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2. If a “Loss of Integrity” (INTEG) or RAIM POSITION WARNING
message is displayed during:
a. Enroute/Terminal; continue to navigate using GPS equipment
and periodically cross-check the GPS guidance to other
approved means of navigation.
b. GPS Approach; GPS approaches are not authorized under
INTEG - execute a missed approach or revert to alternate
navigation.
Revision 01: 11-11-07
P/N 11934-S38 5 of 10
Cirrus Design Section 9
SR20 Supplements
Section 4 - Normal Procedures
Refer to the Systems Description Section of this supplement for
integration differences when single and dual units are installed.
Normal operating procedures are outlined in the Garmin 400W-Series
GPS Navigator Pilot's Guide and Reference, P/N 190-00356-00,
Revision A or later.
Activate Navigator
1. Battery Master Switch................................................................ON
2. Avionics Power Switch ...............................................................ON
3. Navigator COM/ Power Switch....................................... Rotate ON
The Navigator will display a welcome page while the self-test is in
progress. When the self test is successfully completed, the
Navigator asks for NavData database confirmation, acquires
position, and then displays the acquired position on the Navigators
display and on the MFD.
• Note •
The Navigator is not coupled to an air and fuel data computer.
Manual fuel-on-board and fuel flow entries must be made in
order to use the fuel planning function of the AUX pages.
The GPS Navigator utilizes altitude information from the
altitude encoders altitude digitizer to enhance altitude
information.
Deactivate Navigator
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.
Revision 01: 11-11-07
6 of 10 P/N 11934-S38
Section 9 Cirrus Design
Supplements SR20
Section 7 - Systems Description
• Note •
This section provides general description and aircraft
integration information for the Garmin GNC 420W and GNS
430W 400W-Series Navigators. For detailed descriptions and
operational instructions, refer to the Garmin 400W-Series
GPS Navigator Pilot's Guide and Reference, P/N 190-00356-
00, Revision A or later revision
GNC 420W
The GNC 420W, designated as the secondary navigator (GPS 2), is a
GPS Navigator and VHF communications transceiver. The GPS
Navigator consists of a GPS receiver, a navigation computer, and a
Jeppeson NavData database all contained in the GNC 420W control
unit mounted in the center console. Additionally, a VHF
communications receiver, designated COM 2, is also integrated into
the unit.
GPS Navigator
The GNC 420W navigator is coupled to the airplane’s CDI. The GPS 2
antenna is located on top of the fuselage slightly aft of the rear window
along the airplane centerline. The navigator is powered by 28 VDC
through the 5-amp GPS2 and 7.5-amp COM 2 circuit breakers on the
Avionics Non-Essential Bus.
Communication (COM) Transceiver
The GNC 420W includes a digitally-tuned integrated VHF
communications (COM) transceiver. The COM 2 antenna is located
below the cabin on the airplane centerline.
28 VDC for transceiver operating is controlled through the Avionics
Master Switch and supplied through the 7.5-amp COM 2 circuit
breaker on the Avionics Non-Essential Bus.
Revision 01: 11-11-07
P/N 11934-S38 7 of 10
Cirrus Design Section 9
SR20 Supplements
GNS 430W
The GNS 430W, designated as the primary navigator (GPS 1),
includes all of the features of the GNC 420W with the addition of IFR
certified VOR/Localizer and Glideslope receivers. In the event a
second GNS 430W 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.
GPS 2 Navigator and VHF NAV is powered by 28 VDC through the
Avionics Master Switch and the 5-amp GPS 2 circuit breaker on the
Avionics Non-essential Bus. 28 VDC for transceiver operation is
supplied through the Avionics master Switch and the 7.5-amp COM 2
circuit breaker on the Avionics Non-Essential Bus.
The following describes a single GNS 430W unit and its functions.
GPS Navigator
The GNS 430W Navigator is coupled to the airplanes HSI and MFD.
Typically, the second GPS Navigator provides backup and is approved
for VFR use only. If the second GPS is also a GNS 430W, it will be
　
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