Un compte Premium offert sur le site FCL.055 ! Rendez-vous sur www.fcl055-exam.fr puis créez un compte avec le même email que celui...   [Lire la suite]


Given .pt = total pressure.ps = static pressure.pso = static pressure at sea ? [ Attestation AIM ]

Question 44-1 : Pt ps pt pso pt / ps pt pso / ps

exemple 144 Pt - psPt - ps

Given .pt = total pressure.ps = static pressure.pso = static pressure at sea ?

Question 44-2 : Pt ps pt pso pt pso / pso pt ps / ps

exemple 148 Pt - psPt - ps

Given .pt total pressure.ps static pressure.pd dynamic pressure.the airspeed ?

Question 44-3 : Pd ps pt pt pd pd ps

. 959.the asi is a sensitive differential pressure gauge which measures and promptly indicates the difference between pitot total pressure and static pressure total pressure static pressure = dynamic pressure .these two pressures are equal when the aircraft is parked on the ground in calm air .when the aircraft moves through the air the pressure on the pitot line becomes greater than the pressure in the static lines this difference in pressure is registered by the airspeed pointer on the face of the instrument .the airspeed indicator is fed with pt and ps it works on pt ps = pd exemple 152 Pd.Pd.

If an aircraft maintaining a constant cas and flight level is flying from a ?

Question 44-4 : Tas increases tas decreases mach number increases mach number decreases

.flying from a cold air mass into warmer air = density decreases with higher temperature air is expanding density is reduced .cas = 1/2 x density x tas².cas is constant and density decreases then tas must increase .mach = tas / local speed of sound.local speed of sound varies only with temperature lss varies with the square root of absolute temperature formula lss = 39 x square root of oat+273 and the question states 'flying from a cold air mass into warmer air' thus if tas increases and lss increases the mach number remains constant exemple 156 Tas increases.Tas increases.

If an aircraft maintaining a constant cas and flight level is flying from a ?

Question 44-5 : Tas decreases tas increases mach number increases mach number decreases

Admin .flying from a warm air mass into colder air = density increases with lower temperature air is contracting density is inscreased situation is similar to descent with a constant cas .for those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states maintaining a constant cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach . but mach number will not decrease since mach number and lss local speed of sound are proportional to each other which means that the temperature decrease will cause a decrease in lss as well as tas as tas reduces at the same rate the mach number will remain constant exemple 160 Tas decreases.Tas decreases.

If oat decreases when at a constant mach number ?

Question 44-6 : Tas decreases tas increases tas decreases only if the flight level remains constant tas remains constant only if the flight level remains constant

Admin .relation between mach number and tas depends only on oat and is independant of static pressure .at a constant flight level and constant mach number if oat decreases the tas will decrease but it would also do it in a climb in the standard atmosphere and descent in an inversion .mach number = tas /lss.local speed of sound lss changes in proportion to temperature if temperature reduce lss reduce .thus tas must reduce to keep mach number constant exemple 164 Tas decreases.Tas decreases.

If oat decreases when at a constant tas ?

Question 44-7 : Mach number increases mach number decreases mach number remains constant the difference between surrounding conditions and isa must be known to deduce the mach number variation

Admin .relation between mach number and tas depends only on oat and is independant of static pressure .at a constant flight level and constant tas if oat decreases the mach number will increase but it would also do it in a climb in the standard atmosphere and descent in an inversion .mach number = tas / lss.local speed of sound lss changes in proportion to temperature if temperature reduce lss reduce .thus mach number must increase to keep tas constant exemple 168 Mach number increases.Mach number increases.

If oat increases when at a constant mach number ?

Question 44-8 : Tas increases tas decreases tas decreases only if the flight level remains constant tas remains constant only if the flight level remains constant

Relation between mach number and tas depends only on oat and is independant of static pressure .at a constant flight level and constant mach number if oat increases the tas will increase but it would also do it in a climb in the standard atmosphere and descent in an inversion .mach number = tas / lss.local speed of sound lss changes in proportion to temperature if temperature increase lss increase .thus tas must increase to keep mach number constant .you can also say an oat increasing is similar to a decrease in altitude and use the 'ertm' diagram . 1039.the mach line is vertical because the question states at a constant mach number . ertm for e as/ r as rectified air speed or cas / t as/ m ach exemple 172 Tas increases.Tas increases.

If oat increases when at a constant tas ?

Question 44-9 : Mach number decreases mach number increases mach number remains constant the difference between surrounding conditions and isa must be known to deduce the mach number variation

Relation between mach number and tas depends only on oat and is independant of static pressure .at a constant flight level and constant tas if oat increases the mach number will decrease but it would also do it in a climb in the standard atmosphere and descent in an inversion .mach number = tas / lss.local speed of sound lss changes in proportion to temperature if temperature increase lss increase .thus mach number must reduce to keep tas constant exemple 176 Mach number decreases.Mach number decreases.

During a climb at a constant calibrated airspeed cas below the tropopause in ?

Question 44-10 : Tas and mach number increase tas and mach number decrease tas increases and mach number decreases tas decreases and mach number increases

For those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states climb at a constant calibrated airspeed cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach

In standard atmosphere when descending at constant cas ?

Question 44-11 : Tas decreases tas remains constant tas increases tas first increases and then remains constant below the tropopause

For those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states descending at constant cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach .cas = 1/2 rho v².density will increase during descent and in order to maintain constant cas only v tas can be reduced exemple 184 Tas decreases.Tas decreases.

In the absence of position and instrument errors cas is equal to ?

Question 44-12 : Ias eas tas ias and eas

Admin .an airspeed indicator displays ias .the error in altimeter readings caused by the variation of the static pressure near the source is known as position error .instrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicated .cas is ias corrected position and instrument errors

In the absence of position and instrument errors ?

Question 44-13 : Ias = cas ias = eas cas = eas cas = tas

.an airspeed indicator displays ias .the error in altimeter readings caused by the variation of the static pressure near the source is known as position error .instrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicated .cas is ias corrected position and instrument errors exemple 192 Ias = cas.Ias = cas.

The compressibility correction to cas to give eas .1 may be positive .2 is ?

Question 44-14 : 2 3 2 4 1 3 1 4

Admin .equivalent air speed eas is obtained from calibrated air speed cas by correcting for compressibility error .the size of the compressibility error varies with mach number and is always negative .air speed indicator are calibrated for standard atmosphere pressure temperature and density thus the reading is dependent on the dynamic pressure 1/2 x rho x v² the error in the readings is due to compression of the air on the forward part of the pitot tube component moving at high speeds .to avoid this error a compressibility correction has to be applied .compressibility correction = 1 + 1/4 x m² .eas = dynamic pressure x 1 + 1/4 x m² .the compressibility factor is always negative and is directly dependent on mach number exemple 196 2, 3.2, 3.

True air speed tas is obtained from indicated air speed ias by correcting for ?

Question 44-15 : 1 2 3 4 3 4 1 2 1 3 4

exemple 200 1, 2, 3, 4.1, 2, 3, 4.

Tas is ?

Question 44-16 : Eas corrected for density error eas corrected for compressibility error cas corrected for density error cas corrected for compressibility error

.true air speed tas is . ias corrected for instrument position compressibility and density errors . cas corrected for compressibility and density errors . eas corrected for density error exemple 204 Eas corrected for density error.Eas corrected for density error.

When climbing at a constant cas in a standard atmosphere .1 tas decreases .2 ?

Question 44-17 : 2 3 2 4 1 3 1 4

exemple 208 2, 3.2, 3.

When climbing at a constant cas ?

Question 44-18 : Mach number increases mach number decreases mach number remains constant the difference between surrounding conditions and isa must be known to deduce the mach number variation

For those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states climbing at a constant cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach .cas = 1/2 rho v².density will decrease during climb and in order to maintain constant cas only v tas can be increased .mach = tas / local speed of sound.local speed of sound varies only with temperature and temperature decreases during climb thus if tas increases and lss decreases the mach number increases exemple 212 Mach number increases.Mach number increases.

When descending at a constant cas in a standard atmosphere .1 tas increases .2 ?

Question 44-19 : 2 4 2 3 1 3 1 4

exemple 216 2, 4.2, 4.

When descending at a constant cas ?

Question 44-20 : Mach number decreases mach number increases mach number remains constant the difference between surrounding conditions and isa must be known to deduce the mach number variation

Admin .for those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states descending at a constant cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach .cas = 1/2 rho v².density will increase during descent and in order to maintain constant cas only v tas can be reduced .mach = tas / local speed of sound.local speed of sound varies only with temperature and temperature increases during descent thus if tas decreases and lss increases the mach number decreases exemple 220 Mach number decreases.Mach number decreases.

When descending at a constant mach number ?

Question 44-21 : Cas increases cas decreases cas remains constant the difference between surrounding conditions and isa must be known to deduce the cas variation

For those questions use the very simple 'ertm' diagram . 1039.the mach line is vertical because the question states descending at a constant mach number . ertm for e as/ r as rectified air speed or cas / t as/ m ach exemple 224 Cas increases.Cas increases.

When flying in cold air colder than standard atmosphere indicated altitude is ?

Question 44-22 : Higher than the true altitude the same as the true altitude lower than the true altitude equal to the standard altitude

Admin .in standard atmosphere temperature conditions your indicated altitude will be the same as your true altitude .but if it is warmer than isa your true altitude will be higher than your indicated altitude and if it is colder than isa your true altitude will be lower than your indicated altitude exemple 228 Higher than the true altitude.Higher than the true altitude.

When flying in cold air colder than standard atmosphere the altimeter will ?

Question 44-23 : Overestimate underestimate show the actual height above the sea level show the actual height above ground

.in standard atmosphere temperature conditions your indicated altitude will be the same as your true altitude .but if it is warmer than isa your true altitude will be higher than your indicated altitude and if it is colder than isa your true altitude will be lower than your indicated altitude .therefore your altimeter will overestimate in cold air exemple 232 Overestimate.Overestimate.

When flying in warm air warmer than standard atmosphere indicated altitude is ?

Question 44-24 : Lower than the true altitude the same as the true altitude higher than the true altitude equal to the standard altitude

exemple 236 Lower than the true altitude.Lower than the true altitude.

Which of the following statements are correct for an aeroplane cruising at fl ?

Question 44-25 : 1 2 and 3 are all correct 2 and 3 are correct 1 and 2 are correct 1 and 3 are correct

.tas = ias + 2% per 1000 ft altitude .eas is cas corrected for compressibility and at low speed and low altitude compressibility is negligeable .cas is ias corrected position and instrument errors exemple 240 1, 2 and 3 are all correct.1, 2 and 3 are all correct.

With eas and density altitude we can deduce ?

Question 44-26 : Tas cas cas and tas ias

Admin .with eas and density altitude we can deduce tas .with eas and pressure altitude zp we can deduce cas exemple 244 Tas.Tas.

With eas and pressure altitude zp we can deduce ?

Question 44-27 : Cas tas cas and tas ias

.eas is cas corrected for compressibility error which you would work out from pressure altitude .with eas and density altitude we can deduce tas exemple 248 Cas.Cas.

During a climb the total pressure probe of the airspeed indicator becomes ?

Question 44-28 : Decreases until reaching the stall speed increases until reaching vmo decreases by 1% per 600 ft increases by 1% per 600 ft

Admin .if the static system remains clear the airspeed indicator acts as an altimeter . 1004.true air speed tas is ias corrected for instrument position compressibility and density errors .thus with total pressure probe blocked to maintain a constant ias while altitude increases you must pull the stick or control column if not the indicated speed will increase you will quickly reach the stalling speed exemple 252 Decreases until reaching the stall speed.Decreases until reaching the stall speed.

With constant weight and configuration an aircraft always takes off at the same ?

Question 44-29 : Equivalent airspeed ground speed true airspeed indicated airspeed

.pressure errors i e errors in the measurement of pitot and static pressure are specific to the aircraft so we have to allow for them instrument error is specific to the instrument so we have to get the instrument calibrated and take it into account having corrected the indicated airspeed for these two errors we have calibrated airspeed .however small at take off speed we should correct for the effect of compressibility and that will give us equivalent airspeed .for a given weight and configuration the take off speed will depend on the density of the air so we don't correct for that hence the aircraft will take off at the same eas exemple 256 Equivalent airspeed.Equivalent airspeed.

An airspeed indicator includes a capsule inside this capsule is ?

Question 44-30 : Total pressure and outside is static pressure static pressure and outside is dynamic pressure dynamic pressure and outside is static pressure a very low residual pressure and outside is static pressure

Admin . 985.the asi is a sensitive differential pressure gauge which measures and promptly indicates the difference between pitot total pressure and static pressure total pressure static pressure = dynamic pressure .these two pressures are equal when the aircraft is parked on the ground in calm air .when the aircraft moves through the air the pressure on the pitot line becomes greater than the pressure in the static lines this difference in pressure is registered by the airspeed pointer on the face of the instrument exemple 260 Total pressure and outside is static pressure.Total pressure and outside is static pressure.

An aircraft is equipped with one altimeter that is compensated for position ?

Question 44-31 : The greater the speed the greater the error between the two altimeters the greater the speed the lower the error between the two altimeters the lower the speed the greater the error between the two altimeters the error between the two altimeters does not depend on the speed

exemple 264 The greater the speed, the greater the error between the two altimeters.The greater the speed, the greater the error between the two altimeters.

An aneroid capsule .1 measures differential pressure.2 measures absolute ?

Question 44-32 : 2 3 1 3 2 4 1 4

.the aneroid capsule is used to sense absolute pressure it is used for low pressure measurement exemple 268 2, 3.2, 3.

An altimeter contains one or more aneroid capsules inside these capsules is ?

Question 44-33 : A very low residual pressure and outside is static pressure static pressure and outside is dynamic pressure dynamic pressure and outside is static pressure static pressure and outside a very low residual pressure

exemple 272 A very low residual pressure and outside is static pressure.A very low residual pressure and outside is static pressure.

The altimeter of your aircraft indicates 10000 ft with a subscale setting of ?

Question 44-34 : 10000 ft 10400 ft 9600 ft 697 hpa

.an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa exemple 276 10000 ft.10000 ft.

The altimeter indicates true altitude ?

Question 44-35 : In isa conditions only when the temperature on the ground is +15 % with a lapse rate of 2 °c per 1000 feet and correct qnh is set when the temperature on the ground is +15 °c with a lapse rate of 2 °c per 1000 feet and correct qfe is set when pressure at mean sea level is 10135 25 hpa with a ground temperature of +15°c and a density equal to 1 225 kg/m3

exemple 280 In isa conditions only.In isa conditions only.

Tas can be obtained from the following data ?

Question 44-36 : Eas and density altitude eas and pressure altitude cas and density altitude cas and pressure altitude

exemple 284 Eas and density altitude.Eas and density altitude.

The maximum tas is obtained at ?

Question 44-37 : The flight level at which simultaneously cas = vmo and m = mmo the maximum flight level all the flight level s where cas =vmo all the flight level s where m =mmo

Admin .vmo and mmo are not dependent on the same criteria the aerodynamics of the aircraft will dictate these two values but you will ensure maximum tas at the point in the performance envelope where vmo = mmo because you cannot go faster in terms of cas or mach number exemple 288 The flight level at which simultaneously cas = vmo and m = mmo.The flight level at which simultaneously cas = vmo and m = mmo.

The input data of an adc are .1 oat .2 tat.3 static pressure .4 total ?

Question 44-38 : 2 3 4 1 2 3 4 1 3 4 1 2 4

exemple 292 2, 3, 4.2, 3, 4.

Given .mach number m = 0 70.measured impact temperature = 48 °c.the recovery ?

Question 44-39 : 65 °c 45 °c 68 °c 51 °c

Admin .the total temperature can be expressed approximately by the formula .tt = ts 1 + 0 2 kr m² . ts the static temperature sat in kelvin. tt the total temperature tat in kelvin. kr the recovery coefficient. m the mach number..225 15 = ts 1 + 0 2 kr m² .ts = 225 15 / 1 + 0 2 x 0 85 x 0 49 .ts = 225 15 / 1 0833 = 207 83° k.273 15 207 83 = 65 32°c exemple 296 -65 °c-65 °c

During a descent at a constant mach number below the tropopause in isa ?

Question 44-40 : Ias and tas increase ias and tas decrease ias increases and tas decreases ias decreases and tas increases

For those questions use the very simple 'ertm' diagram . 1039.the mach line is vertical because the question states descent at a constant mach number . ertm for e as/ r as rectified air speed or cas / t as/ m ach exemple 300 Ias and tas increase.Ias and tas increase.

~

Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

1719 Free Training Exam Other source study: Ppl exam examen 44