Which of the following combinations adversely affects take-off and initial climb performance?

a Low temperature and high relative humidity.

b High temperature and low relative humidity.

c Low temperature and low relative humidity.

d High temperature and high relative humidity.

 

59 Besides lift, the forces that determine the gradient of climb of an aeroplane are:

a Weight and thrust only.

b Weight and drag only.

c Thrust and drag only.

d Weight, drag and thrust.

 

60 "The pilot of a single engine aircraft has established the climb performance. The carriage of additional pieces of baggage will cause the climb

performance to be:"

a improved.

b unchanged.

c unchanged, if a short field take-off is adopted.

d degraded.

 

61 The landing distance required will be increased as a result of all of the following:

a decreased temperature, decreased pressure altitude, uphill runway slope.

b increased temperature, increased pressure altitude, uphill runway slope.

c increased temperature, decreased pressure altitude, downhill runway slope.

d increased temperature, increased pressure altitude, downhill runway slope.

 

What is the effect of tailwind on the time to climb to a given altitude?

a The time to climb decreases.

b The time to climb increases.

c The time to climb does not change.

d The effect on time to climb will depend on the aeroplane type.

 

Which of the following combinations basically has an effect on the angle of descent in a glide? (Ignore compressibility effects.)

a Configuration and mass.

b Configuration and angle of attack.

c Altitude and configuration.

d Mass and altitude.

 

Assuming that the required lift exists, which forces determine an aeroplane's angle of climb?

a Weight and drag only.

b Weight and thrust only.

c Weight, drag and thrust.

d Thrust and drag only.

 

65 If there is a tailwind:

a the minimum drag speed is decreased by the same velocity as the wind.

b the minimum drag speed is increased.

c the minimum drag speed is decreased.

d the minimum drag speed is not affected.

 

 

66 "An aeroplane executes a steady glide at the speed for minimum glide angle. If the forward speed is kept constant, what is the effect of a

lower mass? Rate of descent, glide angle C|/Cd ratio."

a increases; increases; decreases

b increases; constant; increases

c increases; increases; constant

d decreases; constant; decreases

 

67 As you accelerate in level flight from the speed at Clmax t0 maximum speed the total drag:

a increases then decreases.

b increases.

c decreases.

d decreases then increases.

 

68 An aeroplane is climbing at a speed 10 kts lower than the speed for best rate of climb:

a angle of climb will decrease.

b rate of climb will not change.

c angle of climb will increase.

d angle of climb will not change.

 

69 Density altitude is the:

a height above the surface.

b pressure altitude corrected for 'non standard' temperature.

c altitude read directly from the altimeter.

d altitude reference to the standard datum plane.

 

70 If the thrust available exceeds the thrust required for level flight:

a the aeroplane decelerates If the altitude is maintained.

b the aeroplane accelerates if the altitude is maintained.

c the aeroplane decelerates if it is in the region of reversed command.

d the aeroplane descends if the airspeed is maintained.

 

71 The best EAS / Drag ratio is approximately:

a 1.3 VMD.

b 1,32 VMD.

c 1.8 VMD.

d 1,6 Vmd-

 

72 What is the effect of increased mass on the performance of a gliding aeroplane?

a The gliding angle decreases.

b The speed for best angle of descent increases.

c There is no effect.

d The lift/drag ratio decreases.

 

73 "Compared with still-air, the effect a headwind has on the values of the maximum range speed and the maximum gradient climb speed

respectively is that:"

a the maximum range speed decreases and the maximum gradient climb speed decreases.

b the maximum range speed increases and the maximum gradient climb speed is not affected.

c the maximum range speed decreases and the maximum gradient climb speed increases.

d the maximum range speed decreases and the maximum gradient climb speed is not affected.

 

74 Assuming other factors remain constant and not limiting, increasing the aerodrome pressure altitude:

a has no effect on the maximum permitted take-of mass up to 5000 ft pressure altitude above which it increases.

b will cause the maximum permitted take-off mass to decrease.

c will cause the maximum permitted take-off mass to increase.

d has no effect on the maximum permitted take-off mass.

 

75 What is the effect of extending flaps on Vx and Vy?

a Vx decreases and Vy increases.

b Vx increases and Vy decreases.

c Vx decreases and Vy decreases.

d Vx increases and Vy increases.

 

76 The load factor in a turn in level flight with constant TAS depends on

a the bank angle only.

b the radius of the turn and the bank angle.

c the true airspeed and the bank angle.

d the radius of the turn and the weight of the aeroplane.

 

77 If cruising into a 15 kts headwind and a 180° turn is made so the wind is directly behind the aircraft, the IAS would:

a be the same and the ground speed would increase by 30 kts.

b decrease by 15 kts and the ground speed would increase by 15 kts.

c be the same and the ground speed would increase by 15 kts.

d increase by 30 kts and the ground speed would remain the same.

 

78 An increase in atmospheric pressure has, among other things, the following consequences on take-off performance:

a an increased take-off distance and improved initial climb performance.

b a reduced take-off distance and improved initial climb performance.

c a reduced take-off distance and degraded initial climb performance.

d an increased take-off distance and degraded initial climb performance.

 

79 An increase in atmospheric pressure has, among other things, the following consequences on landing performance:

a an increased landing distance and degraded go-around performance.

b a reduced landing distance and improved go-around performance.

c a reduced landing distance and degraded go around performance.

d an increased landing distance and improved go-around performance.

 

80 "Refer to figure 032-17.

Consider the graphic representation of the power required versus true air speed (TAS), for a piston engined aeroplane with a given mass.

When drawing the tangent from the origin, the point of contact (A) determines the speed of:"

a maximum specific range.

b maximum thrust.

c critical angle of attack.

d maximum endurance.

 

81 Maximum endurance for a piston engined aeroplane is achieved at:

a the speed for maximum lift coefficient.

b the speed for minimum drag.

c the speed that approximately corresponds to the maximum climb angle speed.

d the speed that approximately corresponds to the maximum rate of climb speed.

82 Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed?

a The higher the gross mass the greater is the speed for descent.

b The higher the average temperature (OAT) the lower is the speed for descent.

c The mass of an aeroplane does not have any effect on the speed for descent.

d The higher the gross mass the lower is the speed for descent.

 

83 In a power-off glide in still air, to obtain the maximum glide range, the aircraft should be flown:

a at a speed corresponding to the maximum lift-to-drag ratio.

b at a speed close to Vne-

c at a speed corresponding to the minimum drag coefficient.

d at a speed close to the stall.

 

84 The region of speed instability is:

a the same as the region of reversed command.

b at speeds below the low-speed buffet.

c the region above the thrust available and drag curve intersection.

d the region in which manual control is not possible.

 

85 If the aircraft mass, in a horizontal unaccelerated flight, decreases:

a the minimum drag increases and the IAS for minimum drag decreases.

b the minimum drag increases and the IAS for minimum drag increases.

c the minimum drag decreases and the IAS for minimum drag increases.

d the minimum drag decreases and the IAS for minimum drag decreases.

 

In which of the flight conditions listed below is the thrust required (Tr) equal to the drag (D)?

a In a descent with constant TAS.

b In level flight with constant IAS.

c In accelerated level flight.

d In a climb with constant IAS.

 

87 To obtain a positive rate of climb:

a power required must be less than the power available.

b power available must be equal to power required.

c thrust must exceed drag by the greatest margin.

d power available must be less than the power required.

 

88 In unaccelerated climb:

a lift equals weight plus the vertical component of the drag.

b thrust equals drag plus the downhill component of the gross weight in the flight path direction.

c thrust equals drag plus the uphill component of the gross weight in the flight path direction.

d lift is greater than the gross weight.