[Federal Register Volume 78, Number 87 (Monday, May 6, 2013)]
[Notices]
[Pages 26423-26424]
[FR Doc No: 2013-10684]

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DEPARTMENT OF TRANSPORTATION

Federal Railroad Administration

[Docket No. FRA-2000-7257: Notice No. 74]

Railroad Safety Advisory Committee; Notice of Meeting

AGENCY: Federal Railroad Administration (FRA), Department of
Transportation (DOT).

ACTION: Announcement of Railroad Safety Advisory Committee (RSAC)
Meeting.

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SUMMARY: FRA announces the forty-eighth meeting of the RSAC, a Federal
Advisory Committee that develops railroad safety regulations through a
consensus process. The RSAC meeting topics will include opening remarks
from the FRA Administrator. Status reports will be provided by the
Fatigue Management, Rail Failure, and Risk Reduction Working Groups.
Status reports will also be provided by the Engineering and System
Safety Task Forces. This agenda is subject to change, including the
possible addition of further proposed tasks under the Rail Safety
Improvement Act of 2008.

DATES: The RSAC meeting is scheduled to commence at 9:30 a.m. on
Friday, June 14, 2013, and will adjourn by 4:30 p.m.

ADDRESSES: The RSAC meeting will be held at the National Housing
Center, located at 1201 15th Street NW., Washington, DC 20005. The
meeting is open to the public on a first-come, first-served basis, and
is accessible to individuals with disabilities. Sign and oral
interpretation can be made available if requested 10 calendar days
before the meeting.

FOR FURTHER INFORMATION CONTACT: Mr. Larry Woolverton, RSAC
Administrative Officer/Coordinator, FRA, 1200 New Jersey Avenue SE.,
Mailstop 25, Washington, DC 20590,<PHONE_NUMBER>; or Mr. Robert Lauby,
Deputy Associate Administrator for Regulatory and Legislative
Operations, FRA, 1200 New Jersey Avenue SE., Mailstop 25, Washington,
DC 20590,<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: Pursuant to Section 10(a)(2) of the Federal
    Advisory Committee Act (Pub. L. 92-463), FRA is giving notice of a
meeting of the RSAC. The RSAC was established to provide advice and
recommendations to FRA on railroad safety matters. The RSAC is composed
of 54 voting representatives from 32 member organizations, representing
various rail industry perspectives. In addition, there are non-voting
advisory representatives from the agencies with railroad safety
regulatory responsibility in Canada and Mexico, the National
Transportation Safety Board, and the Federal Transit Administration.
The diversity of the Committee ensures the requisite range of views and
expertise necessary to discharge its responsibilities. See the RSAC Web
site for details on prior RSAC activities and pending tasks at: http://rsac.fra.dot.gov/. Please refer to the notice published in the Federal

Register on March 11, 1996 (61 FR 9740), for additional information
about the RSAC.

    Issued in Washington, DC.
Robert C. Lauby,
Deputy Associate Administrator for Regulatory and Legislative
Operations.
[FR Doc. 2013-10684 Filed 5-3-13; 8:45 am]
BILLING CODE 4910-06-P


[Federal Register: October 20, 2010 (Volume 75, Number 202)]
[Notices]
[Page 64752]
[DOCID:fr20oc10-100]

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SECURITIES AND EXCHANGE COMMISSION

Submission for OMB Review; Comment Request

Upon Written Request, Copies Available From: Securities and Exchange
Commission, Office of Investor Education and Advocacy, Washington, DC
20549-0213.

Extension:
    Form N-CSR, SEC File No. 270-512, OMB Control No. 3235-0570.

    Notice is hereby given that, pursuant to the Paperwork Reduction
Act of 1995 (44 U.S.C. 3501 et seq.), the Securities and Exchange
Commission (the ``Commission'') has submitted to the Office of
Management and Budget (``OMB'') a request for extension of the
previously approved collection of information discussed below.
    Form N-CSR (17 CFR 249.331 and 274.128) is a combined reporting
form used by management investment companies to file certified
shareholder reports under the Investment Company Act of 1940 (15 U.S.C.
80a-1 et seq.) (``Investment Company Act'') and under the Securities
Exchange Act of 1934 (15 U.S.C. 78a et seq.) (``Exchange Act''). Form
N-CSR is to be used for reports under Section 30(b)(2) of the
Investment Company Act and Section 13(a) or 15(d) of the Exchange Act,
filed pursuant to rule 30b2-1(a) under the Investment Company Act (17
CFR 270.30b2-1(a)). Reports on Form N-CSR are to be filed with the
Commission not later than 10 days after the transmission to
stockholders of any report that is required to be transmitted to
stockholders under rule 30e-1 under the Investment Company Act (17 CFR
270.30e-1).
    The Commission estimates that there are 6,640 reports filed on Form
N-CSR annually and that the average number of portfolios referenced in
each filing is 3.75. The Commission further estimates that the hour
burden for preparing and filing a report on Form N-CSR is 7.62 hours
per portfolio. Given that filings on Form N-CSR are filed semi-
annually, filings on Form N-CSR require 15.24 hours per portfolio each
year. The total annual hour burden for Form N-CSR, therefore, is
estimated to be 154,686 hours.
    The current total annual cost burden to respondents for outside
professionals associated with the collection of data relating to Form
N-CSR is currently $1,119,001 and the new total annual cost burden to
respondents is estimated to be $1,556,401, representing an increase of
$437,400.
    The information collection requirements imposed by Form N-CSR are
mandatory. Responses to the collection of information will not be kept
confidential. An agency may not conduct or sponsor, and a person is not
required to respond to a collection of information unless it displays a
currently valid control number.
    Please direct general comments regarding the above information to
the following persons: (i) Desk Officer for the Securities and Exchange
Commission, Office of Management and Budget, Room 10102, New Executive
Office Building, Washington, DC 20503 or send an e-mail to: Shagufta
Ahmed at<EMAIL_ADDRESS>and (ii) Jeffrey Heslop, Acting
Director/CIO, Securities and Exchange Commission, C/O Remi Pavlik-
Simon, 6432 General Green Way, Alexandria, VA 22312, or send an e-mail
to<EMAIL_ADDRESS>Comments must be submitted to OMB within 30
days of this notice.

    Dated: October 13, 2010.
Florence E. Harmon,
Deputy Secretary.
[FR Doc. 2010-26343 Filed 10-19-10; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 80, Number 127 (Thursday, July 2, 2015)]
[Proposed Rules]
[Pages 38036-38038]
[FR Doc No: 2015-16165]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1991; Directorate Identifier 2014-NM-251-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, and -
115 airplanes; Model A320-214 airplanes; and Model A321-111, -112, -
211, -212, and -213 airplanes. This proposed AD was prompted by reports
of cracked cadmium-plated lock nuts that attach the hinge to the fan
cowl door. This proposed AD would require inspecting to determine the
serial number of each engine fan cowl door, inspecting for cracking of
the hinge lock nuts of any affected door, and replacing the lock nuts
if necessary. We are proposing this AD to detect and correct cracking
of the hinge lock nuts, which could result in separation of the hinge
from the fan cowl door, in-flight loss of the door, and consequent
damage to the airplane.

DATES: We must receive comments on this proposed AD by August 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:<PHONE_NUMBER>.
     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 the
following:
    For Airbus service information contact Airbus, Airworthiness
Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email:
<EMAIL_ADDRESS>Internet http://www.airbus.com.
    For Goodrich service information contact Goodrich Aerostructures,
850 Lagoon Drive, Chula Vista, California, 91910-2098; telephone: 619-
691-2719; email<EMAIL_ADDRESS>Internet: http://www.goodrich.com/TechPubs.
    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-
1991; 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<PHONE_NUMBER>) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone:<PHONE_NUMBER>;
fax:<PHONE_NUMBER>.

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-2015-1991;
Directorate Identifier 2014-NM-251-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 2014-0276, dated December 19, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318-111 and -112 airplanes; Model A319-111, -112, and -115 airplanes;
Model A320-214 airplanes; and Model A321-111, -112, -211, -212, and -
213 airplanes. The MCAI states:

    In-service findings have been reported of cracked cadmium plated
lock nuts. This cracking occurs shortly after installation.
Investigation results attribute the cause to an improper
manufacturing procedure of the nuts. It was determined that the
affected batch of lock nuts was used on the fan cowl to attach
hinges to the cowl doors on CFM56-5B engines only.
    This condition, if not corrected, could lead to separation of
the hinge from the fan cowl door, possibly resulting in in-flight
loss of a fan cowl door, with consequent damage to the aeroplane
and/or injury to persons on the ground.
    For the reasons describes above, this [EASA] AD required
identification of the affected fan cowl doors, a one-time inspection
of the fan cowl door hinge nuts and, depending on findings,
replacement of the affected nuts.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1991.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1062, including Appendix
01, dated July 28, 2014. Goodrich Aerostructures has issued Service
Bulletin RA32071-151, dated June 11, 2014. The service information
describes procedures for inspection of the hinge nuts of the fan cowl
door, and replacement if necessary. 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 437 airplanes of U.S.
registry.
    We also estimate that it would take about 2 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 $74,290, or $170 per product.
    We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.

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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

Airbus: Docket No. FAA-2015-1991; Directorate Identifier 2014-NM-
251-AD.

(a) Comments Due Date

    We must receive comments by August 17, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, and -115 airplanes.
    (3) Airbus Model A320-214 airplanes.
    (4) Airbus Model A321-111, -112, -211, 212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports of cracked cadmium-plated lock
nuts that attach the hinge to the fan cowl door. We are issuing this
AD to detect and correct cracking of the hinge lock nuts, which
could result in separation of the hinge from the fan cowl door, the
in-flight loss of the door, and consequent damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Inspect To Determine Serial Number

    Within 24 months after the effective date of this AD: Inspect to
determine if any fan cowl door has a serial number 10029001 through
11092003 inclusive, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28,
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated
June 11, 2014. A review of airplane maintenance records is
acceptable in lieu of the inspection required by this paragraph,
provided those records can be relied upon for that purpose and the
serial number can be positively identified by that review.

(h) Inspection and Replacement

    For any fan cowl door having any serial number identified in
paragraph (g) of this AD: Within 24 months after the effective date
of this AD, do a detailed inspection for cracking of the hinge lock
nuts of the door, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-71-1062, dated July 28, 2014; or
Goodrich Aerostructures Service Bulletin RA32071-151, dated June 11,
2014. If any crack is found, before further flight, replace each
cracked hinge lock nut, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28,
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated
June 11, 2014.

(i) Special Flight Permits

    Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.

(j) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>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 European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must include the DOA-authorized
signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0276, dated December 19,
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-2015-1991.
    (2) For Airbus service information contact Airbus, Airworthiness
Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email:
<EMAIL_ADDRESS>Internet http://www.airbus.com.
    (3) For Goodrich service information contact Goodrich
Aerostructures, 850 Lagoon Drive, Chula Vista, California, 91910-
2098; telephone:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
Internet: http://www.goodrich.com/TechPubs.
    (4) 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<PHONE_NUMBER>.

    Issued in Renton, Washington, on June 24, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-16165 Filed 7-1-15; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 80, Number 121 (Wednesday, June 24, 2015)]
[Notices]
[Pages 36328-36329]
[FR Doc No: 2015-15491]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CD15-18-000]

Soldier Canyon Filter Plant; Notice of Preliminary Determination
of a Qualifying Conduit Hydropower Facility and Soliciting Comments and
Motions To Intervene

    On January 23, 2015, Soldier Canyon Filter Plant filed a notice of
intent to construct a qualifying conduit hydropower facility, pursuant
to section 30 of the Federal Power Act (FPA), as amended by section 4
of the Hydropower Regulatory Efficiency Act of 2013 (HREA). The
proposed Soldier Canyon Micro Hydro Facility would have an installed
capacity of 100 kilowatts (kW), and would be located along the existing
36-inch-diameter Soldier Canyon Pipeline at the Soldier Canyon Filter
Plant. The project would be located near Fort Collins in Larimer
County, Colorado.
    Applicant Contact: Mr. Chris Harris, General Manager, 4424 Laporte
Avenue, Fort Collins, CO 80521, Phone No.<PHONE_NUMBER>.
    FERC Contact: Christopher Chaney, Phone No.<PHONE_NUMBER>, email:
<EMAIL_ADDRESS>    Qualifying Conduit Hydropower Facility Description: The proposed
project would consist of: (1) A proposed 140-square-foot buried
powerhouse; (2) an approximately 30-foot-long, 16-inch-diameter intake
pipe branching off the 36-inch-diameter Soldier Canyon Pipeline; (3)
one 100-kilowatt turbine-generating unit; (4) an approximately 60-foot-
long, 16-inch-diameter discharge pipe returning water to the 36-inch-
diameter Soldier Canyon Pipeline; and (5) appurtenant facilities. The
proposed project would have an estimated annual generating capacity of
880 megawatt-hours.
    A qualifying conduit hydropower facility is one that is determined
or deemed to meet all of the criteria shown in the table below.

      Table 1--Criteria for Qualifying Conduit Hydropower Facility
------------------------------------------------------------------------
                                                              Satisfies
       Statutory provision               Description            (Y/N)
------------------------------------------------------------------------
FPA 30(a)(3)(A), as amended by    The conduit the facility            Y
 HREA.                             uses is a tunnel,
                                   canal, pipeline,
                                   aqueduct, flume, ditch,
                                   or similar manmade
                                   water conveyance that
                                   is operated for the
                                   distribution of water
                                   for agricultural,
                                   municipal, or
                                   industrial consumption
                                   and not primarily for
                                   the generation of
                                   electricity..
FPA 30(a)(3)(C)(i), as amended    The facility is                     Y
 by HREA.                          constructed, operated,
                                   or maintained for the
                                   generation of electric
                                   power and uses for such
                                   generation only the
                                   hydroelectric potential
                                   of a non-federally
                                   owned conduit..
FPA 30(a)(3)(C)(ii), as amended   The facility has an                 Y
 by HREA.                          installed capacity that
                                   does not exceed 5
                                   megawatts..
FPA 30(a)(3)(C)(iii), as amended  On or before August 9,              Y
 by HREA.                          2013, the facility is
                                   not licensed, or
                                   exempted from the
                                   licensing requirements
                                   of Part I of the FPA..
------------------------------------------------------------------------

    Preliminary Determination: Based upon the above criteria,
Commission staff preliminarily determines that the proposal satisfies
the requirements for a qualifying conduit hydropower facility, which is
not required to be licensed or exempted from licensing.
    Comments and Motions to Intervene: Deadline for filing comments
contesting whether the facility meets the qualifying criteria is 45
days from the issuance date of this notice.
    Deadline for filing motions to intervene is 30 days from the
issuance date of this notice.
    Anyone may submit comments or a motion to intervene in accordance
with the requirements of Rules of Practice and Procedure, 18 CFR
385.210 and 385.214. Any motions to intervene must be received on or
before the specified deadline date for the particular proceeding.
    Filing and Service of Responsive Documents: All filings must (1)
bear in all capital letters the ``COMMENTS CONTESTING QUALIFICATION FOR
A CONDUIT HYDROPOWER FACILITY'' or ``MOTION TO INTERVENE,'' as
applicable; (2) state in the heading the name of the applicant and the
project number of the application to which the filing responds; (3)
state the name, address, and telephone number of the person filing; and
(4) otherwise comply with the requirements of sections 385.2001 through
385.2005 of the Commission's regulations.\1\ All comments contesting
Commission staff's preliminary determination that the facility meets
the qualifying criteria must set forth their evidentiary basis.
---------------------------------------------------------------------------

    \1\ 18 CFR 385.2001-2005 (2014).
---------------------------------------------------------------------------

    The Commission strongly encourages electronic filing. Please file
motions to intervene and comments using the Commission's eFiling system
at http://www.ferc.gov/docs-filing/efiling.asp. Commenters can submit
brief comments up to 6,000 characters, without prior registration,
using the eComment system at http://www.ferc.gov/docs-filing/ecomment.asp. You must include your name and contact information at the
end of your comments. For assistance, please contact FERC Online
Support at<EMAIL_ADDRESS>(866) 208-3676 (toll free), or
(202) 502-8659 (TTY). In lieu of electronic filing, please send a paper
copy to: Secretary, Federal Energy Regulatory Commission, 888 First
Street NE., Washington, DC 20426. A copy of all other filings in
reference to this application must be accompanied by proof of service
on all persons listed in the service list prepared by the Commission in
this proceeding, in accordance with 18 CFR 4.34(b) and 385.2010.
    Locations of Notice of Intent: Copies of the notice of intent can
be obtained directly from the applicant or such copies can be viewed
and reproduced at the Commission in its Public Reference Room, Room 2A,
888 First Street NE., Washington, DC 20426. The filing may also be
viewed on the web at http://www.ferc.gov/docs-filing/elibrary.asp using
the ``eLibrary'' link. Enter the docket number (e.g., CD15-18) in the
docket number field to access the document. For assistance, call toll-
free 1-866-208-3676 or email<EMAIL_ADDRESS>For TTY, call
(202) 502-8659.

    Dated: June 18, 2015.
Kimberly D. Bose,
Secretary.
[FR Doc. 2015-15491 Filed 6-23-15; 8:45 am]
 BILLING CODE 6717-01-P


[Federal Register Volume 83, Number 88 (Monday, May 7, 2018)]
[Rules and Regulations]
[Pages 19925-19928]
[FR Doc No: 2018-09280]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD; Amendment
39-19266; AD 2018-09-09]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A318 series airplanes and Model A319 series airplanes; all
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and
all Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the holes of the upper cleat to upper
stringer attachments at certain areas of the left- and right-hand wings
are subject to widespread fatigue damage (WFD). This AD requires
modifying the holes of the upper cleat to upper stringer attachments at
certain areas of the left- and right-hand wings. We are issuing this AD
to address the unsafe condition on these products.

DATES: This AD is effective June 11, 2018.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 11,
2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email: [email protected];
internet: http://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>. It is also available on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2017-1245.

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-
1245; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A318
series airplanes and Model A319 series airplanes; all Model A320-211, -
212, -214, -216, -231, -232, and -233 airplanes; and all Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM
published in the Federal Register on January 12, 2018 (83 FR 1579)
(``the NPRM''). The NPRM was prompted by an evaluation by the DAH
indicating that the holes of the upper cleat to upper stringer
attachments at certain areas of the left- and right-hand wings are
subject to WFD. The NPRM proposed to require modifying the holes of the
upper cleat to upper stringer attachments at certain areas of the left-
and right-hand wings. We are issuing this AD to prevent fatigue
cracking in the stringer attachment holes of the wings, which could
result in reduced structural integrity of the wings.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0117, dated July 7, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Airbus Model A318 series airplanes and
Model A319 series

airplanes; all Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes; and all Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes. The MCAI states:

    Within the scope of work of service life extension for A320
aeroplanes and of widespread fatigue damage evaluations, it has been
determined that a structural modification is required to allow the
aeroplanes to continue operation up to the limit of validity (LoV).
    This condition, if not corrected, may affect the structural
integrity of the wing.
    To address this potential unsafe condition, Airbus issued
[service bulletin] SB A320-57-1208, providing instructions to
oversize the holes of the upper cleat to upper stringer attachments
at Rib 2 to Rib 7 (inclusive).
    For the reason described above, this [EASA] AD requires
modification of the affected holes.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1245.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. United Airlines agreed with the
intent of the NPRM.

Request To Clarify Applicability

    Allegiant Air asked that we clarify the manufacturer serial numbers
(MSNs) identified in the applicability section of the proposed AD.
Allegiant Air stated that the effectivity specified in Airbus Service
Bulletin A320-57-1208, dated November 21, 2016, identifies airplanes up
to and including MSN 7493, and asked about airplanes having MSNs higher
than 7493. Allegiant Air noted that it has 11 Model A320 airplanes with
MSNs outside those listed in Airbus Service Bulletin A320-57-1208,
dated November 21, 2016. Allegiant Air added that it understands the AD
takes precedence over the service information, but there are several
configurations listed therein. Allegiant Air also added that since the
MSNs in question are not listed in the effectivity of the service
information, an operator with an MSN outside the effectivity will not
know which modification kit to order.
    We agree to clarify. The effectivity in Airbus Service Bulletin
A320-57-1208, dated November 21, 2016, does not include all MSNs for
Model A320 airplanes, and the applicability specified in paragraph (c)
of this AD includes all MSNs for Model A320 airplanes, except for
airplanes having certain modifications. We acknowledge that the
referenced service information may not be adequate for certain airplane
configurations. Therefore, we have revised paragraph (g) of this AD to
provide an option for doing the modification, including identification
of the appropriate modification kit, using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA Design Organization Approval (DOA).
    In addition, Airbus has informed us that Revision 1 of the
referenced service information will expand the effectivity to include
MSNs up to 8555. Airbus has also informed us that, upon request, it
will issue a technical adaptation as an interim method of compliance
until a revised service bulletin is issued.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-57-1208, dated
November 21, 2016. This service information describes procedures for
modifying the stringer attachments at rib 2 through rib 7 of the left-
and right-hand wings. The modification includes oversizing the holes,
doing an eddy current inspection of the affected holes for damage, and
repair. 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.

Costs of Compliance

    We estimate that this AD affects 1,136 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification (by oversizing and      125 work-hours x $85 per            $26,260         $36,885     $41,901,360
 doing eddy current inspection).      hour = $10,625.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.

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.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.

Regulatory Findings

    We determined that 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. 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.

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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

2018-09-09 Airbus: Amendment 39-19266; Docket No. FAA-2017-1245;
Product Identifier 2017-NM-099-AD.

(a) Effective Date

    This AD is effective June 11, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers, except airplanes specified in
paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A318 series airplanes on which Airbus Modification
(Mod) 39195 has been embodied in production or Airbus Service
Bulletin A320-00-1219 has been embodied in service.
    (2) Model A319 series airplanes on which Airbus Mod 28238, Mod
28162, and Mod 28342 have been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by an evaluation by the design approval
holder indicating that the holes of the upper cleat to upper
stringer attachments at rib 2 through rib 7 of the left- and right-
hand wings are subject to widespread fatigue damage. We are issuing
this AD to prevent fatigue cracking in the stringer attachment holes
of the wings, which could result in reduced structural integrity of
the wings.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Modification

    Before reaching the upper limit, but not before reaching the
lower limit, as defined in table 1 to paragraph (g) of this AD, as
applicable: Modify the holes of the upper cleat to upper stringer
attachments at rib 2 through rib 7 inclusive, on the left- and
right-hand wings by oversizing the holes, doing eddy current
inspections of the holes for damage, and repairing any damage found
before further flight, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1208, dated November
21, 2016, except as required by paragraph (h) of this AD; or using a
method approved by the Manager, International Section, Transport
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
[GRAPHIC] [TIFF OMITTED] TR07MY18.026

(h) Service Information Exception

    Where Airbus Service Bulletin A320-57-1208, dated November 21,
2016, specifies to contact Airbus for appropriate action, and
specifies that action as ``RC'' (Required for Compliance): Before
further flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (i)(2) of this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (j)(2) of this AD. Information
may be emailed to [email protected]. 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.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (h) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0117, dated July 7, 2017, 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-2017-1245.
    (2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>.

(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) Airbus Service Bulletin A320-57-1208, dated November 21,
2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33
5 61 93 44 51; email: [email protected]; internet:
http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on April 20, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-09280 Filed 5-4-18; 8:45 am]
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[Federal Register Volume 76, Number 105 (Wednesday, June 1, 2011)]
[Notices]
[Page 31604]
[FR Doc No: 2011-13464]

-----------------------------------------------------------------------

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. ER11-3620-000]

Lyonsdale Biomass LLC; Supplemental Notice That Initial Market-
Based Rate Filing Includes Request for Blanket Section 204
Authorization

    This is a supplemental notice in the above-referenced proceeding of
Lyonsdale Biomass LLC's application for market-based rate authority,
with an accompanying rate tariff, noting that such application includes
a request for blanket authorization, under 18 CFR part 34, of future
issuances of securities and assumptions of liability.
    Any person desiring to intervene or to protest should file with the
Federal Energy Regulatory Commission, 888 First Street, NE.,
Washington, DC 20426, in accordance with Rules 211 and 214 of the
Commission's Rules of Practice and Procedure (18 CFR 385.211 and
385.214). Anyone filing a motion to intervene or protest must serve a
copy of that document on the Applicant.
    Notice is hereby given that the deadline for filing protests with
regard to the applicant's request for blanket authorization, under 18
CFR part 34, of future issuances of securities and assumptions of
liability, is June 13, 2011.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://www.ferc.gov. To facilitate electronic service, persons with Internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically should submit an original and
14 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426.
    The filings in the above-referenced proceeding are accessible in
the Commission's eLibrary system by clicking on the appropriate link in
the above list. They are also available for review in the Commission's
Public Reference Room in Washington, DC. 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(s). For assistance with
any FERC Online service, please e-mail<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.

    Dated: May 24, 2011.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2011-13464 Filed 5-31-11; 8:45 am]
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