Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 90, Number 84 (Friday, May 2, 2025)]
[Rules and Regulations]
[Pages 18774-18776]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-07573]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0007; Project Identifier MCAI-2023-00998-R; 
Amendment 39-23021; AD 2025-08-08]
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 SA341G and SA342J helicopters. This AD was 
prompted by reports of corrosion on the contact surfaces of the tail 
rotor inclined and horizontal drive shaft flanges. This AD requires 
repetitively inspecting the inclined and horizontal drive shaft flanges 
and, depending on the results, replacing the inclined or horizontal 
drive shaft. This AD also prohibits installing certain inclined and 
horizontal drive shafts unless certain requirements are met. These 
actions are specified in a European Union Aviation Safety Agency (EASA) 
AD, which is proposed for incorporation by reference. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 6, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 6, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No.FAA-2025-0007; 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 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, 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-2025-0007.

FOR FURTHER INFORMATION CONTACT: Evan Weaver, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 
946-4152; 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 SA341G and SA342J (Gazelle) helicopters. The NPRM published in 
the Federal Register on January 17, 2025 (90 FR 5748). The NPRM was 
prompted by AD 2023-0168, dated August 31, 2023 (EASA AD 2023-0168) 
(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 
there have been several reports of corrosion on the contact surfaces of 
the tail rotor inclined and horizontal drive shaft flanges. More 
detailed non-destructive testing indicated pitting corrosion on the 
mating faces of several flanges and further investigation revealed 
various regions of intergranular failure beneath

[[Page 18775]]

the surface of corrosion pits. The unsafe condition, if not addressed, 
could result in the failure of the tail rotor drive and subsequent loss 
of control of the helicopter.
    In the NPRM, the FAA proposed to require repetitively inspecting 
the inclined and horizontal drive shaft flanges and, depending on the 
results, replacing the inclined or horizontal drive shaft. In the NPRM, 
the FAA also proposed to prohibit installing certain inclined and 
horizontal drive shafts 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-2025-0007.

Discussion of Final Airworthiness Directive

Comments

    The FAA received two comments from an anonymous commenter and an 
individual who supported the NPRM without change.

Conclusion

    These products have been approved by the 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, it has notified the FAA of the unsafe condition described in 
the MCAI referenced above. The FAA reviewed the relevant data, 
considered the comment received, and determined that air safety 
requires adopting the 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.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2023-0168, which specifies procedures for 
repetitively inspecting the flanges of certain part-numbered inclined 
and horizontal drive shafts for corrosion, and if corrosion is found, 
replacing the affected inclined or horizontal drive shaft. EASA AD 
2023-0168 also prohibits installing an affected inclined or horizontal 
drive shaft on any helicopter unless it is a serviceable part as 
defined within.
    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 material referenced in the MCAI specifies sending corroded 
parts to Airbus Helicopters, whereas this AD does not require that 
action.

Costs of Compliance

    The FAA estimates that this AD affects 63 helicopters of U.S. 
registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Visually inspecting the inclined and horizontal drive shaft flanges 
takes 4 work-hours for an estimated cost of $340 per helicopter and 
$21,420 for the U.S. fleet, per inspection cycle. If required, 
replacing the inclined or horizontal drive shaft takes 4 work-hours and 
parts will cost $17,900 (inclined drive shaft) or $35,500 (horizontal 
drive shaft), for an estimated cost of $18,240 or $35,840 respectively 
per helicopter.

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.

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:

2025-08-08 Airbus Helicopters: Amendment 39-23021; Docket No. FAA-
2025-0007; Project Identifier MCAI-2023-00998-R.

(a) Effective Date

    This airworthiness directive (AD) is effective June 6, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model SA341G and SA342J 
helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6510, Tail Rotor 
Drive Shaft.

(e) Unsafe Condition

    This AD was prompted by reports of corrosion on the contact 
surfaces of the tail rotor inclined and horizontal drive shaft 
flanges. The FAA is issuing this AD to detect and address corrosion 
on the inclined and horizontal drive shaft flanges. The unsafe 
condition, if not addressed, could result in the failure of the tail 
rotor drive and subsequent loss of 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 2023-0168, 
dated August 31, 2023 (EASA AD 2023-0168).

[[Page 18776]]

(h) Exceptions to EASA AD 2023-0168

    (1) Where EASA AD 2023-0168 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (2) Where EASA AD 2023-0168 refers to its effective date, this 
AD requires using the effective date of this AD.
    (3) Where the material referenced in paragraph (2) of EASA 2023-
0168 specifies sending corroded inclined or horizontal drive shaft 
to Airbus Helicopters, this AD does not require that action.
    (4) This AD does not adopt the ``Remarks'' section of EASA AD 
2023-0168.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2023-0168 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 (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.

(l) Additional Information

    For more information about this AD, contact Evan Weaver, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (316) 946-4152; email: 
[email protected].

(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 2023-0168, 
dated August 31, 2023.
    (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 this 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 April 21, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2025-07573 Filed 5-1-25; 8:45 am]
BILLING CODE 4910-13-P

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