[Federal Register Volume 90, Number 80 (Monday, April 28, 2025)]
[Rules and Regulations]
[Pages 17547-17550]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-07275]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 90, No. 80 / Monday, April 28, 2025 / Rules
and Regulations
[[Page 17547]]
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.
-----------------------------------------------------------------------
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
[[Page 17548]]
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
[[Page 17549]]
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
----------------------------------------------------------------------------------------------------------------
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 4 work-hours x $85 0 $340 per inspection $9,860 per
per hour = $340. cycle. inspection cycle.
Inspect the universal bearing and 4 work-hours x $85 0 $340 per inspection $9,860 per
hardware. per hour = $340. cycle. inspection cycle.
Re-identify components........... .25 work-hour x $85 0 $22................. $638.
per hour = $22.
Perform a magnetic particle 2 work-hours x $85 0 $170 per inspection $4,930 per
inspection. per hour = $170. 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 bolt.. 4 work-hours x $85 per 374 $714 per part.
hour = $340.
Replace missing cadmium plating......... 4 work-hours x $850 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
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.
[[Page 17550]]
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 2021-24-09, Amendment 39-21830 (86
FR 66158, November 22, 2021); and
0
b. Adding the following new airworthiness directive:
2025-09-03 Bell Textron Canada Limited: Amendment 39-23024; Docket
No. FAA-2025-0743; Project Identifier MCAI-2024-00711-R.
(a) Effective Date
This airworthiness directive (AD) is effective May 13, 2025.
(b) Affected ADs
This AD replaces AD 2021-24-09, Amendment 39-21830 (86 FR 66158,
November 22, 2021).
(c) Applicability
This AD applies to Bell Textron Canada Limited 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 and excessive
wear. 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 uses the term ``new''
in the definition of ``serviceable part,'' this AD requires
replacing that text with ``new (zero hours time-in-service).''
(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 refers to its effective
date, this AD requires using the effective date of this AD.
(4) Where any paragraph in Transport Canada AD CF-2024-40
specifies performing a magnetic particle inspection (MPI) ``if any
suspected defects are found'' after performing a detailed visual
inspection, this AD requires performing an MPI after performing each
detailed visual inspection.
(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 CF-2024-40
specifies ``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,'' for this AD that requirement
does not apply to M/R pitch link assemblies part numbers 430-010-
411-109, -109FM, -111, and -111FM.
(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) Special Flight Permits
A special flight permit may be issued in accordance with 14 CFR
21.197 and 21.199 to fly to a maintenance area to perform the
required actions in this AD, provided there are no passengers
onboard.
(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: AMOC@faa.gov.
(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 Alexis Whitaker,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY; phone: (516) 228-7309; email:
alexis.j.whitaker@faa.gov.
(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) Transport Canada AD CF-2024-40, dated December 3, 2024.
(ii) [Reserved]
(3) 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:
TC.AirworthinessDirectives-Consignesdenavigabilite.TC@tc.gc.ca. You
may find this material on the Transport Canada website at
tc.canada.ca/en/aviation.
(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 fr.inspection@nara.gov.
Issued on April 22, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-07275 Filed 4-23-25; 4:15 pm]
BILLING CODE 4910-13-P