81376 Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 

Product class 

Integrated 

modified 

energy factor 

(cu.ft./kWh/ 

cycle) 

Integrated 

water 

factor 

(gal/cycle/ 

cu.ft.) 

(D) Front-loading, Standard (1.6 ft3 or greater capacity) ........................................................................................ 1.84 4.7 

(ii) Top-loading, standard clothes 

washers with an average cycle time of 

less than 30 minutes and front-loading, 

standard clothes washers with an 

average cycle time of less than 45 

minutes are not currently subject to 

energy or water conservation standards. 

(h) * * * 

(3)(i) Except as provided in paragraph 

(h)(3)(ii) of this section, clothes dryers 

manufactured on or after January 1, 

2015, shall have a combined energy 

factor no less than: 

Product class 

Combined 

energy factor 

(lbs/kWh) 

(A) Vented Electric, Standard 

(4.4 ft3 or greater capacity) ..................................... 3.73 

(B) Vented Electric, Compact 

(120V) (less than 4.4 ft3 

capacity) ............................ 3.61 

(C) Vented Electric, Compact 

(240V) (less than 4.4 ft3 

capacity) ............................ 3.27 

(D) Vented Gas .................... 3.30 

(E) Ventless Electric, Compact (240V) (less than 4.4 

ft3 capacity) ....................... 2.55 

(F) Ventless Electric, Combination Washer-Dryer ...... 2.08 

(ii) Vented, electric standard clothes 

dryers and vented gas clothes dryers 

with a cycle time of less than 30 

minutes are not currently subject to 

energy conservation standards. 

* * * * * 

[FR Doc. 2020–26976 Filed 12–15–20; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3343; Product 

Identifier 2015–SW–078–AD; Amendment 

39–21353; AD 2020–25–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2014–12– 

12, which applied to certain Airbus 

Helicopters Model EC120B and 

EC130B4 helicopters. AD 2014–12–12 

required inspecting and, if necessary, 

replacing parts of the sliding door star 

support attachment assembly. This AD 

requires modifying the sliding door star 

support stringer as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is incorporated by 

reference (IBR). This AD was prompted 

by several incidents involving 

helicopter left-hand side doors (both 

swinging and sliding) that revealed 

weaknesses in the locking mechanism. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective January 21, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 21, 2021. 

ADDRESSES: For material incorporated 

by reference 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 material on the EASA website 

at https://ad.easa.europa.eu. You may 

view this material at the FAA, Office of 

the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3343. 

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–2016– 

3343; 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: 

Kathleen Arrigotti, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA; telephone 

206–231–3218; email 

kathleen.arrigotti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0095, dated April 29, 2020 (EASA 

AD 2020–0095), to correct an unsafe 

condition for certain Airbus Helicopters 

Model EC120B and EC130B4 

helicopters. 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD to supersede AD 2014–12–12, 

Amendment 39–17873 (79 FR 36638, 

June 30, 2014) (AD 2014–12–12). AD 

2014–12–12 applied to certain Airbus 

Helicopters Model EC120B and 

EC130B4 helicopters. The SNPRM 

published in the Federal Register on 

September 22, 2020 (85 FR 59454). The 

FAA preceded the SNPRM with a notice 

of proposed rulemaking (NPRM) that 

published in the Federal Register on 

October 26, 2016 (81 FR 74362). The 

NPRM was prompted by the 

determination to expand the 

applicability to all serial-numbered 

EC120B helicopters with affected 

sliding doors installed and require 

compliance with revised service 

information. The NPRM proposed to 

require inspecting each upper and lower 

locking pin control rod end fitting and 

replacing it if necessary, cleaning and 

dye-penetrant inspecting the star 

support pin for cracking and replacing 

it if necessary, and reinforcing the 

sliding door star support stringer. The 

SNPRM proposed to require modifying 

the door locking/unlocking mechanism, 

as specified in EASA AD 2020–0095. 

The FAA is proposing this AD to 

address failure of the sliding door star 

support, which could inhibit the 

operation of the sliding door from the 

inside, delaying the evacuation of 

passengers during an emergency. See 

EASA AD 2020–0095 for additional 

background information. 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 81377 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the SNPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes and an exception that 

does not affect helicopters of U.S. 

registry. The FAA has determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in-the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed EASA AD 2020– 

0095, which describes improved 

procedures for modifying the door 

locking/unlocking mechanism (e.g. 

modifying the sliding door star support 

by installing a reinforcing bracket and 

replacing rod ends). 

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. 

Differences Between This AD and the 

EASA AD 

EASA AD 2020–0095 specifies to do 

the modification within 24 months. This 

AD requires the modification be done 

within 460 hours time-in-service (TIS), 

based on an average of 230 hours TIS 

per year. The FAA has determined this 

compliance time represents the 

maximum interval of time allowable for 

the affected helicopters to continue to 

safely operate before the modification is 

done. While EASA AD 2020–0095 

allows credit for Airbus Helicopters 

Alert Service Bulletin No. EC120– 

52A018, Revision 0, dated November 

13, 2015 (ASB EC120–52A018 at 

original issue), this AD does not because 

the applicable helicopter is not U.S.- 

registered. 

Costs of Compliance 

The FAA estimates that this AD 

would affect 261 helicopters of U.S. 

Registry. Labor rates are estimated at 

$85 per work-hour. Based on these 

numbers, the FAA estimates that 

operators may incur the following costs 

in order to comply with this proposed 

AD. 

Modifying the door locking/unlocking 

mechanism takes about 20 work-hours 

and parts cost about $642 for an 

estimated cost of $2,342 per helicopter 

and $611,262 for the U.S. fleet. 

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: 

(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) 2014–12–12, Amendment 39– 

17873 (79 FR 36638, June 30, 2014); and 

■ b. Adding the following new AD: 

2020–25–11 Airbus Helicopters: 

Amendment 39–21353; Docket No. 

FAA–2016–3343; Product Identifier 

2015–SW–078–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 21, 2021. 

(b) Affected ADs 

This AD replaces AD 2014–12–12, 

Amendment 39–17873 (79 FR 36638, June 

30, 2014). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC120B and EC130B4 helicopters, 

certificated in any category, as identified in 

European Union Aviation Safety Agency 

(EASA) AD 2020–0095, dated April 29, 2020 

(EASA AD 2020–0095). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5200, Doors. 

(e) Reason 

This AD was prompted by reports of 

passengers not being able to open a 

helicopter’s left-hand door after landing. The 

FAA is issuing this AD to address failure of 

the sliding door star support, which could 

inhibit the operation of the sliding door from 

the inside, delaying the evacuation of 

passengers during an emergency. 

(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 2020–0095. 

(h) Exceptions to EASA AD 2020–0095 

(1) Where EASA AD 2020–0095 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (1) of EASA AD 2020– 

0095 specifies to complete the actions within 

24 months after its effective date, this AD 

requires completion within 460 hours timein-service after the effective date of this AD. 

(3) The ‘‘Remarks’’ section of EASA AD 

2020–0095 does not apply to this AD. 

(4) Although the service information 

referenced in EASA AD 2020–0095 specifies 

to discard certain parts, this AD does not 

include that requirement. 

(5) Where EASA AD 2020–0095 allows 

credit for Airbus Helicopters Alert Service 

Bulletin No. EC120–52A018, Revision 0, 

dated November 13, 2015 (ASB EC120– 

52A018 at original issue), this AD does not. 


khammond on DSKJM1Z7X2PROD with RULES
81378 Federal Register / Vol. 85, No. 242 / Wednesday, December 16, 2020 / Rules and Regulations 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Manager, Strategic Policy Rotorcraft Section, 

FAA, 10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone 817–222–5110; email 9/ 

ASW/FTW/AMOC-Requests@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. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA; telephone 

206–231–3218; email kathleen.arrigotti@

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 2020–0095, dated April 29, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0095, 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 service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. 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–2016–3343. 

(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 https://www.archives.gov/ 

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

Issued on December 3, 2020. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2020–27659 Filed 12–15–20; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0592; Project 

Identifier AD–2020–00251–E; Amendment 

39–21352; AD 2020–25–10] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) GEnx1B64/P2, GEnx-1B67/P2, GEnx-1B70/ 

75/P2, GEnx-1B70/P2, GEnx-1B70C/P2, 

GEnx-1B74/75/P2, GEnx-1B76/P2, 

GEnx-1B76A/P2, and GEnx-2B67/P 

model turbofan engines with a certain 

high-pressure turbine (HPT) rotor stage 

2 disk installed. This AD was prompted 

by a report of the potential for 

undetected subsurface anomalies 

formed during the manufacturing 

process that could result in uncontained 

failure of the HPT rotor stage 2 disk. 

This AD requires an immersion 

ultrasonic inspection (USI) of the HPT 

rotor stage 2 disk and, depending on the 

results of the inspection, replacement of 

the HPT rotor stage 2 disk with a part 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective January 21, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 21, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, GE Aviation, 

Room 285, 1 Neumann Way, Cincinnati, 

OH 45215; phone: (513) 552–3272; 

email: aviation.fleetsupport@ge.com. 

You may view this 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) 238–7759. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0592. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0592; 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: 

Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7743; fax: (781) 238– 

7199; email: Mehdi.Lamnyi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all GE GEnx-1B64/P2, GEnx1B67/P2, GEnx-1B70/75/P2, GEnx1B70/P2, GEnx-1B70C/P2, GEnx-1B74/ 

75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, 

and GEnx-2B67/P model turbofan 

engines with a certain HPT rotor stage 

2 disk installed. The NPRM published 

in the Federal Register on June 12, 2020 

(85 FR 35816). The NPRM was 

prompted by a report of the potential for 

undetected subsurface anomalies 

formed during the manufacturing 

process that could result in uncontained 

failure of the HPT rotor stage 2 disk. In 

the NPRM, the FAA proposed to require 

an immersion USI of the HPT rotor stage 

2 disk and, depending on the results of 

the inspection, replacement of the HPT 

rotor stage 2 disk with a part eligible for 

installation. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from six 

commenters. The commenters were Air 

Line Pilots Association, International 

(ALPA); The Boeing Company (Boeing); 

Cargolux Airlines International S.A. 

(Cargolux); GE Aviation; United Airlines 

(UAL) Engineering; and Qantas Airways 

Limited (Qantas). One commenter 

requested that the FAA update the 

Affected ADs paragraph of this AD. One 

commenter requested that the HPT rotor 

stage 2 disks be replaced instead of 

inspected. One commenter requested 

that the FAA update the Definitions 

paragraph of this AD. Two commenters 

requested adding credit for previous 

action. Three commenters supported the 

AD. The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 


khammond on DSKJM1Z7X2PROD with RULES