[Federal Register Volume 90, Number 177 (Tuesday, September 16, 2025)]
[Rules and Regulations]
[Pages 44493-44496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-17850]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0914; Project Identifier MCAI-2024-00413-R;
Amendment 39-23136; AD 2025-18-09]
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
certain Airbus Helicopters Model AS 332L2 and EC 225LP helicopters.
This AD was prompted by reports of overlengthened and deformed
attachment bolts installed on the link of the main gearbox (MGB)
suspension bar attachment bracket. This AD requires replacing certain
attachment bolts on the MGB suspension bar fittings, inspecting the
[[Page 44494]]
removed bolts, and reporting the results of this inspection to Airbus
Helicopters. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 21, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 21,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0914; 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];
website: 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, 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-2025-0914.
FOR FURTHER INFORMATION CONTACT: George Weir, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817)
222-4045; 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 certain Airbus
Helicopters Model AS 332L2 and EC 225LP helicopters. The NPRM was
published in the Federal Register on June 2, 2025 (90 FR 23297). The
NPRM was prompted by AD 2024-0142, dated July 17, 2024 (EASA AD 2024-
0142) (also referred to as the MCAI), issued by EASA, which is the
Technical Agent for the Member States of the European Union. The MCAI
states that two attachment screws (bolts) were found overlengthened and
deformed on helicopters having the new link of the MGB suspension bar
attachment brackets. The MCAI further states the investigation is still
ongoing and that collecting additional data to support the
investigation is part of addressing the unsafe condition.
In the NPRM, the FAA proposed to require replacing certain
attachment bolts on the MGB suspension bar fittings, inspecting the
removed bolts, and reporting the results of this inspection to Airbus
Helicopters. The FAA is issuing this AD to prevent structural failure
of the MGB suspension bar attachment bolts. This condition, if not
addressed, could result in failure of an MGB attachment assembly,
detachment of an MGB suspension bar, and consequent loss control of the
helicopter.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-0914.
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 2024-0142. This material specifies
procedures for replacing attachment screw part number 332A22-3644-20
with a part that is new (never been installed), inspecting the removed
screws, and reporting the inspection results to Airbus Helicopters. The
attachment screws are installed on the left-hand and right-hand rear
MGB suspension bar fittings. Additionally, EASA AD 2024-0142 prohibits
installing that part-numbered attachment screw on any helicopter unless
it is installed in accordance with certain service 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.
Differences Between This AD and the MCAI
Where the material referenced in the MCAI specifies contacting
Airbus Helicopters for instructions if the difference between (L4) and
(L3) is more than 1.6 mm (.063 in), this AD requires using a repair
method approved by the FAA, EASA, or Airbus Helicopters' EASA Design
Organization Approval.
Where the MCAI prohibits installing an affected part unless it has
been installed in accordance with certain service instructions, this AD
does not contain that prohibition.
Interim Action
The FAA considers that this AD is an interim action. The inspection
reports that are required by this AD will enable the manufacturer to
obtain better insight into the nature and cause of the screw
deformation and eventually to develop final action to address the
unsafe condition. Once a final action has been identified, the FAA
might consider further rulemaking.
Costs of Compliance
The FAA estimates that this AD affects 38 helicopters of U.S.
registry. Labor rates are estimated at $85 per hour. Based on these
numbers, the FAA estimates the following costs to comply with this AD.
Replacing a set of eight rear MGB fitting attachment bolts takes 16
work-hours and parts cost $587 for an estimated cost of $1,947 per
helicopter and $73,986 for the U.S. fleet.
Reporting inspection results takes 1 work-hour for an estimated
cost of $85 per helicopter.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
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instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden, to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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:
2025-18-09 Airbus Helicopters: Amendment 39-23136; Docket No. FAA-
2025-0914; Project Identifier MCAI-2024-00413-R.
(a) Effective Date
This airworthiness directive (AD) is effective October 21, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Model AS 332L2 and EC
225LP helicopters, certificated in any category, as identified in
European Union Aviation Safety Agency AD 2024-0142, dated July 17,
2024 (EASA AD 2024-0142).
(d) Subject
Joint Aircraft System Component (JASC) Code 6330, Main Rotor
Transmission Mount.
(e) Unsafe Condition
This AD was prompted by reports of overlengthened and deformed
attachment bolts installed on the new link of the main gearbox (MGB)
suspension bar attachment bracket. The FAA is issuing this AD to
prevent structural failure of the MGB suspension bar attachment
bolts. The unsafe condition, if not addressed, could result in
failure of an MGB attachment assembly, detachment of an MGB
suspension bar, and consequent loss control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2024-0142.
Note 1 to paragraph (g): EASA AD 2024-0142 and Airbus
Helicopters material that is referenced in EASA AD 2024-0142 refer
to MGB suspension bar attachment ``bolts'' as ``screws.''
(h) Exceptions to EASA AD 2024-0142
(1) Where paragraph (1) of EASA AD 2024-0142 requires compliance
within 2,500 flight hours since first installation, this AD requires
compliance as specified in paragraphs (h)(1)(i) and (ii) of this AD.
(i) For each affected part that has accumulated 2,500 or more
total hours time-in-service (TIS) or if the total hours TIS on the
affected part cannot be determined: Before further flight, and
thereafter at intervals not to exceed 2,500 total hours TIS on the
affected part.
(ii) For each affected part that has accumulated less than 2,500
total hours TIS: Before the affected part accumulates 2,500 total
hours TIS, and thereafter at intervals not to exceed 2,500 total
hours TIS on the affected part.
(2) Where the material referenced in EASA AD 2024-0142 specifies
discarding parts, this AD requires removing those parts from
service.
(3) Instead of the reporting requirement in paragraph (3) of
EASA AD 2024-0142, this AD requires reporting the results of each
inspection to Airbus Helicopters at the compliance time specified in
paragraph (h)(3)(i) or (ii) of this AD. The report must include the
total hours TIS (if known) on each bolt, the batch number and serial
number of the bolt, the length of the bolt, a detailed description
of any findings, any previous maintenance, and any photos (if
possible).
(i) For an inspection done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) For an inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(4) This AD does not require paragraph (4) of EASA AD 2024-0142.
(5) Where the material referenced in EASA AD 2024-0142 specifies
contacting Airbus Helicopters for repair instructions, this AD
requires using a repair method approved by the Manager,
International Validation Branch, FAA; or EASA; or Airbus
Helicopters' EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
(6) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0142.
(i) 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 (j) 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.
(j) Additional Information
For more information about this AD, contact George Weir,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite
[[Page 44496]]
410, Westbury, NY 11590; phone: (817) 222-4045; email:
[email protected].
(k) 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 2024-0142,
dated July 17, 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: [email protected]; website: 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, 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 September 3, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-17850 Filed 9-15-25; 8:45 am]
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