As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
(CAN) DURING INSPECTION OF AFT FUSELAGE TO FIN ATTACH ADAPTER PLATES AS PER CF-99-11. THE AFT PLATE WAS FOUND CRACKED AT STA 535. ALL ADAPTER PLATES ARE THE POST MODIFICATON TYPE OF A MORE CORROSION RESISTANT MATERIAL. SB 6/516 CALLS UP ONLY A SIMPLE VISUAL INSPECTION. THIS CRACK WOULD NOT HAVE BEEN DETECTED IF THE RIB WAS NOT REMOVED FROM THE AIRCRAFT.