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Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations
Related Service Information Under 1
CFR Part 51
The FAA reviewed Finmeccanica Bollettino Tecnico No. 189080, Revision A, dated July 15, 2016, which contains procedures for visual and dye penetrant inspections of the MR damper for cracks and for verifying the torque of the damper body ends.
The FAA also reviewed Leonardo Helicopters Alert Service Bulletin No.
189102, Revision A, dated December 21, 2017, which contains procedures for installing an MR damper with reduced torque values and specifies replacing MR damper P/N 4F6220V00251 with new MR damper P/N 8G6220V00151.
This service information 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.
Other Related Service Information The FAA reviewed Finmeccanica Bollettino Tecnico No. 189069, dated February 12, 2016, which contains procedures for installing a special washer on the MR damper rod end, modifying the installation torque of the MR damper, and inspecting the rod end bearings.
Costs of Compliance The FAA estimates that this AD
affects 3 helicopters of U.S. Registry.
The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour.
Adjusting the tightening torque takes about 10 work-hours, for an estimated cost of $850 per helicopter and $2,550
for the U.S. fleet.
Replacing an MR damper takes about 2 work-hours, and parts cost about $18,000, for an estimated cost of $18,170 per MR damper.
Performing a dye penetrant or eddy current inspection of the MR damper takes about 8 work-hours, for an estimated cost of $680 per helicopter and $2,040 for the U.S fleet.
Visually inspecting the rod ends and body ends takes about 0.5 hour, for an estimated cost of $43 per helicopter and $129 for the U.S. fleet, per inspection cycle.
Inspecting the rod ends and body ends for bearing rotation takes about 0.5
hour, for an estimated cost of $43 per helicopter and $129 for the U.S. fleet, per inspection cycle.
Inspecting the broached ring nut takes about 0.5 hour, for an estimated cost of $43 per helicopter and $129 for the U.S.
fleet, per inspection cycle.
Inspecting for bearing friction takes about 2 hours, for an estimated cost of
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$170 per helicopter and $510 for the U.S
fleet, per inspection cycle.
Inspecting the broached ring teeth for proper alignment and applying torque takes about 8 work-hours, for an estimated cost of $680 per helicopter and $2,040 for the U.S fleet.
Replacing a rod end takes about 3
work-hours and parts cost about $500, for an estimated cost of $755 per rod end.
Replacing a broached ring takes about 3 work-hours and parts cost about $100, for an estimated cost of $355 per broached ring.
Replacing a broached ring nut takes about 3 work-hours and parts cost about $125, for an estimated cost of $380 per broached ring nut.
Replacing an anti-rotation block takes about 3 work-hours and parts cost about $50, for an estimated cost of $305 per anti-rotation block.
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 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 helicopters identified in this rulemaking action.

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.
Adoption of 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:

20210203 Leonardo S.p.a: Amendment 3921386; Docket No. FAA20200503;
Product Identifier 2018SW006AD.
a Applicability This airworthiness directive AD applies to Leonardo S.p.a. Model AW189 helicopters, certificated in any category, with a main rotor MR damper part number P/N
4F6220V00251 installed.
b Unsafe Condition This AD defines the unsafe condition as a crack in an MR damper, which if not detected and corrected, could lead to loss of the lead-lag damping function of the MR
blade, resulting in damage of the MR damper, detachment of the MR damper in-flight, and subsequent loss of control of the helicopter.
c Effective Date This AD becomes effective April 1, 2021.

Regulatory Findings
d Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

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, 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
e Required Actions 1 Within 10 hours time-in-service TIS, reduce the torque of the nut on the bolt attaching each MR damper to the MR hub by following paragraphs 4 through 7 of the Accomplishment Instructions, Part I, of Leonardo Helicopters Alert Service Bulletin No. 189102, Revision A, dated December 21, 2017 ASB 189102.
2 Within 30 hours TIS or before the MR
damper body end body end accumulates 500 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 500 hours TIS, replace the MR damper.
3 Within 30 hours TIS, before the MR
damper accumulates 300 hours TIS, or within 300 hours TIS since the last overhaul, whichever occurs later, dye penetrant inspect using a 5X power magnifying glass or eddy current inspect each MR damper rod end rod
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