Reading...
Play button
Play button
Use LEFT and RIGHT arrow keys to navigate between flashcards;
Use UP and DOWN arrow keys to flip the card;
H to show hint;
A reads text to speech;
62 Cards in this Set
- Front
- Back
|
GEN 2 or GEN 3, GEN 4 or APU GEN OFF light on.
|
Use reset procedure, or place associated BUS MONITORING 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.
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. 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.
|
Pull respective circuit breaker; No. 3 located at the flight station and No. 1 and 2 located at the main load center.
|
|
|
EXTERNAL PWR AVAILABLE light ON (neon), but no power into aircraft.
|
Move EXTERNAL POWER switch to RESET then ON. Check nose gear uplock position. Check battery condition. Check No. 4 runaround feeder circuit breaker. Check external power control circuit breaker.
|
|
|
EXTERNAL PWR AVAILABLE light ON partial power into aircraft.
|
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.
|
|
|
EXTERNAL POWER light ON.
|
EXTERNAL POWER switch is on.
|
|
|
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light on during start (between 16 percent and 65 percent rpm).
|
(No action required if it is functioning normally.)
|
|
|
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light off during start (between 16 percent and 65 percent rpm).
|
Investigate.
|
|
|
No. 1, 2, 3, or 4 PRIMARY FUEL PUMP light on, or momentarily ON then OFF, above 65 percent rpm.
|
Pull FUEL SHUTOFF VALVE circuit breaker on Start Essential DC bus.
a. If the 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. Note: If mission is continued: *Do not use autofeather. *Should maximum *** be limited to approximately 830 °C with or without the parallel light, assume a failure of the 94 percent switch or speed sense control. Place the affected TD switch to NULL and pull the FUEL SHUTOFF VALVE circuit breaker on the Start Essential DC bus. *Do not shut down the affected engine with intent to restart. * Reset the circuit breaker prior to securing the engine with the FUEL AND IGNITION switch. |
|
|
No. 1, 2, 3, and 4 AUTO FEATHER lights are all on.
|
(No action neccesary.)
|
|
|
No. 1, 2, 3, or 4 AUTO FEATHER light on individually.
|
Investigate.
|
|
|
No. 1, 2, 3, or 4 engine STARTER CONTROL VALVE OPEN light on.
|
* 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.
|
a. If light remains on following engine shutdown, pull respective propeller feather control circuit breaker (Eng. 2/3 EMDC, 1/4 MEDC), and execute the Emergency Shutdown procedure, paragraph 15.5.1.
b. If light remains on following pressure cutout override, refer to In‐Flight Restart Procedures, paragraph 8.33.1. |
|
|
FAN OUT light on.
|
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.
|
a. Check engine oil
temperature; if high, correct. b. If unable to control, disconnect, monitor for loss of spread, dump, continue operation. CAUTION The DISCONNECT position should be selected only when the engine is operating in the normal rpm range to prevent EDC damage. c. If spread is indicated after disconnect, execute the Emergency Shutdown procedure, paragraph 15.5.1. If the engine is allowed to operate due to a greater emergency, the EDC should be dumped. d. Refer to Air‐Conditioning System Malfunction (In Flight), paragraph 15.16. |
|
|
EDC PRESS LOW light on.
|
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. CAUTION The DISCONNECT position should be selected only when the engine is operating in the normal rpm range to prevent EDC damage. c. If spread is indicated after disconnect, execute the Emergency Shutdown procedure, paragraph 15.5.1. 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 selected and ground air conditioning on prior to disconnect. d. Refer to Air‐Conditioning System Malfunction (In Flight), paragraph 15.16. |
|
|
REFR OVHT (overheat) light
on. |
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. |
a. Secure wing deicing and
get out of icing area. b. If light remains on, dump appropriate EDC. |
|
|
No. 1, 2, 3, and 4 engine
bleed air valve OPEN lights on. |
N/A
|
|
|
Left and right FUS BLEED
AIR SHUT‐OFF valve OPEN lights on. |
N/A
|
|
|
LE HOT light on.
|
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.
|
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 overheat exists. Continue operation. |
|
|
No. 1, 2, 3, or 4 engine
ANTI‐ICING advisory light on with control switch on. |
N/A
|
|
|
No ANTI‐ICING advisory
light with control switch on. |
a. Check for horsepower drop.
If normal, continue operation. b. If less than normal: (1) Check for ice buildup on air inlet scoop. If excessive, execute the Emergency Shutdown procedure, paragraph 15.5.1. (2) If no ice buildup on air inlet scoop is observed, monitor SHP, ***, 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, paragraph 15.5.1 |
|
|
ANTI‐ICING advisory light
on and control switch off. |
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, paragraph 15.5.1. b. If no SHP drop is observed, continue engine operation. |
|
|
ANTI‐ICING advisory light
remains on after system utilization. |
Allow sufficient time for thermal switch
cooling prior to investigating. If no other abnormal indications exist, engine operation may be continued for the remainder of the flight. |
|
|
Windshield heat CYCLING
lights on (neon). |
If unable to start cycling on a cold
windshield, use OVERRIDE switch. |
|
|
Side windshield heat FAIL
light on. |
Pull side windshield heat power circuit
breaker on main AC bus A. |
|
|
L or R HTR OUT pitot heat
out light on. |
Check respective circuit breaker and
bus. Monitor equipment for proper operation. |
|
|
No. 1, 2, 3 or 4 feather valve
and NTS lights on. a. Switch in NTS position. |
Reset by putting switch to FEATHER
VALVE position and back to NTS position. |
|
|
No. 1, 2, 3 or 4 feather valve
and NTS lights on. b. Switch in FEATHER VALVE position. |
N/A
|
|
|
BOMB BAY COLD light on.
|
Turn bomb bay heat switch ON
(autocycling), open No. 3 or No. 4 engine bleed air valve. |
|
|
BOMB BAY HOT light on.
|
Turn BOMB BAY HEAT switch OFF
until light goes out, then heat bomb bay with switch in OVRD position. Monitor for proper operation. |
|
|
DOORS light on.
|
Do not exceed 225 KIAS.
|
|
|
ARMED light on.
|
If APU is not being used in flight, turn
arming switch off. |
|
|
No. 1, 2, 3, or 4 FILTER light
on. |
If engine continues to function
normally, continue engine operation. |
|
|
No. 1, 2, 3, or 4 PRESS
LOW light on. |
a. If fuel flow and quantity of
the corresponding engine are normal and engine continues to operate normally, inspect nacelle for visible fuel. If fuel is visible, secure engine. b. In flight, if no fuel visible, continue operation, observing engine closely c. During ground operations, if no fuel is visible, cycle respective boost pump or shift engine to normal rpm then back to low rpm. If light goes out and remains out, continue operation. |
|
|
No. 1, 2, 3, or 4 TANK
shutoff valve advisory lights on. |
Investigate.
|
|
|
No. 1, 2, 3, or 4 XFEED
valve advisory lights on. |
Investigate.
|
|
|
Cross ship X FEED valve
advisory light on. |
Investigate.
|
|
|
Tank BOOST pump low
pressure advisory light on. |
Refer to Fuel Boost Pump Failure,
paragraph 15.8.2. |
|
|
Transfer pumps PRESS
LOW advisory lights on. |
Shut off respective pump; refer to
Transfer Pump Failure, Tank 5, paragraph 15.8.3. |
|
|
GEN mechanical failure light
No. 2, 3, or 4 on (steady or intermittent). |
Mission should be aborted. If the
generator switch must be left in the OFF position because of a generator malfunction, execute the Emergency Shutdown procedure, paragraph 15.5.1. |
|
|
CHIPS light No. 1, 2, 3, or 4
on (steady or intermittent). |
Check for secondary indications. If
noted, execute Emergency Shutdown 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, or
4 engine on. |
If power levers in the ground (BETA)
range, open inducers to decrease temperature. If power levers are in flight (ALPHA) range, 100 °C for 5 minutes, then 90 °C. Control with oil cooler flaps position. If unable to control, secure engine. |
|
|
OIL PRESS light No. 1, 2, 3,
or 4 engine on. |
Low rpm, light normal. In flight, check
oil pressure gauges; investigate. If oil pressure is within limits, continue engine operation. If out of limits, execute the Emergency Shutdown procedure. |
|
|
PROP PUMP No. 1 light (1,
2, 3, or 4 engine) on. |
If either or both propeller pump caution
lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12. |
|
|
PROP PUMP No. 2 light
|
If either or both propeller pump caution
lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12. |
|
|
FUS DUCT HOT light on
|
*1. On ground, secure ground
air‐conditioning and all engine and APU bleed air, and return to the line. *2. In flight, close all engine bleed and fuselage shutoff valves. 3. If light remains on, dump EDCs one at a time. 4. If light remains on, land as soon as possible. |
|
|
CABIN PRESS light on.
|
Refer to Pressurization Loss,
paragraph 12.4. |
|
|
Master DE‐ICING light on.
|
Look for cause in deicing systems on
overhead anti‐icing control panel. Activate system or secure if necessary. Reset for continued warning protection. Get out of icing area if system is critical and inoperative. |
|
|
Master ELEC POWER light
on. |
Locate fault on overhead panel.
Secure faulty system. Reset for continued warning protection. |
|
|
Master PRESS SYSTEM
light on. |
Locate fault on overhead panel.
Secure faulty system. Reset for continued warning protection. |
|
|
Master RACK OVHT light
on. |
Initiate Fire of Unknown Origin
checklist/procedures. Locate overheated electronic bay(s) by illuminated individual bay overheat light(s). Provide required cooling or secure equipment as necessary. |
|
|
START VALVE light on.
|
*1. Check overhead panel for
individual engine start control valve open light. |
|
|
FLAP ASYM light on.
|
a. If accompanied by a
change in flight characteristics, refer to split flap Procedures, paragraph 16.6. b. If not, place flap handle in position best corresponding to flap position. c. Execute split flap Procedures. |
|
|
DOOR OPEN light on.
|
Lock the door.
|
|
|
RUDDER POWER light on
(flaps up). |
Actuate rudder pedals to deplete
residual No. 2 hydraulic system pressure in the rudder boost package. If the light remains on: a. Check the rudder boost shutoff valve circuit breaker on MEDC. b. Turn off the No. 2 hydraulic pump. If the warning light goes out, the shutoff valve is inoperative. Turn the No. 2 hydraulic pump on and make no abrupt rudder movements. |
|
|
No. 1 or 1A HYD PRESS
light on. |
Turn off the respective pump;
investigate. Note Gear retraction with one operable hydraulic pump may result in indication of hydraulic system failure and unsafe gear due to heavy system demand. |
|
|
No. 2 HYD PRESS light
on. |
Check No. 2 system pressure. If low,
secure No. 2 pump. |
|
|
No. 1, 1A, or 2 HYD OIL
HOT light on. |
Turn off respective pump.
|
|
|
NTS INOPR.
|
*1. Continue holding out on
feather button. (FE) *2. Emergency Shutdown handle — Pull. (FE) *3. Feather button — Push. (FE) |
|
|
ICING light on.
|
Anticipate icing conditions.
|
