As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
FUSELAGE SKIN CHAFED AT C34 S43R. STRIPPED THE PAINT PER SRM 51-75-20. REMAINING THICKNESS IS 0.051" PER NTM 51-10-04. NO CRACK FOUND PER NTM 51-10-08. ORIGINAL THICKNESS IS 0.063", OUT OF LIMITS PER SRM 53-10-12/101 PARA 7. REPAIRED SKIN PER SRM 53-10-12/201 FIG 216.