As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
DURING A STRUCTURAL INSPECTION, NICKS WERE FOUND ON THE FUSELAGE SKIN AT FR 26 AND STRINGER 27L. THE DAMAGE WAS REMOVED VIA BLEND-OUT IN ACCORDANCE WITH SRM 51-10-03. THE RESULTING BLENDED AREA WAS EVALUATED PER SRM 53-21-01 AD51 AND DETERMINED TO BE OUT OF LIMITS DUE TO EXCEEDING 10% OF THE SKIN THICKNESS. THE CONDITION REPORTED WAS REPAIRED IAW ETD2025-190-930875, AND DOCUMENTED PER COOPESA COO-EO-2025-23374, UNDER JOB A1Q219 NRI 21-89.