Umm, sorry but this is no big deal. What it shows is that the Finite Element Modelling and the testing rig produced failure within 3% of where it was supposed to be - which is nothing.
I haven't found out the Airbus G limits but the failure load was 1.45 times the +G limit so it has no effect on aircraft performance or weights.
Furthermore, both Airbus and Boeing use failsafe design techniques so that the failure of one structural element does not cause the rest of the structure to fail (absent the tail attachments).
This testing will go on forever, with cracks appearing and being fixed etc. etc.