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

Equivalent 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 158 Equivalent airspeed.

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

Total 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 162 Total pressure and outside is static pressure.

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

exemple 166 The greater the speed, the greater the error between the two altimeters.

Question 58-4 : An aneroid capsule .1 measures differential pressure.2 measures absolute pressure.3 is used for low pressure measurement.4 is used for very high pressure measurement.the 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 exemple 170 2, 3.

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

exemple 174 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 1013 25 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 1013 25 hpa exemple 178 10000 ft.

Question 58-7 : The altimeter indicates true altitude ?

In isa conditions only


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

Eas and density altitude

exemple 186 Eas and density altitude.

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

The flight level at which simultaneously cas = vmo and 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

Question 58-10 : The input data of an adc are .1 oat .2 tat.3 static pressure .4 total pressure .the combination regrouping all the correct statements is ?

2 3 4

exemple 194 2, 3, 4.

Question 58-11 : Given .mach number m = 0 70.measured impact temperature = 48 °c.the recovery factor kr of the temperature probe = 0 85.the oat sat is ?

65 °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 198 -65 °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 . 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 202 Ias and tas increase.

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 . 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 206 Cas and tas increase.

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

Mach number and tas decrease

Admin .for those questions use the very simple 'ertm' diagram . 975.the 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 ach .density will increase during descent and in order to maintain constant ias 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 210 Mach number and tas decrease.

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 . 1037.the 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 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 214 Mach number and tas decrease.

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 . 1039.the 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 exemple 218 Ias and tas decrease.

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 exemple 222 3.

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

exemple 226 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

. 1023.the adc uses as input data static pressure total pressure pitot pressure and tat exemple 230 2, 3, 4.

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

Under reads

. 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 .if the pitot tube becomes blocked during a descent the total pressure remains constant the static pressure increases your airspeed indicator will under reads exemple 234 Under-reads.

Question 58-21 : Given .pt total pressure.ps static pressure.pd dynamic pressure.the altimeter is fed by ?

Ps

.the altimeter is supplied with static pressure only exemple 238 Ps.

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

Airspeed indicator


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

Total pressure and static pressure

exemple 246 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

exemple 250 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

exemple 254 Reduce the effect of friction in the linkages.

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

Cas decreases

Admin .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 258 Cas decreases.

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

Eas increases

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 .eas is cas corrected for compressibility exemple 262 Eas increases.

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

Decreases

Admin .mach = tas / local speed of sound.local speed of sound varies only with temperature and the question states 'isothermal layer' temperature remains constant thus lss remains constant and the tas remains constant .cas = 1/2 rho tas².rho is decreasing with altitude thus cas decreases exemple 266 Decreases.

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

Eas decreases

Admin .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 .eas is cas corrected for compressibility cas will always be higher than eas exemple 270 Eas decreases.

Question 58-30 : Vfe is the maximum speed ?

With the flaps extended for each approved flap position

exemple 274 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 exemple 278 Ias corrected for instrument, position, compressibility and density errors.

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 exemple 282 Cas corrected for compressibility and density errors.

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 /s.where p = total pressure pitot .s = static pressure.in the absence of position and instrument errors ias = cas .ias cas is 'p s'.the question states 'mach number remain constant' thus ias remains constant .ias cas = 1/2 rho tas².if air becomes less dense oat increases the only thing that can change in this equation is the tas increasing to compensate exemple 286 Ias remains constant and tas increases.

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 /s.where p = total pressure pitot .s = static pressure.in the absence of position and instrument errors ias = cas .ias cas is 'p s'.the question states 'mach number remain constant' thus ias remains constant .ias cas = 1/2 rho tas².if 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=tas/lss formula if temperature decreases lss decreases so in order to maintain a cte mach tas has to increase i don't understand this question..lss = 39 x square root of oat+273 .if oat decreases lss decreases .in order to maintain a constant mach number tas must decrease .example . oat 40°c tas 450 kt .lss = 39 x square root of 233 = 595 kt.m = tas/lss = 450 / 595 = 0 76. oat 50°c tas 450 kt .lss = 39 x square root of 223 = 582 kt.m = tas/lss = 450 / 582 = 0 77.the only way to maintain mach number constant is to reduce tas . oat 50°c tas 440 kt.m = tas/lss = 440 / 582 = 0 76 exemple 290 Ias remains constant and tas decreases.

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 input ..the 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 exemple 294 The instantaneous static pressure and the static pressure at a previous moment.

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

Remains constant

Admin .the mach number is a function of p s /s.where p = total pressure pitot .s = static pressure.cas is 'p s'.the question states 'mach number constant' thus cas remains constant exemple 298 Remains constant.

Question 58-37 : A temperature sensor has a recovery factor of 0 95 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 0 75 to 0 9 whereas the rosemount temperature probe has a recovery factor of 1 0 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 0 2 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 rise ..the formula's typically used are tat = sat + ram rise.or.tat = sat x 1 + 0 2 kr m² where kr is the recovery factor and m the mach number ..ram rise comes into effect at airspeeds greater than m 0 2..in summary sat temperature sensors are not affected by ram rise whereas tat sensors are exemple 302 Static air temperature (sat) + 95% of the ram rise.

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

exemple 306 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 /s.where p = total pressure pitot .s = static pressure.cas is 'p s'.the question states 'mach number constant' thus cas remains constant exemple 310 Remains constant.

Question 58-40 : The altimeter of your aircraft indicates 15000 ft with a subscale setting of 1013 25 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 1013 25 hpa exemple 314 15000 ft.


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