What was found
CLT - INSPECTION VISUALLY FOUND A 1.5 INCH CRACK LOCATED AT THE FUSELAGE RADIUS OF ANGLE AT FS 1085 AND STRINGER 2L. INSTALLED AND MANUFACTURED ANGLE AS PER BOEING SRM 20-30-06. (M)
As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
CLT - INSPECTION VISUALLY FOUND A 1.5 INCH CRACK LOCATED AT THE FUSELAGE RADIUS OF ANGLE AT FS 1085 AND STRINGER 2L. INSTALLED AND MANUFACTURED ANGLE AS PER BOEING SRM 20-30-06. (M)