Sorry to intrude lads, but back when this happened I was training in an MRO and our instructors ran the (approximate) maths to show the loading this fin was under. They came to the conclusion that any large jet transport aicraft would have lost the fin under that loading, composite or aluminium. The increase in load with each reversal was enormous. The fin on that A306 actually failed far above it's max load certification, our engineers were impressed at how long it held on for.
If you recreated the circumstances on a Boeing, Embraer or any medium or heavier aircraft, that many reversals at that speed that low will rip your tail off was their conclusion