What was found
DURING HEAVY MAINTENANCE: FUSELAGE/ AFT FUSELAGE / EXTERNAL SKIN & INTERNAL STRUCTURE / BTWN FR68-FR72 / TAIL STRIKE DAMAGE – TIME LIMITED REPAIR; REFERENCES: /1/ A321 TASK 05-51-21-200-001-A INSPECTION AFTER A TAIL RUNWAY IMPACT AVTECH TD NO. 0164-CAS-201-IR (TEMPORARY REPAIR) AIRBUS DOSSIER 81750946 AIRBUS TECHNICAL DISPOSITION D/81750946/036/2026#B (PERMANENT REPAIR) AIRBUS TECHNICAL DISPOSITION TD/81750946/020/2026#A (ZERO STRESS JACKING PROCEDURE) AIRBUS REPAIR INSTRUCTION R530-70550 ISSUE B /8/ AIRBUS REPAIR DRAWING R534-70204-000 ISSUE E (S18 LOWER SKIN PANEL REPLACEMENT) /9/ AIRBUS REPAIR DRAWING R534-20614-004 ISSUE E (S18 LOWER SKIN PANEL REPLACEMENT) /10/ AIRBUS REPAIR DRAWING R535-70151-000 ISSUE L (S19 LOWER SKIN PANEL REPLACEMENT) /11/ AIRBUS REPAIR DRAWING R535-70404 ISSUE A (FR70 BUTT STRAP REPAIR) /12 AIRBUS REPAIR DRAWING R535-70400-000 ISSUE Q (FR70 LOWER SECTION PARTIAL REPLACEMENT) /13/ CAS WO 8141 AIRBUS RDAF 81750946/039/2026 ISSUE A (6-MONTH LIMITATION) /15/ MX-244 FOR A26-131-03 (MAJOR). DESCRIPTION: ON 2/09/2026 AT SFO, AC N2188J (MSN 11955) EXPERIENCED A TAIL STRIKE DURING A GO-AROUND AFTER LANDING. JBU ASR TEAM HAD PERFORMED PRELIMINARY PHASE 1 AND PHASE 2 INSPECTIONS AS PER REF /1/ AMM TASK 05-51-21-200-001-A INSPECTION AFTER A TAIL RUNWAY IMPACT. SEE REF /2/ AND REF /3/ FOR ADDITIONAL DETAILS. DUE TO THE EXTENT OF DAMAGE AND LIMITED JBU REPAIR CAPABILITIES, LEADERSHIP HAD ELECTED, CONSISTENT WITH PREVIOUS SIMILAR EVENTS, TO UTILIZE BUSINESS PARTNER CERTIFIED AVIATION SERVICES (CAS) AND THEIR IN-HOUSE DER TO ACCOMPLISH A TEMPORARY REPAIR. THIS ALLOWED THE AIRCRAFT TO BE AUTHORIZED FOR AN UNPRESSURIZED MX FERRY FLIGHT TO A SUITABLE HVY MX STATION FOR PERMANENT REPAIR. AVTECH ENGINEERING ISSUED REF /3/ TD TO ACCOMPLISH THE REQUIRED INSPECTIONS (INCLUDING APPLICABLE NDTS) AND STRUCTURAL DOUBLER REPAIRS AT THREE LOCATIONS TO SUPPORT FERRY OF THE AIRCRAFT UNDER SPECIAL CONDITIONS. THE AIRCRAFT WAS FERRIED TO MZJ FOR PERMANENT REPAIR. CAS CONTACTED AIRBUS VIA REF /4/ DOSSIER WITH REQUEST TO REPAIR THE DAMAGES VIA S18/S19 LOWER SKIN REPLACEMENT, FR70 REPLACEMENT OF BUTT STRAP AND PARTIAL FRAME SEGMENT AND REPLACEMENT OF INTERNAL STRUCTURES IN SECTION 19. AIRBUS PROVIDED INSTRUCTIONS VIA REF /5/ & REF /6/ TD’S WHICH CONSISTED OF ZERO-STRESS JACKING THE AIRCRAFT AND ACCOMPLISHING THE FOLLOWING INSTRUCTIONS: REMOVAL OF TEMPORARY REPAIRS (REF /4/) REMOVAL OF S18 LOWER SKIN PANEL (REF /8/ & REF /9/) REMOVAL OF S19 LOWER SKIN PANEL (REF /10/) REPLACEMENT OF BUTT STRAP AT FR70 & FR70 PARTIAL LOWER SEGMENT (REF /11/ & REF /12) REPLACEMENT OF STRINGERS IN S19 (REF /5/)REPLACEMENT OF CLIPS AT FR76 IN S19 (REF /5/) INSTALLATION OF S18 LOWER SKIN PANEL (REF /8/ & REF /9/) INSTALLATION OF S19 LOWER SKIN PANEL (REF /10/). THE CAS TEAM ACCOMPLISHED THE REF /5/ TD REPAIR WITHOUT DEVIATION AND DOCUMENTED ALL WORK PER REF /13/ CAS WO. AIRBUS APPROVED THE REPAIR AS TIME LIMITED PER REF /14/ RDAF PENDING FURTHER DTA DUE WITHIN 6-MONTHS. THIS EC A26-131-03 ACCOMPLISHES THE TIME LIMITED REPAIR IN ACCORDANCE WITH REF /13/ CAS WO AND COMPLIES WITH REF /14/ RDAF WITHOUT DEVIATION. EC A26-131-04 TRACKS THE PERMANENT REPAIR WHICH IS PENDING 6-MONTH DTA. SUBSTANTIATION: THIS TIME LIMITED REPAIR IS APPROVED PER REF /14/ RDAF AND IS CLASSIFIED AS MAJOR. (E/C: A26-131-03)