The flight director provides information for the pilot ?
Program > pilot
Source: Telepilote theorique examen 50
The horizontal command bar of a flight director ?
The horizontal command bar of a flight director 1 repeats the position information given by the ILS in the horizontal plane 2 repeats the position information given by the ILS in the vertical plane ?
The parameters taken into account the flight director computer in altitude hold mode alt hold are 1 altitude deviation2 engine rpm3 ground speed4 pitch attitudethe combination regrouping all correct statements Gives information about direction the amplitude of corrections to be applied on pitch of aircraft. the action taken the autopilot to maintain an altitude depends on how far aircraft from required altitude (altitude deviation) pitch attitude present altitude deviation are required. 
The purpose of a flight director to Reduce pilots workload presenting data in form of control commands. the action taken the autopilot to maintain an altitude depends on how far aircraft from required altitude (altitude deviation) pitch attitude present altitude deviation are required. 
The vertical command bar of a flight director Gives information about direction the amplitude of corrections to be applied on bank of aircraft. the action taken the autopilot to maintain an altitude depends on how far aircraft from required altitude (altitude deviation) pitch attitude present altitude deviation are required. 
The vertical command bar of a flight director 1 repeats position information given the ehsi 2 repeats position information given the vor 3 supplies information about direction and magnitude of corrections to be applied to bank of aircraftthe combination regrouping all correct statements Gives information about direction the amplitude of corrections to be applied on bank of aircraft. the action taken the autopilot to maintain an altitude depends on how far aircraft from required altitude (altitude deviation) pitch attitude present altitude deviation are required. Question 50-8
To allow coupling of a dual channel flight director Both autopilot channels must be selected on. 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. Question 50-9
An aircraft flies steadily on a heading 270° the flight director engaged in heading select mode hdg sel heading 270° selected if a new heading 360° selected vertical trend bar Deviates to right will be centred as soon as you roll aircraft to bank angle calculated the flight director. 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. Question 50-10
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. Question 50-11
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. Question 50-12
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. Question 50-13
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 50-14
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 50-15
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 50-16
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 50-17
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 50-18
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 50-19
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 50-20
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 50-21
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 50-22
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 50-23
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 50-24
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 50-25
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 50-26
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 50-27
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 50-28
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 50-29
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 50-30
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 50-31
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 50-32
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 50-33
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 50-34
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 50-35
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 50-36
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 50-37
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 50-38
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 50-39
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 50-40
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.
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