AD 2026-04919

[Federal Register Volume 91, Number 49 (Friday, March 13, 2026)] [Rules and Regulations] [Pages 12287-12289] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 2026-04919]

======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. ========================================================================

Federal Register / Vol. 91, No. 49 / Friday, March 13, 2026 / Rules and Regulations

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-5043; Project Identifier MCAI-2024-00780-R; Amendment 39-23279; AD 2026-05-06] RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and SA330J helicopters. This AD was prompted by reports of fatigue cracks found on arms of the tail rotor (TR) pitch change spider due to a load increase originating from degraded bearing stacks. This AD requires reduced life limit intervals for the affected bearing stack and requires replacing the affected bearing stack before exceeding these intervals. This AD also prohibits the installation of the affected bearing stack on a helicopter, unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective April 17, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 17, 2026.

ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2025-5043; 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; phone: +49 221 8999 000; email: [email protected]. You may find this material on the EASA website at ad.easa.europa.eu. You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. It is also available at regulations.gov under Docket No. FAA-2025-5043.

FOR FURTHER INFORMATION CONTACT: Michael Yeshiambel, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946-4133; email: [email protected].

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 all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS 332L1, and SA330J helicopters. The NPRM was published in the Federal Register on December 8, 2025 (90 FR 56699). The NPRM was prompted by EASA AD 2024-0250, dated December 20, 2024 (EASA AD 2024-0250) (also referred to as the MCAI), which is the Technical Agent for the Member States of the European Union. The MCAI states that there were reports of fatigue cracks found on arms of the TR pitch change spider of an affected helicopter. The MCAI further states that subsequent investigation revealed that the cracks resulted from a load increase originating from degraded bearing stacks. Additionally, the MCAI states to address this unsafe condition, reduced life limits are necessary for the affected parts. This condition, if not corrected, could lead to structural failure of the TR assembly, which could result in reduced or loss of control of the helicopter. In the NPRM, the FAA proposed to require introducing reduced life limit intervals for the affected bearing stack and to replace the affected bearing stack before exceeding these intervals. The NPRM also proposed to prohibit the installation of the affected bearing stack on a helicopter, unless certain requirements are met. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA-2025-5043.

Discussion of Final Airworthiness Directive

Comments

The FAA received no comments on the NPRM or on the determination of the costs.

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 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.

Material Incorporated by Reference Under 1 CFR Part 51

The FAA reviewed EASA AD 2024-0250, which introduces reduced life limit intervals for the affected bearing stacks and specifies procedures for replacing the affected bearing stacks before exceeding the reduced life limit intervals. EASA AD 2024-0250 also prohibits installing the affected bearing stack on a helicopter, unless certain requirements are met. 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 10 helicopters of U.S. registry.

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The FAA estimates the following costs to comply with this AD.

Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replace bearing stack.................... 8 work-hours x $85 per hour $920 $1,600 $16,000 = $680. ----------------------------------------------------------------------------------------------------------------

The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators.

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, (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.

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

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

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

Sec. 39.13 [Amended]

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

2026-05-06 Airbus Helicopters: Amendment 39-23279; Docket No. FAA- 2025-5043; Project Identifier MCAI-2024-00780-R.

(a) Effective Date

This airworthiness directive (AD) is effective April 17, 2026.

(b) Affected ADs

None.

(c) Applicability

This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS 332L1, and SA330J helicopters, certificated in any category.

(d) Subject

Joint Aircraft System Component (JASC) Code 6400, Tail rotor system.

(e) Unsafe Condition

This AD was prompted by reports of fatigue cracks found on arms of the tail rotor pitch change spider due to a load increase originating from degraded bearing stacks. The FAA is issuing this AD to prevent degradation of bearing stacks. The unsafe condition, if not addressed, could lead to structural failure of the tail rotor assembly, which could result in reduced or loss of control of the helicopter.

(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, European Union Aviation Safety Agency AD 2024-0250, dated December 20, 2024 (EASA AD 2024-0250).

(h) Exceptions to EASA AD 2024-0250

(1) Where EASA AD 2024-0250 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2024-0250 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (3) Where the material referenced in EASA AD 2024-0250 specifies ``check'', for this AD replace that text with ``inspection''. (4) This AD does not adopt the ``Remarks'' section of EASA AD 2024-0250.

(i) No Reporting or Return of Parts Requirement

Although the material referenced in EASA AD 2024-0250 specifies to submit certain information and to return parts to the manufacturer, this AD does not require those actions.

(j) Special Flight Permit

Special flight permits are prohibited.

(k) Alternative Methods of Compliance (AMOCs)

(1) The Manager, International Validation 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 International Validation Branch, send it to the attention of the person identified in paragraph (l) of this AD and email to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.

(l) Additional Information

For more information about this AD, contact Michael Yeshiambel, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946-4133; email: [email protected].

(m) 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 the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024-0250, dated December 20, 2024. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221

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8999 000; email: [email protected]; website: easa.europa.eu. You may find this EASA material on the EASA website at ad.easa.europa.eu. (4) You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N- 321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (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].

Issued on February 26, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026-04919 Filed 3-12-26; 8:45 am] BILLING CODE 4910-13-P