Airworthiness Directives; Airbus Helicopters

[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]



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

[[Page 12287]]



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.

-----------------------------------------------------------------------

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:
    <bullet> 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.
    <bullet> 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.

[[Page 12288]]

    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

[[Page 12289]]

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

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