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The lowest point of the thrust required curve of a jet aeroplane is the point ? [ Attainment AIM ]

Question 97-1 : Minimum drag maximum specific range maximum endurance minimum specific range

Admin . 1083.max endurance is not a point on the thrust required curve but 'minimum drag' is exemple 197 Minimum drag.Minimum drag.

The airspeed for jet aeroplanes at which 'power required' is minimum ?

Question 97-2 : Is always lower than the minimum drag speed is always higher than the minimum drag speed is lower than the minimum drag speed in the climb and higher than the minimum drag speed in the descent is the same as 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 201 Is always lower than the minimum drag speed.Is always lower than the minimum drag speed.

The speed range between low speed buffet and high speed buffet ?

Question 97-3 : Decreases with increasing mass and increasing altitude decreases with increasing mass and is independent of altitude is only limiting at low altitudes increases with increasing mass

exemple 205 Decreases with increasing mass and increasing altitude.Decreases with increasing mass and increasing altitude.

The danger associated with low speed and/or high speed buffet ?

Question 97-4 : Limits the manoeuvring load factor at high altitudes can be reduced by increasing the load factor exists only above mmo has to be considered at take off and landing

.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 209 Limits the manoeuvring load factor at high altitudes.Limits the manoeuvring load factor at high altitudes.

Which of the jet engine ratings below is not a certified rating ?

Question 97-5 : Maximum cruise thrust maximum continuous thrust go around thrust maximum take off thrust

exemple 213 Maximum cruise thrust.Maximum cruise thrust.

At constant thrust and constant altitude the fuel flow of a jet engine ?

Question 97-6 : Increases slightly with increasing airspeed is independent of the airspeed decreases slightly with increasing airspeed increases with decreasing oat

.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 217 Increases slightly with increasing airspeed.Increases slightly with increasing airspeed.

The thrust of a jet engine at constant rpm ?

Question 97-7 : Increases in proportion to the airspeed does not change with changing altitude is independent of the airspeed is inversely proportional 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 221 Increases in proportion to the airspeed.Increases in proportion to the airspeed.

A higher altitude at constant mass and mach number requires ?

Question 97-8 : A higher angle of attack a lower coefficient of lift a lower coefficient of drag a lower 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 225 A higher angle of attack.A higher angle of attack.

The long range cruise speed is selected because ?

Question 97-9 : The higher speed achieves 99% of the maximum still air range it is the best speed for economy it is the cruise climb speed for one or two engines inoperative it achieves the specific range with a headwind

exemple 229 The higher speed achieves 99% of the maximum still-air range.The higher speed achieves 99% of the maximum still-air range.

The optimum altitude ?

Question 97-10 : Increases as mass decreases and is the altitude at which the specific range reaches its maximum decreases as mass decreases is the altitude at which the specific range reaches its minimum is the altitude up to which cabin pressure of 8 000 ft can be maintained

exemple 233 Increases as mass decreases and is the altitude at which the specific range reaches its maximum.Increases as mass decreases and is the altitude at which the specific range reaches its maximum.

The engine failure take off run is ?

Question 97-11 : 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 1 5 times the distance from the point of brake release to a point equidistant between the point at which vlof is reached and the point at which the aeroplane attains a height of 35 ft above the runway with all engines operative 1 15 times the distance from the point of brake release to the point at which vlof is reached assuming a failure of the critical engine at v1 the distance of the point of brake release to a point equidistant between the point at which vlof is reached and the point at which the aeroplane attains a height of 50 ft above the runway assuming a failure of the critical engine at v1

exemple 237 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.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.

Reduced take off thrust ?

Question 97-12 : Has the benefit of improving engine life can be used if the actual take off mass is higher than the performance limited take off mass is not recommended at very low temperatures oat can be used if the headwind component during take off is at least 10 kt

A 'balanced field length' is said to exist where ?

Question 97-13 : The accelerate stop distance is equal to the take off distance available the clearway does not equal the stopway the accelerate stop distance is equal to the all engine take off distance the one engine out take off distance is equal to the all engine take off distance

exemple 245 The accelerate stop distance is equal to the take-off distance available.The accelerate stop distance is equal to the take-off distance available.

The optimum cruise altitude increases ?

Question 97-14 : If the aeroplane mass is decreased if the temperature oat is increased if the tailwind component is decreased if the aeroplane mass is increased

Below the optimum cruise altitude ?

Question 97-15 : The mach number for long range cruise decreases continuously with decreasing altitude the ias for long range cruise increases continuously with decreasing altitude the tas for long range cruise increases continuously with decreasing altitude the mach number for long range cruise increases 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 253 The mach number for long range cruise decreases continuously with decreasing altitude.The mach number for long range cruise decreases continuously with decreasing altitude.

If after experiencing an engine failure when cruising above the one engine ?

Question 97-16 : Drift down procedure emergency descent procedure etops long range cruise descent

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 257 Drift down procedure.Drift down procedure.

'drift down' is the procedure to be applied ?

Question 97-17 : After engine failure if the aeroplane is above the one engine out maximum altitude after cabin depressurization to conduct an instrument approach at the alternate to conduct a visual approach with one engine out

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

If the level off altitude is below the obstacle clearance altitude during a ?

Question 97-18 : Fuel jettisoning should be started at the beginning of drift down the recommended drift down speed should be disregarded and it should be flown at the stall speed plus 10 kt fuel jettisoning should be started when the obstacle clearance altitude is reached the drift down should be flown with flaps in the approach configuration

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 265 Fuel jettisoning should be started at the beginning of drift down.Fuel jettisoning should be started at the beginning of drift down.

The landing field length required for turbojet aeroplanes at the destination ?

Question 97-19 : 92% 67% 70% 43%

.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 269 92%.92%.

The landing field length required for jet aeroplanes at the alternate wet ?

Question 97-20 : 92% 43% 70% 67%

.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 273 92%.92%.

The speed vsr is defined as ?

Question 97-21 : As reference stall speed and may not be less than 1 g stall speed safe rotation speed for take off design stress speed speed for best specific range

exemple 277 As reference stall speed and may not be less than 1-g stall speed.As reference stall speed and may not be less than 1-g stall speed.

The speed v2 is defined for jet aeroplane as ?

Question 97-22 : Take off climb speed or speed at 35 ft lift off speed take off decision speed critical engine failure speed

exemple 281 Take-off climb speed or speed at 35 ft.Take-off climb speed or speed at 35 ft.

The aerodynamic ceiling ?

Question 97-23 : Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same depends upon thrust setting and increase with increasing thrust is the altitude at which the best rate of climb theoretically is zero is the altitude at which the aeroplane reaches 50 ft/min

Admin .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 285 Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.

'stepped climbs' are used on long distance flights ?

Question 97-24 : To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces only if the headwind is less or the tailwind is greater than forecast at high altitude for piston engined aeroplanes only not for jet aeroplanes to fly as close to the tropopause as possible

exemple 289 To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.

The climb gradientafter take off in a standard atmosphere and still air at 0 ft ?

Question 97-25 : 3 9 % 4 3 % 4 7 % 4 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 293 3.9 %.3.9 %.

The drift down procedure specifies requirements concerning the ?

Question 97-26 : Obstacle clearance after engine failure engine power at the altitude at which engine failure occurs climb gradient during the descent to the net level off altitude weight during landing at the alternate

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 297 Obstacle clearance after engine failure.Obstacle clearance after engine failure.

Given a jet aircraft which order of increasing speeds in the performance ?

Question 97-27 : Vs vx maximum range speed maximum endurance speed long range speed maximum range speed vs maximum range speed vx maximum endurance speed maximum range speed vx

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 301 Vs, vx, maximum range speed.Vs, vx, maximum range speed.

When determining the maximum landing mass of an turbojet powered aeroplane ?

Question 97-28 : 0 60 115/100 1 67 60/115

.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 305 0.60.0.60.

On a segment of the take off flight path an obstacle requires a minimum ?

Question 97-29 : 118455 kg 102150 kg 106425 kg 121310 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 309 118455 kg.118455 kg.

Which statement with respect to the step climb is correct ?

Question 97-30 : Performing a step climb based on economy can be limited by the 1 3g buffet onset requirements in principle a step climb is performed immediately after the aircraft has exceeded the optimum altitude a step climb can only be performed when the altitude exceeds the one engine out service ceiling a step climb provides better economy than a optimum cruise

.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 313 Performing a step climb based on economy can be limited by the 1.3g buffet onset requirements.Performing a step climb based on economy can be limited by the 1.3g buffet onset requirements.

In accordance to cs 25 which of the following listed speeds are used for ?

Question 97-31 : Vsr vmca vmcg v2 vlof vmca v1 vr

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 317 Vsr, vmca.Vsr, vmca.

Reduced take off thrust should normally not be used when ?

Question 97-32 : Anti skid is not usable it is dark the runway is wet obstacles are present close to the end of the runway

.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 321 Anti skid is not usable.Anti skid is not usable.

Maximum tyre speed can limit the lift off speed which kind of speed can be ?

Question 97-33 : Groundspeed ias tas ess

exemple 325 Groundspeed.Groundspeed.

According to cs 25 the landing reference speed vref may not be less than ?

Question 97-34 : 1 23 vsr0 and must be maintained down to 50 ft height vsr0 and must be maintained down to 35 ft height 1 23 vsr0 for turbojet powered and 1 30 for turboprop powered aeroplanes 1 2 vmca

.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 329 1.23 vsr0 and must be maintained down to 50 ft height.1.23 vsr0 and must be maintained down to 50 ft height.

Which statement with respect to the step climb is correct ?

Question 97-35 : Executing a desired step climb at high altitude can be limited by buffet onset at g loads greater than 1 a step climb must be executed immediately after the aeroplane has exceeded the optimum altitude a step climb is executed because atc desires a higher altitude a step climb is executed in principle when just after levelling off the 1 3g altitude is reached

.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 333 Executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1.Executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1.

Select from the following list of conditions those that must prevail in the ?

Question 97-36 : 1 4 6 9 1 5 8 10 2 3 6 9 1 4 5 10

exemple 337 1, 4, 6, 9.1, 4, 6, 9.

V1 for a balanced field is calculated when ?

Question 97-37 : The acceleration/stop distance available is equal to the take off distance available the take off mass is field length limited by the stopway to produce the maximum take off mass the speed is equal to v2 the take off mass is field length limited by the clearway to produce the maximum take off mass

exemple 341 The acceleration/stop distance available is equal to the take-off distance available.The acceleration/stop distance available is equal to the take-off distance available.

With regard to the drift down performance of the twin jet aeroplane why does ?

Question 97-38 : Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level because at this mass the engines slow down at a slower rate after failure there is still some thrust left during four minutes due to higher tas at this mass it takes more time to develop the optimal rate of descent because of the inertia involved all the curves start at the same point which is situated outside the chart

Admin . 2519.you will stay at the original cruising level until you reach the optimum speed for descent exemple 345 Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

The requirements of the take off net flight path for a class a aeroplane assume ?

Question 97-39 : The failure of the critical engine of a multi engined aeroplane at vef the failure of any engine of a multi engined aeroplane at vef the failure of any engine of a multi engined aeroplane at vr the failure of two engines of a three engined or four engined aeroplane at vef

exemple 349 The failure of the critical engine of a multi-engined aeroplane at vef.The failure of the critical engine of a multi-engined aeroplane at vef.

The angle of attack required to attain the maximum still air range for a turbo ?

Question 97-40 : Less than that for the maximum lift to drag ratio the same as that for the maximum endurance the same as that giving zero induced drag greater 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 353 Less than that for the maximum lift to drag ratio.Less than that for the maximum lift to drag ratio.

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