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1) Under normal operating conditions, when an aircraft is in a banked turn, the rate-of-turn indicator is a valuable gyroscopic flight control instrument. When it is associated with an attitude indicator it indicates :
the angular velocity of the aircraft about the yaw axis
the bank of the aircraft
the direction of the aircraft turn
the angular velocity of the aircraft about the real vertical
The combination of correct statements is:
A) 3, 4
B) 1, 2
C) 2, 4
D) 1, 3

2) Inside an artificial horizon:
A) the rotor axis is kept level by a calibrated spring attached to the outer ring and the instrument case.
B) the inner ring is tied to the vertical by a control system.
C) there is only one gimbal ring.
D) the inner ring is pivoted laterally inside the outer ring and the outer ring is pivoted longitudinally inside the case.

3) The fundamental difference between an INS and an IRS is that:
A) The IRS is a strap down system with 3 accelerometers mounted 90º to each other
B) The INS is a strap down system with 2 accelerometers mounted 90º to each other
C) The INS is a strap down system with 3 accelerometers mounted 90º to each other
D) The IRS is a strap down system with 2 accelerometers mounted 90º to each other

4) The purpose of the flux-valve is:
A) to measure the strength of the earth's magnetic field.
B) to provide flux for the automatic slaving system.
C) to align the spokes with the earth's magnetic field in order to get maximum voltage from the pick-up coils.
D) to sense the direction of the earth's magnetic field relative to the airplane.

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4) The purpose of the flux-valve is:
A) to measure the strength of the earth's magnetic field.
B) to provide flux for the automatic slaving system.
C) to align the spokes with the earth's magnetic field in order to get maximum voltage from the pick-up coils.
D) to sense the direction of the earth's magnetic field relative to the airplane.

5) In a left turn, the ball of the turn co-ordinator is out to the right, what corrective action is required?
A) more left rudder.
B) decrease elevator pitch.
C) more right bank.
D) more left bank.

6) A DGI has:
A) one degree of freedom & a vertical spin axis.
B) two degrees of freedom & a horizontal spin axis.
C) one degree of freedom & a horizontal spin axis.
D) two degrees of freedom & a vertical spin axis.

7) The case of an air driven turn and balance indicator is leaking. A rate 1 turn of 360° will take:
A) Less than two minutes
B) More than two minutes
C) None of the above
D) Two minutes exactly

8) In a Gyro magnetic Compass the flux gate transmits information to the:
A) heading indicator.
B) amplifier.
C) erecting system.
D) error detector.

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9) Typical directional gyro indicator errors are:
A) random wander, gimballing errors and apparent wander due to earth's rotation.
B) gimballing errors, position error and friction error.
C) instrument error, synchro error and wandering errors.
D) parallax errors and gimballing errors.

10) The flux valve in a RIMC:
A) is supplied with AC current.
B) is fed with DC current.
C) is made of hard-iron magnetic steel.
D) has its own self exciter unit.

11) (Refer to figure 022-09)�The attached diagram shows a gyro-stabilized platform. 1 is a .... gyro gimbal and 2 is a .... gyro gimbal.
A) ROLL ; PITCH
B) PITCH ; YAW
C) ROLL ; YAW
D) PITCH ; ROLL

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12) The sustained oscillation in the Ring Laser Gyro (RLG) is initially caused by:
A) the spontaneous return of photons to a higher energy level, which in turn produces, excited neon atoms.
B) the corner mirrors, which reflect the radiation energy, back to the photons.
C) the gas (or plasma) inside the triangular cavity is ionised by the voltage, causing helium atoms to collide with and transfer energy to the neon atoms.
D) the pressure fluctuation in the high pressure mixture of helium and neon gases in the triangular cavity.

13) A tied gyro has .... (i) planes of freedom and is always controlled in .... (ii) of these planes by .... (iii):
A) (i) 3 (ii) at least one (iii) an external force
B) (i) 2 (ii) both (iii) gravity
C) (i) 3 (ii) only one (iii) gravity
D) (i) 3 (ii) both (iii) an external force

14) What angle of bank should you adopt on the attitude indicator for a standard rate (rate 1) turn while flying at an IAS of 130 Kt?
A) 30°
B) 15°
C) 10°
D) 20°

15) What indications should you get from the turn-and-slip indicator during taxi?
A) the ball stays fixed in the centre position during the turn, and the needle deflects in the opposite direction of the turn
B) the ball stays fixed in the centre position during the turn, and the needle deflects in the direction of the turn
C) the ball moves freely opposite the turn, and the needle deflects in the direction of the turn
D) the ball moves freely in the direction of the turn, and the needle deflects in the opposite direction of the turn

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16) The purpose of the slaving torque motor is:
A) to produce a precessive force in order to align the gyro with the earth's magnetic field
B) to produce a precessive force in order to align the gyro with the vertical plane
C) to take inputs from the flux valve and apply appropriate correction to the gyro
D) to produce a precessive force in order to align the gyro with the horizontal plane

17) In a Slaved Gyro Compass System the output of the flux-valve is fed to:
A) the slaving torque motor directly.
B) to the power supply of the gyro unit.
C) to the indicator.
D) the stator in the slaved gyro control.

18) The amber ALERT light on an INS control and display unit:
A) flashes for 2 minutes before reaching the next way point
B) illuminates steadily for 2 minutes before reaching the next way point
C) illuminates if power from the aircraft bus bar has been lost and the system is operating on standby battery
D) illuminates steadily after passing a way point in manual mode, until the next leg is programmed in

19) An INS with the accelerometers aligned N/S and E/W is limited to use at latitudes below about 82° . This is because:
A) at high speed on East or West tracks the rate of convergence is faster than the azimuth motor can correct
B) the correction for the Coriolis effect of earth rotation approaches infinity above 82° lat
C) it loses horizontal reference as dip becomes large
D) the functions of Secant Latitude and Tangent Latitude used for certain corrections in the computer start to approach infinity and the computer cannot handle the rapid changes involved

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20) The characteristics of the directional gyro (DG) used in a gyro stabilised compass system are:
A) one degree of freedom, whose horizontal axis is maintained in the horizontal plane by an automatic erecting system.
B) two degrees of freedom, whose axis aligned with the vertical to the location is maintained in this direction by an erecting system.
C) two degrees of freedom, whose horizontal axis corresponding to the reference direction is maintained in the horizontal plane by an automatic erecting system.
D) one degree of freedom, whose vertical axis, aligned with the real vertical to the location is maintained in this direction by an automatic erecting system.

21) What is known as the " Schuler Period" has a length of:
A) 84.4 hours.
B) 84.4 minutes.
C) 84.4 seconds.
D) 84.4 Hertz.

22) Assume a perfectly frictionless DI is corrected to give zero drift on the ground at 30° N. The DI is set to read 270° in an aircraft tracking along the 60° parallel at a groundspeed of 545 knots. The DI reading after 80 minutes:
A) 257.33°
B) 254.66°
C) 286.80°
D) 283.66°

23) The indication of the directional gyro as an on-board instrument are valid only for a short period of time. The causes of this inaccuracy are:
The earth's rotation
The longitudinal acceleration
The aircraft's motion over the surface of the earth.
The mechanical defects of the gyro
The gyro's weight
The gimbal mount of the gyro rings
The combination of correct statements is:
A) 1,2,3,4,5,6.
B) 1,3,4.
C) 1,3,4,6.
D) 2,5,6.

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24) The rotational speed of an air-driven gyro is normally:
A) 9000 - 12000 RPM
B) 14000 - 16000 RPM
C) 4400 - 4600 RPM
D) 6000 - 9000 RPM

25) The corrections fed to the platform gimbal motors of a north referenced inertial navigation system during the ALIGN mode use inputs from:
A) the latitude setting, the accelerometers
B) the longitude setting, the latitude setting, the air data computer
C) all the above
D) the latitude setting, the longitude setting, the accelerometers

26) Erection systems are provided for the purpose of:
A) Erecting and maintaining the gyro in its vertical position
B) Aligning a directional gyro in its vertical position
C) Aligning a directional gyro in its horizontal position
D) Erecting and maintaining the gyro in its horizontal position

27) The rotational speed of the gyro in a rate of turn indicator is .... (i) than in the direction indicator to .... (ii):
A) (i) Higher (ii) reduce apparent wander
B) (i) Higher (ii) increase rigidity
C) (i) Lower (ii) increase the resultant precessional force
D) (i) Lower (ii) reduce rigidity

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28) When an aircraft has turned 270 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
A) too much nose up and bank to high.
B) attitude and bank are correct.
C) too much nose up and bank correct.
D) too much nose up and bank to low.

29) A directional gyro is:
a gyroscope free around two axis
a gyroscope free around one axis
capable of self- orientation around an earth-tied direction
incapable of self-orientation around an earth-tied direction
The combination which regroups all of the correct statements is:
A) 1 - 4.
B) 2 - 3.
C) 2 - 4.
D) 1 - 3.

30) The heading information originating from the gyromagnetic compass flux valve is sent to the:
A) erector system.
B) error detector.
C) heading indicator.
D) amplifier.

31) An aircraft is flying a rate 1 turn at 480 kt TAS. What is the diameter of the turn?
A) 5 NM
B) 2 NM
C) 3 NM
D) 6 NM

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32) At the second state of integration E/W speed is converted into E/W distance gone. To convert this departure into change of longitude it has to:
A) be multiplied by Cosine of the latitude
B) be divided by Tangent of the latitude
C) be multiplied by Secant of the latitude
D) be divided by Secant of the latitude
33) The rate gyro indicates the correct rate of turn when the rate of .... (i) precession due to the spring is .... (ii) to the .... (iii) rate of turn:
A) (i) secondary (ii) equal (iii) aircraft
B) (i) secondary (ii) opposite (iii) aircraft
C) (i) primary (ii) balanced by and equal (iii) aircraft
D) (i) torque (ii) opposite (iii) primary

34) The rotational speed of the gyroscope in a turn indicator falls below the correct operational speed. A 90° turn at an indicated RATE ONE on this turn indicator will take:
A) 30 seconds ± 10 seconds either way
B) less than 30 seconds
C) more than 30 seconds
D) 30 seconds

35) What is the Schuler period?
A) 21 minutes.
B) 84 minutes.
C) 63 minutes.
D) 1 oscillation in azimuth.

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36) Alignment of a RLG INS takes:
A) 15 – 20 minutes
B) 84.4 minutes
C) 10 – 15 minutes
D) Less than 10 minutes

37) A longitude error in an INS will cause:
A) Will be corrected for once the E/W accelerometer has aligned to true north
B) A failure to align
C) Poor alignment and degraded accuracy
D) Will cause no problems at all

38) An airborne instrument, equipped with a gyro with 1 degree of freedom and a horizontal spin axis is a:
A) gyromagnetic compass.
B) directional gyro.
C) fluxgate compass.
D) turn indicator.

39) The heading read on the dial of a directional gyro is subject to errors, one of which is due to the movement of the aircraft. This error...
A) is dependent on the ground speed of the aircraft, its true track and the average latitude of the flight.
B) shows itself by an apparent rotation of the horizontal axis of the gyroscope which seems to turn at 15° per hour to the right in the northern hemisphere.
C) is, in spite of this, insignificant and may be neglected.
D) is at its greatest value when the aircraft follows a meridional track.

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40) The control and display unit of an inertial navigation system indicates a position of 4810.9° N 00012.2° W on a ramp position 4807.5° N 00005.1° E. What is the radial error rate of the system if it has been in NAV mode for 8 hours 20 minutes:
A) 14.3 NM/hr
B) 1.37 Km/hr
C) 1.37 NM/hr
D) 11.42 NM/hr

41) The directional gyro keeps its rotation axis aligned toward:
A) magnetic North.
B) a point on the Earth's surface.
C) geographic North.
D) a point in space.

(Refer to figure 022-08)�42) The diagram representing a left turn with insufficient rudder is:

A) 1
B) 2
C) 3
D) 4

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43) A turn and balance indicator uses a:
A) Space gyro
B) Tied gyro
C) Rate gyro
D) Earth gyro
44) Among the systematic errors of the " directional gyro" , the error due to the earth rotation make the north reference turn in the horizontal plane. At a mean latitude of 45° N, this reference turns by...
A) 7.5° /hour to the left
B) 15° /hour to the right
C) 7.5° /hour to the right
D) 10.5° /hour to the right

45) What is an operational difference between the turn coordinator and the turn and slip indicator?

A) the turn coordinator indicates roll rate, rate of turn, and co-ordination; the turn and slip indicator indicates rate of turn and co-ordination.
B) the turn coordinator indicates bank angle only; the turn and slip indicator indicates rate of turn and co- ordination.
C) the turn coordinator is always electric; the turn and slip indicator is always vacuum-driven.
D) the turn coordinator indicates angle of bank; the turn-and-slip indicator indicates turn rate in co-ordinated flight.

46) What is the main cause of precession?
A) Magnetic declination.
B) Magnetic variation.
C) Bearing friction.
D) The Earth's rotation.

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(Refer to figure 022-25)�47) The turn and slip and artificial horizon shown in attached figure show the aircraft to be turning left at rate one:
A) with too much bank and nose below the horizon
B) slipping in with nose below the horizon
C) with insufficient bank and nose above the horizon
D) and skidding out with nose below the horizon

48) The operational limits of a typical air driven direction indicator:
A) are due to the air jets being attached to the inner gimbal ring
B) are 85° in roll and pitch
C) are overcome by twin air jets
D) are not restrictive to heading

49) The basic properties of a gyroscope are:
A) Torque and inertia
B) Rigidity and inertia
C) Precession and torque
D) Precession and rigidity

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50) The operating principle of the pendulous vane unit erecting system is:
A) The influence of gravity on the gyro rotors.
B) The influence of gravity on the pendulous vanes.
C) The influence of gravity on the pendulous vanes and the gyro rotors.
D) The air flow reaction through the open vanes.

51) The term 'toppling', when applied to gyros is:
A) gyroscopic precession.
B) real wander and apparent wander.
C) wander in the vertical plane.
D) wander in the horizontal plane.

52) Gimballing error:
A) will be zero on only two headings during a 360° turn.
B) will remain until the gyro is reset.
C) will disappear after a turn is completed.
D) will only occur during a 360° turn.

53) The purpose of the caging knob (Directional Gyro) is:
A) to prevent apparent wander.
B) to reset the heading.
C) to reset the heading and to prevent toppling.
D) to prevent the gyro toppling.

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54) Deviation compensation in a flux gate compass is done:
A) Both mechanically and electronically
B) Electronically
C) By the pilot
D) Mechanically

55) The acceleration errors of en electrical artificial horizon are reduced compared to those of an air driven one by:
A) spinning the electrical rotor slower
B) the use of compensation stilts
C) reducing the erection rate of the gyro assembly
D) designing the gyro so that it is not pendulous

56) The torque motor of a gyro stabilised magnetic compass:
A) moves the Selsyn stator.
B) precesses the directional gyro.
C) takes its input from the flux valve.
D) moves the heading pointer.

57) A turn indicator is an instrument which indicates rate of turn. Rate of turn depends upon:
bank angle
aeroplane speed
aeroplane weight
The combination regrouping the correct statements is:
A) 1 and 2.
B) 1, 2, and 3.
C) 2 and 3.
D) 1 and 3.

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58) When an aircraft has turned 90 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
A) too much nose-up and bank correct.
B) too much nose-up and bank too high.
C) too much nose-up and bank too low.
D) attitude and bank correct.

59) The maximum drift error sensed by an uncompensated DGI will be:
A) 60 deg per hour.
B) 45 deg per hour.
C) 15 deg per hour.
D) 30 deg per hour.

60) Where is the earth rate wander, and the transport wander of a gyro equal to zero?
A) 45 N.
B) North Pole.
C) 45 S.
D) Equator.

61) While inertial platform system is operating on board an aircraft, it is necessary to use a device with the following characteristics, in order to keep the vertical line with a pendulous system:
A) with damping and a period of about 84 seconds
B) without damping and a period of about 84 seconds
C) with damping and a period of about 84 minutes
D) without damping and a period of about 84 minutes

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62) The errors of an INS fall into 3 categories:
A) Bounded, unbounded and inherent
B) Bounded, unbounded and velocity
C) Bounded, unbounded and accelerometer
D) Coriolis, unbounded and inherent

63) What is the Schuler period?
A) 84 seconds.
B) 48 seconds.
C) 84 minutes.
D) 48 minutes.

64) The pendulum type detector system of the directional gyro feeds:
A) a levelling erection torque motor.
B) a nozzle integral with the outer gimbal ring.
C) 2 torque motors arranged horizontally.
D) a torque motor on the sensitive axis.

65) A DGI is assumed to be frictionless. Its latitude nut is set for 56° N. The reading that you would expect to see after flying West along the parallel of 48° N for 45 minutes at a TAS of 480 kts with a Wind velocity of 090/60 would be:
A) 278.5°
B) 281.3°
C) 261.3°
D) 277.6°

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66) A Stand-by-horizon or emergency attitude indicator:
A) Is automatically connected to the primary vertical gyro if the alternator fails.
B) Only works of there is a complete electrical failure.
C) Contains its own separate gyro.
D) Is fully independent of external energy resources in an emergency situation.

67) A turn indicator is built around a gyroscope with:
A) 0 degree of freedom.
B) 3 degrees of freedom.
C) 2 degrees of freedom.
D) 1 degree of freedom.

68) An artificial horizon with an electrical driven gyroscope has greatly reduced take-off errors. This is because:
A) the gyro has greater rigidity, is less bottom heavy and there is a linear accelerometer cut-out switch fitted
B) the gyro has greater rigidity, is less bottom heavy and there is a roll cut-out switch fitted
C) the fast erection switch is used to overcome topple by increasing the erection rate to a high value
D) it is fitted with a roll cut-out switch and a linear cut-out switch

69) With reference to Inertial Navigation Systems, the functions of the integrators are:
at the second stage of integration to suppress unbounded errors (when in the NAV mode)
at the first stage of integration to convert acceleration, with respect to time, into speed, (when in the NAV mode)
at the second stage of integration to convert speed, with respect to time, into distance gone, (when in the NAV mode).
to align the platform (when in the level and align modes)
A) only (2) and (3) of the above statements are true
B) only (1), (2) and (3) of the above statements are true
C) all the above statements are true
D) only (2), (3) and (4) of the above statements are true

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70) The basic properties of a gyroscope are:
The gyro's weight
The rigidity in space
The inertia
The high RPM
The precession
The combination of correct statements is:
A) 2, 3, 5
B) 2, 5
C) 1, 3, 5
D) 3, 4

71) A slaved directional gyro derives it's directional signal from:
A) a direct reading magnetic compass
B) the flight director
C) the flux valve
D) the air-data-computer

72) When decelerating in an aircraft with an air driven artificial horizon you would expect to see:
A) A climbing turn to starboard
B) A descending turn to port
C) A descending turn to starboard
D) A climbing turn to port

73) A gyromagnetic compass or heading reference unit is an assembly which always consists of:
a directional gyro
a vertical axis gyro
an earth's magnetic field detector
an azimuth control
a synchronising control
The combination of correct statements is:
A) 1,4.
B) 2,3,5.
C) 1,3,5.
D) 2,5.

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74) A standby artificial horizon must have the following properties:
a remote gyro
its own power supply
only to be used in emergency
its own gyro
one for each certified pilot
A) all the above
B) 1,3, & 5
C) 2, 3, & 4
D) 2 & 4

75) Rigidity in a gyroscope is:
A) a way to express the stability of the inner and outer gimbal rings.
B) the reaction 90° in the direction of rotation when applying force to the spinning wheel.
C) to what extremes the flight attitudes might be before the gyro topples.
D) the tendency it has to remain in its plane of rotation and resist attempts to alter its position.

76) Apparent wander of a gyro is caused by:
A) rotation of the earth.
B) clear air turbulence.
C) gimbal friction.
D) external torque.

77) In a turn at constant angle of bank, the rate of turn is:
A) independent of weight and inversely proportional a to TAS.
B) dependant on weight and proportional to TAS.
C) dependant on weight and inversely proportional to TAS.
D) independent of weight and proportional a to TAS.

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78) When using an INS platform Coriolis affects:
A) Neither a nor b
B) The N/S accelerometer
C) Both a & b
D) The E/W accelerometer

79) The gyromagnetic compass torque motor:
A) feeds the error detector system.
B) causes the directional gyro unit to precess.
C) causes the heading indicator to precess.
D) is fed by the flux valve.

80) The properties of a Turn Indicator are:
One degree of freedom
two degrees of freedom
two springs connected to the aircraft frame
spin axis in the longitudinal plane
spin axis parallel to the yaw axis
spin axis in the lateral plane
A) 1, & 6
B) 2, & 5
C) 1, & 4
D) 2, & 6

81) The input signal of the amplifier of the gyromagnetic compass resetting device originates from the:
A) directional gyro unit.
B) flux valve.
C) directional gyro erection device.
D) error detector.

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82) When, in flight, the needle and ball of a needle-and-ball indicator are on the left, the aircraft is:
A) turning left with not enough bank.
B) turning right with not enough bank.
C) turning right with too much bank.
D) turning left with too much bank.

83) While flying, a red flag labelled " HDG" appears in the indicator (HSI) of a Slaved Gyro Compass System. This indicates that:
A) The flux valve has detected an error between the actual aircraft heading and the pre-selected heading
B) The autopilot has detected an error between the actual aircraft heading and the pre-selected heading
C) The flux valve is not supplying reliable information to the compass system
D) None of the above

84) Apparent drift in a direction indicator is:
A) 7 1/2° /hour at 30° N and 30° S, and zero at the equator.
B) non-existent at all latitudes because of the drift-nut attached to one of the gimbals.
C) 15° /hour at the equator and zero at the poles.
D) 7 1/2° /hour at 30° N and 30° S, and zero at the poles.

85) The latitude nut of the direction indicator is on the .... (i) gimbal and this causes the gyro to precess around its .... (ii) axis:
A) (i) outer (ii) horizontal
B) (i) outer (ii) vertical
C) (i) inner (ii) horizontal
D) (i) inner (ii) vertical

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86) In a DGI what error is caused by the gyro movement relative to the earth?
A) latitude error.
B) real wander.
C) transport Wander.
D) earth Rate.

87) The torque motor of a slaved gyro compass:
A) precesses the gyro in the vertical plane.
B) precesses the gyro in the horizontal plane.
C) moves the heading pointer.
D) moves the Selsyn stator.

88) The rotor spinning axis of the electrically driven artificial horizon is erected and maintained vertical by:
A) commutator switches
B) the fast erection device
C) mercury switches
D) the pendulosity of the rotor assembly

89) You are at 30° N flying on a northerly heading. Your DI reading will:
A) decrease at an increasing rate
B) increase at a decreasing rate
C) increase at an increasing rate
D) decrease at a decreasing rate

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90) In order to align a strapdown inertial unit, it is requited to insert the local geographical coordinates. This is necessary to:
A) Check operation of laser gyros
B) Re-erect laser gyros
C) Determine magnetic or true heading
D) Position the computing trihedron with reference to earth

91) If a 180º steep turn is made to the right and the aircraft is rolled out to straight and level flight by visual reference, the miniature aircraft on the Attitude Indicator will...
A) show a slight slip and descent to the right.
B) show a slight climb and turn to the right.
C) show a slight skid and climb to the right.
D) show a slight climb and turn to the left.

92) On the ground, during a left turn, the turn indicator indicates:
A) needle to the left, ball to the right.
B) needle to the left, ball to the left.
C) needle in the middle, ball to the right.
D) needle in the middle, ball to the left.

93) When an aircraft has turned 360 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon:
A) attitude and bank correct.
B) too much nose-up and bank too high.
C) too much nose-up and bank correct.
D) too much nose-up and bank too low.

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94) Following 180° stabilized turn with a constant attitude and bank, the artificial horizon indicates:
A) too high pitch-up and correct banking.
B) too high pitch up and too high banking.
C) attitude and banking correct.
D) too high pitch-up and too low banking.

95) While accelerating on take-off, what would be the expected indications on an electrically driven Attitude Indicator?
A) none of the above - it will indicate correctly
B) a climbing turn to the left
C) a climbing turn to the right
D) a descending turn to the left

96) During an acceleration phase at constant attitude, the resetting principle of the artificial horizon results in the horizon bar indicating a:
A) nose-down followed by a nose-up attitude.
B) nose-up attitude.
C) constant attitude.
D) nose-down attitude.

97) Air-driven gyro rotors are prevented from spinning too fast by the:
A) electronic speed regulator module
B) vacuum relief valve
C) pressure outflow valve
D) pressure reducing valve

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98) An aircraft is flying at a TAS of 270 knots. What AOB will give a rate 1 turn:
A) 17°
B) 30°
C) 34°
D) 15°

99) Why is an INS platform virtually unusable at very high latitudes?
A) The value of earth rate affecting the E/W accelerometer is a component dependent on the sine Lat. At high latitudes this component is nearly zero and makes alignment to magnetic north virtually impossible
B) The value of earth rate affecting the E/W accelerometer is a component dependent on the cosine Lat. At high latitudes this component is nearly zero and makes alignment to true north virtually impossible
C) The value of earth rate affecting the E/W accelerometer is a component dependent on the sine Lat. At high latitudes this component is nearly zero and makes alignment to true north virtually impossible
D) The value of earth rate affecting the E/W accelerometer is a component dependent on the cosine Lat. At high latitudes this component is nearly zero and makes alignment to magnetic north virtually impossible

100) If the needle and the ball of a Turn & Slip indicator both show right, what does it indicate:
A) turn to right & too little bank.
B) turn to right & too much bank.
C) turn to left & too much bank.
D) turn to left & too little bank.

101) In a turn and slip indicator, the gyro is spinning at a greater speed than normal. What will the effect be on the indicated rate of turn?
A) It will cause more precision and rigidity.
B) It will be more accurate than usual.
C) It will underread.
D) It will overread.

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102) What are the advantages of a laser gyro compared to a conventional gyro?
A) uses more power.
B) takes longer to set up/ spin up.
C) takes longer to align.
D) has a longer cycle life.

103) If an INS platform is not accurately aligned with true north:
A) The N/S accelerometer will sense an acceleration force caused by the rotation of the earth
B) The E/W accelerometer will sense an acceleration force caused by the rotation of the earth
C) The E/W accelerometer will sense a velocity force caused by the rotation of the eart
D) The N/S accelerometer will sense a velocity force caused by the rotation of the earth

104) Which of the following is true regarding the turn co-ordinator?
A) Its gyro is offset by 300 to the longitudinal axis of the aircraft
B) It has a tied gyroscope
C) It responds to rate of turn only
D) It gives angle of bank and rate of turn

105) When, in flight, the needle of a needle-and-ball indicator is on the left and the ball on the right, the aircraft is:
A) turning right with not enough bank
B) turning left with too much bank
C) turning left with not enough bank
D) turning right with too much bank

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106) The principle of operation of the turn and slip indicator is best described as:
A) a single gimbal gyroscope in which a spring, opposing the primary precession, in turn produces a secondary precession equal to the aircraft rate of turn
B) a space gyro which uses the force of precession against a spring to give a reading of the aircraft rate of turn
C) a single gimbal gyroscope whose primary precession is opposed by a spring which, in turn, produces a second precession equal and opposite to the aircraft rate of turn
D) an earth gyro in which a calibrated spring ensures the tilt of the gyro is proportional to the aircraft rate of turn

107) The inertial platform in a north-referenced inertial navigation system is torqued to perform like a Schuler pendulum, so that when the platform moves over the earth:
A) answers b and c are correct
B) the platform remains level and aligned regardless of any aircraft accelerations
C) gyro drift errors are cancelled out
D) the platform will always oscillate with respect to true north

108) The triangular cavity in a RLG is filled with which combination of gases:
A) Helium and neon
B) Helium and argon
C) Hydrogen and argon
D) Hydrogen and neon

109) The inner gimbal assembly of an artificial horizon is pivoted .... (i) in the .... (ii):
A) (i) laterally (ii) case
B) (i) longitudinally (ii) outer gimbal
C) (i) to give freedom (ii) pitch plane
D) (i) longitudinally (ii) rolling plane

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110) A gravity erector system is used to correct the errors on:
A) a directional gyro.
B) an artificial horizon.
C) a gyromagnetic compass.
D) a turn indicator.

111) The heading reference unit of a three-axis data generator is equipped with a gyro with:
A) 1 degree of freedom and horizontal spin axis.
B) 2 degrees of freedom and vertical spin axis.
C) 2 degrees of freedom and horizontal spin axis.
D) 1 degree of freedom and vertical spin axis.

112) An aircraft initiates a rate one turn at a TAS of 270 kt. How far will it have travelled after 25 seconds:
A) 1.96 NM
B) 5.88 NM
C) 3.92 NM
D) 7.84 NM

113) The rate-of-turn is the:
A) aircraft speed in a turn.
B) pitch rate in a turn.
C) change-of-heading rate of the aircraft.
D) yaw rate in a turn.

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114) The position accuracy of an RLG INS is:
A) 1 NM/hr
B) 5 NM/hr
C) 10 NM/hr
D) 2 NM/hr

115) A laser gyro consists of:
A) 2 electrodes (anodes + cathodes).
B) a gyro with 2 degrees of freedom.
C) two moving cavities provided with mirrors.
D) a laser generating two light waves.

116) An IRS with laser gyros should (i) .... be Schuler tuned, and (ii) .... be strapped down.
A) (i) never (ii) always
B) (i) never (ii) never
C) (i) always (ii) never
D) (i) always (ii) always

117) A failed RMI rose is locked on 090° and the ADF pointer indicates 225° . The relative bearing to the station is:
A) 135° .
B) 315° .
C) Impossible to read, due to failure RMI.
D) 225° .

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118) What is the maximum drift of a gyro, due to earth rate:
A) 90 deg per hour.
B) 15 deg per hour.
C) 180 deg per hour.
D) 5 deg per hour.

119) With regard to the turn indicator, the spring:
A) Produces a secondary precession that opposes yaw
B) Directly balances yaw
C) Gives a linear relationship between extension and secondary force
D) Produces a secondary precession equal to yaw

120) A space gyro has .... (i) gimbal rings with .... (ii) planes of freedom:
A) (i) 3 (ii) 3
B) (i) 2 (ii) 3
C) (i) 3 (ii) 2
D) (i) 2 (ii) 2

121) If a turn and balance indicator overspeed the result will be:
A) The rate of turn will be indicated correctly
B) Under-indication of the turn
C) No turn will be indicated
D) Over-indication of the turn

122) An aircraft is flying along the 60° S parallel. After one hour the DI indication has increased by 21° . If the latitude nut of the DI has been set to zero drift on the ground at 30° S, the groundspeed of the aircraft is:
A) 473
B) 537
C) 450
D) 520

123) Laser gyros are used in an IRS. Why must accurate Lat & Long be inserted?
A) to determine the computed trihedron
B) to check the function of the laser gyros
C) to determine magnetic north
D) to compensate for aircraft movement

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124) Among the flight control instruments, the artificial horizon plays an essential part. It uses a gyroscope with:��(Note - in this question, the degrees of freedom of a gyro are determined by the number of gimbal rings it comprises)
A) two degrees of freedom, whose horizontal axis corresponding to a reference direction is maintained in a horizontal plane by an automatic erecting system.
B) two degrees of freedom, whose axis is oriented and continuously maintained to local vertical by an automatic erecting system.
C) one degree of freedom, whose horizontal axis is maintained in a horizontal plane by an automatic erecting
D) one degree of freedom, whose vertical axis oriented in the direction of the real vertical to the location is maintained in this direction by an automatic erecting system.

125) In a right turn while taxiing, the correct indications on a Turn & Slip Indicator are:
A) Needle right, ball left.
B) Needle left, ball left.
C) Needle right, ball right.
D) Needle left, ball right.

126) When, in flight, the needle and ball of a needle-and-ball indicator are on the right, the aircraft is:
A) turning right with not enough bank.
B) turning right with too much bank.
C) turning left with too much bank.
D) turning left with not enough bank.

127) At a low bank angle, the measurement of rate-of-turn actually consists in measuring the:
A) pitch rate of the aircraft
B) roll rate of the aircraft
C) angular velocity of the aircraft
D) yaw rate of the aircraft

128) The rotor in an electric artificial horizon is tied to the vertical by:
A) a jet of air from the rotor impinging on a wedge plate which is on the inner gimbal
B) a jet of air from the outer gimbal striking the rotor buckets
C) mercury switches only
D) torque motors and level switches

129) In a turn at constant rate, the turn indicator reading is:
A) proportional to the aircraft true airspeed.
B) inversely proportional to the aircraft true airspeed.
C) independent to the aircraft true airspeed.
D) proportional to the aircraft weight.

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130) In a left turn while taxiing, the correct indications are:
A) Needle right, ball left.
B) Needle left, ball left.
C) Needle left, ball right.
D) Needle right, ball right.
(Refer to figure 022-29)
131) The turn and slip and artificial horizon illustrated in the attached figure show the aircraft to be turning:
A) left with skid
B) right with insufficient bank and the nose above the horizon
C) right at 30 degrees angle of bank with slip
D) right at 30 degrees angle of bank with skid

132) The vertical reference unit of a three-axis data generator is equipped with a gyro with:
A) 1 degree of freedom and horizontal spin axis
B) 2 degrees of freedom and vertical spin axis
C) 2 degrees of freedom and horizontal spin axis
D) 1 degree of freedom and vertical spin axis

133) The turn rate indicator uses a gyroscope:
with one degree of freedom.
with two degrees of freedom
the frame of which is supported by two return springs.
the spinning wheel axis of which is parallel to the pitch axis.
the spinning wheel axis of which is parallel to the yawing axis.
the spinning wheel axis of which is horizontal.
The combination regrouping all the correct statements is:
A) 2, 3 and 6
B) 2 and 3
C) 1 and 6
D) 1, 3, and 6

134) The gimbal error of the directional gyro is due to the effect of:
A) a bank or pitch attitude of the aircraft.
B) an apparent weight and an apparent vertical.
C) too slow precession on the horizontal gimbal ring.
D) the aircraft's track over the earth.

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135) An aircraft is flying at a 120 kt true airspeed (VV), in order to achieve a rate 1 turn, the pilot will have to bank the aircraft at an angle of:
A) 30° .
B) 12° .
C) 18° .
D) 36° .

136) A 2 axis gyro measuring vertical changes will have:
A) one degree of freedom vertical axis.
B) two degrees of freedom vertical axis.
C) two degrees of freedom horizontal axis.
D) one degree of freedom horizontal axis.

137) The rigidity of a gyro is improved by:
A) increasing RPM and concentrating the mass on the periphery of the rotor.
B) decreasing RPM and concentrating the mass at the hub of the rotor.
C) decreasing RPM and concentrating the mass on the periphery of the rotor.
D) increasing RPM and concentrating the mass at the hub of the rotor.

138) In the building principle of a gyroscope, the best efficiency is obtained through the concentration of the mass:
A) close to the axis and with a high rotation speed..
B) on the periphery and with a high rotation speed.
C) close to the axis and with a low rotation speed..
D) on the periphery and with a low rotation speed..

139) Failure of the electrical supply to an electrically driven direction indicator may be indicated by:
A) Low suction.
B) A low ammeter reading.
C) A red warning flag.
D) A low voltmeter reading.

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140) Which of the following statements is most correct when describing a turn co-ordinator?
A) It indicates the angle of bank and turn rate.
B) It is suitable for a stand-by artificial horizon.
C) It responds to aircraft bank angle as well as turning rate.
D) It displays turn and pitch for a rate one turn only.

141) A rate integrating gyro is a detecting element used in
An inertial attitude unit
An automatic pilot
A stabilizing servo system
An inertial navigation system
A rate-of-turn indicator
The combination of correct statements is:
A) 2,3,4.
B) 2,3,5.
C) 1,4.
D) 1,2,3,4,5.

142) Concerning the directional gyro indicator, the latitude at which the apparent wander is equal to 0 is:
A) the equator.
B) latitude 30° .
C) the North pole.
D) latitude 45° .

143) In a turn indicator, the measurement of rate of turn consists for:
A) high bank angle, in measuring the roll rate
B) low bank angle, in measuring the yaw rate
C) low bank angle, in measuring the roll rate
D) high bank angle, in measuring the yaw rate

144) The directional gyro axis no longer spins about the local vertical when it is located:
A) in the latitude 45° .
B) in the latitude 30° .
C) on the North pole.
D) on the equator.

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145) Which of the following are errors of a DGI:
earth rate
transport wander
banking when pitched up
annual movement of poles
mechanical problems
A) 1, 2, 3, & 5
B) 3, 4, & 5
C) all 5
D) 2, 3, & 5

146) The forces which affect the balance ball in a turn and slip indicator are:
A) weight, lift vector and TAS.
B) weight and centrifugal force.
C) centripetal force, attitude and weight.
D) weight and centripetal force.
The indications on a directional gyroscope or gyrocompass are subject to errors, due to:
rotation of Earth.
aeroplane motion on Earth.
lateral and transversal aeroplane bank angles.
north change.
mechanical defects.

147) Chose the combination with true statements only:
A) 1,2,3,5.
B) 3,4,5.
C) 2,3,5.
D) 1,2,4,5.

148) When turning left on the ground the turn and slip indicator:
A) will show a skid
B) will show a left bank and slip
C) will show a left bank and skid
D) will not indicate on the ground