Question 58-1 : With constant weight and configuration an aircraft always takes off at the same ? [ Course landing ]

Question 58-2 : An airspeed indicator includes a capsule inside this capsule is ?

Total pressure and outside is static pressure.

985the 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 instrument

Question 58-3 : An aircraft is equipped with one altimeter that is compensated for position error and another one altimeter that is not assuming all other factors are equal during a straight symmetrical flight ?

The greater the speed the greater the error between the two altimeters.

Question 58-4 : An aneroid capsule 1 measures differential pressure2 measures absolute pressure3 is used for low pressure measurement4 is used for very high pressure measurementthe combination regrouping all the correct statements is ?

2 3.

The aneroid capsule is used to sense absolute pressure it is used for low pressure measurement

Question 58-5 : An altimeter contains one or more aneroid capsules inside these capsules is ?

A very low residual pressure and outside is static pressure.

Question 58-6 : The altimeter of your aircraft indicates 10000 ft with a subscale setting of 101325 hpa oat is +5°c the pressure altitude of the aircraft is ?

10000 ft.

An altimeter shows a pressure altitude with a sub scale setting of 101325 hpa

Question 58-7 : The altimeter indicates true altitude ?

Question 58-8 : Tas can be obtained from the following data ?

Eas and density altitude.

Question 58-9 : The maximum tas is obtained at ?

Question 58-10 : The input data of an adc are 1 oat 2 tat3 static pressure 4 total pressure the combination regrouping all the correct statements is ?

2 3 4.

Question 58-11 : Given mach number m = 070measured impact temperature = 48 °cthe recovery factor kr of the temperature probe = 085the oat sat is ?

65 °c.

The total temperature can be expressed approximately by the formula tt = ts 1 + 02 kr m² ts the static temperature sat in kelvin tt the total temperature tat in kelvin kr the recovery coefficient m the mach number22515 = ts 1 + 02 kr m² ts = 22515 1 + 02 x 085 x 049 ts = 22515 10833 = 20783° k27315 20783 = 6532°c

Question 58-12 : During a descent at a constant mach number below the tropopause in isa conditions ?

Ias and tas increase.

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

Question 58-13 : During a descent at a constant mach number below the tropopause in isa conditions ?

Cas and tas increase.

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

Question 58-14 : During a descent at a constant ias below the tropopause in isa conditions ?

Mach number and tas decrease.

For those questions use the very simple 'ertm' diagram 975the eas ias line is vertical because the question states descent at a constant ias ertm for e as r as rectified air speed or cas t as m achdensity will increase during descent and in order to maintain constant ias 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 58-15 : During a descent at a constant calibrated airspeed cas below the tropopause in isa conditions ?

Mach number and tas decrease.

For those questions use the very simple 'ertm' diagram 1037the cas line is vertical because the question states descent at a constant calibrated airspeed 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 58-16 : During a climb at a constant mach number below the tropopause in isa conditions ?

Ias and tas decrease.

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

Question 58-17 : If the pitot tube ices up during a flight the affected equipment s is are 1 the altimeter 2 the variometer 3 the airspeed indicator the combination regrouping all the correct statements is ?

3.

Pywee22 some pitot tubes are also equipped with static the question is not clear enough the question says pitot tube so i can assume that it is the entire tube static and total pressure therefore all instruments listed are affected as the question does not specify total pressure or static pressure i think we should consider that both are blocked are you sure about this answer can you explain the altimeter and variometer vertical speed indicator are connected to the static ports but they are not connected to the pitot tube therefore a blocked pitot tube will have no effect on these instruments

Question 58-18 : If during a descent the pneumatic altimeter reading is constant the vertical speed indicator shows zero the ias is increasing the most likely explanation is that ?

The static ports are completely blocked.

Question 58-19 : For tas calculations the adc uses the following parameters 1 sat 2 tat 3 static pressure 4 total pressure the combination regrouping all the correct statements is ?

2 3 4.

1023the adc uses as input data static pressure total pressure pitot pressure and tat

Question 58-20 : If the pitot tube becomes blocked during a descent the airspeed indicator ?

Under reads.

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 instrumentif the pitot tube becomes blocked during a descent the total pressure remains constant the static pressure increases your airspeed indicator will under reads

Question 58-21 : Given pt total pressureps static pressurepd dynamic pressurethe altimeter is fed by ?

Ps.

The altimeter is supplied with static pressure only

Question 58-22 : A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument s ?

Question 58-23 : A dynamic pressure measurement circuit is constituted of the following pressure probes ?

Total pressure and static pressure.

Question 58-24 : The qnh is by definition the value of the ?

Altimeter setting so that the altimeter on the apron of the aerodrome for which it is given reads the elevation.

Question 58-25 : The purpose of the vibrating device of an altimeter is to ?

Reduce the effect of friction in the linkages.

Question 58-26 : When climbing at a constant mach number ?

Cas 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 58-27 : When descending at a constant cas ?

Eas 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 acheas is cas corrected for compressibility

Question 58-28 : When climbing at a constant mach number through an isothermal layer the cas ?

Decreases.

Mach = tas local speed of soundlocal speed of sound varies only with temperature and the question states 'isothermal layer' temperature remains constant thus lss remains constant and the tas remains constantcas = 12 rho tas²rho is decreasing with altitude thus cas decreases

Question 58-29 : When climbing at a constant cas ?

Eas decreases.

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 acheas is cas corrected for compressibility cas will always be higher than eas

Question 58-30 : Vfe is the maximum speed ?

With the flaps extended for each approved flap position.

Question 58-31 : Tas is ?

Ias corrected for instrument position compressibility and density errors.

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 58-32 : Tas is ?

Cas corrected for compressibility and density errors.

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 58-33 : Assuming the flight level and mach number remain constant when the oat increases ?

Ias remains constant and tas increases.

The mach number is a function of p s swhere p = total pressure pitot s = static pressurein the absence of position and instrument errors ias = casias cas is 'p s'the question states 'mach number remain constant' thus ias remains constant ias cas = 12 rho tas²if air becomes less dense oat increases the only thing that can change in this equation is the tas increasing to compensate

Question 58-34 : Assuming the flight level and mach number remain constant when the oat decreases ?

Ias remains constant and tas decreases.

The mach number is a function of p s swhere p = total pressure pitot s = static pressurein the absence of position and instrument errors ias = casias cas is 'p s'the question states 'mach number remain constant' thus ias remains constant ias cas = 12 rho tas²if air becomes denser oat decreases the only thing that can change in this equation is the tas decreasing to compensate joangoris and what about the m=taslss formula if temperature decreases lss decreases so in order to maintain a cte mach tas has to increase i don't understand this questionlss = 39 x square root of oat+273 if oat decreases lss decreasesin order to maintain a constant mach number tas must decreaseexample oat 40°c tas 450 ktlss = 39 x square root of 233 = 595 ktm = taslss = 450 595 = 076 oat 50°c tas 450 ktlss = 39 x square root of 223 = 582 ktm = taslss = 450 582 = 077the only way to maintain mach number constant is to reduce tas oat 50°c tas 440 ktm = taslss = 440 582 = 076

Question 58-35 : A vertical speed indicator measures the difference between ?

The instantaneous static pressure and the static pressure at a previous moment.

Ecair04 vsi requires only static pressure like an inputthe operating principle of the vertical speed indicator vsi is based on the measurement of the rate of change of static pressure although the vertical speed indicator operates from the static pressure source it is a differential pressure instrument the differential pressure is established between the instantaneous static pressure in the diaphragm and the trapped static pressure within the case

Question 58-36 : At flight level and mach number constant if oat increases the cas ?

Remains constant.

The mach number is a function of p s swhere p = total pressure pitot s = static pressurecas is 'p s'the question states 'mach number constant' thus cas remains constant

Question 58-37 : A temperature sensor has a recovery factor of 095 the temperature measured is equal to ?

Static air temperature sat + 95% of the ram rise.

Recovery factor refers to the amount of ram rise that is recoverable by the sensor total head thermometers typically have a recovery factor of 075 to 09 whereas the rosemount temperature probe has a recovery factor of 10 the ram rise is due to adiabatic compression and for simple sat temperature sensors used on light aircraft that fly at speeds less than mach 02 the ram rise factor does not apply the sat sensor measures the actual temperature and is therefore 100% efficient tat is always equal to or higher than sat due to ram risethe formula's typically used are tat = sat + ram riseortat = sat x 1 + 02 kr m² where kr is the recovery factor and m the mach numberram rise comes into effect at airspeeds greater than m 02in summary sat temperature sensors are not affected by ram rise whereas tat sensors are

Question 58-38 : A thermocouple type temperature sensing is composed of ?

Two dissimilar metals joined together at one end called hot junction or measure junction .

Question 58-39 : At flight level and mach number constant if oat decreases the cas ?

Remains constant.

The mach number is a function of p s swhere p = total pressure pitot s = static pressurecas is 'p s'the question states 'mach number constant' thus cas remains constant

Question 58-40 : The altimeter of your aircraft indicates 15000 ft with a subscale setting of 101325 hpa oat is 21°c the pressure altitude of the aircraft is ?

15000 ft.

An altimeter shows a pressure altitude with a sub scale setting of 101325 hpa