Un compte Premium offert sur le site FCL.055 ! Rendez-vous sur www.fcl055-exam.fr puis créez un compte avec le même email que celui...   [Lire la suite]


The mach trim system allows to ? [ Result topography ]

Question 68-1 : Increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number compensates the pitch up tendency at high mach numbers ensures optimum c g location by transferring fuel into the horizontal stabilizer adjust the horizontal stabilizer position during a high speed stall

.at high speed the center of pressure will move aft from its low transonic position at about 25% of the chord to a value at 45% of the chord this will result in a tendency to pitch down .the mach trim system will prevent this phenomenon called 'tuck under' .the mach trim compensates for backing of the aerodynamic centre at high mach numbers by moving the elevator nose up but only above a predetermined mach number mach trim is automatically accomplished above mach 0 6 by adjusting the elevators with respect to the stabilizer as speed increases exemple 168 Increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number.Increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number.

The yaw damper affects ?

Question 68-2 : Rudder only all control surfaces in a coordinated way ailerons and rudder ailerons only

exemple 172 Rudder only.Rudder only.

An aircraft is turning right with too much bank slipping turn the yaw damper ?

Question 68-3 : Is not designed to provide a balanced turn acts on the left rudder pedal to provide a balanced turn acts only in case of skidding turns turn with not enough bank acts on the right rudder pedal to provide a balanced turn

exemple 176 Is not designed to provide a balanced turn.Is not designed to provide a balanced turn.

In a yaw damper system sensing of a disturbance in yaw is usually by ?

Question 68-4 : A rate gyro or an accelerometer measuring the rudder angular movement measuring the ailerons angular movement measuring the roll rate

The yaw damper system acts on ?

Question 68-5 : The rudder without moving the rudder pedals the rudder and simultaneously moves the rudder pedals the ailerons without moving the roll trim the ailerons and simultaneously moves the roll trim

exemple 184 The rudder without moving the rudder pedals.The rudder without moving the rudder pedals.

The main inputs to the flight envelope protection system are .1 gpws signals.2 ?

Question 68-6 : 3 4 1 2 3 4 1 2 2 3 4

The flight envelope protection system prevents the aircraft from exceeding the ?

Question 68-7 : 2 3 4 1 2 3 4 5 2 2 3 4 5

Admin .flight envelope protection is a human machine interface extension of an aircraft's control system that prevents the pilot of an aircraft from making control commands that would force the aircraft to exceed its structural and aerodynamic operating limits .n1 is monitored by the electronic engine control eec the eec provides n1 and n2 redline overspeed protection and limits the maximum thrust .flight level is captured and maintained by the autopilot and protection is given by the altitude warning alert module .the flight envelope protection system in case of an imminent stall will reduce the pitch attitude to decrease the angle of attack in order to regain speed .the flight envelope protection system will also prevent an excessive climbing attitude which will lead to a stall or an excessive descending attitude which will lead to an overspeed condition .the stall protection function and the overspeed protection function apply to both mechanical/conventionnal and fly by wire control systems but other functions e g pitch or bank limitation can only apply to fly by wire control systems exemple 192 2, 3, 4.2, 3, 4.

The flight envelope protection function s consist s in . 1 alerting the flight ?

Question 68-8 : 3 1 1 3 1 2 3

exemple 196 3.3.

When the yaw damper system sends motion orders to the rudder ?

Question 68-9 : No feedback is provided on the rudder pedals a feedback is provided on the rudder pedals only a feedback is provided on the rudder pedals and the roll trim a feedback is provided on the roll trim only

exemple 200 No feedback is provided on the rudder pedals.No feedback is provided on the rudder pedals.

An aircraft is in a steady right turn with not enough right rudder slipping ?

Question 68-10 : Is not designed to provide a balanced turn acts on the left rudder pedal to provide a balanced turn acts on the right rudder pedal to provide a balanced turn acts only in case of skidding turns turn with not enough bank

.the yaw damper is fitted to correct for dutch roll exemple 204 Is not designed to provide a balanced turn.Is not designed to provide a balanced turn.

An aircraft is in a steady left turn with too much left rudder skidding turn ?

Question 68-11 : Is not designed to provide a balanced turn acts on the left rudder pedal to provide a balanced turn acts on the right rudder pedal to provide a balanced turn acts only in case of slipping turns turn with too much bank

exemple 208 Is not designed to provide a balanced turn.Is not designed to provide a balanced turn.

The commands sent out by the yaw damper computer ?

Question 68-12 : Are added to or substracted from the rudder deflection orders sent out by the pilot or the autopilot are inhibited when the pilot acts on the rudder pedals are inhibited when the autopilot is engaged inhibit the rudder deflection orders sent out by the pilot or the autopilot

exemple 212 Are added to or substracted from the rudder deflection orders sent out by the pilot or the autopilot.Are added to or substracted from the rudder deflection orders sent out by the pilot or the autopilot.

The speed exceeds vmo/mmo and according to the type of aeroplane the overspeed ?

Question 68-13 : 3 2 1 2 3 1 2

Cqb15 august 2012..the stall protection function and the overspeed protection function apply to both mechanical/conventionnal and fly by wire control systems but other functions e g pitch or bank limitation can only apply to fly by wire control systems . ebbr1000 .i asked the question to a instructor and pilot for his the good reaction is reduce thrust to idle to decrease the speed in the answer if we inhibit the trim in the nose down position the speed will increase maybe is not good written ..this is a protection function when do we want to descend at vmo/mmo limits when we have a loss of cabin pressurization .the protection can not reduce thrust without the pilots decision in some case you need to maintain a certain amount of thrust to run correctly the anti icing system which picks up some air from the compressor .this system will invite the pilot to take decision such as extend the speed brakes decrease thrust or reduce the rate of descent exemple 216 3.3.

The yaw damper system sends a motion order to the rudder if the yawing rate of ?

Question 68-14 : Is not constant is constant is > 0 only is > 1 only

exemple 220 Is not constant.Is not constant.

The flight envelope protection system prevents the aircraft from exceeding the ?

Question 68-15 : 2 3 4 5 1 2 3 4 5 2 5 1 2 4

exemple 224 2, 3, 4, 5.2, 3, 4, 5.

The yaw damper system is operative ?

Question 68-16 : During manual or automatic flight only if the flight director is engaged only if the autopilot is engaged only when flying manually

exemple 228 During manual or automatic flight.During manual or automatic flight.

The flight envelope protection function s consist s in .1 automatically ?

Question 68-17 : 2 1 2 1 3 2 3 4

exemple 232 22

The flight envelope protection fep can include .1 stall protection.2 the ?

Question 68-18 : 1 2 1 2 3 2 3 1

Admin .the stall protection function and the overspeed protection function of the flight envelope protection fep apply to both mechanical/conventionnal and fly by wire control systems but other functions e g pitch or bank limitation can only apply to fly by wire control systems exemple 236 1, 2.1, 2.

At high angles of attack and according to the type of aeroplane the stall ?

Question 68-19 : 1 3 1 2 3 1 2 3

Cqb15 august 2012..a stall protection system is a part of the flight envelope protection fep of an aircraft .on airbus you have the 'alpha floor' protection which is an auto throttle mode that selects full thrust to prevent the aircraft from stalling .the max angle of attack is alpha max and in normal law normal flight mode this can not be exceded exemple 240 1, 3.1, 3.

The automatic power control system autothrottle of a transport airplane has the ?

Question 68-20 : 1 2 4 1 2 3 5 2 4 1 4 5

exemple 244 1, 2, 41, 2, 4

An airplane is cruising at fl 220 the auto throttle maintains a constant cas if ?

Question 68-21 : Remains constant increases decreases decreases if oat is lower than standard temperature increases in the opposite case

Admin .oat outside air temperature .if temperature changes the tas will change but cas and mach number will remain constant .cas = 1/2 rho tas². the auto throttle maintains a constant cas thus if oat decreases = 'rho' will increase .in order to maintains a constant cas tas will decrease cas will not change .the decrease in temperature will also decrease the local speed of sound mach formula is .m = tas/lss.tas must decrease if oat decreases to maintain a constant cas .lss decreases if oat decreases .the mach number remains constant exemple 248 Remains constant.Remains constant.

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

Question 68-22 : Decreases increases if the static temperature is lower than the standard temperature decreases if higher increases remains constant

Admin .for those questions use the very simple 'ertm' diagram . 1037.the cas line is vertical because the question states descent constant calibrated airspeed . 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 .mach = tas / local speed of sound.local speed of sound varies only with temperature and the question states total temperature remains constant thus if tas decreases and lss remains constant the mach number decreases exemple 252 Decreases.Decreases.

An aeroplane is in steady cruise at flight level 270 the auto throttle ?

Question 68-23 : Remains constant decreases if the outside temperature is higher than the standard temperature increases if lower decreases increases

If oat increases density decreases with higher temperature air is expanding density is decreased .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 exemple 256 Remains constant.Remains constant.

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

Question 68-24 : Increases decreases decreases if the static temperature is lower than the standard temperature remains constant

Admin .for those questions use the very simple 'ertm' diagram . 1037.cas = 1/2 rho tas².rho is decreasing when altitude increases to maintain a constant cas tas must increases .mach = tas / local speed of sound.local speed of sound varies only with temperature and the question states 'total temperature remains constant' thus lss remains constant .since tas increases mach number will increase exemple 260 Increases.Increases.

An aircraft is equipped with an autopilot and an auto throttle when the ?

Question 68-25 : The indicated airspeed ias is maintained constant by the auto throttle system the true airspeed tas is maintained constant by the autopilot by means of elevator the true airspeed tas is maintained constant by the auto throttle system the indicated airspeed ias is maintained constant by the autopilot by means of elevator

.basically the auto throttle will maintain speed in most cases but in a climb or the take off the auto throttle might be asked to maintain n1 or an epr but the usual situation in the cruise where we are likey to have alt hold engaged is that the altitude will be held by the pitch channel and speed maintained by the auto throttle setting .obviously maintaining altitude and airspeed with just the pitch channel is not an option one would have to have auto throttle to be able to do two things at once .what the question is trying to get over is that unlike straight and level flight of a light aircraft power is speed and pitch is altitude exemple 264 The indicated airspeed (ias) is maintained constant by the auto-throttle system.The indicated airspeed (ias) is maintained constant by the auto-throttle system.

During the ground run take off phase the auto throttles allow to ?

Question 68-26 : Hold n1 hold ias maintain v2 under 1 500 ft hold and maintain the mach number

During take off autothrottle will hold constant thrust and allow the aircraft to accelerate exemple 268 Hold n1.Hold n1.

The auto throttles enables to hold .1 a true airspeed. 2 a mach number. 3 an ?

Question 68-27 : 2 3 4 1 2 3 4 1 2 3 1 2 4

.there are two parameters that an a/t autothrottle can maintain or try to attain speed and thrust .in speed mode the throttle is positioned to attain a set target speed tas or mach this mode controls aircraft speed within safe operating margins .for example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed a/t will maintain a speed closest to the target speed that is within the range of safe speeds .in thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff a/t maintains a constant takeoff power until takeoff mode is finished .during climb a/t maintains a constant climb power in descent a/t retards the throttle to idle position and so on when a/t is working in thrust mode speed is controlled by pitch or the control column and not protected by a/t exemple 272 2, 3, 4.2, 3, 4.

The purpose of auto throttle is ?

Question 68-28 : To maintain constant engine power or aeroplane speed to automatically shut down an engine if it is at too high temperature to deactivate manual throttles and transfer engine control to auto pilot to synchronize engines to avoid 'yawing'

exemple 276 To maintain constant engine power or aeroplane speed.To maintain constant engine power or aeroplane speed.

The auto throttle system of a transport aeroplane has the following mode s .1 ?

Question 68-29 : 1 2 4 1 2 3 5 2 4 1 4 5

exemple 280 1, 2, 4.1, 2, 4.

The auto throttle . 1 can capture and maintain the n1 rpm. 2 can capture and ?

Question 68-30 : 1 3 2 3 1 4 1 3 4

exemple 284 1, 3.1, 3.

When cruising the autothrottle system can be engaged in the following mode s ?

Question 68-31 : 2 3 2 1 2 1 2 3

exemple 288 2, 3.2, 3.

The autothrottle system ?

Question 68-32 : Can be used for take off can be engaged in the tas mode holding of constant tas during a final approach can be engaged in the gs mode holding of constant ground speed during a final approach is automatically disconnected when the aircraft is on the ground

exemple 292 Can be used for take-off.Can be used for take-off.

During a manual ils final approach the auto throttle ?

Question 68-33 : Can be operated in the speed mode holding of ias can be operated in the n1 epr mode holding of n1 or epr can not be engaged because autopilot is not engaged is not available

exemple 296 Can be operated in the speed mode (holding of ias).Can be operated in the speed mode (holding of ias).

During an automatic ils final approach the auto throttle ?

Question 68-34 : Can be operated in the speed mode holding of ias can be operated in the n1 / epr mode holding of n1 or epr can be operated in the speed holding of ias or n1 holding of n1 modes is not available

Admin .your approach speed must be stabilized during an automatic ils final approach speed is maintained by the speed mode you select a speed on the mcp mode control panel and you push the spd button .you are not looking for a specific thrust during the approach exemple 300 Can be operated in the speed mode (holding of ias).Can be operated in the speed mode (holding of ias).

During a climb with the autopilot engaged in the v/s mode holding of vertical ?

Question 68-35 : Can be operated in the speed mode holding of ias can be operated in the n1 / epr mode holding of n1 or epr can be operated in the speed holding of ias or n1 holding of n1 modes is not available

Admin .the v/s mode commands pitch to hold selected vertical speed and engages a/t in speed mode to hold selected airspeed on the boeing 737 'speed mode' engages automatically when v/s engages exemple 304 Can be operated in the speed mode (holding of ias).Can be operated in the speed mode (holding of ias).

Considering a modern thrust computer during a steady climb ?

Question 68-36 : N1 is automatically adjusted as aircraft climbs n1 is automatically adjusted as aircraft climbs and n2 remains constant n1 and n2 remain constant n2 is automatically adjusted as aircraft climbs and n1 remains constant

exemple 308 N1 is automatically adjusted as aircraft climbs.N1 is automatically adjusted as aircraft climbs.

When an auto throttle system a/thr is engaged in speed mode a/thr is ?

Question 68-37 : Active armed disarmed disconnected

Admin .speed mode autothrottle holds speed in ias/mach display or a performance or limit speed exemple 312 Active.Active.

When an automatic thrust control system is in the thrust mode ?

Question 68-38 : Thrust is set to a computed thrust according to a performance database thrust is adjusted to maintain a selected speed auto throttle or auto thrust is disconnected thrust is adjusted to maintain a selected vertical speed

Admin .there are two parameters that an a/t autothrottle can maintain or try to attain speed and thrust .in speed mode the throttle is positioned to attain a set target speed tas or mach this mode controls aircraft speed within safe operating margins .for example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed a/t will maintain a speed closest to the target speed that is within the range of safe speeds .in thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff a/t maintains a constant takeoff power until takeoff mode is finished .during climb a/t maintains a constant climb power in descent a/t retards the throttle to idle position and so on when a/t is working in thrust mode speed is controlled by pitch or the control column and not protected by a/t exemple 316 Thrust is set to a computed thrust according to a performance database.Thrust is set to a computed thrust according to a performance database.

An automatic thrust control system can be .1 armed.2 active.3 ?

Question 68-39 : 1 2 3 1 3 1 3 1 2

Revised ecqb03 july 2016 exemple 320 1, 2, 3.1, 2, 3.

When an automatic thrust control system is in the speed mode ?

Question 68-40 : It maintains the selected airspeed it maintains the selected vertical speed thrust is constant and the autopilot adjusts the pitch to maintain the selected airspeed thrust is constant and the pilot manually adjusts the pitch to maintain the selected airspeed

Revised ecqb03 july 2016 ..speed mode autothrottle holds speed in ias/mach display or a performance or limit speed .there are two parameters that an a/t autothrottle can maintain or try to attain speed and thrust .in speed mode the throttle is positioned to attain a set target speed tas or mach this mode controls aircraft speed within safe operating margins .for example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed a/t will maintain a speed closest to the target speed that is within the range of safe speeds .in thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff a/t maintains a constant takeoff power until takeoff mode is finished .during climb a/t maintains a constant climb power in descent a/t retards the throttle to idle position and so on when a/t is working in thrust mode speed is controlled by pitch or the control column and not protected by a/t exemple 324 It maintains the selected airspeed.It maintains the selected airspeed.

~

Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

2679 Free Training Exam