NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be
compatible with all previous alterations to
assure continued conformity with the aoolicable airworthiness reauirements.
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
BELL 412EP SIN 36106 N412SV PAGE 1 of 2
Removed the previously installed Garmin International Inc. GNS 530 VHF COM I VOR I LOC Receiver I GPS Receiver System. All
associated wiring, switches, circuit breakers and miscellaneous components are being incorporated in the Garmin International Inc.
GNS 530W VHF COM IVOR I LOC Receiver I GPS Receiver System installation listed below.
Installed 1 ea. Garmin International Inc. GNS 530W VHF COM I VOR I LOC Receiver I GPS Receiver System, Garmin Installation
Manual 190-00357-02, Rev. E, dated March 2008 (Referencing Garmin International STC SA01933LA).
The GNS 530W system consists of the following equipment:
1 ea. Garmin International Inc. GNS 530W (TSO C146a) at F.S. 28.0 in the same location where the standard GNS 530 was
removed from.
1 ea. Garmin International Inc. GA-35 GPS Antenna, (TSO C144) at F.S. 42.0 on cockpit roof using the existing provisions
left over from the GA56 Antenna removal.
Note: The Garmin International, Inc. GNS 530W GPS Navigation System in this installation is interfaced to Pilot's and Co-pilot's
Autopilot
I Flight Director along with the Pilot's AHRS. The Garmil"! International Inc. GNS 530W is also interfaced to the Transcal
SSD120 Blind Encoder to provide the necessary altitude encoder information and displays course information on the existing Pilot's
and
I or Co-pilot's HSI. The Garmin International Inc. GNS 530W Navigation. ~ystem in this installation is approved for VFR I IFR
navigation to include enroute, terminal and non-precision
instrument approa~hes, installed referencing AC 20-138A, paragraph 9
and evaluated under the criteria in paragraph Be (1) (ii) and has been shown to meet all of the applicable evaluation requirements
listed therein as well as those listed in AC 90-100A. In this installation, vertical navigation from the Garmin International, Inc. GNS
530W GPS is not enabled and the system is limited to LNAV only (reference the Rotorcraft Flight Manual Supplement listed below).
"FAA
A~oved Rotorcraft Flight Manual Supplement for Garmin International Inc. GNS 530W Navigation System", dated
5/20l.2008 was provided and must be maintained with the aircraft at all times. The Garmin International Inc. GNS 530W
Navigation System
was flight tested and it was determined the operation of the system was in accordance with the above listed
Flight Manual Supplement.
The Garmin International Inc. GNS 530W Navigation System was installed referencing the manufacturer's installation instructions;
AC 43.13-18 Change 1, Chapter 4, Paragraph's 4-38 and 4-57; Chapter 6, Section 3, Paragraph's 6-40; Chapter 7, Paragraphs 7-1a,
7-
1e, 7-2a, 7-2j,7-16, 7-64, 7-86, 7-87; Chapter 10, Paragraph 10-14 through 10-19; Chapter 11, Sections 3 through 17; Chapter 12,
Paragraph 12-10, 12-11, 12-14, 12-17, 12-18; AC 43.13-28; Chapter 1, Paragraph's 101 through 113; Chapter 2, Paragraph 203a, 207
through 210; and Chapter 3, Paragraph 301 through 310 along with AC20-138A, Paragraph 8(c) (1) (ii) (2) (3), also complying with
Paragraph's 15 through 20. The Garmin GNS 530W System has been shown to perform its intended function in accordance with FAR
29.1301 and it has been determined that the equipment is compatible with previous installations and all components were installed
in accordance with FAR 29.1309(c) to determine that the malfunction or failure of installed equipment has no adverse effects on
other aircraft systems. Performed EMI evaluation and interference tests in accordance with AC 43.13·1 B Chapter 11, section 8,
paragraph 11-106, & 11·107 for the installed equipment.
All Edwards
& Associates, Inc. drawings were developed from each piece of the equipment manufacturer's installation instructions I
schematics along with BHT's aircraft wiring schematics and were provided to the aircraft's owner I operator.
It has been determined that the electrical load of the aircraft does not exceed 80% of the rated generator capacity. The aircraft was
weighed and a new weight and balance computed. The aircraft's flight manual equipment list was revised. Provided Instructions for
Continued Airworthiness (ICA), as part of this FAA Form 337, as addressed by FSIMS Flight Standards Information Management
System 8900.1, Volume 4, Chapter 9, Section 1 and using the checklist in Chapter 9, Section 1 and Figure 4-66. The ICA contained in
this FAA Form 337 is now part of the aircraft's inspection/maintenance requirements. Log book entry was made.
Reference: W/0 C10223EA/1. ···END···
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1. INTRODUCTION: The Bell Model 412EP is a FAR Part 29 Category B certified helicopter. The above listed modification is for the
installation of optional equipment installed in accordance with this field approved FAA Form 337.
2. DESCRIPTION: The Garmin International Inc. GNS 530W is a panel mounted VHF COM I VOR I LOC Receiver I GPS Receiver
System with a GPS based navigation database.
3. CONTROL, OPERATION INFORMATION: Reference the "FAA Approved Rotorcraft Flight Manual Supplement for Garmin GNS
530W VHF COM Transceiver I VOR I ILS Receiver I GPS Receiver", listed in section 8 of this FAA Form 337 along with Garmin
International Inc. GNS 530W Pilot's Guide, P/N 190-00357-00, Rev. B, dated September 2007 or later appropriate revision for detailed
operating instructions.
4. SERVICING INFORMATION: Reference the applicable manufacturer's installation instructions along with the EA drawing listed
above.
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