As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
FOUND 2 INCH CRACK INDICATION STARTING AT BS 559+9; ENDING AT 559+11; STR S-1. ACCOMPLISHED CRACK VERIFICATION IN REF TO NDT MANUAL PART 4 53-30-06 UTPA AND NDT MANUAL PART 6 53-30-18 CRACK INSPECTION OF OUTER SKIN AT SUBSURFACE EDGES. REPAIRED FUSELAGE CROWN SKIN CRACK PER EA 24-153-00957; EA24-153-00957-WIP1; EA24-153-00957-WIP2; EA24-153-00957-WIP3