CDC 2A354C Volume 2 F-16 Instrumentation And Flight Control Systems

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Avionics Quizzes & Trivia
About This Quiz

This quiz focuses on the F-16's instrumentation and flight control systems, assessing knowledge on flight environment pressures, angle-of-attack, and the pitot-static probe pneumatic system. It is designed for learners aiming to understand technical aspects of aviation and avionics.

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  • 2. 

    Which crash survivable flight data recorder (CSFDR) system control surface position transducer is not​ connected to an integrated servo-actuator (ISA)?

    • Rudder

    • Left flaperon only

    • Left horizontal tail

    • Right horizontal tail

    Correct Answer
    A. Rudder
    Explanation
    The rudder is the correct answer because it is the only control surface position transducer that is not connected to an integrated servo-actuator (ISA). The left flaperon, left horizontal tail, and right horizontal tail are all connected to an ISA, but the rudder is not.

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  • 3. 

    Which crash survivable flight data recorder (CSFDR) type data is known as structural loads environmental data 

    • 1

    • 2

    • 3

    • 4

    Correct Answer
    A. 3
  • 4. 

    What force is created when pressure on the bottom of the airfoil is greater than on the top of the airfoil?

    • Lift

    • Drag

    • Speed

    • Thrust

    Correct Answer
    A. Lift
    Explanation
    When the pressure on the bottom of the airfoil is greater than on the top, it creates a force called lift. Lift is the upward force that allows an aircraft to overcome gravity and stay airborne. This difference in pressure is caused by the shape of the airfoil, with the curved top surface creating lower pressure compared to the flatter bottom surface. The lift force is essential for the aircraft to generate upward motion and maintain flight.

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  • 5. 

    Aircraft pitch is referenced from

    • The nose

    • Either wingtip

    • The left wingtip

    • The right wingtip

    Correct Answer
    A. The nose
    Explanation
    Aircraft pitch refers to the rotation of the aircraft along its lateral axis, causing the nose to move up or down. It is measured by referencing the nose of the aircraft as the point of measurement. This means that the pitch angle is determined based on the movement of the nose, regardless of the position of the wingtips.

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  • 6. 

    On the F-16 what is the principal component of the flight control system?

    • Electronic component assembly (ECA)

    • Flight control computer (FLCC)

    • Flight control panel (FLCP)

    • Manual trim panel (MTP)

    Correct Answer
    A. Flight control computer (FLCC)
    Explanation
    The principal component of the flight control system on the F-16 is the Flight Control Computer (FLCC). This computer is responsible for processing and interpreting inputs from the pilot and other systems, and then sending commands to the various control surfaces of the aircraft to maneuver and control its flight. The FLCC plays a crucial role in ensuring the stability and control of the aircraft during flight.

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  • 7. 

    When does the seat data recorder (SDR) cease recording operations? 

    • Upon flight control system (FLCS) shutdown

    • Upon a weight-on-wheels (WOW) condition

    • During digital backup operations

    • Upon autopilot engagement

    Correct Answer
    A. Upon a weight-on-wheels (WOW) condition
    Explanation
    The seat data recorder (SDR) ceases recording operations upon a weight-on-wheels (WOW) condition. This means that when the aircraft is on the ground and the weight is supported by the wheels, the SDR stops recording. This is likely done to conserve storage space and battery power, as there is no need to record data when the aircraft is not in motion.

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  • 8. 

    True angle-of-attack (AOA) is the angle between an aircraft's wing cord line and its

    • Attitude

    • Altitude

    • Flight path

    • Glide slope

    Correct Answer
    A. Flight path
    Explanation
    The true angle-of-attack (AOA) is the angle between an aircraft's wing cord line and its flight path. This angle is important in determining the lift and drag forces acting on the aircraft. It is different from the aircraft's attitude, which refers to the orientation of the aircraft relative to the horizon, altitude, which is the height above sea level, and glide slope, which is the angle of descent during a landing approach.

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  • 9. 

    What's crash survivable flight data recorder (CSFDR) type 1 data primarily used for?

    • Engine analysis

    • Mishap investigation

    • Individual aircraft tracking

    • Maintenance troubleshooting

    Correct Answer
    A. Mishap investigation
    Explanation
    CSFDR type 1 data is primarily used for mishap investigation. This means that in the event of an aircraft accident or incident, the CSFDR type 1 data can provide crucial information and insights into what happened, helping investigators understand the causes and contributing factors of the mishap. This data can include flight parameters, cockpit voice recordings, and other relevant information that can aid in the investigation process.

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  • 10. 

    Which crash survivable flight data recorder (CSFDR) type data is used for engine analysis?

    • 1

    • 2

    • 3

    • 4

    Correct Answer
    A. 4
    Explanation
    Crash survivable flight data recorders (CSFDR) are used to collect and store data during a flight, including information about the engines. Type 4 CSFDRs are specifically designed to record engine data, making them the correct choice for engine analysis.

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  • 11. 

    What occurs if the maximum recording limit of the seat data recorder (SDR) is reached?

    • Data overwrite

    • SDR stops recording

    • A new SDR is installed

    • Overflow data is recorded to the crash survivable flight data recorder (CSFDR)

    Correct Answer
    A. Data overwrite
    Explanation
    If the maximum recording limit of the seat data recorder (SDR) is reached, data overwrite will occur. This means that the oldest recorded data will be erased to make space for new data.

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  • 12. 

    The digital video recorder system records morse code three-letter ground station identification signals from which systen?

    • Stall warning system

    • Landing gear warning system

    • Identification friend or foe (IFF) system

    • Tactical air navigation (TACAN) system

    Correct Answer
    A. Tactical air navigation (TACAN) system
    Explanation
    The digital video recorder system records morse code three-letter ground station identification signals from the Tactical Air Navigation (TACAN) system. TACAN is a navigation aid used by military aircraft to determine their position and obtain distance and bearing information from ground stations. The ground stations transmit identification signals in morse code, which are recorded by the digital video recorder system for later analysis and reference.

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  • 13. 

    What flight environment pressure is sensed by small holes located on the sides of the pilot and air data probes

    • Pitot

    • Static

    • Impact

    • Differential

    Correct Answer
    A. Static
    Explanation
    Small holes located on the sides of the pilot and air data probes sense the static pressure of the flight environment. Static pressure is the pressure exerted by the surrounding air and remains constant regardless of the aircraft's motion. It is used in various aircraft systems, such as the altimeter, airspeed indicator, and vertical speed indicator, to provide accurate measurements of the aircraft's altitude, airspeed, and rate of climb or descent.

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  • 14. 

    One complete revolution of the altimeter's altitude dial equals 

    • 100 feet of altitude

    • 1,000 feet of altitude

    • 5,000 feet of altitude

    • 10,000 feet of altitude

    Correct Answer
    A. 1,000 feet of altitude
    Explanation
    The correct answer is 1,000 feet of altitude. This means that for every complete revolution of the altimeter's altitude dial, the altitude increases or decreases by 1,000 feet. This is a standard unit of measurement used in aviation to track changes in altitude during flight.

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  • 15. 

    An axis on an aircraft is an imaginary line that

    • Passes through the aircraft's mid section

    • Divides the aircraft in half from nose to tail

    • Passes through the aircraft's center of gravity

    • Divides the aircraft in half from wingtip to wingtip

    Correct Answer
    A. Passes through the aircraft's center of gravity
    Explanation
    The axis on an aircraft that passes through the aircraft's center of gravity is important for maintaining stability during flight. The center of gravity is the point where the aircraft's weight is evenly distributed, and any movement or rotation around this axis will not cause an imbalance. This axis is crucial for controlling the aircraft's pitch and yaw motions. By passing through the center of gravity, it helps ensure that the aircraft remains balanced and stable in flight.

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  • 16. 

    The F-16 flight control system (FLCS) self-test can be performed

    • While the aircraft is in flight

    • Only when weight is on wheels

    • Only when weight is off wheels

    • Anytime the self-control switch is placed to TEST

    Correct Answer
    A. Only when weight is on wheels
    Explanation
    The F-16 flight control system (FLCS) self-test can only be performed when weight is on the wheels. This is because the self-test involves checking the functionality of the control system while the aircraft is in a normal operating condition, which includes having the weight of the aircraft supported by the wheels. Performing the self-test when weight is off the wheels may not accurately reflect the performance of the control system in actual flight conditions.

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  • 17. 

    The F-16 rate gyro assemblies contain pitch, roll, and yaw rate gyros that

    • Are not interchangable

    • Are all unique assemblies

    • Each contain two individual rate gyros

    • Become unique only when connected to aircraft wiring

    Correct Answer
    A. Become unique only when connected to aircraft wiring
    Explanation
    The F-16 rate gyro assemblies become unique only when connected to aircraft wiring because it is the wiring that provides the necessary electrical connections and signals for the gyros to function properly. Without the aircraft wiring, the gyros would not be able to receive or transmit the necessary information, making them ineffective. Therefore, the gyros only become unique and functional when connected to the specific wiring system of the aircraft.

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  • 18. 

    On the F-16, which condition is not a requirement for the digital flight control panel's built-in test (BIT) switch to electrically hold in the BIT position?

    • Engine operating

    • Weight is on the main landing gear

    • Digital flight control system (DFLCS) power is applied

    • Left and right wheel speed sensors indicate less than 28 knots

    Correct Answer
    A. Engine operating
    Explanation
    The condition that is not a requirement for the digital flight control panel's built-in test (BIT) switch to electrically hold in the BIT position is "Engine operating". This means that even if the engine is not operating, the BIT switch can still be held in the BIT position.

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  • 19. 

    The amount of control surface movement in relatin to the amount of pressure applied to the side-stick or rudder pedals is called

    • Override control

    • Gain scheduling

    • Automatic spin prevention

    • Aileron rudder interconnect

    Correct Answer
    A. Gain scheduling
    Explanation
    Gain scheduling refers to the adjustment of control surface movement based on the amount of pressure applied to the side-stick or rudder pedals. It allows for a variable response from the control surfaces based on the pilot's input, providing a more precise and adaptable control system. This ensures that the aircraft responds appropriately to different flight conditions and pilot inputs, enhancing safety and maneuverability.

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  • 20. 

    On the F-16 embedded global positioning system/ intertial navigation system (EGI), which navigation solution is the most accurate and preferred by the pilot?

    • EGI

    • INS-only

    • GPS-only

    • GPS/INS

    Correct Answer
    A. GPS/INS
    Explanation
    The most accurate and preferred navigation solution on the F-16 EGI is GPS/INS. This combination of both the Global Positioning System (GPS) and Inertial Navigation System (INS) provides the pilot with the highest level of accuracy and reliability in determining the aircraft's position and navigating to a destination. GPS provides precise global positioning information, while INS uses accelerometers and gyroscopes to continuously track the aircraft's movement. By combining the strengths of both systems, the GPS/INS solution offers the best navigation capabilities for the pilot.

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  • 21. 

    The pitot-static probe pneumatic system supplies air data to the central air data computer (CADC), airspeed mach indicator (AMI), altimeter, and 

    • Flight control computer (FLCC)

    • Pneumatic sensor assembly (PSA)

    • Electronic component assembly (ECA)

    • Digital flight control computer (DFLCC)

    Correct Answer
    A. Pneumatic sensor assembly (PSA)
    Explanation
    The correct answer is the pneumatic sensor assembly (PSA). The pitot-static probe pneumatic system is responsible for supplying air data to various components, including the central air data computer (CADC), airspeed mach indicator (AMI), altimeter, and flight control computer (FLCC). The pneumatic sensor assembly (PSA) is a crucial part of this system, as it consists of sensors that measure air pressure and provide accurate data to the other components. Without the PSA, the pitot-static probe pneumatic system would not be able to function properly and provide accurate air data to the aircraft's systems.

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  • 22. 

    Which crash survivable flight data recorder (CSFDR) system component utilizes a pendulous device?

    • Crash survivable memory unit (CSMU)

    • Axial accelerometer transmitter

    • Control surface position transducer

    • Engine power lever angle potentiometer

    Correct Answer
    A. Axial accelerometer transmitter
    Explanation
    The axial accelerometer transmitter utilizes a pendulous device in the crash survivable flight data recorder (CSFDR) system. This device is responsible for measuring and transmitting the acceleration data in the axial direction. It is designed to withstand the impact forces during a crash and ensure that the recorded data is preserved for analysis.

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  • 23. 

    Which F-16 hydraulic pressure indicators display the indication for hydraulic system A and B?

    • Left indicators display both A and B systems

    • Right indicators display both A and B systems

    • Left indicators display A and right indicators display B

    • Right indicators display A and left indicators display B

    Correct Answer
    A. Left indicators display A and right indicators display B
    Explanation
    The left indicators display the indication for hydraulic system A, while the right indicators display the indication for hydraulic system B.

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  • 24. 

    What's the display range of the altimeter's altitude drum counter?

    • 0 to 50,000 feet

    • 0 to 80,000 feet

    • -1,000 to 50,000 feet

    • -1,000 to 80,000 feet

    Correct Answer
    A. -1,000 to 80,000 feet
    Explanation
    The display range of the altimeter's altitude drum counter is from -1,000 to 80,000 feet. This means that the altimeter can display altitudes ranging from negative 1,000 feet to 80,000 feet.

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  • 25. 

    Daniel Bernoulli developed a theory on the relationship of fluid speed,

    • And pressure

    • Air, and pressure

    • Time, and pressure

    • Air pressure, and venturi

    Correct Answer
    A. And pressure
  • 26. 

    The F-16 digital flight control panel's RUN/FAIL lamp is only used

    • During the ejection process

    • During built-in test (BIT) operation

    • To denote an integrated servoactuator (ISA) failure

    • To indicate in flight digital flight control computer (DFLCC) failures

    Correct Answer
    A. During built-in test (BIT) operation
    Explanation
    The F-16 digital flight control panel's RUN/FAIL lamp is only used during built-in test (BIT) operation. This means that the lamp is specifically designed to indicate any failures or malfunctions that occur during the self-diagnostic test of the aircraft's systems. It serves as a visual indicator for the pilot to identify any issues that need to be addressed before or during flight.

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  • 27. 

    If  an F-16 experienced a "runaway trim" condition, which manual trim panel function would be used?

    • Yaw trim knob

    • Roll trim thumb wheel

    • TRIM/AP DISC switch

    • Pitch trim thumb wheel

    Correct Answer
    A. TRIM/AP DISC switch
    Explanation
    If an F-16 experienced a "runaway trim" condition, the TRIM/AP DISC switch would be used. This switch is responsible for controlling the trim function and can be used to manually adjust the trim settings. By activating this switch, the pilot can regain control over the trim and correct any issues caused by the runaway trim condition.

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  • 28. 

    How are central air data computer (CADC) analog output signals transferred to their final destination? 

    • Via the A-multiplex (MUX) bus

    • Via the D-MUX bus

    • Via aircraft wiring

    • Via fiber optics

    Correct Answer
    A. Via aircraft wiring
    Explanation
    The central air data computer (CADC) analog output signals are transferred to their final destination via aircraft wiring. This means that the signals are transmitted through the electrical wiring system of the aircraft to reach their intended destination.

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  • 29. 

    The pitot-static probe pneumatic system supplies the airspeed mach indicator (AMI) with 

    • Sideslip (Ps)

    • Pitot pressure (Pt) only

    • Static pressure (P) only

    • Pt and static pressure (Ps)

    Correct Answer
    A. Pt and static pressure (Ps)
    Explanation
    The pitot-static probe pneumatic system supplies the airspeed mach indicator (AMI) with pitot pressure (Pt) and static pressure (Ps). The pitot pressure, which is measured by the pitot tube, represents the dynamic pressure of the air flowing around the aircraft. The static pressure, on the other hand, is measured by static ports and represents the atmospheric pressure. By combining these two pressures, the AMI is able to accurately display the airspeed and mach number of the aircraft.

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  • 30. 

    The angle-of-attack (AOA) indicator is considered a 

    • Back-up indicator

    • Vertical tape indicator

    • Self-contained indicator

    • Horizontal tape indicator

    Correct Answer
    A. Vertical tape indicator
    Explanation
    The angle-of-attack (AOA) indicator is considered a vertical tape indicator because it displays the angle of attack information in a vertical format on a tape or bar graph. This type of indicator is commonly used in aircraft to provide pilots with a visual representation of the aircraft's angle of attack, which is the angle between the oncoming air and the aircraft's reference line. The vertical tape indicator allows pilots to quickly and easily interpret the angle of attack information, helping them maintain safe and efficient flight operations.

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  • 31. 

    What's the crash survivable flight data recorder (CSFDR) system's prime component?

    • Seat data recorder (SDR)

    • Signal acquisition unit (SAU)

    • Crash survivable memory unit (CSMU)

    • Linear variable differential transformer (LVDT)

    Correct Answer
    A. Signal acquisition unit (SAU)
    Explanation
    The crash survivable flight data recorder (CSFDR) system's prime component is the Signal acquisition unit (SAU). The SAU is responsible for collecting and recording various flight data parameters such as altitude, airspeed, heading, and engine performance. It is designed to withstand extreme conditions during a crash and ensure that the recorded data is preserved for analysis during accident investigations. The SAU plays a crucial role in providing valuable information about the aircraft's performance leading up to an accident, aiding in determining the cause of the crash and improving aviation safety.

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  • 32. 

    As fluid passes through a venturi, pressure is

    • Equal throughout the venturi

    • Lowest where speed is the lowest

    • Lowest where speed is the highest

    • A product of fluid speed, time, and distance

    Correct Answer
    A. Lowest where speed is the highest
    Explanation
    As fluid passes through a venturi, the cross-sectional area decreases, causing the fluid speed to increase according to the principle of continuity. According to Bernoulli's principle, as the fluid speed increases, the pressure decreases. Therefore, the pressure is lowest where the speed is the highest in a venturi.

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  • 33. 

    Angle-of-attack (AOA) is the angle between the aircraft's

    • Wings and the ground

    • Wings and flightpath

    • Flightpath and the ground

    • Flightpath and the horizon

    Correct Answer
    A. Wings and flightpath
    Explanation
    The correct answer is "wings and flightpath". Angle-of-attack (AOA) refers to the angle between the aircraft's wings and the direction of its flightpath. It is an important parameter in aviation as it affects the lift and drag forces acting on the aircraft. By adjusting the AOA, pilots can control the aircraft's climb, descent, and maneuverability.

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  • 34. 

    The aircraft axis that runs from the nose to the tail is

    • Lateral

    • Vertical

    • Horizontal

    • Longitudinal

    Correct Answer
    A. Longitudinal
    Explanation
    The correct answer is "longitudinal." This is because the axis that runs from the nose to the tail of an aircraft is known as the longitudinal axis. This axis is responsible for controlling the pitch of the aircraft, which is the up and down movement.

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  • 35. 

    Artificial feel was incorporated into the flight control system to

    • Provide stability augmentation

    • Smooth out and control the angle of surface movement according to airspeed

    • Eliminate the need for force when controlling flight control surface movement

    • Keep the controls from being over controlled or accidentally jarred by the pilot

    Correct Answer
    A. Keep the controls from being over controlled or accidentally jarred by the pilot
    Explanation
    The artificial feel was incorporated into the flight control system to prevent the controls from being over controlled or accidentally jarred by the pilot. This means that the artificial feel helps to provide resistance or feedback to the pilot's inputs, ensuring that they do not make sudden or excessive movements that could potentially destabilize the aircraft. By doing so, it helps to maintain the stability and control of the flight control surfaces, ensuring smooth and controlled movement according to the airspeed.

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  • 36. 

    The use of accelerometers and gyros to smooth out flight control inputs and to automatically adjust the flight control surfaces for turbulance is known as

    • Flight augmentation

    • Direct augmentation

    • Control augmentation

    • Stability augmentation

    Correct Answer
    A. Stability augmentation
    Explanation
    Stability augmentation refers to the use of accelerometers and gyros to improve the stability of an aircraft. By continuously monitoring the aircraft's movement and making adjustments to the flight control surfaces, stability augmentation helps to smooth out flight control inputs and compensate for turbulence. This technology enhances the overall stability and control of the aircraft, making it easier for the pilot to fly and reducing the risk of accidents.

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  • 37. 

    If there's a second electronic failure in a given axis, what indication is there on the F-16 flight control panel (FLCP)?

    • DUAL FC FAIL light illuminates

    • The light for the applicable axis (P,R, or Y) will illuminate

    • The light for the applicable axis (P, R, or Y) will illuminate along with the flight control system (FLCS) caution light

    • The light for the applicable axis (P,R, or Y) will illuminate along with the MASTER CAUTION light

    Correct Answer
    A. DUAL FC FAIL light illuminates
    Explanation
    If there is a second electronic failure in a given axis, the DUAL FC FAIL light on the F-16 flight control panel will illuminate. This indicates that there are two failures in the flight control system for that axis.

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  • 38. 

    The F-16 rudder moves automatically during coordinated turns as a function of

    • Aileron rudder interconnect (ARI)

    • Leading edge flaps (LEF)

    • Dynamic pressure

    • Roll rate gyro

    Correct Answer
    A. Aileron rudder interconnect (ARI)
    Explanation
    The F-16 rudder moves automatically during coordinated turns as a function of the aileron rudder interconnect (ARI). The ARI system is designed to coordinate the movement of the ailerons and rudder, ensuring that the aircraft maintains balanced and coordinated turns. As the pilot inputs aileron commands to roll the aircraft, the ARI system automatically adjusts the rudder to counteract any adverse yaw, keeping the aircraft in a coordinated turn. This helps to maintain stability and control during maneuvering.

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  • 39. 

    How many internal fuel tanks does the F-16 have?

    • Six

    • Seven

    • Eight

    • Twelve

    Correct Answer
    A. Seven
    Explanation
    The F-16 has seven internal fuel tanks.

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  • 40. 

    What's the function of the angle-of-attack (AOA) indexer's lever control switch?

    • On/Off switch

    • Sector light intensity

    • Enables AOA logic circuits

    • Only used during takeoff and landing configurations

    Correct Answer
    A. Sector light intensity
    Explanation
    The function of the angle-of-attack (AOA) indexer's lever control switch is to adjust the sector light intensity. This means that the switch controls the brightness or intensity of the sector lights on the AOA indexer. The sector lights provide visual indications to the pilot about the aircraft's angle of attack, helping them maintain the optimal angle for safe and efficient flight. By adjusting the sector light intensity, the pilot can customize the visibility of these indicators based on their preference and the lighting conditions in the cockpit.

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  • 41. 

    What data is only stored in the crash survivable flight data recorder (CSFDR)?

    • Type 1

    • Type 2

    • Type 3

    • Type 4

    Correct Answer
    A. Type 1
    Explanation
    The data that is only stored in the crash survivable flight data recorder (CSFDR) is Type 1 data. This implies that the other types of data (Type 2, Type 3, and Type 4) are not exclusively stored in the CSFDR and may be stored in other devices or systems.

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  • 42. 

    Which crash survivable flight data recorder (CSFDR) type data is dubbed as individual aircraft tracking data?

    • 1

    • 2

    • 3

    • 4

    Correct Answer
    A. 2
    Explanation
    The correct answer is 2. The crash survivable flight data recorder (CSFDR) type data that is dubbed as individual aircraft tracking data is typically the Aircraft Communications Addressing and Reporting System (ACARS) data. ACARS is a digital datalink system that allows aircraft to communicate with ground stations via satellite or radio frequency. It provides real-time information about the aircraft's position, altitude, speed, and other flight parameters, which can be used for individual aircraft tracking purposes.

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  • 43. 

    On F-16s, to reset an integrated servoactuator (ISA) failure, you must select the SERVO position of the servo electric reset swich and simultaneously depress the

    • MAL/IND switch

    • MASTER CAUTION light

    • Appropriate servo arm switch

    • Flight control system (FLCS) CAUTION/RESET switch

    Correct Answer
    A. Flight control system (FLCS) CAUTION/RESET switch
    Explanation
    To reset an integrated servoactuator (ISA) failure on F-16s, the correct action is to select the SERVO position of the servo electric reset switch and simultaneously depress the flight control system (FLCS) CAUTION/RESET switch. This action will reset the ISA and resolve the failure.

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  • 44. 

    What is the range of motion for the F-16 side-stick?

    • 1/8 inch in any direction

    • 1/4 inch in any direction

    • 1/2 inch in any direction

    • 1 inch in any direction

    Correct Answer
    A. 1/4 inch in any direction
    Explanation
    The range of motion for the F-16 side-stick is 1/4 inch in any direction. This means that the side-stick can be moved a maximum of 1/4 inch in any direction to control the aircraft. This limited range allows for precise and controlled movements of the side-stick, enabling the pilot to maneuver the F-16 effectively and accurately.

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  • 45. 

    If the F-16 embedded global positioning system/inertial navigation system (EGI) does not have GPS almanac data, satellite acquision can take up to how many minutes?

    • 30

    • 60

    • 90

    • 120

    Correct Answer
    A. 90
    Explanation
    If the F-16 embedded global positioning system/inertial navigation system (EGI) does not have GPS almanac data, satellite acquisition can take up to 90 minutes. This means that it can take a maximum of 90 minutes for the EGI to establish a connection with the GPS satellites and obtain the necessary data for navigation.

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  • 46. 

    On a F-16 D-model, what tank is smaller than the one found on a C-model?

    • F-1

    • F-2

    • Aft reservoir

    • Forward reservoir

    Correct Answer
    A. F-1
    Explanation
    The F-1 tank is smaller than the one found on a C-model.

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  • 47. 

    How many sources of pitot pressure (Pt) and static pressure (Ps) are routed by the pitot-static probe pneumatic system?

    • 1

    • 2

    • 3

    • 4

    Correct Answer
    A. 2
    Explanation
    The pitot-static probe pneumatic system routes two sources of pressure: pitot pressure (Pt) and static pressure (Ps). These two pressures are essential for measuring airspeed and altitude. The pitot pressure is measured by the pitot tube, which is positioned facing the oncoming airflow to measure the dynamic pressure. The static pressure is measured by static ports, which are located perpendicular to the airflow to measure the atmospheric pressure. Together, these two pressures provide crucial information for accurate airspeed and altitude measurements.

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  • 48. 

    Which digital video recorder system component controls the electrical power to the digital video recorder (DVR)?

    • Video SEL switch panel

    • Airborne video tape recorder (AVTR) panel

    • Cockpit television sensor electronics unit (CTVS E/U)

    • Cockpit television sensor (CTVS) video sensor head (VSH)

    Correct Answer
    A. Airborne video tape recorder (AVTR) panel
    Explanation
    The correct answer is the Airborne video tape recorder (AVTR) panel. The AVTR panel controls the electrical power to the digital video recorder (DVR). It is responsible for turning the DVR on and off and managing its power supply. The other options listed are not related to controlling the power of the DVR. The Video SEL switch panel is used for selecting different video sources, the Cockpit television sensor electronics unit (CTVS E/U) is responsible for processing video signals, and the Cockpit television sensor (CTVS) video sensor head (VSH) is the sensor that captures the video.

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  • 49. 

    At what degree do most airfoils enter a stall condition

    • 10

    • 20

    • 30

    • 40

    Correct Answer
    A. 20
    Explanation
    Most airfoils enter a stall condition at a 20-degree angle. At this angle, the airflow over the airfoil becomes disrupted and separates from the surface, causing a loss of lift and an increase in drag. This stall condition is a critical aerodynamic phenomenon that pilots need to be aware of and manage to maintain control of the aircraft.

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Quiz Review Timeline (Updated): Mar 21, 2023 +

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  • Current Version
  • Mar 21, 2023
    Quiz Edited by
    ProProfs Editorial Team
  • Apr 04, 2014
    Quiz Created by
    Warthog93

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