What was found
DURING HEAVY MAINTENANCE: FUSELAGE / CENTER FUSELAGE / FR35 & STR 30R SIDESHELL AREA / HOLE #2 / CRACK DAMAGE - PERMANENT REPAIR; REFERENCES: /1/ AAR-LCQ FINAL REO-L25784 REV. IR /2/ AIRBUS DOSSIER 81748154 /3/ AIRBUS RDAF 81748154/003/2026#B /4/ AIRBUS SB A320-53-1372 (JB TC A320-53-1372-01) /5/ AIRBUS REPAIR INSTRUCTION (RI) R533-70258 ISSUE D /6/ MX244. DESCRIPTION: AT THE CURRENT (04/2026) C9 CHECK @ LCQ FOR A/C N524JB (MSN01528), WHILE ACCOMPLISHING REF /4/ SB, AAR REPORTED A CRACK IN FASTENER HOLE #2 (AFT SKIN, FWD SKIN & FR35 LAYERS) AT THE CENTER FUSELAGE RHS FR35 STR 30R SIDESHELL AREA. SEE REF /1/ AAR-LCQ FINAL REO FOR MORE DETAILS. AAR ACCOMPLISHED DAMAGE REMOVAL ALONG WITH NDT INSPECTIONS AND REACHED OUT TO AIRBUS VIA REF /2/ DOSSIER PROPOSING TO REPAIR THE DAMAGE AT HOLE #2 (RHS) IAW REF /5/ RI GUIDELINES. AIRBUS APPROVED AAR’S PROPOSAL AND PROVIDED INSTRUCTIONS TO PERFORM THE REF /4/ SB WITH DEVIATIONS/ADDITIONAL REQUIREMENTS. IN SUMMARY, THE REPAIR WAS ACCOMPLISHED IAW REPAIR INSTRUCTION (RI) R533-70258 ISSUE D, PARAGRAPH 5.8 – REPAIR SOLUTION G (CUTOUT IN AFT SKIN, FREEZE PLUG IN FWD SKIN & COLD EXPANSION IN ALL OTHER LAYERS) AND RESTORATION OF SURFACE PROTECTION. THESE INSTRUCTIONS ARE APPROVED AS PER REF /3/ RDAF AS PERMANENT WITH POST REPAIR INSPECTIONS REQUIRED. EC A26-305-01 IS ISSUED TO ACCOMPLISH THE PERMANENT REPAIR IN ACCORDANCE WITH REF /1/ AAR-LCQ FINAL REO AND COMPLIES WITH REF /3/ RDAF WITHOUT DEVIATION. EC A26-305-02 TRACKS THE POST REPAIR INSPECTIONS AT HOLE #2 IN FRAME FLANGE, AFT SKIN, ANGLE FITTING LAYERS (THRESHOLD: 67,700FC/135,400FH FROM REPAIR ACCOMPLISHMENT, INTERVAL & METHOD: TBD). EC A26-305-03 TRACKS THE POST REPAIR INSPECTIONS AT HOLE #2 IN FWD SKIN (THRESHOLD: 13,100FC/26,200FH FROM REPAIR ACCOMPLISHMENT, INTERVAL: 6,500FC/13,000FH & METHOD: DVI OF FUSELAGE SKIN AT FR35 AND 10CM FORWARD IAW NTM 51-90-00). SUBSTANTIATION: THIS PERMANENT REPAIR IS APPROVED BY THE REF /3/ RDAF AND IS CLASSIFIED AS MAJOR. (E/C: A26-305-01)