EASA & DGCA AME EXAM PAPER:51 TO 100 THEORY OF FLIGHT QUE

ALL THE BEST

51. Vortex generators on the wing are most effective at

a) high speed    b) low speed    # c) high angles of attack

52. The chord line of a wing is a line that runs from

# a) the centre of the leading edge of the wing to the trailing edge

b) half way between the upper and lower surface of the wing

c) one wing tip to the other wing tip

53. The angle of incidence of a wing is an angle formed by lines

# a) parallel to the chord line and longitudinal axis

b) parallel to the chord line and the lateral axis

c) parallel to the chord line and the vertical axis

54. The centre of pressure of an aerofoil is located

# a) 30 - 40% of the chord line back from the leading edge

b) 30 - 40% of the chord line forward of the leading edge

c) 50% of the chord line back from the leading edge

55. Compressibility effect is

a) drag associated with the form of an aircraft

b) drag associated with the friction of the air over the surface of the aircraft

# c) the increase in total drag of an airfoil in transonic flight due to the formation of shock waves

56. Lateral control of an aircraft at high angle of attack can be maximised by using

a) fences    # b) vortex generators     c) wing slots

57. Stall strips are always

a) made of metal   # b) on the leading edge of a wing   c) fitted forward of the ailerons

58. Stall strips

# a) cause the wing root to stall    b) cause the wing tip to stall

c) cause the wings to stall symmetrically

59. Due to the interference of the airflow on a high wing aircraft between the fuselage and the wings, the lateral stability of the aircraft in a gusty wind situation will cause

a) the upper wing to increase its lift      # b) the upper wing to decrease its lift

c) the lower wing to decrease its lift

60. Slats

# a) reduce the stall speed

b) reduce the tendency of the aircraft to Yaw

c) decrease the aerofoil drag at high speeds

61. What is the temperature lapse rate for aircraft flying below 36,000 feet altitude?

a) 1°C per 1000 feet    b) 3°C per 1000 feet    # c) 2°C per 1000 feet

62. For a pressure of 25lbs/in² at sea level, what is the absolute pressure?

# a) 39.7 lbs/in²   b) 49.7 lbs/in²    c) 10.3 lbs/in

63. An aircraft banks into a turn. No change is made to the airspeed or angle of attack. What will happen?

# a) The aircraft enters a side slip and begins to lose altitude

b) The aircraft turns with no loss of height

c) The aircraft yaws and slows down

64. The relationship between induced drag and airspeed is

a) directly proportional to the square of the speed

# b) inversely proportional to the square of the speed

c) directly proportional to speed

65. What is the definition of Angle of Incidence?

a) The angle the underside of the mainplane or tailplane makes with the horizontal

b) The angle the underside of the mainplane or tailplane makes with the longitudinal datum line

# c) The angle the chord of the mainplane or tailplane makes with the horizontal

66. What is Boundary Layer?

a) Separated layer of air forming a boundary at the leading edge

b) Turbulent air moving from the leading edge to trailing edge

# c) Sluggish low energy air that sticks to the wing surface and gradually gets faster until it joins the free stream flow of air

67. The normal axis of an aircraft passes through

# a) the centre of gravity    b) a point at the center of the wings    c) at the centre of pressure

68. On a high winged aircraft, what effect will the fuselage have on the up-going wing?

# a) The up-going wing will have a decrease in angle of attack and therefore a decrease in lift

b) The down-going will have a decrease in angle of attack and therefore a decrease in lift

c) The up-going wing will have an increase in angle of attack and therefore a decrease in lift

69. What is the collective term for the fin and rudder and other surfaces aft of the centre of gravity that helps directional stability?

# a) Effective keel surface     b) Empennage     c) Fuselage surfaces

70. Temperature above 36,000 feet will

a) decrease exponentially    # b) remain constant    c) increase exponentially

71. A decrease in incidence toward the wing tip may be provided to

a) prevent adverse yaw in a turn

b) prevent spanwise flow in maneuvers    # c) retain lateral control effectiveness at high angles of attack

72. The angle of attack which gives the best L/D ratio

a) decreases with a decrease in density

# b) in unaffected by density changes

c) increases with a decrease in density

73. For a given aerofoil production lift, where

P = pressure and V = velocity:

a) P1 is greater than P2, and V1 is greater than V2

b) P1 is less than P2 and V1 is greater than V2

# c) P1 is greater than P2, and V1 is less than V2

74. Low wing loading

a) increases stalling speed, landing speed and landing run

b) increases lift, stalling speed and maneuverability

# c) decreases stalling speed, landing speed and landing run

75. Due to the change in downwash on an untapered wing (i.e. one of constant chord length) it will

a) not provide any damping effect when rolling

# b) tend to stall first at the root

c) not suffer adverse yaw effects when turning

76. True stalling speed of an aircraft increases with altitude

a) because reduced temperature causes compressibility effect

# b) because air density is reduced

c) because humidity is increased and this increases drag

77. As a general rule, if the aerodynamic angle of incidence (angle of attack) of an aerofoil is slightly increased, the centre of pressure will

a) never move     # b) move forward towards the leading edge    c) move towards the tip

78. The "wing setting angle" is commonly known as

# a) angle of incidence    b) angle of attack    c) angle of dihedral

79. On a very humid day, an aircraft taking off would require

a) a shorter take off run    # b) a longer take off run   c) humidity does not affect the takeoff run

80. An aircraft is flying at 350 MPH, into a head wind of 75 MPH, what will its ground speed be?

a) 175 mph    # b) 275 mph    c) 200 mph

81. When does the angle of incidence change?

a) When the aircraft attitude changes

b) When the aircraft is ascending or descending

# c) It never changes

82. As the angle of attack decreases, what happens to the centre of pressure?

a) It moves forward     # b) It moves rearwards

c) Centre of pressure is not affected by angle of attack decrease

83. A decrease in pressure over the upper surface of a wing or aerofoil is responsible for

# a) approximately 2/3 (two thirds) of the lift obtained

b) approximately 1/3 (one third) of the lift obtained

c) approximately 1/2 (one half) of the lift obtained

84. Which of the four forces act on an aircraft?

# a) Lift, gravity, thrust and drag

b) Weight, gravity, thrust and drag

c) Lift, weight, gravity and drag

85. Which of the following types of drag increases as the aircraft gains altitude?

a) Parasite drag     # b) Induced drag    c) Interference drag

86. Correcting for a disturbance which has caused a rolling motion about the longitudinal axis would re-establish which of the following?

# a) Lateral stability    b) Directional stability    c) Longitudinal stability

87. The layer of air over the surface of an aerofoil which is slower moving, in relation to the rest of the airflow, is known as

a) camber layer    # b) boundary layer    c) none of the above

88. What is a controlling factor of turbulence and skin friction?

a) Aspect ratio   b) Fineness ratio   # c) Counter sunk rivets used on skin exterior

89. Changes in aircraft weight

a) will not affect total drag since it is dependant only upon speed

# b) cause corresponding changes in total drag due to the associated lift change

c) will only affect total drag if the lift is kept constant

90. The aircraft stalling speed will

# a) increase with an increase in weight

b) be unaffected by aircraft weight changes since it is dependant upon the angle of attack

c) only change if the MTMA were changed

91. In a bank and turn

a) extra lift is not required    b) extra lift is not required if thrust is increased    # c) extra lift is required

92. To maintain straight and level flight on the aeroplane shown, with a decrease in tail-plane download the mainplane lift would have to

a) remain constant   # b) decrease     c) increase

93. To achieve the maximum distance in a glide, the recommended air speed is

a) as close to the stall as practical    b) as high as possible with VNE   # c) the speed where the L/D ratio is maximum

94. If the C of G is aft of the Centre of Pressure

# a) changes in lift produce a pitching moment which acts to increase the change in lift

b) when the aircraft sideslips, the C of G causes the nose to turn into the sideslip thus applying a restoring moment

c) when the aircraft yaws the aerodynamic forces acting forward of the Centre of Pressure

95. Porpoising is an oscillatory motion in the

# a) pitch plane    b) roll plane   c) yaw plane

96. Directional stability is maintained

a) by the mainplanes, and controlled by the ailerons

b) by the tailplane, and controlled by the elevators

# c) by the keel surface and fin, and controlled by the rudder

97. Due to the interference effects of the fuselage, when a high wing aeroplane sideslips

a) the accompanying rolling due to keel surface area is destabilizing

# b) the accompanying lift changes on the wings produces a stabilizing effect

c) the accompanying rolling due to the fin is destabilizing

98. The power required in a horizontal turn

# a) is greater than that for level flight at the same airspeed

b) must be the same as that for level flight at the same airspeed

c) is less than that for level flight at the same airspeed

99. A wing mounted stall sensing device is located

# a) usually on the under surface    b) always at the wing tip    c) always on the top surface

100. For an aircraft in a glide

a) thrust, drag, lift and weight act on the aircraft

# b) weight, lift and drag act on the aircraft

c) weight and drag only act on the aircraft