Lights Flashcards
Gen 2 or Gen 3, Gen 4 or APU GEN OFF light on cause
Switch: associated bus mon switch is off G: gen failure O: off freq, over/under voltage F: feeder fault T: Tranfer relay 2 or 3 fail Sup: sup panel
NOTE: if the APU gen control cb out, APU GEN OFF light will be on. Automatic APU load monitoring above 8k’ will be disabled; however, the generator will assume the load
Gen 2 or Gen 3, Gen 4 or APU GEN OFF light on action
Use reset procedure, or place associated BUS MON switch ON
If an 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 approrpriste maintenance actions are performed
NOTE: ensure GEN 4 AUX CONT and GEN 4 TRANS cb’s are set
TR overheat light cause and Action
TR overheat about 200 degrees: pull cb
TR1: FLC
TR2 & 3: MLC
EXTERNAL POWER AVAILABLE light on (neon) but NO power into aircraft
Cause and Action
P: wrong phase
U: nose gear up lock improperly positioned
B: battery disconnected
CB’s: gen 4 run around cb or ext pwr cntrl cb
Cycle EXT PWR switch and check all these items
EXTERNAL POWER AVAILABLE light on PARTIAL power into aircraft
Cause and Action
Switch: MON ESS BUS switch off
2 Gangs: TR 3 & MON ESS BUS AC ganged (behind cp) cb’s out
CB: ESS DC BUS FEEDER cb no. 2 out
Switch
Action: check all those things
EXTERNAL POWER light on cause and action
External power supplying power to aircraft system
External power switch is on
PRIMARY FUEL PUMP (parallel) light of no. 1,2,3, or 4 on during start (between 16% and 65%rpm) cause
Secondary fuel pump is functioning properly
PRIMARY FUEL PUMP (parallel) light for no. 1,2,3, or 4 off during start (between 16% and 65%rpm) cause and action
Failure of secondary pump: Investigate
PRIMARY FUEL PUMP (parallel) light for no. 1,2,3, or 4 on or momentarily on then off above 65%rpm cause
1: Failure of the primary pump
2: fuel pumps are in parallel operation possibly due to a speed sense control malfunction
PRIMARY FUEL PUMP (parallel) light for no. 1,2,3, or 4 on or momentarily on then off above 65%rpm action
Pull FUEL SHUTOFF VALVE cb on START ESSENTIAL BUS
a. light remains on, reset the cb and assume the primary pump failed
b. if goes out, leave cb out and assume failure of either 65% switch or speed sense control. If mission continued, refer to Speed Sense Control Malfunction paragraph 15.4
No. 1,2,3 and 4 AUTO FEATHER lights on individually cause and Action
Prop thrust has dropped less than 500lbs of positive thrust, prop has auto feathered: Investigate
No. 1,2,3 and 4 engine STARTER CONTROL VALVE OPEN light on cause and action
Engine starter control valve is open. (Valve should close and light go out when starter button is pulled out and 57-64%rpm during normal start): If light remains on or comes on after start, secure engine by pulling E handle
No. 1, 2, 3 or 4 prop feather button light remains on Cause
1: feather pump relay is closed, supplying electrical power to the feather pump.
2: Possible internal leakage.
3: Incomplete pump cut out circuit
No. 1, 2, 3 or 4 prop feather button light remains on action
If light remains on following engine shutdown: pull respective propeller feather control circuit breaker and execute the emergency shut down procedure paragraph 15.5.1.
If light remains on following pressure cut out override refer to invite restart procedures paragraph 8.3 3.1
FAN OUT light on cause and action
1: Cabin exhaust fan is inoperative o
2: lack of airflow
1: Open equipment doors for additional cooling. 2: Use minimum electronic equipment.
3: If EDC’s are inoperative (no air conditioning available) open AUX event.
EDC TEMP HIGH light on cause
1: EDC or engine oil temperature high
2: Low oil level in sump.
Note: Low intensity illumination of the EDC TEMP HIGH light is acceptable unless accompanied by a master PRESS SYS light
EDC TEMP HIGH light on 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 normal RPM range
c. If spread as indicated after disconnect execute the emergency shut down procedure. if engine is allowed to operate due to a greater emergency the EDC should be dumped
d. Referred to air conditioning system malfunction in fight paragraph 15.16
Caution: Disconnecting the outside of normal engine RPM range will damage the compressor
EDC PRESS LOW light on Cause
1: EDC Oil pressure is low
2: Low level and sump
3: EDC drive shaft shared.
(If edc press pow indications but no light, could be quill shaft fail)
EDC PRESS LOW light on Action
a. With lots of spread disconnect and dump EDC. Continue operation.
b. If spread is indicated disconnect, monitor for loss of spread, dump. Continue operation
c. If spread is indicated after disconnect, execute the emergency shut down procedure. If 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 inground air conditioning on prior to disconnect
d. If APU is operational, select APU air override to ensure a loss of spread on the affected EDC.
e. Referred to air conditioning system malfunction in flight
REFR OVHT (overheat) Light on cause
Temperature in cooling duct exceeds safe limits.
On ground: in operative heat exchanger blower fan.
REFR OVHT (overheat) Light on action
In-flight: dump EDC. After light is out, operation is permitted in the manual mode at the 2 dot position or warmer.
On deck: turn off GRD AIR COND switch: Investigate by checking the heat exchanger circuit breakers on BUS B and blower control circuit breaker on MEDC, If circuit breakers are set in the light is out, operation is permitted in the manual mode 2 dot condition or warmer
L WING HOT and R WING HOT light on cause and action
Air temperature in the wing Plenum area exceed safe limits. Maybe caused by a leak in the bleed air manifold or EDC plumbing
1: Secure wing deicing and get out of icing area.
2: if light remains on, dump appropriate EDC
No. 1,2,3 or 4 engine bleed air valve / left and right FUS BLEED AIR SHUT OFF valve OPEN lights on cause
When the valve begins to open, the light will be on. When the valve is closed, the light should be off
LE HOT light on cause
The wing leading edge skin temperature has increased in excess of 110°C. One of the six modulating valves is either stuck or open or improperly modulating
LE HOT light on action
1: Close all bleed air valves.
2: Locate defective area with temperature selector.
3: Open all modulating valves.
4: When necessary, deice the entire wing using the bleed air valves
EMP DE-ICE light on cause
Empennage overhead condition
Open control power circuit breaker
P: parting / cycling strip power relay deenergized
3: timer motor failure
C: control relay denergized
EMP DE-ICE light on action
1: cycle switch
2: If light remains on: turn switch off, increase Airspeed above 200 kts; vacate icing are.
3: If light does not come back on, a temporary overheat existing. Continue ops.
ANTI-ICING light No. 1,2,3 or 4 engine ANTI-ICING advisory light ON with control switch ON cause
14th stage air of sufficient temperature to melt ice has entered the torquemeter shroud and the inlet scoop