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CDC 2A353-4

Volume 4. A-10/U-2/UAV (RQ-1) Aircraft Maintenance

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
Created by: kjcarter
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