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CDC 2A353-4
Volume 4. A-10/U-2/UAV (RQ-1) Aircraft Maintenance
| Question | Answer |
|---|---|
| The A-10 fuselage components that redistribute loads around cutouts and provide redundant load pats are | auxiliary longerons |
| To prevent potential tank explosion during combat, the A-10's integral fuel tanks are filled with | polyurethane foam |
| The danger associated with a functioning lift transducer on the A-10 is | extreme heat |
| After engine shutdown, A-10 engine exhaust areas are considered hazardous for | 15 minutes |
| The A-10 main landing gear strut component that transmits torque loads from the wheel to the strut cylinder is the | torque strut |
| On the A-10, the main landing gear uplock cylinder hyraulically releases the uplock | hooks |
| The number of fusible plugs incorporated in each A-10 main landing gear wheel is | three |
| 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 | position transducer potentiometer |
| If electrical power is lost, the operable A-10 nose wheel steering mode is | damper-caster |
| The brake system of the A-1o consist of a normal, an emergancy, and an | anti-skid system |
| Should the left and right hydraulic systems fail, emergency braking power for the A-10 is provided by | an accumulator |
| The A-10 anti-skid caution light on the A-10 comes on when the system | is disengaged |
| On the A-10, hydraulic pressure from the left system is directed to the nose drag strut actuators by the | landing gear control valve |
| During auxiliary landing gear extension on the A-10, the left hydraulic system reservoir bootstrap pressure is ported | to the return |
| The position the A-10 feel and trim devices provide the stick to represent any trim set into the elevator actuator is | neutral (zero load) |
| 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 | disconnectors |
| The actuator type A-10 speed brakes use is | unbalanced pistons |
| The number of hydraulic power supply systems on the A-10 is | two |
| The two components that make up the A-10 hydraulic power supply package are the bootstrap hydraulic | reservoir and supply module |
| The A-10 hydraulic system component that allows fluid to pass to and charge the accumulator is the | balanced relief valve |
| When hydraulic pressure is not being supplied by the auxiliary power unit (APU), small amounts of hydraulic fluid are directed to the APU-driven hydraulic pump from the | right hydraulic reservoir |
| You reset the A-10 hydraulic filter differential pressure (ΔP) indicator after it has actuated by | removing the filter bowl, inverting it, and depressing the button |
| The percentage of engine thrust of the A-10's TF34-GE-100A engine fan bypass stream accounts for is | 85 |
| The number of ignitors installed on the combustor of the A-10's TF34-GE-100A engine is | two |
| 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 | auxiliary lubrication system |
| On the A-10's fire extinguishing system, the fire extinguishing discharge switch is a | three-position, double-throw, center-off toggle switch |
| The A-10's fire extinguisher container fired when the extinguisher discharge switch is placed to the right is the | forward |
| 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 | negative pressure relief valve |
| The interface between the A-10's external fuel tanks and plyon-refueling manifold is provided by the | fuel disconnects |
| 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 | piccolo tube |
| The component that allows verification of the operational status of the A-10's refueling system is the | test box assembly |
| The A-10 can be refueled in flight by a tanker aircraft equipped with | flying boom |
| The A-10's integrated drive generator oil supply circuit component that attracts ferrous metal particles is the | magnetic chip detector |
| The external power monitor on the A-10 measures the frequency, voltage, and phase sequence of external AC power applied to the aircraft and | sends the power to the generator control unit |
| The A-10's DC electrical system component that is an air-cooled transformer-rectifier is the | converter |
| The A-10's emergency power system consists of a battery and a | inverter |
| The two exterior lights mounted as an assembly on the wingtips of the A-10 are the | anti-collision and position |
| The nose illumination lights on the A-10 are used for | in-flight refueling |
| The oxygen regulator supply lever on the A-10 is | green |
| During inhalation, the A-10's oxygen regulator flow indicator should show | white |
| 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 | tie down |
| The aft portion of the U-2 canopy is coated with four coats of paint to | combat solar radiation and glare |
| To signal that the emergency start system has been activated in flight, the pilot of a U-2 | turns on the main landing gear lights |
| The automated weight and balance program used on the U-2 is maintained by | quality assurance |
| All items, not part of the basic weight, installed on the U-2 aircraft are recorded on the | AFTO Form 781C, Avionics Configuration and Load Status Document |
| The U-2's aircraft's automated weight and balance programs daily data is gathered from the AFTO Form | 781C |
| The main landing gear strut on the U-2 is constructed of | titanium |
| The auxiliary landing gear on the U-2 are called | pogos |
| If total hydraulic failure occurs on the U-2, the number of full brake applications the emergency brake accumulator supplies hydraulic pressure for is | five |
| 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 | orfice valve |
| The U-2 ailerons are adjusted to the neutral position by a | linear actuator connected to the left aileron tab |
| On the U-2, you set the aileron trim tabs to neutral if they are slightly warped by | aligning the tabs as close to the middle as possible |
| 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 | gust control |
| The wing flaps on the U-2 are controlled | electrically |
| The U-2 aircraft lift spoilers are used to assist in landing and | descent from altitude |
| On the U-2, the speed brakes are located on | each side of the aft fuselage |
| Except during system maintenance, the U-2 hydraulic reservoir should remain pressurized to | eliminate the possibility of air and contaminants entering the system |
| The U-2 hydraulic pump is allowed to vary the volume of fluid delivered to compensate for changes in demand by a | change in the angle between the yoke and pump shaft axis |
| The hydraulic tubing for the U-2 horizontal stabilizer trim is color-coded to | prevent cross-connection of lines during maintenance |
| The allowable leakage for static seals on the U-2 is | none |
| The acceptable leakage for the flap dynamic seals on the U-2 is | a few drops overnight |
| The U-2 exhaust system consists of the tail pipe and | fan flow adapter diverter |
| The three operating modes of the U-2 aircraft mounted accessory drive are | engine-starting, accessory drive, and subsystem checkout |
| The U-2 cockpit indicator that provides an indication of high-pressure compressor rotor operation is the | N²RPM |
| When refueling the U-2, the fuel tank filled first is the | fuselage sump |
| The U-2's sump tank manifolds are checked for moisture during which inspection? | Basic post flight |
| The light that illuminates on the U-2 aircraft when the fuel sump reads 38 (+/- 3) gallons remaining is the | FUEL LEVEL LOW |
| A momentary hammering sound when the U-2 fuel transfer valves are actuated is caused by | air in the system |
| The external DC power required to power the monitored AC bus contactor coil on the U-2 is provided through | pin E of the external AC power receptacle |
| The U-2 DC generator is cooled by | ram air through the left engine air inlet |
| The U-2 exterior lights consist of landing, anti-collision and | navigation lights |
| The navigation lights on the U-2 consist of a | red light on the left wingtip, a green light on the right wingtip, and two clear lights on the upper vertical stabilizer |
| It is critically important on the U-2 that you check the turbine bypass switch to prevent | valve wear |
| The number of liquid oxygen convertors on the U-2 is | two |
| 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 | general information |
| The headings of the U-2 troubleshooting tables are | PROBABLY CAUSE, ISOLATION PROCEDURE, AND REMEDY |
| Peculiar maintenance procedures exist for the U-2 because of the | need to maintain its lightweight characteristics |
| The reference that lists suitable substitutes for U-2 aircraft is the | SP 1977, Engineering Standards Procurement Manual |
| The compression ratio of the RQ-1 Rotax 914F engine is | 9.0:1 |
| The purpose of valve lead and valve lag in the valve mechanism used on the RQ-1's reciprocating engine is to | increase the volumetric efficiency and lower the temperature of the cylinder |
| What type carburetors are installed on the RQ-1's engine? | 32-millimeter, constant depression, cross-draft butterfly valve |
| On the RQ-1's engine, oil is forced out of the sump in the crankcase and back to the oil reservoir by | blow-by gases |
| Ignition power for the spark plugs on the RQ-1's engine is provided by a | dual breaker-less capacitive discharge ignition system |
| Which spark plugs are driven by power box 1 in the RQ-1's engine ignition system? | Top spark plugs in cylinders 1 and 2, and the bottom spark plugs in cylinders 3 and 4 |
| 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 | 1 must be energized |
| 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? | Rack and pinion |
| The RQ-1 is equipped with | disc brakes actuated by electrical servos |
| On the RQ-1, what is the range in degrees that the nose wheel steering operates from either side of center | 15 |
| Under normal conditions, the RQ-1's gear-retract servos stop driving the landing gear | after a stop-detect signal is received or after driving for the minimum expected swing time |
| The purpose of decambering the ailerons and flaps on the RQ-1 is to | provide improved low-speed flight characteristics |
| The component that algebraically adds simultaneous pitch and yaw commands to determine the required tail positions on the RQ-1 is the | primary control module |
| What type fuel tanks are used on the RQ-1? | Rubberized fuel bladders mounted in the fuselage |
| The fuel level sensors used in the RQ-1's fuel system are | capacitance-type probes provided a 12-VDC reference voltage from the SCM |
| 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? | Aft tank valve open on main fuel tray; aft tank valve open on return fuel tray |
| What is the approximate front tank to back tank fuel ratio on the RQ-1? | 3:2 |
| At what engine speed (in revolutions per minute [RPM]) does the starter/alternator automatically start acting as an alternator on the RQ-1? | 1600 |
| If the alternator on the RQ-1 fails, backup power is provided by | two dry-cell nickel-cadmium batteries |
| On the RQ-1, the payload power distribution module is used to power the | primary control module and the components in the forward fuselage |
| The feature on the RQ-1 which, through the primary control module, automatically switches the aircraft lights on is the | Lights-Off Range |
| The ice detector probe on the RQ-1 detects ice | through a change in its resonant frequency |
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kjcarter
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