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Question 96-1 : Which of the following factors determines the maximum flight altitude in the 'buffet onset boundary' graph ? [ Concept Manual ]

Aerodynamics

Admin .anytime that too great a lift demand is made on the wing whether from too fast an airspeed or from too high an angle of attack near the mmo the 'high speed buffet' will occur .mach buffet occurs as a result of supersonic airflow on the wing stall buffet occurs at angles of attack that produce airflow disturbances burbling over the upper surface of the wing which decreases lift as density altitude increases the angle of attack that is required to produce an airflow disturbance over the top of the wing is reduced until the density altitude is reached where mach buffet and stall buffet converge coffin corner .when this phenomenon is encountered serious consequences may result causing loss of airplane control . 1075.this is purely the aerodynamics factors which define the 'buffet onset boundary' graph exemple 196 Aerodynamics.

Question 96-2 : Which data can be extracted from the buffet onset boundary chart ?

The values of the mach number at which low speed and mach buffet occur at various masses and altitudes

Admin .anytime that too great a lift demand is made on the wing whether from too fast an airspeed or from too high an angle of attack near the mmo the 'high speed buffet' will occur . 0175.'buffet onset boundary' graph .mach buffet occurs as a result of supersonic airflow on the wing stall buffet occurs at angles of attack that produce airflow disturbances burbling over the upper surface of the wing which decreases lift as density altitude increases the angle of attack that is required to produce an airflow disturbance over the top of the wing is reduced until the density altitude is reached where mach buffet and stall buffet converge coffin corner exemple 200 The values of the mach number at which low speed and mach buffet occur at various masses and altitudes.

Question 96-3 : Why should the temperature of the wheel brakes be checked prior to take off ?

Because overheated brakes will not perform adequately in the event of a rejected take off

exemple 204 Because overheated brakes will not perform adequately in the event of a rejected take-off.

Question 96-4 : A jet aeroplane is climbing with constant ias which operational speed limit is most likely to be reached ?

The maximum operating mach number

Admin . 975.mach number is increasing with altitude at constant ias you may reached mmo maximum operating mach number .vmca minimum control speed air and stalling speed refer to ias the question states 'climbing with constant ias' so there is no risk exemple 208 The maximum operating mach number.

Question 96-5 : A jet aeroplane descends with constant mach number which speed limit will be exceeded ?

Maximum operating speed

.vmo/mmo is defined as the maximum operating limit speed vmo is expressed in knots calibrated airspeed kcas while mmo is expressed in mach number the vmo limit is usually associated with operations at lower altitudes and deals with structural loads and flutter .the mmo limit is associated with operations at higher altitudes and is usually more concerned with compressibility effects and flutter at lower altitudes structural loads and flutter are of concern at higher altitudes compressibility effects and flutter are of concern .the operational limit that may be exceeded during a descends with constant mach number is vmo maximum operating speed exemple 212 Maximum operating speed.

Question 96-6 : Which of the following statements regarding the reduced thrust take off technique is correct ?

Reduced thrust can be used when the actual take off mass is less than the performance limited take off mass

.a reduced thrust take off is a take off that is accomplished utilizing less thrust than the engines are capable of producing under the existing conditions of temperature and pressure altitude .it is not necessary to use the maximum takeoff thrust when you are not at the maximum takeoff weight performance limited take off mass exemple 216 Reduced thrust can be used when the actual take-off mass is less than the performance limited take-off mass.

Question 96-7 : Which statement in relation to the climb limited take off mass of a jet aeroplane is correct ?

The climb limited take off mass decreases with increasing oat

.the climb limited take off mass is reduced because density rho decreases when air is warmer .the take off climb path has a fixed value to be able to deal with this value we must reduce our maximum take off mass .the climb limited take off mass is the highest takeoff mass that meets all of the following regulatory requirements for minimum one engine inoperative climb gradient . first segment . second segment . final segment . jomargra .why the answer 50% of a headwind is taken into account when determining the climb limited take off mass is wrong ..there are several performance criteria to comply with for take off but they can be broadly split into two groups .1 runway performance.2 climb performance.for 'runway performance' you would include things like field length limits brake energy limits tyre speed limits and obstacle limits for all these you take into account runway length wet/dry slope qnh wind 50% or 150% altitude field elevation and temperature .'climb performance' has nothing to do with runways or obstacles it is simply a regulatory requirement to achieve a minimum gradient of climb in various configurations and at various engine settings and numbers of engines for different climb segments exemple 220 The climb limited take-off mass decreases with increasing oat.

Question 96-8 : What is the advantage of a balanced field length condition ?

A balanced field length gives the minimum required field length in the event of an engine failure

.a balanced field is where toda = asda .toda take off distance available .asda acceleration stop distance available .if you have an engine failure at v1 and you continue the take off you will just make the screen height of 35ft and v2 at the end of toda .but if you stop you will just stop within asda this then must be the minimum required field length exemple 224 A balanced field length gives the minimum required field length in the event of an engine failure.

Question 96-9 : At reference or see performance manual mrjt 1 figure 4 24 .with regard to the drift down performance of the twin jet aeroplane what is meant by 'equivalent gross mass at engine failure' . err a 032 136 ?

The equivalent gross mass at engine failure is the actual gross mass corrected for oat higher than isa +10°c

exemple 228 The equivalent gross mass at engine failure is the actual gross mass corrected for oat higher than isa +10°c.

Question 96-10 : The effects of an increased ambient air temperature beyond the flat rating cut off temperature of the engines on i the field length limited take off mass and ii the climb limited take off mass are ?

I decrease ii decrease

.there are several parameters that determine the maximum thermodynamic output of a turbine engine these are the maximum turbine speed the maximum pressures it can contain and the maximum temperatures it's part can operate at too many rpm and fan blades fail too high of pressures things break too hot and they melt .turbines are often 'flat rated' with the operating parameters set well below the actual possible output of the engine this is very common in turboprops the engine may be capable of 750 hp but can be 'flat rated' at a much lower power perhaps 400 to 500 hp .this is normally done as a way to ensure that the engine can deliver the rated horse power under all conditions or to use the engine in an airframe not certified at the higher power rating .one of the key indications of power output is often the itt the inlet turbine temperature .a flat rated temp would mean that the engine may be capable of higher operating temperatures but in this installation the allowed temperature is limited to maintain the flat rating .thus if ambient air temperature increases beyond the flat rating cut off temperature you will reach the maximum performance of the airplane exemple 232 (i) decrease (ii) decrease.

Question 96-11 : The tangent from the origin to the power required against true airspeed curve for a jet aeroplane determines the speed for ?

Maximum endurance

Admin . 1085.maximum endurance is reached at minimum drag speed vmd .vmd is the speed for minimum fuel consumption maximum endurance in a jet aircraft exemple 236 Maximum endurance.

Question 96-12 : In the drag versus tas curve for a jet aeroplane the speed for maximum range corresponds with ?

The point of contact of the tangent from the origin to the drag curve

Admin . 1078.'drag versus tas curve' is also called 'thrust required curve' or 'drag or thrust required against airspeed' .the speed for maximum range for a jet occurs at 1 32vmd exemple 240 The point of contact of the tangent from the origin to the drag curve.

Question 96-13 : Which cruise system gives minimum fuel consumption during cruise between top of climb and top of descent . still air no turbulence ?

Maximum range

Giulicor12 .vmd for a jet is the max endurance speed so gives the lowest drag and so the lowest fuel consumption isn't it ..the question is talking about 'fuel consumption during cruise' the cruise is not carried out at maximum endurance speed but at maximum range speed passengers don't want to spend their time in flight maximum range speed gives you minimum fuel consumption for the cruise exemple 244 Maximum range.

Question 96-14 : A twin jet aeroplane is in cruise with one engine inoperative and has to overfly a high terrain area in order to allow the greatest clearance height the appropriate airspeed must be the airspeed ?

Of greatest lift to drag ratio

exemple 248 Of greatest lift-to-drag ratio.

Question 96-15 : 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/s2 ?

12 86%

.calculation for the climb gradient .aircraft weight 1500000 n .all engines operating 4 x 75000 n = 300000 n ..lift/drag = 14.drag = lift/14.drag = 1500000n / 14 = 107143 n ..sin angle of climb = thrust drag / weight.sin angle of climb = 300000 107143 / 1500000.sin angle of climb = 0 128571.multiplicate by 100 for a result in percent 12 86% exemple 252 12.86%.

Question 96-16 : The long range cruise speed is in relation to the speed for maximum range cruise ?

Higher

.long range cruise speed is 4% faster than maximum range speed long range cruise speed is speed of 99% best specific range .it is efficient to fly faster than maximum range speed when the whole cost of the operation is taken into account fuel leasing costs maintenance costs crew costs atc costs etc the shorter sector times achieved at the faster speed make the operation more efficient because it reduces overall costs exemple 256 Higher.

Question 96-17 : Field length is balanced when ?

Take off distance available equals accelerate stop distance available

exemple 260 Take-off distance available equals accelerate stop distance available.

Question 96-18 : The second segment begins ?

When landing gear is fully retracted

.the first segment starts at 'reference zero' and ends when the gear comes up .the second segment lasts until levelling off for flap retraction .the third segment ends when ready for the enroute climb it is usually a level burst at 400 ft during which acceleration is made to climb speed flaps are retracted and power is reduced to max continuous exemple 264 When landing gear is fully retracted.

Question 96-19 : An aeroplane operating under the 180 minutes etops rule may be up to ?

180 minutes flying time from a suitable airport in still air with one engine inoperative

exemple 268 180 minutes flying time from a suitable airport in still air, with one engine inoperative.

Question 96-20 : Etops flight is a twin engine jet aeroplane flight conducted over a route where no suitable airport is within an area of ?

60 minutes flying time in still air at the approved one engine out cruise speed

exemple 272 60 minutes flying time in still air at the approved one engine out cruise speed.

Question 96-21 : At reference or see performance manual mrjt 1 figure 4 24 .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 3 minutes at fl370 . err a 032 173 ?

Because at this mass it takes about 3 minutes to decelerate to the optimum speed for drift down at the original cruising level

exemple 276 Because at this mass it takes about 3 minutes to decelerate to the optimum speed for drift down at the original cruising level.

Question 96-22 : At reference or see performance manual mrjt 1 figure 4 5 .with regard to the take off performance of a twin jet aeroplane why does the take off performance climb limit graph show a kink at 30°c and pa 0 ft . err a 032 174 ?

The engines are pressure limited at lower temperature at higher temperatures they are temperature limited

An engine is 'flat rated' at temperatures below isa +15°c approximately and temperature limited above that .when an engine is 'flat rated' it means that an engine of high horsepower rating is constrained to a lower horsepower rating exemple 280 The engines are pressure limited at lower temperature, at higher temperatures they are temperature limited.

Question 96-23 : At reference or see performance manual mrjt 1 figure 4 5 .consider the take off performance for the twin jet aeroplane climb limit chart why has the wind been omitted from the chart . err a 032 175 ?

The climb limit performances are taken relative to the air

There is no wind input to the graph the climb limited take off mass is an air gradient and therefore unaffected by wind exemple 284 The climb limit performances are taken relative to the air.

Question 96-24 : The first segment of the take off flight path ends ?

At completion of gear retraction

.the first segment starts at 'reference zero' and ends when the gear comes up .the second segment lasts until levelling off for flap retraction .the third segment ends when ready for the enroute climb it is usually a level burst at 400 ft during which acceleration is made to climb speed flaps are retracted and power is reduced to max continuous exemple 288 At completion of gear retraction.

Question 96-25 : If the climb speed schedule is changed from 280/ 74 to 290/ 74 the new crossover altitude will be ?

Lower

Admin .the crossosver altitude is the altitude at which a specified cas and mach value represent the same tas value the curves for constant cas and constant mach intersect at this point above this altitude the mach number is used to reference speeds . 1081. typical climb profile exemple 292 Lower.

Question 96-26 : The optimum cruise altitude is ?

The pressure altitude at which the best specific range can be achieved

exemple 296 The pressure altitude at which the best specific range can be achieved.

Question 96-27 : Which of the following statements with regard to the optimum cruise altitude best fuel mileage is correct ?

An aeroplane sometimes flies above the optimum cruise altitude because atc normally does not allow to fly continuously at the optimum cruise altitude

exemple 300 An aeroplane sometimes flies above the optimum cruise altitude, because atc normally does not allow to fly continuously at the optimum cruise altitude.

Question 96-28 : Which of the following statements is applicable to the acceleration height at the beginning of the 3rd climb segment ?

The maximum acceleration height depends on the maximum time take off thrust may be applied

Kaketoe .i am pretty sure that delta is also correct.please inform me if i'm wrong. .by answer 'delta' we suppose you mean there is no requirement for minimum climb performance when flying at the acceleration height .in fact the question specifically states 'at the beginning of the 3rd climb segment' so we do not talk about the entire 3rd segment .we know that the minimum acceleration height can start at 400ft it's the beginning of the 3rd segment but his upper limit even if it's not a limit depends on the maximum time take off thrust may be applied and also on the time the aircraft takes to level off exemple 304 The maximum acceleration height depends on the maximum time take-off thrust may be applied.

Question 96-29 : Which statement regarding the influence of a runway down slope is correct for a balanced take off down slope ?

Reduces v1 and reduces take off distance required todr

.a downhill slope reduces the accelerate stop distance required taking off on a downhill slope does increase the braking distance in the case of a rejected take off but it also decreases the distance taken to accelerate to v1 due to the addition of the downhill component of the weight of the aircraft increasing the rate of acceleration exemple 308 Reduces v1 and reduces take-off distance required (todr).

Question 96-30 : If the field length limited take off mass has been calculated using a balanced field length technique the use of any additional clearway in take off performance calculations may allow ?

A greater field length limited take off mass but with a lower v1

.the balanced field length is the shortest field length at which a balanced field takeoff can be performed a balanced field takeoff is a condition where the accelerate stop distance required asdr is equal to the takeoff distance required todr for the aircraft weight engine thrust aircraft configuration and runway condition .thus 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 312 A greater field length limited take off mass but with a lower v1.

Question 96-31 : Which of the following statements with regard to the actual acceleration height at the beginning of the 3rd climb segment is correct ?

The minimum value according to regulations is 400 ft

.the first segment starts at 'reference zero' and ends when the gear comes up .the second segment lasts until levelling off for flap retraction .the third segment ends when ready for the enroute climb it is usually a level burst at 400 ft during which acceleration is made to climb speed flaps are retracted and power is reduced to max continuous exemple 316 The minimum value according to regulations is 400 ft.

Question 96-32 : According to eu ops 1 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

exemple 320 When determining the maximum allowable landing mass at destination, 60% of the available landing runway length should be taken into account.

Question 96-33 : Which one of the following statements concerning drift down is correct ?

When determining the obstacle clearance during drift down fuel dumping may be taken into account

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 dumping may be taken into account exemple 324 When determining the obstacle clearance during drift-down, fuel dumping may be taken into account.

Question 96-34 : In accordance with cs25 the take off safety speed v2min for turbo propeller powered aeroplanes with more than three engines may not be less than ?

1 08 vsr

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 328 1.08 vsr.

Question 96-35 : The take off safety speed v2 for two engine or three engine turbo propeller powered aeroplanes may not be less than ?

1 13 vsr

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 332 1.13 vsr.

Question 96-36 : What is the minimum field length required for the worst wind situation landing a twin jet aeroplane with the anti skid inoperative .elevation 2000 ft.qnh 1013 hpa.landing mass 50 000 kg.flaps as required for minimum landing distance.runway condition dry.wind maximum allowable tailwind 15 kt.maximum ?

3100 m

Admin . 1127.for minimum landing distance we use flaps 40° exemple 336 3100 m.

Question 96-37 : The lowest point of the thrust required curve of a jet aeroplane is the point for ?

Minimum drag

Admin . 1083.max endurance is not a point on the thrust required curve but 'minimum drag' is exemple 340 Minimum drag.

Question 96-38 : The airspeed for jet aeroplanes at which 'power required' is minimum ?

Is always lower than the minimum drag speed

Admin . 1085.minimum power airspeed vmp is less than minimum drag speed vmd .jomargra .the graph is incorrect the red letter corresponds to vmd and the blue ones to 1 32vmd i suppose the correct answer is is the same as the minimum drag speed . .our graph shows a 'power required curve' not a 'drag curve' .the point at the bottom of the curve is vmp velocity for minimum power .the tangent to the curve is vmd velocity for minimum drag .thus vmp is less than vmd and because it is proportional to vmd it is always less .'power' is thrust required x tas .as thrust required is the same as drag power can also be written as power required = drag x tas .this will in all cases move the drag curve down and left meaning the point of minimum power vmd will be at a lower airspeed than the point of minimum drag speed vmd .power is the rate of doing work as opposed to thrust which is a force exemple 344 Is always lower than the minimum drag speed.

Question 96-39 : The speed range between low speed buffet and high speed buffet ?

Decreases with increasing mass and increasing altitude

exemple 348 Decreases with increasing mass and increasing altitude.

Question 96-40 : The danger associated with low speed and/or high speed buffet ?

Limits the manoeuvring load factor at high altitudes

.at low speed buffet you are near the conventional stall it occurs at higher speeds with altitude in the other hand high speed buffet occurs at lower speeds with altitude so at some stage the buffets will merge the margin between them called 'coffin corner' is reduced by g force caused by turning and turbulence it means that you have to avoid any manoeuvres that can result in an increase of the load factor exemple 352 Limits the manoeuvring load factor at high altitudes.


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