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76 Cards in this Set

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T/R OVERHEAT 1,2,3 ON
PROBABLE CAUSE
transformer rectifier overheat @ 150 deg F

CORRECTIVE ACTION
pull respective C/B
#3 FLC, #1and #2 MLC
GEN 2,3,4 or APU GEN OFF light on
PROBABLE CAUSE
gen failure, off freq, over voltage, under voltage, feeder fault, sup panel failure, transfer relay 2 or 3 failure, or associated bus monitoring s/w OFF

CORRECTIVE ACTION
use reset procedure, or place associated BUS MONITORING s/w on. If an engine driven gen light remains on steady throughout reset procedures, or goes out momentarily and comes back on, mission should be aborted.
External power available light ON (neon), but no power into aircraft.
PROBABLE CAUSE
wrong phase, nosegear uplock not properly positioned, battery not connected, Gen no. 4 runaround feeder C/B out, ext power control C/B out

CORRECTIVE ACTION
move ext pwr s/w to RESET then ON. Check nosegear uplock position. Check battery condition. Check no.4 runaround feeder C/B. Check ext pwr control C/B
External power available light ON, partial power into aircraft
PROBABLE CAUSE
T/R #3 ganged C/B out. Ess DC bus feeder C/B #2 out. MON ESS AC ganged C/B out. MON ESS BUS S/W off

CORRECTIVE ACTION
Check TR3 C/B. Check ESS DC bus feeder C/B #2. Check MON ESS AC ganged C/B in. Check MON ESS Bus S/W
External power light ON
PROBABLE CAUSE
ext pwr supplying power to aircraft system

CORRECTIVE ACTION
ext pwr S/W in on
#1,2,3,or 4 pri fuel pump (parallel) light on during start (16-65% RPM)
PROBABLE CAUSE
indicates the secondary fuel pump is functioning properly.
#1,2,3, or 4 pri fuel pump (parallel) light off during start (16-65% RPM)
PROBABLE CAUSE
failure of secondary pump

CORRECTIVE ACTION
investigate
#1,2,3 or 4 pri fuel pump light on, or momentarily ON then OFF, above 65% RPM
PROBABLE CAUSE
- failure of primary pump
- fuel pumps are in parallel operation possibly due to a speed sense control malfunction

CORRECTIVE ACTION
Pull FUEL SHUTOFF VALVE C/B on SEDC
- if light remains on, reset the C/B, and assume the pri pump has failed
- if the light goes out, leave the C/B out, and assume a failure of either the 65% S/W or the speed sense control
#1,2,3,4 AUTO FEATHER lights are all ON
PROBABLE CAUSE
the automatic feathering circuit has been armed
#1,2,3,4 AUTO FEATHER light on individually
PROBABLE CAUSE
prop thrust has dropped to less than 500 lbs. of positive thrust, prop has auto feathered.

CORRECTIVE ACTION
investigate
#1,2,3,4 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 at 60% RPM)

CORRECTIVE ACTION
secure engine by pulling E handle, if light remains on or comes on after start
#1,2,3,4 prop feather button light remains ON.
PROBABLE CAUSE
indicates feather pump relay is closed, supplying ele pwr to the feather pump

possible internal leakage. incomplete pump cut-out circuit.

CORRECTIVE ACTION
- if light remains on following engine shutdown, pull respective propeller feather control C/B and excute Emergency shutdown procedure.

- If light remains on following pressure cutout override refer to inflight restart procedures.
FAN OUT light ON
PROBABLE CAUSE
cabin exhaust fan is inop or lack of airflow.

CORRECTIVE ACTION
open equipment doors for extra cooling. Use min ele equipment. If EDC's are inop (no A/C avail) open AUX vent
EDC TEMP HIGH light ON
PROBABLE CAUSE
EDC oil temp excessive (121 C).
low oil in sump.
high engine oil temp

CORRECTIVE ACTION
- check engine oil temp, if high correct
- if unable to control, disconnect EDC, monitor for loss of spread, dump, continure op
- If spread is indicated after disconnect, excute the emergency shutdown procedure. If the engine is allowed to operate due to a greater emergency, the EDC should be dumped.
EDC PRESS LOW light ON
PROBABLE CAUSE
- EDC oil press is low (below 50PSI)
- low level in sump
- EDC driveshaft sheared

CORRECTIVE ACTION
- with loss of spread disconnect and dump EDC. continue operation.
- if spread is indicated, disconnect, monitor for loss of spread, dump. continue operation.
- if spread is indicated after disconnect, excute the emergency shutdown procedure. If the engine is allowed to operate due to a greater emergency, the EDC should be dumped.
REFER OVERHEAT light ON
PROBABLE CAUSE
temp in cooling duct exceeds 166 C. ON GROUND: inop heat exchanger blower fan.

CORRECTIVE 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 s/w. investigate by checking the heat exchanger C/B on bus B and blower cont C/B on MEDC. If C/B's are set and the light is out, op is permitted in the man mode 2 dot or warmer.
LW HOT or RW HOT light ON
PROBABLE CAUSE
air temp in the wing plenum area exceeds 110C. May be caused by a leak in the bleed air manifold or EDC plumbing.

CORRECTIVE ACTION
- secure wing deicing and get out of icing area
- if light remains on, dump appropriate EDC.
#1,2,3,4 engine bleed air valve OPEN lights ON.
PROBABLE CAUSE
when vavle begins to open, the light will be on. When the valve is closed, the light should be off.
Left and right fus bleed air shutoff 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.
LE HOT light ON
PROBABLE CAUSE
the wing leading edge skin temp exceeds 110 C. 1 of the 6 modulating valves is either stuck open or improperly modulating.

CORRECTIVE ACTION
close all bleed air valves. locate defective area with temp selector. Open all modulating valves. When necessary, deice the entire wing using bleed air valves.
EMP DEICE light ON
PROBABLE CAUSE
parting strip power relay deenergized, cycling strip power relay deenergized, control relay deenergized, timer motor failure, emp overheat cond, open control pwr c/b.

CORRECTIVE ACTION
turn s/w OFF then ON. If light remains on, turn s/w OFF, increase airspeed above 200 KIAS; vacate icing area. If light doesn't come back on, a temp overheat exists. COntinue operation.
#1,2,3,4 engine ANTI-ICING advisory light ON with control switch ON.
PROBABLE CAUSE
14th stage bleed air of sufficient temp to melt ice has entered the torque-meter shroud and the inlet scoop.
No ANTI-ICING advisory light with control switch ON
PROBABLE CAUSE
one or both areas of system may not be receiving hot air.

CORRECTIVE ACTION
a) check for SHP drop. If normal continue operation.
b) if less then normal:
(1) check for ice buildup on air inlet scoop. if excessive, excute emerg shutdown procedures.
(2) if no ice buildup, monitor SHP, TIT and fuel flow. Initial indications may be a gradual power loss followed by erratic ops. If either of these are seen, excute emerg shutdown procedures.
ANTI-ICING advisory light ON with control switch OFF
PROBABLE CAUSE
- abnormal heat in the area.
- loss of ele pwr to the solenoid valve.

CORRECTIVE ACTION
on deck - investigate, secure engine and return to line.
in flight - turn on anti-ice s/w.
- if a SHP drop is seen, excute emerg shutdown procedures.
- if no SHP drop is seen, continue operation.
ANTI-ICING advisory light remains on after system utilization.
PROBABLE CAUSE
failure of 1 or both thermal s/w and/or anti-ice valves.

CORRECTIVE ACTION
allow time for thermal s/w to cool. If no other abnormal ind, eng may be used rest of flight.
Windshield heat cycling lights ON (neon)
PROBABLE CAUSE
indicates that ele pwr is being supplied to windshield panels.

CORRECTIVE ACTION
if unable to start cycling on a cold windshield, use OVERRIDE S/W.
Side windshield heat FAIL light ON.
PROBABLE CAUSE
windshield pwr relay and/or overheat control relay, stuck in energized pos w/ control s/w off

CORRECTIVE ACTION
pull side windshield heat power C/B on Bus A.
L or R HTR OUT pitot heat out light ON
PROBABLE CAUSE
ele currect flow to the pitot heater element has been interrupted, or current flow detector is inop.

CORRECTIVE ACTION
check respective C/B and bus. Monitor equipment for proper op.
#1,2,3,4 feather valve and NTS lights on.

Switch in NTS position
PROBABLE CAUSE
NTS has occured

CORRECTIVE ACTION
reset by putting switch to feather valve position and back to NTS position.
#1,2,3,4 feather valve and NTS lights on.

switch in Feather valve position.
PROBABLE CAUSE
feather valve is being mechanically positioned to feather pos by NTS action during an NTS check(flashing light), or by emerg shutdown handle when pulled.(steady light)
BOMB BAY COLD light ON
PROBABLE CAUSE
temp below desired level in bomb bay.

CORRECTIVE ACTION
turn bomb bay heat s/w ON, open #3 or #4 eng bleed air valve.
BOMB BAY HOT light ON
PROBABLE CAUSE
temp above desired level, not cycling.

CORRECTIVE ACTION
turn bomb bay heat s/w OFF untill light goes out, then heat bomb bay with s/w in OVERRIDE pos. Monitor for proper op.
DOORS light ON
PROBABLE CAUSE
intake or exhaust door open.

CORRECTIVE ACTION
do not exceed 225 KIAS.
ARMED light ON
PROBABLE CAUSE
arming switch is on.

CORRECTIVE ACTION
if APU is not being used in flight, turn arming s/w OFF.
#1,2,3,4 FILTER light ON
PROBABLE CAUSE
1 or both low press fuel filters are restricing flow.

CORRECTIVE ACTION
if eng continues to function normally, continue eng op.
#1,2,3,4 fuel PRESS LOW light ON.
PROBABLE CAUSE
indicates the diff press across respective eng driven centrifugal boost pump is low. Flickering light indicates partial blockage.

CORRECTIVE ACTION
A) if fuel flow and quanity of the eng are norm, inspect nacelle for visible fuel, if visible, secure eng.
B) in flight, if no fuel visible, continue op, watching eng.
C)on deck, if no fuel visible, cycle boost pump or shift eng to NORM RPM, then back to LOW. If light goes out and remains out, continue op.
#1,2,3,4 tank shutoff valve advisory lights ON.
#1,2,3,4 XFEED valve light ON.
Cross ship XFEED valve light ON.
PROBABLE CAUSE
light will be on whenever the tank valve position doesn't match with the tank valve s/w. Failure of the valve to open or close completely energizes the light.

CORRECTIVE ACTION
investigate.
RESET advisory light ON.
PROBABLE CAUSE
light will be on whenever the refuel control panel has control of the transfer valves.

CORRECTIVE ACTION
push reset button to regain control of transfer valves.
tank BOOST pump low press advisory light ON.
PROBABLE CAUSE
light will be on whenever the output press of the boost pump is low.

CORRECTIVE ACTION
refer to 15.8.2 fuel boost pump failure procedures.
transfer pumps PRESS LOW advisory light ON.
PROBABLE CAUSE
tank #5 is empty or pump output press is low.

CORRECTIVE ACTION
shut off respective pump; refer to 15.8.3 transfer pump failure
GEN MECH fail light #2,3,4 ON
PROBABLE CAUSE
primary gen drive end bearing has failed.

CORRECTIVE ACTION
mission should be aborted. If gen s/w must be left in OFF pos because of gen mal, excute emerg shutdown procedures.
CHIPS light #1,2,3,4 ON
PROBABLE CAUSE
metal particles on mag plug in eng or RGB.

CORRECTIVE ACTION
check for secondaries, if noted, excute emerg shutdown procedures. If not, eng op may be continued.
OIL HOT light #1,2,3,4 ON
PROBABLE CAUSE
eng oil temp > 100C

CORRECTIVE ACTION
if pwr levers in gnd range, open inducers to decrease temp. If in flt range, control oil cooler flaps pos. If unable to control, secure engine.
OIL PRESS light #1,2,3,4 ON
PROBABLE CAUSE
either eng oil press < 40PSI or RGB < 130PSI

CORRECTIVE ACTION
low RPM - light normal
in flight - check oil press guages, investigate. If oil press in limits, continue eng op, if not secure eng.
PROP PUMP #1 or #2 light ON
PROBABLE CAUSE
reduced flow and drop in press from PP1 or PP2 due to pump failure, obstruction, or low oil level.

CORRECTIVE ACTION
continue normal engine op, refer to 15.12 for prop malfunctions.
BETA light #1,2,3,4 prop ON
PROBABLE CAUSE
blade angle below 10deg
FUS DUCT HOT light ON
PROBABLE CAUSE
leak in bleed air manifold, APU bleed air lines, or EDC plumbing.

CORRECTIVE ACTION
a) close all eng bleed and fuselage SOV
b) in flight - if light remains on, dump EDC's one at a time
c) on deck - secure gnd a/c and all eng and APU bleed air.
CABIN PRESS light ON
PROBABLE CAUSE
light on at cabin alt 10,000+/-500 ft., light out by 8,000ft.

CORRECTIVE ACTION
refer to 12.2 press loss
Master DE-ICING light ON
PROBABLE CAUSE
- L or R WING HOT LITE
- LE HOT LITE
- EMP DEICE LITE
- L or R pitot heater lite
- BOMB BAY HOT / COLD LITES
Master ELE POWER light ON
PROBABLE CAUSE
- gen #2,3,4 off light is on
- T/R overheat 1,2,3

CORRECTIVE ACTION
locate fault on overhead panel. secure faulty system. reset for continued warning protection.
Master PRESS SYSTEM light ON
PROBABLE CAUSE
- oil press low or oil temp high on left or right EDC.
- cabin exhaust fan inop.
- refer duct overheat warning.

CORRECTIVE ACTION
locate fault on overhead panel. secure faulty system. reset for continued warning protection.
master RACK OVHT light on.
PROBABLE CAUSE
ele rack overheat exists. MDC loss

CORRECTIVE ACTION
initiate fire of unknown origin procedures. Locate overheated ele bay by illuminated individual bay overheat light. provide required cooling or secure equip as necessary.
IFF light ON
PROBABLE CAUSE
- mode 4 zeroized
- self test has detected a fault
- transponder not replying to mode 4 interrogations

CORRECTIVE ACTION
ensure master s/w in norm, mode 4 s/w on, and proper code selected for inop tactical IFF.
START VALVE light ON
PROBABLE CAUSE
eng starter control valve is not closed.

CORRECTIVE ACTION
if light remains on after start sequence, or comes on during flight, check overhead panel for individual eng starter control valve open light and pull appropriate e handle.
AUTOPILOT amber light on, autopilot disengages.
PROBABLE CAUSE
autopilot or vert gyro power loss. Excessive vert gyro precession. #1 hyd sys press low. Disengagement by paddle s/w

CORRECTIVE ACTION
extinguish light by depressing pilot or copilot yoke button. investigate.
AUTOPILOT flashing red warning light (on glareshield). Autopilot disengages.
PROBABLE CAUSE
hardover pitch has been detected.

CORRECTIVE ACTION
assums manual control.
AUTOPILOT/RAWS flashing red warning lights (glareshield)
PROBABLE CAUSE
- autopilot or vert gyro power loss.
- Excessive vert gyro procession.
- #1 hyd sys press low
- disengagement by paddle s/w

CORRECTIVE ACTION
disengage auto pilot. investigate.
AUTOPILOT/RAWS flashing red warning lights.
PROBABLE CAUSE
autopilot malfunction or certain types of norm/auto disconnects.

CORRECTIVE ACTION
refer to status lights. May be extinguished by pushing WARN/TEST indicator light s/w, by pushing disengage button on control wheel, or by op of the autopilot emerg manual disconnect handle.
AUTOPILOT/RAWS flashing red warning lights with synchronized tone.
PROBABLE CAUSE
RAWS warning: loss of AC power to rad alt. Unreliable rad alt signal.
A/C decending through 380+/-20 feet(3 sec)
A/c decending through 170+/-10 feet(continuous)

CORRECTIVE ACTION
if warning is abnormal; investigate.
FLAP ASYM light ON
PROBABLE CAUSE
flap asym sys has tripped. If there has been a multi flap component failure, the flaps may still be moving or could be moved by use of flap handle.

CORRECTIVE ACTION
if by a change in flight char, refer to split flap procedures. If not, place flap handle in position best corresponding to flap pos.
DOOR OPEN light ON
PROBABLE CAUSE
cabin door or either section of HSC doors are not closed and locked.

CORRECTIVE ACTION
lock the door.
RUDDER POWER light ON (flaps up)
PROBABLE CAUSE
#1 hyd sys press failure.
sov has opened.

CORRECTIVE ACTION
actuate rudder pedals to deplete residual #2 hyd sys press in the rudder boost package. If the light remains on:
- check the rudder boost SOV C/B
- turn off the #2 hyd pump. IF the light goes out, the SOV is inop. Turn #2 hyd pump on and make no abrupt rudder movements.
AUTO TRIM light ON
PROBABLE CAUSE
indicates the auto pitch trim sys has failed. Will also cause the pitch trim off flag to appear in the 3 axis tim ind.

CORRECTIVE ACTION
disengage autopilot. Reset auto trim sys by pulling the 3 AC autopilot C/B's and resetting one time only. If failure persists, extinguish light with AUTO TRIM LT OVERRIDE s/w. Light auto restes when flaps extended. Check 3 axis trim ind before disconnecting autopilot.
#1 or #1A HYD PRESS light ON
PROBABLE CAUSE
respective pump output press is < 1800 PSI

CORRECTIVE ACTION
turn off the respective pump.
#2 HYD PRESS light ON
PROBABLE CAUSE
#2 pump output press is < 1800 PSI.

CORRECTIVE ACTION
check #2 sys press, if low secure pump.
#1, 1A, or 2 HYD OIL HOT light ON
PROBABLE CAUSE
hyd oil temp is excessive, restricted coolant flow, not enough fuel in cooling tank.

CORRECTIVE ACTION
turn off respective pump.
NTS INOPR
PROBABLE CAUSE
inop NTS system.

CORRECTIVE ACTION
continue holding out on feather button; pull E handle, then push in feather button.
ICING light ON
PROBABLE CAUSE
indicates ice detector probe is accumulating ice. The frequency of light cycling indicates amount of ice buildup. Light may indicate high AOA.

CORRECTIVE ACTION
anticipate icing conditions.
AFCS caution light ON
PROBABLE CAUSE
AFCS malfunction

CORRECTIVE ACTION
discontinue use of AFCS and investigate (check seperate channel op)
ATTD caution light ON
PROBABLE CAUSE
attitude signals divergent or erroneous or module failure. AFCS inertial select s/w op when AFCS engaged.

CORRECTIVE ACTION
reestablish valid attitude reference. check inertial s/w
SERVO light ON
PROBABLE CAUSE
failure in servoamp or AFCS hyd actuator.

CORRECTIVE ACTION
Discontinue use of AFCS and investigate
ALT status light ON
PROBABLE CAUSE
- pitch is engaged but not in ALT-HOLD mode
- alt failure when in ALT-HOLD mode
- a/c has deviated from engaged alt by more than 60 ft
- malfunction in AFCS alt sys

CORRECTIVE ACTION
reestablish attitude reference and attidude. If AFCS mal, discontinue ALT-HOLD mode and investigate
AUTOTRIM caution light ON
PROBABLE CAUSE
pitch autotrim malfunction

CORRECTIVE ACTION
desengage and reengage pitch axis. If failure persists, extinguish light with autotrim light override s/w and trim manually. Light auto resets when flaps extended. Check 3 axis trim ind before disconnecting autopilot.
BOMB BAY cue light ON
PROBABLE CAUSE
cue to move bomb bay s/w to opposite pos.

CORRECTIVE ACTION
move bomb bay s/w to opposite pos.
ARM HAZARD light ON
PROBABLE CAUSE
energized buffer relay

CORRECTIVE ACTION
go to reset. If light remains on, use offline mode for weapon release.
SONO DISABLED light ON
PROBABLE CAUSE
sonobouy circuit disabled.

CORRECTIVE ACTION
close sonobouy disable door prior to taxi.