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Federal Register / Vol. 86, No. 106 / Friday, June 4, 2021 / Rules and Regulations Do not add any additional burden upon the public than was already proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
EASA AD 20200250 describes procedures for replacing any forward engine mount shackle assemblies having part number D7121513500xxx xxx can
be any numerical value with a serviceable part, and re-identifying the engine mount, or replacing any forward engine mount assemblies having part number D7121506500xxx xxx can be any numerical value and fitted with an affected engine mount shackle assembly. This material is reasonably available because the interested parties
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have access to it through their normal course of business or by the means identified in the ADDRESSES section.
Costs of Compliance The FAA estimates that this AD
affects 70 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD:

ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
5 work-hours $85 per hour = $425

Up to $75,360

Up to $75,785

According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators.
As a result, the FAA has included all known costs in the cost estimate.
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 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
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3 Will not have a significant economic impact, positive or negative, on a substantial number of small entities 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:

20210919 Airbus SAS: Amendment 39
21533; Docket No. FAA20210028;
Project Identifier MCAI202001516T.
a Effective Date This airworthiness directive AD is effective July 9, 2021.
b Affected ADs None.
c Applicability This AD applies to all Airbus SAS Model A319171N airplanes, Model A320271N, 272N, and 273N airplanes, and Model A321271N, 272N, 271NX, and 272NX
airplanes, certificated in any category.
d Subject Air Transport Association ATA of America Code 71, Powerplant.
e Reason This AD was prompted by a report indicating that during a full scale fatigue test
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Cost on U.S.
operators Up to $5,304,950.

of the forward engine mounts, premature wear was identified on the forward engine mount shackle assemblies; in addition, during bearing replacement, the bearing lock washer was found broken. The FAA is issuing this AD to address premature wear and broken bearing lock washers at the forward engine mounts, which could lead to overload of the forward engine mount beams and engine mount failure, with consequent in-flight engine detachment, and possibly result in reduced controllability of the airplane.
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 20200250, dated November 11, 2020 EASA AD 20200250.
h Exceptions to EASA AD 20200250
1 Where EASA AD 20200250 refers to its effective date, this AD requires using the effective date of this AD.
2 The Remarks section of EASA AD
20200250 does not apply to this AD.
i Other FAA AD Provisions The following provisions also apply to this AD:
1 Alternative Methods of Compliance AMOCs: The Manager, Large Aircraft Section, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph j of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.

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