What was found
DURING TRANSIT CHECK, IT WAS DETECTED A SEVERAL NICKS ON RIGHT ENGINE INNER BARREL ACOUSTIC PANEL INLET COWL. MAINTENANCE PERSONNEL PERFORMED A REVISION, DETECTING SEVERAL NICKS AL 2:30 HRS, 8 HRS AND 9:30 HRS POSITION. THE WO´S 7058591 AND 7058631 WERE ISSUED TO REPAIR THE DAMAGES DETECTED. NICKS WERE REMOVED, IAW SRM 54-10-01-1A-1, PARAGRAPH 4C (2) FIGURE 103, DETAIL C. AN ULTRASONIC THICKNESS MEASUREMENT INSPECTION, TAP TEST AND DETAIL VISUAL INSPECTIONS WERE PERFORMED ON NICKS AREAS, IAW B737 NDTM PART 4, 51-00-00, PROCEDURE 2, SRM 54-10-01 ALLOWABLE DAMAGE 1, PART 4C (2) FIGURE 103, DETAIL C WITHOUT DETECTING ANY CRACKS OR DISBONDS. WITH ORIGINAL THICKNESS OF 0.032" AND MINIMUM REMAINING THICKNESS 0.029" AND 0.027 OUT OF LIMITS, IAW SRM 54-10-01, ALLOWABLE DAMAGE 1, PART 4C(2), FIGURE 103, DETAIL C; PERMANENT REPAIRS WERE PERFORMED, IAW SRM 54-10-01-2R-7, PARAGRAPH 4. A CHEMICAL CONVERSION COATING WAS APPLIED, IAW SRM 51-020-0-0G-0, PARAGRAPH 5. ALUMINIZED EPOXY WAS APPLIED, IAW SRM 51-20-05 PARAGRAPH 4(F) ON LEFT ENGINE ACOUSTIC PANEL SKIN, ALL CORRECT.