AD 2026-12-11

This AD is effective August 3, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 3, 2026.

AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2026-3485; 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; email ADs@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 at regulations.gov under Docket No. FAA-2026-3485.

Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3647; email: nicholas.h.benson@faa.gov.

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 A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. The NPRM was published in the Federal Register on April 15, 2026 (91 FR 20081). The NPRM was prompted by EASA AD 2025-0067, dated March 28, 2025 (EASA AD 2025-0067) (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 review of the cold working process on the assembly line, a deviation to the manufacturing process was detected, which could adversely affect the fatigue life of the affected area ( i.e., center fuselage frame (FR) foot joint connections at FR37 to FR41 inclusive, between stringers (STR) STR21 to STR23, on both left-hand and right-hand sides). This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the airplane.

In the NPRM, the FAA proposed to require repetitive inspections for the nominal design condition of the fastener holes in certain center fuselage frame foot joint connections and, as applicable, an inspection for cracking at the frame foot joint connections and corrective actions, as specified in EASA AD 2025-0067. 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-2026-3485.

The FAA received a comment from an anonymous commenter who supported the NPRM without change.

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 issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator.

EASA AD 2025-0067 specifies procedures for repetitive inspections for any discrepancy of the fastener holes, which consists of doing a check to determine if the fastener holes in the affected area are not in nominal design condition. Nominal design condition is that fasteners installed have a nominal diameter as specified in the material referenced in EASA AD 2025-0067. EASA AD 2025-0067 also specifies procedures for a rototest inspection of the fastener holes for any discrepancy ( i.e., cracking) at each affected area and corrective actions, as applicable. Corrective actions include contacting Airbus for approved repair instructions and accomplishing those instructions. EASA AD 2025-0067 also specifies procedures for repairing fastener holes, which would terminate the repetitive inspections.

EASA AD 2025-0067 also specifies accomplishment of a high frequency eddy current (HFEC) inspection around the fastener holes at an affected area is an acceptable method of compliance for the rototest inspection for that affected area.

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.

The FAA estimates that this AD affects 22 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD:

The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need these on-condition actions:

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.

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:

(1) Is not a “significant regulatory action” under Executive Order 12866,

(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.

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

1. The authority citation for part 39 continues to read as follows:

2. The FAA amends § 39.13 by adding the following new airworthiness directive: