11.9 Flight Controls MCQ's

Question 1

In an aircraft flying control system employing servo-tabs, the installation of external ground locks to the main control surface.
Option A. would not prevent movement of the control column.
Option B. is unnecessary since the system is irreversible and therefore the control surface cannot be displaced by the wind.
Option C. would also prevent movement of the control column.

Answer 1

Correct Answer is. would not prevent movement of the control column.

Question 2

A full time yaw damper system detects.
Option A. band pass frequencies.
Option B. all frequencies.
Option C. only low frequencies.

Answer 2

Correct Answer is. band pass frequencies.

Question 3

With respect to flight spoilers, they.
Option A. can operate both on the ground and in flight.
Option B. only operate on the ground.
Option C. only operate in flight.

Answer 3

Correct Answer is. can operate both on the ground and in flight.
Explanation. Flight spoilers are used in flight and on the ground. However Ground spoilers can ONLY be used on the ground.

Question 4

The bearing used in a fibre pulley is.
Option A. a ball bearing.
Option B. a roller bearing.
Option C. a plain bearing.

Answer 4

Correct Answer is. a ball bearing.
Explanation. Ball bearings are used in fibre pulleys.

Question 5

When the primary stops fitted to a control run have been contacted.
Option A. a clearance exists at the secondary stops.
Option B. the secondary stops have been over-ridden.
Option C. the secondary stops will just be in contact.

Answer 5

Correct Answer is. a clearance exists at the secondary stops.
Explanation. The clearance is on the secondary stops.

Question 6

Excessive wear on both sides of the control cable pulley groove is evidence of.
Option A. excessive cable tension.
Option B. pulley misalignment.
Option C. cable misalignment.

Answer 6

Correct Answer is. pulley misalignment.

Question 7

A universal protractor used to measure degrees of aileron travel should be zeroed.
Option A. when the aircraft is in level flight attitude.
Option B. with the aileron in the neutral position.
Option C. with the aileron in the down position.

Answer 7

Correct Answer is. with the aileron in the neutral position.

Question 8

A flying control static friction check.
Option A. can only be carried out during flight.
Option B. demonstrates the force the pilot requires to overcome system inertia and move the controls.
Option C. will demonstrate that a high force is always necessary to operate non-powered controls.

Answer 8

Correct Answer is. demonstrates the force the pilot requires to overcome system inertia and move the controls.
Explanation. A static friction check demonstrates the force the pilot requires to overcome system inertia and move the controls.

Question 9

What is an aileron balance cable for?.
Option A. To allow the cable to be tensioned.
Option B. To correct for wing heaviness.
Option C. To allow aircraft to fly hands off.

Answer 9

Correct Answer is. To allow the cable to be tensioned.

Question 10

With the elevator trim wheel adjusted fully aft. (nose up), range of movement of the elevator is restricted.
Option A. would make no difference to the movement.
Option B. for ‘down’ travel movement.
Option C. for ‘up’ travel movement.

Answer 10

Correct Answer is. for ‘up’ travel movement.
Explanation. Use of trim reduces the associated control movement direction range.

Question 11

On the ground, spoilers/speedbrakes deploy to.
Option A. 15°.
Option B. 30°.
Option C. 60°.

Answer 11

Correct Answer is. 60°.

Question 12

A horn balance on a control will.
Option A. increase degree of movement at high speed.
Option B. decrease degree of movement at low speed.
Option C. decrease degree of movement at high speed.

Answer 12

Correct Answer is. increase degree of movement at high speed.
Explanation. For a given pilot effort, the horn balance increases movement.

Question 13

In normal flight, if the control column is pulled back, a servo tab fitted to the elevator will.
Option A. move up.
Option B. remain in line with the elevator.
Option C. move down.

Answer 13

Correct Answer is. move down.

Servo tab is a small hinged device installed on an aircraft control surface to assist the movement of the control surfaces.

Question 14

In normal flight, if the control wheel is moved to the left, then the aileron on the right wing will.
Option A. decrease the angle of attack of the right hand wing.
Option B. increase the angle of attack of the right hand wing.
Option C. keep the angle of attack of the right wing constant.

Answer 14

Correct Answer is. increase the angle of attack of the right hand wing.
Explanation. Could also be answered ‘b’, depending on whether it means the cause or the effect. The downgoing aileron (the right one) has an increase in AoA locally, which makes the wing lift, thusreducing the AoA of the wing as a whole.

Question 15

On an aircraft fitted with elevons in normal flight, if a column is moved forward, the elevons will.
Option A. remain stationary.
Option B. both move down.
Option C. both move up.

Answer 15

Correct Answer is. both move down.

Question 16

To avoid moments bending the root of the wing, the aircraft will be fitted with.
Option A. integrated fuel monitoring system.
Option B. symmetrical flight control trim.
Option C. automatic trim control for controlled turns and rudder movements.

Answer 16

Correct Answer is. symmetrical flight control trim.

Question 17

A yaw damper gain could be fitted with.
Option A. decreases sensitivity for decreased speed.
Option B. increased sensitivity for increased speed.
Option C. decreases sensitivity for increased speed.

Answer 17

Correct Answer is. increased sensitivity for increased speed.

Question 18

In an aircraft system employing balance tabs, the installation of external ground locks between the control surface and the balance tabs.
Option A. would prevent the movement of the control column.
Option B. is unnecessary since the system is irreversible.
Option C. would not prevent the movement of the control column.

Answer 18

Correct Answer is. would prevent the movement of the control column.

Question 19

The two switches for pitch trim are located.
Option A. on the control column acting like an ‘AND’ switch.
Option B. on the control column with the captain having priority over the First Officer.
Option C. on the control column acting like an ‘OR’ switch.

Answer 19

Correct Answer is. on the control column acting like an ‘AND’ switch.
Explanation. The ‘split’ trim switch has one half closing a relay to ‘enable’ power to the trim motor, and to engage the clutch. The other switch half is to supply the power to the motor. Both must be operated together, to operate the trim.

Question 20

If the flaps are sluggish or erratic on final approach, the possible cause may be.
Option A. flap tracks out of rigging.
Option B. bearing seized.
Option C. flap motor internal leakage.

Answer 20

Correct Answer is. flap motor internal leakage.

Question 21

In fully Fly By Wire aircraft, wing root bending moments are reduced by.
Option A. transfer of fuel from one wing tank to another.
Option B. operation of the elevator.
Option C. symmetrical application of ailerons.

Answer 21

Correct Answer is. symmetrical application of ailerons.

Question 22

Yaw damping rate changes with.
Option A. airspeed.
Option B. flap position.
Option C. altitude.

Answer 22

Correct Answer is. airspeed.

Question 23

What is the main purpose of a frize aileron?.
Option A. Decrease drag on the up going wing.
Option B. Help pilot overcome aerodynamic loads.
Option C. Increase drag on the up going wing.

Answer 23

Correct Answer is. Decrease drag on the up going wing.
Explanation. The Frise aileron increases drag on the up-going aileron, which is on the downgoing wing. And Vise versa on the other aileron.

Question 24

What happens to a hydraulically operated flight control surface when pressure is removed?.
Option A. Droop.
Option B. Remain in last position.
Option C. Go to neutral.

Answer 24

Correct Answer is. Droop.
Explanation. “The drop in pressure releases a valve which lets the fluid pass easily from one side of actuator piston to the
other. This is to prevent a hydraulic lock and permit manual reversion. Surfaces behave like manually controlled surfaces.

Question 25

Oscillation and hunting of flight control surface are prevented by.
Option A. fitting a tachogenerator.
Option B. feedback from the servo motor.
Option C. feedback from control surface.

Answer 25

Correct Answer is. fitting a tachogenerator.

Question 26

Stick shaker activates at a speed which is above the stalling speed by.
Option A. 4%.
Option B. 7%.
Option C. 10.321%.

Answer 26

Correct Answer is. 7%.

Question 27

A wing mounted stall warning vane.
Option A. moves down at impending stall.
Option B. moves up at impending stall.
Option C. gives a visual indication of impending stall.

Answer 27

Correct Answer is. moves up at impending stall.

Question 28

During an autopilot controlled turn.
Option A. ailerons, rudder and THS will move.
Option B. ailerons and rudder will move.
Option C. ailerons, rudder and elevators will move.

Answer 28

Correct Answer is. ailerons, rudder and elevators will move.

Question 29

On a full fly-by-wire system, a speedbrake screwjack servomotor is controlled by the.
Option A. flight augmentation computer.
Option B. flight control computer.
Option C. flight management and guidance computer.

Answer 29

Correct Answer is. flight control computer.

Question 30

In a fly-by-wire aircraft, what controls the roll spoilers?.
Option A. Flight control computer.
Option B. Flight augmentation computer.
Option C. Flight management computer.

Answer 30

Correct Answer is. Flight control computer.

Question 31

Mass balance weights are used to.
Option A. balance the trailing edge of flying control surfaces.
Option B. counteract flutter on control surfaces.
Option C. balance the tabs.

Answer 31

Correct Answer is. counteract flutter on control surfaces.

Question 32

Active load control involves.
Option A. limiting the deflection of control surface with airspeed.
Option B. intervention & monitoring the human pilot.
Option C. varying lift force to control vertical movement of the aircraft.

Answer 32

Correct Answer is. varying lift force to control vertical movement of the aircraft.

Question 33

Active load control uses.
Option A. elevator and aileron.
Option B. aileron and spoiler.
Option C. elevator and stab.

Answer 33

Correct Answer is. aileron and spoiler.

Question 34

The purpose of the autopilot servo-motor torque setting is to.
Option A. protect the servo motor.
Option B. damp the system oscillation.
Option C. prevent control surface runaway.

Answer 34

Correct Answer is. prevent control surface runaway.

Question 35

In a fully Fly By Wire Aircraft, ground spoilers are deployed automatically when the aircraft is on ground and.
Option A. brakes are deployed.
Option B. thrust reversers are deployed.
Option C. weight on ground switch is activated.

Answer 35

Correct Answer is. thrust reversers are deployed.

Question 36

In a fully Fly By Wire aircraft, rudder trim is nulled by the.
Option A. Flight Augmentation Computers.
Option B. electric flight control unit.
Option C. Flight Guidance and Management Computer.

Answer 36

Correct Answer is. Flight Augmentation Computers.

Question 37

Aileron input is fed into the yaw damper system to.
Option A. prevent nose pitching down.
Option B. prevent nose pitching up.
Option C. prevent adverse yaw in a turn.

Answer 37

Correct Answer is. prevent adverse yaw in a turn.

Question 38

Pitch trimming in autopilot is initiated by.
Option A. C of G movement.
Option B. pitch of aircraft in cruise.
Option C. continued pitch input.

Answer 38

Correct Answer is. continued pitch input.
Explanation. If the elevator is deflected over a long time, the AFCS trims the horizontal stabilizer to eliminate the elevator deflection load.

Question 39

Differential aileron control will.
Option A. cause a nose up moment.
Option B. prevent yawing in conjunction with rudder input.
Option C. cause a nose down moment.

Answer 39

Correct Answer is. prevent yawing in conjunction with rudder input.

Question 40

On a fly-by-wire aircraft, what controls stabilizer trim?.
Option A. SEC.
Option B. ELAC and SEC.
Option C. ELAC.

Answer 40

Correct Answer is. ELAC and SEC.

Question 41

In an automatic flight control system, when may the yaw damper be applied?.
Option A. During manual control only.
Option B. During either manual or automatic control.
Option C. During automatic control only.

Answer 41

Correct Answer is. During either manual or automatic control.

Question 42

Flutter can be prevented by.
Option A. mass balance.
Option B. trim tabs.
Option C. balance panels.

Answer 42

Correct Answer is. mass balance.

Question 43

In a fully fly by wire system, if the elevator loses all electrical power.
Option A. servos lock at last position.
Option B. servos remain stationary and provide damping.
Option C. servos move to neutral and lock.

Answer 43

Correct Answer is. servos remain stationary and provide damping.

Question 44

In an auto trim system, for the trim system to operate.
Option A. operation of the trim controls is required.
Option B. autopilot need not be engaged.
Option C. autopilot must be engaged.

Answer 44

Correct Answer is. autopilot need not be engaged.

Question 45

In an autopilot coordinated turn, when the turn angle is reached.
Option A. both ailerons are down.
Option B. one is up one is down.
Option C. the ailerons are faired.

Answer 45

Correct Answer is. the ailerons are faired.
Explanation. Due to the aircraft’s neutral lateral stability, the ailerons are neutralised (faired) and the aircraft will hold the turn.

Question 46

How is automatic angle of attack protection provided?.
Option A. Fast/Slow indication.
Option B. Reduce flap deployment.
Option C. Autothrottle applying more power.

Answer 46

Correct Answer is. Autothrottle applying more power.

Question 47

A single failure of fly by wire.
Option A. will reduce the operational height and speed.
Option B. will limit the flight profile.
Option C. has no effect on the aircraft’s operation.

Answer 47

Correct Answer is. has no effect on the aircraft’s operation.
Explanation. NIL.

Question 48

Fly-by-wire load alleviation function in turbulent weather conditions will result in.
Option A. spoiler moving symmetrically upward.
Option B. ailerons moving symmetrically upward.
Option C. ailerons and spoiler moving symmetrically upward.

Answer 48

Correct Answer is. ailerons and spoiler moving symmetrically upward.

Question 49

Autotrim will switch to ‘slow’ when.
Option A. flaps are retracted.
Option B. landing gear up and locked.
Option C. flaps are extended.

Answer 49

Correct Answer is. flaps are retracted.

Question 50

How is the stabiliser automatically controlled in normal manual operation?.
Option A. Mach/Speed Trim.
Option B. Pitch Trim.
Option C. Electric Trim.

Answer 50

Correct Answer is. Mach/Speed Trim.

Question 51

Spoiler position feedback is provided by a.
Option A. a S.C.M.
Option B. an R.V.D.T.
Option C. a microswitch.

Answer 51

Correct Answer is. an R.V.D.T.

Question 52

Rudder ‘Q’ limiting.
Option A. restricts rudder movement with increase in airspeed.
Option B. increases rudder movement with increase in airspeed.
Option C. increases feel as airspeed increases.

Answer 52

Correct Answer is. restricts rudder movement with increase in airspeed.

Question 53

Elevons combine the functions of both.
Option A. elevator and aileron.
Option B. rudder and aileron.
Option C. rudder and elevator.

Answer 53

Correct Answer is. elevator and aileron.

Question 54

A differential aileron system is designed to.
Option A. minimise flutter.
Option B. prevent adverse yaw.
Option C. compensate for aileron reversal.

Answer 54

Correct Answer is. prevent adverse yaw.

Question 55

An artificial feel system is required.
Option A. for power assisted control systems.
Option B. for proportional control systems.
Option C. for power operated control systems.

Answer 55

Correct Answer is. for power operated control systems.

Question 56

A tandem P.F.C.U.
Option A. has the actuator rams co-axial.
Option B. has two control surfaces under its control.
Option C. has the actuator rams parallel.

Answer 56

Correct Answer is. has the actuator rams co-axial.

Question 57

What is the purpose of a differential Frise aileron?.
Option A. To decrease the drag and decrease the rate of yaw and turn.
Option B. Has no effect on rate of yaw and turn.
Option C. To increase the drag to increase the rate of yaw and turn.

Answer 57

Correct Answer is. To increase the drag to increase the rate of yaw and turn

Question 58

Active load control uses.
Option A. elevator and stab.
Option B. elevator and ailerons.
Option C. ailerons and spoilers.

Answer 58

Correct Answer is. ailerons and spoilers.

Question 59

An artificial feel system is necessary in a powered flying control system to.
Option A. increasing the sensitivity of the control system.
Option B. provide the pilot with simulated stick forces.
Option C. prevent overloading of the power control units.

Answer 59

Correct Answer is. provide the pilot with simulated stick forces.

Question 60

In the event of hydraulic failure in a power control system, a requirement of the manual reversion is that it must be.
Option A. operated by the standby hydraulic system.
Option B. automatic and instantaneous.
Option C. possible, but not recommended.

Answer 60

Correct Answer is. automatic and instantaneous.

Question 61

The purpose of control cable regulators is to.
Option A. maintain preset cable tensions during flight.
Option B. compensate for high temperature only.
Option C. compensate for low temperature only.

Answer 61

Correct Answer is. maintain preset cable tensions during flight.

Question 62

Range of movements of power operated flying control surfaces are limited by.
Option A. travel of the jack body.
Option B. mechanical stops in the control system.
Option C. travel of the jack ram.

Answer 62

Correct Answer is. mechanical stops in the control system.

Question 63

The aircraft is controlled about the lateral axis by the.
Option A. ailerons.
Option B. rudder.
Option C. elevator.

Answer 63

Correct Answer is. elevator.

Question 64

The aircraft is controlled about the normal axis by the.
Option A. elevato.
Option B. rudder.
Option C. ailerons.

Answer 64

Correct Answer is. rudder.

Normal = Vertical Axis

Question 65

The purpose of the Servo Valve in a power operated control is.
Option A. to provide pressure to operate the control.
Option B. to direct hydraulic fluid to the jack in response to the pilots control in cockpit.
Option C. to revert the system to manual operation.

Answer 65

Correct Answer is. to direct hydraulic fluid to the jack in response to the pilots control in cockpit.

Question 66

A stick shaker is a device which.
Option A. helps extricate an aircraft from soft ground.
Option B. gives a short period of extra lift to assist take off.
Option C. vibrates the control column near stalling speed.

Answer 66

Correct Answer is. vibrates the control column near stalling speed.

Question 67

The aircraft is controlled about the longitudinal axis by the.
Option A. ailerons.
Option B. elevator.
Option C. rudder.

Answer 67

Correct Answer is. ailerons.

Question 68

Ruddervators when moved, will move.
Option A. either opposite each other or together, depending on the selection.
Option B. together only.
Option C. opposite to each other only.

Answer 68

Correct Answer is. either opposite each other or together, depending on the selection.

Question 69

As a consequence of the C of G being close to its aft limit.
Option A. the stick forces when pitching the nose down will be very high.
Option B. the stick forces to manoeuvre longitudinally will be low due to the low stability.
Option C. the stick forces will be high in fore and aft pitch, due to the high longitudinal stability.

Answer 69

Correct Answer is. the stick forces when pitching the nose down will be very high.

Question 70

An anti-balance tab is moved.
Option A. hydraulically.
Option B. when the C.G. changes.
Option C. via a fixed linkage.

Answer 70

Correct Answer is. via a fixed linkage.

Question 71

A servo tab is operated.
Option A. directly by the pilot to produce forces which in turn move the main control surfaces.
Option B. by a trim wheel and moves in the opposite direction to the main control surfaces when moved.
Option C. automatically, and moves in the same direction as the main control surfaces.

Answer 71

Correct Answer is. directly by the pilot to produce forces which in turn move the main control surfaces.

Question 72

When checking full range of control surface movement, they must be positioned by.
Option A. operating the flightdeck/cockpit controls until the system is against the primary stops.
Option B. moving them by hand directly until against the primary stops.
Option C. moving them by hand directly until against the secondary stops.

Answer 72

Correct Answer is. operating the flightdeck/cockpit controls until the system is against the primary stops.

Question 73

The higher speed of the high wing in a banked turn causes it to have more drag than the low wing, this may be compensated for by.
Option A. operating the ailerons into the opposite sense once the correct angle of bank has been reached.
Option B. use of the rudder control.
Option C. increasing the ‘nose up’ pitch by use of the elevators.

Answer 73

Correct Answer is. use of the rudder control.

Question 74

The type of flap which extends rearwards when lowered is called a.
Option A. split flap.
Option B. plain flap.
Option C. Fowler flap.

Answer 74

Correct Answer is. Fowler flap.

Question 75

Which of the following trailing edge flaps give an increase in wing area?.
Option A. Split flap.
Option B. Slotted flap.
Option C. Fowler flap.

Answer 75

Correct Answer is. Fowler flap.

Question 76

Which of the following is not a primary flying control?.
Option A. Tailplane.
Option B. Elevator.
Option C. Rudder.

Answer 76

Correct Answer is. Tailplane.

Question 77

A tab which assists the pilot to move a flying control by moving automatically in the opposite direction to the control surface is called a.
Option A. trim tab.
Option B. servo tab.
Option C. geared balance tab.

Answer 77

Correct Answer is. geared balance tab.

Question 78

What is fitted on the aircraft to enable the pilot to reduce his speed rapidly in event of severe turbulence, or speed tending to rise above the Never Exceed Limit?.
Option A. Wheel brakes.
Option B. Air brakes.
Option C. Lift dumpers.

Answer 78

Correct Answer is. Air brakes.

Question 79

When spoilers are used asymmetrically, they combine with.
Option A. ailerons.
Option B. elevators.
Option C. rudder.

Answer 79

Correct Answer is. ailerons.

Question 80

What is used to correct any tendency of the aircraft to move towards an undesirable flight attitude?.
Option A. Trim tabs.
Option B. Spring tabs.
Option C. Balance tabs.

Answer 80

Correct Answer is. Trim tabs.

Question 81

With hydraulic ram operated flying controls, when the pressure is reduced to zero, the flying control surfaces.
Option A. stay at neutral.
Option B. droop.
Option C. remain in the position they were when power was removed.

Answer 81

Correct Answer is. droop.

Question 82

Powered flying control actuators.
Option A. are operated by the autopilot only.
Option B. transmit pilot input to the control surfaces.
Option C. provide feedback to the pilot.

Answer 82

Correct Answer is. transmit pilot input to the control surfaces.

Question 83

A stick shaker operates.
Option A. just before the stall.
Option B. after the stall.
Option C. at the onset of the stall.

Answer 83

Correct Answer is. just before the stall.

Question 84

In a power assisted flight control system, the feel required is normally supplied by.
Option A. Q feel.
Option B. air loads on the control surfaces.
Option C. stretching springs.

Answer 84

Correct Answer is. air loads on the control surfaces.

Question 85

“Irreversibility of a fully powered control surface is
provided by.”
Option A. nulling of the servo valve.
Option B. air loads on the control surface.
Option C. the jack ram being attached to structure.

Answer 85

Correct Answer is. nulling of the servo valve.

Question 86

Q feel units use.
Option A. pitot pressure only.
Option B. pitot and static pressures.
Option C. static pressure only.

Answer 86

Correct Answer is. pitot and static pressures.

Question 87

Spoiler panels are positioned so that when deployed.
Option A. pitch trim is not affected.
Option B. no yaw takes place.
Option C. roll will not occur.

Answer 87

Correct Answer is. pitch trim is not affected.

Question 88

Powered flight control systems are used on transport aircraft.
Option A. because at low level air density is high.
Option B. because the pilot has too many tasks to perform.
Option C. due to the increase in speed and size of aircraft.

Answer 88

Correct Answer is. due to the increase in speed and size of aircraft.

Question 89

A differential aileron control system results in.
Option A. aileron drag being reduced on the inner wing in a turn.
Option B. aileron drag being compensated by small rudder movements.
Option C. aileron drag being reduced on the outer wing in a turn.

Answer 89

Correct Answer is. aileron drag being reduced on the outer wing in a turn.

Question 90

Spoiler panels are controlled by.
Option A. the aileron control wheel and speed brake lever.
Option B. a speed brake lever only.
Option C. the aileron control wheel only.

Answer 90

Correct Answer is. the aileron control wheel and speed brake lever.

Question 91

A lift transducer is normally fitted.
Option A. on the elevator control system.
Option B. to the nose area of the aircraft.
Option C. on the leading edge of the wing.

Answer 91

Correct Answer is. on the leading edge of the wing.

Explanation. Lift transducer, also known as a stall sensor.

Question 92

“If electrical power is removed from a fly by wire spoiler
system, the spoiler panels.”
Option A. go to down if any are not already down.
Option B. go to full up.
Option C. remain where they are.

Answer 92

Correct Answer is. go to down if any are not already down.

Question 93

In a fly-by-wire control system, the follow-up transducer is fitted to.
Option A. the control system computer.
Option B. the hydraulic actuator.
Option C. the pilots input.

Answer 93

Correct Answer is. the hydraulic actuator.

Question 94

The down position of the speed brake lever is detented to.
Option A. prevent inadvertent operation.
Option B. lock the speed brakes down during flight.
Option C. allow the ground speed brakes to be used on touchdown.

Answer 94

Correct Answer is. prevent inadvertent operation.

Question 95

Asymmetric flap operation is prevented to keep to a minimum the tendancy of.
Option A. yawing.
Option B. rolling.
Option C. pitch changes.

Answer 95

Correct Answer is. rolling.

Question 96

High thrust stall warning is activated when the thrust of opposite engine reads.
Option A. greater than 75%.
Option B. greater than 50%.
Option C. greater than 90%.

Answer 96

Correct Answer is. greater than 75%.

Question 97

A differential aileron control is one which gives.
Option A. a larger aileron up travel than down.
Option B. the down-going aileron more travel than the up-going one.
Option C. equal aileron travel in each direction, but variable for stick movement.

Answer 97

Correct Answer is. a larger aileron up travel than down.

Question 98

When the control column is moved back and the hand-wheel turned to the left.
Option A. the elevators move down and the left aileron moves down.
Option B. the left aileron moves up and the elevators move up.
Option C. the elevators move up and the left aileron moves down.

Answer 98

Correct Answer is. the left aileron moves up and the elevators move up.

Question 99

A series type yaw damper.
Option A. moves the rudder and the ailerons to damp out Dutch roll.
Option B. moves the rudder pedals and the rudder.
Option C. moves the rudder only.

Answer 99

Correct Answer is. moves the rudder only.

Question 100

A stick shaker.
Option A. is a linear actuator attached to the base of the control column.
Option B. is an eccentric flywheel driven by an electric motor and mounted on the control column.
Option C. vibrates the elevators to cause buffeting of the airframe.

Answer 100

Correct Answer is. is an eccentric flywheel driven by an electric motor and mounted on the control column.

Question 101

If the control column is moved forward and to the left.
Option A. left aileron moves down, right aileron up, elevator down.
Option B. left aileron moves up, right aileron down, elevator down.
Option C. left aileron moves up, right aileron moves down, elevator up.

Answer 101

Correct Answer is. left aileron moves up, right aileron down, elevator down.

Question 102

On an aircraft fitted with spoilers for lateral control, roll to the right is caused by.
Option A. left spoiler extending, right spoiler remaining retracted.
Option B. right spoiler extending, left spoiler remaining retracted.
Option C. both spoilers extending.

Answer 102

Correct Answer is. right spoiler extending, left spoiler remaining retracted.

Question 103

When an aileron trim control in the cockpit is moved to counteract a tendency to fly left wing low, an aileron trim tab fitted to the port aileron will.
Option A. move up and cause the left aileron to move down but the right aileron will remain neutral.
Option B. move up and cause the left aileron to move down and the right aileron to move down to a lesser degree.
Option C. move up and this will cause the left aileron to move down and the right aileron to move up.

Answer 103

Correct Answer is. move up and cause the left aileron to move down and the right aileron to move down to a lesser degree.

Question 104

You have adjusted the elevator trim tab to correct for nose heavy. What was the direction of travel of the trim tab?.
Option A. The port elevator tab has moved up and starboard moved down.
Option B. The elevator trim tab has moved up.
Option C. The elevator trim tab has moved down.

Answer 104

Correct Answer is. The elevator trim tab has moved down.

Question 105

Pulleys in a flight control system are made from.
Option A. brass.
Option B. stainless steel.
Option C. Tufnol or aluminium alloy.

Answer 105

Correct Answer is. Tufnol or aluminium alloy.

Question 106

A tension regulator in the flight control cable system of a large all metal aircraft is used primarily to.
Option A. retain a set tension.
Option B. increase cable tension in cold weather.
Option C. decrease cable tension in cold weather.

Answer 106

Correct Answer is. retain a set tension.

Question 107

An interrupter arm incorporated in a flying control locking mechanism.
Option A. locks the ailerons and elevators.
Option B. restricts movement of the throttles.
Option C. dampens the rudder movement.

Answer 107

Correct Answer is. restricts movement of the throttles.

Question 108

The yaw damper must be designed to allow the rudder to control in response to the aircraft’s.
Option A. pitch Frequency.
Option B. roll frequency.
Option C. dutch roll frequency.

Answer 108

Correct Answer is. dutch roll frequency.

Question 109

The alpha vane signal can be fed to __________ when the aircraft is close to stall.
Option A. flap position.
Option B. fast/slow switch.
Option C. throttle lever.

Answer 109

Correct Answer is. throttle lever.

Question 110

Moving the elevator trim wheel fully aft, then the.
Option A. aircraft tends to go nose down.
Option B. aircraft tends to go nose up.
Option C. aircraft tends to roll to the right.

Answer 110

Correct Answer is. aircraft tends to go nose up

Question 111

Ground spoilers are used to.
Option A. increase wing loading on take-off.
Option B. prevent FOD ingestion into the engines on landing and taxiing.
Option C. decrease wing loading on landing.

Answer 111

Correct Answer is. decrease wing loading on landing.

Question 112

The outboard ailerons on some aircraft.
Option A. are isolated at slow speeds.
Option B. are isolated to prevent aileron reversal.
Option C. are isolated to improve sensitivity.

Answer 112

Correct Answer is. are isolated to prevent aileron reversal.

Question 113

The effect of the rudder on an aircraft can be increased by.
Option A. increasing the distance of the control surfaces from the aircraft’s centre of gravity.
Option B. increasing the altitude of the aircraft.
Option C. decreasing the velocity of the aircraft.

Answer 113

Correct Answer is. increasing the distance of the control surfaces from the aircraft’s centre of gravity.