Commercial In Condence
Issue 17 - 11.04.18 - CN 10407
HRS1013-04-02
3.2 Inhibit Connection
To inhibit the ELT system, Pins 10, 11 or 12 on the G-Switch are connected to ground
(aircraft chassis). This is achieved via a separate switch, available on the 503-51,
which allows the inhibit function or normal operation to be selected.
4. SERVICING
The sealed for life construction, and Built in Testing, limits the servicing that is required, or
necessary, to maintain the beacon in a fully serviceable state.
The periodicity of servicing set out below is a recommendation and can be varied to suit
the type of operational use and operating conditions.
4.1 Physical Inspection
It is recommended that the ELT system is inspected for damage at the following
periodicity.
Antenna - Daily
Control Unit - Monthly
Emergency Locator Beacon - 3 months
4.2 Battery Replacement
The ELT battery must be changed every 5 years or sooner, if the ELT has been
used for any other purpose than the Built in Test.
The G-Switch battery must be changed every 2.5 years, and has a storage life of 5
years.
4.3. Troubleshooting
The ELT system consists of a sealed for life ELT beacon complete with battery.
An additional G-Switch and remote controller switch are included to enable the ELT
to be switched to ON either on impact or by the aircrew.
Since the ELT has an in built test system and the test function can be activated at
the ELT and at either of the two switches, the system can be tested.
A test failure at the remote control switch indicates a switch failure, a G-Switch
failure, a wiring failure or an ELT failure. A test at the ELT beacon will indicate the
status of the beacon. If a fail then replace the beacon, if a pass then test the switch
and wiring loom.
A test failure from the G-Switch test switch shows the fault condition to be in the
G-Switch or ELT.
A test at the ELT will indicate pass or fail. Fail will indicate a faulty ELT, a pass
indicates a faulty G-Switch
The testing of the remote controller switch is a simple continuity test and the ELT
itself cannot be tested other than the built in test. The G-Switch is electrically tested
by inducing an overload condition into the solid state ‘G’ switches. If such a failure
occurs then the G-Switch should be replaced.
If using the 503-51, a BIT failure is indicated by the FAULT lamp illuminating.
4.4 Diagnose mode
This mode is used when a G-Switch/ELT system has failed its self-test and been
removed from the aircraft, and is useful to an operator to indicate what part of the
system has failed.
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