Q-AIRCRAFT KEY NOTES IN ABNORMAL SITUATIONS Flashcards
“#1 BLEED HOT” and
“#2 BLEED HOT”
(Caution Lights)
Note: ECS Pack airflow is lost and cabin will
depressurize.
“CABIN PACK HOT” and
“FLT COMPT PACK HOT”
( Caution Lights )
Note: ECS Pack airflow is lost and cabin will
depressurize.
EMERGENCY OPENING OF
AIRSTAIR DOOR
(Door Fails To Open)
Note: The airstair door failure to open may be associated with a failure of IOM 1 or IOM 2.
The checklist will call to pull the air stair door circuit breaker, and then try to open the door. if this doesn’t work then it will call for turning the master off and then trying again, IF all don’t work then use the back doors
NO STARTER CUT OUT
START Light remains illuminated
Note: Engine START and SELECT lights will take approximately 15 seconds to go out
HIGH OIL PRESSURE
Continuous Oil Pressure above 72 psi
Caution: Maximum power reductionmust not exceed 20%
of previously set torque.
Note: Power reduction will be dependant on
performance, including icing, and airspeed requirements. Minimum airspeed will be appropriate to flap configuration and flight
conditions.
The checklist will call for reducing power to the affected engine and monitoring what the pressure does.
If the presaure decreases below 72psi but not below 44psi then continue the flight and have maintenance action when you land.
If the pressure stays or increases above 72psi then ENGINE FAILURE/FIRE/SHUTDOWN
HIGH OIL TEMPERATURE IN FLIGHT
107 _ C or above
Caution: Maximum power reductionmust not exceed 20%of previously set torque.
Note: Power reduction will be dependant on performance, including icing, and airspeed requirements. Minimum airspeed will be
appropriate to flap configuration and flight conditions.
The checklist will call for reducing power to the affected engine and monitoring what the pressure does for 10 minutes
IF oil temperature decreases below 107 _C:
- – Maintain power at or below the adjusted torque setting for remainder of the flight.
- – Maintenance action required prior to next flight.
IF oil temperature does not decrease or increases above 125 _C:
Affected engine:
ENGINE FAILURE/FIRE/SHUTDOWN
DUAL PROPELLER OVERSPEED
Note: During overspeed governor control, an increase in power or turbulence encountermay cause the propeller speed to temporarily exceed 1080 rpm. With Power Levers in the RATING DETENT, the
TRQ indication will be less than the displayed torque rating. Landing
Considerations:
— DO NOT retard Power Levers below FLT IDLE on
landing and during taxi, as propellers will feather.
— Anticipate greater than normal braking requirements
due to increased propeller thrust at FLT IDLE setting.
Note: During the landing roll, propellers will decrease
to approximately 500 - 550 RPMand may cause
the AC generators to drop off-line.
PROPELLER OVERSPEED
Note: If the engine is not shutdown immediately after feathering the propeller with the Alternate Feather system, the propeller may unfeather. Re-select the ALT FTHR switch to feather the propeller.
Symmetric Power levers will give approximately symmetric power.
During overspeed governor control, an increase in power or turbulence encountermay cause the propeller speed to temporarily exceed 1080 rpm.
Landing Considerations ifpropeller does not feather:
— DO NOT retard affected Power Lever below FLIGHT
IDLE on landing.
— Anticipate greater than normal braking requirements
due to increased propeller thrust at FLT IDLE setting.
“#1 PEC” or “#2 PEC”
Caution Light
Landing Considerations:
— DO NOT retard affected Power Lever below FLIGHT
IDLE on landing.
— Anticipate greater than normal braking requirements
due to increased propeller thrust at FLT IDLE setting.
LOSS OF PILOT, CO-PILOT and
STANDBY AIRSPEED and
ALTITUDE INDICATIONS
(Loss of both pitot-static probes on the right side of the
aircraft due to a suspected bird strike)
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
LOSS OF BOTH AIRSPEED and BOTH
ALTITUDE INDICATIONS ON PILOT’s and
CO-PILOT’s PFDs
(Air Data 1 and 2 sources have failed)
Lost Services:
Autopilot and Yaw Damper
Flight Director
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
“IAS FAIL” or “ALT FAIL”
Message on PFD
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
“IAS MISMATCH”
(Message on PFD)
(Air Data 1 and 2 airspeed indications do not match)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR OUTBD” and “RUD CTRL” Caution lights will illuminate. Elevator forces, roll rate and rudder sensitivity may be higher or lower than usual.
“ALT MISMATCH”
(Message on PFD)
(Air data 1 and 2 altitude indications do not match)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
“LOC MISMATCH” or “GS MISMATCH”
(Message on PFD)
(ILS 1 and 2 deviation indications do not match)
Note: If a mismatch appears between the two ILS
sources in DUAL APPR mode, the flight director
will automatically switch back to the HSI (which
may not be valid) that was in use at the
commencement of the approach.
“RA” (Message on PFD)
Both Radar Altimeters have failed
Lost Services:
Stick Pusher
EGPWS
TCAS
— Ensure required clearance from terrain, obstructions
and other aircraft ismaintained using alternate sources of available information.
“RAD ALT MISMATCH”
(Message on PFD)
(Radar Altimeter 1 and 2 indications do not match)
Note: EGPWS ”Minimums” callouts will be based on
Rad Alt 1 altitudes.
“GPS INTEG”
(Message on PFD)
(The integrity of the GPS position cannot be assured to meet minimum requirements for the particular phase of flight)
Note: “GPS INTEG” message can appear on the
ground, due to local obstructions to satellite
reception.
MAIN DC BUS FAULT
Left Main DC Bus F ault:
(“DC BUS”, “#1 DC GEN”, “STBY BATTERY” and “AUX
BATTERY” Caution Lights)
THE CHECKLIST WILL CALL FOR TURNING OFF THE AUX, STAND BY BATTERIES AND #1 DC GEN OFF AND LEAVING THEM OFF AND TRYING A BUS RESET . IF THE LIGHTS REMAIN THEN NO FURTHER ACTION. IF THE DC BUS STAYS ILLUMINATED, THEN DESCEND TO BELOW 14.000 FEET MANUALLY CONTROL THE CABIND DIIF.
Note: ECS pack airflow is lost and cabin will
depressurize.
The aircraft must then be descended below 14.000 feet and ram ventilated.
Right Main DC Bus F ault:
“DC BUS”, “#2 DC GEN”, and “MAIN BATTERY” Caution Lights
Note: ECS pack airflow is lost and cabin will
depressurize.
The aircraft must then be descended below 14.000 feet and ram ventilated.
“L AC BUS” or “R AC BUS”
(Caution Light)
Note: Affected variable AC BUS is depoweredwith loss of associated services.
Lost Services: L AC BUS R AC BUS L Aux Fuel Pump L Prop Deicing L Alpha Vane Heater L TRU L Ice Detection Sensor Pilot Windshield Heat (Norm & Warmup) L Engine Intake Heater L Pitot Static Heater Stick Pusher System R Aux Fuel Pump R Prop Deicing R Alpha Vane Heater R TRU R Ice Detection Sensor Standby Hydraulic Pump Co-pilot Windshield Heat (Norm) Pilot Side Window Heat R Engine Intake Heater R Pitot Static Heater Stick Pusher System
RUDDER JAM
Restricted Rudder Pedal Movement
Warning: Should the rudder pedal (rudder jam)
suddenly break free, do not apply rudder
pedal input in the opposite direction.
“#1 FUEL FLTR BYPASS” or
“#2 FUEL FLTR BYPASS”
(Caution Light)
Note: Monitor fuel flow, ITT, and NH . If erratic, may
indicate contamination has passed filter.
No. 1 HYDRAULIC SYSTEM FAILURE
LOSS of ALL FLUID from No. 1 HYDRAULIC SYSTEM
(“#1 ENG HYD PUMP” and “#1 HYD ISO VLV” Caution
Lights, and ENGINE 1 HYD valve CLOSED Advisory Light
and no Quantity indicated on No. 1 HYD QTY
REF SPEEDS AND LANDING DISTANCES WILL HAVE TO BE INCREASED AND CONSIDERATIONS MUST BE MAD WITH REGARDS TO DECIDING WHERE TO LAND.
Note: “#1 HYD ISOVLV” Caution Light may go out with
very low hydraulic fluid quantity in the No. 1Hydraulic system.)
Caution: Avoid pitch attitudes in excess of 6_ at touchdown.
DO NOT select Power Levers below Flight Idle until indicated airspeed is below 150 kts. Excessive application of emergency braking can
result in skidding and tire failure.
Lost Services:
Flap
Normal/Anti-Skid Brakes
Inbd Roll Spoiler / ElevatorNo. 1 / RudderNo. 1System
“#1 ENG HYD PUMP”
(Caution Light)
(No Pressure Indicated in the No. 1 Hydraulic System)
Note: Hydraulic pressure will be indicated in the No.3
system and the “#1 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 1 Hydraulic system
Caution: With #1 ENG HYD PUMP caution light
illuminated, DO NOT select PTU CNTRL switch
Landing Considerations:
— Flap extension and retraction is slower than normal.
No. 2 HYDRAULIC SYSTEM FAILURE
LOSS of ALL FLUID from No. 2 HYDRAULIC SYSTEM
(“#2 ENG HYD PUMP” and “#2 HYD ISO VLV” Caution
Lights, and ENGINE 2 HYD valve CLOSED Advisory Light
and no Quantity indicated on No. 2 HYD QTY
REF SPEEDS AND LANDING DISTANCES WILL HAVE TO INCREASE AND CONSIDERED WHEN THINKING ABOUT WHERE TO LAND.
THIS WILL LEAD TO A MANUAL GEAR EXTENSION
Note: “#2 HYD ISOVLV” Caution Light may go out with
very low hydraulic fluid quantity in the No. 2
Hydraulic system.
Lost Services:
Normal Gear Extension and Retraction
Nosewheel Steering
Emerg Brakes (when Park Brake pressure depleted)
OutbdRollSpoiler/ElevatorNo.2/RudderNo.2System
“#2 ENG HYD PUMP”
(Caution Light)
(No Pressure Indicated in the No. 2 Hydraulic System)
Note: Hydraulic pressure will be indicated in the No.3
system and the “#2 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 2 Hydraulic system.
“MISTRIM [TRIM L WING DN]” or
“MISTRIM [TRIM R WING DN]”
(Message on PFD)
(Autopilot is holding a roll force)
Caution: Prior to disengaging the autopilot, firmly hold the
controlwheel and be prepared for a control force
in roll.
“MISTRIM [TRIM NOSE DOWN]” or
“MISTRIM [TRIM NOSE UP]”
(Message on PFD)
(Autopilot is holding a pitch force)
Caution: Prior to disengaging the autopilot, firmly hold the
controlwheel and be prepared for a control force
in pitch.
“FD ADC DATA INVLD”
Message on PFD
(Selected air data source to FD is invalid or mismatched)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will be
illuminated. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than normal.
“FD ATT DATA INVLD”
Message on PF
(Selected attitude data input to FD is invalid or mismatched)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL” Caution light will be
illuminated. Elevator forces may be higher or
lower than normal.
“FD HDG DATA INVLD”
Message on PF
(Selected heading data input to FD is invalid or mismatched)
Lost Services:
Autopilot and Yaw Damper
“FD NAV DATA INVLD”
Message on PFD
(Selected navigation data input to FD is invalid or mismatched)
“CAT II FAIL”
Message on PFD
(Required input for a CAT II ILS approach is invalid or mismatched)
Note: If a mismatch appears between the two HSI
sources in DUAL APPR mode, the flight director
will automatically switch back to the HSI (which
may not be valid) that was in use at the
commencement of the approach.
“CHECK PFD1” or “CHECK PFD2”
Message on PFD
(Critical data on the indicated PFD may be displayed incorrectly)
“ATT FAIL”
Message on PFD
(Source of pitch and roll data to PFD has failed)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL” Caution light will illuminate.
Elevator forces may be higher or lower than
usual.
“HDG FAIL”
Message on PFD
(Source of heading data to PFD has failed)
Lost Services:
Autopilot and Yaw Damper
Note: If amalfunction of the flux valve is the cause of the
heading failure, the SLAVE advisory light, on the
AHRS controller, will also illuminate.
“IVSI FAIL”
Message on PFD
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL” Caution light will illuminate.
Elevator forces may be higher or lower than usual. A valid air data input to the selected AHRS is required for IVSI computation.
“PITCH MISMATCH” or “ROLL
MISMATCH”
(Message on PFD)
(AHRS 1 and 2 attitudes do not match)
Lost Services:
Autopilot and Yaw Damper
Note: “ELEVATOR FEEL” Caution light will illuminate.
Elevator forces may be higher or lower than
usual.
“HDG MISMATCH”
Message on PFD
Lost Services:
Autopilot and Yaw Damper
“CUE” (Message on PFD)
(Low speed cue is invalid)
“RAD ALT MISMATCH”
Message on PFD
(Radar Altimeter 1 and 2 indications do not match)
Note: EGPWS ”Minimums” callouts will be based on
Rad Alt 1 altitudes.
“NAV INTEG”
Message on PFD
(The integrity of the FMS position cannot be assured to meet minimum requirements for the particular phase of flight)
“NAV DR”
Message on PFD
(The FMS is navigating by dead reckoning on the last
known track, groundspeed, heading and TAS)
ENGINE DISPLAY FAILURE
(No data displayed on ED screen)
Note: ED display will automatically transfer toMFD 1 in
flight.
“MAIN BATTERY” or
“AUX BATERY” or
“STBY BATTERY”
(Caution Light)
Checklist , essentially just recycling it and marching it.
“MAIN BAT HOT” or
“AUX BATT” or
“STBY BAT HOT”
(Warning Light)
Confirm with the electrical load and excessive temperature.
Must start planning an immediate lading and the nearest suitable airport.
LOSS OF GENERATED POWER
(Loss of BOTH DC Generators and BOTH AC Generators
or loss of BOTH DC Generators and ONE or BOTH TRUs)
Caution: Battery duration for operation of essential
services is 60 minutes (45 minutes JAA).
Note: ECS pack air flow is lost and cabin will
depressurize.
The aircraft must then be descended below 14.000 feet and ram ventilated.
PITCH CONTROL JAM
Caution: With the PITCH disconnect handle pulled, the
autopilot must not be engaged.
Note: Elevator forces will be lighter than normal and
pitch control degraded.
IF jam occurs below 170 KIAS:
D Airspeed 170 KIAS (max)
IF jam occurs above 170 KIAS:
D Airspeed Airspeed at time of jam (max)
SPLR 1 PUSH OFF SWITCHLIGHT (amber)
turns on to indicate a jam in an inboard spoiler PCU or cable / linkage failure
SPLR 1 PUSH OFF switchlight depressurizes both inboard spoiler PCUs (ROLL SPLR INBD HYD cau-
tion light will illuminate)
RUD 1 PUSH OFF SWITCHLIGHT (amber) (alternate action)
turns on to indicate a jam in lower rudder PCU
RUD 1 PUSH OFF switchlight depressurizes the lower rudder PCU
“SMOKE”
Warning Light
(SMOKE Warning Light and BAGGAGE FWD or AFT SMOKE and EXTG Advisory Lights)
RUN THE SMOKE DRILL AND EXT THE ASSOCIATED SMOKE/EXT SWITCH
FUSELAGE FIRE or SMOKE
SMOKE DRILL
THEN RUN THE CHECK LIST TO IDENTIFY SOURCE OF FIRE LIKE CHECKING THE BLEEDS SBD OR PACKS KEEPING IN MIND THAT IF THE SOURCE IS NOT IDENTIFIED THE CHECKLIST WILL CALL FOR A SHUT DOWN OF ELECTRICAL SYSTEM THA WILL REQUIRE THE PLANE TO DESEND BELOW 14,000 DUE TO LOSS OF PACKS AND AND THE AIRCRAFT WILL REQUIRE A RAM VENTILATION.
(Loss of BOTH DC Generators and ONE AC Generator)
The checklist will all to cycle the gens and then monitor the load
AILERON TRIM RUNAWAY
THE CHECKLIST WILL CALL TO REDUCE YOUR AIRSPEED AND PULL THE CIRCUIT BREAKER WHICH IS ON THE LEFT ESSENTIAL
“ROLL SPLR INBD HYD“ or OUTBD HYD”
Caution Light
Note: Illumination of the ROLL SPLR INBD HYD
Caution Light at an airspeed of 165kt IAS or
greater, may be indicative of a spoiler cable
failure.
“ROLL SPLR INBD HYD“ and “ROL SPLR OUTBD HYD”
Caution Lights
(Spoiler Cable Failure)
BOTH SPOILER 1 AND 2 PSUH OFF SWITCHES MUST BE PUSHED. NOW LANDING DISTANCES WILL HAVE TO BE INCREASED AND FACTORED USING FLAP 10-15 WITH A MINIMUM CROSSWIND.
“ROLL SPLR INBD GND” or OUTBD GND”
Caution Light
Landing Considerations:
— Affected Inboard or Outboard roll spoilers may not
extend at touchdown.
THE CHECKLIST WILL CALL FOR INCREASE REF SPEEDS AND LANDING DISTANCES BECAUSE THE FCECU CAN NOT OPERATE THE LIFT DUMP FUNCTIONALITY OF THE SPOILERS.
“SPLR OUTBD”
Caution Light
MAX SPEED 200KTS
“ELEVATOR FEEL” and “PITCH TRIM” and “SPLR OUTBD” and “UD CTRL” (Caution Lights)
AUTO PILOT OFF
SPEED MAX 200
“ELEVATOR ASYMMETRY”
Caution Light
AUTO PILOT OFF
SPEED MAX 200
“ELEVATOR PRESS”
Caution Light
CHECK LIST AND MAINTENANCE ACTION REQUIRED BEFORE NEXT FLIGHT.
“ELEVATOR FEEL”
Caution Light
AUTO PILOT OFF
SPEED MAX 200
“#1 TANK FUEL LOW” or
“#2 TANK FUE LOW”
(Caution Light)
THE CHECKLIST WILL CALL FOR YOU TO LOOK FOR FUEL LEAK AND IF THERE IS ONE SHUT DOWN THE ENGINE
“#1 ENG FUEL PRESS” or
“#2 ENG FUEL PRES”
(Cautionight)
THE CHECK LIST WILL CALL FOR TURNING ON THE TANK AUX PUMP WITHT THE ENGINE THATS INDICATING THE LOW FUEL PRESS. IF THAT DOESNT WORK THEN IT WILL ASK YOU TO LOOK FOR A FUEL LEAK AND SHUT DOWN THE ENGINE IF NEED BE
“#2 ENG HYD PUMP”
Caution Light
Note: Hydraulic pressure will be indicated in the No.3
system and the “#2 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 2 Hydraulic system.
PTU FAILURE
Amber PTU CNTRL “FAIL” Advisory Light is illuminated
Caution: PTU Cntrl must not be selected ON following
illumination of PTU Cntrl Fail advisory light.
“#1 HYD FLUIDHOT“ or
“#2 HYD FLUIDHOT”
(Caution Light)
CHECKLIST WILL CALL TO MONITOR THE HYD FLUID
“#1 STBYHYD PUMP HOT”
Caution Light
THE CHECKLIST WILL CALL FOR THE STBY PUMP TO BE SET TO NORM IF FLAP IS AT 0
“#1 STALL SYST FAIL” or “#2 STALL SYST FAIL”and
“PUSHER SYST FAIL”
(Caution Lights)
AUTO PILOT OFF
“PUSHER SYST FAIL”
Caution Light
AUTO PILOT OFF AND STICK PUSHER SHUT OFF PUSH
ALTERNATE LANDING GEAR EXTENSION
or “LDG GEAR INOP” (Caution Light)
Landing Considerations:
- – Landing Gear cannot be retracted.
- – Nosewheel steering will be inoperative.
SPEED MAX 185
RAPID DEPRESSURIZATION/
EMERGENCY DESCENT
Smoke Drill and Emergency Decent action memory times
RAM VENTILATION
Bleeds Off
Works Best with speeds above 150 knots
The check list will call for turning the recirc fan off, bleeds off, manually changing the cabin diff, and opening both the cabin alt Fwd outflow open and the FWD outflow fully open
“CABIN PRESS”
(Warning Light)
(Loss of cabin pressure control and/or pressurization
controller “FAULT” Annunciation light illuminated)
Cabin Alt is greater then 9800
The checklist will call to verify that the system is in auto mode and if it its and the problem persists, the switch to manual and manuallly try to rectify the pressure problem. If the manual doesn’t rectify the problem then the you must descend to below 14000 and continue on UNPRESSURIZED FLIGHT
UNPRESSURIZED FLIGHT
The Checklist will call for for dumping of the cabin, bleeds to max and oxygen mask if required
LOSS OF CABIN ALTITUDE, CABIN RATE
and CABIN DIFF INDICATORS
(All Indicators at Zero)
The Checklist will call for manually controlling the cabin DIFF and and then referring to UNPRESSURIZED FLIGHT Checklist
BLEED SYSTEM FAILURE ON TAKE-OFF
(Illumination of “#1 BLEED HOT” and “#2 BLEED HOT”
Caution Lights on take-off with Bleed Switches OFF)
The checklist will call for turing on the bleeds for 10 seconds then turning them off. If the caution stays on then refer to the
“#1 BLEED HOT” and “#2 BLEED HOT” checklist
CRACKED WINDSHIELD
slow to below 210 knots and manually reduce the cabin diff to a max of 3.0 and if practical descend to below 14,000 ft
“FUSELAGE DOORS”
Warning Light
Seat belt sign on, confirm on the MFD which door is indicating then confirm that the pressurization is normal.
Warning DO NOT ATTEMPT to secure DOOR. Land at he nearest suitable airport.
Have the Purser or the FA sit away from the affected door if possible.
EMERGENCY OPENING OF
FLIGHT COMPARTMENT DOOR
(Door Jammed)
B hinge
U hinge
M hinge
APU FIRE
Confirm APU Automatic Shutdown (APU RUN
Advisory Light out and, APU FAIL, APU BTL LOW
and FUEL VALVE CLOSED Advisory Lights
illuminate).
IF APU BTL ARM or APU FIRE Advisory Lights remain
illuminated after 7 seconds:
Extg switchpress
POST APU AUTOMATIC SHUTDOWN
APU Bleed off
APU Gen off
APU power off
Caution:Do not restart the APU following an automatic
shutdown if the FIRE Advisory Light is
illuminated.
APU STARTER FAILURE
APU START Light remains illuminated
The check list will call for a turning the main, stby, and aux batteries, then shutting the engines down and turning off the APU
“APU” (Caution Light)
This will come on either with an APU failure and or APU GEN overheat
The checklist will call to confirm the APU automatic shut down then run the POST APU AUTOMATIC SHUTDOWN
APU BLEED AIR OVERHEAT
(FLT COMPT DUCT HOT or CABIN DUCT HOT or CABIN
PACK HOT or FLT COMPT PACK HOT Caution Light)
This will only happen when in the airplane is on the ground.
The checklist will call for turning he APU bleed OFF
OIL PRESSURE BELOW44 PSI or
“#1 ENG OIL PRES”
“#2 ENG OIL PRES”
(Warning Light)
Affected Engine
ENGINE FAILURE/FIRE/SHUTDOWN
LOW OIL PRESSURE
44-60 PSI
The Checklist will call for bringing he affected power lever to light IDLE and and the condition lever to start feather to reduce DRAG
If the pressure falls below 44PSI, then ENGINE FAILURE/FIRE/SHUTDOWN
LOW OIL TEMPERATURE
(0 -65 C)
(Prop Deice On In Flight
— Exit icing conditions as soon as possible.
“#1 ENG FADEC FAIL” or
“#2 ENG FADEC FAIL”
(Warning Light)
Affected Engine:
ENGINE FAILURE/FIRE/SHUTDOWN
Note: FADEC Failuremay cause the affected engine to
shut down automatically.
“#1 ENG FADEC” or
“#2 ENG FADEC”
(Caution Light)
Make slow and gentle power adjustments
Landing Considerations:
— DO NOT retard affected Power Lever below DISC on
landing.
“POWERPLANT”
ED Advisory
Monitor engine performance
Note: Maintenance action required prior to next flight.
“CHECK FIRE DET” Warning Light and
“FAULT A” or
“FAULT B” Advisory Light
(Fire Detector Loop Failure)
No crew action req’d.
Note: Maintenance action required prior to next flight.
“CHECK FIRE DET” Warning Lightand
“BTL LOW” Advisory Light
(Fire Bottle Pressure Low)
Note: Maintenance action required prior to next flight.
“SMOKE”
Warning Light
SMOKE DRILL
Note: The second Baggage compartment FIRE
BOTTLE LOW Advisory Lightmay illuminate after
the first bottle has been discharged.
— Land immediately at the nearest suitable airport.
“#1 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 1 Hydraulic System)
— Monitor quantity in No. 1 Hydraulic system for further
loss of fluid.
Lost Services:
Normal/Anti-Skid Brakes
Inboard Roll Spoilers
Landing Considerations:
— Use Emergency Brake to stop aircraft (unlimited brake
applications available).
— Approach & VREF speeds
LANDING REF SPEEDS DISTANCES WILL INCREASE
“#2 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 2 Hydraulic System)
Lost Services: Normal Gear Extension and Retraction Nosewheel Steering Emerg Brakes (when Park Brake pressure depleted) Outboard Roll Spoilers Landing Considerations:
D Alternate Landing Gear Extension
(Page 14.3) accomplish when required. . . . . . . . . . . .
— Approach & VREF speeds:
REF SPEEDS AND LAMDING DISTANCES WILL INCREASE
