Airworthiness Directives; Leonardo S.p.a. Helicopters

[Federal Register Volume 91, Number 98 (Thursday, May 21, 2026)]
[Rules and Regulations]
[Pages 29890-29892]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-10170]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-0025; Project Identifier MCAI-2025-01294-R; 
Amendment 39-23343; AD 2026-10-03]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.a. 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 
Leonardo S.p.a. Model AB139, AW139, and AW189 helicopters. This AD was 
prompted by a report of cracks on the left-hand (LH) and right-hand 
(RH) tube assemblies installed on the brake pedal assemblies. This AD 
requires repetitively inspecting the LH and RH tube assemblies for 
Model AB139 and AW139 helicopters, and the LH and RH pedal shaft 
assemblies for Model AW189 helicopters, and depending on the results of 
the inspection, corrective actions. This AD also 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 June 25, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publications listed in this AD as of June 25, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-0025; 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, 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-2026-0025.

FOR FURTHER INFORMATION CONTACT: Steven Warwick, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
phone: (817) 222-5225; 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 Leonardo S.p.a. 
Model AB139, AW139, and AW189 helicopters. The NPRM was published in 
the Federal Register on January 26, 2026 (91 FR 3081); corrected 
February 6, 2026 (91 FR 9514). The NPRM was prompted by EASA AD 2025-
0163, dated July 30, 2025, (EASA 2025-0163) (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 occurrences of 
cracking on the LH and RH pilot pedal tubes (also referred to as the 
tube assemblies installed on the brake pedal assemblies) were reported 
on a Model AW139 helicopter. The MCAI further states subsequent 
investigation revealed that the cracks originated from the locking slot 
where the upper clamping bolt engages with the tube; however, the root 
cause of the tube cracking is still under investigation. Additionally, 
the MCAI states that due to design similarity of the braking pedal 
assembly architecture, Model AB139 and AW189 helicopters could be also 
affected by the same structural damage.
    In the NPRM, the FAA proposed to require repetitively inspecting 
the LH and RH tube assemblies for Model AB139 and AW139 helicopters, 
and the LH and RH pedal shaft assemblies for Model AW189 helicopters, 
and depending on the results of the inspection, corrective actions. In 
the NPRM the FAA also proposed to prohibit installing certain parts 
unless certain requirements are met. The FAA is issuing this AD to 
detect and address cracks on the LH and RH tube assemblies and pedal 
shaft assemblies installed on the brake pedal assemblies. This unsafe 
condition, if not addressed, could lead to structural failure of the 
brake pedal assembly and result in reduced control of the helicopter 
around the yaw axis.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2026-0025.

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

[[Page 29891]]

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 2025-0163, which specifies procedures for 
repetitive inspections of certain part-numbered LH and RH tube 
assemblies (for Models AB139 and AW139) and certain part-numbered LH 
and RH pedal shaft assemblies (for Model AW189) installed on the brake 
pedal assemblies. Depending on the inspection results, EASA AD 2025-
0163 specifies procedures for replacing an affected part with a 
serviceable part or, for the copilot side only, as an alternative to 
replacing an affected part, installing a temporary serviceable part for 
the copilot pedal assembly set, performing repetitive inspections, 
manufacturing and installing a placard, and revising the limitations 
section of the rotorcraft flight manual (RFM) for the helicopter. EASA 
AD 2025-0163 also prohibits installing an affected part on any 
helicopter unless certain requirements are met. 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 153 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 LH and RH tube assembly or shaft   2 work-hours x $85 per hour           $0         $170         $26,010
 assembly.                                  = $170.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Replace tube assembly or shaft assembly   1 work-hour x $85 per hour          $3,381  $3,466.
 (1 assembly).                             = $85.
Manufacture and install placard.........  1 work-hour x $85 per hour               0  85.
                                           = $85.
Revise the RFM..........................  1 work-hour x $85 per hour               0  85 per RFM revision.
                                           = $85.
Inspect (repetitively) LH and RH tube     2 work-hours x $85 per                   0  170.
 assembly or shaft assembly.               hour = $170.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

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:

2026-10-03 Leonardo S.p.a.: Amendment 39-23343; Docket No. FAA-2026-
0025; Project Identifier MCAI-2025-01294-R.

[[Page 29892]]

(a) Effective Date

    This airworthiness directive (AD) is effective June 25, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Leonardo S.p.a. Model AB139, AW139, and 
AW189 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6720, Tail rotor 
control system.

(e) Unsafe Condition

    This AD was prompted by a report of cracks on the left-hand (LH) 
and right-hand (RH) tube assemblies installed on the brake pedal 
assemblies. The FAA is issuing this AD to detect and address cracks 
on the LH and RH tube assemblies and pedal shaft assemblies. The 
unsafe condition, if not addressed, could lead to structural failure 
of the brake pedal assembly and result in reduced control of the 
helicopter around the yaw axis.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) 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 
2025-0163, dated July 30, 2025 (EASA AD 2025-0163).
    (2) For this AD, the owner/operator (pilot) holding at least a 
private pilot certificate may revise the existing rotorcraft flight 
manual (RFM) for the helicopter by inserting Appendix 1 of EASA AD 
2025-0163 and must enter compliance into the helicopter maintenance 
records in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The 
record must be maintained as required by 14 CFR 91.417, 121.380, or 
135.439.

(h) Exceptions to EASA AD 2025-0163

    (1) Where EASA AD 2025-0163 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2025-0163 requires compliance in terms of 
flight hours, this AD requires using hours time-in-service.
    (3) Where the material referenced in EASA AD 2025-0163 specifies 
discarding parts, or scrapping parts, this AD requires removing 
those parts from service.
    (4) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0163.

(i) No Reporting Requirement

    Although the service material referenced in EASA AD 2025-0163 
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 Steven Warwick, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (817) 222-5225; 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 2025-0163, 
dated July 30, 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. You may 
find the EASA material on the EASA website at ad.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, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on May 6, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-10170 Filed 5-20-26; 8:45 am]
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