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Federal Register / Vol. 86, No. 108 / Tuesday, June 8, 2021 / Proposed Rules
30397

ESTIMATED COSTS FOR REQUIRED ACTIONS
Action Retained actions from AD
20210415.
New proposed actions

Labor cost
Parts cost
7 work-hours $85 per hour = $595, per inspection/
cleaning cycle.
4 work-hours $85 per hour = $340, per inspection/
cleaning cycle.

The FAA estimates the following costs to do any necessary on-condition actions that would be required based on
Cost per product
Cost on U.S. operators
$0

$595, per inspection/cleaning cycle.

$386,750, per inspection/
cleaning cycle.

0

$340, per inspection/cleaning cycle.

$221,000, per inspection/
cleaning cycle.

the results of any required actions. The FAA has no way of determining the
number of helicopters that might need these on-condition actions:

ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per product
4 work-hours $85 per hour = $340

$17,052

$17,392

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.

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Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
1 Is not a significant regulatory action under Executive Order 12866, 2 Would not affect intrastate aviation in Alaska, and 3 Would not have a significant economic impact, positive or negative, on a substantial number of small entities
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16:16 Jun 07, 2021

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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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 20210415, Amendment 39
21437 86 FR 13165, March 8, 2021;
and b. Adding the following new AD:

Airbus Helicopters: Docket No. FAA2021
0453; Project Identifier MCAI2021
00377R.
a Comments Due Date The FAA must receive comments by July 23, 2021.
b Affected Airworthiness Directives ADs This AD replaces AD 20210415, Amendment 3921437 86 FR 13165, March 8, 2021 AD 20210415.
c Applicability This AD applies to Airbus Helicopters specified in paragraph c1 and 2 of this AD, certificated in any category.
1 Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP
helicopters, all serial numbers.

PO 00000

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2 Model AS350B3 helicopters, all serial numbers except those that have embodied Airbus Helicopters Modification 073148 in production.
d Subject Joint Aircraft System Component JASC
Code 5531, Vertical Stabilizer, Spar/Rib.
e Unsafe Condition This AD was prompted by a report that, during an unscheduled post-flight inspection of the tail cone area of an Airbus Helicopters Model AS355NP helicopter, a crack was found in the spar of the upper fin and fractures were found in the two front attachment screws. The FAA is issuing this AD to address cracking in the spar of the upper part of the vertical fin and fractures in the front attachment screws. This condition could lead to in-flight separation of the upper part of the vertical fin, resulting 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 paragraph h of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency EASA AD 20210099, dated April 9, 2021 EASA AD 20210099.
h Exceptions to EASA AD 20210099
1 Where EASA AD 20210099 refers to its effective date or to July 12, 2017, the effective date of EASA AD 20170114, dated June 28, 2017, this AD requires using the effective date of this AD.
2 The Remarks section of EASA AD
20210099 does not apply to this AD.
3 Where EASA AD 20210099 refers to flight hours FH, this AD requires using hours time-in-service.
4 Where paragraph 4 of EASA AD 2021
0099 specifies to contact the manufacturer for approved repair instructions, for this AD, if
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