Vayudoot Aviation

1. Inputs to the rudder channels initially originate from

AH gyro and turn and slip gyro

Compass gyro and turn and slip gyro

Compass gyro and gyro for AH

Servomotors

2. 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.

Only statement A is correct

Both statements are correct

Only statement B is correct

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

The engaged pitch mode would be FLARE

The engaged roll mode would be GLIDESLOPE

The engaged roll mode would be LOCALISER.

The armed roll mode would be LOCALISER

4. 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, wheel and speed

EPR, Mach and altitude.

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

airspeed and altitude only

airspeed, attitude and Mach Number

airspeed, altitude and Mach Number

airspeed, altitude and decision height

6. 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.

touch down mode and roll out mode

flare mode engage and roll out mode

flare mode arm and touch down mode.

7. A single axis autopilot may also be called

Pitch control loop

Wing leveller

Auto stabilisation loop

Altitude hold

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

mode comparator sensor.

basic altitude capsule stack.

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

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

9. Altitude Select and Altitude Hold are examples of

manometric functions from the ADC

interlocking functions

inner loop functions in pitch

outer loop functions in roll

10. A rate gyro

Supplies rate and displacement information to the computer

Senses rate of turn and positions an indicator on the EHSI

Controls the outer loop inputs

Has three degrees of freedom, two gimbals and a transducer

11. 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

being in a straight and level position

switching on the yaw dampers.

disengaging the autotrim

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

attitude at the time of release.

altitude and attitude

heading, speed and attitude

heading and altitude

13. A single axis autopilot system

Is unsuitable for use in powered aircraft

Provides control about the pitch axis

Provides control about the roll axis

Provides stabilisation about the normal axis

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

Requiring a crew input

Fail passive

Approaching decision height

Fail active or fail operational

15. An automatic flight control system

Can only be used in EFIS equipped aircraft

Is another name for an autopilot system

Is automatically disengaged by a GPWS alert

Applies flight data to the auto pilot system

16. 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 high subsonic speeds with the autopilot engaged or not.

At mach one with the autopilot engaged or not

All the time

17. 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

automatically switches to Heading mode

tunes to the next VOR on the route

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

decouples from the VOR and disconnects

18. An auto pilot

Is a system which will maintain a preselected altitude

Is an outer loop control system

is a system which will maintain a preselected airspeed

is an auto stabilisation system

19. During an autoland approach

Flare is engaged at 1500'agl

localiser roll control is disengaged just prior to touchdown

flare is disengaged prior to touchdown at 5'GA

glideslope is the engaged pitch mode until 5'GA

20. Touch control steering

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

prevents aerodynamic feedback.

will only operate while the flaps are down.,

engages the servomotors during manual operation in pitch and roll.

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

outer loop, pitch, FMC

inner loop, pitch, ADC

outer loop, roll, FMC

inner loop, roll, ADC

22. 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.

23. 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 control wheel mode

fail operational.

24. During an approach to an autoland at 1500 feet

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

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

25. Control wheel steering enables a pilot to

taxy the aircraft on the ground

manoeuvre the aircraft with the autopilot disengaged.

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

26. 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.

27. Inner loop stability is obtained by

inputs from the Air Data Computer.

raw data feed to the data control bus bar.

manometric locks.

‘I' bar displacement.

28. 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 safe

fail operational

fail passive

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

glideslope localiser

flare roll out

flare localiser

glideslope roll out

30. 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.

Both statements are correct

Only statement B is correct

Only statement A is correct

Neither statement is correct.

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

Parallel connected servo motors

A three axis autopilot system

INS inputs to the CADC

Automatic maintenance of c of g position

32. 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

33. Heading hold mode relates to control in

the height lock via the CADC.

the pitch channel via the inner loop.

the roll channel via the outer loop control source.

the manometer mode of the CADC.

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

Azimuth and velocity only

Azimuth and elevation only

Azimuth, elevation and velocity

Azimuth only

35. ALT HOLD is an example of

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

Inner loop control in the roll axis

36. The control laws for an autopilot are known as

alternate law and direct law

normal law and emergency law

normal, alternate and emergency laws

normal, alternate and direct laws.

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

a stable reference device.

an interlock control

feedback

a tacho-generator.

38. Autotrim is functional

In the pitch channel only with the autopilot engaged

In the pitch and roll channel with the autopilot engaged

In the pitch and roll channel with the autopilot disengaged

In the pitch channel only with the autopilot disengaged

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

Land 2 system

Fail soft

Fail operational or fail active

Fail passive

40. 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 safe.

fail active.

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

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

the touch control steering mode which will prevent the flaps retracting

control wheel steering mode which will disengage the servomotors.

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.

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

a three axis autopilot

a two axis autopilot with autothrottle

single axis autopilot

a two axis autopilot

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

A gyro limiter is fitted

A gyro damper is fitted

A torque limiter is fitted

A torque converter is fitted

44. Autopilot synchronisation in an aircraft

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

needs at least two alternators running in parallel.

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

45. 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

46. 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 rate gyro

A servomechanism

A powered flying control unit

An amplifier

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

Can continue with an autoland below alert height

Can continue with an autoland above alert height

Withstand a system failure without excessive deviations from flight path

Have suitable system redundancy

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

fail soft ability.

fail symbol ability.

fail operational ability.

fail passive ability

49. 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

50. 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.

three axes

Altitude Hold and Heading mode

Question Bank

Questions for REVISION QUESTIONS – AFCS (AFCS)