PRINCIPLES OF FLIGHT 080

1. Which wing shape has the greatest induced drag?

Double taper

Elliptical.

Rectangular.

Taper

2. An aeroplane wing stalls when:

It is subjected to unusually high 'G'forces.

The critical angle of attack is exceeded.

The laminar airflow becomes turbulent

The indicated airspeed is too low.

3. Yawing is movement around the ____ axis.

Longitudinal.

Lateral

Horizontal.

Normal.

4. When the aircraft is in a spin, the direction of spin is most reliably found by reference to which of the following indications?

Slip indicator.

Direction indicator.

Turn needle

Artificial horizon.

5. If the indicated air speed of an aircraft is increased from 50 kts to 100 kts, parasite drag will be

Two times greater.

One quarter as much.

Six times greater.

Four times greater.

6. An aircraft rotates about:

Its main undercarriage.

Its centre of gravity.

Its wings

Its rudder.

7. If the control column is moved to the right, a balance tab on the left aileron should:

Move down relative to the aileron.

Move to the neutral position

Not move unless the aileron trim wheel is turned.

Move up relative to the aileron.

8. The symbol for dynamic pressure is:

P

D

Q

R

9. If the velocity of an airstream is doubled the drag coefficient will:

Increase 6-times

Not change

Increase 4-times

Double.

10. If in level flight the airspeed decreases below that for maximum lift/drag, the effect will be that:

Drag increases because of increased parasite drag.

Drag decreases because of lower induced drag.

Drag increases because of increased induced drag.

Drag decreases because of lower parasite drag.

11. If the angle of attack and other factors remain constant, and the airspeed is doubled, lift will be:

One quarter of what it was.

The same

Quadrupled.

Doubled.

12. The definition of lift is:

The aerodynamic force which acts perpendicular to the upper surface of the aerofoil.

The aerodynamic force that results from the pressure differentials about an aerofoil.

The aerodynamic force which acts at 90° to the relative airflow.

The aerodynamic force which acts perpendicular to the chord line of the aerofoil.

13. What is the load factor in a 60° banked level turn? (See LAPL/PPL 080-01)

2.0 G

0.5 G

1 G

1.5 G

14. An aeroplane which is inherently stable will:

Be difficult to stall.

Have a built-in tendency to return to its original state following the removal of any disturbing force.

Require less effort to control.

Not spin.

15. When an aircraft is in a steady climb, the aerodynamic lift is ____ the weight.

Less than

Greater than.

Equal to.

Balanced by.

16. A pilot lowers the flaps while keeping the airspeed constant. In order to maintain level flight, the angle of attack:

Must be kept constant and power required will be constant.

Must be increased.

Must be kept constant but power must be increased.

Must be reduced.

17. The stalling speed of an aircraft in straight and level flight is 60 kt, lAS. What is its stalling speed in a level 60° banked turn?

60 kt.

43 kt.

120 kt.

85 kt.

18. Assuming that the pressure at sea level is ISA, but the temperature is 10 C higher than ISA, the density will be:

Greater than ISA.

Unaffected.

As per ISA.

Less than ISA.

19. An aircraft's rudder is fitted with a balance tab. Movement of the rudder bar to the right, to yaw the aircraft to the right, will move the balance tab to the:

Left and the rudder to the left

Right and the rudder to the right.

Left and the rudder to the right.

Right and the rudder to the left.

20. The angle of climb is proportional to:

The angle of attack of the wing.

The amount by which the thrust exceeds the drag

The amount by which the thrust exceeds the weight.

The amount by which the lift exceeds the weight.

21. If the control column is moved forward and to the left:

The left aileron moves up, right aileron moves down, elevator moves up.

The left aileron moves up, right aileron moves down, elevator moves down.

The left aileron moves down, right aileron moves up, elevator moves down.

The left aileron moves down, right aileron moves up, elevator moves up.

22. The basic stalling speed of an aeroplane is 80 knots. In a level turn with 45° angle bank, the stalling speed is:

95 kt.

113 kt.

86 kt.

33 kt

23. During a manoeuvre, the ailerons are deflected and returned to neutral when the aircraft has attained a small angle of bank. If the aircraft then returns to a wings- level attitude without further control movement, it is:

Statically stable.

Statically stable but dynamically neutral.

Statically and dynamically stable.

Neutrally stable

24. If the cross sectional area of an airflow is mechanically reduced:

The velocity of the airflow remains constant and the mass flow increases.

The mass flow remains constant and the static pressure increases.

The mass flow remains constant and the velocity of the airflow increases.

The velocity of the airflow remains constant and the kinetic energy increases.

25. An aircraft is disturbed from its flight path by a gust of wind. If it tends to return to its original flight path without pilot intervention, the aircraft is said to possess:

Positive Dynamic Stability.

Negative Dynamic Stability.

Instability.

Neutral Dynamic Stability.

26. Which flying control surface(s) give(s) longitudinal control?

The elevator.

The rudder

The flaps.

The ailerons.

27. As indicated air speed (lAS) is reduced, in order to maintain altitude, the pilot must:

Reduce the thrust.

Decrease the angle of attack to reduce the drag.

Deploy the speed brakes to increase drag.

Increase the angle of attack to maintain the correct lift force.

28. Considering the forces acting upon an aeroplane, at constant airspeed, which statement is correct?

The lift force generated by the wings always acts in the opposite direction to the aircraft's weight.

Lift acts perpendicular to the chord line and must always be greater than weight.

Thrust acts parallel to the relative airflow and is greater than drag.

Weight always acts vertically downwards towards the centre of the Earth.

29. The purpose of a trim tab is:

To provide feel to the controls at high speed.

To assist the pilot in initiating movement of the controls.

To increase the effectiveness of the controls.

To zero the load on the pilots controls in the flight attitude required.

30. At the stall, the Centre of Pressure moving backwards will cause the nose to ____, and the decreased lift will cause the aircraft to ____.

Yaw / reduce speed

Drop / reduce speed.

Drop / lose height

Rise / sink.

31. Dynamic pressure may be expressed by the formula:

Q = pV

Q = 1/2pV².

Q = 2pV.

Q = 1/3pV².

32. As airspeed increases, induced drag:

Is dependant on the weight of the aircraft.

Increases.

Remains unchanged.

Decreases.

33. A high wing configuration with no dihedral, compared to a low wing configuration with no dihedral, will provide:

Less lateral stability

Greater longitudinal stability.

Greater lateral stability.

The same degree of longitudinal stability as any other configuration because dihedral gives longitudinal stability.

34. At a given indicated air speed, what effect will an increase in air density have on lift and drag?

Lift and drag will decrease.

Lift and drag will increase.

Lift and drag will remain the same.

Lift will increase but drag will decrease.

35. The boundary layer consists of:

Laminar flow

Turbulent flow at low speeds only.

Laminar and turbulent flow area.

Turbulent flow.

36. After a disturbance in pitch, an aircraft oscillates in pitch with increasing amplitude. It is:

Statically stable but dynamically unstable.

Statically unstable but dynamically stable

Statically and dynamically unstable.

Statically and dynamically stable.

37. When displacing the ailerons from the neutral position:

The down-going aileron causes an increase in induced drag.

The up-going aileron causes an increase in induced drag.

Both cause an increase in induced drag.

Induced drag remains the same; the up-going aileron causes a smaller increase in profile drag than the down-going aileron.

38. What is the approximate percentage increase of a minimum speed if an aircraft mass is increased for 20%?

0%

10%

20%

120%

39. The maximum speed at which the aircraft can be flown with flaps extended is called:

VNE

VNO

VYSE

VFE

40. When an aircraft is disturbed from its established flight path by, for example, turbulence, it is said to have positive stability if it subsequently:

Continues to pitch in the disturbed direction until the displacement is resisted by opposing control forces.

Remains on the new flight path.

Re-establishes its original flight path without any input from the pilot.

Becomes further displaced from its original flight path.

41. The lateral axis of an aircraft is a line which:

Passes through the centre of pressure, at right angles to the direction of the airflow.

Passes through the quarter-chord point of the wing root at right angles to the longitudinal axis.

Passes through the wing tips.

Passes through the centre of gravity, parallel to a line through the wing tips.

42. The tendency of an aircraft to develop forces which restore it to its original flight situation, when disturbed from a condition of steady flight, is known as:

Controllability.

Manoeuvrability.

Instability.

Stability.

43. Wing leading-edge devices such as slots, designed to allow flight at higher angles of attack, do so by:

Changing the shape and hence the lift characteristics of the wing.

Providing an extra lifting surface and hence increase the lift available.

Re-energising the airflow over the top of the wing, delaying separation.

Decreasing lift and hence induced drag.

44. In sub-sonic airflow, as air passes through a venturi, the mass flow ____ , the velocity ____ and the static pressure ____ .

Remains constant / increases then decreases / increases then decreases.

Remains constant / increases then decreases / decreases then increases.

Decreases then increases / remains constant / increases then decreases.

Decreases then increases / increases then decreases / increases then decreases.

45. The stalling speed of an aircraft, assuming weight to be constant, is a function of the:

Square root of the Load Factor

Square of the weight.

Indicated airspeed.

Inverse of the Load Factor.

46. If the velocity of an air mass is increased:

The static pressure will remain constant and the kinetic energy will increase.

The kinetic energy will increase, the dynamic pressure will increase and the static pressure will decrease.

The mass flow will stay constant, the dynamic pressure will decrease and the static pressure will increase.

The dynamic pressure will decrease and the static pressure will increase.

47. Which of the four answer options most correctly completes the sentence? Increasing speed also increases lift because:

The increased velocity of the relative wind overcomes the increased drag.

Lift is directly proportional to velocity.

The increased speed of the air passing over an aerofoil's upper surface decreases the static pressure above the wing, thus creating a greater pressure differential across the upper and lower surface.

Increasing speed decreases drag.

48. Which flying control surface(s) give(s) control about the aircraft's normal axis?

The ailerons.

The flaps.

The elevator

The rudder

49. At a constant angle of attack, a decrease in the airspeed of an aircraft will result in:

Possible increases or decreases in lift or drag, depending on the actual speed.

A decrease in lift and drag.

An increase in lift and a decrease in drag.

An increase in drag and a decrease in lift.

50. What is the significance of the speed known as VNO?

It is the maximum speed at which abrupt movements of the controls will result in a stall, before the aircraft's positive load limit is exceeded.

It signifies the airspeed which must never be exceeded

It is the speed beyond which structural failure of the airframe will occur.

It signifies the upper limit of the normal operating speed range

51. A control surface may be mass balanced by:

Attaching a weight acting forward of the hinge line.

Fitting an anti-balance tab.

Attaching weight acting aft of the hinge line

Fitting a balance tab

52. If a landing is to be made without flaps the landing speed must be:

Reduced.

The same as for a landing with flaps

The same as for a landing with flaps but with a steeper approach.

Increased

53. An aircraft is disturbed from its path by a gust of wind. Neutral stability is when, without pilot intervention, it:

Maintains the new path.

Returns to its original path after overshooting.

Returns to its original path without overshooting.

Continues to move away from the original path.

54. Loading an aircraft so that the C of G exceeds the aft limits could result in:

High stick forces.

Excessive upward force on the tail, and the nose pitching down.

Excessive load factor in turns.

Loss of longitudinal stability and the nose pitching up at slow speeds.

55. The critical angle of attack on the wing polar diagram is marked as: (See LAPL/PPL 080-02)

5

6

1

4

56. Air pressure:

Acts only vertically downwards.

Is measured in Pascals per square inch.

Increases with altitude.

Acts in all directions.

57. That portion of the aircraft's total drag created by the production of lift is called:

Parasite drag, which is inversely proportional to the square of the airspeed.

Parasite drag, which is greatly affected by changes in airspeed.

Induced drag, which is greatly affected by changes in coefficient of lift and airspeed.

Induced drag, which is not affected by changes in airspeed.

58. VNE is

The maximum speed, above which flaps should not be extended.

The maximum airspeed at which the aircraft may be flown.

The maximum airspeed at which manoeuvres approaching the stall may be carried out.

The airspeed which must not be exceeded except in a dive

59. The unit of force is the:

Newton.

Joule.

Mass-kilogram.

Newton-metre.

60. An aircraft has a tendency to fly right wing low with hands off. It is trimmed with a tab the left aileron. The trim tab will:

Move down causing the left aileron to move up and right aileron to move down.

Move down, causing the left aileron to move up, right aileron remains neutral

Move up causing the left wing to move down, ailerons remain neutral.

Move up, causing the left aileron to move up and right aileron to move down.

61. Differential Ailerons' are a design feature that helps to counteract:

Stability about the longitudinal axis.

Adverse roll.

Positive aircraft stability.

Adverse yaw.

62. The angle of attack at which an aeroplane stalls:

Will remain constant, regardless of gross weight.

Will be smaller flying downwind than when flying upwind.

Is a function of speed and density altitude.

Is dependent upon the speed of the airflow over the wing.

63. Density:

Reduces with temperature reduction.

Is unaffected by temperature change.

Increases with altitude increase.

Reduces with altitude increase.

64. The presence of water vapour:

In the atmosphere will increase the amount of lift generated by an aircraft.

In air will reduce its density.

In air will increase its density

In the atmosphere will increase the power output of a piston engine.

65. The air pressure that acts on anything immersed in it:

Is also known as Dynamic Pressure.

Is also known as Static Pressure.

Is greater at altitude than at sea level.

Is also known as Total Pressure

66. Lowering the flaps during a landing approach:

Permits approaches at a higher indicated airspeed

Decreases the angle of descent without increasing power.

Eliminates floating.

Increases the angle of descent without increasing the airspeed.

67. A wing which is inclined downwards from root to tip is said to have:

Anhedral

Taper.

Sweep.

Washout.

68. As airspeed increases induced drag ____, parasite drag ____ and total drag ____.

Decreases / Decreases / Decreases.

Increases / Decreases / Increases then decreases.

Increases / Increases / Increases.

Decreases / Increases / Decreases then increases.

69. When an aircraft is disturbed from its trimmed attitude by, for example, turbulence, it is said to have neutral stability if it subsequently:

Immediately re-establishes its original attitude.

Remains in the new attitude.

Oscillates about its original attitude before settling back to that original attitude.

Continues to move in the disturbed direction until the displacement is resisted by opposing control forces.

70. If the angle of attack is increased above the stalling angle:

Lift and drag will both decrease.

Lift will increase and drag will decrease.

Lift and drag will both increase.

Lift will decrease and drag will increase.

71. Which of the answer options most correctly completes the sentence? The amount of lift a wing produces is directly proportional to:

The air density

The square root of the velocity of the air flowing over it

The dynamic pressure minus the static pressure.

The air temperature

72. The maximum value of the coefficient of lift is found at an angle of attack of approximately:

4 to 6 degrees.

16 degrees

Minus 4 degrees.

0 degrees.

73. When considering the changes in density of the air with altitude, which of the following four options is correct?

The increase in pressure with increasing altitude causes density to reduce.

The temperature increase with increasing altitude causes density to increase.

The temperature reduction with increasing altitude causes density to increase.

The reduction in pressure with increasing altitude causes density to reduce.

74. Following re-trimming for straight and level flight, in an aircraft with a C of G near its forward limit, and an elevator fitted with a conventional trim-tab:

Longitudinal stability will be reduced

Nose-down pitch authority will be reduced

Tailplane down-load will be reduced

Nose-up pitch authority will be reduced.

75. A moving mass of air possesses kinetic energy. An object placed in the path of such a moving mass of air will be subject to:

Dynamic pressure minus static pressure.

Static pressure and dynamic pressure.

Dynamic pressure.

Static Pressure.

76. Longitudinal stability is given:

The wing dihedral

The horizontal tailplane

The ailerons

The fin.

77. By design, the centre of pressure on a particular aircraft remains behind the aircraft's C of G. If the aircraft is longitudinally stable and is displaced in pitch, nose down, by turbulence:

The aircraft will maintain its nose-down attitude.

The tailplane will generate an upward force.

The tailplane will generate a downward force.

Neither an upward nor a downward force will be generated by the tailplane, as the aircraft will already be in equilibrium.

78. Which of the following four options describes the consequence of taking off with the manufacturer's recommended take-off flap setting selected?

An increase in the length of the take-off run compared to a non-flap take-off.

A greater angle of climb.

Easier avoidance of obstacles at the end of a runway.

A decrease in the length of the take-off run compared to a non-flap take-off.

79. With the flaps lowered, the stalling speed will:

Remain the same.

Increase, but occur at a higher angle of attack.

Decrease.

Increase.

80. In straight and level flight, the free stream airflow pressure, compared to that flowing under the wing, is:

Equal.

Lower.

Equal pressure but travelling faster.

Higher.

81. The air flow over the wing's upper surface in straight and level flight, when compared with the airflow that is unaffected by the wing, will have:

A higher density.

A reduced velocity.

A higher velocity.

The same velocity.

82. An aileron could be balanced aerodynamically by:

Attaching a weight to the control surface forward of the hinge.

Having the control hinge set back behind the control surface leading edge

Having springs in the control circuit to assist movement.

Making the up aileron move through a larger angle than the down aileron.

83. Full flaps should be selected when:

Landing into a strong headwind.

On go-around.

Commencing final approach.

Committed to land.

84. Dynamic pressure is:

The total pressure at a point where a moving airflow is brought completely to rest.

The pressure due to the mass of air pressing down on the air beneath.

The amount of the total pressure by which the static pressure rises at a point where a moving airflow is brought completely to rest.

The pressure change caused by heating when a moving airflow is brought completely to rest.

85. A positively cambered aerofoil starts to produce lift at an angle of attack of approximately:

16 degrees.

Minus 4 degrees.

4 to 6 degrees.

0 degrees.

86. Approximately for what percent will the stall speed increase if wing loading increases by 15%?

7%

0%

15%

20%

87. On an aerofoil section, the force of lift acts perpendicular to, and the force of drag acts parallel to, the:

Chord line

Flightpath.

Longitudinal axis.

Aerofoil section upper surface

88. An aircraft wing is constructed with positive dihedral in order to give:

Lateral stability about the normal axis

Directional stability about the normal axis.

Longitudinal stability about the lateral axis.

Lateral stability about the longitudinal axis.

89. What is the maximum allowed bank angle when flying an aircraft with limiting load factor of +2,5 G? (See LAPL/PPL 080-01)

66°

55°

60°

50°

90. With a forward centre of gravity, an aircraft will have:

Reduced longitudinal stability

Decreased elevator effectiveness when flaring.

Lighter forces for control movements.

Shorter take off distances.

91. If the Angle of Attack is increased beyond the Critical Angle of Attack, the wing will stall:

Unless the airspeed is greater than the normal stall speed.

In which case, the control column should be pulled-back immediately.

Regardless of airspeed or pitch attitude.

Unless the pitch attitude is on or below the natural horizon.

92. The maximum value of the coefficient of lift is found:

At the stalling angle of attack.

At negative angles of attack.

When lift equals drag.

During steep turns.

93. A typical stalling angle of attack for an aircraft wing is:

4°

16°

45°

30°

94. The airspeed at which a pilot will not yet overstress the airframe of an aircraft by momentarily up-deflecting the elevator is:

VB

VS

VA

VFE

95. Fixed trim tabs on ailerons:

Can be adjusted on the ground after a test flight to make wings-level flight easier.

Should never be adjusted.

Can be adjusted on the ground after a test flight to make turning easier.

Can be adjusted during flight.

96. Ailerons give:

Directional control about the normal axis

Lateral control about the lateral axis.

Lateral control about the longitudinal axis

Longitudinal control about the lateral axis.

97. The purpose of a spring-bias trim system is

To compensate for temperature changes in cable tension.

To maintain a constant tension in the trim tab system.

To reduce to zero the effort required by the pilot to counter stick force, after making a control movement.

To increase the feel in the control system.

98. Stability around the normal axis:

Is given by the lateral dihedral.

Depends on the longitudinal dihedral.

Is increased if the keel surface behind the C of G is increased.

Is greater if the wing has no sweepback.

99. On an aircraft with a simple trim tab incorporated into a control surface, when the surface is moved, the tab remains in the same position relative to the:

Aircraft horizontal plane.

Relative airflow.

Boundary layer airflow.

Control surface.

100. An imaginary straight line running from the midpoint of the leading edge of an aerofoil to its trailing edge, is called the:

Mean camber.

Chord

Aerofoil thickness

Maximum camber.

101. The dynamic pressure exerted on an aircraft's frontal surface is equal to:

Half the density times the indicated airspeed squared.

Half the density times the true airspeed squared.

Half the true airspeed times the density squared.

Density time's speed squared.

102. When the control column is pushed forward, a balance tab on the elevator:

Will move up relative to the control surface.

Will move down relative to the control surface.

Will only move if the trim wheel is operated.

Moves to the neutral position.

103. If an aircraft is flown at its design manoeuvring speed VA:

It is only possible to subject the aircraft to a load greater than its limit load during violent increases in incidence, i.e. when using excessive stick force to pull-out of a dive.

It is possible to subject the aircraft to a load greater than its limit load during high 'g' manoeuvres.

It must be immediately slowed down if turbulence is encountered.

It is not possible to exceed the positive limit load with movements.

104. If the aircraft weight is increased, without change of C of G position, the stalling angle attack will:

Remain the same. The position of the C of G does not affect the stall speed.

Remain the same.

Increase.

Decrease.

105. The angle of attack is the angle between the:

Camber line and free stream flow.

Chord line and the relative airflow.

Chord line and the longitudinal axis of the aeroplane

Chord line and the horizontal plane.

106. The reason for washout being designed into an aircraft wing is to:

Decrease the effectiveness of the ailerons.

Cause the inboard section of the wing to stall first.

Cause the outboard section of the wing to stall first.

Increase the effectiveness of the flaps.

107. In a climb at a steady speed, the thrust is:

Equal to the aerodynamic drag.

Less than the aerodynamic drag.

Equal to the weight component along the flight path.

Greater than the aerodynamic drag.

108. Controls are mass balanced in order to:

Provide equal control forces on all three controls

Aerodynamically assist the pilot in moving the controls.

Return the control surface to neutral when the controls are released.

Eliminate control flutter

109. The maximum gliding distance from 6.000 feet, for an aircraft in clean configuration, with a lift/drag ratio of 8:1, is approximately 8 nautical miles. If flaps are deployed:

The maximum gliding distance will increase.

The maximum gliding distance will be unaffected.

Lift/Drag ratio will be unaffected but will be achieved at a lower airspeed.

The maximum gliding distance will be less.

110. What must be the relationship between the forces acting on an aircraft in flight, for that aircraft to be in a state of equilibrium?

Lift must equal drag, and thrust must equal weight.

Lift must equal thrust plus drag.

Lift must equal thrust, and weight must equal drag.

Lift must equal weight, and thrust must equal drag.

111. The part that gives most of the directional stability for an aircraft is:

The horizontal tailplane.

The vertical fin.

The rudder trim tab

The rudder

112. If an airplane weights 3.000 pounds, what approximate weight would the airplane structure be required to support during a 20° banked turn while maintaining altitude? (See LAPL/PPL 080-01)

3.180 lbs.

4.000 lbs.

3.000 lbs.

3.350 lbs.

113. The smooth flow of air, where each molecule follows the path of the preceding molecule, is a definition of:

Wind

Turbulent flow

Laminar flow

Free stream flow

114. The primary and secondary effects of applying the left rudder alone are

Right yaw and right roll

Right yaw and left roll.

Left yaw and left roll.

Left yaw and right roll

115. The angle of attack for a minimum drag on the wing polar diagram is marked as: (See LAPL/PPL 080-02)

7

3

4

5

116. The maximum allowable airspeed with flaps extended (VFE) is lower than cruising speed because:

Flaps are used only when preparing to land.

Flaps will stall if they are deployed at too high an airspeed.

Too much drag is induced.

At speeds higher than VFE the aerodynamic forces would overload the flap and wing structures.

117. The phenomenon of flutter is described as:

Oscillatory motion of part or parts of the aircraft relative to the remainder of the structure.

Rapid oscillatory motion involving only rotation of the control surfaces, associated with the shock waves produced around the control surfaces.

Reversal of the ailerons caused by wing torsional flexibility.

Rapid movement of the airframe caused by vibration from the engines.

118. In straight and level powered flight the following principal forces act on an aircraft:

Thrust, lift, drag.

Thrust, lift, weight.

Lift, drag, weight

Thrust, lift, drag, weight.

119. When considering air: 1. Air has mass. 2. Air is not compressible. 3. Air is able to flow or change its shape when subject to even small pressures. 4. The viscosity of air is very high. 5. Moving air has kinetic energy.

1 and 4.

1, 3 and 5.

2, 3 and 4.

1, 2, 3 and 5.

120. Relative airflow is ____ and ____ the movement of the aircraft.

Perpendicular to / Opposite to.

Parallel to / in the same direction as.

Parallel to / Opposite to

Perpendicular to / in the same direction as.

121. If an airplane weights 4.600 pounds, what approximate weight would the airplane structure be required to support during a 50° banked turn while maintaining altitude? (See LAPL/PPL 080-01)

9.200 lbs.

5.400 lbs

7.160 lbs

8.180 lbs

122. If the centre of gravity (C of G) of an aircraft is found to be within limits for take-off:

The C of G limits for landing must be checked, allowing for planned fuel consumption.

The C of G will always be within limits for landing.

The C of G will not change during the flight.

The flight crew will always be certain of being able to adjust the C of G during flight in order to keep it within acceptable limits for landing.

123. Dynamic pressure equals:

Total pressure divided by static pressure.

Static pressure minus total pressure.

Total pressure minus static pressure

Total pressure plus static pressure.

124. What is the maximum allowed bank angle when flying an aircraft with limiting load factor of +3,8 G? (See LAPL/PPL 080-01)

70°

67°

53°

75°

125. An aft centre of gravity will give:

Increased elevator effectiveness when flaring.

Heavy forces for control movements.

Increased longitudinal stability

Longer take-off distances.

126. When flaps are lowered the stalling angle of attack of the wing

Decreases, but CLMAX increases.

Increases and CLMAX increases

Remains the same, but CLMAX increases.

Decreases, but CLMAX remains the same.

127. When the C of G is close to the forward limit:

Very small forces are required on the control column to produce pitch.

Stick forces are the same as for an aft C of G.

Very high stick forces are required to pitch because the aircraft is very stable.

Longitudinal stability is reduced.

128. The purpose of an anti-balance tab is to:

Trim the aircraft.

Reduce the load required to move the controls at all speeds

Ensure that the pilot's physical control load increases with increase of control surface deflection.

Reduce the load required to move the controls at high speeds only.

129. The maximum angle of climb of an aeroplane is determined by:

Wind speed.

Excess airspeed.

Excess engine thrust.

The aircraft weight.

130. A control surface may have a mass balance fitted to it, in order to:

Lighten the forces needed to control the surface.

Help prevent a rapid and uncontrolled oscillation which is called "flutter".

Keep the control surface level.

Provide the pilot with "feel".

First submitted	September 1, 2022
Times taken	357
Average score	21.5%
Report this quiz	Report