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Federal Register / Vol. 86, No. 222 / Monday, November 22, 2021 / Rules and Regulations 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 29 helicopters of U.S. Registry.
Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates the following costs to comply with this AD.
Removing and disassembling each M/
R pitch link assembly and inspecting each M/R clevis and rod end takes about 4 work-hours for an estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
Inspecting each universal bearing takes about 4 work-hours for an estimated cost of $340 per inspection and $9,860 for the U.S. fleet.
If required, replacing each universal bearing takes about 4 work-hours for an estimated cost of $340 and parts cost about $1,000 for an estimated cost of $1,340 per replacement.
If required, replacing each universal bearing and each M/R clevis takes about 8 work-hours for an estimated cost of $680 and parts cost about $3,000 for an estimated cost of $3,680 per replacement of both parts.
Performing a purge grease on each universal bearing takes about 0.25 workhours for an estimated cost of $22 per purge.
Performing a magnetic particle inspection of each M/R clevis takes about 2 work-hours for an estimated cost of $170 per inspection.
Performing a selective brush cadmium plating takes about 4 work-hours for an estimated cost of $340 per helicopter.

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Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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
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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, 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 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

20212409 Bell Textron Canada Limited:
Amendment 3921830; Docket No.
FAA20211011; Project Identifier MCAI202100867R.
a Effective Date This airworthiness directive AD is effective December 7, 2021.
b Affected ADs None.
c Applicability This AD applies to Bell Textron Canada Limited Model 430 helicopters, having serial number 49001 through 49129, inclusive, certificated in any category.
d Subject Joint Aircraft Service Component JASC
Code: 6220, Main Rotor Head.

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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 any wear and damage of the M/R clevis neck or threaded area. 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, resulting in loss of control of the helicopter.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 Within 25 hours time-in-service TIS or 30 days, whichever occurs first, after the effective date of this AD:
i Remove and disassemble each M/R
pitch link assembly part number P/N 430
010411105, or P/N 430010411107, but do not remove the inserts from the tube.
Visually inspect the M/R clevis P/N 430
010432101 and rod end for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. If there is any wear, corrosion or damage, before further flight, remove the affected M/R clevis or the affected rod end from service.
ii Visually inspect each universal bearing P/N 212010412001 for binding, stiffness, wear, looseness, excess axial and radial play, and damage, which for the purposes of this inspection may be indicated by distortion, bending, or a crack.
A If there is any wear, looseness, excess axial and radial play, or damage and the M/
R pitch link assembly is P/N 430010411
105 or P/N 430010411107 and has accumulated 5,000 or less total hours TIS, before further flight, remove the universal bearing P/N 212010412001 from service and replace with an airworthy part.
B If there is any binding or stiffness and the M/R pitch link assembly is P/N 430010
411105 or P/N 430010411107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212010412001 and M/R
clevis from service and replace with airworthy parts.
C If there is any wear, looseness, excess axial and radial play, or damage and the M/
R pitch link assembly is P/N 430010411
105 or P/N 430010411107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212010412001 from service and replace with an airworthy part.
iii Purge grease the bearings of each universal bearing.
iv Perform a magnetic particle inspection for any crack on each M/R clevis by following the Accomplishment Instructions, Part I, paragraphs 8. through 8.d., of Bell Alert Service Bulletin 4302160, dated July 13, 2021 ASB 4302160. If there is any crack, before further flight, remove each affected M/R clevis from service. If there is no crack, before further flight, perform a selective brush cadmium plating to replace
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