A lot of rubbish in the form of conjecture has been written here recently about Fin and Rudder strength and airworthiness requirements. So here is a fact from the UK CAA detailing what IS NOT TESTED for a CofA.
The FAA and I assume the other certification authorities allow an airframe maker to demonstrate Reliability, Safety and Structural integrity by the use of computer analysis if the actual in-flight testing is either too expensive or too dangerous. This has caused a lot of problems as the actual loads or conditions did not compare with the computer analysis. However in the case of proving structural integrity of the flight surfaces in respect to the fuselage attachments the manufacturers will perform structural bending loads on the wings and tail surfaces to the point of destruction.
If Airbus followed these directives they did run the structural bending loads test on all aerodynamic surfaces.
