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Question 97-1 : Which of the jet engine ratings below is not a certified rating ? [ Attainment AIM ]

Maximum cruise thrust

exemple 197 Maximum cruise thrust.

Question 97-2 : At constant thrust and constant altitude the fuel flow of a jet engine ?

Increases slightly with increasing airspeed

.because your mass decreases with time and the question states 'constant altitude' your airspeed will increase at constant thrust because you have to decrease your angle of attack to maintain constant altitude .as more air is entering the engine ram effect is increased the compressor works harder which demands an increase of the fuel flow exemple 201 Increases slightly with increasing airspeed.

Question 97-3 : The thrust of a jet engine at constant rpm ?

Increases in proportion to the airspeed

Jomargra .for a jet engine the net thrust is the difference between the gross thrust and the intake momentum drag increasing speed increases the intake momentum drag which reduces the thrust however at higher speeds the increased intake pressure due to ram effect is insufficient to counteract the loss of thrust due to intake momentum drag therefore during the take off there will be a decrease of thrust from oxford book ..at constant rpm the ram effect increases the mass of air in the intake and at a higher pressure thrust starts to increase exemple 205 Increases in proportion to the airspeed.

Question 97-4 : A higher altitude at constant mass and mach number requires ?

A higher angle of attack

.lift = cl x 1/2 rho v² x s.cl = lift coefficient.rho = density.v = tas in m/s .s = surface.at higher altitude 'rho' and 'tas' are reduced you can only act on lift coefficient you must to increase your angle of attack to maintain lift constant exemple 209 A higher angle of attack.

Question 97-5 : The long range cruise speed is selected because ?

The higher speed achieves 99% of the maximum still air range

exemple 213 The higher speed achieves 99% of the maximum still-air range.

Question 97-6 : The optimum altitude ?

Increases as mass decreases and is the altitude at which the specific range reaches its maximum

exemple 217 Increases as mass decreases and is the altitude at which the specific range reaches its maximum.

Question 97-7 : The engine failure take off run is ?

The horizontal distance along the take off path from the start of the take off to a point equidistant between the point at which vlof is reached and the point at which the aeroplane is 35 ft above the take off surface

exemple 221 The horizontal distance along the take-off path from the start of the take-off to a point equidistant between the point at which vlof is reached and the point at which the aeroplane is 35 ft above the take-off surface.

Question 97-8 : Reduced take off thrust ?

Has the benefit of improving engine life

exemple 225 Has the benefit of improving engine life.

Question 97-9 : A 'balanced field length' is said to exist where ?

The accelerate stop distance is equal to the take off distance available

exemple 229 The accelerate stop distance is equal to the take-off distance available.

Question 97-10 : The optimum cruise altitude increases ?

If the aeroplane mass is decreased

exemple 233 If the aeroplane mass is decreased.

Question 97-11 : Below the optimum cruise altitude ?

The mach number for long range cruise decreases continuously with decreasing altitude

Admin .long range cruise is derived from the drag/eas curve lrc is slightly faster 1 37vmd than maximum range speed 1 32vmd . vmd means velocity minimum drag .lrc is 4% faster than maximum range speed for 99% of the range lrc is flown as a mach number and since it is a point on the drag/eas curve it will be constant eas on the ertm graph thus lrc decreases with decreasing altitude .the 'ertm' diagram ertm for e as/ r as rectified air speed or cas / t as/ m ach . 1960.eas is vertical mach number decreases with altitude and increases with increasing altitude exemple 237 The mach number for long range cruise decreases continuously with decreasing altitude.

Question 97-12 : If after experiencing an engine failure when cruising above the one engine inoperative ceiling an aeroplane is unable to maintain its cruising altitude the procedure that should be adopted is ?

Drift down procedure

Admin .in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport

Question 97-13 : 'drift down' is the procedure to be applied ?

After engine failure if the aeroplane is above the one engine out maximum altitude

Admin .in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport exemple 245 After engine failure if the aeroplane is above the one engine out maximum altitude.

Question 97-14 : If the level off altitude is below the obstacle clearance altitude during a drift down procedure ?

Fuel jettisoning should be started at the beginning of drift down

Admin .in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down

Question 97-15 : The landing field length required for turbojet aeroplanes at the destination wet condition is the demonstrated landing distance plus ?

92%

.for jet aeroplanes the landing field length required at destination and at alternate must be factored by 1 66 to make it 60% of distance available .landing distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 1 15 .1 66 x 1 15 = 1 92 92% .the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92% exemple 253 92%.

Question 97-16 : The landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus ?

92%

.for jet aeroplanes the landing field length required at destination and at alternate must be factored by 1 66 to make it 60% of distance available .landing distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 1 15 .1 66 x 1 15 = 1 92 92% .the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92% exemple 257 92%.

Question 97-17 : The speed vsr is defined as ?

As reference stall speed and may not be less than 1 g stall speed

exemple 261 As reference stall speed and may not be less than 1-g stall speed.

Question 97-18 : The speed v2 is defined for jet aeroplane as ?

Take off climb speed or speed at 35 ft

exemple 265 Take-off climb speed or speed at 35 ft.

Question 97-19 : The aerodynamic ceiling ?

Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same

.if there is no reserve of power available to permit any climb you are at the absolute ceiling .if you have lots of power you can climb until mmo and minimum control speed coincide you are at your aerodynamic ceiling .the aerodynamic ceiling is that altitude at which the low speed buffet and the high speed buffet are equal exemple 269 Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.

Question 97-20 : 'stepped climbs' are used on long distance flights ?

To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces

exemple 273 To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.

Question 97-21 : The climb gradientafter take off in a standard atmosphere and still air at 0 ft pressure altitude is 6% .use the following corrections to determine the climb gradient after take off on a aerodrome 1000 ft aerodrome pressure altitude oat +17°c 1013 25 hpa wing and engine anti ice systems on ?

3 9 %

Admin .6% minus 0 2% for aerodrome elevation = 5 8%.5 8% minus 0 4% for temperature deviation = 5 4%.5 4% minus 1% for wing anti ice on = 4 4%.4 4% minus 0 5% for engine anti ice on = 3 9% exemple 277 3.9 %.

Question 97-22 : The drift down procedure specifies requirements concerning the ?

Obstacle clearance after engine failure

Admin .in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down exemple 281 Obstacle clearance after engine failure.

Question 97-23 : Given a jet aircraft which order of increasing speeds in the performance diagram is correct ?

Vs vx maximum range speed

Admin .this is the order of speeds from slowest to fastest .obviously vs is slowest then vx .vs is stall speed very slow .vx is the speed for best angle of climb climbing at vx allows pilots to maximize the altitude gain per unit ground distance vx is faster than vs .maximum range speed gives you the most lift for the least drag for the most economy and te most distance for altitude lost maximum range speed is found at best lift/drag speed which is faster than vx .long range speed is higher than maximum range speed and is used as the standard speed for cruise it is 4% faster than best range speed for 99% of the range exemple 285 Vs, vx, maximum range speed.

Question 97-24 : 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 ?

0 60

.eu ops 1 515 landing dry runways. a an operator shall ensure that the landing mass of the aeroplane determined in accordance with eu ops 1 475 a for the estimated time of landing at the destination aerodrome and at any alternate aerodrome allows a full stop landing from 50 ft above the threshold . 1 for turbo jet powered aeroplanes within 60% of the landing distance available or. 2 for turbo propeller powered aeroplanes within 70% of the landing distance available . example .an aircraft needs 1200 m to stop landing distance required with maximum braking manufacturers data factored for slope and wind effects .for a dry runway this 1200 m must not represent more than 60% percent of landing distance available lda so the minimum landing distance available is indeed 1200 x 1 67 = 2004 m .now if you start from 2004 m the landing distance available we use a 0 60 factor 2004 x 0 6 = 1200 m exemple 289 0.60.

Question 97-25 : On a segment of the take off flight path an obstacle requires a minimum gradient of climb of 2 6% in order to provide an adequate margin of safe clearance .at a mass of 110000 kg the gradient of climb is 2 8% .for the same power and assuming that the sine of the angle of climb varies inversely with ?

118455 kg

2 8 / 2 6 x 110000 = 118461 kg .as we decrease our climb gradient for the same power our mass can be increased exemple 293 118455 kg.

Question 97-26 : Which statement with respect to the step climb is correct ?

Performing a step climb based on economy can be limited by the 1 3g buffet onset requirements

.in order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 1 3 this value is an operating limitation but not a regulatory one the corresponding altitude is called the '1 3g buffet limited altitude' or 'buffet ceiling' exemple 297 Performing a step climb based on economy can be limited by the 1.3g buffet onset requirements.

Question 97-27 : In accordance to cs 25 which of the following listed speeds are used for determination of v2min ?

Vsr vmca

Cs25 .v2min in terms of calibrated airspeed may not be less than . 1 1 13 vsr for . i two engined and threeengined turbo propeller powered aeroplanes and. ii turbojet powered aeroplanes without provisions for obtaining a significant reduction in the one engine inoperative power on stall speed .. 2 1 08 vsr for . i turbo propeller powered aeroplanes with more than three engines and. ii turbojet powered aeroplanes with provisions for obtaining a significant reduction in the one engine inoperative power on stall speed and. 3 1 10 times vmc established under cs 25 149 .vsr reference stall speed exemple 301 Vsr, vmca.

Question 97-28 : Reduced take off thrust should normally not be used when ?

Anti skid is not usable

.a reduced take off thrust is not permitted with icy or slippery runways contamined runways contamination can have a large and uncertain drag on the take off run .for safety reasons it is preferable to reduce the running distance to reach v1 even if you can accomplish a safety rejected take off on the allowed asda thus you shouldn't use reduced take off thrust when anti skid is not usable exemple 305 Anti skid is not usable.

Question 97-29 : Maximum tyre speed can limit the lift off speed which kind of speed can be directly used to determine this limitation ?

Groundspeed

exemple 309 Groundspeed.

Question 97-30 : According to cs 25 the landing reference speed vref may not be less than ?

1 23 vsr0 and must be maintained down to 50 ft height

.cs 25 125 landing . a the horizontal distance necessary to land and to come to a complete stop from a point 15 m 50 ft above the landing surface for standard temperatures at each weight altitude and wind within the operational limits established by the applicant for the aeroplane with a landing reference speed vref not be less than 1 23 vsr0 .vsr0 reference stall speed in the landing configuration exemple 313 1.23 vsr0 and must be maintained down to 50 ft height.

Question 97-31 : 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

.in order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 1 3 this value is an operating limitation but not a regulatory one the corresponding altitude is called the '1 3g buffet limited altitude' or 'buffet ceiling' exemple 317 Executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1.

Question 97-32 : Select from the following list of conditions those that must prevail in the second segment of the take off net flight path for a class a aeroplane are .1 undercarriage retracted .2 undercarriage extended .3 flaps up .4 flaps in take off position .5 all engines at take off thrust .6 operative engine ?

1 4 6 9

exemple 321 1, 4, 6, 9.

Question 97-33 : V1 for a balanced field is calculated when ?

The acceleration/stop distance available is equal to the take off distance available

exemple 325 The acceleration/stop distance available is equal to the take-off distance available.

Question 97-34 : With regard to the drift down performance of the twin jet aeroplane why does the curve representing 35 000 kg gross mass in the chart for drift down net profiles start at approximately 4 minutes at fl370 . 2128 ?

Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level

Admin . 2519.you will stay at the original cruising level until you reach the optimum speed for descent exemple 329 Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

Question 97-35 : The requirements of the take off net flight path for a class a aeroplane assume ?

The failure of the critical engine of a multi engined aeroplane at vef

exemple 333 The failure of the critical engine of a multi-engined aeroplane at vef.

Question 97-36 : The angle of attack required to attain the maximum still air range for a turbo jet aeroplane is ?

Less than that for the maximum lift to drag ratio

. /com en/com032 334 jpg.for a jet aeroplane maximum l/d ratio is maximum endurance which is vmd where the gap between power required and power available is greatest at this speed for a conventional aerofoil the angle of attack is about 4° .the speed for maximum range maximum still air range occurs at 1 32 times the speed of minimum drag vmd in level flight as speed goes up the angle of attack goes down angle of attack is less than 4° typically at around 2 5° exemple 337 Less than that for the maximum lift to drag ratio.

Question 97-37 : Compared with balanced field calculations for an aerodrome with no stopway or clearway the use of a clearway in the take off calculations will ?

Increase the field length limited take off mass

.a field length is balanced when take off distance available equals accelerate stop distance available .the take off distance available is the length of the take off run available plus the length of the clearway available .a clearway is an area beyond the paved runway free of obstacles . 771.the use of any additional clearway in take off performance calculations may allow a greater field limited take off mass but the v1 will be lower because the extra take off mass means that more distance will be required to stop in the event of an aborted takeoff exemple 341 Increase the field-length-limited take-off mass.

Question 97-38 : The relationship of the reference landing speed vref to the reference stalling speed in the landing configuration vsro is that vref may not be below ?

1 23 vsro

exemple 345 1.23 vsro.

Question 97-39 : The vertical interval by which a class a aeroplane must avoid all obstacles in the drift down path during the drift down following an engine failure is ?

2000 ft

.eu ops 1 500 en route one engine inoperative . . c the net flight path must permit the aeroplane to continue flight from the cruising altitude to an aerodrome where a landing can be made in accordance with eu ops 1 515 or 1 520 as appropriate the net flight path clearing vertically by at least 2 000 ft all terrain and obstructions along the route within 9 3 km 5 nm on either side of the intended track exemple 349 2000 ft.

Question 97-40 : Cs 25 the correct formula is . remark ' ?

Vmcg

.the minimum control speed on the ground vmcg is based on directional control being maintained by primary aerodynamic control only .vef is the speed at which the critical engine is assumed to fail during takeoff .v1 follows vef it is the decision speed at take off and it is the calibrated airspeed below which take off must be rejected if an engine failure is recognized above which take off should be continued exemple 353 Vmcg


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