Rule2026-01956
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
February 2, 2026
Effective
February 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2014-13- 09, which applied to certain Airbus Helicopters Deutschland GmbH (AHD) helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. AD 2014-13-09 required repetitive visual inspections of the ring frame X9227 for a crack, and if there is a crack, replacing the ring frame. Since the FAA issued AD 2014-13-09, AHD Helicopters determined that this unsafe condition also applies to AHD Model EC135P3 and EC135T3 helicopters. This AD continues to require some of the actions required by AD 2014-13-09 and expands the applicability by including AHD Model EC135P3 and EC135T3 helicopters and also reduces the compliance time for the repetitive inspections. This AD also allows the modification of the ring frame X9227 as terminating action for the repetitive visual inspections. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 91 Issue 21 (Monday, February 2, 2026)</title>
</head>
<body><pre>
[Federal Register Volume 91, Number 21 (Monday, February 2, 2026)]
[Rules and Regulations]
[Pages 4434-4438]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-01956]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-0733; Project Identifier MCAI-2025-01329-R;
Amendment 39-23251; AD 2026-03-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(AHD) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2014-13-
09, which applied to certain Airbus Helicopters Deutschland GmbH (AHD)
helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and
EC135T2+ helicopters. AD 2014-13-09 required repetitive visual
inspections of the ring frame X9227 for a crack, and if there is a
crack, replacing the ring frame. Since the FAA issued AD 2014-13-09,
AHD Helicopters determined that this unsafe condition also applies to
AHD Model EC135P3 and EC135T3 helicopters. This AD continues to require
some of the actions required by AD 2014-13-09 and expands the
applicability by including AHD Model EC135P3 and EC135T3 helicopters
and also reduces the compliance time for the repetitive inspections.
This AD also allows the modification of the ring frame X9227 as
terminating action for the repetitive visual inspections. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective February 17, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 17,
2026.
The FAA must receive comments on this AD by March 19, 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.
[[Page 4435]]
<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-2026-0733; 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
street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For European Union Aviation Safety Agency (EASA) material
identified in this final rule, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone +49 221 8999 000; email
<a href="/cdn-cgi/l/email-protection#d59491a695b0b4a6b4fbb0a0a7baa5b4fbb0a0"><span class="__cf_email__" data-cfemail="4001043300252133216e2535322f30216e2535">[email protected]</span></a>; website: easa.europa.eu. You may find the EASA
material on the EASA website at ad.easa.europa.eu.
<bullet> You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 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
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-0733.
FOR FURTHER INFORMATION CONTACT: Shailesh Malla, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5584; email: <a href="/cdn-cgi/l/email-protection#cbb8a3aaa2a7aeb8a3e5a6aaa7a7aa8badaaaae5aca4bd"><span class="__cf_email__" data-cfemail="22514a434b4e47514a0c4f434e4e43624443430c454d54">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments using a method listed under
the ADDRESSES section. Include ``Docket No. FAA-2026-0733; Project
Identifier MCAI-2025-01329-R'' at the beginning of your comments. The
most helpful comments reference a specific portion of the final rule,
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 final rule 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 final rule.
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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to
Shailesh Malla, 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 2014-13-09, Amendment 39-17885 (79 FR 41095, July
15, 2014) (AD 2014-13-09), for AHD Model EC135P1, EC135P2, EC135P2+,
EC135T1, EC135T2, and EC135T2+ helicopters with mounting ring frame
X9227, part number (P/N) L535H2120301, P/N L535H2120303, or P/N
L535H2120304, installed, except those with frame reinforcement P/N
L535H2100201 installed. AD 2014-13-09 was prompted by an MCAI
originated by EASA, which is the Technical Agent for the Member States
of the European Union. EASA issued EASA Emergency AD 2013-0289-E, dated
December 6, 2013 (EASA Emergency AD 2013-0289-E), to correct an unsafe
condition identified as a fatigue crack in the ring frame. AD 2014-13-
09 required visually inspecting the ring frame X9227 for a crack
between the rivets and if there is a crack, replacing the ring frame
with an airworthy part. The FAA issued AD 2014-13-09 to detect a crack
in the ring frame and prevent loss of the tail rotor and consequent
loss of control of the helicopter.
Actions Since AD 2014-13-09 Was Issued
Since the FAA issued AD 2014-13-09, EASA superseded EASA Emergency
AD 2013-0289-E and issued EASA AD 2025-0174, dated August 5, 2025,
which retained the requirements of EASA Emergency AD 2013-0289-E and
expanded the applicability to apply to Model EC135P3 and EC135T3
helicopters. Additionally, EASA issued EASA AD 2025-0174R1, dated
September 22, 2025 (EASA AD 2025-0174R1) (also referred to as the
MCAI). The MCAI states that an additional occurrence of a crack, this
time running along six rivets of the ring frame rather than only three,
was reported.
Accordingly, the manufacturer revised the service information,
which consisted of reducing the repetitive inspection intervals and
also specifying modification instructions, which is a terminating
action for the repetitive inspections. The MCAI also states the
compliance time for the required modification can be extended.
The FAA is issuing this AD to detect a crack in the ring frame and
prevent loss of the tail rotor and consequent loss of control of the
helicopter. The FAA is also considering separate rulemaking to address
the requirements for modifying the helicopter which may constitute as
terminating action for the required repetitive inspections.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-0733.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2025-0174R1, which specifies procedures
for visually inspecting ring frame X9227 for a crack, and depending on
the results of the inspection, contacting AHD for approved repair
instructions. EASA AD 2025-0174R1 also specifies procedures for
modifying the ring frame X9227 which is considered terminating action
for the repetitive inspections.
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
[[Page 4436]]
this AD after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.
AD Requirements
This AD requires accomplishing the actions specified in EASA AD
2025-0174R1, described previously, as incorporated by reference, except
for any differences identified as exceptions in the regulatory text of
this AD. See ``Differences Between this AD and the MCAI'' for a
discussion of the general differences included in this AD.
Differences Between This AD and the MCAI
The MCAI applies to EC635P2+ and EC635T1 helicopters, whereas this
AD does not because those models do not have an FAA type certificate.
The MCAI requires contacting the manufacturer if a crack is found,
whereas this AD requires replacing the ring frame if there is a crack.
The MCAI specifies to modify the helicopter by installing a new
frame reinforcement. The FAA is considering requiring this
modification; in the interim, this AD allows the modification as an
optional terminating action for the repetitive inspections, but does
not require it.
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 2025-0174R1 by reference in the FAA final rule. This AD would,
therefore, require compliance with EASA AD 2025-0174R1 in its entirety
through that incorporation, except for any differences identified as
exceptions in the regulatory text of this AD. Using common terms that
are the same as the heading of a particular section in EASA AD 2025-
0174R1 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 2025-0174R1. Material required in EASA AD 2025-
0174R1 for compliance will be available at <a href="http://regulations.gov">regulations.gov</a> under Docket
No. FAA-2026-0733 after the FAA final rule is published.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because the affected components are part of an assembly that is
critical to the control of a helicopter. In addition, cracking could
lead to instantaneous failure before detection. A crack running along
six rivets of the ring frame was reported. As the FAA currently lacks
definitive information pertaining to the extent of cracking of the
affected components that may already exist in helicopters or how
quickly the condition may propagate to failure. Thus, for certain
helicopters the initial instance of the actions required by this AD
must be accomplished within 50 hours time-in-service (TIS) and
thereafter within intervals not to exceed 25 hours TIS. These
compliance times are shorter than the time necessary for the public to
comment and for publication of the final rule. Accordingly, notice and
opportunity for prior public comment are impracticable and contrary to
the public interest pursuant to 5 U.S.C. 553(b).
In addition, the FAA finds that good cause exists pursuant to 5
U.S.C. 553(d) for making this amendment effective in less than 30 days,
for the same reasons the FAA found good cause to forgo notice and
comment.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 370 helicopters of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect ring frame X9227................. 1 work-hour x $85 per hour $0 $85 $31,450
= $85.
----------------------------------------------------------------------------------------------------------------
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
this replacement.
On-Condition Costs
------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
------------------------------------------------------------------------
Replacing the ring frame 40 work-hours x $10,000 $13,400
X9227. $85 per hour =
$3,400.
Modify ring frame X9227 with 17 work-hours x 3,688 5,133
retrofit kit SB-135-53-030- $85 per hour =
2C1. $1,445.
Modify ring frame X9227 with 17 work-hours x 1,438 2,883
retrofit kit SB-135-53-030- $85 per hour =
2C2. $1,445.
------------------------------------------------------------------------
[[Page 4437]]
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, and
(2) Will not affect intrastate aviation in Alaska.
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:
0
a. Removing Airworthiness Directive 2014-13-09, Amendment 39-17885 (79
FR 41095, July 15, 2014); and
0
b. Adding the following new airworthiness directive:
2026-03-02 Airbus Helicopters Deutschland GmbH (AHD): Amendment 39-
23251; Docket No. FAA-2026-0733; Project Identifier MCAI-2025-01329-
R.
(a) Effective Date
This airworthiness directive (AD) is effective February 17,
2026.
(b) Affected ADs
This AD replaces AD 2014-13-09, Amendment 39-17885 (79 FR 41095,
July 15, 2014).
(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 with mounting ring frame X9227, part number (P/N)
L535H2120301, L535H2120303, or L535H2120304, installed, except those
with frame reinforcement P/N L535H2100201 or L535H2100202 installed.
Note 1 to paragraph (c): Helicopters with an EC135P3H
designation are Model EC135P3 helicopters. Helicopters with EC135T3H
designation are Model EC135T3 helicopters.
(d) Subject
Joint Aircraft System Component (JASC) Code 5302, Rotorcraft
Tail Boom.
(e) Unsafe Condition
This AD was prompted by fatigue crack found on the ring frame
ring that attaches the fuselage tail boom structure to the tail
rotor housing. The FAA is issuing this AD to detect and address
fatigue cracking in the ring frame. The unsafe condition, if not
addressed, could result in loss of a tail rotor 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 paragraphs (h) and (i) of this AD:
Perform all required actions within the compliance times specified
in, and in accordance with, European Union Aviation Safety Agency
(EASA) AD 2025-0174R1, dated September 22, 2025 (EASA AD 2025-
0174R1).
(h) Exceptions to EASA AD 2025-0174R1
(1) Where EASA AD 2025-0174R1 refers to its effective date or
the effective date of August 19, 2025 [the effective date of EASA AD
2025-0174], this AD requires using the effective date of this AD.
(2) Where EASA AD 2025-0174R1 specifies compliance in terms of
flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (2) of EASA AD 2025-0174R1 specifies to
contact AHD for approved repair instructions and accomplish those
actions accordingly, this AD requires accomplishing those actions
using a method approved by the Manager, International Validation
Branch, FAA; EASA; or AHD's EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must include the DOA-authorized
signature.
(4) This AD does not require compliance with paragraph (3) of
EASA AD 2025-0174R1. This AD considers that modification an optional
action and does not require it.
(5) Where the material referenced in EASA AD 2025-0174R1
specifies ``if necessary, use a flashlight. A magnifying glass (at
least x10 magnification) can be used'', this AD requires replacing
that text with ``use a light source and at least 10X
magnification''.
(6) Where paragraph (5) of EASA AD 2025-0174R1 specifies that
modification of a helicopter as required by paragraph (3) of EASA AD
2025-0174R1 constitutes a terminating action for the repetitive
inspections as required by paragraph (1) of EASA AD 2025-0174R1,
this AD considers that modification an optional action and does not
require this action. For this AD, the modification terminates the
repetitive inspection requirement.
(7) This AD does not adopt the ``Remarks'' section of EASA AD
2025-0174R1.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2025-0174R1
specifies to submit certain information to the manufacturer, this AD
does not require that action.
(j) Special Flight Permits
Special flight permits are prohibited.
(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 (k) of
this AD and email to: <a href="/cdn-cgi/l/email-protection#db9a9694989bbdbabaf5bcb4ad"><span class="__cf_email__" data-cfemail="0e4f43414d4e686f6f20696178">[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 Shailesh Malla,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5584; email:
<a href="/cdn-cgi/l/email-protection#27544f464e4b42544f094a464b4b466741464609404851"><span class="__cf_email__" data-cfemail="2d5e454c4441485e4503404c41414c6d4b4c4c034a425b">[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 2025-0174R1,
dated September 22, 2025.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221
[[Page 4438]]
8999 000; email: <a href="/cdn-cgi/l/email-protection#efaeab9caf8a8e9c8ec18a9a9d809f8ec18a9a"><span class="__cf_email__" data-cfemail="b1f0f5c2f1d4d0c2d09fd4c4c3dec1d09fd4c4">[email protected]</span></a>; website: easa.europa.eu. You
may find the EASA 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 Pkwy., 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 <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#f49286da9d9a87849197809d9b9ab49a958695da939b82"><span class="__cf_email__" data-cfemail="dcbaaef2b5b2afacb9bfa8b5b3b29cb2bdaebdf2bbb3aa">[email protected]</span></a>.
Issued on January 28, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-01956 Filed 1-30-26; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on February 2, 2026.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.