2A651 CDC All Volume Random Self Test Questions

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The diffuser section is where the point of highest pressure is within a jet engine. This section is responsible for slowing down and diffusing the high-speed, high-pressure air coming out of the compressor section. As the air enters the diffuser, its velocity decreases, causing an increase in pressure. This high-pressure air is then directed into the combustion chamber for fuel combustion. Therefore, the diffuser section is where the pressure reaches its highest point before entering the combustion process.

The correct answer is 00-20-2. This is because 00-20-2 is a technical manual that provides a block by block explanation of how to document the afto form 350 tag. It contains detailed instructions and guidelines on how to properly fill out the form, ensuring accurate and thorough documentation.

If it is determined that a first-time request part will become a recurring one and the stock level needs to be adjusted, the forms that should be submitted are AF IMT 1996.

Tab type washers are used on grooved shafts because they have a tab or tabbed edge that fits into the groove, providing a secure and stable connection. This type of washer helps prevent rotation or movement of the washer on the shaft, making it ideal for applications where the shaft needs to be locked or held in place.

A high bypass engine usually has a short duct design. This design allows for a larger bypass ratio, which means that a larger amount of air bypasses the engine core and produces more thrust. The shorter duct design also helps to reduce drag and increase fuel efficiency.

The PTO (Power Take-Off) shaft connects the ADG (Air-Driven Generator) to the F-16 engine. The PTO shaft transfers power from the engine to the ADG, allowing it to generate electrical power for various aircraft systems. This connection ensures that the ADG can provide the necessary power backup in case of an engine failure or other power loss situations.

The fuel flow relief valve in the high pressure pump on the AE21OOD3 engine is fully opened at 750 psid.

The diameter of a bolt is measured on the grip. The grip refers to the portion of the bolt that is held or grasped by a tool or a person. This measurement is important for determining the appropriate size of wrench or socket needed to tighten or loosen the bolt. The head, threads, and shank are other parts of the bolt, but the diameter is specifically measured on the grip.

The purpose of the inducer rotor is to pick up the air smoothly and feed it into the impeller. This allows for a continuous and efficient flow of air into the compressor. By picking up the air smoothly, the inducer rotor helps to reduce turbulence and ensure a uniform flow of air, which is essential for optimal compressor performance. The impeller then further compresses the air before it is sent to the turbine or diffuser.

The F108 engine fuel pump high pressure stage is a positive displacement gear type pump. This means that it uses gears to create a fixed volume of fluid that is then pushed through the pump. Positive displacement pumps are known for their ability to provide a consistent flow rate regardless of changes in pressure, making them suitable for applications where precise control is required. In this case, the positive displacement gear type pump is used to ensure that the fuel is delivered at a high pressure to meet the engine's requirements.

Priority 2 should be assigned for performing maintenance on primary mission aircraft, related AGE, and munitions support equipment for the first 8 hours after landing. This indicates that the maintenance should be carried out in a timely manner, but it is not of the highest priority. Priority 1 would be reserved for more critical maintenance tasks, while Priority 4 would be for lower priority or non-essential maintenance.

AFJMAN 24-204 covers reporting an engine that was improperly shipped.

The divergent exhaust nozzle is a free floating system. This means that it is not rigidly attached to any other component and can move or rotate freely. This allows for flexibility and adjustment in the exhaust flow, optimizing performance and efficiency.

The AE2100D3 engine fuel temp switch operates at temperatures below 32 degrees F.

The thrust reverser control valve controls hydraulic power for actuating the fan and core thrust reversers. This means that the valve is responsible for directing hydraulic power to these components, allowing them to be activated and used for thrust reversal. The fan and core thrust reversers are important components in aircraft engines that help to redirect the airflow and assist in braking during landing.

True Brinelling is the bearing discrepancy caused by heavy shock loads or impact. Brinelling refers to the permanent indentation or flattening of the bearing raceway due to excessive pressure, and True Brinelling specifically occurs as a result of heavy shock loads or impact. This can happen when a bearing is subjected to sudden and extreme forces, causing the metal to deform and create indentations on the raceway surface. As a result, the bearing's performance and lifespan can be significantly affected.

When the thermocouples in an EGT (Exhaust Gas Temperature) system are hooked up in parallel, it creates an averaging circuit. In an averaging circuit, the output is the average of the inputs. In this case, the parallel connection of the thermocouples allows for the measurement of the average exhaust gas temperature, providing a more accurate representation of the overall temperature.

The proportion of energy of a fuel that is actually used to propel an aircraft forward is determined by thermal efficiency and propulsive efficiency. Thermal efficiency refers to how effectively the fuel is converted into thermal energy, while propulsive efficiency refers to how effectively the thermal energy is converted into forward propulsion. These two factors together determine the overall efficiency of the aircraft's propulsion system.

The ESS controller is responsible for scheduling the start of fuel and ignition for the JFS (Jet Fuel Starter). It controls the timing and sequence of events required to start the JFS, ensuring that fuel is delivered and ignition is initiated at the correct time. This component plays a crucial role in the overall start-up process of the JFS.

A regional repair center is a type of maintenance facility that combines aspects of both the 2LM (two-level maintenance) and 3LM (three-level maintenance) systems. This means that the regional repair center is responsible for both intermediate-level repairs (2LM) and depot-level repairs (3LM). It serves as a centralized location within a specific region, providing maintenance and repair services for a variety of equipment and systems. This hybrid approach allows for efficient and effective maintenance operations, ensuring that repairs are conducted at the appropriate level and minimizing downtime for equipment.

The correct answer is "Pressure drop and spill valve". In the AE21OOD3 system, the component responsible for maintaining a constant drop of 70 psid to the metering valve and returning excess fuel flow to the inlet side of the high-pressure pump is a combination of pressure drop and spill valve. The pressure drop ensures a consistent drop in pressure, while the spill valve helps in redirecting excess fuel flow back to the pump's inlet side. Both components work together to regulate the fuel flow effectively in the system.

Deicing boots are used to provide ice protection on the leading edge of each propeller blade. These boots are made of a flexible material that expands and contracts, causing any ice that forms on the blade to break off. This helps prevent ice accumulation, which can affect the performance and efficiency of the propeller. By using deicing boots, the leading edge of the propeller blade remains clear of ice, allowing for safe and efficient operation of the aircraft.

Continuous thrust loading during bearing rotation can cause the formation of bands. Bands are localized areas of increased wear and damage on the bearing surface. This occurs due to the continuous pressure and friction caused by the thrust loading, leading to the development of bands. These bands can reduce the effectiveness and lifespan of the bearing, ultimately leading to bearing failure if not addressed.

You can look in TO 00-20-3 to find information concerning how to use the condition tags and the required entries for each.

In a flap type nozzle system, the flaps are operated by air pressure acting on a series of pistons. This means that the movement of the flaps is controlled by the force exerted by the air pressure on the pistons. The air pressure pushes the pistons, which in turn move the flaps to the desired position. This mechanism allows for precise control and adjustment of the flaps, ensuring optimal performance of the nozzle system.

A DR report with a 1C priority indicates that it prevents the accomplishment of an essential capability. This means that the issue identified in the report is of high importance and urgency, and if not addressed, it will significantly hinder or prevent the organization from fulfilling a critical function or achieving a crucial objective. It emphasizes the need for immediate attention and action to resolve the problem and ensure the continuity of essential operations.

The CVG system moves and controls the Compressor IGV (Inlet Guide Vanes) and the first five rows of compressor stator vanes.

A gas filled rectifier is a high energy capacitor ignition part that smoothes out the pulsations in the current. It is designed to convert alternating current (AC) into direct current (DC) by using a gas-filled chamber. The gas-filled rectifier acts as a valve, allowing current to flow in only one direction, thereby eliminating the pulsations in the current and providing a smoother output.

The mid gutter ring is the component that spreads the flame to the radial gutters of the flameholder.

When the corrected core engine speed is below 45 percent, the VSV's (Variable Stator Vanes) are fully closed. This means that the vanes are in a position where they restrict the flow of air through the engine, leading to a decrease in engine power output. By fully closing the VSV's, the engine can maintain a lower speed and prevent any potential damage or instability that may occur at lower speeds.

During start and normal engine operation, the compressor air bleed valves are closed. This means that the valves are shut, preventing any air from being bled off or released from the compressor. Keeping the valves closed allows for maximum efficiency and performance of the engine, as it ensures that all compressed air is directed towards the combustion process.

The control valve operates in three functional modes: stowed and locked, deploying, and stowing. In the stowed and locked mode, the valve is secured in a fixed position. In the deploying mode, the valve is activated to open or release the flow. In the stowing mode, the valve is returned to its original position or closed. These three modes cover the different actions that the control valve can perform, ensuring proper control and regulation of the flow.

The CEDS can replace the DCU, GSU, and EAU units at both the organizational level and the test cell.

When no voltage is being produced in a generator, the rotating loop is in a vertical position. This means that the loop is oriented vertically, perpendicular to the ground.

The ejector nozzle is the point of highest airflow velocity in a jet engine. This is because the ejector nozzle is responsible for expelling the exhaust gases from the engine at high speeds. As the exhaust gases pass through the nozzle, they are accelerated, resulting in the highest airflow velocity at this point.

The C-17 has 12 fan blocker doors.

The basic speed governor is responsible for sensing variations from the desired CSD (Constant Speed Drive) output speed. It is designed to maintain a consistent speed by adjusting the fuel supply to the engine based on the load demand. The basic speed governor continuously monitors the output speed and makes necessary adjustments to ensure that it remains at the desired level. It plays a crucial role in maintaining the stability and efficiency of the CSD system.

The correct answer is 2. This means that the C-17 aircraft has only two 95 percent proximity sensors. These sensors are used to detect the presence or proximity of objects or obstacles around the aircraft. Having only two sensors suggests that the C-17 may rely on other systems or methods for detecting objects and maintaining safe distances during flight.

The correct answer is Mixing Duct. The mixing duct is a component that is supported inside the augmentor liner. It is responsible for mixing the fuel and air to achieve efficient combustion in the engine.

Compressor bleed air is extracted from the 5th stator exit stage for anti-icing.

The correct answer is heat and rotational forces. Turbine rotor blades are subjected to high temperatures due to the combustion process, which creates heat stress on the blades. Additionally, as the rotor spins, it experiences rotational forces that can put mechanical stress on the blades. These two types of stress, heat and rotational forces, act on the turbine rotor blades.

A typical iris type nozzle system has 2 positions. This means that the nozzle system can be adjusted or set in two different positions, providing flexibility and control over the direction and intensity of the fluid flow.

The JFS (Jet Fuel Starter) has a reverse flow, annular type combustion section. In a reverse flow combustion section, the air and fuel flow in the opposite direction of the engine's exhaust gases. This design helps to improve the mixing of fuel and air, resulting in more efficient combustion. An annular type combustion section refers to a circular arrangement of fuel nozzles and combustion chambers around the engine's central axis. This design allows for a more compact and streamlined engine configuration.

The start panel is monitored and controlled by the mission computer using the MIL-STD-1553B data bus. This data bus is a standard used for communication between avionics systems in military aircraft. It allows for the exchange of data and commands between different components of the aircraft, such as the mission computer and the start panel. Therefore, the mission computer is able to monitor and control the start panel through this data bus.

The feather stop in the propeller assembly is formed by the rear face of the piston, front face of the hub, and an adjustment washer. These components work together to control the pitch angle of the propeller blades, allowing them to be adjusted to the desired position for different flight conditions. The rear face of the piston and front face of the hub serve as the contact points for the adjustment washer, which can be moved to change the position of the propeller blades and control their angle of attack.

The vibrator unit in the DC ignition system performs the function of changing direct current to pulsating current. This is important because the ignition system requires a pulsating current to create the spark needed for the combustion process in an engine. By converting the direct current from the battery into pulsating current, the vibrator unit ensures that the spark plugs receive the necessary electrical pulses to ignite the fuel-air mixture in the engine cylinders.

The single manager takes the lead in identifying, tracking, assessing, and correcting R&M deficiencies on their assigned air and space equipment. They also co-chair the PIWG (Product Improvement Working Group). This indicates that the single manager has the responsibility and authority to oversee and manage the maintenance and improvement activities for the equipment, making them the most suitable choice for this role.

The C-17 has 7 core blocker doors.

The answer 14.4 ounces is the correct one because it is the closest option to the actual amount of engine oil required to lubricate the gear train.

The compressor inlet gearbox (CGB) is responsible for transferring power from the engine to the compressor. It provides drive pads and a mounting flange for the fuel control, two speed switch assembly, and CGB itself. These assemblies are crucial for controlling the fuel flow and regulating the speed of the engine. The engine adapter PTO shaft and power turbine overspeed switch are not directly related to the compressor inlet gearbox housing.

The correct answer is ATERS. ATERS is the IMDS-CDB subsystem that tracks maintenance on test equipment. This subsystem is responsible for recording and monitoring all maintenance activities related to test equipment, ensuring that it is properly maintained and functioning effectively. By tracking maintenance on test equipment, ATERS helps to ensure the accuracy and reliability of test results, ultimately contributing to the overall quality and safety of the equipment being tested.

The discharge rate for the main core igniter plug on a F100 engine is 1 to 5 sparks per second.

The correct answer is Bypass flow system. During shutdown, the bypass flow system helps maintain positive pressure in the fuel control. This system allows the fuel to bypass certain components and continue flowing, ensuring that the pressure is maintained and preventing any potential issues or damage to the fuel control system.

The MX SUPT in AMXS/HMXS or MXS works for the MOO.

Air is ducted into the fan flow path through 13 exit slots.

The compressor acceleration bleed control valve is mounted to the aft anti-icing tube at the diffuser housing.

The correct answer is AF IMT 1000. The AF IMT 1000 is the form that should be submitted to have a TO correction or improvement considered under the IDEA program. This form is specifically designed for submitting ideas and suggestions for improvement within the Air Force. It allows individuals to provide detailed information about the problem or issue they have identified, as well as their proposed solution. By using the AF IMT 1000, individuals can ensure that their TO correction or improvement idea is properly documented and considered by the appropriate authorities.

The movement of the piston and shaft is translated to vary the propeller blade angle through the operating pin. This indicates that the operating pin is responsible for transmitting the motion from the piston and shaft to adjust the angle of the propeller blades.

The CVG actuator is controlled by high pressure fuel from the FPMU. The FPMU stands for Fuel Pump Metering Unit, which is responsible for supplying high pressure fuel to various components of the engine. In this case, it provides the necessary fuel pressure to control the CVG actuator.