2a952 Volume 4 Ures (2016)

92 Questions

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2a952 Volume 4 Ures (2016)


Questions and Answers
  • 1. 
    (601) The compass system is synchronized with the earth’s magnetic field by means of a
    • A. 

      Magnetic azimuth detector

    • B. 

      Power adequacy indicator

    • C. 

      Slaving amplifier

    • D. 

      Digital controller

  • 2. 
    (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

  • 3. 
    (601) Any mechanical misalignment between the magnetic azimuth detector and the longitudinal axis of the aircraft creates
    • A. 

      Meridian convergence error

    • B. 

      Transmission error

    • C. 

      Coriolis error

    • D. 

      Index error

  • 4. 
    (601) What component consists of a sensing element that contains a core assembly, excitation coil, and three secondary coils?
    • A. 

      Directional gyro

    • B. 

      Digital controller

    • C. 

      Magnetic compensator

    • D. 

      Magnetic azimuth detector

  • 5. 
    (601) A 400 Hz voltage is applied to the core assembly of the magnetic azimuth detector, what voltage is induced into the output windings?
    • A. 

      200 Hz

    • B. 

      400 Hz

    • C. 

      800 Hz

    • D. 

      1600 Hz

  • 6. 
    (601) The directional gyro provides continuous attitude and heading information throughout
    • A. 

      270 degrees of motion in two axes

    • B. 

      270 degrees of motion in three axes

    • C. 

      360 degrees of motion in two axes

    • D. 

      360 degrees of motion in three axes

  • 7. 
    (601) 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

  • 8. 
    (601) What compass mode is used in latitudes where the meridian convergence is excessive or where the earth’s magnetic field is weak?
    • A. 

      Directional gyro (DG) mode

    • B. 

      SLAVED mode

    • C. 

      Magnetic heading (MAG) mode

    • D. 

      AUTO mode

  • 9. 
    (602) 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

  • 10. 
    (602) 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

  • 11. 
    (602) Which cable is not part of the compass calibration set reel assemblies?
    • A. 

      Power cable

    • B. 

      Monitor cable

    • C. 

      Intercom cable

    • D. 

      Transmitter cable

  • 12. 
    (602) 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

  • 13. 
    (603) 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

  • 14. 
    (603) 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

  • 15. 
    (603) What commands the horizontal situation indicator (HSI) heading bug?
    • A. 

      Rate-of-turn indicator

    • B. 

      Heading slew controls

    • C. 

      Pitch command control

    • D. 

      Remote heading slew switch

  • 16. 
    (603) 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

  • 17. 
    (604) In the rotation go-around (RGA) subsystem, how many degrees of initial climbout are displayed on the attitude direction indicator (ADI) during takeoff with the flaps set at 30 degrees?
    • A. 

      7 degrees

    • B. 

      8 degrees

    • C. 

      8.5 degrees

    • D. 

      9.5 degrees

  • 18. 
    (604) Pressing the rotation go-around (RGA) 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

  • 19. 
    (604) 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
    • A. 

      80 knots

    • B. 

      90 knots

    • C. 

      100 kntos

    • D. 

      110 knots

  • 20. 
    (604) What does the rotation go-around (RGA) computer provide to the control panel to indicate the validity of the vertical steering signal?
    • A. 

      A steering signal

    • B. 

      A chassis ground

    • C. 

      An interlock signal

    • D. 

      An angle-of-attack signal

  • 21. 
    (604) 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

  • 22. 
    (604) 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

  • 23. 
    (605) 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

  • 24. 
    (605) In what flight director mode are the attitude director indicator (ADI) command bars driven out of view?
    • A. 

      Heading (HDG)

    • B. 

      GYRO

    • C. 

      Navigation/localizer (NAV/LOC)

    • D. 

      Approach/manual (APPR MAN)

  • 25. 
    (605) Switching the mode selector on the flight director control panel to the heading (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

  • 26. 
    (605) In the flight director system, the glide slope extension mode is initiated by the
    • A. 

      100 foot altitude trip voltage

    • B. 

      200 foot altitude trip voltage

    • C. 

      300 foot altitude trip voltage

    • D. 

      500 foot altitude trip voltage

  • 27. 
    (605) In the flight director system, what mode overrides the navigation (NAV) lateral and glide slope beam sensors?
    • A. 

      Rotation go-around (RGA)

    • B. 

      Navigation/localizer (NAV/LOC)

    • C. 

      Approach/manual (APPR MAN)

    • D. 

      Approach/automatic (APPR AUTO)

  • 28. 
    (606) In the inertial navigation system (INS), the navigation function is accomplished primarily through the sensing and measurement of
    • A. 

      Magnetic north

    • B. 

      Earth rotation

    • C. 

      Acceleration

    • D. 

      Gravity

  • 29. 
    (606) In the inertial navigation system (INS), what does the inertial navigation unit (INU) use to provide attitude, heading and position information for the aircraft?
    • A. 

      Two ring laser gyros and two accelerometers

    • B. 

      Three ring laser gyros and two accelerometers

    • C. 

      Two ring laser gyros and three accelerometers

    • D. 

      Three ring laser gyros and three accelerometers

  • 30. 
    (606) 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

  • 31. 
    (606) In the inertial navigation system (INS), the inertial navigation unit (INU) accelerometer pendulum moves in response to an applied
    • A. 

      Acceleration

    • B. 

      Wind speed

    • C. 

      Laser beam

    • D. 

      Frequency

  • 32. 
    (606) Which inertial navigation system (INS) component is used to control the mode of operation for its associated inertial navigation unit?
    • A. 

      Global positioning system (GPS)

    • B. 

      Inertial navigation unit (INU)

    • C. 

      Control display unit (CDU)

    • D. 

      Mode select unit (MSU)

  • 33. 
    (606) In the inertial navigation system (INS), the battery (BATT) annunciator come on whenever the battery unit voltage is less than
    • A. 

      20 VDC

    • B. 

      24 VDC

    • C. 

      26 VAC

    • D. 

      115 VAC

  • 34. 
    (606) In the inertial navigation system (INS), the battery unit consists of
    • A. 

      15 nickel-cadmium cells wired in series

    • B. 

      15 nickel-cadmium cells wired in parallel

    • C. 

      19 nickel-cadmium cells wired in series

    • D. 

      19 nickel-cadmium cells wired in parallel

  • 35. 
    (606) What is the maximum time a fully charged battery unit can sustain INS system operation?
    • A. 

      15 minutes

    • B. 

      30 minutes

    • C. 

      1.2 hours

    • D. 

      2.0 hourse

  • 36. 
    (607) Which is not a basic operating mode for the inertial navigation system (INS)?
    • A. 

      Standby

    • B. 

      Power off

    • C. 

      Pure inertial

    • D. 

      Attitude reference

  • 37. 
    (607) In the inertial navigation system (INS), what allows the insertion of data into the inertial navigation unit (INU)?
    • A. 

      Control display unit (CDU)

    • B. 

      Mode select unit (MSU)

    • C. 

      Inertial navigation unit (INU)

    • D. 

      Compass system

  • 38. 
    (607) In the inertial navigation system (INS), when will the inertial navigation unit (INU) perform a self test of its internal systems?
    • A. 

      During gyro alignment

    • B. 

      During power up sequence

    • C. 

      When navigation mode is reached

    • D. 

      When initiated on the control display unit

  • 39. 
    (607) Which is the default alignment mode for the inertial navigation system (INS)?
    • A. 

      Attitude reference

    • B. 

      Stored heading

    • C. 

      Navigation

    • D. 

      Airborne

  • 40. 
    (608) What lists the location of every satellite at any given time and is stored in the global positioning system (GPS) receiver?
    • A. 

      Almanac

    • B. 

      Atomic clock

    • C. 

      Ephemeris error

    • D. 

      Individual satellites

  • 41. 
    (608) In the global positioning system (GPS) what is the term that describes the amount of deviation by a satellite from its predetermined order?
    • A. 

      Almanac

    • B. 

      Atomic clock

    • C. 

      Ephemeris error

    • D. 

      Individual satellites

  • 42. 
    (608) The space segment of the global positioning system (GPS) consists of
    • A. 

      21 satellites in four orbital planes

    • B. 

      24 satellites in four orbital planes

    • C. 

      21 satellites in six orbital planes

    • D. 

      24 satellites in six orbital planes

  • 43. 
    (608) Which segment of the global positioning system (GPS) consists of the master control station and five unmanned monitor stations?
    • A. 

      User segment

    • B. 

      Space segment

    • C. 

      Control segment

    • D. 

      Navigation segment

  • 44. 
    (609) How many satellites are needed to establish present position only?
    • A. 

      1

    • B. 

      2

    • C. 

      3

    • D. 

      4

  • 45. 
    (609) How many satellites are needed to determine aircraft altitude?
    • A. 

      1

    • B. 

      2

    • C. 

      3

    • D. 

      4

  • 46. 
    (609) Satellites and receivers are synchronized to the nanosecond, this accuracy is performed by
    • A. 

      Carbon crystals

    • B. 

      Quartz crystals

    • C. 

      Atomic clocks

    • D. 

      Time warps

  • 47. 
    (610) 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

  • 48. 
    (610) Exhaust gas temperature thermocouple wiring is equal in length and installed in
    • A. 

      Oil

    • B. 

      Fuel

    • C. 

      Series

    • D. 

      Parallel

  • 49. 
    (611) What type of mechanical sensing device is contained in the engine pressure ratio (EPR) transducer?
    • A. 

      Dual bellows

    • B. 

      Variable resistor

    • C. 

      Variable capacitor

    • D. 

      Dual Bourdon tube

  • 50. 
    (611) 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

  • 51. 
    (611) Instead of using a dual bellows sensing element, the digital engine pressure ratio transducer uses a
    • A. 

      Piezocapacitive temperature sensing element

    • B. 

      Piezoresistive temperature sensing element

    • C. 

      Piezocapacitive pressure sensing element

    • D. 

      Piezoresistive pressure sensing element

  • 52. 
    (611) What engine pressure ratio indicates exhaust pressure is equal to inlet pressure? 
    • A. 

      0.1

    • B. 

      1.0

    • C. 

      2.0

    • D. 

      4.1

  • 53. 
    (612) What types of sensing elements are used in the oil pressure transmitter?
    • A. 

      Magnets

    • B. 

      Aneroids

    • C. 

      Dual bellows

    • D. 

      Bourdon tubes

  • 54. 
    (612) The oil pressure transmitter vented Bourdon tube is vented to the
    • A. 

      Atmosphere

    • B. 

      Case

    • C. 

      Fuel

    • D. 

      Oil

  • 55. 
    (612) The only moving part in the oil pressure indicator is the
    • A. 

      Synchro receiver

    • B. 

      Bourdon tube

    • C. 

      Sector gear

    • D. 

      Rotor

  • 56. 
    (612) The oil pressure indicator displays oil pressure from
    • A. 

      0 to 100 PSI

    • B. 

      0 to 200 PSI

    • C. 

      15 to 100 PSI

    • D. 

      15 to 200 PSI

  • 57. 
    (613) What is the speed of the fuel flow transmitter motor?
    • A. 

      50 RPM

    • B. 

      100 RPM

    • C. 

      150 RPM

    • D. 

      1000 RPM

  • 58. 
    (613) The deflection of the impeller relative to the drum within the fuel flow transmitter is measured by
    • A. 

      Magnets

    • B. 

      Thermocouples

    • C. 

      A synchro of a rotor

    • D. 

      A wiper arm of a potentionmeter

  • 59. 
    (613) Where does the low frequency power that drives the fuel flow transmitter motor originate?
    • A. 

      Magnets

    • B. 

      Fuel flow indicator

    • C. 

      Fuel flow electronic package

    • D. 

      Total fuel remaining indicator

  • 60. 
    (613) The four tape fuel flow indicator provides a readout of
    • A. 

      Engine fuel flow rate in pounds per hour

    • B. 

      Engine fuel flow rate in ounces per hour

    • C. 

      Engine fuel used in pounds

    • D. 

      Engine fuel used in ounces

  • 61. 
    (613) In the fuel flow system, the indicator has failure monitor circuits that sense all of the following except
    • A. 

      Motor electrical failure

    • B. 

      Loss of primary power

    • C. 

      An open Lo-z

    • D. 

      Signal loss

  • 62. 
    (614) What causes a signal to be induced in the N1 tachometer transmitter sensor coil?
    • A. 

      Engine fan blade passing by the magnetic field of the N1 tachometer transmitter

    • B. 

      Engine fan blade passing by the magnetic field of the N2 tachometer transmitter

    • C. 

      Engine fan blade passing by the limit index of the N1 tachometer transmitter

    • D. 

      Engine fan blade passing by the limit index of the N2 tachometer transmitter

  • 63. 
    (614) The N2 tachometer transmitter is an alternating current generator whose frequency is directly proportional to
    • A. 

      Rotor speed

    • B. 

      Stator speed

    • C. 

      Ground speed

    • D. 

      Maximum speed

  • 64. 
    (615) The torquemeter assembly consists of
    • A. 

      Three concentric shaft assemblies

    • B. 

      Two concentric shaft assemblies

    • C. 

      Three pickoff coils

    • D. 

      Two pickoff coils

  • 65. 
    (615) From what range does the torquemeter indicator display torque values?
    • A. 

      –4,000 inch pounds to 24,000 inch pounds

    • B. 

      –4,000 inch pounds to 28,000 inch pounds

    • C. 

      –4,000 foot pounds to 24,000 foot pounds

    • D. 

      –4,000 foot pounds to 28,000 foot pounds

  • 66. 
    (615) When are the flange teeth on the torquemeter assembly in alignment?
    • A. 

      Zero torque

    • B. 

      Positive torque

    • C. 

      Negative torque

    • D. 

      Feedback torque

  • 67. 
    (615) When positive torque is applied to the torquemeter assembly, the
    • A. 

      Feedback pulse leads the torque pulse

    • B. 

      Reference pulse leads the torque pulse

    • C. 

      Torque pulse leads the feedback the pulse

    • D. 

      Torque pulse leads the reference the pulse

  • 68. 
    (615) When negative torque is applied to the torquemeter assembly, the
    • A. 

      Feedback pulse leads the torque pulse

    • B. 

      Reference pulse leads the torque pulse

    • C. 

      Torque pulse leads the feedback pulse

    • D. 

      Torque pulse leads the reference pulse

  • 69. 
    (616) How many magnetic reed switches are connected to the oil quantity transmitter’s resistance element?
    • A. 

      7

    • B. 

      8

    • C. 

      9

    • D. 

      10

  • 70. 
    (616) What does the oil quantity transmitter float assembly follow?
    • A. 

      Power level

    • B. 

      Fluid level

    • C. 

      Amplifier

    • D. 

      Torquer

  • 71. 
    (616) The oil quantity indicator pointer is directly connected to the
    • A. 

      Rotor shaft of the torquer

    • B. 

      Rotor shaft of the amplifier

    • C. 

      Power supply of the indicator

    • D. 

      Resistor element of the transmitter

  • 72. 
    (616) The output of the oil quantity indicator amplifier is applied to the
    • A. 

      Resistance element

    • B. 

      Reed switch

    • C. 

      Torquer

    • D. 

      Float

  • 73. 
    (617) Each fuel quantity probe consists of two concentric tubes forming an inner and outer
    • A. 

      Potentiometer

    • B. 

      Electrode

    • C. 

      Resistor

    • D. 

      Float

  • 74. 
    (617) Fuel tanks closer to the wing tips contain more fuel quantity probes to compensate for
    • A. 

      Greater attitude changes during aircraft roll

    • B. 

      Smaller attitude changes during aircraft roll

    • C. 

      Greater attitude changes during aircraft pitch

    • D. 

      Smaller attitude changes during aircraft pitch

  • 75. 
    (617) What fuel quantity indicating system component accounts for changes in the density of the fuel?
    • A. 

      Total fuel quantity indicator

    • B. 

      Fuel quantity indicator

    • C. 

      Compensator probe

    • D. 

      Tank probe

  • 76. 
    (617) What unshielded wire is used as a power lead in the fuel quantity indicating system?
    • A. 

      Lo-Z

    • B. 

      Hi-Z

    • C. 

      Kapton

    • D. 

      Thermocouple

  • 77. 
    (617) What shielded wire is used as a signal lead in the fuel quantity indicating system?
    • A. 

      Lo-Z

    • B. 

      Hi-Z

    • C. 

      Kapton

    • D. 

      Thermocouple

  • 78. 
    (617) What fuel quantity indicating system component supplies excitation voltage to the fuel probes?
    • A. 

      Total fuel quantity indicator

    • B. 

      Fuel quantity indicator

    • C. 

      Ratio unit

    • D. 

      Amplifier

  • 79. 
    (617) What fuel quantity indicator component moves the indicator pointer?
    • A. 

      Rebalance potentiometer

    • B. 

      Reference capacitor

    • C. 

      Servo motor

    • D. 

      Amplifier

  • 80. 
    (617) What measurement does the total fuel quantity indicator use to displays the total amount of fuel onboard the aircraft?
    • A. 

      Pints

    • B. 

      Quarts

    • C. 

      Gallons

    • D. 

      Pounds

  • 81. 
    (617) Outputs from the fuel quantity system bridge circuit reference leg and variable leg are
    • A. 

      90 degrees out-of-phase with each other

    • B. 

      180 degrees out-of-phase with each other

    • C. 

      270 degrees out-of-phase with each other

    • D. 

      360 degrees out-of-phase with each other

  • 82. 
    (617) When fuel is added to the tank, fuel quantity probe capacitance
    • A. 

      Increases and current decreases

    • B. 

      Increases and current increases

    • C. 

      Decreases and current decreases

    • D. 

      Decreases and current increases

  • 83. 
    (617) When fuel is being used, fuel quantity probe capacitance
    • A. 

      Increases and current decreases

    • B. 

      Increases and current increases

    • C. 

      Decreases and current increases

    • D. 

      Decreases and current decreases

  • 84. 
    (617) What type of fuel quantity indicating system malfunction causes an indicator pointer to continuously rotate clockwise?
    • A. 

      Open Lo-Z

    • B. 

      Open Hi-Z

    • C. 

      Open compensator

    • D. 

      Shorted compensator

  • 85. 
    (617) When water contaminates the fuel at the fuel quantity probe, the dielectric constant increases,
    • A. 

      Capacitance increases, and current increases

    • B. 

      Capacitance increases, and current decreases

    • C. 

      Capacitance decreases, and current increases

    • D. 

      Capacitance decreases, and current decreases

  • 86. 
    (618) How is the PSD60–1AF fuel quantity test set powered?
    • A. 

      Rechargeable batteries

    • B. 

      Alternating current

    • C. 

      Alkaline batteries

    • D. 

      Aircraft power

  • 87. 
    (618) Which PSD60–1AF fuel quantity test set function switch position is used to select measurement of TANK UNIT parameters?
    • A. 

      SIM ONLY

    • B. 

      MEASURE INT

    • C. 

      MEASURE EXT

    • D. 

      AIRCRAFT ONLY

  • 88. 
    (618) What is the purpose of the PSD60–1AF fuel quantity test set vernier dials?
    • A. 

      Coarse adjustments of simulation values

    • B. 

      Fine adjustments of simulation values

    • C. 

      Coarse adjustments of power values

    • D. 

      Fine adjustments of ground values

  • 89. 
    (618) When using the PSD60–1AF, voltage checks between the test set chassis and ground
    • A. 

      Are not required

    • B. 

      Are always required

    • C. 

      Ensure accurate measurements

    • D. 

      Are required for resistance checks

  • 90. 
    (619) The bonding meter battery capacity is adequate for
    • A. 

      2 hours of continuous operation

    • B. 

      6 hours of continuous operation

    • C. 

      8 hours of continuous operation

    • D. 

      20 hours of continuous operation

  • 91. 
    (619) On a range setting of two milliohms, from what range does the bonding meter measure?
    • A. 

      0 to 1.999 milliohms

    • B. 

      0 to 19.99 milliohms

    • C. 

      19 to 199.9 milliohms

    • D. 

      199 to 1999 milliohms

  • 92. 
    (619) What is the accuracy of the bonding meter?
    • A. 

      +/–1% of the reading

    • B. 

      +/–2% of the reading

    • C. 

      +/–10% of the reading

    • D. 

      +/–20% of the reading