Can the length of a stopway be added to the runway length to determine the take-off distance available?

Can the length of a stopway be added to the runway length to determine the take-off distance available?

a Yes, but the stopway must have the same width as the runway.

b No, unless its centreline is on the extended centreline of the runway.

c No.

d Yes, but the stopway must be able to carry the weight of the aeroplane.

 

What will be the effect on an aeroplane performance if aerodrome pressure altitude is decreased?

a It will decrease the take-off distance required.

b It will increase the take-off ground run.

c It will increase the accelerate stop distance.

d It will increase the take-off distance required.

 

4 During a climb with all piston engines operating, the altitude where the rate of climb reduces to 100 ft/min is called:

a service ceiling.

b maximum transfer ceiling.

c thrust ceiling.

d absolute ceiling.

 

5 "Refer to figure 032-24.

Considering a rate of climb diagram (ROC versus TAS) for an aeroplane. Which of the diagrams shows the correct curves for FLAPS DOWN

compared to CLEAN configuration?"

a Diagram (D)

b Diagram (A)

c Diagram (B)

d Diagram (C)

 

6 Ignoring the effect of compressibility, the effect a change of altitude has on the value of the coefficient of lift is that it:

a is independent of altitude.

b decreases with increasing altitude.

c increases with increasing altitude.

d decreases with increasing altitude, but only at low speeds.

 

7 On a reciprocating engine aeroplane, to maintain a given angle of attack, configuration and altitude at higher gross mass:

a a higher coefficient of drag is required.

b requires an increase in power and decrease in the airspeed.

c an increase in airspeed and power is required.

d an increase in airspeed is required but power setting does not change.

 

 

How do the best angle of climb and best rate of climb vary with increasing altitude for an aeroplane with a normal aspirated piston engine?

a Both decrease.

b Best angle of climb increases while best rate of climb decreases.

c Both increase.

d Best angle of climb decreases while best rate of climb increases.

9 Uphill slope:

a decreases the accelerate stop distance only.

b decreases the take-off distance only.

c increases the allowed take-off mass.

d increases the take-off distance more than the accelerate stop distance.

10 "You are the commander of a light twin piston aircraft. The aircraft performance has been calculated, but before departure another passenger

is taken on board. What will be the effect of the extra passenger on board?"

a The performance will be degraded, the performance calculations should be performed again.

b The performance will be degraded but the performance calculations need not be performed again as the safety factors are so large.

c No effect.

d The performance will be improved.

11 "Refer to figure 032-21.

The distances X, Y, Z and W are defined as:"

a ADSA, TODA, TORA, LDA.

b TODA, TORA, ASDA, LDA.

c LDA, ASDA, TORA, TODA.

d LDA, TORA, ASDA, TODA.

12 "Propeller aircraft (piston engine) flown at medium altitude at the recommended EAS will have a better specific air range (SAR) than at sea

level because:"

a engine efficiency is greater.

b the thrust required is less.

c drag is the same.

d the power required to maintain level flight is less.

 

13 In straight and level flight the lift is opposed by the:

a drag.

b thrust.

c drag and weight.

d weight.

14 Regarding the best angle and the best rate of descent speeds, which of the following statements is true:

a weight has no effect on the rate of descent only on the descent slope angle.

b a heavier aircraft must descend at a slower airspeed in order to maintain the same slope as a similar lighter aircraft.

c weight has no effect on the descent slope angle or descent rate.

d a heavier aircraft must descend at a faster airspeed in order to maintain the same slope as a similar lighter aircraft.

15 The intersections of the thrust available and the drag curve are the operating points of the aeroplane:

a in unaccelerated climb.

b in descent with constant IAS.

c in accelerated level flight.

d in unaccelerated level flight.

16 During a descent a headwind will:

a increase the rate of descent.

b increase the descent distance overground.

c increase the angle of descent.

d increase the angle of the descent flight path.

17 The absolute ceiling:

a is the altitude at which the best climb gradient attainable is 5%.

b is the altitude at which the maximum rate of climb is zero.

c is the altitude at which the aeroplane reaches a maximum rate of climb of 100 ft/min.

d can be reached only with minimum steady flight speed.

 

18 In a power-off glide, an increase in aircraft mass will:

a not affect the glide angle, but increase the speed for minimum glide angle.

b increase the glide angle, but not affect the speed for minimum glide angle.

c increase the glide angle and increase the speed for minimum glide angle.

d not affect the glide angle, and not affect the speed for minimum glide angle.

 

19 How does an increase in aircraft mass affect the gliding range?

a Has no effect on gliding range.

b Decreases gliding range.

c Increases gliding range.

d None of the above.

 

20 The angle of climb with flaps extended, compared to that with flaps retracted, will normally be:

a increase at moderate flap setting, decrease at large flap setting.

b larger.

c smaller.

d not changed.

 

21 A headwind component increasing with altitude, as compared to zero wind condition (assuming IAS is constant):

a has no effect on rate of climb.

b does not have any effect on the angle of flight path during climb.

c improves angle and rate of climb.

d decreases angle and rate of climb.

22 When flying an aircraft on the back of the drag curve, maintaining a slower speed (but still faster than Vs) would require:

a more flap.

b no change.

c more thrust.

d less thrust due to less parasite drag.

 

What happens if density altitude is 3000 ft at an airport whose elevation is 1000 ft?

a Take-off and landing performance will be unaffected.

b The altimeter will indicate 3000 ft when the aircraft is on the ground.

c Indicated speed at 50 kts on take-off and landing will be higher than in a standard atmosphere.

d Take-off and landing performance will be about the same as for an airport with an elevation of 3000 ft.

 

24For a piston engined aeroplane, the speed for maximum range is:

a that which gives the minimum lift to drag ratio.

b 1,4 times the stall speed in clean configuration.

c that which gives the maximum value of lift.

d that which gives the minimum value of drag.

 

25 A clearway:

a provides an area over which an aeroplane can safely transit from lift off to the required height.

b need not have the same weight bearing qualities as the runway with which it is associated.

c may be water.

d all of the above.

 

26 "Assume glide with zero thrust and zero wind:

Is there any difference between the vertical speed versus forward speed curves for two identical aeroplanes having different masses?"

a No difference.

b Yes, the difference is that the lighter aeroplane will always glide a greater distance.

c Yes, the difference is that the heavier aeroplane will always glide a greater distance.

d Yes, the difference is that for a given angle of attack both the vertical and forward speeds of the heavier aeroplane will be larger.

 

Which 3 speeds are effectively the same for a jet aircraft?

a Range, Best angle of climb, minimum Drag.

b Best angle of climb, minimum Drag, Endurance.

c ROC, Range, minimum Drag.

d Best angle of climb. Range, Endurance.

 

28 Aeroplane is in a glide (power off descent) at the speed for the L/D max. If the pitch angle is increased the glide distance will:

a decrease.

b depend on the aircraft.

c increase.

d remain constant.

 

 

29Pressure altitude is:

a the altimeter indication when QFE is set on the sub-scale.

b the altimeter indication when 1013.25 hPa is set on the sub-scale.

c the altimeter indication when QNH is set on the sub-scale.

d the altitude above sea level.

 

 

30 "EASA AIR OPS states that propeller driven aircraft with a maximum approved passenger seating configuration of or less and a maximum

Take-off Mass of or less must comply with the requirements of Performance Class B."

a 18:5700 kg

b 9; 12500 kg

c 9; 5700 kg

d 18; 12500 kg

 

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.

 

The rate of climb

a is the horizontal component of the true airspeed.

b is approximately climb gradient times true airspeed divided by 100.

c is the downhill component of the true airspeed.

d is angle of climb times true airspeed.

 

155 The tangent from the origin to the thrust required against true airspeed curve, for a jet aeroplane, determines the speed for:

a maximum range.

b minimum power.

c maximum endurance.

d maximum speed.

 

156 The service ceiling of an aircraft is:

a the altitude above which cruising speed cannot be maintained.

b the altitude where a low specific rate of climb is achieved.

c the highest altitude permitted for flight because of manoeuvre capability.

d the altitude where rate of climb is zero.

 

157 The effect of a decrease in air density is to:

a increase the take-off distance and increase the rate of climb.

b increase the take-off distance and reduce the rate of climb.

c decrease the take-off distance and reduce the rate of climb.

d decrease the take-off distance and increase the rate of climb.

 

158 For a piston engine aircraft the service ceiling corresponds to:

a the altitude at which the aircraft is capable of a climb rate of 500 feet per minute.

b the greatest altitude at which more than one speed is available.

c the altitude for which the power required and power available curves are tangential.

d the altitude at which the aircraft is capable of a climb rate of 100 feet per minute.

 

159 A higher outside air temperature:

a reduces the angle and the rate of climb.

b increases the angle of climb but decreases the rate of climb.

c does not have any noticeable effect on climb performance.

d reduces the angle of climb but increases the rate of climb.

 

160 In climb limited mass calculations, the climb gradient is a ratio of:

a height gained over distance traveled through the air.

b TGS over rate of climb.

c height gained over distance traveled across the ground.

d TAS over rate of climb.

 

161 At a higher gross mass on a piston-engined aeroplane, in order to maintain a given angle of attack, configuration and altitude:

a the airspeed must be decreased and the drag will increase.

b the lift/drag ratio must be increased.

c the airspeed must be increased and the drag will remain unchanged.

d the airspeed must be increased and the drag will also increase.

 

162 On a reciprocating engined aeroplane, with increasing altitude at constant gross mass, angle of attack and configuration the power required:

a increases but TAS remains constant.

b increases and the TAS increases by the same percentage.

c decreases slightly because of the lower air density.

d remains unchanged but the TAS increases.

 

Can the length of a stopway be added to the runway length to determine the take-off distance available?

a Yes, but the stopway must have the same width as the runway.

b No, unless its centreline is on the extended centreline of the runway.

c No.

d Yes, but the stopway must be able to carry the weight of the aeroplane.