Proposed Rule2025-22162
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
December 8, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and SA330J helicopters. This proposed 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 proposed AD would introduce reduced life limit intervals for the affected bearing stack and would require replacing the affected bearing stack before exceeding these intervals. This proposed AD would also prohibit the installation of the affected bearing stack on a helicopter, unless certain requirements are met. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 90 Issue 233 (Monday, December 8, 2025)</title>
</head>
<body><pre>
[Federal Register Volume 90, Number 233 (Monday, December 8, 2025)]
[Proposed Rules]
[Pages 56699-56701]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-22162]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-5043; Project Identifier MCAI-2024-00780-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and
SA330J helicopters. This proposed 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 proposed
AD would introduce reduced life limit intervals for the affected
bearing stack and would require replacing the affected bearing stack
before exceeding these intervals. This proposed AD would also prohibit
the installation of the affected bearing stack on a helicopter, unless
certain requirements are met. The FAA is proposing this AD to address
the unsafe condition on these products.
DATES: The FAA must receive comments on this NPRM by January 22, 2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <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 NPRM, 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:
<bullet> For European Union Aviation Safety Agency (EASA) material
identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +49 221 8999 000; email:
<a href="/cdn-cgi/l/email-protection#4302073003262230226d2636312c33226d2636"><span class="__cf_email__" data-cfemail="5011142310353123317e3525223f20317e3525">[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.
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#c0ada9a3a8a1a5aceeadeeb9a5b3a8a9a1ada2a5ac80a6a1a1eea7afb6"><span class="__cf_email__" data-cfemail="2a474349424b4f46044704534f5942434b47484f466a4c4b4b044d455c">[email protected]</span></a>.
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-2025-5043;
Project Identifier MCAI-2024-00780-R'' 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
<a href="http://regulations.gov">regulations.gov</a>, 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
[[Page 56700]]
NPRM. Submissions containing CBI should be sent to Michael Yeshiambel,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590. 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 2024-0250, dated December 20, 2024
(EASA AD 2024-0250) (also referred to as the MCAI), to correct an
unsafe condition on Airbus Helicopters Model SA 330 J, AS 332 C, AS 332
C1, AS 332 L, and AS 332 L1 helicopters. 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.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-5043.
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.
FAA's Determination
These products have been approved by the civil aviation authority
(CAA) 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 on 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 2024-0250, described previously, as incorporated by
reference, 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 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 2024-0250 by reference in the FAA final rule. This proposed AD
would, therefore, require compliance with EASA AD 2024-0250 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 2024-0250 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 2024-0250. Material required by
EASA AD 2024-0250 for compliance will be available at
<a href="http://www.regulations.gov">www.regulations.gov</a> by searching for and locating Docket No. FAA-2025-
5043 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 10 helicopters of U.S. registry.
The FAA estimates the following costs to comply with this proposed
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 $920 $1,600 $16,000
hour = $680.
----------------------------------------------------------------------------------------------------------------
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed 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
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
[[Page 56701]]
(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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
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
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:
Airbus Helicopters: Docket No. FAA-2025-5043; Project Identifier
MCAI-2024-00780-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 22, 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, EASA 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 (k) of this AD and
email to: <a href="/cdn-cgi/l/email-protection#42030f0d01022423236c252d34"><span class="__cf_email__" data-cfemail="c7868a888487a1a6a6e9a0a8b1">[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#7f12161c171e1a13511251061a0c17161e121d1a133f191e1e51181009"><span class="__cf_email__" data-cfemail="adc0c4cec5ccc8c183c083d4c8dec5c4ccc0cfc8c1edcbcccc83cac2db">[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 8999
000; email: <a href="/cdn-cgi/l/email-protection#a4e5e0d7e4c1c5d7c58ac1d1d6cbd4c58ac1d1"><span class="__cf_email__" data-cfemail="0342477043666270622d6676716c73622d6676">[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#7214005c1b1c01021711061b1d1c321c1300135c151d04"><span class="__cf_email__" data-cfemail="791f0b5710170a091c1a0d1016173917180b18571e160f">[email protected]</span></a>.
Issued on December 3, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-22162 Filed 12-5-25; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 8, 2025.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.