As much as I like BS'ing with all of you I must admit that being the only person who took part in the wing breaking who was around the airport this past weekend just about gave me cotton mouth from sharing my opinions of the experience with everyone who stopped by wanting to look at it.
So for the rest of you , here it is. The video Bill shared is invaluable in determining the cause of the failure and we are extremely fortunate that Glenn was there with his cameras and took the time to set them up so well. I'm certainly not an expert or the authority or anything this is just my opinion of how this went down and it very well could be wrong. I'm going to refer to top and bottom in terms of how it is seen in the video. From the video the rear (auxiliary, aft, drag whatever you want to call it) spar failed first and this, almost simultaneously caused a failure in the main spar. The rear spar buckled. We all know buckling is what happens when a column is compressed to its limit. In this case the column was eccentrically loaded with much greater compression in the side adjacent to the load (ie the top in the frame of reference in the video) which is why you notice the top buckles out. There are two load factors at play here. The first is the bending this is from the load (shingles simulating aerodynamic loads) which creates a bending moment, deflecting the spar downwards. This creates compression in the top of the spar. This compression is highest at the mid-span of the root and strut attach point. The second load is from the lifting force transmitted through the strut. Long story short, this creates compression in the axis of the spar which increases linearly from a relatively low value at the strut attachment point and is at its highest at the root. It increased like this because of the angle of the flying wire (strut). It attaches in the vertical axis of the aft spar. It should be noted that when the spar deflects from the bending moment this load becomes eccentric. I don't know if I am expressing that last part properly from an engineering standpoint but it is a factor.
The aft spar buckled about 1/3 of the way from the root to the strut attach point. The portion of the aft spar in between each ribs acts as a beam and I think that if you were to run the numbers on this that when you add up the two loads I described above together they are at there highest in this bay.
Since we need to wing to hold more weight we need to fix this and the fix is to change the way the spar is being loaded and also change the construction (make it stronger) in critical areas.