Garmin International Inc 0212800 Manuel D’Utilisation
190-01561-00
GIA 6300 Installation Manual
Draft1
Page 10
Note 2: See the Environmental Qualification Form for details on surge rating and minimum/maximum
operating voltages.
operating voltages.
7 Environmental Qualifications
8 System Interconnect
8.1 Unit Level Connections
Figure XXX shows the electrical top level design of the GIA 6300. The GIA 6300 consists of 9 separate
circuit boards and the GPS module. External interfaces are passed through the IO Board to the Main A,
Main B, COM Digital, NAV, and Audio boards.
circuit boards and the GPS module. External interfaces are passed through the IO Board to the Main A,
Main B, COM Digital, NAV, and Audio boards.
Main A
Main B
NAV
Glideslope
GPS
COM Digital
COM RF
Audio
IO Board
8.1.1 Main A and Main B Redundancy
Main A and Main B in the GIA6300 function as two independent units, allowing for separation and
redundancy in each GIA. Both GIA 1 and GIA 2 are connected to the sensors, but in each GIA, Main A
and Main B can be connected to a different set of sensors (i.e. Main A is connected to all primary
sensors and Main B is connected to all redundant sensors). Data is shared between the two main
boards through the inter-processor communication.
redundancy in each GIA. Both GIA 1 and GIA 2 are connected to the sensors, but in each GIA, Main A
and Main B can be connected to a different set of sensors (i.e. Main A is connected to all primary
sensors and Main B is connected to all redundant sensors). Data is shared between the two main
boards through the inter-processor communication.
The COM Digital, NAV, and the Audio board each connect to both Main A and B so that there is
redundant communication between these components and the rest of the system. It is possible to wire
the aircraft such that a total failure of either Main A or Main B cannot cause a total loss of COM, NAV, or
Audio functionality. In the event of a single Main Board failure, the second main board would still be
capable of tuning the COM, collecting navigation data, and processing autopilot and flight director
functionality (as examples).
redundant communication between these components and the rest of the system. It is possible to wire
the aircraft such that a total failure of either Main A or Main B cannot cause a total loss of COM, NAV, or
Audio functionality. In the event of a single Main Board failure, the second main board would still be
capable of tuning the COM, collecting navigation data, and processing autopilot and flight director
functionality (as examples).