Antenna Installation; Antenna Bonding; Antenna Environmental Qualifications; Gps Antenna - Avidyne IFD540 Installation Manual

3. Antenna Installation

This section describes the installation of the GPS, NAV, and Glideslope antennas on
unpressurized, metallic fuselage airplanes. 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 airplanes with composite or pressurized fuselages,
and aircraft with certification basis of Amendment 23-45 or later, 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 C
in this manual.
The GPS antenna listed in Table 14 can be installed on unpressurized metal airplanes with a
certification basis of Amendment 23-43, or earlier, 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 200-00260-000, can be installed as shown
in the following Figures in Appendix C: Figure C - 35, Figure C - 36, and Figure C - 37. 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
Fuselage skin thicknesses beyond the range provided in
Table 19 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
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IFD5XX Installation Manual
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