What was found
DURING HEAVY MAINTENANCE: FUSELAGE / REAR FUSELAGE / FR 65-66 & STR 31R / INNER SKIN / CORROSION DAMAGE - TIME LIMITED REPAIR; REFERENCES: /1/ AEROMAN EA 53-0077-25 REV. 1 (COVER + PARTS 1-3) /2/ AIRBUS RDAF 81680476/005/2025 ISSUE B /3/ AIRBUS TD/81680476/037/2025 ISSUE B /4/ AIRBUS A320 ST1 SRM TASK 53-41-11-283-065 /5/ AIRBUS A320 ST1 SRM TASK 53-41-11-300-021. AT THE CURRENT (12/2025) M2 CHECK FOR N583JB AT SAL, AEROMAN REPORTED 1 AREA OF CORROSION ON THE INNER SKIN (P/N D5348002220100) OF THE REAR FUSELAGE BETWEEN FR 65-66 & AT STRINGER 31R. THE CORROSION DAMAGE, AFTER BLEND OUT, IS REPORTED AS 3.930”L X 1.734”W & 0.115” MRT, AND AS SHOWN IN FIGURE 1 IN PART 1 OF THE REF /1/ EA. THE DAMAGE WAS EVALUATED AGAINST THE SRM AND FOUND OUT OF LIMITS OF THE REF /4/ SRM, DUE TO THE MATERIAL LOSS BEING A MAXIMUM OF 29%. THEREFORE, AIRBUS WAS CONTACTED FOR REPAIR DISPOSITION. AIRBUS PROVIDED THE REF /3/ TD WITH INSTRUCTIONS TO REPLACE STR 31R, AND TO CUT OUT THE CORROSION DAMAGE ON THE SKIN AND PERFORM A DOUBLER REPAIR PER THE REF /5/ SRM WITH DEVIATIONS. AEROMAN PERFORMED THE REPAIR PER THE INSTRUCTIONS IN THE REF /3/ AIRBUS TD, AND THIS REPAIR IS APPROVED PER THE REF /2/ AIRBUS RDAF, WITH A 6-MONTH LIMITATION FOR FURTHER DAMAGE TOLERANCE ANALYSIS (DTA) TO BE ACCOMPLISHED. THIS EC ACCOMPLISHES THE PERMANENT REPAIR PER THE REF /1/ EA AND COMPLIES WITH REF /2/ RDAF WITHOUT DEVIATION. THIS EC A25-1162-01 PROVIDES THE TIME LIMITED REPAIR INSTRUCTIONS. EC A25-1162-02 IS ISSUED TO TRACK THE DTA, DUE WITHIN 6 MONTHS FROM REPAIR ACCOMPLISHMENT. SUBSTANTIATION: THIS TIME LIMITED REPAIR HAS BEEN APPROVED VIA REF /2/ RDAF, IS VALID FOR 6 MONTHS, AND IS CLASSIFIED AS MAJOR. (E/C: A25-1162-01)