GARMIN G3X Touch Flight Displays for Experimental Aircraft Instruction Manual
- June 6, 2024
- Garmin
Table of Contents
GARMIN G3X Touch Flight Displays for Experimental Aircraft
Product Information
Specifications
- 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.
FAQs
- Q: Is the G3X system suitable for installation in type-certificated aircraft?
- A: No, the G3X system is not type-certificated and is not suitable for installation in type-certificated aircraft.
- Q: Where can I find additional information about chemicals in the product?
- A: For information about chemicals in the product, refer to our website at www.garmin.com/prop65.
- Q: How many displays do the installation guidance and instructions apply to?
- A: Unless otherwise noted, all installation guidance, requirements, and instructions apply to one, two, three, four, five, and six-display G3X systems.
G3XTM/G3X TouchTM Avionics Installation
Manual
190-01115-01
May, 2024
Revision AV
© 2024 Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced,
copied, transmitted, disseminated, downloaded or stored in any storage medium,
for any purpose without the express prior written consent of Garmin. Garmin
hereby grants permission to download a single copy of this manual and of any
revision to this manual onto a hard drive or other electronic storage medium
to be viewed and to print one copy of this manual or of any revision hereto,
provided that such electronic or printed copy of this manual or revision must
contain the complete text of this copyright notice and provided further that
any unauthorized commercial distribution of this manual or any revision hereto
is strictly prohibited.
Garmin International, Inc. 1200 E. 151st Street
Olathe, KS 66062 USA Garmin (Europe) Ltd. Liberty House, Hounsdown Business
Park Southampton, Hampshire SO40 9LR U.K.
Garmin Würzburg GmbH Beethovenstrasse 1a
97080 Würzburg, Germany
Garmin aviation product support information can be found at flyGarmin.com®
website or contacted by email at g3xpert@garmin.com.
RECORD OF REVISIONS
Revision
AR AS AT AU AV
Revision Date
12/15/22 03/06/23 07/17/23 08/23/23 05/13/24
Description
Various updates Various updates Added GHA 15 info, various updates Updated AOA
configuration info Added new GAD 27 unit info
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CURRENT REVISION DESCRIPTION
Revision AV
Page Number(s) iii 1-5 1-9 2-6 2-6 2-7 2-8 2-8
2-24 3-3 3-5 7-1 21-3, 21-4 21-10 21-28 22-22, 22-24 23-4
23-2423-27
23-30, 23-32, 23-33, 23-3623-38
24-25, 24-32, 24-34, 24-51
26-1, 26-3, 26-5, 26-7 27-2, 27-3
28-228-5
30-6 30-11, 30-12
30-24 30-37 30-104, 30-107, 30-110
30-123, 30-125, 30-127
30-146 30-150 30-157 30-170 30-181, 30-187, 30-18930-193, 30-19830-201,
30-203 30-20630-209, 30-215, 30-218, 30-222, 30-227, 30-232 30-236
31-1 H-109
Section Number Front 1.5.1 1.5.4 2.1.1.7 2.1.1.8
2.1.1.10 2.1.1.11 2.1.1.12 2.3.1.3.2
3.2.1 3.6 7 21.1 21.2.2.2 21.3.5.4 22.7 23.1.3 23.4.2, 23.4.3, 23.4.4 23.4.8,
23.4.11, 23.4.12, 23.4.17, 23.4.18
24.2
26 27.2
28.2
30.4.3 30.4.7 30.4.7.5 30.4.9
30.4.10.10
30.4.13.1, 30.4.13.2, 30.4.13.3
30.4.18 30.4.20 30.4.22 30.4.22
30.4.32
30.5.1 31
H.4.14
Description of Change Added note regarding GEA 24/24B Updated CAN Bus Wire
info Added reference to SDUC cards Updated Engine Information section Updated
GPS info Updated Navigation info Updated COM Radios info Updated NAV Radios
info Updated CAN Bus Wiring info Updated part numbers in GAD 27 Part Numbers
Table 3-1 Updated Figure 3-3 Added reference to SDUC cards Corrected part info
in Table 21-1 Updated Rotax info Added Surefly TACH2 Module section Updated
Circular Connector info Added note regarding Keep Alive Power VOut
Updated J242, J243, and J244 pin names
Updated pin names
Updated Figure 24-2.6 Figure 24-2.12,and Figure 24-2.14,added Figure 24-2.31
Updated Figure 26-1, Figure 26-2.1, Figure 26-2.2, & Figure 26-2.3 Updated
Figure 27-2 p. 1 of 2 and Figure 27-2 p. 2 of 2 Updated Figure 28-2.1 p. 1 of
2, Figure 28-2.1 p. 2 of 2, Figure 28-2.2, and Figure 28-2.3 Updated System
Information Page section Updated ADAHRS Calibration section Added Zero-
Airspeed Calibration section Updated AOA Configuration Page info
Updated Detailed Autopilot Configuration Page Options info
Updated Roll, Pitch, and Yaw Trim Configuration info
Updated Display Configuration Page info Updated Sound Configuration Page info
Updated ARINC 429 Configuration Page info Updated COM Radio Configuration Page
info
Updated Engine and Airframe Configuration info
Updated Updating Garmin Databases info Updated Product Support phone number
Added Aviation Out info
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G3XTM/G3X TouchTM Avionics Installation Manual Page i
INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain
information which is subject to the Export Administration Regulations (“EAR”)
issued by the United States Department of Commerce (15 CFR, Chapter VII
Subchapter C) and which may not be exported, released or disclosed to foreign
nationals inside or outside the United States without first obtaining an
export license. The preceding statement is required to be included on any and
all reproductions in whole or in part of this manual.
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
WARNING This product, its packaging, and its components contain chemicals
known to the State of California to cause cancer, birth defects, or
reproductive harm. This Notice is being provided in accordance with
California’s Proposition 65. If you have any questions or would like
additional information, please refer to our website at www.garmin.com/prop65.
NOTE G3XTM avionics includes non-TSO certified products that have received no
FAA approval or endorsement. Consequently the G3X system is not type-
certificated and is not suitable for installation in type-certificated
aircraft.
NOTE Unless otherwise noted all installation guidance, requirements, and
instructions apply to one, two, three, four, five, and six-display G3X
systems.
NOTE References to the GAD 29 throughout this manual apply equally to the GAD
29C. References to the GAD 29B throughout this manual apply equally to the GAD
29D.
NOTE References to the GDUTM 37X display throughout this manual apply equally
to the GDU 370 and GDU 375 except where specifically noted.
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NOTE References to the GDU 45X throughout this manual apply equally to the GDU 450 and GDU 455 except where specifically noted.
NOTE References to the GDU 46X throughout this manual apply equally to the GDU 460 and GDU 465 except where specifically noted.
NOTE References to the GDU 4XX throughout this manual apply equally to the GDU 45X, GDU 46X, and GDU 47X except where specifically noted.
NOTE References to the GEA 24 throughout this manual apply equally to the GEA 24B except where specifically noted.
NOTE References to the GMC Mode Controller throughout this manual apply equally to the GMC 305, GMC 307, and GMC 507 except where specifically noted.
NOTE References to the GSU 25 throughout this manual apply equally to the GSU 25B, GSU 25C, and GSU 25D except where specifically noted.
NOTE The term LRU, as used throughout this manual is an abbreviation for Line Replaceable Unit. LRU is used generically in aviation for a product (such as a GDU 37X or GTP 59) that can be readily “swapped out” (usually as a single component) for troubleshooting/ repair.
NOTE All GMU 22 information in this Installation Manual also applies to the GMU 44. The GMU 44 had previously been used as the G3X magnetometer but has been replaced by the GMU 22.
NOTE Connector references JXXX(X) and PXXX(X) are used throughout this document. 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 4XX connectors on the LRU are designated as P4X0X.
NOTE The GDU 37X/4XX products contain a lithium battery that must be recycled or disposed by professional services according to applicable governing laws. Only Garmin-authorized service facilities are permitted to perform maintenance on this product.
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NOTE The Bluetooth® word mark and logos are registered trademarks owned by
Bluetooth SIG, Inc. and any use of such marks by Garmin is under license.
NOTE Throughout this document, “GPN” refers to Garmin Part Number.
SOFTWARE LICENSE AGREEMENT
BY USING THE DEVICE, COMPONENT OR SYSTEM MANUFACTURED OR SOLD BY GARMIN (“THE
GARMIN PRODUCT”), YOU AGREE TO BE BOUND BY THE TERMS AND CONDITIONS OF THE
FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT CAREFULLY.
Garmin Ltd. and its subsidiaries (“Garmin”) grants you a limited license to
use the software embedded in the Garmin Product (the “Software”) in binary
executable form in the normal operation of the Garmin Product. Title,
ownership rights, and intellectual property rights in and to the Software
remain with Garmin and/or its third-party providers. You acknowledge that
Software is the property of Garmin and/or its third-party providers and is
protected under the United States of America copyright laws and international
copyright treaties. You further acknowledge that structure, organization, and
code of the Software are valuable trade secrets of Garmin and/or its third-
party providers and that Software in source code form remains a valuable trade
secret of Garmin and/or its third-party providers. You agree not to reproduce,
decompile, disassemble, modify, reverse assemble, reverse engineer, or reduce
to human readable form the Software or any part thereof or create any
derivative works based on the Software. You agree not to export or re-export
the Software to any country in violation of the export control laws of the
United States of America.
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G3XTM/G3X TouchTM Avionics Installation Manual Page xii
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
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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
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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.
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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
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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
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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)
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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)
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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.
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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)
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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)
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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.
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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)
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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
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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.
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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%
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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%
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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.
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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
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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
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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
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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
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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:
info@gigaflightinc.com
· 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.
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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.
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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
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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
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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.
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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.
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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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