2A852 CDC Volume 4

When the junction of the alumel and chromel metals in the exhaust gas temperature indicating system is heated or cooled, a voltage is produced. This voltage can be correlated to the temperature.

The fuel used indicator is a device that measures and displays the amount of fuel consumed by each engine. It provides a continuous digital readout in pounds, which indicates the accumulative fuel consumption. This information is important for monitoring fuel efficiency and managing fuel usage in various applications, such as vehicles or industrial machinery.

When the remote heading slew switch is in the DUAL position, both the pilot and copilot heading bugs will move when the pilot heading slew control is pressed. This means that both the pilot and copilot can adjust the heading bugs simultaneously, allowing for coordinated navigation and communication between the two pilots.

The inertial navigation unit (INU) accelerometer pendulum moves in response to an applied acceleration. This means that when an acceleration is applied to the INU, the accelerometer pendulum will move accordingly. The other options, such as wind speed, laser beam, and frequency, are not relevant to the movement of the accelerometer pendulum in an INU.

Fuel tanks closer to the wing tips contain more fuel quantity probes to compensate for greater attitude changes during aircraft roll. As the aircraft rolls, the wings tilt and the fuel inside the tanks shifts. By having more fuel quantity probes in the wing tanks, the system can accurately measure the fuel levels and ensure proper fuel management, even during significant attitude changes. This helps maintain the stability and balance of the aircraft during roll maneuvers.

The correct answer is a pair of tubes. Engine inlet pressure and engine exhaust pressure are applied to the dual bellows in the engine pressure ratio (EPR) transducer through a pair of tubes. This means that the pressure from the engine is transmitted through these tubes to the transducer, which measures and converts it into an electrical signal. The tubes act as a conduit for the pressure, allowing it to be accurately measured and monitored by the transducer.

When the flange teeth on the torquemeter assembly are in alignment, it means that there is no torque being applied. In other words, there is no twisting force being exerted on the assembly. This can occur when there is no external force or torque acting on the system, resulting in the flange teeth being in a neutral position.

The oil pressure transmitter vented Bourdon tube is vented to the atmosphere. This means that the Bourdon tube, which measures the oil pressure, is connected to the surrounding air. By venting to the atmosphere, any changes in pressure can be accurately measured and transmitted by the transmitter. This allows for precise monitoring of the oil pressure in the system.

The fuel flow indicator is a device that provides information about the rate at which fuel is flowing through the engine in pounds per hour. This is important for monitoring and controlling fuel consumption, as well as for calculating fuel efficiency. By providing both a pointer and digital readouts, the indicator allows for easy and accurate monitoring of the fuel flow rate.

Lo-Z is the correct term used for the unshielded wire used as a power lead in the fuel quantity indicating system. Lo-Z stands for low impedance, which refers to a low resistance in the wire. In the fuel quantity indicating system, a low impedance wire is used to transmit power efficiently and accurately measure the fuel quantity.

The weight-on-wheels test switch must be activated to allow go-around mode testing on the ground. This switch is used to simulate the aircraft being on the ground by indicating that the weight of the aircraft is resting on its wheels. By activating this switch, the RGA interface logic unit can detect that the aircraft is on the ground and enable go-around mode testing. The dim switch, flap test switch, and test reset switch are not relevant to go-around mode testing and do not affect the activation of this mode.

When the engine fan blade passes by the magnetic field of the N1 tachometer transmitter, it induces a signal in the sensor coil. This signal is then used to measure the rotational speed of the engine's N1 (low-pressure) compressor. By detecting the changes in the magnetic field caused by the passing fan blade, the N1 tachometer transmitter can accurately determine the speed of the engine.

The intercom cable is not part of the compass calibration set reel assemblies. The other cables mentioned - power, monitor, and transmitter - are included in the reel assemblies. The intercom cable serves a different purpose and is not necessary for compass calibration.

The oil quantity transmitter float assembly follows the fluid level. This means that the assembly is designed to accurately measure and transmit the level of oil in a system. It is not influenced by power level, amplifier, or torquer, but instead focuses solely on monitoring the amount of fluid present.

The roll and pitch computer lateral and vertical steering commands are displayed on the Attitude Director Indicator (ADI) command bars. The ADI is an instrument that provides the pilot with information about the aircraft's attitude and heading. The command bars on the ADI indicate the desired roll and pitch angles for the aircraft, allowing the pilot to make adjustments and maintain the desired flight path.

If the embedded global positioning and inertial navigation unit (EGI) does not acquire satellites, the early maintenance consideration should be the battery. The battery provides power to the EGI, and if it is not functioning properly or has low power, it can affect the unit's ability to acquire satellites. Therefore, checking and potentially replacing the battery should be a priority in troubleshooting the issue.

The control console is used to conduct the compass swing once the magnetic azimuth detector is transferred to and aligned in the aircraft. This suggests that the control console is specifically designed for use in aircraft and is used to perform a compass swing, which involves aligning the magnetic azimuth detector. The other options, such as tripod, compass rose, and magnetic field monitor, do not align with the context of conducting a compass swing in an aircraft.

The exhaust gas temperature thermocouple wiring is installed in parallel. This means that each thermocouple wire is connected to the same two points in the circuit, allowing for equal lengths of wiring. This configuration ensures that the temperature readings from each thermocouple are accurate and consistent, as any variations in resistance or voltage drop along the wiring will affect all thermocouples equally. Installing the wiring in parallel also allows for redundancy, as if one thermocouple fails, the others can still provide accurate temperature measurements.

The engine pressure ratio indicates the ratio between the exhaust pressure and the inlet pressure of an engine. When the engine pressure ratio is 1.0, it means that the exhaust pressure is equal to the inlet pressure. This indicates a balanced pressure condition within the engine, where the exhaust gases are being efficiently expelled without any excessive back pressure.

The correct answer is Inertial navigation system initialization (INS INIT). After power-up initialization, the embedded global positioning and inertial navigation unit (EGI) automatically enters the INS INIT mode. This mode allows the EGI to initialize and calibrate the inertial navigation system, which is responsible for providing accurate position, velocity, and attitude information. This initialization process is crucial for ensuring the EGI's accuracy and reliability in navigation.

The magnetic azimuth detector sends a signal to the remote magnetic compensator for magnetic compensation in MAG mode.

A blended solution, which combines both the global positioning system (GPS) and inertial navigation, provides the best estimate of position, attitude, velocity, and time. This is because GPS alone may have limitations in certain environments (such as urban canyons or dense foliage), while pure inertial navigation may suffer from drift over time. By blending the two systems, the strengths of each can compensate for the weaknesses of the other, resulting in a more accurate and reliable navigation solution.

The bonding meter is set on a range of two milliohms, which means it can measure values up to two milliohms. The answer "0 to 1.999 milliohms" falls within this range and is the correct answer.

The correct answer is pounds. The total fuel quantity indicator is used to display the total amount of fuel on-board the aircraft, and it is measured in pounds. This is because pounds is the standard unit of measurement for fuel quantity in aviation.

The attitude director indicator (ADI) speed deviation scale and pointer indicates the deviation from the desired approach speed. This means that it provides information on whether the aircraft is flying too fast or too slow during the approach phase. It helps the pilot to adjust the aircraft's speed accordingly to maintain the desired approach speed for a safe landing.

The oil pressure indicator displays the oil pressure in pounds per square inch (psi). The correct answer is 0 to 150, which means that the indicator can display oil pressure ranging from 0 psi to 150 psi.

The purpose of the PSD60-1AF fuel quantity test set vernier dials is to make fine adjustments to the simulation values. These dials allow for precise tuning and calibration of the fuel quantity test set, ensuring accurate and reliable measurements of fuel quantity.

The Coriolis error signal is a result of the rotation of the Earth and the geographic latitude. The Coriolis effect is caused by the rotation of the Earth, which causes moving objects (such as an aircraft) to be deflected to the right in the Northern Hemisphere and to the left in the Southern Hemisphere. This deflection is dependent on the speed and heading of the aircraft, as well as the latitude at which it is located. Therefore, the magnitude of the Coriolis error signal is influenced by the rotation of the Earth and the geographic latitude.

The correct answer is that the five monitored dual navigation systems have a discrepancy. This means that there is a difference or inconsistency between the readings or outputs of these five systems. The warning indicators illuminate to alert the user or operator that there is a problem or inconsistency in the navigation systems, indicating a potential issue with accuracy or reliability.

The correct answer is global positioning. In the embedded global positioning and inertial navigation unit (EGI) airborne alignment mode, the system uses global positioning signals to align and calibrate the navigation unit. Global positioning allows the unit to determine its precise location and orientation by receiving signals from satellites. This information is crucial for accurate navigation and positioning in an aircraft.

A compass swing is necessary after replacing the magnetic azimuth detector or remote magnetic compensator because these components are responsible for measuring and compensating for magnetic deviations in the compass system. By replacing these components, the accuracy and calibration of the compass may be affected, and a compass swing is required to ensure that the compass readings are correct and reliable.

The correct answer is 4 minutes. This is the amount of time it takes for the embedded global positioning and inertial navigation unit (EGI) to transition from gyro compass alignment to navigate mode. During this time, the EGI is calibrating and aligning its gyro compass with the GPS signals to accurately determine its position and navigate effectively.

A misalignment between the magnetic azimuth detector and the aircraft creates an index error. An index error refers to the discrepancy between the indicated heading on the magnetic compass and the actual heading of the aircraft. This misalignment can occur due to various factors such as magnetic field disturbances or improper installation of the compass. The index error can lead to inaccurate navigation and must be corrected to ensure the aircraft is heading in the intended direction.

The correct answer is 180 degrees out-of-phase with each other. In a bridge circuit, the reference leg and variable leg are connected to different sides of the bridge. When the fuel quantity changes, the variable leg's impedance changes, causing a phase shift in the output signal. A 180-degree phase shift means that the outputs are completely opposite to each other, with one being at its maximum while the other is at its minimum. This phase shift allows for accurate measurement of the fuel quantity.

When fuel is being used, the fuel quantity probe capacitance decreases. This is because as fuel is consumed, the level of fuel in the tank decreases, leading to a decrease in the capacitance of the fuel quantity probe. Additionally, the current also decreases as fuel is being used. This is because the decrease in capacitance results in a decrease in the flow of current through the fuel quantity probe. Therefore, both the capacitance and current decrease when fuel is being used.

The rotor is the only moving part in the oil pressure indicator. This means that it is the component responsible for detecting and measuring the oil pressure. The other options mentioned, such as the synchro receiver, Bourdon tube, and sector gear, do not play a role in indicating oil pressure. Therefore, the correct answer is the rotor.

In the pure inertial mode, the INU portion of the EGI operates independently of external input sources. This means that it does not rely on compass, autopilot, or flight director for navigation. However, it still requires digital air data, which provides information such as airspeed, altitude, and vertical speed. This data is essential for the INU to accurately calculate the position and orientation of the aircraft based on its own internal sensors.

The bonding meter battery has an adequate capacity to support 8 hours of continuous operation.

The TEST switch initiates the operation of the bonding meter. This switch is responsible for activating the meter and starting the bonding process. By pressing the TEST switch, the meter begins to measure the bonding resistance between two points. This allows the user to assess the quality of the bond between two objects or surfaces. The other options mentioned, such as built-in display illumination, resistance range setting, and LAMP switch, are not directly related to the initiation of the bonding meter's operation.

Each fuel flow electronic module pulse sent to the fuel used indicator represents 10 pounds of fuel.

Ring laser gyros provide precise angular rate information about the aircraft's pitch, roll, and yaw axes. These gyros use the principle of interference of laser beams to measure the rotation of the aircraft. They are highly accurate and reliable, making them an essential component of inertial navigation systems. Accelerometers, on the other hand, measure linear acceleration and are not specifically designed to provide angular rate information. Synchro repeaters and control/annunciator panels are not directly related to providing angular rate information in an inertial navigation system.

The compensator probe is responsible for accounting for changes in the density of the fuel in the fuel quantity indicating system. This component adjusts the fuel quantity readings based on the density of the fuel, ensuring accurate measurements regardless of variations in fuel density.

In the flight director system, the mode that overrides the navigation (NAV) lateral and glide slope beam sensors is the Approach manual (APPR MAN) mode. This mode allows the pilot to manually control the aircraft's approach and landing, disregarding the input from the navigation sensors. It gives the pilot full control over the aircraft's lateral and vertical guidance during the approach phase.

Bourdon tubes are the types of sensing elements used in the oil pressure transmitter. Bourdon tubes are C-shaped tubes that are sensitive to pressure changes. When pressure is applied, the tube straightens out, and this movement is converted into a mechanical motion that can be measured. Bourdon tubes are commonly used in pressure measurement devices due to their accuracy and reliability. Magnets, aneroids, and dual bellows are not typically used as sensing elements in oil pressure transmitters.

The RGA interface logic unit is responsible for averaging the angle-of-attack signals in a rotation go-around (RGA) system. This component takes the input from multiple angle-of-attack sensors and calculates the average value. It ensures that the RGA system receives a consistent and accurate measurement of the angle of attack, which is crucial for the safe and effective operation of the aircraft during rotation go-around maneuvers.

The glide slope extension mode in the flight director system is initiated by the 200 foot altitude trip voltage. This voltage is triggered when the aircraft reaches an altitude of 200 feet, indicating that it is at a specific point in its descent. This mode helps guide the aircraft to maintain the correct glide slope during approach and landing, ensuring a safe and smooth descent.

The heading bug on the horizontal situation indicator (HSI) is commanded by the heading slew controls. These controls allow the pilot to adjust and set the desired heading on the HSI. By using the heading slew controls, the pilot can align the heading bug with the desired heading, providing a reference for navigation and course tracking. The other options mentioned, such as the remote heading slew switch, pitch command control, and rate-of-turn indicator, are not directly responsible for commanding the heading bug on the HSI.

Pressing the rotation go-around (RGA) control wheel switch on approach causes the attitude direction indicator (ADI) to command a wings-level climb attitude of 7 degrees. This means that when the RGA control wheel switch is activated, the ADI will indicate that the aircraft should be in a climb attitude with the wings level, and the angle of climb will be 7 degrees.

The operating range of the analog pointer on the exhaust gas temperature (EGT) indicator is from 0 to 1000 degrees Celsius.

The N2 tachometer transmitter is an alternating current generator that measures the rotational speed of the rotor. As the rotor speed increases, the frequency of the generated current also increases. Therefore, the frequency of the generated current is directly proportional to the rotor speed.