2a352 H F-16 Avionics

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| By Dlow1902
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Quizzes Created: 1 | Total Attempts: 134
| Attempts: 134
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  • 1/11 Questions

    3. (001) When should worn door/panel fasteners be replaced?

    • IMMEDIATELY
    • BEFORE THE AIRCRAFT TAXIS
    • WHEN SHEET METAL SHOP SEES FIT
    • THE NEXT TIME YOU PERFORM MAINTENANCE UNDER THAT DOOR/PANEL
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About This Quiz

This quiz, titled '2A352 H F-16 AVIONICS', assesses knowledge on the F-16 aircraft's structural and functional details. It covers specifics like fuselage stations, waterline measurements, and maintenance protocols, crucial for professionals in aviation maintenance and avionics.

2a352 H F-16 Avionics - Quiz

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  • 2. 

    5. (001) The leading edge flaps for the F-16 are located on the

    • WING ASSEMBLY

    • EMPENNAGE GROUP

    • FUSELAGE ASSEMBLY

    • HORIZONTAL STABILIZERS

    Correct Answer
    A. WING ASSEMBLY
    Explanation
    The correct answer is WING ASSEMBLY. The leading edge flaps for the F-16 are located on the wing assembly. The leading edge flaps are movable surfaces on the front edge of the wing that can be extended or retracted to control the airflow over the wing and improve the aircraft's performance during takeoff and landing. They help to increase lift and maneuverability at low speeds, allowing the aircraft to maintain control and stability in various flight conditions.

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  • 3. 

    6. (002) On the F-16 installing the emergency power unit (EPU) safety pin will

    • Not prevent the firing of the EPU in flight

    • Prevent the accidental firing of the EPU only in flight

    • Not prevent the firing of the EPUif the external source shuts down

    • Prevent the accidental firing of the EPU during ground maintenance

    Correct Answer
    A. Prevent the accidental firing of the EPU during ground maintenance
    Explanation
    Installing the emergency power unit (EPU) safety pin on the F-16 will prevent the accidental firing of the EPU during ground maintenance. This means that while the aircraft is on the ground and undergoing maintenance, the safety pin will ensure that the EPU does not accidentally activate. It is important to have this safety measure in place to avoid any potential accidents or damage during maintenance procedures.

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  • 4. 

    9. (002) The digital flight control system uses what means to transfer inputs to the control surfaces?

    • Control cables

    • Full fly-by-wire

    • Mechanical linkage

    • A combination of control cables and electrical wire

    Correct Answer
    A. Full fly-by-wire
    Explanation
    The correct answer is "Full fly-by-wire." In a full fly-by-wire system, inputs from the pilot are transmitted electronically to the control surfaces of the aircraft, without the use of control cables or mechanical linkages. This allows for more precise and efficient control of the aircraft, as well as reduced weight and complexity compared to traditional control systems.

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  • 5. 

    1. (001) On the F–16 aircraft, fuselage station zero (FS 0.0) is located

    • AT THE AFT END OF THE NOSE RADOME

    • AT THE FORWARD END OF THE NOSE RADOME

    • 5.0 INCHES AFT OF THE FORWARD END OF THE NOSE RADOME

    • 5.0 INCHES FORWARD OF THE FORWARD END OF THE NOSE RADOME

    Correct Answer
    A. 5.0 INCHES AFT OF THE FORWARD END OF THE NOSE RADOME
    Explanation
    Fuselage station zero (FS 0.0) on the F-16 aircraft is located 5.0 inches aft of the forward end of the nose radome. This means that FS 0.0 is a specific reference point on the aircraft's fuselage, and it is positioned behind the frontmost part of the nose radome by a distance of 5.0 inches.

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  • 6. 

    2. (001) On the F-16 aircraft, waterline 65.0 (WL 65.0) is ocated 65.0 inches in which direction from waterline 0.0?

    • AFT

    • ABOVE

    • BELOW

    • FORWARD

    Correct Answer
    A. ABOVE
    Explanation
    Waterline 65.0 (WL 65.0) is located 65.0 inches above waterline 0.0 on the F-16 aircraft. This means that WL 65.0 is positioned at a higher level compared to waterline 0.0.

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  • 7. 

    7. (002) To operate the aircraft primary flight controls, the F–16 hydraulic systems provide hydraulic pressure at approximately

    • 1,100 psi

    • 2,100 psi

    • 3,100 psi

    • 4,100 psi

    Correct Answer
    A. 3,100 psi
    Explanation
    The correct answer is 3,100 psi. The F-16 hydraulic systems provide hydraulic pressure at this level in order to operate the aircraft's primary flight controls. This high pressure is necessary to ensure that the controls respond quickly and effectively to the pilot's inputs, allowing for precise maneuvering of the aircraft.

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  • 8. 

    10. (002) Artificial feel in the digital flight control system is provided by beams and coil springs

    • Internal to the handgrip assembly

    • Internal to the transducer assembly

    • External to the handgrip assembly

    • External to the transducer assembly

    Correct Answer
    A. Internal to the transducer assembly
    Explanation
    The correct answer is "internal to the transducer assembly" because artificial feel in the digital flight control system is provided by beams and coil springs that are located inside the transducer assembly. These components are designed to simulate the tactile feedback that pilots would feel when operating traditional mechanical flight controls. By incorporating artificial feel, the digital flight control system enhances the pilot's ability to sense and respond to aircraft movements and control inputs.

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  • 9. 

    11. (002) In addition to rudder control, the rudder pedals are also used to generate

    • Brake command signals only

    • Nosewheel steering signals only

    • Brake command and nosewheel steering signals

    • Anti-skid command and nosewheel steering signals

    Correct Answer
    A. Brake command and nosewheel steering signals
    Explanation
    The rudder pedals in addition to controlling the rudder also generate brake command and nosewheel steering signals. This means that when the pilot presses on the rudder pedals, it not only moves the rudder but also sends signals to the brakes and the nosewheel steering system. This allows the pilot to control both the direction of the aircraft on the ground through nosewheel steering and the braking action when needed.

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  • 10. 

    4. (001) Which of the following structures is not part of the empennage group?

    • WINGS

    • RUDDER

    • VENTRAL FINS

    • HORIZONTAL STABILIZERS

    Correct Answer
    A. WINGS
    Explanation
    The wings are not part of the empennage group. The empennage group refers to the tail section of an aircraft, which includes the rudder, ventral fins, and horizontal stabilizers. The wings, on the other hand, are located on the main body of the aircraft and are responsible for generating lift.

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  • 11. 

    8. (002) At aircraft altitudes between 8,000 feet and 23,000 feet, the F–16 cabin pressure is regulated to

    • The 8,000 foot air pressure

    • The 23,000 foot air pressure

    • Ambient (outside) air pressure

    • 5 psi above ambient (outside) air pressure

    Correct Answer
    A. The 8,000 foot air pressure
    Explanation
    At aircraft altitudes between 8,000 feet and 23,000 feet, the F-16 cabin pressure is regulated to the 8,000 foot air pressure. This means that the cabin pressure inside the F-16 is maintained at the same level as the air pressure at 8,000 feet altitude. This is done to ensure the comfort and safety of the occupants, as maintaining a higher cabin pressure could cause discomfort or health issues due to the rapid change in altitude.

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Quiz Review Timeline (Updated): Mar 18, 2024 +

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

  • Current Version
  • Mar 18, 2024
    Quiz Edited by
    ProProfs Editorial Team
  • Jan 08, 2012
    Quiz Created by
    Dlow1902
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