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 ?
Quiz > topography
An aircraft has two certified landing flaps positions 25° and 35° If a pilot chooses 25° instead of 35° the aircraft will have ?
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 ?
Is there any difference between vertical speed versus forward speed curves two identical aeroplanes having different masses assume zero thrust and wind Yes, difference that a given angle of attack both vertical forward speeds of heavier aeroplane will be larger, no difference, yes, difference that heavier aeroplane will always glide a greater distance, yes, difference that lighter aeroplane will always glide a greater distance. 
Which statement regarding relationship between traffic load and range correct The traffic load can be limited the desired range, the maximum zero fuel mass limits maximum quantity of fuel, the maximum landing mass basically equal to maximum zero fuel mass, the maximum traffic load not limited the reserve fuel quantity. on long distance flight you need lots of fuel, fuel does not count as part of traffic load, thus traffic load normally limited the maximum take off mass. if you need more fuel to perform flight, you will normally need to reduce traffic load because maximum take off mass will be reached. 
Which statement regarding v1 correct Vr may not be lower than v , vmay not be higher than vmcg, when determining v , reverse thrust may only be used on remaining symmetric engines, the correction up slope on balanced vnegative. v1 critical engine failure speed or decision speed. engine failure below this speed should result in an aborted takeoff above this speed takeoff run should be continued. vr speed at which rotation of airplane initiated to takeoff attitude. this speed cannot be less than v1 or less than 1.05 x vmca (minimum control speed in air). vmcg the minimum control speed in ground. 
An increase in atmospheric pressure has among other things following consequences on landing performance A reduced landing distance improved go around performance, an increased landing distance degraded go around performance, an increased landing distance improved go around performance, a reduced landing distance degraded 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. Question General 77 Answer 8
A decrease in atmospheric pressure has among other things following consequences on take off performance An increased take off distance degraded initial climb performance, a reduced take off distance improved initial climb performance, an increased take off distance improved initial climb performance, a reduced take off distance 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. Question General 77 Answer 9
An increase in atmospheric pressure has among other things following consequences on take off performance A reduced take off distance improved initial climb performance, an increases take off distance degraded initial climb performance, an increased take off distance improved initial climb performance, a reduced take off distance degraded initial climb performance. an increase in atmospheric pressure = a decrease in altitude. at low altitude, air density higher, take off distance shorter, climb performance improved. any decrease in altitude means an increase in aircraft's optimum performance. Question General 77 Answer 10
The take off distance of an aircraft 600m in standard atmosphere no wind at 0 ft pressure altitude using 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 distance from an airport at 1 000 ft elevation temperature 17°c qnh 1013 25 hpa 1% up slope 10 kt tail wind 755 m, 7 5 m, 555 m, 685 m. take off distance 600 m + airport at 1 000 ft elevation = (1x20m) = +20 m 1% runway up slope = (1x15m) = +15 m at 1000ft, temperature isa+4° = (4x5m) = +20 m 10 kt tail wind = (10x10m) = +100 m total = 755 m. Question General 77 Answer 11
An aircraft has two certified landing flaps positions 25° and 35° if a pilot chooses 35° instead of 25° aircraft will have A reduced landing distance degraded go around performance, a reduced landing distance better go around performance, an increased landing distance degraded go around performance, an increased landing distance better go around performance. Question General 77 Answer 12
A runway contaminated a 0 5 cm layer of wet snow the take off distance in relation to a dry runway will be Increased, unchanged, decreased, very significantly decreased. Question General 77 Answer 13
With an true airspeed of 194 kt and a vertical speed of 1000 ft/min climb gradient about 5. %, 3.5%, 5.4%, 4.5%. 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, small angles of climb, you can use rate of climb / true airspeed. Question General 77 Answer 14
If airworthiness documents do not specify a correction landing on a wet runwaythe landing distance must be increased Question General 77 Answer 15
What percentages of head wind and tail wind component are taken into account when calculating take off field length required 5 % head wind5 % tail wind,% head wind% tail wind, 5 % head wind% tail wind,5 % head wind 5 % tail wind. an operator shall ensure that take off mass does not exceed maximum take off mass specified in aeroplane flight manual the pressure altitude the ambient temperature at aerodrome at which take off to be made. ... not more that 50% of reported head wind component or not less than 150% of the reported tail wind component ... Question General 77 Answer 16
If all other parameters remain constant what the influence of mass on maximum rate of climb roc speed The roc speed increases with increasing mass, the roc speed decreases with increasing mass, the roc affected the mass, but not roc speed, the roc the roc speed are independent of mass. maximum rate of climb reached at maximum rate of climb speed vy. the speed vy changes with pressure altitude mass. on power required curve (drag x tas), maximum rate of climb occurs at point of power required curve where a line draw from origin tangential to curve. if aircraft mass increases, power required curve will move up right taking vy with it. Question General 77 Answer 17
What the equation the climb gradient expressed in percentage during unaccelerated flight applicable to small angles only Climb gradient = ((thrust drag)/weight) x, climb gradient = ((thrust + drag)/lift) x, climb gradient = ((thrust mass)/lift) x, climb gradient = (lift/weight) x Question General 77 Answer 18
The take off runway performance requirements transport category aeroplanes are based upon Failure of critical engine or all engines operating whichever requirement gives greater distance, all engines operating only, one engine inoperative only, failure of critical engine only. 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 remaining engine(s). in certain conditions, your take off distance can be lower than with all engines operating at reduced thrust. Question General 77 Answer 19
Which combination of answers of following parameters give an increase or decrease of take off ground r 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 altitude 8 decreasing pressure altitude , 3, 5 8,, 4, 6 8, 2, 4, 5 7, 2, 3, 6 7. this question exists at exam with without statement which parameters will decrease take off ground run?. as you can see, you find a correct combination 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 permits an earlier take off 8 decreasing pressure altitude it means a lower altitude, if altitude low, density increases, thus take off run will be reduced. boicko question states 'increase or decrease in take off run'. should be 'decrease in take off run'only. as explained before, you can not find an answer with parameters corresponding to an increase of take off ground run. Question General 77 Answer 20
In certain conditions v2 can be limited vmca 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. v2 can be limited 1.1 vmca or 1.13 vsr (or 1.08 vsr turbo propeller powered aeroplanes with more than three engines). at low field elevation there will be a high vmca because of high asymetric thrust. v2 min based on vmca 1.1 vmca. at low take off mass with a large flap selection, 1.13 vsr or 1.08vsr will be less restrictive than 1.1 vmca. (vsr reference stall speed). Question General 77 Answer 21
For turbo prop aeroplanes required runway length at a destination airport 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, 6 % greater than that required at an alternate airport. Question General 77 Answer 22
If actual landing mass higher than planned The landing distance will be longer, landing distance will be unaffected, approach path will be steeper, approach path will be steeper threshold speed higher. Question General 77 Answer 23
Considering vr which statement correct Vr the speed at which rotation should be initiated, vr the lowest climb speed after engine failure, in case of engine failure below vr take off should be aborted, vr the lowest speed directional control in case of engine failure. v1 critical engine failure speed or decision speed. engine failure below this speed should result in an aborted takeoff above this speed takeoff run should be continued. vr speed at which rotation of airplane initiated to takeoff attitude. this speed cannot be less than v1 or less than 1.05 x vmca (minimum control speed in air). vlof the speed at which airplane first becomes airborne. this an engineering term used when airplane certificated must meet certain requirements. if it not listed in airplane flight manual, it within requirements does not have to be taken into consideration the pilot. vmcg the minimum control speed in ground. note vmca (minimum control speed in air) located between v1 vr. Question General 77 Answer 24
Which statement regarding v1 correct Vmust not exceed vr, vmust not exceed vmcg, when determining v , reverse thrust only allowed to be taken into account on remaining symmetric engines, the vcorrection up slope negative. v1 critical engine failure speed or decision speed. engine failure below this speed should result in an aborted takeoff above this speed takeoff run should be continued. vr speed at which rotation of airplane initiated to takeoff attitude. this speed cannot be less than v1 or less than 1.05 x vmca (minimum control speed in air). vlof the speed at which airplane first becomes airborne. this an engineering term used when airplane certificated must meet certain requirements. if it not listed in airplane flight manual, it within requirements does not have to be taken into consideration the pilot. vmcg the minimum control speed in ground. note vmca (minimum control speed in air) located between v1 vr. Question General 77 Answer 25
Which statement correct The climb limited take off mass depends on pressure altitude outer air temperature, the performance limited take off mass the highest offield length limited take off mass climb limited take off mass obstacle limited take off mass, the climb limited take off mass will increase if headwind component increases, the climb limited take off mass increases when a larger take off flap setting used. pressure altitude the height above standard datum plane (usually mean sea level). the effect of pressure altitude ambient temperature to define density altitude its effect on takeoff performance. while subsequent corrections are appropriate 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 reduced net accelerating force if an aircraft of given weight configuration operated at greater heights above standard sea level, aircraft requires same dynamic pressure to become airborne at takeoff lift coefficient. thus, aircraft at altitude will take off at same indicated airspeed (ias) as at sea level, but because of reduced air density, tas will be greater. proper accounting of pressure altitude temperature mandatory accurate prediction of takeoff roll distance. the most critical conditions of takeoff performance are result of some combination of high gross weight, altitude, temperature, unfavorable wind (tailwind). Question General 77 Answer 26
Which statement correct a descent without engine thrust at maximum lift to drag ratio speed A tailwind component increases ground distance, a headwind component increases ground distance, a tailwind component increases fuel time to descent, a tailwind component increases time in descent Question General 77 Answer 27
Which one of following statements true concerning 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 climb gradient, an increase will cause a decrease in take off distance required, an increase will cause a decrease in landing distance required, a decrease will cause an increase in take off ground run. the 'climb gradient' defined as ratio, expressed as a percentage, of change in geometric height divided the horizontal distance traveled. gradient = (change in height/horizontal distance) x 100% a decreased outside air temperature will improve both engine performance lift. the climb gradient will increased. Question General 77 Answer 28
Which of following statements correct The climb limited take off mass independent of wind component, the performance limited take off mass independent of wind component, the accelerate stop distance required independent of runway condition, the take off distance with one engine out independent of wind component. the wind component does not affect climb limited take off mass. climb limit maximum takeoff weight limited climb capability this limit the ability of the aircraft to climb from liftoff to 1500 feet above airport elevation to meet takeoff flight path limiting climb gradients under existing conditions of temperature pressure altitude. it is often referred to as wat limit weight altitude temperature. it important to remember that pressure altitude used not airport elevation. non standard altimeter settings can have a significant effect on climb capability. of course combination of temperature pressure altitude references airport density altitude. as density altitude affects the ability of engine to produce thrust of wing to produce lift, importance of using the correct number cannot be over emphasized. this limit has nothing to do with obstacle clearance must be met all takeoffs. Question General 77 Answer 29
Which of alternatives represents correct relationship Vmcg vshould not exceed vr, vmca v2 should not exceed v , vmcl vshould not exceed vr, v2 vshould not exceed vmcg. Question General 77 Answer 30
With all engines out a pilot wants to fly maximum time therefore he has to fly speed corresponding to The minimum power required, critical mach number, minimum angle of descent, maximum lift. with all engines out, you have two possibilities flying maximum range or flying maximum time. minimum power required speed (vmp) permits maximum airborne time with engines, but also permits lowest rate of descent when you are a glider. if pilot wants to fly maximum range, he has to fly at speed corresponding to best lift/drag ratio (l/d max). Question General 77 Answer 31
Considering take off decision speed v1 which of following correct If an engine failure recognized before reaching v , take off must be aborted, vmay not be less than v2min, minimum take off safety speed, if an engine failure recognized after reaching v , take off must be aborted, vsometimes greater than rotation speed vr. Question General 77 Answer 32
The effect of a higher take off flap setting up to maximum certified take off flap setting An increase of field length limited take off mass but a decrease of climb limited take off mass, a decrease of both field length limited take off mass the climb limited take off mass, a decrease of field length limited take off mass but an increase of climb limited take off mass, an increase of both field length limited take off mass the climb limited take off mass. a larger flap selection will permit to take off earlier, but will decrease path climb angle. if you have a weight limitation at take off due to length of runway, choosing a larger flap setting, you will permit to reduce your take off run, thus you can carry more weight. Question General 77 Answer 33
Which of following statements correct A stopway an area beyond end of tora able to support aeroplane mass during an abandoned take off, a declared safe area an area beyond runway end which can be used an abandoned take off, a clearway an area beyond runway end which can be used an abandoned take off, if a clearway or a stopway used in take off calculations, lift off point may be beyond end of tora. official easa definition stopway means an area beyond take off runway, no less wide than runway centred upon extended centreline of runway, able to support aeroplane during an abortive take off, without causing structural damage to aeroplane, designated the airport authorities use in decelerating aeroplane during an abortive take off. tora take off run available. Question General 77 Answer 34
Besides lift forces that determine gradient of climb of an aeroplane are Weight, drag thrust, weight drag only, thrust drag only, weight thrust only. Question General 77 Answer 35
What happens when flying at 'backside of power curve' The speed unstable, the aeroplane will not stall, the altitude cannot be maintained, the elevator must be pulled to lower nose. Question General 77 Answer 36
The effect that an increased outside air temperature has on climb performance of an aeroplane that it Reduces both climb gradient the rate of climb, increases climb gradient decreases rate of climb, does not affect climb performance, reduces climb gradient increases rate of climb. Question General 77 Answer 37
A headwind component increasing with altitude as compared to zero wind condition assuming ias constant Has no effect on rate of climb, does not have any effect on angle of flight path during climb, improves angle rate of climb, decreases angle rate of climb. wind has no effect on rate of climb (or rate of descent), but a head wind will decrease distance covered over ground to climb a given distance (the slope increases). Question General 77 Answer 38
During a descent a headwind will Increases angle of descent flight path, increases angle of descent, increases rate of descent, increases descent distance over ground. during a descent a headwind will increases angle of descent flight path the descent distance over ground decreased, rate of descent the angle of descent remain unchanged. Question General 77 Answer 39
With an true airspeed of 194 kt and a vertical speed of 1000 ft/min climb angle about 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°. Question General 77 Answer 40
With regard to a jet aeroplane specific range the Tas divided fuel flow, fuel flow divided tas, unit of thrust per unit of fuel, fuel flow per unit of thrust
Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.
3039 Free Training Exam