CDC Volume 3 Edit Code 2

The C-D supersonic inlet uses Bernoulli's law to slow down the airflow. According to Bernoulli's principle, as the speed of a fluid increases, its pressure decreases. The C-D supersonic inlet is designed in a way that it increases the area of the flow passage, causing the airflow to slow down and the pressure to increase. This allows the supersonic airflow to be converted into subsonic flow, which is necessary for the functioning of the inlet.

The compressor bleed system reduces the probability of compressor stall in a dual-rotor engine by reducing the amount of air available to the N2 compressor. This is because compressor stall occurs when there is too much air entering the compressor, causing disruptions in the airflow and a loss of efficiency. By reducing the amount of air available to the N2 compressor, the system helps maintain a more stable airflow and reduces the risk of stall.

The ignition system on the T56 engine is turned off at 65% of engine RPM. This means that once the engine reaches 65% of its maximum rotational speed, the ignition system is no longer needed to maintain combustion and can be safely turned off.

The TD amplifier on the T56 engine compares the desired throttle setting from the coordinator with the actual TIT (Turbine Inlet Temperature) signal from the thermocouples. This comparison helps to ensure that the engine is operating at the correct temperature and that the throttle setting is accurately adjusted based on the TIT signal. The TD amplifier plays a crucial role in maintaining the engine's performance and efficiency.

The correct answer is 4 US gallons. This means that the ACAWS message low oil level advisory for the AE2100D3 engine will occur when the engine oil level drops below 4 US gallons.

The correct answer is "Brushes." In a simple AC generator, the brushes are responsible for taking the current from the slip rings to operate the electrical device. The brushes make contact with the slip rings, which are connected to the rotating loop of wire in the generator. As the loop rotates, the brushes maintain contact with the slip rings, allowing the current to flow from the generator to the electrical device. The brushes act as conductors, transferring the electrical energy from the generator to the device.

The fuel/oil cooler is responsible for heating the augmentor fuel to improve vaporization and combustion. By cooling the oil, the heat is transferred to the fuel, increasing its temperature and enhancing the combustion process. This component plays a crucial role in optimizing the performance of the engine by ensuring efficient fuel combustion.

During jet engine deceleration, a hydromechanical fuel control schedules fuel flow as a function of burner pressure. This means that the fuel flow is adjusted based on the pressure in the burner, which is the part of the engine where fuel is burned to generate thrust. By monitoring and regulating the burner pressure, the fuel control system can ensure that the engine is operating efficiently and safely during deceleration. RPM, inlet temperature, and inlet pressure may also be important factors in engine operation, but in this specific scenario, burner pressure is the most relevant parameter for scheduling fuel flow.

The manifold pressure switch on the T56 engine is designed to open and deenergize the fuel enrichment relay when the fuel pressure in the manifold reaches a certain level. In this case, the correct answer is 50 psi. This means that when the fuel pressure in the manifold reaches or exceeds 50 psi, the manifold pressure switch will open, causing the fuel enrichment relay to be deenergized.

The breather pressurizing valve on an F100 engine is internally mounted in the gearbox. This means that it is located inside the gearbox rather than being a separate component. The purpose of the breather pressurizing valve is to regulate the pressure within the gearbox, ensuring that it is at the appropriate level for optimal performance. By being internally mounted, it is able to directly control the pressure within the gearbox, making it an essential component for the engine's operation.

The GMAD (Gearbox Mounted Accessory Drive) is the component that drives the PGB (Propeller Gearbox) lube and scavenge pump in the AE2100D3 engine. The GMAD is responsible for transmitting power from the engine to various accessories, including the lube and scavenge pump. This ensures proper lubrication and scavenging of the propeller gearbox, which is essential for the smooth operation of the engine. The other options mentioned, such as the alternator stator, prop gearbox, and PUAD, are not directly involved in driving the PGB lube and scavenge pump.

The F117-PW-100 engine uses four linear hydraulic actuators to deploy and stow the fan thrust.

The two main types of augmentor (afterburner) ignition systems are torch igniter and pilot burner ring. Torch igniter is a type of ignition system that uses a high-energy spark to ignite the fuel-air mixture in the afterburner. Pilot burner ring, on the other hand, is a type of ignition system that uses a continuous flame to ignite the fuel-air mixture. These two types of ignition systems are commonly used in afterburners to ensure reliable and efficient ignition of the fuel-air mixture.

The PTO shaft used to drive the CSD is provided by the engine adapter. This component connects the engine to the CSD and allows for the transfer of power from the engine to the CSD through the PTO shaft. Engine fittings, aircraft fittings, and aircraft adapters are not directly involved in providing the PTO shaft for driving the CSD.

The TD valve receives 120 percent of the engine fuel requirement.

The discharge air used for aircraft engine anti-icing is taken from the compressor. The compressor is responsible for compressing the incoming air before it enters the combustion chamber. This compressed air is then used for various purposes, including anti-icing to prevent ice formation on critical areas of the engine. By taking the discharge air from the compressor, it ensures that the air is at a high enough temperature to effectively prevent ice buildup.

The primary input power to the main ignition system is 28 VDC.

The high-energy capacitor-type ignition system does not include a centrifugal switch. A centrifugal switch is a device that is commonly used in ignition systems to control the timing of the spark. It is typically found in older, points-type ignition systems where it is responsible for advancing the spark timing as the engine speed increases. However, in a high-energy capacitor-type ignition system, the timing is controlled electronically and does not require a centrifugal switch.

Compositors in an ignition system are used to step up the voltage to a level that is high enough to break down the air gap of the igniter plug. This is necessary because the air gap acts as an insulator, preventing the flow of current. By increasing the voltage, the compositors ensure that the spark can jump across the gap and ignite the fuel-air mixture in the engine.

The correct answer is the CGB oil system. The CGB (Compressor Gearbox) oil system is responsible for supplying oil to the F-15 JFS (Jet Fuel Starter) to lubricate and cool its components. The oil tank and aircraft filter are not directly involved in supplying oil to the JFS, while the JFS oil system is a broader term that encompasses the entire oil system of the JFS, not just the supply. Therefore, the CGB oil system is the most accurate choice.

Jet engine thrust reversers are used to direct the engine thrust in the opposite direction. This is typically done during landing to help the aircraft slow down by redirecting the exhaust gases forward, creating a reverse thrust. By doing so, the aircraft can effectively decelerate and shorten its landing roll. This is especially useful in situations where the runway length is limited or when landing on wet or icy surfaces. The purpose of thrust reversers is not to provide directional control on the ground, but rather to assist in braking and reducing the aircraft's speed after touchdown.

Air pressure is used to open and close both flap-type and iris-type variable-exhaust nozzle systems. This means that air pressure is responsible for controlling the movement of these nozzle systems, allowing them to adjust the exhaust flow as needed.

A pneumatic starter requires a sufficient volume of air to ensure that there is enough air available to power the starter. This is important because the starter needs a continuous supply of air to operate properly. Additionally, the starter also requires a sufficient pressure of air to ensure that there is enough force to drive the starter mechanism. Without enough pressure, the starter may not be able to generate enough power to start the engine. Therefore, both volume and pressure are necessary air source requirements for a pneumatic starter to operate properly.

The oil pressure in the F100-PW-100 engine is influenced by various factors such as rear compressor rotor speeds, engine inlet oil temperature, and oil jet pressure. However, the condition of the oil nozzle specifically affects the oil pressure.

The JFS (Jet Fuel Starter) uses an annular combustion chamber. An annular combustion chamber is a type of combustion chamber in which the fuel and air are mixed in a ring-shaped chamber surrounding the turbine. This design allows for efficient combustion and provides a compact and lightweight solution for the JFS.

The hot tank oil system design places the oil cooler in the pressure subsystem. In this design, the oil cooler is located in the high-pressure side of the system, which allows for efficient cooling of the oil. This design is commonly used in applications where the oil temperature needs to be closely controlled and maintained within a specific range. By placing the oil cooler in the pressure subsystem, the hot tank design ensures that the oil is adequately cooled before it is returned to the system, helping to prevent overheating and potential damage to the components.

The correct answer is controlling turbine inlet temperature. In a dual-spool, axial-flow engine, the thrust production is controlled by regulating the temperature of the air entering the turbine. By controlling the turbine inlet temperature, the engine can adjust the power output and consequently the thrust produced. This is achieved by regulating the fuel flow and adjusting the combustion process to maintain the desired temperature level.

The TD valve is the component that sends the fuel to the fuel manifold in the T56 engine.

The OSG (OverSpeed Governor) on the cartridge-pneumatic starter consists of two pinned flyweights and a piston. This configuration allows the OSG to regulate the speed of the starter by controlling the flow of air from the cartridge. As the speed of the starter increases, the flyweights move outward, causing the piston to restrict the flow of air. This helps prevent the starter from overspeeding and potentially causing damage.

The turbine plenum on the JFS provides pads for mounting the fuel atomizer assembly.

The AE2100D3 PUAD lube and scavenge pump provides approximately 5 gallons per minute (GPM) at engine PTO.

The F100 engine augmentor's exhaust nozzle is variable to control both the engine's thrust and fan stall margin. By adjusting the size of the exhaust nozzle, the engine can increase or decrease its thrust output. Additionally, the variable nozzle helps maintain a safe margin against fan stall, which is a condition where the airflow over the engine's fan becomes disrupted, leading to a loss of thrust and potential engine damage. Therefore, the variable exhaust nozzle plays a crucial role in managing both thrust and fan stall margin for the F100 engine.

The anti-icing system on an F110-GE-129 engine is designed to prevent the formation and accumulation of ice on various parts of the engine. In this case, it specifically targets the fan inlet guide vane flaps. These flaps are located at the front of the engine and play a crucial role in directing airflow. If ice were to form on these flaps, it could disrupt the airflow and potentially cause damage to the engine. Therefore, the anti-icing system is necessary to ensure the proper functioning and safety of the engine.

The slide-type resistor in the EGT circuit is used to calibrate the EGT indicator in the flight station. This means that it is used to adjust the EGT indicator to ensure its accuracy and reliability. By using the slide-type resistor, the EGT indicator can be calibrated to accurately measure the exhaust gas temperature, allowing for precise monitoring of engine performance. This calibration is important for maintaining the safety and efficiency of the aircraft.

A transformer is a unit of an AC ignition system that develops 20,000 volts. A transformer works by converting the low voltage from the power source into a high voltage output. This high voltage is necessary for the ignition system to create a spark and ignite the fuel mixture in the engine. The other options, such as inverter, capacitor, and generator, are not specifically designed to develop high voltage in an AC ignition system.

The hydraulic motor is the item that initially rotates the JFS (Jet Fuel Starter). This motor is responsible for providing the initial rotation to start the engine. The ESS PTO, electric motor mounted on the aircraft, and engine PTO are not involved in the initial rotation of the JFS.

The air injector on the air regulator of an F108-CF–100 engine anti-ice system is used to control air temperature and pressure. This component helps regulate the flow of air to maintain the desired temperature and pressure levels within the system. It plays a crucial role in ensuring that the engine operates efficiently and prevents any potential damage due to extreme temperatures or pressure imbalances.

Compressor bleed air is used for various purposes in an F110-GE-129 engine, including anti-icing, customer bleed, VSV actuator control, and IGV actuator control. However, the correct answer is low-pressure turbine cooling functions. This means that the compressor bleed air is used to cool the low-pressure turbine, which helps to maintain its efficiency and prevent overheating. This is an important function as the low-pressure turbine plays a crucial role in the overall performance of the engine.

The F117-PW-100 fan thrust reverser door upper right and left sensors send a signal to the A channel of the EEC.

The T56 engine speed-sensitive control allows electrical current to flow to the fuel and ignition system at 16% RPM. This means that at this specific engine speed, the control system activates and enables the necessary electrical current to power the fuel and ignition system, ensuring proper functioning and performance of the engine.

The correct answer is three because an F100-PW-100 engine ignition system consists of three independent circuits.

The rotary movement of the fuel control metering valve on a T56 engine is controlled by the compressor inlet pressure. This pressure is used to regulate the amount of fuel being supplied to the engine, ensuring proper combustion and performance. By adjusting the fuel flow based on the compressor inlet pressure, the engine can maintain optimal operating conditions at different power settings and altitudes.

The correct answer is actuator. The core reverser lock proximity sensors are mounted on the actuator. This means that the sensors are located on the actuator, which is a device responsible for controlling or moving a mechanism. The proximity sensors are likely used to detect the position or movement of the actuator in order to ensure proper functioning of the core reverser lock system.

The variable bleed valves on an F108-CF–100 engine are responsible for bleeding air from the N1 compressor. This means that these valves control the amount of air that is released from the N1 compressor, which is an essential part of the engine. Bleeding air from the N1 compressor helps to regulate the engine's performance and ensure optimal operation. Therefore, the correct answer is N1 compressor.

The main engine control supplies fuel pressure to operate the IGV actuator on an F110-GE-129 engine. This component is responsible for regulating and controlling various functions of the engine, including the fuel system. It ensures that the correct amount of fuel is delivered to the engine components, such as the IGV actuator, to optimize performance and efficiency. The main fuel pump, augmentor engine control, and digital electronic engine control are not directly involved in supplying fuel pressure to operate the IGV actuator.

The correct answer is three because an F110-GE-129 engine contains three stages of Variable Stator Vanes (VSV). Variable Stator Vanes are used in the compressor section of the engine to control the airflow and optimize engine performance at different operating conditions.

The isolation decouplers on the F-15 secondary power system CGB are extended hydraulically.

The correct answer is "Pneumatic." In an F108 engine, the anti-ice air is ducted from the pneumatic manifold. This means that the air used for anti-icing purposes is sourced from the pneumatic system of the engine.

The control valve is the component that controls hydraulic power for actuating both the fan and core thrust reversers on the F117-PW-100 engine. This valve regulates the flow of hydraulic fluid to the actuators, allowing for precise control of the thrust reversers and fan. The electronic engine control, hydraulic pump, and fuel control are not directly responsible for controlling hydraulic power in this context.

The direction of the variable bleed valve rotation on an F108-CF–100 engine is controlled by the fuel gear motor.