Ameri-King AK-451-ELT - Manual (Page 26)

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Note:
Installation in a pressurized aircraft constitutes a major modification. Consult the
Department of Transportation Regional Officer before proceeding.
Note:
Aircraft manufacturers may also have guidance on ELT installation; refer to and
follow any applicable Type Approval or STC data for your aircraft. If located outside
of the US, follow all applicable regulations for your national authority.
By signing either the aircraft logbooks or the FAA Form 337, you are stating that the
installation has been performed in accordance with the current FARs and with the
steps and procedures outlined herein.
In Canada, all installations must be performed in accordance with the Engineering
and Inspection Manual Part II, Chapter III, Section 3.12.
Remember: Your Professional installation may save someone’s life.
2.2.1
ELT MAIN UNIT LOCATION AND INSTALLATION
2.2.1.1 ELT LOCATION DETERMINATION:
Many of the original ELT installations are inadequate as far as unit location and
surface rigidity are concerned. Just because the “old” ELT was located in a particular
position doesn’t mean the “new” ELT should be located there as well.
The tail section of an airplane is least likely to be damaged during a crash and
therefore, it provides a good mounting environment for the ELT unit. Refer to Figure
1 for Direction Determination for Fixed Wing Aircraft and Helicopter, respectively.
Accessibility of the unit is an important factor in the location of the ELT. Mount the
unit as far aft as practical but where it can be easily retrieved for maintenance.
The mounting surface must be extremely rigid; therefore, mounting the ELT directly
to the aircraft skin is unacceptable.
Mounting an ELT directly to the aircraft skin induces “crash hiding” vibration and
provides a very poor structural mounting surface. The mounting location must be
able to support 100 pounds of force in any direction with no appreciable distortion in
the structure. It must also be able to withstand a 350-pound force in any direction
without tearing or breaking the aircraft structure.
Please refer to FAA AC 43.13 for guideline.