2a353: Fighter Aircraft Maintenance Journeyman

153 Questions

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Aircraft Maintenance Quizzes & Trivia

In the air force the aircrafts need to be in top shape in case they are called to action, this is ensured by aircraft maintenance personnel. Are you on the road to becoming a fighter aircraft maintenance journeyman and are looking for revision material? Look no further as the quiz is designed for that purpose. Give it a try.


Questions and Answers
  • 1. 
    The number of positions on the function switch of the AN/PSM-37 multimeter is....
    • A. 

      2

    • B. 

      3

    • C. 

      5

    • D. 

      7

  • 2. 
    To measure current flow, you connect an AN/PSM-37 multimeter in....
    • A. 

      Series in the circuit

    • B. 

      Parallel in the circuit

    • C. 

      Series with the component

    • D. 

      Parallel with the component

  • 3. 
    The symbol entered on the forms if an aircrft exceeds the PDM cycle by 90 days and an extension is not granted is a.....
    • A. 

      Red x

    • B. 

      Red dash

    • C. 

      Red diagonal

    • D. 

      Black signature

  • 4. 
    The AF IMT 2691 is used to .....
    • A. 

      Serve as a receipt document

    • B. 

      Serve as a shipping document

    • C. 

      Transfer aircraft -21 equipment

    • D. 

      Account for aircraft -21 equipment

  • 5. 
    On the F-15 aircraft, what is the useable pressure range for the LOX system?
    • A. 

      35-70 psi

    • B. 

      55-90 psi

    • C. 

      75-100 psi

    • D. 

      95-120 psi

  • 6. 
    On the F-15 aircraft, what component contains the logic circuits for the overheat/fire detection system?
    • A. 

      BIT panel

    • B. 

      Flashing relay

    • C. 

      Control panel

    • D. 

      Controllers

  • 7. 
    The F-100 engine gearbox module is attached to the.....
    • A. 

      Compressor intermediate case

    • B. 

      Fan inlet case assembly

    • C. 

      Rear turbine case

    • D. 

      N1 section

  • 8. 
    The F-100 engine exhaust nozzle position transmitter is driven by......
    • A. 

      The convergent exhaust nozzle control

    • B. 

      115-VAC power

    • C. 

      26-VAC power

    • D. 

      An air motor

  • 9. 
    How many air/oil coolers are there on the -229 engine?
    • A. 

      3

    • B. 

      4

    • C. 

      9

    • D. 

      NONE

  • 10. 
    On the ignition test set, what monitors the output of energy?
    • A. 

      Stored energy meter

    • B. 

      Potentiometer

    • C. 

      Toggle switch

    • D. 

      Rotary meter

  • 11. 
    On the F-15 aircraft, the airframe mounted accessory drive component that takes the input from the pawl carrier assembly and transmits the rotational force to the power takeoff drive shaft for engine starting is the......
    • A. 

      Layshaft

    • B. 

      Face gear

    • C. 

      Gear trian

    • D. 

      Pinion gear

  • 12. 
    On the F-15, the Mach blocking solenoid locks the diffuser ramp in the DOWN position by.....
    • A. 

      Energizing the shutoff valve

    • B. 

      Closing the rate limiter valve

    • C. 

      Opening the rate limiter valve

    • D. 

      Deenergizing the shutoff valve

  • 13. 
    On the F-15, which JFS fuel filter component acts like a jet pump?
    • A. 

      Bypass valve

    • B. 

      Fuel accumulator

    • C. 

      Fuel shutoff valve

    • D. 

      Fluid-flow restrictor

  • 14. 
    On the F-15, what airframe mounted accessory drive switch is commonly called the 50% switch?
    • A. 

      Two-speed switch assembly

    • B. 

      Oil pump and start cut-out

    • C. 

      Power turbine overspeed

    • D. 

      Right decoupler position

  • 15. 
    On the F-15, the JFS start handle input is transmitted to the JFS start control manifold by......
    • A. 

      A torque link

    • B. 

      A cable assembly

    • C. 

      A hydraulic signal

    • D. 

      An electrical signal

  • 16. 
    The function of the F-100 Electronic Engine Control (EEC) is to....
    • A. 

      Provide histroy data storage

    • B. 

      Trim the convergent exhaust nozzle

    • C. 

      Send signals to the cockpit indicators

    • D. 

      Supervise the trim of the UFC and CIVV

  • 17. 
    The light for a borescope is transmitted by the......
    • A. 

      Lens

    • B. 

      Probe

    • C. 

      View finder

    • D. 

      Fiber optic cables

  • 18. 
    What supplies power to the engin ignition system durning an ignition test?
    • A. 

      Electronic scaler

    • B. 

      Ligh-off detector

    • C. 

      Electronic trasmitter

    • D. 

      Alternator simulator output

  • 19. 
    On the F-15, at what pressure differential does the utility thermal control valve allow fluid to bypass the heat exhanger?
    • A. 

      32.5 psid

    • B. 

      42.5 psid

    • C. 

      52.5 psid

    • D. 

      62.5 psid

  • 20. 
    On the F-15, how does the PRCA control the ARI?
    • A. 

      Electrically through the airspeed switch

    • B. 

      Mechanically through the pitch boost actuator

    • C. 

      Hydraulically through the pitch ratio controller

    • D. 

      Hydromechanically through the automatic flight control assembly/PRCA interface

  • 21. 
    When a hydraulic leak occurs in the utility system on an F-15 aircraft, how does circuit A shut off?
    • A. 

      Pneumatically

    • B. 

      Hydraulically

    • C. 

      Mechanically

    • D. 

      Electrically

  • 22. 
    On the F-15 aircraft, how long does utility system non-reservoir level-sensing maintain pressure if the aircraft develops a leak in the utility hydraulic system?
    • A. 

      Until the circuit A and B shutoff valves open.

    • B. 

      Until the circuit A and B shutoff valves close

    • C. 

      As long as there is hydraulic fluid left in the utility reservoir

    • D. 

      As long as there is hydraulic fluid left in the power control backup system

  • 23. 
    On the F-15, what hydraulic indication component uses a Bourdon tube? 
    • A. 

      Pressure transmitter

    • B. 

      Pump pressure switch

    • C. 

      Over-temperature indicator

    • D. 

      Temperature volume indicator

  • 24. 
    On the F-15, what happens to the aileron servo cylinders if they lose hydraulic pressure?
    • A. 

      The pressure sensor unlocks

    • B. 

      Lock to the neutral postion

    • C. 

      The cavitation valves close

    • D. 

      Act as flutter dampers

  • 25. 
    On the F-15, how many over-temperature indicators are there in the hydraulic system?
    • A. 

      One per PC reseroir and two for the utility reservoir

    • B. 

      Two per PC reservoir and one for the utility reservoir

    • C. 

      Two per reservoir

    • D. 

      One per reservoir

  • 26. 
    On the F-15, what holds the aileron switching valve in the primary position?
    • A. 

      Normal PC system pressure

    • B. 

      Normal utility system pressure

    • C. 

      Backup utility system pressure

    • D. 

      Backup PC system pressure

  • 27. 
    On the F-15, the control stick consists of a stick grip and.......
    • A. 

      Control system damper

    • B. 

      Force transducer

    • C. 

      Ratio changer

    • D. 

      Torque tube

  • 28. 
    On the F-15, what comprises the control stick boost-and-pitch compensator?
    • A. 

      PRCA, ARI, and mixer assembly

    • B. 

      Emergency generator/stabilator selector valve and switching valves

    • C. 

      Emergency generator/stabilator selector valve and servocylinders

    • D. 

      PRCA, ARI, and control system damper

  • 29. 
    On the F-15, through which part of the torque tube does longitudinal input from the control stick travel?
    • A. 

      Inner casing

    • B. 

      Outter casing

    • C. 

      Aft control rod

    • D. 

      Center control rod

  • 30. 
    On the F-15, what control system assists the aircraft around the vertical axis?
    • A. 

      Lateral

    • B. 

      Directional

    • C. 

      Longitudinal

    • D. 

      Directional and longitudinal

  • 31. 
    On the F-15, what is the output rotation of the constant speed drive unit of the integrated drive generator?
    • A. 

      4500 RPM

    • B. 

      9000 RPM

    • C. 

      10000 RPM

    • D. 

      12000 RPM

  • 32. 
    On the F-15, the directional feel trim actuator connects to the.....
    • A. 

      Control arm off the control stick linkage

    • B. 

      Torque tube assembly aft of the rudder pedals

    • C. 

      Torque tube assembly forward of the rudder pedals

    • D. 

      Input rod that goes to the ARI

  • 33. 
    On the F-15, what type of system is the directional control system?
    • A. 

      Electrical

    • B. 

      Hydraulic

    • C. 

      Mechanical

    • D. 

      Hydromechanical

  • 34. 
    On the F-15, the speed brake selector valve is located behind...
    • A. 

      Door 88L

    • B. 

      Panel 77R

    • C. 

      Panel 66R

    • D. 

      Panel 59

  • 35. 
    On the F-15 aircraft, an aircrew can ensure they don't dump too much fuel by........
    • A. 

      Calculating their maximum landing weight before the mission

    • B. 

      Using the fuel low level warning system

    • C. 

      Using the bingo fuel indication system

    • D. 

      Closely monitoring the gages.

  • 36. 
    On the F-15, at what pressure above the utility pressure does the blowback check valve automatically retract the speed brake?
    • A. 

      2-8 psi

    • B. 

      8-12 psi

    • C. 

      10-14 psi

    • D. 

      12-16 psi

  • 37. 
    On the F-15, the fuel quantity indicators receive the fuel quantity signal from the ........
    • A. 

      Tank units

    • B. 

      Thermistors

    • C. 

      Signal conditioner

    • D. 

      Fuel low-level control unit

  • 38. 
    When you place the selector knob to the FEED tank position on the F-15 aircraft, the left and right counters, on the fuel quantity indicator represent the quantity of fuel remaining in.........
    • A. 

      Tank 2 and tank 3A, respectively

    • B. 

      Tank 3A and tank 2, respectively

    • C. 

      Tank 2, tanks 3A and 3B, respectively

    • D. 

      Tanks 3A and 3B, and tank 2, respectively

  • 39. 
    On the F-15, what position does the speed brake actuator go to by setting the speed brake switch to aft?
    • A. 

      Retract

    • B. 

      Extend

    • C. 

      Down

    • D. 

      Up

  • 40. 
    What is the main electrical component of the F-16's emergency power unit (EPU) systm?
    • A. 

      EPU/GEN test switch

    • B. 

      Emergency generator

    • C. 

      Speed controller

    • D. 

      Mode switch

  • 41. 
    All metal parts of the F-16 's hydrazine fuel tank are constructed of...
    • A. 

      Kevlar

    • B. 

      Aluminum

    • C. 

      Chromium

    • D. 

      Stainless steel.

  • 42. 
    At what pressure does the F-16's EPU nitrogen valve regulate nitrogen pressure?
    • A. 

      400 (+/- 20) psig

    • B. 

      500 (+/- 50) psig

    • C. 

      2,000 (+/- 100) psig

    • D. 

      3,000 (+/- 100) psig

  • 43. 
    The F-16's emergency generator supplies power to the ......
    • A. 

      Battery buses

    • B. 

      Monitor busus

    • C. 

      Essential buses

    • D. 

      Emergency buses

  • 44. 
    What symbol does the F-16 head-up display project when a fire ondition is detected?
    • A. 

      Fire

    • B. 

      Warn

    • C. 

      Caution

    • D. 

      Eng overtemp

  • 45. 
    The fire detection set sensing elements on the F-16 have an alarm temperature of .....
    • A. 

      400 degrees

    • B. 

      575 degrees

    • C. 

      765 degrees

    • D. 

      875 degrees

  • 46. 
    The F-16's OXY LOW warning light illuminates.......
    • A. 

      When the reserve liquid oxygen(LOX) supply is being used.

    • B. 

      At a LOX quantity level of less than 0.9 liters

    • C. 

      At a LOX quantity level of less that 0.5 liters

    • D. 

      When LOX pressure drops below 55 psig

  • 47. 
    What system malfunction causes the F-16's liquid oxygen quantity indicator to rotate counterclockwise?
    • A. 

      Shorted probe

    • B. 

      Oxygen pressure leak

    • C. 

      Moisture in the converter

    • D. 

      Short-to-ground in the high voltage side of the circuit.

  • 48. 
    A path from the liquid oxygen probes to the quantity indicator on the F-16 is provided by
    • A. 

      Coaxial cables

    • B. 

      Oxygen probes

    • C. 

      The oxygen quantity relay

    • D. 

      The oxygen low-pressure switch

  • 49. 
    On the F-16, the voids and clearances between the center conductor and the outer tube of the fire dectection set sensing elements are filled with........
    • A. 

      A temperature-sensitive salt mixture

    • B. 

      Asbestos

    • C. 

      Sealant

    • D. 

      Halon

  • 50. 
    How long does pure Halon flow to the fuel tanks before the F-16's fuel inerting shutoff valve (B) closes?
    • A. 

      15 seconds

    • B. 

      20 seconds

    • C. 

      25 minutes

    • D. 

      30 minutes

  • 51. 
    How many separate fluid chambers are in the F-16's hydraulic system A reservoir?
    • A. 

      1

    • B. 

      2

    • C. 

      3

    • D. 

      4

  • 52. 
    The F-16's hydraulic pressure filter manifold is located ........
    • A. 

      In the left MLG wheel well

    • B. 

      On the accessory drive grearbox

    • C. 

      In the right MLG wheel well

    • D. 

      In the power drive unit bay

  • 53. 
    Which valve on the F-16 relieves excessive hydraulic pressure due to thermal expansion into system return?
    • A. 

      Reservoir service manifold pressure check

    • B. 

      Reservoir service manifold fill check

    • C. 

      Reservoir service manifold relief

    • D. 

      Reservoir dump

  • 54. 
    What prevents fluid loss when the filter bowl and element are removed from the F-16's hydraulic system A pressure manifold?
    • A. 

      Gravity

    • B. 

      Check valve

    • C. 

      Hydraulic fuse

    • D. 

      Internal shutoff valve

  • 55. 
    The fluid quantity gage on the F-16's hydraulic system A reservoir displays what quantity of measure?
    • A. 

      Pints

    • B. 

      Liters

    • C. 

      Half-pints

    • D. 

      Percent of full fluid level

  • 56. 
    The F-16's flight control accumulators are......
    • A. 

      Port-type

    • B. 

      Piston-type

    • C. 

      Bladder-type

    • D. 

      Cartridge-type

  • 57. 
    Hydraulic fluid for operation of the F-16 speed brakes is supplied by hydraulic .....
    • A. 

      System A only

    • B. 

      System B only

    • C. 

      Systems A and B

    • D. 

      System A, except when the emergency hydraulic pump is operating

  • 58. 
    The delivery rating of one of the F-16 accessory drive gearbox-mounted hydraulic pumps is
    • A. 

      16.5 GPM at 3,000 psi

    • B. 

      27.5 GPM at 4,000 psi

    • C. 

      36.5 GPM at 4,000 psi

    • D. 

      42.5 GPM at 3,100 psi

  • 59. 
    Which valve in the F-16's hydraulic system A ensures emergency power unit (EPU) pump flow is not supplied to the ground test stand if connected during EPU operations?
    • A. 

      Pump pressure check

    • B. 

      Ground pressure check

    • C. 

      Reservoir service manifold relief

    • D. 

      Ground test manifold pressure check

  • 60. 
    Prebraking of the F-16's main wheels is provided to......
    • A. 

      Shorten aircraft stopping distances

    • B. 

      Self-test the brakes prior to landing

    • C. 

      Ready the brakes for high-temperature conditions

    • D. 

      Eliminate gyroscopic moments applied to the main landing gear during retraction

  • 61. 
    Which components of the F-16's brake assembly are keyed on their outside diameters to the wheel?
    • A. 

      End plates

    • B. 

      Torque tubes

    • C. 

      Rotating Discs

    • D. 

      Stationary Discs

  • 62. 
    What warns the F-16 pilot of an anti-skid system failure?
    • A. 

      Caution light

    • B. 

      Warning horn

    • C. 

      Heads up display

    • D. 

      Sinking brake pedals

  • 63. 
    The F-16's brake control unit receives electrical signals.......
    • A. 

      Only from the anti-skid control unit

    • B. 

      Directly from the wheel speed sensors

    • C. 

      Only from the brake pedal position transducers

    • D. 

      From the brake pedal position transducers and anti-skid control unit.

  • 64. 
    Which F-16 fuel tanks equally provide fuel to the engine on demand? 
    • A. 

      F1 and A1

    • B. 

      F2 and A1

    • C. 

      Forward reservoir and A1

    • D. 

      Forward and Aft reservoirs

  • 65. 
    The F-16's solenoid-operated parking valve ports hydraulic pressure from system B or....
    • A. 

      One brake accumulator to all of the brake pistons in each wheel brake assembly

    • B. 

      One brake accumulator to one set of brake pistons in each wheel brake assembly.

    • C. 

      Both brake accumulators to all of the brake pistons in each wheel brake assembly

    • D. 

      Both brake accumulators to one set of brake pistons in each wheel brake assembly

  • 66. 
    Upon landing, the F-16's leading edge flaps are automactically positioned to .......
    • A. 

      2 degrees up

    • B. 

      2 degrees down

    • C. 

      25 degress down

    • D. 

      Streamlined

  • 67. 
    The internal fuel storage styston on the F-16 consists of........
    • A. 

      Five fuel tanks

    • B. 

      Six fuel tanks

    • C. 

      Seven fuel tanks

    • D. 

      Nine fule tanks

  • 68. 
    Each of the external wing tanks on the F-16 holds.......
    • A. 

      300 gallons of fuel

    • B. 

      370 gallons of fuel

    • C. 

      300 pounds of fuel

    • D. 

      370 pounds of fuel

  • 69. 
    What does the F-16's arresting hook caustion light indicate?
    • A. 

      Arresting hook is up and locked

    • B. 

      Arresting hook is not up and locked

    • C. 

      Brake failure, deploy hook immediately

    • D. 

      Arresting hook pneumatic reservoir low

  • 70. 
    How many fuselage tank drain valves are on the F-16?
    • A. 

      5

    • B. 

      7

    • C. 

      11

    • D. 

      14

  • 71. 
    Into which fuel tanks does the F-16 external centerline transfer fuel? 
    • A. 

      A2 AND F2

    • B. 

      A1 AND F1

    • C. 

      Forward and Aft reservoirs

    • D. 

      Left and right internal wing

  • 72. 
    What provides the refuel receptacle with an emergency disconnect feature during F-16 aerial refueling?
    • A. 

      Arc suppresser

    • B. 

      Signal amplifier

    • C. 

      Pressure relief valve

    • D. 

      Hydraulically actuated latches

  • 73. 
    The vent and pressurization valve for the F-16's external fuel tanks is located on the inside of the ......
    • A. 

      Vent tank

    • B. 

      Left main landing gear wheel well

    • C. 

      Right main landing gear wheel well.

    • D. 

      External centerline tank pylon assembly

  • 74. 
    Which F-16 fuel system valve provides a redundant means of allowing air into the vent tank, thus guarding against instances of negative pressure within the fuel tanks? 
    • A. 

      Automatic drain

    • B. 

      Negative pressure relief

    • C. 

      Internal tank vent and pressurization

    • D. 

      External tank vent and pressurization

  • 75. 
    The ground air service connector for F-16 fuel tank pressurization is located.......
    • A. 

      Inside the vent tank

    • B. 

      In the left main landing gear wheel well

    • C. 

      In the right main landing gear wheel well

    • D. 

      On the external centerline tank pylon assembly

  • 76. 
    Continuous oil flow is supplied to the number three bearing of the A-10's TF34-GE-100A engine during zero- or negative-G maneuvers by the.....
    • A. 

      Auxiliary lubrication system

    • B. 

      Scavenge pump

    • C. 

      B-sump

    • D. 

      C-sump

  • 77. 
    What provides a redundant means of relieving excess pressure should the F-16's fuel system interal vent and pressurization valve fail?
    • A. 

      Automatic drain valve

    • B. 

      Remote sensing relief valve

    • C. 

      Negative pressure relief valve

    • D. 

      External tank vent and pressurization valve

  • 78. 
    The A-10 fueslage components that redistribute loads around cutouts and provide redundant load paths are.....
    • A. 

      Ribs

    • B. 

      Spars

    • C. 

      Stringers

    • D. 

      Auxiliary longerons

  • 79. 
    The number of ignitors installed on the combustor of the A-10's TF34-GE-100A engine is......
    • A. 

      1

    • B. 

      2

    • C. 

      3

    • D. 

      4

  • 80. 
    After engine shutdown, A-10 engine exhaust areas are considered hazardous for.....
    • A. 

      10 minutes

    • B. 

      15 minutes

    • C. 

      20 minutes

    • D. 

      25 minutes

  • 81. 
    On the A-10, hydraulic pressure from the left system is directed to the nose drag strut actuators by the.....
    • A. 

      Uplock cylinder

    • B. 

      Downlock override

    • C. 

      Weight-on-wheels switch

    • D. 

      Landing gear control valve

  • 82. 
    During auxiliary landing gear extension on the A-10, the left hydraulic system reservoir bootstrap pressure is ported......
    • A. 

      Overboard

    • B. 

      To the return

    • C. 

      To the accumulator

    • D. 

      To the uplock cylinders

  • 83. 
    The actuator type A-10 speed brakes use is......
    • A. 

      Dual-acting piston

    • B. 

      Unbalanced pistons

    • C. 

      Balanced pistons

    • D. 

      Tandem pistons

  • 84. 
    The percentage of engine thrust the A-10's TF34-GE-100A engine fan bypass stream accounts for is
    • A. 

      75

    • B. 

      80

    • C. 

      85

    • D. 

      90

  • 85. 
    On the A-10's fire extinguishing system, the fire extinguishing discharge switch is a.......
    • A. 

      Two-position, single-throw, center-off toggle switch

    • B. 

      Two-position, double-throw, center-off toggle switch

    • C. 

      Three-position, single-throw, center-on toggle switch

    • D. 

      Three-position, double-throw, center-off toggle switch

  • 86. 
    The A-10's fire extinguisher container fired when the extinguisher discharge switch is placed to the right is the........
    • A. 

      Auiliary power unit

    • B. 

      Forward and aft

    • C. 

      Forward

    • D. 

      Aft

  • 87. 
    The two exterior lights mounted as an assembly on the wingtips of the A-10 are the....
    • A. 

      Anti-collision and nose floodlights

    • B. 

      Nose floodlights and formation

    • C. 

      Anti-collision and position

    • D. 

      Formation and position

  • 88. 
    The nose illumination lights on the A-10 are used for......
    • A. 

      In-flight refueling

    • B. 

      Tower identification

    • C. 

      In-flight visual checks

    • D. 

      Crew chief identification

  • 89. 
    The The four mounted pads on the U-2 center section, aside from being attach points for the RG130 ground handling cart, are used for aircraft....
    • A. 

      Jacking

    • B. 

      Towing

    • C. 

      Hoisting

    • D. 

      Tie down

  • 90. 
    The aft portion of the U-2 canopy is coated with four coats of paint to......
    • A. 

      Provide shade and prevent night blindness

    • B. 

      Provide insulation from low temperatures

    • C. 

      Combat solar radiation and glare

    • D. 

      Reduce solar heat signature

  • 91. 
    To signal that the emergency start system has been activated in flight, the pilot of a U-2.....
    • A. 

      Leaves the speed brakes open

    • B. 

      Turns on the anti-collision lights

    • C. 

      Turns on the main landing gear lights

    • D. 

      Shuts the aircraft down at the end of the runway

  • 92. 
    During normal landing gear extension on the U-2, the main landing gear actuator pressure buildup is delayed until the uplock actuator has unlocked the gear by a(n).......
    • A. 

      Check valve

    • B. 

      Orifice valve

    • C. 

      Control valve

    • D. 

      Selector valve

  • 93. 
    The U-2 ailerons are adjusted to the neutral position by a......
    • A. 

      Linear actuator connected to the right aileron tab

    • B. 

      Linear actuator connedted to the left aileron tab

    • C. 

      Trim motor attached to the right aileron

    • D. 

      Trim motor attached to the left aileron

  • 94. 
    The U-2 flight control system that reduces the wing and empennage structural loading during high speed or rough air operation by shifting both aileron wing surfaces and wing flaps upward is the ......
    • A. 

      Stability augmentation

    • B. 

      Gust control

    • C. 

      Pitch trim

    • D. 

      Roll trim

  • 95. 
    The wing flaps on the U-2 are controlled.........
    • A. 

      Electrically

    • B. 

      Hydraulically

    • C. 

      Mechanically

    • D. 

      Pneumatically

  • 96. 
    The U-2 aircraft lift spoilers are used to assist in landing and ......
    • A. 

      Reduced speed

    • B. 

      Increased speed

    • C. 

      Ascent to altitude

    • D. 

      Descent from altitude

  • 97. 
    On the U-2, the speed brakes are located on.....
    • A. 

      Top of each wing

    • B. 

      The bottom of each wing

    • C. 

      Top of the center fuselage

    • D. 

      Each side of the aft fuselage

  • 98. 
    When refueling the U-2, the fuel tank filled first is the.......
    • A. 

      Left outboard wing

    • B. 

      Left inboard wing

    • C. 

      Fuselage sump

    • D. 

      Extermal

  • 99. 
    The U-2 DC generator is cooled by......
    • A. 

      Engine bleed air through the aircraft mounted accessory drive

    • B. 

      Engine bleed air through the cooling turbine

    • C. 

      Ram air through the left engine air inlet

    • D. 

      Ram air throught the right engine air inlet

  • 100. 
    The U-2 exterior lights consist of landing, anti-collision and .........
    • A. 

      Strip lights

    • B. 

      Parking lights

    • C. 

      Formation lights

    • D. 

      Navigation lights

  • 101. 
    It is critically important on the U-2 that you check the turbine bypass switch to prevent......
    • A. 

      Valve wear

    • B. 

      Battery drain

    • C. 

      Compartment fire

    • D. 

      Indicator light failure

  • 102. 
    The compression ratio of the RQ-1 Rotax 914F engine is.....
    • A. 

      4.0:1

    • B. 

      6.0:1

    • C. 

      8.0:1

    • D. 

      9.0:1

  • 103. 
    The purpose of valve lead and valve lag in the valve mechanism used on the RQ-1's reciprocating engine is to ......
    • A. 

      Decrease head pressure and slow the rate of incoming intake air into the cylinder

    • B. 

      Increase the volumetric efficiency and lower the temperature of the cylinder

    • C. 

      Increase the volumetric efficiency and lower cylinder head compression

    • D. 

      Decrease head pressure and prevent valve contact with the pistons

  • 104. 
    What type carburetors are installed on the RQ-1's engine?
    • A. 

      16-millimeter, variable depression,cross-draft butterfly valve

    • B. 

      32-millimeter, constant depression, cross-draft butterfly valve

    • C. 

      32-millimeter, variable depression, venturi-free, in-line sliding gate valve

    • D. 

      101-millimeter, variable depression, venturi-free, in-line sliding gate valve

  • 105. 
    On the RQ-1's engine, oil is forced out of the sump in the crankcase and back to the oil reservoir by.......
    • A. 

      Blow-by gases

    • B. 

      A camshaft-driven pump mounted in the crankcase

    • C. 

      An electrically operated pump mouned in the crankcase

    • D. 

      An electrically operated suction pump mounted inside the reservoir

  • 106. 
    Ignition power for the spark plugs on the RQ-1's engine is provided by a......
    • A. 

      Dual breaker-type constant discharge ignition system

    • B. 

      Dual breaker-less capacitive discharge ignition system

    • C. 

      Single breaker-type constat discharge ignition system

    • D. 

      Single breaker-less capacitive discharge ignition system

  • 107. 
    Which spark plugs are driven by power box 1 in the RQ-1's engine ignition system?
    • A. 

      Top spark plugs in all cylinders

    • B. 

      Bottom spark plugs in all cylinders

    • C. 

      All spark plugs in the left bank of cylinders

    • D. 

      Top spark plugs in cylinders 1 and 2, and the bottom spark plugs in cylinders 3 and 4

  • 108. 
    The position the A-10 feel and trim devices provide the stick to represent any trim set into the elevator actuator is.........
    • A. 

      Aft load

    • B. 

      Lateral load

    • C. 

      Positive load

    • D. 

      Neutral (zero load)

  • 109. 
    The components of the A-10 pitch and roll flight control systems that free the control stick from a control path jam are the pitch and roll.........
    • A. 

      Tab shifters

    • B. 

      Disconnectors

    • C. 

      Trim actuators

    • D. 

      Geared servo tabs

  • 110. 
    The external DC power required to power the monitored AC bus contactor coil on the U-2 is provided through......
    • A. 

      The transformer-rectifier

    • B. 

      A 28-VDC external power cable

    • C. 

      Pin E of the external AC power receptacle

    • D. 

      The A, B, and C pins of the external power receptacle

  • 111. 
    The component that algebraically adds simultaneous pitch and yaw commands to determine the required tail positions on the RQ-1 is the.........
    • A. 

      Secondary control module

    • B. 

      Primary control module

    • C. 

      Network junction board

    • D. 

      Air data terminal

  • 112. 
    Peculiar maintenance procedures exist for the U-2 because of the......
    • A. 

      Need to maintain it's lightweight characteristics

    • B. 

      Standard reconnaissance design philosophy

    • C. 

      Special purpose of the aircraft

    • D. 

      Its flight characteristics

  • 113. 
    What type of fuel tanks are used on the RQ-1?
    • A. 

      Confromal

    • B. 

      Integral wing tanks

    • C. 

      External fuselage tanks

    • D. 

      Rubberized fuel bladders mounted in the fuselage

  • 114. 
    The RQ-1 is equipped with .........
    • A. 

      Disc brakes actuated by the electrical servos

    • B. 

      Disc brakes actuated by pneumatic pressure

    • C. 

      Drum-and-shoe brakes actuated by electrical servos

    • D. 

      Multiple disc brakes actuated by hydraulic pressure

  • 115. 
    At what engine speed (in revolutions per minute{RPS}) does the starter/alternator automatically start acting as an alternator on the RQ-1?
    • A. 

      550

    • B. 

      1150

    • C. 

      1600

    • D. 

      2200

  • 116. 
    The number of liquid oxygen converters on the U-2 is......
    • A. 

      1

    • B. 

      2

    • C. 

      3

    • D. 

      4

  • 117. 
    On the RQ-1, what is the range in degrees that the nose4 wheel steering operates from either side of center? 
    • A. 

      5

    • B. 

      8

    • C. 

      15

    • D. 

      45

  • 118. 
    The feature on the RQ-1 which, through the primary control module, automatically switches the  aircraft lights on is the.......
    • A. 

      Lights-Off Range

    • B. 

      Airfield Approach

    • C. 

      Proximity detector

    • D. 

      Collision avoidance

  • 119. 
    The purpose of decambering the ailerons and flaps on the RQ-1 is to......
    • A. 

      Provide additional lift and increase takeoff speed

    • B. 

      Provide improved high-speed flight characteristics

    • C. 

      Provide improved low-speed flight characteristics and increase lift

    • D. 

      Incrase pitching moment of the wing and decrease the amount of elevator movement required during flight

  • 120. 
    What is the approximate front to back tank fuel ratio on the RQ-1
    • A. 

      1:1

    • B. 

      1:2

    • C. 

      2:3

    • D. 

      3:2

  • 121. 
    If the alternator on the RQ-1 fails, backup power is provided by.........
    • A. 

      Two lead-acid batteries

    • B. 

      Two dry-cell nickel-cadmium batteries

    • C. 

      An air turbine generator powered by ram air

    • D. 

      Two silver-zinc, rechargeable, alkaline-type batteries

  • 122. 
    On the RQ-1, the payload power distribution module is used to power the......
    • A. 

      Ignition test relays

    • B. 

      Engine bay cooling fan

    • C. 

      Fuel system pumps and relays

    • D. 

      Primary control module and the components in the foward fuselage

  • 123. 
    Outer mold line inspection will be accomplished on the F-22 when maintenance notices......
    • A. 

      Fuel leaks

    • B. 

      Hydraulic spills

    • C. 

      Low observable damage

    • D. 

      Worn nose landing gear tire

  • 124. 
    The fuel level sensors used in the RQ-1's fuel system are........
    • A. 

      Capacitance-type probes provided an 18-VAC reference voltage from the secondary control module (SCM).

    • B. 

      Capacitance-type probes provided a 12-VDC reference voltage from the SCM.

    • C. 

      Mechanical type with a single-level float and diaphragm

    • D. 

      Mechanical type with a dual-level float and diaphragm

  • 125. 
    The F-22 program that deals with the computer software configuration for the respective aircraft system is.......
    • A. 

      Selected flight

    • B. 

      Operational flight

    • C. 

      Operational control

    • D. 

      Primary flight system

  • 126. 
    On the F-22, the responsibility for all low observable maintenance rests with the.....
    • A. 

      Crew chief

    • B. 

      Aero repair

    • C. 

      System specialist

    • D. 

      Aircraft structural maintenance

  • 127. 
    On the F-22 hydraulic system, what service coupling quick-disconnect provides an alternate method to fill the hydraulic reservoir? 
    • A. 

      Auxiliary

    • B. 

      Reservoir fill

    • C. 

      Shuttle Valve

    • D. 

      Return ground service

  • 128. 
    On the F-22, what is the output pressure for the hydraulic system's pumps?
    • A. 

      3750 to 4150 psi

    • B. 

      3850 to 4150 psi

    • C. 

      3950 to 4150 psi

    • D. 

      4050 to 4150 psi

  • 129. 
     On the F-22, what prevents the maintainer from installing the filter bowl without a filter element inside?
    • A. 

      Filter bowl lever

    • B. 

      Ratchet spring lever

    • C. 

      Spring-loaded lever

    • D. 

      Safety lever lock ring

  • 130. 
    On the F-22 hydraulic control software monitors, the hydraulic system is hosted by the........
    • A. 

      IVSC

    • B. 

      CSCI

    • C. 

      ICAW

    • D. 

      FLCS

  • 131. 
    On the F-22, what performs the BIT on the hydraulic components?
    • A. 

      Software

    • B. 

      BIT sensor

    • C. 

      Diagnostics indicator

    • D. 

      Fault component indicator

  • 132. 
    On the F-22, the pressure transducer operates over a pressure range of.......
    • A. 

      0 to 2850 psig

    • B. 

      0 to 3000 psig

    • C. 

      0 to 4850 psig

    • D. 

      0 to 5000 psig

  • 133. 
    On the F-22, what provides the maintainer an indication that the filter element requires replacement? 
    • A. 

      Differential compensator

    • B. 

      Filter element indicator

    • C. 

      Selector unit indicator

    • D. 

      Differential pressure indicator

  • 134. 
    The mode on the F-22 that uses the pneumatic backup system to pressurize the uplock devices to release the landing gear for extending and locking it in the extended position is.......
    • A. 

      Maintenance

    • B. 

      Normal flight

    • C. 

      Emergency flight

    • D. 

      Rapid extension release

  • 135. 
    On the F-22, a base plate and two interchangeable brake modules make up what valve?
    • A. 

      Shuttle

    • B. 

      Anti skid

    • C. 

      Servo control

    • D. 

      Brake control

  • 136. 
    On the F-22, the wheels and tires are protected from excessive brake heat by a heat shield made out of......
    • A. 

      Brass

    • B. 

      Titanium

    • C. 

      Aluminum

    • D. 

      Stainless steel

  • 137. 
    The F-22 nose wheel may normally be turned up to 48 degrees depending on .......
    • A. 

      Nose wheel speed

    • B. 

      Rudder pedals position

    • C. 

      Deceleration of the aircraft

    • D. 

      Main landing gear wheel speed

  • 138. 
    In the F-22 nose-wheel steering system, what valve allows free castering of the nose wheel?
    • A. 

      Shuttle

    • B. 

      Control

    • C. 

      Antiskid

    • D. 

      Bleeder

  • 139. 
    The F-22 arresting gear system is pneumatically actuated and controlled .........
    • A. 

      Manually

    • B. 

      Electrically

    • C. 

      Mechanically

    • D. 

      Hydraulically

  • 140. 
    The F-22's engine fan variable vanes position is controlled by .........
    • A. 

      An actuator

    • B. 

      A control valve

    • C. 

      A manual pump

    • D. 

      An electric motor

  • 141. 
    The F-22's engine lube sustem contains oil in the bearing compartment by using ........
    • A. 

      APU supplied compressor air

    • B. 

      Engine supplied compresor air

    • C. 

      External ram air

    • D. 

      Stored air

  • 142. 
    The presence of an overheat  on the F-22 is reported for display in the cockpit by the........
    • A. 

      Integrated vehicle subsystem controller

    • B. 

      Fire dectection and warning system

    • C. 

      Thermal detection unit

    • D. 

      Optical sensors

  • 143. 
    The presence of a fire in the F-22 engine or APU compartments is reported to the fire protection module by the......
    • A. 

      Over temp sensors

    • B. 

      Voltage supply units

    • C. 

      Thermal dectection unit

    • D. 

      Optical fire dectection system

  • 144. 
    On the F-22, what components take care of the on-board engine monitoring diagnostic functions? 
    • A. 

      FADEC and CEDU

    • B. 

      DTC and CSFDR

    • C. 

      PMA and IMIS

    • D. 

      MVI and IFPC

  • 145. 
    Vibration, oil debris, oil level signals, along with condition monitoring and fault information, are stored in the F-22's resident memory of the ....
    • A. 

      DTC

    • B. 

      Air vehicle processor

    • C. 

      CEDU

    • D. 

      IMIS

  • 146. 
    The fan and compressor variable vanes, as well as the modulated exhaust cooling and exhaust nozzle all make up the F-22's engine......
    • A. 

      Thrust system

    • B. 

      Bleed air system

    • C. 

      Bypass air flow

    • D. 

      Variable geometry system

  • 147. 
    The F-22 engine monitoring system uses how many temperature sensors?
    • A. 

      2

    • B. 

      3

    • C. 

      4

    • D. 

      5

  • 148. 
    The F-22 system component that provides all electrical interconnects between the vehicle management system modules and the aircraft wiring connectors is the ..........
    • A. 

      Backplane assembly

    • B. 

      Flight control system

    • C. 

      Flight control computer

    • D. 

      Navigations system relays.

  • 149. 
    The primary flight control surfaces, engine inlet bypass louvers, nose wheel steering, engine thrust and thrust vectoring all receive commands generated by the ......
    • A. 

      Fight control computer

    • B. 

      Portable maintenance aid

    • C. 

      Avionics maintenance bus

    • D. 

      Flight safety circuit system

  • 150. 
    The F-22 unit designed to detect and shutdown an  over-voltage condition is the.....
    • A. 

      Emergency power shutoff

    • B. 

      Electrical power control

    • C. 

      Power supply module

    • D. 

      Power cut off module

  • 151. 
    Normal start and normal operating state are the two system operations of the ........
    • A. 

      Flight control computer

    • B. 

      Opersational flight program

    • C. 

      Actuator interface modules

    • D. 

      Integrated vehicle system controller

  • 152. 
    When F-22 hydraulic pressure is lost the ailerons are.......
    • A. 

      Aerodynamically centered

    • B. 

      Mechanically positioned

    • C. 

      Electrically locked

    • D. 

      Free flowing

  • 153. 
    The F-22 pitch system is augmented by......
    • A. 

      Extra large stabilizer surfaces

    • B. 

      A hydraulic boost assembly

    • C. 

      Thrust vector nozzles

    • D. 

      Air bypass