Which statement regarding the relationship between traffic load and range is ? [ Study Manual ]

Question 78-1 : The traffic load can be limited by the desired range the maximum zero fuel mass limits the maximum quantity of fuel the maximum landing mass is basically equal to the maximum zero fuel mass the maximum traffic load is not limited by the reserve fuel quantity

exemple 178 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 The traffic load can be limited by the desired range.

Which statement regarding v1 is correct ?

Question 78-2 : Vr may not be lower than v1 v1 may not be higher than vmcg when determining v1 reverse thrust may only be used on the remaining symmetric engines the correction for up slope on the balanced v1 is negative

.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

An increase in atmospheric pressure has among other things the following ?

Question 78-3 : A reduced landing distance and improved go around performance an increased landing distance and degraded go around performance an increased landing distance and improved go around performance a reduced landing distance and degraded go around performance

exemple 186 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 A reduced landing distance and improved go-around performance.

A decrease in atmospheric pressure has among other things the following ?

Question 78-4 : An increased take off distance and degraded initial climb performance a reduced take off distance and improved initial climb performance an increased take off distance and improved initial climb performance a reduced 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

An increase in atmospheric pressure has among other things the following ?

Question 78-5 : A reduced take off distance and improved initial climb performance an increases take off distance and degraded initial climb performance an increased take off distance and improved initial climb performance a reduced take off distance and degraded initial climb performance

exemple 194 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 A reduced take-off distance and improved initial climb performance.

The take off distance of an aircraft is 600m in standard atmosphere no wind at ?

Question 78-6 : 755 m 715 m 555 m 685 m

exemple 198 755 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 755 m.

An aircraft has two certified landing flaps positions 25° and 35° .if a pilot ?

Question 78-7 : A reduced landing distance and degraded go around performance a reduced landing distance and better go around performance an increased landing distance and degraded go around performance an increased landing distance and better go around performance

exemple 202 A reduced landing distance and degraded go-around performance. — A reduced landing distance and degraded go-around performance.

A runway is contaminated by a 0 5 cm layer of wet snow the take off distance in ?

Question 78-8 : Increased unchanged decreased very significantly decreased

With an true airspeed of 194 kt and a vertical speed of 1000 ft/min the climb ?

Question 78-9 : 5 1% 3 5% 5 4% 4 5%

exemple 210 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 5.1%.

If the airworthiness documents do not specify a correction for landing on a wet ?

Question 78-10 : 15% 5% 10% 20%

What percentages of the head wind and tail wind component are taken into ?

Question 78-11 : 50% head wind and 150% tail wind 100% head wind and 100% tail wind 50% head wind and 100% tail wind 150% head wind and 50% tail wind

exemple 218 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 . 50% head wind and 150% tail wind.

If all other parameters remain constant what is the influence of mass on the ?

Question 78-12 : The roc speed increases with increasing mass the roc speed decreases with increasing mass the roc is affected by the mass but not the roc speed the roc and the roc speed are independent of the mass

exemple 222 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 The roc speed increases with increasing mass.

What is the equation for the climb gradient expressed in percentage during ?

Question 78-13 : Climb gradient = thrust drag /weight x 100 climb gradient = thrust + drag /lift x 100 climb gradient = thrust mass /lift x 100 climb gradient = lift/weight x 100

exemple 226 Climb gradient = ((thrust - drag)/weight) x 100 — Climb gradient = ((thrust - drag)/weight) x 100

The take off runway performance requirements for transport category aeroplanes ?

Question 78-14 : Failure of the critical engine or all engines operating whichever requirement gives the greater distance all engines operating only one engine inoperative only failure of the critical engine only

exemple 230 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 Failure of the critical engine or all engines operating whichever requirement gives the greater distance.

Which combination of answers of the following parameters give an increase or ?

Question 78-15 : 1 3 5 and 8 1 4 6 and 8 2 4 5 and 7 2 3 6 and 7

exemple 234 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 1, 3, 5 and 8.

In certain conditions v2 can be limited by vmca ?

Question 78-16 : Low take off mass large flap extension low field elevation low take off mass small flap extension low field elevation high take off mass large flap extension low field elevation high take off mass small flap extension high field elevation

exemple 238 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 Low take-off mass, large flap extension, low field elevation.

For turbo prop aeroplanes the required runway length at a destination airport is ?

Question 78-17 : The same as that required at an alternate airport less then that required at an alternate airport more than that required at an alternate airport 60% greater than that required at an alternate airport

If the actual landing mass is higher than planned ?

Question 78-18 : The landing distance will be longer the landing distance will be unaffected the approach path will be steeper the approach path will be steeper and threshold speed higher

exemple 246 The landing distance will be longer. — The landing distance will be longer.

Considering vr which statement is correct ?

Question 78-19 : Vr is the speed at which rotation should be initiated vr is the lowest climb speed after engine failure in case of engine failure below vr the take off should be aborted vr is the lowest speed for directional control in case of engine failure

exemple 250 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 Vr is the speed at which rotation should be initiated.

Which statement regarding v1 is correct ?

Question 78-20 : V1 must not exceed vr v1 must not exceed vmcg when determining the v1 reverse thrust is only allowed to be taken into account on the remaining symmetric engines the v1 correction for up slope is negative

exemple 254 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 V1 must not exceed vr.

Which statement is correct ?

Question 78-21 : The climb limited take off mass depends on pressure altitude and outer air temperature the performance limited take off mass is the highest of field length limited take off mass climb limited take off mass obstacle limited take off mass the climb limited take off mass will increase if the headwind component increases the climb limited take off mass increases when a larger take off flap setting is used

exemple 258 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 The climb limited take-off mass depends on pressure altitude and outer air temperature.

Which statement is correct for a descent without engine thrust at maximum lift ?

Question 78-22 : A tailwind component increases the ground distance a headwind component increases the ground distance a tailwind component increases fuel and time to descent a tailwind component increases the time in the descent

exemple 262 A tailwind component increases the ground distance. — Admin . 1101 A tailwind component increases the ground distance.

Which one of the following statements is true concerning the effect of changes ?

Question 78-23 : A decrease will cause an increase of the climb gradient an increase will cause a decrease in take off distance required an increase will cause a decrease in the landing distance required a decrease will cause an increase in the take off ground run

exemple 266 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 A decrease will cause an increase of the climb gradient.

Which of the following statements is correct ?

Question 78-24 : The climb limited take off mass is independent of the wind component the performance limited take off mass is independent of the wind component the accelerate stop distance required is independent of the runway condition the take off distance with one engine out is independent of the wind component

exemple 270 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 The climb limited take-off mass is independent of the wind component.

Which of the alternatives represents the correct relationship ?

Question 78-25 : Vmcg and v1 should not exceed vr vmca and v2 should not exceed v1 vmcl and v1 should not exceed vr v2 and v1 should not exceed vmcg

exemple 274 Vmcg and v1 should not exceed vr. — Vmcg and v1 should not exceed vr.

With all engines out a pilot wants to fly for maximum time therefore he has to ?

Question 78-26 : The minimum power required the critical mach number the minimum angle of descent the maximum lift

exemple 278 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 The minimum power required.

Considering the take off decision speed v1 which of the following is correct ?

Question 78-27 : If an engine failure is recognized before reaching v1 the take off must be aborted v1 may not be less than v2min the minimum take off safety speed if an engine failure is recognized after reaching v1 the take off must be aborted v1 is sometimes greater than the rotation speed vr

exemple 282 If an engine failure is recognized before reaching v1, the take-off must be aborted. — If an engine failure is recognized before reaching v1, the take-off must be aborted.

The effect of a higher take off flap setting up to the maximum certified take ?

Question 78-28 : An increase of the field length limited take off mass but a decrease of the climb limited take off mass a decrease of both the field length limited take off mass and the climb limited take off mass a decrease of the field length limited take off mass but an increase of the climb limited take off mass an increase of both the field length limited take off mass and the climb limited take off mass

exemple 286 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 An increase of the field length limited take-off mass but a decrease of the climb limited take-off mass.

Which of the following statements is correct ?

Question 78-29 : A stopway is an area beyond the end of tora able to support the aeroplane mass during an abandoned take off a declared safe area is an area beyond the runway end which can be used for an abandoned take off a clearway is an area beyond the runway end which can be used for an abandoned take off if a clearway or a stopway is used in the take off calculations the lift off point may be beyond the end of tora

exemple 290 A stopway is an area beyond the end of tora able to support the aeroplane mass during an abandoned take-off. — Admin .official easa definition.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 .tora take off run available A stopway is an area beyond the end of tora able to support the aeroplane mass during an abandoned take-off.

Besides lift the forces that determine the gradient of climb of an aeroplane are ?

Question 78-30 : Weight drag and thrust weight and drag only thrust and drag only weight and thrust only

exemple 294 Weight, drag and thrust. — Weight, drag and thrust.

What happens when flying at the 'backside of the power curve' ?

Question 78-31 : The speed is unstable the aeroplane will not stall the altitude cannot be maintained the elevator must be pulled to lower the nose

exemple 298 The speed is unstable. — Admin .vdo919 The speed is unstable.

The effect that an increased outside air temperature has on the climb ?

Question 78-32 : Reduces both the climb gradient and the rate of climb increases the climb gradient and decreases the rate of climb does not affect the climb performance reduces the climb gradient and increases the rate of climb

exemple 302 Reduces both the climb gradient and the rate of climb. — Reduces both the climb gradient and the rate of climb.

A headwind component increasing with altitude as compared to zero wind ?

Question 78-33 : Has no effect on rate of climb does not have any effect on the angle of flight path during climb improves angle and rate of climb decreases angle and rate of climb

exemple 306 Has no effect on rate of climb. — Admin .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 Has no effect on rate of climb.

During a descent a headwind will ?

Question 78-34 : Increases the angle of the descent flight path increases the angle of descent increases the rate of descent increases the descent distance over ground

exemple 310 Increases the angle of the descent flight path. — Admin .during a descent a headwind will increases the angle of the descent flight path . 2518.the descent distance over ground is decreased the rate of descent and the angle of descent remain unchanged Increases the angle of the descent flight path.

With an true airspeed of 194 kt and a vertical speed of 1000 ft/min the climb ?

Question 78-35 : 3° 3% 5° 8%

exemple 314 3°. — Admin .climb angle ° = gradient % x tas kt .1000 = gradient x 194.gradient = 1000 / 194 = 5%.climb angle ° = climb angle % x 0 6.thus climb angle ° = 5 x 0 6 = 3° 3°.

With regard to a jet aeroplane specific range is the ?

Question 78-36 : Tas divided by fuel flow fuel flow divided by tas unit of thrust per unit of fuel fuel flow per unit of thrust

exemple 318 Tas divided by fuel flow. — Ecqb03 july 2016 Tas divided by fuel flow.

Which of the following statements concerning tires is the major consideration ?

Question 78-37 : Rotation rate of the tyre and temperature tyre pressure and brake temperature rotation rate of the tyre and vmbe tyre pressure and temperature

exemple 322 Rotation rate of the tyre and temperature. — Ecqb04 october 2017..vmax tyre the maximum ground speed of the tyres .the highest speed that the tires can handle without becoming damaged it is possible to drive so fast that the tread actually flies of the tires if you drive fast enough the centrifugal forces become so great that the tire falls apart that must be avoided and therefore there is a maximum rolling speed for a tyre that speed is printed on the side of the tyre near the size usually a number in miles per hour .vmbe maximum brake energy speed is the speed from which the aeroplane may be brought to a stop without exceeding the maximum energy absorption capability of the brakes Rotation rate of the tyre and temperature.

What will increase the 'landing field length limited landing mass' when ?

Question 78-38 : A headwind a downslope a contaminated runway an increase in pressure altitude

exemple 326 A headwind. — Ecqb04 october 2017..if you have a weight limitation at landing due to the length of the runway a headwind will help you to have a reduced approach and landing speed therefore you may land at a higher mass .other statements will are wrong since theay lead to an increase in the required landing distance and therefore a decrease in the 'landing field length limited landing mass' A headwind.

When calculating approach speeds the minimum approach speed in the initial ?

Question 78-39 : 1 4 to 1 5 times vs1 2 times vs1 1 15 times vs0 1 05 times vat

exemple 330 1.4 to 1.5 times vs1. — 1.4 to 1.5 times vs1.

You are approaching a wet runway in gusty conditions you should ?

Question 78-40 : Increase approach speed adopt a steeper approach path decrease approach speed increase landing speed

exemple 334 Increase approach speed. — Ecqb04 october 2017..you should in order to avoid windshear increase slightly your approach speed but you must land at your calculated landing speed not less not more Increase approach speed.

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