As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
FUSELAGE SKIN CHAFED AT C32-C33 S43R. STRIPPED THE PAINT PER SRM 51-75-20. REMAINING THICKNESS IS 0.044" 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.