Page 3-6
Installation Instructions
TQG191-IM
Rev 0: 28 Feb 2019
KTX2
Installation Manual
SECTION 3
INSTALLATION INSTRUCTIONS
3.1 INTRODUCTION
This section provides installation information for the KTX2 ADS-B Transponder System.
Installations must be made by qualified personnel in conformance with applicable government
regulations.
3.2 LIMITATIONS
1. The KTX2 transceiver must use an L-Band antenna meeting the requirements
specified in paragraph 2.6.2.
2. The KTX2 must use a GPS source meeting the requirements in paragraph 2.6.1.
3. It is the installer’s responsibility to follow the installation instructions in order to ensure
that the ADS-B Out system is compliant with AC 20-165A, 14 CFR 91.225 (b) and
91.227.
3.3 INSTALLATION PROCEDURES
1. The installer must take the following into consideration prior to installation:
• Follow the FAA approved AML STC installation instructions.
• Ensure the units are properly unpacked and inspected per paragraph 2.2.1.
• Follow the acceptable avionics installation practices in FAA Advisory AC 43.13-2B or
later revisions to this document.
• Installers are responsible for obtaining installation hardware (i.e. screws, supporting
plates, etc). Installation kits may be available for purchase. Refer to the Equipment
Required Not Supplied, paragraph 2.5.
• It is recommended that the aircraft battery be disconnected before performing
installation procedure.
• L-band and GPS antenna cables should be clearly labeled to prevent inadvertently
installing on the wrong connector.
• Tighten all screws to snug (i.e. only such torque that can be applied by hand) unless
specific torque instructions are given.
• After installation, refer to the Installation Checkout section for calibration, power-up
and ground testing procedures.
2. Electrical equipment chassis, shield/ground terminations, antennas, supporting brackets,
and racks must be electrically bonded to the aircraft's main structure (metallic aircraft) or
instrument panel (composite aircraft). Compliance of the electrical bonding should be
verified by inspection using a calibrated milliohm meter. An equivalent OEM procedure
may also be substituted.
• The electrical bond should achieve direct current (DC) resistance less than or equal to
2.5 m
W
to structure local to where the equipment is mounted for metallic aircraft or tube
and fabric aircraft.
• The electrical bond should achieve direct current (DC) resistance less than or equal to
5.0 m
W
to the instrument panel for composite aircraft.
3. The antenna ground plane must be electrically bonded to the antenna baseplate. Do not
