曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

readable and automatically dimmed for low-light operation. The
primary GPS navigator is powered by 28 VDC through the 5-amp GPS
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.
Avionics Configuration B and PFD:
The airplane is equipped with two GPS navigators. Dual Garmin GNS
430s are designated GPS 1 and GPS 2. Both Garmin GPS navigators
are IFR certified. The primary unit, designated GPS 1, is coupled to
the airplane’s HSI or PFD, Autopilot, and MFD. The secondary unit,
designated GPS 2, is coupled to the airplane’s HSI or PFD, and MFD.
The GPS navigators are capable of providing IFR enroute, terminal,
and approach navigation with position accuracies better than 15
meters. Each GPS navigator utilizes the Global Positioning System
(GPS) satellite network to derive the airplane’s position (latitude,
longitude, and altitude) and the altitude encoder to enhance the
altitude calculation.
The GPS1 antenna is located above the headliner along the airplane
centerline. The GPS2 antenna is located below the glareshield and
behind the MFD. All GPS navigator controls and functions are
accessible through the GPS receiver units’ front control panels located
in the center console. The panels include function keys, power
switches, MSG and NAV status annunciators, a color LCD display
(GNS 430), two concentric selector knobs on each panel, and a
Jeppesen NavData card slot in each panel. The displays are daylight
readable and automatically dimmed for low-light operation. The
primary GPS navigator is powered by 28 VDC through the 5-amp GPS
June 2007
Information Manual 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.
June 2007
7-94 Information Manual
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
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(83)