# SDR YENA2025010600021

- Type: Service difficulty report (as reported; unverified)
- Difficulty date: January 3, 2025
- Submitted: January 6, 2025
- Operation: Air carrier
- Aircraft: [N586JB](https://openairdocs.org/aircraft/N586JB), registered now
- Make and model: Airbus A320-232
- Registry model: [Airbus A320-232](https://openairdocs.org/model/airbus-a320-232) (OpenAirDocs)
- Aircraft serial: 02160
- Aircraft time: 75,457 hours, 27,284 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/YENA2025010600021

## Discrepancy

DURING HEAVY MAINTENANCE: FUSELAGE/ NOSE FWD FUSELAGE/ WINDSHIELD FRAME / CENTER POST / LOWER NODE AREA / CRACK DAMAGE - PERMANENT REPAIR; REFERENCE: /1/ AEROMAN EA 53-9061-24 (COVER + PARTS 1-5) /2/ AIRBUS SB A320-53-1331 (REF. FAA AD 2020-17-03) /3/ AIRBUS RDAF 81501304/003/2024#A /4/ AIRBUS MESSAGE 81501304/008 /5/ AIRBUS REPAIR INSTRUCTION R53113430 ISSUE F (MIRROR FITTING INSTALLATION) /6/ AIRBUS REPAIR INSTRUCTION R53112919 ISSUE K (CONTINUITY FITTING REPLACEMENT) /7/ AIRBUS REPAIR INSTRUCTION R53113426 ISSUE F (TITANIUM PANEL REPLACEMENT/REMOVAL) /8/ AIRBUS REPAIR INSTRUCTIONS R53113672 ISSUE C (CRACK ASSESSMENT/REPAIR). DURING THE CURRENT (12/2024) M2 CHECK ON N584JB AT SAL, WHILE PERFORMING NDT INSPECTION PER THE REF /2/ SB, CRACKS WERE FOUND ON THE WINDSHIELD FRAMING CENTER POST LOWER ATTACHMENT AT AREAS A1 (LHS) AND D1 (RHS).  REFER TO REF /1/ EA FOR DETAILS. THE DAMAGES WERE REWORKED, BUT PER THE REQUIREMENTS OF THE REF /2/ SB – AIRBUS MUST BE CONTACTED FOR REPAIR INSTRUCTIONS WITH THESE FINDINGS.  ADDITIONALLY, THERE WAS NO REFERENCE TO REPAIRING THE DAMAGE PER OEM MANUAL.   AEROMAN REVIEWED THE DAMAGES USING THE REF /8/ REPAIR INSTRUCTION, WHICH INDICATES THAT THE MIRROR FITTING REPAIR MUST BE EMBODIED AND THIS ASSESSMENT WAS PROVIDED TO AIRBUS FOR REVIEW.  AIRBUS PROVIDED THE REF /4/ MESSAGES WHICH PROVIDED INSTRUCTIONS AS FOLLOWS: -    AREA A1:  THIS IS TO REPAIRED PER RS2 OF THE REF /8/ RI – WHICH REQUIRES THE MIRROR FITTING INSTALLATION PER THE REF /5/ RI -AREA D1:  THIS HOLE CAN BE REPAIRED PER RS7 OF THE REF /8/ RI – WHICH REQUIRES A FREEZE PLUG REPAIR.  THE LH & RH CONTINUITY FITTINGS WILL ALSO BE REPLACED PER THE REF /6/ RI AND THE TITANIUM PANEL REMOVED FOR ACCESS/REINSTALLED PER THE REF /7/ RI. AIRBUS APPROVED THIS REPAIR PER THE REF /3/ RDAF AS PERMANENT WITH POST REPAIR INSPECTIONS REQUIRED.  THE REF /1/ EA PROVIDES THE INSTRUCTIONS FOR THIS REPAIR.  THIS EC IS ISSUED TO ACCOMPLISH THE PERMANENT REPAIR INSTRUCTIONS PER THE REF /1/ EA AND COMPLIES WITH REF /3/ RDAF WITHOUT DEVIATION. THIS EC A24-1555-01 PROVIDES THE PERMANENT REPAIR INSTRUCTIONS. EC A24-1555-02 PROVIDES THE POST REPAIR INSPECTION INSTRUCTIONS FOR AREA 1 ON THE CONTINUITY FITTINGS AFTER SHIM REMOVAL (METHOD:  HFEC PER NTM 51-10-08, THRESHOLD: 29500FC FROM REPAIR, INTERVAL:  8700FC). EC A24-1555-03 PROVIDES THE POST REPAIR INSPECTION INSTRUCTIONS FOR AREA 2 ON THE WINDSHIELD FRAMINGS AFTER REMOVAL OF MIRROR FITTINGS (METHOD:  HFEC PER NTM 53-11-29, THRESHOLD: 27000FC FROM REPAIR, INTERVAL:  4700FC). EC A24-1555-04 PROVIDES THE POST REPAIR INSPECTION INSTRUCTIONS FOR THE MIRROR FITTING AND RHS HOLE D1  (METHOD:  TBD, THRESHOLD:  60000FC FROM REPAIR, INTERVAL:  TBD). NOTE:  THE REF /2/ SB IS NO LONGER APPLICABLE FOR THIS A/C AND WILL BE ADDRESSED IN EC A320-53-1331 AND 2020-17-03-FAA (BY CHECKING FOR PREVIOUS REPAIRS IN THE AREA, AND CONTACTING AIRCRAFT STRUCTURES ENGINEERING IF FOUND, WHICH WOULD INCLUDE THIS EC). SUBSTANTIATION: THIS CATEGORY B PERMANENT REPAIR HAS BEEN APPROVED VIA REF /3/ RDAF AND IS CLASSIFIED AS MAJOR. (E/C: A24-1555-01)

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