Annunciator Lights

Front 1

T/R OVERHEAT 1,2,3 ON

Back 1

PROBABLE CAUSE
transformer rectifier overheat @ 150 deg F

CORRECTIVE ACTION
pull respective C/B
#3 FLC, #1and #2 MLC

Front 2

GEN 2,3,4 or APU GEN OFF light on

Back 2

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.

Front 3

External power available light ON (neon), but no power into aircraft.

Back 3

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

Front 4

External power available light ON, partial power into aircraft

Back 4

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

Front 5

External power light ON

Back 5

PROBABLE CAUSE
ext pwr supplying power to aircraft system

CORRECTIVE ACTION
ext pwr S/W in on

Front 6

#1,2,3,or 4 pri fuel pump (parallel) light on during start (16-65% RPM)

Back 6

PROBABLE CAUSE
indicates the secondary fuel pump is functioning properly.

Front 7

#1,2,3, or 4 pri fuel pump (parallel) light off during start (16-65% RPM)

Back 7

PROBABLE CAUSE
failure of secondary pump

CORRECTIVE ACTION
investigate

Front 8

#1,2,3 or 4 pri fuel pump light on, or momentarily ON then OFF, above 65% RPM

Back 8

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

Front 9

#1,2,3,4 AUTO FEATHER lights are all ON

Back 9

PROBABLE CAUSE
the automatic feathering circuit has been armed

Front 10

#1,2,3,4 AUTO FEATHER light on individually

Back 10

PROBABLE CAUSE
prop thrust has dropped to less than 500 lbs. of positive thrust, prop has auto feathered.

CORRECTIVE ACTION
investigate

Front 11

#1,2,3,4 engine starter control valve open light ON

Back 11

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

Front 12

#1,2,3,4 prop feather button light remains ON.

Back 12

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.

Front 13

FAN OUT light ON

Back 13

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

Front 14

EDC TEMP HIGH light ON

Back 14

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.

Front 15

EDC PRESS LOW light ON

Back 15

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.

Front 16

REFER OVERHEAT light ON

Back 16

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.

Front 17

LW HOT or RW HOT light ON

Back 17

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.

Front 18

#1,2,3,4 engine bleed air valve OPEN lights ON.

Back 18

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

Front 19

Left and right fus bleed air shutoff valve OPEN lights on.

Back 19

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

Front 20

LE HOT light ON

Back 20

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.

Front 21

EMP DEICE light ON

Back 21

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.

Front 22

#1,2,3,4 engine ANTI-ICING advisory light ON with control switch ON.

Back 22

PROBABLE CAUSE
14th stage bleed air of sufficient temp to melt ice has entered the torque-meter shroud and the inlet scoop.

Front 23

No ANTI-ICING advisory light with control switch ON

Back 23

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.

Front 24

ANTI-ICING advisory light ON with control switch OFF

Back 24

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.

Front 25

ANTI-ICING advisory light remains on after system utilization.

Back 25

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.

Front 26

Windshield heat cycling lights ON (neon)

Back 26

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.

Front 27

Side windshield heat FAIL light ON.

Back 27

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.

Front 28

L or R HTR OUT pitot heat out light ON

Back 28

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.

Front 29

#1,2,3,4 feather valve and NTS lights on.

Switch in NTS position

Back 29

PROBABLE CAUSE
NTS has occured

CORRECTIVE ACTION
reset by putting switch to feather valve position and back to NTS position.

Front 30

#1,2,3,4 feather valve and NTS lights on.

switch in Feather valve position.

Back 30

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)

Front 31

BOMB BAY COLD light ON

Back 31

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.

Front 32

BOMB BAY HOT light ON

Back 32

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.

Front 33

DOORS light ON

Back 33

PROBABLE CAUSE
intake or exhaust door open.

CORRECTIVE ACTION
do not exceed 225 KIAS.

Front 34

ARMED light ON

Back 34

PROBABLE CAUSE
arming switch is on.

CORRECTIVE ACTION
if APU is not being used in flight, turn arming s/w OFF.

Front 35

#1,2,3,4 FILTER light ON

Back 35

PROBABLE CAUSE
1 or both low press fuel filters are restricing flow.

CORRECTIVE ACTION
if eng continues to function normally, continue eng op.

Front 36

#1,2,3,4 fuel PRESS LOW light ON.

Back 36

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.

Front 37

#1,2,3,4 tank shutoff valve advisory lights ON.
#1,2,3,4 XFEED valve light ON.
Cross ship XFEED valve light ON.

Back 37

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.

Front 38

RESET advisory light ON.

Back 38

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.

Front 39

tank BOOST pump low press advisory light ON.

Back 39

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.

Front 40

transfer pumps PRESS LOW advisory light ON.

Back 40

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

Front 41

GEN MECH fail light #2,3,4 ON

Back 41

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.

Front 42

CHIPS light #1,2,3,4 ON

Back 42

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.

Front 43

OIL HOT light #1,2,3,4 ON

Back 43

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.

Front 44

OIL PRESS light #1,2,3,4 ON

Back 44

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.

Front 45

PROP PUMP #1 or #2 light ON

Back 45

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.

Front 46

BETA light #1,2,3,4 prop ON

Back 46

PROBABLE CAUSE
blade angle below 10deg

Front 47

FUS DUCT HOT light ON

Back 47

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.

Front 48

CABIN PRESS light ON

Back 48

PROBABLE CAUSE
light on at cabin alt 10,000+/-500 ft., light out by 8,000ft.

CORRECTIVE ACTION
refer to 12.2 press loss

Front 49

Master DE-ICING light ON

Back 49

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

Front 50

Master ELE POWER light ON

Back 50

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.

Front 51

Master PRESS SYSTEM light ON

Back 51

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.

Front 52

master RACK OVHT light on.

Back 52

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.

Front 53

IFF light ON

Back 53

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.

Front 54

START VALVE light ON

Back 54

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.

Front 55

AUTOPILOT amber light on, autopilot disengages.

Back 55

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.

Front 56

AUTOPILOT flashing red warning light (on glareshield). Autopilot disengages.

Back 56

PROBABLE CAUSE
hardover pitch has been detected.

CORRECTIVE ACTION
assums manual control.

Front 57

AUTOPILOT/RAWS flashing red warning lights (glareshield)

Back 57

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.

Front 58

AUTOPILOT/RAWS flashing red warning lights.

Back 58

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.

Front 59

AUTOPILOT/RAWS flashing red warning lights with synchronized tone.

Back 59

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.

Front 60

FLAP ASYM light ON

Back 60

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.

Front 61

DOOR OPEN light ON

Back 61

PROBABLE CAUSE
cabin door or either section of HSC doors are not closed and locked.

CORRECTIVE ACTION
lock the door.

Front 62

RUDDER POWER light ON (flaps up)

Back 62

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.

Front 63

AUTO TRIM light ON

Back 63

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.

Front 64

#1 or #1A HYD PRESS light ON

Back 64

PROBABLE CAUSE
respective pump output press is < 1800 PSI

CORRECTIVE ACTION
turn off the respective pump.

Front 65

#2 HYD PRESS light ON

Back 65

PROBABLE CAUSE
#2 pump output press is < 1800 PSI.

CORRECTIVE ACTION
check #2 sys press, if low secure pump.

Front 66

#1, 1A, or 2 HYD OIL HOT light ON

Back 66

PROBABLE CAUSE
hyd oil temp is excessive, restricted coolant flow, not enough fuel in cooling tank.

CORRECTIVE ACTION
turn off respective pump.

Front 67

NTS INOPR

Back 67

PROBABLE CAUSE
inop NTS system.

CORRECTIVE ACTION
continue holding out on feather button; pull E handle, then push in feather button.

Front 68

ICING light ON

Back 68

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.

Front 69

AFCS caution light ON

Back 69

PROBABLE CAUSE
AFCS malfunction

CORRECTIVE ACTION
discontinue use of AFCS and investigate (check seperate channel op)

Front 70

ATTD caution light ON

Back 70

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

Front 71

SERVO light ON

Back 71

PROBABLE CAUSE
failure in servoamp or AFCS hyd actuator.

CORRECTIVE ACTION
Discontinue use of AFCS and investigate

Front 72

ALT status light ON

Back 72

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

Front 73

AUTOTRIM caution light ON

Back 73

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.

Front 74

BOMB BAY cue light ON

Back 74

PROBABLE CAUSE
cue to move bomb bay s/w to opposite pos.

CORRECTIVE ACTION
move bomb bay s/w to opposite pos.

Front 75

ARM HAZARD light ON

Back 75

PROBABLE CAUSE
energized buffer relay

CORRECTIVE ACTION
go to reset. If light remains on, use offline mode for weapon release.

Front 76

SONO DISABLED light ON

Back 76

PROBABLE CAUSE
sonobouy circuit disabled.

CORRECTIVE ACTION
close sonobouy disable door prior to taxi.