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Question 67-1 : In the event of a failure a fail operational flight control system will operate as a ? [ Mandatory landing ]

Fail passive system

exemple 167 Fail-passive system.

Question 67-2 : When engaged in the pitch hold mode the autopilot uses data issued by the ?

Attitude reference system

exemple 171 Attitude reference system.

Question 67-3 : During a final approach the flight director is engaged in the loc mode holding of localizer axis if the vertical command bar is deviating to the left it means that the aircraft ?

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 exemple 175 Must be rolled to the left.

Question 67-4 : In an autopilot system the basic stabilisation modes are .1 pitch attitude hold.2 altitude hold.3 horizontal wing hold.4 heading hold.the combination regrouping all the correct statements is ?

1 and 3

exemple 179 1 and 3.

Question 67-5 : Concerning a fail operational flight control system in the event of a failure .1 the system will operate as a fail passive system .2 the landing is not completed automatically .3 the landing is completed automatically .the combination that regroups all of the correct statements is ?

1 3

.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 exemple 183 1, 3.

Question 67-6 : The position of the command bars of a flight director enables the pilot to know ?

The direction and the amplitude of the corrections to apply on the controls

exemple 187 The direction and the amplitude of the corrections to apply on the controls.

Question 67-7 : The components of an autopilot system are the .1 actuators.2 mode control panel.3 efis control panel.4 mode annunciator panel.the combination that regroups all of the correct statements is ?

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 exemple 191 1, 2, 4.

Question 67-8 : The computer of the autopilot system uses among others input signals from the .1 attitude reference system.2 mode annunciator panel.3 adc.4 mode control panel.the combination that regroups all of the correct statements is ?

1 3 4

exemple 195 1, 3, 4.

Question 67-9 : The flight director command bars provide the pilot with corrections to apply to ?

Pitch and/or roll attitude

exemple 199 Pitch and/or roll attitude.

Question 67-10 : In an autopilot system the functions consisting in controlling the path of the aircraft are 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 exemple 203 Guidance functions.

Question 67-11 : In an autopilot system the function consisting in controlling the movements around the center of gravity of the aircraft is provided by the ?

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 exemple 207 Inner loop systems.

Question 67-12 : A flight control system is fail operational if in the event of a failure ?

The approach flare and landing can be completed automatically

exemple 211 The approach, flare and landing can be completed automatically.

Question 67-13 : In an autopilot system ?

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 exemple 215 The inner loops provide the stability functions and the outer loops provide the guidance functions.

Question 67-14 : During a final approach the flight director is engaged in the g/s mode holding of ils glide slope if the horizontal command bar is deviating upward it means that ?

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 exemple 219 The pitch attitude must be increased.

Question 67-15 : In order to know in which mode the auto throttles are engaged the crew will check the .1 auto throttle arm switches.2 auto throttle disengage switches.3 mode control panel.4 mode annunciator panel.the combination regrouping all the correct statements is ?

4

exemple 223 4.

Question 67-16 : On a flight mode annunciator fma the pilot can monitor .1 the engaged and armed modes of the autopilot.2 the automatic landing capacity.3 the acas mode.the combination that regroups all of the correct statements is ?

1 2

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 exemple 227 1, 2.

Question 67-17 : When performing an automatic landing some additional operational limitations may apply like .1 maximum headwind or crosswind.2 airport maximum pressure altitude.3 runway conditions.the combination that regroups all of the correct statements is ?

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 exemple 231 1.

Question 67-18 : Autopilot engagement status can be checked on the ?

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 exemple 235 Fma.

Question 67-19 : According to cs25 the definition of the control wheel steering mode cws is .'where the pilot has the ability to make inputs to the ?

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 exemple 239 ... automatic pilot by movement of the normal control wheel'.

Question 67-20 : On a flight mode annunciator fma the pilot can check .1 the flight director selection.2 the flaps/slats selector.3 the auto throttle modes.the combination that regroups all of the correct statements is ?

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

Question 67-21 : The purpose of the flight mode annunciator fma is to ?

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 exemple 247 Check and confirm in which modes the automatic flight control systems are armed and/or engaged.

Question 67-22 : The flight mode annunciator fma is displayed on the ?

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 exemple 251 Pfd.

Question 67-23 : The purpose of an automatic landing system is to ?

Make the landing possible in poor weather conditions

Ecqb03 july 2016 exemple 255 Make the landing possible in poor weather conditions.

Question 67-24 : Following an automatic landing with the roll out mode engaged the autopilot ?

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 exemple 259 Controls the rudder and nose wheel steering to keep the aeroplane on the localiser centreline.

Question 67-25 : Fans a units utilize the following for data transmissions ?

Satellite based acars systems

Ecqb03 august 2016 ..future air navigation systems fans a uses the acars network exemple 263 Satellite-based acars systems.

Question 67-26 : The 'fans concept' is ?

Different systems to improve the handling and transfer of information extend surveillance and improve navigational accuracy

Ecqb03 august 2016 exemple 267 Different systems to improve the handling and transfer of information, extend surveillance and improve navigational accuracy.

Question 67-27 : Which one of the following statements is true with regard to the operation of a mach trim system ?

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 exemple 271 It only operates above a pre-determined mach number.

Question 67-28 : The purpose of 'auto trim' function in autopilot is to ?

Control elevator trim tab in order to relieve elevator load

exemple 275 Control elevator trim tab in order to relieve elevator load

Question 67-29 : Mach trim is a device to compensate for ?

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 exemple 279 The backward movement of the aerodynamic centre at high mach numbers by moving the elevator to nose-up.

Question 67-30 : The purpose of an aeroplane automatic trim system is to trim out the hinge moment of the ?

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 exemple 283 Elevator(s).

Question 67-31 : The automatic trim is a component of the autopilot pitch channel its function is to ?

Transfer a stabilized aeroplane to the pilot during autopilot disengagement

exemple 287 Transfer a stabilized aeroplane to the pilot during autopilot disengagement.

Question 67-32 : When the autopilot is engaged the role of the automatic trim is to ?

Relieve the a p servo motor and return the aircraft in trim at a p disconnect

exemple 291 Relieve the a.p. servo motor and return the aircraft in-trim at a.p. disconnect

Question 67-33 : The automatic pitch trim .1 ensures the aeroplane is properly trimmed when the autopilot is engaged.2 permits the elevator to always be in neutral position with respect to horizontal stabiliser.3 ensures the aeroplane is properly trimmed when the autopilot is disengaged .the combination ?

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 exemple 295 2, 3.

Question 67-34 : The yaw damper system controls ?

The rudder with the angular rate about the yaw axis as the input signal

exemple 299 The rudder, with the angular rate about the yaw axis as the input signal.

Question 67-35 : The yaw damper system .1 counters any wrong pilot action on the rudder pedals.2 counters dutch roll.3 is active only when autopilot is engaged.the combination regrouping all the correct statements are ?

2

exemple 303 2.

Question 67-36 : When available the yaw damper indicator supplies the pilot with information regarding the ?

Yaw damper action on the rudder

. 970.the yaw damper indicator tells you rudder is moving under yaw damper control and in what direction exemple 307 Yaw damper action on the rudder.

Question 67-37 : The mach trim system allows to ?

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 exemple 311 Increase the longitudinal static stability of the aircraft by changing the horizontal stabilizer according to the mach number.

Question 67-38 : The yaw damper affects ?

Rudder only

exemple 315 Rudder only.

Question 67-39 : An aircraft is turning right with too much bank slipping turn the yaw damper system ?

Is not designed to provide a balanced turn

exemple 319 Is not designed to provide a balanced turn.

Question 67-40 : In a yaw damper system sensing of a disturbance in yaw is usually by ?

A rate gyro or an accelerometer

exemple 323 A rate gyro or an accelerometer.


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