25630 Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1266; Directorate 

Identifier 2014–NM–151–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–300, 747SR, and 747SP series 

airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that certain fuselage skin lap 

joints are subject to widespread fatigue 

damage (WFD). This proposed AD 

would require repetitive postmodification inspections for cracking of 

the skin or internal doubler along the 

edge fastener rows of the modification, 

and repair if necessary. We are 

proposing this AD to detect and correct 

fatigue cracking in certain fuselage skin 

lap joints, which could result in rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 19, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA 2015– 

1266. 

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– 

1266; 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 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6428; fax: 425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–1266; Directorate Identifier 2014– 

NM–151–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as WFD. As an 

airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

This proposed AD was prompted by 

an evaluation by the DAH indicating 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 25631 

that certain fuselage skin lap joints are 

subject to WFD. We are proposing this 

AD to detect and correct fatigue 

cracking in certain fuselage skin lap 

joints, which could result in rapid 

depressurization of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014. This service 

information describes procedures for 

inspections for cracks in the skin and 

doublers along the edge fastener rows of 

modifications in the fuselage, and 

repairs. Refer to this service information 

for information on the procedures and 

compliance times. This service 

information is reasonably available at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

1266. Or see ADDRESSES for other ways 

to access this service information. 

Related Rulemaking 

AD 2010–10–05, Amendment 39– 

16284 (75 FR 27424, May 17, 2010) 

requires, among other things, 

modification of certain lap joints in 

fuselage sections 41 and 42. This 

proposed AD would require repetitive 

post-modification inspections for 

cracking of the skin or internal doubler 

along the edge fastener rows of the 

modification, and repair if necessary. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between this Proposed AD 

and the Service Information.’’ 

Difference Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014, 

specifies to contact the manufacturer for 

instructions on how to repair cracking, 

but this proposed AD would require 

repairing those conditions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 50 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 

Post-modification inspection 124 work-hours × $85 per 

hour = $10,540 per inspection cycle..

$0 $10,540 per inspection cycle $527,000 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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): 

The Boeing Company: Docket No. FAA– 

2014–1266; Directorate Identifier 2014– 

NM–151–AD. 

(a) Comments Due Date 

We must receive comments by June 19, 

2015. 

(b) Affected ADs 

None. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
25632 Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–300, 747SR, and 747SP series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that certain fuselage skin lap joints are 

subject to widespread fatigue damage (WFD). 

We are issuing this AD to detect and correct 

fatigue cracking in certain fuselage skin lap 

joints, which could result in rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Post-Modification Inspections 

for Airplane Groups 1 Through 3, 7, and 8 

For airplanes identified as Groups 1 

through 3, 7, and 8 in Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014: Except as provided by paragraph (m) 

of this AD, at the applicable time specified 

in table 3 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014, do 

internal detailed and surface high frequency 

eddy current (HFEC) inspections for cracks in 

the skin and internal doubler along the edge 

fastener rows of the modification; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

In unrepaired areas, repeat the internal 

detailed and surface HFEC inspections for 

cracks in the skin or internal doubler along 

the edge fastener rows of the modification 

thereafter at the applicable intervals specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(h) Initial Post-Modification Inspections for 

Airplane Groups 4 Through 6, and 9 

Through 11 

For airplanes identified as Groups 4 

through 6, and 9 through 11 in Boeing Alert 

Service Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014, with external doublers 

installed as specified in Boeing Service 

Bulletin 747–53–2272: Except as provided by 

paragraph (m) of this AD, at the applicable 

time specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, do external detailed, low frequency 

eddy current (LFEC), and HFEC inspections 

for cracks in the skin and external doubler, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

(i) Repetitive Post-Modification Inspections 

for Airplane Groups 4 Through 6, and 9 

through 11 

For airplanes with no crack findings during 

the inspections required by paragraph (h) of 

this AD: Do the applicable actions required 

by paragraphs (i)(1) and (i)(2) of this AD. 

(1) For airplanes with less than 15,000 

flight cycles since stringer 6 external 

doublers were installed as specified in 

Boeing Service Bulletin 747–53–2272: At the 

applicable intervals specified in table 4 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, in unrepaired 

areas, repeat the external detailed and LFEC 

inspections for cracks in the skin, and the 

external detailed and HFEC inspections for 

cracks in the external doubler, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(2) For airplanes with 15,000 or more flight 

cycles since the stringer 6 external doublers 

were installed as specified in Boeing Service 

Bulletin 747–53–2272: At the applicable 

intervals specified in table 4 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, in unrepaired areas, do external 

detailed and LFEC inspections for cracks in 

the skin; and do internal and external 

detailed and HFEC inspections for cracks in 

the skin and external doubler; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(j) Repetitive Post-Modification Inspections 

for Airplane Groups 4 Through 6, and 9 

Through 11 With External Doublers 

For airplanes identified as Groups 4 

through 6, and 9 through 11 in Boeing Alert 

Service Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014, with external doublers 

installed as specified in Boeing Alert Service 

Bulletin 747–53A2367: Except as provided 

by paragraph (m) of this AD, at the applicable 

time specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, do internal detailed and surface 

HFEC inspections for cracks in the skin and 

internal doubler along the edge fastener rows 

of the modification; and do internal detailed 

and surface HFEC inspections for cracks in 

the skin or internal doubler along the edge 

fastener rows of the modification; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

In unrepaired areas, repeat the internal 

detailed and surface HFEC inspections for 

cracks in the skin or internal doubler along 

the edge fastener rows of the modification 

thereafter at the applicable interval specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(k) Repetitive Post-Modification Inspections 

for Airplane Groups 12 and 13 

For airplanes identified as Groups 12 and 

13 in Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014: 

Except as provided by paragraph (m) of this 

AD, at the applicable time specified in table 

6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, do internal 

detailed and surface HFEC inspections for 

cracks in the skin and internal doubler along 

the edge fastener rows of the modification, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

In unrepaired areas, repeat the internal 

detailed and surface HFEC inspections for 

cracks in the skin or internal doubler along 

the edge fastener rows of the modification 

thereafter at the applicable interval specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(l) Corrective Actions 

If any cracking is found during any 

inspection required by this AD: Before 

further flight, repair the cracking using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(m) Exception to Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, Dated 

July 8, 2014 

Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, specifies a 

compliance time ‘‘after the Revision 5 date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 ACO, send it to the 

attention of the person identified in 

paragraph (o)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: nathan.p.weigand@faa.gov. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 86 / Tuesday, May 5, 2015 / Proposed Rules 25633 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on April 28, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10316 Filed 5–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 352 

[Docket No. AD12–6–001] 

Retrospective Analysis of Existing 

Rules 

AGENCY: Federal Energy Regulatory 

Commission, DOE. 

ACTION: Notice of staff memorandum. 

SUMMARY: In this document, the 

Commission is seeking public comment 

on whether the existing regulations 

concerning the Uniform Systems of 

Accounts prescribed for oil pipeline 

companies and hydropower prefiling 

requirements, and a requirement 

imposed in 2001 that Western public 

and non-public utilities offer available 

real-time electric energy capacity into 

the markets and post the availability on 

their Web sites and the WSPP Web site, 

warrant a formal public review. 

DATES: Comments are due by May 26, 

2015. 

ADDRESSES: Comments, identified by 

docket number, may be filed in the 

following ways: 

• Electronic Filing through http://

www.ferc.gov. Documents created 

electronically using word processing 

software should be filed in native 

applications or print-to-PDF format and 

not in a scanned format. 

• Mail/Hand Delivery: Those unable 

to file electronically may mail or handdeliver comments to: Federal Energy 

Regulatory Commission, Secretary of the 

Commission, 888 First Street NE., 

Washington, DC 20426. 

Instructions: For detailed instructions 

on submitting comments and additional 

information on the rulemaking process, 

see the Comment Procedures Section of 

this document. 

FOR FURTHER INFORMATION CONTACT: 

Christy Walsh, Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, 202–502–6523, 

Christy.Walsh@ferc.gov. 

SUPPLEMENTARY INFORMATION: Take 

notice that the Commission staff is 

issuing a memorandum seeking public 

comment on whether the existing 

regulations concerning the Uniform 

Systems of Accounts prescribed for oil 

pipeline companies and hydropower 

prefiling requirements, and a 

requirement imposed in 2001 that 

Western public and non-public utilities 

offer available real-time electric energy 

capacity into the markets and post the 

availability on their Web sites and the 

WSPP Web site, warrant a formal public 

review. The memorandum is being 

issued pursuant to the November 8, 

2011 Plan for Retrospective Analysis of 

Existing Rules prepared in response to 

Executive Order 13579, which requested 

independent regulatory agencies issue 

plans for periodic retrospective analysis 

of their existing regulations. 

The Staff Memorandum is being 

placed in the record in the abovereferenced administrative docket. The 

Staff Memorandum will also be 

available on the Commission’s Web site 

at http://www.ferc.gov. 

Comments on the Staff Memorandum 

should be filed within 30 days of the 

issuance of this document. The 

Commission encourages electronic 

submission of comments in lieu of 

paper using the ‘‘eFiling’’ link at http:// 

www.ferc.gov. Persons unable to file 

electronically should submit an original 

of the comment to the Federal Energy 

Regulatory Commission, 888 First Street 

NE., Washington, DC 20426. 

All filings in this docket are 

accessible on-line at http://

www.ferc.gov, using the ‘‘eLibrary’’ link. 

There is an ‘‘eSubscription’’ link on the 

Web site that enables subscribers to 

receive email notification when a 

document is added to a subscribed 

docket. For assistance with any FERC 

Online service, please email 

FERCOnlineSupport@ferc.gov, or call 

(866) 208–3676 (toll free). For TTY, call 

(202) 502–8659. 

Questions regarding this document 

should be directed to: Christy Walsh, 

Office of the General Counsel, Federal 

Energy Regulatory Commission, 888 

First Street NE., Washington, DC 20426, 

202–502–6523, Christy.Walsh@ferc.gov. 

Issued: April 23, 2015. 

Kimberly D. Bose, 

Secretary. 

[FR Doc. 2015–10310 Filed 5–4–15; 8:45 am] 

BILLING CODE 6717–01–P 

DEPARTMENT OF LABOR 

Employment and Training 

Administration 

20 CFR Part 655 

RIN 1205–AB70 

Temporary Agricultural Employment of 

H–2A Foreign Workers in the Herding 

or Production of Livestock on the 

Open Range in the United States; 

Extension of Comment Period 

AGENCY: Employment and Training 

Administration, Labor. 

ACTION: Proposed rule; extension of 

comment period. 

SUMMARY: The Department of Labor 

(Department) issued a proposed rule in 

the Federal Register of April 15, 2015 

[FR Doc. 2015–08505], concerning 

proposed amendments to its regulations 

governing certification of the 

employment of nonimmigrant workers 

in temporary or seasonal agricultural 

employment under the H–2A program 

to codify certain procedures for 

employers seeking to hire foreign 

temporary agricultural workers for job 

opportunities in sheepherding, goat 

herding and production of livestock on 

the open range. This notice extends the 

comment period for 15 days, from May 

15 to June 1, 2015. Multiple commenters 

requested additional time to develop 

their comments concerning the 

proposed rulemaking. The Department 

is therefore extending the comment 

period in order to give all interested 

persons the opportunity to comment 

fully. 

DATES: The comment period for the 

proposed rule published on April 15, 

2015 (80 FR 20300) is extended. 

Interested persons are invited to submit 

written comments on the proposed rule, 

identified by RIN 1205–AB70, on or 

before June 1, 2015 

ADDRESSES: You may submit comments, 

identified by Regulatory Information 

Number (RIN) 1205–AB70, by any one 

of the following methods: 

• Federal e-Rulemaking Portal 

www.regulations.gov. Follow the Web 

site instructions for submitting 

comments. 

• Mail or Hand Delivery/Courier: 

Please submit all written comments 

(including disk and CD–ROM 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS