2A533B Volume 4

1. The global positioning system satellites and receivers are synchronized to the nanosecond by

Carbon crystals

Quartz crystals

Atomic clocks

Time warps

2. The process of using fixed points and their bearings to isolate a position in space is called

Pseudo fixing

Triangulation

Decoding

Shading

3. 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

16

18

24

28

4. Which RGA interface logic unit test switch must be activated to allow go-around mode testing on the ground

X MON

FLP TEST

WOW TEST

TEST RESET

5. Neutralizing or weakening the permanent magnetic field that exists around an aircraft is called

Demoding

Despoiling

Defoliating

Degaussing

6. The shielded wire used as a signal lead is called

Hi-z

Lo-z

Return

Kapton

7. How many global position system satellites are needed to establish our lateral and longitudinal coordinates

1

2

3

4

8. Which flight control surface position indicator displays percentage of surface extension

Flap

Rudder

Ailerons

Horizontal stabilizer

9. When the DC fuel quantity indicating system self-test switch is pressed, the indicators should read

50 percent (+-2 percent) full

75 percent (+-2 percent) full

98 percent (+-2 percent) full

100 percent (+-2 percent) full

10. With the flight director systems HSI remote heading slew switch in the DUAL position, which HSI heading marker(s) move when the pilots heading slew control is pressed?

Pilot's only

Pilot's and copilots

Pilots and navigators

Copilots and navigators

11. The INS mode selector unit BAT light illuminates if the battery unit

Is supplying test power to the INS while in NAV mode

Is supplying test power to the INS during alignment

Is not charged enough to sustain INS operation

Has been removed from the aircraft

12. What do global positioning system receivers have programmed into their computers telling the receiver continually where each satellite is located

Atomic clock

Triangulation

Almanac

Atoms

13. The three attitude heading reference system heading modes of operation are slave,

DG, and compass

Coriolis, and compass

Coriolis, and azimuth

DG, and azimuth

14. The most accurate inertial navigation system alignment is

Direct navigation

Stored heading

Pure inertial

Airborne

15. How many global position system satellites are needed to determine aircraft altitude

1

2

3

4

16. The fuel flow transmitter motor drives the impeller at a

Constant 60 RPM

Constant 50 RPM

Variable 60 RPM

Variable 50 RPM

17. On the vertical scale fuel flow indicator, each numbered increment is read as

Pounds per hour x 1000

Gallons per hour x 1000

Pounds per minute x 100

Gallons per minute x 100

18. What types of gyros are used in the attitude heading reference system

Two vertical gyros

Two direction gyros

One vertical gyro and one directional gyro

One horizontal gyro and one vertical gyro

19. The amount of current produced when the hot junction in the vertical scale exhause gas temperature indicating system is heated is dependent on the difference in temperature between the

Hot and cold junctions

AC and DC generators

Indicator and thermometer

Wiring and ambient temperature

20. The unshielded wire used as a power lead is called

Hi-z

Lo-z

Return

Kapton

21. Near the equator the lines of magnetic force are

Perpendicular to the earth's surface

Perpendicular to the coriolis field

Parallel to the earths surface

Parallel to the coriolis field

22. Which INS unit servers as the communication link between the pilot and the INU digital computer

Mode selector unit

Control display unit

Copilot's control unit

Navigation selector panel

23. Which INS control display unit light illuminates approximately two minutes before reaching a waypoint during flight

BAT

PWR

WARN

ALERT

24. Which fuel quantity tester is approved as safe for use with fuel in the tank

GTF-6

TTU-23

TTU-27E

PSD60-1AF

25. The vertical scale tachometer indicating system monitors the speed of which two engine compressors

N1 (low-speed) and N2(low speed)

N1 (low speed) and N2 (high speed)

N1 (high speed) and N2 (low speed)

N1 (high speed) and N2 (high speed)

26. N1 and N2 RPM tapes indicate a percentage of RPM from 0 to

95

100

110

115

27. The purpose of the cold junction compensator in the vertical scale exhause gas temperature indicating system is to compensate for

Noise from the thermocouples

Changes in exhause temperature

Changes in ambient temperature

Dielectric loss in transmission lines

28. The torquemeter assembly consists of a torquemeter housing assembly, torquemeter pickup assembly, and

A flange-shaped flux resistor

One concentric shaft assembly

Two concentric shaft assemblies

Three concentric shaft assemblies

29. What are the two mechanical adjustments on the resistance liquid quantity indicating system

Centering and maximum

Centering and range

Full and empty

Full and null

30. The three operational modes as selected on the fuel center of gravity management systems panel are OPT CRUISE,

FUEL and CG

MAC and EMP

NORM and SET

NORM and EMP

31. With an input frequency of 400 Hz what is the frequency of the magnetic azimuth detector output

60 hz

200 hz

400 hz

800 hz

32. What is the maximum time a fully charged battery unit can sustain INS operation?

15 minutes

30 minutes

1.5 hours

2.0 hours

33. The tachometer generator most commonly used with vertical scale revolutions per minute indicating systems contains a

3 pole permanent magnet rotor and a 2 phase stator

3 pole permanent magnet rotor and a 3 phase stator

2 pole permanent magnet rotor and a 3 phase stator

2 pole permanent magnet rotor and a 2 phase stator

34. After the torquemeter indicator is adjusted you must return the switch on the back of the indicator to what position

A

B

F

R

35. The DC fuel quantity indicating system uses a compensation capacitor to correct for variations in

Fuel level

Fuel density

Aircraft attitude

Atmospheric pressure

36. The attitude heading reference system DG pitch gimbal is aligned with and continuously follows the

VG pitch gimbal

VG inner roll gimbal

DG leveling gimbal

DG leveling sensor

37. What happens to the output of a fuel quantity probe as the dielectric constant of the fuel increases?

Capacitance increases, capacitive reactance increases, and current increases

Capacitance increases, capacitive reactance decreases, and current increases

Capacitance decreases, capacitive reactance increases, and current decreases

Capacitance decreases, capacitive reactance decreases, and current decreases

38. The telescope on the magnetic field monitor is

40-power and rotates 270 degrees

40-power and rotates 360 degrees

22-power and rotates 270 degrees

22-power and rotates 360 degrees

39. Which light indicates an operator error or out-of-tolerance condition in the INS computer?

BAT

PWR

WARN

ALERT

40. Before you can calibrate the torquemeter indicating system, you must obtain

Air temperature and hydraulic temperature

Oil temperature and hydraulic temperature

Air temperature and barometric temperature

Oil temperature and barometric temperature

41. The AHRS cuts off slaving of the AHRS to magnetic heading when a fore-aft acceleration of

1.736-g or a turn rate of 8 degrees per minute is exceeded

1.736-g or a turn rate of 5 degrees per minute is exceeded

0.055-g or a turn rate of 8 degrees per minute is exceeded

0.055-g or a turn rate of 5 degrees per minute is exceeded

42. The ATT switch position on the INS mode selector unit is used to select

Only attitude signals

Only heading signals

Attitude and heading signals

Attitude and persent position

43. What flight director system's attitude director indicator warning flag indicated faulty command bar information

RT

GYRO

SPEED

CMPTR

44. What mode is entered when both intermediate devices expereince a signal conditioning processor test failure

Throughput

Output

FAIL

EGO

45. The inertial navigation system operates as a self-contained system, but can be updated by

VOR/ILS, STS, or manually.

TACAN, SKE, or manually

VOR/ILS, SKE, or manually

TACAN, STS, or manually

46. What does the RGA computer provide to the control unit to indicate the validity of the vertical steering signal

A sterring signal

A chassis ground

An interlock signal

An AOA light discreet

47. What positions the tape and moves the rotor of the control transformer in the engine pressure ration indicator

Discriminator

Servomotor

Amplifier

Geartrain

48. The torquemeter indicator displays torque value in

Inch-pounds from -4,000 to 24,000

Inch-pounds from -4,000 to 28,000

Foot-pounds from -4,000 to 24,000

Foot-pounds from -4,000 to 28,000

49. The FD/RGA dual integrated FD system is made up of dual FDs, dual angle-of-attack/RGA subsystems, and

An directional gyroscope system

A horizontal gyroscope package

A comparator warning monitor

A radio altimeter system

50. The DC fuel quantity indicating system does not need coaxial cables between the probes and indicator because the

Positive probe output is grounded

Probe diodes filter out any stray capacitance

DC current sensor cannot sense stray capacitance

Probe high frequency output is not susceptible to interference

51. Which device on the sensor-driven N1 RPM indicator represents the maximum achieved RPM during an overspeed condition

N1 maximum limit index

N1 maximum pointer

Drum counter

N1 Pointer

52. Instead of using a dual bellows sensing element, the digital engine pressure ratio transducer uses a

Piezocapacitive temperature converter

Piezoresistive pressure sensing element

Piezocapacitive pressure sensing element

Piezoresistive temperature sensing element

53. The DC fuel quantity indicating system is less susceptible to inaccuracies caused by the fuel contamination because of higher frequency probe excitation and

The use of longer tubes

The use of shorter tubes

Less space between the tubes

More space between the tubes

54. Which magnetic compass error occurs due to magnetism within the aircraft

Interference

Vibration

Deviation

Variation

55. The magnitude of the coriolis error signal depends on the aircraft speed, aircraft heading,

Rotation of the earth, and geographic longitude

Rotation of the earth, and geographic latitude

Aircraft attitude, and geographic longitude

Aircraft attitude, and geographic latitude

56. What is used to develop the single-cycle error compensation signal in the attitude heading reference synchro system

Synchros

Resolvers

Differentials

Variable resistors

57. The MC-200 electronics group consists of a control console, magnetic field monitor,

Turntable, and compass adapter box

Tripods and compass adapter box

Turntable, and alignment tool kit

Tripods, and alignment tool kit

58. What is displayed on the heading marker of the flight director systems horizontal situation indicator

Actual ground track

Desired ground track

Actual compass heading

Manually selected heading

59. How accurately the selsyn posion indicator rotor follows the transmitter depends upon the

Amplitude of the applied voltage

Frequency of the applied voltage

Spacing of the coils and taps

Strength of the rotor magnet

60. The BIT is initiated by rotating a small screw on the front of the N1 revolutions per minute indicator

90 degrees clockwise

45 degrees clockwise

90 degrees counter clockwise

45 degrees counterclockwise

61. What type of mechanical sensing device is contained in the vertical scale analog engine pressure ratio transducer

Dual bellows

Variable resistor

Variable capacitor

Dual bourdon tube

62. The only moving part in the oil pressure indicator is the

Calibrated hairspring

Bourdon tube

Limit gear

Rotor

63. Any misalignment between the magnetic azimuth detector and the longitudinal axis of the aircraft creates

A coriolis effect error

A transmission error

A hard iron error

An index error

64. The attitude heading reference system requires input power consisting of 115-vac, 400 hz, 3 phase aircraft power and

26 VAC, 60-hz single phase power for excitation

26 VDC 60 hz single phase power for excitation

26 VAC 400 hz single phase power for excitation

26 VDC 400 HZ single phase power for excitation

65. The navigation function is accomplished primarily through the sensing and measurement of

Magnetic north

Earth rotation

Acceleration

Gravity

66. 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?

RGA

LOC

RADIO ALT

GLIDESLOPE

67. In the FD/RGA system, what mode overrides the navigation lateral and glideslope beam sensors?

HDG

GYRO

NAV/LOC

APPR MAN

68. What components eliminate the requirement to have numerous fuel probes in the fuel tanks

Signal convertors

Data processors

Attitude sensors

Fuel sensors

69. Which error is due primarily to an electrical imbalance in the windings of the magnetic azimuth detector

Coriolis effect error

Transmission error

Hard iron error

Index error

70. 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

7

8

8.5

10

71. In the FD/RGA system, at what altitude is glideslope extension mode initiated

200

500

800

950

72. Which INS submode enables aided inertial operation using TACAN data

0

2

4

5

73. What is shared by both RGA subsystems of the flight director system

An RGA switch

An RGA computer

A probe heater relay

A longitudinal accelerometer

74. The source of the erection signal for the vg pitch gimbal of the attitude heading reference system is

A fluid type sensor

The light erection sensor

The VG pitch gimbal synchro

The directional gyroscope pitch gimbal synchro

75. What is used only during the field certification and calibration check?

Compass rose adapter box swing assembly

Magnetics azimuth reference detector

Magnetic field monitor

Control console

76. The dual flight director systems provide the pilot with displays of aircraft attitude, heading, and

Airspeed

Distance

Altitude

Course

77. What flight director system component develops the lateral and vertical signals displayed on the attitude director indicator by the command bars?

Rate of turn gyro

Sterring computer

Heading slew control

Majority logic comparator

78. How many degrees apart are the wipers of the selsyn transmitter positioned

60

90

120

180

79. In what FD/RGA operating mode does the roll steering computer use the heading error and bank attitude signals to compute lateral steering commands

HDG

GYRO

NAV/LOC

APPR MAN

80. Which INS control display unit right-hand data display digits display an action code when there is a system failure

1 and 2

2 and 3

1 and 4

2 and 4

81. The four channels of the comparator warning monitor compare the dual outputs of the compass, glideslope, localizer, and

High-range altimeter systems

Low-range altimeter systems

AOA systems

Autoland systems

82. The serial number on the MC-2000 electronics group control console must match the serial number on the

Cable

Turntable

Compass adapter box

Magnetic field monitor

83. In coarse level (state 8), the inertial navigation system platform gimbals are aligned to

Magnetic north

Local vertical

Aircraft axes

True north

84. What type of operating power is required by a selsyn position indicating system?

26 VAC

28 VDC

115 VAC

115 VDC

85. Which malfunction would cause an exhaust gas temperature indicator to read off scale high

Feedback signal from the indicator to the converter

AC signal from the converter to the indicator is lost

AC signal from the indicator to the converter is lost

Feedback signal from the engine probe is lost

86. An open compensator in the fuel quantity idicating system cause the

Reference leg to decrease

Reference leg to increase

Variable leg to decrease

Variable leg to increase

87. What indication is displayed on the oil pressure indicator when there is an open rotor lead in the transmitter

Inoperative

Erratic

High

Low

88. What indication is displayed on the oil pressure indicator when the transmitter vent bourdon tube has a leak

Inoperative

Erratic

High

Low

89. What AOA/RGA system component averages the AOA signals?

An RGA computer

Sterring computer

Instrument amplifier

RGA interface logic unit

90. In what FD/RGA operating mode are the attitude director indicators command bars driven out of view?

HDG

GYRO

NAV/LOC

APPR MAN

91. The pitch command control of the flight director system selects a climb or descent angle from

20 degrees up to 5 degrees down

15 degrees up to 5 degrees down

20 degrees up to 10 degrees down

15 degrees up to 10 degrees down

2a533b Volume 4

1. The global positioning system satellites and receivers are synchronized to the nanosecond by

2.

What first name or nickname would you like us to use?

2. The process of using fixed points and their bearings to isolate a position in space is called

3. 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

4. Which RGA interface logic unit test switch must be activated to allow go-around mode testing on the ground

5. Neutralizing or weakening the permanent magnetic field that exists around an aircraft is called

6. The shielded wire used as a signal lead is called

7. How many global position system satellites are needed to establish our lateral and longitudinal coordinates

8. Which flight control surface position indicator displays percentage of surface extension

9. When the DC fuel quantity indicating system self-test switch is pressed, the indicators should read

10. With the flight director systems HSI remote heading slew switch in the DUAL position, which HSI heading marker(s) move when the pilots heading slew control is pressed?

11. The INS mode selector unit BAT light illuminates if the battery unit

12. What do global positioning system receivers have programmed into their computers telling the receiver continually where each satellite is located

13. The three attitude heading reference system heading modes of operation are slave,

14. The most accurate inertial navigation system alignment is

15. How many global position system satellites are needed to determine aircraft altitude

16. The fuel flow transmitter motor drives the impeller at a

17. On the vertical scale fuel flow indicator, each numbered increment is read as

18. What types of gyros are used in the attitude heading reference system

19. The amount of current produced when the hot junction in the vertical scale exhause gas temperature indicating system is heated is dependent on the difference in temperature between the

20. The unshielded wire used as a power lead is called

21. Near the equator the lines of magnetic force are

22. Which INS unit servers as the communication link between the pilot and the INU digital computer

23. Which INS control display unit light illuminates approximately two minutes before reaching a waypoint during flight

24. Which fuel quantity tester is approved as safe for use with fuel in the tank

25. The vertical scale tachometer indicating system monitors the speed of which two engine compressors

26. N1 and N2 RPM tapes indicate a percentage of RPM from 0 to

27. The purpose of the cold junction compensator in the vertical scale exhause gas temperature indicating system is to compensate for

28. The torquemeter assembly consists of a torquemeter housing assembly, torquemeter pickup assembly, and

29. What are the two mechanical adjustments on the resistance liquid quantity indicating system

30. The three operational modes as selected on the fuel center of gravity management systems panel are OPT CRUISE,

31. With an input frequency of 400 Hz what is the frequency of the magnetic azimuth detector output

32. What is the maximum time a fully charged battery unit can sustain INS operation?

33. The tachometer generator most commonly used with vertical scale revolutions per minute indicating systems contains a

34. After the torquemeter indicator is adjusted you must return the switch on the back of the indicator to what position

35. The DC fuel quantity indicating system uses a compensation capacitor to correct for variations in

36. The attitude heading reference system DG pitch gimbal is aligned with and continuously follows the

37. What happens to the output of a fuel quantity probe as the dielectric constant of the fuel increases?

38. The telescope on the magnetic field monitor is

39. Which light indicates an operator error or out-of-tolerance condition in the INS computer?

40. Before you can calibrate the torquemeter indicating system, you must obtain

41. The AHRS cuts off slaving of the AHRS to magnetic heading when a fore-aft acceleration of

42. The ATT switch position on the INS mode selector unit is used to select

43. What flight director system's attitude director indicator warning flag indicated faulty command bar information

44. What mode is entered when both intermediate devices expereince a signal conditioning processor test failure

45. The inertial navigation system operates as a self-contained system, but can be updated by

46. What does the RGA computer provide to the control unit to indicate the validity of the vertical steering signal

47. What positions the tape and moves the rotor of the control transformer in the engine pressure ration indicator

48. The torquemeter indicator displays torque value in

49. The FD/RGA dual integrated FD system is made up of dual FDs, dual angle-of-attack/RGA subsystems, and

50. The DC fuel quantity indicating system does not need coaxial cables between the probes and indicator because the

51. Which device on the sensor-driven N1 RPM indicator represents the maximum achieved RPM during an overspeed condition

52. Instead of using a dual bellows sensing element, the digital engine pressure ratio transducer uses a

53. The DC fuel quantity indicating system is less susceptible to inaccuracies caused by the fuel contamination because of higher frequency probe excitation and

54. Which magnetic compass error occurs due to magnetism within the aircraft

55. The magnitude of the coriolis error signal depends on the aircraft speed, aircraft heading,

56. What is used to develop the single-cycle error compensation signal in the attitude heading reference synchro system

57. The MC-200 electronics group consists of a control console, magnetic field monitor,

58. What is displayed on the heading marker of the flight director systems horizontal situation indicator

59. How accurately the selsyn posion indicator rotor follows the transmitter depends upon the

60. The BIT is initiated by rotating a small screw on the front of the N1 revolutions per minute indicator

61. What type of mechanical sensing device is contained in the vertical scale analog engine pressure ratio transducer

62. The only moving part in the oil pressure indicator is the

63. Any misalignment between the magnetic azimuth detector and the longitudinal axis of the aircraft creates

64. The attitude heading reference system requires input power consisting of 115-vac, 400 hz, 3 phase aircraft power and

65. The navigation function is accomplished primarily through the sensing and measurement of

66. 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?

67. In the FD/RGA system, what mode overrides the navigation lateral and glideslope beam sensors?

68. What components eliminate the requirement to have numerous fuel probes in the fuel tanks

69. Which error is due primarily to an electrical imbalance in the windings of the magnetic azimuth detector

70. 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

71. In the FD/RGA system, at what altitude is glideslope extension mode initiated

72. Which INS submode enables aided inertial operation using TACAN data

73. What is shared by both RGA subsystems of the flight director system

74. The source of the erection signal for the vg pitch gimbal of the attitude heading reference system is

75. What is used only during the field certification and calibration check?

76. The dual flight director systems provide the pilot with displays of aircraft attitude, heading, and

77. What flight director system component develops the lateral and vertical signals displayed on the attitude director indicator by the command bars?