2A553B Vol. 4 Pretest
Pretest for CDC 2A553B Upgrade.
Questions and Answers
- 1.
(601) Near the equator, the lines of magnetic force are...
- A.
Perpendicular to the Earth's surface.
- B.
Parallel to the Coriolis field.
- C.
Parallel to the Earth's surface.
- D.
Perpendicular to the Coriolis field.
Correct Answer
C. Parallel to the Earth's surface.Explanation
Near the equator, the lines of magnetic force are parallel to the Earth's surface. This is because the Earth's magnetic field is primarily generated by the motion of molten iron in its outer core. Near the equator, the magnetic field lines are relatively horizontal and parallel to the Earth's surface. As we move away from the equator towards the poles, the magnetic field lines become more inclined and eventually become perpendicular to the Earth's surface.Rate this question:
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- 2.
(601) Which magnetic compass error occurs due to magnetism within the aircraft?
- A.
Interference.
- B.
Vibration.
- C.
Deviation.
- D.
Variation.
Correct Answer
C. Deviation.Explanation
Deviation is the correct answer because it refers to the magnetic compass error that occurs due to magnetism within the aircraft. This error is caused by the presence of magnetic materials or electrical systems in the aircraft, which can create their own magnetic fields and interfere with the accuracy of the compass. Deviation is different from variation, which is the angular difference between true north and magnetic north, and is not affected by the aircraft's magnetism. Interference and vibration are not specific compass errors caused by magnetism within the aircraft.Rate this question:
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- 3.
(601) 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.
Correct Answer
B. Rotation of the Earth, and geographic latitude.Explanation
The Coriolis error signal is a measure of the effect of the Earth's rotation on an aircraft's navigation system. It is caused by the rotation of the Earth and the aircraft's position in terms of geographic latitude. The magnitude of the error signal depends on the speed and heading of the aircraft, as well as the latitude of its position. The rotation of the Earth affects the direction of the error signal, while the geographic latitude determines its magnitude. Therefore, the correct answer is "rotation of the Earth, and geographic latitude."Rate this question:
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- 4.
(601) Neutralizing or weakening the permanent magnetic field that exists around an aircraft is called...
- A.
Demoding.
- B.
Despoiling.
- C.
Defoliating.
- D.
Degaussing.
Correct Answer
D. Degaussing.Explanation
The process of neutralizing or weakening the permanent magnetic field that exists around an aircraft is known as degaussing. This is done to prevent the magnetic field from interfering with the aircraft's instruments and systems.Rate this question:
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- 5.
(601) Any misalignment between the magnetic azimuth detector and the longitudinal axis of the aircraft creates...
- A.
A Coriolis effect error.
- B.
A transmission error.
- C.
A hard iron error.
- D.
An index erro.
Correct Answer
D. An index erro.Explanation
Any misalignment between the magnetic azimuth detector and the longitudinal axis of the aircraft creates an index error. This means that the magnetic compass will not accurately indicate the magnetic heading of the aircraft. The index error occurs when the compass card is not aligned with the aircraft's longitudinal axis, causing a deviation in the readings. This can result in incorrect navigation and heading information for the pilot.Rate this question:
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- 6.
(602) With an input frequency of 400 Hz, what is the frequency of the magnetic azimuth detector output?
- A.
60 Hz.
- B.
200 Hz.
- C.
400 Hz.
- D.
800 Hz.
Correct Answer
D. 800 Hz.Explanation
The magnetic azimuth detector measures the direction of the Earth's magnetic field. The input frequency of 400 Hz refers to the frequency of the alternating current supplied to the detector. The magnetic azimuth detector processes this input frequency and produces an output frequency that is double the input frequency, resulting in a frequency of 800 Hz.Rate this question:
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- 7.
(602) What is used to develop the single-cycle error compensation signal in the attitude heading reference system?
- A.
Synchros.
- B.
Resolvers.
- C.
Differentials.
- D.
Variable resistors.
Correct Answer
D. Variable resistors.Explanation
Variable resistors are used to develop the single-cycle error compensation signal in the attitude heading reference system. These resistors can be adjusted to fine-tune the error compensation signal and ensure accurate attitude and heading measurements. Synchros and resolvers are types of electrical devices used for angle measurement, but they are not specifically used for developing error compensation signals in this context. Differentials are mechanical devices used to transmit power between rotating shafts and are not relevant to the development of error compensation signals in the attitude heading reference system.Rate this question:
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- 8.
(602) What type of gyros are used in the attitude heading reference system?
- A.
Two vertical gyros.
- B.
Two directional gyros.
- C.
One vertical and one directional gyro.
- D.
One horizontal and one directional gyro.
Correct Answer
C. One vertical and one directional gyro.Explanation
The attitude heading reference system (AHRS) uses one vertical gyro and one directional gyro. The vertical gyro measures the aircraft's pitch and roll, providing information about its attitude. The directional gyro, also known as the heading gyro, measures the aircraft's yaw, indicating its heading. Together, these two gyros provide crucial information about the aircraft's orientation and movement in three dimensions, allowing for accurate navigation and control.Rate this question:
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- 9.
(602) The source of the erection signal for the VG pitch gimbal of the attitude heading reference system is...
- A.
A fluid type sensor.
- B.
The light erection sensor.
- C.
The VG pitch gimbal synchro.
- D.
The directional gyroscope pitch gimbal synchro.
Correct Answer
A. A fluid type sensor.Explanation
The correct answer is a fluid type sensor. A fluid type sensor is responsible for providing the erection signal for the VG pitch gimbal of the attitude heading reference system. This sensor measures the level or pressure of a fluid, which is then used to determine the orientation of the VG pitch gimbal.Rate this question:
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- 10.
(602) The attitude heading reference system DG pitch gimbal is aligned with and continuously follows the...
- A.
VG pitch gimbal.
- B.
VG inner roll gimbal.
- C.
DG leveling gimbal.
- D.
DG leveling sensor.
Correct Answer
A. VG pitch gimbal.Explanation
The attitude heading reference system (AHRS) DG pitch gimbal is aligned with and continuously follows the VG pitch gimbal. This means that the AHRS DG pitch gimbal adjusts its position to match the movements of the VG pitch gimbal, ensuring accurate and synchronized measurements of the aircraft's pitch attitude. The VG pitch gimbal is responsible for detecting and measuring changes in the aircraft's pitch, and the AHRS DG pitch gimbal is designed to mirror these movements for precise attitude reference.Rate this question:
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- 11.
(603) The attitude heading reference system requires input power consisting of 115VAC, 400 Hz, 3-phase aircraft power, and...
- A.
26VAC, 60 Hz, single-phase power for excitation.
- B.
26VDC, 60 Hz, single-phase power for excitation.
- C.
26VAC, 400 Hz, single-phase power for excitation.
- D.
26VDC, 400 Hz, single-phase power for excitation.
Correct Answer
C. 26VAC, 400 Hz, single-phase power for excitation.Explanation
The correct answer is 26VAC, 400 Hz, single-phase power for excitation. The attitude heading reference system requires this specific power input for excitation.Rate this question:
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- 12.
(603) The AHRS cuts off slaving of the AHRS to magnetic heading when a fore-aft acceleration of...
- A.
1.736-g or a turn rate of 8 degrees per minute is exceeded.
- B.
1.736-g or a turn rate of 5 degrees per minute is exceeded.
- C.
0.055-g or a turn rate of 8 degrees per minute is exceeded.
- D.
0.055-g or a turn rate of 5 degrees per minute is exceeded.
Correct Answer
C. 0.055-g or a turn rate of 8 degrees per minute is exceeded.Explanation
The AHRS cuts off slaving of the AHRS to magnetic heading when a fore-aft acceleration of 0.055-g or a turn rate of 8 degrees per minute is exceeded. This means that if the aircraft experiences an acceleration greater than 0.055 times the force of gravity in the fore-aft direction, or if the turn rate exceeds 8 degrees per minute, the AHRS will no longer use the magnetic heading for its calculations.Rate this question:
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- 13.
(603) The three attitude heading reference system heading modes of operation are slave,...
- A.
DG, and compass.
- B.
Coriolis, and compass.
- C.
Coriolis, and azimuth.
- D.
DG, and azimuth.
Correct Answer
A. DG, and compass.Explanation
The three attitude heading reference system (AHRS) heading modes of operation are DG (Directional Gyro), and compass. The DG mode provides heading information based on the rotation of a gyroscopic device, while the compass mode uses magnetic sensors to determine the heading. Both modes are commonly used in aviation to provide accurate and reliable heading information to pilots. The other options, Coriolis and azimuth, are not related to AHRS heading modes.Rate this question:
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- 14.
(604) The MC-2000 electronics group consists of a control console, magnetic field monitor,...
- A.
Turntable, and compass adapter box.
- B.
Tripods, and compass adapter box.
- C.
Turntable, and alignment tool kit.
- D.
Tripods, and alignment tool kit.
Correct Answer
C. Turntable, and alignment tool kit.Explanation
The MC-2000 electronics group consists of a turntable, and alignment tool kit. This means that these two components are included in the group. The other options mentioned, such as control console, magnetic field monitor, tripods, and compass adapter box, are not mentioned as part of the MC-2000 electronics group. Therefore, the correct answer is turntable, and alignment tool kit.Rate this question:
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- 15.
(604) The serial number on the MC-2000 electronics group control console must match the serial number on the...
- A.
Cable.
- B.
Turntable.
- C.
Compass adapter box.
- D.
Magnetic field monitor.
Correct Answer
D. Magnetic field monitor.Explanation
The serial number on the MC-2000 electronics group control console must match the serial number on the magnetic field monitor. This is important for proper identification and compatibility between the control console and the monitor. It ensures that the correct monitor is being used and that any necessary communication or data exchange between the console and the monitor can take place accurately.Rate this question:
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- 16.
(604) The telescope on the magnetic field monitor is...
- A.
40-power and rotates 270 degrees.
- B.
40-power and rotates 360 degrees.
- C.
22-power and rotates 270 degrees.
- D.
22-power and rotates 360 degrees.
Correct Answer
D. 22-power and rotates 360 degrees.Explanation
The correct answer is 22-power and rotates 360 degrees. This means that the telescope on the magnetic field monitor has a magnification power of 22 and is able to rotate a full 360 degrees.Rate this question:
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- 17.
(604) What is used only during the field certification and calibration check?
- A.
Compass rose adapter box swing assembly.
- B.
Magnetic azimuth reference detector.
- C.
Magnetic field monitor.
- D.
Control console.
Correct Answer
B. Magnetic azimuth reference detector.Explanation
The magnetic azimuth reference detector is used only during the field certification and calibration check. This suggests that the other options, such as the compass rose adapter box swing assembly, magnetic field monitor, and control console, are not specifically used for this purpose. Therefore, the magnetic azimuth reference detector is the correct answer.Rate this question:
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- 18.
(605) The navigation function is accomplished primarily through the sensing element and measurement of...
- A.
Magnetic north.
- B.
Earth rotation.
- C.
Acceleration.
- D.
Gravity.
Correct Answer
C. Acceleration.Explanation
The navigation function is primarily accomplished through the sensing element and measurement of acceleration. Acceleration refers to the rate of change of velocity, and by measuring acceleration, navigation systems can determine the changes in speed and direction of movement. This information is crucial for determining position, velocity, and orientation in navigation. Sensing and measuring magnetic north, Earth rotation, or gravity alone cannot provide the necessary data for navigation purposes, making acceleration the correct answer.Rate this question:
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- 19.
(605) The inertial navigation system operates as a self-contained system, but can be updated by...
- A.
VOR/ILS, STS, or manually.
- B.
TACAN, SKE, or manually.
- C.
VOR/ILS, SKE, or manually.
- D.
TACAN, STS, or manually.
Correct Answer
B. TACAN, SKE, or manually.Explanation
The correct answer is TACAN, SKE, or manually. This means that the inertial navigation system can be updated through TACAN, which is a military navigational aid that provides range and bearing information, SKE (Selective Availability Anti-Spoofing Module Key Encryption), which is a device used to encrypt and secure GPS signals, or manually, indicating that the system can be updated by inputting the information directly.Rate this question:
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- 20.
(606) Which INS unit serves as the communication link between the pilot and the INU digital computer?
- A.
Mode selector unit.
- B.
Control display unit.
- C.
Co-pilot's control unit.
- D.
Navigator's selector panel.
Correct Answer
B. Control display unit.Explanation
The control display unit serves as the communication link between the pilot and the INU digital computer. It is responsible for displaying the information from the INU and allows the pilot to input commands and make selections. The control display unit is an essential component in the communication and interaction between the pilot and the INU digital computer.Rate this question:
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- 21.
(606) Which INS control display unit light illuminates approximately two minutes before reaching a waypoint during flight?
- A.
BAT.
- B.
PWR.
- C.
WARN.
- D.
ALERT.
Correct Answer
D. ALERT.Explanation
The correct answer is ALERT. During flight, the INS control display unit light illuminates approximately two minutes before reaching a waypoint to alert the pilot. This alert indicates that the aircraft is approaching a significant point in its flight plan and serves as a reminder for the pilot to prepare for any necessary actions or maneuvers.Rate this question:
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- 22.
(606) Which INS control display unit right-hand data display digits display an action code when there is a system failure?
- A.
1 and 2.
- B.
2 and 3.
- C.
1 and 4.
- D.
2 and 4.
Correct Answer
B. 2 and 3.Explanation
The correct answer is 2 and 3. This means that the INS control display unit right-hand data display will show an action code when there is a system failure.Rate this question:
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- 23.
(606) Which INS submode enables aided inertial operation using TACAN data?
- A.
0.
- B.
2.
- C.
4.
- D.
5.
Correct Answer
C. 4.Explanation
INS submode 4 enables aided inertial operation using TACAN data. TACAN (Tactical Air Navigation) is a navigation system that provides aircraft with distance and bearing information. In INS submode 4, the aircraft's inertial navigation system (INS) uses the TACAN data to improve its accuracy and reliability. This means that the aircraft's navigation system is aided by the TACAN information, allowing for more precise positioning and navigation.Rate this question:
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- 24.
(606) Which light indicates and operator error or out-of-tolerance condition in the INS computer?
- A.
BAT.
- B.
PWR.
- C.
WARN.
- D.
ALERT.
Correct Answer
C. WARN.Explanation
The correct answer is WARN. The WARN light indicates an operator error or an out-of-tolerance condition in the INS computer. This light is designed to alert the operator to any potential issues or mistakes that may have occurred during the operation of the computer. It serves as a warning signal to prompt the operator to take corrective action or to investigate the error or condition further.Rate this question:
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- 25.
(606) What is the maximum time a fully charged battery unit can sustain INS operation?
- A.
15 minutes.
- B.
30 minutes.
- C.
1.5 hours.
- D.
2.0 hours.
Correct Answer
B. 30 minutes.Explanation
A fully charged battery unit can sustain INS (Inertial Navigation System) operation for a maximum of 30 minutes. This means that the battery can power the INS system for half an hour before it needs to be recharged or replaced. It is important to keep track of the battery life and plan accordingly to ensure uninterrupted operation of the INS system.Rate this question:
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- 26.
(606) The ATT switch position on the INS mode selector unit is used to select...
- A.
Only attitude signals.
- B.
Only heading signals.
- C.
Attitude and heading signals.
- D.
Attitude and present position.
Correct Answer
A. Only attitude signals.Explanation
The ATT switch position on the INS mode selector unit is used to select only attitude signals. This means that when the switch is set to ATT, the INS will only receive and use attitude information, such as pitch and roll, from the aircraft's sensors. It will not receive or use heading signals, present position information, or any other type of data.Rate this question:
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- 27.
(606) The INS mode selector unit BAT light illuminates if the battery unit...
- A.
Is supplying test power to the INS while in NAV mode.
- B.
Is supplying test power to the INS during alignment.
- C.
Is not charged enough to sustain INS operation.
- D.
Has been removed from the aircraft.
Correct Answer
C. Is not charged enough to sustain INS operation.Explanation
The INS mode selector unit BAT light illuminates if the battery unit is not charged enough to sustain INS operation. This means that if the battery is not sufficiently charged, it will not be able to provide the necessary power for the INS system to function properly. Therefore, the BAT light serves as a warning indicator to alert the pilot that the battery needs to be charged or replaced in order to ensure the continued operation of the INS.Rate this question:
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- 28.
(606) The most accurate inertial navigation system alignment is...
- A.
Direct navigation.
- B.
Stored heading.
- C.
Pure inertial.
- D.
Airborne.
Correct Answer
C. Pure inertial.Explanation
The most accurate inertial navigation system alignment is "pure inertial" because it relies solely on the internal sensors of the system to measure and track the aircraft's position and movement. This method does not require any external references or inputs, making it less prone to errors caused by external factors such as magnetic interference or GPS signal loss. Pure inertial alignment provides highly accurate and reliable navigation information, making it the preferred choice for precise aircraft navigation.Rate this question:
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- 29.
(607) What do global positioning system receivers have programmed into their computers telling the receiver continually where each satellite is located?
- A.
Atomic clock.
- B.
Triangulation.
- C.
Almanac.
- D.
Atoms.
Correct Answer
C. Almanac.Explanation
Global positioning system (GPS) receivers have almanacs programmed into their computers to continually determine the location of each satellite. An almanac is a set of data that includes information about the orbit and position of each satellite. By using this information, the receiver can calculate the precise location of each satellite and accurately determine its own position through triangulation. The almanac is updated periodically to ensure accuracy in satellite positioning.Rate this question:
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- 30.
(607) The process of using fixed points and their bearings to isolate a position in space is called...
- A.
Pseudo fixing.
- B.
Triangulation.
- C.
Decoding.
- D.
Shading.
Correct Answer
B. Triangulation.Explanation
Triangulation is the process of using fixed points and their bearings to isolate a position in space. It involves measuring the angles between the fixed points and the unknown position, and then using trigonometry to calculate the distance and direction of the unknown position. This method is commonly used in surveying and navigation to determine the location of objects or to create accurate maps. Pseudo fixing, decoding, and shading are not related to this process and therefore are incorrect answers.Rate this question:
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- 31.
(607) The global positioning system is a worldwide radio-navigation system with ground stations and a receiver, and is formed from a constellation of how many satellites?
- A.
16.
- B.
18.
- C.
24.
- D.
28.
Correct Answer
C. 24.Explanation
The global positioning system (GPS) is a worldwide radio-navigation system that relies on a constellation of satellites. These satellites orbit the Earth and provide signals that a GPS receiver can use to determine its location. The question asks how many satellites are in this constellation, and the correct answer is 24. This means that there are 24 satellites constantly transmitting signals that can be used by GPS receivers to calculate their position accurately.Rate this question:
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- 32.
(608) How many global position system satellites are needed to establish our lateral and longitudinal coordinates?
- A.
1.
- B.
2.
- C.
3.
- D.
4.
Correct Answer
C. 3.Explanation
To establish our lateral and longitudinal coordinates using the global position system (GPS), a minimum of three satellites is needed. This is because GPS works on a principle called trilateration, where the receiver determines its position by measuring the distance to at least three satellites. By intersecting the spheres created by these distances, the receiver can pinpoint its location. Therefore, having three satellites is necessary to accurately establish our lateral and longitudinal coordinates.Rate this question:
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- 33.
(608) How many global positioning system satellites are needed to determine aircraft altitude?
- A.
1.
- B.
2.
- C.
3.
- D.
4.
Correct Answer
D. 4.Explanation
To determine aircraft altitude using global positioning system (GPS), at least four satellites are needed. This is because GPS works on a trilateration principle, where the receiver calculates its position based on the distance from multiple satellites. By receiving signals from four satellites, the GPS receiver can accurately determine the altitude along with the latitude and longitude of the aircraft. Therefore, four GPS satellites are required to determine aircraft altitude.Rate this question:
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- 34.
(608) The global positioning system satellites and receivers are synchronized to the nanosecond by...
- A.
Carbon crystals.
- B.
Quartz crystals.
- C.
Atomic clocks.
- D.
Time warps.
Correct Answer
C. Atomic clocks.Explanation
The global positioning system satellites and receivers need to be synchronized to the nanosecond in order to accurately determine positions on Earth. Atomic clocks are the most precise timekeeping devices available, as they measure time based on the vibrations of atoms. Therefore, atomic clocks are used to synchronize the satellites and receivers, ensuring accurate and reliable positioning information.Rate this question:
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- 35.
(609) The FD/RGA dual integrated FD system is made up of dual FDs, dual angle-of-attack/RGA subsystems, and...
- A.
A directional gyroscope system.
- B.
A horizontal gyroscope package.
- C.
A comparator waring monitor.
- D.
A radio altimeter system.
Correct Answer
C. A comparator waring monitor.Explanation
The FD/RGA dual integrated FD system consists of dual FDs (Flight Directors) and dual angle-of-attack/RGA (Reference Guide Attitude) subsystems. These components provide guidance and information to the pilots for maintaining the desired attitude and flight path. The addition of a comparator warning monitor enhances the system by comparing the inputs from the FDs and RGA subsystems to detect any discrepancies or errors. This allows for early detection of any potential issues and provides a warning to the pilots, ensuring the accuracy and reliability of the flight guidance system.Rate this question:
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- 36.
(609) The dual flight director systems provide the pilot with displays of aircraft attitude, heading, and...
- A.
Airspeed.
- B.
Distance.
- C.
Altitude.
- D.
Course.
Correct Answer
D. Course.Explanation
The dual flight director systems provide the pilot with displays of aircraft attitude, heading, and course. The flight director system helps the pilot to maintain the desired aircraft trajectory by providing guidance cues on the attitude indicator and heading indicator. The course display specifically helps the pilot to stay on the desired course or track during navigation. Therefore, the correct answer is course.Rate this question:
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- 37.
(609) What is shared by both RGA subsystems of the flight director system?
- A.
An RGA switch.
- B.
An RGA computer.
- C.
A probe heater relay.
- D.
A longitudinal accelerometer.
Correct Answer
C. A probe heater relay.Explanation
Both RGA subsystems of the flight director system share a probe heater relay. This suggests that the probe heater relay is a crucial component that is required by both RGA subsystems. The probe heater relay is likely responsible for controlling the heating of the probes, which are used to measure various parameters in the aircraft.Rate this question:
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- 38.
(610) The pitch command control of the flight director system 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.
Correct Answer
D. 15 degrees up to 10 degrees down.Explanation
The pitch command control of the flight director system allows for a climb or descent angle selection ranging from 15 degrees up to 10 degrees down. This means that the system can provide guidance for climbing at angles up to 15 degrees and descending at angles up to 10 degrees.Rate this question:
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- 39.
(610) What flight director system's attitude director indicator warning flag indicates faulty command bar information?
- A.
RT.
- B.
GYRO.
- C.
SPEED.
- D.
CMPTR.
Correct Answer
D. CMPTR.Explanation
The correct answer is CMPTR. The flight director system's attitude director indicator warning flag indicates faulty command bar information when the computer (CMPTR) is not providing accurate guidance commands to the pilot. This warning flag alerts the pilot to the potential issue with the computer's commands, allowing them to take appropriate action.Rate this question:
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- 40.
(610) What is displayed on the heading marker of the flight director system's horizontal situation indicator?
- A.
Actual ground track.
- B.
Desired ground track.
- C.
Actual compass heading.
- D.
Manually selected heading.
Correct Answer
D. Manually selected heading.Explanation
The heading marker on the flight director system's horizontal situation indicator displays the manually selected heading. This means that the pilot can input a specific heading that they want the aircraft to follow, and the flight director system will provide guidance to help the pilot maintain that heading. The other options, such as actual ground track, desired ground track, and actual compass heading, are not displayed on the heading marker.Rate this question:
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- 41.
(610) With the flight director system's HSI remote heading slew switch in the DUAL position, which HSI heading marker(s) move when the pilot's heading slew control is pressed?
- A.
Pilot's only.
- B.
Pilot's and copilot's.
- C.
Pilot's and navigator's.
- D.
Copilot's and navigator's.
Correct Answer
B. Pilot's and copilot's.Explanation
When the flight director system's HSI remote heading slew switch is in the DUAL position, both the pilot's and copilot's HSI heading markers move when the pilot's heading slew control is pressed. This means that both the pilot and copilot can control and adjust the heading marker simultaneously.Rate this question:
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- 42.
(610) What flight director system component develops the lateral and veritcal signals displayed on the attitude director indicator by the command bars?
- A.
Rate of turn gyro.
- B.
Steering computer.
- C.
Heading slew control.
- D.
Majority logic comparator.
Correct Answer
B. Steering computer.Explanation
The steering computer is the flight director system component that develops the lateral and vertical signals displayed on the attitude director indicator by the command bars. It calculates and generates the necessary guidance commands based on inputs such as aircraft attitude, heading, and altitude. These commands are then displayed on the attitude director indicator to assist the pilot in maintaining the desired flight path. The rate of turn gyro measures the rate of turn of the aircraft, the heading slew control adjusts the heading bug on the compass system, and the majority logic comparator compares and selects the most reliable signals from redundant systems.Rate this question:
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- 43.
(611) In the AOA/RGA system, how many degrees of initial climbout are displayed on the attitude director indicator during takeoff with the flaps set at 30 degrees?
- A.
7 degrees.
- B.
8 degrees.
- C.
8.5 degrees.
- D.
10 degrees.
Correct Answer
B. 8 degrees.Explanation
In the AOA/RGA system, the attitude director indicator displays the degrees of initial climbout during takeoff with the flaps set at 30 degrees. The correct answer is 8 degrees, as indicated.Rate this question:
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- 44.
(611) What does the RGA computer provide to the control unit to indicate the validity of the vertical steering signal?
- A.
A steering signal.
- B.
A chassis ground.
- C.
An interlock signal.
- D.
An AOA light discreet.
Correct Answer
C. An interlock signal.Explanation
The RGA computer provides an interlock signal to the control unit to indicate the validity of the vertical steering signal. This interlock signal serves as a safety mechanism, ensuring that the control unit only receives a valid steering signal from the RGA computer. It helps prevent any potential errors or malfunctions in the steering system by confirming the reliability of the signal before it is used by the control unit.Rate this question:
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- 45.
(612) Which comparator warning monitor subsystem indicator lights when a differential error of 3 degrees pitch exists for more than two seconds between the two RGA computers?
- A.
RGA.
- B.
LOC.
- C.
RADIO ALT.
- D.
GLIDESLOPE.
Correct Answer
A. RGA.Explanation
The correct answer is RGA. RGA stands for Rate Gyro Assembly, which is a device that measures the aircraft's pitch and roll rates. In this question, the comparator warning monitor subsystem indicator lights when there is a differential error of 3 degrees pitch for more than two seconds between the two RGA computers. This means that if there is a significant difference in pitch readings between the two RGA computers, the indicator light for RGA will illuminate to alert the pilot of the error.Rate this question:
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- 46.
(613) In what FD/RGA operating mode does the roll steering computer use the heading error and bank attitude signals to compute lateral steering commands.?
- A.
HDG.
- B.
GYRO.
- C.
NAV/LOC.
- D.
APPR MAN.
Correct Answer
A. HDG.Explanation
In the HDG (heading) operating mode, the roll steering computer utilizes the heading error and bank attitude signals to calculate lateral steering commands. This means that the computer takes into account any deviation between the actual heading and the desired heading, as well as the bank angle of the aircraft, to determine the appropriate steering commands for maintaining the desired heading.Rate this question:
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- 47.
(613) In the FD/RGA system, at what altitude is glideslope extension mode initiated?
- A.
200.
- B.
500.
- C.
800.
- D.
950.
Correct Answer
A. 200.Explanation
In the FD/RGA system, glideslope extension mode is initiated at an altitude of 200.Rate this question:
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- 48.
(613) In the FD/RGA system, what mode overrides the navigation and lateral and glideslope beam sensors?
- A.
HDG.
- B.
GYRO.
- C.
NAV/LOC.
- D.
APPR MAN.
Correct Answer
D. APPR MAN.Explanation
The correct answer is APPR MAN. In the FD/RGA system, APPR MAN mode overrides the navigation and lateral and glideslope beam sensors. This mode allows the pilot to manually control the approach and landing of the aircraft, disregarding the guidance provided by the navigation and glideslope systems.Rate this question:
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- 49.
(614) Which flight control surface position indicator displays percentage of surface extension?
- A.
Flap.
- B.
Rudder.
- C.
Ailerons.
- D.
Horizontal stabilizer.
Correct Answer
A. Flap.Explanation
The correct answer is Flap. Flaps are a type of flight control surface that are located on the trailing edge of the wings. They can be extended or retracted to change the shape and surface area of the wing, which helps to increase lift and decrease stall speed during takeoff and landing. The position of the flaps is indicated by a percentage, showing how much they are extended or retracted.Rate this question:
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- 50.
(614) What type of operating power is required by a selsyn position indicating system?
- A.
26 VAC.
- B.
28 VDC.
- C.
115 VAC.
- D.
115 VDC.
Correct Answer
B. 28 VDC.Explanation
A selsyn position indicating system requires 28 VDC operating power. This means that the system operates on a direct current power supply with a voltage of 28 volts.Rate this question:
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Mar 21, 2023Quiz Edited by
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Jun 17, 2009Quiz Created by
Kotadod
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