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Question 88-1 : How does the best angle of climb and best rate of climb vary with increasing altitude for an aeroplane with a normal aspirated piston engine ? [ Attainment AIM ]

Both decrease

The higher you go the less power you will have .you can increase the angle of climb only if you have an excess of thrust or a rate of climb excess power

Question 88-2 : An operator shall ensure that the net take off flight path clears all obstacles the half width of the obstacle corridor at the distance d from the end of the toda is at least ?

90 m + 0 125 d

Admin .take off obstacle clearance . a an operator shall ensure that the take off flight path with one engine inoperative clears all obstacles by a vertical margin of at least 50 ft or by a horizontal distance of at least 90 m plus 0 125 x d where d is the horizontal distance the aeroplane has travelled from the end of the take off distance available .for aeroplanes with a wingspan of less than 60 m a horizontal obstacle clearance of half the aeroplane wingspan plus 60 m plus 0 125 x d may be used exemple 192 90 m + 0.125 d.

Question 88-3 : What is the effect of tail wind on the time to climb to a given altitude ?

The time to climb does not change

exemple 196 The time to climb does not change.

Question 88-4 : The angle of climb with flaps extended compared to that with flaps retracted will normally be ?

Smaller

Admin .we assume same mass and same speed same vertical speed all other conditions unchanged angle of climb will be smaller with flaps extended compared to that with flaps retracted for the same vertical speed center of pressure moves aft when flaps are extended thus we have to lower the nose exemple 200 Smaller.

Question 88-5 : Vx and vy with take off flaps will be ?

Lower than that for clean configuration

Admin .vx is best angle of climb speed and vy is best rate of climb speed they occur at the point where there is the biggest gap between thrust and drag vx and power required and power available vy . 1068.the deployment of flap increases profile drag which moves the red drag curve up and left you can see that vmd which is vx for a jet moves left and the gap closes between thrust available and drag so vx decreases and the angle of climb decreases . 1069.the power required curve also moves up and left with the increase in drag and the point of vy moves left and the gap closes between power required and power available .vx and vy with take off flaps will be lower than that for clean configuration exemple 204 Lower than that for clean configuration.

Question 88-6 : Other factors remaining constant how does increasing altitude affect vx and vy in terms of tas ?

Both will increase

Admin .best explanation ever .pdf929 exemple 208 Both will increase.

Question 88-7 : Considering tas for maximum range and maximum endurance other factors remaining constant ?

Both will increase with increasing altitude

Admin .in flight maximum range speed and maximum endurance speed are eas .use the very simple 'ertm' diagram ertm for e as/ r as rectified air speed or cas / t as/ m ach . 1960.the eas/ias line is vertical tas increase with increasing altitude exemple 212 Both will increase with increasing altitude.

Question 88-8 : Given that .vef= critical engine failure speed.vmcg= ground minimum control speed.vmca= air minimum control speed.vmu= minimum unstick speed.v1= take off decision speed.vr= rotation speed.v2 min= minimum take off safety speed .the correct formula is ?

Vmcg is less than or equal to vef is less than v1

Admin . vmcg it is the minimum speed on ground at which when the critical engine becomes inoperative it is possible to recover control of the airplane with the use of primary aerodynamic control alone .this maneuver must follow the guidelines . to steer only aerodynamic forces may be used . nose wheel steering is not used . rudder force may not exceed 150 lbs . cs 25 107 take off speeds . a v1 must be established in relation to vef as follows . 1 vef is the calibrated airspeed at which the critical engine is assumed to fail vef must be selected by the applicant but may not be less than vmcg determined under cs 25 149 e . 2 v1 in terms of calibrated airspeed is selected by the applicant however v1 may not be less than vef plus the speed gained with the critical engine inoperative during the.time interval between the instant at which the critical engine is failed and the instant at.which the pilot recognises and reacts to the engine failure as indicated by the pilot's.initiation of the first action e g applying brakes reducing thrust deploying speed brakes to stop the aeroplane during accelerate stop tests exemple 216 Vmcg is less than or equal to vef is less than v1.

Question 88-9 : Given .vs= stalling speed.vmca= air minimum control speed.vmu= minimum unstick speed disregarding engine failure .v1= take off decision speed.vr= rotation speed.v2 min= minimum take off safety speed.vlof lift off speed .the correct formula is ?

Vs< vmca < v2 min

Admin .vmca minimum control speed in the air is located between v1 and vr .at vs the aircraft is falling at v2min the aircraft is airborne and flyable v2min is the lowest speed at which the aircraft complies with the handling criteria associated with climb after take off following the failure of an engine exemple 220 Vs< vmca < v2 min

Question 88-10 : Regarding take off the take off decision speed v1 ?

Is the airspeed on the ground at which the pilot is assumed to have made a decision to continue or discontinue the take off

exemple 224 Is the airspeed on the ground at which the pilot is assumed to have made a decision to continue or discontinue the take-off.

Question 88-11 : An airport has a 3000 metres long runway and a 2000 metres clearway at each end of that runway .for the calculation of the maximum allowed take off mass the take off distance available cannot be greater than ?

4500 metres

Admin .the take off distance must not exceed the take off distance available with a clearway distance not exceeding half of the takeoff run available .3000 m runway + only 1500 m clearway = 4500 metres exemple 228 4500 metres.

Question 88-12 : The net flight path gradient after take off compared to the actual climb gradient is ?

Smaller

Admin . cs 25 115 take off flight path . . b the net take off flight path data must be determined so that they represent the actual take off flight paths determined in accordance with cs25 111 and with sub paragraph a of this paragraph reduced at each point by a gradient of climb equal to . 1 0 8% for two engined aeroplanes . 2 0 9% for three engined aeroplanes and. 3 1 0% for four engined aeroplanes exemple 232 Smaller.

Question 88-13 : Which of the following diagrams correctly shows the movement of the power required curve with increasing altitude h3 < h4 . 2106 ?

Figure d

Admin . 1070.tas increases with altitude from ertm graph thus the curve moves right .power required = drag x tas .if tas increases drag increases power required increases thus the curve moves up exemple 236 Figure d.

Question 88-14 : In a steady descending flight descent angle gamma equilibrium of forces acting on the aeroplane is given by . t = thrust d = drag w = weight ?

T + w sin gamma = d

Admin .a descent is a negative climb the more drag we have the steeper the descent angle is .drag thrust/weight = sin descent angle.drag = thrust + weight x sin descent angle.in descent the weight vector on the longitudinal axis of the airplane is added to thrust .this is the reason why airplane needs less energy to descent than to climb exemple 240 T + w sin gamma = d

Question 88-15 : An aeroplane executes a steady glide at the speed for minimum glide angle if the forward speed is kept constant the effect of a lower mass on the following parameters is .rate of descent / glide angle / cl/cd ratio ?

Increases / increases / decreases

Admin .the forward speed is kept constant example if the speed for minimum glide angle is 100 kt when we lower the mass we keep 100 kt .because we maintain this speed we have to increase our rate of descent to reach 100 kt thus the glide angle increases too .cl/cd ratio is reduced because lift is reduced too exemple 244 Increases / increases / decreases.

Question 88-16 : An aeroplane is in a power off glide at speed for minimum glide angle if the pilot increases pitch attitude the glide distance ?

Decreases

Admin .it doesnt matter whether the attitude is changed pitch up or pitch down there is only one attitude that gives you minimum glide angle so any change from it will decrease the distance you glide .the glide angle is the angle of the slope on which the aircraft is descending therefore a minimum glide angle is the smallest angle for this slope and hence the shallowest exemple 248 Decreases.

Question 88-17 : Which of the following combinations basically has an effect on the angle of descent in a glide . ignore compressibility effects ?

Configuration and angle of attack

Admin .your angle of glide/descent is a function of lift/drag ratio all you have to do is fly at vmd velocity minimum drag for your aircraft which means flying at the correct angle of attack then of course extending flap or airbrake or change propeller pitch configuration will also have an effect exemple 252 Configuration and angle of attack.

Question 88-18 : Two identical aeroplanes at different masses are descending at idle thrust .which of the following statements correctly describes their descent characteristics ?

At a given angle of attack both the vertical and the forward speed are greater for the heavier aeroplane

exemple 256 At a given angle of attack, both the vertical and the forward speed are greater for the heavier aeroplane.

Question 88-19 : Compared with still air the effect a headwind has on the values of the maximum range speed and the maximum gradient climb speed respectively is that .attention on parle de la vitesse de meilleur angle de montée et non pas du meilleur angle de montée .la question du livre de qcm de l'institut ?

The maximum range speed increases and the maximum gradient climb speed is not affected

Admin . maximum range speed increases .when striving for maximum range it is advantageous to reduce the time of exposure to a headwind component and increase the time of exposure to a tailwind component .. maximum gradient climb speed .the speed is not affected the ground distance will be reduce with a headwind ground speed is different the gradient over the ground changes but vx speed stays constant .the maximum climb angle speed vx vmd for a jet 1 1vs for a prop is unaffected by wind because the object is to achieve maximum angle exemple 260 The maximum range speed increases and the maximum gradient climb speed is not affected.

Question 88-20 : The maximum speed in horizontal flight occurs when ?

The maximum thrust is equal to the total drag

Admin .as long as available thrust exceeds required thrust in level flight the aircraft will accelerate once drag increases to equal maximum thrust the aircraft will not accelerate thus the maximum speed is achieved when maximum thrust is equal to the total drag exemple 264 The maximum thrust is equal to the total drag.

Question 88-21 : With respect to the optimum altitude which of the following statements is correct ?

An aeroplane sometimes flies above or below the optimum altitude because optimum altitude increases continuously during flight

exemple 268 An aeroplane sometimes flies above or below the optimum altitude because optimum altitude increases continuously during flight.

Question 88-22 : How does the lift coefficient for maximum range vary with altitude . no compressibility effects ?

The lift coefficient is independent of altitude

Admin .when flying at range speed regardless of altitude you will be at 1 32vmd velocity minimum drag on the drag curve for a jet where alpha will be about 2 degrees and at vmd for the propeller where alpha is about 4 degrees . 1135 exemple 272 The lift coefficient is independent of altitude.

Question 88-23 : The speed for maximum lift/drag ratio will result in ?

The maximum range for a propeller driven aeroplane

Admin . 1135. the speed for maximum lift/drag ratio l/d max will result in the maximum range for a propeller driven aeroplane .for the propeller driven aeroplane curve the lowest point of the power required curve is the tas at wich the least power is needed as opposed to producing the least drag and is therefore the best for endurance in level flight it is also the maximum rate of climb speed because the gap between power required and power available is greatest more power is needed above and below the minimum power speed exemple 276 The maximum range for a propeller driven aeroplane.

Question 88-24 : Which of the following provides maximum obstacle clearance during climb ?

The speed for maximum climb angle vx

exemple 280 The speed for maximum climb angle vx.

Question 88-25 : Which of the following factors will lead to an increase of ground distance during a glide while maintaining the appropriate minimum glide angle speed ?

Tailwind

Admin .by maintaining the appropriate minimum glide angle speed it permits to fly the longest ground distance without wind thus the only way to increase the ground distance is to benefit from a tailwind exemple 284 Tailwind.

Question 88-26 : Which of the following factors leads to the maximum flight time of a glide ?

Low mass

.the wind affects only the ground distance .to maintain the flight as longer as possible you must have the lowest rate of descent this rate of descent varies with mass .for a heavier aircraft the lowest rate of descent speed is reach at a higher speed than when this aircraft is empty total drag is proportional to v² therefore his rate of descent is increased exemple 288 Low mass.

Question 88-27 : When v1 has to be reduced because of a wet runway the one engine out obstacle clearance / climb performance ?

Decreases / remains constant

.v1 has to be reduce because in case of stop on a wet runway we will reduce our speed slower than on a dry runway .obstacle clearance decreases if failure occurs after v1 because from v1 to vr we will gain speed on one engine only by decreasing v1 due to the wet runway the take off distance to reach our screen height will be increased margin from obstacle will be reduced .now our climb performance remains constant because it is not affected by the value of v1 we are now flying the question states 'how does v1 affect the one engine out climb performance' our climb performance are not affected by v1 exemple 292 Decreases / remains constant.

Question 88-28 : Which statement concerning the inclusion of a clearway in take off calculation is correct ?

The field length limited take off mass will increase

.a clearway is an area beyond the paved runway free of obstacles the length of the clearway may be included in the length of the take off distance available toda . 771..our maximum takeoff distance is limited by this condition .we must be at 35 ft at the end of toda with an engine out .the takeoff run available is increased we can take off at a later point the field length limited take off mass will increase .the acceleration stop distance available asda remains the same we are not allowed to stop on the clearway this is not a stopway thus v1 is decreased because after passing v1 we must be able to take off with an engine out and make 35 ft within toda . /com en/com032 109b jpg.in both cases v1 must decrease imagine if you maintain v1 at 100 kt what will happen exemple 296 The field length limited take-off mass will increase.

Question 88-29 : Which of the following factors favours the selection of a low flap setting for the take off ?

High field elevation distant obstacles in the climb out path long runway and a high ambient temperature

Admin .obstacles are distant we have a long runway low flap setting will increase the ground run but increases the climb capabilities .the use of flaps is especially beneficial for a short runway with no obstacles or only a low obstacle further away not using flaps is beneficial for a very long runway with a nearby obstacle the picture below shows the choices in a somewhat exaggerated way . 1074 exemple 300 High field elevation, distant obstacles in the climb-out path, long runway and a high ambient temperature.

Question 88-30 : How is v2 affected if t/o flaps 20° is chosen instead of t/o flaps 10° ?

V2 decreases if not restricted by vmca

.vmca minimum control speed in the air is located between v1 and vr .at vs the aircraft is falling at v2min the aircraft is airborne and flyable v2min is the lowest speed at which the aircraft complies with the handling criteria associated with climb after take off following the failure of an engine .basically more flaps will decrease the v speeds in this case since more flaps will result in a lower v1 and vr v2 will also decrase since flaps do decrease stall speed more flaps will reduce the v2 speed unless it is limited by vmca vmca can be high at low pressure altitudes low temperature and low humidity and will be limiting at the lower weights regardless of flap setting exemple 304 V2 decreases if not restricted by vmca.

Question 88-31 : During the flight preparation the climb limited take off mass tom is found to be much greater than the field length limited tom using 5° flap in what way can the performance limited tom be increased .there are no limiting obstacles ?

By selecting a higher flap setting

. the climb limited take off mass tom is found to be much greater than the field length limited tom it means that our first limitation is the runway lenght .you will take off earlier by selecting a higher flap setting but your climb angle will be reduced this is not a problem here since the question states there are no limiting obstacles exemple 308 By selecting a higher flap setting.

Question 88-32 : If on a particular flight the value of v1 used on take off exceeds the correct value of v1 if an engine fails at a speed immediately above the correct value of v1 then ?

The accelerate/stop distance will exceed the accelerate/stop distance available

exemple 312 The accelerate/stop distance will exceed the accelerate/stop distance available.

Question 88-33 : Which is the correct sequence of speeds during take off ?

Vmcg v1 vr v2

Img1459.v1 critical engine failure speed or decision speed engine failure below this speed should result in an aborted takeoff above this speed the takeoff run should be continued .vr speed at which the rotation of the airplane is initiated to takeoff attitude this speed cannot.be less than v1 or less than 1 05 x vmca minimum control speed in the air .vmcg the minimum control speed in the ground .vlof the speed at which the airplane first becomes airborne this is an engineering term used when the airplane is certificated and must meet certain requirements if it is not listed in the airplane flight manual it is within requirements and does not have to be taken into consideration by the pilot exemple 316 Vmcg, v1, vr, v2.

Question 88-34 : Regarding the obstacle limited take off mass which of the following statements is correct ?

A take off in the direction of an obstacle is also permitted in tail wind condition

.when you perform calculation for take off on a graph you have a 'wind reference line' for tailwind or headwind adjustement .there is no restriction for a take off with tail wind until a certain value and in the case of an obstacle on the take off path it will redude the allowed take off mass that's all exemple 320 A take-off in the direction of an obstacle is also permitted in tail wind condition.

Question 88-35 : When an aircraft takes off with the mass limited by the toda ?

The actual take off mass equals the field length limited take off mass

.the field length limited take off mass is based upon the most restrictive distance of tora toda or asda and the ambient conditions pressure altitude and temperature .here the answer states that the actual take off mass is limited by toda it could have also said the actual take off mass is limited by asda or tora .tora take off run available .toda take off distance available .asda acceleration stop available exemple 324 The actual take-off mass equals the field length limited take-off mass.

Question 88-36 : For a take off from a contaminated runway which of the following statements is correct ?

The performance data for take off must be determined in general by means of calculation only a few values are verified by flight tests

.you must use graphs or data sheets which give you the performance data for take off .the take off mass is always reduced by a pre determined amount depending on the depth of contaminant exemple 328 The performance data for take-off must be determined in general by means of calculation, only a few values are verified by flight tests.

Question 88-37 : To minimize the risk of hydroplaning during landing the pilot should ?

Make a 'positive' landing and apply maximum reverse thrust and brakes as quickly as possible

exemple 332 Make a 'positive' landing and apply maximum reverse thrust and brakes as quickly as possible.

Question 88-38 : The stopway is an area which allows an increase only in the ?

Accelerate stop distance available

Admin .a clearway is an area beyond the paved runway free of obstacles the length of the clearway may be included in the length of the take off distance available toda . 771.but we are not allowed to stop on the clearway this is not a stopway .a stopway means an area beyond the take off runway no less wide than the runway and centred upon the extended centreline of the runway able to support the aeroplane during an abortive take off without causing structural damage to the aeroplane and designated by the airport authorities for use in decelerating the aeroplane during an abortive take off . 1851.the stopway is an area which allows an increase only in the accelerate stop distance available exemple 336 Accelerate-stop distance available.

Question 88-39 : Vr cannot be lower than ?

V1 and 105% of vmca

exemple 340 V1 and 105% of vmca.

Question 88-40 : The one engine out take off run is the distance between the brake release point and ?

The middle of the segment between vlof point and 35 ft point

Admin .the one engine out take off run tor n 1 is defined as from the brake release point to a point equidistant between vlof and 35 ft . 1076 exemple 344 The middle of the segment between vlof point and 35 ft point.


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