Airworthiness Directives; Airbus Helicopters

Issuing agencies

Abstract

The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B3, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This proposed AD was prompted by a report of the loss of the tightening torque between the upper ball bearing end and a main rotor (MR) servo-control. This proposed AD would require an inspection of the nut tightening torque of the upper ball bearing end of all the MR servo-controls and, depending on the results, corrective actions. The proposed AD would also require reporting the inspection results. The FAA is proposing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 91 Issue 200 (Monday, October 19, 2026)</title>
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[Federal Register Volume 91, Number 200 (Monday, October 19, 2026)]
[Proposed Rules]
[Pages 66019-66022]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-21387]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-11814; Project Identifier MCAI-2026-00715-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Helicopters Model AS350B3, AS355F, AS355F1, AS355F2, 
AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This proposed AD was 
prompted by a report of the loss of the tightening torque between the 
upper ball bearing end and a main rotor (MR) servo-control. This 
proposed AD would require an inspection of the nut tightening torque of 
the upper ball bearing end of all the MR servo-controls and, depending 
on the results, corrective actions. The proposed AD would also require 
reporting the inspection results. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by December 3, 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-2026-11814; 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

[[Page 66020]]

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#5415102714313527357a3121263b24357a3121"><span class="__cf_email__" data-cfemail="6524211625000416044b0010170a15044b0010">[email&#160;protected]</span></a>; website: easa.europa.eu.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 10101 Hillwood Parkway, 
Fort Worth, TX 76177. For information on the availability of this 
material at the FAA, call (817) 222-5110.

FOR FURTHER INFORMATION CONTACT: Aryanna Sanchez, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (520) 990-9321; email: <a href="/cdn-cgi/l/email-protection#4a2b38332b24242b643e64392b2429222f300a2c2b2b642d253c"><span class="__cf_email__" data-cfemail="dabba8a3bbb4b4bbf4aef4a9bbb4b9b2bfa09abcbbbbf4bdb5ac">[email&#160;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 ADDRESSES. Include ``Docket No. FAA-2026-11814; Project 
Identifier MCAI-2026-00715-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 NPRM. Submissions containing CBI should be sent to 
Aryanna Sanchez, 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 2026-0132, dated July 8, 2026 (EASA 
AD 2026-0132) (also referred to as the MCAI), to correct an unsafe 
condition on all Airbus Helicopters Model AS 350 B3, AS 355 F, AS 355 
F1, AS 355 F2, AS 355 N, AS 355 NP, EC 130 B4, and EC 130 T2 
helicopters. The MCAI states a report was received of the loss of the 
tightening torque between the upper ball bearing end and an MR servo-
control. The MCAI also states further investigations determined that 
the presence of paint or protection on the nut retainer (lock-washer) 
is the root cause for this loss of tightening torque, and that this 
deficiency may occur on any of the three (forward, left, and right) MR 
servo-controls installed on a helicopter.
    The FAA is issuing this proposed AD to inspect the nut tightening 
torque of the upper ball bearing end of all the MR servo-controls and, 
if necessary, accomplish corrective actions. The unsafe condition, if 
not addressed, could result in the disconnection of the upper ball 
bearing end from the MR servo-control and loss of control of a 
helicopter.
    You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2026-11814.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2026-0132, which specifies procedures for 
a one-time inspection and thereafter, after each removal and 
installation of an MR servo-control, inspection of the nut tightening 
torque of the upper ball bearing end of the forward, left, and right MR 
servo-controls, having a part number (P/N) and manufacturer P/N as 
identified in Appendix 1 of the MCAI, and the associated nut retainer 
(lock-washer) having manufacturer P/N 360A27-2121-20 or 365A27-8193-20. 
Depending on the results, the MCAI specifies procedures for re-
inspecting the nut tightening torque and accomplishing corrective 
actions, including inspecting the threads of the MR servo-control and, 
if necessary, cleaning them; replacing the ball bearing end; replacing 
the MR servo-control; or contacting AH [Airbus Helicopters] for 
approved instructions. EASA AD 2026-0132 also requires reporting of all 
inspection results.
    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 2026-0132, described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD. See ``Differences Between this Proposed AD 
and the MCAI'' for a discussion of the general differences included in 
this proposed AD.

Differences Between This Proposed AD and the MCAI

    Where the MCAI specifies contacting Airbus Helicopters if an 
unacceptable value of the nut tightening torque is found, this proposed 
AD would require performing corrective actions in accordance with a 
method approved by the Manager, International Validation Branch, FAA; 
or EASA; or Airbus Helicopters' Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

Interim Action

    The FAA considers that this proposed AD would be an interim action. 
If final actions are later identified, the FAA might consider further 
rulemaking.

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

[[Page 66021]]

coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2026-0132 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2026-0132 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 2026-0132 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 2026-
0132. Material required by EASA AD 2026-0132 for compliance will be 
available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-11814 after the 
FAA final rule is published.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 980 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
----------------------------------------------------------------------------------------------------------------
Inspect the nut tightening torque of the    1 work-hour x $85 per hour =        $190          $275      $269,500
 upper ball bearing end.                     $85.
Report inspection results.................  1 work-hour x $85 per hour =           0            85        83,300
                                             $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any replacements that 
would be required based on the results of the proposed inspection. The 
agency has no way of determining the number of helicopters that might 
need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Inspect ball bearing end threads.....  1 work-hour x $85 per    $0.....................  $85.
                                        hour = $85.
Inspect the MR servo-control threads.  1 work-hour x $85 per    $0.....................  $85.
                                        hour = $85.
Clean MR servo-control threads.......  1 work-hour x $85 per    $0.....................  $85.
                                        hour = $85.
Replace one ball bearing end.........  1 work-hour x $85 per    Up to $530.............  Up to $615.
                                        hour = $85.
Replace one MR servo-control.........  4 work-hours x $85 per   Up to $54,300..........  Up to $54,640.
                                        hour = $340.
----------------------------------------------------------------------------------------------------------------

    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.

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 current 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

    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
    (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:

[[Page 66022]]

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-2026-11814; Project Identifier 
MCAI-2026-00715-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by December 3, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS350B3, AS355F, 
AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 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 a report of the loss of the tightening 
torque between the upper ball bearing end and a main rotor (MR) 
servo-control. The FAA is issuing this AD to inspect the nut 
tightening torque of the upper ball bearing end of all the MR servo-
controls and, if necessary, accomplish corrective actions. The 
unsafe condition, if not addressed, could result in the 
disconnection of the upper ball bearing end from the MR servo-
control and loss of control of a 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 (EASA) AD 
2026-0132, dated July 8, 2026 (EASA AD 2026-0132).

(h) Exceptions to EASA AD 2026-0132

    (1) Where EASA AD 2026-0132 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2026-0132 refers to flight hours, this AD 
requires using hours time-in-service.
    (3) Where paragraph (5) of EASA AD 2026-0132 and the material 
referenced in EASA AD 2026-0132 specify to contact AH [Airbus 
Helicopters] for corrective actions and instructions, this AD 
requires accomplishing corrective actions in accordance with a 
method approved by the Manager, International Validation Branch, 
FAA; or EASA; or Airbus Helicopters' Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (4) Where the material referenced in EASA AD 2026-0132 specifies 
discarding certain parts, this AD requires removing those parts from 
service.
    (5) Where the material referenced in EASA AD 2026-0132 specifies 
``check'', this AD requires replacing that text with ``inspection''.
    (6) This AD does not adopt the ``Remarks'' section of EASA AD 
2026-0132.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the following:
    (1) Airbus Service Bulletin AS350-67-30-0002, dated 01 April 
2026.
    (2) Airbus Service Bulletin AS355-67-30-0001, dated 01 April 
2026.
    (3) Airbus Service Bulletin EC130-67-30-0001, dated 01 April 
2026.

(j) 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 (k) of 
this AD and email to: <a href="/cdn-cgi/l/email-protection#d6979b999596b0b7b7f8b1b9a0"><span class="__cf_email__" data-cfemail="72333f3d31321413135c151d04">[email&#160;protected]</span></a>.
    (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.

(k) Additional Information

    For more information about this AD, contact Aryanna Sanchez, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (520) 990-9321; email: 
<a href="/cdn-cgi/l/email-protection#80e1f2f9e1eeeee1aef4aef3e1eee3e8e5fac0e6e1e1aee7eff6"><span class="__cf_email__" data-cfemail="29485b5048474748075d075a48474a414c53694f4848074e465f">[email&#160;protected]</span></a>.

(l) 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 2026-0132, 
dated July 8, 2026.
    (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#b2f3f6c1f2d7d3c1d39cd7c7c0ddc2d39cd7c7"><span class="__cf_email__" data-cfemail="e7a6a394a782869486c9829295889786c98292">[email&#160;protected]</span></a>; website: easa.europa.eu.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 10101 Hillwood Parkway, 
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#9dfbefb3f4f3eeedf8fee9f4f2f3ddf3fceffcb3faf2eb"><span class="__cf_email__" data-cfemail="8bedf9a5e2e5f8fbeee8ffe2e4e5cbe5eaf9eaa5ece4fd">[email&#160;protected]</span></a>.

    Issued on October 15, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-21387 Filed 10-16-26; 8:45 am]
BILLING CODE 4910-13-P


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