INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG
KANNAD 406 AF / AF-H / AF (6D)
PAGE: 201
JUN 23/2008
INSTALLATION / REMOVAL
1. RTCA / FAR recommendations
"The conditions and tests required for TSO approval of this ELT are minimum
performance standards. It is the responsibility of those desiring to install this
ELT on a specific type or class of aircraft to determine that the aircraft
installation conditions are within the TSO standards. The ELT may be installed
only if further evaluation by the applicant documents an acceptable installation
and it is approved by the Administrator". (TSO-C91a)
"The ELT must be attached to the aircraft in such a manner that the probability
of damage to the transmitter in the event of a crash impact is minimized."
(FAR 91.207)
"The ELT shall be mounted to primary aircraft load-carrying structures such as
trusses, bulkheads, longerons, spars, or floor beams (not aircraft skin). The
mounts shall have a maximum static local deflection no greater than 2.5 mm
(0.1 inch) when a force of 450 Newton (100 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 meters (1 foot) nor more than
1.0 meter (3 feet) from the mounting location." (RTCA-DO183)
The ELT should not be installed at less than 60 cm (2 ft) of a compass or flux
gate.
Use cable of loss
≤
1dB.
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).
If no remote control is used, "ELT controls and displays installed for in-flight use
shall be readily accessible from the pilot's normal seated position. The pilot
shall have an unobstructed view of displayed data when in the normal seated
position." (RTCA DO-183).
Only PART / FAR 145 certified service stations can install the KANNAD
406 AF / AF-H / AF (6D) ELT.
