89000046-014 KSN 780/8XX/900 AeroNav AML STC Installation Manual for Helicopters
Rev 0 Page-3-1
© Honeywell International Inc. Do not copy without express permission of Honeywell.
3. Antenna Installation
This section describes the installation of the GPS, NAV, and Glideslope antennas on unpressurized,
metallic fuselage helicopters. The installer is responsible to ensure the structural aspects of the
installation meet all regulatory requirements and are adequate for the aircraft type. Antenna
installations on helicopters are beyond the scope of this manual and a separate installation approval
is required.
3.1 Antenna Bonding
All antennas should be well bonded to the aircraft. Reference AC 43.13-2b paragraph 307 for
additional information.
3.2 Antenna Environmental Qualifications
Verify the antenna is appropriately qualified to be installed on the aircraft. Reference the antenna
manufacturer’s RTCA DO-160(x) qualification form.
3.3 GPS Antenna
The GPS Antenna should be installed using practices acceptable to the antenna and aircraft
manufacturers. Regulatory guidance for antenna installations can be found in AC 20-138( ) Chapter
12, AC 43.13-2B Chapter 3, and AC 43.13-1B Chapter 4. Also reference Appendix B: STC Permissions
in this manual.
The GPS antenna listed in Table 28 can be installed on unpressurized metal helicopters using the data
below. All other GPS Antenna installations are beyond the scope of this manual and a separate
installation approval is required.
The Avidyne GPS antenna, Avidyne Part Number 200-00282-000, can be installed as shown in Figure C
- 5 through Figure C - 9. The GPS Antenna must be installed using the following guidelines to be in
compliance with the STC.
GPS Antenna Location:
• Fuselage skin must be 2024-T3 aluminum (or equivalent)
• Fuselage skin thicknesses beyond the range provided in Table
33Table
33 below are outside the scope of this installation
• Selected antenna location may not be within one full bay of other
cutouts, skin joints, or load introduction points
• Doubler installation on, or adjacent to, primary or fatigue critical
structure, as defined by the aircraft manufacturer or regulatory
guidance, requires separate approval
• Evaluate the installation per AC43.13-2B, Chapter 3, paragraph
303(b) for gaps due to fuselage curvature. If a saddle is required,
fabrication should be per AC 43.13-1B, and should completely fill
the curvature gaps, and should not be riveted to the fuselage skin.
The only purpose of the saddle is to act as a tapered shim and is
not intended to transfer load into the skin
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