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

requirements of AC 90-96 and is in accordance with AC 20-138,
and JAA AMJ 20X2 Leaflet 2 Revision 1, provided it is receiving
usable navigation information from the GPS receiver.
4. Do not use the TERRAIN Interface for navigation of the aircraft.
The Terrain Display does not provide TAWS capability and is
intended to serve as a situational awareness tool only and does
not provide the accuracy fidelity on which to solely base terrain or
obstacle avoidance maneuvering decisions.
Section 3 - Emergency Procedures
1. If GPS Navigator information is not available or is invalid, utilize
remaining operational navigation equipment as required.
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 13772-132 5 of 10
Cirrus Design Section 9
SR22 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 13772-132
Section 9 Cirrus Design
Supplements SR22
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 13772-132 7 of 10
Cirrus Design Section 9
SR22 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,
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Cirrus Design SR20西銳20飛行員操作手冊和飛機飛行手冊附錄(75)