Question 98-1 : A climb gradient required is 33% for an aircraft maintaining 100 kt true airspeed no wind this climb gradient corresponds to a rate of climb of approximately ? [ Validation Marking ]

Question 98-2 : 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.

Question 98-3 : The take off distance of an aircraft is 800m in standard atmosphere no wind at 0 ft pressure altitudeusing 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 temperaturethe take off distance from an ?

970 m.

Take off distance 800 m +airport at 2 000 ft elevation = 2x20m = +40 m2% runway up slope = 2x15m = +30 mat 2000ft temperature is isa+10° = 10x5m = +50 m5 kt tail wind = 5x10m = +50 mtotal = 970 m

Question 98-4 : 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.

Question 98-5 : 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 massif 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

Question 98-6 : 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 continuedvr speed at which the rotation of the airplane is initiated to takeoff attitude this speed cannotbe less than v1 or less than 105 x vmca minimum control speed in the air vmcg the minimum control speed in the ground

Question 98-7 : 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 altitudelift = cl x 12rho x v² x s rho = density more lift = lower approach speed = landing distance reducedmore lift = go around performance improves

Question 98-8 : 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 densitylift = cl x 12rho x v² x s rho = density less lift = higher take off speed = take off distance increasedless density = less thrust = degraded initial climb performanceless lift = degraded initial climb performance

Question 98-9 : 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 altitudeat low altitude air density is higher take off distance is shorter climb performance is improvedany decrease in altitude means an increase in the aircraft's optimum performance

Question 98-10 : 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 temperaturethe take off distance from an ?

755 m.

Take off distance 600 m +airport at 1 000 ft elevation = 1x20m = +20 m1% runway up slope = 1x15m = +15 mat 1000ft temperature is isa+4° = 4x5m = +20 m10 kt tail wind = 10x10m = +100 mtotal = 755 m

Question 98-11 : 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.

Question 98-12 : A runway is contaminated by a 05 cm layer of wet snow the take off distance in relation to a dry runway will be ?

Question 98-13 : With an true airspeed of 194 kt and a vertical speed of 1000 ftmin the climb gradient is about ?

51%.

Convert tas to ftmin = 194 nm x 6080 ft 60 minutes = 19658 ftminclimb gradient = rate of climb tas ftmin climb gradient = 1000 19658 x 100 = 5086% 6080 ft = 1 nm babar350 or more simply 1000 194 = 515%exact for small angles of climb you can use rate of climb true airspeed

Question 98-14 : If the airworthiness documents do not specify a correction for landing on a wet runwaythe landing distance must be increased by ?

15%.

Question 98-15 : 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.

An operator shall ensure that the take off mass does not exceed the maximum take off mass specified in the aeroplane flight manual for thepressure altitude and the ambient temperature at the aerodrome at which the take off is to be madenot more that 50% of the reported head wind component or not less than 150% ofthe reported tail wind component

Question 98-16 : 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.

Maximum rate of climb is reached at the maximum rate of climb speed vythe speed vy changes with pressure altitude and masson 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 curveif aircraft mass increases power required curve will move up and right taking vy with it

Question 98-17 : 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.

Question 98-18 : 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.

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

Question 98-19 : Which combination of answers of the following parameters give an increase or decrease of the take off ground run 1 decreasing take off mass2 increasing take off mass3 increasing density4 decreasing density5 increasing flap setting6 decreasing flap setting7 increasing pressure altitude8 ?

1 3 5 and 8.

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 reduced3 increasing density density has direct effect on lift drag engine performance when air density increases aircraft performance increases take off run will be reduced5 increasing flap setting higher flap selection will increase lift and permits an earlier take off8 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

Question 98-20 : In certain conditions v2 can be limited by vmca ?

Low take off mass large flap extension low field elevation.

V2 can be limited by 11 vmca or by 113 vsr or 108 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 thrustv2 min based on vmca is 11 vmcaat low take off mass and with a large flap selection the 113 vsr or 108vsr will be less restrictive than the 11 vmca vsr reference stall speed

Question 98-21 : For turbo prop aeroplanes the required runway length at a destination airport is ?

The same as that required at an alternate airport.

Question 98-22 : If the actual landing mass is higher than planned ?

The landing distance will be longer.

Question 98-23 : Considering vr which statement is correct ?

Vr is the speed at which rotation should be initiated.

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 continuedvr speed at which the rotation of the airplane is initiated to takeoff attitude this speed cannotbe less than v1 or less than 105 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 pilotvmcg the minimum control speed in the ground 1459note vmca minimum control speed in the air is located between v1 and vr

Question 98-24 : Which statement regarding v1 is correct ?

V1 must not exceed vr.

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 continuedvr speed at which the rotation of the airplane is initiated to takeoff attitude this speed cannotbe less than v1 or less than 105 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 pilotvmcg the minimum control speed in the ground 1459note vmca minimum control speed in the air is located between v1 and vr

Question 98-25 : Which statement is correct ?

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

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 speed2 decreased thrust and reduced net accelerating forceif 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 greaterproper 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

Question 98-26 : Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed ?

A tailwind component increases the ground distance.

1101

Question 98-27 : 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.

The climb gradient is defined as the ratio expressed as a percentage of the change in geometric height divided by the horizontal distance traveledgradient = change in heighthorizontal distance x 100%a decreased outside air temperature will improve both engine performance and lift the climb gradient will increased

Question 98-28 : Which of the following statements is correct ?

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

The wind component does not affect the climb limited take off massclimb limit maximum takeoff weight limited by climb capability this limit is the ability of theaircraft to climb from liftoff to 1500 feet above the airport elevation and to meet takeoff flightpath limiting climb gradients under existing conditions of temperature and pressure altitude it isoften referred to as the wat limit the weight for altitude and temperatureit is important toremember that pressure altitude is used and not airport elevation non standard altimetersettings can have a significant effect on climb capability of course the combination of temperature and pressure altitude references airport density altitude as density altitude affectsthe ability of the engine to produce thrust and of the wing to produce lift the importance of usingthe correct number cannot be over emphasizedthis limit has nothing to do with obstacle clearance and must be met for all takeoffs

Question 98-29 : Which of the alternatives represents the correct relationship ?

Vmcg and v1 should not exceed vr.

Question 98-30 : 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.

With all engines out you have two possibilities flying for maximum range or flying for maximum timeminimum power required speed vmp permits maximum airborne time with engines but also permits the lowest rate of descent when you are a gliderif the pilot wants to fly for maximum range he has to fly at the speed corresponding to best liftdrag ratio ld max

Question 98-31 : 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.

Question 98-32 : 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.

A larger flap selection will permit to take off earlier but will decrease the path climb angleif 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

Question 98-33 : Which of the following statements is correct ?

A stopway is an area beyond the end of tora able to support the aeroplane mass during an abandoned take off.

Official easa definitionstopway 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 offtora take off run available

Question 98-34 : Besides lift the forces that determine the gradient of climb of an aeroplane are ?

Weight drag and thrust.

Question 98-35 : What happens when flying at the 'backside of the power curve' ?

The speed is unstable.

Vdo919

Question 98-36 : The effect that an increased outside air temperature has on the climb performance of an aeroplane is that it ?

Reduces both the climb gradient and the rate of climb.

Question 98-37 : A headwind component increasing with altitude as compared to zero wind condition assuming ias is constant ?

Has no effect on rate of climb.

Wind has no effect on rate of climb or rate of descent but a head wind will decrease the distance covered over the ground to climb a given distance the slope increases

Question 98-38 : During a descent a headwind will ?

Increases the angle of the descent flight path.

During a descent a headwind will increases the angle of the descent flight path 2518the descent distance over ground is decreased the rate of descent and the angle of descent remain unchanged

Question 98-39 : With an true airspeed of 194 kt and a vertical speed of 1000 ftmin the climb angle is about ?

3°.

Climb angle ° = gradient % x tas kt 1000 = gradient x 194gradient = 1000 194 = 5%climb angle ° = climb angle % x 06thus climb angle ° = 5 x 06 = 3°

Question 98-40 : With regard to a jet aeroplane specific range is the ?

Tas divided by fuel flow.

Ecqb03 july 2016