During descent the total pressure probe of the airspeed indicator becomes blocked In this case 1 IAS becomes greater than CAS2 IAS becomes lower ?
Skills > lift > off
Other study patent: Telepilote theorique examen 43
For the same TAS when pressure altitude decreases below the tropopause ?
For the same TAS when pressure altitude increases below the tropopause ?
Given pt = total pressureps = static pressurepd = dynamic pressure Mach number increases. Pressure altitude increases = climbing for those questions use very simple 'ertm' diagram the tas line vertical because question states for same tas ertm e as/r as(rectified air speed or cas)/t as/m ach. 
Given pt = total pressureps = static pressurepso = static pressure at sea level calibrated airspeed cas a function of Mach number increases. Pressure altitude increases = climbing for those questions use very simple 'ertm' diagram the tas line vertical because question states for same tas ertm e as/r as(rectified air speed or cas)/t as/m ach. 
Given pt = total pressureps = static pressurepso = static pressure at sea leveldynamic pressure Mach number increases. Pressure altitude increases = climbing for those questions use very simple 'ertm' diagram the tas line vertical because question states for same tas ertm e as/r as(rectified air speed or cas)/t as/m ach. 
Given pt total pressureps static pressurepd dynamic pressurethe airspeed indicator fed Mach number increases. 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 the airspeed indicator fed with pt ps it works on pt ps = pd. Question 43-8
If an aircraft maintaining a constant cas and flight level flying from a cold air mass into warmer air Mach number increases. flying from a cold air mass into warmer air = density decreases (with higher temperature air expanding density reduced) cas = 1/2 x density x tas² cas constant density decreases then tas must increase mach = tas / local speed of sound local speed of sound varies only with temperature (lss varies with square root of absolute temperature formula lss = 39 x square root of (oat+273)) the question states 'flying from a cold air mass into warmer air' thus if tas increases lss increases mach number remains constant. Question 43-9
If an aircraft maintaining a constant cas and flight level flying from a warm air mass into colder air Mach number increases. flying from a warm air mass into colder air = density increases (with lower temperature air contracting density inscreased) situation similar to descent with a constant cas for those questions use very simple 'ertm' diagram the cas line vertical because question states maintaining a constant cas ertm e as/r as(rectified air speed or cas)/t as/m ach but mach number will not decrease since mach number lss (local speed of sound) are proportional to each other which means that temperature decrease will cause a decrease in lss as well as tas as tas reduces at same rate mach number will remain constant. Question 43-10
If oat decreases when at a constant mach number Mach number increases. relation between mach number tas depends only on oat is independant of static pressure at a constant flight level constant mach number if oat decreases tas will decrease but it would also do it in a climb in standard atmosphere descent in an inversion mach number = tas /lss local speed of sound (lss) changes in proportion to temperature if temperature reduce lss reduce thus tas must reduce to keep mach number constant. Question 43-11
If oat decreases when at a constant tas Mach number increases. relation between mach number tas depends only on oat is independant of static pressure at a constant flight level constant tas if oat decreases mach number will increase but it would also do it in a climb in standard atmosphere descent in an inversion mach number = tas / lss local speed of sound (lss) changes in proportion to temperature if temperature reduce lss reduce thus mach number must increase to keep tas constant. Question 43-12
If oat increases when at a constant mach number Mach number increases. Relation between mach number tas depends only on oat is independant of static pressure at a constant flight level constant mach number if oat increases tas will increase but it would also do it in a climb in standard atmosphere descent in an inversion mach number = tas / lss local speed of sound (lss) changes in proportion to temperature if temperature increase lss increase thus tas must increase to keep mach number constant you can also say an oat increasing similar to a decrease in altitude use 'ertm' diagram the mach line vertical because question states at a constant mach number ertm e as/r as(rectified air speed or cas)/t as/m ach. Question 43-13
If oat increases when at a constant tas Mach number decreases. Relation between mach number tas depends only on oat is independant of static pressure at a constant flight level constant tas if oat increases mach number will decrease but it would also do it in a climb in standard atmosphere descent in an inversion mach number = tas / lss local speed of sound (lss) changes in proportion to temperature if temperature increase lss increase thus mach number must reduce to keep tas constant. Question 43-14
During a climb at a constant calibrated airspeed cas below tropopause in standard conditions Tas mach number increase. For those questions use very simple 'ertm' diagram the cas line vertical because question states climb at a constant calibrated airspeed (cas) ertm e as/r as(rectified air speed or cas)/t as/m ach. Question 43-15
In standard atmosphere when descending at constant cas Tas mach number increase. For those questions use very simple 'ertm' diagram the cas line vertical because question states descending at constant 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. Question 43-16
In absence of position and instrument errors cas equal to Tas mach number increase. an airspeed indicator displays ias the error in altimeter readings caused the variation of static pressure near source known as position error instrument error refers to combined accuracy precision of a measuring instrument or difference between actual value the value indicated cas ias corrected position instrument errors. Question 43-17
In absence of position and instrument errors Tas mach number increase. an airspeed indicator displays ias the error in altimeter readings caused the variation of static pressure near source known as position error instrument error refers to combined accuracy precision of a measuring instrument or difference between actual value the value indicated cas ias corrected position instrument errors. Question 43-18
The compressibility correction to cas to give eas 1 may be positive 2 always negative3 depends on mach number only 4 depends on pressure altitude only the combination regrouping all correct statements Tas mach number increase. equivalent air speed (eas) obtained from calibrated air speed (cas) correcting compressibility error the size of compressibility error varies with mach number is always negative air speed indicator are calibrated standard atmosphere pressure temperature density thus reading dependent on dynamic pressure 1/2 x rho x v² (the error in readings due to compression of air on forward part of pitot tube component moving at high speeds) to avoid this error a compressibility correction has to be applied compressibility correction = (1 + (1/4 x m²) eas = dynamic pressure x (1 + (1/4 x m²)) the compressibility factor always negative is directly dependent on mach number. Question 43-19
True air speed tas obtained from indicated air speed ias correcting the following errors 1 instrument 2 position 3 compressibility 4 density the combination regrouping all correct statements Tas mach number increase. equivalent air speed (eas) obtained from calibrated air speed (cas) correcting compressibility error the size of compressibility error varies with mach number is always negative air speed indicator are calibrated standard atmosphere pressure temperature density thus reading dependent on dynamic pressure 1/2 x rho x v² (the error in readings due to compression of air on forward part of pitot tube component moving at high speeds) to avoid this error a compressibility correction has to be applied compressibility correction = (1 + (1/4 x m²) eas = dynamic pressure x (1 + (1/4 x m²)) the compressibility factor always negative is directly dependent on mach number. Question 43-20
Tas Eas corrected density error. true air speed (tas) is ias corrected instrument position compressibility density errors cas corrected compressibility density errors eas corrected density error. Question 43-21
When climbing at a constant cas in a standard atmosphere 1 tas decreases 2 tas increases 3 mach number increases 4 mach number decreases the combination regrouping all correct statements Eas corrected density error. true air speed (tas) is ias corrected instrument position compressibility density errors cas corrected compressibility density errors eas corrected density error. Question 43-22
When climbing at a constant cas Mach number increases. 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 cas = 1/2 rho v² density will decrease during climb in order to maintain constant cas 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 43-23
When descending at a constant cas in a standard atmosphere 1 tas increases 2 tas decreases 3 mach number increases 4 mach number decreases the combination regrouping all correct statements Mach number increases. 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 cas = 1/2 rho v² density will decrease during climb in order to maintain constant cas 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 43-24
When descending at a constant cas Mach number decreases. 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 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 43-25
When descending at a constant mach number Mach number decreases. For those questions use very simple 'ertm' diagram the mach line vertical because question states descending at a constant mach number ertm e as/r as(rectified air speed or cas)/t as/m ach. Question 43-26
When flying in cold air colder than standard atmosphere indicated altitude Higher than true altitude. in standard atmosphere temperature conditions your indicated altitude will be same as your true altitude but if it warmer than isa your true altitude will be higher than your indicated altitude if it colder than isa your true altitude will be lower than your indicated altitude. Question 43-27
When flying in cold air colder than standard atmosphere altimeter will Higher than true altitude. in standard atmosphere temperature conditions your indicated altitude will be same as your true altitude but if it warmer than isa your true altitude will be higher than your indicated altitude if it colder than isa your true altitude will be lower than your indicated altitude therefore your altimeter will overestimate in cold air. Question 43-28
When flying in warm air warmer than standard atmosphere indicated altitude Lower than true altitude. in standard atmosphere temperature conditions your indicated altitude will be same as your true altitude but if it warmer than isa your true altitude will be higher than your indicated altitude if it colder than isa your true altitude will be lower than your indicated altitude therefore your altimeter will overestimate in cold air. Question 43-29
Which of following statements are correct an aeroplane cruising at fl 60 with a true airspeed tas of 100 kt in standard atmospheric conditions 1 the tas approximately 10% higher than ias 2 the difference between equivalent airspeed eas and calibrated airspeed cas negligible 3 the speed displayed on airspeed indicator a calibrated airspeed cas if position error and instrument error are zero 2 3 are all correct. tas = ias + 2% per 1000 ft altitude eas cas corrected compressibility at low speed low altitude compressibility negligeable cas ias corrected position instrument errors. Question 43-30
With eas and density altitude we can deduce 2 3 are all correct. with eas density altitude we can deduce tas with eas pressure altitude (zp) we can deduce cas. Question 43-31
With eas and pressure altitude zp we can deduce 2 3 are all correct. eas cas corrected compressibility error which you would work out from pressure altitude with eas density altitude we can deduce tas. Question 43-32
During a climb total pressure probe of airspeed indicator becomes blocked if pilot maintains a constant indicated airspeed true airspeed Decreases until reaching stall speed. if static system remains clear airspeed indicator acts as an altimeter true air speed (tas) ias corrected instrument position compressibility density errors thus with total pressure probe blocked to maintain a constant ias while altitude increases you must pull stick (or control column) if not indicated speed will increase you will quickly reach stalling speed. Question 43-33
With constant weight and configuration an aircraft always takes off at same Decreases until reaching stall speed. pressure errors (i e errors in measurement of pitot static pressure) are specific to aircraft so we have to allow them instrument error specific to instrument so we have to get instrument calibrated take it into account having corrected indicated airspeed these two errors we have calibrated airspeed however small at take off speed we should correct the effect of compressibility that will give us equivalent airspeed for a given weight configuration take off speed will depend on density of air so we don't correct that hence aircraft will take off at same eas. Question 43-34
An airspeed indicator includes a capsule inside this capsule Total pressure outside static pressure. 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. Question 43-35
An aircraft equipped with one altimeter that compensated position error and another one altimeter that not assuming all other factors are equal during a straight symmetrical flight The greater speed greater error between two altimeters. 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. Question 43-36
An aneroid capsule 1 measures differential pressure2 measures absolute pressure3 used low pressure measurement4 used very high pressure measurementthe combination regrouping all correct statements The greater speed greater error between two altimeters. the aneroid capsule used to sense absolute pressure it used low pressure measurement. Question 43-37
An altimeter contains one or more aneroid capsules inside these capsules A very low residual pressure outside static pressure. the aneroid capsule used to sense absolute pressure it used low pressure measurement. Question 43-38
The altimeter of your aircraft indicates 10000 ft with a subscale setting of 1013 25 hpa oat +5°c the pressure altitude of aircraft A very low residual pressure outside static pressure. an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa. Question 43-39
The altimeter indicates true altitude In isa conditions only. an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa. Question 43-40
Tas can be obtained from following data Eas density altitude. an altimeter shows a pressure altitude with a sub scale setting of 1013 25 hpa.
Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.
1679 Free Training Exam