Proposed Rule2026-19890
Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) 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
September 29, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2025-13-06, which applies to certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2025-13-06 requires inspections of the ball pivot, control rod, and yaw actuator assembly and, depending on the results of these inspections, corrective actions. AD 2025-13-06 also prohibits installing an affected part unless it is a serviceable part and certain requirements are met. Since the FAA issued AD 2025-13-06, the manufacturer developed a repetitive inspection of the ball pivot. This proposed AD would retain some of the actions of AD 2025-13-06 and would require repetitive inspection of the ball pivot and, depending on the results of those inspections, corrective actions. This proposed AD would also prohibit installing an affected part unless it is a serviceable part and certain requirements are met. Additionally, this proposed AD would require reporting the results of the inspections. 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 187 (Tuesday, September 29, 2026)</title>
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[Federal Register Volume 91, Number 187 (Tuesday, September 29, 2026)]
[Proposed Rules]
[Pages 61361-61364]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-19890]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-11790; Project Identifier MCAI-2025-01757-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 supersede Airworthiness Directive (AD)
2025-13-06, which applies to certain Airbus Helicopters Deutschland
GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2,
EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2025-13-06 requires
inspections of the ball pivot, control rod, and yaw actuator assembly
and, depending on the results of these inspections, corrective actions.
AD 2025-13-06 also prohibits installing an affected part unless it is a
serviceable part and certain requirements are met. Since the FAA issued
AD 2025-13-06, the manufacturer developed a repetitive inspection of
the ball pivot. This proposed AD would retain some of the actions of AD
2025-13-06 and would require repetitive inspection of the ball pivot
and, depending on the results of those inspections, corrective actions.
This proposed AD would also prohibit installing an affected part unless
it is a serviceable part and certain requirements are met.
Additionally, this proposed AD would require reporting the results of
the inspections. 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 13, 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-2026-11790; 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#d09194a390b5b1a3b1feb5a5a2bfa0b1feb5a5"><span class="__cf_email__" data-cfemail="18595c6b587d796b79367d6d6a776879367d6d">[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: Mahmood Shah, Aviation Safety
[[Page 61362]]
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5538; email: <a href="/cdn-cgi/l/email-protection#90fdf1f8fdfffff4bef7bee3f8f1f8d0f6f1f1bef7ffe6"><span class="__cf_email__" data-cfemail="365b575e5b595952185118455e575e7650575718515940">[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-2026-11790; Project
Identifier MCAI-2025-01757-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 the 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
Mahmood Shah, 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
The FAA issued AD 2025-13-06, Amendment 39-23072 (90 FR 28879, July
2, 2025) (AD 2025-13-06), for certain AHD Model EC135P1, EC135P2,
EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+
helicopters. AD 2025-13-06 was prompted by an MCAI originated by EASA,
which is the Technical Agent for the Member States of the European
Union. EASA issued AD 2025-0108, dated May 8, 2025, (EASA AD 2025-0108)
to correct an unsafe condition identified as damage to the ball bearing
control system.
AD 2025-13-06 requires a one-time visual inspection of the ball
pivot, fluorescent penetrant inspection of the control rod, visual
inspection and measurement of certain parts of the yaw actuator
assembly, and depending on the results of these inspections, corrective
actions. AD 2025-13-06 also prohibits installing an affected part
unless it is a serviceable part and certain requirements are met. The
FAA issued AD 2025-13-06 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.
Actions Since AD 2025-13-06 Was Issued
Since the FAA issued AD 2025-13-06, EASA superseded EASA AD 2025-
0108 and issued EASA AD 2025-0260, dated November 25, 2025 (EASA AD
2025-0260) (also referred to as the MCAI). The MCAI states the
manufacturer developed a repetitive inspection of the ball pivot.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-11790.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2025-0260, which specifies procedures for
a one-time visual inspection of the ball pivot, a fluorescent penetrant
inspection of the control rod of the yaw actuator, inspection of the
yaw actuator interface connections, and a check (inspection) of the
freedom of movement of the tail rotor control. Depending on the
inspection results, EASA AD 2025-0260 specifies procedures for
corrective actions to include further inspections and the replacement
of affected parts.
In addition, EASA AD 2025-0260 specifies procedures for repetitive
inspection of the ball pivot, and depending on the results of the
inspections, corrective actions, which include further inspections and
the replacement of affected parts. EASA AD 2025-0260 requires reporting
the inspection results (including no findings) to AHD and prohibits
installing ball pivot part number (P/N) 92-201-00 and P/N 92-207-00;
yaw actuator assembly P/N L672M2005104, P/N L672M2005105, and P/N
L672M2005106; and control rod P/N L672M2006101 and P/N L672M2006102 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 2025-0260, described previously, 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+, EC635 P3, EC635 T1, and EC635
T3 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 2025-0260 by reference in the FAA final rule. This proposed AD
would, therefore, require compliance with EASA AD 2025-0260 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
[[Page 61363]]
section in EASA AD 2025-0260 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 2025-0260. Material required by
EASA AD 2025-0260 for compliance will be available at <a href="http://regulations.gov">regulations.gov</a>
under Docket No. FAA-2026-11790 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 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 interface 2 work-hours x $85 0 $170................ $64,090.
connections. per hour = $170.
Inspect control rod.............. 1 work-hour x $85 0 $85................. $32,045.
per hour= $85.
Report inspection results........ 1 work-hour x $85 0 $85................. $32,045.
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 inspection. The agency
has no way of determining the number of helicopters that might need
these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace adapter............................... 1 work-hour x $85 per hour = $85 $803 $888
Replace ball pivot............................ 1 work-hour x $85 per hour = $85 2,846 2,931
Replace close tolerance bolt.................. 1 work-hour x $85 per hour = $85 42 127
Replace connector cover....................... 1 work-hour x $85 per hour = $85 571 656
Replace control rod........................... 1 work-hour x $85 per hour = $85 6,835 6,920
Replace input lever........................... 2 work-hours x $85 per hour = 9,755 9,925
$170.
Replace rod end............................... 1 work-hour x $85 per hour = $85 643 728
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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 be
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 that the 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.
[[Page 61364]]
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:
0
a. Removing Airworthiness Directive 2025-13-06, Amendment 39-23072 (90
FR 28879, July 2, 2025); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters Deutschland GmbH (AHD): Docket No. FAA-2026-
11790; Project Identifier MCAI-2025-01757-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by November 13, 2026.
(b) Affected ADs
This AD replaces AD 2025-13-06, Amendment 39-23072 (90 FR 28879,
July 2, 2025).
(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 up to and including 1999.
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 and the
determination that repetitive inspection of the ball pivot is
necessary. 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 2025-0260,
dated November 25, 2025 (EASA AD 2025-0260).
(h) Exceptions to EASA AD 2025-0260
(1) Where EASA AD 2025-0260 requires compliance in terms of
flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2025-0260 refers to its effective date, this
AD requires using the effective date of this AD.
(3) Where EASA AD 2025-0260 refers to May 15, 2025 (the
effective date of EASA AD 2025-0108), this AD requires using July
18, 2025 (the effective date of AD 2025-13-06).
(4) Where the material referenced in EASA AD 2025-0260 specifies
``check'', this AD requires replacing that text with ``inspection''.
(5) Where the material referenced in EASA AD 2025-0260 specifies
to examine the close-tolerance bolt, the input lever, the rod end,
the adapter, and the connector cover for wear and damage, for the
purposes of this AD damage is defined as specified in paragraphs
(h)(5)(i) through (iv) 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 rod end is defined as corrosion, gouges,
bending, and seizing.
(iv) Damage for the adapter or connector cover is defined as
deformation, elongated attachment holes, gouges, cracks, corrosion,
and missing surface coating on the adapter or connector.
(6) Where the material referenced in EASA AD 2025-0260 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.
(7) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0260.
(i) No Returning Parts Requirement
Although the material referenced in EASA AD 2025-0260 specifies
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
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#72333f3d31321413135c151d04"><span class="__cf_email__" data-cfemail="0544484a46456364642b626a73">[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 Mahmood Shah,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5538; email:
<a href="/cdn-cgi/l/email-protection#6c010d0401030308420b421f040d042c0a0d0d420b031a"><span class="__cf_email__" data-cfemail="3459555c595b5b501a531a475c555c745255551a535b42">[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 2025-0260,
dated November 25, 2025.
(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#f1b0b582b194908290df9484839e8190df9484"><span class="__cf_email__" data-cfemail="6322271023060210024d0616110c13024d0616">[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 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#ed8b9fc384839e9d888e99848283ad838c9f8cc38a829b"><span class="__cf_email__" data-cfemail="761004581f1805061315021f1918361817041758111900">[email protected]</span></a>.
Issued on September 24, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-19890 Filed 9-28-26; 8:45 am]
BILLING CODE 4910-13-P
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