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

Exam simulation ATPL Question Bank in English Principles of Flight 120 questions on 120 minutes

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1 - Which aeroplane design has the highest probability of a super stall?
2 - Which statement follows from Bernoulli's equation for incompressible flow when total pressure remains constant?
3 - The wing of an aeroplane will never stall at low subsonic speeds as long as....
4 - In a linear incompressible model of a swept-wing aeroplane at unchanged dynamic pressure, lift coefficient and configuration, ignore Mach effects and assume that the aerodynamic coefficients remain unchanged. As altitude and TAS increase, static lateral stability (1) and natural aerodynamic roll/yaw damping (2) will:
5 - Vortex generators mounted on the upper wing surface will
6 - The following unit of measurement: kg m/s^2 is expressed in the SI-system as:
7 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
8 - At fixed IAS in the ISA troposphere, neglecting instrument, position and compressibility errors, the difference TAS − IAS will:
9 - When the air is passing through an expansion wave the static temperature will
10 - Load factor is:
11 - Compare two conventional trim models: 1. a mechanically linked elevator with a trim tab; 2. an irreversible powered elevator kept neutral by THS trim, whose control-column centring reference stays fixed. After re-trimming for a speed increase, the neutral control-column position:
12 - In steady level flight at constant IAS and unchanged aerodynamic configuration, ignoring compressibility, induced drag is directly affected by:
13 - Critical Mach number is the free stream Mach number at which:
14 - In a swept-back wing aeroplane that exhibits tip-stall pitch-up, this effect is mainly caused by:
15 - A jet has inboard and outboard ailerons, with the outboard ailerons locked out in the high-speed cruise configuration. Which ailerons are active in that configuration?
16 - In the typical conventional positive-lift, pre-stall pressure distribution illustrated in FAA guidance, as angle of attack increases the leading-edge stagnation point moves (I) and the upper-surface minimum-pressure region moves (II):
17 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
18 - The bank angle in a rate-one turn depends on:
19 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
20 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
21 - 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:
22 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. An increase in 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:
23 - For a constant-speed propeller within its governing range, with selected RPM and engine power unchanged, which statement is correct when airspeed increases?
24 - The diagram shows the parameter X versus TAS. If a horizontal flight is considered the axis X shows
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25 - Compared with flight out of ground effect, when a wing enters ground effect at unchanged angle of attack, true airspeed and air density:
26 - Differential aileron deflection:
27 - Gyroscopic precession of a propeller is induced by:
28 - In the linear vertical-gust model, which disturbance creates a positive increment in angle of attack and load factor for an initially steady level-flying aeroplane?
29 - 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)
30 - Interference drag is the result of:
31 - Which statement about stick force per g is correct?
32 - Which statement is correct about a spring tab?
33 - Regarding flight in severe turbulence, which of the following statements is true?
34 - An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is:
35 - Which of the following flight phenomena can occur at Mach numbers below the critical Mach number?
36 - With mechanically linked, hydraulically boosted pitch controls that retain direct aerodynamic force feedback:
37 - In classical thin-aerofoil theory for an unswept symmetrical aerofoil producing lift in supersonic flow, the centre of pressure is approximately:
38 - Extending a simple hinged plain trailing-edge flap normally has which effect in the classical low-speed aerofoil comparison?
39 - The relative thickness of an aerofoil is expressed as:
40 - Which statement is correct about a normal shock wave?
41 - The angle between the airflow (relative wind) and the chord line of an aerofoil is:
42 - The torque effect during the take-off run in respect of a right hand propeller, when viewed from behind, will tend to:
43 - A high aspect ratio wing produces:
44 - Why can unintended leading-edge ice contamination create a serious stall risk during take-off rotation?
45 - Which statement correctly describes the pressure-driven spanwise airflow associated with tip vortices on a finite wing producing positive lift in normal flight?
46 - Geometric wing dihedral, viewed from the front of the aeroplane, is:
47 - During a windmilling idle-power glide at the same true airspeed and air density, reducing propeller blade pitch increases propeller drag. The equilibrium glide ratio and rate of descent then:
48 - The unit of density is:
49 - The lift- and drag forces, acting on a wing cross section:
50 - How will the density and static temperature change in a supersonic flow from a position in front of a shock wave to behind it?
51 - On a transport with fully powered, irreversible elevator controls, what is an important advantage of an adjustable horizontal stabiliser for pitch trim?
52 - The vane of a stall warning system with a flapper switch is activated by the change of the:
53 - Spoiler deflection causes:
54 - What increases the stalling angle of attack? Use of:
55 - In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?
56 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
57 - A correctly loaded and configured jet transport has its CG at the forward limit and its trimmable horizontal stabiliser set to the approved take-off position for that actual CG and configuration. Using the prescribed rotation technique:
58 - For a conventional stable aeroplane, considering pitch responsiveness and remaining within the approved CG range, manoeuvrability is generally greatest when the:
59 - For a conventional aeroplane with fully extended trailing-edge flaps, what is normally required to establish steady level flight at the same IAS as before extension? Consider the lift and drag changes, rather than the transient pitching moment.
60 - Winglets
61 - The 'short period mode' is an:
62 - The angle of attack of a blade section is the angle between the chord line and the:
63 - For a light aeroplane certificated under the legacy utility-category requirements, what is the specified positive manoeuvring limit load factor in the clean configuration?
64 - 'Tuck under' may happen at:
65 - On a swept-wing aeroplane with a T-tail susceptible to deep stall, when the stalled wing’s wake blankets the horizontal tail, the effect can be:
66 - Which of the following statements about dihedral is correct?
67 - Rotation around the normal axis is called:
68 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)
69 - 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:
70 - The aerofoil polar is:
71 - During a windmilling idle-power glide at constant true airspeed, with a constant-speed propeller operating within its governing range, advancing the RPM control to select a higher RPM causes the propeller blade pitch and equilibrium rate of descent to:
72 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
73 - An aeroplane has roll spoilers and both inboard and outboard ailerons. With the outboard ailerons locked out in the high-speed cruise configuration, roll control is provided by:
74 - Positive static lateral stability is the tendency of an aeroplane to:
75 - The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
76 - An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 lbs. What is the stall speed when the weight is 5000 lbs?
77 - Mach buffet occurs:
78 - Rolling is the rotation of the aeroplane about the:
79 - After a calorically perfect gas of unchanged composition passes through a compression shock wave, its local speed of sound is:
80 - In an idealised steady, straight descent at 160 kt TAS and 1000 ft/min, assume that thrust is parallel to the flight path and that acceleration is zero. In this condition:
81 - Which adverse aerodynamic effects have been observed in tests of a wing exposed to very heavy rain?
82 - The effect of a positive wing sweep on static directional stability is as follows:
83 - Which of the following aeroplane parts affect induced drag most?
84 - Examples of aerodynamic balancing of control surfaces are:
85 - Dihedral of the wing:
86 - For a conventional, positively stable aeroplane with a fixed horizontal tail, elevator and simple elevator trim tab, after increasing speed and re-establishing trimmed straight-and-level flight at unchanged mass and configuration:
87 - The function of the slot between an extended slat and the leading edge of the wing is to:
88 - If the control column is pushed forward, a trim tab on the elevator:
89 - The angle of attack of a wing profile is defined as the angle between:
90 - Two identical aircraft A and B, with the same mass, are flying steady level co-ordinated 20 degree bank turns. If the TAS of A is 130 KT and that of B is 200 KT:
91 - When the air has passed through a normal shock wave the Mach number is
92 - For a conventional aerofoil with a simple hinged plain trailing-edge flap, neglect compressibility and wing-area change. When the flap is extended while steady level flight at the same mass and IAS is maintained by reducing angle of attack:
93 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
94 - The application of the area rule on aeroplane design will decrease the
95 - Which statement is correct about the laminar and turbulent boundary layer:
96 - For a constant-speed propeller operating within its governing range, how are small changes in airspeed or propeller load normally handled?
97 - The critical Mach number can be increased by
98 - One disadvantage of a simple unmodified swept-back wing is its stall tendency. As the stall develops:
99 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
100 - In conventional control-force design, which listed device can add a forward stick force that increases with positive normal acceleration, thereby increasing stick force per g?
101 - In the classical low-speed comparison of a conventional aerofoil with a plain trailing-edge flap at a substantial extension, compared with the basic unflapped section the angle of attack at CLmax is normally:
102 - For a conventional aeroplane in level flight, assume that forward CG requires greater tail downforce and that take-off thrust provides both an upward force component and a nose-up moment, reducing the required wing lift. At the same mass, which combination requires the greatest wing lift?
103 - Long period (phugoid) oscillations are characterised by:
104 - The boundary layer of a wing is:
105 - The true airspeed (TAS) is:
106 - When flaps are deployed at constant angle of attack the lift coefficient will:
107 - Shock induced separation results in
108 - In the classical low-Mach comparison of similar, unswept, untwisted wings using the same aerofoil section, increasing aspect ratio generally has the effect of:
109 - For the same upstream conditions and Mach number in a calorically perfect gas, compared with an oblique compression shock inclined at less than 90° to the flow, a normal shock has:
110 - The induced drag:
111 - The function of the stick pusher is:
112 - For an intact aeroplane, a single large up-elevator input at a speed just above the applicable manoeuvring speed VA creates which structural risk?
113 - The units of wing loading (I) W / S and (II) dynamic pressure q are:
114 - 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:
115 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
116 - Which listed flap system moves rearward as it extends, increasing wing area as well as camber?
117 - Which listed design feature reduces adverse yaw during rolling into or out of a turn?
118 - When a pilot makes a turn in horizontal flight, the stall speed:
119 - In the classical fixed-area wing model, extending only the inboard trailing-edge flaps at constant IAS and total wing lift allows angle of attack to be reduced. Assuming attached flow and unchanged outboard aerofoil characteristics, the lift on the unflapped outer wing sections will normally:
120 - On a transonic wing, what is the main purpose of vortex generators fitted to the upper surface?
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