Specifications

In Can ada, all in stal la tions must be
per formed in ac cor dance with Ca na-
dian Avi a tion Reg u la tions (CAR) Part
V, Subparts 37, 51 and 71.
3.1. ELT Mount ing Lo
-
ca tions
Many orig i nal ELT in stal la tions are in-
ad e quate as far as unit lo ca tion and
sur face ri gid ity are con cerned. Just
be cause the “old” ELT was lo cated in
a par tic u lar po si tion does n’t mean the
“new” ELT should be lo cated there.
Sta tis tics show that the tail sec tion of
an air plane is least likely to be dam -
aged dur ing a crash and, there fore,
pro vides a good mount ing en vi ron ment
for the ELT unit.
Ac ces si bil ity of the unit is an im por-
tant fac tor in the lo ca tion of the ELT.
Mount the unit as far aft as prac ti cal,
but where it can be eas ily re trieved
for main te nance.
The mount ing sur face must be ex -
tremely rigid, there fore, mount ing the
ELT di rectly to the air craft skin is un -
ac cept able.
Mount ing an ELT di rectly to the air -
craft skin in duces “crash hid ing” vi bra
-
tions and pro vides a very poor struct-
ural mount ing sur face. The mount ing
lo ca tion must be able to sup port 100
pounds of force in any di rec tion with
no ap pre cia ble dis tor tion in the struc
-
ture.
The fol low ing are the FAA guide lines
for mount ing an ELT (per RTCA
DO-183 Sec 3.1.8)
•
“The ELT shall be mounted to pri mary
air craft load car ry ing struc tures such as
trusses, bulk heads, longerons, spars,
or floor beams.”
ARTEX AIRCRAFT SUPPLIES DOCUMENT #570-5000
04/11/01 PAGE 3-3
#8FLATWASHER
(4PLCS)
8-32x5/8SCREW
(4PLCS)
8-32x1/4HEXNUT
(4 PLCS)
#8LOCKWASHER
(4PLCS)
AIRFRAME
EQUIPMENT
MOUNTINGPLATE
FIG URE 3-2 MOUNTING TRAY IN STAL LA TION