# SDR YENA2026021100169

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: February 8, 2026
- Submitted: February 11, 2026
- Operation: Air carrier
- Aircraft: [N613JB](https://openairdocs.org/aircraft/N613JB), registered now
- Make and model: Airbus A320-232
- Registry model: [Airbus A320-232](https://openairdocs.org/model/airbus-a320-232) (OpenAirDocs)
- Aircraft serial: 02449
- Aircraft time: 76,940 hours, 27,768 cycles
- System (JASC): [5730 · Wing, Plate/Skin](https://openairdocs.org/jasc/5730)
- Part: Skin
- Condition: Corroded
- Location: Zone 600
- Stage of operation: IN
- How discovered: V
- Nature of condition: O
- Precautionary procedure: K
- FAA source: FAA Service Difficulty Reporting System (https://sdrs.faa.gov/)
- Page: https://openairdocs.org/sdr/YENA2026021100169

## Discrepancy

DURING HEAVY MAINTENANCE: RT WING TOP SKIN PANEL CORRODED /1/ - AIRBUS DOSSIER 81709907 /2/ - AIRBUS RDAF REF. & ISSUE.: 81709907/003/2025 ISSUE A /3/ - AIRBUS RI R572-44701 ISSUE B  /4/ - AIRBUS RI R572-58616 ISSUE N /5/ - AIRBUS RI R572-58926 ISSUE E /6/ - AIRBUS RI R572-58979 ISSUE E /7/ - AIRBUS RI R572-58270, ISSUE C /8/ - AIRBUS TECHNICAL DISPOSITION.: TD/81709907/011/2025 ISSUE A /9/ - AIRBUS TECHNICAL DISPOSITION.: TD/81709907/011/2025 ISSUE B /10/ - AIRBUS TECHNICAL DISPOSITION.: TD/81709907/011/2025 ISSUE C  /11/ - AIRBUS TECHNICAL DISPOSITION.: TD/81709907/011/2025 ISSUE D /12/ EA 57-0135-25 (COVER + PARTS 1-9) /13/ - MX-244 MAJOR REPAIR. DESCRIPTION: ON 01/2026, DURING  C7 CHECK ON  A/C N613J MSN 02449 @ SAL, AEM REPORTED SEVERAL CORROSION FINDINGS EXTENDING AT THE REAR SPAR AND SKIN INTERFACE HAVE BEEN FOUND AT RH WING. THE AFFECTED LOCATIONS WERE AT LEVEL OF RIB 7 THRU RIB 9 AND AT LEVEL OF RIB 15. AIRBUS WAS CONTACTED FOR ASSESSMENT AS THERE WERE NO ADL OR SRM TASK AVAILABLE TO PERFORM A REPAIR. DUE TO THE EXTENSION OF THE DAMAGE UNDER THE REAR SPAR SKIN, AIRBUS WAS CONTACTED THROUGH REF /1/ AIRBUS DOSSIER FOR DISPOSITION. SEPARATION WAS REQUIRED TO COMPLETE THE CORROSION REMOVAL PROCESS THROUGH REF /4/ RI. THE REPAIR WAS PERFORMED FOLLOWING THE INSTRUCTIONS PROVIDED ON REF /3/ THROUGH REF /11/. THE A/C WAS PUT ON JACKS AND THEN SEPARATION WAS PERFORMED AND FURTHER BLENDING WAS PERFORMED, DUE THE REMAIN SKIN THICKNESS BETWEEN THE TOP SKIN PANEL 2 WAS TRIMMED OUT, AND A REPAIR PLATE WAS INSTALLED AS PER REF /11/, DIMENSIONS OF THE REPAIR PLATE ARE LENGTH=30.970 INCHES AND WIDTH= 4.734 INCHES, SURFACE PROTECTION WAS RE-PROTECTED AS SRM GUIDELINES. AIRBUS APPROVED THIS REPAIR PER THE REF /2/ RDF AS PERMANENT REPAIR WITH ADDITIONAL INSPECTION REQUIREMENTS. TO PROPERLY TRACK THE INSPECTION REQUIREMENTS, THE FOLLOWING ECS HAVE BEEN ISSUED: EC A26-102-01 ACCOMPLISHES THE PERMANENT REPAIR PER THE REF /12/ EA AND COMPLIES WITH REF /2/ RDAF WITHOUT DEVIATION. EC A26-102-02 IS TO TRACK THE POST REPAIR INSPECTION REQUIREMENT PER REF /2/ RDAF FOR TOP SKIN UPPER SURFACE AT THE FALSE REAR SPAR AND TEOH, BETWEEN OJR RIB 8.5 AT THRESHOLD: 60000FC/ 120000FH, INTERVAL AND METHOD (TBD- PENDING OEM INSTRUCTIONS). EC A26-102-03 WAS CREATED FOR (SECOND INSPECTION) FOR TOP SKIN UPPER SURFACE BETWEEN RIBS 14-16, UNDER REPAIR PLATE AT THE REAR SPARS ATTACHMENTS, FWD AND THREE ROWS OF ATTACHMENTS INBD AND OTBD OF REPAIR PLATE WITH TH AND INTERVAL:15,000FC/ 30,000FH, METHOD: (DET AND SDI). EC A26-102-04 WAS CREATED FOR (THIRD INSPECTION) FOR REAR SPAR TOP FLANGE AT OVERSIZED FASTENERS FOR REPAIR PLATE, BETWEEN RIBS 14-16 WITH TH AND INTERVAL:18,000FC/ 30,000FH, METHOD: (DET). SUBSTANTIATION: THIS REPAIR HAS BEEN APPROVED VIA REF. /2/ RDAF AS A CAT B, PERMANENT REPAIR WITH POST REPAIR INSPECTIONS AND IS CLASSIFIED AS MAJOR PER REF /12/ MX-244 GUIDELINES. (E/C: A26-102-01)

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