Adult > Manual : The flight director command bars provide the pilot with corrections to apply to ?

Question 53-1 : Pitch and/or roll attitude pitch attitude only roll attitude only pitch and/or roll attitude and yaw

exemple 153 pitch and/or roll attitude. — pitch and/or roll attitude.

In an autopilot system the functions consisting in controlling the path of the ?

Question 53-2 : Guidance functions stability functions attitude functions inner loop functions

exemple 157 guidance functions. — .the basic function of an autopilot is stabilisation the stabilisation of the aircraft around its centre of gravity .basic function is achieved by the inner loop systems .the advanced function is 'guidance' monitoring the movements of the centre of gravity in the three dimensions of space .outer loop systems offer the guidance facilities altitude hold heading hold vnav lnav .outer loops act from an external position on the inner loop and 'fool' the inner loop into manoeuvrig the aircraft into achieving its aim guidance functions.

In an autopilot system the function consisting in controlling the movements ?

Question 53-3 : Inner loop systems synchronization system flight management system fms outer loop systems

exemple 161 inner loop systems. — The basic function of an autopilot is stabilisation the stabilisation of the aircraft around its centre of gravity .basic function is achieved by the inner loop systems .the advanced function is 'guidance' monitoring the movements of the centre of gravity in the three dimensions of space .outer loop systems offer the guidance facilities altitude hold heading hold vnav lnav .outer loops act from an external position on the inner loop and 'fool' the inner loop into manoeuvrig the aircraft into achieving its aim inner loop systems.

A flight control system is fail operational if in the event of a failure ?

Question 53-4 : The approach flare and landing can be completed automatically the approach only can be completed automatically the landing is not completed automatically there is no significant out of trim condition or deviation of flight path or attitude but the landing is not completed automatically

exemple 165 the approach, flare and landing can be completed automatically. — the approach, flare and landing can be completed automatically.

In an autopilot system ?

Question 53-5 : The inner loops provide the stability functions and the outer loops provide the guidance functions the outer loops provide the stability functions and the inner loops provide the guidance functions the outer loops provide the stability and the guidance functions the outer loops provide the stability functions only

exemple 169 the inner loops provide the stability functions and the outer loops provide the guidance functions. — .the basic function of an autopilot is stabilisation the stabilisation of the aircraft around its centre of gravity .basic function is achieved by the inner loop systems .the advanced function is 'guidance' monitoring the movements of the centre of gravity in the three dimensions of space .outer loop systems offer the guidance facilities altitude hold heading hold vnav lnav .outer loops act from an external position on the inner loop and 'fool' the inner loop into manoeuvrig the aircraft into achieving its aim the inner loops provide the stability functions and the outer loops provide the guidance functions.

During a final approach the flight director is engaged in the g/s mode holding ?

Question 53-6 : The pitch attitude must be increased the pitch attitude must be reduced the aircraft is above the glide slope the aircraft is below the glide slope

exemple 173 the pitch attitude must be increased. — .example with a crosspointer aircraft symbol .this type of display uses the conventional vertical and horizontal indicators to show the commands just as when flying an ils approach if the 'needle' goes up the pilot raises the nose of the aircraft until the 'miniature airplane' on the attitude indicator rests on top of the horizontal 'needle' if the 'needle' goes left or right the pilot turns the aircraft until the 'miniature airplane' on the attitude indicator rests on top of the vertical 'needle'. 1027.the pilot must pitch up until the horizontal cue centers on the attitude indicator .it does not mean that the aircraft is below the glidepath the flight director gives a tendency we may be on the glidepath but the flight director computer detects that if we don't increase the pitch attitude we are going to pass below the pitch attitude must be increased.

In order to know in which mode the auto throttles are engaged the crew will ?

Question 53-7 : 4 2 4 1 3 3

On a flight mode annunciator fma the pilot can monitor .1 the engaged and ?

Question 53-8 : 1 2 1 2 3 2 3 1 3

Cqb15 may 2012..fma is located on the pfd primary flight display a fma shows the engaged and armed modes respectively in white and green colors .automatic landing capacity will be shown by the word 'flare' boeing or 'retard' airbus on the fma and if automatic capacity is not available you will have single ch instead of cmd while established on the ils approach .acas/tcas mode is displayed on the navigation display not on the fma. 967..you can see on the left of the nd 'tfc' in blue acas/tcas traffic information ra and ta

When performing an automatic landing some additional operational limitations ?

Question 53-9 : 1 1 2 2 3 1 2 3

exemple 185 1. — Cqb15 may 2012.. sudaviation03 .can not the runway conditions apply in the automatic landing conditions i thought that a wet runway or a contaminated runway could prevent the aircraft from performing an auto landing .thanks for your explanations..no the autopilot can not decided to perform automatically a go around .the use of the autopilot automatic landing function is decided by the pilots during cruise or descent there is no runway operational limitations since the approach flare and landing are completed automatically the autopilot can fly the aircraft through specified wind limitations due to limited autopilot speed and actuator reactions .after touch down the plane will reduce speed automatically if you have selected the autobrake function and spoilers will deployed if you also have selected this option before the landing .reverse thrust is used by the pilot if necessary .a pilot can decided not to land on a wet flooded or contaminated runway but this is not due to a limitation from the autopilot 1.

Autopilot engagement status can be checked on the ?

Question 53-10 : Fma control panel and the flight mode annunciator/indicator control panel mcdu

Cqb15 may 2012...the selected mode can be checked on the autopilot control panel but the actual engagement status can only be checked at the fma flight mode annunciator

According to cs25 the definition of the control wheel steering mode cws ?

Question 53-11 : Automatic pilot by movement of the normal control wheel' flight director by movement of the alternate control wheel' automatic pilot by movement of the alternate control wheel' flight director by movement of the normal control wheel'

exemple 193 ... automatic pilot by movement of the normal control wheel'. — .control wheel steering cws .a flight guidance system fgs function which when engaged enables the pilot/first officer to manually fly the aeroplane by positioning the flight control surfaces using the autopilot servos the positions of the flight deck controls e g control column control wheel are determined by the fgs which converts them into autopilot servo commands the autopilot servos in turn drive the appropriate flight control surfaces ... automatic pilot by movement of the normal control wheel'.

On a flight mode annunciator fma the pilot can check .1 the flight director ?

Question 53-12 : 1 3 1 2 3 1 2

exemple 197 1, 3. — Cqb15 august 2012..the fma provides . afcs lateral and vertical modes. auto throttle modes. fd selection ap engagement and automatic landing capacity. failure and alert messages 1, 3.

The purpose of the flight mode annunciator fma is to ?

Question 53-13 : Check and confirm in which modes the automatic flight control systems are armed and/or engaged visually announce any acas alarm visually announce any egpws alarm check and confirm the aeroplane configuration

exemple 201 check and confirm in which modes the automatic flight control systems are armed and/or engaged. — Cqb15 august 2012..the flight mode annunciator fma which is usually located just above the primary flight display pfd shows the status of the autothrust vertical and lateral modes of the auto pilot and flight director approach capabilities and the engagement status of the autopilot ap flight director fd and autothrust a/thr check and confirm in which modes the automatic flight control systems are armed and/or engaged.

The flight mode annunciator fma is displayed on the ?

Question 53-14 : Pfd nd mcdu control panel

exemple 205 pfd. — Ecqb03 july 2016..fma is located on the pfd primary flight display a fma shows the engaged and armed modes respectively in white and green colors . 967 pfd.

The purpose of an automatic landing system is to ?

Question 53-15 : Make the landing possible in poor weather conditions permit the pilot to fly and land the aircraft in poor weather conditions avoid go around decide if the landing is possible or not

exemple 209 make the landing possible in poor weather conditions. — Ecqb03 july 2016 make the landing possible in poor weather conditions.

Following an automatic landing with the roll out mode engaged the autopilot ?

Question 53-16 : Controls the rudder and nose wheel steering to keep the aeroplane on the localiser centreline allows the pilot to control the rudder and nose wheel steering to keep the aeroplane on the localiser centreline controls the rudder to keep the aeroplane on the localiser centreline controls the nose wheel steering to keep the aeroplane on the localiser centreline

exemple 213 controls the rudder and nose wheel steering to keep the aeroplane on the localiser centreline. — Ecqb03 july 2016..'roll out' mode controls the aircraft to maintain the runway centreline on touchdown from a full autoland using both rudder and nose wheel steering controls the rudder and nose wheel steering to keep the aeroplane on the localiser centreline.

Fans a units utilize the following for data transmissions ?

Question 53-17 : Satellite based acars systems vhf data link systems fixed dedicated ground stations navstar/gps satellites

exemple 217 satellite-based acars systems. — Ecqb03 august 2016..future air navigation systems fans a uses the acars network satellite-based acars systems.

The 'fans concept' is ?

Question 53-18 : Different systems to improve the handling and transfer of information extend surveillance and improve navigational accuracy a system that replaces voice communications with atc an upgraded rnav approach system different systems to replace satellite navigation systems

exemple 221 different systems to improve the handling and transfer of information, extend surveillance and improve navigational accuracy. — Ecqb03 august 2016 different systems to improve the handling and transfer of information, extend surveillance and improve navigational accuracy.

Which one of the following statements is true with regard to the operation of a ?

Question 53-19 : It only operates above a pre determined mach number it operates to counteract the larger than normal forward movements of the wing centre of pressure at high subsonic airspeeds it only operates when the autopilot is engaged it operates over the full aircraft speed range

exemple 225 it only operates above a pre-determined mach number. — 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 it only operates above a pre-determined mach number.

The purpose of 'auto trim' function in autopilot is to ?

Question 53-20 : Control elevator trim tab in order to relieve elevator load help auto pilot compensate for crosswind influence tell the pilot when elevator trimming is required trim throttles to obtain smooth engine power variation

exemple 229 control elevator trim tab in order to relieve elevator load — control elevator trim tab in order to relieve elevator load

Mach trim is a device to compensate for ?

Question 53-21 : The backward movement of the aerodynamic centre at high mach numbers by moving the elevator to nose up the effects of fuel transfer between the main tanks and the tank located in the horizontal tail the effects of temperature variation during a climb or descent at constant mach weight reduction resulting from fuel consumption during the cruise

exemple 233 the backward movement of the aerodynamic centre at high mach numbers by moving the elevator to nose-up. — .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 the backward movement of the aerodynamic centre at high mach numbers by moving the elevator to nose-up.

The purpose of an aeroplane automatic trim system is to trim out the hinge ?

Question 53-22 : Elevator s rudder s elevator s and rudder s elevator s rudder s and ailerons

exemple 237 elevator(s). — If an aerodynamic force acts on a control surface it will tend to rotate the control around its hinge in the direction of the force the moment will be the force multiplied by the distance from the hinge to the control surface centre of pressure this is called the hinge moment the force may be due to the angle of attack of the aerofoil or the deflection of the control surface.it is assumed that the total hinge moment is the sum of the separate effects of angle of attack and control surface deflection to maintain the control in its position the pilot has to balance the hinge moment by applying a load to the cockpit control the cockpit control load will therefore depend on the size of the hinge moment . 992.the automatic trim system concerns the elevator s only elevator(s).

The automatic trim is a component of the autopilot pitch channel its function ?

Question 53-23 : Transfer a stabilized aeroplane to the pilot during autopilot disengagement reset the attitude after engaging the autopilot set the attitude to an instantaneous value before engaging the autopilot automatically disengage the autopilot in the case of an excessive pitch up

When the autopilot is engaged the role of the automatic trim is to ?

Question 53-24 : Relieve the a p servo motor and return the aircraft in trim at a p disconnect block the elevator and pilot the aircraft only via the trim tab actuator or the horizontal stabiliser react to altitude changes in altitude hold mode synchronize the longitudinal loop

exemple 245 relieve the a.p. servo motor and return the aircraft in-trim at a.p. disconnect — relieve the a.p. servo motor and return the aircraft in-trim at a.p. disconnect

The automatic pitch trim.1 ensures the aeroplane is properly trimmed when the ?

Question 53-25 : 2 3 1 3 1 2 3 1 2

.the purpose of auto trim is to . prevent snatching of the controls on disengagement of the autopilot. re position the horizontal stabilizer so that the control surfaces can remain in the neutral position thus giving you full movement on the controls. remove the standing load from the control surfaces.failure of the auto trim circuit will prevent connection of the autopilot if the aircraft is not properly trimmed the autopilot cannot be engaged.note .when engaging the autopilot automatic synchronisation function.when disengaging the autopilot automatic pitch trim function

The yaw damper system controls ?

Question 53-26 : The rudder with the angular rate about the yaw axis as the input signal the ailerons with mach number as the input signal the rudder with mach number as the input signal the ailerons with the angular rate about the yaw axis as the input signal

exemple 253 the rudder, with the angular rate about the yaw axis as the input signal. — the rudder, with the angular rate about the yaw axis as the input signal.

The yaw damper system .1 counters any wrong pilot action on the rudder ?

Question 53-27 : 2 1 2 3 1 2 2 3

When available the yaw damper indicator supplies the pilot with information ?

Question 53-28 : Yaw damper action on the rudder rudder displacement by the rudder pedals yaw damper action only on the ground rudder position

exemple 261 yaw damper action on the rudder. — . 970.the yaw damper indicator tells you rudder is moving under yaw damper control and in what direction yaw damper action on the rudder.

The mach trim system allows to ?

Question 53-29 : 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

exemple 265 increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number. — .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 increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number.

The yaw damper affects ?

Question 53-30 : Rudder only all control surfaces in a coordinated way ailerons and rudder ailerons only

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

Question 53-31 : 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 273 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 53-32 : A rate gyro or an accelerometer measuring the rudder angular movement measuring the ailerons angular movement measuring the roll rate

exemple 277 a rate gyro or an accelerometer. — a rate gyro or an accelerometer.

The yaw damper system acts on ?

Question 53-33 : 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 281 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 53-34 : 3 4 1 2 3 4 1 2 2 3 4

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

Question 53-35 : 2 3 4 1 2 3 4 5 2 2 3 4 5

exemple 289 2, 3, 4. — .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 2, 3, 4.

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

Question 53-36 : 3 1 1 3 1 2 3

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

Question 53-37 : 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 297 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 53-38 : 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

exemple 301 is not designed to provide a balanced turn. — .the yaw damper is fitted to correct for dutch roll is not designed to provide a balanced turn.

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

Question 53-39 : 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 305 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 53-40 : 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 309 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.

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