What was found
MAIN CABIN L/H STA 312 JUST ABOVE DOOR CUTOUT UPPER STRUCTURE FLANGE CRACKED / [01] TRIMMED OUT DAMAGED AREA AT MAIN CABIN UPPER CHORD OF FRAME STA 312 BETWEEN S-5L AND S-6L AND EVALUATED SURFACE ROUGHNESS FOUND TO BE SMOOTHER THAN 63 MICROINCHES RA AT CUT EDGE REF B737-700 SRM 51-10-02-0G-0 AND SRM 53-10-07-2R-1 FIG 202. TOOL USED B/C#171854;[21] INSTALLED NEW REPAIR ANGLE AT MAIN CABIN L/H STA 312 JUST ABOVE DOOR CUTOUT UPPER STRUCTURE IAW SRM 53-10-07-2R-1 REPAIR 1 AND SRM 51-40-02-0G-0;[22] (FINAL) TRIMMED OUT DAMAGED AREA AT MAIN CABIN UPPER CHORD OF FRAME STA 312 BETWEEN S-5L AND S-6L AND EVALUATED SURFACE ROUGHNESS FOUND TO BE SMOOTHER THAN 63 MICROINCHES RA AT CUT EDGE REF B737-700 SRM 51-10-02-0G-0 AND SRM 53-10-07-2R-1 FIG 202. TOOL USED B/C#171854. FABRICATED REPAIR ANGLE; MATERIAL USED 7075-O .O63 P.O. # 1557906 IAW B737-700 SRM 53-10-07-2R-1 REPAIR 1. LOCATED AND DRILLED REPAIR ANGLE IAW B737-700 SRM 53-10-07-2R-1 REPAIR 1. INSTALLED NEW REPAIR ANGLE AT MAIN CABIN L/H STA 312 JUST ABOVE DOOR CUTOUT UPPER STRUCTURE IAW SRM 53-10-07-2R-1 REPAIR 1 AND SRM 51-40-02-0G-0.;[23] (RII) VERIFIED STEPS #20 AND #21; INSTALLATION OF NEW REPAIR.;[24] OK TO APPLY CIC ON REPAIR AREA.;[25] APPLIED CIC ON REPAIR AREA IAW SRM 53-10-07-2R-1 REPAIR 1 AND AMM 51-21-91-620-802.;[26] VERIFIED STEP #25.;[27] (RII) FINAL INSPECTION; TRIMMED AND INSTALLED NEW FABRICATED REPAIRED ANGLE AT STA 312 BETWEEN S-5L AND S-6L.