As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
(CAN) DURING COMPRESSOR HALVES INSP, ONE STATOR BLADE OF THE LAST AXIAL COMPRESSOR STAGE WAS TORN AND WAS SIDEWAYS CONTACTING THE ONE NEXT TO IT. THE BLADE WAS ONLY HELD IN PLACE BY 5-10 PERCENT OF THE BLADE ROOT. THIS COULD HAVE CAUSED THE BLADE TO GO THRU THE CENTRIFUGAL COMPRESSOR.