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What will happen to Vx and Vy if the landing gear is extended? ⇐ ПредыдущаяСтр 4 из 4
a Vx and Vy decrease. b Vx and Vy increase. c Vx increases, Vy decreases. d Vx decreases and Vy increases.
104 Which of the following factors leads to the maximum flight time of a glide? a Headwind. b Low mass. c Tailwind. d High mass.
105 The stopway is an area which allows an increase only in the: a take-off distance available. b accelerate-stop distance available. c landing distance available. d take-off run available.
106 In straight horizontal steady flight, at speeds below that for minimum drag: a a higher speed, but still below that for minimum drag, requires a higher thrust. b a lower speed requires a higher thrust. c the aeroplane can be controlled only in level flight. d the aeroplane cannot be controlled manually. 107 The margin between the power available and the power required: a decreases when the aircraft descends. b decreases when the aircraft climbs. c increases when the aircraft climbs. d remains the same.
108 A change in aeroplane weight affects: a glide angle. b glide speed. c glide angle and glide speed. d neither glide angle nor glide speed.
109 In a steady climb at a constant speed: a the power required must be greater than the power available. b the power available must exceed the power required. c the power available must be less than the power required. d the power available must equal the power required.
110 What gives one the greatest gliding time? a A headwind. b A tailwind. c Higher mass. d Lower mass.
111 The induced drag of an aeroplane at constant mass in un-accelerated level flight is greatest at: a Vsi (stalling speed in clean configuration). b Vmo (maximum operating limit speed). c Vso (lowest achievable speed in a given configuration). d Va (design manoeuvring speed).
112 The "climb gradient" is defined as the ratio of: a true airspeed to rate of climb. b the increase of altitude to horizontal air distance expressed as a percentage. c the increase of altitude to distance over ground expressed as a percentage. d rate of climb to true airspeed.
113 "In a steady descending flight (descent angle GAMMA) equilibrium of forces acting on the aeroplane is given by: T = Thrust D = Drag W = Weight" a T + Wsin GAMMA = D b T - D = W Sin GAMMA c T + D = -Wsin GAMMA d T-Wsin GAMMA = D
114 "Which one of the following statements is true concerning the effect of changes of ambient temperature on an aeroplane's performance, assuming all other performance parameters remain constant?" a A decrease will cause an increase of the climb gradient. b An increase will cause a decrease in the landing distance required. c A decrease will cause an increase in the take-off ground run. d An increase will cause a decrease in take-off distance required. 115 The maximum operating altitude for a certain aeroplane with a pressurised cabin: a is only certified for four-engine aeroplanes. b is the highest pressure altitude certified for normal operation. c is dependent on the OAT. d is dependent on aerodynamic ceiling.
116 The landing distance required will be decreased as a result of: a higher aircraft mass, higher air density, uphill runway slope. b higher aircraft mass, higher air density, downhill runway slope. c low aircraft mass, lower air density, uphill runway slope. d low aircraft mass, high air density, uphill runway slope.
117 A higher temperature causes in air density and in lift. a increase; increase b decrease; increase c decrease; decrease d increase; decrease
118 In a glide the maximum range will be obtained by flying at: a VnE- b a speed close to the stalling speed. c Vmo/Mmo- d Vmd-
119 The force exactly opposing and balancing lift in a glide descent a thrust x cos(angle of descent) b thrust * sin(angle of descent)
c weight x sin(angle of descent) d weight x cos(angle of descent) 120 Which of the following statements is correct? a Induced drag decreases with increasing speed. b Induced drag increases with increasing speed. c Induced drag decreases with increasing angle of attack. d Induced drag is independent of the speed.
121 To achieve the maximum range over ground with headwind the airspeed should be: a reduced to the gust penetration speed. b equal to the speed for maximum range cruise with no wind. c higher compared to the speed for maximum range cruise with no wind. d lower compared to the speed for maximum range cruise with no wind.
122 The take-off distance available is: a the total runway length, without clearway even if this one exists. b the runway length minus stopway. c the runway length plus half of the clearway. d the length of the take-off run available plus the length of the clearway available.
123 When does THRUST = DRAG? a Climbing at a constant IAS. b Descending at a constant IAS. c Flying level at a constant IAS. d All of the above.
124 If the aerodrome pressure altitude increases it will: a decrease the take-off distance. b increase the take-off distance available. c decrease the take-off run. d increase the take-off distance. 125 As speed is reduced from Vmd to vmp: a power required increases, drag increases. b power required increases, drag decreases. c power required decreases, drag decreases. d power required decreases, drag increases.
126 Any acceleration in climb, with a constant power setting: a improves the climb gradient if the airspeed is below Vx- b decreases rate of climb and increases angle of climb. c improves the rate of climb if the airspeed is below Vy. d decreases the rate of climb and the angle of climb.
127 "Refer to figure 032-23. Assuming constant L/D ratio, which of the diagrams provided correctly shows the movement of the THRUST REQUIRED CURVE? Mass M1 higher than mass М2." a Diagram (D) b Diagram (A) c Diagram (B) d Diagram (C)
128 Profile drag is: a directly proportional to the square of the speed. b directly proportional to the square root of the speed. c inversely proportional to the square of the speed. d inversely proportional to the square root of the speed.
129 Higher gross mass at the same altitude decreases the gradient and the rate of climb whereas: a Vy and Vx are not affected by a higher gross mass. b Vx is increased and Vy is decreased. c Vy and Vx are decreased. d Vy and Vx are increased.
130 Under what condition does pressure altitude have the same value as density altitude? a At sea level when the temperature is 0 °C. b When the altimeter has no position error. c At standard temperature. d When the altimeter setting is 1013,2 hPa.
Which of the following statements is correct? a The TORA is 50% of the TODA as a declared distance making the TORA 1,5 times the TODA. b The maximum clearway that can be used is limited to 50% of the TORA making the TODA 150% of the TORA. c If any clearway is present it must be reduced to no greater distance than the stopway. d The TODA is always longer than the TORA.
132 An aeroplane is in a power off glide at best gliding speed. If the pilot decreases the pitch attitude the glide distance: a remains the same. b may increase or decrease depending on the aeroplane. c decreases. d increases.
Ignoring the effect of compressibility, what would Cl do with an increase in altitude? a Increase. b Decrease. c Remain the same. d Increase, then decrease.
134 ASDA is defined as:
a TORA plus clearway. b TODA plus stopway. c the same as TODA. d TORA plus stopway.
135 The lowest point of the drag or thrust required curve of a jet aeroplane, respectively, is the point for: a maximum specific range. b minimum endurance. c minimum drag. d minimum specific range.
136 Can a stopway be used in take-off calculations? a Only if the stopway is shorter than the clearway. b Yes. c No. d Only if the clearway is shorter than the stopway.
137 For an aircraft gliding at its best glide range speed, if A of A is reduced: a glide distance will decrease. b glide distance will remain constant if speed is increased. c glide distance will increase. d glide distance will remain unaffected.
138 The maximum horizontal speed occurs when: a the thrust is equal to minimum drag. b the thrust does not increase further with increasing speed. c the maximum thrust is equal to the total drag. d the thrust is equal to the maximum drag.
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