As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
THE LEFT DORSAL FIN ATTACH ANGLE HAS A CONDITION 2 CRACK IN THE VERTICAL LEG REF EO 53-92-32-91 FIG 1. REMOVED THE LEADING EDGE PANEL, REMOVED AND REPLACED THE DORSAL FIN ATTACH ANGLE WITH A NEW ATTACH ANGLE. REINSTALLED THE LEADING EDGE PANEL PER SRM 51-30-AND SRM 51-30-1. (W)