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Question 59-1 : During a climb at a constant ias below the tropopause in isa conditions ? [ Success topography ]
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.
Question 59-2 : The altimeter of your aircraft indicates 11000 ft with a subscale setting of 1013,25 hpa. qnh is 1023 hpa. oat is +3°c. the pressure altitude of the aircraft is ?
11000 ft.
.an altimeter shows a pressure altitude with a sub scale setting of 1013.25 hpa.
Question 59-3 : The altimeter of your aircraft indicates 17000 ft with a subscale setting of 1013,25 hpa. qnh is 1031 hpa. the pressure altitude of the aircraft is ?
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.
Question 59-4 : The altimeter of your aircraft indicates 16000 ft with a subscale setting of 1013,25 mb. qnh is 993 hpa. oat is 3°c. the pressure altitude of the aircraft is ?
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.
Question 59-5 : An aeroplane is in a steady climb. the auto throttle maintains a constant mach number. if the total temperature remains constant, the calibrated airspeed ?
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
Question 59-6 : An angle of attack sensor may consist of..1 an inertial system computing the difference between flight path and flight attitude.2 a slotted probe which positions itself to determine the angle of attack.3 a vane detector which positions the rotor of a synchro transmitter. ?
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..
Question 59-7 : An airplane is in steady cruise at flight level 290. the auto throttle maintains a constant mach number. if the total temperature increases, the calibrated airspeed ?
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.
Question 59-8 : In standard atmosphere, when climbing at constant cas ?
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.
Question 59-9 : In a standard atmosphere and at the sea level, the calibrated airspeed cas is ?
Equal to the true airspeed tas.
Question 59-10 : The parameter that determines the relationship between eas and tas is ?
Density altitude.
Question 59-11 : With cas and pressure altitude, we can deduce ?
Eas.
Question 59-12 : Speed of sound is proportional to ?
The square root of the absolute temperature.
Question 59-13 : The total air temperature tat is ?
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.
Question 59-14 : During a climb, if the total pressure head is rapidly clogged up by ice, the sensed total pressure remains constant and ?
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.
Question 59-15 : The static air temperature sat is ?
The ambient outside air temperature.
.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.
Question 59-16 : The limits of the green scale of an airspeed indicator are ?
Vs1 and vno.
Question 59-17 : Concerning the pitot and static system, the static pressure error varies according to.1 altimeter setting.2 speed.3 angle of attack.the combination that regroups all of the correct statements is ?
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.
Question 59-18 : The alternate static source is used ?
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.
Question 59-19 : The machmeter is subject to position error. this error varies according to.1 angle of attack.2 oat.3 tas.the combination that regroups all of the correct statements is ?
1, 3.
.position pressure error varies with angle of attack and speed but not with temperature.
Question 59-20 : The data output from the adc are..1 barometric altitude.2 mach number.3 cas.4 tas.5 sat..the combination that regroups all of the correct statements is ?
1, 2, 3, 4, 5.
Question 59-21 : An aeroplane is cruising at fl 60 with a tas of 100 kt in standard atmosphere..in these conditions..1 the tas is approximately 10% higher than the ias.2 the difference between the eas and the cas is negligible. ?
1, 2, 3.
.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.
Question 59-22 : The tas is obtained from the cas by correcting for the following errors.1 instrument.2 compressibility.3 position.4 density.the combination that regroups all of the correct statements is ?
2, 4.
Question 59-23 : The cas is obtained from ias by correcting for the following errors.1 position.2 compressibility.3 instrument.4 density.the combination that regroups all of the correct statements is ?
1, 3.
Question 59-24 : The eas is obtained from the cas by correcting for the following errors.1 position.2 compressibility.3 instrument.4 density.the combination that regroups all of the correct statements is ?
2
Question 59-25 : If the static ports are completely clogged up by ice during a climb, the vertical speed indicator shows ?
Zero.
Question 59-26 : Eas is equal to ?
Cas corrected for compressibility error.
Question 59-27 : During a climb at a constant mach number below the tropopause in standard atmosphere ?
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.
Question 59-28 : When climbing at a constant cas through an isothermal layer, the mach number ?
Increases.
.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.
Question 59-29 : If the pilot increases the reference pressure using the sub scale setting knob, the altitude indicated by the altimeter ?
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.
Question 59-30 : The alternate static source of a light non pressurized aircraft is located in the flight deck. when used, the static pressure sensed is likely to be ?
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.
Question 59-31 : Eas can be obtained from the following data ?
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.
Question 59-32 : Cas is equal to ?
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.
Question 59-33 : Eas is equal to ?
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.
Question 59-34 : The altimeter is subject to static pressure error. this error results from ?
Incorrect pressure sensing caused by disturbed airflow around the static ports.
Question 59-35 : The machmeter is subject to position error. this error results from ?
Incorrect pressure sensing caused by disturbed airflow around the pitot tube and/or static ports.
Question 59-36 : The eas is obtained from the ias by correcting for the following errors.1 instrument.2 position.3 density.4 compressibility.the combination that regroups all of the correct statements is ?
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.
Question 59-37 : When descending at a constant cas through an isothermal layer, the mach number ?
Decreases.
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.
Question 59-38 : In standard atmosphere at sea level, the eas is ?
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.
Question 59-39 : The alternate static source of a light non pressurized aircraft is located in the flight deck. as the alternate static source is opened, the vertical airspeed indicator may ?
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.
Question 59-40 : Concerning the pitot and static system, the static pressure error ?
Is caused by disturbed airflow around the static ports.
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