Today's Message Index:
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1. 07:45 AM - I guess it _really_ matters... (prestonkavanagh)
2. 10:02 AM - Re: I guess it _really_ matters... (1rv4)
3. 02:34 PM - Re: I guess it _really_ matters... (Ceengland)
4. 02:54 PM - remove (Jerry Latimer)
Message 1
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| Subject: | I guess it _really_ matters... |
Saw this, thought it worth sharing....
Loose Connection Leads To Crash
By General Aviation News Staff January 13, 2026 13 Comments
According to the pilot, the flight in the experimental Raptor Junior 540 departed
Santa Monica Airport (KSMO) in California, en route to Camarillo Airport (KCMA),
in Camarillo, California, to conduct touch-and-go landings.
About five miles southeast of KCMA, he noticed a warning indication on the airplanes
avionics display alerting him to a loss of electrical power. He stated that
within seconds, the entire display, excluding the Dynon Primary Flight Display,
which had a backup battery, went blank, followed by a total loss of engine
power.
He performed emergency procedures to restore electrical and engine power but was
unsuccessful.
He performed a forced landing to an agricultural field about 4.5 miles southeast
of KCMA, during which the airplane sustained substantial damage. The pilot was
seriously injured in the crash, while a passenger sustained minor injuries.
The airplane was equipped with an electronic fuel injection and ignition system,
manufactured by EFII Systems. Electrical system redundancy was accomplished
by use of a main and auxiliary system, with two independent batteries and an alternator.
The system shared a common ground line that connected the negative
terminals for both batteries and was routed through a ground bus located behind
the nose cone bulkhead to the engine compartment and engine case.
Post-accident examination of the wreckage revealed that the ground feed-through
stud that connected the battery ground terminals to the ground bus was loosely
connected on the nose cone bulkhead. The feed-through nut was 3.5 turns loose,
which corresponded to approximately 3.5 threads of the feed-through stud.
Additionally, neither a spring lock washer nor a secondary locking nut were present
on the feed-through stud assembly, as was found on all other primary electrical
connections throughout the airplane.
Probable Cause: A total loss of engine power due to the loss of power to the electronic
fuel injection and ignition system, which was the result of a loose connection
between a common ground feed-through stud and the ground bus.
NTSB Identification: 193732
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PBK3
PA-12, BD-4, RV6a, gliders, Rutan canards
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Message 2
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| Subject: | Re: I guess it _really_ matters... |
Just wondering why the alternator wouldn't still carry the load ? Wouldn't it be
frame grounded?
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Message 3
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| Subject: | Re: I guess it _really_ matters... |
Problem is, we can't see the entire wiring diagram, nor the physical layout. If
the controller was on the other side of that ground pass-through stud, then the
electrons couldn't make a complete round trip even if the alternator is working
properly.
--------
Charlie
Read this topic online here:
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Message 4
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Please remove my name from forum
Jerry
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