Rule2026-22776
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
November 9, 2026
Effective
December 14, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2024-04-10 which applied to all Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2024-04-10 required repetitively inspecting certain part-numbered tail rotor (T/R) blades for a crack and, depending on the results, removing any cracked T/R blade from service. AD 2024-04-10 also prohibits installing certain T/R blades on any helicopter unless certain requirements are met. Since AD 2024-04-10 was issued, it was determined that inspection Method A should be discontinued and that additional limitations shall be provided. This AD retains the actions of AD 2024-04-10 and requires repetitively inspecting a certain tail rotor blade (TRB) assembly for cracks and, depending on the results, removing any cracked TRB assembly from service and replacing an affected part as terminating action for the repetitive inspections. This AD also prohibits installing an affected TRB assembly on any helicopter unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 215 (Monday, November 9, 2026)</title>
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[Federal Register Volume 91, Number 215 (Monday, November 9, 2026)]
[Rules and Regulations]
[Pages 70771-70774]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-22776]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-7230; Project Identifier MCAI-2026-00185-R;
Amendment 39-23512; AD 2026-22-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(AHD) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2024-04-10
which applied to all Airbus Helicopters Deutschland GmbH (AHD) Model
EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+,
EC135T3, and EC635T2+ helicopters. AD 2024-04-10 required repetitively
inspecting certain part-numbered tail rotor (T/R) blades for a crack
and, depending on the results, removing any cracked T/R blade from
service. AD 2024-04-10 also prohibits installing certain T/R blades on
any helicopter unless certain requirements are met. Since AD 2024-04-10
was issued, it was determined that inspection Method A should be
discontinued and that additional limitations shall be provided. This AD
retains the actions of AD 2024-04-10 and requires repetitively
inspecting a certain tail rotor blade (TRB) assembly for cracks and,
depending on the results, removing any cracked TRB assembly from
service and replacing an affected part as terminating action for the
repetitive inspections. This AD also prohibits installing an affected
TRB assembly on any helicopter unless certain requirements are met. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective December 14, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 14,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-7230; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
<bullet> For European Union Aviation Safety Agency (EASA) material
identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +49 221 8999 000; email: <a href="/cdn-cgi/l/email-protection#bbfaffc8fbdedac8da95decec9d4cbda95dece"><span class="__cf_email__" data-cfemail="2c6d685f6c494d5f4d0249595e435c4d024959">[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. It is also available at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2026-7230.
FOR FURTHER INFORMATION CONTACT: Soban Saeed, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316)
946-4123; email: <a href="/cdn-cgi/l/email-protection#25564a47444b0b5644404041654344440b424a53"><span class="__cf_email__" data-cfemail="5f2c303d3e31712c3e3a3a3b1f393e3e71383029">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
[[Page 70772]]
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2024-04-10, Amendment 39-22689 (89 FR
15431, March 4, 2024), (AD 2024-04-10). AD 2024-04-10 applied to all
AHD Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2,
EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2024-04-10 required
repetitively inspecting T/R blades having part number (P/N)
L642A2002111 or P/N L642A2002112 installed for a crack and, depending
on the results, removing any cracked T/R blade from service. AD 2024-
04-10 also prohibited installing certain T/R blades on any helicopter
unless certain requirements are met. The FAA issued AD 2024-04-10 to
detect and address cracks in affected T/R blades. The unsafe condition,
if not addressed, could result in separation of a T/R blade assembly
and subsequently reduced control of the helicopter.
The NPRM was published in the Federal Register on July 30, 2026 (91
FR 47994). The NPRM was prompted by an MCAI originated by EASA, which
is the Technical Agent for the Member States of the European Union.
EASA issued EASA AD 2026-0032, dated February 19, 2026 (EASA AD 2026-
0032) (also referred to as the MCAI). The MCAI states that a
determination was made by the manufacturer that a previously approved
inspection method (Method A) should be discontinued. Method A consisted
of a dye-penetrant (with increased temperature) inspection.
In the NPRM, the FAA proposed to retain the requirements of AD
2024-04-10 and also proposed to require repetitively inspecting a
certain TRB assembly for cracks and, depending on the results, removing
any cracked TRB assembly from service and replacing an affected part as
terminating action for the repetitive inspections. In the NPRM, the FAA
also proposed to prohibit installing an affected TRB assembly on any
helicopter unless certain requirements are met.
You may examine the MCAI in the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-7230.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These products have been approved by the civil aviation authority
of another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, that authority has notified the FAA of the unsafe condition
described in the MCAI referenced above. The FAA reviewed the relevant
data, considered any comments received, and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. Except for
minor editorial changes, this AD is adopted as proposed in the NPRM.
None of the changes will increase the economic burden on any operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed EASA AD 2026-0032, which specifies procedures for
repetitively inspecting the affected TRB assembly for cracks and, if
any crack is detected, replacing the affected TRB assembly with a
serviceable part. EASA AD 2026-0032 prohibits installing a certain TRB
assembly on any helicopter unless certain requirements are met and
specifies that replacing an affected TRB assembly with an eligible TRB
assembly that is not an affected part is terminating action for certain
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.
Differences Between This AD and the MCAI
The MCAI applies to Airbus Helicopters 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.
The MCAI specifies inspecting cracks by performing a visual
inspection, dye-penetrant inspection, eddy current inspection, or
fluorescent penetrant inspection, whereas this AD requires inspection
methods under certain scenarios as outlined in the regulatory text of
this AD, which are also described in a Note in the regulatory text of
this AD.
Costs of Compliance
The FAA estimates that this AD affects 359 helicopters of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspect one affected TRB 3 work-hours x $50 Up to $305............ Up to $109,495.
assembly (up to 10 per $85 per hour =
helicopter). $255.
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The FAA estimates the following costs to do any replacements that
will 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
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Action Labor cost Parts cost Cost per product
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Replace one TRB assembly (up to 10 3 work-hours x $85 $4,900 per TRB Up to $51,550.
per helicopter). per hour = $255. assembly.
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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.
[[Page 70773]]
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 has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--Airworthiness Directives
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive 2024-04-10, Amendment 39-22689 (89
FR 15431, March 4, 2024); and
0
b. Adding the following new airworthiness directive:
2026-22-10 Airbus Helicopters Deutschland GmbH (AHD):
Amendment 39-23512; Docket No. FAA-2026-7230; Project Identifier
MCAI-2026-00185-R.
(a) Effective Date
This airworthiness directive (AD) is effective December 14,
2026.
(b) Affected ADs
This AD replaces AD 2024-04-10, Amendment 39-22689 (89 FR 15431,
March 4, 2024) (AD 2024-04-10).
(c) Applicability
This AD applies to all Airbus Helicopters Deutschland GmbH (AHD)
Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2,
EC135T2+, EC135T3, and EC635T2+ helicopters, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC) Code 6410, Tail rotor
blades.
(e) Unsafe Condition
This AD was prompted by a report of a separated tail rotor blade
(TRB) assembly due to a crack in the TRB assembly caused by
intergranular corrosion. The FAA is issuing this AD to detect and
address cracks in the TRB assembly. The unsafe condition, if not
addressed, could result in separation of a TRB assembly and reduced
control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
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 2026-0032,
dated February 19, 2026 (EASA AD 2026-0032).
(h) Exceptions to EASA AD 2026-0032
(1) Where EASA AD 2026-0032 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2026-0032 refers to January 29, 2024 (the
effective date of EASA Emergency AD 2024-0028-E), this AD requires
using March 19, 2024 (the effective date of AD 2024-04-10).
(3) Where EASA AD 2026-0032 refers to flight hours, this AD
requires using hours time-in-service (TIS).
(4) Where paragraph (1) of EASA AD 2026-0032 specifies ``Before
an affected part exceeds 685 FH [flight hours] since first
installation on a helicopter'', this AD requires replacing that text
with ``Before an affected part accumulates 685 hours TIS since first
installation on a helicopter, or within 10 hours TIS after March 19,
2024 (the effective date of AD 2024-04-10), whichever occurs
later''.
(5) Where paragraph 4.3 of the material referenced in EASA AD
2026-0032 recommends type II visible dye inspections, this AD
requires the inspection methods in paragraphs (h)(5)(i), (ii), or
(iii) of this AD, as applicable:
(i) If the affected part has previously been inspected using a
type II visible dye method, perform type II visible dye (Method B of
the material referenced in EASA AD 2026-0032) or eddy current
inspections, instead of fluorescent penetrant inspections.
(ii) If the affected part has not previously been inspected
using a type II visible dye inspection, perform eddy current or
fluorescent penetrant inspections, instead of type II visible dye
inspections.
(iii) If you cannot determine whether the affected part has
previously been inspected by a type II visible dye method, clean all
surfaces to be inspected and perform an eddy current or a
fluorescent penetrant inspection, instead of a type II visible dye
inspection.
Note 1 to paragraph (h)(5): The FAA reminds operators of the
airworthiness concern regarding type II visible dye inspections of
critical parts discussed in FAA Special Airworthiness Information
Bulletin (SAIB) CE-18-26R1, dated October 30, 2018 (SAIB CE-18-
26R1). SAIB CE-18-26R1 explains the risks associated with using type
II visible dye inspection methods, including the prohibition in ASTM
E1417 on the use of type II visible dye penetrant prior to the use
of type I fluorescent penetrant on the same surface. SAIB CE-18-26R1
also advises of the importance of pre- and post-inspection cleaning
to ensure proper detection of cracks. You can find SAIB CE-18-26R1
at <a href="http://drs.faa.gov">drs.faa.gov</a>.
Note 2 to paragraph (h)(5): The material referenced in EASA AD
2026-0032 identifies a type II visible dye inspection as Method A
(not allowed) or Method B; eddy current inspection as Method C;
fluorescent penetrant inspection as Method D; and visual inspection
as Method E.
Note 3 to paragraph (h)(5): When entering compliance with the
applicable paragraph of the AD into the helicopter maintenance
records, documenting that a type II visible dye inspection was
performed improves the accuracy of maintenance records.
(6) This AD does not adopt paragraph (3) of EASA AD 2026-0032.
(7) This AD does not adopt the ``Remarks'' section of EASA AD
2026-0032.
(i) No Reporting or Returning of Parts
Where the material referenced in EASA AD 2026-0032 specifies to
submit certain information and to send removed parts to the
manufacturer, this AD does not include those actions.
(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 responsible 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#3f7e72707c7f595e5e11585049"><span class="__cf_email__" data-cfemail="2f6e62606c6f494e4e01484059">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
[[Page 70774]]
of the local flight standards district office/certificate holding
district office.
(l) Additional Information
For more information about this AD, contact Soban Saeed,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (316) 946-4123; email:
<a href="/cdn-cgi/l/email-protection#a0d3cfc2c1ce8ed3c1c5c5c4e0c6c1c18ec7cfd6"><span class="__cf_email__" data-cfemail="2754484546490954464242436741464609404851">[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 2026-0032,
dated February 19, 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#acede8dfecc9cddfcd82c9d9dec3dccd82c9d9"><span class="__cf_email__" data-cfemail="3574714675505446541b5040475a45541b5040">[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, 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="92f4e0bcfbfce1e2f7f1e6fbfdfcd2fcf3e0f3bcf5fde4">[email protected]</span></a>.
Issued on October 30, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-22776 Filed 11-6-26; 8:45 am]
BILLING CODE 4910-13-P
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