Question 57-1 : At a given altitude the hysteresis error of an altimeter varies substantially with the ? [ Job lift off ]

Question 57-2 : Below the tropopause in standard conditions when climbing at a constant mach number ?

Tas decreases.

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

Question 57-3 : Below the tropopause when descending at a constant cas ?

Mach number decreases and the velocity of sound increases.

For those questions use the very simple 'ertm' diagram 1037the 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 achthe velocity of sound is increasing as temperature increases mach number = tas local sound speed

Question 57-4 : Below the tropopause in standard conditions when descending at a constant mach number ?

Tas increases.

For those questions use the very simple ertm diagram 1039the 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

Question 57-5 : Calibrated air speed cas is ?

Indicated air speed ias corrected for position and instrument errors.

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

Question 57-6 : Concerning the airspeed indicator ias is ?

The indicated reading on the instrument.

An airspeed indicator displays ias

Question 57-7 : Considering the relationship between cas and eas ?

Question 57-8 : Due to its conception the altimeter measures a ?

Pressure altitude.

Question 57-9 : During descent the total pressure probe of the airspeed indicator becomes blocked in this case 1 ias becomes greater than cas2 ias becomes lower than cas3 maintaining ias constant vmo may be exceeded4 maintaining ias constant aircraft may stallthe combination regrouping all the correct ?

Question 57-10 : For the same tas when pressure altitude decreases below the tropopause ?

Mach number decreases.

Pressure altitude decreases = descendingfor those questions use the very simple 'ertm' diagram 1040the 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

Question 57-11 : For the same tas when pressure altitude increases below the tropopause ?

Mach number increases.

Pressure altitude increases = climbingfor those questions use the very simple 'ertm' diagram 1040the 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

Question 57-12 : Given pt = total pressureps = static pressurepd = dynamic pressure ?

Pt = pd + ps.

Question 57-13 : Given pt = total pressureps = static pressurepso = static pressure at sea levelcalibrated airspeed cas is a function of ?

Pt ps.

Question 57-14 : Given pt = total pressureps = static pressurepso = static pressure at sea leveldynamic pressure is ?

Pt ps.

Question 57-15 : Given pt total pressureps static pressurepd dynamic pressurethe airspeed indicator is fed by ?

Pd.

959the 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 airwhen 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 instrumentthe airspeed indicator is fed with pt and ps it works on pt ps = pd

Question 57-16 : If an aircraft maintaining a constant cas and flight level is flying from a cold air mass into warmer air ?

Tas increases.

Flying from a cold air mass into warmer air = density decreases with higher temperature air is expanding density is reduced cas = 12 x density x tas²cas is constant and density decreases then tas must increasemach = tas local speed of soundlocal 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

Question 57-17 : If an aircraft maintaining a constant cas and flight level is flying from a warm air mass into colder air ?

Tas 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 casfor those questions use the very simple ertm diagram 1037the 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

Question 57-18 : If oat decreases when at a constant mach number ?

Tas decreases.

Relation between mach number and tas depends only on oat and is independant of static pressureat 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 inversionmach number = tas lsslocal speed of sound lss changes in proportion to temperature if temperature reduce lss reducethus tas must reduce to keep mach number constant

Question 57-19 : If oat decreases when at a constant tas ?

Mach number increases.

Relation between mach number and tas depends only on oat and is independant of static pressureat 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 inversionmach number = tas lsslocal speed of sound lss changes in proportion to temperature if temperature reduce lss reducethus mach number must increase to keep tas constant

Question 57-20 : If oat increases when at a constant mach number ?

Tas increases.

Relation between mach number and tas depends only on oat and is independant of static pressureat 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 inversionmach number = tas lsslocal speed of sound lss changes in proportion to temperature if temperature increase lss increasethus tas must increase to keep mach number constantyou can also say an oat increasing is similar to a decrease in altitude and use the 'ertm' diagram 1039the 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

Question 57-21 : If oat increases when at a constant tas ?

Mach number decreases.

Relation between mach number and tas depends only on oat and is independant of static pressureat 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 inversionmach number = tas lsslocal speed of sound lss changes in proportion to temperature if temperature increase lss increasethus mach number must reduce to keep tas constant

Question 57-22 : During a climb at a constant calibrated airspeed cas below the tropopause in standard conditions ?

Question 57-23 : In standard atmosphere when descending at constant cas ?

Tas decreases.

For those questions use the very simple ertm diagram 1037the 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 achcas = 12 rho v²density will increase during descent and in order to maintain constant cas only v tas can be reduced

Question 57-24 : In the absence of position and instrument errors cas is equal to ?

Question 57-25 : In the absence of position and instrument errors ?

Ias = cas.

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

Question 57-26 : The compressibility correction to cas to give eas 1 may be positive 2 is always negative3 depends on mach number only 4 depends on pressure altitude only the combination regrouping all the correct statements is ?

2 3.

Equivalent air speed eas is obtained from calibrated air speed cas by correcting for compressibility errorthe 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 12 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 appliedcompressibility correction = 1 + 14 x m² eas = dynamic pressure x 1 + 14 x m² the compressibility factor is always negative and is directly dependent on mach number

Question 57-27 : True air speed tas is obtained from indicated air speed ias by correcting for the following errors 1 instrument 2 position 3 compressibility 4 density the combination regrouping all the correct statements is ?

1 2 3 4.

Question 57-28 : Tas is ?

Eas corrected for density 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

Question 57-29 : When climbing at a constant cas in a standard atmosphere 1 tas decreases 2 tas increases 3 mach number increases 4 mach number decreases the combination regrouping all the correct statements is ?

2 3.

Question 57-30 : When climbing at a constant cas ?

Mach number increases.

For those questions use the very simple 'ertm' diagram 1037the 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 achcas = 12 rho v²density will decrease during climb and in order to maintain constant cas only v tas can be increasedmach = tas local speed of soundlocal speed of sound varies only with temperature and temperature decreases during climb thus if tas increases and lss decreases the mach number increases

Question 57-31 : When descending at a constant cas in a standard atmosphere 1 tas increases 2 tas decreases 3 mach number increases 4 mach number decreases the combination regrouping all the correct statements is ?

2 4.

Question 57-32 : When descending at a constant cas ?

Mach number decreases.

For those questions use the very simple ertm diagram 1037the 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 achcas = 12 rho v²density will increase during descent and in order to maintain constant cas only v tas can be reducedmach = tas local speed of soundlocal speed of sound varies only with temperature and temperature increases during descent thus if tas decreases and lss increases the mach number decreases

Question 57-33 : When descending at a constant mach number ?

Cas increases.

For those questions use the very simple 'ertm' diagram 1039the 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

Question 57-34 : When flying in cold air colder than standard atmosphere indicated altitude is ?

Higher than the true altitude.

In standard atmosphere temperature conditions your indicated altitude will be the same as your true altitudebut 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

Question 57-35 : When flying in cold air colder than standard atmosphere the altimeter will ?

Overestimate.

In standard atmosphere temperature conditions your indicated altitude will be the same as your true altitudebut 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 altitudetherefore your altimeter will overestimate in cold air

Question 57-36 : When flying in warm air warmer than standard atmosphere indicated altitude is ?

Lower than the true altitude.

Question 57-37 : Which of the following statements are correct for an aeroplane cruising at fl 60 with a true airspeed tas of 100 kt in standard atmospheric conditions 1 the tas is approximately 10% higher than the ias2 the difference between the equivalent airspeed eas and the calibrated airspeed cas is negligible3 ?

1 2 and 3 are all correct.

Tas = ias + 2% per 1000 ft altitudeeas is cas corrected for compressibility and at low speed and low altitude compressibility is negligeablecas is ias corrected position and instrument errors

Question 57-38 : With eas and density altitude we can deduce ?

Tas.

With eas and density altitude we can deduce taswith eas and pressure altitude zp we can deduce cas

Question 57-39 : With eas and pressure altitude zp we can deduce ?

Cas.

Eas is cas corrected for compressibility error which you would work out from pressure altitudewith eas and density altitude we can deduce tas

Question 57-40 : During a climb the total pressure probe of the airspeed indicator becomes blocked if the pilot maintains a constant indicated airspeed the true airspeed ?

Decreases until reaching the stall speed.

If the static system remains clear the airspeed indicator acts as an altimeter 1004true air speed tas is ias corrected for instrument position compressibility and density errorsthus 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