As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
(CAN) REMOVAL OF COMBUSTION TURBINE MODULE REVEALED TOTAL 360 DEG SEPARATION OF INNER LINER AT THE SPOT WELD LINE AT HEADER MARRY-UP POINT. INNER LINER REMAINED SECURED TO 1ST NOZZLE ATTACH LIP WHEN OUTER LINER AND HEADER REMOVED WITH NOZZLE. NO CHANGE IN ENG PERFORMANCE HAD BEEN REPORTED.