System 60-2 Autopilot Pilot's Operating Handbook

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System 60-2 AutopilotPilot's OperatingHandbook

SYS 60-2 POHList of Effective Pages* Asterisk indicates pages changed, added, or deleted byrevision.Record of RevisionsRetain this record in front of handbook. Upon receipt of arevision, insert changes and complete table below.Revision Numberst1 Editionnd2 Edition2nd Ed: Nov 01, 01Revision DateInsertion Date/Initials29 Mar 199901 Nov 2001i

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SYS 60-2 POHTable of ContentsSectionPage1.0Introduction.1-32.0Block Diagram.2-33.0Autopilot Overview.3-33.1System 60-2 Programmer/Annunciator.3-33.2Roll Modes of Operation.3-43.34.03.2.1Heading (HDG).3-43.2.2Navigation (NAV).3-43.2.3Reverse (REV).3-5Pitch Modes of Operation.3-53.3.1Vertical Speed (VS).3-53.3.2Altitude (ALT).3-63.3.3UP.3-63.3.4Down (DN).3-6Procedures.4-34.14.2Pre-Flight Procedures.4-34.1.1Roll Axis.4-34.1.2Pitch/Altitude and Vertical Speed.4-44.1.3Autotrim.4-5Normal Operating Procedures.4-64.2.12nd Ed: Nov 01, 01Roll Axis Modes.4-64.2.1.1Heading.4-64.2.1.2VOR Intercept and Tracking (DG).4-64.2.1.3VOR Approach (DG).4-84.2.1.4Localizer Intercept and Tracking (DG).4-94.2.1.5VOR/Localizer Intercept and Tracking (HSI).4-144.2.1.6Dual Mode Intercept.4-15iii

SYS 60-2 POHTable of ContentsSectionPage4.2.24.34.4Pitch Axis Modes.4-204.2.2.1Vertical Speed (VS).4-204.2.2.2Altitude Hold (ALT).4-214.2.2.3Intercepting and Coupling the Glideslpoe.4-214.2.2.4Manual Arm/Automatic Capture.4-224.2.2.5Elevator Trim Indicator.4-254.2.2.6Optional Autotrim.4-26Flight Director Operations (Optional).4-264.3.1Single Cue .4-264.3.2Two Cue .4-27Yaw Damper/Rudder Trim System nd Ed: Nov 01, 01

SYS 60-2 POHList of FiguresFigurePage2-1System 60-2 Block Diagram.2-33-1System 60-2 Programmer/Annunciator.3-34-1Directional Gyro.4-64-2VOR/LOC/GPS.4-84-3Straight-In Localizer Approach and Tracking (DG).4-104-4Procedure Turn Localizer Approach and Tracking (DG).4-114-5Back Course Straight-In Approach (DG).4-124-6Back Course Procedure Turn (DG).4-134-7Horizontal Situation Indicator (HSI).4-144-8Straight-In Localizer Approach and Tracking (Optional HSI).4-164-9Procedure Turn Localizer Approach and Tracking (Optional HSI).4-174-10 Back Course Straight-In Approach (Optional HSI).4-184-11Back Course Procedure Turn (Optional HSI).4-194-12 Glideslope Intercept and Track.4-234-13 Procedure Turn for Glideslope Approach.4-242nd Ed: Nov 01, 01v

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SYS 60-2 POHSECTION 1INTRODUCTION2nd Ed: Nov 01, 011-1

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SYS 60-2 POH1.0IntroductionThe primary purpose of the System 60-2 Pilot Operating Handbook (POH)is to provide pilots with step-by-step Functional Preflight and In-Flight Operating Procedures for the installed system.NoticeThis manual should be used in conjunction with an FAA approved autopilotAirplane Flight Manual Supplement (AFMS), Pilots Operating HandbookSupplement (POHS) or Supplemental Flight Manual (SFM). Refer to thespecific AFMS, POHS, or SFM for your aircraft specific information andemergency operating procedures.If the autopilot is to be used during Instrument Flight Rules (IFR) operations, we recommend that you develop a thorough understanding of theautopilot system, its functions, and characteristics in Visual Meteorological Conditions (VMC). Accomplish this before undertaking an IFR flight.2nd Ed: Nov 01, 011-3

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SYS 60-2 POHSECTION 2BLOCK DIAGRAM2nd Ed: Nov 01, 012-1

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SYS 60-2 POH2.0Block DiagramA U TO P IL O TM A STE R SW ITC HPIT CH I NF OR MATNIONOSY S TEM 6 0-2 P R O G R A M M E R /A N N U N C IATO RTURN CO ORDINATOR2 MINTU R N C O O R D IN ATO RA/P DIS CT R IM IN T R PTA U TO P IL O T D ISC O N N EC T /TR IM IN TE R R U PT SW ITC HPITC HC O M PU TE RA B S O L U TEPR E S SU R ETR A N SD U C E RPITC H S ER V OR O LLC O M PU TE RTRIMTR IM SER VO(O PT IO N A L)TR IM C O M M A N DSW ITC H(O PT IO N A L)TR IMM A STE R SW ITC H(O PT IO N A L)R O LL S E RV OGSP US HH DGSNAVD IR E C TIO N A L G Y R O(O PT IO N A L)VO R /LO C /G P S(SH O W N F OR R EF ER EN C E )H SI(O PT IO N A L)YAW S E R VO(O PT IO N A L)YAW D A M PE R(O PT IO N A L)SE L EC TO R /A L ER TE R(O PT IO N A L)FL IG H T D IR E C TO R(O PT IO N A L)Fig. 2-1. System 60-2 Block Diagram2nd Ed: Nov 01, 012-3

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SYS 60-2 POHSECTION 3AUTOPILOT OVERVIEW2nd Ed: Nov 01, 013-1

SYS 60-2 POHPage Intentionally Blank3-22nd Ed: Nov 01, 01

SYS 60-2 POH3.0Autopilot Overview3.1System 60-2 Programmer/AnnunciatorFig. 3-1. System 60-2 Programmer/AnnunciatorThe System 60-2 Programmer/Annunciator is a rate based autopilot thatcontrols the roll and pitch axis of the aircraft. The autopilot's main function is to convert pilot commands to logic signals for both the roll andpitch computers. As the pilot enters the desired mode by pressing themode selector switch, the computer acknowledges the selection by illuminating that annunciator.The Roll Computer receives signal inputs from the turn coordinator,Directional Gyro or optional Horizontal Situation Indicator (HSI), Very HighFrequency Omnidirectional Radio Range (VOR) / Localizer (LOC), LongRange Navigation (LORAN) and the Global Positioning System (GPS)navigation receivers. It then computes roll servo commands for stabilization, turns, radio intercepts, and tracking.The Pitch Computer receives signal inputs from the altitude pressuretransducer, internal accelerometer, glideslope deviation indicator, andoff warning flag contained in the glideslope receiver. The pitch systemprovides vertical speed control and altitude hold, as well as automatic/manual glideslope capture.Vertical speed reference is provided by the barometric pressure transducer, while automatic and manual pitch trim sensing is provided by thepitch servo. Drive for the elevator trim servo is provided by the pitchcomputer. All modes use the transducer signal for a VS or ALT reference.2nd Ed: Nov 01, 013-3

SYS 60-2 POH3.2Roll Modes of Operation3.2.1Heading (HDG)The HDG mode provides heading preselect and turns through the use ofthe heading bug on the Directional Gyro (DG) or optional HorizontalSituation Indicator (HSI).3.2.2Navigation (NAV)The NAV mode provides roll commands for automatic intercept and tracking of selected VOR/LOC/RNAV/LORAN/GPS navigational signals.3-42nd Ed: Nov 01, 01

SYS 60-2 POH3.2.3Reverse (REV)REV mode provides roll commands for automatic intercept and trackingof the back course localizer inbound or the front course localizer outbound.3.3Pitch Modes of OperationNOTE: Before engaging a pitch mode of operation, a roll mode mustfirst be engaged.3.3.1Vertical Speed (VS)The VS mode provides pitch synchronization of the autopilot to the aircraft vertical speed. To activate, press the VS mode switch. This activates the UP/DN (Down) pitch modifier switches for pilot commandedchanges of vertical speed, up to a maximum of /- 1600 feet per minute(rate of climb/descent).2nd Ed: Nov 01, 013-5

SYS 60-2 POH3.3.2Altitude (ALT)The ALT mode engages the altitude hold mode, capturing the altitudeattained at the time of activation.3.3.3UPWhen the VS mode is activated, the UP modifier switch will increase therate-of-climb or decrease the rate-of-descent at 160 FPM for each second of continuous switch depression.3.3.4Down (DN)When the VS mode is activated, the DN switch will increase the rate-ofdescent or decrease the rate-of-climb 160 FPM for each second of continuous switch depression.When the altitude hold mode is engaged, the UP and DN switches maybe used to adjust the altitude. The UP and DN switches produce a 20foot change in altitude for each second of depression, up to a maximumof 200 feet. Altitude changes of more than 200 feet require reactivation ofthe VS mode.3-62nd Ed: Nov 01, 01

SYS 60-2 POHNOTE: For aircraft without auto trim, or where auto trim is disabledor turned off, the UP/DN switches are used to annunciate out of trimconditions when either the VS or ALT modes are engaged. If up trimis required, the UP switch will illuminate. If down trim is needed, theDN switch will illuminate. In both cases, the TRIM annunciation willalso illuminate. The pilot should manually trim the aircraft in thedirection indicated, until the light extinguishes. The aircraft will thenbe trimmed for existing flight conditions.NOTE: There are four ways to disengage the autopilot (A/P):1. Press the A/P disconnect/trim interrupt switch (normallymounted on the control wheel).2. If pitch axis is engaged, operate the trim switch either way.(This will not disconnect the A/P if Autotrim is disabled or notinstalled).3. Turn off the Autopilot Master Switch.4. Locate and pull the autopilot circuit breaker.2nd Ed: Nov 01, 013-7

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SYS 60-2 POHSECTION 4PROCEDURES2nd Ed: Nov 01, 014-1

SYS 60-2 POHPage Intentionally Blank4-22nd Ed: Nov 01, 01

SYS 60-2 POH4.0Procedures4.1Pre-Flight ProceduresNOTE: To perform the system function check, adequate DC voltagemust be supplied to the system, either 12 or 24 VDC, depending onthe aircraft.4.1.1Roll AxisThe following is a step by step procedure for preflighting the Roll Axis:1. Place the A/P Master Switch to the TEST position. This shouldresult in illumination of all annunciation’s: RDY, HDG, VS, FD, NAV,ALT, REV, APR, GS, SEL, UP, DN, FAIL, DSABL, TRIM, CAP, and SOFT.After all annunciation’s are observed, place the A/P Master Switch tothe ON position. If the Turn Coordinator gyro is up to speed, only theRDY annunciation should remain on.2. Rotate the heading knob on the Directional Gyro (DG) to positionthe bug under the lubber line.3. Engage the HDG mode, and observe the HDG annunciation. Thenmove the DG heading knob left and right. The control wheel shouldmove in the direction of bug travel. Return the bug to center.4. Grasp the control wheel and manually turn it left and right tooverpower the roll servo. There should be a noticeable increase incontrol wheel friction, no excessive looseness, no ratcheting or noise.5. Turn on the NAV radio and tune a valid VOR signal. Then engagethe NAV mode, observing the NAV annunciation. Move the VOR/OBSso that the needle swings left and right. The control wheel shouldmove in the direction of needle travel. The NAV annunciation shouldflash when CDI deflection is over 50%.6. Select REV mode, and observe the REV annunciation. Again,rotate the VOR/OBS knob. The control wheel should move oppositethe direction of needle travel. The NAV annunciation should flashwhen CDI deflection is over 50%.7. Channel a nonvalid VOR signal. The NAV annunciation shouldflash, and FAIL annunciation should illuminate (if the radio has aNAV flag output).8. Disconnect by pressing and releasing the control wheel mountedA/P disconnect switch. Move the control wheel to ensure freedom ofcontrols, and check to see that the RDY annunciator is flashing forapproximately 5 seconds to indicate autopilot disconnect.2nd Ed: Nov 01, 014-3

SYS 60-2 POH4.1.2Pitch/Altitude and Vertical SpeedThe following is a step by step procedure for pre-flighting the Pitch/Altitude and Vertical Speed Systems:1. Be sure the Autopilot Master Switch is ON, and that a roll axismode has been selected.2. Move the control wheel to level flight position and engage the VSmode. Press the UP modifier switch and hold. The control wheelshould move aft, slowly. Press the DN switch and hold. The controlwheel should move slowly forward.NOTE: On some aircraft the autopilot may not be able to lift theelevators without pilot assistance during ground operation.3. Overpower the pitch function by pulling the control wheel slowlyaft. The TRIM annunciator and DN switch should illuminate and theaudio warning should sound. Slowly push the control wheel forward.The TRIM annunciation and UP switch should illuminate and audiowarning should sound. During overpower, there should be noexcessive play in the controls or ratcheting noise.4. Pitch Limiter Test:A. Place the Master Switch to TEST position.B. Engage HDG mode.C. Engage ALT mode.D. Center and hold the control wheel, press and hold the UPswitch. Pitch should disengage after about .5 seconds, releaseUP switch, pitch should reengage.E. Hold the control wheel, press and hold the DN switch. Pitchshould disengage after about .5 seconds, release DN switch,pitch should reengage.CAUTIONIf the pitch servo does not disengage when either the UP orDN modifier switch is engaged, the limit accelerometer mayhave failed. Do not use the autopilot pitch section until theproblem is corrected. This check should be performed onceper flight day. (Check FAA approved AFM supplement.)NOTE: If optional autotrim is not installed, this is the end of thepreflight test. Press and release the disconnect switch on thecontrol wheel, and place the Autopilot Master Switch in the OFFor ON position. Move aircraft controls to ensure freedom ofmovement and to make sure the autopilot has disconnected.4-42nd Ed: Nov 01, 01

SYS 60-2 POH5. If the autopilot is equipped with optional autotrim, proceed withthe following steps:A. Place Trim and Autopilot Master Switches to ON.B. Operate Manual Trim Switch (both segments) nose DN.Autopilot TRIM annunciator flashes and trim moves nose down(check manual trim wheel).C. Operate trim switch (both segments) UP, autopilot TRIMannunciator flashes, trim moves nose up (check manual trimwheel). Grasp aircraft trim control and overpower electric trim.D. Operate each segment of the trim switch separately. Trimshould not operate unless both halves of the trim switch areoperated simultaneously in the same direction.E. With trim operating, press trim interrupt switch. Trim motionshould cease while interrupt switch is activated. Trim motionshould resume when interrupt switch is released.4.1.3Autotrim1. Place autopilot and Trim Master Switches to ON and engageautopilot HDG and VS modes.2. Grasp control wheel, slowly push forward. After approximately 3seconds, trim should run nose up.3. Slowly pull control wheel aft. After approximately 3 seconds, trimshould move nose down.4. Move manual trim switch up and down. Autopilot disengages,trim should operate in commanded direction (trim switch willdisengage autopilot only when pitch is engaged).5. Reengage HDG and VS modes and press trim interrupt/APdisconnect switch. Autopilot should disengage.6. Trim aircraft for takeoff and check controls for freedom ofmovement. Be sure the autopilot and trim are disengaged.CAUTIONIf either the manual electric trim or autotrim fails during any portionof the preflight, turn Trim Master Switch OFF. Do not use theelectric trim until the fault is corrected. With Trim Master SwitchOFF, the autopilot trim indicators and audio warning arereactivated. If the electric trim fails, or has an in-flight powerfailure, the system automatically reverts to indicator lights andaudio warning. Should this occur, turn Trim Master Switch OFF,and revert to aircraft manual trim until the fault is corrected.2nd Ed: Nov 01, 014-5

SYS 60-2 POH4.2NORMAL OPERATING PROCEDURESNOTE: In order to activate any mode of the System 60-2 Autopilot, theMaster Switch must be in the ON position and the RDY annunciatormust be illuminated.4.2.1Roll Axis Modes4.2.1.1 Heading1. Trim the aircraft for existing flight conditions.2. Set the heading bug on the DG or optional HSI to the desiredheading and press the HDG switch.NOTE: The HDG annunciator will illuminate. A new heading can beselected by repositioning the heading bug. When operating in theHDG mode, the system is not coupled to any ground navigationdevice. It flies a specific heading, only. It will be necessary to monitornavigation instruments for course deviation due to wind drift, and toestablish wind correction angles.P US HH DGFig. 4-1. Directional Gyro4.2.1.2 VOR Intercept and Tracking (DG)1. To intercept and track a VOR signal, tune the navigation radioreceiver to the proper frequency.2. Select the desired VOR radial on the NAV indicator.3. Move the heading bug in the direction of desired travel, to matchthe course of selected radial.4. Engage the NAV mode.4-62nd Ed: Nov 01, 01

SYS 60-2 POHNOTE: If the VOR needle is at full-scale deviation, the autopilot willestablish a 45º intercept angle to the desired course. As the aircraftapproaches the selected radial, the autopilot senses the closurerate, and gradually, smoothly shallows the intercept angle. Thepoint at which this turn begins is variable, depending on the aircraftposition and closure rate to the

3.0 Autopilot Overview 3.1 System 60-2 Programmer/Annunciator Fig. 3-1. System 60-2 Programmer/Annunciator The System 60-2 Programmer/Annunciator is a rate based autopilot that controls the roll and pitch axis of the aircraft. The autopilot's main func-tion is to convert pilot commands to logic signals for both the roll and pitch computers.

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