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Control > visibility : A 'balanced field length' is said to exist where ?

Question 83-1 : The accelerate stop distance is equal to the take off distance available the clearway does not equal the stopway the accelerate stop distance is equal to the all engine take off distance the one engine out take off distance is equal to the all engine take off distance

exemple 183 the accelerate stop distance is equal to the take-off distance available.the accelerate stop distance is equal to the take-off distance available.

The optimum cruise altitude increases ?

Question 83-2 : If the aeroplane mass is decreased if the temperature oat is increased if the tailwind component is decreased if the aeroplane mass is increased

exemple 187 if the aeroplane mass is decreased.if the aeroplane mass is decreased.

Below the optimum cruise altitude ?

Question 83-3 : The mach number for long range cruise decreases continuously with decreasing altitude the ias for long range cruise increases continuously with decreasing altitude the tas for long range cruise increases continuously with decreasing altitude the mach number for long range cruise increases continuously with decreasing altitude

.long range cruise is derived from the drag/eas curve lrc is slightly faster 1 37vmd than maximum range speed 1 32vmd . vmd means velocity minimum drag .lrc is 4% faster than maximum range speed for 99% of the range lrc is flown as a mach number and since it is a point on the drag/eas curve it will be constant eas on the ertm graph thus lrc decreases with decreasing altitude.the 'ertm' diagram ertm for e as/ r as rectified air speed or cas / t as/ m ach . 1960.eas is vertical mach number decreases with altitude and increases with increasing altitude exemple 191 the mach number for long range cruise decreases continuously with decreasing altitude.the mach number for long range cruise decreases continuously with decreasing altitude.

If after experiencing an engine failure when cruising above the one engine ?

Question 83-4 : Drift down procedure emergency descent procedure etops long range cruise descent

.in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport exemple 195 drift down procedure.drift down procedure.

'drift down' is the procedure to be applied ?

Question 83-5 : After engine failure if the aeroplane is above the one engine out maximum altitude after cabin depressurization to conduct an instrument approach at the alternate to conduct a visual approach with one engine out

.in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport exemple 199 after engine failure if the aeroplane is above the one engine out maximum altitude.after engine failure if the aeroplane is above the one engine out maximum altitude.

If the level off altitude is below the obstacle clearance altitude during a ?

Question 83-6 : Fuel jettisoning should be started at the beginning of drift down the recommended drift down speed should be disregarded and it should be flown at the stall speed plus 10 kt fuel jettisoning should be started when the obstacle clearance altitude is reached the drift down should be flown with flaps in the approach configuration

.in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down exemple 203 fuel jettisoning should be started at the beginning of drift down.fuel jettisoning should be started at the beginning of drift down.

The landing field length required for turbojet aeroplanes at the destination ?

Question 83-7 : 92% 67% 70% 43%

.for jet aeroplanes the landing field length required at destination and at alternate must be factored by 1 66 to make it 60% of distance available .landing distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 1 15.1 66 x 1 15 = 1 92 92% .the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92% exemple 207 92%.92%.

The landing field length required for jet aeroplanes at the alternate wet ?

Question 83-8 : 92% 43% 70% 67%

.for jet aeroplanes the landing field length required at destination and at alternate must be factored by 1 66 to make it 60% of distance available .landing distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 1 15.1 66 x 1 15 = 1 92 92% .the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92% exemple 211 92%.92%.

The speed vsr is defined as ?

Question 83-9 : As reference stall speed and may not be less than 1 g stall speed safe rotation speed for take off design stress speed speed for best specific range

exemple 215 as reference stall speed and may not be less than 1-g stall speed.as reference stall speed and may not be less than 1-g stall speed.

The speed v2 is defined for jet aeroplane as ?

Question 83-10 : Take off climb speed or speed at 35 ft lift off speed take off decision speed critical engine failure speed

exemple 219 take-off climb speed or speed at 35 ft.take-off climb speed or speed at 35 ft.

The aerodynamic ceiling ?

Question 83-11 : Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same depends upon thrust setting and increase with increasing thrust is the altitude at which the best rate of climb theoretically is zero is the altitude at which the aeroplane reaches 50 ft/min

.if there is no reserve of power available to permit any climb you are at the absolute ceiling .if you have lots of power you can climb until mmo and minimum control speed coincide you are at your aerodynamic ceiling .the aerodynamic ceiling is that altitude at which the low speed buffet and the high speed buffet are equal exemple 223 is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.

'stepped climbs' are used on long distance flights ?

Question 83-12 : To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces only if the headwind is less or the tailwind is greater than forecast at high altitude for piston engined aeroplanes only not for jet aeroplanes to fly as close to the tropopause as possible

exemple 227 to fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.to fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.

The climb gradientafter take off in a standard atmosphere and still air at 0 ft ?

Question 83-13 : 3 9 % 4 3 % 4 7 % 4 9 %

.6% minus 0 2% for aerodrome elevation = 5 8%..5 8% minus 0 4% for temperature deviation = 5 4%..5 4% minus 1% for wing anti ice on = 4 4%..4 4% minus 0 5% for engine anti ice on = 3 9% exemple 231 3.9 %.3.9 %.

The drift down procedure specifies requirements concerning the ?

Question 83-14 : Obstacle clearance after engine failure engine power at the altitude at which engine failure occurs climb gradient during the descent to the net level off altitude weight during landing at the alternate

.in a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdown .this would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s .then achieving a computed 'driftdown' airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining . 2519.the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down exemple 235 obstacle clearance after engine failure.obstacle clearance after engine failure.

Given a jet aircraft which order of increasing speeds in the performance ?

Question 83-15 : Vs vx maximum range speed maximum endurance speed long range speed maximum range speed vs maximum range speed vx maximum endurance speed maximum range speed vx

.this is the order of speeds from slowest to fastest .obviously vs is slowest then vx .vs is stall speed very slow .vx is the speed for best angle of climb climbing at vx allows pilots to maximize the altitude gain per unit ground distance vx is faster than vs .maximum range speed gives you the most lift for the least drag for the most economy and te most distance for altitude lost maximum range speed is found at best lift/drag speed which is faster than vx .long range speed is higher than maximum range speed and is used as the standard speed for cruise it is 4% faster than best range speed for 99% of the range exemple 239 vs, vx, maximum range speed.vs, vx, maximum range speed.

When determining the maximum landing mass of an turbojet powered aeroplane ?

Question 83-16 : 0 60 115/100 1 67 60/115

.eu ops 1 515 landing dry runways. a an operator shall ensure that the landing mass of the aeroplane determined in accordance with eu ops 1 475 a for the estimated time of landing at the destination aerodrome and at any alternate aerodrome allows a full stop landing from 50 ft above the threshold. 1 for turbo jet powered aeroplanes within 60% of the landing distance available or.. 2 for turbo propeller powered aeroplanes within 70% of the landing distance available. example .an aircraft needs 1200 m to stop landing distance required with maximum braking manufacturers data factored for slope and wind effects.for a dry runway this 1200 m must not represent more than 60% percent of landing distance available lda so the minimum landing distance available is indeed 1200 x 1 67 = 2004 m.now if you start from 2004 m the landing distance available we use a 0 60 factor 2004 x 0 6 = 1200 m

On a segment of the take off flight path an obstacle requires a minimum ?

Question 83-17 : 118455 kg 102150 kg 106425 kg 121310 kg

2 8 / 2 6 x 110000 = 118461 kg.as we decrease our climb gradient for the same power our mass can be increased exemple 247 118455 kg.118455 kg.

Which statement with respect to the step climb is correct ?

Question 83-18 : Performing a step climb based on economy can be limited by the 1 3g buffet onset requirements in principle a step climb is performed immediately after the aircraft has exceeded the optimum altitude a step climb can only be performed when the altitude exceeds the one engine out service ceiling a step climb provides better economy than a optimum cruise

.in order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 1 3 this value is an operating limitation but not a regulatory one the corresponding altitude is called the '1 3g buffet limited altitude' or 'buffet ceiling' exemple 251 performing a step climb based on economy can be limited by the 1.3g buffet onset requirements.performing a step climb based on economy can be limited by the 1.3g buffet onset requirements.

In accordance to cs 25 which of the following listed speeds are used for ?

Question 83-19 : Vsr vmca vmcg v2 vlof vmca v1 vr

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.vsr reference stall speed exemple 255 vsr, vmca.vsr, vmca.

Reduced take off thrust should normally not be used when ?

Question 83-20 : Anti skid is not usable it is dark the runway is wet obstacles are present close to the end of the runway

.a reduced take off thrust is not permitted with icy or slippery runways contamined runways contamination can have a large and uncertain drag on the take off run .for safety reasons it is preferable to reduce the running distance to reach v1 even if you can accomplish a safety rejected take off on the allowed asda thus you shouldn't use reduced take off thrust when anti skid is not usable exemple 259 anti skid is not usable.anti skid is not usable.

Maximum tyre speed can limit the lift off speed which kind of speed can be ?

Question 83-21 : Groundspeed ias tas ess

exemple 263 groundspeed.groundspeed.

According to cs 25 the landing reference speed vref may not be less than ?

Question 83-22 : 1 23 vsr0 and must be maintained down to 50 ft height vsr0 and must be maintained down to 35 ft height 1 23 vsr0 for turbojet powered and 1 30 for turboprop powered aeroplanes 1 2 vmca

.cs 25 125 landing . a the horizontal distance necessary to land and to come to a complete stop from a point 15 m 50 ft above the landing surface for standard temperatures at each weight altitude and wind within the operational limits established by the applicant for the aeroplane with a landing reference speed vref not be less than 1 23 vsr0 .vsr0 reference stall speed in the landing configuration exemple 267 1.23 vsr0 and must be maintained down to 50 ft height.1.23 vsr0 and must be maintained down to 50 ft height.

Which statement with respect to the step climb is correct ?

Question 83-23 : Executing a desired step climb at high altitude can be limited by buffet onset at g loads greater than 1 a step climb must be executed immediately after the aeroplane has exceeded the optimum altitude a step climb is executed because atc desires a higher altitude a step climb is executed in principle when just after levelling off the 1 3g altitude is reached

.in order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 1 3 this value is an operating limitation but not a regulatory one the corresponding altitude is called the '1 3g buffet limited altitude' or 'buffet ceiling' exemple 271 executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1.executing a desired step climb at high altitude can be limited by buffet onset at g-loads greater than 1.

Select from the following list of conditions those that must prevail in the ?

Question 83-24 : 1 4 6 9 1 5 8 10 2 3 6 9 1 4 5 10

exemple 275 1, 4, 6, 9.1, 4, 6, 9.

V1 for a balanced field is calculated when ?

Question 83-25 : The acceleration/stop distance available is equal to the take off distance available the take off mass is field length limited by the stopway to produce the maximum take off mass the speed is equal to v2 the take off mass is field length limited by the clearway to produce the maximum take off mass

exemple 279 the acceleration/stop distance available is equal to the take-off distance available.the acceleration/stop distance available is equal to the take-off distance available.

With regard to the drift down performance of the twin jet aeroplane why does ?

Question 83-26 : Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level because at this mass the engines slow down at a slower rate after failure there is still some thrust left during four minutes due to higher tas at this mass it takes more time to develop the optimal rate of descent because of the inertia involved all the curves start at the same point which is situated outside the chart

. 2519.you will stay at the original cruising level until you reach the optimum speed for descent exemple 283 because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

The requirements of the take off net flight path for a class a aeroplane assume ?

Question 83-27 : The failure of the critical engine of a multi engined aeroplane at vef the failure of any engine of a multi engined aeroplane at vef the failure of any engine of a multi engined aeroplane at vr the failure of two engines of a three engined or four engined aeroplane at vef

exemple 287 the failure of the critical engine of a multi-engined aeroplane at vef.the failure of the critical engine of a multi-engined aeroplane at vef.

The angle of attack required to attain the maximum still air range for a turbo ?

Question 83-28 : Less than that for the maximum lift to drag ratio the same as that for the maximum endurance the same as that giving zero induced drag greater than that for the maximum lift to drag ratio

. /com en/com032 334 jpg.for a jet aeroplane maximum l/d ratio is maximum endurance which is vmd where the gap between power required and power available is greatest at this speed for a conventional aerofoil the angle of attack is about 4°.the speed for maximum range maximum still air range occurs at 1 32 times the speed of minimum drag vmd in level flight as speed goes up the angle of attack goes down angle of attack is less than 4° typically at around 2 5° exemple 291 less than that for the maximum lift to drag ratio.less than that for the maximum lift to drag ratio.

Compared with balanced field calculations for an aerodrome with no stopway or ?

Question 83-29 : Increase the field length limited take off mass not affect the value of the field length limited take off mass increase the value of v1 not affect the value of v1

.a field length is balanced when take off distance available equals accelerate stop distance available.the take off distance available is the length of the take off run available plus the length of the clearway available.a clearway is an area beyond the paved runway free of obstacles . 771..the use of any additional clearway in take off performance calculations may allow a greater field limited take off mass but the v1 will be lower because the extra take off mass means that more distance will be required to stop in the event of an aborted takeoff exemple 295 increase the field-length-limited take-off mass.increase the field-length-limited take-off mass.

The relationship of the reference landing speed vref to the reference stalling ?

Question 83-30 : 1 23 vsro vsro 1 1 vsro 1 32 vsro

exemple 299 1.23 vsro.1.23 vsro.

The vertical interval by which a class a aeroplane must avoid all obstacles in ?

Question 83-31 : 2000 ft 1000 ft 1500 ft 35 ft

.eu ops 1 500 en route one engine inoperative . . c the net flight path must permit the aeroplane to continue flight from the cruising altitude to an aerodrome where a landing can be made in accordance with eu ops 1 515 or 1 520 as appropriate the net flight path clearing vertically by at least 2 000 ft all terrain and obstructions along the route within 9 3 km 5 nm on either side of the intended track exemple 303 2000 ft.2000 ft.

Cs 25 the correct formula is . remark ' ?

Question 83-32 : Vmcg 1 05 vmc 1 05 vmcg< vef v2min

.the minimum control speed on the ground vmcg is based on directional control being maintained by primary aerodynamic control only .vef is the speed at which the critical engine is assumed to fail during takeoff .v1 follows vef it is the decision speed at take off and it is the calibrated airspeed below which take off must be rejected if an engine failure is recognized above which take off should be continued exemple 307 vmcgvmcg

Calculate the one engine failed climb gradient of a four engine aeroplane given ?

Question 83-33 : 7 8 % 6 8 % 14 7 % 3 4 %

Ecqb03 july 2016....calculation for the climb gradient.aircraft weight in newton 3 580 000 n.3 engines operating 3 x 245000 n = 300000 n.drag = 455000 n...sin angle of climb = thrust drag / weight..sin angle of climb = 735000 455000 / 3580000..sin angle of climb = 0 078212....multiplicate by 100 for a result in percent 7 82% exemple 311 7.8 %7.8 %

For jet propelled aeroplanes the maximum endurance speed corresponds with the ?

Question 83-34 : Minimum drag speed mach maximum range mach long range minimum power and minimum drag speed

Ecqb03 july 2016 exemple 315 minimum drag speed.minimum drag speed.

Complete the following statement regarding the take off performance of an ?

Question 83-35 : I v1 ii 2 seconds iii accelerate stop distance available i v2 ii 3 seconds iii take off distance available i v1 ii 1 seconds iii accelerate stop distance available i v1 ii 2 seconds iii take off distance available

Ecqb03 august 2016 exemple 319 (i) v1 (ii) 2 seconds (iii) accelerate-stop distance available(i) v1 (ii) 2 seconds (iii) accelerate-stop distance available

Performance class a take off.by mistake the take off speed are selected for a ?

Question 83-36 : A tail strike might occur the selected take off speeds are higher than the current speeds the actual accelerate stop distance is increased the accelerate go distance is shorter than calculated

Ecqb04 october 2017 exemple 323 a tail strike might occur.a tail strike might occur.

A 'balanced field take off' means ?

Question 83-37 : One engine inoperative asdr = one engine inoperative todr one engine inoperative asda = one engine inoperative toda all engines operating asrd = one engine inoperative todr all engines operating asrd = all engines operating todr

.a balanced field is where toda = asda .toda take off distance available .asda acceleration stop distance available .if you have an engine failure at v1 and you continue the take off you will just make the screen height of 35ft and v2 at the end of toda .but if you stop you will just stop within asda this then must be the minimum required field length.a balanced field take off is where 'one engine inoperative asdr' = 'one engine inoperative todr' you have a balanced v1.todr take off distance required .asdr accelerate stop distance required exemple 327 one engine inoperative asdr = one engine inoperative todr.one engine inoperative asdr = one engine inoperative todr.

The quick turnaround limit weight qtlw is the maximum landing weight for which ?

Question 83-38 : There is no minimum ground time required with respect to possible fuse plug melting before executing a subsequent takeoff there is no more guarantee for sufficient brake energy absorption in case of a long landing the landing gear structure will resist between two successive landings

Ecqb04 october 2017...sorry incomplete feedback .during stop internal friction of the rotors and stators of the brakes cause brake heating the temperature rise in the brakes will dissipate throughout the wheel use of the recommended cooling schedule will help avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff .for normal operation on crj embraer b737 and a320 most landings are at weights below the quick turnaround limit weight exemple 331 there is no minimum ground time required, with respect to possible fuse plug melting, before executing a subsequent takeoff.there is no minimum ground time required, with respect to possible fuse plug melting, before executing a subsequent takeoff.

The purpose of the 'quick turnaround limits' is to ?

Question 83-39 : Avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff enhance the carbon brakes life protect the wheel fuse plugs from melting during landing reduce the time between full unloading and full reloading an aircraft

Ecqb04 october 2017...during stop internal friction of the rotors and stators of the brakes cause brake heating the temperature rise in the brakes will dissipate throughout the wheel use of the recommended cooling schedule will help avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff .for normal operation on crj embraer b737 and a320 most landings are at weights below the quick turnaround limit weight exemple 335 avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff.avoid brake overheat and fuse plug problems that could result from repeated landings at short time intervals or a rejected takeoff.

Is credit given for the use of reverse thrust in a rejected take off on a dry ?

Question 83-40 : No only for the torr only for the todr only for the asdr

Ecqb04 november 2017..for a dry runway you cannot take into account reverse thrust for asdr but you can for a wet runway exemple 339 no.no.

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