CHAPTER 3

AUTOMATIC FLIGHT

Page

TABLE OF CONTENTS 03-00-01/02

DESCRIPTION

General 03-10-01

Description 03-10-01

Controls and Indicators 03-10-10

COMPONENTS (Not Used)

CONTROLS AND INDICATORS 03-30-01

FUNCTIONAL SCHEMATICS

System Interface 03-40-01/02

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AUTOMATIC FLIGHT

GENERAL

The design of the DC-10 flight gui-dance system (FGS) provides thecapability for automatically control-led flight during climb, cruise, andletdown to a Cat III landing and, ifrequired, a go-around. The automaticflight system is an integral part ofthe airplane. Control is centralizedat the FGS panel on the glareshield.

The contributing components aresignal source sensors, computers,cockpit displays, flight controls,and allied subsystems. The guidancesystem utilizes the output of theautothrottle computers, the flightguidance computers and when installed,the performance management system(PMS) computer. Displays, in theform of commands, appear on theattitude director indicators (ADI's).The flight controls used in automaticflight are the ailerons, rudders,elevators, horizontal stabilizer, andspoilers. The throttles are control-led by the automatic throttle system(ATS).

Automatic flight capabilities includecontrol wheel steering, turn coor-dination, vertical speed control,automatic pitch trim, altitudepreselect, altitude hold, Mach hold,IAS hold, heading select, headinghold, VOR tracking, INS tracking(when installed), ILS (localizer andglideslope) tracking, automaticlanding, go-around, turbulencepenetration control and performancemanagement (when installed). Manualoverride is possible at all times.

DEFINITIONS

Fail Operational - A system whichprovides redundant operationalcapability using two (or possiblymore) automatic systems. If one ofthe automatic systems fails below thealert height, the flare and touchdownmay be accomplished using the remain-ing automatic system.

Fail Passive - An automatic flightcontrol system which, upon occurrenceof any failure not shown to beextremely improbable, is protectedagainst hardovers, leaves the air-plane in trim, causes a warningsignal and does not interfere withthe pilot's normal control of theairplane.

DESCRIPTION

SENSORS

The sensors consist of compass system,INS platforms (when installed) orvertical gyros, yaw rate gyros,central air data computers, radioaltimeters, accelerometers, VHF NAVreceivers, surface position sensorsand angle-of-attack transducers.

FLIGHT GUIDANCE COMPUTERS

Within the guidance group are twoindependent guidance systems eachreceiving individual sensor inputsand each capable of providing thefull spectrum of guidance signals.Within each system are three guidancecomputers (roll, pitch, and yaw),

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each of which has dual channels forselected functions. Together withother system redundancies, the dualsystems permit positive flightcontrol even if portions of thesystem are not operative. Incorpo-rated in the two independent systemsare four separate yaw damper systems,two separate flight director systems,two separate autopilot systems duringcruise, and four separate autopilotsystems during dual automatic landing.This permits autoflight operationduring cruise if only one guidancesystem (one yaw damper system and oneautopilot system) is operative.

During an automatic landing, programlogic inhibits land mode selectionunless all of the preset conditionshave been satisfied. Dual land, forexample, cannot be implemented withonly one operative autopilot. How-ever, any one computer (or certainother components) which fails duringa dual land sequence will disconnectautomatically without disruption ofthe landing sequence. The landingwill continue but the mode willchange to single land.

Each integrated autopilot/flightdirector system provides simultaneousand parallel outputs to its asso-ciated control surfaces and ADI.Flight director outputs are reflectedin pitch and roll commands on theADI. Autopilot outputs result incontrol surface displacement.

FLIGHT DIRECTOR (FD)

The flight director provides visualguidance to the pilot to either flythe computed flight path manually orto visually monitor autopilotresponse to the guidance signals.The ADI is the display member of theflight director system and functions

as the focal point for visual com-mands generated by the flight direc-tor circuitry in the guidancecomputers.

Roll, pitch, yaw, and autothrottle/speed control data from the inte-grated autopilot/flight directorsystem and speed control computersare displayed. Command bars (pitchand roll) on the face of the ADIdirect the pilot to turn, climb, ordescend. A Fast/Slow indicator (onADI) reflects current speed inrelation to the speed selection onthe ATS control panel, the computedsafe speed (ALPHA SPD), the takeoff/go-around speeds or the target speedcomputed by the PMS. Flight directorcapabilities can be utilized with theautopilot either disengaged (OFF) orengaged in the CWS (control wheelsteering) mode. Either flight direc-tor can be engaged by moving theassociated FD switch to the FD posi-tion. The basic engagement mode ofthe flight director system is HDGHOLD and ALT HOLD (or VERT SPD).With the flight director engaged,the command bars are indicating aresponse is required whenever eitheris displaced from the center position.In the autopilot CMD (command) mode,the command bars will be monitoringautopilot operation. If the CWSpushbutton mode is selected with aflight director ON and the AP leverin the CMD position, the flightdirector command bars on the ADIremain in view and display thecommands for the mode which waspreviously engaged. The autopilotoperates in the CWS mode.

When an autopilot lever is moved tothe CMD position with a flightdirector mode conflict, the ADIcommand bars of the system that is inconflict will be removed from view.

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Aug 1/82

AUTOMATIC THROTTLE AND SPEED CONTROLSYSTEM

The Flight Guidance System includesan Automatic Throttle and SpeedControl System. Speed Control isprovided from lift off to landing andautomatic throttle can be used duringthe takeoff and throughout flight tolanding. The Automatic ThrottleSystem is independent of the inte-grated autopilot/flight directorsystem and is designed for use in allphases of flight except reversethrust and final roll-out.

Speed Control System (SCS)

The dual Speed Control System pro-vides signals for the flight direc-tors, the ADI fast/slow indicators,and the Automatic Throttle System."Speed Guidance" signals for attitudecontrol are displayed by the FD pitchcommand bars during takeoff andgo-around. "Speed Control" signalsfor throttle control, both manual andautothrottle, are displayed by theADI fast/slow indicators.

During "Speed Guidance" operation,thrust is controlled to the selectedEPR limit either manually or by theATS, and the FD pitch command barsprovide attitude commands to maintaina computed Takeoff /go-around speed.

In the takeoff (TO) and go-around(G/A) modes, "Speed Guidance" appearsas FD pitch commands to maintain V2 +10 knots for three engine operationand V2 for two engine operation. Thefast/slow indicators will display theairspeed error between the computedspeed and the actual speed. Thrustis set by the flight crew or the ATSwhile the EPR limit is displayed bythe EPR LIM readout on the thrustrating computer (TRC) indicator.

If the ATS is operating in the SPD(speed) mode at the time of go-aroundmode engagement, it switches to theEPR mode and will control to the G/AEPR limit displayed. If the ATS isengaged during go-around mode opera-tion, it will engage directly intothe EPR mode and control thrust tothe G/A EPR limit.

During "Speed Control", verticalspeed is controlled by the pilot orautopilot and airspeed is controlledby manual or ATS adjustment ofthrottle positions.

The SPD mode provides "Speed Control"signals to the ADI fast/slow indi-cators to command the pilot or ATS toadjust the throttles to maintain thehigher reference speed of either thesafe stall margin speed (ALPHA SPD)or the airspeed selected on the ATScontrol panel. The pilot can selectany desired airspeed but the "SpeedControl" signals are limited toprevent commands which exceed flapdesign speeds and to prevent commandslower than safe stall margin speed.

Automatic Throttle System (ATS)

The Automatic Throttle System posi-tions the throttles to maintain theairspeed or thrust level as definedfor the operational mode and airplaneconfiguration. The system is engagedby moving the ATS lever to the ONposition. The lever will not moveout of OFF position until all inter-locks and engage requirements aresatisfied and will automaticallyrevert to the OFF position if systemmonitors detect a malfunction.

The ATS is disengaged by pushingeither ATS disengage button on throt-tles 1 or 3, moving the throttlesinto reverse thrust, or moving the

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ATS lever to OFF. A red ATS faillight on each instrument panel comeson flashing if the ATS is disengagedby any means, except when the thrustlevers are reversed after landingwith LAND mode engaged. If one ATSis disengaged with the other ATSengaged, the associated amber faillight will come on. With DUAL LANDmode operative, the ATS amber faillights are inhibited at 100 feetradio altitude.

When the ATS is engaged and on theground (nosewheel strut compressedfor more than 20 seconds), the servobrake will clamp the throttle servooutput shaft and automatic movementof the throttles cannot occur. TheATS SPD mode cannot be engaged on theground (except for test). The ATSEPR mode or normal manual throttleoperation is available. Placing theSPEED CONT TEST selector in FAST orSLO position will cause the servobrake to release (ATS SPD mode willengage and be displayed in the ATSflight mode annunciators), and allowautothrottle operation for mainten-ance. If the ATS EPR mode is engagedto set takeoff thrust, the servobrake will damp the servo outputshaft when the airspeed reachesapproximately 80 knots and CLAMP willbe displayed in the ATS flight modeannunciators. The servo brake can bereleased in flight by pushing the EPRswitch or pulling the SPD select knobon the ATS control panel.

The SPD mode is the basic ATS mode ofoperation. In this mode the throt-tles seek and maintain the airspeedselected on the ATS control panel.SPD is displayed in both ATS flightmode annunciators (FMA's) when theATS is in the SPD mode.

There are limits on the ATS operationwhich prevent over-boosting engines,prevent airspeeds below a safe marginabove stall, and prevent commands in

excess of flap design speeds. Thereis no annunciation when throttletravel is restricted by EPR limit orflap limit speed. However, when thethrottles stop at the thrust settingto provide the safe stall marginspeed, the ATS flight mode annun-ciators will display ALPHA SPD.Minimum authority limit switchesrestrict throttle travel in the lowEPR regions.

The EPR mode of operation controlsthe throttles to maintain the EPRdisplayed by the EPR LIM readout onthe TRC indicator. In the event of afailure of the thrust rating computer,the ATS will disengage if it is inthe EPR mode and a flag will coverthe EPR LIM readout.

If the thrust rating computer fails,SPD mode is still available but thepilot must manually set the EPR com-mand bug on the EPR gage. When thethrust rating computer is valid, thelogic signals from the EPR gages areoverridden internally to AT/SC com-puter and ATS operation is limitedto not exceed the EPR limit on theTRC indicator.

The ALPHA SPD mode is automaticallyselected when the ATS is engaged inthe SPD mode and the selected air-speed is lower than the safe stallmargin speed.

The ATS may be manually overriddenat anytime by the flight crew. Ifall throttles are overridden simul-taneously and then released, theATS will readjust the throttles tomaintain the selected speed or N1limit except for minor adjustments.One throttle may be manually overrid-den and when released it will main-tain its relative position to theother throttles until repositionedmanually or throttles are closedautomatically.

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May 1/83

CONTROLLABILITY WITH ALLENGINE FLAMEOUT

EMER POWER Switch ON C

OVRD & AIR START Switch OVRD & AIR START C

NOTE

EGT's decreasing (below normal) confirms engineflameout. If EGT's are normal/ refer to Emer-gency Procedures, LOSS OF ALL GENERATORS.

ADG RELEASE Handle RELEASED F/E

ADG Switch HYD C

NOTES

With ADG as the sole hydraulic power source,trim with longitudinal trim handles. Usesparingly and for short periods.

If gear extension is required while engine-driven hydraulic pumps are off, use alternategear extension lever to extend the gear.

CAB PRESS MAN/AUTO Handle MAN F/E

OUTFLOW VALVE Position Indicator . CLOSED F/E

Push in and rotate manual cabin altitude control downwarduntil outflow valve position indicator is at the closedposition.

ENG 1 and 3 HYD PUMP Switches OFF F/E

(Continued)

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Each of the two autopilot systems has dualchannels identified as A and B. Channel Aprovides computations for all cruise modes inaddition to approach and landing. Channel Bautomatically augments channel A forapproach and landing when both localizer andglide slope are being tracked and the LANDmode has been selected.

If one autopilot fails and disengages during aDUAL LAND approach, one half of the avail-able channels will be utilized and the modeannunciation will change to SNGL LAND.The landing will continue under the SNGLLAND mode.

An autopilot engaged in CMD will not dis-engage if its respective hydraulic systemshould fail except during LAND mode.Failure of an autopilot's respective hydraulicsystem, while in the LAND mode, will causethe engaged autopilot to disengage and theAP lever to drop to OFF.

PERFORMANCE MANAGEMENTSYSTEM

The Performance Management System (PMS)operates as a fully integrated selectable modeof the flight guidance system. The PMSprovides automatic control and coordinationof pitch attitude and thrust during climb,cruise, and descent phases of flight. In addi-tion, PMS waypoint control provides mastercontrol of inertial navigation system positionupdating and flight plan by automatic controland coordination of pitch attitude, thrust, ver-tical navigation and horizontal navigation.The PMS provides efficient fuel usage or costefficiency within the constraints of com-manded flight plan, attitude clearance limits,and airplane performance limits. The PMSoptimizes the entire flight profile by makingcontinuous limits. The PMS optimizes the

entire flight profile by making continuouschanges in that profile when up to date dataare obtained and considers the entire remain-ing flight when new data are inputed. Alsoprovides an advisory display of numerousflight parameters on a full time real time basis.The parameters and other functional data ontime, distance, and fuel remaining are derivedfrom continuous and automatic inputs fromother systems and from manually inputteddata.

The PMS controls pitch attitude and thrust ineach of several submodes within each flightmode (climb, cruise, and descent).

The climb mode can be operated in:

1. Optimum submode for minimum tripcost.

2. Maximum submode for maximum climbangle.

3. Non-optimum submode for manuallyselected climb speed (IAS and/or Mach).

The cruise mode can be operated in:

1. Optimum submode for minimum tripcost.

2. Non-optimum submode for manuallyselected cruise speed (IAS or Mach).

3. Hold endurance mode.

The descent mode can be operated in:

1. Optimum submode for minimum tripcost. Throttles at idle.

2. Non-optimum submode for manuallyselected Mach/IAS descent.

3. Non-optimum submode for manuallyselected descent/vertical speed.

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PMS consists of a PMS Computer Unit(PMCU), a PMS Control Display Unit(CDU), a PMS switching Unit, and PMSadvisory lights. The PCU providesinformation to the CDU for messageand data displays and to the PMSswitching unit for interface withother systems. The PCU is programedto compute a cost efficient flightprofile, while considering fuel andtime costs, airplane performance, andmanual inputs. It also processesdata for input to the FGS and fordisplay. The computer programcontains airplane performance char-acteristics (i.e., speed envelope,lift, drag), engine limits, andairplane maximum and minimum speeds(including flap placard speeds) forall flight modes. Based upon pro-grammed limits, the PCU providesautomatic protection against engineoverboost, overspeed, and minimumspeed. Both PMS hardware and soft-ware self-tests are continuallyperformed to insure that PMS inputsare valid, computer operation isnormal and computer outputs arevalid. When a failure is detected,warning flags, warning annunciations,advisory messages and malfunctionmessages are provided. The PMSautomatically releases control of theautothrottles, autopilot, flightdirector and navigation system when adetected failure will cause impropercontrol of those systems. Data inputreasonableness tests are included inthe computer program. The reasonable-ness tests applied to input datainclude the following:

1. Comparison of entered GrossWeight (GWT) to airplane maximumand minimum limits.

2. Comparison of entered fuel tomaximum limit and GWT minus (-)zero fuel weight.

3. Comparison of computed Bottom ofDescent (BOD) GWT and maximum GWTfor landing.

4. Computed BOD fuel weight less than15,000 or greater than maximum forairplane type.

Failure of these reasonableness testswill cause messages to appear in theCDU. Messages will continue to bedisplayed in CDU until a new entryhas been made or the message iscleared. An automatic longitudinalspeed restriction of 250 knots forall altitudes below 10,000 feet arealso included in the computer program.The speed restriction can be manuallyoverridden using the CDU. PMS soft-ware provides data protection sothat all necessary data is retainedin the event that power to the PMS islost and regained during flight.

The PMS switching unit interfaces thePMS with the pitch computer, auto-throttle system, and flight modeannunciators. The PMS advisorylights indicate that a message isbeing displayed on the CDU or that avertical leg change is imminent.Automatic system mode selection isprovided so that when the PERF modeis selected on the FGS panel, the PMSwill engage into the appropriateclimb, cruise, or descent mode ofoperation. The PMS will use presentvertical speed and the currentaltitude with respect to the selectedor armed altitude to determine thecurrent flight regime. For example,if PERF mode is selected duringclimb, the PMS will automatically andsmoothly provide climb power controland pitch control to the selectedaltitude. At the selected altitudethe PMS will accomplish a smoothtransition from climb to cruise. Theclimb or cruise mode which will be

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entered is the currently armed mode with adefault to optimum. Once in a cruise mode,the PMS will not leave the current altitude toclimb or descend until the new altitude hasbeen armed and the mode change com-manded by the pilot.

The CDU accepts data and command entriesand displays mode, planning, performance,navigation, and status information necessaryfor operation of the PMS. The displays alsoprovide messages to direct flight crew actionwhen needed. The general structure of aCDU data display page is applicable to alldisplay pages. The top line (not numbered) isused as a combination page title/scratchpadline. The remaining three numbered lines areused for data entry and display or in conjunc-tion with line select keys for call up of sub-pages (expansion of information on a givenline). Page title relates the displayed page tothe function key calling up that page. Alert/advisory messages appear in the scratchpadarea. Data entered will first be displayed inthe scratchpad.

When appropriate line select key is pushed,data will be transferred to the left side of theselected data line. If data is to be transferredto the right side of the selected data line, theslash (/) data entry key must be pushed beforeentering data into the scratchpad. All dataentries are loaded in the scratchpad from leftto right. Data entries of more than 12 charac-ters (i.e., position latitude and longitude) areaccommodated by an automatic shift of thefirst 12 characters one space to the left foreach additional character entered, thus spill-ing into the page title area. Data loading haspriority over other display information or alert/

advisory messages which may be displayedwhen data loading is initiated.

PMS interpretation of data entries is as fol-lows:

1. When using the first planning page thePMS interprets gross weight and fuelweight entries as follows:

a. Three to six numeric charactersentered with a decimal point isdisplayed on a data line roundedto the nearest thousand pounds(KLB).

b. Two or three numeric charactersentered without a decimal point isdisplayed on a data line asentered.

c. Five to six numeric charactersentered without a decimal point isdisplayed on a data line roundedto nearest (KLB).

2. Distance (ground distance) entries areentered to nearest nautical mile (NM).

3. When using the second planning page,cruise altitudes are displayed on a dataline in flight level (FL) format, separatedby a slash (/) as necessary. Altitudesbelow 18,000 feet can also be enteredin feet for short range flights. The PMSinterprets cruise altitude entries as fol-lows:

a. Three or less numeric charactersentered is interpreted as an entryto the nearest 100 feet.

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Jun 1/97

b. Four or five numeric char-acters entered is interpretedas an entry to the nearestfoot.

c. Entries of either type willbe displayed on a data linein FL format rounded to thenearest 100 feet.

4. When using climb pages the PMSinterprets speed entries asfollows:

a. A maximum of three numericcharacters are permitted andcan be preceded by a decimalpoint.

b. If the first characterentered is a number l,2,3, or4, the entry is interpretedas indicated airspeed (IAS).If first character entered iseither a decimal point or anumber greater than four, theentry is interpreted as aMach number. The data linedisplay will be padded with atrailing "0" to display twonumeric characters for asingle numeric characterentry.

For display selection, any displaypage can be called up at any timewith one exception. During preflightand prior to entering GWT, the climb,

cruise, and descent pages cannot bedisplayed. In addition, informationavailable to the PMS at its interfaceis used to provide automatic displaypage selection as follows:

1. Selects first planning page uponlanding and all engines are shutdown.

2. Selects cruise page when armedclearance altitude is reachedduring climb or descent in PMS.

3. Selects climb or descent pagewhen in PMS cruise and a newclearance altitude is armed.

ALTITUDE ADVISORY SYSTEM

The altitude advisory system automat-ically alerts the flight crew thatthe airplane is approaching thepre-selected altitude or that it isdeviating from a previously selectedand acquired altitude. The system isindependent of either flight directoror autopilot systems. An aural toneand an amber advisory light providethe alert stimuli.

An altitude selected with thealtitude preselect knob on the pitchcontrol panel will be directed toboth pitch computers. A steady amberadvisory light on the altimeter willcome on and a momentary aural tonewill sound at the altitude advisory

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threshold. If vertical speed is lessthan 3750 fpm, the altitude advisorythreshold is 750 feet (minimum) fromthe selected altitude. If verticalspeed is 3750 fpm or greater, thealtitude advisory threshold will varyas a function of vertical speed(approximately 200 feet increase foreach additional 1000 fpm of verticalspeed). For example, if verticalspeed is 4750 fpm, the steady amberlight on the altimeter will come onand the momentary aural tone willsound 950 feet from the selectedaltitude. Within 250 feet of theselected altitude, the amber advisorylight will go off. If subsequentdeviations are more than 250 feetfrom the selected altitude, the amberadvisory light will flash and themomentary aural tone will sound.Pushing the altitude advisory RESETbutton will turn off the flashingaltitude advisory light and reset thealtitude advisory system to monitorsubsequent deviations of 250 feet ormore from selected altitude.

PERFORMANCE AND FAILURE ASSESSMENTMONITOR (PAFAM)

NOTE

Operation of the PAFAM in the ILSmode is applicable only to thoseairplanes with PAFAM ILS modeactivated by Service Bulletin22-88 or production equivalent.

PAFAM is an integral part of theautomatic landing system. Thisinstrument provides an added levelof confidence to the autolandmaneuver by independently checkingperformance levels and registeringa warning if necessary. PAFAM alsoadvises on the probable success ofthe proposed landing by predictingthe touchdown point on a symbolic

runway. Uncertainty in the predic-tion is reflected in the length ofthe touchdown predictor vectors(crossed lines).

With LAND or ILS mode selected thePAFAM is energized when LOC TRK modeengages. PAFAM will automaticallyshut down 12 minutes after beingenergized above 1000 feet radioaltitude and can be re-energized bypushing the LAND or ILS switch. Justafter glideslope track, during thepre-land test, the PAFAM test patternshould be displayed and after thetest period, the normal PAFAM displayshould appear.

Additional displays can occur whenevents deviate from normal operation.With LAND mode selected, TAKEOVERwill be displayed on the PAFAM mon-itor when a system malfunctions orthe airplane performance will resultin a landing that is not in theacceptable touchdown zone. Inconjunction with the TAKEOVER display,an arrow will point to the side ofthe cockpit which contains equipmentmost capable of performing a success-ful go-around. If both sides arecapable of making the go-around, botharrows will appear. TAKEOVER mode ofthe PAFAM is inhibited in the ILSmode of operation except for the NOTRACK takeover condition describedbelow.

NO TRACK will be displayed on thePAFAM monitor below 600 feet radioaltitude and the autopilot has notgone into the LOC TRK and GS TRKmode. After NO TRACK has beendisplayed for 2 minutes, the PAFAMwill shut down. If radio altitudedecreases to 300 feet or below, theNO TRACK display will be replaced byTAKEOVER display.

The flashing NO ILS display occurswhen a normal approach is initiated

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Aug 1/82

and the localizer and/or glideslopesignal is removed for more than 1/2second. With LAND mode selected, ifthe signal is not restored withinapproximately 3 seconds, the NO ILSdisplay will be replaced by theTAKEOVER display. If the signal isrestored within the 3 seconds, thenormal display will reappear. If thesignal is not restored within 5seconds or if excessive deteriorationof performance is detected, theautopilots will disengage from CMDand the AP levers will drop to OFF.With ILS mode selected, the autopilotwill disengage when the NO ILSdisplay occurs. The normal displaywill reappear if the signal isrestored.

PAFAM will be operative during DualLand, Single Land, or ILS approach.During a Dual Land or Single Landapproach, PAFAM will automaticallyshut down shortly after touchdown.

During an ILS approach, PAFAM willautomatically shut down at 100 feetradio altitude.

The PAFAM can be tested on the groundby pushing the LAND switch. Afterapproximately 30 seconds warmup,TAKEOFF and both arrows will bedisplayed for a short period and thenthe system will shut down.

CONTROLS AND INDICATORS

Controls and indicators associatedwith automatic flight are on the over-head panel, glareshield, controlwheel, pedestal, center instrumentpanel, and the Captain's and FirstOfficer's instrument panels.Illustrations of these major panelsare in Chapter 1. Individual con-trols and indicators are illustratedand described elsewhere in thischapter.

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AUTOMATIC FLIGHT - Controls and Indicators

FD SwitchPermits commands from flightguidance system to be displayed aspitch and roll commands on therespective ADI

BACK CRS SwitchProvides correct (reverse) sensing oflocalizer deviation to FGS when approaching in Back Course Mode BackCourse inhibited with either autopilotLever in CMD The previouslyselected pitch axis mode will bemaintained or another pitch modemay be selected

TURB SwitchPushing either switch automaticallyreverts autopilot from CMD to CWSturns autothrottles OFF and biasespitch and roll command bars fromview on both ADI s Fast/slow indicators wi l l remain in v iewAutomatic pitch trim functions are inhibited

FLIGHT DIRECTOR (FD) CONTROL PANEL (2)

NAV Frequency ReadoutDigital readout of the VOR or ILSfrequency selected with the NAVfrequency select knob

NAV Frequency Select KnobLarge outer knob changes first threedigits of frequency Small inner knobchanges last two digits of frequency

HSI SwitchRAD— HSI will receive and display

data from ILS and VORreceivers

INS— HSI will receive and displaydata from the inertial navigation system

CRS ReadoutDigital readout of the VHF NAVcourse selected with the CRS selectknob

CRS Select KnobRotate to select VHF NAV courseAlso positions course pointer in HSI ifthe HSI switch is in the RAD positionPush in for fast course selection

DME SwitchSTBY— Permits selected portions

of the distance measuringequipment to be prewarmed prior to operation

NORM— Provides normal rangeoperations of the distancemeasur ing equipment(under 200 nm)

OVRD— Permits extended rangeoperat ions (up to approximately 400 nm)

CAUTIONThe possibility of receiving an unwanted station is increased when theswitch is in the OVRD position

NAVIGATION CONTROL PANEL (2)

FLIGHT GUIDANCE SYSTEM (FGS) PANELGLARESHIELD

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AUTOMATIC FLIGHT - Controls and Indicators

EPR SwitchWhen pushed, causes throttle leversto advance to the EPR limit readoutdisplayed on TRC indicator. ATS FMAwill display EPR (with one or bothATS levers in ON) Fast/Stow in-dicators are removed from viewexcept during TAKE-OFF or G/Amode

NOTEFailure of thrust rating computer in-hibits use of EPR mode. If ATS isengaged in EPR mode at time offailure, ATS levers will drop to OFF.

ATS Levers (2)Permits engagement of either or bothautothrottle systems. Moving lever toON (inflight) will engage SPD modeunless TAKEOFF or G/A mode isenergized. On the ground, movinglever to ON will engage CLAMP modeunless TAKEOFF mode is energized.No automatic movement of throttlescan occur with CLAMP modeengaged.

SPD ReadoutDigital readout of airspeed (in knots)selected with SPD select knob.Airspeed set in readout is the com-mand speed for ATS when operatingin SPD mode.

SPD Select KnobThree position knob is spring-loadedto center. Push in for fast speedadjustment. Pull out to change speedreference control mode from EPR toSPD. Center position provides finespeed adjustment. Selected speedchanges are also reflected onMach/AS indicator by repositioningairspeed command bug. SPD modeengagement inhibits IAS HOLD andMACH HOLD mode.

NOTEMACH HOLD mode not applicablewhen PMS is installed

AUTOMATIC THROTTLE SYSTEM(ATS) CONTROL PANEL

ILS Switch

When pushed, arms FGS to captureand track ILS tuned on NAV panel.Arm FMA will display ILS.

INS SwitchWhen pushed, arms FGS to captureand track course commanded by iner-tial navigation system. Arm FMA willdisplay INS

VOR LOC SwitchWhen pushed, arms FGS to captureand track omni-range or localizertuned on NAV panel. Arm FMA willdisplay VOR or LOC

HDG ReadoutDigital readout of the heading select-ed with the HDG control knob.

Bank Angle SelectorProvides bank angle limit for all FGSmodes except LOC CAP, FDTAKEOFF, and G/A.

HDG Control KnobKnob has four functions. Normal,spring-held position provides fineadjustment of heading. Push to firstdetent for fast heading select. Pushfull in to engage AP and FD HDGHOLD and to cancel all armed orengaged lateral modes. Pull out toengage HDG SEL mode. HDG knobalso positions heading bugs on HSI'swhen HSI switch is in RAD position.

DIRECTIONAL CONTROL PANEL

FLIGHT GUIDANCE SYSTEM (FGS) PANELGLARESHIELD

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AUTOMATIC FLIGHT - Controls and Indicators

Vertical Speed Select WheelCommands selected vertical speedwhen FD and/or autopilot areengaged. Vertical speed select wheelis synchronized to airplane verticalspeed at all times except when ALTHOLD or VERT SPD is engaged.Center detent position selects ALTHOLD mode Positions ADI pitchcommand bars

NOTEManual rotation of vertical speedselect wheel will engage verticalspeed mode at all times except duringautoland G/S TRK mode.

ALT Preselect ReadoutDigital readout of the altitudepreselected with ALT preselect knob.

NOTEAltitude Readout Limits:

Upper - 49900Lower - 00000

AP Lever (2)

CMD - Provides autopilot control forselected autoflight modes.When AP lever is movedfrom OFF to CMD, pressuremust be re leased uponreaching CWS and then re-applied.

C W S - P e r m i t s control wheelsteering.

LAND SwitchWhen pushed, arms FGS for anautomatic landing. LAND will be an-nunciated initially in arm FMA. Ifpreset conditions for DUAL LAND aremet, arm FMA will then display DUALLAND after preland test is complete(G/S TRK). If not, SNGL LAND willbe displayed. On ground, pushing thisswitch initiates a PAFAM test displayafter which PAFAM shuts down.

CWS SwitchWhen pushed, initiates (AP in CMD)control wheel steering. Pitch and rollFMA's will both display CWS if ALTHOLD or VERT SPD was notpreviously annunciated in pitch FMA.If ALT HOLD or VERT SPD waspreviously annunciated, CWS will bedisplayed in roll FMA.

Altitude Advisory RESET ButtonPush to cancel altitude preselectmode, reset altitude advisory system,and to turn off flashing altitude ad-visory light

PERF Switch (Applicable when PMSis installed)When pushed, seeks and maintainscomputed PMS outputs by controllingpitch attitude and throttle position.ATS and pitch FMAs will displayPERF

ORMACH Switch (Applicable when PMSis NOT installed)When pushed, holds present Machnumber by controlling pitch attitude.Must be in EPR mode if ATS isengaged Pitch FMA will displayMACH HOLD

IAS SwitchWhen pushed, holds present indicatedairspeed by controlling pitch attitudeMust be in EPR mode if ATS isengaged Pitch FMA will display IASHOLD

ALT Preselect KnobKnob has 3 functions Normal, spring-held position provides fine altitudeadjustment. Push for fast altitudeadjustment Pull to arm altitudepreselect mode. Altitude preselectmode will provide automatic altitudecapture (if an AP lever is in CMD) orFD pitch bar guidance to capture theselected altitude. Airplane will notautomatically start to climb or des-cend after altitude preselect mode isarmed

PITCH CONTROLPANEL

FLIGHT GUIDANCE SYSTEM (FGS) PANELGLARESHIELD

JLFeb 1/85 03-30-03

AUTOMATIC FLIGHT - Controls and IndicatorsFLIGHT GUIDANCE SYSTEM MODE ANNUNCIATION

Test will be annunciated when mode test but-ton is pushed All test annunciators will begreenAUTOTHROTTLE ANNUNCIATOR MODES

Speed indicates the basic mode of ATS opera-tion in which throttles are controlled to seekand maintain selected airspeedEPR indicates EPR mode selected with eitheror both ATS levers engaged ATS controlsthrottles to seek and maintain EPR limitAlpha speed indicates ATS is automaticallymaintaining a computed safe speed basedupon established stall margins Annunciatedwhen minimum safe (Alpha) speed is greaterthan selected airspeedRetard ind icates thro t t les are beingautomatically retarded during a landing (atabout 50 feet radio altitude) Retard modewill not engage until approach slats areextended or Land mode is engagedClamp indicates ATS engaged on the groundand ATS cannot move throttle levers Whentakeoff mode is engaged, clamp modechanges to EPR mode At 80 knots clampmode will re-engage Clamp mode can be dis-engaged by pushing EPR switch or pulling outSPD select knob after airplane is in flightPerformance indicates PMS selected witheither or both ATS levers engaged ATS con-trols throttles to seek and maintain computedPMS outputs

ARM ANNUNCIATOR MODES

INS indicates system is armed to capture andtrack course commanded by inertial navigation system

INS/Altitude indicates system is armed tocapture and track course commanded by iner-tial navigation system and altitude preselectmode is armed to capture selected altitude

Applicable when PMS is installed

VOR indicates system is armed to capture andtrack selected omnirange

VOR/Altitude indicates system is armed tocapture and track selected omnirange, andaltitude preselect mode is armed to captureselected altitude

Altitude indicates altitude preselect mode isarmed to capture selected altitude

Back Course/Altitude indicates system isarmed to accept ILS back course steering(localizer only) and altitude preselect mode isarmed to capture selected altitude (FD modeonly)Back Course indicates system is armed tocapture and track ILS back course (localizeronly) (FD mode only)Localizer/Altitude indicates system is armedto capture and track selected localizer andaltitude preselect mode is armed to captureselected altitudeLocalizer indicates system is armed to cap-ture and track localizer only

ILS/Altitude indicates system is armed tocapture and track selected localizer andassociated glide slope and altitude preselectmode is armed to capture selected altitudeILS indicates system is armed to capture andtrack selected localizer and associated glideslopeLand indicates system is armed for anautomatic landing

Land/Altitude indicates system is armed foran automatic landing and altitude preselectmode is armed to capture selected altitude

Dual Land indicates system is armed for afail/operational autoland operation, i e, allrequisite primary and backup components arefunctioning Dual Land will appear only afterall integral preland tests have beensuccessfully completed and airplane istracking both localizer and glide slopeSingle Land indicates airplane is tracking bothlocalizer and glide slope but autopilot prelandtest has determined that a failure exists inone of the dual autopilot systems or only oneautopilot is engagedApproach Only indicates airplane is trackingboth localizer and glide slope but an automaticlanding will not be made - either because ofautoland failure or pilot election

03-30-04JL

Aug 1/82

AUTOMATIC FLIGHT - Controls and Indicators

FLIGHT GUIDANCE SYSTEM MODE ANNUNCIATION (Continued)ROLL ANNUNCIATOR MODES

Heading Select indicates HDG control knobhas been pulled out with either an autopilotand/or FD engaged Autopilot will maneuverthe airplane to acquire and maintain headingshown in HDG readout, if engagedHeading Hold is basic engagement mode ofautopilot and flight director and indicatesmagnetic heading existing at time of modeengagement is being maintainedINS Capture indicates inertial navigationsystem is providing commands throughautopilot or flight director to maneuver air-plane to capture selected track.INS Track indicates airplane is tracking thecourse commanded by inertial navigationsystemVOR Capture indicates VOR mode has beeninitiated and airplane has entered VOR beamcapture threshold.VOR Track indicates airplane is trackingselected VOR radial

Control Wheel Steering indicates CWS modehas been initiated by pushing CWS switchwith either AP lever in CMDBack Course/Capture indicates ILS backcourse mode selected and airplane hasentered back course threshold of localizerbeam (FD mode only)Back Course/Track indicates airplane istracking ILS back course of localizer (FDmode only)Localizer Capture indicates the LOC, ILS orLand mode selected and airplane is in capturesequence approaching localizer beam (withintwo dots on HSI course deviation scale).Localizer track indicates LOC, ILS, or Landmode selected and airplane is trackingselected localizer centerlineAlign indicates Land mode is engaged and air-plane has entered localizer alignment phaseand is within 140 feet (sensed by radio alt) ofthe ground Existing crab will be convertedinto a forward slip maneuver ADI decrab in-dicator moves from center by an amountequal to initial yaw command, and centers asalignment is completed

Go Around indicates TO/GA button on throttle2 pushed, in flight, and flaps are out of full upposition. If an autopilot and/or FD is engaged,the go around mode command will be initiatedto roll wings level and maintain headingexisting when roll attitude is less than 3°

Takeoff indicates TO/GA button on throttle 2pushed on the ground. Roll command bars willprovide guidance after liftoff to maintainexisting magnetic heading (FD mode only)

VOR Course indicates airplane is over VORstation (zone of confusion), or is departingfrom a VOR beam centerline (at a rate greaterthan 1/2 degree per second), or is two dots ormore deviation from VOR beam centerline, orwhen a new VOR frequency and/or course hasbeen selected. VOR CRS will normally bereplaced by VOR TRK anytime after aminimum of 30 seconds and up to a maximumof 3 minutes. After 3 minutes if VOR TRKcriteria is not satisfied, HDG HOLD will be an-nunciated

During autoland, Roll Out will engage aftermam gear wheel spin up and disengage afternose gear touchdown.

PITCH ANNUNCIATOR MODES

IAS Hold indicates IAS switch pushed causingsystem to maintain existing airspeed by con-trol of pitch attitude.

Mach Hold indicates Mach switch pushedcausing system to maintain existing Mach bycontrol of pitch attitude.

Turbulence indicates either TURB switchpushed. Autothrottles will revert to OFF,autopilot will revert from CMD to CWS, andpitch and roll commands will be removed fromboth ADI's.

Vertical Speed is basic engagement mode ofautopilot and flight director and indicates thatvertical speed mode is engaged and verticalspeed selected on vertical speed select wheelis being maintained

Altitude Capture indicates altitude preselectmode engaged and airplane is within capturethreshold and maneuvering to captureselected altitude.

JLAug 1/88 03-30-05/06

Altitude Hold indicates vertical speed selectwheel is in ALT HLD detent and altitudeexisting at time of mode engagement is beingmaintained

Control Wheel Steering indicates CWS switchpushed with either AP lever in CMD and ALTHOLD or VERT SPD was not previouslyengaged

Glide Slope Capture indicates a localizerfrequency tuned, ILS or LAND mode selected,and airplane is entering glide slope capturethreshold Point of annunciation is variable, afunction of rate of beam closure and beamdeviation

Glide Slope Track indicates ILS or Land modeselected and airplane is aligned with glideslope centerline and is tracking inbound

Flare indicates Land mode is engaged and air-plane has begun landing flare maneuver (atabout 50 feet radio altitude)

Go Around indicates TO/GA button on throttle2 pushed, in flight, and flaps are out of full upposition If an autopilot and/or FD is engaged,go around mode will command a pitch attitudeto maintain V2 + 10 KIAS on 3 engines, V2on 2 engines, or a pitch attitude limit of 15degrees Fast/slow indicator will be centeredwhen stabilized airspeed corresponds to V2 +10 KIAS (3 engines) or V2 (2 engines)

Takeoff indicates TO/GA button on throttle 2pushed on the ground After liftoff Fast/Slowindicators and pitch command bars arereferenced to V2 + 10 KIAS on 3 engines or,prior to incorporation of DAC S/B 22-107, V2on 2 engines After incorporation of DAC S/B22-107 or production equivalent, upon an en-gine failure, the Flight Director Pitch CommandBar will provide commands to control the fol-lowing speeds• At or below V2 speeds, control to V2 speeds• between V2 and V2 + 10 control to existing

speeds• at or above V2 + 10 speed, control to V2

+ 10However, if pitch attitude required to maintainV2 + 10 KIAS (3 engines) or V2 (2 engines)speed is greater than 22 degrees, pitch com-mand will limit stabilized pitch attitude to notexceed 22 degrees (FD mode only)

Performance indicates PMS selected causingsystem to maintain computed PMS outputs bycontrolling pitch attitude

Applicable when PMS is not installed

Applicable when PMS is installed

AUTOMATIC FLIGHT - Controls and Indicators

ARM Annunciator (Amber except for DUAL LAND andthe E in TEST which are green.)

Displays mode of operation FGS is armed to accept orcurrent FGS status.

ROLL Annunciator (Green)

Displays mode currently steering airplane

ATS Annunciator (Green)Displays engaged operating mode of autothrottlesystem.

PITCH Annunciator (Green)Displays mode currently controlling pitch angle

FLIGHT MODE ANNUNCIATOR

MODE TEST Button

Pushing will test flight mode annunciator (FMA) lightsand tape and reset overrun detector. T-E-S-T will appearin four windows of mode annunciator.

AP OUT OF TRIM LightIndicates elevator is out of faired position (with respectto stabilizer) for a specified amount of time. Light will goout when stabilizer is trimmed. Light is inhibited when inTURB mode and during DUAL LAND upon reaching 100feet radio altitude.

FLIGHT GUIDANCE SYSTEM ANNUNCIATOR

AP Fail Light (Red 1, 2; Amber 1, 2)There is a red (upper) and an amber (lower) lightfor each autopilot system. During normal opera-tion, when an autopilot lever moves from CMD toCWS, CMD to OFF, or CWS to OFF, associatedred light flashes and an aural tone will sound. Lightcan be shut off and aural tone silenced by pushinglight cap or either control wheel AP release button.When LAND mode has been selected:One AP - If disengaged after having beenengaged engaged in SNGL LAND, associated

red AP fail light flashes and auralwarning sounds.

Two APs - If during a dual land approach, oneengaged AP lever drops to OFF, its respective

amber fail light will remain on. ArmFMA's will change to SNGL LAND.Pushing amber fail light will turn it off.

If one or both APs fail to the degreethat a fail operative capability cannotbe maintained (but either or both APlevers remain in CMD), associatedamber fail light comes on steady.During an autoland, an aural warningwill sound in addition to red flashingfail lights if autopilot completely dis-engages from CMD Amber fail lightsare inhibited during DUAL LANDupon reaching 100 feet radio altitude.

ATS Fail Light (Red 1. 2, Amber 1, 2)There is a red (upper) and an amber (lower) lightfor each autothrottle system A red light willflash whenever both autothrottles are disengag-ed. Red fail light can be shut off by pushing thelight cap or either ATS disengage button Anamber light will come on (steady) when either oftwo previously engaged autothrottles becomesdisengaged. Amber fail light can be shut off byre-engaging the disengaged autothrottle or bydisengaging and then re-engaging the remainingengaged autothrottle. Amber fail lights are in-hibited during DUAL LAND upon reaching 100feet radio altitude

CAPTAIN'SAND FIRSTOFFICER'S

INSTRUMENTPANELS

AP Release Button (2)On outboard horn of each control wheel, providesone means of disengaging autopilot Pushingeither button disengages autopilot, and red AP faillights come on flashing Pushing autopilot releasebutton again or pushing any AP-1 or AP-2 faillights will turn off lights

JLAug 1/85 03-30-07

AUTOMATIC FLIGHT - Controls and Indicators

Fixed Airplane SymbolIndicates position of airplane in rela-tion to horizon index

Bank Angle IndicatorIndicates airplane bank angle.

Fast/Slow IndicatorIn speed mode fast/slow indicatorsare referenced to ATS SPD readoutor safe stall margin speed (ALPHAspeed) Full deflection either side ofcenter equals approximately 10knots. If a selected airspeed is lessthan a minimum safe percentageabove stall for that configuration, in-dicator will be centered when ALPHAspeed is maintained. In takeoff andG/A modes indicator will display air-speed error between computed speedand actual speed. Not valid in takeoffmode until after liftoff Indicator notin view in RETD mode, or EPR mode(FD takeoff or go-around mode notengaged)

NOTEWhen PMS is installed with PERFmode engaged, fast/slow indicatorwill display airspeed error betweentarget airspeed computed by PMScomputer and actual speed.

Radio Altimeter Altitude DisplayIndicates relative height of airplanefrom runway and is controlled byradio altimeter Indicator starts torise at 200 feet radio altitude.Removed from view if radio altimeterfails

TEST Button

When pushed, displays ATT and FDflags, rotates sphere for 20° rightbank and 10° climb, roll and pitchcommand bars deflect right and uprespectively, and decrab indicatordeflects to right edge of airplane sym-bol

Localizer IndicatorIndicates lateral deviation fromlocalizer course on localizer scaleOut of view m back course mode. Fulldeviation of localizer indicator symbolcorresponds to approximately 1/4 dotlocalizer deviation on HSI scale

Pitch Command BarProvides pitch guidance commandsfrom FGS computer. Pitch commandbar will be removed from view if pitchguidance is invalid or if guidance in-formation is not compatible withengaged autopilot.

NOTEMaximum pitch attitude for AT/SCsystem is 22° for takeoff and 15° forgo around.

Roll Command BarProvides lateral guidance commandsfrom FGS computer. FD roll commandbar is removed from view if lateralguidance is invalid or if guidance in-formation is not compatible withengaged autopilot.

DH LightComes on at 1800 feet and whendecision height selected on radioaltimeter is reached. Pushing DH lighton radio altimeter turns off DH lightat 1800 feet. At decision height, DHlight can be turned off by selecting alower decision height on radioaltimeter.

Glide Slope PointerIndicates glide slope plane relative tothe position of the airplane Pointerout of view in back course mode.

Decrab IndicatorComes into view and centers at glideslope track after a successfulpreland test. Becomes operative at140 ft when align mode is engagedRemains centered as long as ruddersare responding to input signals.

Horizon IndexProvides a horizon position referencerelated to airplane symbol

Rate Of Turn Indicator

Displays rate of turn

Slip IndicatorIf ball is displaced from center, air-plane is either slipping or skidding.

'ATTITUDEDIRECTORINDICATOR

(ADI)

CAPTAIN'S AND FIRST OFFICER'SINSTRUMENT PANELS

03-30-08JL

Aug 1/82

AUTOMATIC FLIGHT - Controls and Indicators

SPD FlagAppears when speed command dataare unusable

ATT FlagAppears for test and to indicate thatthe attitude data are unusable.

FD FlagAppears for test or to indicate thatFD command bar servo failure hasoccurred. In the latter instance, FDcommand bars are removed fromview.

RT FlagAppears when rate of turn data un-usable. Rate of turn indicator isremoved from view.

GS FlagAppears for ILS test and when glideslope data are unusable. Glide slopepointer is removed from view

ATTITUDE DIRECTOR INDICATOR(ADI)

(WITH FLAGS DISPLAYED)

CAPTAIN'S AND FIRST OFFICER'SINSTRUMENT PANELS

JLFeb 1/75 03-30-09

AUTOMATIC FLIGHT - Controls and Indicators

DH Light

Comes on at 1800 feet, and when air-plane reaches selected decision heightEach time DH light comes on, a momen-tary aural tone will sound Light may beturned off at 1800 feet by pushinglight

Radio Altimeter TapeGraduated from 0 to 2500 feetGraduations are at 10 foot intervals(linear) between 0 and 500 feet and at100 foot intervals (compressed) above500 feet Between 0 and 500 feet,tape is green with a tapered yellow areaalong right edge between 0 and 190feet Between 500 feet and 2500 feettape is blue Tape has alternating blackand yellow diagonal lines below 0 feetand is black above 2500 feet

Height Reference BugA reference index which works in con-junction with digital reading in DH setreadout Both are adjusted by rotatingSET/TEST knob

Height Reference IndexA fixed index (tape moves) which in-dicates current altitude above terrainMaximum indication is 2500 feet

SET/TEST KnobRotating knob will change decisionheight Pushing knob will test system bycausing airplane altitude to read 40feet above terrain, and deploying war-ning flag

NOTETest is inhibited after localizer orglideslope capture

DH Set ReadoutA digital readout of preselected deci-sion height which works in conjunctionwith height reference bug Both areadjusted by rotating SET/TEST knobWarning Flag

Deploys for test and to indicate radioaltimeter data are unusable

RADIO ALTIMETER

Altitude Advisory LightWorks in conjunction with altitude ad-visory system Provides steady onsignal (in conjunction with aural tone)when airplane is at altitude advisorythreshold (minimum of 750 feet fromselected altitude) and goes off whenwithin 250 feet of selected altitude Advisory light flashes (in conjunction withaural tone) when airplane deviates 250feet or more from previously selectedand acquired altitude Pushing altitudeadvisory RESET button will turn offflashing advisory light and re setaltitude advisory system to monitorsubsequent deviations of 250 feet ormore from selected altitudeSteady light can be turned off any timein flight by rotating ALT preselect knobto set in new altitude

ALTIMETER

Airpseed Command BugReflects whatever airspeed is set inSPD readout on ATS control panel

NOTEWhen PMS is installed with PERF modeengaged bug will display target airspeed computed by PMS computer

MACH/AS INDICATOR

CAPTAIN'S AND FIRST OFFICER SINSTRUMENT PANELS

03-30-10JL

Aug 1/82

AUTOMATIC FLIGHT - Controls and Indicators

ATS Disengage Button (2)Pushing an ATS disengage buttonwill disengage autothrottle system.Pushing button a second time willreset flashing red ATS light.

TO/GA Button1. Pushing TO/GA button on the

ground engages FD T.O. mode.(Pitch guidance is provided whilein FD T.O. mode or GA mode tomaintain V2 + 10 knots for 3engine operation or V2 for 2engine operation.)

2. Pushing TO/GA button while inflight with flaps out of full upposition:A. Engages FD and/or autopilot

GA mode.B. Automatically selects GA

mode EPR thrust on thrustcomputer and sets EPR com-mand bugs.

C. Automatic throttle systemswitches EPR mode if it wasengaged in speed or retardmode and t h r o t t l e sautomatically advance to GAmode EPR thrust if either orboth ATS levers are engaged.

D. Speed control automaticallygoes to GA mode.

THROTTLES(PEDESTAL)

JLAug 1/82 03-30-11

AUTOMATIC FLIGHT - Controls and Indicators

THRUST RATING COMPUTER (TRC)INDICATOR (TYPICAL)

ENGINE PRESSURE RATIO (EPR)GAGE (TYPICAL)

CENTER INSTRUMENT PANEL(For Description of above Controls and Indicators

refer to Powerplant Chapter.)

03-30-12JL

Aug 1/82

AUTOMATIC FLIGHT - Controls and Indicators

SPEED CONT TEST SelectorNOTE

Operative only when on the groundSLO - Generates an error signal

into speed control circuitsFast/Slow indicator movesapproximately one-half fullscale towards slow If ATSengaged, thrott les wil lmove toward max thrustsetting Releases servobrake

FAST - Fast/slow indicator movesapproximately one half fullscale towards fast If ATSengaged, thrott les wil lmove aft to mechanicalstops Releases servobrake

FD CMD SelectorNORM - Command bars (pitch

and roll) in Captain's ADIare being driven by flightguidance system 1 andFirst Officer's commandbars are being driven bysystem 2

BOTH - Both Captain's and FirstON 1 Officer's command bars

are being driven by flightguidance system 1

BOTH - Both Captain's and FirstON 2 Officers command bars

are being driven by flightguidance system 2

FD CMD Annunciator Light

Comes on to indicate FD CMDselector not in NORM andswitching unit has switched to correct position

YAW DAMP Switch (4)Turns on associated upper or lowerrudder segment yaw damp channelAn off yaw damp switch will inhibitits respective YAW DAMP INOPlight

Yaw Damp TEST Switch-LightA dual switch which permits testingof the upper and lower rudder yawdamp system by initiating the testcycle When light is on, signifiesthat a test is in progress for itsrespective channel Upper andlower halves of light are indepen-dent

NOTEDuring test cycle, rudder indicators(Surface Position Indicator) shoulddeflect to left, slowly return toneutral, deflect to right, and thenslowly return to neutral

YAW DAMP TEST FAIL Light (2)Comes on during test cycle If lightr e m a i n s on , i n d i c a t e s t ha tassociated yaw damp test hasfailedUPPER/LOWER YAW DAMP

INOP LightComes on to indicate upper/loweryaw damp system failure, andduring yaw damp test cycle

OVERHEAD

JLAug 1/82 03-30-13

AUTOMATIC FLIGHT - Controls and Indicators

Photo Electric Ceil (2)

Provides automatic control of the videodisplay intensity

Intensity Control KnobRotating the knob will override theautomatic photo electric cell intensitycontrol and increase or decrease thevideo display intensity (Beginning ap-proach display shown )TEST- In-flight

In the LAND mode-appears during theautomatic preland test (just after glide-slope track annunciation) and lastsabout 30 secondsIn the ILS mode-appears just afterglideslope track annunciation and lastsabout 10 secondsBeginning approach display appears atcomplet ion of test

NOTEPAFAM cannot be manually tested inflight

Touchdown ZoneNominally ±60 ft wide and ±1000 ftlong about the ideal touchdown point

NOTEIdeal touchdown point is on the runwaycenter line and approximately 450 ftbeyond the glideslope transmitter

Runway SymbolBottom edge corresponds to runwaythreshold Perspective of runway symboldoes not change to reflect attitude orlateral translation

Touchdown Indicator (LAND mode only)Triangle will appear at touchdown andremain for three seconds, after whichPAFAM is de-energized

Touchdown Predictor VectorsA symbolic representation of the pre-dicted touchdown point expressed interms of direction and magnitude of un-certainity The sample shown representsan assessment of marginal character ofthe automatic landing in that the touch-down point is shown as left of center-line The uncertainty aspect is repre-sented in the disproportionate length ofthe vectors In this case, left and long

The Captain is advised his instrumentsare valid for go-around

The First Officer is advised his instru-ments are valid for go-around

NOTEIf both Captain's and First Officer's in-struments are operating both arrowswill show simultaneously

TAKEOVERIn the LAND mode-appears if systemmalfunction or airplane performance willresult in landing that is not in the ac-ceptable touchdown zoneAlso appears when LAND switch ispushed for ground test

NOTEInhibited during ILS approach exceptfor NO TRACK takeover condition de-scribed below

NO ILS (Flashing)Appears when either localizer or glide-slope signal is lost

NOTEIn the LAND mode, if signal is not re-stored in approximately 3 seconds,TAKEOVER display will appear and afterapproximately 5 seconds, autopilots willdisengage In the ILS mode, autopilotwill disengage when NO ILS displayoccurs

NO T R A C KAppears if localizer and glideslopetrack has not taken place and airplaneis below 600 ft and TAKEOVER will bedisplayed if airplane descends to orbelow 300 ft

PERFORMANCE AND FAILURE ASSESMENT MONITORCAPTAIN'S AND FIRST OFFICER'S INSTRUMENT PANELS

NOTE: Operation of the PAFAM in the ILS mode is applicable only to those airplanes withPAFAM ILS mode activated by S/B 22-88 or production equivalent.

03-30-14JL

Jun 1/97

AUTOMATIC FLIGHT - Controls and Indicators

CDU MESSAGE Light (2)Comes on when a message is dis-played in scratchpad of PMS CDUand goes off when CLEAR Key on PMSCDU is pressed

VERTICAL ALERT Light (2)Comes on 15 seconds prior to a PMSgenerated vertical leg change at topof descent point or at start of a decel-eration maneuver to reach 250 kts at10,000 feet or accelerating from 250 ktsclimbing thru 10,000 feet, and goes offwhen vertical leg change is started

INS UPDATE Annunciator (4)Indicates green on both the 1 and 2 INSUPDATING annunciators when DME up-dating is taking place

CAPTAIN'S AND FIRST OFFICER'SINSTRUMENT PANELS

Effect ive for airplanes with PMS installed

Effective for airplanes with PMS installed.

AUTOMATIC FLIGHT - Controls and Indicators

Light SensorSenses ambient light level andautomatically adjusts the referencebrightness level

Line Select Keys (1, 2, 3)When pushed, can transfer data entries from scratchpad to selecteddata line, or arm and/or select PMSsubmodes, or call up additional datarelevant to a specific display lineIntegral key light comes on to indicatethat displayed submode data is notactive but can be engaged by pushingthat key

Data Display1 Four line display of up to 24

characters per line2 Each character formatted within 5

x 7 Light Emitting Diode (LED) dotmatrix

Title/Scratchpad LineTitle uses characters 1 thru 12Scratchpad uses characters 13 thru24

NUMBERED DATALINES (3)

Mode Annunciator Lights (CLB CRZDES)Mode annunciator lights are notnecessarily related to the displaymode selectedCLB - Comes on when in climb mode

of operationCRZ ~ Comes on when in cruise

mode of operationDES - Comes on when in descent

mode of operation

DIM Control KnobRotated to adjust intensity data dis-play, line select key integral lights,and mode annunciator lights aboutthe intensity reference level es-tablished by the light sensor

NOTELight intensity of function keys anddata entry keys controlled by pedestalpanel light knob on aft pedestal

PMS Failure LightComes on when PMS is not valid andduring STS/TEST

PMS CONTROLDISPLAY UNIT

(CDU)

ALTERNATE FUNCTIONDATA ENTRY KEY

PEDESTAL

Effective for airplanes with PMS installed.

03-30-16JL

May 1/83

AUTOMATIC FLIGHT - Controls and Indicators

Function Keys (11)

Includes two blank spare keys for future expansion

CLB - When pushed, selects display of performanceand related data associated with climb

CRZ - When pushed, selects display of performanceand related data associated with cruise

DES - When pushed, selects display of performanceand related data associated with descent

WPTS - When pushed, provides for display of datarelative to vertical waypoints

NAV AID - When pushed, provides for display of storednavigational aid data and for insertion ofpilot defined navigational aid data

PLAN - When pushed, calls up data pages relevant topreflight and enroute planning

DIR - When pushed, calls up waypoints display forimplementation of a lateral "direct to" leg toa pilot specified waypoint

CLEAR - When pushed, clears last data loaded inscratchpad, or clears aler t /advisorymessages which appear in scratchpad, orclears data previously entered in a data linewhen the related line select key is pushed i e ,

when neither a data load is in progress or analert/advisory message is in scratchpad, theword CLEAR appears in scratchpad When aline select key is pushed, the previouslyentered data is cleared The slash (/) data en-try key is used in conjunction with CLEAR keyto selectively clear data when more than oneparameter was previously entered onselected line

STS/TEST - Combination lamp test command and statusdisplay select key When pushed and heldfunctions as a lamp/display test Line selectkey (1, 2,3) integral lights increase inbrightness, PMS failure light and mode annun-ciator (CLB, CRZ, DES) lights come on, fourrows of 24, 5 x 7 LED dot matrix is displayedWhile key is being held, all other key/switchescan be operated to generate specific displaycharacters as a verification of properkey/switch operation and CDU input decodingWhen key is released, STS (status) page isdisplayed, line select keys integral lights dimand all other tested lights go off

Slew SwitchWhere multiple pages are available under the same title,operation of switch in either up (advance) or down(backup) direction will display those pages A cue in theform of a symbol ( or | or both) will appear in last twocharacters of scratchpad to indicate which direction tooperate switch to obtain display of additional pages

Data Entry Keys (13)Provides ten numeric keys (0 thru 9) some of which aredual function, a decimal point (), a slash (/), and an "alternate function" key

Pushing any key except "alternate function" key enters acharacter, left to right, in scratchpadDual function data entry keys will enter numeric charactersunless "alternate function" key is pushed first (i e , "W 4"key will enter number 4 in scratchpad, pushing "alternatefunction" key first and then pushing "W 4" key will enterletter W in scratchpad) Next numeric key pushed will enterthat numeric character in scratchpad if "alternate func-tion" key is not pushed firstSlash (/) key is used if data line has more than oneloadable parameter

PEDESTAL

Effective for airplanes with PMS installed.JLFeb 1/84 03-30-17/18

AUTOMATIC FLIGHT - System Interface

Test will be annunciated when mode test but-ton is pushed. All test annunciators will begreen.

AUTOTHROTTLE ANNUNCIATOR MODES

Speed indicates the basic mode of ATS opera-tion in which throttles are controlled to seekand maintain selected airspeed.EPR indicates EPR mode selected with eitheror both ATS levers engaged. ATS controlsthrottles to seek and maintain EPR limit.Alpha speed indicates ATS is automaticallymaintaining a computed safe speed basedupon established stall margins. Annunciatedwhen minimum safe (Alpha) speed is greaterthan selected airspeed.Retard ind icates th ro t t les are beingautomatically retarded during a landing (atabout 50 feet radio altitude). Retard modewill not engage until approach slats areextended or Land mode is engaged.Clamp indicates ATS engaged on the groundand ATS cannot move throttle levers. Whentakeoff mode is engaged, clamp modechanges to EPR mode. At 80 knots, clampmode will re-engage. Clamp mode can be dis-engaged by pushing EPR switch or pulling outSPD select knob after airplane is in flight.Performance indicates PMS selected witheither or both ATS levers engaged. ATS con-trols throttles to seek and maintain computedPMS outputs.

Applicable when PMS is installed.

ARM ANNUNCIATOR MODES

INS indicates system is armed to capture andtrack course commanded by inertial naviga-tion system.INS/Altitude indicates system is armed tocapture and track course commanded by iner-tial navigation system and altitude preselectmode is armed to capture selected altitude.VOR indicates system is armed to capture andtrack selected omnirange.

VOR/Altitude indicates system is armed tocapture and track selected omnirange, andaltitude preselect mode is armed to captureselected altitude.Altitude indicates altitude preselect mode isarmed to capture selected altitude.

Back Course/Altitude indicates system isarmed to accept ILS back course steering(localizer only) and altitude preselect mode isarmed to capture selected altitude (FD modeonly).Back Course indicates system is armed tocapture and track ILS back course (localizeronly). (FD mode only).Localizer/Altitude indicates system is armedto capture and track selected localizer andaltitude preselect mode is armed to captureselected altitude.Localizer indicates system is armed to cap-ture and track localizer only.

ILS/Altitude indicates system is armed tocapture and track selected localizer andassociated glide slope and altitude preselectmode is armed to capture selected altitude.ILS indicates system is armed to capture andtrack selected localizer and associated glideslope.Land indicates system is armed for anautomatic landing.

Land/Altitude indicates system is armed foran automatic landing and altitude preselectmode is armed to capture selected altitude.Dual Land indicates system is armed for afail/operational autoland operation, i.e., allrequisite primary and backup components arefunctioning. Dual Land will appear only afterall integral preland tests have beensuccessfully completed and airplane istracking both localizer and glide slope.Single Land indicates airplane is tracking bothlocalizer and glide slope but autopilot prelandtest has determined that a failure exists inone of the dual autopilot systems or only oneautopilot is engaged.Approach Only indicates airplane is trackingboth localizer and glide slope but an automaticlanding will not be made - either because ofautoland failure or pilot election.

ROLL ANNUNCIATOR MODES

Heading Select indicates HDG control knobhas been pulled out with either an autopilotand/or FD engaged. Autopilot will maneuverthe airplane to acquire and maintain headingshown in HDG readout, if engaged.Heading Hold is basic engagement mode ofautopilot and flight director and indicatesmagnetic heading existing at time of modeengagement is being maintained.INS Capture indicates inertial navigationsystem is providing commands throughautopilot or flight director to maneuver air-plane to capture selected track.INS Track indicates airplane is tracking thecourse commanded by inertial navigationsystem.VOR Capture indicates VOR mode has beeninitiated and airplane has entered VOR beamcapture threshold.VOR Track indicates airplane is trackingselected VOR radial.

Control Wheel Steering indicates CWS modehas been initiated by pushing CWS switchwith either AP lever in CMD.Back Course/Capture indicates ILS backcourse mode selected and airplane hasentered back course threshold of localizerbeam (FD mode only).Back Course/Track indicates airplane istracking ILS back course of localizer (FDmode only).Localizer Capture indicates the LOC, ILS orLand mode selected and airplane is in capturesequence approaching localizer beam (withintwo dots on HSI course deviation scale).Localizer track indicates LOC, ILS, or Landmode selected and airplane is trackingselected localizer centerline.Align indicates Land mode is engaged and air-plane has entered localizer alignment phaseand is within 140 feet (sensed by radio alt) ofthe ground. Existing crab will be convertedinto a forward slip maneuver. ADI decrab in-dicator moves from center by an amountequal to initial yaw command, and centers asalignment is completed.Go Around indicates TO/GA button on throttle2 pushed, in flight, and flaps are out of full upposition. If an autopilot and/or FD is engaged,the go around mode command will be initiatedto roll wings level and maintain headingexisting when roll attitude is less than 3°.Takeoff indicates TO/GA button on throttle 2pushed on the ground. Roll command bars willprovide guidance after liftoff to maintainexisting magnetic heading (FD mode only).VOR Course indicates airplane is over VORstation (zone of confusion), or is departingfrom a VOR beam centerline (at a rate greaterthan 1/2 degree per second), or is two dots ormore deviation from VOR beam centerline, orwhen a new VOR frequency and/or course hasbeen selected. VOR CRS will normally bereplaced by VOR TRK anytime after aminimum of 30 seconds and up to a maximumof 3 minutes. After 3 minutes if VOR TRKcriteria is not satisfied, HDG HOLD will be an-nunciated.During autoland, Roll Out will engage aftermain gear wheel spin up and disengage afternose gear touchdown.

PITCH ANNUNCIATOR MODES

IAS Hold indicates IAS switch pushed causingsystem to maintain existing airspeed by con-trol of pitch attitude.Mach Hold indicates Mach switch pushedcausing system to maintain existing Mach bycontrol of pitch attitude.Turbulence indicates either TURB switchpushed. Autothrottles will revert to OFF,autopilot will revert from CMD to CWS, andpitch and roll commands will be removed fromboth ADI's.Vertical Speed is basic engagement mode ofautopilot and flight director and indicates thatvertical speed mode is engaged and verticalspeed selected on vertical speed select wheelis being maintained.

Altitude Capture indicates altitude preselectmode engaged and airplane is within capturethreshold and maneuvering to captureselected altitude.Altitude Hold indicates vertical speed selectwheel is in ALT HLD detent and altitudeexisting at time of mode engagement is beingmaintained.Control Wheel Steering indicates CWS switchpushed with either AP lever in CMD and ALTHOLD or VERT SPD was not previouslyengaged.

Glide Slope Capture indicates a localizerfrequency tuned, ILS or LAND mode selected,and airplane is entering glide slope capturethreshold. Point of annunciation is variable, afunction of rate of beam closure and beamdeviation.Glide Slope Track indicates ILS or Land modeselected and airplane is aligned with glideslope centerline and is tracking inbound.Flare indicates Land mode is engaged and air-plane has begun landing flare maneuver (atabout 50 feet radio altitude).Go Around indicates TO/GA button on throttle2 pushed, in flight, and flaps are out of full upposition. If an autopilot and/or FD is engaged,go around mode will command a pitch attitudeto maintain V2 + 10 KIAS on 3 engines, V2on 2 engines, or a pitch attitude limit of 15degrees. Fast/slow indicator will be centeredwhen stabilized airspeed corresponds to V2 +10 KIAS (3 engines) or V2 (2 engines)Takeoff indicates TO/GA button on throttle 2pushed on the ground. After liftoff Fast/Slowindicators and pitch command bars arereferenced to V2 + 10 KIAS on 3 engines or,prior to incorporation of DAC S/B 22-107, V2on 2 engines. After incorporation of DAC S/B22-107 or production equivalent, upon an en-gine failure, the Flight Director Pitch CommandBar will provide commands to control the fol-lowing speeds:• At or below V2 speeds, control to V2 speeds• between V2 and V2 + 10 control to existing

speeds• at or above V2 + 10 speed, control to V2

+ 10.However, if pitch attitude required to maintainV2 + 10 KIAS (3 engines) or V2 (2 engines)speed is greater than 22 degrees, pitch com-mand will limit stabilized pitch attitude to notexceed 22 degrees. (FD mode only).Performance indicates PMS selected causingsystem to maintain computed PMS outputs bycontrolling pitch attitude.Applicable when PMS is not installed.Applicable when PMS is installed