Fighter Aircraft Maintenance Volume 4. A-10/u-2/uav (rq-1)

100 Questions

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Aircraft Maintenance Quizzes & Trivia

Aircraft maintenance Journeyman CDC.


Questions and Answers
  • 1. 
    The A-10 Fuselage components the redistribute loads around cutouts and provide redundant load paths are
    • A. 

      Stingers

    • B. 

      Spars

    • C. 

      Auxillary longerons

    • D. 

      Ribs

  • 2. 
    To prevent potential tank explosion during combat, the Z-10's integral fuel tanks are filled with
    • A. 

      Rubber

    • B. 

      Ballistic foam

    • C. 

      Polyurethane foam

    • D. 

      Composite materials

  • 3. 
    The danger associated with a functioning lift transducer on the A-10 is
    • A. 

      Radiation

    • B. 

      Extreme heat

    • C. 

      Electrical shock

    • D. 

      Sudden movement

  • 4. 
    After engine shutdown, A-10 engine exhaust areas are considered hazardous for
    • A. 

      10 minutes

    • B. 

      15 minutes

    • C. 

      20 minutes

    • D. 

      25 minutes

  • 5. 
    The A10 main landing gear strut component that transmits torque loads from the wheel to the strut cylinder is the 
    • A. 

      Trunnion

    • B. 

      Shock strut

    • C. 

      Torque arms

    • D. 

      Piston assembly

  • 6. 
    On the A-10, the main landing gear uplock cylinder hydraulically releases the uplock
    • A. 

      Hooks

    • B. 

      Rollers

    • C. 

      Switch

    • D. 

      Mechanism

  • 7. 
    The number of fusible plugs incorporated in each A-10 main landing gear wheel is
    • A. 

      Two

    • B. 

      Three

    • C. 

      Four

    • D. 

      Five

  • 8. 
    The A-10 nose wheel steering is initiated in the commanded direction by the movement of the rudder pedals in conjunction with a steering command signal generated by the
    • A. 

      Steering switch

    • B. 

      Steering collar assembly

    • C. 

      Position transducer potentiometer

    • D. 

      Steering unit

  • 9. 
    If electrical power is lost, the operable A-10 nose wheel steering mode is 
    • A. 

      Steering

    • B. 

      Fail-safe

    • C. 

      Auxiliary

    • D. 

      Damper-caster

  • 10. 
    The brake system of the A-10 consist of a normal, an emergency, and an 
    • A. 

      Electronic stability system

    • B. 

      All-weather system

    • C. 

      All-terrain system

    • D. 

      Anti-skid systerm

  • 11. 
    Should the left and right hydraulic systems fail, emergency braking power for the A-10 is provided by
    • A. 

      The dual power brake valve

    • B. 

      The auxiliary power unit

    • C. 

      The cable assembly

    • D. 

      An accumulator

  • 12. 
    The A-10 anti-skid caution light on the A-10 comes on when the system 
    • A. 

      Is engaged

    • B. 

      Is disengaged

    • C. 

      Has a malfunction

    • D. 

      Engages the brakes

  • 13. 
    On the A-10, hydraulic pressure from the left system is directed to the nose drag strut actuators by 
    • A. 

      Uplock cylinder

    • B. 

      Landing gear control valve

    • C. 

      Weight-on-wheels switch

    • D. 

      Downlock override

  • 14. 
    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

  • 15. 
    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)

  • 16. 
    The components of the A-110 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. 

      Trim actuators

    • C. 

      Disconnectors

    • D. 

      Geared servo tabs

  • 17. 
    The actuator type A-10 speed brakes use is 
    • A. 

      Dual-acting pistons

    • B. 

      Unbalanced pistons

    • C. 

      Balanced pistons

    • D. 

      Tandem pistons

  • 18. 
    The number of hydraulic power supply systems on the A-10 is 
    • A. 

      One

    • B. 

      Two

    • C. 

      Three

    • D. 

      Four

  • 19. 
    The two components that make up the A-10 hydraulic power supply package are the bootstrap hydraulic
    • A. 

      Reservoir and balanced relief valve

    • B. 

      Accumulator and balanced relief valve

    • C. 

      Reservoir and supply module

    • D. 

      Accumulator and supply module

  • 20. 
    The A-10 hydraulic system component that allows fluid to pass to and charge the accumulator is the 
    • A. 

      Hydraulic pressure switch

    • B. 

      Balanced relief valve

    • C. 

      Fill rate restrictor

    • D. 

      Supply module

  • 21. 
    When hydraulic pressure is not being supplied by the auxiliary power unit (APU), small amounts of hydraulic fluid are directed the APU-driven hydraulic pump from the 
    • A. 

      Left hydraulic reservoir

    • B. 

      Right hydraulic reservoir

    • C. 

      Left engine hydraulic pump

    • D. 

      Right engine hydraulic pump

  • 22. 
    You reset the A-10hydraulic filter differential pressure (ΔP) indicator after it has actuated by 
    • A. 

      Pushing the ΔP indicator in

    • B. 

      Removing the filter bowl, inverting it, and depressing the button

    • C. 

      Removing the filter bowl, and then resetting the button

    • D. 

      Changing out the filter bowl assembly

  • 23. 
    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

  • 24. 
    The number of ignigors installed on the combustor of the A-10's TF34-GE-100A engine is 
    • A. 

      One

    • B. 

      Two

    • C. 

      Three

    • D. 

      Four

  • 25. 
    Continuous oil flow is supplied to the number three bearing if the A-10's TF34-GE-100A engine during zero- or negative-G maneuvers by the 
    • A. 

      Scavenge pump

    • B. 

      Auxiliary lubrication system

    • C. 

      B-sump

    • D. 

      C-sump

  • 26. 
    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

  • 27. 
    The A-10's fire extinguisher container fired when the extinguisher discharge switch is placed to the right is the 
    • A. 

      Auxiliary power unit

    • B. 

      Foward and aft

    • C. 

      Forward

    • D. 

      Aft

  • 28. 
    The A-10's external tank fuel feed system component that prevents the external tank from collapsing when the air pressure within the tank is less than the ambient pressure is the 
    • A. 

      Pylon pressure air line

    • B. 

      Fuel vent pressure tank

    • C. 

      Fuel vent pressure tube

    • D. 

      Negative pressure relief valve

  • 29. 
    The interface between the A-10's external fuel tanks and pylon-refueling manifold is provided by the 
    • A. 

      Boost pumps

    • B. 

      Fuel system test box

    • C. 

      Fuel control pannel

    • D. 

      Fuel disconnects

  • 30. 
    The A-10's fuel system component that diffuses the fuel spray to reduce static buildup caused by the fuel pouring into the fuel tanks during refueling is the 
    • A. 

      Pitot tube

    • B. 

      Vent tube

    • C. 

      Drain tube

    • D. 

      Piccolo tube

  • 31. 
    The component that allows verification of the operational status of the A-10's refueling system is the 
    • A. 

      Pilot valves

    • B. 

      Refueling manifold

    • C. 

      Fuel management panel

    • D. 

      Test box asembly

  • 32. 
    The A-10 can be refueled in flight by a tanker aircraft equipped with a 
    • A. 

      Static boom

    • B. 

      Flying boom

    • C. 

      Refueling basket

    • D. 

      Refueling drogue

  • 33. 
    The A-10's integrated drive generator oil supply circuit component that attracts ferrous metals particles is the 
    • A. 

      Filter

    • B. 

      Air oil cooler

    • C. 

      Pressure fill port

    • D. 

      Magnetic chip detector

  • 34. 
    The external power monitor on the A-10 measures the frequency, voltage sequence, and phase sequence of external AC power applied to the aircraft and
    • A. 

      Converts the voltage to that of the aircraft

    • B. 

      Sends the power to the generator control unit

    • C. 

      Makes the power compatible with the aircraft DC system

    • D. 

      Determines whether the power is compatible with the aircraft electrical system

  • 35. 
    The A-10's DC electrical system component that is an air-cooled transformer-rectifier is the 
    • A. 

      Inverter

    • B. 

      Converter

    • C. 

      Integrated drive generator

    • D. 

      DC motor-driven AC generator

  • 36. 
    The A-10's emergency power system consists of a battery and a(n)
    • A. 

      Directional control unit

    • B. 

      Inverter

    • C. 

      Generator control unit

    • D. 

      Converter

  • 37. 
    The two exterior lights mounted as an assembly on the wingtips of the A-10 are the
    • A. 

      Anti-collision and position

    • B. 

      Nose floodlights and formatoin

    • C. 

      Formation and position

    • D. 

      Anti-collision and nose floodlights

  • 38. 
    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 identifcation

  • 39. 
    The oxygen regulator supply lever on the A-10 is
    • A. 

      Red

    • B. 

      Blue

    • C. 

      Green

    • D. 

      White

  • 40. 
    During inhalation,the A-10's oxygen regulator flow indicator should show
    • A. 

      White

    • B. 

      Black

    • C. 

      Red

    • D. 

      Green

  • 41. 
    The four mount 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

  • 42. 
    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

  • 43. 
    To signal that the emergency start system has been activated in flight, the pilot of a U-2 
    • A. 

      Turns on the anti-collision lights

    • B. 

      Turns on the main landing gear lights

    • C. 

      Leaves the speed brakes open

    • D. 

      Shuts the aircraft down at the end of the runway

  • 44. 
    The automated weight and balance program used on the U-2 is maintained by 
    • A. 

      The crew chief

    • B. 

      Quality assureance

    • C. 

      Factory representives

    • D. 

      The Senior Year program officer

  • 45. 
    All items, not part of the basic weight, installed on the U-2 aircraft are recorded on the
    • A. 

      AFTO Form 781A, Maintenance Discrepancy and Work Document

    • B. 

      AFTO Form 781C, Avionics Configuration and Load Status Document

    • C. 

      WR-ALC/LR Form 52, Automated Weight and Balance Form

    • D. 

      LR Form 52, Manual Weight and Balance Form

  • 46. 
    The U-2 aircraft's automated weight and balance programs daily data is gathered form the AFTO Form
    • A. 

      781A

    • B. 

      781C

    • C. 

      781H

    • D. 

      781J

  • 47. 
    The main landing gear strut on the U-2 is constructed of
    • A. 

      Aluminum alloy

    • B. 

      Stainless steel

    • C. 

      Composites

    • D. 

      Titanium

  • 48. 
    The auxiliary landing gear on the U-2 are called
    • A. 

      Wing skids

    • B. 

      Outriggers

    • C. 

      Pagos

    • D. 

      Outboard gear

  • 49. 
    If total hydraulic failure occurs on the U-2, the number of full brake applications the emergency brake accumulator supplies hydraulic pressure for is
    • A. 

      Three

    • B. 

      Five

    • C. 

      Seven

    • D. 

      Nine

  • 50. 
    During normal landing gear extension on the U-2, the main landing gear actuator pressure buildup is delayed until the uplock acuator has unlocked the gear by a(n)
    • A. 

      Check valve

    • B. 

      Orifice valve

    • C. 

      Control valve

    • D. 

      Selector valve

  • 51. 
    The U-2 ailerons are adjusted the neutral position by a 
    • A. 

      Linear actuator connected the the left aileron tab

    • B. 

      Trim motor attached to the left aileron

    • C. 

      Trim motor attached to the rifht aileron

    • D. 

      Linear actuator connected to the right aileron tab

  • 52. 
    On the U-2, you set the aileron trim tabs to neutral if they are slightly warped by 
    • A. 

      Bending the tabe until it is straight

    • B. 

      Installing a jig to realign the wing

    • C. 

      Replacing the tab and rig the roll control system

    • D. 

      Aligning the tabs as close to the middle as possible

  • 53. 
    The U-2 flight control system that reduced 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

  • 54. 
    The wing flaps on the U-2 are controlled
    • A. 

      Electrically

    • B. 

      Hydraulically

    • C. 

      Mechanically

    • D. 

      Pneumatically

  • 55. 
    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

  • 56. 
    On the U-2, the speed brakes are located on 
    • A. 

      Each side of the aft fuselage

    • B. 

      The bottom of each wing

    • C. 

      Top of the center fuselage

    • D. 

      Top of each wing

  • 57. 
    Except during system maintenance, the U-2 hydraulic reservoir should remain pressuirzed to
    • A. 

      Ensure the system seals do not dry out between flights

    • B. 

      Reduce the time required to prepared the aircraft for a mission

    • C. 

      Reduce the wear on the pressurization system during engine start

    • D. 

      Eliminate the possibility of air and contaminants entering the system

  • 58. 
    The U-2 hydraulic pump is allowed to vary the volume of fluid delivered to compensate for changes in demand by a(n)
    • A. 

      Increase or decrease in engine revolutions per minute

    • B. 

      Change in the angle between the pressure compensator and actuating cylinder

    • C. 

      Increase or decrease in the aircraft mounted accessory drive

    • D. 

      Change in the angle between the yoke and pump shaft axis

  • 59. 
    The hydraulic tubing for the U-2 horizontal stabilizer trim is color-coded to 
    • A. 

      Show it is a flight control line

    • B. 

      Identify the type of tubing used

    • C. 

      Show the tubing is not twisted or spliced

    • D. 

      Prevent cross-connection of lines during maintenance

  • 60. 
    The allowable leakage for static seals on the U-2 is
    • A. 

      None

    • B. 

      A few drops overnight

    • C. 

      Two drops per minute when pressurized

    • D. 

      Two drops per minute when not pressurized

  • 61. 
    The acceptable leakage for the flap dynamic seals on the U-2 is
    • A. 

      None

    • B. 

      A few drops overnight

    • C. 

      Two drops per minute when pressurized

    • D. 

      Two drops per minute when not pressurized

  • 62. 
    The U-2 exhaust system consists of the tail pipe and
    • A. 

      Accessory gear box

    • B. 

      Main engine control

    • C. 

      Low pressure turbine

    • D. 

      Fan flow adapter diverter

  • 63. 
    The three operating modes of the U-2 aircraft mounted accessory drive are
    • A. 

      Overdrive, straight drive, and subsystem checkout

    • B. 

      Engine-starting, accessory drive, and subsystem checkout

    • C. 

      Engine-starting, accessory drive, and underdrive

    • D. 

      Overdrive, underdrive, and straight drive

  • 64. 
    The U-2 cockpit indicator that provides an indication of high-pressure compressor rotor operation is the
    • A. 

      N1 RPM

    • B. 

      N2 RPM

    • C. 

      Fan discharge sensor

    • D. 

      Engine pressure ratio

  • 65. 
    When refueling the U-2, the fuel tank filled first is the 
    • A. 

      Left outboard wing

    • B. 

      Left inboard wing

    • C. 

      Fuselage sump

    • D. 

      External

  • 66. 
    The U-2's sump tank manifolds are checked for moisture during which inspection?
    • A. 

      Baisc post flight

    • B. 

      Thru-flight

    • C. 

      Pre-flight

    • D. 

      Periodic

  • 67. 
    The light that illuminates on the U-2 aircraft when the fuel sump reads 38 (±3) gallons remaining is the 
    • A. 

      FUEL TRANSFER

    • B. 

      FUEL UNEQUAL

    • C. 

      FUEL LEVEL LOW

    • D. 

      FUEL IMBALANCE

  • 68. 
    A momentary hammering sound when the U-2 fuel transfer valves are actuated is caused by
    • A. 

      A malfunctioning valve

    • B. 

      High fuel pressure

    • C. 

      Air in the system

    • D. 

      Low fuel level

  • 69. 
    The external DC power required to power the monitored AC bus contactor coil on the U-2 is provided through 
    • A. 

      Pin E of the external AC power receptacle

    • B. 

      The transformer-rectifier

    • C. 

      A 28-VDC external power cable

    • D. 

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

  • 70. 
    The U-2 DC generator is cooled by
    • A. 

      Engine bleed air through the aircraft mounted accessory drive

    • B. 

      Engine bleed air through the colling turbine

    • C. 

      Ram air through the left engine air inlet

    • D. 

      Ram air through the right air inlet

  • 71. 
    The U-2 exterior lights consist of landing, anti-collision and
    • A. 

      Strip lights

    • B. 

      Parking lights

    • C. 

      Formation lights

    • D. 

      Navigation lights

  • 72. 
    The navigation lights on the U-2 consist of a
    • A. 

      Red light on the left wingtip, a green light on the right wingtip, and two clear lights on the upper vertical stabilizer

    • B. 

      Green light on the left wingtip, a red light on the right wingtip, and a clear light on the upper vertical stabilizer

    • C. 

      Red light on the left wingtip, a green light on the right wingtip, and a clear light on the upper vertical stabilizer

    • D. 

      Green light on the left wingtip, a green light on the right wingtip, and two amber lights on the upper vertical stabilizer

  • 73. 
    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

  • 74. 
    The number of liquid oxygen converters on the U-2 is
    • A. 

      One

    • B. 

      Two

    • C. 

      Three

    • D. 

      Four

  • 75. 
    The U-2 technical manual section that provides you with a description of the aircraft, aircraft stations, access provisions, and drain and vent points is
    • A. 

      System

    • B. 

      General information

    • C. 

      Master drawing index

    • D. 

      Explanation of contents

  • 76. 
    The headings of the U-2 troubleshooting tables are
    • A. 

      ROOT CAUSE, INDICATED PROBLEM, AND SOLUTIONS

    • B. 

      ROOT CAUSE, ISOLATION PROCEDURE, AND SOLUTION

    • C. 

      PROBABLE CAUSE, ISOLATION OF MALFUNCTION, AND REMEDY

    • D. 

      PROBABLE CAUSE, ISOLOATION PROCEDURE, AND REMEDY

  • 77. 
    Peculiar maintenance procedures exist for the U-2 because of the 
    • A. 

      Need to maintain its lightweight characteristics

    • B. 

      Standard reconnaissance design philosophy

    • C. 

      Special purpose of the aircraft

    • D. 

      Its flight characteristics

  • 78. 
    The reference that lists suitable substitutes for U-2 aircraft is the 
    • A. 

      SP 1977, Engineering Standards Procurement Manual

    • B. 

      Consolidated Aircraft Maintenance System database listing

    • C. 

      Spare parts and Application Data List

    • D. 

      Engineering Master Drawing Index

  • 79. 
    The compression ratio of the RQ-1's Rotax 914F engine is
    • A. 

      4.0:1

    • B. 

      6.0:1

    • C. 

      8.0:1

    • D. 

      9.0:1

  • 80. 
    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

  • 81. 
    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

  • 82. 
    On 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 crankcase

    • C. 

      An electrically operated pump mounted in crankcase

    • D. 

      An electrically operated suction pump mounted inside the reservoir

  • 83. 
    Ignition power for the spark plugs on the RQ-1's engine is provided by a 
    • A. 

      Dual breaker-less capacitive discharge ignition system

    • B. 

      Dual breaker-type constant discharge ignition system

    • C. 

      Single breaker-type constant discharge ignition system

    • D. 

      Single breaker-less capacitive discharge ignition sysem

  • 84. 
    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

  • 85. 
    To disable ignition power box 1 when performing a test of ignition power box 2 in the RQ-1's ignition test circuit, ignition test relay
    • A. 

      1 must be de-energized

    • B. 

      2 must be de-energized

    • C. 

      1 must be energized

    • D. 

      2 must be energized

  • 86. 
    What type of mechanism is incorporated on the RQ-1's variable pitch propeller assembly to facilitate or perform pitch movement of the propeller blades?
    • A. 

      Rack and pinion

    • B. 

      Ring gear and drive gear

    • C. 

      Ring gear and splined shaft

    • D. 

      Gear and chain

  • 87. 
    The RQ-1 is equipped with
    • A. 

      Disc brakes actuated by electrical servos

    • B. 

      Disc brakes actuated by pneumatic pressure

    • C. 

      Drum-and-shoe brakes actuated by electrical servos

    • D. 

      Mutiple disc brakes actuated by hydraulic pressure

  • 88. 
    On the RQ-1, what is the range in degrees that the nose wheel steering operates from either side of center?
    • A. 

      5

    • B. 

      8

    • C. 

      15

    • D. 

      45

  • 89. 
    Under normal conditions, the RQ-1's gear-retract servos stop driving the landing gear
    • A. 

      After the gear has fully retracted, regardless of the amount of swing time required

    • B. 

      After a stop-detect signal is received or after driving for the maximum expected swing time

    • C. 

      Four minutes after the maximum expected swing time

    • D. 

      Three minutes after the minimum expected swing time

  • 90. 
    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. 

      Increase ptiching moment of the wing and decrease the amount of elevator movement required during flight

  • 91. 
    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

  • 92. 
    What type fuel tanks are used on the RQ-1?
    • A. 

      Conformal

    • B. 

      Rubberized fuel bladders mounted in the fuselage

    • C. 

      External fuselage tanks

    • D. 

      Integral wing tanks

  • 93. 
    The fuel level sensors used in the RQ-1's fuel system are 
    • A. 

      Mechanical type with a single-level float and diaphragm

    • B. 

      Mechanical type with a dual-level float and diaphragm

    • C. 

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

    • D. 

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

  • 94. 
    When the RQ-1's fuel system is in the normal operating mode, what are proper positions for the valves on the main and return fuel trays?
    • A. 

      Aft tank valve open on main fuel tray; forward tank valve open on return fuel tray

    • B. 

      Aft tank valve open on main fuel tray; aft tank valve open on return fuel tray

    • C. 

      Forward tank valve open on main fuel tray; aft tank valve open on return fuel tray

    • D. 

      Forward and aft tank valves open on main fuel tray; forward and aft tank valves closed on return fuel tray

  • 95. 
    What is the approximate front tank to back tank fuel ratio on the RQ-1?
    • A. 

      1:1

    • B. 

      1:2

    • C. 

      2:3

    • D. 

      3:2

  • 96. 
    At what engine speed (in revolutions per minute [RPM]) does the starter/alternator automatically start acting as an alternator on the RQ-1?
    • A. 

      550

    • B. 

      1,150

    • C. 

      1,600

    • D. 

      2,200

  • 97. 
    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

  • 98. 
    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 forward fuselage

  • 99. 
    The feature on the RQ-1 which, through the primary control module, automatically switches the aircraft lights on is the
    • A. 

      Proximity Detector

    • B. 

      Airfield Approach

    • C. 

      LIghts-Off Range

    • D. 

      Collision Avoidance

  • 100. 
    The ice detector probe on the RQ-1 detects ice
    • A. 

      Through temperature calculations

    • B. 

      Through a change in its resonant frequency

    • C. 

      By calculating probe deflection caused by the excess mass of ice

    • D. 

      By calculating the electrical resistance of the super-cooled probe surface