The maximum TAS is obtained at ?
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Other study patent: Telepilote theorique examen 44
The input data of an ADC are 1 OAT 2 TAT3 static pressure 4 total pressure The combination regrouping all the correct statements is ?
Given Mach number M = 0 70Measured impact temperature = 48 °CThe recovery factor Kr of the temperature probe = 0 85The OAT SAT is ?
During a descent at a constant mach number below tropopause in isa conditions The flight level at which simultaneously cas = vmo m = mmo. For those questions use very simple 'ertm' diagram the mach line vertical because question states descent at a constant mach number ertm e as/r as(rectified air speed or cas)/t as/m ach. 
During a descent at a constant mach number below tropopause in isa conditions The flight level at which simultaneously cas = vmo m = mmo. For those questions use very simple 'ertm' diagram the mach line vertical because question states descent at a constant mach number ertm e as/r as(rectified air speed or cas)/t as/m ach. 
During a descent at a constant ias below tropopause in isa conditions Mach number tas decrease. for those questions use very simple 'ertm' diagram the eas (ias) line vertical because question states descent at a constant ias ertm e as/r as(rectified air speed or cas)/t as/m ach density will increase during descent 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 temperature increases during descent thus if tas decreases lss increases mach number decreases. 
During a descent at a constant calibrated airspeed cas below tropopause in isa conditions Mach number tas decrease. For those questions use very simple 'ertm' diagram the cas line vertical because question states descent at a constant calibrated airspeed (cas) ertm e as/r as(rectified air speed or cas)/t as/m ach cas = 1/2 rho v² density will increase during descent 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 temperature increases during descent thus if tas decreases lss increases mach number decreases. Question 44-8
During a climb at a constant mach number below tropopause in isa conditions Mach number tas decrease. For those questions use very simple 'ertm' diagram the mach line vertical because question states climb at a constant mach number ertm e as(ias)/r as(rectified air speed or cas)/t as/m ach. Question 44-9
If pitot tube ices up during a flight affected equipment s are 1 altimeter 2 variometer 3 airspeed indicator the combination regrouping all correct statements Mach number tas decrease. pywee22 some pitot tubes are also equipped with static the question not clear enough the question says pitot tube so i can assume that it the entire tube (static total pressure) therefore all instruments listed are affected as 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 variometer (vertical speed indicator) are connected to static ports but they are not connected to pitot tube therefore a blocked pitot tube will have no effect on these instruments. Question 44-10
If during a descent pneumatic altimeter reading constant vertical speed indicator shows zero ias increasing the most likely explanation that The static ports are completely blocked. pywee22 some pitot tubes are also equipped with static the question not clear enough the question says pitot tube so i can assume that it the entire tube (static total pressure) therefore all instruments listed are affected as 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 variometer (vertical speed indicator) are connected to static ports but they are not connected to pitot tube therefore a blocked pitot tube will have no effect on these instruments. Question 44-11
For tas calculations adc uses following parameters 1 sat 2 tat 3 static pressure 4 total pressure the combination regrouping all correct statements The static ports are completely blocked. the adc uses as input data static pressure total pressure (pitot pressure) tat. Question 44-12
If pitot tube becomes blocked during a descent airspeed indicator The static ports are completely blocked. the asi a sensitive differential pressure gauge which measures promptly indicates difference between pitot (total pressure) static pressure (total pressure static pressure = dynamic pressure) these two pressures are equal when aircraft parked on ground in calm air when aircraft moves through air pressure on pitot line becomes greater than pressure in static lines this difference in pressure registered the airspeed pointer on face of instrument if pitot tube becomes blocked during a descent total pressure remains constant static pressure increases your airspeed indicator will under reads. Question 44-13
Given pt total pressureps static pressurepd dynamic pressurethe altimeter fed The static ports are completely blocked. the altimeter supplied with static pressure only. Question 44-14
A pitot tube covered ice which blocks ram air inlet will affect following instrument s The static ports are completely blocked. the altimeter supplied with static pressure only. Question 44-15
A dynamic pressure measurement circuit constituted of following pressure probes Total pressure static pressure. the altimeter supplied with static pressure only. Question 44-16
The qnh by definition value of Altimeter setting so that altimeter on apron of aerodrome which it given reads elevation. the altimeter supplied with static pressure only. Question 44-17
The purpose of vibrating device of an altimeter to Reduce effect of friction in linkages. the altimeter supplied with static pressure only. Question 44-18
When climbing at a constant mach number Reduce effect of friction in linkages. for those questions use very simple 'ertm' diagram the mach line vertical because question states climbing at a constant mach number ertm e as/r as(rectified air speed or cas)/t as/m ach. Question 44-19
When descending at a constant cas Reduce effect of friction in linkages. for those questions use very simple 'ertm' diagram the cas line vertical because question states descending at a constant cas ertm e as/r as(rectified air speed or cas)/t as/m ach eas cas corrected compressibility. Question 44-20
When climbing at a constant mach number through an isothermal layer cas Reduce effect of friction in linkages. mach = tas / local speed of sound local speed of sound varies only with temperature the question states 'isothermal layer' (temperature remains constant) thus lss remains constant the tas remains constant cas = 1/2 rho tas² rho decreasing with altitude thus cas decreases. Question 44-21
When climbing at a constant cas Reduce effect of friction in linkages. for those questions use very simple 'ertm' diagram the cas line vertical because question states climbing at a constant cas ertm e as/r as(rectified air speed or cas)/t as/m ach eas cas corrected compressibility cas will always be higher than eas. Question 44-22
Vfe the maximum speed With flaps extended each approved flap position. for those questions use very simple 'ertm' diagram the cas line vertical because question states climbing at a constant cas ertm e as/r as(rectified air speed or cas)/t as/m ach eas cas corrected compressibility cas will always be higher than eas. Question 44-23
Tas Ias corrected instrument position compressibility density errors. True air speed (tas) is ias corrected instrument position compressibility density errors cas corrected compressibility density errors eas corrected density error. Question 44-24
Tas Cas corrected compressibility density errors. true air speed (tas) is ias corrected instrument position compressibility density errors cas corrected compressibility density errors eas corrected density error. Question 44-25
Assuming flight level and mach number remain constant when oat increases Ias remains constant tas increases. the mach number a function of (p s)/s where p = total pressure (pitot) s = static pressure in absence of position instrument errors ias = cas ias (cas) is 'p the question states 'mach number remain constant' thus ias remains constant ias (cas) = 1/2 rho tas² if air becomes less dense (oat increases) only thing that can change in this equation the tas increasing to compensate. Question 44-26
Assuming flight level and mach number remain constant when oat decreases Ias remains constant tas decreases. the mach number a function of (p s)/s where p = total pressure (pitot) s = static pressure in absence of position instrument errors ias = cas ias (cas) is 'p the question states 'mach number remain constant' thus ias remains constant ias (cas) = 1/2 rho tas² if air becomes denser (oat decreases) only thing that can change in this equation the tas decreasing to compensate joangoris and what about 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 to reduce tas oat 50°c tas 440 kt m = tas/lss = 440 / 582 = 0 76. Question 44-27
A vertical speed indicator measures difference between The instantaneous static pressure the static pressure at a previous moment. ecair04 vsi requires only static pressure like an input the operating principle of vertical speed indicator (vsi) based on measurement of rate of change of static pressure although vertical speed indicator operates from static pressure source it a differential pressure instrument the differential pressure established between instantaneous static pressure in diaphragm the trapped static pressure within case. Question 44-28
At flight level and mach number constant if oat increases cas The instantaneous static pressure the static pressure at a previous moment. the mach number a function of (p s)/s where p = total pressure (pitot) s = static pressure cas is 'p the question states 'mach number constant' thus cas remains constant. Question 44-29
A temperature sensor has a recovery factor of 0 95 the temperature measured equal to Static air temperature (sat) + 95% of ram rise. recovery factor refers to amount of ram rise that recoverable the sensor total head thermometers typically have a recovery factor of 0 75 to 0 9 whereas rosemount temperature probe has a recovery factor of 1 0 the ram rise due to adiabatic compression for simple sat temperature sensors used on light aircraft that fly at speeds less than mach 0 2 ram rise factor does not apply the sat sensor measures actual temperature is therefore 100% efficient tat 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 the recovery factor m mach number ram rise comes into effect at airspeeds greater than m 0 2 in summary sat temperature sensors are not affected ram rise whereas tat sensors are. Question 44-30
A thermocouple type temperature sensing composed of Two dissimilar metals joined together at one end (called hot junction or measure junction). recovery factor refers to amount of ram rise that recoverable the sensor total head thermometers typically have a recovery factor of 0 75 to 0 9 whereas rosemount temperature probe has a recovery factor of 1 0 the ram rise due to adiabatic compression for simple sat temperature sensors used on light aircraft that fly at speeds less than mach 0 2 ram rise factor does not apply the sat sensor measures actual temperature is therefore 100% efficient tat 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 the recovery factor m mach number ram rise comes into effect at airspeeds greater than m 0 2 in summary sat temperature sensors are not affected ram rise whereas tat sensors are. Question 44-31
At flight level and mach number constant if oat decreases cas Two dissimilar metals joined together at one end (called hot junction or measure junction). the mach number a function of (p s)/s where p = total pressure (pitot) s = static pressure cas is 'p the question states 'mach number constant' thus cas remains constant. Question 44-32
The altimeter of your aircraft indicates 15000 ft with a subscale setting of 1013 25 hpa oat 21°c the pressure altitude of aircraft Two dissimilar metals joined together at one end (called hot junction or measure junction). an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa. Question 44-33
During a climb at a constant ias below tropopause in isa conditions The mach number the true airspeed increase. for those questions use very simple 'ertm' diagram the eas (ias) line vertical because question states climb at a constant ias ertm e as/r as(rectified air speed or cas)/t as/m ach density will decrease during climb 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 temperature decreases during climb thus if tas increases lss decreases mach number increases. Question 44-34
The altimeter of your aircraft indicates 11000 ft with a subscale setting of 1013 25 hpa qnh 1023 hpa oat +3°c the pressure altitude of aircraft The mach number the true airspeed increase. an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa. Question 44-35
The altimeter of your aircraft indicates 17000 ft with a subscale setting of 1013 25 hpa qnh 1031 hpa the pressure altitude of aircraft The mach number the true airspeed increase. They ask 'pressure altitude' with a subscale already set to 1013 25 hpa we only have to read our altimeter 17000 ft. Question 44-36
The altimeter of your aircraft indicates 16000 ft with a subscale setting of 1013 25 mb qnh 993 hpa oat 3°c the pressure altitude of aircraft The mach number the true airspeed increase. They ask 'pressure altitude' with a subscale already set to 1013 25 mb we only have to read our altimeter 16000 ft. Question 44-37
An aeroplane in a steady climb the auto throttle maintains a constant mach number if total temperature remains constant calibrated airspeed The mach number the true airspeed increase. Mach = tas / local speed of sound local speed of sound varies only with temperature the question states 'total temperature remains constant' thus lss remains constant the tas remains constant cas = 1/2 rho tas² rho decreasing with altitude thus cas decreases . Question 44-38
An angle of attack sensor may consist of 1 an inertial system computing difference between flight path and flight attitude2 a slotted probe which positions itself to determine angle of attack3 a vane detector which positions rotor of a synchro transmitter the combination regrouping all correct statements The mach number the true airspeed increase. conical slotted probe the angle of attack (aoa) probe provides aoa or sideslip (ss) sensing direction of local airflow it mounted on fuselage with sensing probe extending through aircraft fuselage the sensing probe continually driven to null pressure differential between upper lower slots in its forward surface these features sense direction of air stream flow (local aoa or ss) the angular position of sensing probe converted to an electrical output an angular sensor vane detector the angle of attack sensor of wind vane type its sensing element a small wing which positioned in direction of airflow the small wing mechanically linked to a free turn shaft which drives devices transmitting local angle of attack signal . Question 44-39
An airplane in steady cruise at flight level 290 the auto throttle maintains a constant mach number if total temperature increases calibrated airspeed The mach number the true airspeed increase. Mach = tas / local speed of sound local speed of sound varies only with temperature the question states 'total temperature increase 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 increased cas will remain constant you can use your computer those questions mach number cas are attached on inner scale they move together with temperature adjustments. Question 44-40
In standard atmosphere when climbing at constant cas Tas mach number increase. for those questions use very simple 'ertm' diagram the cas line vertical because question states climb at a constant cas ertm e as/r as(rectified air speed or cas)/t as/m ach mach number = tas/local speed of sound tas mach number increase during a climb at a constant cas lss decreases if oat (outside air temperature) decreases.
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