What was found
DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE / FR 36 LH & RH SIDES / PRESSURE PANEL / CRACK DAMAGES AT MULTIPLE HOLES – TIME LIMITED REPAIR; REFERENCES: /1/ AEROMAN EA 53-0071-25 REV. 0 (COVER + PARTS 1-11) /2/ AIRBUS RDAF 81680593/005/2025#A /3/ AIRBUS MESSAGES 81680593/013, /020, /028,/038, /053, /065, /080 /4/ AIRBUS SB A320-53-1263 /5/ AIRBUS SB A320-53-1240 /6/ FAA AD 2018-06-04 /7/ AIRBUS REPAIR INSTRUCTION R533-70349 ISSUE B /8/ AIRBUS REPAIR INSTRUCTION R533-70350 ISSUE E /9/ AIRBUS MPD TASK 533185-01-2. AT THE CURRENT (12/2025) M2 CHECK FOR N583JB AT SAL, DURING THE ACCOMPLISHMENT MPD 533185-01-2, AEROMAN REPORTED SEVERAL CRACKED HOLES ON THE FR36 LHS & RHS PRESSURE PANEL. THE DAMAGES ARE REPORTED AS, AND AS SHOWN IN THE REF /1/ EA: LHS. HOLE 4 – PRESURE PANEL LAYER & CORNER FITTING LAYER. HOLE 5 – PRESSURE PANEL LAYER. HOLE 13 – PRESSURE PANEL LAYER. HOLE 14 – PRESSURE PANEL LAYER. HOLE 100 – PRESSURE PANEL LAYER. RHS. HOLE 3 – CORNER FITTING LAYER. HOLE 7 – PRESURE PANEL LAYER & CORNER FITTING LAYER. THE SRM WAS CONSULTED AND THERE ARE NO REPAIRS AVAILABLE FOR THIS DAMAGE. THEREFORE, AIRBUS WAS CONTACTED FOR REPAIR INSTRUCTIONS. NOTE: INSPECTIONS WERE PERFORMED PER THE REF /6/ FAA AD AND TERMINATING ACTION PER THE REF /5/ SB ON 12/16/2017 @ 19987FC/57060FH & ONCE THE REF /5/ SB IS PERFORMED THE REF /5/ SB CANNOT BE PERFORMED WITHOUT AIRBUS APPROVAL. AIRBUS REQUESTED FURTHER ASSESSMENT PER THE REF /7/ RI AND THEN AFTER ADDITIONAL FEEDBACK WAS PROVIDED BY AEROMAN, AIRBUS PROVIDED THE REF /3/ AIRBUS MESSAGES WHICH PROVIDE INSTRUCTIONS TO PERFORM THE REF /4/ SB ON EACH SIDE AND THEN ALSO REPAIR EACH DAMAGE & PERFORM ADDITIONAL ACTIONS AS FOLLOWS: LHS HOLES 4 & 5 – PERFORM THE CUTOUT/REINFORCEMENT REPAIR PER THE REF /4/ SB. REPLACE THE CORNER FITTING. HOLES 8 & 9 (PREVIOUSLY WITH THE REF /5/ SB EMBODIED) - COLDWORKING OF HOLE IN FILLER AND DOUBLER ONLY, INSTALLING FASTENERS PER REF /8/ & CONTINUATION OF REF /4/ SB. HOLES 13 & 14 – REAMING HOLE IN PRESSURE PANEL LAYER ONLY, COLDWORKING OF HOLE, INSTALLATION OF FREEZE PLUG, PERFORMING FINAL REAM THROUGH ALL LAYERS AND THEN INSTALLATION OF FASTENER PER REF. /4/. HOLE 100 – COLDWORKING OF HOLE & INSTALLATION OF FASTENER PER REF. /8/. RHS HOLE 3 - REPLACE THE CORNER FITTING HOLE 7 – PERFORM THE CUTOUT/REINFORCEMENT REPAIR PER THE REF /4/ SB. HOLES 8 & 9 (PREVIOUSLY WITH THE REF /5/ SB EMBODIED) - COLDWORKING OF HOLE IN FILLER AND DOUBLER ONLY & CONTINUATION OF REF /4/ SB. HOLE 100 – COLDWORKING OF HOLE & INSTALLATION OF FASTENER PER REF. /8/. AEROMAN PERFORMED THE REPAIR PER THE INSTRUCTIONS IN THE REF /3/ AIRBUS MESSAGES AND THIS REPAIR IS APPROVED PER 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 A25-1161-01 PROVIDES THE TIME LIMITED REPAIR INSTRUCTIONS. EC A25-1161-02 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: A25-1161-01)