85504 Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 

available documents online in the 

ADAMS Public Documents collection at 

https://www.nrc.gov/reading-rm/ 

adams.html. To begin the search, select 

‘‘Begin Web-based ADAMS Search.’’ For 

problems with ADAMS, please contact 

the NRC’s Public Document Room (PDR) 

reference staff at 1–800–397–4209, 301– 

415–4737, or by email to pdr.resource@

nrc.gov. 

• Attention: The Public Document 

Room (PDR), where you may examine 

and order copies of public documents, 

is currently closed. You may submit 

your request to the PDR via email at 

pdr.resource@nrc.gov or call 1–800– 

397–4209 between 8:00 a.m. and 4:00 

p.m. (EST), Monday through Friday, 

except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: 

Stewart Schneider, Office of Nuclear 

Material Safety and Safeguards, 

telephone: 301–415–4123, 3453, email: 

Stewart.Schneider@nrc.gov, or On Yee, 

Office of Nuclear Reactor Regulation, 

telephone: 301–415–1905, email: 

On.Yee@nrc.gov. Both are staff of the 

U.S. Nuclear Regulatory Commission, 

Washington, DC 20555–0001. 

SUPPLEMENTARY INFORMATION: On 

October 2, 2020 (85 FR 62199), the NRC 

published a direct final rule amending 

its regulations in appendix H, ‘‘Reactor 

Vessel Material Surveillance Program 

Requirements’’ (appendix H), to part 50 

of title 10 of the Code of Federal 

Regulations (10 CFR), ‘‘Domestic 

Licensing of Production and Utilization 

Facilities,’’ to revise the NRC’s reactor 

vessel material surveillance program 

requirements for commercial light-water 

reactors. The direct final rule revises the 

requirements in appendix H to 10 CFR 

part 50 associated with the testing of 

specimens contained within 

surveillance capsules and reporting the 

surveillance test results. The direct final 

rule also clarifies the requirements for 

the design of surveillance programs and 

the capsule withdrawal schedules for 

surveillance capsules in reactor vessels 

purchased after 1982. 

In the direct final rule published on 

October 2, 2020, the NRC stated that if 

no significant adverse comments were 

received, the direct final rule would 

become effective on February 1, 2021. 

The NRC received and docketed two 

comment submissions on the 

companion proposed rule (85 FR 62234; 

October 2, 2020). Electronic copies of 

the comments can be obtained from the 

Federal Rulemaking website at https://

www.regulations.gov under Docket ID 

NRC–2017–0151 and are also available 

in ADAMS under Accession Nos. 

ML20301A624 and ML20308A229, 

respectively. 

The NRC determined that the two 

comment submissions addressed issues 

that were outside the scope of the direct 

final rule or were not significant nor 

adverse. One comment submission 

questioned (1) the use of Charpy Vnotch testing procedures, (2) the 

subsequent license renewal and 

extended power uprate for Turkey Point 

Nuclear Generating Units 3 and 4, (3) 

the use of Integrated Surveillance 

Programs, and (4) the timing associated 

with specimen testing and capsule 

report submittal. With respect to the 

items 1–3, these issues are outside the 

scope of this direct final rule. While 

item 4 is within the scope of the direct 

final rule, the NRC determined that the 

comment was not significant nor 

adverse. The other comment submission 

is outside the scope of this direct final 

rule. Therefore the direct final rule will 

become effective as scheduled. 

Paperwork Reduction Act Statement 

The direct final rule contains a new 

or amended collection of information 

subject to the Paperwork Reduction Act 

of 1995 (44 U.S.C. 3501 et seq.). The 

collections of information were 

approved by the Office of Management 

and Budget (OMB), approval number 

3150–0011. 

Public Protection Notification 

The NRC may not conduct or sponsor, 

and a person is not required to respond 

to a collection of information unless the 

document requesting or requiring the 

collection displays a currently valid 

OMB control number. 

Dated: December 21, 2020. 

For the Nuclear Regulatory Commission. 

Pamela J. Shepherd-Vladimir, 

Acting Chief, Regulatory Analysis and 

Rulemaking Support Branch, Division of 

Rulemaking, Environmental, and Financial 

Support, Office of Nuclear Material Safety 

and Safeguards. 

[FR Doc. 2020–28814 Filed 12–28–20; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0858; Project 

Identifier MCAI–2020–00949–T; Amendment 

39–21370; AD 2020–26–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2016–07– 

14, which applied to certain Airbus 

Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. AD 

2016–07–14 required replacing the 

clips, shear webs, and angles, related 

investigative actions, and repair if 

necessary. This AD retains the actions of 

AD 2016–07–14, and requires modifying 

(replacing) the clips, shear webs, and 

angles at a certain rear fuselage area 

with new parts, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is incorporated by 

reference. The FAA has also determined 

that additional airplanes are subject to 

the unsafe condition. This AD was 

prompted by fatigue testing that 

determined that fatigue damage could 

appear on clips, shear webs, and angles 

at certain rear fuselage sections and 

certain frames. The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective February 2, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 2, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

the EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +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 206–231–3195. 


KHAMMOND on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 85505 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0858. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0858; 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, M– 

30, West Building Ground Floor, Room 

W12–140, 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; 

telephone and fax 206–231–3223; 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 

2020–0153, dated July 10, 2020 (EASA 

AD 2020–0153) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain Airbus 

Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

Model A320–211, –212, –214, –215 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

EASA AD 2020–0153 superseded EASA 

AD 2014–0177, dated July 25, 2014 

(which corresponds to FAA AD 2016– 

07–14, 39–18459 (81 FR 21244, April 

11, 2016) (AD 2016–07–14)). Model 

A320–215 airplanes are not certificated 

by the FAA and are not included on the 

U.S. type certificate data sheet; this AD 

therefore does not include those 

airplanes in the applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2016–07–14. 

AD 2016–07–14 applied to certain 

Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The NPRM published in the Federal 

Register on October 1, 2020 (85 FR 

61892). The NPRM was prompted by 

fatigue testing that determined that 

fatigue damage could appear on clips, 

shear webs, and angles at certain rear 

fuselage sections and certain frames. 

The NPRM proposed to retain the 

actions of AD 2016–07–14, and require 

modifying (replacing) the clips, shear 

webs, and angles at a certain rear 

fuselage area with new parts, as 

specified in EASA AD 2020–0153. The 

NPRM also proposed to apply to 

additional airplanes subject to the 

unsafe condition. 

The FAA is issuing this AD to address 

fatigue damage on the clips, shear webs, 

and angles, which could affect the 

structural integrity of the airplane. See 

the MCAI for additional background 

information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA has considered 

the comments received. United Airlines 

and an anonymous commenter 

indicated their support for the NPRM. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• 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 2020–0153 describes 

procedures for replacement of affected 

parts (as required by FAA AD 2016–07– 

14). EASA AD 2020–0153 also describes 

procedures for a modification by 

replacing the clips, shear webs, and 

angles at the rear fuselage area of section 

19 at frame 72 and frame 74 with new 

parts without pilot holes, and installing 

oversized Hi-Loks, nominal aluminum 

rivets, and nominal Hi-Loks in certain 

positions. This material is reasonably 

available because the interested parties 

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 219 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained actions from AD 2016–07–14 (for 44 

airplanes affected).

Up to 110 work-hours × $85 per hour = Up to 

$9,350.

$10,000 Up to $19,350 .. Up to $851,400. 

New actions ..................................................... 126 work-hours × $85 per hour = $10,710 ..... 51,750 62,460 .............. 13,678,740. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s 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 Agency’s 

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: 


KHAMMOND on DSKJM1Z7X2PROD with RULES
85506 Federal Register / Vol. 85, No. 249 / Tuesday, December 29, 2020 / Rules and Regulations 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(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 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

(AD) 2016–07–14, Amendment 39– 

18459 (81 FR 21244, April 11, 2016), 

and 

■ b. Adding the following new AD: 

2020–26–15 Airbus SAS: Amendment 39– 

21370; Docket No. FAA–2020–0858; 

Project Identifier MCAI–2020–00949–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 2, 2021. 

(b) Affected ADs 

This AD replaces AD 2016–07–14, 

Amendment 39–18459 (81 FR 21244, April 

11, 2016) (AD 2016–07–14). 

(c) Applicability 

This AD applies to Airbus SAS airplanes 

specified in paragraphs (c)(1) through (3) of 

this AD, certificated in any category, as 

identified in European Union Aviation Safety 

Agency (EASA) AD 2020–0153, dated July 

10, 2020 (EASA AD 2020–0153). 

(1) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(2) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(3) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by fatigue testing 

that determined that fatigue damage could 

appear on clips, shear webs, and angles at 

certain rear fuselage sections and certain 

frames. The FAA is issuing this AD to 

address fatigue damage on the clips, shear 

webs, and angles, which could affect the 

structural integrity 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, EASA AD 2020–0153. 

(h) Exceptions to EASA AD 2020–0153 

The ‘‘Remarks’’ section of EASA AD 2020– 

0153 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email Sanjay.Ralhan@

faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0153, dated July 10, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0153, contact the 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. 

(4) You may view this 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 

206–231–3195. This material may be found 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–0858. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to: http://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on December 11, 2020. 

Lance T. Gant, Director, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–28858 Filed 12–28–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0781; Product 

Identifier 2018–CE–045–AD; Amendment 

39–21369; AD 2020–26–14] 

RIN 2120–AA64 

Airworthiness Directives; Mitsubishi 

Heavy Industries, Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 75–16–20, 

which applied to all Mitsubishi Heavy 

Industries, Ltd., Model MU–2B, MU– 

2B–10, MU–2B–15, MU–2B–20, MU– 

2B–25, MU–2B–26, MU–2B–30, MU– 

2B–35, and MU–2B–36 airplanes. AD 

75–16–20 required repetitive 

inspections of the propeller pitch 

control (PPC) lever for security and 

proper rigging. This AD requires 


KHAMMOND on DSKJM1Z7X2PROD with RULES