Garmin 400W-Series Manual de usuario

P/N 11934-S38 1 of 10

Cirrus Design Section 9

SR20 Supplements

Pilots Operating Handbook and

FAA Approved Airplane Flight Manual

Supplement

For

Garmin 400W-Series GPS Navigator

When a Garmin 400W-Series GPS Navigator is installed in the Cirrus

Design SR20, this Supplement is applicable and must be inserted in

the Supplements Section (Section 9) of the Cirrus Design SR20 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 SR20 Pilot's Operating Handbook.

• Note •

This POH Supplement Change, dated Revision 02: 10-29-13,

supersedes and replaces Revision 01 of this POH

Supplement dated 11-11-07.

Revision 02: 10-29-13

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Section 9 Cirrus Design

Supplements SR20

Section 1 - General

The WAAS-enabled, Garmin 400W-Series GPS Navigator is capable

of providing primary navigation information for enroute, terminal, non-

precision, and precision approaches with typical position accuracies of

1 meter horizontally and 2 meters vertically.

The Wide Area Augmentation System (WAAS) consists of ground

reference stations positioned across the United States that monitor

GPS satellite data. Two master stations, located on either coast,

collect data from the reference stations and create a GPS correction

message. This correction accounts for GPS satellite orbit and clock

drift plus signal delays caused by the atmosphere and ionosphere.

The corrected data is then broadcast through geostationary satellites.

WAAS also provides the capability of quickly determining when signals

from a given satellite are wrong and removing that satellite from the

navigation solution using Receiver Autonomous Integrity Monitoring

(RAIM), a technology developed to assess the integrity of GPS

signals.

• Note •

WAAS satellite coverage is only available in North America.

User in other parts of the world can receive WAAS data,

however, the signal has not been corrected and thus does not

improve the accuracy of your receiver.

Models Covered

Two Garmin 400W-Series GPS Navigators are covered in this

publication; the GNC 420W and GNS 430W. Generally, both models

will be referred to as the Navigator, except where there are physical or

operational differences.

• Note •

For detailed descriptions and full operation instructions for the

GNC 420W or GNS 430W Navigators, refer to the Garmin

400W-Series GPS Navigator Pilot's Guide and Reference, P/N

190-00356-00, Revision A or later revision.

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SR20_FM09_1285

SR20_FM09_1109

Figure - 1

GNC 420W and GNS 430W 400W-Series Navigators

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Section 2 – Limitations

1. The Garmin 400W-Series GPS Navigator Pilot's Guide and

Reference, P/N 190-00356-00, Revision A or later must be

immediately available to the pilot during flight. The software status

stated in the pilot's guide must match that displayed on the

equipment.

2. IFR enroute and terminal navigation is prohibited unless the pilot

verifies the currency of the database or verifies each selected

waypoint for accuracy by reference to current approved data.

3. The Garmin 400W-Series GPS Navigator meets RNP5 (BRNAV)

requirements of AC 90-96 and is in accordance with AC 20-138A,

and JAA AMJ 20X2 Leaflet 2 Revision 01, 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.

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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.

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Section 9 Cirrus Design

Supplements SR20

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.

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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,

the NAV receiver is designated NAV 2, and the VHF communications

receiver is designated COM 2.

GPS 2 Navigator and VHF NAV is powered by 28 VDC through the

Avionics Master Switch and the 5-amp GPS 2 circuit breaker on the

Avionics Non-essential Bus. 28 VDC for transceiver operation is

supplied through the Avionics master Switch and the 7.5-amp COM 2

circuit breaker on the Avionics Non-Essential Bus.

The following describes a single GNS 430W unit and its functions.

GPS Navigator

The GNS 430W Navigator is coupled to the airplanes HSI and MFD.

Typically, the second GPS Navigator provides backup and is approved

for VFR use only. If the second GPS is also a GNS 430W, it will be

coupled to the CDI and is also approved for IFR use.

The GPS 1 antenna is located on top of the fuselage slightly aft of the

rear window along the airplane centerline and the GPS 2 antenna is

located on top of the fuselage slightly forward of the rear window along

the airplane centerline. The GNS 430W Navigator is powered by 28

VDC through the 5-amp GPS 1 circuit breaker on the Avionics

Essential Bus.

Navigation (NAV) Receiver

The GNS 430W provides an integrated Navigation (NAV) receiver with

VHF Omnirange/Localizer (VOR/LOC) and Glideslope (G/S) capability.

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.

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Communication (COM) Transceiver

The GNS 430W includes a digitally-tuned integrated VHF

communications (COM) transceiver. The COM 1 antenna is located

above 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 1 circuit

breaker on the Avionics Essential Bus.

Avionics Integration

The GNS 430W Navigator is integrated into the airplane avionics

installation in three configurations:

1. Single GNS 430W (GPS 1) interfaced with the PFD and MFD and

a single Garmin GNC 250XL (GPS 2) interfaced with the PFD and

MFD.

• GPS 1 in this configuration is a GNS 430W Navigator with VHF

COM interfaced with the PFD and MFD as GPS 1/VLOC 1.

Select NAV Source to GPS 1 or VLOC 1 through the PFD’s

NAV select button. With source set to GPS 1 or VLOC 1, it can

be alternately set between GPS or VLOC by the CDI button on

the navigator. The active source is identified on the PFD.

• GPS 2 in this configuration is a GNC 250XL Navigator

interfaced with the PFD and MFD as GPS 2. Select NAV

Source to GPS 2 through the PFD’s NAV select button. The

active source is identified on the PFD.

2. Single GNS 430W (GPS 1) interfaced with the PFD and MFD and

a single GNC 420W (GPS 2) interfaced with the MFD (VOR/LOC)

indicator.

• GPS 1 in this configuration is a GNS 430W Navigator with VHF

COM interfaced with the PFD and MFD as GPS 1/VLOC 1.

Select NAV Source to GPS 1 or VLOC 1 through the PFD’s

NAV select button. With source set to GPS 1 or VLOC 1, it can

be alternately set between GPS or VLOC by the CDI button on

the navigator. The active source is identified on the PFD.

• GPS 2 in this configuration is a GNS 420W Navigator with VHF

COM interfaced with the PFD and MFD as GPS 2. Select NAV

Source to GPS 2 through the PFD’s NAV select button. The

active source is identified on the PFD.

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3. Dual GNS 430W units are installed. GPS 1 in this configuration is

the uppermost GNS 430W unit in the console and GPS 2 is the

lower GNS 430W unit.

• GPS 1 in this configuration is a GNS 430W Navigator with VHF

COM interfaced with the PFD and MFD as GPS 1/VLOC 1.

Select NAV Source to GPS 1 or VLOC 1 through the PFD’s

NAV select button. With source set to GPS 1 or VLOC 1, it can

be alternately set between GPS or VLOC by the CDI button on

the navigator. The active source is identified on the PFD.

• GPS 2 in this configuration is a GNS 430W Navigator with VHF

COM interfaced with the PFD and MFD as GPS 2/VLOC 2.

Select NAV Source to GPS 2 or VLOC 2 through the PFD’s

NAV select button. With source set to GPS 2 or VLOC 2, it can

be alternately set between GPS or VLOC by the CDI button on

the navigator. The active source is identified on the PFD.

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Section 9 Cirrus Design

Supplements SR20

TERRAIN Interface

• Note •

TERRAIN functionality is a standard feature found in GNS

430W units with main software version 5.01 or above and valid

terrain and obstacle databases installed.

Garmin TERRAIN is a terrain awareness system incorporated into

GNS 430W units to increase situational awareness and aid in reducing

controlled flight into terrain. The TERRAIN function displays altitudes

of terrain and obstructions relative to the aircraft’s altitude and are

advisory in nature only. Individual obstructions may be shown if

available in the database, however, not all obstructions may be

available in the database and data may be inaccurate. TERRAIN

information should be used as an aid to visual acquisition and not use

to navigate or maneuver to avoid terrain.

For for a more detailed description of the TERRAIN function, refer to

the Garmin 400W-Series GPS Navigator Pilot's Guide and Reference,

P/N 190-00356-00, Revision A or later revision.

Revision 02: 10-29-13

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