Meggitt 60-2 Скачать руководство пользователя страница 5

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2nd Ed: Nov 01, 01

SYS 60-2 POH

Table of Contents

Section

Page

4.2.2

Pitch Axis Modes.....................................................................4-20

4.2.2.1

Vertical Speed (VS)................................................4-20

4.2.2.2

Altitude Hold (ALT).................................................4-21

4.2.2.3

Intercepting and Coupling the Glideslpoe......4-21

4.2.2.4

Manual Arm/Automatic Capture..........................4-22

4.2.2.5

Elevator Trim Indicator..........................................4-25

4.2.2.6

Optional Autotrim....................................................4-26

4.3

Flight Director Operations (Optional)................................................4-26

4.3.1

Single Cue ............................................................................4-26

4.3.2

Two Cue .................................................................................4-27

4.4

Yaw Damper/Rudder Trim System (Optional)................................4-27

5.0

Appendixes..........................................................................................................5-3

6.0

Glossary................................................................................................................6-3

Содержание 60-2

Страница 1: ...System 60 2 Autopilot Pilot s Operating Handbook ...

Страница 2: ...s pages changed added or deleted by revision Record of Revisions Retain this record in front of handbook Upon receipt of a revision insert changes and complete table below Revision Number Revision Date Insertion Date Initials 1 st Edition 29 Mar 1999 2 nd Edition 01 Nov 2001 ...

Страница 3: ...ii 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 4: ...on 3 5 3 3 1 Vertical Speed VS 3 5 3 3 2 Altitude ALT 3 6 3 3 3 UP 3 6 3 3 4 Down DN 3 6 4 0 Procedures 4 3 4 1 Pre Flight Procedures 4 3 4 1 1 Roll Axis 4 3 4 1 2 Pitch Altitude and Vertical Speed 4 4 4 1 3 Autotrim 4 5 4 2 Normal Operating Procedures 4 6 4 2 1 Roll Axis Modes 4 6 4 2 1 1 Heading 4 6 4 2 1 2 VOR Intercept and Tracking DG 4 6 4 2 1 3 VOR Approach DG 4 8 4 2 1 4 Localizer Intercept...

Страница 5: ...d ALT 4 21 4 2 2 3 Intercepting and Coupling the Glideslpoe 4 21 4 2 2 4 Manual Arm Automatic Capture 4 22 4 2 2 5 Elevator Trim Indicator 4 25 4 2 2 6 Optional Autotrim 4 26 4 3 Flight Director Operations Optional 4 26 4 3 1 Single Cue 4 26 4 3 2 Two Cue 4 27 4 4 Yaw Damper Rudder Trim System Optional 4 27 5 0 Appendixes 5 3 6 0 Glossary 6 3 ...

Страница 6: ...nd Tracking DG 4 11 4 5 Back Course Straight In Approach DG 4 12 4 6 Back Course Procedure Turn DG 4 13 4 7 Horizontal Situation Indicator HSI 4 14 4 8 Straight In Localizer Approach and Tracking Optional HSI 4 16 4 9 Procedure Turn Localizer Approach and Tracking Optional HSI 4 17 4 10 Back Course Straight In Approach Optional HSI 4 18 4 11 Back Course Procedure Turn Optional HSI 4 19 4 12 Glides...

Страница 7: ...vi 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 8: ...2nd Ed Nov 01 01 1 1 SYS 60 2 POH SECTION 1 INTRODUCTION ...

Страница 9: ...1 2 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 10: ...opilot Airplane Flight Manual Supplement AFMS Pilots Operating Handbook Supplement POHS or Supplemental Flight Manual SFM Refer to the specific AFMS POHS or SFM for your aircraft specific information and emergency operating procedures If the autopilot is to be used during Instrument Flight Rules IFR opera tions we recommend that you develop a thorough understanding of the autopilot system its func...

Страница 11: ...1 4 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 12: ...2nd Ed Nov 01 01 2 1 SYS 60 2 POH SECTION 2 BLOCK DIAGRAM ...

Страница 13: ...2 2 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 14: ...IONAL AUTOPILOT MASTE R SW ITCH TRIM MASTE R SW ITCH OPTIONAL S NAV G S HSI OPTIONAL PITCH S ERVO TURN COORDINATOR DIRECTIONAL GYRO OPTIONAL ABSOLUTE PRESSURE TRANSDUCER PUSH H DG ROLL SERV O YAW SERVO OPTIONAL YAW DAMPE R OPTIONAL N O P ITCH INFORMAT I O N TURN COORDINATOR 2 MIN FLIGHT DIRECTOR OPTIONAL A P DISC TRIM INTRPT ROLL COMPUTER PITCH COMPUTER SELECTOR ALERTER OPTIONAL SYSTEM 60 2 PROGRA...

Страница 15: ...2 4 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 16: ...2nd Ed Nov 01 01 3 1 SYS 60 2 POH SECTION 3 AUTOPILOT OVERVIEW ...

Страница 17: ...3 2 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 18: ...cator HSI Very High Frequency Omnidirectional Radio Range VOR Localizer LOC Long Range Navigation LORAN and the Global Positioning System GPS navigation receivers It then computes roll servo commands for stabili zation turns radio intercepts and tracking The Pitch Computer receives signal inputs from the altitude pressure transducer internal accelerometer glideslope deviation indicator and off war...

Страница 19: ...rovides heading preselect and turns through the use of the heading bug on the Directional Gyro DG or optional Horizontal Situation Indicator HSI 3 2 2 Navigation NAV The NAV mode provides roll commands for automatic intercept and track ing of selected VOR LOC RNAV LORAN GPS navigational signals ...

Страница 20: ...es of Operation NOTE Before engaging a pitch mode of operation a roll mode must first be engaged 3 3 1 Vertical Speed VS The VS mode provides pitch synchronization of the autopilot to the air craft vertical speed To activate press the VS mode switch This acti vates the UP DN Down pitch modifier switches for pilot commanded changes of vertical speed up to a maximum of 1600 feet per minute rate of c...

Страница 21: ... ond of continuous switch depression 3 3 4 Down DN When the VS mode is activated the DN switch will increase the rate of descent or decrease the rate of climb 160 FPM for each second of con tinuous switch depression When the altitude hold mode is engaged the UP and DN switches may be used to adjust the altitude The UP and DN switches produce a 20 foot change in altitude for each second of depressi...

Страница 22: ...ciation will also illuminate The pilot should manually trim the aircraft in the direction indicated until the light extinguishes The aircraft will then be 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 normally mounted on the control wheel 2 If pitch axis is engaged operate the trim switch either way T...

Страница 23: ...3 8 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 24: ...2nd Ed Nov 01 01 4 1 SYS 60 2 POH SECTION 4 PROCEDURES ...

Страница 25: ...4 2 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 26: ... bug to center 4 Grasp the control wheel and manually turn it left and right to overpower the roll servo There should be a noticeable increase in control wheel friction no excessive looseness no ratcheting or noise 5 Turn on the NAV radio and tune a valid VOR signal Then engage the NAV mode observing the NAV annunciation Move the VOR OBS so that the needle swings left and right The control wheel s...

Страница 27: ...should sound During overpower there should be no excessive 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 UP switch Pitch should disengage after about 5 seconds release UP switch pitch should reengage E Hold the control wheel press and hold the DN swi...

Страница 28: ...DG and VS modes 2 Grasp control wheel slowly push forward After approximately 3 seconds trim should run nose up 3 Slowly pull control wheel aft After approximately 3 seconds trim should move nose down 4 Move manual trim switch up and down Autopilot disengages trim should operate in commanded direction trim switch will disengage autopilot only when pitch is engaged 5 Reengage HDG and VS modes and p...

Страница 29: ...eading can be selected by repositioning the heading bug When operating in the HDG mode the system is not coupled to any ground navigation device It flies a specific heading only It will be necessary to monitor navigation instruments for course deviation due to wind drift and to establish wind correction angles Fig 4 1 Directional Gyro 4 2 1 2 VOR Intercept and Tracking DG 1 To intercept and track ...

Страница 30: ...begin between 100 full scale needle deflection and 20 of full scale During the intercept sequence the system operates in maximum gain and sensitivity to needle position and can command 90 of a standard rate turn When the selected course is intercepted and the needle is within 15 of centered the CAP annunciator illuminates indicating course capture and initiation of the tracking gain sequence This ...

Страница 31: ...AV annunciator flashes as a warning It should flash at station passage because of short term needle excursion beyond 50 It also flashes when the NAV flag is in view When that occurs the FAIL annunciation will illuminate NOTE When operating in the NAV SOFT mode and needle deflection of 50 or more is experienced for 1 minutes the gain program will switch to NAV CAP SOFT increasing sensitivity and au...

Страница 32: ...s the high sensitivity gain scheduling 4 2 1 4 Localizer Intercept and Tracking DG When a localizer frequency is channeled and NAV mode is selected the system will automatically execute high sensitivity gain for the approach and automatically activates the APR mode The APR annunciator illuminates Set the heading bug to the inbound localizer course and engage the NAV mode to intercept and track the...

Страница 33: ...course c Press NAV mode switch Autopilot will intercept capture and track the localizer course 2 If a missed approach is declared at the middle marker a Disconnect the autopilot and stabilize the aircraft for the missed approach climb b Set the HDG bug to the published missed approach heading c Press the HDG mode switch d Press the VS mode switch if desired Fig 4 3 ...

Страница 34: ...ing bug to published outbound LOC heading c Push REV mode switch 2 a Set heading bug to outbound procedure turn heading b Press HDG mode switch 3 In 90 increments set heading bug to inbound procedure turn heading 4 a Set heading bug to inbound LOC heading b Press NAV mode switch Autopilot will intercept track and capture localizer course inbound to the airport Fig 4 4 ...

Страница 35: ...ght In Approach DG 1 a Tune navigation radio to LOC frequency b Set heading bug to the back course inbound final approach heading c Press REV mode switch Autopilot will intercept and track the back course to the airport Fig 4 5 265 085 Back Course 310 N ...

Страница 36: ...NAV mode switch 2 a Set heading bug to outbound procedure turn heading b Press HDG mode switch 3 In 90 increments set heading bug to inbound procedure turn heading 4 a Set heading bug to published final approach course heading b Press REV mode switch Autopilot will complete intercept capture and tracking of localizer back course inbound Fig 4 6 265 N 085 310 130 1 2 Back Course ...

Страница 37: ...e required frequency Set the desired VOR radial or Localizer course with the course selector Press and release the NAV mode switch NOTE Localizer approaches with an HSI require that the inbound front course be set on the course selector for either front course or back course operations To track inbound on the front course activate the NAV mode NAV mode also is used for tracking outbound on the bac...

Страница 38: ...ill follow the heading bug until the aircraft reaches the proper on course turn point It will then switch from HDG to NAV mode automatically Selected angle intercepts may be used during VOR localizer front course and back course REV operations Localizer intercept angles greater than 45º usually result in some course overshoot depending on the distance from the station and speed of the aircraft The...

Страница 39: ...ch is declared disconnect the autopilot and stabilize the aircraft for the missed approach climb before engaging HDG mode NOTE To establish a pilot selectable angle of intercept dual mode intercept set the course pointer to the published inbound front course heading and the heading bug to the desired heading to establish the selected angle intercept or to the Radar Vector HDG Press the HDG and NAV...

Страница 40: ...ter c Push REV mode switch 2 a Set heading bug to published outbound procedure turn heading b Press HDG mode switch 3 a In 90 increments set heading bug to inbound procedure turn heading b When established on inbound procedure turn heading press NAV mode switch Autopilot will intercept track and capture the localizer 4 Once established in NAV APR mode the heading bug can be set to the published mi...

Страница 41: ...ectable angle of intercept dual mode intercept on the back course set the course pointer to the published inbound front course heading and the heading bug to the desired heading to establish the selected angle intercept or to the Radar Vector HDG Press the HDG and REV mode switches simultaneously Upon capture of the back course the autopilot automatically cancels HDG mode and tracks the final appr...

Страница 42: ...ointer to the published inbound LOC front course heading c Press the NAV mode switch The autopilot will track the back course outbound 2 a Set the heading bug to the published outbound procedure turn heading b Press the HDG mode switch 3 a In 90 increments set the heading bug to the inbound procedure turn heading b Position the aircraft on the localizer Back Course with the HDG bug c Press REV mod...

Страница 43: ...sh a 500 FPM rate of climb press and hold the UP modifier switch for approximately 3 seconds to transition from level flight to a 500 FPM climb To descend at approximately 500 FPM press the DN switch for approximately 3 seconds NOTE If the VS mode annunciator flashes it indicates an excessive error between the actual VS compared to the selected VS The pilot should adjust the aircraft power or corr...

Страница 44: ...ssion will change the altitude approximately 20 ft up to a maximum of 200 feet NOTE If more than 200 feet of altitude correction is necessary reengage the VS mode fly to the desired altitude and reengage the ALT mode 4 2 2 3 Intercepting and Coupling the Glideslope To arm the automatic glideslope GS capture function the following conditions must be met 1 NAV receiver must be tuned to the appropria...

Страница 45: ... arming of the GS This is done by 1 Pressing the ALT switch once if operating in the altitude hold mode 2 Pressing the ALT switch twice if operating in the VS mode Once capture is achieved the GS annunciation will illuminate and the ALT annunciation will extinguish NOTE If it becomes necessary to establish a holding pattern at the outer marker automatic glideslope arming can be disabled by pressin...

Страница 46: ...aps to the proper position refer to FAA AFM supplement for flap use limitations 3 At glideslope intercept lower the landing gear if applicable and adjust power for the desired descent speed and published rate of descent For best tracking results make small power adjustments to maintain the desired rate of descent and airspeed 4 At the decision height or the autopilot s minimum operating altitude w...

Страница 47: ...ready in altitude hold d When the NAV mode switch is pressed and if the aircraft is below the glideslope the APR and GS annunciations will illuminate 3 a Upon capture of LOC course NAV APR ALT and GS will illuminate if all conditions for glideslope operation are met see text ref Glideslope Operation This signifies automatic arming of the Glideslope function b Upon Glideslope capture the ALT annunc...

Страница 48: ...e the approach rearm the GS function by pressing and releasing the NAV switch once again Rearming will occur when all other required functions have been met 4 2 2 5 Elevator Trim Indicator The autopilot pitch servo contains a sensor for detection of elevator out of trim loads Without optional Autotrim when such forces exceed a preset level the TRIM annunciator will illuminate and either the UP or ...

Страница 49: ...zontal display to compensate for different seat heights And a remote switch allows manual flight control via Flight Director commands For proper flight technique the system presentation requires the pilot to roll and pitch the aircraft toward the display until the delta shaped reference is tucked into the steering command bars indicating that commands have been satisfied For example if the display...

Страница 50: ...horizon and right of desired course or centerline A left bank and a pitch up attitude is dictated As bank angle and vertical speed approach desired values the bars will move to the center or crossed hair position At this point commands have been satisfied Thereafter it is necessary only to maneuver the aircraft to keep the bars centered in order to accurately fly programmed modes It should be note...

Страница 51: ...4 28 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 52: ...2nd Ed Nov 01 01 5 1 SYS 60 2 POH SECTION 5 APPENDIXES ...

Страница 53: ...5 2 2nd Ed Nov 01 01 SYS 60 2 POH Table of Contents Appendix A System Failure and Caution Annunciations 5 3 Roll Axis 5 3 Pitch Axis 5 4 Appendix B Specifications 5 5 ...

Страница 54: ... by 50 needle until problem is deflection identified Cross check raw NAV data compass HDG and radio operation Flashing NAV or Indicates invalid Check navigation REV steadyFAIL radio navigational radio Use HDG mode signal until problem is corrected NOTE If any of the above annunciations s occur at low altitude or during an actual instrument approach disengage the autopilot execute a missed approach...

Страница 55: ...n signal approach inform ATC Flashing VS Indicates excessive Reduce command vertical speed error VS and or adjust over selected VS power usually in climb Flashing GS Indicates manual To reenable reset steady DSBL glideslope disable NAV switch NOTE If any of the above annunciations occur at low altitude or during an actual instrument approach disengage the autopilot and execute a missed approach In...

Страница 56: ...Approx Flag RPM detector operating limits Nominal less 20 Current requirements 8 amp Weight 1 8 lbs Dimensions 3 275 x 3 275 x 5 62 in Roll Computer Power required 14 28 VDC Weight 2 3 lbs Dimensions 5 25 x 2 1 x 13 3 in Pitch Computer Power required 14 28 VDC Weight 3 0 lbs Dimensions 5 25 x 2 1 x 13 3 in NOTE Unit will operate with either 14 or 28 VDC However servo ampli fier circuit board must ...

Страница 57: ...25 x 3 75 in Pitch Servo Trim Sensor Power required 14 28 VDC Current Included in system value power required Weight 2 9 lbs Dimensions 7 25 x 3 75 in Altitude Pressure Transducer Power required supplied by pitch computer 10 VDC Pressure range 0 15 PSI Absolute Overpressure 150 operating maximum System Current Requirement Average operating current 1 0 amp Maximum current 5 0 amp ...

Страница 58: ...2nd Ed Nov 01 01 6 1 SYS 60 2 POH SECTION 6 GLOSSARY ...

Страница 59: ...6 2 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 60: ...tioning System GS Glideslope HDG Heading HSI Horizontal Situation Indicator IFR Instrument Flight Rules IN Inches LBS Pounds LOC Localizer LORAN Long Range Navigation N A Not Applicable NAV Navigation REV Reverse OBS Omnibearing Selector POH S Pilot Operating Handbook Supplement PSI Pounds Per Square Inch RDY Ready REV Reverse RPM Revolutions Per Minute SFM Supplemental Flight Manual TC Turn Coord...

Страница 61: ...6 4 2nd Ed Nov 01 01 SYS 60 2 POH Page Intentionally Blank ...

Страница 62: ...lephone 940 325 9406 FAX 940 325 3904 1 800 USA STEC www s tec com Information in this document is subject to change without notice 2001 S TECCorporation Allrightsreserved PrintedintheUnitedStatesofAmerica S TEC and the S TEC logo are registered trademarks of S TEC Corporation P N 8783 Date 01 November 20 01 Printed in USA ...

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