Avionics 2a352g Volume 3

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  • 1/100 Questions

    AIRCRAFT PITCH IS REFERENCED FROM

    • THE NOSE
    • EITHER WINGTIP
    • THE LEFT WINGTIP
    • THE RIGHT WINGTIP
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Avionics Quizzes & Trivia
About This Quiz

This AVIONICS 2A352G VOLUME 3 quiz assesses knowledge on aircraft systems, focusing on the pitot static probe pneumatic system, angle of attack, and data communication methods. It is designed for learners interested in avionics and aerospace engineering, enhancing both theoretical understanding and practical skills.

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  • 2. 

    WHAT FLIGHT ENVIRONMENTAL PRESSURE IS SENSED BY SMALL HOLES LOCATED ON THE SIDES OF THE PITOT AND AIR DATA PROBES?

    • PITOT

    • STATIC

    • IMPACT

    • DIFFERNTIAL

    Correct Answer
    A. STATIC
    Explanation
    Small holes located on the sides of the pitot and air data probes sense the static pressure of the flight environment. The static pressure is the atmospheric pressure exerted on the aircraft when it is not in motion. This pressure is used to measure altitude and airspeed. By comparing the static pressure with the total pressure measured by the pitot tube, the airspeed can be accurately determined. Therefore, the correct answer is STATIC.

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  • 3. 

    WHAT FORCE OPPOSES THE MOVEMENT OF THE AIRCRAFT THROUGH THE AIR?

    • LIFT

    • DRAG

    • GRAVITY

    • PROPULSION

    Correct Answer
    A. DRAG
    Explanation
    Drag is the force that opposes the movement of an aircraft through the air. It is caused by the resistance of the air against the aircraft's forward motion. Drag can be influenced by factors such as the shape of the aircraft, its speed, and the air density. Increasing drag can make it more difficult for the aircraft to move through the air and can affect its performance and fuel efficiency.

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  • 4. 

    THE CADC OUTPUTS ITS DATA USING THREE METHODS. THESE METHODS ARE SERIAL DIGITAL DATA WORDS, DISCRETES, AND

    • ANALOG

    • DISTINCT

    • ISOLATED

    • COMBINED

    Correct Answer
    A. ANALOG
    Explanation
    The correct answer is ANALOG. The question states that the CADC outputs its data using three methods, which are serial digital data words, discretes, and another method that is not mentioned. Since the options provided are analog, distinct, isolated, and combined, the most logical choice would be analog as it is a common method of data output in electronic devices.

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  • 5. 

    ONE COMPLETE REVOLUTION OF THE ALTIMETERS ALTITUDE DIAL EQUALS

    • 100 FEET OF ALTITUDE

    • 1000 FEET OF ALTITUDE

    • 5000 FEET OF ALTITUDE

    • 10000 FEET OF ALTITUDE

    Correct Answer
    A. 1000 FEET OF ALTITUDE
    Explanation
    One complete revolution of the altimeter's altitude dial equals 1000 feet of altitude. This means that for every full rotation of the dial, the altitude increases or decreases by 1000 feet.

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  • 6. 

    WHAT IS THE PRIMARY FORCE AN AIRCRAFT MUST OVERCOME?

    • LIFT

    • DRAG

    • THRUST

    • GRAVITY

    Correct Answer
    A. GRAVITY
    Explanation
    An aircraft must overcome the force of gravity in order to stay in the air. Gravity is the force that pulls objects towards the center of the Earth, and it acts in the opposite direction of lift. In order for an aircraft to maintain altitude or climb, it must generate enough lift to counteract the force of gravity. If the force of gravity is greater than the lift produced by the aircraft, it will descend or fall. Therefore, gravity is the primary force that an aircraft must overcome.

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  • 7. 

    AS AIR RUSHES PAST AN AIRFOIL, WHAT FORCE IS CREATED?

    • LIFT

    • DRAG

    • SPEED

    • THRUST

    Correct Answer
    A. LIFT
    Explanation
    As air rushes past an airfoil, the shape of the airfoil creates a pressure difference between the upper and lower surfaces. This pressure difference generates a lifting force called lift. This force acts perpendicular to the direction of the airflow and is responsible for keeping the aircraft in the air. Therefore, the correct answer is lift.

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  • 8. 

    ON F-16s, WHAT PROVIDES SIDE STICK ARTIFICIAL FEEL?

    • A CALIBRATED ACTUATOR WITHIN THE TRANSDUCER ASSEMBLY

    • BEAMS AND COIL SPRINGS WITHIN THE TRANSDUCER ASSEMBLY

    • A CALIBRATED LOCK MECHANISM IN THE TRANSDUCER ASSEMBLY

    • CYLINDRICAL COMPRESSED AIR WITHIN THE TRANSDUCER ASSEMBLY

    Correct Answer
    A. BEAMS AND COIL SPRINGS WITHIN THE TRANSDUCER ASSEMBLY
    Explanation
    The correct answer is beams and coil springs within the transducer assembly. In an F-16, the side stick artificial feel is provided by beams and coil springs within the transducer assembly. These components help to simulate the resistance and feedback that a pilot would experience when manipulating the side stick controls.

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  • 9. 

    WHAT IS THE RELATIONSHIP BETWEEN LIFT AND THE AOA?

    • LIFT EQUALS AOA

    • LIFT INCREASES WITH AOA

    • LIFT DECREASES WITH AOA

    • THE TERMS ARE INTERCHANGEABLE

    Correct Answer
    A. LIFT INCREASES WITH AOA
    Explanation
    The correct answer is that lift increases with AOA (Angle of Attack). The angle of attack refers to the angle between the wing's chord line and the oncoming airflow. When the AOA increases, the lift generated by the wing also increases. This is because a higher AOA causes the airflow to be deflected more, resulting in a greater pressure difference between the upper and lower surfaces of the wing, thus generating more lift. Therefore, as the AOA increases, the lift force acting on the wing also increases.

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  • 10. 

    WHAT IS THE PRINCIPAL COMPONENT OF THE F-16 FLIGHT CONTROL SYSTEM?

    • ECA

    • FLCC

    • FCC

    • FLCP

    Correct Answer
    A. FLCC
    Explanation
    The principal component of the F-16 flight control system is the FLCC.

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  • 11. 

    IN A TYPICAL SYNCHRO SYSTEM, THE TRANSMITTER IS LOCATED AT OR NEAR THE POINT WHERE PRESSURE OR MOVEMENT

    • IS AT ITS LOWEST LEVEL

    • CAN BE MEASURED MOST ACCURATELY

    • IS LIKELY TO REACH ITS HIGHEST LEVEL

    • CAN BE INPUT TO THE SYSTEM BEING MEASURED

    Correct Answer
    A. CAN BE MEASURED MOST ACCURATELY
    Explanation
    The transmitter in a typical synchro system is located at or near the point where pressure or movement can be measured most accurately. This is because the transmitter needs to accurately measure the pressure or movement in order to provide accurate data to the system being measured. By placing the transmitter at the point where the measurement can be most accurately obtained, it ensures that the data provided by the transmitter is reliable and precise.

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  • 12. 

    TRUE AOA IS THE ANGLE BETWEEN AN AIRCRAFTS 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 for determining the lift and drag forces acting on the aircraft. It is crucial in maintaining the aircraft's stability and controlling its performance during flight. The AOA affects the aircraft's lift, stall speed, and maneuverability. Therefore, understanding and adjusting the AOA is essential for safe and efficient flight operations.

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  • 13. 

    THE 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 AOA indicator is considered a vertical tape indicator because it provides a visual representation of the aircraft's angle of attack. The vertical tape on the indicator displays the angle of attack values, allowing the pilot to monitor and adjust the aircraft's pitch attitude for optimal performance and safety. This type of indicator is commonly used in aircraft to provide crucial information about the aircraft's angle of attack during flight.

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  • 14. 

    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
    Explanation
    Daniel Bernoulli developed a theory on the relationship of fluid speed and pressure. This theory, known as Bernoulli's principle, states that as the speed of a fluid increases, the pressure exerted by the fluid decreases. Conversely, as the speed of a fluid decreases, the pressure exerted by the fluid increases. This principle is applicable to various fluid systems, including air and water. Bernoulli's principle is widely used in various fields, such as aerodynamics, hydraulics, and fluid dynamics.

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  • 15. 

    AS FLUID PASSES THROUGH A VENTURI, PRESSURE IS

    • EQUAL THROUGHOUT THE VENTURI

    • LOWEST WHERE SPEED IS LOWEST

    • LOWEST WHERE SPEED IS HIGHEST

    • A PRODUCT OF FLUID SPEED, TIME, AND DISTANCE

    Correct Answer
    A. LOWEST WHERE SPEED IS HIGHEST
    Explanation
    According to the Venturi effect, as fluid passes through a constricted area of a pipe (such as a Venturi), the speed of the fluid increases while the pressure decreases. This is because the conservation of mass principle states that the mass flow rate of the fluid must remain constant. Therefore, when the fluid speeds up in the constricted area, the pressure decreases. Hence, the pressure is lowest where the speed is highest.

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  • 16. 

    IN A STAIGHT AND LEVEL FLIGHT, LIFT EQUALS GRAVITY AND THRUST EQUALS

    • DRAG

    • SPEED

    • PROPULSION

    • TIME/DISTANCE RATIO

    Correct Answer
    A. DRAG
    Explanation
    In a straight and level flight, lift equals gravity to maintain the aircraft at a constant altitude. Similarly, thrust is equal to drag to maintain a constant speed. Drag is the resistance force that opposes the motion of the aircraft through the air. Therefore, the correct answer is drag.

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  • 17. 

    TO DECREASE ALTITUDE, YOU WOULD NEED TO

    • REDUCE DRAG

    • REDUCE THRUST

    • INCREASE DRAG

    • INCREASE GRAVITY

    Correct Answer
    A. REDUCE THRUST
    Explanation
    To decrease altitude, reducing thrust is necessary. Thrust is the force that propels an aircraft forward and upward. By reducing thrust, the aircraft's engines produce less power, resulting in a decrease in upward force. As a result, the aircraft will descend and decrease its altitude.

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  • 18. 

    WHAT TYPE OF MEMORY DOES THE F-16 FLCC CONTAIN?

    • VOLATILE

    • AUXILIARY

    • NONVOLATILE

    • THE FLCC HAS NO MEMORY, THE SDR RECORDS FLIGHT EVENT

    Correct Answer
    A. NONVOLATILE
    Explanation
    The F-16 FLCC contains nonvolatile memory. Nonvolatile memory is a type of computer memory that retains its stored data even when the power is turned off or lost. This is in contrast to volatile memory, which requires a continuous power supply to retain its data. Nonvolatile memory is commonly used in electronic devices such as computers, smartphones, and aircraft systems to store important data that needs to be retained even in the absence of power. Therefore, the F-16 FLCC's nonvolatile memory allows it to store and retain critical information even when the power is not available.

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  • 19. 

    WHEN DOES THE SDR CEASE RECORDING OPERATIONS?

    • UPON FLCS SHUTDOWN

    • UPON A WOW CONDITION

    • DURING DIGITAL BACKUP OPERATIONS

    • UPON AUTOPILOT ENGAGEMENT

    Correct Answer
    A. UPON A WOW CONDITION
    Explanation
    The SDR (System Data Recorder) ceases recording operations upon a WOW (Weight on Wheels) condition. This means that when the aircraft is on the ground and the weight of the aircraft is supported by its wheels, the SDR stops recording data. This is a safety measure to ensure that only relevant data is recorded during flight operations and prevents unnecessary recording of data when the aircraft is not in use or on the ground.

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  • 20. 

    AOA IS MOST IMPORTANT DURING TAKEOFF, LANDING, AND

    • STRAFING

    • LOW AIRSPEED

    • HIGH AIRSPEED

    • STEEP CLIMBS OR DIVES

    Correct Answer
    A. LOW AIRSPEED
    Explanation
    AOA (Angle of Attack) is most important during takeoff, landing, and low airspeed situations. During takeoff and landing, maintaining the correct AOA is crucial for safe and efficient operations. Low airspeed situations require careful management of AOA to prevent stalling or loss of control. AOA becomes increasingly important at lower speeds as the margin between the critical AOA (stall angle) and the current AOA decreases. Therefore, the correct answer is "LOW AIRSPEED" because it accurately identifies a critical phase of flight where AOA plays a significant role.

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  • 21. 

    WHICH AXIS ON AN AIRCRAFT EXTEDS CROSSWISE FROM WINGTIP TO WINGTIP?

    • LATERAL

    • VERTICAL

    • HORIZONTAL

    • LONGITUDINAL

    Correct Answer
    A. LATERAL
    Explanation
    The lateral axis on an aircraft extends crosswise from wingtip to wingtip. This axis is responsible for controlling the roll motion of the aircraft, allowing it to bank and turn. The other axes, such as the vertical axis, control the yaw motion (nose left or right) and the longitudinal axis controls the pitch motion (nose up or down). The term "lateral" is used to describe the side-to-side movement, which is why it is the correct answer in this context.

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  • 22. 

    YAW MOVEMENTS ARE ACHIEVED BY

    • DEFLECTION OF THE RUDDER

    • DEFLECTION OF THE FLAPERONS AND RUDDER

    • EQUAL DEFLECTION OF THE HORIZONTAL STABILIZERS

    • EQUAL DEFLECTION OF THE FLAPERONS AND HORIZONTAL STABS

    Correct Answer
    A. DEFLECTION OF THE RUDDER
    Explanation
    YAW MOVEMENTS ARE ACHIEVED BY DEFLECTION OF THE RUDDER. The rudder is responsible for controlling the yaw movement of an aircraft. By deflecting the rudder, the pilot can create a yawing motion, which is the side-to-side movement of the aircraft's nose. This movement helps in controlling the direction of the aircraft during flight. The deflection of the rudder creates a force that counteracts any unwanted yawing moments and helps maintain stability and control of the aircraft.

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  • 23. 

    THE USE OF ACCELEROMETERS AND GYROS TO SMOOTH OUT FLIGH CONTROL INPUTS AND TO AUTOMATICALLY ADJUST THE FLIGHT CONTROL SURFACES TO TURBULENCE IS KNOWN AS WHAT AUGMENTATION?

    • FLIGHT

    • DIRECT

    • CONTROL

    • STABILITY

    Correct Answer
    A. STABILITY
    Explanation
    The use of accelerometers and gyros to smooth out flight control inputs and automatically adjust the flight control surfaces to turbulence is known as stability augmentation.

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  • 24. 

    WHICH STATEMENT ABOUT THE F-16 PRIMARY FLCS IS MOST ACCURATE?

    • THE FLIGHT CONTROL SYSTEM IS QUAD-REDUNDANT

    • THERE ARE FOUR SEPARATE, BUT IDENTICAL, ELECTRONIC FLIGHT CONTROL BRANCHES

    • THE WIRING IS SEPARATED BY BRANCH, TWO SEPARATE BRANCHES ARE LOCATED ON EACH SIDE OF THE AIRCRAFT

    • ALL OF THE ABOVE

    Correct Answer
    A. ALL OF THE ABOVE
    Explanation
    The F-16 Primary FLCS (Flight Control System) is quad-redundant, meaning that there are four separate, but identical, electronic flight control branches. The wiring is separated by branch, with two separate branches located on each side of the aircraft. Therefore, all of the above statements are accurate.

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  • 25. 

    WHAT F-16 CONTROL SURFACES FUNCTION AS AILERONS FOR ROLL CONTROL AND AS FLAPS TO AID AIRCRAFT TAKEOFF AND LANDING?

    • RUDDERS

    • FLAPERONS

    • LEADING EDGE FLAPS

    • HORIZONTAL STABS

    Correct Answer
    A. FLAPERONS
    Explanation
    Flaperons are the correct answer because they serve the dual function of ailerons for roll control and flaps to aid aircraft takeoff and landing. Ailerons are control surfaces on the wings that are used to control the roll or banking motion of the aircraft. Flaps, on the other hand, are extended surfaces on the wings that increase lift and drag, allowing for shorter takeoff and landing distances. Flaperons combine these two functions, providing both roll control and additional lift during takeoff and landing.

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  • 26. 

    WHAT AXIS IS ATT HOLD AUTOPILOT MODE AVAILABLE IN ON THE F-16?

    • YAW ONLY

    • ROLL ONLY

    • YAW AND ROLL

    • PITCH AND ROLL

    Correct Answer
    A. PITCH AND ROLL
    Explanation
    The correct answer is PITCH AND ROLL. In the F-16, the ATT HOLD autopilot mode is available in the pitch and roll axis. This means that the autopilot system can maintain the desired pitch and roll attitudes of the aircraft, allowing the pilot to focus on other tasks or maneuvers. The yaw axis is not included in the ATT HOLD autopilot mode.

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  • 27. 

    HOW ARE CADC ANALOG OUTPUT SIGNALS TRANSFERRED TO THEIR FINAL DESTINATION?

    • VIA THE A MUX

    • VIA THE D MUX

    • VIA AIRCRAFT WING

    • VIA FIBER OPTICS

    Correct Answer
    A. VIA AIRCRAFT WING
  • 28. 

    ROLL IS ACHIEVED BY DEFLECTION OF THE

    • RUDDER

    • FLAPERONS ONLY

    • FLAPERONS AND RUDDER

    • FLAPERONS AND HORIZONTAL STABS

    Correct Answer
    A. FLAPERONS AND HORIZONTAL STABS
    Explanation
    The correct answer is FLAPERONS AND HORIZONTAL STABS. Roll is achieved by the deflection of both the flaperons and the horizontal stabs. Flaperons are control surfaces that combine the functions of both ailerons and flaps, and they are located on the wings. Horizontal stabs, also known as horizontal stabilizers, are fixed surfaces located at the tail of an aircraft. By deflecting both the flaperons and the horizontal stabs, the aircraft can generate a rolling motion around its longitudinal axis.

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  • 29. 

    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 correct answer is to keep the controls from being over controlled or accidentally jarred by the pilot. Artificial feel was incorporated into the flight control system to provide a sense of resistance or feedback to the pilot, which helps them maintain control and prevents them from making sudden or excessive movements that could destabilize the aircraft. This feature ensures smoother and more controlled movement of the flight control surfaces, enhancing stability and safety during flight.

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  • 30. 

    WHICH FLCP SWITCH RESETS THE F-16 FLCS FAULT LIGHT ALERTING FUNCTION?

    • SERVO/ELEC RESET

    • MASTER CAUTION

    • MASTER MODE RESET

    • FLCS CAUTION/RESET

    Correct Answer
    A. FLCS CAUTION/RESET
    Explanation
    The FLCS Caution/Reset switch resets the F-16 FLCS (Flight Control System) Fault Light Alerting Function. This switch is specifically designed to address any faults or issues detected in the FLCS, which is responsible for controlling the aircraft's flight surfaces. By resetting the FLCS Caution/Reset switch, any fault indications or alerts related to the FLCS can be cleared, allowing the pilot to continue operating the aircraft without the distraction or concern of a faulty FLCS.

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  • 31. 

    THE F-16 FLCS SELF TEST CAN BE PERFORMED

    • WHILE 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 FLCS self test can only be performed when weight is on the wheels. This means that the aircraft must be on the ground for the self test to be conducted. The weight on the wheels ensures that the necessary parameters for the self test are met and accurate results can be obtained. If the aircraft is in flight or the weight is off the wheels, the self test cannot be performed as the required conditions are not met.

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  • 32. 

    WHAT FEATURE OF THE F-16 FLCS SMOOTHES OUT TURBULENCE OF THE FLIGHT PATH IN ALL THREE AXES BY INCORPORATING MOTION SENSOR INPUTS INTO THE CONTROL LOGIC?

    • STABILITY AUGMENTATION

    • COMMAND AUGMENTATION

    • AUTOMATIC AOA LIMITING

    • AUTOMATIC LEF POSITIONING

    Correct Answer
    A. STABILITY AUGMENTATION
    Explanation
    The feature of the F-16 FLCS that smooths out turbulence of the flight path in all three axes by incorporating motion sensor inputs into the control logic is stability augmentation. This feature helps to enhance the stability of the aircraft during flight by automatically adjusting the control inputs based on the motion sensor inputs. It ensures that the aircraft remains stable and smooth even in turbulent conditions.

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  • 33. 

    WHAT FUEL TANKS ARE PART OF THE AFT TANK SYSTEM?

    • LEFT INTERNAL WING, LEFT EXTERNAL WING, A 1, AND AFT RESERVOIR

    • RIGHT INTERNAL WING, RIGHT EXTERNAL WING, A 1, AND AFT RESERVOIR

    • LEFT INTERNAL WING, LEFT EXTERNAL WING, F 1, F 2, AND AFT RESERVOIR

    • RIGHT INTERNAL WING, RIGHT EXTERNAL WING, F 1, F 2, AND AFT RESERVOIR

    Correct Answer
    A. LEFT INTERNAL WING, LEFT EXTERNAL WING, A 1, AND AFT RESERVOIR
    Explanation
    The correct answer is LEFT INTERNAL WING, LEFT EXTERNAL WING, A 1, AND AFT RESERVOIR. This answer is correct because it includes all the fuel tanks that are part of the Aft Tank System. The Left Internal Wing and Left External Wing are both part of the system, along with the A 1 tank and the Aft Reservoir. The other options do not include all of these tanks, making them incorrect.

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  • 34. 

    WHATS THE DISPLAY RANGE OF THE ALTIMETERS ALTITUDE DRUM COUNTER?

    • 0 - 50000

    • 0 - 80000

    • -1000 - 50000

    • -1000 - 80000

    Correct Answer
    A. -1000 - 80000
    Explanation
    The display range of the altimeter's altitude drum counter is from -1000 to 80000. This means that the altimeter can display altitudes ranging from -1000 feet to 80000 feet.

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  • 35. 

    WHY WOULD A PILOT ADJUST THE ALTIMETER TO DISPLAY PRESSURE ALTITUDE?

    • TO DISPLAY ALTITUDE ABOVE TERRAIN

    • TO DISPLAY ALTITUDE BELOW SEA LEVEL

    • TO STANDARDIZE AIRCRAFT ALTITUDES FOR LOW ALTITUDE AIR TRAFFIC CONTROL

    • TO STANDARDIZE AIRCRAFT ALTITUDES FOR HIGH ALTITUDE AIR TRAFFIC CONTROL

    Correct Answer
    A. TO STANDARDIZE AIRCRAFT ALTITUDES FOR HIGH ALTITUDE AIR TRAFFIC CONTROL
    Explanation
    A pilot would adjust the altimeter to display pressure altitude in order to standardize aircraft altitudes for high altitude air traffic control. This ensures that all aircraft are using the same reference point for altitude measurements, making it easier for air traffic controllers to manage and separate aircraft at high altitudes. Pressure altitude is calculated by setting the altimeter to a standard atmospheric pressure, which allows for accurate altitude readings regardless of changes in local atmospheric pressure.

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  • 36. 

    WHATS THE FUNCTION OF THE AOA INDEXERS LEVER CONTROL SWITCH?

    • ON/OFF SWITCH

    • SECTOR LIGHT INTENSITY

    • ENABLES AOA LOGIC CIRCUITS

    • ONLY USED DURING TAKEOFF AND LANDING CONFIGURES

    Correct Answer
    A. SECTOR LIGHT INTENSITY
    Explanation
    The function of the AOA indexers lever control switch is to control the intensity of the sector lights. The sector lights are used to provide visual cues to the pilot regarding the aircraft's angle of attack. By adjusting the sector light intensity, the pilot can customize the visibility of these cues based on their preference and the lighting conditions. This switch is not related to enabling AOA logic circuits or specific takeoff and landing configurations.

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  • 37. 

    WHATS 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 when an aircraft is involved in an accident or incident, the CSFDR Type 1 data can be analyzed to determine the cause of the mishap. This data can provide valuable information about the aircraft's performance, systems, and any abnormalities that may have occurred leading up to the mishap. By analyzing this data, investigators can gain insights into what went wrong and take steps to prevent similar incidents in the future.

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  • 38. 

    WHAT GENERATES THE FLOW OF AIR OVER AN AIRCRAFTS WINGS?

    • LIFT

    • THRUST

    • VENTURI

    • POWER PLANT

    Correct Answer
    A. THRUST
    Explanation
    Thrust is the force that propels an aircraft forward, and it is generated by the engines. As the engines produce thrust, the aircraft moves through the air, creating a flow of air over its wings. This flow of air is crucial for generating lift, which is the upward force that allows the aircraft to stay airborne. Therefore, thrust is what generates the flow of air over an aircraft's wings.

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  • 39. 

    THE F-16 ECA USES THE ANGLE OF SIDESLIP DIFFERENTIAL PRESSURE SENSOR SIGNAL TO COMPENSATE FOR

    • BOTH AOA TRANSMITTER PROBES

    • AOA OUTPUT BY THE PNEUMATIC SENSOR ASSEMBLY

    • THE RIGHT AOA TRANSMITTER PROBE

    • THE LEFT AOA TRANSMITTER PROBE

    Correct Answer
    A. AOA OUTPUT BY THE PNEUMATIC SENSOR ASSEMBLY
    Explanation
    The F-16 ECA uses the angle of sideslip differential pressure sensor signal to compensate for the AOA output by the pneumatic sensor assembly. This means that the sensor assembly may provide inaccurate or fluctuating AOA readings, and the angle of sideslip differential pressure sensor signal is used to correct and adjust the AOA output accordingly. This ensures that the aircraft receives accurate and reliable AOA information for proper operation and control.

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  • 40. 

    THE F-16 RATE GYRO ASSEMBLIES CONTAIN PITCH, ROLL, AND YAW RATE GYROS THAT

    • ARE NOT INTERCHANGEABLE

    • 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. This means that the individual rate gyros themselves are not unique or interchangeable, but they acquire their uniqueness when they are connected to the specific wiring configuration of the aircraft. This suggests that the wiring plays a crucial role in determining the functionality and performance of the rate gyros in the F-16 aircraft.

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  • 41. 

    THE F-16 USES THERMISTOR SENSORS TO GENERATE AIR EJECTOR AND FUEL LOW SIGNALS BY DETECTING CHANGES IN SENSOR

    • VOLTAGE

    • CURRENT

    • RESISTANCE

    • CONTINUITY

    Correct Answer
    A. RESISTANCE
    Explanation
    The F-16 uses thermistor sensors to generate air ejector and fuel low signals by detecting changes in resistance. Thermistors are temperature-sensitive resistors that change their resistance with temperature. By monitoring the resistance of the thermistor sensors, the F-16 can detect changes in temperature and use this information to generate signals for air ejector and fuel low conditions.

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  • 42. 

    IF THE LANDING GEAR HANDLE IS UP AND STANDBY GAINS ARE SELECTED, THE F-16 LEADING EDGE FLAPS DRIVE TO

    • -2 DEGREES

    • 0 DEGREES

    • 15 DEGREES

    • 25 DEGREES

    Correct Answer
    A. 0 DEGREES
    Explanation
    When the landing gear handle is up and standby gains are selected, the F-16 leading edge flaps drive to 0 degrees. This means that the leading edge flaps are fully retracted and in their neutral position.

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  • 43. 

    CADC SERIAL DIGITAL DATA WORDS ARE AVAILABLE ON THE

    • A MUX

    • B MUX

    • C MUX

    • D MUX

    Correct Answer
    A. A MUX
  • 44. 

    WHAT PROVIDES THE MEANS OF CONNECTING THE F-16 PNEUMATIC SYSTEM TO THE PSA?

    • PSA MANIFOLD

    • PSA DRAIN ASSEMBLY

    • PSA COVER ASSEMBLY

    • PNEUMATIC SYSTEM LINES

    Correct Answer
    A. PSA MANIFOLD
    Explanation
    The PSA manifold provides the means of connecting the F-16 pneumatic system to the PSA. It acts as a central hub or junction point where the different pneumatic system lines can be connected, allowing for the distribution of air or gases throughout the system. The PSA manifold ensures that the pneumatic system is properly connected and allows for efficient operation and control of the system.

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  • 45. 

    ON F-16, WHAT CONTROL SURFACE CONTROLS PITCH AND ASSISTS IN AIRCRAFT ROLL CONTROL?

    • ECA

    • MMC

    • FLCC

    • FCC

    Correct Answer
    A. FLCC
    Explanation
    The FLCC (Flight Control Computer) is responsible for controlling the pitch and assisting in the roll control of the F-16 aircraft. It receives inputs from the pilot's control stick and processes them to adjust the control surfaces accordingly. The FLCC plays a crucial role in maintaining the aircraft's stability and maneuverability during flight.

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  • 46. 

    WHAT CSFDR TYPE DATA IS DUBBED AS INDIVIDUAL AIRCRAFT TRAKCING DATA?

    • 1

    • 2

    • 3

    • 4

    Correct Answer
    A. 2
  • 47. 

    AT WHAT POINT DO MOST AIRFOILS ENTER A STALL CONDITION?

    • 10

    • 20

    • 30

    • 40

    Correct Answer
    A. 20
    Explanation
    Most airfoils enter a stall condition at a certain angle of attack. When the angle of attack exceeds a critical value, the airflow over the airfoil becomes separated, resulting in a loss of lift and an increase in drag. This is known as a stall condition. The correct answer of 20 suggests that most airfoils enter a stall condition at an angle of attack of 20 degrees.

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  • 48. 

    AIRCRAFT ROLL IS REFERENCED FROM

    • THE NOSE

    • EITHER WINGTIP

    • THE LEFT WINGTIP

    • THE RIGHT WINGTIP

    Correct Answer
    A. EITHER WINGTIP
    Explanation
    Aircraft roll is referenced from either wingtip. This means that when an aircraft rolls, it rotates around its longitudinal axis, which is an imaginary line running from the nose to the tail of the aircraft. The roll can be measured or referenced from either the left wingtip or the right wingtip, depending on the specific aircraft and its design. This allows for accurate measurement and control of the aircraft's roll movement during flight.

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  • 49. 

    WHAT INDIVATOIN IS THERE ON THE F-16 FLCP THAT THERE'S A SECOND ELECTRONIC FAILURE IN A GIVEN AXIS?

    • DUAL FC FAIL LIGHT ILLUMINATES

    • THE LIGHT FOR THE APPLICABLE AXIS WILL ILLUMINATE

    • THE LIGHT FOR THE APPLICABLE AXIS WILL ILLUMINATE ALONG WITH THE FLIGHT CONTROL SYSTEM CAUTION LIGHT

    • THE LIGHT FOR THE APPLICABLE AXIS 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 on the F-16 FLCP, the Dual FC Fail light will illuminate. This indicates that there is a failure in both flight control channels for that axis.

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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
  • Oct 20, 2011
    Quiz Created by
    Robdduarte1

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