ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
ME406 (453-6603), ME406HM (453-6604)
Page 43 of 72
Mar 19/15
25-62-30
completed Form 337 is provided to the FAA and also becomes a permanent part of the aircraft
maintenance records in accordance with AC43-9, Paragraph 17.
SUBTASK 25-62-30-990-004
D.
Canada
1)
All installations must be performed in accordance with Canadian Aviation Regulations (CAR) Part V,
Chapter 551, Paragraph 551.104.
SUBTASK 25-62-30-990-005
E.
Other Countries
1)
Installations in aircraft outside of the United States and Canada, must be performed in accordance with
applicable regulatory authority rules and regulations.
SUBTASK 25-62-30-990-006
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.
c)
The antenna coax cable should not cross any production breaks, e.g., major structure sections, such
that the ELT and antenna are in the same section of the aircraft and as close together as possible.
d)
If the ELT and external antenna are on opposite sides of an airframe production break, the
components should be secured to each other by a tether that can support a 100
g
load (ELT weight
x 100). The interconnecting antenna-to-ELT coax cable should have sufficient slack on both ends
that it will not be subjected to any tensile load and should be tied loosely to the tether.
