Mike identified it as Q-Talk #87 in the previous post.
I actually had less than 300 hours on the plane at the time now that
I think about it.
--- In Q-LIST@..., REBECCA SIMPSON
How do I get a copy of the article and pics ?
Jim Patillo <logistics_engineering@m...> wrote:
My spar had about 300 hours on it when it failed. When I originally
jigged and put the spars together, I looked them over very
and did not see any sign of stress or cracks. They looked perfect.
After I talked with Scott Swing, the guy who load tested spars for
QAC, I feel confident their testing proceedure was flawed and
my problem. I believe there are other bad spars out there in flying
airplanes but will only surface if the spars were aligned like
How long that will take I cannot say.
I believe some spars were over stressed (due to a bad load test
fixture)when tested and are predisposed to failure. I belive there
are stress risers on some spars. Since there were no alignment
markings on the spars indicating top from bottom (after being
one can randomly place the stress riser in the position I did and
failure will occur.
I will say again, it is very important to monitor the areas just
under pilot and pax legs at the radius. That is the approximate
location where the failure can occur. If you notice the slightest
mark in those areas, ground the airplane and check it out
immediately. My crack appeared so small on the surface that it
have been easily overlooked. Once I opened it up for investigation
was glad I did. Read the article I wrote. MAKE SURE TO CHECK LS1
SPARS ON A REGULAR BASIS!
Some may say the failure will only occur on the ground like mine
James' did but that may not be true.
Jim Patillo N46JP Q200
--- In Q-LIST@..., Mike Perry <dmperry1012@c...> wrote:
I haven't seen any comments on the list since James Postma posted this
report, but I think we need to discuss it. This is apparently a spar
failure similar to what Jim Patillo found at annual in 2001 (Q-
87). As Jim elegantly documented, the spars may have been
the testing process, leaving a weakened area around BL12 in some spars --
likely only a few spars, but still a concern.for some
My questions are:
Did anyone else have a similar failure?
Is there a one time inspection procedure we can do?
Any special inspection we can do if we have the canard off
Is there a recurrent inspection that should be done?
If so what inspection and how often?
Finally, how much time did each airframe have?
At 09:54 AM 5/20/2005 -0700, James Postma wrote:
Subject: BROKEN SPAR
I had a landing accident at Chino on April 21 which resulted in
This was in a Q2 with the LS-1 canard. It broke just inside the
the right side in the area that Jim Patillo has repaired on his
The landing was smooth and the right canard did not impact
swerved right, then left, then right and the spar broke. When
settled to the ground, it ground looped to the right 200 degrees.
The NTSB and the FAA is investigating. I asked the FAA accident
investigator if they would take any action regarding the
he said that seeing as it is experimental, it is up to the
take some action. There probably will be an NTSB accident
was substantial damage to the airplane. I was not injured.
The airplane does not have the wheel alinement.
If you want to comment on this, please send mail to me as well
list as I am not getting mail from the list. Telephone calls
(253) 584-1182 9:00 to 8:00 PDT
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