Originally Posted by
hans brinker
Wing is still producing the same lift, so no change in load on wing attachments.
There is a distinct difference between load (force) and stress. I was talking of internal stress. The stresses on the wing attachments may change significantly due to a change in total aeroplane mass.
Originally Posted by
hans brinker
But the releasing the load does not lead to an instant increase in positive load on the wing attachment, if anything in a decrease in positive load.
You need to distinguish between total loading on the entire aeroplane, which has a defined positive and negative direction, and internal stresses for which the coordinate system may be completely different. You're trying to equate total loading to internal stresses and that doesn't work. In the same vein, the analogy you used with the string on the balloon has no relation to what happens inside a wing structure.
I think we'll have to leave the engineering track for now. There is enough information and speculation, as well as very useful information, in this thread and until we can learn more from a preliminary report, or the final one, we will most likely continue to run in circles.