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Skills > lift > off : During descent the total pressure probe of the airspeed indicator becomes ?

Question 43-1 : 2 3 2 4 1 3 1 4

Joangoris .the only way to maintain a constant ias with a blocked pitot tube is maintaining your altitude nothing to do with your throttle or tas no matter if you are near stall or near overspeed so i don't understand the last two statements please help .thanks..total pressure probe = pitot tube.when it becomes blocked the total pressure in the capsule is fixed dynamic pressure + static .during descent static pressure from the static port will increase and compresses the capsule causing the indicated airspeed ias to decrease your airspeed indicator becomes an altimeter .when you read 'maintaining ias constant vmo may be exceeded' you must understand that you are in the cockpit and your speed is decreasing so your action will be to accelerate and your vmo may be exceeded exemple 143 2, 3.2, 3.

For the same tas when pressure altitude decreases below the tropopause ?

Question 43-2 : 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

Pressure altitude decreases = descending.for those questions use the very simple 'ertm' diagram. 1040..the tas line is vertical because the question states for the same tas. ertm for e as/ r as rectified air speed or cas / t as/ m ach exemple 147 mach number decreases.mach number decreases.

For the same tas when pressure altitude increases below the tropopause ?

Question 43-3 : 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

Pressure altitude increases = climbing.for those questions use the very simple 'ertm' diagram. 1040..the tas line is vertical because the question states for the same tas. ertm for e as/ r as rectified air speed or cas / t as/ m ach exemple 151 mach number increases.mach number increases.

Given .pt = total pressure.ps = static pressure.pd = dynamic pressure ?

Question 43-4 : Pt = pd + ps pd = pt + ps ps = pt + pd pd = pt / ps

exemple 155 pt = pd + pspt = pd + ps

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

Question 43-5 : Pt ps pt pso pt / ps pt pso / ps

exemple 159 pt - pspt - ps

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

Question 43-6 : Pt ps pt pso pt pso / pso pt ps / ps

exemple 163 pt - pspt - ps

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

Question 43-7 : 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 167 pd.pd.

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

Question 43-8 : 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 171 tas increases.tas increases.

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

Question 43-9 : Tas decreases tas increases mach number increases mach number decreases

.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 175 tas decreases.tas decreases.

If oat decreases when at a constant mach number ?

Question 43-10 : Tas decreases tas increases 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 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 179 tas decreases.tas decreases.

If oat decreases when at a constant tas ?

Question 43-11 : 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

.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 183 mach number increases.mach number increases.

If oat increases when at a constant mach number ?

Question 43-12 : 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 187 tas increases.tas increases.

If oat increases when at a constant tas ?

Question 43-13 : 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 191 mach number decreases.mach number decreases.

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

Question 43-14 : 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 exemple 195 tas and mach number increase.tas and mach number increase.

In standard atmosphere when descending at constant cas ?

Question 43-15 : 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 199 tas decreases.tas decreases.

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

Question 43-16 : Ias eas tas ias and eas

.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 203 ias.ias.

In the absence of position and instrument errors ?

Question 43-17 : 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 207 ias = cas.ias = cas.

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

Question 43-18 : 2 3 2 4 1 3 1 4

.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 211 2, 3.2, 3.

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

Question 43-19 : 1 2 3 4 3 4 1 2 1 3 4

exemple 215 1, 2, 3, 4.1, 2, 3, 4.

Tas is ?

Question 43-20 : 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 219 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 43-21 : 2 3 2 4 1 3 1 4

exemple 223 2, 3.2, 3.

When climbing at a constant cas ?

Question 43-22 : 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 227 mach number increases.mach number increases.

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

Question 43-23 : 2 4 2 3 1 3 1 4

exemple 231 2, 4.2, 4.

When descending at a constant cas ?

Question 43-24 : 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

.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 235 mach number decreases.mach number decreases.

When descending at a constant mach number ?

Question 43-25 : 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 239 cas increases.cas increases.

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

Question 43-26 : Higher than the true altitude the same as the true altitude lower than the true altitude equal to the standard altitude

.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

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

Question 43-27 : 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 247 overestimate.overestimate.

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

Question 43-28 : Lower than the true altitude the same as the true altitude higher than the true altitude equal to the standard altitude

exemple 251 lower than the true altitude.lower than the true altitude.

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

Question 43-29 : 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 255 1, 2 and 3 are all correct.1, 2 and 3 are all correct.

With eas and density altitude we can deduce ?

Question 43-30 : Tas cas cas and tas ias

.with eas and density altitude we can deduce tas .with eas and pressure altitude zp we can deduce cas exemple 259 tas.tas.

With eas and pressure altitude zp we can deduce ?

Question 43-31 : 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 263 cas.cas.

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

Question 43-32 : Decreases until reaching the stall speed increases until reaching vmo decreases by 1% per 600 ft increases by 1% per 600 ft

.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 267 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 43-33 : 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 271 equivalent airspeed.equivalent airspeed.

An airspeed indicator includes a capsule inside this capsule is ?

Question 43-34 : 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

. 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 275 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 43-35 : 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 279 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 43-36 : 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 283 2, 3.2, 3.

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

Question 43-37 : 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 287 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 43-38 : 10000 ft 10400 ft 9600 ft 697 hpa

.an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa exemple 291 10000 ft.10000 ft.

The altimeter indicates true altitude ?

Question 43-39 : 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 295 in isa conditions only.in isa conditions only.

Tas can be obtained from the following data ?

Question 43-40 : Eas and density altitude eas and pressure altitude cas and density altitude cas and pressure altitude

exemple 299 eas and density altitude.eas and density altitude.

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