Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 91, Number 156 (Friday, August 14, 2026)]
[Rules and Regulations]
[Pages 52494-52496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-16641]



[[Page 52494]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-4644; Project Identifier MCAI-2024-00418-R; 
Amendment 39-23440; AD 2026-16-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2023-25-
14, which applied to certain Airbus Helicopters Model EC130T2 
helicopters. AD 2023-25-14 revised the procedures for inspecting the 
vibration level on the tail rotor drive shaft and, depending on these 
results, required replacing certain parts. Since the FAA issued AD 
2023-25-14, the manufacturer developed a modification of the rear drive 
shaft, sliding flange, and equipped splined sleeve. This AD requires 
installing this modification and repetitively inspecting the vibration 
level of the tail rotor drive shaft. This AD also prohibits the 
installation of certain parts and prohibits the performance of a 
balance correction unless certain requirements are met. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective September 18, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
18, 2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-4644; 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; telephone +49 221 8999 000; email [email protected]; 
You may find this material on the website ad.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 
regulations.gov under Docket No. FAA-2026-4644.

FOR FURTHER INFORMATION CONTACT: Eric Rivera, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (773) 
412-9048; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2023-25-14, Amendment 39-22641 (88 FR 
89568, December 28, 2023) (AD 2023-25-14). AD 2023-25-14 applied to 
certain Airbus Helicopters Model EC130T2 helicopters. AD 2023-25-14 
required repetitively checking the balancing of the tail rotor drive 
shaft by measuring the vibration level. Depending on the results, AD 
2023-25-14 required replacing certain parts with new parts. AD 2023-25-
14 also prohibited installing certain part-numbered tail rotor drive 
shafts on any helicopter unless its requirements are met. The FAA 
issued AD 2023-25-14 to address an excessive vibration level on the 
tail rotor drive shaft. The unsafe condition, if not addressed, could 
result in failure of the tail rotor drive shaft and loss of yaw control 
of the helicopter.
    The NPRM was published in the Federal Register on May 22, 2026 (91 
FR 30257). The NPRM was prompted by EASA AD 2024-0144, dated July 19, 
2024 (EASA AD 2024-0144) (also referred to as the MCAI), issued by 
EASA, which is the Technical Agent for the Member States of the 
European Union. The MCAI states that the manufacturer developed a 
modification consisting of a new rear rotor drive shaft, a new sliding 
flange, and a new equipped splined sleeve, and that while these parts 
are less susceptible to cracks, insufficient data is available to treat 
them as terminating action for that AD's repetitive actions. In 
addition, EASA AD 2024-0144 expands the list of affected part numbers 
to include the new modified parts.
    In the NPRM, the FAA proposed to require installing this 
modification and repetitively inspecting the vibration level of the 
tail rotor drive shaft. In the NPRM, the FAA also proposed to prohibit 
the installation of certain parts and prohibit the performance of a 
balance correction unless certain requirements are met.
    The FAA is issuing this AD to address the unsafe condition on these 
products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2026-4644.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from an anonymous commenter who restated 
the applicability of the AD. The FAA infers that the commenter 
supported the NPRM without change.

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 2024-0144, which specifies procedures for 
repetitively checking the balancing of the tail rotor drive shaft by 
measuring the vibration level and, depending on the results, replacing 
certain parts with either used, new, or modified parts. EASA AD 2024-
0144 also prohibits performing a balance correction unless this action 
is performed concurrently with replacing certain parts. If a balance 
correction has already been performed independently of replacing those 
parts, EASA AD 2024-0144 specifies contacting Airbus Helicopters to 
obtain approved instructions and accomplishing those instructions. EASA 
AD 2024-0144 also specifies reporting the vibration measurements to 
Airbus Helicopters and installing modified rear drive shaft, sliding 
flange, and equipped splined sleeve parts. Lastly, EASA AD 2024-0144 
prohibits installing certain part-numbered tail rotor drive shafts, 
sliding flanges, or equipped splined sleeves on any helicopter.
    This material is reasonably available because the interested 
parties have

[[Page 52495]]

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

    Where EASA AD states to contact Airbus Helicopters, this AD would 
require contacting either the Manager, International Validation Branch, 
FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval 
(DOA).

Interim Action

    The FAA considers that this AD is an interim action. If final 
action is later identified, the FAA might consider further rulemaking 
then.

Costs of Compliance

    The FAA estimates that this AD affects 108 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
----------------------------------------------------------------------------------------------------------------
Vibration level.......................  1 work-hour x $85 per                 $0             $85          $9,180
inspection............................   hour = $85.
Install modified sliding flange,        8 work-hours x $85 per            61,716          62,396       6,738,768
 equipped splined sleeve, and rear       hour = $680.
 rotor drive shaft.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace sliding flange and equipped splined  8 work-hours x $85 per hour = $680.         $72,749         $73,429
 sleeve.
Balance correction.........................  3 work-hours x $85 per hour = $255.               0             255
----------------------------------------------------------------------------------------------------------------

    For helicopters that accomplished a balance correction in 
accordance with the instructions of the applicable AMM before the 
effective date of this AD, except those that accomplished a balance 
correction before the next flight after installing a new (zero total 
hours time-in-service) sliding flange and a new (zero total hours time-
in-service) equipped splined sleeve, the corrective action that may be 
needed could vary significantly from helicopter to helicopter. The FAA 
has no data to determine the costs to accomplish the corrective action 
or the number of helicopters that may require corrective action.

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 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 2023-25-14, Amendment 39-22641 (88 
FR 89568, December 28, 2023); and
0
b. Adding the following new airworthiness directive:

2026-16-10 Airbus Helicopters: Amendment 39-23440; Docket No. FAA-
2026-4644; Project Identifier MCAI-2024-00418-R.

(a) Effective Date

    This airworthiness directive (AD) is effective September 18, 
2026.

(b) Affected ADs

    This AD replaces AD 2023-25-14, Amendment 39-22641 (88 FR 89568, 
December 28, 2023).

(c) Applicability

    This AD applies to all Airbus Helicopters Model EC130T2 
helicopters, certificated in any category, as identified in European 
Union Aviation Safety Agency AD 2024-0144, dated July 19, 2024 (EASA 
AD 2024-0144).

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(d) Subject

    Joint Aircraft System Component (JASC) Code 6510, Tail rotor 
drive shaft.

(e) Unsafe Condition

    This AD was prompted by a report of a crack in the tailboom. The 
FAA is issuing this AD to address an excessive vibration level on 
the tail rotor drive shaft. The unsafe condition, if not addressed, 
could result in failure of the tail rotor drive shaft and loss of 
yaw 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, EASA AD 2024-0144.

(h) Exceptions to EASA AD 2024-0144

    (1) Where EASA AD 2024-0144 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) Where EASA AD 2024-0144 refers to its effective date, or 
where EASA AD 2024-0144 refers to November 6, 2023 [the effective 
date of EASA Emergency AD 2023-0190-E], this AD requires using the 
effective date of this AD.
    (3) Where EASA AD 2024-0144 refers to ``checks'', this AD 
requires replacing that text with ``inspections''.
    (4) Where paragraph (4) of EASA AD 2024-0144 specifies to 
``contact AH [Airbus Helicopters] to obtain approved instructions'', 
this AD requires replacing that text with ``accomplish corrective 
action in accordance with a method approved by the Manager, 
International Validation Branch, FAA; or EASA; or Airbus 
Helicopters' EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature''.
    (5) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0144.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0144 specifies 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (k) of 
this AD and email to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Additional Information

    For more information about this AD, contact Eric Rivera, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (773) 412-9048; email: 
[email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material identified in this AD 
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 2024-0144, 
dated July 19, 2024.
    (ii) [Reserved]
    (3) For EASA material identified in this AD, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
8999 000; email [email protected]; website easa.europa.eu. You may 
find the EASA material on the EASA website 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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on August 5, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-16641 Filed 8-13-26; 8:45 am]
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