Un compte Premium offert sur le site FCL.055 ! Rendez-vous sur www.fcl055-exam.fr puis créez un compte avec le même email que celui...   [Lire la suite]


Exercise > lift > off : What affect has a tailwind on the maximum endurance speed ?

Question 75-1 : No affect tailwind only effects holding speed the ias will be increased the ias will be decreased

exemple 175 no affect.no affect.

During climb with all engines the altitude where the rate of climb reduces to ?

Question 75-2 : Service ceiling absolute ceiling thrust ceiling aerodynamic ceiling

exemple 179 service ceiling.service ceiling.

The maximum rate of climb that can be maintained at the absolute ceiling is ?

Question 75-3 : 0 ft/min 125 ft/min 500 ft/min 100 ft/min

exemple 183 0 ft/min.0 ft/min.

A twin engine aeroplane is flying at the minimum control speed with take off ?

Question 75-4 : Straight flight straight flight and altitude heading altitude and a positive rate of climb of 100 ft/min altitude

. minimum control speed is vmca minimum control speed in the air vmca is located between v1 and vr .vmca is a controlling speed where straight flight can be maintained when the critical engine has failed exemple 187 straight flight.straight flight.

The speed v2 is ?

Question 75-5 : The take off safety speed that speed at which the pic should decide to continue or not the take off in the case of an engine failure the lowest airspeed required to retract flaps without stall problems the lowest safety airspeed at which the aeroplane is under control with aerodynamic surfaces in the case of an engine failure

exemple 191 the take-off safety speed.the take-off safety speed.

Which take off speed is affected by the presence or absence of stopway and/or ?

Question 75-6 : V1 v2 vmcg vmca

exemple 195 v1.v1.

Maximum and minimum values of v1 are limited by ?

Question 75-7 : Vr and vmcg v2 and vmca vr and vmca v2 and vmcg

exemple 199 vr and vmcg.vr and vmcg.

Take off run is defined as the ?

Question 75-8 : 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 distance to v1 and stop assuming an engine failure at v1 distance to 35 feet with an engine failure at v1 or 115% all engine distance to 35 feet distance from brake release to v2

exemple 203 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.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 minimum value of v2 must exceed vmc by ?

Question 75-9 : 10% 15% 20% 30%

.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 exemple 207 10%.10%.

Which of the following is true according to the relevant regulations for turbo ?

Question 75-10 : Maximum landing distance at the destination aerodrome and at any alternate aerodrome is 0 7 x lda landing distance available maximum landing distance at destination is 0 95 x lda landing distance available maximum take off run is 0 5 x runway maximum use of clearway is 1 5 x runway

exemple 211 maximum landing distance at the destination aerodrome and at any alternate aerodrome is 0.7 x lda (landing distance available).maximum landing distance at the destination aerodrome and at any alternate aerodrome is 0.7 x lda (landing distance available).

For take off obstacle clearance calculations obstacles may be avoided ?

Question 75-11 : By banking not more than 15° between 50 ft and 400 ft above the runway elevation by banking as much as needed if aeroplane is more than 50 ft above runway elevation only by using standard turns by standard turns but only after passing 1500 ft

exemple 215 by banking not more than 15° between 50 ft and 400 ft above the runway elevation.by banking not more than 15° between 50 ft and 400 ft above the runway elevation.

The speed vr ?

Question 75-12 : Is the speed at which rotation to the lift off angle of attack is initiated must be higher than v2 must be higher than vlof must be equal to or lower than v1

exemple 219 is the speed at which rotation to the lift-off angle of attack is initiated.is the speed at which rotation to the lift-off angle of attack is initiated.

If the take off mass of an aeroplane is brake energy limited a higher uphill ?

Question 75-13 : Increase the maximum mass for take off decrease the maximum mass for take off have no effect on the maximum mass for take off decrease the required take off distance

.if the runway has an uphill slope it will help to stop and the question states that the mass is only limited by brake energy in that particular case an uphill slope permits to increase the maximum mass for take off exemple 223 increase the maximum mass for take-off.increase the maximum mass for take-off.

If the take off mass of an aeroplane is tyre speed limited downhill slope would ?

Question 75-14 : Have no effect on the maximum mass for take off decrease the maximum mass for take off increase the maximum mass for take off increase the required take off distance

.your weight limitation at take off is due to a maximum tyre speed restriction in other words your maximum mass for take off is tyre speed limited .with a downhill slope you will accelerate to v1 faster thus reaching vr in a smaller distance and that's all .it will not increase or decrease the maximum mass for take off it will only reduce the required take off distance. dalton .why q25 has another answer..q25 is not talking about an aeroplane which is tyre speed limited . q25 how does runway slope affect allowable take off mass assuming other factors remain constant and not limiting .answer a downhill slope increases allowable take off mass exemple 227 have no effect on the maximum mass for take-off.have no effect on the maximum mass for take-off.

The take off mass could be limited by ?

Question 75-15 : The take off distance available toda the maximum brake energy and the climb gradient with one engine inoperative the take off distance available toda only the maximum brake energy only the climb gradient with one engine inoperative only

exemple 231 the take-off distance available (toda), the maximum brake energy and the climb gradient with one engine inoperative.the take-off distance available (toda), the maximum brake energy and the climb gradient with one engine inoperative.

The climb limited take off mass can be increased by ?

Question 75-16 : A lower flap setting for take off and selecting a higher v2 selecting a lower v1 selecting a lower v2 selecting a lower vr

. 1080 exemple 235 a lower flap setting for take-off and selecting a higher v2.a lower flap setting for take-off and selecting a higher v2.

In the event that the take off mass is obstacle limited and the take off flight ?

Question 75-17 : 15 degrees up to height of 400 ft 10 degrees up to a height of 400 ft 20 degrees up to a height of 400 ft 25 degrees up to a height of 400 ft

exemple 239 15 degrees up to height of 400 ft.15 degrees up to height of 400 ft.

Which speed provides maximum obstacle clearance during climb ?

Question 75-18 : The speed for which the ratio between rate of climb and forward speed is maximum v2 + 10 kt the speed for maximum rate of climb v2

.if you wish to avoid obstacles during a climb with the maximum clearance as possible your speed will be the speed for maximum climb angle vx best ratio between rate of climb and forward speed

The take off mass of an aeroplane is restricted by the climb limit what would ?

Question 75-19 : None the effect would vary depending upon the height of any obstacle within the net take off flight path the climb limited take off mass would increase the climb limited take off mass would decrease

.the wind component does not affect the climb limited take off mass.climb limit maximum takeoff weight limited by climb capability .this limit is the ability of the.aircraft to climb from liftoff to 1500 feet above the airport elevation and to meet takeoff flight.path limiting climb gradients under existing conditions of temperature and pressure altitude it is.often referred to as the wat limit the weight for altitude and temperature .it is important to.remember that pressure altitude is used and not airport elevation non standard altimeter.settings can have a significant effect on climb capability of course the combination of temperature and pressure altitude references airport density altitude as density altitude affects.the ability of the engine to produce thrust and of the wing to produce lift the importance of using.the correct number cannot be over emphasized .this limit has nothing to do with obstacle clearance and must be met for all takeoffs exemple 247 none.none.

If other factors are unchanged the fuel mileage nautical miles per kg is ?

Question 75-20 : Lower with a forward centre of gravity position independent from the centre of gravity position lower with an aft centre of gravity position higher with a forward centre of gravity position

.with a forward cg the aircraft is 'nose heavy' it has a nose down moment thus the downforce on the tail on a steady flight must increase the total aircraft weight increases and therefore more weight = more drag = more power.the fuel mileage nautical miles per kg is lower with a forward centre of gravity position .example . with a aft cg fuel mileage = 10 nm for 100 kg . with a forward cg fuel mileage = only 8 nm for 100 kg exemple 251 lower with a forward centre of gravity position.lower with a forward centre of gravity position.

Considering a rate of climb diagram rate of climb versus tas for an aeroplane ?

Question 75-21 : Diagram a diagram b diagram c diagramd

.graph 'a' shows that at all tas you will climb with a better rate of climb in clean configuration than with flap down which is logical exemple 255 diagram a.diagram a.

What is the effect of increased mass on the performance of a gliding aeroplane ?

Question 75-22 : The speed for best angle of descent increases there is no effect the gliding angle decreases the lift/drag ratio decreases

.with an increased mass you need more lift ==> more lift = more induced drag . 1082.induced drag will increase displacing the total drag curve upwards and to the right ias for minimum drag vmd velocity minimum drag increases exemple 259 the speed for best angle of descent increases.the speed for best angle of descent increases.

Which force compensates the weight in unaccelerated straight and level flight ?

Question 75-23 : The lift the thrust the drag the resultant from lift and drag

exemple 263 the lift.the lift.

In which of the flight conditions listed below is the thrust required equal to ?

Question 75-24 : In level flight with constant ias in accelerated level flight in a climb with constant ias in a descent with constant tas

.while in steady state flight the attitude direction and speed of the airplane will remain constant until one or more of the basic forces changes in magnitude in unaccelerated flight steady flight the opposing forces are in equilibrium lift and thrust are considered as positive forces while weight and drag are considered as negative forces and the sum of the opposing forces is zero in other words lift equals weight and thrust equals drag exemple 267 in level flight with constant ias.in level flight with constant ias.

The load factor in a turn in level flight with constant tas depends on ?

Question 75-25 : The bank angle only the radius of the turn and the bank angle the true airspeed and the bank angle the radius of the turn and the weight of the aeroplane

exemple 271 the bank angle only.the bank angle only.

The induced drag of an aeroplane ?

Question 75-26 : Decreases with increasing airspeed decreases with increasing gross weight is independent of the airspeed increases with increasing airspeed

.induced drag is the drag produced as a consequence of generating lift it is inversely proportional to speed squared 1/v² exemple 275 decreases with increasing airspeed.decreases with increasing airspeed.

The induced drag of an aeroplane at constant mass in un accelerated level ?

Question 75-27 : The lowest achievable speed in a given configuration vs1 vmo va

.induced drag is the drag produced as a consequence of generating lift it is inversely proportional to speed squared 1/v² exemple 279 the lowest achievable speed in a given configuration.the lowest achievable speed in a given configuration.

The point where drag coefficient/lift coefficient is a minimum is ?

Question 75-28 : The lowest point of the drag curve the point where a tangent from the origin touches the drag curve at stalling speed vs on the 'back side' of the drag curve

. 1084 exemple 283 the lowest point of the drag curve.the lowest point of the drag curve.

On the power versus tas graph for level flight the point at which a tangent ?

Question 75-29 : Is the point where the lift to drag ratio is a maximum is the point where drag coefficient is a minimum is the point where the lift to drag ratio is a minimum is the maximum drag speed

. 1086.for a jet aeroplane the point at which the tangent from the origin touches the power required curve is the maximum endurance instead of maximum range exemple 287 is the point where the lift to drag ratio is a maximum.is the point where the lift to drag ratio is a maximum.

Assuming the gross mass altitude and airspeed remain unchanged moving the ?

Question 75-30 : Decreases the induced drag and reduces the power required increases the power required affects neither drag nor power required increases the induced drag

.induced drag is the drag produced as a consequence of generating lift it is inversely proportional to speed squared.for a forward cg the downforce from the tail to maintain steady flight increases total aircraft weight and therefore more weight = more drag = more power exemple 291 decreases the induced drag and reduces the power required.decreases the induced drag and reduces the power required.

Compared to a more forward position a centre of gravity close to but not beyond ?

Question 75-31 : Improves the maximum range increases the stalling speed improves the longitudinal stability decreases the maximum range

.for a aft cg the downforce from the tail to maintain steady flight decreases total aircraft weight and therefore less weight = less drag = less power = maximum range increases exemple 295 improves the maximum range.improves the maximum range.

The intersections of the thrust available and the drag curve are the operating ?

Question 75-32 : In unaccelerated level flight in descent with constant ias in accelerated level flight in unaccelerated climb

.at the intersections thrust available = drag .the aircraft cannot accelerate in level flight.in the jet case the thrust is not dependent on speed . 1087..in the propeller case the thrust curve varies with speed . 1088 exemple 299 in unaccelerated level flight.in unaccelerated level flight.

In straight horizontal steady flight at speeds below that for minimum drag ?

Question 75-33 : A lower speed requires a higher thrust the aeroplane can be controlled only in level flight a higher speed requires a higher thrust the aeroplane can not be controlled manually

exemple 303 a lower speed requires a higher thrust.a lower speed requires a higher thrust.

A lower airspeed at constant mass and altitude requires ?

Question 75-34 : A higher coefficient of lift less thrust and a lower coefficient of lift more thrust and a lower coefficient of lift more thrust and a lower coefficient of drag

.lift = cl x 1/2 rho v² x s..cl = lift coefficient.rho = density.v = tas in m/s .s = surface..if v is decreased to maintain lift we must increase our angle of attack which means an increase in lift coefficient exemple 307 a higher coefficient of lift.a higher coefficient of lift.

The coefficient of lift can be increased either by flap extension or by ?

Question 75-35 : Increasing the angle of attack increasing the tas decreasing the 'nose up' elevator trim setting increasing the cas

exemple 311 increasing the angle of attack.increasing the angle of attack.

When flying the 'backside of thrust curve' means ?

Question 75-36 : A lower airspeed requires more thrust the thrust required is independent of the airspeed a thrust reduction results in an acceleration of the aeroplane a lower airspeed requires less thrust because drag is decreased

exemple 315 a lower airspeed requires more thrust.a lower airspeed requires more thrust.

'maximum endurance' ?

Question 75-37 : Is achieved in unaccelerated level flight with minimum fuel flow is the same as maximum specific range with wind correction can be flown in a steady climb only can be reached with the 'best rate of climb' speed in level flight

exemple 319 is achieved in unaccelerated level flight with minimum fuel flow.is achieved in unaccelerated level flight with minimum fuel flow.

The speed for maximum endurance ?

Question 75-38 : Is always lower than the speed for maximum specific range is the speed at which the aeroplane achieves 99% of maximum specific range can be either higher or lower than the speed for maximum specific range is always higher than the speed for maximum specific range

.if you want to stay in flight the longest time possible you need to fly at the maximum endurance speed which is minimum power required speed vmp velocity for minimum power .if you want to travel the maximum distance possible you need to fly at the maximum range speed the speed that wich gives maximum lift to drag ratio vmd velocity for minimum drag . 1135.you can notice that the maximum endurance speed is always lower than the maximum specific range speed exemple 323 is always lower than the speed for maximum specific range.is always lower than the speed for maximum specific range.

Which of the equations below defines specific range sr ?

Question 75-39 : Sr = true airspeed/total fuel flow sr = indicated airspeed/total fuel flow sr = mach number/total fuel flow sr = groundspeed/total fuel flow

.specific range sr is the enroute tas divided by the current fuel flow .the units of sr are nautical miles per gallon or nautical miles per pound of fuel exemple 327 sr = true airspeed/total fuel flow.sr = true airspeed/total fuel flow.

To achieve the maximum range over ground with headwind the airspeed should be ?

Question 75-40 : Higher compared to the speed for maximum range cruise with no wind equal to the speed for maximum range cruise with no wind lower compared to the speed for maximum range cruise with no wind reduced to the gust penetration speed

.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 .therefore the airspeed should be higher with a headwind in order to achieve the maximum range exemple 331 higher compared to the speed for maximum range cruise with no wind.higher compared to the speed for maximum range cruise with no wind.

~

Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

2959 Free Training Exam