7 Flashes – Indicates that the ELT battery has too much accumulated operation time (> 1hr). Battery may still power ELT; however, it must be replaced to meet FAA specifications. May also indicate damage to the battery circuit.
2.8.2 Self-Test Schedule
Artex recommends that the ELT be tested every 1-2 months. Follow the steps outlined above.
NOTE: the self-test time is accumulated in a register on the battery pack. The register records activation time in 30 second increments so all activations will count as at least 30 seconds, even if the actual time is much less. Total allowable time is 60 minutes as determined by FAR 91.207 and RTCA DO-204. After this time has been accumulated a 7-flash error will be presented after the self-test. The battery must be replaced at this point for the ELT to remain in compliance. Always follow ELT testing requirements per local or national authorities.
2.9 Sealing Connectors in Wet Environments
This step is optional. Once all tests have satisfactorily been completed and all harness connections have been verified to be correct, the connectors at the remote cockpit switch and the ELT may be sealed to help prevent moisture from wicking into the connector pins.
Seal using an electronics grade (‘neutral cure’), non-slumping RTV such as GE Silicones RTV162, Dow Corning 748RTV or Silastic 1080RTV. (Sourcing hint: Check pet stores that sell aquariums.)
Caution!
Non-electronics grade RTV may cause corrosion of the electrical wiring.
The curing chemicals of some types of RTV contain a type of acid which will corrode the copper wiring. This corrosion may cause failure of the wiring hhkl
Apply RTV to the rear of the 9-pin connector remote switch (Artex P/N 151-5009), forcing the sealant into the wire holes and around exposed wire ends.
Disassemble the harness D-sub connector and cover exposed wire ends and all connector pins with RTV. Coat all exposed metal, taking care to keep away from the thumb screws. Reassemble after sealing.
2.10 Helicopter Installations
The ME406P incorporates six G-switches which sense a crash impulse along each of the three main (orthogonal) axes of the ELT. The ‘direction of flight’ arrow on the ELT product label represents the direction in which the primary crash sensor is oriented. Mount the ELT so that the arrow aligns with the longitudinal axis of the aircraft. If necessary, the ELT may be tilted forward up to 10 degrees (see Figure 14). The ELT mount may be rotated about the aircraft center axis, i.e. the ELT can be mounted on the floor, walls or over head, so long as it ‘points’ to the front of the aircraft.
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