ARTEX PRODUCTS / ACR ELECTRONICS, INC
DESCRIPTION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL
C406-2 (453-5000), C406-2HM (453-5001)
570-5000 Rev. U
Company Confidential
25-62-11
Page 20 of 66
TASK 25-62-11-870-802
2.
Operation
SUBTASK 25-62-11-870-001
A.
Operational Overview
1)
See Figure 7.
Figure 7 ELT Operational Flow Diagram
2)
A primary feature of the C406-2 Series ELT is its simplicity of operation. As long as the ELT is
connected to the remote switch harness ELT connector, such that pins 5 and 8 are jumpered (G-
switch loop), it will activate in the event of a crash.
NOTE:
Neither the cockpit remote switch or the ELT local switch can be positioned in such a
manner as to prevent automatic activation when the ELT is connected properly.
3)
ELT operation is designed to prevent human error and misuse in regards to automatic activation. The
ELT cannot be activated by dropping, rough handling or during shipping.
4)
When the ELT is activated, the presence of the emergency sweep tone and the flashing cockpit
remote switch panel LED indicates an active, normal functioning ELT. The cockpit panel LED must
immediately begin to flash continuously upon ELT activation.
5)
The ELT is cons
idered to be either “ACTIVE” or “INACTIVE”. When “INACTIVE”, the ELT is in a state
of rest and performs no functions. Taking the ELT from the “INACTIVE” state to the
“ACTIVE” state
requires a positive switch transition from either the cockpit remote switch, ELT local switch, or G-
switch.
a)
It is possible the primary G-switch or one of the auxiliary G-switches could activate the ELT in
either a fixed or rotor wing aircraft as the result of severe maneuvers or a very hard landing.
b)
To take the ELT from an “ACTIVE” state back to an “INACTIVE” state, a “RESET” must occur. See
6)
A warning buzzer is required under C126 TSO approval. The buzzer is powered by the ELT and
therefore not dependent upon the aircraft battery for operation. It is not designed to operate
