2a674 Volume 2 CDC's Ure's

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2a674 Volume 2 CDC

Questions and Answers
  • 1. 

    1. (201) What type of pump is used for engine feed in the forward (FWD) and aft reservoir tanks of a fighter aircraft?

    • A.

      Dual-impeller, turbine-driven. 

    • B.

      Single-impeller, turbine-driven. 

    • C.

      Dual-impeller, electrically driven. 

    • D.

      Single-impeller, electrically driven. 

    Correct Answer
    C. Dual-impeller, electrically driven. 
  • 2. 

    2. (201) To correct a fuel imbalance caused by too much fuel in the forward fuel system of a fighter aircraft, you would place the ENGINE FEED switch in the

    • A.

      AFT position. 

    • B.

      FWD position. 

    • C.

      NORMAL position. 

    • D.

      BALANCE position. 

    Correct Answer
    B. FWD position. 
    Explanation
    To correct a fuel imbalance caused by too much fuel in the forward fuel system of a fighter aircraft, you would place the ENGINE FEED switch in the FWD position. This is because the FWD position directs fuel flow to the forward fuel system, which helps to balance the fuel distribution in the aircraft.

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  • 3. 

    3. (202) Fuel flow to the engine on a tanker aircraft is controlled by

    • A.

      An electric motor-driven shutoff valve. 

    • B.

      An electric motor-driven shuttle valve. 

    • C.

      A manually operated shutoff valve. 

    • D.

      A manually operated shuttle valve. 

    Correct Answer
    A. An electric motor-driven shutoff valve. 
    Explanation
    The fuel flow to the engine on a tanker aircraft is controlled by an electric motor-driven shutoff valve. This means that the valve is operated by an electric motor, allowing for precise control of the fuel flow. This type of valve is likely used because it provides more accurate and efficient control compared to a manually operated valve.

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  • 4. 

    4. (202) To use body tank fuel to feed the engines on a tanker aircraft, the

    • A.

      Air refueling pumps must be operating. 

    • B.

      Main tank pumps must be operating. 

    • C.

      Alternate pumps must be operating. 

    • D.

      Override pumps must be operating. 

    Correct Answer
    A. Air refueling pumps must be operating. 
    Explanation
    The correct answer is that the air refueling pumps must be operating in order to use body tank fuel to feed the engines on a tanker aircraft. This means that the aircraft is being refueled while in flight, and the air refueling pumps are responsible for transferring the fuel from the body tanks to the engines. The main tank pumps, alternate pumps, and override pumps are not relevant in this scenario and do not play a role in using body tank fuel for the engines.

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  • 5. 

    6. (202) How is fuel transferred from the reserve tank on a tanker aircraft during flight?

    • A.

      Air pressure. 

    • B.

      Gravity flow. 

    • C.

      Boost pump pressure. 

    • D.

      Override pump pressure. 

    Correct Answer
    B. Gravity flow. 
    Explanation
    Fuel is transferred from the reserve tank on a tanker aircraft during flight through gravity flow. This means that the fuel flows from the reserve tank to the main tank due to the force of gravity. This method does not require any external pressure or pumps to transfer the fuel.

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  • 6. 

    5. (202) To feed all engines from the center wing tank on a tanker aircraft, the

    • A.

      Gravity feed valve must be opened. 

    • B.

      Override wing valves must be opened. 

    • C.

      Tank to manifold valves must be opened. 

    • D.

      Air refueling to engine manifold valves must be opened. 

    Correct Answer
    C. Tank to manifold valves must be opened. 
    Explanation
    To feed all engines from the center wing tank on a tanker aircraft, the tank to manifold valves must be opened. This means that the fuel from the center wing tank needs to be allowed to flow into the manifold, which distributes the fuel to the engines. Opening the gravity feed valve would not be necessary as the fuel is not being fed by gravity alone. The override wing valves and air refueling to engine manifold valves are not mentioned in relation to feeding the engines from the center wing tank, so they are not the correct answer.

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  • 7. 

    7. (203) The output pressure and the flow ratings of a centrifugal pump are greater than the amount the system needs to

    • A.

      Provide an ample supply of fuel in case of a single pump failure. 

    • B.

      Prevent fuel boiling and evaporation in the wing tanks at high altitudes. 

    • C.

      Provide fuel to the engines during negative Gs or inverted flight conditions. 

    • D.

      Prevent the reverse flow of fuel from a pump with a greater pressure output.

    Correct Answer
    A. Provide an ample supply of fuel in case of a single pump failure. 
    Explanation
    The output pressure and flow ratings of a centrifugal pump being greater than the system's fuel requirements ensures that even if one pump fails, there will still be enough fuel supply to meet the needs of the system. This is important for maintaining the continuous operation and functionality of the system, preventing any disruptions or failures due to fuel shortage.

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  • 8. 

    8. (203) When fuel supply is required during negative gravity conditions,

    • A.

      A rotary-vane centrifugal pump is used. 

    • B.

      A dual-impeller centrifugal pump is used. 

    • C.

      An in-line ejector centrifugal pump is used. 

    • D.

      A top-mounted pump centrifugal pump is used. 

    Correct Answer
    B. A dual-impeller centrifugal pump is used. 
    Explanation
    During negative gravity conditions, a dual-impeller centrifugal pump is used to supply fuel. This type of pump is designed with two impellers, which allows it to generate higher pressure and flow rates compared to a single impeller pump. The dual-impeller design helps to overcome the challenges of negative gravity conditions and ensures efficient fuel supply.

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  • 9. 

    9. (203) For ease of maintenance, the type of centrifugal pump designed to be installed from the top of the fuel tank is a

    • A.

      Rotary-vane pump. 

    • B.

      Dual-impeller pump. 

    • C.

      Quick-change pump. 

    • D.

      Top-mounted electrically driven pump. 

    Correct Answer
    C. Quick-change pump. 
    Explanation
    A quick-change pump is designed to be easily installed and replaced, making maintenance more convenient. This type of pump allows for quick and efficient access to the fuel tank, as it can be installed from the top without the need for extensive disassembly or removal of other components. This feature reduces downtime and labor costs associated with pump maintenance, making it an ideal choice for ease of maintenance.

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  • 10. 

    10. (203) Which item would you use as a reference guide for the removing tool when installing a quick-change pump?

    • A.

      Guide plate. 

    • B.

      Guide tongue. 

    • C.

      Scroll housing. 

    • D.

      Spring-loaded safety lug. 

    Correct Answer
    A. Guide plate. 
    Explanation
    The correct answer is Guide plate. When installing a quick-change pump, the guide plate would be used as a reference guide for the removing tool. The guide plate helps to ensure that the removing tool is aligned properly and inserted correctly for the installation process.

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  • 11. 

    11. (203) Which is an advantage of the quick-change electrically driven fuel pump?

    • A.

      Requires no special tools to install. 

    • B.

      It is possible to install the wrong pump. 

    • C.

      Increases the time required for pump changes. 

    • D.

      Requires either physically entering or completely defueling the tank. 

    Correct Answer
    A. Requires no special tools to install. 
    Explanation
    The advantage of the quick-change electrically driven fuel pump is that it does not require any special tools to install. This means that it can be easily and quickly installed without the need for additional equipment or resources.

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  • 12. 

    12. (204) The flapper on a flapper-type check valve is opened by

    • A.

      Spring pressure. 

    • B.

      Hydromechanical action. 

    • C.

      Gravity flow or pump pressure. 

    • D.

      An electrical impulse to the flapper mechanism. 

    Correct Answer
    C. Gravity flow or pump pressure. 
    Explanation
    The flapper on a flapper-type check valve is opened by gravity flow or pump pressure. This means that when there is enough flow or pressure from either gravity or a pump, the flapper is pushed open, allowing fluid to pass through the valve. This is a common mechanism in check valves, which are used to allow flow in one direction while preventing backflow.

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  • 13. 

    13. (204) What type of seal is found between the disc and valve body on a disc-type valve?

    • A.

      V-ring. 

    • B.

      O-ring. 

    • C.

      Gasket. 

    • D.

      Metal-to-metal. 

    Correct Answer
    B. O-ring. 
    Explanation
    An O-ring is a type of seal that is commonly used between the disc and valve body on a disc-type valve. It is a round rubber ring that is placed in a groove on the valve body and creates a tight seal when compressed between the disc and the valve body. O-rings are known for their ability to provide a reliable and leak-free seal, making them a popular choice for various applications in the industry.

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  • 14. 

    14. (205) If you suspect leaking, the best method for troubleshooting a fighter engine feed system component is to

    • A.

      Operate the component, while looking for leaks. 

    • B.

      Pressurize the manifold with fuel and look for leaks. 

    • C.

      Stand-test with fuel for 30 minutes and look for leaks. 

    • D.

      Pressurize the manifold with air and listen for leaks. 

    Correct Answer
    B. Pressurize the manifold with fuel and look for leaks. 
    Explanation
    The best method for troubleshooting a fighter engine feed system component when suspecting leaking is to pressurize the manifold with fuel and look for leaks. This method allows for a direct examination of the component under operating conditions, ensuring that any leaks can be identified and addressed promptly.

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  • 15. 

    15. (205) You are troubleshooting a boost pump problem on a fighter aircraft. To do this properly, your first step is to check for

    • A.

      Power to the boost pump. 

    • B.

      A pressure switch reading. 

    • C.

      Continuity of the pressure switch. 

    • D.

      A direct pressure reading of the pump.

    Correct Answer
    D. A direct pressure reading of the pump.
    Explanation
    To troubleshoot a boost pump problem on a fighter aircraft, the first step is to check for a direct pressure reading of the pump. This is important because it allows you to determine if the pump is receiving the appropriate amount of pressure, which can help identify any potential issues with the pump itself. By checking the direct pressure reading, you can rule out any problems with power, pressure switch readings, or continuity of the pressure switch, and focus specifically on the pump itself.

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  • 16. 

    16. (206) Which tanks are the engines on a tanker aircraft directly fed from?

    • A.

      Main. 

    • B.

      Body. 

    • C.

      Fuselage. 

    • D.

      Auxiliary. 

    Correct Answer
    A. Main. 
    Explanation
    The engines on a tanker aircraft are directly fed from the main tanks.

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  • 17. 

    17. (206) On a tanker aircraft, where must fuel be routed to feed any engine from any main tank?

    • A.

      Forward body tank. 

    • B.

      Crossfeed manifold. 

    • C.

      Transfer manifold. 

    • D.

      Center wing tank. 

    Correct Answer
    B. Crossfeed manifold. 
    Explanation
    The fuel on a tanker aircraft must be routed to feed any engine from any main tank through the crossfeed manifold. The crossfeed manifold allows for fuel to be transferred between tanks, ensuring that all engines have access to fuel regardless of which tank it is stored in. This system allows for flexibility in fuel distribution and helps to maintain balance and stability in the aircraft during flight.

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  • 18. 

    18. (207) You are troubleshooting a malfunction of the crossfeed system on a tanker aircraft when you determine there is no pressure available to route fuel to the crossfeed manifold. The most probable cause of this malfunction is

    • A.

      A stuck open check valve. 

    • B.

      A malfunctioning boost pump. 

    • C.

      An inoperative pressure transmitter. 

    • D.

      Foreign object damage stuck in a shutoff valve. 

    Correct Answer
    B. A malfunctioning boost pump. 
    Explanation
    A malfunctioning boost pump is the most probable cause of the malfunction in the crossfeed system. The boost pump is responsible for providing pressure to route fuel to the crossfeed manifold. If the boost pump is not functioning properly, it would result in a lack of pressure and the fuel would not be able to flow to the crossfeed manifold. This would explain why there is no pressure available to route fuel in this situation.

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  • 19. 

    19. (207) You are troubleshooting a malfunction in the crossfeed system when you determine the circuit breaker for a shutoff valve continues to “pop.” The most probable of this malfunction is a. a defective circuit breaker. b. the valve motor has shorted

    • A.

      A defective circuit breaker. 

    • B.

      The valve motor has shorted out. 

    • C.

      There is too much pressure in the system. 

    • D.

      An open in the circuit shutoff valve circuit. 

    Correct Answer
    B. The valve motor has shorted out. 
    Explanation
    The most probable cause for the circuit breaker to continue "popping" in the crossfeed system is that the valve motor has shorted out. This means that there is an electrical issue with the motor, causing it to malfunction and draw excessive current, which leads to the circuit breaker tripping. This is a likely explanation because a short circuit in the motor can cause an overload in the electrical system, resulting in the circuit breaker being activated to protect the circuit from further damage.

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  • 20. 

    20. (207) Which component is designed to sense low pressure and send a signal to an indicator light?

    • A.

      Light. 

    • B.

      Gauge. 

    • C.

      Pressure switch. 

    • D.

      Pressure transmitter.

    Correct Answer
    C. Pressure switch. 
    Explanation
    A pressure switch is designed to sense low pressure and send a signal to an indicator light. When the pressure drops below a certain threshold, the pressure switch is triggered and sends an electrical signal to activate the indicator light, alerting the user to the low pressure condition. This allows for timely action to be taken to address the low pressure situation.

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  • 21. 

    21. (208) The purpose of the power transfer method on a fighter aircraft is to

    • A.

      Pressurize the tanks only. 

    • B.

      Augment fuel transfer only. 

    • C.

      Pressurize and scavenge the tanks. 

    • D.

      Augment fuel transfer and scavenge the tanks. 

    Correct Answer
    D. Augment fuel transfer and scavenge the tanks. 
    Explanation
    The purpose of the power transfer method on a fighter aircraft is to augment fuel transfer and scavenge the tanks. This means that the power transfer method is used to increase the rate at which fuel is transferred from one tank to another, as well as to remove any excess fuel or air from the tanks. This ensures that the aircraft has a steady and efficient fuel supply during flight.

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  • 22. 

    22. (208) Which fighter aircraft tank will empty first during fuel transfer of the forward (FWD) fuel system?

    • A.

      F–1. 

    • B.

      F–2. 

    • C.

      Right wing. 

    • D.

      FWD reservoir. 

    Correct Answer
    C. Right wing. 
    Explanation
    During fuel transfer of the forward (FWD) fuel system, the right wing tank will empty first.

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  • 23. 

    23. (208) How many pumps are used in the power transfer system on a fighter aircraft?

    • A.

      2

    • B.

      3

    • C.

      4

    • D.

      6

    Correct Answer
    D. 6
    Explanation
    Fighter aircraft typically have multiple pumps in their power transfer systems to ensure reliable and efficient operation. These pumps are responsible for transferring fuel, hydraulic fluid, and other essential fluids throughout the aircraft. Having multiple pumps also provides redundancy, so that if one pump fails, the others can still function and maintain the necessary power transfer. Therefore, the correct answer to the question is 6, indicating that there are six pumps used in the power transfer system of a fighter aircraft.

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  • 24. 

    24. (208) On a fighter aircraft, what type of pumps are the scavenge pumps and where are they located?

    • A.

      Ejector-type; located in the F–2 tank. 

    • B.

      Turbine-type; located in the F–2 tank. 

    • C.

      Ejector-type; located in the F–1 tank. 

    • D.

      Turbine-type; located in the F–1 tank. 

    Correct Answer
    A. Ejector-type; located in the F–2 tank. 
    Explanation
    The scavenge pumps on a fighter aircraft are ejector-type pumps and they are located in the F-2 tank.

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  • 25. 

    25. (209) You are troubleshooting a problem on a fighter aircraft. You find that none of the external tanks transferred fuel with the select switch in NORM position; however, the external wing tanks did transfer fuel with the select switch in WING FIRST position. The most probable cause of this malfunction is the

    • A.

      Inoperative wing float valve. 

    • B.

      External transfer shutoff valve is bad. 

    • C.

      External vent and pressurization valve is bad. 

    • D.

      Centerline refuel/transfer valve is inoperative. 

    Correct Answer
    D. Centerline refuel/transfer valve is inoperative. 
    Explanation
    The most probable cause of this malfunction is the inoperative centerline refuel/transfer valve. This is because the question states that none of the external tanks transferred fuel with the select switch in NORM position, but the external wing tanks did transfer fuel with the select switch in WING FIRST position. This indicates that the issue is specific to the centerline refuel/transfer valve, which is responsible for transferring fuel to the external tanks.

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  • 26. 

    26. (210) While transferring fuel from an auxiliary tank on a cargo aircraft, in order to determine if the auxiliary tank is empty, you would observe the

    • A.

      Pressure gauge. 

    • B.

      Fuel no-flow light. 

    • C.

      Fuel quantity indicator. 

    • D.

      Low-level warning light.

    Correct Answer
    C. Fuel quantity indicator. 
    Explanation
    To determine if the auxiliary tank is empty while transferring fuel from it, you would observe the fuel quantity indicator. This instrument provides a visual indication of the amount of fuel remaining in the tank. By monitoring the fuel quantity indicator, you can determine when the tank is empty and the transfer process can be stopped. The pressure gauge, fuel no-flow light, and low-level warning light are not specifically designed to indicate the fuel level in the tank, so they would not provide an accurate measurement of the tank's emptiness.

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  • 27. 

    27. (211) Which indication shows that a boost pump on a cargo aircraft is putting out sufficient pressure?

    • A.

      Pressure indicator reads 20 pounds per square inch (psi). 

    • B.

      PRESS LOW light extinguishes. 

    • C.

      Pressure indicator reads 16 psi. 

    • D.

      PRESS LOW light illuminates. 

    Correct Answer
    B. PRESS LOW light extinguishes. 
    Explanation
    When the PRESS LOW light extinguishes, it indicates that the boost pump on the cargo aircraft is putting out sufficient pressure. This means that the pump is functioning properly and maintaining the required pressure levels.

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  • 28. 

    28. (212) To prevent the introduction of foreign objects into the fuel transfer system of a cargo aircraft, the jettison mast is equipped with a

    • A.

      Flame arrestor screen. 

    • B.

      Safety wire device. 

    • C.

      Check valve. 

    • D.

      Flapper. 

    Correct Answer
    A. Flame arrestor screen. 
    Explanation
    The jettison mast in a cargo aircraft is equipped with a flame arrestor screen to prevent the introduction of foreign objects into the fuel transfer system. This screen acts as a barrier, allowing fuel to pass through while preventing any debris or foreign objects from entering the system. This helps to ensure the safety and proper functioning of the fuel transfer process.

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  • 29. 

    29. (212) Which type of fuel valves control the flow of fuel through the jettison system?

    • A.

      Vent. 

    • B.

      Refuel. 

    • C.

      Transfer. 

    • D.

      Dump. 

    Correct Answer
    D. Dump. 
    Explanation
    Fuel valves control the flow of fuel through various systems in an aircraft. In this case, the question specifically asks about the fuel valves that control the flow of fuel through the jettison system. The jettison system is used to quickly and safely dump fuel from the aircraft in emergency situations or to reduce weight for landing. Therefore, the correct answer is "Dump" as it refers to the fuel valves that control the flow of fuel through the jettison system.

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  • 30. 

    30. (213) What safety feature in the bomber aircraft fuel dump system prevents the accidental dumping of fuel while the aircraft is on the ground?

    • A.

      The DUMP switch cover is safety-wired closed. 

    • B.

      The landing gear must be in the airborne (UP) position 

    • C.

      The DUMP switch is spring-loaded to the OFF position. 

    • D.

      A shorting plug must be connected for the dump valve to open. 

    Correct Answer
    B. The landing gear must be in the airborne (UP) position 
    Explanation
    The correct answer is that the landing gear must be in the airborne (UP) position. This safety feature prevents the accidental dumping of fuel while the aircraft is on the ground. When the landing gear is in the airborne position, it ensures that the aircraft is not on the ground and therefore the fuel dump system will not activate. This is an important safety measure to prevent fuel from being accidentally dumped while the aircraft is on the ground, which could cause damage or pose a safety risk.

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  • 31. 

    31.(214) Using fuel-level control valves makes refueling a safer operation because the valves will

    • A.

      Signal the refueling monitor when to stop the fuel flow.

    • B.

      Shut down the refueling vehicle if the tanks start to overflow.

    • C.

      Provide an automatic refueling of a tank to any desired level.

    • D.

      Automatically stop the flow of fuel into a tank prior to overflow.

    Correct Answer
    D. Automatically stop the flow of fuel into a tank prior to overflow.
    Explanation
    Using fuel-level control valves can make refueling a safer operation because these valves are designed to automatically stop the flow of fuel into a tank before it reaches the point of overflow. This helps to prevent any potential accidents or spills that could occur if the tank were to overfill. By automatically shutting off the fuel flow, the valves provide a reliable safety mechanism during the refueling process.

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  • 32. 

    32.(214) What principle is used to operate fuel-level control valves?

    • A.

      Static.

    • B.

      Venturi.

    • C.

      Pressure.

    • D.

      Hydromechanical.

    Correct Answer
    D. Hydromechanical.
    Explanation
    The correct answer is Hydromechanical. Hydromechanical principle is used to operate fuel-level control valves. This means that the valves are operated by a combination of hydraulic and mechanical components, allowing for precise control of the fuel level in a system.

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  • 33. 

    33.(214) What part of a piston-type fuel-level control valve prevents fuel from entering the tank?

    • A.

      The float.

    • B.

      A spring.

    • C.

      A pilot valve.

    • D.

      The diaphragm.

    Correct Answer
    C. A pilot valve.
    Explanation
    A pilot valve is the part of a piston-type fuel-level control valve that prevents fuel from entering the tank. It is responsible for regulating the flow of fuel and ensuring that only the required amount enters the tank. The pilot valve acts as a gatekeeper, allowing fuel to pass through only when necessary and preventing any excess fuel from entering the tank. This helps maintain the appropriate fuel level and prevents overflow or leakage.

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  • 34. 

    34.(215) Approximately what percent of air space is left at the top of the tanks of a cargo aircraft afterground refueling?

    • A.

      1

    • B.

      3

    • C.

      5

    • D.

      7

    Correct Answer
    B. 3
    Explanation
    After ground refueling, approximately 3% of air space is left at the top of the tanks of a cargo aircraft.

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  • 35. 

    35.(215) Which cargo aircraft components should be operationally checked during the first fewminutes of a ground refueling operation?

    • A.

      Fuel-level control valves.

    • B.

      Separation shutoff valves.

    • C.

      Refueling isolation shutoff valves.

    • D.

      Single-point receptacle drain pump and valve.

    Correct Answer
    A. Fuel-level control valves.
    Explanation
    During the first few minutes of a ground refueling operation, it is important to operationally check the fuel-level control valves on a cargo aircraft. These valves are responsible for controlling the flow of fuel and maintaining the appropriate fuel levels in the aircraft. By checking these valves, any potential issues or malfunctions can be identified early on, ensuring the safe and efficient refueling of the aircraft.

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  • 36. 

    36.(215) To allow fuel to flow from a cargo aircraft single-point receptacle to the main wingmanifold during ground refueling, the

    • A.

      Single-point receptacle drain valve must be open.

    • B.

      Center separation valve must be open.

    • C.

      Refuel isolation valve must be open.

    • D.

      Right separation valve must be open.

    Correct Answer
    C. Refuel isolation valve must be open.
    Explanation
    The refuel isolation valve must be open in order to allow fuel to flow from a cargo aircraft single-point receptacle to the main wing manifold during ground refueling. This valve acts as a barrier between the fuel system and the refueling system, and it needs to be open to allow the fuel to pass through. The other options, such as the single-point receptacle drain valve, center separation valve, and right separation valve, are not directly involved in this process.

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  • 37. 

    37.(216) Which fuel tank on the fighter aircraft contains a bladder cell for fuel storage?

    • A.

      A–1

    • B.

      F–1.

    • C.

      Aft reservoir.

    • D.

      Foward reservoir.

    Correct Answer
    B. F–1.
    Explanation
    The correct answer is F-1. The F-1 fuel tank on the fighter aircraft contains a bladder cell for fuel storage.

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  • 38. 

    38.(216) When the forward (FWD) fuel system on the fighter aircraft is refueled, what tank will fill first?

    • A.

      F–1.

    • B.

      Left wing.

    • C.

      Right wing.

    • D.

      Reservoir.

    Correct Answer
    D. Reservoir.
    Explanation
    When the forward (FWD) fuel system on the fighter aircraft is refueled, the reservoir tank will fill first.

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  • 39. 

    39.(216) What is the refueling sequence for the aft fuel system on a fighter aircraft?

    • A.

      Aft reservoir, A–1 tank, then left wing tank.

    • B.

      A–1 tank, aft reservoir, then left wing tank.

    • C.

      Left wing tank, A–1 tank, then aft reservoir.

    • D.

      Left wing tank, aft reservoir, then A–1 tank.

    Correct Answer
    A. Aft reservoir, A–1 tank, then left wing tank.
    Explanation
    The correct answer is "Aft reservoir, A–1 tank, then left wing tank." This sequence indicates the order in which the fuel is refueled in the aft fuel system of a fighter aircraft. First, the fuel is transferred to the aft reservoir, then it is transferred to the A–1 tank, and finally, it is transferred to the left wing tank.

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  • 40. 

    40.(217) You are preparing to troubleshoot a problem on the ground refueling system for a fighter aircraft. To do this properly, you would

    • A.

      Refer to the applicable aircraft technical order.

    • B.

      Select a probable cause and remove the easiest component first.

    • C.

      Select a probable cause and remove the most difficult component first.

    • D.

      Make a list of the possible causes of the problem and begin replacing the components on your list.

    Correct Answer
    A. Refer to the applicable aircraft technical order.
    Explanation
    To troubleshoot a problem on the ground refueling system for a fighter aircraft, it is important to refer to the applicable aircraft technical order. This is because the technical order provides detailed instructions and procedures specific to the aircraft, which can help identify and resolve the issue effectively. By following the guidance in the technical order, the technician can ensure that the troubleshooting process is done properly and in accordance with the manufacturer's recommendations.

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  • 41. 

    41.(218) The reverse aerial refueling shutoff valve is aa

    • A.

      Motor-operated butterfly valve.

    • B.

      Cable-operated butterfly valve.

    • C.

      Motor-operated gate valve.

    • D.

      Cable-operated gate valve.

    Correct Answer
    A. Motor-operated butterfly valve.
    Explanation
    The reverse aerial refueling shutoff valve is a motor-operated butterfly valve. This means that it is controlled by a motor that opens and closes the valve by rotating a disc or plate in the valve body. This type of valve is commonly used in applications where a tight shut-off is required, such as in the reverse aerial refueling system. The motor-operated butterfly valve offers precise control over the flow of fluid, making it ideal for this application.

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  • 42. 

    42.(219) Which condition will result in an automatic disconnect of the boom and receptacle during aerial refueling on a bomber aircraft?

    • A.

      Low-pressure condition exists.

    • B.

      Boom travel limits are exceeded.

    • C.

      Fuel center of gravity is off balance.

    • D.

      Reset trigger on pilot’s stick is pressed.

    Correct Answer
    B. Boom travel limits are exceeded.
    Explanation
    If the boom travel limits are exceeded during aerial refueling on a bomber aircraft, it will result in an automatic disconnect of the boom and receptacle.

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  • 43. 

    43.(220) When a system malfunction on a bomber aircraft is detected by the Central Integrated Test System (CITS), a

    • A.

      Fault code is generated.

    • B.

      CITS isolation code is generated.

    • C.

      Fault identification diagram is generated.

    • D.

      CITS maintenance code (CMC) is generated.

    Correct Answer
    D. CITS maintenance code (CMC) is generated.
    Explanation
    When a system malfunction on a bomber aircraft is detected by the Central Integrated Test System (CITS), a CITS maintenance code (CMC) is generated. This code is used to identify the specific maintenance action that needs to be taken to address the fault. It helps maintenance personnel in troubleshooting and fixing the issue efficiently. The CMC provides valuable information about the fault and guides the maintenance process, ensuring that the problem is resolved effectively.

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  • 44. 

    45.(220) You are troubleshooting a problem on a bomber aircraft. At a certain point, the fault isolation diagram requests that you enter a parameter monitor code (PMC). To comply with the request, you would enter the code on the

    • A.

      Central Integrated Test System (CITS) control and display panel in the aft crew station.

    • B.

      CITS control and display panel on the windshield center post.

    • C.

      System status panel on the windshield center post.

    • D.

      System status panel in the aft crew station. 

    Correct Answer
    A. Central Integrated Test System (CITS) control and display panel in the aft crew station.
    Explanation
    The correct answer is the Central Integrated Test System (CITS) control and display panel in the aft crew station. This is because the fault isolation diagram specifically requests that the parameter monitor code (PMC) be entered on the CITS control and display panel. The other options mentioned, such as the CITS control and display panel on the windshield center post or the system status panel, are not specified in the diagram as the correct location for entering the PMC. Therefore, the correct location to comply with the request is the CITS control and display panel in the aft crew station.

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  • 45. 

    46.(221) On a cargo aircraft, the SUMP LOW lights for the main tanks 1 and 4 normally illuminate at less than how many pounds of fuel?

    • A.

      1,000.

    • B.

      1,600.

    • C.

      2,000.

    • D.

      2,600.

    Correct Answer
    A. 1,000.
    Explanation
    The SUMP LOW lights for the main tanks 1 and 4 on a cargo aircraft normally illuminate when the fuel level is less than 1,000 pounds.

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  • 46. 

    47.(222) You can determine whether the tank scavenge system on a cargo aircraft is operating properly by checking the

    • A.

      Sump low lights only.

    • B.

      Fuel quantity indicators only.

    • C.

      Sump low lights and the fuel quantity indicators.

    • D.

      Fuel-pressure indicators and the fuel quantity indicators.

    Correct Answer
    C. Sump low lights and the fuel quantity indicators.
    Explanation
    To determine whether the tank scavenge system on a cargo aircraft is operating properly, you need to check both the sump low lights and the fuel quantity indicators. The sump low lights indicate if there is any water or contaminants in the fuel tanks, while the fuel quantity indicators show the level of fuel in the tanks. By checking both of these indicators, you can ensure that the tank scavenge system is effectively removing any water or contaminants and that the fuel quantity is at the appropriate level.

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  • 47. 

    48.(223) Which situation could have a negative effect on the operation of the tank scavenge system?

    • A.

      Low-boost pump pressure.

    • B.

      Trapped fuel in surge box.

    • C.

      Jet pump control inoperative.

    • D.

      Boost-pump inlet screens clogged.

    Correct Answer
    D. Boost-pump inlet screens clogged.
    Explanation
    If the boost-pump inlet screens are clogged, it can restrict the flow of fuel into the tank scavenge system. This can result in reduced fuel supply to the engine, leading to a negative effect on the operation of the tank scavenge system.

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  • 48. 

    49.(223) What effect, if any, would a missing flapper valve in the sump box have on the operation of the tank scavenge system?

    • A.

      None.

    • B.

      Fuel would be stuck in the sump box.

    • C.

      Undesired fuel would flow into the sump box.

    • D.

      Fuel would be allowed to flow out of the sump box.

    Correct Answer
    D. Fuel would be allowed to flow out of the sump box.
    Explanation
    If the flapper valve in the sump box is missing, fuel would be allowed to flow out of the sump box. The flapper valve is responsible for preventing fuel from flowing out of the sump box and into other parts of the tank scavenge system. Without the flapper valve, there would be no barrier to stop the fuel from escaping the sump box, potentially causing fuel leakage and affecting the operation of the tank scavenge system.

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  • 49. 

    49.(223) What effect, if any, would a missing flapper valve in the sump box have on the operation of the tank scavenge system?

    • A.

      None.

    • B.

      Fuel would be stuck in the sump box.

    • C.

      Undesired fuel would flow into the sump box.

    • D.

      Fuel would be allowed to flow out of the sump box.

    Correct Answer
    D. Fuel would be allowed to flow out of the sump box.
    Explanation
    If the flapper valve is missing in the sump box, it means there is no barrier preventing fuel from flowing out of the sump box. This would allow fuel to freely flow out of the sump box, potentially causing fuel leakage or loss.

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  • 50. 

    50.(224) How is the fuel drained from the main wing manifold of a cargo aircraft after a defuel operation?

    • A.

      Gravity flow.

    • B.

      Ejector pump.

    • C.

      Rotary vane pump.

    • D.

      Poppet drain valve.

    Correct Answer
    A. Gravity flow.
    Explanation
    After a defuel operation, the fuel is drained from the main wing manifold of a cargo aircraft through gravity flow. This means that the fuel is allowed to flow out of the manifold naturally, without the need for any additional pumps or valves. Gravity flow is a simple and efficient method for draining fuel, as it relies on the force of gravity to move the fuel out of the manifold and into a collection container. This method is commonly used in aircraft fuel systems to ensure that all the fuel is safely and completely drained.

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Our quizzes are rigorously reviewed, monitored and continuously updated by our expert board to maintain accuracy, relevance, and timeliness.

  • Current Version
  • Mar 21, 2023
    Quiz Edited by
    ProProfs Editorial Team
  • Feb 05, 2020
    Quiz Created by
    Joey Gardner
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