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Revision A7
P/N 13772-001 7-93
Cirrus Design Section 7
SR22 Airplane Description
1 and 7.5-amp COM 1 circuit breakers on the Avionics Essential Bus.
The secondary GPS navigator is powered by 28 VDC through the 5-
amp GPS 2 and the 7.5-amp COM 2 circuit breaker on the Avionics
Non-Essential Bus.
Communication (COM) Transceivers
Avionics Configuration A, B, and PFD:
Two VHF communications (COM) transceivers are installed to provide
VHF communication. The transceivers and integrated controls are
mounted in the Garmin GNS 430 or GNS 420 units. The transceivers
receive all narrow- and wide-band VHF communication transmissions
transmitted within range of the selected frequency. The antennas pick
up the signals and route the communication signals to the
transceivers, which digitize the audible communication signal. The
digitized audio is then routed to the audio control unit for distribution to
the speakers or headphones.
COM 1 – The upper Garmin GNS 430 is designated COM 1. The
Garmin GNS 430 control panel provides COM 1 transceiver active and
standby frequency indication, frequency memory storage, and knoboperated
frequency selection. The COM 1 transceiver provides either
720-channel (25 kHz spacing) or 2280-channel (8.33 kHz spacing)
operation in a frequency range from 118.000 to 136.975 MHz. The
COM 1 antenna is located above the cabin on the airplane centerline.
28 VDC for COM 1 transceiver operation is controlled through the
Avionics Master Switch on the bolster switch panel and supplied
through the 7.5-amp COM 1 circuit breaker on the Essential Avionics
Bus.
COM 2 – The lower Garmin GNS 420 is designated COM 2. The
Garmin GNS control panel provides COM 2 transceiver active and
standby frequency indication, frequency memory storage, and knoboperated
frequency selection. The COM 2 transceiver provides either
720-channel (25 kHz spacing) or 2280-channel (8.33 kHz spacing)
operation in a frequency range from 118.000 to 136.975 MHz. The
COM 2 antenna is located on the underside of the cabin on the
airplane centerline. 28 VDC for COM 2 transceiver operation is
controlled through the Avionics Master Switch on the bolster switch
panel and supplied through the 7.5-amp COM 2 circuit breaker on the
Non-Essential Avionics Bus.
Revision A7
7-94 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
Navigation (Nav) Receiver
Serials with Avionics Configuration A - 0002 through 1601, 1603
through 1643 and 1645 through 1662 without PFD:
The airplane is equipped with one NAV receiver integrated into the
Garmin GNS 430 GPS Navigators (the GNS 420 does not incorporate
a NAV receiver). Mounted in the upper radio rack slot, this unit is
designated NAV 1. The GNS 430 has VHF Omnirange/Localizer
(VOR/LOC) capability. The VOR/LOC receiver receives VOR/LOC on
a frequency range from 108.000 Mhz to 117.950 Mhz with 50 kHz
spacing. The GNS 430 has glideslope capability. Glideslope is
received from 329.150 to 335.000 in 150 kHz steps. The receivers and
integrated controls are mounted in the Garmin GNS 430 control
display. The receiver controls provide 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, mounted on top of the vertical tail,
provides VOR/LOC input for both Nav receivers.
NAV 1 – The upper GARMIN GNS 430 is designated NAV 1. 28 VDC
for navigation receiver operation is controlled through the Avionics
Master Switch on the bolster switch panel and supplied through the 5-
amp GPS1 circuit breaker on the Avionics Essential Bus row.
Avionics Configuration B and PFD:
The airplane is equipped with two NAV receivers integrated into the
Garmin GNS 430 GPS Navigators. The upper unit is designated NAV
1 and the lower unit is designated NAV 2. The Nav receiver controls
are integrated into the Garmin GNS control mounted in the center
console. Each unit has VHF Omnirange/Localizer (VOR/LOC)
capability. The VOR/LOC receiver receives VOR/LOC on a frequency
range from 108.000 Mhz to 117.950 Mhz with 50 kHz spacing. The
GNS 430 has glideslope capability. Glideslope is received from
329.150 to 335.000 in 150 kHz steps. 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, mounted
on top of the vertical tail, provides VOR/LOC input for both Nav
receivers.
Revision A7
P/N 13772-001 7-95
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CIRRUS DESIGN SR22西锐22飞行员操作手册和飞机飞行手册(88)
