Airworthiness Directives; Airbus Helicopters

[Federal Register Volume 91, Number 115 (Tuesday, June 16, 2026)]
[Rules and Regulations]
[Pages 36083-36085]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-12048]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-5387; Project Identifier MCAI-2024-00399-R; 
Amendment 39-23337; AD 2026-09-15]
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) 2023-01-04 
for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, 
AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP 
helicopters. AD 2023-01-04 required, for helicopters with certain part-
numbered tail rotor head (TRH) spider pitch change units installed, 
inspecting the pitch change spider nut (nut) for correct installation; 
marking a 2 to 5 mm wide black paint index mark and repetitively 
inspecting the alignment of the marking; and performing additional 
inspections and corrective actions if necessary. Since the FAA issued 
AD 2023-01-04, new or more restrictive airworthiness limitations were 
issued, which terminated the requirement for the repetitive inspections 
of the black paint index marking. This AD requires the same actions as 
AD 2023-01-04, except for the repetitive black paint index marking 
inspections and prohibits installing certain parts unless certain 
requirements are met. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective July 21, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 21, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2025-5387; 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 Airbus Helicopters material identified in this AD, 
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 
75052; phone: (972) 641-0000 or (800) 232-0323; fax: (972) 641-3775; 
website: airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
    <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-2025-5387.

FOR FURTHER INFORMATION CONTACT: Matthew Williams, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (316) 946-4134; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2023-01-04, Amendment 39-22298 (88 FR 6618, 
February 1, 2023), (AD 2023-01-04). AD 2023-01-04 applied to Airbus 
Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, 
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 
2023-01-04 required, for helicopters with certain part-numbered TRH 
spider pitch change units installed, inspecting for correct 
installation of the nut; marking a 2 to 5 mm wide black paint index 
mark to identify the position of certain parts; and after the initial 
marking, repetitively inspecting the alignment of the marking; and 
additional inspections and corrective actions if necessary. 
Additionally, AD 2023-01-04 prohibited installing an affected part on a 
helicopter unless certain requirements were met. The FAA issued AD 
2023-01-04 to detect improper installation of the nut and improper 
alignment of a black index marking.
    The NPRM was published in the Federal Register on December 17, 2025 
(90 FR 58512). The NPRM was prompted by European Union Aviation Safety 
Agency (EASA) AD 2021-0282R1, Revision 1, dated July 10, 2024 (EASA AD 
2021-0282R1) (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 revised the Airworthiness Limitations 
Section (ALS), as applicable, which now includes the repetitive black 
index marking checks (inspections).
    In the NPRM, the FAA proposed to require the same actions as AD 
2023-01-04, except the NPRM only proposed to require the initial black 
paint index marking inspection, not the repetitive inspections. The FAA 
also proposed to prohibit installing an affected part on a helicopter 
unless certain requirements are met.
    You may examine the AD docket at regulations.gov under Docket No. 
FAA-2025-5387.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from an individual commenter. The 
following presents the comment received on the NPRM and the FAA's 
response to the comment.

Request To Clarify Black Paint Index Mark Visual Inspection for New 
Units

    The commenter requested that the FAA add language to paragraph 
(g)(2) of the proposed AD to clarify whether a 10 hour time-in-service 
visual inspection of the black paint index mark is required on a pitch 
change unit that is new or newly overhauled.
    The FAA disagrees with the request to update paragraph (g)(2) of 
this AD but

[[Page 36084]]

agrees to clarify that the repetitive black paint index mark visual 
inspections are now integrated into the ALS for affected part numbers 
350A33-2030-00, 350A33-2167-00, and 350A33-2167-01, in accordance with 
the applicable ALS. No changes were made to this AD as a result of this 
comment.

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 and technical corrections in paragraph (h) to 
accurately reflect the parts installation limitations, 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 Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS350-05.01.03, and Airbus Helicopters ASB No. AS355-05.00.86, both 
Revision 1 and dated July 8, 2024, which include Figure 1 that 
identifies the position of the TRH pitch change unit and of the bearing 
spacer to be marked with a 2 to 5 mm wide black paint index mark. This 
material also specifies procedures for inspecting the condition and 
installation of the nut; and inspecting the application and alignment 
of the black index mark on the TRH pitch change unit and the bearing 
spacer.
    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 AS350BB, whereas this 
AD does not because that model does not have an FAA type certificate.

Costs of Compliance

    The FAA estimates that this AD affects 972 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
----------------------------------------------------------------------------------------------------------------
Inspect the nut............................  1 work-hour x $85 per hour =           $0         $85       $82,620
                                              $85.
Inspect alignment of marking...............  1 work-hour x $85 per hour =            0          85        82,620
                                              $85.
Place black paint marking..................  1 work-hour x $85 per hour =            0          85        82,620
                                              $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any repairs/
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 repairs or replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                  Action                            Labor cost           Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Inspect the TRH pitch change unit........  13 work-hours x $85 per               $0  $1,105.
                                            hour = $1,105.
Replace bushes...........................  1 work-hour x $85 per hour         5,918  6,003 per helicopter.
                                            = $85.
Replace a rotating plate.................  1 work-hour x $85 per hour        27,375  27,460 per helicopter.
                                            = $85.
----------------------------------------------------------------------------------------------------------------

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:

[[Page 36085]]

0
a. Removing Airworthiness Directive 2023-01-04, Amendment 39-22298 (88 
FR 6618, February 1, 2023); and
0
b. Adding the following new airworthiness directive:

2026-09-15 Airbus Helicopters: Amendment 39-23337; Docket No. FAA-
2025-5387; Project Identifier MCAI-2024-00399-R.

(a) Effective Date

    This airworthiness directive (AD) is effective July 21, 2026.

(b) Affected ADs

    This AD replaces AD 2023-01-04, Amendment 39-22298 (88 FR 6618, 
February 1, 2023).

(c) Applicability

    This AD applies to all Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, 
AS355N, and AS355NP helicopters, certificated in any category.
    Note 1 to paragraph (c): Helicopters with AS350B3e designation 
are Model AS350B3 helicopters.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6420, Tail rotor 
head.

(e) Unsafe Condition

    This AD was prompted by an occurrence reported where, during an 
inspection of a tail rotor head (TRH) pitch change unit, excessive 
play and excessive wear were detected, due to an unwanted rotating 
motion and updated airworthiness limitations and maintenance tasks. 
The FAA is issuing this AD to detect improper installation of the 
pitch change spider nut (nut) and improper alignment of a black 
index marking. The unsafe condition, if not addressed, could result 
in loss of the TRH pitch change control 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

    (1) For helicopters with TRH pitch change unit, part number (P/
N) 350A33-2030-00, 350A33-2167-00, or 350A33-2167-01 installed, 
within 50 hours time-in-service (TIS) after the effective date of 
this AD, inspect the nut for correct installation. If the nut is 
missing or loose, before further flight, remove the bearing from the 
TRH pitch change unit and do the following:
    (i) Inspect the TRH pitch change unit for corrosion. If there is 
any corrosion, before further flight, remove the affected part from 
service and replace with an airworthy part.
    Note 2 to paragraph (g)(1)(i): Airbus Helicopters Mechanical 
Repair Manual (MRM) AS350 65-20-00-713, dated March 29, 2017, also 
known as Work Card 65-20-00-713 MRM, and Airbus Aircraft Maintenance 
Manual (AMM) AS350 65-21-00, 4-9b, dated May 16, 2019, also known as 
Task 65-21-00, 4-9 AMM, specify disassembly and reassembly 
information for the TRH pitch change unit.
    (ii) Inspect for rotation and wear on the faces of the bushes. 
For the purposes of this AD, indications of rotation and wear 
include tearing, peening, metal pick-up, and hammering. If there is 
any rotation or any wear on the faces of the bushes, before further 
flight, remove the bushes from service and replace with airworthy 
bushes.
    (iii) Using 5X or higher power magnification, visually inspect 
the rotating plate and the rotating plate threads for damage. For 
the purposes of this AD, indications of damage include wear, 
deformation, stripping, galling, and corrosion. If there is any 
damage on the rotating plate or the rotating plate threads, before 
further flight, remove the rotating plate from service and replace 
with an airworthy rotating plate.
    (iv) Identify the position of the TRH pitch change unit (item a) 
and of bearing spacer (item b) by marking a 2 to 5 mm wide black 
paint index mark (item C) with black paint as depicted in Figure 1, 
Section B-B, of Airbus Helicopters Alert Service Bulletin (ASB) No. 
AS350-05.01.03, (ASB AS350-05.01.03 Rev 1), or Airbus Helicopters 
ASB No. AS355-05.00.86 (ASB AS355-05.00.86 Rev 1), both Revision 1, 
and dated July 8, 2024, as applicable to the model helicopter.
    (2) Within 10 hours TIS after the initial marking required by 
paragraph (g)(1)(iv) of this AD, visually inspect the alignment of 
the marking. An example of a properly aligned marking is depicted in 
Figure 1, Section B-B of ASB AS350-05.01.03 Rev 1 and ASB AS355-
05.00.86 Rev 1, as applicable to the model helicopter. If the black 
paint index mark (item C) is misaligned, before further flight, 
inspect the TRH pitch change unit by accomplishing the actions 
required by paragraphs (g)(1)(i) and (ii) of this AD.

(h) Parts Installation Limitations

    As of the effective date of this AD, do not install a TRH pitch 
change unit P/N 350A33-2030-00, 350A33-2167-00, or 350A33-2167-01 on 
any helicopter, unless you do the actions required by paragraphs 
(g)(1)(i) through (iv) of this AD before further flight after 
installation, and thereafter do the actions required by paragraph 
(g)(2) of this AD at the times specified in paragraph (g)(2) of this 
AD.

(i) Credit for Previous Actions

    This paragraph provides credit for the initial inspections and 
actions required by paragraph (g)(1) of this AD, if those actions 
were performed before the effective date of this AD using Airbus 
Helicopters ASB No. AS350-05.01.03, or ASB No. AS355-05.00.86, both 
Revision 0, and dated December 16, 2021.

(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)(1) 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

    (1) For more information about this AD, contact Matthew 
Williams, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 
410, Westbury, NY 11590; phone: (316) 946-4134; email: 
[email protected].
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (l)(3) 
of this AD.

(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) Airbus Helicopters Alert Service Bulletin (ASB) No. AS350-
05.01.03, Revision 1, dated July 8, 2024.
    (ii) Airbus Helicopters ASB No. AS355-05.00.86 Revision 1, dated 
July 8, 2024.
    (3) For Airbus Helicopters material identified in this AD, 
contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, 
TX 75052; phone: (972) 641-0000 or (800) 232-0323; fax: (972) 641-
3775; website: airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
    (4) You may view this material at the FAA, Office of the 
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 June 11, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-12048 Filed 6-15-26; 8:45 am]
BILLING CODE 4910-13-P

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