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Federal Register / Vol. 86, No. 55 / Wednesday, March 24, 2021 / Rules and Regulations
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 Fred Guerin, Aerospace Engineer, General Aviation &
Rotorcraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone 206 2313500; email fred.guerin@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking.
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.

khammond on DSKJM1Z7X2PROD with RULES

Costs of Compliance The FAA estimates that this AD
affects 72 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.
Each tap inspection will take about 3
work-hours and there are no parts costs for an estimated cost of about $255 per helicopter per inspection cycle.
Each visual inspection will take about 1 work-hour and there are no parts cost for an estimated cost of about $85 per helicopter per inspection cycle.
Each dye-penetrant inspection will take about 3 work-hours and parts will cost about $100 for an estimated cost of about $355 per helicopter per inspection cycle.
Replacing a blade, if required, will take about 2 work-hours and parts will cost about $98,435 per blade, for an estimated cost of about $98,605 per replacement.
Replacing a tip cap, if required, will take about 30 work-hours and parts will cost about $3,034 per tip cap, for an estimated cost of about $5,584 per replacement.
The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under
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warranty, thereby reducing the cost impact on affected operators.
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 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.
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:
a. Removing Airworthiness Directive AD 20072652, Amendment 39
15519 73 FR 26316, May 9, 2008; and

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b. Adding the following new AD:

20210705 Leonardo S.p.a. Type Certificate Previously Held by Agusta S.p.A. Leonardo: Amendment 39
21482; Docket No. FAA20210194;
Project Identifier MCAI202001434R.
a Effective Date This airworthiness directive AD is effective April 8, 2021.
b Affected ADs This AD replaces AD 20072652, Amendment 3915519 73 FR 26316, May 9, 2008.
c Applicability This AD applies to Leonardo Model A109C, A109E, and A109K2 helicopters, certificated in any category, with a main rotor blade MRB part number P/N 7090103
01-all dash numbers installed.
d Subject Joint Aircraft Service Component JASC
Code: 6210, Main Rotor Blades.
e Unsafe Condition This AD was prompted by reports of the inflight loss of tip caps. The FAA is issuing this AD to prevent loss of a tip cap from an MRB.
The unsafe condition, if not addressed, could result in an increase in MRB vibration and subsequent loss of control of the helicopter.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 For an MRB with a serial number that has a prefix of either EMor A5-, except an MRB with a tip cap P/N 709010329109
installed, within 10 hours time-in-service TIS after the effective date of this AD, unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS:
i Tap inspect the upper and lower sides of each tip cap for bonding separation between the metal shells and the honeycomb core using a steel hammer P/N 109310158
1 or a coin quarter in the area indicated as honeycomb core on Figure 1 of Agusta Alert Bollettino Tecnico BT No. 109106, BT No.
109K22, or BT No. 109EP1, each Revision B and each dated December 19, 2000 BT No.
109106, BT No. 109K22, or BT No. 109EP
1, as applicable to your helicopter model.
Also, tap inspect for bonding separation in the tip cap to blade bond area no bonding voids are permitted in this area.
ii Visually inspect the upper and lower sides of each blade tip cap for swelling or deformation.
iii Dye-penetrant inspect the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack in accordance with the Compliance Instructions, steps 3. through 3.2.6., of BT
No. 109106, BT No. 109K22, or BT No.
109EP1, as applicable to your helicopter model.
iv If there is any swelling, deformation, or crack; or bonding separation that exceeds
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