Question 59-1 : During a climb at a constant ias below the tropopause in isa conditions ? [ Success topography ]

Question 59-2 : The altimeter of your aircraft indicates 11000 ft with a subscale setting of 101325 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 101325 hpa

Question 59-3 : The altimeter of your aircraft indicates 17000 ft with a subscale setting of 101325 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 101325 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 101325 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 101325 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 soundlocal speed of sound varies only with temperature and the question states 'total temperature remains constant' thus lss remains constant and the tas remains constantcas = 12 rho tas²rho 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 attitude2 a slotted probe which positions itself to determine the angle of attack3 a vane detector which positions the rotor of a synchro transmitter the combination regrouping ?

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 999vane 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 soundlocal speed of sound varies only with temperature and the question states 'total temperature increases' thus lss increasesto maintain a constant mach number tas must increasecas = 12 rho tas²rho decreases when temperature increases ans since tas is increased cas will remain constantyou 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.

For those questions use the very simple 'ertm' diagram 1037the 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 achmach number = taslocal speed of soundtas and mach number increase during a climb at a constant caslss 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 .

In a standard atmosphere and at the sea level this is the starting point of the following table 1037

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 decreasesif the total pressure head is clogged up by ice the airspeed indicator will then show an increasing speedindicated airspeed = dynamic pressure + static pressure static pressuresince 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 setting2 speed3 angle of attackthe 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.

The alternate static vent of an unpressurised aircraft senses the air pressure in the flight deckcockpit 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 attack2 oat3 tasthe 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 altitude2 mach number3 cas4 tas5 satthe 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 atmospherein these conditions 1 the tas is approximately 10% higher than the ias2 the difference between the eas and the cas is negligible3 the speed displayed on the airspeed indicator is a cas if the position error and ?

1 2 3.

Tas = ias + 2% per 1000 ft altitudeeas is cas corrected for compressibility and at low speed and low altitude compressibility is negligeablecas is ias corrected position and instrument errors

Question 59-22 : The tas is obtained from the cas by correcting for the following errors 1 instrument2 compressibility3 position4 densitythe combination that regroups all of the correct statements is ?

Question 59-23 : The cas is obtained from ias by correcting for the following errors 1 position2 compressibility3 instrument4 densitythe 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 position2 compressibility3 instrument4 densitythe 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.

For those questions use the very simple 'ertm' diagram 1039the 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 1037the 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 achtas will increase since density decreases with altitudemach = tas local speed of soundlocal 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.

514you have to turn altimeter setting adjustement knob in a clockwise direction to increase the indicated pressurethis 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.

The alternate static vent of an unpressurised aircraft senses the air pressure in the flight deckcockpit 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 iasthe error in altimeter readings caused by the variation of the static pressure near the source is known as position errorinstrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicatedcas 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 errorsposition error error in altimeter readings caused by the variation of the static pressure near the sourceinstrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicatedcompressibility 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 andor static ports.

Question 59-36 : The eas is obtained from the ias by correcting for the following errors 1 instrument2 position3 density 4 compressibilitythe 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 errorsposition error error in altimeter readings caused by the variation of the static pressure near the sourceinstrument error refers to the combined accuracy and precision of a measuring instrument or the difference between the actual value and the value indicatedcompressibility 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.

For those questions use the very simple 'ertm' diagram 1037the 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 achtas will decrease since density increases with altitudemach = tas local speed of soundlocal 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.

The terms 'vertical speed indicator' or 'vsi' or 'vertical airspeed indicator' are used for the variometeran 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.