Garmin | GNS 430W | Garmin GNS 430W 400W Series Instructions for Continued Airworthiness Bell 407

Garmin GNS 430W 400W Series Instructions for Continued Airworthiness Bell 407
400W Series
Instructions for Continued Airworthiness
Bell 407
Reg. No.____________
S/N_______________
Dwg. Number:
190-01226-14 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 407
190-01226-14 Rev. 3
Page 2 of 26
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 ............................................................................. 11
2.4 Servicing Information ............................................................................................ 11
2.5 Periodic Maintenance Instructions ........................................................................ 12
2.6 Troubleshooting Information ................................................................................. 14
2.7 Removal and Installation Information ................................................................... 23
2.8 Diagrams............................................................................................................... 24
2.9 Special Inspection Requirements ......................................................................... 25
2.10 Application of Protective Treatments .................................................................... 25
2.11 Data Relative to Structural Fasteners ................................................................... 25
2.12 Special Tools ........................................................................................................ 25
2.13 Additional Instructions........................................................................................... 25
2.14 Overhaul Period .................................................................................................... 25
2.15 ICA Revision and Distribution ............................................................................... 26
2.16 Assistance............................................................................................................. 26
2.17 Implementation and Record Keeping ................................................................... 26
3. AIRWORTHINESS LIMITATIONS ........................................................................................ 26
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 3 of 26
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 407 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 407
190-01226-14 Rev. 3
Page 4 of 26
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 407 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 190-01226-10 Rev. 1 “400W/500W Series
Installation Bell 407” 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 407
190-01226-14 Rev. 3
Page 5 of 26
2.2
Description of Alteration
This STC upgrades existing avionics for the Bell 407 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
console of the Bell 407. 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 407 forward engine cowl. A monitored avionics
cooling fan is installed in the instrument panel support with a fan fail fault annunciation located in the
existing caution and warning annunciator panel.
(1)
(1)
‐
‐
‐
(1)
(1)
‐
1
1
1
1
1
‐
‐
1
8
‐
1
2
(1)
‐
1
7
6
5
4
3
013‐00103‐00
011‐00351‐00
011‐00351‐01
011‐00351‐03
011‐00676‐00
011‐00671‐00
115‐00345‐00
115‐00243‐00
011‐01061‐XX
011‐01060‐XX
011‐01059‐XX
011‐01058‐XX
011‐01057‐XX
011‐01066‐XX
011‐01064‐XX
011‐01062‐XX
5XX 4XX
ITEM NO. PART NUMBER
QTY.
GFC 3XX 3‐PORT COOLING FAN
CONNECTOR KIT GNS 430W GNS 430AW
CONNECTOR KIT GNC 420W GNC 420AW
CONNECTOR KIT GPS 400W GPS 500W
BACKPLATE SUB‐ASSEMBLY 400W SERIES NAVIGATOR
BACKPLATE SUB‐ASSEMBLY 500W SERIES NAVIGATOR
MOUNTING RACK 500W SERIES NAVIAGATOR
MOUNTING RACK 400W SERIES NAVIAGATOR
GNS 430AW NAVIGATOR
GNS 430W NAVIGATOR
GNC 420AW NAVIGATOR
GNC 420W NAVIGATOR
GPS 400W NAVIGATOR
GNS 530AW NAVIGATOR
GNS 530W NAVIGATOR
GPS 500W NAVIGATOR
DESCRIPTION
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 6 of 26
This STC also provides the data for installation of optional remote HTAWS annunciators and optional
cyclic stick switches for remote control of COM and HTAWS functions.
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 in the panel located in existing
overhead console, as shown below. (Note: circuit breakers for dual navigator installation are shown).
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 7 of 26
A/R
1 FT
2 FT
2
13
12
11
10
MIL‐A‐46106
MIL‐R‐6130
5700‐1
218089
5
9
MS3367‐3
2
8
MB3APT
7
7
MS20426AD3‐3
2
6
MS21071L06
2
5
AN525‐832R6
2
4
1
3
1
2
1
1
QTY. ITEM NO.
MS51957‐37
011‐02558‐00
190‐01226‐10‐01
013‐00103‐00
PART NUMBER
ADHESIVE SEALANT, SILICONE RTV, ONE COMPONENT
SILICONE SPONGE, MEDIUM DENSITY, GENERAL PURPOSE
AIRDUCT, FLEXIBLE, 5/8 INCH
CAP, EPDM, ID 0.625 [STOCKCAP.COM]
STRAP, TIEDOWN, ELECTRICAL COMPONENTS, ADJUSTABLE, SELF
CLINCHING, PLASTIC
MOUNTING BASE, CABLE TIE, HIGH TEMPERATURE, HEAVY BOND
ADHESIVE
RIVET, SOLID, COUNTERSUNK 100 DEG. PRECISION HEAD, 3‐32 IN OD,
3/16" LONG
NUT, SLEF LOCKING, PLATE, ONE LUG, REDUCED RIVET SPACING, LOW
HEIGHT, 0.1380‐32UNJC‐3B
SCREW, WASHER HEAD, CROSS‐RECESSED, 0.1640‐32UNC‐3A, 3/8 INCH
LONG
SCREW, MACHINE, PAN HEAD, CROSS‐RECESSED, CRES, 0.1380‐32UNC‐2A
LOUVER, ROUND, SCREENED, 3‐INCH, BLACK, FAA‐PMA
BRACKET, COOLING FAN
AVIONICS COOLING FAN WITH FAULT DETECTION
DESCRIPTION
400W Series
Instructions for Continued Airworthiness Bell 407
EDMO
TYTON
GARMIN
GARMIN
SUPPLIER
190-01226-14 Rev. 3
Page 8 of 26
The installed 400W Series equipment can be accessed as described below:
LRU Access: Bell models 407
1. GA 35/36/37 ANTENNA: FS84.0 for dual antenna installation; FS79.0 for single antenna installations.
Remove environmental seal, remove four antenna screws and lift the antenna enough to disconnect
antenna connector.
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: FS24.63 Access by removing 407-030-202-148 COVER, LOWER, RH. Remove two
screws, disconnect connector and air duct.
5. 400W SERIES UNIT: FS40 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 407
190-01226-14 Rev. 3
Page 9 of 26
2.2.1 Weight and Balance Information
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 10 of 26
GA 37 GPS/WASS + XM ANTENNA
7
6
5
4
3
2
1
GA 36 GPS/WASS ANTENNA
GA 35 GPS/WASS ANTENNA (UNIT ONLY)
SWITCH, RP MODE, HTAWS
STATUS ANNUNCIATOR, HTAWS
CAUTION AND WARNING INDICATOR, HTAWS
GFC X33 3‐PORT COOLING FAN
GNS 430AW NAVIGATOR
GNS 430W NAVIGATOR
GNC 420AW NAVIGATOR
GNC 420W NAVIGATOR
GPS 400W NAVIGATOR
GNS 530AW NAVIGATOR
GNS 530W NAVIGATOR
GPS 500W NAVIGATOR
ITEM DESCRIPTION
013‐00245‐00
013‐00244‐00
013‐00235‐XX
LED‐41‐11‐BB‐E11ND
485‐00003‐01
LED‐40‐17‐BB‐E11R9
013‐00103‐00
011‐01061‐XX
011‐01060‐XX
011‐01059‐XX
011‐01058‐XX
011‐01057‐XX
011‐01066‐XX
011‐01064‐XX
011‐01062‐XX
PART NUMBER
0.50
0.47
0.06
0.70
40.03
39.50
[42.00]
37.13
[39.48]
2.40
42.52
2.55
29.92
20.94
79.00
[84.00]
6.20
5.50
6.80
WEIGHT
[LB]
0
0
0
0
254.45
41.04
5.00
8.20
‐4.73
10.04
‐6.57
2.67
0.00
[2.50]
0.00
[2.35]
‐0.28
0.60
‐0.39
1.87
0.00
[5.00]
225.72
205.20
39.48
323.74
268.46
ARM [IN] MOMENT ARM [IN] MOMENT
LONGITUDINAL
LATERAL
[1] Rotorcraft weight and balance is required after installation of the 400W Series Unit. Refer to the
500W 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).
[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.
[5] FS and BL numbers in square brackets apply to dual antenna installation.
[6] GNS navigator weight includes the unit, unit mounting rack, back plate, and connectors
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 407
190-01226-14 Rev. 3
Page 11 of 26
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 407
190-01226-14 Rev. 3
Page 12 of 26
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. For
annunciator installation with annunciator mounted in
instrument panel verify mating surfaces are clean and free
of corrosion.
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. For installations with the annunciator
mounted in instrument panel clean the mating surfaces.
3. Reinstall the bonding strap (or annunciator when mounted
in instrument panel) 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 407
190-01226-14 Rev. 3
Page 13 of 26
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.
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
The 400W Series unit  The unit is not getting power to the 
main connector P4001.
does not power on.
The 400W Series unit  Not receiving signals.
does not compute a
position.
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.

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.
The GPS signal levels  Improper antenna installation or
coax routing.
are very low.

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.
GPS signal levels
drop when avionics
are turned on.
 Noise interference from other
avionics.
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 14 of 26
Problem
Possible Cause

The
PTT
input is not being pulled
The 400W Series unit
low.
does not transmit.
 No transmit power to the COM.
Solution

Check that the PTT (mic key) input is
pulled low for transmit.

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
too low or too high.
 Wrong type of headsets, or level
needs adjustment.

OBS Resolver won’t
calibrate.
 Incompatible resolver or improper
connection.

If necessary, adjust the sidetone level.
Sidetone adjustment is found on the
COM Setup page.
Check the resolver specifications and
wiring.
OBS indication on
400W Series unit
does not agree with
OBS setting.
 400W Series unit resolver input not 
calibrated correctly.
 Resolver has not been calibrated.
 ARINC 429 input port speed not
400W Series unit is
correct
not receiving heading
from compass system
(ARINC 429 heading
input used)
 Wiring connections are incorrect.
RMI pointer does not
indicate correctly
Tuning data not
updating DME
ARINC 429 device is
not receiving data
from the
400W/420W/430W.
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.
 Desired RMI source has not been
selected.

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.
 400W Series unit ARINC 429
output not configured correctly.

Check ARINC 429 output port setting for
port that device is connected to.
 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.
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 15 of 26
Problem
RS-232 device is not
communicating with
the
400W/420W/430W.
Possible Cause
 400W Series unit RS-232 port not 
configured correctly.
Solution
Check RS-232 port setting for port that
device is connected to.
 Improper setup on the remote
device.
Verify the configuration of the other
device.

 Device not compatible, or improper 
connection.
Verify 400W Series unit RX is connected
to remote device TX and 400W Series
unit TX is connected to remote device
Rx.
 Multiple TX lines connected
together.

Verify that there is only one TX source
per RX port.
 Wiring connections are incorrect.

Check wiring.
Fan Fail Annunciation.  Wiring connections are incorrect.

Check wiring.

Replace fan.
 Fan has failed.
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 16 of 26
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
Possible Cause
 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
 The ADS-B unit has detected a
position input fault.
ADS-B fault - Check ADS-B  An equipment fault has been
Status Page
detected.
ADS-B - Connection has
 The GNS is configured for a traffic
been 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 reporting
available
that the CSA application has failed.
Traffic alerting on ADS-B traffic is
unavailable.
Airport terrain database
 The 400W Series unit has detected a
integrity error
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 a
date or missing
problem with the built-in HTAWS
Audio Data-base. HTAWS audio
alerts are not available.
Aviation database integrity  The 400W Series unit has detected a
error
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 a
error
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.
Boot block verify failed  System integrity testing has
Return unit for repair
determined that the boot block has
become corrupted.
400W Series
Instructions for Continued Airworthiness Bell 407
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.
190-01226-14 Rev. 3
Page 17 of 26
Alert Text
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)
COM transfer key stuck
(420W and 430W only)
COM transmitter power has
been reduced (420W and
430W only)
Configuration error - Config
service req’d
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
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.
 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 still
communication between the main
working, it will automatically tune
processor and the COM transceiver
to 121.500 MHz. Transmit and
has failed. Operational status of the
receive functions may still
COM transceiver is unknown.
operate regardless of the
displayed frequency.
 The unit has detected a failure in its  Contact Garmin technical
support
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
 Try pressing the switch again to
 The remote COM transfer switch is
cycle its operation.
stuck in the enabled (or “pressed”)
state.
 Verify the wiring is correct.
 If the message persists, contact
Garmin technical support.
 The COM flip-flop key is stuck in the  Try pressing the switch again to
cycle its operation.
enabled (or “pressed”) state.
 If the message persists, contact
Garmin technical support.
 The unit has detected excessive unit  Check for adequate ventilation
or check cooling airflow. Refer to
temperature. The COM transceiver
Section 2.7 of the Installation
transmit power has been
automatically reduced to compensate Manual.
for the condition.
 Insufficient voltage level
 Check the input voltage
 Reconfigure the unit
 The configuration information has
been lost or corrupted.
 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.
Data transfer cancelled (data  An attempt to transfer a single user
 Select a user waypoint and reinvalid)
attempt the transfer.
waypoint during a unit-to-unit crossfill
was cancelled. No waypoint was
specified on the Crossfill Page.
Data transfer cancelled
(crossfill is busy)
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 18 of 26
Alert Text
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)
Possible Cause
 An attempt to transfer data during 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-tounit crossfill of user data (user
waypoints and/or flight plans).
 The 400W Series unit has detected a
failure in the display backlighting.
 The 400W Series unit is in Demo
Mode and must not be used for
actual navigation.
 The unit has detected a failure in its
glideslope receiver.
Solution
 If necessary, update the
database(s) so they match.
 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.
 Contact Garmin technical
support.
 The data transfer should be reattempted.
 Contact Garmin technical
support.
 Check that the DEMO MODE
SELECT pin, P5001 Pin 75, is
not connected.
 Contact Garmin technical
support.
 Contact Garmin technical
support.
 Check for proper configuration
 Check wiring
 Contact Garmin technical
support.
GDL 88 ADS-B traffic has
 The GDL 88 is reporting that it has a  Refer to the GDL 84H/88H STC
failed
Installation Manual.
problem processing ADS-B traffic
data. The traffic picture may be
degraded.
GDL 88 Traffic Alerting not  The GDL 88 is reporting to the GTN  Ensure the aircraft has a clear
available
view of the sky. If problem
that the CSA application has failed.
persists contact Garmin
Traffic alerting on ADS-B traffic is
technical support.
unavailable.
GDL 88 Connection has
 Check for proper configuration
 The GNS unit cannot communicate
been lost
with the datalink
 Ensure the GDL 88 is powered
up
 Check wiring
GDL 88 ADS-B transmit has  The GDL 88 is not able to transmit an  Check the GDL 88 status page
failed
in Aux mode
ADS-B message due to a failure with
the GDL 88 system or antenna(s)
 Refer to the GDL 84H/88H STC
Installation Manual
GDL 88 ADS-B is not
 The GDL 88 has detected a position  Refer to the GDL 84H/88H STC
transmitting position
Installation Manual
input fault
GDL 69 is not responding
GDL 88 ADS-B fault - Check  The GDL 88 has detected an
GDL 88 Status Page
equipment fault
400W Series
Instructions for Continued Airworthiness Bell 407
 Check the GDL 88 status page
in Aux mode
 Refer to the GDL 84H/88H STC
Installation Manual
190-01226-14 Rev. 3
Page 19 of 26
Alert Text
Possible Cause
 GPS antenna cable is shorted
GPS is not responding –
check GPS antenna (main
software version 3.20 and
later).
 Internal system-to-system
communication between the main
processor and the GPS receiver has
failed. Operational status of the GPS
receiver is unknown.
GPS needs service
 The 400W Series unit has detected a
failure in its GPS receiver.
GTN transfer canceled,
 The protocol version or database
version mismatch
version don’t match between the
GTN and GNS units
Insufficient Terrain Database  The installed terrain database does
Resolution
not have sufficient resolution to
support HTAWS
Large magnetic variance
 A valid value of magnetic variation is
not available for this location.
 Verify all course angles
Loss of integrity — cross Improper antenna installation or coax
check NAV
routing
Solution
 Verify that the center conductor
is not shorted to the braid in the
coaxial cable.
 Contact Garmin technical
support.
 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.
Low Battery - Unit Needs
Service
 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  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 reradiation.
 Time data may have been lost due to  Contact Garmin technical
support.
a memory battery failure.
MAIN processor requires
service
 The 400W Series unit has detected a  Contact Garmin technical
support.
failure in the main system processor.
No altitude input is being
received
 Refer to Table 2 “RS-232 device
 No altitude data is being received
is not communicating with the
from RS-232 (Serializer: Icarus,
400W/420W/430W”.
Rosetta or Shadin) or grey code
inputs.
 The 400W Series unit has detected a  Contact Garmin technical
support to reload the basemap
failure in the built-in basemap (land
data.
data) memory. Land data does not
appear on the Map Page. Other unit
functions continue to work normally.
 Refer to Table 2 “ARINC 429
 No data has been received on the
device is not receiving data from
ARINC 429 channel #1 connection
the 400W/420W/430W”
for a period exceeding five seconds.
No basemap data available
Not receiving input data on
429 Channel #1 or #2
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 20 of 26
Alert Text
Possible Cause
Not receiving input data on  No data has been received on one (or 
232 Channel #(1 through 5)
more) of the RS-232 channel
connections for a period exceeding
ten seconds.
Not receiving traffic data

 No traffic data is being received.


OBS key stuck
OBS not available
Obstacle database integrity
error
RAIM position warning
Searching the sky
Stored data was lost
TAWS has failed
TAWS inhibit key stuck
TAWS mute caution key is
stuck
TAWS reduced protection
key is stuck
TERRAIN configuration
conflict
Solution
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.
 The OBS key is stuck in the enabled  Contact Garmin technical
support.
(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
 Refer to Table 2: “The 400W
determine its position.
Series unit does not compute a
position.”
 The 400W Series unit has detected a  The data is not usable. Try
reloading the information onto
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.
 Wait 20 minutes for unit to
 The 400W Series unit is searching
complete cycle or until the
the sky for GPS satellites.
current position is located.
 If system was not reset contact
 All user waypoints, flight plans and
Garmin technical support.
system settings have been lost due
to 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.
 Try pressing the TAWS mute
 The external HTAWS aural
key again to cycle its operation.
suppression input is stuck
If problem persists contact
Garmin technical support.
 Try pressing the TAWS reduced
 The external TAWS reduced
protection key to cycle its
protection key is stuck
operation. If the problem
persists contact Garmin
technical support.
 The current Terrain configuration is  Reconfigure the unit.
not supported by the hardware.
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 21 of 26
Alert Text
Possible Cause
TERRAIN configuration has  The unit’s terrain settings have
changed
changed since it was last turned on
in normal mode.
Terrain database integrity
error
TERRAIN has failed
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)
Stormscope device has
failed
Stormscope heading has
failed
Solution
 Reconfigure TERRAIN settings
 Contact Garmin technical
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  Ensure that Terrain database is
inserted in the right most card
terrain system.
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  Refer to the Traffic system
a system failure.
installation manual.
 Refer to the Traffic system
 The traffic device is reporting a
installation manual.
system failure.
 Reload the information onto the
 A data card has been inserted, but
card. If that does not solve the
the format of the card is not
problem replace the card.
recognized.
 Contact Garmin technical
 The GNC 420/GNS 430W has
support.
detected a failure in its VLOC
receiver.
 Contact Garmin technical
 Internal system-to-system
support.
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  Contact Garmin technical
support.
VLOC receiver. The VLOC receiver
may still be usable.
 The remote VLOC transfer switch is  Try pressing the switch again to
cycle its operation.
stuck in the enabled (or “pressed”)
state.
 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.
 Contact Garmin technical
support.
 Check for proper configuration
 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.
 Check for proper configuration of
 The WX-500 is reporting invalid
WX-500
heading data.
 The failure may be within the
WX-500 or other connected
equipment.
400W Series
Instructions for Continued Airworthiness Bell 407
190-01226-14 Rev. 3
Page 22 of 26
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 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 407
190-01226-14 Rev. 3
Page 23 of 26
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. Remove screws from 407-030-202-148 COVER, LOWER, RH.
2. Disconnect air duct from cooling fan port.
3. Remove 407-030-202-148 COVER, LOWER, RH.
4. Disconnect cooling fan electrical connector located next to fan cooling ports.
5. Remove two (2X) cooling fan screws and remove cooling fan.
2.7.3.2 Installation
1. Install cooling fan using removed hardware.
2. Reconnect electrical connector to cooling fan.
3. Connect air duct to cooling fan port.
4. Verifying silicone sponge foam used to seal cooling fan intake remains in place on 407-030-202148 COVER, LOWER, RH and properly seals the fan intake to the louver installed in 407-030202-148 COVER, LOWER, RH. Reinstall 407-030-202-148 COVER, LOWER, RH using
removed fasteners.
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 407, 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 407
190-01226-14 Rev. 3
Page 24 of 26
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
6‐32 Screw
6‐32 Screw
8‐32 Screw
10‐32 Screw
(see Installation Drawing)
4±2 inch‐pounds
12‐15 inch‐pounds
12‐15 inch‐pounds
12‐15 inch‐pounds
400W Unit Mounting Rack
X
GPS Antenna
Cooling Fan
X
X
Cooling Fan Bracket
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 407
190-01226-14 Rev. 3
Page 25 of 26
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