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Exam simulation Principles of Flight - ATPL - Airline Transport Pilot license

Exam simulation ATPL Principles of Flight 120 questions on 120 minutes

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1 - Deflection of leading edge flaps will:
2 - When the air is passing through an expansion wave the local speed of sound will
3 - Which statement is correct? I. Propeller gyroscopic effect occurs during aeroplane yaw changes. II. Propeller gyroscopic effect is most noticeable during low speed flight at high propeller RPM.
4 - The function of the stick pusher is:
5 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
6 - When 'spoilers' are used as speed brakes:
7 - Which combination of design features is known to be responsible for deep stall?
8 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
9 - What increases the stalling angle of attack? Use of:
10 - The stall speed in a 60° banked turn increases by the following factor:
11 - 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:
12 - The 'short period mode' is an:
13 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
14 - The lift formula is: (rho = density)
15 - In straight and level flight, as speed is increased:
16 - The consequences of exceeding Mcrit in a swept-wing aeroplane may be: (assume no corrective devices, straight and level flight)
17 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
18 - The stalling speed in IAS will change according to the following factors:
19 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
20 - The most important problem of ice accretion on a transport aeroplane during flight is:
21 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
22 - An aeroplane has a servo tab controlled elevator. What will happen if the elevator jams during flight?
23 - Which aeroplane behaviour will be corrected by a yaw damper?
24 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
25 - A high aspect ratio wing produces:
26 - If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
27 - Which statement about stick force per g is correct?
28 - Spoiler deflection causes:
29 - The SI units of air density (I) and force (II) are:
30 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
31 - The aspect ratio of the wing:
32 - Dangerous stall characteristics, in large transport aeroplanes that require stick pushers to be installed, include:
33 - 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)
34 - Rolling is the rotation of the aeroplane about the:
35 - Upon extension of a spoiler on a wing:
36 - An engine failure can result in a windmilling (1) propeller and a feathered (2) propeller. Which statement about propeller drag is correct?
37 - The following factors increase stall speed:
38 - VA is:
39 - Shock induced separation results in
40 - Long period (phugoid) oscillations are characterised by:
41 - Load factor is:
42 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability?
43 - Mass-balancing of control surfaces is used to:
44 - Critical Mach number is the free stream Mach number at which:
45 - The effect of a ventral fin on the static stability of an aeroplane is as follows: (1=longitudinal, 2=lateral, 3=directional)
46 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
47 - Tuck under will happen
48 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
49 - An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed?
50 - 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:
51 - The stall speed:
52 - High speed buffet is induced by
53 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
54 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
55 - Flaperons are controls which combine the function of:
56 - A jet aeroplane cruises buffet free at high constant altitude. Which type of stall can occur if this aeroplane decelerates during an inadvertent increase in load factor?
57 - Mach buffet occurs:
58 - The angle of attack of a wing profile is defined as the angle between:
59 - An aeroplane, with a CG location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:
60 - What data may be obtained from buffet onset boundary data?
61 - The lift- and drag forces, acting on a wing cross section:
62 - In what flight phase are the outboard ailerons (if present) not operated?
63 - Which has the effect of increasing load factor? (all other relevant factors being constant)
64 - A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case
65 - Positive static lateral stability is the tendency of an aeroplane to:
66 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
67 - 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)
68 - In the transonic range lift will decrease at the shock stall due to the
69 - At higher altitudes, the stall speed (IAS):
70 - For an aeroplane with one fixed value of VA the following applies. VA is:
71 - If the nose of an aeroplane yaws left, this causes:
72 - How does stalling speed (IAS) vary with altitude?
73 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
74 - 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:
75 - 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:
76 - Static lateral stability will be increased by:
77 - The correct drag formula is:
78 - In a convergent tube with an incompressible sub-sonic airflow, the following pressure changes will occur: Ps = static pressure. Pdyn = dynamic pressure. Ptot = total pressure.
79 - The wing of an aeroplane will never stall at low subsonic speeds as long as....
80 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
81 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
82 - Positive static stability of an aeroplane means that following a disturbance from the equilibrium condition:
83 - When flaps are deployed at constant angle of attack the lift coefficient will:
84 - What is the effect on induced drag of mass and speed changes? (all other factors of importance remaining constant)
85 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
86 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
87 - Differential aileron deflection:
88 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
89 - An aeroplane has a stall speed of 100 kt at a mass of 1000 kg. If the mass is increased to 2000 kg, the new value of the stall speed will be:
90 - An aeroplane performs a steady horizontal turn with a TAS of 200 KT. The turn radius is 2000m. The load factor (n) is approximately:
91 - The trailing edge flaps when extended:
92 - The relative thickness of an aerofoil is expressed as:
93 - The units of wing loading (I) W / S and (II) dynamic pressure q are:
94 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
95 - Drag is in the direction of - and lift is perpendicular to the:
96 - Total pressure is: (rho = density)
97 - The value of the manoeuvre stability of an aeroplane is 150 N / g. The stick force required to achieve a load factor of 2.5 from steady level flight is:
98 - Which kind of boundary layer has the strongest change in velocity close to the surface?
99 - Static lateral stability should not be too small, because:
100 - Induced drag may be reduced by:
101 - The aerodynamic centre of the wing is the point, where:
102 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
103 - The angle of attack for a propeller blade is the angle between the blade chord line and the:
104 - How can wing flutter be prevented?
105 - Regarding flight in severe turbulence, which of the following statements is true?
106 - In case the Mach trimmer fails:
107 - When the air is passing through an expansion wave the static temperature will
108 - In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?
109 - 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?
110 - Which of the following statements about the difference between Krueger flaps and slats is correct?
111 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
112 - Which statement is correct at the speed for minimum drag (subsonic)?
113 - After the transition point between the laminar and turbulent boundary layer
114 - What is the limit load factor of a large transport aeroplane?
115 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:
116 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
117 - What is the SI unit of measurement for power?
118 - 'Tuck under' may happen at:
119 - Which of the following statements about the spin is correct?
120 - 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:
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