Rule2026-04919
Airworthiness Directives; Airbus Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
March 13, 2026
Effective
April 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 91 Issue 49 (Friday, March 13, 2026)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-04919]
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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.
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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.
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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 <a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#78393c0b381d190b19561d0d0a170819561d0d"><span class="__cf_email__" data-cfemail="16575265567377657738736364796677387363">[email protected]</span></a>.
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
<a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#b5d8dcd6ddd4d0d99bd89bccd0c6dddcd4d8d7d0d9f5d3d4d49bd2dac3"><span class="__cf_email__" data-cfemail="610c08020900040d4f0c4f1804120908000c03040d210700004f060e17">[email protected]</span></a>.
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 <a href="http://regulations.gov">regulations.gov</a> 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
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Replace bearing stack.................... 8 work-hours x $85 per hour $920 $1,600 $16,000
= $680.
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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: <a href="/cdn-cgi/l/email-protection#de9f93919d9eb8bfbff0b9b1a8"><span class="__cf_email__" data-cfemail="f4b5b9bbb7b4929595da939b82">[email protected]</span></a>.
(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:
<a href="/cdn-cgi/l/email-protection#0d60646e656c686123602374687e65646c606f68614d6b6c6c236a627b"><span class="__cf_email__" data-cfemail="b6dbdfd5ded7d3da98db98cfd3c5dedfd7dbd4d3daf6d0d7d798d1d9c0">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#aeefeaddeecbcfddcf80cbdbdcc1decf80cbdb"><span class="__cf_email__" data-cfemail="5e1f1a2d1e3b3f2d3f703b2b2c312e3f703b2b">[email protected]</span></a>; 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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#9ef8ecb0f7f0edeefbfdeaf7f1f0def0ffecffb0f9f1e8"><span class="__cf_email__" data-cfemail="b7d1c599ded9c4c7d2d4c3ded8d9f7d9d6c5d699d0d8c1">[email protected]</span></a>.
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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