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Warning Lights Flashcards

1
Q

Cabin Press

red

A

PROBABLE CAUSE
Cabin altitude exceeds 10,000 ft.

IMMEDIATE ACTION
Check FAULT light on CABIN ALTITUDE panel for illumination. If illuminated, select pressurization mode selector switch to MAN and AIR CONDITIONING BLEED selector to MAX. Regulate cabin altitude by manipulation of MAN knob on CABIN ALTITUDE panel.

REMARKS
If FAULT light is not illuminated, select AIR CONDITIONING BLEED selector to MAX and see the QRH for inflight depressurization procedure. CABIN PRESS caution light goes out when cabin pressure goes below 10,000 ft.

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2
Q

FLT COMPT DUCT HOT

amber

A

PROBABLE CAUSE
Flight compartment supply duct temperature exceeds 88 degrees C.

IMMEDIATE ACTION
If caution light repeatedly illuminates and goes out, adjust FLT COMP TEMP CONTROL to a lower setting. If cycling continues, bleed switch off.

REMARKS
Normal operation automatically interrupted and full cool air is routed through ducts until duct temperature is 82 degrees C. Caution light goes out and normal operation resumes.

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3
Q

CABIN DUCT HOT

amber

A

PROBABLE CAUSE
Cabin supply duct temperature exceeds 88 degrees C.

IMMEDIATE ACTION
If caution light repeatedly illuminates and goes out adjust CABIN TEMP CONTROL to a lower setting. If cycling continues, bleed switch off.

REMARKS
Normal operation is automatically interrupted and full cool air is routed through ducts until duct temperature is 82 degrees C. Caution light goes out and normal operation resumes.

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4
Q

AIR COND PACK HOT

amber

A

PROBABLE CAUSE
Air cycle machine (ACM) compressor discharge temperature exceeds 207 degrees C.

IMMEDIATE ACTION
Gradual depressurization will occur while bleed is shut down. If caution light repeatedly illuminates and goes out, reduce ACM cooling demand by adjusting CABIN temperature control and FLT COMP temperature control to higher setting. If cycling continues bleed switch off.

REMARKS
Normal operation is automatically interrupted and both bleed air sub-systems are shut down until air cycle machine cools. Caution light goes out and normal operation resumes.

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5
Q

PRI INV

amber

A

PROBABLE CAUSE
Primary inverter inoperative.

IMMEDIATE ACTION
Check left essential dc circuit breaker panel PRIM INV PWR and PRIM INV CONT circuit breakers (F8, G8). Primary inverter switch - OFF.

REMARKS
With only one inverter operational (two inverters inoperative), power is maintained to all fixed frequency buses via bus tie circuit breaker. Shed loads where possible to minimize load on remaining inverter.

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6
Q

AUX INV

amber

A

PROBABLE CAUSE
Auxiliary inverter inoperative.

IMMEDIATE ACTION
Check left main dc circuit breaker panel AUX INV CONT circuit breakers (D8, E8). Auxiliary inverter switch OFF.

REMARKS
With failure of primary or secondary inverter, auxiliary inverter automatically switches to failed side, regardless of AUX INV switch position.

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7
Q

L 26 AC

amber

A

PROBABLE CAUSE
Left 26 volt fixed frequency transformer inoperative.

IMMEDIATE ACTION
Check avionics circuit breaker panel L26V FAIL circuit breaker (P1). Auxiliary inverter select to operating side.

REMARKS
None.

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8
Q

R 26 AC

amber

A

PROBABLE CAUSE
Right 26 volt fixed frequency transformer inoperative.

IMMEDIATE ACTION
Check avionics circuit breaker panel R 26 V FAIL circuit breaker (P2). Auxiliary inverter select to operating side.

REMARKS
None.

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9
Q

L AC BUS

amber

A

PROBABLE CAUSE
Left ac variable frequency bus not powered.

IMMEDIATE ACTION
None.

REMARKS
If an ac generator fails, left and right ac variable frequency buses automatically tie.

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10
Q

R AC BUS

amber

A

PROBABLE CAUSE
Right ac variable frequency bus not powered.

IMMEDIATE ACTION
None.

REMARKS
None.

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11
Q

DC BUS

amber

A

PROBABLE CAUSE
Dc bus fault detected.

IMMEDIATE ACTION
None.

REMARKS
Bus Bar protection unit inhibits buses from tying, then after 7 seconds delay isolates and shuts down the affected dc generator and removes affected battery from faulty main bus. All services on affected left or right main dc buses are affected.

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12
Q

L TRU

amber

A

PROBABLE CAUSE
Left TRU inoperative.

IMMEDIATE ACTION
Check L TRU circuit breaker on 115 V AC VARIABLE FREQUENCY circuit breaker panel.

REMARKS
Secondary dc buses tie in the event of a TRU failure. If DC bus caution light illuminates, no reset of the bus fault reset switch should be attempted.

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13
Q

R TRU

amber

A

PROBABLE CAUSE
Right TRU inoperative.

IMMEDIATE ACTION
Check R TRU circuit breaker on 115 V AC VARIABLE FREQUENCY circuit breaker panel.

REMARKS
If a double TRU failure occurs secondary dc buses tie to main dc buses.

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14
Q

MAIN BATTERY

amber

A

PROBABLE CAUSE
Main battery is isolated from main bus.

IMMEDIATE ACTION
Cycle MAIN BATT switch on DC CONTROL panel OFF then ON. If caution light remains ON, MAIN BATT - OFF.

REMARKS
Main battery is removed from main bus automatically if a right main bus fault occurs or if external dc power is connected.

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15
Q

AUX BATTERY

amber

A

PROBABLE CAUSE
Auxiliary battery is isolated from main bus.

IMMEDIATE ACTION
Cycle AUX BATT switch on the DC CONTROL panel OFF then ON. If caution light remains on, AUX BATT - OFF.

REMARKS
Auxiliary battery is removed from the main bus automatically if a left main bus fault occurs or if external dc power is connected.

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16
Q 
#1 DC GEN
amber
A

PROBABLE CAUSE
No. 1 dc generator off-line or failed.

IMMEDIATE ACTION
A generator reset attempt may be made by selecting DC CONTROL GEN 1 switch off then on.

REMARKS
Main dc buses automatically tie.

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17
Q 
#2 DC GEN
amber
A

PROBABLE CAUSE
No. 2 dc generator off-lined or failed.

IMMEDIATE ACTION
A generator reset attempt may be made by selecting DC CONTROL GEN 2 switch off then on.

REMARKS
Main DC buses automatically tie.

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18
Q 
#1 AC GEN
amber
A

PROBABLE CAUSE
No. 1 AC generator off-line or failed.

IMMEDIATE ACTION
A generator reset attempt may be made by selecting AC CONTROL GEN 1 switch off then on again.

REMARKS
Variable frequency buses automatically tie.

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19
Q

2 AC GEN

A

PROBABLE CAUSE
No. 2 AC generator off-line or failed.

IMMEDIATE ACTION
A generator reset attempt may be made by selecting AC CONTROL GEN 2 switch off then on.

REMARKS
Variable frequency buses automatically tie.

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20
Q

MAIN BAT HOT

red

A

PROBABLE CAUSE
Main battery temperature exceeds 65 degrees C.

IMMEDIATE ACTION
Confirm battery overheat on temperature monitor. Select MAIN BATT switch OFF to isolate main battery from charging system.

REMARKS
None.

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21
Q

AUX BAT HOT

red

A

PROBABLE CAUSE
Auxiliary battery temperature exceeds 65 degrees C.

IMMEDIATE ACTION
Confirm battery overheat on temperature monitor. Select AUX BATT switch to OFF to isolate auxiliary battery from charging system.

REMARKS
None.

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22
Q

L TRU HOT

amber

A

PROBABLE CAUSE
Left transformer/rectifier unit overheated.

IMMEDIATE ACTION
Left TRU must be shut down by pulling L TRU circuit breaker on 115 V AC VARIABLE FREQUENCY panel.

REMARKS
Left and right secondary buses automatically tie when left TRU is shut down. Left TRU may be re-energized when it has cooled and caution light goes out.

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23
Q

R TRU HOT

amber

A

PROBABLE CAUSE
Right transformer/rectifier unit overheated.

IMMEDIATE ACTION
Right TRU must be shut down by pulling R TRU circuit breaker on 115 V AC VARIABLE FREQUENCY panel.

REMARKS
Left and right secondary buses automatically tie when right TRU is shut down. Right TRU may be re-energized when cooled and caution light goes out.

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24
Q 
#1 DC HOT
amber
A

PROBABLE CAUSE
No. 1 dc generator windings overheating.

IMMEDIATE ACTION
Shut down No. 1 dc generator.

REMARKS
Caution light will go out when generator cools. Reselect generator and reduce dc electrical load.

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25
``` #2 DC HOT amber ```
PROBABLE CAUSE No. 2 dc generator windings overheating. IMMEDIATE ACTION Shut down No. 2 dc generator. REMARKS Caution light will go out when generator cools. Reselect generator and reduce dc electrical load.
26
``` #1 AC HOT amber ```
PROBABLE CAUSE No. 1 ac generator windings overheating. IMMEDIATE ACTION Shut down No. 1 ac generator. REMARKS Caution light will go out when generator cools. Reselect generator and reduce ac electrical load.
27
``` #2 AC HOT amber ```
PROBABLE CAUSE No. 2 ac generator windings overheating. IMMEDIATE ACTION Shut down No. 2 ac generator. REMARKS Caution light will go out when generator cools. Reselect generator and reduce ac electrical load.
28
PASS DOOR | red
PROBABLE CAUSE Passenger entry door not properly secured. IMMEDIATE ACTION Secure door if aircraft on ground. If in flight and depressurization is necessary see the QRH for inflight depressurization. REMARKS Warn all personnel to remain clear of door. PASS DOOR caution light goes out when door is closed securely.
29
BAG DOOR | red
PROBABLE CAUSE Baggage door not properly closed. IMMEDIATE ACTION Secure door if aircraft on ground. If in flight and depressurization is necessary see the QRH for inflight depressurization procedure. REMARKS Warn all personnel to remain clear of door. BAG DOOR caution light goes out when door is closed securely.
30
CHECK FIRE DET | red
PROBABLE CAUSE Engine fire detected or detector loop circuit malfunction. IMMEDIATE ACTION Check fire protection panel for illuminated PULL FUEL OFF handle and glareshield for flashing ENGINE FIRE light. If those indications are present proceed with the QRH engine fire procedure. REMARKS If fire warnings are not present and a FAULT light is illuminated select appropriate loop arming selector to remaining detector loop.
31
SMOKE | red
PROBABLE CAUSE Smoke present in baggage area. IMMEDIATE ACTION Have flight attendant investigate cause of smoke and proceed with the QRH inflight fire procedure. REMARKS SMOKE caution light remains illuminated as long as smoke is present in baggage compartment.
32
RUD PRESS | amber
PROBABLE CAUSE No. 1 or 2 rudder actuator pressure fails to decrease when aircraft exceeds 196 kts. (Mod 8/0503 140 kts) IMMEDIATE ACTION Reduce airspeed to 200 kts. or below. REMARKS None.
33
ROLL SPLR INBD GND | amber
PROBABLE CAUSE An inboard roll spoiler left dump valve failed. IMMEDIATE ACTION None. REMARKS If illumination occurs in flight, one of the inboard left dump valves has failed to open. Inboard roll spoilers will remain in flight mode and will deploy normally in ground mode at touchdown. If illumination occurs at touchdown one inboard left dump valve has failed to open to deploy spoiler in ground mode. Inboard roll spoilers will remain in flight mode.
34
ROLL SPLR OUTBD GND | amber
PROBABLE CAUSE An outboard roll spoiler lift dump valve has failed. IMMEDIATE ACTION None. REMARKS If illumination occurs in flight, one of the outboard lift dump valves has failed to open. Outboard roll spoilers will remain in flight mode and will deploy normally in ground mode at touchdown. If illumination occurs at touchdown one outboard lift dump valve has failed to open to deploy spoilers in ground mode. Outboard roll spoilers will remain in flight mode.
35
``` #1 RUD HYD amber ```
PROBABLE CAUSE No. 1 rudder actuator depressurized (pressure decreasing below 600 psi). IMMEDIATE ACTION None. REMARKS No. 2 rudder actuator operates at 3000 psi and RUD FULL PRESS caution light illuminates.
36
#2 RUD HYD
PROBABLE CAUSE No. 2 rudder actuator depressurized (pressure decreasing below 600 psi). IMMEDIATE ACTION None. REMARKS No. 1 rudder actuator operates at 3000 psi and RUD FULL PRESS caution light illuminates.
37
RUD FULL PRESS | amber
PROBABLE CAUSE Either the rudder actuator has depressurized causing 3000 psi to be applied to the remaining actuator. IMMEDIATE ACTION None. REMARKS RUD PRESS caution light of remaining actuator illuminates if aircraft speed exceeds 196 kts. (Mod 8/0503 140 Kt.)
38
GROUND SPLR | amber
PROBABLE CAUSE Ground spoiler lift dump valve failed. IMMEDIATE ACTION None. REMARKS If illumination occurs in flight or in TAXI modes on ground, one valve has failed open. Ground spoilers will operate normally. If illumination occurs at touchdown one valve has failed to open. Ground spoilers will not deploy.
39
FLAP DRIVE | amber
PROBABLE CAUSE Main flap drive failure. IMMEDIATE ACTION None. REMARKS Flaps will continue to operate using secondary transmission shaft. Flaps may be operated normally for remainder of flight.
40
FLAP POWER | amber
PROBABLE CAUSE Loss of hydraulic pressure in flap power unit during flap extension or retraction. IMMEDIATE ACTION Check No. 1 MAIN and STANDBY hydraulic pressure indicators and quantity indicators. REMARKS Unless hydraulic power to flap drive is restored, flaps are immobilized at existing position.
41
L STALL WARNING | amber
PROBABLE CAUSE Left lift transducer or lift computer failed or de-energized. IMMEDIATE ACTION Check stall warning switch at STALL WARNING. Check left dc circuit breaker panel STALL WRN & HTR (S7) and right dc circuit breakers STALL FAIL MIN 1, (R7). REMARKS None.
42
R STALL WARNING | amber
PROBABLE CAUSE Right lift transducer or left computer failed or de-energized. IMMEDIATE ACTION Check stall warning switch at STALL WARNING. Check right dc circuit breaker panel STALL WRN 7 HRT 2 (S7) and left dc circuit breaker STALL FAIL MIN 1 (R7). REMARKS None.
43
``` #1 ENG FUEL PRESS amber ```
PROBABLE CAUSE No. 1 engine boost ejector pump failed (output pressure below 5.5 psi). IMMEDIATE ACTION Select TANK 1 AUX PUMP on. REMARKS Caution light should go out as fuel boost pressure increases to 7.5 psi.
44
``` #2 ENG FUEL PRESS amber ```
PROBABLE CAUSE No. 2 engine boost ejector pump failed (output pressure below 5.5 psi). IMMEDIATE ACTION Select TANK 2 AUX PUMP on. REMARKS Caution light should go out as fuel boost pressure increases to 7.5 psi.
45
``` #1 TANK FUEL LOW amber ```
PROBABLE CAUSE No. 1 fuel tank quantity less than 130 lbs. IMMEDIATE ACTION Transfer fuel from other tank or land as soon as practical to refuel. REMARKS None.
46
``` #2 TANK FUEL LOW amber ```
PROBABLE CAUSE No. 2 fuel tank quantity less than 130 lbs. IMMEDIATE ACTION Transfer fuel from other tank or land as soon as practical to refuel. REMARKS None.
47
FUELING ON | amber
PROBABLE CAUSE REFUEL or DEFUEL selection made on the refuel/defuel control panel. IMMEDIATE ACTION If fueling not in progress check position of refuel/defuel switch in right nacelle. REMARKS Illumination of FUELING ON caution light does not activate the MASTER CAUTION light. Aircraft tank to tank fuel transferring can not be accomplished when refuel/defuel switch is selected to either REFUEL or DEFUEL.
48
``` #1 FUEL FLTR BYPASS amber ```
PROBABLE CAUSE Fuel filter restricted or blocked. IMMEDIATE ACTION None. REMARKS Fuel bypasses filter to supply engine. Report condition on landing.
49
``` #2 FUEL FLTR BYPASS amber ```
PROBABLE CAUSE Fuel filter restricted or blocked. IMMEDIATE ACTION None. REMARKS Fuel bypasses filter to supply engine. Report condition on landing.
50
``` #1 HYD FLUID HOT amber ```
PROBABLE CAUSE No. 1 hydraulic system fluid exceeds 109 degrees C. IMMEDIATE ACTION If condition exists on ground because of high ambient temperatures, operate flight controls actuated by the No. 2 hydraulic system (wing flaps, inboard roll spoilers, rudder, brakes) to circulate fluid. If condition exists in flight probable cause is failed pressure regulator; land as soon as practical for repairs. REMARKS Caution light goes out when fluid cools to 95 degrees C.
51
``` #2 HYD FLUID HOT amber ```
PROBABLE CAUSE No. 2 hydraulic system fluid exceeds 109 degrees C. IMMEDIATE ACTION If condition exists on ground because of high ambient temperatures, operate flight controls actuated by the No. 2 hydraulic system (parking brake, landing gear, nosewheel steering, rudder ground spoilers, outboard roll spoilers) to circulate fluid. If condition exists in flight probable cause is failed pressure regulator; land as soon as practical for repairs. REMARKS Caution light goes out when fluid cools to 95 degrees C.
52
``` #1 STBY HYD PUMP HOT amber ```
PROBABLE CAUSE No. 1 standby hydraulic pump electric motor temperature motor temperature exceeds 170 degrees C. IMMEDIATE ACTION If condition occurs when main hydraulic system is inoperative, select No. 1 standby hydraulic pump to NORM if flight condition permit loss of No. 1 hydraulic services. Avoid selection of wing flaps. If condition occurs with main system operative and wing flaps extended, raise wing flaps as soon as possible and select STBY HYD PRESS switch to NORM. REMARKS When pump motor cools to 160 degrees C caution light will go out and pump may be selected on if needed.
53
``` #2 STBY HYD PUMP HOT amber ```
PROBABLE CAUSE No. 2 standby hydraulic pump electric motor temperature motor temperature exceeds 170 degrees C. IMMEDIATE ACTION If condition occurs when main hydraulic system in inoperative, select No. 2 standby hydraulic pump to NORM if flight condition permit loss of No. 2 hydraulic services. Avoid selection of wing flaps. If condition occurs with main system operative and wing flaps extended, raise wing flaps as soon as possible and select STBY HYD PRESS switch to NORM. REMARKS When pump motor cools to 160 degrees C caution light goes out and pump may be selected on if needed.
54
``` #1 ENG HYD PUMP amber ```
PROBABLE CAUSE No. 1 engine driven hydraulic pump failed (pressure below 2000 psi). IMMEDIATE ACTION Select STBY HYD PRESS 1 switch to on. REMARKS Caution light will remain on and standby hydraulic pump pressure will be displayed on No. 1 STANDBY and MAIN hydraulic pressure indicators.
55
``` #2 ENG HYD PUMP amber ```
PROBABLE CAUSE No. 2 engine driven hydraulic pump failed (pressure below 2000 psi). IMMEDIATE ACTION Select STBY HYD PRESS switch to ON. REMARKS Caution light will remain on and standby hydraulic pump pressure will be displayed on the No. 2 STANDBY and MAIN hydraulic pressure indicators.
56
PITOT HEAT 1 | amber
PROBABLE CAUSE No. 1 pitot heater selected OFF with dc electrical system energized. IMMEDIATE ACTION Select PITOT STATIC 1 switch on. REMARKS None.
57
PITOT HEAT 2 | amber
PROBABLE CAUSE No. 2 pitot heater selected OFF with dc electrical system energized. IMMEDIATE ACTION Select PITOT STATIC 2 switch on. REMARKS None.
58
L OR R ELV HORN HEATER | amber
PROBABLE CAUSE Elevator horn heater failure. Light will flash momentarily on when heaters are first selected. IMMEDIATE ACTION Check ELEV HORN HT 1 (N7) circuit breaker on left dc circuit breaker panel and ELEV HORN HT 1 and ELEV HORN HT 2 circuit breaker on 115 v AC VARIABLE FREQUENCY circuit breaker panel. REMARKS None.
59
L WSHLD HOT | amber
PROBABLE CAUSE Left windshield overheated. Normal temperature sensor or normal temperature control circuits in right window controller inoperative. IMMEDIATE ACTION Operate windshield heat at WARM-UP. caution light should go out as windshield cools. REMARKS If necessary, windshield heat may be selected to NORMAL for short intervals to maintain clear vision. OR L W/SHLD HT circuit breaker could be pulled to deenergize left windshield and allow normal operation of right windshield and pilot’s side window by selecting windshield heat to NORMAL and selection of PLT WDO/HT switch to ON.
60
R WSHLD HOT | amber
PROBABLE CAUSE Right windshield overheated. Normal temperature sensor or normal temperature control circuits in right window controller inoperative. IMMEDIATE ACTION Operate windshield heat at WARM-UP. Caution light should go out as windshield cools. REMARKS If necessary, windshield heat may be selected to NORMAL for short intervals to maintain clear vision. OR R W/SHLD HT circuit breaker could be pulled to deenergize right windshield and allow normal operation of left windshield and pilot’s side window by selecting windshield heat to NORMAL and selection of PLT WDO/HT switch to ON.
61
SIDE WDO HOT | amber
PROBABLE CAUSE Pilot’s side window overheated. Temperature sensor or temperature control circuits in side window controller inoperative. IMMEDIATE ACTION Select PLT WDO/HT switch to OFF. Caution light should go out as window cools. REMARKS Select PLT WDO/HT switch to ON. if SIDE WDO HOT caution light goes out.
62
DEICE PRESS | amber
PROBABLE CAUSE Airframe deice system pressure insufficient for deicer boot operation (fallen below 5.5 psi). IMMEDIATE ACTION Airframe auto selector - OFF. Select BOOT air switch to ISO. Manually select inner and outer tailplane boots and engine intake boot on operative side. REMARKS Exit icing conditions if possible.
63
NOSE STEERING | amber
PROBABLE CAUSE Nosewheel steering ECU malfunction. IMMEDIATE ACTION Center steering handle and nosewheel. Select nosewheel STEERING to OFF. REMARKS None.
64
PARKING BRAKE | amber
PROBABLE CAUSE Emergency/parking brake is on. IMMEDIATE ACTION None. REMARKS Caution light goes out when EMERG BRAKE lever is released.
65
OUTBD or INBD ANTI-SKID | amber
PROBABLE CAUSE Outboard or inboard anti-skid control unit failed. IMMEDIATE ACTION Check anti-skid switch - ON. Check right dc circuit breaker panel ANTISKID INBD (Q6) and OUTBOARD (R6) circuit breakers. REMARKS Anti-skid control will be reduced by 50%. Also illuminates during anti-skid test.
66
LDG GEAR INOP | amber
PROBABLE CAUSE Landing gear door sequence valve relay failed with aircraft airborne and gear up. IMMEDIATE ACTION DO NOT attempt to lower gear by normal selection. Use landing gear alternate procedure in Flight Manual to extend gear. REMARKS Landing gear door of the corresponding failed relay will not open before gear extends if normal extension is selected, resulting in structural damage.
67
WT ON WHEELS | amber
PROBABLE CAUSE Fault in a weight on wheels sensing circuit within PSEU. IMMEDIATE ACTION Flight may be completed, but rectification must be carried out before the next flight, even though the caution light goes out on touch down. REMARKS Landing gear may not retract. Systems dependent on weight on wheels sensing circuits will remain operational because of redundancy of the weight on wheels sensors.
68
EMER LTS DISPLAY | amber
PROBABLE CAUSE Emergency lights not armed with dc electrical system energized. IMMEDIATE ACTION Select pilot’s EMER LIGHTS switch to ARM. REMARKS None.
69
``` #1 BLEED HOT amber ```
PROBABLE CAUSE No. 1 Bleed air supply duct exceeds 287 degrees C. IMMEDIATE ACTION If light repeatedly illuminates and goes out, select No. 1 BLEED switch off or reduce BLEED flow control setting as much as inflow requirements allow. REMARKS Normal operation is automatically interrupted and bleed air is shut off until supply duct cools. Caution light goes out and normal operation resumes when supply duct cools.
70
``` #2 BLEED HOT amber ```
PROBABLE CAUSE No. 2 Bleed air supply duct temperature exceeds 287 degrees C. IMMEDIATE ACTION If light repeatedly illuminates and goes out, select No. 2 BLEED switch off or reduce BLEED flow control setting as much as inflow requirements allow. REMARKS Normal operation is automatically interrupted and bleed air is shut off until supply duct cools. Caution light goes out and normal operation resumes, when supply duct cools.
71
``` #1 ENG OIL PRESS red ```
PROBABLE CAUSE No. 1 Engine oil pressure below 42 +/- 3 psi. IMMEDIATE ACTION Check oil pressure indicator. If low oil pressure is confirmed shut engine down. REMARKS None.
72
``` #2 ENG OIL PRESS red ```
PROBABLE CAUSE No. 2 Engine oil pressure below 42 +/- 3 psi. IMMEDIATE ACTION Check oil pressure indicator. If low oil pressure is confirmed, shut engine down. REMARKS None.
73
``` #1 ENG MANUAL amber ```
PROBABLE CAUSE No. 1 Engine electronic control unit failed or deactivated by MANUAL selection on ENG 1 ECU MODE switchlight. IMMEDIATE ACTION Select ENG 1 ECU MODE selector ON. Check left dc circuit breaker panel ECU ENG 1 circuit breaker (K4) and right DC circuit breaker panel ECU ENG 1 circuit breaker (J7). REMARKS If ECU fault is not cleared power lever advancement will be required to keep engine torque symmetric.
74
``` #2 ENG MANUAL amber ```
PROBABLE CAUSE No. 2 Engine electronic control unit failed or deactivated by MANUAL selection on ENG 2 ECU MODE switchlight. IMMEDIATE ACTION Select ENG 2 ECU MODE selector ON. Check right dc circuit breaker panel ECU ENG 2 circuit breaker (H3) and left dc circuit breaker panel ECU ENG 2 circuit breaker (M8). REMARKS If ECU fault is not cleared power lever advancement will be required to keep engine torque symmetric.
75
FLT DATA RECORDER | amber
PROBABLE CAUSE Flight data recorder failed or deenergized. IMMEDIATE ACTION Check the avionics circuit breaker panel FDR (A9) circuit breaker and left dc circuit breaker panel FDAU and FDR STAT circuit breakers (G2, H2). Check anti-collision lights switch selected to RED or WHITE if aircraft on ground. REMARKS Flight data recorder is energized when aircraft is airborne or when on ground with anti-collision lights on.
76
GPWS | amber
PROBABLE CAUSE Ground proximity warning system computer failure or deenergized. IMMEDIATE ACTION Check avionics circuit breaker panel GPWS (B9 and B3) circuit breakers. REMARKS None.

Dash 8 Training (7 decks)

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