Turbine D,
What is important to understand is the significance of the assembly orientation and the possible stresses put on the rib feet that would not be realized in service
I suppose no one could pre conceive the results of in service stresses, and I suppose this is an expected factor ...To an extent. From the alloy's that were used to general design of the aircraft, much is new. It is certain that more problems will reveal themselves over time (it does happen with all aircraft), it is the structural ones like this that have potential to cost $$$$$ in loss of time in service.
I would be just as critical of Boeing's composite fuselage. We are engineering aircraft w/o set precedent. We are using process standards based on what we know, skating the razors edge of the unknown.