190-01115-01 G3X™/G3X Touch™ Avionics Installation Manual
Rev. AV Page G-2
G.1 Core Interconnect Drawings
Figure G-1.1 Core (w/GSU 73) Interconnect Notes for Appendix G.1 and 2 Display CAN
Bus Interconnect Drawing
SHIELD TERMINATED TO GROUND
TWISTED SHIELDED 3 CONDUCTOR
SHIELD FLOATS
TWISTED SHIELDED 3 CONDUCTOR
4. SYMBOL DESIGNATIONS
TWISTED SHIELDED PAIR
SHIELD TERMINATED TO GROUND
SHIELD FLOATS
TWISTED SHIELDED PAIR
TWISTED SHIELDED SINGLE CONDUCTOR
SHIELD TERMINATED TO GROUND
SHIELD FLOATS
TWISTED SHIELDED SINGLE CONDUCTOR
1. UNLESS OTHERWISE NOTED, ALL STRANDED WIRE MUST CONFORM TO MIL-W-22759/16 OR EQUIVALENT
2. UNLESS OTHERWISE NOTED, ALL SHIELDED WIRE MUST CONFORM TO MIL-C-27500 OR EQUIVALENT
3. UNLESS OTHERWISE NOTED, ALL WIRES ARE 24 GAUGE MINIMUM.
5. UNLESS OTHERWISE NOTED, ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS.
ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE.
8. INSTALLATION INFORMATION IS PROVIDED FOR CONNECTORS, CONFIGURATION MODULES AND THERMOCOUPLES IN SECTION 21,
NOTES:
WIRE SPLICE CONNECTION
COAXIAL CABLE
SHIELD TERMINATED TO GROUND
TWISTED SHIELDED 4 CONDUCTOR
SHIELD FLOATS
TWISTED SHIELDED 4 CONDUCTOR
N/C = NO CONNECTION
S
GARMIN SHIELD BLOCK GROUND
6. WIRE COLORS ARE NOTED FOR ADVISORY PURPOSES ONLY, EXCEPT FOR THE CONFIG MODULE AND GTP 59.
9. IN A 2 DISPLAY INSTALLATION, THE SECOND DISPLAY CAN BE CONNECTED AS SHOWN.
AND IN SECTION 17 FOR THE GTP 59.
AIRCRAFT GROUND
10. OPTIONAL INTERFACE.
12. ONLY ONE GDU 46X/37X GPS ANTENNA CONNECTION IS REQUIRED FOR THE G3X SYSTEM. ADDITIONAL ANTENNAS CAN BE ADDED
FOR REDUNDANCY IF DESIRED. SEE SECTION 17 FOR GPS CONFIGURATION INFORMATION.
11. THE GDU 46X/37X CAN BE CONFIGURED TO ACCEPT A 14V OR 28V LIGHTING BUS INPUT. SEE APPDX H FOR CONFIGURATION.
13. THE CAN BUS SHOULD ONLY BE TERMINATED AT ONE GDU 46X/37X WHEN THE CAN BUS IS TERMINATED AT THE GSU 73.
14. TO MINIMIZE THE CHANCE OF THE SYSTEM RESETTING DURING ENGINE CRANKING, THE OPTIONAL REDUNDANT (DIODE OR'D) POWER INPUTS MAY BE
CONNECTED TO AN AUXILIARY BATTERY (SUCH AS THE TCW TECHNOLOGIES INTEGRATED BACK-UP BATTERY SYSTEM) OR STABILIZED
POWER INPUT (SUCH AS THE TCW TECHNOLOGIES INTELLIGENT POWER STABILIZER IPS-12V-8A) TO MAINTAIN THE NECESSARY
LRU MINIMUM INPUT VOLTAGE. HAVING A STABLIZED SOURCE OF POWER DURING ENGINE CRANKING SHOULD ALLOW THE SYSTEM
TO PROVIDE CONTINUOUS ENGINE INDICATING SYSTEM (EIS) OPERATION DURING ENGINE START AND MAINTAIN ANY DESIRED
PRE-FLIGHT SYSTEM SETUP OR FLIGHT PLANNING THAT WAS ACCOMPLISHED PRIOR TO ENGINE START. VISIT WWW.TCWTECH.COM
15. THE DISCRETE OUTPUT FROM THE TCW IBBS CAN BE WIRED TO A DISCRETE INPUT ON THE GSU 73 TO PROVIDE THE PILOT WITH AN
ANNUNCIATION WHEN THE BACK-UP BATTERY IS BEING UTILIZED. SEE APPDX H FOR MORE INFORMATION ON CONFIGURATION
OF GSU 73 DISCRETE INPUTS.
FOR ADDITIONAL DETAILS.
7. NOTE REMOVED
GDU 46X/37X (PFD #1)
CONFIG MODULE DATA
CONFIG MODULE CLOCK
CONFIG MODULE GROUND
CONFIG MODULE POWER
49
17
50
33
CAN BUS TERMINATION28
CAN BUS LO45
CAN BUS HI46
WHT
BLU
OPT GDU 46X/37X (MFD)
CAN BUS TERMINATION28
CAN BUS LO45
CAN BUS HI46
CAN BUS HI
GSU 73
7
CAN BUS LO 8
WHT
BLU
S
CAN BUS TERMINATION 29
P731
P4602/P3701
P4602/P3701
WHT
BLU
SEE NOTE 13
WHT
BLU
SEE NOTE 9
S
NOTE: NODE CONNECTIONS FROM DEVICE TO
CAN BUS OF ONLY A FEW INCHES
MAY USE UNSHIELDED 22 AWG WIRE
CAN BUS
CAN NODE
S
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