What was found
CORROSION ON FUSELAGE SKIN AT B.S. 1016 - 1016+25; L.B.L. 14 - R.B.L. 14; W.L. 306.5. / [01] VERIFIED SRM 53-00-01-1A-1 ALLOWABLE DAMAGE 1 IS APPLICABLE FOR THIS AIRCRFT;[02] REMOVED CORROSION ON FUSELAGE SKIN AT B.S. 1016 - 1016+25; L.B.L. 14 - R.B.L. 14; W.L. 306.5 AREA 2EA (15'X1.5'); 1EA (12'X1.5') AND 1EA (3'X4') IAW SRM 51-10-02-0G-0.;[03] REMOVED FASTENERS COMMON TO STR 2L; 2R AND 2AR IAW SRM 51-40-02-0G-0;[04] VERIFIED CORRECTIVE ACTION #1; 2;[05] UT THICKNESS TESTED BLENDED AREAS PER 737NDT PART 4 51-00-00 PROCEDURE 2. FILLED OUT GRID MAP WITH REMAINING THICKNESS DIMENSIONS. LOWEST REMAINING IN POCKETED BAYS IS .063. LOWEST REMAINING AT PAD UP AREAS IS .075'. TOOL E650 ATS2031.;[06] CORRECTED MEASUREMENTS PER NDI;[07] CORROSION ON FUSELAGE SKIN AT B.S. 1016 - 1016+25; L.B.L. 14 - R.B.L. 14; W.L. 306.5 LOWEST REMAINING IN POCKETED BAY IS .063' FROM .063' AND LOWEST REMAINING AT PAD UP AREAS IS .075' FROM .080'.<BR><BR> FOUND TO BE OUT OF LIMITS DUE TO NO MORE THAN THREE FASTENERS IN ALL GROUP OF TEN AROUND THE REMOVAL OF MATERIAL IS PERMITTED IAW SRM 53-00-01-1A-1 STEP 4.C.(2) FIGURE 103 ALLOWABLE DAMAGE 1 DETAIL 'D'.<BR><BR>ENGINEERING REQUIRED.;[08] VERIFIED CORRECTIVE ACTION #7;[09] AS PER EA 22-153-01214; THE DAMAGE IS ACCEPTABLE AS A CONTINUE-IN-SERVICE CONDITION WITHOUT REPETITIVE INSPECTIONS AND NO TERMINATING ACTION REQUIREMENTS.;[10] CORRECTED MEASUREMENTS.;[11] VERIFIED ALL STEPS COMPLETE.