ACR&Artex ELT to Nav Interface - Manual (Page 42)

ARTEX PRODUCTS / ACR ELECTRONICS, INC.
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
453-6500
25-69-10
Page 42 of 58
APR 30/12
SUBTASK 25-69-10-990-006
F. RTCA
(1) DO-204, § 3.1.8 guidelines for mounting a ELT:
(a) The ELT shall be mounted to primary aircraft load carrying structures, such as trusses,
bulkheads, longerons, spars, or floor beams.
(b) The mounts shall have a maximum static local deflection no greater than 0.1 inches (2.5
mm) when a force of 100 lbs (450 newtons) is applied to the mount in the most flexible
direction. Deflection measurements shall be made with reference to another part of the
aircraft not less than 1 foot (0.3 meters) nor more than 3 feet (1.0 meters) from the
mounting location.
(2) DO-182, § 6.2.2.b recommends that:
(a) To maximize the probability of the ELT transmitting a detectable signal after a crash, all
ELT system components, which must survive a crash intact, e.g., transmitter and
external antenna, should be attached to the airframe in such a manner that the
attachment system can support a 100 g load, (ELT weight x 100, ELT antenna weight x
100, etc.) applied through the center of gravity of the component (ELT, antenna, etc.) in
the plus and minus directions of the three principal axes of the aircraft.
(b) Post-crash critical components of the ELT system, e.g., transmitter and external
antenna, should be mounted as close to each other as possible.