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Question 230-1 : Before departure outside temperature is 3°c icing conditions is encountered on the ground you ? [ Formation assignment ]

Follow the 'clean aircraft concept'

Pdf676 exemple 330 Follow the 'clean aircraft concept'.

Question 230-2 : What should a pilot do if his/her aircraft is subject to an act of unlawful interference and contact to an ats unit cannot be established ?

Proceed at a level which differs from the cruising levels normally used for ifr flight by 150 m 500 ft in an area where a vertical separation minimum of 300 m 1000 ft is applied

exemple 334 Proceed at a level which differs from the cruising levels normally used for ifr flight by 150 m (500 ft) in an area where a vertical separation minimum of 300 m (1000 ft) is applied.

Question 230-3 : An 'unidentified baggage' is a baggage ?

At an airport with or without a baggage tag which is not picked up by or identified with a passenger

Admin . icao annex 9 facilitations exemple 338 At an airport, with or without a baggage tag, which is not picked up by or identified with a passenger.

Question 230-4 : Just after passing v1 during a take off roll you suddenly hear a fire warning bell and notice the illumination of engine fire warning light your first action is to ?

Establish a safe climb

exemple 342 Establish a safe climb.

Question 230-5 : Define 'frost' ?

A deposit of ice respectively crystallized water vapour having a crystalline appearance generally assuming the form of scales needles or fans

exemple 346 A deposit of ice, respectively crystallized water vapour, having a crystalline appearance, generally assuming the form of scales, needles or fans.

Question 230-6 : If a cabin crew notices a slow decompression of the cabin the first action will be ?

Inform the flight crew

Ecqb04 january 2019 exemple 350 Inform the flight crew.

Question 230-7 : Senior cabin crew member notices traces of smoke in the passenger cabin but can not positively identify its source of origin the aircraft commander is notified and after the relevant abnormal checklist has been completed his/her action will normally be to ?

Divert to the nearest aerodrome

exemple 354 Divert to the nearest aerodrome.

Question 230-8 : The horizontal wind shear ?

Is measured at the same height on different masts placed along runway

exemple 358 Is measured at the same height on different masts placed along runway.

Question 230-9 : Following an engine failure after take off while on a noise abatement departure procedure 1 nadp 1 the pilot should ?

Disregard the noise abatement procedure if necessary

Ecqb04 january 2019 exemple 362 Disregard the noise abatement procedure if necessary.

Question 230-10 : Who is responsible for providing information to passengers and cargo shippers regarding dangerous goods ?

The operator

Icao gives informations to the operators operators give informations to passengers and cargo shippers exemple 366 The operator.

Question 230-11 : According to cs 25 an altitude warning system must alert the crew when the cabin pressure altitude exceeds ?

10000 ft 3000 m

exemple 370 10000 ft (3000 m).

Question 230-12 : You will begin the approach to your destination airport and windshear has been reported at the runway threshold your decision will be to ?

Hold

Admin .windshear will not last for long you should hold 10 to 20 minutes and try to perform the approach .for all landings you are prepared to carry out a missed approach exemple 374 Hold.

Question 230-13 : During heavy turbulence in flight if the flight crew forget to turn on the seatbelt sign the senior cabin crew member ?

Shall suspend all non safety related duties and inform the flight crew

Admin . oro cc 200 senior cabin crew member . . d the senior cabin crew member shall be responsible to the commander for the conduct and coordination of normal and emergency procedures specified in the operations manual including for discontinuing non safety related duties for safety or security purposes exemple 378 Shall suspend all non-safety-related duties and inform the flight crew.

Question 230-14 : For operations with more than one cabin crew member ?

The operator shall nominate one cabin crew member accountable to the pilot in command or the commander

Admin .oro cc 100 number and composition of cabin crew. .for operations with more than one cabin crew member the operator shall nominate one cabin crew member accountable to the pilot in command or the commander exemple 382 The operator shall nominate one cabin crew member accountable to the pilot-in-command or the commander.

Question 230-15 : The reference document you shall use when a piece of equipment on your aeroplane fails during taxy is ?

The operations manual under the heading 'abnormal and emergency procedures'

Admin .if an equipment becomes inoperable while parked you consult the 'mel' and while translating for take off or after landing you must refer to the 'abnormal and emergency procedures' in the qrh quick reference handbook exemple 386 The operations manual under the heading 'abnormal and emergency procedures'.

Question 230-16 : The angle of attack of an aerofoil section is defined as the angle between the ?

Undisturbed airflow and the chord line

Img669 exemple 390 Undisturbed airflow and the chord line.

Question 230-17 : In a stationary subsonic streamline flow pattern if the streamlines converge in this part of the pattern the static pressure i will and the velocity ii will ?

I decrease ii increase

Img1466.static pressure decreases in a venturi and airflow speed increases exemple 394 (i) decrease, (ii) increase.

Question 230-18 : The si units of air density i and force ii are ?

I kg/m3 ii n

The use of units follow the international rules and style conventions click on the following link to open a pdf file of units of measurement in a new tab .pdf678.pdf679 exemple 398 (i) kg/m3, (ii) n

Question 230-19 : The units of wing loading i w / s and ii dynamic pressure q are ?

I n / m² ii n / m²

The use of units follow the international rules and style conventions click on the following link to open a pdf file of units of measurement in a new tab .pdf679 exemple 402 (i) n / m², (ii) n / m².

Question 230-20 : The aeroplane drag in straight and level flight is lowest when the ?

Parasite drag is equal to the induced drag

.total drag is lowest when parasite drag is equal to the induced drag . 1084 exemple 406 Parasite drag is equal to the induced drag.

Question 230-21 : Considering a positive cambered aerofoil the pitch moment when cl=0 is ?

Negative pitch down

.it is because the pressure distribution is producing negative lift at the front and positive lift at the back of the airfoil .remember when cl = 0 a cambered section will have a negative alpha . 2416.other questions you will see on this refer to a symmetrical section it has no pitch and a negative cambered section will pitch nose up exemple 410 Negative (pitch-down).

Question 230-22 : An aeroplane maintains straight and level flight while the ias is doubled the change in lift coefficient will be ?

X 0 25

.in straight and level flight lift does not change as it is only balancing against weight .aircraft is maintaining level flight and therefore lift cannot change .lift = cl 1/2rho v² s rho = density . example with .s = 2 rho = 10 cl = 1 and ias = 100.lift = 1 x 0 5 x 10 x 100 x 100 x 2 = 100000. and now with .s = 2 rho = 10 cl = 1 and ias = 200.lift = 1 x 0 5 x 10 x 200 x 200 x2 = 400000.we can't modify s and rho we can only change lift coefficient cl and in order to maintain lift at 100000 we have to multiply cl by 0 25 exemple 414 X 0.25

Question 230-23 : Which formula or equation describes the relationship between force f acceleration a and mass m ?

F=m a

.force energy brought to bear which tends to cause a motion or change .mass a measure of the amount of material contained in a body .acceleration rate of change of velocity velocity + time or distance + time² exemple 418 F=m.a

Question 230-24 : Static pressure is acts ?

In all directions

Static pressure is atmospheric pressure measured at a point where there is no external disturbance and the flow of air over the surface is perfectly smooth exemple 422 In all directions.

Question 230-25 : Lift is generated when ?

The flow direction of a certain mass of air is changed

.lift is an upward force whose line of action is at right angles to the relative airflow direction and acts on the centre of pressure .lift =.cl x 1/2 rho v² x s.cl = lift coefficient.rho = density.v = tas in m/s .s = surface.if an aircraft is providing a lift force upwards there must be something going downwards to react this would be the change of direction of the airflow exemple 426 The flow direction of a certain mass of air is changed.

Question 230-26 : Consider the steady flow through a stream tube where the velocity of the stream is v an increase in temperature of the flow at a constant value of v will ?

Decrease the mass flow

.the mass flow is .density x area x velocity.area and velocity remain constant the only thing that changes is rho .with a temperature increase the density decreases thus the mass flow decreases through the stream tube exemple 430 Decrease the mass flow.

Question 230-27 : Which one of the following statements about bernoulli's theorem is correct ?

The dynamic pressure increases as static pressure decreases

.pt total pressure.ps static pressure.pd dynamic pressure 1/2 x density x tas² .bernoulli's theorem is .pt = ps + pd.then if pd inscreases ps decreases as pt always remains constant exemple 434 The dynamic pressure increases as static pressure decreases.

Question 230-28 : If in a two dimensional incompressible and subsonic flow the streamlines converge the static pressure in the flow will ?

Decrease

.total pressure pt always remains constant and bernoulli's theorem is pt = ps + pd. ps = static pressure and pd = dynamic pressure .the streamlines converge the speed will increase which increases the dynamic pressure thus static pressure must decrease for the total pressure to remain constant exemple 438 Decrease.

Question 230-29 : Bernoulli's equation can be written as . pt= total pressure ps = static pressure and q=dynamic pressure ?

Pt = ps + q

.pt total pressure.ps static pressure.pd dynamic pressure 1/2 x density x tas² .bernoulli's theorem is .pt = ps + pd exemple 442 Pt = ps + q

Question 230-30 : Which of the following statements about boundary layers is correct ?

The turbulent boundary layer has more kinetic energy than the laminar boundary layer

.the pressure pattern over the wing goes from high at the leading edge to low at the point of maximum camber and then back to high again at the trailing edge so from the point of max camber backwards the airflow is moving from a low pressure to a high pressure region called an adverse pressure gradient the air would not do this unless it was being pushed by some other factor and this factor is the kinetic energy of the moving air the boundary layer has less kinetic energy than the freestream air and gradually slows down when it stops or reverses it breaks away from the surface or separates .as the laminar type of boundary layer has less kinetic energy than the turbulent type it will slow down quicker and break away earlier so the laminar boundary layer has less kinetic energy and breaks away earlier the laminar layer however causes less drag .to try for the highest possible lift at high angles of attack you need to keep the airflow attached as long as possible and this means having a high kinetic energy boundary layer various high lift devices are there simply to re energise a boundary layer that is slowing down never mind the drag it is lift we want at the stall exemple 446 The turbulent boundary layer has more kinetic energy than the laminar boundary layer.

Question 230-31 : On an asymmetrical single curve aerofoil in subsonic airflow at low angle of attack when the angle of attack is increased the centre of pressure will assume a conventional transport aeroplane ?

Move forward

The pressure created by an aerofoil at any point may be represented by a vector at right angles to its surface whose length is proportional to the difference between absolute pressure at the point and the free stream static pressure .all of them can be represented by a single vector acting at a particular point called the centre of pressure . 669.the centre of pressure is a theoretical point on the chord line through which the resultant of all forces the total reaction is said to act .its position is usually around 25% of the way from the leading edge simply because more lift is generated there but it moves steadily forward as the angle of attack is increased until just before the stalling angle when it moves rapidly backwards the centre of pressure's most forward point is just before the stalling angle this is why an aeroplane's nose drops when the wings stall and the centre of pressure moves behind the cg .thus when speed is increased in straight and level flight on a positively cambered aerofoil you have to decrease the angle of attack to keep the the total lift force constant and the point where the resultant of all forces are acting the centre of pressure moves aft exemple 450 Move forward.

Question 230-32 : The cl alpha curve of a positive cambered aerofoil intersects with the vertical axis of the cl alpha graph ?

Above the origin

.cl = coefficient of lift.alpha = angle of attack. 2773.for a positive cambered aerofoil the curve intersects the vertical axis of the graph above the origin because a positive cambered aerofoil produces lift with a zero pitching moment 0° angle of attack exemple 454 Above the origin.

Question 230-33 : The angle of attack of a two dimensional wing section is the angle between ?

The chord line of the aerofoil and the free stream direction

. 680 exemple 458 The chord line of the aerofoil and the free stream direction.

Question 230-34 : The angle between the airflow relative wind and the chord line of an aerofoil is ?

Angle of attack

Img680.'alpha' angle of attack is the angle between the airflow relative wind and the chord line of an aerofoil exemple 462 Angle of attack.

Question 230-35 : The angle between the aeroplane longitudinal axis and the chord line is the ?

Angle of incidence

.aeroplane's angle of incidence the angle between the longitudinal axis and the wing root chord line .the angle of incidence is a fixed value . 681.others important angles .aeroplane's angle of attack the angle between its speed vector and longitudinal axis .aeroplane's pitch angle the angle between its longitudinal axis and the horizontal plane .aeroplane's flight path the angle between its speed vector and the horizontal plane . 682 exemple 466 Angle of incidence.

Question 230-36 : With increasing angle of attack the stagnation point will move i and the point of lowest pressure will move ii respectively i and ii are ?

I down ii forward

. 1576.in red the stagnation point will move down .in blue the point of lowest pressure will move forward

Question 230-37 : The aerodynamic centre of the wing is the point where ?

The pitching moment coefficient does not vary with angle of attack

.when upper and lower surface lift act through different points the result is a pitching moment .the aerodynamic centre of the wing is the fixed point on the chord line about which no change in pitching moment is felt when the angle of attack varies .this is not the center of pressure which is a theoretical point on the chord line through which the resultant of all forces the total reaction is said to act the center of pressure moves forward when the angle of attack is increased exemple 474 The pitching moment coefficient does not vary with angle of attack.

Question 230-38 : On a swept wing aeroplane at low airspeed the pitch up phenomenon ?

Is caused by wingtip stall

.flying at low speed means flying at high angle of attack there is a tendency for the swept wing to develop a strong spanwise flow towards the wingtip when the wing is at high angles of attack . /com en/com080 27 jpg.stall occurs at the wingtips first resulting in a shift of the center of lift of the wing in a forward direction relative to the center of gravity of the airplane causing the nose to pitch up exemple 478 Is caused by wingtip stall.

Question 230-39 : The lift of an aeroplane of weight w in a constant linear climb with a climb angle gamma is approximately ?

W cos gamma

Lift = weight x cos climb angle. 1526 exemple 482 W.cos.gamma

Question 230-40 : Which one of the following statements about the lift to drag ratio in straight and level flight is correct ?

At the highest value of the lift/drag ratio the total drag is lowest

.lift/drag ratio is maximum at the speed for minimum total drag exemple 486 At the highest value of the lift/drag ratio the total drag is lowest.


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