It may be hard to tell between the yaw damper and the flight control system inputs on the Airbus. I believe centered rudder pedals on the Airbus command the flight control system to automatically do what's necessary to point the nose straight ahead, effectively a yaw damper.
Looking at the NTSB photos of the forward attachment points on the fuselage, they seem to be the same size as the center and rear attachment points. As we have just seen, the forward attachment points are more critical and perhaps more vulnerable to aerodynamic forces. Damage at the center or rear attachment points MIGHT have been survivable, but once a forward attachment point fails, its mate takes on the entire load in that area and in this case could not shoulder the added burden. Corrective rudder inputs in response to forward fin flexing add a substantial extra burden to the remaining forward fitting at the worst possible time.
Given the criticality of the forward attachment, why is it apparently the same size as the center and rear attachments?
We also see a fat composite lug fitted into a substantially smaller metal fitting and not much contact surface in the area surrounding the pin.