P-3 Orion Lights

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  1. GEN 2, GEN 3, GEN 4, OR APU GEN OFF LIGHT
    • Probable Cause: Generator failure, Off frequency, Over Voltage, Feeder Fault, Transfer Relay 2 or 3 failure, Under voltage, Bus monitoring switch OFF, Supervisory Panel Failure. (GOOFTUBS)
    • N: 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.
    • Action: 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.
    • C: Generator supervisory panels shall not be exchanged until appropriate maintenance actions are performed
    • N: Ensure GEN 4 AUX CONT and GEN 4 TRANS Circuit Breakers are set appropriately.
    • Power Sources: Gen Control Circuit Breakers – MON D
  2. TRANSFORMER RECTIFIER OVERHEAT LIGHT ON
    • Probable Cause: Transformer Rectifier (TR) Overheated
    • Action: Pull respective circuit breaker; No. 3 located at the flight station and No. 1 and 2 located at the main load center.
    • Power Sources: No. 1 – Bus A, No.2 - Bus B, No. 3 - Mon AC
  3. EXTERNAL PWR AVAILABLE LIGHT ON (neon) A)... But no power into aircraft B)... Partial Power into aircraft
    • Probable Cause: Indicates electrical power is connected to the aircraft
    • Action: Light will glow whether or not external power is selected.
    • A) Probable Cause: Wrong phase, nose gear uplock not properly positioned, battery not connected, Gen No. 4 runaround feeder CB out, external power control CB out.
    • Action: Move External Power switch to Reset then ON. Check nose gear uplock position. Check battery condition. Check No. 4 runaround feeder CB. Check external power control circuit breaker.
    • B) Probable Cause: TR No. 3 ganged circuit breaker out. Essential DC bus feeder circuit breaker No. 2 out. Mon AC ganged circuit breaker behind copilot out. Mon Essential Bus switch off.
    • Action: Check TR 3 CB. Check essential DC feeder CB No. 2. Check Mon AC ganged CB in. Check Mon essential bus switch.
    • Power Sources: TR3 – Mon AC; EXT PWR CONT – GOB;
  4. EXTERNAL POWER LIGHT ON
    • Probable Cause: External power supplying power to aircraft system.
    • Action: External Power switch is on Power
    • Sources: External Power switch - GOB
  5. PRIMARY FUEL PUMP (parallel light) on No. 1, 2, 3, or 4 PRIMARY FUEL PUMP light on during start between 16 and 65 rpm
    • Probable Cause: Indicates the secondary fuel pump is functioning properly.
    • If not on during start:Probable Cause – Failure of secondary pump.
    • Action – Investigate
  6. NO. 1, 2, 3, OR 4 PRIMARY FUEL PUMP light on, or momentarily ON then OFF above 65 rpm
    • Probable Cause: A) Failure of the primary pump. B) Fuel pumps are in parallel possibly due to a speed sense control malfunction.
    • Action: Pull Fuel Shutoff valve circuit breaker on Start 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% switch or the speed sense control.
    • N: If mission is continued: Do not use autofeather. Should max TIT be limited to approx. 830 C with or without the parallel light, assume a failure of the 94% switch or speed sense control. Place affected TD switch to null and pull the fuel shutoff valve CB on Start DC. 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 swith
  7. NO. 1,2,3, AND 4 AUTO FEATHER lights are all on
    Probable Cause: The automatic feathering circuit has been armed.
  8. NO. 1, 2, 3, OR 4 AUTO FEATHER light on individually.
    • Probable Cause: Propeller thrust has dropped to less than 500 pounds of positive thrust; propeller has automatically feathered.
    • Action: Investigate
    • Power Sources: Auto-feather – EMDC
  9. NO. 1, 2, 3, OR 4 ENGINE STARTER CONTROL VALVE OPEN light on
    • Probable Cause: Engine starter control valve is open. (Valve should
    • close and light go out when started button is pulled out at 57 to 64%
    • rpm during normal start)
    • Action: * If light remains on or comes on after start, secure engine by pulling the emergency shutdown handle.
  10. NO. 1, 2, 3, OR 4 prop feather button light remains on
    • Probable Cause: Indicates feather pump relay is closed, supplying
    • electrical power to the feather pump. Possible internal leakage.
    • Incomplete pump cut-out circuit.
    • Action: If light remains on following engine shutdown, pull respective propeller feather control circuit breaker, and execute the emergency shutdown procedure, paragraph 15.5.1. If light remains on following pressure cutout override, refer to In-flight Restart Procedures, paragraph 8.33.1.
    • Power Sources: Prop feather cont -- MEEM
  11. FAN OUT light on
    • Probable Cause: Cabin exhaust fan is inoperative or lack of airflow.
    • Action: Open equipment doors for additional cooling. Use minimum electronic equipment. If EDCs are inoperative (no cooling airflow available), open AUX vent.
    • Power Sources: Cabin Exhaust Fan – Bus B, EMDC; AUX Vent – Mon AC
  12. EDC TEMP HIGH light on
    • Probable Cause: EDC oil temperature excessive. Low oil level in sump. High engine oil temperature.
    • Action: a) Check engine oil temperature; if high, correct. B) If unable to control, disconnect, monitor for loss of spread, dump, continue operation.
    • C: 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 paragraph 15.16
  13. EDC PRESS LOW light on
    • Probable Cause: EDC oil pressure is low. Low level in sump. EDC driveshaft sheared.
    • Action: 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.
    • C: 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. If the engine is allowed to operate due to a greater emergency the EDC should be dumped.
    • N: 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 paragraph 15.16
  14. REFR OVHT (overheat) light on
    • Probable Cause: Temperature in cooling duct exceeds safe limits. On ground:inoperative heat exchanger blower fan.
    • Action: In flight, dump EDC. After light is out, operation is permitted in 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 CBs on Mon DC. If CBs are set and the light is out, operation is permitted in the manual mode two dot position or warmer.
    • Power Sources: EDC Disconnect and Dump – Mon DC
  15. L WING HOT OR R WING HOT light on
    • Probable Cause: Air temperature in the wing plenum area exceeds safe
    • limits. May be caused by a leak in the bleed air manifold or EDC
    • plumbing.
    • Action: a) Secure wing deicing and get out of icing area b) If light emains on, dump appropriate EDC
  16. NO. 1, 2, 3, AND 4 engine bleed air valve OPEN lights on
    • Probable Cause: When the valve begins to open, the light will be on. When the valve is closed, the light should be off
    • Power Sources: Bleed Air Valves – SDC
  17. Left and right FUS BLEED AIR SHUT-OFF 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
    • Power Sources: Bleed Air Valves – SDC
  18. LE HOT light on
    • Probable Cause: 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.
    • Action: 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.
    • Power Sources: Modulating Valves – EMDC
  19. EMP DE-ICE light on
    • Probable Cause: Parting strip power relay deenergized, cycling power
    • relay deenergized, control relay deenergized, timer motor failure,
    • empennage overheat condition, Open control power circuit breaker.
    • Action: 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.
    • Power Sources: Parting Strips – Bus A; Cycling Power – Bus B; Timer motor – Mon AC
  20. ANTI-ICING light a) No. 1, 2, 3, or 4 engine ANTI-ICING advisory light on with control switch on. b) No ANTI-ICING advisory light with control switch on
    • A) Probable Cause: Fourteenth stage air of sufficient temperature to
    • melt ice has entered the torquemeter shroud and the inlet scoop.
    • B) Probable Cause: One or both areas of system may not be receiving hot air.
    • Action:
    • 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, TIT, 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
  21. ANTI-ICING advisory light on and control switch off.
    • Probable Cause: a) Abnormal heat in the area. b) Loss of electrical power to the solenoid valve.
    • Action: 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.
  22. ANTI-ICING advisory light remains on after system utilization
    • Probable Cause: Failure of one or both thermal switches and/or anti-icing valves.
    • Action: 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
  23. Windshield heat CYCLING lights on (neon)
    • Probable Cause: Indicates that electrical power is being supplied to the
    • windshield panels. When lights are out, electrical power is cycled off.
    • Action: If unable to start cycling on a cold windshield use OVERRIDE switch.
    • Power Sources: Windshield Heat – Mon AC; Windshield Heat Cont – Mon DC
  24. Side windshield heat FAIL light on
    • Probable Cause: Windshield power relay and/or overheat control relay stuck in energized position when control switch off.
    • Action: Pull side windshield heat power circuit breaker on main AC Bus A
  25. L or R HTR OUT pitot heat out light on.
    • Probable Cause: Indicates electrical current flow to the pitot heater
    • element has been interrupted, or current flow detector is inoperative.
    • Action: Check respective circuit breaker and bus. Monitor equipment for proper operation.
    • Power Sources: Pilot Pitot Heat – Flight AC; Co-pilot pitot heat – 28V FLB
  26. No. 1, 2, 3, or 4 feather valve and NTS lights on A) Switch in NTS position. B) Switch in FEATHER VALVE position
    • A) Probable Cause: NTS has occurred
    • Action: Reset valve by putting switch to FEATHER VALVE position and back to NTS position
    • B) Probable Cause: 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)
    • Action: Reset valve by putting switch to FEATHER VALVE position and back to NTS position
  27. BOMB BAY COLD light on
    • Probable Cause: Temperature below desired level in bomb bay.
    • Action: Turn bomb bay heat switch ON (auto-cycling), open No. 3 or 4 engine bleed air valve
    • Power Sources: Bomb Bay heat Cont – MDC
  28. BOMB BAY HOT light on
    • Probable Cause: Temperature above desired level, not cycling
    • Action: Turn BOMB BAY HEAT switch off until light goes out, then heat bomb bay with switch in IVRD position. Monitor for proper operation
  29. DOORS light on
    • Probable Cause: Intake or exhaust door open. (Should close when APU is shut down.)
    • Action: Do not exceed 225 KIAS
    • Power Sources: APU Doors – APU ESS
  30. ARMED light on
    • Probable Cause: Arming switch on
    • Action: If APU is not being used in flight, turn arming switch off
  31. No. 1, 2, 3, or 4 FILTER light on
    • Probable Cause: One or both of the low pressure fuel filters are restricting flow.
    • Action: If engine continues to function normally, continue engine operation
  32. No. 1, 2, 3, or 4 PRESS LOW light on
    • Probable Cause: Indicates the differential pressure across the
    • corresponding engine driven centrifugal boost pump is low. A flickering
    • light indicates a partial obstruction of the fuel line.
    • N: The FUEL PRESS LOW light should be out by low rpm. After start, possible faulty or stuck pressure switch.
    • Action: 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 visible, cycle respective boost pump of shift engine to normal rpm then back to low rpm. If light goes out and remains out, continue operation
  33. No. 1, 2, 3, or 4 TANK shutoff valve advisory lights on
    • Probable Cause: 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.
    • Action: Investigate
  34. No. 1, 2, 3, or 4 XFEED valve advisory light on
    • Probable Cause: 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.
    • Action: Investigate.
  35. Cross ship X FEED valve advisory light on
    • Probable Cause: 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.
    • Action: Investigate.
  36. RESET advisory light on
    • Probable Cause: Light will illuminate whenever the refuel control panel has control of the transfer valves, which are also used to refuel tanks No. 1, 2, 3, and 4
    • Action: Push reset button to regain control of transfer valves
  37. Tank BOOST pump low pressure advisory light on
    • Probable Cause: Light will illuminate whenever the output pressure of the corresponding boost pump is low.
    • Action: Refer to Fuel Boost Pump Failure, paragraph 15.8.2
  38. Transfer pumps PRESS LOW advisory light on.
    • Probable Cause: Tank No. 5 is empty or pump output pressure is low.
    • Action: Shut off respective pump; refer to Transfer Pump Failure, Tank 5, paragraph 15.8.3
  39. GEN mechanical failure light No. 2, 3, or 4 on (steady or intermittent).
    • Probable Cause: Primary generator drive end bearing has failed.
    • Action: 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
  40. CHIPS light No. 1, 2, 3, or 4 on (steady or intermittent).
    • Probable Cause: Metal particles on magnetic plug in power section or gearbox.
    • Action: 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
  41. OIL HOT light No. 1, 2, 3, or 4 engine on
    • Probable Cause: Engine oil Temperature 100 C or over.
    • Action: 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.
    • Power Sources: Oil cooler flaps – Mon AC
  42. OIL PRESS light No. 1, 2, 3, or 4 engine on
    • Probable Cause: Either engine oil pressure is below 40 psi or gearbox pressure below 130 psi
    • Action: 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.
  43. PROP PUMP No. 1 light (1, 2, 3, or 4 engine) on
    • Probable Cause: Reduced flow and drop in pressure from prop pump 1 due to pump failure obstruction or low oil level.
    • Action: If either or both propeller pump caution lights illuminate: continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12
  44. PROP PUMP No. 2 light (1, 2, 3, or 4 engine) on
    • Probable Cause: Reduced flow and drop in pressure from prop pump 2 due to pump failure obstruction or low oil level.
    • Action: If either or both propeller pump caution lights illuminate: continue normal engine operation and refer to Propeller Malfunctions, paragraph 15.12
  45. BETA light No. 1, 2, 3, or 4 prop on
    Probable Cause: Blade angle at 10 degrees or less
  46. FUS DUCT HOT light on.
    • Probable Cause: Leak in are around cross ship manifold, creating excessive temperature. Can be caused by a leak in the bleed air manifold, APU bleed air lines, or EDC plumbing.
    • Action:
    • *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 valves.
    • 3. If light remains on, dump EDC’s one at a time
    • 4. If light remains on, land as soon as possible
  47. CABIN PRESS light on
    • Probable Cause: Light on at cabin altitude 10,000 (+/- 500 feet). CABIN PRESS light out by 8,000 feet on descent.
    • Action: Refer to Pressurization Loss, paragraph 12.4
  48. Master DE-ICING light on
    • Probable Cause: 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).
    • Action: 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.
  49. Master ELEC Power light on
    • Probable Cause: Generator No. 2, 3, or 4 OFF light is on. Overheat of TR No. 1, 2, or 3.
    • Action: Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection.
  50. Master PRESS SYSTEM light on
    • Probable Cause: Oil pressure low or oil temperature high on left or right EDC. Cabin exhaust fan inoperative. Refrigeration duct overheat warning.
    • Action: Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection.
  51. Master RACK OVHT light on
    • Probable Cause: Electronic rack overheat condition exists. Also comes on during main DC bus failure. The ASH-33 will cause a rack overheat indication when the system is initially turned on, or will illuminate continuously when a loss of airflow is detected.
    • Action: 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.
  52. IFF light on (Operational only if KIT-C transponder computer is installed)
    • Probable Cause: Mode 4 zeroized, self-test function of computer has detected a faulty computer, transponder not replying to proper mode 4 interrogations.
    • Action: Ensure MASTER switch in NORM mode 4 toggle switch ON and proper code selected. If light persists, fly selected operational procedure for inoperative tactical IFF.
  53. START VALVE light on
    a. During start sequence (normal)
    b. After start sequence or during engine operation (abnormal)
    • Probable Cause: Indicates one of the four engine start control valves is open.
    • Action: *1. Check overhead panel for individual engine start control valve open light. Power Sources: Start Control valve – SDC
  54. FLAP ASYM light on
    • Probable Cause: 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.
    • Action: A) If accompanied by a change in flight characteristics refer to Uncommanded Roll/Yaw Procedures, paragraph 16.6 B) If not place flap handle in position best corresponding to flap position. C) Execute Uncommanded Roll/Yaw Procedures.
    • Power Sources: Flap asym system: MDC
  55. DOOR OPEN light on
    • Probable Cause: Cabin door (either section), hydraulic service center door is not locked.
    • Action: Lock the door.
  56. RUDDER POWER light on (flaps up)
    • Probable Cause: No. 1 hydraulic system pressure failure. Shutoff valve has opened.
    • Action: 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.
    • Power Sources: Rudder Boost Shutoff Valve – Mon DC
  57. HYD PRESS light
    a) No. 1 or 1A HYD PRESS light on.
    b) No. 2 HYD PRESS light on.
    • Probable Cause: Respective pump output pressure is below 1,800 psi.
    • A) Action: Turn off the respective pump; investigate. N: Gear retraction with one operable hydraulic pump may result in indication of hydraulic system failure and unsafe gear due to heavy system demand.
    • B) Action: Check No. 2 system pressure. If low secure No. 2 pump.
  58. No. 1, 1A, or 2 HYD OIL HOT light on.
    • Probable Cause: Hydraulic oil temperature is excessive, restricted coolant flow, not enough fuel in respective inboard fuel tank (minimum 1,000 lb).
    • Action: Turn off respective pump
  59. NTS INOPR
    • Probable Cause: Inoperative NTS system.
    • Action:
    • *1. Continue holding out on feather button. (FE)
    • *2. Emergency Shutdown handle – PULL. (FE)
    • *3. Feather button – Push (FE)
  60. ICING light on
    • Probable Cause: 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.
    • Action: Anticipating icing conditions. Power Sources: Ice Detector – Mon AC
  61. BOMB BAY cue light on
    • Probable Cause: Cue to move BOMB BAY switch to opposite position.
    • Action: Move BOMB BAY switch to opposite position.
  62. ARM HAZARD light on
    • Probable Cause: Energized buffer relay.
    • Action: Go to RESET. If light remains on, use offline mode for weapon release.
  63. SONO DISABLED light on
    • Probable Cause: sonobuoy circuit disabled.
    • Action: Close sonobuoy disable door prior to taxi.
Author
ID
312865
Card Set
P-3 Orion Lights
Description
Lights
Updated
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