Airworthiness Directives; Leonardo S.p.A. Helicopters

[Federal Register Volume 90, Number 162 (Monday, August 25, 2025)]
[Rules and Regulations]
[Pages 41295-41298]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-16261]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-2264; Project Identifier MCAI-2025-01204-R; 
Amendment 39-23120; AD 2025-17-10]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Leonardo S.p.A. Model A109A, A109A II, A109C, A109K2, and A119 
helicopters and certain AW119 MKII helicopters. This AD was prompted by 
a report of incorrect installation of the bolts that attach the pitch 
(longitudinal) actuator assembly and the roll (lateral) actuator 
assembly to their respective bellcrank assemblies of the cyclic control 
system. This AD requires inspecting the bolts for proper installation 
and, depending on the results, performing corrective actions. The FAA 
is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective September 9, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 9, 
2025.
    The FAA must receive comments on this AD by October 9, 2025.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 41296]]

    <bullet> Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2025-2264; 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 
street address for Docket Operations is listed above.
    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, 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-2025-2264.

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: 

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments using a method listed under 
the ADDRESSES section. Include ``Docket No. FAA-2025-2264; Project 
Identifier MCAI-2025-01204-R'' at the beginning of your comments. The 
most helpful comments reference a specific portion of the final rule, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this AD, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this AD. Submissions containing CBI should be sent to Steven 
Warwick, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590. Any commentary that the FAA receives which is not 
specifically designated as CBI will be placed in the public docket for 
this rulemaking.

Background

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2025-0142, dated July 7, 2025 (EASA 
AD 2025-0142) (also referred to as the MCAI), to correct an unsafe 
condition on all Leonardo S.p.A. Model A109A, A109AII, A109C, A109K2, 
and A119 helicopters and on certain serial-numbered AW119MKII 
helicopters. The MCAI states a report was received of incorrect 
installation of the bolts that attach the pitch (longitudinal) actuator 
assembly and the roll (lateral) actuator assembly to their respective 
bellcrank assemblies of the cyclic control system. Investigation 
determined that the maintenance instructions to install the bolt 
included potentially misleading information. The unsafe condition, if 
not addressed, could result in the reduced range of the helicopter 
cyclic control and loss of control of the helicopter.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2025-2264.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2025-0142, which specifies procedures for 
a one-time inspection of the bolts that attach the pitch (longitudinal) 
actuator assembly and the roll (lateral) actuator assembly to their 
respective bellcrank assemblies for proper installation. Depending on 
the results, EASA AD 2025-0142 specifies inspecting the bolts and 
support assemblies for damage and interference and replacing any 
damaged or incorrectly installed bolt with a serviceable bolt. In 
addition, EASA AD 2025-0142 prohibits accomplishing any maintenance 
action using certain maintenance instructions. 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.

FAA's Determination

    These products have been approved by the civil aviation authority 
(CAA) 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 is issuing 
this AD after determining that the unsafe condition described 
previously is likely to exist or develop on other products of the same 
type design.

AD Requirements

    This AD requires accomplishing the actions specified EASA AD 2025-
0142, described previously, as incorporated by reference, except for 
any differences identified as exceptions in the regulatory text of this 
AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some CAA ADs as the primary 
source of information for compliance with requirements for 
corresponding FAA ADs. The FAA has been coordinating this process with 
manufacturers and CAAs. As a result, EASA AD 2025-0142 is incorporated 
by reference in this AD. This AD requires compliance with EASA AD 2025-
0142 in its entirety through that incorporation, except for any 
differences identified as exceptions in the regulatory text of this AD. 
Using common terms that are the same as the heading of a particular 
section in EASA AD 2025-0142 does not mean that operators need comply 
only with that

[[Page 41297]]

section. For example, where the AD requirement refers to ``all required 
actions and compliance times,'' compliance with this AD requirement is 
not limited to the section titled ``Required Action(s) and Compliance 
Time(s)'' in EASA AD 2025-0142. Material referenced in EASA AD 2025-
0142 for compliance will be available at regulations.gov under Docket 
No. FAA-2025-2264 after this AD is published.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 
551 et seq.) authorizes agencies to dispense with notice and comment 
procedures for rules when the agency, for ``good cause,'' finds that 
those procedures are ``impracticable, unnecessary, or contrary to the 
public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because incorrect installation of the bolts that attach the pitch 
(longitudinal) actuator assembly to the pitch (longitudinal) bellcrank 
assembly and the roll (lateral) actuator assembly to the roll (lateral) 
bellcrank assembly could cause the bolts to interfere with the support 
assembly. Incorrect installation of the bolts could result in the 
reduced range of the helicopter cyclic control, which could lead to 
loss of control of the helicopter. For this reason, the actions 
required by this AD must be accomplished within 25 hours time in-
service. This compliance time is shorter than the time necessary for 
the public to comment and for publication of the final rule. 
Accordingly, notice and opportunity for prior public comment are 
impracticable and contrary to the public interest pursuant to 5 U.S.C. 
553(b).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without prior notice and 
comment, RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 238 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 affected bolts................  1 work-hour x $85 per                 $0             $85         $20,230
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any repairs 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:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace worn bolts and perform rigging          39 work-hours x $85 per hour =               $24          $3,339
 procedure.                                      $3,315.
----------------------------------------------------------------------------------------------------------------

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, and
    (2) Will not affect intrastate aviation in Alaska.

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:


[[Page 41298]]


2025-17-10 Leonardo S.p.A.: Amendment 39-23120; Docket No. FAA-2025-
2264; Project Identifier MCAI-2025-01204-R.

(a) Effective Date

    This airworthiness directive (AD) is effective September 9, 
2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Leonardo S.p.A. Model A109A, A109A II, A109C, 
A109K2, A119, and AW119 MKII helicopters, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2025-0142, dated July 7, 2025 (EASA AD 2025-0142).

(d) Subject

    Joint Aircraft System Component (JASC) Code 6710, Main Rotor 
Control.

(e) Unsafe Condition

    This AD was prompted by a report of incorrect installation of 
the bolts that attach the pitch (longitudinal) actuator assembly and 
the roll (lateral) actuator assembly to their respective bellcrank 
assemblies of the cyclic control system. The FAA is issuing this AD 
to address incorrect installation of the bolts. The unsafe 
condition, if not addressed, could result in the reduced range of 
the helicopter cyclic control and 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, EASA AD 2025-0142.

(h) Exceptions to EASA AD 2025-0142

    (1) Where EASA AD 2025-0142 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) Where EASA AD 2025-0142 refers to flight hours, this AD 
requires using hours time-in-service.
    (3) Where EASA AD 2025-0142 refers to damage or damaged, for 
this AD, damage means any wear.
    (4) Where paragraph (3) of EASA AD 2025-0142 states ``contact 
Leonardo for approved corrective action instructions and accomplish 
those instructions accordingly'', this AD requires replacing that 
text with ``repair the discrepancy using a method approved by the 
Manager, International Validation Branch, FAA; or EASA; or Leonardo 
Helicopters' EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature''.
    (5) Where paragraph (6) of EASA AD 2025-0142 states ``From the 
effective date of this AD, do not accomplish any maintenance action 
on a helicopter in accordance with Leonardo maintenance instructions 
as listed in Table 1 of this AD'', this AD requires replacing that 
text with ``After the effective date of this AD, revise the existing 
maintenance or inspection program to prohibit the use of the 
Leonardo maintenance instructions listed in Table 1 of EASA AD 2025-
0142''.
    (6) This AD does not adopt the ``Remarks'' section of EASA AD 
2025-0142.

 (i) No Reporting Requirement

    Although the material referenced in EASA AD 2025-0142 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 Steven Warwick, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; phone: (817) 222-5225; 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 2025-0142, 
dated July 7, 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, 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 18, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2025-16261 Filed 8-21-25; 4:15 pm]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T01:22:37.304488+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

98325f6ddeea336c319fc1a468983e7953457371c2eb1ce90cbc439bb8b75ff0

Text SHA-256

2b91e21c2caa9f14e68346952b458d82260e457193bc1d67d42d4e562bfa4df0