5454 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules 

VI. Approval of the Office of the 

Secretary 

The Secretary of Energy has approved 

publication of this notice of proposed 

rulemaking. 

List of Subjects in 10 CFR Part 431 

Administrative practice and 

procedure, Confidential business 

information, Energy conservation, 

Imports, Intergovernmental relations, 

Small businesses. 

Issued in Washington, DC, on December 

23, 2016. 

David J. Friedman, 

Acting Assistant SecretaryEnergy Efficiency 

and Renewable Energy. 

For the reasons set forth in the 

preamble, DOE proposes to amend part 

431 of chapter II, subchapter D, of title 

10 of the Code of Federal Regulations, 

as set forth below: 

PART 431—ENERGY EFFICIENCY 

PROGRAM FOR CERTAIN 

COMMERCIAL AND INDUSTRIAL 

EQUIPMENT 

■ 1. The authority citation for part 431 

continues to read as follows: 

Authority: 42 U.S.C. 6291–6317; 28 U.S.C. 

2461 note. 

■ 2. Section 431.462 is amended by 

adding the definition for ‘‘pool pump 

timer’’ in alphabetical order to read as 

follows: 

§ 431.462 Definitions. 

* * * * * 

Pool pump timer means a pool pump 

control that automatically turns off a 

dedicated-purpose pool pump after a 

run-time of no longer than 10 hours. 

* * * * * 

■ 3. Section 431.465 is amended by 

adding paragraphs (e), (f), (g) and (h) to 

read as follows: 

§ 431.465 Pumps energy conservation 

standards and their compliance dates. 

* * * * * 

(e) For the purposes of paragraph (f) 

of this section, ‘‘WEF’’ means the 

weighted energy factor and ‘‘hhp’’ 

means the rated hydraulic horsepower, 

as determined in accordance with the 

test procedure in § 431.464(b) and 

applicable sampling plans in § 429.59 of 

this chapter. 

(f) Each dedicated-purpose pool pump 

that is not a submersible pump and is 

manufactured starting on July 19, 2021 

must have a WEF rating that is not less 

than the value calculated from the 

following table: 

Equipment class Minimum 

allowable 

WEF score 

[kgal/kWh] Minimum allowable WEF score [kgal/kWh] 

Dedicated-Purpose Pool Pump Variety hhp 

Applicability 

Motor phase 

Self-priming pool filter pumps ............................... 0.711 hp ≤ hhp < 2.5 hp Single ............. WEF = ¥2.30 * ln (hhp) + 6.59. 

Self-priming pool filter pumps ............................... hhp < 0.711 hp ............. Single ............. WEF = 5.55, for hhp ≤ 1.30. hp 

¥ 1.30 * ln (hhp) + 2.90, for hhp > 0.13 hp. 

Non-self-priming pool filter pumps ........................ hhp < 2.5 hp ................. Any ................. WEF = 4.60, for hhp ≤ 0.13 hp 

¥0.85 * ln (hhp) + 2.87, for hhp > 0.13 hp. 

Pressure cleaner booster pumps ......................... Any ................................ Any ................. WEF = 0.42 

(g) Each integral cartridge filter pool 

pump and integral sand filter pool 

pump that is manufactured starting on 

July 19, 2021 must be distributed in 

commerce with a pool pump timer that 

is either integral to the pump or a 

separate component that is shipped 

with the pump. 

(h) For all dedicated-purpose pool 

pumps distributed in commerce with 

freeze protection controls, the pump 

must be shipped with freeze protection 

disabled or with the following default, 

user-adjustable settings: 

(1) The default dry-bulb air 

temperature setting is no greater than 

40 °F; 

(2) The default run time setting shall 

be no greater than 1 hour (before the 

temperature is rechecked); and 

(3) The default motor speed shall not 

be more than 1⁄2 of the maximum 

available speed. 

[FR Doc. 2016–31665 Filed 1–17–17; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0755; Directorate 

Identifier 2010–NE–12–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2012–04– 

01 that applies to all Rolls-Royce plc 

(RR) RB211–Trent 800 model turbofan 

engines. AD 2012–04–01 requires 

removal from service of certain critical 

engine rotating parts based on reduced 

life limits. Since we issued AD 2012– 

04–01, RR has further revised the life 

limits of certain critical engine rotating 

parts. This proposed AD would make 

additional revisions to the life limits of 

certain critical engine rotating parts. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by March 6, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2010– 

0755; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules 5455 

contains this proposed AD, the 

mandatory continuing airworthiness 

information, regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0755; Directorate Identifier 

2010–NE–12–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On February 10, 2012, we issued AD 

2012–04–01, Amendment 39–16956 (77 

FR 10355, February 22, 2012), ‘‘AD 

2012–04–01,’’ for all RR RB211–Trent 

800 model turbofan engines. AD 2012– 

04–01 requires removal from service of 

certain critical engine rotating parts 

based on reduced life limits. AD 2012– 

04–01 resulted from RR reducing the life 

limits of certain critical engine rotating 

parts. We issued AD 2012–04–01 to 

prevent the failure of critical engine 

rotating parts, which could result in 

damage to the engine and damage to the 

airplane. 

Actions Since AD 2012–04–01 Was 

Issued 

Since we issued AD 2012–04–01, RR 

has reduced the life limit of two affected 

critical engine rotating parts and 

extended the life of an additional 

critical engine rotating part. Also since 

we issued AD 2012–04–01, the 

European Aviation Safety Agency 

(EASA) has issued AD 2016–0223, dated 

November 8, 2016, which imposes new 

life limits on certain critical engine 

rotating parts. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

replacement of certain critical engine 

rotating parts at a newer, lower life 

limit. This proposed AD would also 

extend the life limit for an additional 

critical engine rotating part. 

Costs of Compliance 

We estimate that this proposed AD 

affects 16 engines installed on airplanes 

of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement of critical engine rotating parts ............. 0 work-hours × $85 per 

hour = $0.

$45,000 (pro-rated cost of 

parts).

$45,000 $720,000 

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. 

We are 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 

We have 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 that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2012–04–01, Amendment 39–16956 (77 

FR 10355, February 22, 2012), and 

adding the following new AD: 

Rolls-Royce plc: Docket No. FAA–2010– 

0755; Directorate Identifier 2010–NE– 

12–AD. 

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5456 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by March 6, 

2017. 

(b) Affected ADs 

This AD supersedes AD 2012–04–01, 

Amendment 39–16956 (77 FR 10355, 

February 22, 2012). 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RR RB211–Trent 875–17, 877–17, 884–17, 

884B–17, 892–17, 892B–17, and 895–17 

turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7200, Engine (Turbine/Turboprop). 

(e) Unsafe Condition 

This AD was prompted by RR revising the 

life limits of certain critical engine rotating 

parts. We are issuing this AD to prevent the 

failure of critical engine rotating parts, 

damage to the engine, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) After the effective date of this AD, 

remove from service the parts listed in Table 

1 to paragraph (f) of this AD before exceeding 

the new life limit indicated: 

TABLE 1 TO PARAGRAPH (f)—REDUCED PART LIVES

Part nomenclature Part No. 

Life in 

standard 

duty cycles 

Life in cycles 

using the 

HEAVY profile 

Intermediate Pressure (IP) Compressor Rotor Shaft .................................................................. FK24100 12,500 11,500 

IP Compressor Rotor Shaft ......................................................................................................... FK24496 8,860 8,180 

High-Pressure Compressor (HPC) Stage 1 to 4 Rotor Discs Shaft ........................................... FK24009 4,560 4,460 

HPC Stage 1 to 4 Rotor Discs Shaft ........................................................................................... FK26167 5,580 5,280 

HPC Stage 1 to 4 Rotor Discs Shaft ........................................................................................... FK32580 5,580 5,280 

HPC Stage 1 to 4 Rotor Discs Shaft ........................................................................................... FW11590 8,550 6,850 

HPC Stage 1 to 4 Rotor Discs Shaft ........................................................................................... FW61622 8,550 6,850 

HPC Stage 5 and 6 Discs and Cone .......................................................................................... FK25230 5,000 5,000 

HPC Stage 5 and 6 Discs and Cone .......................................................................................... FK27899 5,000 5,000 

IP Turbine Rotor Disc .................................................................................................................. FK21117 11,610 10,400 

IP Turbine Rotor Disc .................................................................................................................. FK33083 0 0 

(2) Reserved. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any IP turbine discs, P/N FK33083, 

into any engine. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency, AD 2016–0223, dated 

November 8, 2016, for more information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2010–0755. 

Issued in Burlington, Massachusetts, on 

January 11, 2017. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2017–00890 Filed 1–17–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0019; Directorate 

Identifier 2016–CE–038–AD] 

RIN 2120–AA64 

Airworthiness Directives; GROB 

Aircraft AG Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for GROB 

Aircraft AG Models GROB G 109 and 

GROB G 109B gliders. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as broken pivots of the tail 

wheel mounting bracket resulting from 

corrosion and damage due to wear. We 

are issuing this proposed AD to require 

actions to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by March 6, 2017. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact GROB 

Aircraft AG, Product Support, 

Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Germany, 

telephone: + 49 (0) 8268–998–105; fax: 

+ 49 (0) 8268–998–200; email: 

productsupport@grob-aircraft.com; 

Internet: grob-aircraft.com. You may 

review this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0019; or in person at the Docket 

Management Facility between 9 a.m. 

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