Fighter Aircraft Maintenance Volume 4. A-10/U-2/Uav (Rq-1)
Aircraft maintenance Journeyman CDC.
- 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
Correct Answer
C. Auxillary longeronsExplanation
Auxiliary longerons are fuselage components that help redistribute loads around cutouts and provide redundant load paths. They are additional structural members that run parallel to the main longerons and provide extra support and strength to the fuselage structure. These longerons help to distribute the loads evenly and prevent stress concentrations around cutouts, ensuring the structural integrity of the A-10 fuselage.Rate this question:
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- 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
Correct Answer
C. Polyurethane foamExplanation
Polyurethane foam is used to fill the integral fuel tanks of the Z-10 helicopter to prevent potential tank explosions during combat. Polyurethane foam is known for its excellent fire resistance and insulation properties. It acts as a barrier between the fuel and the external environment, reducing the risk of ignition and explosion. This foam also helps to absorb impact and reduce the chances of fuel leakage in case of any damage to the tanks. Therefore, filling the fuel tanks with polyurethane foam is an effective safety measure to enhance the combat survivability of the Z-10 helicopter.Rate this question:
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- 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
Correct Answer
B. Extreme heatExplanation
The danger associated with a functioning lift transducer on the A-10 is extreme heat. This means that the lift transducer can become excessively hot, posing a risk to the aircraft or personnel. Extreme heat can lead to damage or malfunction of the transducer, potentially affecting the lift control system of the aircraft. It is important to ensure proper cooling mechanisms and maintenance procedures to prevent overheating and mitigate the associated dangers.Rate this question:
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- 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
Correct Answer
B. 15 minutesExplanation
After engine shutdown, A-10 engine exhaust areas are considered hazardous for 15 minutes. This means that for the first 15 minutes after the engine is shut down, the exhaust areas of the A-10 aircraft pose a potential danger. During this time, it is important to exercise caution and avoid getting too close to these areas as they may still be hot or contain harmful substances.Rate this question:
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- 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
Correct Answer
C. Torque armsExplanation
The correct answer is torque arms. Torque arms are components of the A10 main landing gear strut that are responsible for transmitting torque loads from the wheel to the strut cylinder. They play a crucial role in maintaining stability and balance during landing and takeoff by effectively distributing the torque forces.Rate this question:
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- 6.
On the A-10, the main landing gear uplock cylinder hydraulically releases the uplock
- A.
Hooks
- B.
Rollers
- C.
Switch
- D.
Mechanism
Correct Answer
A. HooksExplanation
The main landing gear uplock cylinder on the A-10 releases the uplock hooks. These hooks are responsible for securing the landing gear in the up position. When the hydraulics release the uplock hooks, the landing gear is able to be lowered or deployed.Rate this question:
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- 7.
The number of fusible plugs incorporated in each A-10 main landing gear wheel is
- A.
Two
- B.
Three
- C.
Four
- D.
Five
Correct Answer
B. ThreeExplanation
The correct answer is three because each A-10 main landing gear wheel is equipped with three fusible plugs. These plugs are designed to melt at a specific temperature, allowing the release of hydraulic pressure and preventing the wheel from overheating or exploding in case of a fire. Having three plugs ensures redundancy and increases the safety of the landing gear system.Rate this question:
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- 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
Correct Answer
C. Position transducer potentiometerExplanation
The A-10 nose wheel steering is initiated by the movement of the rudder pedals, which provides the directional input. However, this movement alone is not sufficient to steer the nose wheel. A steering command signal is also required, which is generated by the position transducer potentiometer. This potentiometer measures the position of the rudder pedals and sends a signal to the steering unit, which then activates the nose wheel steering in the commanded direction. The steering switch and steering collar assembly are not directly involved in initiating the nose wheel steering.Rate this question:
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- 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
Correct Answer
D. Damper-casterExplanation
The operable A-10 nose wheel steering mode in the event of electrical power loss is the damper-caster mode. In this mode, the nose wheel steering is controlled by a combination of hydraulic dampers and castering action. The hydraulic dampers provide stability and control, while the castering action allows the nose wheel to freely rotate and follow the direction of the aircraft's movement. This mode ensures that the aircraft can still be maneuvered safely even without electrical power.Rate this question:
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- 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
Correct Answer(s)
A. Electronic stability system
D. Anti-skid systermExplanation
The correct answer is "electronic stability system" and "anti-skid system". The A-10 brake system includes these two components in addition to a normal and emergency system. The electronic stability system helps to maintain control and stability during braking, especially in challenging conditions. The anti-skid system prevents the wheels from locking up and skidding, improving overall braking performance and safety.Rate this question:
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- 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
Correct Answer
D. An accumulatorExplanation
In the event of both the left and right hydraulic systems failing, the A-10 relies on an accumulator to provide emergency braking power. An accumulator is a device that stores hydraulic energy, allowing it to be released when needed. In this case, the accumulator would release the stored energy to power the brakes, ensuring that the aircraft can still come to a stop safely even without hydraulic assistance.Rate this question:
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- 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
Correct Answer
B. Is disengagedExplanation
The A-10 anti-skid caution light on the A-10 comes on when the system is disengaged. This means that when the anti-skid system, which helps prevent the wheels from skidding during braking, is turned off or not functioning properly, the caution light will illuminate to alert the pilot.Rate this question:
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- 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
Correct Answer
B. Landing gear control valveExplanation
The landing gear control valve on the A-10 directs hydraulic pressure from the left system to the nose drag strut actuators. This valve is responsible for controlling the flow of hydraulic fluid to different components of the landing gear system, including the nose drag strut actuators. By directing the hydraulic pressure, the landing gear control valve ensures proper operation and functionality of the landing gear during takeoff, landing, and taxiing.Rate this question:
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- 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
Correct Answer
B. To the returnExplanation
During auxiliary landing gear extension on the A-10, the left hydraulic system reservoir bootstrap pressure is ported to the return. This means that the pressure from the left hydraulic system reservoir is redirected back to the return system. This is done to ensure proper functioning and balance of the hydraulic system during the landing gear extension process.Rate this question:
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- 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)
Correct Answer
D. Neutral (zero load)Explanation
The A-10 feel and trim devices provide the stick with a representation of the trim set into the elevator actuator. This means that the stick will not experience any load or force in any direction, indicating a neutral or zero load.Rate this question:
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- 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
Correct Answer
C. DisconnectorsExplanation
The correct answer is disconnectors. Disconnectors are components of the pitch and roll flight control systems that allow the control stick to be freed from a control path jam. These devices are designed to disconnect the control stick from the control surfaces, allowing the pilot to regain control of the aircraft in case of a jam or malfunction. Disconnectors ensure that the control stick is not mechanically linked to the control surfaces, preventing any interference or restriction in the pilot's ability to maneuver the aircraft.Rate this question:
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- 17.
The actuator type A-10 speed brakes use is
- A.
Dual-acting pistons
- B.
Unbalanced pistons
- C.
Balanced pistons
- D.
Tandem pistons
Correct Answer
B. Unbalanced pistonsExplanation
The actuator type A-10 speed brakes use unbalanced pistons. Unbalanced pistons are designed to create an uneven force distribution, which helps in quickly and forcefully retracting or extending the speed brakes. This design allows for efficient and rapid deployment of the speed brakes, enhancing the aircraft's control and maneuverability during deceleration or descent.Rate this question:
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- 18.
The number of hydraulic power supply systems on the A-10 is
- A.
One
- B.
Two
- C.
Three
- D.
Four
Correct Answer
B. TwoExplanation
The A-10 aircraft has two hydraulic power supply systems. This means that there are two separate systems in place to provide hydraulic power for various functions and components of the aircraft. Having two systems ensures redundancy and reliability, as if one system fails, the other can still provide the necessary hydraulic power. This is crucial for the safe operation of the aircraft and allows for continued functionality even in the event of a failure in one of the systems.Rate this question:
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- 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
Correct Answer
C. Reservoir and supply moduleExplanation
The correct answer is reservoir and supply module. The A-10 hydraulic power supply package consists of two components: the reservoir, which stores hydraulic fluid, and the supply module, which provides the necessary pressure and flow of hydraulic fluid to operate the aircraft's systems. These two components work together to ensure that the aircraft's hydraulic system functions properly.Rate this question:
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- 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
Correct Answer
B. Balanced relief valveExplanation
The balanced relief valve is the A-10 hydraulic system component that allows fluid to pass to and charge the accumulator. The balanced relief valve is designed to maintain a specific pressure in the hydraulic system by diverting excess fluid to the accumulator. This helps to protect the system from overpressure and ensures that the accumulator is properly charged for future use.Rate this question:
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- 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
Correct Answer
B. Right hydraulic reservoirExplanation
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.Rate this question:
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- 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
Correct Answer
B. Removing the filter bowl, inverting it, and depressing the buttonExplanation
To reset the A-10 hydraulic filter differential pressure (ΔP) indicator after it has actuated, you need to remove the filter bowl, invert it, and depress the button. This process allows the indicator to be reset and ready for further use. By removing the filter bowl, you can access the indicator, and inverting it helps to release any trapped pressure. Depressing the button ensures that the indicator is properly reset and can accurately measure the differential pressure again.Rate this question:
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- 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
Correct Answer
C. 85Explanation
The A-10's TF34-GE-100A engine fan bypass stream accounts for 85% of the engine thrust. This means that a significant portion of the engine's thrust is generated by the bypass stream, which is the air that bypasses the combustion process and flows directly out of the engine's exhaust. This design allows for improved fuel efficiency and reduced noise levels.Rate this question:
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- 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
Correct Answer
B. TwoExplanation
The correct answer is two because the question is asking about the number of ignitors installed on the combustor of the A-10's TF34-GE-100A engine. The word "ignitors" suggests that there are multiple ignitors, and the correct number is two.Rate this question:
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- 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
Correct Answer
B. Auxiliary lubrication systemExplanation
The auxiliary lubrication system is responsible for supplying continuous oil flow to the number three bearing of the A-10's TF34-GE-100A engine during zero- or negative-G maneuvers. This system ensures that the bearing is properly lubricated and protected even when the aircraft is in unconventional flight positions. The scavenge pump, B-sump, and C-sump are not specifically designed for this purpose, making the auxiliary lubrication system the correct answer.Rate this question:
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- 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
Correct Answer
D. Three-position, double-throw, center-off toggle switchExplanation
The correct answer is three-position, double-throw, center-off toggle switch. This means that the switch has three possible positions: one in which it is in the center and off, and two other positions in which it can be thrown to either side. The switch is double-throw, meaning it can connect or disconnect two different circuits. In this case, it is used for the fire extinguishing system, so it likely controls the activation and deactivation of the system. The center-off position allows for a neutral state where the system is not active.Rate this question:
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- 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
Correct Answer
C. ForwardExplanation
When the extinguisher discharge switch is placed to the right, the A-10's fire extinguisher container is fired. The term "forward" refers to the direction in which the container is fired. This suggests that the fire extinguisher container is located towards the front of the aircraft.Rate this question:
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- 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
Correct Answer(s)
A. Pylon pressure air line
D. Negative pressure relief valveExplanation
The A-10's external tank fuel feed system includes a component called the pylon pressure air line. This component is responsible for preventing the external tank from collapsing when the air pressure within the tank is lower than the ambient pressure. Additionally, the negative pressure relief valve also plays a role in maintaining the tank's integrity by releasing any excess negative pressure that may build up.Rate this question:
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- 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
Correct Answer
D. Fuel disconnectsExplanation
The interface between the A-10's external fuel tanks and pylon-refueling manifold is provided by the fuel disconnects. These fuel disconnects are responsible for connecting and disconnecting the fuel lines between the tanks and the manifold. They ensure a secure and reliable connection, allowing fuel to flow from the tanks to the manifold during refueling operations.Rate this question:
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- 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
Correct Answer
D. Piccolo tubeExplanation
The correct answer is the piccolo tube. The piccolo tube is a fuel system component in the A-10 aircraft that diffuses the fuel spray to reduce static buildup caused by the fuel pouring into the fuel tanks during refueling. It helps to prevent any potential ignition or static discharge hazards that could occur due to the fuel pouring into the tanks. The other options mentioned, such as the pitot tube, vent tube, and drain tube, are not specifically designed for this purpose.Rate this question:
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- 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
Correct Answer
D. Test box asemblyExplanation
The test box assembly is the component that allows verification of the operational status of the A-10's refueling system. It is used to test and diagnose any issues with the system, ensuring that it is functioning properly. The pilot valves, refueling manifold, and fuel management panel are not specifically designed for this purpose, making the test box assembly the correct answer.Rate this question:
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- 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
Correct Answer
B. Flying boomExplanation
The A-10 can be refueled in flight by a tanker aircraft equipped with a flying boom. A flying boom is a rigid tube that extends from the tanker aircraft and is inserted into a receptacle on the receiving aircraft, in this case, the A-10. This method of refueling allows for a faster and more efficient transfer of fuel compared to other methods such as using a refueling basket or drogue. The flying boom provides a stable and secure connection between the tanker and the A-10, ensuring a safe and successful refueling operation.Rate this question:
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- 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
Correct Answer
D. Magnetic chip detectorExplanation
The A-10's integrated drive generator oil supply circuit component that attracts ferrous metals particles is the magnetic chip detector. This component is designed to detect and collect any metallic debris or chips that may be present in the oil system. It uses a magnetic field to attract and hold onto ferrous particles, allowing maintenance crews to inspect and analyze the collected debris for any signs of engine wear or damage. This helps in identifying potential issues early on and taking necessary maintenance actions to prevent further damage to the aircraft.Rate this question:
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- 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
Correct Answer
D. Determines whether the power is compatible with the aircraft electrical systemExplanation
The external power monitor on the A-10 determines whether the power is compatible with the aircraft electrical system. This means that it checks if the frequency, voltage sequence, and phase sequence of the external AC power applied to the aircraft are within the acceptable range for the aircraft's electrical system. If the power is not compatible, the monitor may prevent the power from being sent to the generator control unit or convert it to a compatible voltage for the aircraft's DC system.Rate this question:
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- 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
Correct Answer
B. ConverterExplanation
The correct answer is converter. The A-10's DC electrical system component that is an air-cooled transformer-rectifier is a converter. A converter is a device that converts the electrical energy from one form to another. In this case, it converts the direct current (DC) power from the transformer-rectifier into alternating current (AC) power.Rate this question:
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- 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
Correct Answer
B. InverterExplanation
The A-10's emergency power system requires an inverter to convert the DC power from the battery into AC power. This is necessary because many of the aircraft's systems, such as the avionics and communication equipment, operate on AC power. The inverter ensures that these systems can continue to function even in emergency situations when the main power source is not available. The directional control unit, generator control unit, and converter are not directly related to the emergency power system of the A-10.Rate this question:
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- 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
Correct Answer
A. Anti-collision and positionExplanation
The correct answer is anti-collision and position. The A-10 aircraft has two exterior lights mounted together on its wingtips. These lights serve two purposes. The first purpose is to function as anti-collision lights, which are used to make the aircraft more visible to other aircraft in order to prevent collisions. The second purpose is to serve as position lights, indicating the aircraft's position and direction to other pilots and ground personnel. Therefore, the lights on the A-10 wingtips are specifically designed to serve both anti-collision and position functions.Rate this question:
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- 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
Correct Answer
A. In-flight refuelingExplanation
The nose illumination lights on the A-10 are used for in-flight refueling. These lights help the pilot and the tanker aircraft to visually align and connect the refueling boom with the A-10's receptacle. They provide a clear visual reference during the refueling process, ensuring safe and efficient fuel transfer while in flight.Rate this question:
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- 39.
The oxygen regulator supply lever on the A-10 is
- A.
Red
- B.
Blue
- C.
Green
- D.
White
Correct Answer
C. GreenExplanation
The oxygen regulator supply lever on the A-10 is green. This color is likely chosen to indicate that it is the correct lever to use for supplying oxygen. Green is often associated with safety and is commonly used to indicate "go" or "safe" in various contexts. In this case, the green lever would be easily identifiable and distinguishable from other levers, helping to prevent any confusion or mistakes when using the oxygen regulator.Rate this question:
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- 40.
During inhalation,the A-10's oxygen regulator flow indicator should show
- A.
White
- B.
Black
- C.
Red
- D.
Green
Correct Answer
A. WhiteExplanation
During inhalation, the A-10's oxygen regulator flow indicator should show white. This is because white indicates that the oxygen flow is normal and there are no issues with the oxygen supply. The color coding system is used to ensure that the pilots can easily identify any abnormalities or malfunctions in the oxygen flow. White is the standard color for normal flow, while other colors like black, red, and green may indicate different levels of issues or warnings.Rate this question:
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- 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
Correct Answer
D. Tie downExplanation
The four mount pads on the U-2 center section serve multiple purposes. Apart from being attach points for the RG130 ground handling cart, they are also used for aircraft jacking, towing, hoisting, and tie down. This means that the mount pads can be utilized to secure the aircraft in place during various operations, ensuring its stability and safety.Rate this question:
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- 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
Correct Answer
C. Combat solar radiation and glareExplanation
The aft portion of the U-2 canopy is coated with four coats of paint to combat solar radiation and glare. This coating helps to protect the pilot's eyes from the intense sunlight and glare that can occur at high altitudes. It also helps to reduce the amount of solar radiation that enters the cockpit, which can help to keep the interior of the aircraft cooler. This is important because excessive solar heat can affect the performance and functionality of the aircraft's instruments and systems.Rate this question:
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- 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
Correct Answer
B. Turns on the main landing gear lightsExplanation
When the emergency start system is activated in flight, the pilot of a U-2 turns on the main landing gear lights. This is because the main landing gear lights are a signal to other aircraft and ground personnel that there is an emergency situation. By turning on these lights, the pilot can alert others to the fact that they are experiencing an emergency and may require assistance or priority landing.Rate this question:
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- 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
Correct Answer
B. Quality assureanceExplanation
The correct answer is quality assurance. Quality assurance is responsible for maintaining the automated weight and balance program used on the U-2. This program ensures that the aircraft's weight is properly distributed, which is crucial for safe and efficient operation. Quality assurance personnel are trained to monitor and verify the accuracy and reliability of the program, ensuring that it is up to date and functioning correctly. They play a vital role in ensuring the overall safety and performance of the U-2 aircraft.Rate this question:
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- 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
Correct Answer
B. AFTO Form 781C, Avionics Configuration and Load Status Document -
- 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
Correct Answer
B. 781CExplanation
The correct answer is 781C. The U-2 aircraft's automated weight and balance programs gather daily data from the AFTO Form 781C.Rate this question:
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- 47.
The main landing gear strut on the U-2 is constructed of
- A.
Aluminum alloy
- B.
Stainless steel
- C.
Composites
- D.
Titanium
Correct Answer
D. TitaniumExplanation
The main landing gear strut on the U-2 is constructed of titanium. Titanium is known for its high strength-to-weight ratio, making it an ideal material for aerospace applications. It is lightweight, yet strong enough to withstand the forces and stress during landing. Additionally, titanium is highly resistant to corrosion, which is crucial for an aircraft that operates at high altitudes and in various weather conditions. Therefore, using titanium for the main landing gear strut ensures durability, reliability, and optimal performance of the U-2 aircraft.Rate this question:
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- 48.
The auxiliary landing gear on the U-2 are called
- A.
Wing skids
- B.
Outriggers
- C.
Pagos
- D.
Outboard gear
Correct Answer
C. Pagos -
- 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
Correct Answer
B. FiveExplanation
The emergency brake accumulator on the U-2 supplies hydraulic pressure for a total of five full brake applications in the event of a total hydraulic failure.Rate this question:
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- 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
Correct Answer
B. Orifice valveExplanation
The correct answer is orifice valve. 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 an orifice valve. This valve restricts the flow of hydraulic fluid, causing a delay in the pressure buildup, which allows the uplock actuator to unlock the gear before the pressure is applied. This ensures that the gear is fully unlocked and ready to extend before the pressure is applied, preventing any potential damage or malfunction during landing.Rate this question:
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Mar 22, 2023Quiz Edited by
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Jan 07, 2010Quiz Created by
Mike872208
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