Fighter Aircraft Maintenance Volume 4. A-10/U-2/Uav (Rq-1)

The A-10's integrated drive generator oil supply circuit component that attracts ferrous metals particles is the magnetic chip detector. This component is designed to detect and collect any metallic debris or chips that may be present in the oil system. It uses a magnetic field to attract and hold onto ferrous particles, allowing maintenance crews to inspect and analyze the collected debris for any signs of engine wear or damage. This helps in identifying potential issues early on and taking necessary maintenance actions to prevent further damage to the aircraft.

The hydraulic tubing for the U-2 horizontal stabilizer trim is color-coded to prevent cross-connection of lines during maintenance. This means that the different colors on the tubing help to ensure that the correct lines are connected to each other during maintenance procedures, reducing the risk of cross-connection and potential malfunctions. By using color-coding, maintenance personnel can easily identify which lines should be connected together, improving safety and efficiency during maintenance operations.

When the fuel sump reads 38 (±3) gallons remaining, it indicates that the fuel level is low. This means that there is not much fuel left in the aircraft's tanks, and it is approaching a critical level. The light that illuminates in this situation serves as a warning to the pilot that they should consider refueling soon to avoid running out of fuel during the flight.

The correct answer is "general information." In the U-2 technical manual, the section on general information provides a comprehensive description of the aircraft, including its various stations, access provisions, and drain and vent points. This section serves as a useful reference for understanding the overall structure and features of the aircraft. It helps technicians and operators familiarize themselves with the basic details of the U-2, enabling them to effectively maintain and operate the aircraft. The general information section is an essential part of the technical manual, providing crucial information for anyone working with the U-2 aircraft.

The momentary hammering sound when the U-2 fuel transfer valves are actuated is caused by air in the system. When the valves are actuated, air bubbles can get trapped in the fuel lines, causing the hammering sound. This is a common issue in fuel systems and can be resolved by bleeding the air out of the system.

The aft portion of the U-2 canopy is coated with four coats of paint to combat solar radiation and glare. This coating helps to protect the pilot's eyes from the intense sunlight and glare that can occur at high altitudes. It also helps to reduce the amount of solar radiation that enters the cockpit, which can help to keep the interior of the aircraft cooler. This is important because excessive solar heat can affect the performance and functionality of the aircraft's instruments and systems.

The oxygen regulator supply lever on the A-10 is green. This color is likely chosen to indicate that it is the correct lever to use for supplying oxygen. Green is often associated with safety and is commonly used to indicate "go" or "safe" in various contexts. In this case, the green lever would be easily identifiable and distinguishable from other levers, helping to prevent any confusion or mistakes when using the oxygen regulator.

When refueling the U-2, the fuel tank filled first is the fuselage sump. The fuselage sump is located in the central part of the aircraft's body, and it serves as a storage tank for fuel. Filling this tank first ensures that the fuel is distributed evenly throughout the aircraft, providing balance and stability during flight.

The correct answer is two because the question states that the number of liquid oxygen converters on the U-2 is being asked. Therefore, the answer is the option that states "two," indicating that there are two liquid oxygen converters on the U-2.

The A-10 feel and trim devices provide the stick with a representation of the trim set into the elevator actuator. This means that the stick will not experience any load or force in any direction, indicating a neutral or zero load.

The nose illumination lights on the A-10 are used for in-flight refueling. These lights help the pilot and the tanker aircraft to visually align and connect the refueling boom with the A-10's receptacle. They provide a clear visual reference during the refueling process, ensuring safe and efficient fuel transfer while in flight.

The correct answer is 781C. The U-2 aircraft's automated weight and balance programs gather daily data from the AFTO Form 781C.

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Pressurizing the U-2 hydraulic reservoir helps eliminate the possibility of air and contaminants entering the system. This is important because air and contaminants can cause damage to the hydraulic system and compromise its functionality. By maintaining pressure in the reservoir, the system remains sealed, preventing any outside elements from entering and potentially causing problems.

The backup power for the RQ-1 in case of alternator failure is provided by two dry-cell nickel-cadmium batteries. These batteries are commonly used for backup power in various applications due to their ability to provide a stable and reliable power source. They have a longer shelf life, can operate in extreme temperatures, and have a high energy density, making them suitable for backup power in critical situations.

The correct answer is the piccolo tube. The piccolo tube is a fuel system component in the A-10 aircraft that diffuses the fuel spray to reduce static buildup caused by the fuel pouring into the fuel tanks during refueling. It helps to prevent any potential ignition or static discharge hazards that could occur due to the fuel pouring into the tanks. The other options mentioned, such as the pitot tube, vent tube, and drain tube, are not specifically designed for this purpose.

The correct answer is each side of the aft fuselage. The U-2 aircraft has speed brakes located on each side of the aft fuselage. Speed brakes are used to increase drag and reduce the speed of an aircraft. In the case of the U-2, the speed brakes are positioned on the sides of the rear part of the fuselage to help control the aircraft's speed and descent during landing or other maneuvers.

The correct answer is engine-starting, accessory drive, and subsystem checkout. The U-2 aircraft mounted accessory drive has three operating modes: engine-starting, which is used to start the aircraft's engine; accessory drive, which provides power to the aircraft's accessories; and subsystem checkout, which allows for testing and verification of the aircraft's subsystems.

Checking the turbine bypass switch on the U-2 is crucial because it helps prevent valve wear. Valve wear can occur if the switch is not checked, which can lead to malfunctioning valves and potential damage to the turbine system. By regularly checking the switch, any issues can be detected early on and necessary maintenance can be performed to prevent valve wear and ensure the smooth operation of the U-2.

The power box 1 in the RQ-1's engine ignition system drives the top spark plugs in cylinders 1 and 2, and the bottom spark plugs in cylinders 3 and 4.

The correct answer is 1,600 RPM. This means that at an engine speed of 1,600 revolutions per minute, the starter/alternator on the RQ-1 will automatically start acting as an alternator.

Auxiliary longerons are fuselage components that help redistribute loads around cutouts and provide redundant load paths. They are additional structural members that run parallel to the main longerons and provide extra support and strength to the fuselage structure. These longerons help to distribute the loads evenly and prevent stress concentrations around cutouts, ensuring the structural integrity of the A-10 fuselage.

During inhalation, the A-10's oxygen regulator flow indicator should show white. This is because white indicates that the oxygen flow is normal and there are no issues with the oxygen supply. The color coding system is used to ensure that the pilots can easily identify any abnormalities or malfunctions in the oxygen flow. White is the standard color for normal flow, while other colors like black, red, and green may indicate different levels of issues or warnings.

When the emergency start system is activated in flight, the pilot of a U-2 turns on the main landing gear lights. This is because the main landing gear lights are a signal to other aircraft and ground personnel that there is an emergency situation. By turning on these lights, the pilot can alert others to the fact that they are experiencing an emergency and may require assistance or priority landing.

The correct answer is "none". This means that there should be no leakage at all for static seals on the U-2. Static seals are designed to prevent any fluid or gas from leaking out or entering into a system when there is no movement or pressure applied. Therefore, it is crucial for these seals to have zero leakage to ensure the proper functioning and safety of the U-2.

The main landing gear uplock cylinder on the A-10 releases the uplock hooks. These hooks are responsible for securing the landing gear in the up position. When the hydraulics release the uplock hooks, the landing gear is able to be lowered or deployed.

The main landing gear strut on the U-2 is constructed of titanium. Titanium is known for its high strength-to-weight ratio, making it an ideal material for aerospace applications. It is lightweight, yet strong enough to withstand the forces and stress during landing. Additionally, titanium is highly resistant to corrosion, which is crucial for an aircraft that operates at high altitudes and in various weather conditions. Therefore, using titanium for the main landing gear strut ensures durability, reliability, and optimal performance of the U-2 aircraft.

On the U-2, if the aileron trim tabs are slightly warped, the correct action is to align them as close to the middle as possible. This means adjusting the tabs so that they are in a neutral position, neither causing the aircraft to roll to one side nor the other. This adjustment ensures that the ailerons function properly and maintain the desired level of control during flight.

The U-2 flight control system that shifts both aileron wing surfaces and wing flaps upward reduces the wing and empennage structural loading during high speed or rough air operation. This helps to counteract the effects of gusts of wind, hence providing better control and stability to the aircraft. Therefore, the correct answer is gust control.

The U-2's sump tank manifolds are checked for moisture during the basic post flight inspection. This inspection is conducted after each flight to ensure that the aircraft is in proper working condition. Checking for moisture in the sump tank manifolds is important as it can indicate the presence of any leaks or damage in the fuel system. By identifying and addressing these issues during the basic post flight inspection, the aircraft's safety and performance can be maintained.

The U-2 aircraft has peculiar maintenance procedures because it needs to maintain its lightweight characteristics. This suggests that the maintenance procedures are specifically designed to ensure that the aircraft remains lightweight, which is likely important for its performance and functionality. It implies that any maintenance or repairs done on the U-2 must be carried out in a way that does not compromise its lightweight nature.

Rubberized fuel bladders mounted in the fuselage are used on the RQ-1. This type of fuel tank is designed to be flexible and conform to the shape of the fuselage, allowing for efficient use of space. The rubberized material provides durability and helps prevent fuel leaks. By being mounted inside the fuselage, these fuel bladders also offer protection from external elements and potential damage.

Polyurethane foam is used to fill the integral fuel tanks of the Z-10 helicopter to prevent potential tank explosions during combat. Polyurethane foam is known for its excellent fire resistance and insulation properties. It acts as a barrier between the fuel and the external environment, reducing the risk of ignition and explosion. This foam also helps to absorb impact and reduce the chances of fuel leakage in case of any damage to the tanks. Therefore, filling the fuel tanks with polyurethane foam is an effective safety measure to enhance the combat survivability of the Z-10 helicopter.

The danger associated with a functioning lift transducer on the A-10 is extreme heat. This means that the lift transducer can become excessively hot, posing a risk to the aircraft or personnel. Extreme heat can lead to damage or malfunction of the transducer, potentially affecting the lift control system of the aircraft. It is important to ensure proper cooling mechanisms and maintenance procedures to prevent overheating and mitigate the associated dangers.

The A-10 nose wheel steering is initiated by the movement of the rudder pedals, which provides the directional input. However, this movement alone is not sufficient to steer the nose wheel. A steering command signal is also required, which is generated by the position transducer potentiometer. This potentiometer measures the position of the rudder pedals and sends a signal to the steering unit, which then activates the nose wheel steering in the commanded direction. The steering switch and steering collar assembly are not directly involved in initiating the nose wheel steering.

The correct answer is quality assurance. Quality assurance is responsible for maintaining the automated weight and balance program used on the U-2. This program ensures that the aircraft's weight is properly distributed, which is crucial for safe and efficient operation. Quality assurance personnel are trained to monitor and verify the accuracy and reliability of the program, ensuring that it is up to date and functioning correctly. They play a vital role in ensuring the overall safety and performance of the U-2 aircraft.

The oil is forced out of the sump in the crankcase and back to the oil reservoir by blow-by gases. This means that when the engine is running, some of the gases produced during combustion can leak past the piston rings and into the crankcase. These gases then create pressure in the crankcase, which pushes the oil out of the sump and back into the reservoir. This process helps to ensure proper lubrication of the engine components and prevents oil from accumulating in the crankcase.

The approximate front tank to back tank fuel ratio on the RQ-1 is 3:2. This means that for every 3 units of fuel in the front tank, there are 2 units of fuel in the back tank. This ratio is important for maintaining the balance and stability of the aircraft during flight.

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The ice detector probe on the RQ-1 detects ice through a change in its resonant frequency. This means that when ice forms on the probe, it causes a shift in the frequency at which the probe naturally vibrates. By detecting this change, the probe can determine the presence of ice. This method is effective because the presence of ice alters the physical properties of the probe, leading to a change in its resonant frequency.

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 different components of the landing gear system, including the nose drag strut actuators. By directing the hydraulic pressure, the landing gear control valve ensures proper operation and functionality of the landing gear during takeoff, landing, and taxiing.

The A-10 aircraft has two hydraulic power supply systems. This means that there are two separate systems in place to provide hydraulic power for various functions and components of the aircraft. Having two systems ensures redundancy and reliability, as if one system fails, the other can still provide the necessary hydraulic power. This is crucial for the safe operation of the aircraft and allows for continued functionality even in the event of a failure in one of the systems.

To reset the A-10 hydraulic filter differential pressure (ΔP) indicator after it has actuated, you need to remove the filter bowl, invert it, and depress the button. This process allows the indicator to be reset and ready for further use. By removing the filter bowl, you can access the indicator, and inverting it helps to release any trapped pressure. Depressing the button ensures that the indicator is properly reset and can accurately measure the differential pressure again.

The A-10's TF34-GE-100A engine fan bypass stream accounts for 85% of the engine thrust. This means that a significant portion of the engine's thrust is generated by the bypass stream, which is the air that bypasses the combustion process and flows directly out of the engine's exhaust. This design allows for improved fuel efficiency and reduced noise levels.

The A-10 can be refueled in flight by a tanker aircraft equipped with a flying boom. A flying boom is a rigid tube that extends from the tanker aircraft and is inserted into a receptacle on the receiving aircraft, in this case, the A-10. This method of refueling allows for a faster and more efficient transfer of fuel compared to other methods such as using a refueling basket or drogue. The flying boom provides a stable and secure connection between the tanker and the A-10, ensuring a safe and successful refueling operation.

The correct answer is three because each A-10 main landing gear wheel is equipped with three fusible plugs. These plugs are designed to melt at a specific temperature, allowing the release of hydraulic pressure and preventing the wheel from overheating or exploding in case of a fire. Having three plugs ensures redundancy and increases the safety of the landing gear system.

The four mount pads on the U-2 center section serve multiple purposes. Apart from being attach points for the RG130 ground handling cart, they are also used for aircraft jacking, towing, hoisting, and tie down. This means that the mount pads can be utilized to secure the aircraft in place during various operations, ensuring its stability and safety.

The correct answer is 9.0:1. The compression ratio of an engine is the ratio of the maximum volume of the combustion chamber to the minimum volume. A higher compression ratio indicates that the fuel-air mixture is compressed to a smaller volume before ignition, resulting in a more efficient combustion process. A compression ratio of 9.0:1 means that the mixture is compressed to 1/9th of its original volume before ignition, indicating a high level of compression and efficient combustion.

The external power monitor on the A-10 determines whether the power is compatible with the aircraft electrical system. This means that it checks if the frequency, voltage sequence, and phase sequence of the external AC power applied to the aircraft are within the acceptable range for the aircraft's electrical system. If the power is not compatible, the monitor may prevent the power from being sent to the generator control unit or convert it to a compatible voltage for the aircraft's DC system.

The U-2 aircraft lift spoilers are used to assist in descent from altitude. Spoilers are devices on the wings that disrupt the airflow and reduce lift, allowing the aircraft to descend more quickly. By deploying the spoilers, the U-2 can increase drag and decrease lift, enabling a controlled descent from higher altitudes. This helps the aircraft to safely and efficiently descend to lower altitudes during its flight.