DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-0743; Project Identifier MCAI-2024-00711-R;
Amendment 39-23024; AD 2025-09-03]
RIN 2120-AA64

Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-24-
09, which applied to certain Bell Textron Canada Limited Model 430
helicopters. AD 2021-24-09 required a visual inspection of the main
rotor (M/R) pitch link clevis (clevis), rod end, and a certain part-
numbered universal bearing, performing a purge grease, and performing a
magnetic particle inspection of each M/R clevis, and depending on the
inspection results, removing or replacing certain parts and performing
additional actions. AD 2021-24-09 also required recurring inspections
of each M/R clevis and each universal bearing. Since the FAA issued AD
2021-24-09, the manufacturer has reduced the life limits of the
affected parts and introduced new M/R pitch link assemblies by re-
identifying the M/R pitch link assemblies that were required to be
inspected by AD 2021-24-09. This AD requires similar actions as AD
2021-24-09 but reduces the life limits and requires replacing the M/R
pitch link assemblies with re-identified part numbered assemblies.
These actions are specified in a Transport Canada AD, which is
incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective May 13, 2025.

The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 13, 2025.

The FAA must receive comments on this AD by June 12, 2025.

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

Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.

Fax: (202) 493-2251.

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.

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-2025-0743; 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:

For Transport Canada material identified in this AD,
contact Transport Canada, Transport Canada National Aircraft
Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, CANADA;
phone: (888) 663-3639; email: TC.AirworthinessDirectives-Consignesdenavigabilite.TC
@tc.gc.ca. You may find the Transport Canada material on the Transport
Canada website at tc.canada.ca/en/aviation.

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-2025-0743.

FOR FURTHER INFORMATION CONTACT: Alexis Whitaker, Aviation Safety
Engineer, FAA, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY;
phone: (516) 228-7309; email: alexis.j.whitaker@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
the ADDRESSES section. Include "Docket No. FAA-2025-0743; Project
Identifier MCAI-2024-00711-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 Alexis
Whitaker, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY. Any commentary that the FAA receives which is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.

Background

The FAA issued AD 2021-24-09, Amendment 39-21830 (86 FR 66158,
November 22, 2021) (AD 2021-24-09), for Bell Textron Canada Limited
Model 430 helicopters, serial numbers 49001 through 49129, inclusive. AD
2021-24-09 was prompted by an MCAI originated by Transport Canada,
which is the aviation authority for Canada. Transport Canada issued AD
CF-2021-26, dated July 26, 2021 (Transport Canada AD CF-2021-26) to
address an in-flight failure of an M/R clevis, which resulted in loss
of control of the helicopter and fatal injuries to occupants. AD 2021-
24-09 required a visual inspection of the M/R clevis, rod end, and a
certain part-numbered universal bearing, performing a purge grease, and
performing a magnetic particle inspection of each M/R clevis. Depending
on the visual inspection and magnetic particle inspection results, AD
2021-24-09 required removing certain parts from service, replacing
certain parts, and performing additional actions. AD 2021-24-09 also
required recurring inspections of each M/R clevis and each universal
bearing. The FAA issued AD 2021-24-09 to detect and address any wear
and damage of the M/R clevis neck or threaded area, which could lead to
crack initiation at the M/R clevis neck and failure of the M/R pitch
link, resulting in loss of control of the helicopter.

Actions Since AD 2021-24-09 Was Issued

Since the FAA issued AD 2021-24-09, Transport Canada superseded
Transport Canada AD CF-2021-26 and issued Transport Canada AD CF-2024-
40, dated December 3, 2024 (Transport Canada AD CF-2024-40) (also
referred to after this as "the MCAI"). The MCAI states that Bell
Textron Canada Limited has revised Chapter 4, Airworthiness Limitations
Section (ALS) of the Model 430 helicopter maintenance manual. Rather
than having an airworthiness life assigned to the M/R pitch link
assembly, Bell Textron Canada Limited has assigned individual life
limits on the M/R clevises, universal bearings, universal to pitch link
bolts, the tube assembly, and the rod end assembly. Bell Textron Canada
Limited also revised its service information, which specifies re-
identifying M/R pitch link assemblies from part number (P/N) 430-010-
411-105 and P/N 430-010-411-107, which were required to be inspected by
AD 2021-24-09, to P/N 430-010-411-109 and P/N 430-010-411-111,
respectively. According to the MCAI, the unsafe condition, if not
addressed, could lead to crack initiation at the M/R clevis neck or
threaded area and failure of the M/R pitch link, which could result in
loss of control of the helicopter.

You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2025-0743.

Material Incorporated by Reference Under 1 CFR Part 51

The FAA reviewed Transport Canada AD CF-2024-40, which specifies
procedures for verifying rotorcraft historical records to determine the
total accumulated hours air time of certain parts, replacing the M/R
pitch link assembly components that have exceeded their life limit, re-
identifying the M/R pitch link assemblies, and performing a detailed
visual inspection of the pitch link tube assembly, rod end assembly,
and universal pitch link bolt. Transport Canada AD CF-2024-40 also
requires performing repetitive detailed visual inspections of the M/R
clevises and universal bearings (including hardware). Depending on the
inspection results, Transport Canada CF-2024-40 specifies replacing any
part that does not meet inspection criteria or further corrective
actions. Additionally, Transport Canada AD CF-2024-40 specifies
performing a purge grease of each universal bearing and performing a
magnetic particle inspection of the M/R clevis and either replacing any
M/R clevis with cracks or replacing any missing cadmium plating.
Transport Canada AD CF-2024-40 specifies reporting any cracks or M/R
clevises with damage beyond published limits to Bell Product Support
Engineering.

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 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 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 similar actions as AD 2021-24-09 but reduces the
life limits of the affected parts and requires re-identifying the M/R
pitch link assemblies with new part numbered assemblies by
accomplishing the actions specified in the MCAI, except for any
differences identified in the regulatory text of this AD. See
"Differences Between this AD and the MCAI" for a discussion of these
differences.

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 civil aviation
authority (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,
Transport Canada AD CF-2024-40 is incorporated by reference in this AD.
This AD requires compliance with Transport Canada AD CF-2024-40 in its
entirety through that incorporation, except for any differences
identified as exceptions in the regulatory text of this AD. Material
required by Transport Canada AD CF-2024-40 for compliance will be
available at regulations.gov under Docket No. FAA-2025-0743 after this
AD is published.

Differences Between This AD and the MCAI

The MCAI uses the term "new," while this AD uses the term "new
(zero hours time-in-service)."

The MCAI requires performing a magnetic particle inspection (MPI)
if any suspected defects are found, while this AD requires performing
an MPI after performing each detailed visual inspection.

The MCAI requires replacing M/R pitch link assembly P/Ns 430-010-
411-109, -109 FM, -111, and -111FM before they exceed their life limit.
This AD does not contain that requirement because those assemblies do
not have a life limit and are replaced on condition; instead, the
individual components of the assembly are life-limited.

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 if the M/R pitch link clevises, the
universal bearings, and the universal to pitch link bolt remain in
service beyond their reduced life limits, this could lead to crack
initiation at the M/R clevis neck or threaded area and consequent
failure of the M/R pitch link, which could result in loss of control of
the helicopter. In addition, the compliance time for the required
actions is within 50 hours time-in-service or 60 days, whichever occurs
first after the effective date of this AD, which is a shorter time
period 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 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 29 helicopters of U.S.
registry. Labor rates are estimated at $85 per hour. Based on these
numbers, the FAA estimates that operators may incur the following costs
to comply with this AD.

Estimated Costs

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

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

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]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2021-24-09, Amendment 39-21830 (86
FR 66158, November 22, 2021); and

b. Adding the following new airworthiness directive: