Elt Installation; Elt And Bracket Installation Recommendations; Faa Recommendations; Tso C126A Section 5 B. Application Data Requirements - Kannad 406 AF-COMPACT Installation Manual

4. ELT Installation

A. ELT and bracket installation recommendations
The ELT shall not be installed within 60cm (2 ft) of a compass or flux gate.
The distance between ELT and antenna shall be determined so that, according
to the coaxial cable choosen, the cable lost should be ≤1dB at 400 MHz.
The ELT front panel should be easily accessible to connect the outside antenna
and the remote control panel device and to check the ELT good operation
(controls and lights).

(1)FAA Recommendations

Installation must be made by qualified personnel in accordance with FAA
regulations. Duplicating a previous installation may not be acceptable.
Refer to:
FAA - Advisory Circular 43.13-2A (Acceptable Methods, Techniques,
and Practices - Aircraft Alterations), specifically, Chapters 1, 2, 11
and 13.

(2) TSO C126a Section 5 b. Application Data Requirements

"The conditions and tests for TSO approval of this article are minimum
performance standards. Those installing this article, on or in a specific type
or class of aircraft, must determine that the aircraft installation conditions
are within the TSO standards. TSO articles must have separate approval
for installation in an aircaft. The article may be installed only according to
14 CFR part 43 of the applicable airworthiness requirements".

(3) RTCA DO-182 Recommandations

"All ELT system components which must survive to a crash intact,...should
be attached to the airframe in such a manner that the attachment system
can support a 100g load... in the plus and minus directions of the three
principal axes of the aircraft."

(4) RTCA DO-204a Requirements

"The ELT unit shall be mounted to primary aircraft load-carrying
structures such as trusses, bulkheads, longerons, spars or floor beams
(not aircraft skin) or a structure that meets the requirements of the
following test. The mounts shall have a maximum static local deflection
no greater than 2.5 mm when a force of 450 Newtons (l00 lbf) is applied
to the mount in the most flexible direction. Deflection measurements shall
be made with reference to another part of the airframe not less than 0.3
m or more than 1.0 m from the mounting location. Typical approaches for
adding shelf and rail platform mounting provisions to aircraft structure as
shown an FAA Advisory circular 43.13-2(), Chapter 2."
INITIAL INSTALLATION MANUAL
KANNAD 406 AF-COMPACT / KANNAD 406 AF COMPACT ER
PAGE: 8
SEP 16/2009