Airworthiness Directives: Airbus SAS Airplanes

Airworthiness Directives; Airbus SAS Airplanes

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments using a method listed under the ADDRESSES section. Include "Docket No. FAA-2026-3485; Project Identifier MCAI-2025-00437-T" at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments.

Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM.

Confidential Business Information

CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as "PROPIN." The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3647; email: [email protected] . Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking.

Background

EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2025-0067, dated March 28, 2025 (EASA AD 2025-0067) (also referred to as the MCAI), to correct an unsafe condition for certain Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes. 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.

The FAA is proposing 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.

Material Incorporated by Reference Under 1 CFR Part 51

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.

FAA's Determination

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 is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop in other products of the same type design.

Proposed AD Requirements in This NPRM

This proposed AD would require accomplishing the actions specified in EASA AD 2025-0067 described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD.

Explanation of Required Compliance Information

In the FAA's ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, the FAA proposes to incorporate EASA AD 2025-0067 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2025-0067 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Using common terms that are the same as the heading of a particular section in EASA AD 2025-0067 does not mean that operators need comply only with that section. For example, where the AD requirement refers to "all required actions and compliance times," compliance with this AD requirement is not limited to the section titled "Required Action(s) and Compliance Time(s)" in EASA AD 2025-0067. Material required by EASA AD 2025-0067 for compliance will be available at regulations.gov under Docket No. FAA-2026-3485 after the FAA final rule is published.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would affect 22 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed 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:

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

The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

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

(2) Would not affect intrastate aviation in Alaska, and

(3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

The Proposed Amendment

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

PART 39-AIRWORTHINESS DIRECTIVES

Airbus SAS: Docket No. FAA-2026-3485; Project Identifier MCAI-2025-00437-T.

(a) Comments Due Date

The FAA must receive comments on this airworthiness directive (AD) by June 1, 2026.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus SAS Model A321-251NX, -252NX, -253NX, -271NX, and -272NX airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025-0067, dated March 28, 2025 (EASA AD 2025-0067).

(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by a review of the cold working process on the assembly line that detected a deviation to the manufacturing process. The FAA is issuing this AD to address a deviation to the manufacturing process, which could adversely affect the fatigue life of the center fuselage frame (FR) foot joint connections at FR37 to FR41 inclusive, between stringer (STR) STR21 to STR23. The unsafe condition, if not addressed, could lead to crack initiation and propagation, resulting in reduced 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2025-0067.

(h) Exceptions to EASA AD 2025-0067

(1) Where paragraph (2) of EASA AD 2025-0067 specifies "any discrepancy is detected, as defined in the SB", this AD requires replacing that text with "any fastener hole is not in nominal design condition, as defined in the SB".

(2) Where paragraph (3) of EASA AD 2025-0067 specifies "no discrepancy is detected", this AD requires replacing that text with "fastener holes are in nominal design condition, as defined in the SB".

(3) Where paragraph (4) of EASA AD 2025-0067 specifies a "High Frequency Eddy Current (HFEC) inspection around the fastener holes at an affected area is an acceptable method", this AD requires replacing that text with "High Frequency Eddy Current (HFEC) inspection around the fastener holes at an affected area, in accordance with the instructions of the SB, is an acceptable method".

(4) Where paragraph (5) of EASA AD 2025-0067 specifies "any crack is detected, as defined in the SB, 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 "any crack is detected, the crack must be repaired before further flight using a method approved by the Manager, AIR-520, Continued Operational Safety Branch, 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."

(5) Where paragraph (7) of EASA AD 2025-0067 specifies "no discrepancy", this AD requires replacing that text with "no cracking".

(6) This AD does not adopt the "Remarks" section of EASA AD 2025-0067.

(i) No Reporting Requirement

Although the material referenced in EASA AD 2025-0067 specifies to submit certain information to the manufacturer, this AD does not include that requirement.

(j) Additional AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-520, Continued Operational Safety Branch, 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 (k) of this AD and email to: [email protected]. 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, Continued Operational Safety Branch, 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 paragraphs (h)(3), (h)(4), and (j)(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.

(k) Additional Information

For more information about this AD, contact Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3647; email: [email protected].

(l) 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 2025-0067, dated March 28, 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 [email protected]; website 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.

(5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

[FR Doc. 2026-07297 Filed 4-14-26; 8:45 am]

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