When disengaging the autopilot the function providing a smooth 'hand over' is ? [ Mandatory landing ]

Question 67-1 : Automatic pitch trim function automatic synchronisation function mach trim function automatic cws control wheel steering function

exemple 167 Automatic pitch trim function. — Admin .when engaging the autopilot automatic synchronisation function .when disengaging the autopilot automatic pitch trim function Automatic pitch trim function.

During an autocoupled ils approach followed by an automatic landing the ?

Question 67-2 : Radio altitude barometric altitude with the altimeter set to the qfe barometric altitude with the altimeter set to the qnh barometric altitude with the altimeter set to the 1013 25

exemple 171 Radio altitude. — Radio altitude.

The computer of the autopilot system uses among others the following parameters ?

Question 67-3 : Cas altitude vertical speed heading attitude cas altitude temperature inertial position attitude altitude vertical speed heading attitude gps position altitude heading temperature fuel flow attitude

exemple 175 Cas, altitude, vertical speed, heading, attitude. — Cas, altitude, vertical speed, heading, attitude.

The flight director computer continuously ?

Question 67-4 : Compares the current attitude with the computed attitude compares the computed attitude with the egpws signals compares the computed attitude with the acas signals computes the required attitude for the autopilot synchronization

exemple 179 Compares the current attitude with the computed attitude. — Compares the current attitude with the computed attitude.

In the event of a failure a fail operational flight control system will operate ?

Question 67-5 : Fail passive system fail safe system fail operational hybrid system fail redundant system

exemple 183 Fail-passive system. — Fail-passive system.

When engaged in the pitch hold mode the autopilot uses data issued by the ?

Question 67-6 : Attitude reference system flight management computer fmc adc inertial vertical speed indicator

exemple 187 Attitude reference system. — Attitude reference system.

During a final approach the flight director is engaged in the loc mode holding ?

Question 67-7 : Must be rolled to the left is left of the loc axis must be rolled to the right is right of the loc axis

exemple 191 Must be rolled to the left. — Admin .the flight director computes and displays the proper pitch and bank angles required in order for the aircraft to follow a selected path we can be left or righ from the axis . 1022.and if the vertical command bar is deviating to the left it means that the aircraft must be rolled to the left Must be rolled to the left.

In an autopilot system the basic stabilisation modes are .1 pitch attitude ?

Question 67-8 : 1 and 3 1 2 3 and 4 1 2 and 3 1 and 4

Concerning a fail operational flight control system in the event of a failure ?

Question 67-9 : 1 3 1 2 2 3 3

exemple 199 1, 3. — Admin .a fail operational autoland system can withstand one failure it becomes now a fail passive autoland system it can continue to autoland automatically .in case of a second failure the landing cannot be completed automatically 1, 3.

The position of the command bars of a flight director enables the pilot to know ?

Question 67-10 : The direction and the amplitude of the corrections to apply on the controls only the direction of the corrections to apply on the controls the position of the aircraft the attitude of the aircraft

exemple 203 The direction and the amplitude of the corrections to apply on the controls. — The direction and the amplitude of the corrections to apply on the controls.

The components of an autopilot system are the .1 actuators.2 mode control ?

Question 67-11 : 1 2 4 1 2 3 4 1 2 3 3 4

exemple 207 1, 2, 4. — .the components of an autopilot system are the actuators the mode control panel the mode annunciator panel and the computer .an efis electronic flight instrument system control panel permits to display different informations on the nd navigation display and the pfd primary flight display 1, 2, 4.

The computer of the autopilot system uses among others input signals from the ?

Question 67-12 : 1 3 4 1 2 3 4 1 4 2 3

The flight director command bars provide the pilot with corrections to apply to ?

Question 67-13 : Pitch and/or roll attitude pitch attitude only roll attitude only pitch and/or roll attitude and yaw

exemple 215 Pitch and/or roll attitude. — Pitch and/or roll attitude.

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

Question 67-14 : Guidance functions stability functions attitude functions inner loop functions

exemple 219 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 67-15 : Inner loop systems synchronization system flight management system fms outer loop systems

exemple 223 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 67-16 : 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 227 The approach, flare and landing can be completed automatically. — The approach, flare and landing can be completed automatically.

In an autopilot system ?

Question 67-17 : 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 231 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 67-18 : 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 235 The pitch attitude must be increased. — Admin .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 67-19 : 4 2 4 1 3 3

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

Question 67-20 : 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 67-21 : 1 1 2 2 3 1 2 3

exemple 247 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 67-22 : Fma control panel and the flight mode annunciator/indicator control panel mcdu

exemple 251 Fma. — 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 Fma.

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

Question 67-23 : 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 255 ... 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 67-24 : 1 3 1 2 3 1 2

exemple 259 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 67-25 : 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 263 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 67-26 : Pfd nd mcdu control panel

exemple 267 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 67-27 : 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 271 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 67-28 : 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 275 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 67-29 : Satellite based acars systems vhf data link systems fixed dedicated ground stations navstar/gps satellites

exemple 279 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 67-30 : 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 283 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 67-31 : 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 287 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 67-32 : 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 291 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 67-33 : 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 295 The backward movement of the aerodynamic centre at high mach numbers by moving the elevator to nose-up. — Admin .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 67-34 : Elevator s rudder s elevator s and rudder s elevator s rudder s and ailerons

exemple 299 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 67-35 : 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

exemple 303 Transfer a stabilized aeroplane to the pilot during autopilot disengagement. — Transfer a stabilized aeroplane to the pilot during autopilot disengagement.

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

Question 67-36 : 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 307 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 67-37 : 2 3 1 3 1 2 3 1 2

exemple 311 2, 3. — Admin .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 2, 3.

The yaw damper system controls ?

Question 67-38 : 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 315 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 67-39 : 2 1 2 3 1 2 2 3

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

Question 67-40 : Yaw damper action on the rudder rudder displacement by the rudder pedals yaw damper action only on the ground rudder position

exemple 323 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.

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