As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
PREVIOUS SKIN BLEND-OUT REWORK HAS DIAMETER LARGER THAN .346 INCHES SEE AMDS CARD 5331-01297-02C STEP 5. ACCOMPLISH DVI OF THE FUSELAGE BOTTOM SKIN BEHIND THE SCUFF PLATE FOOTPRINT PER AND TP BD500-A-J51-00-900-1AAA-018A-A AND VERIFY NO CORROSION REMAINS ON THE SKIN ADJACENT TO CSKS, THE CSK AND THE BORE HOLES. CORROSION REMOVED AND AREA REWORKED PER ER/A 604722-14. (LP 1289383)