What was found
CRACK WAS FOUND ON FUSELAGE SKIN OF 0.187" AT UPPER FORWARD CORNER BS 160. FASTENERS WERE REMOVED DAMAGE WAS REMOVED AND REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIG 112.
As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
CRACK WAS FOUND ON FUSELAGE SKIN OF 0.187" AT UPPER FORWARD CORNER BS 160. FASTENERS WERE REMOVED DAMAGE WAS REMOVED AND REPAIR PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-05, FIG 112.