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92 Cards in this Set
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GEN 2 or GEN 3, GEN 4 or APU GEN OFF light on |
Generator failure, off frequency, overvoltage, undervoltage, feeder fault, supervisory panel failure, transfer relay 2 or 3 failure, or associated bus monitoring switch OFF. |
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. |
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TRANSFORMER RECTIFIER OVERHEAT
light on. |
Transformer Rectifier (TR) overheated.
--- Pull respective circuit breaker; No. 3 located at the flight station and Nos. 1 and 2 located at the main load center. |
Pull respective circuit breaker; No. 3 located at the flight station and Nos. 1 and 2 located at the main load center.
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EXTERNAL PWR AVAILABLE light on (neon).
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Indicates electrical power is connected to the aircraft.
--- Light will glow whether or not external power is selected. |
Light will glow whether or not external power is selected.
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EXTERNAL PWR AVAILABLE light on (neon), but no power into aircraft.
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Wrong phase, nosegear uplock not properly positioned, battery not connected, generator No. 4 runaround feeder circuit breaker out, external power control circuit breaker out.
--- Move EXTERNAL POWER switch to RESET then ON. Check nosegear uplock position. Check battery condition. Check No. 4 runaround feeder circuit breaker. Check external power control circuit breaker. |
Move EXTERNAL POWER switch to RESET then ON. Check nosegear uplock position. Check battery condition. Check No. 4 runaround feeder circuit breaker. Check external power control circuit breaker.
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EXTERNAL PWR AVAILABLE light on partial power into aircraft.
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Transformer-rectifier No. 3 ganged circuit breaker out. ESSENTIAL DC BUS FEEDER circuit breaker No. 2 out. Monitorable Essential AC ganged circuit breaker behind copilot out. Monitorable Essential BUS switch off. (MEET)
--- 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. |
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.
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EXTERNAL POWER light on.
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External power supplying power to aircraft system.
--- EXTERNAL POWER switch is ON. |
EXTERNAL POWER switch is ON.
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No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light on during start (between 16 percent and 65 percent rpm).
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Indicates the secondary fuel pump is functioning properly.
--- n/a |
n/a
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No. 1, 2, 3, or 4 PRIMARY FUEL PUMP (parallel) light off during start (between 16 percent and 65 percent rpm).
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Failure of secondary pump. (or paralleling valve solenoid, or FSV popped right after lightoff, or it was quick and you just missed it)
--- Investigate. |
Investigate.
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No. 1, 2, 3, or 4 PRIMARY FUEL PUMP light on, or momentarily on then off, above 65 percent rpm.
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a. Failure of the primary pump.
b. Fuel pumps are in parallel operation possibly due to a speed sense control malfunction. --- Pull FUEL SHUTOFF VALVE circuit breaker on START ESSENTIAL DC BUS. 2 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 T.I.T. 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. |
Pull FUEL SHUTOFF VALVE circuit breaker on START ESSENTIAL DC BUS. 2
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. 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. |
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No. 1, 2, 3, and 4 AUTO FEATHER lights are all on
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The automatic feathering circuit has been armed.
--- n/a |
n/a
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No. 1, 2, 3, or 4 AUTO FEATHER light on individually.
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Propeller thrust has dropped to less than 500 pounds of positive thrust; propeller has automatically feathered.
--- Investigate. |
Investigate.
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No. 1, 2, 3, or 4 engine STARTER CONTROL VALVE OPEN light on.
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Engine starter control valve is open. (Valve should close and light go out when starter button is pulled out at 57 to 64 percent rpm during normal start.)
--- *If light remains on or comes on after start, secure engine by pulling emergency shutdown handle. |
If light remains on or comes on after start, secure engine by pulling emergency shutdown handle.
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No. 1, 2, 3, or 4 prop feather button light remains on.
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Indicates feather pump relay is closed, supplying electrical power to the feather pump.
Possible internal leakage. Incomplete pump cut-out circuit. --- a. If light remains on following engine shutdown, pull respective propeller feather control circuit breaker, 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. |
a. If light remains on following engine shutdown, pull respective propeller feather control circuit breaker, 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. |
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FAN OUT light on.
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Cabin exhaust fan is inoperative or lack of airflow.
--- Open equipment doors for additional cooling. Use minimum electronic equipment. If EDCs are inoperative (no air-conditioning available), open AUX vent. |
Open equipment doors for additional cooling. Use minimum electronic equipment. If EDCs are inoperative (no air-conditioning available), open AUX vent.
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EDC TEMP HIGH light on.
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EDC oil temperature excessive. Low oil level in sump. High engine oil temperature.
--- 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. |
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. |
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EDC PRESS LOW light on.
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EDC oil pressure is low. Low level in sump. EDC drive shaft sheared.
--- 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. |
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. |
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REFR OVHT (overheat) light on.
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Temperature in cooling duct exceeds safe limits. On ground: inoperative heat exchanger blower fan.
--- 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. |
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. |
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L WING HOT or R WING HOT light on.
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Air temperature in the wing plenum area exceeds safe limits. May be caused by a leak in the bleed air manifold or EDC plumbing.
--- a. Secure wing deicing and get out of icing area. b. If light remains on, dump appropriate EDC. |
a. Secure wing deicing and get out of icing area.
b. If light remains on, dump appropriate EDC. |
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LEAK TEST ACCEPT light.
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n/a
--- Maintenance function. Refer to appropriate maintenance manuals. |
Maintenance function. Refer to appropriate maintenance manuals.
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No. 1, 2, 3, and 4 engine bleed air valve OPEN lights on.
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When the valve begins to open, the light will be on. When the valve is closed, the light should be off.
--- n/a |
n/a
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Left and right FUS BLEED AIR SHUT-OFF valve OPEN lights on.
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When the valve begins to open, the light is on. When the valve is closed, the light should be off.
--- n/a |
n/a
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LE HOT light on.
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The wing leading edge skin temperature has increased in excess of 110 °C. One of the six modulating valves is either stuck open or improperly modulating.
--- 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. (also check the CBs on EMDC) |
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.
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EMP DE-ICE light on.
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Parting strip power relay deenergized, cycling power relay deenergized, control relay deenergized, timer motor failure, empennage overheat condition. Open control power circuit breaker. (TOP CCC)
--- Turn switch OFF (2-3 seconds) then ON. If light remains on, turn switch OFF, increase airspeed above 200 KIAS (check CB on EMDC); vacate icing area. If light does not come back on, a temporary overheat exists. Continue operation. |
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.
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No. 1, 2, 3, or 4 engine ANTI-ICING advisory light on with control switch on.
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Fourteenth stage air of sufficient temperature to melt ice has entered the torquemeter shroud and the inlet scoop.
--- n/a |
n/a
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No ANTI-ICING advisory light with control switch on.
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One or both areas of system may not be receiving hot air.
--- 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, T.I.T., 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. |
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. |
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ANTI-ICING advisory light on and control switch off.
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a. Abnormal heat in the area.
b. Loss of electrical power to the solenoid valve. --- 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. |
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. |
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ANTI-ICING advisory light remains on after system utilization.
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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 abnormal indications exist, engine operation may be continued for the remainder of the flight. |
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.
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Windshield heat CYCLING lights on (neon).
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Indicates that electrical power is being supplied to the windshield panels. When lights are out, electrical power is cycled off. (keeps temp between 90 to 100 F)
--- If unable to start cycling on a cold windshield, use OVERRIDE switch. |
If unable to start cycling on a cold windshield, use OVERRIDE switch.
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Side windshield heat FAIL light on.
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Windshield power relay and/or overheat control relay stuck in energized position when control switch off.
--- Pull side windshield heat power circuit breaker on main AC BUS A. |
Pull side windshield heat power circuit
breaker on main AC BUS A. |
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L or R HTR OUT pitot heat out light on.
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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. |
Check respective circuit breaker and bus. Monitor equipment for proper operation.
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No. 1, 2, 3, or 4 feather valve and NTS lights on, switch in NTS position.
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NTS has occurred.
--- Reset by putting switch to FEATHER VALVE position and back to NTS position. |
Reset by putting switch to FEATHER VALVE position and back to NTS position.
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No. 1, 2, 3, or 4 feather valve and NTS lights on, switch in FEATHER VALVE position.
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Feather valve is being mechanically positioned to the feather position by NTS action during an NTS check (flashing light), or by the emergency shutdown handle when pulled (steady light).
--- n/a |
n/a
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BOMB BAY COLD light on.
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Temperature below desired level in bomb bay. (-5 C)
--- Turn BOMB BAY HEAT switch ON (autocycling), open No. 3 or No. 4 engine bleed air valve. |
Turn BOMB BAY HEAT switch ON (autocycling), open No. 3 or No. 4 engine bleed air valve.
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BOMB BAY HOT light on.
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Temperature above desired level, not cycling. (+54 C)
--- Turn BOMB BAY HEAT switch OFF until light goes out, then heat bomb bay with switch in OVRD position. Monitor for proper operation. |
Turn BOMB BAY HEAT switch OFF until light goes out, then heat bomb bay with switch in OVRD position. Monitor for proper operation.
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APU DOORS light on.
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Intake or exhaust door open. (Should close when APU is shut down.)
--- Do not exceed 225 KIAS. |
Do not exceed 225 KIAS.
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APU ARMED light on.
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Arming switch on.
--- If APU is not being used in flight, turn arming switch off. |
If APU is not being used in flight, turn arming switch off.
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No. 1, 2, 3, or 4 FILTER light on.
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One or both of the low pressure fuel filters are restricting flow.
--- If engine continues to function normally, continue engine operation. |
If engine continues to function normally, continue engine operation.
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No. 1, 2, 3, or 4 PRESS LOW light on.
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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 pressure switch. --- 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. |
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. |
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No. 1, 2, 3, or 4 TANK shutoff valve advisory lights on.
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Light will 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. |
Investigate.
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No. 1, 2, 3, or 4 XFEED valve advisory lights on.
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Light will 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. |
Investigate.
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Cross−ship X FEED valve advisory light on.
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Light will 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. |
Investigate.
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Fuel RESET advisory light on.
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Light will illuminate whenever the refuel control panel has control of the transfer valves, which are also used to refuel tank Nos. 1, 2, 3, 4.
--- Push reset button to regain control of transfer valves. |
Push reset button to regain control of transfer valves.
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Tank BOOST pump low pressure advisory light on.
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Light will illuminate whenever the output pressure of the corresponding boost pump is low.
--- Refer to Fuel Boost Pump Failure, paragraph 15.8.2. |
Refer to Fuel Boost Pump Failure, paragraph 15.8.2.
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Transfer pumps PRESS LOW advisory lights on.
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Tank No. 5 is empty or pump output pressure is low.
--- Shut off respective pump; refer to Transfer Pump Failure, Tank 5, paragraph 15.8.3. |
Shut off respective pump; refer to Transfer Pump Failure, Tank 5, paragraph 15.8.3.
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GEN mechanical failure light No. 2, 3, or 4 on (steady or intermittent).
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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 Shutdown procedure, paragraph 15.5.1. |
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.
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CHIPS light No. 1, 2, 3, or 4 on (steady or intermittent).
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Metal particles on magnetic plug in power section or gearbox.
--- 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. |
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.
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OIL HOT light No. 1, 2, 3, or 4 engine on.
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Engine oil temperature 100 °C or over.
--- 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. |
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.
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OIL PRESS light No. 1, 2, 3, or 4 engine on.
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Either engine oil pressure is below 40 psi or gearbox pressure below 130 psi.
--- 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. |
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.
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PROP PUMP No. 1 light (1, 2, 3, or 4 engine) on.
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Reduced flow and drop in pressure from prop pump 1 due to pump failure, obstruction, or low oil level.
--- If either or both propeller pump caution lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12. |
If either or both propeller pump caution lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12.
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PROP PUMP No. 2 light (1, 2, 3, or 4 engine) on.
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Reduced flow and drop in pressure from prop pump 2 due to pump failure, obstruction, or low oil level.
--- If either or both propeller pump caution lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12. |
If either or both propeller pump caution lights illuminate: Continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12.
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BETA light No. 1, 2, 3, or 4 prop on.
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Blade angle at 10° or less.
--- n/a |
n/a
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FUS DUCT HOT light on.
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Leak in area around crossship manifold, creating excessive temperature. Can be caused by a leak in the bleed air manifold, APU bleed air lines, or EDC plumbing.
--- *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. |
*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. |
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CABIN PRESS light on.
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Light on at cabin altitude 10,000 (±500) feet. CABIN PRESS light out by 8,000 feet on descent.
--- Refer to Pressurization Loss, paragraph 12.4. --- 12.4: If cabin altitude exceeds 10,000 ft, the flight station shall: *1. Don smoke masks. *2. Alert the crew. |
Refer to Pressurization Loss, paragraph 12.4.
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Master DE-ICING light on.
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Alert or fault in deicing system or bomb bay heating system (L or R WING HOT, LE HOT, EMP DEICE, L or R pitot heater, or BOMB BAY HOT or COLD).
--- 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. |
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.
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Master ELEC POWER light on.
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Generator No. 2, 3, or 4 OFF light is on. Overheat of TR No. 1, 2, or 3.
--- Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection. |
Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection.
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Master PRESS SYSTEM light on.
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Oil pressure low or oil temperature high on left or right EDC. Cabin exhaust fan inoperative. Refrigeration duct overheat warning.
--- Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection. |
Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection.
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Master RACK OVHT light on.
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Electronic rack overheat condition exists. Also comes on during MAIN DC BUS failure. The ASH-33 (DMTS) will cause a rack overheat indication when the system is initially turned on, or will illuminate continuously when a loss of airflow is detected.
--- 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. |
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.
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IFF light on. (Operational only if KIT-C transponder computer is installed.)
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Mode 4 zeroized, self-test function of computer has detected a faulty computer, transponder not replying to proper Mode 4 interrogations.
--- 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. |
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.
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Vertical START VALVE light on.
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Indicates one of the four engine start control valves is open.
--- *1. Check overhead panel for individual engine start control valve open light. |
*1. Check overhead panel for individual engine start control valve open light.
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AUTOPILOT/RAWS flashing red warning lights (glareshield) with synchronized tone.
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RAWS warning: Loss of ac power to radar altimeter. Unreliable radar altimeter signal. Aircraft descending through 380 (±20) feet (3-second warning) or 170 (±10) feet (continuous warning). (All warnings are canceled when nosegear is down and locked or flap handle is below MANEUVER.)
--- If warning is abnormal, investigate. |
If warning is abnormal, investigate.
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FLAP ASYM light on.
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Flap asymmetry system has tripped. If there has been a multiple flap component failure, the flaps may still be moving or could be moved by use of the flap handle.
--- a. If accompanied by a change in flight characteristics, execute Split−Flap Procedures, paragraph 16.6. b. If not, place flap handle in position best corresponding to flap position. c. Refer to Split−Flap Procedures. |
a. If accompanied by a change in flight
characteristics, execute Split−Flap Procedures, paragraph 16.6. b. If not, place flap handle in position best corresponding to flap position. c. Refer to Split−Flap Procedures. |
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DOOR OPEN light on.
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Cabin door (either section), hydraulic service center door is not locked.
--- Lock the door. |
Lock the door.
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RUDDER POWER light on (flaps up).
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No. 1 hydraulic system pressure failure. Shutoff valve has opened.
--- 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. 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. |
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. 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. |
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No. 1 or 1A HYD PRESS light on.
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Respective pump output pressure is below 1,800 psi.
--- 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. |
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. |
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No. 2 HYD PRESS light on.
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No. 2 pump output pressure is below 1,800 psi.
--- Check No. 2 system pressure. If low, secure No. 2 pump. |
Check No. 2 system pressure. If low, secure No. 2 pump.
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No. 1, 1A, or 2 HYD OIL HOT light on.
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Hydraulic oil temperature is excessive, restricted coolant flow, not enough fuel in respective inboard fuel tank (minimum 1,000 lb).
--- Turn off respective pump. |
Turn off respective pump.
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NTS INOPR.
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Inoperative NTS system.
--- *1. Continue holding out on feather button. (FE) *2. Emergency shutdown handle — Pull. (FE) *3. Feather button — Push. (FE) |
*1. Continue holding out on feather button. (FE)
*2. Emergency shutdown handle — Pull. (FE) *3. Feather button — Push. (FE) |
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ICING light on.
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Indicates the ice detector probe is accumulating ice. The frequency of the light cycling indicates the amount of ice buildup. Long “off” period indicates a slow buildup. Light may illuminate at high angles of attack.
--- Anticipate icing conditions. |
Anticipate icing conditions.
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BOMB BAY cue light on.
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Cue to move BOMB BAY switch to opposite position.
--- Move BOMB BAY switch to opposite position. |
Move BOMB BAY switch to opposite position.
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ARM HAZARD light on.
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Energized buffer relay.
--- Go to RESET. If light remains on, use offline mode for weapon release. |
Go to RESET. If light remains on, use offline mode for weapon release.
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SONO DISABLED light on.
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Sonobuoy circuit disabled.
--- Close sonobuoy disable door prior to taxi. |
Close sonobuoy disable door prior to taxi.
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Boldface: Vertical START VALVE light on.
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Indicates one of the four engine start control valves is open.
--- *1. Check overhead panel for individual engine start control valve open light. |
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Boldface: No. 1, 2, 3, or 4 engine STARTER CONTROL VALVE OPEN light on.
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*If light remains on or comes on after start, secure engine by pulling emergency shutdown handle.
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Boldface: FUS DUCT HOT light on.
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*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. |
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Boldface: NTS INOPR light on.
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*1. Continue holding out on feather button. (FE)
*2. Emergency shutdown handle — Pull. (FE) *3. Feather button — Push. (FE) |
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Boldface: FUSELAGE FIRE OR ELECTRICAL FIRE OF UNKNOWN ORIGIN
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*1. Alert crew, activate fire bill — Alerted. (CP, TC)
*2. Cabin exhaust fan — OFF. (FE) |
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Boldface: PRESSURIZATION LOSS
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If cabin altitude exceeds 10,000 feet, the flight station shall:
*1. Don smoke masks. *2. Alert crew. |
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Boldface: Rapid Decompression
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In the event of a scissor switch failure and loss of associated aircraft system functions, perform the following steps:
*1. Pressurization ground check switch — TEST. (FE) *2. Ground air-conditioning switch — ON. (FE) |
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Boldface: Emergency Depressurization Procedure
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With electrical power available:
*1. AUX VENT — OPEN. (FE) *2. OUTFLOW VALVE — OPEN. (FE) *3. EDCs — DUMP. (FE) *4. AUX VENT — Close at 1-inch differential. (FE) Without electrical power available: *5. FREE-FALL CHUTE — Open. (OBS) |
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Boldface: Emergency Descent Procedure
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*1. Autopilot — Disengaged. (P)
*2. Power levers— FLIGHT IDLE. (P) *3. Landing gear lever — As required. (CP) *4. Airspeed — As required. (P) *5. Pressurization — As required. (FE) |
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Boldface: Ditching Procedures
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*1. Alert crew time to impact — Alerted. (CP)
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Boldface: BRAKE FIRE
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*1. Request ground firefighting equipment. (CP)
*2. Stop the aircraft. (P) |
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Boldface: ENGINE FIRE ON THE GROUND
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*1. Emergency shutdown handle — Pull. (FE)
*2. HRD — Discharged. (P, FE) |
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Boldface: Emergency Shutdown Procedure
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*1. Emergency shutdown handle (on pilot command) — Pull. (FE)
*2. HRD (fire only) — Discharged. (P, FE) |
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Boldface: Shifting to Boost Off
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*1. Disconnect the autopilot.
*2. Attempt to obtain a safe altitude. *3. Set Condition V. *4. Trim tab setting — Check for normal position. If abnormal force is still present: *5. Booster shift handle — Pull. |
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Boldface: Propeller Malfunctions
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*1. If rpm at or above 115 percent — Reduce airspeed (150 KIAS minimum) and perform Operation with a Pitchlocked Propeller procedure, paragraph 15.12.2. (P, FE)
*2. If rpm below 115 percent — Smoothly advance power lever(s) toward cruise conditions and increase TAS, noting engine indications (normal rated power if range is a factor). (P, FE) |
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Boldface: Propeller Fails to Feather
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*1. Feather button — In.
*2. PCO — Press. *3. Alternate bus (propellers 1 and 4) — Select. *4. PROP FEATHER circuit breakers — Check in. *5. Airspeed — Decrease toward 150 KIAS. If feather button light remains on: *6. PROP FEATHER CONT circuit breaker — Pull. |
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Boldface: Flight with Cracked Front Windshield
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*1. Turn off heat of affected panels.
*2. Helmets on, visors down. (P, CP, FE) |
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Boldface: LOSS OF ALL AIRSPEED INDICATION
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*1. Check pitot heat — ON. (FE)
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Boldface: OUT OF CONTROLLED FLIGHT, SPIRAL AND SPIN RECOVERY
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*1. Power levers — FLIGHT IDLE. (P)
*2. Flight controls — Neutralize. (P) *3. Airspeed, AOA, turn needle — Check. (P) If in a spin: *4. Rudder — Full opposite turn needle. (P) As soon as yawing motion stops: *5. Controls — Neutralize. (P) *6. Unusual attitude — Recover. (P) |
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Boldface: Windshear Escape Procedure
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*1. Max power — Set. (P, FE)
*2. Pitch attitude — 10 up. (P) *3. Landing gear — UP. (P, CP) *4. FLAPS — Do not change until out of windshear. (P) |
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Boldface: SPLIT FLAP PROCEDURES
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*1. If uncontrollable, reset the flap handle to the previous position.
*2. If controllable, land with the flap handle in the selected position. |
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