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In an adc air data computer the altitude is computed from ? [ Understand DGAC ]

Question 47-1 : Measurement of barometric pressure from a static source on the fuselage static pressure the difference between absolute and dynamic pressure at the fuselage measurement of outside air temperature oat measurement of elapsed time for a radio signal transmitted to the ground surface and back

exemple 147 Measurement of barometric pressure from a static source on the fuselage (static pressure).Measurement of barometric pressure from a static source on the fuselage (static pressure).

Indication of mach number is obtained from ?

Question 47-2 : Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid an ordinary airspeed indicator scaled for mach numbers instead of knots a kind of echo sound comparing velocity of sound with indicated speed indicated speed ias compared with true air speed tas from the air data computer

Admin .the mach meter modifies the output from an airspeed capsule by using an altimeter aneroid capsule exemple 151 Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid.Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid.

The altimeter consists of one or several aneroid capsules located in a sealed ?

Question 47-3 : I vacuum or a very low pressure ii static pressure i static pressure at time t ii static pressure at time t dt i total pressure ii static pressure i static pressure ii total pressure

exemple 155 (i) vacuum (or a very low pressure) (ii) static pressure(i) vacuum (or a very low pressure) (ii) static pressure

In case of accidental closing of an aircraft's left static pressure port rain ?

Question 47-4 : Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight underreads the altitude overreads the altitude in case of a side slip to the right and displays the correct information during symmetric flight keeps on providing reliable reading in all situations

Amassa .with a side slip to the left pressure will increase on the left side of the aircraft and decrease on the right .if both static ports are open the pressures are compensated this is why two static ports are used .so a lower static pressure will be sensed and the altimeter will overread the aircraft's altitude exemple 159 Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight.Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight.

The vertical speed indicator vsi is fed by ?

Question 47-5 : Static pressure dynamic pressure total pressure differential pressure

exemple 163 Static pressureStatic pressure

The altimeter is supplied with ?

Question 47-6 : Static pressure dynamic pressure total pressure differential pressure

exemple 167 Static pressure.Static pressure.

Total air temperature tat is ?

Question 47-7 : Higher or equal to static air temperature sat depending on mach number and sat lower than static air temperature sat depending on altitude and sat higher or equal to static air temperature sat depending on altitude and sat lower than static air temperature sat depending on mach number and sat

Admin .tat = sat 1 + 0 2 x kr x m² . sat the static temperature in kelvin. tat the total temperature in kelvin. kr the recovery coefficient. m the mach number.if mach is 0 sat = tat .if sat is 0 tat = sat .absolute zero in kelvin is almost impossible to reach but from the formula tat will be 0 if sat is 0 exemple 171 Higher or equal to static air temperature (sat) depending on mach number and sat.Higher or equal to static air temperature (sat) depending on mach number and sat.

An air data computer .1 supplies gs and drift angle.2 determines tat and true ?

Question 47-8 : 3 4 5 1 2 2 5 2 3 4

Admin .the adc air data computer uses as input data static pressure total pressure pitot pressure and tat . 1023 exemple 175 3, 4, 5.3, 4, 5.

An aircraft is flying at flight level fl180 and mach number 0 36 its onboard ?

Question 47-9 : Standard + 10°c standard + 30°c standard + 20°c standard

Admin .what is the oat outside air temperature at fl180 in standard atmosphere .15° 2 x 18 ° = 21ºc at fl180 .calculation . 997.oat at fl180 is 11°c instead of 21°c the present weather conditions compared with the standard atmosphere are standard + 10°c exemple 179 Standard + 10°c.Standard + 10°c.

An airspeed indicator displays ?

Question 47-10 : Ias eas cas tas

Img1034.ias for indicated air speed exemple 183 Ias.Ias.

The angle of attack transmitter placed laterally on the forward part of the ?

Question 47-11 : 2 3 1 2 3 1 2 1 3

.conical slotted probe the angle of attack aoa probe provides aoa or sideslip ss by sensing the direction of local airflow it is mounted on the fuselage with the sensing probe extending through the aircraft fuselage the sensing probe is continually driven to null pressure differential between the upper and lower slots in its forward surface these features sense the direction of air stream flow local aoa or ss the angular position of the sensing probe is converted to an electrical output by an angular sensor . 998. 999.vane detector the angle of attack sensor is of the wind vane type its sensing element is a small wing which is positioned in the direction of airflow the small wing is mechanically linked to a free turn shaft which drives the devices transmitting the local angle of attack signal . 1000. exemple 187 2, 3.2, 3.

At a given altitude the hysteresis error of an altimeter varies substantially ?

Question 47-12 : Time passed at this altitude mach number of the aircraft aircraft attitude static temperature

Admin .hysteresis this error is a lag in the altitude indications caused by the elasticity of the aneroid capsule it occurs when an aircraft initiates a large rapid altitude change or an abrupt level off from a rapid climb or descent it takes a period of time for the aneroid to catch up with the new pressure environment hence a lag in indications this error has been significantly reduced in modern altimeters and is considered negligible at normal rates of descent for jet aircraft exemple 191 Time passed at this altitude.Time passed at this altitude.

Below the tropopause in standard conditions when climbing at a constant mach ?

Question 47-13 : Tas decreases tas increases tas remains constant the difference between surrounding conditions and isa must be known to deduce the tas variation

For those questions use the very simple 'ertm' diagram . 1039.the 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 exemple 195 Tas decreases.Tas decreases.

Below the tropopause when descending at a constant cas ?

Question 47-14 : Mach number decreases and the velocity of sound increases mach number increases and the velocity of sound decreases mach number and the velocity of sound increase mach number and the velocity of sound decrease

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 .the velocity of sound is increasing as temperature increases .mach number = tas / local sound speed exemple 199 Mach number decreases and the velocity of sound increases.Mach number decreases and the velocity of sound increases.

Below the tropopause in standard conditions when descending at a constant mach ?

Question 47-15 : Tas increases tas decreases tas remains constant the difference between surrounding conditions and isa must be known to deduce the tas variation

Admin .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 203 Tas increases.Tas increases.

Calibrated air speed cas is ?

Question 47-16 : Indicated air speed ias corrected for position and instrument errors indicated air speed ias corrected for compressibility error equivalent air speed eas corrected for density error equivalent air speed eas corrected for compressibility and density errors

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 exemple 207 Indicated air speed (ias) corrected for position and instrument errors.Indicated air speed (ias) corrected for position and instrument errors.

Concerning the airspeed indicator ias is ?

Question 47-17 : The indicated reading on the instrument the indicated reading on an instrument presumed to be perfect the indicated airspeed corrected for instrument and position errors the indicated airspeed corrected for instrument error only

.an airspeed indicator displays ias exemple 211 The indicated reading on the instrument.The indicated reading on the instrument.

Considering the relationship between cas and eas ?

Question 47-18 : Eas is always lower than or equal to cas eas is always greater than or equal to cas eas may be lower or greater than cas depending on pressure altitude eas may be lower or greater than cas depending on density altitude

Admin .eas is cas corrected for compressibility .compressibility error always results in an incorrect and a higher ias/cas being observed on the airspeed indicator exemple 215 Eas is always lower than or equal to cas.Eas is always lower than or equal to cas.

Due to its conception the altimeter measures a ?

Question 47-19 : Pressure altitude density altitude temperature altitude true altitude

exemple 219 Pressure altitudePressure altitude

During descent the total pressure probe of the airspeed indicator becomes ?

Question 47-20 : 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 223 2, 3.2, 3.

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

Question 47-21 : 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 227 Mach number decreases.Mach number decreases.

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

Question 47-22 : 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

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 231 Mach number increases.Mach number increases.

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

Question 47-23 : Pt = pd + ps pd = pt + ps ps = pt + pd pd = pt / ps

exemple 235 Pt = pd + psPt = pd + ps

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

Question 47-24 : Pt ps pt pso pt / ps pt pso / ps

exemple 239 Pt - psPt - ps

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

Question 47-25 : Pt ps pt pso pt pso / pso pt ps / ps

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

Question 47-26 : 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 247 Pd.Pd.

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

Question 47-27 : 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 251 Tas increases.Tas increases.

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

Question 47-28 : 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 255 Tas decreases.Tas decreases.

If oat decreases when at a constant mach number ?

Question 47-29 : 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 259 Tas decreases.Tas decreases.

If oat decreases when at a constant tas ?

Question 47-30 : 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 263 Mach number increases.Mach number increases.

If oat increases when at a constant mach number ?

Question 47-31 : 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 267 Tas increases.Tas increases.

If oat increases when at a constant tas ?

Question 47-32 : 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 271 Mach number decreases.Mach number decreases.

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

Question 47-33 : 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 275 Tas and mach number increase.Tas and mach number increase.

In standard atmosphere when descending at constant cas ?

Question 47-34 : 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 279 Tas decreases.Tas decreases.

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

Question 47-35 : 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 exemple 283 Ias.Ias.

In the absence of position and instrument errors ?

Question 47-36 : 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 287 Ias = cas.Ias = cas.

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

Question 47-37 : 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 291 2, 3.2, 3.

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

Question 47-38 : 1 2 3 4 3 4 1 2 1 3 4

exemple 295 1, 2, 3, 4.1, 2, 3, 4.

Tas is ?

Question 47-39 : 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 299 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 47-40 : 2 3 2 4 1 3 1 4

exemple 303 2, 3.2, 3.

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