# 2a352 H F-16 Avionics

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URE QUIZ FOR FIRST SET OF 2A352 CDC'S

• 1.

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

• A.

AT THE AFT END OF THE NOSE RADOME

• B.

AT THE FORWARD END OF THE NOSE RADOME

• C.

5.0 INCHES AFT OF THE FORWARD END OF THE NOSE RADOME

• D.

5.0 INCHES FORWARD OF THE FORWARD END OF THE NOSE RADOME

C. 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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• 2.

### 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?

• A.

AFT

• B.

ABOVE

• C.

BELOW

• D.

FORWARD

B. 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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• 3.

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

• A.

IMMEDIATELY

• B.

BEFORE THE AIRCRAFT TAXIS

• C.

WHEN SHEET METAL SHOP SEES FIT

• D.

THE NEXT TIME YOU PERFORM MAINTENANCE UNDER THAT DOOR/PANEL

A. IMMEDIATELY
Explanation
Worn door/panel fasteners should be replaced immediately because they may not be able to securely hold the door or panel in place. This can pose a safety risk during flight as the door or panel could become loose or detach, potentially causing damage to the aircraft or endangering the occupants. Therefore, it is important to replace worn fasteners as soon as possible to ensure the integrity of the door or panel.

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• 4.

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

• A.

WINGS

• B.

RUDDER

• C.

VENTRAL FINS

• D.

HORIZONTAL STABILIZERS

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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• 5.

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

• A.

WING ASSEMBLY

• B.

EMPENNAGE GROUP

• C.

FUSELAGE ASSEMBLY

• D.

HORIZONTAL STABILIZERS

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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• 6.

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

• A.

Not prevent the firing of the EPU in flight

• B.

Prevent the accidental firing of the EPU only in flight

• C.

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

• D.

Prevent the accidental firing of the EPU during ground maintenance

D. 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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• 7.

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

• A.

1,100 psi

• B.

2,100 psi

• C.

3,100 psi

• D.

4,100 psi

C. 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.

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

• A.

The 8,000 foot air pressure

• B.

The 23,000 foot air pressure

• C.

Ambient (outside) air pressure

• D.

5 psi above ambient (outside) air pressure

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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• 9.

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

• A.

Control cables

• B.

Full fly-by-wire

• C.

• D.

A combination of control cables and electrical wire

B. 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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• 10.

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

• A.

Internal to the handgrip assembly

• B.

Internal to the transducer assembly

• C.

External to the handgrip assembly

• D.

External to the transducer assembly

B. 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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• 11.

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

• A.

Brake command signals only

• B.

Nosewheel steering signals only

• C.

Brake command and nosewheel steering signals

• D.

Anti-skid command and nosewheel steering signals

C. 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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• Current Version
• Mar 18, 2024
Quiz Edited by
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• Jan 08, 2012
Quiz Created by
Dlow1902

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