Lights Flashcards
GEN 2 or GEN 3, GEN 4 or APU GEN OFF light on
Probable Cause:
Generator failure, off frequency, overvoltage, undervoltage, feeder fault, supervisory panel failure, transfer relay 2 or 3 failure, or associated bus monitoring switch OFF.
Note: if the APU generator control circuit breaker is out, the APU GEN OFF light will be on. Automatic APU load monitoring above 8,000 feet will be disabled; however, the generator will assume the load.
Action:
Use reset procedure, or place associated BUS MONITORING switch ON. If engine-driven generator light remains on steady throughout reset procedures, or goes out momentarily and comes back on, mission should be aborted.
Caution:
Generator supervisory panels shall not be exchanged until appropriate maintenance actions are performed.
Note: Ensure GEN 4 AUX CONT and GEN 4 TRANS circuit breakers are set appropriately.
TRANSFORMER RECTIFIER OVERHEAT light on
Probable Cause: Transformer Rectifier (TR) overheated
Action: Pull respective circuit breaker; No. 3 located at the flight station and Nos. 1 and 2 located at the main load center.
EXTERNAL PWR AVAILABLE
Probable Cause:
Indicates electrical power is connected to the aircraft
Action:
Light will glow whether or not external power is selected.
EXTERNAL PWR AVAILABLE light on (neon), but no power into aircraft
Probable Cause:
Wrong phase, nosegear uplock not properly positioned, battery not connected, generator No. 4 runaround feeder circuit breaker out, external power control circuit breaker out.
Action:
Move EXTERNAL POWER switch to RESET then ON. Check nosegear uplock position. Check battery condition. Check No. 4 runaround feeder circuit breaker. Check external power control circuit breaker.
B. U. P. E. R.
EXTERNAL PWR AVAILABLE light on partial power into aircraft
Probable Cause:
Tranformer-rectifier No. 3 ganged circuit breaker out. ESSENTIAL DC BUS FEEDER circuit breaker No. 2 out. Monitorable Essential AC ganged circuit breaker behind copilot out. Monitorable Essential BUS switch off.
Action:
Check TR 3 circuit breaker. Check ESSENTIAL DC BUS FEEDER circuit breaker No. 2. Check Monitorable Essential AC ganged circuit breaker in. Check Monitorable Essential BUS switch.
32 MM
EXTERNAL POWER light on
Probable Cause:
External power supplying power to aircraft system
Action:
EXTERNAL POWER switch is ON
PRIMARY FUEL PUMP (parallel) light
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light on during start (between 16 percent and 65 percent rpm)
Probable Cause:
Indicates the secondary fuel pump is functioning properly
Action:
PRIMARY FUEL PUMP (parallel) light
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light off during start (between 16 percent and 65 percent rpm)
Probable Cause:
Failure of secondary fuel pump.
Action:
Investigate
PRIMARY FUEL PUMP (parallel) light
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP light on, or momentarily on then off, above 65 percent rpm.
Probable Cause:
a. Failure of the primary pump
b. Fuel pumps are in parallel operations possibly due to a speed sense control malfunction
Action:
Pull FUEL SHUTOFF VALVE circuit breaker on START ESSENTIAL DC BUS.
a. If light remains on, reset the circuit breaker, and assume the primary pump has failed.
b. If the light goes out, leave the circuit breaker out, and assume a failure of either the 65 percent switch or the speed sense control. If mission is continued, refer to Speed Sense Control Malfunction, Paragraph 15.4
No. 1, 2, 3, and 4 AUTO FEATHER lights are all on
Probable Cause:
The automatic feathering circuit has been armed.
Action:
No. 1, 2, 3, or 4 AUTO FEATHER light on individually.
Probable Cause:
Propeller thrust has dropped to less than 500 pounds of positive thrust; propeller has automatically feathered.
Action:
Investigate
No. 1, 2, 3, or 4 engine STARTER CONTROL VALVE OPEN light on
Probable Cause:
Engine starter control valve is open. (Valve should close and light go out when starter button is pulled out at 57 to 64 percent rpm during normal start.)
Action:
*If light remains on or comes on after start, secure engine by pulling emergency shutdown handle.
No. 1, 2, 3, or 4 prop feather button light remains on
Probable Cause:
Indicates feather pump relay is closed, supplying electrical power to the feather pump.
Possible internal leakage. Incomplete pump cut-out circuit.
Action:
a. If light remains on following engine shutdown, pull respective propeller feather control circuit breaker, and execute the Emergency Shutdown procedure.
b. If light remains on following pressure cutout override, refer to In-Flight Restart Procedures
FAN OUT light on
Probable Cause:
Cabin Exhaust fan is inoperative or lack of airflow
Action:
Open equipment doors for additional cooling. Use minimum electronic equipment. If EDCs are inoperative (no air-conditioning available), open AUX vent.
EDC TEMP HIGH light on.
Probable Cause:
EDC oil temperature excessive. Low oil level in sump. High engine oil temperature.
Note: Low intensity illumination of the EDC TEMP HIGH light is acceptable unless accompanied by a master PRESS SYS light.
Action:
a. Check engine oil temperature; if high, correct.
b. If unable to control, disconnect, monitor for loss of spread, dump, continue operation.
The DISCONNECT position shall be selected only when the engine is operating in the normal RPM range.
Caution: Disconnecting the EDC outside of normal engine RPM range will damage the compressor.
c. If spread is indicated after disconnect, execute the Emergency Shutdown procedure. If the engine is allowed to operate due to a greater emergency, the EDC should be dumped.
d. Refer to Air-Conditioning system Malfunction
EDC PRESS LOW light on
Probable Cause:
EDC oil pressure is low. Low level in sump. EDC drive shaft sheared.
Action:
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.
The DISCONNECT position shall be selected only when the engine is operating in the normal RPM range.
Caution: Disconnecting the EDC outside of normal engine RPM range will damage the compressor.
c. If spread is indicated after disconnect, execute the Emergency Shutdown procedure. 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 is selected and ground air conditioning on prior to disconnect.
d. Refer to Air-Conditioning system Malfunction
REFR OVHT (overheat) light on
Probable Cause:
Temperature in cooling duct exceeds safe limits. On ground: inoperative heat exchanger blower fan.
Action:
In flight, dump EDC. After light is out, operation is permitted in the manual mode at the two-dot position or warmer.
On deck, turn off GRD AIR COND switch; investigate by checking the HEAT EXCHANGER cbs on BUS B and BLOWER CONT cb on MEDC. If cbs are set and the light is out, operation is permitted in the manual mode two-dot position or warmer.
L WING HOT or R WING HOT light on
Probable Cause:
Air temperature in the wing plenum exceeds safe limits. May be caused by a leak in the bleed air manifold or EDC plumbing.
Action:
a. Secure wing deicing and get out of icing area.
b. If light remains on, dump appropriate EDC
LEAK TEST ACCEPT light
Probable Cause:
Action:
Maintenance function. Refer to appropriate maintenance manuals.
No. 1, 2, 3, and 4 engine bleed air valve open lights on.
Probable Cause:
When the valve begins to open, the light will be on. When the valve is closed, the light should be off.
Action:
Left and right FUS BLEED SHUT-OFF valve OPEN lights on.
Probable Cause:
When the valve begins to open, the light is on. When the valve is closed, the light should be off.
Action:
LE HOT light on
Probable Cause:
The wing leading edge skin temperature has increase in excess of 110C. One of the six modulating valves is either stuck open or improperly modulating.
Action:
Close all bleed air valves. Locate defective area with temperature selector. Open all modulating valves. When necessary, deice the entire wing using the bleed air valves.
EMP DE-ICE light on
Probable Cause:
Parting strip power relay deenergized, cycling power relay deenergized, control relay deenergized, timer motor failure, empennage overheat condition. Open control power circuit breaker.
Action:
Turn switch OFF then ON. If light remains on, turn switch OFF, increase airspeed above 200 KIAS; vacate icing area. If light does not come back on, a temporary overhead condition exists. Continue operation.
ANTI-ICING light
No. 1, 2, 3, or 4 engine ANTI-ICING advisory light on with control switch on.
Probable Cause:
Fourteenth stage air of sufficient temperature to melt ice has entered the torquemeter shroud and the inlet scoop.
Action:
ANTI-ICING light
No ANTI-ICING advisory light with control switch on.
Probable Cause:
One of both areas of system may not be receiving hot air.
Action:
a. Check for horsepower drop. If normal, continue operation.
b. If less than normal:
Check for ice buildup on air inlet scoop. If excessive, execute the Emergency Shutdown procedure.
If no ice buildup 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 of these indications is observed, execute the Emergency Shutdown procedure.
ANTI-ICING light
ANTI-ICING advisory light on and control switch off
Probable Cause:
a. Abnormal heat in the area
b. Loss of electrical power to the solenoid valve.
Action:
On deck, investigate, secure engine, and return to the line.
In flight, turn on anti-ice control switch.
a. If a shp drop is observed, execute the Emergency Shutdown procedure.
b. If no shp drop is observed, continue engine operation.