Garmin | GNS 430W | Garmin GNS 430W 400W Series Instructions for Continued Airworthiness Bell 206B

Garmin GNS 430W 400W Series Instructions for Continued Airworthiness Bell 206B
400W Series
Instructions for Continued Airworthiness
Bell 206B
Reg. No.____________
S/N_______________
Dwg. Number:
190-01226-04 Rev. 5
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
Description of Change
1
2
07/16/10
08/11/10
3
4
5
04/09/15
06/18/15
02/08/17
Initial Release
Updated ref. doc. revisions in section 2.1, revised part number and weight
of item 2 in table 2.2.1.
Add information for remote HTAWS annunciators.
Updated Airworthiness Limitations section
Updated troubleshooting table section to add GDL 88H and GTX 3X5
Company Proprietary Information
This drawing and the specifications contained herein are the property of Garmin International or its
subsidiaries and may not be reproduced or used in whole or in part as the basis for manufacture or sale
of products without written permission.
Copyright  2010-2017 Garmin Ltd. or its subsidiaries. All rights reserved.
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 U.S.A.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 2 of 23
1. INTRODUCTION................................................................................................................... 4
1.1 Purpose................................................................................................................. 4
1.2 Scope .................................................................................................................... 4
1.3 Document Control ................................................................................................. 4
1.4 Permission to Use Certain Documents ................................................................. 4
1.5 Definitions ............................................................................................................. 4
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 5
2.1 Introduction ........................................................................................................... 5
2.2 Description of Alteration........................................................................................ 6
2.3 Control, Operating Information ............................................................................. 8
2.4 Servicing Information ............................................................................................ 8
2.5 Periodic Maintenance Instructions ........................................................................ 8
2.6 Troubleshooting Information ................................................................................. 11
2.7 Removal and Installation Information ................................................................... 20
2.8 Diagrams............................................................................................................... 21
2.9 Special Inspection Requirements ......................................................................... 22
2.10 Application of Protective Treatments .................................................................... 22
2.11 Data Relative to Structural Fasteners ................................................................... 22
2.12 Special Tools ........................................................................................................ 22
2.13 Additional Instructions........................................................................................... 22
2.14 Overhaul Period .................................................................................................... 22
2.15 ICA Revision and Distribution ............................................................................... 23
2.16 Assistance............................................................................................................. 23
2.17 Implementation and Record Keeping ................................................................... 23
3. AIRWORTHINESS LIMITATIONS ........................................................................................ 23
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 3 of 23
1. INTRODUCTION
1.1 Purpose
This document is designed for use by the installing agency of the Garmin Model 400W series
GPS/WAAS Nav/Com as Instructions for Continued Airworthiness in response to Title 14 CFR Part
27.1529, Part 27 Appendix A. This ICA includes information required by the operator to adequately
maintain the Garmin 400W unit and additional equipment installed under STC SR02080SE.
1.2 Scope
This document identifies the Instruction for Continued Airworthiness for the Bell 206B series rotorcraft,
modified by the installation of the Garmin Models 400W series GPS/WAAS Nav/Com unit and additional
equipment under STC SR02080SE.
1.3 Document Control
This document shall be released, archived, and controlled in accordance with the Garmin document
control system. When this document is revised, refer to Section 2.15 for information on how to gain FAA
acceptance or approval and how to notify customers of changes.
1.4 Permission to Use Certain Documents
Permission is granted to any corporation or person applying for approval of a Garmin Model 400W series
to use and reference appropriate STC documents to accomplish the Instructions for Continued
Airworthiness and show compliance with STC engineering data. This permission does not construe
suitability of the documents. It is the responsibility of the applicant to determine the suitability of the
documents for the ICA.
1.5 Definitions
The following terminology is used within this document:
1)
2)
3)
4)
5)
6)
7)
ACO: Aircraft Certification Office
AEG: Aircraft Evaluation Group
CFR: Code of Federal Regulations
FAA: Federal Aviation Administration
ICA: Instructions for Continued Airworthiness
PMI: Principle Maintenance Inspector
STC: Supplemental Type Certificate
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 4 of 23
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
2.1 Introduction
Content, Scope, Purpose and Arrangement:
This document identifies the Instructions for
Continued Airworthiness for the modification of the
rotorcraft by installation of a 400W series
GPS/WAAS Nav/Com unit under the Garmin Bell
400W/500W HTAWS STC SR02080SE.
Applicability:
Applies to Bell models 206B rotorcraft altered by
installation of a 400W series GPS/WAAS Nav/Com
unit under the Garmin Bell 400W/500W HTAWS
STC SR02080SE.
Definition of Abbreviations:
See Section 1.5
Precautions:
None
Units of measurement:
None
Referenced publications:
Garmin 005-00610-03 Rev. 2 “Equipment List
400W/500W Series Installation Bell 206B STC” or
later FAA Approved Revisions
Garmin 190-01226-02 Rev. 3 “400W Series
Rotorcraft STC Installation Manual” or later FAA
Approved Revisions
Additional Maintenance Data:
Garmin 190-01226-07 Rev. 4 “400W/500W Series
Installation Bell 206B” or later FAA Approved
Revisions
Retention:
This document, or the information contained within,
will be included in the rotorcraft’s permanent
records.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 5 of 23
2.2 Description of Alteration
This STC upgrades existing avionics for the Bell 206B rotorcraft as summarized below.
The Garmin Model 400W Series GPS/WAAS Nav/Com unit is a 6 ¼ inch wide unit mounted in the center
pedestal of the Bell 206B. The 400W Series units combine a large number of easily accessible controls
to use the color multi-function display, Nav and Com transceiver, GPS/WAAS navigator in a single unit.
A GPS/WAAS antenna is installed on the top of the Bell 206B forward engine cowl. A monitored avionics
cooling fan is installed in the center pedestal with a fan fail fault annunciation located in the existing Bell
206B annunciator panel.
Installation of optional remote HTAWS annunciators, and optional cyclic stick switches for remote control
of COM and HTAWS functions are also covered under this STC.
The 400W Series unit can interface to the Garmin G500H system GDU 620 PFD/MFD for display of
navigation information and HTAWS annunciation.
Rotorcraft modified under this STC are restricted to VFR only, including rotorcraft that may not have
previously been restricted to VFR. To clarify this operation limitation, a placard with the text,
“APPROVED FOR DAY/NIGHT VFR” is required to be in the pilot’s view.
The installed equipment is connected to an avionics bus that receives power as soon as the battery and
avionics master switches are turned on. Circuit breakers are installed on an overhead circuit breaker
panel as shown below. Note: dual navigator system installation as shown.
The installed 400W Series equipment can be accessed as described below:
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 6 of 23
LRU Access: Bell models 206B
1. GA 35/36/37 ANTENNA: FS80.0 remove by extracting the four mounting screws in the body of
the antenna. Note: location may vary slightly depending whether or not a dual navigator system is
installed.
2. OVERHEAD CIRCUIT BREAKER PANEL: FS61.0, WL 71.0 Access or remove by extracting the
mounting screws along the side of the circuit breaker panel.
3. CYCLIC CONTROL GRIPS: remove by extracting mounting screw at bottom of grip.
4. COOLING FAN: FS28.5 Access by removing copilot side (LH) cover plate. Remove by extracting
three mounting screws and disconnecting connector.
5. 400W SERIES UNIT: FS39.7 Access or remove by using a 3/32 allen head screwdriver to loosen
the locking mechanism through the access hole on the front of the unit. Note: location may vary
slightly depending whether or not a dual navigator system is installed.
2.2.1 Weight and Balance Information
Moment ARM [IN]
WEIGHT
ITEM DESCRIPTION
PART NUMBER [LB] LONGITUDINAL LATERAL
4.0
GPS 400W (Unit Only)
011‐01057‐XX
5.0
GPS 400W (Installed with rack and back plate)
4.5
GNC 420W (Unit Only)
011‐01058‐XX
5.5
GNC 420W (Installed with rack and back plate)
4.5
GNC 420AW (Unit Only)
011‐01059‐XX
GNC 420AW (Installed with rack and back
41.97
0.0
1
5.5
plate)
5.1
GNS 430W (Unit Only)
011‐01060‐XX
6.2
GNS 430W (Installed with rack and back plate)
5.1
GNS 430AW (Unit Only)
011‐01061‐XX
GNS 430AW (Installed with rack and back
6.2
plate)
2 GCF 3XX 3‐Port Cooling Fan (Unit Only)
013‐00103‐00 0.70
31.22
3.59
GA 35 GPS/WAAS Antenna (Unit Only)
013‐00235‐00 0.47
73.50/78.50
0.0/±5.0
3 GA 36 GPS/WAAS Antenna (Unit Only)
013‐00244‐00 0.47
(Single/Dual (Single/ Dual
Installation)
Installation)
GA 37 GPS/WAAS + XM Antenna (Unit Only)
013‐00245‐00 0.50
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 7 of 23
[1] A rotorcraft weight and balance is required after installation of the 400W Series Unit. Refer to the
400W Rotorcraft STC Installation Manual listed in paragraph 2.1 of this document, for additional
information, including overall size and center of gravity location of all LRUs.
[2] The longitudinal arm is measured in terms of the fuselage station (FS) number.
[3] The lateral arm is measured in terms of the butt line (BL). The centerline of the helicopter is BL0.00.
The moment arms to the left side (looking forward) are negative (-) and the moment arms to the right
side are positive (+).
[4] Location of the 400W Series unit and GPS antenna may vary slightly depending whether or not a
dual navigator system is installed.
2.3 Control, Operating Information
See the Pilot’s Guides or the 400W Rotorcraft STC Installation Manual for system operation and self-test
information. The 400W Rotorcraft STC Installation Manual is listed under the reference documentation in
paragraph 2.1 of this document, and the Pilot’s Guides are listed in the related documents section of the
400W Rotorcraft STC Installation Manual.
2.4 Servicing Information
None. In the event of system failure, troubleshoot the 400W Series unit in accordance with Section 2.6.
2.5 Periodic Maintenance Instructions
The 400W Series units are designed to detect internal failure. A thorough self-test is executed
automatically upon application of power to the units, and built-in test is continuously executed. Detected
errors are indicated on the equipment via failure annunciations.
Maintenance of the components installed by this STC is on condition, except as noted in the following
table.
Table 1 Periodic Maintenance Inspections
Item
Interval
Description/Procedure
Conduct a visual inspection (look for signs of wear, deterioration,
or damage to wires, backshells, or connectors) of the 400W
Series unit and wiring harnesses to ensure installation integrity:
400W Series
Unit
400W Series
Mounting Rack
12 Months
12 Months
1. Inspect the unit for security of attachment.
2. Inspect all knobs and buttons for legibility.
3. Inspect condition of wiring, routing and
attachment/clamping.
4. Inspect related antennas for proper sealing and attachment.
5. Inspect integrity of shield terminations.
6. Inspect for signs of corrosion on equipment, racks and it’s
backplates and rack mounting.
Inspect the mounting rack for any signs of excessive wear,
corrosion, or damage. Check mounting rack corners for cracks.
Check integrity of connector plate attachment to the back of
mounting rack. Check the tightness of fasteners attaching
mounting rack to rotorcraft structure and re-torque 12 to 15 in-lbs
if required.
Replace unit mounting rack if any damage has been found.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 8 of 23
Item
Avionics
Cooling Fan
Interval
Description/Procedure
12 Months
Conduct a visual inspection (look for signs of wear, deterioration,
or damage to wire harness and connector) of the cooling fan to
ensure installation integrity. Inspect for signs of corrosion on
equipment and mounting brackets.
Perform an electrical bonding test:
400W Series
Mounting Rack
Every 2000
flight hours or
ten (10)
years,
whichever is
first
1. Remove 400W Series unit from mounting rack
2. Measure the resistance between the mounting rack and a
nearby exposed portion of aircraft metallic structure and
verify it is less than 10 milliohms.
In the event of a bonding test failure, remove the rack and verify
that the countersunk areas around the holes that are used to
attach the rack are free of corrosion or other debris. Clean
countersunk areas using an approved solvent per Bell
specification BHT-ELEC-SPM CHP8. Reattach the rack and reverify the resistance between the mounting rack and nearby
exposed portion of aircraft metallic structure and ensure that the
resistance is less than or equal to 2.5 milliohms.
Reinstall the 400W Series unit in the mounting rack
Perform an electrical bonding test on antennas installed by this
STC:
GPS Antennas
(Only if antenna
is installed by
this STC)
Every 2000
flight hours or
ten (10)
years,
whichever is
first
1. Disconnect coaxial cable(s) from the antenna connector(s).
2. Measure the resistance between the antenna connector and
a nearby exposed portion of the antenna foil ground plane.
3. Verify the resistance is equal to or less than 10 milliohms.
4. Reconnect the coaxial cable(s) to the antenna connector(s)
and ensure it is secured.
In the event of bonding test failure, remove antenna, and clean
and prepare the hardware mating surfaces as follows:
Clean countersunk areas of the antenna. Clean countersunk
areas using an approved solvent per Bell Specification BHTELEC-SPM, CHP 8.
Reinstall using unit replacement procedures contained in the
installation drawing listed in paragraph 2.1 of this document. Any
reworked antenna installation shall have a resistance of less than
or equal to 2.5 milliohms.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 9 of 23
Item
Interval
Description/Procedure
Perform an electrical bonding test:
1. Measure the resistance between the metallic body of each
Vivisun annunciator and the console assembly and verify
that the resistance is less than or equal to 20 milliohms.
HTAWS
Annunciators (if
installed)
Every 2000
flight hours or
ten (10)
years,
whichever is
first
In the event of bonding test failure:
1. Inspect the grounding strap which is installed between the
annunciator panel and the instrument panel. Ensure that the
fastener hardware is secure and that the strap is not
damaged. If damaged, replace the bonding strap.
2. If problem persists, remove the bonding strap and clean the
mating surfaces of the bonding strap and
annunciator/instrument panel per Bell specification BHTELEC-SPM CHP8.
3. Reinstall the bonding strap and verify that the resistance
between the annunciators and the console assembly after
prepping bonding surface is less than 10 milliohms.
2.5.1 Cleaning the Front Panel
The front bezel, keypad, and display can be cleaned with a soft cotton cloth dampened with clean water.
DO NOT use any chemical-cleaning agents. Care should be taken to avoid scratching the surface of the
display.
2.5.2 Display Backlight
The display backlight lamp is rated by the manufacturer as having a usable life of 20,000 hours. This life
may be more or less than the rated time depending on the operating conditions of the 400W Series unit.
Over time, the backlight lamp may dim and the display may not perform as well in direct sunlight
conditions. The user must determine by observation when the display brightness is not adequate.
Contact the Garmin factory repair station when the backlight lamp requires service.
2.5.3 Battery Replacement
The 400W series has an internal keep-alive battery that will last about 10 years. The battery is used for
GPS system information. Regular planned replacement is not necessary. The 400W series will display a
‘low battery’ message when replacement is required. Once the low battery message is displayed, the
battery should be replaced within 1 to 2 months.
If the battery is not replaced and becomes totally discharged, the 400W Series unit will remain fully
operational, but the GPS signal acquisition time may be increased. This acquisition time can be reduced
by entering a new seed position each time the unit is powered on. There is no loss of function or
accuracy of the 400W Series unit with a dead battery.
The battery must be replaced by the Garmin factory repair station or factory authorized repair station.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 10 of 23
2.6 Troubleshooting Information
If error indications are displayed on the 400W series unit, consult the Troubleshooting section contained
below:
Table 2 Troubleshooting Guide
Problem
Possible Cause
Solution
The 400W Series
unit does not power
on.
 The unit is not getting power to 
the main connector P4001.
Make sure power is connected to the
main 78-pin connector P4001, pins
19 and 20 and ground to P4001, pins
77 and 78. Check circuit breakers
and main avionics switch.
The 400W Series
unit does not
compute a position.
 Not receiving signals.

Check the GPS antenna connections.
Make sure the aircraft is clear of
hangars, buildings, trees, etc.

Wait 20 minutes for unit to complete
cycle.

Turn all avionics off, then turn on
each piece one at a time to isolate
the source of the interference. Route
GPS cable and locate GPS antenna
away from sources of interference.
GPS signal levels
drop when avionics
are turned on.
 Noise interference from other
avionics.
The GPS signal
levels are very low.
 Improper antenna installation or 
coax routing.
Check GPS antenna installation,
connections, and cable routing. The
GPS antenna must be mounted on
the top of the aircraft.
 Antenna shaded from satellites. 
Make sure the aircraft is clear of
hangars, buildings, trees, etc.
 RF interference at 1575.42
MHz from VHF COM.

Move GPS antenna further from the
COM antenna. Add a 1575.42 MHz
notch filter in COM coax. Fix or
replace the COM. Disconnect the
ELT antenna coax to check for
possible re-radiation.
 The PTT input is not being
pulled low.

Check that the PTT (mic key) input is
pulled low for transmit.
The 400W Series
unit does not
transmit.
 No transmit power to the COM. 
Make sure power input is connected
to the COM 25-pin connector P4002
11 and 12 and ground to P4002 21
and 22.
 The input voltage is too low.

Increase input supply voltage to
>12VDC. (>24VDC for 430AW
models)
The sidetone level is  Wrong type of headsets, or
too low or too high.
level needs adjustment.

OBS Resolver won’t  Incompatible resolver or
calibrate.
improper connection.

If necessary, adjust the sidetone
level. Sidetone adjustment is found
on the COM Setup page.
Check the resolver specifications and
wiring.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 11 of 23
Problem
Possible Cause
Solution
OBS indication on
400W Series unit
does not agree with
OBS setting.
 400W Series unit resolver input 
not calibrated correctly.
400W Series unit is
not receiving
heading from
compass system
(ARINC 429
heading input used)
 ARINC 429 input port speed
not correct

Check ARINC 429 input port speed
setting for port that device is
connected to and verify that the
speed is correct for that device.
 Wiring connections are
incorrect.

Check wiring.

Check the OBI source selection on
the Main CDI/OBS Config page.
 Wiring connections are
incorrect.

Check wiring.
 Incorrect configuration.

Check the DME Channel Mode on
the VOR/LOC/GS CDI page.
 Wiring connections are
incorrect.

Check wiring.
 Resolver has not been
calibrated.
RMI pointer does
 Desired RMI source has not
not indicate correctly
been selected.
Tuning data not
updating DME
ARINC 429 device
 400W Series unit ARINC 429

is not receiving data
output not configured correctly.
from the
 ARINC 429 input port speed

400W/420W/430W.
not correct
RS-232 device is
not communicating
with the
400W/420W/430W.
Fan Fail
Annunciation.
Check wiring and calibration.
 Wiring connections are
incorrect.
 400W Series unit RS-232 port
not configured correctly.
 Improper setup on the remote
device.
 Device not compatible, or
improper connection.
 Multiple TX lines connected
together.
 Wiring connections are
incorrect.
 Wiring connections are
incorrect.
 Fan has failed.
400W Series
Instructions for Continued Airworthiness Bell 206B
Check ARINC 429 output port setting
for port that device is connected to.
Check ARINC 429 input port speed
setting for port that device is
connected to and verify that the
speed is correct for that device.

Check wiring.


Check RS-232 port setting for port
that device is connected to.
Verify the configuration of the other
device.
Verify 400W Series unit RX is
connected to remote device TX and
400W Series unit TX is connected to
remote device Rx.
Verify that there is only one TX
source per RX port.
Check wiring.

Check wiring.

Replace fan.



190-01226-04 Rev. 5
Page 12 of 23
2.6.1 400W Series Alerts
The 400W Series will display a number of alerts. These are listed in Table 3 below.
Table 3. 400W Series Alert Troubleshooting Guide
Alert Text
Possible Cause
ADS-B traffic has failed
 The ADS-B traffic system may have
lost GPS position or detected an
internal fault.
ADS-B transmit has failed
 ADS-B unit is not able to transmit a
message due to a failure with the
ADS-B system or antenna(s).
ADS-B is not transmitting
position
ADS-B fault - Check ADS-B
Status Page
 The ADS-B unit has detected a
position input fault.
 An equipment fault has been
detected.
 The GNS is configured for a traffic
device but is not receiving data from
it. Traffic will not be displayed on the
GNS.
 The ADS-B traffic system is reporting
ADS-B Traffic Alerting not
that the CSA application has failed.
available
Traffic alerting on ADS-B traffic is
unavailable.
 The 400W Series unit has detected a
Airport terrain database
problem with a database on the
integrity error
Terrain data card. The message
“<database name> database integrity
error” indicates the data base in error.
 The 400W-series unit has detected a
Audio database error out of
problem with the built-in HTAWS
date or missing
Audio Data-base. HTAWS audio
alerts are not available.
 The 400W Series unit has detected a
Aviation database integrity
problem with a database on the
error
NavData® card. The message
“<database name> database integrity
error” indicates the data base in error.
 The 400W Series unit has detected a
Basemap database integrity
failure in the built-in basemap (land
error
data) database. Land data does not
appear on the Map Page. Other unit
functions continue to work normally.
 System integrity testing has
Boot block verify failed determined that the boot block has
Return unit for repair
become corrupted.
ADS-B - Connection has
been lost
400W Series
Instructions for Continued Airworthiness Bell 206B
Solution
 Check the applicable ADS-B
traffic source status page in Aux
mode
 Contact Garmin technical
support.
 Check system and antenna
wiring. If problem persists
contact Garmin technical
support.
 Verify GPS position source is
functional. If problem persists
contact Garmin technical
support.
 Contact Garmin technical
support.
 Verify traffic system is
configured correctly. If problem
persists contact Garmin
technical support.
 Ensure the aircraft has a clear
view of the sky. If problem
persists contact Garmin
technical support.
 The data is not usable, try
reloading the information onto
the card. If that does not solve
the problem replace the card.
 Contact Garmin technical
support.
 The data is not usable, try
reloading the information onto
the card. If that does not solve
the problem replace the card.
 Reload the Basemap database
 Contact Garmin technical
support.
190-01226-04 Rev. 5
Page 13 of 23
Alert Text
Possible Cause
 The CDI key is stuck in the enabled
(or “pressed”) state. Try pressing the
CDI key again to cycle its operation.
 “Ignore CDI key” has been selected
CDI key disabled
on the MAIN CDI/OBS CONFIG
page.
 The 400W Series unit has detected
Check unit cooling
excessive display backlighting
temperature. The backlighting has
been automatically dimmed to reduce
the temperature.
 The unit has detected a failure in its
COM has failed (420W and
communications transceiver.
430W only)
CDI key stuck
COM is not responding
(420W and 430W only)
 Internal system-to-system
communication between the main
processor and the COM transceiver
has failed. Operational status of the
COM transceiver is unknown.
 The unit has detected a failure in its
communications transceiver. The
COM transceiver may still be usable.
 The external push-to-talk (PTT) switch
COM push-to-talk key stuck
is stuck in the enabled (or “pressed”)
(420W and 430W only)
state.
 Wiring is incorrect.
 The remote COM transfer switch is
COM remote transfer key is
stuck in the enabled (or “pressed”)
stuck (420W and 430W
state.
only)
COM needs service
(420W and 430W only)
Solution
 Contact Garmin technical
support.
 Go to the MAIN CDI/OBS
CONFIG page and deselect
“Ignore CDI key”
 Check for adequate ventilation
or check cooling airflow. Refer
to Section 2.7 of the Installation
Manual.
 Contact Garmin technical
support.
 Contact Garmin technical
support. If the COM board is
still working, it will automatically
tune to 121.500 MHz. Transmit
and receive functions may still
operate regardless of the
displayed frequency.
 Contact Garmin technical
support
 Try pressing the PTT switch
again to cycle its operation.
 Check Wiring
 Try pressing the switch again to
cycle its operation.
 Verify the wiring is correct.
 If the message persists, contact
Garmin technical support.
COM transfer key stuck
(420W and 430W only)
COM transmitter power has
been reduced (420W and
430W only)
Configuration error - Config
service req’d
 The COM flip-flop key is stuck in the
enabled (or “pressed”) state.
 Try pressing the switch again to
cycle its operation.
 If the message persists, contact
Garmin technical support.
 The unit has detected excessive unit  Check for adequate ventilation
or check cooling airflow. Refer
temperature. The COM transceiver
to Section 2.7 of the Installation
transmit power has been
Manual.
automatically reduced to compensate
for the condition.
 Insufficient voltage level
 Check the input voltage
 The configuration information has
been lost or corrupted.
400W Series
Instructions for Continued Airworthiness Bell 206B
 Reconfigure the unit
190-01226-04 Rev. 5
Page 14 of 23
Alert Text
Data transfer cancelled
(crossfill is busy)
Data transfer cancelled
(data invalid)
Data transfer cancelled
(version mismatch)
Data transfer error, please
re-transmit
Display backlight failure
Do not use for navigation
G/S has failed
(420W and 430W only)
G/S is not responding
(420W and 430W only)
G/S needs service
(420W and 430W only)
GDL 69 is not responding
Possible Cause
 An attempt to transfer flight plan data  The host unit is busy. Wait until
any previous crossfill operation
during a unit-to-unit crossfill was
is complete, before reattempting
cancelled.
the transfer.
 Select a user waypoint and re An attempt to transfer a single user
attempt the transfer.
waypoint during a unit-to-unit crossfill
was cancelled. No waypoint was
specified on the Crossfill Page.
 If necessary, update the
 An attempt to transfer data during a
database(s) so they match.
unit-to-unit crossfill was cancelled.
The database versions of the two
400W-series unit are not identical.
 An error was detected during unit-to-  The data transfer should be reattempted.
unit crossfill of user data (user
waypoints and/or flight plans).
 The 400W Series unit has detected a  Contact Garmin technical
support.
failure in the display backlighting.
 Check that the DEMO MODE
 The 400W Series unit is in Demo
Mode and must not be used for actual SELECT pin, P5001 Pin 75, is
not connected.
navigation.
 Contact Garmin technical
 The unit has detected a failure in its
support.
glideslope receiver.
 Internal system-to-system
communication between the main
processor and the glideslope receiver
has failed. Operational status of the
glideslope receiver is unknown.
 The unit has detected a failure in its
glideslope receiver. The glideslope
receiver may still be usable.
 No data is being received from the
GDL 69.
 The GDL 88 is reporting that it has a
problem processing ADS-B traffic
data. The traffic picture may be
degraded.
 The GDL 88 is reporting to the GTN
GDL 88 Traffic Alerting not
that the CSA application has failed.
available
Traffic alerting on ADS-B traffic is
unavailable.
 The GNS unit cannot communicate
GDL 88 Connection has
with the datalink
been lost
GDL 88 ADS-B traffic has
failed
GDL 88 ADS-B transmit
has failed
Solution
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 Check for proper configuration
 Check wiring
 Contact Garmin technical
support.
 Refer to the GDL 84H/88H STC
Installation Manual.
 Ensure the aircraft has a clear
view of the sky. If problem
persists contact Garmin
technical support.
 Check for proper configuration
 Ensure the GDL 88 is powered
up
 Check wiring
 The GDL 88 is not able to transmit an  Check the GDL 88 status page
ADS-B message due to a failure with
in Aux mode
the GDL 88 system or antenna(s)
 Refer to the GDL 84H/88H STC
Installation Manual
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 15 of 23
Alert Text
GDL 88 ADS-B is not
transmitting position
GDL 88 ADS-B fault Check GDL 88 Status Page
Possible Cause
 The GDL 88 has detected a position
input fault
 Refer to the GDL 84H/88H STC
Installation Manual
 The GDL 88 has detected an
equipment fault
 Check the GDL 88 status page
in Aux mode
 Refer to the GDL 84H/88H STC
Installation Manual
 Verify that the center conductor
is not shorted to the braid in the
coaxial cable.
 Contact Garmin technical
support.
 GPS antenna cable is shorted
GPS is not responding –
check GPS antenna (main
software version 3.20 and
later).
GPS needs service
GTN transfer canceled,
version mismatch
Insufficient Terrain
Database Resolution
Large magnetic variance
Loss of integrity — crosscheck NAV
Solution
 Internal system-to-system
communication between the main
processor and the GPS receiver has
failed. Operational status of the GPS
receiver is unknown.
 The 400W Series unit has detected a
failure in its GPS receiver.
 The protocol version or database
version don’t match between the GTN
and GNS units
 The installed terrain database does
not have sufficient resolution to
support HTAWS
 A valid value of magnetic variation is
not available for this location.
 Verify all course angles
 Improper antenna installation or coax
routing
 Antenna shaded from satellites
 Contact Garmin technical
support.
 Load the most current cycles of
the navigation database to each
unit
 Load a 6 arc second terrain
database
 Contact Garmin technical
support.
 Check GPS antenna installation,
connections, and cable routing.
The GPS antenna must be
mounted on the top of the
aircraft.
 Make sure the aircraft is clear of
hangars, buildings, trees, etc.
 RF interference at 1575.42 MHz from  Move GPS antenna further from
VHF COM.
the COM antenna. Add a
1575.42 MHz notch filter in
COM coax. Fix or replace the
COM. Disconnect the ELT
antenna coax to check for
possible re-radiation.
Low Battery - Unit Needs
Service
MAIN processor requires
service
No altitude input is being
received
 Time data may have been lost due to  Contact Garmin technical
support.
a memory battery failure.
 The 400W Series unit has detected a  Contact Garmin technical
support.
failure in the main system processor.
 No altitude data is being received
from RS-232 (Serializer: Icarus,
Rosetta or Shadin) or grey code
inputs.
400W Series
Instructions for Continued Airworthiness Bell 206B
 Refer to Table 2 “RS-232 device
is not communicating with the
400W/420W/430W”.
190-01226-04 Rev. 5
Page 16 of 23
Alert Text
Possible Cause
 The 400W Series unit has detected a
failure in the built-in basemap (land
data) memory. Land data does not
appear on the Map Page. Other unit
functions continue to work normally.
 No data has been received on the
Not receiving input data on
ARINC 429 channel #1 connection for
429 Channel #1 or #2
a period exceeding five seconds.
 No data has been received on one (or
Not receiving input data on
more) of the RS-232 channel
232 Channel #(1 through 5)
connections for a period exceeding
ten seconds.
 No traffic data is being received.
Not receiving traffic data
No basemap data available
OBS key stuck
OBS not available
Solution
 Contact Garmin technical
support to reload the basemap
data.
 Refer to Table 2 “ARINC 429
device is not receiving data from
the 400W/420W/430W”
 Refer to Table 2 “RS-232 device
is not communicating with the
400W/420W/430W”
 Check for proper configuration
 Check the wiring
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 The OBS key is stuck in the enabled
(or pressed) state. Try pressing the
OBS key again to cycle its operation.
 Select a waypoint
 No destination waypoint has been
selected.
 The GPS receiver cannot currently
determine its position.
 Refer to Table 2: “The 400W
Series unit does not compute a
position.”
 The 400W Series unit has detected a  The data is not usable. Try
Obstacle database integrity
reloading the information onto
problem with a database on the
error
the card. If that does not solve
Terrain data card.
the problem replace the card.
RAIM position warning
Searching the sky
Stored data was lost
TAWS has failed
TAWS inhibit key stuck
 Wait for GPS satellite geometry
 Although sufficient GPS satellite
to improve.
coverage may exist, Receiver
Autonomous Integrity Monitoring
(RAIM) has determined the
information from one or more GPS
satellites may be in error.
 The 400W Series unit is searching the  Wait 20 minutes for unit to
complete cycle or until the
sky for GPS satellites.
current position is located.
 If system was not reset contact
 All user waypoints, flight plans and
system settings have been lost due to Garmin technical support.
a memory battery failure or system
reset.
 The 400W Series unit has detected a  Ensure that terrain database is
inserted in right most card slot.
failure in its TAWS system.
 Reload the terrain database.
 Contact Garmin technical
support.
 Verify that the wiring is not
 The external TAWS inhibit key is
shorted to ground.
stuck.
 Contact Garmin technical
support.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 17 of 23
Alert Text
TAWS mute caution key is
stuck
TAWS reduced protection
key is stuck
TERRAIN configuration
conflict
TERRAIN configuration has
changed
Terrain database integrity
error
TERRAIN has failed
Possible Cause
 The external HTAWS aural
suppression input is stuck
 The external TAWS reduced
protection key is stuck
 The current Terrain configuration is
not supported by the hardware.
Solution
 Try pressing the TAWS mute
key again to cycle its operation.
If problem persists contact
Garmin technical support.
 Try pressing the TAWS reduced
protection key to cycle its
operation. If the problem
persists contact Garmin
technical support.
 Reconfigure the unit.
 Reconfigure TERRAIN settings
 The unit’s terrain settings have
changed since it was last turned on in
 Contact Garmin technical
normal mode.
support
 The 400W Series unit has detected a  Reloading the information onto
the card.
problem with a database on the
Terrain data card.
 Replace the card.
 The unit has detected a failure in the
terrain system.
 Ensure that Terrain database is
inserted in the right most card
slot.
 Reload the TERRAIN database.
 Contact Garmin technical
support.
 Check for proper configuration
 The 400W Series unit cannot
communicate with the traffic system  Check for correct wiring
and/or the traffic system is reporting a
 Refer to the Traffic system
system failure.
installation manual.
 Refer to the Traffic system
 The traffic device is reporting a
Traffic device needs service
installation manual.
system failure.
Traffic device has failed
 A data card has been inserted, but the  Reload the information onto the
format of the card is not recognized.
card. If that does not solve the
problem replace the card.
 Contact Garmin technical
 The GNC 420/GNS 430W has
VLOC has failed (420W and
support.
detected a failure in its VLOC
430W only)
receiver.
 Contact Garmin technical
 Internal system-to-system
VLOC is not responding
support.
communication between the main
(420W and 430W only)
processor and the VLOC receiver has
failed. Operational status of the
VLOC receiver is unknown.
 Contact Garmin technical
 The unit has detected a failure in its
VLOC needs service
support.
VLOC receiver. The VLOC receiver
(420W and 430W only)
may still be usable.
User card format unknown
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 18 of 23
Alert Text
VLOC remote transfer key
is stuck (420W and 430W
only)
VLOC transfer key stuck
(420W and 430W only)
Stormscope device has
failed
Stormscope heading has
failed
Possible Cause
Solution
 Try pressing the switch again to
cycle its operation.
 Contact Garmin technical
support.
 The VLOC flip-flop key is stuck in the  Try pressing the VLOC flip-flop
key again to cycle its operation.
enabled (or “pressed”) state.
 The remote VLOC transfer switch is
stuck in the enabled (or “pressed”)
state.
 The 400W- Series unit cannot
communicate with the WX-500.
 The WX-500 is reporting a system
failure.
 The WX-500 is reporting invalid
heading data.
400W Series
Instructions for Continued Airworthiness Bell 206B
 Contact Garmin technical
support.
 Check for proper configuration
 Check the wiring
 Refer to the WX-500 installation
manual for additional
troubleshooting information.
 Check for proper configuration
of WX-500
 The failure may be within the
WX-500 or other connected
equipment.
190-01226-04 Rev. 5
Page 19 of 23
2.7 Removal and Installation Information
If any work has been done on the rotorcraft that could affect the system wiring, antenna cable, or any
interconnected equipment, verify the 400W Series unit power-up self-test sequence is successfully
completed and no failure messages are annunciated.
Whenever removing or installing units, remove power from the LRU by removing rotorcraft power or
opening the LRU circuit breaker.
2.7.1 400W Series Unit
2.7.1.1 Removal
1. Insert a 3/32-inch hex drive tool into the access hole at the bottom of the unit face.
2. Rotate the hex tool counterclockwise until the unit is forced out about 3/8 inches and can be
freely pulled from the rack.
2.7.1.2 Installation
1. Slide the 400W unit in the rack straight in until it stops, about 1 inch short of the final position.
2. Insert the hex drive tool into the access hole at the bottom of the unit face.
3. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly
seated in the rack.
NOTE
The installation configuration and user settings are stored internally in the 400W Series
unit, and will be lost when the 400W Series is replaced with a new unit.
Original 400W Series unit is Reinstalled
If the original 400W Series is reinstalled, then no configuration is required.
New, Repaired or Exchange 400W Series is Installed
If the 400W Series unit is removed for repair and reinstalled, or if the 400W unit is removed and replaced
with a different 400W Series unit, then verify the correct software versions are on the 400W Series unit
as specified in the Equipment List 400W/500W Series Installation Bell 206B STC listed in paragraph 2.1
of this document. In addition, complete the ‘Post Installation Configuration & Checkout Procedures’
contained in the 400W Rotorcraft STC Installation Manual listed in paragraph 2.1 of this document to
restore the proper installation configuration settings.
2.7.1.3 Return to Service
After removing and reinstalling the 400W Series unit per the instructions above, verify that the power-up
self-test sequence is successfully completed and no failure messages are annunciated.
Note: There are no special handling requirements for the 400W Series units.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 20 of 23
2.7.2 GA 35 GPS, GA 36 GPS, and GA 37 GPS/XM Antennas
2.7.2.1 Removal
1. Remove the screws from the outside of the rotorcraft.
2. Remove old sealant.
3. Lift the antenna off the rotorcraft and detach the coax (from the outside). If a GA 37 antenna
verify coax(s) are properly labeled with correct color band. Note: GPS coax is labeled with a blue
band and XM cable with a yellow band.
2.7.2.2 Installation
For GA 35, GA 36, or GA 37 GPS antenna installation, follow the installation procedures contained in the
installation drawing listed in paragraph 2.1 of this document.
2.7.2.3 Return to Service
After removing and reinstalling the GPS antenna, verify the 400W Series unit power-up self-test
sequence is successfully completed and no failure messages are annunciated. If the unit is unable to
acquire satellites, move the rotorcraft away from obstructions which might be shading GPS reception. If
the situation does not improve, check the GPS antenna installation.
2.7.3 Cooling Fan
2.7.3.1 Removal
1. Extract the screws from the copilot side (LH side) center console cover plate.
2. Remove copilot side (LH side) center console cover plate.
3. Disconnect cooling fan electrical connector located under cooling ports on fan.
4. Extract the three (3X) cooling fan mounting screws to remove cooling fan.
2.7.3.2 Installation
1. Install cooling fan using removed hardware.
2. Reconnect electrical connector to cooling fan.
3. Reinstall center console cover plate using removed hardware, verifying silicone sponge foam
used to seal cooling fan intake remains in place on center console cover plate and properly
seals the fan intake to the louver installed on the center console cover plate.
2.7.3.3 Return to Service
After removing and reinstalling the cooling fan verify proper operation of the cooling fan. Apply power to
the avionics, verify the cooling fan is operating and the FAN FAIL light on the annunciator panel is not
illuminated.
2.8 Diagrams
Rotorcraft specific LRU locations and wire routing diagrams are contained in the 400W/500W Series
Installation drawing Bell 206B, listed in Section 2.1 of this document Point to point wiring diagrams are
in the Appendix of the 400W Rotorcraft STC Installation Manual. Refer to the GNS 400W Series PostInstallation Checkout Log retained in the rotorcraft permanent records for a list of the interfaced
equipment and port configurations.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 21 of 23
2.9 Special Inspection Requirements
2.9.1 Post-Lightning Strike Inspection
In the event of a suspected or actual lightning strike to the rotorcraft, the GA 35, GA 36, or GA 37 GPS
antenna installation shall be inspected to ensure that there is no structural damage around the areas
where lightning may have attached. If there is visible sign of damage to the antenna then it must be
replaced.
Verify that the 400W series unit receives and displays GPS satellite information normally.
2.9.2 Post-Hard Landing Inspection
In the event of a hard landing complete all the inspections specified in Table 1 Periodic Maintenance
Inspections.
2.10 Application of Protective Treatments
None, N/A.
2.11 Data Relative to Structural Fasteners
FASTENER TYPE AND TORQUE
Location
(see Installation
Drawing)
6‐32 Screw
6‐32 Screw
8‐32 Screw
10‐32 Screw
10‐32 Screw
4±2 inch‐pounds
12‐15 inch‐pounds
12‐15 inch‐pounds
12‐15 inch‐pounds
20‐25 inch‐pounds
400W Unit Mounting
Rack
X
GPS Antenna
Cooling Fan
X
X
Cooling Fan Bracket
X
X
2.12 Special Tools
For electrical bonding testing, a milliohm meter is required.
2.13 Additional Instructions
None
2.14 Overhaul Period
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT
will monitor the health of the 400W Series unit. If the unit indicates an internal failure, the unit may be
removed and replaced. See troubleshooting section 2.6 contained in this document.
400W Series
Instructions for Continued Airworthiness Bell 206B
190-01226-04 Rev. 5
Page 22 of 23
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