If memory serves (and in this isolated case, I think it does) the 200 series wing was "point load" tested before Lance delivered the first kit. I remember the photos in the very early builder's publication by Lancair of a wing outer panel, mounted upsidedown by it's inboard spar extension to a concrete ground and piled with sand bags to the point that the wingtip was deflected by at least 18 inches. The first iteration of the wing failed at the point load equivalent of about 9 G's - with which Lance was not happy. The spar cap graphite lay-ups were redesigned (increased) and the test was repeated. Subsequent testing indicated that the spar/wing structure would fail catastrophically at a point load of ~15 G's. At the time, I thought Lance was trying to be sure that the wing would hold up to normal usage no matter that the wing was going to be built by a wide range of builders with a wide range of capabilites.

I'm not sure how to interpret the data regarding a "point load" so don't know how such testing (and resulting data) can be referred to the common method of rating an aircraft's structural limits. I do know that I've pulled about 3+ G's on my early 235 at times and have seen no adverse effect- on the airframe, at least.

Dan Schaefer
Early 235    N235SP