Proposed Rule2026-19971
Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters
Primary source
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Published
September 30, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. This proposed AD was prompted by a report of a loss of the tail rotor controls due to a broken control rod of the yaw actuator. This proposed AD would require a one-time inspection of the ball pivot, yaw actuator assembly, and associated parts, and a repetitive inspection of the ball pivot. Depending on the inspection results, this proposed AD would require replacement of affected parts, further inspections, and application of new sealing compound. This proposed AD would also prohibit the installation of an affected part unless it is a serviceable part and certain requirements are met. 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 188 (Wednesday, September 30, 2026)</title>
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[Federal Register Volume 91, Number 188 (Wednesday, September 30, 2026)]
[Proposed Rules]
[Pages 61803-61806]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-19971]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-11792; Project Identifier MCAI-2026-00135-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(AHD) 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 certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1,
EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and
EC635T2+ helicopters. This proposed AD was prompted by a report of a
loss of the tail rotor controls due to a broken control rod of the yaw
actuator. This proposed AD would require a one-time inspection of the
ball pivot, yaw actuator assembly, and associated parts, and a
repetitive inspection of the ball pivot. Depending on the inspection
results, this proposed AD would require replacement of affected parts,
further inspections, and application of new sealing compound. This
proposed AD would also prohibit the installation of an affected part
unless it is a serviceable part and 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 November 16, 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-2026-11792; 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#befffacdfedbdfcddf90dbcbccd1cedf90dbcb"><span class="__cf_email__" data-cfemail="5e1f1a2d1e3b3f2d3f703b2b2c312e3f703b2b">[email 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: Anthony Kenward, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5152; email: <a href="/cdn-cgi/l/email-protection#4d2c233925222334632f632628233a2c3f290d2b2c2c632a223b"><span class="__cf_email__" data-cfemail="0869667c60676671266a26636d667f697a6c486e6969266f677e">[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 ADDRESSES. Include ``Docket No. FAA-2026-11792; Project
Identifier MCAI-2026-00135-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
Anthony Kenward, 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 2026-0024, dated February 5, 2026
(EASA AD 2026-0024) (also referred to as the MCAI), to correct an
unsafe condition on certain AHD Model EC135 P1, EC135 P2, EC135 P2+,
EC135 P3, EC135 T1, EC135 T2, EC135 T2+, EC135 T3, EC635 P2+, EC635 T1,
and EC635 T2+ helicopters. The MCAI states an occurrence was reported
where the pilot lost the tail rotor controls after hearing a noise from
the rear of the helicopter, and investigation revealed a broken control
rod of the yaw actuator. The unsafe condition, if not addressed, could
result in loss of tail rotor controls and 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-2026-11792.
[[Page 61804]]
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2026-0024, which specifies procedures for
a one-time inspection of the yaw actuator and ball pivot and, depending
on the inspection results, corrective actions to include further
inspections and the replacement of affected parts. EASA AD 2026-0024
also specifies procedures for a fluorescent penetrant inspection of the
rod end, if applicable, the connecting part of the yaw actuator,
replacement of the sealing compound on the rod end, and a check
(inspection) of the freedom of movement of the tail rotor control.
Depending on the inspection results, EASA AD 2026-0024 specifies
procedures for corrective actions to include further inspections and
the replacement of affected parts.
In addition, EASA AD 2026-0024 specifies procedures for repetitive
inspection of the ball pivot, and depending on the results of the
inspections, corrective actions. EASA AD 2026-0024 also prohibits
installing a yaw actuator assembly part number (P/N) L672M2005107; and
dual yaw actuator assembly P/N L221M1047101, L221M1047102,
L221M1047103, L221M1047104, L221M1047105 and L221M1047106; or a certain
part-numbered control rod or ball pivot on any 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 2026-0024, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this proposed 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
The MCAI applies to Model EC635 P2+, and EC635 T1 helicopters,
whereas this AD does not because those models do not have an FAA type
certificate.
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 2026-0024 by reference in the FAA final rule. This proposed AD
would, therefore, require compliance with EASA AD 2026-0024 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 2026-0024 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 2026-0024. Material required by
EASA AD 2026-0024 for compliance will be available at <a href="http://regulations.gov">regulations.gov</a>
under Docket No. FAA-2026-11792 after the FAA final rule is published.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 377 helicopters of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspect ball pivot................ 2 work-hours x $85 $0 $170 per inspection. $64,090 per
per hour = $170. inspection.
Perform fluorescent penetrant 2 work-hours x $85 $0 $170................ $64,090.
inspection. per hour = $170.
Inspect yaw actuator assembly, 2 work-hours x $85 $0 $170................ $64,090.
control rod, and interface per hour = $170.
connections.
Replace or inspect sealing 1 work-hour x $85 nominal $85................. $32,045.
compound. per hour = $85.
Inspect freedom of movement....... 1 work-hour x $85 $0 $85 per inspection.. $32,045 per
per hour = $85. inspection.
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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
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Replace adapter.............. 1 work-hour x $803 $888
$85 per hour =
$85.
[[Page 61805]]
Replace ball pivot........... 1 work-hour x 2,846 2,931
$85 per hour =
$85.
Replace close tolerance bolt. 1 work-hour x 42 127
$85 per hour =
$85.
Replace connector cover...... 1 work-hour x 571 656
$85 per hour =
$85.
Replace control rod.......... 1 work-hour x 6,835 6,920
$85 per hour =
$85.
Replace input lever.......... 2 work-hours x 9,755 9,925
$85 per hour =
$170.
Replace rod end.............. 1 work-hour x 643 728
$85 per hour =
$85.
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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:
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 Deutschland GmbH (AHD): Docket No. FAA-2026-
11792; Project Identifier MCAI-2026-00135-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by November 16, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH (AHD)
Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2,
EC135T2+, EC135T3, and EC635T2+ helicopters, certificated in any
category, serial numbers 0005 through 1276.
Note 1 to paragraph (c): Helicopters with an EC135P3H
designation are Model EC135P3 helicopters, and helicopters with an
EC135T3H designation are Model EC135T3 helicopters.
(d) Subject
Joint Aircraft System Component (JASC) Code 6720, Tail rotor
control system.
(e) Unsafe Condition
This AD was prompted by a report of a loss of tail rotor
controls due to a broken control rod of the yaw actuator. The FAA is
issuing this AD to detect and address damage to the ball bearing
control system. The unsafe condition, if not addressed, could result
in loss of tail rotor controls and 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 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 2026-0024,
dated February 5, 2026 (EASA AD 2026-0024).
(h) Exceptions to EASA AD 2026-0024
(1) Where EASA AD 2026-0024 requires compliance in terms of
flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2026-0024 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where the material referenced in EASA AD 2026-0024 specifies
``check'', this AD requires replacing that text with ``inspection''.
(4) Where the material referenced in EASA AD 2026-0024 specifies
to examine the close-tolerance bolt, the input lever, the adapter,
and the connector part of the control rod for wear and damage, for
the purposes of this AD damage is defined as specified in paragraphs
(h)(4)(i) through (iii) of this AD, as applicable.
(i) Damage for the close-tolerance bolt is defined as deformed
or stripped, rounded head; bent, stripped, or missing threads; bent
shank; grooves in the shank, corrosion or rust; and gouges.
(ii) Damage for the input lever is defined as deformation or
elongated attachment hole; bent flange; gouges; corrosion; and
cracks.
(iii) Damage for the adapter or connecting part is defined as
deformation, elongated attachment holes, gouges, cracks, corrosion,
and missing surface coating on the adapter or connecting part.
(5) Where the material referenced in EASA AD 2026-0024 specifies
if the ball pivot shows rough stiffness, hard stops, corrosion, or
damage, for the purposes of this AD damage is defined as deformation
(bent flanges), gouges, areas of bare metal, or missing finish.
(6) This AD does not adopt the ``Remarks'' section of EASA AD
2026-0024.
(i) No Reporting or Returning of Parts Requirement
Although the material referenced in EASA AD 2026-0024 specifies
to submit certain information or to return parts to the
manufacturer, this AD does not require that action.
(j) Special Flight Permits
Special flight permits, as described in 14 CFR 21.197 and
21.199, are not allowed.
(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
[[Page 61806]]
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 (l) of
this AD and email to: <a href="/cdn-cgi/l/email-protection#edaca0a2aead8b8c8cc38a829b"><span class="__cf_email__" data-cfemail="581915171b183e3939763f372e">[email 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.
(l) Additional Information
For more information about this AD, contact Anthony Kenward,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5152; email:
<a href="/cdn-cgi/l/email-protection#55343b213d3a3b2c7b377b3e303b22342731153334347b323a23"><span class="__cf_email__" data-cfemail="bfded1cbd7d0d1c691dd91d4dad1c8decddbffd9dede91d8d0c9">[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 2026-0024,
dated February 5, 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#c08184b380a5a1b3a1eea5b5b2afb0a1eea5b5"><span class="__cf_email__" data-cfemail="9bdadfe8dbfefae8fab5feeee9f4ebfab5feee">[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, 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#096f7b2760677a796c6a7d6066674967687b68276e667f"><span class="__cf_email__" data-cfemail="e98f9bc780879a998c8a9d808687a987889b88c78e869f">[email protected]</span></a>.
Issued on September 25, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-19971 Filed 9-29-26; 8:45 am]
BILLING CODE 4910-13-P
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