For a turboprop powered aeroplane a 2200 m long runway at the destination ? [ Free topography ]

Question 95-1 : 1339 m 1771 m 1540 m 1147 m

exemple 195 1339 m. — 2200/1 15 x 0 7 = 1339 m..notice .0 7 turboprop .0 6 turbojet ..factor 1 15 for a wet runway . brudef .isn't it asked the 'dry runway' landing distance in that case 1 15 shouldn't be taken into account ..the runway at destination is expected to be 'wet' you must be able to stop your aeroplane in the wet required landing distance even if at the time of arrival the runway is dry 1339 m.

Characteristics of a three engine turbojet aeroplane are as follows .thrust = ?

Question 95-2 : 101 596 kg 74 064 kg 209 064 kg 286 781 kg

exemple 199 101 596 kg. — Sin angle of climb = thrust drag / weight .or .weight = thrust drag / sin angle of climb .weight = 50000x2 72569 / 0 027.weight = 1015960 n.divide newtons by g = 101596 kg .as we are calculating maximum take off mass for a path to avoid obstacles we must assume one engine out unless the question states otherwise our available thrust is only 2x50000 n . amassa .i'm missing something with the formula explanation .it says .weight = thrust drag / sin angle of climb .weight = 50000 x2 72569 / 0 027.but sin angle of climb is 0 047 .0 027 is angle of climb / 100..2 7% express as a decimal is 0 027 .angle = arctan 0 027 = 1 55°.sin 1 55° = 0 027 101 596 kg.

Minimum control speed on the ground 'vmcg' is based on directional control ?

Question 95-3 : Primary aerodynamic control only primary aerodynamic control and nose wheel steering primary aerodynamic control nose wheel steering and differential braking nose wheel steering only

exemple 203 Primary aerodynamic control only. — Primary aerodynamic control only.

Which of the following represents the maximum value for v1 assuming max tyre ?

Question 95-4 : Vr vmca v2 vref

exemple 207 Vr. — Admin . 1459.note vmca minimum control speed in the air is located between v1 and vr but vmca is not the maximum value for v1 .vr is the speed at which the rotation of the airplane is initiated to takeoff attitude Vr.

During certification flight testing on a four engine turbojet aeroplane the ?

Question 95-5 : 3050 m 2938 m 3513 m 2555 m

exemple 211 3050 m. — .you multiply the all engine performance by 1 15 and then compare to the one engine inoperative distance you take the higher figure .all engines operating distance = 2555 x 1 15 = 2938 m .3050 m distance with failure of the critical engine recognised at v1 is the highest distance adopted for the certification file 3050 m.

In which of the following distances can the length of a stopway be included ?

Question 95-6 : In the accelerate stop distance available in the one engine failure case take off distance in the all engine take off distance in the take off run available

exemple 215 In the accelerate stop distance available. — In the accelerate stop distance available.

At which minimum height will the second climb segment end ?

Question 95-7 : 400 ft above field elevation 35 ft above ground when gear retraction is completed 1500 ft above field elevation

exemple 219 400 ft above field elevation. — .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 400 ft above field elevation.

How does tas vary in a constant mach climb in the troposphere under isa ?

Question 95-8 : Tas decreases tas increases tas is constant tas is not related to mach number

exemple 223 Tas decreases. — Admin .for those questions use the very simple 'ertm' diagram . 1039.the mach line is vertical because the question states in a constant climb mach . ertm for e as/ r as rectified air speed or cas / t as/ m ach .mach number = tas / local sound speed .the velocity of sound is decreasing as temperature decreases to maintain constant mach as the velocity of sound reduces tas has to reduce Tas decreases.

The optimum long range cruise altitude for a turbojet aeroplane ?

Question 95-9 : 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 227 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 95-10 : First increases then decreases decreases does not change increases only if there is no wind

exemple 231 First increases then decreases. — .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 First increases then decreases.

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

Question 95-11 : C a b d

exemple 235 C — 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 C

Long range cruise is a flight procedure which gives ?

Question 95-12 : 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 239 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 95-13 : 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

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

Question 95-14 : 1565 m 2070 m 1800 m 2609 m

exemple 247 1565 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 1565 m.

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

Question 95-15 : 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

exemple 251 Lower than the angle of attack corresponding to maximum endurance. — 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 Lower than the angle of attack corresponding to maximum endurance.

Two identical turbojet aeroplane whose specific fuel consumptions are ?

Question 95-16 : 3804 kg/h 3578 kg/h 3365 kg/h 4044 kg/h

exemple 255 3804 kg/h. — 115/130 x4300 = 3803 kg/h 3804 kg/h.

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

Question 95-17 : 8 17 kg/nm 11 7 kg/nm 10 7 kg/nm 14 kg/nm

exemple 259 8.17 kg/nm. — 14 x 0 035/0 06 = 8 1666 kg/nm 8.17 kg/nm.

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

Question 95-18 : 67700 kg / 15° 69000 kg / 15° 72200 kg / 5° 69700 kg / 25°

exemple 263 67700 kg / 15°. — .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° 67700 kg / 15°.

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

Question 95-19 : 2009 m 1950 m 2096 m 2243 m

exemple 267 2009 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 2009 m.

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

Question 95-20 : 56 000 kg 53 000 kg 52 000 kg 70 000 kg

exemple 271 56 000 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 56 000 kg.

The lowest take off safety speed v2 min is ?

Question 95-21 : 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

exemple 275 1.13 vsr for two and three engine turbo-propeller and turbojet 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 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 95-22 : 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

exemple 279 Holding, maximum climb angle and minimum glide angle. — .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 Holding, maximum climb angle and minimum glide angle.

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

Question 95-23 : Ias increases aircraft mass decreases tas decreases glide angle increases

exemple 283 Ias 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 Ias increases.

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

Question 95-24 : 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

exemple 287 Increase, 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 Increase, because the lift coefficient decreases.

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

Question 95-25 : Reduce / decrease reduce / remain constant remain constant / decrease remain constant / become larger

exemple 291 Reduce / decrease. — .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 Reduce / decrease.

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

Question 95-26 : Increase / decrease increase / increase decrease / increase decrease / decrease

exemple 295 Increase / 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 Increase / decrease.

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

Question 95-27 : Decrease increase increase at first and decrease later on remain constant

exemple 299 Decrease. — 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 Decrease.

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

Question 95-28 : Decrease / decrease increase / decrease increase / increase decrease / increase

exemple 303 Decrease / decrease. — 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 Decrease / decrease.

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

Question 95-29 : I increases ii remains constant i increases ii decreases i remains constant ii decreases i decreases ii increases

exemple 307 (i) increases (ii) remains constant. — 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 (i) increases (ii) remains constant.

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

Question 95-30 : The maximum cl/cd ratio 1 1 vs the maximum cl/cd² ratio 1 2 vs

exemple 311 The maximum cl/cd ratio. — 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 The maximum cl/cd ratio.

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

Question 95-31 : The drag remains almost constant the drag increases considerably the drag decreases the drag increases initially and decreases thereafter

exemple 315 The drag remains almost constant. — 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 The drag remains almost constant.

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

Question 95-32 : 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 319 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 95-33 : A higher cruise mach number a lower cruise mach number an increased maximum range an increased long range performance

exemple 323 A higher cruise mach number. — 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 A higher cruise mach number.

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

Question 95-34 : Minimum specific fuel consumption minimum fuel flow longest flight duration minimum drag

exemple 327 Minimum specific fuel consumption. — .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 Minimum specific fuel consumption.

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

Question 95-35 : 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

exemple 331 The lift coefficient increases. — 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 The lift coefficient increases.

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

Question 95-36 : 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

exemple 335 It is efficient to fly slightly faster than with maximum range speed. — 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 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 95-37 : 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

exemple 339 V1 must be increased to at least the value of vmcg. — .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 V1 must be increased to at least the value of vmcg.

Reduced take off thrust should normally not be used when ?

Question 95-38 : Windshear is reported on the take off path it is dark the runway is dry the runway is wet

exemple 343 Windshear is reported on the take-off path. — 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 Windshear is reported on the take-off path.

Reduced take off thrust should normally not be used when ?

Question 95-39 : The runway is contaminated it is dark the runway is wet obstacles are present close to the end of the runway

exemple 347 The runway is contaminated. — 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 The runway is contaminated.

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

Question 95-40 : 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

exemple 351 The actual take-off mass (tom) is lower than the field length 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 The actual take-off mass (tom) is lower than the field length limited tom.

~

Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

3759 Free Training Exam