Quiz
4. Performance
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Fragen in diesem Quiz (26)
1124) In unaccelerated climb
- Athrust equals drag plus the uphill component of the gross weight in the flight path direction.
- Bthrust equals drag plus the downhill component of the gross weight in the flight path direction.
- Clift is greater than the gross weight.
- Dlift equals weight plus the vertical component of the drag.
2125) The optimum cruise altitude increases
- Aif the aeroplane mass is decreased.
- Bif the temperature (OAT) is increased.
- Cif the tailwind component is decreased.
- Dif the aeroplane mass is increased.
3126) Regarding the obstacle limited take-off mass, which of the following statements is correct?
- AThe obstacle limited mass can never be lower than the climb limited take-off mass.
- BThe maximum bank angle which can be used is 10°.
- CA take-off in the direction of an obstacle is also permitted in tail wind condition.
- DWind speed plays no role when calculating this particular mass.
4127) A jet aeroplane is climbing at a constant IAS and maximum climb thrust, how will the climb angle / the pitch angle change?
- ARemain constant / decrease.
- BRemain constant / become larger.
- CReduce / decrease.
- DReduce / remain constant.
5128) Reduced take-off thrust should normally not be used when:
- Athe runway is wet.
- Bthe OAT is ISA +10°C
- Canti skid is not usable.
- Dit is dark.
6144) How is wind considered in the take-off performance data of the Aeroplane Operations Manuals ?
- AUnfactored headwind and tailwind components are used.
- BNot more than 80% headwind and not less than 125% tailwind.
- CSince take-offs with tailwind are not permitted, only headwinds are considered.
- DNot more than 50% of a headwind and not less than 150% of the tailwind.
7131) On a reciprocating engined aeroplane, with increasing altitude at constant gross mass, angle of attack and configuraton the drag
- Aremains unchanged but the TAS increases.
- Bremains unchanged but the the CAS increases
- Cincreases at constant TAS.
- Ddecreases and the CAS decreases too because of the lower air density.
8120) The drift down procedure specifies requirements concerning the:
- Aengine power at the altitude at which engine failure occurs
- Bclimb gradient during the descent to the net level-off altitude
- Cweight during landing at the alternate
- Dobstacle clearance during descent to the net level-off altitude
9133) Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed?
- AThe mass of an aeroplane does not have any effect on the speed for descent.
- BThe higher the gross mass the greater is the speed for descent.
- CThe higher the gross mass the lower is the speed for descent.
- DThe higher the average temperature (OAT) the lower is the speed for descent.
10134) What will be the influence on the aeroplane performance if aerodrome pressure altitude is increased?
- AIt will increase the take-off distance.
- BIt will decrease the take-off distance.
- CIt will increase the take-off distance available.
- DIt will increase the accelerate stop distance available.
11135) An aeroplane is in a power off glide at best gliding speed. If the pilot increases pitch attitude the glide distance:
- Aincreases.
- Bremains the same.
- Cmay increase or decrease depending on the aeroplane.
- Ddecreases.
12136) Which statement concerning the inclusion of a clearway in take-off calculation is correct?
- AThe field length limited take-off mass will increase.
- BThe usable length of the clearway is not limited.
- CV1 is increased.
- DV1 remains constant.
13137) What affect has a tailwind on the maximum endurance speed?
- ANo affect
- BTailwind only effects holding speed.
- CThe IAS will be increased.
- DThe IAS will be decreased.
14138) Which of the equations below defines specific range (SR)?
- ASR = Groundspeed/Total Fuel Flow
- BSR = True Airspeed/Total Fuel Flow
- CSR = Indicated Airspeed/Total Fuel Flow
- DSR = Mach Number/Total Fuel Flow
15139) Take-off performance data, for the ambient conditions, show the following limitations with flap 10° selected:
- runway limit: 5 270 kg
- obstacle limit: 4 630 kg
Estimated take-off mass is 5 000kg. Considering a take-off with flaps at:- A20°, both limitations are increased
- B5°, the obstacle limit is increased but the runway limit
decreases - C5°, both limitations are increased
- D20°, the obstacle limit is increased but the runway limit decreases
16140) Is there any difference between the vertical speed versus forward speed curves for two identical aeroplanes having different masses ? (assume zero thrust and wind)
- AYes, the difference is that the lighter aeroplane will always glide a greater distance.
- BYes, the difference is that for a given angle of attack both the vertical and forward speeds of the heavier aeroplane will be larger.
- CNo difference.
- DYes, the difference is that the heavier aeroplane will always
glide a greater distance.
17141) Which of the following statements with regard to the optimum cruise altitude (best fuel mileage) is correct?
- AAn aeroplane usually flies above the optimum cruise altitude, as this provides the largest specific range.
- BAn aeroplane sometimes flies above the optimum cruise altitude, because ATC normally does not allow to fly continuously at the optimum cruise altitude.
- CAn aeroplane always flies below the optimum cruise altitude, as otherwise Mach buffet can occur.
- DAn aeroplane always flies on the optimum cruise altitude, because this is most attractive from an economy point of view.
18130) A four jet-engined 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 Newtons. The gradient of climb is:
(given: g= 10 m/s2)- A1.286%.
- B27%.
- C7.86%.
- D12.86%.
1918. How does the best angle of climb and best rate of climb vary with increasing altitude?
- ABoth decrease.
- BBoth increase.
- CBest angle of climb increases while best rate of climb decreases.
- DBest angle of climb decreases while best rate of climb increases.
2028. The optimum altitude
- Ais the altitude up to which cabin pressure of 8 000 ft can be maintained.
- Bincreases as mass decreases and is the altitude at which the specific range reaches its maximum.
- Cdecreases as mass decreases.
- Dis the altitude at which the specific range reaches its minimum.
218) A lower airspeed at constant mass and altitude requires
- Aless thrust and a lower coefficient of lift.
- Bmore thrust and a lower coefficient of lift.
- Cmore thrust and a lower coefficient of drag.
- Da higher coefficient of lift.
229) At a constant Mach number the thrust and the fuel flow of a jet engine
- Aincrease in proportion to the ambient pressure at constant temperature.
- Bdecrease in proportion to the ambient pressure at constant temperature.
- Cincrease with increasing altitude.
- Dare independent of outside air temperature (OAT).
2310) Following a take-off determined by the 50ft (15m) 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 10 000 m from the 50 ft clearing point with an obstacle clearance of- A85m
- BIt will not clear the obstacle
- C115 m
- D100 m
2411) Moving the center of gravity from the forward to the aft limit (gross mass, altitude and airspeed remain unchanged)
- Aincreases the power required.
- Baffects neither drag nor power required.
- Cincreases the induced drag.
- Ddecreases the induced drag and reduces the power required.
2512) On a reciprocating engined aeroplane, with increasing altitude at constant gross mass, angle of attack and configuraton the power required
- Aremains unchanged but the TAS increases.
- Bincreases and the TAS increases by the same percentage.
- Cincreases but TAS remains constant.
- Ddecreases slightly because of the lower air density.
2613) 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 feet 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?- A1950 m.
- B2009 m.
- C2243 m.
- D2096 m.
Informationen
- Beschreibung
- Tema 1 Performances Quiz am 4. Performance, erstellt von Jose Antonio Vazquez am 06/11/2018.
- Autor
- Jose Antonio Vazquez
- Sprache
- Español
- Aufrufe
- 333
- Schlagwörter
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