2a353: Fighter Aircraft Maintenance Journeyman

The U-2 has peculiar maintenance procedures due to the need to maintain its lightweight characteristics. This suggests that the maintenance procedures are specifically designed to ensure that the aircraft remains lightweight, which is crucial for its performance. This could involve regular inspections and repairs to prevent any damage or modifications that could add unnecessary weight to the aircraft. By maintaining its lightweight characteristics, the U-2 can continue to operate effectively and efficiently in its intended roles.

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.

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.

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.

The negative pressure relief valve in the F-16 fuel system provides a redundant means of allowing air into the vent tank. This is important because it guards against instances of negative pressure within the fuel tanks. Negative pressure can occur when fuel is consumed or when there are changes in altitude, which can lead to fuel starvation and engine failure. The negative pressure relief valve helps maintain proper pressure within the fuel tanks by allowing air to enter when needed, ensuring a continuous fuel supply to the engine.

Auxiliary longerons are components in the A-10 fuselage that help redistribute loads around cutouts and provide redundant load paths. They work in conjunction with ribs, spars, and stringers to ensure structural integrity and strength in the fuselage. The auxiliary longerons play a crucial role in maintaining the overall stability and durability of the aircraft, especially during high-stress situations or in the presence of cutouts that can weaken the structure.

The F-22 nose wheel can be turned up to 48 degrees depending on the main landing gear wheel speed. This means that the angle of the nose wheel is determined by how fast the main landing gear wheels are spinning. The faster the wheels are spinning, the greater the angle that the nose wheel can be turned. This is likely because the speed of the main landing gear wheels affects the stability and maneuverability of the aircraft, and adjusting the angle of the nose wheel helps to maintain control during different speeds.

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.

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.

The F-16's brake control unit receives electrical signals from the brake pedal position transducers and the anti-skid control unit. This means that the brake control unit is able to receive information about both the position of the brake pedal and the anti-skid control, allowing it to effectively control the brakes in response to the pilot's input and the conditions of the aircraft.

The four mounted pads on the U-2 center section serve as attach points for the RG130 ground handling cart. These pads also have the purpose of securing or fastening the aircraft in place, which is known as tie down. This ensures that the aircraft remains stable and stationary, especially during periods of maintenance or when it is not in use.

The U-2 flight control system that reduces the wing and empennage structural loading during high speed or rough air operation by shifting both aileron wing surfaces and wing flaps upward is gust control. This system helps to counteract the effects of turbulent air or gusts, minimizing the stress on the aircraft's wings and tail. By shifting the aileron wing surfaces and wing flaps upward, the gust control system helps maintain stability and control of the aircraft in challenging flying conditions.

The approximate front to back tank fuel ratio on the RQ-1 is 3:2. This means that the front tank contains 3 parts of fuel while the back tank contains 2 parts of fuel. This ratio helps to distribute the weight of the fuel evenly and maintain balance in the aircraft during flight.

The software on the F-22 performs the Built-In Test (BIT) on the hydraulic components. This means that the software is responsible for running diagnostic tests and checking the functionality of the hydraulic system. It is likely that the software is programmed to detect any faults or issues with the hydraulic components and provide the necessary information for maintenance and troubleshooting.

The correct answer is CEDU. The CEDU (Central Engine Data Unit) in the F-22 stores various information related to vibration, oil debris, oil level signals, condition monitoring, and fault information. This data is important for monitoring the health and performance of the aircraft's engine. The CEDU acts as a central hub for collecting and storing this information, allowing for analysis and troubleshooting if any issues arise.

The primary flight control surfaces, engine inlet bypass louvers, nose wheel steering, engine thrust, and thrust vectoring all receive commands generated by the flight control computer. This computer is responsible for processing and interpreting inputs from the pilot and other systems, and then translating them into specific commands for the various control surfaces and systems of the aircraft. By receiving and executing these commands, the flight control computer ensures that the aircraft maintains stability and responds accurately to the pilot's inputs.

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.

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.

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.

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.

The external wing tanks on the F-16 are designed to hold 370 gallons of fuel. These tanks are used to increase the aircraft's fuel capacity, allowing for longer flight durations and extended range. By carrying additional fuel externally, the F-16 can maintain a higher fuel load without sacrificing internal space for other equipment or weapons. This increased fuel capacity is crucial for missions that require long-range capabilities or extended time in the air.

The correct answer is 85. This means that 85% of the engine thrust of the A-10's TF34-GE-100A engine is accounted for by the fan bypass stream. The fan bypass stream refers to the air that bypasses the engine core and is directed around the engine. This stream contributes to the overall thrust generated by the engine. In the case of the A-10's engine, 85% of the thrust is attributed to this bypass stream.

When the emergency start system is activated in flight, the pilot of a U-2 turns on the main landing gear lights. This is likely done to signal to other aircraft and ground personnel that there is an emergency situation and the U-2 may require immediate assistance or priority landing. The main landing gear lights are easily visible and can help to alert others of the emergency situation.

When the F-22 hydraulic pressure is lost, the ailerons are aerodynamically centered. This means that the ailerons will automatically return to their neutral position due to the balance of aerodynamic forces acting on them. This allows for the aircraft to maintain stability and control even without hydraulic assistance.

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.

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.

The A-10 aircraft has two exterior lights mounted on its wingtips. These lights serve different purposes. The anti-collision lights are used to increase the aircraft's visibility and alert other aircraft of its presence, thus preventing collisions. On the other hand, the position lights are used to indicate the aircraft's position and direction to other pilots. Therefore, the correct answer is "anti-collision and position" lights.

Blow-by gases are responsible for forcing oil out of the sump in the crankcase and back to the oil reservoir in the RQ-1's engine.

The components of the A-10 pitch and roll flight control systems that free the control stick from a control path jam are the disconnectors. These disconnectors are responsible for separating the control stick from the control path in case of a jam, allowing the pilot to regain control of the aircraft.

The payload power distribution module on the RQ-1 is responsible for powering the primary control module and the components in the forward fuselage. This module ensures that the necessary power is supplied to these critical components, allowing them to function properly. It does not power the ignition test relays, engine bay cooling fan, or fuel system pumps and relays.

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.

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

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.

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

The correct answer is 42.5 GPM at 3,100 psi. This means that the delivery rating of the F-16 accessory drive gearbox-mounted hydraulic pump is 42.5 gallons per minute at a pressure of 3,100 pounds per square inch. This indicates the maximum flow rate and pressure that the pump can deliver.

Upon landing, the F-16's leading edge flaps are automatically positioned 2 degrees up. This positioning helps to increase the lift generated by the wings, allowing for a smoother landing and reducing the risk of stalling. By angling the flaps upward, the airflow over the wings is redirected, creating more lift and providing better control during the landing phase. This upward positioning of the leading edge flaps is a standard procedure for the F-16 aircraft upon landing.

The U-2 aircraft lift spoilers are used to assist in descent from altitude. Spoilers are devices on the wings that disrupt the airflow, reducing lift and increasing drag. By deploying the spoilers, the aircraft can generate more drag, which helps in descending from high altitudes. This allows for a controlled and gradual descent, ensuring a safe landing.

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.

The F-16's hydraulic system has two separate fluid chambers in its reservoir. These chambers are used to store and distribute hydraulic fluid to various components of the aircraft's systems. Having two separate chambers allows for redundancy and ensures that there is always a backup source of hydraulic fluid in case of a failure or leakage in one of the chambers.

The correct answer is 15. This means that the nose wheel steering on the RQ-1 operates within a range of 15 degrees from either side of the center. This indicates that the nose wheel can turn up to 15 degrees to the left or right of the center position.

The primary control module is the component that algebraically adds simultaneous pitch and yaw commands to determine the required tail positions on the RQ-1. It is responsible for controlling the movement and positioning of the tail based on the input commands received. The secondary control module, network junction board, and air data terminal may have other functions in the system, but they do not specifically handle the algebraic addition of pitch and yaw commands.

The correct answer is "brake control" because on the F-22, the brake system consists of a base plate and two interchangeable brake modules. These components work together to control the braking function of the aircraft. The base plate provides a foundation for the brake system, while the interchangeable brake modules allow for flexibility and maintenance of the braking system. Therefore, "brake control" accurately describes the valve that is made up of these components on the F-22.

The wheels and tires on the F-22 are protected from excessive brake heat by a heat shield made out of stainless steel. Stainless steel is known for its high heat resistance and durability, making it an ideal material for this purpose. It can withstand the intense temperatures generated during braking without deforming or losing its protective properties. Additionally, stainless steel is also corrosion-resistant, ensuring the longevity of the heat shield in the demanding conditions of an aircraft.

The F-16's hydraulic pressure filter manifold is located in the right MLG wheel well.

The F-16 has a total of 7 fuselage tank drain valves. These valves are used to drain fuel from the fuselage tanks.

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 has been turned off, the exhaust areas of the A-10 aircraft pose a potential danger. During this time, there may still be residual heat, fumes, or other hazards present in the exhaust areas that could cause harm to personnel or equipment. It is important to exercise caution and avoid these areas until the 15-minute period has elapsed.

The correct answer is 32-millimeter, constant depression, cross-draft butterfly valve. This type of carburetor is installed on the RQ-1's engine. It has a constant depression, meaning that the pressure inside the carburetor remains constant regardless of the engine's speed or load. The cross-draft butterfly valve allows for precise control of the air and fuel mixture entering the engine. The 32-millimeter size refers to the diameter of the carburetor's venturi, which affects the amount of air and fuel mixture that can flow into the engine.

The correct answer is Lights-Off Range. The Lights-Off Range feature on the RQ-1 automatically switches the aircraft lights on through the primary control module. This feature allows the lights to be turned off at a specific range, ensuring that the aircraft is not easily detectable or visible during certain operations.

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.

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.

The F-22 pitch system is augmented by thrust vector nozzles. Thrust vectoring allows the aircraft to control its pitch by manipulating the direction of the exhaust gases. By adjusting the angle of the nozzles, the F-22 can generate additional lift or increase maneuverability, enhancing its pitch control capabilities. This feature is particularly useful during high-speed maneuvers or combat situations, enabling the aircraft to quickly change its pitch and maintain stability in various flight conditions.

The correct answer is unbalanced pistons. This means that the speed brakes in actuator type A-10 are controlled by pistons that are not balanced, resulting in an uneven force distribution. This design allows for quick and efficient deployment of the speed brakes when needed.

The return ground service coupling quick-disconnect provides an alternate method to fill the hydraulic reservoir on the F-22 hydraulic system. This coupling allows for the hydraulic fluid to be returned to the reservoir from the ground service equipment, ensuring that the reservoir is properly filled.

The correct answer is variable geometry system. The fan and compressor variable vanes, along with the modulated exhaust cooling and exhaust nozzle, all contribute to the F-22's engine thrust system. The variable geometry system allows for the adjustment and optimization of airflow and exhaust flow, maximizing the engine's performance and efficiency in different flight conditions.

The correct answer is Forward and Aft reservoirs. In an F-16 aircraft, the Forward and Aft reservoirs are fuel tanks that equally provide fuel to the engine on demand. These reservoirs are strategically placed to ensure a balanced distribution of fuel to maintain stability and performance during flight. The fuel from both reservoirs is utilized simultaneously to ensure a continuous and uninterrupted fuel supply to the engine.

The correct answer is orifice valve. During normal landing gear extension on the U-2, the orifice valve is responsible for delaying the main landing gear actuator pressure buildup until the uplock actuator has unlocked the gear. This valve restricts the flow of hydraulic fluid, causing a delay in the pressure buildup, which allows the uplock actuator to complete its unlocking function before the gear starts to extend. This ensures a smooth and controlled extension of the landing gear during the landing process.

In emergency flight mode, the F-22 uses the pneumatic backup system to pressurize the uplock devices, which allows the landing gear to be released and locked in the extended position. This mode is specifically designed for emergency situations where quick and reliable extension of the landing gear is necessary for safe landing.

The F-22's engine fan variable vanes position is controlled by an actuator. An actuator is a device that converts energy into motion, in this case, it controls the position of the variable vanes in the engine fan. It is responsible for adjusting the vanes to optimize airflow and improve engine performance based on the aircraft's needs. This allows for better control over the engine's output and enhances the overall efficiency of the F-22.

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.

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.

The F-16 external centerline transfers fuel into the left and right internal wing fuel tanks.

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 the landing gear components, allowing for the extension and retraction of the gear. By directing the hydraulic pressure to the nose drag strut actuators, the landing gear control valve ensures that the nose gear is properly extended and locked in place during landing and takeoff operations.

The correct answer is 2. This suggests that there are two ignitors installed on the combustor of the A-10's TF34-GE-100A engine.

The correct answer is the optical fire detection system. This system is responsible for detecting the presence of a fire in the F-22 engine or APU compartments. It uses optical sensors to detect the presence of flames or smoke, and then reports this information to the fire protection module. This allows for quick and accurate detection of fires, ensuring that appropriate measures can be taken to extinguish the fire and prevent further damage or danger.

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.

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 remains properly lubricated even when the aircraft is in a maneuver that would normally cause oil flow to be interrupted or reduced. The auxiliary lubrication system is designed to provide a constant supply of oil to the bearing, preventing any potential damage or failure that could occur due to inadequate lubrication.

When the extinguisher discharge switch is placed to the right, the A-10's fire extinguisher container fires in the forward direction.

The correct answer is "dual breaker-less capacitive discharge ignition system." This means that the ignition power for the spark plugs on the RQ-1's engine is provided by a system that does not have breakers and uses capacitive discharge. The use of dual systems indicates redundancy and backup in case of failure.

The correct answer is pin E of the external AC power receptacle. This pin is specifically designed to provide the external DC power required to power the monitored AC bus contactor coil on the U-2. It serves as a connection point for the external power source, allowing the necessary power to be supplied to the coil.

The output pressure for the hydraulic system's pumps on the F-22 is between 4050 to 4150 psi.

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.

The reservoir service manifold relief valve on the F-16 is responsible for relieving excessive hydraulic pressure that occurs due to thermal expansion into the system return. This valve ensures that the pressure does not exceed safe levels and helps to maintain the proper functioning of the hydraulic system.

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 reservoir is redirected back into the hydraulic system's return line. This is likely done to maintain the proper pressure balance within the system and ensure that the hydraulic fluid is properly circulated and returned to the reservoir for future use.

The U-2 exterior lights consist of landing, anti-collision, and navigation lights. Navigation lights are essential for aircraft to signal their position and direction to other pilots and air traffic controllers. These lights are usually located on the wings and tail of the aircraft and are colored to indicate the aircraft's orientation. They help prevent collisions by making the aircraft more visible in low-light conditions or during nighttime operations.

The RQ-1 is equipped with disc brakes that are actuated by electrical servos. This means that the braking system of the RQ-1 drone utilizes disc brakes, which are a type of braking system that uses friction to slow down or stop the rotation of the wheels. These disc brakes are operated or controlled by electrical servos, which are devices that convert electrical signals into mechanical movement. By using electrical servos to actuate the disc brakes, the RQ-1 is able to efficiently and accurately control its braking system.

The F-22 arresting gear system is electrically actuated and controlled. This means that the system uses electrical power to operate and control the mechanism responsible for arresting the aircraft during landing. Electrically actuated systems are commonly used in modern aircraft due to their efficiency and precision in controlling various functions.

The fire extinguishing discharge switch on the A-10's fire extinguishing system is a three-position, double-throw, center-off toggle switch. This means that the switch has three positions: one in which it is off, one in which it is in the center, and one in which it is on. It is also a double-throw switch, which means it can control two separate circuits or functions. In this case, the switch is used to control the discharge of the fire extinguishing system, allowing the pilot to turn it on or off as needed.

The wing flaps on the U-2 are controlled electrically. This means that the movement of the flaps is controlled by an electrical system, rather than by hydraulic, mechanical, or pneumatic means. Using electrical control allows for more precise and responsive adjustments to the position of the flaps, which is important for maintaining stability and maneuverability during flight.

Valve lead and valve lag in the valve mechanism of the RQ-1's reciprocating engine are used to increase the volumetric efficiency and lower the temperature of the cylinder. Valve lead refers to the early opening of the intake valve, allowing more time for the air-fuel mixture to enter the cylinder. This increases the amount of fresh charge in the cylinder, improving volumetric efficiency. Valve lag, on the other hand, refers to the delayed closing of the exhaust valve, allowing more time for the exhaust gases to exit the cylinder, reducing the temperature inside. By optimizing the intake and exhaust processes, the engine can operate more efficiently and maintain lower cylinder temperatures.

The correct answer is IVSC. The IVSC stands for Integrated Vehicle Systems Controller, which is responsible for monitoring the hydraulic system on the F-22 aircraft. It is a crucial component that ensures the proper functioning and control of the hydraulic system, which is essential for the aircraft's maneuverability and operation. The IVSC plays a vital role in maintaining the overall performance and safety of the aircraft during flight.

The backplane assembly is the F-22 system component that provides all electrical interconnects between the vehicle management system modules and the aircraft wiring connectors. It serves as a central hub for connecting various modules and components, allowing for efficient communication and control within the aircraft's systems. This assembly plays a crucial role in ensuring the smooth operation and integration of the F-22's electrical systems.

The F-16's solenoid-operated parking valve directs hydraulic pressure from one brake accumulator to one set of brake pistons in each wheel brake assembly. This means that the valve controls the flow of hydraulic pressure to a specific set of brake pistons, allowing for precise control of braking in each wheel brake assembly.

The ground air service connector for F-16 fuel tank pressurization is located in the right main landing gear wheel well.

The F-22's engine lube system contains oil in the bearing compartment by using engine supplied compressor air. This means that the air from the engine's compressor is used to pressurize the oil and distribute it to the bearing compartment for lubrication.

The correct answer is 1600. At an engine speed of 1600 revolutions per minute (RPM), the starter/alternator on the RQ-1 automatically switches from acting as a starter to acting as an alternator.

The correct answer is "control". In the F-22 nose-wheel steering system, the control valve allows free castering of the nose wheel. This means that the nose wheel can rotate freely in any direction without being restricted or locked into a specific position. The control valve is responsible for regulating the flow of hydraulic fluid to the nose-wheel steering system, allowing the pilot to have precise control over the direction and movement of the nose wheel.

The correct answer is the internal shutoff valve. When the filter bowl and element are removed from the F-16's hydraulic system, the internal shutoff valve prevents fluid loss. This valve is designed to close off the flow of fluid when the filter bowl and element are removed, ensuring that the hydraulic system remains sealed and preventing any leakage or fluid loss.

The pressure transducer on the F-22 operates over a pressure range of 0 to 5000 psig. This means that it is capable of measuring pressures from 0 psi (no pressure) to 5000 psi (high pressure). This wide range allows the transducer to accurately monitor and measure various pressure levels within the aircraft system.

The pressure relief valve provides the refuel receptacle with an emergency disconnect feature during F-16 aerial refueling. This valve is designed to release excess pressure in the refueling system, ensuring the safety of the aircraft and preventing any potential damage or accidents. If the pressure exceeds a certain threshold, the valve opens, allowing the fuel to escape and disconnecting the refueling process. This feature acts as a safeguard in case of emergencies or abnormal situations during refueling operations.

The vent and pressurization valve for the F-16's external fuel tanks is located on the inside of the vent tank.

The U-2 DC generator is cooled by ram air through the left engine air inlet. This means that the generator is cooled by the incoming airflow that enters through the left engine air inlet. The ram air, which is the high-speed air entering the engine, passes through the air inlet and helps to cool the generator. This cooling method is essential to prevent overheating and ensure the proper functioning of the generator.

The correct answer is capacitance-type probes provided a 12-VDC reference voltage from the SCM. This means that the fuel level sensors in the RQ-1's fuel system use capacitance-type probes, which measure the fuel level based on changes in capacitance. These probes are supplied with a 12-VDC reference voltage from the secondary control module (SCM), which allows for accurate and reliable fuel level measurement.

The correct answer is integrated vehicle system controller. The question is asking about the two system operations of a specific component, which is the integrated vehicle system controller. The other options mentioned (flight control computer, operational flight program, actuator interface modules) are not the correct answers as they are not specifically mentioned in the question. Therefore, the integrated vehicle system controller is the correct answer.

The correct answer is system A only because it states that the hydraulic fluid for operation of the F-16 speed brakes is supplied by system A only. This means that system B is not involved in supplying the hydraulic fluid for the speed brakes. Additionally, the answer mentions that system A is the only supplier of hydraulic fluid, except when the emergency hydraulic pump is operating. This further clarifies that system B is not involved in supplying the hydraulic fluid for the speed brakes.

Decambering the ailerons and flaps on the RQ-1 is done to provide improved high-speed flight characteristics. This means that by adjusting the shape and angle of the ailerons and flaps, the aircraft can achieve better performance at higher speeds. This could include increased stability, reduced drag, and improved maneuverability, allowing the RQ-1 to fly more efficiently and effectively at high speeds.