Airworthiness Directive Airbus A350-1041 Flap Shaft Misalignment

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Rule

Airworthiness Directives; Airbus SAS Airplanes

A Rule by the Federal Aviation Administration on 04/14/2026

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3. Document Details Published Content - Document Details Agencies Department of Transportation Federal Aviation Administration Agency/Docket Numbers Docket No. FAA-2026-3478 Project Identifier MCAI-2025-00934-T Amendment 39-23307 AD 2026-07-11 CFR 14 CFR 39 Document Citation 91 FR 19070 Document Number 2026-07183 Document Type Rule Pages 19070-19073 (4 pages) Publication Date 04/14/2026 RIN 2120-AA64 Published Content - Document Details

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• Document Details Published Content - Document Details Agencies Department of Transportation Federal Aviation Administration Agency/Docket Numbers Docket No. FAA-2026-3478 Project Identifier MCAI-2025-00934-T Amendment 39-23307 AD 2026-07-11 CFR 14 CFR 39 Document Citation 91 FR 19070 Document Number 2026-07183 Document Type Rule Pages 19070-19073 (4 pages) Publication Date 04/14/2026 RIN 2120-AA64 Published Content - Document Details
• Document Dates Published Content - Document Dates Effective Date 2026-04-29 Dates Text This AD is effective April 29, 2026. Published Content - Document Dates

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  • AGENCY:
  • ACTION:
  • SUMMARY:
  • DATES:
  • ADDRESSES:
  • FOR FURTHER INFORMATION CONTACT:
  • SUPPLEMENTARY INFORMATION:
  • Comments Invited
  • Confidential Business Information
  • Background
  • Material Incorporated by Reference Under 1 CFR Part 51
  • FAA's Determination
  • Requirements of This AD
  • Explanation of Required Compliance Information
  • Justification for Immediate Adoption and Determination of the Effective Date
  • Regulatory Flexibility Act (RFA)
  • Costs of Compliance
  • Authority for This Rulemaking
  • Regulatory Findings
  • List of Subjects in 14 CFR Part 39
  • The Amendment
  • PART 39—AIRWORTHINESS DIRECTIVES
  • (a) Effective Date
  • (b) Affected ADs
  • (c) Applicability
  • (d) Subject
  • (e) Unsafe Condition
  • (f) Compliance
  • (g) Requirements
  • (h) Exceptions to EASA AD 2025-0117
  • (i) No Reporting Requirement
  • (j) Additional AD Provisions
  • (k) Additional Information
  • (l) Material Incorporated by Reference Enhanced Content - Table of Contents

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Department of Transportation

Federal Aviation Administration

1. 14 CFR Part 39
2. [Docket No. FAA-2026-3478; Project Identifier MCAI-2025-00934-T; Amendment 39-23307; AD 2026-07-11]
3. RIN 2120-AA64

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Final rule; request for comments.

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-1041 airplanes. This AD was prompted by a report of a misalignment between a certain flap shaft and the catcher due to incorrect installation of the bracket supporting the catcher. This AD requires an inspection of affected parts and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.

DATES:

This AD is effective April 29, 2026.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 29, 2026.

The FAA must receive comments on this AD by May 29, 2026.

ADDRESSES:

You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments.
• Fax: 202-493-2251.
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2026-3478; 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 street address for Docket Operations is listed above.

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-2026-3478.

FOR FURTHER INFORMATION CONTACT:

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

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments using a method listed under the ADDRESSES section. Include “Docket No. FAA-2026-3478; Project Identifier MCAI-2025-00934-T” at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, 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 final rule because of those comments.

Except for Confidential Business Information (CBI) as described in the following paragraph, and other ( printed page 19071) 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 final rule.

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 AD 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 AD, 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 AD. 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: Nicholas.H.Benson@faa.gov. 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 2025-0117, dated May 19, 2025 (EASA AD 2025-0117) (also referred to as the MCAI), to correct an unsafe condition for certain Airbus SAS Model A350-1041 airplanes. The MCAI states that a misalignment between flap shaft F02 and the catcher was reported during an inspection on the final assembly line. The root cause is an incorrect installation of the bracket supporting the catcher, which was mounted 180 degrees inverted, causing the flap shaft F02 and catcher to be misaligned. This could lead to premature wear and possible rupture of the flap shaft under specific loads. This condition, if not addressed, could lead to a flap surface detachment, resulting in reduced control of the airplane and parts detached from the airplane, which could damage the airplane.

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-2026-3478.

Material Incorporated by Reference Under 1 CFR Part 51

The FAA reviewed EASA AD 2025-0117, which specifies procedures for performing a one-time detailed inspection to ensure the correct installation of the bracket supporting the catcher on both the left- and right-hand sides and applicable corrective actions. Corrective actions include replacing the flap shaft and catcher, doing a detailed inspection of the bracket and fastener holes for any discrepancy (any scratch or wear mark), performing a rototest inspection and a dimensional check of each fastener hole, and depending on findings, replacing the bracket, or contacting Airbus for approved instructions and accomplishing those instructions. 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 AD after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design.

Requirements of This AD

This AD requires accomplishing the actions specified in EASA AD 2025-0117 described previously, except for any differences identified as exceptions in the regulatory text of this 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, EASA AD 2025-0117 is incorporated by reference in this AD. This AD requires compliance with EASA AD 2025-0117 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this AD. Using common terms that are the same as the heading of a particular section in EASA AD 2025-0117 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 2025-0117. Material required by EASA AD 2025-0117 for compliance will be available at regulations.gov under Docket No. FAA-2026-3478 after this AD is published.

Justification for Immediate Adoption and Determination of the Effective Date

Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for “good cause,” finds that those procedures are “impracticable, unnecessary, or contrary to the public interest.” Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause.

There are currently no domestic operators of these products. Accordingly, notice and opportunity for prior public comment are unnecessary, pursuant to 5 U.S.C. 553(b). In addition, for the foregoing reason(s), the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days.

Regulatory Flexibility Act (RFA)

The requirements of the RFA do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required.

Costs of Compliance

Currently, there are no affected U.S.-registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, the FAA provides the following cost estimates to comply with this AD: ( printed page 19072)

| Labor cost | Parts cost | Cost per
product |
| --- | --- | --- |
| 1 work-hour × $85 per hour = $85 | $0 | $85 |
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:

Labor cost	Parts cost	Cost per product
13 work-hours × $85 per hour = $1,105	Up to $24,240	Up to $25,345.

According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all known costs in the cost estimate.

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:

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

(2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

The Amendment

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

PART 39—AIRWORTHINESS DIRECTIVES

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

Authority: 49 U.S.C. 106(g), 40113, 44701.

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

2026-07-11 Airbus SAS: Amendment 39-23307; Docket No. FAA-2026-3478; Project Identifier MCAI-2025-00934-T.

(a) Effective Date

This airworthiness directive (AD) is effective April 29, 2026.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus SAS Model A350-1041 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025-0117, dated May 19, 2025 (EASA AD 2025-0117).

(d) Subject

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

(e) Unsafe Condition

This AD was prompted by a report of a misalignment between a flap shaft and the catcher due to incorrect installation of the bracket supporting the catcher. The FAA is issuing this AD to address premature wear and possible rupture of the flap shaft under specific loads. This condition, if not addressed, could lead to a flap surface detachment, resulting in reduced control of the airplane and parts detached from the airplane, which could damage 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 2025-0117.

(h) Exceptions to EASA AD 2025-0117

(1) Where EASA AD 2025-0117 refers to its effective date, this AD requires using the effective date of this AD.

(2) Where EASA AD 2025-0117 defines “Affected parts” and refers to “in the AOT”, this AD requires replacing that text with “in Airbus Alert Operators Transmission (AOT) A53P018-25, dated March 24, 2025”.

(3) Where paragraph (3) of EASA AD 2025-0117 specifies if “any discrepancy is detected, as defined in the AOT, before next flight, contact Airbus for approved instructions and, within the compliance time identified therein, accomplish those instructions accordingly”, this AD requires replacing that text with “any discrepancy is detected, the discrepancy 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”.

(4) This AD does not adopt the “Remarks” section of EASA AD 2025-0117.

(i) No Reporting Requirement

Although the material referenced in EASA AD 2025-0117 specifies to submit certain information to the manufacturer, this AD does not include that requirement. ( printed page 19073)

(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: 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, 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.

(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: Nicholas.H.Benson@faa.gov.

(l) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) 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 2025-0117, dated May 19, 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.

(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 fr.inspection@nara.gov.

Issued on April 2, 2026.

Victor Wicklund,

Acting Director, Integrated Certificate Management Division, Aircraft Certification Service.

[FR Doc. 2026-07183 Filed 4-13-26; 8:45 am]

BILLING CODE 4910-13-P

Published Document: 2026-07183 (91 FR 19070)