Question 95-1 : 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 ? [ Success topography ]
3050 m

Question 95-2 : In which of the following distances can the length of a stopway be included ?
Question 95-3 : At which minimum height will the second climb segment end ?
400 ft above field elevation

Question 95-4 : How does tas vary in a constant mach climb in the troposphere under isa conditions ?
Tas decreases

Question 95-5 : The optimum long range cruise altitude for a turbojet aeroplane ?
Question 95-6 : How does the specific range change when the altitude increases for jet aeroplane flying with the speed for maximum range ?
First increases then decreases

Question 95-7 : At reference .assuming constant l/d ratio which of the diagrams provided correctly shows the movement of the 'thrust required curve' .mass m1 is higher than mass m2 . err a 032 55 ?
C

Question 95-8 : Long range cruise is a flight procedure which gives ?
Question 95-9 : A commercial flight is planned with a turbojet aeroplane to an aerodrome with a landing distance available of 2400 m .the aeroplane mass must be such that on arrival the aeroplane can be landed within ?
1 440 m

Question 95-10 : At the destination aerodrome the landing distance available is 3000m .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 ?
1565 m

Question 95-11 : 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

Question 95-12 : Two identical turbojet aeroplane whose specific fuel consumptions are considered to be equal are at holding speed at the same altitude .the mass of the first aircraft is 130 000 kg and its ho y fuel consumption is 4300 kg/h the mass of the second aircraft is 115 000 kg and its ho y fuel consumption ?
Question 95-13 : 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 mileage of 14 kg per nautical mile .in the same flying conditions the same aeroplane equipped with modern engines with a specific fuel ?
8 17 kg/nm
Question 95-14 : The determination of the maximum mass on brake release of a certified turbojet aeroplane with 5° 15° and 25° flaps angles on take off leads to the following values with wind .flap angle 5° 15° 25°.flltom kg 66 000 69 500 71 500.cltom 72 200 69 000 61 800.wind correction .head wind ?
67700 kg / 15°

Question 95-15 : 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 ?
Question 95-16 : For a twin engine turbojet aeroplane two take off flap settings 5° and 15° are certified .given .field length avalaible= 2400 m.outside air temperature= 10°c.airport pressure altitude= 7000 ft.the maximum allowed take off mass is . 2105 ?
Question 95-17 : The lowest take off safety speed v2 min is ?
1 13 vsr for two and three engine turbo propeller and turbojet aeroplanes

Question 95-18 : Which of the following three speeds of a jet aeroplane are basically identical .the speeds for ?
Holding maximum climb angle and minimum glide angle

Question 95-19 : The lift coefficient decreases during a glide with constant mach number mainly because the ?
Question 95-20 : During a descent at constant mach number the margin to low speed buffet will ?
Increase because the lift coefficient decreases
Question 95-21 : A jet aeroplane is climbing at a constant ias and maximum climb thrust how will the climb angle / the pitch angle change ?
Question 95-22 : A jet aeroplane is flying long range cruise how does the specific range / fuel flow change ?
Increase / decrease

Question 95-23 : During a glide at constant mach number the pitch angle of the aeroplane will ?
Question 95-24 : During a cruise flight of a jet aeroplane at constant flight level and at the maximum range speed the ias / the drag will ?
Decrease / decrease
Question 95-25 : An aeroplane descends from fl 410 to fl 270 at its cruise mach number and from fl 270 to fl 100 at the ias achieved at fl 270 .assuming idle thrust a clean configuration and ignoring compressibility effects how does the angle of descent change i in the first and ii in the second part of the descent ?
I increases ii remains constant

Question 95-26 : With a jet aeroplane the maximum climb angle can be flown at approximately ?
Question 95-27 : 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 remains almost constant

Question 95-28 : Which of the following sequences of speed for a jet aeroplane is correct . from low to high speeds ?
Question 95-29 : If a flight is performed with a higher 'cost index' at a given mass which of the following will occur ?
A higher cruise mach number

Question 95-30 : For a jet transport aeroplane which of the following is the reason for the use of 'maximum range speed' ?
Minimum specific fuel consumption

Question 95-31 : What happens when an aeroplane climbs at a constant mach number ?
The lift coefficient increases

Question 95-32 : Which of the following is a reason to operate an aeroplane at 'long range speed' ?
It is efficient to fly slightly faster than with maximum range speed

Question 95-33 : If the value of the balanced v1 is found to be lower than vmcg which of the following is correct ?
V1 must be increased to at least the value of vmcg

Question 95-34 : Reduced take off thrust should normally not be used when ?
Windshear is reported on the take off path

Question 95-35 : Reduced take off thrust should normally not be used when ?
Question 95-36 : The use of reduced take off thrust is permitted only if ?
The actual take off mass tom is lower than the field length limited tom

Question 95-37 : Which combination of circumstances or conditions would most likely lead to a tyre speed limited take off ?
Question 95-38 : The drift down requirements are based on ?
The obstacle clearance during a descent to the new cruising altitude if an engine has failed

Question 95-39 : Which of the following statements concerning the obstacle limited take off mass for performance class a aeroplane is correct ?
Question 95-40 : The 'maximum tyre speed' limits ?
Vlof in terms of ground speed

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