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Question 91-1 : Vx is ? [ Level reports ]

The speed for best angle of climb

exemple 191 The speed for best angle of climb.

Question 91-2 : The speed for best rate of climb is called ?

Vy

.vy is the indicated airspeed for best rate of climb climbing at vy allows pilots to maximize the altitude gain per unit time .vx is the indicated airspeed for best angle of climb climbing at vx allows pilots to maximize the altitude gain per unit ground distance .vx is slower than vy exemple 195 Vy.

Question 91-3 : The stalling speed or the minimum steady flight speed at which the aeroplane is controllable in landing configuration is abbreviated as ?

Vso

.vs is the stalling speed or the minimum steady flight speed at which the aircraft is controllable bottom of the white arc .vs0 is the stalling speed or the minimum steady flight speed in the landing configuration .vs1 is the stalling speed or the minimum steady flight speed obtained in a specific configuration usually a 'clean' configuration without flaps landing gear and other sources of drag exemple 199 Vso.

Question 91-4 : The absolute ceiling ?

Is the altitude at which the rate of climb theoretically is zero

exemple 203 Is the altitude at which the rate of climb theoretically is zero.

Question 91-5 : The maximum operating altitude for a certain aeroplane with a pressurised cabin ?

Is the highest pressure altitude certified for normal operation

exemple 207 Is the highest pressure altitude certified for normal operation.

Question 91-6 : The approach climb requirement has been established to ensure ?

Minimum climb gradient in case of a go around with one engine inoperative

.you must be able to perform a go around with one engine inoperative this is the reason why the approach climb requirement has been established .the steady gradient of climb may not be less than 2 4% for two engined aeroplanes 2 7% for three engined aeroplanes and 3 0% for four engined aeroplanes exemple 211 Minimum climb gradient in case of a go-around with one engine inoperative.

Question 91-7 : Which statement relating to a take off from a wet runway is correct ?

A reduction of screen height is allowed in order to reduce weight penalties

.screen height for take off is the vertical distance between the take off surface and the take off flight path at the end of take off distance .on a wet runway you have to reduce v1 because brake efficiency is reduced this will reduced the max take off weight because in case of failure at v1 the distance on the ground to reach take off speed vr has increased .in that particular case you are allowed to reduce the screen height from 35 ft to 15 ft exemple 215 A reduction of screen height is allowed in order to reduce weight penalties.

Question 91-8 : Take off performance data for the ambient conditions show the following limitations with flap 10° selected . runway limit 5 270 kg. obstacle limit 4 630 kg.estimated take off mass is 5 000kg .considering a take off with flaps at ?

5° the obstacle limit is increased but the runway limit decreases

.high flaps selection gives a greater field length limited take off mass but decreases the climb limited and the obstacle limited take off mass because of the reduced climb gradient ..low flaps selection gives a reduction of the field length limited take off mass but increases the climb limited and the obstacle limited take off mass because of the improved climb gradient ..take off with flaps at 5° will increased the obstacle limited take off mass but will decreased the field length limited take off mass exemple 219 5°, the obstacle limit is increased but the runway limit decreases.

Question 91-9 : A climb gradient required is 3 3% for an aircraft maintaining 100 kt true airspeed no wind this climb gradient corresponds to a rate of climb of approximately ?

330 ft/min

.climb gradient = rate of climb / true airspeed.rate of climb = 100 x 3 3 = 330 ft/min exemple 223 330 ft/min.

Question 91-10 : An aircraft has two certified landing flaps positions 25° and 35° if a pilot chooses 25° instead of 35° the aircraft will have ?

An increased landing distance and better go around performance

exemple 227 An increased landing distance and better go-around performance.

Question 91-11 : The take off distance of an aircraft is 800m in standard atmosphere no wind at 0 ft pressure altitude .using the following corrections ± 20 m / 1 000 ft field elevation. 5 m / kt headwind.+ 10 m / kt tail wind.± 15 m / % runway slope.± 5 m / °c deviation from standard temperature.the take off ?

970 m

Take off distance 800 m +.airport at 2 000 ft elevation = 2x20m = +40 m.2% runway up slope = 2x15m = +30 m.at 2000ft temperature is isa+10° = 10x5m = +50 m.5 kt tail wind = 5x10m = +50 m.total = 970 m exemple 231 970 m.

Question 91-12 : Is there any difference between the vertical speed versus forward speed curves for two identical aeroplanes having different masses . assume zero thrust and wind ?

Yes the difference is that for a given angle of attack both the vertical and forward speeds of the heavier aeroplane will be larger

exemple 235 Yes, the difference is that for a given angle of attack both the vertical and forward speeds of the heavier aeroplane will be larger.

Question 91-13 : Which statement regarding the relationship between traffic load and range is correct ?

The traffic load can be limited by the desired range

.on long distance flight you need lots of fuel and fuel does not count as part of the traffic load thus the traffic load is normally limited by the maximum take off mass .if you need more fuel to perform the flight you will normally need to reduce the traffic load because the maximum take off mass will be reached exemple 239 The traffic load can be limited by the desired range.

Question 91-14 : Which statement regarding v1 is correct ?

Vr may not be lower than v1

.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

Question 91-15 : An increase in atmospheric pressure has among other things the following consequences on landing performance ?

A reduced landing distance and improved go around performance

.an increase in atmospheric pressure = higher density = lower altitude.lift = cl x 1/2rho x v² x s. rho = density .more lift = lower approach speed = landing distance reduced .more lift = go around performance improves exemple 247 A reduced landing distance and improved go-around performance.

Question 91-16 : A decrease in atmospheric pressure has among other things the following consequences on take off performance ?

An increased take off distance and degraded initial climb performance

.a decrease in atmospheric pressure = similar to a higher altitude = less density..lift = cl x 1/2rho x v² x s. rho = density ..less lift = higher take off speed = take off distance increased .less density = less thrust = degraded initial climb performance .less lift = degraded initial climb performance exemple 251 An increased take-off distance and degraded initial climb performance.

Question 91-17 : An increase in atmospheric pressure has among other things the following consequences on take off performance ?

A reduced take off distance and improved initial climb performance

.an increase in atmospheric pressure = a decrease in altitude .at low altitude air density is higher take off distance is shorter climb performance is improved .any decrease in altitude means an increase in the aircraft's optimum performance exemple 255 A reduced take-off distance and improved initial climb performance.

Question 91-18 : The take off distance of an aircraft is 600m in standard atmosphere no wind at 0 ft pressure altitude using the following corrections .± 20 m / 1 000 ft field elevation . 5 m / kt headwind + 10 m / kt tail wind .± 15 m / % runway slope .± 5 m / °c deviation from standard temperature .the take ?

755 m

Admin .take off distance 600 m +.airport at 1 000 ft elevation = 1x20m = +20 m.1% runway up slope = 1x15m = +15 m.at 1000ft temperature is isa+4° = 4x5m = +20 m.10 kt tail wind = 10x10m = +100 m.total = 755 m exemple 259 755 m.

Question 91-19 : An aircraft has two certified landing flaps positions 25° and 35° .if a pilot chooses 35° instead of 25° the aircraft will have ?

A reduced landing distance and degraded go around performance

exemple 263 A reduced landing distance and degraded go-around performance.

Question 91-20 : A runway is contaminated by a 0 5 cm layer of wet snow the take off distance in relation to a dry runway will be ?

Increased

exemple 267 Increased.

Question 91-21 : With an true airspeed of 194 kt and a vertical speed of 1000 ft/min the climb gradient is about ?

5 1%

.convert tas to ft/min = 194 nm x 6080 ft / 60 minutes = 19658 ft/min..climb gradient = rate of climb / tas ft/min .climb gradient = 1000 / 19658 x 100 = 5 086%.. 6080 ft = 1 nm . babar350 .or more simply 1000 / 194 = 5 15% ..exact for small angles of climb you can use rate of climb / true airspeed exemple 271 5.1%.

Question 91-22 : If the airworthiness documents do not specify a correction for landing on a wet runway.the landing distance must be increased by ?

15%

exemple 275 15%.

Question 91-23 : What percentages of the head wind and tail wind component are taken into account when calculating the take off field length required ?

50% head wind and 150% tail wind

Admin .an operator shall ensure that the take off mass does not exceed the maximum take off mass specified in the aeroplane flight manual for the.pressure altitude and the ambient temperature at the aerodrome at which the take off is to be made . .not more that 50% of the reported head wind component or not less than 150% of.the reported tail wind component . exemple 279 50% head wind and 150% tail wind.

Question 91-24 : If all other parameters remain constant what is the influence of mass on the maximum rate of climb roc speed ?

The roc speed increases with increasing mass

Admin .maximum rate of climb is reached at the maximum rate of climb speed vy .the speed vy changes with pressure altitude and mass .on the power required curve drag x tas maximum rate of climb occurs at the point of the power required curve where a line is draw from the origin tangential to the curve .if aircraft mass increases power required curve will move up and right taking vy with it exemple 283 The roc speed increases with increasing mass.

Question 91-25 : What is the equation for the climb gradient expressed in percentage during unaccelerated flight applicable to small angles only ?

Climb gradient = thrust drag /weight x 100

exemple 287 Climb gradient = ((thrust - drag)/weight) x 100

Question 91-26 : The take off runway performance requirements for transport category aeroplanes are based upon ?

Failure of the critical engine or all engines operating whichever requirement gives the greater distance

Admin .for a standard take off we are usually considering a derated or flex take off then take off run will be longer than a normal take off .if a failure occurs just after v1 you may apply full thrust on the remaining engine s in certain conditions your take off distance can be lower than with all engines operating at reduced thrust exemple 291 Failure of the critical engine or all engines operating whichever requirement gives the greater distance.

Question 91-27 : Which combination of answers of the following parameters give an increase or decrease of the take off ground run .1 decreasing take off mass .2 increasing take off mass .3 increasing density .4 decreasing density .5 increasing flap setting .6 decreasing flap setting .7 increasing pressure ?

1 3 5 and 8

Admin .this question exists at the exam with and without the statement which parameters will decrease the take off ground run as you can see you find a correct combination for a decreasing take off run .1 decreasing take off mass vr will be lower take off run will be reduced .3 increasing density density has direct effect on lift drag engine performance when air density increases aircraft performance increases take off run will be reduced .5 increasing flap setting higher flap selection will increase lift and permits an earlier take off.8 decreasing pressure altitude it means a lower altitude and if altitude is low density increases thus take off run will be reduced .boicko .question states 'increase or decrease in the take off run' should be 'decrease in the take off run'only . .as explained before you can not find an answer with parameters corresponding to an increase of the take off ground run exemple 295 1, 3, 5 and 8.

Question 91-28 : In certain conditions v2 can be limited by vmca ?

Low take off mass large flap extension low field elevation

Admin .v2 can be limited by 1 1 vmca or by 1 13 vsr or 1 08 vsr for turbo propeller powered aeroplanes with more than three engines .at low field elevation there will be a high vmca because of the high asymetric thrust .v2 min based on vmca is 1 1 vmca .at low take off mass and with a large flap selection the 1 13 vsr or 1 08vsr will be less restrictive than the 1 1 vmca . vsr reference stall speed exemple 299 Low take-off mass, large flap extension, low field elevation.

Question 91-29 : For turbo prop aeroplanes the required runway length at a destination airport is ?

The same as that required at an alternate airport

exemple 303 The same as that required at an alternate airport.

Question 91-30 : If the actual landing mass is higher than planned ?

The landing distance will be longer

exemple 307 The landing distance will be longer.

Question 91-31 : Considering vr which statement is correct ?

Vr is the speed at which rotation should be initiated

Admin .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 .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 .vmcg the minimum control speed in the ground . 1459.note vmca minimum control speed in the air is located between v1 and vr exemple 311 Vr is the speed at which rotation should be initiated.

Question 91-32 : Which statement regarding v1 is correct ?

V1 must not exceed vr

Admin .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 .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 .vmcg the minimum control speed in the ground . 1459.note vmca minimum control speed in the air is located between v1 and vr exemple 315 V1 must not exceed vr.

Question 91-33 : Which statement is correct ?

The climb limited take off mass depends on pressure altitude and outer air temperature

Admin .pressure altitude is the height above the standard datum plane usually mean sea level .the effect of pressure altitude and ambient temperature is to define the density altitude and its effect on takeoff performance while subsequent corrections are appropriate for the effect of temperature on certain items of powerplant performance density altitude defines specific effects on takeoff performance an increase in density altitude can produce a twofold effect on takeoff performance .1 greater takeoff speed.2 decreased thrust and reduced net accelerating force.if an aircraft of given weight and configuration is operated at greater heights above standard sea level the aircraft requires the same dynamic pressure to become airborne at the takeoff lift coefficient thus the aircraft at altitude will take off at the same indicated airspeed ias as at sea level but because of the reduced air density the tas will be greater .proper accounting of pressure altitude and temperature is mandatory for accurate prediction of takeoff roll distance the most critical conditions of takeoff performance are the result of some combination of high gross weight altitude temperature and unfavorable wind tailwind exemple 319 The climb limited take-off mass depends on pressure altitude and outer air temperature.

Question 91-34 : Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed ?

A tailwind component increases the ground distance

Admin . 1101 exemple 323 A tailwind component increases the ground distance.

Question 91-35 : Which one of the following statements is true concerning the effect of changes of ambient temperature on an aeroplane's performance assuming all other performance parameters remain constant ?

A decrease will cause an increase of the climb gradient

Admin .the 'climb gradient' is defined as the ratio expressed as a percentage of the change in geometric height divided by the horizontal distance traveled .gradient = change in height/horizontal distance x 100%.a decreased outside air temperature will improve both engine performance and lift the climb gradient will increased exemple 327 A decrease will cause an increase of the climb gradient.

Question 91-36 : Which of the following statements is correct ?

The climb limited take off mass is independent of the wind component

Admin .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 331 The climb limited take-off mass is independent of the wind component.

Question 91-37 : Which of the alternatives represents the correct relationship ?

Vmcg and v1 should not exceed vr

exemple 335 Vmcg and v1 should not exceed vr.

Question 91-38 : With all engines out a pilot wants to fly for maximum time therefore he has to fly the speed corresponding to ?

The minimum power required

Admin .with all engines out you have two possibilities .flying for maximum range or flying for maximum time .minimum power required speed vmp permits maximum airborne time with engines but also permits the lowest rate of descent when you are a glider .if the pilot wants to fly for maximum range he has to fly at the speed corresponding to best lift/drag ratio l/d max exemple 339 The minimum power required.

Question 91-39 : Considering the take off decision speed v1 which of the following is correct ?

If an engine failure is recognized before reaching v1 the take off must be aborted

exemple 343 If an engine failure is recognized before reaching v1, the take-off must be aborted.

Question 91-40 : The effect of a higher take off flap setting up to the maximum certified take off flap setting is ?

An increase of the field length limited take off mass but a decrease of the climb limited take off mass

Admin .a larger flap selection will permit to take off earlier but will decrease the path climb angle .if you have a weight limitation at take off due to the length of the runway by choosing a larger flap setting you will permit to reduce your take off run thus you can carry more weight exemple 347 An increase of the field length limited take-off mass but a decrease of the climb limited take-off mass.


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