Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 91, Number 155 (Thursday, August 13, 2026)]
[Rules and Regulations]
[Pages 52221-52223]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-16507]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-4646; Project Identifier MCAI-2025-01763-R; 
Amendment 39-23435; AD 2026-16-05]
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 
certain Airbus Helicopters Model AS350B2 helicopters. This AD was 
prompted by a report of magnetization on the solenoid valves for the 
three main servo-controls, the regulator block, and the tail servo-
control due to a diode not properly installed in the hydraulic circuit. 
This AD requires performing a cut-off test of the rear rotor actuator 
valve and, depending on the results of the test, performing corrective 
actions. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective September 17, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
17, 2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-4646; 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 Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; phone: +49 221 8999 000; email: [email protected]; 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 
regulations.gov under Docket No. FAA-2026-4646.

FOR FURTHER INFORMATION CONTACT: Aryanna Sanchez, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (817) 222-4058; 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 certain Airbus 
Helicopters Model AS350B2 helicopters. The NPRM was published in the 
Federal Register on May 28, 2026 (91 FR 31673). The NPRM was prompted 
by an MCAI, issued by EASA, which is the Technical Agent for the Member 
States of the European Union. EASA issued EASA AD 2025-0263, dated 
November 26, 2025; corrected December 9, 2025 (EASA AD 2025-0263) (also 
referred to as the MCAI). The MCAI states that during maintenance on a 
helicopter, magnetization was observed on the solenoid valves for the 
three main servo-controls, the regulator block, and the tail servo-
control. The MCAI also states that after further investigation, it was 
determined that diode 43D2 was not installed in the hydraulic circuit. 
In the NPRM, the FAA proposed to require performing a cut-off test of 
the rear rotor actuator valve and depending on the results of the test, 
the FAA proposed to require performing corrective actions. 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-2026-4646.

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 2025-0263, which specifies procedures for 
performing a cut-off test, and, if any discrepancy (failure of the 
test) is detected, replacing any affected diodes, or installing any 
missing diodes. This material is reasonably available because the 
interested parties have access to it through their normal course of 
business

[[Page 52222]]

or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 12 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
----------------------------------------------------------------------------------------------------------------
Perform cut-off test..................  3 work-hours x $85 per                $0            $255          $3,060
                                         hour = $255.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any installations or 
replacements that would be required based on the results of the test. 
The agency has no way of determining the number of helicopters that 
might need these installations or replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace diode.................................  1 work-hour x $85 per hour = $85            $180            $265
Install diode.................................  5 work-hours x $85 per hour =              1,000           1,425
                                                 $425.
----------------------------------------------------------------------------------------------------------------

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:

2026-16-05 Airbus Helicopters: Amendment 39-23435; Docket No. FAA-
2026-4646; Project Identifier MCAI-2025-01763-R.

(a) Effective Date

    This airworthiness directive (AD) is effective September 17, 
2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS350B2 
helicopters as specified in European Union Aviation Safety Agency AD 
2025-0263, dated November 26, 2025; corrected December 9, 2025 (EASA 
AD 2025-0263).

(d) Subject

    Joint Aircraft System Component (JASC) Code 2900, Hydraulic 
power system.

(e) Unsafe Condition

    This AD was prompted by a report of magnetization on the 
solenoid valves for the three main servo-controls, the regulator 
block, and the tail servo-control due to a diode not properly 
installed in the hydraulic circuit. The FAA is issuing this AD to 
prevent loss of the efficiency of the yaw load compensator and of 
hydraulic assistance for the three main servo-controls and the tail 
servo-control. The unsafe condition, if not addressed, could result 
in reduced 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 2025-0263.

(h) Exceptions to EASA AD 2025-0263

    (1) Where EASA AD 2025-0263 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2025-0263 requires compliance in terms of 
flight hours, this AD requires using hours' time-in-service.
    (3) Where the material referenced in EASA AD 2025-0263 specifies 
``remove the diode 43D2'', this AD requires replacing that text with 
``remove the diode 43D2 from service''.
    (4) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0263.

(i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0263 specifies 
to submit certain information to the manufacturer, this AD does not 
require that action.

[[Page 52223]]

(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 Aryanna Sanchez, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (817) 222-5110; email: 
[email protected].

(l) 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 2025-0263, 
dated November 26, 2025; corrected December 9, 2025.
    (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.
    (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, the availability of this material at NARA, 
visit www.archives.gov/federal-register/cfr/ibr-locations or email 
[email protected].

    Issued on July 30, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-16507 Filed 8-12-26; 8:45 am]
BILLING CODE 4910-13-P

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