NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alte,ation must be
compatible with all
previous alterations to assure continued conformitv with the applicable 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 SIN 36106
N412SV
PAGE 1 of 3
Installed 1 ea. Honeywell International, Inc. KMD 550/850 Multi-Function Display System; [(TSO C113, TSO C110a) (Reference:
Honeywell International Inc. STC SA00920WI-D for previously approved data)]; at F.S. 22.0 in the left side instrument
panel using 2
ea. 202413 .040" brackets attached with "AD" rivets and "MS" hardware referencing the Bendix/King KMD 550/850 Multi-Function
Display System Installation Manual 006-10608-0010, Rev. 10, dated July 2004 with wiring performed in accordance with EA DWG #
AV-07-8119.
Note: The primary function of the Honeywell International, Inc. KMD 550/850 in this installation is to be the
Controller/Display/Indicator for the previously installed Honeywell International, Inc. RDR 2000 Weather Radar System. The
Honeywell International, Inc. KMD 550/850 is also interfaced to the Garmin International, Inc. GNS530 Navigation System and the
aircraft heading system. The Bendix/King KMD 550/850 Multi-Function Display Pilot's Guide PIN: 006-18222-0000, Rev 6
1
dated June
2004, the KMD 550/850 Multi-Function Display Weather Radar Guide P/N 006-18235-000 Rev 3, dated June 2004, and the KMD 550/850
Multi-Function Display Traffic Addendum PIN 006-18238-0000, Rev 3, dated June 2004 were all provided to the aircraft
owner/operator for detailed operating instructions.
Removed the factory installed Honeywell International, Inc. KXP 756 Mode S Transponder System to include the Transceiver and
Mount from F.S. 12.0
I - 24.0 on the upper nose avionics shelf and the Control from F.S. 45.0 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 ine:orporated in the
Garmin International Inc. GTX 330 Mode S Transponder System installation listed below.
Installed 1 ea. Garmin International Inc. GTX 330 Mode S Transponder, {(TSO C112, JTS0-2C112a) (previous approval basis STC No.
01125WI)} at F.S. 34.0 in the avionics slant console pedestal secured in accordance with EA Fabrication
Follower# FF-412-36-GPS
using standard "MS" hardware. The GTX 330 uses the existing transponder antenna from the removed KXP 756 system listed above.
The installation was completed referencing Garmin International, Inc. Installation Manual 190-00207-02, Rev. F, dated March 2004
with wiring in
accorda,w,Qzwj.th~,\~G # AV-07-3018. "FAA Approved Flight Manual Supplement for Garmin GiTX 330 Mode S
Transponder", dated
LUU
~
, NI II was provided and must be maintained with the aircraft at all times. The Garmin GTX330
Transponder System was flight tested and it was determined the operation of the system was in accordance with the above listed
Flight Manual Supplement.
Installed 1 ea. Trans-Cal Industries, Inc. SSD120 Altitude Encoder, (TSO C88A), at F.S. - 9.0 in the aircraft nose avionics bay on a
202413 .090" angle bracket attached to the existing avionics shelf using potted inserts, P/N 80-005-2 and
"MS" hardware referencing
Bell Helicopter Textron Structural Repair Manual, BHT-MED-SPM-1 along with Transcal Industries, Inc. Owner/Installation Manual
Doc.# 930005, Rev. I, dated 18 August 2005. All wiring was performed in accordance with EA DWG # AV-07-3018.
Note: The Trans-
Cal Industries, Inc. SSD120 Encoder is plumbed to the pilot's pitot
I static system.
Removed the previously installed Garmin International Inc. GDL ™ 49 Weather Data Link System to include the data link unit and the
antenna. All associated wiring, switches and circuit breakers were removed from the aircraft and the system is being replaced with
the Garmin International Inc. GDL ™ 69 XM Radio/Weather Data Link System installation listed below.
Installed 1 ea. Garmin International Inc. GDL
TM 69 XM Radio/Weather Data Link System referencing Garmin International Inc.
Installation Manual 190-00355-02, Rev. E, and dated May 2006 with wiring performed in accordance with EA DWG # AV-07-8115. The
system is interfaced to the installed Garmin International Inc. GNS 530 referencing Garmin International Inc. lnstallaltion Manual 190-
00181-02, Rev. R, dated November 2006 and EA DWG # AV-07-5037. The GDL
™ 69 system is a remote-mounted satellite data link
transceiver which provides data communication between Garmin International Inc. 400/500 Series unit and the Echc, Flight Message
service over the ORBCOMM low earth orbit (LEO) satellite constellation. The Echo Flight Message service provides NEXRAD and
METAR data from the National Weather Service and a position tracking subscription service by Echo Flight. The Garmin
International Inc. GDL
TM 69 System installation consists of the following equipment:
1 ea. Garmin International Inc. GDL™ 69 XM Radio/Weather Data Receiver, P/N 011-00987-00, (RTCDA D0-160D) at F.S. 4.0
on the nose avionics shelf in the location where the above listed GDL
TM 49 was removed from using "IMS" hardware.
1 ea. Comant Industries, Inc. GX-55 XM/Weather Antenna, located at F.S. 45.0 on the aircraft roof secured! using a 202413
.040" internal doubler and "MS" hardware.
Removed the factory installed Honeywell International, Inc. Radar Altimeter System. All associated wiring, switc:hes and circuit
breakers were either removed from the aircraft, capped and stowed, or are being incorporated in the Honeywell International, Inc.
AN/APN-209 Radar Altimeter installation listed below. Installed 2 ea. 202413 .063" blanking plates to cover the holes left from the
removal of the radar altimeter antennas.
Installed 1 ea. Honeywell International, Inc. AN/APN-209 Radar Altimeter, P/N HG7209AD02 at F.S. 23.0 in the pilot instrument panel
with 1 ea. Honeywell International, Inc. "slave" Radar Altimeter Indicator, P/N A3060591 at F.S. 22.0 in the copilot instrument panel.
All wiring was performed referencing EA DWG # AV-07-7152.
Installed 2 ea. Sensor Systems Radar Altimeter Antennas, PIN 071-01501-0000 at F.S 0.0
I± 10.0 on the lower nose inspection panel
using 2 ea. 202413 .040" doublers and "MS" hardware.
Instructions for Continued Airworthiness contained on page
2 and 3 of this FAA Form 337.
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