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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 the glareshield. All GPS
navigator controls and functions are accessible through the GNS 430
front control panel located in the center console. The panel includes
function keys, power switches, MSG and Nav status annunciators,
color LCD display, two concentric selector knobs on each panel, and a
Jeppesen NavData card slot in each panel. The GNS 430 navigator is
powered by 28 VDC through the 5-amp GPS1 circuit breaker on the
Avionics Essential Bus.
The Jeppesen Navigation Database provides access to data on
Airports, Approaches, Standard Instrument Departures (SIDs),
Standard Terminal Arrivals (STARs), VORs, NDBs, Intersections,
Minimum Safe Altitudes, Controlled Airspace Advisories and
Revised: May 25, 2005
P/N 13772-103 9 of 10
Cirrus Design Section 9
SR22 Supplements
Frequencies. North American and International databases are
available. Database information is provided on a card that can be
inserted into the card slot on the GPS unit. Subscription information is
provided in a subscription packet provided with each system.
Navigation (Nav) Receiver
The Garmin GNS 430 provides an integrated Navigation (NAV)
receiver with VHF Omnirange/Localizer (VOR/LOC) and Glideslope
(G/S) capability. The VOR/LOC receiver receives on a frequency
range from 108.000 Mhz to 117.950 Mhz with 50 kHz spacing.
Glideslope is received from 329.150 to 335.00 in 150 kHz steps. The
Nav receiver controls are integrated into the Garmin GNS 430 control
mounted in the center console. The receiver control provides active
and standby frequency indication, frequency memory storage, and
knob-operated frequency selection. IDENT audio output for VOR and
LOC is provided to the audio system. The Nav antenna is mounted on
top of the vertical tail. 28 VDC for navigation receiver operation is
controlled through the Avionics Master Switch on the bolster switch
panel and supplied through the 5-amp GPS 1 circuit breaker on the
Avionics Essential Bus. The airplane is equipped with a Garmin GNS
430 integrated GPS Navigator, Navigation (NAV) receiver with VHF
Omnirange/Localizer (VOR/LOC) and Glideslope receiver.
Communication (COM) Transceiver
The GNS 430 includes a digitally-tuned integrated VHF
communications (COM) transceiver. The transceiver and integrated
controls are mounted in the Garmin GNS 430 unit. The transceiver
receives all narrow- and wide-band VHF communication transmissions
transmitted within a frequency range of 118.000 MHz to 136.975 MHz
in 25.0 kHz steps (720 channels). For European operations, the COM
can be operator configured for 8.33 kHz channel spacing (2280
channels). The tuning controls are collocated with the NAV at the left
side of the GNS 430 front panel. Frequency tuning is accomplished by
rotating the large and small concentric knobs to select a standby
frequency and then transferring the frequency to the active window.
The COM frequency display window is at the upper left corner of the
GNS 430 display. Auto-tuning can be accomplished by entering a
frequency from a menu. The COM 1 antenna is located above the
cabin on the airplane centerline. 28 VDC for transceiver operating is
Revised: May 25, 2005
10 of 10 P/N 13772-103
Section 9 Cirrus Design
Supplements SR22
controlled through the Avionics Master Switch and supplied through
the 7.5-amp COM1 circuit breaker on the Avionics Essential Bus.
Revised: May 25, 2005
P/N 13772-104 1 of 8
Cirrus Design Section 9
SR22 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
For
Garmin GNC 420 GPS Navigator
When a GARMIN GNC 420 GPS Navigator with VHF COM is installed
in the Cirrus Design SR22, this Supplement is applicable and must be
inserted in the Supplements Section (Section 9) of the Cirrus Design
SR22 Pilot’s Operating Handbook. This document must be carried in
the airplane at all times. Information in this supplement either adds to,
supersedes, or deletes information in the basic SR22 Pilot’s Operating
Handbook.
• Note •
This POH Supplement Revision dated Revision 1: 05-25-05
supersedes and replaces the original release of this
supplement dated 12-12-00.
Revision 1: 05-25-05
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(109)
