Page 1 ® CIRRUS PERSPECTIVE LINE MAINTENANCE MANUAL (SR20/SR22/SR22TN) 190‐00920‐00 September 2009 Revision E ...
Page 3 Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one ...
Page 4 ____________________________________________________________ Blank Page Page ii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00...
Page 5 A 5/28/08 ‐‐‐‐‐‐ ‐‐‐‐‐‐ Initial Release B 6/25/08 ‐‐‐‐‐‐ ‐‐‐‐‐‐ Revised manual to more closely match specific production aircraft troubleshooting issues, and to match revised GDU software version 9.01. C 11/19/08 ‐‐‐‐‐‐ Cover Changed cover style to match other Garmin LMMs Global All Global change from “De‐Ice Protection Option” to “Ice Protection Installation Option” D 4/24/09 ‐‐‐‐‐‐ Cover Added SR20 to title. vi Changed GDU software version from ‐‐‐‐‐‐ 9.01 to 9.14. ...
Page 6 ____________________________________________________________ REVISION DATE SECTION PAGE DESCRIPTION 4‐1 Added SR20 to section 4.1. 4 4‐3 Added Maintenance Log page to 4 table 4‐1. Changed GDC page Group name to ADC. Added ADC Configuration page. Switched the positions of the GFC and GMA groups in Table 4‐1. Switched the position of the GDL and GFC groups in Table 4‐1. Added the OTHER configuration page (optional STEC®) in Table 4‐1. Added Remote Controller Status Configuration Group in Table 4‐1. Added Fuel Tank Calibration Page to CAL group in Table 4‐1. 4‐5 Updated figure 4‐4. 4 Global Changed all references of PFD1 to 5 PFD. Removed all references to PFD2. Changed all PFDs to PFD. ...
Page 7 ____________________________________________________________ REVISION DATE SECTION PAGE DESCRIPTION 7‐15 Added SR20 to first paragraph. 7 7‐16 Added SR20 to opening paragraph 7 of section 7.3.7. 7‐17 Updated figure 7‐5. Revised 7 procedure to match current GDU software. 7‐19 Removed statement regarding the 7 location of the startup screens, checklist files and ChartView database. 7‐32 Added SR20 to step one. 7 7‐35 Added SR20 to step one. ...
Page 8 ____________________________________________________________ REVISION DATE SECTION PAGE DESCRIPTION 10‐8 Revised entire section 10.4.4 10 through step T. Added important statement regarding loading splash screen. 10‐25 Added SR20 to step 2. 10 10‐27 Revised section 10.9. 10 E 9/21/09 ix GDU software version to 10.0. Front Content 1‐1 Page 1‐1: changed name of SR22T to 1 “SR22 Turbo Normalized.” 2‐1 Changed name of SR22T to “SR22 ...
Page 9 ____________________________________________________________ REVISION DATE SECTION PAGE DESCRIPTION 8‐4 Edited opening paragraph in section 8 8.5. 8‐8 Added new section 8.5.1, Port Status Tests and added new screen shots to support text. Global Changed name of SR22T to “SR22 10 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 ...
Page 10 ____________________________________________________________ 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 Page viii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00...
Page 11 ____________________________________________________________ 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. ...
Page 12 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 ...
Page 13: Table Of Contents
____________________________________________________________ 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 ...
Page 14 ____________________________________________________________ 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 ...
Page 15 ____________________________________________________________ 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 ...
Page 16 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 Page xiv Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00...
Page 17 ____________________________________________________________ 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 ...
Page 18 ____________________________________________________________ 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 ...
Page 19 ____________________________________________________________ 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 ...
Page 20 ____________________________________________________________ Blank Page Page xviii Cirrus Perspective™ System Maintenance Manual Rev. E 190-00920-00...
Page 21: Manual Organization
____________________________________________________________________ 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). 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 ...
Page 22 ____________________________________________________________________ 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. ...
Page 23: Section 2-Lru Descriptions
____________________________________________________________________ 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) ...
Page 24: Gdu 1240A-30/1040A-30 (1)
____________________________________________________________________ 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. Page 2-2 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 25: Gma 347 Audio Panel
____________________________________________________________________ 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. Cirrus Perspective™ Line Maintenance Manual Page 2-3 190-00920-00...
Page 26: Gdc 74A Air Data Computer
____________________________________________________________________ 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. Page 2-4 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 27: Gtx 32/33 Transponders
____________________________________________________________________ 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. Cirrus Perspective™ Line Maintenance Manual Page 2-5 190-00920-00 Rev. E...
Page 28: Grs 77 Attitude, Heading, And Reference Unit (Ahrs)
____________________________________________________________________ 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. Page 2-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 29: Gdl69/69A Satellite Data Link Receiver
____________________________________________________________________ 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. Cirrus Perspective™ Line Maintenance Manual Page 2-7 190-00920-00 Rev. E...
Page 30: Gsm 85A Servo Gear Box
____________________________________________________________________ 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. Page 2-8 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 31: Gmc 705 Afcs Control Unit
____________________________________________________________________ 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. Cirrus Perspective™ Line Maintenance Manual Page 2-9 190-00920-00 Rev. E...
Page 32: Miscellaneous Lrus
____________________________________________________________________ 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. Page 2-10 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 33: Section 3-System Overview
____________________________________________________________________ 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 34 ____________________________________________________________________ Figure 3‐2. Dual AHRS, Dual ADC Configuration Page 3-2 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 35 ____________________________________________________________________ Figure 3‐3. GFC 700 System Interface Cirrus Perspective™ Line Maintenance Manual Page 3-3 190-00920-00 Rev. E...
Page 36: 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 ...
Page 37: Manual Electric Pitch Trim
____________________________________________________________________ 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 ...
Page 38: Navigation And Communication System
____________________________________________________________________ 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. Page 3-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 39: Section 4-Configuration Mode
____________________________________________________________________ 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) Cirrus Perspective™ Line Maintenance Manual Page 4-1 190-00920-00 Rev. E...
Page 40: Softkeys
____________________________________________________________________ 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”. ...
Page 41 ____________________________________________________________________ Table 4‐1. Configuration Page Groups and Pages SYSTEM System Status RS-232/ARINC 429 Config RS-232/ARINC 429 Config Date/Time Setup GDU Status RS-485 Configuration Main Lighting GDU Test GIA I/O Configuration Audio Alert Configuration Diagnostics COM Setup System Upload Serial / Ethernet I/O GIA Status File Manager Video CAN Configuration Diagnostics Terminal...
Page 42: Secure Digital (Sd) Cards
____________________________________________________________________ 4.4 SECURE DIGITAL (SD) CARDS Software files are uploaded into the system using a secure digital (SD) data card. The card contains all necessary files to load software and configuration settings to all LRUs. Basically, all software and configuration parameters are pre‐determined by Garmin and/or Cirrus. During removal and replacement of LRUs, software and configuration files may need to be reloaded (refer to Section 7). It is important to use the correct card part number because each card part number defines all files found on the card for a specific installation except for certain configuration settings such as the aircraft registration number (N#) which must be entered manually. Be careful when using the card during maintenance. The system is designed to immediately initialize the card upon power‐up. Pay attention to all on‐screen prompts to avoid possible loss of data. The GDU data card slots accept secure digital (SD) cards and are located on the top right portion of the display bezels (Figure 4‐3). Each display bezel has two card slots, top and bottom. The top slot is for SD cards containing aviation database and system software updates and supplemental database storage files. NOTE The SD card label should be on the left side when inserted into the display. Do not force the card if there is resistance. Remove and reinsert gently. To install an SD card: Turn the system off. Insert the SD card in the SD card slot, pushing the card in until the spring latch engages. The front of the card should remain flush with the face of the display bezel. To remove an SD card: Gently press on the SD card to release the spring latch and eject the card. Figure 4‐3. GDU Bezel SD Card Slots Page 4-4 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 43: Set' And 'Active' Commands
____________________________________________________________________ 4.5 'SET' AND 'ACTIVE' COMMANDS The SET and ACTIVE commands which are displayed on various configuration pages (Figure 4‐4) are used for setting system input/output conditions. Figure 4‐4. SET and ACTIVE Softkeys and Columns 4.5.1 SET and ACTIVE Softkeys Look for inequalities (configuration mismatches) between the SET and ACTIVE columns during troubleshooting. Certain problems can be resolved by pressing the SET>ACTV softkey which reloads settings to the specific LRU (this can also be accomplished by reloading the configuration files for the LRU using the system software loader card). Use the ACTV>SET softkey with care. If an improperly configured unit is installed, this softkey causes the wrong configuration to replace the correct one. Definitions: SET—refers to a setting or group of settings that reside in the PFDs internal memory and/or master configuration module. ACTIVE—refers to a current setting stored and used in a LRU. LRUs store the ‘active’ settings within internal memory. Cirrus Perspective™ Line Maintenance Manual Page 4-5 190-00920-00 Rev. E...
Page 44: Configuration Status
____________________________________________________________________ Data can be manually copied from one column to the other by using the following two softkeys: SET>ACTV (Set to Active)— sends the information in the SET column (data stored in the master configuration module) to the ACTV column (data used by the LRU). ACTV>SET (Active to Set)—copies the current settings of the LRU to the master configuration module as SET items. 4.6 CONFIGURATION STATUS When configuration settings are changed, the following configuration and/confirmation prompts are displayed. Figure 4‐5. Configuration/Confirmation Prompts 4.7 DATA TRANSMISSION INDICATORS Several configuration pages use an indicator light system to show discrete (ON/OFF) data and/or hardware component status. Unless otherwise noted, the following applies to all configuration page status indicators: • Green―expected data is successfully received and is ON. A green light can also indicate that the parameter/component is working correctly. • Red―expected data is not received. A red light can also indicate that a parameter/component is invalid. • Black―expected data is successfully received and is OFF, or no data is expected. A black light can also indicate that the parameter/component is not responding. Figure 4‐6. Data Transmission Indicators A blank ACTIVE column displays the loss of communication between the display and a specific LRU (Figure 4‐7). Page 4-6 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 45 ____________________________________________________________________ Figure 4‐7. Loss of Communication Indication Cirrus Perspective™ Line Maintenance Manual Page 4-7 190-00920-00 Rev.
Page 46 ____________________________________________________________________ Blank Page Page 4-8 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 47: Section 5-Troubleshooting
____________________________________________________________________ SECTION 5 TROUBLESHOOTING This section provides troubleshooting guidance for failed LRU's. 5.1 CIRRUS PERSPECTIVE™ ALERTING SYSTEM 5.1.1 Display Fields A red X through a display field (such as COM frequencies, NAV frequencies, or engine data) indicates a display field which is not receiving valid data (see Figure 5‐1). Figure 5‐1. Invalid Display Fields Cirrus Perspective™ Line Maintenance Manual Page 5-1 190-00920-00 Rev. E...
Page 48: System Annunciation Troubleshooting
____________________________________________________________________ 5.1.2 System Annunciation Troubleshooting Annunciation Associated Solution LRU • Check PFD Alert Window for GIA1 configuration, software or failed data path error messages. Correct any errors before proceeding. NAV1 or COM1 • Swap GIA1 and GIA2 and reconfigure. GIA1 − If problem follows GIA1, replace GIA1. • Check Ethernet interconnect from GIA1 to PFD and unit connector pins for faults. • If problem persists, replace PFD. • Check PFD Alert Window for GIA2 configuration, software or failed data path error messages. Correct any errors before proceeding. NAV2 or COM2 • Swap GIA1 and GIA2 and reconfigure. GIA2 − If problem follows GIA2, replace GIA2. • Check Ethernet interconnect from GIA2 to MFD and unit connector pins for faults. •...
Page 49 ____________________________________________________________________ System Annunciation Troubleshooting (continued) Annunciation Associated Solution LRU • Check PFD Alert Window for GIA1/2 configuration, software or failed data path error messages. Correct any errors before proceeding. • Make sure the aircraft is located where the GPS antennas have a clear view of the sky. • Check for possible external interference to the GPS receivers. 1. Make sure a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. 2. Turn to the MFD AUX – GPS STATUS page and GPS INTEG or Time check the GPS strength bars on both GPS receivers. If the signal strength levels are erratic, disappear and reappear rapidly, or switch between a solid and hollow bar, there GIA1 or 2 could be an external device interfering with the GPS receivers. Turn off any devices that radiate a signal in the area or move the aircraft to another location to remove the interference. 3. Make sure the aircraft is not parked in close proximity to a hanger with the doors open and equipped with a GPS repeater. •...
Page 50 ____________________________________________________________________ Annunciation Associated Solution LRU • Check PFD Alert Window for GIA1/2 and GTX 32/33 configuration, software or failed data path error messages. Correct any errors before proceeding. • Perform a SET>ACTV configuration reset on the GTX Transponder Configuration page for each installed GTX. GTX 32 or XPDR FAIL Optional GTX • For GTX 33 transponders, make sure the aircraft 33 registration is entered in the GTX Transponder Configuration page. • Check the GIA and GTX racks for connector pin faults (pushed back or bent) on the RS‐232 interconnect lines. • Replace the GTX 32/33. • AIRSPEED FAIL, Check PFD Alert Window for PFD, MFD or GDC ALTITUDE FAIL, configuration, software or failed data path error VERT SPEED FAIL messages. Correct any errors before proceeding. • Make sure the GDC’s are online by checking for a green checkmark next to the GDC on the MFD Aux – System Status page. 1.
Page 51 • Cycle GRS 77 power to restart initialization. • Check the GRS 77 connecter for security and that proper wire harness strain relief is provided. • Check to see if the GRS 77 is fastened down tightly in its mounting rack and that the mounting rack is not loose (CAUTION ‐ do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re‐leveled and the PITCH/ROLL OFFSET procedure performed). • Perform an Engine Run‐Up Test to check if engine vibration is causing the GRS 77 to go offline. • Replace the GRS 77. • If problem persists, replace the GRS 77 configuration module. • Contact Garmin Aviation Product Support if condition continues after replacing the GRS 77 and/or config module. Cirrus Perspective™ Line Maintenance Manual Page 5-5 190-00920-00 Rev. E...
Page 52 ____________________________________________________________________ System Annunciation Troubleshooting (continued) Annunciation Associated Solution LRU • Check PFD Alert Window for PFD, MFD or GRS configuration, software or failed data path error messages. Correct any errors before proceeding. • Check for metal objects (tool boxes, power carts, nearby large steel structures, etc.) around the aircraft that could be interfering with the magnetometer. • Make sure a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Cycle power after moving aircraft away from metal objects to determine if metal objects were the source of the interference. Allow up to five minutes for the heading to reinitialize. • Is the aircraft stationary if GPS is not available? GRS 77 #1& Aircraft movement (rocking the wings or moving GMU 44 #1 HDG FAIL the tail) may cause the attitude and heading to fail or Optional if it believes the aircraft is in motion without GPS GRS77 #2 & input. GMU #2 • Perform a Magnetometer Interference Test to check for interference from onboard electrical system components (e.g. NAV lights). Pay attention ...
Page 53 ____________________________________________________________________ System Annunciation Troubleshooting (continued) Annunciation Associated Solution LRU Engine/Airframe Sensors • Check PFD Alert Window for GIA1/2 or GEA configuration, software or failed data path error messages. Correct any errors before proceeding. • On the PFD in Configuration Mode, turn to the GEA STATUS page and make sure the GEA internal power supply, configuration, and calibration status boxes are green. − If the internal power supply box is red, check for shorted engine/airframe sensors that receive 5V, 10V, or 12V power from the GEA (tach sensor, MAP sensor, Fuel Flow sensor, oil pressure sensor and pitot heat sensor). − The configuration and calibration boxes should GEA 71 & be green. If the calibration status boxes are GIA 63W red, replace the GEA 71. • Make sure the internal, external, and reference voltages listed in the Main Analog and I/O Analog boxes are not dashed out (this does not include Aircraft Power 1 and 2). If any voltages are dashed out, replace the GEA. • Check the MFD AUX – SYSTEM STATUS page if the GEA is online (green checkmark on the AUX – SYSTEM STATUS page is present). If GEA is not online, (red‐X is present), make sure the unit is receiving power at the GEA rack connector. •...
Page 54: Messages & Annunciations
____________________________________________________________________ 5.2 Messages & Annunciations NOTE See Appendix A in the Perspective™ System Pilot’s Guide for a list of all messages and annunciations not covered in this Line Maintenance Manual. Figure 5‐2. Messages & Annunciations In normal mode, the system displays a variety of system messages and/or annunciations. System messages are normally presented on the PFD and can be viewed by pressing the bezel key located below the flashing annunciation. This section provides a listing of possible messages, alerts, and annunciations. Aircraft specific alerts are not covered in this manual. Page 5-8 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 55: System Status Page (Mfd-Normal Mode)
____________________________________________________________________ 5.3 System Status Page (MFD―Normal Mode) Figure 5‐3. System Status Page (AUX Group) The AUX – SYSTEM STATUS page on the MFD displays LRU health status when the system is in normal mode. Failed Path Messages A ‘FAILED PATH’ message indicates that a data path connected to the GDU (PFD or MFD) or the GIA 63W (1 or 2) has failed. This ‘FAILED PATH’ message is triggered by a timeout of any digital channel. The channels that are checked are displayed on the following pages in configuration mode: 1. GDU RS‐232 / ARINC 429 CONFIG (PFD and MFD) 2. GIA RS‐232 / ARINC 429 CONFIG (GIA1 and GIA2) 3. GIA CAN / RS‐485 CONFIGURATION (GIA1 and GIA2) Once the FAILED PATH message has been triggered, it remains on the list of messages until the next power cycle. This latching was implemented so that the message would remain through the end of the flight during intermittent failures (to alert the maintenance crew). This also keeps the crew from having to repeatedly acknowledge messages in the case of intermittent failures. Cirrus Perspective™ Line Maintenance Manual Page 5-9 190-00920-00 Rev. E...
Page 56 ____________________________________________________________________ The box color next to each channel indicates the current status of the channel: • Red = data path is known to be failed. • Black = data path status is unknown. • Green = data path is known to be good. The applicable data paths can be verified by viewing the configuration mode pages listed below. 5.4 Data Path Indications on the Main and GIA Configuration Pages NOTE Pre GDU 9.11 software uses solid green, black, and red indicator boxes on the configuration pages. Post GDU 9.11 software uses green check, red x, black N/A, and yellow ? indicator boxes on the configuration pages. Although the manual uses pre GDU 9.11 boxes in the troubleshooting tables, the technician should be ...
Page 57: System Data Paths
____________________________________________________________________ In addition to failure messages, the data path can be checked by observing the indication boxes on the GDU and GIA Configuration Pages. The status of the channel is indicated by the following colors: (Pre GDU 9.11 Software): Red = data path has failed • Black = data path status is unknown • Green = data path is good • (Post GDU 9.11 Software): Red X = data path has failed • Green check mark = data path is good • N/A = data path status is not applicable • ? = data path is unknown • 5.4.1 System Data Paths In addition to troubleshooting via the GDU and GIA Configuration Pages, the System Data Path Configuration Page displays port status and information. The System Data Paths Configuration page (Figures 5‐4 through 5‐7) displays the following data when the A429, CAN, RS‐232, or RS‐ 485 data path softkey is selected: A table containing one row for each configured LRU with the following information per row, ordered from left to right: • A text field indicating the LRU name in the column • A text field indicating the channel name • A status indicator showing: o An N/A indication if the monitor is on and data path status is not applicable o A positive indication if the monitor is on and data path status is "OK" o A negative indication if the monitor is on and data path status is "FAIL" o An unknown indication if the monitor is off or the monitor is "ON" and data path ...
Page 58 ____________________________________________________________________ • A text field indicating the following port status: o "OK" if the port is communicating o "FAIL" if the port is not communicating o "N/A" if the port is not applicable o "UNKNOWN" if the port status is unknown Figure 5‐4. A429 Data Path Page Page 5-12 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 59 ____________________________________________________________________ Figure 5‐5. CAN Data Path Page Figure 5‐6. RS‐232 Data Path Page Cirrus Perspective™ Line Maintenance Manual Page 5-13 190-00920-00 Rev. E...
Page 60 ____________________________________________________________________ Figure 5‐7. RS‐485 Data Path Page Page 5-14 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 61 ____________________________________________________________________ The System Data Paths Configuration page displays the following data when the HSDB data path softkey is selected: • A table containing one row for each configured LRU with the following data per row, ordered from left to right: o A text field indicating the LRU name in the column o A drop down selectable field indicating the expected LRU for each HSDB port o A white text field indicating the current LRU for each HSDB port o A status indicator for each HSDB port: An N/A indicator if the expected LRU is configured to none and there is no actual LRU online. A positive indicator if the expected LRU matches actual LRU online A negative indicator if the expected LRU does not match actual LRU online Figure 5‐8. HSDB Data Path Page Cirrus Perspective™ Line Maintenance Manual Page 5-15 190-00920-00 Rev. E...
Page 62: Troubleshooting Tables
____________________________________________________________________ 5.5 Troubleshooting Tables GDU RS‐232/ARINC 429 Configuration Page (PFD1/2 and MFD) Figure 5‐9. Main RS‐232/ARINC 429 Configuration Page The Main RS‐232/ARINC 429 Configuration Page (Figure 5‐9) troubleshooting tables show channel, LRU, status indication, and troubleshooting helps. Channel assignments with their associated LRUs differ depending on the specific aircraft configuration. The tables are only examples. Page 5-16 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 63 ____________________________________________________________________ GDU RS‐232 / ARINC 429 CONFIG Page PFD RS‐232 Channel LRU Indicator Status PFD/GCU 478 data path is functioning correctly. PFD/GCU 478 data path is not functioning correctly. • Check PFD Alert Window for PFD or GCU configuration or software error messages. Correct any errors before proceeding. Make sure the GCU is powered on by pressing the “ANN TEST” softkey on the MFD AUX ‐ SYSTEM STATUS page to see if the key indicators turn on. • If GCU will not power on, remove unit and make sure power and ground are present at the GCU connector. CHNL 1 GCU 478 − If power or ground is not present, troubleshoot aircraft wiring for faults. If power and ground are present, check the PFD and GCU connector for damaged or pushed back pins. • Swap PFD and MFD to see if the problem is in the PFD. − Replace original PFD if box turns green after swapping displays. • Replace the GCU. PFD/GCU 478 data path functionality is unknown. Reload PFD configuration file. PFD/GMC 705 data path is functioning correctly. PFD/GMC 705 data path is not functioning correctly. ...
Page 64 ____________________________________________________________________ PFD ARINC 429 Channel LRU Indicator Status PFD/GRS 77 #1 data path is functioning correctly. PFD/GRS 77 #1 data path is not functioning correctly. • Check PFD Alert Window for PFD or GRS77 configuration or software error messages. Correct any errors before proceeding. Make sure the GRS77 #1 status is OK using the AUX – SYSTEM STATUS PAGE on the MFD. If there is a red‐x, troubleshoot why the GRS is offline before proceeding. Make sure the GRS77 #1 connecter is secure and proper wire harness strain relief is provided. • Swap GRS77#1 and GRS77 #2 (if a GRS77 #2 is installed) to see if the problem is in the original GRS77 IN 1 GRS 77 #1 #1. − Replace original GRS77 #1 if box turns green after swapping units. • Swap PFD and MFD to see if the problem is in the PFD. − Replace original PFD if box turns green after swapping displays. • Check the PFD/GRS 77 #1 interconnect wiring and unit connector pins for faults. • Replace GRS 77 #1. PFD/GRS 77 #1 data path functionality is unknown. Reload PFD configuration file. ...
Page 65 ____________________________________________________________________ MFD RS‐232 Channel LRU Indicator Status MFD/GCU 478 data path is functioning correctly. MFD/GCU 478 data path is not functioning correctly. • Check PFD Alert Window for MFD or GCU configuration or software error messages. Correct any errors before proceeding. • Make sure the GCU is powered on by pressing the “ANN TEST” softkey on the MFD AUX ‐ SYSTEM STATUS page to see if the key indicators turn on. • If GCU will not power on, remove unit and make sure power and ground are present at the GMC connector. − If power or ground is not present, troubleshoot CHNL 1 GCU 478 aircraft wiring for faults. − If power and ground are present, check the MFD and GCU connectors for damaged or pushback pins. • Swap PFD and MFD to see if the problem is in the original MFD. − Replace original MFD if box turns green after swapping displays. • Replace the GCU 478. MFD/GCU 478 data path functionality is unknown. Reload MFD configuration file. ...
Page 66 ____________________________________________________________________ MFD/GMC 705 data path is functioning correctly. MFD/GMC 705 data path is not functioning correctly. • Check PFD Alert Window for MFD or GMC configuration or software error messages. Correct any errors before proceeding. • Make sure the GMC is powered on by pressing the “ANN TEST” softkey on the MFD AUX ‐ SYSTEM STATUS page to see if the key indicators turn on. • If GMC will not come on, remove unit and make sure power and ground are present at the GMC connector. CHNL 2 GMC 705 − If power or ground is not present, troubleshoot aircraft wiring for faults. − If power and ground are present, check the MFD and GMC connector for damaged or pushback pins. • Swap PFD and MFD to see if the problem is in the PFD. − Replace original MFD if box turns green after swapping displays. • Replace the GMC. MFD/GMC 705 data path functionality is unknown. Reload MFD configuration file. Page 5-20 Cirrus Perspective™...
Page 67 ____________________________________________________________________ MFD ARINC 429 Channel LRU Indicator Status MFD/GRS 77 #2 data path is functioning correctly. MFD/GRS 77 #2 data path is not functioning correctly. • Check PFD Alert Window for MFD or GRS77 configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #2 status is OK using the AUX – SYSTEM STATUS PAGE on the MFD. If there is a red‐x, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #2 connecter is secure and proper wire harness strain relief is provided. GRS 77 #2 • Swap GRS77 #1 and GRS77 #2 to see if the problem is IN 1 (if in the original GRS77 #2. equipped) − Replace original GRS77 #2 if box turns green after swapping units. • Swap PFD and MFD to see if the problem is in the MFD. − Replace original MFD if box turns green after swapping displays. • Check the MFD/GRS 77 #2 interconnect wiring and unit connector pins for faults. •...
Page 68 ____________________________________________________________________ MFD/GDC 74A #2 data path is functioning correctly MFD/GDC 74A #2 data path is not functioning correctly. • Check PFD Alert Window for PFD or GDC74 configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74 #2 status is OK using the System Status Page on the MFD. If there is a red‐x, troubleshoot why the GDC is offline before GDC 74A #2 proceeding. IN 2 (if • Swap PFD and MFD to see if the problem is in the equipped) original MFD. − Replace original MFD if box turns green after swapping displays. • Check the MFD/GDC 74 #2 interconnect wiring and unit connector pins for faults. • Replace GDC 74 #2 if problem remains. MFD/GDC 74A #2 data path functionality is unknown. Reload MFD configuration file. Page 5-22 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 69 ____________________________________________________________________ GIA RS‐232 / ARINC 429 CONFIG Page GIA1 RS‐232 Channel LRU Indicator Status GIA1/GDC 74A #1 data path is functioning correctly. GIA1/GDC 74A #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74 #1 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a red‐x, troubleshoot why the GDC is offline before proceeding. CHNL 1 GDC 74A #1 • Swap GIA1 and GIA2, reconfigure both GIA’s at their new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. Check the GIA1/GDC 74#1 interconnect wiring and unit • connector pins for faults. • Replace GDC 74#1 if problem remains. GIA1/GDC 74A #1 data path functionality is unknown. Reload GIA1 configuration files. GRS 77 #2 GIA1/GRS 77 #2 output data path is not monitored. A CHNL 2 (output ...
Page 70 ____________________________________________________________________ GIA1/RDM data path is functioning correctly. GIA1/RDM data path is not functioning correctly. • Check PFD Alert Window for GIA or RDM configuration or software error messages. Correct any errors before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their Recoverable new locations to see if the problem is in the original Data CHNL 4 GIA1. Module − Replace original GIA1 if box turns green after (RDM) swapping units. • Check the GIA1/RDM interconnect wiring and connector pins for faults. Replace RDM if problem remains. GIA1/RDM output data path is not monitored. A black box is normal GIA1/GTX 32/33 #1 data path is functioning correctly. GIA1/GTX 32/33 #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GTX configuration or software error messages. Correct any errors before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GTX 32/33 CHNL 5 ...
Page 71 ____________________________________________________________________ GIA1 RS‐232 (continued) Channel LRU Indicator Status GIA1/GRS 77 #1 data path is functioning correctly. GIA1/GRS 77 #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #1 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #1 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2, reconfigure both GIA’s at their new locations to see if the problem is in the original CHNL 6 GRS 77 #1 GIA1. − Replace original GIA1 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 (if a GRS77 #2 is installed) to see if the problem is in the original GRS77 #1. − Replace original GRS77 #1 if box turns green after swapping units. • Check the GIA1/GRS 77 #1 interconnect wiring and unit connector pins for faults. •...
Page 72 ____________________________________________________________________ GIA1 RS‐232 (continued) Channel LRU Indicator Status GIA1/GMA 347 data path is functioning correctly. GIA1/GMA 347 data path is not functioning correctly. • Check PFD Alert Window for GIA or GMA configuration or software error messages. Correct any errors before proceeding. • Make sure the GMA 347 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. GMA • Swap GIA1 and GIA2. Reconfigure both GIA’s at their CHNL 7 347* new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/GMA 347 interconnect wiring and unit connector pins for faults. • Replace GMA 347. GIA1/GMA 347 data path functionality is unknown. Reload GIA1 configuration files. NOTE * ‐ The path is identified by the Cirrus Perspective™ System as GMA 1347#1 on the GIA RS‐232/RS‐485 CONFIG page. ...
Page 73 ____________________________________________________________________ GIA1 ARINC 429 Channel LRU Indicator Status GIA1/FIKI Stall Warning Computer data path is functioning correctly. GIA1/FIKI Stall Warning Computer data path is not functioning correctly. • Check PFD Alert Window for GIA or FIKI Stall Warning Computer configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #1 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐ FIKI X, troubleshoot why the GDC is offline before Optional proceeding. IN 1 Stall • Swap GIA1 and GIA2. Reconfigure both GIA’s at their Warning new locations to see if the problem is in the original Computer GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/FIKI Stall Warning Computer interconnect wiring and unit connector pins for faults. • Check FIKI Stall Warning Computer Operation. Replace GDC 74A #1. GIA1/FIKI Stall Warning Computer data path functionality ...
Page 74 ____________________________________________________________________ GIA1/GDC 74A #1 data path is functioning correctly. GIA1/GDC 74A #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #1 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐ X, troubleshoot why the GDC is offline before proceeding. IN 5 GDC 74A #1 • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/GDC 74A #1 interconnect wiring and unit connector pins for faults. • Replace GDC 74A #1. GIA1/GDC 74A #1 data path functionality is unknown. Reload GIA1 configuration files. Page 5-28 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 75 ____________________________________________________________________ GIA1 ARINC 429 (continued) Channel LRU Indicator Status GIA1/GRS 77 #1 data path is functioning correctly. GIA1/GRS 77 #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #1 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #1 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original IN 6 GRS 77 #1 GIA1. − Replace original GIA1 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 (if a GRS77 #2 is installed) to see if the problem is in the original GRS1. − Replace original GRS77 #1 if box turns green after swapping units. • Check the GIA1/GRS 77 #1 interconnect wiring and unit connector pins for faults. •...
Page 76 ____________________________________________________________________ GIA1 ARINC 429 (continued) Channel LRU Indicator Status GIA1/GDC 74A #2 data path is functioning correctly. GIA1/GDC 74A #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #2 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐ X, troubleshoot why the GDC is offline before GDC 74A #2 proceeding. IN 7 (if • Swap GIA1 and GIA2. Reconfigure both GIA’s at their equipped) new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/GDC 74A #2 interconnect wiring and unit connector pins for faults. • Replace GDC 74A #2. GIA1/GDC 74A #2 data path functionality is unknown. Reload GIA1 configuration files. Page 5-30 Cirrus Perspective™...
Page 77 ____________________________________________________________________ GIA1 ARINC 429 (continued) Channel LRU Indicator Status GIA1/GRS 77 #2 data path is functioning correctly. GIA1/GRS 77 #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #2 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #2 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their GRS 77 #2 new locations to see if the problem is in the original IN 8 (if GIA1. equipped) − Replace original GIA1 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 to see if the problem is in the original GRS77 #2. − Replace original GRS77 #2 if box turns green after swapping units. • Check the GIA1/GRS 77 #2 interconnect wiring and ...
Page 78 ____________________________________________________________________ GIA2 RS‐232 Channel LRU Indicator Status GIA2/GDC 74A #2 data path is functioning correctly. GIA2/GDC 74A #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #2 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐X, troubleshoot why the GDC CHNL 1 GDC 74A #2 is offline before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA2. − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/GDC 74A #2 interconnect wiring and unit connector pins for faults. • Replace GDC 74A #2. GIA2/GDC 74A #2 data path functionality is unknown. Reload GIA2 configuration files. GRS 77 #1 (output GIA2/GRS 77 #1 output data path is not ...
Page 79 ____________________________________________________________________ GIA2 RS‐232 (continued) Channel LRU Indicator Status GIA2/WX 500 data path is functioning correctly. GIA2/WX 500 data path is not functioning correctly. • Check PFD Alert Window for GIA configuration or software error messages. Correct any errors before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA2. CHNL 3 WX 500 − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/WX500 interconnect wiring and connector pins for faults. • Troubleshoot WX500 according to manufacturer’s instructions if problem remains. GIA2/WX 500 data path functionality is unknown. Reload GIA2 configuration files. ...
Page 80 ____________________________________________________________________ GIA2/Guardian data path is functioning correctly. GIA2/Guardian data path is not functioning correctly. • Check PFD Alert Window for GIA configuration or software error messages. Correct any errors before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is Guardian CO2 CHNL 4 in the original GIA2. Detector − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/Guardian interconnect wiring and connector pins for faults. Troubleshoot detector according to manufacturer’s instructions if problem remains. GIA2/Guardian data path functionality is unknown. Reload GIA2 configuration files. GIA2/GTX 32/33 data path is functioning correctly. GIA2/GTX 32/33 data path is not functioning correctly. • Check PFD Alert Window for GIA or GTX ...
Page 81 ____________________________________________________________________ GIA2 RS‐232 (continued) Channel LRU Indicator Status GIA2/GRS 77 #2 data path is functioning correctly. GIA2/GRS 77 #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #2 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #2 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their GRS 77 #2 new locations to see if the problem is in the original CHNL 6 (if GIA2. equipped) − Replace original GIA2 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 to see if the problem is in the original GRS77 #2. − Replace original GRS77 #2 if box turns green after swapping units. • Check the GIA2/GRS 77 #2 interconnect wiring and ...
Page 82 ____________________________________________________________________ GIA2 RS‐232 (continued) Channel LRU Indicator Status GIA1/GMA 347 data path is functioning correctly. GIA1/GMA 347 data path is not functioning correctly. • Check PFD Alert Window for GIA or GMA configuration or software error messages. Correct any errors before proceeding. • Make sure the GMA 347 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GMA is offline before proceeding. GMA CHNL 7 • Swap GIA1 and GIA2. Reconfigure both GIA’s at their 347* new locations to see if the problem is in the original GIA2. − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/GMA 347 interconnect wiring and connector pins for faults. • Replace GMA 347 GIA1/GMA 347 data path functionality is unknown. Reload GIA1 configuration files. NOTE * ‐ The path is identified by the Cirrus Perspective™ System as GMA 1347#1 ...
Page 83 ____________________________________________________________________ GIA2 ARINC 429 Channel LRU Indicator Status GIA2/SKYWATCH 497 data path is functioning correctly. GIA2/SKYWATCH 497 data path is not functioning correctly. • Check PFD Alert Window for GIA configuration or software error messages. Correct any errors before proceeding. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their SKYWATCH new locations to see if the problem is in the original IN 4 497 GIA2. (Optional) − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/Skywatch interconnect wiring and connector pins for faults. • Troubleshoot Skywatch according to manufacturer’s instructions if problem remains. GIA2/SKYWATCH 497 data path functionality is unknown. Reload GIA2 configuration files. ...
Page 84 ____________________________________________________________________ GIA2/GDC 74A #1 data path is functioning correctly. GIA2/GDC 74A #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #1 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐ X, troubleshoot why the GDC is offline before proceeding. IN 5 GDC 74A #1 • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA2. − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/GDC 74A #1 interconnect wiring and unit connector pins for faults. • Replace GDC 74A #1. GIA2/GDC 74A #1 data path functionality is unknown. Reload GIA2 configuration files. Page 5-38 Cirrus Perspective™...
Page 85 ____________________________________________________________________ GIA2 ARINC 429 (continued) Channel LRU Indicator Status GIA2/GRS 77 #1 data path is functioning correctly. GIA2/GRS 77 #1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #1 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #1 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original IN 6 GRS 77 #1 GIA2. − Replace original GIA2 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 (if a GRS77 #2 is installed) to see if the problem is in the original GRS77 #1. − Replace original GRS77 #1 if box turns green after swapping units. • Check the GIA2/GRS 77 #1 interconnect wiring and unit connector pins for faults. •...
Page 86 ____________________________________________________________________ GIA2 ARINC 429 (continued) Channel LRU Indicator Status GIA2/GDC 74A #2 data path is functioning correctly. GIA2/GDC 74A #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GDC configuration or software error messages. Correct any errors before proceeding. • Make sure the GDC 74A #2 status is OK using the AUX – SYSTEM STATUS page on the MFD. If there is a Red‐ X, troubleshoot why the GDC is offline before GDC 74A #2 proceeding. IN 7 (if • Swap GIA1 and GIA2. Reconfigure both GIA’s at their equipped) new locations to see if the problem is in the original GIA2. − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/GDC 74A #2 interconnect wiring and unit connector pins for faults. • Replace GDC 74A #2. GIA2/GDC 74A #2 data path functionality is unknown. Reload GIA2 configuration files. Page 5-40 Cirrus Perspective™...
Page 87 ____________________________________________________________________ GIA2 ARINC 429 (continued) GIA2/GRS 77 #2 data path is functioning correctly. GIA2/GRS 77 #2 data path is not functioning correctly. • Check PFD Alert Window for GIA or GRS configuration or software error messages. Correct any errors before proceeding. • Make sure the GRS77 #2 status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GRS is offline before proceeding. • Make sure the GRS77 #2 connecter is secure and proper wire harness strain relief is provided. • Swap GIA1 and GIA2. Reconfigure both GIA’s at their GRS 77 #2 new locations to see if the problem is in the original IN 8 (if GIA2. equipped) − Replace original GIA2 if box turns green after swapping units. • Swap GRS77 #1 and GRS77 #2 to see if the problem is in the original GRS77 #2. − Replace original GRS77 #2 if box turns green after swapping units. • Check the GIA2/GRS 77 #2 interconnect wiring and unit connector pins for faults. • Replace GRS 77 #2. GIA2/GRS 77 #2 data path functionality is unknown. ...
Page 88 ____________________________________________________________________ GIA RS‐485 Configuration Page NOTE Do not load any GEA configuration files unless it is absolutely necessary. The HSCM circuits must be recalibrated if they are reloaded. GIA1 RS‐485 Channel LRU Indicator Status GIA1/GEA1 data path is functioning correctly. GIA1/GEA1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GEA configuration or software error messages. Correct any errors before proceeding. • Make sure the GEA status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐X, troubleshoot why the GEA is offline before proceeding. • CHNL 1 GEA1 Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/GEA1 interconnect wiring and connector pins for faults. • Replace GEA71. GIA1/GEA1 data path functionality is unknown. Reload GIA1 configuration files. ...
Page 89 ____________________________________________________________________ GIA1/GFC 700 data path is functioning correctly. GIA1/GFC 700 data path is not functioning correctly. • Check PFD Alert Window for GIA, GFC, GTA or GSA configuration or software error messages. Correct any errors before proceeding. • Make sure all GSA/GTA servo statuses are OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If one or all show a Red‐X, troubleshoot why the servos are offline before proceeding. CHNL 4 GFC 700 • Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA1. − Replace original GIA1 if box turns green after swapping units. • Check the GIA1/GSA/GTA interconnect wiring and connector pins for faults. • Proceed to the Autopilot Troubleshooting section for further assistance. GIA1/GFC 700 data path functionality is unknown. Reload GIA1 and GFC700 configuration files. Cirrus Perspective™ Line Maintenance Manual Page 5-43 190-00920-00 Rev.
Page 90 ____________________________________________________________________ GIA2 RS‐485 Channel LRU Indicator Status GIA2/GEA1 data path is functioning correctly. GIA2/GEA1 data path is not functioning correctly. • Check PFD Alert Window for GIA or GEA configuration or software error messages. Correct any errors before proceeding. • Make sure the GEA status is OK using the AUX ‐ SYSTEM STATUS PAGE on the MFD. If there is a Red‐ X, troubleshoot why the GEA is offline before proceeding. • CHNL 1 GEA1 Swap GIA1 and GIA2. Reconfigure both GIA’s at their new locations to see if the problem is in the original GIA2. − Replace original GIA2 if box turns green after swapping units. • Check the GIA2/GEA1 interconnect wiring and connector pins for faults. • Replace GEA71. GIA2/GEA1 data path functionality is unknown. Reload GIA2 configuration files. Page 5-44 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 91: Gdu Related Alerts And Problems
____________________________________________________________________ 5.6 GDU RELATED ALERTS AND PROBLEMS 5.6.1 General Problems Symptom Recommended Action • Display will not track Go to the GDU TEST page in configuration mode. Cover and photocell uncover the photocells and make sure that PHOTOCELL A or PHOTOCELL B value changes. Keyboard will not track − photocell If values do not change, replace the display. • Reload GDU configuration files. • Display will not track dimmer Reload GDU configuration files. bus • Swap PFD or MFD to see if problem remains with display. Keyboard will not track − Replace display if condition remains with the same unit. dimmer bus − If condition remains in original position after swapping displays, check GDU dimmer input for the presence of voltage. • Display is blank Make sure a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Cycle power. •...
Page 92 DO NOT force the SD Card out. • Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card. • Push the card in further to release the card locking mechanism. • Check SD Card for having more than one label. Two or more labels on the card will cause sticking. • Remove all but one label. • Insure the SD card is from SanDisk. Use of other brand of SD Cards is not recommended due to variances in card thickness. • If card was inserted with the label facing to the right, do not attempt to remove. Return the unit to Garmin for repair. • A button/knob/joystick does Go to the GDU TEST page in configuration mode and make sure not appear to function the button, knob, or joystick operates correctly by observing a change in color from red to green in the button/knob/joystick icon when the button/knob/joystick is pressed. If a button is stuck, the button icon will be green without pressing the button as soon as you turn to the GDU TEST page. • If problem is verified, replace GDU. • Terrain/Obstacle/SafeTaxi/ Check the PFD ALERT window for any Database Error Messages. FliteCharts does not display Correct before proceeding. on map • Make sure the supplemental data cards are inserted correctly in ...
Page 93: Database And Software Alerts
____________________________________________________________________ 5.6.2 Database and Software Alerts Message Cause Solutions • MFD1 DB ERR – MFD1 The MFD has encountered Reload aviation database into the aviation database error exists. an error in the Jeppesen display. database. • Contact Garmin Technical Support PFD DB ERR – PFD aviation PFD has encountered an for assistance. database error exists. error in the Jeppesen database. • MFD1 DB ERR – MFD1 The MFD has encountered Make sure the supplemental data basemap database error an error in the basemap card is inserted fully in the bottom exists. database. slot of the display. • PFD DB ERR – PFD basemap PFD has encountered an Remove the supplemental data card database error exists. error in the basemap from the bottom slot of the display ...
Page 94 ____________________________________________________________________ Database and Software Alerts (continued) Message Cause Solutions • MFD1 DB ERR – MFD1 terrain The MFD has encountered Make sure the supplemental data database error exists. an error in the terrain card is inserted fully in the bottom database. slot of the display. • PFD DB ERR – PFD terrain PFD has encountered an Remove the supplemental data card database error exists. error in the terrain from the bottom slot of the display database. and insert in the top slot. − MFD1 DB ERR – MFD1 The MFD has encountered If the problem is resolved, the obstacle database error an error in the obstacle bottom card slot is dirty or has exists. database. failed. Try reinserting the card multiple times in the bottom PFD DB ERR – PFD obstacle PFD has encountered an slot to clean the card contacts. database error exists. error in the obstacle If the problem remains in the ...
Page 95 ____________________________________________________________________ Database and Software Alerts (continued) Message Cause Solutions • Make sure the supplemental data PFD DB ERR – PFD Safe Taxi® PFD has encountered an card is inserted fully in the bottom database error exists. error in the SafeTaxi® slot of the display. database. • Remove the supplemental data card from the bottom slot of the display and insert in the top slot. If the problem is resolved, the bottom card slot is dirty or has failed. Try reinserting the card multiple times in the bottom slot to clean the card contacts. • If the problem remains in the bottom slot, you may leave the card in the top slot (if the top slot if unused) or replace the display. • Swap with a supplemental data card from another display in the same system. • If problem moves to the other display, reload the database or replace all the supplemental datacards as a set. • If problem remains in the same GDU, replace that GDU. ...
Page 96 ____________________________________________________________________ Database and Software Alerts (continued) Message Cause Solutions • MFD1 DB ERR – MFD1 The MFD has encountered Make sure the supplemental data ChartView database error. an error in the ChartView card is inserted fully in the top slot database. of the display. • Remove the supplemental data card from the top slot of the display and insert in the bottom slot. − If the problem is resolved, the top card slot is dirty or has failed. Try reinserting the card multiple times in the top slot to clean the card contacts. If the problem remains in the top slot, replace the display. • Reload the Jeppesen ChartView database onto the card. • MFD1 DB ERR – MFD1 The MFD has encountered Make sure the supplemental data Terminal Procs database error an error in the Terminal card is inserted fully in the bottom exists. Procedures database. slot of the display. •...
Page 97 ____________________________________________________________________ DB MISMATCH – Aviation The system has found the • database version mismatch. Jeppesen aviation Load the same cycle of aviation Xtalk is off. database in the PFD and database to all displays. MFD do not match. DB MISMATCH – Aviation The system has found the • database type mismatch. Jeppesen aviation Load same type aviation database database types do not to all displays. match. Cirrus Perspective™ Line Maintenance Manual Page 5-51 190-00920-00 Rev. E...
Page 98 ____________________________________________________________________ Database and Software Alerts (continued) Message Cause Solutions DB MISMATCH – Terrain The PFD and/or MFD have database version mismatch. different terrain database versions installed. DB MISMATCH – Obstacle The PFD and/or MFD have database version mismatch. different obstacle • Insert two identical version database versions supplemental database cards in the installed. PFD and MFD. DB MISMATCH – Terrain The PFD and/or MFD have database type mismatch. different terrain database types installed. DB MISMATCH – Airport The PFD and/or MFD have Terrain database mismatch. different airport terrain Xtalk is off. database types installed. CAS INOP The system has found the • PFD and/or MFD software Reload PFD and MFD software. versions do not match. •...
Page 99: Cooling Alerts
____________________________________________________________________ 5.6.3 Cooling Alerts NOTE The following alerts only apply if the cooling fan inputs are configured on. Message Cause Solutions • MFD1 COOLING – has poor The MFD has exceeded its Check cooling fan and wiring for cooling. Reducing power operating temperature proper operation. usage. range. − Replace cooling fan if unable to determine if operating correctly. • If problem persists, replace the MFD. • PFD COOLING – has poor PFD has exceeded its Check cooling fan and wiring for cooling. Reducing power operating temperature proper operation. usage. range. − Replace cooling fan if unable to determine if operating correctly. • If problem persists, replace the PFD. ...
Page 100: Miscellaneous Alerts
____________________________________________________________________ 5.6.5 Miscellaneous Alerts Message Cause Solutions • XTALK ERROR – A flight A communication error Check the PFD ALERTS Window for display cross talk error has has occurred between the database error Messages. Correct occurred. MFD and PFD. all errors before proceeding. • Check display Ethernet interconnect wiring and pins for faults. • Replace PFD with a known good unit, to verify location of problem: − If problem persists, reinstall original PFD. − Replace MFD. • SIMULATOR – Sim mode is The system is in simulator Check wiring (pin 54 in all GDU active. Do not use for mode. connectors should be empty). navigation. • Replace PFD with a known good unit, to verify location of problem: − If problem persists, reinstall ...
Page 101 ____________________________________________________________________ Miscellaneous Alerts (continued) Message Cause Solutions • DATA LOST – Pilot stored data Pilot stored data has been If the CLR key was held during a lost. Recheck settings. lost. power cycle, disregard message. • Cycle power to PFD: − Make sure the CLR key is not stuck on the GDU TEST page. − If problem persists, replace PFD. • MFD1 SERVICE – needs The system has Make sure the MFD connector is service. Return unit for determined the MFD fully seated and locked. repair. needs service. • If the unit was started in a very dark environment, the photocells may not have enough light to initially raise the CCFT level. Go to the GDU STATUS page in configuration mode, make sure the CCFT CRNT 1 & 2 levels are above 50. − If the CCFT levels are not above 50, apply light to the photocell and observe if the CCFT level ...
Page 102 ____________________________________________________________________ Miscellaneous Alerts (continued) • PFD SERVICE – needs service. The system has Make sure the PFD connector is fully Return unit for repair. determined PFD needs seated and locked. service. • If the unit was started in a very dark environment, the photocells may not have enough light to initially raise the CCFT level. Go to the GDU STATUS page in configuration mode, make sure the CCFT CRNT 1 & 2 levels are above 50. − If the CCFT levels are not above 50, apply light to the photocell and observe if the CCFT level rises. − If the CCFT level rises, disregard the message. − If the CCFT level does not rise, replace the PFD. • Inspect the master configuration module connections in the PFD connector • In configuration mode, check the SDRAM and BKUP CAPS status on the GDU TEST page. If a red indication exists for either of these, the PFD needs to be repaired or replaced. ...
Page 103 ____________________________________________________________________ Miscellaneous Alerts (continued) Message Cause Solutions • PFD CONFIG – PFD The system has detected a Reload PFD configuration files from configuration error. Config PFD configuration SD Loader Card. service req’d. mismatch. • Reload system configuration files by pressing the UPDT CFG softkey on the Configuration Upload Page in the System Page Group to load configuration files into the configuration module. − If message persists, check config module wiring for faults and replace if necessary. − If problem persists, replace the PFD. Cirrus Perspective™ Line Maintenance Manual Page 5-57 190-00920-00 Rev. E...
Page 104 ____________________________________________________________________ Miscellaneous Alerts (continued) Message Cause Solutions • MFD CONFIG – MFD The system has detected a Reload MFD configuration files configuration error. Config MFD configuration from SD Loader Card. service req’d. mismatch. • Reload system configuration files by pressing the UPDT CFG softkey on the Configuration Upload Page in the System Page Group to load configuration files into the configuration module. − If message persists, check config module wiring for faults and replace if necessary. − If problem persists, replace the MFD. • PFD VOLTAGE – PFD has low PFD is not receiving Check input voltage to PFD. voltage. Reduce power sufficient voltage. − If input voltage is ok, replace usage. PFD. • MFD1 VOLTAGE – MFD1 has ...
Page 105 • TAWS INHB TAWS system alerting is Enable TAWS system alerting by disabled pressing the MENU button from the MAP – TAWS page. • TAWS N/A GPS system integrity not Make sure a valid GPS position is high enough to enable received from the AUX – GPS TAWS STATUS page. • TRAFFIC FAIL Communication with the If a non‐Garmin traffic device is traffic device has failed. installed, refer to the manufacturer’s maintenance manual to determine if it is operating correctly. • Check GIA2/Traffic Device wiring and connectors for faults. Cirrus Perspective™ Line Maintenance Manual Page 5-59 190-00920-00 Rev. E...
Page 106: Gma 347 Related Alerts And Problems
____________________________________________________________________ 5.7 GMA 347 RELATED ALERTS AND PROBLEMS 5.7.1 Common Problems Symptom Recommended Action Noise in Audio Most often the cause of the noise is external to the GMA 347. Try the following to locate the source of the noise before replacing the 347: • Try a different pair of headsets. Noise cancelling headsets may pick up and/or generate more noise than standard headsets from their own circuitry. • Check for noise with engine turned off. − If the noise is present only when the engine is running, check the generator and/or ignition system as possible sources of noise (see Cirrus Maintenance Manual). • Check for noise as all electrical equipment is turned on and off (strobes, other radios, etc.). − If the noise is identified from one electrical system or component refer to the Cirrus airframe maintenance manual. • Make sure the NAV/COM squelch is not open. • Make sure the ADF and DME audio is not active. • Make sure the marker beacon audio is not active. • Make sure the ICS squelch is not open. Master squelch level can be adjusted on the GMA CONFIGURATION page for higher noise environments. • Check resistors in line with Music 1 and Music 2 wiring at the GMA 347 in accordance with system wiring diagrams ...
Page 107 ____________________________________________________________________ • COM Bleed over Make sure on the GMA CONFIGURATION page that “MUTE AUDIO ON TX” has a green box. Due to the closeness of the COM antennas and high power of the COM transmitters, COM bleed‐ over may occur if this option is enabled. If the box is black, highlight “MUTE AUDIO ON TX” with the cursor and press the ENT key to turn the box green. • Speaker Cuts Out Reduce the volume of the item that caused the speaker to cut out when turned up. A speaker protection circuit disables the speaker output if the volume is too high. If the volume is not sufficient, replace aircraft cabin speaker, reference the Cirrus Maintenance Manual. • MIC Audio Heard in Speaker Reduce ICS Volume. Cirrus Perspective™ Line Maintenance Manual Page 5-61 190-00920-00 Rev. E...
Page 108: Gma 347 Alerts
____________________________________________________________________ 5.7.2 GMA 347 Alerts Message Cause Solutions MANIFEST – GMA1 software The system has detected mismatch. Communication an incorrect software • Load correct software version. Halted. version loaded in GMA 347. GMA1 SERVICE – GMA1 needs The system has • service. Return unit for determined GMA 347 Replace the GMA 347. repair. needs service. • GMA1 FAIL – GMA 1 is The system has detected a Make sure the 347 is receiving inoperative. failure in GMA 347. power. • Make sure both GIAs are receiving power. • Make sure all GDUs are receiving power. • Make sure the 347/GIA RS‐232 data lines are working properly. •...
Page 109: Gia 63W Related Alerts And Problem
____________________________________________________________________ 5.8 GIA 63W RELATED ALERTS AND PROBLEMS 5.8.1 COM Symptom Recommended Action • Weak COM transmit power Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, replace GIA. − If problem does not follow unit, check COM antenna and cabling for faults. • Weak COM receiver Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, replace GIA. − If problem does not follow unit, check COM antenna and cabling for faults. • No COM sidetone Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, replace GIA. − If problem persists, replace 347. • COM Bleed over Make sure on the GMA CONFIGURATION page that “MUTE AUDIO ON TX” has a green box. Due to the closeness of the COM antennas and high power of the COM transceivers, COM bleed‐ over may occur if this option is enabled. If the box is black, highlight “MUTE AUDIO ON TX” with the cursor and press the ENT key to turn the box green. 5.8.1.1 COM Adjustment Procedure ...
Page 110 ____________________________________________________________________ 6. Turn off the PFD and MFD by pulling their circuit breakers. 7. Restart the PFD and MFD in Configuration Mode. 8. On the PFD, turn to the COM SETUP page. 9. Activate the cursor and select the desired tuning frequency using the FMS knobs. Only the frequencies 118.00, 127.00, & 136.975 may be used when setting squelch and sidetone levels. 10. Select GIA1 or GIA2 in the COM Setup window. This forces an update of the calibration data values and must be accomplished prior to making any changes. Failure to do so may allow COM calibration values to be inadvertently stored into incorrect memory locations requiring GIA replacement. 11. For 25kHz operation, adjust the SQ 250 value. It may be set to any value between 0 (zero) and 63. The higher the number, the less signal is required to break squelch. 12. For 8.33kHz operation, adjust the SQ 833 value. It may be set to any value between 0 (zero) and 63. The higher the number, the more signal is required to break squelch. 13. After the squelch value is adjusted to the desired number, press the STORE softkey at the bottom of the display to save the value to the GIA. 14. Repeat steps 7‐11 for tuning additional frequencies. Page 5-64 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 111: Gps
____________________________________________________________________ 5.8.2 GPS Symptom Recommended Action • Will not acquire satellites Make sure a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Check for possible external interference to the GPS receivers by turning to the GPS page on the MFD and check the GPS strength bars on both GPS receivers. If the signal strength level is erratic, or they disappear and reappear rapidly, or switch between a solid and hollow bar frequently there is an external device interfering with the GPS receivers. Turn off any devices that radiate a signal in the local area or move the aircraft to another location to remove the interference. • Check date and time on Date/Time Setup Page. − If date and time are incorrect, enter the correct date and time. • Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, clear the GPS almanac by performing the following steps – • Using the PFD in config mode, go to the GIA RS‐ 232/ARNIC 429 Config Page. • At the top of the screen, select the GIA that cannot acquire satellites (GIA1 or GIA2) and press the ENT key. • Press the “CLR NV” softkey at the bottom of the screen. • Select “OK” in the “Clear GIA nonvolatile memory?” pop‐ up window. •...
Page 112: Nav
____________________________________________________________________ 5.8.3 NAV Symptom Recommended Action • Weak NAV receiver Set up a NAV/COM Ramp Test Set to radiate a test signal. • Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, replace GIA. − If problem does not follow unit, check NAV antenna, coupler, and cabling for faults. 5.8.4 G/S Symptom Recommended Action • Weak G/S receiver Set up a NAV/COM Ramp Test Set to radiate a test signal. • Switch GIA1 and GIA2, to verify location of problem: − If problem follows unit, replace GIA. − If problem does not follow unit, check NAV antenna, coupler, and cabling for faults. 5.8.5 COM Related Alerts Message Cause Solutions COM1 SERVICE – COM1 needs The system has ...
Page 113 ____________________________________________________________________ • COM1 PTT – COM1 push‐to‐ The COM1 external push‐ Press the push‐to‐talk switch(s) talk key is stuck. to‐talk (PTT) switch is again to cycle its operation. stuck in the enabled (or • Check push‐to‐talk switch(s) and “pressed”) state. wiring. • Switch GIA1 and GIA2, to verify location of problem: − If problem follows the unit, replace GIA1. • Check GIA1/GMA 347 interconnect. • Replace GMA 347. • COM2 PTT – COM2 push‐to‐ The COM2 external push‐ Press the push‐to‐talk switch(s) talk key is stuck. to‐talk (PTT) switch is again to cycle its operation. stuck in the enabled (or • Check push‐to‐talk switch(s) and “pressed”) state. wiring. • Switch GIA2 and GIA1, to verify location of problem: − If problem follows the unit, ...
Page 114: Nav Related Alerts
____________________________________________________________________ 5.8.6 NAV Related Alerts Message Cause Solutions NAV1 SERVICE – NAV1 needs The system has detected a • service. Return unit for failure in NAV1 receiver. Replace GIA1. repair. NAV2 SERVICE – NAV2 needs The system has detected a • service. Return unit for failure in NAV2 receiver. Replace GIA2. repair. 5.8.7 G/S Related Alerts Message Cause Solutions G/S1 SERVICE – G/S1 needs The system has detected a • service. Return unit for failure in G/S1 receiver. Replace GIA1. repair. G/S2 SERVICE – G/S2 needs The system has detected a • service. Return unit for failure in G/S1 receiver. Replace GIA2. ...
Page 115: Gps Related Alerts
____________________________________________________________________ 5.8.8 GPS Related Alerts NOTE Before troubleshooting, make sure no cell phones or devices using cell phone technology are turned on in the cabin (even in a monitoring state). Message Cause Solutions GPS1 SERVICE – GPS1 needs The System has detected • service. Return unit for a failure in GPS1 receiver. Replace GIA1. repair. GPS2 SERVICE – GPS2 needs The system has detected a • service. Return unit for failure in GPS2 receiver. Replace GIA2. repair. • The system has detected a GPS1 FAIL – GPS1 is Switch GIA1 and GIA2, to verify failure in GPS1 receiver. inoperative. location of problem: − If problem follows the unit, replace GIA1. If problem does not follow the unit, check GPS1 antenna and cabling. • GPS2 FAIL – GPS2 is The system has detected a ...
Page 116: Gia Configuration Alerts
____________________________________________________________________ 5.8.9 GIA Configuration Alerts Message Cause Solutions GIA1 CONFIG – GIA1 The system has detected a • See Section 7 for GIA configuration configuration error. Config GIA configuration instructions. service req’d. mismatch. • If problem persists, check config GIA2 CONFIG – GIA2 module harness for faults and configuration error. Config replace if necessary. service req’d. GIA1 CONFIG – GIA1 audio The system has detected a • See Section 7 for GIA configuration config error. Config service GIA audio configuration instructions. req’d. mismatch. • If problem persists, check config GIA2 CONFIG – GIA2 audio module harness for faults and config error. Config service replace if necessary. req’d. HW MISMATCH – GIA hardware mismatch. GIA1 ...
Page 117: Grs 77/Gmu 44 Related Alerts And Problems
• Check GRS 77 connector for bent pins. − If no damage can be found, replace GRS 77 configuration module. • If problem persists, replace the GRS 77. • Attitude appears unstable Make sure a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. • Make sure the four GRS 77 mounting screws are tight. Finger tight is not sufficient, a screwdriver must be used to verify. • Make sure the mounting rack and airframe shelf are secure and all hardware and brackets are present (CAUTION ‐ do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re‐leveled and the PITCH/ROLL OFFSET procedure performed). • Make sure the GRS 77 connector is securely fastened and proper strain relief is provided. • Remove GRS 77 connector and make sure there are no bent pins. • Replace the GRS 77. • Contact Garmin for further troubleshooting if required. Cirrus Perspective™ Line Maintenance Manual Page 5-71 190-00920-00 Rev. E...
Page 118: Grs 77 Related Alerts
The GRS 77 #2 is acquire a position lock. operating exclusively in no‐ operating in the absence Troubleshoot GPS problems using GPS mode. of GPS. Sections 5.1.2 and 5.6.2. AHRS2 GPS – AHRS2 not GRS 77 #2 is not receiving • Replace the GRS 77. receiving any GPS GPS data from either information. GIA 63W. • AHRS1 SRVC – AHRS1 AHRS #1 magnetic field Reference Garmin SB 0533 for magnetic field model needs model has expired. update instructions. update. AHRS2 SRVC – AHRS2 AHRS #2 magnetic field magnetic field model needs model has expired. update. Page 5-72 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 119: Gmu 44 Related Alerts
Halted. version loaded in GRS 77 • Load correct software version in the #1. GRS77. MANIFEST – AHRS2 software The system has detected mismatch. Communication an incorrect software Halted. version loaded in GRS 77 #2. AHRS MAG DB – AHRS The system has detected a • Reference Garmin SB 0533 for magnetic model database magnetic model database update instructions. version mismatch. version mismatch. 5.9.3 GMU 44 Related Alerts Message Cause Solutions MANIFEST – GMU1 The system has detected an software mismatch. incorrect software version Communication Halted. loaded in GMU 44 #1. • Load correct software version in the ...
Page 120: Gdc 74A Related Alerts And Problems
____________________________________________________________________ 5.10 GDC 74A RELATED ALERTS AND PROBLEMS 5.10.1 Common Problems Symptom Recommended Action • Altitude is different than Perform a pitot/static check (see the Cirrus Maintenance Manual standby altimeter for procedure). Allow the GDC 74A to warm up for fifteen minutes before checking accuracy, see Garmin Service Advisory 0606. • Determine which instrument is outside limits and recalibrate or replace. Note: Both units may individually be in spec but show a difference in altitude. Do not return a GDC 74A to Garmin for service if not outside limits. • If GDC is outside limits, recalibration may be performed in accordance with Section 5.9. • GDC 74A Config file does not Replace GDC 74A config module. load. • If problem persists, replace GDC 74A config module wire harness. 5.10.2 GDC 74A Related Alerts Message Cause Solutions MANIFEST – GDC 74A#1 The system has detected an software mismatch incorrect software version ...
Page 121: Gdc 74A Field Calibration Utility
±5 feet at sea level, ±15 feet at 30,000 feet, and ±15 feet at 41,000 feet. For calibration of the GDC 74A, the pressure control system must control altitude automatically. Purpose The GDC 74(X) Field Calibration utility (P/N T06‐A0156‐00) is designed to adjust the calibration of GDC 74A units that have failed the 14 CFR Part 43 Appendix E tests due to altitude drift. Limitations These procedures should be performed on the bench (not in the aircraft) at room • temperature. The GDC 74(X) Field Calibration utility should only be used to correct errors due to • altitude drift. If the drift is greater than the limits defined in the GDC 74(X) Field Calibration utility at • any of the test points, the utility will not allow the calibration to continue and the GDC 74A unit must be returned to Garmin. If the GDC 74A unit does not pass 14 CFR Part 43 Appendix E after the calibration utility • has been run, the GDC 74A unit should be returned to Garmin. Requirements GDC 74A unit. • Power supply (14/28V, 500mA). • PC with a Serial Port or serial port adapter. • Pressure control system capable of generating the correct static pressures for 0 feet, • 11,000 feet, 30,000 feet, and 41,000 feet. Fabricate a cable built to interface a GDC 74A to a PC Serial Port (see Figure 5‐10). The •...
Page 122 ____________________________________________________________________ Software Installation Before beginning the software field upgrade procedure, the GDC 74(X) Field Calibration utility must be downloaded from the Garmin website. 1. Enter the Dealer Resource portion of the Garmin website (www.garmin.com). 2. From the Technical Resource list, click on the link for the GDC 74(X) Field Calibration utility. 3. Follow the instructions to save the file to the PC (it is recommended to create a folder ‘C:\Garmin’ as a target directory for the file). Procedure 1. Connect the GDC 74A to the pressure control system. 2. Connect the GDC 74A to the PC serial port using the GDC 74A – PC Interface Cable (Figure 5‐10). 3. Connect the GDC 74A PC Interface Cable to the power supply (Figure 5‐10). 4. Power on the GDC 74A and the pressure control system. 5. Set the pressure control system to a pressure altitude of 40,000 feet and determine that leakage is less than 140 feet per minute. 6. Run GDC_FieldCal.exe. 7. Click on ‘Begin Field Calibration’. NOTE The GDC 74(X) Field Calibration utility requires that the GDC 74A and the ...
Page 123 ____________________________________________________________________ Figure 5‐12. Serial Port Pull‐down List 9. After communication with the GDC 74A is established, the ‘Full Backup’ screen appears while a full backup of the original unit setting is saved to a file named BKUP_(serial_num)_YYYYMMDD_ HHMMSS.txt. This file can be used by Garmin to restore the unit to the original settings if necessary. 10. After the full backup file has been created, the ‘Prepare To Take Measurements’ screen appears while the program retrieves the unit type from the GDC 74A. 11. After the unit type has been determined, the ‘Set altitude to 0 ft’ screen (Figure 5‐13) appears. 12. According to the on‐screen instructions, set the pressure control system to a pressure altitude of 0 feet. 13. Allow the on‐screen altitude reading to stabilize, then click ‘OK’. Figure 5‐13. 0 Feet Calibration Screen Cirrus Perspective™ Line Maintenance Manual Page 5-77 190-00920-00 Rev. E...
Page 124 ____________________________________________________________________ NOTE If any of the three measurements (Altitude, Vertical Speed, Power On Time) are outside of their respective displayed limits, the displayed measurement will appear in red, and the ‘OK’ button will be unavailable (grayed‐out). If successful calibration is not achievable, clicking ‘Cancel’ will halt the program and produce the following popup message: Figure 5‐14. Calibration Failed Screen 14. After the 0 feet calibration is complete, the ‘Set altitude to 11,000 ft’ screen appears. 15. According to the on‐screen instructions, set the pressure control system to a pressure altitude of 11,000 feet. 16. Allow the on‐screen altitude reading to stabilize, then click ‘OK’. 17. After the 11,000 feet calibration is complete, the ‘Set altitude to 30,000 ft’ screen appears. ...
Page 125 ____________________________________________________________________ Figure 5‐15. Program Calibration to Unit Screen 24. Make sure the pop‐up cal result window shows ‘PASSED’, then press ‘OK’ to confirm message. Figure 5‐16. Field Calibration Result Screen 25. Return the pressure control system to ambient pressure before disconnecting the pitot and static lines from the GDC 74A. 26. Click on ‘Exit’ in the upper left corner to exit the program. 27. The field calibration is now completed, the unit may be installed in the aircraft (according to the instructions in this manual) to perform the operational system testing portion of 14 CFR Part 43 Appendix E. Cirrus Perspective™ Line Maintenance Manual Page 5-79 190-00920-00 Rev. E...
Page 126 ____________________________________________________________________ To Restore Original Calibration (if needed) If needed, the original calibration can be restored to the unit according to the following procedure: 1. Run GDC_FieldCal.exe. 2. Select ‘Restore’ from the upper left‐hand corner of the page. 3. Select the CAL_(serial_num)_YYYYMMDD_HHMMSS.txt calibration file to restore to the unit and click ‘Open’. Figure 5‐17. Calibration Files Screen 4. Select the Serial Port on the PC that will be used to communicate with the GDC 74(X), and click ‘OK’. A progress bar screen appears while the calibration is being restored to the unit. 5. If cal restoration is successful, the screen will display ‘Completed’ before returning to the main entry screen. 6. Click on ‘Exit’ in the upper left corner to exit the program. 7. The original calibration is now restored, the unit may be installed in the aircraft (according to the instructions in this manual) to perform the operational system testing portion of 14 CFR Part 43 Appendix E. Page 5-80 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 127 ____________________________________________________________________ Calibration File Storage Save copies of the calibration (BKUP and CAL) files for permanent storage. These files are located in the C:\Garmin directory, or in the same directory where the GDC_FieldCal.exe file resides. Email copies of these files to avionics@garmin.com. Please enter “GDC 74(X) Field Calibration Data” in the subject line, as shown in Figure 5‐18. Figure 5‐18. Example Post‐Calibration E‐mail Software Version 1. Click on ‘About’ in the upper right hand corner of the program, the software version is displayed. Figure 5‐19. About Screen 2. Click ‘OK’ to return to previous screen. Cirrus Perspective™ Line Maintenance Manual Page 5-81 190-00920-00 Rev. E...
Page 128: Gea 71 Related Alerts And Problems
____________________________________________________________________ 5.12 GEA 71 Related Alerts and Problems Message Cause Solutions • GEA1 CONFIG – GEA1 The system has detected a See Section 7 for instructions on configuration error. Config GEA 71 configuration configuration. service req’d. mismatch. • If problem persists, check config module harness for faults and replace if necessary. MANIFEST – GEA1 software The system has detected • mismatch. Communication an incorrect software Load correct software version. Halted. version loaded in GEA 71. • ALT1, ALT2, and BAT1 Refer to Section 5.10.1 for the High Discharged standby battery circuits needs to be Side Current Monitor calibration Indication. recalibrated Procedure. Page 5-82 Cirrus Perspective™...
Page 129 ____________________________________________________________________ 5.12.1 GEA 71 High‐Side Current Monitor Calibration Procedure NOTE This procedure must be performed anytime a GEA is replaced, or anytime GEA configuration is loaded to an aircraft in the field. If none of the aforementioned conditions exist, check accuracy of amps readings to determine if HSCM calibration is necessary. ...
Page 130 ____________________________________________________________________ Figure 5‐21. HSCM Enabled GEA I/O A Channel Selection Box 6. Make sure all displayed Current and Calibration data is appropriate: a. CURRENT DATA: i. VALUE –the instantaneous reading from the GEA if the current offset was zero (any calibration offset has been taken out). ii. CURRENT OFFSET –the calibration offset that is presently loaded on the channel (this will be zero if the channel has never been calibrated). iii. CURRENT CORRECTED VALUE – the current output of the GEA channel with the above current offset applied (what would be displayed on the EIS strip if the GDU was in normal mode). If the channel is calibrated and the calibration setup is correct, this parameter should be near zero, and fluctuation should be minimal. Be sure to take note of the range of fluctuation. b. CALIBRATION DATA: i. VALUE –the instantaneous current reading from the GEA if the current offset was zero (any calibration has been taken out). ii. CALIBRATION OFFSET –the instantaneous calculation of what the offset should be in order to properly calibrate the channel (assuming the shunt is properly set up for calibration, see step 1). iii. CALIBRATION CORRECTED VALUE ‐ the output of the GEA channel if the above offset were applied (should always be zero). 7. Press the STORE softkey, the following calibrate confirmation box appears: Figure 5‐22. Calibrate Confirmation Box 8. Press the ENT Key to accept the CALIBRATION OFFSET value. The instantaneous CALIBRATION OFFSET value is stored as the CURRENT OFFSET. ...
Page 131 ____________________________________________________________________ 9. The system will now re‐verify the GEA configuration (this may take several minutes). During this time the box shown in Figure 5‐23 is displayed. Do not perform any actions until this is complete. Figure 5‐23. Configuration Verification Processing 10. When the configuration is complete, press the ENT key to confirm. Figure 5‐24. Configured Confirmation Box 11. Once verification is complete, the CURRENT CORRECTED VALUE should be zero, within a range of fluctuation that is equal to or less than noted prior to calibration. If this is the case, the calibration has been successfully completed. Cirrus Perspective™ Line Maintenance Manual Page 5-85 190-00920-00 Rev. E...
Page 132: Gtx 32/33 Related Alerts And Problems
____________________________________________________________________ 5.13 GTX 32/33 RELATED ALERTS AND PROBLEMS Message Cause Solutions XPDR1 CONFIG – XPDR1 The system has detected a configuration error. Config GTX 32/33 configuration service req’d. mismatch. • Perform a SET>ACTV configuration reset on the GTX Config page. • For a GTX33, make sure the aircraft registration is present in the GTX Configuration page. • If error is still present, reload config files from a loader card. See Section 7. MANIFEST – GTX1 software The system has detected mismatch. Communication an incorrect software • Load correct software version Halted. version loaded in GTX 32/33 #1. XPDR1 SRVC – XPDR1 needs The system has detected a • service. Return unit for failure in GTX 32/33. Replace GTX 32/33. repair. ...
Page 133: Gdl 69A Related Alerts And Problems
____________________________________________________________________ 5.14 GDL 69/69A RELATED ALERTS AND PROBLEMS 5.14.1 Common Problems Symptom Recommended Action No XM audio is • Check the PFD Alert Window for MFD or GDL configuration or software error heard messages. Correct any errors before proceeding. No XM weather • Make sure the GDL69/69A software option has been loaded to the aircraft by information is the presence of the MFD AUX – XM RADIO page. displayed • Make sure the following items are not preventing the audio panel from distributing XM audio (reference applicable Cirrus Perspective Pilot’s Guide for intercom operation and isolation modes): • Make sure nothing is plugged into the Music 1 or 2 jacks. Make sure the XM volume is not muted on the MFD AUX – XM RADIO page. Make sure the headphone volume is turned up. • Make sure the COM squelch is not open. Make sure the ICS squelch is not open. Make sure the marker beacon tones are not being received. • Go to the AUX – SYSTEM STATUS page on the MFD and make sure the unit is online. If a red X is present, make sure the unit is receiving power at the rack connector. • Restart the PFD and MFD in configuration mode and go to the GDL page. • Make sure unit is active. Make sure the signal number is “2” or “3”. If it is “0” or “1”, check the GDL 69/69A antenna and cabling for faults. • Reseat the GDL 69/69A to make sure the coax connector is fully seated. ...
Page 134: Gdl 69/69A Related Alerts
____________________________________________________________________ 5.14.2 GDL 69/69A Related Alerts Message Cause Solutions • GDL 69 FAIL – GDL 69 has The system has detected a If a GDL 69 is not installed, failed. failure in the GDL 69A. deactivate the option by performing the following steps: Turn the system on in Configuration Mode. On the PFD, go to the “System Configuration” Page in the System Group. Turn the Cursor on by pressing the FMS Knob. The “GDL69” text should be flashing. Press the ENT key to turn the GDL 69 off (indicated by the green light box changing to black). Turn the system off. • Replace GDL 69A. • Check GDL 69A antenna and cabling. • Check the GDL 69A and MFD interconnect. GDL69 CONFIG – GDL 69 The system has detected a • See Section 7 for GDL configuration configuration error. Config GDL 69A configuration ...
Page 135: Gmc 705 Related Alerts And Problems
____________________________________________________________________ 5.15 GMC 705 RELATED ALERTS AND PROBLEMS Message Cause Solutions • GMC CNFG – GMC Config The system has detected a Load GMC configuration files, see error. Config service req’d. GMC 705 configuration Section 7. mismatch. • Replace GMC. • If problem persists, check config module wiring for faults and replace if necessary. • GMC FAIL – GMC is The system has detected a Replace the GMC 705 inoperative. failure in the GMC 705. • MANIFEST – GMC software The system has detected Load correct software version mismatch. Communication an incorrect software halted. version loaded in the GMC 705. Cirrus Perspective™ Line Maintenance Manual Page 5-89 190-00920-00 Rev.
Page 136: Afcs System Troubleshooting
____________________________________________________________________ 5.16 AFCS SYSTEM TROUBLESHOOTING The information in this section is specific to the GFC 700. If a problem is encountered during the operation of the GFC 700, the pilot and technician should first evaluate the overall status and condition of the system on the AUX – System Status Page (MFD). Observe any alert messages, annunciations, or other abnormal behavior to help isolate a fault. 5.16.1 Annunciations and Alerts The GFC 700 AFCS Annunciation field is located above the airspeed tape on the PFD as shown in Figure 5‐25. Figure 5‐25. AFCS Annunciation Field Page 5-90 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 137 ____________________________________________________________________ The following annunciations may appear in the AFCS Annunciation field: Annunciation Condition Solutions • Check the PFD ALERT Window for any GIA, GRS, GDC, GSA or GTA error messages. Correct all before proceeding. AFCS System • Make sure no red X’s are present on the MFD and PFDs. Failure • Go to the MFD AUX ‐ SYSTEM STATUS page and make sure all LRUs have a ‘green’ check. • Troubleshoot according to Section 5.14.2. • Check the AUX – SYSTEM STATUS page to see if the Pitch Axis Failure servo is online (green check). Yaw Axis Failure • Make sure the affected servo is receiving power. Pitch Trim Axis • Check the servo wiring and connector. Failure • Make sure the PTRM switches are not stuck. • Roll Axis Failure Replace the affected servo if the failure condition still exists. •...
Page 138: Gfc 700 Pre-Flight Test And Troubleshooting
____________________________________________________________________ 5.16.2 GFC 700 Pre‐Flight Test and Troubleshooting This section helps the technician determine why the GFC 700 Pre‐Flight Test (PFT) indicated by the red PFT annunciation has failed. The PFT is performed by both GIA’s at system startup, and needs to pass on both GIA’s before the autopilot can be engaged. The PFT is only started if the AHRS has aligned, the GIA’s and servos are configured, and the certification gains are valid. If the PFT does not complete after one minute after initialization, it will fail. After the system PFT has passed, it will be performed again if a servo resets, if the autopilot servo breaker is reset, or if the cross‐side GIA restarts it. The PFT failure fault is logged in the GIA Maintenance Log and not in the Servo Maintenance Logs unless the GIA log fault identifies a servo problem. NOTE Thoroughly understanding the operation of the system in configuration mode before starting this procedure. The GFC Status Page may be used to check the status of the servos as an aid in troubleshooting. To access the GIA and GSA/GTA Maintenance Logs 1. Start the system in configuration mode. 2. Use the FMS knob on the PFD to display the Diagnostics Terminal Page in the system group. This page allows the technician to view maintenance logs associated with the GFC 700. ...
Page 139 ____________________________________________________________________ The GIA Maintenance Log can record any of the following faults: • FCS Task not started: Bad gains The FCS task has not started because the gains are not present or have been corrupted. Reload the gain files to correct. • FCS Task not started: Gain structure out of range The FCS task has not started because the gains are not compatible with the GIA software. Reload the gain files to correct. • PFT FAIL: Timeout, <STEP> Pre‐flight test has failed because the specified step has not passed in the allotted time. See the GIA pre‐flight steps for a description of the possible values for <STEP> on the failed GIA and for corrective actions. • PFT FAIL: Cross GIA Failed, State: <STEP> Pre‐flight test has failed on opposite GIA. <STEP> specifies the pre‐flight test step on the selected GIA was in progress when the pre‐flight test failed on the opposite GIA. See the GIA pre‐flight steps for a description of the possible values for <STEP> on the failed GIA and for corrective actions. • PFT FAIL: <STEP> Pre‐flight has failed because the step specified has failed. See the GIA pre‐flight test steps for a description of the possible values for <STEP> on the failed GIA and for corrective actions. • AHRS MON invalid: <STATE> The AHRS monitor has detected that the AHRS data is invalid. The possible values for <STATE> are: Mon Prmtr Invalid: The ARINC 429 data used by one of the monitors has not been received. Attitude Prmtr Invalid: The ARINC 429 pitch or roll angle has not been received. Exceeded Attitude Limits: The pitch or roll angle has exceeded the engagement limits. Cross Hdg Accel Fail: Cross heading acceleration monitor failed. Vert Accel Fail: Vertical acceleration monitor failed. Fltrd Cross Hdg Accel Fail: Filtered cross heading acceleration monitor failed. Fltrd Vert Accel Fail: Filtered vertical acceleration monitor failed. Roll Accel Fail: Roll acceleration monitor has failed. Normal Accel Fail: Normal acceleration has failed. Troubleshoot the GRS 77 for the cause of the failure. ...
Page 140 ____________________________________________________________________ • Stuck switch invalidated parameter: <AXIS> A MET switch in the specified axis is stuck. Check the MET (trim) switches for proper operation. • PRMTR: <PARAMETER> MODE:<MODE> Parameter lost The mode specified by <MODE> has disengaged because the parameter specified by <PARAMETER> has become invalid. The following is a list of some of the possible values for <PARAMETER>: AD TDM Comm Valid: The specified mode has been disengaged because communication with the servos, via the Time Division Multiplexer protocol, has been lost. Troubleshoot possible loss of communication paths to servos or loss of servo/AP disconnect power to the servos. AP Pitch MET not stuck: The specified mode has been disengaged due to a stuck pitch MET switch. Check the MET (trim) switches for proper operation. GIA Pre‐Flight Test Steps • PFT Step 0: System initializing, verify GFC powered This step checks to make sure the GFC is powered up. Make sure the GIA is connected to the autopilot disconnect on the GFC Configuration page. Make sure all configured servos are communicating on the System Status page. • PFT Step 1: System initializing, verify GIA audio is valid This step checks to make sure the GIA audio region has been loaded and configured. Load GIA audio files to correct. • PFT Step 2: System initializing, verify required servos are configured This step checks to make sure the current servo configuration matches the servo configuration specified in the certification gain file. Reload the gain files to correct. • PFT Step 3: System initializing, verify selected side This step checks to make sure the PFD is online and sending the selected AFCS side data over HSDB to the GIA. Make sure the PFD is turned on. Make sure the Ethernet connection from the PFD to the GIA is functioning. Page 5-94 Cirrus Perspective™...
Page 141 ____________________________________________________________________ • PFT Step 4: System initializing, verify AHRS monitor This step checks to make sure the AHRS monitor is valid and not reporting an AHRS failure. NOTE: AHRS monitor will be assumed valid if on the ground. Make sure the GRS 77 and GDC 74A are turned on and sending valid data. • PFT Step 5: System initializing, verify configured servos are valid This step checks to make sure that none of the servos are reporting any type of failure. Note that trim servos will report a failure on stuck MET switches. Make sure the MET switch is not stuck. Cycle power on all servos. • PFT Step 6: System initializing, verify cross GIA valid This step checks to make sure the cross‐side GIA is online and communicating with all servos from ARINC 485 data lines. The cross‐side GIA must also pass its AHRS monitoring. Make sure both GIAs are online and communicating with all servos. • PFT Step 7: Verify cross GIA initialized This step checks to make sure the cross‐side GIA is initialized. Cycle power on all servos and GIAs. Make sure the PFD and MFD are turned on. • PFT Step 8: Verify servo type This step checks to make sure the servos are the correct type. Make sure the servos are correct type. • PFT Step 9: Verify servo first certification data This step checks to make sure the servos and the GIAs have the same certification gains. Reload the certification gains to all GIAs and servos. • PFT Step 10: Verify servo second certification data This step checks to make sure the servos and the GIAs have the same certification gains. Reload the certification gains to all GIAs and servos. • PFT Step 11: Updating servo RTC This step sets the servo system time to the GIA system time. If fails this step, GIA’s cannot communicate with servos. Check for GIA/servo data path issues and power/AP disconnect loss. Cirrus Perspective™ Line Maintenance Manual Page 5-95 190-00920-00 Rev.
Page 142 ____________________________________________________________________ • PFT Step 12: Verify servo PFT status This step checks to make sure all servos have passed their own pre‐flight test. • PFT Step 13: Verify AP disconnect enabled This step checks to make sure GIA 1, GIA 2, and all servos are connected to the 28 volt autopilot disconnect. Make sure the autopilot disconnect is connected to all GIAs and servos and is registering 28 volts. Make sure the autopilot disconnect switch is not pressed. • PFT Step 14: Verify servo validity This step checks to make sure all servos are online and communicating with valid data. Make sure all servos are turned on and communicating. • PFT Step 15: Verify cross GIA PFT is completed This step checks to make sure the cross‐side GIA is also on step 14. Cycle power on all servos and GIAs. Make sure the PFD and MFD are turned on. • PFT Step 16: PFT completed The pre‐flight test is successfully completed. • PFT Step 17: PFT failed The pre‐flight test has failed. Page 5-96 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 143 ____________________________________________________________________ Servo Faults and Troubleshooting A status message is logged to the corresponding servo control or maintenance log whenever a servo fault occurs. This information is also accompanied by a time and date stamp. An “RTC DATE” entry is made every time a servo is powered on, and is normally not useful for troubleshooting. The following is a listing of possible faults that could be reported in a GSA fault log. Faults can occur in the monitor board processor or the control board processor, both of which are contained in the GSA. Monitor Processor The monitor processor contains the logs that are found in the following processors: 2 – Pitch Servo 4 – Roll Servo 6 – Yaw Servo 8 – Pitch Trim Servo There are two main groupings of faults that can occur in the monitor processor: The first grouping of faults can occur during the GSA unit pre‐flight test (PFT). If there is a fault during PFT, the unit will not be able to transition to normal mode and the only way to clear this state is to cycle unit power. The second grouping of faults can occur during normal mode. These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA. The notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician. Any faults that are not listed here indicate an internal problem requiring replacement of the servo. If the items in the notes column check out ok, replace the servo. PFT Faults MONITOR PFT STEP NOTES This can be a result of a failure on the other internal servo "INTERNAL COMM FAIL" board, check faults on the other processor "UNSW POWER INV" Check unit power "MON SOL PWR ON FAIL" Check unit power and AP Disconnect power "CTL SOL PWR ON FAIL" Check unit power and AP Disconnect power "SOL PWR FAIL" Check unit power and AP Disconnect power ...
Page 144 ____________________________________________________________________ Normal Mode Faults MONITOR FAULT NOTES "GIA DIS FAULT" Check the AP Disconnect power into the unit "HOST DATA DIF" Check the AHRS wiring to the system "HOST DATA INV" Check the AHRS wiring to the system "SVO PWR INV" Check unit power and AP Disconnect power “STRP CODE CHNG” Check the connector strap inputs to the unit “MET STUCK SWTCH” Check the MET switch inputs into the system “MET STATUS DIF” Check the MET switch inputs into the system Control Processor The control processor contains the following logs: 3 – Pitch Servo 5 – Roll Servo 7 – Yaw Servo 9 – Pitch Trim Servo There are two main groupings of faults that can occur in the control processor. The first grouping of faults can occur during the GSA unit pre‐flight test (PFT). If there is a fault during PFT, the unit will not be able to transition to normal mode and the only way to clear this state is to cycle unit power. The second grouping of faults can occur during normal mode. These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA. The notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician. Any faults that are not listed here indicate an internal problem requiring replacement of the servo. If the items in the notes column check out ok, replace the servo. Page 5-98 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 145 ____________________________________________________________________ PFT Faults CONTROL PFT STEP NOTES This can sometimes be a result of a failure on the other board, "INT COMM TEST FAIL" check faults on other processor "CTL MOT PWR ON FAIL" Check unit power and AP Disconnect power "MON MOT PWR ON FAIL" Check unit power and AP Disconnect power "HALL 1 FAIL" Check unit power and AP Disconnect power "HALL 2 FAIL" Check unit power and AP Disconnect power "HALL 3 FAIL" Check unit power and AP Disconnect power "HALL 4 FAIL" Check unit power and AP Disconnect power "HALL 5 FAIL" Check unit power and AP Disconnect power "HALL 6 FAIL" Check unit power and AP Disconnect power "CURR OFFST FAIL" Check unit power and AP Disconnect power "SVO TYPE FAIL" Check unit power and AP Disconnect power "CERT DATA UNINSTALLED" Upload the certification gain file to the Control board "STRAP CODE MISMATCH" Check the connector strap inputs to the unit Normal Mode Faults CONTROL FAULT NOTES "GIA DIS FAULT" Check the AP Disconnect power into the unit "HOST DATA DIF" Check the AHRS wiring to the system ...
Page 146 5. Enable the cursor by pressing the FMS knob, select “GIA1” in the LRU drop down menu and then press the ENT key to select it. 6. Skip the SERVO box and move the cursor to the COMMAND box and select “View Maintenance Log” in the drop down menu then press the ENT key. The error log data will be displayed in the OUTPUT box. If you see the “more…press any key to continue” text at the bottom of the screen, you may need to reselect “View Maintenance Log” for GIA data to allow it to continue scrolling down the screen (pressing any key will not continue, disregard the text instruction you to do so). Continue to scroll through all the OUTPUT data until you see the text, “End of Fault Log”. 7. Move the cursor back to the LRU box, select “GIA2” in the LRU drop down menu and then press the ENT key to select it. 8. Skip the SERVO box and move the cursor to the COMMAND box and select “View Maintenance Log” in the drop down menu then press the ENT key. The error log data will be displayed in the OUTPUT box. If you see the “more…press any key to continue” text at the bottom of the screen, you may need to reselect “View Maintenance Log” for GIA data to allow it to continue scrolling down the screen (pressing any key will not continue, disregard the text instruction you to do so). Continue to scroll through all the OUTPUT data until you see the text, “End of Fault Log”. 9. If you need to download Servo fault logs (usually done at the request of Garmin Product Support), perform the following steps. Otherwise, skip to step 10. a. In the LRU box, you may select either “GIA1” or “GIA2”. b. In the SERVO box, choose a servo using the FMS knobs. Each servo contains two logs, one in the Monitor (MON) processor and one in the Control (CTL) processor. You must download both for each servo separately. Page 5-100 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 147 ____________________________________________________________________ c. In the COMMAND box, select “View Maintenance Log” and press the ENT key. d. The log will appear in the OUTPUT box. It will scroll to the end automatically. When it is complete, repeat steps a‐c for the other servos in the aircraft. Be sure to note the order the servos were downloaded in including the Monitor or Control logs to email to Garmin Product Support. Without knowing the order in which the logs were downloaded, Garmin will be unable to process them and will ask for another full download. 10. Press the LG2CRD softkey to turn off the recording function. 11. Wait one minute for the system to save the data to the SD card. 12. While you are waiting for the data to be saved to the SD card, record the order of the LRU’s and/or Servos were downloaded so that you can provide that information to Cirrus or Garmin to help decipher the order of the error data. 13. Power down the system and remove the SD card. 14. Insert the SD card in the card reader of a laptop or desktop computer and open the “diag_buf_log.txt” file from the SD card using the WordPad program. Make sure all of the fault logs were downloaded by checking for the “End of Fault Log” message at the end of the GIA data. Also make sure the last servo log entry has the current date. 15. Insert the fault log as an attachment to an email and include the LRU order (how the data was downloaded) and send to Garmin Aviation Product Support at avionics@Garmin.com. Cirrus Perspective™ Line Maintenance Manual Page 5-101 190-00920-00 Rev. E...
Page 148: Troubleshooting The S-Tec 55X Interface
____________________________________________________________________ 5.17 Troubleshooting the S‐TEC 55x Interface 5.17.1 Interface Summary • Autopilot computer is interfaced to GIA2 only • Utilizes S‐TEC pitch servo and Cirrus pitch trim motor for vertical control • Utilizes Cirrus roll trim motor only for lateral control • Utilizes S‐TEC turn coordinator and S‐TEC altitude hold chamber • Mode annunciation and FD are displayed on the PFD in normal mode and on the MFD if the Perspective system is in reversionary mode • Eaton switches on LH side of instrument panel annunciate “AP ON” (bottom half of switch) and “AP OFF/FD ON” (top half of switch) • GPS steering utilizes an ARINC 429 buss between GIA2 and the 55x • Altitude preselect data utilizes an RS 485 buss between GIA2 and the 55x • Analog outputs from GIA2 drive the GS deviation, GS flag, Nav deviation, Nav flag to the 55x • Pitch and Roll analog steering outputs from the 55x drive the FD bar inputs to GIA2 which in turn are displayed on the PFD • Clock, Sync and Data are used to transfer the mode annunciation information from the 55x to GIA2 which in turn is displayed on the PFD or MFD in reversionary mode • DC course and heading datum outputs from GIA2 drive the 55x associated inputs 5.17.2 Failure Modes • Loss of MFD or GIA2 o All mode annunciation removed from PFD ...
Page 149: Troubleshooting Interface Problems
____________________________________________________________________ 5.17.3 Troubleshooting Interface Problems Use the following screenshots to help verify proper configuration and signal integrity. In some cases, monitoring signals is not possible via configuration pages on the Perspective system. Symptom Check or Perform • Clock, sync and data lines between No modes annunciated on PFD GIA2 and 55x computer.* • Configuration**ClockSyncData • RS 485 connection between GIA2 Autopilot won’t capture selected altitude and 55x computer. * • Configuration**RS485 • Check analog deviation and flag Autopilot won’t follow CDI or VDI deflections outputs between GIA2 and 55x computer* • Configuration**AnalogOutputs • Check ARINC 429 GPS steering Autopilot won’t follow GPS track in GPSS mode input to 55x from GIA2 computer* • Configuration**GPSSteering •...
Page 150 ____________________________________________________________________ “RDY” annunciation on PFD during AHRS alignment: Normal display prior to AP or FD engagement: Page 5-104 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 151 ____________________________________________________________________ Autopilot engaged in HDG mode only: Autopilot driven failure annunciation: Cirrus Perspective™ Line Maintenance Manual Page 5-105 190-00920-00 Rev. E...
Page 152 ____________________________________________________________________ Autopilot engaged in heading and altitude hold modes: Autopilot engaged in heading and vertical speed modes. Note vertical speed selection from controller is displayed above VSI: Page 5-106 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 153 ____________________________________________________________________ Autopilot engaged in heading, vertical speed and altitude hold armed to capture at 1500 ft: Autopilot engaged in altitude hold and nav modes, tracking a GPS course: Cirrus Perspective™ Line Maintenance Manual Page 5-107 190-00920-00 Rev. E...
Page 154 ____________________________________________________________________ Autopilot has been disengaged but the flight director output from the S‐TEC computer can still be selected via the instrument panel EATON switch: Page 5-108 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 155 ____________________________________________________________________ Valid RS 485 path used for altitude select data: RS‐485 path status indicator showing missing data from the 55x computer. Note: this page may take >10 seconds to update: Cirrus Perspective™ Line Maintenance Manual Page 5-109 190-00920-00 Rev. E...
Page 156 ____________________________________________________________________ Clock, sync and data configuration set to “DME KN63 1”. Used for mode annunciation data from the 55x computer: Status unknown indication for the FD Valid is normal in configuration mode, so it isn’t useful from a troubleshooting standpoint: Page 5-110 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 157 ____________________________________________________________________ ANNUN*2 ILS/GPS APPCH output will toggle to “L” and “T” when in Localizer or Approach mode. Case shown above is in VOR or Enroute mode. ANNUN*4 GPS output is shown “L” and “T”, which enables the S‐TEC 55x ARINC 429 GPS steering: Shows the FD pitch and roll analog inputs turned on in GIA2. These signals come from the 55x computer. There is no signal monitoring capability from a configuration page: Cirrus Perspective™ Line Maintenance Manual Page 5-111 190-00920-00 Rev. E...
Page 158 ____________________________________________________________________ Shows the analog outputs from GIA2 to the 55x that are required to be turned on: Normal data shown for the 55x computer: Page 5-112 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 159 ____________________________________________________________________ Failed 55x computer condition shown: Cirrus Perspective™ Line Maintenance Manual Page 5-113 190-00920-00 Rev. E...
Page 160: Backshell Connectors
____________________________________________________________________ 5.18 BACKSHELL CONNECTORS The following figures show the backshell connectors (viewed with the LRU removed). COM ANTENNA CONNECTOR COOLING PORT COM BOARD CONNECTOR (P601) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 2223 24 25 26 2728 2930 31 32 3334 35 3637 3839 40 41 42 43 44 MAIN DISCRETE CONNECTOR (P604) MAIN SERIAL CONNECTOR (P603)
Page 161 ____________________________________________________________________ P702 P701 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 ...
Page 162 ____________________________________________________________________ Figure 5‐30. GDU 1240A Backshell Connector (P10001) Figure 5‐31. GRS 77 Backshell Connector (P771) Figure 5‐32. GDC 74A Backshell Connector (P741) Figure 5‐33. GDL 69A Backshell Connector (P691) Page 5-116 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 163 ____________________________________________________________________ Figure 5‐34. GMC 705 Backshell Connector (P7101) Figure 5‐35. GCU 478 Backshell Connector (P4751) Figure 5‐36. GSA 80/81 Backshell Connector (P801) Figure 5‐37. GTA 82 Backshell Connector (P821) Figure 5‐38. GTX 32 Backshell Connector (P3271) Cirrus Perspective™ Line Maintenance Manual Page 5-117 190-00920-00 Rev. E...
Page 164 ____________________________________________________________________ Blank Page Page 5-118 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 165: Section 6-Lru Replacement Procedures
__________________________________________________________________________ SECTION 6 LRU REPLACEMENT PROCEDURES NOTE LRUs must be configured and tested after removal and replacement. Refer to Section 7. This section contains replacement procedures for a defective LRU. Replacement of an LRU is on condition of failure. 6.1 ACCESSING LRUs Refer to the installation and outline drawings in each LRU installation manual for detailed installation/removal information. Before removing any LRU, verify the LRU software part number and version against the software configuration listed in the Required Equipment List. To check an LRU software part number and/or version: 1. Start the system in configuration mode. 2. The System Status Page (Figure 6‐1) shows a list of LRUs in the LRU window. Activate the cursor and use the FMS knob to scroll through the list in the window and select the displayed LRUs. 3. The software part number and version is displayed in the DATA window. Compare this to the software configuration in the Required Equipment List. 4. If a faulty LRU is not reporting its software version and part number, check aircraft maintenance logs for the last software version that was loaded and verify against the the Required Equipment List. The Software Manifest Page can also be used to check part numbers and versions. Figure 6‐1. System Status Page (Configuration Mode) Cirrus Perspective™ Line Maintenance Manual Page 6-1 190-00920-00 Rev.
Page 166: Gdus
To install: 1. Inspect connector(s) for damaged pins. 2. Insert a 3/32” hex drive tool into the access hole and rotate the mechanism 90° counterclockwise to insure correct position prior to placing the unit in the rack. 3. Gently push unit into the rack to engage the connectors. 4. Insert a 3/32” hex drive tool into the access hole and rotate the mechanism clockwise until the unit is firmly seated in the rack, avoiding excessive tightening. 6.4 GIA 63W To remove: 1. Loosen the Phillips screw to unlock unit handle. 2. Pull the GIA lever up towards the top of the unit. This disengages the locking stud with the dogleg slot. To install: 1. Inspect connector(s) for damaged pins. 2. Gently push unit into the rack to engage the connectors. 3. Push the GIA lever down towards the bottom of the unit, avoiding the use of excessive force. 4. Lock the handle into the GIA body and tighten the Phillips screw. age 6-2 Garmin Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 167: Grs 77
__________________________________________________________________________ 6.5 GRS 77 To remove: 1. Disconnect Backshell connector from unit. 2. Loosen four screws holding the unit to the mounting rack (do not loosen mounting rack bolts). To install: 1. Inspect connector(s) for damaged pins. 2. Fasten unit to mounting rack. 3. Connect Backshell assembly to unit. 6.6 GMU 44 To remove: 1. Loosen three screws connecting the unit to the aircraft mounting plate. 2. Disconnect cable. To install: 1. Inspect connector for damaged pins. 2. Connect cable and properly secure connector in a stationary fashion. 3. Fasten unit to the aircraft mounting rack. 6.7 GDC 74A To remove: 1. Loosen two thumb screws that secure the unit to the mounting rack. 2. Disconnect Backshell assembly and pitot‐static plumbing from unit. 3. Remove all Teflon tape or sealing compound. Take care not to allow Teflon tape or sealing compound to fall inside unit. To install: ...
Page 168: Gtx 32/33
5. Lock the handle into the GTX 33(X) body and tighten the Phillips screw. 6.10 GDL 69A To remove: 1. Loosen the Phillips screw to unlock unit handle. 2. Pull the GDL lever up towards the top of the unit. This disengages the locking stud with the dogleg slot. To install: 1. Inspect connector(s) for damaged pins. 2. Gently push unit into the rack to engage the connectors. 3. Push the GDL lever down towards the bottom of the unit, avoiding the use of excessive force. 4. If lever fails to go down, adjust backplate while engaging unit. 5. Lock the handle into the GDL body and tighten the Phillips screw. 6.11 GSA 80/81 SERVO ACTUATOR The GSA 80/81 Servo Actuator, when mated with the GSM 85(A) Servo Gearbox, drives a single flight‐control axis of the airplane, or its associated trim. Once installed into the aircraft, the GSA 8X servo actuator may be easily removed for maintenance, without removing or de‐rigging the GSM 85(A) servo gearbox. Note that while the GSA 8X is removed, it is recommended to use the Servo Gearbox Protective Cover (P/N 145‐00807‐00) to cover the opening of the GSM 85(A). The protective cover is included with the GSM 85(A) unit, and is designed to prevent foreign objects from falling into the GSM 85(A). age 6-4 Garmin Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 169: Gta 82 Pitch Trim Adapter
__________________________________________________________________________ To remove: 1. Gain access to the desired servo(s). 2. Disconnect the servo harness connector. 3. Use a socket or open‐wrench to loosen and remove the servo attachment bolts. Remove the Pitch‐Trim servo bracket to access all the Pitch‐Trim servo attachment bolts. 4. Carefully remove the servo and place a protective cover on the output gear. 5. Place a protective cover over the GSM 85A servo mount. WARNING The servo motor and servo mount must fit flush together with no gaps before tightening the mounting bolts. Do not under any circumstances try to close the gap by tightening the mounting bolts or damage will occur to the servo mount requiring replacement. To install: 1.
Page 170: Gcu 478 Keypad
__________________________________________________________________________ 6.13 GCU 478 KEYPAD To remove: 1. Remove the setscrew securing the keypad with a 3/32 hex tool and carefully remove keypad. 2. While supporting the keypad disconnect the connector. 3. Remove the unit. To install: Connect the connector to the back of keypad. Gently place keypad into position. Secure with setscrew using a 3/32 hex tool. Do not over‐tighten. Load software, configure and test age 6-6 Garmin Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 171: Configuration Module
__________________________________________________________________________ 6.14 CONFIGURATION MODULE Figure 6‐2. Configuration Module To remove: 1. Remove two screws (item 8) from cover (item 7) and remove cover. 2. Unplug connector from configuration module (item 1). 3. Remove configuration module. To install: 1. Inspect connector for damaged pins. 2. Place configuration module (item 1) in position. 3. Insert connector into configuration module (item 1). 4. If the GRS configuration module is replaced, proceed to Section 6.6. 5. If the GDC configuration module is replaced, proceed to Section 6.5. 6. If master configuration module is replaced: 7. Turn the PFD on in configuration mode (press and hold the ENT key while powering the unit). 8. Go to the Configuration Upload Page in the System Page Group. 9. Press the UPDT CFG softkey. 10. If the PFD and master configuration module is replaced, proceed to Section 9. Cirrus Perspective™ Line Maintenance Manual Page 6-7 190-00920-00 Rev.
Page 172: Gea Backshell Thermocouple
Item # Description Qty. Needed Garmin Part Number 1 3” Thermocouple, K type 1 925‐L0000‐00 2 Pins #22 AWG 2 336‐00021‐00 3 Screw 1 211‐60234‐08 To remove: 1. Remove the GEA. 2. Remove the GEA connector backplate. 3. Remove connector J701, item 5, from the backplate. 4. Remove cover, item 6, from the backplate. 5. Unscrew thermocouple from boss on Backshell. Extract the thermocouple pins from the connector. age 6-8 Garmin Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 173 __________________________________________________________________________ To install: 1. Crimp pins, item 2, onto each of the thermocouples wires, item 1. Ensure that pre‐ stripped wire length is 1/8" prior to crimping. 2. Insert newly crimped pins and wires into the appropriate connector housing location, item 6. 3. Place thermocouple body, item 1, onto the Backshell boss, item 5. Place the thermocouple as shown, so the wires exit towards the bottom of the Backshell. 4. Fasten thermocouple tightly to Backshell using the provided screw, item 6. 5. Fasten cover, item 6, to Backshell using the provided screw, item 7. ...
Page 174 __________________________________________________________________________ Blank Page age 6-10 Garmin Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 175: Section 7-Lru Software Installation And Testing
LRU SOFTWARE INSTALLATION AND TESTING This section describes how to upload software and configuration files to a replacement LRU. Section 10 explains how to completely reinstall system software anytime after the original upload (which took place at the time of installation; refer to the installation manual for detailed information). Perform the following steps before starting a software upload: Remove supplemental database cards from the lower slot of all displays before loading • software into any unit. Not removing the cards may corrupt them. Replacing corrupted database cards are not covered under warranty. Approved software versions and part numbers can be found in Cirrus documentation. Garmin recommends the use of SanDisk brand SD cards to load system software and • configuration files. If another brand of card is used, and software loading problems occur, replace the card with a SanDisk brand card and reattempt the software load. Connect a ground power unit to the aircraft for software loading. Do not rely on only the • aircraft batteries to prevent loss of power during the software loading process. Do not allow power to be removed from the system when loading software. Remove power only when told to do so by the procedure. Generally, all displays should be on and in configuration mode, unless instructed differently. NOTE Pressing the ENT key will check and uncheck the highlighted software or configuration box and allow selective loading of files on the PFD SYSTEM ...
Page 176: Gdu 1240A
__________________________________________________________________ 7.1 GDU 1240A Original Display Reinstalled If the removed display(s) are reinstalled in their original positions, no software or configuration loading is required. This does not include units that were returned for repair, since their software and configuration files were deleted during the repair testing process. Original Displays Installed in Opposite Locations for Troubleshooting If the PFD and MFD are installed in opposite locations, no software or configuration loading is required. Some button/knob functions may not work correctly until the displays are reinstalled in their original location. Return the displays to their original location after troubleshooting. New, Repaired, or Exchange Display(s) Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchange GDU is installed. See Section 10 for aviation database update instructions. Retain the Supplemental Database and other SD cards from the original display to reinstall in the new display after loading software. 7.1.1 GDU Software Loading 1. Remove the supplemental database card from the bottom slot of each GDU and the Cirrus data card from the top slot of the MFD. 2. Insert the Cirrus airframe specific System Software Loader Card into top slot of the new GDU. 3. Power on the display in Configuration mode. 4. Press the YES softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 5. Press any key to confirm update completion after the software has finished loading. 6. Press the YES softkey at the “DO YOU WANT TO UPDATE SPLASHSCREEN” prompt. 7. Press any key to confirm update completion after the splashscreen has finished loading. 8. Power off the display. If a PFD was installed in the MFD position to load software per the NOTE above, remove the display and install in the PFD position then reinstall the original MFD. 9. Proceed to Section 7.1.2 to install the configuration files for the new display. ...
Page 177 __________________________________________________________________ 5. Activate the cursor, turn the small FMS knob to show the list of Airframe choices, highlight your airframe model in the pop‐up box and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of File choices, highlight the appropriate airframe configuration file in the pop‐up box and press the ENT key. Load the following configuration files: • For a PFD replacement: i. Press the CLR ALL softkey at the bottom of the display. ii. Use the FMS knob and ENT key to select the AIRFRAME, SYSTEM, MANIFEST and PFD Configuration box. iii. Press the LOAD softkey. iv. When the upload is complete, press the ENT key to select OK in the Upload Complete window. • For a MFD replacement: i. Press the CLR ALL softkey at the bottom of the display. ii. Use the FMS knob and ENT key to select the MFD Configuration box. iii. Press the LOAD softkey. iv. When the upload is complete, press the ENT key to select OK in the Upload Complete window. NOTE Pressing the ENT key will check and uncheck the highlighted software and configuration boxes. 7. Once the files are selected press the LOAD softkey. 8. When the upload is complete, press the ENT key to select OK in the Upload Complete window. 9. Move the curser to the AIRFRAME window, turn the small FMS knob to show the list of Airframe choices, highlight “Options” in the pop‐up box and press the ENT key. ...
Page 178 __________________________________________________________________ vi. GDL 69/69A Installation Option vii. GFC 700 (without YD) Installation Option viii. GFC 700 (with YD) Installation Option ix. GTX 32 Installation Option x. GTX 33 Installation Option xi. GTX 33 Installation Option xii. KN63 DME Installation Option xiii. KN87 ADF Installation Option xiv. No‐Hazard IPS Installation Option xv. SR22/TN DIN IEC 751 Oil Temp Sensor Configuration xvi. SR22/TN MS28043 Oil Temp Sensor Configuration xvii. Oxygen Installation Option xviii. Skywatch 497 Installation Option xix. S‐TEC 55X/55SR Installation Option xx. WX‐500 Stormscope Installation Option • For a MFD replacement: i. GFC700 w/YD ‐ MFD Configuration file ii. GFC700 w/o YD ‐ MFD Configuration file 11. Move the curser to the AIRFRAME window, turn the small FMS knob to show the list of Airframe choices, highlight “AHRS ADC Options” in the pop‐up box and press the ENT key. ...
Page 179 __________________________________________________________________ iv. When the upload is complete, press the ENT key to select OK in the Upload Complete window. 13. Turn off the system. 14. For a PFD replacement, or whenever the AIRFRAME file is loaded from the main aircraft configuration file, you must unlock additional features such as SVT, Jeppesen ChartView and TAWS by using the unlock cards that should be with the aircraft. Follow these instructions for unlocking these optional features – • Insert the unlock card in the top slot of the PFD. • Turn on the system in Config mode. • After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. • Activate the cursor, turn the small FMS knob to show the list of Airframe choices, highlight ‘Configuration Files’ in the pop‐up box and press the ENT key. • In the FILE box, turn the small FMS knob to show the list of File choices, highlight ‘Enable X (SVS, TAWS, or Chartview)’ in the pop‐up box and press the ENT key. • Press the LOAD softkey. • When the upload is complete, press the ENT key to select OK in the Upload Complete window. • Turn off the system. • Repeat for additional unlock cards. 15. Turn off the system. 16. Restart the system in normal mode and allow to initialize. This sets the System ID and is needed before inserting the Supplemental Database cards. 17. Turn off the system. 18.
Page 180 __________________________________________________________________ 20. Press the ENT key to confirm the database update. The following prompt is displayed: 21. After the update completes, the display starts in normal mode. Turn off the display and remove the aviation database update SD Card. 22. Reinsert the Supplemental Database Cards in the bottom slot of each display. Be sure to insert the card removed from the MFD back into the MFD. Page 7-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 181: Gdu Testing
__________________________________________________________________ 7.1.3 GDU Testing If the display is removed or replaced, the following checks are recommended. Start PFD and MFD in normal mode. Press the ENT key to acknowledge the agreement on the MFD. Allow the displays to initialize for approximately one minute. The GRS 77 and GDC 74A require longer initialization periods than do the other LRUs. During startup, this causes the attitude, airspeed, and altitude fields to be invalid during the first ~40‐60 seconds of PFD power‐up. Check the PFD and MFD displays for the following: 1. Check in the top corners of the PFD and MFD to see that all COM/NAV display fields are valid. 2. Check to see that altitude, airspeed, vertical speed and OAT fields are valid on the PFD. 3. Check to see that attitude and heading are valid (unless an AHRS calibration is required). 4. Check to see that the engine instrument fields are valid on the MFD. 5. Push the red display reversion button on the instrument panel. Make sure both displays enter reversionary mode (both should have valid altitude, airspeed, vertical speed, and engine instruments). 6. De‐activate reversionary mode by pushing the red reversion button. NOTE Make sure the Jeppesen aviation database is present and that optional equipment and features such as SVT, Jeppesen ChartView, and TAWS are operational. ...
Page 182: Gma 347
__________________________________________________________________ GMA 347 Original GMA 347 Reinstalled No software or configuration loading is required if the original GMA 347 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchange GMA 347 Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchange GMA 347 is installed. 7.2.1 GMA Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into the top slot of the PFD. 2. Apply system power. Make sure the MFD and PFD are in Configuration Mode. Press the NO softkey at the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt on the PFD. 3. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 4. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight the airframe model in the pop‐up box, and press the ENT key. 5. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the appropriate airframe configuration file in the pop‐up box, and press the ENT key. 6. Press the CLR ALL softkey. 7. Using the FMS knob and ENT key select the following files: GMA software • GMA configuration • NOTE Pressing the ENT key will check and uncheck the highlighted software and configuration boxes. 8. Once the desired files are selected, press the LOAD softkey. 9. When the upload is complete, press the ENT key to select OK in the Upload Complete window. Move the cursor to the AIRFRAME window, turn the small FMS knob to show the list of Airframe choices, highlight “Options” in the pop‐up box, and press the ENT ...
Page 183: Gma Testing
__________________________________________________________________ 7.2.2 GMA Testing An in‐aircraft checkout may be performed in the aircraft on the ramp with known good microphone, headset, and speaker. 7.2.2.1 Intercom System (ICS) and Music Input Check 1. Plug in headsets at each ICS position. 2. Make sure the MAN SQ key is off (no LED). If the LED is on, toggle it off by pressing and holding the pilot side volume knob until the LED turns off. 3. Adjust the volume for each position and confirm that the ICS is working properly. Rear passenger volume is controlled by pulling the co‐pilot volume knob to the outer detent position. 4. Check Pilot and Copilot ICS positions for isolation and proper operation of volume and squelch controls. 5. Input Music 1 and Music 2 inputs and check for proper operation at all headphone locations. 7.2.2.2 Transceiver Operational Check Perform a ramp test radio check by operating the installed transceivers, microphone, microphone key and audio over the headphones and speaker. Verify that communications are clear and PTT operation is correct for each pilot position. 1. Select the audio source corresponding to each installed avionics unit (i.e. NAV1, NAV2, COM1, COM2) and check for audio over the headsets. 2. Press the SPKR key and verify that the selected audio is heard over the speaker. 7.2.2.3 Failsafe Operation Check 1. Turn the GMA 347 off by pulling the AUDIO circuit breaker. This directs all COM 1 phone audio, MIC audio and MIC key to the pilot’s position. 2. Check the failsafe operation by operating the COM 1 microphone, microphone key and audio over the headphones. All volume control for the COM audio should be through the PFD/GCU478 volume controls. Verify proper operation of COM 1 using the failsafe operation. 3. Close the AUDIO circuit breaker and continue testing. ...
Page 184 __________________________________________________________________ 7.2.2.4 Marker Beacon Test Figure 7‐1. Marker Beacon Symbology Using a ramp tester, simulate the outer marker, middle marker and inner marker signals by following the test equipment manufacturer’s instructions. Verify that each marker audio signal is present over the headphones and speaker. Verify that the outer, middle, and inner annunciations appear on the PFD when the corresponding signal is applied. Marker beacon annunciations appear at the upper left corner of the altitude indicator on the PFD (Figure 7‐1). Operate the MKR MUTE key on the GMA 347 and confirm that the audio signal is muted. Page 7-10 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 185: Gia 63W
__________________________________________________________________ GIA 63W Original GIA 63W(s) Reinstalled No software or configuration loading is required if the GIA that was removed is reinstalled in its original position (GIA1 and GIA2 in their original racks). This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. Original GIA 63W(s) Installed in Opposite Locations for Troubleshooting Purposes No software loading is required if the original GIA units are installed in opposite locations (GIA1 and GIA2 in opposite unit racks). However, the units must be reconfigured in their new positions. Follow these instructions to reconfigure the units without using the Cirrus Perspective™ software loader card: 1. Apply system power, insuring both MFD and PFD are in Configuration Mode. 2. On the PFD, use the FMS knob to navigate to the GIA RS‐232/ARNIC 429 CONFIG page. 3. In the SELECT UNIT box in the upper left corner of the screen, verify GIA1 is listed. 4. Press the SET>ACTV softkey in the lower left corner of the screen. 5. When the “Activate parameter settings?” window appears, verify OK is highlighted and press the ENT key. 6. When the “GIA #1 Configured” window shows “Complete”, press the ENT key to select OK in the window. 7. Activate the cursor, turn the small FMS knob to show the list of GIA choices, highlight GIA2 in the pop‐up box and press the ENT key. 8. Press the SET>ACTV softkey in the lower left corner of the screen. 9. When the “Activate parameter settings?” window appears, verify OK is highlighted and press the ENT key. 10. When the “GIA #2 Configured” window shows “Complete”, press the ENT key to select OK in the window. 11. Turn off the system. Cirrus Perspective™ Line Maintenance Manual Page 7-11 190-00920-00 Rev.
Page 186: Gia Software And Configuration Loading
__________________________________________________________________ New, Repaired, or Exchange GIA 63W(s) Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GIA 63W is installed. 7.3.1 GIA Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into the top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight your airframe model in the pop‐up box and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the appropriate airframe configuration file in the pop‐up box and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files: 9. GIA (1 or 2) – SYS Software and Configuration files 10. GIA (1 or 2) – AUDIO Software file 11. GIA (1 or 2) – GPS Software file 12. AUDIO Configuration file 13. Once the files are selected, press the LOAD softkey. 14. When the upload is complete, press the ENT key to select OK in the Upload Complete window. 15. Proceed to Section 7.3.2 to install the Optional Equipment Configuration files. Page 7-12 Cirrus Perspective™...
Page 187: Gia Optional Equipment Configuration Loading
__________________________________________________________________ 7.3.2 GIA Optional Equipment Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight “Options” in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, and load any of the following files if the aircraft is equipped with the following optional equipment: For a GIA1 replacement: • i. Oxygen – GIA 1 Configuration file ii. Ice Protection (NH and FIKI) – GIA 1 Configuration file iii. GTX 33 – GIA 1 Configuration file iv. GTX 32 – GIA 1 Configuration file v. GFC700 w/YD – GIA 1 ‐ Gains Software and Configuration files vi. GFC700 w/o YD ‐ GIA 1 ‐ Gains Software and Configuration files For a GIA2 replacement: • i. WX‐500 ‐ GIA 2 Configuration file ii. Skywatch 497 – GIA 2 Configuration file iii. Oxygen – GIA 2 Configuration file iv.
Page 188 __________________________________________________________________ 7. Move the cursor to the AIRFRAME window, turn the small FMS knob to show the list of airframe choices, highlight “AHRS ADC Options” in the pop‐up box, and press the ENT key. 8. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the file that matches the number of AHRS and ADC units installed on the aircraft, and press the ENT key. For a GIA1 replacement: • i. Press the CLR ALL softkey at the bottom of the display. ii. Use the FMS knob and ENT key to select the GIA 1 configuration box. iii. Press the LOAD softkey. iv. When the upload is complete, press the ENT key to select OK in the ‘Upload Complete’ window. For a GIA2 replacement: • i. Press the CLR ALL softkey at the bottom of the display. ii. Using the FMS knob and ENT key, select the GIA 2 configuration box. iii. Press the LOAD softkey. iv. When the upload is complete, press the ENT key to select OK in the ‘Upload Complete’ window. 9. Turn the system off. Page 7-14 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 189: Gia Options Interface Testing
__________________________________________________________________ 7.3.3 GIA Options Interface Testing This section describes the checks that must be completed in order to verify that the optional systems interfaced to the Perspective™ System are operating correctly. The checks must be completed only for those systems that are installed. Following the interface verification additional system checks may be required (refer to the appropriate system installation manual for additional details). 7.3.4 Optional Stormscope Functional Test This procedure assumes familiarity with the setup and operation of the WX‐PA portable analyzer kit. NOTE The MFD should be set at 100 NM (or next highest available range) on the 360 degree weather screen and in strike mode. NOTE The WX‐500 will plot data at one‐half the range selected on the WX‐PA. Apply power to the WX‐500 and verify that no failed test messages appear. If fault messages do appear, refer to the WX‐500 Installation Manual for troubleshooting. Following successful power up, verify the following modes: • Access to both 360° and 120° weather view modes. • All available ranges can be displayed. • Access to the cell mode and strike mode. • Strike counter is displayed in all weather modes and ranges. 1. Key COM1 and COM2 several times on different frequencies representing the lower, mid, and upper portion of the VHF COM frequency band. Make sure the keying of COM1 or COM2 does not cause strike data to appear on the MFD. 2. Operate the DME and XPDR. Make sure these systems do not cause strike data to appear on the MFD. 3. Connect the WX‐PA cable to the WX‐PA antenna. 4. Position the WX‐PA antenna on the WX‐500 antenna. Make sure the connection is tight. If necessary, use tape to secure the WX‐PA antenna. Make sure the “FORWARD” arrows are ...
Page 190 __________________________________________________________________ 8. Set the WX‐500 to STRIKE mode, 100 NM range (or next highest available range). 9. Select the ‘Continuous Out’ mode from the WX‐PA menu then press MENU/ENTER. 10. Select the bottom mount antenna configuration on the WX‐PA keyboard (“A” key). 11. Select a cardinal bearing and a range of 120 NM. 12. Use the F1 and F2 keys to adjust range and F3 and F4 keys to adjust heading. Press MENU/ENTER to start the test. 13. Observe the MFD to ensure the proper positioning of the strikes, based on range and azimuth settings on the WX‐PA. Change the cardinal bearings and verify correct test strikes. Verify the strikes are within 10 degrees of the selected azimuth and plot at 60 NM (½ of 120 NM). 14. Verify after 20 seconds of operation that the strike counter reads 580 ± 40. 15. After testing for all indicated ranges and bearings, press second, then MENU/ENTER to return to the main menu. 16. Select Circular Pattern mode from the WX‐PA mode menu then press MENU/ENTER. 17. Select the bottom mount antenna configuration on the WX‐PA keyboard (“A” key). Use the F1 and F2 keys to select the 120 NM range and press MENU/ENTER to start the test. Make sure the WX‐500 plots discharge points at approximately 60 NM. 18. Observe the MFD to ensure the proper positioning of the test strikes. Verify the strikes are within 10 degrees of the 30 degree azimuth increment and within 12 NM of 60 NM. 19. When complete, set WX‐PA for 55 NM, set the MFD for 50 NM (or the next highest available range) and repeat the test. 20. On the MFD, verify the sensor plots points just outside of 25 NM and the strikes are within 10 degrees of the 30 degree azimuth and within 5 NM of 27.5 NM. 21. Repeat the above setting on the MFD for 25 NM (or the next highest available range) and the WX‐PA for 15 NM. 22.
Page 191: Optional Skywatch Functional Test
__________________________________________________________________ 7.3.5 Optional Skywatch Functional Test Figure 7‐2. Skywatch Display Follow the instructions in the L‐3 Communications Skywatch Installation Manual for using a terminal device to calibrate and configure the system. 1. Select the TRAFFIC MAP page on the MFD. 2. Verify that the STANDBY, OPERATE, TEST (only when in Standby mode) and ALT MODE soft keys are available on the bottom of the display. Verify that a TAS mode (not TAS FAIL) is displayed in the upper left corner of the traffic map. Make sure that NO DATA is not displayed in yellow in the center of the display over the aircraft symbol. 3. Verify that the system comes up in STANDBY, indicating proper squat switch interconnect. 4. Press the OPERATE softkey and verify that OPERATING is displayed in the upper left corner of the traffic map. 5. Press the STANDBY softkey and verify that STANDBY is displayed in the upper left corner of the traffic map. 6. Press the TEST soft key and verify that TEST is displayed in the upper left corner of the traffic map and a traffic test pattern is displayed. Upon completion of the test, verify that “SKYWATCH SYSTEM TEST PASSED” is heard over the cockpit speaker. 7. Open the TRAFFIC circuit breaker on the avionics circuit breaker panel. On the MFD, make sure that NO DATA is displayed in yellow after several seconds. 8. Close the TRAFFIC circuit breaker on the avionics circuit breaker panel and verify that NO DATA is removed after several seconds. Cirrus Perspective™ Line Maintenance Manual Page 7-17 190-00920-00 Rev.
Page 192 __________________________________________________________________ 9. Setup a traffic simulation on a ramp generator with TAS functionality. 10. Using the ramp generator, simulate a TA and verify the proper target display and associated “Traffic, Traffic” audio alert. 11. Provide a valid GPS signal and verify TAS (True Airspeed) is valid. Connect a pitot/static test set and increase the pitot pressure to >30 knots. 12. Regenerate a simulated TA and make sure the proper target is displayed with no audio alert. Page 7-18 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 193: Optional Dme Function Test
__________________________________________________________________ 7.3.6 Optional DME Function Test This check verifies that the DME‐to‐Garmin interface operates correctly. This check is only required for SR20/SR22/SR22T aircraft with the Honeywell remote mounted KN63 DME installed. Figure 7‐3. DME Display 1. On the PFD, check to see if the DME window is displayed. If not, press the PFD softkey, then press the DME softkey to display the DME window (located next to the HSI). 2. Press the ADF/DME softkey. Verify that the ADF/DME TUNING screen is displayed. 3. With the ADF/DME TUNING screen displayed, use the large FMS knob and highlight the DME field. Verify that the NAV1, NAV2 and HOLD modes can be selected by turning the small FMS knob. 4. Verify that NAV1 and NAV2 frequencies are set to 108.00 and 117.00 MHz. 5. Select the DME NAV1 mode by pressing the ENT softkey. Verify that the DME window display is set to the NAV1 frequency of 108.00 MHz. 6. Select the DME NAV2 mode by pressing the ENT softkey. Verify that the DME window display is set to the NAV2 frequency of 117.00 MHz. 7. Select the DME HOLD mode by pressing the ENT softkey. Verify that the last selected NAV frequency of 117.00 MHz remains the same when the NAV2 frequency is changed. 8. On the NAV Test Set, set up a DME test and note the NAV frequency. Tune NAV 1 to the test set frequency and set the DME MODE to NAV1. Ensure that NAV 2 is set to a frequency other than the test set frequency. Cirrus Perspective™ Line Maintenance Manual Page 7-19 190-00920-00 Rev.
Page 194 __________________________________________________________________ 9. Verify that the DME distance on the PFD matches the test set. 10. Press the DME and SPKR buttons on the audio panel to select the DME audio and turn on the speaker. Verify that the DME audio can be heard over the speaker. 11. On the PFD, set the DME mode to NAV2 and verify that the DME distance is dashed out. 12. Tune NAV 2 to the test set frequency. 13. Verify that the DME distance on the PFD matches the test set. 7.3.7 Optional ADF Function Test This check verifies that the ADF‐to‐Garmin interface operates correctly. This check is only required for SR20/SR22/SR22T aircraft with KR‐87 ADF installed. window Tuning window Figure 7‐4. ADF Display 1. On the PFD, check to see if the ADF window(s) is displayed. If not, press the PFD softkey. Using the BRG1 or BRG2 softkey, toggle until the ADF bearing is shown. Press the BACK softkey. 2. Verify that the ADF window is not invalid (no red ‘X’). 3. Verify that the audio from the tuned station is heard on the pilots and copilot's headset. 4. Verify that the audio from the tuned station is heard over the cabin speaker. Page 7-20 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 195: Taws Functional Test
__________________________________________________________________ 7.3.8 TAWS Functional Test (if unlocked) Figure 7‐5. TAWS Display 1. Select the TAWS page from the MAP group on the MFD. 2. Verify that the title at the top of the page reads “MAP – TAWS‐B”. If TAWS has not been enabled, the title will read “MAP – TERRAIN PROXIMITY” or “MAP – TERRAIN”. 3. Press the MENU button and select “Test TAWS” from the pop‐up menu (Figure 7‐5). 4. After the TAWS test is completed, verify that “TAWS System Test OK” is heard over the cockpit speaker. 5. Press the MENU button again and select “Inhibit TAWS” from the pop‐up menu and press ENT. Verify “TAWS INHB “ is displayed in the lower right hand corner of the PFD. 6. Press the MENU button again and select “Enable TAWS” from the prop‐up menu and press ENT. Verify the “TAWS INHB” annunciation on the PFD is removed. 7. With a GPS position acquired, shield or disconnect the GPS antennas to remove the GPS signal. Verify “DR” shows on the MFD and the “TAWS N/A” annunciation shows on both the MFD and PFD. 8. Reconnect or remove the shield from the GPS antennas, verify the MFD indications and PFD annunciation are removed and verify that “TAWS Available” is heard over the cockpit speaker after about 10 seconds from the moment a 3D GPS solution is re‐ acquired. Cirrus Perspective™ Line Maintenance Manual Page 7-21 190-00920-00 Rev.
Page 196 __________________________________________________________________ 7.3.8.1 TAWS Aural Alerts Verification Perform the following check if the system is equipped with the TAWS option. 1. Place the PFD in configuration mode by holding down the ENTER or rightmost softkey while applying power. 2. Select the Audio Alert Configuration page. 3. Press the SPKR button on the GMA 347W audio panel to activate the cockpit speaker. Make sure the SPKR button is illuminated. 4. On the Audio Alert Configuration page, use the FMS knob to activate the cursor and scroll through the MSG FIELD audio alert menu. When the desired alert is selected, press the ENT key on the display. To play the alert, highlight the ‘PLAY?’ option and press the ENT key. Perform this action for each of the following audio messages, verifying that each can heard both in the pilot/co‐pilot headset and over the cockpit speaker: Five Hundred • Caution Obstacle (2x) • Caution Terrain (2x) • Don’t Sink • Obstacle Ahead (2x) • Obstacle Ahead, Pull‐Up (2x) • Obstacle Ahead (x2), Pull‐Up (2x) • Pull‐Up • Sink Rate • Terrain Ahead, Pull‐Up (2x) • Terrain Ahead (2x) •...
Page 197: Garmin Flite Chart Functional Test
__________________________________________________________________ 7.3.9 Garmin FliteChart® Functional Test NOTE This test is not required if Jeppesen ChartView is enabled. If ChartView is enabled, the Garmin FliteChart® database will not be shown on either the MFD startup screen or the AUX – System Status page as described below. 1. Select “AUX – System Status” page on the MFD, then select DBASE softkey. 2. Use the small FMS knob and scroll to CHART. 3. Verify “FliteCharts” is displayed in blue text adjacent to “CHART”. 4. Verify the FliteChart® database ‘REGION’, ‘CYCLE’ number, ‘EFFECTIVE’, ‘EXPIRES’, and ‘DISABLES’ dates of the subscription appear in blue text. 5. Use the GCU large FMS knob to select the Navigation Map Page then press the SHW ...
Page 198 __________________________________________________________________ 7.3.10 Jeppesen ChartView Database Location and Functional Test ChartView must be enabled using a ChartView Unlock Card as specified in 005‐xxxxx‐xx and a current ChartView database obtained from Jeppesen. Reference section “ChartView Configuration” for enabling procedures. NOTE Do not erase the Cirrus specific startup screen and airframe_info.xml files when loading or updating the ChartView data via the Jeppesen website. NOTE The required ChartView databases are subscription‐based and are to be procured by the aircraft owner directly from Jeppesen. 1. Apply power and select ‘AUX – System Status’ page. Make sure the ChartView database cycle number is displayed in blue text. 2. On the Navigation Map page, press the SHW CHRT softkey and verify airport chart is displayed and the following softkeys are displayed: CHRT OPT • CHRT •...
Page 199 __________________________________________________________________ 5. Press the GCU MENU key to display the PAGE MENU. Turn the GCU large FMS knob and scroll through the OPTIONS Menu to ‘Show Chart’. Press the GCU ENT key to display the chart and make sure that the airport diagram is displayed. 6. Press the GCU FMS knob to activate the cursor. Turn the GCU large FMS knob to select the Airport Identifier Box. 7. Turn the GCU small and large FMS knobs to enter the airport identifier for New Century Airport (KIXD) then press the GCU ENT key to complete the airport selection. 8. Press the APR softkey. Turn the GCU large FMS knob to select the Approach Box then turn the small FMS knob to show the approach chart selection choices. 9. Turn either GCU FMS knob to scroll through the available charts and select a chart for viewing by pressing the GCU ENT key. Make sure the appropriate ChartView chart is displayed. 7.3.11 SafeTaxi® Functional Test Figure 7‐6. SAFETAXI® Display The maximum map ranges for enhanced detail are configurable by the flight crew. When zoomed in close enough to show airport detail, the map reveals runways with numbers, taxiways with identifying letters/numbers and airport landmarks. The landmarks include ramps, buildings, control towers, and other prominent features. Map resolution is greater at lower ranges. When the aircraft location is within the screen boundary (including within SafeTaxi® ranges) an airplane symbol is shown on any of the navigation map views for enhanced position awareness. Any map page that displays the navigation view can also show the SafeTaxi® airport layout within the maximum configured range. The following is a list of pages where the SafeTaxi® feature can be seen: • Navigation Map Page • Inset Map • Weather Datalink Page • Airport Information Page • ...
Page 200: Gia Testing
__________________________________________________________________ • V OR Information Page • U ser Waypoint Information Page • T rip Planning Page • N earest Pages 1. Select the AUX System Status page and verify that current revision levels are displayed for the following: REGION • VERSION • CYCLE • EFFECTIVE • EXPIRES • 2. Select Navigation Map page. 3. Press MENU. With ‘Map Setup’ highlighted, press ENT. Turn the small GCU FMS knob to select the aviation group. Press the ENT key. 4. Turn the large FMS knob to scroll through the Aviation Group options and select ‘SAFETAXI’. 5. Turn the small FMS knob to display range distances. 6. Turn either FMS knob to select 5000 ft. as the distance for the maximum SafeTaxi® display range. Press the ENT key to complete the selection. 7. Using the range knob, select a range of 5000 ft. or less. Verify SafeTaxi® display represents the current aircraft location and the airport layout. ...
Page 201: Vor/Loc/Gs Test
__________________________________________________________________ 7. Repeat steps 5 and 6 and re‐transmit while monitoring GPS2 signal levels on the MFD. 8. Repeat steps 4 through 7 at the following frequencies: 121.175 MHz • 121.200 MHz • 131.250 MHz • 131.275 MHz • 131.300 MHz • 9. Repeat steps 4 through 8 for the COM2 transceiver (GIA2). 10. On the MFD, select the fourth AUX page. 11. Change the COM channel spacing from 25 kHz to 8.33 kHz in the Com Config field. 12. Go back to the third AUX page. 13. Select 121.185 MHz on the COM1 and COM2 transceivers. 14. Transmit for 35 seconds while monitoring GPS1 signal strength levels. 15. During the transmit period, verify that the GPS’DR’ or ‘LOI’ flags do not come into view on the PFD HSI and verify on the MFD that GPS 1 does not lose 3D navigation. 16. Repeat steps 14 and 15 and re‐transmit while monitoring GPS2 signal levels on the MFD. 17. Repeat steps 14 through 16 at each of the following frequencies: 121.190 MHz • 130.285 MHz • 131.290 MHz • 18.
Page 202: Vor Test
__________________________________________________________________ 7.3.15 VOR Test 1. Simulate a VOR signal on radial 360° on the ramp tester. Tune both NAV1 and NAV2 receivers to the ramp test frequency. 2. Set the HSI on the PFD to VOR1 by pressing the CDI softkey. Set the VOR1 CDI course to 360° using the CRS knob on the GCU478. 3. On the ramp tester, apply a 10° deviation signal in both right and left directions and verify full scale deflection of the VOR1 CDI in the corresponding directions. 4. On the ramp tester, set the signal deviations to one dot, then two dots deflection in both right and left directions. Verify proper response from the VOR1 CDI. 5. Set the HSI on the PFD to VOR2 by pressing the CDI softkey. Set the VOR2 CDI course to 360° using the CRS knob on the PFD. 6. On the ramp tester, apply a 10° deviation signal in both right and left directions and verify full scale deflection of the VOR2 CDI in the corresponding directions. 7. On the ramp tester, set the signal deviations to one dot, then two dots deflection in both right and left directions. Verify proper response from the VOR2 CDI. 7.3.16 Localizer/Glideslope Test 1. Simulate a localizer signal on the ramp tester. Tune both NAV1 and NAV2 receivers to the ramp test frequency. 2. Set the HSI on the PFD to LOC1 by pressing the CDI softkey. 3. On the ramp tester set the signal deviations to one dot, then two dots deflection in both right and left directions. Verify proper response from the LOC1 CDI. 4. With LOC1 CDI selected, exercise the Glideslope deviation indicator with up and down deviation indications and verify the Glideslope deviation indicator responds correctly to the ramp test signal deviations. 5. Set the HSI on the PFD to LOC2 by pressing the CDI softkey. 6. On the ramp tester set the signal deviations to one dot, then two dots deflection in both right and left directions. Verify proper response from the LOC2 CDI. ...
Page 203 __________________________________________________________________ 2. Set the HSI on the PFD to VOR1 by pressing the CDI softkey. Adjust the HSI course as necessary using the CRS knob so that the CDI is centered (should correspond to current aircraft heading). 3. Engage the Autopilot in altitude hold mode and press the NAV key on the GMC 705. 4. Apply a right signal deviation on the ramp tester. Verify the VOR1 CDI indicates a right deviation and that the Flight Director and aircraft controls follow the CDI to the right. 5. Apply a left signal deviation and verify the Flight Director and aircraft controls follow the CDI to the left. 6. Press the CDI softkey to select the VOR2 receiver. Verify that the green ‘NAV’ autopilot annunciation flashes yellow, then returns to default ‘ROL’ mode in green. 7. With the VOR2 source selected on the HSI, re‐engage NAV mode and repeat Steps 4 through 5. 8. Simulate a Localizer/Glideslope signal on the ramp tester. Tune this frequency on NAV1 and NAV2 receivers. Set the HSI to LOC1. 9. Adjust the ramp tester signals to center the course and Glideslope deviation indicators on the PFD. 10. Press the APR key on the MFD. Verify that the LOC and GS annunciations are green on the PFD. 11. Apply right/left and up/down localizer/Glideslope signals using the ramp tester. Verify that the Flight Director and flight controls respond appropriately. 12. Repeat Steps 9 through 11 for the NAV2 receiver (LOC2 CDI). Cirrus Perspective™ Line Maintenance Manual Page 7-29 190-00920-00 Rev.
Page 204: Grs 77/Gmu 44
__________________________________________________________________ 7.4 GRS 77/GMU 44 Original GRS 77 is Reinstalled No software loading is required if the original GRS 77 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchange GRS 77 is Installed Load software from the Cirrus Perspective™ software loader card if the GRS 77 was replaced with a new, repaired, or exchanged unit. New GRS 77 Configuration Module is Installed No software loading is required if the GRS 77 configuration module was replaced. However, the GRS77 Pitch/Roll Offset and GMU44 Magnetometer Calibration Procedures need to be performed. Original GMU 44 is Reinstalled No software loading is required if the original GMU 44 is reinstalled. New, Repaired, or Exchange GMU 44 is Installed Load software from the Cirrus Perspective™ software loader card if the GMU 44 was replaced with a new, repaired, or exchanged unit. 7.4.1 GRS Software Loading (a configuration file is not used in the GRS 77) 1. Insert the Cirrus Perspective™ software loader card into the top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor. 6. Turn the small FMS knob to show the list of Airframe choices. 7. Highlight “AHRS ADC Options” in the pop‐up box and press the ENT key. 8. In the FILE box, turn the small FMS knob to show the list of File choices. 9. Highlight the AHRS/ADC configuration file that matches the number of units in the system in the pop‐up box. ...
Page 205: Gmu Software Loading (A Config File Is Not Used In The Gmu)
__________________________________________________________________ 13. Once the desired files are selected, press the LOAD softkey. 14. When the upload is complete, press the ENT key to select OK in the Upload Complete window. 7.4.2 GMU Software Loading (a configuration file is not used in the GMU 44) 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor. 6. Turn the small FMS knob to display the list of airframe choices. 7. Highlight “AHRS ADC Options” in the pop‐up box and press the ENT key. 8. Turn the small FMS knob to display the list of file choices In the FILE box. 9. Highlight the AHRS/ADC configuration file that matches the number of units in the system in the pop‐up box. 10. Press the ENT key. 11. Press the CLR ALL softkey. 12. Using the FMS knob and ENT key select GMU (1 or 2) – Software file. NOTE Pressing the ENT key will check and uncheck the highlighted software box. 13. Once the desired files are selected, press the LOAD softkey. 14. When the upload is complete, press the ENT key to select OK in the Upload Complete window. ...
Page 206 __________________________________________________________________ 7.4.3 GRS 77/GMU 44 Alignment NOTE Cirrus Perspective™ system software allows valid outputs from the AHRS prior to completion of the AHRS and magnetometer calibration procedures, as long as the GRS 77 can definitively determine that the aircraft is not moving. This gives a technician the ability to perform functional tests during aircraft assembly that require valid AHRS outputs. Additionally, a “CALIBRATE AHRS/MAG” message is displayed on the PFD until a successful magnetic calibration has been completed. The following criteria is used by the AHRS to determine the aircraft is moving: 1. If valid GPS data is available and each component of 3D GPS velocity is less than 4 knots, the aircraft is considered “not moving” and attitude/heading will become valid. 2. If valid 3D GPS data is not available, but valid true airspeed is less than 30 knots, the aircraft is considered “not moving” and attitude/heading will become valid. 3. If both 3D GPS and true airspeed are unavailable, attitude/heading will not become valid. No configuration is required for the GRS 77, unless the mounting bolts that secure the mounting rack are loosened. If the mounting bolts are loosened a new post‐installation calibration is required. Any GMU 44 that is removed and/or replaced requires a magnetometer calibration. There are five calibration procedures available: • Pitch/Roll Offset (Procedure A1) •...
Page 207 __________________________________________________________________ Calibration Procedure Required Condition A1 B D Removed or replaced the GRS 77 without None Required loosening mounting rack bolts Continue to Test Section Replaced the GRS 77 and loosened mounting rack X X X bolts Replaced the GRS 77 Configuration Module X X X Replaced the GMU 44 X GMU 44 was temporarily removed and reinstalled in None Required the Continue to Test Section same location Table 7‐1. GRS 77/GMU 44 Calibration 7.4.3.1 Procedure A: GRS 77 Pitch/Roll Offset Calibration Figure 7‐7. GRS/GMU Calibration Page ...
Page 208 __________________________________________________________________ Figure 7‐8. GRS/GMU Calibration Page‐GRS77 #2 This procedure must be carried out with the engine off and the aircraft still. Avoid performing any other maintenance activity or entering/exiting the aircraft during this procedure. 1. Level the aircraft to 1.2° pitch nose up and wings level. 2. Initiate the AHRS Ground Pitch/Roll Aircraft Level compensation mode by performing the following steps: a) Enter Configuration Mode and go to GRS/GMU CALIBRATION page as shown in Figure 7‐8. b) This page is protected and requires a keystroke password to perform the calibration. Press the following softkeys in sequence: softkey 9 softkey 10 iii) softkey 11 iv) softkey 12 c) Ensure that the No. 1 GRS 77 is selected. d) Select PITCH/ROLL OFFSET, then press the ENT key. e) Follow the checklist items which are displayed and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. f) After several seconds, a new checklist appears in the lower half of the PFD. Press the ENT key as each item is confirmed. When the ‘CONFIRM AIRCRAFT IS LEVEL’ field is blinking, press the ENT key to continue. 3. The result of the pitch/roll offset compensation is displayed. If successful, the AHRS records the required pitch and roll offsets, informs the operator of a successful conclusion, and returns to normal operation. ...
Page 209 __________________________________________________________________ 7.4.3.2 Procedure B: GMU 44 Magnetometer Calibration Procedure The Magnetometer Calibration Procedure must be carried out at a site that is free of magnetic disturbances. A site evaluation for magnetic disturbances can be performed for the magnetometer calibration procedure if a compass rose is not available. The accuracy of the GRS 77 and GMU 44 cannot be guaranteed if this calibration is not performed in a magnetically clean area. NOTE Typically, a compass rose is an acceptable location to perform the magnetometer calibration procedure. However, because not all compass roses are well maintained, even an existing compass rose should be regularly evaluated using the method described here to determine if it is free of magnetic disturbances. If evaluation of an existing compass rose indicates that magnetic disturbances are present, then an alternative location must be found to perform the procedure. ...
Page 210 __________________________________________________________________ If, upon completion of the Magnetometer Calibration Procedure in either of the two directions, the PFD displays either the “MAG FIELD AT SITE NOT UNIFORM”, or “MAG FIELD AT SITE DIFFERS FROM IGRF MODEL” message, then the site contains magnetic disturbances that are too large. 1. Start the aircraft engine according to the procedures listed in the SR20/SR22/SR22T AFMS. 2. After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose or magnetically clean location determined previously. 3. At the compass rose, align the aircraft to a heading of magnetic north (±5°) with sufficient offset to the left (west) of the North/South axis to allow a clockwise turn around the compass rose to be performed. See figure below: 4. Restart the PFD and MFD in configuration mode. NOTE If needed, advise the control tower or ground control you may temporarily not be able to receive or transmit on your COM radios during this procedure. 5. On the PFD, go to the GRS/GMU CALIBRATION Page. Engine instruments may be monitored on this page during the procedure. Page 7-36 Cirrus Perspective™...
Page 211 __________________________________________________________________ Figure 7‐9. GRS/GMU Calibration Page 6. Press the following softkeys in order to unlock the page: 9, 10, 11,12. 7. On the PFD, verify GRS77 #1 is in the SELECT GRS UNIT window. 8. Move the cursor to the SELECT PROCEDURE window and use the FMS knob and ENT key to select MAGNETOMETER. If both GMU 44 units need to be calibrated at the same time, follow these steps: • Go to the GRS/GMU CALIBRATION page on the MFD. • Press the following softkeys in order to unlock the page: 9, 10, 11, 12. • Activate the cursor and select GRS77 #2 in the SELECT GRS UNIT window. • Move the cursor to the SELECT PROCEDURE window and use the FMS knob and ENT key to select MAGNETOMETER. • Perform the following steps on the PFD and MFD at the same time. 9. Use the large FMS knob to move the cursor to the first item in the BEFORE CALIBRATION window. 10. Follow the checklist items displayed on the PFD and press the ENT key as each one is completed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. If calibrating both GMU 44 units at the same time, be sure to complete the steps on both displays at the same time. The PFD advises the operator when to turn the aircraft, when to stop, and when to turn again. 11. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of turn from the last heading, the PFD advises the operator to stop the aircraft. Cirrus Perspective™ Line Maintenance Manual Page 7-37 190-00920-00 Rev.
Page 212 __________________________________________________________________ NOTE Due to the difficulties in executing smooth and accurate turns, the PFD may incorrectly interpret a station and instruct to “HOLD POSITION” prior to full completion of a 30° turn. If this scenario occurs, ignore the “HOLD POSITION” command and use outside references to complete the approximate 30° turn. Instead of using the PFD instruction to turn as a real‐time indication of when to turn, simply judge the 30° (±5°) turn increments of the aircraft by using the compass rose radials. Dwelling at these 30° increments for the time recommended by the PFD should result in ...
Page 213 __________________________________________________________________ 7.4.3.3 Procedure D: GRS77 Engine Run‐Up Vibration Test Calibration Procedures A1 and B are not required prior to performing this procedure. This procedure verifies the AHRS mounting is sufficiently rigid and insensitive to vibration. Figure 7‐10. Engine Run‐Up Test Display 1. Start the aircraft engine according to the procedures listed in the SR20/SR22/SR22T AFMS. NOTE If needed, advise the control tower or ground control you may temporarily not be able to receive or transmit on your COM radios during this procedure before restarting the system in config mode. 2. Restart the PFD and MFD in configuration mode. 3. Go to the GRS/GMU CALIBRATION Page on the PFD. Engine instruments may be monitored on this page during this procedure. 4. Press the following softkeys in order to unlock the page: 9, 10, 11,12. 5. Use the FMS knob and ENT key in the SELECT GRS UNIT window to select the GRS 77 you need to test. 6. Move the cursor to the SELECT PROCEDURE window and use the FMS knob and ENT key to select ENGINE RUN‐UP TEST. 7. Follow the checklist items and press the ENT key as each one is completed or confirmed. Cirrus Perspective™ Line Maintenance Manual Page 7-39 190-00920-00 Rev. E...
Page 214 __________________________________________________________________ 8. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over a period of 1‐2 minutes. 9. When the operator has completed the engine run‐up and the engine is back to an idle setting, press the ENT key. The TEST COMPLETE field stops blinking and the process is complete. 10. The PFD informs the operator if the installation has passed or failed the vibration test. If the test fails, the specific measurements causing the failure are identified and associated numeric values are displayed on the PFD. 11. The following are potential causes for failure of the engine run‐up test. Correct the condition and retest to confirm resolution. Vibration motion of GRS77 and/or GMU44 caused by neighboring equipment and/or • supports. The mounting screws and other hardware for GRS77 and/or GMU44 are not firmly • attached. The GRS77 connector is not firmly attached to the unit. • Cabling leading to GRS77 or GMU44 is not firmly secured to the supporting • structure. An engine/propeller may be significantly out of balance. • Page 7-40 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 215 __________________________________________________________________ 7.4.3.4 Procedure E: GMU 44 Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and/or verifying a magnetically ‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could affect the magnetic field as measured by the GMU 44 (examples include navigation/strobe lights, control servos, etc). It is generally not necessary to start the aircraft engine to run this test (in certain instances where it is suspected that the alternator or magnetos are causing magnetic interference, it may be appropriate to start the engine and turn the alternator on and then off during a portion of the test). Procedures A1, B, C and D are not required before performing this test. Figure 7‐11. Magnetometer Interference Test 1. Apply system power, insuring both MFD and PFD are in Configuration Mode. 2. Go to the GRS/GMU CALIBRATION page on the PFD. 3. Press the following softkeys in order to unlock the page: 9, 10, 11, 12. 4. In the SELECT GRS UNIT window, use the FMS knob and ENT key to select the GRS 77 you need to test. 5. Move the cursor to the SELECT PROCEDURE window and use the FMS knob and ENT key to select MAG INTERFERENCE TEST. 6. Follow the checklist items on the PFD, and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. 7. Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed or confirmed. Cirrus Perspective™ Line Maintenance Manual Page 7-41 190-00920-00 Rev.
Page 216 __________________________________________________________________ NOTE The third item on the checklist instructs the operator to “prepare a detailed test sequence with precise start and stop times for exercising all electronic devices”. Only the electronic devices that are likely to affect the operation of the GMU 44 magnetometer need be included in the test sequence. The list of relevant electronic devices varies from aircraft to aircraft. An example of an appropriate test sequence is given in Table 7‐3. Table 7‐3. Magnetometer Interference Test Sequence Elapsed Action Time Since Start of Test (min:secs) 0:00 Test begins 0:10 Aileron full right 0:20 Aileron full left 0:30 Aileron level 0:40 Flaps down 0:50 Flaps up 1:00 ...
Page 217 10. When the actions in the test sequence have been completed, press the ENTER button to indicate that the process is complete. When this is done, the TEST COMPLETE field stops blinking. 11. The PFD informs the operator if the installation has passed or failed the magnetometer interference test. If the test passes, no further action is required for this test. 12. If the test fails, the installation should be considered unreliable until the source of magnetic interference is identified and remedied. When the magnetometer interference test fails, record the three magnetometer maximum deviation values and their corresponding timestamps. Any maximum deviation value greater than 2.5 milliGauss indicates a problem that must be resolved. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem. NOTE Two common reasons for a failed magnetometer interference test are: new equipment is installed in close proximity to the GMU 44 magnetometer, and an existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair. 13. Press the ENT key on the PFD to conclude this procedure. Cirrus Perspective™ Line Maintenance Manual Page 7-43 190-00920-00...
Page 218: Grs Ahrs Testing
__________________________________________________________________ 7.4.4 GRS AHRS Testing Verify attitude and heading on the PFD in normal mode. The AHRS attitude and heading information displayed should become valid within 1 minute of power‐up, as shown in Figure 7‐ 13 provided both GPS receivers have a valid position. If GPS is unavailable, AHRS initialization may take as long as 2 minutes (the aircraft must remain stationary). Figure 7‐12. AHRS Information Valid Test the AHRS reversionary paths by pressing the red reversionary mode button on the audio panel located between the displays. Make sure both displays have valid AHRS information, as shown in Figure 7‐14. Figure 7‐13. Reversionary Mode AHRS Information Page 7-44 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 219 __________________________________________________________________ 7.4.4.1 Optional Second AHRS Test Press the ‘SENSOR’ softkey on the PFD then select AHRS2. Figure 7‐14. AHRS Information Valid Cirrus Perspective™ Line Maintenance Manual Page 7-45 190-00920-00 Rev. E...
Page 220: Gdc 74A
__________________________________________________________________ 7.5 GDC 74A Original GDC 74A is Reinstalled No software or configuration loading is required if the original GDC 74A is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchanged GDC 74A is Installed Load software from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GDC 74A is installed. New GDC 74A Configuration Module is Installed The GDC configuration files must be loaded if the GDC 74A configuration module has been replaced. NOTE Pitot/static covers must be removed in order to successfully execute the GDC 74A software and/or configuration loading. 7.5.1 GDC Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight “AHRS ADC Options” in the pop‐up box and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the AHRS/ADC configuration file that matches the number of units in the system in the pop‐ up box and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select GDC (1 or 2) – software and configuration files. NOTE ...
Page 221: Gdc Testing
__________________________________________________________________ 7.5.2 GDC Testing NOTE Allow unit to warm up for 15 minutes before performing the following tests. Verification of the altimeter and airspeed must be performed using a pitot/static ramp tester. The static port and altimeter must be verified in accordance with Title 14 of the Code of Federal Regulations (CFR) § 91.411 and Part 43, Appendix E. The MFD must be in reversionary mode to perform the tests outlined in Appendix E. 7.5.2.1 Preparing the Perspective™ System for Part 43 Appendix E Testing 1. Press and hold the ENT key on the PFD and apply system power. Allow the MFD to start in normal mode. 2. On the PFD, rotate the FMS knob to until the display shows the GRS page group. Within the AIR DATA 1 and AIR DATA 2 (in dual ADC installations only) sub windows is the field “B ALT” which is Barometric Altitude. B ALT is equivalent to the altitude that will be displayed to the pilot on the altitude display. B ALT will be used for all CFR Part 43 Appendix E tests for system altitude. 3. Push the red reversionary button located between the displays. This activates the reversionary mode for the MFD. Baro settings can now be read from the MFD for the CFR Part 43 Appendix E tests. 4. When viewing the baro setting for the second GDC in dual installations, press the ”SENSORS” softkey on the MFD and then select “ADC 2”. 5. After completing the tests specified by § 91.411 and Part 43 Appendix E, return the MFD back to normal mode by pushing the reversionary button. NOTE The following tests are beyond the requirements set forth in Appendix E. 7.5.2.2 Airspeed Test 1. Use an Air Data Test Set (ADTS) to simulate air speeds shown in the table below. Wait for the ADTS to report that target values have been achieved. 2. Verify that computed air speeds shown on the PFD are within the tolerances specified in the following table: Calibrated air speed, knots Allowed tolerance, ±knots ...
Page 222 __________________________________________________________________ 7.5.2.3 Static Port Vertical Speed (Rate of Climb) Test 1. Use the ADTS to change the altitude at the rates shown in the table below. 2. Wait for the ADTS to report that target rates have been achieved. 3. Verify that the rate of climb reported by the vertical speed field on the PFD is within the tolerances specified in the table below: Vertical Speed, Allowed tolerance, feet/minute ±feet/minute 2000 100 0 45 ‐2000 100 4. Press the “SENSOR” PFD softkey and then select ADC2 (if equipped). Repeat steps 1‐3. 7.5.2.4 OAT Probe Test Check the outside air temperature (OAT) measurement shown on the PFD to make sure it reads ambient temperature. 7.5.2.5 Second OAT Probe Test in Dual ADC Installations Select the ‘SENSORS’ softkey on the PFD then select ADC2 to view the second OAT ...
Page 223: Gea 71
__________________________________________________________________ 7.6 GEA 71 Original GEA 71 Reinstalled No software or configuration loading is required if the original GEA 71 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchanged GEA 71 Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GEA 71 is installed. NOTE Do not cancel a software upload that is in progress. A canceled software upload may result in an unresponsive GEA 71. 7.6.1 GEA Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into the top card slot of the PFD. 2. Apply system power, insuring the MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight your airframe model in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the appropriate airframe configuration file in the pop‐up box, and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files: GEA software • GEA configuration • NOTE Pressing the ENT key will check and uncheck the highlighted software and ...
Page 224: Gea Testing
__________________________________________________________________ 12. In the FILE box, turn the small FMS knob to show the list of File choices, you will need to load any of the following Files if the aircraft is equipped with the following optional equipment : a. Oxygen ‐ GEA Configuration file b. Ice Protection (NH and FIKI) – GEA Configuration file c. SR22 (only) Oil Temperature Sensors (2) – GEA Configuration file 13. Turn off the system. 7.6.2 GEA Testing The following tests are recommended if the unit is removed or replaced. 1. Each GEA 71 sensor input must be checked with the aircraft engine off. Make sure all engine information systems are valid on the MFD, and that no GEA 71 related alerts appear on the PFD. Exercise and test all discrete, analog, and/or digital inputs and check for appropriate responses. 2. With the STBY BATT CB pulled, check to see that the STBY BATT S current from the bottom right corner of the EIS strip on the MFD is indicating 0.0 amps. No other maintenance is required when the indication is 0.0. If the STBY BATT current is indicating anything other than 0.0 amps, perform the GEA 71 Standby Battery High‐Side Current Monitor Calibration procedure. Page 7-50 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 225: Gtx 32/33
__________________________________________________________________ 7.7 GTX 32/33 Original GTX 32/33 Reinstalled No software or configuration loading is required if the original GTX 32/33 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchanged GTX 32/33 is Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GTX 32/33 is installed. NOTE If the PFD shows that an upload has stopped before reaching 100%, the system will allow the installer to restart the upload procedure multiple times until a successful upload is accomplished. In some instances multiple software upload attempts may be required especially if a previous load was cancelled or corrupted by power loss. 7.7.1 GTX32/33 Software and Configuration Loading 1.
Page 226: Gtx 32/33 Testing
__________________________________________________________________ 7.7.2 GTX 32/33 Testing The following tests are recommended if the unit is removed or replaced. 1. The integrated transponder/altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations (CFR) §§ 91.411 and 91.413. 2. For the GTX 33 transponder, make sure the aircraft registration number is properly entered in the PFD TRANSPONDER CONFIGURATION page. 3. The GTX 33 test requires the use of a Mode S Ramp Generator. The GTX 32 requires a Mode A/C Ramp Generator. Refer to Title 14 CFR Part 43 Appendix F for specific testing criteria. Page 7-52 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 227: Gdl 69A
__________________________________________________________________ 7.8 GDL 69A Original GDL 69A Reinstalled No software or configuration loading is required if the original GDL 69A is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchange GDL 69A is Installed Load software and configuration files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GDL 69A is installed. NOTE See the GDL 69A XM Satellite Radio Activation Instructions, Garmin document part number 190‐00355‐04, for instructions on activating the GDL 69A. 7.8.1 GDL 69A Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight “Options” in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, you will need to highlight GDL 69/69A in the pop‐up box and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files: GDL 69A software • GDL 69A configuration • NOTE ...
Page 228: Gdl 69/69A Testing
XM data link radio. If the XM Radio is activated, the channel list will contain more channels than the three that are shown for a radio that has not been activated. Complete instructions for activating the XM data link are in Garmin document part number 190‐00355‐04. 1. Select the AUX – XM INFORMATION page on the MFD as shown below. The graphic shown below is for the AUX – XM INFORMATION page only. ...
Page 229: Gcu 478
__________________________________________________________________ 7.9 GCU 478 Original GCU 478 Reinstalled No software loading is required if the original GCU 478 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchanged GCU 478 Installed Load software and gains files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GCU 478 is installed. 7.9.1 GCU Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight your airframe model in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the appropriate airframe configuration file in the pop‐up box, and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files: GCU software • GCU configuration • NOTE Pressing the ENT key will check and uncheck the highlighted software and configuration boxes. 9. Once the desired files are selected press the LOAD softkey. 10.
Page 230: Gcu Testing
__________________________________________________________________ 7.9.2 GCU Testing Check for the proper operation of knobs and buttons. 7.10 GMC 705 Original GMC 705 Reinstalled No software loading is required if the original GMC 705 is reinstalled. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchange GMC 705 Installed Load software and gains files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GMC 705 is installed. 7.10.1 GMC Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight “Options” in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the GFC 700 (with or without YD) configuration file that matches the aircraft autopilot system in the pop‐up box and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files: GMC 705 software • GMC 705 configuration • NOTE Pressing the ENT key will check and uncheck the highlighted software and configuration boxes. ...
Page 231: Gsa/Gta Software And Configuration Loading
__________________________________________________________________ 7.11 GSA 80/81 Autopilot Servos and GTA82 Pitch Trim Adapter Original GSA80/81 Servo(s) or GTA82 Reinstalled No software loading is required if the removed servo(s) are re‐installed in the same position. This does not include units that were returned for repair since their software and configuration files were deleted during the repair testing process. New, Repaired, or Exchanged GSA80/81 Servo(s) or GTA82 Installed Load software and gains files from the Cirrus Perspective™ software loader card if a new, repaired, or exchanged GSA 81 servo is installed; 7.11.1 GSA/GTA Software and Configuration Loading 1. Insert the Cirrus Perspective™ software loader card into top slot of the PFD. 2. Apply system power, insuring both MFD and PFD are in Configuration Mode. 3. On the PFD, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt. 4. After the SYSTEM STATUS page appears on the PFD, use the small FMS knob to turn to the SYSTEM UPLOAD page. 5. Activate the cursor, turn the small FMS knob to show the list of airframe choices, highlight “Options” in the pop‐up box, and press the ENT key. 6. In the FILE box, turn the small FMS knob to show the list of file choices, highlight the GFC 700 (with or without YD) configuration file that matches the aircraft autopilot system in the pop‐up box and press the ENT key. 7. Press the CLR ALL softkey. 8. Using the FMS knob and ENT key select the following files for the servo axis or GTA that was replaced: Pitch/Pitch Trim/Roll/Yaw software • Pitch/Pitch Trim/Roll/Yaw gains • NOTE Pressing the ENT key will check and uncheck the highlighted software and configuration boxes. ...
Page 232: Gfc 700 Autopilot Testing
__________________________________________________________________ 7.11.2 GFC 700 Autopilot Testing The following procedure verifies the proper operation of the GFC 700 AFCS. The technician performing these checks must be thoroughly familiar with how to operate the GFC 700 system. Refer to the Garmin Perspective™ System Cockpit Reference Guide for detailed operating information. 7.11.2.1 Pre‐Flight Test Figure 7‐16. Pre‐Flight Test 1. Turn on the system. 2. A red AFCS annunciation ( ) is displayed in the upper left side of the PFD until the attitude comes up. 3. Verify that a white ‘PFT’ annunciation is displayed on the PFD after the attitude comes up, as shown in Figure 7‐16. NOTE There is a failure in the autopilot system preventing the preflight test from starting if the AFCS annunciation remains on the PFD after the attitude comes up and never switches to a white PFT annunciation. 4. An aural alert will sound and the annunciation will clear if the test is successful. NOTE ...
Page 233 __________________________________________________________________ 6. If the aural alert is not heard, but pre‐flight testing passes, engage the Autopilot by pressing the AP key and disengage the Autopilot by pressing the AP key again. Visual and aural disconnect alerting should occur. If no alert is heard, the digital audio interface between the GIA and audio panel should be checked. 7.11.2.2 AFCS Switch Checks Perform the following checks to verify that the AFCS system buttons and switches are operating correctly. 1. Actuate the Manual Electric Pitch Trim (MEPT) switch located on the pilot control stick. The stick should drive in the requested direction. Check operation in both directions. 2. Repeat step 1 using the co‐pilot MEPT. 3. Press and hold the AP DISC button while actuating the MEPT switch. Trim should not run. Release the AP DISC button. 4. Engage the Autopilot by pressing the ‘AP’ key on the GMC 705. Pull the AUTOPILOT circuit breaker. The Autopilot should disengage, with abnormal disconnect alerting consisting of a continuous disconnect tone and a flashing red/white ‘AP’ annunciation. No AFCS annunciations (e.g. AFCS, PFT, and Mistrim) should remain on the PFD. Press the A/P DISC switch to cancel the abnormal alert. Reset the AUTOPILOT breaker and watch the pre‐flight test sequence again. 5. Press the GA button on the throttle lever. ‘GA’ should be annunciated on the PFD for both pitch and roll modes, and the command bars should indicate a wings‐level climb to 7 degrees. 6. Disengage the Autopilot by pressing the AP DISC switch. Engage VS mode by pressing the VS key on the GMC 705. Verify the PFD display ‘VS’ in green and indicates a pitch reference of ‘0 FPM’. 7. Press the IAS key on the FMC 705 and verify that ‘IAS’ is annunciated on the PFD in green with a reference of 80 KTS (NOTE: This is the minimum speed reference for the GFC 700). 8. Press the ALT key on the FMC 705 and verify that the ‘ALT’ annunciation is displayed in green on the PFD with an altitude reference equal to the aircraft altitude (within the nearest 20 feet). 9.
Page 234 __________________________________________________________________ 7.11.2.3 Autopilot Clutch Overpower Check NOTE The GFC 700 uses electronic torque limiting and mechanical slip clutches to limit the maximum servo effort. When the system is on the ground, the electronic torque limiting is removed, allowing manual checks of the slip‐ clutch settings. ...
Page 235 __________________________________________________________________ 11. Press the AP DISC switch to disconnect the Autopilot, then re‐engage by pressing the AP and YD keys (on YD equipped aircraft). 12. Externally push the tail of the aircraft to the left and observe the rudder deflection. Rudder movement should also be to the left. 13. Externally push the tail of the aircraft to the right and observe the rudder deflection. Rudder movement should also be to the right. ...
Page 236 __________________________________________________________________ Blank Page Page 7-62 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 237: Section 8-Return To Service Testing
__________________________________________________________________ SECTION 8 RETURN TO SERVICE TESTING The tests described in this section test various secondary communications paths to ensure that the desired backup paths are in place. Before starting, create a simple direct‐to flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position. Make sure the phase of flight displayed on the GPS CDI is ENR. 8.1 GPS TESTING 8.1.1 Single GPS Test Procedure 1. Place a shroud over the GIA1 GPS antenna to prevent signal reception. Verify the loss of signal on MFD AUX page. Remove the shroud. 2. Place a shroud over the GIA2 GPS antenna to prevent signal reception. Verify the loss of signal on MFD AUX page 3. Remove the shroud. 3. The following shall remain valid on the PFD: Attitude and Heading from AHRS. • Airspeed, Altitude, Vertical Speed, and OAT from Air Data Computer. • GPS Course Deviation Indicator remains valid on PFD. • Press the ALERTS softkey and verify that the ‘AHRS1 GPS – AHRS using backup • GPS source' alert is given. (GPS1 failure only). 8.1.2 Dual GPS Test Procedure 1. Cover both GPS antennas. Verify the loss of signal on MFD AUX page 3. Check for desired results. 2. Remove shrouds. Allow both receivers to re‐acquire satellite signals before continuing. 3. The following shall occur for a dual GPS: GPS CDI is removed. •...
Page 238: Gia Testing
__________________________________________________________________ After ~10 seconds of stable GPS position reacquisition, verify the TAWS • AVAILABLE aural alert is given. Verify that the system returns to normal navigation mode (GPS CDI restored, DR • annunciation removed, & GPS data magenta). 8.2 GIA TESTING 8.2.1 Single GIA Test Procedure 1. Remove power from GIA1 by pulling the NAV/GPS1 and COM1 breakers. Check for desired results. 2. Restore power to GIA1. Allow GPS1 to re‐acquire satellites. 3. Remove power from GIA2 by pulling the NAV/GPS2 and COM2 breakers. Check for desired results. 4. Restore power to GIA2. Allow GPS2 to re‐acquire satellites. 5. For a GIA1 failure, only the following shall flag invalid: COM1/NAV1 field (PFD & MFD). • NAV1 CDI loses deviation bar (PFD only). • ‘AHRS1 using backup GPS’ alert given. • 6. For a GIA2 failure, only the following shall flag invalid: COM2/NAV 2 field (PFD & MFD). • NAV2 CDI loses deviation bar (PFD only). • ‘AHRS not receiving backup GPS information’ alert is given. • ADF/DME windows flag invalid (if equipped). • 8.2.2 ...
Page 239: Display Testing
__________________________________________________________________ ‘GMA1 Fail’ alert given. • ‘Traffic Fail’ alert given (if equipped). • Red AFCS status annunciation given (if equipped). • TAWS FAIL annunciation given (if equipped). • ADF/DME windows flag invalid (if equipped). • 8.3 DISPLAY TESTING Engage the autopilot (if equipped) by pressing the AP key on the MFD. 8.3.1 MFD Display Test Procedure 1. Remove power from the MFD. Check for desired results. Restore power. 2. The following shall occur when power is removed from the MFD: PFD switches to reversion mode. • AFCS does not disconnect (if equipped). • Attitude and Heading remain valid from AHRS. • Airspeed, Altitude, Vertical Speed, and OAT remain valid from Air Data • Computer. Valid Engine Instrumentation appears on PFD. • XPDR field remains valid on PFD. • COM2/NAV2 fields flag invalid. • NAV2 CDI deviation bar is removed. • ADF/DME windows flag invalid (if equipped). • ‘GDL 69 Fail’ alert is given (if equipped). •...
Page 240: Gcu 478 Test Procedure
__________________________________________________________________ NAV1 CDI deviation bar is removed. • XTALK ERROR alert is given. • 8.4 GCU 478 TEST PROCEDURE Perform a basic operational check on the GCU 478. Ensure the following: 1. Proper response to button presses, joystick positions, and knob turns. 2. Proper keypad back light dimming capability. 3. No stuck keys. 4. Proper response to joystick movements and positions. 5. Ensure the photocell is well lit. 8.5 BACKUP PATH TESTS Pull the PFD and MFD circuit breakers and remove power from both displays before performing these tests. Reboot the PFD and MFD by pressing and holding the 12 softkey on the MFD until the words INITIALIZING SYSTEM appear. 1. Go to the GDU Page Group on the PFD in configuration mode. 2. Activate the cursor 3. Select PFD1 in the SELECT UNIT field and press ENT. 4. View the GRS 77 #1 and GDC 74 #1 DATA indicators in the ARINC 429 window and make sure both indicators are GREEN which indicates the channels are receiving data as shown in Figure 8‐1. 5. Activate the cursor. 6. Select MFD1 in the SELECT UNIT field, and press the ENT key. 7. View the GRS 77 #2 and GDC 74 #2 DATA indicators in the ARINC 429 window. Make sure both indicators are GREEN which indicates the channels are receiving data as ...
Page 241 __________________________________________________________________ Figure 8‐1. RS‐232/ARINC‐429 Config Page (PFD1) 8. On the PFD go to the GIA Page Group. Select the RS‐232/ARINC 429 CONFIG page. 9. Verify that GIA1 is selected in the SELECT UNIT field. 10. View the data indicators for all configured RS‐232 and ARINC 429 channels (except GIA DEBUG), including the GRS 77 and GDC 74 ARINC 429 channels. 11. Make sure all DATA indicators for configured channels are GREEN which indicates the channels are receiving data as shown in Figure 8‐2. Figure 8‐2. CAN/RS‐485 Config Page (GIA1) Cirrus Perspective™ Line Maintenance Manual Page 8-5 190-00920-00 Rev. E...
Page 242 __________________________________________________________________ 12. Activate the cursor and select GIA2 in the SELECT UNIT field, then press the ENT key. 13. Repeat Steps 9 and 10. 14. On the PFD, go to the CAN/RS‐485 CONFIGURATION page in the GIA Page Group. 15. Verify that GIA1 is selected in the SELECT UNIT field. 16. Observe the data indicators for all configured RS‐485 channels. 17. Make sure all DATA indicators for configured channels are GREEN, indicating the channels are receiving data as shown in Figure 8‐3 and 8‐4. Figure 8‐3. CAN/RS‐485 Config Page (GIA1 Data Indicators) 18. Activate the cursor and select GIA2 in the SELECT UNIT field then press the ENT key. 19. Repeat Steps 15 and 16. Page 8-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 243 __________________________________________________________________ Figure 8‐4. CAN/RS‐485 Config Page (GIA2 Data Indicators) Cirrus Perspective™ Line Maintenance Manual Page 8-7 190-00920-00 Rev. E...
Page 244: Port Status Tests
__________________________________________________________________ 8.5.1 Port Status Tests In addition to troubleshooting via the GDU and GIA Configuration Pages, the System Data Path Configuration Page displays port status and information. The System Data Paths Configuration page (Figures 8‐5 through 8‐9) displays the following data when the A429, CAN, RS‐232, or RS‐ 485 data path softkey is selected: A table containing one row for each configured LRU with the following information per row, ordered from left to right: • A text field indicating the LRU name in the column • A text field indicating the channel name • A status indicator showing: o An N/A indication if the monitor is on and data path status is not applicable o A positive indication if the monitor is on and data path status is "OK" o A negative indication if the monitor is on and data path status is "FAIL" o An unknown indication if the monitor is off or the monitor is "ON" and data path status is "UNKNOWN" • A text field indicating the port monitor status: o "ON" if the monitor is turned on o "OFF" if the monitor is turned off • A text field indicating the following port status: o "OK" if the port is communicating o "FAIL" if the port is not communicating o "N/A" if the port is not applicable o "UNKNOWN" if the port status is unknown ...
Page 245 __________________________________________________________________ Figure 8‐5. A429 Data Path Page Figure 8‐6. CAN Data Path Page Cirrus Perspective™ Line Maintenance Manual Page 8-9 190-00920-00 Rev. E...
Page 246 __________________________________________________________________ Figure 8‐7. RS‐232 Data Path Page Figure 8‐8. RS‐485 Data Path Page Page 8-10 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 247 __________________________________________________________________ The System Data Paths Configuration page displays the following data when the HSDB data path softkey is selected: • A table containing one row for each configured LRU with the following data per row, ordered from left to right: o A text field indicating the LRU name in the column o A drop down selectable field indicating the expected LRU for each HSDB port o A white text field indicating the current LRU for each HSDB port o A status indicator for each HSDB port: An N/A indicator if the expected LRU is configured to none and there is no actual LRU online. A positive indicator if the expected LRU matches actual LRU online A negative indicator if the expected LRU does not match actual LRU online Figure 8‐9. HSDB Data Path Page Cirrus Perspective™ Line Maintenance Manual Page 8-11 190-00920-00 Rev. E...
Page 248 __________________________________________________________________ Blank Page Page 8-12 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 249: Section 9-Periodic Maintenance
• 3/32 inch Hex Tool • Digital Level with 0.25 degrees of accuracy capability • VHF NAV/COM/ILS Ramp Tester • Transponder Ramp Tester including Mode S capability for Mode S transponder equipped aircraft • Air Data Test Set (ADTS) capable of simulating altitude up to the aircraft’s service ceiling • GPS Indoor Repeater (if outside GPS signals cannot be acquired) • Headset/Microphone 9.3 GENERAL MAINTENANCE PROCEDURES Pitot/Static Leak Test Before starting the pitot static test, allow the GDC to operate at least 15 minutes according to Garmin Service Advisory 0608. Perform a pitot/static leak test as described in Title 14 CFR §§ 91.411 and Part 43 Appendix E. Altimeter (GDC and PFD) According to Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub‐paragraphs (iv; Friction) and (vi; Barometric Scale Error) are not applicable because the digital outputs of the GDC are not susceptible to these types of errors. Airspeed Function Test (GDC and PFD) Check for correct indication. Vertical Speed Indicator (GDC and PFD) Check for correct indication. Cirrus Perspective™ Line Maintenance Manual Page 9-1 190-00920-00 Rev. E...
Page 250: Gfc 700 Visual Inspection Procedure
__________________________________________________________________ GTX Transponder Test according to Title 14 CFR §§ 91.411 and 91.413 and Part 43 Appendix F. GRS Earth Magnetic Field Updates The GRS utilizes an earth magnetic field model which is updated once every five years. The update is expected to be available from Garmin by July 1 of each of the following years: 2005, 2010, 2015, and every five years thereafter, as long as the GRS remains a Garmin‐supported product. Otherwise, maintenance of the GRS is on condition of failure only. GSA Servos Conduct a visual inspection every 1000 hours or at every annual. Clean and apply grease to output gear every 1000 hours or 3 years. GSM Servo Gearbox Conduct a visual inspection and check slip clutches once every 12 months. Automatic Slip Clutch Test Procedure The automated slip clutch test procedure is installation‐specific. Refer to aircraft‐specific documentation as appropriate. 9.4 GFC 700 VISUAL INSPECTION PROCEDURE 1. Remove the access panels according to Cirrus maintenance documentation. 2. Inspect the servos, connectors, support structures, and control cables and make sure no corrosion, chaffing, cracks, or other defects exist. 3. Manually move the ailerons (for roll servo), elevators (for pitch servo), elevator trim wheel (for pitch trim servo), and rudder pedals (for yaw servo) from stop to stop and observe the servo, capstan, and control surface rigging. Make sure there is no binding in the control cabling and that the capstan pullies rotate freely. 4. Check the servo control cables to make sure no fraying, corrosion, or other damage exists. Replace the cable if the condition is questionable. Check the tension of each servo control cable. Refer to Cirrus maintenance documentation for cable tension specifications. 5. Inspect the GFC 700 system wiring to make sure no chaffing, wear, or other damage exists. 9.5 GSA GREASING PROCEDURE NOTE Clean and apply Aeroshell 33MS grease (which is preferred), or Aeroshell 17 to output gear every 1000 hours or 3 years, whichever comes first. Page 9-2 Cirrus Perspective™...
Page 251: Gdc Rvsm Altitude Inspection
Error, |x| (ft) at Inspection Action for Associated Error (ft) 29,000 x ≤ 40 No Action 40 < x ≤ 120 Use Field Calibration Tool 120 < x Replace Unit 35,000 x ≤ 40 No Action 40 < x ≤ 120 Use Field Calibration Tool 120 < x Return Unit to Garmin 41,000 x ≤ 40 No Action 40 < x ≤ 120 Use Field Calibration Tool 120 < x Return Unit to Garmin ...
Page 252 __________________________________________________________________ Blank Page Page 9-4 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 253: Section 10-System Reconfiguration
SECTION 10 SYSTEM RECONFIGURATION The information in this section describes how to completely reconfigure the system. The initial system software upload and configuration took place at the time of installation as described in the installation manual. Section 7 of this manual explained how to upload, configure, and test software for a replacement LRU. NOTES Perform system reconfiguration only after talking with GARMIN Field Service to find out if there is an alternate solution to a problem. System reconfiguration is a last resort when all other troubleshooting efforts have been exhausted. 10.1 DATA CARDS Garmin recommends using SanDisk cards to load system software and configuration files. If software loading problems occur when using another brand of card, replace the card with a SanDisk card and attempt the upload procedure again. 10.2 SOFTWARE PART NUMBERS ...
Page 254: Hardware And Software Compatibility Check
__________________________________________________________________ 10.3 HARDWARE AND SOFTWARE COMPATIBILITY CHECK Before installing hardware, ensure that hardware part numbers are compatible with the Garmin SR20/SR22/SR22 Turbo Normalized loader card that is to be used. The part number of this card is directly associated with the combination of software file part numbers and version levels that are defined on the card. Should software part numbers or versions change, a new loader card part number is issued. Cirrus drawings show all available combinations of hardware and loader cards for the appropriate TC configuration. Using the correct Cirrus drawing, the technician must verify that all hardware part numbers are compatible with the loader card to be used. The Cirrus drawing allows the technician to correlate each LRU hardware part number to a compatible loader. NOTE After verifying hardware/loader card compatibility, record the loader card part number, and all LRU hardware part and serial numbers in the appropriate aircraft records before proceeding. Page 10-2 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 255 __________________________________________________________________ 10.4 SYSTEM SOFTWARE LOADING AND CONFIGURATION PROCEDURE The Perspective™ system is not airworthy unless software loading and configuration procedures are accomplished successfully as described in the following procedures. The following diagram gives an overview of the software/configuration sequence for the system. Each LRU software load must be completed successfully. Figure 10‐1. Software Sequence Overview Cirrus Perspective™ Line Maintenance Manual Page 10-3 190-00920-00 Rev. E...
Page 256: System Power Up
__________________________________________________________________ 10.4.1 System Power Up 1. Turn on the ground power unit (if used). 2. Turn on the BATTERY master switches. 3. Turn on the AVIONICS MASTER switch. All system equipment should be receiving power. 10.4.1 Cooling Fan Check 1. Verify display cooling fan operation. If necessary, remove each display temporarily and visually make sure they are operating. 2. Make sure the avionics cooling fans in the remote avionics bay are operating. 10.4.2 MFD and PFD Software Load 1. Pull the MFD and PFD circuit breakers. 2. Insert the correct loader card into the top card slot on the MFD. 3. While holding the rightmost softkey on the MFD, restore power by closing the MFD circuit breaker. 4. When the words ‘INITIALIZING SYSTEM’ appear in the upper left corner of the MFD, release the key. 5. Press the rightmost softkey on the MFD to acknowledge the prompt to load new software. An ‘Updating System Files’ screen appears. New software is now being loaded to the MFD. After the system files are loaded to the MFD the user will be prompted to load the splash screen. Refer to step 8. When complete, the MFD starts in configuration mode. 6. Remove the loader card from the MFD and insert it into the top card slot on the PFD. Repeat steps 3 through 5 for the PFD. 7. When the PFD load is complete, it starts in the configuration mode. Do not remove power. After the system files are loaded to the PFD the user will be prompted to load ...
Page 257: System Software Upload
__________________________________________________________________ 10.4.3 System Software Upload 1. Select the System Upload page on the PFD using the small FMS knob (Figure 10‐2). 2. Activate the cursor, and use the small FMS knob to highlight the airframe type in the AIRFRAME field. Select the appropriate aircraft type (SR20/SR22/SR22 Turbo Normalized). 3. Press the ENT key. NOTE Ensure that the correct airframe type is selected before proceeding, otherwise incorrect configuration information will be loaded. 4. Once an airframe type is selected the cursor moves to the FILE window. Turn the small FMS knob to active the drop‐down menu. Move the cursor to highlight the appropriate aircraft model and press ENT. Figure 10‐2. System Upload Page 5. The PRODUCT window will populate and display software and configuration file information for each LRU. The ‘LRU VERS’ column shows the currently loaded software version in the LRU, whereas the ‘CARD VERS’ column shows the LRU software version stored on the loader card. Each check designates a file to be loaded to the system. By default, if an inequality between the LRU and CARD columns exists, the SOFTWARE and CONFIGURATION boxes will be preselected (checked). The following softkeys provide an easy way to select files: Cirrus Perspective™ Line Maintenance Manual Page 10-5 190-00920-00 Rev. E...
Page 258 __________________________________________________________________ • CHK ALL: Selects all files, both configuration and software. • CHK SW: Selects all SW files only. • CHK CFG: Selects all configuration files only. • CLR ALL: Clears all selections. NOTE Leave all check boxes selected for a first time software and configuration load to a new installation. 6. After making sure the desired software and configuration files are checked, press the LOAD softkey. The system automatically begins loading software and default configuration files to the selected LRUs in their proper order. 7. When the system finishes loading, it prompts the technician accordingly. Press the ENT key to acknowledge that the upload is finished: 8. Verify that each column indicates in green when the loading process has finished and inspect the SUMMARY window as well to ensure a successful load. Page 10-6 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 259 __________________________________________________________________ Figure 10‐3. Upload Complete Window Cirrus Perspective™ Line Maintenance Manual Page 10-7 190-00920-00 Rev. E...
Page 260: Optional Systems Activation
__________________________________________________________________ 10.4.4 Optional Systems Activation This section describes the steps that must be completed in order to configure the system with optional equipment. IMPORTANT: After loading all the options, place the loader card back in the MFD, select ‘NO’ when prompted for system load then select ‘YES’ to update the Splash Screen. Do this as the last step since loading the AIRFRAME file deletes the Cirrus Splash Screen. Do the same thing with the PFD. NOTE If the splash screen is not loaded, the ‘Splash Screen Cannot Be Found’ message continues to be displayed whenever power is applied. NOTE If the configuration for an optional system is inadvertently loaded for a system that is NOT installed, the aircraft configuration files must be reloaded. For example, if the ADF option is loaded, and the aircraft is not equipped with an ADF, the default configuration files must be reloaded. All optional systems must ...
Page 261 __________________________________________________________________ B. DME Option Follow this procedure if the aircraft being updated is equipped with the Honeywell model KN63 DME option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘KN63 DME Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. C. ADF Option Follow this procedure to configure the system if the aircraft is equipped with the Bendix/King KR‐87 ADF option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘KR87 ADF Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check box. Cirrus Perspective™ Line Maintenance Manual Page 10-9 190-00920-00 Rev.
Page 262 __________________________________________________________________ D. Ice Protection Installation Option (No‐Hazard) Follow this procedure to configure the system if the aircraft being updated is equipped with the Ice Protection (NH) option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘No‐Hazard IPS Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. E. SR22 TN DIN IEC 751 Oil Temperature Sensor Follow this procedure to configure the system if the aircraft being updated is equipped with a SR22 TN DIN IEC 751 Oil Temperature Sensor. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘SR22 TN DIN IEC 751 Oil Temperature Sensor Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. ...
Page 263 __________________________________________________________________ F. SR22 TN MS 28034 Oil Temperature Sensor Follow this procedure to configure the system if the aircraft being updated is equipped with a SR22 TN MS 28034 Oil Temperature Sensor. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘SR22 TN MS 28034 Oil Temperature Sensor Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. G. Oxygen Option Follow this procedure to configure the system if the aircraft being updated is equipped with the Precise Flight Oxygen System option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Oxygen Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. ...
Page 264 __________________________________________________________________ H. SKYWATCH Option Follow this procedure to configure the system if the aircraft being updated is equipped with the L‐3 SKY 497 SKYWATCH option. Skip this option if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Skywatch 497 Installation Option’ from the FILE window and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. S‐TEC 55X/55SR Follow this procedure to configure the system if the aircraft being updated is equipped with an S‐TEC 55X/55SR. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘S‐TEC 55X/55SR Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are complete. Verify that PASS appears in green at the check boxes. Page 10-12 Cirrus Perspective™...
Page 265 __________________________________________________________________ J. STORMSCOPE Option Follow this procedure to configure the system if the aircraft being updated is equipped with an L‐3 WX‐500 STORMSCOPE option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Stormscope 500 Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. K. Carbon Monoxide Detection Option NOTE If the aircraft being updated is equipped with the Guardian CO Carbon Monoxide detector follow this procedure to configure the system. Skip this procedure if the aircraft is not equipped with this option. ...
Page 266 __________________________________________________________________ L. Avidyne TAS 6XX Follow this procedure to configure the system if the aircraft being updated is equipped with an Avidyne TAS 6xx. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Avidyne TAS 6XX Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. M. Disable GDU Fan Monitoring NOTE Always load this option to deactivate the fan monitoring. Follow this procedure to configure the system if the aircraft being updated is equipped with the Disable GDU Fan Monitoring option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Disable GDU Fan Monitoring Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. ...
Page 267 __________________________________________________________________ N. EVS Installation Follow this procedure to configure the system if the aircraft being updated is equipped with an EVS Installation option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘EVS Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. O. Ice Protection Installation Option (Flight Into Known Icing; FIKI) Follow this procedure if the aircraft being updated is equipped with the Ice Protection (FIKI) option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘FIKI IPS Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. Cirrus Perspective™ Line Maintenance Manual Page 10-15 190-00920-00 Rev.
Page 268 __________________________________________________________________ P. GDL 69/69A Option Follow this procedure to configure the system if the aircraft being updated is equipped with the Garmin GDL 69/69A. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘GDL 69/69A Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. Q. GFC 700 Option (with and without Yaw Damper) Perform the following procedure if the aircraft is equipped with the Garmin GFC 700 AFCS option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘GFC 700 Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. Page 10-16 Cirrus Perspective™...
Page 269 __________________________________________________________________ R. GTX 32/33 Option Follow this procedure if the aircraft being updated is equipped with the GTX 33 or 32 option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘GTX 33 Installation Option’ or ‘GTX 32 Installation Option’ as appropriate from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. S. Single AHRS/Single ADC Option Follow this procedure to configure the system if the aircraft is equipped with a single AHRS and ADC option. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Single AHRS / Single ADC Installation Option’ from the FILE window and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. ...
Page 270 __________________________________________________________________ T. Dual AHRS/Single ADC Option The following configuration procedure MUST be performed if the aircraft is equipped with a Dual AHRS and a single ADC. Skip this procedure if the aircraft is not equipped with this option. 1. Activate the cursor and rotate the FMS knob once to activate the AIRFRAME menu on the System Upload page. 2. Select ‘Options’ from the AIRFRAME window and press ENT. 3. Select ‘Dual AHRS / SingleADC Installation Option’ from the FILE window, and press ENT. 4. Press the LOAD softkey. 5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge. 6. View the SUMMARY field and ensure that all items are ‘complete’. Verify that PASS appears in green at the check boxes. Figure 10‐4. Dual AHRS Option . Page 10-18 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 271 __________________________________________________________________ U. TAWS Unlock Option Once an unlock SD card is utilized for a particular installation, that card becomes locked with the system ID for that aircraft. The unlock cards must be retained for that aircraft should there be a need to unlock the feature again in the field. Perform this procedure only if the aircraft is equipped with the Garmin TAWS option. 1. Remove power from the PFD and MFD by opening the PFD and MFD circuit breakers. 2. A special TAWS unlock card is required to enable TAWS. Refer to the appropriate Cirrus drawing for the correct part number. Insert this card in the upper slot of the PFD. 3. While holding the ENT key on the PFD and MFD, restore power to the displays. 4. When the words ‘INITIALIZING SYSTEM’ appear in the upper left corner of both displays, release the ENT keys. 5. On the PFD, go to the System Upload page using the FMS knob. 6. Activate the cursor. Use the small FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the ENT key. 7. Highlight the FILE field. Use the small FMS knob to select the ‘Enable TAWS’ option and press the ENT key. Once the option is selected, the configuration files in the PRODUCT field will be displayed. All files should be checked. If not, press the CHK ALL softkey. 8. Press the LOAD softkey. 9. Monitor the status of the upload. When the upload is finished, press the ENT key to acknowledge the upload complete confirmation. 10. View the SUMMARY field and ensure that the item is ‘COMPLETE’. 11. De‐activate the cursor. 12. Power down the system and remove the TAWS Enable card from the PFD. Cirrus Perspective™ Line Maintenance Manual...
Page 272 __________________________________________________________________ V. Terrain‐Synthetic Vision (SVS) Unlock Option Once an unlock SD card is utilized for a particular installation that card becomes locked with the system ID for that aircraft. The unlock cards must be retained for that aircraft should there be a need to unlock the feature again in the field. Perform this procedure only if the aircraft is to be equipped with the Garmin Terrain‐SVS option. 1. Remove power from the PFD and MFD by opening the PFD and MFD circuit breakers. 2. A special Synthetic Vision unlock card is required to enable SVS. Refer to the appropriate Cirrus drawing for the correct part number. Insert this card in the top slot of the PFD. 3. While holding the ENT key on the PFD and MFD, restore power to the displays. 4. When the words ‘INITIALIZING SYSTEM’ appear in the upper left corner of both displays, release the ENT keys. 5. On the PFD, go to the System Upload page using the FMS knob. 6. Activate the cursor. Use the small FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the ENT key. 7. Highlight the FILE field. Use the small FMS knob to select the ‘Enable Synthetic Vision’ option and press the ENT key. Once the option is selected, the configuration files in the PRODUCT field will be displayed. All files should be checked. If not, press the CHK ALL softkey. 8. Press the LOAD softkey. 9. Monitor the status of the upload. When the upload is finished, press the ENT key to acknowledge the upload complete confirmation. 10. View the SUMMARY field and ensure that the item is ‘COMPLETE’. 11. De‐activate the cursor. 12. Power down the system and remove the Synthetic Vision Enable card from the PFD. Page 10-20 Cirrus Perspective™...
Page 273 __________________________________________________________________ W. ChartView Unlock Option NOTE ChartView databases are subscription‐based and are to be procured by the aircraft owner directly from Jeppesen. This procedure is only required if the ChartView option is purchased by the customer. NOTE Once an unlock SD card is utilized for a particular installation that card becomes locked with the system ID for that aircraft. The unlock cards must be retained for that aircraft should there be a need to unlock the feature again in the field. 1. Remove power from the PFD and MFD by opening the PFD and MFD circuit breakers. 2. A special ChartView unlock card is required to activate this feature. Refer to the appropriate Cirrus drawing for the correct part number. Insert this card in the upper slot of the PFD. ...
Page 274: Software Load Confirmation
__________________________________________________________________ 10.5 SOFTWARE LOAD CONFIRMATION Figure 10‐5. System Status Page 1. Select the System Status page using the FMS knob. Activate the cursor and toggle to the LRU window. 2. Highlight each of the following item in the LRU window, and verify that the software part number and version matches the information in the appropriate Cirrus drawing (use the following table). 3. De‐activate the cursor. NOTE If any software version and/or part number does not match those specified by the General Arrangement Drawing, or if the software is not successfully loaded, DO NOT continue with upload procedures. Troubleshoot and resolve the issue before continuing. Page 10-22 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 275 __________________________________________________________________ LRU SW VER OK LRU SW VER OK GCU ___________ GMU1 __________ _ GDC1 ___________ GMU1 FPGA __________ _ GDC1 FPGA ___________ GMU2** __________ _ GDC2*** ___________ GMU2 FPGA** __________ _ GDC2 FPGA*** ___________ GRS1 __________ _ GEA1 ___________ GRS1 FPGA __________ _ GFC CERT GIA1* ___________ GRS2** __________ _ ...
Page 276: Aircraft Registration Number Entry (Gtx33 Option Only)
__________________________________________________________________ 10.6 Aircraft Registration Number Entry (GTX33 Option Only) Figure 10‐6. XPDR1 Option 1. Select the GTX page group on the PFD then select the TRANSPONDER CONFIGURATION page. 2. Make sure the ‘ADDRESS TYPE’ is ‘US TAIL’ under the ‘SET’ and ‘ACTIVE’ columns. 3. Activate the cursor and highlight the ‘ADDRESS’ field. Use the small/large FMS knobs to enter the aircraft registration number. Once the correct registration number is entered, press the ENT key. The transponder is configuring: 4. The transponder then alerts the technician of complete configuration: 5. Press the ENT key on the PFD. 6. At this point, the technician may enter a Flight ID Type and Flight ID number if desired. The system defaults to ‘SAME AS TAIL’. After transponder configuration is complete, deactivate the cursor. Page 10-24 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 277: Navigation Databases
10.7 Navigation Databases Features Perspective systems with GDU software version 10.0 and above may utilize the following database features: Dual Navigation Database Support: the GDU is able to store an upcoming navigation database on the bottom SD card so that the system can automatically load it to replace the active database when the new database becomes effective. Automatic Database Synchronization: the Perspective system is able to automatically check all databases stored on the bottom SD cards in each GDU and transfer the most recent cycle of each database to any cards that do not have the most recent cycle. This gives users the option of downloading database updates to the database card from only one GDU and letting the system synchronize the updates to the cards on the other GDU(s). See the Garmin Pilot’s Guide for complete details regarding these features. NOTE Use only blank SD cards to load the Navigation Database into the GDUs. Do not copy the navigation database (not including Chartview) onto 010‐00330‐42 (or ‐ 43) supplemental data cards to load into the GDUs. Doing so may corrupt the supplemental database cards making them unusable. Replacing corrupt cards is not covered under warranty. The navigation database is updated on a 28‐day cycle and is provided directly from Jeppesen. The navigation database may be installed from the Jeppesen supplied SD data card. After the navigation database is installed, the card may be removed after loading the update to each GDU. NOTE Do not load the Navigation Database to a Supplemental Database Card to load into the displays. SD cards used for loading the navigation database are ...
Page 278 __________________________________________________________________ 1. With the Perspective system off, insert the navigation database SD Card into the top card slot of PFD2. 2. Turn the Perspective system on. The following prompt is displayed in the upper left corner of PFD2: 3. Press the ENT key to confirm the database update. The following screen is displayed: 4. After the update completes, the MFD starts in normal mode. Remove the navigation database update SD Card from the MFD. 5. Power the Perspective system down. 6. Repeat steps 1 through 4 for the PFD. On the PFD, pressing the ENT key will not work. Press the YES Softkey. 7. Confirm that the correct update cycle and version is loaded during startup of the MFD. Page 10-26 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 279: Aviation Database Loading (Pre Gdu 10.0)
__________________________________________________________________ 10.8 Aviation Database Loading (Pre GDU 10.0) NOTE Retain the Jepp SD cards for future updates. 1. Insert a database card containing the Jeppesen aviation database (card & database supplied by Jeppesen) into the top slot of the PFD. 2. Apply power to the PFD. The following prompt is displayed in the upper left corner of the PFD: 3. Press the ENT key to confirm the database update. The following prompt is displayed: 4. After the update completes the PFD starts in normal mode. Remove the aviation database update card from the PFD. 5. Repeat steps 2 through 4 for the MFD. The MFD and PFD aviation databases are now updated. 6. Confirm that the correct update cycle and version is loaded at the power‐up page of the MFD. 7. Remove the aviation database update card from the MFD. Cirrus Perspective™ Line Maintenance Manual Page 10-27 190-00920-00 Rev. E...
Page 280: Other Perspective Databases
__________________________________________________________________ 10.9 Other Perspective Databases Terrain/Obstacle/SafeTaxi®/FliteCharts®/Expanded Basemap Database Cards There is no unlock card required for Garmin FliteCharts®. A single cycle of Garmin FliteCharts® is loaded on the database cards when they are manufactured at Garmin. Additional FliteChart® database updates are obtained directly from Garmin’s web site and are updated on a periodic basis. The system automatically detects the FliteChart® databases and activates the display feature. Once Jepp ChartView is unlocked the system will make use of the Jepp data and will not display FliteChart® data or version. 1. Remove power from the PFD and MFD using the respectively labeled breakers. 2. Remove the Garmin SR20/SR22/SR22 Turbo Normalized software loader card from the PFD. 3. Insert two Terrain/Obstacle/SafeTaxi®/FliteChart® database cards into the bottom slots of the MFD and PFD, respectively. Refer to the appropriate Cirrus drawing for correct database card part numbers. 4. Continue to the aviation database loading procedure. Jeppesen ChartView, Cirrus Startup Screens, and Cirrus Checklist If the Perspective™ System is to be equipped with the Jeppesen ChartView display option, the appropriate ChartView database must be loaded onto the Terrain/Obstacle/SafeTaxi/FliteChart database card (bottom ‐43 card) installed in the MFD along with any Cirrus startup screen images and Cirrus checklist files. ChartView database subscription services must be procured directly from Jeppesen and are usually sourced by the aircraft owner. Further, the ChartView feature must be ‘unlocked’ before the system can use the databases. 1. Obtain ChartView data and copy onto an SD card. Refer to Cirrus drawing for SD card requirement. 2. Obtain Cirrus startup screen images and checklist files and copy onto the same SD card. Refer to Cirrus drawing for image location. 3. Insert the card into the bottom slot on the MFD. Page 10-28 Cirrus Perspective™ Line Maintenance Manual Rev.
Page 281: Software/Configuration Troubleshooting
__________________________________________________________________ 10.10 SOFTWARE/CONFIGURATION TROUBLESHOOTING Problem Solutions • Ensure power is present at display backshell MFD or PFD displays do not power up connector. • Replace display. Software file load fails: • Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’). Check data path wiring as needed. • Retry software file load or try using a different card. Ensure that the MFD is not touched during the loading process. • Ensure that LRU part number is compatible with software version and Card Loader. Refer to the General Arrangement Drawing and to Section TBD of this document. • Restart MFD & PFD in Configuration Mode and retry software file load or try using a different card. • Replace LRU. Configuration file load fails: • Ensure that LRU is reporting data on System Status page (LRU is ‘ONLINE’). Check data path wiring as needed. •...
Page 282 __________________________________________________________________ GIA1 and/or GIA2 to ‘LRU’ data path not working • Ensure GIA1 and GIA2 are configured correctly. • Check wiring, connectors & pins as needed. Software File Mismatch Alert appears in lower • Ensure that proper software file part number right corner of PFD when started in normal mode: and version were loaded to LRU. Refer to the General Arrangement Drawing. • Check and ensure that correct Card Loader was used during load process. Refer to the General Arrangement Drawing. • Reload software to LRU. Optional Equipment does not work. • Load optional config file to enable the system to interface with the optional unit. • If optional equipment still does not operate, reference optional equipment documentation for further troubleshooting. • “SYN VIS” softkey does not Verify that the PFD and MFD software appear on PFD softkey tier. versions are shown to be 9.01 or above by checking the AUX – System Status Page on the MFD. • If version 9.01 or above software is installed in the MFD and PFD, reactivate the SVS/Pathways feature. ...
Page 283 __________________________________________________________________ The following table provides SVS specific alert messages which may appear in the Alerts Window on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window): SVS‐Related Alert Messages Failure Message Cause Solution SVS is disabled because the Ensure that operations are SVS – SVS DISABLED: Out of aircraft exceeded the within the required geographic available terrain region. boundaries of the loaded area. terrain database. Ensure the P/N 010‐00330‐43 Terrain Cards are installed in the lower slot of each display. SVS is disabled because a 9 SVS – SVS DISABLED: Terrain Arc‐Second or better database If terrain data has been recently DB resolution too low is not currently loaded. updated, ensure that the correct 9 Arc‐Second databases were used. ...
Page 284 __________________________________________________________________ Blank Page Page 10-32 Cirrus Perspective™ Line Maintenance Manual Rev. E 190-00920-00...
Page 285: Gia 63W
__________________________________________________________________ APPENDIX CONNECTOR PIN ASSIGNMENTS The tables in this section provide connector pinout information for the system. A.1 GIA 63W P601 (COM) View of J601 connector looking at unit Pin Pin Name I/O 1 UNSQUELCHED AUDIO TEST ‐‐ 2 RESERVED ‐‐ 3 RESERVED ‐‐ 4 COM MIC KEY* In 5 INTERCOM MIC IN HI In 6 INTERCOM MIC IN LO (GROUND) ‐‐ 7 COM MIC AUDIO IN HI In 8 COM MIC AUDIO IN LO (GROUND) ‐‐ 9 Out COM 500Ω AUDIO OUT HI ...
Page 286 __________________________________________________________________ 31 POWER GROUND ‐‐ 32 COM RS‐232 OUT 1 Out 33 COM RS‐232 IN 1 In 34 COM REMOTE TUNE ENABLE* In 35 COM AUDIO IN HI In 36 COM AUDIO IN LO (GROUND) ‐‐ 37 VOR/LOC AUDIO IN HI In 38 VOR/LOC AUDIO IN LO (GROUND) ‐‐ 39 AUX AUDIO IN HI In 40 AUX AUDIO IN LO (GROUND) ‐‐ 41 SUMMED 4Ω AUDIO OUT HI Out 42 SUMMED 4Ω AUDIO OUT LO (GROUND) ‐‐ 43 POWER GROUND ‐‐ ...
Page 287: P602 (Vor/Ils
__________________________________________________________________ A.2 P602 (VOR/ILS) View of J602 connector looking at unit Pin Pin Name I/O 1 VOR/LOC +TO Out 2 VOR/LOC +FROM (VOR/LOC COMMON) ‐‐ 3 VOR/LOC +FLAG Out 4 VOR/LOC ‐FLAG (VOR/LOC COMMON) ‐‐ 5 VOR/LOC +LEFT Out 6 VOR/LOC +RIGHT (VOR/LOC COMMON) ‐‐ 7 RESERVED (VOR/LOC IF AGC) ‐‐ 8 VOR/LOC COMPOSITE OUT Out 9 VOR OBS ROTOR C Out 10 VOR OBS ROTOR H (GROUND) ‐‐ 11 VOR OBS STATOR E (VOR/LOC COMMON) ...
Page 288 __________________________________________________________________ 38 GLIDESLOPE SUPERFLAG Out 39 PARALLEL DME 100 KHZ‐B Out 40 PARALLEL DME 100 KHZ‐C Out 41 DME COMMON In 42 PARALLEL DME 100 KHZ‐D Out 43 PARALLEL DME 50 KHZ Out 44 SPARE ‐‐ 45 PARALLEL DME 1 MHZ‐A Out 46 PARALLEL DME 1 MHZ‐B Out 47 PARALLEL DME 1 MHZ‐C Out 48 RESERVED ‐‐ 49 SIGNAL GROUND ‐‐ 50 RESERVED ...
Page 289 __________________________________________________________________ A.3 P603 (Main Serial) View of J603 connector looking at unit 41 42 51 52 21 22 Pin Pin Name I/O 1 RESERVED ‐‐ 2 ETHERNET OUT A Out 3 ETHERNET OUT B Out 4 RS‐485 4 A (SERVO) I/O 5 RS‐485 4 A (SERVO) I/O 6 RS‐485 4 B (SERVO) I/O 7 RS‐485 4 B (SERVO) I/O 8 MAIN ARINC 429 IN 3 A In 9 MAIN ARINC 429 IN 3 B ...
Page 290 __________________________________________________________________ Connector P603, continued Pin Pin Name I/O 37 RS‐485 5 B/RS‐422 OUT B I/O 38 RESERVED ‐‐ 39 CAN BUS 2 TERMINATION ‐‐ 40 RESERVED ‐‐ 41 MAIN RS‐232 IN 1 In 42 SIGNAL GROUND ‐‐ 43 MAIN RS‐232 OUT 1 Out 44 MAIN RS‐232 IN 2 In 45 SIGNAL GROUND ‐‐ 46 MAIN RS‐232 OUT 2 Out 47 MAIN RS‐232 IN 3 In 48 SIGNAL GROUND ...
Page 291 __________________________________________________________________ A.4 P604 (MAIN DISCRETE) View of J604 connector looking at unit Pin Pin Name I/O 1 ANNUNCIATE* 22 Out 2 Out VOICE ALERT 500Ω AUDIO OUT HI 3 ‐‐ VOICE ALERT 500Ω AUDIO OUT LO (GROUND) 4 DISCRETE IN 13 In 5 DISCRETE IN 14 In 6 ANNUNCIATE* 1 Out 7 DISCRETE IN* 1 In 8 DISCRETE IN* 2 In 9 DISCRETE IN* 3 In 10 DISCRETE IN 15 In 11 ...
Page 292 __________________________________________________________________ 37 ANNUNCIATE* 14 Out 38 ANNUNCIATE* 15 Out 39 ANNUNCIATE* 16 Out 40 ANNUNCIATE* 17 Out 41 ANNUNCIATE* 18 Out 42 ANNUNCIATE* 19 Out 43 ANNUNCIATE* 20 Out 44 ANNUNCIATE* 21 Out Page A-8 Cirrus Perspective Line Maintenance Manual Rev. D 190-00920-00...
Page 293 __________________________________________________________________ A.5 P605 (I/O #1) View of J605 connector looking at unit 41 42 51 52 21 22 Pin Pin Name I/O 1 RADAR ALTIMETER DC HI In 2 RADAR ALTIMETER DC LO In 3 DISCRETE IN 18A In 4 SPARE ‐‐ 5 SPARE ‐‐ 6 SPARE ‐‐ 7 SPARE ‐‐ 8 FLIGHT DIRECTOR PITCH +UP In 9 FLIGHT DIRECTOR PITCH +DOWN ...
Page 294 __________________________________________________________________ Connector P605, continued Pin Pin Name I/O 37 DISCRETE IN* 1A In 38 DISCRETE IN* 2A In 39 DISCRETE IN* 3A In 40 DISCRETE IN* 4A In 41 DISCRETE IN* 5A In 42 DISCRETE IN* 6A In 43 DISCRETE IN* 7A In 44 DISCRETE IN* 8A In 45 DISCRETE IN* 9A In 46 DISCRETE IN* 10A In 47 DISCRETE OUT* 1A 48 SIGNAL GROUND ‐‐ ...
Page 295 __________________________________________________________________ A.6 P606 (I/O #2) View of J606 connector looking at unit 41 42 51 52 21 22 Pin Pin Name I/O 1 26 VAC VERTICAL GYRO REF HI In 2 26 VAC VERTICAL GYRO REF LO In 3 26 VAC ADF REF HI In 4 26 VAC ADF REF LO In 5 26 VAC AFCS REF HI In 6 26 VAC AFCS REF LO In 7 DIRECTIONAL GYRO MOTOR A In 8 DIRECTIONAL GYRO MOTOR B In 9 ...
Page 296 __________________________________________________________________ Connector P606, continued Pin Pin Name I/O 37 HEADING BOOTSTRAP OUT X 38 HEADING BOOTSTRAP OUT Y 39 HEADING BOOTSTRAP OUT Z (GROUND) 40 AC ROLL ATTITUDE OUT HI 41 AC ROLL ATTITUDE OUT LO (GROUND) 42 AC PITCH ATTITUDE OUT HI 43 AC PITCH ATTITUDE OUT LO (GROUND) 44 YAW RATE +RIGHT 45 YAW RATE +LEFT (GROUND) 46 HEADING DATUM HI 47 HEADING DATUM LO (GROUND) 48 COURSE DATUM HI 49 COURSE DATUM LO (GROUND) 50 SIGNAL GROUND ‐‐ 51 26 VAC DIRECTIONAL GYRO REF HI In 52 26 VAC DIRECTIONAL GYRO REF LO In ...
Page 297 __________________________________________________________________ A.7 P12001 Connector (GDU 1240A) View of J12001 connector from back of unit Pin Pin Name I/O 1 CONFIG MODULE GROUND Out 2 ETHERNET OUT 1 A Out 3 ETHERNET OUT 1 B Out 4 ETHERNET IN 1 A In 5 ETHERNET IN 1 B In 6 ETHERNET OUT 2 A Out 7 ETHERNET OUT 2 B Out 8 ETHERNET IN 2 A In 9 ETHERNET IN 2 B In 10 ETHERNET OUT 3 A Out 11 ...
Page 298 __________________________________________________________________ Connector P12001, continued Pin Pin Name I/O 35 AIRCRAFT POWER 1 In 36 SIGNAL GROUND ‐‐ 37 AIRCRAFT POWER 1 In 38 SIGNAL GROUND ‐‐ 39 AIRCRAFT POWER 2 In 40 SIGNAL GROUND ‐‐ 41 AIRCRAFT POWER 2 In 42 SIGNAL GROUND ‐‐ 43 CONFIG MODULE CLOCK Out 44 RS‐232 OUT 1 Out 45 RS‐232 IN 1 In 46 RS‐232 OUT 2 ...
Page 299 __________________________________________________________________ A.8 GRS 77 P771 View of J771 connector looking at unit Pin Pin Name I/O 1 CONFIG MODULE GROUND ‐‐ 2 AHRS SYSTEM ID PROGRAM* 1 In 3 AHRS SYSTEM ID PROGRAM* 2 In 4 RESERVED ‐‐ 5 SPARE ‐‐ 6 GPS 2 RS‐232 IN In 7 RESERVED ‐‐ 8 SPARE RS‐232 IN 1 In 9 MAGNETOMETER POWER OUT Out 10 MAGNETOMETER RS‐232 OUT Out 11 ...
Page 300 __________________________________________________________________ 36 SPARE ‐‐ 37 SIGNAL GROUND ‐‐ 38 SIGNAL GROUND ‐‐ 39 MAGNETOMETER RS‐485 IN B In 40 MAGNETOMETER GROUND ‐‐ 41 SIGNAL GROUND ‐‐ 42 SIGNAL GROUND ‐‐ 43 SIGNAL GROUND ‐‐ 44 SIGNAL GROUND ‐‐ A.9 GMU 44 P441 View of J441 connector looking at pigtail Pin Pin Name I/O 1 ...
Page 301 __________________________________________________________________ A.10 GDC 74A P741 View of J741 connector looking at unit 51 52 41 42 21 22 Pin Pin Name I/O 1 CONFIG MODULE GROUND ‐‐ 2 OAT PROBE POWER OUT Out 3 OAT PROBE IN HI In 4 OAT PROBE IN LO In 5 SIGNAL GROUND ‐‐ 6 ADC SYSTEM ID PROGRAM* 1 In 7 SIGNAL GROUND ‐‐ 8 DISCRETE IN* 6 In 9 ...
Page 302 __________________________________________________________________ Connector P741, continued Pin Pin Name I/O 37 SIGNAL GROUND ‐‐ 38 SPARE ‐‐ 39 SPARE ‐‐ 40 CONFIG MODULE DATA I/O 41 ARINC 429 OUT 1 A Out 42 ARINC 429 OUT 1 B Out 43 SIGNAL GROUND ‐‐ 44 ARINC 429 OUT 2 A Out 45 ARINC 429 OUT 2 B Out 46 SIGNAL GROUND ‐‐ 47 ARINC 429 OUT 3 A Out 48 ARINC 429 OUT 3 B ...
Page 303 __________________________________________________________________ A.11 GEA 71 P701 View of J701 connector looking at unit 41 42 51 52 21 22 Pin Pin Name I/O 1 CONFIG MODULE GROUND ‐‐ 2 DIGITAL IN* 1 In 3 DIGITAL IN* 2 In 4 SIGNAL GROUND ‐‐ 5 RS‐485 1 A I/O 6 RS‐485 1 B I/O 7 RS‐485 2 A I/O 8 RS‐485 2 B I/O 9 ...
Page 304 __________________________________________________________________ Connector P701, continued Pin Pin Name I/O 39 SIGNAL GROUND ‐‐ 40 CONFIG MODULE DATA I/O 41 DIGITAL IN* 3 In 42 ANALOG IN 3 HI In 43 ANALOG IN 3 LO In 44 ANALOG IN 4 HI In 45 ANALOG IN 4 LO In 46 ANALOG IN 5 HI In 47 ANALOG IN 5 LO In 48 ENGINE TEMP ANALOG IN 7 HI In 49 ENGINE TEMP ANALOG IN 7 LO In 50 ...
Page 305 __________________________________________________________________ A.12 P702 View of J702 connector looking at unit 71 72 51 52 41 42 21 22 29 30 38 39 11 12 Pin Pin Name I/O 1 ANNUNCIATE* 1A Out 2 ANNUNCIATE* 2A Out 3 ANNUNCIATE* 3A Out 4 ANNUNCIATE* 4A Out 5 ANNUNCIATE* 5A Out 6 ANNUNCIATE* 6A Out ...
Page 306 __________________________________________________________________ Connector P702, continued Pin Pin Name I/O 40 DISCRETE IN* 17A In 41 DISCRETE IN* 18A In 42 DISCRETE IN* 19A In 43 DISCRETE IN* 20A In 44 ANALOG/CURRENT MONITOR IN 1A HI In 45 ANALOG/CURRENT MONITOR IN 1A LO In 46 ANALOG/CURRENT MONITOR IN 2A HI In 47 ANALOG/CURRENT MONITOR IN 2A LO In 48 ANALOG/CURRENT MONITOR IN 3A HI In 49 ANALOG/CURRENT MONITOR IN 3A LO In 50 ANALOG/CURRENT MONITOR IN 4A HI In 51 ...
Page 307 __________________________________________________________________ A.13 GMA 347 The GMA 347 has two 78‐pin connectors located at the rear of the unit designated P3471 and P3472. P3471 and P3472 are clearly marked on the back of the rack. P3471 and P3472 pins are configured as shown in the following illustration: 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 ...
Page 308 __________________________________________________________________ J3471 Pin Assignments Pin Pin Name I/O 1 FAIL SAFE WARN AUDIO IN In 2 RESERVED ‐‐ 3 TEL RINGER AUDIO IN HI In 4 TEL RINGER AUDIO IN LO In 5 RESERVED ‐‐ 6 ON‐SIDE NAV AUDIO IN HI In 7 ON‐SIDE COM AUDIO IN HI In 8 ON‐SIDE COM AUDIO LO I/O 9 PILOT HEADSET AUDIO OUT LEFT Out 10 PILOT HEADSET AUDIO OUT RIGHT Out 11 PILOT HEADSET AUDIO OUT LO Out 12 CROSS‐SIDE COM AUDIO IN HI In ...
Page 309 __________________________________________________________________ J3471 Pin Assignments (Continued) Pin Pin Name I/O 38 UNSWITCHED AUDIO IN 3 HI In 39 UNSWITCHED AUDIO IN LO In 40 RESERVED ‐‐ 41 RESERVED ‐‐ 42 TEL AUDIO IN HI In 43 TEL AUDIO IN LO In 44 PASS 3 MIC AUDIO IN HI In 45 PASS 3 MIC AUDIO IN LO In 46 PASS 1 MIC AUDIO IN HI In 47 PASS 1 MIC AUDIO IN LO In 48 PASS HEADSET AUDIO OUT LO Out 49 COPILOT MIC AUDIO IN HI In ...
Page 310 __________________________________________________________________ J3472 Pin Assignments Pin Pin Name I/O 1 CONFIG MODULE GROUND ‐‐ 2 RESERVED ‐‐ 3 PROGRAM GROUND ‐‐ 4 RECORDER PLAY* In 5 PROGRAM GROUND ‐‐ 6 RS‐232 OUT 1 Out 7 RS‐232 IN 1 In 8 RESERVED ‐‐ 9 RESERVED ‐‐ 10 RESERVED ‐‐ 11 PROGRAM GROUND ‐‐ 12 RESERVED ‐‐ ...
Page 311 __________________________________________________________________ J3472 Pin Assignments (Continued) Pin Pin Name I/O 38 RS‐232 OUT 2 Out 39 RS‐232 IN 2 In 40 CONFIG MODULE DATA I/O 41 SPEAKER AUDIO OUT LO Out 42 SPEAKER AUDIO OUT HI Out 43 RESERVED ‐‐ 44 PROGRAM GROUND ‐‐ 45 RESERVED ‐‐ 46 PROGRAM GROUND ‐‐ 47 RESERVED ‐‐ 48 RESERVED ‐‐ 49 RESERVED ‐‐ ...
Page 312: Gtx 32/33
__________________________________________________________________ A.14 GTX 32/33 P3301 View of J3301 connector looking at unit Pin Pin Name I/O 1 RESERVED ‐‐ 2 ALTITUDE A1 In 3 ALTITUDE C2 In 4 ALTITUDE A2 In 5 ALTITUDE A4 In 6 ALTITUDE C4 In 7 ALTITUDE B1 In 8 ALTITUDE C1 In 9 ALTITUDE B2 In 10 ALTITUDE B4 In ...
Page 313 __________________________________________________________________ 39 RESERVED ‐‐ 40 SPARE ‐‐ 41 CURRENT TEMPERATURE PROBE OUT Out 42 AIRCRAFT POWER 1 In 43 POWER GROUND ‐‐ 44 CURRENT TEMPERATURE PROBE IN In 45 NOT USED In 46 TIS CONNECT SELECT* In 47 AUDIO MUTE SELECT* In 48 ARINC 429 IN 4 A In 49 ARINC 429 IN 4 B In 50 ALTITUDE COMMON (GROUND) In 51 SIGNAL GROUND ‐‐ 52 ...
Page 314 __________________________________________________________________ A.15 GDL 69A P691 View of J691 connector from back of unit 51 52 41 42 21 22 Pin Pin Name I/O 1 CONFIG MODULE GROUND Out 2 RS‐232 OUT 2 Out 3 RS‐232 OUT 3 Out 4 SIGNAL GROUND ‐‐ 5 RS‐232 IN 2 In 6 RS‐232 IN 3 In 7 RS‐232 IN 1 In 8 RS‐232 OUT 1 Out ...
Page 315 __________________________________________________________________ 38 SPARE ‐‐ 39 SIGNAL GROUND ‐‐ 40 CONFIG MODULE DATA I/O 41 SPARE ‐‐ 42 SPARE ‐‐ 43 SPARE ‐‐ 44 SPARE ‐‐ 45 SPARE ‐‐ 46 SPARE ‐‐ 47 SPARE ‐‐ 48 SPARE ‐‐ 49 SPARE ‐‐ 50 SPARE ‐‐ 51 ...
Page 316 __________________________________________________________________ A.16 GMC 710 P701 View of J7101 connector looking at unit Pin Pin Name I/O 1 RS‐232 OUT 1 2 RS‐232 IN 1 In 3 RS‐232 OUT 2 4 RS‐232 IN 2 In 5 POWER GROUND ‐‐ 6 SIGNAL GROUND ‐‐ 7 AIRCRAFT POWER 1 In 8 SIGNAL GROUND ‐‐ 9 AIRCRAFT POWER 2 In 10 CONTROL UNIT REMOTE POWER OFF In 11 LIGHTING BUS HI In ...

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