After alignment of the stable platform of an Inertial Navigation System INS the output data from the platform is ?
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Source: Telepilote theorique examen 49
In an Inertial Reference System accelerations are measured in relation to ?
The full alignment of the stable platform of an Inertial Navigation System INS ?
Which of following statements concerning aircraft positions indicated on a triple fit ins/irs on cdu correct The positions are likely to differ because they are calculated from different sources. all ins/irs in an aircraft are independent the positions each irs/ins will be slightly different. 
A pilot accidentally turning off irs in flight and then turns it back on a few moments later following this incident It can only be used attitude reference. all ins/irs in an aircraft are independent the positions each irs/ins will be slightly different. 
Concerning operation of an ins/irs nav mode must be selected Prior to movement of aircraft off gate. all ins/irs in an aircraft are independent the positions each irs/ins will be slightly different. 
The data that needs to be inserted into an inertial reference system in order to enable system to make a successful alignment of navigation Aircraft position in latitude longitude. an irs needs to know latitude only alignment but needs starting latitude longitude navigation. Question 49-8
Which of following statements concerning loss of alignment an inertial reference system irs in flight correct The navigation mode including present position ground speed outputs inoperative the remainder of flight. you can only perform a re alignment on ground the system inoperative navigation but it remains usable attitude reference. Question 49-9
Mode 'localizer arm' active on flight director means System armed localizer approach coupling will occur upon capturing centre line. you can only perform a re alignment on ground the system inoperative navigation but it remains usable attitude reference. Question 49-10
A closed loop control system in which a small power input controls a much larger power output in a strictly proportionate manner known as System armed localizer approach coupling will occur upon capturing centre line. a servomechanism a type of control system in which a small signal or a small force used to control a much larger force in which output accurately follows input even if it varying rapidly the system constantly compares input the output until error signal becomes zero. Question 49-11
The essential components of a flight director are 1 a computer 2 an automatic pilot 3 an auto throttle 4 command bars the combination regrouping all correct statements System armed localizer approach coupling will occur upon capturing centre line. a servomechanism a type of control system in which a small signal or a small force used to control a much larger force in which output accurately follows input even if it varying rapidly the system constantly compares input the output until error signal becomes zero. Question 49-12
The control law of a transport airplane autopilot control channel may be defined as relationship between Computer input deviation data the output control deflection signals. The autopilot control laws determine how computer interprets a performance demand in terms of a control response. Question 49-13
In a transport airplane an autopilot comprises in addition to mode display devices following fundamental elements 1 airflow valve2 sensors3 comparators4 computers5 amplifiers6 servo actuatorsthe combination regrouping all correct statements Computer input deviation data the output control deflection signals. The autopilot control laws determine how computer interprets a performance demand in terms of a control response. Question 49-14
A pilot engages control wheel steering cws of a conventional autopilot and carries out a manoeuvre in roll when control wheel released autopilot will Maintain flight attitude obtained at that moment. The autopilot control laws determine how computer interprets a performance demand in terms of a control response. Question 49-15
The basic modes of an autopilot consist in Stabilizing aircraft around its centre of gravity. 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 49-16
On a modern aircraft flight director modes are displayed on Upper strip of pfd (primary flight display). 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 49-17
In order to know in which mode auto throttles are engaged crew will check Pfd (primary flight display). 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 49-18
An automatic landing system necessitating that landing be continued manually in case of a system failure during an automatic approach called 'fail ' Pfd (primary flight display). 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 49-19
When an aircraft operating in vor coupled mode approaches 'cone of confusion' over a vor station roll channel of autopilot Temporarily maintains a heading. 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 49-20
The command bars of a flight director are generally represented on an Adi (attitude director indicator). 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 49-21
After having programmed your flight director you see that indications of your adi attitude director indicator are as represented in diagram n°1 of appended annex on this instrument command bars indicate that you must bank your airplane to left 1043 Increase flight attitude until command bars recentre on symbolic airplane. 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 49-22
An autopilot capable of holding at least altitude and heading mode compulsory For ifr or night flights with only one pilot. For a private flight an autopilot not compulsory but cpl/atpl we are talking about commercial air transportation ops 1 655 additional equipment single pilot operation under ifr an operator shall not conduct single pilot ifr operations unless aeroplane equipped with an autopilot with at least altitude hold heading mode. Question 49-23
Among following functions of an autopilot those related to airplane guidance are 1 pitch attitude holding2 horizontal wing holding3 indicated airspeed or mach number holding4 altitude holding5 vor axis holding6 yaw dampingthe combination regrouping all correct statements For ifr or night flights with only one pilot. the question asking about 'guidance' functions of autopilot the 'guidance' functions of a autopilot consist in monitoring movements of centre of gravity in three dimensions of space 'guidance' functions are altitude hold heading hold airspeed hold vnav (vertical navigation) lnav (lateral navigation) pitch attitude holding horizontal wing holding yaw damper are parts of 'basic' function of autopilot (the stabilisation of aircraft around its centre of gravity). Question 49-24
The ias or mach hold mode provided 1 autopilot pitch channel in climb mode at a constant ias or mach number2 autothrottles in climb mode at a constant ias or mach number3 autopilot pitch channel in altitude or glide path holding mode4 autothrottles in altitude or glide path holding modethe combination regrouping all correct statements For ifr or night flights with only one pilot. during climb when ias or mach hold speed mode engaged (speed mode) speed maintained the autopilot pitch channel (by adjusting elevator position in order to decrease climb angle thrust maintained constant) when you are established at your cruising level or when established on glide path autothrottles will maintain speed constant increasing or decreasing thrust the elevator not adjusted controlling speed in alt hold or app mode. Question 49-25
After having programmed your flight director you see that indications of your adi attitude director indicator are as represented in diagram n°1 of appended annex on this instrument command bars indicate that you must 1044 Increase flight attitude bank your airplane to left until command bars recentre on symbolic aeroplane. during climb when ias or mach hold speed mode engaged (speed mode) speed maintained the autopilot pitch channel (by adjusting elevator position in order to decrease climb angle thrust maintained constant) when you are established at your cruising level or when established on glide path autothrottles will maintain speed constant increasing or decreasing thrust the elevator not adjusted controlling speed in alt hold or app mode. Question 49-26
When being engaged and without selecting a particular mode an automatic pilot enables Aeroplane stabilisation with attitude hold or maintaining vertical speed possibly automatic trim. 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 49-27
The position of a flight director command bars Indicates manoeuvres to execute to achieve or maintain a flight situation. 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 49-28
In an auto pilot slaved powered control circuit system which ensures synchronisation Can itself when it fails prevent automatic pilot from being engaged. 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 49-29
An autopilot system Must provide at least aircraft stabilisation functions. 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 49-30
During an automatic landing between 50 ft agl and touch down autopilot maintains A vertical speed according to radio altimeter height. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-31
A flight control system which can in event of a failure complete automatically approach flare and landing called 'fail ' A vertical speed according to radio altimeter height. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-32
Command bars of flight director may be present on 1 hsi 2 cdu 3 adi the combination that regroups all of correct statements A vertical speed according to radio altimeter height. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-33
Considering a flight director of 'command bar type The vertical bar associated with roll channel. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-34
Considering a flight director of 'command bar type 1 vertical bar always associated with roll channel2 vertical bar may be associated with pitch channel3 horizontal bar may be associated with roll channel4 horizontal bar always associated with pitch channelthe combination regrouping all correct statements The vertical bar associated with roll channel. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-35
During a final approach flight director system engaged in loc mode holding of localizer axis the position of vertical command bar indicates The correction on bank to be applied to join follow localizer axis. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-36
Flying manually during a final approach flight director system engaged in g/s mode holding of ils glide slope if aircraft above ils glide slope horizontal command bar May be centred if pilot correcting to come back on to ils glide slope. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-37
Flying manually during a final approach flight director system engaged in g/s mode holding of ils glide slope if aircraft below ils glide slope horizontal command bar May be centred if pilot correcting to come back on ils glide slope. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-38
Flying manually during a final approach flight director system engaged in loc mode holding of localizer axis if aircraft left of localizer axis vertical command bar May be centred if pilot correcting to come back on localizer axis. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-39
Flying manually during a final approach flight director system engaged in loc mode holding of localizer axis if aircraft right of localizer axis vertical command bar May be centred if pilot correcting to come back on localizer axis. the autopilot flares out at this stage progressively reducing vertical velocity. Question 49-40
The flight director engaged in heading select mode hdg sel heading 180° selected when heading 160° vertical bar of fd Is centered if bank angle of aircraft equal to bank angle computed the flight director calculator. the autopilot flares out at this stage progressively reducing vertical velocity.
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