# 2A852 CDC Volume 4

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Matthew Kenney
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Quizzes Created: 6 | Total Attempts: 890
Questions: 90 | Attempts: 94

Settings

• 1.

### From what degrees is the compass system latitude knob on the digital controller continuously variable?

• A.

0 to 90.

• B.

0 to 180.

• C.

45 to 90

• D.

45 to 180.

A. 0 to 90.
Explanation
The compass system latitude knob on the digital controller is continuously variable from 0 to 90 degrees. This means that it can be adjusted to any angle within that range, allowing for precise control over the latitude settings.

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• 2.

### The magnitude of the Coriolis error signal depends on the aircraft speed, aircraft heading,

• A.

Rotation of the Earth, and geograpHic longitude.

• B.

Rotation of the Earth, and geograpHic latitude

• C.

Aircraft attitude, and geograpHic longitude

• D.

Aircraft attitude, and geograpHic latitude

B. Rotation of the Earth, and geograpHic latitude
Explanation
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.

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• 3.

### What does a misalignment between the magnetic azimuth detector and the aircraft create?

• A.

Meridian convergence error

• B.

Transmission error.

• C.

Coriolis error.

• D.

Index error

D. Index error
Explanation
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.

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• 4.

### What component contains the earth’s rate and coriolis compensation computer?

• A.

Directional gyro

• B.

Digital controller

• C.

Remote compensator

• D.

Magnetic azimuth detector.

B. Digital controller
Explanation
The digital controller contains the earth's rate and coriolis compensation computer. This component is responsible for calculating and compensating for the earth's rotation and the Coriolis effect, which affect the accuracy of navigation systems. The digital controller uses algorithms and sensor data to make the necessary adjustments, ensuring that the navigation system provides accurate and reliable information.

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• 5.

### The one-cycle error compensator consists of

• A.

Two variable resistors and three isolation resistors

• B.

Three variable resistors and two isolation resistors

• C.

Two variable diodes and three isolation diodes.

• D.

Three variable diodes and two isolation diodes

A. Two variable resistors and three isolation resistors
Explanation
The correct answer is two variable resistors and three isolation resistors. This is because a one-cycle error compensator is used to correct for timing errors in digital systems. Variable resistors are used to adjust the timing of the system, while isolation resistors are used to prevent any interference between different components. Therefore, having two variable resistors and three isolation resistors would provide the necessary control and isolation for the compensator to effectively correct timing errors.

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• 6.

### In what compass mode does the magnetic azimuth detector send a signal to the remote magnetic compensator for magnetic compensation?

• A.

DG mode

• B.

RGA mode.

• C.

MAG mode

• D.

AUTO mode.

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

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• 7.

### The control console is used to conduct the compass swing once the magnetic azimuth detector is transferred to and aligned in the

• A.

Tripod

• B.

Aircraft

• C.

Compass rose

• D.

Magnetic field monitor

B. Aircraft
Explanation
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.

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• 8.

### The telescope on the magnetic field monitor is

• A.

42-power and rotates 180 degrees

• B.

42-power and rotates 360 degrees

• C.

22-power and rotates 180 degrees

• D.

22-power and rotates 360 degrees.

D. 22-power and rotates 360 degrees.
Explanation
The telescope on the magnetic field monitor is 22-power, which means it magnifies the image by 22 times. It also rotates 360 degrees, allowing for a full range of observation.

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• 9.

### Which cable is not part of the compass calibration set reel assemblies?

• A.

Power

• B.

Monitor

• C.

Intercom

• D.

Transmitter

C. Intercom
Explanation
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.

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• 10.

### A compass swing must be performed after replacing the

• A.

Magnetic azimuth detector or remote magnetic compensator.

• B.

Remote magnetic compensator or digital controller

• C.

Magnetic azimuth detector or digital controller

• D.

Compass controller or compass amplifier

A. Magnetic azimuth detector or remote magnetic compensator.
Explanation
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.

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• 11.

### The flight director control panel pitch command selects a climb or descent angle from

• A.

20 degrees up to 5 degrees down

• B.

15 degrees up to 5 degrees down

• C.

20 degrees up to 10 degrees down.

• D.

15 degrees up to 10 degrees down

D. 15 degrees up to 10 degrees down
Explanation
The flight director control panel pitch command allows for a climb or descent angle selection. The correct answer is "15 degrees up to 10 degrees down." This means that the pitch command can be set to a climb angle of up to 15 degrees or a descent angle of up to 10 degrees.

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• 12.

### The attitude director indicator (ADI) speed deviation scale and pointer indicates deviation from desired

• A.

Approach speed.

• B.

Approach track

• C.

Ground speed

• D.

Ground track.

A. Approach speed.
Explanation
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.

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• 13.

### What commands the horizontal situation indicator (HSI) heading bug?

• A.

• B.

Pitch command control

• C.

• D.

Rate-of-turn indicator

Explanation
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.

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• 14.

### With the remote heading slew switch in the DUAL position, which heading bug(s) will move when the pilot heading slew control is pressed?

• A.

Pilot only

• B.

Copilot only.

• C.

Pilot and copilot.

• D.

Pilot and navigator

C. Pilot and copilot.
Explanation
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.

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• 15.

### Where are the roll and pitch computer lateral and vertical steering commands displayed?

• A.

Horizontal situation indicator (HSI) lubber line.

• B.

Attitude director indicator (ADI) command bars

• C.

Horizontal situation indicator (HSI) compass card.

• D.

Attitude director indicator (ADI) speed deviation scale.

B. Attitude director indicator (ADI) command bars
Explanation
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.

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• 16.

### In the rotation go-around (RGA) subsystem with the flaps are set at 30 degrees, how many degrees of initial climbout are displayed on the attitude direction indicator (ADI) during takeoff?

• A.

7

• B.

8

• C.

8.5

• D.

9.5

B. 8
Explanation
The correct answer is 8. During takeoff, the attitude direction indicator (ADI) displays the degrees of initial climbout. In this case, with the flaps set at 30 degrees in the rotation go-around (RGA) subsystem, the ADI displays 8 degrees of initial climbout.

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• 17.

### Pressing the rotation go-around (RGA) control wheel switch on approach causes the attitude direction indicator (ADI) to command a

• A.

Wings-level dive attitude of 7 degrees

• B.

Wings-level dive attitude of 8 degrees.

• C.

Wings-level climb attitude of 7 degrees.

• D.

Wings-level climb attitude of 8 degrees.

C. Wings-level climb attitude of 7 degrees.
Explanation
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.

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• 18.

### In the rotation go-around (RGA) subsystem, the angle-of-attack transmitters detect and transmit changes in local angle-of-attack at aircraft speeds above how many knots?

• A.

70

• B.

80

• C.

90

• D.

100

C. 90
Explanation
The angle-of-attack transmitters in the rotation go-around (RGA) subsystem detect and transmit changes in local angle-of-attack at aircraft speeds above 90 knots. This means that the transmitters are only operational and able to detect changes in angle-of-attack when the aircraft is flying at speeds higher than 90 knots.

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• 19.

### What rotation go-around (RGA) component averages the angle-of-attack signals?

• A.

RGA computer

• B.

RGA control panel.

• C.

RGA interface logic unit

• D.

Longitudinal accelerometer

C. RGA interface logic unit
Explanation
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.

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• 20.

### The rotation go-around (RGA) interface logic unit flap indicators indicate the presence of

• A.

15 or 25 degree flap discrete signals.

• B.

20 or 25 degree flap discrete signals

• C.

25 or 30 degree flap discrete signals.

• D.

25 or 35 degree flap discrete signals

A. 15 or 25 degree flap discrete signals.
Explanation
The rotation go-around (RGA) interface logic unit flap indicators are used to indicate the presence of discrete signals for the flaps. These signals can be either 15 or 25 degrees.

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• 21.

### Which rotation go-around (RGA) interface logic unit test switch must be activated to allow go-around mode testing on the ground?

• A.

Dim switch

• B.

Flap test switch.

• C.

Test reset switch.

• D.

Weight-on-wheels test switch.

D. Weight-on-wheels test switch.
Explanation
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.

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• 22.

### The comparator warning monitor subsystem continuously monitors and compares the inputs to the flight director from the

• A.

Compass, localizer, glide slope, and autopilot systems

• B.

Compass, localizer, glide slope, and radio altimeter systems

• C.

Compass, localizer, glide slope, and flight management systems.

• D.

Compass, localizer, glide slope, and barometric altimeter systems

B. Compass, localizer, glide slope, and radio altimeter systems
Explanation
The correct answer is compass, localizer, glide slope, and radio altimeter systems. The comparator warning monitor subsystem is responsible for continuously monitoring and comparing the inputs to the flight director from these specific systems. This subsystem ensures that the information provided by the compass, localizer, glide slope, and radio altimeter is accurate and consistent, helping to maintain the safety and accuracy of the flight director system.

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• 23.

### The comparator warning indicators illuminate when one of the

• A.

Five monitored dual navigation systems has a discrepancy

• B.

Seven monitored dual navigation systems has a discrepancy.

• C.

Five monitored dual navigation systems is operating correctly

• D.

Seven monitored dual navigation systems is operating correctly.

A. Five monitored dual navigation systems has a discrepancy
Explanation
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.

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• 24.

### After localizer capture, how many degrees of error must be detected for the compass system indicator on the comparator warning monitor display panel to illuminate?

• A.

3

• B.

4

• C.

5

• D.

6

A. 3
Explanation
The correct answer is 3. This means that after the localizer capture, the compass system indicator on the comparator warning monitor display panel will illuminate if there is a detection of a 3-degree error. This suggests that the compass system is designed to provide a warning if there is a significant deviation from the correct heading by at least 3 degrees.

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• 25.

### The rotation go-around (RGA) system indicator on the comparator warning monitor display panel illuminates when a differential error of

• A.

Two degrees pitch exists for more than three seconds between the RGA computers

• B.

Three degrees pitch exists for more than two seconds between the RGA computers.

• C.

Two degrees pitch exists for more than three seconds between the steering computers

• D.

Three degrees pitch exists for more than two seconds between the steering computers.

B. Three degrees pitch exists for more than two seconds between the RGA computers.
Explanation
The correct answer is three degrees pitch exists for more than two seconds between the RGA computers. This is indicated by the rotation go-around (RGA) system indicator on the comparator warning monitor display panel illuminating. It means that if there is a difference of three degrees in pitch between the RGA computers for more than two seconds, the warning will be triggered.

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• 26.

### What drives the attitude director indicator (ADI) command bars to a wings-level attitude in the rotation go-around (RGA) mode of the flight director system?

• A.

RGA interface logic unit.

• B.

Pitch steering computer

• C.

Roll steering computer

• D.

RGA computer

C. Roll steering computer
Explanation
The roll steering computer drives the attitude director indicator (ADI) command bars to a wings-level attitude in the rotation go-around (RGA) mode of the flight director system. This means that the roll steering computer is responsible for providing the necessary commands to maintain a level flight attitude during the RGA mode.

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• 27.

### In what flight director mode are the attitude director indicator (ADI) command bars driven out of view?

• A.

• B.

GYRO.

• C.

• D.

Approach/manual (APPR MAN).

B. GYRO.
Explanation
In the GYRO flight director mode, the attitude director indicator (ADI) command bars are driven out of view. This means that the command bars, which provide guidance to the pilot on the desired aircraft attitude, are not displayed on the ADI when the GYRO mode is selected.

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• 28.

### Switching the mode selector on the flight director control panel to the HDG position causes the pitch steering computer to operate in either the

• A.

Manual pitch or altitude hold mode

• B.

Altitude hold or glide slope mode.

• C.

Manual pitch or localizer mode

• D.

Altitude hold or localizer mode

A. Manual pitch or altitude hold mode
Explanation
Switching the mode selector on the flight director control panel to the HDG position allows the pitch steering computer to operate in either the manual pitch or altitude hold mode. This means that the pilot can manually control the pitch of the aircraft or set a desired altitude for the aircraft to maintain.

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• 29.

### In the flight director system, what initiates the glide slope extension mode?

• A.

100 foot altitude trip voltage.

• B.

200 foot altitude trip voltage.

• C.

300 foot altitude trip voltage

• D.

500 foot altitude trip voltage.

B. 200 foot altitude trip voltage.
Explanation
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.

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• 30.

### In the flight director system, what mode overrides the navigation (NAV) lateral and glide slope beam sensors?

• A.

Rotation go-around (RGA).

• B.

• C.

Approach manual (APPR MAN).

• D.

Approach automatic (APPR AUTO).

C. Approach manual (APPR MAN).
Explanation
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.

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• 31.

### The inertial navigation unit (INU) section of the embedded global positioning and inertial navigation unit (EGI) consists of

• A.

Two ring laser gyros and two accelerometers

• B.

Two ring laser gyros and three accelerometers

• C.

Three ring laser gyros and two accelerometers

• D.

Three ring laser gyros and three accelerometers

D. Three ring laser gyros and three accelerometers
Explanation
The correct answer is three ring laser gyros and three accelerometers. The inertial navigation unit (INU) section of the embedded global positioning and inertial navigation unit (EGI) requires a combination of ring laser gyros and accelerometers to accurately measure both angular velocity and linear acceleration. Having three of each ensures redundancy and improves the overall accuracy and reliability of the EGI system.

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• 32.

### What inertial navigation system (INS) component provides precise angular rate information about the aircraft pitch, roll, and yaw axes?

• A.

Accelerometers.

• B.

Ring laser gyros

• C.

Synchro repeaters

• D.

Control/annunciator panel.

B. Ring laser gyros
Explanation
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.

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• 33.

### The inertial navigation unit (INU) accelerometer pendulum moves in response to an applied

• A.

Acceleration.

• B.

Wind speed.

• C.

Laser beam.

• D.

Frequency.

A. Acceleration.
Explanation
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.

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• 34.

### What component replacement should be an early maintenance consideration if the embedded global positioning and inertial navigation unit (EGI) does not acquire satellites?

• A.

Battery

• B.

Accelerometer.

• C.

Ring laser gyro

• D.

Synchro repeater

A. Battery
Explanation
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.

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• 35.

### Synchro repeaters amplify and distribute inertial navigation unit (INU) attitude signals to the

• A.

Flight director, flight displays, color weather radar, and autopilot systems

• B.

Flight director, flight displays, color weather radar, and compass systems

• C.

Flight director, compass, color weather radar, and autopilot systems

• D.

Flight director, flight displays, compass, and autopilot systems

A. Flight director, flight displays, color weather radar, and autopilot systems
Explanation
Synchro repeaters amplify and distribute inertial navigation unit (INU) attitude signals to the flight director, flight displays, color weather radar, and autopilot systems. This means that the synchro repeaters are responsible for amplifying and distributing the INU attitude signals to these specific systems, allowing them to receive and utilize the signals for their respective functions.

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• 36.

### What mode does the embedded global positioning and inertial navigation unit (EGI) automatically enter following power-up initialization?

• A.

Airborne alignment

• B.

Gyro compass alignment

• C.

Inertial navigation system initialization (INS INIT).

• D.

Global positioning system initialization (GPS INIT).

C. Inertial navigation system initialization (INS INIT).
Explanation
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.

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• 37.

### How long does it take the embedded global positioning and inertial navigation unit (EGI) to transition from gyro compass alignment to navigate mode?

• A.

4 seconds

• B.

4 minutes

• C.

20 seconds

• D.

20 minutes

B. 4 minutes
Explanation
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.

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• 38.

### The embedded global positioning and inertial navigation unit (EGI) stored heading (SH) alignment is completed in

• A.

30 seconds

• B.

60 minutes

• C.

30 minutes.

• D.

60 seconds

A. 30 seconds
Explanation
The embedded global positioning and inertial navigation unit (EGI) completes the stored heading (SH) alignment process in just 30 seconds. This indicates that the EGI system is able to quickly and accurately determine the heading of the device. The shorter the alignment time, the more efficient and reliable the EGI system is in providing accurate navigation information.

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• 39.

### What system signals are used in the embedded global positioning and inertial navigation unit (EGI) airborne (AIR) alignment mode?

• A.

Global positioning

• B.

Flight director

• C.

Autopilot.

• D.

Compass.

A. Global positioning
Explanation
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.

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• 40.

### In the pure inertial mode, the inertial navigation unit (INU) portion of the embedded global positioning and inertial navigation unit (EGI) acts independent of all external input sources except

• A.

Compass

• B.

Autopilot.

• C.

Flight director

• D.

Digital air data.

D. Digital air data.
Explanation
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.

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• 41.

### Which embedded global positioning and inertial navigation unit (EGI) navigation solution provides the best estimate of position, attitude, velocity, and time?

• A.

Global positioning system only.

• B.

Pure inertial

• C.

• D.

Blended solution.

D. Blended solution.
Explanation
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.

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• 42.

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

• A.

Temperature.

• B.

Pressure

• C.

Torque.

• D.

Speed.

A. Temperature.
Explanation
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.

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• 43.

### Exhaust gas temperature thermocouple wiring is equal in length and installed in

• A.

Oil

• B.

Fuel

• C.

Series

• D.

Parallel

D. Parallel
Explanation
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.

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• 44.

### What is the operating range of the analog pointer on the exhaust gas temperature (EGT) indicator?

• A.

0 to 1000 degrees Celsius

• B.

20 to 975 degrees Celsius

• C.

0 to 1000 degrees Fahrenheit

• D.

70 to 975 degrees Fahrenheit.

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

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• 45.

### What will the exhaust gas temperature (EGT) indicator digital readout indicate during the built-in-test?

• A.

975 degrees (±20 degrees Celsius).

• B.

999 degrees (±20 degrees Celsius).

• C.

975 degrees (±70 degrees Fahrenheit).

• D.

999 degrees (±70 degrees Fahrenheit).

C. 975 degrees (±70 degrees Fahrenheit).
Explanation
During the built-in-test, the exhaust gas temperature (EGT) indicator digital readout will indicate 975 degrees with a margin of error of ±70 degrees Fahrenheit.

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• 46.

### Engine inlet pressure and engine exhaust pressure are applied to the dual bellows in the engine pressure ratio (EPR) transducer through

• A.

An electrical connector

• B.

A pair of tubes

• C.

Shock mounts.

• D.

An amplifier.

B. A pair of tubes
Explanation
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.

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• 47.

### Instead of using a dual bellows sensing element, what type sensing element does the digital engine pressure ratio transducer use?

• A.

Piezocapacitive temperature

• B.

Piezoresistive temperature

• C.

Piezocapacitive pressure

• D.

Piezoresistive pressure

D. Piezoresistive pressure
Explanation
The correct answer is Piezoresistive pressure. The digital engine pressure ratio transducer uses a piezoresistive pressure sensing element instead of a dual bellows sensing element. Piezoresistive pressure sensors measure pressure by detecting changes in electrical resistance caused by the applied pressure. This type of sensing element is commonly used in various applications, including engine pressure measurement, due to its accuracy, reliability, and ability to withstand harsh operating conditions.

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• 48.

### What engine pressure ratio indicates exhaust pressure is equal to inlet pressure?

• A.

0.1

• B.

1.0

• C.

2.0

• D.

4.1

B. 1.0
Explanation
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.

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• 49.

### What types of sensing elements are used in the oil pressure transmitter?

• A.

Magnets.

• B.

Aneroids

• C.

Dual bellows

• D.

Bourdon tubes.

D. Bourdon tubes.
Explanation
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.

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• 50.

### The oil pressure transmitter vented Bourdon tube is vented to the

• A.

AtmospHere

• B.

Case

• C.

Fuel

• D.

Oil

A. AtmospHere
Explanation
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.

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• Current Version
• Jul 09, 2024
Quiz Edited by
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• Feb 03, 2016
Quiz Created by
Matthew Kenney

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