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 requirements.
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 5/N 36106 N412SV PAGE 1 of2
Removed the previously installed Garmin International Inc. GPS 500 System. All associated wiring, switches, circuit breakers and
miscellaneous components were either removed from the aircraft or are being incorporated in the Garmin International Inc. GNS
530 VHF COM IVOR
I LOC Receiver I GPS Receiver System installation listed below.
Removed the factory installed Honeywell International, Inc. KTR 908 VHF #1 COMM System to include the Transc1!iver and Mount
from F.S. 10.1 I - 7.8 on the nose avionics shelf and the Control from F.S. 39.0 I - 4.3 in the aircraft slant console pedestal. All
associated wiring, switches, circuit breakers were either removed from the aircraft or are being incorporated in the Garmin
International Inc. GNS 530 VHF COM IVOR I LOC Receiver I GPS Receiver System installation listed below.
Removed the factory installed Honeywell International, Inc. KNR 634 #1 NAV System to include the Transceiver and Mount from F.S.
10.1 I - 16.0 on the nose avionics shelf and the Control from F.S. 42.0 I - 4.3 in the aircraft slant console pedestal. All associated
wiring, switches and circuit breakers were either removed from the aircraft or are being incorporated in the Gam1in International
Inc. GNS 530 VHF COM IVOR I LOC Receiver I GPS Receiver System installation listed below.
Installed 1 ea. Garmin International Inc. GNS 530 VHF COM I VOR I LOC Receiver I GPS Receiver System, (Reference: Garmin
International Inc. STC No. SA00864WI) referencing Garmin International Inc. Installation Manual 190-00181-02, Rev. R, dated
November 2006 with wiring performed in accordance with EA DWG # AV-07-5037.
The GNS 530 system consists of the following equipment:
1 ea. Garmin International Inc. GNS 530 (TSO C129a Class A (1)) at F.S. 30.0 in the avionics slant
consol1:i pedestal using
"MS" hardware. The installation of the Transceiver unit was performed in accordance with EA Fabricatic1n Follower# FF-
412-36-GPS.
1 ea. Garmin International Inc. GA-56 GPS Antenna, (TSO C129 CLASS A1) at F.S. 30.0 on cockpit roof using a 2024T3 .050"
doubler picking up the existing stiffeners using "MS" hardware.
Note: The Garmin International, Inc. GNS 530 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 Garmin International Inc. GNS 530 is also interfaced to the Transcal
550120 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 530 Navigation System in this installation is approvE!d for VFR I IFR
navigation to include enroute, terminal and non-precision instrument approaches, installed referencing AC 20-138A, paragraph 9
and evaluated under the criteria in paragraph
Sc (1) (ii) and has been shown to meet all of the applicable evaluation requirements
listed in FSAW 94-32C, Paragraph 4(A) and 4(8) as well as those listed in AC 90-100A.
"FAA
~p9eoxe<J. B,o,torcraft Flight Manual Supplement for Garmin International Inc. GNS 530 Navigation System", dated
JUl'L Z
~
Z0Ut was provided and must be maintained with the aircraft at all times. The Garmin lnternatio11al Inc. GNS 530
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 530 Navigation System was installed referencing the manufacturer's installation instructions; AC
43.13-18 Change 1, Chapter 3, Section's 1 & 2; Chapter 4, Section's 1 & 4, Paragraph's 4-50 through 4-58; Chapter 6, Section's 1 & 3,
Paragraph's 6-29, 6-30 and 6-40; Chapter 7, Section's 1 through 7 and Section 11; Chapter 10; Chapter 11; Chapter 12; and Chapter
13; AC 43.13-2A; Chapter 1, Paragraph's 1 through 11; Chapter 2; and Chapter 3, Paragraph 36 through 44 along
with AC20-138A,
Paragraph 8(c) (1) (ii) (2) (3), also complying with Paragraph's 15 through 20. The Garmin GNS 530 System has been shown to
perform its intended function in accordance with FAR 27.1301 and it has been determined that the equipment is compatible with
previous installations and all components were installed in accordance with FAR 27.1309(c) to determine that
th1! malfunction or
failure of installed equipment has no adverse effects on other aircraft systems.
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.
An electrical load analysis was completed and it has been determined that the electrical load of the aircraft does nc1t 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
FAA Airworthiness Inspector's Handbook 8300.10, Volume 2, Chapter 1, Section 1 and using the checklist in Chapter 1, Section 2
and Figure 1-1. This ICA is now part of the aircraft's inspection/maintenance requirements. Log book entry was made. Reference:
W/0 C07268EA/2. --- 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 530 is a panel mounted VHF COM IVOR
I LOC Receiver I GPS Receiver System
with a GPS based navigation database. The Garmin International Inc. GNS 530 Navigation System in this installation is approved for
VFR I IFR navigation to include enroute, terminal and non-precision instrument approaches as described in AC20-138A and meets
the requirements described in AC 90-100A.
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