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
ANTI-ICING light NO ANTI-ICING advisory light with control switch ON cause and action
One or both areas of system may not be receiving hot air
(1) Check for horsepower drop. If normal, continue operation. If less than normal: check for ice buildup on air inlet the scoop. If excessive, execute the emergency shut down procedure
(2) If no ice build up on air inletscoop is observed, monitor horsepower, TIT, and fuel flow. Initial indications may be a gradual power loss followed by erratic operations. If either of these indications observed, execute the emergency shut down procedure
ANTI-ICING advisory light ON and control switch OFF cause and action
Abnormal heat in the area
a. Loss of electrical power to the solenoid valve
b. Failure of one or both thermal Switches
On deck: investigate, secure engine, and return to the line
In-flight: turn on anti-ice control switch.
Loss of electrical power to solenoid valve: If a shaft horsepower drop is observed, execute the emergency shut down procedure
failure of 1 or both of thermal switches: If no Shaft horsepower drop is observed, continue and an operation
ANTI-ICING advisory Light remains on after system utilization cause and action
Failure of one or both thermal Switches and or anti-icing valves
Allow sufficient time for thermal switch cooling prior to investigating. If no other of normal indications exist, and an operation maybe continued for the remainder of the flight
Windshield heat CYCLING lights on (neon) cause
Indicates that electrical power is being supplied to the windshield panels. When lights are out, electrical power is cycled off
If unable to start cycling on a cold windshield, use override switch
Side windshield heat FAIL light on cause and action
Windshield Power Relay and or overheat control Relay stuck in energize position when control switch off
Pull side windshield heat power circuit breaker on bus a
L or R HTR OUT pilot heat out light on cause and action
Indicates electrical current flow to the pitot heater element has been interrupted, or current flow detector is inoperative
Check respective circuit breaker and bus. Monitor equipment for proper operation
No. 1,2,3 or 4 feather valves and NTS lights on cause
a. Switch in NTS position
b. in FEATHER VALVE postion
a. NTS has occurred (reset by putting switch to feather valve position and back to NTS position)
b. Feather valve is being mechanically positioned to the feather postion by NTS action during the NTS check (flashing) or by the emergency shutdown handle when pulled (steady)
Bomb bay cold light on cause and action / hot?
COLD: Temperature below desired level in bomb bay
Turn Bomb bay what switch ON (auto cycling) open No. 3 or 4 engine bleed air valve
HOT: Temp above desired level, not cycling
Turn bomb bay heat switch OFF until light goes out. Heat bomb bay with switch in OVD. Monitor.
DOORS light on cause
- action
Intake or exhaust door open (should close when APU is shut down)
- do not exceed 225kts
No. 1,2,3 or 4 Filter light on cause
One or both of the low pressure fuel filters are restricting flow
If engine continues to function normally, continue engine operation
No. 1,2,3 or 4 PRESS LOW light on cause
Indicates the differential pressure across the corresponding engine driven centrifugal boost pump is low.
A flickering light indicates a partial obstruction of the fuel line.
Note: the fuel PRESS LOW light should be out by low rpm. After start, possible faulty or stuck px switch
No. 1,2,3 or 4 PRESS LOW light on action
a. If fuel flow and quantity of the corresponding engine are normal and it continues to operate normally, inspect nacelle for visible fuel. If visible, secure engine.
In flight: if no fuel visible, continue operation, observing engine closely
On ground: if no fuel visible, cycle respective boost pump or shift engine to normal rpm. If light goes out and remains out, continue operation
No. 1,2,3 or 4 TANK Shut off valve advisory lights on cause
- action
Like all illuminate whenever the corresponding tank valve position does not coincide with the tank valve switch. Failure of the valve to open or close completely energizes the light
- investigate
No. 1,2,3 or 4 XFEED valve advisory lights on cause
- action
Same as No. 1,2,3 or 4 TANK Shut off valve advisory lights on cause and action
Cross ship X FEED valve advisory light on cause and action
Same as No. 1,2,3 or 4 TANK Shut off valve advisory lights on cause and action
RESET Advisory light on cause and action.
Light will illuminate whenever the refuel control panel has control of the transfer valves, which are also used to refuel tank numbers one, two, three, four
Push the reset button to regain control of transfer valves
Tank BOOST Pump low pressure advisory light on cause and action
Light will illuminate whenever the output pressure of the corresponding boost pump is low
Ref fuel boost pump failure paragraph 15.8.2
Transfer pumps PRESS LOW advisory lights on causes
1: Take a number five is empty
2: pump output pressure is low
Shut off respective pump; refer to transfer pump failure tank five paragraphs 15.8.3
GEN Mechanical failure light No. 2,3,4 (on study or intermittent) cause and action
Primary generator drive end bearing has failed
Mission should be aborted. If the generator switch must be left in the OFF position because of a generator malfunction, execute the emergency shut down procedure
CHIPS light no. 1,2,3,4 on (steady or intermittent) cause and action
Metal particles on magnetic plug in power section or gearbox
Check for secondary indications. If noted, execute emergency shut down procedure. If no secondary indications are present, engine operation may be continued. Refer to magnetic chip detector indication paragraph 15.10
OIL HOT light no. 1,2,3,4 engine on cause
Engine oil temperature 100°C or over
In Beta range: open inducers to decrease the temperature.
In Alpha range: 100°C for five minutes, then 90 degrees Celsius. Control with oil cooler Flaps position. If unable to control, secure engine
OIL PRESS light no. 1,2,3,4 engine on cause
Either engine oil pressure is below 40 psi or box pressure below 130 PSI
Low RPM: light normal.
In-flight: check oil pressure gauges; investigate. If oil pressure is within limits: continue operation. If out of limits: execute the emergency shut down procedure
PROP PUMP no. 1 light (1,2,3 or 4 engine) on cause
Pump failure / obstruction/ low oil level : Reduced flow and drop in pressure from prop pump
If either or both propeller pump caution lights illuminate: continue normal operation and referred to prop functions paragraph 15.2
FUS DUCT HOT light on cause
Leak in the area around cross ship manifold, creating excessive temperature. Can be caused by a leak in the bleed air manifold, APU lead airlines, or EDC plumbing
FUS DUCT HOT light on action
1: On ground, secure ground air conditioning and all engine and APU bleed air and returned to the line
2: In-flight, close all engine bleed and fuselage shut off valves
3: If light remains on, dump EDC’s one at a time
4: If light remains on, land as soon as possible
CABIN PRESS light on cause
- action
Light on at Kevin Altitude 10,000 feet (Plus or minus 500 feet) Cabin Press light out by 8000 feet on descent
- Referred to pressurization loss paragraph 12.4
Master RACK OVHT light on cause
Electronically rack overheat condition exists. Also comes on during main DC bus failure. ASH-33 (DMTS) Will cause a wreck overheat indication when the system is initially turned on initially or will illuminate continuously when a loss of airflow is detected
Master RACK OVHT light on action
Initiate fire of unknown origin Checklist Procedures. Locate overheated electronic bay by illuminated individual overheat light. Provide required cooling or secure equipment as necessary
IFF light on cause
Mode 4 zeroized, self test function of computer has detected a faulty computer, trx n out replying to proper Mode 4 interrogations
IFF light on action
Ensure MASTER switch in NORM, mode 4 toggle switch ON, and proper code selected. If light persists, fly selected operational procedure for inoperative tactical IFF
START VALVE light on cause
a. During start sequence (normal)
b. After start sequence or during engine operation (abnormal)
Indicates one of four engine start control valves is open
1: Check overhead panel for individual engine start control valve open light
AUTOPILOT light cause
a. AUTOPILOT amber light (on annunciator panel) Autopilot disengages
b. AUTOPILOT flashing red warning light (on glare shield) Autopilot disengages cause and action
Autopilot or vertical gyro power loss. Excessive vertical gyro precession. No. 1 hyd system px low. Disengagement by paddle switch
Hardcover pitch has been detected. Assume manual control
Action: Extinguish light by depressing pilot or copilot yoke button and investigate
AUTOPILOT/ RAWS
a. AUTOPILOT/ RAWS flashing red warning lights (glare shield) cause and action (for PB-20N)
Autopilot or vertical gyro power loss. Excessive vertical gyro precession. No. 1 hyd system px low. Disengagement by paddle switch.
Disengage ap and investigate
For ASW-31: Cause: AP malfunction or certain types of Normal/auto disconnects. Action: ref. Status lights. Mayb be extinguished by pushing WARN/TEST indicator light switch, 2 detent on control wheel or ap emergency manual disconnect handle
AUTOPILOT/ RAWS flashing red warning lights (glareshield) with synchronized tone cause and action
RAWS warning: loss of ac power to RADALT. Unreliable RADALT signal. Aircraft descending through 380 +- 20ft (3sec warning) or 170 +- 10ft (continuous warning). All warnings are cancelled when nose gear down and locked or flap handle us below MANEUVER.
If warning is abnormal, investigate
FLAP ASYM light on cause and action
Flap asymmetry system has tripped.
If there has been multiple flap component failure, flaps may still be moving or could be moved with flap handle
If change in flight characteristics: execute split flap procedures paragraph 16.6
If not: place flap handle in best corresponding position. Ref split flap procedures
DOOR OPEN light on cause
Cabin door (either one) or HSC door not locked
RUDDER POWER light on (flaps up) cause
1: No. 1 hyd system px failure
2: shutoff valve has opened
RUDDER POWER light on (flaps up) action
Kick it: actuate rudder pedals to deplete residual no. 2 hyd sys px in the rudder boost package
If light remains on…
Check it: rudder boost shutoff valve cb
Kill it: turn off No. 2 hyd pump.
If light goes out… shutoff valve is inop
Turn it on: turn no. 2 hyd pump back on and make no abrupt movements
AUTO TRIM light on cause and action
Auto pitch trim system failed (will cause pitch trim off flag to appear in the trim indicator
1: disengage ap
2: reset auto trim by pulling 3 AC ap cb’s and reset one at a time
If failure persists…
1: extinguish lihh go t with AUTO TRIM LT OVD switch (lights auto reset when flaps extend)
2: check trim indicator before disconnecting ap
No. 1 or 1A HYD PRESS light cause and action
Respective pump output px is below 1800psi
Turn off the pump and investigate
NOTE: gear retraction with one operable hyd pump may result in indication of system failure and unsafe gear due to heavy system demands
No. 2 HYD PRESS light on cause and action
No. 2 output px is below 1800psi
1: check no. 2 sys px
2: if pow, secure pump
No. 1, 1A or 2 HYD OIL HOT light on cause and action
1: Hyd oil temp is high
2: Restricted coolant flow
3: Not enough fuel in respective inboard fuel tank (min 1k lbs)
Turn off respective pump
