Cirrus SR20 Pilot Operating Handbook page 270

Section 7 Cirrus Design
Airplane and Systems Description SR20
GIA 63W Integrated Avionics Units
The Integrated Avionics Units, located behind the MFD and instrument
panel, function as the main communication hub, linking all Integrated
Avionics System components with the PFD. Each Integrated Avionics
Unit contains a GPS WAAS receiver, VHF COM/NAV/GS receivers,
system integration microprocessors, and flight director if the optional
AFCS is installed. The Integrated Avionics Units are not paired
together and do not communicate with each other directly.
28 VDC for Integrated Avionics Unit 1 operation is supplied through
the 7.5-amp COM 1 and 5-amp GPS NAV GIA 1 circuit breakers on
the ESS BUS 1. 28 VDC for Integrated Avionics Unit 2 operation is
supplied through the 7.5-amp COM 2 and 5-amp GPS NAV GIA 2
circuit breakers on the MAIN BUS 2.
GEA 71 Engine Airframe Unit
The Engine Airframe Unit, mounted behind the MFD, receives and
processes analog signals from the fuel gaging system, CHT, EGT,
MAP, RPM and other sensors and transmits this data to the Integrated
Avionics Unit.
28 VDC for Engine Airframe Unit operation is supplied through the 3-
amp ENGINE INSTR circuit breaker on the ESS BUS 2.
GTX 32 Transponder
The GTX 32 solid-state transponder communicates with the primary
Integrated Avionics Unit and provides Modes A and C interrogation/
reply capabilities. The transponder is controlled via the PFD or Flight
Management System Keyboard and is located in the empennage
avionics compartment.
28 VDC for Transponder operation is supplied through the 2-amp
XPONDER circuit breaker on AVIONICS BUS. Refer to the
Perspective Integrated Avionics System Pilot's Guide for a complete
description of the system, its operating modes, and additional detailed
operating procedures.
7-86 P/N 21399-004
Revision A1