Growler: EPs and Systems relationships

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  1. APU FIRE warning light, what does it mean
    *Fire/overheat condition detected in the APU bay.

    APU FIRE extinguishing system operates automatically with WonW and must be manually activated with WoffW. System activation secures fuel to the APU, arms the fire bottle, and discharges the bottle after a 10 second delay.Discharge is delayed to allow the APU time to spool down before extinguishing agent is introduced.
  2. APU fire extinguishing system requires ... , the fire bottle may not be discharged if the ...during the ... delay time.
    APU fire extinguishing system requires 28 vdc essential bus power, the fire bottle may not be discharged if the BATT switch is turned OFF during the 10 second delay time.
  3. BLEED warning lights, what do they mean
    Bleed air leak or fire detected in common ducting AND the overheat condition still exists (e.g., automatic BALD shutdown did not secure the leak)
  4. To prevent loss of aircraft, during compound emergencies or in the event of an engine bay fire, the ... procedures should be completed immediately prior to completion of any other procedures.
    To prevent loss of aircraft, during compound emergencies or in the event of an engine bay fire, the fire warning procedures should be completed immediately prior to completion of any other procedures.
  5. FIRE warning, what does it mean
    Fire/overheat condition detected in corresponding engine/AMAD bay
  6. An engine bay fire may damage the engine bay door, which is critical to structural integrity. Following an engine bay fire, limit maneuvering to ... , limit descent rate at touchdown to less than ... , and minimize ... at landing. An off‐center arrestment following an engine fire can lead to ...
    An engine bay fire may damage the engine bay door, which is critical to structural integrity. Following an engine bay fire, limit maneuvering to 5g, limit descent rate at touchdown to less than 1,000 fpm, and minimize roll and yaw at landing. An off‐center arrestment following an engine fire can lead to catastrophic structural failure.
  7. How many fire extinguisher bottles are there?
    2. One for the APU and one for the engine/AMAD bay
  8. APU fire extinguishing system is ... with WonW.
    automatically activated
  9. A separate... is incorporated to automatically detect and extinguish a fire or explosion in the dry bays below fuel tanks 2, 3, and 4.
    A separate dry bay fire suppression (DBFS) system is incorporated to automatically detect and extinguish a fire or explosion in the dry bays below fuel tanks 2, 3, and 4.
  10. Pushing the FIRE light ...
    Arms the fire extinguisher bottle and closes the corresponding engine feed shutoff valve, the crossfeed valve, and the crosscooling valve
  11. The fire lights in the rear cockpit...
    are advisory only. These lights are not push buttons, and they do not arm the fire extinguisher bottle or shut down the engines or APU.
  12. How can you know if there is a fault in the fire detection system
    The light will not illuminate and voice annunciation will not occur during the fire test during engine start
  13. If a bleed air leak is detected, the system attempts to isolate the affected ducting by ... . A leak detected ... closes only the appropriate primary bleed air shutoff valve. A leak detected downstream of the secondary bleed air shutoff valve closes ....
    If a bleed air leak is detected, the system attempts to isolate the affected ducting by automatically closing the appropriate bleed air shutoff valve(s). A leak detected upstream of the secondary bleed air shutoff valve closes only the appropriate primary bleed air shutoff valve. A leak detected downstream of the secondary bleed air shutoff valve closes all three valves (secondary and both primaries).
  14. The L BLEED and/or R BLEED warning lights extinguish ... and may not be on long enough to be recognized by the aircrew.
    as soon as bleed air is removed from the leaking duct
  15. WARNING: Automatic functioning of the BALD system may extinguish the L(R)BLEED warning lights prior to aircrew recognition and may not trigger the appropriate voice alerts. In this case, ... to remove the L and/or R BLD OFF cautions reintroduces hot bleed air to the leaking duct. If the sensing element was damaged by the leak, automatic shutdown and isolation capability may be lost. Extensive damage and/or fire may result.
    cycling the BLEED AIR knob
  16. Sustained high power, high speed operation at low to medium altitude may result in ... due to ...
    Sustained high power, high speed operation at low to medium altitude may result in dual BLEED warnings and loss of OBOGS, cabin pressurization,and g‐suit due to secondary bleed air pressure regulator bay overheat.
  17. Additionally, the BALD controller requires ... between FIRE TEST A and TEST B to successfully reset
    Additionally, the BALD controller requires 3 seconds between FIRE TEST A and TEST B to successfully reset
  18. The dry bay fire suppression system is armed and capable of suppressing a fire/explosion in the dry bays when ...
    The dry bay fire suppression system is armed and capable of suppressing a fire/explosion in the dry bays when the LDG GEAR handle is up and at least one generator is on line.
  19. With the LDG GEAR handle down, the dry bay fire suppression system ... but ...
    With the LDG GEAR handle down, the dry bay fire suppression system still gives a fire warning (BAY FIRE caution) but is not capable of extinguishing a dry bayfire.
  20. With the HOOK light on, the HOOK handle up, and the hook up, ... during engine shutdown
    the hook will drop
  21. If the hook is unlocked (HOOK handle down) but fails to leave the up position, an arresting hook system failure may be applying HYD ... pressure to hold the hookup. For this reason, ... deenergizes the hook selector
    If the hook is unlocked (HOOK handle down) but fails to leave the up position, an arresting hook system failure may be applying HYD 2B pressure to hold the hookup. For this reason, pulling the HOOK circuit breaker deenergizes the hook selector
  22. Flashing Gear handle and Wheels warning is caused by
    • 1. less than 7,500 feet
    • 2. less than 175 KCAS
    • 3. over 250 fpm descent rate
  23. A L/R AMAD PR caution could be an indication of ... which may result in ...
    A L/R AMAD PR caution could be an indication of an AMAD oil leak which may result in an engine/AMAD bay fire.
  24. A ... accompanied by ... is a potential indication of major mechanical damage to the generator and AMAD.
    A single GEN failure accompanied by an AMAD PR caution on the same side is a potential indication of major mechanical damage to the generator and AMAD. Minimize engine operation if practical to prevent overheating the components and potential FIRE warnings.
  25. With a L/R AMAD PR caution, securing the GEN...
    greatly reduces the heat load imparted to the AMAD oil and may prevent heat‐related damage to the generator.
  26. Unregulated engine anti-ice airflow may...
    damage the inlet device and cause potential engine FOD
  27. L/R ANTI ICE caution, what does it mean
    engine anti-ice valves failed to close when commanded by the FADEC
  28. Do not cycle the ANTI SKID switch in response to an ANTISKID caution immediately prior to landing for the following reasons:
    a. The ANTI SKID caution is removed for up to 13.5 seconds as the system performs IBIT even though the anti‐skid system may still be failed.

    b. If the system is not failed, wheel motion at touchdown or during landing rollout may cause a false BIT failure and a dump of normal brake pressure when brakes are applied.
  29. If the ANTI SKID switch is not placed to ... with an ANTISKID caution displayed,...
    If the ANTI SKID switch is not placed to OFF with an ANTISKID caution displayed,normal braking capability may be lost completely.
  30. The APU ACCUM caution can be expected...
    The APU ACCUM caution can be expected after APU start or after emergency gear/probe extension in flight.
  31. With WonW, the APU accumulator ... .With WoffW, the HYD ISOL switch may need to be held for up to ... seconds following emergency gear/probe extension or APU start to remove the APU ACCUM caution and ... seconds to provide a full charge (up to ... seconds after in‐flight APU start)
    With WonW, the APU accumulator recharges automatically.With WoffW, the HYD ISOL switch may need to be held for up to 20 seconds following emergency gear/probe extension or APU start to remove the APU ACCUM caution and 30 seconds to provide a full charge (up to 40 seconds after in‐flight APU start)
  32. If the APU ACCUM caution appears in flight and is not related to emergency gear/probe extension or APU start, it may indicate...
    a possible leak in the isolated HYD 2B system.
  33. L/R ATS caution, what does it mean
    Designated air turbine starter rpm too high (e.g., both sources of ATS overspeed cutout protection have failed).
  34. Regardless of the engine start air source utilized, the corresponding ... switch should be ..., as the ... provides primary overspeed cutout protection for the ATS.
    Regardless of the engine start air source utilized, the corresponding GEN switch should be ON, as the generator provides primary overspeed cutout protection for the ATS.
  35. Selection of MAN with the ECS MODE switch is ... . Selecting MAN while the aft cooling fan shutoff valve is open may cause the fan to ...resulting in ... potentially leading to ...
    Selection of MAN with the ECS MODE switch is prohibited. Selecting MAN while the aft cooling fan shutoff valve is open may cause the fan to overspeed resulting in a catastrophic fan failure potentially leading to loss of OBOGS.
  36. Essential bus backup is provided from...
    the PMGs and battery
  37. BAY FIRE caution, what does it mean
    • With LDG GEAR handle UP:
    •    *Dry bay fire condition still detected 3 seconds after DBFSS discharge (e.g., fire was not extinguished).

    • With LDG GEAR handle DN:
    •    *Dry bay fire detected. (No extinguishing capabilityavailable).
    •    *If dry bay fire goes out, the BAY FIRE caution is removed
  38. The BINGO voice alert is repeated every ... until ...
    The BINGO voice alert is repeated every 30 seconds until the BINGO setting is adjusted.
  39. L/R BLD OFF, what does it mean
    the corresponding primary bleed air shutoff valve has been commanded closed. Not an indication of actual valve position
  40. L/R BOOST LO, what does it mean
    • 1. Loss of fuel boost pressure to designated engine
    • 2. May indicate fuselage fuel leak.
    • 3. May indicate fuel transfer failure.
    • 4. May indicate a power transmission shaft failure if accompanied with the corresponding GEN, DC FAIL,and both HYD circuit cautions.
    • 5. May result from prolonged transitions through zero g (greater than 2 seconds).
  41. BRK ACCUM caution, what does it mean
    Brake accumulator pressure low (below 2,000 psi).Emergency brakes may not be available.
  42. A BRK ACCUM caution in flight is not normal and may indicate a possible leak in the isolated ... system. If the caution appears in flight, do not attempt to recharge the accumulator as this may result in additional loss of ... fluid.
    A BRK ACCUM caution in flight is not normal and may indicate a possible leak in the isolated HYD 2B system. If the caution appears in flight, do not attempt to recharge the accumulator as this may result in additional loss of HYD 2B fluid.
  43. CABIN caution light, what does it mean
    • 1. Cabin pressure altitude above 21,000 +/- 1,100 feet.
    • 2. AEA PRECOOL relay failed.

    Cabin light may not extinguish until cabin pressure altitudeis below 16,500 feet.
  44. CABIN light may appear with normal cabin pressurization when aircraft altitude is above ... . If altitude is maintained with CABIN light on, aircrew should continuously monitor physiological condition and cabin pressure altimeter since there will be no additional warnings or cautions if cabin pressurization fails.
    47,000 ft MSL
  45. Emergency oxygen will last...
    10-20 minutes

    *Under less than optimum conditions (low altitude, heavy breathing, loose-fitting mask, etc.), as few as 3 minutes of emergency oxygen may be available
  46. CK SEAT caution light comes on with ... and throttle advanced beyond...
    CK SEAT caution light comes on with seats not armed and throttle advanced beyond 27° THA
  47. L/R DC FAIL caution, what does it mean
    • 1. All three PMG outputs have failed on the corresponding side.
    • 2. May indicate a power transmission shaft failure if accompanied with the corresponding BOOST LO,GEN, and both HYD circuit cautions.
  48. If the dump valve cannot be closed, fuel continues to dump until Tanks ... are empty. Selecting ... diverts re-circulation fuel from the wings to the feed tanks. Stopping external transfer may make this fuel available if the dump valve is subsequently closed. When uncommanded fuel dump ceases, the feed tanks should contain between ... lb,depending on JLS cycling.
    If the dump valve cannot be closed, fuel continues to dump until Tanks 1 and 4 are empty. Selecting WING INHIBIT diverts re-circulation fuel from the wings to the feed tanks. Stopping external transfer may make this fuel available if the dump valve is subsequently closed. When uncommanded fuel dump ceases (Tanks 1 and 4 empty),the feed tanks should contain between 4,200 and 4,900 lb,depending on JLS cycling.
  49. EXT TANK caution, what can cause it inflight
    External tank pressurization is terminated for in‐flight refueling (PROBE switch in EXTEND) and for arrested landing (both HOOK and LDG GEAR handles down).
  50. Carrier launch prohibited with less than ... lbs and greater than ... lbs in external drop tank.
    Carrier launch prohibited with less than 2,700 lbs and greater than 100 lbs in external drop tank.
  51. Effects of icing on external tank transfer
    Icing may occur in the external fuel tank pressurization system inhibiting external tank transfer and refueling. Descending and accelerating may reduce the effects of icing.
  52. FADEC HOT caution, what does it mean
    • WonW, both engines shutdown:
    •    *Left or right engine FADEC indicates an overheat condition.


    • WonW, IDLE or above:
    •    *Insufficient fuel flow through the FADEC for adequate cooling.
  53. Ignition automatic when throttle ... whenever flameout sensed
    at or above IDLE
  54. Restarting an engine that has flamed out for no apparent reason...
    may result in an engine bay fuel leak/fire
  55. As corresponding HYD pressure decays below ... psi, aileron, rudder, and LEF switching valves function (typically within ...).
    As corresponding HYD pressure decays below 900 psi, aileron, rudder, and LEF switching valves function (typically within 2 seconds).
  56. If a windmilling engine causes HYD pressure to fluctuate between ... psi, the switching valves cycle between their primary and backup circuits. If this occurs, reduce airspeed until ...
    If a windmilling engine causes HYD pressure to fluctuate between 800 and 2,000 psi, the switching valves cycle between their primary and backup circuits. If this occurs, reduce airspeed until hydraulic pressure fluctuations cease.
  57. Generators drop offline as rpm decays through...
    60%
  58. ... supply power to run flight controls down to approximately ...% N2
    PMGs supply power to run flight controls down to approximately 20% N2
  59. L/R FUEL HOT caution, what does it mean
    • *Engine FUEL NOZ TEMP high (177 °C).
    • *FEED TANK TEMP high.
    •      *WoffW: >60 °C for 10 min, or >65 °C for 15 sec
    •      *WonW: >79 °C for 15 sec (5,000 lb fuel), or >60 °C for 10 min, or >65 °C for 15 sec (>5,000 lb fuel)
  60. The FUEL HOT caution will clear upon landing if feed tank temperature is less than ...°C with less than ...lb fuel.
    The FUEL HOT caution will clear upon landing if feed tank temperature is less than 80 °C with less than 5,000 lb fuel.
  61. L/R FUEL INLT caution, what does it mean
    The designated fuel/air heat exchanger is leaking, and the fuel system has failed to shut off flow to the heat exchanger.

    Due to fuel/air heat exchanger location (above the engine inlet), engine fuel ingestion is possible if fuel flow is not immediately secured.
  62. FUEL LO caution light, what does it mean
    • *At least one feed tank below 1,125 lb.
    • *May also be an indication of a fuel transfer failure.
    • *May indicate fuselage fuel leak.
    • *Sideslip may be required to transfer wing fuel.
  63. If a fuel low level indication was caused by a transient condition such as prolonged negative g flight, the FUEL LO caution remains for ... after the low level indication has cleared.
    60 seconds
  64. FUEL XFER caution, what does it mean
    • *Internal wing tank fuel asymmetry exceeds 350 lbs.
    • *Tank 1 and 4 fuel is not scheduling properly (e.g.,Tank 4 full and Tank 1 empty).
  65. FUEL XFER caution meanings: Internal wing tank failure
    • *Most likely result of a valve failure.
    • *If one internal wing tank fails to transfer, the other is commanded to stop transferring when wing tank balance logic detects a 200 lb split.
    • *When Tank 4 drops to approximately 3,000 lbs,the SDC declares a wing transfer failure, cancels wing balance logic, and re-initiates transfer from the good internal wing tank.
    • *All fuel from the failed internal wing tank should gravity transfer with the aid of bank angle changes or a steady sideslip.
    • *Selecting INTR WING INHIBIT isolates normal wing transfer/refuel and diverts recirculation fuel to the feed tanks.
  66. FUEL XFER caution meanings: Tank 1 transfer failure
    • *Tank 1 fails to stop transfer (pump and/or valve failure).
    • *Tank 1 depletes as soon as the feed tanks can accept its fuel causing FUEL XFER caution.
    • *Assuming normal Tank 4 transfer, caution is removed when Tank 4 depletes to approximately 2,100 lbs.
  67. FUEL XFER caution meanings: Tank 4 transfer failure
    • *Tank 4 fails to transfer (pump failure).
    • *Tank 1 also stops transferring when it reaches the fuel transfer schedule (approximately 1,000 lbs).
    • *Tank 4 continuously gravity transfers to Tank 3 and, when feed tank balance logic is initiated, to Tank 2 using scavenge pump.
    • *The last 1,000 lbs of Tank 1 transfers when Tank 2 cycles in and out of FUEL LO.
    • *With Tank 4 near full, the FUEL XFR caution is set when Tank 1 drops below 400-500 lbs.
  68. A single GEN failure accompanied by an AMAD PR caution on the same side is ...
    a potential indication of major mechanical damage to the generator and AMAD. Minimize engine operation if practical to prevent overheating the components and potential FIRE warnings.
  69. Primary indications of dual Gen failure
    • *loss of all displays
    • *loss of cabin pressurization (both bleed valves close)
  70. What shows displays do we have with a dual Gen failure
    Standbys and EFD shows RPM and EGT
  71. How much battery power with a dual Gen failure
    Only 5 to 10 minutes of battery power remains to power essential bus and the FCCs if battery gauge indicates 24 vdc or below.
  72. GEN TIE light, what does it mean
    • *Left and right 115 vac buses are isolated (bus tie open).
    • *May be caused by electrical fault protection circuitry.
    • *May be caused by initial engine start with the PARK BRK released.
  73. If the left and right buses are isolated because of a detected fault, cycling the GEN TIE CONTROL switch ...
    reenergizes the faulty bus/equipment and may cause further damage or loss of the remaining generator.
  74. G-LIM 7.5G caution, what does it mean
    *Nz REF (g‐command limiter) set to 7.5g regardless of gross weight.

    G‐command limiter will not prevent an aircraft overstress at gross weights above 42,097 lbs. Above 42,097 lbs gross weight, pilot must limit g to prevent an overstress.
  75. G-LIM OVRD caution, what can we do to make it go off
    Selected by momentarily pressing the paddle switch when the stick is near the full aft limit. Maximum allowed g‐limit increased by 33% (allows a 10g command at 7.5g Nz REF). Unless g‐limiter override is desired, control maximum g‐level. If the paddle switch has failed electrically, NWS and the autopilot may be commanded off without pilot action or notification.
  76. HOME FUEL caution, what does it mean
    Fuel remaining sufficient to fly to HOME waypoint with 2,000 lbs reserve or less.
  77. INLET ICE caution, what does it mean
    • *Engine inlet icing conditions detected.
    • *INLET ICE caution comes on when 0.025 inch of ice has accumulated on the ice detector located in the left inlet.
  78. As little as ... of ice ingested by the engine can result in compressor stalls and major FOD.
    As little as 0.5 inch of ice ingested by the engine can result in compressor stalls and major FOD.
  79. INLET ICE WITH NO ICE VISIBLE ON AIRCRAFT, what can we do
    Maintain INLET TEMP of at least +5 °C(+10 °C preferred) to provide sufficient aerodynamic heating to prevent ice accumulation on LEFs and inlet lips.
  80. INLET ICE WITH ICE CLEARLY VISIBLE ON LEFs what can we do
    Reduce throttle settings below 80% N2 rpm while descending below the freezing level to prevent ice shedding into the engine.— Avoid throttle transients above 90% N2 rpm,abrupt maneuvers, and bank angles over 20° to prevent ice from detaching from the inlet lip.
  81. OBOGS DEGD caution, what does it mean
    • *Oxygen concentration is below acceptable limits.
    • *Disconnected oxygen hose.
    • *Removing oxygen mask without placing the OXY FLOW knob to OFF.
    • *System gas leak (broken integrity).
  82. L/R OIL HOT caution, what does it mean
    • *Designated ENG OIL TEMP high (149 °C or above).
    • *Designated AMAD OIL TEMP high (88 °C or above).
  83. L/R OIL HOT caution, what could cause it
    • *engine malfunction
    • *hot fuel at low fuel states
    • *an over-serviced AMAD
    • *AMAD/fuel heat exchanger failure
    • *fuel recirculation system failure
    • *motive flow system failure
    • *normally operating system during extended ground operations with OAT greater than 103°F.
  84. Prolonged operation of a hot AMAD may result in ...
    an engine bay fire.
  85. If OIL HOT caution caused by extended ground operations (OAT > ...), increasing affected engine rpm should  clear the caution within ...(normal operating system).
    If OIL HOT caution caused by extended ground operations (OAT > 103 °F), increasing affected engine rpm should  clear the caution within 20 seconds (normal operating system).
  86. Zero oil pressure without the L/R OIL PR caution indicates the ... has failed and the ... is detecting oil pressure greater than .... Flight (may/may not) be continued.
    Zero oil pressure without the L/R OIL PR caution indicates the oil pressure transmitter has failed and the oil pressure switch is detecting oil pressure greater than 35 psi. Flight may be continued.
  87. OIL PR caution is disabled or clears when g is less than ... and is not enabled until g is greater than ... for ....
    OIL PR caution is disabled or clears when g is less than 0.7 and is not enabled until g is greater than 0.7 for one minute.
  88. Even if PARK BRAKE caution is extinguished in flight, ...
    the possibility exists that the parking brake may still be engaged.
  89. POS ERROR caution: ANAV is preventing aided navigation because horizontal position is more than ... different, or vertical position is greater than ... different.
    POS ERROR caution: ANAV is preventing aided navigation because horizontal position is more than 20 nm different, or vertical position is greater than 5,000 feet different.
  90. Engine stall indications
    • *audible bangs
    • *airframe vibration
    • *visible flames out the exhaust and/or inlet
  91. Self‐recovering single pop or surge stalls (DO/DO NOT) result in L or R STALL caution unless engine limits are exceeded.
    Self‐recovering single pop or surge stalls DO NOT result in L or R STALL caution unless engine limits are exceeded.
  92. Hung stall or multiple pop stalls (three or more in ...), will result in L or R STALL caution with following indications:
         a.  
         b. 
         c.
    • Hung stall or multiple pop stalls (three or more in 5 seconds), will result in L or R STALL caution with following indications:     
    •      a. Lack of throttle response
    •      b. Increasing EGT
    •      c. Steady or decreasing rpm (rpm that continues to decrease may result in L or R FLAMEOUT caution).
  93. A L or R STALL caution caused by a ... stall will time out after ... regardless of whether the stall has actually cleared.
    A L or R STALL caution caused by a hung stall will time out after 5 seconds regardless of whether the stall has actually cleared.
  94. L/R THERMAL caution, what does it mean
    Designated engine thermal control valve (TCV) has failed open. Fuel thermal management system has lost capability to regulate fuel system temperatures.

    If a TCV fails open, hot feed fuel is recirculated back to the fuel tanks instead of being burned. May eventually lead to a corresponding FUEL HOT caution.
  95. Extended operation of the windshield anti-ice/rain removal system on a (wet/dry) windshield may result in heat damage to the windshield.
    dry
  96. If WDSHLD HOT caution remains with the switch in ..., an ECS valve failure may be directing hot air to the windshield. In this case, ... may be the only means to stop windshield airflow.
    If WDSHLD HOT caution remains with the switch in OFF, an ECS valve failure may be directing hot air to the windshield. In this case, securing the ECS may be the only means to stop windshield airflow.
  97. Ensure the WINGFOLD switch islever‐locked in the SPREAD position during takeoff checks. If the wings are commanded to unlock or fold during a catapult shot, bolter, or touch and go, ...
    the wings will unlock, the ailerons will fair, the wings may fold partially, and the aircraft will settle.
  98. Avoid multiple FCS reset attempts of a recurring FCS failure to ...
    preclude the failure from occurring during a critical phase of flight (e.g., during final approach to landing).
  99. With a four channel AHRS failure, the aircraft is not controllable with the flaps in .... At altitudes above ... feet, loss of control will occur below Mach .... For loss of AHRS above ... feet, maintain airspeed above Mach ... while descending.
    With a four channel AHRS failure, the aircraft is not controllable with the flaps in HALF or FULL. At altitudes above 25,000 feet, loss of control will occur below Mach 0.92. For loss of AHRS above 25,000 feet, maintain airspeed above Mach 0.92 while descending.
  100. If an AOA probe is ... , AOA errors may be unannunciated if the AOA split thresholds (are/are not) exceeded.
    If an AOA probe is stuck or damaged (IFR basket impact,bird strikes, probe icing), AOA errors may be unannunciated if the AOA split thresholds are not exceeded.
  101. GAIN ORIDE limits
    • *AOA - 10°
    • *Flaps AUTO - 350 KCAS
    • *Flaps HALF - 200 KCAS
    • *Flaps FULL - 190 KCAS
  102. When emergency high gain nosewheel steering mode is entered, nosewheel steering indications ...
    may not be displayed on the HUD. As a result, inadvertent nosewheel steering actuation may injure ground personnel.
  103. At what pressure will a HYD caution turn on
    <1,400 psi
  104. With HYD 2A failed we loose
       a. 
       b. 
       c. 
       d. 
       e. 
       f.
    • a. No landing gear retraction/normal extension.
    • b. No normal NWS (flashing NWS in HUD).
    • c. No normal braking.
    • d. No anti‐skid.
    • e. No probe retraction/normal extension.
    • f. No launch bar extension.
  105. HYD 5000 caution, what does it mean
    Hydraulic pressure is less than 4,600 psi when 5,000 psi operation is requested from the hydraulic system.
  106. HYD 1/2 HOT caution, what does it mean
    Hydraulic pump case temperature exceeds 400 °F and either the respective case drain temperature exceeds 275 °F or the respective reservoir temperature exceeds 250 °F.

    May be an indication of an internal hydraulic pump failure.
  107. Hydraulic pump overheat may result in ... and ...
    Hydraulic pump overheat may result in pump case failure and fire in the AMAD bay.
  108. What advisories can we not takeoff for
    a. ECSDR - ECS auxiliary duct door not in commanded position.

    b. LOAD Xd - Improper weapon load, codes, or incompatible fuzing.

    c. MNTCD - MU/maintenance card problem.

    d. DISCH - Fire extinguisher bottle discharge initiated or pressure drop detected

    e. FADEC - Left or right FADEC has lost backup redundancy in one channel.
  109. What does a flashing RIGHT/LEFT gear light indicate
    Planing link failure on that side
  110. A Hung start is when there is no rise in EGT within ... after throttle advance or rpm stabilizes below IDLE
    20 seconds
  111. How long do you crank the engine after turning it off on a hung start
    3 minutes
  112. Hot brakes and/or melted wheel assembly fuse plugs can be expected any time ...
    maximum effort braking is used at heavy gross weights with or without anti‐skid, e.g., aborted takeoff or heavy weight landing with high taxi brake usage.
  113. What types of fires are related to the brake system
    • a. flash fires
    • b. fires due to continuous hydraulic fluid leakage onto hot brakes.
  114. If brake system fire occurs with the parking brake set, ...
    the parking brake may become non‐operational and the aircraft may need to be chocked.
  115. Avoid setting the parking brake with hot brakes until the brake assembly has cooled to ...
    prevent damage by heat and/or fire to the brakes, wheel, tire,and landing gear components.
  116. CANOPY JETT rocket thrusters may ignite ... and may injure ...
    CANOPY JETT rocket thrusters may ignite spilled fuel or hydraulic fluid and may injure ground crew in the immediate vicinity.
  117. The CANOPY switch should be used to raise the canopy unless there are overriding circumstances. If weight is not on the ... main gear (e.g., gear up landing), the CANOPY switch...
    The CANOPY switch should be used to raise the canopy unless there are overriding circumstances. If weight is not on the left main gear (e.g., gearup landing), the CANOPY switch must be held to raise the canopy.
  118. During emergency catapult flyaway, exceeding 10° to 12° pitch attitude may...
    result in rapid loss of lateral directional control
  119. A rule of thumb to ensure full hook extension is ... feet prior to the arresting gear.
    1,000 feet
  120. Go Around Procedure
    • 1. Throttles — MIL or MAX.
    • 2. Maintain on-speed AOA and balanced flight.
    • 3. EMERG JETT button — PUSH (if required).
  121. Loss of directional control Warning: If the decision to takeoff is made...
    If the decision to takeoff is made, nose rotation and/or takeoff may be delayed by abnormal aircraft attitudes due to failures, increased drag, and lack of or reduced rudder toe due to rudder deflection to counter directional motion.
  122. If decision is made to takeoff after a loss of thrust consider:
       a. 
       b.
       c.
       d.
    a. Best rate of climb during single-engine operation occurs at or near on-speed AOA regardless of configuration or gross weight.

    b. Raising the landing gear to improve acceleration.

    c. Jettison of external stores to reduce gross weight.

    d. If one engine fails, asymmetric thrust effects are exacerbated at MAX power but are nonetheless controllable if AOA is maintained near on-speed.
  123. At least ... is required to maintain ... rpm for a windmill airstart
    At least 350 KCAS is required to maintain 12% rpm for a windmill airstart
  124. Continuing automatic restart attempts at high altitude or high AOA may cause ...
    the engine to overtemp
  125. If the engine is shut down from a high power setting and rpm decays to 0%, ... may occur. In this case,engine rotation will not be regained until ... (about  ...). Windmill restart attempts made after rpm has degraded to 0% may require up to ... knots to obtain 12% rpm for ignition.
    If the engine is shut down from a high power setting and rpm decays to 0%, temporary rotor binding may occur. In this case,engine rotation will not be regained until the engine cools evenly (about 10 to 15 minutes). Windmill restart attempts made after rpm has degraded to 0% may require up to 450 knots to obtain 12% rpm for ignition.
  126. APU restart envelope
    below 250 KCAS, below 10,000 ft
  127. Fuel loss rates can be in excess of ... ppm from failed main fuel lines
    1,000
  128. Fuel leaks may occur upstream of ...
    the throttle‐operated fuel shutoff valve in the fuel control, shutting down the throttle may not stop the leak
  129. Possible indications of fuselage fuel leak
    • a. FUEL LO caution
    • b. erratic engine operation at high power settings
    • c. abnormal fuel flow indications.
  130. Afterburner operation with a fuselage fuel leak ...
    may result in a fire.
  131. During a fuselage fuel leak securing the good engine may result in ...
    flameout of both engines.
  132. Full opposing rudder may not be sufficient to prevent a departure when ... if ... selected. Large single engine throttle transients can cause ...
    Full opposing rudder may not be sufficient to prevent a departure when single engine if MAX power selected. Large single engine throttle transients can cause significant yaw and roll.
  133. With a dual transformer-rectifier failure essential bus is powered by the ...
    EBB PMGs with the battery charger and the battery as backups
  134. Different types of smoke that may enter the cockpit and their sources
    The most probable source of visible smoke or fumes in the cockpit is from the engine bleed air or residual oil in the ECS ducts. This smoke is blue gray in color, has a characteristic pungent odor, and may cause the eyes to sting.

    Another source of smoke or fumes is an electrical malfunction or overheat of equipment located in the cockpit. In the event of an electrical short or overload condition, this equipment may generate electrical smoke (usually white or gray in color) but should not cause an open fire since cockpit equipment uses very little electrical current. Cockpit electrical wiring insulation may smolder and create smoke, but will not erupt into a seriously damaging fire.
  135. Failure to ensure all dive recovery criteria are met may result in...
    re-departure during recovery.
  136. Post departure dive recovery pull and maintain...
    25° to 35° AOA until positive rate of climb established
  137. Delaying IFR probe retraction with feed tank fuel quantity near or below the fuel low level may result in ... since normal wing transfer cannot be restored by selecting ... once the .. caution has been set for ...
    Delaying IFR probe retraction with feed tank fuel quantity near or below the fuel low level may result in fuel starvation since normal wing transfer cannot be restored by selecting RETRACT once the FUEL LO caution has been set for 5 minutes.
  138. Retracting a damaged IFR probe or one with the drogue/hose still attached may result in ...
    damage to the AOA probe, canopy, and control surfaces, as well as engine FOD/shutdown/un-contained failure/fire.
  139. In flaps up/AUTO, whenever a filtered difference of the left and right AOA probe values exceeds about ... (a ...), the L‐versus‐R AOA monitor is tripped, a ... failure is declared,and the HUD AOA numeric value is ...
    In flaps up/AUTO, whenever a filtered difference of the left and right AOA probe values exceeds about 10° (a 15.5° uncorrected, local AOA probe‐split), the L‐versus‐R AOA monitor is tripped, a four‐channel AOA failure is declared,and the HUD AOA numeric value is blanked
  140. Do not crossbleed if ...
    engine and/or AMAD related damage is suspected.
  141. Starting the APU airborne may result in ...
    a BALD shutdown due to ingestion of exhaust gases into the APU ducting.
  142. Single engine waveoff/bolter Procedure
    • 1. Throttles — MAX.
    • 2. Maintain on‐speed AOA and balanced flight.
    • 3. Climb, then accelerate to a safe altitude/airspeed.
  143. Selective jettison can only be performed with ...
    LDG GEAR handle UP and all landing gear up and locked.
  144. Planing link failure may not be annunciated until...
    after touchdown, providing the pilot with little to no reaction time between initial annunciation and a violent yaw/swerve. If flyaway airspeed is available, pilots should be prepared to make the decision to execute the Go Around procedure immediately at initial planing link failure annunciation.
  145. Use of symmetrical wheel brakes with a planing link failure ...
    may cause a sudden swerve in the direction of the failed gear.
  146. An increased risk of severe injury or death during parachute landing fall (PLF) exists with surface winds exceeding ...
    25 knots.
  147. With wings level and no sink rate, ejection is feasible within the following parameters:
    • 1. Ground level — zero airspeed.
    • 2. Surface to 50,000 feet MSL — 600 KCAS maximum.
  148. If downed in seawater, SEAWARS releases the parachute canopy within .... However, if able, manually... immediately on seawater entry. The SEAWARS (does/does not) operate in freshwater.
    If downed in seawater, SEAWARS releases the parachute canopy within 2 seconds. However, if able, manually unlock each canopy release immediately on seawater entry. The SEAWARS does not operate in freshwater.

Card Set Information

Author:
dcbailo
ID:
317848
Filename:
Growler: EPs and Systems relationships
Updated:
2016-03-25 16:24:47
Tags:
Growler
Folders:
Growler
Description:
How do the systems relate to EPs and EP actions
Show Answers:

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