What was found
PREVIOUS BLEND OUT FOUND ON FUSELAGE STA 1197+66 AND 1197+88 STR 35L. HFEC INSPECTION RESULTED IN A CRACK MEASUES 0.025. SKIN THICKNES S IS 0.160. REPAIRED AS PER SRM 53-00-01, REPAIR 14, FIG 201, TABLEII. PAGE 205.THIS IS A CATEGORAY B REPAIR INSPECTION REQUIR MENTS IS 37,000 FLIGHT CYCLES FROM DATE OF DELIVERY, OR 6,000 CYCLES FROM DATE OF REPAIR INSTALLATIONS WHICH EVER IS GREATER. AND 12,000 FLIGHT CYCLES INTERVAL.