As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
CRACK DAMAGE WAS DISCOVERED ON THE CENTER TAIL CONE SKIN (PN: L533M1022262) MEASURING APPROXIMATELY 0.60”. ADDITIONAL DAMAGE REQUIRING REPAIR IN THIS AREA DUE TO A DOUBLE DRILLED FASTENER HOLE WAS DISCOVERED ON THE RH ENGINE DECK (PN: L533M1018346) AND ON THE RH OMEGA STRINGER (PN: L533M1022324). A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2024-1732, ISSUE B DATED 26 JUN 2024.