FLYING CONTROLS – Air – DGCA Question Bank For Politics

#1. What control inputs are required to maintain airspeed a d altitude when turning in a jet aircraft?

Increase thrust and angle of attack.

Increase turn radius and decrease thrust.

Increase pitching angle.

Increase bank angle.

#2. Torsional aileron flutter involves?

c of G aft of hinge line and cyclic twisting of wings.

C of G aft of C of P and cyclic twisting of wings.

C of P fwd of torsional axis and cyclic twisting of wings.

None of the above.

#3. Flexural aileron flutter involves?

C of G aft of the hinge line and cyclic bending of wings.

C of G aft of C of P and cyclic twisting of wings.

C of p fwd of torsional axis and cyclic twisting of wings.

None of the above.

#4. Swept back wings are ........ to divergence?

More prone.

Less prone.

Never prone.

None of the above.

#5. Divergence is caused by?

Weak wings, high speeds and C of P forward of torsional axis.

Strong wings, lorn speeds, and C of G aft of torsional axis.

Weak wings, high speed and C of G aft of torsional axis.

Swept wings, high speed and C of G aft of C of P.

#6. Why might trim tabs be employed in power assisted flying controls?

To enable control to be maintained following hydraulic failure.

To reduce control forces to zero.

To prevent overstressing of hydraulic actuators.

To provide mach trim.

#7. What is VMcL? 1. The minimum speed at which control can be maintained following a critical engine failure in the air, in the landing configuration. 2. Limited by the maximum roll rate of the aircraft.

Neither 1 nor 2 are correct.

Both 1 and 2 are correct.

1 only is correct.

2 only is correct.

#8. What is roll?

Rotation of the aircraft about its longitudinal axis.

Rotation of the aircraft about its lateral axis.

Rotation of the aircraft about its normal axis.

Caused by adverse yaw.

#9. How is control mass balance achieved?

By fitting weight aft of the hinge.

By fitting weights onto the leading edge.

By fitting weights into the tip cap.

By fitting a horn balance.

#10. What is a flaperon?

A combined elevon and flap.

A combined aileron and flap.

A combined trim tab and flap.

A variable incidence tailplane.

#11. Which of the following minimise adverse yaw?

Yaw damper.

Dorsal fin.

Roll spoilers.

Trim damper.

#12. Which of the following reduces the effects of asymmetric when rolling?

Dorsal fin.

Vortilons.

Trim damper.

Aileron-rudder coupling.

#13. What action taken in the cockpit will cause a pitch trim tab to move up in a fully powered flying control system?

The trim switch must be moved in the nose up direction.

The trim switch must be moved in the nose down direction.

The trim wheel must be turned to the right.

Trim occurs automatically so no action is required.

#14. What action should be taken if the turn and slip indicator shows needle to the left and ball to the left?

Reduce right bank.

Increase Right bank.

Increase speed.

Decrease speed.

#15. Aerodynamic balance methods include?

Split flaps and split rudders.

Weights added to the leading edge of the control surfaces.

Inset hinge and horn balance.

Rudder-aileron coupling.

#16. What will roll spoilers do when an aircraft enters a high speed turn?

Move down on the up going wing.

Move up on the down going wing.

Move up on the up going wing.

Move down on the down going wing.

#17. What will happen when an aircraft employing combined roll spoilers and speed . brakes is in ;dive with speed brakes deployed, enters a left turn?

Right roll spoiler will go up or left roll spoiler will retract.

Left roll spoiler will go up or right roll spoiler will retract.

Ailerons will provide roll control.

Elevons will provide roll control.

#18. Adverse yaw in a turn may be corrected by?

Balance tabs.

Anti-balance tabs.

Differential ailerons.

Mass balance.

#19. Which of the following parameters affects control in the transonic speed range?

TAS.

RAS.

Mach number.

IAS.

#20. Which of the following is true of power assisted flying controls?

None of the aerodynamic loads are felt by the pilot.

Some proportion of the aerodynamic loads are felt by the pilot.

The full aerodynamic loads are felt by the pilot.

Control is lost in the event of hydraulic failure.

#21. At what angle must a variable incidence tailplane be set to trim the aircraft?

It depends on the speed, thrust and C of G position of the aircraft.

Slightly nose up if trailing edge flaps are deployed.

Slightly nose down if leading edge flaps are deployed.

Zero incidence, the trim tabs provide trim.

#22. At what angle relative to the variable incidence stabilizer will the elevator be when the aircraft is in trim in straight and level flight?

Up if C of G is forward.

Down if C of G is forward.

Neutral.

Depends on speed.

#23. What elevator movement will be required to trim for a thrust increase in a low wing aircraft with engines mounted below the wings?

Down.

Up.

Neutral.

Depends on C of G.

#24. What advantage is provided by a variable incidence tailplane in comparison to a conventional tailplane with elevator and trim tab?

It is lighter, stronger and of more simple construction.

It makes the aircraft more stable about the lateral axis.

It provides more effective trimming whilst maintaining pitch control authority.

It requires less power to operate.

#25. Which of the following statements is true of servo tabs?

The servo tabs also provide trim control.

The controls are less effective at low speeds.

They enable the use of smaller hydraulic actuators.

They enable the use of smaller control surfaces.

#26. What is motion about the longitudinal axis called?

Pitching

Rolling

Yawing

Phugoid

#27. Where are Mass balance weights fitted?

Behind the hinge line.

Ahead of the hinge line.

At the tips.

At the trailing edge.

#28. What benefit is provided by fitting the engines at the rear of the fuselage?

The wings can be lighter and thinner.

Engine failure results in less control problems.

The wings are less liable to flutter.

Better response to deep stall.

#29. Which of the following methods can be used in the event of hydraulic failure in a power assisted flying control system?

Balance tabs.

Mass balance.

Variable incidence tailplane.

Horn balance.

#30. Which of the following methods can be used in the event of hydraulic failure in a power assisted flying control system?

Anti-balance tabs.

Aerodynamic balance.

Trim tabs.

Mass balance.

#31. Which of the following will happen if trim tabs are used for emergency control following hydraulic failure?

The tab will act as a balance tab.

The tab will act as an anti-balance tab.

The controls will be reversed.

Control effectiveness will be unaffected.

#32. What is the advantage of a stabilator compared to a conventional system?

More powerful control.

Less power required.

No power required.

Better longitudinal stability.

#33. What is the immediate effect of pushing the left rudder pedal forward?

Right yaw about the longitudinal axis and roll to the right.

Left yaw about the normal axis and roll to the right.

Left yaw about the normal axis and roll to the left.

None of the above.

#34. How is roll control achieved in high speed aircraft when cruising?

Ailerons.

Inboard ailerons and/or lift spoilers.

Inboard ailerons and/or roll spoilers.

Spoilers.

#35. What benefit is provided by fitting the tailplane at the top of the fin?

Improved longitudinal stability.

Improved directional stability.

Improved roll stability.

Improved response in deep stall.

#36. What is roll?

Rotation about the normal axis.

Rotation about the lateral axis.

Rotation about the pitch axis.

Rotation about the longitudinal axis.

#37. What is the standard spin recovery technique?

Minimum power, use ailerons to arrest roll, stick forward, rudder to oppose yaw.

Maximum power, centralise ailerons, opposite rudder to oppose yaw, stick forward.

Minimum or maximum power depending on propulsion system type, ailerons neutral, opposite rudder to oppose roll, stick forward.

Minimum or maximum power depending on propulsion system type, ailerons neutral, opposite rudder to oppose yaw, stick forward.

#38. Control flutter is reduced by?

Mass balance aft of the hinge line.

Aerodynamic balance forward of the hinge line.

Mass balance forward of the hinge line.

Power assisted flying controls.

#39. What is the purpose of a down spring in a control system?

To increase hinge moments.

To increase stick force gradient

To decrease stick force gradient.

To prevent control flutter.

#40. How is control flutter minimised?

Aerodynamic balance.

Control lock out at high speed.

Mass balance.

Power assisted control systems.

#41. How do ailerons and rr 1 spoilers respond if the control wheel is moved to the left.

Left aileron down, left spoiler does not move, right aileron and spoiler up.

Right aileron and spoiler down, left aileron and spoiler up.

Left aileron and spoiler down, right aileron and spoiler up.

Left aileron and spoiler up, right aileron down, right spoiler remains retracted.

#42. What would be the effect if the C of G were at the forward limit for take-off?

Longitudinal stick force would be higher.

Longitudinal stick force would be lower.

VMcc would be lower.

Longitudinal stick force would be unchanged.

#43. Methods of providing aerodynamic balance include?

Weights in front of the leading edge.

Q feel units.

Power assisted flying controls.

Horn balance.

#44. VMCA.. .......w ith altitude and VMCG .......... with altitude?

Increases, Increases.

Increases, Is not relevant.

Decreases, Decreases.

#45. VMCG is limited by?

Critical engine failure on take off.

Yaw control authority.

Engine power.

Slippery runways.

#46. A yaw damper?

Improves lateral stability.

Prevents spiral instability.

Is useful at low speeds only.

Is not necessary in swept wing aircraft.

#47. VMCLis minimum control speed in the .......... Configuration and is determined by.. ... ..?

Landing, Pitch authority.

Landing, Yaw and roll authority.

Take-off, Pitch authority.

Take-off, Yaw and roll authority.

#48. Aerodynamic balance is provided to?

Minimise pitching moment changes.

Prevent control flutter.

Prevent reverse control.

Reduce control hinge moments.

#49. Adverse yaw is caused by?

Angle of attack changes.

Speed changes.

Spinning

Ailerons

#50. Spring tabs?

Reduce hinge moments at low speeds.

Reduce hinge moments at high speeds.

Reduce hinge moments at all speeds.

Stiffen the controls to prevent flutter.

#51. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

Elevons. '

Ventral fin.

Yaw damper.

Frise ailerons.

#52. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

Dorsal fin.

Elevons.

Yaw damper.

Roll spoilers.

#53. If an elevator is moved to counter a forward C of @ position, in what direction will the trim tabs move in relation to the elevator?

Up.

Down.

Up or down depending on type.

They will not move relative to the elevator.

#54. If a trim tab is used to reduce elevator hinge moments to zero, what will be the response of the elevators?

Move up.

Move down.

Not move.

Up or down depending on airspeed

#55. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

Dorsal fin.

Differential ailerons.

Yaw damper.

Flaperons.

#56. What device ensures correct response to control inputs when an aircraft enters or pulls out of a turn?

Vortex generators.

Vortilons.

Dorsal fin.

Rudder-aileron coupling.

#57. If the total moments about an axis are not zero, what will be the result?

Constant angular acceleration about the axis.

Equilibrium about the axis.

Stability about the axis.

Continuous rate rotation about the axis.

#58. How is aerodynamic balance achieved?

Fitting weights at the leading edge of the control surface.

Balance tabs.

Placing the hinge aft of the C of P of the control.

Rudder-aileron coupling.

#59. How is aerodynamic balance achieved?

Fitting weights at the leading edge of the control surface.

Horn balance.

Hinge line aft of C of G.

Aileron-rudder coupling.

#60. What will be the immediate effect of pushing the right rudder pedal forward?

Right yaw and left roll.

Left yaw and right roll.

Right yaw and right roll.

Left yaw and left roll.

#61. How is aerodynamic balance achieved?

Hinge line aft of C of P.

Balance tabs.

Rudder-elevator coupling.

Fitting weights at the leading edge of the control surface.

#62. How is aerodynamic balance achieved?

Fitting weights at the leading edge of the control.

Placing hinge line closer to, but in front of C of P of control surface.

Placing hinge line aft of C of G of control surface.

Hydraulic power systems.

#63. Which of the following statements best describes the purpose of the T-tail configuration?

Reduce interference between wing downwash and tailplane?

Prevent deep stall.

Enable engines to be located at sides of fuselage.

Increase fin effectiveness.

#64. How is aerodynamic balance achieved?

Fitting weights at the leading edge of the control surface.

Internal balance using pressure differences above and below the wing.

Hinge line aft of C of P.

Pneumatic or electrical power assistance.

#65. Servo tabs?

Make controls less effective at low airspeeds.

Are balance tabs.

Are activated by motion of parent control surface.

Permit use of smaller control surfaces.

#66. If after suffering a right engine failure, the pilot of a twin engine aircraft maintains altitude whilst keeping the wings level and the aircraft on track as indicated below, what will the turn and slip indicator will show?

Right turn, ball to the left.

Left turn, ball to the right.

No turn, ball central.

No turn, ball right.

#67. When establishing V Min ~a pr~otot ype aircraft the nose wheel is considered inoperative in order to?

Prevent weather-cocking in strong cross-wind take-offs.

Allow for slippery runways.

Allow for take-off abandonment after nose wheel lift-off.

Allow for aft C of G take-offs.

#68. Servo tabs?

Are always used as trim tabs.

Are never used as trim tabs.

Are sometimes used as trim tabs.

Do not require trimming.

#69. Servo tabs?

Cannot be used following hydraulic power failure.

Can always provide control following hydraulic power failure.

Can never be used in power-assisted control systems.

#70. If an elevator becomes jammed its servo-tab will?

Act as an anti-balance tab, increasing control hinge moment.

Jam.

Provide limited control but acting in the opposite sense to the elevator.

Cause all longitudinal control to be lost.

#71. The greatest control authority is required when dealing with?

Single engine failure in a single propeller aircraft.

Single engine failure in a four engine jet aircraft.

Single engine failure in a four engine propeller aircraft.

Single engine failure in a twin propeller aircraft.

#72. The principal advantage of mounting engines on rear fuselage is?

Reduced wing flutter.

Reduce wing strength required.

Engines less affected by turbulence in a stall.

Yaw and pitch moments are less affected by thrust changes.

#73. When cruising at high mach numbers high speed jet aircraft usually employ ................ for roll control?

Outboard ailerons and lift spoilers.

Inboard ailerons and lift spoilers.

Inboard ailerons and roll spoilers.

Outboard or inboard ailerons.

#74. When handling critical engine failure in a heavily loaded twin engine aircraft?

Use rudder to arrest yaw and to get back on heading, then use aileron to eliminates side-slip.

Use aileron to counter both yaw and side-slip.

Use rudder to counter both yaw and side-slip.

Use rudder to arrest and to turn beyond the original heading so that the aircraft side-slips along the desired track. Use ailerons to keep wings level.

#75. VMCG may be limited by? 1. Maximum roll rate available. 2. Engine failure during take-off roll.

1 and 2 are correct.

1 only is correct.

2 only is correct.

Neither 1 nor 2 are correct.

#76. Pushing the control column to the right produces ....... in an aircraft exhibiting adverse yaw?

Right roll and right yaw.

Left roll and left yaw.

Right roll and left yaw.

Left roll and right yaw.

#77. Fully powered flying controls?

Are not required in large aircraft.

Generate high stick forces at high speeds.

Generate high stick forces at low speeds.

Generate low stick forces.

#78. Power assistance produces?

High stick forces at low speeds.

High stick forces at high speeds.

No stick forces.

Constant stick forces.

#79. The rudder trim wheel and the rudder bar?

Operate in opposite directions.

Operate in the same direction.

Operate together.

Cannot be operated together.

#80. To trim for a left engine failure turning the trim wheel . . . . . . . . . moves the rim tab ...... and the rudder .......?

Left, Left, Left.

Left, Right, Left.

Right, Left, Right.

Right, Right, Left.

#81. When making a large change in airspeed .............. then ............?

Trim, Adjust speed.

Adjust power, , Trim.

Adjust speed, Trim.

Trim, Adjust attitude.

#82. The principal method of speed control is?

Power

Propeller RPM.

Attitude

Thrust

#83. The principal method of altitude control is?

Power

Propeller RPM.

Attitude

Thrust

#84. Positive pitching is?

Nose up.

Nose down.

Nose horizontal.

Nose up or down depending on load factor.

#85. Positive rolling is?

Right wing down.

Right wing up.

Left wing down.

Wings level.

#86. Positive yaw is?

Occurs only in the transonic speed range.

Cannot occur in the transonic speed range.

Is most likely at high speeds.

Is most likely at low speeds.

#87. Control flutter?

Is prevented by powered flying controls.

Is prevented by power assisted flying controls.

Is minimised by anti-balance tabs.

Is minimised by mass balancing.

#88. Ailerons produce?

Roll only.

Roll and yaw.

Roll, yaw and pitch.

Yaw only.

#89. Stabilators provide?

Longitudinal stability and pitch control.

Longitudinal stability arld roll control.

Longitudinal stability, pitch control and roll control.

All of the above plus trimming.

#90. The three axes of motion?

Never cross.

Cross at the C of P.

Cross at the C of G.

Cross at the neutral point.

#91. Fly-by-wire control systems?

Are heavier than conventional systems.

Are lighter than conventional systems.

Do not require hydraulic power.

Use servo tabs.

#92. Ruddervators?

Replace rudders and ailerons.

Replace rudders and elevators.

Replace elevators and ailerons.

Are used only for trimming.

#93. Servo tabs . . . . . ... in a fully powered flying control system?

Cannot be used.

Act as trim tabs.

Provide emergency control following hydraulic failure.

Act as balance tabs.

#94. For JAR certification the stick force gradient?

Is not permitted.

Must be positive.

Must be negative.

Must be constant.

#95. A down spring?

Decreases stick force gradient.

Increases stick force gradient.

Increases stick forces in a pull up manoeuvre.

Is not used in JAR certificated aircraft.

#96. A bob weight?

Decreases stick force gradient.

Increases stick forces at high speeds only.

Increases stick forces in a pull up manoeuvre.

Is not used in JAR certificated aircraft.

#97. Primary flying controls include?

Ailerons, elevons and roll spoilers.

Ailerons, air brakes and lift spoilers.

Elevons, rudder and stabilisers.

Rudder, roll spoilers and nose wheel steering.

#98. Aileron reversal?

Is not possible with fully powered flying controls.

Is most likely with power assisted controls.

Is most likely with fully powered controls.

Is most likely with manual controls.

#99. Control reversal?

Occurs only in the transonic speed range.

Cannot occur in the transonic speed range.

Is most likely at high speeds.

Is most likely at low speeds.

Dgca Question Bank For Pilots

Results

#1. What control inputs are required to maintain airspeed a d altitude when turning in a jet aircraft?

#2. Torsional aileron flutter involves?

#3. Flexural aileron flutter involves?

#4. Swept back wings are ........ to divergence?

#5. Divergence is caused by?

#6. Why might trim tabs be employed in power assisted flying controls?

#7. What is VMcL? 1. The minimum speed at which control can be maintained following a critical engine failure in the air, in the landing configuration. 2. Limited by the maximum roll rate of the aircraft.

#8. What is roll?

#9. How is control mass balance achieved?

#10. What is a flaperon?

#11. Which of the following minimise adverse yaw?

#12. Which of the following reduces the effects of asymmetric when rolling?

#13. What action taken in the cockpit will cause a pitch trim tab to move up in a fully powered flying control system?

#14. What action should be taken if the turn and slip indicator shows needle to the left and ball to the left?

#15. Aerodynamic balance methods include?

#16. What will roll spoilers do when an aircraft enters a high speed turn?

#17. What will happen when an aircraft employing combined roll spoilers and speed . brakes is in ;dive with speed brakes deployed, enters a left turn?

#18. Adverse yaw in a turn may be corrected by?

#19. Which of the following parameters affects control in the transonic speed range?

#20. Which of the following is true of power assisted flying controls?

#21. At what angle must a variable incidence tailplane be set to trim the aircraft?

#22. At what angle relative to the variable incidence stabilizer will the elevator be when the aircraft is in trim in straight and level flight?

#23. What elevator movement will be required to trim for a thrust increase in a low wing aircraft with engines mounted below the wings?

#24. What advantage is provided by a variable incidence tailplane in comparison to a conventional tailplane with elevator and trim tab?

#25. Which of the following statements is true of servo tabs?

#26. What is motion about the longitudinal axis called?

#27. Where are Mass balance weights fitted?

#28. What benefit is provided by fitting the engines at the rear of the fuselage?

#29. Which of the following methods can be used in the event of hydraulic failure in a power assisted flying control system?

#30. Which of the following methods can be used in the event of hydraulic failure in a power assisted flying control system?

#31. Which of the following will happen if trim tabs are used for emergency control following hydraulic failure?

#32. What is the advantage of a stabilator compared to a conventional system?

#33. What is the immediate effect of pushing the left rudder pedal forward?

#34. How is roll control achieved in high speed aircraft when cruising?

#35. What benefit is provided by fitting the tailplane at the top of the fin?

#36. What is roll?

#37. What is the standard spin recovery technique?

#38. Control flutter is reduced by?

#39. What is the purpose of a down spring in a control system?

#40. How is control flutter minimised?

#41. How do ailerons and rr 1 spoilers respond if the control wheel is moved to the left.

#42. What would be the effect if the C of G were at the forward limit for take-off?

#43. Methods of providing aerodynamic balance include?

#44. VMCA.. .......w ith altitude and VMCG .......... with altitude?

#45. VMCG is limited by?

#46. A yaw damper?

#47. VMCLis minimum control speed in the .......... Configuration and is determined by.. ... ..?

#48. Aerodynamic balance is provided to?

#49. Adverse yaw is caused by?

#50. Spring tabs?

#51. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

#52. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

#53. If an elevator is moved to counter a forward C of @ position, in what direction will the trim tabs move in relation to the elevator?

#54. If a trim tab is used to reduce elevator hinge moments to zero, what will be the response of the elevators?

#55. What components ensure correct response to control inputs when an aircraft enters or pulls out of a turn?

#56. What device ensures correct response to control inputs when an aircraft enters or pulls out of a turn?

#57. If the total moments about an axis are not zero, what will be the result?

#58. How is aerodynamic balance achieved?

#59. How is aerodynamic balance achieved?

#60. What will be the immediate effect of pushing the right rudder pedal forward?

#61. How is aerodynamic balance achieved?

#62. How is aerodynamic balance achieved?

#63. Which of the following statements best describes the purpose of the T-tail configuration?

#64. How is aerodynamic balance achieved?

#65. Servo tabs?

#66. If after suffering a right engine failure, the pilot of a twin engine aircraft maintains altitude whilst keeping the wings level and the aircraft on track as indicated below, what will the turn and slip indicator will show?

#67. When establishing V Min ~a pr~otot ype aircraft the nose wheel is considered inoperative in order to?

#68. Servo tabs?

#69. Servo tabs?

#70. If an elevator becomes jammed its servo-tab will?

#71. The greatest control authority is required when dealing with?

#72. The principal advantage of mounting engines on rear fuselage is?

#73. When cruising at high mach numbers high speed jet aircraft usually employ ................ for roll control?

#74. When handling critical engine failure in a heavily loaded twin engine aircraft?

#75. VMCG may be limited by? 1. Maximum roll rate available. 2. Engine failure during take-off roll.

#76. Pushing the control column to the right produces ....... in an aircraft exhibiting adverse yaw?

#77. Fully powered flying controls?

#78. Power assistance produces?