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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 Garmin GNC 250XL (lower unit) is designated COM 2.
The Garmin GNC 250XL control panel provides COM 2 transceiver
active and standby frequency indication, frequency memory storage,
and knob-operated frequency selection. The COM 2 transceiver
provides 760-channel (25 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. 14 VDC for COM 2
transceiver operation is controlled through the Avionics Master Switch
on the bolster switch panel and supplied through the 28 to 14 VDC
voltage converter from the 7.5-amp COM 2 circuit breaker on the Non-
Essential Avionics Bus.
March 2010
7-74 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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 VOR/LOC on a
frequency range from 108.000 Mhz to 117.950 Mhz with 50 kHz
spacing. Glideslope is received from 329.150 to 335.000 in 150 kHz
steps. The Nav receiver controls are integrated into the Garmin GPS
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 GPS1 circuit
breaker on the Avionics Non-Essential Bus.
Transponder
The airplane is equipped with a single Garmin GTX 320 or GTX 327
ATC Mode C (identification and altitude) transponder with squawk
capability. The transponder system consists of the integrated receiver/
transmitter control unit, an antenna, and an altitude digitizer. The
receiver/transmitter receives interrogations from a ground-based
secondary radar transmitter and then transmits to the interrogating Air
Traffic Control Center. Digitized altitude information is provided by a
altitude digitizer (encoder) plumbed into the airplane static system.
The transponder and integrated controls are mounted in the center
console. The transponder control provides active code display, code
selection, IDENT button, and test functions. The display is daylight
readable and dimming is operator controlled through the INST lights
control on the instrument panel bolster. The transponder antenna is
mounted on the underside of the fuselage just aft of the firewall. 28
VDC for transponder operation is controlled through the Avionics
Master Switch on the bolster switch panel. 28 VDC for receiver,
transmitter, and altitude encoder operation is supplied through the 2-
amp ENCODER/TRANSPONDER circuit breaker on the Avionics
Essential Bus.
March 2010
Information Manual 7-75
Cirrus Design Section 7
SR20 Airplane Description
Audio System
The Garmin GMA 340 audio control unit, located in the center console,
provides audio amplification, audio selection, marker beacon control,
and a voice activated intercom system for the cabin speaker,
headsets, and microphones. The system allows audio switching for up
to three transceivers (COM 1, COM 2, and COM 3) and five receivers
(NAV 1, NAV2, ADF, DME, and MKR). In addition, there are two unswitched
audio inputs for telephone ringer and altitude warning.
Additional inputs are provided for two individual personal
entertainment devices. Push buttons select the receiver audio source
provided to the headphones. A fail-safe mode connects the pilot
headphone and microphone to COM 1 if power is removed or if the Mic
Selector switch is turned to the OFF position.
Headset/Microphone Installation
The airplane is equipped with provisions for four noise-canceling
headsets with integrated microphones. The forward microphone
headsets use remote Push-To-Talk (PTT) switches located on the top
of the associated control yoke grip. The rear headsets do not have
COM transmit capabilities and do not require PTT switches. The
microphone (MIC), headset, and automatic noise reduction (ANR)
power jacks for the pilot and front seat passenger are located in the
map case and similar jacks for the aft passengers are located on the
aft portion of the center console. Audio to all four headsets is
controlled by the individual audio selector switches on the audio
　
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本文鏈接地址：西銳20飛機信息手冊 SR22 AIRPLANE INFORMATION MANUAL 1148-126(75)