2A553B Vol. 3 Pretest

The master caution light can be extinguished or reset by depressing it momentarily. This means that simply pressing the light for a short period of time will turn it off or reset it. This action does not require any additional steps such as pressing it several times, resetting a circuit breaker, or using a light reset switch.

The vertical velocity indicator helps the pilot maintain a specific rate of climb or dive. This instrument provides information on the rate at which the aircraft is ascending or descending, allowing the pilot to adjust the aircraft's pitch and throttle settings to achieve the desired climb or descent rate. The altimeter measures the aircraft's altitude, the machmeter indicates the aircraft's speed relative to the speed of sound, and true A/S refers to true airspeed, which is the aircraft's speed relative to the air mass in which it is flying. However, none of these indicators specifically assist in maintaining a specific rate of climb or dive like the vertical velocity indicator does.

MIL-STD-1553B is the controlling protocol used by an optical data bus for high-speed message transfer. This protocol is widely used in military and aerospace applications for reliable and efficient communication between different devices. It provides a standardized method for data transmission, synchronization, error detection, and fault isolation. The use of MIL-STD-1553B ensures compatibility and interoperability between various systems and allows for seamless integration of different components in a network.

When the bus controller detects a transmission error while communicating with a RT on the Military Standard 1553B data bus, the bus controller will retransmit the command several times in an attempt to establish successful communication. If the retransmissions are unsuccessful, the bus controller will then try the backup data bus as an alternative means of communication. This process allows for multiple attempts to establish contact with the RT and ensures that communication is maintained through the use of the backup data bus if necessary.

The correct answer is "Installation error." This type of error is caused by the location and manner in which a pitot tube is installed. The installation of the pitot tube is crucial for accurate measurements of airspeed, and if it is not installed correctly, it can lead to inaccurate readings. This error is specifically related to the installation process and does not involve any issues with the instrument itself or other factors such as air density or angle of attack.

The standard datum plane is a theoretical plane where the atmospheric pressure is 29.92" Hg and the temperature is +15 degrees C. This is because the standard atmospheric pressure at sea level is generally considered to be 29.92 inches of mercury (Hg), and the standard temperature is +15 degrees Celsius. These values are used as a reference point for various calculations and measurements in aviation and meteorology.

The ground proximity warning system is active between altitudes of 50 - 2,450 feet. This means that the system will provide warnings and alerts to the pilot when the aircraft is flying at these altitudes and is in danger of colliding with the ground. Altitudes below 50 feet and above 2,450 feet are not covered by the ground proximity warning system, so no warnings or alerts will be provided at these altitudes.

The symbol generator unit receives compass, A/S (airspeed), roll/pitch, and radio altitude information via the system electronic unit. This unit is responsible for generating and displaying the video symbology on the display system. It takes the input data and converts it into graphical representations such as aircraft symbols, altitude indicators, and other navigational information.

The correct answer is the Pilot's SCADC self-test switch. This switch, when activated, causes the No. 1 SCADC (Stability and Control Augmentation System Digital Computer) to output fixed values of altitude, vertical speed, mach, airspeed, and true airspeed. This allows the pilot to test the SCADC system and ensure its proper functioning. The Copilot's SCADC self-test switch and test disconnect do not have the same function.

The color weather radar system is capable of detecting airborne targets. It uses radar technology to detect and display weather conditions, including the presence of other aircraft in the vicinity. This system helps pilots to avoid potential collisions by providing them with real-time information about the location and movement of nearby airborne targets. The other options, such as the automatic flight display system, global positioning system, and inertial navigation system, do not have the capability to detect airborne targets.

The correct answer is the global positioning system. The global positioning system (GPS) is a satellite-based navigation system that uses multiple satellites to calculate the aircraft's present longitude and latitude. It provides accurate and real-time positioning information, allowing pilots to navigate and track their aircraft's location during flight. The automatic flight display system, color weather radar system, and inertial navigation system do not specifically use multiple satellites to calculate the aircraft's present longitude and latitude.

An active on-board collision system has several advantages, such as working anywhere in the world, having an on-board system that queries local transponders for replies, and creating images of the local traffic for display on the multifunction displays. However, it does not rely on local radar to generate transponder replies. This means that the system does not depend on the radar of the surrounding area to receive responses from other aircraft's transponders. Instead, it actively queries the transponders directly, allowing for more accurate and reliable collision avoidance capabilities.

According to the principles applicable to the A/S indicator, as altitude increases, the maximum allowable airspeed decreases. This is because as altitude increases, the air density decreases, resulting in less air molecules to provide lift and support the aircraft. Therefore, the maximum allowable airspeed must decrease to maintain safe and stable flight conditions.

To make an A/S (airspeed) indicator display true A/S, the errors that need to be corrected are altitude and temperature. Both altitude and temperature can affect the accuracy of the airspeed reading. Altitude affects air density, which in turn affects the airspeed measurement. Temperature also affects air density, as warmer air is less dense than colder air. Therefore, to ensure an accurate airspeed reading, both altitude and temperature errors need to be corrected.

Green caution/advisory warning lights indicate actuation and normal operation of aircraft equipment. These lights are used to provide information about the status of various systems and equipment on the aircraft. Green lights typically indicate that a system is functioning properly or that a specific action has been completed successfully. This helps the pilot and crew to monitor the aircraft's performance and ensure everything is operating as expected.

Static pressure is the pressure exerted by a fluid at rest. In the context of this question, it refers to the air pressure surrounding an aircraft. At low altitudes, the air density is higher, resulting in a greater number of air molecules per unit volume, and therefore a greater static pressure. As the altitude increases, the air density decreases, leading to a lower number of air molecules and a lower static pressure. Therefore, static pressure is greater at low altitudes and less at higher altitudes.

The correct answer is "instrument error." In this context, an instrument error refers to a mechanical error within the A/S (airspeed) indicator. This error could be caused by various factors such as a malfunctioning component or incorrect calibration, leading to inaccurate readings or indications of airspeed. It is important to identify and rectify instrument errors to ensure the safety and reliability of the aircraft's systems.

The primary difference between indicated A/S (airspeed) and true A/S is the density error. Indicated A/S is the airspeed value displayed on the aircraft's instrument panel, while true A/S is the actual airspeed of the aircraft in relation to the surrounding air. Density error refers to the variation in air density due to factors such as altitude, temperature, and humidity. This variation affects the accuracy of the indicated A/S, causing a difference between the indicated and true airspeed values.

The correct answer is the barometric scale on the front of the indicator. This is because density is affected by atmospheric pressure, and the barometric scale on the front of the indicator allows for adjustment of the pressure reading. By adjusting the barometric scale on the front, the correct density can be obtained. Adjusting the barometric scale on the back or the high-pressure scale would not have any impact on correcting the density error.

The HUD (Head-Up Display) master control switch has four positions: OFF, NIGHT, AUTO, and DAY. The OFF position completely turns off the HUD display. The NIGHT position adjusts the brightness of the display for optimal visibility during nighttime conditions. The AUTO position allows the HUD to automatically adjust its brightness based on the ambient lighting conditions. The DAY position sets the display to a standard brightness level for daytime use.

To view data on the alphanumeric display of the CITS computer display panel, the DIS mode switch must be in the "CMPTR" position. This suggests that the alphanumeric display is connected to the computer and will only show data when the switch is set to the "CMPTR" position. The other options, "STIM," "KYBD," and "START," do not indicate a connection to the computer or the ability to display data on the alphanumeric display.

The data loader system is composed of a data card and a data receptacle. This implies that the system requires both a data card, which is likely used for storing and transferring data, and a data receptacle, which is likely used for connecting the data card to the system or device. The other options, such as a data cable and data recorder, do not align with the given information about the system's components.

The correct answer is "Provides recommendations to the pilot for aircraft maneuvers." This is not a function of the TCAS traffic advisory system. The TCAS system is designed to provide alerts and warnings to the aircrew regarding potential traffic conflicts, but it does not provide specific recommendations for aircraft maneuvers. The aircrew is responsible for making decisions and executing maneuvers based on the information provided by the TCAS system.

The correct answer is 20 bits long with a 3-bit sync character, 16 information bits, and one parity bit. This means that each type of word used on the Military Standard 1553B data bus consists of a total of 20 bits. The word starts with a 3-bit sync character, followed by 16 information bits, and ends with one parity bit. This format allows for the synchronization and error checking of the data transmitted on the bus.

not-available-via-ai

During a dive, the aircraft is descending rapidly, causing an increase in airspeed. As the airspeed increases, the static pressure on the outside of the diaphragm of the vertical velocity indicator decreases. However, the static pressure inside the diaphragm remains relatively constant, resulting in a greater pressure differential and causing the static pressure inside the diaphragm to be greater than on the outside. This allows the vertical velocity indicator to accurately display the rate of descent during a dive.

The Military Standard 1553B data bus is capable of transferring data between a maximum of 32 avionics units. This means that the data bus can facilitate communication and data transfer between up to 32 different avionics devices or systems.

The tape capacity of the digital flight data recorder system is 25 hours. This means that the system is capable of recording and storing data for a continuous period of 25 hours. This is important for flight data recorders as they need to capture and store a large amount of data during a flight, including parameters such as altitude, airspeed, and engine performance. Having a capacity of 25 hours ensures that the system can capture data for long-haul flights and provide valuable information for accident investigation and analysis.

The correct answer is "Acquisition." The acquisition system unit samples aircraft system data and converts it into digital form. This process allows for the recording and analysis of flight data, providing valuable information for maintenance and investigation purposes. The acquisition system is an essential component of the digital flight data recorder system.

To locate a CMC autoflow chart in the system integration manual, you would use the CMC-to-Autoflow Cross-Reference List. This list provides a reference to the specific page or entry point where the autoflow chart can be found. It serves as a guide to quickly navigate through the manual and locate the desired information related to CMC autoflow charts.

The correct answer is 50-600 knots. This indicates that the A/S tape on the Mach-A/S indicator can display speeds ranging from 50 knots to 600 knots.

Each total air temperature probe contains two variable resistance-type sensing elements. This means that the probe has two sensors that measure the temperature by varying their resistance based on the surrounding air temperature. The use of resistance-type sensing elements allows for accurate temperature measurements in different conditions.

The correct answer is 30 degrees horizontal and 24 degrees vertical. This means that the heads-up displays (HUDs) are adjusted to show a wide field of view of 30 degrees horizontally and 24 degrees vertically. This allows the HUDs to display a large amount of information to the user, covering a wide area in their field of vision.

The fault indicators on the front of the flight data acquisition unit are solid white when a fault condition exists. This indicates that there is an issue or malfunction with the unit. The color white is commonly used to signify a fault or error in various systems and devices.

The stall prevention system control panel test switch is used to activate the shaker. In order to activate the shaker, the angle-of-attack (AOA) vane needs to be manually moved. Therefore, the correct answer is angle-of-attack (AOA) vane.

The control display unit (CDU) provides the primary processing and interface functions for the flight management system. It allows pilots to input and manage flight plans, navigate through different pages and menus, and monitor various aircraft systems. The CDU acts as the central control panel for the flight management system, enabling pilots to interact with and control the system efficiently during flight operations.

The stall prevention computer produces a shaker signal if the aircraft angle-of-attack (AOA) and the permissible AOA are equal. This means that when the actual AOA of the aircraft matches the maximum allowable AOA, the stall prevention computer will activate the shaker signal to warn the pilot of an imminent stall. If the AOA and permissible AOA differ by any amount, the shaker signal will not be activated.

The correct answer is static pressure. In an A/S (airspeed) indicator, the sensing elements are surrounded by static pressure. Static pressure is the pressure exerted by the surrounding air and is used to measure the aircraft's altitude and airspeed. Pitot pressure, on the other hand, is the pressure exerted by the airflow as the aircraft moves through the air and is used to measure the aircraft's airspeed. Engine pressure and methyl chloride gas are not relevant to the functioning of the A/S indicator.

Symbols generated by the traffic alert and collision avoidance system change in shape and color to represent increasing levels of urgency or threat. This means that as the urgency or threat level increases, the symbols will not only change in color but also in shape. The combination of shape and color provides a clear and easily understandable visual representation of the urgency or threat level to the pilot or driver.

Mode 1, Excessive Sink Rate is always active when the aircraft is between 50 and 2,450 feet, regardless of aircraft configuration. This mode is designed to provide a warning if the aircraft is descending at a rate that is considered excessive and could potentially lead to a collision with the ground. It is an important safety feature that helps pilots maintain a safe rate of descent during approach and landing.

The video symbology display system is designed to show a visual representation of navigation data, A/S (airspeed), altitude, axis velocities, and various cautions. This means that the system provides information about the velocity along different axes as well as alerts and warnings for potential issues or dangers.

The correct answer is pressure-sensitive diaphragm. The vertical velocity indicator measures the rate of climb or descent of an aircraft. It does this by using a pressure-sensitive diaphragm, which is sensitive to changes in air pressure. As the aircraft climbs or descends, the air pressure around the diaphragm changes, causing it to move and indicate the rate of vertical movement. The other options, such as a barometric scale, expansion valve, or differential diaphragm, are not directly related to the function of the vertical velocity indicator.

The system integration manual does not include a description of the CITS system. This means that the manual does not provide any information or details about the CITS system. It may contain information about other aspects such as aircraft power control management, aircraft software configuration, and CITS system autoflow, but it does not specifically describe the CITS system itself.

When the DISPLAY switch on the CITS computer display panel is momentarily pressed to DIS RESET, all lighted matrix switches are turned off and reset.

The correct answer is Pitot. The A/S (airspeed) indicator measures the dynamic pressure of the air flowing around the aircraft. The Pitot tube, which is located on the aircraft's exterior, is responsible for measuring this dynamic pressure and transmitting it to the A/S diaphragm. The static pressure, on the other hand, is measured by the static ports and is used for other instruments like the altimeter. The engine pressure and barometric pressure are not directly related to the A/S diaphragm.

The correct answer is 20 minutes to reach 0 degrees C. This indicates that after the ADTD (Air Data Test Display) is initially turned on, it takes approximately 20 minutes for the heaters/ADTD to cool down to 0 degrees Celsius.

During a self-test of the ALT-vertical speed indicator, the barometric counter is set to 29.92. This setting represents the standard pressure at sea level. When the self-test is initiated, the ALT display should slew to a specific altitude to confirm that the indicator is functioning correctly. The correct altitude for this test is 50,000 feet.

The Mach-A/S indicators that are manually inserted are the command Mach and command IAS. These indicators require manual input from the pilot to display the desired values. The other options either do not require manual input or display different values.

The stall prevention computer produces a pusher signal if the aircraft angle-of-attack (AOA) equals the permissible AOA for five seconds. This means that if the aircraft's AOA remains at the permissible level for a continuous duration of five seconds, the stall prevention computer will activate the pusher system to prevent a stall.

The correct answer is two-degree increments from -70 degrees C to +80 degrees C. This means that the total air temperature is calibrated in intervals of two degrees, starting from -70 degrees Celsius and going up to +80 degrees Celsius. This calibration range allows for a wide range of temperatures to be measured with a reasonable level of accuracy.