What was found
DURING AIRCRAFT C-CHECK, MAINTENANCE DISCOVERED A CRACK ON THE FUSELAGE SKIN (SECTION 46) LOCATED AT STATION 1541 AND STRINGER S29L. THE DAMAGE WAS EVALUATED PER 767-200 SRM 53-00-01, FIGURE 101 AND FOUND TO EXCEED ALLOWABLE LIMITS, REQUIRING A REPAIR. THE DAMAGE CAN BE REPAIRED PER 767-200 SRM 53-00-01, FIGURE 201, REPAIR 1 EXCEPT THE PROPOSED REPAIR WILL FALL WITHIN 22” OF THE OUTFLOW VALVE CUT OUT (SKIN EOP), REQUIRING SPECIFIC APPROVAL. THE SKIN PANEL (P/N 146T3231-1) IS FABRICATED FROM 2024-T3 X 0.200” ALUMINUM CLAD SHEET (QQ-A-250/5) CHEM. MILLED DOWN TO 0.056” MINIMUM (0.108” AT THE DAMAGE/REPAIR LOCATION). AIRBORNE MAINTENANCE AND ENGINEERING SERVICES CONTACTED FLIGHT VEHICLES CONSULTING INC. WITH A PROPOSED REPAIR FOR EVALUATION AND APPROVAL. REPAIR COMPLETED PER ABX-REA-5365-64368-00