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12. MFD
13. PFD Direct-to-Course
14. PFD Flight Plan Page
15. PFD Clear/Cancel Information
16. PFD Flight Management System
17. GFC 705 Mode Controller (opt)
18. Audio Panel
19. PFD Enter Key
20. PFD Procedures
21. PFD Menu Key
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-71
Figure 7-16
Perspective Integrated Avionics System (Sheet 2 of 2)
Flight Management System Keyboard
RANGE
PUSH
- +
PAN
HDG
CRS
ALT SEL
GARMIN
A B C D E F
G H I J K
L M N O P Q
R
W
S
X
T
Y
U
Z
V
SPC BKSP
1 2 3
4 5 6
7 8 9
0 +/-
CRSR/1-2 EMERG
PUSH
FMS/XPDR
COM/NAV
IDENT
DFLT MAP
PUSH SYNC
PUSH CTR
PUSH SYNC
D
FPL
CLR
MENU
PROC
ENT
FMS XPDR
COM NAV
Legend
22. MFD Clear/Cancel Information
(Default Map)
23. MFD Flight Plan Page
24. MFD Direct-to-Course
25. MFD Menu
26. MFD Procedures
27. MFD Enter Key
28. COM Tuning Mode
29. FMS Mode
30. Transponder Mode (Ident)
22 23
40 32
35
33
31. NAV Tuning Mode
32. MFD Range/Pan Joystick
33. Frequency Transfer (121.5 Tune)
34. MFD FMS XPDR/NAV/COM Control
35. Alphanumeric Keys
36. Backspace Key
37. Space Key
38. Altitude Selection (PFD)
39. Course Selection (HSI)
40. Heading Selection (PFD HSI)
SR22_FM07_2821
34
35 37 36
39
38
24 25 26 27 28 29 30 31
March 2010
7-72 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
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.
GMA 347 Audio Panel with Integrated Marker Beacon Receiver
The Audio Panel, installed on the center console below the Flight
Management System Keyboard, integrates NAV/COM digital audio,
intercom and marker beacon controls. The VHF communications
portion of the unit interfaces with both Integrated Avionics Units to
provide external radio communication, receive and demodulate VOR,
Localizer, and Glide Slope signals.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-73
28 VDC for Audio Panel operation is supplied through the 5-amp
AUDIO PANEL circuit breaker on the AVIONICS bus.
• Note •
COM swap mode is not available in this installation.
For a detailed operating instructions, refer to the GMA 347 Audio
Panel Pilot’s Guide.
Optional Avionics supplied for use with the Perspective
Integrated Avionics System
GFC 700 3-Axis Autopilot and GMC 705 Autopilot Controller
Refer to Section 9, Supplements for GFC 700 3-Axis Autopilot
operating information.
GTX 33 Mode S Transponder
　
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