The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, ...
[Docket No. FAA-2026-3879; Project Identifier MCAI-2025-01452-T; Amendment 39-23444; AD 2026-17-01]
RIN 2120-AA64
AGENCY:
Federal Aviation Administration (FAA), DOT.
ACTION:
Final rule.
SUMMARY:
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a fatigue test that identified cracks in the forward and aft upper corner of the bulk cargo door. This AD requires a rototest inspection for cracks and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
DATES:
This AD is effective October 1, 2026.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 1, 2026.
ADDRESSES:
AD Docket:
You may examine the AD docket at
regulations.gov
under Docket No. FAA-2026-3879; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For European Union Aviation Safety Agency (EASA) material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; emailADs@easa.europa.eu.
You may find this material on the EASA website at
ad.easa.europa.eu.
You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available atregulations.gov
under Docket No. FAA-2026-3879.
FOR FURTHER INFORMATION CONTACT:
Camille Seay, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-222-5149; email:
Camille.L.Seay@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM was published in the
Federal Register
on May 4, 2026 (91 FR 23922). The NPRM was prompted by EASA AD 2025-0193, dated September 8, 2025 (EASA AD 2025-0193) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states that during a fatigue test on a Model A320 airplane in support of the extended service goal (ESG) campaign, cracks were identified in the area of fastener holes at the forward and aft upper corner of the bulk cargo door at section 16 and 17, both left-hand (LH) and right-hand (RH) sides. This condition, if not addressed, could affect the structural integrity of the airplane.
In the NPRM, the FAA proposed to require a rototest inspection for cracks and applicable on-condition actions, as specified in EASA AD 2025-0193. The FAA is issuing this AD to address the unsafe condition on these products.
You may examine the MCAI in the AD docket at
regulations.gov
under Docket No. FAA-2026-3879.
Discussion of Final Airworthiness Directive
Comments
The FAA received and reviewed a comment that did not include a specific request to change the AD. This comment is outside the scope of this AD.
Conclusion
These products have been approved by the civil aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA's bilateral agreement with this State of Design Authority, that authority has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered any comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is
( printed page 55251)
issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2025-0193 specifies procedures for a rototest inspection for cracks in the area of the fastener holes at the forward and aft upper corner of the bulk cargo door at section 16 and 17, both LH and RH sides, and applicable on-condition actions. On-condition actions include contacting the manufacturer for repair instructions and doing the repair if cracks are detected, or modifying the affected area by cold working the fastener holes if no crack is detected.
This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the
ADDRESSES
section.
Costs of Compliance
The FAA estimates that this AD affects 1,069 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
Labor cost
Parts cost
Cost per
product
Cost on U.S. operators
4 work-hours × $85 per hour = $340
$0
$340
$363,460
Estimated Costs of On-Condition Modification *
Labor cost
Parts cost
Cost per
product
4 work-hours × $85 per hour = $340
$0
$340
* The FAA has received no definitive data on which to base the cost estimates for the on-condition repairs specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
This airworthiness directive (AD) is effective October 1, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025-0193, dated September 8, 2025 (EASA AD 2025-0193), having an extended service goal (ESG) in the airworthiness limitations section of the instructions for continued airworthiness.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a fatigue test that identified cracks in the area of the fastener holes at the forward and aft upper corner of the bulk cargo door at section 16 and 17. The FAA is issuing this AD to address cracks in the forward and aft upper corner of the bulk cargo door, which, if not addressed, could affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2025-0193.
(h) Exceptions to EASA AD 2025-0193
(1) Where EASA AD 2025-0193 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where the definition of the “affected area” in EASA AD 2025-0193 specifies “as
( printed page 55252)
defined in the SB”, this AD requires replacing that text with “as specified in Airbus Service Bulletin A320-53-1303, dated March 7, 2025”.
(3) Where paragraph (2) of EASA AD 2025-0193 specifies “if any crack is detected, before next flight, contact Airbus for approved repair instructions and, within the compliance time specified therein accomplish those instructions accordingly”, this AD requires replacing that text with “if any crack is detected, the crack must be repaired before further flight using a method approved by the Manager, AIR-520, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature”.
(4) This AD does not adopt the “Remarks” section of EASA AD 2025-0193.
(i) Additional AD Provisions
The following provisions also apply to this AD:
(1)
Alternative Methods of Compliance (AMOCs):
The Manager, AIR-520, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to:
AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(2)
Contacting the Manufacturer:
For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, AIR-520, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(3)
Required for Compliance (RC):
Except as required by paragraph (i)(2) of this AD, if any material contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
(j) Additional Information
For more information about this AD, contact Camille Seay, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 817-222-5149; email:
Camille.L.Seay@faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2025-0193, dated September 8, 2025.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
ADs@easa.europa.eu.
You may find this material on the EASA website at
ad.easa.europa.eu.
(4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.
Use this for formal legal and research references to the published document.
91 FR 55250
Web Citation
Suggested Web Citation
Use this when citing the archival web version of the document.
“Airworthiness Directives; Airbus SAS Airplanes,” thefederalregister.org (August 27, 2026), https://thefederalregister.org/documents/2026-17552/airworthiness-directives-airbus-sas-airplanes.
14 CFR part 39
49 U.S.C. 106(g)
www.archives.gov/federal-register/cfr/ibr-locations