P-3 Lights

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Author:
donconquistador
ID:
214878
Filename:
P-3 Lights
Updated:
2014-06-04 17:46:17
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orion memory electrical
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Description:
lights with action and probable cause
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  1. GEN 2 or GEN 3, GEN 4 or APUGEN 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.

    • 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.

    -------------

    • Generator failure, off frequency, over voltage, under voltage, feeder fault, supervisory panel failure, transfer relay 2 or 3 failure, or associated bus monitoring switch OFF.
    • 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.
  2. 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.

    -----------------------

    Transformer Rectifier (TR) overheated .
  3. EXTERNAL PWR AVAILABLE light ON (neon)
    Light will glow whether or not external power is selected.

    --------------

    Indicates electrical power is connected to the aircraft.
  4. External Power 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.

    ----------

    Wrong phase, nosegear uplock not properly positioned, battery not connected, generator No. 4 runaround feeder circuit breaker out, external power control circuit breaker out.
  5. External Power 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.

    ------------

    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.
  6. No. 1, 2, 3, or 4 primary fuel pump (parallel) light on during start (between 16 percent and 65 percent RPM).
    Indicates the secondary fuel pump is functioning properly.

    No Action
  7. No. 1, 2, 3, or 4 primary fuel pump (parallel) light off during start (between 16 percent and 65 percent RPM).
    Investigate

    -------------

    Failure of secondary pump.
  8. 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 TIT 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.

    -----------------------

    a. Failure of the primary pump.b. Fuel pumps are in parallel operation possibly due to a speed sense control malfunction.
  9. No. 1, 2, 3, and 4 AUTO FEATHER lights are all on.
    The automatic feathering circuit has been armed.

    NO ACTION
  10. No. 1, 2, 3, or 4 AUTO FEATHER light on individually.
    Investigate.

    -----------------

    Propeller thrust has dropped to less than 500 pounds of positive thrust; propeller has automatically feathered.
  11. No. 1, 2, 3, or 4 engine STARTER CONTROL VALVE OPEN light on.
    *If the light remains on or comes on after start, secure engine by pulling emergency shutdown handle.

    -------------------

    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.)
  12. 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, 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.

    --------------------

    • Indicates feather pump relay is closed, supplying electrical power to the feather pump.
    • Possible internal leakage. Incomplete pump cut-out circuit.
  13. FAN OUT light on
    Open equipment doors for additional cooling. Use minimum electronic equipment. If EDCs are inoperative (no air-conditioning available), openAUX vent.

    --------------------------

    Cabin exhaust fan is inoperative or lack of airflow.
  14. 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 (InFlight), paragraph 15.16.

    ---------------------

    EDC oil temperature excessive. Low oil level in sump. High engine oil temperature.

    Note - Low intensity illumination of the EDC TEMP HIGH light is acceptable unless accompanied by a master PRESS SYS light.
  15. 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 (InFlight), paragraph 15.16.

    -------------------

    EDC oil pressure is low. Low level in sump. EDC drive shaft sheared.
  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.

    ----------------

    Temperature in cooling duct exceeds safe limits. On ground: inoperative heat exchanger blowerfan.
  17. 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.

    -------------------------

    Air temperature in the wing plenum area exceeds safe limits. May be caused by a leak in the bleed air manifold or EDC plumbing.
  18. LEAK TEST ACCEPT light
    Maintenance function. Refer to appropriate maintenance manuals.
  19. No. 1, 2, 3, and 4 engine bleed air valve OPEN lights on.
    When the valve begins to open, the light will be on. When the valve is closed, the light should be off.
  20. Left and right FUS BLEED AIR SHUT-OFF valve OPEN lights on.
    When the valve begins to open, the light is on. When the valve is closed, the light should be off.
  21. 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.

    ------------------

    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.
  22. 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.

    ----------------------

    • Parting strip power relay deenergized,
    • cycling power relay deenergized,
    • control relay deenergized,
    • timer motor failure,
    • empennage overheat condition.
    • Open control power circuit breaker.
  23. ANTI-ICING light  - No. 1, 2, 3, or 4 engine ANTI-ICING advisory light on with control switch on.
    Fourteenth stage air of sufficient temperature to melt ice has entered the torquemeter shroud and the inlet scoop.
  24. ANTI - ICING light
    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, 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.

    -----------------

    One or both areas of system may not be receiving hot air.
  25. 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.

    ----------------

    a. Abnormal heat in the area.

    b. Loss of electrical power to the solenoid valve.
  26. 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.

    -----------------------

    Failure of one or both thermal switches and/or anti-icing valves.
  27. Windshield heat CYCLING lights on (neon).
    If unable to start cycling on a cold windshield, use OVERRIDE switch.

    -------------------------

    Indicates that electrical power is being supplied to the windshield panels. When lights are out, electrical power is cycled off.
  28. Side windshield heat FAIL light on.
    Pull side windshield heat power circuit breaker on main AC BUS A.

    ---------------------

    Windshield power relay and/or overheat control relay stuck in energized position when control switch off.
  29. L or R HTR OUT pitot heat out light on.
    Check respective circuit breaker and bus. Monitor equipment for proper operation.

    ---------------------

    Indicates electrical current flow to the pitot heater element has been interrupted, or current flow detector is inoperative.
  30. Fx Light on - Switch in NTS position
    Reset by putting switch to FEATHER VALVE position and back to NTS position.

    ----------------

    NTS has occurred.
  31. Fx Valve light on - in Fx Valve position
    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).
  32. BOMB BAY COLD light on
    Turn BOMB BAY HEAT switch ON (autocycling), open No. 3 or No. 4 engine bleed air valve.

    -----------------------

    Temperature below desired level in bomb bay.
  33. 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.

    ----------------------

    Temperature above desired level, not cycling.
  34. DOORS light on
    Do not exceed 225 KIAS.

    ------------------

    Intake or exhaust door open. (Should close when APU is shut down.)
  35. ARMED light on
    If APU is not being used in flight, turn arming switch off.

    -------------------

    Arming switch on
  36. No. 1, 2, 3, or 4 FILTER light on.
    If engine continues to function normally, continue engine operation.

    -----------------------

    One or both of the low pressure fuel filters are restricting flow.
  37. 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.

    -----------------

    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.
  38. No. 1, 2, 3, or 4 TANK shutoff valve advisory lights on.
    Investigate

    -------------------

    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.
  39. No. 1, 2, 3, or 4 XFEED valve advisory lights on.
    Investigate

    -------------------

    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.
  40. Cross−ship X FEED valve advisory light on.
    Investigate

    -------------------

    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.
  41. RESET advisory light on
    Push reset button to regain control of transfer valves.

    ---------------

    Light will illuminate whenever there fuel control panel has control of the transfer valves, which are also used to refuel tank Nos. 1, 2, 3, 4.
  42. Tank BOOST pump low pressure advisory light on
    Refer to Fuel Boost Pump Failure, paragraph 15.8.2.

    -----------------------

    Light will illuminate whenever the output pressure of the corresponding boost pump is low.
  43. Transfer pumps PRESS LOW advisory lights on
    Shut off respective pump; refer to Transfer Pump Failure, Tank 5,paragraph 15.8.3.

    -----------------------

    Tank No. 5 is empty or pump output pressure is low.
  44. 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.

    --------------------

    Primary generator drive end bearing has failed.
  45. 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.

    ---------------

    Metal particles on magnetic plug in power section or gearbox.
  46. 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.

    ---------------------

    Engine oil temperature 100 °C or over
  47. 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.

    -------------

    Either engine oil pressure is below 40 psi or gearbox pressure below 130 psi.
  48. 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.

    --------------------

    Reduced flow and drop in pressure from prop pump 1 due to pump failure, obstruction, or low oil level.
  49. BETA light No. 1, 2, 3, or 4 prop on.
    Blade angle at 10° or less
  50. 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.

    -------------------

    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.
  51. CABIN PRESS light on.
    Refer to Pressurization Loss, paragraph 12.4.

    ----------------

    Light on at cabin altitude 10,000 (±500) feet. CABIN PRESS light out by 8,000 feet on descent.
  52. 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

    -----------------

    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).
  53. Master ELEC POWER light on
    Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection.

    -------------------

    Generator No. 2, 3, or 4 OFF light is on. Overheat of TR No. 1, 2, or 3.
  54. Master PRESS SYSTEM light on.
    Locate fault on overhead panel. Secure faulty system. Reset for continued warning protection

    -----------------------

    Oil pressure low or oil temperature high on left or right EDC. Cabin exhaust fan inoperative. Refrigeration duct overheat warning.
  55. Master RACK OVHT lighton
    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.

    -----------------------

    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.
  56. IFF light on. (Operational only if KIT-C transponder computer is installed.)
    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.

    ---------------------

    Mode 4 zeroized, self-test function of computer has detected a faulty computer, transponder not replying to proper Mode 4 interrogations.
  57. START VALVE light on.

    a. During start sequence (normal).
    b. After start sequence or during engine operation (abnormal).
    *1. Check overhead panel for individual engine start control valve open light.

    ----------------------

    Indicates one of the four engine start control valves is open.
  58. AUTOPILOT amber light (on annunciator panel). Autopilot disengages.
    Extinguish light by depressing pilot or copilot yoke button. Investigate.

    ------------------

    Autopilot or vertical gyro power loss. Excessive vertical gyro precession. No. 1 hydraulic system pressure low. Disengagement by paddle switch.
  59. AUTOPILOT flashing red warning light (on glareshield). Autopilot disengages.
    Assume manual control

    ----------------

    Hardover pitch has been detected.
  60. AUTOPILOT/RAWS flashing red warning lights (glareshield).
    Disengage autopilot. Investigate.

    ---------------------

    Autopilot or vertical gyro power loss. Excessive vertical gyro precession. No. 1 hydraulic system pressure low. Disengagement by paddle switch.
  61. AUTOPILOT/RAWS flashing red warning lights (glareshield).
    Refer to status lights. May be extinguished by pushing WARN/TEST indicator light switch, by pushing (second detent) disengage button on control wheel, or by operation of the autopilot emergency manual disconnect handle.

    ----------------

    Autopilot malfunction or certain types of normal/automatic disconnects.
  62. AUTOPILOT/RAWS flashing red warning lights (glareshield) with synchronized tone.
    If warning is abnormal, investigate.

    ---------------------

    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.)

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