A temperature sensor has a recovery factor of 0 95 the temperature measured is ? [ Free topography ]

Question 59-1 : Static air temperature sat + 95% of the ram rise ram air temperature rat + 95% of the ram rise 95% of the static air temperature sat 95% of the ram air temperature rat

exemple 159 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 Static air temperature (sat) + 95% of the ram rise.

A thermocouple type temperature sensing is composed of ?

Question 59-2 : Two dissimilar metals joined together at one end called hot junction or measure junction two identical metals joined together at one end called hot junction or measure junction two identical metals joined together at both ends called hot and cold junctions a single wire metal winding

exemple 163 Two dissimilar metals joined together at one end (called hot junction or measure junction). — Two dissimilar metals joined together at one end (called hot junction or measure junction).

At flight level and mach number constant if oat decreases the cas ?

Question 59-3 : Remains constant increases decreases decreases if oat is lower than standard temperature increases in the opposite case

exemple 167 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 Remains constant.

The altimeter of your aircraft indicates 15000 ft with a subscale setting of ?

Question 59-4 : 15000 ft 14640 ft 15360 ft 572 hpa

exemple 171 15000 ft. — .an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa 15000 ft.

During a climb at a constant ias below the tropopause in isa conditions ?

Question 59-5 : The mach number and the true airspeed increase the mach number and the true airspeed decrease the mach number increases and the true airspeed decreases the mach number decreases and the true airspeed increases

exemple 175 The mach number and the true airspeed increase. — Admin .for those questions use the very simple 'ertm' diagram . 975.the eas ias line is vertical because the question states climb at a constant ias . ertm for e as/ r as rectified air speed or cas / t as/ m ach .density will decrease during climb and in order to maintain constant ias only v tas can be increased .mach = tas / local speed of sound.local speed of sound varies only with temperature and temperature decreases during climb thus if tas increases and lss decreases the mach number increases The mach number and the true airspeed increase.

The altimeter of your aircraft indicates 11000 ft with a subscale setting of ?

Question 59-6 : 11000 ft 11740 ft 10260 ft 670 hpa

exemple 179 11000 ft. — .an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa 11000 ft.

The altimeter of your aircraft indicates 17000 ft with a subscale setting of ?

Question 59-7 : 17000 ft 17540 ft 16460 ft 527 hpa

exemple 183 17000 ft. — They ask for 'pressure altitude' with a subscale already set to 1013 25 hpa we only have to read our altimeter 17000 ft 17000 ft.

The altimeter of your aircraft indicates 16000 ft with a subscale setting of ?

Question 59-8 : 16000 ft 14300 ft 17700 ft 549 hpa

exemple 187 16000 ft. — They ask for 'pressure altitude' with a subscale already set to 1013 25 mb we only have to read our altimeter 16000 ft 16000 ft.

An aeroplane is in a steady climb the auto throttle maintains a constant mach ?

Question 59-9 : Decreases increases remains constant decreases if the static temperature is lower than the standard temperature increases if higher

exemple 191 Decreases. — Mach = tas / local speed of sound.local speed of sound varies only with temperature and the question states 'total 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 . 964 Decreases.

An angle of attack sensor may consist of .1 an inertial system computing the ?

Question 59-10 : 2 3 1 2 3 1 2 1 3

exemple 195 2, 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. 2, 3.

An airplane is in steady cruise at flight level 290 the auto throttle maintains ?

Question 59-11 : Remains constant increases decreases increases if the static temperature is higher than the standard temperature decreases if lower

exemple 199 Remains constant. — Mach = tas / local speed of sound.local speed of sound varies only with temperature and the question states 'total temperature increases' thus lss increases .to maintain a constant mach number tas must increase ..cas = 1/2 rho tas².rho decreases when temperature increases ans since tas is increased cas will remain constant .you can use your computer for those questions mach number and cas are attached on the inner scale they move together with temperature adjustments Remains constant.

In standard atmosphere when climbing at constant cas ?

Question 59-12 : Tas and mach number increase tas and mach number decrease tas increases and mach number decreases tas decreases and mach number increases

exemple 203 Tas and mach number increase. — Admin .for those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states climb at a constant cas . ertm for e as/ r as rectified air speed or cas / t as/ m ach .mach number = tas/local speed of sound.tas and mach number increase during a climb at a constant cas .lss decreases if oat outside air temperature decreases Tas and mach number increase.

In a standard atmosphere and at the sea level the calibrated airspeed cas is ?

Question 59-13 : 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 207 Equal to the true airspeed (tas). — Equal to the true airspeed (tas).

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

Question 59-14 : Density altitude pressure altitude oat mach number

exemple 211 Density altitude. — Density altitude.

With cas and pressure altitude we can deduce ?

Question 59-15 : Eas tas eas and tas nothing

Speed of sound is proportional to ?

Question 59-16 : 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 219 The square root of the absolute temperature. — The square root of the absolute temperature.

The total air temperature tat is ?

Question 59-17 : 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 223 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 59-18 : 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 227 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 59-19 : 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 231 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 59-20 : Vs1 and vno vs1 and vmo vs0 and vne vs1 and vne

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

Question 59-21 : 2 and 3 1 2 and 3 1 and 3 1 and 2

exemple 239 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 59-22 : 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

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

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

Question 59-23 : 1 3 1 2 3 3 1

exemple 247 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 59-24 : 1 2 3 4 5 1 4 2 3 4 1 3 5

exemple 251 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 59-25 : 1 2 3 2 3 1 2 1 3

exemple 255 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 59-26 : 2 4 2 4 1 2 3 4

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

Question 59-27 : 1 3 3 1 3 4 2 3 4

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

Question 59-28 : 2 4 2 4 1 2 3 4

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

Question 59-29 : 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 59-30 : Cas corrected for compressibility error cas corrected for density error tas corrected for compressibility error tas corrected for compressibility and density errors

exemple 275 Cas corrected for compressibility error. — Cas corrected for compressibility error.

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

Question 59-31 : Cas and tas decrease cas increases and tas decreases cas decreases and tas increases cas and tas increase

exemple 279 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 59-32 : Increases decreases remains constant decreases if oat is lower than the standard temperature

exemple 283 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 59-33 : Increases decreases decreases if qnh > 1013 hpa decreases if qnh < 1013 hpa

exemple 287 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 59-34 : 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 291 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 59-35 : Cas and pressure altitude ias and density altitude tas and pressure altitude cas and density altitude

exemple 295 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 59-36 : 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 299 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 59-37 : Ias corrected for position instrument and compressibility errors ias corrected for compressibility error cas corrected for density error tas corrected for compressibility error

exemple 303 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 59-38 : 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 307 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 59-39 : 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 311 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 59-40 : 1 2 4 1 2 3 1 2 1 2 3 4

exemple 315 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.

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2319 Free Training Exam