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Exam simulation Performance - ATPL - Airline Transport Pilot license

Exam simulation ATPL Performance 120 questions on 120 minutes

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1 - The 'maximum tyre speed' limits:
2 - Which of the following statements, concerning the obstacle limited take-off mass for performance class A aeroplane, is correct?
3 - During climb to the cruising level, a headwind component:
4 - A higher outside air temperature (OAT):
5 - Which of the following is true according to regulations for turbo propeller powered aeroplanes not performing a steep approach?
6 - The determination of the maximum mass on brake release, of a certified turbojet aeroplane with 5°, 15° and 25° flap angles on take-off, leads to the following values: Flap angle: 5° 15° 25°; Runway limitation (kg): 66000 69500 71500; 2nd segment climb limitation: 72200 69000 61800; Wind correction: Headwind: +120 kg / KT Tailwind: -360 kg / KT; Given that the tailwind component is equal to 5 KT, the maximum mass on brake release and corresponding flap angle will be:
7 - Which of the following represents the minimum for V1?
8 - The approach climb requirement has been established to ensure:
9 - Why are 'step climbs' used on long distance flights?
10 - Which statement concerning the inclusion of a clearway in take-off calculation is correct?
11 - An aircraft has two certified landing flaps positions, 25° and 35°. If a pilot chooses 35° instead of 25°, the aircraft will have:
12 - An aeroplane carries out a descent from FL 410 to FL 270 at cruise Mach number, and from FL 270 to FL 100 at the IAS reached at FL 270. How does the angle of descent change in the first and in the second part of the descent? Assume idle thrust and clean configuration and ignore compressibility effects.
13 - Complete the following statement regarding the take-off performance of an aeroplane in performance class A. Following an engine failure at (i)........... and allowing for a reaction time of (ii)........... a correctly loaded aircraft must be capable of decelerating to a halt within the (iii).........
14 - According to CS-25 the landing reference speed VREF may not be less than:
15 - With regard to an unaccelerated horizontal flight, which of the following statements is correct? (no compressibility effects)
16 - A four jet-engine aeroplane (mass = 150 000 kg) is established on climb with all engines operating. The lift-to-drag ratio is 14. Each engine has a thrust of 75 000 Newton. The gradient of climb is: (given: g = 10 m/s²)
17 - Field length is balanced when:
18 - During certification flight testing on a four engine turbojet aeroplane the actual take-off distances measured are: -3050 m with failure of the critical engine recognised at V1; -2555 m with all engines operating and all other things being equal. The take-off distance adopted for the certification file is:
19 - The centre of gravity near, but still within, the aft limit:
20 - Considering TAS for maximum range and maximum endurance, other factors remaining constant:
21 - The optimum long-range cruise altitude for a turbojet aeroplane:
22 - An increase in atmospheric pressure has, among other things, the following consequences on take-off performance:
23 - The landing field length required for jet aeroplanes at the alternate (wet condition) is the demonstrated landing distance plus
24 - Other factors remaining constant, how does increasing altitude affect Vx and Vy in terms of TAS?
25 - The use of reduced take-off thrust is permitted, only if:
26 - Under which condition should you fly considerably lower (4 000 ft or more) than the optimum altitude?
27 - Density altitude is the:
28 - Is there any difference between the vertical speed versus forward speed curves for two identical aeroplanes having different masses? (assume zero thrust and wind)
29 - The following parameters affect the take-off ground run: 1. decreasing take-off mass 2. increasing take-off mass 3. increasing density 4. decreasing density 5. increasing flap setting 6. decreasing flap setting 7. increasing pressure altitude 8. decreasing pressure altitude. Which parameters will decrease the take-off ground run?
30 - A lower airspeed at constant mass and altitude requires:
31 - The landing field length required for turbojet aeroplanes at the destination (wet condition) is the demonstrated landing distance plus:
32 - The landing reference speed VREF has, in accordance with CS-25, the following margins above reference stall speed in landing configuration:
33 - Following a take-off determined by the 50' (15 m) screen height, a light twin climbs on a 10% over-the-ground climb gradient. It will clear a 900 m high obstacle in relation to the runway (horizontally), situated at 10000 m from the 50' clearing point with an obstacle clearance of:
34 - The rate of climb:
35 - Which of the following combinations adversely affects take-off and initial climb performance?
36 - A jet aeroplane is climbing with constant IAS. Which operational speed limit is most likely to be reached?
37 - Below the optimum cruise altitude:
38 - A headwind component increasing with altitude, as compared to zero wind condition, (assuming IAS is constant):
39 - Which data can be extracted from buffet onset boundary data?
40 - For a jet transport aeroplane, which of the following is the reason for the use of 'maximum range speed'?
41 - The speed V1 is defined as:
42 - Any acceleration in climb, with a constant power setting:
43 - The angle of climb with flaps extended, compared to that with flaps retracted, will normally be:
44 - Can the length of a stopway be added to the runway length to determine the take-off distance available?
45 - When compared to still air conditions, a constant headwind component:
46 - A headwind will:
47 - A runway is contaminated by a 0.5 cm layer of wet snow. The take-off is nevertheless authorized by a light-twin's flight manual. The take-off distance in relation to a dry runway will be:
48 - Regarding take-off performance limitations, which of the following statements is correct?
49 - V1 has to be:
50 - What happens to the drag of a jet aeroplane if, during the initial climb after take-off, constant IAS is maintained? (Assume a constant mass)
51 - According to PART-CAT, which one of the following statements concerning the landing distance for a turbojet aeroplane is correct?
52 - If the take-off mass of an aeroplane is brake energy limited a higher uphill slope would:
53 - The pilot of a single engine aircraft has established the climb performance. The carriage of an additional passenger will cause the climb performance to be:
54 - The climb gradient of an aircraft after take-off is 6% in standard atmosphere, no wind, at 0' pressure altitude. Using the following corrections: '± 0.2 % / 1000' field elevation'; '± 0.1 % / °C from standard temperature' '- 1 % with wing anti-ice'; '- 0.5% with engine anti-ice'. The climb gradient after take-off from an airport situated at 1000', 17°C; QNH 1013.25 hPa, with wing and engine anti-ice operating for a functional check is:
55 - Considering VR, which statement is correct?
56 - Which statement about reduced thrust is correct?
57 - A 'Balanced Field Length' is said to exist where:
58 - Density Altitude:
59 - The optimum cruise altitude increases
60 - In accordance to CS-25 which of the following listed speeds are used for determination of V2min:
61 - The optimum altitude:
62 - If the aircraft mass, in a horizontal unaccelerated flight, decreases:
63 - The stopway is an area which allows an increase only in the:
64 - Which of the following will decrease V1?
65 - Which is the correct sequence of speeds during take-off?
66 - The 'climb gradient' is defined as the ratio of:
67 - Which take-off speed is affected by the presence or absence of stopway and / or clearway?
68 - The approach climb requirement has been established so that the aeroplane will achieve:
69 - At a given mass, the reference stall speed of a twin engine turboprop aircraft is 100 KT in the landing configuration. The minimum speed a pilot must maintain in short final is:
70 - In twin-jet drift-down performance data, why can the curve for 35 000 kg gross mass start at approximately 4 minutes at FL 370?
71 - Long range cruise is selected as
72 - The take-off mass of an aeroplane is restricted by the climb limit. What would be the effect on this limit of an increase in the headwind component?
73 - Refer to Performance Manual MEP1 Figure 3.1 Normal Procedure Given: OAT 24 °C; Pressure Altitude: 3000 ft; RWY 30R; Wind 060/04 KT; Take-off Mass: 3800 lbs. Other conditions as associated in the header of the graph. What is the Ground Roll Distance under the conditions given?
question perf3.webp
74 - Refer to Performance Manual MEP 1 Figure 3.2. Given: OAT -10°C; pressure altitude 4 000 ft; RWY 30L; wind 180°/10 kt; take-off mass 4 600 lb; heavy-duty brakes installed. Other conditions are as stated in the graph header. What is the accelerate-stop distance under the conditions given?
question perf8.webp
75 - Maximum Tyre Speed can limit the Lift-off Speed. Which kind of speed can be directly used to determine this limitation?
76 - What is the effect of a headwind component, compared to still air, on the maximum range speed (IAS) and the speed for maximum climb angle respectively?
77 - How does the best angle of climb and best rate of climb vary with increasing altitude for an aeroplane with a normal aspirated piston engine?
78 - What is the equation for the climb gradient expressed in percentage during unaccelerated flight (applicable to small angles only)?
79 - Which of the alternatives represents the correct relationship?
80 - If accelerate-stop distance data assume take-off power is set before brake release, will the published accelerate-stop distance still be achieved if the brakes are released before take-off power is set?
81 - The point at which a tangent out of the origin touches the power required curve
82 - Consider the graphic representation of the power required versus true air speed (TAS), for a piston engine aeroplane with a given mass. When drawing the tangent from the origin, the point of contact (A) determines the speed of:
question perf6.webp
83 - An aircraft has two certified landing flaps positions, 25° and 35°. If a pilot chooses 25° instead of 35°, the aircraft will have:
84 - Long range cruise is a flight procedure which gives:
85 - What is the influence of the mass on maximum rate of climb (ROC) speed if all other parameters remain constant?
86 - On a long distance flight the gross mass decreases continuously as a consequence of the fuel consumption. The result is:
87 - What is the effect of tailwind on the time to climb to a given altitude?
88 - For a jet aeroplane, the maximum climb angle is achieved at a speed corresponding to:
89 - At reference or see Performance Manual MRJT 1 Figure 4.28. What is the minimum field length required for the worst wind situation, landing a twin jet aeroplane with the anti-skid inoperative? Elevation: 2000 ft QNH: 1013 hPa Landing mass: 50 000 kg Flaps: as required for minimum landing distance Runway condition: dry Wind: Maximum allowable tailwind: 15 kt Maximum allowable headwind: 50 kt
question perf1.webp
90 - VX is:
91 - The danger associated with low speed and/or high speed buffet
92 - The tangent from the origin to the power required against true airspeed curve, for a jet aeroplane, determines the speed for:
93 - According to PART-CAT, for turbo-prop aeroplanes, the required runway length at a destination airport is:
94 - If a flight is performed with a higher 'Cost Index' at a given mass which of the following will occur?
95 - Regarding the obstacle limited take-off mass, which of the following statements is correct?
96 - During a glide at constant Mach number, the pitch angle of the aeroplane will:
97 - Uphill slope:
98 - Which combination of circumstances or conditions would most likely lead to a tyre speed limited take-off?
99 - Which of the following factors leads to the maximum flight time of a glide?
100 - In straight horizontal steady flight, at speeds below that for minimum drag:
101 - Two identical turbojet aeroplanes (whose specific fuel consumption is assumed to be constant) are in a holding pattern at the same altitude. The mass of the first one is 95000 kg and its hourly fuel consumption is equal to 3100 kg/h. Since the mass of the second one is 105000 kg, its hourly fuel consumption is:
102 - If the climb speed schedule is changed from 280/.74 to 290/.74 the new crossover altitude will be:
103 - On a dry runway the accelerate-stop distance is increased:
104 - Which of the following are to be taken into account for the runway in use for take-off?
105 - What will be the influence on the aeroplane performance if aerodrome pressure altitude is increased?
106 - Which of the following combinations basically has an effect on the angle of descent in a glide? (Ignore compressibility effects.)
107 - During certification test flights for a turbojet aeroplane, the actual measured take-off runs from brake release to a point equidistant between the point at which VLOF is reached and the point at which the aeroplane is 35' above the take-off surface are: - 1747 m, all engines operating; - 1950 m, with the critical engine failure recognized at V1, the other factors remaining unchanged. Considering both possibilities to determine the take-off run (TOR). What is the correct distance?
108 - Take-off performance data, for the ambient conditions, show the following limitations with flap 10° selected: - runway limit: 5270 kg - obstacle limit: 4630 kg. Estimated take-off mass is 5000 kg. Considering a take-off with flaps at:
109 - The speed V2 is defined for jet aeroplane as:
110 - The net flight path gradient after take-off compared to the actual climb gradient is:
111 - A twin engine aeroplane in cruise flight with one engine inoperative has to fly over high ground. In order to maintain the highest possible altitude the pilot should choose:
112 - After engine failure the aeroplane is unable to maintain its cruising altitude. What is the procedure which should be followed?
113 - The length of a clearway may be included in:
114 - The long range cruise speed is in relation to the speed for maximum range cruise.
115 - The lowest point of the thrust required curve of a jet aeroplane is the point for:
116 - Given that the characteristics of a three engine turbojet aeroplane are as follows: Thrust = 50000 Newton / Engine. g = 10 m/s². Drag = 72569 N. Minimum steady gradient of climb (2nd segment) = 2.7%. SIN (Angle of climb) = (Thrust - Drag) / Weight. The maximum take-off mass under 2nd segment conditions with 1 engine out is:
117 - Other factors remaining constant and not limiting, how does increasing pressure altitude affect allowable take-off mass?
118 - The thrust of a jet engine at constant RPM
119 - In relation to the net take-off flight path, the required 35 ft vertical distance to clear all obstacles is:
120 - The maximum indicated air speed of a piston engine aeroplane without turbo charger, in level flight, is reached:
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