The adc uses the following parameters as input data ? [ Result LAPL ]

Question 48-1 : Static pressure total pressure tat mach number baro altitude cas tas baro altitude tat total pressure static pressure tat egt

exemple 148 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 48-2 : 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 152 To locate it outside the boundary layer. — To locate it outside the boundary layer.

In case of static blockage the airspeed indicator ?

Question 48-3 : 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 156 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 48-4 : Pitot tubes and static ports pitot tubes only static ports only alternate static sources only

exemple 160 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 48-5 : Pt ps ps pt pd ps pt pd

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

Question 48-6 : Total pressure static pressure total pressure plus static pressure dynamic pressure

exemple 168 Total pressure. — Total pressure.

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

Question 48-7 : Tas and angle of attack tas and altimeter setting angle of attack and oat tas and oat

exemple 172 Tas and angle of attack. — Tas and angle of attack.

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

Question 48-8 : Tas and angle of attack tas and oat oat only tas only

exemple 176 Tas and angle of attack. — Tas and angle of attack.

When climbing at a constant cas in standard atmosphere ?

Question 48-9 : Tas increases tas decreases tas remains constant tas first decreases then remains constant above the tropopause

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

Question 48-10 : 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 184 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 48-11 : Standard standard +26°c standard 26°c standard +10°c

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

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

Question 48-12 : Tends to over read tends to under read indicates zero is blocked

exemple 192 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 48-13 : 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 196 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 48-14 : 0 51 0 53 0 41 0 43

exemple 200 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 48-15 : 0 8 0 82 0 83 0 53

exemple 204 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 48-16 : 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 208 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 48-17 : 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 212 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 48-18 : 44°c 54°c 41°c 51°c

exemple 216 -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 48-19 : 2 3 1 3 1 2 3 1 2

exemple 220 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 48-20 : 27°c standard 34°c 10°c

exemple 224 -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 48-21 : 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 228 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 48-22 : Increases decreases remains constant decreases if the static temperature is lower than the standard temperature increases if higher

exemple 232 Increases. — Img964 Increases.

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

Question 48-23 : Flux valve adc direct indicating compass directional gyro

exemple 236 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 48-24 : Map showing the isogonal lines map showing the isoclinic lines deviation correction curve compass swinging curve

exemple 240 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 48-25 : 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 48-26 : Error detector flux valve directional gyro unit directional gyro erection device

exemple 248 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 48-27 : Error detector erector system heading indicator amplifier

exemple 252 Error detector. — Error detector.

The gyromagnetic compass torque motor ?

Question 48-28 : 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 256 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 48-29 : 160° 200° 170° 190°

exemple 260 160°. — 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 48-30 : 030° 355° 330° 015°

exemple 264 030° — 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 48-31 : 1 3 4 5 1 4 2 3 5 2 3

In a gyromagnetic compass the flux valve feeds the ?

Question 48-32 : Error detector erecting system heading indicator amplifier

exemple 272 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.

The operating principle of the vertical speed indicator vsi is based on the ?

Question 48-33 : Static pressure dynamic pressure total pressure kinetic pressure

exemple 276 Static pressure — Static pressure

A pilot wishes to turn right through 90° on to north at rate 2 at latitude of ?

Question 48-34 : 330° 360° 030° 010°

exemple 280 330°. — 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 .only 330° is an undershoot value when you perform a right turn to the north 330°.

An aircraft takes off on a runway with an alignment of 045° the compass is ?

Question 48-35 : A value below 045° 045° a value above 045° in the southern hemisphere a value above 045° in the northern hemisphere

exemple 284 A value below 045°. — Acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh A value below 045°.

In the northern hemisphere during deceleration following a landing in a ?

Question 48-36 : No apparent turn an apparent turn to the east an apparent turn to the west an apparent turn to the south

exemple 288 No apparent turn. — Acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh No apparent turn.

In the northern hemisphere during deceleration following a landing in a ?

Question 48-37 : No apparent turn an apparent turn to the east an apparent turn to the west an apparent turn to the north

exemple 292 No apparent turn. — Acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh No apparent turn.

During deceleration following a landing in a westerly direction a magnetic ?

Question 48-38 : An apparent turn to the south an apparent turn to the north no apparent turn no apparent turn only on northern latitudes

exemple 296 An apparent turn to the south. — Acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh An apparent turn to the south.

During deceleration following a landing in a westerly direction a magnetic ?

Question 48-39 : An apparent turn to the north an apparent turn to the south no apparent turn no apparent turn only on southern latitudes

exemple 300 An apparent turn to the north. — .acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh An apparent turn to the north.

During deceleration following a landing in an easterly direction a magnetic ?

Question 48-40 : An apparent turn to the south an apparent turn to the north no apparent turn no apparent turn only on northern latitudes

exemple 304 An apparent turn to the south. — .acceleration/deceleration errors are false compass indications of a swing to the north or south during speed changes of the airplane this error is most pronounced when flying on a heading of east or west and decreases when flying closer to a north or south heading in a direct north or south heading this error does not occur .in the northern hemisphere the compass swings towards the north during acceleration and towards the south during deceleration in the southern hemisphere this error occurs the other way round when the speed stabilises the error disappears .learn this for northern hemisphere ands . a cceleration gives apparent turn to n orth . d eceleration gives apparent turn to s outh An apparent turn to the south.

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