Question 67-1 : The flight director computer continuously ? [ Mandatory landing ]

Question 67-2 : In the event of a failure a fail operational flight control system will operate as a ?

Fail passive system.

Question 67-3 : When engaged in the pitch hold mode the autopilot uses data issued by the ?

Attitude reference system.

Question 67-4 : 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.

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 1022and if the vertical command bar is deviating to the left it means that the aircraft must be rolled to the left

Question 67-5 : In an autopilot system the basic stabilisation modes are 1 pitch attitude hold2 altitude hold3 horizontal wing hold4 heading holdthe combination regrouping all the correct statements is ?

1 and 3.

Question 67-6 : Concerning a fail operational flight control system in the event of a failure 1 the system will operate as a fail passive system2 the landing is not completed automatically3 the landing is completed automaticallythe 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 automaticallyin case of a second failure the landing cannot be completed automatically

Question 67-7 : 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.

Question 67-8 : The components of an autopilot system are the 1 actuators2 mode control panel3 efis control panel4 mode annunciator panelthe 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 computeran efis electronic flight instrument system control panel permits to display different informations on the nd navigation display and the pfd primary flight display

Question 67-9 : The computer of the autopilot system uses among others input signals from the 1 attitude reference system2 mode annunciator panel3 adc4 mode control panelthe combination that regroups all of the correct statements is ?

1 3 4.

Question 67-10 : The flight director command bars provide the pilot with corrections to apply to ?

Pitch andor roll attitude.

Question 67-11 : 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 systemsthe 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

Question 67-12 : 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 systemsthe 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

Question 67-13 : A flight control system is fail operational if in the event of a failure ?

The approach flare and landing can be completed automatically.

Question 67-14 : 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 systemsthe 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

Question 67-15 : During a final approach the flight director is engaged in the gs mode holding of ils glide slope if the horizontal command bar is deviating upward it means that ?

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' 1027the pilot must pitch up until the horizontal cue centers on the attitude indicatorit 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

Question 67-16 : In order to know in which mode the auto throttles are engaged the crew will check the 1 auto throttle arm switches2 auto throttle disengage switches3 mode control panel4 mode annunciator panelthe combination regrouping all the correct statements is ?

4.

Question 67-17 : On a flight mode annunciator fma the pilot can monitor 1 the engaged and armed modes of the autopilot2 the automatic landing capacity3 the acas modethe combination that regroups all of the correct statements is ?

1 2.

Cqb15 may 2012fma 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 approachacastcas mode is displayed on the navigation display not on the fma 967you can see on the left of the nd 'tfc' in blue acastcas traffic information ra and ta

Question 67-18 : When performing an automatic landing some additional operational limitations may apply like 1 maximum headwind or crosswind2 airport maximum pressure altitude3 runway conditionsthe 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 landingthanks for your explanations no the autopilot can not decided to perform automatically a go aroundthe 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 landingreverse thrust is used by the pilot if necessarya pilot can decided not to land on a wet flooded or contaminated runway but this is not due to a limitation from the autopilot

Question 67-19 : Autopilot engagement status can be checked on the ?

Fma.

Cqb15 may 2012the 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

Question 67-20 : According to cs25 the definition of the control wheel steering mode cws is 'where the pilot has the ability to make inputs to the ?

Question 67-21 : On a flight mode annunciator fma the pilot can check 1 the flight director selection2 the flapsslats selector3 the auto throttle modesthe combination that regroups all of the correct statements is ?

1 3.

Cqb15 august 2012the fma provides afcs lateral and vertical modes auto throttle modes fd selection ap engagement and automatic landing capacity failure and alert messages

Question 67-22 : The purpose of the flight mode annunciator fma is to ?

Check and confirm in which modes the automatic flight control systems are armed andor engaged.

Cqb15 august 2012the 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 athr

Question 67-23 : The flight mode annunciator fma is displayed on the ?

Pfd.

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

Question 67-24 : The purpose of an automatic landing system is to ?

Make the landing possible in poor weather conditions.

Ecqb03 july 2016

Question 67-25 : 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

Question 67-26 : Fans a units utilize the following for data transmissions ?

Satellite based acars systems.

Ecqb03 august 2016future air navigation systems fans a uses the acars network

Question 67-27 : The 'fans concept' is ?

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

Ecqb03 august 2016

Question 67-28 : 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 downthe 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 06 by adjusting the elevators with respect to the stabilizer as speed increases

Question 67-29 : The purpose of auto trim function in autopilot is to ?

Control elevator trim tab in order to relieve elevator load.

Question 67-30 : 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.

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 downthe 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 06 by adjusting the elevators with respect to the stabilizer as speed increases

Question 67-31 : 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 surfaceit 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 992the automatic trim system concerns the elevator s only

Question 67-32 : 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.

Question 67-33 : When the autopilot is engaged the role of the automatic trim is to ?

Relieve the ap servo motor and return the aircraft in trim at ap disconnect.

Question 67-34 : The automatic pitch trim 1 ensures the aeroplane is properly trimmed when the autopilot is engaged2 permits the elevator to always be in neutral position with respect to horizontal stabiliser3 ensures the aeroplane is properly trimmed when the autopilot is disengagedthe combination regrouping all ?

2 3.

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 surfacesfailure 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 functionwhen disengaging the autopilot automatic pitch trim function

Question 67-35 : The yaw damper system controls ?

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

Question 67-36 : The yaw damper system 1 counters any wrong pilot action on the rudder pedals2 counters dutch roll3 is active only when autopilot is engagedthe combination regrouping all the correct statements are ?

2.

Question 67-37 : When available the yaw damper indicator supplies the pilot with information regarding the ?

Yaw damper action on the rudder.

970the yaw damper indicator tells you rudder is moving under yaw damper control and in what direction

Question 67-38 : 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 downthe 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 06 by adjusting the elevators with respect to the stabilizer as speed increases

Question 67-39 : The yaw damper affects ?

Rudder only.

Question 67-40 : An aircraft is turning right with too much bank slipping turn the yaw damper system ?

Is not designed to provide a balanced turn.