# 2a353: Fighter Aircraft Maintenance Journeyman

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Quizzes Created: 1 | Total Attempts: 490
Questions: 153 | Attempts: 490

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In the air force the aircrafts need to be in top shape in case they are called to action, this is ensured by aircraft maintenance personnel. Are you on the road to becoming a fighter aircraft maintenance journeyman and are looking for revision material? Look no further as the quiz is designed for that purpose. Give it a try.

• 1.

### The number of positions on the function switch of the AN/PSM-37 multimeter is....

• A.

2

• B.

3

• C.

5

• D.

7

D. 7
Explanation
The AN/PSM-37 multimeter has a function switch with 7 different positions. This means that the multimeter can be used for a variety of functions, such as measuring voltage, current, resistance, and other electrical parameters. Having 7 positions on the function switch allows for more versatility and flexibility in using the multimeter for different measurement tasks.

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• 2.

### To measure current flow, you connect an AN/PSM-37 multimeter in....

• A.

Series in the circuit

• B.

Parallel in the circuit

• C.

Series with the component

• D.

Parallel with the component

A. Series in the circuit
Explanation
To measure current flow, you connect an AN/PSM-37 multimeter in series in the circuit. This means that the multimeter is connected in line with the current path, allowing it to measure the current passing through the circuit. Connecting it in parallel with the component or in series with the component would not accurately measure the current flow in the circuit.

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• 3.

### The symbol entered on the forms if an aircrft exceeds the PDM cycle by 90 days and an extension is not granted is a.....

• A.

Red x

• B.

Red dash

• C.

Red diagonal

• D.

Black signature

A. Red x
Explanation
If an aircraft exceeds the PDM cycle by 90 days and an extension is not granted, the symbol entered on the forms is a red x. This symbol is used to indicate that the aircraft has exceeded the allowed time for maintenance and requires immediate attention. It serves as a visual indicator for maintenance personnel to identify the aircraft that needs to be addressed promptly.

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• 4.

### The AF IMT 2691 is used to .....

• A.

Serve as a receipt document

• B.

Serve as a shipping document

• C.

Transfer aircraft -21 equipment

• D.

Account for aircraft -21 equipment

D. Account for aircraft -21 equipment
Explanation
The AF IMT 2691 is used to account for aircraft -21 equipment. This means that it is a document that helps keep track of and record the inventory of equipment specifically used for aircraft -21. It serves as a tool to ensure that all equipment is properly documented and accounted for, making it easier to manage and maintain the inventory.

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• 5.

### On the F-15 aircraft, what is the useable pressure range for the LOX system?

• A.

35-70 psi

• B.

55-90 psi

• C.

75-100 psi

• D.

95-120 psi

B. 55-90 psi
Explanation
The usable pressure range for the LOX (liquid oxygen) system on the F-15 aircraft is between 55-90 psi. This range indicates the acceptable pressure levels for the system to function properly and deliver the required amount of liquid oxygen. Pressure below or above this range may lead to inefficient operation or potential damage to the system.

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• 6.

### On the F-15 aircraft, what component contains the logic circuits for the overheat/fire detection system?

• A.

BIT panel

• B.

Flashing relay

• C.

Control panel

• D.

Controllers

D. Controllers
Explanation
The logic circuits for the overheat/fire detection system on the F-15 aircraft are contained in the controllers. These controllers are responsible for receiving and processing signals from various sensors and components within the aircraft to detect any signs of overheating or fire. They play a crucial role in ensuring the safety and functionality of the overheat/fire detection system.

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• 7.

### The F-100 engine gearbox module is attached to the.....

• A.

Compressor intermediate case

• B.

Fan inlet case assembly

• C.

Rear turbine case

• D.

N1 section

A. Compressor intermediate case
Explanation
The F-100 engine gearbox module is attached to the compressor intermediate case. This case is a part of the engine's compressor section, which is responsible for compressing incoming air before it enters the combustion chamber. The gearbox module, which contains gears and other components, is connected to the compressor intermediate case to transmit power from the engine to various systems and components.

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• 8.

### The function of the F-100 Electronic Engine Control (EEC) is to....

• A.

Provide histroy data storage

• B.

Trim the convergent exhaust nozzle

• C.

Send signals to the cockpit indicators

• D.

Supervise the trim of the UFC and CIVV

D. Supervise the trim of the UFC and CIVV
Explanation
The F-100 Electronic Engine Control (EEC) is responsible for supervising the trim of the UFC (Upper Face Contour) and CIVV (Convergent Inlet Vane Vortex). It does not provide history data storage, trim the convergent exhaust nozzle, or send signals to the cockpit indicators. Its main function is to oversee the adjustment of the UFC and CIVV, ensuring optimal performance and efficiency.

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• 9.

### The F-100 engine exhaust nozzle position transmitter is driven by......

• A.

The convergent exhaust nozzle control

• B.

115-VAC power

• C.

26-VAC power

• D.

An air motor

A. The convergent exhaust nozzle control
Explanation
The F-100 engine exhaust nozzle position transmitter is driven by the convergent exhaust nozzle control. This means that the position of the exhaust nozzle is controlled by the convergent exhaust nozzle control, and the transmitter is responsible for transmitting the position information. It is not driven by 115-VAC power, 26-VAC power, or an air motor.

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• 10.

• A.

3

• B.

4

• C.

9

• D.

NONE

D. NONE
• 11.

### On the F-15, the Mach blocking solenoid locks the diffuser ramp in the DOWN position by.....

• A.

Energizing the shutoff valve

• B.

Closing the rate limiter valve

• C.

Opening the rate limiter valve

• D.

Deenergizing the shutoff valve

B. Closing the rate limiter valve
Explanation
The Mach blocking solenoid on the F-15 is responsible for locking the diffuser ramp in the DOWN position. This is achieved by closing the rate limiter valve. By closing this valve, the flow of air is restricted, preventing the diffuser ramp from moving upwards. This helps maintain the desired position of the ramp during high-speed flight, ensuring optimal engine performance and aircraft stability.

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• 12.

### On the F-15, which JFS fuel filter component acts like a jet pump?

• A.

Bypass valve

• B.

Fuel accumulator

• C.

Fuel shutoff valve

• D.

Fluid-flow restrictor

D. Fluid-flow restrictor
Explanation
The fluid-flow restrictor component in the JFS fuel filter of the F-15 acts like a jet pump. It restricts the flow of fuel, creating a pressure difference that helps to draw fuel from the fuel tank and deliver it to the engine. This jet pump effect is crucial for maintaining a steady fuel supply to the engine during flight operations.

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• 13.

### On the F-15, what airframe mounted accessory drive switch is commonly called the 50% switch?

• A.

Two-speed switch assembly

• B.

Oil pump and start cut-out

• C.

Power turbine overspeed

• D.

Right decoupler position

B. Oil pump and start cut-out
Explanation
The correct answer is "oil pump and start cut-out." On the F-15, the airframe mounted accessory drive switch commonly referred to as the 50% switch is the oil pump and start cut-out. This switch is responsible for controlling the operation of the oil pump and cutting off the start sequence once it reaches 50% RPM. It is an essential component in ensuring the proper functioning of the aircraft's systems.

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• 14.

### On the F-15 aircraft, the airframe mounted accessory drive component that takes the input from the pawl carrier assembly and transmits the rotational force to the power takeoff drive shaft for engine starting is the......

• A.

Layshaft

• B.

Face gear

• C.

Gear trian

• D.

Pinion gear

A. Layshaft
Explanation
The layshaft on the F-15 aircraft is responsible for taking the input from the pawl carrier assembly and transmitting the rotational force to the power takeoff drive shaft for engine starting. It is a crucial component that helps in transferring power effectively and efficiently.

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• 15.

### On the F-15, the JFS start handle input is transmitted to the JFS start control manifold by......

• A.

• B.

A cable assembly

• C.

A hydraulic signal

• D.

An electrical signal

B. A cable assembly
Explanation
The JFS start handle input on the F-15 is transmitted to the JFS start control manifold by a cable assembly. This means that the movement of the start handle is translated into mechanical motion through the use of a cable. The cable assembly ensures that the input from the pilot is accurately transmitted to the JFS start control manifold, allowing for the proper operation of the JFS (Jet Fuel Starter) system on the aircraft.

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• 16.

### The light for a borescope is transmitted by the......

• A.

Lens

• B.

Probe

• C.

View finder

• D.

Fiber optic cables

D. Fiber optic cables
Explanation
The light for a borescope is transmitted by fiber optic cables. Fiber optic cables are used to transmit light from a source to the lens of the borescope. These cables are made of thin strands of glass or plastic that can carry light over long distances without significant loss or interference. By using fiber optic cables, the light can be directed precisely to illuminate the area being inspected by the borescope, providing clear visibility and accurate imaging.

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• 17.

### On the ignition test set, what monitors the output of energy?

• A.

Stored energy meter

• B.

Potentiometer

• C.

Toggle switch

• D.

Rotary meter

A. Stored energy meter
Explanation
The stored energy meter on the ignition test set monitors the output of energy. It measures and displays the amount of energy that is stored and released during the ignition process. This allows technicians to accurately assess the performance and efficiency of the ignition system. The potentiometer, toggle switch, and rotary meter are not specifically designed to monitor the output of energy in this context.

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• 18.

### What supplies power to the engin ignition system durning an ignition test?

• A.

Electronic scaler

• B.

Ligh-off detector

• C.

Electronic trasmitter

• D.

Alternator simulator output

D. Alternator simulator output
Explanation
During an ignition test, the alternator simulator output supplies power to the engine ignition system. The alternator simulator is a device that mimics the output of an alternator, which is responsible for generating electrical power in a vehicle. By providing power to the ignition system, the alternator simulator allows for testing and troubleshooting of the ignition system without the need for the actual alternator.

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• 19.

### On the F-15, at what pressure differential does the utility thermal control valve allow fluid to bypass the heat exhanger?

• A.

32.5 psid

• B.

42.5 psid

• C.

52.5 psid

• D.

62.5 psid

C. 52.5 psid
Explanation
The utility thermal control valve on the F-15 allows fluid to bypass the heat exchanger when the pressure differential reaches 52.5 psid.

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• 20.

### When a hydraulic leak occurs in the utility system on an F-15 aircraft, how does circuit A shut off?

• A.

Pneumatically

• B.

Hydraulically

• C.

Mechanically

• D.

Electrically

C. Mechanically
Explanation
When a hydraulic leak occurs in the utility system on an F-15 aircraft, circuit A shuts off mechanically. This means that there is a mechanical mechanism in place that automatically shuts off circuit A when a hydraulic leak is detected. This is likely a safety feature to prevent further damage or potential hazards in the system.

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• 21.

### On the F-15, what holds the aileron switching valve in the primary position?

• A.

Normal PC system pressure

• B.

Normal utility system pressure

• C.

Backup utility system pressure

• D.

Backup PC system pressure

A. Normal PC system pressure
Explanation
The aileron switching valve on the F-15 is held in the primary position by normal PC (Primary Control) system pressure. The PC system is responsible for controlling the primary flight controls, including the ailerons. The normal PC system pressure ensures that the aileron switching valve remains in the primary position, allowing for proper control of the aircraft's roll movements.

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• 22.

### On the F-15 aircraft, how long does utility system non-reservoir level-sensing maintain pressure if the aircraft develops a leak in the utility hydraulic system?

• A.

Until the circuit A and B shutoff valves open.

• B.

Until the circuit A and B shutoff valves close

• C.

As long as there is hydraulic fluid left in the utility reservoir

• D.

As long as there is hydraulic fluid left in the power control backup system

C. As long as there is hydraulic fluid left in the utility reservoir
Explanation
The correct answer states that the utility system non-reservoir level-sensing maintains pressure as long as there is hydraulic fluid left in the utility reservoir. This means that even if there is a leak in the utility hydraulic system, the pressure will be maintained as long as there is fluid available in the reservoir.

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• 23.

### On the F-15, what hydraulic indication component uses a Bourdon tube?

• A.

Pressure transmitter

• B.

Pump pressure switch

• C.

Over-temperature indicator

• D.

Temperature volume indicator

A. Pressure transmitter
Explanation
A pressure transmitter is a hydraulic indication component that uses a Bourdon tube. A Bourdon tube is a type of pressure measuring device that consists of a curved tube that expands or contracts based on the pressure applied to it. This movement is then converted into an electrical signal by the pressure transmitter, which can be used to indicate the hydraulic pressure in the system.

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• 24.

### On the F-15, how many over-temperature indicators are there in the hydraulic system?

• A.

One per PC reseroir and two for the utility reservoir

• B.

Two per PC reservoir and one for the utility reservoir

• C.

Two per reservoir

• D.

One per reservoir

D. One per reservoir
Explanation
The correct answer is one per reservoir. This means that there is only one over-temperature indicator for each reservoir in the hydraulic system of the F-15 aircraft.

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• 25.

### On the F-15, the control stick consists of a stick grip and.......

• A.

Control system damper

• B.

Force transducer

• C.

Ratio changer

• D.

Torque tube

B. Force transducer
Explanation
The control stick on the F-15 consists of a stick grip and a force transducer. A force transducer is a device that measures the force applied to it and converts it into an electrical signal. In the context of the F-15, the force transducer would measure the force applied by the pilot on the control stick and transmit that information to the aircraft's control system. This allows the pilot to have precise control over the aircraft's movements based on the force they apply to the control stick.

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• 26.

### On the F-15, what comprises the control stick boost-and-pitch compensator?

• A.

PRCA, ARI, and mixer assembly

• B.

Emergency generator/stabilator selector valve and switching valves

• C.

Emergency generator/stabilator selector valve and servocylinders

• D.

PRCA, ARI, and control system damper

D. PRCA, ARI, and control system damper
Explanation
The control stick boost-and-pitch compensator on the F-15 comprises the PRCA (Pitch Rate Command Amplifier), ARI (Automatic Recovery Interceptor), and control system damper. These components work together to enhance the control stick input and provide stability and control during flight. The PRCA amplifies the pilot's input, the ARI helps with automatic recovery from certain flight conditions, and the control system damper helps dampen any oscillations or vibrations in the control system.

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• 27.

### On the F-15, how does the PRCA control the ARI?

• A.

Electrically through the airspeed switch

• B.

Mechanically through the pitch boost actuator

• C.

Hydraulically through the pitch ratio controller

• D.

Hydromechanically through the automatic flight control assembly/PRCA interface

C. Hydraulically through the pitch ratio controller
Explanation
The PRCA (Pitch Ratio Controller Assembly) controls the ARI (Automatic Recovery System) on the F-15 hydraulically. This means that the PRCA uses hydraulic power to manipulate the pitch ratio of the aircraft, which helps in maintaining stability and control during flight. The hydraulics system allows for precise and efficient control of the ARI, ensuring smooth and accurate adjustments to the pitch ratio as needed.

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• 28.

### On the F-15, what happens to the aileron servo cylinders if they lose hydraulic pressure?

• A.

The pressure sensor unlocks

• B.

Lock to the neutral postion

• C.

The cavitation valves close

• D.

Act as flutter dampers

D. Act as flutter dampers
Explanation
If the aileron servo cylinders on the F-15 lose hydraulic pressure, they will act as flutter dampers. Flutter is a phenomenon that occurs when there is an uncontrolled oscillation of the aircraft's control surfaces, which can be dangerous. The aileron servo cylinders, in this case, will help dampen the flutter and stabilize the aircraft, preventing further damage or loss of control.

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• 29.

### On the F-15, through which part of the torque tube does longitudinal input from the control stick travel?

• A.

Inner casing

• B.

Outter casing

• C.

Aft control rod

• D.

Center control rod

B. Outter casing
Explanation
The correct answer is "outter casing". On the F-15, longitudinal input from the control stick travels through the outer casing of the torque tube. The torque tube is a component that helps transmit control inputs from the pilot to the aircraft's control surfaces. In this case, the outer casing specifically carries the longitudinal input, which refers to inputs that control the aircraft's pitch or nose-up/nose-down movement.

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• 30.

### On the F-15, what control system assists the aircraft around the vertical axis?

• A.

Lateral

• B.

Directional

• C.

Longitudinal

• D.

Directional and longitudinal

B. Directional
Explanation
The correct answer is "Directional." The directional control system on the F-15 assists the aircraft in maneuvering around the vertical axis. This system helps the pilot control the aircraft's yawing motion, allowing for stable and controlled flight.

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• 31.

### On the F-15, the directional feel trim actuator connects to the.....

• A.

Control arm off the control stick linkage

• B.

Torque tube assembly aft of the rudder pedals

• C.

Torque tube assembly forward of the rudder pedals

• D.

Input rod that goes to the ARI

C. Torque tube assembly forward of the rudder pedals
Explanation
The directional feel trim actuator on the F-15 connects to the torque tube assembly forward of the rudder pedals. This assembly is responsible for transmitting the control inputs from the pilot's control stick to the various control surfaces of the aircraft, including the rudder. By connecting to this assembly, the directional feel trim actuator can effectively adjust the trim of the rudder and provide the desired directional feel to the pilot during flight.

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• 32.

### On the F-15, what type of system is the directional control system?

• A.

Electrical

• B.

Hydraulic

• C.

Mechanical

• D.

Hydromechanical

D. Hydromechanical
Explanation
The directional control system on the F-15 is a hydromechanical system. This means that it uses both hydraulic and mechanical components to control the direction of the aircraft. Hydraulic power is used to actuate the control surfaces, while mechanical linkages transmit the pilot's inputs to these surfaces. This combination of hydraulic and mechanical systems provides the necessary force and precision for effective control of the aircraft's direction.

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• 33.

### On the F-15, the speed brake selector valve is located behind...

• A.

Door 88L

• B.

Panel 77R

• C.

Panel 66R

• D.

Panel 59

D. Panel 59
Explanation
The correct answer is panel 59. This means that the speed brake selector valve on the F-15 is located behind panel 59.

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• 34.

### On the F-15, at what pressure above the utility pressure does the blowback check valve automatically retract the speed brake?

• A.

2-8 psi

• B.

8-12 psi

• C.

10-14 psi

• D.

12-16 psi

A. 2-8 psi
Explanation
The correct answer is 2-8 psi. This means that the blowback check valve on the F-15 will automatically retract the speed brake when the pressure is between 2 and 8 psi above the utility pressure. This mechanism ensures that the speed brake is retracted at the appropriate pressure to maintain the aircraft's stability and control during flight.

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• 35.

### On the F-15, what position does the speed brake actuator go to by setting the speed brake switch to aft?

• A.

Retract

• B.

Extend

• C.

Down

• D.

Up

B. Extend
Explanation
When the speed brake switch on the F-15 is set to aft, the speed brake actuator moves to the "extend" position. This means that the speed brake is deployed or opened, creating additional drag on the aircraft and helping to reduce its speed. By extending the speed brake, the pilot can effectively slow down the aircraft during flight.

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• 36.

### On the F-15, the fuel quantity indicators receive the fuel quantity signal from the ........

• A.

Tank units

• B.

Thermistors

• C.

Signal conditioner

• D.

Fuel low-level control unit

C. Signal conditioner
Explanation
The fuel quantity indicators on the F-15 receive the fuel quantity signal from the signal conditioner. The signal conditioner is responsible for processing and conditioning the fuel quantity signal before it is sent to the indicators. It ensures that the signal is accurate and reliable, allowing the indicators to display the correct fuel quantity information to the pilot.

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• 37.

### When you place the selector knob to the FEED tank position on the F-15 aircraft, the left and right counters, on the fuel quantity indicator represent the quantity of fuel remaining in.........

• A.

Tank 2 and tank 3A, respectively

• B.

Tank 3A and tank 2, respectively

• C.

Tank 2, tanks 3A and 3B, respectively

• D.

Tanks 3A and 3B, and tank 2, respectively

D. Tanks 3A and 3B, and tank 2, respectively
Explanation
When the selector knob is placed on the FEED tank position, the left counter on the fuel quantity indicator represents the quantity of fuel remaining in tank 3A, the right counter represents the quantity of fuel remaining in tank 3B, and the center counter represents the quantity of fuel remaining in tank 2.

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• 38.

### On the F-15 aircraft, an aircrew can ensure they don't dump too much fuel by........

• A.

Calculating their maximum landing weight before the mission

• B.

Using the fuel low level warning system

• C.

Using the bingo fuel indication system

• D.

Closely monitoring the gages.

C. Using the bingo fuel indication system
Explanation
The bingo fuel indication system is used on the F-15 aircraft to ensure that the aircrew does not dump too much fuel. This system provides a warning when the fuel level reaches a predetermined minimum level, known as the "bingo fuel." By monitoring this indication, the aircrew can make sure they have enough fuel to safely complete their mission and land without wasting excessive fuel. This helps to optimize fuel usage and prevent unnecessary fuel dumping.

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• 39.

### On the F-15, what is the output rotation of the constant speed drive unit of the integrated drive generator?

• A.

4500 RPM

• B.

9000 RPM

• C.

10000 RPM

• D.

12000 RPM

D. 12000 RPM
Explanation
The correct answer is 12000 RPM. The constant speed drive unit of the integrated drive generator on the F-15 has an output rotation of 12000 RPM.

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• 40.

### What is the main electrical component of the F-16's emergency power unit (EPU) systm?

• A.

EPU/GEN test switch

• B.

Emergency generator

• C.

Speed controller

• D.

Mode switch

C. Speed controller
Explanation
The main electrical component of the F-16's emergency power unit (EPU) system is the speed controller. The speed controller is responsible for regulating the speed of the EPU, which is crucial for maintaining the proper functioning of the emergency power unit. It ensures that the EPU operates at the appropriate speed to provide the necessary power during emergency situations.

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• 41.

### All metal parts of the F-16 's hydrazine fuel tank are constructed of...

• A.

Kevlar

• B.

Aluminum

• C.

Chromium

• D.

Stainless steel.

D. Stainless steel.
Explanation
The metal parts of the F-16's hydrazine fuel tank are constructed of stainless steel because it is a highly corrosion-resistant material that can withstand the harsh conditions and corrosive properties of hydrazine fuel. Stainless steel is also known for its durability and strength, making it suitable for use in an aircraft fuel tank.

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• 42.

### At what pressure does the F-16's EPU nitrogen valve regulate nitrogen pressure?

• A.

400 (+/- 20) psig

• B.

500 (+/- 50) psig

• C.

2,000 (+/- 100) psig

• D.

3,000 (+/- 100) psig

A. 400 (+/- 20) psig
Explanation
The F-16's EPU nitrogen valve regulates nitrogen pressure at 400 (+/- 20) psig. This means that the valve maintains the pressure of nitrogen within the range of 380 to 420 psig. This specific pressure range is important for the proper functioning of the aircraft's systems and components that rely on nitrogen pressure.

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• 43.

### The F-16's emergency generator supplies power to the ......

• A.

Battery buses

• B.

Monitor busus

• C.

Essential buses

• D.

Emergency buses

C. Essential buses
Explanation
The F-16's emergency generator supplies power to the essential buses. These buses are responsible for providing power to critical systems and components in the aircraft, ensuring their operation in emergency situations. By supplying power to the essential buses, the emergency generator helps maintain the functionality of vital systems, such as navigation, communication, and flight control, during power outages or failures.

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• 44.

### A path from the liquid oxygen probes to the quantity indicator on the F-16 is provided by

• A.

Coaxial cables

• B.

Oxygen probes

• C.

The oxygen quantity relay

• D.

The oxygen low-pressure switch

A. Coaxial cables
Explanation
Coaxial cables provide a path from the liquid oxygen probes to the quantity indicator on the F-16. These cables are commonly used in electronic systems to transmit signals with high frequency and low loss. In this case, the coaxial cables are used to transmit the information from the liquid oxygen probes, which measure the quantity of oxygen, to the quantity indicator on the F-16. This allows the pilot or operator to monitor the oxygen levels in the aircraft. The other options mentioned, such as oxygen probes, the oxygen quantity relay, and the oxygen low-pressure switch, may be components or devices related to the oxygen system but they do not directly provide the path for the information to reach the quantity indicator.

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• 45.

### The F-16's OXY LOW warning light illuminates.......

• A.

When the reserve liquid oxygen(LOX) supply is being used.

• B.

At a LOX quantity level of less than 0.9 liters

• C.

At a LOX quantity level of less that 0.5 liters

• D.

When LOX pressure drops below 55 psig

C. At a LOX quantity level of less that 0.5 liters
Explanation
The F-16's OXY LOW warning light illuminates at a LOX quantity level of less than 0.5 liters. This means that when the amount of reserve liquid oxygen (LOX) in the aircraft drops below 0.5 liters, the warning light will turn on. This is an important safety feature as it alerts the pilot to the low oxygen level, indicating the need to take appropriate actions to replenish the LOX supply and ensure the availability of breathable air for the pilot.

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• 46.

### What system malfunction causes the F-16's liquid oxygen quantity indicator to rotate counterclockwise?

• A.

Shorted probe

• B.

Oxygen pressure leak

• C.

Moisture in the converter

• D.

Short-to-ground in the high voltage side of the circuit.

D. Short-to-ground in the high voltage side of the circuit.
Explanation
A short-to-ground in the high voltage side of the circuit can cause the F-16's liquid oxygen quantity indicator to rotate counterclockwise. This means that there is an electrical connection between the high voltage side of the circuit and the ground, causing a malfunction in the system. This malfunction leads to the incorrect rotation of the indicator, indicating a lower quantity of liquid oxygen than what is actually present.

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• 47.

### On the F-16, the voids and clearances between the center conductor and the outer tube of the fire dectection set sensing elements are filled with........

• A.

A temperature-sensitive salt mixture

• B.

Asbestos

• C.

Sealant

• D.

Halon

A. A temperature-sensitive salt mixture
Explanation
The voids and clearances between the center conductor and the outer tube of the fire detection set sensing elements on the F-16 are filled with a temperature-sensitive salt mixture. This mixture is used to detect any changes in temperature, which can indicate the presence of a fire. As the temperature increases, the salt mixture undergoes a chemical reaction that triggers an alarm, alerting the pilot to the potential fire. This ensures that any fires can be quickly detected and addressed, increasing the safety of the aircraft.

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• 48.

### The fire detection set sensing elements on the F-16 have an alarm temperature of .....

• A.

400 degrees

• B.

575 degrees

• C.

765 degrees

• D.

875 degrees

C. 765 degrees
Explanation
The correct answer is 765 degrees because the fire detection set on the F-16 has a specific alarm temperature set at this level. This means that if the temperature reaches or exceeds 765 degrees, the fire detection system will activate an alarm to alert the pilot of a potential fire. It is crucial for the system to have a high alarm temperature to ensure that it only triggers in the event of an actual fire and not false alarms caused by normal operating temperatures.

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• 49.

### What symbol does the F-16 head-up display project when a fire ondition is detected?

• A.

Fire

• B.

Warn

• C.

Caution

• D.

Eng overtemp

B. Warn
Explanation
The F-16 head-up display projects the symbol "warn" when a fire condition is detected. This symbol serves as a warning to the pilot, indicating that there is a fire onboard the aircraft. It is crucial for the pilot to be alerted to this condition so that appropriate actions can be taken to mitigate the fire and ensure the safety of the aircraft and its occupants.

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• 50.

### How long does pure Halon flow to the fuel tanks before the F-16's fuel inerting shutoff valve (B) closes?

• A.

15 seconds

• B.

20 seconds

• C.

25 minutes

• D.

30 minutes

B. 20 seconds
Explanation
The pure Halon flows to the fuel tanks for 20 seconds before the F-16's fuel inerting shutoff valve (B) closes.

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• Current Version
• Mar 21, 2023
Quiz Edited by
ProProfs Editorial Team
• Sep 14, 2009
Quiz Created by
Rcs2004

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