267

72.7 378 222 263

120

94.1 447 247 286

90.6 434 243 284

86.6 420 238 281

82.7 406 233 278

78.5 391 227 274

74.2 376 222 269

70.2 362 217 265

140

90.1 429 241 288

86.8 415 237 285

83.5 403 233 283

79.8 388 228 280

76.1 376 223 277

72.0 361 217 272

68.1 347 212 268

160

85.6 409 234 288

82.9 397 231 287

79.8 384 226 284

76.6 372 222 282

73.2 359 217 278

69.7 346 212 275

66.0 333 207 270

80.5 386 227 288 75.0 361 219 287

78.0 375 223 286 72.7 350 215 285

75.4 363 220 285 70.4 340 212 283

72.5 351 215 282 68.0 329 208 281

69.4 339 211 279 65.4 319 204 278

66.3 327 206 275 62.5 308 199 275

63.0 316 201 271 59.6 297 194 270

220

69.6 335 210 285

67.6 326 207 283

65.5 317 203 281

63.4 308 200 279

61.1 298 196 277

58.7 289 191 273

56.1 279 187 269

240

64.4 311 202 282

62.6 303 198 281

60.8 294 195 279

58.8 286 191 277

56.9 278 187 274

54.8 269 183 270

52.6 261 179 267

250

62.0 300 197 281

60.2 291 194 279

58.4 283 190 277

56.6 275 187 275

54.7 267 183 272

52.9 260 179 269

50.8 252 175 265

180 200


NOT THERMO LIMITED

Model : 212A

4.32

OPS DATA R

14 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

110 (Flaps 0)

110 (Flaps 15)


109 (Flaps 0)

103 (Flaps 15) 131 (Flaps 0)


FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.5 458 252 275

94.5 461 251 277

94.5 463 250 278

89.8 447 244 274

84.7 429 238 270

80.2 413 233 266

75.7 397 227 262

100

94.5 452 250 281

94.5 455 249 283

90.8 442 244 280

86.1 426 239 276

81.3 409 233 272

76.8 393 227 267

72.7 378 222 263

120

94.1 447 247 286

90.6 434 243 284

86.6 420 238 281

82.7 406 233 278

78.5 391 227 274

74.2 376 222 269

70.2 362 217 265

140

90.1 429 241 288

86.8 415 237 285

83.5 403 233 283

79.8 388 228 280

76.1 376 223 277

72.0 361 217 272

68.1 347 212 268

160

85.6 409 234 288

82.9 397 231 287

79.8 384 226 284

76.6 372 222 282

73.2 359 217 278

69.7 346 212 275

66.0 333 207 270

80.5 386 227 288 75.0 361 219 287

78.0 375 223 286 72.7 350 215 285

75.4 363 220 285 70.4 340 212 283

72.5 351 215 282 68.0 329 208 281

69.4 339 211 279 65.4 319 204 278

66.3 327 206 275 62.5 308 199 275

63.0 316 201 271 59.6 297 194 270

220

69.6 335 210 285

67.6 326 207 283

65.5 317 203 281

63.4 308 200 279

61.1 298 196 277

58.7 289 191 273

56.1 279 187 269

240

64.4 311 202 282

62.6 303 198 281

60.8 294 195 279

58.8 286 191 277

56.9 278 187 274

54.8 269 183 270

52.6 261 179 267

250

62.0 300 197 281

60.2 291 194 279

58.4 283 190 277

56.6 275 187 275

54.7 267 183 272

52.9 260 179 269

50.8 252 175 265

180 200


NOT THERMO LIMITED

Model : 212A

4.33

OPS DATA

15 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

114 (Flaps 0)

110 (Flaps 15)


FLIGHT LEVEL


114 (Flaps 0)

107 (Flaps 15) 136 (Flaps 0)

95

97

100

101


-5

0

+5

+10

+15

+20

80

94.5 458 252 275

94.5 461 251 276

94.5 463 250 278

89.7 447 244 274

84.7 429 238 270

80.1 413 232 266

75.7 397 227 261

100

94.5 453 250 281

94.5 455 249 282

90.7 441 244 279

86.1 426 238 276

81.3 409 232 271

76.8 393 227 267

72.6 378 221 263

120

94.1 447 247 286

90.6 434 243 284

86.6 419 238 281

82.7 406 233 277

78.4 391 227 273

74.1 376 221 269

70.1 362 216 265

140

90.0 429 241 287

86.8 415 236 285

83.4 402 232 283

79.7 388 227 279

76.1 375 222 276

72.0 361 217 271

68.0 347 211 267

160

85.5 409 234 288

82.9 397 230 286

79.8 383 226 284

76.6 372 222 281

73.1 358 217 278

69.7 346 212 274

65.9 333 206 269

80.5 386 226 287 74.9 360 218 286

77.9 374 223 286 72.6 349 214 284

75.3 363 219 284 70.3 339 211 282

72.4 351 215 281 67.9 329 207 280

69.4 339 210 278 65.2 319 203 277

66.2 327 205 274 62.4 308 198 273

62.9 316 200 269 59.5 297 193 269

220

69.5 335 209 283

67.5 325 206 282

65.4 316 202 280

63.3 307 199 278

61.0 297 194 275

58.6 289 190 271

56.0 278 185 267

240

64.3 310 201 281

62.4 302 197 279

60.6 294 193 277

58.6 285 190 274

56.7 277 186 271

54.6 269 181 268

52.5 261 177 264

250

61.8 299 196 279

60.0 290 192 277

58.2 282 189 275

56.4 275 185 272

54.5 267 181 269

52.7 259 177 266

50.6 252 173 262

180 200


NOT THERMO LIMITED

Model : 212A

4.33

OPS DATA R

15 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

114 (Flaps 0)

110 (Flaps 15)


114 (Flaps 0)

107 (Flaps 15) 136 (Flaps 0)


FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.5 458 252 275

94.5 461 251 276

94.5 463 250 278

89.7 447 244 274

84.7 429 238 270

80.1 413 232 266

75.7 397 227 261

100

94.5 453 250 281

94.5 455 249 282

90.7 441 244 279

86.1 426 238 276

81.3 409 232 271

76.8 393 227 267

72.6 378 221 263

120

94.1 447 247 286

90.6 434 243 284

86.6 419 238 281

82.7 406 233 277

78.4 391 227 273

74.1 376 221 269

70.1 362 216 265

140

90.0 429 241 287

86.8 415 236 285

83.4 402 232 283

79.7 388 227 279

76.1 375 222 276

72.0 361 217 271

68.0 347 211 267

160

85.5 409 234 288

82.9 397 230 286

79.8 383 226 284

76.6 372 222 281

73.1 358 217 278

69.7 346 212 274

65.9 333 206 269

80.5 386 226 287 74.9 360 218 286

77.9 374 223 286 72.6 349 214 284

75.3 363 219 284 70.3 339 211 282

72.4 351 215 281 67.9 329 207 280

69.4 339 210 278 65.2 319 203 277

66.2 327 205 274 62.4 308 198 273

62.9 316 200 269 59.5 297 193 269

220

69.5 335 209 283

67.5 325 206 282

65.4 316 202 280

63.3 307 199 278

61.0 297 194 275

58.6 289 190 271

56.0 278 185 267

240

64.3 310 201 281

62.4 302 197 279

60.6 294 193 277

58.6 285 190 274

56.7 277 186 271

54.6 269 181 268

52.5 261 177 264

250

61.8 299 196 279

60.0 290 192 277

58.2 282 189 275

56.4 275 185 272

54.5 267 181 269

52.7 259 177 266

50.6 252 173 262

180 200


NOT THERMO LIMITED

Model : 212A

4.34

OPS DATA

16 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

118 (Flaps 0)

110 (Flaps 15)


FLIGHT LEVEL


118 (Flaps 0)

111 (Flaps 15) 140 (Flaps 0)

95

100

103

104


-5

0

+5

+10

+15

+20

80

94.5 458 251 275

94.5 461 250 276

94.5 463 249 278

89.7 447 244 274

84.7 429 238 269

80.1 413 232 265

75.6 397 226 261

100

94.5 453 249 280

94.5 455 248 282

90.7 441 243 279

86.1 426 238 275

81.3 409 232 271

76.8 393 226 266

72.6 378 220 262

120

94.1 447 247 285

90.5 434 242 283

86.6 419 237 280

82.6 406 232 277

78.4 391 226 272

74.1 376 221 268

70.1 362 215 264

140

90.0 429 240 287

86.7 414 236 284

83.4 402 232 282

79.6 388 227 279

76.0 375 221 275

72.0 361 216 270

68.0 347 210 266

160

85.5 409 233 287

82.8 397 230 285

79.7 383 225 283

76.5 371 221 280

73.1 358 216 276

69.6 346 211 272

65.9 333 205 268

80.3 385 226 286 74.8 360 217 285

77.8 374 222 285 72.5 349 213 283

75.2 363 218 283 70.2 339 210 281

72.3 350 214 280 67.7 328 206 278

69.3 339 209 276 65.1 318 201 275

66.1 327 204 272 62.3 307 196 271

62.8 315 198 268 59.4 297 191 266

220

69.3 334 208 282

67.3 325 205 280

65.2 316 201 278

63.1 306 197 276

60.8 297 193 273

58.4 288 188 269

55.9 278 183 264

240

64.1 310 199 279

62.2 301 196 277

60.4 293 192 274

58.4 285 188 272

56.5 276 184 269

54.5 268 180 265

52.3 260 175 261

250

61.6 298 195 277

59.7 290 191 275

58.0 282 187 272

56.2 274 183 270

54.3 266 179 267

52.5 259 175 263

50.4 251 170 259

180 200


NOT THERMO LIMITED

Model : 212A

4.34

OPS DATA R

16 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

118 (Flaps 0)

110 (Flaps 15)


118 (Flaps 0)

111 (Flaps 15) 140 (Flaps 0)


FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.5 458 251 275

94.5 461 250 276

94.5 463 249 278

89.7 447 244 274

84.7 429 238 269

80.1 413 232 265

75.6 397 226 261

100

94.5 453 249 280

94.5 455 248 282

90.7 441 243 279

86.1 426 238 275

81.3 409 232 271

76.8 393 226 266

72.6 378 220 262

120

94.1 447 247 285

90.5 434 242 283

86.6 419 237 280

82.6 406 232 277

78.4 391 226 272

74.1 376 221 268

70.1 362 215 264

140

90.0 429 240 287

86.7 414 236 284

83.4 402 232 282

79.6 388 227 279

76.0 375 221 275

72.0 361 216 270

68.0 347 210 266

160

85.5 409 233 287

82.8 397 230 285

79.7 383 225 283

76.5 371 221 280

73.1 358 216 276

69.6 346 211 272

65.9 333 205 268

80.3 385 226 286 74.8 360 217 285

77.8 374 222 285 72.5 349 213 283

75.2 363 218 283 70.2 339 210 281

72.3 350 214 280 67.7 328 206 278

69.3 339 209 276 65.1 318 201 275

66.1 327 204 272 62.3 307 196 271

62.8 315 198 268 59.4 297 191 266

220

69.3 334 208 282

67.3 325 205 280

65.2 316 201 278

63.1 306 197 276

60.8 297 193 273

58.4 288 188 269

55.9 278 183 264

240

64.1 310 199 279

62.2 301 196 277

60.4 293 192 274

58.4 285 188 272

56.5 276 184 269

54.5 268 180 265

52.3 260 175 261

250

61.6 298 195 277

59.7 290 191 275

58.0 282 187 272

56.2 274 183 270

54.3 266 179 267

52.5 259 175 263

50.4 251 170 259

180 200


NOT THERMO LIMITED

Model : 212A

4.35

OPS DATA

17 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

121 (Flaps 0)

111 (Flaps 15)


FLIGHT LEVEL


121 (Flaps 0)

115 (Flaps 15) 145 (Flaps 0)

96

104

107

108


-5

0

+5

+10

+15

+20

80

94.5 458 251 274

94.5 461 250 276

94.5 463 249 277

89.7 447 243 273

84.6 429 237 269

80.0 413 231 264

75.6 397 225 260

100

94.5 453 249 280

94.5 455 248 281

90.7 441 243 279

86.0 425 237 274

81.2 409 231 270

76.7 393 225 265

72.5 378 220 261

120

94.0 447 246 285

90.5 434 242 283

86.5 419 237 279

82.6 405 231 276

78.3 391 226 272

74.0 376 220 267

70.0 362 214 262

140

89.9 429 240 286

86.6 414 235 284

83.3 402 231 281

79.6 388 226 278

75.9 375 221 274

71.9 361 215 269

67.9 347 209 264

160

85.4 408 233 286

82.7 397 229 285

79.6 383 224 282

76.4 371 220 279

73.0 358 215 275

69.5 346 210 271

65.8 333 204 266

80.2 385 225 285 74.6 359 216 283

77.7 374 221 283 72.3 348 212 281

75.1 362 217 281 70.0 338 208 279

72.2 350 213 278 67.6 328 204 276

69.1 338 208 275 64.9 318 200 273

65.9 326 203 271 62.1 307 195 269

62.7 315 197 266 59.2 296 190 264

220

69.1 333 207 280

67.1 324 203 278

65.0 315 199 276

62.9 306 195 273

60.7 296 191 270

58.3 288 187 266

55.7 278 181 262

240

63.8 309 197 277

62.0 300 194 274

60.2 292 190 272

58.2 284 186 269

56.3 275 182 266

54.2 268 177 262

52.1 260 172 257

250

61.3 297 193 275

59.5 289 189 272

57.7 281 185 269

55.9 273 181 266

54.1 265 177 263

52.2 258 172 259

50.1 250 167 254

180 200


NOT THERMO LIMITED

Model : 212A

4.35

OPS DATA R

17 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

104 110

FINAL TAKE OFF

VFTO

121 (Flaps 0)

111 (Flaps 15)


121 (Flaps 0)

115 (Flaps 15) 145 (Flaps 0)


FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.5 458 251 274

94.5 461 250 276

94.5 463 249 277

89.7 447 243 273

84.6 429 237 269

80.0 413 231 264

75.6 397 225 260

100

94.5 453 249 280

94.5 455 248 281

90.7 441 243 279

86.0 425 237 274

81.2 409 231 270

76.7 393 225 265

72.5 378 220 261

120

94.0 447 246 285

90.5 434 242 283

86.5 419 237 279

82.6 405 231 276

78.3 391 226 272

74.0 376 220 267

70.0 362 214 262

140

89.9 429 240 286

86.6 414 235 284

83.3 402 231 281

79.6 388 226 278

75.9 375 221 274

71.9 361 215 269

67.9 347 209 264

160

85.4 408 233 286

82.7 397 229 285

79.6 383 224 282

76.4 371 220 279

73.0 358 215 275

69.5 346 210 271

65.8 333 204 266

80.2 385 225 285 74.6 359 216 283

77.7 374 221 283 72.3 348 212 281

75.1 362 217 281 70.0 338 208 279

72.2 350 213 278 67.6 328 204 276

69.1 338 208 275 64.9 318 200 273

65.9 326 203 271 62.1 307 195 269

62.7 315 197 266 59.2 296 190 264

220

69.1 333 207 280

67.1 324 203 278

65.0 315 199 276

62.9 306 195 273

60.7 296 191 270

58.3 288 187 266

55.7 278 181 262

240

63.8 309 197 277

62.0 300 194 274

60.2 292 190 272

58.2 284 186 269

56.3 275 182 266

54.2 268 177 262

52.1 260 172 257

250

61.3 297 193 275

59.5 289 189 272

57.7 281 185 269

55.9 273 181 266

54.1 265 177 263

52.2 258 172 259

50.1 250 167 254

180 200


NOT THERMO LIMITED

Model : 212A

4.36

OPS DATA

18 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

107 111

FINAL TAKE OFF

VFTO

125 (Flaps 0)

115 (Flaps 15)


FLIGHT LEVEL


125 (Flaps 0)

118 (Flaps 15) 149 (Flaps 0)

99

107

110

111


-5

0

+5

+10

+15

+20

80

94.5 458 251 274

94.5 461 250 275

94.5 463 249 277

89.6 447 243 273

84.6 429 236 268

80.0 413 231 264

75.5 397 225 259

100

94.5 453 249 279

94.5 455 248 281

90.6 441 243 278

86.0 425 237 274

81.2 409 230 269

76.6 393 224 264

72.5 378 219 260

120

93.9 447 246 284

90.4 434 241 282

86.5 419 236 279

82.5 405 231 275

78.3 391 225 271

74.0 376 219 266

70.0 361 213 261

140

89.8 429 239 285

86.5 414 235 283

83.2 402 230 280

79.5 388 225 277

75.8 375 220 273

71.8 361 214 268

67.8 347 208 263

160

85.3 408 232 285

82.6 397 228 284

79.5 383 224 281

76.3 371 219 278

72.9 358 214 274

69.4 346 208 269

65.7 333 203 264

80.1 384 224 284 74.4 358 215 282

77.5 373 220 282 72.1 348 211 279

74.9 362 216 280 69.8 338 207 277

72.0 349 211 277 67.4 327 203 274

69.0 338 206 273 64.8 317 198 271

65.8 326 201 269 62.0 307 193 267

62.6 315 196 264 59.1 296 188 262

220

68.9 333 205 278

66.9 323 202 276

64.8 314 198 274

62.7 305 194 271

60.5 296 189 268

58.1 287 184 263

55.5 277 179 258

240

63.6 308 196 274

61.7 299 192 272

59.9 291 188 269

57.9 283 184 266

56.0 275 179 262

54.0 267 174 258

51.8 259 169 252

250

61.1 296 191 272

59.2 288 187 269

57.4 280 183 266

55.6 272 178 263

53.8 264 174 259

51.9 257 169 254

49.8 249 163 248

180 200


NOT THERMO LIMITED

Model : 212A

4.36

OPS DATA R

18 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

107 111

FINAL TAKE OFF

VFTO

125 (Flaps 0)

115 (Flaps 15)


125 (Flaps 0)

118 (Flaps 15) 149 (Flaps 0)


FLIGHT LEVEL


-5

0

+5

+10

+15

+20

80

94.5 458 251 274

94.5 461 250 275

94.5 463 249 277

89.6 447 243 273

84.6 429 236 268

80.0 413 231 264

75.5 397 225 259

100

94.5 453 249 279

94.5 455 248 281

90.6 441 243 278

86.0 425 237 274

81.2 409 230 269

76.6 393 224 264

72.5 378 219 260

120

93.9 447 246 284

90.4 434 241 282

86.5 419 236 279

82.5 405 231 275

78.3 391 225 271

74.0 376 219 266

70.0 361 213 261

140

89.8 429 239 285

86.5 414 235 283

83.2 402 230 280

79.5 388 225 277

75.8 375 220 273

71.8 361 214 268

67.8 347 208 263

160

85.3 408 232 285

82.6 397 228 284

79.5 383 224 281

76.3 371 219 278

72.9 358 214 274

69.4 346 208 269

65.7 333 203 264

80.1 384 224 284 74.4 358 215 282

77.5 373 220 282 72.1 348 211 279

74.9 362 216 280 69.8 338 207 277

72.0 349 211 277 67.4 327 203 274

69.0 338 206 273 64.8 317 198 271

65.8 326 201 269 62.0 307 193 267

62.6 315 196 264 59.1 296 188 262

220

68.9 333 205 278

66.9 323 202 276

64.8 314 198 274

62.7 305 194 271

60.5 296 189 268

58.1 287 184 263

55.5 277 179 258

240

63.6 308 196 274

61.7 299 192 272

59.9 291 188 269

57.9 283 184 266

56.0 275 179 262

54.0 267 174 258

51.8 259 169 252

250

61.1 296 191 272

59.2 288 187 269

57.4 280 183 266

55.6 272 178 263

53.8 264 174 259

51.9 257 169 254

49.8 249 163 248

180 200


NOT THERMO LIMITED

Model : 212A

4.37

OPS DATA

19 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

104 110

110 114

FINAL TAKE OFF

VFTO

129 (Flaps 0)

119 (Flaps 15)


FLIGHT LEVEL


129 (Flaps 0)

121 (Flaps 15) 153 (Flaps 0)

102

109

113

114


-5

0

+5

+10

+15

+20

80

94.5 458 250 273

94.5 461 249 275

94.5 464 248 276

89.6 447 242 272

84.5 429 236 267

79.9 413 230 263

75.5 397 224 258

100

94.5 453 248 279

94.5 455 247 280

90.5 441 242 277

85.9 425 236 273

81.1 409 230 268

76.6 393 224 263

72.4 377 218 259

120

93.9 447 245 284

90.3 434 240 281

86.4 419 235 278

82.4 405 230 274

78.2 391 224 269

73.9 376 218 265

69.9 361 212 260

140

89.7 428 238 284

86.5 414 234 282

83.1 402 229 279

79.4 388 224 275

75.8 375 219 271

71.7 361 213 266

67.8 347 207 261

160

85.1 408 231 284

82.5 396 227 282

79.4 382 223 279

76.2 371 218 276

72.8 357 212 272

69.4 346 207 268

65.6 333 201 263

79.9 384 223 283 74.2 358 213 280

77.3 372 219 281 71.9 347 209 278

74.8 361 214 278 69.6 337 205 275

71.9 349 210 275 67.2 327 201 272

68.8 338 205 271 64.6 317 196 269

65.7 326 200 267 61.8 306 191 264

62.4 315 194 262 58.9 296 185 259

220

68.7 332 204 276

66.7 323 200 274

64.6 313 196 271

62.4 304 192 268

60.2 295 187 265

57.8 286 182 260

55.2 276 176 254

240

63.3 307 194 271

61.4 298 190 269

59.6 290 186 266

57.7 282 181 262

55.7 273 176 258

53.6 266 171 253

51.4 258 165 246

250

60.8 295 189 269

58.9 286 184 266

57.1 279 180 262

55.3 271 175 258

53.4 263 170 253

51.5 256 164 248

49.4 248 158 240

180 200


NOT THERMO LIMITED

Model : 212A

4.37

OPS DATA R

19 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

104 110

110 114

FINAL TAKE OFF

VFTO

129 (Flaps 0)

119 (Flaps 15)


FLIGHT LEVEL


129 (Flaps 0)

121 (Flaps 15) 153 (Flaps 0)

102

109

113

114


-5

0

+5

+10

+15

+20

80

94.5 458 250 273

94.5 461 249 275

94.5 464 248 276

89.6 447 242 272

84.5 429 236 267

79.9 413 230 263

75.5 397 224 258

100

94.5 453 248 279

94.5 455 247 280

90.5 441 242 277

85.9 425 236 273

81.1 409 230 268

76.6 393 224 263

72.4 377 218 259

120

93.9 447 245 284

90.3 434 240 281

86.4 419 235 278

82.4 405 230 274

78.2 391 224 269

73.9 376 218 265

69.9 361 212 260

140

89.7 428 238 284

86.5 414 234 282

83.1 402 229 279

79.4 388 224 275

75.8 375 219 271

71.7 361 213 266

67.8 347 207 261

160

85.1 408 231 284

82.5 396 227 282

79.4 382 223 279

76.2 371 218 276

72.8 357 212 272

69.4 346 207 268

65.6 333 201 263

79.9 384 223 283 74.2 358 213 280

77.3 372 219 281 71.9 347 209 278

74.8 361 214 278 69.6 337 205 275

71.9 349 210 275 67.2 327 201 272

68.8 338 205 271 64.6 317 196 269

65.7 326 200 267 61.8 306 191 264

62.4 315 194 262 58.9 296 185 259

220

68.7 332 204 276

66.7 323 200 274

64.6 313 196 271

62.4 304 192 268

60.2 295 187 265

57.8 286 182 260

55.2 276 176 254

240

63.3 307 194 271

61.4 298 190 269

59.6 290 186 266

57.7 282 181 262

55.7 273 176 258

53.6 266 171 253

51.4 258 165 246

250

60.8 295 189 269

58.9 286 184 266

57.1 279 180 262

55.3 271 175 258

53.4 263 170 253

51.5 256 164 248

49.4 248 158 240

180 200


NOT THERMO LIMITED

Model : 212A

4.38

OPS DATA

20 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

105 110

114 118

FINAL TAKE OFF

VFTO

132 (Flaps 0)

122 (Flaps 15)


FLIGHT LEVEL


132 (Flaps 0)

125 (Flaps 15) 157 (Flaps 0)

105

114

117

118


-5

0

+5

+10

+15

+20

80

94.5 459 250 273

94.5 461 249 274

94.5 464 248 276

89.5 447 241 271

84.4 429 235 266

79.9 412 229 262

75.4 396 223 257

100

94.5 453 247 278

94.5 455 246 280

90.4 441 241 276

85.8 425 235 272

81.0 409 229 267

76.5 392 222 262

72.3 377 216 257

120

93.8 446 244 283

90.2 433 240 280

86.3 419 234 277

82.4 405 229 273

78.1 390 223 268

73.9 376 217 263

69.8 361 211 258

140

89.6 428 237 283

86.3 413 233 281

83.0 401 228 278

79.3 387 223 274

75.7 374 217 270

71.7 361 211 265

67.7 347 205 260

160

85.0 407 230 283

82.3 396 226 281

79.2 382 221 278

76.1 370 216 275

72.6 357 211 270

69.3 345 206 266

65.5 332 199 261

79.7 383 221 281 74.0 357 212 278

77.1 372 217 279 71.7 346 208 276

74.6 361 213 276 69.4 336 204 273

71.7 348 208 273 67.0 326 199 270

68.7 337 203 269 64.4 316 194 266

65.5 325 198 264 61.6 305 189 261

62.3 314 192 259 58.7 295 183 255

220

68.4 331 202 274

66.4 322 198 271

64.3 313 194 268

62.2 303 189 265

60.0 294 185 261

57.5 285 179 256

54.9 276 172 249

240

63.0 306 191 268

61.1 297 187 265

59.3 289 183 262

57.3 281 178 257

55.3 272 172 252

53.2 265 166 246

50.9 256 159 238

250

60.4 294 186 265

58.5 285 181 261

56.7 277 176 257

54.8 269 171 252

52.9 261 165 246

50.9 254 158 238

48.7 246 149 227

180 200


NOT THERMO LIMITED

Model : 212A

4.38

OPS DATA R

20 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

105 110

114 118

FINAL TAKE OFF

VFTO

132 (Flaps 0)

122 (Flaps 15)


FLIGHT LEVEL


132 (Flaps 0)

125 (Flaps 15) 157 (Flaps 0)

105

114

117

118


-5

0

+5

+10

+15

+20

80

94.5 459 250 273

94.5 461 249 274

94.5 464 248 276

89.5 447 241 271

84.4 429 235 266

79.9 412 229 262

75.4 396 223 257

100

94.5 453 247 278

94.5 455 246 280

90.4 441 241 276

85.8 425 235 272

81.0 409 229 267

76.5 392 222 262

72.3 377 216 257

120

93.8 446 244 283

90.2 433 240 280

86.3 419 234 277

82.4 405 229 273

78.1 390 223 268

73.9 376 217 263

69.8 361 211 258

140

89.6 428 237 283

86.3 413 233 281

83.0 401 228 278

79.3 387 223 274

75.7 374 217 270

71.7 361 211 265

67.7 347 205 260

160

85.0 407 230 283

82.3 396 226 281

79.2 382 221 278

76.1 370 216 275

72.6 357 211 270

69.3 345 206 266

65.5 332 199 261

79.7 383 221 281 74.0 357 212 278

77.1 372 217 279 71.7 346 208 276

74.6 361 213 276 69.4 336 204 273

71.7 348 208 273 67.0 326 199 270

68.7 337 203 269 64.4 316 194 266

65.5 325 198 264 61.6 305 189 261

62.3 314 192 259 58.7 295 183 255

220

68.4 331 202 274

66.4 322 198 271

64.3 313 194 268

62.2 303 189 265

60.0 294 185 261

57.5 285 179 256

54.9 276 172 249

240

63.0 306 191 268

61.1 297 187 265

59.3 289 183 262

57.3 281 178 257

55.3 272 172 252

53.2 265 166 246

50.9 256 159 238

250

60.4 294 186 265

58.5 285 181 261

56.7 277 176 257

54.8 269 171 252

52.9 261 165 246

50.9 254 158 238

48.7 246 149 227

180 200


NOT THERMO LIMITED

Model : 212A

4.39

OPS DATA

21 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

108 111

117 121

FINAL TAKE OFF

VFTO

136 (Flaps 0)

125 (Flaps 15)


FLIGHT LEVEL


136 (Flaps 0)

128 (Flaps 15) 161 (Flaps 0)

108

117

120

121


-5

0

+5

+10

+15

+20

80

94.5 459 249 272

94.5 461 248 273

94.5 464 247 275

89.4 446 241 270

84.4 429 234 265

79.8 412 228 260

75.3 396 222 255

100

94.5 453 247 277

94.5 456 246 279

90.3 440 240 275

85.7 425 234 271

80.9 408 228 266

76.4 392 221 261

72.2 377 215 256

120

93.7 446 243 282

90.1 433 239 279

86.2 418 233 276

82.3 405 228 271

78.1 390 222 267

73.8 376 215 262

69.8 361 209 257

140

89.5 428 237 282

86.2 413 232 280

82.9 401 227 277

79.2 387 222 272

75.5 374 216 268

71.6 361 210 263

67.6 347 204 258

160

84.8 407 229 282

82.2 395 225 279

79.1 381 220 276

76.0 370 215 273

72.5 357 210 269

69.2 345 204 264

65.4 332 198 258

79.5 382 220 279 73.8 356 210 276

76.9 371 216 277 71.5 346 206 273

74.4 360 212 274 69.1 336 202 270

71.5 348 207 271 66.8 325 197 267

68.5 337 202 267 64.1 315 192 263

65.3 325 196 262 61.4 305 186 257

62.1 314 190 256 58.4 294 180 251

220

68.1 330 200 271

66.1 320 196 268

64.0 312 191 265

61.8 302 187 261

59.6 293 181 256

57.2 284 175 250

54.6 275 167 242

240

62.6 304 189 265

60.7 296 184 261

58.8 288 179 257

56.8 279 173 251

54.8 270 167 245

52.6 263 159 236

50.1 254 148 222

250

60.0 292 182 260

58.0 283 177 256

56.1 275 172 250

54.2 267 165 244

52.1 258 157 234

49.8 251 145 219

180 200


NOT THERMO LIMITED

Model : 212A

4.39

OPS DATA R

21 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

108 111

117 121

FINAL TAKE OFF

VFTO

136 (Flaps 0)

125 (Flaps 15)


FLIGHT LEVEL


136 (Flaps 0)

128 (Flaps 15) 161 (Flaps 0)

108

117

120

121


-5

0

+5

+10

+15

+20

80

94.5 459 249 272

94.5 461 248 273

94.5 464 247 275

89.4 446 241 270

84.4 429 234 265

79.8 412 228 260

75.3 396 222 255

100

94.5 453 247 277

94.5 456 246 279

90.3 440 240 275

85.7 425 234 271

80.9 408 228 266

76.4 392 221 261

72.2 377 215 256

120

93.7 446 243 282

90.1 433 239 279

86.2 418 233 276

82.3 405 228 271

78.1 390 222 267

73.8 376 215 262

69.8 361 209 257

140

89.5 428 237 282

86.2 413 232 280

82.9 401 227 277

79.2 387 222 272

75.5 374 216 268

71.6 361 210 263

67.6 347 204 258

160

84.8 407 229 282

82.2 395 225 279

79.1 381 220 276

76.0 370 215 273

72.5 357 210 269

69.2 345 204 264

65.4 332 198 258

79.5 382 220 279 73.8 356 210 276

76.9 371 216 277 71.5 346 206 273

74.4 360 212 274 69.1 336 202 270

71.5 348 207 271 66.8 325 197 267

68.5 337 202 267 64.1 315 192 263

65.3 325 196 262 61.4 305 186 257

62.1 314 190 256 58.4 294 180 251

220

68.1 330 200 271

66.1 320 196 268

64.0 312 191 265

61.8 302 187 261

59.6 293 181 256

57.2 284 175 250

54.6 275 167 242

240

62.6 304 189 265

60.7 296 184 261

58.8 288 179 257

56.8 279 173 251

54.8 270 167 245

52.6 263 159 236

50.1 254 148 222

250

60.0 292 182 260

58.0 283 177 256

56.1 275 172 250

54.2 267 165 244

52.1 258 157 234

49.8 251 145 219

180 200


NOT THERMO LIMITED

Model : 212A

4.40

OPS DATA

21.5 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

109 113

119 122

FINAL TAKE OFF

VFTO

138 (Flaps 0)

126 (Flaps 15)


FLIGHT LEVEL


138 (Flaps 0)

129 (Flaps 15) 163 (Flaps 0)

109

119

121

122


-5

0

+5

+10

+15

+20

80

94.5 459 249 272

94.5 461 248 273

94.5 464 247 274

89.4 446 240 270

84.3 429 234 265

79.8 412 227 260

75.3 396 221 255

100

94.5 453 246 277

94.5 456 245 279

90.3 440 240 275

85.7 425 234 270

80.9 408 227 265

76.4 392 221 260

72.2 377 214 255

120

93.6 446 243 281

90.1 433 238 279

86.1 418 233 275

82.2 405 227 271

78.0 390 221 266

73.7 375 215 261

69.7 361 209 256

140

89.4 427 236 282

86.2 413 231 279

82.8 401 226 276

79.1 387 221 272

75.5 374 215 267

71.5 361 209 262

67.6 346 203 257

160

84.8 406 228 281

82.1 395 224 279

79.0 381 219 275

75.9 370 214 272

72.5 357 209 268

69.1 345 203 263

65.3 332 197 257

79.4 382 219 278 73.6 355 209 275

76.8 371 215 276 71.3 345 205 272

74.3 360 211 273 69.0 335 201 269

71.4 348 206 270 66.7 325 196 266

68.4 337 201 266 64.0 315 191 261

65.2 324 195 260 61.2 304 185 255

62.0 314 188 254 58.3 294 178 248

220

68.0 329 199 269

65.9 320 195 267

63.8 311 190 263

61.7 302 185 259

59.4 293 179 254

56.9 284 172 247

54.3 274 164 237

240

62.4 303 187 262

60.5 295 182 258

58.6 287 177 254

56.5 278 171 248

54.4 269 163 239

52.2 262 154 228

250

59.8 291 181 258

57.7 282 175 252

55.8 274 169 246

53.8 266 161 237

51.5 256 150 224

180 200


NOT THERMO LIMITED

Model : 212A

4.40

OPS DATA R

21.5 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

109 113

119 122

FINAL TAKE OFF

VFTO

138 (Flaps 0)

126 (Flaps 15)


FLIGHT LEVEL


138 (Flaps 0)

129 (Flaps 15) 163 (Flaps 0)

109

119

121

122


-5

0

+5

+10

+15

+20

80

94.5 459 249 272

94.5 461 248 273

94.5 464 247 274

89.4 446 240 270

84.3 429 234 265

79.8 412 227 260

75.3 396 221 255

100

94.5 453 246 277

94.5 456 245 279

90.3 440 240 275

85.7 425 234 270

80.9 408 227 265

76.4 392 221 260

72.2 377 214 255

120

93.6 446 243 281

90.1 433 238 279

86.1 418 233 275

82.2 405 227 271

78.0 390 221 266

73.7 375 215 261

69.7 361 209 256

140

89.4 427 236 282

86.2 413 231 279

82.8 401 226 276

79.1 387 221 272

75.5 374 215 267

71.5 361 209 262

67.6 346 203 257

160

84.8 406 228 281

82.1 395 224 279

79.0 381 219 275

75.9 370 214 272

72.5 357 209 268

69.1 345 203 263

65.3 332 197 257

79.4 382 219 278 73.6 355 209 275

76.8 371 215 276 71.3 345 205 272

74.3 360 211 273 69.0 335 201 269

71.4 348 206 270 66.7 325 196 266

68.4 337 201 266 64.0 315 191 261

65.2 324 195 260 61.2 304 185 255

62.0 314 188 254 58.3 294 178 248

220

68.0 329 199 269

65.9 320 195 267

63.8 311 190 263

61.7 302 185 259

59.4 293 179 254

56.9 284 172 247

54.3 274 164 237

240

62.4 303 187 262

60.5 295 182 258

58.6 287 177 254

56.5 278 171 248

54.4 269 163 239

52.2 262 154 228

250

59.8 291 181 258

57.7 282 175 252

55.8 274 169 246

53.8 266 161 237

51.5 256 150 224

180 200


NOT THERMO LIMITED

Model : 212A

4.41

OPS DATA

22 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

111 114

120 123

FINAL TAKE OFF

VFTO

139 (Flaps 0)

128 (Flaps 15)


FLIGHT LEVEL


139 (Flaps 0)

131 (Flaps 15) 165 (Flaps 0)

111

120

123

124


-5

0

+5

+10

+15

+20

80

94.5 459 248 271

94.5 461 247 273

94.5 464 246 274

89.3 446 240 269

84.3 429 233 264

79.7 412 227 259

75.3 396 220 254

100

94.5 453 246 277

94.5 456 245 278

90.2 440 239 274

85.6 425 233 269

80.9 408 226 264

76.3 392 220 259

72.2 377 214 254

120

93.6 446 243 281

90.0 433 238 278

86.1 418 232 274

82.2 404 226 270

78.0 390 220 265

73.7 375 214 260

69.7 361 208 255

140

89.3 427 235 281

86.1 413 231 278

82.8 401 226 275

79.1 387 220 271

75.4 374 215 267

71.5 360 208 261

67.5 346 202 255

160

84.7 406 228 280

82.0 395 223 278

78.9 381 219 275

75.8 370 214 271

72.4 357 208 267

69.0 345 202 262

65.2 332 195 255

79.3 381 219 278 73.5 355 208 273

76.7 370 214 275 71.2 345 204 271

74.2 359 210 272 68.9 335 200 268

71.3 347 205 268 66.5 324 195 264

68.3 336 200 264 63.9 314 189 259

65.1 324 193 259 61.1 304 183 253

61.9 313 187 252 58.1 293 175 245

220

67.8 328 197 268

65.8 319 193 265

63.6 310 188 261

61.4 301 183 256

59.2 292 177 251

56.7 283 170 243

54.0 273 160 231

240

62.2 303 185 260

60.2 294 180 255

58.3 286 174 250

56.2 277 167 243

53.9 268 158 232

51.1 258 141 209

250

59.5 290 178 254

57.4 281 172 248

55.3 272 164 240

53.2 264 155 228

180 200


NOT THERMO LIMITED

Model : 212A

4.41

OPS DATA R

22 t

72

JUL 15

500

Speeds

Normal

Icing


V1 = VR V2

111 114

120 123

FINAL TAKE OFF

VFTO

139 (Flaps 0)

128 (Flaps 15)


FLIGHT LEVEL


139 (Flaps 0)

131 (Flaps 15) 165 (Flaps 0)

111

120

123

124


-5

0

+5

+10

+15

+20

80

94.5 459 248 271

94.5 461 247 273

94.5 464 246 274

89.3 446 240 269

84.3 429 233 264

79.7 412 227 259

75.3 396 220 254

100

94.5 453 246 277

94.5 456 245 278

90.2 440 239 274

85.6 425 233 269

80.9 408 226 264

76.3 392 220 259

72.2 377 214 254

120

93.6 446 243 281

90.0 433 238 278

86.1 418 232 274

82.2 404 226 270

78.0 390 220 265

73.7 375 214 260

69.7 361 208 255

140

89.3 427 235 281

86.1 413 231 278

82.8 401 226 275

79.1 387 220 271

75.4 374 215 267

71.5 360 208 261

67.5 346 202 255

160

84.7 406 228 280

82.0 395 223 278

78.9 381 219 275

75.8 370 214 271

72.4 357 208 267

69.0 345 202 262

65.2 332 195 255

79.3 381 219 278 73.5 355 208 273

76.7 370 214 275 71.2 345 204 271

74.2 359 210 272 68.9 335 200 268

71.3 347 205 268 66.5 324 195 264

68.3 336 200 264 63.9 314 189 259

65.1 324 193 259 61.1 304 183 253

61.9 313 187 252 58.1 293 175 245

220

67.8 328 197 268

65.8 319 193 265

63.6 310 188 261

61.4 301 183 256

59.2 292 177 251

56.7 283 170 243

54.0 273 160 231

240

62.2 303 185 260

60.2 294 180 255

58.3 286 174 250

56.2 277 167 243

53.9 268 158 232

51.1 258 141 209

250

59.5 290 178 254

57.4 281 172 248

55.3 272 164 240

53.2 264 155 228

180 200


NOT THERMO LIMITED

Model : 212A

4.42

OPS DATA

22.5 t

72

Speeds

DEC 14 500

Normal

Icing

Never exceed certified weight limitations NON LIMITING RWY TAKE-OFF (Flaps 15)

V1 = VR V2

112 115

122 125

FINAL TAKE OFF

VFTO

140 (Flaps 0)

130 (Flaps 15)


FLIGHT LEVEL


140 (Flaps 0)

133 (Flaps 15) 167 (Flaps 0)

113

122

124

125


-5

0

+5

+10

+15

+20

94.5 459 248 271 94.5 453 246 276

94.5 461 247 272 94.5 456 245 278

94.5 464 246 274 90.2 440 239 274

89.3 446 239 269 85.6 424 232 269

84.2 428 233 263 80.8 408 226 264

79.7 412 226 258 76.3 392 219 258

75.2 396 220 253 72.1 377 213 253

120

93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140

89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160

84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180

79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200

73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

67.6 328 196 266 61.9 302 183 257

65.6 318 192 263 59.9 293 178 252

63.4 310 186 258 57.9 284 171 246

61.2 300 181 253 55.7 275 162 236

59.0 291 174 247 53.1 265 149 219

56.4 282 166 237

53.6 272 154 223

59.2 289 176 251

57.0 279 168 243

54.7 270 158 232

80 100

220 240 250


NOT THERMO LIMITED

Model : 212A

4.42

OPS DATA R

22.5 t

72

Speeds

JUL 15

Normal

500

Icing


V1 = VR V2

112 115

122 125

FINAL TAKE OFF

VFTO

140 (Flaps 0)

130 (Flaps 15)


FLIGHT LEVEL


140 (Flaps 0)

133 (Flaps 15) 167 (Flaps 0)

113

122

124

125


-5

0

+5

+10

+15

+20

94.5 459 248 271 94.5 453 246 276

94.5 461 247 272 94.5 456 245 278

94.5 464 246 274 90.2 440 239 274

89.3 446 239 269 85.6 424 232 269

84.2 428 233 263 80.8 408 226 264

79.7 412 226 258 76.3 392 219 258

75.2 396 220 253 72.1 377 213 253

120

93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140

89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160

84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180

79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200

73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

67.6 328 196 266 61.9 302 183 257

65.6 318 192 263 59.9 293 178 252

63.4 310 186 258 57.9 284 171 246

61.2 300 181 253 55.7 275 162 236

59.0 291 174 247 53.1 265 149 219

56.4 282 166 237

53.6 272 154 223

59.2 289 176 251

57.0 279 168 243

54.7 270 158 232

80 100

220 240 250


NOT THERMO LIMITED

Model : 212A

4.43

OPS DATA

23 t

72

DEC 14 500

Speeds

Normal

Icing


V1 = VR V2

114 117

123 126

FINAL TAKE OFF

VFTO

141 (Flaps 0)

132 (Flaps 15)


FLIGHT LEVEL


141 (Flaps 0)

135 (Flaps 15) 169 (Flaps 0)

115

124

126

127


-5

0

+5

+10

+15

+20

94.5 459 248 271 94.5 453 246 276

94.5 461 247 272 94.5 456 245 278

94.5 464 246 274 90.2 440 239 274

89.3 446 239 269 85.6 424 232 269

84.2 428 233 263 80.8 408 226 264

79.7 412 226 258 76.3 392 219 258

75.2 396 220 253 72.1 377 213 253

120

93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140

89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160

84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180

79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200

73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

67.6 328 196 266 61.9 302 183 257

65.6 318 192 263 59.9 293 178 252

63.4 310 186 258 57.9 284 171 246

61.2 300 181 253 55.7 275 162 236

59.0 291 174 247 53.1 265 149 219

56.4 282 166 237

53.6 272 154 223

59.2 289 176 251

57.0 279 168 243

54.7 270 158 232

80 100

220 240 250


NOT THERMO LIMITED

Model : 212A

4.43

OPS DATA R

23 t

72

JUL 15

Speeds

Normal

500

Icing


V1 = VR V2

114 117

123 126

FINAL TAKE OFF

VFTO

141 (Flaps 0)

132 (Flaps 15)


FLIGHT LEVEL


141 (Flaps 0)

135 (Flaps 15) 169 (Flaps 0)

115

124

126

127


-5

0

+5

+10

+15

+20

94.5 459 248 271 94.5 453 246 276

94.5 461 247 272 94.5 456 245 278

94.5 464 246 274 90.2 440 239 274

89.3 446 239 269 85.6 424 232 269

84.2 428 233 263 80.8 408 226 264

79.7 412 226 258 76.3 392 219 258

75.2 396 220 253 72.1 377 213 253

120

93.5 446 242 280

89.9 433 237 277

86.0 418 232 273

82.1 404 226 269

77.9 390 220 265

73.7 375 213 259

69.6 361 207 254

140

89.2 427 235 280

86.0 412 230 277

82.7 401 225 274

79.0 387 219 270

75.4 374 214 266

71.4 360 208 260

67.5 346 201 254

160

84.6 406 227 279

81.9 394 223 277

78.8 381 218 274

75.7 369 213 270

72.3 356 207 265

68.9 345 201 260

65.1 331 194 254

180

79.2 381 218 277

76.6 370 213 274

74.1 359 209 271

71.2 347 204 267

68.2 336 198 263

65.0 324 192 257

61.8 313 185 250

200

73.4 354 207 272

71.0 344 203 269

68.7 334 199 266

66.4 324 194 262

63.7 314 188 257

60.9 304 181 250

57.9 293 173 241

67.6 328 196 266 61.9 302 183 257

65.6 318 192 263 59.9 293 178 252

63.4 310 186 258 57.9 284 171 246

61.2 300 181 253 55.7 275 162 236

59.0 291 174 247 53.1 265 149 219

56.4 282 166 237

53.6 272 154 223

59.2 289 176 251

57.0 279 168 243

54.7 270 158 232

80 100

220 240 250


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


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


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


PW127M – BOOST ON

SINGLE ENGINE GROSS CEILING (FT) ICING CONDITIONS (FLAPS 15) WEIGHT x 1000 kg

ISA - 10

ISA

ISA + 10

ISA + 15

ISA + 20

WEIGHT x 1000 lb

13.0

25000 25000 25000 25000 25000 25000 25000 25000 25000 25000

29

14.0

25000 25000 25000 25000 25000 25000 25000 25000 25000 25000

31

15.0

25000 25000 25000 25000 24200 24300 23600 23600 22900 23000

33

16.0

25000 25000 23600 23800 22300 22600 21700 21900 21000 21200

35

17.0

23200 23600 21800 22200 20500 20900 19900 20300 19000 19400

37

18.0

21500 22000 20100 20700 18800 19300 18000 18600 17200 17700

39

19.0

19800 20500 18400 19100 17100 17800 16200 16900 15500 16200

41

20.0

18200 19000 16800 17600 15400 16300 14600 15400 15000 15100

43

21.0

16700 17600 15400 16200 13800 14800 13100 14000

-

-

45

22.0

15400 16300 14000 15000 12400 13400 12600 12700

-

-

47

22.8

14400 15100 13000 13700 11400 12100

-

-

14500

-

13100

-

11500

-

12500

-

-

49

-

-

-

-

50

Note : When bolt-underlined figures, icing conditions do not exist.

Eng : PW127M

Model : 212A

4.63

OPS DATA 72

SEP 10

500

PW127F / PW127M

REDUCED FLAPS LANDING CONFIGURATION – VAPP (kt) NOTE: For a go around flaps 15 configuration increase speed up to VmLB0 before selecting flaps 0

FLAPS 0 VmHB0 + 5 kt

FLAPS 15 VmHB15

KG WEIGHT (x 1000kg)

Normal

Icing

Normal

Icing

13 14 15 16 17 18 19 20 21 22 22.5 * 23 *

115 119 123 127 131 135 139 142 146 149 151 152

136 141 146 151 155 160 164 168 172 176 178 180

97 97 100 103 107 110 113 116 120 123 124 126

102 106 110 114 118 122 125 129 132 135 137 139

FLAPS 0 VmHB0 + 5 kt

FLAPS 15 VmHB15

Lb WEIGHT (x 1000Lb)

Normal

Icing

Normal

Icing

29 31 33 35 37 39 41 43 45 47 49 49.6 * 50.7 *

115 119 123 127 130 134 137 141 144 147 150 151 152

137 142 146 150 154 158 162 166 170 173 177 178 180

97 97 100 103 106 109 112 115 118 121 123 124 126

103 107 110 114 117 121 124 127 130 133 136 137 139

* Never exceed the certified Maximum Landing Weight : PW127E Eng :Eng PW127F-PW127M

4.64

OPS DATA 72

OCT 08 500

PW127F / PW127M 1.1 VMCA IAS * OAT °C -30

-20

-10

0

+ 10

+ 20

+30

+ 40

+ 50

0

111

110

109

108

108

107

106

104

100

2000

109

108

108

107

106

105

104

101

97

4000

108

107

106

105

105

104

100

97

94

6000

106

106

105

104

103

100

97

94

91

8500

104

104

103

100

98

96

93

90

88

ZP (ft)

* Conservative values calculated for the maximum landing weight.

Model : 212A

4.64

OPS DATA 72

JUL 15

500

R

PW127F / PW127M 1.1 VMCA IAS * OAT °C

-50

-40

-30

-20

-10

0

+ 10

+ 20

+30

+ 40

+ 50

-1000

112

111

111

110

109

109

108

107

106

106

102

0

111

111

110

109

109

108

107

106

106

104

100

2000

110

110

109

108

107

106

106

105

104

100

97

4000

108

108

107

107

106

105

104

103

100

97

94

6000

107

107

106

105

104

103

102

99

97

94

91

8500

105

105

104

103

102

100

98

95

93

90

87

ZP (ft)

* Conservative values calculated for the maximum landing weight. Legend : Grey background = Out of operational envelope Grey text color = Below Vmcl

Model : 212A

4.65

OPS DATA 72

SEP 10

600

PW127F / PW127M ACTUAL LANDING DISTANCE (M) - SEA LEVEL

NORMAL CONDITIONS - FLAPS 30 15

16

17

18

19

20

21

22

22.5

23

570

570

570

570

570

590

610

630

650

670

680

700

WET

690

690

690

690

700

730

760

780

810

840

850

860

WATER OR SLUSH <1/2 in

640

680

710

750

780

820

860

900

940

980 1000 1020

COMPACT 690 SNOW

720

760

790

830

860

900

930

970 1000 1020 1030

RUNWAY CONDITION

14

DRY

CONTAMINATED BY

R WEIGHT (1000 KG) 13

ICE

1010 1070 1120 1170 1230 1280 1340 1390 1450 1500 1530 1560

ICING CONDITIONS – FLAPS 30

RUNWAY CONDITION

CONTAMINATED BY

WEIGHT (1000 KG) 13

14

15

16

17

18

19

20

21

22

22.5

23

DRY

610

610

620

620

620

640

670

690

710

740

750

770

WET

760

760

760

760

770

800

830

860

890

920

940

950

WATER OR SLUSH <1/2 in

700

740

780

820

860

900

950

990 1040 1080 1100 1130

COMPACT 760 SNOW

800

840

880

920

960 1000 1040 1080 1120 1140 1160

ICE

1140 1200 1260 1320 1390 1450 1520 1580 1640 1710 1740 1770

CORRECTION ON LANDING DISTANCES

-Wind

: • dry or wet runway add 10% per 5 kt tailwind. subtract 2% per 5 kt headwind. • contaminated runway add 16% per 5 kt tailwind. subtract 2% per 5 kt headwind. -Airport elevation : • dry or wet runway add 3% per 1000 ft above sea level. • contaminated runway add 5% per 1000 ft above sea level. -Effect of reverse : landing distances are decreased by : • 2% on dry runway. R • 4% on wet runway. • 8% on runway contaminated by water or slush. • 10% on runway contaminated by compact snow. • 30 % on runway contaminated by ice. CAUTION: On contaminated runway, performances without reverser only are to be used for flight preparation. NOTE: Landing on damp runway. A runway is damp when it is not perfectly dry, but when the water which is on it does not give it a shiny appearance. For damp runway, we consider no performance limitation.

Mod : 5561

Model : 212A

OPS DATA 72

4.66 DEC 14 001

LEFT INTENTIONALLY BLANK

4.67

OPS DATA 72

DEC 14 500

Maximum Landing Weight (Kg) limited by maximum Brake Energy (8.3 MJ) NORMAL CONDITIONS FLAPS 30°- Vref – Dry or Wet Run way – no wind ( * never exceed certified MLW) Landing ISA-30°C ISA-20°C ISA-10°C ISA elevation

ISA+10°C ISA+20°C ISA+30°C ISA+40°C

8500 ft

23 100

22 600

22 200

21 800

21 400

21 000

20 700

20 300

7000 ft

23 700

23 200

22 700

22 300

21 900

21 600

21 200

20 800

5000 ft

24 400

24 000

23 500

23 100

22 700

22 300

21 900

21 500

3000 ft

25 200

24 800

24 300

23 900

23 500

23 100

22 600

22 300

1000 ft

26 100

25 600

25 100

24 700

24 300

23 800

23 400

23 000

0 ft

26 500

26 000

25 500

25 100

24 700

24 200

23 800

23 400

-1000 ft

26 900

26 400

26 000

25 600

25 100

24 600

24 200

23 800

Corrections on Weight limited by maximum brake energy at landing:

• Head wind: increase weight by 3% per 10kt • Tail wind: decrease weight by 11% per 10kt • Vref +10kt: decrease weight by 6% • Icing conditions: decrease weight by 6% • One brake inoperative: decrease weight by 13% • Effect of reverse: increase weight by 2% • Runway slope: - increase weight by 1% per 1% uphill slope - decrease weight by 1% per 1% downhill slope

NORMAL CONDITIONS FLAPS 15°- Vref – Dry or Wet Run way – no wind Landing ISA-30°C ISA-20°C ISA-10°C ISA elevation


8500 ft

20 800

20 400

20 000

19 700

19 300

19 000

18 700

18 400

7000 ft

21 400

20 900

20 500

20 200

19 800

19 500

19 200

18 800

5000 ft

22 000

21 600

21 200

20 900

20 500

20 100

19 800

19 500

3000 ft

22 800

22 300

21 900

21 600

21 200

20 800

20 500

20 100

1000 ft

23 500

23 100

22 700

22 300

21 900

21 500

21 100

20 800

0 ft

23 900

23 400

23 000

22 600

22 200

21 900

21 500

21 100

-1000 ft

24 300

23 800

23 400

23 000

22 600

22 200

21 800

21 500


• Head wind: increase weight by 4% per 10kt • Tail wind: decrease weight by 13% per 10kt • Vref +10kt: decrease weight by 7% • Icing conditions: decrease weight by 7% • Effect of reverse: increase weight by 3% • Runway slope: - increase weight by 1% per 1% uphill slope - decrease weight by 1% per 1% downhill slope

Model : 212A

4.68

OPS DATA 72

DEC 14 500

Maximum Landing Weight (Kg) limited by maximum Brake Energy (8.3 MJ) NORMAL CONDITIONS FLAPS 0°- Vref + 5kt – Dry or We t Runway – no wind Landing ISA-30°C ISA-20°C ISA-10°C ISA elevation


8500 ft

17 600

17 200

16 900

16 600

16 400

16 100

15 900

15 600

7000 ft

18 000

17 700

17 400

17 100

16 800

16 500

16 300

16 000

5000 ft

18 600

18 300

17 900

17 600

17 300

17 100

16 800

16 500

3000 ft

19 200

18 800

18 500

18 200

17 900

17 600

17 300

17 000

1000 ft

19 800

19 400

19 100

18 800

18 500

18 200

17 900

17 600

0 ft

20 100

19 700

19 400

19 100

18 800

18 500

18 100

17 900

-1000 ft

20 400

20 000

19 700

19 400

19 100

18 800

18 400

18 100


• Head wind: increase weight by 4% per 10kt • Tail wind: decrease weight by 15% per 10kt • Vref +10kt: prohibited • Icing conditions: decrease weight by 13% • Effect of reverse: increase weight by 2% • Runway slope: - increase weight by 1% per 1% uphill slope - decrease weight by 1% per 1% downhill slope

Model : 212A

CHECK LIST L.T.R. 72

List of Temporary Revisions

5.01 JUL 15 RO

TR

EDITION DATE

DESTROYED

INSERTION DATE

01

MAY 11

AT REV 32 DATED NOV 11

TR 16 ENV

02

JUN 12

AT REV 33 DATED SEP 13

TR 18 ENV

03

JUL 15

REASON

SEE RTR

104

CHECK LIST R.T.R. 72

Reason of Temporary Revisions

5.02 JUL 15

001

ENV TEMPORARY REVISION N°1 TO 18 ARE NO LONGER AVAILABL E

TR

EDITION DATE

REASON

FOLLOWING FAILURES/ POWER PLANT : SINGLE ENG OPERATION, Procedure “V APP” reviewed

19

JUL 15

FOLLOWING FAILURES/ FLIGHT CONTROL: Pitch disconnect, procedure “At parking “reviewed OPS DATA : Entirely Reviewed with go Around Speed

AFFECTED PAGES

2.04

2.22 From 4.31 to 4.43 and 4.64

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List of Normal Revisions

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EDITION DATE

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OCT 89

01

DEC 89

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MAR 90

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TOTAL EDITION

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TOTAL EDITION

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REMARKS

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REASON FOR ISSUE

CHAP INVOLVED

TR n°18: Banking: - Some Emergency procedure update for 72-212A 1.02-1.02A-1.051.05A-1.06-1.08following AFM 72-212A revision. 1.08A-1.09-1.10 2.01.5002.13.500 - Fuel feed lo pr procedure updated for 72-212A 2.13 EMERGENCY PROCEDURES ; -Content page : Updated - IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE: Procedure improved -ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE : Procedure improved - EMERGENCY DESCENT: Procedure updated - DITCHING: Procedure reviewed( New variant) - FORCED LANDING: Procedure reviewed( New variant) - SEVERE ICING: Procedure reviewed - RECOVERY AFTER STALL and UNRELIABLE AIRSPEED INDICATION: Procedure reviewed PROCEDURES FOLLOWING FAILURES : - AFR AIR BLEED FAULT : All variants reviewed - EFIS COMP : Procedure updated NORMAL PROCEDURES : - BEFORE PROPELLER ROTATION : New variant for the boost (Mod 5908) - BEFORE LANDING: Procedure reviewed - LANDING: Procedure reviewed - ATPCS- Dynamic test : All variants reviewed - CHECK LIST : All variants updated

34

DEC 14

5.06

OPS DATA : Reviewed with Go Around Speeds Mod : 7055 Brake Energy – High Altitude runways Operations Brake Energy – Normal Altitude runways

1.01 1.02 1.02 1.07A 1.08 1.08A 1.09 1.10 2.28 2.31

3.09 & 3.11 3.13 3.14 3.18 6.01 From 4.31 to 4.43 4.66 4.67- 4.68

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List of Modifications

5-09 page 1-104

L.O.M.

DEC 14

MODIF

PARTS

TITLE VALIDITY

1368

2.4

ICE AND RAIN PROTECTION - INSTALL INNER WING DE-ICING SYSTEM

1603

1

ELECTRICAL POWER - INSTALL TRU ON PROVISION

2735

4

ENGINE INDICATING - CHANGE SOFTWARE AS 06 IN E.E.C

3168

2

AUTO FLIGHT - REPLACE AFC COMPUTER

3246

2

ELECTRICAL POWER - ADD BATTERIES DISCHARGE INDICATION IN FLIGHT

3530

1.2

FLIGHT CONTROLS - ELEVATORS INSTALL CLUTCH RECONDITIONING DEVICE ON EXISTING PROVISION (PRODUCTION SCHEME)

3827

2

PROPELLERS - ADD FAILURE INDICATION OF SYNCHROPHASER

4111

1.2.3.6

CONTINUOUS IGNITION TRANSFORMATION IN "MAN IGNITION"

4116

1.2

HYDRAULIC POWER - RELOCATE GREEN PUMP CONTROL CIRCUIT BREAKER

4237

2

INDICATING & RECORDING SYSTEMS INSTALL STANDARD L52 MFC

4238

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INDICATING & RECORDING SYSTEMS INSTALL STANDARD L23 MFC

4366

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List of Modifications

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DEC 14

MODIF

PARTS

TITLE VALIDITY

4371

1.2.3

PROPELLERS 14SF - 11E -PROPELLER CONTROL INSTALL ELECTRONIC REGULATION ON ATR 72-200

4373

2

FLIGHT CONTROLS - AILERONS CONTROLS - INSTALL SPRING TAB

4457

1.2.3

PROPELLERS - INSTALL 568F PROPELLERS ON ATR 72-210

4686

2

CARBURANT - INDIC. QUANTITY INDICATION - ADD LOW LEVEL DETECTION SYSTEM

5205

2

NAVIGATION - ATC/TCAS - ACQUIRE ALTITUDE VIA BUS ARINC 429

5377

1.2.3.6

EQUIPMENT/FURNISHINGS - WIRING FOR COCKPIT ENTRANCE SECURISED

5434

1.2.3.6

EQUIPMENT/FURNISHINGS - INSTALL DOOR ON ELECTRICAL PROVISION

5465

2.3.6

EQUIPMENT/FURNISHINGS - SECURISED DOOR INSTALLATION ON ELECTRICAL SUPPLY

5561

4

LANDING GEAR-MLG-REPLACE DUNLOP WHEELS & BRAKES BY MESSIERBUGATTI ONES

ALL

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Cross Reference Table

5-10 page 1-104

C.R.T.

DEC 14

This table shows, for each delivered aircraft, the cross reference between : - the fleet serial number (F.S.N.) - the manufacturing serial number (M.S.N.) - the registration number It is the F.S.N. which appears in the L.E.N.P. or L.E.T.P.

End

F.S.N.

M.S.N.

REGISTRATION

RO0051

0861

YR-ATH

RO0052

0867

YR-ATI

RO

6.01

NORMAL PROCEDURES 72 R

SEP 13

100

IN CASE OF ICING CONDITIONS REFER TO 3.21

IN CASE OF SEVERE ICING REFER TO 1.09 FINAL COCKPIT PREPARATION

DESCENT

ALTIMETERS ........................................... SET PARKING BRK ...............ON / PRESS CHECK LANDING ELEVATION............................. SET COM / NAV / GPS..................................... SET FUEL QTY ........................................... CHECK ENG F/U ...............................................RESET MEMO PANEL..................................... CHECK PWR MGT .................................................. TO

CCAS.........................................................RCL LDG ELEVATION................................. CHECK GNSS * ...................................... SET / CHECK LDG BUGS ................................ SET / CHECK ARRIVAL BREIFING..................... COMPLETE

BEFORE PROPELLER ROTATION CDLS *........................................................ ON T/O BUGS ...........................SET AND CHECK TRIMS ...................................................... SET TAIL PROP................................... ON BOARD DOORS .............................................CLOSED SEAT BELTS .............................................. ON BEACON .................................................... ON BEFORE TAXI PROP BRK *............................................. OFF COCKPIT COM HATCH ....................CLOSED CL 1 + 2................................................. AUTO ANTI-ICING ........................................AS RQD ANTI-SKID.............................................. TEST FLAPS ...................................................... SET NWS ........................................................... ON TAXI TAXI & T.O LIGHTS.................................... ON BRAKES .............................................. CHECK AFCS......................................... SET / CHECK TO CONFIG............................................ TEST TAKE OFF BRIEFING................... COMPLETE BEFORE TAKE OFF GUST LOCK .................................... RELEASE FLIGHT CONTROLS ........................... CHECK XPDR / TCAS *.................................... CHECK AIR FLOW ............................................ NORM CCAS ............................... RCL then TO INHIB APM* ...................................SET AND CHECK BLEED VALVES .................................AS RQD EXT LIGHTS............................................... ON FD BAR (When lined up)....................CENTER RUDDER CAM ..................................CENTER AFTER TAKE OFF LDG GEAR ................................................. UP FLAPS ..........................................................0° PWR MGT / NP ......................... CLB / CHECK BLEED VALVES ......................................... ON TAXI & T.O LIGHTS.................................. OFF ALTIMETERS ............................ SET / CHECK

APPROACH SEAT BELTS .............................................. ON LDG LIGHTS .............................................. ON ALTIMETERS ...................... SET AND CHECK CABIN ALTITUDE................................ CHECK BEFORE LANDING LDG GEAR ....................................... 3 GREEN FLAPS ................................................. CHECK PWR MGT ...................................................TO TLU......................................................LO SPD ICING AOA LIGHT............................... CHECK EXT LIGHTS............................................... ON AFTER LANDING RADAR ....................................................STBY FLIGHT CONTROLS ......................... LOCKED FLAPS .......................................................... 0° TRIMS ....................................................... SET LAND LIGHTS / STROBES........................OFF ANTI-/DE-ICING ........................................OFF  After at least one minute CL 1........................... FTR THEN FUEL SO PARKING PARKING BRK ........................................... ON TAXI & T.O LIGHTS.................................. OFF CL 2 ......................................................... FTR PROP BRK *............................................... ON BEACON .................................................. OFF TAIL PROP ............................... ON POSITION SEAT BELTS ............................................ OFF  When leaving aircraft OXYGEN MAIN SUPPLY ................... OFF ICE AND RAIN PROTECTION ........... OFF EXT LIGHTS....................................... OFF EMER EXIT LIGHT.......................DISARM EFIS / RADAR / COM / NAV............... OFF CL 2............................................ FUEL SO FUEL PUMPS 1 + 2............................ OFF CDLS * ............................................... OFF EXT PWR ........................................... OFF BAT .................................................... OFF

* : if applicable / if installed

ON GROUND EMER EVACUATION AIRCRAFT / PARKING BRAKE ...........................................................STOP / ENGAGE AUTO PRESS....................................................................................................... DUMP ATC (VHF 1)...................................................................................................... NOTIFY CL 1 + 2......................................................................................... FTR THEN FUEL SO MIN CAB LIGHT ........................................................................................................ ON CABIN CREW (PA)............................................................................................ NOTIFY FIRE HANDLES 1 + 2.............................................................................................PULL AGENTS............................................................................................................AS RQD ENG START ROTARY SELECTOR..............................................OFF / START ABORT FUEL PUMPS 1 + 2................................................................................................. OFF EVACUATION .................................................................................................. INITIATE  Before leaving aircraft, BAT............................................................................... OFF

Mod : 3973 or 4371 or 4457

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