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What is the effect of using engine bleed air on the take off distance ? [ Deepen EASA ]

Question 93-1 : Reduces available thrust and increases the take off distance reduces available thrust and take off distance bleed air has no effect on take off distance increases available thrust and take off distance

exemple 193 Reduces available thrust and increases the take-off distance.Reduces available thrust and increases the take-off distance.

Which of the following will decrease landing distance ?

Question 93-2 : The spoilers a wet runway a tailwind a high altitude airfield

Ecqb04 november 2017 exemple 197 The spoilers.The spoilers.

If cabin altitude cannot be controlled eg rapid decompression while in cruise ?

Question 93-3 : Target speed mmo speedbrake deployed no flaps target speed vmo speedbrake deployed no flaps target speed mmo speedbrake up flaps 10° target speed mmo speedbrake deployed full flaps

Ecqb04 november 2017 exemple 201 Target speed mmo, speedbrake deployed, no flaps.Target speed mmo, speedbrake deployed, no flaps.

The climb gradient is ?

Question 93-4 : Always larger than the angle of climb always smaller than the angle of climb the same as the angle of climb represents the angle of variation

Ecqb04 november 2017 ..the 'climb gradient' is defined as the ratio expressed as a percentage of the change in geometric height divided by the horizontal distance travelled .climb gradient = change in height / distance travelled.the value of the climb gradient is given as percent the value of the angle of climb is given in degree .for example 5% = 3° .we can say that the climb gradient is always larger than the angle of climb exemple 205 Always larger than the angle of climb.Always larger than the angle of climb.

Induced drag is caused by ?

Question 93-5 : Movement of the aerofoil through the air boundary layer effects the shape of aerofoil increased zero lift drag

Ecqb04 feedback november 2017 exemple 209 Movement of the aerofoil through the air.Movement of the aerofoil through the air.

How does an increase in aircraft mass affect the gliding range ?

Question 93-6 : Has no effect on gliding range increases gliding range decreases gliding range none of the above

exemple 213 Has no effect on gliding range.Has no effect on gliding range.

Under what condition does pressure altitude has the same value as density ?

Question 93-7 : At standard temperature at sea level when temperature is 0°c when altimeter setting is 1013 25 hpa when altimeter has no position error

Ecqb04 revised november 2017 exemple 217 At standard temperature.At standard temperature.

What is true about a clearway ?

Question 93-8 : A clearway can be water or land and must be under the control of the aerodrome authority a clearway has a virtual gradient of 1 5% a clearway can be used to bring the aircraft to a full stop after an engine failure a clearway has a minimum width of 90m

Ecqb04 november 2017 exemple 221 A clearway can be water or land and must be under the control of the aerodrome authority.A clearway can be water or land and must be under the control of the aerodrome authority.

The effect an increase of weight has on the value of stalling speed las is that ?

Question 93-9 : Increases decreases remains constant increases or decreases depending on the amount of weight increase

Admin .stall speed of an aircraft changes in proportion to the square root of the change in mass .for example if an aeroplane has a stall speed of 78 kt at its mass of 5000 kg the stall speed when the mass is 6850 kg will be .change in mass ratio = new mass / old mass = 6850/5000 = 1 37.square root of 1 37 = 1 17.original stall speed = 78 kt.stall speed for a weight of 6850 kg ==> 78 x 1 17 = 91 kt .vs increases for an increase of weight stall will occur earlier exemple 225 Increases.Increases.

An aircraft has a stall speed of 83 kt on short final its speed will be ?

Question 93-10 : 108 kt 90 kt 120 kt 100 kt

Admin .on short final you are supposed to be at 1 3 x vs exemple 229 108 kt.108 kt.

The parameters taken into account for take off performance calculations are ?

Question 93-11 : Outside temperature pressure altitude wind mass standard temperature pressure altitude wind mass standard temperature standard pressure wind mass outside temperature standard pressure wind mass

exemple 233 Outside temperature, pressure altitude, wind, mass.Outside temperature, pressure altitude, wind, mass.

For a piston engine aeroplane the speed for maximum range is ?

Question 93-12 : That which gives the maximum lift to drag ratio that which gives the minimum value of induced drag that which gives the maximum value of lift 1 4 times the stall speed in clean configuration

Admin .if you want to stay in flight the longest time possible maximum endurance you need to fly at the minimum power required speed vmp velocity for minimum power .if you want to travel the maximum distance possible maximum range you need to fly at the speed that wich gives maximum lift to drag ratio vmd velocity for minimum drag . 1066 exemple 237 That which gives the maximum lift to drag ratio.That which gives the maximum lift to drag ratio.

Maximum endurance for a piston engine aeroplane is achieved at ?

Question 93-13 : The speed that approximately corresponds to the maximum rate of climb speed the speed for maximum lift coefficient the speed for minimum drag the speed that corresponds to the speed for maximum climb angle

Admin .maximum endurance in a piston engine aeroplane will occur at vmp minimum power speed you want to use as little fuel as possible in order to stay airborne as longer as possible you are not concerned with distance ..the best rate of climb will occur where you have excess power available that is vy best rate of climb speed and in a piston engine aeroplane that is definitely slower than speed for minimum drag vmd thus maximum endurance for a piston engine aeroplane is achieved at a speed that approximates the best rate of climb speed vmp .a common mistake is done between the trhust required curve showing drags and power required curve showing required power . 1135.for the propeller driven aircraft curve the lowest point of the curve is the tas at wich the least power is needed as opposed to producing the least drag and is therefore the best for endurance in level flight it is also the maximum rate of climb speed because the gap between power required and power available is greatest more power is needed above and below the minimum power speed

The maximum indicated air speed of a piston engine aeroplane without turbo ?

Question 93-14 : At the lowest possible altitude at the optimum cruise altitude at the service ceiling at the practical ceiling

Admin .maximum ias will always be achieved at sea level because this is where density is highest the dynamic pressure is 1/2 rho v² which is sensed by the pitot system exemple 245 At the lowest possible altitude.At the lowest possible altitude.

At reference or see performance manual sep1 1 figure 2 4 .with regard to the ?

Question 93-15 : 10 kt no wind 5 kt 15 kt

Admin .please find hereafter the full completed graph . 1072.be aware that we must assume a factored runway a piston engine airplane has to land in the 70% of the runway length .1300 ft x 0 7 = 910 ft with this distance none of the answers are correct

How does the thrust of a propeller vary during take off run assuming unstalled ?

Question 93-16 : Decreases while the aeroplane speed builds up increases while the aeroplane speed builds up varies with mass changes only has no change during take off and climb

Admin .the angle of attack as in the case of a aircraft wing is defined as the angle between the chord line and relative airflow with a propeller however the relative airflow is the resultant of the airflow due to rotation and forward speed change either of these values and the angle of attack will change . 1079.the angle of attack decreases similar to a decreases of angle of attack for an aircraft wing less lift will be produce for a propeller it results in less thrust exemple 253 Decreases while the aeroplane speed builds up.Decreases while the aeroplane speed builds up.

In a given configuration the endurance of a piston engine aeroplane only ?

Question 93-17 : Altitude speed mass and fuel on board altitude speed and mass speed and mass speed mass and fuel on board

Oszklarska .the fuel on board weight is contained in airplane mass is it not .therefore the 'altitude speed and mass' answer is equivalent to 'altitude speed mass and fuel' . .no you need to know the quantity of fuel on board to be able to calculate endurance to stay airborne as longer as possible exemple 257 Altitude, speed, mass and fuel on board.Altitude, speed, mass and fuel on board.

At a higher gross mass on a piston engined aeroplane in order to maintain a ?

Question 93-18 : The airspeed must be increased and the drag will also increase the airspeed must be decreased and the drag will increase the lift/drag ratio must be increased the airspeed must be increased and the drag will remain unchanged

Admin .at a higher gross mass we need to increase lift if we consider to maintain same altitude .lift = cl x 1/2 rho v² x s.cl = lift coefficient.rho = density.v = tas in m/s .s = surface.since density surface and lift coefficient e g change in angle of attack do not change only speed can changed .therefore the airspeed must be increased and the drag will also increase exemple 261 The airspeed must be increased and the drag will also increase.The airspeed must be increased and the drag will also increase.

On a reciprocating engine aeroplane to maintain a given angle of attack ?

Question 93-19 : An increase in airspeed and power is required a higher coefficient of drag is required an increase in airspeed is required but power setting does not change requires an increase in power and decrease in the airspeed

Admin .at a higher gross mass we need to increase lift if we consider to maintain same altitude .lift = cl x 1/2 rho v² x s.cl = lift coefficient.rho = density.v = tas in m/s .s = surface.since density surface and lift coefficient e g change in angle of attack do not change only speed can changed .therefore power required increases airspeed will increased and the drag will also increase .notice whatever the propulsion system prop or jet it doesn't play a role as seen by its absence in the lift formula exemple 265 An increase in airspeed and power is required.An increase in airspeed and power is required.

An aeroplane with reciprocating engines is flying at a constant angle of attack ?

Question 93-20 : Remains unchanged but the tas increases increases at constant tas decreases and the cas decreases too because of the lower air density remains unchanged but the the cas increases

Admin .with increasing altitude density rho decreases angle of attack mass and configuration remain constant to maintain lift tas has to increase .drag = cd x 1/2 x rho x v² velocity = tas .v increases while rho decreases drag remains constant exemple 269 Remains unchanged but the tas increases.Remains unchanged but the tas increases.

On a reciprocating engine aeroplane with increasing altitude at constant gross ?

Question 93-21 : Increases and the tas increases by the same percentage increases but tas remains constant decreases slightly because of the lower air density remains unchanged but the tas increases

Admin .this question compares an aircraft at a certain weight and angle of attack for a first altitude and then in the same configuration at a second altitude .you have to understand that the aircraft is in straight and level flight it is not climbing .our aircraft has to produce the same lift .lift l = 1/2 rho cl s v².for a higher altitude density reduces cl and s remain unchanged thus only tas v can and must increase .for that reason the power required must increase exemple 273 Increases and the tas increases by the same percentage.Increases and the tas increases by the same percentage.

At reference or see performance manual sep 1 figure 2 4 .with regard to the ?

Question 93-22 : Approximately 1850 feet approximately 1700 feet approximately 1370 feet approximately 1120 feet

Admin . 1091 exemple 277 Approximately : 1850 feet.Approximately : 1850 feet.

Performance manual sep 1 figure 2 4 .with regard to the landing chart for the ?

Question 93-23 : Approximately 1930 feet approximately 950 feet approximately 1400 feet approximately 750 feet

Admin . 1128 exemple 281 Approximately : 1930 feet.Approximately : 1930 feet.

For this question use annex 032 005 or performance manual sep 1 figure 2 4 ?

Question 93-24 : Approximately 1800 feet approximately 1300 feet approximately 2000 feet approximately 1450 feet

Img /com en/com032 295 jpg. oat isa +15°c so oat is +30°c at 0 ft pressure altitude .runway wet grass .landing factor for short grass is 1 15 and landing factor for wet runway is 1 15.1275 ft x 1 15 = 1466 ft.1466 ft x 1 15 = 1686 ft.approximately 1800 feet is our answer exemple 285 Approximately: 1800 feet.Approximately: 1800 feet.

With regard to the take off performance chart for the single engine aeroplane ?

Question 93-25 : 3200 lbs 3000 lbs 2900 lbs > 3650 lbs

Admin .complete the graph with the data . 1093.you will find 3200 lbs exemple 289 3200 lbs.3200 lbs.

At reference or see performance manual sep 1 figure 2 2 .with regard to the ?

Question 93-26 : Approximately 2050 ft approximately 1150 ft approximately 2450 ft approximately 1260 ft

Complete the graph with the data . /com en/com032 297 jpg.you find 1900 ft the closest answer is 2050 ft exemple 293 Approximately: 2050 ft.Approximately: 2050 ft.

At reference or see performance manual sep 1 figure 2 1 .with regard to the ?

Question 93-27 : 71 and 82 kias 65 and 75 kias 73 and 84 kias 68 and 78 kias

Img /com en/com032 298 jpg. exemple 297 71 and 82 kias.71 and 82 kias.

At reference or see performance manual sep 1 figure 2 2 .with regard to the ?

Question 93-28 : Approximately 3960 ft approximately 3680 ft approximately 4150 ft approximately 5040 ft

Img /com en/com032 299 jpg.do not forget to apply 'grass.correction factor' .3300 ft x 1 2 = 3960 ft exemple 301 Approximately: 3960 ft.Approximately: 3960 ft.

With regard to the climb performance chart for the single engine aeroplane ?

Question 93-29 : 1290 ft/min 1370 ft/min 1210 ft/min 1150 ft/min

Admin . 1129.youssef92 .for me i find that the answer is 1370ft/min . .if you start at 15°c instead of 30°c you will find around 1350 1370 ft but the question states o a t isa + 15°c .it means an outside temperature of 30°c at sea level exemple 305 1290 ft/min.1290 ft/min.

At reference or see performance manual sep 1 figure 2 2 .with regard to the ?

Question 93-30 : 2275 ft 1900 ft 1600 ft 2000 ft

Img /com en/com032 3587 jpg..1750 ft x surface factor 1 3 = 2275 ft exemple 309 2275 ft.2275 ft.

Using the landing diagram for single engine aeroplane determine the landing ?

Question 93-31 : 1350 ft 1550 ft 1020 ft 880 ft

Admin . 1097.1320 ft close to 1350 ft exemple 313 1350 ft.1350 ft.

The pilot of a single engine aircraft has established the climb performance ?

Question 93-32 : Degraded improved unchanged unchanged if a short field take off is adopted

exemple 317 Degraded.Degraded.

An extract of the flight manual of a single engine propeller aircraft is ?

Question 93-33 : 465 m 615 m 540 m 395 m

Admin . 1099.1270 kg = 2800 lbs .convert 1520 ft to meters .1520 x 0 3048 = 463 m exemple 321 465 m.465 m.

With regard to the landing chart for the single engine aeroplane determine the ?

Question 93-34 : Approximately 1700 feet approximately 1150 feet approximately 1500 feet approximately 920 feet

Admin . 1102.you will find 1760 ft close enough to 1700 feet exemple 325 Approximately : 1700 feet.Approximately : 1700 feet.

With regard to the take off performance chart for the single engine aeroplane ?

Question 93-35 : Approximately 2470 feet approximately 1440 feet approximately 2800 feet approximately 2200 feet

Admin . 1131 exemple 329 Approximately : 2470 feet.Approximately : 2470 feet.

For this question use reference or performance manual sep 1 figure 2 1.with ?

Question 93-36 : 3240 lbs 3000 lbs 2900 lbs greater than 3650 lbs

Complete the graph with the data . /com en/com032 359 jpg.you will find 3240 lbs exemple 333 3240 lbs.3240 lbs.

Consider the graphic representation of the power required versus true air speed ?

Question 93-37 : Maximum specific range maximum endurance maximum thrust critical angle of attack

Admin . 1085.maximum specific range is reached at minimum drag speed vmd for a piston engined aeroplane . 1135.vmd is the speed for maximum range in a prop aircraft .vmd is the speed for maximum endurance in a jet aircraft exemple 337 Maximum specific range.Maximum specific range.

For this question use reference sep 1 figure 2 3 .using the climb performance ?

Question 93-38 : 15640 ft 18909 ft 20109 ft 16665 ft

At 5000 ft isa t° is 5°c ..1500/1080= 1 39 minute.ground speed 100 + 5 = 105 kt.. 105/60 x 1 39 = 2 43 nm..2 43 = 4 5 km = 14722 ft . /com en/com032 362 jpg.closest answer is 15640 ft normally we should use the climb gradient since the question gives a speed in ias but rate of climb can also lead closely to the correct answer. ebbr1000 .tas= 108 kt.height difference x 100/ climb gradient= 1500 x 100 / 9 9 = 15151 ft. 15151 x gs / tas= 15151 x 113 / 108 = 15852 ft exemple 341 15640 ft.15640 ft.

For this question use reference .using the climb performance chart for the ?

Question 93-39 : 1140 ft/min and 10 6% 1030 ft/min and 8 4% 1170 ft/min and 9 9% 1140 ft/min and 8%

Isa at 3000 ft .15° 2° x 3 = +9°c.for a given ias the true airspeed is about 2% higher than ias per 1000ft of altitude above sea level . /com en/com032 363 jpg.rate of climb 1140 ft/min .gradient of climb 10 6% . atplea .figure cap698 figure 2 3 exemple 345 1140 ft/min and 10.6%.1140 ft/min and 10.6%.

At reference or use performance manual sep 1 figure 2 1.airport characteristics ?

Question 93-40 : 1500 ft 2000 ft 1750 ft 1350 ft

Img /com en/com032 405 png. exemple 349 1500 ft.1500 ft.

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