This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

67348 

Vol. 80, No. 211 

Monday, November 2, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4808; Directorate 

Identifier 2014–NM–134–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. This proposed AD was 

prompted by reports that cracks were 

found on an adjacent hole of certain 

frames of the center wing box (CWB). 

This proposed AD would require 

removing fasteners, a rototest inspection 

of fastener holes, installing new 

fasteners; and if necessary, oversizing 

the holes and doing rototest inspections 

for cracks, and repairing any cracking 

that is found. We are proposing this AD 

to detect and correct cracking on certain 

holes of certain frames of the CWB, 

which could affect the structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by December 17, 

2015. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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–2015– 

4808; 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 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

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–2015–4808; Directorate Identifier 

2014–NM–134–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 based on 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0149, dated June 13, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A330–200, –200 Freighter, and 

–300 series airplanes; and Model A340– 

200 and –300 series airplanes. The 

MCAI states: 

During accomplishment of A330 

Airworthiness Limitation Item (ALI) task 57– 

11–04 on the rear fitting of the Frame (FR) 

40 between stringers 38 and 39 on both [lefthand] LH/[right-hand] RH sides, cracks were 

found on an adjacent hole. After reaming at 

second oversize of the subject hole, the crack 

was still present. 

Other crack findings on this adjacent hole 

have been reported on A330 and A340–200/ 

–300 aeroplanes as a result of sampling 

inspections. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires removal of the fasteners 

and repetitive rototest inspections of fastener 

holes at FR40 vertical web located above 

Center Wing Box (CWB) lower panel 

reference and/or below CWB lower panel 

reference on both sides and, depending on 

findings, accomplishment of the applicable 

corrective actions. 

Note: These holes affected by this [EASA] 

AD are different from the ones affected by 

EASA AD 2009–0001 [http://

ad.easa.europa.eu/blob/easa_ad_2009_

0001.pdf/AD_2009-0001_1]. 

Required actions also include 

oversizing certain holes, installing new 

fasteners, and repairing any cracking 

that is found. The initial compliance 

times range from 13,500 to 30,900 flight 

cycles, or 57,000 to 162,000 flight hours, 

depending on operation and utilization. 

The repetitive compliance times are 

7,400 flight cycles/24,300 flight hours or 

5,950 flight cycles/40,400 flight hours 

from ALI embodiment. You may 

examine the MCAI in the AD docket on 


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the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4808. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The service 

information describes procedures for 

removing the fasteners and doing a 

repetitive rototest inspection of fastener 

holes at frame (FR) 40 vertical web on 

both sides, installing new fasteners in 

transition fit, and oversizing the holes. 

• Airbus Service Bulletin A330–57– 

3114, dated March 12, 2013. 

• Airbus Service Bulletin A330–57– 

3115, dated April 4, 2013. 

• Airbus Service Bulletin A330–57– 

3116, dated March 12, 2013. 

• Airbus Service Bulletin A340–57– 

4123, dated March 12, 2013. 

• Airbus Service Bulletin A340–57– 

4124, Revision 01, dated August 22, 

2013. 

• Airbus Service Bulletin A340–57– 

4125, dated March 12, 2013. 

This service information 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 of 

this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 35 airplanes of U.S. registry. 

We also estimate that it would take 

about 78 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $232,050, or $6,630 per 

product, per inspection cycle. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 98 work-hours and require parts 

costing $136,400, for a cost of up to 

$144,730 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

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 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. 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; 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 adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–4808; 

Directorate Identifier 2014–NM–134–AD. 

(a) Comments Due Date 

We must receive comments by December 

17, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers, except those on which 

Airbus Modification (Mod) 55792 or Mod 

55306 has been embodied in production, and 

except those on which Airbus Repair 

Instruction R57115092 has been embodied in 

service on both right-hand (RH) and left-hand 

(LH) sides. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243 –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports that 

cracks were found on an adjacent hole of 

certain frames of the center wing box (CWB). 

We are issuing this AD to detect and correct 

cracking on certain holes of the CWB, which 

could affect the structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Do a rototest inspection of the fastener 

holes at the frame (FR) 40 vertical web, on 

both sides, as specified in table 1 to 

paragraph (g) of this AD, except as required 

by paragraph (k) of this AD. 


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67350 Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / Proposed Rules 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE LOCATION, METHOD, AND TIME

For model In configuration Inspect 

In accordance with the 

accomplishment instructions of 

At the later of— 

The applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of 

And the earlier of 

A330–300 series 

airplanes.

Pre-mod 44360 .. Below the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A330–57–3114, dated 

March 12, 2013.

Airbus Service Bulletin 

A330–57–3114, dated 

March 12, 2013.

Within 2,400 flight cycles 

or 24 months after the 

effective date of this 

AD. 

A330–200 and 

–300 series airplanes.

Post-mod 44360 

and pre-mod 

49202.

Below the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A330–57–3116, dated 

March 12, 2013.

Airbus Service Bulletin 

A330–57–3116, dated 

March 12, 2013.

Within 2,400 flight cycles 

or 24 months after the 

effective date of this 

AD. 

A330–200 and 

–300 series airplanes.

Pre-mod 55306 

and pre-mod 

55792.

Above the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A330–57–3115, dated 

April 4, 2013.

Airbus Service Bulletin 

A330–57–3115, dated 

April 4, 2013.

Within 2,400 flight cycles 

or 24 months after the 

effective date of this 

AD. 

A340–200 and 

–300 series airplanes.

Pre-mod 44360 .. Below the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A340–57–4123, dated 

March 12, 2013.

Airbus Service Bulletin 

A340–57–4123, dated 

March 12, 2013.

Within 1,300 flight cycles 

or 24 months after the 

effective date of this 

AD. 

A340–200 and 

–300 series airplanes.

Pre-mod 55306 

and pre-mod 

55792.

Above the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A340–57–4124, Revision 01, dated August 

22, 2013.

Airbus Service Bulletin 

A340–57–4124, Revision 01, dated August 

22, 2013.

Within 1,300 flight cycles 

or 24 months after the 

effective date of this 

AD. 

A340–200 and 

–300 series airplanes.

Post-mod 44360 

and pre-mod 

4902.

Below the CWB 

lower panel 

reference.

Airbus Service Bulletin 

A340–57–4125, dated 

March 12, 2013.

Airbus Service Bulletin 

A340–57–4125, dated 

March 12, 2013.

Within 1,300 flight cycles 

or 24 months after the 

effective date of this 

AD. 

(h) Follow-On Actions: No Cracking 

If no crack is found during any inspection 

required by paragraph (g) of this AD, do the 

actions specified in paragraphs (h)(1) and 

(h)(2) of this AD. 

(1) Before further flight, install new 

fasteners in the transition fit, in accordance 

with the Accomplishment Instructions of the 

service information identified in table 1 to 

paragraph (g) of this AD; as applicable. 

(2) Repeat the inspection required by 

paragraph (g) of this AD thereafter at the 

applicable time identified in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

identified in table 1 to paragraph (g) of this 

AD; as applicable. 

(i) Follow-On Actions for Crack Findings 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, oversize the holes to the first 

oversize in comparison with the current hole 

diameter, and do a rototest inspection for 

cracks, in accordance with the 

Accomplishment Instructions of the service 

information identified in table 1 to paragraph 

(g) of this AD; as applicable. 

(1) If no cracking is found during the 

rototest inspection required by paragraph (i) 

of this AD, do the actions specified in 

paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. 

(i) Before further flight: Install new 

fasteners in the transition fit, in accordance 

with the Accomplishment Instructions of the 

service information identified in table 1 to 

paragraph (g) of this AD; as applicable. 

(ii) Repeat the inspection required by 

paragraph (g) of this AD thereafter at the 

applicable time identified in paragraph 1.E., 

‘‘COMPLIANCE,’’ of the service information 

identified in table 1 to paragraph (g) of this 

AD; as applicable. 

(2) If cracking is found during the rototest 

inspection required by paragraph (i) of this 

AD, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(j) Terminating Action Specifications 

Accomplishment of the initial and 

repetitive inspections required by this AD 

terminates accomplishment of Airworthiness 

Limitation Items Tasks 57–11–04 and 57–11– 

02 of the Airworthiness Limitation Section 

(ALS) Part 2, Damage Tolerant Airworthiness 

Limitation Items (DT ALI). 

(1) Installation of new fasteners as 

specified in paragraph (h)(1) of this AD does 

not terminate the repetitive inspections 

required by paragraph (g) of this AD. 

(2) Accomplishment of the corrective 

actions specified in paragraphs (i) and (i)(1) 

of this AD does not terminate the repetitive 

inspections required by paragraph (g) of this 

AD. 

(3) Accomplishment of the repair specified 

in paragraph (i)(2) of this AD does not 

terminate repetitive inspections required by 

paragraph (g) of this AD, unless the approved 

repair method specified otherwise. 

(k) Exceptions to Service Information 

(1) If the service information identified in 

table 1 to paragraph (g) of this AD specifies 

contacting Airbus for appropriate action: 

Before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the EASA; or Airbus’s 

EASA DOA. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

the service information specified in table 1 to 

paragraph (g) of this AD specifies a 

Compliance Time in terms of a ‘‘Threshold’’ 

and ‘‘Grace Period,’’ this AD requires 

compliance at the later of the applicable 

Threshold and Grace Period. 

(3) Where paragraph 1.E., ‘‘Compliance,’’ of 

the service information specified in table 1 to 

paragraph (g) of this AD specifies a 

Threshold as ‘‘before next flight,’’ this AD 

requires compliance before the next flight 

after the applicable finding. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (i) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (l)(1), 

(l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or 

(l)(9) of this AD. This service information is 

not incorporated by reference in this AD. 

(1) Airbus Technical Disposition Reference 

LR57D11023270, Issue B, dated July 12, 

2011. 

(2) Airbus Technical Disposition Reference 

LR57D11029171, Issue B, dated September 6, 

2011. 

(3) Airbus Technical Disposition Reference 

LR57D11029173, Issue B, dated September 6, 

2011. 

(4) Airbus Technical Disposition Reference 

LR57D11030741, Issue B, dated September 

22, 2011. 

(5) Airbus Technical Disposition Reference 

LR57D11029170, Issue C, dated September 6, 

2011. 

(6) Airbus Technical Disposition Reference 

LR57D11023714, Issue B, dated July 12, 

2011. 


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Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / Proposed Rules 67351 

1 44 FR 66466 (Nov. 19, 1979) (Rule’s initial 

promulgation). 

2 42 U.S.C. 6294. EPCA also requires DOE to 

develop test procedures that measure how much 

energy appliances use, and to determine the 

representative average cost a consumer pays for 

different types of energy. 

3 16 CFR 305.10. 

4See 77 FR 15298 (Mar. 15, 2012); and 79 FR 

34642 (June 18, 2014). 

(7) Airbus Technical Disposition Reference 

LR57D11029172, Issue B, dated September 6, 

2011. 

(8) Airbus Technical Disposition Reference 

LR57D11030740, Issue C, dated September 

22, 2011. 

(9) Airbus Service Bulletin A340–57–4124, 

dated April 4, 2013. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0149, dated 

June 13, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–4808. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on October 

21, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–27725 Filed 10–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

FEDERAL TRADE COMMISSION 

16 CFR Part 305 

RIN 3084–AB15 

Energy Labeling 

AGENCY: Federal Trade Commission 

(‘‘FTC’’ or ‘‘Commission’’). 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Commission proposes 

amendments to the Energy Labeling 

Rule to create requirements related to a 

new label database on the Department of 

Energy’s (DOE’s) Web site, redesign 

ceiling fan labels, improve and update 

the comparability ranges for refrigerator 

labels, revise central air conditioner 

labels in response to new DOE 

enforcement requirements, improve 

water heater labels, and update current 

plumbing disclosures. 

DATES: Written comments must be 

received on or before January 11, 2016. 

ADDRESSES: Interested parties may file a 

comment online or on paper, by 

following the instructions in the 

Request for Comment part of the 

SUPPLEMENTARY INFORMATION section 

below. Write ‘‘Energy Labeling 

Amendments (16 CFR part 305) (Project 

No. R611004)’’ on your comment, and 

file your comment online at https://

ftcpublic.commentworks.com/ftc/

energylabeling, by following the 

instructions on the web-based form. If 

you prefer to file your comment on 

paper, mail your comment to the 

following address: Federal Trade 

Commission, Office of the Secretary, 

600 Pennsylvania Avenue NW., Suite 

CC–5610 (Annex E), Washington, DC 

20580, or deliver your comment to the 

following address: Federal Trade 

Commission, Office of the Secretary, 

Constitution Center, 400 7th Street SW., 

5th Floor, Suite 5610 (Annex E), 

Washington, DC 20024. 

FOR FURTHER INFORMATION CONTACT: 

Hampton Newsome, Attorney, (202) 

326–2889, Division of Enforcement, 

Bureau of Consumer Protection, Federal 

Trade Commission, 600 Pennsylvania 

Avenue NW., Washington, DC 20580. 

SUPPLEMENTARY INFORMATION: 

I. Background 

The Commission issued the Energy 

Labeling Rule (‘‘Rule’’) in 1979,1

pursuant to the Energy Policy and 

Conservation Act of 1975 (EPCA).2 The 

Rule requires energy labeling for major 

home appliances and other consumer 

products to help consumers compare 

competing models. It also contains 

labeling requirement for refrigerators, 

refrigerator-freezers, freezers, 

dishwashers, water heaters, clothes 

washers, room air conditioners, 

furnaces, central air conditioners, heat 

pumps, plumbing products, lighting 

products, ceiling fans, and televisions. 

The Rule requires manufacturers to 

attach yellow EnergyGuide labels for 

many of the covered products and 

prohibits retailers from removing the 

labels or rendering them illegible. In 

addition, it directs sellers, including 

retailers, to post label information on 

Web sites and in paper catalogs from 

which consumers can order products. 

EnergyGuide labels for most covered 

products contain three key disclosures: 

estimated annual energy cost; a 

product’s energy consumption or energy 

efficiency rating as determined from 

Department of Energy (DOE) test 

procedures; and a comparability range 

displaying the highest and lowest 

energy costs or efficiency ratings for all 

similar models. For energy cost 

calculations, the Rule specifies national 

average costs for applicable energy 

sources (e.g., electricity, natural gas, oil) 

as calculated by DOE. Under the Rule, 

the Commission periodically updates 

comparability range and annual energy 

cost information based on manufacturer 

data submitted pursuant to the Rule’s 

reporting requirements.3

II. Proposed Amendments to the Energy 

Labeling Rule 

This Notice seeks comment on several 

proposed changes to the Energy 

Labeling Rule, including requirements 

related to a new label database on DOE’s 

Web site, revised ceiling fan labels, new 

refrigerator comparability range 

information, portable air conditioner 

labeling, labeling for dual-mode 

refrigerators, revised central air 

conditioner labels in response to 

proposed changes to DOE’s enforcement 

rules, water heater labels, and plumbing 

disclosures. The Commission sought 

comment on a few of these issues during 

its regulatory review of the Energy 

Labeling Rule.4 Other issues discussed 

in this Notice reflect recent 

developments from DOE rulemakings 

and the consumer product marketplace. 

A. Online Label Database 

Background: In a June 18, 2014 

Supplemental Notice of Proposed 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS