Principles of Flight (Aeroplane) (081)
JAAExam.com/ATPL
Much, most, or all of the data, organization, and electronic encoding of the text, images, and other material presented below is (c) 1997-2013 Dauntless Software. This document is to be used ONLY as study material supplemental to Dauntless Software's series of JAA Knowledge test prep software by the person or persons described in the following paragraph. Any other use, including attempts at operational uses such as utilizing the data provided for flight or flight planning purposes, is strictly prohibited. Re-publishing this data, for example, by placing this document or a document materially derived from this document on a public web page or by incorporating the data provided here into another product is strictly prohibited. This document was created under a PERSONAL licence of the GroundSchool software issued to Parul Vohra 504, Technology Apartments / Patparganj / New Delhi / India 110092 - 9545457093 -
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1. JAAExam.com/ATPL Question ID: 1380
Answer B is correct.
In a single acting constant speed propeller, the actuator spring:
The correct answer is B moves the propeller through coarse to feather.
A. opposes the CSU weights. B. moves the propeller through coarse to feather.
References
C. moves the propeller through coarse to a fine pitch. D. moves the propeller out of the feathered position when selected.
2. JAAExam.com/ATPL Question ID: 1459
Answer A is correct.
For an aircraft with a right hand propeller, the slipstream rotation will cause:
The correct answer is A yaw to the left.
A. yaw to the left. B. yaw to the right.
References
C. roll to the left. D. roll to the right.
3. JAAExam.com/ATPL Question ID: 944
Answer B is correct.
Which is the most critical phase regarding ice on a wing leading edge?
The correct answer is B The last part of rotation.
A. During the take off run. B. The last part of rotation.
References
C. Climb with all engines operating. D. All phases are equally important.
4. JAAExam.com/ATPL Question ID: 1312
Answer B is correct.
Which speed represents the maximum flap extended speed?
The correct answer is B Vfe
A. Vs1 B. Vfe
References
C. Vlof D. Vfc
5. JAAExam.com/ATPL Question ID: 471
Answer B is correct.
Lift is a function of:
The correct answer is B
A. velocity, density, wing shape and lift coefficient.
velocity, wing area, CL and density.
B. velocity, wing area, CL and density.
References
C. velocity, wing shape, wing area and CL. D. velocity, density, gross wing area and CD.
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6. JAAExam.com/ATPL Question ID: 983
Answer C is correct.
At what speed does a shock wave move forward over the ground?
The correct answer is C Aircraft ground speed.
A. Speed of sound at ground level. B. Flight level airspeed.
References
C. Aircraft ground speed. D. Aircraft TAS.
7. JAAExam.com/ATPL Question ID: 1153
Answer D is correct.
After a disturbance about the lateral axis, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
The correct answer is D
A. Statically unstable - Dynamically neutral
Statically stable - Dynamically neutral References
B. Statically unstable - Dynamically stable C. Statically stable - Dynamically unstable D. Statically stable - Dynamically neutral
8. JAAExam.com/ATPL Question ID: 1063
Answer C is correct.
The bow wave will appear first at:
The correct answer is C
A. M= 0.6 B. M= Mcrit
M= 1.0
C. M= 1.0
References
D. M= 1.3
9. JAAExam.com/ATPL Question ID: 1181
Answer C is correct.
Rotation about the lateral axis is called:
The correct answer is C
A. yawing. B. rolling. C. pitching.
pitching. References
D. slipping.
10. JAAExam.com/ATPL Question ID: 792
Answer C is correct.
Which of the following aircraft designs would be most prone to super stall?
The correct answer is C Swept back wing.
A. T-tail. B. Swept forward wing.
References
C. Swept back wing. D. Pod mounted engines beneath the wing.
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11. JAAExam.com/ATPL Question ID: 1335
Answer D is correct.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. Increase in angle of attack of 1 degree will increase CL by 0.079. A vertical up gust instantly changes the angle of attack by 2 degrees. The load factor will be:
The correct answer is D 1.45 References
A. 1.9 B. 0.9 C. 0.45 D. 1.45
12. JAAExam.com/ATPL Question ID: 1377
Answer B is correct.
A right-hand propeller:
The correct answer is B
A. is always contra-rotating. B. rotates clockwise viewed from the rear. C. rotates clockwise viewed from the front. D. is an engine fitted to the starboard side.
rotates clockwise viewed from the rear. References
13. JAAExam.com/ATPL Question ID: 928
Answer C is correct.
The optimum angle of attack for a typical airfoil is about..., and the actual angle of attack will be close to this optimum angle during...
The correct answer is C
A. 4° , a stall.
4° , cruise. References
B. 16° , a stall. C. 4° , cruise. D. 16° , cruise.
14. JAAExam.com/ATPL Question ID: 774
Answer B is correct.
An aeroplane has a stalling speed of 100 kt in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is:
The correct answer is B
A. 141 kt.
122 kt. References
B. 122 kt. C. 82 kt. D. 150 kt.
15. JAAExam.com/ATPL Question ID: 1225
Answer A is correct.
The effect of differential ailerons in a turn will be:
The correct answer is A
A. increased profile drag on the inner wing. B. reduced drag on the inner wing. C. produced equal form drag on the inner and outer wings.
increased profile drag on the inner wing. References
D. reduced induced drag on the inner and outer wings.
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16. JAAExam.com/ATPL Question ID: 854
Answer D is correct.
The load factor is:
The correct answer is D
A. the ratio of lift to drag. B. the ratio of centripetal force to lift. C. the ratio of thrust to weight.
the ratio of lift to weight. References
D. the ratio of lift to weight.
17. JAAExam.com/ATPL Question ID: 509
Answer C is correct.
The angle between the airflow (relative wind) and
The correct answer is C
the chord line of an aerofoil is: A. climb path angle.
angle of attack. References
B. glide path angle. C. angle of attack. D. same as the angle between chord line and fuselage axis.
18. JAAExam.com/ATPL Question ID: 980
Answer D is correct.
To be able to predict compressibility effects you have to determine the:
The correct answer is D Mach Number.
A. IAS. B. EAS.
References
C. TAS. D. Mach Number.
19. JAAExam.com/ATPL Question ID: 1005
Answer A is correct.
Vortex generators mounted on the upper wing surface will:
The correct answer is A decrease the shock wave induced separation.
A. decrease the shock wave induced separation. B. decrease the interference drag of the trailing edge flaps.
References
C. decrease the stalling speed by increase of the tangential velocity of the swept wing. D. increase the effectiveness of the spoiler due to increase in parasite drag.
20. JAAExam.com/ATPL Question ID: 1219
Answer A is correct.
What happens during an engine failure with two similar aeroplanes with wing mounted engines, one of them with jet engines, the other one with corotating propellers:
The correct answer is A
A. more roll tendency for the propeller aeroplane.
more roll tendency for the propeller aeroplane. References
B. the same yaw tendency for both aeroplanes regardless of left or right engine failure. C. the same roll tendency for both aeroplanes. D. less roll tendency for the propeller aeroplane.
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21. JAAExam.com/ATPL Question ID: 576 The movement of an aircraft is defined along three
Answer B is correct.
axes which all pass through: The correct answer is B A. the centre of pressure. B. the centre of gravity.
the centre of gravity.
C. the intersection of the centrelines of the fuselage and wings.
References
D. the intersection of the normal vertical datum.
22. JAAExam.com/ATPL Question ID: 1507
Answer A is correct.
When an aircraft is in a steady climb (constant IAS), how will be the wing stalling angle be affected?
The correct answer is A
A. The wing stalling angle will remain the same, regardless of altitude. B. The wing stalling angle will increase with increasing altitude.
The wing stalling angle will remain the same, regardless of altitude. References
C. The stalling angle of the wing will decrease with increasing altitude. D. The stalling angle of the wing is only affected by true airspeed which remains constant during climb.
23. JAAExam.com/ATPL Question ID: 1025
Answer B is correct.
Mcrit is the free stream Mach number at which:
The correct answer is B
A. the bottom shock wave reaches the wing trailing edge.
the first local Mach number at any point on the aircraft equals M 1.0
B. the first local Mach number at any point on the aircraft equals M 1.0
References
C. he bow shock wave attaches to the wing leading edge. D. the centre of pressure is at its most rearward point.
24. JAAExam.com/ATPL Question ID: 1456
Answer C is correct.
The CTM of a propeller is:
The correct answer is C
A. a force which turns the blades towards coarse pitch.
a force which turns the blades towards fine pitch.
B. the distance a blade moves forward in one revolution.
References
C. a force which turns the blades towards fine pitch. D. a force which directly opposes the torque force.
25. JAAExam.com/ATPL Question ID: 1429
Answer C is correct.
The more blades a propeller has, the more power it is able to absorb. The limitation on blade number from an aerodynamic standpoint is:
The correct answer is C the loss of efficiency of one blade if it follows to the path of the preceding blade to closely.
A. engine speed if the engine is not geared. B. the blade diameter as compared to the maximum width.
References
C. the loss of efficiency of one blade if it follows to the path of the preceding blade to closely. D. the loss of efficiency as the propeller tip approaches sonic speed.
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26. JAAExam.com/ATPL Question ID: 1494
Answer B is correct.
An aeroplane performs a steady horizontal turn with 20 degrees bank and 150 kt TAS. The same aeroplane with the same bank angle and the same speed, but at a lower mass will:
The correct answer is B
A. turn with a higher turn rate.
turn with the same turn radius. References
B. turn with the same turn radius. C. turn with a larger turn radius. D. turn with a smaller turn radius.
27. JAAExam.com/ATPL Question ID: 1048
Answer A is correct.
When the air is passing through an expansion wave the static temperature will?
The correct answer is A decrease.
A. decrease. B. increase.
References
C. stay constant. D. decrease and beyond a certain Mach number start increasing again.
28. JAAExam.com/ATPL Question ID: 1328
Answer B is correct.
On FAR 23 airplane, the limit load factor in normal category is:
The correct answer is B +3,8 G
A. 4,4 G B. +3,8 G
References
C. +6,0 G D. +3,2 G
29. JAAExam.com/ATPL Question ID: 1348
Answer C is correct.
Which of the following is a correct statement of gust factors applied in certification under JAR 25?
The correct answer is C 50fps at VC
A. 55fps at VC B. 66fps at VD
References
C. 50fps at VC D. 25fps at VB
30. JAAExam.com/ATPL Question ID: 1514
Answer C is correct.
An aeroplane performs a continuous descent with 160 kts IAS and 1.000 feet/min vertical speed. In this condition:
The correct answer is C
A. lift is less than drag.
weight is greater than lift. References
B. drag is less than the combined forces that move the aeroplane forward. C. weight is greater than lift. D. lift is equal to weight.
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31. JAAExam.com/ATPL Question ID: 743
Answer B is correct.
Ground effect has the following influence on the landing distance:
The correct answer is B increases.
A. decreases. B. increases.
References
C. does not change. D. increases, only if the landing flaps are fully extended.
32. JAAExam.com/ATPL Question ID: 1527
Answer B is correct.
When are the four forces that act on an airplane in equilibrium during flight?
The correct answer is B In an unaccelerated horizontal flight.
A. In a vertical dive. B. In an unaccelerated horizontal flight.
References
C. In an unaccelerated turn. D. In an accelerated climb and/or descent.
33. JAAExam.com/ATPL Question ID: 488
Answer C is correct.
The Principle of Continuity states that in a Stream tube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will:
The correct answer is C increase.
A. remain the same.
References
B. decrease. C. increase. D. sonic.
34. JAAExam.com/ATPL Question ID: 615
Answer A is correct.
In a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure will (I) and the velocity will (II):
The correct answer is A
A. (I) decrease; (II) increase
(I) decrease; (II) increase References
B. (I) increase; (II) increase C. (I) increase; (II) decrease D. (I) decrease; (II) decrease
35. JAAExam.com/ATPL Question ID: 1445
Answer D is correct.
For a tail wheel aircraft with a right handed propeller, at the start of the take off run, asymmetric blade effect causes:
The correct answer is D
A. yaw to right.
yaw to left. References
B. no effect. C. nose down pitch (tail up). D. yaw to left.
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36. JAAExam.com/ATPL Question ID: 1340
Answer A is correct.
What is the positive limit load factor for large jet transport aircraft?
The correct answer is A n = 2.5
A. n = 2.5 B. n = 3.75
References
C. n = 1.5 D. n = 1.0
37. JAAExam.com/ATPL Question ID: 866
Answer D is correct.
What is the most effective flap system?
The correct answer is D
A. Single slotted flap. B. Split flap. C. Plain flap. D. Fowler flap.
Fowler flap. References
38. JAAExam.com/ATPL Question ID: 460
Answer C is correct.
What is the SI unit that results from multiplying kg and m/s2?
The correct answer is C Newton.
A. Joule. B. Psi.
References
C. Newton. D. Watt.
39. JAAExam.com/ATPL Question ID: 906
Answer A is correct.
Extension of FOWLER type trailing edge lift augmentation devices, will produce:
The correct answer is A a nose-down pitching moment.
A. a nose-down pitching moment. B. no pitching moment.
References
C. a nose-up pitching moment. D. a force which reduces drag.
40. JAAExam.com/ATPL Question ID: 885
Answer B is correct.
When the trailing edge flaps are deflected in level flight, the change in pitch moment will be:
The correct answer is B nose down.
A. dependent on c.g. location. B. nose down.
References
C. nose up. D. zero.
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41. JAAExam.com/ATPL Question ID: 521
Answer C is correct.
If an aircraft is pitching up:
The correct answer is C
A. the incidence angle increases. B. the incidence angle decreases. C. the incidence angle remains fixed.
the incidence angle remains fixed. References
D. the incidence angle first increases and than decreases.
42. JAAExam.com/ATPL Question ID: 1078
Answer D is correct.
The effect of a ventral fin on the static stability of an aeroplane is as follows: (1=longitudinal, 2=lateral, 3=directional)
The correct answer is D
A. 1: no effect, 2: positive, 3: negative
1: no effect, 2: negative, 3: positive References
B. 1: positive, 2: negative, 3: negative C. 1: negative, 2: positive, 3: positive D. 1: no effect, 2: negative, 3: positive
43. JAAExam.com/ATPL Question ID: 750
Answer B is correct.
On the approach to land, ground effect will begin to be felt at:
The correct answer is B half the wingspan above the ground.
A. twice the wingspan above the ground. B. half the wingspan above the ground.
References
C. when the angle of attack is increased. D. upon elevator deflection.
44. JAAExam.com/ATPL Question ID: 1524
Answer C is correct.
A pitch up could be caused by:
The correct answer is C
A. forward movement of the center of gravity. B. a reduction in varying loads due to G. C. forward movement of the center of pressure.
forward movement of the center of pressure. References
D. lateral movement of the center of gravity.
45. JAAExam.com/ATPL Question ID: 466
Answer C is correct.
Bernoulli’ s equation states that:
The correct answer is C
A. static pressure equals stagnation pressure. B. dynamic pressure equals stagnation pressure. C. the sum of static pressure and dynamic pressure is equal to stagnation pressure.
the sum of static pressure and dynamic pressure is equal to stagnation pressure. References
D. the sum of centre of pressure and dynamic pressure is total pressure.
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46. JAAExam.com/ATPL Question ID: 1372
Answer C is correct.
Thrust forces acting on a propeller blade in flight will tend to:
The correct answer is C bend the blades forward in the direction of flight.
A. bend the blades back opposite to the direction of flight. B. bend the blades in the direction of rotation. C. bend the blades forward in the direction of flight. D. bend the blades opposite to the direction of rotation.
References
47. JAAExam.com/ATPL Question ID: 1132
Answer B is correct.
The C.G. position of an aeroplane is forward of the neutral point in a fixed location. Speed changes cause a departure from the trimmed position. Which of the following statements about the stick force stability is correct?
The correct answer is B
A. Increase of speed generates pull forces.
Increasing 10 kt trimmed at low speed has more effect on the stick force than increasing 10 kt trimmed at high speed. References
B. Increasing 10 kt trimmed at low speed has more effect on the stick force than increasing 10 kt trimmed at high speed. C. Aeroplane nose up trim decreases the stick force stability. D. Stick force stability is not affected by trim.
48. JAAExam.com/ATPL Question ID: 1347
Answer B is correct.
Which combination of speeds is applicable for structural strength in gust (clean configuration)?
The correct answer is B 50 ft/sec and VC.
A. 66 ft/sec and VD. B. 50 ft/sec and VC.
References
C. 65 ft/sec at all speeds. D. 55 ft/sec and VB.
49. JAAExam.com/ATPL Question ID: 725
Answer B is correct.
What are the effects of tropical rain on:
The correct answer is B
i. ii.
CLMAX Drag
(i) decrease (ii) increase References
A. (i) increase (ii) decrease B. (i) decrease (ii) increase C. (i) increase (ii) increase D. (i) decrease (ii) decrease
50. JAAExam.com/ATPL Question ID: 973
Answer D is correct.
The Mach number:
The correct answer is D
A. increases at a given TAS, when the temperature rises.
is the ratio between the TAS of the aeroplane and the local speed of sound.
B. is the ratio between the TAS of the aeroplane and the speed of sound at sea level.
References
C. is the ratio between the IAS of the aeroplane and the local speed of sound. D. is the ratio between the TAS of the aeroplane and the local speed of sound.
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51. JAAExam.com/ATPL Question ID: 1214
Answer B is correct.
What is the purpose of the rudder on an airplane?
The correct answer is B
A. To increase lateral stability. B. To control the aircraft about the yaw-axis. C. To control over banking tendency.
To control the aircraft about the yaw-axis. References
D. To control roll.
52. JAAExam.com/ATPL Question ID: 1052
Answer D is correct.
As an aircraft goes from subsonic to supersonic flight the CP:
The correct answer is D moves aft.
A. remains in the same position. B. moves aft and then forward.
References
C. moves forward. D. moves aft.
53. JAAExam.com/ATPL Question ID: 762
Answer B is correct.
What must happen to the CL when flaps are deployed while maintaining a constant IAS in straight and level flight?
The correct answer is B
A. Increase then decrease.
Remain constant. References
B. Remain constant. C. Decrease. D. Increase.
54. JAAExam.com/ATPL Question ID: 1522
Answer A is correct.
Which of the following statements is correct?
The correct answer is A
I. II.
VMCL is the minimum control speed in the landing configuration.
I is correct, II is correct.
The speed VMCL can be limited by the available maximum roll rate
References
A. I is correct, II is correct. B. I is incorrect, II is incorrect. C. I is correct, II is incorrect. D. I is incorrect, II is correct.
55. JAAExam.com/ATPL Question ID: 649
Answer C is correct.
The aerofoil polar is:
The correct answer is C
A. the relation between the horizontal and the vertical speed.
a graph of the relation between the lift coefficient and the drag coefficient.
B. a graph of the relation between the lift coefficient and the angle of attack.
References
C. a graph of the relation between the lift coefficient and the drag coefficient. D. a graph, in which the thickness of the wing aerofoil is given as a function of the chord.
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56. JAAExam.com/ATPL Question ID: 872
Answer B is correct.
Refer to Figure: 081-15
The correct answer is B
(Refer to figure 081-15) The trailing edge device shown in the figure is a:
Fowler flap. References
A. Krueger flap B. Fowler flap. C. plain flap. D. split flap.
57. JAAExam.com/ATPL Question ID: 1201
Answer D is correct.
An aeroplane has a servo-tab controlled elevator. What will happen when only the elevator jams during flight?
The correct answer is D
A. The pitch control forces double.
Pitch control reverses direction. References
B. Pitch control has been lost. C. The servo-tab now works as a negative trimtab. D. Pitch control reverses direction.
58. JAAExam.com/ATPL Question ID: 1217
Answer C is correct.
When inner and outer ailerons are mounted, outer ailerons are used:
The correct answer is C at low speeds.
A. during take off only. B. at high speeds.
References
C. at low speeds. D. when flaps are in landing configuration only.
59. JAAExam.com/ATPL Question ID: 1081
Answer A is correct.
Stability on an aircraft means:
The correct answer is A
A. the ability to return to the original trimmed
the ability to return to the original trimmed position
position when disturbed. B. the ability to continue flight in the disturbed position.
when disturbed. References
C. the ability to roll around an axis. D. divergence from the original trimmed position when disturbed.
60. JAAExam.com/ATPL Question ID: 754
Answer B is correct.
On entering ground effect, maintaining flight at the same speed:
The correct answer is B less power is required.
A. ground effect has no effect on power. B. less power is required.
References
C. more power is required. D. lift decreases.
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61. JAAExam.com/ATPL Question ID: 1508
Answer D is correct.
The bank angle in a rate-one turn depends on:
The correct answer is D
A. wind. B. weight. C. load factor.
TAS. References
D. TAS.
62. JAAExam.com/ATPL Question ID: 458
Answer B is correct.
The maximum angle of attack for the flaps down configuration, compared to flaps up is:
The correct answer is B smaller.
A. greater. B. smaller.
References
C. unchanged. D. smaller or greater, depending on CG position.
63. JAAExam.com/ATPL Question ID: 1498
Answer D is correct.
The load factor is defined as:
The correct answer is D
A. lift divided by drag.
lift divided by weight.
B. centripetal force divided by lift. C. thrust divided by weight. D. lift divided by weight.
References
64. JAAExam.com/ATPL Question ID: 1268
Answer A is correct.
Which statement about a primary control surface controlled by a servo tab, is correct?
The correct answer is A
A. The position is undetermined during taxiing, in particular with tailwind. B. The servo tab can also be used as a trimtab.
The position is undetermined during taxiing, in particular with tailwind. References
C. The control effectiveness of the primary surface is increased by servo tab deflection. D. Due to the effectiveness of the servo tab the control surface area can be smaller.
65. JAAExam.com/ATPL Question ID: 1237
Answer A is correct.
An aircraft rolls about the:
The correct answer is A
A. longitudinal axis. B. lateral and longitudinal axis. C. vertical axis.
longitudinal axis. References
D. lateral axis.
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66. JAAExam.com/ATPL Question ID: 1061
Answer C is correct.
If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the centre of lift will move:
The correct answer is C aft to the mid chord.
A. forward to the leading edge. B. aft to the trailing edge.
References
C. aft to the mid chord. D. forward to the mid chord.
67. JAAExam.com/ATPL Question ID: 1131
Answer B is correct.
The centre of gravity of an aircraft is on its most forward limit in straight and level flight. What effect will this have on longitudinal stability?
The correct answer is B
A. Longitudinal stability will be reduced with an increased download existing on the tailplane. B. An increased download will exist on the tailplane with an associated increase in longitudinal stability. C. A reduced download will exist on the tailplane with an associated reduction in longitudinal stability. D. A reduction in longitudinal stability will exist with no change in loading on the tailplane.
An increased download will exist on the tailplane with an associated increase in longitudinal stability. References
68. JAAExam.com/ATPL Question ID: 711
Answer A is correct.
At an aeroplanes minimum drag speed, what is the ratio between induced drag Di and profile drag Dp (Di/Dp)?
The correct answer is A
A. 1/1
1/1 References
B. It varies between aeroplane types. C. 2/1 D. 1/2
69. JAAExam.com/ATPL Question ID: 948
Answer C is correct.
The Mach trim system will:
The correct answer is C
A. pump the fuel from tank to tank, depending on the Mach Number.
adjust the stabilizer, depending on the Mach Number.
B. keep the Mach Number automatically constant.
References
C. adjust the stabilizer, depending on the Mach Number. D. adjust the elevator trim tab, depending on the Mach Number.
70. JAAExam.com/ATPL Question ID: 991
Answer B is correct.
Which of the following flight phenomena can only happen at Mach Numbers above the critical Mach Number?
The correct answer is B
A. Elevator stall.
Mach buffet. References
B. Mach buffet. C. Dutch roll. D. Speed instability.
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71. JAAExam.com/ATPL Question ID: 995
Answer D is correct.
Tuck under is caused by which
The correct answer is D
i. ii.
movement of the centre of pressure of the wing, and change of the downwash angle at the location of the stabilizer.
A. (i) forward (ii) increasing B. (i) forward (ii) decreasing C. (i) aft (ii) increasing D. (i) aft (ii) decreasing
(i) aft (ii) decreasing References
72. JAAExam.com/ATPL Question ID: 1093
Answer D is correct.
The Mach trim system will prevent:
The correct answer is D
A. Dutch roll. B. buffeting. C. shock stall.
tuck under. References
D. tuck under.
73. JAAExam.com/ATPL Question ID: 1562
Answer A is correct.
Refer to Figure: 081-08
The correct answer is A
(Refer to figure 081-08) Which point in the diagram gives the lowest speed in horizontal flight?
Point A. References
A. Point A. B. Point B. C. Point C. D. Point D.
74. JAAExam.com/ATPL Question ID: 698
Answer D is correct.
When taking off or landing at an airport where heavy aircraft are operating, one should be particularly alert to the hazards of wingtip vortices because this wake turbulence tends to:
The correct answer is D
A. increase its strength during the first minutes after creation.
sink into the flight path of aircraft operating below the aircraft generating the turbulence. References
B. rise very rapidly, creating a local low pressure area. C. remain in the vicinity of the airport for hours. D. sink into the flight path of aircraft operating below the aircraft generating the turbulence.
75. JAAExam.com/ATPL Question ID: 1130
Answer A is correct.
If the centre of gravity of an aircraft moves aft during flight, ...
The correct answer is A a reduction in longitudinal stability will result.
A. a reduction in longitudinal stability will result. B. an increase in lateral stability will result.
References
C. stability will not be affected. D. an increase in longitudinal stability will result.
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76. JAAExam.com/ATPL Question ID: 946
Answer A is correct.
Which statement with respect to the speed of sound is correct? A. Varies with the square root of the absolute temperature. B. Increases always if the density of the air decreases.
The correct answer is A Varies with the square root of the absolute temperature. References
C. Is independent of altitude. D. Doubles if the temperature increases from 9° to 36° Centigrade.
77. JAAExam.com/ATPL Question ID: 1272
Answer B is correct.
A device designed to assist the pilot in moving the controls against the force of the air flow is known as a:
The correct answer is B
A. mass balance.
aerodynamic balancing surface. References
B. aerodynamic balancing surface. C. trim tab. D. elevon.
78. JAAExam.com/ATPL Question ID: 945
Answer B is correct.
When accelerating through the region of transonic flight:
The correct answer is B
A. the centre of pressure will move to the rear and cause a nose up trim change. B. the centre of pressure will move aft and cause an increased stability in pitch.
the centre of pressure will move aft and cause an increased stability in pitch. References
C. the centre of pressure will move forward and cause a nose up trim change. D. the centre of pressure will move forward and contribute to a better lift-to-drag ratio.
79. JAAExam.com/ATPL Question ID: 805
Answer B is correct.
The stall speed increases, when? (all other factors of importance being constant)
The correct answer is B pulling out of a dive.
A. weight decreases. B. pulling out of a dive.
References
C. spoilers are retracted. D. minor altitude changes occur e.g. 0-10.000 ft.
80. JAAExam.com/ATPL Question ID: 1393 The blade angle of a fixed pitch propeller remains
Answer A is correct.
the same in flight. The angle of attack of the blade: The correct answer is A A. increases when airspeed decreases and vice versa.
increases when airspeed decreases and vice versa.
B. is controlled by the CSU. C. is always directly proportional to aircraft speed.
References
D. also remains the same.
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81. JAAExam.com/ATPL Question ID: 1204
Answer A is correct.
The centre of gravity moving aft will:
The correct answer is A
A. increase the elevator up effectiveness. B. decrease the elevator up effectiveness. C. not affect the elevator up or down effectiveness.
increase the elevator up effectiveness. References
D. increase or decrease the elevator up effectiveness, depending on wing location.
82. JAAExam.com/ATPL Question ID: 1440
Answer A is correct.
A propeller rotating anti-clockwise when viewed from the front, during the take-off ground roll will:
The correct answer is A
A. produce an increased load on the left wheel due to torque reaction. B. produce an increased load on the right wheel due to gyroscopic effect.
produce an increased load on the left wheel due to torque reaction. References
C. produce an increased load on the right wheel due to torque reaction. D. produce an increased load on the left wheel due to gyroscopic effect.
83. JAAExam.com/ATPL Question ID: 1284
Answer B is correct.
In general transport aeroplanes with power assisted flight controls are fitted with an adjustable stabilizer instead of trim tabs on the elevator. This is because:
The correct answer is B effectiveness of trim tabs is insufficient for those aeroplanes.
A. the pilot does not feel the stick forces at all. B. effectiveness of trim tabs is insufficient for those aeroplanes.
References
C. mechanical adjustment of trim tabs creates too many problems. D. trim tab deflection increases Mcrit.
84. JAAExam.com/ATPL Question ID: 513
Answer D is correct.
Which of the following is the correct formula for drag?
The correct answer is D 1/2 RHO V2 CD S
A. 1/2 RHO V2 CL S B. 1/2 RHO V (CL)2 S
References
C. 1/2 RHO V2 AR CD S D. 1/2 RHO V2 CD S
85. JAAExam.com/ATPL Question ID: 993
Answer D is correct.
At higher altitudes, the stall speed (IAS):
The correct answer is D
A. decreases until the tropopause. B. decreases. C. remains the same.
increases. References
D. increases.
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86. JAAExam.com/ATPL Question ID: 1565
Answer D is correct.
With a L/D ratio of 9:1 and flying at 12000 ft the glide range in still air would be:
The correct answer is D 18 nm
A. 15 nm B. 20 nm
References
C. 14 nm D. 18 nm
87. JAAExam.com/ATPL Question ID: 977
Answer A is correct.
What comes about due to an increase of the effectiveness of the spoiler which increases parasite drag.
The correct answer is A
A. Mach buffet.
Mach buffet. References
B. Dutch roll. C. Speed instability. D. Elevator stall.
88. JAAExam.com/ATPL Question ID: 1156
Answer C is correct.
Lateral stability can be increased using:
The correct answer is C
A. spoilers. B. frise ailerons. C. wing dihedral.
wing dihedral. References
D. wing anhedral.
89. JAAExam.com/ATPL Question ID: 826
Answer C is correct.
The stalling speed in IAS will change according to the following factors:
The correct answer is C
A. increase with increased load factor, icing conditions and an aft c.g. location. B. decrease in a forward c.g. location, higher altitude and due to the slip stream from a propeller on an engine located forward of the wing.
increase during turn, increased mass and forward c.g. location. References
C. increase during turn, increased mass and forward c.g. location. D. increase with increased load factor, more flaps but will not increase due to the bank angle in a turn.
90. JAAExam.com/ATPL Question ID: 836
Answer A is correct.
As the center of gravity is changed, recovery from a stall becomes progressively:
The correct answer is A more difficult as the center of gravity moves aft.
A. more difficult as the center of gravity moves aft.
References
B. more difficult as the center of gravity moves forward. C. less difficult as the center of gravity moves aft. D. is unaffected by center of gravity position, only by all up weight.
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91. JAAExam.com/ATPL Question ID: 1395
Answer B is correct.
A propeller blade is twisted to:
The correct answer is B
A. ensure equal thrust is generated along the length of the blade.
maintain a constant angle of attack along the length of the blade.
B. maintain a constant angle of attack along the length of the blade.
References
C. balance stress forces generated on the blade. D. increase the effective solidity of the blade.
92. JAAExam.com/ATPL Question ID: 1311
Answer D is correct.
VA is:
The correct answer is D
A. the speed that should not be exceeded in the climb.
the maximum speed at which maximum elevator deflection up is allowed.
B. the maximum speed at which rolls are allowed.
References
C. the speed at which a heavy transport aeroplane should fly in turbulence. D. the maximum speed at which maximum elevator deflection up is allowed.
93. JAAExam.com/ATPL Question ID: 1098
Answer D is correct.
The Mach-trim function is installed on most commercial jets in order to minimize the adverse effects of:
The correct answer is D
A. compressibility effects on the stabilizer
changes in the position of centre of pressure References
B. increased drag due to shock wave formation C. uncontrolled changes in stabilizer setting D. changes in the position of centre of pressure
94. JAAExam.com/ATPL Question ID: 1182
Answer A is correct.
Which statement is true for an aircraft in a fully developed spin?
The correct answer is A The inner wing is more stalled.
A. The inner wing is more stalled. B. The outer wing is more stalled.
References
C. The aircraft will automatically stabilise after a few turns. D. Full elevator deflection up is required at once, in order to restore straight and level flight.
95. JAAExam.com/ATPL Question ID: 1531
Answer D is correct.
As fuel is consumed during a level flight cruise at high level:
The correct answer is D induced drag will decrease.
A. the angle of attack must be increased. B. the stalling speed will increase.
References
C. the centre of pressure will move forward. D. induced drag will decrease.
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96. JAAExam.com/ATPL Question ID: 584
Answer D is correct.
Consider a certain stream line tube. The velocity of the stream in the tube is V. An increase of temperature of the stream at constant value of V will:
The correct answer is D
A. increase the mass flow when the tube is divergent in the direction of the flow.
decrease the mass flow. References
B. increase the mass flow. C. not affect the mass flow. D. decrease the mass flow.
97. JAAExam.com/ATPL Question ID: 1223
Answer C is correct.
In a roll manoeuvre, the down going wing:
The correct answer is C
A. provides a force to increase the rate of roll. B. has an increase in wash out. C. provides a damping force.
provides a damping force. References
D. has a reduced angle of attack.
98. JAAExam.com/ATPL Question ID: 483
Answer D is correct.
Pitch angle is defined as:
The correct answer is D
A. the angle between the chord line and the relative airflow.
the angle between the longitudinal axis of the aircraft and the local horizon.
B. the angle between the chord line and the free stream flow velocity.
References
C. the angle between the lower wing surface and the relative airflow. D. the angle between the longitudinal axis of the aircraft and the local horizon.
99. JAAExam.com/ATPL Question ID: 685
Answer A is correct.
The induced drag:
The correct answer is A
A. increases as the lift coefficient increases. B. increases as the aspect ratio increases. C. has no relation to the lift coefficient.
increases as the lift coefficient increases. References
D. increases as the magnitude of the tip vortices decreases.
100. JAAExam.com/ATPL Question ID: 1323
Answer A is correct.
Flutter may be caused by:
The correct answer is A
A. distortion by bending and torsion of the structure causing increasing vibration in the resonance frequency. B. low airspeed aerodynamic wing stall. C. roll control reversal.
distortion by bending and torsion of the structure causing increasing vibration in the resonance frequency. References
D. high airspeed aerodynamic wing stall.
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101. JAAExam.com/ATPL Question ID: 1468
Answer C is correct.
What are the two forces into which the lift force may be resolved when an aircraft is executing a turn?
The correct answer is C
A. a force equal and opposite to thrust and the centrifugal force. B. a force equal and opposite to drag and the centripetal force.
centripetal force and a force equal and opposite to weight. References
C. centripetal force and a force equal and opposite to weight. D. a force opposite to weight and a force equal and opposite to thrust.
102. JAAExam.com/ATPL Question ID: 484
Answer D is correct.
Compared to a wing at sea level at 200kt TAS, a wing at 40,000ft at 400kt TAS and the same angle of attack will have:
The correct answer is D
A. 1.4 times the lift.
the same lift. References
B. twice the lift. C. four times the lift. D. the same lift.
103. JAAExam.com/ATPL Question ID: 648
Answer A is correct.
Refer to Figure: 081-08
The correct answer is A
(Refer to figure 081-08) Which point shown in the figure corresponds with CL for minimum horizontal flight speed?
Point A References
A. Point A B. Point B C. Point C D. Point D
104. JAAExam.com/ATPL Question ID: 618
Answer A is correct.
The lift force, acting on an aerofoil:
The correct answer is A
A. is mainly caused by suction on the upper side of the aerofoil.
is mainly caused by suction on the upper side of the aerofoil.
B. increases, proportional to the angle of attack until 40 degrees.
References
C. is mainly caused by overpressure at the underside of the aerofoil. D. is maximum at an angle of attack of 2 degrees.
105. JAAExam.com/ATPL Question ID: 1218
Answer A is correct.
Left rudder input will cause:
The correct answer is A
A. left yaw about the vertical axis and left roll about the longitudinal axis.
left yaw about the vertical axis and left roll about the longitudinal axis.
B. right yaw about the vertical axis and right roll about the longitudinal axis.
References
C. left yaw about the vertical axis and right roll about the longitudinal axis. D. right yaw about the vertical axis and left roll about the longitudinal axis.
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106. JAAExam.com/ATPL Question ID: 588
Answer B is correct.
Bernoulli’ s Theorem states:
The correct answer is B
A. dynamic pressure increase and static pressure increase.
dynamic pressure increase and static pressure decrease.
B. dynamic pressure increase and static pressure decrease.
References
C. dynamic pressure is maximum at stagnation point. D. zero pressure at zero dynamic pressure.
107. JAAExam.com/ATPL Question ID: 1071
Answer A is correct.
An aircraft is placed in a level balanced turn and the controls released. It is spirally unstable if:
The correct answer is A the bank steadily increases.
A. the bank steadily increases. B. the bank remains the same.
References
C. the bank reduces. D. the pitch attitude increases.
108. JAAExam.com/ATPL Question ID: 489
Answer B is correct.
When the stick is moved forward, the stabilizer lift?
The correct answer is B
A. decreases. B. increases. C. usually remains the same.
increases. References
D. always remains the same.
109. JAAExam.com/ATPL Question ID: 1414 A twin-engine aircraft is available in both jet and propeller variants. The engines are mounted on the
Answer A is correct.
wings in the same position in both types. In the case of failure of one engine how would the engine torque effect show itself? A. Jet: roll toward the dead engine; Propeller: roll toward the dead engine. B. Jet: no change; Propeller: roll in the direction of rotation of the dead engine.
The correct answer is A Jet: roll toward the dead engine; Propeller: roll toward the dead engine. References
C. Jet: roll toward the live engine; Propeller: roll toward the dead engine. D. Jet: no change but; Propeller: roll away from the live engine.
110. JAAExam.com/ATPL Question ID: 541
Answer A is correct.
Which of the following quantities determines the mass flow in a nozzle?
The correct answer is A Velocity, density and area.
A. Velocity, density and area. B. Density and the square of the flow velocity.
References
C. Density and flow velocity. D. Velocity of flow and section area.
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111. JAAExam.com/ATPL Question ID: 1534
Answer C is correct.
If the temperature decreases it will cause a:
The correct answer is C
A. increase in take-off distance required and a reduced maximum rate of climb.
decrease in take-off distance required and an increase the maximum rate of climb.
B. decrease in take-off distance required and a reduced maximum rate of climb.
References
C. decrease in take-off distance required and an increase the maximum rate of climb. D. increase in take-off distance required and an increased maximum rate of climb.
112. JAAExam.com/ATPL Question ID: 1157
Answer C is correct.
Which statement is correct for a side slip condition at constant speed and side slip angle, where the geometric dihedral of an aeroplane is increased?
The correct answer is C
A. the required lateral control force does not change.
the required lateral control force increases. References
B. the required lateral control force decreases. C. the required lateral control force increases. D. the stick force per g decreases.
113. JAAExam.com/ATPL Question ID: 1327
Answer A is correct.
Which of the following statements is true? A. Limiting factors in severe turbulence are the possibility of a stall and the margin to the structural limitations. B. Through extension of the flaps in severe turbulence it is possible to reduce the speed and increase the margins to the structural limits.
The correct answer is A Limiting factors in severe turbulence are the possibility of a stall and the margin to the structural limitations. References
C. By increasing the flap setting in severe turbulence the stall speed will be reduced and the risk for exceeding the structural limits will be decreased. D. Through extension of the flaps in severe turbulence the centre of pressure will move aft which will increase the margins to the structural limits.
114. JAAExam.com/ATPL Question ID: 1069
Answer A is correct.
At constant EAS, what is the effect on aerodynamic damping as height increases?
The correct answer is A Damping in all axes is reduced.
A. Damping in all axes is reduced. B. Damping in pitch manoeuvres only is reduced.
References
C. Damping in roll is increased. D. Damping in all axes is increased.
115. JAAExam.com/ATPL Question ID: 1320
Answer D is correct.
By what percentage does VA (EAS) alter when the aeroplanes weight decreases by 19%?
The correct answer is D 10% lower.
A. 19% lower. B. 4.36% lower.
References
C. No change. D. 10% lower.
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116. JAAExam.com/ATPL Question ID: 1021
Answer A is correct.
The principle reason for employing wing sweep on an aircraft is to:
The correct answer is A increase the critical flight Mach-number (Mcrit).
A. increase the critical flight Mach-number (Mcrit). B. decrease the critical Mach-number (Mcrit). C. improve high and low speed aeroplane handling characteristics. D. improve wing tip stall at high speeds.
References
117. JAAExam.com/ATPL Question ID: 1057
Answer A is correct.
When a fluid element flows through an oblique shock wave:
The correct answer is A
A. Total temperature stays the same, Machnumber decreases and static temperature increases.
Total temperature stays the same, Mach-number decreases and static temperature increases. References
B. Total temperature increases, Mach-number increases and static temperature increases. C. Total temperature decreases, Mach-number decreases and static temperature decreases. D. Total temperature stays the same, Machnumber decreases and static temperature stays the same.
118. JAAExam.com/ATPL Question ID: 739
Answer B is correct.
High aspect ratio:
The correct answer is B
A. reduces parasite drag. B. reduces induced drag. C. increases stalling speed.
reduces induced drag. References
D. reduces manoeuvrability
119. JAAExam.com/ATPL Question ID: 665
Answer B is correct.
An increase in aspect ratio will:
The correct answer is B
A. have no effect on a wing or airfoil section. B. cause VIMD to be reduced. C. cause induced drag to increase.
cause VIMD to be reduced. References
D. cause VIMD to be increased.
120. JAAExam.com/ATPL Question ID: 897
Answer B is correct.
Refer to Figure: 081-14
The correct answer is B
(Refer to figure 081-14) Which type of flap is shown in the picture?
Split flap. References
A. Plain flap. B. Split flap. C. Single slotted flap. D. Fowler flap.
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121. JAAExam.com/ATPL Question ID: 708
Answer B is correct.
Which of the following is the cause of wing tip vortices? A. Air spilling from the top surface to the bottom surface at the wing tip. B. Air spilling from the bottom surface to the top surface at the wing tip.
The correct answer is B Air spilling from the bottom surface to the top surface at the wing tip. References
C. Air spilling from the bottom surface to the top surface at the left wing tip and from the top. surface to the bottom surface at the right wing tip. D. Span wise flow vector from the tip to the root on the bottom surface of the wing.
122. JAAExam.com/ATPL Question ID: 1439
Answer B is correct.
Propeller torque is caused by:
The correct answer is B
A. the propeller trying to reduce the pitch angle owing to the centrifugal turning moment.
the aerodynamic forces on the propeller blades.
B. the aerodynamic forces on the propeller blades.
References
C. the forward thrust on the propeller. D. the gyroscopic effect of the rotating propeller.
123. JAAExam.com/ATPL Question ID: 819
Answer B is correct.
Which of the following is the correct designation of stall speed in the landing configuration:
The correct answer is B VS0
A. VSL B. VS0
References
C. VS1 D. VS1g
124. JAAExam.com/ATPL Question ID: 656
Answer C is correct.
Extending the flaps while maintaining a constant angle of attack (all other factors constant):
The correct answer is C the aircraft will climb.
A. the aircraft will sink suddenly. B. the aircraft will yaw.
References
C. the aircraft will climb. D. the aircraft will roll.
125. JAAExam.com/ATPL Question ID: 1389
Answer C is correct.
With a fixed pitch propeller increasing speed will ... propeller alpha and increasing power (and therefore
The correct answer is C
propeller RPM) will ... propeller alpha. A. decrease, decrease
decrease, increase References
B. increase, decrease C. decrease, increase D. increase, increase
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126. JAAExam.com/ATPL Question ID: 746
Answer A is correct.
The influence of ground affect on landing distance will be to:
The correct answer is A increase landing distance.
A. increase landing distance. B. decrease landing distance.
References
C. have no affect on landing distance. D. depend on flap position.
127. JAAExam.com/ATPL Question ID: 1541
Answer B is correct.
The difference between power available and power required...
The correct answer is B decreases when the aircraft climbs.
A. increases when the aircraft climbs. B. decreases when the aircraft climbs.
References
C. decreases when the aircraft descends. D. is independent of altitude.
128. JAAExam.com/ATPL Question ID: 763
Answer A is correct.
In level flight an increase in angle of attack will cause:
The correct answer is A the stagnation point to move down and aft.
A. the stagnation point to move down and aft. B. the boundary layer to become thinner.
References
C. a decrease in pitch angle. D. the centre of pressure to move aft.
129. JAAExam.com/ATPL Question ID: 1286
Answer D is correct.
A balance tab is installed to provide:
The correct answer is D
A. movement of the control surface. B. balancing of the loads on the control surface. C. movement of the surface C of G to the hinge line. D. reduced control column movement resistance,
reduced control column movement resistance, References
130. JAAExam.com/ATPL Question ID: 879
Answer B is correct.
When spoilers are used as speed brakes:
The correct answer is B
A. at same angle of attack, CL remains unaffected.
at same angle of attack, CD is increased and CL is decreased.
B. at same angle of attack, CD is increased and CL is decreased.
References
C. CLmax of the polar curve is not affected. D. they do not affect wheel braking action during landing.
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131. JAAExam.com/ATPL Question ID: 1471
Answer D is correct.
In a coordinated and level turn:
The correct answer is D
A. the stall speed remains the same. B. the stall speed decreases. C. an aeroplane cannot stall.
the stall speed increases. References
D. the stall speed increases.
132. JAAExam.com/ATPL Question ID: 570
Answer C is correct.
The service ceiling of an aircraft is:
The correct answer is C
A. the altitude where rate of climb is zero. B. the highest altitude permitted for flight because of manoeuvre capability. C. the altitude where a low specific rate of climb is achieved.
the altitude where a low specific rate of climb is achieved. References
D. the altitude above which cruising speed cannot be maintained.
133. JAAExam.com/ATPL Question ID: 850
Answer B is correct.
Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
The correct answer is B (1) decreases; (2) increases.
A. (1) increases; (2) decreases. B. (1) decreases; (2) increases.
References
C. (1) decreases; (2) decreases. D. (1) increases; (2) increases.
134. JAAExam.com/ATPL Question ID: 1257
Answer B is correct.
An anti balance tab:
The correct answer is B
A. increases control surface vibration. B. improves the feel of the controls. C. protects against control reversal.
improves the feel of the controls. References
D. is a form of mass balance tab.
135. JAAExam.com/ATPL Question ID: 1278
Answer C is correct.
A tab which remains in line with the control surface when that surface is deflected, when the aircraft is on the ground is a:
The correct answer is C
A. servo tab.
spring tab. References
B. anti-balance tab. C. spring tab. D. balance tab.
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136. JAAExam.com/ATPL Question ID: 933
Answer C is correct.
Speed brakes are a device used on large transport category aircraft:
The correct answer is C
A. for speed reduction after landing. B. and are an old version of anti block system. C. to increase drag in order to maintain a steeper gradient of descent.
to increase drag in order to maintain a steeper gradient of descent. References
D. used at high speeds for turning when a yaw damper is not installed.
137. JAAExam.com/ATPL Question ID: 1220
Answer C is correct.
An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is:
The correct answer is C less influence on longitudinal control of thrust changes.
A. a wing which is less sensitive to flutter. B. easier maintenance of the engines.
References
C. less influence on longitudinal control of thrust changes. D. lighter wing construction.
138. JAAExam.com/ATPL Question ID: 1184
Answer A is correct.
Which of the following statements is correct?
The correct answer is A
I. II.
When the critical engine fails during takeoff the speed VMCL can be limiting. The speed VMCL is always limited by
I is incorrect, II is incorrect.
maximum rudder deflection.
References
A. I is incorrect, II is incorrect. B. I is correct, II is correct. C. I is correct, II is incorrect. D. I is incorrect, II is correct.
139. JAAExam.com/ATPL Question ID: 704
Answer D is correct.
How does aerodynamic drag vary when airspeed is doubled? By a factor of:
The correct answer is D 4
A. 2 References
B. 1 C. 16 D. 4
140. JAAExam.com/ATPL Question ID: 782
Answer C is correct.
How are the wing stalling angle and the lift coefficient affected when altitude increases and EAS is held constant?
The correct answer is C
A. The lift coefficient remains constant and the wing stalling angle will reduce.
The lift coefficient and the wing stalling angle both remain constant. References
B. The lift coefficient and the wing stalling angle both decrease. C. The lift coefficient and the wing stalling angle both remain constant. D. The lift coefficient decreases and the stalling angle remains the same.
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141. JAAExam.com/ATPL Question ID: 918
Answer A is correct.
Slats:
The correct answer is A
A. increases Clmax. B. decrease the minimum angle of attack. C. both A and B.
increases Clmax. References
D. neither A or B.
142. JAAExam.com/ATPL Question ID: 888
Answer A is correct.
Flaps are used in order to:
The correct answer is A
A. decrease stalling speed and reduce max angle of attack thereby achieving a more nose
decrease stalling speed and reduce max angle of attack thereby achieving a more nose down attitude near and at stalling speed.
down attitude near and at stalling speed.
References
B. increase max lift coefficient by increasing max angle of attack. C. increase max L/D. D. reducing drag.
143. JAAExam.com/ATPL Question ID: 862
Answer D is correct.
A slotted flap will increase the CLmax by:
The correct answer is D
A. increasing the critical angle of attack. B. decreasing the skin friction. C. increasing only the camber of the aerofoil.
increasing the camber of the aerofoil and improving the boundary layer. References
D. increasing the camber of the aerofoil and improving the boundary layer.
144. JAAExam.com/ATPL Question ID: 690
Answer C is correct.
Low speed pitch up is caused by the:
The correct answer is C
A. wing tip vortex. B. Mach trim system. C. span wise flow on a swept back wing.
span wise flow on a swept back wing. References
D. span wise flow on a swept forward wing.
145. JAAExam.com/ATPL Question ID: 545
Answer B is correct.
As it applies to airfoils. which statement is in agreement with Bernoullis Principle?
The correct answer is B
A. The speed of a fluid increases at points where the static pressure of the fluid increases. B. The static pressure of a fluid decreases at points where the speed of the fluid increases.
The static pressure of a fluid decreases at points where the speed of the fluid increases. References
C. The static pressure of a fluid increases at points where the speed of the fluid increases. D. The static pressure of a fluid decreases at points where the speed of the fluid decreases.
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146. JAAExam.com/ATPL Question ID: 468
Answer A is correct.
Which of the following statements, about a venturi in a sub-sonic airflow are correct?
The correct answer is A 1 is incorrect and 2 is correct.
1.
the dynamic pressure in the undisturbed flow and in the throat are equal.
2.
the total pressure in the undisturbed flow
and in the throat are equal.
References
A. 1 is incorrect and 2 is correct. B. 1 and 2 are correct. C. 1 is correct and 2 is incorrect. D. 1 and 2 are incorrect.
147. JAAExam.com/ATPL Question ID: 1144
Answer C is correct.
An aeroplane that has positive static stability:
The correct answer is C
A. is never dynamically stable. B. is always dynamically stable. C. can be dynamically stable, neutral or unstable.
can be dynamically stable, neutral or unstable. References
D. is always dynamically unstable.
148. JAAExam.com/ATPL Question ID: 454
Answer C is correct.
Under what condition is indicated altitude the same as true altitude?
The correct answer is C At sea level in standard conditions (ISA).
A. Never. B. If the altimeter has no mechanical error.
References
C. At sea level in standard conditions (ISA). D. When at 18,000 feet MSL with the altimeter set at 29.92.
149. JAAExam.com/ATPL Question ID: 1008
Answer A is correct.
Which kind of flow separation occurs at the smallest angle of attack?
The correct answer is A shock stall.
A. shock stall. B. high-speed stall.
References
C. low-speed stall. D. deep stall.
150. JAAExam.com/ATPL Question ID: 715
Answer B is correct.
Balancing of the weight component along the flight path in a glide is achieved by:
The correct answer is B lift.
A. thrust and drag. B. lift. C. thrust. D. drag.
References
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151. JAAExam.com/ATPL Question ID: 736
Answer B is correct.
Refer to Figure: 081-06
The correct answer is B
(Refer to figure 081-06) The diagram shows the parameter X versus TAS. If a horizontal flight is considered the axis X shows:
the induced drag. References
A. the total drag. B. the induced drag. C. the lift force. D. the parasite drag.
152. JAAExam.com/ATPL Question ID: 661
Answer B is correct.
Which of the following wing planform produces the lowest induced drag? (all other relevant factors constant)
The correct answer is B
A. Rectangular.
Elliptical. References
B. Elliptical. C. Tapered. D. Circular.
153. JAAExam.com/ATPL Question ID: 700
Answer D is correct.
The greatest vortex strength occurs when the generating aircraft is:
The correct answer is D heavy, clean, and slow.
A. dirty. B. light, dirty, and fast.
References
C. heavy, dirty, and fast. D. heavy, clean, and slow.
154. JAAExam.com/ATPL Question ID: 839
Answer D is correct.
Entering the stall the centre of pressure of a straight (1) wing and of a strongly swept back wing (2) will:
The correct answer is D (1) move aft, (2) move forward.
A. (1) move aft, (2) not move. B. (1) move aft, (2) move aft.
References
C. (1) not move (2) move forward. D. (1) move aft, (2) move forward.
155. JAAExam.com/ATPL Question ID: 1281 When a large modern aircraft employs a variable
Answer B is correct.
incidence tailplane, trim changes are made by: The correct answer is B A. adjusting the trim tab on the trailing edge of the elevator.
changing the angle of the entire tailplane.
B. changing the angle of the entire tailplane. C. varying the spring bias trimming system.
References
D. adjusting the Q feel unit.
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156. JAAExam.com/ATPL Question ID: 730
Answer C is correct.
Refer to Figure: 081-04
The correct answer is C
(Refer to figure 081-04) Which line represents the total drag line of an aeroplane?
Line c. References
A. Line b. B. Line a. C. Line c. D. Line d.
157. JAAExam.com/ATPL Question ID: 1203
Answer C is correct.
When the control column is moved forward and to the right:
The correct answer is C
A. the elevator goes down, the starboard aileron moves down and the port aileron moves up. B. the elevator goes up, the starboard aileron moves up and the port aileron moves down.
the elevator goes down, the starboard aileron moves up and the port aileron moves down. References
C. the elevator goes down, the starboard aileron moves up and the port aileron moves down. D. the elevator goes up, the starboard aileron moves down and the port aileron moves up.
158. JAAExam.com/ATPL Question ID: 1163
Answer A is correct.
What happens to lateral stability when flaps are extended?
The correct answer is A Lateral stability is decreased.
A. Lateral stability is decreased. B. Lateral stability is increased as lift is increased. C. Lateral stability is unaffected, as the wings are symmetrical. D. Lateral stability is increased as the centre of pressure moves inboard.
References
159. JAAExam.com/ATPL Question ID: 1336
Answer D is correct.
An aircraft in straight and level flight has a CL of 0.35, and a 1s increase in angle of attack would increase the CL by 0.079. If a vertical gust increased angle of attack from the 1g value by 2s, what load factor would result?
The correct answer is D 1.45 References
A. 0.45 B. 5.08 C. 4.43 D. 1.45
160. JAAExam.com/ATPL Question ID: 1224
Answer A is correct.
One method to compensate adverse yaw is a:
The correct answer is A
A. differential aileron. B. balance tab. C. antibalance tab.
differential aileron. References
D. balance panel.
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161. JAAExam.com/ATPL Question ID: 719
Answer B is correct.
Two identical aircraft of the same weight fly at two different altitudes (in straight and level flight and the same angle of attack). All other important factors remaining constant, assuming no compressibility and ISA conditions, what is the TAS of each:
The correct answer is B Greater in the higher aircraft. References
A. The same. B. Greater in the higher aircraft. C. Greater in the lower aircraft. D. Altitude has no effect on TAS.
162. JAAExam.com/ATPL Question ID: 1443
Answer D is correct.
A propeller rotating clockwise as seen from the rear tends to rotate the aircraft to the:
The correct answer is D
A. right around the vertical axis, and to the right around the longitudinal axis. B. right around the vertical axis, and to the left around the longitudinal axis. C. left around the vertical axis, and to the right around the longitudinal axis. D. left around the vertical axis, and to the left around the longitudinal axis.
left around the vertical axis, and to the left around the longitudinal axis. References
163. JAAExam.com/ATPL Question ID: 637
Answer A is correct.
Wing tip vortices have the highest intensity during:
The correct answer is A
A. take off. B. cruise. C. high speed.
take off. References
D. turns.
164. JAAExam.com/ATPL Question ID: 1106
Answer B is correct.
Moving the C of G of an aircraft aft in flight will:
The correct answer is B
A. increase the angle of attack. B. reduce longitudinal stability. C. increase longitudinal stability.
reduce longitudinal stability. References
D. have no effect on longitudinal stability.
165. JAAExam.com/ATPL Question ID: 1566
Answer C is correct.
Refer to Figure: 081-07
The correct answer is C
(Refer to figure 081-07) Which point in the diagram gives the best glide condition?
Point B. References
A. Point C. B. Point A. C. Point B. D. Point D.
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166. JAAExam.com/ATPL Question ID: 1254
Answer A is correct.
Adverse aileron yaw may be reduced by the employment of differential ailerons. What is the principle of differential aileron operation?
The correct answer is A
A. The up going aileron on the down going wing moves through a greater angle of deflection than the down going aileron. B. The down going aileron on the down going wing moves through a greater angle of deflection than the up going aileron on the up going wing. C. The down going aileron on the up going wing moves through a greater angle of deflection than the up going aileron. D. Both the up and down going ailerons move through the same a angle of deflection,
The up going aileron on the down going wing moves through a greater angle of deflection than the down going aileron. References
however the up going aileron produces greater profile drag than the down going aileron.
167. JAAExam.com/ATPL Question ID: 558
Answer A is correct.
Angle of attack is the angle between:
The correct answer is A
A. undisturbed airflow and chord line. B. undisturbed airflow and mean camber line. C. local airflow and chord line.
undisturbed airflow and chord line. References
D. local airflow and mean camber line.
168. JAAExam.com/ATPL Question ID: 1116
Answer C is correct.
If an aircraft has static longitudinal instability, it:
The correct answer is C
A. will be dynamically stable.
will be dynamically unstable.
B. may or may not be dynamically stable, depending on momentum and damping factors.
References
C. will be dynamically unstable. D. will be dynamically stable only at low speed.
169. JAAExam.com/ATPL Question ID: 1065
Answer D is correct.
If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will:
The correct answer is D decrease.
A. decrease and beyond a certain Mach number start increasing again.
References
B. increase. C. stay constant. D. decrease.
170. JAAExam.com/ATPL Question ID: 482
Answer B is correct.
Which of the following wing planform gives the highest local lift coefficient at the wing root?
The correct answer is B Rectangular.
A. Elliptical. B. Rectangular.
References
C. Positive angle of sweep. D. Tapered.
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171. JAAExam.com/ATPL Question ID: 1085
Answer A is correct.
In a twin-engined jet powered aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero?
The correct answer is A
A. Down.
Down. References
B. Up. C. No elevator movement will required because the thrust line of the engines remains unchanged. D. It depends on the position of the centre of gravity.
172. JAAExam.com/ATPL Question ID: 964
Answer A is correct.
A mach trim system operates:
The correct answer is A
A. at high Mach number. B. at all Mach numbers. C. at low Mach numbers.
at high Mach number. References
D. above the critical Mach number.
173. JAAExam.com/ATPL Question ID: 1117
Answer A is correct.
When the aircraft CG is on the aft limit, it is:
The correct answer is A
A. in front of the neutral point. B. above the neutral point. C. behind the neutral point.
in front of the neutral point. References
D. on the neutral point.
174. JAAExam.com/ATPL Question ID: 1164
Answer D is correct.
Which of the following statements about dihedral is correct?
The correct answer is D
A. Dihedral is necessary for the execution of slip-free turns. B. Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane.
The effective dihedral of an aeroplane component means the contribution of that component to the static lateral stability. References
C. Dihedral contributes to dynamic but not to static lateral stability. D. The effective dihedral of an aeroplane component means the contribution of that component to the static lateral stability.
175. JAAExam.com/ATPL Question ID: 682
Answer C is correct.
An aeroplane accelerates from 80 kt to 160 kt at a load factor equal to 1. The induced drag coefficient (i) and the induced drag (ii) alter with the following factors: A. (i) 1/2; (ii) 1/16
The correct answer is C (i) 1/16 (ii) 1/4 References
B. (i) 1; (ii) 1/2 C. (i) 1/16 (ii) 1/4 D. (i) 1/4 (ii) 2
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176. JAAExam.com/ATPL Question ID: 703
Answer C is correct.
Extending flight spoilers (air brake) during flight:
The correct answer is C
A. has no effect on minimum drag speed (VDmin).
reduces minimum drag speed (Vdmin).
B. increases minimum drag speed (VDmin).
References
C. reduces minimum drag speed (Vdmin). D. is never allowed for structural reasons.
177. JAAExam.com/ATPL Question ID: 934
Answer C is correct.
Why are vortex generators often fitted on aircraft with straight wings?
The correct answer is C To delay boundary layer separation.
A. To reduce span wise airflow towards the wing tips on the extrados.
References
B. To reduce span wise airflow towards the wing root on the intrados. C. To delay boundary layer separation. D. To reduce induced drag.
178. JAAExam.com/ATPL Question ID: 748
Answer C is correct.
What is the effect on induced drag on entering the ground effect?
The correct answer is C Induced drag decreases.
A. Induce drag increases, but profile drag decreases.
References
B. Induced drag remains the same. C. Induced drag decreases. D. Induced drag increases.
179. JAAExam.com/ATPL Question ID: 1449
Answer A is correct.
Propeller efficiency is best described as:
The correct answer is A
A. thrust HP to shaft HP. B. thrust HP to overall power. C. brake HP to maximum power.
thrust HP to shaft HP. References
D. thermal HP to shaft HP.
180. JAAExam.com/ATPL Question ID: 1406
Answer B is correct.
The purpose of the CSU oil booster pump of a variable pitch propeller is to:
The correct answer is B
A. lubricate the constant speed unit.
increase the engine oil pressure for propeller operation.
B. increase the engine oil pressure for propeller operation.
References
C. increase engine oil pressure for propeller feathering. D. unfeather the propeller.
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181. JAAExam.com/ATPL Question ID: 1437
Answer C is correct.
For a fixed-pitch propeller designed for cruise, the angle of attack of each blade, measured at the reference section:
The correct answer is C
A. is lower in ground run than in flight (with identical engine RPM).
is optimum when the aircraft is in a stabilized cruising flight. References
B. decreases when the aircraft speed decreases (with identical engine RPM). C. is optimum when the aircraft is in a stabilized cruising flight. D. is always positive during idling descent.
182. JAAExam.com/ATPL Question ID: 595
Answer B is correct.
The relative thickness of an aerofoil is expressed in:
The correct answer is B
A. degrees cross section tail angle. B. % chord. C. camber.
% chord. References
D. meters.
183. JAAExam.com/ATPL Question ID: 621
Answer B is correct.
The vane of a stall warning system with a flapper switch is activated by the change of the:
The correct answer is B stagnation point.
A. point of lowest pressure. B. stagnation point.
References
C. centre of pressure. D. centre of gravity.
184. JAAExam.com/ATPL Question ID: 629
Answer C is correct.
Lift is generated when:
The correct answer is C
A. an aerofoil is placed in a high velocity air stream.
a certain mass of air is accelerated downwards.
B. the shape of the aerofoil is slightly cambered.
References
C. a certain mass of air is accelerated downwards. D. a certain mass of air is retarded.
185. JAAExam.com/ATPL Question ID: 1497
Answer B is correct.
An aircraft in flight is affected by loads. These may be classified as:
The correct answer is B compressive, tensile, shear and torsional.
A. tensile, shear, twisting and stretching. B. compressive, tensile, shear and torsional.
References
C. thrust, drag, lift and weight. D. compressive, bending, shear and torsional.
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186. JAAExam.com/ATPL Question ID: 1300
Answer D is correct.
VMO:
The correct answer is D
A. should be chosen in between VC and VD.
should be not greater than VC.
B. is equal to the design speed for maximum gust intensity.
References
C. is the calibrated airspeed at which MMO is reached at 35.000 ft. D. should be not greater than VC.
187. JAAExam.com/ATPL Question ID: 564
Answer D is correct.
A laminar boundary layer is a layer, in which:
The correct answer is D
A. the vortices, are weak. B. the velocity is constant. C. the temperature varies constantly.
no velocity components exist normal to the surface. References
D. no velocity components exist normal to the surface.
188. JAAExam.com/ATPL Question ID: 1373
Answer D is correct.
Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?
The correct answer is D Yes slightly.
A. Yes, but only if the pitch is full-fine. B. Yes strongly.
References
C. No. D. Yes slightly.
189. JAAExam.com/ATPL Question ID: 1400
Answer A is correct.
Which of the following statements about a constant speed propeller is correct?
The correct answer is A The blade angle increases with increasing speed.
A. The blade angle increases with increasing speed.
References
B. The propeller system keeps the aeroplane speed constant. C. The RPM decreases with increasing aeroplane speed. D. The selected RPM is kept constant by the manifold pressure.
190. JAAExam.com/ATPL Question ID: 589
Answer C is correct.
On an airfoil the centre of pressure will be most forward:
The correct answer is C just below the stalling angle.
A. at the optimum angle. B. at the stalling angle.
References
C. just below the stalling angle. D. just above the stalling angle.
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191. JAAExam.com/ATPL Question ID: 640
Answer B is correct.
Aerodynamic forces and moments exerted on a body moving through a fluid stem from two sources:
The correct answer is B pressure distribution and shear stress distribution.
A. bending force and torsion moment. B. pressure distribution and shear stress distribution.
References
C. pressure distribution and airstream velocity. D. water and wind.
192. JAAExam.com/ATPL Question ID: 1466
Answer C is correct.
Asymmetric propeller blade effect is mainly induced
The correct answer is C
by:
the inclination of the propeller axis to the relative airflow.
A. large angles of yaw. B. large angles of climb.
References
C. the inclination of the propeller axis to the relative airflow. D. high speed.
193. JAAExam.com/ATPL Question ID: 571
Answer A is correct.
What happens when the CG is on the forward limit?
The correct answer is A
A. Vs increases, stall angle remains constant. B. Vs increases, stall angle increases. C. Vs decreases, stall angle remains constant.
Vs increases, stall angle remains constant. References
D. Vs decreases, stall angle decreases.
194. JAAExam.com/ATPL Question ID: 1023
Answer A is correct.
What is the effect of a decreasing aeroplane weight on Mcrit at n=1, when flying at constant IAS? The value of Mcrit:
The correct answer is A
A. increases.
increases. References
B. remains constant. C. is independent of the angle of attack. D. decreases.
195. JAAExam.com/ATPL Question ID: 1499
Answer A is correct.
Which statement is correct at the speed for minimum drag (subsonic)?
The correct answer is A The gliding angle is minimum.
A. The gliding angle is minimum. B. The CL/CD ratio is minimum.
References
C. Induced drag is greater than the parasite drag. D. Propeller aeroplanes fly at that speed at max. endurance.
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196. JAAExam.com/ATPL Question ID: 1474
Answer A is correct.
The theoretical best range speed for a jet aircraft at low level is:
The correct answer is A approximately 1.32 times the minimum drag speed.
A. approximately 1.32 times the minimum drag speed.
References
B. the minimum drag speed. C. the same as for a propeller aircraft. D. the minimum power speed.
197. JAAExam.com/ATPL Question ID: 1255
Answer B is correct.
Stick forces, provided by an elevator feel system, depend on:
The correct answer is B elevator deflection, dynamic pressure.
A. stabilizer position, static pressure. B. elevator deflection, dynamic pressure.
References
C. elevator deflection, static pressure. D. stabilizer position, total pressure.
198. JAAExam.com/ATPL Question ID: 780
Answer D is correct.
On a swept wing aeroplane at low airspeed, the pitch up phenomenon:
The correct answer is D is caused by wingtip stall.
A. is caused by boundary layer fences mounted on the wings.
References
B. never occurs, since a swept wing is a remedy to pitch up. C. is caused by extension of trailing edge lift augmentation devices. D. is caused by wingtip stall.
199. JAAExam.com/ATPL Question ID: 858
Answer A is correct.
The sensor of a stall warning system can be activated by a change in the location of the:
The correct answer is A stagnation point.
A. stagnation point. B. centre of lift.
References
C. transition region. D. centre of gravity.
200. JAAExam.com/ATPL Question ID: 1263
Answer C is correct.
The following is true concerning a balance tab. It is:
The correct answer is C
A. used to increase feel. B. a form of mass balance. C. a form of aerodynamic balance.
a form of aerodynamic balance. References
D. only operating at high speed.
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201. JAAExam.com/ATPL Question ID: 1530
Answer C is correct.
The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
The correct answer is C shift forward.
A. shift aft. B. shift in span wise direction.
References
C. shift forward. D. not shift.
202. JAAExam.com/ATPL Question ID: 1293
Answer B is correct.
An aircraft is equipped with an all flying tailplane which has a combined antibalance and trimming tab. The top of the trim wheel is moved forward. Which of the following statements is most correct?
The correct answer is B
A. The tab moves up, so that less effort is required when the pilot attempts to move the control column to the rear.
The tab moves up, so that more effect is required when the pilot attempts to move the control column to the rear. References
B. The tab moves up, so that more effect is required when the pilot attempts to move the control column to the rear. C. The tab moves down, so that less effort is requires when the pilot attempts to move the control column to the rear. D. The tab moves down, so that more effort is required when the pilot attempts to move the control column to the rear.
203. JAAExam.com/ATPL Question ID: 1346
Answer A is correct.
The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed:
The correct answer is A VD
A. VD B. VC
References
C. Vflutter D. VMO
204. JAAExam.com/ATPL Question ID: 1248
Answer A is correct.
Dutch roll will occur when the dihedral effect is ... when compared to ... directional...
The correct answer is A large, static, stability.
A. large, static, stability. B. small, static, stability.
References
C. large, dynamic, stability. D. small, dynamic, stability.
205. JAAExam.com/ATPL Question ID: 530
Answer A is correct.
Which of the following is the correct description of the method for measuring the dihedral angle? References A. The angle between the wing plane and the horizontal. B. The angle between a line which passes through the 25% wing chord and the horizontal axis. C. The angle between the 25% chord line and the horizontal axis. D. The angle between 25% chord and the lateral axis.
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206. JAAExam.com/ATPL Question ID: 940
Answer D is correct.
A laminar boundary layer is... and has... drag than a turbulent layer:
The correct answer is D thin; less
A. thick; more B. thick; less
References
C. thin; more D. thin; less
207. JAAExam.com/ATPL Question ID: 1410
Answer B is correct.
Given two identical aeroplanes with wing mounted engines, one fitted with jet engines and the other with counter rotating propellers, what happens following an engine failure?
The correct answer is B
A. The same yaw tendency for both aeroplanes regardless of left or right engine failure.
More roll tendency for the propeller aeroplane. References
B. More roll tendency for the propeller aeroplane. C. Less roll tendency for the propeller aeroplane. D. The same roll tendency for both aeroplanes.
208. JAAExam.com/ATPL Question ID: 770
Answer B is correct.
The centre of pressure (c.o.p) is in its most forward position:
The correct answer is B
A. the centre of pressure on an aerofoil has no most forward position. B. when the angle of attack is equal to the stalling angle of attack. C. when the angle of attack exceeds the stalling angle of attack D. when the angle of attack is smaller than the stalling angle of attack.
when the angle of attack is equal to the stalling angle of attack. References
209. JAAExam.com/ATPL Question ID: 1388
Answer C is correct.
Mechanically driven pump, contained within a propeller constant speed unit, is used to:
The correct answer is C
A. feather the propeller, and is called the feathering pump. B. boost the feathering pump oil pressure, and is called the booster pump.
increase engine oil pressure for propeller operation and is called the booster pump. References
C. increase engine oil pressure for propeller operation and is called the booster pump. D. feather the propeller and is called the emergency pump.
210. JAAExam.com/ATPL Question ID: 1488
Answer A is correct.
During cruise, the weight of an aircraft reduces by 19%. Therefore the manoeuvring speed will:
The correct answer is A decrease by 10%.
A. decrease by 10%. B. increase by 10%.
References
C. increase by 19%. D. decrease by 19%.
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211. JAAExam.com/ATPL Question ID: 610
Answer D is correct.
When an aircraft pitches up, the angle of attack of the tailplane will:
The correct answer is D increase.
A. remain the same. B. depend solely upon the rigger´ s angle of incidence.
References
C. decrease. D. increase.
212. JAAExam.com/ATPL Question ID: 650
Answer A is correct.
In order to remain in level balanced flight:
The correct answer is A
A. the wing lift must be greater than weight, if the tailplane is giving a download for balance.
the wing lift must be greater than weight, if the tailplane is giving a download for balance.
B. the wing lift has to be less than weight, if the tailplane is giving a download for balance.
References
C. the wing lift must be equal to weight. D. the wing lift must be less than weight at all times.
213. JAAExam.com/ATPL Question ID: 1290
Answer B is correct.
How does the exterior view of an aeroplane change, when the trim is used during a speed decrease? A. The elevator is deflected further downwards by means of an upwards deflected trim tab. B. The elevator is deflected further upwards by means of a downwards deflected trim tab.
The correct answer is B The elevator is deflected further upwards by means of a downwards deflected trim tab. References
C. The elevator is deflected further downwards by mean's of a trimmable horizontal stabiliser. D. Nothing changes in the exterior view.
214. JAAExam.com/ATPL Question ID: 1212
Answer C is correct.
A yaw damper is a system which:
The correct answer is C
A. increase lateral stability. B. decrease lateral stability. C. increase directional stability
increase directional stability References
D. reduce the stall speed
215. JAAExam.com/ATPL Question ID: 827
Answer C is correct.
With the centre of gravity on the forward limit, the stalling speed would be:
The correct answer is C
A. independent of the centre of gravity position.
higher than with the centre of gravity on the aft limit.
B. lower than with the centre of gravity on the aft limit.
References
C. higher than with the centre of gravity on the aft limit. D. the same as with the centre of gravity on the aft limit.
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216. JAAExam.com/ATPL Question ID: 1027
Answer B is correct.
Which of the following (1) aerofoil and (2) angles of attack will produce the lowest Mcrit values?
The correct answer is B (1) thick and (2) large.
A. (1) thick and (2) small. B. (1) thick and (2) large.
References
C. (1) thin and (2) large. D. (1) thin and (2) small.
217. JAAExam.com/ATPL Question ID: 1371 The twisting of a propeller blade from root to tip has
Answer A is correct.
been made to: The correct answer is A A. provide a constant angle of attack from root to tip.
provide a constant angle of attack from root to tip.
B. to provide its greatest thrust toward the blade root.
References
C. to ensure its optimum thrust is always achieved at take off. D. to prevent excessive stress at the blade tip at high RPM.
218. JAAExam.com/ATPL Question ID: 714
Answer C is correct.
Induced drag is caused by:
The correct answer is C
A. increased pressure at the leading edge stagnation point.
wing tip vortices and downwash.
B. wing mounted fuel tanks.
References
C. wing tip vortices and downwash. D. winglets and washout.
219. JAAExam.com/ATPL Question ID: 1109
Answer D is correct.
Why do some wings have dihedral?
The correct answer is D
A. To increase longitudinal stability. B. To reduce directional stability. C. To increase directional stability.
To increase lateral stability. References
D. To increase lateral stability.
220. JAAExam.com/ATPL Question ID: 556
Answer A is correct.
If you want to maintain a constant TAS during a climb, you should during the climb:
The correct answer is A reduce to a lower IAS.
A. reduce to a lower IAS. B. maintain a stable IAS.
References
C. increase the IAS. D. increase A.o.A.
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221. JAAExam.com/ATPL Question ID: 1014
Answer D is correct.
When the air is passing through a shock wave the density will:
The correct answer is D increase.
A. decrease and beyond a certain Mach number start increasing again.
References
B. decrease. C. stay constant. D. increase.
222. JAAExam.com/ATPL Question ID: 1092
Answer C is correct.
Dynamic longitudinal stability requires:
The correct answer is C
A. an effective elevator. B. a small CG range. C. positive static longitudinal stability.
positive static longitudinal stability. References
D. a variable incidence (trimming) tailplane.
223. JAAExam.com/ATPL Question ID: 1469
Answer C is correct.
What is the relationship between lift and weight when an airplane is in an accelerated climbing flight?
The correct answer is C Lift exceeds weight.
A. Lift is less than weight. B. Lift equals weight.
References
C. Lift exceeds weight. D. Depends mainly on the thrust setting.
224. JAAExam.com/ATPL Question ID: 793
Answer A is correct.
The stall speed in a 60° banked turn increases by the following factor:
The correct answer is A 1.41
A. 1.41 B. 1.07
References
C. 1.30 D. 2.00
225. JAAExam.com/ATPL Question ID: 1126
Answer B is correct.
A C.G location beyond the aft limit leads to:
The correct answer is B
A. a too high pulling stick force during rotation in the take off.
an unacceptable low value of the manoeuvre stability (stick force per g, Fe/g).
B. an unacceptable low value of the manoeuvre stability (stick force per g, Fe/g).
References
C. an increasing static longitudinal stability. D. a better recovery performance in the spin.
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226. JAAExam.com/ATPL Question ID: 904
Answer A is correct.
Vortex generators mounted on the upper wing surface will:
The correct answer is A decrease the shock wave induced separation.
A. decrease the shock wave induced separation. B. decrease the interference drag of the trailing edge flaps.
References
C. decrease the stalling speed by increase of the tangential velocity of the swept wing. D. increase the effectiveness of the spoiler due to increase in parasite drag.
227. JAAExam.com/ATPL Question ID: 1564
Answer A is correct.
Refer to Figure: 081-11
The correct answer is A
(Refer to figure 081-11) In the diagram below, an aircraft polar diagram of CL against CD, point B is:
best lift/drag ratio angle of attack. References
A. best lift/drag ratio angle of attack. B. angle of attack for minimum power required in level flight. C. minimum drag point. D. zero lift angle of attack.
228. JAAExam.com/ATPL Question ID: 1314
Answer C is correct.
The maximum load factor that can be imposed on an airplane depends mainly on:
The correct answer is C The speed of the airplane.
A. All of the above. B. The position of the centre of gravity.
References
C. The speed of the airplane. D. The operators decision.
229. JAAExam.com/ATPL Question ID: 1332
Answer D is correct.
Which has the effect of increasing load factor? (all other relevant factors being constant).
The correct answer is D Vertical gusts.
A. Rearward CG location. B. Increased aeroplane mass.
References
C. Increased air density. D. Vertical gusts.
230. JAAExam.com/ATPL Question ID: 1475 Flying for maximum range in a jet aircraft, will you
Answer C is correct.
get a higher specific air range by increasing altitude if:
The correct answer is C
A. you are below the tropopause, at MCDR and above VIMD.
you are below or above the tropopause, at MCDR and above VIMD.
B. you are above the tropopause, at MCDR and at VIMD.
References
C. you are below or above the tropopause, at MCDR and above VIMD. D. you are above the tropopause, at MCDR and above VIMD.
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231. JAAExam.com/ATPL Question ID: 1101
Answer C is correct.
If an airplane has poor longitudinal stability in flight, what can be done to increase the stability?
The correct answer is C Increase stabiliser surface area.
A. Reduce in keel surface area. B. Install a yaw damper.
References
C. Increase stabiliser surface area. D. Increase elevator range of movement.
232. JAAExam.com/ATPL Question ID: 1102
Answer B is correct.
The longitudinal stability of an airplane is mainly dependent on the size and/or position of:
The correct answer is B the centre of gravity position.
A. the Krueger flaps. B. the centre of gravity position.
References
C. the rudder. D. the fuselage.
233. JAAExam.com/ATPL Question ID: 520
Answer B is correct.
Load factor is the actual lift supported by the wings at any given time:
The correct answer is B divided by the total weight of the aircraft.
A. divided by the surface area of the wing. B. divided by the total weight of the aircraft.
References
C. subtracted from the aircraft’ s total weight. D. divided by the aircrafts empty weight
234. JAAExam.com/ATPL Question ID: 667
Answer B is correct.
Induced drag at constant IAS is affected by:
The correct answer is B
A. engine thrust.
aeroplane weight.
B. aeroplane weight.
References
C. aeroplane wing location. D. angle between wing chord and fuselage centre line.
235. JAAExam.com/ATPL Question ID: 843
Answer A is correct.
A boundary layer fence on a swept wing will:
The correct answer is A
A. improve the low speed characteristics. B. improve the high speed characteristics. C. increase the critical Mach Number.
improve the low speed characteristics. References
D. improve the lift coefficient of the trailing edge flap.
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236. JAAExam.com/ATPL Question ID: 935
Answer C is correct.
The boundary layer of a body in a moving airstream is:
The correct answer is C
A. a thin layer of air over the surface where the air is stationary. B. a layer of separated flow where the air is turbulent.
a layer of air over the surface where the airspeed is changing from free stream velocity to zero velocity. References
C. a layer of air over the surface where the airspeed is changing from free stream velocity to zero velocity. D. a layer of air which is moving at free stream speed.
237. JAAExam.com/ATPL Question ID: 517
Answer B is correct.
Lift and drag on an aerofoil are vertical respectively parallel to the:
The correct answer is B relative wind/airflow.
A. horizon. B. relative wind/airflow.
References
C. chord line. D. longitudinal axis.
238. JAAExam.com/ATPL Question ID: 1094
Answer D is correct.
A Machtrimmer:
The correct answer is D
A. has no effect on the shape of the elevator position versus speed (IAS) curve for a fully hydraulic controlled aeroplane.
corrects insufficient stick force stability at high Mach Numbers.
B. increases the stick force per g at high Mach
References
Numbers. C. is necessary for compensation of the autopilot at high Mach Numbers. D. corrects insufficient stick force stability at high Mach Numbers.
239. JAAExam.com/ATPL Question ID: 1397
Answer C is correct.
A propeller mounted forward of the engine is termed:
The correct answer is C a tractor propeller.
A. a pusher propeller. B. a paddle propeller.
References
C. a tractor propeller. D. a hydropneumatic propeller.
240. JAAExam.com/ATPL Question ID: 1103
Answer D is correct.
The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is:
The correct answer is D 225 N. References
A. 150 N. B. 375 N. C. 450 N. D. 225 N.
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241. JAAExam.com/ATPL Question ID: 631
Answer D is correct.
If the camber of an aerofoil is increased:
The correct answer is D
A. the coefficient of lift will increase for a given angle of attack.
all of the above.
B. the stalling angle will decrease.
References
C. the critical Mach-number will decrease. D. all of the above.
242. JAAExam.com/ATPL Question ID: 808
Answer C is correct.
What is the percentage increase in stall speed in a 45 bank turn
The correct answer is C 19%
A. 45% B. 41% C. 19%
References
D. 10%
243. JAAExam.com/ATPL Question ID: 1241
Answer A is correct.
In an aircraft fitted with spoilers for lateral control, and not deployed as speed brakes, a roll to the right is initiated by:
The correct answer is A
A. right spoiler extended, left spoiler retracted.
right spoiler extended, left spoiler retracted. References
B. both spoilers extended. C. left spoiler extended, right spoiler retracted. D. right spoiler extended, but left spoiler extended more.
244. JAAExam.com/ATPL Question ID: 1139
Answer C is correct.
Positive static stability of an aeroplane means that once it has been displaced the:
The correct answer is C
A. tendency will be to move with an oscillating motion of decreasing amplitude. B. tendency will be to move with an oscillating motion of increasing amplitude.
initial tendency to move is towards its equilibrium position. References
C. initial tendency to move is towards its equilibrium position. D. initial tendency to move is away from its equilibrium position.
245. JAAExam.com/ATPL Question ID: 1324
Answer B is correct.
Aileron flutter is most likely to occur:
The correct answer is B
A. at low airspeed when the wing is rigid. B. at high airspeed when the wing is flexible. C. at high airspeed when the wing is rigid.
at high airspeed when the wing is flexible. References
D. at low airspeed when the wing is flexible.
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246. JAAExam.com/ATPL Question ID: 1297
Answer D is correct.
If the elevator trim tab is deflected up, the cockpit trim indicator presents:
The correct answer is D nose-down.
A. nose-left. B. neutral. C. nose-up. D. nose-down.
References
247. JAAExam.com/ATPL Question ID: 475
Answer A is correct.
The angle of attack of a wing profile is defined as the angle between:
The correct answer is A the undisturbed airflow and the chord line.
A. the undisturbed airflow and the chord line. B. the local airflow and the mean camber line.
References
C. the local airflow and the chord line. D. the undisturbed airflow and the mean camber line.
248. JAAExam.com/ATPL Question ID: 876
Answer D is correct.
An aeroplane has the following flap settings: 0° , 15° , 30° and 45° . Slats can be selected too. Which of the above selections will produce the greatest negative influence on the CL/CD ratio?
The correct answer is D
A. Flaps from 15° to 30° .
Flaps from 30° to 45° . References
B. The slats. C. Flaps from 0° to 15° . D. Flaps from 30° to 45° .
249. JAAExam.com/ATPL Question ID: 760
Answer D is correct.
Flap selection at constant IAS in straight and level flight will increase the:
The correct answer is D maximum lift coefficient (CLmax) and the drag.
A. lift coefficient and the drag. B. stall speed.
References
C. lift and the drag. D. maximum lift coefficient (CLmax) and the drag.
250. JAAExam.com/ATPL Question ID: 1510
Answer C is correct.
For a steady unaccelerated climb:
The correct answer is C
A. lift is greater than weight. B. lift is equal to weight. C. lift is less than weight.
lift is less than weight. References
D. lift is equal to drag.
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251. JAAExam.com/ATPL Question ID: 546
Answer B is correct.
Vectors:
The correct answer is B
A. have a direction only. B. have a magnitude and a direction. C. have a magnitude only.
have a magnitude and a direction. References
D. none of the above.
252. JAAExam.com/ATPL Question ID: 1305
Answer A is correct.
For an aeroplane with one fixed value of VA the following applies. VA is:
The correct answer is A
A. the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW. B. the maximum speed in smooth air.
the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW. References
C. the speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor. D. just another symbol for the rough air speed.
253. JAAExam.com/ATPL Question ID: 1118
Answer C is correct.
Which of the following statements about a Mach trimmer is correct?
The correct answer is C
A. A Mach trimmer reduces the stick force stability of a straight wing aeroplane to zero at high Mach numbers. B. A straight wing aeroplane always needs a Mach trimmer for flying at Mach numbers close to MMO.
A Mach trimmer corrects the change in stick force stability of a swept wing aeroplane above a certain Mach number. References
C. A Mach trimmer corrects the change in stick force stability of a swept wing aeroplane above a certain Mach number. D. The Mach trimmer corrects the natural tendency of a swept wing aeroplane to pitchup.
254. JAAExam.com/ATPL Question ID: 495
Answer C is correct.
Aspect ratio is defined as:
In aerodynamics, the aspect ratio of a wing is defined as the square of the wing span divided by the wing area
A. wing span / mean chord. B. wing span / mean camber.
References
C. span squared / wing area. D. mean chord / wing area.
255. JAAExam.com/ATPL Question ID: 1493
Answer B is correct.
Which forces produce the necessary normal
The correct answer is B
acceleration to make an aircraft turn? A. The horizontal component of weight.
The horizontal component of lift. References
B. The horizontal component of lift. C. The vertical component of lift. D. Centrifugal force.
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256. JAAExam.com/ATPL Question ID: 851
Answer C is correct.
The standard procedure for recovery from a stall in a light single engine aircraft is:
The correct answer is C
A. idle power; stick - roll neutral and forward.
maximum power; stick - roll neutral and forward, correct for bank with rudder.
B. maximum power; stick - roll neutral and forward, correct for bank with stick.
References
C. maximum power; stick - roll neutral and forward, correct for bank with rudder. D. idle power; stick neutral, wait for normal nose down tendency.
257. JAAExam.com/ATPL Question ID: 1299
Answer D is correct.
The reason for having a trim system on powered assisted flying controls is:
The correct answer is D enables the stick force to be reduced to zero.
A. enables the pilot to maintain control in case of hydraulic failure.
References
B. relieve stresses on the trim tab. C. relieve stresses on the hydraulic actuators. D. enables the stick force to be reduced to zero.
258. JAAExam.com/ATPL Question ID: 831
Answer C is correct.
A low wing loading (aircraft weight has been reduced):
The correct answer is C decreases stalling speed and landing speed.
A. increases stalling speed. B. increases take-off run, stalling speed and landing speed.
References
C. decreases stalling speed and landing speed. D. does not affect any of the above.
259. JAAExam.com/ATPL Question ID: 1359
Answer D is correct.
The output of a turboprop engine is usually indicated by?
The correct answer is D Torque.
A. Engine RPM as a percentage.
B. Propeller RPM.
References
C. SHP D. Torque.
260. JAAExam.com/ATPL Question ID: 1532
Answer C is correct.
The angle of climb of an aircraft is proportional to ... and ... as weight increases:
The correct answer is C excess thrust; decreases
A. excess power; decreases B. excess thrust; increases
References
C. excess thrust; decreases D. excess power; increases
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261. JAAExam.com/ATPL Question ID: 643
Answer A is correct.
When considering an angle of attack versus coefficient of lift graph for a cambered aerofoil, where does the lift curve intersect the vertical CL axis?
The correct answer is A
A. Above the origin.
Above the origin. References
B. Below the origin. C. At the point of origin. D. To the left of the origin.
262. JAAExam.com/ATPL Question ID: 1073
Answer C is correct.
If the total moments about an axis are not zero, what will be the result around that axis?
The correct answer is C Angular acceleration.
A. Equilibrium. B. Constant angular velocity.
References
C. Angular acceleration. D. Constant angular displacement.
263. JAAExam.com/ATPL Question ID: 1485
Answer A is correct.
At a true airspeed of 300kt and in a 45° bank level turn, the radius of turn would be... (assume a value of 10m/sec/sec for g).
The correct answer is A
A. 2387m B. 2765m C. 8000m D. 23780m
2387m References
264. JAAExam.com/ATPL Question ID: 1194
Answer B is correct.
When ice is present on the stabilizer, deflection of flaps may cause:
The correct answer is B the stabilizer to stall and a vertical dive.
A. the stabilizer to stall and a pitch up situation. B. the stabilizer to stall and a vertical dive.
References
C. both wings and stabilizer to stall. D. a roll movement due to directional instable.
265. JAAExam.com/ATPL Question ID: 626
Answer D is correct.
At zero angle of attack in flight, a symmetrical wing section will produce:
The correct answer is D zero lift with some drag.
A. some lift and drag. B. zero lift with some induced and profile drag.
References
C. zero lift and drag. D. zero lift with some drag.
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266. JAAExam.com/ATPL Question ID: 867
Answer D is correct.
An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is?
The correct answer is D
A. Wing roots: L.E. flaps Wing tips: no devices.
Wing roots: L.E. flaps Wing tips: slats. References
B. Wing roots: slats Wing tips: L.E. flaps. C. Wing roots: slats Wing tips: no devices. D. Wing roots: L.E. flaps Wing tips: slats.
267. JAAExam.com/ATPL Question ID: 1178
Answer B is correct.
When spinning to the left, which wing(s) are stalled?
The correct answer is B
A. Only the right wing is stalled. B. Both wings are stalled. C. Neither wing is stalled.
Both wings are stalled. References
D. Only the left wing is stalled.
268. JAAExam.com/ATPL Question ID: 1252
Answer B is correct.
An aircrafts tendency to Dutch roll may be reduced by:
The correct answer is B giving the wings an angle of anhedral.
A. reducing the size of the fin.
B. giving the wings an angle of anhedral.
References
C. sweeping the wings. D. giving the aircraft longitudinal dihedral.
269. JAAExam.com/ATPL Question ID: 929
Answer B is correct.
Upon extension of a spoiler on a wing:
The correct answer is B
A. only CL is decreased (CD remains unaffected).
CD is increased and CL is decreased.
B. CD is increased and CL is decreased.
References
C. both CL and CD are increased. D. CD is increased, while CL remains unaffected.
270. JAAExam.com/ATPL Question ID: 1538
Answer C is correct.
For an aircraft in level flight, if the wing centre of pressure is aft of the centre of gravity and there is no thrust- drag couple, the tailplane load must be:
The correct answer is C
A. directed upwards.
directed downwards. References
B. up or down depending on the position of the flight spoilers. C. directed downwards. D. zero at all times.
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271. JAAExam.com/ATPL Question ID: 1558
Answer A is correct.
The maximum glide range of an aircraft will depend on wind and:
The correct answer is A
A. the ratio to lift to drag which varies according to angle of attack. B. speed for minimum power required.
the ratio to lift to drag which varies according to angle of attack. References
C. CL MAX. D. minimum Lift / Drag ratio.
272. JAAExam.com/ATPL Question ID: 922
Answer B is correct.
Following the deployment of leading edge slats:
The correct answer is B
A. the boundary layer is re-energised and the peak pressure moves forward onto the slat. B. the boundary layer is re-energised and the peak pressure moves forward towards the wing leading edge. C. the boundary layer is de-energised and the peak pressure moves forward onto the slat.
the boundary layer is re-energised and the peak pressure moves forward towards the wing leading edge. References
D. the boundary layer is de-energised and the peak pressure moves forward towards the wing leading edge.
273. JAAExam.com/ATPL Question ID: 701
Answer B is correct.
Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant):
The correct answer is B
A. the drag is only affected by the ground speed.
the drag increases. References
B. the drag increases. C. this has no effect. D. the drag decreases.
274. JAAExam.com/ATPL Question ID: 788
Answer D is correct.
As the angle of attack of a wing is increased, the centre of pressure will reach its most forward position on the wing...
The correct answer is D
A. after stall recovery.
just before the wing stalls. References
B. at the optimum angle of attack. C. when the aircraft is stalling. D. just before the wing stalls.
275. JAAExam.com/ATPL Question ID: 1277
Answer B is correct.
When power assisted controls are used for pitch control, this:
The correct answer is B
A. makes trimming superfluous.
ensures that a part of the aerodynamic forces is still felt on the column.
B. ensures that a part of the aerodynamic forces is still felt on the column.
References
C. makes aerodynamic balancing of the control surfaces meaningless. D. can only function in combination with an elevator trim tab.
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276. JAAExam.com/ATPL Question ID: 886
Answer A is correct.
If the flaps are lowered but the airspeed is kept constant, to maintain level flight:
The correct answer is A the nose must be pitched down.
A. the nose must be pitched down. B. the nose must be pitched up. C. the altitude must be held constant.
References
D. spoilers must be deployed.
277. JAAExam.com/ATPL Question ID: 485
Answer A is correct.
What is the effect of deploying trailing edge flaps?
The correct answer is A
A. Increased minimum glide angle. B. Decreased minimum glide angle. C. Increased glide range.
Increased minimum glide angle. References
D. Decreased sink rate.
278. JAAExam.com/ATPL Question ID: 645
Answer A is correct.
Comparing the lift coefficient and drag coefficient at normal angle of attack:
The correct answer is A CL is much greater than CD.
A. CL is much greater than CD. B. CL has approximately the same value as CD.
References
C. CL is lower than CD. D. CL is much lower than CD.
279. JAAExam.com/ATPL Question ID: 777
Answer C is correct.
What effect does an increased load have on an aircraft?
The correct answer is C The aircraft will stall at a higher speed.
A. The aircraft will have a tendency to spin. B. The aircraft will suffer immediate structural failure.
References
C. The aircraft will stall at a higher speed. D. The aircraft will have a tendency to roll and yaw.
280. JAAExam.com/ATPL Question ID: 1526
Answer C is correct.
What is the approximate value of the lift of an aeroplane at a gross weight of 50 000 N, in a horizontal coordinated 45 degrees banked turn?
The correct answer is C
A. 50 000 N
70 000 N References
B. 60 000 N C. 70 000 N D. 80 000 N
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281. JAAExam.com/ATPL Question ID: 1504
Answer B is correct.
When making a level turn...
The correct answer is B
A. less power is required than in straight and level flight.
more power is required than in straight and level flight.
B. more power is required than in straight and level flight.
References
C. the same power is required as in straight and level flight. D. the load factor will decrease.
282. JAAExam.com/ATPL Question ID: 814
Answer B is correct.
The purpose of a fixed spoiler on the leading edge of a wing at the root is to:
The correct answer is B
A. reduce the landing distance required.
ensure that the root of the wing stalls before the tip does.
B. ensure that the root of the wing stalls before the tip does.
References
C. prevent the wing from stalling at the root. D. imparting fresh momentum to the particles in the boundary layer on the top of the wing.
283. JAAExam.com/ATPL Question ID: 1197
Answer C is correct.
Over tensioned cables is a flying control system could result in:
The correct answer is C excessive friction in the system.
A. no appreciable difference. B. insufficient friction in the system.
References
C. excessive friction in the system. D. restricted movement of control surfaces.
284. JAAExam.com/ATPL Question ID: 472
Answer A is correct.
Considering a positive cambered aerofoil, the pitch moment when Cl=0 is:
The correct answer is A negative (pitch-down).
A. negative (pitch-down). B. equal to zero.
References
C. infinite. D. positive (pitch-up).
285. JAAExam.com/ATPL Question ID: 982
Answer B is correct.
When the presence of a shock wave causes airflow to separate from a body, this is known as:
The correct answer is B a shock stall.
A. a transonic effect.
B. a shock stall.
References
C. a stall. D. a boundary layer stall.
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286. JAAExam.com/ATPL Question ID: 461
Answer B is correct.
Compared to a cambered airfoil, the zero lift angle of attack of a symmetrical airfoil is:
The correct answer is B higher.
A. lower. B. higher.
References
C. the same. D. depending on airspeed.
287. JAAExam.com/ATPL Question ID: 1473
Answer B is correct.
Weight acts:
The correct answer is B
A. perpendicular to the chord line. B. parallel to the gravitational force. C. perpendicular to the longitudinal axis.
parallel to the gravitational force. References
D. perpendicular to the relative airflow.
288. JAAExam.com/ATPL Question ID: 679
Answer A is correct.
That portion of the aircrafts total drag created by the production of lift is called?
The correct answer is A
A. Induced drag, and is greatly affected by changes in airspeed. B. Parasite drag, and is greatly affected by changes in airspeed.
Induced drag, and is greatly affected by changes in airspeed. References
C. Induced drag, and is not affected by changes in airspeed. D. Profile drag, and is not affected by changes in airspeed.
289. JAAExam.com/ATPL Question ID: 923
Answer D is correct.
What is the effect of deploying leading edge flaps?
The correct answer is D
A. Decrease CLMAX. B. Decrease the critical angle of attack. C. Not affect the critical angle of attack. D. Increase the critical angle of attack.
Increase the critical angle of attack. References
290. JAAExam.com/ATPL Question ID: 453
Answer A is correct.
The fineness ratio of an airfoil is:
The correct answer is A
A. thickness / chord ratio. B. thickness / span ratio. C. mean chord / thickness ratio.
thickness / chord ratio. References
D. mean camber chord ratio / thickness ratio.
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291. JAAExam.com/ATPL Question ID: 925
Answer A is correct.
Which of the following occurs when trailing edge flaps are extended?
The correct answer is A
A. The critical angle of attack decreases and CLMAX increases. B. CLMAX increases and the critical angle of attack increases.
The critical angle of attack decreases and CLMAX increases. References
C. The critical angle of attack is constant, but CLMAX increases. D. The critical angle of attack remains constant and stall speed increases.
292. JAAExam.com/ATPL Question ID: 1158
Answer A is correct.
The dihedral construction of an aircraft wing provides:
The correct answer is A lateral stability about the longitudinal axis.
A. lateral stability about the longitudinal axis. B. lateral stability about the normal axis.
References
C. longitudinal stability about the lateral axis. D. directional stability about the lateral axis.
293. JAAExam.com/ATPL Question ID: 803
Answer A is correct.
Load factors has the following meaning:
The correct answer is A
A. the ratio of a specified load to the weight of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions
the ratio of a specified load to the weight of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions
B. the loads assumed to occur in the anticipated operating conditions
References
C. the ratio of a specified load to the mass or the aircraft the former being expressed in terms of aerodynamic and inertia forces D. the ratio of a specified load to the mass of the aircraft, the former being expressed in terms of aerodynamic forces, inertia forces and ground reactions
294. JAAExam.com/ATPL Question ID: 1062
Answer B is correct.
When the air is passing through an expansion wave the Mach number will:
The correct answer is B increase.
A. decrease. B. increase.
References
C. stay constant. D. decrease and beyond a certain Mach number start increasing again.
295. JAAExam.com/ATPL Question ID: 859
Answer D is correct.
Which type of stall has the largest associated angle of attack?
The correct answer is D Deep stall.
A. Low speed stall. B. Shock stall.
References
C. Accelerated stall. D. Deep stall.
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296. JAAExam.com/ATPL Question ID: 596
Answer C is correct.
A symmetrical aerofoil section at CL = 0 will produce?
The correct answer is C Zero pitching moment.
A. A negative (nose down) pitching moment. B. A positive (nose up) pitching moment.
References
C. Zero pitching moment. D. No aerodynamic force.
297. JAAExam.com/ATPL Question ID: 594
Answer D is correct.
What effect on stall speed do the following have?
The correct answer is D
A. Increased anhedral increases stall speed. B. Fitting a T tail will reduce stall speed. C. Increasing sweepback decreases stall speed.
Decreasing sweep angle decreases stall speed. References
D. Decreasing sweep angle decreases stall speed.
298. JAAExam.com/ATPL Question ID: 559
Answer D is correct.
In a symmetrical airfoil the mean camber line is?
The correct answer is D
A. A line joining points of mean camber along the wing.
A straight line co-incident with the chord line.
B. A line joining points of maximum camber along the wing.
References
C. A curve co-incident with the top surface of the airfoil. D. A straight line co-incident with the chord line.
299. JAAExam.com/ATPL Question ID: 910
Answer D is correct.
If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less than wing span)
The correct answer is D
A. increase.
decrease. References
B. remain the same. C. increase or decrease, depending on the initial angle of attack. D. decrease.
300. JAAExam.com/ATPL Question ID: 1394
Answer C is correct.
The greatest drag produced by the variable pitch propeller on a piston engine will occur when the propeller is:
The correct answer is C
A. stopped in fine pitch.
windmilling. References
B. stopped in coarse pitch. C. windmilling. D. used during a powered glide.
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301. JAAExam.com/ATPL Question ID: 490
Answer C is correct.
What are the correct SI units for density and force?
The correct answer is C
A. Kg/N, Nm3 B. N/m3, Kg C. Kg/m3, Newton
Kg/m3, Newton References
D. Kg/m3, Kg
302. JAAExam.com/ATPL Question ID: 908
Answer A is correct.
In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will:
The correct answer is A
A. increase. B. decrease. C. remain constant.
increase. References
D. increase or decrease depending on type of flap.
303. JAAExam.com/ATPL Question ID: 716
Answer B is correct.
Total Drag at high Mach numbers is a combination of:
The correct answer is B
A. wave drag, interference drag, form drag, and induced drag. B. induced drag, wave drag, form drag, skin friction drag and interference drag.
induced drag, wave drag, form drag, skin friction drag and interference drag. References
C. profile drag, form drag, induced drag and wave drag. D. induced drag, form drag, interference drag and zero lift drag.
304. JAAExam.com/ATPL Question ID: 503
Answer D is correct.
If a pilot changes the altimeter setting from 30.11 Hg to 29.96 Hg, what will be the approximate change in indication?
The correct answer is D
A. Depends on the outside temperature.
Altimeter will indicate 150 feet lower. References
B. Altimeter will indicate .15 Hg higher. C. Altimeter will indicate 150 feet higher. D. Altimeter will indicate 150 feet lower.
305. JAAExam.com/ATPL Question ID: 1028
Answer A is correct.
Two methods to increase the critical Mach Number are:
The correct answer is A thin aerofoil and sweep back of the wing.
A. thin aerofoil and sweep back of the wing. B. thin aerofoil and dihedral of the wing.
References
C. positive cambering of the aerofoil and sweep back of the wing. D. thick aerofoil and dihedral of the wing.
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306. JAAExam.com/ATPL Question ID: 1075
Answer A is correct.
As the centre of gravity moves, recovery from a stall:
The correct answer is A
A. is more difficult with the centre of gravity moving aft. B. is more difficult with the centre of gravity moving forward. C. is less difficult when the centre of gravity
is more difficult with the centre of gravity moving aft. References
moves aft. D. in unaffected by centre of gravity position, only by all up weight (AUW).
307. JAAExam.com/ATPL Question ID: 755
Answer D is correct.
Floating due to ground effect during an approach to land will occur:
The correct answer is D
A. at a speed approaching the stall.
when the height is less than halve of the length of the wing span above the surface.
B. when the height is less than twice the length of the wing span above the surface.
References
C. when a higher than normal angle of attack is used. D. when the height is less than halve of the length of the wing span above the surface.
308. JAAExam.com/ATPL Question ID: 1097
Answer B is correct.
The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
The correct answer is B (1) forward C.G. position (2) aeroplane nose up trim.
A. (1) forward C.G. position (2) forward CG. position.
References
B. (1) forward C.G. position (2) aeroplane nose up trim. C. (1) aft C.G. position (2) aft CG. position. D. (1) aeroplane nose up trim (2) aeroplane nose up trim.
309. JAAExam.com/ATPL Question ID: 877
Answer B is correct.
The effect of Winglets is:
The correct answer is B
A. elliptical pressure distribution increases. B. reduction in induced drag. C. decrease in stall speed.
reduction in induced drag. References
D. longitudinal static stability increases.
310. JAAExam.com/ATPL Question ID: 1040
Answer A is correct.
When a supersonic airflow passes through an oblique shockwave static pressure will ... and temperature will...
The correct answer is A
A. rise; rise. B. fall; rise. C. fall; fall. D. rise; fall.
rise; rise. References
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311. JAAExam.com/ATPL Question ID: 865
Answer B is correct.
When the angle of attack of an aircraft is progressively increased, the wing center of pressure will reach its most forward position:
The correct answer is B
A. at the optimum angle of attack of the wing.
at the maximum lift coefficient (Clmax). References
B. at the maximum lift coefficient (Clmax). C. when the airplane flies at an angle of attack where the lift-to-drag ratio is maximum. D. when the aircraft has stalled.
312. JAAExam.com/ATPL Question ID: 508
Answer B is correct.
In straight and level flight the center of pressure is behind the center of gravity. With the resultant force from the elevators and tailplane action to maintain straight and level flight, the force would be action:
The correct answer is B
A. upward.
downward. References
B. downward. C. horizontally. D. in a direction depending on the thrust/drag couple.
313. JAAExam.com/ATPL Question ID: 1467
Answer B is correct.
To counteract the effect of slipstream on a single engined aircraft:
The correct answer is B the fin may be offset.
A. the fin may be reduced in size. B. the fin may be offset.
References
C. the fin may be inverted. D. frise ailerons may be used.
314. JAAExam.com/ATPL Question ID: 544
Answer B is correct.
The angle of attack of a two dimensional wing section is the angle between:
The correct answer is B
A. the chord line of the aerofoil and the fuselage centreline. B. the chord line of the aerofoil and the free stream direction. C. the fuselage core line and the free stream direction. D. the chord line and the camber line of the aerofoil.
the chord line of the aerofoil and the free stream direction. References
315. JAAExam.com/ATPL Question ID: 978
Answer C is correct.
The formula for the Mach Number is: (a = speed of sound) is?
The correct answer is C M= TAS / a
A. M= TAS*a B. M= a / TAS
References
C. M= TAS / a D. M= IAS / a
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316. JAAExam.com/ATPL Question ID: 659
Answer B is correct.
The wake vortices behind a large aircraft begin on takeoff ... and end on landing...
The correct answer is B on rotation; as the nosewheel goes down.
A. at V2; in the flare. B. on rotation; as the nosewheel goes down.
References
C. at V1; when lift dump is selected. D. at 80kt; on touchdown.
317. JAAExam.com/ATPL Question ID: 1221
Answer B is correct.
Rolling is a rotation about:
The correct answer is B
A. the lateral axis. B. the longitudinal axis. C. the normal axis.
the longitudinal axis. References
D. any or all of the axes depending on the altitude of the aeroplane time.
318. JAAExam.com/ATPL Question ID: 822
Answer A is correct.
What is the standard stall recovery for a light aircraft?
The correct answer is A
A. Pitch down, stick neutral roll, correct for bank with rudder. B. Pitch down, stick neutral roll, correct for bank with aileron.
Pitch down, stick neutral roll, correct for bank with rudder. References
C. Pitch down, stick neutral, wait for neutral tendency. D. Pitch down, stick neutral roll, do not correct for bank
319. JAAExam.com/ATPL Question ID: 744
Answer A is correct.
If EAS is increased by a factor of 4, by what factor
The correct answer is A
would profile drag increase? A. 16
16 References
B. 12 C. 8 D. 4
320. JAAExam.com/ATPL Question ID: 476
Answer D is correct.
Where does the lift act on the wing?
The correct answer is D
A. Suction. B. Always forward of the CG. C. Centre of Gravity.
Centre of Pressure. References
D. Centre of Pressure.
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321. JAAExam.com/ATPL Question ID: 691
Answer B is correct.
At zero angle of attack, a symmetrical wing section (viscous flow) will produce:
The correct answer is B zero lift and some profile drag.
A. zero lift and zero drag. B. zero lift and some profile drag.
References
C. only induced drag. D. zero lift and some induced drag.
322. JAAExam.com/ATPL Question ID: 1111
Answer A is correct.
During landing of a low-winged jet aeroplane, the maximum elevator up deflection is normally required when the flaps are:
The correct answer is A
A. fully down and the C.G. is fully forward.
fully down and the C.G. is fully forward. References
B. up and the C.G. is fully forward. C. fully down and the C.G. is fully aft. D. up and the C.G. is fully aft.
323. JAAExam.com/ATPL Question ID: 511
Answer D is correct.
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
The correct answer is D F = m.a
A. m = F.a B. a = F.m C. F = m/a D. F = m.a
References
324. JAAExam.com/ATPL Question ID: 1187
Answer B is correct.
The type of flap which extends rearward from the trailing edge of the wing as it is lowered is called:
The correct answer is B a fowler flap.
A. a zap flap. B. a fowler flap.
References
C. a split flap. D. a Krueger flap.
325. JAAExam.com/ATPL Question ID: 737
Answer B is correct.
If the aspect ratio of a wing (for a given wing area) is decreased:
The correct answer is B induced drag, for a given angle of attack, increases.
A. lift coefficient remains unaffected at a given angle of attack.
References
B. induced drag, for a given angle of attack, increases. C. induced drag decreases for a given angle of attack. D. lift coefficient increases for a given angle of attack.
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326. JAAExam.com/ATPL Question ID: 1026
Answer D is correct.
Critical Mach-number is the:
The correct answer is D
A. highest speed at which the aeroplane is certificated for operation (MMO).
highest speed without supersonic flow over any part of the aeroplane.
B. speed at which there is subsonic airflow over all parts of the aircraft(Mach number < 1).
References
C. speed at which there is supersonic airflow over all parts of the aeroplane. D. highest speed without supersonic flow over any part of the aeroplane.
327. JAAExam.com/ATPL Question ID: 1030
Answer C is correct.
Mcrit is the free stream Mach Number at which:
The correct answer is C
A. shock stall occurs. B. Mach buffet occurs. C. somewhere about the airframe Mach 1 is reached locally.
somewhere about the airframe Mach 1 is reached locally. References
D. the critical angle of attack is reached.
328. JAAExam.com/ATPL Question ID: 579
Answer A is correct.
What does parasite drag vary with? A. Square of the speed. B. CLmax. C. Speed.
The correct answer is A Square of the speed. References
D. Surface area.
329. JAAExam.com/ATPL Question ID: 723
Answer C is correct.
The interference drag is created as a result of:
The correct answer is C
A. separation of the induced vortex. B. the addition of induced and parasite drag. C. interaction between aeroplane parts (e.g. wing/fuselage).
interaction between aeroplane parts (e.g. wing/fuselage). References
D. downwash behind the wing.
330. JAAExam.com/ATPL Question ID: 1405
Answer A is correct.
With a constant speed propeller, which of the following statements is true?
The correct answer is A Pitch angle increases with increasing TAS.
A. Pitch angle increases with increasing TAS. B. Pitch angle decreases with increasing TAS.
References
C. RPM decreases with increasing TAS. D. RPM increases with increasing TAS.
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331. JAAExam.com/ATPL Question ID: 1091
Answer A is correct.
What is the purpose of the mach trim?
The correct answer is A
A. to counteract the tuck-under effect.
to counteract the tuck-under effect.
B. to compensate for variations in lateral stability at high mach numbers.
References
C. to prevent wing tip stall on swept wings. D. to compensate for the centre of gravity shift in the transonic speed range.
332. JAAExam.com/ATPL Question ID: 860
Answer D is correct.
Which statement is correct about the laminar and turbulent boundary layer:
The correct answer is D friction drag is lower in the laminar layer
A. separation point will occur earlier in the turbulent layer.
References
B. friction drag will be equal in both types of layers. C. friction drag is lower in the turbulent layer. D. friction drag is lower in the laminar layer
333. JAAExam.com/ATPL Question ID: 775
Answer A is correct.
A wing stalling angle is:
The correct answer is A
A. unaffected by a turn. B. increased in a high rate of turn. C. decreased in a high rate of turn.
unaffected by a turn. References
D. decreased in any turn.
334. JAAExam.com/ATPL Question ID: 535
Answer B is correct.
The Principle of Continuity states that in a tube of increasing cross-sectional area, the speed of a subsonic and incompressible airflow will:
The correct answer is B
A. remain the same.
decrease. References
B. decrease. C. sonic. D. increase.
335. JAAExam.com/ATPL Question ID: 1520
Answer C is correct.
During straight descent, lift is equal to:
The correct answer is C
A. weight. B. W x sin(climb angle). C. W x cos(climb angle).
W x cos(climb angle). References
D. thrust.
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336. JAAExam.com/ATPL Question ID: 1470
Answer D is correct.
To obtain both a small turn radius and a large turn rate, we want:
The correct answer is D
A. the lowest possible load factor and the lowest possible velocity. B. the highest possible load factor and the highest possible velocity. C. the lowest possible load factor and the highest possible velocity. D. the highest possible load factor and the
the highest possible load factor and the lowest possible velocity. References
lowest possible velocity.
337. JAAExam.com/ATPL Question ID: 528
Answer A is correct.
Which of the following wing planform gives the highest local profile lift coefficient at the wing root?
The correct answer is A Rectangular.
A. Rectangular. B. Elliptical.
References
C. Tapered. D. Positive angle of sweep.
338. JAAExam.com/ATPL Question ID: 1318
Answer B is correct.
An aircraft has a mass of 60,000kg and a limiting positive load factor of 2,5. VA is calculated as the EAS at which full positive elevator deflection will give the limiting load factor at the stall, and is 237kts. If the aircraft mass is reduced to 40,000kg by fuel burn, what will be the new VA?
The correct answer is B 194 kts References
A. 375 kts B. 194 kts C. 237 kts D. 150 kts
339. JAAExam.com/ATPL Question ID: 525
Answer A is correct.
A high aspect ratio wing:
The correct answer is A
A. has a long span and short chord. B. has a short span and short chord. C. has a long span and long chord.
has a long span and short chord. References
D. has a short span and long chord.
340. JAAExam.com/ATPL Question ID: 967
Answer A is correct.
Compressibility effects are usually insignificant below:
The correct answer is A Mach 0.4
A. Mach 0.4 B. 661 knots at sea level.
References
C. 350 knots at sea level. D. are always significant.
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341. JAAExam.com/ATPL Question ID: 1150
Answer C is correct.
Directional stability is the stability around the:
The correct answer is C
A. Longitudinal axis. B. Lateral axis. C. Normal axis.
Normal axis. References
D. Pitch axis.
342. JAAExam.com/ATPL Question ID: 574
Answer C is correct.
When the undercarriage is lowered in flight:
The correct answer is C
A. form drag will increase and the aircrafts nose down pitching moment will be unchanged.
form drag will increase and the aircrafts nose down pitching moment will increase.
B. induced drag will increase and the aircrafts nose down pitching moment will increase.
References
C. form drag will increase and the aircrafts nose down pitching moment will increase. D. induced drag will decrease and the aircrafts nose down pitching moment will increase.
343. JAAExam.com/ATPL Question ID: 560
Answer B is correct.
Flying at the maximum rate of climb speed (Vy) you will obtain maximum:
The correct answer is B altitude in the shortest time.
A. altitude in the shortest distance. B. altitude in the shortest time.
References
C. altitude in the shortest distance and time D. altitude at maximum boost setting.
344. JAAExam.com/ATPL Question ID: 1043
Answer D is correct.
If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:
The correct answer is D to the mid chord position.
A. to a position near the trailing edge. B. forward.
References
C. to a position near the leading edge. D. to the mid chord position.
345. JAAExam.com/ATPL Question ID: 602
Answer C is correct.
Which of the following is the greatest factor causing lift?
The correct answer is C Suction above the wing.
A. Increased airflow velocity below the wing. References
B. Increased pressure below wing. C. Suction above the wing. D. Decreased airflow velocity above the wing.
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346. JAAExam.com/ATPL Question ID: 941
Answer A is correct.
When pulling out of a dive (e.g. looping) the angle of attack:
The correct answer is A increases.
A. increases. B. decreases.
References
C. remains the same. D. cannot be increased at all for structural reasons.
347. JAAExam.com/ATPL Question ID: 1549
Answer B is correct.
In a steady turn at constant height:
The correct answer is B
A. the radius of turn depends upon the weight and load factor.
the rate of turn depends upon the TAS and angle of bank.
B. the rate of turn depends upon the TAS and angle of bank.
References
C. the rate of turn depends upon the weight, TAS and angle of bank. D. the radius of turn depends only upon load factor.
348. JAAExam.com/ATPL Question ID: 747
Answer B is correct.
When an aircraft enters ground effect:
The correct answer is B
A. the lift vector is inclined rearwards which increases the thrust required.
the lift vector is inclined forwards which reduces the thrust required.
B. the lift vector is inclined forwards which reduces the thrust required.
References
C. the lift vector is unaffected, the cushion of air increases. D. the lift vector is inclined forward which increases the thrust required.
349. JAAExam.com/ATPL Question ID: 623
Answer D is correct.
Cambered wing sections give... maximum CL at a relatively... angles of attack.
The correct answer is D high; low
A. high; high B. low; high
References
C. low; low D. high; low
350. JAAExam.com/ATPL Question ID: 871
Answer B is correct.
When, in flight, you lower the trailing edge flaps fully down:
The correct answer is B
A. the wing C of P moves forward and the L/D ratio increases. B. the wing C of P moves aft and the L/D ratio decreases.
the wing C of P moves aft and the L/D ratio decreases. References
C. the stalling angle increases and the L/D ratio reduces. D. the stalling angle reduces and the L/D ratio increases.
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351. JAAExam.com/ATPL Question ID: 457
Answer A is correct.
Which statement is correct about the Cl and angle of attack?
The correct answer is A
A. For a symmetric aerofoil, if angle of attack = 0, Cl =0. B. For a symmetric aerofoil, if angle of attack = 0, Cl is not equal to 0.
For a symmetric aerofoil, if angle of attack = 0, Cl =0. References
C. For an asymmetric aerofoil, if angle of attack = 0, Cl =0. D. For an asymmetric aerofoil with positive camber, if angle of attack is greater than 0, Cl = 0.
352. JAAExam.com/ATPL Question ID: 1396
Answer B is correct.
Running an engine fitted with a fixed pitch propeller at full throttle with the aircraft stationary and nose into strong wind will result in:
The correct answer is B
A. a variable rpm depending on the CSU.
higher rpm than in still air. References
B. higher rpm than in still air. C. lower rpm than in still air. D. the same rpm as in still air.
353. JAAExam.com/ATPL Question ID: 1477
Answer B is correct.
In a level banked turn, the stalling speed will:
The correct answer is B
A. decrease. B. increase.
increase.
C. remain the same.
References
D. vary inversely with wing loading.
354. JAAExam.com/ATPL Question ID: 710
Answer D is correct.
The induced drag of an aircraft in level flight:
The correct answer is D
A. increases with increasing speed. B. is not affected by airspeed. C. increases as the wing aspect ratio is increased.
decreases with increasing airspeed. References
D. decreases with increasing airspeed.
355. JAAExam.com/ATPL Question ID: 811
Answer B is correct.
Stick pusher is installed in aircraft when:
The correct answer is B
A. The aircraft is directional unstable. B. The a/c has failed to meet the stalling requirements by normal category. C. The a/c has not yaw damper installed.
The a/c has failed to meet the stalling requirements by normal category. References
D. The a/c is used in supersonic speeds.
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356. JAAExam.com/ATPL Question ID: 1099
Answer D is correct.
Which of the following components is most important in determining longitudinal static stability?
The correct answer is D Horizontal tailplane.
A. Fuselage. B. Wings.
References
C. Engines D. Horizontal tailplane.
357. JAAExam.com/ATPL Question ID: 1360
Answer D is correct.
The booster pump fitted to the CSU of a constant speed propeller:
The correct answer is D
A. provides emergency oil pressure for feathering. B. is electrically operated, which is used to feather double acting propellers. C. is driven by the propeller to provide oil pressure to unfeather single acting propellers. D. increases the engine lubricating oil pressure for propeller operation.
increases the engine lubricating oil pressure for propeller operation. References
358. JAAExam.com/ATPL Question ID: 605
Answer A is correct.
If the angle of attack is maintained constant, what happens to the coefficient of lift when flaps are deployed?
The correct answer is A
A. Increased.
Increased. References
B. Decreased. C. Changes with the square of IAS. D. Remains constant because angle of attack remains the same.
359. JAAExam.com/ATPL Question ID: 612
Answer B is correct.
Which statement is true for a symmetrical wing section:
The correct answer is B
A. the centre of pressure is infinitely far behind the wing. B. the centre of pressure is at the aerodynamic centre of the wing.
the centre of pressure is at the aerodynamic centre of the wing. References
C. the centre of pressure is in the front of the aerodynamic centre of the wing. D. the centre of pressure is behind the aerodynamic centre of the wing.
360. JAAExam.com/ATPL Question ID: 903
Answer B is correct.
The purpose of a fixed spoiler on the leading edge of a wing at the root is to:
The correct answer is B ensure that the root of the wing stalls before the tip.
A. reduce the landing run. B. ensure that the root of the wing stalls before the tip.
References
C. prevent the wing from stalling at the root.g D. re-energise the boundary layer thereby delaying the stall (although at a cost of increased from drag).
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361. JAAExam.com/ATPL Question ID: 1119
Answer D is correct.
If an aircraft continues to oscillate with a constant amplitude after having encountered a vertical gust. This kind of stability is called:
The correct answer is D
A. longitudinal neutral static stability. B. lateral instability. C. longitudinal dynamic instability. D. longitudinal neutral dynamic stability.
longitudinal neutral dynamic stability. References
362. JAAExam.com/ATPL Question ID: 498
Answer A is correct.
As a smooth flow of subsonic air at a velocity less than M0.4 flows through a divergent duct:
The correct answer is A (i) increases and (ii) decreases
i. ii.
static pressure velocity
References
A. (i) increases and (ii) decreases B. (i) increases and (ii) increases C. (i) decreases and (ii) decreases D. (i) decreases and (ii) increases
363. JAAExam.com/ATPL Question ID: 1058
Answer B is correct.
The additional increase of drag at Mach Numbers above the critical Mach Number is due to:
The correct answer is B wave drag.
A. increased angle of attack. B. wave drag.
References
C. increased interference drag. D. increased skin friction.
364. JAAExam.com/ATPL Question ID: 898
Answer B is correct.
During the retraction of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant):
The correct answer is B
A. bank.
sink suddenly. References
B. sink suddenly. C. climb. D. yaw.
365. JAAExam.com/ATPL Question ID: 756
Answer B is correct.
During acceleration in level flight:
The correct answer is B
A. the wing stagnation point moves aft. B. the lift coefficient reduces. C. the aircraft centre of gravity moves aft.
the lift coefficient reduces. References
D. the transition point on the wing moves forward.
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366. JAAExam.com/ATPL Question ID: 1209 In a mechanically controlled aeroplane, the most
Answer A is correct.
forward allowable position of the centre of gravity could be limited by the: A. elevator capability, elevator control forces.
The correct answer is A elevator capability, elevator control forces.
B. engine thrust, engine location. C. trim system, trim tab surface.
References
D. wing surface, stabilizer surface.
367. JAAExam.com/ATPL Question ID: 1539
Answer D is correct.
Which of the following statements is correct?
The correct answer is D
A. Lift acts perpendicular to the horizontal and drag parallel in a rearwards direction.
Drag acts in the same direction as the relative wind and lift perpendicular to it.
B. Drag acts parallel to the chord and opposite to the direction of motion of the aircraft and lift acts perpendicular to the chord.
References
C. Lift acts at right angles to the top surface of the wing and drag acts at right angles to lift. D. Drag acts in the same direction as the relative wind and lift perpendicular to it.
368. JAAExam.com/ATPL Question ID: 673
Answer B is correct.
Induced drag may be reduced by:
The correct answer is B
A. an increase in the taper ratio of the wing. B. an increase in aspect ratio. C. a decrease of the aspect ratio.
an increase in aspect ratio. References
D. the use of a wing tip with a much thinner aerofoil.
369. JAAExam.com/ATPL Question ID: 1072
Answer B is correct.
A statically unstable aeroplane is:
The correct answer is B
A. always dynamically stable. B. never dynamically stable. C. sometimes dynamically stable.
never dynamically stable. References
D. sometimes dynamically unstable.
370. JAAExam.com/ATPL Question ID: 791
Answer B is correct.
One disadvantage of the swept back wing is it is stalling characteristics. At the stall:
The correct answer is B
A. wing root stall will occur first, which produces a rolling moment.
tip stall will occur first, which produces a pitch-up moment.
B. tip stall will occur first, which produces a pitch-up moment.
References
C. tip stall will occur first, which produces a nose-down moment. D. leading edge stall will occur first, which produces a nose-down moment.
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371. JAAExam.com/ATPL Question ID: 1265
Answer D is correct.
On take-off with the CG at the forward limit:
The correct answer is D
A. elevator stick force is less because of the increased tailplane arm.
elevator stick forces will be higher at VR.
B. elevator stick force to rotate the aircraft at VR will be unchanged, because the aircraft on the ground rotates about the main wheels.
References
C. VMCG is lower due to the increased fin arm. D. elevator stick forces will be higher at VR.
372. JAAExam.com/ATPL Question ID: 478
Answer D is correct.
The (subsonic) static pressure:
The correct answer is D
A. increases in a flow in a tube when the diameter decreases.
decreases in a flow in a tube when the diameter decreases.
B. is the total pressure plus the dynamic pressure.
References
C. is the pressure in a point at which the velocity has become zero. D. decreases in a flow in a tube when the diameter decreases.
373. JAAExam.com/ATPL Question ID: 1034
Answer B is correct.
The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
The correct answer is B
A. the maximum operating temperature is reached. B. sonic speed (M=1) is reached at a certain point on the upper side of the aerofoil.
sonic speed (M=1) is reached at a certain point on the upper side of the aerofoil. References
C. a shock-wave appears on the upper surface. D. a supersonic bell appears on the upper surface.
374. JAAExam.com/ATPL Question ID: 892
Answer D is correct.
CLmax may be increased by the use of:
The correct answer is D
A. flaps. B. slats. C. boundary layer control.
A, B and C. References
D. A, B and C.
375. JAAExam.com/ATPL Question ID: 1567
Answer B is correct.
Refer to Figure: 081-11
The correct answer is B
(Refer to figure 081-11) On the polar diagram, point C corresponds to:
the critical angle of attack. References
A. best lift/drag ratio angle of attack. B. the critical angle of attack. C. minimum drag. D. zero lift angle of attack.
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376. JAAExam.com/ATPL Question ID: 1357
Answer C is correct.
The angle of attack for a propeller blade is the angle between blade chord line and:
The correct answer is C Local air speed vector.
A. Aeroplane heading. B. Direction of propeller axis.
References
C. Local air speed vector. D. Principal direction of propeller blade.
377. JAAExam.com/ATPL Question ID: 937
Answer B is correct.
The boundary layer is considered to be turbulent?
The correct answer is B
A. Just in front of the transition point. B. Between the transition and separation points. C. Just aft of the separation point.
Between the transition and separation points. References
D. Just in front of the centre of pressure.
378. JAAExam.com/ATPL Question ID: 493
Answer C is correct.
In accordance with Bernoulli’ s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure:
The correct answer is C
A. PT + PS = q B. PT = PS - q C. PT - PS = q
PT - PS = q References
D. PS + PT = q
379. JAAExam.com/ATPL Question ID: 1134
Answer A is correct.
Dutch roll occurs when:
The correct answer is A
A. lateral stability is too great compared to directional stability.
lateral stability is too great compared to directional stability.
B. directional stability is too great compared to lateral stability.
References
C. directional and lateral stability is equal. D. directional stability is compensated by ailerons.
380. JAAExam.com/ATPL Question ID: 1121
Answer C is correct.
If an aircraft has neutral static stability, what will happen if it is disturbed (e.g. vertical gust):
The correct answer is C will remain in the disturbed attitude forever.
A. will continue to diverge away from the neutral position.
References
B. will oscillate with a fixed amplitude around the trimmed position. C. will remain in the disturbed attitude forever. D. will return to the trimmed position.
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381. JAAExam.com/ATPL Question ID: 1239
Answer D is correct.
Adverse aileron yaw can be countered by:
The correct answer is D
A. aileron reversal.
differential ailerons.
B. nothing (it is all a desirable flight characteristic).
References
C. aileron snatch. D. differential ailerons.
382. JAAExam.com/ATPL Question ID: 801
Answer D is correct.
An aeroplane has a stall speed of 78 KCAS at its gross weight of 6.850 lbs. What is the stall speed when the weight is 5.000 lbs?
The correct answer is D
A. 91 KCAS B. 78 KCAS C. 57 KCAS D. 67 KCAS
67 KCAS References
383. JAAExam.com/ATPL Question ID: 776
Answer C is correct.
What is a high speed stall?
The correct answer is C
A. Separation of the airflow due to shockwave formation.
A stall due to exceeding the critical angle of attack at high speed during a manoeuvre.
B. A stall caused by increasing the load factor (g) during a manoeuvre.
References
C. A stall due to exceeding the critical angle of attack at high speed during a manoeuvre. D. Excessive dynamic pressure causing airflow separation.
384. JAAExam.com/ATPL Question ID: 677
Answer B is correct.
How do vortex generators work?
The correct answer is B
A. Re-direct slantwise flow. B. Take energy from free stream and introduce it into the boundary layer. C. Reduce kinetic energy to delay separation.
Take energy from free stream and introduce it into the boundary layer. References
D. Reduce the adverse pressure gradient.
385. JAAExam.com/ATPL Question ID: 1331
Answer A is correct.
For airplanes which have a high wing loading (W/S):
The correct answer is A
A. Vertical gusts have less influence on the load factor.
Vertical gusts have less influence on the load factor.
B. Total drag is mainly induced drag.
References
C. Total drag is mainly profile drag. D. Vertical gusts have more influence on the load factor.
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386. JAAExam.com/ATPL Question ID: 1000
Answer B is correct.
When air has passed an expansion wave, the static pressure is:
The correct answer is B decreased.
A. decreased or increased, depending on Mach Number.
References
B. decreased. C. increased. D. unchanged.
387. JAAExam.com/ATPL Question ID: 1009 When the air is passing through a shock wave the
Answer A is correct.
static temperature will: The correct answer is A A. increase. B. decrease. C. stay constant. D. decrease and beyond a certain Mach number start increasing again.
increase. References
388. JAAExam.com/ATPL Question ID: 1555
Answer B is correct.
The greatest gliding range would be obtained from a wing at:
The correct answer is B a small angle of attack at maximum lift/drag ratio.
A. a high angle of attack at maximum lift/drag ratio.
References
B. a small angle of attack at maximum lift/drag ratio. C. a small angle of attack at minimum lift/drag ratio. D. a high angle of attack at minimum lift/drag ratio.
389. JAAExam.com/ATPL Question ID: 1518
Answer A is correct.
For an aircraft in straight and level flight, which forces are in equilibrium?
The correct answer is A Thrust, drag, lift and weight.
A. Thrust, drag, lift and weight. B. Compressive, tensile, shear and torsional loads.
References
C. Tensile, shear, twisting and stretching forces. D. Compressive, bending, shear and torsional forces.
390. JAAExam.com/ATPL Question ID: 619
Answer B is correct.
In flight the C of P by increasing angle of attack, will reach its most forward point on an airfoil:
The correct answer is B just below the stalling angle.
A. at the stalling angle. B. just below the stalling angle.
References
C. at the optimum angle of attack. D. at the stall.
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391. JAAExam.com/ATPL Question ID: 1140 If the forces and moments on a body caused by a disturbance tend initially to return the body toward
Answer D is correct.
its equilibrium position, the body is ... stable. The body has ... stability. A. statically; negative static stability
The correct answer is D statically; positive static stability.
B. dynamically; negative static stability C. dynamically; positive static stability
References
D. statically; positive static stability.
392. JAAExam.com/ATPL Question ID: 766
Answer C is correct.
What is the effect on TAS if altitude is increased to 35,000 ft while flying at a constant Mach number?
The correct answer is C Decrease.
A. Increase then remain constant. B. Increase.
References
C. Decrease. D. Increase then decrease.
393. JAAExam.com/ATPL Question ID: 593
Answer B is correct.
The fineness ratio is:
The correct answer is B
A. the inverse of the thickness-to-chord ratio. B. equal to the thickness-to-chord ratio. C. the inverse of the taper ratio.
equal to the thickness-to-chord ratio. References
D. equal to the taper ratio.
394. JAAExam.com/ATPL Question ID: 1544
Answer A is correct.
In a turn, the load factor n and the stalling speed VS will be:
The correct answer is A
A. n greater than 1, VS higher than in straight and level flight. B. n smaller than 1, VS lower than in straight and level flight.
n greater than 1, VS higher than in straight and level flight. References
C. n greater than 1, VS lower than in straight and level flight. D. n smaller than 1, VS higher than in straight and level flight.
395. JAAExam.com/ATPL Question ID: 963
Answer C is correct.
The speed of sound in a perfect gas depends only on the ... of the gas.
The correct answer is C temperature
A. pressure B. density
References
C. temperature D. free stream velocity
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396. JAAExam.com/ATPL Question ID: 1422
Answer D is correct.
Propeller blades are said to be feathered when:
The correct answer is D
A. the blades are at fully fine pitch. B. the blades are at coarse pitch. C. the propeller is windmilling.
the blades leading edges face forward in the direction of the flight. References
D. the blades leading edges face forward in the direction of the flight.
397. JAAExam.com/ATPL Question ID: 1038
Answer D is correct.
When a supersonic airflow passes through an expansion wave speed will... and temperature wil...
The correct answer is D increase; fall.
A. decrease; fall. B. decrease; rise.
References
C. increase; rise. D. increase; fall.
398. JAAExam.com/ATPL Question ID: 1172
Answer D is correct.
Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?
The correct answer is D
A. An aft C.G. position shortens the period time of the phugoid.
Damping of the phugoid is normally very weak. References
B. Speed remains constant during one period of the phugoid. C. Period time of the phugoid is normally 5 sec. D. Damping of the phugoid is normally very weak.
399. JAAExam.com/ATPL Question ID: 504
Answer C is correct.
The resistance, or skin friction, due to the viscosity of the air as it passes along the surface of the wing is part of the:
The correct answer is C
A. induced drag. B. form drag. C. parasite drag D. interference drag.
parasite drag References
400. JAAExam.com/ATPL Question ID: 563
Answer C is correct.
High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
The correct answer is C decreasing induced drag and critical angle of attack.
A. increasing lift and drag. B. increasing induced drag and decreasing critical angle of attack.
References
C. decreasing induced drag and critical angle of attack. D. increasing lift and critical angle of attack
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401. JAAExam.com/ATPL Question ID: 1267
Answer B is correct.
Possible solutions to reduce the control column forces required to deflect large control surfaces in flight are:
The correct answer is B
A. static balancing.
aerodynamic balancing. References
B. aerodynamic balancing. C. mass balancing. D. moving the hinge line further forward towards the control surface leading edge.
402. JAAExam.com/ATPL Question ID: 604
Answer B is correct.
Increasing the angle of attack in flight will cause the:
The correct answer is B
A. separation point to move aft. B. stagnation point to move down and aft. C. boundary layer to become thinner.
stagnation point to move down and aft. References
D. laminar flow to increase.
403. JAAExam.com/ATPL Question ID: 994
Answer C is correct.
Shockwaves at MFS above MDET will be:
The correct answer is C
A. Sufficient to slow the local airflow to subsonic values.
Oblique.
B. Normal.
References
C. Oblique. D. Detached.
404. JAAExam.com/ATPL Question ID: 1386
Answer A is correct.
A fixed pitch propeller is usually:
The correct answer is A
A. at too coarse an angle on take off. B. at too fine an angle on take off. C. at too coarse an angle in the cruise.
at too coarse an angle on take off. References
D. at its optimum angle on take off
405. JAAExam.com/ATPL Question ID: 794
Answer C is correct.
The speed range between high and low speed buffet:
The correct answer is C
A. decreases during a descent at a constant Mach number.
increases during a descent at a constant IAS.
B. is always positive at Mach numbers below MMO.
References
C. increases during a descent at a constant IAS. D. increases during climb.
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406. JAAExam.com/ATPL Question ID: 1276
Answer C is correct.
When flutter damping of control surfaces is obtained by mass balancing, these weights will be located with respect to the hinge of the control surface:
The correct answer is C
A. above the hinge.
in front of the hinge. References
B. below the hinge C. in front of the hinge. D. behind the hinge.
407. JAAExam.com/ATPL Question ID: 828
Answer C is correct.
With the center of gravity on the forward limit, the stalling speed would be:
The correct answer is C
A. independent of the center of gravity position.
higher than with the center of gravity on the aft limit.
B. lower than with the center of gravity on the aft limit.
References
C. higher than with the center of gravity on the aft limit. D. the same as with the center of gravity on the aft limit.
408. JAAExam.com/ATPL Question ID: 1168
Answer B is correct.
Which of the following statements about static lateral and directional stability is correct?
The correct answer is B
A. The effects of static lateral and static directional stability are completely independent of each other because they take
An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to spiral dive. (spiral instability).
place about different axis.
References
B. An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to spiral dive. (spiral instability). C. An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to Dutch roll. D. Static directional stability can be increased by installing more powerful engines.
409. JAAExam.com/ATPL Question ID: 1447
Answer D is correct.
A propeller turns to the right, seen from behind. The torque effect in the take-off will:
The correct answer is D roll the aeroplane to the left.
A. pitch the aeroplane nose up. B. pitch the aeroplane nose down.
References
C. roll the aeroplane to the right. D. roll the aeroplane to the left.
410. JAAExam.com/ATPL Question ID: 1361
Answer D is correct.
If you push forward the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
The correct answer is D
A. decrease and the rate of descent will increase.
decrease and the rate of descent will decrease. References
B. increase and the rate of descent will decrease. C. increase and the rate of descent will increase. D. decrease and the rate of descent will decrease.
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411. JAAExam.com/ATPL Question ID: 1064
Answer C is correct.
One way to increase Mcrit is to:
The correct answer is C
A. increase the chamber of the airfoil. B. sweep the wings. C. move the section with maximum thickness well aft.
move the section with maximum thickness well aft. References
D. install vortex generators.
412. JAAExam.com/ATPL Question ID: 1500
Answer D is correct.
The four forces of lift, weight, thrust and drag in
The correct answer is D
level flight act through: A. the C of P.
the C of G. References
B. the Aerodynamic Centre. C. the Aft Limit. D. the C of G.
413. JAAExam.com/ATPL Question ID: 896
Answer A is correct.
What is the effect of lowering leading edge and trailing edge flaps in flight?
The correct answer is A
A. Cl increases, Cd increases and the stalling angle of attack increases. B. Cl decreases, Cd increases and the stalling angle of attack reduces.
Cl increases, Cd increases and the stalling angle of attack increases. References
C. Cl increases, Cd remains the same and the stalling angle of attack increases. D. Cl remains constant, Cd increases and the stalling angle of attack remains the same.
414. JAAExam.com/ATPL Question ID: 565
Answer B is correct.
The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
The correct answer is B chord line and the relative undisturbed airflow.
A. bottom surface and the chord line. B. chord line and the relative undisturbed airflow.
References
C. bottom surface and the Horizontal. D. bottom surface and the relative airflow.
415. JAAExam.com/ATPL Question ID: 987
Answer B is correct.
When a fluid element flows through a normal shock wave:
The correct answer is B
A. the Mach-number decreases and static pressure decreases. B. the Mach-number decreases and static pressure increases.
the Mach-number decreases and static pressure increases. References
C. the Mach-number increases and static pressure increases. D. the Mach-number increases and static pressure decreases.
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416. JAAExam.com/ATPL Question ID: 639
Answer A is correct.
The L/D ratio in flight will be at its highest value at: A. the optimum angle of attack. B. the stalling angle. C. a point just below the stalling angle.
The correct answer is A the optimum angle of attack. References
D. an angle of attack between 5 degrees and 8 degrees.
417. JAAExam.com/ATPL Question ID: 1042
Answer B is correct.
In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is:
The correct answer is B
A. high (supersonic).
small but still supersonic. References
B. small but still supersonic. C. lower than 1. D. exactly 1.
418. JAAExam.com/ATPL Question ID: 1435
Answer C is correct.
The propeller noise can be minimised by:
The correct answer is C
A. Reduce the RPM of the engine. B. Decrease the angle of attack of the propeller C. Increase number of blades.
Increase number of blades. References
D. Reduce the propeller area.
419. JAAExam.com/ATPL Question ID: 861
Answer B is correct.
When a pilot makes a turn in horizontal flight, the stall speed:
The correct answer is B increases with the square root of load factor.
A. increases with flap extension. B. increases with the square root of load factor.
References
C. decreases with increasing bank angle. D. increases with the load factor squared.
420. JAAExam.com/ATPL Question ID: 1166
Answer B is correct.
What is the effect on the lateral stability of an aircraft, when a high wing is employed?
The correct answer is B Lateral stability will be improved.
A. Lateral stability will be the same as for a low wing aircraft. B. Lateral stability will be improved.
References
C. Lateral stability will be reduced because the airflow at the wing root is disturbed. D. Lateral stability will be reduced because of the lower centre of gravity position.
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421. JAAExam.com/ATPL Question ID: 1452
Answer C is correct.
Which of the following would change the magnitude of the gyroscopic precession effect of the propeller?
The correct answer is C Propeller RPM.
A. Propeller blade angle. B. Rate of roll.
References
C. Propeller RPM. D. TAS
422. JAAExam.com/ATPL Question ID: 487
Answer A is correct.
Which one of the following statements about the liftto-drag ratio in straight and level flight is correct?
The correct answer is A
A. At the highest value of the lift/drag ratio the total drag is lowest. B. The highest value of the lift/drag ratio is reached when the lift is zero.
At the highest value of the lift/drag ratio the total drag is lowest. References
C. The lift/drag ratio always increases as the lift decreases. D. The highest value of the lift/drag ratio is reached when the lift is equal to, the aircraft weight.
423. JAAExam.com/ATPL Question ID: 975
Answer C is correct.
If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will:
The correct answer is C
A. not change.
increase. References
B. decrease. C. increase. D. increase or decrease, depends of the type of aeroplane.
424. JAAExam.com/ATPL Question ID: 1322
Answer D is correct.
Which wind condition would be most critical during taxi with a tricycle landing gear airplane?
The correct answer is D Quartering headwind.
A. Full crosswind. B. Quartering tailwind.
References
C. Direct crosswind. D. Quartering headwind.
425. JAAExam.com/ATPL Question ID: 1233
Answer B is correct.
Flaperons are controls which are used simultaneously as:
The correct answer is B ailerons and flaps.
A. flaps and elevator. B. ailerons and flaps.
References
C. ailerons and elevator. D. flaps and speed brakes.
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426. JAAExam.com/ATPL Question ID: 582
Answer D is correct.
The point about which the wing pitching moment is independent of angle of attack is called:
The correct answer is D the aerodynamic centre.
A. the pitching centre. B. the centre of gravity.
References
C. the centre of pressure. D. the aerodynamic centre.
427. JAAExam.com/ATPL Question ID: 1146
Answer C is correct.
When considering the relationship between lateral static stability and directional stability:
The correct answer is C
A. dominant directional static stability gives an increased tendency for dutch roll. B. dominant lateral static stability gives an increased tendency for spiral instability.
dominant lateral static stability gives an increased tendency for dutch roll. References
C. dominant lateral static stability gives an increased tendency for dutch roll. D. they are mutually independent and have no effect on each other.
428. JAAExam.com/ATPL Question ID: 847
Answer B is correct.
How does stalling speed vary with load factor?
The correct answer is B
A. It decreases inversely with the square root of the load factor.
It increases proportionally with the square root of the load factor.
B. It increases proportionally with the square root of the load factor.
References
C. It decreases inversely with the load factor. D. It increases proportionally with the load factor.
429. JAAExam.com/ATPL Question ID: 1244
Answer D is correct.
Which of the following statements concerning control is correct?
The correct answer is D
A. In general the maximum downward elevator deflection is larger than upward.
In a differential aileron control system the control surfaces have a larger upward than downward maximum deflection.
B. On some aeroplanes, the servo tab also serves as a trim tab.
References
C. Hydraulically powered control surfaces do not need mass balancing. D. In a differential aileron control system the control surfaces have a larger upward than downward maximum deflection.
430. JAAExam.com/ATPL Question ID: 902
Answer C is correct.
When deploying the flaps the effective angle of attack:
The correct answer is C increases.
A. decreases. B. remains the same.
References
C. increases. D. may increase of decrease depending on the aircraft type.
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431. JAAExam.com/ATPL Question ID: 1253
Answer C is correct.
A spring tab is used:
The correct answer is C
A. to reduce a possible tendency of control surface flutter at high speeds.
to reduce the effort required in moving the controls at high airspeed.
B. to provide feel (feed back) in a control system.
References
C. to reduce the effort required in moving the controls at high airspeed. D. to provide a constant spring tension in a trim control system.
432. JAAExam.com/ATPL Question ID: 804
Answer A is correct.
How does the wings centre of pressure move with increasing angle of attack?
The correct answer is A Forward.
A. Forward. B. To the rear. C. It does not move at all. D. To the right.
References
433. JAAExam.com/ATPL Question ID: 1032
Answer B is correct.
Compared to a straight wing of the same airfoil section a wing swept at 30 should theoretically have an Mcrit ... times Mcrit for the straight wing, but will, in practice gain ... that increase:
The correct answer is B
A. cosine 30; twice
1.154; half References
B. 1.154; half C. sine 30; half D. 1.414; twice
434. JAAExam.com/ATPL Question ID: 494
Answer A is correct.
The units of wing loading (I) W / S and (II) dynamic pressure q are:
The correct answer is A (I) N/m2, (II) Nm2
A. (I) N/m2, (II) Nm2 B. (I) N/m3, (II) kg/m2
References
C. (I) kg/m, (II) N/m2 D. (I) N/m, (II) kg
435. JAAExam.com/ATPL Question ID: 789
Answer A is correct.
Which of the following are used as stall warning devices?
The correct answer is A Stick shaker and angle of attack indicator.
A. Stick shaker and angle of attack indicator. B. Stick shaker and stall strip.
References
C. Angle of attack indicator and speed indicator. D. Angle of attack sensor and stall strip.
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436. JAAExam.com/ATPL Question ID: 786
Answer A is correct.
If angle of attack is increased beyond the critical angle of attack, the lift coefficient ... and the stagnation point moves...
The correct answer is A
A. decreases; rearward.
decreases; rearward. References
B. increases; rearward. C. decreases; forward. D. increases; forward.
437. JAAExam.com/ATPL Question ID: 1399
Answer B is correct.
Fixed pitch propellers are usually designed for maximum efficiency at:
The correct answer is B normal cruising speed.
A. take off.
References
B. normal cruising speed. C. maximum RPM. D. best climb speed.
438. JAAExam.com/ATPL Question ID: 1275
Answer C is correct.
Which kind of tab is commonly used in case of manual reversion of fully powered flight controls?
The correct answer is C Servo tab.
A. Balance tab. B. Spring tab.
References
C. Servo tab. D. Anti-balance tab.
439. JAAExam.com/ATPL Question ID: 1138
Answer C is correct.
Ventral fin has its greatest effect at:
The correct answer is C
A. speeds above Mcrit. B. transonic speed. C. low speed, high angle of attack.
low speed, high angle of attack. References
D. high wing loading.
440. JAAExam.com/ATPL Question ID: 764
Answer C is correct.
Induced drag in straight and level flight is:
Unlike parasitic drag on an object (which is proportional to the square of the airspeed), for a given lift, induced drag on an airfoil is inversely proportional to the square of the airspeed.
A. proportional to the square of the speed (TAS). B. constant.
References
C. inversely proportional to the square of speed (TAS). D. always equal to profile drag.
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441. JAAExam.com/ATPL Question ID: 1036
Answer D is correct.
The critical Mach number can be increased by:
The correct answer is D
A. an increase in wing aspect ratio. B. positive dihedral of the wings. C. a T-tail. D. sweepback of the wings.
sweepback of the wings. References
442. JAAExam.com/ATPL Question ID: 1044
Answer C is correct.
In supersonic flight, all disturbances produced by an aeroplane are:
The correct answer is C
A. in front of the aeroplane. B. very weak and negligible. C. in between a conical area, depending on the Mach Number.
in between a conical area, depending on the Mach Number. References
D. outside the conical area depending on the Mach Number.
443. JAAExam.com/ATPL Question ID: 1363
Answer D is correct.
In cruise, the propellers ATM is:
The correct answer is D
A. equal to the CTM (Centrifugal Twisting Moment).
less than the CTM.
B. greater than the CTM.
References
C. equal to the DTM (Dynamic Turning Moment). D. less than the CTM.
444. JAAExam.com/ATPL Question ID: 1446
Answer C is correct.
The torque reaction of a clockwise turning propeller will cause:
The correct answer is C roll to the left.
A. roll to the right. B. nose up pitch.
References
C. roll to the left. D. nose down pitch.
445. JAAExam.com/ATPL Question ID: 990
Answer C is correct.
Compared with an oblique shock wave at the same Mach number a normal shock wave has a:
The correct answer is C higher compression.
A. smaller compression. B. higher expansion.
References
C. higher compression. D. smaller expansion.
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446. JAAExam.com/ATPL Question ID: 1080
Answer C is correct.
If the aircraft is properly loaded the CG, the neutral point and the manoeuvre point will be in the order given, forward to aft:
The correct answer is C CG, neutral point, manoeuvre point.
A. manoeuvre point, neutral point, CG.
References
B. manoeuvre point, CG, neutral point. C. CG, neutral point, manoeuvre point. D. CG, manoeuvre point, neutral point.
447. JAAExam.com/ATPL Question ID: 512
Answer B is correct.
Which of the following expressions is correct (F=force; m=mass, a=acceleration):
The correct answer is B F=MxA
A. A = F x M B. F = M x A
References
C. M = F x A D. A = M / F
448. JAAExam.com/ATPL Question ID: 936
Answer B is correct.
The transition point located on the wing is the point where...
The correct answer is B
A. airflow starts separating from the wing.
the boundary layer changes from laminar flow to turbulent flow.
B. the boundary layer changes from laminar flow to turbulent flow.
References
C. the static pressure reaches its highest value. D. the airflow changes from subsonic to supersonic flow.
449. JAAExam.com/ATPL Question ID: 1202
Answer A is correct.
An aircraft is approaching to land with its CG at the forward limit. It will be ... to flare and VREF will be ... than normal.
The correct answer is A
A. difficult; higher
difficult; higher References
B. easy; lower C. easy; higher D. difficult; lower
450. JAAExam.com/ATPL Question ID: 1535
Answer A is correct.
Thrust available ... and power available ... as altitude decreases.
The correct answer is A increases; increases
A. increases; increases B. increases; decreases
References
C. decreases; decreases D. decreases; increases
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451. JAAExam.com/ATPL Question ID: 1355
Answer B is correct.
Which of the following statements is correct?
The correct answer is B
A. The use of flaps during severe turbulence reduces the stall speed and the risk of exceeding structural limitations decreases.
Extending flaps in turbulence reduces the stall speed but will reduce the margin to structural limitations.
B. Extending flaps in turbulence reduces the stall speed but will reduce the margin to structural limitations.
References
C. By extending flaps during extreme turbulence, the CP moves aft which will increase the margin to structural limitations. D. By extending flaps during severe turbulence it is possible to reduce speed and increase the margins to structural limitations.
452. JAAExam.com/ATPL Question ID: 533
Answer B is correct.
The mean chord is calculated by:
The correct answer is B
A. dividing the chord by the maximum thickness.
dividing the gross wing area by the wing span.
B. dividing the gross wing area by the wing span.
References
C. dividing the net wing area by the wing span. D. dividing the gross wing area by the root chord.
453. JAAExam.com/ATPL Question ID: 1521
Answer C is correct.
The glide range of an aircraft is affected by:
The correct answer is C
A. aircraft all up weight. B. drag only. C. the lift/drag ratio.
the lift/drag ratio. References
D. the wingspan only.
454. JAAExam.com/ATPL Question ID: 1170
Answer B is correct.
The max aft position of the centre of gravity is amongst others limited by the:
The correct answer is B Yaw damper.
A. Roll spoilers. B. Yaw damper.
References
C. Spoiler mixer. D. Rudder limiter.
455. JAAExam.com/ATPL Question ID: 486
Answer C is correct.
Lift is the component of the total aerodynamic force which is:
The correct answer is C perpendicular to the free stream airflow.
A. perpendicular to the longitudinal axis of the aircraft.
References
B. parallel to the longitudinal axis of the aircraft. C. perpendicular to the free stream airflow. D. parallel to the free stream airflow.
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456. JAAExam.com/ATPL Question ID: 1329
Answer D is correct.
An aircraft is flown at 20% below its normal weight. Because of this, VA will be:
The correct answer is D 10% lower
A. 20% lower B. 10% higher
References
C. 20% higher D. 10% lower
457. JAAExam.com/ATPL Question ID: 1242
Answer C is correct.
When an aileron is deflected downward, it causes:
The correct answer is C
A. an increase in induced drag only. B. an increase in profile drag only. C. an increase in both induced drag and profile drag.
an increase in both induced drag and profile drag. References
D. an increase in lift on that wing area without any drag penalty.
458. JAAExam.com/ATPL Question ID: 1174
Answer B is correct.
Which one of the following systems suppresses the tendency to Dutch roll?
The correct answer is B Yaw damper.
A. Rudder limiter. B. Yaw damper.
References
C. Roll spoilers. D. Spoiler mixer.
459. JAAExam.com/ATPL Question ID: 1159
Answer C is correct.
The effect of a high wing with zero dihedral is as follows:
The correct answer is C Positive dihedral effect.
A. Its only purpose is to ease aeroplane loading.
B. Negative dihedral effect.
References
C. Positive dihedral effect. D. Zero dihedral effect.
460. JAAExam.com/ATPL Question ID: 1018
Answer A is correct.
Tuck under will happen:
The correct answer is A
A. only above the critical Mach number. B. only at the critical Mach number. C. only below the critical Mach number.
only above the critical Mach number. References
D. above or below the critical Mach number depending on the angle of attack.
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461. JAAExam.com/ATPL Question ID: 1100
Answer D is correct.
When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be:
The correct answer is D
A. downwards because it is always negative regardless of the position of the centre of gravity.
downwards. References
B. upwards. C. zero because in steady flight all loads are in equilibrium. D. downwards.
462. JAAExam.com/ATPL Question ID: 807
Answer B is correct.
The normal stall recovery procedure for a light single engined aeroplane is:
The correct answer is B
A. full power and stick roll-neutral nose-down, correction for angle of bank with stick. B. full power and stick roll-neutral nose-down, correcting for angle of bank with rudder.
full power and stick roll-neutral nose-down, correcting for angle of bank with rudder. References
C. idle power and stick roll-neutral nose-down and no other corrections. D. idle power and stick neutral, waiting for the natural nose-down tendency.
463. JAAExam.com/ATPL Question ID: 731
Answer B is correct.
If you are flying at 100 kts and you increase your airspeed to 200 kts, profile drag:
The correct answer is B quadruples.
A. increases with 100%.
B. quadruples.
References
C. decreases with 200%. D. remains the same.
464. JAAExam.com/ATPL Question ID: 1430
Answer A is correct.
Which is one of the disadvantages of increasing the number of propeller blades?
The correct answer is A Decrease propeller efficiency.
A. Decrease propeller efficiency. B. Increased noise.
References
C. Less power can be absorbed by the propeller. D. Higher tip-speed.
465. JAAExam.com/ATPL Question ID: 628
Answer D is correct.
What is true regarding deployment of Slats / Krueger flaps?
The correct answer is D Slats form a slot, Krueger flaps do not.
A. Slats increase the critical angle of attack, Krueger flaps do not.
References
B. Krueger flaps increase the critical angle of attack, Slats do not. C. Krueger flaps form a slot, Slats do not. D. Slats form a slot, Krueger flaps do not.
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466. JAAExam.com/ATPL Question ID: 1110
Answer B is correct.
If the radius of a turn, flown at constant IAS is increased, the angle of bank will:
The correct answer is B decrease.
A. increase. B. decrease.
References
C. remain the same. D. change proportional to the change of the radius.
467. JAAExam.com/ATPL Question ID: 1319
Answer B is correct.
Which speed represents the manoeuvring speed?
The correct answer is B
A. Vso B. Va C. Vlo D. Vne
Va References
468. JAAExam.com/ATPL Question ID: 1315
Answer D is correct.
In transonic flight the ailerons will be less effective than in subsonic flight because:
The correct answer is D
A. aileron deflection only affects the air in front of the shock wave. B. behind the shock wave pressure is lower.
aileron deflection only partly affects the pressure distribution around the wing. References
C. aileron down deflection moves the shock wave forward. D. aileron deflection only partly affects the pressure distribution around the wing.
469. JAAExam.com/ATPL Question ID: 506
Answer A is correct.
What phenomena causes induced drag?
The correct answer is A
A. Wing tip vortices. B. Wing tanks. C. The increased pressure at the leading edge.
Wing tip vortices. References
D. The span wise flow, inward below the wing and outward above.
470. JAAExam.com/ATPL Question ID: 534
Answer C is correct.
Consider a uniform flow of air at velocity V in a Stream tube. If the temperature of the air in the tube is raised:
The correct answer is C
A. the mass flow remains constant and velocity V decreases.
the mass flow will decrease and velocity V will remain constant. References
B. the mass flow will increase and velocity V remain constant C. the mass flow will decrease and velocity V will remain constant. D. the mass flow remains constant and the velocity V will increase.
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471. JAAExam.com/ATPL Question ID: 1295
Answer A is correct.
What is the position of the elevator in relation to the trimmable horizontal stabilizer of a power assisted aeroplane, which is in trim?
The correct answer is A
A. The position depends on speed, the position of slats and flaps and the position of the centre of gravity. B. The elevator deflection (compared to the stabilizer position) is always zero. C. At a forward CG the elevator is deflected upward and at an aft CG the elevator is deflected downward.
The position depends on speed, the position of slats and flaps and the position of the centre of gravity. References
D. The elevator is always deflected slightly downwards in order to have sufficient remaining flare capability.
472. JAAExam.com/ATPL Question ID: 721
Answer D is correct.
The speed in flight at which the power required is at a minimum, is: References A. usually a constant at all altitudes. B. minimum drag speed Vmd. C. above Vmd. D. below Vmd.
473. JAAExam.com/ATPL Question ID: 652
Answer D is correct.
For large Reynolds numbers, the... forces are of much greater importance than the... forces.
The correct answer is D inertia, viscosity
A. hear, viscosity B. pressure, bending
References
C. viscosity, inertia D. inertia, viscosity
474. JAAExam.com/ATPL Question ID: 543
Answer B is correct.
Bernoulli’ s equation can be written as (pt = total pressure, ps = static pressure, q = dynamic pressure):
The correct answer is B
A. pt = ps - q
pt - q = ps References
B. pt - q = ps C. pt + ps = q D. pt = q - ps
475. JAAExam.com/ATPL Question ID: 856
Answer C is correct.
The input to a stick shaker comes from:
The correct answer is C
A. the airspeed, and sometimes the rate of change in airspeed. B. the angle of incidence. C. angle of attack, and sometimes the rate of change in angle of attack.
angle of attack, and sometimes the rate of change in angle of attack. References
D. the angle of attack only.
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476. JAAExam.com/ATPL Question ID: 550
Answer B is correct.
If pressure is kept constant and temperature increases, the density:
The correct answer is B decreases.
A. increases. B. decreases.
References
C. remains constant. D. temperature have no effect.
477. JAAExam.com/ATPL Question ID: 773
Answer A is correct.
Stall speed in a turn is proportional to:
The correct answer is A
A. the square root of the load factor. B. weight. C. lift.
the square root of the load factor. References
D. TAS squared.
478. JAAExam.com/ATPL Question ID: 1186
Answer A is correct.
Rudder controls:
The correct answer is A
A. Yaw. B. Pitch. C. Roll.
Yaw. References
D. Turn.
479. JAAExam.com/ATPL Question ID: 547
Answer D is correct.
Assuming ISA conditions, which statement with respect to the climb is correct?
The correct answer is D At constant IAS the Mach number increases.
A. At constant TAS the Mach number decreases. B. At constant Mach number the IAS increases.
References
C. At constant IAS the TAS decreases. D. At constant IAS the Mach number increases.
480. JAAExam.com/ATPL Question ID: 1492
Answer C is correct.
When an aircraft is in a climb at a constant indicated airspeed:
The correct answer is C
A. thrust is equal to the component of weight acting along the flight path. B. thrust is less than the aerodynamic drag. C. the aerodynamic drag component is less than
the aerodynamic drag component is less than the thrust. References
the thrust. D. thrust is exactly equal to the aerodynamic drag component.
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481. JAAExam.com/ATPL Question ID: 1016
Answer A is correct.
The application of the area rule on aeroplane design will decrease the:
The correct answer is A wave drag.
A. wave drag. B. skin friction drag.
References
C. induced drag. D. form drag.
482. JAAExam.com/ATPL Question ID: 1107
Answer B is correct.
If the centre of gravity is aft of the limits:
The correct answer is B
A. longitudinal stability is unaffected. B. the aircraft becomes unstable. C. longitudinal stability is improved.
the aircraft becomes unstable. References
D. lateral stability is improved.
483. JAAExam.com/ATPL Question ID: 1060
Answer B is correct.
The shock wave angle of a supersonic aircraft at increasing Mach number:
The correct answer is B decreases.
A. remain the same. B. decreases.
References
C. increases. D. decreases, then increases above certain Mach number.
484. JAAExam.com/ATPL Question ID: 1383
Answer D is correct.
If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
The correct answer is D
A. decrease and the rate of descent will increase. B. increase and the rate of descent will increase. C. decrease and the rate of descent will decrease. D. increase and the rate of descent will decrease.
increase and the rate of descent will decrease. References
485. JAAExam.com/ATPL Question ID: 785
Answer D is correct.
The most common stall sensing devices are normally located:
The correct answer is D at or near the wing leading edge.
A. on the upper surface of the wing. B. on the lower surface of the wing.
References
C. at the transition point. D. at or near the wing leading edge.
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486. JAAExam.com/ATPL Question ID: 1266
Answer C is correct.
Aerodynamic balance can be obtained by:
The correct answer is C
A. a weight mounted forward of the control surface hinge line. B. an external balance, provided by a seal from the wing to the trailing edge of the aileron. C. an internal balance (the leading edge of the aileron is housed within a box inside the wing trailing edge, vented to atmosphere, with a seal from the wing to the leading edge of the aileron).
an internal balance (the leading edge of the aileron is housed within a box inside the wing trailing edge, vented to atmosphere, with a seal from the wing to the leading edge of the aileron). References
D. the down going aileron moving through a smaller angle than the up going aileron.
487. JAAExam.com/ATPL Question ID: 1251
Answer D is correct.
A secondary effect of using left rudder in level flight would be:
The correct answer is D roll to the left.
A. yaw to the right. B. roll to the right.
References
C. yaw to the left. D. roll to the left.
488. JAAExam.com/ATPL Question ID: 761
Answer D is correct.
In straight and level flight, if airspeed ... the angle of attack ... and the incidence angle...
The correct answer is D decreases; increases; remains constant.
A. increases; decreases; decreases. B. increases; increases; decreases.
References
C. decreases; decreases; decreases. D. decreases; increases; remains constant.
489. JAAExam.com/ATPL Question ID: 942
Answer C is correct.
If ice is present on the leading edge of the wings, it may increase the landing distance due to higher Vth with: A. 5-10 %
The correct answer is C 30-40 % References
B. 10-20 % C. 30-40 % D. 40-50 %
490. JAAExam.com/ATPL Question ID: 1088
Answer D is correct.
Tuck under may happen at:
The correct answer is D
A. low Mach numbers. B. all Mach numbers. C. only at low altitudes.
high Mach numbers. References
D. high Mach numbers.
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491. JAAExam.com/ATPL Question ID: 632
Answer A is correct.
On a swept back wing, in which of the following locations would Krueger Flaps be fitted?
The correct answer is A Inboard leading edge.
A. Inboard leading edge. B. Outboard leading edge.
References
C. The leading edge. D. The trailing edge.
492. JAAExam.com/ATPL Question ID: 1402
Answer C is correct.
The propeller blade angle of attack on a fixed pitch propeller is increased when:
The correct answer is C RPM increases and forward velocity decreases.
A. forward velocity increases and RPM decreasing.
References
B. velocity and RPM increase. C. RPM increases and forward velocity decreases. D. velocity and RPM decrease.
493. JAAExam.com/ATPL Question ID: 924
Answer B is correct.
The lift coefficient CL of a wing at a given angle of attack:
The correct answer is B is increased by the use of high lift devices.
A. is dependent on the surface area of the wing.
B. is increased by the use of high lift devices.
References
C. is constant and not affected by high lift devices. D. is reduced when high lift devices are used.
494. JAAExam.com/ATPL Question ID: 1483
Answer B is correct.
In order to achieve the maximum rate of climb, aircraft should be flown at the indicated airspeed which:
The correct answer is B
A. gives the best lift/drag ratio.
gives maximum excess power. References
B. gives maximum excess power. C. gives the best thrust/drag ratio. D. gives the best speed/drag ratio.
495. JAAExam.com/ATPL Question ID: 870
Answer A is correct.
Vortex generators:
The correct answer is A
A. transfer energy from the free airflow into the boundary layer.
transfer energy from the free airflow into the boundary layer.
B. change the turbulent boundary layer into a laminar boundary layer.
References
C. reduce the span wise flow on swept wing. D. take kinetic energy out of the boundary layer to reduce separation.
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496. JAAExam.com/ATPL Question ID: 1441
Answer D is correct.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect in the climb will:
The correct answer is D yaw the aeroplane to the left.
A. roll the aeroplane to the right. B. roll the aeroplane to the left.
References
C. yaw the aeroplane to the right. D. yaw the aeroplane to the left.
497. JAAExam.com/ATPL Question ID: 911
Answer B is correct.
Refer to Figure: 081-12
note that "Krueger Flaps" are also generically known as "leading edge flaps" in places.
(Refer to figure 081-12) The high lift device shown in the figure is a: A. Slot or slat. B. Krueger flap.
References
C. Fowler flap. D. Slotted flap.
498. JAAExam.com/ATPL Question ID: 572
Answer C is correct.
When does P-factor cause the airplane to yaw to the left?
The correct answer is C When the angle of attack on both wings is high.
A. In a vertical dive. B. When the angle of attack on both wings is low.
References
C. When the angle of attack on both wings is high. D. When the aircraft is flying at high airspeeds.
499. JAAExam.com/ATPL Question ID: 913
Answer A is correct.
A plain flap will increase CLmax by:
The correct answer is A
A. increasing the camber of the aerofoil. B. increasing angle of attack. C. boundary layer control.
increasing the camber of the aerofoil. References
D. centre of lift movement.
500. JAAExam.com/ATPL Question ID: 1554
Answer C is correct.
In a steady unaccelerated descent:
The correct answer is C
A. thrust is greater than drag, lift is less than weight.
thrust is less than drag, lift less than weight.
B. lift is greater than weight, thrust less than drag.
References
C. thrust is less than drag, lift less than weight. D. thrust is equal to drag, lift equal to weight.
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501. JAAExam.com/ATPL Question ID: 1542
Answer B is correct.
In a steady climb:
The correct answer is B
A. thrust equals drag plus the weight component perpendicular to the flight path and lift equals the weight component along the flight path.
thrust equals drag plus the weight component along the flight path and lift equals the weight component perpendicular to the flight path.
B. thrust equals drag plus the weight component along the flight path and lift equals the weight component perpendicular to the flight path.
References
C. thrust equals the weight component along the flight path and lift equals the sum of the components of drag and weight along the
flight path. D. if the angle of climb is 20 deg, lift equals weight times sin(20 deg).
502. JAAExam.com/ATPL Question ID: 1351
Answer C is correct.
What effect will gusts and turbulence have on the load factor of an airplane when it changes its airspeed?
The correct answer is C
A. Airspeed has no influence on the load factor.
Load factor increases as airspeed increases. References
B. Load factor decreases as airspeed increases. C. Load factor increases as airspeed increases. D. The load factor can increase or decrease, depending on the weight of the aircraft.
503. JAAExam.com/ATPL Question ID: 492
Answer B is correct.
The following unit of measurement kgm/s2 is expressed in the SI-system as:
Note:
A. Pascal.
kg m/s = Pascal kg m/s2 = Newton
B. Newton. C. Joule.
References
D. Watt.
504. JAAExam.com/ATPL Question ID: 1316
Answer A is correct.
When flying at speeds above VA:
The correct answer is A
A. full elevator deflection may result in damage to the airframe or structural failure. B. an overspeed warning will be activated. C. the aircraft may self-destruct in a turn.
full elevator deflection may result in damage to the airframe or structural failure. References
D. the aircraft cannot be stalled.
505. JAAExam.com/ATPL Question ID: 1068
Answer C is correct.
If the total sum of moments about one of its axis is not zero, an aeroplane:
The correct answer is C
A. would fly a path with a constant curvature. B. would be difficult to control. C. would experience an angular acceleration about that axis. D. would not be affected because the situation is normal.
would experience an angular acceleration about that axis. References
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506. JAAExam.com/ATPL Question ID: 972
Answer A is correct.
The maximum acceptable cruising altitude is limited by a minimum acceptable load factor because exceeding that altitude:
The correct answer is A
A. turbulence may induce Mach buffet.
turbulence may induce Mach buffet. References
B. turbulence may exceed the limit load factor. C. a sudden necessary bank angle may exceed the limit load factor. D. Mach buffet will occur immediately.
507. JAAExam.com/ATPL Question ID: 1481
Answer B is correct.
An aeroplane is in a steady turn, at a constant TAS of 300 kt, and a bank angle of 45° . Its turning radius is equal to:
The correct answer is B
A. 3.354 metres.
2.381 metres. References
B. 2.381 metres. C. 4.743 metres. D. 9.000 metres.
508. JAAExam.com/ATPL Question ID: 1199
Answer A is correct.
Which of the following devices is used to counter adverse yaw on rolling into or out of a turn?
The correct answer is A Differential ailerons.
A. Differential ailerons. B. A yaw damper.
References
C. A dorsal fin. D. Vortex generators.
509. JAAExam.com/ATPL Question ID: 1436
Answer B is correct.
The thickness of a propeller blade ... from root to tip.
The correct answer is B
A. increases B. decreases C. remains constant
decreases References
D. increases or decreases depending on the propeller pitch angle
510. JAAExam.com/ATPL Question ID: 553
Answer A is correct.
The angle between the aeroplane longitudinal axis and the chord line is the:
The correct answer is A angle of incidence.
A. angle of incidence.
References
B. glide path angle. C. angle of attack. D. climb path angle.
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511. JAAExam.com/ATPL Question ID: 1229
Answer C is correct.
When an airplane is rotating about the longitudinal axis (roll), the down going wing:
The correct answer is C
A. creates a force to increase the roll rate.
creates a damping moments, which resists the rolling motion.
B. generates a higher lift compared to the up going wing.
References
C. creates a damping moments, which resists the rolling motion. D. has a reduced angle of attack.
512. JAAExam.com/ATPL Question ID: 914
Answer B is correct.
If a smaller flap setting is selected for take-off compared to a larger angle of flap selection:
The correct answer is B stalling speed, V2, VR and VLOF all increase.
A. stalling speed and V2 both decrease, while VR and VLOF both increase.
References
B. stalling speed, V2, VR and VLOF all increase. C. VR and VLOF decrease and the stalling speed remains the same. D. the stalling speed decreases and V2, VR and VLOF remain the same.
513. JAAExam.com/ATPL Question ID: 1425
Answer B is correct.
The number of blades in a propeller would be increased:
The correct answer is B to increase power absorption capability.
A. to increase the efficiency of the variable pitch mechanism.
References
B. to increase power absorption capability. C. to reduce noise. D. to enable a longer undercarriage to be fitted.
514. JAAExam.com/ATPL Question ID: 1552
Answer C is correct.
The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with:
The correct answer is C
A. V
1/V2 References
B. 1/V C. 1/V2 D. v2
515. JAAExam.com/ATPL Question ID: 1133
Answer A is correct.
The effect of a swept wing is to give:
The correct answer is A
A. positive dihedral effect. B. negative dihedral effect. C. decreased roll-with-yaw effect.
positive dihedral effect. References
D. adverse yaw effect.
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516. JAAExam.com/ATPL Question ID: 1053
Answer B is correct.
In supersonic flight aerofoil pressure distribution is:
The correct answer is B
A. irregular. B. rectangular. C. triangular.
rectangular. References
D. the same as in subsonic flight.
517. JAAExam.com/ATPL Question ID: 818
Answer B is correct.
The critical angle of attack:
The correct answer is B
A. changes with an increase in gross weight.
remains unchanged regardless of gross weight.
B. remains unchanged regardless of gross weight.
References
C. increases if the CG is moved forward. D. decreases if the CG is moved aft.
518. JAAExam.com/ATPL Question ID: 1366
Answer B is correct.
When there is no oil flow to or from the actuator of the CSU, the propeller is:
The correct answer is B on speed.
A. pitch-locked. B. on speed.
References
C. under speeding. D. overspeeding.
519. JAAExam.com/ATPL Question ID: 1308
Answer B is correct.
In a high speed descent at MMO you will reach VMO at:
The correct answer is B FL270
A. M0.8 B. FL270
References
C. 350kts D. FL250
520. JAAExam.com/ATPL Question ID: 1313
Answer B is correct.
What is the danger when recovering from an emergency descent?
The correct answer is B Structural damage.
A. Engine stall. B. Structural damage.
References
C. Directional stability. D. The landing gear may collapse.
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521. JAAExam.com/ATPL Question ID: 1339
Answer D is correct.
Which load factor determines VA?
The correct answer is D
A. manoeuvring flap limit load factor. B. manoeuvring ultimate load factor. C. gust load factor at 66 ft/sec gust.
manoeuvring limit load factor References
D. manoeuvring limit load factor
522. JAAExam.com/ATPL Question ID: 1215
Answer C is correct.
An aircraft is maintaining height and heading with the left engine inoperative and 5deg of bank toward the live engine. Which of the following indications will be displayed?
The correct answer is C
A. Turn indicator right, ball to the right.
Turn indicator neutral, ball to the right. References
B. Turn indicator left, ball to the left. C. Turn indicator neutral, ball to the right. D. Turn indicator neutral, ball to the left.
523. JAAExam.com/ATPL Question ID: 467
Answer A is correct.
If temperature in a gas is kept constant and pressure increases, the density:
The correct answer is A increases.
A. increases.
B. decreases.
References
C. remains constant. D. Nove of the above - it depends on the type of gas.
524. JAAExam.com/ATPL Question ID: 1490
Answer A is correct.
By what percentage does the lift increase in a steady level turn at 45° angle of bank, compared to straight and level flight?
The correct answer is A
A. 41%
41% References
B. 19% C. 31% D. 52%
525. JAAExam.com/ATPL Question ID: 601
Answer C is correct.
Which of the following is the most effective type of flap system?
The correct answer is C Fowler.
A. Slotted. B. Split.
References
C. Fowler. D. Plain.
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526. JAAExam.com/ATPL Question ID: 815
Answer C is correct.
Which combination of design features is known to be responsible for deep stall:
The correct answer is C Swept back wings and a T-tail.
A. Swept back wings and wing mounted engines. B. Straight wings and a T-tail.
References
C. Swept back wings and a T-tail. D. Straight wings and aft fuselage mounted engines.
527. JAAExam.com/ATPL Question ID: 501
Answer B is correct.
At a given CAS an aircraft flying below sea level will have:
The correct answer is B a lower TAS than at sea level.
A. the same TAS as at sea level. B. a lower TAS than at sea level. C. a higher TAS than at sea level. D. the same TAS as at sea level but an increased IAS.
References
528. JAAExam.com/ATPL Question ID: 868
Answer B is correct.
Which of the following statements about the difference between Krueger flaps and slats is correct?
The correct answer is B
A. Deploying a Krueger flap will increase critical angle of attack, deploying a slat does not.
Deploying a slat will form a slot deploying a Krueger flap does not. References
B. Deploying a slat will form a slot deploying a Krueger flap does not. C. Deploying a Krueger flap will form a slot, deploying a slat does not. D. Deploying a slat will increase critical angle of attack, deploying a Krueger flap does not.
529. JAAExam.com/ATPL Question ID: 1309
Answer A is correct.
Aileron reversal can be caused by:
The correct answer is A
A. twisting of the wing above reversal speed. B. frise type ailerons at low angles of attack. C. both A and B.
twisting of the wing above reversal speed. References
D. neither A nor B.
530. JAAExam.com/ATPL Question ID: 496
Answer A is correct.
The SI unit of energy is:
The correct answer is A
A. Joule. B. Watt. C. Ampere.
Joule. References
D. BTU.
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531. JAAExam.com/ATPL Question ID: 635
Answer D is correct.
If IAS is increased from 80 kt to 160 kt at a constant air density TAS will double. What would be the effect on (i) CDI and (ii) DI?
The correct answer is D
A. (i) 2; (ii) 2
(i) 1/16; (ii) 1/4 References
B. (i) 4; (ii) 2 C. (i) 1/4; (ii) 4 D. (i) 1/16; (ii) 1/4
532. JAAExam.com/ATPL Question ID: 738 As the speed of an aircraft at 20,000ft increases,
Answer D is correct.
profile drag: The correct answer is D A. decreases at first, then increases. B. decreases. C. increases at first, then decreases at Mcrit. D. increases as the square of the TAS.
increases as the square of the TAS. References
533. JAAExam.com/ATPL Question ID: 1271
Answer B is correct.
The inputs to the Q feel unit are from:
The correct answer is B
A. static pressure and temperature. B. pitot and static pressures. C. altitude and pitot pressure.
pitot and static pressures. References
D. pitot pressure and total head pressure.
534. JAAExam.com/ATPL Question ID: 806
Answer C is correct.
Which of the following is the correct order of configuration to give an increasing critical angle of attack?
The correct answer is C
A. Clean wing, trailing edge flaps extended, slats extended.
Trailing edge flaps extended, clean wing, slats extended. References
B. Slats extended, clean wing, trailing edge flaps extended. C. Trailing edge flaps extended, clean wing, slats extended. D. Clean wing, slats extended, trailing edge flaps extended.
535. JAAExam.com/ATPL Question ID: 1502
Answer B is correct.
Load factor is defined as the actual lift produced by the wings...
The correct answer is B divided by the total weight of the aircraft.
A. divided by the surface area of the wing. B. divided by the total weight of the aircraft.
References
C. divided by cos(bank angle). D. divided by the aircrafts empty weight.
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536. JAAExam.com/ATPL Question ID: 1390
Answer D is correct.
The angle of attack of a fixed pitch propeller can be
The correct answer is D
increased by: A. reducing power and reducing TAS.
increasing power and reducing TAS. References
B. increasing power and increasing TAS. C. reducing power and increasing TAS. D. increasing power and reducing TAS.
537. JAAExam.com/ATPL Question ID: 1404
Answer A is correct.
The geometric pith of a propeller is:
The correct answer is A
A. the distance it would go forward in one revolution at the blade angle.
the distance it would go forward in one revolution at the blade angle.
B. the angle the blade makes with the plane of rotation.
References
C. the distance the propeller actually moves forward in one revolution. D. the difference between A and C.
538. JAAExam.com/ATPL Question ID: 1545
Answer C is correct.
For an aircraft in a steady climb, what is the relationship between lift, weight, thrust and drag?
The correct answer is C Weight is greater than the lift force.
A. The lift force is greater than weight. B. The lift force is exactly equal to the weight.
References
C. Weight is greater than the lift force. D. Weight plus drag is equal to lift (W + D = L).
539. JAAExam.com/ATPL Question ID: 1035
Answer B is correct.
The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
The correct answer is B
A. buffet.
local sonic flow. References
B. local sonic flow. C. shock wave. D. supersonic flow.
540. JAAExam.com/ATPL Question ID: 1196
Answer B is correct.
A control surface has its limitations in movement by:
The correct answer is B
A. control cable tension. B. primary stops at the surface. C. primary stops at the control column. D. secondary stops at the control column.
primary stops at the surface. References
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541. JAAExam.com/ATPL Question ID: 1424
Answer A is correct.
Why does the blade angle of a propeller change from root to tip?
The correct answer is A
A. To compensate for the increased velocity of the blade tip. B. Cross-sectional segment increases from tip to root.
To compensate for the increased velocity of the blade tip. References
C. To provide increased thrust at root. D. To compensate for the change in geometric cross section.
542. JAAExam.com/ATPL Question ID: 1368
Answer A is correct.
For an aircraft with a right hand propeller, the slipstream rotation will cause:
The correct answer is A yaw to the left.
A. yaw to the left. B. yaw to the right.
References
C. roll to the left. D. roll to the right.
543. JAAExam.com/ATPL Question ID: 608
Answer D is correct.
What is the purpose of a slat on the leading edge?
The correct answer is D
A. Decelerate the air over the top surface.
Allow greater angle of attack.
B. Thicken the laminar boundary layer over the top surface.
References
C. Increase the camber of the wing. D. Allow greater angle of attack.
544. JAAExam.com/ATPL Question ID: 1421
Answer A is correct.
After feathering an engine in flight, how is the propeller of a single acting type being unfeathered?
The correct answer is A
A. By use of oil pressure stored in a hydraulic accumulator. B. By the action of the spring in the propeller actuator.
By use of oil pressure stored in a hydraulic accumulator. References
C. With oil pressure generated by an electrically driven pump, with its own oil supply. D. With oil pressure from the CSU booster pump.
545. JAAExam.com/ATPL Question ID: 662
Answer B is correct.
What pitching moment will be generated when Fowler flaps are deployed on an aircraft with a high mounted (T tail) tailplane? A. An aircraft nose up pitching moment.
The correct answer is B An aircraft nose down pitching moment. References
B. An aircraft nose down pitching moment. C. The nose up pitching moment will be balanced by the nose down pitching moment. D. The resultant aircraft pitching moment will depend upon the relative position of the CP and CG.
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546. JAAExam.com/ATPL Question ID: 751
Answer C is correct.
Ground effect is most likely to result in which problem?
The correct answer is C
A. Deep stall. B. Hard landings. C. Becoming airborne before reaching recommended takeoff speed.
Becoming airborne before reaching recommended takeoff speed. References
D. Inability to get airborne even though airspeed is sufficient for normal takeoff needs.
547. JAAExam.com/ATPL Question ID: 1334
Answer D is correct.
What is the limit load factor of a large transport aeroplane in the manoeuvring diagram?
The correct answer is D 2.5
A. 6 B. 1.5
References
C. 3.75 D. 2.5
548. JAAExam.com/ATPL Question ID: 1570
Answer D is correct.
Refer to Figure: 081-01
The correct answer is D
(Refer to figure 081-01) Which point gives minimum speed in level flight on the whole aeroplane polar curve (refer to the picture)?
D
A. A B. B C. C D. D
References
549. JAAExam.com/ATPL Question ID: 742
Answer B is correct.
What is ground effect?
The correct answer is B
A. The effect of hitting the ground. B. The result of interference of the surface of the Earth with the airflow around the wing and tailplane.
The result of interference of the surface of the Earth with the airflow around the wing and tailplane. References
C. The result of an alteration in airflow, increasing induced drag on the wings of an airplane. D. The result of disturbing airflow around the wings of an airplane to the point where the wings will no longer support the airplane in flight.
550. JAAExam.com/ATPL Question ID: 1519
Answer B is correct.
A sailplane has a best glide ratio of 30:1. How many nautical miles will the glider travel while losing 2,000 feet?
The correct answer is B
A. 6000 nautical miles.
10 nautical miles. References
B. 10 nautical miles. C. 15 nautical miles. D. 21 nautical miles.
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551. JAAExam.com/ATPL Question ID: 455
Answer B is correct.
The dynamic pressure increases proportionally with:
The correct answer is B
A. velocity and density. B. density and the square of the velocity. C. the static pressure.
density and the square of the velocity. References
D. velocity and the square of the density.
552. JAAExam.com/ATPL Question ID: 499
Answer C is correct.
A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil. This definition is applicable for:
The correct answer is C
A. the mean aerodynamic chord line.
the camber line. References
B. the chord line. C. the camber line. D. the upper camber line.
553. JAAExam.com/ATPL Question ID: 519
Answer A is correct.
What is the SI unit which results from multiplying kg and m/s squared?
The correct answer is A Newton
A. Newton B. Psi
References
C. Joule D. Watt
554. JAAExam.com/ATPL Question ID: 1087
Answer C is correct.
Which statement about stick force per g is correct?
The correct answer is C
A. The stick force per g can only be corrected by means of electronic devices (stability augmentation) in case of an unacceptable value.
The stick force per g must have both an upper and lower limit in order to assure acceptable control characteristics.
B. The stick force per g increases, when centre of gravity is moved aft.
References
C. The stick force per g must have both an upper and lower limit in order to assure acceptable control characteristics. D. If the slope of the Fe-n line becomes negative, generally speaking this is not a problem for control of an aeroplane.
555. JAAExam.com/ATPL Question ID: 502
Answer B is correct.
The term angle of attack is defined as:
The correct answer is B
A. the angle that determines the magnitude of the lift force.
the angle between the wing chord line and the relative wind.
B. the angle between the wing chord line and the relative wind.
References
C. the angle between the relative airflow and the horizontal axis. D. the angle between the wing and tailplane incidence.
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556. JAAExam.com/ATPL Question ID: 1495
Answer C is correct.
To cover the greatest distance when gliding, the gliding speed must be:
The correct answer is C the one which gives the highest lift/drag ratio.
A. near to the stalling speed. B. as high as possible within V limits. C. the one which gives the highest lift/drag ratio. D. the one that gives the lowest drag.
References
557. JAAExam.com/ATPL Question ID: 567
Answer B is correct.
What is the unit of measurement for power?
The correct answer is B
A. N/m B. Nm/s C. kgm/s2
Nm/s References
D. Pa/m2
558. JAAExam.com/ATPL Question ID: 456
Answer C is correct.
How is the thickness of an aerofoil section measured?
The correct answer is C As the percentage of chord.
A. As the ratio of wing angle. B. Related to camber.
References
C. As the percentage of chord. D. In metres.
559. JAAExam.com/ATPL Question ID: 1084
Answer B is correct.
For a normal stable aeroplane, the centre of gravity is located:
The correct answer is B
A. aft of the neutral point of the aeroplane.
with a sufficient minimum margin ahead of the neutral point of the aeroplane.
B. with a sufficient minimum margin ahead of the neutral point of the aeroplane.
References
C. at the neutral point of the aeroplane. D. between the aft limit and the neutral point of the aeroplane.
560. JAAExam.com/ATPL Question ID: 1260
Answer C is correct.
Some airplanes have spring tabs mounted into the control system: This is to provide:
The correct answer is C
A. feel feedback in a control system. B. constant spring tension to a trim system. C. a reduction in the pilots effort to move the controls against high airloads.
a reduction in the pilots effort to move the controls against high airloads. References
D. reduced control surface loads at all speeds.
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561. JAAExam.com/ATPL Question ID: 1262
Answer D is correct.
To hold a given sideslip angle and airspeed, increased geometric dihedral would:
The correct answer is D increase the stick force.
A. reduce the stick force to zero.
References
B. have no effect on stick force. C. decrease the stick force. D. increase the stick force.
562. JAAExam.com/ATPL Question ID: 800
Answer C is correct.
With increasing angle of attack, the C of P on an airfoil will reach its most forward point:
The correct answer is C at the stalling angle.
A. below the stalling angle. B. above the stalling angle.
References
C. at the stalling angle. D. at various points dependent on aircraft weight.
563. JAAExam.com/ATPL Question ID: 675
Answer C is correct.
With flaps deployed, at a constant IAS in straight and level flight, the magnitude of tip vortices:
The correct answer is C decreases.
A. increases. B. increases or decreases depending upon the initial angle of attack.
References
C. decreases. D. remains the same.
564. JAAExam.com/ATPL Question ID: 1029
Answer D is correct.
The critical Mach Number of an aeroplane can be increased by:
The correct answer is D sweep back of the wings.
A. dihedral of the wings. B. vortex generators.
References
C. control deflection. D. sweep back of the wings.
565. JAAExam.com/ATPL Question ID: 539
Answer D is correct.
If an increase in power tends to make the nose of the aircraft to dip, this is the result of the:
The correct answer is D Line of thrust being above the centre of gravity.
A. Centre of lift being ahead of the centre of gravity. B. Line of thrust passing through the centre of gravity. C. Centre of lift and centre of gravity being collocated. D. Line of thrust being above the centre of
References
gravity.
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566. JAAExam.com/ATPL Question ID: 1413
Answer B is correct.
The purpose of the feathering stop on a variable pitch propeller is to:
The correct answer is B
A. prevent the propeller from feathering above a set RPM. B. prevent the propeller blades from moving beyond the feather position.
prevent the propeller blades from moving beyond the feather position. References
C. allow the blades to be feathered on engine shut down. D. allow the blades to be feathered when ground running.
567. JAAExam.com/ATPL Question ID: 586
Answer B is correct.
Drag is in the direction of - and lift is perpendicular to the:
The correct answer is B relative wind/airflow.
A. chord line. B. relative wind/airflow.
References
C. horizon. D. longitudinal axis.
568. JAAExam.com/ATPL Question ID: 880
Answer D is correct.
When a trailing edge flap is lowered during flight from take-off position to fully down position, one will experience:
The correct answer is D
A. a large increase in lift and a small increase in drag.
a small increase in lift and a large increase in drag. References
B. a large increase in lift and a large increase in drag. C. a small increase in lift and a small increase in drag. D. a small increase in lift and a large increase in drag.
569. JAAExam.com/ATPL Question ID: 869
Answer B is correct.
The function of the slot between an extended slat and the leading edge of the wing is to:
The correct answer is B
A. allow space for vibration of the slat.
cause a venturi effect which energizes the boundary layer.
B. cause a venturi effect which energizes the boundary layer.
References
C. reduce the wing loading. D. slow the air flow in the slot so that more pressure is created under the wing.
570. JAAExam.com/ATPL Question ID: 772
Answer D is correct.
The following factors increase stall speed:
The correct answer is D
A. a lower weight, decreasing bank angle, a smaller flap setting.
an increase in load factor, a forward c.g. shift, decrease in thrust.
B. a higher weight, selecting a higher flap setting, a forward c .g. shift.
References
C. increasing bank angle, increasing thrust, slat extension. D. an increase in load factor, a forward c.g. shift, decrease in thrust.
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571. JAAExam.com/ATPL Question ID: 845
Answer A is correct.
If the straight and level stall speed is 100 kt, what will be the stall speed in a 1.5g turn?
The correct answer is A 122 kts
A. 122 kts B. 150 kts
References
C. 81 kts D. 100 kts
572. JAAExam.com/ATPL Question ID: 14022
Answer A is correct.
Refer to Figure: 081-16
The correct answer is A
Refer to figure 081-16 What type of trailing edge device is shown in this figure?
Plain Flap References
A. Plain Flap B. Slotted Flap C. Split Flap D. Krueger Flap
573. JAAExam.com/ATPL Question ID: 473 The unit of density is: A. Bar B. psi C. kg/cm
Answer D is correct.
Bar and PSI are units of force. kg/cm is a mostly nonsensical unit kg/ml, while somewhat nonstandard, is a unit of density since ml is a unit of volume (=1cm3).
D. kg/ml
References
574. JAAExam.com/ATPL Question ID: 683
Answer C is correct.
An increase in angle of attack (below the stalling angle of attack) increases lift because:
The correct answer is C the lift coefficient increases.
A. induced drag is reduced. B. the vertical component of weight is reduced.
References
C. the lift coefficient increases. D. the impact pressure of the air on the lower surface of the airfoil creates less positive pressure.
575. JAAExam.com/ATPL Question ID: 603
Answer C is correct.
Lift is created over a wing because:
The correct answer is C
A. airflow speed increases over the wing surface causing a increase in dynamic pressure.
airflow accelerates of the top surface of the airfoil creating a reduction in static pressure.
B. airflow slows down on the extrados causing a reduction in static pressure.
References
C. airflow accelerates of the top surface of the airfoil creating a reduction in static pressure. D. airflow slows down over a wing causing an increase in static pressure.
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576. JAAExam.com/ATPL Question ID: 1127
Answer A is correct.
The manoeuvrability of an aeroplane is best when the:
The correct answer is A C.G. is on the aft C.G. limit.
A. C.G. is on the aft C.G. limit. B. speed is low.
References
C. C.G. position is on the forward C.G. limit. D. flaps are down.
577. JAAExam.com/ATPL Question ID: 901
Answer C is correct.
Slats:
The correct answer is C
A. de-energise the boundary layer, thereby decreasing the stalling angle of attack.
re-energise the boundary layer thereby increasing the stalling angle of attack.
B. re-energise the boundary layer thereby decreasing the stalling angle of attack.
References
C. re-energise the boundary layer thereby
increasing the stalling angle of attack. D. de-energise the boundary layer thereby increasing the stalling angle of attack.
578. JAAExam.com/ATPL Question ID: 846
Answer A is correct.
The function of the stick pusher is:
The correct answer is A
A. to activate and push the stick forward at or beyond a certain value of angle of attack.
to activate and push the stick forward at or beyond a certain value of angle of attack.
B. to activate and push the stick forward prior to stick shaker.
References
C. to vibrate the controls. D. to pull the stick, to avoid a high speed stall.
579. JAAExam.com/ATPL Question ID: 997
Answer B is correct.
Shock induced separation results in:
The correct answer is B
A. constant lift. B. decreasing lift. C. increasing lift.
decreasing lift. References
D. decreasing drag.
580. JAAExam.com/ATPL Question ID: 1046
Answer A is correct.
The aft movement of the centre of pressure during the acceleration through the transonic flight regime will:
The correct answer is A
A. increase the static longitudinal stability.
increase the static longitudinal stability. References
B. decrease the longitudinal stability. C. increase the static lateral stability. D. decrease the static lateral stability.
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581. JAAExam.com/ATPL Question ID: 1292
Answer A is correct.
Which statement about the trim position is true related to centre of gravity and adjustable stabiliser position?
The correct answer is A
A. A nose heavy aeroplane requires that the stabiliser leading edge is lower than compared with a tail heavy aeroplane. B. Because characteristic speeds at take off do not vary with centre of gravity location, the need for stabiliser adjustment is dependent on flap position only.
A nose heavy aeroplane requires that the stabiliser leading edge is lower than compared with a tail heavy aeroplane. References
C. A nose heavy aeroplane requires that the stabiliser leading edge is higher than compared with a tail heavy aeroplane. D. At the forward limit for centre of gravity, stabiliser trim is adjusted maximum Nose Down to obtain maximum elevator authority at take off rotation.
582. JAAExam.com/ATPL Question ID: 951
Answer B is correct.
The maximum obtainable lift coefficient ... when the Mach-number...
The correct answer is B decreases, increases.
A. increases, decreases. B. decreases, increases.
References
C. stays the same, increases. D. decreases, decreases.
583. JAAExam.com/ATPL Question ID: 1165
Answer C is correct.
The pendulum effect on a high wing aeroplane:
The correct answer is C
A. reduces lateral stability. B. reduces longitudinal stability. C. improves lateral stability.
improves lateral stability. References
D. has no effect on lateral stability.
584. JAAExam.com/ATPL Question ID: 797
Answer D is correct.
The stalling speed in IAS will change according to the following factors?
The correct answer is D
A. Will increase with increased load factor, more flaps and increased bank angle in a turn. B. May increase when the c.g. moves forward, with higher altitude and due to the slip stream from a propellor on an engine located forward of the wing.
May increase with altitude, especially high altitude, will increase during icing conditions and will increase when the c.g. moves forward. References
C. Will increase in a turn, higher temperature and will increase when the c.g. moves aft. D. May increase with altitude, especially high altitude, will increase during icing conditions and will increase when the c.g. moves forward.
585. JAAExam.com/ATPL Question ID: 1135
Answer B is correct.
One function of the Mach trim is to:
The correct answer is B
A. adjust the stick force per g gradient.
maintain the required stick force gradient.
B. maintain the required stick force gradient.
References
C. adjust for aileron reversal. D. trim the aircraft nose down.
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586. JAAExam.com/ATPL Question ID: 1235
Answer B is correct.
Which motion occurs about the longitudinal axis?
The correct answer is B
A. Sideslip. B. Rolling. C. Pitching.
Rolling. References
D. Yawing.
587. JAAExam.com/ATPL Question ID: 568
Answer C is correct.
For an aircraft in level flight, if the wing center of pressure is aft of the center of gravity and there is no thrust/drag couple, the tailplane load must be:
The correct answer is C
A. upward.
downward. References
B. unknown-insufficient information has been provided. C. downward. D. zero.
588. JAAExam.com/ATPL Question ID: 726
Answer C is correct.
The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
The correct answer is C square of the speed.
A. angle of attack. B. square of the angle of attack.
References
C. square of the speed. D. speed.
589. JAAExam.com/ATPL Question ID: 1548
Answer B is correct.
Which of the following will give an increase of ground range when gliding at VDmin?
The correct answer is B A tailwind.
A. Increased weight. B. A tailwind. C. A headwind. D. Decreased weight.
References
590. JAAExam.com/ATPL Question ID: 1274
Answer A is correct.
Control surface overbalancing may be the result of:
The correct answer is A
A. the control surface centre of pressure being located in front of the surface hinge line. B. applying excessive force to the controls. C. a sudden movement of the centre of pressure aft of the surface hinge line.
the control surface centre of pressure being located in front of the surface hinge line. References
D. bad pilot skills.
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591. JAAExam.com/ATPL Question ID: 636
Answer B is correct.
A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor:
The correct answer is B
A. 4
2 References
B. 2 C. 8 D. 1.4
592. JAAExam.com/ATPL Question ID: 905
Answer A is correct.
It is possible to reduce the span wise airflow over swept wings, due to adverse pressure gradients, by:
The correct answer is A wing fences.
A. wing fences. B. trailing edge vortex generators.
References
C. increased anhedral. D. leading edge stall inducers.
593. JAAExam.com/ATPL Question ID: 686
Answer C is correct.
Induced drag is created by the:
The correct answer is C
A. separation of the boundary layer over the wing.
span wise flow pattern resulting in the tip vortices.
B. interference of the air stream between wing and fuselage.
References
C. span wise flow pattern resulting in the tip vortices. D. propeller wash blowing across the wing.
594. JAAExam.com/ATPL Question ID: 957
Answer D is correct.
Reducing the thickness/chord ratio on a wing will:
The correct answer is D
A. reduce the transonic variations in drag coefficient.
all of the above.
B. reduce the transonic variations in lift coefficient.
References
C. delay the onset of shockwave formation. D. all of the above.
595. JAAExam.com/ATPL Question ID: 1154
Answer B is correct.
Dihedral of the wing:
The correct answer is B
A. is the only way to increase the static lateral stability.
increases the static lateral stability.
B. increases the static lateral stability.
References
C. is only positive for aeroplanes with high mounted wings. D. decreases the static lateral stability.
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596. JAAExam.com/ATPL Question ID: 1013
Answer C is correct.
Compared with an oblique shock wave at the same Mach number a normal shock wave has a:
The correct answer is C higher loss in total pressure.
A. higher total temperature. B. higher total pressure.
References
C. higher loss in total pressure. D. lower static temperature.
597. JAAExam.com/ATPL Question ID: 1082
Answer B is correct.
Loading an airplane to the aft centre of gravity limit will cause the airplane to be:
The correct answer is B less stable for all airspeeds.
A. more stable for all airspeeds. B. less stable for all airspeeds.
References
C. less stable at slow speed, but more stable at high speed. D. less stable at high speed, but more stable at low speed.
598. JAAExam.com/ATPL Question ID: 642
Answer B is correct.
CDI is proportional to which of the following?
The correct answer is B CL2
A. CLmax
References
B. CL2 C. the square root of the CL D. CL
599. JAAExam.com/ATPL Question ID: 1228
Answer C is correct.
How is adverse yaw compensated for during entry into and roll out from a turn?
The correct answer is C Differential aileron deflection.
A. Anti-balanced rudder control. B. Horn-balanced controls.
References
C. Differential aileron deflection. D. Servo tabs.
600. JAAExam.com/ATPL Question ID: 1536
Answer A is correct.
If VS1G is 100kt, the stalling speed in a 45° bank level turn will be:
The correct answer is A 119 kts
A. 119 kts B. 80 kts
References
C. 141 kts D. 100 kts
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601. JAAExam.com/ATPL Question ID: 950
Answer A is correct.
A jet aeroplane is cruising at high altitude with a Mach-number, that provides a buffet margin of 0.3g incremental. In order to increase the buffet margin to 0.4g incremental the pilot must:
The correct answer is A
A. fly at a lower altitude and the same Machnumber.
fly at a lower altitude and the same Mach-number. References
B. extend the flaps to the first selection. C. fly at a higher Mach-number. D. fly at a larger angle of attack.
602. JAAExam.com/ATPL Question ID: 1190
Answer D is correct.
During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection:
The correct answer is D downward on the up going wing and upward on the down going wing.
A. on the down going wing only. B. upward on the up going wing and downward on the down going wing.
References
C. on the up going wing only. D. downward on the up going wing and upward on the down going wing.
603. JAAExam.com/ATPL Question ID: 1238
Answer D is correct.
The ailerons on the wing of an aircraft are used for:
The correct answer is D
A. longitudinal control about the normal axis. B. longitudinal control about the lateral axis. C. lateral control about the lateral axis.
lateral control about the longitudinal axis. References
D. lateral control about the longitudinal axis.
604. JAAExam.com/ATPL Question ID: 874
Answer C is correct.
During the extension of the flaps at a constant angle of attack the aeroplane starts to: (all other factors of importance being constant)
The correct answer is C
A. sink suddenly.
climb. References
B. bank. C. climb. D. yaw.
605. JAAExam.com/ATPL Question ID: 573
Answer D is correct.
As subsonic air flows through a convergent duct:
The correct answer is D
i. ii.
static pressure velocity
(i) decreases and (ii) increases References
A. (i) increases and (ii) decreases B. (i) increases and (ii) increases C. (i) decreases and (ii) decreases D. (i) decreases and (ii) increases
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606. JAAExam.com/ATPL Question ID: 1246
Answer A is correct.
Which moments or motions interact in a Dutch roll?
The correct answer is A
A. Rolling and yawing. B. Pitching and yawing. C. Pitching and rolling. D. Pitching and adverse yaw.
Rolling and yawing. References
607. JAAExam.com/ATPL Question ID: 949
Answer C is correct.
The speed of sound is affected by the:
The correct answer is C
A. pressure of the air. B. density of the air. C. temperature of the air.
temperature of the air. References
D. humidity of the air.
608. JAAExam.com/ATPL Question ID: 1108
Answer B is correct.
What determines the longitudinal stability of an airplane?
The correct answer is B
A. The weight of an aircraft.
The location of the CG with respect to the neutral point of the airplane.
B. The location of the CG with respect to the neutral point of the airplane.
References
C. The effectiveness of the horizontal stabilizer, rudder and rudder trim tab. D. The relationship between lift and drag.
609. JAAExam.com/ATPL Question ID: 1417
Answer D is correct.
With a propeller feathered:
The correct answer is D
A. the best windmilling speed is achieved.
there will be minimum drag on the propeller.
B. the engine will turn over just fast enough to lubricate it.
References
C. there will be minimum lift to drag ratio. D. there will be minimum drag on the propeller.
610. JAAExam.com/ATPL Question ID: 1478
Answer D is correct.
How many feet will a sailplane sink in 15 nautical miles if its lift/drag ratio is 22:1?
The correct answer is D 4,100 feet
A. 5,200 feet B. 2,700 feet
References
C. 3,600 feet D. 4,100 feet
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611. JAAExam.com/ATPL Question ID: 1090
Answer D is correct.
What is the effect of an aft shift of the centre of gravity on
The correct answer is D (1) reduces (2) reduces
1.
static longitudinal stability and
2.
the required control deflection for a given pitch change?
References
A. (1) reduces (2) increases B. (1) increases (2) increases C. (1) increases (2) reduces D. (1) reduces (2) reduces
612. JAAExam.com/ATPL Question ID: 644
Answer A is correct.
An increase in the speed at which an airfoil passes through the air increases lift because:
The correct answer is A
A. the increased speed of air passing over the airfoils upper surface decreases the pressure, thus creating a greater pressure differential between upper and lower surface. B. the increased speed of the airflow creates a lesser pressure differential between The upper and lower airfoil surfaces.
the increased speed of air passing over the airfoils upper surface decreases the pressure, thus creating a greater pressure differential between upper and lower surface. References
C. the increased velocity of the relative wind increases the angle of attack. D. the impact pressure of the air on the lower surface of the airfoil creates less positive pressure.
613. JAAExam.com/ATPL Question ID: 1232
Answer C is correct.
Differential aileron deflection:
The correct answer is C
A. increases the CLmax.
equals the drag of the right and left aileron.
B. is required to keep the total lift constant when ailerons are deflected.
References
C. equals the drag of the right and left aileron. D. is required to achieve the required roll-rate.
614. JAAExam.com/ATPL Question ID: 1517
Answer C is correct.
A jet aeroplane is rolled into a turn, while maintaining airspeed and holding altitude. In such a case, the pilot has to:
The correct answer is C
A. increase thrust and decrease angle of attack.
increase thrust and angle of attack. References
B. increase thrust and keep angle of attack unchanged. C. increase thrust and angle of attack. D. increase angle of attack and keep thrust unchanged.
615. JAAExam.com/ATPL Question ID: 1401
Answer B is correct.
When forward speed ..., the ... of the propeller blades (fixed pitch)...
The correct answer is B increases, angle of attack, decreases.
A. increases, blade angle, increases. B. increases, angle of attack, decreases.
References
C. increases, angle of attack, increases. D. increases, blade angle, decreases.
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616. JAAExam.com/ATPL Question ID: 697
Answer C is correct.
Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
The correct answer is C CL? and AR (aspect ratio).
A. CL and b (wing span). B. CL and CD.
References
C. CL? and AR (aspect ratio). D. CL? and S (wing surface).
617. JAAExam.com/ATPL Question ID: 824
Answer C is correct.
An aeroplane has a stall speed of 100 kt at a load factor n=1. In a turn with a load factor of n=2, the stall speed is:
The correct answer is C
A. 70 kts
141 kts References
B. 282 kts C. 141 kts D. 200 kts
618. JAAExam.com/ATPL Question ID: 1321
Answer B is correct.
A commercial jet aeroplane is performing a straight descent at a constant Mach Number with constant weight. The operational limit that may be exceeded is:
The correct answer is B
A. MMO
VMO References
B. VMO C. VNE D. VD
619. JAAExam.com/ATPL Question ID: 1505
Answer C is correct.
A particular SID requires a minimum climb gradient of 210 feet per NM to 8,000 feet. If you climb with a groundspeed of 140 knots, what is the rate of climb
The correct answer is C
required in feet per minute? A. 304
490 References
B. 210 C. 490 D. 450
620. JAAExam.com/ATPL Question ID: 1115
Answer D is correct.
When the CG is close to the forward limit:
The correct answer is D
A. very small forces are required on the control column to produce pitch. B. longitudinal stability is reduced. C. the stalling speed is reduced.
very high stick forces are required in pitch because the aircraft is very stable. References
D. very high stick forces are required in pitch because the aircraft is very stable.
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621. JAAExam.com/ATPL Question ID: 1169
Answer B is correct.
Longitudinal dynamic oscillation takes two forms. One of these, long period oscillation, involves slow changes in:
The correct answer is B
A. height and load factor.
height and speed. References
B. height and speed. C. pitch and load factor. D. speed and load factor.
622. JAAExam.com/ATPL Question ID: 1354
Answer B is correct.
An aircraft flying at a given EAS is subject to a positive gust of 50kt EAS. Which of the following correctly describes the increase in positive g felt by the aircraft?
The correct answer is B
A. More at high aircraft weight.
More with a high aspect ratio straight wing. References
B. More with a high aspect ratio straight wing. C. Less at altitude. D. More with a swept wing.
623. JAAExam.com/ATPL Question ID: 1501
Answer B is correct.
What is the percentage increase in stall speed in a 45° bank turn?
The correct answer is B 19%
A. 10% References
B. 19% C. 41% D. 45%
624. JAAExam.com/ATPL Question ID: 1385
Answer B is correct.
A propeller is said to be double acting when it:
The correct answer is B
A. employs a spring to move the propeller blade toward fine.
uses oil pressure to move the blade toward fine and coarse.
B. uses oil pressure to move the blade toward fine and coarse.
References
C. produces thrust on both its front and flat faces of its blades. D. employs an electrically driven booster pump to move the blades in both directions.
625. JAAExam.com/ATPL Question ID: 757
Answer D is correct.
As altitude increases, the equivalent airspeed at which an airplane stalls in a particular configuration will:
The correct answer is D
A. remain equal to the calibrated airspeed.
remain the same regardless of altitude. References
B. decrease as the true airspeed decreases. C. decrease as the true airspeed increases. D. remain the same regardless of altitude.
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626. JAAExam.com/ATPL Question ID: 1183
Answer D is correct.
The range of control surface movements is limited by:
The correct answer is D mechanical control stops.
A. high tension in the control cables. B. normal tension in the control cables.
References
C. defined limits in the operations manual. D. mechanical control stops.
627. JAAExam.com/ATPL Question ID: 474
Answer C is correct.
Which of the following expressions could represent the relationship between force, mass and acceleration:
The correct answer is C
A. a = m / F B. m = F x a C. F = m x a
F=mxa References
D. a = F x m
628. JAAExam.com/ATPL Question ID: 646
Answer C is correct.
A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
The correct answer is C
A. 8
16 References
B. 4 C. 16 D. 12
629. JAAExam.com/ATPL Question ID: 926
Answer A is correct.
The maximum lift-to-drag ratio for an aircraft 13,6. Calculate the minimum glide angle and the maximum range measured along the ground covered by the airplane in a power-off glide that starts at an altitude of 10.000ft.
The correct answer is A
A. Minimum glide angle = 4.2 degrees, maximum range = 25.6 miles.
Minimum glide angle = 4.2 degrees, maximum range = 25.6 miles. References
B. Minimum glide angle = 3.2 degrees, maximum range = 15.6 miles. C. Minimum glide angle = 5.2 degrees, maximum range = 35.6 miles. D. Minimum glide angle = 2.2 degrees, maximum range = 25.6 miles.
630. JAAExam.com/ATPL Question ID: 976
Answer C is correct.
By definition, that free stream Mach number at which sonic flow is first obtained somewhere on the airfoil surface is called the ... of the airfoil.
The correct answer is C
A. drag-divergence Mach-number
critical Mach number References
B. high speed Mach number C. critical Mach number D. free stream Mach number
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631. JAAExam.com/ATPL Question ID: 1438
Answer B is correct.
In a single engine a/c with clockwise rotating propeller, a left yaw is generated due to:
The correct answer is B the slipstream, striking the fin on the left side.
A. the torque effect. B. the slipstream, striking the fin on the left side.
References
C. higher lift on the right wing. D. higher helix angle.
632. JAAExam.com/ATPL Question ID: 1350
Answer B is correct.
A high aspect ratio wing:
The correct answer is B
A. increases induced drag. B. decreases induced drag. C. is structurally stiffer than a low aspect ratio.
decreases induced drag. References
D. has a higher stall angle than a low aspect ratio.
633. JAAExam.com/ATPL Question ID: 1362
Answer C is correct.
Which of these definitions of propeller parameters is correct?
The correct answer is C
A. Propeller angle of attack = angle between blade chord line and propeller vertical plane.
Geometric propeller pitch = the theoretical distance a propeller blade element is travelling in forward direction in one propeller revolution.
B. Blade angle = angle between blade chord line and propeller axis.
References
C. Geometric propeller pitch = the theoretical distance a propeller blade element is travelling in forward direction in one propeller revolution. D. Critical tip velocity = propeller speed at which risk of flow separation at some parts of propeller blade occurs.
634. JAAExam.com/ATPL Question ID: 1198
Answer B is correct.
A primary stop is mounted on an elevator control system in order to:
The correct answer is B restrict the range of movement of the elevator.
A. restrict the range of movement of the control column.
References
B. restrict the range of movement of the elevator. C. maintain constant control cable tension. D. prevent overloading of control cables.
635. JAAExam.com/ATPL Question ID: 1568
Answer C is correct.
The polar curve of an aerofoil is a graphic relation between:
The correct answer is C CL and CD.
A. angle of attack and CL. B. CD and angle of attack. C. CL and CD.
References
D. TAC and stall speed.
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636. JAAExam.com/ATPL Question ID: 1367
Answer B is correct.
Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
The correct answer is B
A. have a higher maximum efficiency than a fixed-pitch propeller.
produce an almost maximum efficiency over a wider speed range. References
B. produce an almost maximum efficiency over a wider speed range. C. produce a greater maximum thrust than a fixed-pitch propeller. D. have more blade surface area than a fixedpitch propeller.
637. JAAExam.com/ATPL Question ID: 1465
Answer D is correct.
Counter rotating propellers have the effect of:
The correct answer is D
A. increasing the torque but decreasing the gyroscopic effect.
cancelling out the torque and gyroscopic effects.
B. decreasing the torque but increasing the gyroscopic effect.
References
C. increasing the torque and gyroscopic effects. D. cancelling out the torque and gyroscopic effects.
638. JAAExam.com/ATPL Question ID: 1484
Answer A is correct.
An aircraft has a basic stalling speed (level flight) of 200 kts. In a 75 degrees coordinated and level turn the stall speed is:
The correct answer is A
A. 393 kts
393 kts References
B. 203 kts C. 197 kts D. 102 kts
639. JAAExam.com/ATPL Question ID: 890
Answer B is correct.
On a wing fitted with a fowler type trailing edge flap, the Full extended position will produce:
The correct answer is B an increase in wing area and camber.
A. an unaffected wing area and increase in camber. B. an increase in wing area and camber. C. an unaffected CD, at a given angle of attack.
References
D. an increase in wing area only.
640. JAAExam.com/ATPL Question ID: 938
Answer D is correct.
The advantage of a turbulent boundary layer over a laminar boundary layer is:
The correct answer is D less tendency to separate.
A. decreases energy. B. thinner.
References
C. increased skin friction. D. less tendency to separate.
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641. JAAExam.com/ATPL Question ID: 970
Answer C is correct.
Should a transport aeroplane fly at a higher Mach number than the buffet-onset Mach number?
The correct answer is C No, this is not acceptable.
A. Yes, but only during approach. B. Yes, this causes no problems.
References
C. No, this is not acceptable. D. Yes, if you want to fly fast at very high altitudes.
642. JAAExam.com/ATPL Question ID: 930
Answer D is correct.
An aircraft has trailing edge flap positions of 0, 15, 30 and 45 degrees plus slats can be deployed. What will have the greatest negative influence on CL / CD?
The correct answer is D
A. Deploying slats.
30 - 45 flaps. References
B. 0 - 15 flaps. C. 15 - 30 flaps. D. 30 - 45 flaps.
643. JAAExam.com/ATPL Question ID: 1419
Answer A is correct.
The windmilling of a propeller will cause:
The correct answer is A
A. drag to be produced instead of thrust. B. some thrust to be produced. C. the CTM tend to cause the propeller to move to coarse pitch.
drag to be produced instead of thrust. References
D. the external weights to move the propeller to fine pitch.
644. JAAExam.com/ATPL Question ID: 974
Answer A is correct.
Define the term Mach number.
The correct answer is A
A. The ratio between TAS and the speed of sound.
The ratio between TAS and the speed of sound.
B. The ratio between IAS and the speed of sound.
References
C. The ratio between GS and the speed of sound D. The ratio between EAS and the speed of sound
645. JAAExam.com/ATPL Question ID: 538
Answer B is correct.
What is the effect on EAS as height is increased when you are holding a constant IAS?
The correct answer is B EAS falls.
A. EAS remains the same. B. EAS falls.
References
C. EAS rises. D. The effect depends on the temperature.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
646. JAAExam.com/ATPL Question ID: 702
Answer C is correct.
Minimum total drag of an aircraft occurs:
The correct answer is C
A. when induced drag is minimum. B. at the stalling speed. C. when profile drag equals induced drag.
when profile drag equals induced drag. References
D. at the best rate of climb speed.
647. JAAExam.com/ATPL Question ID: 587
Answer B is correct.
What effect does aspect ratio have on induced drag?
The correct answer is B
A. Increased aspect ratio increases induced drag.
Increased aspect ratio reduces induced drag.
B. Increased aspect ratio reduces induced drag.
References
C. Changing aspect ratio has no effect. D. Induced drag will equal 1+3 x aspect ratio/chord ratio.
648. JAAExam.com/ATPL Question ID: 1551
Answer C is correct.
A light twin is in a turn at 20 degrees bank and 150 kt TAS. A more heavy aeroplane at the same bank and the same speed will:
The correct answer is C turn at the same turn radius.
A. turn at a smaller turn radius.
References
B. turn at a bigger turn radius. C. turn at the same turn radius. D. turn at a higher turn rate.
649. JAAExam.com/ATPL Question ID: 526
Answer C is correct.
Which of the following statements is true?
The correct answer is C
A. Energy can be created and destroyed. B. Energy can be created but not be destroyed. C. Energy can not be created nor destroyed.
Energy can not be created nor destroyed. References
D. Energy can not be created but destroyed.
650. JAAExam.com/ATPL Question ID: 1270
Answer B is correct.
The inputs to the Q unit are from:
The correct answer is B
A. static and temperature. B. pitot and static. C. altitude and pitot.
pitot and static. References
D. pitot and altitude.
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651. JAAExam.com/ATPL Question ID: 1210
Answer D is correct.
What is the effect on the aeroplanes static longitudinal stability of a shift of the centre of gravity to a more aft location and on the required control deflection for a certain pitch up or down?
The correct answer is D
A. The static longitudinal stability is smaller and the required control deflection is larger.
The static longitudinal stability is smaller and the required control deflection is smaller. References
B. The static longitudinal stability is larger and the required control deflection is smaller. C. The static longitudinal stability is larger and the required control deflection is larger. D. The static longitudinal stability is smaller and the required control deflection is smaller.
652. JAAExam.com/ATPL Question ID: 1176
Answer B is correct.
With increasing altitude and constant IAS the static lateral stability (1) and the dynamic lateral/directional stability (2) of an aeroplane with swept-back wing will:
The correct answer is B
A. (1) increase (2) increase.
(1) increase (2) decrease. References
B. (1) increase (2) decrease. C. (1) decrease (2) decrease D. (1) decrease (2) increase.
653. JAAExam.com/ATPL Question ID: 853
Answer C is correct.
The wing of an aeroplane will never stall at low subsonic speeds as long as:
The correct answer is C
A. the CAS exceeds the power-on stall speed. B. the IAS exceeds the power-on stall speed. C. the angle of attack is smaller than the value at which the stall occurs.
the angle of attack is smaller than the value at which the stall occurs. References
D. there is a nose-down attitude.
654. JAAExam.com/ATPL Question ID: 849
Answer A is correct.
What factors determine the distance travelled over the ground of an aeroplane in a glide?
The correct answer is A
A. The wind and the lift/drag ratio, which changes with angle of attack. B. The wind and the aeroplane s mass.
The wind and the lift/drag ratio, which changes with angle of attack. References
C. The wind and CLmax. D. The wind and weight together with power loading, which is the ratio of power output to the weight.
655. JAAExam.com/ATPL Question ID: 515
Answer C is correct.
Which of the following would tend to increase the density altitude at a given airport?
The correct answer is C An increase in ambient temperature.
A. A large tailwind. B. An increase in barometric pressure.
References
C. An increase in ambient temperature. D. A decrease in relative humidity.
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656. JAAExam.com/ATPL Question ID: 1076
Answer C is correct.
If the sum of moments in flight is not zero, the aeroplane will rotate about:
The correct answer is C the centre of gravity.
A. the aerodynamic centre of the wing. B. the neutral point of the aeroplane. C. the centre of gravity. D. the centre of pressure of the wing.
References
657. JAAExam.com/ATPL Question ID: 1304
Answer C is correct.
A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that could be exceeded is:
Mach increases with altitude at a constant IAS. References
A. VA B. VMO C. MMO D. MD
658. JAAExam.com/ATPL Question ID: 832
Answer C is correct.
Stalling speed in a 15s bank level turn is 60kt. The stalling speed in a 45s bank level turn will be:
The correct answer is C 70 kts
A. 60 kts B. 85 kts
References
C. 70 kts D. 83 kts
659. JAAExam.com/ATPL Question ID: 562
Answer A is correct.
What are the SI units of the following?
The correct answer is A
A. Density is kilograms per cubic metre, Force is Newton’ s.
Density is kilograms per cubic metre, Force is Newton’ s.
B. Density is Newton’ s per cubic metre, Force is kilograms.
References
C. Density is kilograms per Newton, Force is Newton-metre squared. D. Density is kilograms per square metre, Force is kilograms.
660. JAAExam.com/ATPL Question ID: 838
Answer D is correct.
The angle of attack at which a wing stalls will:
The correct answer is D
A. increase if the centre of gravity is moved aft.
remain the same regardless of gross weight.
B. increase if the centre of gravity is moved forward.
References
C. change with an increase in gross weight. D. remain the same regardless of gross weight.
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661. JAAExam.com/ATPL Question ID: 1408
Answer B is correct.
A variable pitch propeller during take-off will move
The correct answer is B
towards: A. coarse pitch to achieve the highest possible thrust.
fine pitch to ensure that the engine can develop its maximum power. References
B. fine pitch to ensure that the engine can develop its maximum power. C. coarse pitch to ensure the best angle of attack is achieved. D. fine pitch to ensure minimum aerodynamic drag is generated.
662. JAAExam.com/ATPL Question ID: 1104
Answer C is correct.
The effect of Mach trim on stick forces for power operated controls:
The correct answer is C is to maintain the required stick force gradient.
A. is to decrease the stick force gradient to prevent the possibility of high speed stall.
References
B. is to decrease the stick force gradient to ensure the pilot can manoeuvre the aircraft adequately when flying at high transonic Mach number. C. is to maintain the required stick force gradient. D. a Mach trim system is not required if an aircraft has power operated controls.
663. JAAExam.com/ATPL Question ID: 1384
Answer C is correct.
If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will.
The correct answer is C
A. decrease and the rate of descent will decrease.
decrease and the rate of descent will increase. References
B. increase and the rate of descent will increase. C. decrease and the rate of descent will increase. D. increase and the rate of descent will decrease.
664. JAAExam.com/ATPL Question ID: 694
Answer A is correct.
For a given angle of attack, a swept wing will:
The correct answer is A
A. have a lower lift coefficient than an equivalent straight one.
have a lower lift coefficient than an equivalent straight one.
B. have the same lift coefficient as an equivalent straight one.
References
C. have reduced lateral stability than an equivalent straight one. D. have the same lateral stability as an equivalent straight one.
665. JAAExam.com/ATPL Question ID: 919
Answer D is correct.
Refer to Figure: 081-13
The correct answer is D
(Refer to figure 081-13) What type of high lift device is depicted on the attached picture?
Slot References
A. Slotted flap. B. Fowler flap. C. Krueger flap. D. Slot
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666. JAAExam.com/ATPL Question ID: 1179
Answer A is correct.
The flaperon is a control that operates simultaneously as:
The correct answer is A flaps and ailerons.
A. flaps and ailerons. B. elevators and ailerons.
References
C. flaps and speed brakes. D. flaps and elevators.
667. JAAExam.com/ATPL Question ID: 1143
Answer C is correct.
Directional static stability is determined by:
The correct answer is C
A. aircraft weight. B. tail volume. C. fin volume.
fin volume. References
D. elevator angle for trim.
668. JAAExam.com/ATPL Question ID: 1444
Answer B is correct.
Propeller torque is caused by:
The correct answer is B
A. the propeller trying to reduce the pitch angle owing to the centrifugal turning moment.
the forces caused by the airflow on the propeller.
B. the forces caused by the airflow on the propeller.
References
C. the forward thrust on the propeller. D. the sideways thrust of the propeller.
669. JAAExam.com/ATPL Question ID: 1123
Answer C is correct.
Longitudinal static stability is created by the fact that
The correct answer is C
the:
centre of gravity is located in front of the neutral point of the aeroplane.
A. wing surface is greater than the horizontal tail surface.
References
B. centre of gravity is located in front of the leading edge of the wing. C. centre of gravity is located in front of the neutral point of the aeroplane. D. aeroplane possesses a large trim speed range.
670. JAAExam.com/ATPL Question ID: 1287
Answer D is correct.
How would the exterior appearance of an aeroplane change, when trimming for speed increase?
The correct answer is D
A. The exterior appearance of the aeroplane will not change. B. The elevator is deflected further up by a downward deflected trim tab.
Elevator deflection is increased further downward by an upward deflected trim tab. References
C. The elevator is deflected further downward by means of a movable horizontal stabiliser. D. Elevator deflection is increased further downward by an upward deflected trim tab.
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671. JAAExam.com/ATPL Question ID: 979
Answer B is correct.
The free stream Mach-number at which the drag coefficient begins to increase rapidly is defined as the ... Mach- number.
The correct answer is B
A. critical
drag divergence References
B. drag divergence C. supersonic D. shock stall
672. JAAExam.com/ATPL Question ID: 767
Answer A is correct.
If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight?
The correct answer is A
A. 0.25
0.25 References
B. 0.5 C. 2.0 D. 4.0
673. JAAExam.com/ATPL Question ID: 1559
Answer B is correct.
Refer to Figure: 081-10
The correct answer is B
(Refer to figure 081-10) Which point on the whole aeroplane polar diagram will give minimum sink rate?
C References
A. A B. C C. B D. D
674. JAAExam.com/ATPL Question ID: 883
Answer A is correct.
Which of the following series of configurations has an increasing critical angle of attack?
B. clean wing, flaps only extended, slats only extended.
One user wrote to us claiming that two of the answers are the same, and that the order of the items within the answers don't matter. Actually, this is false. The order certainly does matter. The best answer that shows a progression in critical angle of attack (stalling angle of attack) of the wing is flaps only extended, clean wing, and then slats only extended.
C. slats only extended, clean wing, flaps only extended.
References
A. flaps only extended, clean wing, slats only extended.
D. slats only extended, flaps only extended, clean wing.
675. JAAExam.com/ATPL Question ID: 1403
Answer C is correct.
When maximum RPM is selected at take-off, what happens with the propeller blades if a CSU is installed?
The correct answer is C
A. The propeller blades move to a coarser pitch in order to generate the maximum thrust. B. The propeller blades move to a finer pitch to allow the engine to develop maximum power.
The blades move to coarse pitch to enable the propeller to absorb the high power which is developed by the engine. References
C. The blades move to coarse pitch to enable the propeller to absorb the high power which is developed by the engine. D. The blades move to fine pitch to prevent propeller overspeeding.
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676. JAAExam.com/ATPL Question ID: 536
Answer C is correct.
Maintaining thickness/chord ratio but changing to a supercritical wing section will:
The correct answer is C give the aircraft an increased range.
A. lead to more prominent shockwave formation. B. make lateral stability more critical. C. give the aircraft an increased range. D. reduce the aft shift of CP in the transonic
References
range.
677. JAAExam.com/ATPL Question ID: 884
Answer B is correct.
Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
The correct answer is B upper side trailing edge.
A. lower side leading edge. B. upper side trailing edge.
References
C. upper side leading edge. D. lower side trailing edge.
678. JAAExam.com/ATPL Question ID: 1337
Answer B is correct.
The distribution of ... and ... in a structure determine natural frequencies and modes of vibration.
The correct answer is B mass, stiffness
A. passengers, payload B. mass, stiffness
References
C. stringers, longerons D. flaps, slats
679. JAAExam.com/ATPL Question ID: 1409
Answer C is correct.
If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
The correct answer is C increase and the rate of descent will decrease.
A. decrease and the rate of descent will decrease.
References
B. increase and the rate of descent will increase. C. increase and the rate of descent will decrease. D. decrease and the rate of descent will increase.
680. JAAExam.com/ATPL Question ID: 709
Answer D is correct.
With increasing altitude the following occurs:
The correct answer is D
A. the stalling angle increases for a given indicated airspeed.
drag remains the same for a given indicated airspeed.
B. the stalling angle reduces for a given indicated airspeed.
References
C. drag reduces for a given indicated airspeed. D. drag remains the same for a given indicated airspeed.
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681. JAAExam.com/ATPL Question ID: 1243
Answer B is correct.
Rolling is the rotation of the aeroplane about the:
The correct answer is B
A. wing axis. B. longitudinal axis. C. vertical axis.
longitudinal axis. References
D. lateral axis.
682. JAAExam.com/ATPL Question ID: 753
Answer D is correct.
If an aeroplane flies in the ground effect:
The correct answer is D
A. drag and lift are reduced. B. the effective angle of attack is decreased. C. the induced angle of attack is increased.
the lift is increased and the drag is decreased. References
D. the lift is increased and the drag is decreased.
683. JAAExam.com/ATPL Question ID: 479
Answer D is correct.
The wing area divided by the span of a wing is called:
The correct answer is D mean cord.
A. aspect ratio. B. wash out.
References
C. fineness ratio. D. mean cord.
684. JAAExam.com/ATPL Question ID: 577
Answer B is correct.
What is the MAC of a wing?
The correct answer is B
A. Area of wing divided by the span. B. The same as the mean chord of a rectangular wing of the same span. C. The mean chord of the whole aeroplane.
The same as the mean chord of a rectangular wing of the same span. References
D. The 25% chord of a swept wing.
685. JAAExam.com/ATPL Question ID: 14023
Answer D is correct.
Refer to Figure: 081-17
The correct answer is D
Refer to figure 081-17 What type of trailing edge device is shown in this figure?
Slotted Fowler Flap
A. Split Flaperon
References
B. Split Flap C. Krueger Flap D. Slotted Fowler Flap
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686. JAAExam.com/ATPL Question ID: 1370
Answer D is correct.
The de-icing of a propeller by fluid is achieved through:
The correct answer is D slinger rings.
A. spray mats. B. de-icing paste.
References
C. ground application of fluid only. D. slinger rings.
687. JAAExam.com/ATPL Question ID: 647
Answer A is correct.
The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
The correct answer is A the airstream velocity.
A. the airstream velocity. B. the specific mass of the body.
References
C. the weight of the body. D. the c.g. location of the body.
688. JAAExam.com/ATPL Question ID: 1227
Answer D is correct.
Which phenomenon is counteracted with differential aileron deflection?
The correct answer is D Adverse yaw.
A. Turn co-ordination. B. Aileron reversal.
References
C. Sensitivity for spiral dive. D. Adverse yaw.
689. JAAExam.com/ATPL Question ID: 784
Answer D is correct.
Increase of wing loading will:
The correct answer is D
A. decrease the minimum gliding angle. B. increase CLmax. C. decrease take off speeds.
increase the stall speeds. References
D. increase the stall speeds.
690. JAAExam.com/ATPL Question ID: 878
Answer B is correct.
When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually:
The correct answer is B increase.
A. remain the same. B. increase.
References
C. decrease. D. first increase and then decrease.
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691. JAAExam.com/ATPL Question ID: 1342
Answer A is correct.
Load factor is:
The correct answer is A
A. Lift/Weight B. Weight/Lift C. 1/Bank angle
Lift/Weight References
D. Wing loading
692. JAAExam.com/ATPL Question ID: 1303
Answer B is correct.
Which speed represents maximum landing gear extended speed?
The correct answer is B Vle
A. Vs0 B. Vle
References
C. Vlo D. Vfe
693. JAAExam.com/ATPL Question ID: 477
Answer D is correct.
If the TAS is increased by a factor of 4, by what factor would the drag increase?
The correct answer is D 16
A. 4 B. 8
References
C. 12 D. 16
694. JAAExam.com/ATPL Question ID: 1002
Answer C is correct.
When an aeroplane is flying through the transonic range with increasing Mach Number the centre of the pressure of the wing will move aft. This requires:
The correct answer is C
A. much more thrust from the engine. B. a higher IAS to compensate the nose down
a pitch up input of the stabilizer. References
effect. C. a pitch up input of the stabilizer. D. a stability augmentation system.
695. JAAExam.com/ATPL Question ID: 1273
Answer A is correct.
An anti-balance tab moves in the:
The correct answer is A
A. same sense as its associated control surface, to increase aerodynamic loading.
same sense as its associated control surface, to increase aerodynamic loading.
B. same sense as its associated control surface to reduce aerodynamic loading.
References
C. opposite sense as its associated control surface to increase aerodynamic loading. D. opposite sense as its associated control surface to reduce aerodynamic loading.
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696. JAAExam.com/ATPL Question ID: 1173
Answer C is correct.
Which aeroplane behaviour will be corrected by a yaw damper?
The correct answer is C Dutch roll.
A. Spiral dive. B. Tuck under.
References
C. Dutch roll. D. Buffeting.
697. JAAExam.com/ATPL Question ID: 590
Answer B is correct.
At a constant CAS when flying below sea level an aircraft will have:
The correct answer is B a lower TAS than at sea level at ISA conditions.
A. a higher TAS than at sea level. B. a lower TAS than at sea level at ISA conditions.
References
C. the same TAS as at sea level. D. the same TAS, but an increased IAS.
698. JAAExam.com/ATPL Question ID: 1231
Answer D is correct.
What is the purpose of the ailerons?
The correct answer is D
A. To provide directional control about the normal or vertical axis.
To give lateral control about the longitudinal axis.
B. To give lateral control about the lateral axis.
References
C. To provide longitudinal control about the lateral axis.
D. To give lateral control about the longitudinal axis.
699. JAAExam.com/ATPL Question ID: 705
Answer A is correct.
How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?
The correct answer is A
A. Decreasing, then increasing.
Decreasing, then increasing. References
B. Decreasing. C. Increasing. D. Increasing, then decreasing.
700. JAAExam.com/ATPL Question ID: 768
Answer B is correct.
Stick shaker stall warnings should be activated at:
The correct answer is B
A. 1.2 VS B. 1.05 VS C. 1.5 VS
1.05 VS References
D. VS
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701. JAAExam.com/ATPL Question ID: 1432
Answer C is correct.
The geometric pitch of a propeller is:
The correct answer is C
A. equal to the blade angle. B. the mean chord of the propeller blade. C. the distance the propeller would travel per revolution if it were retarded in a solid medium.
the distance the propeller would travel per revolution if it were retarded in a solid medium. References
D. the distance between the propeller blades.
702. JAAExam.com/ATPL Question ID: 462
Answer A is correct.
The correct drag formula is:
The drag equation is a practical formula used to calculate the force of drag experienced by an object due to a fluid that it is moving through. The equation is attributed to Lord Rayleigh, who originally used in place of (L being some linear dimension). The force on a moving object due to a fluid is:
A. D = CD 1/2 RHO V2 S B. D = CD 2 RHO V2 S C. D = CD 1/2 RHO V S D. D = CD 1/2 1/RHO V2 S
where
Fd is the force of drag,
v is the velocity of the object relative to the fluid,
A is the reference area, and
ρ is the density of the fluid (Note that for the Earth's atmosphere, the density can be found using the barometric formula. Air is 1.293 kg/m3 at 0°C and 1 atmosphere),
Cd is the drag coefficient (a dimensionless constant, e.g. 0.25 to 0.45 for a car).
The reference area A is the area of the projection of the object on a plane perpendicular to the direction of motion (ie cross-sectional area). Sometimes different reference areas are given for the same object in which case a drag coefficient corresponding to each of these different areas must be given. The reference for a wing would be the plane area rather than the frontal area. (The above description is more formal than the one in tje JAA question. When converting to the JAA question's notation, FD = D, CD = CD and S = A. Also, V2 is written here as V2. ) References
703. JAAExam.com/ATPL Question ID: 464
Answer D is correct.
The load factor n is:
The correct answer is D
A. always larger than 1. B. always smaller than 1. C. always equal to 1.
smaller, equal to or larger than 1, depending on the manoeuvre. References
D. smaller, equal to or larger than 1, depending on the manoeuvre.
704. JAAExam.com/ATPL Question ID: 1525
Answer B is correct.
If in level flight an aircraft has a stalling speed of 90 kts IAS, what will be its stalling speed in a 60° level and balanced turn?
The correct answer is B
A. 99 kts
127 kts References
B. 127 kts C. 112 kts D. 90 kts
705. JAAExam.com/ATPL Question ID: 1185
Answer C is correct.
Which of the following is the reason for putting the horizontal stabiliser on top of the fin, known as a T-
The correct answer is C
tail?
to improve the aerodynamic efficiency of the vertical tail.
A. to improve ground clearance during take-off and landing on a contaminated runway.
References
B. to decrease the tendency for super stall. C. to improve the aerodynamic efficiency of the vertical tail. D. to improve the wing efficiency.
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706. JAAExam.com/ATPL Question ID: 1247
Answer C is correct.
When an aircraft is rolled to port, adverse yaw will be reduced by:
The correct answer is C a Frise aileron being effective on the port wing.
A. the leading edge of the down going aileron protruding into the airflow.
References
B. Frise ailerons producing increased profile leading edge drag on both surfaces. C. a Frise aileron being effective on the port wing. D. the down going aileron producing a greater angle of deflection than the up going aileron.
707. JAAExam.com/ATPL Question ID: 1037
Answer C is correct.
The regime of flight from the critical Mach number up to M = 1.3 is called:
The correct answer is C transonic range.
A. hypersonic range. B. supersonic range.
References
C. transonic range. D. subsonic range.
708. JAAExam.com/ATPL Question ID: 540
Answer C is correct.
Dihedral of the wing is:
The correct answer is C
A. the angle between the 0.25 chord line of the wing and the vertical axis.
the angle between the 0.25 chord line of the wing and the lateral axis.
B. the angle between the leading edge of the wing and the lateral axis.
References
C. the angle between the 0.25 chord line of the wing and the lateral axis. D. the angle between the 0.25 chord line of the wing and the horizon.
709. JAAExam.com/ATPL Question ID: 729 If dynamic (kinetic) pressure increases, what is the
Answer B is correct.
effect on total drag (if all important factors remain constant)? A. Drag decreases.
The correct answer is B Drag increases.
B. Drag increases. C. It has no effect on drag.
References
D. Drag only changes with changing ground speed.
710. JAAExam.com/ATPL Question ID: 965
Answer D is correct.
On a typical transonic airfoil the transonic rearward shift of the CP occurs at about:
The correct answer is D M 0.89 to M 0.98
A. M 0.75 to M 0.98 B. M 0.81 to M 1.4
References
C. M 0.75 to M 0.89 D. M 0.89 to M 0.98
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711. JAAExam.com/ATPL Question ID: 463
Answer B is correct.
Mean chord is equal to:
The correct answer is B
A. (tip chord + root chord) / 2. B. wing area divided by wing span. C. wing span divided by wing area.
wing area divided by wing span. References
D. mean aerodynamic chord.
712. JAAExam.com/ATPL Question ID: 1216
Answer D is correct.
An aeroplane performs a right turn, the slip indicator is left of neutral. One way to co-ordinate the turn is to apply:
The correct answer is D
A. more right rudder.
more right bank. References
B. less right bank. C. a higher turn-rate. D. more right bank.
713. JAAExam.com/ATPL Question ID: 1191
Answer D is correct.
The range of control surface movements is limited by:
The correct answer is D providing control stops.
A. leaving control cables a little stack. B. tensioning control cables correctly.
References
C. defined limits is the operations manual. D. providing control stops.
714. JAAExam.com/ATPL Question ID: 592
Answer C is correct.
Dynamic pressure is expressed as:
The correct answer is C
A. q*Cd*surface B. q*Cl*surface C. (density/2)* V2
(density/2)* V2 References
D. (density/2)*V
715. JAAExam.com/ATPL Question ID: 907
Answer B is correct.
After take-off the slats (when installed) are always retracted later than the flaps. Why?
The correct answer is B
A. Because SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED. B. Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag.
Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag. References
C. Because VMCA with SLATS EXTENDED is more favourable compared to the FLAPS EXTENDED situation. D. Because FLAPS EXTENDED gives a large decrease in stall speed with relatively less drag.
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716. JAAExam.com/ATPL Question ID: 561
Answer C is correct.
In a subsonic flow venturi the relationship between total pressure, static pressure and dynamic pressure of undisturbed air and air in the throat of will be:
The correct answer is C
i.
Dynamic pressure will be constant, static pressure will decrease
ii.
Total pressure will be constant, dynamic pressure will increase
(ii) is correct and (i) is incorrect References
A. both (i) and (ii) are correct B. (i) is correct and (ii) is incorrect C. (ii) is correct and (i) is incorrect D. both (i) and (ii) are incorrect
717. JAAExam.com/ATPL Question ID: 1294 If an elevator trim tab is in its neutral position and
Answer D is correct.
the elevator is moved up: The correct answer is D A. the tab will move up relative to the elevator. B. the tab will remain parallel to the chord line of the tailplane.
the tab will remain in line with the elevator.
C. the tab will move down relative to the elevator applying the trim input has been made.
References
D. the tab will remain in line with the elevator.
718. JAAExam.com/ATPL Question ID: 1001
Answer C is correct.
In the transonic range lift will decrease at the shock stall due to the:
The correct answer is C separation of the boundary layer at the shock waves.
A. first appearance of a shock wave at the upper side of the wing.
References
B. attachment of the shock wave on the trailing edge of the wing. C. separation of the boundary layer at the shock waves. D. appearance of the bow wave.
719. JAAExam.com/ATPL Question ID: 1206
Answer B is correct.
An aircraft is fitted with an elevator with a servo tab mechanism in the pitch control system. If the elevator becomes jammed, what is the effect on pitch control?
The correct answer is B
A. The servo tab will become a negative trim tab.
Some pitch control will be retained, working in the reverse sense. References
B. Some pitch control will be retained, working in the reverse sense. C. The servo tab will become an anti-balance tab. D. Pitch control will be lost.
720. JAAExam.com/ATPL Question ID: 575
Answer C is correct.
The SI unit of force is:
The correct answer is C
A. Joule. B. Watt. C. Newton.
Newton. References
D. Kilogram.
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721. JAAExam.com/ATPL Question ID: 699
Answer A is correct.
A function of vortex generators in the transonic regime is to: A. reduce boundary layer separation drag when shockwaves form. B. prevent the rearward shift of CP on swept wing stalls.
The correct answer is A reduce boundary layer separation drag when shockwaves form. References
C. reduce wing root compression effects. D. increase directional static stability.
722. JAAExam.com/ATPL Question ID: 1207
Answer A is correct.
When the C.G. position is moved forward, the elevator deflection for a manoeuvre with a load factor greater than 1 will be:
The correct answer is A
A. larger.
larger. References
B. smaller. C. unchanged. D. dependent on trim position.
723. JAAExam.com/ATPL Question ID: 614
Answer A is correct.
Subsonic flow over a cambered airfoil at 4° angle of attack will cause: References A. an increase in speed and drop in pressure over the upper surface and a decrease in speed and a rise in pressure over the lower surface. B. a decrease in speed and drop in pressure over the upper surface and a decrease in speed and a drop in pressure over the lower surface. C. an increase in speed and drop in pressure over the upper surface and an increase in speed and a drop in pressure over the lower surface. D. a decrease in speed and drop in pressure over the upper surface and an increase in speed and a drop in pressure over the lower surface.
724. JAAExam.com/ATPL Question ID: 1382
Answer C is correct.
When the flyweights of the propeller CSU, during operation, move outwards overcoming the spring force:
The correct answer is C
A. the propeller is on speed. B. the propeller is in underspeed. C. the propeller is in overspeed.
the propeller is in overspeed. References
D. the propeller is locked in pitch.
725. JAAExam.com/ATPL Question ID: 740
Answer B is correct.
What effect on induced drag does entering ground effect have:
The correct answer is B Decrease.
A. Increase. B. Decrease.
References
C. Remain the same. D. Induced drag will increase, but profile drag will decrease.
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726. JAAExam.com/ATPL Question ID: 1031
Answer C is correct.
Vortex generators on the upper side of the wing:
The correct answer is C
A. increase critical Mach Number. B. increase wave drag. C. decrease wave drag.
decrease wave drag. References
D. decrease critical Mach Number.
727. JAAExam.com/ATPL Question ID: 899
Answer B is correct.
What increases the stalling angle of attack? Use of:
The correct answer is B
A. flaps. B. slats. C. spoilers.
slats. References
D. fuselage mounted speed-brakes.
728. JAAExam.com/ATPL Question ID: 953
Answer C is correct.
On a typical symmetrical airfoil, as the free stream Mach number approaches M 1.0, the centre of pressure will:
The correct answer is C
A. move from 25% chord to the leading edge.
move aft to about 45% chord. References
B. move forward to about 25% chord. C. move aft to about 45% chord. D. move aft to the trailing edge.
729. JAAExam.com/ATPL Question ID: 1006
Answer D is correct.
For minimum wave drag, an aircraft should be operated at which of the following speeds?
The correct answer is D Subsonic.
A. Mach 1.0 B. High supersonic.
References
C. Low supersonic. D. Subsonic.
730. JAAExam.com/ATPL Question ID: 985
Answer B is correct.
The least energy loss through a normal shockwave occurs when the local Mach number is:
The correct answer is B just above 1.0 M
A. well above 1.0 M B. just above 1.0 M
References
C. just below 1.0 M D. exactly 1.0 M
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731. JAAExam.com/ATPL Question ID: 583
Answer B is correct.
Wing span is defined as the distance:
The correct answer is B
A. from leading edge to trailing edge. B. from wing tip to wing tip. C. from wing tip to fuselage centre line.
from wing tip to wing tip. References
D. between top and bottom of the wing at the thickest point.
732. JAAExam.com/ATPL Question ID: 1279
Answer D is correct.
If an aircraft is fitted with powered flying controls, which of the following would be used in the case of manual reversion?
The correct answer is D
A. Balance tab.
Servo tab. References
B. Anti-balance tab. C. Spring tab. D. Servo tab.
733. JAAExam.com/ATPL Question ID: 668
Answer B is correct.
Increasing the aspect ratio of a wing...
The correct answer is B
A. increases induced drag. B. decreases induced drag.
decreases induced drag. References
C. decreases skin friction drag. D. has no effect on induced drag.
734. JAAExam.com/ATPL Question ID: 783
Answer D is correct.
The stall speed:
The correct answer is D
A. increases with the length of the wingspan. B. decreases with an increased weight. C. does not depend on weight.
increases with an increased weight. References
D. increases with an increased weight.
735. JAAExam.com/ATPL Question ID: 620
Answer A is correct.
Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
The correct answer is A
A. Upper side.
Upper side. References
B. Lower side. C. In front of the stagnation point. D. In the stagnation point.
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736. JAAExam.com/ATPL Question ID: 1560
Answer B is correct.
If an aircraft dumps fuel after an engine failure, and the aircraft is flown for maximum glide range:
The correct answer is B the approach speed will be lower.
A. the optimum gliding angle will be shallower. B. the approach speed will be lower.
References
C. the stalling speed will increase. D. the range will be increased mainly due to less induced drag.
737. JAAExam.com/ATPL Question ID: 505
Answer B is correct.
The true airspeed (TAS) is:
The correct answer is B
A. higher than the speed of the undisturbed airstream about the aeroplane.
lower than the indicated airspeed (IAS) at ISA conditions and altitudes below sea level.
B. lower than the indicated airspeed (IAS) at ISA conditions and altitudes below sea level.
References
C. equal to the IAS, multiplied by the air density at sea level. D. lower than the speed of the undisturbed airstream about the aeroplane.
738. JAAExam.com/ATPL Question ID: 1136
Answer D is correct.
An aeroplane has static directional stability; in a side-slip to the right, initially the:
The correct answer is D nose of the aeroplane tends to move to the right.
A. nose of the aeroplane tends to move to the left.
References
B. right wing tends to go down. C. nose of the aeroplane will remain in the same direction. D. nose of the aeroplane tends to move to the right.
739. JAAExam.com/ATPL Question ID: 971
Answer D is correct.
An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed?
The correct answer is D
A. It remains constant.
It increases as temperature increases. References
B. It decreases as pressure increases. C. It decreases as altitude decreases. D. It increases as temperature increases.
740. JAAExam.com/ATPL Question ID: 1020
Answer A is correct.
What is the influence of decreasing aeroplane weight on Mcrit at constant IAS?
The correct answer is A
A. Mcrit increases as a result of flying at a smaller angle of attack. B. Mcrit increases as a result of compressibility effects.
Mcrit increases as a result of flying at a smaller angle of attack. References
C. Mcrit decreases. D. Mcrit decreases as a result of flying at a greater angle of attack.
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741. JAAExam.com/ATPL Question ID: 1415
Answer A is correct.
A windmilling propeller produces:
The correct answer is A
A. drag, and rotates in the same direction. B. thrust, and rotates in the same direction. C. drag, and rotates in the opposite direction.
drag, and rotates in the same direction. References
D. thrust, and rotates in the opposite direction.
742. JAAExam.com/ATPL Question ID: 1122
Answer C is correct.
In case the Mach trimmer fails: A. the speed must be kept constant. B. try to relocate the centre-of-gravity aft. C. the Mach number must be limited.
The correct answer is C the Mach number must be limited. References
D. the aeroplane weight must be limited.
743. JAAExam.com/ATPL Question ID: 1434
Answer A is correct.
A reversible propeller is one that:
The correct answer is A
A. will deliver negative thrust. B. is mounted behind the main wing. C. is a pusher rather than a tractor.
will deliver negative thrust. References
D. can be operated in either direction of rotation.
744. JAAExam.com/ATPL Question ID: 666
Answer A is correct.
The relationship between induced drag and the aspect ratio is:
The correct answer is A
A. a decrease in the aspect ratio increases the induced drag. B. there is no relationship.
a decrease in the aspect ratio increases the induced drag. References
C. induced drag = 1.3 aspect ratio value. D. an increase in the aspect ratio increases the induced drag.
745. JAAExam.com/ATPL Question ID: 630
Answer D is correct.
Refer to Figure: 081-03
The correct answer is D
(Refer to figure 081-03) With reference to attached diagram, how do the speeds relate to relative wind/airflow (V)?
V1 = 0 and V2 > V References
A. V1 < V2 and V2 < V B. V1 = 0 and V2 = V C. V1 > V2 and V2 < V D. V1 = 0 and V2 > V
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746. JAAExam.com/ATPL Question ID: 1017
Answer A is correct.
Just above the critical Mach number the first
The correct answer is A
evidence of a shock wave will appear at the A. upper side of the wing.
upper side of the wing. References
B. lower side of the wing. C. leading edge of the wing. D. trailing edge of the wing.
747. JAAExam.com/ATPL Question ID: 1004
Answer B is correct.
The critical speed where the speed is too low and too high at the same time is called:
The correct answer is B Coffin corner.
A. Mcrit. B. Coffin corner.
References
C. Supersonic. D. High speed buffet.
748. JAAExam.com/ATPL Question ID: 943
Answer A is correct.
In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
The correct answer is A
A. The last part of the rotation.
The last part of the rotation. References
B. The take-off run. C. During climb with all engines operating. D. All phases of the take-off are equally critical.
749. JAAExam.com/ATPL Question ID: 507
Answer D is correct.
The Cl - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl - alpha graph:
The correct answer is D
A. in the origin.
above the origin. References
B. below the origin. C. nowhere. D. above the origin.
750. JAAExam.com/ATPL Question ID: 1054
Answer C is correct.
The phugoid motion is a long term oscillation around the:
The correct answer is C lateral axis.
A. normal axis. B. longitudinal axis C. lateral axis. D. vertical axis.
References
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751. JAAExam.com/ATPL Question ID: 1317
Answer A is correct.
Flutter can be eliminated using:
The correct answer is A
A. mass balancing. B. powered flying controls. C. a canard in front of the main wing.
mass balancing. References
D. a T-tail.
752. JAAExam.com/ATPL Question ID: 1161
Answer A is correct.
Lateral static stability is determined by:
The correct answer is A
A. aircraft response to sideslip. B. aspect ratio. C. wingspan.
aircraft response to sideslip. References
D. cg position.
753. JAAExam.com/ATPL Question ID: 1450
Answer A is correct.
During the take-off roll, what affect does torque have on an aircraft with a clockwise rotating propeller?
The correct answer is A
A. Weight on left wheel increased, weight on right wheel decreased.
Weight on left wheel increased, weight on right wheel decreased. References
B. Weight on left wheel increased, weight on right wheel remains constant. C. Weight on left wheel decreased, weight on right wheel increased. D. Weight on right wheel increased, weight on left wheel decreased.
754. JAAExam.com/ATPL Question ID: 1145
Answer B is correct.
Which of the following gives an unstable contribution in sideslip?
The correct answer is B Flap extension.
A. Wing sweep. B. Flap extension.
References
C. Dihedral. D. High wing.
755. JAAExam.com/ATPL Question ID: 722 For a constant aircraft weight at constant IAS and in
Answer C is correct.
level flight: The correct answer is C A. VIMD will increase with increased altitude. B. VIMD will constantly vary regardless of altitude.
VIMD will remain the same regardless of altitude.
C. VIMD will remain the same regardless of altitude.
References
D. VIMD will reduce with increased altitude.
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756. JAAExam.com/ATPL Question ID: 921
Answer D is correct.
The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
The correct answer is D
A. it changes the camber of the wing.
it delays the stall to a higher angle of attack. References
B. the laminar part of the boundary layer gets thicker. C. it decelerates the upper surface boundary layer air. D. it delays the stall to a higher angle of attack.
757. JAAExam.com/ATPL Question ID: 634
Answer A is correct.
What changes in angle of attack must be made to maintain altitude while the airspeed is being increased?
The correct answer is A
A. Decrease the angle of attack to compensate for the increasing lift.
Decrease the angle of attack to compensate for the increasing lift. References
B. Increase the angle of attack to produce more lift than drag. C. Decrease the angle of attack to compensate for the increasing drag. D. Maintain a constant angle of attack until the desired airspeed is reached, then increase the angle of attack.
758. JAAExam.com/ATPL Question ID: 1086
Answer B is correct.
The effects of CG position on longitudinal static stability and control response will be:
The correct answer is B
A. forward movement of the CG will reduce stability and increase control response. B. forward movement of the CG will reduce control response and increase stability. C. rearward movement of the CG will increase stability and reduce control response. D. rearward movement of the CG will reduce stability and control response.
forward movement of the CG will reduce control response and increase stability. References
759. JAAExam.com/ATPL Question ID: 810
Answer C is correct.
At the same weight, with the CG at its forward limit:
The correct answer is C
A. VS is lower, the stalling angle is unchanged. B. VS is higher, the stalling angle is greater. C. VS is higher, the stalling angle is unchanged.
VS is higher, the stalling angle is unchanged. References
D. VS is lower, the stalling angle is less.
760. JAAExam.com/ATPL Question ID: 1256
Answer A is correct.
It is possible to have an aileron control aerodynamically balanced by:
The correct answer is A setting the hinge back into the control surface.
A. setting the hinge back into the control surface.
References
B. causing the surface to move through a greater angle in up deflection than down deflection. C. attaching weights which act forward of the hinge line. D. the surface C of G acting through the hinge line.
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761. JAAExam.com/ATPL Question ID: 1148
Answer A is correct.
When an aircraft is in a sideslip:
The correct answer is A
A. wing dihedral will cause a rolling moment which reduces the sideslip.
wing dihedral will cause a rolling moment which reduces the sideslip.
B. wing anhedral will cause a rolling moment which reduces the sideslip.
References
C. the fin will cause the rolling moment which increases the sideslip. D. wing dihedral will cause a yawing moment to reduce the sideslip.
762. JAAExam.com/ATPL Question ID: 752
Answer B is correct.
Ground Effect:
The correct answer is B
A. is usually only considered when the approach phase has commenced.
is only effective up to 1 wingspan from the ground.
B. is only effective up to 1 wingspan from the ground.
References
C. has the same effect as a decrease in aspect ratio. D. increases induced drag.
763. JAAExam.com/ATPL Question ID: 1125
Answer D is correct.
The max aft position of the centre of gravity is amongst others limited by the:
The correct answer is D minimum value of the stick force per g.
A. too small effect of the controls on the aeroplane.
References
B. maximum longitudinal stability of the aeroplane. C. maximum elevator deflection. D. minimum value of the stick force per g.
764. JAAExam.com/ATPL Question ID: 1033
Answer D is correct.
Compared to straight wings of the same airfoil section swept wings ... the onset of the transonic drag rise and have a ... CD in supersonic flight:
The correct answer is D
A. delay, lower
delay, higher References
B. hasten, lower C. hasten, higher D. delay, higher
765. JAAExam.com/ATPL Question ID: 852
Answer C is correct.
After the transition point between the laminar and turbulent boundary layer:
The correct answer is C the mean speed and friction drag increases.
A. the mean speed increases and the friction drag decreases.
References
B. the boundary layer gets thicker and the speed decreases. C. the mean speed and friction drag increases. D. the boundary layer creates thinner and the speed increases.
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766. JAAExam.com/ATPL Question ID: 1291
Answer D is correct.
One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that:
The correct answer is D it is a more powerful means of trimming.
A. the systems complexity is reduced. B. the structure weighs less.
References
C. it leads to greater stability in flight. D. it is a more powerful means of trimming.
767. JAAExam.com/ATPL Question ID: 706
Answer B is correct.
The aeroplane drag in straight and level flight is lowest when the:
The correct answer is B parasite drag is equal to the induced drag.
A. parasite drag equals twice the induced drag. B. parasite drag is equal to the induced drag.
References
C. induced drag is equal to zero. D. induced drag is lowest.
768. JAAExam.com/ATPL Question ID: 707
Answer D is correct.
Induced drag can be reduced by: A. increased taper ratio.
References
B. decreased taper ratio. C. use of a wing tip with a thinner aerofoil section. D. increased aspect ratio.
769. JAAExam.com/ATPL Question ID: 1455
Answer C is correct.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by:
The correct answer is C high angles of attack.
A. large angles of yaw. B. high speed.
References
C. high angles of attack. D. large angles of climb.
770. JAAExam.com/ATPL Question ID: 597
Answer C is correct.
The angle of attack is the angle between:
The correct answer is C
A. chord line and the longitudinal axis. B. wing and lateral axis. C. the chord line and the direction of the airflow.
the chord line and the direction of the airflow. References
D. the direction of the airflow and the longitudinal axis.
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771. JAAExam.com/ATPL Question ID: 641
Answer A is correct.
An aeroplane performs a straight and level horizontal flight at the same angle of attack at two different altitudes: (all other factors of importance being constant, assume ISA conditions and no compressibility effects)
The correct answer is A the TAS at the higher altitude is higher. References
A. the TAS at the higher altitude is higher. B. the TAS at both altitudes is the same. C. the TAS at the higher altitude cannot be determined. D. the TAS at the higher altitude is lower.
772. JAAExam.com/ATPL Question ID: 917
Answer B is correct.
The trailing edge flaps when extended:
The correct answer is B
A. increase the zero lift angle of attack. B. worsen the best angle of glide. C. significantly increase the angle of attack for maximum lift.
worsen the best angle of glide. References
D. significantly lower the drag.
773. JAAExam.com/ATPL Question ID: 470
Answer B is correct.
The term angle of attack is defined as the angle:
The correct answer is B
A. between the wing chord line and the local horizon.
between the wing chord line and the relative wind.
B. between the wing chord line and the relative wind.
References
C. between the airplanes climb angle and the horizon. D. formed by the longitudinal axis of the airplane and the chord line of the wing.
774. JAAExam.com/ATPL Question ID: 1398
Answer C is correct.
The normal tendency of a propeller blade when it rotates is:
The correct answer is C
A. to go into high pitch if not equipped with counterweights. B. to go into low pitch if equipped with counterweights.
to go into low pitch if not equipped with counterweights. References
C. to go into low pitch if not equipped with counterweights. D. to remain in current pitch if equipped with counterweights.
775. JAAExam.com/ATPL Question ID: 1175
Answer B is correct.
Sensitivity for spiral dive will occur when:
The correct answer is B
A. the static directional stability is negative and the static lateral stability is positive. B. the static directional stability is positive and
the static directional stability is positive and the static lateral stability is relatively weak.
the static lateral stability is relatively weak.
References
C. the static lateral and directional stability are both negative. D. the Dutch roll tendency is too strongly suppressed by the yaw damper.
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776. JAAExam.com/ATPL Question ID: 674
Answer B is correct.
A cambered airfoil with zero angle of attack, will in flight produce:
The correct answer is B some lift and some drag.
A. no lift but some drag. B. some lift and some drag.
References
C. some lift with no drag. D. no lift and no drag
777. JAAExam.com/ATPL Question ID: 1019
Answer B is correct.
At what speed does the front of a shock wave move across the earths surface?
The correct answer is B The ground speed of the aeroplane.
A. The speed of sound at ground level. B. The ground speed of the aeroplane.
References
C. The speed of sound at flight level. D. The true air speed of the aeroplane.
778. JAAExam.com/ATPL Question ID: 759
Answer A is correct.
To maintain level flight, if the angle of attack is increased the speed must be:
The correct answer is A reduced.
A. reduced. B. reduced in the same ratio as the lift/drag ratio increases.
References
C. increased in the same ratio as the lift/drag ratio decreases. D. increased.
779. JAAExam.com/ATPL Question ID: 1149
Answer C is correct.
What will increase the sensitivity to Dutch Roll?
The correct answer is C
A. A forward movement of the centre of gravity. B. An increased anhedral. C. An increased static lateral stability. D. An increased static directional stability.
An increased static lateral stability. References
780. JAAExam.com/ATPL Question ID: 1193
Answer D is correct.
The axes of an aircraft by definition must all pass through the:
The correct answer is D center of gravity.
A. flight desk. B. aircraft datum.
References
C. center of pressure. D. center of gravity.
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781. JAAExam.com/ATPL Question ID: 1269
Answer B is correct.
Control surface aerodynamic balancing:
The correct answer is B
A. is achieved using a vertical and horizontal tail.
will decrease surface hinge moments and pilot effort.
B. will decrease surface hinge moments and pilot effort.
References
C. will alleviate control surface flutter tendencies. D. will increase surface feel therefore increasing control effectiveness.
782. JAAExam.com/ATPL Question ID: 720
Answer A is correct.
For a given Indicated airspeed (IAS), a swept wing compared to a straight wing of the same wing area and same angle of attack produces:
The correct answer is A
A. less lift, improved lateral stability and less total drag.
less lift, improved lateral stability and less total drag. References
B. less lift, reduced lateral stability and less total drag. C. the same lift, increased lateral stability, with the same total drag. D. increased lift, increased lateral stability, and less total drag.
783. JAAExam.com/ATPL Question ID: 1192
Answer A is correct.
Rolling is the rotation of the aeroplane about the:
The correct answer is A
A. longitudinal axis. B. vertical axis. C. lateral axis.
longitudinal axis. References
D. wing axis.
784. JAAExam.com/ATPL Question ID: 557
Answer A is correct.
On a symmetrical aerofoil, the pitch moment for which Cl=0 is:
The correct answer is A zero.
A. zero. B. equal to the moment coefficient for stabilized angle of attack.
References
C. positive (pitch-up). D. negative (pitch-down).
785. JAAExam.com/ATPL Question ID: 969
Answer A is correct.
The Mach cone semi-angle:
The correct answer is A
A. decreases with increasing speed. B. increases with increasing speed. C. decreases up to a certain speed, then increases.
decreases with increasing speed. References
D. remains constant at all speeds above MCRIT.
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786. JAAExam.com/ATPL Question ID: 1374
Answer D is correct.
The first action in event of propeller runaway (overspeed condition), should be to:
The correct answer is D close the throttle.
A. feather the propeller. B. reduce the RPM. lever setting.
References
C. push the RPM. lever fully forward. D. close the throttle.
787. JAAExam.com/ATPL Question ID: 891
Answer B is correct.
During flap down selection in a continuous straight and level flight at constant IAS and weight:
The correct answer is B the centre of pressure moves aft.
A. the lift coefficient and the drag coefficient increase.
References
B. the centre of pressure moves aft. C. the stall speed increases. D. the total boundary layer becomes laminar.
788. JAAExam.com/ATPL Question ID: 1245
Answer D is correct.
Roll is:
The correct answer is D
A. rotation about the longitudinal axis due to speed brake selection.
rotation about the longitudinal axis.
B. rotation about the normal axis.
References
C. due to aileron deflection and is motion about the lateral axis. D. rotation about the longitudinal axis.
789. JAAExam.com/ATPL Question ID: 1553
Answer D is correct.
During a correctly balanced turn:
The correct answer is D
A. the thrust is a component of the centrifugal force.
the lift force provides a centripetal force and a force that opposes the weight of the aircraft.
B. the centrifugal force directly balances the weight of the aircraft.
References
C. the lift force balances the aircraft weight. D. the lift force provides a centripetal force and a force that opposes the weight of the aircraft.
790. JAAExam.com/ATPL Question ID: 1454
Answer B is correct.
Which of the following definitions of propeller parameters is correct?
The correct answer is B
A. Blade angle is the angle between chord line and propeller axis. B. Geometric propeller pitch is the theoretical distance travelled forward by the propeller in one rotation.
Geometric propeller pitch is the theoretical distance travelled forward by the propeller in one rotation. References
C. Critical tip speed is the propeller speed at which there is a risk of the flow separating at some part of the propeller. D. Blade angle of attack is the angle between chord line and propeller vertical axis.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
791. JAAExam.com/ATPL Question ID: 1155
Answer B is correct.
The short period mode is an:
The correct answer is B
A. oscillation about the vertical axis. B. oscillation about the lateral axis. C. oscillation about the longitudinal axis.
oscillation about the lateral axis. References
D. unstable movement of the aeroplane, induced by the pilot.
792. JAAExam.com/ATPL Question ID: 820
Answer C is correct.
An airplane has been loaded in such a manner that the centre of gravity is located behind the aft centre of gravity limit. One undesirable flight characteristic
The correct answer is C
a pilot might experience with this airplane would be: A. the tendency of a wing to stall at high airspeed.
difficulty in recovering from a stalled condition. References
B. a longer takeoff run. C. difficulty in recovering from a stalled condition. D. stalling at higher-than-normal airspeed.
793. JAAExam.com/ATPL Question ID: 1411
Answer C is correct.
An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?
The correct answer is C
A. (2) is larger than (1).
(1) is larger than (2). References
B. (1) is equal to (2). C. (1) is larger than (2). D. impossible to say which one is largest.
794. JAAExam.com/ATPL Question ID: 1167
Answer A is correct.
Which of the following will reduce lateral stability?
The correct answer is A
A. Anhedral. B. Tip tanks. C. Dihedral.
Anhedral. References
D. Wing root fairing.
795. JAAExam.com/ATPL Question ID: 1249
Answer D is correct.
Dutch roll is:
The correct answer is D
A. a type of slow roll. B. primarily a pitching instability. C. a type of static instability.
a combined rolling and yawing motion. References
D. a combined rolling and yawing motion.
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796. JAAExam.com/ATPL Question ID: 684
Answer B is correct.
The induced drag coefficient, CDi is proportional with:
The correct answer is B CL2
A. CL B. CL2
References
C. square root (CL) D. CLmax
797. JAAExam.com/ATPL Question ID: 988
Answer D is correct.
The high speed buffet is induced by:
The correct answer is D
A. a shift of the centre of gravity. B. boundary layer control. C. expansion waves on the wing upper side.
boundary layer separation due to shock waves. References
D. boundary layer separation due to shock waves.
798. JAAExam.com/ATPL Question ID: 1458
Answer A is correct.
On a single engined aircraft with a right hand propeller the gyroscopic effect causes:
The correct answer is A the nose to rise in left turns.
A. the nose to rise in left turns. B. the nose to fall in left turns.
References
C. roll to the right in left turns. D. roll to the left in right turns.
799. JAAExam.com/ATPL Question ID: 548
Answer D is correct.
The chord line is:
The correct answer is D
A. a line tangential to the wing surface at the leading edge.
a straight line from the leading edge of the wing to the trailing edge of the wing.
B. a line perpendicular to the longitudinal axis of the aircraft.
References
C. a line equidistant between intrados and extrados. D. a straight line from the leading edge of the wing to the trailing edge of the wing.
800. JAAExam.com/ATPL Question ID: 500
Answer D is correct.
What is the CL and CD ratio at normal angles of attack?
The correct answer is D CL much higher.
A. CL higher. B. CD higher.
References
C. The same. D. CL much higher.
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801. JAAExam.com/ATPL Question ID: 1416
Answer C is correct.
In an aircraft with a two-lever power control system, in a descent with the throttle closed, what would be the effect if the pitch control were pulled fully back to the flight stop?
The correct answer is C
A. Rate of descent would remain the same and RPM would decrease.
Rate of descent would decrease and RPM would decrease. References
B. Rate of descent would remain the same and RPM would increase. C. Rate of descent would decrease and RPM would decrease. D. Rate of descent would increase and RPM would increase.
802. JAAExam.com/ATPL Question ID: 771
Answer B is correct.
The angle of attack at which an aircraft stalls:
The correct answer is B
A. decreases with an increase in engine power. B. remains constant regardless of gross weight. C. increases with an increase in engine power.
remains constant regardless of gross weight. References
D. varies with gross weight and density altitude.
803. JAAExam.com/ATPL Question ID: 1234
Answer C is correct.
When ailerons are deployed:
The correct answer is C
A. induced drag does not increase on either wing.
induced drag increases on the up going wing.
B. induced drag increases on the down going wing.
References
C. induced drag increases on the up going wing. D. induced drag increases on both wings.
804. JAAExam.com/ATPL Question ID: 1205
Answer B is correct.
Which statement about a jet transport aeroplane is correct during take-off with the cg at the forward limit and the trimmable horizontal stabiliser (THS) positioned at the maximum allowable aeroplane nose down position?
The correct answer is B The rotation will require extra stick force. References
A. If the THS position is just within the limits of the green band, the take off warning system will be activated. B. The rotation will require extra stick force. C. Rotation will be normal. D. Early nose wheel raising will take place.
805. JAAExam.com/ATPL Question ID: 712
Answer A is correct.
The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are:
The correct answer is A decrease of CLmax and increase of drag.
A. decrease of CLmax and increase of drag. B. decrease of CLmax and decrease of drag.
References
C. increase of CLmax and increase of drag. D. increase of CLmax and decrease of drag.
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806. JAAExam.com/ATPL Question ID: 881
Answer B is correct.
What is the purpose of an auto-slat system?
The correct answer is B
A. Provide automatically slat IN selection after take-off.
Extend automatically when a certain value of angle of attack is exceeded.
B. Extend automatically when a certain value of angle of attack is exceeded.
References
C. Ensures that the slats are always extended when the ground/flight system is in the ground position. D. Assist the ailerons during rolling.
807. JAAExam.com/ATPL Question ID: 537
Answer D is correct.
The wing dihedral angle is defined as:
The correct answer is D
A. another term for the sweepback.
the upward inclination of the wing to the lateral axis.
B. the inclination of the wing to the longitudinal axis.
References
C. the inclination of the wing to the vertical axis. D. the upward inclination of the wing to the lateral axis.
808. JAAExam.com/ATPL Question ID: 1571
Answer C is correct.
Refer to Figure: 081-09
The correct answer is C
(Refer to figure 081-09) What flight condition would be represented at point A?
Maximum gliding range. References
A. VMO. B. Minimum power required for level flight. C. Maximum gliding range. D. Best rate of climb speed.
809. JAAExam.com/ATPL Question ID: 1540
Answer C is correct.
Propeller aircraft flown at medium altitude at the recommended EAS will have a better specific air range (SAR) than at sea level because: A. drag is the same.
The correct answer is C engine efficiency is greater. References
B. the power required to maintain level flight is less. C. engine efficiency is greater. D. the thrust required is less.
810. JAAExam.com/ATPL Question ID: 1211
Answer D is correct.
Pitch is movement around the:
The correct answer is D
A. longitudinal axis. B. vertical axis. C. yaw axis.
lateral axis. References
D. lateral axis.
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811. JAAExam.com/ATPL Question ID: 927
Answer D is correct.
Which of the following is the most important result/problem caused by ice formation?
The correct answer is D Reduction in CLMAX.
A. Increased drag. B. Increased weight.
References
C. Blockage of the controls. D. Reduction in CLMAX.
812. JAAExam.com/ATPL Question ID: 835
Answer D is correct.
Which of the following statements about boundary layers is correct?
The correct answer is D
A. The turbulent boundary layer is thinner than the laminar boundary layer. B. The turbulent boundary layer gives a lower skin friction than the laminar boundary layer.
The turbulent boundary layer has more kinetic energy than the laminar boundary layer. References
C. The turbulent boundary layer will separate more easily than the laminar boundary layer. D. The turbulent boundary layer has more kinetic energy than the laminar boundary layer.
813. JAAExam.com/ATPL Question ID: 1433 Increasing the camber on propeller blades will, if all
Answer B is correct.
else is the same: The correct answer is B A. increase the propeller solidity. B. increase the power absorption capability. C. increase the propeller efficiency. D. give the aircraft greater range.
increase the power absorption capability. References
814. JAAExam.com/ATPL Question ID: 812
Answer C is correct.
Two identical aeroplanes A and B are flying horizontal steady turns. Further data are:
The correct answer is C The rate of turn A is larger than the rate of turn B.
A. B.
W=1500 kg Bank= 20° TAS= 130 kt W= 1500 kg Bank= 20° TAS= 200 kt
References
Which of the following statements is correct? A. The turn radius A is larger than the turn radius B. B. The load factor A is larger than the load factor B. C. The rate of turn A is larger than the rate of turn B. D. The lift coefficient A is smaller than the lift coefficient B
815. JAAExam.com/ATPL Question ID: 524
Answer C is correct.
The formula for lift is:
The correct answer is C
A. L = W B. L = 2 RHO V2 S CL C. L = 1/2 RHO V2 S CL
L = 1/2 RHO V2 S CL References
D. L = RHO V S CL
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816. JAAExam.com/ATPL Question ID: 1077
Answer C is correct.
If an aircraft has its CG ahead of its CP, in straight and level flight:
The correct answer is C there will normally be a download on the tailplane.
A. there will normally be an upload on the tailplane. B. the tailplane will have a negative angle of attack. C. there will normally be a download on the tailplane. D. there will normally be no load on the tailplane.
References
817. JAAExam.com/ATPL Question ID: 585
Answer C is correct.
Under which condition will pressure altitude be equal to true altitude?
The correct answer is C When standard atmospheric conditions exist.
A. Never. B. When the atmospheric pressure is 29.92 Hg.
References
C. When standard atmospheric conditions exist. D. When indicated altitude is equal to the pressure altitude.
818. JAAExam.com/ATPL Question ID: 1341
Answer B is correct.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42, increase in angle of attack of 1 degree increases CL by is 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:
The correct answer is B 1.71 References
A. 0.74 B. 1.71 C. 1.49 D. 2.49
819. JAAExam.com/ATPL Question ID: 895
Answer B is correct.
How is the pitching moment affected if flaps are deployed in straight and level flight?
The correct answer is B Pitch down.
A. Pitch up. B. Pitch down.
References
C. Depends on CG position. D. Flap deployment has no effect on aircraft pitching moment.
820. JAAExam.com/ATPL Question ID: 527
Answer A is correct.
The Mean Aerodynamic Chord (MAC) for a given wing of any platform is:
The correct answer is A
A. the chord of a rectangular wing with same moment and lift. B. the chord of a large rectangular wing.
the chord of a rectangular wing with same moment and lift. References
C. the average chord of the actual aeroplane. D. the wing area divided by the wing span.
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821. JAAExam.com/ATPL Question ID: 1039
Answer D is correct.
Which statement is correct about an expansion wave in supersonic flow?
The correct answer is D 1 is correct and 2 is incorrect.
1. 2.
The temperature in front of an expansion wave is higher than the temperature behind it
References
The speed in front of an expansion wave is higher than the speed behind it.
A. 1 and 2 are incorrect. B. 1 and 2 are correct. C. 1 is incorrect and 2 is correct. D. 1 is correct and 2 is incorrect.
822. JAAExam.com/ATPL Question ID: 864
Answer D is correct.
Which statement is correct?
The correct answer is D
A. Spoiler extension decreases the stall speed and the minimum rate of descent, but increases the minimum descent angle.
Extension of flaps causes a reduction of the stall speed, the maximum glide distance also reduces.
B. Extension of flaps will increase (CL/CD)max, causing the minimum rate of descent to decrease.
References
C. Extension of flaps has no influence on the minimum rate of descent, as only the TAS has to be taken into account. D. Extension of flaps causes a reduction of the stall speed, the maximum glide distance also reduces.
823. JAAExam.com/ATPL Question ID: 765
Answer D is correct.
If VS is 100 kt in straight and level flight, during a 45 bank turn VS will be:
The correct answer is D 119 kts
A. 100 kts B. 140 kts
References
C. 80 kts D. 119 kts
824. JAAExam.com/ATPL Question ID: 1050
Answer D is correct.
In order to expand a gas to supersonic speeds, starting with a stagnant gas in a reservoir, a... duct must be used.
The correct answer is D
A. convergent B. convergent-divergent C. constant area D. divergent
divergent References
825. JAAExam.com/ATPL Question ID: 889
Answer A is correct.
Deflection of leading edge flaps will:
The correct answer is A
A. increase critical angle of attack. B. decrease CLmax. C. decrease drag.
increase critical angle of attack. References
D. not affect critical angle of attack.
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826. JAAExam.com/ATPL Question ID: 713
Answer C is correct.
Extending airbrakes during an approach will:
The correct answer is C
A. increase induced drag. B. increase minimum drag speed (VDmin). C. reduce the minimum drag speed (VDmin).
reduce the minimum drag speed (VDmin). References
D. decrease profile drag.
827. JAAExam.com/ATPL Question ID: 1358
Answer B is correct.
Running an engine fitted with a fixed pitch propeller at full throttle with the aircraft stationary and nose into a strong headwind will result in a:
The correct answer is B
A. variable RPM depending on the CSU.
higher RPM than in still air. References
B. higher RPM than in still air. C. lower RPM than in still air. D. the same RPM as in still air.
828. JAAExam.com/ATPL Question ID: 1259
Answer B is correct.
A horn balance is an example of a:
The correct answer is B
A. mass balance. B. aerodynamic balancing panel. C. trim tab.
aerodynamic balancing panel. References
D. convergent-divergent nozzle.
829. JAAExam.com/ATPL Question ID: 622
Answer B is correct.
With increasing angle of attack, the stagnation point will move (I) and the point of lowest pressure will move (II).
The correct answer is B
A. (I) up, (II) aft.
(I) down, (II) forward. References
B. (I) down, (II) forward. C. (I) down, (II) aft. D. (I) up, (II) forward.
830. JAAExam.com/ATPL Question ID: 1302
Answer C is correct.
In flight the flutter of a control surface is normally reduced by:
The correct answer is C weights acting forward of the hinge line.
A. use of balance tabs. B. weights acting aft of the hinge line.
References
C. weights acting forward of the hinge line. D. weights acting on the hinge line.
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831. JAAExam.com/ATPL Question ID: 552
Answer D is correct.
What happens to total drag when accelerating from CL MAX to maximum speed?
The correct answer is D Decreases then increases.
A. Increases. B. Increases then decreases.
References
C. Decreases. D. Decreases then increases.
832. JAAExam.com/ATPL Question ID: 1120
Answer C is correct.
Longitudinal stability will be greatest: A. with the centre of gravity on the forward limit.
References
B. with the centre of gravity on the aft limit. C. when the centre of gravity is most forward. D. when the centre of gravity is coincident with the centre of pressure.
833. JAAExam.com/ATPL Question ID: 1230
Answer B is correct.
Rolling means rotating about the:
The correct answer is B
A. lateral axis. B. longitudinal axis. C. normal axis. D. airplane axis.
longitudinal axis. References
834. JAAExam.com/ATPL Question ID: 1200
Answer C is correct.
Rotation about the lateral axis is called:
The correct answer is C
A. yawing. B. slipping. C. pitching.
pitching. References
D. rolling.
835. JAAExam.com/ATPL Question ID: 1310
Answer C is correct.
What is the relationship of VMO and MMO, in a climb and descent?
The correct answer is C If climbing at VMO, it is possible to exceed MMO.
A. If climbing at VMO, Mach number is decreasing.
References
B. If climbing at MMO, Indicated Airspeed is increasing. C. If climbing at VMO, it is possible to exceed MMO. D. If descending at MMO, VMO cannot be exceeded.
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836. JAAExam.com/ATPL Question ID: 554
Answer D is correct.
If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow:
The correct answer is D
A. The density depends on the change of the tube area.
rho1 = rho2 References
B. rho1 < rho2 C. rho1 > rho2 D. rho1 = rho2
837. JAAExam.com/ATPL Question ID: 842
Answer D is correct.
Which of the following statements about the stall of a straight wing aeroplane is correct?
The correct answer is D
A. The horizontal tail will stall at a higher speed than the wing. B. Buffeting is the result of flow separation on the tail plane. C. The nose down effect is the result of increasing downwash, due to flow separation. D. Just before the stall the aeroplane will have a nose-down tendency.
Just before the stall the aeroplane will have a nosedown tendency. References
838. JAAExam.com/ATPL Question ID: 887
Answer C is correct.
The effects of leading edge slats:
The correct answer is C
A. increase boundary layer energy, move suction peak on to slat and increase CLMAX angle of attack.
increase boundary layer energy, increase suction peak on main wing section, move CLMAX to a higher angle of attack.
B. increase camber, increase suction peak on main wing, increase effective angle of attack and move CLMAX to higher angle of attack.
References
C. increase boundary layer energy, increase suction peak on main wing section, move CLMAX to a higher angle of attack. D. decrease boundary layer energy, move suction peak onto slat, move CLMAX to a lower angle of attack.
839. JAAExam.com/ATPL Question ID: 1349
Answer B is correct.
What wing shape or wing characteristic is the least sensitive to turbulence:
The correct answer is B swept wings.
A. straight wings. B. swept wings.
References
C. wing dihedral. D. winglets.
840. JAAExam.com/ATPL Question ID: 1515
Answer C is correct.
For a glider to obtain a maximum gliding distance, the airspeed to be flown is:
The correct answer is C
A. the minimum power speed. B. the minimum control speed. C. the airspeed which corresponds to the best lift-to-drag ratio.
the airspeed which corresponds to the best lift-todrag ratio. References
D. the minimum sink speed.
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841. JAAExam.com/ATPL Question ID: 1003
Answer A is correct.
The buffet margin:
The correct answer is A
A. increases during a descent with a constant IAS.
increases during a descent with a constant IAS.
B. is always greatest after a step climb has been executed.
References
C. decreases during a descent with a constant Mach number. D. is always positive at Mach numbers below MMO.
842. JAAExam.com/ATPL Question ID: 1461
Answer D is correct.
Counter-rotating propellers have the effect of:
The correct answer is D
A. increasing the torque but decreasing the gyroscopic effect.
cancelling out the torque and gyroscopic effects.
B. decreasing the torque but increasing the gyroscopic effect.
References
C. increasing the torque and gyroscopic effects. D. cancelling out the torque and gyroscopic effects.
843. JAAExam.com/ATPL Question ID: 1512
Answer B is correct.
In a level turn:
The correct answer is B
A. lift equals the weight. B. the component of the lift in the vertical direction equals the weight. C. the component of the lift in the horizontal direction equals the weight.
the component of the lift in the vertical direction equals the weight. References
D. the load factor decreases.
844. JAAExam.com/ATPL Question ID: 532
Answer B is correct.
Longitudinal dihedral is:
The correct answer is B
A. the difference between the wing and tail angle of sweep.
the difference between the wing and tail angle of incidence.
B. the difference between the wing and tail angle of incidence.
References
C. when the wing has anhedral and the tail dihedral. D. the difference between the wing and tail dihedral angles.
845. JAAExam.com/ATPL Question ID: 653
Answer B is correct.
The drag coefficient of a sphere is approximately:
The correct answer is B
A. 0.0015 B. 0.25 C. 2
0.25 References
D. 250
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846. JAAExam.com/ATPL Question ID: 1543 An aeroplane performs a continuous descent with
Answer D is correct.
160 kts IAS and 1000 feet/min vertical speed. In this condition:
The correct answer is D
A. drag is less than the combined forces that move the aeroplane forward.
weight is greater than lift.
B. lift is equal to weight.
References
C. lift is less than drag. D. weight is greater than lift.
847. JAAExam.com/ATPL Question ID: 1306
Answer D is correct.
The relationship between the stall speed VS and VA (EAS) for a large transport aeroplane can be expressed in the following formula: (SQRT= square root)
The correct answer is D
A. Va = VA SQRT(3.75)
VA = VS SQRT(2.5) References
B. VS = VA SQRT(2.5) C. VS = VA SQRT(3.75) D. VA = VS SQRT(2.5)
848. JAAExam.com/ATPL Question ID: 1353
Answer D is correct.
Which statement is correct about the gust load on an aeroplane (IAS and all other factors of importance remaining constant:
The correct answer is D
1.
the gust load increases, when the weight decreases.
2.
the gust load increases, when the altitude increases.
1 is correct and 2 is incorrect. References
A. 1 is incorrect and 2 is correct. B. 1 and 2 are correct. C. 1 and 2 are incorrect. D. 1 is correct and 2 is incorrect.
849. JAAExam.com/ATPL Question ID: 1509
Answer B is correct.
Which of the following is the correct formula to calculate the lift component in a steady climb (µ is the angle of climb)?
The correct answer is B
A. W x (1-sin(µ ))
W x cos(µ ) References
B. W x cos(µ ) C. W x (1-tan(µ )) D. W / cos(µ )
850. JAAExam.com/ATPL Question ID: 758
Answer C is correct.
When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be: A. 169%.
The correct answer is C 59%. References
B. 130%. C. 59%. D. 77%.
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851. JAAExam.com/ATPL Question ID: 1486
Answer D is correct.
The stalling speed of an aircraft in a turn is equal to:
The correct answer is D
A. the basic stalling speed x the cos(angle of bank). B. the inverse of the load factor. C. the basic stalling speed.
the basic stalling speed x the square root of the load factor. References
D. the basic stalling speed x the square root of the load factor.
852. JAAExam.com/ATPL Question ID: 514
Answer B is correct.
The direction of drag is:
The correct answer is B
A. parallel to longitudinal axis of the aircraft. B. parallel to the free stream airflow. C. perpendicular to the longitudinal axis of the aircraft.
parallel to the free stream airflow. References
D. perpendicular to the free stream airflow.
853. JAAExam.com/ATPL Question ID: 1431
Answer D is correct.
Why is a propeller blade twisted from root to tip?
The correct answer is D
A. To ensure that the tip produces most thrust. B. Because the local angle of attack of a blade segment is dependent on the ratio of that segments speed in the plane of rotation and the angular velocity of the propellers. C. To ensure that the root produces most thrust.
Because the local angle of attack of a blade segment is dependent on the ratio of that segments speed in the plane of rotation and the true airspeed of the aeroplane. References
D. Because the local angle of attack of a blade segment is dependent on the ratio of that segments speed in the plane of rotation and the true airspeed of the aeroplane.
854. JAAExam.com/ATPL Question ID: 627
Answer C is correct.
On a cambered airfoil the zero lift angle of attack will be:
The correct answer is C negative.
A. dependent on the wing aspect ratio. B. positive.
References
C. negative. D. zero.
855. JAAExam.com/ATPL Question ID: 598
Answer D is correct.
Which one of the following statements about Bernoulli’ s theorem is correct?
The correct answer is D
A. The dynamic pressure is maximum in the stagnation point. B. The dynamic pressure decreases as static pressure decreases.
The dynamic pressure increases as static pressure decreases. References
C. The total pressure is zero when the velocity of the stream is zero. D. The dynamic pressure increases as static pressure decreases.
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856. JAAExam.com/ATPL Question ID: 1011
Answer D is correct.
In transonic flight the ailerons will be less effective than in subsonic flight because:
The correct answer is D
A. behind the shock wave pressure is lower.
aileron deflection only partly affects the pressure distribution around the wing.
B. aileron down deflection moves the shock wave forward.
References
C. aileron deflection only affects the air in front of the shock wave. D. aileron deflection only partly affects the pressure distribution around the wing.
857. JAAExam.com/ATPL Question ID: 469
Answer A is correct.
The units of the density of the air (I) and the force (II) are:
The correct answer is A w(I) kg / m3, (II) N.
A. w(I) kg / m3, (II) N. B. w(I) kg / m?, (II) kg.
References
C. w(I) N / m3, (II) N. D. w(I) N / kg, (II) kg
858. JAAExam.com/ATPL Question ID: 1563
Answer A is correct.
The effect of a headwind is to ... the climb gradient and to ... the rate of climb.
The correct answer is A increase; not affect
A. increase; not affect B. increase; decrease
References
C. decrease; increase D. not affect; increase
859. JAAExam.com/ATPL Question ID: 1015
Answer D is correct.
When the air has passed through a normal shock wave the Mach number is?
The correct answer is D Less than 1.
A. Higher than before. B. Lower than before but still greater than 1.
References
C. Equal to 1. D. Less than 1.
860. JAAExam.com/ATPL Question ID: 1288
Answer C is correct.
What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
The correct answer is C
A. If possible, relocate as many passengers as possible to the front of the cabin.
Choose a higher landing speed than normal and/or use a lower flap setting for landing. References
B. Choose a lower landing speed than normal. C. Choose a higher landing speed than normal and/or use a lower flap setting for landing. D. Use the Mach trimmer until after landing.
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861. JAAExam.com/ATPL Question ID: 696
Answer C is correct.
Which location on the aeroplane has the largest effect on the induced drag?
The correct answer is C Wing tip.
A. Wing root junction. B. Engine cowling.
References
C. Wing tip. D. Landing gear.
862. JAAExam.com/ATPL Question ID: 1113
Answer B is correct.
The effect of a highly cambered airfoil on longitudinal stability will be?
The correct answer is B No effect.
A. Positive effect because the lift vector is inclined rearwards as angle of attack increases.
References
B. No effect. C. Negative effect because the lift vector is inclined forwards as angle of attack increases. D. Positive effect as CP moves backwards as angle of attack increases.
863. JAAExam.com/ATPL Question ID: 1129
Answer B is correct.
Tuck under is:
The correct answer is B
A. the tendency to nose up when speed is increased into the transonic flight regime.
the tendency to nose down when speed is increased into the transonic flight regime.
B. the tendency to nose down when speed is increased into the transonic flight regime.
References
C. shaking of the control column at high Mach Number. D. the tendency to nose down when the control column is pulled back.
864. JAAExam.com/ATPL Question ID: 1022
Answer D is correct.
The consequences of exceeding Mcrit in a sweptwing aeroplane may be: (assume no corrective devices, straight and level flight)
The correct answer is D
A. buffeting of the aeroplane and a tendency to pitch up.
buffeting of the aeroplane and a tendency to pitch down. References
B. an increase in speed and a tendency to pitch up. C. engine unbalance and buffeting. D. buffeting of the aeroplane and a tendency to pitch down.
865. JAAExam.com/ATPL Question ID: 1160
Answer B is correct.
Considering the lateral stability of a swept wing aircraft, at high level the static lateral stability will be ... and the dynamic lateral stability will be...
The correct answer is B
A. greater; greater.
the same; less. References
B. the same; less. C. less; greater. D. the same; greater.
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866. JAAExam.com/ATPL Question ID: 491
Answer C is correct.
If the weight an aircraft is increased, the maximum lift/drag ratio will:
The correct answer is C not be affected.
A. decrease. B. increase.
References
C. not be affected. D. increase although the aircraft will have to be flown more slowly.
867. JAAExam.com/ATPL Question ID: 986
Answer C is correct.
At an aircraft weight of 70,000lb your aerodynamic ceiling in 1g level flight will be:
The correct answer is C FL420
A. FL320 B. FL390
References
C. FL420 D. FL440
868. JAAExam.com/ATPL Question ID: 523
Answer D is correct.
The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is:
The correct answer is D
A. sonic.
decreasing. References
B. not changing. C. increasing. D. decreasing.
869. JAAExam.com/ATPL Question ID: 954
Answer A is correct.
The speed of sound is a function of altitude because:
The correct answer is A
A. temperature varies with altitude. B. pressure varies with altitude. C. both pressure and temperature vary decrease when altitude increases.
temperature varies with altitude. References
D. sound waves reflect on the ionosphere.
870. JAAExam.com/ATPL Question ID: 657
Answer B is correct.
The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:
The correct answer is B
A. the top to beneath the wing via the wings trailing edge.
beneath to the top of the wing via the wing tip. References
B. beneath to the top of the wing via the wing tip. C. beneath to the top of the wing via the trailing edge. D. the top to beneath the wing via the leading edge.
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871. JAAExam.com/ATPL Question ID: 1482
Answer B is correct.
When an aircraft is descending with the engines running at idle RPM:
The correct answer is B thrust is less than drag.
A. lift is equal to weight. B. thrust is less than drag.
References
C. thrust equals weight. D. only profile drag is produced.
872. JAAExam.com/ATPL Question ID: 1343
Answer D is correct.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. Increase of angle of attack of 1 degree will increase CL by 0.09. A vertical up gust instantly changes the angle of attack by 5 degrees. The load factor will be:
The correct answer is D 2.13 References
A. 3.18 B. 1.09 C. 2.0 D. 2.13
873. JAAExam.com/ATPL Question ID: 459
Answer A is correct.
In recovery from a spin:
The correct answer is A
A. ailerons should be kept neutral. B. airspeed increases. C. ailerons used to stop the spin.
ailerons should be kept neutral. References
D. rudder and ailerons used against the direction of spin rotation.
874. JAAExam.com/ATPL Question ID: 833
Answer C is correct.
Which of the following is the speed in level flight that would activate the stall warning?
The correct answer is C 1.05VS1G
A. VS1G + 15kts B. 1.2VS1G C. 1.05VS1G
References
D. 1.5VS1G
875. JAAExam.com/ATPL Question ID: 1289
Answer A is correct.
Which statement about a jet transport aeroplane is correct, during take-off at the maximum allowable forward centre of gravity limit, while the THS (Trimmable Horizontal Stabilizer) has been positioned at the maximum allowable AND (Aeroplane Nose Down) position.
The correct answer is A The rotation will require extra stick force. References
A. The rotation will require extra stick force. B. If the THS position is just within the limits of the green band, the take off warning system will be activated. C. Early nose wheel raising will take place. D. Nothing special will happen.
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876. JAAExam.com/ATPL Question ID: 796
Answer D is correct.
The most important problem of ice accretion on an aeroplane during flight is:
The correct answer is D reduction in CLmax.
A. blocking of control surfaces. B. increase in weight.
References
C. increase in drag. D. reduction in CLmax.
877. JAAExam.com/ATPL Question ID: 830
Answer B is correct.
The following take place at the transition point on a wing:
The correct answer is B
A. the airflow separates completely from the wing surface. B. the boundary layer makes the transition from laminar flow to the turbulent boundary layer.
the boundary layer makes the transition from laminar flow to the turbulent boundary layer. References
C. the total dynamic and static pressure comes to a standstill. D. the laminar flow meets the separation point.
878. JAAExam.com/ATPL Question ID: 732
Answer C is correct.
In straight and level flight, which of the following would cause induced drag to vary linearly if weight is constant:
The correct answer is C
A. 1/V B. V
1/V2 References
C. 1/V2 D. V2
879. JAAExam.com/ATPL Question ID: 1407
Answer B is correct.
A typical fixed pitch propeller (C-172) is designed to achieve its optimum angle of attack at:
The correct answer is B cruise speed.
A. low forward speeds, such as during take off. B. cruise speed.
References
C. rest to case engine starting. D. maximum speed for high performance.
880. JAAExam.com/ATPL Question ID: 1480
Answer D is correct.
The turn indicator shows a right turn. The slip indicator is left of neutral. To coordinate the turn:
The correct answer is D more right bank is required.
A. a higher turn rate is required. B. more right rudder is required.
References
C. less right bank is required. D. more right bank is required.
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881. JAAExam.com/ATPL Question ID: 841
Answer B is correct.
If an aircraft has a stalling speed of 90 kts IAS (n=1), what will be the stalling speed in a 60° level and coordinated turn?
The correct answer is B
A. 99 kts
127 kts References
B. 127 kts C. 112 kts D. 90 kts
882. JAAExam.com/ATPL Question ID: 1261
Answer D is correct.
Examples of aerodynamic balancing of control surfaces are:
The correct answer is D
A. spring tab, servo tab, and power assisted control. B. balance tab, horn balance, and mass balance. C. mass in the nose of the control surface, horn balance and mass balance. D. servo tab, spring tab, seal between the wing trailing edge and the leading edge of control surface.
servo tab, spring tab, seal between the wing trailing edge and the leading edge of control surface. References
883. JAAExam.com/ATPL Question ID: 840
Answer D is correct.
Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
The correct answer is D
A. 1.20 VS
greater than VS. References
B. 1.30 VS C. 1.12 VS D. greater than VS.
884. JAAExam.com/ATPL Question ID: 616
Answer B is correct.
When Fowler flaps are deployed?
The correct answer is B
A. Only the area increases. B. They move backwards then downwards. C. They move downwards then backwards.
They move backwards then downwards. References
D. They move forwards.
885. JAAExam.com/ATPL Question ID: 1007
Answer A is correct.
Vortex generators on the upper side of the wing surface will:
The correct answer is A
A. decrease the intensity of shock wave induced air separation. B. increase the critical Mach Number.
decrease the intensity of shock wave induced air separation. References
C. decrease the span wise flow at high Mach Numbers. D. increase the magnitude of the shock wave.
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886. JAAExam.com/ATPL Question ID: 1147
Answer A is correct.
A swept wing will for a given angle of attack and wing area:
The correct answer is A be more laterally stable and produce less lift.
A. be more laterally stable and produce less lift. B. produce more lift and be more laterally stable.
References
C. increase lateral stability with reduced tip stall tendency. D. advance Mcrit.
887. JAAExam.com/ATPL Question ID: 664
Answer B is correct.
Which ratio is defined as the aspect ratio of a wing?
The correct answer is B
A. Ratio between wing span and gross wing area.
Ratio between span and mean chord.
B. Ratio between span and mean chord.
References
C. Ratio between the span and the square of the gross wing area. D. Ratio between the square of the span and the mean chord.
888. JAAExam.com/ATPL Question ID: 718
Answer B is correct.
During cruise, VDmin (Minimum drag speed) will:
The correct answer is B
A. increase. B. decrease. C. remain unchanged.
decrease. References
D. increase or decrease depending on the centre of gravity position.
889. JAAExam.com/ATPL Question ID: 998
Answer B is correct.
What data may be obtained from the Buffet Onset Boundary chart?
The correct answer is B
A. The values of MMO at different weights and altitudes. B. The values of the Mach Number at which low speed and Mach Buffet occur at different weights and altitudes.
The values of the Mach Number at which low speed and Mach Buffet occur at different weights and altitudes. References
C. The values of Mcrit at different weights and altitudes. D. The values of the Mach Number at which low speed and shock-stall occur at different weights and altitudes.
890. JAAExam.com/ATPL Question ID: 1059
Answer C is correct.
When an aircraft is flying at speeds above Mach 1, pressure disturbances from the aircraft will be felt only:
The correct answer is C
A. in front of the normal shock wave.
within the Mach cone. References
B. in front of the Mach cone. C. within the Mach cone. D. in front of the oblique shock wave.
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891. JAAExam.com/ATPL Question ID: 1457
Answer B is correct.
Gyroscopic precession of the propeller is induced by: A. pitching and rolling. B. pitching and yawing. C. increasing RPM and yawing.
The correct answer is B pitching and yawing. References
D. increasing RPM and rolling.
892. JAAExam.com/ATPL Question ID: 816
Answer B is correct.
In a level turn with 60° lateral bank, the load factor is 2.0 and the stall speed increases by:
The correct answer is B 40 %
A. 50 % B. 40 %
References
C. 10 % D. 20 %
893. JAAExam.com/ATPL Question ID: 1364
Answer B is correct.
The centrifugal turning or twisting moment on a propeller will:
The correct answer is B
A. cause the blades to move to a coarser pitch when rotating. B. cause the blades to move to a finer pitch when rotating.
cause the blades to move to a finer pitch when rotating. References
C. cause the blades to pitch lock in neutral when rotating. D. cause the blades to the feathering position when oil supply pressure fails.
894. JAAExam.com/ATPL Question ID: 1171
Answer A is correct.
When pulling out of a dive the angle of attack:
The correct answer is A
A. increases. B. decreases. C. remains the same.
increases. References
D. cannot be increased at all due to structural considerations.
895. JAAExam.com/ATPL Question ID: 1296
Answer C is correct.
If an elevator gets jammed in the neutral position during flight, moving the elevator trim tab down will cause:
The correct answer is C
A. a pitch-up moment.
a pitch-down moment. References
B. no effect at all. C. a pitch-down moment. D. the airplane to maintain its attitude.
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896. JAAExam.com/ATPL Question ID: 1356
Answer B is correct.
On an aircraft fitted with a variable pitch propeller, if engine RPM is to remain constant when engine power is increased, it requires:
The correct answer is B
A. a decrease in blade angle.
an increase in blade angle. References
B. an increase in blade angle. C. a decrease in blade angle of attack. D. a constant blade angle of attack to be maintained.
897. JAAExam.com/ATPL Question ID: 452
Answer B is correct.
the density change in the flow is less than:
The correct answer is B
A. 1%. B. 5%. C. 15%.
5%. References
D. 30%.
898. JAAExam.com/ATPL Question ID: 580
Answer D is correct.
Wing loading is:
The correct answer is D
A. the ratio of lift to wing weight. B. the ratio of wing area to wing weight. C. the ratio of lift to aircraft weight.
the ratio of aircraft weight to wing area. References
D. the ratio of aircraft weight to wing area.
899. JAAExam.com/ATPL Question ID: 680
Answer B is correct.
Which statement about induced drag and tip vortices is correct?
The correct answer is B
A. Tip vortices can be diminished by vortex generators. B. The flow direction at the upper side of the wing has a component in wing root direction, the flow at the underside of the wing in wing tip direction. C. The flow direction at the upper and under side of the wing, both deviate in wing tip
The flow direction at the upper side of the wing has a component in wing root direction, the flow at the underside of the wing in wing tip direction. References
direction. D. The wing tip vortices and the induced drag decrease at increasing angle of attack.
900. JAAExam.com/ATPL Question ID: 1378
Answer C is correct.
During normal operation of a constant speed propeller, what might be the reason for no oil flow within the C.S.U.?
The correct answer is C
A. The propeller is moving to the feathered position.
The propeller is on speed. References
B. Propeller RPM is too low. C. The propeller is on speed. D. The propeller is in overspeed.
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901. JAAExam.com/ATPL Question ID: 1141
Answer C is correct.
Compared to straight wings, swept back wings have:
The correct answer is C
A. less directional stability. B. better longitudinal stability. C. better directional stability.
better directional stability. References
D. less longitudinal stability
902. JAAExam.com/ATPL Question ID: 1298
Answer D is correct.
Power assisted flying control systems have trim controls primarily in order to:
The correct answer is D bring the control forces to zero in steady flight.
A. allow the pilot to maintain control in case of hydraulic failure.
References
B. relieve stresses on the trim tab. C. relieve stresses on the hydraulic actuators. D. bring the control forces to zero in steady flight.
903. JAAExam.com/ATPL Question ID: 510
Answer C is correct.
In subsonic flight, which is correct for VMD?
The correct answer is C
A. Parasite drag greater than induced drag. B. CL and CD are minimum. C. Best glide range achieved. D. Best endurance speed for a piston engine.
Best glide range achieved. References
904. JAAExam.com/ATPL Question ID: 1338
Answer D is correct.
The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is:
The correct answer is D 2.0
A. 3.75 B. 1.5
References
C. 2.5 D. 2.0
905. JAAExam.com/ATPL Question ID: 749
Answer C is correct.
What will happen in ground effect?
The correct answer is C
A. An increase in strength of the wing tip vortices.
The induced angle of attack and induced drag decreases.
B. The wing downwash on the tail surfaces increases.
References
C. The induced angle of attack and induced drag decreases. D. A significant increase in thrust required.
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906. JAAExam.com/ATPL Question ID: 1345
Answer C is correct.
The shape of the gust load diagram is also determined by the following three vertical speed in ft/s (clean configuration):
The correct answer is C
A. 25, 55, 75
25, 50, 66 References
B. 15, 56, 65 C. 25, 50, 66 D. 35, 55, 66
907. JAAExam.com/ATPL Question ID: 778
Answer C is correct.
Which stall has the greatest angle of attack?
The correct answer is C
A. Low speed stall. B. High speed stall (shock stall). C. Deep stall.
Deep stall. References
D. Accelerated stall.
908. JAAExam.com/ATPL Question ID: 1128
Answer C is correct.
Which of the following statements is correct?
The correct answer is C
A. Dynamic stability means that after being
Dynamic stability is possible only when the aeroplane
displaced from original equilibrium condition, the aeroplane will return to that condition without oscillation.
is statically stable about the relevant axis. References
B. Static stability means that the aeroplane is also dynamically stable about the relevant axis. C. Dynamic stability is possible only when the aeroplane is statically stable about the relevant axis. D. A dynamically stable aeroplane would be almost impossible to fly manually.
909. JAAExam.com/ATPL Question ID: 481
Answer A is correct.
The lateral axis is also called the:
The correct answer is A
A. pitch axis. B. normal axis. C. roll axis.
pitch axis. References
D. horizontal axis.
910. JAAExam.com/ATPL Question ID: 1079
Answer C is correct.
In which situation would the wing lift of an aeroplane in straight and level flight have the highest value? (The engines are mounted below the wing)?
The correct answer is C
A. Forward centre of gravity and take-off thrust.
Forward centre of gravity and idle thrust. References
B. Aft centre of gravity and idle thrust. C. Forward centre of gravity and idle thrust. D. Aft centre of gravity and take-off thrust.
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911. JAAExam.com/ATPL Question ID: 633
Answer A is correct.
An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
The correct answer is A
A. x 0.25
x 0.25 References
B. x 2.0 C. x 0.5 D. x 4.0
912. JAAExam.com/ATPL Question ID: 956
Answer A is correct.
A shock stall occurs when laminar flow breaks down:
The correct answer is A
A. behind the shock wave.
behind the shock wave.
B. behind the trailing edge.
References
C. behind the leading edge. D. at a high angle of attack and high Mach number.
913. JAAExam.com/ATPL Question ID: 1556
Answer C is correct.
During the glide, the forces acting on an aircraft are:
The correct answer is C
A. thrust, lift and drag. B. lift, weight and thrust. C. lift, drag and weight.
lift, drag and weight. References
D. drag, thrust and weight.
914. JAAExam.com/ATPL Question ID: 660
Answer A is correct.
Induced drag is also known as:
The correct answer is A
A. vortex drag. B. skin friction drag. C. interference drag.
vortex drag. References
D. form drag.
915. JAAExam.com/ATPL Question ID: 968
Answer D is correct.
In the transonic range the aeroplane characteristics are strongly determined by:
The correct answer is D the Mach Number.
A. the CAS. B. the TAS.
References
C. the IAS. D. the Mach Number.
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916. JAAExam.com/ATPL Question ID: 1177
Answer A is correct.
When are outboard ailerons (if present) deactivated?
The correct answer is A
A. Flaps (and slats) retracted or speed above a certain value. B. Flaps (and/or slats) extended or speed below a certain value. C. Landing gear retracted. D. Landing gear extended.
Flaps (and slats) retracted or speed above a certain value. References
917. JAAExam.com/ATPL Question ID: 1056
Answer C is correct.
Consider insentropic flow in a stream tube. If the flow is supersonic (M>1), for the velocity to increase:
The correct answer is C
A. the area of the stream tube must decrease.
the area of the stream tube must increase. References
B. the area of the stream tube must first increase and then decrease. C. the area of the stream tube must increase. D. the area of the nozzle must first decrease and then increase.
918. JAAExam.com/ATPL Question ID: 566
Answer B is correct.
If density is kept constant, the dynamic pressure increases proportionally with:
The correct answer is B the square of the velocity.
A. velocity. B. the square of the velocity.
References
C. the static pressure. D. inversely with the square of the velocity
919. JAAExam.com/ATPL Question ID: 1412
Answer C is correct.
A twin-engine aircraft is available in both jet and propeller variants. The engines are mounted on the wings in the same position in both types. In the case of failure of one engine how would the resultant roll effect show itself?
The correct answer is C
A. Jet: roll toward the dead engine; Propeller roll toward the live engine.
Jet: roll away from the live engine; Propeller: roll away from the live engine more rapidly. References
B. Jet: roll toward the live engine; Propeller: roll toward the dead engine. C. Jet: roll away from the live engine; Propeller: roll away from the live engine more rapidly. D. Jet: no change but; Propeller roll opposite to direction of rotation of the live engine.
920. JAAExam.com/ATPL Question ID: 1460
Answer C is correct.
The torque reaction of a right-hand propeller will cause:
The correct answer is C roll to the left.
A. roll to the right. B. nose up pitch.
References
C. roll to the left. D. nose down pitch.
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921. JAAExam.com/ATPL Question ID: 844
Answer C is correct.
Which aeroplane design has the highest probability of a super stall?
The correct answer is C Swept wings.
A. A canard wing. B. A T-tail.
References
C. Swept wings. D. A low horizontal tail.
922. JAAExam.com/ATPL Question ID: 733
Answer A is correct.
If pressure increases, with OAT and TAS constant, what happens to drag?
The correct answer is A Increase.
A. Increase. B. Decrease.
References
C. Remain constant. D. Drag is dependant only on dynamic pressure.
923. JAAExam.com/ATPL Question ID: 837
Answer C is correct.
Which of the following statements about the spin is correct?
The correct answer is C
A. In the spin, airspeed continuously increases.
During spin recovery the ailerons should be kept in the neutral position.
B. An aeroplane is prone to spin when the stall starts at the wing root.
References
C. During spin recovery the ailerons should be kept in the neutral position. D. Every aeroplane should be designed such that it can never enter a spin.
924. JAAExam.com/ATPL Question ID: 1451
Answer A is correct.
On a single engined aircraft with a right hand propeller the gyroscopic effect causes:
The correct answer is A the nose to rise during turn to the left.
A. the nose to rise during turn to the left. B. the nose to fall during turns to the left.
References
C. roll to the right during turns to the left. D. roll to the left during turns to the right.
925. JAAExam.com/ATPL Question ID: 1124
Answer C is correct.
The short-period mode of longitudinal dynamic stability is:
The correct answer is C a rapid oscillation about the lateral axis.
A. a rapid oscillation about the normal axis.
B. a rapid oscillation about the longitudinal axis.
References
C. a rapid oscillation about the lateral axis. D. always induced by the pilot.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
926. JAAExam.com/ATPL Question ID: 966
Answer A is correct.
The speed of sound in a more compressible fluid, compared to a less compressible fluid is:
The correct answer is A higher.
A. higher. B. lower.
References
C. the same. D. lower or higher depending on fluid density.
927. JAAExam.com/ATPL Question ID: 939
Answer C is correct.
There are two types of boundary layer: laminar and turbulent. One important advantage the turbulent boundary layer has over the laminar type is that:
The correct answer is C
A. skin friction drag is less.
it has less tendency to separate from the surface. References
B. it is thinner. C. it has less tendency to separate from the surface. D. energy is less.
928. JAAExam.com/ATPL Question ID: 1012
Answer B is correct.
When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
The correct answer is B
A. on the underside of the wing.
at the wing root segment, upper side. References
B. at the wing root segment, upper side. C. somewhere on the fin. D. somewhere on the horizontal tail.
929. JAAExam.com/ATPL Question ID: 1464
Answer D is correct.
For a tail wheel aircraft with a clockwise turning propeller, the asymmetric blade effect at the start of the take off run causes:
The correct answer is D
A. yaw to right. B. no significant effects. C. nose down pitching moment (tail up). D. yaw to left.
yaw to left. References
930. JAAExam.com/ATPL Question ID: 931
Answer C is correct.
If the weight of an aircraft is increased, the maximum lift-to-drag ratio will:
The correct answer is C not be affected.
A. decrease. B. increase.
References
C. not be affected. D. increases although the corresponding airspeed will be lower.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
931. JAAExam.com/ATPL Question ID: 798
Answer B is correct.
The pitch up effect of an aeroplane with swept wing in a stall is due to the:
The correct answer is B wing tip stalling first.
A. aft movement of the centre of gravity. B. wing tip stalling first.
References
C. forward movement of the centre of gravity. D. wing root stalling first.
932. JAAExam.com/ATPL Question ID: 1476
Answer C is correct.
In a steady unaccellerated glide:
The correct answer is C
A. the resultant aerodynamic force is equal to drag.
the resultant aerodynamic force is equal to weight.
B. the resultant aerodynamic force is equal to lift.
References
C. the resultant aerodynamic force is equal to weight. D. none of these statements is true.
933. JAAExam.com/ATPL Question ID: 1546
Answer C is correct.
A sailplane has a best glide ratio of 23:1. How many feet will the glider lose in 8 nautical miles?
The correct answer is C 2,100 feet.
A. 330 feet. B. 1,840 feet.
References
C. 2,100 feet. D. 2,750 feet.
934. JAAExam.com/ATPL Question ID: 1423
Answer A is correct.
A propeller blade is twisted in order to:
The correct answer is A keep the local angle of attack constant along the
A. keep the local angle of attack constant along the blade.
blade.
B. allow higher mechanical stresses.
References
C. avoid local transonic flow to develop on the propeller blades. D. decrease tangential speed from propeller blade root to propeller blade tip.
935. JAAExam.com/ATPL Question ID: 920
Answer D is correct.
One of the main purposes of using flaps during approach and landing is to:
The correct answer is D
A. shift the centre of gravity aft.
increase the angle of descent without increasing the airspeed.
B. decrease the angle of descent without increasing the airspeed.
References
C. permit a higher reference speed (Vref) for landing. D. increase the angle of descent without increasing the airspeed.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
936. JAAExam.com/ATPL Question ID: 958
Answer A is correct.
Climbing at a constant Mach Number up to FL 350 the TAS will:
The correct answer is A decrease.
A. decrease. B. first increase, then decrease.
References
C. increase. D. remain constant.
937. JAAExam.com/ATPL Question ID: 688
Answer B is correct.
How will frost on the wings of an airplane affect takeoff performance?
The correct answer is B
A. Frost has no influence on airplane performance. B. Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability.
Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability. References
C. Frost will change the camber of the wing, increasing its lifting capability. D. Frost will cause the airplane to become airborne with a higher angle of attack, decreasing the stall speed.
938. JAAExam.com/ATPL Question ID: 1569
Answer A is correct.
A glider reduces weight by dumping water ballast. A ten per cent reduction in weight would give:
The correct answer is A a decrease in best rate of descent.
A. a decrease in best rate of descent. B. a ten per cent increase in best glide angle.
References
C. a five per cent reduction in best glide angle. D. no change in best rate of descent.
939. JAAExam.com/ATPL Question ID: 857
Answer C is correct.
Stick pushers must be installed in aeroplanes with dangerous stall characteristics. Dangerous stall characteristics include:
The correct answer is C
A. pitch down and minor wing drop.
excessive wing drop and deep stall. References
B. pitch down and yaw. C. excessive wing drop and deep stall. D. pitch down and increase in speed.
940. JAAExam.com/ATPL Question ID: 609
Answer B is correct.
Which statement is correct?
The correct answer is B
A. The centre of pressure is the point on the wings leading edge where the airflow splits up.
As the angle of attack increases, the stagnation point on the wings profile moves downwards.
B. As the angle of attack increases, the stagnation point on the wings profile moves downwards.
References
C. The stagnation point is another name for centre of pressure. D. The stagnation point is always situated on the chord line, the centre of pressure is not.
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941. JAAExam.com/ATPL Question ID: 1453
Answer B is correct.
The tendency for propeller-driven aircraft to swing to one side on take-off is causes by:
The correct answer is B
A. a damaged propeller.
asymmetric blade effect, torque reaction, slipstream effect and gyroscopic effect.
B. asymmetric blade effect, torque reaction, slipstream effect and gyroscopic effect.
References
C. the aft position of the centre of gravity. D. poor pilot control.
942. JAAExam.com/ATPL Question ID: 916
Answer C is correct.
When flaps are deployed at constant angle of attack the lift coefficient will:
The correct answer is C increase.
A. remain the same. B. decrease.
References
C. increase. D. vary as the square of IAS.
943. JAAExam.com/ATPL Question ID: 741
Answer B is correct.
When an aircraft enters ground effect:
The correct answer is B
A. the total reaction vector is unaffected. B. the total reaction vector is inclined forwards, reducing drag. C. the total reaction vector is inclined rearwards, increasing drag.
the total reaction vector is inclined forwards, reducing drag. References
D. the total reaction vector is inclined forwards, increasing drag.
944. JAAExam.com/ATPL Question ID: 813
Answer C is correct.
Which of the following situations leads to a decreasing stall speed (IAS)?
The correct answer is C decreasing weight.
A. increasing air density. B. increasing load factor.
References
C. decreasing weight. D. increasing altitude.
945. JAAExam.com/ATPL Question ID: 724
Answer C is correct.
An aircraft flying straight and level; if density halves, aerodynamic drag will:
The correct answer is C decrease by a factor of two.
A. increase by a factor of four. B. increase by a factor of two.
References
C. decrease by a factor of two. D. decrease by a factor of four.
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946. JAAExam.com/ATPL Question ID: 1226
Answer B is correct.
In order to reduce adverse aileron yaw, aircraft are fitted with:
The correct answer is B frize ailerons.
A. differential elevators.
B. frize ailerons.
References
C. offset rudder. D. horn balanced ailerons.
947. JAAExam.com/ATPL Question ID: 727
Answer C is correct.
Profile drag in straight and level flight:
The correct answer is C
A. depends mainly on the gross weight of the aircraft.
is proportional to the square of the speed.
B. is the sum of induced drag and skin friction drag.
References
C. is proportional to the square of the speed. D. is inversely proportional to the square of the speed.
948. JAAExam.com/ATPL Question ID: 613
Answer B is correct.
In a two-dimensional flow pattern, where the streamlines converge the static pressure will:
The correct answer is B decrease.
A. increase initially, then decrease. B. decrease.
References
C. increase. D. not change.
949. JAAExam.com/ATPL Question ID: 1024
Answer D is correct.
When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of:
The correct answer is D
A. Lower stalling speed.
Higher critical Mach number. References
B. Greater strength. C. Increased longitudinal stability. D. Higher critical Mach number.
950. JAAExam.com/ATPL Question ID: 1442
Answer C is correct.
To counteract the effect of slipstream on a single engined aircraft:
The correct answer is C
A. the horizontal stabilizer should be reduced in size. B. higher power settings should be used. C. the fin should be placed as far as possible from the propeller. D. frise ailerons should be used.
the fin should be placed as far as possible from the propeller. References
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951. JAAExam.com/ATPL Question ID: 1369
Answer C is correct.
When an aircraft fitted with a constant speed propeller is in level flight, and a climb is initiated:
The correct answer is C
A. the RPM will increase as the blades will move to fine pitch. B. the blades will move to coarse pitch and RPM will reduce.
the RPM will remain constant as the blades move to a finer pitch. References
C. the RPM will remain constant as the blades move to a finer pitch. D. the RPM will increase as the blades move to a coarser pitch.
952. JAAExam.com/ATPL Question ID: 658
Answer C is correct.
Induced drag on a wing in level flight:
The correct answer is C
A. is uniform across its span. B. is greatest at the wing root. C. is greatest at the tip.
is greatest at the tip. References
D. is greatest at the leading edge.
953. JAAExam.com/ATPL Question ID: 678
Answer B is correct.
A wing with higher span compared with a lower wing span has (equal wing surface):
The correct answer is B lower induced drag.
A. higher profile drag. B. lower induced drag.
References
C. higher induced drag. D. a higher lift/drag ratio.
954. JAAExam.com/ATPL Question ID: 984
Answer A is correct.
Air passes a normal shock wave. Which of the following statements is correct?
The correct answer is A The temperature increases.
A. The temperature increases. B. The pressure decreases.
References
C. The temperature decreases. D. The velocity increases.
955. JAAExam.com/ATPL Question ID: 1496
Answer C is correct.
A sailplane has lost 2.000 feet in 9 nautical miles. The best glide ratio for this sailplane is
The correct answer is C
approximately: A. 18:1
27:1 References
B. 24:1 C. 27:1 D. 30:1
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956. JAAExam.com/ATPL Question ID: 607
Answer B is correct.
The point, where the aerodynamic lift acts on a wing is:
The correct answer is B the centre of pressure.
A. the c.g. location. B. the centre of pressure.
References
C. the point of maximum thickness of the wing. D. the suction point of the wing.
957. JAAExam.com/ATPL Question ID: 569
Answer D is correct.
In a stream tube, if density is halved, drag will be reduced by a factor of:
The correct answer is D 2
A. 8 B. 4
References
C. 6 D. 2
958. JAAExam.com/ATPL Question ID: 1180
Answer C is correct.
What is the advantage of a variable incidence tailplane over a fixed incidence tailplane with elevator and trim tab?
The correct answer is C Less trim drag and maximum elevator authority retained.
A. Linkages and mechanism less complicated. B. Increased flight stability and less weight.
References
C. Less trim drag and maximum elevator authority retained. D. Elevator movement is restricted at high speed.
959. JAAExam.com/ATPL Question ID: 1137
Answer B is correct.
The primary function of the fin is to give:
The correct answer is B
A. lateral stability - about the longitudinal axis. B. directional stability - about the normal axis. C. directional stability - about the longitudinal
directional stability - about the normal axis. References
axis. D. directional stability - about the lateral axis.
960. JAAExam.com/ATPL Question ID: 790
Answer C is correct.
Which kind of boundary layer has the strongest change in velocity close to the surface?
The correct answer is C Turbulent boundary layer.
A. No difference. B. Laminar boundary layer.
References
C. Turbulent boundary layer. D. Transition boundary layer.
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961. JAAExam.com/ATPL Question ID: 1511
Answer B is correct.
When an aircraft is in a gliding flight:
The correct answer is B
A. thrust equals drag. B. thrust is replaced by a component of weight to maintain airspeed. C. thrust is replaced by a component of lift and weight to maintain airspeed.
thrust is replaced by a component of weight to maintain airspeed. References
D. lift is greater than weight and drag.
962. JAAExam.com/ATPL Question ID: 1330
Answer B is correct.
The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
The correct answer is B
A. 2.5
4.4 References
B. 4.4 C. 3.8 D. 6.0
963. JAAExam.com/ATPL Question ID: 1041
Answer A is correct.
How will the density and temperature change in a supersonic flow from a position in front of a shock wave to behind it?
The correct answer is A
A. Density will increase, temperature will increase. B. Density will increase, temperature will decrease. C. Density will decrease, temperature will increase. D. Density will decrease, temperature will
Density will increase, temperature will increase. References
decrease.
964. JAAExam.com/ATPL Question ID: 551
Answer B is correct.
When looking at the airflow over the wing, from the wing surface and up, the air is:
The correct answer is B accelerated to the transition point.
A. caused to tend to flow from root to tip over a straight wing.
References
B. accelerated to the transition point. C. decelerated to the transition point. D. accelerated to the separation point.
965. JAAExam.com/ATPL Question ID: 955
Answer A is correct.
As an aircraft accelerates through the transonic speed range:
The correct answer is A The coefficient of drag increases then decreases.
A. The coefficient of drag increases then decreases.
References
B. The coefficient of drag increases. C. The coefficient of drag decreases then increases. D. The coefficient of drag decreases.
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966. JAAExam.com/ATPL Question ID: 1391
Answer A is correct.
For a variable propeller, which way does the blade twist from root to tip?
The correct answer is A To finer pitch angle.
A. To finer pitch angle. B. To coarser pitch angle.
References
C. Depend on the variable pitch setting. D. Depends if it a left handed or right handed propeller.
967. JAAExam.com/ATPL Question ID: 465
Answer A is correct.
A wing has a span of 50 feet and an area of 200 square feet. Its mean chord would be:
The correct answer is A 4 feet.
A. 4 feet. B. 10 feet. C. 7.5 feet D. 2.5 feet
References
968. JAAExam.com/ATPL Question ID: 1250
Answer C is correct.
When a jet aircraft enters a turn or straightens-up from a turn, what device ensures correct response?
The correct answer is C Aileron - rudder coupling.
A. Dorsal fin. B. Yaw damper.
References
C. Aileron - rudder coupling. D. Vortex generators.
969. JAAExam.com/ATPL Question ID: 692
Answer C is correct.
What is the effect of high aspect ratio of an aeroplanes wing on induced drag?
The correct answer is C
A. It is unaffected because there is no relation between aspect ratio and induced drag. B. It is increased because high aspect ratio produces greater downwash.
It is reduced because the effect of wing-tip vortices is reduced. References
C. It is reduced because the effect of wing-tip vortices is reduced. D. It is increased because high aspect ratio has greater frontal area.
970. JAAExam.com/ATPL Question ID: 1561
Answer C is correct.
In order to optimise gliding distance, the gliding speed must be:
The correct answer is C
A. equal to the minimum power speed.
equal to the speed which gives the highest lift-todrag ratio.
B. as high as possible but lower than the never exceeding speed.
References
C. equal to the speed which gives the highest lift-to-drag ratio. D. as low as possible.
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971. JAAExam.com/ATPL Question ID: 1045
Answer C is correct.
When the air is passing through an expansion wave the local speed of sound will:
The correct answer is C decrease.
A. stay constant. B. increase.
References
C. decrease. D. decrease and beyond a certain Mach number start increasing again.
972. JAAExam.com/ATPL Question ID: 669
Answer C is correct.
Which relationship is correct when comparing drag and airspeed? A. If you double the airspeed you double the induced drag. B. If you double the airspeed the induced drag is halved.
The correct answer is C If you double the airspeed the induced drag is reduced to 1/4. References
C. If you double the airspeed the induced drag is reduced to 1/4. D. If you double the airspeed the parasite drag is doubled.
973. JAAExam.com/ATPL Question ID: 1392
Answer C is correct.
The Beta Range of a propeller is used...
The correct answer is C
A. for takeoff at high temperatures.
for ground manoeuvring.
B. to move the propeller blades to the feathering position in an emergency.
References
C. for ground manoeuvring. D. to bring the propeller out of the feathering position.
974. JAAExam.com/ATPL Question ID: 1462
Answer C is correct.
The left turning tendency of an airplane caused by Pfactor is the result of:
The correct answer is C
A. an unbalanced propeller. B. the propeller turning the airplane counterclockwise. C. the propeller blade descending on the right hand side, producing more thrust than the ascending blade on the left.
the propeller blade descending on the right hand side, producing more thrust than the ascending blade on the left. References
D. gyroscopic forces applied to the rotating propeller blades acting 90° in advance of the point the force was applied.
975. JAAExam.com/ATPL Question ID: 606
Answer D is correct.
When the angle of attack increases in straight and level flight, we will observe:
The correct answer is D forward movement of the centre of pressure.
A. lateral movement of the centre of gravity. B. a reduction in varying loads due to g.
References
C. forward movement of the centre of gravity. D. forward movement of the centre of pressure.
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976. JAAExam.com/ATPL Question ID: 1258
Answer D is correct.
A horn balance in a control system has the following purpose:
The correct answer is D to decrease stick forces.
A. to decrease the effective longitudinal dihedral of the aeroplane.
References
B. to prevent flutter. C. to obtain mass balancing. D. to decrease stick forces.
977. JAAExam.com/ATPL Question ID: 1236
Answer B is correct.
If a turbulent gust causes an aeroplane to roll:
The correct answer is B
A. the down going wing experiences a decreases in angle of attack.
the down going wing experiences an increases in angle of attack.
B. the down going wing experiences an increases in angle of attack.
References
C. the down going wing has no angle of attack. D. the angle of attack depends on whether the aeroplane changes speed.
978. JAAExam.com/ATPL Question ID: 893
Answer C is correct.
Compared with the flap up configuration the maximum angle of attack for the flaps down configuration is:
The correct answer is C
A. unchanged.
smaller. References
B. larger. C. smaller. D. smaller or larger depending on flap deflection.
979. JAAExam.com/ATPL Question ID: 855
Answer B is correct.
An aircraft whose weight is 237402 N stalls at 132 kt. At a weight of 356103 N it would stall at:
The correct answer is B 162 kt
A. 88 kt B. 162 kt
References
C. 108 kt D. 172 kt
980. JAAExam.com/ATPL Question ID: 578
Answer B is correct.
The CP on a swept wing aircraft will move forward due to:
The correct answer is B tip stall of the wing.
A. boundary layer fences and span wise flow.
References
B. tip stall of the wing. C. flow separation at the root due to span wise flow. D. change in wing angle of incidence.
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981. JAAExam.com/ATPL Question ID: 1547
Answer B is correct.
Flying horizontally in a turn:
The correct answer is B
A. less power is required than in level flight. B. more power is required than in level flight. C. the same power is required.
more power is required than in level flight. References
D. more or less power may be required depending on which side of the drag curve the aeroplane is sitting.
982. JAAExam.com/ATPL Question ID: 1365
Answer C is correct.
The propeller CTM will:
The correct answer is C
A. Cause the propeller CSU to pitch lock. B. Tend to move the blades to a coarse pitch. C. Move the blades about their longitudinal axis.
Move the blades about their longitudinal axis. References
D. Act in reverse when propeller braking is applied.
983. JAAExam.com/ATPL Question ID: 745
Answer B is correct.
Ground Effect occurs:
The correct answer is B
A. acts like a decrease in aspect ratio.
is only effective up to 1 wingspan from the ground..
B. is only effective up to 1 wingspan from the ground..
References
C. during the approach to landing. D. aids landing by increasing the induced drag..
984. JAAExam.com/ATPL Question ID: 787
Answer A is correct.
In a turn, the wing stalling angle:
The correct answer is A
A. remains unchanged. B. increases when the rate of turn is high. C. decreases when the rate of turn is low. D. increases on the outer wing.
remains unchanged. References
985. JAAExam.com/ATPL Question ID: 1010
Answer C is correct.
A normal shock wave:
The correct answer is C
A. is a discontinuity plane in an airflow, in which the pressure drops suddenly.
can occur at different points on the aeroplane in transonic flight.
B. is a discontinuity plane in an airflow, in which the temperature drops suddenly.
References
C. can occur at different points on the aeroplane in transonic flight. D. is a discontinuity plane in an airflow, which is always normal to the surface.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
986. JAAExam.com/ATPL Question ID: 1376
Answer A is correct.
A reversible propeller is one that:
The correct answer is A
A. can deliver negative thrust. B. is mounted behind the main wing. C. is a PUSHER rather than a TRACTOR.
can deliver negative thrust. References
D. can be operated clockwise or counter clockwise.
987. JAAExam.com/ATPL Question ID: 695
Answer B is correct.
Winglets:
The correct answer is B
A. create an elliptical lift distribution. B. decrease the induced drag. C. decrease the static lateral stability.
decrease the induced drag. References
D. increase the manoeuvrability.
988. JAAExam.com/ATPL Question ID: 875
Answer B is correct.
Deploying a Fowler flap, the flap will:
The correct answer is B
A. turn down, then move aft. B. move aft, then turn down. C. just move aft.
move aft, then turn down. References
D. just turn down.
989. JAAExam.com/ATPL Question ID: 1375
Answer C is correct.
A double acting propeller is one which the blades are:
The correct answer is C moved to coarse and fine by oil pressure.
A. moved to coarse by oil pressure and to fine by spring pressure.
References
B. moved to coarse and fine by oil pressure with spring operation provided for emergency use. C. moved to coarse and fine by oil pressure. D. moved to coarse and fine by spring pressure.
990. JAAExam.com/ATPL Question ID: 1344
Answer B is correct.
An aircraft is in straight, level flight has a CL of 0.42, and a 1° increase in angle of attack would increase the CL by 0.1. Following a gust that increases the angle of attack by 3° , what load factor would the aircraft be subject to?
The correct answer is B n = 1.7 References
A. n = 0.7 B. n = 1.7 C. n = 1.4 D. n = 1.0
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991. JAAExam.com/ATPL Question ID: 1047
Answer B is correct.
Tuck under is a phenomenon which occur:
The correct answer is B
A. only on small airplanes during landing. B. on a/c in transonic flight. C. on a/c at supersonic speeds.
on a/c in transonic flight. References
D. when deploying flaps.
992. JAAExam.com/ATPL Question ID: 932
Answer C is correct.
Spoiler deflection causes:
The correct answer is C
A. an increase in lift and drag. B. an increase in lift only. C. an increase in drag and decrease in lift.
an increase in drag and decrease in lift. References
D. decrease in lift and drag.
993. JAAExam.com/ATPL Question ID: 1379
Answer C is correct.
Reverse pitch propellers are used:
The correct answer is C
A. to slow up aircraft when making an approach to land.
to provide aerodynamic braking on the ground.
B. only for ground checking the pitch change mechanism.
References
C. to provide aerodynamic braking on the ground. D. to provide differential thrust during crosswind landings.
994. JAAExam.com/ATPL Question ID: 1142
Answer D is correct.
The effect of a positive wing sweep on static directional stability is as follows:
The correct answer is D stabilizing effect.
A. negative dihedral effect. B. no effect.
References
C. destabilizing dihedral effect. D. stabilizing effect.
995. JAAExam.com/ATPL Question ID: 676
Answer C is correct.
The wind condition that requires maximum caution when avoiding wake turbulence on landing is?
The correct answer is C Light, quartering tailwind.
A. Strong crosswind. B. Light, quartering headwind.
References
C. Light, quartering tailwind. D. Strong headwind.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
996. JAAExam.com/ATPL Question ID: 1381
Answer D is correct.
A propeller which rotates clockwise when viewed from the front and is mounted on the starboard engine is termed:
The correct answer is D
A. a right handed propeller.
a left handed propeller. References
B. a clockwise propeller. C. an anti-clockwise propeller. D. a left handed propeller.
997. JAAExam.com/ATPL Question ID: 1420
Answer C is correct.
When the blades of a propeller are in the feathered position:
The correct answer is C the drag of the propeller is then minimal.
A. the windmilling RPM is the maximum. B. the propeller produces an optimal windmilling RPM. C. the drag of the propeller is then minimal. D. the RPM is then just sufficient to lubricate the engine.
References
998. JAAExam.com/ATPL Question ID: 1089
Answer D is correct.
Deflecting the elevator up, when the trim tab is in neutral, will cause the tab to:
The correct answer is D remain in line with the elevator.
A. move down relative to the elevator chord line. B. move up relative to the elevator chord line.
References
C. remain in line with the tailplane. D. remain in line with the elevator.
999. JAAExam.com/ATPL Question ID: 451
Answer D is correct.
The term angle of attack in a two dimensional flow is defined as:
The correct answer is D
A. the angle for maximum lift/drag ratio.
the angle between the wing chord line and the direction of the relative wind/airflow.
B. the angle between the aeroplane climb path and the horizon..
References
C. the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing. D. the angle between the wing chord line and the direction of the relative wind/airflow.
1000. JAAExam.com/ATPL Question ID: 1537
Answer C is correct.
When the load factor increases...
The correct answer is C
A. an aircraft will have a tendency to spin.
an aircraft will stall at a higher speed.
B. an aircraft will suffer immediate structural failure.
References
C. an aircraft will stall at a higher speed. D. an aircraft will have a tendency to roll and yaw.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
1001. JAAExam.com/ATPL Question ID: 829
Answer C is correct.
At the point of stall:
The correct answer is C
A. lift decreases, drag decreases. B. lift constant, drag increases. C. lift decreases, drag increases.
lift decreases, drag increases. References
D. lift decreases, drag constant.
1002. JAAExam.com/ATPL Question ID: 1105
Answer A is correct.
One of the requirements for dynamic stability is:
The correct answer is A
A. positive static stability. B. a large deflection range of the stabilizer trim. C. a small C.G. range.
positive static stability. References
D. effective elevator.
1003. JAAExam.com/ATPL Question ID: 952
Answer B is correct.
Shock stall is:
The correct answer is B
A. separation of the flow behind the bow wave. B. separation of the boundary layer behind the shock wave. C. separation of the flow at high angles of attack and at high Mach Numbers.
separation of the boundary layer behind the shock wave. References
D. separation of the flow at the trailing edge of the wing at high Mach Numbers.
1004. JAAExam.com/ATPL Question ID: 1528
Answer C is correct.
In a steady banked turn the lift will:
The correct answer is C
A. equal the weight. B. equal the centrifugal force. C. equal the resultant of weight and centrifugal force.
equal the resultant of weight and centrifugal force. References
D. equal the centrifugal force minus the weight.
1005. JAAExam.com/ATPL Question ID: 1387
Answer C is correct.
Propeller efficiency may be defined as the ratio between:
The correct answer is C
A. the usable (power available) power and the maximum power. B. the thrust and the maximum thrust.
usable (power available) power of the propeller and shaft power. References
C. usable (power available) power of the propeller and shaft power. D. the thermal power of fuel-flow and shaft power.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
1006. JAAExam.com/ATPL Question ID: 581
Answer A is correct.
Which of the following statements are correct?
The correct answer is A
A. Drag acts in the same direction as the relative airflow and lift perpendicular to it. B. Lift acts at right angles to the top surface of
Drag acts in the same direction as the relative airflow and lift perpendicular to it. References
the wing and drag acts at right angles to lift. C. Drag acts parallel to the chord and opposite to the direction of motion of the aircraft and lift acts perpendicular to the chord. D. Lift acts perpendicular to the horizontal and drag parallel in a rearwards direction.
1007. JAAExam.com/ATPL Question ID: 672
Answer C is correct.
Geometric washout means that:
The correct answer is C
A. there is an airflow along the wing that keeps it clean.
the tip of the wing has less angle of attack than the root.
B. the tip of the wing has more angle of attack than the root.
References
C. the tip of the wing has less angle of attack than the root. D. the horizontal tail has less angle of attack than the wing.
1008. JAAExam.com/ATPL Question ID: 480
Answer D is correct.
An A310 aeroplane weighing 100 tons is turning at FL 350 at constant altitude with a bank of 50 degrees. Its flight Mach range between low-speed buffering and high-speed buffering goes from:
The correct answer is D
A. M = 0.72 to M higher than 0.84
M = 0.69 to M higher than. 0.84 References
B. M = 0.65 to M higher than 0.84 C. M = 0.74 to M = 0.84 D. M = 0.69 to M higher than. 0.84
1009. JAAExam.com/ATPL Question ID: 1240
Answer A is correct.
A modern jet aeroplane equipped with inboard and outboard ailerons plus roll control spoilers is cruising at its normal cruise Mach number:
The correct answer is A
A. only the inboard ailerons are active, the spoilers may be active.
only the inboard ailerons are active, the spoilers may be active. References
B. the inboard and outboard ailerons are active, the spoilers may be active. C. only the outboard ailerons are active, the spoilers may be active. D. only the spoilers will be active, not the ailerons.
1010. JAAExam.com/ATPL Question ID: 894
Answer B is correct.
How is the pitching moment affected if flaps are deployed in straight and level flight?
The correct answer is B
A. Pitch up. B. Pitch down. C. Depends on CG position.
Pitch down. References
D. Flap deployment has no effect on aircraft pitching moment.
This document was created by Dauntless Software's GroundSchool software. JAAExam.com/ATPL
1011. JAAExam.com/ATPL Question ID: 624
Answer D is correct.
If the angle of attack is increased, the centre of pressure will:
The correct answer is D
A. move aft.
move forward towards the aerodynamic centre of the wing.
B. move forward or aft, depending on the location of the centre of gravity.
References
C. will remain stationary. D. move forward towards the aerodynamic centre of the wing.
1012. JAAExam.com/ATPL Question ID: 1479
Answer B is correct.
Which of the following statements is true for a glider aircraft?
The correct answer is B Wind affects range and not endurance.
A. Weight affects range and not endurance. B. Wind affects range and not endurance.
References
C. Weight affects endurance and not range. D. Wind has no influence on range and endurance.
1013. JAAExam.com/ATPL Question ID: 529
Answer A is correct.
The units of a turning moment are?
The correct answer is A
A. Newton x meters. B. Joule. C. Kilogram.
Newton x meters. References
D. Rad / second.
1014. JAAExam.com/ATPL Question ID: 1070
Answer C is correct.
If an aircraft is disturbed (e.g. vertical gust) and initially returns to its original position:
The correct answer is C it is statically stable and may be dynamically stable.
A. it is neutrally stable. B. it is neutrally unstable. C. it is statically stable and may be dynamically stable.
References
D. it is dynamically unstable.
1015. JAAExam.com/ATPL Question ID: 863
Answer B is correct.
When a trailing edge flap is lowered fully:
The correct answer is B
A. the C of P moves to the rear and lift/drag ratio is unaffected.
the C of P moves to the rear and lift/drag ratio is decreased.
B. the C of P moves to the rear and lift/drag ratio is decreased.
References
C. the C of P moves forwards and lift/drag ratio is decreased. D. the C of P moves to the rear and lift/drag ratio is increased.
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1016. JAAExam.com/ATPL Question ID: 992
Answer B is correct.
If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing:
The correct answer is B
A. moves into leading edge direction.
moves into trailing edge direction. References
B. moves into trailing edge direction. C. stays all the time at the same position. D. disappears.
1017. JAAExam.com/ATPL Question ID: 555
Answer C is correct.
Aspect ratio of a wing is defined as the ratio of the:
The correct answer is C
A. wingspan to the wing root. B. square of the chord to the wingspan. C. square of the wing span to the wing area.
square of the wing span to the wing area. References
D. wing spat to the main compression rib.
1018. JAAExam.com/ATPL Question ID: 1557
Answer C is correct.
A twin-engine aeroplane loses both engines. How many feet will it sink in 10 nautical miles if its lift-todrag ratio is 23:1?
The correct answer is C
A. 2,300 feet. B. 2,400 feet. C. 2,600 feet. D. 4,300 feet.
2,600 feet. References
1019. JAAExam.com/ATPL Question ID: 769
Answer A is correct.
When an aircraft is in a steady climb, how will be the wing stalling angle be affected?
The correct answer is A
A. The stalling angle will remain the same, regardless of altitude. B. The stalling angle will reduce with increasing altitude.
The stalling angle will remain the same, regardless of altitude. References
C. The stalling angle will increase with increasing altitude. D. The stalling angle will only be affected by airspeed.
1020. JAAExam.com/ATPL Question ID: 848
Answer D is correct.
When entering a stall, the CP of a straight wing will (i) and of a strongly swept wing will (ii):
The correct answer is D (i) move aft, (ii) move forward
A. (i) not move, (ii) not move B. (i) move aft, (ii) not move
References
C. (i) move aft, (ii) move aft D. (i) move aft, (ii) move forward
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1021. JAAExam.com/ATPL Question ID: 734
Answer C is correct.
Which of the following decreases induced drag?
The correct answer is C
A. Wing fences. B. Anhedral. C. Winglets.
Winglets. References
D. Low aspect ratio plan form.
1022. JAAExam.com/ATPL Question ID: 821
Answer B is correct.
Vso is defined as the:
The correct answer is B
A. minimum second segment speed. B. stalling speed or minimum steady flight speed in the landing configuration. C. stalling speed or minimum steady flight speed in a specified configuration.
stalling speed or minimum steady flight speed in the landing configuration. References
D. stalling speed or minimum takeoff safety speed.
1023. JAAExam.com/ATPL Question ID: 996 When air has passed through a shock wave the
Answer C is correct.
speed of sound is? The correct answer is C A. decreased. B. not affected. C. increased. D. decreased and beyond a certain Mach number start increasing again.
increased. References
1024. JAAExam.com/ATPL Question ID: 663
Answer A is correct.
The induced angle of attack is the result of:
The correct answer is A
A. downwash due to tip vortices.
downwash due to tip vortices.
B. a large local angle of attack in a two dimensional flow.
References
C. downwash due to flow separation. D. change in direction of flow due to the effective angle of attack.
1025. JAAExam.com/ATPL Question ID: 1049
Answer A is correct.
When a non swept is accelerated from subsonic to supersonic speeds, the aerodynamic centre:
The correct answer is A shifts from 25% to about 50% of the aerofoil chord.
A. shifts from 25% to about 50% of the aerofoil chord.
References
B. shifts aft by about 10%. C. remains unchanged. D. slightly shifts forward.
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1026. JAAExam.com/ATPL Question ID: 1448
Answer B is correct.
Refer to Figure: 081-02
The correct answer is B
(Refer to figure 081-02) Using the diagram below of the forces affecting a propeller in flight, which arrow represents the torque moment?
A References
A. B B. A C. C D. D
1027. JAAExam.com/ATPL Question ID: 1055 Which statement is correct about an expansion wave
Answer A is correct.
in a supersonic flow? 1. 2.
The density in front of an expansion wave is higher than behind. The pressure in front of an expansion wave is higher than behind.
The correct answer is A 1 and 2 are correct. References
A. 1 and 2 are correct. B. 1 is correct and 2 is incorrect. C. 1 is incorrect and 2 is correct. D. 1 and 2 are incorrect.
1028. JAAExam.com/ATPL Question ID: 900
Answer C is correct.
Lowering the inboard flaps causes the wing Centre of Pressure:
The correct answer is C to move inboard towards the wing root.
A. to move forward. B. to move outboard towards the wing tips.
References
C. to move inboard towards the wing root. D. to move inward and forward.
1029. JAAExam.com/ATPL Question ID: 1152
Answer B is correct.
With a swept wing aircraft, with an increase in altitude, which of the following statements about lateral stability is correct?
The correct answer is B
A. Static lateral stability increases, dynamic lateral stability increases.
Static lateral stability remains the same, dynamic lateral stability decreases. References
B. Static lateral stability remains the same, dynamic lateral stability decreases. C. Static lateral stability decreases, dynamic lateral stability increases. D. Static lateral stability increases, dynamic lateral stability decreases.
1030. JAAExam.com/ATPL Question ID: 1307
Answer B is correct.
What can happen to the aeroplane structure flying at a speed just exceeding VA?
The correct answer is B
A. It may break if the elevator is fully deflected upwards. B. It may suffer permanent deformation if the elevator is fully deflected upwards.
It may suffer permanent deformation if the elevator is fully deflected upwards. References
C. It may suffer permanent deformation because the flight is performed at too large dynamic pressure. D. It will collapse if a turn is made.
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1031. JAAExam.com/ATPL Question ID: 689
Answer D is correct.
Induced drag:
The correct answer is D
A. increases when increasing the wing aspect ratio.
increases when reducing the wing aspect ratio.
B. is proportional to the square of the speed.
References
C. always exceeds profile drag. D. increases when reducing the wing aspect ratio.
1032. JAAExam.com/ATPL Question ID: 600
Answer A is correct.
The airfoil chord line is:
The correct answer is A
A. a straight line from the wing leading edge to the trailing edge.
a straight line from the wing leading edge to the trailing edge.
B. a line equidistant from the upper and lower wing surfaces.
References
C. a line tangential to the wing surface at the point of maximum curvature. D. a line drawn at 15% chord from the root to the tip.
1033. JAAExam.com/ATPL Question ID: 1162
Answer D is correct.
Which type of wing arrangement decreases the static lateral stability of an aeroplane?
The correct answer is D Anhedral.
A. Increased wing span. B. Dihedral.
References
C. High wing. D. Anhedral.
1034. JAAExam.com/ATPL Question ID: 1067
Answer C is correct.
Superstall is a condition:
The correct answer is C
A. Where the wings have stalled at high speed. B. Which is easily to recover from. C. Which is a stable stall with almost a constant pitch attitude.
Which is a stable stall with almost a constant pitch attitude. References
D. Where the a/c is in a spin.
1035. JAAExam.com/ATPL Question ID: 591
Answer C is correct.
Static pressure acts:
The correct answer is C
A. parallel to airflow.
in all directions.
B. parallel to dynamic pressure.
References
C. in all directions. D. downwards.
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1036. JAAExam.com/ATPL Question ID: 1427
Answer D is correct.
Increasing the number of propeller blades will:
The correct answer is D
A. decrease the torque in the propeller shaft at maximum power.
increase the maximum absorption of power.
B. increase the propeller efficiency.
References
C. increase the noise level at maximum power. D. increase the maximum absorption of power.
1037. JAAExam.com/ATPL Question ID: 549
Answer C is correct.
The static pressure is acting:
The correct answer is C
A. only perpendicular to the direction of the flow.
in all directions.
B. only in the direction of the total pressure.
References
C. in all directions. D. only in direction of the flow.
1038. JAAExam.com/ATPL Question ID: 1095
Answer B is correct.
The aerodynamic centre of the wing is the point, where:
The correct answer is B
A. change of lift due to variation of angle of attack is constant. B. pitching moment coefficient does not vary with angle of attack.
pitching moment coefficient does not vary with angle of attack. References
C. aerodynamic forces are constant. D. the aeroplanes lateral axis intersects with the centre of gravity.
1039. JAAExam.com/ATPL Question ID: 962
Answer A is correct.
Which of the following flight phenomena can happen at Mach Numbers below the critical Mach Number?
The correct answer is A Dutch roll.
A. Dutch roll. B. Tuck under. C. Mach buffet. D. Shock stall.
References
1040. JAAExam.com/ATPL Question ID: 1463
Answer D is correct.
An aerodynamic force on a propeller blade, which tends to turn the blade to coarse pitch during operation, is called:
The correct answer is D
A. CTM (Centrifugal Twisting Moment.
ATM. References
B. Beta range. C. a slip force. D. ATM.
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1041. JAAExam.com/ATPL Question ID: 497
Answer A is correct.
Bernoulli’ s theorem states that in a perfect and constant airstream?
The correct answer is A The sum of static and dynamic pressure is constant.
A. The sum of static and dynamic pressure is constant.
References
B. The dynamic pressure is equal to the static pressure. C. The dynamic pressure is always greater than the static pressure. D. The sum of dynamic pressure and total pressure is constant.
1042. JAAExam.com/ATPL Question ID: 617
Answer A is correct.
On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane):
The correct answer is A
A. move forward.
move forward. References
B. move aft. C. remain matching the airfoil aerodynamic centre. D. remain unaffected.
1043. JAAExam.com/ATPL Question ID: 1195
Answer B is correct.
Refer to Figure: 081-15
The correct answer is B
Refer to 081-15 The trailing edge device shown in the figure is a:
Fowler flap. References
A. slot flap. B. Fowler flap. C. plain flap. D. split flap.
1044. JAAExam.com/ATPL Question ID: 1213
Answer B is correct.
The pilot use the rudder to provide control around the:
The correct answer is B Normal axis.
A. Lateral axis. B. Normal axis.
References
C. Longitudinal axis. D. Turn axis.
1045. JAAExam.com/ATPL Question ID: 1283
Answer C is correct.
What is the reason for mass balancing a control surface?
The correct answer is C
A. To make it easy for the pilot to move the control surface. B. To move the centre of gravity of the control surface aft of the hinge line, thereby preventing flutter.
To move the centre of gravity forward thereby preventing flutter. References
C. To move the centre of gravity forward thereby preventing flutter. D. Both a and b are correct.
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1046. JAAExam.com/ATPL Question ID: 781
Answer C is correct.
Which of the following statements about stall speed is correct?
The correct answer is C
A. Use of a T-tail will decrease the stall speed.
Decreasing the angle of sweep of the wing will decrease the stall speed.
B. Increasing the angle of sweep of the wing will decrease the stall speed.
References
C. Decreasing the angle of sweep of the wing will decrease the stall speed. D. Increasing the anhedral of the wing will decrease the stall speed.
1047. JAAExam.com/ATPL Question ID: 779
Answer B is correct.
A jet aeroplane cruises buffet free at high constant altitude in significant turbulence. Which type of stall can occur if this aeroplane decelerates?
The correct answer is B
A. Low speed stall.
Accelerated stall. References
B. Accelerated stall. C. Shock stall. D. Deep stall.
1048. JAAExam.com/ATPL Question ID: 522
Answer B is correct.
What causes deep stall in a swept back wing? A. CP moves aft. B. CP moves forward. C. Root stall.
The correct answer is B CP moves forward. References
D. Span wise flow from tip to root on wing upper surface.
1049. JAAExam.com/ATPL Question ID: 1489
Answer A is correct.
The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:
The correct answer is A
A. Wcos.gamma.
Wcos.gamma. References
B. W(1-sin.gamma). C. W(1-tan.gamma). D. W/cos.gamma.
1050. JAAExam.com/ATPL Question ID: 999
Answer D is correct.
The loss of total pressure in a shock wave is due to the fact that:
The correct answer is D
A. the friction in the boundary layer is higher. B. the speed reduction is too high. C. the static pressure decrease is comparatively high.
kinetic energy in the flow is changed into heat energy. References
D. kinetic energy in the flow is changed into heat energy.
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1051. JAAExam.com/ATPL Question ID: 1074
Answer B is correct.
An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:
The correct answer is B
A. zero.
upwards. References
B. upwards. C. downwards. D. upwards or downwards depending on elevator deflection.
1052. JAAExam.com/ATPL Question ID: 1491
Answer D is correct.
In a climbing turn:
The correct answer is D
A. the angle of attack on the inner wing will be greater than the angle of attack on the outer wing.
the angle of attack on the outer wing will be greater than the angle of attack on the inner wing.
B. the outer wing aileron must be deflected through a greater angle than the aileron on the inner wing.
References
C. the angle of attack on each wing will be the same. D. the angle of attack on the outer wing will be greater than the angle of attack on the inner wing.
1053. JAAExam.com/ATPL Question ID: 1352
Answer C is correct.
Which statement regarding the gust load factor on an aeroplane is correct (all other factors of importance being constant)?
The correct answer is C
1.
Increasing the aspect-ratio of the wing will increase the gust load factor.
2.
Increasing the speed will increase the gust load factor.
1 and 2 are correct. References
A. 1 and 2 are incorrect. B. 1 is incorrect and 2 is correct. C. 1 and 2 are correct. D. 1 is correct and 2 is incorrect.
1054. JAAExam.com/ATPL Question ID: 1516
Answer B is correct.
The four basic forces acting on an airplane in unaccelerated flight are:
The correct answer is B lift, weight, thrust and drag.
A. pressure forces, centrifugal forces, centripetal forces and inertia forces.
References
B. lift, weight, thrust and drag. C. lift, weight, gravity and thrust. D. lift, gravity, power, and friction.
1055. JAAExam.com/ATPL Question ID: 909
Answer B is correct.
Deploying a Fowler flap, the flap will:
The correct answer is B
A. just turn down. B. move aft, then turn down. C. turn down, then move aft.
move aft, then turn down. References
D. just move aft.
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1056. JAAExam.com/ATPL Question ID: 1550
Answer C is correct.
For a jet aircraft the best rate of climb is achieved:
The correct answer is C
A. at the optimum lift to drag ratio.
when excess power available is at a maximum.
B. when excess thrust available is at a maximum.
References
C. when excess power available is at a maximum. D. at the optimum angle of attack, nominally 4& #351;.
1057. JAAExam.com/ATPL Question ID: 1533
Answer D is correct.
When an aircraft is in a non-accelerated level flight, what are the relationships between lift, weight, thrust and drag?
The correct answer is D
A. Lift is greater than weight and thrust exceeds drag.
Lift is equal to weight and thrust is equal to drag. References
B. Lift is greater than weight and thrust is equal to drag. C. Lift is equal to weight and thrust exceeds drag. D. Lift is equal to weight and thrust is equal to drag.
1058. JAAExam.com/ATPL Question ID: 655
Answer C is correct.
Increasing dynamic (kinetic) pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant):
The correct answer is C
A. the drag decreases.
the drag increases. References
B. this has no effect. C. the drag increases. D. the drag is only affected by the ground speed.
1059. JAAExam.com/ATPL Question ID: 1096
Answer C is correct.
In what way is the longitudinal stability affected by the degree of positive camber of the aerofoil?
The correct answer is C
A. Negative, because the lift vector rotates forward at increasing angle of attack.
No effect, because camber of the aerofoil produces a constant pitch down moment coefficient, independent of angle of attack.
B. Positive, because the centre of pressure shifts rearward at increasing angle of attack.
References
C. No effect, because camber of the aerofoil produces a constant pitch down moment coefficient, independent of angle of attack. D. Positive, because the lift vector rotates backward at increasing angle of attack.
1060. JAAExam.com/ATPL Question ID: 1487
Answer B is correct.
The speed for minimum sink rate in a glide, compared to the speed for maximum distance VIMD is:
The correct answer is B
A. equal to VIMD.
slower than VIMD. References
B. slower than VIMD. C. faster than VIMD. D. not related to VIMD.
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1061. JAAExam.com/ATPL Question ID: 1208
Answer A is correct.
The purpose of the horizontal stabilizer is to:
The correct answer is A
A. give the aeroplane sufficient longitudinal stability.
give the aeroplane sufficient longitudinal stability.
B. give the aeroplane sufficient directional stability.
References
C. give the aeroplane enough weight in the tail. D. give the aeroplane sufficient lateral stability.
1062. JAAExam.com/ATPL Question ID: 959
Answer A is correct.
How does temperature influence the speed of sound?
The correct answer is A
A. Speed of sound increases with temperature increase.
Speed of sound increases with temperature increase.
B. Speed of sound decreases with temperature increase.
References
C. Speed of sound is not influenced by temperature. D. Speed of sound remains constant.
1063. JAAExam.com/ATPL Question ID: 873
Answer A is correct.
When vortex generators are fitted they will normally be found:
The correct answer is A
A. near the wing leading edge in front of control surfaces. B. towards the wing root to act as a stall inducer.
near the wing leading edge in front of control surfaces. References
C. on the underside of the wing towards the leading edge. D. towards the wing trailing edge.
1064. JAAExam.com/ATPL Question ID: 1222
Answer B is correct.
An example of differential aileron deflection during initiation of left turn is:
The correct answer is B left aileron: 5° up Right aileron: 2° down.
A. left aileron: 2° up Right aileron: 5° down. B. left aileron: 5° up Right aileron: 2° down.
References
C. left aileron: 5° down Right aileron: 2° up. D. left aileron: 2° down Right aileron: 5° up.
1065. JAAExam.com/ATPL Question ID: 687
Answer B is correct.
At the tip of the wing in level flight, the air flows:
The correct answer is B
A. from the upper surface to the lower surface. B. from the lower surface to the upper surface and then down at the trailing edge. C. from the lower surface to the upper surface and then diverges away from the fuselage.
from the lower surface to the upper surface and then down at the trailing edge. References
D. to produce induced drag at its lowest value.
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1066. JAAExam.com/ATPL Question ID: 960
Answer B is correct.
The two areas of speed instability in transonic aircraft are:
The correct answer is B below VDmin, M 0.89 to 0.98
A. above VDmin, above M 0.4 B. below VDmin, M 0.89 to 0.98
References
C. above VDmin, M 0.75 to 0.81 D. below VDmin, above M 1.0
1067. JAAExam.com/ATPL Question ID: 654
Answer D is correct.
The frontal area of a body, placed in a certain airstream is increased by a factor 3. The shape will not alter. The aerodynamic drag will increase with a factor:
The correct answer is D
A. 1.5
3 References
B. 9 C. 6 D. 3
1068. JAAExam.com/ATPL Question ID: 795
Answer D is correct.
The boundary layer of a wing is caused by:
The correct answer is D
A. suction at the upper wing side.
a layer on the wing in which the stream velocity is lower than the free stream velocity, due to friction.
B. the normal shock wave at transonic speeds
References
C. a turbulent stream pattern around the wing. D. a layer on the wing in which the stream velocity is lower than the free stream velocity, due to friction.
1069. JAAExam.com/ATPL Question ID: 981
Answer B is correct.
Compared to a normal transonic airfoil section a supercritical section has:
The correct answer is B a flatter top surface.
A. a more cambered top surface. B. a flatter top surface.
References
C. a flatter bottom surface. D. a very sharp leading edge.
1070. JAAExam.com/ATPL Question ID: 1114
Answer B is correct.
Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability?
The correct answer is B
A. The engine.
The horizontal tailplane. References
B. The horizontal tailplane. C. The fuselage. D. The wing.
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1071. JAAExam.com/ATPL Question ID: 717
Answer A is correct.
Interference drag can be reduced using:
The correct answer is A
A. fairings. B. winglets. C. wing fences
fairings. References
D. fairings, winglets and wing fences.
1072. JAAExam.com/ATPL Question ID: 1264
Answer B is correct.
A balance tab is a form of aerodynamic balance and is designed to:
The correct answer is B
A. move in the same direction as the control surface. B. move in the opposite direction to the elevator when it is deflected up, but remain approximately parallel to the tailplane chord line.
move in the opposite direction to the elevator when it is deflected up, but remain approximately parallel to the tailplane chord line. References
C. be operated direct by the control column, which aerodynamically then moves the control surface. D. operate in conjunction with hydraulic servo units.
1073. JAAExam.com/ATPL Question ID: 611
Answer D is correct.
When the angle of attack is increased, the stagnation point moves ... and the separation point moves...
The correct answer is D Backwards; Forward
A. Forward; Forward B. Forward; Backwards
References
C. Backwards; Back D. Backwards; Forward
1074. JAAExam.com/ATPL Question ID: 825
Answer A is correct.
During an erect spin recovery:
The correct answer is A
A. the ailerons are held in the neutral position.
the ailerons are held in the neutral position.
B. the control stick is moved side ways, against the angle of bank.
References
C. the control stick is moved side ways, in the direction of the angle of bank. D. the control stick is pulled to the most aft position.
1075. JAAExam.com/ATPL Question ID: 1513
Answer D is correct.
Which of the following forces enables an aircraft to make a level turn?
The correct answer is D Lift.
A. Weight. B. Aeroplane drag.
References
C. Engine thrust. D. Lift.
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1076. JAAExam.com/ATPL Question ID: 1066
Answer B is correct.
When airflow over a wing becomes supersonic, the pressure pattern on the top surface will become:
The correct answer is B irregular.
A. the same as subsonic. B. irregular. C. rectangular. D. triangular.
References
1077. JAAExam.com/ATPL Question ID: 1503
Answer A is correct.
For a jet aircraft, the best rate of climb is achieved:
The correct answer is A
A. when excess power available is maximum. B. when excess thrust available is maximum. C. at the optimum lift to drag ratio.
when excess power available is maximum. References
D. at the optimum angle of attack.
1078. JAAExam.com/ATPL Question ID: 735
Answer B is correct.
Total Drag is the sum of:
The correct answer is B
A. profile drag, form drag, induced drag and wake drag.
induced drag, pressure drag, skin friction drag and interference drag.
B. induced drag, pressure drag, skin friction drag and interference drag.
References
C. wake drag, interference drag and form drag. D. induced drag, form drag, interference drag and zero lift drag.
1079. JAAExam.com/ATPL Question ID: 802
Answer C is correct.
What causes a swept wing aircraft to pitch-up at the stall:
The correct answer is C Span wise flow.
A. Negative camber at the root. B. Separated airflow at the root.
References
C. Span wise flow. D. Rearward movement of the CP
1080. JAAExam.com/ATPL Question ID: 915
Answer B is correct.
A deployed slat will:
The correct answer is B
A. decrease the boundary layer energy and decrease the suction peak on the slat, so that CLmax is reached at lower angles of attack. B. increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher angles of attack.
increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher angles of attack. References
C. increase the boundary layer energy, move the suction peak from the fixed part of the wing to the slat, so that the stall is postponed to higher angles of attack. D. increase the camber of the aerofoil and increase the effective angle of attack, so that CLmax is reached at higher angles of attack.
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1081. JAAExam.com/ATPL Question ID: 728
Answer A is correct.
Which of the following will reduce induced drag?
The correct answer is A
A. Elliptical lift distribution. B. Low aspect ratio. C. Flying at high angles of attack.
Elliptical lift distribution. References
D. Extending the flaps.
1082. JAAExam.com/ATPL Question ID: 1326
Answer D is correct.
Control surface vibration at high airspeed is known as:
The correct answer is D flutter.
A. vibration. B. snatch.
References
C. reversal. D. flutter.
1083. JAAExam.com/ATPL Question ID: 809
Answer D is correct.
When an aircraft wing stalls:
The correct answer is D
A. a swept back wing will stall from the root and the CP will move aft.
a swept back wing will stall from the tip and the CP will move forward.
B. a wing which is not swept back will stall from the root and the CP will move forwards.
References
C. a straight wing will tend to stall from the tip and the CP will move backwards. D. a swept back wing will stall from the tip and the CP will move forward.
1084. JAAExam.com/ATPL Question ID: 912
Answer B is correct.
Refer to Figure: 081-13
The correct answer is B
(Refer to figure 081-13) The high lift device shown in the figure is a:
Leading edge slot References
A. Krueger flap. B. Leading edge slot C. Fowler flap. D. Slotted flap.
1085. JAAExam.com/ATPL Question ID: 670
Answer A is correct.
Which of the following descriptions most accurately describes the airflow that causes wing tip vortices?
The correct answer is A From the tip to the root on the top surface and from
A. From the tip to the root on the top surface and from the root to the tip on the bottom surface over the wing tip.
the root to the tip on the bottom surface over the wing tip.
B. From the tip to the root on the top surface and from the root to the tip on the bottom surface over the trailing edge.
References
C. From the root to the tip on the top surface and from the tip to the root on the bottom surface over the trailing edge. D. From the root to the tip on the top surface and from the tip to the root on the bottom surface over the wing tip.
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1086. JAAExam.com/ATPL Question ID: 625
Answer D is correct.
The airflow over the upper surface of the wing of an aircraft in level flight compared to the free stream air will:
The correct answer is D
A. have the same velocity, resulting in reduced pressure.
experience an increase in velocity and a reduction in pressure. References
B. have greater velocity, resulting in increased pressure. C. experience a reduction in velocity producing increased pressure. D. experience an increase in velocity and a reduction in pressure.
1087. JAAExam.com/ATPL Question ID: 947
Answer A is correct.
In the transonic range Clmax will ... and the 1g stalling speed will...
The correct answer is A decrease, increase.
A. decrease, increase. B. decrease, decrease.
References
C. increase, decrease. D. increase, increase.
1088. JAAExam.com/ATPL Question ID: 651
Answer A is correct.
The lift formula is:
The correct answer is A
A. L= CL 1/2 RHO V? S B. L= W C. L= CL 2 RHO V? S
L= CL 1/2 RHO V? S References
D. L= n W
1089. JAAExam.com/ATPL Question ID: 799
Answer D is correct.
When an aircraft with a typical aerofoil is in level flight at low speed and high angle of attack, the normal axis is: A. vertical.
The correct answer is D nearly vertical. References
B. horizontal from side to side. C. horizontal from front to rear. D. nearly vertical.
1090. JAAExam.com/ATPL Question ID: 1333
Answer A is correct.
Load Factor is defined as:
The correct answer is A
A. lift divided by weight. B. the inverse of the secant bank angle. C. thrust divided by weight.
lift divided by weight. References
D. a multiplying factor which converts a force into a moment of a force.
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1091. JAAExam.com/ATPL Question ID: 599
Answer B is correct.
What are the standard temperature and pressure values for sea level?
The correct answer is B 15° C and 29.92 Hg.
A. 1013.25Pa and 13° C. B. 15° C and 29.92 Hg.
References
C. 59° C and 1013.2 millibar. D. 59° F and 29.92 millibar
1092. JAAExam.com/ATPL Question ID: 989
Answer D is correct.
Which statement is correct about a normal shock wave?
The correct answer is D The airflow changes from supersonic to subsonic.
A. The airflow expands when passing the aerofoil.
References
B. The airflow changes direction. C. The airflow changes from subsonic to supersonic. D. The airflow changes from supersonic to subsonic.
1093. JAAExam.com/ATPL Question ID: 961
Answer C is correct.
The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
The correct answer is C 500 kts
A. 480 kts
References
B. 320 kts C. 500 kts D. 600 kts
1094. JAAExam.com/ATPL Question ID: 882
Answer B is correct.
The type of flap which extends rearward from the trailing edge as it is lowered is:
The correct answer is B a fowler flap.
A. a zap flap. B. a fowler flap.
References
C. a split flap. D. a Krueger flap
1095. JAAExam.com/ATPL Question ID: 671
Answer D is correct.
What is the effect on induced drag of weight and speed changes?
The correct answer is D
A. Induced drag decreases with decreasing speed and induced drag decreases With increasing weight.
Induced drag decreases with increasing speed and induced drag decreases with decreasing weight. References
B. Induced drag increases with increasing speed and induced drag increases with decreasing weight. C. Induced drag decreases with decreasing speed and induced drag increases with increasing weight. D. Induced drag decreases with increasing speed and induced drag decreases with decreasing weight.
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1096. JAAExam.com/ATPL Question ID: 1051
Answer A is correct.
Mcrit is the speed at which:
The correct answer is A
A. sonic flow is first achieved above the surface of the airfoil. B. the a/c is passing the sound barrier. C. the centre of pressure is moving aft.
sonic flow is first achieved above the surface of the airfoil. References
D. the aircraft is not controllable.
1097. JAAExam.com/ATPL Question ID: 1426
Answer D is correct.
In the alpha and beta ranges respectively the governed elements of turboprop propeller controls
The correct answer is D
are as follows: A. fuel flow and pitch.
propeller RPM and engine RPM. References
B. reverse thrust and blade angle. C. engine RPM and fuel flow. D. propeller RPM and engine RPM.
1098. JAAExam.com/ATPL Question ID: 638
Answer B is correct.
The terms q and S in the lift formula are:
The correct answer is B
A. square root of surface and wing loading. B. dynamic pressure and the area of the wing. C. static pressure and wing surface area.
dynamic pressure and the area of the wing. References
D. static pressure and dynamic pressure.
1099. JAAExam.com/ATPL Question ID: 531
Answer C is correct.
VS is 100 kt at n = 1, what will the stall speed be at n = 2?
The correct answer is C 141 kts
A. 200 kts B. 119 kts
References
C. 141 kts D. 100 kts
1100. JAAExam.com/ATPL Question ID: 1523
Answer D is correct.
What action must the pilot take to maintain altitude and airspeed when turning in a jet aircraft?
The correct answer is D Increase angle of attack and thrust.
A. Increase thrust B. Increase angle of attack.
References
C. Decrease the turn radius. D. Increase angle of attack and thrust.
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1101. JAAExam.com/ATPL Question ID: 1188
Answer A is correct.
Manoeuvrability is best at:
The correct answer is A
A. aft CG position. B. forward CG position. C. high flap settings. D. low speed.
aft CG position. References
1102. JAAExam.com/ATPL Question ID: 1282
Answer D is correct.
The location of mass balance weights is:
The correct answer is D
A. on the hinge line if the control surface has an inset hinge.
in front of the hinge line.
B. on the hinge line if the control surface does not have an inset hinge.
References
C. always on the hinge line, irrespective of the type of aerodynamic balance. D. in front of the hinge line.
1103. JAAExam.com/ATPL Question ID: 1506
Answer B is correct.
The margin between the power available and the power required:
The correct answer is B decreases when the aircraft climbs.
A. increases when the aircraft climbs. B. decreases when the aircraft climbs.
References
C. decreases when the aircraft descends. D. remains the same.
1104. JAAExam.com/ATPL Question ID: 516
Answer C is correct.
An aircraft is flying at sea level with an indicated airspeed of 210kts. What will be the true airspeed at that time?
The correct answer is C
A. More than 210 kts.
210 kts. References
B. Less than 210 kts. C. 210 kts. D. 0 kts.
1105. JAAExam.com/ATPL Question ID: 1083
Answer C is correct.
The distance between the CG Datum and the CG Neutral Point in straight and level flight is called the:
The correct answer is C CG static margin.
A. CG forward limit. B. CG aft limit.
References
C. CG static margin. D. CG manoeuvre margin
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1106. JAAExam.com/ATPL Question ID: 1428
Answer B is correct.
One a variable pitch propeller, were can you find the largest blade angle?
The correct answer is B at the blade root.
A. depends on the pitch setting of the propeller.
References
B. at the blade root. C. at the blade tip. D. depends on the rotation direction of the propeller.
1107. JAAExam.com/ATPL Question ID: 1189
Answer A is correct.
The sweepback on a wing will:
The correct answer is A
A. increase the possibility of a wing tip stall.
increase the possibility of a wing tip stall.
B. cause the stall to occur at lower angles of attack.
References
C. reduce the possibility for the wing tip to stall. D. have no effect on the stall characteristics.
1108. JAAExam.com/ATPL Question ID: 817
Answer A is correct.
By what approximate percentage will the stall speed increase in a horizontal coordinated turn with a bank angle of 45° ?
The correct answer is A
A. 19%
19% References
B. 31% C. 41% D. 52%
1109. JAAExam.com/ATPL Question ID: 834
Answer C is correct.
How does stalling speed (IAS) vary with altitude?
The correct answer is C
A. It remains constant at lower altitudes but decreases at higher altitudes due to compressibility effects.
It increases with increasing altitude, because the density decreases.
B. It remains constant.
References
C. It increases with increasing altitude, because the density decreases. D. It remains constant at lower altitudes but increases at higher altitudes due to compressibility effects.
1110. JAAExam.com/ATPL Question ID: 1418
Answer B is correct.
With the propeller windmilling after an engine failure, the:
The correct answer is B ATM and CTM will act in the same direction.
A. CTM will rapidly increase. B. ATM and CTM will act in the same direction. C. ATM and CTM will immediately reduce to
References
zero. D. ATM will rapidly increase.
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1111. JAAExam.com/ATPL Question ID: 542
Answer B is correct.
The total pressure is:
The correct answer is B
A. can be measured in a small hole in a surface, parallel to the local stream.
static pressure plus the dynamic pressure.
B. static pressure plus the dynamic pressure.
References
C. static pressure minus the dynamic pressure. D. 1/2 rho V2
1112. JAAExam.com/ATPL Question ID: 1112
Answer A is correct.
Which of the following best describes the function of the Mach trim system?
The correct answer is A It adjusts the longitudinal trim of the aircraft.
A. It adjusts the longitudinal trim of the aircraft. B. It adjusts the stabiliser trim position.
References
C. It adjusts the fore and aft fuel balance. D. It adjusts the elevator trim tab.
1113. JAAExam.com/ATPL Question ID: 681
Answer A is correct.
The characteristics of a high aspect ratio wing has are:
The correct answer is A short chord, long span.
A. short chord, long span. B. long span, long chord.
References
C. long chord, short span. D. short chord, short span.
1114. JAAExam.com/ATPL Question ID: 1529
Answer A is correct.
From the polar diagram of the entire aeroplane one can read:
The correct answer is A
A. the maximum CL/CD ratio and maximum lift coefficient. B. the minimum drag and the maximum lift. C. the minimum drag coefficient and the maximum lift. D. the minimum CL/CD ratio and the minimum drag.
the maximum CL/CD ratio and maximum lift coefficient. References
1115. JAAExam.com/ATPL Question ID: 1280
Answer A is correct.
Mass balance to reduce control flutter is not required on:
The correct answer is A
A. aircraft with a fully powered irreversible control system with no manual emergency system.
aircraft with a fully powered irreversible control system with no manual emergency system. References
B. aircraft with a fully powered irreversible control system. C. aircraft limited to speeds below 200kt. D. aircraft with short rigid wings.
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1116. JAAExam.com/ATPL Question ID: 693
Answer B is correct.
When landing behind a large aircraft, the pilot should avoid wake turbulence by flying:
The correct answer is B
A. below the large aircrafts final approach path and landing behind the large aircrafts touchdown point.
above the large aircrafts final approach path and landing behind the large aircrafts touchdown point. References
B. above the large aircrafts final approach path and landing behind the large aircrafts touchdown point. C. below the large aircrafts final approach path and landing before the large aircrafts touchdown point. D. above the large aircrafts final approach path and landing before the large aircrafts touchdown point.
1117. JAAExam.com/ATPL Question ID: 1285
Answer D is correct.
Which of the following is an advantage of engines mounted on the rear fuselage over those mounted in wing pods?
The correct answer is D
A. Wings can have a lighter form of construction.
Longitudinal trim is less affected by changes in thrust. References
B. The wing is less likely to suffer from flutter. C. Easier maintenance access. D. Longitudinal trim is less affected by changes in thrust.
1118. JAAExam.com/ATPL Question ID: 1151
Answer C is correct.
Which of the following lists aeroplane features that each increase static lateral stability?
The correct answer is C High wing, sweep back, large and high vertical fin.
A. Fuselage mounted engines, dihedral, T-tail. B. Low wing, dihedral, elliptical wing planform. C. High wing, sweep back, large and high
References
vertical fin. D. Sweep back, under wing mounted engines, winglets.
1119. JAAExam.com/ATPL Question ID: 1472
Answer B is correct.
During a power-off glide, the forces acting on an aircraft are:
The correct answer is B lift, drag and weight.
A. thrust, lift and drag. B. lift, drag and weight.
References
C. drag, thrust and weight. D. lift, weight and inertia forces.
081-03 - 081-03
Principles of Flight (Aeroplane) (081) - JAAExam.com/ATPL
081-02 - 081-02
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081-10 - 081-10
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081-16 - 081-16
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081-17 - 081-17
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081-11 - 081-11
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081-07 - 081-07
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081-01 - 081-01
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081-09 - 081-09
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081-08 - 081-08
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081-04 - 081-04
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081-06 - 081-06
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081-15 - 081-15
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081-14 - 081-14
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081-12 - 081-12
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081-13 - 081-13
Principles of Flight (Aeroplane) (081) - JAAExam.com/ATPL
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