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81 Cards in this Set
- Front
- Back
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The F-22 inspection that is accomplished within six hours of launch and only if the preflight is over 48 hours but still valid is the
(A) launch inspection (B) walk around inspection (C) end of runway inspection (D) quick turnaround inspection |
(B) walk around inspection
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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 |
(C) low observable damage
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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 |
(D) aircraft structural maintenance
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The purpose of the SAS is to outline the repair and restoration process, reliability and maintainability data collection, and time accounting for the managing the F-22's
(A) low observable system (B) scheduled maintenance (C) repair and reclaimation cycles (D) upgrade of the portable maintenance aid |
(A) low observable system
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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 |
(D) 4050 to 4150 psi
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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 |
(D) return ground service
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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 |
(C) spring-loaded lever
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On the F-22 hydraulic control software monitors, the hydraulic is hosted by the
(A) IVSC (B) CSCI (C) ICAW (D) FLCS |
(A) IVSC
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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 |
(D) 0 to 5000 psig
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On the F-22, what provides the maintainers an indication that the filter element requires replacement
(A) differential compensator (B) filter element indicator (C) selector unit indicator (D) differential pressure indicator |
(D) differential pressure indicator
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The mode on the F-22 that uses pneumatic backup system to pressurize the unlock 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 |
(C) emergency flight
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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 |
(D) brake control
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On the F-22, the wheels and tires are protected from excessive brake heat by a heat shield make out of
(A) brass (B) titanium (C) aluminum (D) stainless steel |
(D) stainless steel
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The F-22 nose-wheel may normally be turned up to 48 depending on
(A) nose wheel speed (B) rudder pedals position (C) deceleration of the aircraft (D) main landing gear wheel speed |
(D) main landing gear wheel speed
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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 |
(B) control
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The F-22 arresting gear system is pneumatically actuated and controlled
(A) manually (B) electrically (C) mechanically (D) hydraulically |
(B) electrically
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The F-22 engine fan variable vanes position is controlled by
(A) an actuator (B) a control valve (C) a manual pump (D) an electric motor |
(A) an actuator
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The engine on the F-22 contains three assemblies; external hardware, supporting ring and the fan bypass ducts that are referred to as
(A) modular (B) non-modular (C) auxiliary modular (D) augmented modular |
(B) non-modular
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The F-22's engine lube system contains oil in the bearing compartment by using
(A) APU generator (B) engine supplied compressor air (C) external ram air (D) stored air |
(B) engine supplied compressor air
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The F-22's primary source of power for the full authority digital electric control, the comprehensive engine diagnostic unit, and the ignition exciter is the
(A) APU generator (B) DC bus (C) engine generator (D) external power |
(C) engine generator
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The F-22 program that acquires data for engine mission capability, on-board diagnostic system failures, propulsion data, and characterizing mission usage is the
(A) turbine engine monitoring (B) engine data collection unit (C) advanced engine failure resolution (D) integrated management information system |
(D) advanced engine failure resolution
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IMIS displays input screens to enable the maintainer to enter suspected
(A) bit ball errors (B) fault identification codes (C) airframe management codes (D) turbine engine management codes |
(B) fault identification codes
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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 detection and warning system (C) thermal detection unit (D) optical sensors |
(A) integrated vehicle subsystem controller
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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 detection unit (D) optical fire detection system |
(D) optical fire detection system
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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 |
(A) FADEC and CEDU
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Vibration, oil debris, oil level signals, along with conditions monitoring and fault information, are stored in the F-22's resident memory of the
(A) air vehicle processor (B) DTC (C)CEDU (D) IMIS |
(C) CEDU
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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 |
(D) variable geometry system
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The F-22 engine monitoring system uses how many temperature sensors?
(A) 2 (B) 3 (C) 4 (D) 5 |
(B) 3
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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 |
(A) backplane assembly
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The primary flight control surfaces, engine inlet bypass louvers, nose wheel steering, engine thrust and thrust vectoring all receive commands generated by the
(A) flight control computer (B) potable maintenance aid (C) avionics maintenance bus (D) flight safety circuit systems |
(A) Flight contol computer
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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 |
(C) power supply module
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The F-22 program that deals with the coumputer software configuration for the respective aircraft system is
(A) selected flight (B) operational flight (C) operational control (D) primary flight system |
(B) operational fight
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Normal start and normal operating state are the two system operations of the
(A) flight control computer (B) operational flight program (C) actuator interface modules (D) integrated vehicle system controller |
(D) integrated vehicle system controller
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When the F-22 hydraulic pressure is lost the ailerons are
(A) aerodynamically centered (B) mechanically positioned (C) electrically locked (D) free flowing |
(A) aerodynamically centered
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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 |
(C) Thrust vector nozzles
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The three position, momentary action, center off switch on the F-22 flight control system panel is for the
(A) yaw trim (B) emergency flaps (C) speed brake retract (D) neutral flight control |
(A) yaw trim
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The landing gear handle controls flap settings when norm is selected on the F-22's
(A) auto pitch rock switch (B) built-in switch (C) flap alt switch (D) reset switch |
(C) flap alt switch
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F-22 lift augmentation is performed by
(A) spoilers (B) vectoring thrust (C) large stabilators (D) leading edge flaps |
(D) leading edge flaps
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The F-22 leading edge flap position is based on AOA, Mach , and altitude information computed by the
(A) flight control system (B) vehicle management system (C) stability augmentation system (D) flight management control system |
(B) vehicle management system
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On the F-22, which valve allows aerial refuel flow to the aircraft plumping and prevents flow in the reverse direction?
(A) Relief (B) check (C) bypass (D) control |
(B) check
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The primary integrated maintenance information tool used by F-22 technicians during the performance of maintenance task is the
(A) DDU (B) EPU (C) PMA (D) CAMS |
(C) PMA
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All PMA screens are provided guaranteed communication through the
(A) help menu (B) function keys (C) trusted path menu (D) start-up procedures |
(C) trusted path menu
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The F-22's PMA battery pack can increase the battery life in cold temperatures and facilitate effective charging of the battery with the use of
(A) an internal heater (B) a compartment fan (C) an automatic shutdown (D) an inactive sleep mode |
(A) an internal heater
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The U-2 hydraulic pump is allowed to vary the volume of fluid delivered to compensate for changes in demand by an
(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 |
(D) change in the angle between the yoke and pump shaft axis
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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 |
(A) scavenge pump
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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 |
(D) negative pressure relief valve
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The number of hydraulic power supply systems on the A-10 is
(A) One (B) Two (C) Three (D) Four |
(B) Two
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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 |
(C) reservoir and supply module
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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 |
(D) anti-skid systerm
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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 |
(D) PROBABLE CAUSE, ISOLOATION PROCEDURE, AND REMEDY
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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 |
(B) is disengaged
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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 restricter (D) supply module |
(B) balanced relief valve
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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 assembly |
(D) test box asembly
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The interface between the A-10's external fuel tanks and pylon-refueling manifold is provided by the
(A) boost pump (B) fuel system test box (C) fuel control panel (D) fuel disconnects |
(D) fuel disconnects
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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 |
(D) eliminate the possibility of air and contaminants entering the system
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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 |
(B) converter
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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 |
(A) each side of the aft fuselage
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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 |
(B) Aft tank valve open on main fuel tray; aft tank valve open on return fuel tray
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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) |
(C) capacitance-type probes provided a 12-VDC reference voltage from the SCM
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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 |
(D) an accumulator
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The wing flaps on the U-2 are controlled
(A) electrically (B) hydraulically (C) mechanically (D) pneumatically |
(A) electrically
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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 |
(B) right hydraulic reservoir
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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 |
(A) anti-collision and position
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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 |
(C) 15
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The vent and pressurization valve for the F-16's external fuel tank is located on the inside of the
(A) left main landing gear wheel well (B) external centerline tank pylon assembly (C) vent tank (D) right main landing gear wheel well |
(C) vent tank
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The F-16's hydraulic system A pressure filter manifold is located
(A) in the power drive unit bay (B) in the left MLG wheel well (C) on the accessory drive gearbox (D) in the right MLG wheel well |
(D) in the right MLG wheel well
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13 The hydraulic pressure transmitters on the F-16 are located
(A) In the right MLG wheel well only (B) In the left MLG wheel well only (C) in the right and left main landing gear (MLG) wheel wells (D) on each system's hydraulic pump |
(C) in the right and left main landing gear (MLG) wheel wells
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What provides a redundant means of relieving excess pressure should the F-16's fuel system internal vent and pressurization valve fail?
(A) negative pressure relief valve (B) external tank vent and pressurization valve (C) remote sensing relief valve (D) automatic drain valve |
(C) remote sensing relief valve
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The F-16's flight control accumulators are
(A) bladder-type (B) cartridge-type (C) piston-type (D) port-type |
(C) piston-type
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What serves as a central interface for the upper and lower oxygen supply hoses, vest hose, and emergency oxygen hose on F-16's modified with the pressure breathing for gravity system?
(A) oxygen distribution manifold (B) integrated terminal block (C) oxygen mask to regulator connector (D) oxygen pressure regulator |
(B) integrated terminal block
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The F-16's hydraulic linear actuator receives hydraulic pressure from
(A) Hydraulic system B only (B) Hydraulic system A only (C) Either hydraulic system A or B (D) Both hydraulic systems A and B |
(A) Hydraulic system B only
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At what pressure does the F-16's emergency power unit nitrogen valve regulate nitrogen pressure?
(A) 500 (+- 50) psig (B) 400 (+- 20) pounds per square inch gage (psig) (C) 3000 (+- 100) psig (D) 4000 (+- 100) psig |
(B) 400 (+- 20) pounds per square inch gage (psig)
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What F-16 landing gear compenent prevents extend hydraulic pressure from reaching the nose landing gear (NLG) retract actuator until the NLG door is open?
(A) NLG door sequence valve (B) NLG downlock switch (C) Landing gear selector valve (D) NLG mecanical sequence valve |
(D) NLG mecanical sequence valve
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Which F-16 flight control component receives signals from the angle- of attack transmitters?
(A) Pneumatic sensor assembly (B) Leadin edge flap command servo (C) Electronic component assembly (D) Manual trim panel |
(C) Electronic component assembly
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The fuel scavenge pumps on the F-16 receive their power from
(A) hydraulic system A (B) hydraulic system B (C) fuel bled off the transfer pumps (D) fuel bled off the boost pump |
(D) fuel bled off the boost pump
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The fuel scavenge pumps on the F-16 move the residual fuel to the
(A) Aft reservoir (B) F1 fuel tank (C) A1 fuel tank (D) Forward reservoir |
(D) Forward reservoir
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The F-16's emergency power unit provides a self-contained backup source of
(A) aircraft electrical and hydraulic power (B) thrust (C) bleed air (D) system B hydraulic power |
(A) aircraft electrical and hydraulic power
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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) Both brake accumulators to all of the brake pistons in each wheel brake assembly (C) Both brake accumulators to one set of the brake pistons in each wheel brake assembly (D) One brake accumulator to one set of the brake pistons in each wheel brake assembly |
(D) One brake accumulator to one set of the brake pistons in each wheel brake assembly
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The F-16's fuel-flow proportioner is powered by
(A) hydraulic system A (B) fuel bled off the boost pumps (C) hydraulic system B (D) fuel bled off the transfer pumps |
(A) hydraulic system A
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If the F-16's F100-PW-220's digital electronic engine control fails, engine control transfers to
(A) the engine diagnostic unit (B) electrohydraulic servo valves (C) secondary mode of operation (D) the pilot |
(C) secondary mode of operation
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After initial ignition, the main ignition spark on the F-16's F100-PW-220 engine is suppressed by
(A) two shorting switches within the main fuel control (B) combustion chamber pressure (C) the light-off detector (D) the digital electronic engine control |
(B) combustion chamber pressure
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