The vertical command bar of a flight director 1 repeats the position information given by the EHSI 2 repeats the position information given by the ?
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To allow the coupling of a dual channel flight director ?
An aircraft flies steadily on a heading 270° The flight director is engaged in the heading select mode HDG SEL heading 270° selected If a new heading 360° is selected the vertical trend bar ?
An automatic ils approach can be flown only Within a range of crosswinds levels of turbulence. coupling of both flight director necessary to perform a full autoland when establish on an ils between 3000 ft 1500 ft above ground you can switch on both autopilot it allows coupling of a dual channel flight director to realize full autoland. 
The 'guidance' functions of a autopilot consist in Monitoring movements of centre of gravity in three dimensions of space. the basic function of an autopilot stabilisation (the stabilisation of aircraft around its centre of gravity) basic function achieved the inner loop systems the advanced function 'guidance' (monitoring movements of centre of gravity in three dimensions of space) outer loop systems offer guidance facilities (altitude hold heading hold vnav lnav) outer loops act from an external position on inner loop 'foo inner loop into manoeuvrig aircraft into achieving its aim. 
The 'airspeed hol mode can be engaged and maintained during Climbs descents turns power changes. the basic function of an autopilot stabilisation (the stabilisation of aircraft around its centre of gravity) basic function achieved the inner loop systems the advanced function 'guidance' (monitoring movements of centre of gravity in three dimensions of space) outer loop systems offer guidance facilities (altitude hold heading hold vnav lnav) outer loops act from an external position on inner loop 'foo inner loop into manoeuvrig aircraft into achieving its aim. 
The output data of flight director computer are Two channels pitch roll. the basic function of an autopilot stabilisation (the stabilisation of aircraft around its centre of gravity) basic function achieved the inner loop systems the advanced function 'guidance' (monitoring movements of centre of gravity in three dimensions of space) outer loop systems offer guidance facilities (altitude hold heading hold vnav lnav) outer loops act from an external position on inner loop 'foo inner loop into manoeuvrig aircraft into achieving its aim. Question 52-8
The initiation of an automatic go around can be In a range of approach airspeeds. a go around will be initiated while established on approach usually between 5 nm the runway threshold you are in approach configuration (flaps deployed possibly slats deployed gear down) you will initiate automatic go around procedure pressing to/ga switch located on engine thrust lever. Question 52-9
During a final approach if flight director system engaged in g/s mode holding of ils glide slope position of horizontal command bar indicates The correction on pitch to be applied to join follow ils glide slope. a go around will be initiated while established on approach usually between 5 nm the runway threshold you are in approach configuration (flaps deployed possibly slats deployed gear down) you will initiate automatic go around procedure pressing to/ga switch located on engine thrust lever. Question 52-10
If in event of a failure there no significant out of trim condition or deviation of flight path or attitude but landing not completed automatically such an automatic landing system considered as The correction on pitch to be applied to join follow ils glide slope. the question specifically states that failure has occured the landing was not completed automatically this 'fail passive' with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-11
If in event of a failure approach flare and landing can be completed the remaining part of automatic system such an automatic landing system considered as The correction on pitch to be applied to join follow ils glide slope. with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-12
Considering a flight director of 'command bar type The horizontal bar associated with pitch channel. with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-13
The command bars of a flight director May be displayed when flying manually or with autopilot engaged. with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-14
The purpose s of flight director system are to 1 give position of aircraft according to radioelectric axis2 give position of aircraft according to waypoints3 to aid pilot when flying manuallythe combination that regroups all of correct statements May be displayed when flying manually or with autopilot engaged. with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-15
Concerning command bars of a flight director It possible to remove them switching flight director off. with a three autopilot system failure of one system still leaves two operating so that fail operational. Question 52-16
The lateral flight path modes of an autopilot system are 1 speed hold2 localiser intercept and track3 track hold4 fms lateral navigation5 pitch attitude hold the combination that regroups all of correct statements It possible to remove them switching flight director off. autopilot lateral mode roll attitude heading vor mode navigation mode (gps/fms/ins) autopilot longitudinal mode altitude hold capture speed hold capture with a/t (ias and/or mach) thrust hold capture with a/t pitch attitude. Question 52-17
The purpose of autopilot control wheel steering cws mode To consider as target parameters current pitch roll angles at time mode becomes active. pushing a cws engage switch engages a/p pitch roll axes in cws mode displays cws p cws r on fmas with cws engaged a/p maneuvers airplane in response to control pressures applied the pilot the control pressure similar to that required manual flight when control pressure released a/p holds existing attitude. Question 52-18
When engaged in fms lateral navigation mode lnav autopilot uses command provided the To consider as target parameters current pitch roll angles at time mode becomes active. pushing a cws engage switch engages a/p pitch roll axes in cws mode displays cws p cws r on fmas with cws engaged a/p maneuvers airplane in response to control pressures applied the pilot the control pressure similar to that required manual flight when control pressure released a/p holds existing attitude. Question 52-19
In an autopilot system flight path modes are 1 pitch attitude hold2 ias and mach number hold3 altitude hold4 glide slope intercept and trackthe combination regrouping all correct statements To consider as target parameters current pitch roll angles at time mode becomes active. pushing a cws engage switch engages a/p pitch roll axes in cws mode displays cws p cws r on fmas with cws engaged a/p maneuvers airplane in response to control pressures applied the pilot the control pressure similar to that required manual flight when control pressure released a/p holds existing attitude. Question 52-20
The lateral flight path modes of an autopilot system are 1 heading hold2 speed hold3 fms lateral navigation4 tas hold5 localizer intercept and trackthe combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. autopilot lateral mode roll attitude heading vor/ils mode navigation mode (gps/fms/ins) autopilot longitudinal mode altitude hold capture speed hold capture with a/t (ias and/or mach) thrust hold capture with a/t pitch attitude. Question 52-21
The vertical flight path modes of an autopilot system are 1 pitch attitude hold2 altitude hold3 track hold4 glide slope intercept and trackthe combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. the question about vertical flight path modes only pitch attitude holding horizontal wing holding yaw damper are parts of 'basic' function of autopilot (the stabilisation of aircraft around its centre of gravity) 'track hol a function of horizontal flight path modes. Question 52-22
The automatic synchronisation function of an autopilot control system 1 operates only when autopilot engaged 2 prevents aircraft's control system from jerking when disengaging autopilot 3 prevents aircraft's control system from jerking when engaging autopilot the combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. before autopilot can be engaged certain conditions must be met these conditions vary with aircraft type (eg no force being applied to control wheel) it must also be ensured that on engagement 'take over' affected smoothly without 'snatching' of aircraft's control system in other words aircraft must be trimmed the desired flight attitude before engagement the automatic control system must be synchronised to maintain that attitude on engagement the automatic synchronisation operates before autopilot engaged. Question 52-23
The components of an autopilot system are 1 actuators2 mode control panel3 mode annunciator panel4 computerthe combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. ashahabpour hi there another question that looks like this (i think it's exactly same) but answer different mode annunciator panel not in combination that regroups all of correct statements do you have an explanation? the question you are talking about n°882 'the computer of autopilot system uses among others input signals from the 1 attitude reference system 2 mode annunciator panel 3 adc 4 mode control panel answer 1 3 4 as you can see question slightly different it talks about computer of autopilot only. Question 52-24
Concerning a fail passive flight control system in event of a failure 1 there may be a significant deviation of flight path or attitude 2 there no significant deviation of flight path or attitude 3 there no significant out of trim condition 4 there may be a significant out of trim conditionthe combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. «fail passive flight control system» a flight control system fail passive if in event of a failure there no significant out of trim condition or deviation of flight path or attitude but landing not completed automatically for a fail passive automatic flight control system pilot assumes control of aeroplane after a failure «fail operational flight control system» a flight control system fail operational if in event of a failure below alert height approach flare landing can be completed automatically in event of a failure automatic landing system will operate as a fail passive system. Question 52-25
Concerning a fail passive flight control system in event of a failure there may be a significant deviation of flight path or attitude2 there no significant deviation of flight path or attitude3 landing not completed automatically4 landing completed automaticallythe combination that regroups all of correct statements To consider as target parameters current pitch roll angles at time mode becomes active. «fail passive flight control system» a flight control system fail passive if in event of a failure there no significant out of trim condition or deviation of flight path or attitude but landing not completed automatically for a fail passive automatic flight control system pilot assumes control of aeroplane after a failure «fail operational flight control system» a flight control system fail operational if in event of a failure below alert height approach flare landing can be completed automatically in event of a failure automatic landing system will operate as a fail passive system. Question 52-26
For a fms designed with lateral navigation lnav capability coupled to autopilot fms lateral command output A roll angle or a heading target. «fail passive flight control system» a flight control system fail passive if in event of a failure there no significant out of trim condition or deviation of flight path or attitude but landing not completed automatically for a fail passive automatic flight control system pilot assumes control of aeroplane after a failure «fail operational flight control system» a flight control system fail operational if in event of a failure below alert height approach flare landing can be completed automatically in event of a failure automatic landing system will operate as a fail passive system. Question 52-27
The cs 25 gives following definition 'where pilot has ability to make inputs to automatic pilot movement of normal control whee the corresponding mode Control wheel steering (cws). «fail passive flight control system» a flight control system fail passive if in event of a failure there no significant out of trim condition or deviation of flight path or attitude but landing not completed automatically for a fail passive automatic flight control system pilot assumes control of aeroplane after a failure «fail operational flight control system» a flight control system fail operational if in event of a failure below alert height approach flare landing can be completed automatically in event of a failure automatic landing system will operate as a fail passive system. Question 52-28
When engaging autopilot function providing a smooth 'take over' the Automatic synchronisation function. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-29
When disengaging autopilot function providing a smooth 'hand over' the Automatic pitch trim function. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-30
During an autocoupled ils approach followed an automatic landing guidance signals in vertical plane under 200 ft are computed according to Automatic pitch trim function. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-31
The computer of autopilot system uses among others following parameters Cas altitude vertical speed heading attitude. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-32
The flight director computer continuously Compares current attitude with computed attitude. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-33
In event of a failure a fail operational flight control system will operate as a Compares current attitude with computed attitude. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-34
When engaged in pitch hold mode autopilot uses data issued the Attitude reference system. when engaging autopilot automatic synchronisation function when disengaging autopilot automatic pitch trim function. Question 52-35
During a final approach flight director engaged in loc mode holding of localizer axis if vertical command bar deviating to left it means that aircraft Must be rolled to left. the flight director computes displays proper pitch bank angles required in order the aircraft to follow a selected path we can be left or righ from axis and if vertical command bar deviating to left it means that aircraft must be rolled to left. Question 52-36
In an autopilot system basic stabilisation modes are 1 pitch attitude hold2 altitude hold3 horizontal wing hold4 heading holdthe combination regrouping all correct statements Must be rolled to left. the flight director computes displays proper pitch bank angles required in order the aircraft to follow a selected path we can be left or righ from axis and if vertical command bar deviating to left it means that aircraft must be rolled to left. Question 52-37
Concerning a fail operational flight control system in event of a failure 1 system will operate as a fail passive system 2 landing not completed automatically 3 landing completed automatically the combination that regroups all of correct statements Must be rolled to left. 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 landing cannot be completed automatically. Question 52-38
The position of command bars of a flight director enables pilot to know The direction the amplitude of corrections to apply on controls. 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 landing cannot be completed automatically. Question 52-39
The components of an autopilot system are 1 actuators2 mode control panel3 efis control panel4 mode annunciator panelthe combination that regroups all of correct statements The direction the amplitude of corrections to apply on controls. the components of an autopilot system are actuators mode control panel mode annunciator panel the computer an efis (electronic flight instrument system) control panel permits to display different informations on nd (navigation display) the pfd (primary flight display). Question 52-40
The computer of autopilot system uses among others input signals from 1 attitude reference system2 mode annunciator panel3 adc4 mode control panelthe combination that regroups all of correct statements The direction the amplitude of corrections to apply on controls. the components of an autopilot system are actuators mode control panel mode annunciator panel the computer an efis (electronic flight instrument system) control panel permits to display different informations on nd (navigation display) the pfd (primary flight display).
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