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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 - 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:
2 - Why can unintended leading-edge ice contamination create a serious stall risk during take-off rotation?
3 - 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:
4 - Which listed design feature reduces adverse yaw during rolling into or out of a turn?
5 - Which aeroplane design has the highest probability of a super stall?
6 - A conventional stabiliser on a stable aeroplane in a normal cruise condition: 1 - always provides negative lift. 2 - contributes to the total lift of the aeroplane. 3 - may stall before the wing, in icing conditions, with large flap settings, unless adequate design and/or operational precautions are taken. 4 - is necessary to balance the total pitch moment of the aeroplane. Which of the following lists all the correct statements?
7 - For a constant-speed propeller within its governing range, with selected RPM and engine power unchanged, which statement is correct when airspeed increases?
8 - With wing loading and other relevant properties comparable, which listed wing feature normally reduces vertical-gust sensitivity by reducing lift-curve slope?
9 - The diagram shows the parameter X versus TAS. If a horizontal flight is considered the axis X shows
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10 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
11 - Which of the following will reduce induced drag?
12 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?
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13 - In a first-order sideslip model, a symmetrical ventral fin on the centreline lies behind and below the CG. Neglecting secondary interference effects, its contribution to static stability is: (1 = longitudinal, 2 = lateral, 3 = directional)
14 - A "slat" is:
15 - The SI units of air density (I) and force (II) are:
16 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
17 - Which one of the bodies in motion (all bodies have the same cross section area) will have lowest drag?
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18 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
19 - Following a Mach-trimmer failure, which general action is appropriate?
20 - In the classical design model where a published VA is chosen at MTOW as the intersection of the positive stall boundary and manoeuvring limit-load line, VA is:
21 - In steady level flight at unchanged altitude and aerodynamic configuration, ignoring compressibility, which option describes an induced-drag change that is guaranteed by its combination of mass and airspeed changes, regardless of their relative amounts?
22 - In a swept-back wing aeroplane that exhibits tip-stall pitch-up, this effect is mainly caused by:
23 - Which statement is correct about the effect of an aileron on a transonic wing shock wave?
24 - The stalling speed in IAS will change according to the following factors:
25 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
26 - One disadvantage of a simple unmodified swept-back wing is its stall tendency. As the stall develops:
27 - On a transport aeroplane fitted with a conventional high-speed lockout for its low-speed outboard ailerons, inhibition is normally associated with:
28 - The formula for the Mach Number is: (a= speed of sound)
29 - In steady level flight (weight, altitude and configuration constant), an increase of dynamic pressure has the following effect on the total drag of an aeroplane:
30 - Compared with flight out of ground effect, when a wing enters ground effect at unchanged angle of attack, true airspeed and air density:
31 - The high lift device shown in the figure is a:
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32 - A high aspect ratio wing produces:
33 - Which statement correctly describes a mass-distribution measure used in the design against wing bending-torsion flutter?
34 - 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:
35 - The polar curve of an aerofoil is a graphic relation between:
36 - The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
37 - Under CS 25.345(a)(1), which positive manoeuvring limit load factor is used for the high-lift-device design condition at the relevant design flap speed and flap position?
38 - Which of the following statements about a Mach trimmer is correct?
39 - The angle of attack of a two dimensional wing section is the angle between:
40 - During a climb at a constant IAS, the Mach Number:
41 - For a conventional aeroplane with reversible elevator controls and natural aerodynamic stick-force feel, which statements are correct? I. Stick force per g is independent of altitude. II. Stick force per g increases as the CG moves forward.
42 - The units of wing loading (I) W / S and (II) dynamic pressure q are:
43 - The correct drag formula is:
44 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
45 - What data may be obtained from buffet onset boundary data?
46 - A line connecting the leading edge and trailing edge midway between the upper and lower surface of an aerofoil. This definition is applicable for:
47 - When the air is passing through an expansion wave the Mach number will
48 - An automatic high-angle-of-attack slat-extension function is primarily intended to:
49 - For an intact aeroplane, a single large up-elevator input at a speed just above the applicable manoeuvring speed VA creates which structural risk?
50 - The 'short period mode' is an:
51 - Induced drag is created by the:
52 - When 'spoilers' are used as speed brakes:
53 - When a calorically perfect gas of unchanged composition passes through an isentropic expansion fan, its local speed of sound will:
54 - In the transonic range the aeroplane characteristics are strongly determined by:
55 - For steady, inviscid, incompressible flow through a horizontal stream tube, if the tube converges, static pressure (I) and velocity (II) change as follows:
56 - For the usual applicable manoeuvring-speed concept, VA is:
57 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
58 - When the air is passing through an expansion wave the static temperature will
59 - What is the SI unit of measurement for power?
60 - The high lift device shown in the figure below is a:
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61 - What increases the stalling angle of attack? Use of:
62 - For an aeroplane in trim with an adjustable horizontal stabiliser, which general statement about elevator deflection relative to the stabiliser is correct?
63 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
64 - For the conventional spin-recovery template described in FAA guidance, subject to the aircraft manufacturer’s approved procedures, which statement is correct?
65 - 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:
66 - If the nose of an aeroplane yaws left, this causes:
67 - A maximum cruise altitude chosen to preserve an adequate buffet manoeuvre margin is intended primarily to reduce which risk?
68 - A leading-edge flapper-vane stall-warning switch can be activated by a change in the location of the:
69 - In the classical comparison of untwisted wings with comparable span, area and aerofoil section at low Mach number and equal overall lift, which listed planform has the greatest root section lift coefficient?
70 - Vortex generators:
71 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
72 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
73 - When conventional plain or split trailing-edge flaps are already at a large extension, further extension generally:
74 - On a conventional cambered wing aerofoil, extending a Fowler trailing-edge flap normally produces which aerodynamic pitching-moment change, before accounting for tail compensation and whole-aircraft trim effects?
75 - For the classical comparison of the same conventional aerofoil with 1. no high-lift device, 2. only a leading-edge slat opening a slot, and 3. only a plain trailing-edge flap, place the configurations in order of increasing stall angle of attack:
76 - 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?
77 - What is the main aerodynamic mechanism by which deploying a leading-edge slat can increase CLmax?
78 - The angle of attack of a blade section is the angle between the chord line and the:
79 - A commercial jet aeroplane is performing a straight descent at a constant Mach number with constant mass. The operational speed limit that may be exceeded is:
80 - The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
81 - An aeroplane is flying through the transonic range. As the Mach Number increases the centre of pressure of the wing will move aft. This movement requires:
82 - Long period (phugoid) oscillations are characterised by:
83 - The aspect ratio of the wing:
84 - For a conventional twin-engine aeroplane with both propellers turning clockwise as viewed from the pilot’s seat, under power at positive angle of attack:
85 - 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:
86 - 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?
87 - If the control column is pushed forward, a trim tab on the elevator:
88 - For a conventional aeroplane whose tail supplies a balancing downforce and whose thrust contributes to lift or vertical support, which listed group of changes tends to increase stall speed?
89 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
90 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
91 - For a conventional, positively stable aeroplane with a fixed horizontal tail, elevator and simple elevator trim tab, after reducing speed and re-establishing trimmed straight-and-level flight at unchanged mass and configuration:
92 - 'Tuck under' may happen at:
93 - At unchanged mass and configuration, if high-altitude compressibility effects reduce CLmax, the indicated stall speed:
94 - The aeroplane drag in straight and level flight is lowest when the:
95 - 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:
96 - In steady level flight at constant IAS and unchanged aerodynamic configuration, ignoring compressibility, induced drag is directly affected by:
97 - Vortex generators mounted on the upper wing surface will
98 - A four-engine jet has identical, symmetrically placed wing-mounted engines producing equal thrust. During the take-off roll, a strong crosswind from the left produces a left-yawing weathercock moment. Considering this moment and the yawing moment from asymmetric thrust, which single engine failure above V1 gives the greatest combined left-yawing tendency?
99 - At unchanged mass and configuration, how can indicated stall speed vary with altitude, if compressibility becomes significant at high altitude?
100 - The effect of a positive wing sweep on static directional stability is as follows:
101 - Static lateral stability that is weak relative to static directional stability tends to be undesirable because:
102 - The boundary layer of a wing is:
103 - Fully extending conventional plain or split trailing-edge flaps normally has which effect on the best power-off glide performance?
104 - Assume a manoeuvring speed in EAS defined by VA = VS√n, with configuration, CLmax and limiting load factor n unchanged. By what percentage does this speed change if mass decreases by 19%?
105 - An aeroplane descends from FL350 at a constant Mach number in ISA conditions, remaining below the tropopause. What happens to its true airspeed?
106 - For steady inviscid incompressible flow along a horizontal streamline, Bernoulli’s equation states: (ρ is the local constant fluid density, V is local flow speed, pstat is static pressure, pdyn is dynamic pressure and ptot is total pressure)
107 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
108 - Where a powered-control system uses aerodynamic tab assistance for manual reversion after hydraulic failure, which listed tab type performs that function?
109 - The bank angle in a rate-one turn depends on:
110 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
111 - Examples of aerodynamic balancing of control surfaces are:
112 - Increase of wing loading will:
113 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
114 - Rotation about the lateral axis is called:
115 - For dry air of fixed composition in the ideal-gas approximation, the local speed of sound depends on:
116 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
117 - 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:
118 - How will the density and static temperature change in a supersonic flow from a position in front of a shock wave to behind it?
119 - For a conventional straight-wing aeroplane designed to have a natural nose-down stall characteristic within its approved CG range, which statement is correct?
120 - In a twin engine jet aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero?
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