garmin g3x experimental installation manual

• GARMIN G3X Touch Flight Displays for Experimental Aircraft Instruction Manual

GARMIN G3X Touch Flight Displays for Experimental Aircraft

Product Information

• Product Name: G3XTM/G3X TouchTM Avionics Installation Manual
• Model Number: 190-01115-01
• Revision: AV
• Release Date: May, 2024
• Manufacturer: Garmin International, Inc.
• Locations: Olathe, KS, USA and Southampton, U.K.

Product Usage Instructions

Installation Follow the step-by-step instructions provided in the manual for a successful installation of the G3XTM/G3X TouchTM Avionics system. Usage Once installed, power on the avionics system and follow the on-screen instructions to set up and configure the various features. Maintenance Regularly check for software updates on the Garmin website to ensure your avionics system is up to date.

• A: No, the G3X system is not type-certificated and is not suitable for installation in type-certificated aircraft.
• A: For information about chemicals in the product, refer to our website at www.garmin.com/prop65 .
• A: Unless otherwise noted, all installation guidance, requirements, and instructions apply to one, two, three, four, five, and six-display G3X systems.

INVENTORY OF MATERIALS

This manual provides all of the mechanical and electrical information required for the installation of the G3XTM avionics. This manual is intended to be a step-by-step guide to the installation, therefore it is important the steps in all sections be performed in order. All materials that are required/optional for the installation of the G3X are listed in this section (as such, some of the information in this section is repeated in following sections). Before beginning the G3X installation, it is recommended the installer perform a complete inventory of all materials listed in this section (some materials are optional and may not be applicable to the installation). Section 1 should be used to verify that all components ordered from Garmin have been delivered correctly, and to identify any required materials that are not provided by Garmin. 1.1 Unpacking Unit Carefully unpack the equipment and make a visual inspection of all contents for evidence of damage incurred during shipment. If any component of the G3X is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return any equipment to Garmin until the carrier has authorized the claim. Retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement. 1.2 Required Garmin Equipment 1.2.1 Garmin LRU (Line Replaceable Unit) List for G3X systems Table 1-1 and Table 1-2 list the two available G3X System LRU kits. The standard kit includes the GSU 25 and GMU 11, the performance kit includes the GSU 25 and the GMU 22. Available GDUTM displays are listed in Table 1-3. All other G3X LRUs (listed in Table 1-7) are ordered separately. Table 1-1 Contents of High Performance G3X LRU Kit* (K10-00016-03) Item Part Number Quantity GSU 25D, Unit Only 010-01071-51 1 GMU 22, Unit Only 010-01196-00 1 Configuration Module, EEPROM, Temp 010-12253-00 1 GTP 59 OAT Probe Kit 011-00978-00 1 The High Performance Kit must be used if the aircraft performance exceeds that specified for the GSU 25, see Appendix D.12.2 Table 1-2 Contents of G3X Standard LRU (K10-00016-04) Item GSU 25C, Unit Only GMU 11, Unit Only Configuration Module, EEPROM, Temp GTP 59 OAT Probe Kit Part Number 010-01071-50 010-01788-00 010-12253-00 011-00978-00 Quantity 1 1 1 1 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-1 Table 1-3 Available GDU Display Units Item Part Number G3X - GDU 370, 7" Portrait Non-Touch Display** 010-00667-15 G3X TouchTM Avionics - GDU 460, 10.6" Display 010-01057-00 G3X Touch - GDU 465, 10.6" Display with SXM Receiver 010-01057-10 G3X Touch - GDU 470, 7" Portrait Display 010-01765-00 G3X Touch - GDU 450, 7" Landscape Display 010-01056-00 G3X Touch - GDU 455, 7" Landscape Display with SXM Receiver 010-01056-10 *Any combination of G3X Touch displays can be installed in a single system (maximum of six displays) **Not compatible with G3X Touch displays 1.3 Optional Garmin Equipment 1.3.1 Garmin Optional LRU Installation Kits Table 1-4 LRU Connector/Installation Kits LRU GAD 27 Flaps/Lights/Trim Controller GAD 29 ARINC 429 Adapter GAP 26 Air Data Probe GDU 37X Display GDU 45X Display GDU 46X Display GDU 470 Display GDL® 39R data transceiver (9 Pin Connector) GDL 5XR Data Link GEATM 24 Engine Interface Module GHA 15 Height Advisor GMC 305 Mode Controller GMC 307 Mode Controller GMC 507 Mode Controller GMU 11 Magnetometer GMU 22 Magnetometer GPS 20A Connector/Installation Kit Part Number 011-03877-00 (Table 3-2) 011-03271-00 (Table 4-2) 011-03609-00 (Table 5-2) 011-01921-00 (Table E-1) 010-12150-01 (Table 6-1) 010-12150-00 (Table 6-2) 010-12150-02 (Table 6-3) 010-11825-20 (Table 1-6) 010-12498-60 (Table 1-6) 011-02886-00 (Table 7-2) 011-05278-00, Conn Kit (Table 8-3) 011-06097-00, Install Kit (Table 8-4) 010-12034-00 (Table 10-2) 010-12421-00 (Table 11-2) 010-01946-00 (Table 12-2) 011-04349-90, Install Kit (Table 13-3) 011-00871-10, Conn Kit (Table 14-3) 011-03914-00 (Table 15-3) Installation Kit Included with LRU? N N N Y N N N N N N N N N N N N N 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-2 Table 1-4 LRU Connector/Installation Kits LRU GSA 28 Servo Actuator GSU 25 ADAHRS GSU 73 ADAHRS/EIS GTP 59 Temperature Probe GTR 20 Garmin GPS and/or XM Antennas Connector/Installation Kit Part Number 011-02950-00, Conn Kit (Table 16-6) 011-02950-01, 90° Conn Kit (Table 16- 7) K10-00181-00, Conn Kit (Table 17-2 ) NA 011-00978-00 (Table 18-2) 011-03241-00 (Table 19-3) NA Installation Kit Included with LRU? N Y Y Y Y N Table 1-5 Contents of GDL 39R Connector Kit (010-11825-20) Item Backshell w/Hdw, Jackscrew, 9/15 pin Conn, Receptacle, d-Sub, Crimp Socket, Commercial, 9 CKT Contact, Sckt, Mil Crimp, size 20, 20-24 AWG Part Number 011-01855-00 330-00625-09 336-00022-02 Quantity 1 1 9 Table 1-6 Contents of GDL 5XR Connector Kit (010-12498-60) Item Backshell w/Hdw, Jackscrew, 15/26 pin Conn, Receptacle, d-Sub, Crimp Socket, Commercial, 15 CKT Contact, Sckt, Mil Crimp, size 20, 20-24 AWG Part Number 011-01855-01 330-00625-15 336-00022-02 Quantity 1 1 16 1.3.2 GPS/XM Antenna(s) A Garmin or non-Garmin GPS antenna is required for a G3X installation. A Garmin or non-Garmin XM antenna is required for G3X installations using SiriusXM® weather. See Section 20 for required materials for antenna installation including mounting brackets, doubler plates, rivets, hardware, cables, connectors, and sealant. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-3 1.4 Optional Garmin LRUs Table 1-7 lists optional Garmin LRUs that can be installed with the G3X system. If any of these LRUs are to be used in this installation, verify that all required installation materials such as connector kits have been acquired. Installation information for LRUs not documented in this manual can be found in the Installation Manual for each respective LRU. Table 1-7 Optional Garmin LRUs LRU All Install Info Included In This Manual? GAD 27 Flaps/Lights/Trim Controller Yes GAD 29 ARINC 429 Adapter Yes GAP 26 Air Data Probe Yes GDL 39/GDL 39R Data Link No GDL 5XR Data Link No GDU 37X* Display (if installing more than one) Yes GDU 45X* Display (if installing more than one) Yes GDU 46X* Display (if installing more than one) Yes GDU 470* Display (if installing more than one) Yes GEA 24 EIS Yes GHA 15 Yes GI 260 Yes GMC 305 Mode Controller Yes GMC 307 Mode Controller Yes GMC 507 Mode Controller Yes GMU 11 Magnetometer Yes GNSTM 4XX/5XX Avionics No GNS 480 GPS/Comm Navigator No GSA 28 Servo Actuator Yes GSU 25** ADAHRS Yes GSU 73** ADAHRS/EIS Yes GTNTM 6XX/7XX Avionics Units No GTR 20 Yes GTR 200 No *One GDU 37X or one GDU 4XX are required **One GSU 25 and/or GSU 73 is required Section Section 3 Section 4 Section 5 NA NA Appendix E Section 6 Section 6 Section 6 Section 7 Section 8 Section 9 Section 10 Section 11 Section 12 Section 13 NA NA Section 16 Section 17 Appendix F NA Section 19 NA 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-4 Table 1-7 Optional Garmin LRUs LRU All Install Info Included In This Manual? GTXTM Transponder No SL30 Nav/Comm Transceiver No SL40 Comm Transceiver No *One GDU 37X or one GDU 4XX are required **One GSU 25 and/or GSU 73 is required Section NA NA NA 1.5 Required non-Garmin Equipment The following items may be required for system installation. 1.5.1 Wiring/Cabling Considerations BNC/TNC Coaxial Connectors - May be required to terminate the antenna cable, depending upon which antenna is used. Check the antenna installation instructions for detailed information. Example below: · Connector, BNC/TNC Coaxial, male, crimp (MIL-PRF-39012) CAN Bus Wire - See Section 2.3.1.3.2 Cable Ties - (MS3367) or lacing cord A-A-52080 (MIL-T-43435) Cabling and Wiring: (all are provided by the installer unless otherwise noted) · MIL-W-22759/16 (or other approved wire) AWG #22 or larger wire for all connections unless otherwise specified. The supplied standard pin contacts are compatible with up to AWG #22 wire. · Shielded wire (MIL-C-27500 cable utilizing M22759/34 wire (SD) and ETFE jacket or MIL-C-27500 cable utilizing M22759/16 wire (TE) and ETFE jacket) · HSDB (Ethernet) connections may use either aviation grade Category 5 Ethernet cable, or MIL-C-27500 shielded twisted-pair cable. · RG-400 or RG-142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation. Circuit Breakers - Circuit breakers (MS26574), replaceable fuses, or other circuit protection devices, sized appropriately for the wire gauges used. Clamps (Adel Clamp) - Various sizes for routing new wiring in the engine cowl (MS21919WDGXX). Coaxial Cable, 50 - MIL-DTL-17 (i.e. RG-400) Current Shunts - Qualified to AA55524 Environmental Splice - AS81824/1-X (where X=size) or equivalent Fiberglass Sleeving - Qualified to MIL-I-3190/6 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-5 Flat or Tubular Braid: · 1/16" for the GMU (AA59569F36T0062, AA59569R36T0062, or equivalent) · 0.171" and to be round or tubular for fuel flow transducer overbraid if required (e.g. QQB575R36T171, AA59569R36N171, or equivalent). Fuse Holders - Qualified to MIL-PRF-19207 (FHN series holders) or GPN 330-01791-10 (P/O kit 330-01791-00) Fuses: Qualified to MIL-F-15160 size 3AG (i.e. F02A, F03A, F03B) Heat Shrink Tubing: (M23053/5, X=color) · M23053/5-104-X for single conductor wire · M23053/5-105-X for insulating twisted-pair wire · M23053/5-106-X for insulating triple conductor wire or RG-400 coax Heat Shrink Tubing, Self-Sealing - Qualified to AMS-DTL-23054/4: · P/N M23053/4-103 · Tyco P/N SCL-1/4-0-STK · Alpha wire FIT-300-1/4 Lamps, Master Warning/Caution Indicator: · MS25041-2 (red) · MS25041-4 (amber) · MS25237-327 (GE or JKL lamp number 327, 28VDC) · MS25237-330 (GE or JKL lamp number 330, 14VDC) Resistors: · 400k (±10%), 0.5W minimum resistors qualified to MIL-R-10509 or MIL-PRF-26 (i.e. RN70C4023BB14) · 1 k (±1%), 0.5W resistors qualified to MIL-R-10509 or MIL-PRF-26 (i.e. RN70C1001FRE5, RN65E1001FB14) · 390 (±5%), 0.25W minimum resistors qualified to MIL-R-10509 or MIL-PRF-26 (i.e. RN60D3900FB14, RN60D3920FB14, RN65C3900FB14). (For GMATM 245R Audio Panel) Ring Terminals - MS25036 or M7928 (for GAD 27) Shield Terminators: · AS83519/1-X, AS83519/2-X or equivalent · AS83519/X-2 for single conductor wire · AS83519/X-3 for twisted-pair and triple conductor wire · AS83519/X-4 for RG-400 coax Silicone Fusion Tape - A-A-59163 (MIL-I-46852C or equivalent) 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-6 Switches - Wig-wag installation, high current (>5A) MIL-DTL-3950 (i.e. Honeywell P/N 2TL1-10). Switches (GAP 26 installation): Conform to MIL-DTL-3950 (i.e. Honeywell P/N 1TL1-2) Thermocouple Extension Wire, K-type, or J-type Non-shielded: 150°C or higher - Stranded AWG 24-20, colored per ASTM E 230, and tested in accordance with at least one of the following STDS: · ASTM E 207 · ASTM E 220 · AMS 2750 (e.g. Watlow, SERV-RITE P/Ns K24-3-507 and J20-3-507) 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-7 1.5.2 Contact and Crimp Tools Table 1-8 lists recommended crimp tools used to build the wiring harnesses for the G3X LRUs, other equivalent tooling may also be used. Table 1-8 Pin Contact and Crimp Tools Part Numbers LRU Contact Type Garmin Contact Part Number Recommended Positioner Recommended Recommended Insertion/ Hand Extraction Tool Crimping Tool GDU 37X GDU 4XX GMC 305/ 307/507 GSU 73 GTP 59 011-00979-20 (Config module w/ EEPROM kit) 011-00981-00 (thermocouple kit) Socket, Size 20 Pin, Size 22D 336-00022-02 M22520/2-08, or 336-00094-00 Daniels K13-1 336-00021-00 (MIL P/N M39029/58-360) M22520/2-09 Positronic P/N 9502-4, Daniels P/N K42 GMU 22 Socket, Size 20 011-00979-22 (Config module w/ Sockets & Jackscrew kit) GAD 27/29 GEA 24 (J241, J243, J244) GMU 11 GSA 28 GSU 25 GTR 20/200 GAD 29 GEA 24 (J242 only) Socket, Size 20, 26-30 AWG Socket, Size 20, 20-24 AWG Pin, Size 20 GHA 15 Pin Size 22D 336-00022-00 (MIL P/N M39029/63-368) 336-00022-01 336-00022-02 336-00024-00 (MIL P/N M39029/64-369) 336-00051-00 (MIL P/N 39029/56-348) M22520/2-08, Daniels K13-1 M22520/2-08, Daniels K13-1 Use crimp setting 6 for 28 AWG M22520/2-08, Daniels K13-1 M22520/2-07 M22520/7-05 M81969/1-04 for size 22D pins and M81969/1-02 for size 20 pins M22520/2-01 NOTE Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice. 1.5.3 Hex Driver A 3/32" hex drive tool is required to secure the GDU to the panel as described in Appendix E.7.1 GDU 37X Unit Installation and Section 6.6.1 GDU 4XX Unit Installation. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-8 1.5.4 SD Card An SD Card is required to be used as a DataCard. Garmin recommends a 2 GB SanDisk® brand SD card for GDU 37X units, and an 8 GB SanDisk® brand SD card for GDU 4XX units. SD or SDHC cards up to 32 GB using the FAT32 file format are supported, SDXC and SDUC cards are not supported. See Appendix H.5.1, Section 30.5.1, and Section 31.3.1 for detailed information. 1.5.5 Non-Magnetic Tools (GMU Units) Use of non-magnetic tools (e.g. beryllium, copper, or titanium) is recommended when installing or servicing the GMU magnetometer. Do not use a screwdriver that contains a magnet when installing or servicing a magnetometer. 1.5.6 Pneumatic Hoses and Connectors Air hoses and fittings are required to connect pitot and static air to the ADAHRS (GSU 25/73). The ADAHRS (GSU 25/73) has a female 1/8-27 ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to pitot, static, and Angle of Attack (AOA on GSU 25 only) system lines. 1.5.7 GAD 27/GAD 29/GEA 24/GPS 20A/GSU 25 Mounting Hardware If the installer does not use the applicable installation kit, an example of alternate mounting hardware is: (4 ea.) #10-32 pan or hex head screws. 1.5.8 GAP 26 Mounting Hardware The materials listed in Table 1-9 are required to assemble and mount the GAP 26: Table 1-9 GAP 26 Mounting Hardware Quantity 4 2 2 2 Item Screw #6 Washer #6 Nut #6 4 Screw #8 4 Washer #8 4 Nut #8 Part Number MS51957-26 MS51957-32 NAS1149CN632R MS21044C06 MS24693-CXX (Countersunk) OR MS51957-XX (Pan Head) NAS1149CN832R MS21044C08 Notes Mount tube to probe Mount tube to mount bracket Mount bracket to inspection panel 1.5.9 GMU 11 Mounting Materials The following materials (or equivalents) required to install the GMU 11 in a non-metallic wingtip: · Tinned copper flat braid, 1/4", QQB575F36T0250 · Electrical tie-down strap, adjustable, MS3367- (1, 2, or 7)-X · Terminal lug, #10, uninsulated, MS25036-108 · Terminal stud, #10 · Terminal lug, #8, uninsulated, MS25036-153 1.5.10 GSU 73 Mounting Hardware An example of GSU 73 mounting hardware is: #10-32 pan or hex head screw (4 ea.) and #10-32 selflocking nut (4 ea). (see Appendix F.5.13) 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-9 1.6 Optional Garmin Equipment (non-LRU) 1.6.1 Optional GMU 22 Mounting Racks The Universal Mounting Rack is an optional mounting rack for the GMU 22, refer to the AHRS Magnetometer Installation Considerations (190-01051-00) document available from www.garmin.com. Refer to Appendix B for airframe specific GMU 22 mounting racks and related mounting hardware. 1.6.2 Antenna Brackets/Doubler Plates See Section 20 for detailed information. 1.6.3 Silicon Fusion Tape Garmin Part Number 249-00114-00 or similar, used to wrap the wiring/cable bundles. 1.7 Optional non-Garmin Equipment 1.7.1 Engine/Airframe Sensors See Section 21.1 for a list of compatible sensors, and Section 21.3 for a list of available sensor kits. 1.7.2 Mounting Hardware Some sensors may require a torque screwdriver, copper crush gasket, #10 screws, or #8 ring terminals for installation. 1.8 Optional 3rd Party Sensors/LRUs Refer to Section 26, Section 27, Section 28, and Section 29 for wiring/configuration guidance of supported third party equipment. 1.9 Garmin Software and Documents The below are available for free download from www.garmin.com. · AHRS Magnetometer Installation Considerations · Aviation Checklist Editor (ACE) software · Flightlog Conversion Software · GDU 37X Cockpit Display Unit Software · GDU 4XX Cockpit Display Unit Software · GSU 73 Data Logger Software · GSU 73 Field Calibration Tool · Panel Cut-out DXF Files (GDU 37X/4XX, GMC 30X) 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 1-10

INSTALLATION PREPARATION

This section provides electrical and mechanical information needed for planning the physical layout of the G3XTM avionics installation. This information is applicable to all items comprising the G3X installation. Each LRU/Sensor has unique installation requirements. These requirement are detailed in the Installation portion of Section 3 through Section 21 (and Appendix E and Appendix F for GDUTM 37X display, GSU 73 installations). Use all of Section 2 to become familiar with all aspects of the installation before actually beginning the physical installation of any equipment into the aircraft. Some information from this section is repeated in following sections of this document. Garmin recommends the installer become familiar with all sections of this document before beginning the installation. The sections of this document are (as much as possible) in the order that should be followed for most installations. In general terms, the below steps are recommended to be followed in order. 1. Inventory of all needed parts 2. Planning/layout of the installation 3. Installation of LRUs, antennas, and sensors 4. Construction of wiring harness, cables, and connectors 5. Software installation/configuration 6. Post-installation checkout procedure and calibration 2.1 System Overview NOTE G3X refers to both the legacy GDUTM 37X system and GDU 4XX systems. For items only applicable to the GDU 4XX systems, the system name is referred to as G3X TouchTM avionics. The G3X is an advanced technology avionics suite designed to integrate pilot/aircraft interaction into one central system. The system combines primary flight instrumentation, aircraft systems instrumentation, and navigational information, all displayed on one, two, three, four, five, or six displays. The G3X system is composed of several sub-units or Line Replaceable Units (LRUs). LRUs have a modular design and can be installed directly behind the instrument panel (or mounted to the panel in the case of a GDU display or GMC control panel) or in a separate avionics bay if desired. This design greatly eases troubleshooting and maintenance of the G3X system. A failure or problem can be isolated to a particular LRU, which can be replaced quickly and easily. Each LRU has a particular function, or set of functions, that contributes to the system's operation. For additional information on LRU functions, see the applicable section of this manual. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-1 2.1.1 System Architecture and Interface Capabilities The functionality of the G3X system is distributed between multiple interconnected devices, some of which are located in the instrument panel and some of which are remote-mounted elsewhere. An individual device in the G3X system is often referred to as a "Line Replaceable Unit", or LRU. This term is used generically in aviation for devices that can be readily "swapped out" for troubleshooting or repair. LRUs in the G3X system are interconnected with RS-232 interfaces and a shared CAN bus network (see Section 2.3.1.3). The G3X system can interface to a variety of other devices using RS-232 and ARINC 429 connections. GDL 39/5XR Traffic/Weather Receiver (optional) GI 275 (optional) RS-232 RS-232 GAP 26 Pitot/AOA (Optional) RS-232 Static Source GMU 22 Magnetometer RS-232/ GTP 59 RS-485 Temp Probe GMC 305/307 A/P Controller (Optional) GMU 11 GMA 245/245R Magnetometer Audio Panel (Optional) G5 Standby Flight Display (Optional) RS-232 Static GDU 4XX PFD1 Pitot AOA RS-232 (Optional) GSU 25 ADAHRS 1 GSU 25 GSU 25 GSA 28 GSA 28 ADAHRS 2 ADAHRS 3 Pitch Servo Yaw Servo (Optional) (Optional) (Optional) (Optional) GSA 28 GSA 28 GSA 28 Roll Servo (Optional) Pitch Trim Servo (Optional) Roll Trim Servo (Optional) RS-232 CAN BUS GAD 27 Elec System Controller (Optional) GI 260 AOA Indicator (Optional) GTR 20/200 COM Radio (Optional) GTR 20/200 COM Radio (Optional) RS-232 GAD 29(B) Data Concentrator (Optional) Third-party Digital Autopilot (Optional) GTX GDU 4XX GDU 4XX GDU 4XX GDU 4XX GDU 4XX Transponder PFD2 PFD3 MFD3 MFD2 MFD1 (Optional) (Optional) (Optional) (Optional) (Optional) (Optional) GPS 20A Position Source (Optional) GMC 507 A/P Controller (Optional) GHA 15 RAGL (Optional) A429 (NAV) A429 (GPS) A429 (Air Data) RS-232 (ADS-B) RS-232 (GPS/COM) RS-232 (Connext) No. 1 GPS/Com (Optional*) RS-232 GEA 24 GEA 24 Engine Analyzer Engine Analyzer (Optional) (Optional) Engine #1/ Airframe Sensors Engine #2 Sensors A429 (NAV) A429 (GPS) Analog Output From GAD 29B Only A429 (Autopilot) Third-party Analog Autopilot (Optional) No. 2 GPS/Com (Optional*) RS-232 GARMIN COM OR NAV/COM (Optional*) Notes: *Maximum of two (2) COM/NAV units installed. Figure 2-1 G3X Interconnect Example (GDU 4XX) 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-2 2.1.1.1 Displays The foundation of a G3X system is one or more GDU display units. A GDU display is configured with wiring connections as either a primary flight display (PFD) or multi-function display (MFD), with options for arranging display layouts and combining different types of data on a single display. In the event that power is removed from a GDU display, important flight data can still be accessed on the remaining display(s). A legacy (non-Touch) G3X system can have between one and three GDU 37X displays. Figure E-2 shows some of the various interface options for a GDU 37X-based system. For GDU 37X installation information, refer to Appendix E. A G3X Touch system can have between one and six GDU 4XX displays, with any combination of 10.6" (GDU 46X) and 7" (GDU 45X or GDU 470) display sizes. Figure 2-1 shows some of the various interface options for a GDU 4XX-based system. For GDU 4XX installation information, refer to Section 6. NOTE GDU 37X and GDU 4XX displays may not be combined in the same system. A G3X system can have up to two G5 standby flight displays. For G5 installation information, refer to the G5 installation manual (190-02072-01). GDU displays communicate with other LRUs using the CAN bus (with optional RS-232 backup paths supported for some LRUs) and with other devices using RS-232. A G3X Touch system installed with no ADAHRS units can display MFD data, including engine information, on up to six GDU 4XX displays. This system configuration can also support Garmin autopilot functionality when paired with one or more G5 flight displays. A single GDU display, installed without any other G3X system components, may be configured as a standalone MFD. A standalone GDU 37X MFD does not support flight or engine instruments, or advanced interface capabilities, and is intended for applications where only basic mapping and navigation features are required. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-3 2.1.1.2 ADAHRS The GSU 25 is the ADAHRS (air data, attitude, and heading reference system) unit for the G3X system. An ADAHRS senses the aircraft's attitude, measures all air data parameters, and calculates aircraft heading. Up to three ADAHRS units are supported. In a system with multiple GDU displays and multiple ADAHRS units, each display can present data from a separate ADAHRS, and any GDU display may also be switched to display data from any ADAHRS. Data from multiple ADAHRS units is also automatically crosscompared, and disagreements are noted on the PFD display. Each GSU 25 ADAHRS is connected to pneumatic pressure inputs for pitot, static, and angle of attack (AOA). Connection of the AOA input is only required for GSU 25 #1, and is optional for GSU 25 #2 and #3. For aircraft capable of indicated airspeeds greater than 300 knots, the GSU 25D is used. The GSU 25 communicates with other LRUs using the CAN bus, and can optionally be connected to the PFD1 GDU using RS-232 for redundancy. For GSU 25 installation information, refer to Section 17 and Section 24. The older GSU 73 ADAHRS is also supported. The GSU 73 does not provide AOA data, but a system that includes a GSU 73 may also include additional GSU 25 units. For GSU 73 installation information, refer to Appendix F and Appendix G. In a system installed with one or more dedicated ADAHRS units and one or more G5 standby flight displays, attitude and air data from the G5 will also be displayed on the GDU displays, in the event that valid data is not available from any dedicated ADAHRS unit. In a G3X Touch system installed with no dedicated ADAHRS units, attitude and air data from the G5 will be used throughout the system, including for autopilot functionality, but will not be visible on the GDU 4XX displays. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-4 2.1.1.3 Magnetometer The G3X system requires a minimum of one magnetometer (magnetic field sensor) to provide the ADAHRS unit(s) and/or G5 standby display(s) with magnetic field information. In an installation with multiple ADAHRS units, magnetometer data is shared by the CAN bus. When multiple ADAHRS units are installed, additional magnetometers may be installed for redundancy, although this is not commonly done. In a G3X Touch system with a G5 but no ADAHRS units, only a single magnetometer is supported. Several different magnetometers are supported: The GMU 11 magnetometer connects to the G3X system using the CAN bus. Refer to Section 13 for GMU 11 installation information. The GSU 73 does not support the GMU 11. The GMU 22 magnetometer connects to the ADAHRS LRU using RS-232 and RS-485 interfaces. Refer to Section 14 for GMU 22 installation information. The GMU 44 is also supported and is functionally identical to the GMU 22. Refer to Appendix B for magnetometer placement information. 2.1.1.4 Outside Air Temperature The outside air temperature (OAT) probe used in the G3X system is the GTP 59. A minimum of one OAT probe is required, and is connected to the #1 ADAHRS. In an installation with multiple ADAHRS units, air temperature data is shared by the CAN bus. Additional OAT probes may be connected to the other ADAHRS LRUs for redundancy, although this is not commonly done. Refer to Section 18 for GTP 59 installation information. In a G3X Touch system with one or more G5 displays but no ADAHRS units, a GTP 59 can optionally be connected by the GAD 13 temperature probe adapter. If the system is later expanded with the addition of one or more ADAHRS units, the GAD 13 may be retained, or the GAD 13 may be removed and the GTP 59 connected to the #1 GSU 25 ADAHRS unit. Refer to the G5 installation manual (190-02072-01) for GAD 13 information. 2.1.1.5 Pitot/Static The ADAHRS units (and optional G5 displays) in the G3X system must be connected to the aircraft's pitot/static system. The airframe manufacturer's guidance should be followed to find the proper location of the pitot tube and static port. The GAP 26 pitot/AOA probe is a combination pitot tube and angle of attack (AOA) probe. It is available in several configurations, including heated and unheated versions. Refer to Section 5 for GAP 26 installation information. G3X ADAHRS units and G5 displays may also be used with any other pitot tube, if AOA is not required. Refer to Section 32 for information on conducting periodic tests of the static system. 2.1.1.6 Angle of Attack The G3X system is capable of sensing and displaying the aircraft's current angle of attack (AOA) when installed with a GSU 25 ADAHRS and a GAP 26 pitot/AOA probe. The GDU displays present on-screen AOA information, and also generate AOA audio alerts. The optional GI 260 AOA indicator can also be added to provide a separate heads-up indication of AOA. Refer to Section 9 for GI 260 installation information. The angle of attack sensor can be calibrated to compensate for flap position, which requires either a flap position sensor or a dedicated discrete input. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-5 2.1.1.7 Engine Information The G3X system includes highly flexible capabilities for monitoring numerous engine sensors and parameters, and can support most piston and turbine engines, including twin-engine installations. Airframe sensors such as voltage, fuel quantity, and discrete (switch/contact) inputs are also supported. Refer to Section 21 for engine application and sensor installation information, and Section 26, Section 27, Section 28, and Section 29 for engine/airframe sensor wiring information. The engine information system (EIS) unit for the G3X system is the GEATM 24 engine interface module. The GEA 24 provides the ability to monitor numerous analog, digital, and discrete signals from a variety of engine and airframe sensors. Multiple GEA 24 units may be installed in order to monitor large piston engines, or for twin-engine applications. The GEA 24 also supports a digital interface to a number of FADEC (Full Authority Digital Engine Control) engines. The GEA 24 communicates with other LRUs using the CAN bus, and can optionally be connected to the MFD GDU by RS-232 for redundancy. For GEA 24 installation information, refer to Section 7. For information on EIS sensor configuration and calibration, refer to Appendix H or Section 30. If replacing a GEA 24 with a GEA 24B, please review the guidance in Section 32.2.5. The GSU 73 also supports EIS inputs. Alternatively, a system that includes a GSU 73 may instead use a GEA 24 for EIS, if the GEA 24 is wired as EIS LRU #2. The GEA 24 and GSU 73 can drive external annunciator lamps for Master Caution and Master Warning, to provide additional notification of abnormal engine indications. Refer to Section 23 for information on connecting annunciator lamps to GEA 24 or GSU 73 discrete output pins. 2.1.1.8 GPS Each GDU display includes an internal VFR GPS receiver, and a connection for an external antenna. GPS position data is shared between GDU displays using the CAN bus. For a list of GPS antennas supported by the GDU display, refer to Appendix E, or Section 6. The GPS 20A is a TSO-compliant WAAS GPS position source that is compatible with the G3X system. The GPS 20A provides GPS data to the G3X system using the CAN bus, and can send ADS-B position data to a transponder using RS-232. For GPS 20A installation information and a list of supported GPS antennas, refer to Section 15. GPS data is used for ADAHRS performance monitoring, so at least one source of GPS data is required. This requirement can be met by installing a GPS 20A, or by connecting a GPS antenna to at least one GDU GPS receiver. A GTX Series Transponder with built-in GPS, or a GNX 375 connected to the system will also satisfy this requirement. In a system with multiple GDU displays, additional GPS antennas may be connected to the other displays for redundancy, if desired. The G3X system is capable of displaying basic position data from an external IFR GPS navigator, but this data is not used for ADAHRS monitoring and thus does not satisfy the above requirement. For general GPS antenna installation information, refer to Section 20. 2.1.1.9 ARINC 429 ARINC 429 is an industry-standard data bus format that is primarily used with IFR GPS or GPS/NAV receivers (see below). The GAD 29 is the primary ARINC 429 data adapter for the G3X system; the GSU 73 also supports ARINC 429 input/output. ARINC 429 data is relayed to and from the rest of the G3X system using the CAN bus. For GAD 29 installation information, refer to Section 4. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-6 2.1.1.10 Navigation Basic VFR GPS navigation with the G3X system is performed by the GDU displays, using their internal navigation databases in conjunction with GPS data from GDU GPS receivers or the GPS 20A. Flight plan entry and modification is also performed using the GDU displays. For VFR operations, no other source of navigation data is required. The G3X system also supports up to two external navigation sources. Supported external navigation sources include IFR GPS, VHF NAV, and GPS/NAV receivers. Lateral and vertical deviation (CDI/VDI) and status data from external navigators is displayed on the GDU displays, as well as external GPS navigator flight plan information. On-screen controls allow switching the current source of navigation data between multiple external sources, as well as to the G3X system's internal flight plan for VFR navigation. The Garmin GNC® 355 radio, GNSTM 4XX/5XX receiver, GNXTM 375 IFR navigator, GPS 175, and GTNTM 6XX/7XX moving map navigators are supported by the G3X system, including WAAS approach capability. This integration requires the use of a GAD 29 ARINC 429 interface module. GPS navigation data is provided to the G3X system through one RS-232 input and one ARINC 429 input for each GNC 355, GNS 4XX/5XX, GNX 375, GPS 175, and GTN 6XX/7XX IFR GPS navigator unit. The G3X system sends flight data and selected course information back to the external GPS navigator through an ARINC 429 output. The G3X system uses an additional ARINC 429 input to receive VOR, localizer, and glideslope deviation information from a Garmin GTN 650/750 or GNS 430/480/530 IFR GPS/NAV receiver. VOR, localizer, and glideslope information from a Garmin GNC 255, GNC 215, or SL30 VHF NAV receiver is also supported. These radios connect to the G3X system using an RS-232 connection to a GDU display. When two external navigation sources are connected to the G3X system, the determination of which source is #1 and which is #2 is determined by the ordering of the RS-232 connections to the GDU displays. The #1 navigation source should be connected to a lower-numbered RS-232 port on the PFD1 GDU, and the #2 navigation source should be connected either to a higher-numbered RS-232 port on the PFD1 GDU, or to any RS-232 port on the MFD1 GDU. For additional information, refer to Section 2.5.1. The G3X Touch system can send basic flight plan data to a GNC 355, GNS 4XX/5XX, GNX 375, GPS 175, or GTN 6XX/7XX IFR GPS navigator, allowing VFR flight plans to be created on the G3X system and uploaded to the IFR navigator. The GDU 4XX display in a G3X Touch system can also act as a relay between the GNC 355, GNS 4XX/5XX, GNX 375, GPS 175, and GTN 6XX/7XX IFR GPS navigator and a tablet computer using Bluetooth (see Section 2.1.1.23). Flight plan transfer capability requires a second RS-232 connection between the PFD1 GDU and the #1 GNC 355, GNS 4XX/5XX, GNX 375, GPS 175, or GTN 6XX/7XX IFR GPS navigator, using the "Connext®" RS-232 format. The Connext® computer application and Bluetooth are not supported by the legacy G3X system and GDU 37X display. If a G5 standby display instrument is installed, data from the external navigation source selected on the G3X PFD is also displayed on the G5. This requires an ARINC 429 connection between the navigator, GAD 29, and G5. For detailed information on connecting external navigators to a G3X system, refer to Section 24. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-7 2.1.1.11 COM Radios The G3X Touch system is capable of displaying and controlling up to two VHF COM radios. Supported COM radios include: · GNC 215 · GNC 355 · GTR 20 · GTR 205 · SL30 · GNC 255 (software version 2.10 or later) · GTN 635/650/750 (software version 6.11 or later) · GTR 200/200B · GTR 225 (software version 2.10 or later) · SL40 Supported Garmin panel-mount COM radios can be controlled either using the GDU displays or through their own front-panel controls. The GTR 20 is a remote-mounted COM radio that is entirely controlled by the G3X Touch display, with no front-panel interface. For GTR 20 installation information, refer to Section 19 and Section 25. The interface between the G3X Touch system and the COM radio portion of a GTN, GNC 255, GNC 215, or SL30 uses the same RS-232 connection described above for navigation data. Interface to a GTR 205 or SL40 COM radio requires a dedicated RS-232 connection to a GDU display. The GTR 20 and GTR 200 connect to the G3X Touch system through the CAN bus. For information on connecting and configuring COM radios with the G3X Touch system, refer to Section 24 and Section 30. The legacy G3X system and GDU 37X displays do not support on-screen display or control of COM radios, and are not compatible with the GTR 20. However, GDU 37X displays do have the ability to send a COM frequency using RS-232 to the standby position of connected radio. 2.1.1.12 NAV Radios NAV Tuning The G3X Touch system is capable of displaying and controlling up to two VHF NAV radios. Supported NAV radios include: · GNC 215 · GNC 255 (software version 2.20 or later) · GTN 650/750 (software version 6.70 or later) · SL30 Supported Garmin panel-mount NAV radios can be controlled either by the GDU displays or through their own front-panel controls. The interface between the G3X Touch system and the NAV radio portion of a GTN, GNC 255, or SL30 uses the same RS-232 connection described above for navigation data. For information on connecting and configuring NAV radios with the G3X Touch system, refer to Section 30.4.28. The legacy G3X system and GDU 37X displays do not support on-screen display or control of NAV radios. However, GDU 37X displays do have the ability to send a NAV frequency by RS-232 to the standby position of a connected radio. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-8 2.1.1.13 ADS-B When equipped with a Mode S transponder with extended squitter capability, and a GPS position source that meets TSO performance requirements, the G3X system provides full ADS-B Out capability. Refer to Section 2.1.1.14 for additional information. The G3X system also supports full ADS-B In capabilities, including FIS-B weather and dual-frequency traffic data reception. In a legacy G3X system with GDU 37X displays, ADS-B In is provided by the GDL® 39R data transceiver. A G3X Touch system with GDU 4XX displays supports ADS-B In using the GTXTM 45R/345/345R transponder, the GDL 39R, or the GDL 52R. For additional information on interfacing a transponder to the G3X Touch system, see Section 2.1.1.14. For information on interfacing a GDL 39R or GDL 52R ADS-B receiver, see the appropriate installation guide (190-11110-00 or 190-02087-10). 2.1.1.14 Transponder The G3X system can interface to any Garmin transponder with a digital interface (all models except the GTX 320). The transponder code, operating mode, and flight ID can all be displayed and controlled using the GDU displays. A panel-mount transponder such as the GNX 375, GTX 327, 328, 330, 335 and 345 can be controlled either from the GDU displays or by the transponder's front-panel interface. Remote-mount transponders such as the GTX 23ES, 32, 33, 35R/45R and GTX 335R/345R lack front-panel controls, and are controlled only using the GDU displays. The diversity GTX 345D, GTX 335D, GTX 335RD, and GTX 345RD are all supported. The transponder connects using RS-232 to the #1 ADAHRS unit, which relays transponder data to the rest of the G3X system through the CAN bus. The ADAHRS provides pressure altitude data to the transponder, so a separate altitude encoder is not required. A second connection from the transponder to the #2 ADAHRS can be made to provide a backup datapath for this information. In a G3X system with a transponder and a GTN, the transponder is typically controlled by the G3X system, not the GTN. Note the GTX 23ES and GTX 35R/45R can only be controlled by the G3X system, not by the GTN. The GTX 23ES, 33ES, 35R, 45R, 330ES, 335/335R/335D/335RD, and GTX 345/345R/345D/345RD are Mode S transponders with extended squitter capability. When provided with a GPS position source that meets the TSO performance requirements specified in 14 CFR 91.227, these transponders are an acceptable method of complying with the requirements for ADS-B Out. Compliant GPS position sources include the GPS 20A, GTN, GNS WAAS units, or the internal WAAS GPS contained in certain models of the GTX 335/345. The GDU GPS receiver does not meet the TSO GPS requirements, thus it is not sufficient to provide position data to a transponder for ADS-B Out compliance. Certain transponders support ADS-B or TIS-A traffic data, and/or FIS-B weather data. See below for information on traffic (Section 2.1.1.17) and weather (Section 2.1.1.16) interface capabilities. For information on connecting and configuring a transponder with the G3X system, refer to Section 24 and Appendix H or Section 30. Refer to Section 32 for information on performing periodic tests of the transponder. For information on installing remote transponders, refer to 190-00906-01 for the GTX 23ES, or 190-01499-10 for the GTX 35R/45R. For all other transponders, refer to the appropriate installation manual. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-9 2.1.1.15 Autopilot The GFC 500X is an advanced digital flight director and autopilot, based around the GSA 28 smart autopilot servo. Servo installation kits are available for numerous popular aircraft, and universal installation brackets are available for other aircraft. Up to five GSA 28 servos are supported (pitch, roll, yaw damper, pitch trim, and roll trim). GSA 28 servos can optionally control aircraft electric trim motors; this keeps the aircraft in trim when the autopilot is engaged, and also provides trim motor speed control and stuck-switch protection when hand-flying. The GSA 28 can also be used as the trim actuator in the pitch and roll axes. The GSA 28 servos also support enhanced stability and protection features (ESPTM corrective technology) which increase safety when hand-flying. For GSA 28 installation information, refer to Section 16 and Section 24. For GFC 500X autopilot and ESP setup and adjustment information, refer to Appendix H or Section 30. Refer to the G3X Pilot's Guide or G3X Touch Pilot's Guide for information on GFC 500X autopilot and flight director operation. The GMC mode control panels are a family of optional accessories that provide a convenient set of dedicated controls for the GFC 500X autopilot and flight director. A GFC 500X autopilot installation with a GMC mode control panel also has increased redundancy, allowing control of basic autopilot modes using the GMC even when power is removed from all GDU displays. The GMC 307 supports all the features of the GMC 305, and adds dedicated control knobs for heading and altitude. Autopilot operation in a reversionary condition without operational GDU displays is provided by an RS-232 connection from the GMC 305/307 to the GSA 28 roll servo. For GMC 305/307 installation information, refer to sections Section 10 and Section 11. The GMC 507 is physically similar to the GMC 307, but it connects to the G3X system through the shared CAN bus. Up to two GMC 507 Mode Control panels can be installed. The GMC 507 adds an additional flight director mode button. For GMC 507 installation information, refer to section Section 12. In a G3X Touch system with GDU 4XX displays and one or more ADAHRS units, all autopilot and flight director functions can be controlled either from the GDU display or the optional GMC control panel. Refer to the G3X Touch Pilot's Guide (190-01754-00) for more information. In a G3X Touch system with no ADAHRS units, one or more G5 displays and a GMC control panel are required for autopilot and flight director operation using the G5. Refer to the G5 Pilot's Guide (190-02072-00) for more information. In a legacy G3X system with GDU 37X displays, a GMC control panel is required to enable certain advanced flight director modes; refer to the G3X Pilot's Guide (190-01115-00) for more information. Certain third-party autopilots that are designed to be integrated with the G3X system may also be used in conjunction with the G3X flight director and GMC control panel. Consult the third-party autopilot manufacturer for further information. Third-party digital autopilots that are not integrated with the G3X system are typically connected either through a GDU display RS-232 output that provides NMEA 0183 format data, or through various connections to a GTN/GNS navigator. Consult the autopilot manufacturer for further information. The GAD 29B can provide analog heading and course error outputs to non-Garmin analog autopilots. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-10 2.1.1.16 Weather Data The G3X system supports a variety of airborne weather data sources: FIS-B weather data can be provided to GDU displays from a GDL 39R remote-mounted ADS-B receiver. The GDL 39R can be connected to a single GDU display using RS-232. In a G3X Touch system, the GDL 39R may also be connected to additional GDU 4XX displays wirelessly using Bluetooth. A G3X Touch system with GDU 4XX displays can receive FIS-B weather data from GTX 45R, and GTX 345/345R transponders through an RS-232 connection from the GTX to each GDU display. These transponders can also simultaneously provide FIS-B weather data to a GTN or GNS WAAS navigator. The legacy G3X system with GDU 37X displays does not support FIS-B weather data from GTX transponders. The GDU 3X5 and GDU 4X5 displays contain a built-in XM satellite weather receiver. These displays require a separate antenna connection and active XM subscription in order to receive satellite weather data. For XM antenna installation information, refer to Section 20. A G3X Touch system with GDU 4XX displays is also compatible with the GDL 51R SXM receiver and the GDL 52R dual ADS-B/SXM receiver. The GDL 51R/52R connect to each GDU 4XX display using an RS-232 connection, or wirelessly through Bluetooth. A WX-500 or similar lightning detector can be used with the G3X Touch system using an RS-232 connection to a GDU 4XX display. The G3X system displays lightning strike or cell data and provides heading data output to the lightning detector. For any of the above data sources, weather data is displayed only on the GDU displays that are connected to the weather source (either by an RS-232 connection, wirelessly through Bluetooth, or from an internal XM receiver). Weather data is not shared between GDU displays through the CAN bus. On a GDU display that has access to multiple sources of weather data simultaneously, the pilot may switch between available weather sources at any time. When connected to a FIS-B weather receiver, the GDU 4XX can receive METARs, TAFs, Winds aloft, NEXRAD, TFRs, AIRMETs, SIGMETs, PIREPs, NOTAMs, Cloud Tops Forecast, Icing Forecast, Lightning, and Turbulence Forecast over either an RS-232 or Bluetooth connection. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-11 2.1.1.17 Traffic The G3X system supports a variety of airborne traffic data sources: ADS-B traffic data can be provided by a GDL 39R receiver using the same connection method used for FIS-B weather data. A G3X Touch system with GDU 4XX displays can receive traffic data from a GDL 52R dual ADS-B/ SXM receiver through the same connection method used for FIS-B weather data. A G3X Touch system with GDU 4XX displays can receive ADS-B traffic data from GTX 45R and GTX 345/345R transponders using the same RS-232 connection used for FIS-B weather data. These transponders can also simultaneously provide ADS-B traffic data to a GTN or GNS WAAS navigator. The legacy G3X system with GDU 37X displays does not support ADS-B traffic data from GTX transponders. The GTSTM 8XX traffic system is compatible with the G3X system. The GTS interface to the G3X system requires an RS-232 connection to a GDU display. TCAS-capable GTS 8XX units also require a separate data connection to the GTX transponder. TIS-A traffic data can be provided by GTX 23ES, 33, 330, and GTX 335/335R transponders. Traffic data is provided to the G3X system using the CAN bus from the #1 ADAHRS unit, to which the transponder is connected. Traffic data from various third-party devices that emulate the Garmin TIS-A format is supported using an RS-232 connection from the traffic device to a GDU display. For any of the above data sources, traffic data is shared between GDU displays using the CAN bus. If multiple sources of traffic data are available, the best source is selected automatically. Refer to the Pilot's Guide for further information on traffic data source selection. In an installation that includes a GTN/GNS navigator and transponder with ADS-B or TIS-A traffic capability, traffic data is provided to the GTN/GNS through an ARINC 429 or HSDB (High Speed Data Bus) connection. For further information, refer to Section 24 and the transponder installation manual. 2.1.1.18 Electrical System The G3X system supports a variety of connections to the aircraft's electrical system: Most important LRUs support dual power inputs, allowing them to be powered from separate dual electrical busses. Alternatively, one of the power inputs may be connected to a backup battery to provide adequate electrical power supply in the event of alternator failure, or during engine start. Backup batteries designed for the G3X system are available from third-party suppliers, or a backup battery can be integrated into the aircraft's electrical system design in order to power additional devices. In a G3X Touch system with GDU 4XX displays, the GAD 27 electrical control system provides lowvoltage protection during engine start, as well as control of the flaps, trim, external lighting, and cockpit lights. The GAD 27 is not compatible with legacy G3X systems that use GDU 37X displays. For further GAD 27 installation information, refer to Section 3 and Section 24. If the aircraft is equipped with a cockpit light dimming system, the GDU displays and various other Garmin panel-mount avionics support connection to the dimming bus to control display brightness. The G3X system is compatible with Vertical Power products through an RS-232 connection to a GDU display. For further information on interfacing Vertical Power products to the G3X system, consult the manufacturer. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-12 2.1.1.19 Audio The G3X system interacts with the aircraft's audio system in the following ways: · Audio alerts are generated by the GDU displays for various events, including audio notification of abnormal conditions. Typically, alert audio from the PFD1 GDU is wired to the aircraft's audio panel or intercom. · Stereo audio for XM music is provided by the GDU 3X5 and GDU 4X5 displays, and can be connected to any stereo audio panel or intercom. · A G3X Touch system with GDU 4XX displays may be connected using the CAN bus to the GMATM 245/245R audio panel, allowing full control of audio panel functionality from the GDU display. The GMA 245 is a panel-mounted digital audio panel with intercom and Bluetooth input; the GMA 245R has the same capabilities but is remote-mounted with no front-panel controls. For further information, refer to Section 30.4.25, the GMA 245/245R Pilot's Guide (190-01879-10), and Installation Manual (190-01879-11). · The GTR 20 and GTR 200 COM radios contain a built-in two-place intercom with alert audio and stereo music inputs. For simple two-place VFR aircraft, the GTR 20 or GTR 200 can provide all audio functionality, with no separate audio panel required. For installations with more complex audio switching requirements, including multiple COM radios, NAV radios, or 4+ seat aircraft, a separate audio panel is recommended. 2.1.1.20 Video In a G3X Touch system with GDU 4XX displays, each display has a rear connector which supports composite (NTSC/PAL/SECAM) video. Video input to a GDU 4XX display can be used with various cameras or entertainment systems, with the video image displayed on a dedicated MFD page, or in an inset window on the GDU 46X PFD. Wireless remote control of Garmin VIRB® action cameras is also supported, allowing recording to be started or stopped from the GDU 4XX display. 2.1.1.21 Carbon Monoxide Detector A CO Guardian or other compatible carbon monoxide detector can be connected to a GDU display using RS-232, and its data relayed to other displays through the CAN bus. Alerts will appear on the PFD display for excessive carbon monoxide levels, and the current CO level can be displayed in a data field. Cabin Altitude as determined by a CO Guardian can be displayed in a data field. CO detectors with pulse oximeter functions are also supported. For installation information, consult the CO detector manufacturer. 2.1.1.22 Emergency Locator Transmitter (ELT) The G3X system can provide NMEA 0183 formatted GPS position data to an ELT through an RS-232 output from a GDU display. In an installation with a GTN/GNS navigator, an RS-232 output from the IFR GPS using the "Aviation" data format may be preferred. For further ELT interface guidance, consult the ELT manufacturer. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-13 2.1.1.23 Bluetooth The GDU 4XX displays in a G3X Touch system include Bluetooth transceivers. This allows a wireless connection to a tablet computer, using Garmin PilotTM app or another application that supports the Garmin Connext protocol. The tablet computer can receive GPS position and attitude data from the G3X Touch system, and can exchange flight plan information with the GDU 4XX or with a connected GTN navigator. In an installation with multiple GDU 4XX displays, the Bluetooth connection to the tablet computer should be made to the PFD1 GDU only. Refer to the G3X Touch Pilot's Guide (190-01754-00) for Bluetooth connection information. A tablet computer can also establish a separate Bluetooth connection to a GDL 39R/51R/52R ADS-B receiver, or to a GTX 45R/345/345R transponder. This allows the display of ADS-B traffic and weather data on the tablet computer, using Garmin Pilot or another application that supports the Garmin Connext protocol. In a G3X Touch system with a GDL 39R ADS-B receiver, the primary connection between the GDL and a single GDU 4XX display is through RS-232. However, Bluetooth may also be used to connect additional GDU 4XX displays to the GDL 39R, in order to view FIS-B weather data on multiple displays. 2.1.1.24 Standby Instruments Although there is no regulatory requirement to equip the aircraft with backup flight instruments, Garmin strongly recommends the installation of backup instruments for aircraft that will be flown in other than Day VFR conditions. In case of an electrical system failure, or in the unlikely event of an issue with the G3X system, backup instruments should at minimum provide a secondary reference for aircraft attitude, airspeed, and altitude. The G5 standby flight display is designed as a complementary backup instrument for the G3X system. It features dissimilar hardware and software design to eliminate common-mode failures, supports an optional built-in backup battery, and synchronizes data such as baro setting and selected heading with the G3X system. In conjunction with a GMC mode control panel, the G5 is also capable of driving the GSA 28 autopilot servos even if power is removed from all GDU displays. A G3X Touch system with no ADAHRS units can also operate the GSA 28 autopilot servos if a G5 and a GMC mode control panel are present. For further information, refer to the G5 installation/operation manual (190-02072-00). The GI 275 is also capable of being installed as a standby flight display with GDU 4XX systems. The altitude bug, heading track bug, and barometric setting are synced between the two displays. The G3X Touch syncs course, minimum's bug, CDI selection, and VFR GPS guidance to the GI 275, in addition to sending OAT and magnetic heading to the GI 275. A connection can optionally be made from the GSU 25 serial port to the GI 275, to facilitate comparison between the two ADAHRS sources to notify the pilot of a disagreement in attitude, altitude or airspeed. Unlike the G5, the GI 275 cannot act as a backup flight director when installed alongside a G3X Touch system in the case of a primary display failure. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-14 2.1.1.25 Smart GlideTM Engine-Out Navigation Smart Glide is designed to assist the pilot by enhancing situational awareness and providing helpful automation during an emergency inoperative engine event. The G3X Touch is capable of providing this assistance internally, without the need for an external navigator. Upon activation, Smart Glide assists the pilot with three critical components of a safe recovery from an engine failure: · If equipped with a compatible autopilot, provides flight director guidance to pitch for and hold best glide airspeed · Identifies and provides navigation guidance, as well as optional flight director guidance to a suitable landing location (if one is available) · Provides quick access to relevant communication channels and emergency checklists When GSA 28 Smart Autopilot servos or other compatible autopilot is installed, the autopilot automatically couples to the flight director guidance provided by Smart Glide, if sufficient altitude is available. An optional discrete input can be programmed to provide a dedicated external panel mounted switch for Glide Activation (Garmin p/n 011-05930-00). 2.1.1.26 Radar Altimeter and Radio AGL Knowing precise height above the ground can be helpful to pilots during landings and flying in areas where limited barometric altimeter setting information is available. The Garmin GHA 15 uses radar technology to provide height above ground level (RAGL) information for the G3X Touch. GHA 15 AGL data is available up to 500 feet AGL. Alternatively, the G3X Touch system can receive Radar Altimeter AGL data from a connected radar altimeter unit via ARINC 429. Audible alerts based on radio AGL or radar altitude can be configured beginning at 300 feet AGL, and at select intervals down to 1 foot AGL 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-15 2.2 Electrical Considerations This section presents information required for planning the electrical layout of the G3X installation. CAUTION To avoid damage to the LRUs, take precautions to prevent Electro-Static Discharge (ESD) when handling connectors and associated wiring. ESD damage can be prevented by touching an object that is of the same electrical potential as the LRU before handling the LRU itself. 2.2.1 Power Specifications All G3X LRUs are capable of operating at either 14 or 28 VDC (except the GAD 27 which is 14 VDC only, and the GAP 26, see Note in Section 5). Table 2-1 and Table 2-2 list supply voltage and current draw info for the G3X LRUs, use this information when determining power supply requirements. All installed electrical appliances must be considered when determining total power requirements. 2.2.1.1 GAP 26 Power Requirements The 010-01074-00 version of the GAP 26 does not require power as it does not have a heater. The initial current vs temperature requirements for the 010-01074-10 and 010-01074-20 are listed in Table 2-1. See Section 5.5.2 for acceptable wiring configurations. CAUTION Do not connect the heated/regulated version of the GAP 26 (010-01074-20) to 28 VDC. The heated/non-regulated version of the GAP 26 (010-01074-10) may be connected to either 14V or 28V. See Section 5 for wiring information. Table 2-1 GAP 26 Initial Current Draw vs Probe Temperature (-10, -20 units only) Probe Temperature Amps -40°C (-40°F) 0°C (32°F) 12 Amp 9.25 Amp 50°C (122°F) 7.3 Amp 100°C (212°F) 175°C (347°F) 5.85 Amp 4.36 Amp Table 2-1 refers to probe temperature at initial turn-on. For example, upon turn-on at -40°C, the standard (-10) or regulated (-20) heated probes will initially draw 12 amps, but will draw less current as they warm up. The -10 non-regulated probe draws current proportional to the probe temperature as shown in Table 2-1. The -20 heated regulated probe uses similar power to the -10 probe when airborne, but will limit the current to regulate the probe temperature to ~75°C (167°F) when the probe temperature reaches this value. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-16 2.2.1.2 Other LRU Power Requirements Table 2-2 G3X LRU Power Requirements LRU Supply Voltage Current Draw GAD 27 14 Vdc 28 Vdc 0.2 Amp (varies with connected devices) Not supported, do not use in 28V installations GAD 29 14 Vdc 28 Vdc 0.2 Amp 0.1 Amp GDL 39/39R 14 Vdc 28 Vdc 0.25 Amp 0.125 Amp GDL 51R 14 Vdc 28 Vdc 0.16 Amp 0.09 Amp GDL 52R 14 Vdc 28 Vdc 0.29 Amp 0.15 Amp GDU 37X** 14 Vdc 28 Vdc 1.10 Amp 0.540 Amp GDU 45X** 14 Vdc 28 Vdc 1.25 Amp 0.7 Amp GDU 46X** 14 Vdc 28 Vdc 2.0 Amp 1.0 Amp GDU 470** 14 Vdc 28 Vdc 1.25 Amp 0.7 Amp GEA 24 14 Vdc 28 Vdc 0.43 Amp max (typical external sensor loading) 0.21 Amp max (typical external sensor loading) GHA 15 14 VDC 28 VDC 0.272 Amp typical, 0.350 Amps max 0.139 Amp typical, 0.175 Amps max GI 260 14 Vdc 28 Vdc 0.4 Amp 0.2 Amp GMC 305 14 Vdc 28 Vdc 0.050 A (50 mA) 0.028 A (28 mA) GMC 307 14 Vdc 28 Vdc 0.120 A (120 mA) 0.067 A (67 mA) *Garmin recommends using Mod 1 level GSU 73 in aircraft that use a +28 V supply voltage and intend to monitor current on high voltage devices such as the aircraft alternator. **The specified current draw is measured with the display backlight set to 100% 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-17 Table 2-2 G3X LRU Power Requirements LRU Supply Voltage Current Draw GMC 507 14 Vdc 28 Vdc 0.20 A (200 mA) 0.11 A (110 mA) GMU 11 14/28 Vdc 0.1 A (100 mA) GMU 22 12 Vdc (from GSU 25/GSU 73) Included in GSU 25/GSU 73 Current Draw GPS 20A 14 Vdc 28 Vdc 0.2 Amp 0.1 Amp GSA 28 14 Vdc 28 Vdc 0.36 Amp (typical) 1.80 Amp (max) 2.80 Amp (max with 1 Amp trim motor at full load) 0.20 Amp (typical) 0.90 Amp (max) 1.40 Amp (max with 1 Amp trim motor at full load) GSU 25 14 Vdc 28 Vdc 0.2 Amp (includes GMU 22 load) 0.11 Amp (includes GMU 22 load) GSU 73* 14 Vdc 28 Vdc 1.75 Amp (max) 0.80 Amp (max) GTR 20 GTR 200** 14 Vdc 28 Vdc 0.6 Amp, Typical when receiving 3.0 Amp, Typical when transmitting 7.50Amp, Maximum, 90% modulated into 3:1 VSWR and 11V power input voltage 0.30 Amp, Typical when receiving 1.40 Amp, Typical when transmitting 3.75 Amp, Maximum, 90% modulated into 3:1 VSWR and 22 V power input voltage *Garmin recommends using Mod 1 level GSU 73 in aircraft that use a +28 V supply voltage and intend to monitor current on high voltage devices such as the aircraft alternator. **The specified current draw is measured with the display backlight set to 100% 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-18 2.3 Wiring/Cabling Considerations Section 23 lists the pin information for all LRU connectors. Section 23 lists the connector (including configuration modules) installation information. Section 24 through Section 29 contain interconnect drawings for all required/optional LRUs and sensors. These sections, along with Section 3 through Section 21 contain all the information needed to construct the wiring harnesses/cables. It is recommended that LRUs/sensors be installed before constructing the wiring harnesses and cables. Use MIL-W-22759/16 (or other approved wire) AWG #22 or larger wire for all connections unless otherwise specified. The supplied standard pin contacts are compatible with up to AWG #22 wire. In cases where some installations have more than one LRU sharing a common circuit breaker, sizing and wire gauge is based on aircraft circuit breaker layout, length of wiring, current draw on units, and internal unit protection characteristics. Do not attempt to combine more than one unit on the same circuit breaker. Use MIL-C-27500 (or other approved cable) for all shielded cable connections unless otherwise specified. HSDB (Ethernet) connections may use either aviation grade Category 5 Ethernet cable, or MIL-C-27500 shielded twisted-pair cable. RG-400 or RG-142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation. 2.3.1 Wiring Harness Installation Use cable meeting the applicable aviation regulation for the interconnect wiring. Any cable meeting specifications is acceptable for the installation. When routing cables, follow these precautions: · All cable routing should be kept as short and as direct as possible. · Check there is ample space for the cabling and mating connectors. · Avoid sharp bends in cabling. · Avoid routing near aircraft control cables. · Avoid routing cables near heat sources, RF sources, EMI interference sources, power sources (e.g., 400 Hz generators, trim motors, etc.) or near power for fluorescent lighting. · Route the GPS antenna cable as far as possible away from all COM transceivers and antenna cables. · Analog Input wires routed too close to spark plugs, plug wires, or magnetos may result in erratic readings. The installer shall supply and fabricate all of the cables. Required connectors, pins, etc. are provided with LRU Installation Kits. Electrical connections for the GMU 22 are made through a round 9-pin connector, and are made through D subminiature connectors for all other LRUs. Section 23 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit. Contacts for the connectors must be crimped onto the individual wires of the aircraft wiring harness. Table 1-8 lists contact part numbers (for reference) and recommended crimp tools. CAUTION Check wiring connections for errors before connecting any wiring harnesses. Incorrect wiring could cause internal component damage. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-19 2.3.1.1 Backshell Assemblies Connector kits include backshell assemblies. The backshell assembly houses the configuration module and a thermocouple reference junction. Garmin's backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, Shield Block Ground, and Thermocouple are located in Section 22. 2.3.1.2 Configuration Module The G3X system is designed to store configuration and calibration data in multiple locations to retain the configuration of the system during maintenance. A configuration module (Figure 2-2 and Figure 2-3) is installed in the connector backshell of the PFD1 display to store important configuration data. Only the PFD1 display uses a configuration module; in systems using a GSU 73, an additional configuration module is installed in the GSU 73 connector backshell. See Section 22 for installation instructions. Figure 2-2 Original Green Configuration Module P/N 011-00979-20 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-20 Figure 2-3 shows the Apple® iOS compatible configuration module that installs on the GDU 4XX (PFD 1) connector backshell. This configuration module is required for using Connext capability with Apple products. Contact Garmin Aviation Product Support if the GDU 4XX unit was sold with an original green configuration module. See Section 22 for installation instructions. NOTE Please refer to the G3X Touch Pilot's Guide (190-01754-00) for guidance in using Connext Bluetooth connections to Garmin Pilot device(s). To test for the installation of the Apple iOS compatible configuration module, enter config mode, select the System Information page, highlight PFD1, press Menu, and run the Apple compatibility test. Figure 2-3 Apple iOS Compatible Black Configuration Module P/N 010-12253-00 2.3.1.3 CAN Bus The primary digital interface used to exchange data between LRUs in the G3X system is the Controller Area Network, also known as the CAN bus. CAN was developed by Bosch GmbH in the 1980s, and its specifications are currently governed by ISO 11898-2. CAN is widely used in aviation, automotive, and industrial applications due to its simplicity and reliability. 2.3.1.3.1 CAN Bus Architecture The electrical architecture of the CAN bus takes the form of a linear "backbone" consisting of a single twisted wire pair with an LRU connected (terminated) at each end (Figure 2-4). The overall length of the CAN bus from end to end should be 20 meters (66 feet) or less. At each of the two extreme ends of the CAN bus, a 120 resistor is installed to "terminate" the bus. In the G3X system, termination resistors are provided either within the LRUs themselves, or using termination adapters that plug into an LRUs CAN connection (see Section 2.3.1.3.3). CAN BUS BACKBONE: CONSISTS OF TWISTED, SHIELDED PAIR WIRING CONNECTED TO CAN HI AND CAN LO OF EACH LRU, AND PROPERLY TERMINATED LRUs ON BOTH ENDS OF BUS. LRU LRU TERM TERM 190-01115-01 Rev. AV TERMINATION CONNECTIONS Figure 2-4 CAN Bus Backbone G3XTM/G3X TouchTM Avionics Installation Manual Page 2-21 Multiple LRUs may be connected in a daisy-chain manner along the backbone of the CAN bus (Figure 2-5). DAISY-CHAINED LRUs LRU TERM LRU LRU LRU TERM LRU TERMINATED BACKBONE LRUs Figure 2-5 Daisy-chained LRUs on Backbone Daisy-chained LRUs (LRUs not at the extreme ends of the CAN bus) connect to the CAN backbone through short "stub" or "node" connections (Figure 2-6). The length of each node connection should be kept as short as possible, and should not exceed 0.3 meters (1 foot). The best way to connect devices between the ends of the CAN bus while maintaining short stub node lengths is to splice the connections as close to the device as practical (Section 22.2.9). Unshielded wire sections should be kept as short as practical. Multiple devices must not connect to the CAN bus backbone at the same point. Rather than splicing two or more stub node connections together, the CAN bus should instead be daisy chained from one device to the next (Figure 2-6). LRU TERM LRU Max. node length 0.3 meter (1 ft) LRU LRU Figure 2-6 Node Connections TERM LRU 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-22 The layout of the CAN bus must be a single linear backbone with exactly two distinct end points (Figure 2-7). Other layouts such as "star" or "Y" arrangements must be avoided. Similarly, hub devices must not be used with the G3X CAN bus. (Figure 2-8) TERM TERM LRU LRU LRU LRU LRU LINEAR CAN BACKBONE, DAISY-CHAINED CONNECTIONS WITH SHORT STUB NODE LENGTHS. MULTIPLE LRUs ARE NOT CONNECTED TO BACKBONE AT THE SAME LOCATION. Figure 2-7 Correct CAN Wiring Example LRU LRU LRU LRU LRU LRU LRU LRU LRU HUB DEVICE LRU LRU AVOID "T" OR "Y" SHAPE AVOID STAR SHAPE DO NOT USE THIRD-PARTY HUB DEVICES Figure 2-8 Incorrect CAN Wiring Examples 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-23 2.3.1.3.2 CAN Bus Wiring Wiring used for the CAN bus should be shielded twisted-pair cable, MIL-C-27500 or equivalent. 22 AWG or larger wire is recommended for physical robustness and ease of installation. While not required, it is recommended to use one of the following 2 options for CAN wire, especially if the CAN bus length is on the upper end of the maximum 66 foot bus length: CAN Bus Wire, 120: · GigaFlight Connectivity P/N GF120-24CANB-1: GigaFlight Connectivity Inc. 6180 Industrial Ct. Greendale, WI 53129 United States Toll Free: +1 (844) 303-1093 Phone: +1 (414) 488-6320 Email: [email protected] · Carlisle IT P/N CAN24TST120(CIT), (must be ordered from the following Carlisle IT facility): Carlisle Interconnect Technologies 5300 W. Franklin Drive Franklin, WI 53132 United States Toll Free: +1 (800) 327-9473 Phone: +1 (414) 421-5300 Fax: +1 (414) 421-5301 The shields for each CAN bus wire segment should be interconnected, forming a continuously connected shield from one end of the CAN bus to the other (Figure 2-9 and Section 2.3.1.3.2). At minimum, the CAN bus shield should always be grounded to the device connector backshells at the two extreme ends of the bus, but it is acceptable to also ground the shield at any or all other devices on the CAN bus. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-24 The shields for each CAN bus wire segment should be interconnected, forming a continuously connected shield from one end of the CAN bus to the other (Figure 2-9 and Section 22-13). At minimum, the CAN bus shield should always be grounded to the device connector backshells at the two extreme ends of the bus, but it is acceptable to also ground the shield at any or all other devices on the CAN bus. SHIELD GROUNDED AT EACH DAISY-CHAINED LRU, RECOMMENDED DAISY-CHAINED LRU ON CAN BUS PXXX JXXX CAN-H CAN-L SHIELD GROUND CAN BUS TERMINATION JXXX PXXX CAN-H CAN-L SHIELD GROUND CAN BUS TERMINATION PXXX JXXX CAN-H CAN-L SHIELD GROUND SHIELD GROUNDED AT CAN BUS TERMINATIONS, REQUIRED ALL WIRING SHOWN IS TWISTED SHIELDED PAIR Figure 2-9 CAN Bus Shield Grounding For proper CAN bus operation, it is important for all devices on the CAN bus to share a common power ground reference. Connect all LRU power ground pins to a single common ground point - do not use local ground points or use the aircraft structure as a ground return path. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-25 2.3.1.3.3 CAN Bus Termination At each of the two extreme ends of the CAN bus backbone, a 120 resistor is installed to terminate the bus. In the G3X system, separate resistors are not required. Instead, termination resistors are provided either within the LRUs themselves, or using termination adapters that plug into an LRU's CAN connection. · The GAD 29, GEA 24, GMU 11, GPS 20A, GSU 25, and G5 installation kits provide a 9-pin termination adapter that provides termination when attached to the device's main connector. The termination adapter contains a 120 resistor that is connected between pins 1 and 2 (Figure 2-10). · The GDU 37X, GDU 4XX, GAD 27, GHA 15, and GSU 73 contain a 120 resistor inside the unit that provides termination when the CAN LO pin is connected externally to the CAN TERM pin (Figure 2-11). · The GMC 507, GSA 28, and GTR 20/200 contain a 120 resistor inside the unit that provides termination when the two CAN TERM pins are connected together (Figure 2-12 and Figure 2-13). · The GI 260 and GMA 245 do not have provisions for CAN termination. The GI 260 cannot be installed at the end of the CAN bus. The total amount of extra wire length the GI 260 adds to the CAN HI and CAN LO wires should not exceed 0.4 meters (15 inches). The GMA 245 can use the 9 pin termination adapter (011-02887-00) for a termination solution, by installing the unit in-line rather than directly to the LRU connector. See GMA 245 Installation Manual for further information. GARMIN CAN TERMINATOR Figure 2-10 CAN Bus Termination (011-02887-00) for GAD 29, GEA 24, GMA 245, GMU 11, GPS 20A, GSU 25, and G5 GAD 27 & GDU 37X/45X/46X/47X P271 1 2 3 P3701/ P4X01 Figure 2-11 CAN Bus Termination for GAD 27, GDU 37X/4XX, GHA 15, and GSU 73 GSA 28 PITCH SERVO CAN_TERM_1 3 CAN_TERM_2 4 NOTE: JUMPER (BETWEEN PINS 3 & 4) REQUIRED WHEN GSA 28 IS LOCATED AT END OF CAN BUS 190-01115-01 Rev. AV Figure 2-12 CAN Bus Termination for GSA 28 G3XTM/G3X TouchTM Avionics Installation Manual Page 2-26 GTR 20/200 CAN BUS HI CAN BUS LO CAN_TERM_A CAN_TERM_B P2001 7 6 25 26 NOTE: JUMPER (BETWEEN PINS 25 & 26) REQUIRED WHEN GTR 20/200 IS LOCATED AT END OF CAN BUS Figure 2-13 CAN Bus Termination for GTR 20/200 Both ends of the CAN bus should be terminated (Figure 2-14), but devices that are not at the ends of the CAN bus should not be terminated (Figure 2-15). LRU TERM LRU LRU LRU TERM LRU CORRECT - CAN BUS TERMINATED AT EACH END OF BACKBONE Figure 2-14 Correct CAN Bus Termination Example LRU LRU TERM LRU LRU TERM LRU INCORRECT - ONE OF THE TERMINATIONS IS NOT AT END OF BACKBONE LRU TERM LRU LRU LRU LRU INCORRECT - ONLY ONE END OF BACKBONE IS TERMINATED Figure 2-15 Incorrect CAN Bus Termination Examples 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-27 2.3.1.3.4 CAN Bus LRU Removal Guidelines The following should be considered when removing an LRU from the ends of G3X CAN network: · GEA 24, GSU 25, GAD 29, GPS 20A, G5, or other devices that uses the 9-pin CAN termination adapter: The CAN bus will remain terminated as long as the CAN termination adapter is left connected. · GDU 37X, GDU 4XX, GAD 27, GMC 507, or GSU 73: The CAN bus will be unusable until the LRU is reconnected, or the bus is properly terminated at both ends of the CAN backbone. · GSA 28: A removal adapter (part number 011-03158-00) is provided with each GSA 28 connector kit. This adapter can be used when a GSA 28 is removed from the aircraft. The removal adapter keeps the node on the CAN bus in the same state as when the servo was installed (either terminated or un-terminated). The removal adapter also allows trim signals to pass through when no servo is installed. 2.3.1.3.5 CAN Bus Installation Guidelines For maximum reliability of the CAN bus, the following guidelines should be followed: · The CAN bus backbone must be a single linear path with exactly two distinct ends. CAN bus connections should be "daisy chained" from device to device. Avoid "star" and "Y" topologies, and do not use a hub device (see Figure 2-11). · The overall length of the bus should not exceed 20 meters (66 feet). · Keep all stub node connections as short as practical. The maximum length of any stub node connection is 0.3 meters (1 foot). · Avoid connecting more than one device to the CAN bus backbone at the same point. Instead, daisy chain the CAN bus backbone from one device to the next. · Follow proper wiring, shielding, and grounding requirements described in section Section 2.3.1.3.2. · Terminate the CAN bus at the two extreme ends of the bus, as described in Section 2.3.1.3.3. · When adding a new device to the CAN bus, evaluate proposed modifications to the CAN bus wiring connections to maintain compliance with all above requirements. 2.3.1.3.6 CAN Bus Troubleshooting CAN is very simple, and a properly installed CAN bus is normally very reliable. If problems are occurring, there is a good reason and the following steps can help to identify the issue. 1. Review the status LED of devices on the CAN bus such as the GSU25, GEA24, and GSA 28 servos (see Section 31.1.1). The status indications are listed in Table 2-3. Table 2-3 Status LED Indications LED Indication No Light Steady Green Flashing Green Red Alternating Red/Green Description No Power On, but not communicating through CAN Bus On and communicating through CAN Bus Hardware Fault CAN bus network error two similar devices are configured with the same unit ID 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-28 2. Make sure the CAN bus is daisy-chained between CAN device around the system, and that CAN devices are not connected by a single point like a star or routed through a hub device. This can cause unwanted signal reflections and "orphan" some devices on the bus and prevent their communication. 3. Make sure the CAN bus is terminated in only two locations, and only at the extreme ends of the CAN bus. 4. With power removed, remove a connector from one of the devices that is not located at either of the extreme ends of the CAN bus. a) Using an ohm meter, verify the resistance between the CAN HI and CAN LO pins on the connector is 60 ohms. This will verify the CAN backbone is properly terminated at each end (two 120 ohm terminating resistors in parallel). b) A resistance of 120 ohms indicates that one of the two required CAN terminations is missing. c) A resistance of 40 ohms or less indicates that too many terminations are installed. 5. Verify the CAN HI and CAN LO signals are not swapped, shorted together, or open-circuited at any LRU connector. 6. Verify the CAN HI and CAN LO signals are not shorted to ground (this can happen when shielded wire is installed incorrectly). 7. Highlight each device on the configuration mode system information page (Section 30.4.3) and verify the value displayed for Network Error Rate is a steady 0% (Figure 2-16). Figure 2-16 Network Error Rate (configuration mode) 8. Start only the PFD1 display and one other CAN device at a time, and verify the connection quality for each device. Sometimes a device will communicate with PFD1 only when it is the only powered device on the CAN bus, if one or more of the above issues is present. Evaluating each CAN device in turn can help narrow down a problem. 9. It is very important for each device on the CAN bus to share a common power/signal ground. Ground potential differences between devices on the CAN bus can cause communication errors. Ground devices to a common ground bus, not to the airframe or to multiple grounding buses. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-29 2.4 Mechanical Considerations This section presents all information required for planning the physical layout of the G3X installation. 2.4.1 Physical Specifications Follow the panel requirements in Table 2-4. All width, height, and depth measurements are taken with unit rack (if applicable) and connectors. LRU dimensions are listed in each LRU section. Panel cutout templates are available for the GDU 37X, GDU 45X, GDU 46X, GDU 470, GMC 305, and GMC 307 in the respective LRU sections of this document. Cutout templates for the GDU 37X/4XX displays and the GMC 507 are also available in digital form (.DXF files) from the G3X manuals download page on www.garmin.com. Table 2-4 G3X LRU Physical Specifications LRU Width Height Depth Unit Weight Weight of Unit and Connector(s) GAD 27 (Flaps/ Lights/Trim Controller) 3.78 inches [96.01 mm] 1.954 inches [49.63 mm] no connector 3.569 inches [90.65 mm] with connector 5.204 inches [132.18 mm] no connector 6.533 inches [165.93 mm] with connector 0.64 lbs (0.29 kg) 0.97 lbs (0.44 kg) GAD 29 (ARINC 429 Adapter) 6.10 inches 1.48 inches [154.9 mm] [37.6 mm] 3.23 inches [82.0 mm] no connector 5.10 inches [129.4 mm] w/connector 5.54 inches 140.7 mm] w/connector and CAN terminator GAD 29 0.38 lbs (0.172 kg) GAD 29 0.63 lbs (0.285 kg) GAP 26 -00, -10 (Air Data Probe) 0.82 inches 16.0 inches [20.9 mm] [406.4 mm] 6.12 inches [157.7 mm] -00 probe: 0.33 lbs (0.15 kg) -10 probe: 0.39 lbs (0.18 kg) -00 probe with adjustable mounting kit: **0.53 lbs (0.20 kg) -010 probe with adjustable mounting kit: **0.59 lbs (0.22 kg) *weight includes nut plate **Previous versions of the mounting kit used a steel mount tube that is heavier by 0.14 lbs than the weights listed in this table. The steel mount tube has welded mounting tabs and a constant wall thickness. The currently used aluminum mount tube has machined mounting tabs and the wall thickness is greater at the upper end vs. the lower end. Add 0.14 lbs to listed weights when using the steel mounting tube. 190-01115-01 Rev. AV G3XTM/G3X TouchTM Avionics Installation Manual Page 2-30 Table 2-4 G3X LRU Physical Specifications LRU Width Height Depth Unit Weight Weight of Unit and Connector(s) GAP 26 -20 (Air Data Probe and Heater Control Box) Probe .82 inches [20.9 mm] Probe 16.0 inches [406.4 mm] Control Box 2.25 inches [57.0 mm] (includes wiring grommet and screw heads, but not harness) Control Box: 1.11 inches [28.2 mm] 6.12 inches [157.7 mm] Control Box: 4.55 inches [115.6 mm] -20 probe: 0.39 lbs (0.18 kg) **-20 probe with adjustable mounting kit: 0.59 lbs (0.22 kg) -20 control box 0.36 lbs NA (0.16 kg) GDL 39R 5.00 inches (127.0 mm) 1.63 inches (41.35 mm) 6.17 inches (156.7 mm) 17.7 oz (502 g) 19.5 oz (552 g) GDL 51R GDL 52R 6.10 inches (154.9 mm) 1.60 inches (40.6 mm) 5.00 inches (127.0 mm) 0.78 lbs (0.35 kg) 0.83 lbs (0.38 kg) 0.904 lbs (0.41 kg) 0.954 lbs (0.43 kg) GDU 370 6.04 inches 7.83 inches (Display) (153.4 mm) (198.8 mm) 3.41 inches (86.6 mm) 1.6 lbs (0.71 kg) 1.8 lbs*, (0.803 kg) GDU 375 6.04 inches 7.83 inches (Display) (153.4 mm) (198.8 mm) 3.41 inches (86.6 mm) 1.7 lbs (0.77 kg) 1.9 lbs*, (0.862 kg) GDU 450 8.00 inches 5.93 inches (Display) (203.0 mm) (150.5 mm) Depth behind panel including recommended backshell 3.68 inches (93.4 mm) 2.71 lbs (1.23 kg) 2.98 lbs*, (1.35 kg) GDU 455 8.00 inches 5.93 inches (Display) (203.0 mm) (150.5 mm) Depth behind panel including recommended backshell 3.68 inches (93.4 mm) 2.84 lbs (1.29 kg) 3.11 lbs*, (1.41 kg) GDU 460 (Display) 10.85 inches (275.5 mm) 7.82 inches (198.6 mm) 3.57 inches (90.7 mm) 4.60 lbs (2.09 kg) 4.81 lbs*, (2.18 kg) *weight includes nut plate **Previous versions of the mounting kit used a steel mount tube that is heavier by 0.14 lbs than the weights listed in this table. The steel mount tube has welded mounting tabs and a constant wall thickness. The currently used aluminum mount tube has machined mounting tabs and the wall thickness is greater at the upper end vs. the lower end. Add 0.14 lbs to listed weights when using the steel mounting tube. 190-01115-01 Rev. AV G3XTM

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Garmin G3X is a multi-function display (MFD) that combines navigation, flight planning, hazard avoidance, and additional features to enhance situational awareness and safety during flight operations. Its advanced capabilities make it a valuable tool for pilots of all experience levels.

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Pages: 59 Garmin G3X Installation manual

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Garmin G3X Touch Pilot's Manual

• Installation manual (1011 pages)
• Pilot's manual (470 pages)
• Maintenance manual (134 pages)
• page of 346 Go / 346

Table of Contents

• Troubleshooting

Section 1 System Overview

Line replaceable units.

• System Overview
• G3X Touch System
• External Navigators (Optional)

Display Overview

Secure digital (sd) cards, system power-up, system operation.

• PFD Display Configuration
• G3X Touch System Annunciations
• AHRS Operation

Accessing System Functionality

• Nearest Pages

Accessing Additional Information

• New Location
• Entering a New Location
• Acquiring Satellites
• Satellite Information

System Settings

• Transponder
• Airport Criteria

Section 2 Flight Instruments

Flight instruments.

• Airspeed Indicator
• Attitude Indicator
• Setting the Selected Altitude
• Barometric Pressure
• Selecting the Altimeter Barometric Pressure Setting
• Vertical Speed Indicator (VSI)
• Vertical Deviation Indicator and VNAV Indicator
• Vnav Indicator
• Horizontal Situation Indicator (HSI)
• Bearing Pointers and Information Windows
• Trim and Flap Position Indicators (Optional)
• Turn Rate Indicator
• Supplemental Flight Data
• Outside Air Temperature
• Angle of Attack (AOA)

Vertical Navigation (VNAV)

• Using the VNAV Feature

Section 3 Engine Indication System

Eis display & eng page, lean assist mode (optional), fuel calculator (optional).

• CAS Messages (Optional)

Section 4 CNS Interface

Auto-tuning frequencies (optional), com radio (optional).

• Automatic Squelch

Remote Transponder Interface (Optional)

• Transponder CODE and Mode Selection
• Flight ID Reporting

Section 5 GPS Navigation

Introduction.

• Compass Arc

Using Map Displays

• Map Page Setup
• Gps Navigation
• Map Panning
• Fuel Range Ring
• Measuring Bearing and Distance
• Map Page Traffic
• Map Symbols
• Displaying/Removing Airways
• Reviewing Information for an Airway
• Nearest Information

Weather Information

• Intersections
• User Waypoints
• Deleting User Waypoints

5.5 Airspace

• Automatic Waypoint Selection
• Airspace Alert Messages
• Smart Airspace

Direct-To Navigation Using the G3X Touch

Section 6 flight planning.

• Flight Plan Data Fields
• Manually Switching between Internal and External Flight Plan Sources
• Failure of the External GPS Navigation Source

Flight Plan Creation Using the G3X Touch

• Flight Planning

Flight Plan Storage Using the G3X Touch

Flight plan activation using the g3x touch, flight plan editing.

• Adding Waypoints to an Existing Flight Plan
• Editing Flight Plan Speed, Fuel, And/Or Name
• Copying Flight Plans
• Deleting Flight Plans
• Inverting a Flight Plan
• Importing/Exporting Flight Plans

Approaches (Without External Navigator Configured)

• Selecting an Approach
• Activating Vectors-To-Final

Section 7 Hazard Avoidance

• Weather Source
• Hazard Avoidance
• Nexrad Abnormalities
• Synthetic Vision
• Terrain Information
• Terrain Views
• Obstacle Information
• Terrain Settings
• Terrain Alerts

Traffic Systems

• Traffic Symbology
• Displaying Traffic Information
• Theory of Operation
• Switching from Standby Mode to Operating Mode
• Traffic Page
• Traffic Description
• Symbol Description

Section 8 Additional Features

Synthetic vision (svx).

• Additional Features
• Flight Path Marker
• Airport Signs
• Safetaxi Cycle Number and Revision
• Aircraft Symbol
• Chart Range
• Jeppesen Database-Published Notams

Flitecharts

• Flitecharts Cycle Number and Expiration Date

Airport Directory Data

S irius xm radio entertainment (optional).

• Activating Siriusxm Satellite Radio Services
• Selecting a Category
• Selecting a Channel

Vertical Power (Optional)

Electronic checklists (optional).

• Flight Data Logging

Section 9 Automatic Flight Control Systems (Optional)

• AFCS System Architecture
• G3X Touch AFCS Installations Options
• Control Wheel Steering (CWS) (Optional)
• G3X Touch AFCS Status Box

AFCS Operation

• AFCS PRE-FLIGHT Actions
• AFCS Controls
• Engaging the Autopilot
• Flight Director Modes
• Command Bars

Vertical Modes

• Pitch Hold Mode (PIT)
• Selected Altitude Capture Mode (ALTS)
• Altitude Hold Mode (ALT)
• Vertical Speed Mode (VS)
• Indicated Airspeed Mode (IAS) (GMC 305 Only)
• Vertical Navigation Mode (VNAV)
• VNAV Target Altitude Capture Mode (ALTV)
• Glidepath Mode (GP) (with External WAAS Enabled IFR Navigator ONLY)
• Glideslope Mode (GS)
• Go Around (GA) and Takeoff (TO) Modes (GMC 305 Only)

Lateral Modes

• Roll Hold Mode (ROL)
• Heading Select Mode (HDG)
• Navigation Modes (GPS, VOR, LOC, BC)
• Approaches Without Vertical Guidance
• Approaches with Lateral + Vertical Guidance

10.1 Miscellaneous Message Advisories

Section 10 annunciations & alerts, miscellaneous message advisories.

• Airspace Messages
• System Status Messages

Audio Alerts

• Voice Alerts
• AOA Aural Alert

PFD Annunciations and Alerting Functions

• Terrain Annunciations
• Traffic Annunciations
• AHRS Alerts (Optional)
• AFCS Alerts (Optional)
• Vertical Power Fault Indications

Section 11 Appendices

Appendix a: data field options, appendix b: utilities.

• Displaying/Removing the Track Log on the Map Page
• Changing Track Log Settings
• Heading Line
• Weight & Balance
• Proximity Waypoints

Appendix C: SD Card Use and Databases

• Installing and Removing SD Cards
• G3X Touch Databases
• Navigation Database
• Updating G3X Touch Databases
• Importing/Exporting/Renaming Flight Plans

Appendix D: Map Datum and Location Formats

• Location Formats

Appendix E: General TIS-A Information

• TIS-A Vs. TAS/TCAS
• TIS-A Limitations

Appendix F: Abnormal Operation

• Loss of GPS Position
• Hazard Display with Loss of GPS Position
• G3X Touch System Failure Annunciations
• Unusual Attitudes
• Reversionary Mode (Full-Screen)
• AFCS Reversionary Mode
• Synthetic Vision Troubleshooting

Appendix G: Display Symbols

• VFR Symbols
• IFR Symbols
• Airspace Symbols

Appendix H: Glossary

Appendix i: license agreement and warranty.

• Contact Garmin
• Software License Agreement
• Limited Warranty
• AOPA Airport Directory Notice
• Ac-U-Kwik License Agreement
• S Irius XM Satellite Radio Service Agreement
• Weather Data Warranty

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Summary of Contents for Garmin G3X Touch

• Page 1 G3X Touch ™ Pilot’s Guide...
• Page 3 SYSTEM OVERVIEW FLIGHT INSTRUMENTS CNS INTERFACE GPS NAVIGATION FLIGHT PLANNING HAZARD AVOIDANCE ADDITIONAL FEATURES AFCS ANNUNCIATIONS & ALERTS APPENDIX INDEX...
• Page 5 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...
• Page 6 Warnings, Cautions & Notes WARNING: Navigation and terrain separation must NOT be predicated upon the use of the terrain function. The G3X Touch Terrain Proximity feature is NOT intended to be used as a primary reference for terrain avoidance and does not relieve the pilot from the responsibility of being aware of surround- ings during flight.
• Page 7 System and is solely responsible for its accuracy and maintenance. The GPS system is subject to changes which could affect the accuracy and performance of all GPS equipment. Portions of the Garmin G3X Touch utilize GPS as a precision electronic NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G3X Touch can be misused or misinterpreted and, therefore, become unsafe.
• Page 8 WARNING: Do not use the approach information provided by the VFR naviga- tion database residing within the G3X Touch as a means of navigating any instrument approach. The G3X Touch VFR navigation database is limited to present only the waypoints for the final approach leg of a published procedure.
• Page 9 Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G3X Touch. It is thus the responsibility of the pilot to detect such an occurrence by means of cross-checking with all redundant or correlated information available in the cockpit.
• Page 10 Warnings, Cautions & Notes Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 11 Part Number Change Summary 190-001754-00 Initial release Date Description March, Production Release 2014 RR-1 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 12 Blank Page RR-2 Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 13: Table Of Contents

• Page 14 Weather Information ......................99 Intersections ........................99 ..........................100 ..........................100 User Waypoints ........................ 101 Automatic Waypoint Selection ..................103 5.5 Airspace ........................... 103 Airspace Alert Messages ....................104 Smart Airspace ....................... 104 ™ Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 15 Manually Switching Between Internal and External Flight Plan Sources ......108 Failure of the External GPS Navigation Source ..............108 6.2 Flight Plan Creation Using the G3X Touch ............... 109 6.3 Flight Plan Storage Using the G3X Touch ..............111 6.4 Flight Plan Activation Using the G3X Touch ............
• Page 16 Section 9 Automatic Flight Control Systems (Optional) ........207 AFCS System Architecture ....................207 G3X Touch AFCS Installations Options ................209 Control Wheel Steering (CWS) (Optional) ................210 G3X Touch AFCS Status Box ..................... 210 9.1 AFCS Operation ......................212 AFCS PRE-FLIGHT Actions ....................
• Page 17 Appendix F: Abnormal Operation ..................301 Loss of GPS Position ......................301 Hazard Display with Loss of GPS Position ................301 G3X Touch System Failure Annunciations ................302 Unusual Attitudes ......................302 Reversionary Mode (Full-Screen) ..................303 AFCS Reversionary Mode ....................304 Failure of the External GPS Navigation Source ..............
• Page 18 Software License Agreement ..................... 317 Limited Warranty ......................317 AOPA Airport Directory Notice ..................318 AC-U-KWIK LICENSE AGREEMENT ..................319 XM Satellite Radio Service Agreement ............... 319 irius Weather Data Warranty ....................319 Index ...........................Index-1 Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 19: Section 1 System Overview

Page 20: system overview.

• Page 21 System Overview • GSU 25 Garmin Sensor Unit sub-system for the G3X Touch (Air Data Computer (ADC), and – the Attitude and Heading Reference System (AHRS)) – ADC: Processes data from the pitot-static system and outside air tem- perature (OAT) sensor.
• Page 22 Temperature Probe: Provides raw air temperature data. – GTP 59 • GAP 26 – Pitot/AOA Probe: Sends dynamic air pressure for airspeed and angle of attack (AOA), when paired with a GSU 25. GAP 26 Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 23 Auto Pilot Servo: Used for automatic control of pitch, roll, and yaw. GSA 28 • GEA 24 – Engine and Airframe Unit: Receives and processes signals from the engine and airframe sensors. GEA 24 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 24: G3X Touch System

• Page 25 Audio Panel Notes: (Optional) A429 *Maximum of two (2) COM/NAV (Autopilot) units installed. Third-party GARMIN COM OR Autopilot **Same as (*) plus GDU to SL40 NAV/COM is Tx-only. (Optional) (Optional**) G3X Touch System 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 26: External Navigators (Optional)

Page 27: secure digital (sd) cards.

• Page 28 When this information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to continue. Database Information Touch Press To Accept to acknowledge the information. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 29: System Operation

Page 30: ahrs operation, page 31: accessing system functionality, page 32: data entry.

• Page 33 Touch the desired page on the page navigation bar or turn the large Knob associated with the MFD to cycle through the pages. Page Navigation 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 34: Main Pages

Page 35: accessing additional information, page 36: viewing gps receiver status, page 37: new location, page 38: position, page 39: system settings, page 40: transponder, page 41: display.

• Page 42 • User Selected—Enables the user to choose between ‘AUTO’ and ‘PFD’ via the Display Setup menu. For more information on how to enable the ‘EIS Display Location’ setting in Configuration Mode refer to the G3X Touch Installation Manual. Changing the EIS display location: 1) Press the MENU Key twice.

Page 43: Sound

Page 44: units, page 45: position, page 46: airport criteria.

• Page 47 Touch Private Airports. Touch Heliports. Restoring airport criteria defaults: 1) Press the NRST Key. 2) Press the MENU Key. 3) Touch Set Airport Criteria. 4) Press the MENU Key. 5) Touch Restore Default. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 48 System Overview Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 49: Section 2 Flight Instruments

• Page 50 Flight Instruments Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 51: Airspeed Indicator

• Page 52 . Using TAS instead of IAS causes V to be reduced at high altitudes. If configured, the G3X Touch can calculate and display this reduction in V A solid red band is used between the TAS adjusted V and the actual indicated value for V Garmin G3X Touch Pilot’s Guide...

Page 53: Attitude Indicator

Page 54: altimeter, page 55: setting the selected altitude, page 56: barometric pressure.

• Page 57 • After reaching the Selected Altitude, if the pilot flies outside the deviation band (±200 Feet of the Selected Altitude), the Selected Altitude changes to yellow text on a black background, flashes for 5 seconds, and an aural tone is generated. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 58: Vertical Speed Indicator (Vsi)

Page 59: vertical deviation indicator and vnav indicator.

• Page 60 GPS approach. The glidepath is analogous to the glideslope for GPS approaches supporting WAAS vertical guidance (LNAV+V, L/VNAV, LPV). The Glidepath Indicator appears on the G3X Touch as a magenta diamond. If the approach type downgrades past the final approach fix (FAF), “NO GP” is annunciated.

Page 61: Vnav Indicator

Page 62: horizontal situation indicator (hsi).

• Page 63 Course Deviation & To/From Rotating Compass Rose Indicator Selected Heading Bug Selected Heading Aircraft Symbol Current Heading To/From Indicator Turn Rate Indicator Lateral Deviation Scales Navigation Source Course Deviation Indicator (CDI) Horizontal Situation Indicator (HSI) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 64: Bearing Pointers And Information Windows

• Page 65 VOR station active waypoint is not selected Bearing Bearing Pointer 2 Pointer 1 Bearing 1 Information Window Bearing 2 Information Window -Identifier -Identifier -Bearing Source -Distance HSI with Bearing Pointers 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 66 Scale The CDI is capable of displaying two sources of navigation: GPS or NAV (VOR, localizer) depending on the external navigator(s) configured (refer to the G3X Touch Installation Manual for more information). Color indicates the current navigation source: magenta (for GPS) or green (for VOR and LOC). The full-scale limits for the CDI are defined by a GPS-derived distance when coupled to GPS.
• Page 67 G loads. When in the auto display mode, the G-meter will automatically be displayed when an unusual attitude is sensed (i.e., greater than +/- 65° roll or +30°/-20° pitch). Refer to the G3X Touch installation manual for more information on configuring the G-meter.
• Page 68 While in ‘Auto Trk/Hdg’ the HSI will remain heading-based when the aircraft is on the ground or when the autopilot is in HDG mode. Refer to the G3X Touch installation manual for more information on configuring the HSI Orientation.
• Page 69 Touch FPL Source > Internal on the Active Flight Plan Page, to temporarily allow flight planning through the G3X Touch using the internal GPS flight plan when an external GPS Navigator is configured. Touch FPL Source > External GPS to return to the external GPS navigator’s flight plan.
• Page 70 • CDI scale = 5.0 nm - if the previous two conditions do not exist. lewing The G3X Touch will automatically slew the LOC course pointer to the correct final approach course when an ILS, LOC, BC, LDA, or SDF approach is active in the external navigator and the appropriate CDI and navigation source are selected on the G3X Touch.

Page 71: Trim And Flap Position Indicators (Optional)

Page 72: obs mode.

• Page 73 4) Touch Sync Course or enter the desired course to/from the waypoint using the keypad and touch OK. 5) To cancel OBS Mode and return to automatic waypoint sequencing, press the MENU Key. 6) Touch Release Hold. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 74: Supplemental Flight Data

Page 75: angle of attack (aoa).

• Page 76 GSU 25 Static Air Data Sensor Unit Pressure GAP 26 Air Data Probe Pressure Pitot Pressure (Display Unit) Pneumatic CAN Bus Angle of Attack (AOA) System Angle of Attack Angle of Attack (AOA) Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 77: Vertical Navigation (Vnav)

• Page 78 At 200 ft above the target altitude, the “Approaching Target Altitude” message appears, and the VNAV indicator disappears from the PFD. Distance to Profile Target Altitude Distance to Target Airport Visual Representation of VNAV Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 79: Using The Vnav Feature

• Page 80 Canceling the VNAV profile: 1) While navigating a flight plan or Direct-to with a valid VNAV profile, press the MENU Key twice. 2) Touch VNAV. 3) Press the MENU Key. 4) Touch Cancel VNAV Profile. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 81: Section 3 Engine Indication System

• Page 82 Aileron trim indicator Rudder Rudder trim indicator Elevator Elevator trim indicator Flaps Flaps position indicator Total Hours Refer to the G3X Touch Installation Manual. Fuel Calculator Calculates fuel endurance, range, and economy Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 83 Main Tab on the Eng Page Aux Tab on the Eng Page 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 84 If sensory data to an instrument becomes invalid or unavailable, a red “X” is displayed across the instrument. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 85: Lean Assist Mode (Optional)

• Page 86 The peak temperature is depicted by a hollow blue pointer, and the temperature deviation from peak (DEGT or DTIT) is displayed in place of the normal temperature number in light blue text. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 87 Cylinder with the Temperature Closest to Its Peak Value Difference Between Present and Peak Temperature Cylinder Peak Temperature Lean Assist (EIS) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 88: Fuel Calculator (Optional)

Page 89: cas messages (optional).

• Page 90 Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 91: Section 4 Cns Interface

• Page 92 2) Touch the page navigation bar. 3) Touch Airspace. 4) Touch the desired airspace. 5) Touch Frequencies. 6) Touch the desired frequency to tune. 7) OPTIONAL: Touch the desired COM radio if configured with more than one. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 93: Com Radio (Optional)

• Page 94 Waypoint. 3) Touch STBY to transfer the frequency to the Active Field. Adjusting COM Volume: 1) Touch the STBY frequency field. 2) Touch Volume. 3) Touch the slider to adjust the percentage. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 95: Automatic Squelch

• Page 96 Transponder Reply Touch to Code Status Ident Mode Transponder Data Box on PFD Transponder tuning for panel mount transponders like GTX 327 (Mode C) and GTX330ES is also supported. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 97: Transponder Code And Mode Selection

• Page 98 The VFR code can be entered either manually or by touching VFR on the Transponder Page. The pre-programmed VFR code is automatically displayed in the code field of the Transponder Data Box. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 99: Ads-B Out

• Page 100 CNS Interface Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 101: Section 5 Gps Navigation

Page 102: using map displays, page 103: map page setup, page 104: gps navigation, page 105: map range, page 106: map panning, page 107: fuel range ring, page 108: measuring bearing and distance, page 109: topography, page 110: map page traffic, page 111: airways, page 112: displaying/removing airways, page 113: waypoints.

• Page 114 2) Touch the waypoint identifier at the top of the page. 3) Enter the waypoint identifier using the keypad and touch OK. Touch Find > Search Name > Search by Facility Name. Enter the facility name using the keypad and touch OK. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 115 * May include Additional Information Frequency Abbreviations 1) With the Waypoint (WPT) Page displayed, touch the Freq Tab. 2) Touch a frequency denoted with an * to view additional information. 3) Touch Tune. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 116: Nearest Information

Page 117: weather information, page 118: ndbs, page 119: user waypoints, page 120: deleting user waypoints, page 121: automatic waypoint selection, page 122: airspace alert messages.

• Page 123 Once a direct-to is activated, the G3X Touch establishes a point-to-point course line from the present position to the selected direct-to destination. Course guidance is provided until the direct-to is replaced with a new direct-to or flight plan, or cancelled.
• Page 124 4) Touch Activate. Cancelling or resuming a direct-to: 1) Press the Direct-to Key. 2) If an external navigator is configured, touch FLP Source > Internal. 3) Touch Stop Navigation or Resume Flight. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 125: Section 6 Flight Planning

Page 126: flight plan data fields, page 127: flight plan creation using the g3x touch, page 128: flight planning, page 129: flight plan storage using the g3x touch, page 130: flight plan activation using the g3x touch, page 131: flight plan editing, page 132: editing flight plan speed, fuel, and/or name, page 133: copying flight plans, page 134: deleting flight plans, page 135: inverting a flight plan, page 136: approaches (without external navigator configured), page 137: selecting an approach.

• Page 138 Removing an approach from the Active Flight Plan: 1) From the Active Flight Plan, touch FLP Source > Internal if an external navigator is configured. 2) Press the MENU Key. 3) Touch Remove Approach. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 139: Activating Vectors-To-Final

• Page 140 3) Touch Activate Vectors-to-Final. Cancelling Vectors-to-Final: 1) From the Active Flight Plan, touch FLP Source > Internal if an external navigator is configured. 2) With Vectors-to-Final activated, press the MENU Key. 3) Touch Cancel Vectors-to-Final. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 141: Section 7 Hazard Avoidance

Page 142: hazard avoidance.

• Page 143 It is designed to receive, process, and output traffic (ADS-B air-to-air, and TIS-B traffic information), and weather (Flight Information Service-Broadcast (FIS-B)) information to the G3X Touch system through an RS-232 serial connection. As a UAT receiver, the GDL 39/39R can receive and, when connected to the G3X Touch, display Flight Information Service-Broadcast (FIS-B) weather products as well as traffic.
• Page 144 SIGMET 12 hours minute intervals for 1 hour PIREP 8 hours As Available Winds and 12 hours 12 hours Temperatures Aloft NOTAM (D)/FDC 12 hours As Available (Including TFRs) Weather Product Timing Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 145 SiriusXM Satellite Radio with a Radio ID. SiriusXM Satellite Radio uses the Radio ID to send an activation signal that allows the G3X Touch to display weather data and/or entertainment programming. SXM Weather Information • Radio ID—Eight-digit ID number used for activation.
• Page 146 Restoring default weather data for the Map Page: 1) From the Map Page press the MENU Key. 2) Touch Set Up Map. 3) Touch the Weather Tab. 4) Press the MENU Key. 5) Touch Restore Category Defaults. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 147 NEXRAD Radar (CONUS high resolution) NEXRAD Radar (CONUS low resolution) NEXRAD Radar (Regional high resolution) NEXRAD Radar (Canada) Satellite Mosaic Surface Precipitation Surface Analysis Sea Surface Temperatures Echo Tops Surface Pressure Lightning Storm Cells 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 148 Due to the inherent delays and the relative age of the data, it should be used for long-range planning purposes only. Never use NEXRAD data or any radar data to penetrate hazardous weather. Rather, use it in an early-warning capacity of pre-departure and enroute evaluation. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 149: Nexrad Abnormalities

• Page 150 When Combined radar data is viewed, Regional Radar data is displayed on top of CONUS data and the time shown in the lower left corner is associated with Regional Radar data only. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 151 Echo Tops at or above the altitude you select are displayed, in 5,000 foot increments up to 70,000 ft. Echo Tops can be helpful in determining the severity of thunderstorms. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 152 A short wind flag is 5 knots, a long wind flag is 10 knots, and a triangle flag is 50 knots. Winds Aloft Data Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 153 Isobars that are packed closely together show a strong pressure gradient. Strong gradients are associated with areas of stronger winds. Pressure units can be displayed in Millibars (mb) and Inches of Mercury (in). Surface Pressure Data 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 154 The tip of the arrow indicates where the storm should be in 15 minutes. Critical information about the storm cell (tops and intensity) can be viewed by touching the storm cell. Storm Cell Data Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 155 IFR (ceiling 500 to below 1000 feet AGL and/or visibility 1 mile to less than 3 miles) Low IFR (ceiling below 500 feet AGL or visibility less than 1 mile) METAR text does not contain adequate information to determine flight conditions 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 156 A SIGMET is widespread and must affect or be forecast to affect an area of at least 3,000 square miles. SIGMETs are displayed as a yellow-dashed line. AIRMET Selected Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 157 PIREPs are issued as either Routine (UA) (blue) or Urgent (UUA) (yellow). Urgent (UUA) PIREP Routine (UA) PIREP Selected PIREP Data 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 158 Turbulence data identifies the potential for erratic movement of high-altitude air mass associated winds. Turbulence is classified as light, moderate, severe, or extreme. Turbulence data is intended to supplement AIRMETs and SIGMETs. Severe Turbulence Selected Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 159 Forecasts are available for intervals of 12, 24, 36, and 48 hours. Forecast Data Sunny Thunderstorms Windy Very Hot Partly Cloudy Rain Haze Mostly Cloudy Freezing Rain Foggy Cloudy Snow Very Cold Forecast Legend 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 160: Terrain

Page 161: synthetic vision, page 162: obstacle information, page 163: terrain settings, page 164: terrain alerts.

• Page 165 “terrain ahead! pull “obstacle ahead! pull “sink rate, pull up!” up!” up!” Warning “terrain! terrain! pull “obstacle! obstacle! “pull up!” up! pull up!” pull up! pull up!” Aural Alerts Summary 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 166 Hazard Avoidance PFD Terrain Alert Pop-up Alert MFD Terrain Alerts Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 167: Traffic Systems

Page 168: traffic information service (tis-a) (optional), page 169: traffic symbology.

• Page 170 A traffic voice alert is generated whenever the number of Traffic Advisories on the G3X Touch screen increases from one scan to the next. Limiting Traffic Advisories only reduces the “nuisance” alerting due to proximate aircraft. For example, when the first Traffic Advisories appear on the TIS-A display, the user is alerted audibly.
• Page 171 Traffic Warning Window Traffic Warning Window NOTE: The Traffic Warning Window is disabled when the aircraft ground speed is less than 30 knots or when on the approach leg of a route. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 172: Displaying Traffic Information

Page 173: garmin gts 800 traffic (optional), page 174: theory of operation.

• Page 175 TA criteria. A Traffic Advisory that is beyond the selected display range (off scale) is indicated by a half TA symbol at the edge of the screen at the relative bearing of the intruder. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 176 Traffic Page and in the lower-left of the PFD inset map instead of a TA symbol. The text will indicate “TA” followed by the distance, relative altitude, and vertical trend arrow for the TA traffic, if known. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 177 600 feet. Intruder range is within 0.2 nm and vertical separation is within 600 feet. Intruder closing rate provides less than 15 seconds of separation. Intruder range is less than 20 seconds. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 178 1) From the Traffic Page, touch + or - to set the range to 2/6 nm to allow the full test pattern to be displayed during test. 2) Press the MENU Key. 3) Touch Self-test. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 179: Switching From Standby Mode To Operating Mode

Page 180: traffic page.

• Page 181 Hazard Avoidance Traffic Non-Threat Advisory, Traffic, 700’ above, 500’ above, Climbing Descending Traffic Display Range Rings Traffic Page (GTS 800) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 182: Data Link Traffic (Gdl 39/39R) (Optional)

• Page 183 Currently, rule-compliant ADS-B Out capability in the United States requires a TSO’ed SBAS-enabled GPS, such as a Garmin GPS 400W or similar, and one of two possible data links: 1090 ES transponder or a 978 MHz UAT. Either data link system is capable of transmitting the aircraft’s position, velocity, identification, and other...
• Page 184 GPS and 1090 ES transponder, a GBT may not identify it as an ADS-B participating aircraft. The squitter of some 1090 ES transponders, including the Garmin GTX 23ES, must be configured to communicate that the aircraft has 978 MHz receive capability in order to be identified as an ADS-B participating aircraft.

Page 185: Traffic Description

Page 186: symbol description.

• Page 187 See the Additional Features Section for more information about Synthetic Vision. ADS-B Symbol on the PFD Description (Synthetic Vision Only) Proximity Advisory (PA) Traffic Advisory (TA) Non-threat traffic PFD ADS-B Symbology (Synthetic Vision Only) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 188 TRAFFIC ALERTS (ADS-B TIS-B) A traffic voice alert is generated whenever the number of Traffic Advisories on the G3X Touch display increases. Limiting Traffic Advisories only reduces the “nuisance” alerting due to proximate aircraft. For example, when the first Traffic Advisories appear on the display, the user is alerted audibly.
• Page 189 10) Touch Off, Auto, or a range. Enabling/disabling traffic on the Synthetic Vision display: 1) Touch the HSI or Attitude Indicator on the PFD. 2) Touch More Options. 3) Touch Traffic to toggle traffic on and off. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 190 ‘Normal’ Displaying/Removing the Traffic Page: 1) From the Traffic Page, press the MENU Key. 2) Touch the Traffic Page 3) Touch Show or Hide. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 191 • Unrest: (unrestricted): All traffic is displayed from 9900 feet above and 9900 feet below the aircraft. Traffic Display Range Rings Altitude/ Operating Mode Directional Traffic, 300 feet above Traffic System Status Receiving Air-to-Air and no TIS-B Traffic Traffic Page (GDL 39/39R) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 192 The TargetTrend look-ahead time interval is automatically adjusted from 30 seconds to five minutes and corresponds to the traffic display range setting. The greater the range setting, the longer the time interval and vise versa. Refer to the table below for more details. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 193 Motion vector selection is made from the Traffic Page Menu by enabling/disabling TargetTrend. Absolute vectors are selected by default and are replaced when TargetTrend is enabled. Enabling/Disabling TargetTrend: 1) From the Traffic Page, press the MENU Key. 2) Touch the TargetTrend. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 194 Hazard Avoidance Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 195: Section 8 Additional Features

Page 196: synthetic vision (svx), page 197: additional features, page 198: synthetic vision operation.

• Page 199 Climb profiles cannot be displayed due to the variables associated with aircraft performance. Flight plan legs requiring a climb are indicated by pathways displayed at a level above the aircraft at the altitude selected. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 200 If LOC is the selected navigation source on the HSI, the pathways boxes are green for the ILS. Pathways boxes are not displayed for segments such as heading legs or VOR radials. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 201 Descending final approach segment displayed by pathway Pathways - Enroute, Descent, and Approach iSSed PProaCh Pathways are displayed at the selected altitude upon activating the missed approach on the external GPS navigator. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 202: Flight Path Marker

• Page 203 1) Touch the Attitude Indicator or HSI to display the PFD Options. 2) Touch More Options. 3) Touch and drag to scroll down. 4) Touch Traffic to toggle synthetic vision traffic on and off. Traffic Synthetic Vision Traffic 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 204: Airport Signs

• Page 205 As the aircraft gets closer to the runway, more detail such as runway numbers and centerlines are displayed. Other Runway on Airport Runway Selected for Approach Airport Runways 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 206 In these cases, the conflict is outside the Synthetic Vision field of view and the alert will have arrows indicating the direction of the alert. Terrain Annunciation Terrain Warning PFD Terrain Alert Potential Impact Points Pop-up Alert MFD Terrain Alerts Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 207 (earth) or blue (sky) colored bar at the top or bottom of the screen is displayed to prevent the pilot from losing sight of the horizon. Blue Band Terrain Completely Fills Display Blue Sky Bar with Full Display Terrain 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 208 1) From the Map Page press the MENU Key. 2) Touch Set Up Map. 3) Touch and drag the tabs to scroll. 4) Touch the Miscellaneous Tab. 5) Touch the Field of View 6) Touch On or Off. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 209: Safetaxi

Page 210: safetaxi cycle number and revision.

• Page 211 Therefore, when the aircraft symbol appears within one of these areas, the aircraft position indicated is relative to the chart planview, not to the off-scale area. Off-Scale Area Off-Scale Areas Sample Chart Indicating Off-Scale Areas 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 212: Aircraft Symbol

Page 213: jeppesen database-published notams.

• Page 214 Therefore, when the aircraft symbol appears within one of these areas, the aircraft position indicated is relative to the chart planview, not to the off- scale area. Off-Scale Off-Scale Areas Area Off-Scale Areas Off-Scale Area Sample Chart Indicating Off-Scale Areas Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 215 “CHART NOT AVAILABLE” appears on the screen. The “CHART NOT AVAILABLE” banner does not refer to the FliteCharts subscription, but rather the availability of a particular airport chart selection or procedure for a selected airport. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 216: Aircraft Symbol

Page 217: airport directory data.

• Page 218 Additional Features Airport Identifier Service Icon Airport Directory Information Icon Description Restaurant on Field Self Serve Fuel Courtesy Car Airport Directory Service Icons Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 219: S Irius Xm Radio Entertainment (Optional)

Page 220: selecting a category, page 221: vertical power (optional).

• Page 222 Selecting and controlling an electrical device from the list: 1) With the VP-X Page displayed, touch the desired device. 2) Press the MENU Key. 3) Touch the desired function from the list. Select touch Reset, to reset a faulted device. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 223: Electronic Checklists (Optional)

• Page 224 Additional Features Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 225: Section 9 Automatic Flight Control Systems (Optional)

• Page 226 The pitch trim servo commands the motor to reduce the average pitch servo effort. NOTE: Auto-trim may also be configured for the roll and/or yaw axis. Consult the G3X Touch installation manual for configuration and installation options. The autopilot roll axis uses roll rate to stabilize aircraft roll attitude during flight director maneuvers.

Page 227: G3X Touch Afcs Installations Options

Page 228: control wheel steering (cws) (optional).

• Page 229 AFCS Flight Director Autopilot Modes Yaw Damper Status Lateral Modes Vertical Modes Active Active Active Armed Active Autopilot Status Box Selected Altitude Autopilot Display 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 230: Afcs Operation

• Page 231 The G3X Touch can also communicate with various third-party autopilot units. With an appropriate third-party autopilot installed and the G3X Touch Integrated Autopilot Interface is configured (refer to the G3X Touch Installation Manual), the G3X Touch issues pitch and roll steering commands to the autopilot unit. The autopilot unit is then responsible for moving the flight controls.

Page 232: Afcs Pre-Flight Actions

Page 233: afcs controls.

• Page 234 Speed, Indicated Airspeed, and Altitude Hold modes Selects/deselects Indicated Airspeed Mode Selects/deselects Altitude Hold Mode VNAV Selects/deselects vertical navigation Selects/deselects approach mode APPR Selects/deselects Vertical Speed Mode Activates/deactivates the flight director only Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 235 AFCS G3X Touch Autopilot 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 236 When properly configured with a GTN, if an approach procedure is loaded, this switch also activates the missed approach when the selected navigation source is GPS or when the navigation source is VOR/LOC and a valid frequency has been tuned. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 237: Engaging The Autopilot

• Page 238 3) Retrim the aircraft as needed. Substantial trim adjustment may be needed. 4) Pull the appropriate circuit breaker(s) to electrically isolate the servo and solenoid components. 5) Release the AP DISC Switch. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 239: Flight Director Operation

Page 240: flight director modes, page 241: command bars, page 242: vertical modes.

• Page 243 Selected Altitude VS G3X Touch IAS Key Maintains the current aircraft Indicated airspeed in IAS while the aircraft (GMC Airspeed 1 kt is climbing/descending to the (IAS) Selected Altitude only) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 244 * ALTS armed automatically when PIT, VS, IAS, or GA active, and under VNAV when Selected Altitude is to be captured instead of VNV Target Altitude ** ALTV armed automatically under VNAV when VNV Target Altitude is to be captured instead of Selected Altitude Flight Director Vertical Modes Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 245: Pitch Hold Mode (Pit)

Page 246: selected altitude capture mode (alts), page 247: altitude hold mode (alt), page 248: vertical speed mode (vs), page 249: indicated airspeed mode (ias) (gmc 305 only), page 250: vertical navigation mode (vnav), page 251: vnav target altitude capture mode (altv).

• Page 252 10 seconds to indicate the automatic transition. Automatic Transition to ALTV Mode with ALT Mode Armed Automatic Transition Altitude from ALTV to ALT Mode Reference Automatic Mode Transitions During Altitude Capture Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 253: Glidepath Mode (Gp) (With External Waas Enabled Ifr Navigator Only)

Page 254: glideslope mode (gs), page 255: go around (ga) and takeoff (to) modes (gmc 305 only), page 256: lateral modes.

• Page 257 Flight Director Lateral Modes The CWS Button (if equipped) does not change lateral references for HDG or NAV modes. The autopilot guides the aircraft back to the Selected Heading/Course upon release of the CWS Button. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 258: Roll Hold Mode (Rol)

Page 259: heading select mode (hdg), page 260: navigation modes (gps, vor, loc, bc).

• Page 261 2) EXTERNAL NAVIGATOR: Load the approach (LOC, ILS, LDA, SDF, etc) into the flight plan. 3) G3X Touch: While GPS is still the selected navigation source on the external navigator, press the APR Key (GMC 305) or touch APPR to arm LOC and GS (Glideslope) Modes even with GPS Mode still active.
• Page 262 Flight Plan Page menu option is now available. 2) From the Active Flight Plan Page press the MENU Key while navigating a flight plan or Direct-to. 3) Touch Set OBS and Hold. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 263 3) G3X Touch: Ensure that VOR1 or VOR2 is the selected navigation source. It should say ‘VOR1’ or ‘VOR2’ on the HSI and the needle should be green. 4) G3X Touch: From the PFD, touch the course on the PFD and touch Sync Course.

Page 264: Approaches Without Vertical Guidance

• Page 265 2) EXTERNAL NAVIGATOR: Ensure the ‘GPS’ indication is showing in the . If not, press the CDI Key. lower-left corner 3) G3X Touch: Ensure that GPS1 is the selected navigation source on the PFD. 4) EXTERNAL NAVIGATOR: Select and activate the GPS approach using the PROC Key.
• Page 266 2) G3X Touch: Ensure that LOC1 is the selected navigation source. The HSI should automatically slew the needle to the correct course. 3) G3X Touch: From the PFD, touch the autopilot and touch NAV to activate LOC Mode. Or: Press or the NAV Key on the GMC 305...

Page 267: Approaches With Lateral + Vertical Guidance

• Page 268 LOC Mode (lateral) and GS Mode (vertical) are both armed by touching APPR from the G3X Touch PFD or by pressing the APR Key on the GMC 305. LOC/ILS approach captures are inhibited if the difference between aircraft heading and localizer course exceeds 105˚.
• Page 269 VLOC Flip-flop Key. (Note: The external navigator should have automatically loaded the localizer frequency into the standby VLOC slot.) 6) G3X Touch: From the PFD touch the autopilot and touch APPR to arm LOC and GS modes. Touch ALT.
• Page 270 LVL Key is pressed all armed and active modes are cancelled and the autopilot and flight director revert to LVL mode for pitch and roll. While in level mode, all other modes are available by pressing the corresponding button. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 271: Section 10 Annunciations & Alerts

Page 272: airspace messages, page 273: system status messages, page 274: system status messages.

• Page 275 [GDU name] terrain database The PFD and MFD have different terrain mismatch database versions installed. Install the correct terrain database on all displays for proper terrain/obstacle alerting. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 276 The display should be serviced when possible. Not receiving external GPS Not receiving RS-232 data from the specified [number] RS-232 Aviation data external GPS navigator. Not receiving GTX TIS-A RS-232 Not receiving RS-232 data from the GTX. data Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 277 Power unit. Using internal flight plan for Communication with the external GPS navigation navigation source has failed. The G3X Touch internal flight plan is being used for navigation. Aviation waypoint was deleted A waypoint that was part of a stored flight plan was deleted from the latest navigation database.

Page 278: Audio Alerts

Page 279: pfd annunciations and alerting functions, page 280: ahrs alerts (optional), page 281: afcs alerts (optional), page 282: vertical power fault indications, page 283: section 11 appendices.

• Page 284 WPT - Next Waypoint The next waypoint in the flight plan or direct-to route. XTK - Crosstrack Error The distance the aircraft is from a desired course in either direction, left or right. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 285 Flight Timer (FLT TIMER) Total time in-flight (HH:MM). Fuel Economy (ECONOMY) Current Mile Per Gallon (MPG), based upon ground speed and fuel flow. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 286 The selection now playing on SiriusXM Radio. (SXM) Time En Route (Destination) The estimated time it takes to reach the destination waypoint from the present position, based upon (ETE DEST) current ground speed. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 287 The relative humidity at the nearest weather reporting station. (WX HUMIDITY) Wx (Temperature) The temperature at the nearest weather reporting station. (WX TEMP) Wx (Wind) (WX WIND) The wind speed and direction at the nearest weather reporting station. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 288 Appendix A Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 289: Appendix B: Utilities

• Page 290 Appendix B Flight Log List (Split-Screen) Flight Log Map (Split-Screen) Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 291: Track Log

Page 292: displaying/removing the track log on the map page.

• Page 293 Appendix B Map Page Menu Map Setup Page - Line Tab 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 294: Changing Track Log Settings

• Page 295 5) If Selected Flight or Selected Dates are chosen, select the flight or dates using the buttons. 6) Touch the OK Button to save the track, or touch the Cancel Button to cancel the save. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 296: Heading Line

• Page 297 Touch the Time Button to define the length of the heading line by time. Touch the + Button or - Button to select the time. 6) Press the BACK Key to return to the Map Page. Heading Line Settings (Map Setup Page) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 298: Weight & Balance

• Page 299 1) From the Weight & Balance page, press the MENU Key. 2) Touch the Empty Aircraft Button. 3) Touch the Yes Button to empty the aircraft, or touch the No Button to cancel the action. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 300: Proximity Waypoints

• Page 301 1) Press the MENU Key twice to open the Main Menu. 2) Touch the Setup Button. The Setup Page is displayed. 3) Touch the Alarms Button. The Alarms Setup Page is displayed. 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 302 4) Press the MENU Key. The Proximity Waypoint Menu is displayed. 5) Touch the Delete All Button. 6) Touch the Yes Button to delete all proximity waypoints, or touch the No Button to cancel the deletion. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 303: Appendix C: Sd Card Use And Databases

Page 304: g3x touch databases, page 305: navigation database.

• Page 306 70 days after the expiration date and is no longer available for viewing. The ChartView database is always on the SD Card and is not copied to the GDU’s internal memory. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 307: Updating G3X Touch Databases

• Page 308 • Windows-compatible PC computer (Windows 2000 or XP recommended) • Verbatim 96504 SD Card Reader or equivalent • Updated database obtained from the flyGarmin website • SD Card, 8 GB recommended (Garmin recommends SanDisk or Toshiba SD cards) Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 309 2) Power on the display. The Update Databases Page is displayed. A green checkbox indicates that the database installed on the G3X Touch is up to date. An empty checkbox indicates that the database on the SD card is more current and should be installed.

Page 310: Importing/Exporting/Renaming Flight Plans

Page 311: flight data logging.

• Page 312 Appendix C Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 313: Appendix D: Map Datum And Location Formats

• Page 314 Appendix D Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 315: Appendix E: General Tis-A Information

Page 316: tis-a limitations.

• Page 317 • By telephone to the nearest Flight Service Station (FSS) facility • By FAA Form 8000-7, Safety Improvement Report (postage-paid card can be obtained at FAA FSSs, General Aviation District Offices, Flight Standards District Offices, and General Aviation Fixed Base Operators) 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 318 Appendix E Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 319: Appendix F: Abnormal Operation

Page 320: g3x touch system failure annunciations, page 321: reversionary mode (full-screen), page 322: afcs reversionary mode, page 323: appendix g: display symbols, page 324: ifr symbols.

• Page 325 VOR/DME VFR, Soft Surface, Non- ILS/DME or DME Only serviced VFR, Soft Surface, Serviced VORTAC VFR, Soft Surface, Private TACAN VFR, Paved, Private Navaids VFR Seaplane Base VFR Heliport Americas/Pacific Database Airports 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 326: Airspace Symbols

• Page 327 Appendix G Item Symbol Item Symbol Danger or Alert Training Area Area Restricted, IFR Atlantic Database Exceptions Prohibited, or Warning Area Training Area VFR Atlantic Database Exceptions 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 328 Appendix G Blank Page Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 329: Appendix H: Glossary

• Page 330 Estimated Time The estimated time it takes to reach the destination waypoint Enroute from the present position, based upon current ground speed. Estimated Time of Arrival Estimated Time Enroute Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 331 Transceiver participating aircraft. Ground Track see Track Ground speed The direction an aircraft is pointed, based upon indications Heading from a magnetic compass or a properly set directional gyro. mercury hectopascal hour 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 332 Missed Approach Point METAR Meteorological Aviation Routine megahertz Minimum Safe Uses Grid MORAs to determine a safe altitude within ten Altitude miles of the aircraft present position. Military Operations Area Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 333 SBAS Satellite-Based Augmentation System Secure Digital second(s) SIGMET Significant Meteorological Information TACAN Tactical Air Navigation System Terminal Aerodrome Forecast True Airspeed terrain Temporary Flight Restriction TOPO topographic TIS-A Traffic Information Service 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 334 VHF Omni-directional Range very high frequency omnidirectional range station and VORTAC tactical air navigation Vertical Speed Indicator Vertical Speed Required vector to final WAAS Wide Area Augmentation System waypoint weather Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...

Page 335: Appendix I: License Agreement And Warranty

Page 336: aopa airport directory notice, page 337: ac-u-kwik license agreement.

• Page 338 Neither NGA nor its personnel will be liable for any claims, losses, or damages arising from or connected with the use of this product. The user agrees to hold harmless the United States National Geospatial-Intelligence Agency. The user’s sole and exclusive remedy is to stop using the DAFIF product. Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 339 Course Deviation Indicator (CDI) 46 Approach 118 Crew Alerting System (CAS) 67, 70, 71, Activating Vectors-to-Final 121 Chart 119 Current Icing Product (CIP) 141 Loading 119 Cylinder Head Temperature 64 Removing 120 Selecting 119 Index-1 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 340 Fuel Range Ring 89 Field of View 190 FIS-B 165 Garmin Display Unit (GDU) 28 Flight director (FD) 212 Garmin Sensor Unit (GSU) 2, 3 Modes, vertical 224–238 GBT 165 Flight Information Service-Broadcast GDL 39 125, 126, 149, 164, 166, 173...
• Page 341 Lean Assist 67 METAR 137 Legends 129 Flag Color 137 License Agreement 317 Limited Warranty 317 Line Replaceable Unit (LRU) 1 Navigation Mode 242–243 Location Formats 27, 295 Navigation Source 49 Index-3 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...
• Page 342 PIREP 139 Synthetic Vision (SVX) 177 Pitch Hold Mode 227 System Position 20 Annunciations 11 Settings 27 Date & Time 26 Power-up 9 Functionality 13 Proximity Waypoints 282 Initialization 9 Power-up 9 Index-4 Garmin G3X Touch Pilot’s Guide 190-01754-00 Rev. A...
• Page 343 Limitations 298 traffic warning window 170 Warranty 317 Traffic Warning Window 152, 153 Waypoints 95, 101 Transponder Creating 101 Status Box 33 User 101 True Airspeed (TAS) 33 Weather Information 99 Index-5 190-01754-00 Rev. A Garmin G3X Touch Pilot’s Guide...

Page 344: Index

• Page 346 Hounsdown Business Park Southampton, SO40 9RB, U.K. Toll free (within U.K.) 0808.2380000 p: 44/0870.8501241 f: 44/0870.8501251 Garmin Corporation No. 68, Jangshu 2nd Road Shijr, Taipei County, Taiwan p: 886/2.2642.9199 f: 886/2.2642.9099 www.garmin.com 190-01754-00 Rev. A © 2014 Garmin Ltd. or its subsidiaries...

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Garmin G3X GEA 24B Engine Interface Unit Only 010-02770-00

GARMIN GAD 29C ARINC 429 INTERFACE

Garmin G3X GDU 450 455 7 Inch Screen Install Kit

Garmin G3X GDU 470 7 INCH PORTRAIT TOUCH DISPLAY

Garmin GTR 20 Remote COM Radio For G3X Touch Only

GARMIN GAD 29 CONNECTOR KIT

Garmin G3X LRU Standard Kit GSU 25C GMU 11 GTP 59 And Config Mod

GARMIN GSU C/D CONNECTOR KIT K10-00181-00

GARMIN GMU 11 CONNECTOR KIT

Great product with excellent quality...

This is a most when you need redundancy...

Great product as always very reliable. Great compatibility easy installation and operation with great features.

Battery worked fine. To install you need an Allen wrench the same size as your battery screws. This winch also fits the Allen screw in the center bottom hole on the G-5. The one screw holds the G-5 in the panel. Slide it out and replace the battery. Very easy.

The part is as expected, good quality

Garmin G3X AOA GAP 26 Heated And Regulated Pitot Tube 14v

Great service and product

GARMIN GMC 507 AUTOPILOT MODE CONTROLLER INSTALL RACK

Not only does it melt accumulated ice, it makes a great hand warmer.

Garmin G3X AOA GAP 26 Heated Pitot Tube 14v

Garmin GMU 11 Magnetometer For G3X / G5 010-01788-00

CAUTION! Excelent option for cheap, easy, and quick glass upgrade, BUT unit only comes with NOTHING! You MUST purchase an installation kit with it just to mount it and turn it on. THIS SHOULD BE MADE CLEARER UPFRONT! Other that that, love it.

just simply the best! cheap and reliably

This product was ordered to complete an installation for a customer and it arrived on time as promised. The quality is standard Garmin, no problems.

Good product and good service

Expensive but supposed to be better for backseat passengers...Nice part

GARMIN GSA 28 MOUNTING KIT RV 10 YAW DAMPER

Excellent part

GARMIN GSA 28 SERVO INSTALL KIT FOR RV 10 PITCH

I do not like anything made by Garmin. They do not know what intuitive user interface is. Period. Also their technical support is terrible. I purchased this radio for lack of options. The ones that I wanted to buy were out of stock. Well, here I was purchasing a Garmin product for the first time. I have to admit, the radio impressed me very well. What I really like about the whole thing is the installation manual. Its really well written. It explains every single step of the way on how to install it. Seriously, a kid can do it just reading the manual. After installation I call Ground here at KCHD and the radio was working great. Clear and loud. One of the high points of this radio for me is the display. I can see the big number even when the sun is hitting the panel directly. Very good radio. I cannot say anything about lasting. Time will tell. Will see.

A must have when one buys the G5

GARMIN GSA 28 SERVO INSTALL KIT FOR RV 4 8 PITCH

I received the next day thank you just what I ordered

So far, we purchased 2 dead ones.

Everything was as expected, nicely put together kit.

GARMIN GSA 28 SERVO INSTALL KIT FOR RV 7 8 10 ROLL

Comprehensive kit, arrived quickly.

GARMIN GSA 28 SERVO INSTALL KIT FOR RV 6 7 9 PITCH

Great radio

I ordered this to replace a 14 year old Garmin SL40 that was functioning as Com 2 but had fading reception and an inop volume control. The only connections the GTR200 needed were the external antenna, power, ground, and five wires going to the audio panel. Fabricating a new wiring harness was made relatively simple by the fact that during the original build, I had positioned in-line connectors (DB9 or DB25 computer connectors, to be exact) in between all avionics in the stack and all other units. So it was only necessary to terminate the new wiring in a DB9 connector that matched the pinouts of the original wiring. A bonus of having the new unit is that it has a 10 watt transmitter vs. 8 watts for the old one, and a much more informative digital display e.g., when monitoring two frequencies at once, it shows which one is receiving a transmission at the moment. A minor annoyance was that Garmin radio trays apparently now are just a smidge wider than they used to be. The standard 6.25 inch width has now become 6.30” – just enough that new trays won’t slide easily into stacks of older radios without some creativity with a flat file to make the opening a bit wider. Luckily the height of the GTR200 is the same as the SL40 (even though the Garmin specs say it isn’t!) so neither the GNS480 navigator above the radio or the GTX330ES transponder below it had to be moved. Oh, and the new unit works great. : )

GARMIN GSA 28 SERVO INSTALL KIT GENERIC WITH MOUNT BRACKET

Works alright

Cannot leave review of this product as I have not installed it yet.

The GSA-28 is a good servo, I hope. But I was not lucky - she did not work a single day and broke down. The PFD started showing the message Servo Hardware Fault a year after installation, although I did not turn on the autopilot even once. And one more thing: GSA-28s have insufficient power, for example, the Pitch-servo cannot raise the elevator of stabilizer on my Cessna-182 when its on th ground. I have ordered one new and got it during 10 days - its very good!

Excellent product. Easy to install.

This is a high-quality connector kit. It was a better deal to buy this than two separate connector kits.

Well built but too expensive for what you get. Unfortunately it is the only option unless you want to build it yourself

The only reason I didn’t give this probe 5 stars was that I had to wait over 2 weeks for it to arrive...

First battery I got was dead out of the box and would not charge. I had to pay for shipping to return it, which was annoying. 2nd one is working fine so far...

Aircraft Spruce gets 5 stars, Garmin 2. The batteries are very expensive and unreliable. The last one failed after 2 years of light use. Garmin needs to find somebody else to make their batteries. To be fair, the battery installed easily, worked properly and I received what I expected. Unfortunately, it may not last very long. At least they are readily available and easy to replace.

This Garmin product has been quite the disappointment. I have 3 G-5’s installed and two batteries have already become unserviceable and needed replacement at a cost of over $400 USD. After installing the two “new” batteries neither of them will attain a 100% charge and continue to discharge at a very high rate requiring me to regularly charge the batteries while connected to an external charger. All three G-5’s have the latest firmware update too. The strange thing is that the original battery installed in one of the G-5’s continues to function as advertised. I would not purchase another one of these batteries until Garmin addresses this problem which they are already aware of.

Still have yet to receive this portion of my order. After two weeks on the phone with support no one seems to care to make this right.

this radio will not integrate with 2 radio panel making the built in intercom useless.

Please note, Aircraft Spruce's personnel are not certified aircraft mechanics and can only provide general support and ideas, which should not be relied upon or implemented in lieu of consulting an A&P or other qualified technician. Aircraft Spruce assumes no responsibility or liability for any issue or problem which may arise from any repair, modification or other work done from this knowledge base. Any product eligibility information provided here is based on general application guides and we recommend always referring to your specific aircraft parts manual, the parts manufacturer or consulting with a qualified mechanic.

You would have to run the GDU 370/375 completely separate with its own GPS signal and rewire the G3X touch to be the main display with your existing LRUs.

Yes, you would still need to purchase the connector kit in addition to the harness.

You would need the GDU 460/465 Install Kit (11-12646), GSU 25 Connector Kit (11-11433), and the GMU 22 Install Kit (11-12213).

For the VFR harness all of the components including the engine leads are included minus connection to an auto pilot and audio panel (which have there own part numbers on our list). When ordering a G3X system, we will send you a worksheet to fill out for your unique setup.

As each G3X harness we create is unique, there is a form that you would fill out which will includes the features you want including and pricing.

11-11433 is the GSU 25 connector kit by itself. Part # 11-15303 is the GSU 25 connector kit with a custom harness.

The non-touch screens are no longer available. We only offer the touch screen G3X now.

You will need to purchase a GMA 245 audio panel or 245R remote audio panel to support a 4 place aircraft.

Per the manual, yes, the G3x can display twin engine data.

Included: (2) 10" GDU 460, ADAHRS GSU 25, Magnetometer GMU 22, GEA 24, Temperature Probe GTP 59, Config Mod, w/sockets, Jackscrew. Connector kits are available but sold separately.

The dimensions are 6.01 inch x 7.82 inch x 3.68 inch

(6 ea) CHT Type K Thermocouple, 3/8-24 Bayonet (6 ea) EGT Type K Thermocouple, Bayonet Oil Temperature, RTD, 5/8-18 UNG-3A Fuel Flow, 1/4" Female NPT Ammeter, Shunt, +/-50 mV, 100 amps Oil Pressure, 150 PSIG, 1/8-27 NPT Manifold Pressure, 30 PSIA, 1/8-27 NPT

The heated, regulated version of the GAP 26 (010-010704-20) has a small box with the regulating circuitry that is mounted near the probe. This version of the GAP 26 probe is also equipped with an internal temperature sensor which the regulating circuit uses to only supply as much current as the probe needs to remain ice free. This current, of course, varies with the operating conditions.

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Garmin G3X Touch Installation Manual online

Table of Content

• Installation manual 1
• Record of revisions 2
• 01115 01 g3x installation manual rev u page i 3
• Current revision description 3
• Cautions are used to alert the individual that damage to equipment may result if the procedural step is not followed to the letter 4
• Definitions of warnings cautions and notes 4
• Notes are used to expand and explain the preceding step and provide further understanding of the reason for the particular operation 4
• Warnings are used to bring to the installer s immediate attention that not only damage to the equipment but personal injury may occur if the instruction is disregarded 4
• Limited warranty for g3x products 6
• Section 1 inventory of materials 1 7
• Section 2 installation preparation 1 7
• Section 3 gad 29 arinc 429 adapter installation 1 7
• Section 4 gap 26 pitot aoa probe installation 1 7
• Section 5 gdu 37x display unit installation 1 7
• Section 10 gmc 305 afcs mode controller installation 0 1 8
• Section 6 gdu 45x display unit installation 1 8
• Section 7 gdu 46x display unit installation 1 8
• Section 8 gea 24 eis interface installation 1 8
• Section 9 gi 260 aoa indicator installation 1 8
• Section 11 gmc 307 afcs mode controller installation 1 1 9
• Section 12 gmu 22 magnetometer installation 2 1 9
• Section 13 gps 20a waas gps position source installation 3 1 9
• Section 14 gsa 28 autopilot servo installation 4 1 9
• Section 15 gsu 25 25b ahrs air data sensor unit installation 5 1 9
• Section 16 gsu 73 sensor unit installation 6 1 9
• Section 17 gtp 59 temperature probe installation 7 1 10
• Section 18 gtr 20 vhf communications radio installation 8 1 10
• Section 19 gps xm antenna installation 9 1 10
• Section 20 engine airframe sensor installation 0 1 10
• Section 21 connector installation instructions 1 1 10
• Section 22 lru pinouts 2 1 10
• Section 23 g3x w gsu 25 and or gad 29 interconnect drawings 3 1 11
• Section 24 g3x w gsu 73 interconnect drawings 4 1 11
• Section 25 g3x w gtr 20 interconnect drawings 5 1 11
• Section 26 sensor wiring examples 6 1 11
• Section 27 lycoming continental sensor wiring examples 7 1 11
• Section 28 rotax sensor wiring examples 8 1 11
• Section 29 jabiru sensor wiring examples 9 1 11
• Appendix a airframe specific installation guidance a 1 12
• Section 30 gdu 37x configuration and post installation checkout 0 1 12
• Section 31 gdu 45x 46x configuration and post installation checkout 1 1 12
• Section 32 troubleshooting 2 1 12
• Section 33 maintenance 3 1 12
• Appendix b rs 232 text output format b 1 13
• Appendix c lru performance specifications licensing compliance c 1 13
• Inventory of materials 14
• Required garmin equipment 14
• The g3x lru kit w gsu 25 no eis table 1 1 is intended for customers who have previously purchased only a gdu 37x or 46x display this kit includes the lrus needed to complete a g3x system installation does not include connector installation kits listed in table 1 29 14
• Unpacking unit 14
• 01115 01 g3x installation manual inventory of materials rev u page 1 2 15
• Garmin lru line replaceable unit list for gdu 37x systems 15
• Table 1 2 contents of g3x w gsu 73 lru kit k10 00016 00 15
• Table 1 2 through table 1 9 list the available core g3x lrus for gdu 37x systems the g3x lru kit table 1 2 is for g3x installations using the gsu 73 the kits in table 1 3 through table 1 9 are for g3x installations using the gsu 25 25b each gdu 37x 010 00667 xx comes with all equipment needed for installation table 1 10 15
• Table 1 3 contents of gdu 370 single display kit no eis k10 00016 05 15
• Table 1 4 contents of gdu 370 single display kit w eis k10 00016 10 15
• 01115 01 g3x installation manual inventory of materials rev u page 1 3 16
• Table 1 5 contents of gdu 370 dual display kit k10 00016 20 16
• Table 1 6 contents of gdu 370 triple display kit k10 00016 30 16
• Table 1 7 contents of gdu 375 w sirius xm single display kit k10 00016 15 16
• 01115 01 g3x installation manual inventory of materials rev u page 1 4 17
• Each gdu 37x assembly 010 00667 xx listed in table 1 3 through table 1 9 includes the gdu and the items listed in table 1 1 17
• Table 1 10 contents of gdu 37x assembly 010 00667 xx 17
• Table 1 8 contents of gdu 370 375 w sirius xm dual display kit k10 00016 25 17
• Table 1 9 contents of gdu 370 370 375 w sirius xm triple display kit k10 00016 35 17
• 01115 01 g3x installation manual inventory of materials rev u page 1 5 18
• Garmin lru line replaceable unit list for gdu 45x systems 18
• Table 1 11 contents of single display gdu 450 system w out eis k10 00016 42 18
• Table 1 11 through table 1 19 list the available core g3x lrus for gdu 45x systems table 1 16 18
• Table 1 12 contents of single display gdu 455 system w sxm w out eis k10 00016 43 18
• Table 1 13 contents of single display gdu 450 system w eis k10 00016 47 18
• Table 1 18 and table 1 19 are mixed gdu 45x 46x systems a gdu 45x installation kit table 1 20 is required for each gdu 45x 010 01056 xx installed 18
• 01115 01 g3x installation manual inventory of materials rev u page 1 6 19
• Table 1 14 contents of single display gdu 455 system w eis w sxm k10 00016 52 19
• Table 1 15 contents of dual display gdu 450 system w eis k10 00016 57 19
• Table 1 16 contents of dual display gdu 460 450 system w eis w sxm k10 00016 58 19
• 01115 01 g3x installation manual inventory of materials rev u page 1 7 20
• Table 1 17 contents of dual display gdu 450 455 system w eis w sxm k10 00016 62 20
• Table 1 18 contents of dual display gdu 455 460 system w eis w sxm k10 00016 63 20
• Table 1 19 contents of dual display gdu 450 465 system w eis w sxm k10 00016 64 20
• 01115 01 g3x installation manual inventory of materials rev u page 1 8 21
• Table 1 20 contents of gdu 45x installation kit 010 12150 01 21
• 01115 01 g3x installation manual inventory of materials rev u page 1 9 22
• Garmin lru line replaceable unit list for gdu 46x systems 22
• Table 1 18 and table 1 19 are mixed gdu 45x 46x systems a gdu 46x installation kit table 1 27 is required for each gdu 46x 010 01057 xx installed 22
• Table 1 21 contents of single display gdu 460 system w out eis k10 00016 40 22
• Table 1 21 through table 1 26 list the available core g3x lrus for gdu 46x systems table 1 16 22
• Table 1 22 contents of single display gdu 465 system w sxm w out eis k10 00016 41 22
• Table 1 23 contents of single display gdu 460 system w eis k10 00016 45 22
• 01115 01 g3x installation manual inventory of materials rev u page 1 10 23
• Table 1 24 contents of single display gdu 465 system w eis w sxm k10 00016 50 23
• Table 1 25 contents of dual display gdu 460 system w eis k10 00016 55 23
• Table 1 26 contents of dual display gdu 460 465 system w eis w sxm k10 00016 60 23
• 01115 01 g3x installation manual inventory of materials rev u page 1 11 24
• Each item listed in table 1 28 contains its own parts list to verify that all parts are included 24
• Garmin lru installation kits 24
• Table 1 27 contents of gdu 46x installation kit 010 12150 00 24
• Table 1 28 contents of g3x w gsu 73 installation kit k10 00017 00 24
• The g3x w gsu 73 installation kit contains the items listed in table 1 28 which are required for the installation of the g3x 24
• The gdu 37x is not included in either the g3x w gsu 73 installation kit k10 00017 00 or the g3x w gsu 73 lru kit k10 00016 00 24
• 01115 01 g3x installation manual inventory of materials rev u page 1 12 25
• A garmin or non garmin gps antenna is required for a g3x installation a garmin or non garmin xm antenna is required for g3x installations using siriusxm weather see section 19 for required materials for antenna installation including mounting brackets doubler plates rivets hardware cables connectors and sealant 25
• Gps xm antenna s 25
• Table 1 29 lru connector installation kits 25
• 01115 01 g3x installation manual inventory of materials rev u page 1 13 26
• Optional garmin lrus 26
• Table 1 30 lists optional garmin lrus that can be installed with the g3x system if any of these lrus are to be used in this installation verify that all required installation materials such as connector kits have been acquired installation information for lrus not documented in this manual can be found in the installation manual for each respective lru 26
• Table 1 30 optional garmin lrus 26
• 01115 01 g3x installation manual inventory of materials rev u page 1 14 27
• Contact and crimp tools table 1 31 lists recommended crimp tools used to build the wiring harnesses for the g3x lrus other equivalent tooling may also be used 27
• Non garmin part numbers shown are not maintained by garmin and consequently are subject to change without notice 27
• Required non garmin equipment 27
• Table 1 31 pin contact and crimp tools part numbers 27
• Wiring cabling considerations the installer will provide all wiring and cabling unless otherwise noted use mil w 22759 16 or other approved wire awg 22 or larger wire for all connections unless otherwise specified the supplied standard pin contacts are compatible with up to awg 22 wire rg400 or rg142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation 27
• Ahrs magnetometer installation considerations aviation checklist editor ace software flightlog conversion software gdu 37x cockpit display unit software gdu 45x cockpit display unit software gdu 46x cockpit display unit software gsu 73 data logger software gsu 73 field calibration tool panel cut out dxf file 29
• Garmin software and documents 29
• Optional 3rd party sensors lrus 29
• Optional garmin equipment non lru 29
• Optional non garmin equipment 29
• Installation preparation 30
• System overview 30
• 01115 01 g3x installation manual installation preparation rev u page 2 2 31
• A g3x system installation can use either gdu 37x or gdu 45x 46x displays but a g3x system installation cannot use gdu 37x and gdu 45x 46x displays 31
• Figure 2 1 g3x interconnect example gdu 37x 31
• Figure 2 1 illustrates an example block diagram of a g3x installation using gdu 37x lrus figure 2 2 illustrates an example block diagram of a g3x installation using gdu 45x 46x lrus the flexibility of the system allows the installer to determine the architecture that best fits each installation only one gdu 37x or gdu 45x 46x display is required but up to three may be used 31
• Refer to figure 2 1 and figure 2 2 to determine which of the optional lrus will be used in the installation and to determine the required interface connections 31
• System architecture 31
• 01115 01 g3x installation manual installation preparation rev u page 2 3 32
• Figure 2 2 g3x interconnect example gdu 45x 46x 32
• Please refer to the g3x touch pilot s guide 190 01754 00 for guidance in using connext bluetooth connections to garmin pilot device s 32
• 01115 01 g3x installation manual installation preparation rev u page 2 4 33
• Do not connect the gap 26 to 28 vdc 33
• Electrical considerations 33
• Gap 26 the 010 01074 00 version of the gap 26 does not require power as it does not have a heater the initial current vs temperature requirements for the 010 01074 10 and 010 01074 20 are listed in table 2 1 see 33
• Gdu 37x current draw must be multiplied by the number of installed gdu 37x units 33
• Power specifications all g3x lrus are capable of operating at either 14 or 28 vdc except the gap 26 010 01074 10 table 2 1 table 2 2 and table 2 3 list supply voltage and current draw for the g3x lrus use this information when determining power supply requirements all installed electrical appliances must be considered when determining total power requirements 33
• Section 4 for acceptable wiring configurations 33
• Table 2 1 gap 26 initial current draw vs probe temperature 10 20 units only 33
• Table 2 2 gdu 37x power requirements 33
• This section presents information required for planning the electrical layout of the g3x installation 33
• To avoid damage to the lrus take precautions to prevent electro static discharge esd when handling connectors and associated wiring esd damage can be prevented by touching an object that is of the same electrical potential as the lru before handling the lru itself 33
• 01115 01 g3x installation manual installation preparation rev u page 2 5 34
• Lru supply voltage current draw 34
• Other lru power requirements 34
• Table 2 3 g3x lru power requirements 34
• Wiring cabling considerations 35
• 01115 01 g3x installation manual installation preparation rev u page 2 11 40
• Figure 6 3 figure 7 6 and figure 10 5 are panel cutout templates for the gdu 37x gdu 45x gdu 46x and gmc 305 respectively 40
• Lru width height depth unit weight weight of unit and connector s 40
• Mechanical considerations 40
• Physical specifications 40
• Table 2 4 g3x lru physical specifications 40
• This section presents all information required for planning the physical layout of the g3x installation 40
• Use table 2 4 to determine panel requirements all width height and depth measurements are taken with unit rack if applicable and connectors lru dimensions are listed in each lru section figure 5 4 40
• 01115 01 g3x installation manual installation preparation rev u page 2 12 41
• Lru width height depth unit weight weight of unit and connector s 41
• Table 2 4 g3x lru physical specifications 41
• Lru sensor installation information 42
• Equipment description 43
• Gad 29 arinc 429 adapter installation 43
• Equipment available 44
• General specifications 44
• Mounting requirements 44
• Unit installation 44
• 01115 01 g3x installation manual gad 29 installation rev u page 3 3 45
• Dimensions are nominal and tolerances are not implied unless speifically stated 45
• Dimensionsin inches mm metric values are for reference only 45
• Figure 3 2 gad 29 outline drawing 45
• Outline and installation drawings 45
• 01115 01 g3x installation manual gad 29 installation rev u page 3 4 46
• Figure 3 3 gad 29 installation drawing no can terminator 46
• 01115 01 g3x installation manual gad 29 installation rev u page 3 5 47
• Figure 3 4 gad 29 installation drawing with can terminator 47
• Optional 47
• Equipment description 48
• Gap 26 pitot aoa probe installation 48
• Equipment available 49
• General specifications 49
• Required equipment 49
• Unit installation 49
• Banded wire 50
• 01115 01 g3x installation manual gap 26 installation rev u page 4 4 51
• 20 version gap 26 20 version gap 26 51
• 20 version gap 26 probe 20 version gap 26 probe 51
• Connect the white connector from the probe to the white connector from the control box this allows the control box to sense probe temperature connect the red connectors from the probe to the red connectors from the control box figure 4 6 this provides power and ground to the heaters the red wires with red connectors from the control box connect to the plain wires with red connectors from the heater and the black wires with red connectors from the control box connect to the banded wires with red connectors from the heater figure 4 5 figure 4 6 the bare red and black heater wires from the control box should be connected to 14 vdc as shown in figure 4 5 the bare blue wire from the control box can be run to a spare discrete input on the gea 24 or gsu 73 section 4 51
• Control box installation 20 version only mount the control box figure 4 8 to a suitable mounting location within two feet of the gap 26 using 4 4 or 6 pan or hex head screws choose screw length that is appropriate to mounting location 51
• Figure 4 4 gap 26 28v installation configuration 010 01074 10 only 51
• Figure 4 5 011 02964 20 probe wiring 51
• Gea 24 or gsu 73 gea 24 or gsu 73 51
• Heater control box heater control box 51
• Notes for 28v installation 1 caution 28v installations must follow this guidance and connect heaters in series as shown or probe will be damaged 2 aircraft power wiring to probe should be minimum 18 awg up to 12 ft 16 awg from 13 to 20 ft and 14 awg from 21 to 30 ft ac 43 3 1b 3 connect banded wires with insulated ms25181 22 18 awg butt splice connector or equivalent banded wires may be shortened if desired 51
• Optional optional 51
• 01115 01 g3x installation manual gap 26 installation rev u page 4 6 53
• Figure 4 7 gap 26 outline drawing 53
• Interpret per asme y14 m 1994 53
• Outline and installation drawings 53
• 01115 01 g3x installation manual gap 26 installation rev u page 4 7 54
• 1 39 1 76 54
• Figure 4 8 gap 26 heater control box used with 20 unit only 54
• Equipment description 55
• Gdu 37x display unit installation 55
• General specifications 56
• Installation information 56
• Antennas 58
• Block ground block ground 58
• Garmin shield garmin shield 58
• Gdu 37x gdu 37x 58
• Mounting requirements 58
• P3701 p3701 58
• Signal ground 35 signal ground 35 58
• Unit installation 58
• Gdu 37x panel cutout template 59
• Important ensure the page scaling setting is set to none when printing this page verify dimensions of printed template are accurate before cutting panel 59
• 01115 01 g3x installation manual gdu 37x installation rev u page 5 6 60
• Dimensions inchesmm 60
• Figure 5 5 gdu 37x outline drawing 60
• Outline and installation drawings 60
• Equipment description 62
• Gdu 45x display unit installation 62
• General specifications 63
• Installation information 63
• Block ground block ground 64
• Garmin shield garmin shield 64
• Gdu 45x gdu 45x 64
• P4501 p4501 64
• Signal ground 35 signal ground 35 64
• Unit installation 64
• Antennas 65
• Mounting requirements 65
• 01115 01 g3x installation manual gdu 45x installation rev u page 6 5 66
• Figure 6 3 gdu 45x outline drawing 66
• Notes dimensions inches mm 1 dimensions are shown for reference only 2 66
• Outline and installation drawings 66
• 01115 01 g3x installation manual gdu 45x installation rev u page 6 7 68
• Figure 6 5 gdu 45x panel cutout drawing not to scale 68
• Gdu 45x panel cutout drawing 69
• Equipment description 70
• Gdu 46x display unit installation 70
• General specifications 71
• Installation information 71
• Block ground block ground 72
• Garmin shield garmin shield 72
• Gdu 46x gdu 46x 72
• P4602 p4602 72
• Signa signa l ground ground 72
• Unit installation 72
• Antennas 73
• Mounting requirements 73
• 01115 01 g3x installation manual gdu 46x installation rev u page 7 5 74
• Figure 7 3 gdu 46x outline drawing 74
• Outline and installation drawings 74
• 01115 01 g3x installation manual gdu 46x installation rev u page 7 7 76
• Figure 7 5 gdu 46x panel cutout drawing not to scale 76
• This drawing not to scale this drawing not to scale 76
• 0 mm 185 0 mm 77
• 0 mm 262 0 mm 77
• Gdu 46x panel cutout drawing 77
• In 10 1 in 77
• Equipment description 78
• Gea 24 eis interface installation 78
• 01115 01 g3x installation manual gea 24 installation rev u page 8 2 79
• Additional equipment required 79
• Equipment available 79
• Required equipment 79
• Table 8 1 gea 24 part numbers 79
• Table 8 2 contents of gea 24 connector kit 011 02886 00 79
• Table 8 2 lists the content of the gea 24 connector kit which is required to install the unit use of the can termination kit is detailed in section 2 79
• General specifications 80
• Mounting requirements 80
• Unit installation 80
• 01115 01 g3x installation manual gea 24 installation rev u page 8 4 81
• Figure 8 2 gea 24 outline drawing 81
• Outline and installation drawings 81
• 01115 01 g3x installation manual gea 24 installation rev u page 8 6 83
• Figure 8 4 gea 24 assembly drawing with can terminator 83
• Equipment available 84
• Equipment description 84
• Gi 260 aoa indicator installation 84
• General specifications 85
• Unit calibration 85
• Unit installation 85
• Unit operation 85
• 01115 01 g3x installation manual gi 260 installation rev u page 9 3 86
• 03562 00 011 03562 00 socket socket mount mount 86
• Figure 9 3 gi 260 outline assembly drawing 86
• Mounting mounting details details 86
• Outline and installation drawings 86
• 01115 01 g3x installation manual gmc 305 installation rev u page 10 1 87
• Additional equipment required 87
• Equipment available 87
• Equipment description 87
• Figure 10 1 gmc 305 unit view 20 version shown 00 version has no yd button 87
• Gmc 305 afcs mode controller installation 87
• Required equipment 87
• Table 10 1 gmc 305 part numbers 87
• Table 10 2 contents of gmc 305 installation kit 010 12034 00 87
• Table 10 3 contents of connector kit 011 01824 00 87
• The following accessories are not provided with the gmc 305 unit the installation kit table 10 2 is required to install the unit the installation kit includes the connector kit table 10 3 and the mounting kit table 10 4 87
• The gmc 305 is a garmin automatic flight control system afcs mode controller that can be used in a g3x installation the gmc 305 provides a user interface for the autopilot function of the g3x system the gmc 305 mounts flush to the aircraft instrument panel using four threaded cap screws 87
• This section contains general information as well as installation information for the gmc 305 use this section to mount the gmc 305 unit 87
• General specifications 88
• Mounting and wiring requirements 88
• 01115 01 g3x installation manual gmc 305 installation rev u page 10 3 89
• Figure 10 2 gmc 305 outline drawing 89
• Outline and installation drawings 89
• 01115 01 g3x installation manual gmc 305 installation rev u page 10 4 90
• Figure 10 3 gmc 305 installation drawing 90
• 01115 01 g3x installation manual gmc 305 installation rev u page 10 5 91
• Figure 10 4 gmc 305 cutout drawing not to scale 91
• 01115 01 g3x installation manual gmc 305 installation rev u page 10 6 92
• Figure 10 5 gmc 305 panel cutout template 92
• 01115 01 g3x installation manual gmc 307 installation rev u page 11 1 93
• Additional equipment required 93
• Equipment available 93
• Equipment description 93
• Figure 11 1 gmc 307 unit view 00 version shown 20 version has no yd button 93
• Gmc 307 afcs mode controller installation 93
• Required equipment 93
• Table 11 1 gmc 307 part numbers 93
• Table 11 2 contents of gmc 307 installation kit 010 12034 00 93
• Table 11 3 contents of connector kit 011 01824 00 93
• The following accessories are not provided with the gmc 307 unit the installation kit table 11 2 is required to install the unit 93
• The gmc 307 is a garmin automatic flight control system afcs mode controller that can be used in a g3x installation the gmc 307 provides a user interface for the autopilot function of the g3x system the gmc 307 mounts flush to the aircraft instrument panel using two pawl latches 93
• This section contains general information as well as installation information for the gmc 307 use this section to mount the gmc 307 unit 93
• General specifications 94
• Mounting and wiring requirements 94
• 01115 01 g3x installation manual gmc 307 installation rev u page 11 3 95
• Figure 11 3 gmc 307 outline drawing 95
• Outline and installation drawings 95
• 01115 01 g3x installation manual gmc 307 installation rev u page 11 4 96
• Figure 11 4 gmc 307 installation drawing 96
• 01115 01 g3x installation manual gmc 307 installation rev u page 11 5 97
• Figure 11 5 gmc 307 cutout drawing not to scale 97
• 01115 01 g3x installation manual gmc 307 installation rev u page 11 6 98
• Cut out panel to inside line 98
• Figure 11 6 gmc 307 panel cutout template 98
• Equipment description 99
• General specifications 99
• Gmu 22 magnetometer installation 99
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 2 100
• Equipment available 100
• Fabrication of a wiring harness is required sound mechanical and electrical methods and practices are required for installation of the gmu 22 refer to section 2 for wiring considerations and to section 22 for pinouts 100
• If the requirements listed in table 12 4 cannot be met a magnetometer interference test must be performed to ensure proper operation of the g3x system refer to the ahrs magnetometer installation considerations document 190 01051 00 available from the garmin website www garmin co 100
• Table 12 1 gmu 22 part numbers 100
• Table 12 2 gmu 22 accessories 100
• Table 12 3 contents of gmu 22 connector kit 011 00871 10 100
• Table 12 4 specifies recommended distances from magnetic disturbances for gmu 22 location 100
• The following guidelines describe proper mechanical installation of the garmin gmu 22 magnetometer the guidelines include requirements for proper location selection in the aircraft requirements for supporting structure and mechanical alignment and restriction on nearby equipment 100
• The gmu 22 is an extremely sensitive three axis magnetic sensor it is more sensitive to nearby magnetic disturbances than a flux gate magnetometer for this reason when choosing a mounting location for the gmu 22 observe the following distances from objects or devices that can disturb the magnetic field 100
• Unit installation 100
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 4 102
• A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted gmu 22 102
• Adahrs gsu 25 73 to gmu 22 interconnect harness fabrication instructions 102
• Consideration for wing grounded lighting fixtures 102
• Figure 12 6 the gmu 22 magnetometer has an attached pigtail with male polarity the harness connector for the gmu 22 has female polarity 102
• Included in g3x w gsu 73 installation kit k10 00017 00 102
• Refer to section 12 for outline and installation drawings 102
• Table 12 5 lists parts needed for the gmu 22 interconnect harness some of the parts for installation are included in the gmu 22 connector installation kit other parts are provided by the installer reference numbers refer to item bubble numbers shown in figure 12 6 102
• Table 12 5 parts needed for gmu 22 installation 102
• Table 12 6 gmu 22 connector kit 011 00871 00 contents reference figure 12 6 102
• Table 12 6 lists material in the gmu 22 connector kit and the associated reference number as shown in 102
• The following installation practices are recommended if the required gmu 22 mounting bracket is located in the wing 102
• The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting 102
• These installation practices will prevent magnetically interfering currents from flowing in the wing skin that encloses the gmu 22 electrically isolating the light assembly should not be used as an alternative to item 1 above unless the isolated light assembly has been analyzed for adequate protection against direct attachment of lightning 102
• 00481 00 104
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 6 104
• Aircraft mounting holes 104
• Figure 12 3 gmu 22 mounting rack 104
• Gmu 22 mounting rack 104
• Outline and installation drawings 104
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 7 105
• Figure 12 4 gmu 22 top mounted installation 105
• From above preferred 105
• Gmu 22 installation 105
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 8 106
• Figure 12 5 gmu 22 bottom mounted installation 106
• From below 106
• Gmu 22 installation 106
• Not preferred 106
• 01115 01 g3x installation manual gmu 22 installation rev u page 12 9 107
• Figure 12 6 gmu 22 wiring details 107
• Equipment description 108
• Gps 20a waas gps position source installation 108
• 01115 01 g3x installation manual gps 20a installation rev u page 13 2 109
• Additional equipment required 109
• Equipment available 109
• For details 109
• Required equipment 109
• Status led 109
• Table 13 1 gps status led indications 109
• Table 13 2 gps 20a part numbers 109
• Table 13 3 contents of gps 20a connector kit 011 03914 00 109
• The connector kit in table 13 3 is required to install the unit it is not provided with the gps 20a unit 109
• The gps 20a has two leds on its outer case that indicate its current unit and gps status figure 13 1 109
• The gps status led is on the edge of the outer case to the left of the coax connector table 13 1 lists the gps status indications 109
• The unit status led is in the middle of the outer case between the coax and 9 pin connectors see section 109
• Antennas 110
• General specifications 110
• Mounting requirements 110
• Unit installation 110
• 01115 01 g3x installation manual gps 20a installation rev u page 13 4 111
• Figure 13 2 gps 20a outline drawing 111
• Outline and installation drawings 111
• 01115 01 g3x installation manual gps 20a installation rev u page 13 5 112
• Figure 13 3 gps 20a installation drawing no can terminator 112
• 01115 01 g3x installation manual gps 20a installation rev u page 13 6 113
• Figure 13 4 gps 20a installation drawing with can terminator 113
• Equipment description 114
• Gsa 28 autopilot servo installation 114
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 2 115
• Equipment available 115
• General specifications 115
• Power specifications 115
• Status led 115
• Table 14 1 gsa 28 part numbers 115
• Table 14 2 general specifications 115
• Table 14 3 gsa 28 power specifications 115
• Table 14 4 gsa 28 torque specifications 115
• The gsa 28 has an led on its outer case that indicates its current status see section 32 for details 115
• The gsa is compatible with 14 vdc trim systems only do not connect the gsa 28 to a 28 vdc trim system 115
• The trim outputs are capable of sourcing a maximum of 1 amp of current to drive a brushed dc motor the trim outputs drive a maximum output voltage of 12 vdc 115
• Torque specifications 115
• 011 02950 01 116
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 3 116
• Additional equipment required 116
• Cables the installer will fabricate and supply all system cables mounting hardware is included in the available mounting kits 116
• Required equipment 116
• Table 14 5 gsa 28 available equipment w weights 116
• Table 14 5 lists the kits available for the gsa 28 116
• Table 14 6 contents of connector kit 011 02950 00 116
• Table 14 7 contents of connector kit 9 116
• Unit installation 117
• Warning 117
• Warning 118
• Caution 119
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 8 121
• Garmin currently provides the mounting kits listed in table 14 8 for the gsa 28 servo 121
• Gsa 28 mounting kits 121
• Table 14 8 mounting kits 121
• The generic kits listed in table 14 8 011 02952 00 01 02 are not specific to any airframe the airframe specific kits gpn 011 02952 10 through 16 are for use with the specified experimental aircraft the contents of each kit as well as specific instructions for their use are detailed in the figures listed in table 14 8 121
• Warning 122
• Caution 124
• Caution 125
• Warning 125
• Outline and installation drawings 127
• Unit wiring 127
• Gsa28 standard 128
• Gsa28 standard accessories 129
• Gsa28 crank arm attachments 130
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 18 131
• Description 131
• Figure 14 8 gsa 28 with capstan kit and cable instructions 011 02952 02 131
• Gsa28 with capstan kit 011 02952 02 131
• Recommended bracket cutout dimensions 132
• Recommended gsa28 mounting hardware 133
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 21 134
• 02952 00 134
• Figure 14 8 gsa 28 generic push pull mounting kit no bracket 011 02952 00 134
• Mounting bracket not included gsa28 mounting kit generic push pull 134
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 22 135
• 02952 01 gsa28 mounting kit generic push pull w bracket 135
• Figure 14 8 gsa 28 generic push pull mounting kit w bracket 011 02952 01 135
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 23 136
• Dimensions inches 136
• Figure 14 9 gsa 28 rv 6 roll mounting kit 011 02952 10 page 1 of 3 136
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 25 138
• Figure 14 9 gsa 28 rv 6 roll mounting kit 011 02952 10 page 3 of 3 138
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 26 139
• Description 139
• Figure 14 10 gsa 28 rv 4 8 pitch mounting kit 011 02952 11 page 1 of 4 139
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 27 140
• All versions 140
• Bell crank modification rv 4 8 140
• Figure 14 10 gsa 28 rv 4 8 pitch mounting kit 011 02952 11 page 2 of 4 140
• Gsa28 stop bracket position rv 4 8 140
• Rv 4 and pre september 2006 rv 8 installation 141
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 30 143
• Figure 14 11 gsa 28 rv 7 8 10 roll mounting kit 011 02952 12 page 1 of 2 143
• Garmin part number 011 02952 12 143
• Rv 7 8 10 right wing roll mounting kit for gsa28 143
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 32 145
• Figure 14 12 gsa 28 rv 9 roll mounting kit 011 02952 13 page 1 of 2 145
• Garmin part number 011 02952 13 145
• Rv 9 right wing roll mounting kit 145
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 36 149
• Dimensions inches 149
• Figure 14 14 gsa 28 rv 10 pitch mounting kit 011 02952 15 page 1 of 2 149
• Installing servo 149
• 01115 01 g3x installation manual gsa 28 installation rev u page 14 38 151
• Description 151
• Figure 14 15 gsa 28 rv 10 yaw mounting kit 011 02952 16 page 1 of 3 151
• Bracket installation 152
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 1 154
• Equipment description 154
• Gsu 25 25b ahrs air data sensor unit installation 154
• References to the gsu 25 throughout this manual apply equally to the gsu 25b except where specifically noted 154
• Section 8 for engine airframe interface using the gea 24 up to three gsu 25 units may be installed to provide redundancy and cross checking of attitude heading and air data 154
• Table 15 1 gsu 25 functions 154
• The gsu 25 can be installed as part of the g3x system this section contains general information as well as installation information for the gsu 25 use this section to mount the gsu 25 unit 154
• The gsu 25 is an lru that provides ahrs and air data information in a single mechanical package the gsu 25 interfaces to a remote mounted gmu 22 for heading information and also computes oat and tas from inputs provided by the gtp 59 the gsu 25 does not provide engine airframe interface see 154
• The gsu 25 is intended for experimental aircraft and lsa light sport aircraft markets the garmin gsu 25 sensor unit is not a tso certified product and has received no faa approval or endorsement the gsu 25 is intended to be used as a part of the g3x system and it is not suitable for installation in type certificated aircraft 154
• The gsu 25 provides the functions in table 15 1 154
• There is no tso etso applicable to the gsu 25 154
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 3 156
• Additional equipment required wiring the installer will fabricate cables and supply all wire for system connector kits 011 03002 00 and 011 03002 01 156
• Air hoses and fittings to connect pitot air static air and aoa air to the gsu 25 the gsu 25 uses a female 1 8 27 anpt fitting for each of these ports use appropriate aircraft fittings to connect to pitot static and aoa system lines per section 15 156
• General specifications 156
• Required equipment 156
• See section 2 for power current specifications and section 2 for dimension weight specifications 156
• Table 15 2 gsu 25 available equipment 156
• Table 15 2 lists the kits available for the gsu 25 156
• Table 15 3 contents of 9 pin connector kit 011 03002 00 156
• Table 15 4 contents of 15 pin connector kit 011 03002 01 contains mounting hardware 156
• Unit installation 157
• Caution 160
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 8 161
• Figure 15 4 gsu 25 outline drawing 161
• Outline and installation drawings 161
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 9 162
• Figure 15 5 gsu 25 installation drawing 162
• Gsu25 with connector kits and hardware 162
• Includes optional can terminator 162
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 10 163
• Figure 15 6 gsu 25 orientation drawings page 1 of 3 163
• Tubes down orientations 163
• Tubes up orientations 163
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 11 164
• Figure 15 6 gsu 25 orientation drawings page 2 of 3 164
• Tubes aft orientations 164
• Tubes forward orientations 164
• 01115 01 g3x installation manual gsu 25 installation rev u page 15 12 165
• Figure 15 6 gsu 25 orientation drawings page 3 of 3 165
• Forward 165
• Starboard 165
• Tubes port connectors aft 165
• Tubes port connectors forward tubes port connectors down 165
• Tubes port connectors up 165
• Tubes portside orientations 165
• Tubes starboard connectors down 165
• Tubes starboard connectors forward tubes starboard connectors aft 165
• Tubes starboard connectors up 165
• Tubes starboard orientations 165
• Equipment description 166
• Gsu 73 sensor unit installation 166
• General specifications 167
• 01115 01 g3x installation manual gsu 73 installation rev u page 16 3 168
• Gsu 73 configuration module 168
• Included in g3x w gsu 73 installation kit k10 00017 00 168
• Required equipment 168
• Table 16 1 gsu 73 available equipment 168
• Table 16 1 lists the kits available for the gsu 73 168
• Table 16 2 contents of p731 connector kit 011 01818 00 168
• Table 16 3 contents of p732 connector kit 011 01818 01 168
• The gsu 73 configuration module stores a duplicate copy of the ahrs magnetometer calibration values which are recorded upon completion of post installation calibration procedures the gsu configuration module also provides a reference temperature measurement which is used for calculating thermocouple temperatures all thermocouple temperature readouts will be red x d section 32 if the gsu configuration module is not present 168
• Unit installation 169
• 01115 01 g3x installation manual gsu 73 installation rev u page 16 7 172
• Figure 16 4 gsu 73 outline drawing 172
• Outline and installation drawings 172
• Gsu 73 possible orientations 173
• Equipment description 174
• Gtp 59 temperature probe installation 174
• General specifications 175
• Unit installation 175
• Gtp 59 icing 177
• 01115 01 g3x installation manual gtp 59 installation rev u page 17 5 178
• Figure 17 2 gtp 59 o a t probe installation drawing 178
• Outline and installation drawings 178
• Equipment description 179
• Gtr 20 vhf communications radio installation 179
• 01115 01 g3x installation manual gtr 20 installation rev u page 18 2 180
• Additional equipment required 180
• Caution 180
• Equipment available 180
• Status led 180
• Table 18 2 gtr 20 part numbers 180
• Table 18 3 contents of gtr 20 connector kit 011 03241 00 180
• The connector kit in table 18 3 is required to install the unit it is not provided with the gtr 20 unit only 010 01076 00 180
• The gtr 20 has an led located in the hole to the right of the d sub connector j2001 that indicates its current status see section 32 for details 180
• The use of ground based cellular telephones while aircraft are airborne is prohibited by fcc rules due to potential interference with onboard systems the use of ground based cell phones while the aircraft is on the ground is subject to faa regulation 14 cfr 91 1 fcc regulation 47 cfr 22 25 prohibits airborne operation of ground based cellular telephones installed in or carried aboard aircraft ground based cellular telephones must not be operated while aircraft are off the ground when any aircraft leaves the ground all ground based cellular telephones on board that aircraft must be turned off ground based cell phones that are on even in a monitoring state can disrupt gps sbas performance 180
• Unit configurations 180
• 01115 01 g3x installation manual gtr 20 installation rev u page 18 3 181
• Com specifications 181
• General specifications 181
• See table 2 3 for power current specifications and table 2 4 for dimension weight specifications 181
• Table 18 4 transmitter specifications 181
• Table 18 5 receiver specifications 181
• The gtr 20 receiver meets the requirements of rtca do 186b section 2 for a class c receiver 181
• The gtr 20 transmitter meets the requirements of rtca do 186b section 2 for a class 4 transmitter 181
• Antenna considerations 182
• Caution 182
• Installation considerations 182
• Mounting considerations 184
• Mounting wiring and power checks 185
• Outline and installation drawings 187
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 1 190
• Ga 35 ga 36 and ga 37 antennas cannot be used with gdu 37x 4xx units 190
• Gps xm antenna installation 190
• In an installation with multiple gdu 37x 4xx units each gdu can be configured to use its own internal gps receiver or to receive gps data transmitted by another gdu a minimum of one gps antenna is required for installations using more than one gdu 37x 4xx unit as the gdu will share the gps information with all gdu units additional gps antennas may be used for redundancy but are not required see section 30 4 for gdu 37x systems or section 31 8 for gdu 4xx systems for further information 190
• Non garmin antennas 190
• Table 19 1 lists non garmin antennas currently supported by the gdu 37x 4xx for non garmin antennas follow the manufacturer s installation instructions it is the installer s responsibility to ensure that their choice of antenna meets faa standards according to the specific installation 190
• Table 19 1 supported non garmin antennas 190
• The gps 20a can only be used with ga 35 ga 36 or ga 37 antennas 190
• The gps antenna should provide a gain of 16 to 25 db the gdu 37x 4xx supplies power to the antenna at 4 v 5v with a maximum current of 50 ma 190
• This section contains general information as well as installation information for gps gps waas and xm antennas use this section to mount the antenna s 190
• When a gps 20a and connected gps waas antenna is installed it can be used as the sole gps for the system however it is recommended to install a gps antenna on at least one of the gdu 37x 4xx units for redundancy 190
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 2 191
• Garmin antennas 191
• Garmin recommends the antennas shown in table 19 2 however any equivalent gps gps waas or xm antenna that meets the specifications listed in table 19 3 and table 19 4 should work with the g3x 191
• If using a garmin ga 26c or ga 26xm refer to the accompanying installation instructions 190 00082 00 or 190 00522 03 for ga 35 ga 55 55a or ga 56 or ga 57x antennas refer to this section and the outline and installation drawings in section 19 191
• Table 19 2 supported garmin antennas 191
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 3 192
• It is the installer s responsibility to ensure that their choice of antenna meets faa standards according to the specific installation this installation manual discusses only the antennas listed in table 19 2 other antennas may be acceptable but their installation is not covered by this manual 192
• Table 19 3 gps or gps waas antenna minimum requirements 192
• Table 19 4 xm satellite radio antenna minimum requirements 192
• There are several critical factors to take into consideration before installing an antenna for a satellite communications system these factors are addressed in the following sections 192
• Antenna mounting considerations 193
• Teardrop footprint antenna installation ga 35 ga 55 and ga 56 198
• Caution 199
• Arinc 743 footprint antenna installation ga 36 ga 37 ga 55a ga 57x 205
• Caution 206
• Non structural mount installation 214
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 30 219
• Figure 19 31 example teardrop footprint antenna mounting under fabric skin 219
• Figure 19 31 shows minimum distance from metal tube structure requirements for internal non structural mounting of the antenna table 19 7 presents minimum distance requirements between the tube structure and the antenna for cases where the antenna sits underneath the fabric in a metal tube structure aircraft figure 19 31 illustrates the tube diameter d and minimum distance l references in the table 19 7 219
• Minimum distance from metal tube structure requirements 219
• Table 19 7 minimum distance required between tube structure and antenna 219
• Outline and installation drawings 220
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 32 221
• Figure 19 33 ga 36 installation drawing 221
• Mounting cutout 221
• Notes 1 dimensions inches mm 221
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 33 222
• Figure 19 34 ga 37 installation drawing 222
• Mounting cutout 222
• Notes 1 dimensions inches mm 222
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 34 223
• Figure 19 35 ga 55 installation drawing 223
• Forward 223
• Ga 55 stud mount 223
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 35 224
• Figure 19 36 ga 55a installation drawing 224
• Forward 224
• Ga 55a flange mount 224
• Mounting cutout 224
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 36 225
• Figure 19 37 ga 56 installation drawing 225
• Forward 225
• Ga 56 stud mount 225
• 01115 01 g3x installation manual gps xm antenna installation rev u page 19 37 226
• Figure 19 38 ga 57x installation drawing 226
• Forward 226
• Mounting cutout 226
• 01115 01 g3x installation manual engine airframe sensor installation rev u page 20 1 227
• Engine airframe sensor installation 227
• Engine airframe sensor options 227
• In addition to the engine sensors listed in table 20 1 the g3x system can also work with many other sensors not listed that output a compatible signal refer to the sensor specifications to determine compatibility 227
• Section 31 3 for gdu 45x 46x systems prior to use 227
• Table 20 1 compatible engine airframe input sensors 227
• Table 20 1 lists the types of engine airframe sensors that may be used for the various engine airframe inputs many of these sensors are included in the garmin g3x sensor kits section 20 each of the sensors must be correctly installed and configured section 30 8 for gdu 37x systems and 227
• 01115 01 g3x installation manual engine airframe sensor installation rev u page 20 2 228
• Table 20 1 compatible engine airframe input sensors 228
• 01115 01 g3x installation manual engine airframe sensor installation rev u page 20 3 229
• Table 20 1 compatible engine airframe input sensors 229
• 01115 01 g3x installation manual engine airframe sensor installation rev u page 20 4 230
• Table 20 1 compatible engine airframe input sensors 230
• 01115 01 g3x installation manual engine airframe sensor installation rev u page 20 6 232
• Garmin g3x sensor kits 232
• Table 20 2 contents of g3x sensor kit 4 cylinder lycoming continental k00 00512 00 232
• Table 20 2 table 20 3 and table 20 4 list garmin sensor kits available for g3x installations refer to sensor interface drawings in section 27 when installing sensor kits k00 00512 00 and k00 00513 00 refer to sensor interface drawings in section 28 when installing sensor kit k00 00514 00 232
• Table 20 3 contents of g3x sensor kit 6 cylinder lycoming continental k00 00513 00 232
• Table 20 4 contents of g3x sensor kit rotax 912 k00 00514 00 232
• Engine sensor installation 233
• Actual k factor measured at 16 gph 248
• Connector installation instructions 251
• Thermocouple installation into a backshell 251
• 01115 01 g3x installation manual connector installation instructions rev u page 21 3 253
• Jackscrew configuration module installation into a jackscrew backshell 253
• Table 21 2 gpn 011 00979 20 kit w eeprom and pins 253
• Table 21 2 table 21 3 list parts needed to install a jackscrew configuration module with pins or with sockets parts for these installations are included in the 011 00979 20 and 011 00979 22 kits which are included in the g3x w gsu 73 installation kit k10 00017 00 configuration modules are to be installed in the backshells of the p732 connector for the gsu 73 use 011 00979 20 in table 21 2 the p3701 connector for gdu 37x designated as pfd1 use 011 00979 22 in table 21 3 or the p4501 4601 connector for the gdu 45x 46x designated as pfd1 use 010 12553 00 in table 21 4 item numbers in table 21 2 table 21 3 and table 21 4 correspond to figure 21 3 and figure 21 4 253
• Table 21 3 gpn 011 00979 22 kit w eeprom and sockets 253
• Table 21 4 gpn 010 12253 00 config module w eeprom temp connext 253
• 01115 01 g3x installation manual connector installation instructions rev u page 21 6 256
• Jackscrew backshell installation instructions 256
• Shield block installation parts 256
• Table 1 29 parts listed in table 21 6 are to be provided by the installer 256
• Table 21 5 and table 21 6 list the parts needed to install a shield block the item numbers in these tables correspond to figure 21 5 parts listed in table 21 5 are supplied in the lru connector kits see 256
• Table 21 5 parts supplied for a shield block installation figure 21 5 256
• Table 21 6 parts not supplied for a shield block installation figure 21 5 256
• 01115 01 g3x installation manual connector installation instructions rev u page 21 14 264
• Figure 21 9 method b quick term for shield termination 264
• Reference the following mil spec for general teflon heat shrinkable tubing m23053 5 x y 264
• Secondary method 264
• Solder a flat braid item 4 figure 21 9 to the folded back shield on the prepared cable assembly item 2 figure 21 5 ensure a solid electrical connection through the use of acceptable soldering practices use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire slide a minimum of 0 5 inches of teflon heat shrinkable tubing item 3 figure 21 9 onto the prepared wire assembly and shrink using a heat gun the chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable as well as the flat braid item 4 figure 21 9 to be attached 264
• Table 21 8 shielded cable preparations quick term 264
• Teflon heat shrinkable tubing 264
• Warning 266
• Warning 267
• 01115 01 g3x installation manual lru pinouts rev u page 22 1 268
• Connector references jxxx x and pxxx x are used throughout this section and in section 23 through section 29 the letter j or p designates the connector whether on the lru or wiring harness j jack refers to the connector on the lru and p plug refers to the connector on the wiring harness j or p designate the connector only regardless of contact type pin or socket however gdu 46x connectors on the lru are designated as p460x 268
• Figure 22 1 j291 on gad 29 as viewed looking at connector on unit 268
• J291 connector 268
• Lru pinouts 268
• Use the information in this section along with other applicable sections appendices in this document to construct the wiring required for the g3x installation 268
• 01115 01 g3x installation manual lru pinouts rev u page 22 2 269
• Figure 22 2 j292 on gad 29 as viewed looking at connector on unit 269
• J292 connector 269
• 01115 01 g3x installation manual lru pinouts rev u page 22 3 270
• Arinc 429 rx tx 270
• The arinc 429 outputs conform to arinc 429 electrical specifications when loaded with up to 5 standard arinc 429 receivers each arinc 429 transmitter pin is physically connected to two dsub pins when running one transmitter to two receivers use two separate pins to avoid splicing wires running one transmitter to more than two receivers will require splicing wires 270
• This section covers the power input requirements aircraft power 1 and aircraft power 2 are diode ored to provide power redundancy 270
• 01115 01 g3x installation manual lru pinouts rev u page 22 4 271
• Can bus 271
• The can bus conforms to the bosch standard for controller area network 2 b and complies with iso 11898 pins 9 and 21 are used to terminate the can bus to terminate the can bus at the gad 29 short the pins 9 and 21 together refer to section 2 for details on configuring and terminating the can bus the can bus on j241 shall be used for communications between g3x lrus 271
• 01115 01 g3x installation manual lru pinouts rev u page 22 5 272
• Figure 22 3 j3701 on gdu 37x as viewed looking at connector on unit 272
• Gdu 37x 272
• J3701 connector 272
• 01115 01 g3x installation manual lru pinouts rev u page 22 6 273
• The gdu 37x rear connector j3701 is electrically isolated for installations using shielded cables a ground pin must be tied to the connector shell 273
• 01115 01 g3x installation manual lru pinouts rev u page 22 7 274
• Aircraft power 274
• In a single display system configure the display as pfd1 in a two display system configure one display as pfd1 and the other display as mfd in a three display system one display is pfd1 one is the mfd and the third is pfd2 configure the gdu 37x units per the following tables a gdu 37x can be manually placed in reversionary mode by wiring pin 25 to a two pole switch that toggles between open and ground when the switch is open the display will operate normally when the switch is grounded the display changes to reversionary mode showing the engine bar at the top of the display and a split screen pfd and mfd below other displays in the system will not be affected by manually placing a display into reversionary mode do not connect a switch to ground for pins 9 or 10 doing so can cause communication errors grounding pin 42 will place the gdu 37x in demo mode which is for in store demonstration use only never ground pin 42 in an aircraft installation 274
• Mode selections cdu system id program pins 274
• The gdu 37x can operate using power from one or both inputs aircraft power 1 and aircraft power 2 the pins are internally connected using diodes to prevent current from flowing between the two power inputs aircraft power 2 is for connecting to an alternate power source such as on aircraft with two electrical buses 274
• 01115 01 g3x installation manual lru pinouts rev u page 22 8 275
• Can bus 275
• Channels of rs 232 i o data 275
• Configuration module 275
• Connect the configuration module to the pfd1 unit do not connect a config module to pfd2 or the mfd 275
• Serial data 275
• This data bus conforms to the bosch standard for controller area network 2 b this bus complies with iso 11898 can bus termination should be connected to can bus lo for the gdu that is located at the end of the bus farthest from the gsu 73 see section 2 for details 275
• 01115 01 g3x installation manual lru pinouts rev u page 22 9 276
• Lighting 276
• Mono audio 276
• Stereo audio 276
• The gdu 37x display brightness can be configured to track 28 vdc or 14 vdc lighting busses using these inputs 276
• The left and right common pins pins 2 and 20 may be tied together or only one may be used it is not necessary to use both common pins 276
• The mono audio output provides audio alerts for connection to an unswitched input on an intercom or audio panel 276
• The stereo audio output provides siriusxm audio for connection to an entertainment input on an intercom or audio panel audio alerts may optionally be reproduced on the stereo audio output in addition to the mono audio output see section 30 2 for instructions regarding the sound config page 276
• 01115 01 g3x installation manual lru pinouts rev u page 22 10 277
• Figure 22 4 p4501 4601 on gdu 45x 46x as viewed looking at connector on unit 277
• Figure 22 5 gdu 45x 46x to gsu 25 backup data path connections 277
• Gdu 45x 46x 277
• It is recommended to connect the serial port from the gsu 25 use the gsu 25 designated as 1 in a multiple gsu 25 installation to the p4x01 connector regardless of mounting method used for the gsu 25 per figure 22 5 277
• P4501 4601 connector 277
• The p4501 4601 connector can be used for connections to the gsu 25 when mounting the gsu 25 to the back of the gdu 45x 46x figure 7 3 this mounting method may not be recommended for all installations contact garmin for details before using this method 277
• 01115 01 g3x installation manual lru pinouts rev u page 22 11 278
• Figure 22 6 view of p4502 4602 connector from back of unit 278
• P4502 4602 connector 278
• 01115 01 g3x installation manual lru pinouts rev u page 22 12 279
• 01115 01 g3x installation manual lru pinouts rev u page 22 13 280
• Do not use p4503 4603 this connector is reserved for future development 280
• Figure 22 7 view of p4503 4603 connector from back of unit 280
• P4503 4603 connector 280
• 01115 01 g3x installation manual lru pinouts rev u page 22 16 283
• Configuration module 283
• Configure the gdu 45x 46x units per the following tables a gdu 45x 46x can be manually placed in reversionary mode by wiring pin 25 to a two pole switch that toggles between open and ground when the switch is open the display will operate normally when the switch is grounded the display changes to reversionary mode showing the engine bar at the top of the display and a split screen pfd and mfd below other displays in the system will not be affected by manually placing a display into reversionary mode do not connect a switch to ground for pins 9 or 10 doing so can cause communication errors grounding pin 42 will place the gdu 45x 46x in demo mode which is for in store demonstration use only never ground pin 42 in an aircraft installation 283
• Connect the configuration module to the pfd1 unit do not connect a config module to pfd2 mfd1 or mfd2 283
• 01115 01 g3x installation manual lru pinouts rev u page 22 17 284
• Can bus 284
• Channels of rs 232 i o data 284
• Lighting 284
• Serial data 284
• The gdu 45x 46x display and keys can be configured to track 28 vdc or 14 vdc lighting busses using these inputs these inputs are reference voltage inputs not power inputs with a high impedance of 100 kω for pin 43 and 200 kω for pin 26 this backlight level reference signal may be supplied with something as simple as a 10k potentiometer connected to power and ground drawing 1 ma 14 vdc the center tap on this potentiometer is connected to one of the pins 43 or 26 in the following table for providing this reference signal to more than one device a commercially available regulated backlight voltage reference is recommended 284
• This data bus conforms to the bosch standard for controller area network 2 b this bus complies with iso 11898 can bus termination should be connected to can bus lo for the gdu that is located at the end of the bus farthest from the gsu 73 see section 2 for details 284
• 0 mono audio 285
• 01115 01 g3x installation manual lru pinouts rev u page 22 18 285
• 1 stereo audio 285
• The mono audio output provides audio alerts for connection to an unswitched input on an intercom or audio panel 285
• The stereo audio output provides siriusxm audio for connection to an entertainment input on an intercom or audio panel audio alerts may optionally be reproduced on the stereo audio output in addition to the mono audio output see section 31 5 for instructions regarding the sound config page 285
• 01115 01 g3x installation manual lru pinouts rev u page 22 19 286
• Figure 22 9 j241 on gea 24 as viewed looking at connector on unit 286
• J241 connector 286
• 01115 01 g3x installation manual lru pinouts rev u page 22 20 287
• Figure 22 10 j242 on gea 24 as viewed looking at connector on unit 287
• J242 connector 287
• 01115 01 g3x installation manual lru pinouts rev u page 22 21 288
• Figure 22 11 j243 on gea 24 as viewed looking at connector on unit 288
• J243 connector 288
• 01115 01 g3x installation manual lru pinouts rev u page 22 22 289
• Figure 22 12 j244 on gea 24 as viewed looking at connector on unit 289
• Indicates active low 289
• J244 connector 289
• 01115 01 g3x installation manual lru pinouts rev u page 22 23 290
• 01115 01 g3x installation manual lru pinouts rev u page 22 24 291
• Aircraft power 291
• Both data buses conform to the bosch standard for controller area network 2 b the busses comply with iso 11898 refer to section 2 for details on configuring and terminating the can bus the can bus on j241 shall be used for communications between g3x lrus the can 2 bus on j244 shall be used to communicate with fadec engine controllers and shall not be connected to other g3x lrus the can2 bus is not terminated at the unit refer to the wiring diagrams for how to terminate the second can bus if used 291
• Can bus 291
• The gea 24 has two pins for aircraft power inputs of 14 28 vdc and can operate using power from one or both inputs aircraft power 1 and aircraft power 2 the pins are internally connected using diodes to prevent current from flowing between the two power inputs aircraft power 2 is for connecting to an alternate power source such as on aircraft with two electrical buses the two aircraft power inputs may optionally be used to monitor aircraft bus voltage see section 28 7 for configuration 291
• 01115 01 g3x installation manual lru pinouts rev u page 22 25 292
• Digital inputs 292
• The inputs are capable of sensing frequencies of the range 1 hz to 100 khz with a configurable debounce filter sensed signals can be either an ac voltage with a peak to peak value of greater than 1 v or an open collector type input these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and section 31 3 for gdu 45x 46x systems 292
• 01115 01 g3x installation manual lru pinouts rev u page 22 26 293
• A low 0 vdc vin 3 vdc or rin 375 ω active 293
• B high 8 vdc vin 36 vdc active 293
• Discrete inputs 293
• Kω inactive 293
• Kω or rin 375 ω inactive 293
• Section 31 3 for gdu 45x 46x systems 293
• The gea 24 has 4 configurable discrete inputs that can be used as either active high or active low these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to 293
• When configured as active high the inputs conform to the following specification 293
• When configured as active low the inputs conform to the following specification 293
• 0 fuel quantity 294
• 01115 01 g3x installation manual lru pinouts rev u page 22 27 294
• Active vout 0 vdc with 20 ma sink current 294
• Discrete out 1 is master warning goes low when a red warning cas alert is active 294
• Discrete out 2 is master caution goes low when a yellow caution cas alert is active 294
• Discrete outputs 294
• Fuel quantity inputs have an internal pull up resistor that can be enabled for resistive fuel sensor inputs the inputs can also support capacitive sensors as either voltage inputs or digital inputs these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to section 31 3 for gdu 45x 46x systems 294
• Inactive floating can be pulled up to externally sourced vout in the range 0 vout 33 vdc 294
• Leakage current in the inactive state is typically 10 ua to ground 294
• Sink current must be externally limited to 20 ma max 294
• The gea 24 has 2 annunciator outputs these outputs do not require any configuration and can be optionally wired to an external annunciator discrete out 1 acts as a master warning annunciator and is active any time a warning cas message red alert is displayed on the pfd discrete out 2 acts as a master caution annunciator and is active any time a caution cas message yellow alert is displayed on the pfd reference section 26 for wiring guidance 294
• The two states of these outputs are as follows 294
• 01115 01 g3x installation manual lru pinouts rev u page 22 28 295
• 1 gp general purpose inputs 295
• 3 for gdu 45x 46x systems and are capable of reading any voltage up to 40 vdc the gea 24 has 7 position inputs labeled pos 1 through 7 and 7 general purpose inputs gp 1 through 7 to limit the length of pin names gpx is not used on all pins each of these are paired together 295
• Potentiometer based sensors can be used by connecting the potentiometer across a 5 v supply and ground and reading back the center tap voltage on gp1 g7 pos1 7 some general purpose inputs have multiple functions 295
• These inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to section 295
• 01115 01 g3x installation manual lru pinouts rev u page 22 29 296
• 2 pressure inputs 296
• 3 voltage inputs 296
• 4 shunt 296
• All pressure inputs are capable of accepting input voltages of up to 40 vdc the oil pressure input can also accommodate resistive and constant current source sensors these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to section 31 3 for gdu 45x 46x systems 296
• The two bus voltage inputs are capable of accepting voltages of up to 40 vdc these inputs are configured by the gdu section 30 8 for gdu 37x systems and to section 31 3 for gdu 45x 46x systems 296
• 01115 01 g3x installation manual lru pinouts rev u page 22 30 297
• 5 system id 297
• 6 temperature inputs 297
• If installing an ungrounded thermocouple to an analog in input a dc reference must be added to the lo input this can be accomplished by adding a resistance of 1 mω or less between ground and the analog in lo input that the ungrounded thermocouple is installed on 297
• Pins 1 2 3 and 4 must be left open floating for a single gea 24 installation when using a gea 24 and gsu 73 in the same system pins 1 and 2 should be connected together in order to configure the gea 24 as the eis 2 lru 297
• Some thermocouple inputs are multi purpose capable and have several configuration options cht5 cht6 gp6 gp7 misc temp 1 misc temp 2 and oil temp can be used for resistive based temperature sensors these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to section 31 3 for gdu 45x 46x systems 297
• 01115 01 g3x installation manual lru pinouts rev u page 22 31 298
• The pinout of j242 is compatible with 25 pin thermocouple wiring harnesses used in some third party eis systems 298
• 01115 01 g3x installation manual lru pinouts rev u page 22 32 299
• 7 transducer output power 299
• The gea 24 supplies output power for engine airframe sensors that may require supply voltage excitation the gea 24 outputs voltage levels of 5 and 12 vdc each output can supply a maximum of 50 ma if more than 50 ma is needed for a sensor 3 outputs of the same voltage may be spliced together to allow an output current of up to 100 ma transducers that require more current such as princeton capacitive fuel quantity converters must be supplied from aircraft power instead of gea 24 transducer power output pins 299
• The transducer output pins are listed in the following table additionally the pins are also listed in the tables for their respective default functionality 299
• 01115 01 g3x installation manual lru pinouts rev u page 22 33 300
• Aircraft power 1 and power ground are connected to a 14 28 vdc supply 300
• Can bus 300
• Figure 22 13 gi 260 pigtail harness 300
• Pigtail connections 300
• The can bus conforms to the bosch standard for controller area network 2 b and complies with iso 11898 refer to section 2 for details on wiring the can bus using the can bus is the preferred data interconnect for the gi 260 in a g3x system 300
• 01115 01 g3x installation manual lru pinouts rev u page 22 34 301
• Lighting 301
• Mono audio 301
• Mono out provides audio alerts for connection to an unswitched input on an intercom or audio panel audio shield is grounded at the gi 260 if the audio lines in the gi 260 pigtail harness are not long enough to connect directly to the audio panel audio shield may be used to splice the shields together on the audio lines for other installations the shields should be spliced together but the audio panel shield should be left floating figure 23 1 refer to the audio panel installation manual for further guidance on connecting and terminating the shield 301
• Rs 232 channel 301
• The gi 260 display brightness can track either a 28 vdc or 14 vdc lighting bus using these inputs if left unconnected unit will use a photocell to adjust lighting 301
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load this channel is not used in typical g3x installations 301
• 01115 01 g3x installation manual lru pinouts rev u page 22 35 302
• Figure 22 14 j3051 on gmc 305 as viewed looking at connector on unit 302
• Gmc 305 302
• J3051 connector 302
• This section covers the power input requirements the gmc 305 is compatible with 14v and 28v systems aircraft power 1 and aircraft power 2 are diode ored to provide power redundancy 302
• 01115 01 g3x installation manual lru pinouts rev u page 22 36 303
• Figure 23 1 303
• Lighting 303
• Rs 232 channel 1 should be connected to an available rs 232 port on a gdu display rs 232 channel 2 should be connected to the gsa 28 roll servo rs 232 port in a garmin autopilot system see 303
• Serial data 303
• The gmc 305 can track a 14 vdc lighting bus using these inputs the gmc 305 can also automatically adjust for ambient lighting conditions based on photocell input if no voltage is supplied to the lighting bus input the gmc 305 will automatically adjust for ambient lighting conditions using its built in photocell 303
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load 303
• 01115 01 g3x installation manual lru pinouts rev u page 22 37 304
• Figure 22 15 j3071 on gmc 307 as viewed looking at connector on unit 304
• Gmc 307 304
• J3071 connector 304
• This section covers the power input requirements the gmc 307 is compatible with 14v and 28v systems aircraft power 1 and aircraft power 2 are diode ored to provide power redundancy 304
• 01115 01 g3x installation manual lru pinouts rev u page 22 38 305
• Figure 23 1 305
• Lighting 305
• Rs 232 channel 1 should be connected to an available rs 232 port on a gdu display rs 232 channel 2 should be connected to the gsa 28 roll servo rs 232 port in a garmin autopilot system see 305
• Serial data 305
• The gmc 307 can track a 14 vdc lighting bus using these inputs the gmc 307 can also automatically adjust for ambient lighting conditions based on photocell input if no voltage is supplied to the lighting bus input the gmc 307 will automatically adjust for ambient lighting conditions using its built in photocell 305
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load 305
• 01115 01 g3x installation manual lru pinouts rev u page 22 39 306
• Figure 22 16 j441 on gmu 22 as viewed looking at connector on unit 306
• J441 connector 306
• Power function 306
• Power input pins accept supply voltage from adahrs gsu 25 73 306
• Rs 485 the rs 485 pins provide data to the adahrs gsu 25 73 306
• Serial data 306
• The rs 232 input pin accepts data from the adahrs gsu 25 73 306
• 01115 01 g3x installation manual lru pinouts rev u page 22 40 307
• Can bus 307
• Figure 22 17 j201 on gps 20a as viewed looking at connector on unit 307
• Gps 20a 307
• J201 connector 307
• Power function 307
• The can bus conforms to the bosch standard for controller area network 2 b and complies with iso 11898 refer to section 2 for details on wiring the can bus using the can bus is the preferred data interconnect for the gps 20a in a g3x system 307
• This section covers the power input requirements the gps 20a is compatible with 14v and 28v systems aircraft power 1 and aircraft power 2 are diode ored to provide power redundancy 307
• 01115 01 g3x installation manual lru pinouts rev u page 22 41 308
• Rs 232 channel 308
• Rs 232 tx 1 is always configured to provide garmin ads b data to be used by a mode s extended squitter es transponder such as the gtx 23es or gtx 330es 308
• Rs 232 tx 2 is always configured to provide nmea out at 9600 baud 1 start bit 1 stop bit 8 data bits and no parity the supported nmea sentences are gprmc gpgga gpgsa gpgsv gpvtg and pgrmt 308
• See figure 23 2 for wiring information 308
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load 308
• 01115 01 g3x installation manual lru pinouts rev u page 22 42 309
• Figure 22 18 j281 on gsa 28 as viewed looking at connector on unit 309
• J281 connector 309
• Power function 309
• Supply voltage 14 28vdc inputs 309
• 01115 01 g3x installation manual lru pinouts rev u page 22 43 310
• Ap disconnect 310
• Ap disconnect should be connected to an active low push button switch that disengages the autopilot and optionally engages it if configured press and hold the switch to allow for control wheel steering by disengaging the clutch and servo motor the ap disconnect input must be connected to both the pitch and the roll servos and can optionally be connected to the yaw damper servo 310
• Can bus 310
• Id strap 310
• Pins 7 and 8 tx and rx connect to the gmc 30x rs232 channel 2 on the roll servo only 310
• Pitch servo jumper wire installed from pin 5 to pin 8 310
• Roll servo no jumper wire installed 310
• The id strap inputs are used to configure the gsa 28 as a roll pitch or yaw servo by installing a jumper wire or not installing a jumper wire per the following 310
• This data bus conforms to the bosch standard for controller area network 2 b this bus complies with iso 11898 see section 2 for can bus details 310
• Yaw servo jumper wire installed from pin 6 to pin 7 310
• 01115 01 g3x installation manual lru pinouts rev u page 22 44 311
• A removal adapter gpn 011 03158 00 is provided with each gsa 28 connector kit that can be used when a gsa 28 is removed the adapter keeps that node on the can bus in the same state as when the servo was connected either terminated or un terminated the adapter also allows trim signals to pass through when the servo is removed 311
• The trim inputs should connect to the panel trim switch the trim outputs should connect to the trim servo maximum output current of the trim outputs is 1 amp if the gsa 28 is not powered a fail safe feature causes the trim inputs to connect directly to the trim outputs if the servo is powered and configured for speed scheduling the servo drives the trim outputs based on the trim inputs and aircraft speed if the servo is powered with the autopilot and auto trim feature is enabled the servo has full control of the trim outputs 311
• 01115 01 g3x installation manual lru pinouts rev u page 22 45 312
• Figure 22 19 j251 on gsu 25 as viewed looking at connector on unit 312
• Gsu 25 25b 312
• 01115 01 g3x installation manual lru pinouts rev u page 22 46 313
• Figure 22 20 j252 on gsu 25 as viewed looking at connector on unit 313
• 01115 01 g3x installation manual lru pinouts rev u page 22 47 314
• Aircraft power 314
• Channels of rs 232 rx and 3 channels of rs 232 tx data 314
• Rs 232 1 can optionally be connected to a gdu display to provide a redundant path for attitude data also used to configure a gsu 25 as adahrs 3 314
• Rs 232 2 transmits data to the gmu 22 314
• Rs 232 3 connects to a gtx transponder to provide pressure altitude data and remote transponder control transponder should only be connected to adahrs 1 not 2 or 3 314
• Serial data 314
• The gsu 25 can operate using power from one or both inputs aircraft power 1 and aircraft power 2 the pins are internally connected using diodes to prevent current from flowing between the two power inputs aircraft power 2 is for connecting to an alternate power source such as on aircraft with two electrical buses 314
• The gsu 25 outputs supply voltage to the gmu 22 via pins 6 7 314
• 01115 01 g3x installation manual lru pinouts rev u page 22 48 315
• Can bus this data bus conforms to the bosch standard for controller area network 2 b this bus complies with iso 11898 see section 2 for details 315
• Refer to figure 23 1 for connection drawing 315
• Rs 485 input the gsu 25 contains one channel of rs 485 serial data communications for receiving data from the gmu 22 315
• Temperature inputs temperature input is used for outside air temperature oat computations the temperature input is a three wire temperature probe interface oat power out and oat high are connected internally at the oat probe a gtp 59 or other supported temperature probe is required for the adahrs gsu 25 73 installation that is configured as adahrs 1 the gtp 59 is a resistive temperature device rtd refer to figure 17 2 for the temperature probe interconnect 315
• Unit id 315
• 01115 01 g3x installation manual lru pinouts rev u page 22 49 316
• Connector description 316
• Figure 22 21 rear view of connector end plate 316
• Figure 22 22 j731 on gsu 73 as viewed looking at connector on unit 316
• J731 connector 316
• J731 pins are configured as shown in preceding figure j731 pin assignments are given in the following table additional tables group pin connections by function 316
• The gsu 73 has one 62 pin connector j731 and one 78 pin connector j732 located on the connector end of the unit as shown below j731 and j732 are clearly marked on the connector end plate 316
• 01115 01 g3x installation manual lru pinouts rev u page 22 50 317
• 01115 01 g3x installation manual lru pinouts rev u page 22 51 318
• Figure 22 23 j732 on gsu 73 as viewed looking at connector on unit 318
• J732 connector 318
• 01115 01 g3x installation manual lru pinouts rev u page 22 52 319
• 01115 01 g3x installation manual lru pinouts rev u page 22 53 320
• Aircraft power 320
• Power i o 320
• The gsu 73 has four inputs for aircraft power bus inputs of 14 28 vdc and can operate using power from one or both inputs aircraft power 1 and aircraft power 2 the pins are internally connected using diodes to prevent current from flowing between the two power inputs aircraft power 2 is for connecting to an alternate power source such as on aircraft with two electrical buses the two aircraft power inputs may optionally be used to monitor aircraft bus voltage see section for configuration 320
• 01115 01 g3x installation manual lru pinouts rev u page 22 54 321
• Magnetometer power 321
• The gsu 73 outputs supply voltage to the gmu 22 via pins 38 39 321
• The gsu 73 supplies output power for engine airframe sensors that may require supply voltage excitation the gsu 73 outputs voltage levels of 5 10 and 12 vdc these outputs may be spliced to allow connection to multiple sensors if needed max current specs are listed in the following table 321
• Transducer output power 321
• Transducers that require more current such as princeton capacitive fuel quantity converters must be supplied from aircraft power instead of gsu 73 transducer power output pins 321
• 01115 01 g3x installation manual lru pinouts rev u page 22 55 322
• Arinc 429 input output 322
• Rs 232 input output 322
• Serial data electrical characteristics 322
• The arinc 429 outputs conform to arinc 429 electrical specifications when loaded with up to 5 standard arinc 429 receivers 322
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load rs 232 out 2 is not currently active rs 232 in out 3 is used for connection to a transponder figure 24 2 figure 24 2 and is not configurable always on by default 322
• 01115 01 g3x installation manual lru pinouts rev u page 22 56 323
• Can bus 323
• Configuration module interface 323
• Connect the gsu 73 to the configuration module using the 4 pins listed below 323
• Rs 485 input 323
• Section 2 for details 323
• The gsu 73 contains one channel of rs 485 serial data communications for receiving data from the gmu 22 323
• This data bus conforms to the bosch standard for controller area network 2 b this bus complies with iso 11898 one gdu should be terminated can bus termination connected to can bus lo and the gsu should be terminated if gsu is located at the end of the bus see section 23 see 323
• 01115 01 g3x installation manual lru pinouts rev u page 22 57 324
• Active low discrete inputs 324
• Active vout 0 vdc with 20 ma sink current sink current must be externally limited to 20 ma max 324
• Discrete i o 324
• Discrete out 1 is master warning goes low when a red warning cas alert is active discrete out 2 is master caution goes low when a yellow caution cas alert is active 324
• Discrete outputs 324
• Kω inactive 324
• Low 0 vdc vin 3 vdc or rin 375 ω active 324
• The gsu 73 has 2 annunciator outputs these outputs do not require any configuration and can be optionally wired to an external annunciator discrete out 1 acts as a master warning annunciator and is active any time a warning cas message red alert is displayed on the pfd discrete out 2 acts as a master caution annunciator and is active any time a caution cas message yellow alert is displayed on the pfd reference section 26 for wiring guidance 324
• The gsu 73 has 4 configurable discrete inputs conforming to 324
• The two states of these outputs are as follows inactive floating can be pulled up to externally sourced vout in the range 0 vout 33 vdc leakage current in the inactive state is typically 10 ua to ground 324
• 01115 01 g3x installation manual lru pinouts rev u page 22 58 325
• Analog input configuration 325
• If installing an ungrounded thermocouple to an analog in input a dc reference must be added to the lo input this can be accomplished by adding a resistance of 1 mω or less between ground and the analog in lo input that the ungrounded thermocouple is installed on 325
• Some analog inputs are multi purpose capable and have several configuration options these inputs are configured by the gdu refer to section 30 8 for gdu 37x systems and to section 31 3 for gdu 45x 46x systems and are capable of reading any voltage up to 40 vdc 325
• 01115 01 g3x installation manual lru pinouts rev u page 22 59 326
• 01115 01 g3x installation manual lru pinouts rev u page 22 60 327
• Each frequency counter channel will be configured for a high or low speed input based on the signal being measured 327
• Frequency counter inputs 327
• Rpm rotax maximum frequency 6 khz rpm other maximum frequency 4 khz fuel flow floscan 201 b6 maximum frequency 500 hz fuel flow ei ft60 maximum frequency 1 khz fuel quantity capacitive maximum frequency 50 khz 327
• Temperature input is used for outside air temperature oat computations the temperature input is a three wire temperature probe interface oat power out and oat high are connected internally at the oat probe a gtp 59 or other supported temperature probe is required for the gsu 73 installation the gtp 59 is a resistive temperature device rtd refer to figure 17 2 for the temperature probe interconnect 327
• Temperature inputs 327
• The following table lists the minimum frequency maximum frequency and duty cycles for each of these inputs 327
• 01115 01 g3x installation manual lru pinouts rev u page 22 63 330
• Figure 22 26 j2001 looking at rear of unit 330
• J2001 connector 330
• Table 22 1 j2001 connector 330
• 01115 01 g3x installation manual lru pinouts rev u page 22 64 331
• Can bus 331
• Pins 1 20 supply power to the gtr 20 refer to drawings in section 25 for power and ground wire gauges 331
• Refer to drawings in section 25 for id connections 331
• Table 22 1 j2001 connector 331
• The can bus conforms to the bosch standard for controller area network 2 b and complies with iso 11898 pins 25 and 26 are used to terminate the can bus to terminate the can bus at the gtr 20 short the pins 25 and 26 together refer to section 2 for details on configuring and terminating the can bus the can bus on j2001 shall be used for communications between g3x lrus 331
• Unit id 331
• 01115 01 g3x installation manual lru pinouts rev u page 22 65 332
• Aux mono audio 332
• Auxiliary audio mono audio inputs have a nominal input impedance of 600 ω max rated input level is 5 vrms 332
• Headset audio 332
• Headset audio outputs 332
• Mic audio 332
• Pilot mic in and copilot mic in are set in the factory so that 150 mvrms modulates the transmitter to 90 nominally at 1000 hz the microphone gain adjustment is made through configuration mode 332
• Pilot mic in and copilot mic in are standard carbon or dynamic mic inputs with integrated preamps providing minimum 20 mvrms into a 150 ω ac load 332
• 01115 01 g3x installation manual lru pinouts rev u page 22 66 333
• 0pilot copilot ptt inputs 333
• Active low discrete inputs are considered active if either the voltage to ground is 3 vdc or the resistance to ground is 375 333
• Music inputs 333
• Receiver audio 333
• Receiver audio out is a 40 mw audio output that is intended to drive a recording device or an audio panel 333
• Receiver audio out is the summation of the receiver audio com sidetone audio intercom audio and aux audio 333
• Receiver audio out supplies 40 mw 4 vrms into a 600 load and is generally connected to the audio panel if used this output can also drive a recording device when driving a recording device the output level will typically need to be reduced the output level is controlled through configuration mode 333
• The music inputs are noise rejecting and have a nominal input impedance of 600 ω the max rated input level is 1 vrms the music lo must be connected to the music source along with music right and music left if music lo is not connected music volume will be low or inaudible noisy and distorted 333
• When pulled low these inputs allow the audio that is present on the pilot copilot mic in to be transmitted over the radio 333
• 01115 01 g3x installation manual lru pinouts rev u page 22 68 335
• Connector description 335
• Figure 22 27 j2301 on gtx 23 as viewed looking at connector on unit 335
• J2301 connector 335
• Pin pin name i o 335
• The gtx 23 has one 62 pin connector j2301 as shown below all electrical connections are made through j2301 except for the antenna and shield ground 335
• 01115 01 g3x installation manual lru pinouts rev u page 22 69 336
• Pin pin name i o 336
• 01115 01 g3x installation manual lru pinouts rev u page 22 70 337
• Aircraft power 337
• Discrete functions 337
• Discrete inputs 337
• Discrete outputs 337
• External ident select remote ident is a momentary input when grounded it activates the ident pulse for 18 seconds in mode a replies 337
• External standby select remote standby is not a momentary input when external standby select is grounded the gtx 23 operates in standby mode in this mode the transponder will not squitter or reply to interrogations 337
• External suppression should be connected if a dme or tcas is installed in the aircraft avionics system the gtx 23 suppression i o pulses may not be compatible with all models of dme or tcas known incompatible dme units include the bendix king kn 62 kn 64 and kns 80 these models have an output only suppression port and can be damaged by the gtx 23 mutual suppression output in this case do not connect the gtx 23 s suppression pin to the incompatible unit s suppression pin however do connect the gtx 23 s suppression pin to any other compatible unit s suppression pin 337
• Power input requirements are listed in the following tables the power input pins accept 14 28 vdc refer to figure c 1 and c 2 for power interconnections aircraft power 1 and aircraft power 2 are diode ored to provide power redundancy 337
• Sink current is internally limited to 200 ua max for a grounded input 337
• Tis connect select is a momentary input when grounded it toggles whether tis a is in standby or operating 337
• 01115 01 g3x installation manual lru pinouts rev u page 22 71 338
• Arinc 429 input output 338
• For installations that enable ads b rs 232 input channel 2 should be connected to a gns 400w 500w series waas enabled unit or a gtn 6xx 7xx series unit this connection provides the gtx 23 with gps data for ads b the rs 232 output channel 2 is unused on the gtx 23 338
• Rs 232 input channel 1 is used to receive pressure altitude and control commands and to provide status tis a traffic and other data rs 232 output channel 1 provides unit status and tis data rs 232 channel 1 input and output are also used for software upgrades rs 232 port channel 1 on the gtx should be connected to the channel 1 rs 232 port on adahrs 1 338
• Rs 232 input output 338
• Serial data electrical characteristics 338
• The arinc 429 outputs conform to arinc 429 electrical specifications when loaded with up to five standard arinc 429 receivers arinc 429 out channel 1 is configured for low speed tis a data and arinc 429 out channel 2 is configured for high speed tis a data for a gns 4xx 5xx unit 338
• The rs 232 outputs conform to eia standard rs 232c with an output voltage swing of at least 5 v when driving a standard rs 232 load refer to figures in section 23 for the rs 232 serial data interconnect 338
• Core interconnect drawings w gsu 25 and or gad 29 339
• G3x w gsu 25 and or gad 29 interconnect drawings 339
• 01115 01 g3x installation manual g3x w gsu 25 and or gad 29 interconnect drawings rev u page 23 7 345
• Center off 2a center off 2a 345
• Dpdt momentary dpdt momentary 345
• Dual trim switches dual trim switches 345
• Figure 23 1 gsa 28 trim switch interconnect drawing 345
• Gsa 28 servo gsa 28 servo 345
• Single trim switch single trim switch 345
• External interconnect drawings w gsu 25 346
• Core interconnect drawings 362
• G3x w gsu 73 interconnect drawings 362
• External interconnect drawings w gsu 73 366
• G3x w gtr 20 interconnect drawings 376
• Notes for section 25 drawings 377
• Single gtr 20 interconnect drawings 378
• 01115 01 g3x installation manual g3x w gtr 20 interconnect drawings rev u page 25 7 382
• Can node length 0 meters maximum 0 meters maximum can node length 382
• Can node length 0 meters maximum can node length 0 meters maximum 382
• Dual gtr 20 interconnect drawings 382
• Figure 25 3 dual gtr 20 can bus interconnect drawing 382
• Garmin garmin 382
• Gtr 20 as com 1 gtr 20 as com 1 382
• Gtr 20 as com 2 gtr 20 as com 2 382
• 01115 01 g3x installation manual g3x w gtr 20 interconnect drawings rev u page 25 9 384
• Figure 25 4 j2001 connector layout 384
• J2001 as viewed looking at rear of unit 384
• J2001 connector layout 384
• Notes for section 26 drawings 385
• Sensor wiring examples 385
• Sensor wiring examples w gea 24 386
• 01115 01 g3x installation manual sensor wiring examples rev u page 26 4 388
• Figure 26 2 page 1 of 2 electrical and discrete input output examples w gea 24 388
• 01115 01 g3x installation manual sensor wiring examples rev u page 26 5 389
• Figure 26 2 page 2 of 2 electrical and discrete input output examples w gea 24 389
• Sensor wiring examples w gsu 73 391
• Lycoming continental sensor wiring examples 396
• Notes for section 27 drawings 396
• Gea 24 lycoming continental sensor drawings 397
• Gsu 73 lycoming continental sensor drawings 399
• 01115 01 g3x installation manual lycoming continental sensor wiring examples rev u page 27 5 400
• Figure 27 3 gsu 73 4 6 cylinder lycoming continental sensor wiring examples page 2 of 3 400
• Notes for section 28 drawings 402
• Rotax sensor wiring examples 402
• Gea 24 rotax sensor drawings 403
• Gsu 73 rotax sensor drawings 406
• 01115 01 g3x installation manual rotax sensor wiring examples rev u page 28 6 407
• Figure 28 3 gsu 73 rotax 912 914 sensor wiring examples page 2 of 2 407
• Ground ground 407
• Gsu 73 gsu 73 j732 j732 407
• Output output 407
• Rotax p n 965531 rotax p n 965531 407
• Supply voltage supply voltage 407
• 01115 01 g3x installation manual jabiru sensor wiring examples rev u page 29 1 408
• Figure 29 1 notes for jabiru sensor drawings for all section 29 drawings 408
• Jabiru sensor wiring examples 408
• Notes for section 29 drawings 408
• Gea 24 jabiru sensor drawings 409
• 01115 01 g3x installation manual jabiru sensor wiring examples rev u page 29 4 411
• 70 shunt 1 hi shunt 1 hi 411
• Battery contactor battery contactor 411
• Battery positive battery positive 411
• Blk ground pin a blk ground pin a 411
• Blu blu 411
• Figure 29 3 gsu 73 jabiru sensor wiring examples page 1 of 2 411
• Fuel press sensor fuel press sensor 411
• Grn output pin c grn output pin c 411
• Gsu 73 gsu 73 j732 j732 411
• Gsu 73 jabiru sensor drawings 411
• Manifold press hi manifold press hi 411
• Manifold press lo manifold press lo 411
• Ohm 005 ohm 411
• Red voltage in pin b red voltage in pin b 411
• Shunt 1 lo shunt 1 lo 411
• Wht wht wht wht 411
• 01115 01 g3x installation manual jabiru sensor wiring examples rev u page 29 5 412
• Figure 29 3 gsu 73 jabiru sensor wiring examples page 2 of 2 412
• Caution 413
• Gdu 37x configuration and post installation checkout 413
• Recommended test equipment 413
• Configuration mode 414
• Software loading procedure 414
• Caution 416
• Configuration pages 417
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 9 421
• After mechanical and electrical installation of the gsu 25 gsu 73 ahrs and gmu 22 magnetometer have been completed prior to operation a set of post installation calibration procedures must be carried out 421
• Gsu 25 gsu 73 gmu 22 post installation calibration procedures 421
• Table 30 1 describes the calibration procedures 421
• Table 30 1 post installation calibration procedure summary 421
• The calibration procedures section 30 section 30 may require that certain status boxes on the gsu page configuration mode indicate a positive state green check marks before starting the procedure table 30 2 and table 30 3 list the status box requirements for each calibration procedure 421
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 10 422
• A repeat of the pitch roll offset procedure procedure b requires a repeat of the magnetometer calibration procedure procedure d 422
• Any gmu 22 removal or replacement requires repeating the magnetometer calibration 422
• For each calibration procedure table 30 2 lists the lru s that require valid calibration data 422
• If removal and replacement of a gmu 22 unit is required after post installation calibration has been completed the gmu 22 mounting rack must not be moved if the mounting screws that secure the gsu 25 gsu 73 unit or the gmu 22 mounting rack are loosened for any reason post installation calibration procedure a b d and e must be repeated before the aircraft can be returned to service 422
• Table 30 2 data validity requirements for ahrs calibration procedures 422
• Table 30 3 configuration mode ahrs page status boxes 422
• Table 30 3 lists the type of valid calibration data required to be output by each lru for the calibration procedures listed in table 30 2 422
• The ahrs configuration page status boxes referred to in table 30 2 and table 30 3 are shown in the following figure 422
• Caution 429
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 20 432
• Table 30 4 magnetometer interference test sequence example 432
• Caution 442
• Bank left bank right 452
• Nose down nose up 453
• Nose left nose right 454
• Warning 463
• Warning 467
• Below and should only be adjusted after studying the description to properly understand their effect on the yaw servo 469
• The yaw servo has additional advanced and expert level settings that can be adjusted to achieve the desired yaw damping performance these settings are detailed in 469
• Re verify proper trim movement in described in section 30 steps 6 7 8 471
• Warning 472
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 62 474
• Detailed autopilot configuration options 474
• Figure 30 16 general autopilot configuration page 474
• General configuration page 474
• Table 30 5 general autopilot configuration settings 474
• The installer needs to make the following autopilot configuration selections when setting up the gsa 28 based autopilot system 474
• These selections are made in configuration mode using the ap config page 474
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 63 475
• Roll servo configuration 475
• Table 30 6 roll servo autopilot configuration settings 475
• The installer needs to make the following roll servo configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode using the ap config page and the roll servo setup screen in the autopilot setup menu in normal mode 475
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 64 476
• Figure 30 17 roll servo autopilot configuration page 476
• Table 30 6 roll servo autopilot configuration settings 476
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 65 477
• Pitch servo configuration 477
• Table 30 7 pitch servo autopilot configuration settings 477
• The installer needs to make the following pitch servo configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode using the ap config page and the pitch servo setup screen in the autopilot setup menu in normal mode 477
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 66 478
• Figure 30 18 pitch servo autopilot configuration page 478
• Table 30 7 pitch servo autopilot configuration settings 478
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 67 479
• Table 30 8 yaw damper autopilot configuration settings 479
• The installer needs to make the following yaw damper configuration selections when setting up the gsa 28 based yaw damper system these selections are made in configuration mode using the ap config page and the yaw damper setup screen in the autopilot setup menu in normal mode 479
• Yaw damper configuration 479
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 68 480
• Figure 30 19 yaw damper autopilot configuration page 480
• Table 30 8 yaw damper autopilot configuration settings 480
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 69 481
• Pitch gain configuration 481
• Table 30 9 pitch gain autopilot configuration settings 481
• The installer needs to make the following pitch gain configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode on the pfd under the ap tab and the pitch gain setup screen in the autopilot setup menu in normal mode 481
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 70 482
• Figure 30 20 pitch gain autopilot configuration page 482
• Table 30 9 pitch gain autopilot configuration settings 482
• 01115 01 g3x installation manual gdu 37x configuration and post installation checkout rev u page 30 71 483
• Manual electric trim configuration 483
• Table 30 10 manual electric trim autopilot configuration settings 483
• The installer needs to make the following manual electric trim configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode on the pfd under the ap tab and the pitch gain setup screen in the autopilot setup menu in normal mode 483
• Warning 485
• Automatic backlight control window settings apply only to auto setting 507
• Display backlight configuration window 507
• Garmin database updates 545
• Siriusxm activation instructions gdu 375 only 549
• External interface configuration garmin units only 550
• Checklist editor 553
• Gdu splash screen 553
• Caution 554
• Gdu 45x 46x configuration and post installation checkout 554
• Configuration mode 555
• Recommended test equipment 555
• Software loading procedure 556
• Caution 557
• Configuration pages 558
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 9 562
• After mechanical and electrical installation of the gsu 25 gsu 73 adahrs and gmu 22 magnetometer have been completed prior to operation a set of post installation calibration procedures must be carried out 562
• Gsu 25 gsu 73 gmu 22 post installation calibration procedures 562
• Table 31 1 describes the calibration procedures 562
• Table 31 1 post installation calibration procedure summary 562
• Table 31 2 and table 31 3 list the status box requirements for each calibration procedure 562
• The calibration procedures 31 31 may require that certain status boxes on the gsu page configuration mode indicate a positive state green check marks before starting the procedure 562
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 10 563
• A repeat of the pitch roll offset procedure procedure b requires a repeat of the magnetometer calibration procedure procedure d 563
• Any gmu 22 removal or replacement requires repeating the magnetometer calibration 563
• Figure 31 3 adahrs status boxes 563
• For each calibration procedure table 31 2 lists the lrus that require valid calibration data 563
• If removal and replacement of a gmu 22 unit is required after post installation calibration has been completed the gmu 22 mounting rack must not be moved if the mounting screws that secure the gsu 25 gsu 73 unit or the gmu 22 mounting rack are loosened for any reason post installation calibration procedure a b d and e must be repeated before the aircraft can be returned to service 563
• Table 31 2 data validity requirements for adahrs calibration procedures 563
• Table 31 3 configuration mode adahrs calibration page status boxes 563
• Table 31 3 lists the type of valid calibration data required to be output by each lru for the calibration procedures listed in table 31 2 563
• The adahrs calibration page status boxes referred to in table 31 2 and table 31 3 are shown in figure 31 3 563
• Caution 569
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 19 572
• Table 31 4 magnetometer interference test sequence example 572
• Caution 580
• Warning 584
• Bank left bank right 611
• Nose down nose up 612
• Nose left nose right 613
• Warning 622
• Warning 628
• Below and should only be adjusted after studying the description to properly understand their effect on the yaw servo 631
• The yaw servo has additional advanced and expert level settings that can be adjusted to achieve the desired yaw damping performance these settings are detailed in 631
• Re verify proper trim movement in described in section 31 steps 6 7 8 633
• Warning 634
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 83 636
• Detailed autopilot configuration options 636
• Figure 31 25 general autopilot configuration page 636
• General configuration page 636
• Table 31 5 general autopilot configuration settings 636
• The installer needs to make the following autopilot configuration selections when setting up the gsa 28 based autopilot system 636
• These selections are made in configuration mode using the ap config page 636
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 84 637
• Roll servo configuration 637
• Table 31 6 roll servo autopilot configuration settings 637
• The installer needs to make the following roll servo configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode using the ap config page and the roll servo setup screen in the autopilot setup menu in normal mode 637
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 85 638
• Table 31 6 roll servo autopilot configuration settings 638
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 87 640
• Pitch servo configuration 640
• Table 31 7 pitch servo autopilot configuration settings 640
• The installer needs to make the following pitch servo configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode using the ap config page and the pitch servo setup screen in the autopilot setup menu in normal mode 640
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 88 641
• Table 31 7 pitch servo autopilot configuration settings 641
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 90 643
• Table 31 8 yaw damper autopilot configuration settings 643
• The installer needs to make the following yaw damper configuration selections when setting up the gsa 28 based yaw damper system these selections are made in configuration mode using the ap config page and the yaw damper setup screen in the autopilot setup menu in normal mode 643
• Yaw damper configuration 643
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 91 644
• Table 31 8 yaw damper autopilot configuration settings 644
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 93 646
• Pitch gain configuration 646
• Table 31 9 pitch gain autopilot configuration settings 646
• The installer needs to make the following pitch gain configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode on the pfd under the ap tab and the pitch gain setup screen in the autopilot setup menu in normal mode 646
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 94 647
• Figure 31 29 pitch gain autopilot configuration page 647
• Table 31 9 pitch gain autopilot configuration settings 647
• 01115 01 g3x installation manual gdu 45x 46x configuration and post install checkout rev u page 31 95 648
• Figure 31 30 manual electric trim autopilot configuration page 648
• Manual electric trim configuration the installer needs to make the following manual electric trim configuration selections when setting up the gsa 28 based autopilot system these selections are made in configuration mode on the pfd under the ap tab and the pitch gain setup screen in the autopilot setup menu in normal mode 648
• Table 31 10 manual electric trim autopilot configuration settings 648
• Garmin database updates 708
• Siriusxm activation instructions gdu 455 465 only 711
• External interface configuration garmin units only 712
• Checklist editor 715
• General troubleshooting 716
• Troubleshooting 716
• Gdu 37x 46x 717
• Air data troubleshooting 718
• Engine indication troubleshooting 719
• Adahrs troubleshooting 720
• Post installation calibration procedures 722
• Gsu 73 data logging 723
• Inspections continued airworthiness maintenance 726
• Maintenance 726
• Return to service information 728
• A introduction 731
• Appendix a airframe specific installation guidance 731
• A van s aircraft 732
• A lancair aircraft 734
• When routing the gmu 22 wiring with other power sources ensure each power source contains an adequate return ground it is important to route the return ground with the power wire to help cancel stray magnetic fields route nav light wiring as far as practical away from the gmu 22 736
• The gmu 22 installation rack 115 00481 00 should be installed parallel to the mount ing surface of the magnetometer bracket 115 01017 00 to ensure the finished gmu 22 installation will be in alignment with the lancair es es p aircraft heading the gmu 22 installation rack 115 00481 00 should be installed with the forward arrow marked on the ring indicating a direction parallel with the outboard wing rib which acts as a reference for the aircraft s forward direction 737
• 00481 00 gmu 22 installation rack 747
• 01115 01 g3x installation manual airframe specific installation guidance rev u page a 17 747
• Assemble the gmu 22 installation rack to the magnetometer shelf as shown in figure a 27 747
• Figure a 26 magnetometer shelf with hole pattern for gmu 22 installation rack 747
• Figure a 27 assembly of gmu 22 installation rack to magnetometer shelf 747
• Magnetometer shelf ref 747
• X 6 32 stainless nuts ms21083c06 or equivalent 747
• X 6 32 stainless screws 100 countersunk ms24693c or equivalent 747
• X an960c6 washers 747
• Appendix b rs 232 text output format 749
• B electrical interface 749
• B general message output format 749
• B message output selection 749
• 01115 01 g3x installation manual rs 232 text output format rev u page b 2 750
• B attitude air data message format 750
• Field name offset width units notes min max 750
• Table b 1 attitude air data message format 750
• The attitude air data message is transmitted approximately 10 times per second 750
• 01115 01 g3x installation manual rs 232 text output format rev u page b 3 751
• B engine data message format 751
• Field name offset width units notes min max 751
• Table b 2 engine data message format 751
• The engine data message is transmitted approximately 5 times per second 751
• 01115 01 g3x installation manual rs 232 text output format rev u page b 4 752
• Field name offset width units notes min max 752
• Table b 2 engine data message format 752
• 01115 01 g3x installation manual rs 232 text output format rev u page b 5 753
• B gps data message format 753
• Field name offset width units notes min max 753
• Table b 3 gps data message format 753
• The gps data message is transmitted once per second 753
• 01115 01 g3x installation manual rs 232 text output format rev u page b 6 754
• Field name offset width units notes min max 754
• For more information on the gps data message see http www8 garmin com support text_out html 754
• Table b 3 gps data message format 754
• Appendix c lru performance specifications licensing compliance 755
• C gad 29 755
• C gap 26 755
• C gdu 37x 755
• C gdu 45x 46x 756
• C gea 24 756
• C gmc 305 307 756
• 01115 01 g3x installation manual lru performance specs licensing compliance rev u page c 3 757
• C environmental specifications 757
• C gmu 22 757
• C gsa 28 757
• C gsu 25 757
• Table c 4 gmu 22 environmental specifications 757
• Table c 4 lists general environmental specifications 757
• Table c 5 gsa 28 environmental specifications 757
• Table c 5 lists general environmental specifications 757
• Table c 6 gsu 25 environmental specifications 757
• Table c 6 lists general environmental specifications for the gsu 25 table c 7 lists general environmental specifications for the gsu 25b 757
• C 0 gsu 73 759
• 01115 01 g3x installation manual lru performance specs licensing compliance rev u page c 6 760
• C 1 gtp 59 760
• C 1 tso etso compliance 760
• C 1 tso etso deviations 760
• Table c 10 tso etso deviations for the gtp 59 760
• Table c 9 applicable tso etsos for the gtp 59 760
• The following deviations have been requested and granted for the gtp 59 760
• The following table provides a list of applicable tso etsos for the gtp 59 760
• C 2 gtr 20 200 761

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