Airworthiness Directives; Bell Textron Canada Limited Helicopters

[Federal Register Volume 91, Number 128 (Tuesday, July 7, 2026)]
[Rules and Regulations]
[Pages 41539-41542]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-13685]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-3476; Project Identifier MCAI-2025-01366-R; 
Amendment 39-23395; AD 2026-13-12]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2025-09-
03, which applied to certain Bell Textron Canada Limited (Bell) Model 
430 helicopters. AD 2025-09-03 reduced the life limits on the main 
rotor (M/R) clevises, universal bearings, and universal to pitch link 
bolts and required re-identifying the M/R pitch link assemblies with 
new part numbered assemblies. Since the FAA issued AD 2025-09-03, the 
FAA received comments proposing changes to the actions of AD 2025-09-
03. This AD requires changes to the actions in AD 2025-09-03 and 
addresses the comments received on that AD. The FAA is issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective August 11, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 13, 2025 
(90 FR 17547, April 28, 2025).

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-3476; 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 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: [email protected]. You may find the Transport Canada 
material on the Transport Canada website at tc.canada.ca/en/aviation.
    <bullet> You may 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-2026-3476.

FOR FURTHER INFORMATION CONTACT: Alexis Whitaker, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 15590; 
phone: (516) 228-7309; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2025-09-03, Amendment 39-23024 (90 FR 
17547, April 28, 2025) (AD 2025-09-03). AD 2025-09-03 applied to 
certain Bell Model 430 helicopters. AD 2025-09-03 was prompted by 
Transport Canada AD CF-2024-40, dated December 3, 2024 (Transport 
Canada AD CF-2024-40) (also referred to as the MCAI), issued by 
Transport Canada, which is the aviation authority for Canada. AD 2025-
09-03 was prompted by an in-flight failure of the main rotor pitch link 
clevis due to fatigue damage caused by excessive wear of the universal 
bearing. AD 2025-09-03 required a visual inspection of the M/R clevis, 
rod end, and a certain part-numbered universal bearing; performing a 
purge grease; performing a magnetic particle inspection after each 
detailed visual inspection of each M/R clevis; and depending on the 
inspection results, removing or replacing certain parts, and performing 
additional actions. AD 2025-09-03 also required recurring inspections 
of each M/R clevis and each universal bearing. Additionally, AD 2025-
09-03 required reducing the life limits of affected parts and re-
identifying the M/R pitch link assemblies with new part numbered 
assemblies. The FAA issued AD 2025-09-03 to detect and address wear and 
damage of the M/R pitch link assembly components. The unsafe condition, 
if not addressed, could result in crack initiation at the M/R clevis 
neck and failure of the M/R pitch link, which could result in loss of 
control of the helicopter.
    The NPRM was published in the Federal Register on April 7, 2026 (91 
FR 17610). The NPRM was prompted by comments from Bell and Superior 
Aviation Services requesting changes to the required actions of AD 
2025-09-03, specifically in regard to some of the exceptions in the 
regulatory text of AD 2025-09-03.
    In the NPRM, the FAA proposed to require all the actions of AD 
2025-09-03 and proposed to replace the requirement of performing a 
magnetic particle inspection after every detailed inspection with a 
conditional requirement.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2026-3476.

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

[[Page 41540]]

issuing this AD to address the unsafe condition on these products. 
Except for minor editorial changes, and any other changes described 
previously, 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 Transport Canada AD CF-2024-40, which was approved 
for incorporation by reference as of May 13, 2025 (90 FR 17547, April 
28, 2025). Transport Canada AD CF-2024-40 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 
inspection of the pitch link tube assembly, rod end assembly, and 
universal to pitch link bolt.
    Transport Canada AD CF-2024-40 also specifies procedures for 
performing repetitive detailed inspections of the M/R clevises and 
universal bearings (including hardware) and depending on the inspection 
results, replacing any part that does not meet inspection criteria or 
further corrective actions. Additionally, Transport Canada AD CF-2024-
40 specifies procedures for performing a purge grease, performing a 
magnetic particle inspection and either replacing any M/R clevis with 
cracks or replacing any missing cadmium plating. Furthermore, 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.

Differences Between This AD and the MCAI

    The MCAI requires replacing M/R pitch link assembly part number 
430-010-411-109, -109FM, -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 as 
required by the Airworthiness Limitations Section.

Costs of Compliance

    The FAA estimates that this AD affects 29 helicopters of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Review records to determine total  .25 work-hour x $85            $0  $22.................  $638.
 time on each part.                 per hour = $22.
Inspect the pitch link tube        4 work-hours x $85              0  $340................  $9,860.
 assembly, rod end assembly and     per hour = $340.
 universal to pitch link bolt.
Inspect the M/R pitch link clevis  2 work-hours x $85              0  $170 per inspection   $4,930 per
                                    per hour = $170.                   cycle.                inspection cycle.
Inspect the universal bearing and  2 work-hours x $85              0  $170 per inspection   $4,930 per
 hardware.                          per hour = $170.                   cycle.                inspection cycle.
Re-identify components...........  1 work-hour x $85               0  $85.................  $2,465.
                                    per hour = $85.
Perform a magnetic particle        4 work-hours x $85              0  $340 per inspection   $9,860 per
 inspection.                        per hour = $340.                   cycle.                inspection cycle.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
Replace an M/R clevis................  4 work-hours x $85 per           $432  $772 per part.
                                        hour = $340.
Replace a universal bearing..........  4 work-hours x $85 per         $3,566  $3,906 per part.
                                        hour = $340.
Replace a universal to pitch link      4 work-hours x $85 per           $374  $714 per part.
 bolt.                                  hour = $340.
Replace missing cadmium plating......  4 work-hours x $85 per             $0  $340.
                                        hour = $340.
Replace a pitch link tube assembly or  4 work-hours x $85 per         $6,463  $6,803 per part.
 rod end assembly.                      hour = $340.
----------------------------------------------------------------------------------------------------------------

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

[[Page 41541]]

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:
0
a. Removing Airworthiness Directive 2025-09-03, Amendment 39-23024 (90 
FR 17547, April 28, 2025); and
0
b. Adding the following new airworthiness directive:

2026-13-12 Bell Textron Canada Limited: Amendment 39-23395; Docket 
No. FAA-2026-3476; Project Identifier MCAI-2025-01366-R.

(a) Effective Date

    This airworthiness directive (AD) is effective August 11, 2026.

(b) Affected ADs

    This AD replaces AD 2025-09-03, Amendment 39-23024 (90 FR 17547, 
April 28, 2025).

(c) Applicability

    This AD applies to Bell Textron Canada Limited (Bell) Model 430 
helicopters, serial numbers 49001 through 49129 inclusive, 
certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 6220, Main rotor 
head.

(e) Unsafe Condition

    This AD was prompted by an in-flight failure of the main rotor 
(M/R) pitch link clevis (clevis) due to fatigue damage caused by 
excessive wear of the universal bearing. The FAA is issuing this AD 
to detect and address wear and damage of the M/R pitch link assembly 
components. The unsafe condition, if not addressed, could result in 
crack initiation at the M/R clevis neck and failure of the M/R pitch 
link, which could result in 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, Transport Canada AD CF-2024-40, dated December 3, 
2024 (Transport Canada AD CF-2024-40).

(h) Exceptions to Transport Canada AD CF-2024-40

    (1) Where Transport Canada AD CF-2024-40 refers to its effective 
date, this AD requires using May 13, 2025, the effective date of AD 
2025-09-03.
    (2) Where Transport Canada AD CF-2024-40 requires compliance in 
terms of hours air time, this AD requires using hours time-in-
service.
    (3) Where Transport Canada AD CF-2024-40 uses the term ``new'' 
in the definition of ``serviceable part,'' this AD requires 
replacing that text with ``new (zero hours time-in-service)''.
    (4) Where any paragraph in Transport Canada AD CF-2024-40 
specifies performing a magnetic particle inspection (MPI) if any 
suspected defects are found as a result of the DI [detailed 
inspection], this AD requires replacing that text with ``if any 
suspected defects (evidenced by linear indications) are found on the 
M/R clevis as a result of the detailed inspection''.
    Note 1 to paragraph (h)(4): a linear indication is defined as an 
indication for which the longest dimension is at least three times 
longer than the smallest one.
    (5) Where Part I paragraph A.8. and Part III paragraph B. of 
Transport Canada AD CF-2024-40 specify to purge grease the bearings, 
for this AD those actions are not required if already accomplished 
when doing Part I paragraph A.7 and Part III paragraph A. of 
Transport Canada AD CF-2024-40.
    (6) Where Part I paragraph A.9. of Transport Canada AD CF-2024-
40 specifies to re-identify the main rotor pitch link assemblies and 
sub-components, for this AD those actions are not required if 
already accomplished when doing Part I paragraphs A.2. through A.4. 
of Transport Canada AD CF-2024-40.
    (7) Where Part I paragraph B. of Transport Canada AD CF-2024-40 
specifies to ``replace each component listed in Table 1 of the Bell 
ASB before exceeding the applicable airworthiness life limit 
indicated in Table 4-1 of the applicable ALS [Airworthiness 
Limitations Section]'', for this AD that requirement does not apply 
to M/R pitch link assemblies part numbers 430-010-411-109, -109FM, -
111, and -111FM, as those parts are replaced on-condition.

(i) No Reporting Requirement

    Although the material referenced in Transport Canada AD CF-2024-
40 specifies to submit certain information to the manufacturer, this 
AD does not require that action.

(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 Alexis Whitaker, 
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY; phone: (516) 228-7309; email: 
[email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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.
    (3) The following material was approved for IBR on May 13, 2025 
(90 FR 17547, April 28, 2025).
    (i) Transport Canada AD CF-2024-40, dated December 3, 2024.
    (ii) [Reserved]
    (4) For Transport Canada material identified in this AD, contact 
Transport Canada National Aircraft Certification, 159 Cleopatra 
Drive, Nepean, Ontario K1A 0N5, Canada; phone: 888-663-3639; email: 
[email protected]. You 
may find this material on the Transport Canada website at 
tc.canada.ca/en/aviation.
    (5) 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.
    (6) 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].


[[Page 41542]]


    Issued on June 29, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-13685 Filed 7-6-26; 8:45 am]
BILLING CODE 4910-13-P

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