2A374 : F-15 Flight Control System and Radar! Hardest Trivia Quiz

The correct answer is "CAUTION." In the given question, it is stated that the light will come on or flash when moisture is detected inside the video tape recorder. The word "CAUTION" is commonly used to indicate a warning or potential danger. Therefore, it is logical to assume that the "CAUTION" light would be designed to alert the user about the presence of moisture, indicating a need for caution or potential damage to the system.

The fuel flow transmitter is the component that provides a synchro signal to the engine monitor display (EMD) to drive the liquid crystal display (LCD) window FF PPH (fuel flow pounds per hour). This means that the fuel flow transmitter is responsible for measuring and transmitting the information about the fuel flow rate to the EMD, which then displays it on the LCD window. The other options, avionics interface unit no. 1, engine diagnostic unit (EDU), and advanced display core processor (ADCP), are not directly related to providing the synchro signal for the fuel flow display.

The pilot utilizes the Precision velocity update mode of the F-15C/D APG-70 radar before making a bomb run. This mode provides the pilot with accurate and precise velocity information of the target, allowing for more precise targeting and delivery of the bombs.

The sensor control panel would be used to zeroize the F-15E fighter data link (FDL) crypto codes.

The F-15E pitch control augmentation system (CAS) will disengage when the yaw rate reaches 41.5 degrees per second.

The F-15E APG-70 air-to-ground (A/G) radar mode that provides a slant range measurement used for target altitude determination, target designation, or position updates is the air-to-ground ranging mode. This mode allows the radar to measure the distance between the aircraft and the target, which is essential for determining the target's altitude and accurately designating it for attack or updating its position. The other modes mentioned, such as real beam map mode, high-resolution map mode, and air-to-ground beacon mode, do not specifically provide slant range measurements for these purposes.

The mode select assembly is used to control the flow of hydraulic fluid to the pitch and roll channel assembly (PRCA) in the F-15. It is responsible for selecting and adjusting the different flight modes of the aircraft, which in turn affects the hydraulic fluid flow to the PRCA. The other options, such as the roll ratio controller, lateral feel trim actuator, and aileron rudder interconnect, do not directly control the flow of hydraulic fluid to the PRCA.

The input data converter (IDC) section of the F-15E air data processor (ADP) is responsible for conditioning and converting all received inputs to the ADP. It takes in the raw data from various sensors and sources, such as airspeed, altitude, temperature, and pressure, and processes them into a format that can be understood and used by the ADP. This conversion ensures that the ADP receives accurate and reliable data for its calculations and operations.

The JTIDS mode control panel would be used to zeroize the F-15C/D fighter data link (FDL) crypto code.

The band 1 and band 2 amplifiers use 2 traveling wave tube (TWT) circuits to produce leveled high power radio frequency (RF) signals.

The F-15 directional feel trim actuator position is supplied to the limit level detectors by the Linear Variable Differential Transducer (LVDT) A. This is done in order to prevent the actuator from driving beyond its limit. The LVDT A is a type of sensor that measures linear displacement and converts it into an electrical signal. By providing this information to the limit level detectors, the LVDT A ensures that the actuator does not exceed its designated range of motion.

The correct answer is the data processor. The data processor is responsible for storing the radar operational flight program (OFP). It processes and analyzes the data received from the radar system, and it also stores and retrieves the OFP, which contains the instructions and algorithms for the radar's operation. The data processor plays a crucial role in the overall functioning of the radar system by managing and storing the necessary software for its operation.

The correct answer is the Rudder control breakout assembly. This component is responsible for transmitting the input force from the aileron rudder interconnect (ARI) into two separate push-pull cables. It serves as a connection point between the ARI and the cables, allowing for the control and movement of the rudder. The other options, such as the rudder actuator, rudder limiter actuator, and directional feel trim actuator, are not specifically designed to perform this function.

The F-15E flight control computer (FCC) is responsible for producing the output discrete signals to control the automatic speed brake retract. This means that the FCC is responsible for activating the mechanism that retracts the speed brake automatically. The other options mentioned - roll engage command, pitch engage command, and trim actuator position signals - are not related to the control of the automatic speed brake retract.

The F-15 air intake system has four variable inlet ramps. These ramps are adjustable components that control the airflow into the engine, allowing for optimal performance at different speeds and altitudes. By adjusting the position of these ramps, the aircraft can maintain a consistent and efficient airflow into the engine, improving fuel efficiency and overall performance.

The longitudinal mass balance is used to help neutralize the effect of acceleration on the control stick during maneuvers in an F-15 aircraft. This component helps to counteract the forces experienced by the pilot when the aircraft accelerates or decelerates, ensuring that the control stick remains stable and easy to manipulate. By incorporating a mass balance system, the F-15 can maintain control and stability throughout various maneuvers, improving the overall performance of the aircraft.

The VME64 main and essential busses within the advanced display core processor (ADCP) on the F-15E aircraft are responsible for servicing the multipurpose display processing and central computer processing functions. These busses provide the necessary communication pathways for data transfer and control between the various components of the ADCP system.

The directional feel trim actuator contains centering springs that provide an artificial feel to keep the rudder pedals centered. This means that when the pilot releases pressure on the rudder pedals, the centering springs will automatically return the pedals to their neutral position. This helps the pilot maintain control and stability during flight. The other options, such as the rudder actuator, rudder limiter actuator, and directional control breakout assembly, do not specifically mention centering springs or the function of keeping the rudder pedals centered. Therefore, the correct answer is the directional feel trim actuator.

The output data converter on the F-15E air data processor (ADP) is responsible for conditioning the ADP signals in order to interface with the indicators and other onboard systems. This converter takes the raw data from the ADP and converts it into a format that can be easily understood and utilized by the indicators and systems. It ensures that the signals are properly translated and compatible with the various components of the aircraft, allowing for accurate and efficient communication between the ADP and the other systems.

The Digital Map Processor (DMP) component of the F-15E digital map system (DMS) uses present position information and scale select information to determine which map to display. The DMP processes the data and selects the appropriate map based on the aircraft's current position and the desired scale. It then displays the selected map on the aircraft's display system, providing the pilot with accurate and up-to-date navigation information. The Mission Cartridge (MC) and Theater Cartridge (TC) are not directly involved in determining which map to display, and the Advanced Display Core Processor (ADCP) is responsible for processing and displaying sensor video data, not map information.

The band 3 RF amplifier is the component that performs the final amplification of the band 3 oscillator signals in a traveling wave tube (TWT) system. The TWT system uses the band 3 RF amplifier to boost the power of the oscillator signals before they are transmitted. The magic tee is not responsible for the final amplification, but rather for signal splitting and combining. The preamplifier is used to amplify weak signals before they are sent to the main amplifier. The summing network is used to combine multiple signals into a single output.

The correct answer is RGH. The question is asking about the F-15C/D APG-70 radar air-to-air (A/A) search mode that uses the "intermediate" pulse repetition frequency (PRF) to detect targets in intermediate-range and short-range. The RGH mode is specifically designed for this purpose, allowing the radar to detect and track targets at shorter distances.

The F-15 APG-63 radar system uses a programmable signal processor to process clutter rejection. This component is responsible for analyzing the radar signals and distinguishing between clutter (unwanted signals) and actual targets. By programming the signal processor, the system can effectively filter out clutter and focus on detecting and tracking real targets, improving the radar's performance and accuracy. The data processor, analog processor, and RF oscillator are not directly involved in clutter rejection.

A low confidence target is displayed as a diamond on the F-15 air-to-air interrogator (AAI) display. The diamond symbol indicates that the tracking system has a lower level of confidence in the target's identification or classification. This could be due to factors such as poor signal quality, limited data, or ambiguity in the target's characteristics. The diamond symbol helps the operator to be aware that there is a higher degree of uncertainty associated with that particular target.

The F-15A through D automatic flight control system (AFCS) accelerometer assembly consists of a total of four accelerometers.

The correct answer is ± 10° symmetrical movement. This means that the pitch control augmentation system (CAS) on an F-15 can add or subtract up to 10 degrees of movement to the manual flight controls in a symmetrical manner. This allows for greater control and maneuverability of the aircraft in pitch movements.

The correct answer is "Yaw CAS engaged." The F-15 roll control augmentation system requires the yaw control augmentation system to be engaged in order to function properly. This means that the system relies on the yaw CAS being activated in order to provide the necessary control and stability during roll maneuvers. The pitch CAS being engaged or disengaged does not directly affect the roll control augmentation system.

The F-15 diffuser ramp actuator's Mach blocking valve solenoid is designed to prevent the actuator from retracting when the aircraft speed exceeds Mach 1.5. This is because at high speeds, the diffuser ramp needs to remain extended in order to maintain optimal airflow and prevent turbulence. By blocking the actuator from retracting, the solenoid ensures that the diffuser ramp stays in the correct position for efficient aerodynamics and safe operation of the aircraft.

The AIU1A functions as the primary bus controller for the F-15E up-front controller (UFC). This means that it is responsible for managing and controlling the communication and data transfer between various avionics systems and components within the aircraft. The UFC relies on the AIU1A to effectively communicate and exchange information with other systems, ensuring smooth operation and coordination of the aircraft's avionics functions.

The receiver-exciter component of the F-15E APG-70 radar set is responsible for establishing the basic operating radio frequency (RF) for the transmitter. It receives incoming signals, amplifies them, and then modulates them to the desired frequency for transmission. The power supply provides electrical power to the radar set, the radar data processor processes and analyzes the received signals, and the analog signal converter converts analog signals into digital format. However, none of these components specifically establish the basic operating RF for the transmitter.

The correct answer is the Longitudinal feel trim actuator (LFTA). This component has built-in centering springs that resist stick movement, providing the pilot with a stick feel force. This allows the pilot to have a better sense of control and feedback when maneuvering the aircraft in pitch. The other options mentioned, such as the PITCH RATIO switch, Pitch ratio controller, and Longitudinal mass balance, do not have the same function of providing stick feel force to the pilot.

During band 3 operation, the aft amplifier pulse radio frequency (RF) signal is sent to the pulse element of the aft antenna. This means that the signal is specifically directed to the component of the aft antenna that is responsible for generating pulses of radio frequency energy.

The pitch control augmentation system (CAS) gain is reduced to 13 degrees to implement the stall inhibit function. This means that when the angle-of-attack (AOA) reaches a certain threshold, the CAS will automatically adjust the pitch control to prevent the aircraft from stalling. The specific value of 13 degrees is determined based on the aircraft's design and performance characteristics, ensuring a safe and efficient operation during critical flight conditions.

The F-15 #1 and #2 modular relay panels provide logic signals to the pitch computer for monitoring the landing gear and flap position, as well as the weight off wheels condition. These signals are important for the pitch computer to accurately calculate and adjust the aircraft's pitch control based on the current configuration and weight distribution. The other options mentioned in the question, such as CAS engage, speed brake, and AOA signals, are not directly related to the functions of the relay panels in providing logic signals to the pitch computer.

The correct answer is the Pitch ratio controller. The Pitch ratio controller is a component of the F-15 longitudinal flight control subsystem. It contains an airspeed scheduling valve, a Mach factor computer, and an aileron rudder interconnect (ARI) Mach valve. This controller is responsible for adjusting the pitch ratio of the aircraft based on its speed and Mach number, ensuring proper control and stability during flight.

When impact pressure is present, the pointer of the F-15 standby airspeed indicator moves. Impact pressure is the pressure created by the airflow impacting the aircraft's pitot tube. This pressure is used to measure airspeed and is crucial for the accurate functioning of the airspeed indicator. Therefore, when impact pressure is present, the pointer on the standby airspeed indicator moves.

The rate gyro assembly is responsible for providing pitch rate signals that are proportional to the angular motion about the pitch axis to the pitch computer. This assembly measures the rate of change of pitch, allowing the pitch computer to accurately control the aircraft's pitch movement. The stick force sensor measures the force applied to the control stick, the accelerometer assembly measures the acceleration of the aircraft, and the control surface actuator LVDT is responsible for providing position feedback for the control surface actuators.

The acceleration indicator is designed to provide a visual indication of the g-forces imposed on the cockpit of the aircraft during climbs, dives, and turns. It is specifically designed to show g-forces within the range of -5 to +10, allowing the pilot to monitor and adjust their maneuvers accordingly. The accelerometer, counter display unit, and counter accelerometer unit do not have the same function as the acceleration indicator in providing this specific visual indication of g-forces.

The flight director function handles the processing of TACAN, NAV, and ILS steer mode for display on the HSI. The flight director provides guidance to the pilot by indicating the desired aircraft attitude and flight path. It uses inputs from various navigation systems, including TACAN, NAV, and ILS, to calculate and display the appropriate steer commands on the HSI. This helps the pilot to accurately navigate and fly the aircraft according to the desired flight path.

The advanced display core processor (ADCP) on the F-15E aircraft communicates with the internal countermeasures set (ICMS) over the avionics 1553 MUX bus 5A/5B. The ICMS is responsible for detecting and countering threats to the aircraft, such as enemy radar and missiles. By communicating with the ICMS, the ADCP can receive information about potential threats and display it on the aircraft's advanced display system, allowing the pilot to take appropriate defensive actions.

The engine monitor display (EMD) on the F-15E sends its serial data to the Avionics Interface Unit (AIU) 2.

The maximum amount of rudder travel the F-15E yaw control augmentation system (CAS) can add or subtract is 15°.

The Advanced Display Core Processor (ADCP) determines if a low oil pressure condition exists on the F-15E. This component is responsible for processing and displaying information related to the aircraft's systems. It receives data from various sensors, including those monitoring oil pressure, and analyzes it to determine if there is a low oil pressure condition. Based on this analysis, the ADCP can alert the pilot and initiate appropriate actions to address the issue.

The F-15E radar data processor supplies an air-to-air interrogator (AAI) system interrogate command to the programmable signal processor when the radar mode is compatible. The programmable signal processor is responsible for processing and analyzing the radar data received from the antenna array. It controls the radar's operation and performs various signal processing tasks, such as filtering, target detection, and tracking. Therefore, it is the component that receives the interrogate command and carries out the necessary actions to fulfill the radar mode requirements.

The preamplifier receives four radio frequency (RF) inputs and one agile tuning unit 1/built-in test (BIT) RF signal input from the high band receiver and band 3 aft RF amplifier.

The correct answer is the data processor. The data processor is responsible for sending antenna positioning commands to the servo electronics in the power supply of the F-15 APG-63 radar system. It processes the data received from the radar system and determines the appropriate positioning commands to ensure accurate and efficient radar operation. The data processor plays a crucial role in controlling the radar antenna's movement and positioning, allowing the radar system to effectively track and detect targets.

The Pitch Trim Controller (PTC) is the correct answer because it automatically compensates for trim changes caused by accelerating from subsonic to supersonic flight. It adjusts the pitch trim to maintain the desired aircraft attitude and stability during this transition. The other options, such as the Mechanical Mixer, Pitch Ratio Controller (PRC), and Longitudinal Feel Trim Actuator (FTA), do not specifically address the compensation for trim changes in this specific flight scenario.

The roll ratio controller is responsible for adjusting the lateral control of the F-15 based on various factors such as airspeed, longitudinal position, landing gear position, and yaw rate. It ensures that the aircraft maintains stability and control during flight by increasing or decreasing the lateral control as needed. The other options mentioned, such as the mode select assembly, lateral feel trim actuator, and aileron rudder interconnect, do not specifically address the mentioned variations in airspeed, longitudinal position, landing gear position, and yaw rate.

The central computer (CC) is responsible for sending fighter data link (FDL) symbology positioning information to the programmable signal data processor (PSDP). This means that the CC is the component that handles the transmission of this data to the PSDP, allowing for the processing and interpretation of the symbology positioning information.

The programmable signal data processor is the component of the F-15 overload warning system (OWS) that processes the OWS information displayed on the multiple indicator control panel (MICP), head-up display (HUD), and is heard in the headset. It is responsible for receiving and analyzing the data from various sensors and systems, and then converting it into the appropriate format for display and audio output. This processor plays a crucial role in providing pilots with real-time information about potential overloads and warnings during flight.