Vayudoot Aviation

1. Touch control steering

engages the servomotors during manual operation in pitch and roll.

prevents aerodynamic feedback.

will only operate while the flaps are down.,

allows the pilot to control the aircraft with the servomotors disengaged.

2. During an approach to an autoland at 1500 feet

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

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

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

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

maintains its altitude

changes its altitude in accordance with the change in pressure setting

trips out of altitude hold.

switches barometric input over to the 1st Pilot setting

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

control wheel steering.

touch control steering.

the outer loop control.

the electronic inner / outer axis loop.

5. An auto pilot

Is a system which will maintain a preselected altitude

Is an outer loop control system

is an auto stabilisation system

is a system which will maintain a preselected airspeed

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

a tacho-generator.

an interlock control

feedback

a stable reference device.

7. The fundamental components of an autopilot control loop are

Torque limiter, error signal generator, servomotor

Rate gyro, servomotor, error signal generator

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

Rate gyro, servo motor, torque limiter

8. 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

fail safe

fail operational

fail passive

duplex

9. Altitude Select and Altitude Hold are examples of

manometric functions from the ADC

outer loop functions in roll

inner loop functions in pitch

interlocking functions

10. Inner loop stability is obtained by

raw data feed to the data control bus bar.

inputs from the Air Data Computer.

manometric locks.

‘I' bar displacement.

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

Have suitable system redundancy

Can continue with an autoland above alert height

Withstand a system failure without excessive deviations from flight path

Can continue with an autoland below alert height

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

carry out a missed approach.

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

disengage autoland and take over manually.

continue descent and land automatically.

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

Fail passive

Fail soft

Fail operational or fail active

Land 2 system

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

A gyro damper is fitted

A torque limiter is fitted

A torque converter is fitted

A gyro limiter is fitted

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

Fail redundant system

Fail passive system

Fail operational system

Three axis system

16. A single axis autopilot may also be called

Altitude hold

Pitch control loop

Wing leveller

Auto stabilisation loop

17. Consider the following statements regarding flight envelope protection: A High speed protection prevents the airspeed from exceeding Vmo/Mmo B High angle of attack protection comes in when the aircraft reaches the stalling AoA

Only statement A is correct

Both statements are correct

Neither statement is correct.

Only statement B is correct

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

a two axis autopilot

a three axis autopilot

single axis autopilot

a two axis autopilot with autothrottle

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

Altitude Hold and Heading mode

Heading mode

three axes

Altitude Hold, Heading mode and Speed.

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

fail control wheel mode

fail passive and the landing may continue.

fail operational.

a manual disconnect.

21. An aircraft on Autopilot is engaged in the VOR mode and loses the VOR signals as it flies through the VOR cone of silence. The autopilot

decouples from the VOR and flies the last heading for a fixed period.

decouples from the VOR and disconnects

automatically switches to Heading mode

tunes to the next VOR on the route

22. A single axis autopilot system

Provides control about the roll axis

Is unsuitable for use in powered aircraft

Provides control about the pitch axis

Provides stabilisation about the normal axis

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

operates only in conjunction with the autopilot

usually operates on all three axes

can be engaged without the autopilot

is not needed if the autopilot is engaged

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

control wheel steering mode which will disengage the servomotors.

the touch control steering mode which will prevent the flaps retracting

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

25. Inputs to the rudder channels initially originate from

Compass gyro and gyro for AH

AH gyro and turn and slip gyro

Compass gyro and turn and slip gyro

Servomotors

26. A rate gyro

Supplies rate and displacement information to the computer

Controls the outer loop inputs

Has three degrees of freedom, two gimbals and a transducer

Senses rate of turn and positions an indicator on the EHSI

27. Autopilot corrections affecting Pitch are carried out by

elevators only

autotrim and elevators

autothrottle

autotrim only

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

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

the AoA reaches the stalling angle

TOGA button is pressed

reverse thrust is selected in flight

29. 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

parallel connected system.

control wheel steering

series connected system

touch control steering

30. Heading hold mode relates to control in

the roll channel via the outer loop control source.

the manometer mode of the CADC.

the height lock via the CADC.

the pitch channel via the inner loop.

31. During an autoland approach

flare is disengaged prior to touchdown at 5'GA

Flare is engaged at 1500'agl

localiser roll control is disengaged just prior to touchdown

glideslope is the engaged pitch mode until 5'GA

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

EPR, Mach and Speed.

EPR, wheel and altitude.

EPR, Mach and altitude.

EPR, wheel and speed

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

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

mode comparator sensor.

basic altitude capsule stack.

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

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

reverse thrust is engaged

the aircraft touches down

the autopilot is manually disengaged by the pilot

the aircraft reaches the end of the runway.

35. 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

An amplifier

A powered flying control unit

A rate gyro

A servomechanism

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

INS inputs to the CADC

Parallel connected servo motors

Automatic maintenance of c of g position

A three axis autopilot system

37. When localiser and glide slope are captured at 1,500 feet during an automatic landing sequence, two other functions will be activated at the same time, they are

flare mode arm and off line channels engaged.

flare mode arm and touch down mode.

touch down mode and roll out mode

flare mode engage and roll out mode

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

flare localiser

glideslope localiser

flare roll out

glideslope roll out

39. An automatic flight control system

Applies flight data to the auto pilot system

Can only be used in EFIS equipped aircraft

Is another name for an autopilot system

Is automatically disengaged by a GPWS alert

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

Azimuth only

Azimuth and velocity only

Azimuth and elevation only

Azimuth, elevation and velocity

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

Fail active or fail operational

Approaching decision height

Requiring a crew input

Fail passive

42. Autopilot synchronisation in an aircraft

needs at least two alternators running in parallel.

requires that the interlocks are made before the autopilot will engage

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

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

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

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

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

The CWS is only there for steering on the ground

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

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

airspeed and altitude only

airspeed, altitude and decision height

airspeed, altitude and Mach Number

airspeed, attitude and Mach Number

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

At mach one with the autopilot engaged or not

At high mach numbers with the autopilot engaged

All the time

At high subsonic speeds with the autopilot engaged or not.

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

The engaged roll mode would be LOCALISER.

The engaged roll mode would be GLIDESLOPE

The engaged pitch mode would be FLARE

The armed roll mode would be LOCALISER

47. For an aircraft with a non-synchronised autopilot system, ‘snatching' of the controls by the autopilot when engaging or disengaging can be prevented by

disengaging the autotrim

being in a straight and level position

switching on the yaw dampers.

the pilot ensuring that the aircraft is trimmed out before selecting or disengaging the autopilot

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

fail safe.

fail operational.

fail passive.

fail active.

49. 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

50. 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, speed and attitude

heading and altitude

Question Bank

Questions for REVISION QUESTIONS – AFCS (AFCS)