Vayudoot Aviation

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

fail symbol ability.

fail operational ability.

fail soft ability.

fail passive ability

2. An auto pilot

Is an outer loop control system

is an auto stabilisation system

Is a system which will maintain a preselected altitude

is a system which will maintain a preselected airspeed

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

maintains its altitude

switches barometric input over to the 1st Pilot setting

changes its altitude in accordance with the change in pressure setting

trips out of altitude hold.

4. During an approach to an autoland at 1500 feet

Off line channels are manually engaged, flare mode is armed

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

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

5. Autopilot corrections affecting Pitch are carried out by

elevators only

autotrim only

autotrim and elevators

autothrottle

6. ALT HOLD is an example of

Inner loop control in the pitch axis

Outer loop input to the pitch channel

Inner loop control in the roll axis

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

7. 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

a three axis autopilot

a two axis autopilot with autothrottle

8. 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 engage and roll out mode

touch down mode and roll out mode

flare mode arm and touch down mode.

flare mode arm and off line channels engaged.

9. Control wheel steering enables a pilot to

manoeuvre the aircraft in the air while the autopilot is engaged

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

manoeuvre the aircraft with the autopilot disengaged.

taxy the aircraft on the ground

10. During an autoland approach

localiser roll control is disengaged just prior to touchdown

glideslope is the engaged pitch mode until 5'GA

flare is disengaged prior to touchdown at 5'GA

Flare is engaged at 1500'agl

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

A gyro damper is fitted

A torque converter is fitted

A gyro limiter is fitted

A torque limiter is fitted

12. The control laws for an autopilot are known as

alternate law and direct law

normal, alternate and emergency laws

normal law and emergency law

normal, alternate and direct laws.

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

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.

control wheel steering mode which will disengage the servomotors.

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

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

Land 2 system

Fail passive

Fail operational or fail active

Fail soft

15. A rate gyro

Controls the outer loop inputs

Senses rate of turn and positions an indicator on the EHSI

Supplies rate and displacement information to the computer

Has three degrees of freedom, two gimbals and a transducer

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

disengage autoland and take over manually.

continue descent and land automatically.

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

carry out a missed approach.

17. 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

touch control steering

parallel connected system.

control wheel steering

series connected system

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

control wheel steering.

touch control steering.

the electronic inner / outer axis loop.

the outer loop control.

19. Inputs to the rudder channels initially originate from

Compass gyro and turn and slip gyro

AH gyro and turn and slip gyro

Servomotors

Compass gyro and gyro for AH

20. 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 channel only with the autopilot disengaged

In the pitch and roll channel with the autopilot engaged

21. 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

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

The engaged roll mode would be LOCALISER.

The armed roll mode would be LOCALISER

The engaged pitch mode would be FLARE

The engaged roll mode would be GLIDESLOPE

23. 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

reverse thrust is selected in flight

TOGA button is pressed

the AoA reaches the stalling angle

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

EPR, Mach and altitude.

EPR, wheel and altitude.

EPR, Mach and Speed.

EPR, wheel and speed

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

Fail operational system

Fail redundant system

Three axis system

Fail passive system

26. Inner loop stability is obtained by

‘I' bar displacement.

inputs from the Air Data Computer.

raw data feed to the data control bus bar.

manometric locks.

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

inner loop, pitch, ADC

outer loop, pitch, FMC

inner loop, roll, ADC

outer loop, roll, FMC

28. A single axis autopilot may also be called

Wing leveller

Pitch control loop

Auto stabilisation loop

Altitude hold

29. 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

Altitude Hold, Heading mode and Speed.

three axes

Heading mode

30. 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 disconnects

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

tunes to the next VOR on the route

automatically switches to Heading mode

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

A three axis autopilot system

Parallel connected servo motors

INS inputs to the CADC

Automatic maintenance of c of g position

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

the autopilot is manually disengaged by the pilot

reverse thrust is engaged

the aircraft touches down

the aircraft reaches the end of the runway.

33. 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.

a manual disconnect.

fail operational.

fail control wheel mode

34. 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 rate gyro

An amplifier

A servomechanism

35. 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

Neither statement is correct.

Both statements are correct

Only statement B is correct

Only statement A is correct

36. 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 operational

fail passive

duplex

fail safe

37. 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

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

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

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

airspeed, attitude and Mach Number

airspeed, altitude and Mach Number

airspeed, altitude and decision height

airspeed and altitude only

39. An automatic flight control system

Is automatically disengaged by a GPWS alert

Applies flight data to the auto pilot system

Can only be used in EFIS equipped aircraft

Is another name for an autopilot system

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

glideslope roll out

glideslope localiser

flare roll out

flare localiser

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

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

basic altitude capsule stack.

mode comparator sensor.

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

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

altitude and attitude

heading, speed and attitude

attitude at the time of release.

heading and altitude

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

can be engaged without the autopilot

operates only in conjunction with the autopilot

usually operates on all three axes

is not needed if the autopilot is engaged

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

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

switching on the yaw dampers.

disengaging the autotrim

being in a straight and level position

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

Azimuth and elevation only

Azimuth, elevation and velocity

Azimuth only

Azimuth and velocity only

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

fail passive.

fail safe.

fail active.

fail operational.

47. The fundamental components of an autopilot control loop are

Rate gyro, servo motor, torque limiter

Rate gyro, servomotor, error signal generator

Torque limiter, error signal generator, servomotor

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

48. Altitude Select and Altitude Hold are examples of

inner loop functions in pitch

outer loop functions in roll

manometric functions from the ADC

interlocking functions

49. Autopilot synchronisation in an aircraft

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

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

needs at least two alternators running in parallel.

requires that the interlocks are made before the autopilot will engage

50. 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

Question Bank

Questions for REVISION QUESTIONS – AFCS (AFCS)