# SDR YENA2026020400113

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: February 2, 2026
- Submitted: February 4, 2026
- Operation: Air carrier
- Aircraft: [N587JB](https://openairdocs.org/aircraft/N587JB), registered now
- Make and model: Airbus A320-232
- Registry model: [Airbus A320-232](https://openairdocs.org/model/airbus-a320-232) (OpenAirDocs)
- Aircraft serial: 02177
- Aircraft time: 80,243 hours, 29,180 cycles
- System (JASC): [5310 · Fuselage Main, Structure](https://openairdocs.org/jasc/5310)
- Part: Window Frame
- Condition: Cracked
- Location: Zone 200
- 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/YENA2026020400113

## Discrepancy

DURING HEAVY MAINTENANCE: FUSELAGE / NOSE FWD FUSELAGE / WINDSHIELD FRAME / CTR POST LOWER NODE AREA VERTICAL FLANGE RHS & CONT. FITTING LHS / CRACKS - PERMANENT REPAIR; REFERENCES: /1/ AEROMAN EA 53-0081-25 (COVER + PARTS 1-5) /2/ AIRBUS DOSSIER 81689336 /3/ AIRBUS RDAF 81689336/003/2025 ISSUE A /4/ AIRBUS RI R53113672 ISSUE C RS4 /5/ AIRBUS RI R53112919  ISSUE K /6/ R531-13426 ISSUE G – FWD LOWER TITANIUM PANEL REMOVAL/INSTALLATION. /7/ R531-13467 ISSUE C – FRONT WINDOW FRAME REPLACEMENT.  /8/ R531-12972 ISSUE H – LATERAL PANEL FR1-12 REMOVAL/INSTALLATION. /9/ R531-13355 ISSUE C – CROWN PANELS REMOVAL/INSTALLATION. /10/ R531-13470 ISSUE D – FRONT LATERAL WINDOW FRAME JUNCTION. /11/ R531-13241 ISSUE A – SHIM FRONT WINDSHIELD. /12/ R531-13300 ISSUE A – COVER STRIP. DESCRIPTION: DURING CURRENT H6 CHECK OF AC N587JB (MSN 02177) AT SAL,  AEROMAN WHILE PERFORMING SB A320-53-1331, REPORTED CRACK WAS FOUND ON THE WINDSHIELD FRAMING CENTER POST LOWER NODE AREA  RHS VERTICAL FLANGE. IN ADDITION, THE CONTINUITY FITTING WAS ALSO FOUND TO BE CRACKED.  SEE REF /1/ AEROMAN EA FOR FULL DAMAGE DETAILS. AEROMAN REACHED OUT TO AIRBUS FOR REPAIR DISPOSITION VIA REF /2/ DOSSIER.  AIRBUS PROVIDED REPAIR DISPOSITION VIA REF/2/ DOSSIER AND APPROVED BY REF/3/ RDAF AS FOLLOWS: CRACK ASSESSMENT WAS PERFORMED AND MIRROR FITTINGS REPLACED AS PER REF /4/ RI R53113672 ISSUE C RS4, CONTINUITY FITTINGS WERE REPLACED AS PER AIRBUS RI R53112919 010 ISSUE K. ADDITIONALLY REPAIR INSTRUCTIONS REF /6/ - REF /12/ WERE REQUIRED EC A25-1024-01 IS RELEASED TO ACCOMPLISH THE PERMANENT REPAIR OF THE CRACK DAMAGES AS PER REF/1/ AEROMAN EA AND REF /3/ RDAF.EC A25-1024-02 IS RELEASED TO ACCOMPLISH THE POST REPAIR INSPECTIONS (HFEC) OF THE CONTINUITY FITTINGS AS REQUIRED BY REF /3/ RDAF AS FOLLOWS: THRESHOLD = 30,600FC (FH NOT RELEVANT) INTERVAL = 8,800 FC (FH NOT RELEVANT) METHOD: HFEC OF CONTINUITY FITTINGS AS PER NTM 53-11-29. NOTE: AS PER REF/3/ RDAF SB 53-1331 IS NO LONGER APPLICABLE ANYMORE TO THIS A/C. SUBSTANTIATION: THIS CAT B PERMANENT REPAIR IS APPROVED BY REF /3/ RDAF AND IS CLASSIFIED AS MAJOR.(E/C: A26-062-01)

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