Vayudoot Aviation

1. In an aircraft which requires a mach trim system it will apply inputs to the horizontal stabilizer

At high mach numbers with the autopilot engaged

At mach one with the autopilot engaged or not

At high subsonic speeds with the autopilot engaged or not.

All the time

2. A system which can still function without degradation of performance after a failure has

fail symbol ability.

fail passive ability

fail soft ability.

fail operational ability.

3. The rules for the use of Autotrim are that it

is not needed if the autopilot is engaged

can be engaged without the autopilot

usually operates on all three axes

operates only in conjunction with the autopilot

4. An automatic flight control system is fitted with control wheel steering (CWS)

Manoeuvring commands may be input by applying normal forces to the control yoke without first disengaging the autopilot

The autopilot must be disengaged before the pilot can input manoeuvring commands

The CWS is only there for steering on the ground

Manoeuvring commands may be input using pitch and turn controls on the automatic flight system control panel, without first disengaging the autopilot

5. Control wheel steering enables a pilot to

taxy the aircraft on the ground

manoeuvre the aircraft in the air while the autopilot is engaged

manoeuvre the aircraft with the autopilot disengaged.

alter the flight path while the autopilot is engaged by applying a breakout force

6. The auto-throttle is used to control some factors during the three primary control modes, they are

EPR, wheel and altitude.

EPR, Mach and altitude.

EPR, wheel and speed

EPR, Mach and Speed.

7. During an autoland approach

flare is disengaged prior to touchdown at 5'GA

localiser roll control is disengaged just prior to touchdown

Flare is engaged at 1500'agl

glideslope is the engaged pitch mode until 5'GA

8. A fundamental requirement of a closed loop servo-mechanism is

a tacho-generator.

feedback

a stable reference device.

an interlock control

9. During an autoland at 50 ft AGL (45' GA) the pitch control of the autopilot is ............. and the roll control is ....................

flare roll out

flare localiser

glideslope roll out

glideslope localiser

10. The Autothrottle will come on automatically even with the A/T switch OFF when

the AoA reaches the stalling angle

in a FBW aircraft the AoA reaches a critical value called floor

TOGA button is pressed

reverse thrust is selected in flight

11. During an approach to an autoland at 1500 feet

Provided both localiser and glideslope signals are valid LAND 3 will illuminate

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

Off line channels are manually engaged, flare mode is armed

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

12. The JAR OPS requirements for single pilot operation under IFR state that the aircraft must be fitted with

single axis autopilot

a two axis autopilot with autothrottle

a two axis autopilot

a three axis autopilot

13. With the Autopilot engaged in the Alt mode the Captain alters the barometric setting. The aircraft:

switches barometric input over to the 1st Pilot setting

maintains its altitude

changes its altitude in accordance with the change in pressure setting

trips out of altitude hold.

14. L.NAV is an............. input to the ..............channel using data from the...........

inner loop, roll, ADC

outer loop, pitch, FMC

inner loop, pitch, ADC

outer loop, roll, FMC

15. The system which allows the pilot to control the aircraft with the servomotors engaged is called

touch control steering.

control wheel steering.

the electronic inner / outer axis loop.

the outer loop control.

16. In an autoland at 1000' AGL with two autopilots engaged

The engaged roll mode would be LOCALISER.

The engaged pitch mode would be FLARE

The armed roll mode would be LOCALISER

The engaged roll mode would be GLIDESLOPE

17. Inputs to the rudder channels initially originate from

AH gyro and turn and slip gyro

Servomotors

Compass gyro and turn and slip gyro

Compass gyro and gyro for AH

18. Autotrim is functional

In the pitch channel only with the autopilot engaged

In the pitch and roll channel with the autopilot disengaged

In the pitch and roll channel with the autopilot engaged

In the pitch channel only with the autopilot disengaged

19. If a fault develops in a Triplex auto-pilot system during an approach, the system will revert to

fail passive and the landing may continue.

fail operational.

a manual disconnect.

fail control wheel mode

20. The type of automatic landing system which would necessitate a manual landing after a system failure during an automatic approach is

fail passive.

fail operational.

fail active.

fail safe.

21. The mode that enables the pilot to manoeuvre his aircraft in pitch and roll by use of the automatic control system is called the

control wheel steering mode which will disengage the servomotors.

the touch control steering mode which will prevent the flaps retracting

control wheel steering (CWS )mode that allows the pilot to control the aircraft, and when the wheel is released, the aircraft holds the newly established attitude.

touch control steering that will permit the pilot to control the aircraft via the air data computer.

22. Central Air Data Computers (CADC's) transmit data concerning

airspeed, altitude and decision height

airspeed, altitude and Mach Number

airspeed, attitude and Mach Number

airspeed and altitude only

23. JAR 25 operational requirements for the installation of automatic pilot state that the system must have: A. automatic synchronisation B quick release controls on both control wheels.

Neither statement is correct.

Only statement A is correct

Only statement B is correct

Both statements are correct

24. Altitude Select and Altitude Hold are examples of

inner loop functions in pitch

outer loop functions in roll

interlocking functions

manometric functions from the ADC

25. Autopilot corrections affecting Pitch are carried out by

autothrottle

autotrim only

autotrim and elevators

elevators only

26. A single axis autopilot may also be called

Auto stabilisation loop

Wing leveller

Altitude hold

Pitch control loop

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

Fail soft

Fail passive

Land 2 system

Fail operational or fail active

28. For a commercial aircraft operating with a single pilot in IFR the minimum requirement is that the autopilot should have control in

Heading mode

Altitude Hold, Heading mode and Speed.

Altitude Hold and Heading mode

three axes

29. An automatic flight system which can safely continue with an automatic landing after a system failure is a

Three axis system

Fail redundant system

Fail operational system

Fail passive system

30. During a CAT 2 ILS automatic approach, the source for altitude information is the

radio altimeter which becomes effective below about 2,500 feet.

radar altimeter which becomes effective below about 2,500 feet.

mode comparator sensor.

basic altitude capsule stack.

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

Approaching decision height

Requiring a crew input

Fail active or fail operational

Fail passive

32. An auto pilot

is an auto stabilisation system

is a system which will maintain a preselected airspeed

Is an outer loop control system

Is a system which will maintain a preselected altitude

33. A single axis autopilot system

Provides control about the pitch axis

Is unsuitable for use in powered aircraft

Provides control about the roll axis

Provides stabilisation about the normal axis

34. An automatic flight control system

Can only be used in EFIS equipped aircraft

Applies flight data to the auto pilot system

Is automatically disengaged by a GPWS alert

Is another name for an autopilot system

35. Autopilot synchronisation in an aircraft

ensures that, when the autopilot is engaged, the take-over is effected smoothly and without snatching on the control system

requires that the interlocks are made before the autopilot will engage

requires that the aircraft is trimmed out before the autopilot can be engaged

needs at least two alternators running in parallel.

36. A rate gyro

Has three degrees of freedom, two gimbals and a transducer

Controls the outer loop inputs

Senses rate of turn and positions an indicator on the EHSI

Supplies rate and displacement information to the computer

37. The Autoland. sequence is considered to be complete when

the aircraft reaches the end of the runway.

reverse thrust is engaged

the aircraft touches down

the autopilot is manually disengaged by the pilot

38. An aircraft has yaw damping included in its auto stabilisation system. An essential requirement of such a system is

A three axis autopilot system

INS inputs to the CADC

Automatic maintenance of c of g position

Parallel connected servo motors

39. Heading hold mode relates to control in

the pitch channel via the inner loop.

the height lock via the CADC.

the manometer mode of the CADC.

the roll channel via the outer loop control source.

40. With the autopilot in CWS the pilot manoeuvres the aircraft and releases control. The aircraft will maintain

altitude and attitude

attitude at the time of release.

heading and altitude

heading, speed and attitude

41. To prevent servo motor runaway from producing excessive demands to the control surface

A torque limiter is fitted

A gyro damper is fitted

A gyro limiter is fitted

A torque converter is fitted

42. Inner loop stability is obtained by

raw data feed to the data control bus bar.

manometric locks.

‘I' bar displacement.

inputs from the Air Data Computer.

43. An autoland system that, in the event of an autopilot failure, continues to function without degradation of performance beyond the limits required automatic, would be one with the status

duplex

fail passive

fail operational

fail safe

44. For an autoland system to meet FAIL PASSIVE criteria it must

Can continue with an autoland above alert height

Have suitable system redundancy

Can continue with an autoland below alert height

Withstand a system failure without excessive deviations from flight path

45. The fundamental components of an autopilot control loop are

Rate gyro, servo motor, torque limiter

Servo motor, rate gyro, torque limiter, error signal generator

Rate gyro, servomotor, error signal generator

Torque limiter, error signal generator, servomotor

46. Automatic flight systems may be capable of controlling the aircraft flight in

Azimuth and elevation only

Azimuth and velocity only

Azimuth, elevation and velocity

Azimuth only

47. ALT HOLD is an example of

Inner loop control in the roll axis

Outer loop control about the longitudinal axis Outer loop control about the longitudinal axis

Inner loop control in the pitch axis

Outer loop input to the pitch channel

48. An automatic flight control system in which the application of normal forces on the control column allows the pilot to input demands to the autopilot is a

control wheel steering

touch control steering

series connected system

parallel connected system.

49. After a failure of one of the necessary redundant systems below alert height you would

carry out a missed approach.

continue descent and land automatically.

continue the descent but revert to a higher D.H.

disengage autoland and take over manually.

50. A device in a closed loop control system in which a small power input controls a much larger power output in a strictly proportionate manner is

A powered flying control unit

A servomechanism

A rate gyro

An amplifier

Question Bank

Questions for REVISION QUESTIONS – AFCS (AFCS)