STRUCTURE – Air – DGCA Question Bank For Politics

#1. An aircraft that has been designed for long haul operations cannot be used for short haul because?

It will have an uneconomical seating arrangement.

Separate JAR certification is required for each type of operation.

The structure is not designed to sustain the different life cycle stresses patterns of short haul operations.

The aircraft will have too much fuel capacity and too little payload capacity.

#2. Fail safe structures?

Are designed to remain safe for a specified number of hours or flight cycles.

Are designed such that if any element of structure fails, the loads will be carried by the adjacent elements of structure.

Do not require regular inspection.

Are designed such that all parts that are likely to fails are inspected regularly.

#3. Trim tabs ?

Reduce manoeuvring forces.

Trim the aircraft in normal flight.

Trim the aircraft in low speed flight.

Reduce or cancel out control hinge moments.

#4. A Q-fell unit would be connected?

In parallel with the rudder control.

In series with the aileron control.

In parallel with the pitch control.

In series with the pitch control.

#5. Duralumin is made of? 1. Aluminium. 2.Copper. 3.Aluminium copper alloy. 4.Is easy to weld. 5.Is difficult to weld. 6. Is susceptible to corrosion. 7.Is highly resistant to corrosion. 8.Has good thermal conductivity. 9.Has poor thermal conductivity.

3, 5, 6, 8.

1, 2, 5, 9.

3, 4, 5, 7.

1, 5, 7, 9.

#6. . Krueger flaps are used? Outboard only.

Outboard only.

Inboard only.

Usually inboard with slats outboard.

Along the inboard trailing edge only.

#7. Trim tabs are fitted in order to?

Reduce control effectiveness at high speed.

Increase control effectiveness at low speed.

Reduce stick holding forces to zero.

Reduce stick forces when manoeuvring.

#8. Flaperons are?

Combined rudder and flaps.

Combined slats and flaps.

Combined ailerons and flaps.

Combined elevators and flaps.

#9. Inboard ailerons?

Are more effective at low speed.

Reduce wing twist at low speed.

Reduce the danger of aileron reversal.

Reduce flutter at all speeds.

#10. Fail safe construction?

Is used in all modern aircraft.

Is used only in highly stressed military or aerobatic aircraft.

Is no longer used in commercial passenger aircraft.

Has never been used in commercial passenger aircraft.

#11. 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.

#12. 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.

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

More prone.

Less prone.

Never prone.

None of the above.

#14. Divergence is caused by?

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

Strong wings, low 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.

#15. 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.

#16. 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.

#17. How is control mass balance achieved?

By fitting weight aft of the hinge.

By fitting weights onto the leading adge.

By fitting weights into the tip cap.

By fitting a horn balance.

#18. What is a flaperon?

A combined elevon and flap.

A combined aileron and flap.

A combined trim tab and flap.

A variable incidence tailplane.

#19. Which of the following minimise adverse yaw?

Yaw damper.

Dorsal fin.

Roll spoilers.

Trim damper.

#20. 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.

#21. 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.

#22. 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.

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

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

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

Ailerons will provide roll control.

Elevons will provide roll control.

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

Balance tabs.

Anti-balance tabs.

Differential ailerons.

Mass balance.

#25. 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 a total hydraulic failure.

#26. 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.

#27. 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.

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

Down.

Up.

Neutral.

Depends on C of G.

#29. 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.

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

The controls are less effective at low speeds.

The servo tabs also provide trim control.

They enable the use of smaller hydraulic actuators.

They enable the use of smaller control surfaces.

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

Pitching.

Rolling.

Yawing.

Phugoid.

#32. Where are Mass balance weights fitted?

Behind the hinge line.

Ahead of the hinge line.

At the tips.

At the trailing edge.

#33. 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.

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

Balance tabs.

Mass balance.

Variable incidence tailplane.

Horn balance.

#35. 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.

#36. Which of the following will happen if trim tabs are used for emergency control in a fully powered control system 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.

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

More powerful control.

Less power required.

No power required.

Better longitudinal stability.

#38. What is the purpose of the mach trim system in a high speed aircraft ?

To damp out phugoid motion in yaw.

To prevent pitch up in shock stall.

To prevent pitch down in shock stall.

To prevent Dutch Roll.

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

Ailerons.

Inboard ailerons and/or lift spoilers.

Inboard ailerons and/or roll spollers.

Spoilers.

#40. What is roll?

Rotation about the normal axis.

Rotation about the lateral axis.

Rotation about the pitch axis.

Rotation about the longitudinal axis.

#41. 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.

#42. 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.

#43. How is control flutter minimised?

Aerodynamic balance.

Control lock out at high speed.

Mass balance.

Power assisted control systems.

#44. How do ailerons and roll 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.

#45. 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.

VMCG would be lower.

Longitudinal stick force would be unchanged.

#46. Methods of providing aerodynamic balance include?

Weights in front of the leading edge.

Q feel units.

Power assisted flying controls

Horn balance.

#47. A yaw damper?

Improves lateral stability.

Prevents spiral instability.

Is useful at low speeds only.

Is not necessary in swept wing aircraft.

#48. Aerodynamic balance is provided to?

Minimise pitching moment changes.

Prevent control flutter.

Prevent reverse control.

Reduce control hinge moments.

#49. 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.

#50. If an elevator is moved to counter a forward C of G 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.

#51. 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.

#52. 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.

#53. 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.

#54. 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.

#55. 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.

#56. 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.

#57. 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.

#58. Servo tabs?

Make controls less effective at low airspeeds.

Are activated by motion of parent control surface.

Permit use of smaller control surfaces.

Are balance tabs.

#59. Servo tabs?

Are always used as trim tabs.

Are never used as trim tabs.

Are sometimes used as trim tabs.

Do not require trimming.

#60. Servo tabs?

Can sometimes be used following hydraulic power failure.

Can never provide control following hydraulic power failure.

Can always provide control following hydraulic power failure.

Can never be used in power - assisted control systems.

#61. 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.

#62. The principle 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.

#63. 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.

#64. 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.

#65. Power assistance produces?

High stick forces at low speeds.

High stick forces at high speeds.

No stick forces.

Constant stick forces.

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

Operate in opposite directions.

Operate in the same direction.

Operate together.

Cannot be operated together.

#67. 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.

#68. Control reversal?

Occurs only in transonic speed range.

Cannot occur in the transonic speed range.

Is most likely at high speeds.

Is most likely at low speeds.

#69. 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.

#70. Stabilators provide?

Longitudinal stability and pitch control.

Longitudinal stability androll control.

Longitudinal stability, pitch control and roll control.

All of the above plus trimming.

#71. The three axes of motion?

Never cross.

Cross at the C of P.

Cross at the C of G.

Cross at the neutral point.

#72. Fly-by-wire control systems?

Are heavier than conventional systems.

Are lighter than conventional systems.

Do not require hydraulic power.

Use servo tabs.

#73. Ruddervators?

Replace rudders and ailerons.

Replace rudders and elevators.

Replace elevators and ailerons.

Are used only for trimming.

#74. 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.

#75. 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?

#76. 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.

#77. Failsafe structure?

.Relies on components not failing.

Relies on components failing gradually.

Relies on other components when components fail.

Relies on detailed inspections to detect faults before catastrophic failure

#78. Krueger flaps?

Are located at the wing tips.

Are located at the wing roots.

Are located at the trailing edge.

Are no longer used in commercial aircraft.

#79. Why are trim tabs not used on all-moving tailplanes?

Because the entire tailplane moves to trim the aircraft.

Trim is provide by elevators.

Because the powered flying controls do not require trim tabs.

Because spring boxes and parallel actutors are used instead.

#80. The main stresses on the upper and lower skins of a wing in flight are?

Compression tension.

Compression Compression

Tension tension.

Tension Compression

#81. Aerodynamic balance is achieved by means of?

Tabs.

Spring boxes and actuators.

Hydraulic servo units.

Leading edge weights.

#82. With under-wing engines the main stresses on the leading edges in the area of engine mountings in flight are?

Tension and torsion.

Compression and tension.

Shear and tension.

Torsion and compression.

#83. Rear fuselage engine configurations?

Improve handling in deep stall.

Enable lighter wings to be used.

Reduce the danger of compressor surge.

Reduce asymmetric power problems.

#84. Composite materials?

Are used for furnishings only.

Are used throughout modern aircraft structures.

Are insensitive to high temperatures.

Are easily maintained and give good warning of impending failure.

#85. Box girder construction?

Is never used in aircraft.

Is used in some aircraft wings, fins and stabilisers.

Is used only in fuselages.

Is too heavy use in aircraft.

#86. Fitting the engines of an aircraft to its rear fuselage instead of on wing pylons?

Permits lighter wing structures to be used.

Permits more wing sweepback to be used.

Requires stronger wing structures.

Improves post-stall handling.

#87. Boron is a material used in?

Duralumin.

Magnesium alloys.

Aluminium alloys.

Composite materials.

#88. A glass windscreen will ....., compared to a Perspex one?

Shorter wear life.

Greater resistance to brittle fracture.

Greater birdstrike resistance.

Greater weight.

#89. The impact resistance of a glass windscreen is?

Greatest when the anti-icing heaters are switched on.

Greatest when the anti-icing heaters are switched off.

Not affected by the anti icing heaters.

Greatest at high altitude.

#90. Large aircraft fuselages are usually made up of?

Magnesium alloys.

Monocoque structures.

Semi-monocoque structures.

Composite structures.

#91. Fireproof bulkheads are usually made of?

Stainless steel.

Mild steel.

Composite materials.

Titanium.

#92. Divergence is most likely to occur?

At high speed with strong swept back wings.

At high speed with light swept back wings.

At high speed with C of P aft of torsional axis.

At high speed with C of P forward of torsional axis.

#93. Wing flutter is?

Vertical flapping motion.

A combination of twisting and flapping.

A combination of twisting flapping and sweeping.

Twisting motion.

#94. Bending loads in modern aircraft wings are carried by?

Spars.

Both the skin and the spars.

Shear webs.

Longerons.

#95. What is wing loading of a 50000 kg aircraft of 90000 square meter wing area when in level flight?

0.56 kg/m2.

1.8 kg/m2.

5.56 kg/m2.

0.18 kg/m2.

#96. Magnesium alloy structures?

Are very light, corrode easily, burn fiercely and cannot be extinguished.

Are very light, resist corrosion well, burn slowly and and can be extinguished with water.

Are very light, corrode easily, burn fiercely and can be extinguished with sand or dry powder.

Are very heavy ; resist corrosion and do not burn.

#97. Composite materials?

Are very light, corrode easily, burn fiercely and cannot be extinguished.

Are very light, resist corrrosion well, produce toxic fumes when burning and can be extinguished with water.

Are very light , corrode easily, burn fiercely and can be extinguished with sand or dry powder.

Are very heavy , resist corrosion and do not burn.

#98. Select the material with the lowest melting temperature?

GRP.

Aluminium.

Titanium.

Steel.

#99. Fuselage fatigue life of a large commercial aircraft is based on?

Landings.

Take-offs.

Flying hours.

Pressurisation cycles.

#100. The windscreens of large commercial airgraft are usually?

Laminated perspex.

Heat treated Perspex.

Laminated glass.

Heat treated glass.

Dgca Question Bank For Pilots

Results

#1. An aircraft that has been designed for long haul operations cannot be used for short haul because?

#2. Fail safe structures?

#3. Trim tabs ?

#4. A Q-fell unit would be connected?

#5. Duralumin is made of? 1. Aluminium. 2.Copper. 3.Aluminium copper alloy. 4.Is easy to weld. 5.Is difficult to weld. 6. Is susceptible to corrosion. 7.Is highly resistant to corrosion. 8.Has good thermal conductivity. 9.Has poor thermal conductivity.

#6. . Krueger flaps are used? Outboard only.

#7. Trim tabs are fitted in order to?

#8. Flaperons are?

#9. Inboard ailerons?

#10. Fail safe construction?

#11. Torsional aileron flutter involves ?

#12. Flexural aileron flutter involves?

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

#14. Divergence is caused by?

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

#16. What is roll?

#17. How is control mass balance achieved?

#18. What is a flaperon?

#19. Which of the following minimise adverse yaw?

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

#21. Aerodynamic balance methods include?

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

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

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

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

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

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

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

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

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

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

#32. Where are Mass balance weights fitted?

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

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

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

#36. Which of the following will happen if trim tabs are used for emergency control in a fully powered control system following hydraulic failure?

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

#38. What is the purpose of the mach trim system in a high speed aircraft ?

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

#40. What is roll?

#41. Control flutter is reduced by?

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

#43. How is control flutter minimised?

#44. How do ailerons and roll spoilers respond if the control wheel is moved to the left.

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

#46. Methods of providing aerodynamic balance include?

#47. A yaw damper?

#48. Aerodynamic balance is provided to?

#49. Spring tabs?

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

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

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

#53. How is aerodynamic balance achieved?

#54. How is aerodynamic balance achieved?

#55. How is aerodynamic balance achieved?

#56. How is aerodynamic balance achieved?

#57. How is aerodynamic balance achieved?

#58. Servo tabs?

#59. Servo tabs?

#60. Servo tabs?

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

#62. The principle advantage of mounting engines on rear fuselage is?

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

#64. Fully powered flying controls?

#65. Power assistance produces?

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

#67. Aileron reversal?

#68. Control reversal?

#69. Control flutter?

#70. Stabilators provide?

#71. The three axes of motion?

#72. Fly-by-wire control systems?

#73. Ruddervators?

#74. A down spring?

#75. A bob weight?

#76. Primary flying controls include?

#77. Failsafe structure?

#78. Krueger flaps?