Question 68-1 : In a yaw damper system sensing of a disturbance in yaw is usually by ? [ Result topography ]

Question 68-2 : The yaw damper system acts on ?

The rudder without moving the rudder pedals.

Question 68-3 : The main inputs to the flight envelope protection system are 1 gpws signals2 acas signals3 angle of attack4 bank anglethe combination that regroups all of the correct statements is ?

3 4.

Question 68-4 : The flight envelope protection system prevents the aircraft from exceeding the limits of the following parameters among others 1 n12 angle of attack3 speed4 pitch attitude5 flight levelthe combination that regroups all of the correct statements is ?

Question 68-5 : The flight envelope protection function s consist s in 1 alerting the flight crew in case of dangerous proximity with the ground 2 avoiding midair collision 3 preventing the aircraft from exceeding some aerodynamic limits the combination that regroups all of the correct statements is ?

3.

Question 68-6 : When the yaw damper system sends motion orders to the rudder ?

Question 68-7 : An aircraft is in a steady right turn with not enough right rudder slipping turn the yaw damper system ?

Is not designed to provide a balanced turn.

The yaw damper is fitted to correct for dutch roll

Question 68-8 : An aircraft is in a steady left turn with too much left rudder skidding turn the yaw damper system ?

Is not designed to provide a balanced turn.

Question 68-9 : The commands sent out by the yaw damper computer ?

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

Question 68-10 : The speed exceeds vmommo and according to the type of aeroplane the overspeed protection function can 1 extend the speed brakes2 reduce thrust to idle3 inhibit the pitch trim orders in the nose down directionthe combination that regroups all of the correct statements is ?

3.

Cqb15 august 2012the stall protection function and the overspeed protection function apply to both mechanicalconventionnal and fly by wire control systems but other functions eg 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 writtenthis is a protection function when do we want to descend at vmommo limits when we have a loss of cabin pressurizationthe 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

Question 68-11 : The yaw damper system sends a motion order to the rudder if the yawing rate of the aircraft ?

Is not constant.

Question 68-12 : The flight envelope protection system prevents the aircraft from exceeding the limits of the following parameters among others 1 cabin altitude 2 bank angle 3 angle of attack 4 speed 5 pitch attitude the combination that regroups all of the correct statements is ?

2 3 4 5.

Question 68-13 : The yaw damper system is operative ?

During manual or automatic flight.

Question 68-14 : The flight envelope protection function s consist s in 1 automatically performing an evasion manoeuvre if necessary2 preventing the aircraft from exceeding the limits for specific flight parameters3 alerting the flight crew in case of dangerous proximity with a threatening traffic4 preventing ?

2.

Question 68-15 : The flight envelope protection fep can include 1 stall protection2 the overspeed protection3 the maximum vertical speed protectionthe combination that regroups all of the correct statements is ?

1 2.

The stall protection function and the overspeed protection function of the flight envelope protection fep apply to both mechanicalconventionnal and fly by wire control systems but other functions eg pitch or bank limitation can only apply to fly by wire control systems

Question 68-16 : At high angles of attack and according to the type of aeroplane the stall protection system can 1 inhibit the pitch trim orders in the nose up direction2 retract the speed brakes3 increase thrustthe combination that regroups all of the correct statements is ?

1 3.

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

Question 68-17 : The automatic power control system autothrottle of a transport airplane has the following mode s 1 capture and holding of speeds 2 capture and holding of mach number 3 capture and holding of flight angle of attack 4 capture and holding of n1 or epr engine power ratio 5 capture and holding of ?

1 2 4.

Question 68-18 : An airplane is cruising at fl 220 the auto throttle maintains a constant cas if the oat decreases the mach number ?

Remains constant.

Oat outside air temperatureif temperature changes the tas will change but cas and mach number will remain constantcas = 12 rho tas² the auto throttle maintains a constant cas thus if oat decreases = rho will increasein order to maintains a constant cas tas will decrease cas will not changethe decrease in temperature will also decrease the local speed of sound mach formula is m = taslsstas must decrease if oat decreases to maintain a constant caslss decreases if oat decreasesthe mach number remains constant

Question 68-19 : An aeroplane is in steady descent the auto throttle maintains a constant calibrated airspeed if the total temperature remains constant the mach number ?

Decreases.

For those questions use the very simple 'ertm' diagram 1037the 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 achcas = 12 rho v²density will increase during descent and in order to maintain constant cas only v tas can be reducedmach = tas local speed of soundlocal 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

Question 68-20 : An aeroplane is in steady cruise at flight level 270 the auto throttle maintains a constant calibrated airspeed if the static air temperature increases the mach number ?

Remains constant.

If oat increases density decreases with higher temperature air is expanding density is decreased 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 temperatureformula lss = 39 x square root of oat+273 thus if tas increases and lss increases the mach number remains constant

Question 68-21 : An aeroplane is in steady climb the auto throttle maintains a constant calibrated airspeed if the total temperature remains constant the mach number ?

Increases.

For those questions use the very simple 'ertm' diagram 1037cas = 12 rho tas²rho is decreasing when altitude increases to maintain a constant cas tas must increasesmach = tas local speed of soundlocal speed of sound varies only with temperature and the question states 'total temperature remains constant' thus lss remains constantsince tas increases mach number will increase

Question 68-22 : An aircraft is equipped with an autopilot and an auto throttle when the altitude hold mode alt hold is active ?

The indicated airspeed ias is maintained constant by the auto throttle system.

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 settingobviously 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 oncewhat 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

Question 68-23 : During the ground run take off phase the auto throttles allow to ?

Hold n1.

During take off autothrottle will hold constant thrust and allow the aircraft to accelerate

Question 68-24 : The auto throttles enables to hold 1 a true airspeed 2 a mach number 3 an indicated airspeed 4 a n1 thrust the combination regrouping all the correct statements is ?

2 3 4.

There are two parameters that an at 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 marginsfor example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed at will maintain a speed closest to the target speed that is within the range of safe speedsin thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff at maintains a constant takeoff power until takeoff mode is finishedduring climb at maintains a constant climb power in descent at retards the throttle to idle position and so on when at is working in thrust mode speed is controlled by pitch or the control column and not protected by at

Question 68-25 : The purpose of auto throttle is ?

To maintain constant engine power or aeroplane speed.

Question 68-26 : The auto throttle system of a transport aeroplane has the following mode s 1 capture and holding of ias2 capture and holding of mach number3 capture and holding of an altitude4 capture and holding of n1 or epr5 capture and holding of flight paths the combination that regroups all of the correct ?

1 2 4.

Question 68-27 : The auto throttle 1 can capture and maintain the n1 rpm 2 can capture and maintain the n2 rpm 3 can capture and maintain an ias 4 is always engaged automatically at the same time as the autopilot the combination that regroups all of the correct statements is ?

1 3.

Question 68-28 : When cruising the autothrottle system can be engaged in the following mode s holding of constant 1 tas2 ias 3 mach numberthe combination that regroups all of the correct statements is ?

2 3.

Question 68-29 : The autothrottle system ?

Can be used for take off.

Question 68-30 : During a manual ils final approach the auto throttle ?

Can be operated in the speed mode holding of ias .

Question 68-31 : During an automatic ils final approach the auto throttle ?

Can be operated in the speed mode holding of ias .

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

Question 68-32 : During a climb with the autopilot engaged in the vs mode holding of vertical speed the auto throttle ?

Can be operated in the speed mode holding of ias .

The vs mode commands pitch to hold selected vertical speed and engages at in speed mode to hold selected airspeed on the boeing 737 speed mode engages automatically when vs engages

Question 68-33 : Considering a modern thrust computer during a steady climb ?

N1 is automatically adjusted as aircraft climbs.

Question 68-34 : When an auto throttle system athr is engaged in speed mode athr is ?

Active.

Speed mode autothrottle holds speed in iasmach display or a performance or limit speed

Question 68-35 : When an automatic thrust control system is in the thrust mode ?

Thrust is set to a computed thrust according to a performance database.

There are two parameters that an at 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 marginsfor example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed at will maintain a speed closest to the target speed that is within the range of safe speedsin thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff at maintains a constant takeoff power until takeoff mode is finishedduring climb at maintains a constant climb power in descent at retards the throttle to idle position and so on when at is working in thrust mode speed is controlled by pitch or the control column and not protected by at

Question 68-36 : An automatic thrust control system can be 1 armed2 active3 disconnectedthe combination regrouping all the correct statements is ?

1 2 3.

Revised ecqb03 july 2016

Question 68-37 : When an automatic thrust control system is in the speed mode ?

It maintains the selected airspeed.

Revised ecqb03 july 2016speed mode autothrottle holds speed in iasmach display or a performance or limit speedthere are two parameters that an at 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 marginsfor example if the pilot selects a target speed which is slower than stall speed or a speed faster than maximum speed at will maintain a speed closest to the target speed that is within the range of safe speedsin thrust mode the engine is maintained at a fixed power setting n1 according to the different flight phases for example during takeoff at maintains a constant takeoff power until takeoff mode is finishedduring climb at maintains a constant climb power in descent at retards the throttle to idle position and so on when at is working in thrust mode speed is controlled by pitch or the control column and not protected by at

Question 68-38 : Landing shall be considered as having been carried out automatically when the autopilot and the auto throttle of an aircraft are disengaged by flight crew ?

During ground roll.

Question 68-39 : A landing is performed automatically when the autopilot and auto throttle ensure good performance from the final approach ?

During the landing roll and sometimes until the aircraft comes to a complete stop.

Question 68-40 : The cpdlc messages may concerne 1 route modifications2 speed changes3 voice contact request 4 emergency messagesthe combination regrouping all the correct statements is ?

1 2 3 4.

Cpdlc controller pilot data link communications