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Thought I'd share an issue and resolution from a recent incident

Rotax 915is, ~500 hours.

Lane A solid light came on during a routine flight.  Rough running symptoms for about 2 seconds before the light.  Landed nearest airfield

FADEC page showed ignition/injector driver error and Cylinder 2 EGT fault

Had to leave the plane overnight - no time for in-depth diagnostic

Next day, most engine instruments were x'd out on G3X EFIS: Manifold pressure, RPM, oil pressure, oil temp, coolant temp, EGTs, fuel flow and FADEC data all unavailable

Engine ran normally on lane B, very rough on lane A

Diagnosed the cylinder 3 was not firing on bottom plug.  Inspection and swap of plug, boot, and wires yielded no change.

After lots of dead-ends, finally replaced the coil, which eliminated the rough-running problem.  The failed coil had tight connections with both plug wires.  This wasn't the first route of thinking as normally 2 cylinders would fail from a bad coil, but only cyl 3 was failing.

Engine instruments still not working.  Replaced the Garmin GEA24B with a loaner, all instruments came back.

This is the second incident I'm aware of where a failed coil and failed GEA24B occurred together.  Not sure how it's related, but I don't think it's a coincidence.  This engine has the old-style connectors on the coil.  

 

  • Re: ignition coil and Garmin GEA24B failure

    by » 11 hours ago


    a while ago I posted on this forum that the Fastenal clips were faulty on my engine which caused a lane error. The coils were good. The spark plugs were good. They were just loose and the fix from an instructor was claimed to be not good, but my engine has run flawlessly since with no other replacements other than than the fix


  • Re: ignition coil and Garmin GEA24B failure

    by » 7 hours ago


    Charles,

    Do you have the shield for the Rotax CAN bus grounded at both ends?  Most of the time the thinking is to ground the shield at least at one end, but both is preferable.  However, since the airframe and Rotax engine electrical systems are fully isolated from each other (both positive and ground), it seems to me that if you land the shield at both ends it ties the airframe and engine grounds together across the shield. This can create a ground loop and associated stray currents.  So I believe that when considering the shield grounding between the GEA-24(b) and the Rotax ECU then only the Garmin end should be grounded at the back shell.  The Garmin wiring diagrams are ambiguous regarding this.   


    Also, if you are connecting CAN A and CAB B to the GEA-24B independently, you need to have the 120 ohm resistor across the CAN-lo and CAN-hi terminals for each termination at the GEA-24(b).  The resistor is built into the ECUs on the Rotax end. Once fully installed, there should always be 60 ohms across the CAN-Lo and CAN-hi terminals.


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