Vayudoot Aviation

1. An aircraft is descending at a constant mach number. If the aircraft is descending through an inversion layer, the CAS will

Decrease then decrease more slowly

Increase

Decrease

Remain constant

2. In a Schuler tuned INS, the largest unbounded errors are

Created at the first stage of integration

Due to acceleration errors

Track errors due to initial misalignment

Due to real wander of the platform gyroscopes

3. What input is there to TCAS 2?

Mode ‘A’ transponder which gives TA and RAs

Mode ‘C’ and ‘S’ transponders which co-ordinate avoidance manoeuvres

Mode ‘S’ transponder which co-ordinates avoidance manoeuvres

Mode ‘C’ transponder which co-ordinates avoidance manoeuvres

4. What are the components of a CVR 1 Microphone 2 Crash/Fire resistant construction 3 Independent battery 4 A Flight data recorder

1 & 4

1, 2, 3 & 4

1, 2 & 4

1 & 2

5. You are flying at a constant FL 290 and constant mach number. The total temperature increases by 5°. The CAS will

decrease by 10 kts

remain approximately constant

will increase or decrease depending on whether you are above or below ISA.

increase by 10 kts

6. Which of the following will effect a direct reading compass? ferrous metals, non-ferrous metals, electrical equipment

1 & 2

1 only

all 3

1 & 3

7. An aircraft taking off from an airfield with QNH set in the altimeter has both static vents blocked by ice. As the aircraft climbs away the altimeter will

Read the height of the aircraft above the airfield

Show only a very small increase in height

Read the airfield elevation

Indicate the aircraft height amsl

8. EPR is the ratio of

Jet pipe pressure to compressor inlet pressure on a turbo-prop engine only

Jet pipe pressure to the compressor inlet pressure on a gas turbine engine

The compressor outlet pressure to the compressor inlet pressure

Jet pipe pressure to the compressor outlet pressure on a gas turbine engine

9. The rigidity (gyroscopic interia. of a gyroscope may be increased by

Increasing the speed of rotation and decreasing the mass of the rotor

Increasing the number of gimbals and decreasing the number of planes of rotation

Increasing the speed of rotation and increasing the mass of the rotor

Decreasing the speed of rotation and increasing the speed of the rotor.

10. Which of the following apply to the a Yaw damper : 1. May aid the pilot in the event of asymmetric thrust after engine failure 2. Applies measured amounts of aileron to counter dutch roll 3. Increases lateral stability to stop dutch roll 4. Is required at high altitude 5. Can automatically help in turn co-ordination 6. May deflect the rudder to counteract the natural oscillating frequency of the aircraft.

1, 4 & 5

1, 4 & 6

2, 3 & 4

2, 3 & 6

11. During an approach to autoland at 1500feet

Off line channels are manually engaged, flare mode is armed

Localiser is controlling the roll channel, off line channels are automatically engaged and flare mode is armed

Localiser is controlling the roll channel, stabiliser is trimmed nose up and roll out is armed

Provided both localiser and glideslope signals are valid LAND 3 will

12. Select the correct statement

EAS = IAS corrected for position error

EAS = CAS corrected for compressibility error

CAS = TAS corrected for density error

TAS = EAS corrected for compressibility error

13. What are the colours used on an EFIS display to show a tuned navigation aid and an airport?

white & magenta

white & yellow

green & white

green & cyan

14. During a CAT 1 ILS approach, height is indicated by

Barometric

Radio Altimeter

Marker

GPS

15. The amber ALERT sign is on an INS control and display unit

Start flashing 2 minutes before reaching the next waypoint and goes out at 30 seconds to run

Illuminates steadily after passing a waypoint in manual mode, until the next leg is programmed in

Illuminates if power from the aircraft bus bar has been lost and the system is operating on standby battery

Illuminates steadily for 2 minutes before reaching the next waypoint

16. To improve the horizontality of a compass, the magnet assembly is suspended from a point

Below the centre of gravity

Varying with magnetic latitude

Above the centre of gravity

On the centre line of the magnet

17. Which of the following are modes of the GPWS? 1. Excessive sink rate. 2. Altitude loss after T/O or go-around. 3. Excessive Glideslope deviation. 4. High climb rate. 5. Flaps in incorrect position. 6. High altitude descent. 7. Stall.

1, 2, 3, & 5

1, 2 & 3

1, 3, 5 & 7

All 7

18. The principle of the fuel-monitoring device giving an indication of the total fuel burnt is

capacitance variation of a capacitor

multiplying flight time by fuel consumption

difference of indication according to departure value

integration of instantaneous flow

19. Weather Radar returns can be displayed in which of the following EFIS Modes

Map Exp ILS Exp VOR

Plan Exp ILS Map

Plan Exp ILS Exp VOR

Map ILS VOR

20. Torque meters provide a reliable measure of power output from

A noise suppression unit

An APU

A turbo-propeller engine

A turbo-jet engine

21. The Altitude Alert system alerts the pilot

At the selected altitude

When deviating from the selected altitude

At decision height

When reference altitude equals the selected altitude

22. What are the advantages of an IRS compared to an INS?

Insensitively to “g” and reduced wander of the gyroscope.

Reduce spin-up time and a dither motor to prevent “lock-out”.

Reduce spin-up time and accuracy not adversely affect by “g”

Increase accuracy and a dither motor to prevent “lock-out”.

23. During an autoland the caption LAND 2 is illuminated. The system is

Fail passive

Requiring a crew input

Approaching decision height

Fail active or fail operational

24. Which of the following is the FMS normal operating condition in the cruise?

L NAV or V NAV

L NAV and V NAV

L NAV only

V NAV only

25. What is the purpose of the auto-synchronisation system in an A/P: 1. Prevents snatching on disengagement 2. Prevents snatching on engagement 3. Cross feeds rudder and aileron inputs for co-ordination 4. May not allow the A/P to engage if unserviceable 5. Displays the control positions 6. Removes standing demands from the autopilot system prior to the CMD button being selected

1,4&6

2,4&6

1,3&5

2,3&5

26. TCAS 2 when fitted with mode C transponder may give

TA and RA in horizontal plane.

TA and RA in vertical plane.

TA only

TA and RA in vertical plane.

27. When the pointer of a rate of turn indicator shows a steady rate of turn

The force produced by the spring is producing a precession equal to but

The spring is providing a force which produces a precession equal to the rate of turn (in the same direction as the turn)

The calibrated spring is exerting a force about the lateral axis equal to the rate of turn

The spring is providing a force which produces a precession equal to the rate of turn (in the opposite direction to the turn)

28. With reference to the flux valve of a remote indicating compass

The flux valve is pendulously mounted and so it is not subject to or affected by the earth’s magnetic field

The flux valve is fixed to the aircraft and so turns with the aircraft to measure the angle between the aircraft and the earth’s magnetic field

The flux valve is not subject to acceleration errors

The flux valve is pendulously mounted and is free to turn to remain aligned with the earth magnetic field

29. If the rpm of the rotor in a turn and slip indicator is higher than normal, the turn indicator wil

Indicate correctly

Not indicate due to the increased rigidity

Overread the correct rate of turn

Underread the correct rate of turn

30. An aircraft has a compensated capacitance fuel contents gauging system and is refuelled so that the total fuel contents are 76000kg at a temperature of 18°C and an S.G. of 0.81. Whilst the aircraft is parked the temperature increases to 26°C and the S.G. becomes 0.80. The indicated fuel contents have

decreased by 5%

remained the same

increased by 10%

increased by 5%

31. The gravity erecting device on a vertical gyro is used on which instrument

directional gyro unit

artificial horizon

turn indicator

gyromagnetic device

32. What type of autoland system would be required for the landing to continue following a single failure below alert height?

Land 2 system

Fail operation or fail active

Fail passive

Fail soft

33. A factor giving an error on a direct indicating compass would be

parallax due to oscillations of the compass rose

acceleration on east/west headings

crosswinds - particularly on east/west headings

turning through east/west headings

34. Which of the following types of pressure gauge would be best suited to a high pressure input?

aneroid capsule

dynamic probe

bellows

bourdon tube

35. To obtain heading information from a Gyro Stabilised platform, the gyros should have

2 degrees of freedom and a horizontal axis

1 degree of freedom and a vertical axis

1 degree of freedom and a horizontal axis

2 degrees of freedom and a vertical axis

36. If only a single A/P is used to climb, cruise and approach; following a failure

it is fail operational and will not disconnect

it is fail safe and will disconnect

it is fail soft and will not disconnect

it is fail passive with redundancy

37. In an inertial-lead VSI the source of the most pronounced error is

Position

Steep turn

Instrument

Missed approach manoeuver

38. The red arc in the middle of the green band of a piston engine RPM indicator signifies

Minimum RPM

RPM at which a greater level of vibration is encountered

Maximum RPM

RPM that must never be exceeded in the cruise

39. What errors can the Air Data Computer correct for? 1. instrument error & ram rise 2. compressibility & density error 3. lag & density error 4. position & temperature error 5. temperature & instrument error 6. manoeuvre error & ram rise 7. manoeuvre & position errors

2 & 4

1 & 6

3 & 7

3 & 5

40. An aircraft maintaining a constant CAS and altitude is flying from a cold airmass into warmer air. The effect of the change of temperature on the speed will be

CAS will increase

TAS will increase

EAS will decrease

41. An autopilot delivers roll commands to the ailerons to achieve a bank angle

proportional to TAS, but below a specified maximum

set bank of 25 degrees

set bank of 30 degrees

proportional to the deviation from the desired heading, but not exceeding a specified maximum

42. VLO is defined as

the maximum speed at which to fly with the landing gear retracted

the minimum speed at which to fly with the landing gear extended

the maximum speed at which the landing gear may be retracted or extended

the maximum speed at which to fly with the landing gear extended

43. An aircraft equipped with digital avionics includes an ECAM system. This centralised system, if a failure in one of the monitored systems is displayed, the crew must

analyse initially the failure and only respond to a level 1 warning

apply the immediate actions as directed by the checklist on the left of the two screens

cancel the warning

reset the warning display after noting the failure on the left screen

44. At 200ft on an auto-land

The LOC mode is engaged in the roll channel and the FLARE mode is engaged in the pitch channel

The auto-throttle is maintaining the speed and the pitch channel is maintaining the height.

The LOC mode is engaged in the roll channel and the G/S mode is engaged in pitch

The ROLL OUT mode is engaged in the Roll channel and the G/S mode is engaged in pitch.

45. A warning message on the EICAS system screen would be

displayed in amber, normally on the upper screen, indented one space to the right

displayed in amber, normally on the upper screen with aural warnings .

displayed in amber on the lower screen with associated caution lights and aural tones

displayed in red, normally on the upper screen , and requiring immediate corrective action

46. Altitude select and altitude hold are examples of

Interlocking functions

Manometric functions from the ADC

Inner loop functions in pitch

Outer loop functions in roll

47. The combined Machmeter/ASI is subject to the following errors

Instrument and compressibility only

Instrument, pressure and temperature only

Position, density, instrument, compressibility, manoeuvre induced

Those of the Machmeter only

48. If an aircraft, fitted with a DRMC, takes off on a westerly heading, in the northern hemisphere, the DRMC will indicate

no turn

a turn to south

oscillates about west

a turn to the north

49. A stall warning system fitted to a large aircraft will always include

Various inputs including EGT, a warning module and an aural warning

Stick shakers and/or stick push

Various inputs including speed brake position, a warning module and a visual or aural warning

Various inputs including landing gear micro switch, a warning module and an aural warning

50. If one probe of a multi-sensor EGT system became disconnected, the reading would

Increase by between 20°C to 30°C

Be largely unaffected

Decrease by between 20°C to 30°C

Fall to zero

Question Bank

Questions for REVISION 2