Garmin SR02080SE Instruction Manual
400W Series
Instructions for Continued Airworthiness
Bell 206B
Reg. No.____________ S/N_______________
Dwg. Number:
190-01226-04 Rev. 2
Garmin International, Inc.
1200 E. 151st Street
Olathe, Kansas 66062 USA
Record of Revision
Rev. Date Description of Change
1 7/16/10 Initial Release
2 8/11/10 Updated ref. doc. revisions in section 2.1, revised part number and weight
of item 2 in table 2.2.1.
1.
INTRODUCTION...................................................................................................................3
1.1 Purpose.................................................................................................................3
1.2 Scope....................................................................................................................3
1.3 Document Control.................................................................................................3
1.4 Permission to Use Certain Documents.................................................................3
1.5 Definitions.............................................................................................................3
2. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 4
2.1 Introduction...........................................................................................................4
2.2 Description of Alteration........................................................................................5
2.3 Control, Operating Information............................................................................. 7
2.4 Servicing Information............................................................................................ 7
2.5 Periodic Maintenance Instructions........................................................................7
2.6 Troubleshooting Information................................................................................. 8
2.7 Removal and Installation Information...................................................................19
2.8 Diagrams...............................................................................................................20
2.9 Special Inspection Requirements.........................................................................21
2.10 Application of Protective Treatments....................................................................21
2.11 Data Relative to Structural Fasteners................................................................... 21
2.12 Special Tools ........................................................................................................ 21
2.13 Additional Instructions...........................................................................................21
2.14 Overhaul Period....................................................................................................21
2.15 ICA Revision and Distribution............................................................................... 21
2.16 Assistance.............................................................................................................22
2.17 Implementation and Record Keeping...................................................................22
3. AIRWORTHINESS LIMITATIONS........................................................................................ 22
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 2 of 22
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 installed.
1.2 Scope
This document identifies the Instruction for Continued Airworthiness for the modification of the rotorcraft
for installation of the Garmin Models 400W series GPS/WAAS Nav/Com unit installed.
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 Instru ctions for Continued
Airworthiness and show compliance with STC engineering data. This permission does not con strue
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) ACO: Aircraft Certification Office
2) AEG: Aircraft Evaluation Group
3) CFR: Code of Federal Regulations
4) FAA: Federal Aviation Administration
5) ICA: Instructions for Continued Airworthiness
6) PMI: Principle Maintenance Inspector
7) STC: Supplemental Type Certificate
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 3 of 22
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 the Garmin 400W Series
GPS/WAAS Nav/Com units.
Applicability: Applies to Bell models 206B rotorcraft altered by
installation of the Garmin 400W Series GPS/WAAS
Nav/Com units.
Definition of Abbreviations: See Section 1.5
Precautions: None
Units of measurement: None
Referenced publications: Garmin 005-00610-03 Rev. 1 “Equipment List
400W/500W Series Installation Bell 206B STC” or
later FAA Approved Revisions
Garmin 190-01226-02 Rev. 1 “400W Series
Rotorcraft STC Installation Manual” or later FAA
Approved Revisions
Additional Maintenance Data: Garmin 190-01226-07 Rev. 3 “400W/500W Series
Installation Bell 206B” or later FAA Approved
Revisions
Garmin 005-W0223-00 Rev. 3 “400W/500W Series
Harness Assembly Bell 206B” or later FAA
Approved Revisions
Retention: This document, or the information contained within,
will be included in the rotorcraft’s permanent
records.
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 4 of 22
2.2 Description of Alteration
This STC upgrades existing avionics for the Bell 206B rotorcraft as summarized below.
The Garmin Model 400W Series GPS/WAAS Nav/Com unit is a 6 ¼ inch wide unit mounted in the center
pedestal of the Bell 206B. The 400W Series units combine a large number of easily accessible controls
to use the color multi-function display, Nav and Com transceiver, GPS/WAAS navigator in a single unit.
A GPS/WAAS antenna is installed on the top of the Bell 206B forward engine cowl. The 400W Series
unit interfaces to the Garmin G500H system GDU 620 PFD/MFD for display of navigation information,
and optional cyclic stick switches for remote control of COM and HTAWS functions. A monit ored avionics
cooling fan is installed in the center pedestal with a fan fail fault annunciation located in the existing Bell
206B annunciator panel.
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 a lower circuit breaker panel
located in the DART console as shown below. Note: dual navigator system installation as shown.
The installed 400W Series equipment can be accessed as describe d below:
LRU Access: Bell models 206B
3
4
1
2
5
6
1. GA 36/37 ANTENNA: FS80.0 remove by extracting the four mounting screws in the body of
the antenna. Note: location may vary slightly depending whether or not a dual navigator
system is installed.
2. OVERHEAD CIRCUIT BREAKER PANEL: FS61.0, WL 71.0 Access or remove by extracting
the mounting screws along the side of the circuit breaker panel.
3. CYCLIC CONTROL GRIPS: remove by extracting mounting screw at bottom of grip.
4. COOLING FAN: FS28.5 Access by removing copilot side (LH) cover plate. Remove by
extracting three mounting screws and disconnecting connector.
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 5 of 22
5. 400W SERIES UNIT: FS39.7 Access or remove by using a 3/32 allen head screwdriver to
loosen the locking mechanism through the access hole on the front of the unit. Note: location
may vary slightly depending whether or not a dual navigator system is installed.
6. LOWER CIRCUIT BREAKER PANEL: FS60.8, WL26.5 Access or remove by extracting the
four mounting ¼ turn fasteners along the sides of the circuit breaker panel.
2.2.1 Weight and Balance Information
ITEM DESCRIPTION
GPS400W(UnitOnly)
GPS400W(Installedwithrackandback
plate)
GNC420W(UnitOnly)
GNC420W(Installedwithrackandback
plate)
GNC420AW(UnitOnly)
1
GNC420AW(Installedwithrackandback
plate)
GNS430W(UnitOnly)
GNS430W(Installedwithrackandback
plate)
GNS430AW(UnitOnly)
GNS430AW(Installedwithrackandback
plate)
2
GCF3XX3‐PortCoolingFan(UnitOnly)
GA36GPS/WAASAntenna(UnitOnly)
3
GA37GPS/WAAS+XMAntenna(Unit
Only)
PART
NUMBER
011‐01057‐XX
011‐01058‐XX
011‐01059‐XX
011‐01060‐XX
011‐01061‐XX
013‐00103‐00 0.70 28.5‐3.2
013‐00244‐00 0.47
013‐00245‐00 0.50
WEIGHT
[LB]
4.0
5.0
4.5
5.5
4.5
5.5
5.1
6.2
5.1
6.2
MomentARM[IN]
LONGITUDINAL LATERAL
39.7 0.1
80.0 0.0
[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.
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 6 of 22
2.3 Control, Operating Information
See the Pilot’s Guides or the 400W Rotorcraft STC Installation Manual for system operation and self-test
information. The 400W Rotorcraft STC Installation Manual is listed under the reference documentation in
paragraph 2.1 of this document, and the Pilot’s Guides are listed in the related documents section of the
400W Rotorcraft STC Installation Manual.
2.4 Servicing Information
None. In the event of system failure, troubleshoot the 400W Series unit in accordance with Section 2.6.
2.5 Periodic Maintenance Instructions
The 400W Series units are designed to detect internal failure. A thorough self-test is executed
automatically upon application of power to the units, and built-in test is continuously executed. Detected
errors are indicated on the equipment via failure annunciations.
Maintenance of the components installed by this STC is on condition, except as noted in the following
table.
Table 1 Periodic Maintenance Inspections
Item Interval Description/Procedure
Conduct a visual inspection (look for signs of wear, deterioration,
or damage to wires, backshells, or connectors) of the 400W
Series unit and wiring harnesses to ensure installation integrity:
1. Inspect the unit for security of attachment.
400W Series
Unit
400W Series
Mounting Rack
400W Series
Mounting Rack
12 Months
12 Months
Every 2000
flight hours or
ten (10)
years,
whichever is
first
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.
Perform an electrical bonding test:
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.
Reinstall the 400W Series unit in the mounting rack
Conduct a visual inspection (look for signs of wear, deterioration,
Avionics
Cooling Fan
400W Series 190-01226-04 Rev. 2
Instructions for Continued Airworthiness Bell 206B Page 7 of 22
12 Months
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.
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