A couple of questions.....
(1) Has it been established that the rudder moved to it's limiter controlled maximum deflection, or (perhaps) did it deflect beyond those limits? How many degrees of deflection at 230 Kt with all systems operating normally?
(2) I understand that the vertical stab failed at approximately 195% of design load (I believe FAR part 25 requires a minimum of integrity to 150%). Does anyone know to what values/loads Boeing designs their vertical stabilizers/rudders?
The finger pointing at the dead pilots is repulsive, but not unanticipated. The legal implications are enormous, and if the basic design of the tail is found to be inadequate, the entire Airbus consortium is at risk (it is my understanding that the entire Airbus family have vertical stabs with similar design/material).