What was found
>>> CORROSION >> VERTICAL STABILIZER ; LEFT FRON SPAR FITTING CORROSION ; / [01] REMOVED BUSHING AT VERTICAL STABILIZER LEFT FRONT SPAR FITTING AS PER B737-700 SOPM 20-50-03; [02] REMOVED CORROSION AT VERTICAL STABILIZER LEFT FROM SPAR FITTING REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [05] CORRECTION ON STEP# 4 MIN. THICKNESS IS .850'; [06] REMOVED CORROSION AT VERTICAL STAB. LEFT FROM SPAR FITTING FWD AND AFT FACES REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [07] VERIFIED STEP 1;2 AND 6.; [08] CORRECTION:REMOVED CORROSION REF B737-7 SRM 51-10-02-0G-0 STEP 15.A(3); [09] VERIFIED STEP 8 FOR CORRECTION ENTRY ON PREVIOUS STEPS 2 AND 6.; [10] L/H FITTING MAX. MAT. REMOVAL FWD SIDE 0.008'; AFT SIDE 0.009'; [11] PREVIOUS FITTING LOSS MEAUREMENTS ENTERED IN ERROR ---- CORRECT MEASUREMENT IS L/H FWD SIDE 0.011'; [12] PERFORMED PENETRANT INSP ON VERTICAL STAB LEFT FRONT SPAR FITTING IAW B737 SOPM 20-20-02; NO CRACKS<BR>TOOL USED : TFS4 B/C 170330 CALDUE: 01/22; [13] NOTE TO ADD DETAILED DIMENSIONS: VERTICAL STAB LEFT FRONT SPAR FITTING FWD FACE SPOTFACE DIMENSION 1.755' AND AFT FACE SPOTFACE DIMENSION 1.770'.; [14] VERIFIED 13; [15] ISSUED SUMMARY EA 21-155-03013; [16] REMAINING WORK WAS ACCOMPLISHED ON TASKCARD TTG8Q006V6S5 AND TTG8Q006WK7R.; [17] VERIFIED STEPS 10 AND 11; [18] VERIFIES STEP 16