Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 90, Number 167 (Tuesday, September 2, 2025)]
[Rules and Regulations]
[Pages 42310-42312]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-16761]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0752; Project Identifier MCAI-2024-00340-R; 
Amendment 39-23124; AD 2025-17-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters Model EC 130 B4 and EC 130 T2 helicopters. This AD 
was prompted by a report of heavy damage on the fenestron due to the 
loss of the tail rotor (TR) blade, which broke at the TR hub tension-
torsion bar (tension-torsion bar). This AD requires inspecting the 
tension-torsion bar and, depending on the inspection results, replacing 
the part with a serviceable part. This AD also prohibits performing 
maintenance using certain maintenance

[[Page 42311]]

manuals. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective October 7, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 7, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No.FAA-2025-0752; 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: [email protected]; 
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, FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, 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 
regulations.gov under Docket No. FAA-2025-0752.

FOR FURTHER INFORMATION CONTACT: Tara Lucas, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 
231-3189; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to all Airbus Helicopters 
Model EC 130 B4 and EC 130 T2 helicopters. The NPRM was published in 
the Federal Register on May 9, 2025 (90 FR 19660). The NPRM was 
prompted by AD 2024-0113, dated June 13, 2024 (EASA AD 2024-0113) (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 an 
occurrence was reported of heavy damage on the fenestron due to the 
loss of the TR blade, which broke at the tension-torsion bar and 
separated from the hub assembly.
    In the NPRM, the FAA proposed to require inspecting the tension-
torsion bar and, depending on the inspection results, replacing the 
part with a serviceable part. The NPRM also proposed to prohibit 
performing maintenance using certain maintenance manuals. The FAA is 
issuing this AD to prevent failure of the tension-torsion bar, which 
could result in loss of the TR anti-torque function and consequent loss 
control of the helicopter.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2025-0752.

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 2024-0113, which specifies procedures for 
inspecting all lamellas that compose the tension-torsion bar and, if 
any discrepancy is detected, replacing the part with a serviceable 
part. The material referenced by EASA AD 2024-0113 defines 
discrepancies as cracks, nail-sensitive scratches, distorted lamellas, 
circular contact indications, and marks. EASA AD 2024-0113 also 
prohibits accomplishing maintenance using certain maintenance manuals 
dated prior to March 5, 2024.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 108 helicopters of U.S. 
registry. Labor rates are estimated at $85 per hour. Based on these 
numbers, the FAA estimates the following costs to comply with this AD.
    Inspecting all 10 tension-torsion bars on each helicopter (to 
include removing any corrosion) will take 4 work-hours for an estimated 
cost of $340 per helicopter and $36,720 for the U.S. fleet.
    If required, replacing a tension-torsion bar will take 4 work-hours 
and parts will cost $1,144 for an estimated cost of $1,484 per 
replacement.

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,
    (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.

[[Page 42312]]

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 adding the following new airworthiness 
directive:

2025-17-14 Airbus Helicopters: Amendment 39-23124; Docket No. FAA-
2025-0752; Project Identifier MCAI-2024-00340-R.

(a) Effective Date

    This airworthiness directive (AD) is effective October 7, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model EC 130 B4 and EC 130 
T2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6500, Tail Rotor 
Drive System.

(e) Unsafe Condition

    This AD was prompted by a report of heavy damage on the 
fenestron due to the loss of the tail rotor (TR) blade, which broke 
at the TR hub tension-torsion bar. The FAA is issuing this AD to 
prevent failure of the tension-torsion bar. The unsafe condition, if 
not addressed, could result in loss of the TR anti-torque function 
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: Comply 
with all required actions and compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency AD 2024-0113, 
dated June 13, 2024 (EASA AD 2024-0113).

(h) Exceptions to EASA AD 2024-0113

    (1) Where EASA AD 2024-0113 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) Where EASA AD 2024-0113 refers to its effective date, this 
AD requires using the effective date of this AD.
    (3) Where EASA AD 2024-0113 defines Groups, for this AD, Group 1 
also includes those helicopters for which it cannot be determined if 
maintenance was accomplished using Aircraft Maintenance Manual (AMM) 
64-21-00.6-27A or 64-21-00.6-27B, dated earlier than March 5, 2024.
    (4) Where paragraph (2) of EASA AD 2024-0113 specifies 
``discrepancies as identified in the ASB are'', this AD requires 
replacing that text with, ``a discrepancy, which is defined as a 
crack, nail-sensitive scratch, deformed lamella, broken lamella, 
mark, circular contact indication (other than those on the first and 
last lamella of the tension-torsion bar), or the P/N is not written 
on the first and the last lamella, is''.
    (5) Where paragraph (3) of EASA AD 2024-0113 specifies ``an 
aeroplane'', this AD requires replacing that text with ``any 
helicopter''.
    (6) Where the material referenced in EASA AD 2024-0113 specifies 
to discard parts, this AD requires removing those parts from 
service.
    (7) Where the material referenced in EASA AD 2024-0113 specifies 
actions for non-installed equipment or parts, this AD does not 
require those actions.
    (8) This AD does not adopt the ``Remarks'' section of EASA AD 
2024-0113.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2024-0113 specifies 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

(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 (l) 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. The following provisions also apply to this AD.

(l) Additional Information

    For more information about this AD, contact Tara Lucas, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; phone: (206) 231-3189; email: [email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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 2024-0113, 
dated June 13, 2024.
    (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: [email protected]; 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 Parkway, 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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on August 20, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2025-16761 Filed 8-29-25; 8:45 am]
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