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Federal Register / Vol. 86, No. 50 / Wednesday, March 17, 2021 / Rules and Regulations
tank valves being either intentionally or inadvertently closed.
Section 29.979d requires that the helicopter defueling system not including fuel tanks and fuel tank vents withstand an ultimate load that is 2.0
times the load arising from the maximum permissible defueling pressure positive or negative at the helicopters fueling connection. As the design proposed by AWPC does not include a defueling capability, these special conditions do not include a requirement derived from 14 CFR
29.979d.
These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
Discussion of Comments The FAA issued Notice of Proposed Special Conditions No. 27051SC for the Leonardo Model A119 and AW119
MKII helicopters, which was published in the Federal Register on November 2, 2020 85 FR 69265. No comments were received, and the special conditions are adopted as proposed.
Applicability As discussed above, these special conditions are applicable to Leonardo Model A119 and AW119 MKII
helicopters. Should AWPC apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. H7EU
to incorporate the same novel or unusual design feature, these special conditions would apply to that model as well.
Conclusion This action affects only one novel or unusual design feature on the Leonardo Model A119 and AW119 MKII
helicopters. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of this feature on these helicopters.
List of Subjects in 14 CFR Part 27
Aircraft, Aviation safety, Reporting and recordkeeping requirements.

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Authority Citation The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106f, 106g, 40113, 44701, 44702, 44704.

The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are

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issued as part of the type certification basis for Leonardo S.p.A. Model A119
and AW119 MKII helicopters, as modified by AgustaWestland Philadelphia Corporation.
The pressure refueling system must be designed and installed as follows:
a For systems intended for pressure refueling, a means in addition to the normal means for limiting the tank content must be installed to prevent damage to the fuel tank in case of failure of the normal means.
b The helicopter pressure fueling system not fuel tanks and fuel tank vents must withstand an ultimate load that is 2.0 times the load arising from maximum pressure, including surge, that is likely to occur during fueling.
The maximum surge pressure must be established with any combination of tank valves being either intentionally or inadvertently closed.
Issued in Fort Worth, Texas, on December 11, 2020.
Jorge Castillo, Manager, Rotorcraft Standards Branch, AIR
680, Policy & Innovation Division, Aircraft Certification Service.
FR Doc. 202105263 Filed 31621; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Docket No. FAA20200914; Product Identifier 2020NM058AD; Amendment 3921463; AD 20210520
RIN 2120AA64

Airworthiness Directives; Airbus SAS
Airplanes Federal Aviation Administration FAA, Department of Transportation DOT.
ACTION: Final rule.
AGENCY:

The FAA is superseding Airworthiness Directive AD 201816
02, which applied to all Airbus SAS
Model A318111 and 112 airplanes;
Model A319111, 112, 113, 114, and 115 airplanes; Model A320211, 212, 214, and 216 airplanes; and Model A321111, 112, 211, 212, and 213
airplanes. AD 20181602 required modifying and re-identifying the 3-lug aft engine mount assemblies. This AD
continues to require modifying and reidentifying the 3-lug aft engine mount assemblies, and also requires modifying and re-identifying the 4-lug aft engine mount assemblies; as specified in a European Union Aviation Safety Agency
SUMMARY:

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This AD is effective April 21, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD
as of April 21, 2021.
ADDRESSES: For material incorporated by reference IBR in this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49
221 8999 000; email: ADs@
easa.europa.eu; internet:
www.easa.europa.eu. You may find this IBR material on the EASA website at https ad.easa.europa.eu. You may view this IBR material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 2062313195.
It is also available in the AD docket on the internet at https
www.regulations.gov by searching for and locating Docket No. FAA2020
0914.
DATES:

Examining the AD Docket
14 CFR Part 39

PO 00000

EASA AD, which is incorporated by reference. This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. The FAA is issuing this AD to address the unsafe condition on these products.

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You may examine the AD docket on the internet at https
www.regulations.gov by searching for and locating Docket No. FAA2020
0914; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M30, West Building Ground Floor, Room W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
phone and fax: 2062313223; email:
sanjay.ralhan@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD
20200085, dated April 6, 2020 EASA
AD 20200085 also referred to as the
E:FRFM17MRR1.SGM

17MRR1