If the static source of an altimeter becomes blocked during a descent the instrument will ?
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Source: Telepilote theorique examen 40
If the static source to an altimeter becomes blocked during a climb the instrument will ?
If the static source to an airspeed indicator ASI becomes blocked during a descent the instrument will ?
A leak in pitot total pressure line of a non pressurized aircraft to an airspeed indicator would cause it to Continue to indicate reading at which blockage occurred. airspeed indicator (asi) the asi a sensitive differential pressure gauge which measures promptly indicates difference between pitot (impact/dynamic pressure) static 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 which calibrated in miles per hour knots (nautical miles per hour) or both airspeed indication on airspeed indicator is total pressure static pressure = dynamic pressure therefore with a leak in pitot total pressure line it similar to a reduction of speed (a reduction of relative flow entering in pitot tube) the airspeed indicator will under read. 
Machmeter readings are subject to Position pressure error. machmeter errors mach number proportional to ratio of pitot pressure to static pressure ie to (pt ps)/ps this exaclty what machmeter measures thus any non standard temperature or density do not affect accuracy of machmeter the only error worth considering the pressure (position error) in addition to usually small instrument error a mach meter can be considered accurate to within +/ 0 01 mach in normal operating range or to within +/ 0 02 at limits of that range. 
Vno the maximum speed Not to be exceeded except in still air with caution. machmeter errors mach number proportional to ratio of pitot pressure to static pressure ie to (pt ps)/ps this exaclty what machmeter measures thus any non standard temperature or density do not affect accuracy of machmeter the only error worth considering the pressure (position error) in addition to usually small instrument error a mach meter can be considered accurate to within +/ 0 01 mach in normal operating range or to within +/ 0 02 at limits of that range. 
Vne the maximum speed Which must never be exceeded. machmeter errors mach number proportional to ratio of pitot pressure to static pressure ie to (pt ps)/ps this exaclty what machmeter measures thus any non standard temperature or density do not affect accuracy of machmeter the only error worth considering the pressure (position error) in addition to usually small instrument error a mach meter can be considered accurate to within +/ 0 01 mach in normal operating range or to within +/ 0 02 at limits of that range. Question 40-8
Vlo the maximum Speed at which landing gear can be operated with full safety. machmeter errors mach number proportional to ratio of pitot pressure to static pressure ie to (pt ps)/ps this exaclty what machmeter measures thus any non standard temperature or density do not affect accuracy of machmeter the only error worth considering the pressure (position error) in addition to usually small instrument error a mach meter can be considered accurate to within +/ 0 01 mach in normal operating range or to within +/ 0 02 at limits of that range. Question 40-9
The position error of static vent on which altimeter connected varies substantially with Mach number of aircraft. the pressure errors on a pitot/static systems vary with aircraft speed but specifically with mach number. Question 40-10
The density altitude The altitude of standard atmosphere on which density equal to actual density of atmosphere. the density altitude the altitude in standard atmosphere at which prevailing density occurs meaning your real altitude from effects of height temperature humidity is used to establish performance as it a figure that expresses where your machine thinks it is as opposed to where it actually is. Question 40-11
The response time of a vertical speed detector may be decreased adding a Correction based on an accelerometer sensor. on a vertical speed indicator pointer takes a few seconds to steady because of time taken to build up a steady pressure difference on climb or descent there will also be a time lag on levelling out because of time to overcome problem of lag instantaneous vertical speed indicator (i v s i) incorporates an accelerometer sensor which responds quickly to a change of altitude the figure below shows an ivsi at beginning of a descent the piston in vertical acceleration pump immediately rises in cylinder causes a temporary increase of pressure in capsule the capsule expands the pointer will give an instant indication of descent as initial acceleration turned into a steady rate of descent piston will slowly descend to its original position but this time correct differential pressure between capsule the case will have been set up the correct rate of descent will continue to be shown. Question 40-12
The pressure altitude the altitude corresponding In standard atmosphere to pressure ps prevailing at this point. The altimeter calibrated to standard atmosphere conditions it nothing more than a barometer which measures atmospheric pressure relates it to altitude at which that pressure found in a standard atmosphere in a standard atmosphere pressure at 5000 feet 850 hpa so if static pressure (ps) 850 hpa altimeter tells you that you are 5000 feet this your pressure altitude. Question 40-13
The atmospheric pressure at fl 70 in a 'standard + 10' atmosphere In standard atmosphere to pressure ps prevailing at this point. 7000 ft / 28 ft hpa = 250 hpa pressure at mean sea level (msl) in international standard atmosphere 1013 25 hpa 1013 25 250 = 763 25 this answer close to 781 85 hpa lucastefanon fl 70 ==> 770 hpa true altitude 7x4x10= 280 ft 280/27=10 5 hpa as it's warmer then must be added so 770+10 5= 780 5 which i think it's more precise value respect to answer. Question 40-14
Sound propagates through air at a speed which only depends on In standard atmosphere to pressure ps prevailing at this point. 7000 ft / 28 ft hpa = 250 hpa pressure at mean sea level (msl) in international standard atmosphere 1013 25 hpa 1013 25 250 = 763 25 this answer close to 781 85 hpa lucastefanon fl 70 ==> 770 hpa true altitude 7x4x10= 280 ft 280/27=10 5 hpa as it's warmer then must be added so 770+10 5= 780 5 which i think it's more precise value respect to answer. Question 40-15
The velocity of sound at sea level in a standard atmosphere In standard atmosphere to pressure ps prevailing at this point. the velocity of sound varies only with temperature s = 39 x sqrt °kelvin to get kelvin add 273 to centigrade +15°c + 273 = 288°k s = 39 x sqrt 288°k = 660 8 kt sqrt square root. Question 40-16
The limits of yellow scale of an airspeed indicator are Vno the lower limit vne the upper limit. the velocity of sound varies only with temperature s = 39 x sqrt °kelvin to get kelvin add 273 to centigrade +15°c + 273 = 288°k s = 39 x sqrt 288°k = 660 8 kt sqrt square root. Question 40-17
The limits of green scale of an airspeed indicator are Vs the lower limit vno the upper limit. the velocity of sound varies only with temperature s = 39 x sqrt °kelvin to get kelvin add 273 to centigrade +15°c + 273 = 288°k s = 39 x sqrt 288°k = 660 8 kt sqrt square root. Question 40-18
The limits of white scale of an airspeed indicator are Vso the lower limit vfe the upper limit. white scale vso to vfe (fe from flap extended) green scale vs (without flaps) to vno yellow scale vno to vne red line vne (speed of never exceed). Question 40-19
The reading of a mach indicator independent of The outside temperature. The mach number a function of (p s)/s where p = total pressure (pitot) s = static pressure indications on mach indicator will vary with p s (p s) which the differential pressure measurement tas will vary with temperature but not mach indicator. Question 40-20
After an aircraft has passed through a volcanic cloud which has blocked total pressure probe inlet of airspeed indicator pilot begins a stabilized descent and finds that indicated airspeed The outside temperature. franck the asi (air speed indicator) provided the pitot static vent the pitot blocked so asi going to react like an altimeter. Question 40-21
The principle of mach indicator based on computation of ratio The outside temperature. pt total pressure ps static pressure dynamic pressure = pt ps mach number proportional to (dynamic pressure/static pressure). Question 40-22
The mach number the True airspeed (tas) divided the local speed of sound. pt total pressure ps static pressure dynamic pressure = pt ps mach number proportional to (dynamic pressure/static pressure). Question 40-23
Given ts static temperature sat tt total temperature tat kr recovery coefficient m mach numberthe total temperature can be expressed approximately the formula True airspeed (tas) divided the local speed of sound. this question a little bit tricky if you add recovery coefficient to formula you will have exactly 'total temperature' without you only have an approximation. Question 40-24
A blocked pitot head with a clear static source causes airspeed indicator to React like an altimeter. this question a little bit tricky if you add recovery coefficient to formula you will have exactly 'total temperature' without you only have an approximation. Question 40-25
Given m the mach numberts the static temperaturett the total temperature Ts = tt /( + 2 m²). this question a little bit tricky if you add recovery coefficient to formula you will have exactly 'total temperature' without you only have an approximation. Question 40-26
The airspeed indicator of a twin engine aircraft comprises different sectors and colour marks the blue line corresponds to Optimum climbing speed with one engine inoperative or vy. this question a little bit tricky if you add recovery coefficient to formula you will have exactly 'total temperature' without you only have an approximation. Question 40-27
The mach number The ratio of aircraft true airspeed to sonic velocity at altitude considered. mach number formula m = tas/a (a= local speed sound). Question 40-28
In an adc air data computer altitude computed from Measurement of barometric pressure from a static source on fuselage (static pressure). mach number formula m = tas/a (a= local speed sound). Question 40-29
Indication of mach number obtained from Indicated speed altitude using a speed indicator equipped with an altimeter type aneroid. the mach meter modifies output from an airspeed capsule using an altimeter (aneroid) capsule. Question 40-30
The altimeter consists of one or several aneroid capsules located in a sealed casing the pressures in aneroid capsule i and casing ii are respectively (i) vacuum (or a very low pressure) (ii) static pressure. the mach meter modifies output from an airspeed capsule using an altimeter (aneroid) capsule. Question 40-31
In case of accidental closing of an aircraft's left static pressure port rain birds altimeter Overreads altitude in case of a sideslip to left displays correct information during symmetric flight. amassa with a side slip to left pressure will increase on left side of aircraft decrease on right if both static ports are open pressures are compensated (this why two static ports are used) so a lower static pressure will be sensed the altimeter will overread aircraft's altitude. Question 40-32
The vertical speed indicator vsi fed Overreads altitude in case of a sideslip to left displays correct information during symmetric flight. amassa with a side slip to left pressure will increase on left side of aircraft decrease on right if both static ports are open pressures are compensated (this why two static ports are used) so a lower static pressure will be sensed the altimeter will overread aircraft's altitude. Question 40-33
The altimeter supplied with Overreads altitude in case of a sideslip to left displays correct information during symmetric flight. amassa with a side slip to left pressure will increase on left side of aircraft decrease on right if both static ports are open pressures are compensated (this why two static ports are used) so a lower static pressure will be sensed the altimeter will overread aircraft's altitude. Question 40-34
Total air temperature tat Higher or equal to static air temperature (sat) depending on mach number sat. tat = sat (1 + 0 2 x kr x m²) sat static temperature in kelvin tat total temperature in kelvin kr recovery coefficient m mach number if mach 0 sat = tat if sat 0 tat = sat absolute zero in kelvin almost impossible to reach but from formula tat will be 0 if sat 0. Question 40-35
An air data computer 1 supplies gs and drift angle2 determines tat and true altitude3 receives static pressure and total pressure4 supplies tas to ins computer5 determines mach number and oatthe combination regrouping all correct statements Higher or equal to static air temperature (sat) depending on mach number sat. the adc (air data computer) uses as input data static pressure total pressure (pitot pressure) tat . Question 40-36
An aircraft flying at flight level fl180 and mach number 0 36 its onboard thermometer reads tat = 5°c considering that probe recovery coefficient 0 84 present weather conditions compared with standard atmosphere are Higher or equal to static air temperature (sat) depending on mach number sat. what the oat (outside air temperature) at fl180 in standard atmosphere? 15° (2 x 18)° = 21ºc at fl180 calculation oat at fl180 11°c instead of 21°c present weather conditions compared with standard atmosphere are standard + 10°c. Question 40-37
An airspeed indicator displays Higher or equal to static air temperature (sat) depending on mach number sat. ias indicated air speed. Question 40-38
The angle of attack transmitter placed laterally on forward part of fuselage supplies an electrical signal which can indicate angular position of 1 a specific slaved pitot probe 2 a vane detector 3 a conical slotted probe the combination regrouping all correct statements Higher or equal to static air temperature (sat) depending on mach number sat. 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 40-39
At a given altitude hysteresis error of an altimeter varies substantially with Time passed at this altitude. hysteresis this error a lag in altitude indications caused the elasticity of aneroid capsule it occurs when an aircraft initiates a large rapid altitude change or an abrupt level off from a rapid climb or descent it takes a period of time the aneroid to catch up with new pressure environment hence a lag in indications this error has been significantly reduced in modern altimeters is considered negligible at normal rates of descent jet aircraft. Question 40-40
Below tropopause in standard conditions when climbing at a constant mach number Time passed at this altitude. 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.
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