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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Proposed Rules
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 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 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:

1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

General Electric Company: Docket No. FAA
20201179; Project Identifier AD2020
00818E.

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a Comments Due Date The FAA must receive comments on this airworthiness directive AD by April 8, 2021.
b Affected ADs None.
c Applicability This AD applies to all General Electric Company GE CF680A, CF680A1, CF6
80A2, CF680A3, CF680C2A1, CF6
80C2A2, CF680C2A3, CF680C2A5, CF6
80C2A5F, CF680C2A8, CF680C2B1, CF6
80C2B1F, CF680C2B1F1, CF680C2B1F2,
VerDate Sep<11>2014

18:29 Feb 19, 2021

Jkt 253001

d Subject Joint Aircraft System Component JASC
Code 7250, Turbine Section.
e Unsafe Condition This AD was prompted by an inspection by the manufacturer that revealed cracking of the high-pressure turbine HPT rotor stage 1
disk, caused by initial flange-to-flange cracking on the HPT thermal shield between the HPT rotor stage 1 disk and the HPT rotor stage 2 disk. The FAA is issuing this AD to prevent failure of the HPT rotor stage 1 disk and the HPT rotor stage 2 disk. The unsafe condition, if not addressed, could result in uncontained release of the HPT rotor stage 1
and stage 2 disks, damage to the engine, and damage to the airplane.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions 1 After the effective date of this AD, at every piece-part exposure of the HPT rotor stage 1 disk, HPT rotor stage 2 disk, or the HPT thermal shield, perform a visual inspection and a fluorescent penetrant inspection FPI of the HPT thermal shield.
2 During any inspection required by paragraph g1 of this AD, if a crack extending through either the forward or aft flange of the HPT thermal shield is detected, remove the HPT thermal shield, the HPT
rotor stage 1 disk, and the HPT rotor stage 2
disk from service.
h Installation Prohibition Do not install onto any engine an HPT
rotor stage 1 disk or HPT rotor stage 2 disk that was removed from service due to the requirements of paragraph g2 of this AD.

PART 39AIRWORTHINESS
DIRECTIVES

39.13

CF680C2B2, CF680C2B2F, CF680C2B3F, CF680C2B4, CF680C2B4F, CF680C2B5F, CF680C2B6, CF680C2B6F, CF6
80C2B6FA, CF680C2B7F, CF680C2B8F, CF680C2D1F, CF680C2K1F and CF6
80C2L1F model turbofan engines.

i Definition For the purpose of this AD, piece-part exposure is when the HPT rotor stage 1
disk, HPT rotor stage 2 disk, or HPT thermal shield is separated from their mating rotor parts within the HPT rotor module.
j Alternative Methods of Compliance AMOCs 1 The Manager, ECO 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ECO Branch, send it to the attention of the person identified in Related Information. You may email your request to: ANE-AD-AMOC@faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/
certificate holding district office.

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k Related Information 1 For more information about this AD, contact Kevin M. Clark, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781
2387088; fax: 781 2387199; email:
Kevin.M.Clark@faa.gov.
2 For service information identified in this AD, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: 513 5523272; email:
aviation.fleetsupport@ae.ge.com; website:
www.ge.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781 2387759.
Issued on January 20, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202101814 Filed 21921; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210014; Project Identifier MCAI202001457T
RIN 2120AA64

Airworthiness Directives; Airbus SAS
Airplanes Federal Aviation Administration FAA, DOT.
ACTION: Notice of proposed rulemaking NPRM.
AGENCY:

The FAA proposes to adopt a new airworthiness directive AD for certain Airbus SAS Model A330200
Freighter series airplanes. This proposed AD was prompted by a report indicating occurrences of broken brackets of the support structure of the halon fire extinguishing bottle 4005WX;
investigation showed that fatigue cracks initiated in the attachment brackets at the cross beams due to dynamic loading, and in some cases propagated in the struts. This proposed AD would require replacing the support brackets of the 4005WX fire extinguisher bottle with reinforced support brackets, and replacing the strut assembly at the affected location, as specified in a European Union Aviation Safety Agency EASA AD, which is proposed for incorporation by reference. The FAA is proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by April 8, 2021.
SUMMARY:

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