Question 60-1 : The output data from the adc are used by 1 transponder2 efis3 automatic flight control system afcs the combination that regroups all of the correct statements is ? [ Exam pilot ]

Question 60-2 : Maintaining cas and flight level constant a fall in ambient temperature results in ?

Lower tas because air density increases.

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 1037the cas line is vertical because cas is constant ertm for e as r as rectified air speed or cas t as m achcas = 12 rho v²density will increase during descent and in order to maintain constant cas only v tas can be reduced

Question 60-3 : If oat increases whilst maintaining a constant cas and flight level ?

Mach number remains constant.

If oat increases density decreases with higher temperature air is expanding density is reduced cas = 12 x density x tas²cas is constant and density decreases then tas must increasemach = tas local speed of soundlocal 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

Question 60-4 : If oat decreases whilst maintaining a constant cas and flight level ?

Mach number remains constant.

If oat decreases density increases with lower temperature air is contracting density is increased cas = 12 x density x tas²cas is constant and density increases then tas must decreasemach = tas local speed of soundlocal 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

Question 60-5 : The adc uses the following parameters as input data ?

Static pressure total pressure tat.

Question 60-6 : The total pressure head comprises a mast which moves its port to a distance from the aircraft skin in order ?

Question 60-7 : In case of static blockage the airspeed indicator ?

Under reads in climb and over reads in descent.

959the 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 airwhen 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 instrumentthus 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 increaseswhile climbing the total pressure decreases and the static pressure from the static source does not your airspeed indicator will under read

Question 60-8 : The machmeter is subject to position error this error concerns ?

Question 60-9 : Given pt total pressureps static pressurepd dynamic pressurethe airspeed indicator measures ?

Pt ps.

Question 60-10 : The open ended tube parallel to the longitudinal axis of the aircraft senses the ?

Total pressure.

Question 60-11 : The altimeter is subject to static pressure error this error varies according to ?

Tas and angle of attack.

Question 60-12 : The machmeter is subject to position error this error varies according to ?

Tas and angle of attack.

Question 60-13 : When climbing at a constant cas in standard atmosphere ?

Tas 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 ach

Question 60-14 : The compressibility error must be taken into account only for aeroplane with ?

Tas greater than approximately 200 kt.

Question 60-15 : An aeroplane is flying at fl300 and mach number 076the indicated total air temperature is 19°cconsidering that the probe recovery coefficient is 096oat is ?

Standard.

Revised ecqb03 july 2016the total temperature can be expressed approximately by the formula tt = ts 1 + 02 kr m² ts the static temperature sat in kelvin tt the total temperature tat in kelvin kr the recovery coefficient m the mach number25415 = ts 1 + 02 kr m² ts = 25415 1 + 02 x 096 x 05776 ts = 25415 111 = 229° koat = 27315 229 = 4415°cat fl300 isa temperature is 15°c 2°c x 30 = 45°cwe can say that oat is standard

Question 60-16 : The alternate static source of a light non pressurized aeroplane is located in the flight deck when used the altimeter ?

Tends to over read.

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 aircraftthe altimeter will sense a lower pressure than the outside pressure it will tend to over read

Question 60-17 : The alternate static source of a light non pressurized aeroplane is located in the flight deck when used ?

The airspeed indicator tends to over read.

The alternate static vent of a 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 60-18 : An airplane is flying at fl140 with a cas of 260 kt in standard conditions the mach number is ?

051.

Isa temperature at fl140 is 13°c on the nav computer find tas 982next step find mach number 983 jripoche tas=ias+2%1000ft=3328ktoat= 1272°c=26043°kmn=3328 3894sqrt26043 =05295so the most accurate answer shouldn't be 053 cas = ias in the absence of position and instrument errorsyou can't say cas = ias without those informations

Question 60-19 : An aeroplane is flying at fl300 with a tas of 470 kt in standard conditions the mach number is ?

08.

In standard conditions at fl300 temperature is 15°c 30 x 2°c = 45° 1026set 45° in airpseed window in front of 'm kt' indicatorread in the inner scale in front of 470 kt a mach number of 0805

Question 60-20 : During a climb at a constant cas below the tropopause in standard atmosphere ?

The mach number increases and the speed of sound 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 achthe velocity of sound is decreasing as temperature decreases mach number = tas local sound speed

Question 60-21 : A servo assisted altimeter is more accurate than a simple altimeter because the small movements of ?

The capsules are detected by a very sensitive electro magnetic pick off.

Question 60-22 : An aeroplane is flying at fl100 and mach number 076 the indicated total air temperature is 19°cconsidering that the probe recovery coefficient is 096 oat is ?

44°c.

The total temperature can be expressed approximately by the formula tt = ts 1 + 02 kr m² ts the static temperature sat in kelvin tt the total temperature tat in kelvin kr the recovery coefficient m the mach number25415 = ts 1 + 02 kr m² ts = 25415 1 + 02 x 096 x 05776 ts = 25415 111 = 229° k27315 229 = 4415°c

Question 60-23 : Concerning the pitot and static system the position error varies with 1 altimeter setting2 mach number3 angle of attackthe combination that regroups all of the correct statements is ?

2 3.

Cqb15 may 2012this 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'

Question 60-24 : An aeroplane is flying at fl 320 and mach number 079the oat is 53°cconsidering that the probe recovery coefficient is 096 the indicated total air temperature is ?

27°c.

Ecqb03 july 2016the total temperature can be expressed approximately by the formula tt = ts 1 + 02 kr m² ts the static temperature sat in kelvin tt the total temperature tat in kelvin kr the recovery coefficient m the mach numbertt = 220°k 1 + 02 x 096 x 079² tt = 220°k 1 + 012 tt = 246°ktt = 27315 246 = 2675°c

Question 60-25 : Which of these statements is true ?

The probes used for sat measurements have a recovery factor of 075 to 090 while the probes used for tat measurements have a recovery factor of around 100.

Ecqb03 july 2016recovery factor refers to the amount of ram rise that is recoverable by the sensor total head thermometers typically have a recovery factor of 075 to 09 whereas the rosemount temperature probe has a recovery factor of 10 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 02 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 risethe formula's typically used are tat = sat + ram riseortat = sat x 1 + 02 kr m² where kr is the recovery factor and m the mach numberram rise comes into effect at airspeeds greater than m 02in summary sat temperature sensors are not affected by ram rise whereas tat sensors are

Question 60-26 : After takeoff from a contaminated runway that blocked the pitot pressure intake of the left airspeed indicator the right pilot continues the climb at a constant airspeed using the right instrument the left and right airspeed circuits supply power to the left and right airspeed indicators ?

Increased steadily.

Question 60-27 : An aeroplane is in a steady descend the auto throttle maintains a constant mach number if the total temperature remains constant the calibrated airspeed ?

Increases.

Img964

Question 60-28 : In a gyromagnetic compass the direction of the earth's magnetic field is given by the ?

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

Question 60-29 : The magnetic heading can be derived from the true heading by means of a ?

Map showing the isogonal lines.

1425isogonic lines connect positions that have the same variationagonic line a line which joins all points where the value of magnetic variation is zeromagnetic heading is the direction that the aircraft is pointing in relation to magnetic northtrue heading is the direction that the aircraft is pointing in relation to true northsince 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 differto 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 deviationto get the true heading simply take the reading from the magnetic compass and either add an easterly or subtract a westerly magnetic deviation

Question 60-30 : The fields affecting a magnetic compass originate from 1 magnetic masses 2 ferrous metal masses 3 non ferrous metal masses 4 electrical currents the combination regrouping all the correct statements is ?

1 2 4.

Question 60-31 : The input signal of the amplifier of the gyromagnetic compass resetting device originates from the ?

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 zeroselsyn or synchro is an electro mechanical device used for the easy and precise transmission of angular data between two or more remote points

Question 60-32 : In the gyromagnetic compass the heading information from the flux valve is sent to the ?

Error detector.

Question 60-33 : The gyromagnetic compass torque motor ?

Causes the directional gyro unit to precess.

Question 60-34 : A pilot wishes to turn left on to a southerly heading with 20° bank at a latitude of 20° north using a direct reading compass in order to achieve this he must stop the turn on an approximate heading of ?

160°.

In the northern hemisphere as you turn through north you must roll out early onto your required headingif you turn through south you roll out lateuse unos to remember this un = undershoot north os = overshoot souththe 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°

Question 60-35 : A pilot wishes to turn left on to a northerly heading with 10° bank at a latitude of 50° north using a direct reading compass in order to achieve this he must stop the turn on an approximate heading of ?

030°.

In the northern hemisphere as you turn through north you must roll out early onto your required headingif you turn through south you roll out lateuse unos to remember this un = undershoot north os = overshoot souththe 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°

Question 60-36 : A gyromagnetic compass is a system which always consists of 1 a horizontal axis gyro 2 a vertical axis gyro 3 an earth's magnetic field detector 4 an erection mechanism to maintain the gyro axis horizontal 5 a torque motor to make the gyro precess in azimuth the combination regrouping all the ?

1 3 4 5.

Question 60-37 : In a gyromagnetic compass the flux valve feeds the ?

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 gyrothe magnetic detector unit flux valve feeds the error detector with information about the earth's magnetic field

Question 60-38 : The operating principle of the vertical speed indicator vsi is based on the measurement of the rate of change of ?

Static pressure.

Question 60-39 : A pilot wishes to turn right through 90° on to north at rate 2 at latitude of 40 north using a direct reading compass in order to achieve this the turn should be stopped on an indicated heading of approximately ?

330°.

In the northern hemisphere as you turn through north you must roll out early onto your required headingif you turn through south you roll out lateuse unos to remember this un = undershoot north os = overshoot souththe 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

Question 60-40 : An aircraft takes off on a runway with an alignment of 045° the compass is made for the northern hemisphereduring rolling take off the compass indicates ?

A value below 045°.

Accelerationdeceleration 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 occurin 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 disappearslearn this for northern hemisphere ands a cceleration gives apparent turn to n orth d eceleration gives apparent turn to s outh