2a353 Volume 2 Aircraft
Questions and Answers
- 1.
On the F-15 aircraft, what is the usable pressure rage for the LOX system?
- A.
35-70 psi
- B.
55-90 psi
- C.
75-100 psi
- D.
95-120 psi
Correct Answer
B. 55-90 psiExplanation
The correct answer is 55-90 psi. This range represents the usable pressure for the LOX (Liquid Oxygen) system on the F-15 aircraft. LOX is used as an oxidizer in the aircraft's engines and is stored under pressure. The range of 55-90 psi ensures that the LOX system operates efficiently and provides the necessary oxygen supply for the engines. Pressure below or above this range could lead to improper functioning of the LOX system and potential issues with engine performance.Rate this question:
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- 2.
On the F-15 aircraft, what can the maintainer or aircrew use to check the oxygen indication system?
- A.
Oxygen test switch
- B.
Oxygen quantity switch
- C.
Oxygen pressure test switch
- D.
Oxygen regulator test switch
Correct Answer
A. Oxygen test switchExplanation
The maintainer or aircrew can use the oxygen test switch to check the oxygen indication system on the F-15 aircraft. This switch allows them to test the functionality of the system and ensure that it is working properly. By using the oxygen test switch, they can verify that the oxygen levels are being accurately indicated and that the system is functioning as it should.Rate this question:
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- 3.
On the F-15 aircraft, the product gas in the MSOGS that does not go to the console-mounted regulators
- A.
Returns to the molecular sieve beds for processing
- B.
Ports to the regenerative heat exchanger
- C.
Stores in the backup oxygen supply
- D.
Dumps overboard
Correct Answer
D. Dumps overboardExplanation
The correct answer is "dumps overboard". This means that the product gas in the MSOGS (Molecular Sieve Oxygen Generation System) that is not needed for the console-mounted regulators is released or discharged overboard. This suggests that the excess gas is not stored or reused, but rather discarded outside of the aircraft.Rate this question:
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- 4.
How does the windshield anti-ice valve operate on the F-15 aircraft?
- A.
Manually
- B.
Electrically
- C.
Hydraulically
- D.
Pneumatically
Correct Answer
B. ElectricallyExplanation
The windshield anti-ice valve on the F-15 aircraft operates electrically. This means that it is controlled and activated by an electrical system. The electrical system sends signals to the valve to open or close, allowing the anti-ice system to function and prevent ice from forming on the windshield. This method of operation provides precise control and allows for quick and efficient activation of the anti-ice system when needed.Rate this question:
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- 5.
On the F-15 aircraft, what component contains the logic circuits for the overheat/fire detection system?
- A.
BIT panel
- B.
Flashing relay
- C.
Control panel
- D.
Controllers
Correct Answer
D. ControllersExplanation
The controllers on the F-15 aircraft contain the logic circuits for the overheat/fire detection system. These controllers are responsible for processing and analyzing data from various sensors to detect any signs of overheating or fire. They play a crucial role in ensuring the safety of the aircraft by triggering appropriate warnings and taking necessary actions in case of any potential fire hazards.Rate this question:
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- 6.
On the F-15 aircraft, what part of the AB burn-through system does the BIT control panel test?
- A.
Responders
- B.
Switches
- C.
Sensors
- D.
None
Correct Answer
D. NoneExplanation
The correct answer is "None" because the question is asking about the part of the AB burn-through system that the BIT control panel tests on the F-15 aircraft. However, the answer options provided (Responders, Switches, Sensors) do not include the correct part. Therefore, the correct answer is "None" as it indicates that the BIT control panel does not test any specific part of the AB burn-through system.Rate this question:
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- 7.
On the F-100 engine, what is the benefit of the modular construction concept?
- A.
Prevents engine vibration
- B.
Modular construction decreases the weight of the engine
- C.
Allows depot maintenance to ship each module separately
- D.
Allows for removal and replacement of sections of the engine that are bad
Correct Answer
D. Allows for removal and replacement of sections of the engine that are badExplanation
The benefit of the modular construction concept on the F-100 engine is that it allows for the removal and replacement of sections of the engine that are bad. This means that if a particular section of the engine is faulty or damaged, it can be easily removed and replaced without having to replace the entire engine. This saves time and cost in maintenance and repair, as only the specific problematic section needs to be addressed rather than the entire engine.Rate this question:
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- 8.
On the F-15 aircraft, aircraft intake air is prevented from getting into the engine bay area by
- A.
A bellmouth seal
- B.
A peripheral seal
- C.
The primary ram air inlet duct
- D.
The secondary ram air inlet duct
Correct Answer
B. A peripheral sealExplanation
A peripheral seal is used on the F-15 aircraft to prevent aircraft intake air from entering the engine bay area. This seal is located around the perimeter of the engine bay and creates a barrier to ensure that only the necessary amount of air enters the engine through the designated intake ducts. It helps maintain the integrity of the engine bay by preventing any foreign objects or excessive airflow from entering, which could potentially cause damage or affect the performance of the engine.Rate this question:
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- 9.
On the F-100 engine, the tips of the FTIT sensors protude into the
- A.
1st-stage nozzle guide vanes
- B.
2nd-stage nozzle guide vanes
- C.
3rd-stage nozzle guide vanes
- D.
4th-stage nozzle guide vanes
Correct Answer
C. 3rd-stage nozzle guide vanesExplanation
The tips of the FTIT sensors on the F-100 engine protrude into the 3rd-stage nozzle guide vanes.Rate this question:
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- 10.
The function of the F-100 electronic engine control is to
- A.
Provide history data storage
- B.
Trim the convergent exhaust nozzle
- C.
Send signals to the cockpit indicators
- D.
Supervise the trim of the UFC and CIVV
Correct Answer
D. Supervise the trim of the UFC and CIVVExplanation
The F-100 electronic engine control is responsible for supervising the trim of the UFC (Unison Fuel Control) and CIVV (Convergent Inlet Vane Vibration). This means that it ensures that these components are properly adjusted and functioning correctly. It does not provide history data storage, trim the convergent exhaust nozzle, or send signals to the cockpit indicators.Rate this question:
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- 11.
If the outputs from the F-100 electronic engine control deenergize, the engine is trimmed by the
- A.
MFC
- B.
UFC
- C.
EDU
- D.
Electrohydraulic servo valve
Correct Answer
B. UFCExplanation
If the outputs from the F-100 electronic engine control deenergize, the engine is trimmed by the UFC.Rate this question:
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- 12.
On the F-100 engine, what reduces the fuel flow during engine start
- A.
MFC
- B.
Fuel flow transmitters
- C.
Fuel derichment valve
- D.
Fuel depressurizing and dump valve
Correct Answer
C. Fuel derichment valveExplanation
The fuel derichment valve reduces the fuel flow during engine start on the F-100 engine. This valve is responsible for controlling the fuel-air mixture ratio during the start-up process. By reducing the fuel flow, the valve helps to ensure a proper and controlled ignition of the engine, preventing any potential issues or damage that could occur from an excessive fuel flow.Rate this question:
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- 13.
The F-100 engine exhaust nozzle postion transmitter is driven by
- A.
The convergent exhaust nozzle control
- B.
115-VAC power
- C.
26-VAC power
- D.
An air motor
Correct Answer
A. The convergent exhaust nozzle controlExplanation
The F-100 engine exhaust nozzle position transmitter is driven by the convergent exhaust nozzle control. This means that the transmitter receives its power and control signals from the convergent exhaust nozzle control system. It is not driven by the 115-VAC power or 26-VAC power, nor is it driven by an air motor.Rate this question:
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- 14.
How many air/oil coolers are there on the -229 engine?
- A.
Three
- B.
Four
- C.
Nine
- D.
None
Correct Answer
D. NoneExplanation
The given question asks about the number of air/oil coolers on the -229 engine. The correct answer is "None" which means that there are no air/oil coolers on the -229 engine.Rate this question:
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- 15.
When taking a JOAP sample, how much oil should be drained into a container proir ro filling the sample bottle?
- A.
None
- B.
One pint
- C.
Enough to fill the bottle
- D.
Enough to wash out any sediment trapped in the drain valve
Correct Answer
D. Enough to wash out any sediment trapped in the drain valveExplanation
When taking a JOAP sample, it is important to drain enough oil into a container to wash out any sediment that may be trapped in the drain valve. This ensures that the oil sample collected is representative of the overall condition of the system and does not contain any contaminants or debris that may have settled at the bottom. Simply draining none, one pint, or enough to fill the bottle may not effectively remove any sediment present in the drain valve.Rate this question:
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- 16.
On the F-15 aircraft, which ramp is the last ramp in the air inductin system?
- A.
Diffuser
- B.
Third
- C.
Second
- D.
First
Correct Answer
A. DiffuserExplanation
The diffuser is the last ramp in the air induction system of the F-15 aircraft. The purpose of the diffuser is to slow down and increase the pressure of the incoming air before it enters the engine. This allows for better engine performance and efficiency. The diffuser is located after the third and final ramp in the air induction system, making it the last ramp in the system.Rate this question:
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- 17.
On the F-15 aircraft, what does the air induction system use to get rid of the friction air riding on the surface of the ramps?
- A.
Oblique shock waves
- B.
Normal shock waves
- C.
Bleed air holes
- D.
Bypass door
Correct Answer
C. Bleed air holesExplanation
The air induction system on the F-15 aircraft uses bleed air holes to get rid of the friction air riding on the surface of the ramps. Bleed air holes allow a controlled release of compressed air, which helps to reduce the friction and improve the performance of the aircraft.Rate this question:
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- 18.
On the F-15 aircraft, what is the air that retards along the surface of the aircraft while the aircraft is in flight called?
- A.
Mach tuck air
- B.
Boundary layer air
- C.
Normal shock wave
- D.
Oblique shock wave
Correct Answer
B. Boundary layer airExplanation
Boundary layer air refers to the layer of air that flows along the surface of an aircraft while it is in flight. This layer of air is affected by the friction between the air and the aircraft's surface, causing it to slow down and retard. Understanding the behavior of the boundary layer air is important in aerodynamics as it can impact the aircraft's performance and stability.Rate this question:
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- 19.
On the F-15 aircraft, what type of shock wave begins to form at transsonic airspeed?
- A.
Induced
- B.
Oblique
- C.
Parasite
- D.
Normal
Correct Answer
D. NormalExplanation
At transonic airspeed, a normal shock wave begins to form on the F-15 aircraft. A normal shock wave occurs when the airflow over the aircraft becomes supersonic, causing a sudden and drastic increase in air pressure. This shock wave is perpendicular to the direction of the airflow and can have significant effects on the aircraft's aerodynamics and performance.Rate this question:
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- 20.
On the F-15 aircraft, the Mach blocking solenoid locks the diffuser ramp in the down position by
- A.
Energizing the shutoff valve
- B.
Closing the rate limiter valve
- C.
Opening the rate limiter valve
- D.
Deenergizing the shutoff valve
Correct Answer
B. Closing the rate limiter valveExplanation
The Mach blocking solenoid on the F-15 aircraft locks the diffuser ramp in the down position by closing the rate limiter valve. This means that when the solenoid is activated, it prevents the diffuser ramp from moving or adjusting, keeping it in a fixed position. By closing the rate limiter valve, the flow of air is restricted, preventing any adjustments to the diffuser ramp. This is important for maintaining the desired airflow and performance of the aircraft at high speeds.Rate this question:
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- 21.
On the F-15 aircraft, which JFS fuel filter component acts like a jet pump?
- A.
Bypass valve
- B.
Fuel accumulator
- C.
Fuel shutoff valve
- D.
Fluid-flow restrictor
Correct Answer
D. Fluid-flow restrictorExplanation
The fluid-flow restrictor component in the JFS fuel filter of the F-15 aircraft acts like a jet pump. This means that it helps to regulate and control the flow of fuel through the system, similar to how a jet pump operates. It is responsible for maintaining the correct pressure and flow rate of the fuel, ensuring that the engine receives the necessary fuel supply for optimal performance.Rate this question:
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- 22.
On the F-15 aircraft, the purpose of the central gearbox right decoupler position switch is to
- A.
Allow limited-duty-mode operation
- B.
Prevent limited-duty-mode operation
- C.
Sense the position of the clutch control valve
- D.
Prevent both decouplers from extending at the same time
Correct Answer
D. Prevent both decouplers from extending at the same timeExplanation
The central gearbox right decoupler position switch on the F-15 aircraft is designed to prevent both decouplers from extending at the same time. This is important because if both decouplers were to extend simultaneously, it could lead to an imbalance in the aircraft's thrust and potentially cause instability or loss of control. By preventing this from happening, the switch helps to ensure safe and efficient operation of the aircraft.Rate this question:
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- 23.
On the F-15 aircraft, what airframe-mounted accessory drive switch is commonly called the 50 percent switch?
- A.
Two-speed switch assembly
- B.
Oil pump and starter cutout
- C.
Power turbine overspeed
- D.
Right decoupler position
Correct Answer
B. Oil pump and starter cutoutExplanation
The correct answer is "Oil pump and starter cutout." On the F-15 aircraft, the airframe-mounted accessory drive switch commonly referred to as the 50 percent switch is the oil pump and starter cutout. This switch is responsible for controlling and cutting off the oil pump and starter at 50 percent power.Rate this question:
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- 24.
On the F-15 aircraft, the airframe-mounted accessory drive component that takes the input from the pawl carrier assembly and transmits the rotational force to the power takeoff drive shaft for engine starting is the
- A.
Layshaft
- B.
Face gear
- C.
Gear train
- D.
Pinion gear
Correct Answer
C. Gear trainExplanation
The correct answer is gear train. The gear train is the component on the F-15 aircraft that takes the input from the pawl carrier assembly and transmits the rotational force to the power takeoff drive shaft for engine starting. The gear train consists of a series of gears that work together to transfer power and torque from one part of the aircraft to another.Rate this question:
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- 25.
On the F-15 aircraft, the F-100 engine start cycle begins in the
- A.
Cockpit
- B.
Start manifold
- C.
Hydraulic components
- D.
Fuel and ignition components
Correct Answer
A. CockpitExplanation
The F-100 engine start cycle on the F-15 aircraft begins in the cockpit. This means that the process of starting the engine is initiated and controlled from the cockpit of the aircraft. The pilot or the crew in the cockpit would typically engage the necessary systems and mechanisms to start the engine, such as activating the ignition and fuel components. This is an important step in the overall start-up process of the engine, and it is crucial for the pilot to have control and access to these functions from the cockpit.Rate this question:
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- 26.
On the F-15 aircraft, the engine start system permanent magnet generator sends its AC voltage to the
- A.
JFS igniters
- B.
JFS Fuel shutoff valve
- C.
Generator control unit
- D.
JFS ignition unit
Correct Answer
C. Generator control unitExplanation
The engine start system permanent magnet generator on the F-15 aircraft sends its AC voltage to the generator control unit.Rate this question:
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- 27.
On the F-15 aircraft, what are the two types of borescopes?
- A.
Rigid and flexible
- B.
Remote and stationary
- C.
Stationary and portable
- D.
Fiber optic and solid core
Correct Answer
A. Rigid and flexibleExplanation
On the F-15 aircraft, there are two types of borescopes: rigid and flexible. Rigid borescopes are fixed and cannot be bent or adjusted, while flexible borescopes have a flexible shaft that allows for easier maneuverability and access to tight spaces. These two types of borescopes are commonly used for inspection and maintenance purposes on the F-15 aircraft.Rate this question:
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- 28.
What should you use periodically to clean the borescope lens?
- A.
Windex
- B.
Rubbing alcohol
- C.
Isopropyl alcohol
- D.
Static lens cleaner
Correct Answer
C. Isopropyl alcoholExplanation
Isopropyl alcohol should be used periodically to clean the borescope lens. Isopropyl alcohol is a commonly used solvent that effectively removes dirt, smudges, and fingerprints from lenses without leaving residue or streaks. It is a safe and effective option for cleaning sensitive optical surfaces like the borescope lens.Rate this question:
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- 29.
On the ignition test set, what monitors the output of energy?
- A.
Stored energy meter
- B.
Potentionmeter
- C.
Toggle switch
- D.
Rotary meter
Correct Answer
A. Stored energy meterExplanation
The stored energy meter is the component on the ignition test set that monitors the output of energy. It is responsible for measuring and displaying the amount of energy that is stored in the system. This allows technicians to accurately assess the energy levels and ensure that they are within the desired range for proper ignition. The other options listed (potentiometer, toggle switch, and rotary meter) do not have the capability to monitor energy output in the same way as a stored energy meter.Rate this question:
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- 30.
What supplies power to the engine ignition system during an ignition test?
- A.
Electronic scaler
- B.
Light-off detector
- C.
Electronic transmitter
- D.
Alternator simulator output
Correct Answer
D. Alternator simulator outputExplanation
The alternator simulator output supplies power to the engine ignition system during an ignition test. This output simulates the power generated by the alternator, which is responsible for charging the battery and supplying electrical power to the various systems of the vehicle. During an ignition test, the alternator simulator output ensures that the ignition system receives the necessary power to start the engine and operate properly.Rate this question:
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- 31.
On the F-15 aircraft, the PC system hydraulic pumps are located on the
- A.
Outboard side of each AMAD
- B.
Inboard side of each AMAD
- C.
Right side of each AMAD
- D.
Left side of each AMAD
Correct Answer
A. Outboard side of each AMADExplanation
The correct answer is outboard side of each AMAD. The PC system hydraulic pumps on the F-15 aircraft are positioned on the outboard side of each AMAD (Aircraft Mounted Accessory Drive). This placement allows for efficient distribution of hydraulic power to various systems and components on the aircraft.Rate this question:
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- 32.
On the F-15's PC system, what prevents complete fluid loss if one of the return lines develops a leak?
- A.
System relief valve
- B.
Return check valve
- C.
Return bypass valve
- D.
Thermal control valve
Correct Answer
B. Return check valveExplanation
The return check valve prevents complete fluid loss if one of the return lines develops a leak. This valve allows fluid to flow in one direction, from the system back to the reservoir, but prevents it from flowing back in the opposite direction. Therefore, if there is a leak in one of the return lines, the check valve will ensure that the fluid does not escape from the system and instead returns to the reservoir, preventing complete fluid loss.Rate this question:
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- 33.
On the F-15 aircraft, what happens when PC circuit B is mechanically shut off?
- A.
Circuit A isolates and circuit B opens
- B.
Circuit B isolates and circuit A opens
- C.
The utility system takes over for the PC system
- D.
The PC system takes over for the utility system
Correct Answer
C. The utility system takes over for the PC systemExplanation
When PC circuit B is mechanically shut off on the F-15 aircraft, the utility system takes over for the PC system. This means that the utility system becomes the primary system responsible for providing power and functionality, replacing the PC system which is no longer operational.Rate this question:
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- 34.
On the F-15 aircraft, the aircraft-mounted accessory drive pushes the utility hydraulic pumps at what speed to deliver 53.7 gpm of flow?
- A.
2,210 RPM
- B.
3,210 RPM
- C.
4,210 RPM
- D.
5,210 RPM
Correct Answer
C. 4,210 RPMExplanation
The correct answer is 4,210 RPM. The utility hydraulic pumps on the F-15 aircraft are driven by the aircraft-mounted accessory drive. In order to deliver a flow rate of 53.7 gpm, the accessory drive needs to operate at a speed of 4,210 RPM.Rate this question:
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- 35.
On the F-15 aircraft, what do the utility pump manifolds have in common with the power control pump manifolds?
- A.
They are indentical and interchangeable
- B.
They develop head pressure for the pumps
- C.
They have pressure switches inside the pumps
- D.
They all connect to the aircraft-mounted accessory drive with D-band clamps
Correct Answer
A. They are indentical and interchangeableExplanation
The utility pump manifolds and power control pump manifolds on the F-15 aircraft are identical and interchangeable. This means that they have the same design and can be used interchangeably without any issues.Rate this question:
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- 36.
On the F-15 aircraft, what is the cracking pressure of the right utility hydraulic pump pressure check valve?
- A.
250-290 psi
- B.
210-240 psi
- C.
150-190 psi
- D.
110-140 psi
Correct Answer
B. 210-240 psiExplanation
The cracking pressure of the right utility hydraulic pump pressure check valve on the F-15 aircraft is between 210-240 psi. This means that the valve will open and allow hydraulic fluid to flow when the pressure in the system reaches this range.Rate this question:
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- 37.
On the F-15 aircraft, what occurs if the right utility hydraulic pump fails?
- A.
Right utility pump, hydraulic, and master caution lights illuminate
- B.
Utility A and B, hydraulic, and master caution lights illuminate
- C.
The utility non-reservoir level-sensing does not function
- D.
Nothing
Correct Answer
A. Right utility pump, hydraulic, and master caution lights illuminateExplanation
If the right utility hydraulic pump fails on the F-15 aircraft, the right utility pump, hydraulic, and master caution lights will illuminate. This indicates that there is a problem with the right utility hydraulic system, alerting the pilot to the failure.Rate this question:
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- 38.
On the F-15 aircraft, at what pressure differential does the utility thermal control valve allow fluid to bypass the heat exchanger?
- A.
32.5 psid
- B.
42.5 psid
- C.
52.5 psid
- D.
62.5 psid
Correct Answer
C. 52.5 psidExplanation
The utility thermal control valve on the F-15 aircraft allows fluid to bypass the heat exchanger when the pressure differential reaches 52.5 psid. This means that when the pressure difference between the two sides of the heat exchanger reaches 52.5 pounds per square inch, the valve opens and allows some of the fluid to bypass the heat exchanger, preventing damage or failure due to excessive pressure.Rate this question:
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- 39.
When a hydraulic leak occurs in the utility system on an F-15 aircraft, how does circuit A shut off?
- A.
Pneumatically
- B.
Hydraulically
- C.
Mechanically
- D.
Electrically
Correct Answer
C. MechanicallyExplanation
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 or device in place that automatically shuts off the circuit when a hydraulic leak is detected. This could be a valve or a similar component that is triggered by the presence of a leak, preventing further flow of hydraulic fluid and minimizing the risk of damage or malfunction in the system.Rate this question:
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- 40.
On the F-15 aircraft, what holds the aileron switching valve in the primary position?
- A.
Normal PC system pressure
- B.
Normal utility system pressure
- C.
Backup utility system pressure
- D.
Backup PC system pressure
Correct Answer
A. Normal PC system pressureExplanation
The aileron switching valve on the F-15 aircraft is held in the primary position by normal PC system pressure. This means that the valve is controlled and maintained by the normal pressure in the primary control (PC) system of the aircraft. This ensures that the aileron switching valve functions properly and controls the movement of the ailerons effectively during flight.Rate this question:
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- 41.
On the F-15 aircraft, how long does utility system non-reservoir level-sensing maintain pressure if the aircraft develops a leak in the utility hydraulic system?
- A.
Until the circuit A and B shutoff valves open
- B.
Until the circuit A and B shutoff valves close
- C.
As long as there is hydraulic fluid left in the utility reservoir
- D.
As long as there is hydraulic fluid left in the power control backup system
Correct Answer
C. As long as there is hydraulic fluid left in the utility reservoirExplanation
The correct answer is "As long as there is hydraulic fluid left in the utility reservoir." This means that the utility system non-reservoir level-sensing will maintain pressure as long as there is hydraulic fluid remaining in the utility reservoir. Once the fluid runs out, the pressure will no longer be maintained.Rate this question:
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- 42.
On the F-15 aircraft, you determine the fluid level in a hydraulic reservoir by
- A.
Subtracting the amount put in from the amount taken out
- B.
The position of the pointer relative to the fixed gage
- C.
The position of the pointer realtive to the outer dial
- D.
Measuring with a dipstick
Correct Answer
C. The position of the pointer realtive to the outer dialExplanation
The correct answer is the position of the pointer relative to the outer dial. This is because the outer dial is marked with specific fluid level indicators, and the position of the pointer will indicate the current fluid level in the hydraulic reservoir. By observing the position of the pointer relative to the outer dial, one can determine whether the fluid level is at the desired level or if it needs to be adjusted.Rate this question:
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- 43.
On the F-15 aircraft, how many overtemperature indicators are there in the hydraulic system?
- A.
One per PC reservoir and two for the utility reservoir
- B.
Two per PC reservoir and one for the utility reservoir
- C.
Two per reservoir
- D.
One per reservoir
Correct Answer
D. One per reservoirExplanation
The correct answer is "One per reservoir." On the F-15 aircraft, there is one overtemperature indicator for each reservoir in the hydraulic system. This means that there is one overtemperature indicator for the PC reservoir and one for the utility reservoir.Rate this question:
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- 44.
On the F-15 aircraft, the control stick consists of a stick grip and
- A.
Control system damper
- B.
Force transducer
- C.
Ratio changer
- D.
Torque tube
Correct Answer
B. Force transducerExplanation
The control stick on the F-15 aircraft includes a stick grip and a force transducer. A force transducer is a device that measures the amount of force applied to it. In this context, the force transducer would measure the force exerted by the pilot on the control stick, allowing the aircraft's control system to interpret and respond to the pilot's inputs accordingly. This is important for maintaining control and maneuverability of the aircraft during flight.Rate this question:
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- 45.
On the F-15 aircraft, what comprises the control stick boost-and-pitch compensator?
- A.
PRCA, ARI, and mixer assembly
- B.
Emergency generator/stabilator selector valve and switching valves
- C.
Emergency generator/stabilator selector valve and servocylinders
- D.
PRCA, ARI, and control system damper
Correct Answer
D. PRCA, ARI, and control system damperExplanation
The control stick boost-and-pitch compensator on the F-15 aircraft is comprised of the PRCA (Pitch Rate Command Amplifier), ARI (Angle Rate Integrator), and control system damper. These components work together to provide enhanced control and stability during flight. The PRCA amplifies the pilot's input on the control stick, the ARI integrates the rate of change of the control stick input to determine the desired aircraft pitch, and the control system damper helps to dampen any oscillations or vibrations in the control system.Rate this question:
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- 46.
On the F-15 aircraft, how does the lateral system utilize the horizontal stabilator hydraulic servo cylinder?
- A.
Differentially for yaw
- B.
Differentially for roll
- C.
Combined for yaw
- D.
Combined for roll
Correct Answer
B. Differentially for rollExplanation
The lateral system on the F-15 aircraft utilizes the horizontal stabilator hydraulic servo cylinder differentially for roll. This means that the hydraulic servo cylinder is used to control the roll movement of the aircraft by applying different amounts of hydraulic pressure to each side of the stabilator. By doing so, the aircraft can achieve differential movement of the stabilator, allowing for precise control and maneuverability during roll maneuvers.Rate this question:
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- 47.
On the F-15 aircraft, how does the PRCA control the ARI?
- A.
Electrically through the airspeed switch
- B.
Mechanically through the pitch boost actuator
- C.
Hydraulically through the pitch ratio controller
- D.
Hydromechanically through the automatic flight control assembly/PRCA interface
Correct Answer
C. Hydraulically through the pitch ratio controllerExplanation
The PRCA (Pitch Ratio Controller Assembly) controls the ARI (Automatic Recovery System) on the F-15 aircraft. The pitch ratio controller operates hydraulically, meaning it uses hydraulic fluid to control the movement and position of the ARI. This allows for precise control and adjustment of the aircraft's pitch, ensuring stability and maneuverability during flight. The other options, such as electrical control through the airspeed switch or mechanical control through the pitch boost actuator, are not the correct methods of controlling the ARI on the F-15 aircraft.Rate this question:
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- 48.
On the F-15 aircraft, what happens to the aileron servo cylinders if they lose hydraulic pressure?
- A.
The pressure sensor unlocks
- B.
Lock to the neutral position
- C.
The cavitation valves close
- D.
Act as a flutter dampers
Correct Answer
D. Act as a flutter dampersExplanation
If the aileron servo cylinders on the F-15 aircraft lose hydraulic pressure, they will act as flutter dampers. Flutter is an unstable oscillation that can occur in aircraft, particularly at high speeds. The aileron servo cylinders, when functioning properly, help control the movement of the ailerons, which are the control surfaces on the wings that allow the aircraft to roll. When hydraulic pressure is lost, the servo cylinders can no longer move the ailerons, but they still provide some resistance and stability to mitigate flutter.Rate this question:
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- 49.
On the F-15 aircraft, what counters aft stick movement during rapid acceleration of the aircraft?
- A.
Mass weight
- B.
Pitch boost actuator
- C.
Torque tube assembly
- D.
Lateral feel trim actuator
Correct Answer
A. Mass weightExplanation
Mass weight counters aft stick movement during rapid acceleration of the aircraft. As the aircraft accelerates, the mass weight located in the nose of the aircraft moves aft, exerting a force that opposes the aft stick movement. This helps to maintain stability and prevent excessive pitch changes during acceleration.Rate this question:
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- 50.
On the F-15 aircraft, what is the adjustment that results in a collective output to the stabilators for altitude and speed called?
- A.
Roll ratio
- B.
Pitch ratio
- C.
Aileron washout
- D.
Stabilator washout
Correct Answer
B. Pitch ratioExplanation
The adjustment that results in a collective output to the stabilators for altitude and speed is called pitch ratio. This adjustment allows the pilot to control the aircraft's pitch, which is the up and down movement of the aircraft's nose. By adjusting the pitch ratio, the pilot can change the aircraft's altitude and speed.Rate this question:
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