When descending at a constant cas through an isothermal layer the mach number ? [ Exam pilot ]

Question 60-1 : Decreases increases remains constant increases if oat is lower than the standard temperature decreases if higher

exemple 160 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 Decreases.

In standard atmosphere at sea level the eas is ?

Question 60-2 : Equal to the tas independent of the tas higher than the tas lower than the tas

exemple 164 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 Equal to the tas.

The alternate static source of a light non pressurized aircraft is located in ?

Question 60-3 : Indicate a momentary climb indicate a slight momentary descent indicate a high rate of descent be blocked

exemple 168 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 Indicate a momentary climb.

Concerning the pitot and static system the static pressure error ?

Question 60-4 : Is caused by disturbed airflow around the static ports is a direct effect of heating of the static ports affects the alternate static port only is a direct effect of a blockage of the static port

exemple 172 Is caused by disturbed airflow around the static ports. — Is caused by disturbed airflow around the static ports.

The output data from the adc are used by .1 transponder.2 efis.3 automatic ?

Question 60-5 : 1 2 3 1 2 1 3 2 3

Maintaining cas and flight level constant a fall in ambient temperature results ?

Question 60-6 : Lower tas because air density increases lower tas because air density decreases higher tas because air density increases higher tas because air density decreases

Admin .lower temperature means an increase of air density air mass is contracting it is similar to a descent to a lower altitude .you can use the 'ertm' diagram . 1037.the cas line is vertical because cas is constant . ertm for e as/ r as rectified air speed or cas / t as/ m ach .cas = 1/2 rho v².density will increase during descent and in order to maintain constant cas only v tas can be reduced

If oat increases whilst maintaining a constant cas and flight level ?

Question 60-7 : Mach number remains constant mach number decreases tas remains constant tas decreases

exemple 184 Mach number remains constant. — .if oat increases density decreases with higher temperature air is expanding density is reduced .cas = 1/2 x density x tas².cas is constant and density decreases then tas must increase .mach = tas / local speed of sound.local speed of sound varies only with temperature lss varies with the square root of absolute temperature formula lss = 39 x square root of oat+273 thus if tas increases and lss increases the mach number remains constant Mach number remains constant.

If oat decreases whilst maintaining a constant cas and flight level ?

Question 60-8 : Mach number remains constant mach number increases tas remains constant tas increases

.if oat decreases density increases with lower temperature air is contracting density is increased .cas = 1/2 x density x tas².cas is constant and density increases then tas must decrease .mach = tas / local speed of sound.local speed of sound varies only with temperature lss varies with the square root of absolute temperature formula lss = 39 x square root of oat+273 thus if tas decreases and lss decreases the mach number remains constant

The adc uses the following parameters as input data ?

Question 60-9 : Static pressure total pressure tat mach number baro altitude cas tas baro altitude tat total pressure static pressure tat egt

exemple 192 Static pressure, total pressure, tat. — Static pressure, total pressure, tat.

The total pressure head comprises a mast which moves its port to a distance ?

Question 60-10 : To locate it outside the boundary layer not to disturb the aerodynamic flow around the aircraft it is protected from icing it is easily accessible during maintenance checks

exemple 196 To locate it outside the boundary layer. — To locate it outside the boundary layer.

In case of static blockage the airspeed indicator ?

Question 60-11 : Under reads in climb and over reads in descent over reads in climb and under reads in descent over reads in climb only under reads in descent only

exemple 200 Under-reads in climb and over-reads in descent. — . 959.the asi is a sensitive differential pressure gauge which measures and promptly indicates the difference between pitot total pressure and static pressure total pressure static pressure = dynamic pressure .these two pressures are equal when the aircraft is parked on the ground in calm air .when the aircraft moves through the air the pressure on the pitot line becomes greater than the pressure in the static lines this difference in pressure is registered by the airspeed pointer on the face of the instrument .thus while descending the total pressure increases* and the static pressure from the static source does not your airspeed indicator will over read .*while descending density increases so total pressure increases .while climbing the total pressure decreases and the static pressure from the static source does not your airspeed indicator will under read Under-reads in climb and over-reads in descent.

The machmeter is subject to position error this error concerns ?

Question 60-12 : Pitot tubes and static ports pitot tubes only static ports only alternate static sources only

exemple 204 Pitot tubes and static ports. — 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 Pitot tubes and static ports.

Given .pt total pressure.ps static pressure.pd dynamic pressure.the airspeed ?

Question 60-13 : Pt ps ps pt pd ps pt pd

The open ended tube parallel to the longitudinal axis of the aircraft senses the ?

Question 60-14 : Total pressure static pressure total pressure plus static pressure dynamic pressure

exemple 212 Total pressure. — Total pressure.

The altimeter is subject to static pressure error this error varies according to ?

Question 60-15 : Tas and angle of attack tas and altimeter setting angle of attack and oat tas and oat

exemple 216 Tas and angle of attack. — Tas and angle of attack.

The machmeter is subject to position error this error varies according to ?

Question 60-16 : Tas and angle of attack tas and oat oat only tas only

exemple 220 Tas and angle of attack. — Tas and angle of attack.

When climbing at a constant cas in standard atmosphere ?

Question 60-17 : Tas increases tas decreases tas remains constant tas first decreases then remains constant above the tropopause

exemple 224 Tas increases. — 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 increases.

The compressibility error must be taken into account only for aeroplane with ?

Question 60-18 : Tas greater than approximately 200 kt tas greater than approximately 100 km/h mach number greater than 0 8 mach number greater or equal to 1

exemple 228 Tas greater than approximately 200 kt. — Tas greater than approximately 200 kt.

An aeroplane is flying at fl300 and mach number 0 76 .the indicated total air ?

Question 60-19 : Standard standard +26°c standard 26°c standard +10°c

exemple 232 Standard. — Revised ecqb03 july 2016 ..the total temperature can be expressed approximately by the formula .tt = ts 1 + 0 2 kr m² .. ts the static temperature sat in kelvin. tt the total temperature tat in kelvin. kr the recovery coefficient. m the mach number..254 15 = ts 1 + 0 2 kr m² .ts = 254 15 / 1 + 0 2 x 0 96 x 0 5776 .ts = 254 15 / 1 11 = 229° k..oat = 273 15 229 = 44 15°c .at fl300 isa temperature is .15°c 2°c x 30 = 45°c .we can say that oat is standard Standard.

The alternate static source of a light non pressurized aeroplane is located in ?

Question 60-20 : Tends to over read tends to under read indicates zero is blocked

exemple 236 Tends to over-read. — 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 .the altimeter will sense a lower pressure than the outside pressure it will tend to over read Tends to over-read.

The alternate static source of a light non pressurized aeroplane is located in ?

Question 60-21 : The airspeed indicator tends to over read the airspeed indicator tends to under read the airspeed indicator indicates a consistent decreasing speed it has no influence on airspeed indicator reading

exemple 240 The airspeed indicator tends to over-read. — Admin .the alternate static vent of a 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 The airspeed indicator tends to over-read.

An airplane is flying at fl140 with a cas of 260 kt in standard conditions the ?

Question 60-22 : 0 51 0 53 0 41 0 43

exemple 244 0.51 — Admin .isa temperature at fl140 is 13°c on the nav computer find tas . 982.next step find mach number . 983.jripoche .tas=ias+2%/1000ft=332 8kt.oat= 12 72°c=260 43°k.mn=332 8/ 38 94sqrt260 43 =0 5295.so the most accurate answer shouldn't be 0 53 . .cas = ias in the absence of position and instrument errors .you can't say cas = ias without those informations 0.51

An aeroplane is flying at fl300 with a tas of 470 kt in standard conditions the ?

Question 60-23 : 0 8 0 82 0 83 0 53

exemple 248 0.8 — ..in standard conditions at fl300 temperature is .15°c 30 x 2°c = 45°. 1026.set 45° in airpseed window in front of 'm kt' indicator .read in the inner scale in front of 470 kt a mach number of 0 805 0.8

During a climb at a constant cas below the tropopause in standard atmosphere ?

Question 60-24 : The mach number increases and the speed of sound decreases the mach number decreases and the speed of sound increases the mach number and the speed of sound increase the mach number and the speed of sound decrease

exemple 252 The mach number increases and the speed of sound 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 .the velocity of sound is decreasing as temperature decreases .mach number = tas / local sound speed The mach number increases and the speed of sound decreases.

A servo assisted altimeter is more accurate than a simple altimeter because the ?

Question 60-25 : The capsules are detected by a very sensitive electro magnetic pick off the pointers are detected by a very sensitive electro magnetic pick off the capsules are inhibited the capsules are not taken into account

exemple 256 The capsules are detected by a very sensitive electro-magnetic pick-off. — The capsules are detected by a very sensitive electro-magnetic pick-off.

An aeroplane is flying at fl100 and mach number 0 76 the indicated total air ?

Question 60-26 : 44°c 54°c 41°c 51°c

exemple 260 -44°c. — Admin .the total temperature can be expressed approximately by the formula .tt = ts 1 + 0 2 kr m² . ts the static temperature sat in kelvin. tt the total temperature tat in kelvin. kr the recovery coefficient. m the mach number..254 15 = ts 1 + 0 2 kr m² .ts = 254 15 / 1 + 0 2 x 0 96 x 0 5776 .ts = 254 15 / 1 11 = 229° k.273 15 229 = 44 15°c -44°c.

Concerning the pitot and static system the position error varies with .1 ?

Question 60-27 : 2 3 1 3 1 2 3 1 2

exemple 264 2, 3. — Cqb15 may 2012..this question exists n°626 in the database with static pressure error varies instead of position error varies .statement n°2 speed is replaced here by 'mach number' 2, 3.

An aeroplane is flying at fl 320 and mach number 0 79 .the oat is 53°c ?

Question 60-28 : 27°c standard 34°c 10°c

exemple 268 -27°c. — Ecqb03 july 2016 ..the total temperature can be expressed approximately by the formula .tt = ts 1 + 0 2 kr m² .. ts the static temperature sat in kelvin. tt the total temperature tat in kelvin. kr the recovery coefficient. m the mach number..tt = 220°k 1 + 0 2 x 0 96 x 0 79² .tt = 220°k 1 + 0 12 .tt = 246°k..tt = 273 15 246 = 26 75°c -27°c.

Which of these statements is true ?

Question 60-29 : The probes used for sat measurements have a recovery factor of 0 75 to 0 90 while the probes used for tat measurements have a recovery factor of around 1 00 the probes used for sat measurements have a recovery factor of around 1 00 the probes used for tat measurements are directly connected to the temperature indicator instruments the probes used for sat measurements have a recovery factor ranging from 75 to 90 percent

exemple 272 The probes used for sat measurements have a recovery factor of 0.75 to 0.90, while the probes used for tat measurements have a recovery factor of around 1.00. — Ecqb03 july 2016..recovery factor refers to the amount of ram rise that is recoverable by the sensor total head thermometers typically have a recovery factor of 0 75 to 0 9 whereas the rosemount temperature probe has a recovery factor of 1 0 the ram rise is due to adiabatic compression and for simple sat temperature sensors used on light aircraft that fly at speeds less than mach 0 2 the ram rise factor does not apply the sat sensor measures the actual temperature and is therefore 100% efficient tat is 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 is the recovery factor and m the mach number ..ram rise comes into effect at airspeeds greater than m 0 2..in summary sat temperature sensors are not affected by ram rise whereas tat sensors are The probes used for sat measurements have a recovery factor of 0.75 to 0.90, while the probes used for tat measurements have a recovery factor of around 1.00.

An aeroplane is in a steady descend the auto throttle maintains a constant mach ?

Question 60-30 : Increases decreases remains constant decreases if the static temperature is lower than the standard temperature increases if higher

exemple 276 Increases. — Img964 Increases.

In a gyromagnetic compass the direction of the earth's magnetic field is given ?

Question 60-31 : Flux valve adc direct indicating compass directional gyro

exemple 280 Flux valve. — A flux valve is a sensitive detector that receives an electrical signal from the earth's magnetic field and directs it to an amplifier and then into a gyro stabilized compass indicator Flux valve.

The magnetic heading can be derived from the true heading by means of a ?

Question 60-32 : Map showing the isogonal lines map showing the isoclinic lines deviation correction curve compass swinging curve

exemple 284 Map showing the isogonal lines. — Admin . 1425.isogonic lines connect positions that have the same variation .agonic line a line which joins all points where the value of magnetic variation is zero .magnetic heading is the direction that the aircraft is pointing in relation to magnetic north .true heading is the direction that the aircraft is pointing in relation to true north .since true north directly over the earth's axis of rotation and magnetic north somewhere over northern canada are not at the same place both headings often differ .to find out the difference at a particular location look at the isogonic lines on your area the lines labeled 20°e 15°e 10°e etc they will indicate the magnetic deviation .to get the true heading simply take the reading from the magnetic compass and either add an easterly or subtract a westerly magnetic deviation Map showing the isogonal lines.

The fields affecting a magnetic compass originate from .1 magnetic masses .2 ?

Question 60-33 : 1 2 4 1 2 3 1 2 3 4 1 3 4

The input signal of the amplifier of the gyromagnetic compass resetting device ?

Question 60-34 : Error detector flux valve directional gyro unit directional gyro erection device

exemple 292 Error detector. — The flux valve sends a signal containing information on the earth's magnetic field but not at this stage carrying any information about the 'error' between the compass display and and aircraft heading the 'error' is detected at the selsyn with its 'error detector' the selsyn now sends information on the error to the amplfier and precession systems that reduce the error to zero .selsyn or synchro is an electro mechanical device used for the easy and precise transmission of angular data between two or more remote points Error detector.

In the gyromagnetic compass the heading information from the flux valve is sent ?

Question 60-35 : Error detector erector system heading indicator amplifier

exemple 296 Error detector. — Error detector.

The gyromagnetic compass torque motor ?

Question 60-36 : Causes the directional gyro unit to precess causes the heading indicator to precess feeds the error detector system is fed by the flux valve

exemple 300 Causes the directional gyro unit to precess. — Causes the directional gyro unit to precess.

A pilot wishes to turn left on to a southerly heading with 20° bank at a ?

Question 60-37 : 160° 200° 170° 190°

exemple 304 160°. — Admin .in the northern hemisphere as you turn through north you must roll out early onto your required heading .if you turn through south you roll out late .use unos to remember this un = undershoot north os = overshoot south .the value you need to overshoot or undershoot does vary with latitude due to compass dip and bank angle due to acceleration .to calculate the value use this approximation formula . bank angle + latitude /2. 20°bank + 20°latitude /2 = 20° .180° 20° = 160° 160°.

A pilot wishes to turn left on to a northerly heading with 10° bank at a ?

Question 60-38 : 030° 355° 330° 015°

exemple 308 030° — Admin .in the northern hemisphere as you turn through north you must roll out early onto your required heading .if you turn through south you roll out late .use unos to remember this un = undershoot north os = overshoot south .the value you need to overshoot or undershoot does vary with latitude due to compass dip and bank angle due to acceleration .to calculate the value use this approximation formula . bank angle + latitude /2. 10°bank + 50°latitude /2 = 30° .000° 30° = 030° 030°

A gyromagnetic compass is a system which always consists of . 1 a horizontal ?

Question 60-39 : 1 3 4 5 1 4 2 3 5 2 3

In a gyromagnetic compass the flux valve feeds the ?

Question 60-40 : Error detector erecting system heading indicator amplifier

exemple 316 Error detector. — .the gyro magnetic compass is made up of . a magnetic detector unit flux valve which electrically senses the direction of earth's magnetic field . a gyroscope which points to a fixed point in space regardless of any manoeuvres the aircraft makes . an error detector to sense any difference between the gyro and magnetic headings and apply corrections to the gyro .the magnetic detector unit flux valve feeds the error detector with information about the earth's magnetic field Error detector.

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