1. The stall speed or the minimum steady flight speed at which the aeroplane is controllable is: A) VS B) VS0 C) VS1
A) VS
2. The stall speed or the minimum steady flight speed in the landing configuration is: A) VS0 B) VS C) VS1
A) VS0
3. The stall speed or the minimum steady flight speed obtained in a specified configuration is: A) VS1 B) VS1G C) VS
A) VS1
4. The 1g stall speed at which the aeroplane can develop a lift force (normal to the flight path) equal to its weight is: A) VS1G B) VSR0 C) VS1
A) VS1G
5. The speed at which the pilot starts to apply back pressure to initiate rotation on take-off is: A) VR B) VSR0 C) VREF
A) VR
6. The reference stall speed in the landing configuration is: A) VSR0 B) VR C) VREF
A) VSR0
7. The reference speed of the aeroplane, in a specified landing configuration, at the point where it descends through the landing screen height in the determination of the landing distance for manual landings is: A) VREF B) VSR0 C) VR
A) VREF
8. The Performance Class B take-off flight path: A) Begins at 50 ft above the surface at the end of the TODR and ends at approximately 1500 ft above the surface. B) Begins at the point of lift-off and ends at the 50 ft screen height. C) Begins at 50 ft above the surface at the end of the TODR and ends at approximately 1000 ft above the surface. D) Begins at the start of the take-off and ends at approximately 1500 ft above the surface.
A) Begins at 50 ft above the surface at the end of the TODR and ends at approximately 1500 ft above the surface.
9. Which of the following are valid assumptions made in the regulations governing the take-off flight path for Class B aeroplanes: A) It begins at 50 ft above the surface at the end of the TODR and ends at approximately 1500 ft above the surface. B) The aircraft is not banked before it has reached a height of 50 ft above the surface. C) The angle of bank does not exceed 15° after this point. D) Failure of the critical engine occurs at the cloud base.
A) It begins at 50 ft above the surface at the end of the TODR and ends at approximately 1500 ft above the surface. B) The aircraft is not banked before it has reached a height of 50 ft above the surface. C) The angle of bank does not exceed 15° after this point. D) Failure of the critical engine occurs at the cloud base.
10. For multi-engine Class B aeroplanes, the operator must ensure that the aircraft is capable of continuing flight, at or above the relevant minimum altitudes for safe flight stated in the Operations Manual, to a point __________ft above the aerodrome.
1000
11. The operator must ensure that the aircraft, in the meteorological conditions expected for the flight, and in the event of engine failure, is capable of reaching a place at which a safe forced landing can be made. A) This requirement applies only to single-engine Class B aeroplanes. B) This requirement applies to all multi-engine Class B aeroplanes. C) This requirement applies to all Class B aeroplanes. D) This requirement applies to single-engine Class B aeroplanes taking-off in IMC.
A) This requirement applies only to single-engine Class B aeroplanes.
12. The departure sector begins at the point where the aircraft reaches __________ ft above the surface. At this point the width of the departure sector is half the aeroplane's wingspan plus __________ metres. A) 50; 60 B) 60; 50 C) 50; 50 D) 60; 60
A) 50; 60
13. A Class B aeroplane has a wingspan of 10 metres. 1000 metres from the start of the departure sector, the width of the sector is __________ metres.
190
14. The gradient of the take-off flight path from 50 ft to the engine failure height is the average all-engine gradient multiplied by a factor of __________.
0.77
15. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine the distance to a height of 50 ft, and the length of the take-off roll, given:OAT 30°CPressure altitude: 1000 ftMass 3400 lbsTailwind 10 ktFlaps at ApproachDry, asphalt runway. A) TOD 2500 ft TOR 1300 ft. B) TOD 1300 ft TOR 2500 ft. C) TOD 1800 ft TOR 900 ft. D) TOD 2750 ft TOR 145 ft.
A) TOD 2500 ft TOR 1300 ft.
16. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine the distance to a height of 50 ft given:OAT-7°CPressure altitude: 5800 ftQNH 973 hPaMass 2950 lbsHeadwind 5 ktFlaps upRunway dry. A) 1750 ft. B) 1900 ft. C) 2050 ft. D) 1000 ft.
A) 1750 ft.
17. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine the distance to a height of 50 ft given:OAT+38°CPressure altitude: 4000 ftQNH 973 hPaMass 3400 lbsTailwind 5 ktFlaps at ApproachFirm, dry grass runway. A) 3900 ft. B) 3250 ft. C) 4050 ft. D) 1700 ft.
A) 3900 ft.
18. For an SEP Aircraft.Using the data provided in CAP698 as required.Determine the ground roll distance given:OAT+40°CPressure altitude: 6000 ftQNH 973 hPaMass 3400 lbsTailwind 5 ktFlaps at ApproachDry asphalt runway. A) 2150 ft. B) 3800 ft. C) 3500 ft. D) 2000 ft.
A) 2150 ft.
19. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine the required headwind given:OAT+20°CPressure altitude: sea levelQNH 973 hPaTODA 1700 ftMass 3450 lbsFlaps approach Dry asphalt runway A) 26 kt. B) 20 ft. C) 14 ft. D) 10 ft.
A) 26 kt.
20. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine the required headwind given:OAT+30°CPressure altitude: 2000 ftTODA 1900 ftMass 3200 lbsFlaps at ApproachDry asphalt runway. A) 22 kt. B) 20 kt. C) 15 kt. D) 10 kt.
A) 22 kt.
21. For an SEP Aircraft.Using the data provided in CAP 698 as required.Determine MTOM with a TOD of 2500 ft, given:OAT+20°CPressure altitude: 4000 ftTailwind 5 ktFlaps at ApproachRunway dry asphalt. A) 3250 lb. B) 3250 kg. C) 2750 lb. D) 4000 lb.
A) 3250 lb.
22. For an SEP Aircraft.Using the data provided in CAP 698 as required.You have identified a suitable forced landing area 4 nm off route at an altitude of 2000 ft. Given the following conditions, calculate the minimum net glide height needed to make it to the forced landing site:OAT at forced landing site +30C, ISA pressure.Gross air gradient 10%.Glide speed 75 KIAS.Tailwind of 20 kt.” A) 2055 ft. B) 2550 ft. C) 1800 ft. D) 2430 ft.
A) 2055 ft.
23. For an SEP Aircraft.Using the data provided in CAP 698 as required.Calculate the obstacle clearance over an obstacle 900 ft high, 3 nm from the end of TODA given a climb gradient of 10%. A) 975 ft. B) 1825 ft. C) 1875 ft. D) 2775 ft.
A) 975 ft.
24. For an MEP Aircraft.Using the data provided in CAP698 as required.Determine the TOD for an aircraft, mass 4500 lb, flaps up, 1000 ft pressure altitude, 20°C and 10 kt headwind component. A) 1700 ft. B) 1400 ft. C) 1900 ft. D) 2000 ft.
A) 1700 ft.
25. For an MEP Aircraft.Using the data provided in CAP698 as required.Determine the ASD for an aircraft, mass 4500 lb, flaps up, 1000 ft pressure altitude, 20°C and 10 kt headwind component. A) 3450 ft. B) 3450 m. C) 3800 ft. D) 3750 ft.
A) 3450 ft.
26. For an MEP Aircraft.Using the data provided in CAP698 as required.Determine the all-engine and one engine inoperative (OEI) rate of climb for the MEP1 aeroplane given the following:Flaps UPMass 4000 lb+20°C10 kt headwind. A) 1880 fpm for the all-engine climb. B) 410 fpm for the OEI climb. C) 1400 fpm for the all-engine climb. D) 240 fpm for the OEI climb.
A) 1880 fpm for the all-engine climb. B) 410 fpm for the OEI climb.
27. For an MEP Aircraft.Using the data provided in CAP698 as required.Calculate the planned clearance above an obstacle 700 ft high, 2 nm from reference zero. The aircraft’s take-off mass is 4000 lb, flaps are UP, the aerodrome pressure altitude is 4000 ft and the temperature is +20°C. The cloud base is 500 ft and there is a 10 kt headwind. A) 186 ft. B) 386 ft. C) 786 ft. D) 586 ft.
A) 186 ft.
28. For an MEP Aircraft.Using the data provided in CAP698 as required.Determine the landing distance, and speed at screen height, for a MEP 1 commercial air transport flight given the following data:Pressure altitude 3000 ftOAT +10°CMass 4250 lb5 kt tailwind. A) 88 kt and 3260 ft. B) 89 kt and 3260 ft. C) 88 kt and 1310 ft. D) 88 kt and 1420 ft.
A) 88 kt and 3260 ft.
29. For an MEP Aircraft.Using the data provided in CAP698 as required.The landing distance for a MEP 1 private flight was calculated as 3260 ft from the following data:Pressure altitude 3000 ftOAT +10°CMass 4250 lb5 kt tailwind.If this had been a commercial flight the landing distance would be: A) 4660 ft B) 2280 ft C) 3260 ft D) 3010 ft
A) 4660 ft
30. For an MEP Aircraft.Using the data provided in CAP698 as required.What is the MTOM for a commercial flight conducting a normal take-off from a field length of 1870 ft, given the following conditions. MSL, OAT +18°C, wind calm, paved level dry surface. No stopway or clearway. A) 3550 lb B) 2500 lb C) 3150 lb D) 4100 lb
A) 3550 lb
31. For an MEP Aircraft.Using the data provided in CAP698 as required.What is the FLL limited landing mass for a commercial MEP 1 flight given the following conditions: Pressure altitude sea level; OAT 0°C; LDA 2430 ft; 15 kt headwind on a dry runway. A) 3300 lb B) 3000 lb C) 3400 lb D) 3450 lb
A) 3300 lb
32. For an MEP Aircraft.Using the data provided in CAP698 as required.You plan an approach to an airfield at a pressure altitude of 5000 ft and an OAT of +38°C. With the aeroplane at its AUM of 4513 lb, you must determine whether it can satisfy the balked landing climb gradient requirement. What is the achievable balked landing climb gradient? What is the minimum required balked climb gradient? A) 7.35% achievable and 2.5% required. B) 7.35% achievable and 1.43% required. C) 7% achievable and 2.5% required. D) 2.6% achievable and 7.5% required.
A) 7.35% achievable and 2.5% required.
33. [CAP 698]With reference to CAP 698 Figure 3.7. Given: OAT: -20°C Pressure altitude: 18 000 ft Gross mass: 4000 lbs Mixture: Leaned to 25°F Rich of peak EGT Other conditions as associated in the header of the graph. What is the two engine rate of climb for the conditions given? [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
1050 ft/min.
34. Refer to CAP 697 SEP 1 Figure 2.1. Given the following information, what is the required fuel to climb? Airport Pressure Altitude: 4000 ft Airport OAT: +10°C Climb to: FL100 OAT at FL100: -5°C Take-off Mass: 3400 lb Gear: up [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
2.8 gal
35. Refer to CAP 698 Figure 4.1. For a maximum allowable tailwind of 10 kt calculate the maximum wind strength that can be accepted for a take off from runway 06 with wind from 180 degrees. [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
20
36. Ref to CAP 698 MEP 1 Figure 3.1. OAT: 24°C Pressure Altitude: 3000 ft RWY: 30R Wind: 060°/4 kt Take-off Mass: 3800 lb Other conditions are as associated in the header of the graph. Given the following information, what is the Take-Off Distance? [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
2000 ft
37. [CAP 698]With reference to CAP 698 Figure 3.6. Given the following data, determine the aircraft height gain after 2.5 NM. Mass: 4200 lbs PA: 4000 ft OAT: +30°C Wind: 20 kt headwind (All engines operating). [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
3300 ft
38. [CAP 698]With reference to CAP 698 Figure 3.9. For a multi-engine piston aeroplane, calculate the maximum landing mass given the following conditions: Temperature: 10°C Pressure altitude: 2000 ft LDA: 2600 ft Headwind: 14 kt [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
3350 Ib
39. [CAP 698]With reference to CAP 698 Figure 3.2. Given: OAT: 25°C Pressure altitude: 3000 ft RWY: 24L Wind: 310°/20 kts Take-off mass: 4400 lbs Heavy Duty Brakes: installed Other conditions as associated in the header of the chart. What is the Accelerate and Stop Distance under the conditions given? [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
3750 ft
40. [CAP 698]With reference to CAP 698 Figure 3.2. Given: OAT: 20°C Pressure Altitude: 2000 ft RWY: 24L Wind: 120°/8 kts Take-off Mass: 4500 lbs Heavy Duty Brakes: installed Other conditions as associated in the header of the chart. What is the Accelerate and Stop Distance under the conditions given? [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
4200 ft
41. A commercial air transport flight is to be conducted in a single-engined piston aircraft. At the most critical point during the flight, the distance to be travelled to a safe landing place is 10 NM. Given the following information, what is the lowest altitude the aircraft should fly over this critical point? Terrain elevation: 0 ft Gross glide gradient: 10% TAS: 110 kt Expected tailwind component: 20 kt 1 NM = 6080 ft Still air distance = (height difference / net gradient) x 100 Ground distance = Still Air Distance x (GS / TAS)
5400 ft
42. [CAP 698]With reference to CAP 698 Figure 3.10. Given the following information, calculate the barrier speed for a multi-engine piston airplane. Pressure altitude: 4000 ft Outside air temp: 10°C Aircraft mass: 3450 lb [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
72 kt
43. Refer to CAP 698 Figure 2.4. Given the following information, determine the minimum or maximum wind component for the SEP aircraft to land: Pressure altitude: 10 000 ft Mass: 2860 lb Temperature: -2° C Runway LDA: 2000 ft. [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
Minimum 19 kt headwind.
44. [CAP 698]With reference to CAP 698 Figure 3.7. Why is wind omitted from the graph? [Referenz erforderlich: die in der Frage genannte CAP-Abbildung separat verwenden. Grafiken sind nicht in dieser CSV enthalten.]
The data is measured with reference to the air.
45. The maximum angle of bank permitted after take-off below 50 ft for an aeroplane in Performance Class B is:
0°
46. Which factor must be applied, if not stated differently in AFM, for a Performance Class B aeroplane when taking-off on a runway with 1% upslope?
1.05
47. Which factor must be applied, if not stated differently in AFM, for a Performance Class B aeroplane when landing on a runway with short grass?
1.15
48. Consider a Performance Class B aeroplane which is used for commercial transport and a runway where a clearway or a stopway is available. The take-off mass shall not exceed the maximum take-off mass specified in the AFM for the pressure altitude and the ambient temperature at the aerodrome of departure. The unfactored take-off distance, specified in the AFM, shall not exceed the take-off distance available (TODA), when multiplied by a factor of:
49. For an aeroplane in Performance Class B the following factors must be applied in determining the take-off distance from dry grass and wet pavement respectively:
1.2 and 1.0
50. Consider a Performance Class B aeroplane which is used for commercial transport and a runway where a clearway or a stopway is available. The take-off mass shall not exceed the maximum take-off mass specified in the AFM for the pressure altitude and the ambient temperature at the aerodrome of departure. The unfactored take-off distance, specified in the AFM, shall not exceed the accelerate stop distance available (ASDA), when multiplied by a factor of:
1.3
51. VREF for a Class B aircraft is defined as:
1.3 VSO
52. Following a take-off determined by the 50 ft (15 m) screen height, a light twin aircraft 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 10 000 m from the 50 ft clearing point with an obstacle clearance of:
115 m
53. At the planning stage for a Class B performance aircraft, what minimum climb gradient do you use?
300 ft min climb speed with all engines operating.
54. What is the screen height for take off from a wet runway for a Class B aircraft?
50
55. Assume a normal approach and landing with a class B airplane on a dry runway. Which of the following values shows the corresponding screen height?
50 ft
56. Assume a normal approach and landing with a class B aircraft on a wet runway. Which of the following values shows the corresponding screen height?
57. For an aeroplane in Performance Class B the net take-off flight path begins at a height of __________ and ends at a height of __________.
50 ft; 1500 ft
58. What percentages of the head wind and tail wind component are taken into account when calculating the take off field length required?
50% head wind and 150% tail wind.
59. You are in a single engine piston aircraft with a stall speed of 68 kt. What is the minimum value of VR for this aircraft?
68 kt
60. For a piston-engine, at what altitude will it have the best endurance?
about Mean Sea Level
61. What is the effect of excess thrust on a climb at constant angle?
Accelerates and rate of climb increases.
62. Compared with clean configuration, a take off with a 10° flaps setting will result in:
An increased field length limited TOM and a decreased climb limited TOM.
63. For a Performance Class B, multi-engined aeroplane, in order to eliminate any problems associated with a critical engine failure:
counter rotating propellers are installed.
64. For a performance Class B, multi-engined aeroplane, in order to eliminate any problems associated with a critical engine failure:
Counter rotating propellers are installed.
65. The effect of increasing the flap setting, from zero to the recommended take-off setting, on the length of the Take-off Distance Required (TODR) and the Field Length Limited Take-off mass (TOM) is:
Decreased TOD required and increased field length limited TOM.
66. How does a downslope runway affect the take off and landing performance of an aeroplane? It:
decreases the take off distance, and increases the landing distance.
67. In comparison to both engines operative, the power required for a Performance Class B multi-engined aeroplane to maintain level flight with the critical engine inoperative is:
Greater, due to the increase of the total drag.
68. The pilot of an aircraft has calculated a 4000 m service ceiling, based on the forecast general conditions for the flight and a take-off mass of 3250 kg. If the take-off mass is 3000 kg, the service ceiling will be:
higher than 4000 m.
69. What is the effect on performance when the outside air pressure is low:
Increases take-off roll due to decrease in thrust available.
70. The critical engine inoperative:
Increases the power required and the total drag due to the additional drag of the windmilling engine and the compensation of the yaw moment.
71. Which of the following is correct concerning fuel consumption change, at altitude, of a propeller driven aeroplane?
It increases after VMP.
72. What is the effect of tail wind on the time to climb to a given altitude?
No change
73. A headwind during the climb will result in:
No change in the time to climb.
74. What conditions allow the "increase V1" technique to increase the allowable take- off mass? The take off mass is:
Not limited by the field nor by the maximum tyre speed.
75. How is wind considered in the take-off performance data of the Aeroplane Operations Manuals?
Not more than 50% of a headwind and not less than 150% of the tailwind.
76. Which of the following is a Performance Class B aircraft?
Propeller driven aircraft, with a MOPSC equal to or less than 9 passenger seats and with a MTOM of 5700 kg or less.
77. For a multi engined aircraft not certified under EASA CS 25 and in Performance Class B, service ceiling is defined as:
The altitude which at maximum power the rate of climb of an aircraft has fallen to 100 ft per minute.
78. Which of the following provides maximum obstacle clearance during climb?
The speed for maximum climb angle Vx.
79. Maximum endurance for a turbojet aeroplane is achieved at:
The speed that corresponds to the speed for maximum climb angle.
80. The rotation speed VR for normal utility single-engined landplanes (MTOM 5700 kg or less) must be the same as or faster than:
VS1
81. The stalling speed or the minimum steady flight speed at which the aeroplane is controllable in landing configuration is abbreviated as:
VSO.
Last changed7 days ago