2A852 CDC Volume 5

Leading-edge slats and trailing-edge flaps are used during landings and takeoffs. These devices are deployed to increase the lift generated by the wings at lower speeds, allowing the aircraft to maintain lift and control at slower speeds during these critical phases of flight. The increased lift provided by the slats and flaps helps to reduce the aircraft's stall speed, allowing for safer landings and takeoffs.

The control of the aircraft in the yaw axis is achieved through the use of rudders. The rudders are located on the vertical stabilizer at the tail of the aircraft. By deflecting the rudders, the pilot can change the direction of the aircraft's nose left or right. This is important for maintaining stability and controlling the aircraft during turns or when dealing with crosswinds. The elevators control the aircraft's pitch, the ailerons control the roll, and the spoilers are used to decrease lift and increase drag.

Hydraulic powered actuators are designed to convert hydraulic pressure into mechanical force, allowing them to control the movement of various control surfaces on an aircraft. These control surfaces, such as ailerons, elevators, and rudders, are responsible for maneuvering the aircraft and maintaining stability during flight. By converting hydraulic pressure into controlled movements of these surfaces, hydraulic powered actuators play a crucial role in the overall control and maneuverability of the aircraft.

When the control panel NAV LOC switch is in the ON position, it indicates that the flight control set (FCS) will automatically navigate the aircraft along the selected course. This means that the FCS will use the navigation systems onboard the aircraft to follow the desired flight path, ensuring that the aircraft stays on track and reaches its intended destination. The FCS will make adjustments to the aircraft's heading, altitude, and speed as necessary to maintain the selected course.

The flap position indicator is designed to display the percentage of surface extension. Flaps are used to increase lift and drag during takeoff and landing, and their position can be adjusted to different degrees. The flap position indicator allows pilots to visually monitor the extension of the flaps, ensuring they are set correctly for the desired flight phase.

The electromagnetic pulse (EMP) components are mounted in the flight control augmentation system (FCAS) air data computer (ADC) survivability/vulnerability (S/V) box to filter out undesirable pulses. This means that these components are designed to remove or block any unwanted or harmful pulses that could potentially interfere with the proper functioning of the system. By filtering out these undesirable pulses, the ADC can ensure that it receives and processes only the necessary and accurate signals related to altitude and airspeed.

The copilot's elevator input system is connected to the outboard elevators. This means that the copilot has control over the outboard elevators, which are the elevators located on the outer edges of the aircraft's wings. This allows the copilot to adjust the pitch of the aircraft by moving the outboard elevators up or down. The inboard elevators, on the other hand, are located closer to the center of the aircraft and are controlled by the pilot. The upper and lower rudders are not connected to the copilot's elevator input system and are used for controlling the aircraft's yaw.

Electronic flight control computers can be programmed to prevent stalling, which is an undesirable and dangerous characteristic in an aircraft. Stalling occurs when the airflow over the wings is disrupted, causing a loss of lift and a sudden decrease in altitude. By detecting the conditions that lead to a stall, the flight control computers can automatically adjust the aircraft's control surfaces and engine power to prevent it from happening. This programming ensures that the aircraft remains within safe flight parameters and reduces the risk of accidents.

All analog signals that come into the flight control set processor (FCSP) need to be converted to digital format in order to be processed by the digital system. This conversion allows for easier manipulation, storage, and transmission of the signals, as well as providing better accuracy and reliability in the flight control system. Therefore, the correct answer is digital.

In the flight control set (FCS) system, control surface movement from a neutral position produces a synchro electrical output signal. This signal needs to be processed in order to control the flight. The flight control set processor is responsible for processing this signal and translating it into appropriate control commands for the aircraft. The other options mentioned, such as the status/test panel, control panel, and controller, may have different functions within the FCS system but they do not specifically handle the processing of the synchro electrical output signal. Therefore, the flight control set processor is the correct answer.

The roll command module is responsible for ensuring that the aircraft rolls smoothly into a turn, regardless of the speed at which the turn knob is moved. This module receives the input from the pilot's control inputs and generates the appropriate commands to control the aircraft's roll motion. It ensures that the roll rate and acceleration during the turn are smooth and consistent, providing a comfortable and predictable flying experience for the pilot and passengers.

The continuous built-in-test (BIT) monitors and records errors within each axis of operation while the aircraft is in flight and the flight control set (FCS) is engaged. This means that the BIT system is active and functioning while the aircraft is in motion and the flight control set is being used. This allows for real-time monitoring and detection of any errors or issues that may arise during flight, ensuring the safety and proper functioning of the aircraft's flight control system.

The correct answer is VERIFY because the VERIFY pushbutton switch on the flight control set (FCS) status/test panel (STP) allows personnel to confirm or verify the status or test results without bypassing any reported failures.

The rudder input system incorporates a single cable system that runs from the flight station to the upper and lower rudder servo input quadrants. This means that there is only one cable used for transmitting the rudder inputs, providing a simpler and more efficient system compared to multiple cable systems.

The flap and slat power package receives hydraulic pressure from the number one and number four hydraulic systems.

The flight control set processor is responsible for providing a drive voltage to the flight control set (FCS) servo motor. This component is specifically designed to process and control the flight control system, including the servo motor. It generates the necessary voltage to drive the motor, allowing for precise control and adjustment of the aircraft's flight controls. The other options mentioned, such as the controller, control panel, and status/test panel, may play important roles in the overall functioning of the FCS but do not directly provide the drive voltage to the servo motor.

The yaw damper (SYD) is a system that helps stabilize the aircraft's yaw motion. It does this by applying rudder inputs in response to signals from various sensors. In this case, the correct answer is the yaw angle rate gyro. This sensor measures the rate at which the aircraft is yawing, or rotating around its vertical axis. By using this information, the yaw damper can determine if the aircraft is experiencing any unwanted yaw motion and apply corrective rudder inputs to counteract it. The other options, such as the pitch angle rate gyro or heading rate gyro, are not directly related to the yaw motion of the aircraft.

The left arrow (←) pushbutton switch on the flight control set (FCS) status/test panel (STP) allows personnel to repeat a test. This is because the left arrow is commonly used as a symbol for "previous" or "back," indicating that pressing this button will take the user back to a previous step or action, in this case, repeating the test.

When the flight control set (FCS) mode select switch is switched ON, it sends a 28 VDC engage signal to the flight control set processor. This signal indicates that the FCS mode has been selected and activates the processor to initiate the desired control actions. The engage signal is crucial for the proper functioning of the flight control system, as it allows the processor to receive the necessary input and execute the appropriate commands.

The correct answer is two telescoping ballscrew actuators. These actuators are responsible for extending and retracting the slat surface. The use of two actuators ensures stability and control over the movement of the slat surface. Having only two actuators is sufficient for the task at hand, and there is no need for three actuators or variable slat drive roller carriages.

The mechanical flight control system includes cables, torque tubes, and push-pull tubes, which are all mechanisms used to transmit control inputs from the pilot to the control surfaces of an aircraft. Electrically powered actuators, on the other hand, are not part of the mechanical system as they use electrical power to move the control surfaces.

In case of total hydraulic system failure, some aircraft incorporate flight control systems that automatically revert to servo-tab control. This means that if the hydraulic system fails, the servo-tabs on the aircraft's control surfaces will take over and provide limited control to the pilot. This is important because without hydraulic power, the pilot would not be able to control the aircraft's movements effectively. The servo-tabs help to maintain some level of control and allow the pilot to safely maneuver the aircraft in such situations.

A selsyn position indicating system requires 28 VDC (Volts Direct Current) as the operating power.

The flight control set processor software is responsible for controlling the flight control set tests on the status/test panel (STP). It allows maintenance personnel to initialize and step through these tests. The software processes the inputs from the air data computer software, analog to digital conversion, and flight control set controller software to carry out the necessary tests.

Artificial feel systems are designed to provide pilots with a sense of the aerodynamic forces acting on the aircraft. At higher speeds, the aerodynamic forces are stronger, and therefore, the artificial feel system increases resistance to the flight controls. This increased resistance allows pilots to have a better feel of the aircraft's response and improves their ability to make precise control inputs.

The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned 120 degrees apart. This means that each tap is separated from the other by 120 degrees on the circular resistance winding. This arrangement allows for accurate and precise position indication in the system.

The correct answer is screw drive. Horizontal stabilizer pitch trim console switches use a screw drive mechanism to operate the actuator. This means that the switches control the movement of the actuator by rotating a screw, which in turn moves the stabilizer to adjust the pitch. This type of drive mechanism is commonly used in aircraft systems for its precision and reliability.

The flight control set (FCS) control panel LOC ARM/CAP and G/S ARM/CAP indicators are controlled by the flight control set processor. This processor is responsible for receiving and processing signals related to the localizer (LOC) and glide slope (G/S) modes of the aircraft's flight control system. It ensures that the indicators accurately display the status of these modes, allowing the pilot to monitor and control the aircraft's approach and landing.

The pilot can override the flight control augmentation system (FCAS) inputs by applying rudder pedal force. This means that the pilot can manually control the rudder by exerting force on the rudder pedals, allowing them to override any automated inputs from the FCAS. This gives the pilot direct control over the aircraft's rudder movement, providing them with the ability to make adjustments or corrections as needed during flight.

The pitch trim actuator screw drive and nut drive receive hydraulic power from two hydraulic systems operating at 3000 pounds per square inch (PSI). This high pressure allows for efficient and reliable operation of the pitch trim actuator, ensuring precise control of the aircraft's pitch trim. The use of two hydraulic systems adds redundancy and enhances safety, as the failure of one system would still allow the other system to provide power to the actuator.

The pilot's elevator input system is connected to the inboard elevators. This means that when the pilot moves the control input, it will directly affect the movement of the inboard elevators. The inboard elevators are the control surfaces located closer to the center of the aircraft, and they play a crucial role in controlling the pitch of the aircraft. By connecting the pilot's input system to the inboard elevators, the pilot has direct control over the pitch of the aircraft.

The flight control set (FCS) uses one servo motor to move the ailerons and one to move the elevators. The ailerons are control surfaces on the wings that help control the roll of the aircraft, while the elevators are control surfaces on the horizontal stabilizer that help control the pitch of the aircraft. The rudders are control surfaces on the vertical stabilizer that help control the yaw of the aircraft, and the spoilers are used to disrupt the airflow over the wings and reduce lift. Therefore, the correct answer is elevators.

The secondary goal of the flight control set continuous built-in-test (CBIT) is to isolate failures to a particular line replaceable unit (LRU) and store the information in the flight control set processor non-volatile memory. This means that the CBIT is designed to identify and localize any failures that occur within the flight control set, specifically to a specific LRU. The information about these failures is then stored in the flight control set processor's non-volatile memory, which ensures that it is retained even when power is lost.

The correct answer is gear train. In the horizontal stabilizer pitch trim system, the hydraulic motor torque is transferred to the nut and screw drives through a gear train. A gear train is a system of gears that transmit torque and motion from one part of a machine to another. In this case, the gear train is responsible for transferring the torque from the hydraulic motor to the nut and screw drives, allowing for the adjustment of the pitch trim on the horizontal stabilizer.

The flight control set processor provides all switch holding voltages to the flight control set (FCS) control panel. This component is responsible for regulating and supplying the necessary voltages to ensure proper functioning of the switches on the control panel. It plays a crucial role in the overall operation and control of the flight control system.

The primary function of the flight control set (FCS) roll loop is to maintain the aircraft at a wings level attitude while in heading hold mode. In this mode, the FCS roll loop continuously adjusts the ailerons to counteract any roll deviations and keep the aircraft's wings level. This is essential for maintaining a stable flight and ensuring that the aircraft maintains its intended heading. The FCS roll loop does not directly control altitude, glide slope, or Mach hold modes, making heading hold mode the correct answer.

Synchro position indicating systems convert mechanical shaft angles to electrical signals. This means that the system takes the position of a mechanical shaft and converts it into an electrical signal. This conversion allows for the transmission and processing of the shaft position data in an electrical form, which can be more easily utilized and interpreted by other electronic systems.

The flight control set (FCS) status/test panel (STP) is responsible for providing personnel with an interface to the flight control set processor. This means that the panel allows personnel to interact with and monitor the flight control set processor, which is a crucial component in the aircraft's flight control system. It is responsible for processing and executing commands from the flight control set control panel, ensuring the proper functioning of the flight control system.

The correct answer is Automatic Direction Finder (ADF). In the flight control set (FCS) navigation/localizer (NAV/LOC) mode, the navigation signals that can be selected include Instrument Landing System (ILS), Tactical Air Navigation (TACAN), and Flight Management System (FMS). However, Automatic Direction Finder (ADF) is not one of the navigation signals that can be selected in this mode. ADF is a radio navigation system that determines the direction of a radio signal, but it is not typically used for precision approach and landing guidance like ILS, TACAN, and FMS.

The hydraulic pressure to the rudder power control unit must exceed 1000 pounds per square inch (PSI) in order for the flight control augmentation system (FCAS) to be operative.

The limit switches are responsible for cutting off electrical power to the screw drive unit when the horizontal stabilizer reaches certain angles. In this case, with the flaps up, the limit switches will cut off power when the aircraft is at 1.5° nose down or 6.0° nose up. This means that if the horizontal stabilizer reaches either of these angles, the power to the screw drive unit will be cut off, ensuring that the stabilizer does not move any further in that direction.

The engine fail assist system (EFAS) provides the greatest rudder assistance when the airspeed is below 160 knots indicated airspeed (KIAS). This means that at lower speeds, the EFAS is more effective in assisting with rudder control. At higher speeds, the system may still provide some assistance, but it is not as effective as at lower speeds.

The correct answer is the Trim direction solenoid. The simultaneous actuation of the horizontal stabilizer trim control wheel switches energizes the Trim direction solenoid. This solenoid is responsible for adjusting the trim of the aircraft's horizontal stabilizer, which helps to maintain the desired pitch attitude of the aircraft.

The engine fail assist system (EFAS) is engaged during all takeoff and landing phases of flight when the airspeed is less than 200 knots indicated airspeed (KIAS). This means that the EFAS is activated when the aircraft is flying at a slower speed during critical phases of flight. The system is designed to provide assistance in the event of an engine failure, helping the pilot maintain control and safely land the aircraft.

The prerequisite for entering the flight control set (FCS) localizer (LOC) capture mode is a valid radio altimeter signal. This signal is necessary for the aircraft to accurately measure its altitude above the ground and determine when it is at the correct altitude to capture the localizer signal. Without a valid radio altimeter signal, the aircraft would not be able to accurately capture the localizer and maintain its course during the approach.

The degree rotation of the flight control set (FCS) controller thumbwheels is 360. This means that the thumbwheels can be rotated a full 360 degrees, allowing for precise control and adjustment of the flight controls.

When the turn knob is returned to the detent position, the flight control set (FCS) will not enter the flight management system (FMS) steering mode. This means that the FCS will not engage the FMS steering mode until the turn knob is no longer in the detent position. This indicates that the aircraft is no longer in a turning maneuver and is ready to enter the FMS steering mode.

The flight control set control panel is the component that enables the flight crew to engage and disengage the flight control set (FCS). This panel allows the crew to control and manage the various functions and settings of the FCS, such as activating or deactivating certain control modes or adjusting control parameters. It serves as the interface between the crew and the FCS, providing them with the necessary controls and indicators to effectively operate and monitor the aircraft's flight controls.

When the control panel ROLL axis switch is engaged, the flight control set (FCS) will hold the existing heading of the aircraft. This means that regardless of any external factors or disturbances, the FCS will make adjustments to ensure that the aircraft maintains its current heading. This is important for maintaining the desired direction of flight and ensuring stability during maneuvers.

The servo drum and bracket provide the only mechanical connection from the flight control set (FCS) servo motor to the aircraft control cables. This connection allows for the transmission of mechanical force from the servo motor to the control cables, enabling the pilot to control the aircraft's movements. The horizontal position sensor, jackscrew assembly, and trim actuator are not directly involved in this mechanical connection.