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The optimum long range cruise altitude for a turbojet aeroplane ? [ Control visibility ]

Question 83-1 : Increases when the aeroplane mass decreases is always equal to the powerplant ceiling is independent of the aeroplane mass is only dependent on the outside air temperature

exemple 183 Increases when the aeroplane mass decreases.Increases when the aeroplane mass decreases.

How does the specific range change when the altitude increases for jet ?

Question 83-2 : First increases then decreases decreases does not change increases only if there is no wind

.specific air range = tas / fuel flow.as altitude increases tas increases therefore specific air range increases .but as for jet aircraft maximum range in still air is achieved at maximum tas/drag ratio and approximately 95% rpm engine efficiency the speed for maximum still air range occurs at 1 32 times the speed of minimum drag as you climb past a certain height the engines go past their best efficiency so initially you increase specific fuel consumption then it decreases exemple 187 First increases then decreases.First increases then decreases.

At reference .assuming constant l/d ratio which of the diagrams provided ?

Question 83-3 : C a b d

The curve is the total drag on the 'thrust required curve' or 'drag or thrust required against airspeed' .with less mass you need less lift ==> less lift = less induced drag .induced drag will decrease displacing the total drag curve downwards and to the left .the lowest point on the curve is vmd eas for minimum drag vmd velocity minimum drag decreases exemple 191 CC

Long range cruise is a flight procedure which gives ?

Question 83-4 : A specific range which is approximately 99% of maximum specific range and a higher cruise speed a 1% higher tas for maximum specific range an ias which is 1% higher than the ias for maximum specific range a specific range which is approximately 99% of maximum specific range and a lower cruise speed

exemple 195 A specific range which is approximately 99% of maximum specific range and a higher cruise speed.A specific range which is approximately 99% of maximum specific range and a higher cruise speed.

A commercial flight is planned with a turbojet aeroplane to an aerodrome with a ?

Question 83-5 : 1 440 m 1 250 m 1 090 m 1 655 m

.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 . 2400 x 0 6 = 1440 m exemple 199 1 440 m.1 440 m.

At the destination aerodrome the landing distance available is 3000m .the ?

Question 83-6 : 1565 m 2070 m 1800 m 2609 m

.eu ops 1 515 landing dry runways allows a full stop landing from 50 ft above the threshold . 1 for turbo jet powered aeroplanes within 60% of the landing distance available .landing wet and contaminated runways a the landing distance available is at least 115% of the required landing distance determined in accordance with eu ops 1 515 .3000 m x 0 6 = 1800 m.1800 m / 1 15 = 1565 m exemple 203 1565 m.1565 m.

With zero wind the angle of attack for maximum range for an aeroplane with ?

Question 83-7 : Lower than the angle of attack corresponding to maximum endurance equal to the angle of attack corresponding to maximum endurance equal to the angle of attack corresponding to zero induced drag equal to the angle of attack corresponding to maximum lift to drag ratio

Admin . 1100.for a jet aeroplane maximum endurance is achieved at a speed corresponding to the maximum l/d ratio 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 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° .example .at 10° you are at the maximum range aoa .at 16° you are at the maximum endurance aoa . 2416 exemple 207 Lower than the angle of attack corresponding to maximum endurance.Lower than the angle of attack corresponding to maximum endurance.

Two identical turbojet aeroplane whose specific fuel consumptions are ?

Question 83-8 : 3804 kg/h 3578 kg/h 3365 kg/h 4044 kg/h

115/130 x4300 = 3803 kg/h exemple 211 3804 kg/h.3804 kg/h.

A jet aeroplane equipped with old engines has a specific fuel consumption of 0 ?

Question 83-9 : 8 17 kg/nm 11 7 kg/nm 10 7 kg/nm 14 kg/nm

14 x 0 035/0 06 = 8 1666 kg/nm exemple 215 8.17 kg/nm.8.17 kg/nm.

The determination of the maximum mass on brake release of a certified turbojet ?

Question 83-10 : 67700 kg / 15° 69000 kg / 15° 72200 kg / 5° 69700 kg / 25°

.cltom climb limited take off mass.flltom field length limited take off mass..the climb limited take off mass is based on still air so the wind correction is only applied to the runway limitation .tailwind component is 5 kt correction is 360 x 5 = 1800 kg..field length limited take off mass .runway limit for flap 5° = 66000 1800 = 64200 kg .runway limit for flap 15° = 69500 1800 = 67700 kg .runway limit for flap 25° = 71500 1800 = 69700 kg ..the climb limited take off mass remain unchanged..so maximum take off mass is 67700 kg and flap 15° exemple 219 67700 kg / 15°.67700 kg / 15°.

During certification test flights for a turbojet aeroplane the actual measured ?

Question 83-11 : 2009 m 1950 m 2096 m 2243 m

.the certificated value of the take off run is the greater of the 'all engine distance x 1 15' or 'engine out distance' ..all engine distance x 1 15 = 1747 x 1 15 = 2009 m .engine out distance = 1950 m exemple 223 2009 m.2009 m.

For a twin engine turbojet aeroplane two take off flap settings 5° and 15° ?

Question 83-12 : 56 000 kg 53 000 kg 52 000 kg 70 000 kg

Admin .we'll gonna perform a flap 15° take off . 1815.you have to be very precise when you are drawing the line otherwise you will always find something closer to 55 000kg than 56 000 kg exemple 227 56 000 kg.56 000 kg.

The lowest take off safety speed v2 min is ?

Question 83-13 : 1 13 vsr for two and three engine turbo propeller and turbojet aeroplanes 1 20 vsr for all aeroplanes 1 15 vsr for all turbojet and turbo propeller aeroplanes 1 20 vsr for all turbo propeller aeroplanes

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 231 1.13 vsr for two and three engine turbo-propeller and turbojet aeroplanes.1.13 vsr for two and three engine turbo-propeller and turbojet aeroplanes.

Which of the following three speeds of a jet aeroplane are basically identical ?

Question 83-14 : Holding maximum climb angle and minimum glide angle maximum drag maximum endurance and maximum climb angle maximum range minimum drag and minimum glide angle maximum climb angle minimum glide angle and maximum range

.holding speed for a jet is at the vmd speed vmd means velocity minimum drag this is the speed for minimum fuel consumption .for a jet aeroplane the maximum climb angle is achieved at a speed corresponding to the maximum cl/cd ratio which is vmd where the gap between power required and power available is greatest .minimum glide angle speed permits to fly the longest ground distance without wind it is achieved at a speed corresponding to the maximum cl/cd ratio which is vmd exemple 235 Holding, maximum climb angle and minimum glide angle.Holding, maximum climb angle and minimum glide angle.

The lift coefficient decreases during a glide with constant mach number mainly ?

Question 83-15 : Ias increases aircraft mass decreases tas decreases glide angle increases

.tas and ias increase during a descent at constant mach number thus we must decrease our angle of attack otherwise the lift will increase lift = 1/2 rho s v² cl and the descent may be stopped .so it is the increase in tas and ias which lead to decreasing the lift coefficient exemple 239 Ias increases.Ias increases.

During a descent at constant mach number the margin to low speed buffet will ?

Question 83-16 : Increase because the lift coefficient decreases remain constant because the mach number remains constant increase because the lift coefficient increases decrease because the lift coefficient decreases

.during a descent at constant mach number your tas increases .with increasing tas ias is increasing thus from the lift formula the lift coefficient decreases .the gap between your speed and the stall speed increases the margin to low speed buffet will increase because the lift coefficient decreases

A jet aeroplane is climbing at a constant ias and maximum climb thrust how will ?

Question 83-17 : Reduce / decrease reduce / remain constant remain constant / decrease remain constant / become larger

.to maintain a constant ias while climbing you have to reduce the climb angle power available is decreasing with an increase of altitude .and a reduction of the climb angle is done by reducing the pitch angle exemple 247 Reduce / decrease.Reduce / decrease.

A jet aeroplane is flying long range cruise how does the specific range / fuel ?

Question 83-18 : Increase / decrease increase / increase decrease / increase decrease / decrease

Jjansen .isn't it 'decrease/increase' long range cruise = 1% less range specific range decrease 4% faster fuel flow increase ..the question doesn't compare long range cruise and maximum range cruise .specific range is given as 'distance covered per unit of fuel'.as you are flying the aircraft mass decreases for the same long range cruise speed the fuel flow decreases .thus the specific range increases along the flight since for a same distance covered your fuel consumption is decreased exemple 251 Increase / decrease.Increase / decrease.

During a glide at constant mach number the pitch angle of the aeroplane will ?

Question 83-19 : Decrease increase increase at first and decrease later on remain constant

Admin .during a glide the aircraft is descending .descent + constant mach number => tas increase.see ertm diagram . 1039.the mach line is vertical because the question states a glide at constant mach number .if tas increase => pitch angle decrease to remain at constant mach exemple 255 Decrease.Decrease.

During a cruise flight of a jet aeroplane at constant flight level and at the ?

Question 83-20 : Decrease / decrease increase / decrease increase / increase decrease / increase

To maintain flight at max range speed which is the tangent to the drag curve and 1 32 vmd we must reduce speed as mass decreases to maintain 1 32 vmd the mass reduction as a consequence of fuel burn means less induced drag the total drag curve moves down and left and takes 1 32 vmd with it exemple 259 Decrease / decrease.Decrease / decrease.

An aeroplane descends from fl 410 to fl 270 at its cruise mach number and from ?

Question 83-21 : I increases ii remains constant i increases ii decreases i remains constant ii decreases i decreases ii increases

Descending at constant mach ias and tas will increase .total drag is proportional to v² drag will increase while descending and in order to maintain a constant mach number you must increased descent angle at idle thrust .at fl270 now we perform descent with a constant ias tas will decrease and density will increase and drag will stay constant our angle of descent will also stay contant exemple 263 (i) increases (ii) remains constant.(i) increases (ii) remains constant.

With a jet aeroplane the maximum climb angle can be flown at approximately ?

Question 83-22 : The maximum cl/cd ratio 1 1 vs the maximum cl/cd² ratio 1 2 vs

Admin . 1100.for a jet aeroplane the maximum climb angle is achieved at a speed corresponding to the maximum cl/cd ratio which is vmd where the gap between power required and power available is greatest exemple 267 The maximum cl/cd ratio.The maximum cl/cd ratio.

What happens to the drag of a jet aeroplane if during the initial climb after ?

Question 83-23 : The drag remains almost constant the drag increases considerably the drag decreases the drag increases initially and decreases thereafter

Admin .during initial climb if ias is maintained constant tas increases see ertm graph below and density decreases .you can maintain a constant angle of attack to produce the same lift and if lift does not change the drag remains almost constant . 1960.the eas/ias line is vertical because the question states constant ias is maintained exemple 271 The drag remains almost constant.The drag remains almost constant.

Which of the following sequences of speed for a jet aeroplane is correct . from ?

Question 83-24 : Vs maximum angle climb speed maximum range speed vs maximum range speed maximum angle climb speed maximum endurance speed maximum range speed maximum angle of climb speed maximum endurance speed long range speed maximum range speed

exemple 275 Vs, maximum angle climb speed, maximum range speed.Vs, maximum angle climb speed, maximum range speed.

If a flight is performed with a higher 'cost index' at a given mass which of ?

Question 83-25 : A higher cruise mach number a lower cruise mach number an increased maximum range an increased long range performance

Cost index is the ratio of time related costs crew salaries maintenance etc to fuel cost as one of the independent variables in the speed schedule computation . cost index ci = flight time related cost/fuel cost ..the cost index allows airlines to weight time and fuel costs based on their daily operations .a higher 'cost index' will result in a higher cruising speed . jomargra .but at a higher cruise mach number the aircraft will burn more fuel and the ci will reduce ..no we are talking about fuel cost not quantity .cost index is a made up figure which when input into the fmc is used to calculate econ speed the higher the cost index number the faster the aircraft flies basically the company decides on the cost of keeping the aircraft in the air and includes all sorts of costs such as crew aircraft operating costs fuel etc they then decide whether they want the aircraft to fly faster or slower and adjust the cost index as needed exemple 279 A higher cruise mach number.A higher cruise mach number.

For a jet transport aeroplane which of the following is the reason for the use ?

Question 83-26 : Minimum specific fuel consumption minimum fuel flow longest flight duration minimum drag

.specific fuel consumption is weight of fuel consumed per unit power per unit time .the reason for the use of 'maximum range speed' is because you want to go the far as possible .usually a commercial airplane fly at 'long range speed' which is 4% faster than 'maximum range speed' you will lose only 1% of the maximum specific range but you will save time and thus you will reduce the whole costs atc fees engines ho y costs leasing costs crew costs .if you are looking for the longest flight duration you will fly at minimum fuel flow consumption exemple 283 Minimum specific fuel consumption.Minimum specific fuel consumption.

What happens when an aeroplane climbs at a constant mach number ?

Question 83-27 : The lift coefficient increases the '1 3g' altitude is exceeded so mach buffet will start immediately the tas continues to increase which may lead to structural problems ias stays constant so there will be no problems

Admin .lift = cl x 1/2 rho v² x s.cl = lift coefficient.rho = density. v = tas in m/s .s = surface.for a standard commercial aircraft the climb is first carried out at constant ias and after the crossover altitude at constant mach number .if you look at the ertm diagram for a climb at constant ias . 1960.we can see that tas increases when altitude increases .now if you look at the ertm diagram for a climb at constant mach number . 1039.we can see that tas decreases when altitude increases .since rho decreases in both case and tas decreases when we climb at constant mach number to maintain lift we must increase our angle of attack which means an increase in lift coefficient exemple 287 The lift coefficient increases.The lift coefficient increases.

Which of the following is a reason to operate an aeroplane at 'long range speed' ?

Question 83-28 : It is efficient to fly slightly faster than with maximum range speed in order to achieve speed stability the aircraft can be operated close to the buffet onset speed in order to prevent loss of speed stability and tuck under

Jomargra .is not more efficient to fly at the maximum range speed .with a 1% less of specific range the speed can be increased to 4% more the nordian book states 'it also gives the aeroplane better handling qualities' ..long range speed is 4% faster than maximum range speed you will lose only 1% of the maximum specific range .you will save time and thus you will reduce the whole costs atc fees engines ho y costs leasing costs crew costs .maximum range speed is a certified 'safe speed' you are stable and you do not risk a loss of control exemple 291 It is efficient to fly slightly faster than with maximum range speed.It is efficient to fly slightly faster than with maximum range speed.

If the value of the balanced v1 is found to be lower than vmcg which of the ?

Question 83-29 : V1 must be increased to at least the value of vmcg the one engine out take off distance will become greater than the asdr the vmcg will be lowered to v1 the asdr will become greater than the one engine out take off distance

.vmcg is the minimum speed at which it is possible to maintain control following the failure of the critical engine during the take off run if the failure occurs before vmcg then the aircraft will go out of control and run off the side of the runway for this reason v1 must never be less than vmcg if pre take off performance calculations reveal that v1 is less than vmcg then v1 must be increased to equal vmcg exemple 295 V1 must be increased to at least the value of vmcg.V1 must be increased to at least the value of vmcg.

Reduced take off thrust should normally not be used when ?

Question 83-30 : Windshear is reported on the take off path it is dark the runway is dry the runway is wet

Apstudent46 .reduced thrust take off is used for engine life it is not permitted for . slippery runway. contamined runway. antiskid unserviceable. reverse thrust unserviceable..nadp the noise abatment departure procedure should not be used under one the following conditions . runway surface condition adversly affected. horizontal visibility < 1nm. crosswind > 15kt. tailwnd > 5kt. windshear reported or forecast. thunderstorm expected to affect approche or departure..windshear is a condition to avoid the nadp not for the reduced thrust ..the correct answer regarding jeppesen book is the wet runway ..reduced thrust is not permitted with icy or slippery runways a wet runway is defined in air law as being dark in colour and has no effect on the braking coefficient a wet runway is not dangerous .reduced thrust should not be used when anti skid is unserviceable reduced thrust should not be used when windshear is reported on the take off path exemple 299 Windshear is reported on the take-off path.Windshear is reported on the take-off path.

Reduced take off thrust should normally not be used when ?

Question 83-31 : The runway is contaminated it is dark the runway is wet obstacles are present close to the end of the runway

Apstudent46 .in jeppesen book obstacles aren't condition for 'reduced take off thrust' to be used .these 4 conditions are . runway slippery. runway contamined. antiskid unserviceable. reverse thrust unserviceable exemple 303 The runway is contaminated.The runway is contaminated.

The use of reduced take off thrust is permitted only if ?

Question 83-32 : The actual take off mass tom is lower than the field length limited tom the take off distance available is lower than the take off distance required one engine out at v1 the actual take off mass tom including a margin is greater than the performance limited tom the actual take off mass tom is greater than the climb limited tom

.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 307 The actual take-off mass (tom) is lower than the field length limited tom.The actual take-off mass (tom) is lower than the field length limited tom.

Which combination of circumstances or conditions would most likely lead to a ?

Question 83-33 : A high runway elevation and tail wind a low runway elevation and a cross wind a high runway elevation and a head wind a low runway elevation and a head wind

.conditions would most likely lead to a tyre speed limited take off are high tas high groundspeeds high temperatures tailwinds and high pressure altitudes .you need to increase take off speed since the density is reducing to gain your lift exemple 311 A high runway elevation and tail wind.A high runway elevation and tail wind.

The drift down requirements are based on ?

Question 83-34 : The obstacle clearance during a descent to the new cruising altitude if an engine has failed the actual engine thrust output at the altitude of engine failure the maximum flight path gradient during the descent the landing mass limit 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 exemple 315 The obstacle clearance during a descent to the new cruising altitude if an engine has failed.The obstacle clearance during a descent to the new cruising altitude if an engine has failed.

Which of the following statements concerning the obstacle limited take off mass ?

Question 83-35 : It should be determined on the basis of a 35 ft obstacle clearance with the respect to the 'net take off flight path' it should not be corrected for 30° bank turns in the take off path it should be calculated in such a way that there is a margin of 50 ft with respect to the 'net take off flight path' it cannot be lower than the corresponding climb limited take off mass

exemple 319 It should be determined on the basis of a 35 ft obstacle clearance with the respect to the 'net take-off flight path'.It should be determined on the basis of a 35 ft obstacle clearance with the respect to the 'net take-off flight path'.

The 'maximum tyre speed' limits ?

Question 83-36 : Vlof in terms of ground speed v1 in kt tas vr or vmu if this is lower than vr v1 in kt ground speed

.vlof the lift off speed .the speed at which the main wheels lift from the ground this speed marks an important point the end of the rolling part of the takeoff also called the end of the 'ground roll' .vmax tyre the maximum ground speed of the tyres .the highest speed that the tires can handle without becoming damaged it is possible to drive so fast that the tread actually flies of the tires if you drive fast enough the centrifugal forces become so great that the tire falls apart that must be avoided and therefore there is a maximum rolling speed for a tyre that speed is printed on the side of the tyre near the size usually a number in miles per hour .vlof &le vmax tyre in terms of ground speed exemple 323 Vlof in terms of ground speed.Vlof in terms of ground speed.

Which of the following factors determines the maximum flight altitude in the ?

Question 83-37 : Aerodynamics theoretical ceiling service ceiling economy

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 327 Aerodynamics.Aerodynamics.

Which data can be extracted from the buffet onset boundary chart ?

Question 83-38 : The values of the mach number at which low speed and mach buffet occur at various masses and altitudes the value of maximum operating mach number mmo at various masses and power settings the value of the critical mach number at various masses and altitudes the value of the mach number at which low speed and shockstall 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 331 The values of the mach number at which low speed and mach buffet occur at various masses and altitudes.The values of the mach number at which low speed and mach buffet occur at various masses and altitudes.

Why should the temperature of the wheel brakes be checked prior to take off ?

Question 83-39 : Because overheated brakes will not perform adequately in the event of a rejected take off to ensure that the brake wear is not excessive to ensure that the wheels have warmed up evenly to ensure that the thermal blow out plugs are not melted

exemple 335 Because overheated brakes will not perform adequately in the event of a rejected take-off.Because overheated brakes will not perform adequately in the event of a rejected take-off.

A jet aeroplane is climbing with constant ias which operational speed limit is ?

Question 83-40 : The maximum operating mach number the stalling speed the minimum control speed air the mach limit for the mach trim system

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 339 The maximum operating mach number.The maximum operating mach number.

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