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a. GPS 1 in this configuration is a GARMIN GNS 430 GPS
Navigator with VHF COM interfaced with the HSI and ARNAV
ICDS 2000 Multifunction Display (MFD). Pressing the
alternate-action CDI push-button on GPS 1 alternately selects
GPS or NAV for display in the HSI and MFD each time the
button is depressed. The HSI source is indicated by
illumination of the “GPS” or “VLOC” annunciation in the lower
left corner of the GNS 430 display.
• Note •
The HSI displays course deviation from a VOR, Localizer
(LOC) or Glideslope (G/S) when VLOC is the navigation
source and displays GPS track deviation when GPS is the
selected navigation source.
b. GPS 2 in this configuration is a GARMIN GNS 430 GPS
Navigator with VHF COM interfaced with the CDI (VOR/LOC/
ILS/GS Indicator). Pressing the alternate-action CDI pushbutton
on GPS 2 alternately selects GPS or NAV for display in
the CDI each time the button is depressed. The HSI source is
Revised: May 25, 2005
11934-S03 7 of 10
Cirrus Design Section 9
SR20 Supplements
indicated by illumination of the “GPS” or “VLOC” annunciation
in the lower left corner of the GNS 430 display.
• Note •
The CDI displays course deviation from a VOR, Localizer
(LOC) or Glideslope (G/S) when VLOC is the navigation
source and displays GPS track deviation when GPS is the
selected navigation source.
Deactivate GPS
1. Navigator COM/ Power Switch.......................... Rotate CCW ‘OFF’
Section 5 - Performance
No change from basic Handbook.
Section 6 - Weight & Balance
No change from basic Handbook.
Section 7 - Systems Description
• Note •
This supplement provides a general description of the Garmin
GNS 430, its operation, and SR20 interface. For a detailed
description of the GNS 430 and full operation instructions refer
to the Garmin GNS 430 Pilot's Guide and Reference, P/N 190-
00140-00, Revision A dated December 1998 (or later
appropriate revision).
The following paragraphs describe a single GARMIN GNS
430 unit and its functions. In the event a second GNS 430 is
installed, the second unit will function as described below
except that the GPS navigator is designated ‘GPS 2,’ the NAV
receiver is designated ‘NAV 2,’ and the VHF communications
receiver is designated ‘COM 2.’ The GPS 2 GPS navigator
and VHF NAV is powered by 28 VDC through the Avionics
Master Switch and the 5-amp GPS2 circuit breaker on the
Avionics Essential Bus. 28VDC for transceiver operation is
supplied through the Avionics master Switch and the 7.5-amp
COM2 circuit breaker on the Avionics Non-Essential Bus.
Revised: May 25, 2005
8 of 10 11934-S03
Section 05-25-05 Cirrus Design
11934-S03 R2 SR20
GNS 430 Integrated GPS/NAV/COM System
This airplane is equipped with a GNS 430 integrated GPS navigator,
NAV receiver, and COM transceiver. The GPS navigator consists of a
GPS receiver, a navigation computer, and a Jeppesen NavData
database all contained in the GNS 430 control unit mounted in the
center console. The GPS is designated ‘GPS 1.’ A VHF NAV receiver
and tuner for receiving VHF Omnirange (VOR), Localizer (LOC), and
Glideslope (G/S) is also integrated into the control unit. The NAV
receiver is designated ‘NAV 1.’ Additionally, a VHF communications
receiver, designated ‘COM 1,’ is also integrated into the unit. All tuning
and display controls for the GPS, NAV, and COM are located in the
GNS 430 control/display in the center console. The following
paragraphs describe the GPS, NAV, and COM functions of this unit.
For a complete description, as well as full operating instructions, refer
to the Garmin GNS 430 Pilot’s Guide and Reference.
GPS Navigator
The Garmin GNS 430 GPS navigator is the primary system (GPS 1),
is IFR certified, and is coupled to the airplane’s HSI (or HSI) and
ARNAV moving map display. Normally, the second GPS Navigator
provides backup and is approved for VFR use only. If the second GPS
is also a Garmin 430, it will be coupled to the CDI and is also approved
for IFR use. The Garmin GPS 430 is capable of providing IFR enroute,
terminal, and approach navigation with position accuracies better than
15 meters. The system utilizes the Global Positioning System (GPS)
satellite network to derive the airplane’s position (latitude, longitude,
and altitude) and the altitude digitizer to enhance the altitude
calculation. The GPS 1 antenna is located beneath the cabin roof
along the airplane centerline and the GPS 2 antenna is located under
　
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