ATR 72-500 QRH

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

R The boxed items correspond to actions performed by memory by the crew within a minimum period of time

 : highlights a precondition to apply an action

 : highlights the moment when an action is to be applied PROCEDURES INITIATION

No action will be taken (apart from depressing MC/MW pushbutton) : R

R

- 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

R R R

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 : - PL

- flight path and airspeed control - aircraft configuration

- navigation

PNF, Pilot Non Flying, responsible for :

- Check List reading

- execution of required actions - actions on OVHD panel - CL

- communications The AFCS is always coupled to the PF side (CPL selection) ANALYSIS OF CONSEQUENCES OF A FAILURE ON FLIGHT

Basic airmanship calls for a management review of the remaining aircraft capabilities under the responsibility of CM1.

72

EMERGENCY

1 - EMERGENCY PROCEDURES

IN FLIGHT ENG FIRE OR SEVERE MECHANICAL DAMAGE ………... 1.02 ON GROUND ENG FIRE OR SEVERE MECHANICAL DAMAGE ……. 1.02 ON GROUND EMER EVACUATION ……… 1.02

R ENG FIRE AT TAKE OFF ……….. 1.02A

BOTH ENGINES FLAME OUT ……….. 1.03 ENG FLAME OUT AT TAKE OFF ………. 1.04 BOMB ON BOARD ……….. 1.04 COCKPIT DOOR SECURITY SYSTEM ……….. 1.04A SMOKE ………. 1.05 ELECTRICAL SMOKE………. 1.05A AIR COND SMOKE ………. 1.05A

FWD SMOKE………...………. 1.06

AFT SMOKE……….. 1.06 AUX AFT COMPT SMOKE……….. 1.06 DUAL DC GEN LOSS ………. 1.07 EMERGENCY DESCENT ……….. 1.07A DITCHING ………. 1.08 FORCED LANDING ………. 1.08A SEVERE ICING ……… 1.09 RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL………. 1.10 R

UNRELIABLE AIRSPEED INDICATION………. 1.11

72 JUN 12 500

IN FLIGHT ENG FIRE

OR SEVERE MECHANICAL DAMAGE

If condition persist after 10 seconds

AGENT 1 affected side ... DISCH

If condition persist after 30 seconds

AGENT 2 affected side ... DISCH LAND ASAP

SINGLE ENG OPERATION procedure (2.04) ... APPLY

ON GROUND ENG FIRE

OR SEVERE MECHANICAL DAMAGE

 When aircraft stopped

PARKING BRAKE ... ENGAGE CL 1 + 2 ... FTR THEN FUEL SO FIRE HANDLE affected side...PULL
If condition persist

AGENT 1 affected side ... DISCH

If condition persist after 30 seconds ... AGENT 2 affected side ... DISCH

If evacuation required

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

ON GROUND EMER EVACUATION

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

 Before leaving aircraft

BAT ... OFF

72

EMERGENCY

JUN 12 500

ENG FIRE AT TAKE OFF

Note: Captain may decide to shut down affected engine before reaching acceleration altitude, but not before 400ft AGL.

When airborne LDG GEAR ...UP
At Acceleration Altitude PWR MGT...MCT
At VFTO  If normal condition FLAPS... 0°  If icing condition FLAPS... MAINTAIN 15° PL affected side ... FI CL affected side... FTR THEN FUEL SO FIRE HANDLE illuminated……….. ...PULL  If fire persist after 10 seconds

AGENT 1 affected side ... DISCH

 If fire persist after 30 seconds

AGENT 2 affected side... DISCH BLEED engine alive ... OFF if necessary LAND ASAP

SINGLE ENG OPERATION procedure (2.04) ... APPLY

72 OCT 09 100

BOTH ENGINES FLAME OUT

R

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

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

72

EMERGENCY

OCT 09 100

BOTH ENGINES FLAME OUT

R

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

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

72 NOV 11 500

ENG FLAME OUT AT TAKE OFF

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

1.04A

72

EMERGENCY

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

72

EMERGENCY

JUN 12 500

SMOKE

CREW OXY MASKS... ON / 100% GOGGLES ...SET CREW COMMUNICATIONS ...ESTABLISH RECIRC FANS 1 + 2 ... OFF AP ... ON SMOKE SOURCE... IDENTIFY

If source not identified or electrical smoke suspected Note: ELEC light may be activated by an air conditioning smoke source

ELECTRICAL SMOKE procedure (1.05A) ... APPLY

If air conditioning smoke identified

AIR COND SMOKE procedure (1.05A) ... APPLY

If FWD SMK illuminated or smoke in FWD zone of aircraft FWD SMOKE procedure (1.06)... APPLY

If AFT SMK illuminated or smoke in AFT zone of aircraft

AFT SMOKE procedure (1.06) ... APPLY

If AUX AFT COMPT SMK illuminated (depending on models)

AUX AFT COMPT SMK procedure (1.06) ... APPLY

72 JUN 12 500

ELECTRICAL SMOKE

SMOKE procedure (1.05) ... APPLY AVIONICS VENT EXHAUST MODE ... OVBD AIR FLOW...HIGH DC SVCE AND UTLY BUS... OFF DC BTC... ISOL ACW GEN 1 + 2... OFF SUSPECTED EQUIPMENTS ... OFF

If smoke origin not identified LAND ASAP

ACW TOTAL LOSS procedure (2.16A) ... APPLY

If smoke origin identified

NOT AFFECTED EQUIPMENTS ... RESTORE

 When ∆∆∆∆P below 1 PSI

OVBD VALVE ...FULL OPEN AVIONICS VENT EXHAUST MODE ...NORM

AIR COND SMOKE

SMOKE procedure (1.05) ... APPLY PACK VALVE 1... OFF MAX FL ...200 / MEA

If smoke persists

PACK VALVE 1 ... ON PACK VALVE 2 ... OFF CAUTION: Evacuation of air conditioning smoke may trigger

electrical smoke warning. Disregard it.

ENGINES PARAMETERS... CAREFULLY MONITOR

If any anomaly occurs, such as:

- amber engine caution illumination associated to local ITT alert

- total loss of NL indication

- engine abnormality clearly identified (NH, NL, ITT indications, noise, surge…)

CAUTION: Confirm which engine is showing signs of abnormal operation in order to avoid shutting down safe engine. PL affected side ... FI CL affected side... FTR THEN FUEL SO LAND ASAP

SINGLE ENG OPERATION procedure (2.04)... APPLY

72

EMERGENCY

JUN 12 502

FWD SMK

SMOKE procedure (1.05) ... APPLY 1) PASSENGERS VERSION

CABIN CREW (PA)... ADVISE AVIONICS VENT EXHAUST MODE ... OVBD AIR FLOW ...HIGH EXTRACT AIR FLOW LEVER (RH MAINT PANEL) ...CLOSED CABIN CREW WITH PORTABLE EXTINGUISHER,

LOCATE AND KILL SOURCE OF SMOKE LAND ASAP

When ∆∆∆∆P below 1 PSI

OVBD VALVE ...FULL OPEN AVIONICS VENT EXHAUST MODE ...NORM 2) CARGO VERSION

CAB PRESS MODE SEL...MAN CAB ALT ... MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)... OFF PACK VALVE 2 (Except when in single pack operation) ... OFF CAB VENT AIR FLOW ... OFF FLIGHT COMPT TEMP SEL ... HOT CAUTION: LAND ASAP. If a quick landing is not possible, climb and maintain minimum FL160; FL200 is recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

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

AFT SMK

SMOKE procedure (1.05) ... APPLY 1) PASSENGERS VERSION

CABIN CREW (PA)... ADVISE FOR ACTION AIR FLOW ...HIGH 2) CARGO VERSION

CAB PRESS MODE SEL...MAN CAB ALT ... MAX INCREASE ENG 2 BLEED (Except when in single bleed operation)... OFF PACK VALVE 2 (Except when in single pack operation) ... OFF CAB VENT AIR FLOW ... OFF FLIGHT COMPT TEMP SEL ... HOT CAUTION: LAND ASAP. If a quick landing is not possible, climb

and maintain minimum FL160; FL200 is

recommended. When “Excess CAB ALT” warning, maintain FL160, maintain CAB ALT maw increase.

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

AUX AFT COMPT SMK

(depending on models)

SMOKE procedure (1.05) ... APPLY AUX AFT COMPT AGENT ... DISCH

72 OCT 09 300

DUAL DC GEN LOSS

R

DC GEN 1 + 2 ... OFF then ON

If no generator recovered

HYD GREEN PUMP ... OFF TRU... ON 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

1.07A

72

EMERGENCY

SEP 07 100

EMERGENCY DESCENT

OXYGEN MASKS / CREW COMMUNICATIONS ...AS RQD GOOGLES ...AS RQD DESCENT...INITIATE PL 1 + 2... FI CL 1 + 2 ... 100% OVRD OXYGEN PAX SUPPLY ...AS RQD SPEED... MMO / VMO (or less if structural damage is suspected) SIGNS... ON ATC ... NOTIFY MEA ... CHECK

72 JUN 12 500

DITCHING

Preparation (time permitting)

ATC (VHF1 or HF) ... NOTIFY XPDR ... EMERGENCY CABIN CREW (PA)... NOTIFY SIGNS... ON GPWS... OFF TERR (If TAWS installed) ... OFF CABIN AND COCKPIT ... PREPARE

- Loose equipment secured

- Survival equipment prepared

- Belts and shoulder harnesses locked

AUTO PRESS - LDG ELEVATION...SET

Approach

AUTO PRESS... DUMP PACKS 1 + 2... OFF OVBD VALVE ...FULL CLOSE HYD AUX PUMP pushbutton ... DEPRESS FLAPS (If available)...30 LDG GEAR LEVER ...UP

30 seconds before impact or 1250 ft above sea level

DITCH PB ... ON ENG START ROTARY SELECTOR... OFF / START ABORT CABIN REPORT... OBTAINED

Before ditching (200 ft) MINIMIZE IMPACT SLOPE

OPTIMAL PITCH ATTITUDE FOR IMPACT ... 9° BRACE FOR IMPACT ...ORDER Note: In case of night ditching, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). CL 1 + 2 ... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ...PULL FUEL PUMPS 1 + 2... OFF

After ditching

Note: After ditching, one aft door will be under the water line. CABIN CREW (PA)... NOTIFY EVACUATION ...INITIATE

Before leaving aircraft

BAT ... OFF

72

EMERGENCY

JUN 12 500

FORCED LANDING

Preparation (time permitting)

ATC (VHF1 or HF) ... NOTIFY XPDR ... EMERGENCY CABIN CREW (PA)... NOTIFY SIGNS... ON GPWS... OFF TERR (If TAWS installed) ... OFF CABIN AND COCKPIT ... PREPARE

- loose equipment secured

- survival equipment prepared

- belts and shoulder harnesses locked

AUTO PRESS - LDG ELEVATION...SET

Approach

HYD AUX PUMP pushbutton ... DEPRESS FLAPS (If available)...30 LDG GEAR LEVER ...AS RQD AUTO PRESS... DUMP ENG START ROTARY SELECTOR... OFF / START ABORT CABIN REPORT... OBTAINED

Before impact (200 ft)

BRACE FOR IMPACT ...ORDER Note: In case of night forced landing, shutting down both engines may be performed at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). CL 1 + 2 ... FTR THEN FUEL SO FIRE HANDLES 1 + 2 ...PULL FUEL PUMPS 1 + 2... OFF

After impact, when aircraft stopped

CABIN CREW (PA)... NOTIFY AGENTS ... DISCH EVACUATION ...INITIATE

Before leaving aircraft

BAT ... OFF

72 JUN 12 500

SEVERE ICING

MINIMUM ICING SPEED ... INCREASE 10 kt PWR MGT...MCT CL 1 + 2 ...100% OVRD PL 1 + 2...NOTCH AP (if engaged) ... FIRMLY HOLD CONTROL WHEEL and DISENGAGE SEVERE ICING CONDITIONS...ESCAPE ATC ... NOTIFY

If an unusual roll response or uncommanded roll control movement is observed :

Push firmly on the control wheel

FLAPS...EXTEND 15

If the flaps are extended, do not retract them until the airframe is clear of ice.

For approach, if the aircraft is not clear of ice:

GPWS ... FLAP/GPWS OVRD STEEP SLOPE APPROACH (≥4.5°) ...PROHIBITED APP/LDG CONF ... MAINTAIN FLAPS 15 APP SPEED ... "REDUCED FLAPS 15 LDG icing speeds" + 5 kt Multiply landing distance FLAPS 30 by 2.12.

DETECTION

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

and / or Unexpected decrease in speed or rate of climb

and / or The following secondary indications :

. Water splashing and streaming on the windshield

. Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice

. Accumulation of ice on the lower surface of the wing aft of the protected areas

. Accumulation of ice on propeller spinner farther aft than normally observed

The following weather conditions may be conducive to severe in-flight icing :

. Visible rain at temperatures close to 0°C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0°C

ambient air temperature (SAT)

Eng : PW127F / PW127M 72

EMERGENCY

JUN 12 500

RECOVERY AFTER STALL

or ABNORMAL ROLL CONTROL

R R

R R R

CONTROL WHEEL... PUSH FIRMLY

If flaps 0° configuration FLAPS ... 15° PWR MGT ...MCT CL 1 + 2 ... 100% OVRD PL 1 + 2 ...NOTCH ATC ... NOTIFY

If flaps are extended

PWR MGT ...MCT CL 1 + 2 ... 100% OVRD PL 1 + 2 ...NOTCH ATC ... NOTIFY Note: this procedure is applicable regardless the LDG GEAR

position is (DOWN or UP)

UNRELIABLE AIRSPEED INDICATION

AP/YD/FD BARS ...OFF/OFF/STBY PITCH AND TQ ... MAINTAIN

If at take off or GA below 1500 ft:

PITCH IMMEDIATELY ... 8° ICING / VOLCANIC ASHES CONDITIONS...ESCAPE PROBE HEATING, DE-/ANTI-ICING ... CHECK ON APM... OFF WARNING: respect STALL alarm.

Note: Use any GPS speed information if available.

 Take off phase, at or above acceleration altitude

ALTITUDE... MAINTAIN AT LEAST 30 SECONDS FLAPS... 0° PITCH ... 8° Note: Use climb table here after to adjust pitch if required.

AFTER TAKE OFF normal procedure ... APPLY LAND AT THE NEAREST SUITABLE AIRPORT

 Climb

TLU ... LO SPD PWR MGT... CLB PL 1 + 2...NOTCH

Altitude (ft) 5000 10000 15000 20000

Normal conditions pitch 7° 5° 4° 3°

Icing conditions pitch 6° 4° 3° 2°

Eng : PW127F / PW127M

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:

TQ (Altitude of 3000ft) Aircraft configuration - Average speed _{14 T 18 T 22 T} Flaps 0° - 180 kt 35% 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%

72

FOLLOWING FAILURES

JUN 12 500

2 - PROCEDURES FOLLOWING FAILURES

Content 1/3 POWER PLANT

SINGLE ENG OPERATION………. 2.04

START FAULT………... 2.04

X START FAIL……… 2.04

ABNORMAL PARAMETERS DURING START……… 2.05 EXCESSIVE ITT DURING START………. 2.05

NO ITT DURING START……….. 2.05

NO NH DURING START……….. 2.05

ENG NAC OVHT 2.06

ABNORMAL ENG PARAMETERS IN FLIGHT……… 2.06

FIRE LOOP FAULT……….. 2.06

ABNORMAL PROP BRK………. 2.07

ENG RESTART IN FLIGHT………. 2.08

ENG STALL……… 2.08

ONE EEC FAULT……….. 2.09

BOTH EEC FAULT……… 2.09

ENG FLAME OUT………. 2.10

IDLE GATE FAIL……… 2.10

SYNPHR FAIL (if applicable) ………. 2.10A CL PNEUMATIC ACTUATOR BLOCKING (if applicable) ………. 2.10A UNCOMMANDED 100% NP ON ONE OR TWO PROPELLERS (if applicable) ……… 2.10A PEC SGL CH (if applicable) ……… 2.10A PEC FAULT (if applicable) ……….. 2.10A

LO PITCH IN FLIGHT………... 2.11

ENG OVER LIMIT………. 2.11

PROP OVER LIMIT……….. 2.11

ENG OIL TEMP BELOW 45°C ……… 2.12

ENG OIL TEMP HIGH……….. 2.12

ENG OIL LO PR………. 2.12

ENG BOOST FAULT (if applicable) ……….. 2.12A

FUEL

FUEL ABNORMAL TEMP……… 2.13

FUEL CLOG……… 2.13

FUEL FEED LO PR……….……….. 2.13

FUEL LEAK ALERT CONDITION……….. 2.14

FUEL LO LVL………. 2.14 FUEL LEAK……… 2.14 ELEC DC BUS 1 OFF ………. 2.15 AC BUS 1 OFF ………. 2.15

DC BUS 2 OFF ………. 2.15A

AC BUS 2 OFF ………. 2.15A

ACW BUS 1 OFF / ACW BUS 2 OFF……… 2.16

ACW TOTAL LOSS……….. 2.16A

DC ESS BUS OFF……… 2.17

DC EMER BUS OFF………. 2.17

DC GEN FAULT………. 2.18

INV FAULT………. 2.18

ACW GEN FAULT………. 2.18

DC SVCE/UTLY BUS SHED……… 2.18

BAT CHG FAULT……….. 2.18

DUAL BAT CHG LOSS………. 2.18

BAT DISCHARGE IN FLIGHT (if applicable) ………... 2.18 STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS………... 2.18A _2.18B

ESS BUS AND EMER BUS LOST EQUIPMENT LISTS………. Cargo configuration only…..

2.42 2.42A

72 OCT 09 001

2 - PROCEDURES FOLLOWING FAILURES

Content 2/3 HYDRAULIC

R HYD LO LVL ……….. 2.19

BOTH MAIN HYD PUMPS LOSS ……….. 2.19

BOTH HYD SYS LOSS ……… 2.20

HYD LO PR / HYD OVHT ……… 2.20

FLIGHT CONTROL

FLAPS UNLK ………. 2.21

FLAPS JAM / UNCOUPLED / ASYM ……… 2.21

REDUCED FLAPS LANDING ………. 2.21

STICK PUSHER / SHAKER FAULT ……….. 2.21 PITCH TRIM ASYM (LOCAL LIGHT) ……… 2.22 PITCH TRIM INOPERATIVE ……….. 2.22 DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTER UNIT FAIL …... 2.22

PITCH DISCONNECT ………. 2.22

PITCH RECONNECTION ON GROUND (If applicable) ……… 2.22A

TLU FAULT ……… 2.22A

AIL LOCK LIT (if applicable) ………... 2.22A

ELEVATOR JAM ……….. 2.23

AILERON JAM / SPOILER JAM ………. 2.23

RUDDER JAM ………... 2.23

LANDING GEAR

LDG GEAR GRAVITY EXTENSION ………. 2.24 LANDING WITH ABNORMAL LDG GEAR ……….. 2.24 LDG GEAR UNSAFE INDICATION ……….. 2.25 LDG GEAR RETRACTION IMPOSSIBLE ……… 2.25

ANTI-SKID FAULT ……… 2.25

BRK TEMP HOT ………... 2.25

AIR

BLEED VALVE FAULT ……… 2.26

BLEED OVHT ……… 2.26

BLEED LEAK ……… 2.26

X VALVE OPEN ……… 2.26

PACK VALVE FAULT ……….. 2.26

BOTH PACK VALVES FAULT ……… 2.26

RECIRC FAN FAULT ………... 2.26

DUCT OVHT ……….. 2.26A

EXCESS CAB ALT ………... 2.26A

AUTO PRESS FAULT ………. 2.26A

EXCESS CAB ∆P ………. 2.26A

AVIONICS VENT EXHAUST MODE FAULT ………... 2.27

OVBD VALVE FAULT ……….. 2.27

72

FOLLOWING FAILURES

SEP 10 001

2 - PROCEDURES FOLLOWING FAILURES

Content 3/3 ANTI ICE

AFR AIR BLEED FAULT ………. 2.28

DE-ICING AIR FRAME FAULT ……….. 2.28

DE-ICING MODE SEL FAULT ……… 2.28

MODE SEL AUTO FAULT (if applicable) ………. 2.28

ICE DETECT FAULT ……… 2.29

DE- / ANTI-ICING ENG FAULT ………. 2.29

ANTI-ICING PROP FAULT ………. 2.29

ANTI-ICING HORNS FAULT ……….. 2.29 SIDE WINDOW / WINDSHIELD HTG FAULT ………. 2.29

PROBES HTG FAULT ………. 2.29

AUTO PILOT

AILERON MISTRIM (ADU message)

or EXCESSIVE LATERAL TRIM REQUIRED ……….. or ABNORMAL FLIGHT CHARACTERISTICS

2.30

PITCH MISTRIM (ADU message) ………. 2.30 PITCH TRIM FAIL (ADU message) (if applicable) ……….. 2.30 DADC DATA INVALID (ADU message) ……… 2.30

MPC

APM FAULT ……….. 2.30A

DEGRADED PERF ……….. 2.30A

INCREASE SPEED ………. 2.30A

AVIONICS

AUDIO SEL FAULT ……….. 2.31

AHRS A / ERECT FAIL ……… 2.31

EFIS COMP ………... 2.31 ADC SW FAULT ………... 2.31 ADU FAILURE ……….. 2.32 ADC FAULT ……….. 2.32 AHRS FAIL ……… 2.32 SGU FAIL ……….. 2.32 CRT FAIL ……….. 2.32 MISCELLANEOUS

COCKPIT DOOR CONTROL PANEL FAULT (if installed) ……… 2.32A

VOLCANIC ASH ENCOUNTER……… ………. 2.32A

LOSS OF RADIO ALTIMETER INFORMATION ………. 2.33

R SMK DET FANS FAULT ………. 2.33

DOORS UNLK IN FLIGHT ………. 2.33

COCKPIT WINDOW CRACKED ……… 2.33

OXYGEN LO PR ……….. 2.33 MFC MFC 1A FAULT ……… 2.34 MFC 1B FAULT ……… 2.34 MFC 2A FAULT ……… 2.35 MFC 2B FAULT ……… 2.35 MFC 1A + 1B FAULT ………... 2.36 MFC 1A + 2A FAULT ………... 2.37 MFC 1A + 2B FAULT ………... 2.38 MFC 1B + 2A FAULT ………... 2.39 MFC 2A + 2B FAULT ………... 2.40 MFC 1B + 2B FAULT ………... 2.41

ELEC Section for EMER & ESS BUS lost equipment lists……….……… Cargo configuration only……

2.42 2.42A

72 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

2.05

72

POWER PLANT

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

R

Note: On BAT only, OIL PRESS IND is not available.

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 SEP 10 001

R

_{ENG NAC OVHT}

R R

R R R

 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

 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

72

POWER PLANT

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

72 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

2.09

72

POWER PLANT

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 OCT 09 050

ENG FLAME OUT

R R R

PL affected side ... FI

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

72

POWER PLANT

UNCOMMANDED 100% NP ON ONE OR

TWO PROPELLERS

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

72 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

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

2.12

72

POWER PLANT

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 JUN 12 500

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

72

FUEL

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

72 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 26 AC BUS 1

BLEED LEAK DET 1 & 2 TRIMS IND

For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60

72

ELEC

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

R 115 AC BUS 2 26 AC BUS 2

R GPWS CM2 ASI, VSI, ALTI

Heading RMI#1

Bearing VOR#2&ADF#2 to RMI/SGU 1/2 Course#2 and Heading#2 Select

R R R For more information on BUS EQUIPMENT LISTS see F

COM 1.06.60

72 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

ELEC

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)

R R R R R R R R

72 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.

DC ESS BUS LOST EQUIPMENT LIST R

R

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)

2.18

72

ELEC

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

72 APR 08 550

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

2.18B

72

ELEC

STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS

72 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 GREEN

FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable)

EMER AND PARKING BRK (on accu only)

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

BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST

R R

BLUE

recovered when LDG GEAR lever is DOWN

GREEN

R R R

FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable)

EMER AND PARKING BRK (on accu only)

LDG GEAR EXT / RET NORM BRK

72

HYDRAULIC

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 BLUE GREEN

R R R

FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable)

EMER AND PARKING BRK (on accu only)

LDG GEAR EXT / RET NORM BRK

HYD LO PR / HYD OVHT

PUMP affected side ... OFF X FEED ... ON

72 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

72

FLIGHT CONTROL

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

DUTCH ROLL TENDENCY /

RUDDER RELEASABLE CENTERING

UNIT FAIL

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 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

2.23

72

FLIGHT CONTROL

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

72 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

2.25

72

LANDING GEAR

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 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

2.26A

72

AIR

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

72 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

2.28

72

DE/ANTI ICE

AFR AIR BLEED FAULT

LEAVE AND AVOID ICING CONDITIONS

AFR AIR BLEED ... OFF „ If DE-ICING ENG FAULT light illuminates after 10 s

DE-ICING ENG affected side ... OFF AFR AIR BLEED... ON AFR AIR BLEED light ...CHECK EXTINGUISH „ If DE-ICING ENG FAULT light does not illuminate on any side

DE-ICING AIR FRAME FAULT procedure (2.28)... APPLY

DE-ICING AIR FRAME FAULT

DE-ICING AIR FRAME ... OFF LEAVE AND AVOID ICING CONDITIONS

MINIMUM ICING SPEEDS ... INCREASE BY 10 kt „ If in icing conditions

LDG DIST ... MULTIPLY BY 1.13 Note: Refer to Part 4 to determine SPEEDS and LDG DIST

„ If ice accretion

STEEP SLOPE APPROACH (≥4.5°)... PROHIBITED

DE-ICING MODE SEL FAULT

OVRD...SELECT MONITOR DE-ICING

„ In case of engine flame out

OVRD... RELEASE

MODE SEL AUTO FAULT

MODE SEL ...MAN DE-ICING and ANTI-ICING MANUAL MODE PBs:

ACCORDING TO CURRENT SAT ...SELECT

72 OCT 09 500

ICE DETECT FAULT

ICE ACCRETION... VISUALLY MONITOR

DE-/ANTI-ICING ENG FAULT

ENGINE PARAMETERS affected side...MONITOR

ANTI-ICING PROP FAULT

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

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