What was found
RIGHT FUSELAGE SKIN CHAFED FROM AFT WING FLAP STAB FAIRING. REMOVED AFT INBOARD , TOP RIGHT WING PANNEL FOR ACCESS IAW SRM 51-42-21. ORINGIAL MATERIAL .063, BLENDED AREA TO DEPTH .012, WIDE .8 LENGTH 1.2 INCHES. SECONDARY STRUCTURE (APRON) BETWEEN FS 820 AND 830 FS. SUBMITTED DAMAGE REPORT TO MANUFACTURER, REMOVED AND REPLACED DAMAGED RIVET IAW SRM 51-42-06. PERFORMED LPI ON BLENDED AREA. NO CRACKS FOUND AT THIS TIME IAW 51-20-008 NDTM. TREATED AND PRIMED AFFECTED AREA IAW SRM 51-21-16 PAINTED AFFECTED AREA IAW REO 670-53-42-010 AND SRM 51-25-01. REINSTALLED PANEL. ALL WORK DONE IAW SRM 51-42-21 AND 51-42-00.