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Natops > Lights > Flashcards

Lights Flashcards

1
Q

Gen 2 or Gen 3, Gen 4 or Apu Gen off light on.

Probable Cause

A

Generator failure, off frequency, overvoltage, undervoltage, feeder fault, supervisory panel failure, or associated bus monitoring switch off.
NOTE
if the APU gen control CB is out the apu gen off light will be on. Automatic load monitoring above 8000’ will be disabled however the genterator will assume the load.

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2
Q

Transformer rectifier overheat.

Probable Cause

A

Transformer rectifier (TR) overheated.

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3
Q

External power light on (neon)

Probable Cause

A

Indicates electrical power is connected to the A/C

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4
Q

Gen 2 or Gen 3, Gen 4 or Apu Gen off light on.

Corrective Action

A

Use reset procedures or place associated bus monitoring switch on. if an eng driven gen light remains on throughout reset procedures, or goes out momentarily mission should be aborted.
CAUTION
Generator supervisory panels shall not be exchanged until appropriate maintenance actions have been performed.
NOTE
Ensure Gen 4 aux and Gen 4 trans Cb’s are set appropriately.

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5
Q

Transformer rectifier overheat.

Corrective Action

A

Corrective action: Pull respective cb; No. 3 located at the flight station, Nos. 1,2,4 and 5 located at the main load center.

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6
Q

External power light on (neon)

Corrective Action

A

Light will glow whether or not external power is selected

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7
Q

External Power Avail. light on: But no Power Into A/C

Probable Cause

A

Wrong Phase, nose gear uplock not properly positioned, battery not connected, Gen No. 4 RAR feeder cb out, external power control cb out.

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8
Q

External Power Avail. light on: But no Power Into A/C

Corrective Action

A

Move external power switch to reset then on, check nose gear uplock position, check battery condition, check No. 4 RAR feeder cb, check external power control cb.

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9
Q

External Power Avail. light on: Partial power into aircraft

Probable Cause

A

TR 3 ganged cb out. Ess. DC bus feeder cb No.2 out, MEAC ganged cb behind CoPilot out, mon ess. bus switch off.

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10
Q

External Power Avail. light on: Partial power into aircraft

Corrective Action

A

Check TR 3 cb, check ess dc bus feeder cb no.2, check meac ganged cb in. check mon ess bus switch

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11
Q

External Power Light on

Probable Cause

A

External power supplying power to A/C system

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12
Q

External Power Light on

Corrective action

A

External Power switch is on

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13
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light on during start (between 16 and 65 percent rpm)
Probable cause

A

indicates the secondary fuel pump is functioning properly.

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14
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light on during start (between 16 and 65 percent rpm)
corrective action

A

N/A

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15
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light off during start (between 16 and 65 percent rpm)
Probable cause

A

Failure of the secondary pump.

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16
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light on during start (between 16 and 65 percent rpm)
Corrective action

A

Investigate

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17
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light on, or momentarily on then off above 65 percent rpm
probable cause

A

a. Failure of the primary pump

b. Fuel pumps are in parallel operation possibly due to a speed sense control malfunction.

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18
Q

PRIMARY FUEL PUMP FAILURE LIGHT:
No. 1,2,3 or 4 Primary Fuel pump (parallel) light on, or momentarily on then off above 65 percent rpm
Corrective action

A

Pull fuel SOV cb on sedc

a. If the light remains on, reset the cb, and assume the primary pump has failed
b. If the light goes out leave the CB out and assume a failure of either the 65% switch or the speed sense control.

NOTE:

  • Do not use Autofx
  • Should maximum Tit be limited to approximately 830*c with or without the paralleling light assume a failure of either the 94% switch or the speed sense control Place the affected TD to null and pull the fuel SOV cb on the SEDC bus
  • Do not shutdown the affected eng with the intent to restart.
  • Reset the CB prior to securing the engine with the F/I switch.
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19
Q

No 1,2,3, and 4 autofx lights are all on

probable cause

A

The automatic feathering circuit has been armed.

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20
Q

No 1,2,3, and 4 autofx lights are all on

Corrective action

A

N/A

21
Q

No 1,2,3, and 4 autofx lights are all on Individually.

Probable cause

A

Propeller thrust has dropped to less than 500 lbs of positive thrust; propeller has automatically feathered.

22
Q

No 1,2,3, and 4 autofx lights are all on Individually.

Corrective action

A

investigate

23
Q

No. 1,2,3 or 4 engine start control valve open light on

Probable Cause

A

Engine starter control valve is open. (Valve should close and light go out when the start button is pulled out at 57 to 64 percent rpm during normal start)

24
Q

No. 1,2,3 or 4 engine start control valve open light on

Corrective action

A

*if light remains on or comes on after start, secure engine by pulling emergency shutdown handle.

25
Q

N0. 1,2,3, or 4 prop feather button light remains on

Probable cause

A

indicates feather pump relay is closed, supplying electrical power to the feather pump.
Possible internal leakage. incomplete pump cutout circuit.

26
Q

N0. 1,2,3, or 4 prop feather button light remains on

Corrective action

A

a. If light remains on following engine shutdown, pull respective propeller feather control circuit breaker and execute Emergency Shutdown procedure paragraph 15.5.1
b. If light remains on following pressure cutout override, refer to in-flight restart procedures paragraph 8.33.1

27
Q

Fan out light on.

Probable cause

A

Cabin exhaust fan is inoperative or lack of airflow.

28
Q

Fan out light on

Corrective Action

A

Open equipment doors for additional cooling. use minimum electronic equipment. If EDC’s are inoperative (no A/C available). open aux vent.

29
Q

EDC temp high light on

Probable cause

A

EDC oil temperature excessive. Low oil level in sump high engine oil temperature

30
Q

EDC temp high light on

Corrective action

A

a. Check engine oil temperature; if high correct
b. if unable to control, disconnect, monitor for loss of spread, dump continue operation.

CAUTION:
The Disconnect position should be selected only when the engine is operation in the Normal RPM range to prevent EDC damage.

c. If spread is indicated after disconnect execute the emergency shutdown procedure paragraph 15.5.1. If the engine is allowed to operate due to a greater emergency, the edc should be dumped
d. Refer to A/C system malfunction paragraph 15.16

31
Q

EDC press low light on

probable cause

A

EDC oil pressure is low. low level in sump. EDC drive shaft sheared.

32
Q

EDC press low light on.

Corrective action

A

a. With loss of spread disconnect and dump edc. continue operation.
b. if spread is indicated, disconnect, monitor for loss of spread, dump. continue operation.

CAUTION:
The Disconnect position should be selected only when the engine is operation in the Normal RPM range to prevent EDC damage.

c. If spread is indicated after disconnect execute the emergency shutdown procedure paragraph 15.5.1. If the engine is allowed to operate due to a greater emergency, the edc should be dumped

NOTE:
if on ground and mission is continued; ensure normal rpm selected and ground air conditioning on prior to disconnect

d. Refer to A/C system malfunction paragraph 15.16

33
Q

Refer overheat light on.

Probable cause

A

Temperature in cooling duct exceeds safe limits. On ground: inoperative heat exchanger blower fan.

34
Q

Refer overheat light on.

Corrective action

A

In flight dump EDC. After light is out, operation is permitted in the manual mode two dot position or warmer.
On deck, turn off ground air conditioning switch; investigate by checking the heat exchanger cbs on bus b and blower control cb on MEDC. If the circuit breakers are set and the light is out operation is permitted in the manual mode two dot position or warmer.

35
Q

L or R wing hot light on.

Probable cause

A

Air temperature in the wing plenum area exceeds safe limits. May be caused by a leak in the bleed air manifold or EDC plumbing.

36
Q

L or R wing hot light on.

Corrective action

A

a. Secure wing deicing and get out of icing area.

b. if light remains on, dump appropriate edc

37
Q

Leak test accept light

probable cause

A

N/A

38
Q

leak test accept light

corrective action

A

Maintenance function, refer to appropriate maintenance manuals

39
Q

No. 1,2,3 or 4 engine bleed air valve OPEN lights on.

Probable cause

A

When the valve begins to open, the light will be on. when the valve is closed the light should go off.

40
Q

No. 1,2,3 or 4 engine bleed air valve OPEN lights on.

Corrective action

A

N/A

41
Q

Left and RIght Fus Bleed Air shut-off valve open lights on.

Probable cause

A

When the valve begins to open, the light is on. when the valve is closed the light should go off.

42
Q

LE Hot light on

Probable Cause

A

The wing leading edge skin temperature has increased in excess of 110*c. One of the six modulating valves is either stuck open or improperly modulating.

43
Q

LE Hot light on

Corrective action

A

Close all bleed air valves. Locate defective area with temperature selector. Open all modulating valves. When necessary deice entire wing using Bleed Air Vlaves

44
Q

EMP Deice light on

Probable cause

A

Parting strip power relay deenergized, cycling power relay deenergized, control relay deenergized, timer motor failure, empennage overheat condition. Open control power circuit breaker.

45
Q

EMP Deice light on

corrective action

A

Turn switch On then off. if light remains on turn switch off. Increase airspeed above 200 KIAS vacate icing area. if light does not come back on a temporary overheat condition exists. continue operation.

46
Q

Anti icing light on
No. 1,2,3 or 4 engine anti icing advisory light on with control switch on
probable cause

A

Fourteenth stage air of sufficient temperature to melt ice has entered the touquemeter shroud and the inlet scoop.

47
Q

Anti icing light on
No. 1,2,3 or 4 engine anti icing advisory light on with control switch on
Corrective action

A

N/A

48
Q

Anti icing light on
No Anti Icing advisory light with control switch on.
Probable Cause

A

One or both areas of system may not be receiving hot air

49
Q

Anti icing light on
No Anti Icing advisory light with control switch on.
Corrective action

A

a. Check for horsepower drop, if normal continue operation
b. if less than normal
(1) Check for ice buildup on air inlet scoop. if excessive execute emergency shutdown procedure paragraph 15.5.1
(2) If no ice build up on air inlet scoop is observed, monitor SHP, TIT and Fuel Flow. Initial indications may be a gradual power loss followed by erratic operations. if either or both of these indications is observed. execute emergency shutdown procedure paragraph 15.5.1.

Natops (1 decks)

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