Cirrus Perspective Line Maintenance Manual

REVISION DATE SECTION PAGE DESCRIPTION 10 10‐8 Revised entire section 10.4.4 through step T. Added important statement regarding loading splash screen. 10 10‐25 Added SR20 to step 2. 10 10‐27 Revised section 10.9. E 9/21/09 Front Content ix GDU software version to 10.0. 1 1‐1 Page 1‐1: changed name of SR22T to “SR22 Turbo Normalized.” 2 2‐1 Changed name of SR22T to “SR22 Turbo Normalized.” 4 4‐2 Added statement at the end of section 4.3. 4‐4 Revised table 4‐1 to support GDU 10.0 software. 5 5‐10 Added new section 5.4, Data Path Indications oin the Main and GIA Configuration pages. 5‐16 Added new section 5.5, Troubleshooting Tables. 5‐102 Added new section 5.17, Troubleshooting the S‐TEC 55x Interface. 7 7‐2 Revised sections 7.1.1 and 7.1.2, GDU Software Loading and Configuration Procedure. ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page vii 190-00920-00 Rev. E REVISION DATE SECTION PAGE DESCRIPTION 8 8‐4 Edited opening paragraph in section 8.5. 8‐8 Added new section 8.5.1, Port Status Tests and added new screen shots to support text. 10 Global Changed name of SR22T to “SR22 Turbo Normalized.” 10‐25 Added section 10.7, Navigation Databases for GDU 10.0. 10‐27 Added “Pre GDU 10.0” to section title. 10‐28 Added “Expanded Basemap” to section title. Changed wording of Jeppesen ChartView, Cirrus Startup Screens, and Cirrus Checklist text. 10‐29 Added steps to troubleshooting table. 10‐31 Added SVS related alert message table. ____________________________________________________________ Page viii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 DOCUMENT PAGINATION Section Pages Front Matter I to xviii Section 1 1‐1 to 1‐2 Section 2 2‐1 to 2‐10 Section 3 3‐1 to 3‐6 Section 4 4‐1 to 4‐8 Section 5 5‐1 to 5‐118 Section 6 6‐1 to 6‐10 Section 7 7‐1 to 7‐62 Section 8 8‐1 to 8‐12 Section 9 9‐1 to 9‐4 Section 10 10‐1 to 10‐32 Appendix A‐1 to A‐32 ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page ix 190-00920-00 Rev. E This manual reflects the operation and configuration of GDU software version 10.0. The following are general safety precautions that are not related to any specific procedure and therefore do not appear elsewhere in this maintenance manual. These are recommended precautions that personnel should understand and apply during the many phases of maintenance and repair. KEEP AWAY FROM LIVE CIRCUITS. Maintenance personnel shall observe all safety regulations at all times. Turn off system power before making or breaking electrical connections. Regard any exposed connector, terminal board, or circuit board as a possible shock hazard. Components which retain a charge shall be discharged only when such grounding does not result in equipment damage. If a test connection to energized equipment is required, make the test equipment ground connection before probing the voltage or signal to be tested. DO NOT SERVICE ALONE. Personnel shall not under any circumstances reach into or enter any enclosure for the purpose of servicing or adjusting the equipment without immediate presence or assistance of another person capable of rendering aid. INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual. ____________________________________________________________ Page x Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 WARNING This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to the Garmin web site at www.garmin.com/prop65. CAUTION The GDU lamps contain mercury and must be recycled or disposed of according to local, state, or federal laws. If you have any questions or would like additional information, please refer to our web site at the following website: www.garmin.com/aboutGarmin/environment/disposal.jsp. CAUTION The GDU 1xxx lens is coated with a special anti‐reflective coating which is very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI‐ REFLECTIVE COATING. It is very important to clean the lens using a clean, lint‐free cloth and an eyeglass lens cleaner that is specified as safe for anti‐reflective coatings. NOTE Actual software configuration may differ between different aircraft models. Procedures given in this manual are for general reference only. Always refer to approved OEM aircraft installation and/or maintenance information for correct software versions/part numbers and procedures for a specific aircraft model when returning an aircraft to service. NOTE To more closely match the LRU nomenclature displayed on the configuration pages, and where appropriate, only the prefix of the LRU will be listed (i.e., GTX 33(X); GTX, etc.). The only duplicate in the prefix of any LRU pertains to the GDL 69(X) XM Satellite Receiver and the GDL 90 GPS WAAS Receiver/UAT. The suffix will be added in that situation. ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page xi 190-00920-00 Rev. E CONTENTS SECTION 1—INTRODUCTION 1.1 MANUAL ORGANIZATION .............................................................................. 1‐1 SECTION 2—LRU DESCRIPTIONS 2.1 GDU 1240A‐30/1040A‐30 (1) ......................................................................... 2‐2 2.2 GDU 1240A‐20/1040A‐20 (1) ......................................................................... 2‐2 2.3 GMA 347 AUDIO PANEL ................................................................................. 2‐3 2.4 GIA 63W INTEGRATED AVIONICS UNIT (IAU) (WAAS ENABLED) ................... 2‐3 2.5 GDC 74A AIR DATA COMPUTER ..................................................................... 2‐4 2.6 GEA 71 ENGINE/AIRFRAME UNIT................................................................... 2‐4 2.7 GTX 32/33 TRANSPONDERS ........................................................................... 2‐5 2.7.1 GTX 32 TRANSPONDER .................................................................................. 2‐5 2.7.2 GTX 33 TRANSPONDER .................................................................................. 2‐5 2.8 GRS 77 ATTITUDE, HEADING, AND REFERENCE UNIT (AHRS) ........................ 2‐5 2.9 GMU 44 MAGNETOMETER ............................................................................ 2‐6 2.10 GDL69/69A SATELLITE DATA LINK RECEIVER ................................................. 2‐6 2.11 GSA 80/81 AFCS SERVO ACTUATOR/GSM 85A SERVO GEARBOX ................. 2‐7 2.11.1 GSA 81 SERVO ACTUATOR ............................................................................. 2‐7 2.11.2 GSA 80 SERVO ACTUATOR ............................................................................. 2‐7 2.11.3 GSM 85A SERVO GEAR BOX ........................................................................... 2‐7 2.12 GTP 59 OAT PROBE ........................................................................................ 2‐8 2.13 GCU 478 REMOTE CONTROLLER .................................................................... 2‐8 2.14 GMC 705 AFCS CONTROL UNIT ...................................................................... 2‐9 2.15 GTA 82 TRIM ADAPTER .................................................................................. 2‐9 2.16 MISCELLANEOUS LRUS ................................................................................. 2‐10 2.16.1 GRC 10 XM REMOTE CONTROL.................................................................... 2‐10 2.16.2 GRT 10 XM WIRELESS TRANSCEIVER ........................................................... 2‐10 ____________________________________________________________ Page xii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 SECTION 3—SYSTEM OVERVIEW 3.1 FLIGHT INSTRUMENTATION ........................................................................... 3‐4 3.2 GFC 700 AUTOPILOT ...................................................................................... 3‐4 3.2.1 FLIGHT DIRECTOR ........................................................................................... 3‐4 3.2.2 AUTOPILOT ..................................................................................................... 3‐4 3.2.3 MANUAL ELECTRIC PITCH TRIM ..................................................................... 3‐5 3.2.4 YAW DAMPER ................................................................................................ 3‐5 3.3 S‐TEC 55X/55SR AUTOPILOT .......................................................................... 3‐5 3.4 NAVIGATION AND COMMUNICATION SYSTEM ............................................. 3‐6 SECTION 4—CONFIGURATION MODE 4.1 SYSTEM OPERATION ...................................................................................... 4‐1 4.2 CONFIGURATION MODE ................................................................................ 4‐1 4.2.1 SOFTKEYS ....................................................................................................... 4‐2 4.3 CONFIGURATION PAGE GROUPS AND PAGES ............................................... 4‐2 4.4 SECURE DIGITAL (SD) CARDS.......................................................................... 4‐4 4.5 'SET' AND 'ACTIVE' COMMANDS .................................................................... 4‐5 4.5.1 SET AND ACTIVE COMMANDS ....................................................................... 4‐5 4.6 CONFIGURATION STATUS .............................................................................. 4‐6 4.7 DATA TRANSMISSION INDICATORS ............................................................... 4‐6 SECTION 5—TROUBLESHOOTING 5.1 CIRRUS PERSPECTIVE™ ALERTING SYSTEM.................................................... 5‐1 5.1.1 DISPLAY FIELDS............................................................................................... 5‐1 5.1.2 SYSTEM ANNUNCIATION TROUBLESHOOTING .............................................. 5‐2 5.2 MESSAGES & ANNUNCIATIONS ..................................................................... 5‐8 5.3 SYSTEM STATUS PAGE (MFD NORMAL MODE) ............................................. 5‐9 5.4 DATA PATH INDICATIONS‐MAIN AND GIA CONFIGURATION PAGES .......... 5‐10 5.4.1 SYSTEM DATA PATHS ................................................................................... 5‐11 5.5 TROUBLESHOOTING TABLES ........................................................................ 5‐16 5.6 GDU RELATED ALERTS AND PROBLEMS ....................................................... 5‐45 5.6.1 GENERAL PROBLEMS ................................................................................... 5‐46 5.6.2 DATABASE AND SOFTWARE ALERTS ............................................................ 5‐47 5.6.3 COOLING ALERTS ......................................................................................... 5‐53 5.6.4 KEY ALERTS ................................................................................................... 5‐53 5.6.5 MISCELLANEOUS ALERTS ............................................................................. 5‐54 ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page xiii 190-00920-00 Rev. E 5.7 GMA 347 RELATED ALERTS AND PROBLEMS ............................................... 5‐60 5.7.1 COMMON PROBLEMS .................................................................................. 5‐60 5.7.2 GMA 347 ALERTS ......................................................................................... 5‐62 5.8 GIA 63W RELATED ALERTS AND PROBLEM .................................................. 5‐63 5.8.1 COM ............................................................................................................. 5‐63 5.8.1.1 COM ADJUSTMENT PROCEDURE ................................................................. 5‐63 5.8.2 GPS ............................................................................................................... 5‐65 5.8.3 NAV .............................................................................................................. 5‐66 5.8.4 G/S................................................................................................................ 5‐66 5.8.5 COM RELATED ALERTS ................................................................................. 5‐66 5.8.6 NAV RELATED ALERTS .................................................................................. 5‐68 5.8.7 G/S RELATED ALERTS ................................................................................... 5‐68 5.8.8 GPS RELATED ALERTS ................................................................................... 5‐69 5.8.9 GIA CONFIGURATION ALERTS ...................................................................... 5‐70 5.9 GRS 77/GMU 44 RELATED ALERTS AND PROBLEMS .................................... 5‐71 5.9.1 COMMON PROBLEMS .................................................................................. 5‐71 5.9.2 GRS 77 RELATED ALERTS .............................................................................. 5‐72 5.9.3 GMU 44 RELATED ALERTS ............................................................................ 5‐73 5.10 GDC 74A RELATED ALERTS AND PROBLEMS ................................................ 5‐74 5.10.1 COMMON PROBLEMS .................................................................................. 5‐74 5.10.2 GDC 74A RELATED ALERTS ........................................................................... 5‐74 5.11 GDC 74A FIELD CALIBRATION UTILITY ......................................................... 5‐75 5.12 GEA 71 RELATED ALERTS AND PROBLEMS .................................................. 5‐82 5.12.1 GEA 71 HIGH‐SIDE CURRENT CALIBRATION PROCEDURE............................ 5‐83 5.13 GTX 32/33 RELATED ALERTS AND PROBLEMS ............................................. 5‐86 5.14 GDL 69A RELATED ALERTS AND PROBLEMS ................................................ 5‐87 5.14.1 COMMON PROBLEMS .................................................................................. 5‐87 5.14.2 GDL 69/69A RELATED ALERTS ...................................................................... 5‐88 5.15 GMC 705 RELATED ALERTS AND PROBLEMS ............................................... 5‐89 5.16 AFCS SYSTEM TROUBLESHOOTING .............................................................. 5‐90 5.16.1 ANNUNCIATIONS AND ALERTS .................................................................... 5‐90 5.16.2 GFC 700 PRE‐FLIGHT TEST AND TROUBLESHOOTING .................................. 5‐92 5.17 TROUBLESHOOTING THE S‐TEC 55X INTERFACE........................................ 5‐102 5.17.1 INTERFACE SUMMARY ............................................................................... 5‐102 5.17.2 FAILURE MODES ......................................................................................... 5‐102 5.17.3 TROUBLESHOOTING INTERFACE PROBLEMS ............................................. 5‐103 5.18 BACKSHELL CONNECTORS.......................................................................... 5‐114 ____________________________________________________________ Page xiv Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 SECTION 6—LRU REPLACEMENT PROCEDURES 6.1 ACCESSING LRUS ............................................................................................ 6‐1 6.2 GDUS .............................................................................................................. 6‐2 6.3 GMA 347 ........................................................................................................ 6‐2 6.4 GIA 63W ......................................................................................................... 6‐2 6.5 GRS 77 ............................................................................................................ 6‐3 6.6 GMU 44 .......................................................................................................... 6‐3 6.7 GDC 74A ......................................................................................................... 6‐3 6.8 GEA 71 ............................................................................................................ 6‐3 6.9 GTX 32/33 ...................................................................................................... 6‐4 6.10 GDL 69A.......................................................................................................... 6‐4 6.11 GSA 80/81 SERVO ACTUATOR........................................................................ 6‐4 6.12 GTA 82 PITCH TRIM ADAPTER ........................................................................ 6‐5 6.13 GCU 478 KEYPAD............................................................................................ 6‐6 6.14 CONFIGURATION MODULE ............................................................................ 6‐7 6.15 GEA BACKSHELL THERMOCOUPLE ................................................................. 6‐8 SECTION 7—LRU SOFTWARE INSTALLATION AND TESTING 7.1 GDU 1240A ..................................................................................................... 7‐2 7.1.1 GDU SOFTWARE LOADING ............................................................................. 7‐2 7.1.2 GDU CONFIGURATION LOADING ................................................................... 7‐2 7.1.3 GDU TESTING ................................................................................................. 7‐7 7.2 GMA 347 ....................................................................................................... 7‐8 7.2.1 GMA SOFTWARE AND CONFIGURATION LOADING ....................................... 7‐8 7.2.2 GMA TESTING................................................................................................. 7‐9 7.3 GIA 63W ....................................................................................................... 7‐11 7.3.1 GIA SOFTWARE AND CONFIGURATION LOADING ....................................... 7‐12 7.3.2 GIA OPTIONAL EQUIPMENT CONFIGURATION LOADING ............................ 7‐13 7.3.3 GIA OPTIONS INTERFACE TESTING............................................................... 7‐15 7.3.4 OPTIONAL STORMSCOPE FUNCTIONAL TEST .............................................. 7‐15 7.3.5 OPTIONAL SKYWATCH FUNCTIONAL TEST ................................................... 7‐17 7.3.6 OPTIONAL DME FUNCTION TEST ................................................................. 7‐19 7.3.7 OPTIONAL ADF TEST..................................................................................... 7‐20 7.3.8 TAWS FUNCTIONAL TEST ............................................................................. 7‐21 7.3.9 GARMIN FLITE CHART FUNCTIONAL TEST ................................................... 7‐23 7.3.10 JEPP CHART VIEW DATABASE LOCATION AND TEST.................................... 7‐24 ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page xv 190-00920-00 Rev. E 7.3.11 SAFE TAXI TEST ............................................................................................. 7‐25 7.3.12 GIA TESTING ................................................................................................. 7‐26 7.3.13 VHF COM INTERFERENCE TEST .................................................................... 7‐26 7.3.14 VOR/LOC/GS TEST ........................................................................................ 7‐27 7.3.15 VOR TEST ...................................................................................................... 7‐28 7.3.16 LOCALIZER/GLIDESLOPE TEST ...................................................................... 7‐28 7.3.17 GFC 700 VOR/LOC/GS TEAT ......................................................................... 7‐28 7.4 GRS 77/GMU 44 ........................................................................................... 7‐30 7.4.1 GRS SOFTWARE LOADING (A CONFIG FILE IS NOT USED IN THE GRS) ........ 7‐30 7.4.2 GMU SOFTWARE LOADING (A CONFIG FILE IS NOT USED IN THE GMU) .... 7‐31 7.4.3 GRS/GMU 44 ALIGNMENT ........................................................................... 7‐32 7.4.4 GRS AHRS TESTING....................................................................................... 7‐44 7.5 GDC 74A ....................................................................................................... 7‐46 7.5.1 GDC SOFTWARE AND CONFIGURATION LOADING ...................................... 7‐46 7.5.2 GDC TESTING ................................................................................................ 7‐47 7.6 GEA 71 ......................................................................................................... 7‐49 7.6.1 GEA SOFTWARE AND CONFIGURATION LOADING ...................................... 7‐49 7.6.2 GEA TESTING ................................................................................................ 7‐50 7.7 GTX 32/33 .................................................................................................... 7‐51 7.7.1 GTX 32/33 SOFTWARE AND CONFIGURATION LOADING ............................ 7‐51 7.7.2 GTX 32/33 TESTING ...................................................................................... 7‐52 7.8 GDL 69A ....................................................................................................... 7‐53 7.8.1 GDL 69A SOFTWARE AND CONFIGURATION LOADING ............................... 7‐53 7.8.2 GDL 69/69A TESTING ................................................................................... 7‐54 7.9 GCU 478 ...................................................................................................... 7‐55 7.9.1 GCU SOFTWARE AND CONFIGURATION LOADING ...................................... 7‐55 7.9.2 GCU TESTING................................................................................................ 7‐56 7.10 GMC 705 ...................................................................................................... 7‐56 7.10.1 GMC SOFTWARE AND CONFIGURATION LOADING ..................................... 7‐56 7.10.2 GMC TESTING ............................................................................................... 7‐56 7.11 GSA 80/81 AUTOPILOT SERVOS AND GTA 82 PTA ....................................... 7‐57 7.11.1 GSA/GTA SOFTWARE AND CONFIGURATION LOADING .............................. 7‐57 7.11.2 GFC 700 AUTOPILOT TESTING ...................................................................... 7‐58 ____________________________________________________________ Page xvi Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 SECTION 8—RETURN TO SERVICE TESTING 8.1 GPS TESTING .................................................................................................. 8‐1 8.1.1 SINGLE GPS TEST PROCEDURE ....................................................................... 8‐1 8.1.2 DUAL GPS TEST PROCEDURE.......................................................................... 8‐1 8.2 GIA TESTING ................................................................................................... 8‐2 8.2.1 SINGLE GIA TEST PROCEDURE........................................................................ 8‐2 8.2.2 DUAL GIA TEST PROCEDURE .......................................................................... 8‐2 8.3 DISPLAY TESTING ........................................................................................... 8‐3 8.3.1 MFD DISPLAY TEST PROCEDURE .................................................................... 8‐3 8.3.2 PFD DISPLAY TEST PROCEDURE ..................................................................... 8‐3 8.4 GCU 478 TEST PROCEDURE ............................................................................ 8‐4 8.5 BACKUP PATH TESTS ...................................................................................... 8‐4 8.5.1 PORT STATUS TESTS ....................................................................................... 8‐8 SECTION 9—PERIODIC MAINTENANCE 9.1 MAINTENANCE INTERVALS ............................................................................ 9‐1 9.2 RECOMMENDED TOOLS ................................................................................. 9‐1 9.3 GENERAL MAINTENANCE PROCEDURES ........................................................ 9‐1 9.4 GFC 700 VISUAL INSPECTION PROCEDURE .................................................... 9‐2 9.5 GSA GREASING PROCEDURE .......................................................................... 9‐2 9.6 GDC RVSM ALTITUDE INSPECTION ................................................................ 9‐3 9.7 CATEGORY B POWER INTERRUPT INSPECTION PROCEDURE......................... 9‐3 ____________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page xvii 190-00920-00 Rev. E SECTION 10—SYSTEM RECONFIGURATION 10.1 DATA CARDS ................................................................................................. 10‐1 10.2 SOFTWARE PART NUMBERS ........................................................................ 10‐1 10.3 HARDWARE AND SOFTWARE COMPATIBILITY CHECK ................................. 10‐2 10.4 SYSTEM SOFTWARE LOADING AND CONFIG PROCEDURE .......................... 10‐3 10.4.1 SYSTEM POWER UP ...................................................................................... 10‐4 10.4.1 COOLING FAN CHECK ................................................................................... 10‐4 10.4.2 MFD AND PFD SOFTWARE LOAD ................................................................. 10‐4 10.4.3 SYSTEM SOFTWARE UPLOAD ....................................................................... 10‐5 10.4.4 OPTIONAL SYSTEMS ACTIVATION ................................................................ 10‐8 10.5 SOFTWARE LOAD CONFIRMATION ............................................................ 10‐22 10.6 AIRCRAFT REGISTRATION NUMBER ENTRY (GTX33 OPTION ONLY) .......... 10‐24 10.7 NAVIGATION DATABASES .......................................................................... 10‐25 10.8 AVIATION DATABASE LOADING (PRE GDU 10.0) ....................................... 10‐27 10.9 OTHER PERSPECTIVE DATABASES .............................................................. 10‐28 10.10 SOFTWARE/CONFIGURATION TROUBLESHOOTING .................................. 10‐29 APPENDIX—CONNECTOR PIN ASSIGNMENTS A.1 GIA 63W ......................................................................................................... A‐1 A.2 P602 (VOR/ILS) ............................................................................................... A‐3 A.3 P603 (MAIN/SERIAL) ...................................................................................... A‐5 A.4 P604 (MAIN DISCRETE) .................................................................................. A‐7 A.5 P605 (I/O #1) .................................................................................................. A‐9 A.6 P606 (I/O #2) ................................................................................................ A‐11 A.7 GDU (P10001) .............................................................................................. A‐13 A.8 GRS 77 (P771)............................................................................................... A‐15 A.9 GMU 44 (P441)............................................................................................. A‐16 A.10 GDC 74A (P741) ............................................................................................ A‐17 A.11 GEA 71 (P701) .............................................................................................. A‐19 A.12 P702 ............................................................................................................. A‐21 A.13 GMA 347 ...................................................................................................... A‐23 A.14 GTX 32/33 .................................................................................................... A‐28 A.15 GDL 69A (P691) ............................................................................................ A‐30 A.16 GMC 710 (P701) ........................................................................................... A‐32 ____________________________________________________________ Page xviii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00 Blank Page ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 1-1 190-00920-00 Rev. E SECTION 1 INTRODUCTION This manual provides maintenance information for the Cirrus Perspective™ System by Garmin configured in Cirrus SR20, SR22, and SR22 Turbo Normalized aircraft. Troubleshooting, LRU replacement, uploading/ configuring software, and return to service testing procedures are included. NOTE This manual presumes familiarity with the basic operating procedures covered in the Garmin Perspective™ Pilot's Guide (P/N 190‐00820‐00) and Cockpit Reference Guide (P/N 190‐00821‐00). 1.1 MANUAL ORGANIZATION Section 1 Introduction Section 2 LRU Descriptions Section 3 System Overview Section 4 Configuration Mode Section 5 Troubleshooting Section 6 Replacement Procedures Section 7 LRU Software Installation and Testing Section 8 Return To Service Testing Section 9 Periodic Maintenance Section 10 System Reconfiguration Appendix Connector Pin Assignments Section one describes manual organization. Sections two and three describe the LRUs and give an overview of the system. Section four explains the configuration mode and the role it plays in troubleshooting along with limited user interface information. Section five describes troubleshooting procedures that help isolate a defective LRU. Section six lists procedures helping the technician replace a defective LRU. ____________________________________________________________________ Page 1-2 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 Section seven gives details on how to install, configure, and test software for a replacement LRU. Sections eight and nine present return to service tests and periodic maintenance procedures. Section 10 describes how to completely reconfigure the system should it become necessary. The appendix illustrates and lists the names of system connector pins. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 2-1 190-00920-00 Rev. E SECTION 2 LRU DESCRIPTIONS This section describes the standard and optional Garmin Line Replaceable Units (LRUs) that can be configured in a Perspective™ System for Cirrus SR20, SR22, and SR22 Turbo Normalized aircraft. Table 2‐1. SR20/SR22/SR22 Turbo Normalized LRU Configurations LRU/FUNCTION O/S GDU 1240A MFD/PFD (12” Screen) • GDU 1040A MFD/PFD (10” Display) • GDC 74A #1 (Air Data Computer) • GDC 74A #2 (Air Data Computer) OPT GRS 77 #1 (AHRS) • GRS 77 #2 (AHRS) OPT GIA 63W #1 (GPS/Com/Nav) • GIA 63W #2 (GPS/Com/Nav) • GMA 347 (Audio Panel) • GCU 478 (Keypad) • GTX 32 (Mode A/C Transponder) • GTX 33 ES (no TIS‐A) (Mode S Transponder) OPT GEA 71 (I/O Unit) • GDL 69 (XM Weather) OPT GDL 69A (XM Weather and Audio) OPT GRC 10/GRT 10 (XM Audio Remote) OPT GFC 700 (without YD) AFCS OPT GFC 700 (with YD) AFCS OPT GMC 705 (AFCS Controller) OPT GSA 80/81 Servo Actuators OPT GTA 82 Pitch Trim Adapter OPT Terrain • TAWS‐B OPT ChartView (Jepp Charts) OPT FliteCharts® (NACO Charts) • SafeTaxi® (Garmin Data) • Flight Director • Terrain‐SVS • • Standard Equipment; OPT=Optional ____________________________________________________________________ Page 2-2 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 2.1 GDU 1240A‐30/1040A‐30 (1) Figure 2‐1. GDU 1240A‐30/1040A‐30 Display This unit features a 12 or 10.4‐inch LCD with 1024 x 768 resolution. The unit installed on the left/pilot side is designated as the PFD. This PFD communicates with the GDU 1240A‐20/1040A‐ 20 (MFD), and with the on‐side GIA 63W Integrated Avionics Unit through a High‐Speed Data Bus (HSDB) connection. 2.2 GDU 1240A‐20/1040A‐20 (1) Figure 2‐2. GDU 1240A‐20/1040A‐20 Display This unit features a 12 or 10.4‐inch LCD with 1024 x 768 resolution. The unit installed on the right/copilot side is designated as the MFD. This MFD communicates with the GDU 1240A‐ 30/1040A‐30 (PFD), and with the on‐side GIA 63W Integrated Avionics Unit through a High‐ Speed Data Bus (HSDB) connection. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 2-3 190-00920-00 Rev. E 2.3 GMA 347 AUDIO PANEL Figure 2‐3. GMA 347 Audio Panel The Garmin GMA 347 is a horizontally oriented panel‐mounted audio control panel and marker beacon system. The GMA 347 is FAA TSO Authorized to C50c, and C35d Class A. Warning and alert audio provided by the GMA 347 is received from the GIA 63W Integrated Avionics Units (IAUs). The GMA 347 communicates with both GIA 63W LRUs using RS‐232. Software and configuration settings are received through a RS‐232 digital interface with the GIA 63W. 2.4 GIA 63W INTEGRATED AVIONICS UNIT (IAU) (WAAS Enabled) Figure 2‐4. GIA 63W Integrated Avionics Unit The GIA 63W is the central ‘Integrated Avionics Unit’ (IAU) in the Perspective™ system, linking all LRUs to the PFD and MFD. The GIA 63W contains the following hardware: • MAIN1 – contains all processor circuitry, digital I/O, 3.3V power supply, and the COM power supply. The COM and WAAS Module plug directly onto the MAIN1 board. • COM – 16W communications transceiver. • GPS ‐ WAAS Module. • MAIN2 – contains all analog and unique I/O, a power supply for the synchro outputs, and the MAIN1 power supply with capacitor backup. The NAV receiver plugs directly onto the MAIN2 board. • NAV receiver – VOR/LOC (VLOC) and Glideslope receivers. ____________________________________________________________________ Page 2-4 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 The GIA 63W communicates directly with the displays through an HSDB Ethernet connection. Software and configuration settings are sent from the displays through the GIA 63W to other LRUs in the system. 2.5 GDC 74A AIR DATA COMPUTER Figure 2‐5. GDC 74A Air Data Computer The GDC 74A provides pressure altitude, airspeed, vertical speed, and OAT information to the system using data received from the pitot/static system and the OAT probe. The GDC 74A communicates with the GIA 63Ws, GDU 1240As and GRS 77s using an ARINC 429 digital interface. 2.6 GEA 71 ENGINE/AIRFRAME UNIT Figure 2‐6. GEA 71 Engine/Airframe Unit The unit is a microprocessor based input/output system used to monitor sensor inputs and drive annunciator outputs for aircraft airframes and engine systems. Sensors include engine temperature and pressure and fuel measurement and pressure. The GEA communicates directly with both GIA 63Ws using RS‐485 digital interface. Software and configuration settings for operation are received through RS‐232 digital interface with the GIA. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 2-5 190-00920-00 Rev. E 2.7 GTX 32/33 TRANSPONDERS Figure 2‐7. GTX 32 Transponder Figure 2‐8. GTX 33 Transponder 2.7.1 GTX 32 Transponder The GTX 32 ATCRBS Transponder provides Mode A and C capabilities for ATC and TCAS I surveillance requirements. The GTX 32 interfaces with the No. 1 and No. 2 GIA 63W LRUs via RS‐232. 2.7.2 GTX 33 Transponder The GTX 33 Mode S Transponder provides Mode A, C, and S capabilities for ATC and TCAS I surveillance requirements. The GTX 33 interfaces with the No. 1 and No. 2 GIA 63W LRUs via RS‐232. ____________________________________________________________________ Page 2-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 2.8 GRS 77 ATTITUDE, HEADING, AND REFERENCE UNIT (AHRS) Figure 2‐9. GRS 77 AHRS Unit The Garmin GRS 77 is an attitude and heading reference systems (AHRS) that provides aircraft attitude (roll, pitch, and heading), angular rate, and acceleration information to the GIAs, and GDU 1240A LRUs. 2.9 GMU 44 MAGNETOMETER Figure 2‐10. GMU 44 Magnetometer The GMU 44 is a three‐axis magnetometer providing the following: • Measurement of three axes of magnetic field strength. • Measurement of two axes of tilt. • Measurement of GMU44 internal temperature. • Output of the above information in digital form to the GRS 77 through RS‐485. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 2-7 190-00920-00 Rev. E 2.10 GDL69/69A SATELLITE DATA LINK RECEIVER Figure 2‐11. GDL 69A Satellite Data Link Receiver The GDL 69A is a satellite data link receiver providing weather information in real‐time and digital audio entertainment. The weather information is displayed on the MFD and PFD inset map. The GDL 69A communicates with the MFD through an HSDB connection. A subscription to the XM satellite radio service is required before the GDL 69A can be enabled. 2.11 GSA 80/81 AFCS SERVO ACTUATOR/GSM 85A SERVO GEARBOX Figure 2‐12. GSA 80/81 Servo Actuator 2.11.1 GSA 81 Servo Actuator The GSA 81 Servo Actuator is an electromechanical component that provides automatic control of the aircraft pitch and roll control surfaces. 2.11.2 GSA 80 Servo Actuator The GSA 80 Servo Actuator is an electromechanical component that provides automatic control of the aircraft yaw control surfaces. ____________________________________________________________________ Page 2-8 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 2.11.3 GSM 85A Servo Gear Box The GSM 85A Servo Gear Box is used with a Garmin GSA 80 or GSA 81 (GSA 8X) servo actuator to control one axis of flight control, or its associated trim, as part of the GFC 700 flight control system. It connects directly into the flight control system via cables, chains, push rods, or other means and transmits the power from the motor in the servo actuator to the flight controls, when engaged. The GSM 85A is a mechanical appliance with no software of electronic hardware. 2.12 GTP 59 OAT PROBE Figure 2‐13. GTP 59 OAT Probe The GTP 59 OAT Probe provides outside air temperature measurements which are used by the GDC 74A. The GTP 59 communicates to the system through the GDC 74A/B. 2.13 GCU 478 REMOTE CONTROLLER Figure 2‐14. GCU 478 Control Unit The GCU 478 provides certain redundant control features and is the control for HDG, CRS, and ALT SEL. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 2-9 190-00920-00 Rev. E 2.14 GMC 705 AFCS Control Unit Figure 2‐15. GMC 705 AFCS Control Unit The GMC 705 is a panel‐mounted user interface that enables the aircraft’s flight crew to control the GFC 700 Automatic Flight Control System (AFCS). The GMC 705 has nine mode‐select keys and a thumbwheel encoder. The GMC 705 sends (over an RS‐232 serial data bus) the switch status information to be used elsewhere in the Perspective™ System. The CDU (Control Display Unit) defines the functionality of the user inputs, the GMC only reports which buttons are pressed or encoder turns. 2.15 GTA 82 TRIM ADAPTER Figure 2‐16. GTA 82 Trim Adapter The Garmin GTA 82 Trim Adapter is a remote mounted device that is used to allow the GFC 700 to drive a trim actuator provided by the airframe manufacturer. In such cases, the trim adapter provides the required interface. ____________________________________________________________________ Page 2-10 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 2.16 MISCELLANEOUS LRUs Figure 2‐17. GRT 10 Remote Controller and GRC 10 Wireless Transceiver 2.16.1 GRC 10 XM Remote Control The GRC 10 allows a passenger to interface with the GDL XM radio without inputs from the pilot or co‐pilot. 2.16.2 GRT 10 XM Wireless Transceiver The GRT 10 allows the user to remotely interface with the GDL XM radio. ____________________________________________________________________ SECTION 3 SYSTEM OVERVIEW This section describes the basic characteristics of the Perspective™ System. Figures 3‐1 through 3‐3 illustrate system interconnect block diagrams showing single and dual AHRS and ADC configurations. Figure 3‐1. Dual AHRS, Single ADC Configuration Cirrus Perspective™ Line Maintenance Manual Page 3-1 190-00920-00 Rev. E ____________________________________________________________________ Page 3-2 Cirrus Perspective™ Line Maintenance Manual Figure 3‐2. Dual AHRS, Dual ADC Configuration Rev. E 190-00920-00 ____________________________________________________________________ Figure 3‐3. GFC 700 System Interface Cirrus Perspective™ Line Maintenance Manual Page 3-3 190-00920-00 Rev. E ____________________________________________________________________ Page 3-4 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 3.1 FLIGHT INSTRUMENTATION The GRS 77 AHRS, GDC 74A Air Data Computer, and GMU 44 Magnetometer provide the system with flight instrumentation data. The data consists of aircraft attitude, heading, altitude, airspeed, vertical speed, and outside air temperature information, all displayed on the PFD (the same data is displayed on the MFD in reversionary mode). Data outputs from the GRS 77 and GDC 74A are sent directly to the PFD using ARINC 429. Additional communications paths connect the GRS and GDC 74A to GIA 63W units providing quadruple redundancy. The GRS 77 receives GPS data from both GIAs, airspeed data from the GDC 74A, and magnetic heading from the GMU. Using these three external sources, combined with internal sensor data, the GRS accurately calculates aircraft attitude and heading (Figure 2‐1). In addition to using internal sensors, the GRS 77 uses GPS information, magnetic field data, and air data to assist in attitude/heading calculations. In normal mode, the GRS 77 relies upon GPS and magnetic field measurements. If either of these external measurements is unavailable or invalid, the GRS 77 uses air data information for attitude determination. Four GRS 77 modes of operation are available and depend upon the combination of available sensor inputs. Loss of air data, GPS, or magnetometer sensor inputs is communicated to the pilot by message advisory alerts. 3.2 GFC 700 AUTOPILOT The GFC 700 is a fail‐passive digital flight control system composed of multiple Garmin LRUs and servos. The following functions are provided by the GFC 700 in a Perspective™ installation: • Flight Director • Autopilot • Pitch Trim • Yaw Damper (optional) 3.2.1 Flight Director The Flight Directors operate within the GIA 63Ws and use data from the GARMIN system, including air, attitude, and flight data, to calculate commands for display to the pilot and for the Autopilot. Flight director command bars and mode annunciations are sent to the PFDs through a high‐speed Ethernet connection for display to the pilot and copilot. The flight director operates independently of the autopilot and allows the pilot to hand‐fly the command bars if desired. 3.2.2 Autopilot The autopilot operates within two GSA 81 servos (pitch and roll). Flight director data is processed within the servos and turned into aircraft flight control surface commands. The autopilot cannot operate unless the flight director is engaged. ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 3-5 190-00920-00 Rev. E 3.2.3 Manual Electric Pitch Trim When the autopilot is not engaged the pitch trim motor may be used to provide a Manual Electric Pitch Trim (MEPT) function. This allows the pilot or co‐pilot to adjust pitch trim from the PITCH TRIM switch on the control stick. The MEPT trim command is routed through the GIA 63Ws where the trim speeds are scheduled to provide easier control over a wide speed or configuration range. In manual mode, the MEPT is routed through the GTA 82. Activation of the MEPT (or Manual Electric Roll Trim) does not disengage the Autopilot. 3.2.4 Yaw Damper The yaw damper reduces Dutch roll tendencies and coordinates turns. It can operate independently of the autopilot and may be used during normal hand‐flight maneuvers. A GSA 80 servo provides the control surface interface and the mode selection occurs via the GMC 705 controller. 3.3 S‐TEC 55X/55SR AUTOPILOT The Perspective™ System can interface with the S‐TEC 55X/55SR Autopilot to provide the following information to the System 55X/55SR for normal operation of the autopilot: • Cross‐track deviation • Navigation flag • Localizer Tuned state • Heading error • Course error • Glideslope deviation • Glideslope flag • Pre‐selected altitude • Baro‐corrected altitude • GPS Steering The interface will allow the Perspective™ System to obtain and respond to, as needed, the following information from the S‐TEC 55X/55SR: 1. Annunciations: All annunciations that would normally be made available to the S‐TEC Remote Annunciator. 2. Altitude Information Requests: All requests for pre‐selected altitude and baro‐ corrected altitude that would normally be provided to the S‐TEC SA‐200 Altitude Selector Alerter. In the case of the GFC 700, both of the GIAs communicate to the servos through RS‐485. In the case of the S‐TEC autopilot, the #2 GIA outputs analog HSI signals to the S‐TEC 55X/55SR, along with ARINC 429 roll steering, altitude data, and digital selected altitude data. ____________________________________________________________________ Page 3-6 Cirrus Perspective™ Line Maintenance Manual Figure 3‐4. S‐TEC Interface 3.4 NAVIGATION AND COMMUNICATION SYSTEM The GIAs contain VHF COM, VHF NAV, and GPS receivers. COM and NAV audio is sent via digital audio to the GMA 347 Audio Panel. GPS information is sent to the GRS 77 AHRS and both displays for processing. The GTX 32/33 Mode S Transponder communicates with both GIAs. Transponder data is sent from the GIAs to the PFD. Rev. E 190-00920-00 ____________________________________________________________________ Cirrus Perspective™ Line Maintenance Manual Page 4-1 190-00920-00 Rev. E SECTION 4 CONFIGURATION MODE This section provides an overview of the configuration mode of operation. This section presumes basic familiarity with the basic operation of the Cirrus Perspective™ system. 4.1 SYSTEM OPERATION Control and operation of the Perspective™ System and the GFC 700 occurs through the PFD, MFD, GCU 478, GMA 347, and GMC 705. See the following documents for detailed information regarding system control and operation. • Garmin/GFC 700 Cirrus SR20/SR22/SR22T Airplane Flight Manual Supplement • Garmin Cirrus SR20/SR22/SR22T Cockpit Reference Guide (Garmin P/N 190‐00821‐00) 4.2 CONFIGURATION MODE Configuring, calibrating, and troubleshooting tasks are performed when the system is in configuration mode. To enter the system into configuration mode: • Press and hold the ENT key on the PFD and the rightmost softkey on the MFD and apply power. Release the keys when the words ‘INITIALIZING SYSTEM’ are displayed in the upper left corner of each display. The System Status Page is displayed (Figure 4‐1). Figure 4‐1. System Status Page (Configuration Mode) ____________________________________________________________________ Page 4-2 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00 Once the system is placed in configuration mode, the large and small FMS knobs are used to cycle through the different configuration pages, to change page groups, and to change pages in a group. The FMS knob is also used to perform the following: • To activate the cursor, press the small FMS knob. • To cycle the cursor through different data fields, rotate the large FMS knob. • To change the contents of a highlighted data field, rotate the small FMS knob. This action displays an options menu for the particular field, or in some cases, allows the user to enter data for the field. • To confirm a selection, press the ENT key. To cancel a selection, press the small FMS knob. Pressing the small FMS knob again turns the cursor off. The CLR key can also be used to cancel a selection or turn the cursor off. 4.2.1 Softkeys Some configuration pages have commands or selections that are activated by display softkeys (Figure 4‐2). If a softkey is associated with a command, that command will be displayed directly above the key. A grayed‐out softkey shows a command that is unavailable. A softkey that is highlighted shows the current active selection. Figure 4‐2. System Softkeys 4.3 CONFIGURATION PAGE GROUPS AND PAGES NOTE Certain configuration pages critical to aircraft operation and safety are “protected”. The technician is unable to modify or change settings on these pages unless they are authorized and equipped to do so. They are viewable to aid in troubleshooting. Configuration pages are grouped according to function. The active page title is displayed at the top of the screen in the center. In the bottom right corner of the screen, the current configuration page group, number of pages available in the group, and placement of the current page within the group are indicated by icons. Table 4‐1 shows the order and organization of various page groups and pages shown in configuration mode. The table is an example only; configuration pages may change depending on the specific installation requirements.