What was found
SUPPLEMENTAL INFORMATION: CORROSION AROUND FASTENER AT B.S. 907+14; B.L. 0; W.L. 306.5 ON FUSELAGE SKIN UNDER DORSAL FIN. ; / [01] REMOVED 1 EA FASTENER AT DISCREPANCY AREA PER SRM 51-40-02. REMOVED CORROSION AT DISCREPANCY AREA L=0.5 W= 0.5 PERFORMED VISUAL INSPECTION WITH 10-POWER MAGNIFYING GLASS TO MAKE SURE ALL OF THE CORROSION WAS REMOVED PER SRM 51-10-02 PARAGRAPH 15.A.6.A. NO ADDITIONAL DAMAGE NOTED.; [02] VERIFIED CORRECTIVE ACTION 1; [03] HFEC INSPECTED SKIN BLENDOUT AREA; IAW B737 NDTM P6; 51-00-00 PROC 23. NO DISCREPANCIES NOTED. TOOL ID ATS1465; N600; [04] INSPECTED OPEN HOLE IAW B737 NDTM P6; 51-00-00 PROC 16. NO CRACKS NOTED. TOOL ID ATS1465; N600; TOOL ID ATS1411; MINIMITE; [05] UT INSPECTED SKIN BLENDOUT AREA IAW B737 NDTM P4; 51-00-00 PROC 2. REMAINING MAT. 0.069 TOOL ID ATS2341; E650; [06] EVALUATED DAMAGED REMOVAL AT DISCREPANCY AREA L=0.5' W=0.5' ORIG. THICKNESS 0.071' REMAINING 0.069' LOSS 0.002' FOUND OUT OF LIMITS DUE TO AREA REMOVAL OF MATERIAL AROUND OF MORE THAN THREE FASTENERS IN ALL GROUPS OF TEN IS NOT PERMITTED PER SRM 5-00-01-1A-1 FIG 103 DETAIL D.; [07] VERIFIED OUT OF LIMITS CORRECTIVE ACTION 6; [08] CORRECTED MEASUREMENTS; [09] INSTALLATION OF 1 EACH FASTENER WAS ACCOMPLISHED ON EA# 21-153-02635-WIP1; [10] REFER TO FAULT TTG8Q006DPMC WHERE EA 21-153-02635 WAS ADDED AS A SUBTASK; [11] VERIFIED CORRECTIVE ACTION ENTRIES 9 & 10.; [12] VERIFIED CARD COMPLETE