Airworthiness Directive · Amendment 39-18958 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2025-17-05. Comply with the one in force.
This AD applies to Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A321 series airplanes. This AD was prompted by a determination from fatigue testing that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. This AD requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
Before exceeding 36,900 total flight cycles since first flight of the airplane, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking of the frame to cabin floor beam junction on the aft and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand and right-hand sides, in accordance with the Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the inspection of the frame to cabin floor beam junction on the aft and forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand sides thereafter at intervals not to exceed 15,300 flight cycles.
(1) Airbus Service Bulletin A320-53-1317, dated December 15, 2015 (FR 35.1 right-hand side).
(2) Airbus Service Bulletin A320-53-1318, dated October 9, 2015 (FR 35.1 left-hand side).
(3) Airbus Service Bulletin A320-53-1319, dated October 9, 2015 (FR 35.2 right-hand side).
(4) Airbus Service Bulletin A320-53-1320, dated October 9, 2015 (FR 35.2 left-hand side).
If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Although the service information specified in paragraph (g) of this AD specifies to contact Airbus for repair instructions, and specifies that action as “RC” (Required for Compliance), this AD requires repair as specified in this paragraph. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive actions required by paragraph (g) of this AD, unless otherwise specified in the instructions provided by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
