The total air temperature tat is ? [ Progression visibility ]

Question 46-1 : 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

exemple 146 The temperature resulting from the aircraft motion in the air. — .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 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 46-2 : 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

exemple 150 The static pressure decreases, implying an increasing 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 The static pressure decreases, implying an increasing ias.

The static air temperature sat is ?

Question 46-3 : 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

exemple 154 The ambient outside air temperature. — Admin .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 The ambient outside air temperature.

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

Question 46-4 : Vs1 and vno vs1 and vmo vs0 and vne vs1 and vne

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

Question 46-5 : 2 and 3 1 2 and 3 1 and 3 1 and 2

exemple 162 2 and 3. — .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 2 and 3.

The alternate static source is used ?

Question 46-6 : 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

exemple 166 When the static ports become blocked. — Admin .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 When the static ports become blocked.

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

Question 46-7 : 1 3 1 2 3 3 1

exemple 170 1, 3. — .position pressure error varies with angle of attack and speed but not with temperature 1, 3.

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

Question 46-8 : 1 2 3 4 5 1 4 2 3 4 1 3 5

exemple 174 1, 2, 3, 4, 5. — 1, 2, 3, 4, 5.

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

Question 46-9 : 1 2 3 2 3 1 2 1 3

exemple 178 1, 2, 3. — Admin .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 1, 2, 3.

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

Question 46-10 : 2 4 2 4 1 2 3 4

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

Question 46-11 : 1 3 3 1 3 4 2 3 4

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

Question 46-12 : 2 4 2 4 1 2 3 4

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

Question 46-13 : 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

Eas is equal to ?

Question 46-14 : Cas corrected for compressibility error cas corrected for density error tas corrected for compressibility error tas corrected for compressibility and density errors

exemple 198 Cas corrected for compressibility error. — Cas corrected for compressibility error.

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

Question 46-15 : Cas and tas decrease cas increases and tas decreases cas decreases and tas increases cas and tas increase

exemple 202 Cas and tas decrease. — Admin .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 Cas and tas decrease.

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

Question 46-16 : Increases decreases remains constant decreases if oat is lower than the standard temperature

exemple 206 Increases. — 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 .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 Increases.

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

Question 46-17 : Increases decreases decreases if qnh > 1013 hpa decreases if qnh < 1013 hpa

exemple 210 Increases. — . 514.you have to turn altimeter setting adjustement knob in a clockwise direction to increase the indicated pressure .this will increase the indicated altitude Increases.

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

Question 46-18 : 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

exemple 214 Lower than ambient pressure due to aerodynamic suction. — Admin .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 Lower than ambient pressure due to aerodynamic suction.

Eas can be obtained from the following data ?

Question 46-19 : Cas and pressure altitude ias and density altitude tas and pressure altitude cas and density altitude

exemple 218 Cas and pressure altitude. — .eas is cas corrected for compressibility which you would work out from pressure altitude with eas and density altitude we can deduce tas Cas and pressure altitude.

Cas is equal to ?

Question 46-20 : Ias corrected for position and instrument errors ias corrected for compressibility error eas corrected for density error eas corrected for compressibility and density errors

exemple 222 Ias corrected for position and instrument 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 Ias corrected for position and instrument errors.

Eas is equal to ?

Question 46-21 : Ias corrected for position instrument and compressibility errors ias corrected for compressibility error cas corrected for density error tas corrected for compressibility error

exemple 226 Ias corrected for position, instrument and compressibility errors. — .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 Ias corrected for position, instrument and compressibility errors.

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

Question 46-22 : 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 230 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 46-23 : 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

exemple 234 Incorrect pressure sensing caused by disturbed airflow around the pitot tube and/or static ports. — Incorrect pressure sensing caused by disturbed airflow around the pitot tube and/or static ports.

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

Question 46-24 : 1 2 4 1 2 3 1 2 1 2 3 4

exemple 238 1, 2, 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 1, 2, 4.

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

Question 46-25 : Decreases increases remains constant increases if oat is lower than the standard temperature decreases if higher

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 .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

In standard atmosphere at sea level the eas is ?

Question 46-26 : Equal to the tas independent of the tas higher than the tas lower than the tas

exemple 246 Equal to 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 Equal to the tas.

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

Question 46-27 : Indicate a momentary climb indicate a slight momentary descent indicate a high rate of descent be blocked

exemple 250 Indicate a momentary climb. — Admin .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 Indicate a momentary climb.

Concerning the pitot and static system the static pressure error ?

Question 46-28 : 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 254 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 46-29 : 1 2 3 1 2 1 3 2 3

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

Question 46-30 : Lower tas because air density increases lower tas because air density decreases higher tas because air density increases higher tas because air density decreases

exemple 262 Lower tas because air density increases. — Admin .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 Lower tas because air density increases.

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

Question 46-31 : Mach number remains constant mach number decreases tas remains constant tas decreases

exemple 266 Mach number remains constant. — .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 Mach number remains constant.

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

Question 46-32 : Mach number remains constant mach number increases tas remains constant tas increases

exemple 270 Mach number remains constant. — .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 Mach number remains constant.

The adc uses the following parameters as input data ?

Question 46-33 : Static pressure total pressure tat mach number baro altitude cas tas baro altitude tat total pressure static pressure tat egt

exemple 274 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 46-34 : 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 278 To locate it outside the boundary layer. — To locate it outside the boundary layer.

In case of static blockage the airspeed indicator ?

Question 46-35 : 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

exemple 282 Under-reads in climb and over-reads in descent. — . 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 Under-reads in climb and over-reads in descent.

The machmeter is subject to position error this error concerns ?

Question 46-36 : Pitot tubes and static ports pitot tubes only static ports only alternate static sources only

exemple 286 Pitot tubes and static ports. — Admin .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 Pitot tubes and static ports.

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

Question 46-37 : Pt ps ps pt pd ps pt pd

The open ended tube parallel to the longitudinal axis of the aircraft senses the ?

Question 46-38 : Total pressure static pressure total pressure plus static pressure dynamic pressure

exemple 294 Total pressure. — Total pressure.

The altimeter is subject to static pressure error this error varies according to ?

Question 46-39 : Tas and angle of attack tas and altimeter setting angle of attack and oat tas and oat

exemple 298 Tas and angle of attack. — Tas and angle of attack.

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

Question 46-40 : Tas and angle of attack tas and oat oat only tas only

exemple 302 Tas and angle of attack. — Tas and angle of attack.

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