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

Garmin GNS 430W 400W Series Instructions for Continued Airworthiness Bell 206L Series
400W Series
Instructions for Continued Airworthiness
Bell 206L Series
Reg. No.____________
S/N_______________
Dwg. Number:
190-01226-12 Rev. 3
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev.
Date
1
2
3
04/09/15
06/18/15
02/08/17
Description of Change
Initial Release
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  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 206L Series
190-01226-12 Rev. 3
Page 2 of 24
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 ........................................................................ 9
2.6 Troubleshooting Information ................................................................................. 12
2.7 Removal and Installation Information ................................................................... 21
2.8 Diagrams............................................................................................................... 22
2.9 Special Inspection Requirements ......................................................................... 23
2.10 Application of Protective Treatments .................................................................... 23
2.11 Data Relative to Structural Fasteners ................................................................... 23
2.12 Special Tools ........................................................................................................ 23
2.13 Additional Instructions........................................................................................... 23
2.14 Overhaul Period .................................................................................................... 23
2.15 ICA Revision and Distribution ............................................................................... 24
2.16 Assistance............................................................................................................. 24
2.17 Implementation and Record Keeping ................................................................... 24
3. AIRWORTHINESS LIMITATIONS ........................................................................................ 24
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 3 of 24
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 206L 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 206L Series
190-01226-12 Rev. 3
Page 4 of 24
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 206L series 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 206 and 407
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 190-01226-09 Rev. 1 “400W/500W Series
Installation Bell 206L Series” 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 206L Series
190-01226-12 Rev. 3
Page 5 of 24
2.2
Description of Alteration
This STC upgrades existing avionics for the Bell 206L series 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 206L. 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 206L 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
206L 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.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 6 of 24
The installed 400W Series equipment can be accessed as described below:
LRU Access: Bell models 206L Series
1. GA 35/36/37 ANTENNA: FS82.0 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: 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: FS29.3 Access by removing copilot side (LH) cover plate. Remove by extracting
three mounting screws and disconnecting connector.
5. 400W SERIES UNIT: FS40.7 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.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 7 of 24
2.2.1 Weight and Balance Information
Moment ARM [IN]
PART
WEIGHT
ITEM DESCRIPTION
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
40.7
0.0
1
5.5
GNC 420AW (Installed with rack and back 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
6.2
GNS 430AW (Installed with rack and back plate)
2 GCF 3XX 3‐Port Cooling Fan (Unit Only)
013‐00103‐00 0.70
29.3
3.6
013‐00235‐00 0.47
GA 35 GPS/WAAS Antenna (Unit Only)
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)
013‐00245‐00 0.50
GA 37 GPS/WAAS + XM Antenna (Unit Only)
[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.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 8 of 24
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
400W Series
Unit
400W Series
Mounting Rack
Interval
12 Months
12 Months
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:
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.
Avionics
Cooling Fan
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.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 9 of 24
Item
GPS Antennas
(Only if antenna
is installed by
this STC)
Interval
Every 2000
flight hours or
ten (10)
years,
whichever is
first
Description/Procedure
Perform an electrical bonding test on antennas installed by this
STC:
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.
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.
In the event of bonding test failure:
HTAWS
Annunciators (if
installed)
Every 2000
flight hours or
ten (10)
years,
whichever is
first
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
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 10 of 24
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 206L Series
190-01226-12 Rev. 3
Page 11 of 24
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
The 400W Series
unit does not power
on.
The 400W Series
unit does not
compute a position.
GPS signal levels
drop when avionics
are turned on.
The GPS signal
levels are very low.
Possible Cause
 The unit is not getting power to
the main connector P4001.
Solution

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.
 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.
 Noise interference from other
avionics.

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.
 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.
The 400W Series
unit does not
transmit.
 The PTT input is not being pulled 
low.
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 reradiation.
Check that the PTT (mic key) input is
pulled low for 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 level 
needs adjustment.
too low or too high.
OBS Resolver won’t  Incompatible resolver or
calibrate.
improper connection.
400W Series
Instructions for Continued Airworthiness Bell 206L Series

If necessary, adjust the sidetone level.
Sidetone adjustment is found on the
COM Setup page.
Check the resolver specifications and
wiring.
190-01226-12 Rev. 3
Page 12 of 24
Problem
OBS indication on
400W Series unit
does not agree with
OBS setting.
Possible Cause
 400W Series unit resolver input
not calibrated correctly.
 Resolver has not been
calibrated.
Solution

400W Series unit is  ARINC 429 input port speed not 
correct
not receiving
heading from
compass system
(ARINC 429 heading  Wiring connections are incorrect.

input used)
RMI pointer does not  Desired RMI source has not

been selected.
indicate correctly
 Wiring connections are incorrect. 
Tuning data not
updating DME
 Incorrect configuration.

 Wiring connections are incorrect. 
ARINC 429 device is  400W Series unit ARINC 429

output not configured correctly.
not receiving data
from the
 ARINC 429 input port speed not 
400W/420W/430W.
correct
 Wiring connections are incorrect. 
RS-232 device is not  400W Series unit RS-232 port
not configured correctly.
communicating with
 Improper setup on the remote
the
device.
400W/420W/430W.
 Device not compatible, or
improper connection.
Fan Fail
Annunciation.

Check wiring and calibration.
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 the OBI source selection on the
Main CDI/OBS Config page.
Check wiring.
Check the DME Channel Mode on the
VOR/LOC/GS CDI page.
Check wiring.
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.
 Multiple TX lines connected

together.
 Wiring connections are incorrect. 
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.
 Wiring connections are incorrect. 
Check wiring.
 Fan has failed.
Replace fan.
400W Series
Instructions for Continued Airworthiness Bell 206L Series



190-01226-12 Rev. 3
Page 13 of 24
2.6.1 400W Series Alerts
The 400W Series will display a number of alerts. These are listed in the following table.
Table 3. 400W Series Alert Troubleshooting Guide
Alert Text
ADS-B traffic has failed
ADS-B transmit has failed
ADS-B is not transmitting
position
ADS-B fault - Check ADS-B
Status Page
Possible Cause
Solution
 Check the applicable ADS-B
 The ADS-B traffic system may
traffic source status page in Aux
have lost GPS position or detected
mode
an internal fault.
 Contact Garmin technical
support.
 ADS-B unit is not able to transmit a  Check system and antenna
wiring. If problem persists
message due to a failure with the
contact Garmin technical
ADS-B system or antenna(s).
support.
 Verify GPS position source is
 The ADS-B unit has detected a
functional. If problem persists
position input fault.
contact Garmin technical
support.
 Contact Garmin technical
 An equipment fault has been
support.
detected.
ADS-B - Connection has been  The GNS is configured for a traffic
lost
device but is not receiving data
from it. Traffic will not be
displayed on the GNS.
ADS-B Traffic Alerting not
 The ADS-B traffic system is
available
reporting that the CSA application
has failed. Traffic alerting on ADSB traffic is unavailable.
Airport terrain database
 The 400W Series unit has detected
integrity error
a problem with a database on the
Terrain data card. The message
“<database name> database
integrity error” indicates the data
base in error.
Audio database error out of
 The 400W-series unit has detected
date or missing
a problem with the built-in HTAWS
Audio Data-base. HTAWS audio
alerts are not available.
Aviation database integrity
 The 400W Series unit has detected
error
a problem with a database on the
NavData® card. The message
“<database name> database
integrity error” indicates the data
base in error.
Basemap database integrity
 The 400W Series unit has detected
error
a failure in the built-in basemap
(land data) database. Land data
does not appear on the Map Page.
Other unit functions continue to
work normally.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
 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
190-01226-12 Rev. 3
Page 14 of 24
Alert Text
Boot block verify failed Return unit for repair
CDI key stuck
CDI key disabled
Check unit cooling
COM has failed (420W and
430W only)
COM is not responding
(420W and 430W only)
COM needs service
(420W and 430W only)
COM push-to-talk key stuck
(420W and 430W only)
COM remote transfer key is
stuck (420W and 430W only)
Possible Cause

 System integrity testing has
determined that the boot block has
become corrupted.
 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 on the MAIN CDI/OBS
CONFIG page.
 The 400W Series unit has detected 
excessive display backlighting
temperature. The backlighting has
been automatically dimmed to
reduce the temperature.

 The unit has detected a failure in
its communications transceiver.
Solution
Contact Garmin technical
support.
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
 Internal system-to-system
support. If the COM board is
communication between the main
still working, it will automatically
processor and the COM
transceiver has failed. Operational tune to 121.500 MHz. Transmit
and receive functions may still
status of the COM transceiver is
operate regardless of the
unknown.
displayed frequency.
 Contact Garmin technical
 The unit has detected a failure in
support
its communications transceiver.
The COM transceiver may still be
usable.
 Try pressing the PTT switch
 The external push-to-talk (PTT)
again to cycle its operation.
switch is stuck in the enabled (or
“pressed”) state.
 Wiring is incorrect.
 Check Wiring
 The remote COM transfer switch is  Try pressing the switch again to
cycle its operation.
stuck in the enabled (or “pressed”)
state.
 Verify the wiring is correct.
 If the message persists, contact
Garmin technical support.
COM transfer key stuck
(420W and 430W only)
 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.
COM transmitter power has
been reduced (420W and
430W only)
 The unit has detected excessive
unit temperature. The COM
transceiver transmit power has
been automatically reduced to
compensate for the condition.
 Insufficient voltage level
 Check for adequate ventilation
or check cooling airflow. Refer
to Section 2.7 of the Installation
Manual.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
 Check the input voltage
190-01226-12 Rev. 3
Page 15 of 24
Alert Text
Configuration error - Config
service req’d
Possible Cause
 The configuration information has
been lost or corrupted.
Data transfer cancelled
(crossfill is busy)
 An attempt to transfer flight plan
data during a unit-to-unit crossfill
was cancelled.
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
Solution
 Reconfigure the unit
 The host unit is busy. Wait until
any previous crossfill operation
is complete, before reattempting
the transfer.
 An attempt to transfer a single user  Select a user waypoint and rewaypoint during a unit-to-unit
attempt the transfer.
crossfill was cancelled. No
waypoint was specified on the
Crossfill Page.
 An attempt to transfer data during  If necessary, update the
database(s) so they match.
a unit-to-unit crossfill was
cancelled. The database versions
of the two 400W-series unit are not
identical.
 An error was detected during unit-  The data transfer should be reattempted.
to-unit crossfill of user data (user
waypoints and/or flight plans).
 The 400W Series unit has detected  Contact Garmin technical
a failure in the display backlighting. support.
 The 400W Series unit is in Demo  Check that the DEMO MODE
SELECT pin, P5001 Pin 75, is
Mode and must not be used for
not connected.
actual navigation.
 Contact Garmin technical
 The unit has detected a failure in
support.
its 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.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 Check for proper configuration
 Check wiring
 Contact Garmin technical
support.
190-01226-12 Rev. 3
Page 16 of 24
Alert Text
GDL 88 ADS-B traffic has
failed
Possible Cause
 The GDL 88 is reporting that it has
a problem processing ADS-B
traffic data. The traffic picture may
be degraded.
GDL 88 Traffic Alerting not
 The GDL 88 is reporting to the
available
GTN that the CSA application has
failed. Traffic alerting on ADS-B
traffic is unavailable.
GDL 88 Connection has been  The GNS unit cannot communicate
lost
with the datalink
GDL 88 ADS-B transmit has
failed
GDL 88 ADS-B is not
transmitting position
Solution
 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  Check the GDL 88 status page
in Aux mode
an ADS-B message due to a
failure with the GDL 88 system or  Refer to the GDL 84H/88H STC
antenna(s)
Installation Manual
 Refer to the GDL 84H/88H STC
 The GDL 88 has detected a
Installation Manual
position input fault
 Check the GDL 88 status page
in Aux mode
 Refer to the GDL 84H/88H STC
Installation Manual
 Verify that the center conductor
 GPS antenna cable is shorted
is not shorted to the braid in the
GPS is not responding – check
coaxial cable.
GPS antenna (main software  Internal system-to-system
 Contact Garmin technical
version 3.20 and later).
communication between the main
support.
processor and the GPS receiver
has failed. Operational status of
the GPS receiver is unknown.
GPS needs service
 The 400W Series unit has detected  Contact Garmin technical
support.
a failure in its GPS receiver.
GTN transfer canceled,
 The protocol version or database  Load the most current cycles of
version mismatch
the navigation database to each
version don’t match between the
unit
GTN and GNS units
Insufficient Terrain Database  The installed terrain database does  Load a 6 arc second terrain
Resolution
database
not have sufficient resolution to
support HTAWS
Large magnetic variance
 A valid value of magnetic variation  Contact Garmin technical
support.
is not available for this location.
 Verify all course angles
GDL 88 ADS-B fault - Check
GDL 88 Status Page
 The GDL 88 has detected an
equipment fault
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 17 of 24
Alert Text
Loss of integrity — crosscheck NAV
Possible Cause
 Improper antenna installation or
coax routing
 Antenna shaded from satellites
 RF interference at 1575.42 MHz
from VHF COM.
Solution
 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.
 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.
Low Battery - Unit Needs
Service
 Time data may have been lost due  Contact Garmin technical
support.
to a memory battery failure.
MAIN processor requires
service
 The 400W Series unit has detected
a failure in the main system
processor.
 No altitude data is being received
from RS-232 (Serializer: Icarus,
Rosetta or Shadin) or grey code
inputs.
 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
ARINC 429 channel #1 connection
for a period exceeding five
seconds.
 No data has been received on one
(or more) of the RS-232 channel
connections for a period exceeding
ten seconds.
 No traffic data is being received.
No altitude input is being
received
No basemap data available
Not receiving input data on
429 Channel #1 or #2
Not receiving input data on
232 Channel #(1 through 5)
Not receiving traffic data
 Contact Garmin technical
support.
 Refer to Table 2 “RS-232 device
is not communicating with the
400W/420W/430W”.
 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
OBS key stuck
 The OBS key is stuck in the
enabled (or pressed) state. Try
pressing the OBS key again to
cycle its operation.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
 Contact Garmin technical
support.
 Contact Garmin technical
support.
190-01226-12 Rev. 3
Page 18 of 24
Alert Text
OBS not available
Obstacle database integrity
error
Possible Cause
 No destination waypoint has been
selected.
Solution
 Select a waypoint
 The GPS receiver cannot currently  Refer to Table 2: “The 400W
determine its position.
Series unit does not compute a
position.”
 The 400W Series unit has detected  The data is not usable. Try
reloading the information onto
a problem with a database on the
the card. If that does not solve
Terrain data card.
the problem replace the card.
 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.
Searching the sky
 The 400W Series unit is searching  Wait 20 minutes for unit to
complete cycle or until the
the sky for GPS satellites.
current position is located.
Stored data was lost
 All user waypoints, flight plans and  If system was not reset contact
Garmin technical support.
system settings have been lost
due to a memory battery failure or
system reset.
TAWS has failed
 Ensure that terrain database is
 The 400W Series unit has
inserted in right most card slot.
detected a failure in its TAWS
system.
 Reload the terrain database.
 Contact Garmin technical
support.
TAWS inhibit key stuck
 The external TAWS inhibit key is  Verify that the wiring is not
shorted to ground.
stuck.
 Contact Garmin technical
support.
TAWS mute caution key is
 Try pressing the TAWS mute
 The external HTAWS aural
stuck
key again to cycle its operation.
suppression input is stuck
If problem persists contact
Garmin technical support.
TAWS reduced protection key  The external TAWS reduced
 Try pressing the TAWS reduced
is stuck
protection key to cycle its
protection key is stuck
operation. If the problem
persists contact Garmin
technical support.
TERRAIN configuration
 The current Terrain configuration  Reconfigure the unit.
conflict
is not supported by the hardware.
RAIM position warning
TERRAIN configuration has
changed
 The unit’s terrain settings have
changed since it was last turned
on in normal mode.
 Reconfigure TERRAIN settings
 Contact Garmin technical
support
Terrain database integrity error  The 400W Series unit has detected  Reloading the information onto
the card.
a problem with a database on the
Terrain data card.
 Replace the card.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
190-01226-12 Rev. 3
Page 19 of 24
Alert Text
TERRAIN has failed
Possible Cause
 The unit has detected a failure in
the terrain system.
Solution
 Ensure that Terrain database is
inserted in the right most card
slot.
 Reload the TERRAIN database.
 Contact Garmin technical
support.
Traffic device has failed
Traffic device needs service
User card format unknown
VLOC has failed (420W and
430W only)
VLOC is not responding
(420W and 430W only)
VLOC needs service
(420W and 430W only)
VLOC remote transfer key is
stuck (420W and 430W only)
VLOC transfer key stuck
(420W and 430W only)
 Check for proper configuration
 The 400W Series unit cannot
communicate with the traffic
 Check for correct wiring
system and/or the traffic system is
 Refer to the Traffic system
reporting a system failure.
installation manual.
 Refer to the Traffic system
 The traffic device is reporting a
installation manual.
system failure.
 A data card has been inserted, but
the format of the card is not
recognized.
 The GNC 420/GNS 430W has
detected a failure in its VLOC
receiver.
 Internal system-to-system
communication between the main
processor and the VLOC receiver
has failed. Operational status of
the VLOC receiver is unknown.
 The unit has detected a failure in
its VLOC receiver. The VLOC
receiver may still be usable.
 The remote VLOC transfer switch
is stuck in the enabled (or
“pressed”) state.
 The VLOC flip-flop key is stuck in
the enabled (or “pressed”) state.
 Reload the information onto the
card. If that does not solve the
problem replace the card.
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 Try pressing the switch again to
cycle its operation.
 Contact Garmin technical
support.
 Try pressing the VLOC flip-flop
key again to cycle its operation.
 Contact Garmin technical
support.
 Check for proper configuration
Stormscope device has failed  The 400W- Series unit cannot
communicate with the WX-500.
 The WX-500 is reporting a system  Check the wiring
failure.
 Refer to the WX-500 installation
manual for additional
troubleshooting information.
Stormscope heading has failed  The WX-500 is reporting invalid
heading data.
400W Series
Instructions for Continued Airworthiness Bell 206L Series
 Check for proper configuration
of WX-500
 The failure may be within the
WX-500 or other connected
equipment.
190-01226-12 Rev. 3
Page 20 of 24
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 206 and 407 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 206L Series
190-01226-12 Rev. 3
Page 21 of 24
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 206L Series, 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 Post-Installation 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 206L Series
190-01226-12 Rev. 3
Page 22 of 24
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.
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 206L Series
190-01226-12 Rev. 3
Page 23 of 24
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