Test 120 exam questions on Performance for ATPL - Airline Transport Pilot license

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1 - Which of the following is true according to regulations for turbo propeller powered aeroplanes not performing a steep approach? Maximum Landing Distance at destination is 0,95 x LDA (Landing Distance Available). Maximum use of clearway is 1,5 x runway. Maximum Landing Distance at the destination aerodrome and at any alternate aerodrome is 0,7 x LDA (Landing Distance Available). Maximum Take-off Run is 0,5 x runway.

2 - The lowest point of the thrust required curve of a jet aeroplane is the point for: Maximum specific range Minimum drag Minimum specific range Minimum endurance

3 - According to CS 25 the landing reference speed VREF may not be less than: 1.23 VSRO and must be maintained down to 50' height 1.2 VMCA 1.23 VSRO for turbojet powered and 1.3 for turboprop powered aeroplanes VSRO and must be maintained down to 35' height

4 - For a jet aeroplane, the maximum climb angle is achieved at a speed corresponding to: 1.2 Vs The maximum CL/CD2 ratio 1.1 Vs The maximum CL/CD ratio

5 - 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? 2243 m 2096 m 2009 m 1950 m

6 - Which of the following statements is applicable to the acceleration height at the beginning of the 3rd climb segment? There is no requirement for minimum climb performance when flying at the acceleration height The minimum legally allowed acceleration height is at 1500' The minimum one engine out acceleration height must be maintained in case of all engines operating The maximum acceleration height depends on the maximum time take-off thrust may be applied

7 - 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 ftQNH: 1013 hPaLanding mass: 50 000 kgFlaps: as required for minimum landing distance Runway condition: dryWind:Maximum allowable tailwind: 15 kt Maximum allowable headwind: 50 kt

3100 m. 2900 m. 2700 m. 2600 m.

8 - Refer to CAP698 Section 3 - MEP1 Figure 3.1 Normal Procedure Given:OAT 24 °CPressure Altitude: 3000' RWY, 12LWind· 080/12 KTTake-off Mass: 3800 lbsOther conditions as associated in the header of the graph. What is the take-off distance over a 50 ft obstacle?

1950 ft 1420 ft 1600 ft 1700 ft

9 - Reduced take-off thrust should normally not be used when: The runway is wet It is dark The OAT is ISA +10°C Anti-skid is not usable

10 - 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) The drag decreases The drag increases considerably The drag increases initially and decreases thereafter The drag remains almost constant

11 - With an true airspeed of 194 KT and a vertical speed of 1000 fpm, the climb gradient is about: 5° 3% 8% 3°

12 - If the aircraft mass, in a horizontal unaccelerated flight, decreases: The minimum drag increases and the IAS for minimum drag increases The minimum drag increases and the IAS for minimum drag decreases The minimum drag decreases and the IAS for minimum drag increases The minimum drag decreases and the IAS for minimum drag decreases

13 - 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: 115 KT 125 KT 123 KT 120 KT

14 - Under which condition should you fly considerably lower (4 000 ft or more) than the optimum altitude ? If the maximum altitude is below the optimum altitude. If at the lower altitude either considerably less headwind or considerably more tailwind can be expected. If at the lower altitude either more headwind or less tailwind can be expected. If the temperature is lower at the low altitude (high altitude inversion).

15 - An aircraft has two certified landing flaps positions, 25° and 35°. If a pilot chooses 35° instead of 25°, the aircraft will have: A reduced landing distance and better go-around performance A reduced landing distance and degraded go-around performance An increased landing distance and better go-around performance An increased landing distance and degraded go-around performance

16 - According to PART-CAT, which one of the following statements concerning the landing distance for a turbojet aeroplane is correct? When determining the maximum allowable landing mass at destination, 60% of the available landing runway length should be taken into account. The landing distance is the distance from 35 ft above the surface of the runway to the full stop. Malfunctioning of an anti-skid system has no effect on the required runway length. Reverse thrust is one of the factors always taken into account when determining the landing distance required.

17 - With regard to an unaccelerated horizontal flight, which of the following statements is correct?(no compressibility effects) The minimum drag is proportional to the aircraft mass The minimum drag is independent of the aircraft mass The minimum drag is a function of the density altitude The minimum drag is a function of the pressure altitude

18 - The 'climb gradient' is defined as the ratio of: The increase of altitude to horizontal air distance expressed as a percentage Rate of climb to true airspeed True airspeed to rate of climb The increase of altitude to distance over ground expressed as a percentage

19 - What is the minimum field length required for the worst wind situation, landing a twin jet aeroplane with the anti-skid inoperative?Elevation: 2000 ftQNH: 1013 hPaLanding mass: 50 000 kgFlaps: as required for minimum landing distance Runway condition: dryWind:Maximum allowable tailwind: 15 kt Maximum allowable headwind: 50 kt 2600 m. 3100 m. 2900 m. 2700 m.[see Annex]

20 - Which combination of circumstances or conditions would most likely lead to a tyre speed limited take-off? A high runway elevation and tail wind A low runway elevation and a head wind A high runway elevation and a head wind A low runway elevation and a cross wind

21 - The best rate of climb at a constant gross mass: Increases with increasing altitude due to the higher true airspeed Increases with increasing altitude since the drag decreases due to the lower air density Is independent of altitude Decreases with increasing altitude since the thrust available decreases due to the lower air density

22 - The stopway is an area which allows an increase only in the: Accelerate-stop distance available Landing distance available Take-off distance available Take-off run available

23 - Regarding the obstacle limited take-off mass, which of the following statements is correct? Wind speed plays no role when calculating this particular mass A take-off in the direction of an obstacle is also permitted in tail wind condition The maximum bank angle which can be used is 10° The obstacle limited mass can never be lower than the climb limited take-off mass

24 - The following parameters affect the take off ground run: 1 decreasing take off mass2 increasing take off mass 3 increasing density4 decreasing density5 increasing flap setting 6 decreasing flap setting7 increasing pressure altitude 8 decreasing pressure altitudeWhich parameters will decrease the take off ground run? 2, 4, 5 and 7 1, 4, 6 and 8 2, 3, 6 and 7 1, 3, 5 and 8

25 - What is the equation for the climb gradient expressed in percentage during unaccelerated flight (applicable to small angles only)? Climb Gradient = ((Thrust - Drag) / Weight) x 100 Climb Gradient = (Lift / Weight) x 100 Climb Gradient = ((Thrust - Mass) / Lift) x 100 Climb Gradient = ((Thrust + Drag) / Lift) x 100

26 - Refer to CAP698 Section 3 - MEP1 Figure 3.1 Normal Procedure Given:OAT 24 °CPressure Altitude: 3000 ft RWY 30RWind· 060/04 KTTake-off Mass: 3800 lbsOther conditions as associated in the header of the graph. What is the Ground Roll Distance under the conditions given?

1670 ft 2000 ft 1780 ft 2150 ft

27 - A higher outside air temperature (OAT): Increases the climb limited take-off mass Increases the field length limited take-off mass Decreases the take-off distance Decreases the brake energy limited take-off mass

28 - Which statement concerning the inclusion of a clearway in take-off calculation is correct? The field length limited take-off mass will increase V1 remains constant V1 is increased The usable length of the clearway is not limited

29 - Any acceleration in climb, with a constant power setting: Improves the rate of climb if the airspeed is below VY Improves the climb gradient if the airspeed is below VX Decreases rate of climb and increases angle of climb Decreases the rate of climb and the angle of climb

30 - Which of the following statements with regard to the actual acceleration height at the beginning of the 3rd climb segment is correct? A lower height than 400 ft is allowed in special circumstances e.g. noise abatement The minimum value according to regulations is 1000' The minimum value according to regulations is 400' There is no legal minimum value, because this will be determined from case to case during the calculation of the net flight path

31 - The rate of climb: Is angle of climb times true airspeed Is the downhill component of the true airspeed Is the horizontal component of the true airspeed Is approximately climb gradient times true airspeed divided by 100

32 - The approach climb requirement has been established so that the aeroplane will achieve: Manoeuvrability in the event of landing with one engine inoperative. Minimum climb gradient in the event of a go-around with one engine inoperative. Obstacle clearance in the approach area. Manoeuvrability during approach with full flaps and gear down, all engines operating.

33 - The point at which a tangent out of the origin touches the power required curve Is the point where Drag coefficient is a minimum. Is the point where the Lift to Drag ratio is a minimum. Is the point where the Lift to Drag ratio is a maximum. Is the maximum drag speed.

34 - 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: 4.7 % 4.3 % 4.9 %

35 - Which of the following provides maximum obstacle clearance during climb? 1.2Vs The speed for maximum climb angle Vx The speed, at which the flaps may be selected one position further UP The speed for maximum rate of climb

36 - Long range cruise is a flight procedure which gives: A specific range which is approximately 99% of maximum specific range and a higher cruise speed A specific range which is approximately 99% of maximum specific range and a lower cruise speed An IAS which is 1% higher than the IAS for maximum specific range A 1% higher TAS for maximum specific range

37 - Long range cruise is selected as The climbing cruise with one or two engines inoperative. The speed for best economy. Specific range with tailwind. The higher speed to achieve 99% of maximum specific range in zero wind.

38 - When determining the maximum landing mass of an turbojet powered aeroplane during the planning phase what factor must be used on the landing distance available (dry runway) 115/100 1.67 0.60 60/115

39 - The force exactly opposing and balance lift in a glide descent is: Thrust x sin(angle of descent) Weight x sin(angle of descent) Weight x cos(angle of descent) Thrust x cos(angle of descent)

40 - With regard to the drift down performance of the twin jet aeroplane, what is meant by 'equivalent gross weight at engine failure'? The increment represents fuel used before engine failure The equivalent gross weight at engine failure is the actual gross weight corrected for OAT higher than ISA +10°C The increment accounts for the higher fuel flow at higher temperatures This gross weight accounts for the lower Mach number at higher temperatures[see Annex]

41 - Which of the alternatives represents the correct relationship? V2 and V1 should not exceed VMCA VMCG and V1 should not exceed VR V2 and V1 should not exceed VMCG VMCL and V1 should not exceed VR

42 - With all engines out, a pilot wants to fly for maximum time. Therefore he has to fly the speed corresponding to: The minimum power required The maximum lift The minimum angle of descent The critical Mach number

43 - Which of the following statements, concerning the obstacle limited take-off mass for performance class A aeroplane, is correct? It should be calculated in such a way that there is a margin of 50 ft with respect to the 'net take off flight path' It should not be corrected for 30° bank turns in the take-off path It cannot be lower than the corresponding climb limited take-off mass It should be determined on the basis of a 35 ft obstacle clearance with the respect to the 'net take- off flight path'

44 - The net flight path gradient after take-off compared to the actual climb gradient is: Smaller Depends on type of aircraft and may be smaller or larger respectively Equal Larger

45 - During take-off the third segment begins: When landing gear is fully retracted When acceleration to flap retraction speed is started When flap retraction is completed When acceleration starts from VLOF to V2

46 - The maximum rate of climb that can be maintained at the absolute ceiling is: 0 fpm 100 fpm 500 fpm 125 fpm

47 - Which of the following are to be taken into account for the runway in use for take-off? Airport elevation, runway slope, standard temperature, pressure altitude and wind components Airport elevation, runway slope, standard temperature, standard pressure and wind components Airport elevation, runway slope, outside air temperature, standard pressure and wind components Airport elevation, runway slope, outside air temperature, pressure altitude and wind components

48 - The intersections of the thrust available and the drag curve are the operating points of the aeroplane In accelerated level flight. In descent with constant IAS. In unaccelerated climb. In unaccelerated level flight.

49 - The danger associated with low speed and/or high speed buffet Can be reduced by increasing the load factor. Limits the manoeuvring load factor at high altitudes. Has to be considered at take-off and landing. Exists only above MMO.

50 - To minimize the risk of hydroplaning during landing the pilot should: Use maximum reverse thrust, and should start braking below the hydroplaning speed. Use normal landing-, braking- and reverse technique. Make a 'positive' landing and apply maximum reverse thrust and brakes as quickly as possible. Postpone the landing until the risk of hydroplaning no longer exists.

51 - Which statement about reduced thrust is correct? Reduced thrust is primarily a noise abatement procedure Reduced thrust can be used when the actual take-off mass is less than the field length limited take-off mass In case of reduced thrust V1 should be decreased Reduced thrust is used in order to save fuel

52 - If there is a tail wind, the climb limited TOM will: Not be affected Increase in the flaps extended case Decrease Increase

53 - Which of the following three speeds of a jet aeroplane are basically identical? The speeds for: Maximum drag, maximum endurance and maximum climb angle Maximum range, minimum drag and minimum glide angle Holding, maximum climb angle and minimum glide angle Maximum climb angle, minimum glide angle and maximum range

54 - If a flight is performed with a higher 'Cost Index' at a given mass which of the following will occur? A lower cruise Mach number. An increased maximum range. A higher cruise Mach number. An increased long range performance.

55 - Which statement, in relation to the climb limited takeoff mass of a jet aeroplane, is correct? The climb limited takeoff mass is determined at the speed for best rate of climb The climb limited takeoff mass decreases with increasing OAT On high elevation airports equipped with long runways the aeroplane will always be climb limited 50% of a head wind is taken into account when determining the climb limited takeoff mass

56 - Is there any difference between the vertical speed versus forward speed curves for two identical aeroplanes having different masses ? (assume zero thrust and wind) Yes, the difference is that the heavier aeroplane will always glide a greater distance. No difference. Yes, the difference is that the lighter aeroplane will always glide a greater distance. Yes, the difference is that for a given angle of attack both the vertical and forward speeds of the heavier aeroplane will be larger.

57 - If the climb speed schedule is changed from 280/.74 to 290/.74 the new crossover altitude will be: Higher Lower Only affected by the aeroplane gross mass Unchanged

58 - Other factors remaining constant, how does increasing altitude affect Vx and Vy in terms of TAS? Both will remain the same Both will decrease Both will increase Vx will decrease and Vy will increase

59 - In a given configuration the endurance of a piston engine aeroplane only depends on: Altitude, speed, mass and fuel on board. Speed, mass and fuel on board. Speed and mass. Altitude, speed and mass.

60 - If the take-off mass of an aeroplane is brake energy limited a higher uphill slope would: Decrease the maximum mass for take-off Increase the maximum mass for take-off Decrease the required take-off distance Have no effect on the maximum mass for take-off

61 - The speed V2 is defined for jet aeroplane as: Take-off decision speed Lift off speed Critical engine failure speed Take-off climb speed or speed at 35'

62 - Density altitude is the: Altitude read directly from the altimeter Altitude reference to the standard datum plane Height above the surface Pressure altitude corrected for 'non standard' temperature

63 - The speed for maximum endurance Is the lower speed to achieve 99% of maximum specific range. Can either be higher or lower than the speed for maximum specific range. Is always lower than the speed for maximum specific range. Is always higher than the speed for maximum specific range.

64 - In the event of engine failure below V1, the first action to be taken by the pilot in order to decelerate the aeroplane is to: Apply wheel brakes Reverse engine thrust Deploy airbrakes or spoilers Reduce the engine thrust

65 - Given that the characteristics of a three engine turbojet aeroplane are as follows:Thrust = 50000 Newton / Engine g = 10 m/s2Drag = 72569 NMinimum steady gradient of climb (2nd segment) = 2.7% SIN (Angle of climb) = (Thrust - Drag) / WeightThe maximum take-off mass under 2nd segment conditions with 1 engine out is: 101596 kg 209064 kg 74064 kg 286781 kg

66 - If the take-off mass of an aeroplane is tyre speed limited, downhill slope would: Have no effect on the maximum mass for take-off Increase the required take-off distance Increase the maximum mass for take-off Decrease the maximum mass for take-off

67 - Maximum Tyre Speed can limit the Lift-off Speed.Which kind of speed can be directly used to determine this limitation? Groundspeed EAS TAS IAS

68 - Which take-off speed is affected by the presence or absence of stopway and / or clearway? V1 VMCA VMCG V2

69 - According to PART-CAT, for turbo-prop aeroplanes, the required runway length at a destination airport is: Less then that required at an alternate airport. More than that required at an alternate airport. The same as that required at an alternate airport. 60% greater than that required at an alternate airport

70 - The speed V1 is defined as: Take-off climb speed Speed for best angle of climb Take-off decision speed Engine failure speed

71 - The speed for maximum lift/drag ratio will result in: The maximum endurance for a propeller driven aeroplane The maximum range for a jet aeroplane The maximum angle of climb for a propeller driven aeroplane The maximum range for a propeller driven aeroplane

72 - On a reciprocating engine aeroplane, to maintain a given angle of attack, configuration and altitude at higher gross mass: The airspeed will be decreased and the drag increased The airspeed and the drag will be increased The airspeed will be increased but the drag does not change The lift / drag ratio must be increased

73 - The landing field length required for jet aeroplanes at the alternate (wet condition) is the demonstrated landing distance plus 92% 67% 70% 43%

74 - 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: 100 m 115 m It will not clear the obstacle 85 m

75 - Considering TAS for maximum range and maximum endurance, other factors remaining constant: Both will stay constant regardless of altitude Both will decrease with increasing altitude TAS for maximum range will increase with increased altitude while TAS for maximum endurance will decrease with increased altitude Both will increase with increasing altitude

76 - Considering VR, which statement is correct? VR is the lowest climb speed after engine failure In case of engine failure below VR the take-off should be aborted VR is the speed at which rotation should be initiated VR is the lowest speed for directional control in case of engine failure

77 - At the destination aerodrome the landing distance available is 3000 m. The appropriate weather forecast indicates that the runway at the estimated time of arrival will be wet. For a commercial flight the mass of a turbojet aeroplane at landing must be such that the aeroplane can be landed within: 2609 m 1800 m 2 070 m 1565 m

78 - During a glide at constant Mach number, the pitch angle of the aeroplane will: Increase Increase at first and decrease later on Decrease Remain constant

79 - If other factors are unchanged, the fuel mileage (nautical miles per kg) is: Independent from the centre of gravity position Lower with an aft centre of gravity position Lower with a forward centre of gravity position Higher with a forward centre of gravity position

80 - In which of the following distances can the length of a stopway be included? In the one-engine failure case, take-off distance In the accelerate stop distance available In the take-off run available In the all-engine take-off distance

81 - The drift down requirements are based on: The obstacle clearance during a descent to the new cruising altitude if an engine has failed The landing mass limit at the alternate The maximum flight path gradient during the descent The actual engine thrust output at the altitude of engine failure

82 - The take-off distance available is: The runway length plus half of the clearway The runway length minus stopway The total runway length, without clearway even if this one exists The length of the take-off run available plus the length of the clearway available

83 - 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: 3259 kg/h 3426 kg/h 3602 kg/h 3787 kg/h

84 - The optimum cruise altitude increases If the temperature (OAT) is increased. If the tailwind component is decreased. If the aeroplane mass is decreased. If the aeroplane mass is increased.

85 - On a reciprocating engine aeroplane, with increasing altitude at constant gross mass, angle of attack and configuration the power required: Decreases slightly because of the lower air density Increases but TAS remains constant Remains unchanged but the TAS increases Increases and the TAS increases by the same percentage

86 - Below the optimum cruise altitude: The IAS for long range cruise increases continuously with decreasing altitude The TAS for long range cruise increases continuously with decreasing altitude The Mach number for long range cruise decreases continuously with decreasing altitude The Mach number for long range cruise increases continuously with decreasing altitude

87 - Which of the following factors will lead to an increase of ground distance during a glide, while maintaining the appropriate minimum glide angle speed? Increase of aircraft mass Decrease of aircraft mass Tailwind Headwind

88 - 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/s 2) 27%. 1.286%. 7.86%. 12.86%.

89 - What is the effect of tail wind on the time to climb to a given altitude? The time to climb increases The time to climb decreases The time to climb does not change The effect on the time to climb will depend on the helicopter type

90 - The angle of climb with flaps extended, compared to that with flaps retracted, will normally be: Larger Smaller Increase at moderate flap setting, decrease at large flap setting Not change

91 - In case of an engine failure which is recognized at or above V1: A height of 50 ft must be reached within the take-off distance The take-off must be rejected if the speed is still below VLOF The take-off should be rejected if the speed is still below VR The take-off must be continued

92 - Density Altitude: Is equal to the pressure altitude Is used to establish minimum clearance of 2000' over mountains Is used to determine the aeroplane performance Is used to calculate the FL above the Transition Altitude

93 - In relation to the net take-off flight path, the required 35 ft vertical distance to clear all obstacles is: Based on pressure altitudes The minimum vertical distance between the lowest part of the aeroplane and all obstacles within the obstacle domain The height at which power is reduced to maximum climb thrust The height by which acceleration and flap retraction should be completed

94 - 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? The climb limited take-off mass would increase The effect would vary depending upon the height of any obstacle within the net take-off flight path The climb limited take-off mass would decrease None

95 - At reference or use or Performance Manual MEP 1 Figure 3.2 Given:OAT: 25°CPressure Altitude: 3000 ft RWY: 24LWind: 310°/20ktsTake off Mass: 4400 lbs Heavy Duty Brakes installed.Other conditions as associated in the header of the graph.What is the Accelerate and Stop Distance under the conditions given? 3750 ft 3350 ft 4000 ft 4300 ft

96 - A lower airspeed at constant mass and altitude requires: Less thrust and a lower coefficient of lift A higher coefficient of lift More thrust and a lower coefficient of drag More thrust and a lower coefficient of lift

97 - Complete the following statement regarding the take-off performance of an aeroplane in performance class Following an engine failure at (i) ........... and allowing for a reactiontime of (ii) ........... a correctly loaded aircraft must be capable of decelerating to a halt withinthe (iii) ......... (i) V2 (ii) 3 seconds (iii) Take-off distance available (i) V1 (ii) 2 seconds (iii) Accelerate - stop distance available (i) V1 (ii) 2 seconds (iii) Take-off distance available (i) V1 (ii) 1 second (iii) Accelerate - stop distance available

98 - 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. Increases in the first part is constant in the second. Is constant in the first part Decreases in the second.

99 - Which of the following combinations adversely affects take-off and initial climb performance? High temperature and high relative humidity Low temperature and low relative humidity High temperature and low relative humidity Low temperature and high relative humidity

100 - Which of the following sets of factors will increase the climb-limited TOM (every factor considered independently)? Low flap setting, low pressure altitude, low OAT Low flap setting, high pressure altitude, low OAT Low flap setting, high pressure altitude, high OAT High flap setting, low pressure altitude, low OAT

101 - If the thrust available exceeds the thrust required for level flight The aeroplane descends if the airspeed is maintained. The aeroplane accelerates if the altitude is maintained. The aeroplane decelerates if the altitude is maintained. The aeroplane decelerates if it is in the region of reversed command.

102 - During the flight preparation the climb limited take-off mass (TOM) is found to be much greater than the field length limited TOM using 5° flap. In what way can the performance limited TOM be increased? There are no limiting obstacles. By selecting a higher V2 By selecting a lower V2 By selecting a higher flap setting By selecting a lower flap setting

103 - With zero wind, the angle of attack for maximum range for an aeroplane with turbojet engines is: Lower than the angle of attack corresponding to maximum endurance Equal to the angle of attack corresponding to maximum lift to drag ratio Equal to the angle of attack corresponding to zero induced drag Equal to the angle of attack corresponding to maximum endurance

104 - The climb limited take-off mass can be increased by: Selecting a lower V2 Selecting a lower V1 Selecting a lower VR A lower flap setting for take-off and selecting a higher V2

105 - The tangent from the origin to the power required against true airspeed curve, for a jet aeroplane, determines the speed for: Maximum endurance Critical angle of attack Maximum specific range Minimum power

106 - A climb gradient required is 3.3%. For an aircraft maintaining 100 KT true airspeed, no wind, this climb gradient corresponds to a rate of climb of approximately: 3 300 fpm 330 fpm 33.0 m/s 3.30 m/s

107 - The optimum altitude: Decreases as mass decreases Increases as mass decreases and is the altitude at which the specific range reaches its maximum Is the altitude up to which cabin pressure of 8 000 ft can be maintained Is the altitude at which the specific range reaches its minimum

108 - The minimum climb gradient required on the 2nd flight path segment after the take-off of a jet aeroplane is defined by the following parameters:1 Gear up2 Gear down3 Wing flaps retracted4 Wing flaps in take-off position 5 N engines at the take-off thrust6 (N- 1) engines at the take-off thrust7 Speed over the path equal to V2 + 10 kt 8 Speed over the path equal to 1.3 VS9 Speed over the path equal to V210 At a height of 35 ft above the runway The correct statements are: 1, 4, 5, 10 2, 3, 6, 9 1, 5, 8, 10 1, 4, 6, 9

109 - The use of reduced take-off thrust is permitted, only if: The actual take-off mass (TOM) including a margin is greater than the performance limited TOM The take-off distance available is lower than the take-off distance required one engine out at V1 The actual take-off mass (TOM) is greater than the climb limited TOM The actual take-off mass (TOM) is lower than the field length limited TOM

110 - Considering a rate of climb diagram (ROC versus TAS) for an aeroplane. Which of the diagrams shows the correct curves for 'flaps down' compared to 'clean' configuration?

B C A D

111 - As long as an aeroplane is in a positive climb: VX may be greater or less than VY depending on altitude VX is always below VY VY is always above VMO VX is always above VY

112 - An aircraft has two certified landing flaps positions, 25° and 35°. If a pilot chooses 25° instead of 35°, the aircraft will have: A reduced landing distance and better go-around performance An increased landing distance and better go-around performance A reduced landing distance and degraded go-around performance An increased landing distance and degraded go-around performance

113 - Can the length of a stopway be added to the runway length to determine the takeoff distance available? Yes, but the stopway must be able to carry the weight of the aeroplane No, unless its centreline is on the extended centreline of the runway Yes, but the stopway must have the same width as the runway No

114 - 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 V12555 m with all engines operating and all other things being equal The take-off distance adopted for the certification file is: 3513 m 3050 m 2938 m 2555 m

115 - Which statement with respect to the step climb is correct? Executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1 A step climb is executed in principle when, just after levelling off, the 1.3g altitude is reached A step climb is executed because ATC desires a higher altitude A step climb must be executed immediately after the aeroplane has exceeded the optimum altitude

116 - What is the effect of increased mass on the performance of a gliding aeroplane? There is no effect The gliding angle decreases The speed for best angle of descent increases The lift / drag ratio decreases

117 - At reference or use Performance Manual MEP 1 Figure 3.2 Given:OAT: -10°CPressure Altitude: 4000' RWY: 30LWind: 180°/10 KTTake off Mass: 4600 lbs Heavy Duty Brakes installedOther conditions as associated in the header of the graph.What is the Accelerate and Stop Distance under the conditions given?

4250 ft 3550 ft 3800 ft 4600 ft

118 - What is the result of a large take off flap setting compared to a small take off flap setting on required Take-off Distance (TOD) and the field length limited Take-off Mass (TOM)? Increased TOD required and decreased field length limited TOM Decreased TOD required and increased field length limited TOM Decreased TOD required and decreased field length limited TOM Increased TOD required and increased field length limited TOM

119 - A headwind component increasing with altitude, as compared to zero wind condition, (assuming IAS is constant): Does not have any effect on the angle of flight path during climb Has no effect on rate of climb Decreases angle and rate of climb Improves angle and rate of climb

120 - A jet aeroplane equipped with old engines has a specific fuel consumption of 0.06 kg per Newton of thrust and per hour and, in a given flying condition, a fuel consumption of 14 kg per NM. In the same flying conditions, the same aeroplane equipped with modern engines with a specific fuel consumption of 0.035 kg per Newton of thrust and per hour, has a fuel consumption per NM of: 11.7 kg / NM 14 kg / NM 10.7 kg / NM 8.17 kg / NM

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