spitzy Posted May 9, 2007 Share Posted May 9, 2007 I completed my shear web layup and found there was delamination around the corners in some spots. I started to sand out the bad areas and plan to complete the 4 unidirectional ply layup followed by on ply of bid. This is per the instructions to make a repare that is 100% of the origional strength. Given this is the main load bearing member in the aircraft, I've been having second thoughts about doing this. 1) Will the extra thickness or bump under the spar cap caused by the imperfection in my shear web reduce strength? 2) Should I trust a repare in a part like this? I have a feeling that this wing spar was designed to handle a load that is WAY above any actual load experienced to complensate for any small deviations in strength due to the manufacturing process. Any thoughts? I'm considering finishing this one, measuring the breaking point of the thing to satisfy my own curiosity. Then I'll either buy or build another one for my plane. Quote Link to comment Share on other sites More sharing options...
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