Avionics 2a352g Volume 3

Aircraft pitch is referenced from the nose because the nose of an aircraft is the forwardmost part and acts as a reference point for measuring the pitch angle. Pitch refers to the up and down movement of the aircraft's nose in relation to the horizon. By referencing the pitch from the nose, pilots can accurately control the aircraft's attitude and maintain stability during flight.

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.

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.

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.

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.

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.

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.

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.

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.

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.

The principal component of the F-16 flight control system is the FLCC.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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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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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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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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.

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.

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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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.

The correct answer is 60. This means that on F-16s, the speed brake panels open symmetrically to a maximum of 60.