[Federal Register Volume 90, Number 130 (Thursday, July 10, 2025)]
[Rules and Regulations]
[Pages 30581-30583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-12873]
[[Page 30581]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0617; Project Identifier MCAI-2024-00331-R;
Amendment 39-23075; AD 2025-13-09]
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 AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-
365N, and SA-365N1 helicopters. This AD was prompted by reports of loss
of tightening torque between the upper ball bearing end and the main
rotor (MR) servo-control. This AD requires inspecting the tightening
torque and, depending on the results, taking corrective action. This AD
also requires reporting information. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 14, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 14,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0617; 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-2025-0617.
FOR FURTHER INFORMATION CONTACT: Peter Schmitt, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (206) 231-3377; 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 Airbus Helicopters
Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N, and SA-365N1
helicopters. The NPRM was published in the Federal Register on April
15, 2025 (90 FR 15667). The NPRM was prompted by EASA AD 2024-0110,
dated June 6, 2024 (EASA AD 2024-0110) (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 two occurrences were reported of
loss of tightening torque between the upper ball bearing end and the MR
servo-control, which in one occurrence, led to the disconnection of
these two parts. The MCAI further states that the investigation is
still on-going to determine the root cause. EASA considers this MCAI an
interim action and further action may follow.
In the NPRM, the FAA proposed to require inspecting the tightening
torque and, depending on the results, taking corrective action.
Additionally, in the NPRM the FAA proposed to require reporting certain
information.
The FAA is issuing this AD to detect loss of tightening torque. The
unsafe condition, if not addressed, could result in disconnection
between the upper ball bearing end and the MR servo-control, and
consequent loss of control of the helicopter.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-0617.
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 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.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0110 requires a one-time check of the torque on each
nut connecting the upper ball bearing end to all three MR servo-
controls and, depending on the results, taking corrective actions,
which include applying torque, lockwire, and sealing compound to the
upper ball bearing end of the MR servo-control, inspecting the ball
bearing end of the MR-servo control, replacing a ball bearing end,
inspecting the upper end fitting of the MR-servo control, and replacing
the MR servo-control. EASA AD 2024-0110 also requires reporting the
inspection results (including no findings) to AH [Airbus Helicopters].
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
The MCAI, as well as the material referenced in the MCAI, refer to
the ``torque inspection'' as a ``check.'' In an FAA AD, a ``check'' may
be done by the owner/operator (pilot) holding at least a private pilot
certificate provided certain criteria are met. The authorization for a
``check'' in an FAA AD is an exception to the FAA's standard
maintenance regulations and the criteria is not met in this AD.
Accordingly, this AD requires those actions be accomplished by persons
authorized under 14 CFR 43.3.
Interim Action
The FAA considers that this AD is an interim action. If final
action is later identified, the FAA might consider further rulemaking
then.
Costs of Compliance
The FAA estimates that this AD affects 63 helicopters of U.S.
registry. Labor costs are estimated at $85 per hour. Based on these
numbers, the FAA estimates the following costs to comply with this AD.
Inspecting the tightening torque of the upper ball bearing end of
each MR servo control will take 1 work-hour for an
[[Page 30582]]
estimated cost of $255 per helicopter (three MR servo-controls per
helicopter) and $16,065 for the U.S. fleet.
Reporting the results of the inspection will take 1 work-hour for
an estimated cost of $85 per helicopter and $5,355 for the U.S. fleet.
If required, applying torque, lock-wire, and sealing compound to
the upper ball bearing end of each MR servo-control will take .5 work-
hour and parts will cost a nominal amount for an estimated cost of
$127.50 per helicopter (for up to three MR servo-controls per
helicopter).
If required, inspecting the threads of a ball bearing end will take
1 work-hour for an estimated cost of $85 per ball bearing end.
Depending on the results, replacing a ball bearing end will take 1
work-hour and parts will cost $1,299 for an estimated cost of $1,384
per ball bearing end.
If required, inspecting the threads of an upper end fitting will
take 1 work-hour for an estimated cost of $85 per upper-end fitting.
Depending on the results, replacing an MR servo-control will take 1
work-hour and parts will cost $41,039 for an estimated cost of $41,124
per MR servo-control.
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
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:
2025-13-09 Airbus Helicopters: Amendment 39-23075; Docket No. FAA-
2025-0617; Project Identifier MCAI-2024-00331-R.
(a) Effective Date
This airworthiness directive (AD) is effective August 14, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Model AS-365N2, AS 365 N3,
EC 155B, EC155B1, SA-365N, and SA-365N1 helicopters, certificated in
any category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6710, Main rotor
control.
(e) Unsafe Condition
This AD was prompted by reports of two occurrences of loss of
tightening torque between the upper ball bearing end and the main
rotor (MR) servo-control. The FAA is issuing this AD to detect loss
of tightening torque. The unsafe condition, if not addressed, could
result in disconnection between the upper ball bearing end and the
MR servo-control, and consequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency AD 2024-0110,
dated June 6, 2024 (EASA AD 2024-0110).
(h) Exceptions to EASA AD 2024-0110
(1) Where EASA AD 2024-0110 defines ``the ASB'', this AD
requires replacing that definition with ``Airbus Helicopters Alert
Service Bulletin (ASB) AS365-67-30-0001, AS366-67-30-0001, or EC155-
67-30-0001, each Issue 2 and dated May 15, 2024, as applicable for
the model helicopter. For compliance with this AD, Model SA-365N and
SA-365N1 helicopters are to use ASB AS365-67-30-0001, Issue 2, dated
May 15, 2024''.
(2) Where EASA AD 2024-0110 requires compliance in terms of
flight hours, this AD requires using hours time-in-service.
(3) Where EASA AD 2024-0110 refers to its effective date, this
AD requires using the effective date of this AD.
(4) Where paragraph (1) of EASA AD 2024-0110 and the material
referenced in EASA AD 2024-0110 specify ``check'', this AD requires
replacing that text with ``inspect'' or ``inspection'' as
applicable.
(5) Where the material referenced in EASA AD 2024-0110 specifies
discarding parts, this AD requires removing those parts from
service.
(6) Where the material referenced in EASA AD 2024-0110 specifies
hard point, for this AD a hard point may be indicated by resistance,
ratcheting, blocking, or difficulty when turning the ball bearing
end into the upper end fitting of the MR servo-control by hand.
[[Page 30583]]
(7) Where paragraph (3) of EASA AD 2024-0110 specifies reporting
inspection results (including no findings) to AH [Airbus
Helicopters] within 7 days after the inspection required by
paragraph (1) of EASA AD 2024-0110, this AD requires reporting that
information at the applicable time in paragraph (h)(7)(i) or (ii) of
this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection
required by paragraph (1) of EASA AD 2024-0110.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(8) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0110.
(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 local Flight
Standards District 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. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(j) Additional Information
For more information about this AD, contact Peter Schmitt,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (206) 231-3377; 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 2024-0110,
dated June 6, 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 EASA AD 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 July 1, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-12873 Filed 7-9-25; 8:45 am]
BILLING CODE 4910-13-P