CHAPTER 3 --- AUTOMATIC FLIGHT CONTROL SYSTEM
AUTOMATIC FLIGHT CONTROL SYSTEMTable of ContentsVol. 103--00--1REV 3, May 03/05CHAPTER 3 --- AUTOMATIC FLIGHT CONTROL SYSTEMPageTABLE OF CONTENTSTable of -1003--10--1FLIGHT CONTROL AND GUIDANCEFlight Control and GuidanceFlight DirectorSynchronizationFlight Mode AnnunciatorLateral Modes of OperationVertical Modes of OperationAltitude Alert SystemSystem Circuit topilot03--3003--30--1LIST OF ILLUSTRATIONSFLIGHT CONTROL AND GUIDANCEFigure 03--20--1Flight Control Panel -- LayoutFigure 03--20--2Flight Director -- SchematicFigure 03--20--3Flight Director -- Controls and IndicationsFigure 03--20--4Course Pointer Control and IndicationFigure 03--20--5FD SynchronizationFigure 03--20--6Flight Mode AnnunciatorFigure 03--20--7AFCS EICAS IndicationsAUTOPILOTFigure 03--30--1Figure 03--30--2Figure 03--30--3Figure 03--30--4Figure ilot------SchematicGeneralControlsPFD FlagsEICAS MessagesFlight Crew Operating ManualCSP -403--30--603--30--7
AUTOMATIC FLIGHT CONTROL SYSTEMTable of ContentsVol. 1THIS PAGE INTENTIONALLY LEFT BLANKFlight Crew Operating ManualCSP C--013--06703--00--2Sep 09/02
AUTOMATIC FLIGHT CONTROL SYSTEMIntroduction1.Vol. 103--10--1Sep 09/02INTRODUCTIONThe automatic flight control system (AFCS) provides integration of the autopilot and flightdirector systems. The system consists of two interlinked flight control computers, anautopilot, two yaw dampers, automatic elevator trim control and assorted servos andactuators.The flight control computer receives mode selections from the flight control panel and sensorinformation from the air data system, navigation systems, inertial reference system, radioaltimeter and surface position sensors. The flight control computer provides flight guidancecommands to the autopilot. The autopilot provides the control signals to drive the aileronand elevator servos as well as the horizontal stabilizer trim. The flight director providesvisual guidance using a command bar on the attitude director indicator portion of the primaryflight displays. 1025 Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMIntroductionVol. 103--10--2REV 3, May 03/05AUTOFLIGHTINTEGRATEDAVIONICSPROCESSINGSYSTEM (IAPS)AUTOMATICFLIGHT CONTROLSYSTEM (AFCS)FLIGHT DIRECTORAUTOPILOTFLIGHT CONTROLCOMPUTER(FCC) DIAGNOSTICSYAW DAMPERAUTO TRIMCRUISE MODESROLLPITCHHDGALT SELVORALT HOLDFMSCLIMB MODESROLLPITCHHDGVSSPDVORPITCHFMSDESCENT MODESROLLPITCHHDGPITCHVORVSLOCSPDFMSGO--AROUND MODESPITCHROLLHDG10 DEGREESROLL HOLDNOSE UPTAKEOFF MODEROLLPITCHWINGS NOSE UPLEVEL DEGREESVARIES WITHHDGSPEED ANDHOLDFLAP SETTINGAPPROACH MODESROLLPITCHGSLOCVORFMSAuto Flight Systems and Modes --- GeneralFigure 03---10---1Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and Guidance1.Vol. 103--20--1REV 1, Jan 13/03FLIGHT CONTROL AND GUIDANCEIntegration among the various avionics systems is provided by the integrated avionicsprocessing system (IAPS) which is located in the avionics compartment. Two flight controlcomputers (FCCs), mounted inside the IAPS, are the main computers for the automatic flightcontrol system (AFCS). Control logic for the dual flight directors, the two axes autopilot withautomatic pitch trim and the dual yaw dampers is contained in the two FCCs. The FCCs usethe inertial reference system (IRS) and air data computer (ADC) system information tocalculate flight path and control parameters for the AFCS. Other inputs to the flight controlcomputers include selections made on the flight control panel, flight management computeroutputs and radio system outputs. 1025 The flight control panel is the mode selection panel for selecting and controlling the flightdirector and autopilot functions.Autopilot PanelContains switchesto couple, uncouple,transfer control andreduce gains on theautopilot.Flight Control PanelCenter GlareshieldMode IndicatorsWhen a mode switch is pressed,a mode request is sent to theon--side flight control computer.If conditions are within limits, thecomputer acknowledges byilluminating the green lightsadjacent to the mode switch.The primary flight displayindicates the selected mode.Flight Director andCourse Selector PanelsContains switches toselect basic pitch and rollmodes (when not coupled)and set course on primaryflight display.Flight Control Panel --- LayoutFigure 03---20---1Using the flight control panel, the crew can select the following functions:S Remove flight director cues from the primary flight display and revert to basic pitch and rolldisplaysS Set course and fly to the active navigation sourceS Engage, disengage and transfer control of the autopilotFlight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--2REV 1, Jan 13/03S Reduce autopilot gainsS Set and maintain airspeed, vertical speed, and altitudeS Set navigation, heading selection and approach modesA.Flight DirectorThe flight director provides visual guidance, by means of command bars on the attitudedirector indicator, to fly the airplane manually or to visually monitor autopilot response tothe guidance commands. The visual guidance commands (pitch and roll control) areintegrated with the AFCS modes, selected on the flight control panel, for autopilotoperation. AFCS operating modes can be selected to the flight directors with theautopilot disengaged. Pitch (including speed control) and roll guidance cues from theAFCS are displayed on the attitude director indicator portion of the primary flightdisplays.The flight director system provides commands to perform the following:S Hold a desired attitudeS Maintain a pressure altitudeS Hold a vertical speedS Hold a Mach number or indicated airspeedS Capture and maintain a preselected barometric-corrected altitudeS Capture and track a preselected headingS Capture and track a selected navigation source (VOR, LOC, G/S or FMS)S Capture and track a localizer and glideslopeS Maintain a wings-level, fixed pitch-up attitude for takeoff or go-aroundS Provide windshear escape guidanceFlight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--3REV 3, May 03/05FCPFD SYNCSWITCHFD SYNCSWITCHPILOTCONTROL WHEELCOPILOTCONTROL WHEELIAPSPFD 2PFD 1FCC 1FLIGHT DIRECTORFUNCTIONFCC 2FLIGHT DIRECTORFUNCTIONFlight Director --- Schematic 1015 Figure 03---20---2Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--4REV 3, May 03/05Flight directors are simultaneously turned on by either selecting a vertical mode,selecting a lateral mode, or by engaging the autopilot. Flight director selection activatesall flight control mode annunciations and presents steering commands for the selectedmode(s). When both flight directors are turned on, by engaging the autopilot, basicmodes (pitch and roll) are automatically selected. When both flight directors are turnedon, by selecting a vertical or lateral mode, basic modes are automatically selected forthe other axis.Transfer mode controls the routing of flight guidance commands to the autopilot andflight directors. When transfer mode is selected, the copilot’s flight guidance commanddrives both flight directors. When not transferred, the pilot’s flight guidance commanddrives both flight directors.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--5REV 3, May 03/05Flight Control PanelCenter GlareshieldFlight Director(magenta)FDFD Flag (red)Indicates that either thepitch or roll data is invalid.Primary Flight DisplayPilot’s and Copilot’s Instrument PanelsFlight Director --- Controls and Indications 1015 Figure 03---20---3Flight Crew Operating ManualCSP C--013--067
Vol. 1AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceAP ENGXFRSPEEDAPPRHDGNAVALTREV 3, May 03/05DOWNVSCRS2PUSHI R ECTURBSPEED/MHDGPUS HSYACALT1/2 BANKANNCFDSHPUCIASB/CLAP DISCHFDPUSHTECDDIRTCRS103--20--6CEUPFlight Control PanelCenter GlareshieldCourse PointerIndicates position on compass rosethat corresponds to selected course.Color matches navigation source.10Selected Course ReadoutIndicates selected course as set usingcourse knob on flight control panel.Color matches navigation source.10Primary Flight DisplayPilot’s and Copilot’s Instrument PanelsTo / From IndicatorIndicates direction to or from thetuned station or waypoint. Colormatches navigation source.Multifunction Display -- HSI ModePilot’s and Copilot’s Instrument PanelsCross--Side Course Pointer (cyan)Indicates position on compass rose thatcorresponds to cross--side selected course.Displayed when activated by navigationsource knob on display control panel.Course Pointer Control and Indication 1015 Figure 03---20---4Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceB.Vol. 103--20--7REV 3, May 03/05SynchronizationFlight director synchronization is used to set the vertical and/or lateral reference to thecurrent flight value. Selecting synchronization has no effect if the autopilot is engaged.The vertical reference being synchronized is IAS (if in IAS mode), MACH (if in MACHmode), VS (if in VS mode), altitude hold memory (if in altitude hold, CLB or DES mode),or pitch angle memory (if in pitch mode). Overspeed and vertical capture modes arenot affected by synchronization operation. The only lateral references that can besynchronized are the bank and heading memories of roll mode.Synchronization is annunciated with a yellow SYNC on the primary flight display. Themessage will remain for 3 seconds, or until the sync switch is released, whichever islonger.SYNC (yellow)Displayed when flightdirector synchronizationis selected.Flight DirectorSynchronizationSwitch (black)Used when autopilot isnot coupled, tosynchronize verticaland lateral referencesto those currentlyflown.Primary Flight DisplayPilot’s and Copilot’s Instrument PanelsControl WheelRear ViewFD Synchronization 1015 Figure 03---20---5Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceC.Vol. 103--20--8REV 3, May 03/05Flight Mode AnnunciatorFlight mode annunciation is located above the blue (sky) portion of the attitude directorIndicator. The flight mode annunciator presents flight mode information in two fieldsseparated by a vertical cyan line. To the left of the line is the active or captured field(green) and to the right of the line is the armed field (white). The bottom line in each ofthe two fields contains vertical mode information and the upper lines contain lateralinformation.LATERAL CAPTUREOR ACTIVE FIELDLATERAL ARMEDFIELD1/2 BNK10HDGIAS 400LOC1ALTSGS101/2 BANKANNUNCIATIONVERTICAL ARMEDFIELDVERTICAL CAPTUREOR ACTIVE FIELDPrimary Flight DisplayPilot’s and Copilot’s Instrument PanelsFlight Mode Annunciator 1015 Figure 03---20---6Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceD.Vol. 103--20--9REV 3, May 03/05Lateral Modes of Operation(1)Lateral Take-Off ModeLateral take-off mode generates a wings level command while on the ground.After take-off, it generates a heading hold command, with a 5-degree bank limit,using the heading which existed at take-off. Selecting a lateral take-off modeturns on both flight directors, disengages the autopilot and clears all other lateralmodes.Lateral take-off mode is selected by pushing one of the thrust lever-mountedTOGA switches while on the ground. Lateral take-off mode is cleared by theselection of flight director synchronization or another lateral mode.Lateral take-off mode is annunciated with a green TO message in the lateralcapture field on the primary flight display.(2)Navigation ModeNavigation mode generates commands to capture and track a selectednavigation source displayed on the primary flight display. Navigation mode isarmed when selected, but cannot capture if the flight control computer is notreceiving valid navigation data.The capture point is a function of closure rate, with the capture point movingaway from the radial/beam for high closure rates.Navigation capture clears the heading selected. A localizer capture clears halfbank and turbulence modes.Dead reckoning is provided during VOR station passage. When DME data isavailable, dead reckoning region is approximately where the horizontal distanceto the station is less than the altitude to the station. Without DME data, deadreckoning is based on a high rate of VOR deviation.Navigation mode is selected by pushing the NAV switch on the flight controlpanel. Navigation mode is cleared by pushing the NAV switch again, by selectinganother lateral mode or by changing the source of the on-side navigation signal.Navigation mode arming is annunciated with two messages on the primary flightdisplay, a green HDG message in the lateral capture field, and a white navigationsource identifier (VOR1/2, LOC1/2 or FMS1/2) in the lateral arm field.Navigation mode capture/tracking is annunciated with a green message in thelateral capture field on the primary flight display which identifies the navigationsource (VOR1/2, LOC1/2 or FMS1/2). Dead reckoning operation is annunciatedwith a white DR message on the primary flight display.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and Guidance(3)Vol. 103--20--10REV 3, May 03/05Heading Select ModeHeading select mode generates commands to capture and maintain the selecteddigital heading readout and heading bug on the primary flight display. Theselected heading can be changed by rotating the HDG knob (up to 360 degrees)on the flight control panel. Pushing the HDG knob will set the selected headingto the current heading.Heading select mode is selected by pushing the HDG switch on the flight controlpanel. Heading select mode is cleared by pushing HDG switch or by selectinganother lateral mode.Heading select mode is annunciated with a green HDG message in the lateralcapture field.(4)Back Course ModeBack course mode generates commands to capture and track the selected backcourse displayed on the primary flight display. Back course is armed whenselected, but cannot capture if the flight control computer is not receiving validlocalizer data.The capture point is a function of closure rate, with the capture point movingaway from the radial/beam for high closure rates. Back course capture clearsturbulence, half bank and heading modes.Back course mode is selected by pushing the B/C switch on the flight controlpanel. Back course mode is cleared by pushing the B/C switch again, byselecting another lateral mode, or by changing the source of the navigation signalto something other than a localizer.Back course mode arming is annunciated with two messages on the primaryflight display, a green HDG message in the lateral capture field, and a whitenavigation source identifier (B/C 1/2) in the lateral arm field. Back course modecapture/tracking is annunciated with a green message in the lateral capture fieldon the primary flight display which identifies the navigation source (B/C 1/2).Back course steering information is invalidated when the navigation source is nota localizer.(5)Roll ModeRoll mode generates commands to hold the heading that exists when the mode isinitiated, unless the roll angle upon initiation is over 5 degrees (commands arethen generated to hold the roll angle). The roll mode reference is reset to thecurrent heading, or current roll angle, upon autopilot engagement orsynchronization.Roll mode is automatically selected, when no other lateral mode is active, and theflight director is on. Roll mode is cleared by the selection of another lateral mode.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--11REV 3, May 03/05Roll mode is annunciated with a green ROLL message in the lateral capture fieldon the primary flight display.(6)Half Bank ModeHalf bank mode reduces the maximum commanded bank angle to 15 degrees.Half bank mode is selected by pushing the 1/2 BANK switch on the flight controlpanel. Half bank mode is automatically selected when climbing through 31,600feet (pressure altitude) or if the airplane is above the half bank transition altitudewhen the flight director is turned on. Selection is inhibited when in the take-offmode, go-around mode, on-side approach mode capture, or any on-side localizercapture.Half bank mode is manually cleared by pushing the 1/2 BANK switch again, andis automatically cleared when descending through the half bank transitionaltitude.Half bank is annunciated with a white 1/2 BNK message on the primary flightdisplay.(7)Lateral Go-Around ModeLateral go-around mode generates a heading hold command, with a 5 degreebank limit. Selection of lateral go-around mode turns on both flight directors,disengages the autopilot, and clears all other lateral modes. Lateral and verticalgo-around mode selections are coincident. When lateral go-around causes anautopilot disengage, the resultant autopilot disengage warning may be cancelledby another push of a TOGA switch, or by pushing the AP disconnect switch.Lateral go-around mode is selected by pushing one of the thrust lever-mountedTOGA switches while airborne. Lateral go-around mode is cleared by selection ofsynchronization or another lateral mode.Lateral go-around is annunciated with a green GA message in the lateral capturefield on the primary flight display.(8)Approach ModeApproach mode generates commands to capture and track the selectednavigation source displayed on the primary flight display. Tracking performanceis higher, than in navigation mode. Approach mode is armed when selected, butcannot capture if the flight control computer is not receiving valid navigation data.The capture point is a function of closure rate, with the capture point movingaway from the radial/beam for high closure rates.If the other side does not concurrently capture, it will continue to operate inheading select, until it independently captures.Approach mode may automatically select glideslope mode. An on-side localizercapture clears turbulence mode on both sides.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--12REV 3, May 03/05Dead reckoning is provided during VOR station passage. When DME data isavailable, dead reckoning region is where DME distance to the station is less than0.6 nautical mile (DME). Without DME data, dead reckoning is based on a highrate of VOR deviation.Approach mode is selected by pushing the APPR switch on the flight controlpanel. Approach mode is cleared by pushing the APPR switch again, byselecting another lateral mode, or by changing the source of the on-sidenavigation signal.Approach mode arming is annunciated with two messages on the primary flightdisplay, a green HDG message in the lateral capture field, and a white navigationsource identifier (VOR1/2, LOC1/2 or FMS1/2) in the lateral arm field. Approachmode capture/tracking is annunciated with a green message in the lateral capturefield on the primary flight display which identifies the navigation source (VOR1/2,LOC1/2 or FMS1/2). Dead reckoning operation is annunciated with a white DRmessage on the primary flight display.E.Vertical Mode of Operation(1)Vertical Take-Off ModeVertical take-off mode generates a variable fixed pitch-up command dependanton flap setting for takeoff and the spread between V2 and Vr. Loss of an enginereduces the pitch-up command.Selecting vertical mode turns on both flight directors, disengages the autopilot,clears all other vertical modes and switches the flight guidance commands to adual independent configuration. Lateral and vertical take-off mode selections arecoincident.When take-off causes an autopilot disengagement, the resultant warning may becancelled by another push of a TOGA switch, or by pushing the autopilotdisconnect switch.Vertical take-off mode is selected by pushing one of the thrust lever-mountedTOGA switches while on the ground. Vertical take-off mode is cleared byengaging the autopilot, by selecting synchronization, or by the selection orcapture of another active mode.Vertical take-off mode is annunciated with a green TO message in the verticalcapture field on the primary flight display.(2)Pitch ModeWhen pitch mode is selected, the pitch reference (pitch command on the primaryflight display) is set to the current pitch angle. Pitch mode generates commandsto maintain the pitch reference value.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--13REV 3, May 03/05The pitch reference value can be changed using the VS pitch wheel. Rotation ofthe VS pitch wheel will change the pitch reference by 1/2 degree per click. Thepitch reference is reset to the current pitch attitude upon either autopilotengagement, transferring to pitch mode, or synchronization.When the preselected altitude is captured, rotating the VS pitch wheel alsorearms the altitude preselect mode.When capturing or tracking a preselected altitude, a new preselected altitudemust be chosen prior to the selection of pitch mode, to avoid an immediaterecapture of the existing preselected altitude.Pitch mode is automatically selected when no other vertical mode is active, andthe flight director is on. Rotating the VS pitch wheel on the flight control panel willmanually select pitch mode when the flight director is on, unless in glideslopecapture or VS mode. Pitch mode is cleared by the selection of a vertical holdmode, or by a vertical mode capture.Pitch mode is annunciated with a green PTCH message in the vertical capturefield on the primary flight display.(3)Altitude Hold ModeAltitude hold mode generates commands to capture and maintain the altitudereference. When altitude hold mode is selected, the altitude reference is set tothe current pressure altitude.The altitude reference is reset to current pressure altitude by selection ofsynchronization. There is no display of altitude reference value.Altitude hold mode is selected by pushing the ALT switch on the flight controlpanel, or by changing the altitude preselect setting while in altitude preselectedtrack. Selection is inhibited when in glideslope capture or overspeed.Altitude hold mode is cleared by pushing the ALT switch again, by selection of avertical hold mode, or by vertical mode capture.Altitude hold mode is annunciated with a green ALT message in the verticalcapture field on the primary flight display.(4)Altitude Preselect ModeAltitude preselect mode generates commands to capture and track preselectedaltitudes. The barometric preselected altitude is displayed on the primary flightdisplay, and controlled via the ALT knob on the flight control panel.Altitude preselect mode is armed upon selection. The capture point is a functionof closure rate, with the capture point moving away from the preselected altitudefor high closure rates.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--14REV 3, May 03/05During altitude capture (within 200 ft of the preselect altitude), if the preselectedaltitude is changed or if the VS pitch wheel is rotated, the autopilot or flightdirector will continue to capture the original preselected altitude.If a new preselect altitude is not set, then selection of IAS, MACH, PTCH or VSmode, will result in the current altitude being captured.After capturing preselected altitude (altitude track), if preselect altitude ischanged, altitude hold is automatically selected and altitude preselect rearmed.Pushing in the ALT knob will cancel aural and visual alerts associated with thepreselected altitude.Altitude preselect mode is automatically selected upon selection of any verticalmode, except glideslope capture or overspeed. Altitude preselect mode iscleared by glideslope capture or overspeed.Altitude preselect is annunciated on the primary flight display with a white ALTSmessage in the vertical arm field for arm; a green ALTS CAP message in thevertical capture field for capture, and a green ALTS message in the verticalcapture field for track. Altitude captures, which are cleared without a subsequentselection of altitude track or arm, are annunciated with a yellow ALTS message onthe primary flight display, which will remain for 10 seconds, or until altitudepreselect is rearmed, whichever is shorter.(5)Speed Mode (CLB, DES, IAS)Speed mode generates commands to maintain the airspeed reference value.When speed mode is selected, the IAS reference (primary flight display) is set tothe current airspeed.The airspeed reference can be manually set, using the speed knob. The airspeedreference is reset to current airspeed by the selection of autopilot engagement orsynchronization.Upon altitude capture, (selected altitude), speed mode is disabled.Speed mode is displayed in either IAS CLB or DES. Selection of the speedreadout is accomplished by pushing the SPEED knob on the flight control panel.In DES mode, if a large reduction in target airspeed is commanded withsimultaneous spoiler deployment, the autopilot may enter a Pitch Holdsub---mode (no annuciation of Pitch Hold sub---mode is provided). Pitch Holdsub---mode was designed to maintain a constant pitch attitude as a means ofdecelerating to the new target airspeed without sacrificing rate of decent orpassenger comfort. The only indication that the autopilot has entered Pitch Holdsub---mode is that the airspeed is not decreasing and stays well above the targetairspeed. In DES mode, if the airspeed is not decreasing, the Pilot can eitherdisconnect the autopilot and assume manual control, or select another verticalmode such as VS or PTCH and adjust the vertical speed or pitch as required toresume deceleration to the target airspeed.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and Guidance(6)Vol. 103--20--15REV 3, May 03/05Vertical Speed ModeVertical speed mode generates commands to maintain the VS reference value.When vertical speed mode is selected, the VS reference (primary flight display) isset to the current vertical speed.The VS reference value can be changed, throughout a 12,000 feet/minute range,using the VS pitch wheel on the flight control panel. The VS reference is reset tothe current vertical speed by the selection of autopilot engagement orsynchronization.When capturing or tracking a preselected altitude, a new preselected altitudemust be chosen prior to selection of vertical speed mode, to avoid an immediaterecapture of existing preselected altitude.Vertical speed mode is manually selected by pushing the VS switch on the flightcontrol panel. Selection is inhibited when in glideslope capture or overspeed.Vertical speed mode is cleared by pushing the VS switch again, by selecting avertical hold mode, or by a vertical mode capture.Vertical speed mode is annunciated with a green VS #.# or VS #.# in thevertical capture field on the primary flight display. The #.# is the VS referencevalue, in thousands of feet/minute (values over 10,000 feet/minute are displayedwithout a decimal point). The up arrow displays a positive reference and thedown arrow displays a negative reference.The flight control computer operates in the active mode. Capture will not occur ifthe localizer is not captured, or if the flight control computer is not receiving validglideslope data. Upon glideslope capture, other vertical modes are automaticallycleared on the captured side. If the other side does not concurrently capture theglideslope, it will continue to operate in the current active vertical mode, orensuing vertical mode, until it independently captures glideslope.Climb or descent rate is achieved by moving the rotary switch on the flight controlpanel.(7)Glideslope ModeGlideslope mode will generate commands to capture and track the glideslope.Captures can be performed from above or below the beam.The capture point is a function of closure rate, with the capture point movingaway from the beam for high closure rates.Glideslope mode is automatically selected when in an approach mode, inbound,with a valid localizer as the lateral navigation source. Glideslope mode isautomatically cleared by the loss of approach mode. When armed, glideslopemode is also cleared by turning outbound, or by the loss of a valid localizer as thelateral navigation source. When captured, glideslope mode is cleared bychanging the source of the lateral navigation signal to an invalid localizer.Flight Crew Operating ManualCSP C--013--067
AUTOMATIC FLIGHT CONTROL SYSTEMFlight Control and GuidanceVol. 103--20--16REV 3, May 03/05Glideslope arming is annunciated with a white GS message in the vertical armfield on the primary flight display. Glideslope capture is annunciated with a greenGS message in the vertical capture field on the primary flight display.(8)Vertical Go-Around ModeGo-around mode generates a fixed pitch-up command, the value depending onwhether both engines are operating or if one engine is inoperative (OEI).Selection of vertical go-around mode turns on both flight directors, disengagesthe autopilot, clears all other vertical modes and switches the flight guidancecommands to a dual-independent configuration. Vertical and lateral modescoincide.When a go-around causes the autopilot to disengage, the autopilot warning canbe cancelled by another push to the TOGA switch, or by pushing the autopilotdisconnect switch.Vertical go-around mode is selected by pushing either one of the thrustlever-mounted TOGA switches while airbor
AUTOMATIC FLIGHT CONTROL SYSTEM Flight Control and Guidance REV3,May03/05 Flight Crew Operating Manual CSP C--013--067 Course Pointer Control and Indication 1015 Figure 03---20---4 10 10 Primary Flight Display Pilot’s and Copilot’s Instrument Panels Flight Control Panel Center
Part One: Heir of Ash Chapter 1 Chapter 2 Chapter 3 Chapter 4 Chapter 5 Chapter 6 Chapter 7 Chapter 8 Chapter 9 Chapter 10 Chapter 11 Chapter 12 Chapter 13 Chapter 14 Chapter 15 Chapter 16 Chapter 17 Chapter 18 Chapter 19 Chapter 20 Chapter 21 Chapter 22 Chapter 23 Chapter 24 Chapter 25 Chapter 26 Chapter 27 Chapter 28 Chapter 29 Chapter 30 .
TO KILL A MOCKINGBIRD. Contents Dedication Epigraph Part One Chapter 1 Chapter 2 Chapter 3 Chapter 4 Chapter 5 Chapter 6 Chapter 7 Chapter 8 Chapter 9 Chapter 10 Chapter 11 Part Two Chapter 12 Chapter 13 Chapter 14 Chapter 15 Chapter 16 Chapter 17 Chapter 18. Chapter 19 Chapter 20 Chapter 21 Chapter 22 Chapter 23 Chapter 24 Chapter 25 Chapter 26
DEDICATION PART ONE Chapter 1 Chapter 2 Chapter 3 Chapter 4 Chapter 5 Chapter 6 Chapter 7 Chapter 8 Chapter 9 Chapter 10 Chapter 11 PART TWO Chapter 12 Chapter 13 Chapter 14 Chapter 15 Chapter 16 Chapter 17 Chapter 18 Chapter 19 Chapter 20 Chapter 21 Chapter 22 Chapter 23 .
Flight Operation Quality Assurance (FOQA) programs are today customary among major . EASA European Aviation Safety Agency F/D Flight Director . FAF Final Approach and Fix point FCOM Flight Crew Operating Manual FCTM Flight Crew Training Manual FDAP Flight Data Analysis Program FDM Flight Data Monitoring FLCH Flight Level Change FMC Flight .
Using ASA’s Flight Planner A flight log is an important part in the preparation for a safe flight. The flight log is needed during flight to check your groundspeed and monitor flight progress to ensure you are staying on course. The Flight Planner has two sections; the Preflight side is used for pre-
automatic flight control system. Thus, manufacturers develop and make available a wide range of complementary systems, the basic principles of which have also been included in this book. Chapter IO deals with what may be termed the ultimate in automatic flight control evolution, namely automatic landing and autothrottle systems.
‘757 Captain’ Sim FLIGHT MANUAL Part III – Normal Procedures DO NOT USE FOR FLIGHT AMPLIFIED PROCEDURES EXTERIOR INSPECTION Prior to each flight, a flight crew member or the maintenance crew must verify the airplane is acceptable for flight. Check: - Flight control surfaces unobstructed and all surfaces clear of ice, snow, or frost.
AS 8 PROTEIN SYNTHESIS QUESTIONSHEET 10 (b) (i) genetic code on DNA is copied into mRNA; double helix of DNA unwinds (in region to be copied); complementary nucleotides line up along coding strand of DNA; A to U and C to G; assemble together to make a complementary strand of mRNA; under influence of RNA polymerase; mRNA unzips from DNA template and passes to ribosomes; max 5 (ii) ATP provides .
