Garmin | GNS 430W | Garmin GNS 430W Rotorcraft STC approvd Flight Manual Supplement

Garmin GNS 430W Rotorcraft STC approvd Flight Manual Supplement
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
Table of Contents
SECTION
PAGE
Section 1. GENERAL
1.1 Garmin 400W Series GPS/WAAS Nav Com
1.2 Operation
1.3 Class II Oceanic, Remote, and other Operations
Section 2. LIMITATIONS
2.1 Pilot’s Guide
2.2 System Software:
2.3 Navigation Database
2.4 Terrain Database
2.5 Navigation
2.6 Approaches
2.7 Autopilot Coupling
2.8 Terrain Display
2.9 VNAV
2.10 Weather Display
2.11 Traffic Display
2.12 Groundspeed Function Limitations
Section 3. EMERGENCY PROCEDURES
3.1 Emergency Procedures
3.2 Abnormal Procedures
Section 4. NORMAL PROCEDURES
4.1 Approaches with Vertical Guidance
4.2 Autopilot Operation
4.3 Coupling the Autopilot during approaches
4.4 Fix-to-Altitude (FA) and Hold-to-Altitude (HA) Leg Types
4.5 External Navigation Indicator(s)
4.6 External Navigation Source Selection or GPS Annunciation
4.7 External Display Interfaces
4.8 WFDE Prediction Program
Section 5. PERFORMANCE
Section 6. WEIGHT AND BALANCE
Section 7. SYSTEM DESCRIPTIONS
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FAA APPROVED
190-00356-23 Rev. 1
Page 3 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
Section 1. GENERAL
1.1 Garmin 400W Series GPS/WAAS Nav Com
The Garmin 400W Series GPS/WAAS Navigator is a panel-mounted
product that contains a GPS/WAAS receiver for GPS approved primary
navigation, under TSO C146a (plus optional VHF Com and VHF Nav
radios) in an integrated unit with a moving map and color display. The 400W
Series unit features a graphical display which may also be used to depict
traffic, weather, or terrain data.
The navigation functions are operated by dedicated keys and graphical
menus which are controlled by the buttons and the dual concentric rotary
knob along the bottom and right side of the display.
Optional VHF Com and VHF Nav radio functions are controlled via
dedicated buttons and knobs on the left side of the display and adjacent to
frequencies they are controlling.
Comm Freq
Flip/Flop
Photocell
for AutoDimming
Com Freq
Window
Nav Freq
Window
Graphic Moving
Map Display and
Navigation Info
Direct-To Key
Range Keys
Power and Com
Volume/Squelch
Clear Key
Data
Cards
Enter Key
Function and
Page Number
Nav Radio
Volume
Nav Radio
Flip/Flop
Large Knob
Com/VLOC
Freq (MHz)
Small Knob
Com/VLOC
Freq (kHz)
Menu Key
Large Knob
Terrain, Flight
Phase, and
GPS Integrity
Annunciator Mounting
Screw
Small Knob
(Cursor - Press
to activate)
CDI
Key
Navigation
Source: GPS,
VLOC, or
GPS-PTK
OBS
Key
Flight Plan
Key
Procedure Key
Message
Key
Figure 1 - 400W Series Control and Display Layout
FAA APPROVED
190-00356-23 Rev. 1
Page 4 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
1.2 Operation
GPS/WAAS TSO-C146a Class 3 Operation: The Garmin 400W Series
unit, when installed in accordance with STC SR02232LA, uses GPS and
WAAS (within the coverage of a Space-Based Augmentation System
complying with ICAO Annex 10) for enroute, terminal area, nonprecision approach operations (including “GPS”, “or GPS”, and “RNAV”
approaches), and approach procedures with vertical guidance (including
“LNAV/VNAV” and “LPV”).
Navigation is accomplished using the WGS-84 (NAD-83) coordinate
reference datum. GPS navigation data is based upon use of only the Global
Positioning System (GPS) operated by the United States of America.
1.3 Class II Oceanic, Remote, and other Operations
The Garmin 400W Series, as installed, has been found to comply with the
requirements for GPS primary means of Class II navigation in oceanic and
remote airspace, when used in conjunction with WAAS Garmin Prediction
Program part number 006-A0154-03. Oceanic operations are supported
when the 400W Series unit annunciates OCN. This provides an alarm limit
of four NMI and a mask angle of five degrees. The 400W series unit also has
the ability to predict RAIM availability at any waypoint in the database or if
WAAS corrections are expected to be absent or disabled. This RFMS does
not constitute an operational approval for Oceanic or Remote area
operations. Additional equipment installations or operational approvals may
be required.
a) Oceanic navigation requires an additional approved long range oceanic
and/or remote area navigation system with independent display, sensors,
antenna, and power source. (It may be a second 400W/500W Series unit.)
b) Redundant VHF Com and VHF Nav systems may be required for other
than U.S. 14 CFR Part 91 operations. Check foreign regulation
requirements as applicable. (It may be a second 400W/500W Series unit.)
c) Operations approval may be granted for the use of the 400W Series unit
RAIM prediction function in lieu of the Prediction Program for operators
requiring this capability. Refer to your appropriate civil aviation
authorities for these authorizations.
FAA APPROVED
190-00356-23 Rev. 1
Page 5 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
Section 2. LIMITATIONS
2.1 Pilot’s Guide
The GARMIN 400W Series Pilot’s Guide, part number and revision listed
below (or later revisions), must be immediately available for the flight crew
whenever navigation is predicated on the use of the 400W Series unit.
y 400W Series Pilot’s Guide & Reference P/N 190-00356-00 Rev C
y 400W/500W Series Optional Displays P/N 190-00356-30 Rev C
y 400W/500W Series Display Interfaces P/N 190-00356-31 Rev C
This RFM supplement does not grant approval for IFR operations to
rotorcraft limited to VFR operations. Additional rotorcraft systems may be
required for IFR operational approval. Systems limited to VFR shall be
placarded in close proximity to the 400W Series unit
“GPS LIMITED TO VFR USE ONLY”.
2.2 System Software:
The system must utilize the Main and GPS software versions listed below (or
later FAA approved versions for this STC). The software versions are
displayed on the self-test page immediately after turn-on for approximately 5
seconds or they can be accessed in the AUX pages.
Subsequent software versions may support different functions. Check the
400W Series Pilot’s Guide for further information.
Table 1 - Approved Software Versions
Approved Software Version
(or later FAA approved versions for this STC)
Software Item
SW version
As displayed on unit
Main SW Version
3.20
3.20
GPS SW Version
3.2
3.2
FAA APPROVED
190-00356-23 Rev. 1
Page 6 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
2.3 Navigation Database
The 400W Series unit database cards must be installed and up to date. The
software automatically precludes invalid databases for use by the 400W.
Database cycle information is displayed at power up on the screen, but more
detailed information is available on the AUX – UTILITY page.
a) 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.
b) GPS instrument approaches using the 400W Series units are prohibited,
unless the 400W Series unit’s approach data is verified by the pilot or
crew to be current. Instrument approaches must be accomplished in
accordance with an approved instrument approach procedure that is
loaded from the 400W Series unit database.
c) Installations with dual 400W/500W Series units will only crossfill
between units when they contain the same database cycle. Updating of
each database must be accomplished on the ground prior to flight.
2.4 Terrain Database
The 400W Series unit supports Terrain and requires a Terrain database card
to be installed in order for the feature to operate. Database cycle information
is displayed at power up on the screen, but more detailed information is
available on the AUX – UTILITY page. Terrain database cards contain the
following data:
a)
The Terrain Database has an area of coverage from North 75° Latitude
to South 60° Latitude in all longitudes.
b) The Airport Terrain Database has an area of coverage that includes the
United States, Canada, Mexico, Latin America, and South America.
c) The Obstacle Database has an area of coverage that includes the United
States, and is updated as frequently as every 56 days.
NOTE: The area of coverage may be modified as additional terrain data
sources become available.
FAA APPROVED
190-00356-23 Rev. 1
Page 7 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
2.5 Navigation
No navigation is authorized north of 89° (degrees) north latitude or south of
89° (degrees) south latitude.
2.6 Approaches
a) GPS approaches are prohibited at groundspeeds of 30 knots or less.
b) During GPS approaches, the pilot must verify the 400W Series unit is
operating in the approach mode. (LNAV, LNAV+V, L/VNAV, or LPV)
c) When conducting approaches referenced to true North, the heading
selection on the AUX pages must be adjusted to TRUE.
d) Accomplishment of an ILS, LOC, LOC-BC, LDA, SDF, MLS, VOR
approach, or any other type of approach not approved for GPS overlay, is
not authorized with GPS navigation guidance.
e) Use of the GNS 430W VOR/LOC/GS receiver to fly approaches not
approved for GPS requires VOR/LOC/GS navigation data to be present
on the external indicator (i.e. proper CDI source selection).
f) For rotorcraft with remote source selection annunciation or remote GPS
navigation annunciations installed, conducting IFR approaches is
prohibited if the remote annunciation is found to be inoperative during
pre-flight. (This limitation does not prohibit the conduct of an IFR
approach if the required remote annunciation fails during flight. The
indications provided on the 400W Series unit display may be used as a
backup).
g) Except in emergency conditions, IFR approaches are prohibited
whenever any physical or visual obstruction restricts pilot view or access
to the 400W Series unit or the affected CDI.
FAA APPROVED
190-00356-23 Rev. 1
Page 8 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
2.7
Autopilot Coupling
Note: This section only applies if the 400W Series unit is coupled to an
autopilot.
IFR installations of a Garmin 400W Series unit allow the operator to fly all
phases of flight based on the navigation information presented to the pilot;
however, not all modes may be coupled to the autopilot. All autopilots may
be coupled in Oceanic (OCN), Enroute (ENR), and Terminal (TERM)
modes; however, the FAA requires that vertical coupling of an autopilot for
approaches be demonstrated to meet their intended function and provide safe
and proper operation to published minimums. This installation is limited to:
No limitations for autopilot coupling.
Lateral GPS coupling (LNAV only). For 430W units: The GS of an
ILS (VLOC) may be coupled to the autopilot without any limitations.
This limitation may be removed after an FAA Flight Test demonstration.
Contact Garmin International, Tech Support for additional information.
2.8 Terrain Display
TERRAIN refers to the display of terrain information and comprises of a 2D picture of the surrounding terrain and obstacles relative to the position and
altitude of the rotorcraft. In addition TERRAIN can provide advanced visual
alerts of predicted dangerous terrain conditions. The TERRAIN alerting
feature is designed for fixed wing aircraft and due to the ability of a
rotorcraft to hover and rotate its direction of travel, it is recommended that
TERRAIN be used in “inhibit mode” to prevent nuisance alerts. This setting
will allow the TERRAIN display to remain active while inhibiting all
TERRAIN messages and alerts.
Pilots are NOT authorized to deviate from their current ATC clearance to
comply with terrain/obstacle alerts. Terrain unit alerts are advisory only and
are not equivalent to warnings provided by TAWS. Navigation must not be
predicated upon the use of the terrain display.
The terrain display is intended to serve as a situational awareness tool only.
By itself, it may not provide either the accuracy or the fidelity on which to
base decisions and plan maneuvers to avoid terrain or obstacles.
FAA APPROVED
190-00356-23 Rev. 1
Page 9 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
2.9 VNAV
VNAV information may be utilized for advisory information only. Use of
VNAV information for Instrument Approach Procedures does not guarantee
Step-Down Fix altitude protection, or arrival at approach minimums in a
normal position to land.
2.10 Weather Display
If an optional weather receiver is interfaced to the 400W Series unit, the
weather information displayed is limited to supplemental use only and may
not be used in lieu of an official weather data source.
2.11 Traffic Display
Traffic may be displayed on the 400W Series unit when connected to an
approved optional TCAS, TAS, or TIS traffic device. These systems are
capable of providing traffic monitoring and alerting to the pilot. Traffic
shown on the display may or may not have traffic alerting available. The
display of traffic is an aid to visual acquisition and may not be utilized for
rotorcraft maneuvering. Display of this traffic data and related operations are
described in the 400W Series unit Pilot’s Guide.
FAA APPROVED
190-00356-23 Rev. 1
Page 10 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
2.12 Groundspeed Function Limitations
Some functions performed by the Garmin 400W Series navigator require
groundspeed to be greater than 30 knots to achieve proper operation. The
following functions are not available when groundspeed is 30 knots or less:
• Traffic advisory warning window (traffic pop-ups)
• Terrain proximity alerts (terrain pop-ups)
• Enroute VNAV
• Turn anticipation
• Estimated time enroute
• Wind direction and speed display
• Holding pattern size and shape adjustment for winds aloft
• Hold entry depiction on moving map
• Curved transition onto Direct To legs
• Curved transitions onto or off of DME arcs
The following function resets each time the groundspeed transitions through
30 knots.
• Departure time and trip timer reset
FAA APPROVED
190-00356-23 Rev. 1
Page 11 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
Section 3. EMERGENCY PROCEDURES
3.1 Emergency Procedures
No change.
3.2 Abnormal Procedures
a) If the Garmin 400W Series unit GPS navigation information is not
available, or is invalid, utilize other remaining operational navigation
equipment installed in the airplane as appropriate. If the 400W Series unit
loses GPS position and reverts to Dead Reckoning mode (indicated by
the annunciation of “DR” in the lower left of the display), the moving
map will continue to be displayed. Rotorcraft position will be based upon
the last valid GPS position and estimated by Dead Reckoning methods.
Changes in airspeed or winds aloft can affect the estimated position
substantially. Dead Reckoning is only available in Enroute mode;
Terminal and Approach modes do not support DR.
b) If a “Loss of Integrity” (INTEG) message is displayed during:
y Enroute/Terminal: continue to navigate using GPS equipment and
periodically cross-check the GPS guidance to other approved
means of navigation.
y GPS Approach: GPS approaches are not authorized under INTEG
- Execute missed approach or revert to alternate navigation.
c) During a GPS LPV precision approach or GPS LNAV/VNAV approach,
the 400W Series unit will downgrade the approach if the Vertical alarm
limits are exceeded. This will cause the vertical guidance to flag as
unavailable. The procedure may be continued using the LNAV only
minimums.
d) During any GPS approach in which precision and non-precision alarm
limits are exceeded, the 400W Series unit will flag the lateral guidance
and generate a system message “ABORT APPROACH loss of
navigation”. Immediately upon viewing the message the unit will revert
to Terminal alarm limits. If the position integrity is within these limits
lateral guidance will be restored and the GPS may be used to execute the
missed approach, otherwise alternate means of navigation should be
utilized.
FAA APPROVED
190-00356-23 Rev. 1
Page 12 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
Section 4. NORMAL PROCEDURES
Refer to the 400W Series unit Pilot’s Guide defined in paragraph 2.1 of this
document for normal operating procedures. This includes all GPS
operations, VHF COM and NAV, and Multi-Function Display information.
For information on TIS traffic, or data linked weather see the Pilot’s Guide
addendum for optional displays. For information on active traffic sensor or
Stormscope operation and displays see the Pilot’s Guide addendum for
display interfaces.
For dual Garmin WAAS Navigator installations where the WAAS
navigators and their corresponding CDIs are installed in a vertical
configuration it is assumed that the top Navigator and CDI are the #1
Garmin WAAS Navigator and #1 CDI/HSI and the lower Navigator and CDI
are the #2 Garmin WAAS Navigator and #2 CDI/HSI. For all other
installations the WAAS navigators and CDIs will be placarded with their
unit number.
Although intuitive and user friendly the 400W Series unit requires a
reasonable degree of familiarity to prevent operations without becoming too
engrossed at the expense of basic instrument flying in IMC and basic seeand-avoid in VMC. Pilot workload will be higher for pilots with limited
familiarity in using the unit in an IFR environment, particularly without the
autopilot engaged. Garmin provides excellent training tools with the Pilot’s
Guide and PC based simulator. Pilots should take full advantage of these
training tools to enhance system familiarization. Use of an autopilot is
strongly encouraged when using the 400W Series unit in IMC conditions
4.1 Approaches with Vertical Guidance
The 400W Series unit supports three types of GPS approaches with vertical
guidance: LPV approaches, LNAV/VNAV (annunciated as L/VNAV)
approaches, and LNAV approaches with advisory vertical guidance
(annunciated as LNAV+V). For LNAV approaches with advisory vertical
guidance, the 400W Series will annunciate LNAV+V indicating vertical
guidance is available. LNAV minimums will be controlling in this case.
FAA APPROVED
190-00356-23 Rev. 1
Page 13 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
NOTE:
If flying an LPV or LNAV/VNAV approach, be prepared to fly
the LNAV only approach prior to reaching the final approach fix
(FAF). If the GPS integrity is not within vertical approach
limits, the system will flag the vertical guidance. This may be
annunciated by a downgrade to LNAV message.
For additional information on approaches with vertical guidance refer to the
400W Series unit Pilot’s Guide.
4.2 Autopilot Operation
The Garmin 400W Series may be coupled to an optional autopilot if installed
in the rotorcraft when operating as prescribed in the LIMITATIONS section
of this manual. For lateral guidance, some installations may utilize GPSS or
GPS Roll Steering in lieu of the analog deviation information. If an HSI is
used with GPSS engaged, the pilot should rotate the course pointer as
prompted on the 400W Series unit to prevent loss of situational awareness
and to prevent the rotorcraft from turning inappropriately if the autopilot is
switched from digital (GPSS) to analog mode. For autopilot operational
instructions, refer to the FAA approved Flight Manual or Flight Manual
Supplement for the autopilot.
The 400W Series unit is coupled to an autopilot.
The 400W Series unit is NOT coupled to an autopilot.
4.3 Coupling the Autopilot during approaches
The Garmin 400W Series supports analog and digital (GPSS) control
interfaces to an optionally installed autopilot. Some autopilots revert to
ROLL mode (wings level) and/or flag a NAV failure if the digital data
becomes unavailable or is inhibited. The CDI selection of VLOC should
inhibit the digital control interface.
NOTE: When switching between GPS and VLOC the pilot should
be aware that the autopilot may need to be re-engaged into
approach or navigation mode after changing the CDI source.
FAA APPROVED
190-00356-23 Rev. 1
Page 14 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
In this installation approach mode for GPS or ILS is selected using the
APR mode on the autopilot.
In this installation approach mode for GPS or ILS is selected using the
ILS mode on the autopilot.
Autopilot coupling to GPS vertical guidance requires that the autopilot be
engaged in an approach mode identical to coupling to an ILS.
To capture the vertical guidance, the pilot may engage the autopilot in
approach mode at any time when the GPS Glide Slope (VDI) becomes
valid.
The autopilot does not support any vertical capture or tracking in this
installation.
NOTE: Autopilots with GPSS may utilize GPSS for LNAV
only approaches.
4.4 Fix-to-Altitude (FA) and Hold-to-Altitude (HA) Leg Types
The Garmin 400W Series supports automatic sequencing of FA and HA leg
types when a valid baro-corrected pressure altitude source is connected to
the Garmin 400W Series unit. If no baro-corrected pressure altitude source is
connected, FA and HA legs must be manually sequenced.
This installation includes a baro-corrected pressure altitude source to the
Garmin 400W unit. When flying FA and HA leg types, the leg
sequences automatically when the required altitude is reached.
This installation does NOT include a baro-corrected pressure altitude
source to the Garmin 400W unit. When flying FA and HA leg types,
“SUSP” appears over the OBS key. When the required altitude is
reached the pilot must press the OBS key to return to automatic leg
sequencing.
FAA APPROVED
190-00356-23 Rev. 1
Page 15 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
4.5 External Navigation Indicator(s)
The Garmin 400W Series unit installation may include external navigation
indicators, such as CDI/HSI or RMI indicators interfaced to the Garmin
400W Series unit.
This installation includes external CDI/HSI or RMI indicator(s)
interfaced to the Garmin 400W Series unit as described below.
External
Navigation
Indicator
 #1 CDI/HSI :
 #2 CDI/HSI :
Needle
#1 :
 RMI
Needle
#2 :
Data Displayed
 GPS+VLOC
(CDI Switched)
 GPS+VLOC
(CDI Switched)
 GPS+VOR
Bearing
(Switched)
 GPS+VOR
Bearing
(Switched)
 GPS Only
 VLOC
 GPS Only
 VLOC
 GPS
Bearing Only
 VOR
Bearing Only
 GPS
Bearing Only
 VOR
Bearing Only
Only
Only
This installation does NOT include any external CDI/HSI or RMI
indicator interfaced to the Garmin 400W Series unit.
FAA APPROVED
190-00356-23 Rev. 1
Page 16 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
4.6 External Navigation Source Selection or GPS Annunciation
Some installations of the Garmin 400W Series unit include External
Navigation Source Selection Annunciation and GPS Annunciation
supplemental to the display built into the 400W Series Unit. When installed;
the external navigation source annunciations are GPS and VLOC which
indicate the navigation information being displayed on the CDI or HSI. The
external GPS annunciations are: WPT, TERM, APR, MSG, and INTEG.
This installation includes external GPS/VLOC navigation source
annunciation.
This installation includes external GPS annunciations
This installation does NOT include any external navigation source
selection or GPS annunciators from the Garmin 400W Series unit.
4.7 External Display Interfaces
Some installations of the Garmin 400W Series unit may include external
interfaces for display of Traffic, Weather Datalink, or Stormscope
information on the 400W Series unit. This Garmin 400W Series unit
installation includes the following external interfaces.
Traffic
Weather Datalink
Stormscope
FAA APPROVED
190-00356-23 Rev. 1
Page 17 of 18
DATE: April 22, 2009
GARMIN Ltd. or its subsidiaries
c/o Garmin International
1200 E. 151st Street, Olathe, KS 66062 USA
ROTORCRAFT FLIGHT MANUAL SUPPLEMENT
or SUPPLEMENTAL ROTORCRAFT FLIGHT MANUAL
for a Garmin 400W Series Navigation System
4.8 WFDE Prediction Program
The Garmin WAAS Fault Detection and Exclusion (WFDE) Prediction
Program is required for Remote/Oceanic operations. The Prediction
Program should be used in conjunction with the Garmin 400W/500W
Simulator. After entering the intended route of flight in the Simulator flight
plan the pilot selects the FDE Prediction Program under the Options menu of
the Simulator program.
For detailed information refer to the WFDE prediction program instructions
(190-00643-01). The availability of FDE is only required for Oceanic or
Remote operations.
Section 5. PERFORMANCE
No change.
Section 6. WEIGHT AND BALANCE
See current weight and balance data.
Section 7. SYSTEM DESCRIPTIONS
See Garmin 400W Series unit Pilot’s Guide for a complete description of the
400W Series unit.
FAA APPROVED
190-00356-23 Rev. 1
Page 18 of 18
DATE: April 22, 2009
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