Un compte Premium offert sur le site FCL.055 ! Rendez-vous sur www.fcl055-exam.fr puis créez un compte avec le même email que celui...   [Lire la suite]


Free > airport : In a standard atmosphere and at the sea level the calibrated airspeed cas is ?

Question 45-1 : Equal to the true airspeed tas independent of the true airspeed tas higher than the true airspeed tas lower than the true airspeed tas

exemple 145 equal to the true airspeed (tas).equal to the true airspeed (tas).

The parameter that determines the relationship between eas and tas is ?

Question 45-2 : Density altitude pressure altitude oat mach number

exemple 149 density altitude.density altitude.

With cas and pressure altitude we can deduce ?

Question 45-3 : Eas tas eas and tas nothing

exemple 153 eas.eas.

Speed of sound is proportional to ?

Question 45-4 : The square root of the absolute temperature the square root of the tas the square of the absolute temperature the square of the tas

exemple 157 the square root of the absolute temperature.the square root of the absolute temperature.

The total air temperature tat is ?

Question 45-5 : The temperature resulting from the aircraft motion in the air the static air temperature sat multiplied by the recovery factor the impact air temperature measured by the pitot probe the average temperature resulting from the temperature measure of the pitot and tat probes

.total air temperature tat is the temperature that would be measured by a temperature probe if all of the kinetic energy of air resulting from aircraft's motion was totally recovered this can never be very accurately measured because 100% recovery of kinetic energy is impossible for a number of reasons exemple 161 the temperature resulting from the aircraft motion in the air.the temperature resulting from the aircraft motion in the air.

During a climb if the total pressure head is rapidly clogged up by ice the ?

Question 45-6 : The static pressure decreases implying an increasing ias the static pressure decreases implying a decreasing ias the ias remains also constant the static pressure increases implying a decreasing ias

.'total pressure head' = pitot tube it senses the dynamic pressure + the static pressure .while climbing the static pressure decreases.if the total pressure head is clogged up by ice the airspeed indicator will then show an increasing speed .indicated airspeed = dynamic pressure + static pressure static pressure.since the question states the sensed total pressure remains constant the value ' dynamic pressure + static pressure ' does not change only 'static pressure' reduces the consequence is an increasing indicated airspeed exemple 165 the static pressure decreases, implying an increasing ias.the static pressure decreases, implying an increasing ias.

The static air temperature sat is ?

Question 45-7 : The ambient outside air temperature the temperature resulting from the aircraft motion in the air the outside air temperature measured by the pitot probe the tat divided by the recovery factor

.in aviation terminology the outside air temperature oat or static air temperature sat refers to the temperature of the air around an aircraft but unaffected by the passage of the aircraft through it exemple 169 the ambient outside air temperature.the ambient outside air temperature.

The limits of the green scale of an airspeed indicator are ?

Question 45-8 : Vs1 and vno vs1 and vmo vs0 and vne vs1 and vne

exemple 173 vs1 and vno.vs1 and vno.

Concerning the pitot and static system the static pressure error varies ?

Question 45-9 : 2 and 3 1 2 and 3 1 and 3 1 and 2

.the static port will be affected by speed compressibility effect and by angle of attack air flow aournd the fuselage will change altimeter setting is irrelevant to the pressure sensed at the static port exemple 177 2 and 3.2 and 3.

The alternate static source is used ?

Question 45-10 : When the static ports become blocked when the drain holes freeze to compensate the static pressure error to compensate the hysteresis of the aneroid capsule

.the alternate static vent of an unpressurised aircraft senses the air pressure in the flight deck/cockpit in flight the air outside the flight deck accelerates over the aircraft canopy venturi effect this causes a drop in static pressure air will always flow from a high pressure to a low pressure so air in the flight deck flows outside this flow to the outside causes the pressure in the cabin to be lower than the undisturbed static pressure around the aircraft

The machmeter is subject to position error this error varies according to .1 ?

Question 45-11 : 1 3 1 2 3 3 1

.position pressure error varies with angle of attack and speed but not with temperature exemple 185 1, 3.1, 3.

The data output from the adc are.1 barometric altitude.2 mach number.3 cas.4 ?

Question 45-12 : 1 2 3 4 5 1 4 2 3 4 1 3 5

An aeroplane is cruising at fl 60 with a tas of 100 kt in standard atmosphere ?

Question 45-13 : 1 2 3 2 3 1 2 1 3

.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 193 1, 2, 3.1, 2, 3.

The tas is obtained from the cas by correcting for the following errors .1 ?

Question 45-14 : 2 4 2 4 1 2 3 4

exemple 197 2, 4.2, 4.

The cas is obtained from ias by correcting for the following errors .1 ?

Question 45-15 : 1 3 3 1 3 4 2 3 4

exemple 201 1, 3.1, 3.

The eas is obtained from the cas by correcting for the following errors .1 ?

Question 45-16 : 2 4 2 4 1 2 3 4

exemple 205 22

If the static ports are completely clogged up by ice during a climb the ?

Question 45-17 : Zero a descent if the outside static pressure is less than the pressure in the instrument's gauge a constant rate of climb even if the aircraft is levelling out an increasing rate of climb if the ambient static pressure decreases

exemple 209 zero.zero.

Eas is equal to ?

Question 45-18 : Cas corrected for compressibility error cas corrected for density error tas corrected for compressibility error tas corrected for compressibility and density errors

exemple 213 cas corrected for compressibility error.cas corrected for compressibility error.

During a climb at a constant mach number below the tropopause in standard ?

Question 45-19 : Cas and tas decrease cas increases and tas decreases cas decreases and tas increases cas and tas increase

.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/ r as rectified air speed or cas / t as/ m ach exemple 217 cas and tas decrease.cas and tas decrease.

When climbing at a constant cas through an isothermal layer the mach number ?

Question 45-20 : Increases decreases remains constant decreases if oat is lower than the standard temperature

.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.tas will increase since density decreases with altitude .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 increases exemple 221 increases.increases.

If the pilot increases the reference pressure using the sub scale setting knob ?

Question 45-21 : Increases decreases decreases if qnh > 1013 hpa decreases if qnh < 1013 hpa

. 514.you have to turn altimeter setting adjustement knob in a clockwise direction to increase the indicated pressure .this will increase the indicated altitude exemple 225 increases.increases.

The alternate static source of a light non pressurized aircraft is located in ?

Question 45-22 : Lower than ambient pressure due to aerodynamic suction higher than ambient pressure due to aerodynamic suction higher than ambient pressure if qnh is greater than 1013 hpa lower than ambient pressure if qnh is greater than 1013 hpa

.the alternate static vent of an unpressurised aircraft senses the air pressure in the flight deck/cockpit in flight the air outside the flight deck accelerates over the aircraft canopy venturi effect this causes a drop in static pressure air will always flow from a high pressure to a low pressure so air in the flight deck flows outside this flow to the outside causes the pressure in the cabin to be lower than the undisturbed static pressure around the aircraft exemple 229 lower than ambient pressure due to aerodynamic suction.lower than ambient pressure due to aerodynamic suction.

Eas can be obtained from the following data ?

Question 45-23 : Cas and pressure altitude ias and density altitude tas and pressure altitude cas and density altitude

.eas is cas corrected for compressibility which you would work out from pressure altitude with eas and density altitude we can deduce tas exemple 233 cas and pressure altitude.cas and pressure altitude.

Cas is equal to ?

Question 45-24 : Ias corrected for position and instrument errors ias corrected for compressibility error eas corrected for density error eas corrected for compressibility and density errors

.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 237 ias corrected for position and instrument errors.ias corrected for position and instrument errors.

Eas is equal to ?

Question 45-25 : Ias corrected for position instrument and compressibility errors ias corrected for compressibility error cas corrected for density error tas corrected for compressibility error

.eas is cas corrected for compressibility and cas is ias corrected position and instrument errors therefore eas is ias corrected for position instrument and compressibility errors.position error error in altimeter readings caused by the variation of the static pressure near the source.instrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicated.compressibility the error in the readings of a differential pressure type airspeed indicator due to compression of the air on the forward part of the pitot tube component moving at high speeds

The altimeter is subject to static pressure error this error results from ?

Question 45-26 : Incorrect pressure sensing caused by disturbed airflow around the static ports imperfect elasticity of the aneroid capsules frictions inside the instrument cabin pressure slightly lower than outside air pressure due to airflow over the fuselage

exemple 245 incorrect pressure sensing caused by disturbed airflow around the static ports.incorrect pressure sensing caused by disturbed airflow around the static ports.

The machmeter is subject to position error this error results from ?

Question 45-27 : Incorrect pressure sensing caused by disturbed airflow around the pitot tube and/or static ports incorrect altimeter setting imperfect elasticity of the capsules non standard atmospheric conditions

The eas is obtained from the ias by correcting for the following errors .1 ?

Question 45-28 : 1 2 4 1 2 3 1 2 1 2 3 4

.eas is cas corrected for compressibility and cas is ias corrected position and instrument errors therefore eas is ias corrected for position instrument and compressibility errors.position error error in altimeter readings caused by the variation of the static pressure near the source.instrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicated.compressibility the error in the readings of a differential pressure type airspeed indicator due to compression of the air on the forward part of the pitot tube component moving at high speeds exemple 253 1, 2, 4.1, 2, 4.

When descending at a constant cas through an isothermal layer the mach number ?

Question 45-29 : Decreases increases remains constant increases if oat is lower than the standard temperature decreases if higher

.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.tas will decrease since density increases with altitude .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 decreases exemple 257 decreases.decreases.

In standard atmosphere at sea level the eas is ?

Question 45-30 : Equal to the tas independent of the tas higher than the tas lower than the tas

True air speed tas is obtained from equivalent air speed eas by correcting for density error thus in a standard atmosphere and at the sea level eas = tas exemple 261 equal to the tas.equal to the tas.

The alternate static source of a light non pressurized aircraft is located in ?

Question 45-31 : Indicate a momentary climb indicate a slight momentary descent indicate a high rate of descent be blocked

.the terms 'vertical speed indicator' or 'vsi' or 'vertical airspeed indicator' are used for the variometer.an alternate source for static pressure is provided in some airplanes in the event the static ports become blocked this source usually is vented to the pressure inside the cockpit because of the venturi effect of the flow of air over the cockpit this alternate static pressure is usually lower than the pressure provided by the normal static air source when the alternate static source is used the following differences in the instrument indications usually occur the altimeter will indicate higher than the actual altitude the airspeed will indicate greater than the actual airspeed and the vertical speed will indicate a climb while in level flight exemple 265 indicate a momentary climb.indicate a momentary climb.

Concerning the pitot and static system the static pressure error ?

Question 45-32 : Is caused by disturbed airflow around the static ports is a direct effect of heating of the static ports affects the alternate static port only is a direct effect of a blockage of the static port

exemple 269 is caused by disturbed airflow around the static ports.is caused by disturbed airflow around the static ports.

The output data from the adc are used by .1 transponder.2 efis.3 automatic ?

Question 45-33 : 1 2 3 1 2 1 3 2 3

. 1023. exemple 273 1, 2, 3.1, 2, 3.

Maintaining cas and flight level constant a fall in ambient temperature results ?

Question 45-34 : Lower tas because air density increases lower tas because air density decreases higher tas because air density increases higher tas because air density decreases

.lower temperature means an increase of air density air mass is contracting it is similar to a descent to a lower altitude .you can use the 'ertm' diagram. 1037..the cas line is vertical because cas is constant. 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 277 lower tas because air density increases.lower tas because air density increases.

If oat increases whilst maintaining a constant cas and flight level ?

Question 45-35 : Mach number remains constant mach number decreases tas remains constant tas decreases

.if oat increases 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 thus if tas increases and lss increases the mach number remains constant exemple 281 mach number remains constant.mach number remains constant.

If oat decreases whilst maintaining a constant cas and flight level ?

Question 45-36 : Mach number remains constant mach number increases tas remains constant tas increases

.if oat decreases density increases with lower temperature air is contracting density is increased .cas = 1/2 x density x tas²..cas is constant and density increases then tas must decrease.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 thus if tas decreases and lss decreases the mach number remains constant exemple 285 mach number remains constant.mach number remains constant.

The adc uses the following parameters as input data ?

Question 45-37 : Static pressure total pressure tat mach number baro altitude cas tas baro altitude tat total pressure static pressure tat egt

exemple 289 static pressure, total pressure, tat.static pressure, total pressure, tat.

The total pressure head comprises a mast which moves its port to a distance ?

Question 45-38 : To locate it outside the boundary layer not to disturb the aerodynamic flow around the aircraft it is protected from icing it is easily accessible during maintenance checks

exemple 293 to locate it outside the boundary layer.to locate it outside the boundary layer.

In case of static blockage the airspeed indicator ?

Question 45-39 : Under reads in climb and over reads in descent over reads in climb and under reads in descent over reads in climb only under reads in descent only

. 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.thus while descending the total pressure increases* and the static pressure from the static source does not your airspeed indicator will over read.*while descending density increases so total pressure increases.while climbing the total pressure decreases and the static pressure from the static source does not your airspeed indicator will under read exemple 297 under-reads in climb and over-reads in descent.under-reads in climb and over-reads in descent.

The machmeter is subject to position error this error concerns ?

Question 45-40 : Pitot tubes and static ports pitot tubes only static ports only alternate static sources only

.the alternate static vent of an unpressurised aircraft senses the air pressure in the flight deck/cockpit in flight the air outside the flight deck accelerates over the aircraft canopy venturi effect this causes a drop in static pressure air will always flow from a high pressure to a low pressure so air in the flight deck flows outside this flow to the outside causes the pressure in the cabin to be lower than the undisturbed static pressure around the aircraft exemple 301 pitot tubes and static ports.pitot tubes and static ports.

~

Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

1759 Free Training Exam Other source study: Ppl exam examen 45