[Federal Register Volume 82, Number 8 (Thursday, January 12, 2017)]
[Notices]
[Page 3766]
[FR Doc No: 2017-00564]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings #2

    Take notice that the Commission received the following electric
rate filings:

    Docket Numbers: ER10-2507-010.
    Applicants: Westar Energy, Inc.
    Description: Notice of Non-Material Change in Status of Westar
Energy, Inc.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5116.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER16-2190-003; ER16-2191-003; ER16-2453-004.
    Applicants: Brady Wind, LLC, Brady Wind II, LLC, Brady
Interconnection, LLC.
    Description: Notice of Non-material Change in Status of Brady Wind,
LLC, et. al.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5093.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-752-000.
    Applicants: PJM Interconnection, L.L.C.
    Description: Notice of Cancellation of First Revised Service
Agreement No. 2359, Queue No. U3-003 of PJM Interconnection, L.L.C.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5057.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-753-000.
    Applicants: PJM Interconnection, L.L.C.
    Description: Sec.  205(d) Rate Filing: Revisions to OATT Schedule
12--Appendix A re: RTEP Projects Approved in Dec 2016 to be effective
4/6/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5061.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-754-000.
    Applicants: Southern California Edison Company.
    Description: Sec.  205(d) Rate Filing: GIA and Distribution Service
Agmt Lendlease California City Solar LLC to be effective 1/7/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5067.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-755-000.
    Applicants: Midcontinent Independent System Operator, Inc.
    Description: Sec.  205(d) Rate Filing: 2017-01-06_MISO Tariff
Clean-up filing to be effective 1/7/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5078.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-756-000.
    Applicants: Midcontinent Independent System Operator, Inc.
    Description: Sec.  205(d) Rate Filing: 2017-01-06_SA 2884 Otter
Tail-Crowned Ridge 1st Rev GIA (G736) to be effective 1/7/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5085.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-756-000.
    Applicants: Midcontinent Independent System Operator, Inc.
    Description: Sec.  205(d) Rate Filing: 2017-01-06_SA 2884 Otter
Tail-Crowned Ridge 1st Rev GIA (G736) to be effective 1/7/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5086.
    Comments Due: 5 p.m. ET 1/27/17.

    Docket Numbers: ER17-757-000.
    Applicants: Duke Energy Carolinas, LLC.
    Description: Sec.  205(d) Rate Filing: Amendment to NCEMC NITSA SA
210 to be effective 1/1/2017.
    Filed Date: 1/6/17.
    Accession Number: 20170106-5147.
    Comments Due: 5 p.m. ET 1/27/17.

    The filings are accessible in the Commission's eLibrary system by
clicking on the links or querying the docket number.
    Any person desiring to intervene or protest in any of the above
proceedings must file in accordance with Rules 211 and 214 of the
Commission's Regulations (18 CFR 385.211 and 385.214) on or before 5:00
p.m. Eastern time on the specified comment date. Protests may be
considered, but intervention is necessary to become a party to the
proceeding.
    eFiling is encouraged. More detailed information relating to filing
requirements, interventions, protests, service, and qualifying
facilities filings can be found at: http://www.ferc.gov/docs-filing/efiling/filing-req.pdf. For other information, call<PHONE_NUMBER>
(toll free). For TTY, call<PHONE_NUMBER>.

    Dated: January 6, 2017.
Kimberly D. Bose,
Secretary.
[FR Doc. 2017-00564 Filed 1-11-17; 8:45 am]
 BILLING CODE 6717-01-P


[Federal Register Volume 77, Number 226 (Friday, November 23, 2012)]
[Notices]
[Page 70160]
[FR Doc No: 2012-28403]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Notice of Commission Staff Attendance

    The Federal Energy Regulatory Commission hereby gives notice that
members of the Commission's staff may attend the following meetings
related to the interregional transmission planning activities of the
Southwest Power Pool (SPP):

SPP Seams FERC Order 1000 Task Force Meeting--November 16, 2012

    The above-referenced meeting will be a teleconference.
    The above-referenced meeting is open to the public.
    Further information may be found at www.spp.org.
    The discussions at the meeting described above may address matters
at issue in the following proceedings:

Docket No. ER09-35-001, Tallgrass Transmission, LLC
Docket No. ER09-36-001, Prairie Wind Transmission, LLC
Docket No. ER09-548-001, ITC Great Plains, LLC
Docket No. ER09-659-002, Southwest Power Pool, Inc.
Docket No. ER11-4105-000, Southwest Power Pool, Inc.
Docket No. EL11-34-001, Midwest Independent Transmission System
Operator, Inc.
Docket No. ER12-1401-000, Southwest Power Pool, Inc.
Docket No. ER12-1402-000, Southwest Power Pool, Inc.
Docket No. ER12-1415-000, Southwest Power Pool, Inc.
Docket No. ER12-1460-000, Southwest Power Pool, Inc.
Docket No. ER12-1586-000 et al., Southwest Power Pool, Inc.
Docket No. ER12-1610-000, Southwest Power Pool, Inc.
Docket No. ER12-1772-000, Southwest Power Pool, Inc.
Docket No. ER12-2366-000, Southwest Power Pool, Inc.
Docket No. EL12-2-000, Southwest Power Pool, Inc.
Docket No. EL12-60-000, Southwest Power Pool, Inc., et al.
Docket No. ER12-2387-000 et al., Southwest Power Pool, Inc.

    For more information, contact Luciano Lima, Office of Energy
Markets Regulation, Federal Energy Regulatory Commission at (202) 288-
6738 or<EMAIL_ADDRESS>
    Dated: November 16, 2012.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2012-28403 Filed 11-21-12; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 75, Number 141 (Friday, July 23, 2010)]
[Proposed Rules]
[Pages 43105-43107]
[FR Doc No: 2010-18019]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0734; Directorate Identifier 2010-CE-036-AD]
RIN 2120-AA64

Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model
PIAGGIO P-180 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:

    Due to a manufacturing error, some rivets, required by drawings,
were not installed in the joints between two ceiling beams and the
rear pressurized bulkhead.
    If left uncorrected, long term fatigue stress could locally
weaken the structure, compromising the fuselage structural
integrity.

The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by September 7,
2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<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 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Sarjapur Nagarajan, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
e-mail<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0734;
Directorate Identifier 2010-CE-036-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

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No.: 2010-0126, dated June 23, 2010 (referred to after this as ``the
MCAI''), to correct an

unsafe condition for the specified products. The MCAI states:

    Due to a manufacturing error, some rivets, required by drawings,
were not installed in the joints between two ceiling beams and the
rear pressurized bulkhead.
    If left uncorrected, long term fatigue stress could locally
weaken the structure, compromising the fuselage structural
integrity.
    This AD requires the accomplishment of Piaggio Aero Industries
(PAI) Service Bulletin (SB) 80-0268 original issue, which contains
instructions to rework the affected area, thus restoring the
fuselage design strength as well as the fatigue specifications of
the structure.

You may obtain further information by examining the MCAI in the AD
docket.

Relevant Service Information

    Piaggio Aero Industries S.p.A. has issued Service Bulletin
(Mandatory) N.: 80-0268, REV. 0, dated December 18, 2008. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the 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 this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.

Differences Between This Proposed AD and the MCAI or Service
Information

    We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 6 products of U.S.
registry. We also estimate that it would take about 30 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 $100 per product.
    Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $15,900, or $2,650 per product.

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); and
    3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Piaggio Aero Industries S.p.A: Docket No. FAA-2010-0734; Directorate
Identifier 2010-CE-036-AD.

Comments Due Date

    (a) We must receive comments by September 7, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to PIAGGIO AERO INDUSTRIES S.p.A Model
PIAGGIO P-180 airplanes, serial numbers 1166 through 1175,
certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 53:
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:

    Due to a manufacturing error, some rivets, required by drawings,
were not installed in the joints between two ceiling beams and the
rear pressurized bulkhead.
    If left uncorrected, long term fatigue stress could locally
weaken the structure, compromising the fuselage structural
integrity.
    This AD requires the accomplishment of Piaggio Aero Industries
(PAI) Service Bulletin (SB) 80-0268 original issue, which contains
instructions to rework the affected area, thus restoring the
fuselage design strength as well as the fatigue specifications of
the structure.

Actions and Compliance

    (f) Unless already done, within 200 hours time-in-service (TIS)
after the effective date of this AD, replace the rivets of the joint
brackets on the right-hand and left-hand beam with ``Hi-Lok''
fasteners, following the accomplishment instructions of Piaggio Aero
Industries S.p.A. Service Bulletin (Mandatory) N.: 80-0268, REV. 0,
dated December 18, 2008.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:

    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Sarjapur Nagarajan, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; e-
mail<EMAIL_ADDRESS>Before using any approved AMOC on
any airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2010-0126, dated June 23, 2010; and Piaggio Aero Industries S.p.A.
Service Bulletin (Mandatory) N.: 80-0268, REV. 0, dated December 18,
2008, for related information.

    Issued in Kansas City, Missouri, on July 15, 2010.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010-18019 Filed 7-22-10; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 69 (Thursday, April 10, 2014)]
[Notices]
[Page 19960]
[FR Doc No: 2014-08116]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

Office of Commercial Space Transportation: Waypoint 2 Space
Safety Approval Performance Criteria

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice.

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SUMMARY: This is notification of criteria used to evaluate the Waypoint
2 Space, Inc. (W2S) safety approval application. The FAA issued W2S a
safety approval, subject to the provisions of Title 51 U.S.C Subtitle
V, ch. 509, and the orders, rules and regulations issued under it.
Pursuant to Title 14 Code of Federal Regulations (14 CFR) Sec.  414.35,
this Notice publishes the criteria that were used to evaluate the
safety approval application.

FOR FURTHER INFORMATION CONTACT: For questions about the performance
criteria, you may contact Randal Maday, Licensing and Evaluation
Division (AST-200), FAA Office of Commercial Space Transportation
(AST), 800 Independence Avenue SW., Room 331, Washington, DC 20591,
telephone<PHONE_NUMBER>; Email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:
    Background: W2S applied for, and received, a safety approval for
its ability to provide as a service that includes classroom training
in: Aerospace Physiology, Centrifuge, Altitude Chambers,
Weightlessness, Neutral Buoyancy, Aerobatic Flight, Spacecraft Systems,
Crew Resource Management, Pilot Procedures, Nominal and Off Nominal
Procedures, Emergency Procedures, Egress, Survival, Search and Rescue,
and Extra-Vehicular Activity. The training service includes Space
Flight Participant, Commercial Payload Specialist, and Spaceflight
Instructor Training Programs. In addition, the service includes
practical Sub-Orbital and Orbital Flight training in: Neutral Buoyancy
Environments, Parabolic Flight, Flight Simulators, Altitude Chambers,
Spin and Upset Recovery, and G-Force adaptation.
    W2S may offer its commercial space training service to a
prospective launch and reentry operator to meet the applicable crew and
space flight participant training requirements of 14 CFR 460.5 and 14
CFR 460.51.

Criteria Used To Evaluate Safety Approval Application

    The performance criteria for this safety approval include: Air
Education and Training Instruction 11-219 Initial Flight Screening, Air
Force Instruction (AFI) 11-401 Aerospace Physiological Training
Program, AFI 11-202V1 Aircrew Training, AFI11-202V2 Aircrew
Standardization/Evaluation Program, NASA/TP-2001-213726 A Review of
Training Methods and Instructional Techniques, AFI 11-2C-130V1 C-130
Aircrew Training, and AFI 11-301V1 Aircrew Flight Equipment (AFE)
Program. Furthermore, the performance criteria include 14 CFR 61.31(g)
for additional training required for operating pressurized aircraft
capable of operating at high altitudes. These United States Air Force,
NASA, and FAA criteria are acceptable technical criteria for reviewing
a safety approval application per 14 CFR 414.19. Many aspects of
aviation training also apply to aerospace operations because it
addresses human-vehicle interactions common to both aviation and
aerospace. Training for Extra Vehicular Activity (EVA) is also
applicable because it pertains to operations that include Intra
Vehicular Activity (IVA) in microgravity, which is performed during
ascent and entry.
    The Spaceflight Instructor Training Program serves to develop
instructors to better train space flight participants and crew. The
FAA's evaluation included assessment of W2S's commercial space training
service lesson plans and objectives, which include classroom,
simulator, and flight training for crew and space flight participants
to experience and demonstrate knowledge of the following through
testing:
     Understand operations, environments, and the physiological
effects associated with space flight.
     Understand and demonstrate crew resource management
operations.
     Demonstrate adaptation and the ability to conduct
applicable operations in spaceflight environments, which include flight
during high and low gravity phases.
     Demonstrate competence in operations requiring use of a
partial pressure suit.
     Demonstrate emergency egress procedures and proper use of
life support equipment without assistance.
     Understand and experience nominal and off nominal vehicle
conditions during flight.

    Issued in Washington, DC, on February 24, 2014.
 George C. Nield,
Associate Administrator for Commercial Space Transportation.
[FR Doc. 2014-08116 Filed 4-9-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 86, Number 14 (Monday, January 25, 2021)]
[Notices]
[Pages 6963-6964]
[FR Doc No: 2021-01522]

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DEPARTMENT OF TRANSPORTATION

Pipeline and Hazardous Materials Safety Administration

[Docket No. PHMSA-2020-0008]

Pipeline Safety: Request for Special Permit; El Paso Natural Gas
Company, L.L.C.

AGENCY: Pipeline and Hazardous Materials Safety Administration (PHMSA);
DOT.

ACTION: Notice.

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

SUMMARY: PHMSA is publishing this notice to solicit public comments on
a request for special permit received from the El Paso Natural Gas
Company, L.L.C. (EPNG). The special permit request is seeking relief
from compliance with certain requirements in the Federal pipeline
safety regulations. At the conclusion of the 30-day comment period,
PHMSA will review the comments received from this notice as part of its
evaluation to grant or deny the special permit request.

DATES: Submit any comments regarding this special permit request by
February 24, 2021.

ADDRESSES: Comments should reference the docket number for this
specific special permit request and may be submitted in the following
ways:
     E-Gov Website: http://www.Regulations.gov. This site
allows the public to enter comments on any Federal Register notice
issued by any agency.
     Fax: 1-202-493-2251.
     Mail: Docket Management System: 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: Docket Management System: U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590, between
9:00 a.m. and 5:00 p.m., Monday through Friday, except Federal
holidays.
    Instructions: You should identify the docket number for the special
permit request you are commenting on at the beginning of your comments.
If you submit your comments by mail, please submit two (2) copies. To
receive confirmation that PHMSA has received your comments, please
include a self-addressed stamped postcard. Internet users may submit
comments at http://www.Regulations.gov.

    Note:  There is a privacy statement published on http://www.Regulations.gov. Comments, including any personal information
provided, are posted without changes or edits to http://www.Regulations.gov.

    Confidential Business Information: Confidential Business
Information (CBI) is commercial or financial information that is both
customarily and actually treated as private by its owner. Under the
Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from
public disclosure. If your comments responsive to this notice contain
commercial or financial information that is customarily treated as
private, that you actually treat as private, and that is relevant or
responsive to this notice, it is important that you clearly designate
the submitted comments as CBI. Pursuant to 49 Code of Federal
Regulations (CFR) Sec.  190.343, you may ask PHMSA to give confidential
treatment to information you give to the agency by taking the following
steps: (1) Mark each page of the original document submission
containing CBI as ``Confidential''; (2) send PHMSA, along with the
original document, a second copy of the original document with the CBI
deleted; and (3) explain why the information you are submitting is CBI.
Unless you are notified otherwise, PHMSA will treat such marked
submissions as confidential under the FOIA, and they will not be placed
in the public docket of this notice. Submissions containing CBI should
be sent to Kay McIver, DOT, PHMSA-PHP-80, 1200 New Jersey Avenue SE,
Washington, DC 20590-0001. Any commentary PHMSA receives that is not

specifically designated as CBI will be placed in the public docket for
this matter.

FOR FURTHER INFORMATION CONTACT:
    General: Ms. Kay McIver by telephone at<PHONE_NUMBER>, or by email
at<EMAIL_ADDRESS>    Technical: Mr. Steve Nanney by telephone at<PHONE_NUMBER>, or by
email at<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: PHMSA received a special permit request from
EPNG seeking a waiver from the requirements of 49 CFR 192.611(a) and
(d): Change in class location: Confirmation or revision of maximum
allowable operating pressure, and Sec.  192.619(a): Maximum allowable
operating pressure: Steel or plastic pipelines. This special permit is
being requested in lieu of pipe replacement or pressure reduction for
one (1) special permit segment of 650 feet (0.123 miles) on the EPNG
pipeline system. The proposed special permit segment is located in Ward
County, Texas. The EPNG pipeline class location in the special permit
segment has changed from a Class 2 to a Class 3 location. The EPNG
pipeline special permit segment is a 30-inch diameter pipeline with an
existing maximum allowable operating pressure of 944 pounds per square
inch gauge. The installation of the special permit segment occurred in
2003.
    The special permit request, proposed special permit with
conditions, and Draft Environmental Assessment (DEA) for the EPNG
pipeline are available for review and public comment in Docket No.
PHMSA-2020-0008. We invite interested persons to review and submit
comments on the special permit request and DEA in the docket. Please
include any comments on potential safety and environmental impacts that
may result if the special permit is granted. Comments may include
relevant data.
    Before issuing a decision on the special permit request, PHMSA will
evaluate all comments received on or before the comment closing date.
Comments received after the closing date will be evaluated, if it is
possible to do so without incurring additional expense or delay. PHMSA
will consider each relevant comment it receives in making its decision
to grant or deny this special permit request.

    Issued in Washington, DC, under authority delegated in 49 CFR
1.97.
Alan K. Mayberry,
Associate Administrator for Pipeline Safety.
[FR Doc. 2021-01522 Filed 1-22-21; 8:45 am]
BILLING CODE 4910-60-P


P-20-0004 Sanitized Support Documents Index:
 P-20-0004 Sanitized Determination Document (linked)
 P-20-0004 Sanitized CHEM Report (attached)
 P-20-0004 Sanitized ECO Report (attached)
 P-20-0004 Sanitized ENG Report (attached)
 P-20-0004 Sanitized EXP Report (attached)
 P-20-0004 Sanitized Fate Report (attached)
 P-20-0004 Sanitized HLTH Report_POST-FOCUS FINAL (attached)


[Federal Register Volume 81, Number 54 (Monday, March 21, 2016)]
[Notices]
[Page 15098]
[FR Doc No: 2016-06253]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. EL16-39-000]

Tri-State Generation and Transmission Association, Inc.; Notice
of Supplement to Petition for Declaratory Order

    Take notice that on March 10, 2016, pursuant to Rule 207 of the
Federal Energy Regulatory Commission's (Commission) Rules of Practice
and Procedure, 18 CFR 385.207(a)(2) (2015), Tri-State Generation and
Transmission Association, Inc. (Petitioner) filed a supplement to its
petition for declaratory order filed on February 17, 2016, requesting
that the Commission find that its fixed cost recovery proposal
contained in the proposed revised Board Policy 101 is consistent with
the Public Utility Regulatory Policies Act of 1978 (PURPA) and the
Commission's regulations implementing PURPA, as more fully explained in
the petition.
    Any person desiring to intervene or to protest in this proceeding
must file in accordance with Rules 211 and 214 of the Commission's
Rules of Practice and Procedure (18 CFR 385.211 and 385.214) on or
before 5:00 p.m. Eastern time on the specified comment date. Protests
will be considered by the Commission in determining the appropriate
action to be taken, but will not serve to make protestants parties to
the proceeding. Any person wishing to become a party must file a notice
of intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date.
Anyone filing a motion to intervene or protest must serve a copy of
that document on the Petitioner.
    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
5 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First Street NE., Washington, DC 20426.
    The filings in the above 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 email<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.
    Comment Date: 5:00 p.m. Eastern time on March 25, 2016.

    Dated: March 15, 2016.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2016-06253 Filed 3-18-16; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70453-70458]
[FR Doc No: 2014-27361]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0062; Directorate Identifier 2012-NM-031-AD;
Amendment 39-18025; AD 2014-23-09]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2000-17-03 for
all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000-17-

03 required inspections of the nose landing gear (NLG) main fitting to
detect cracking of the NLG main fitting subassembly, and corrective
actions if necessary. This new AD retains the requirements of AD 2000-
17-03, requires installing a new part number NLG unit that terminates
the repetitive inspections, and adds airplanes to the applicability.
This AD was prompted by a report of an NLG main fitting failure. We are
issuing this AD to prevent cracking of the NLG main fitting, which
could lead to collapse of the NLG during takeoff and landing, and
possible injury to the flight crew and passengers.

DATES: This AD becomes effective December 31, 2014.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 31,
2014.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
October 3, 2000 (65 FR 52298, August 29, 2000).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0062; or in person at the
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.
    For service information identified in this AD, contact Fokker
Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; email<EMAIL_ADDRESS>Internet http://www.myfokkerfleet.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<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, 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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000). AD 2000-17-03 applied to all Fokker Services B.V.
Model F.28 Mark 0100 airplanes. The NPRM published in the Federal
Register on February 28, 2014 (79 FR 11351). The NPRM proposed to
continue to require a one-time visual inspection, and repetitive eddy
current and dye penetrant inspections of the NLG main fitting to detect
cracking of the NLG main fitting subassembly, and corrective actions if
necessary. The NPRM also proposed to require installing a new part
number NLG unit that would terminate the repetitive inspections, and
adding airplanes to the applicability.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0002R1, dated March 30, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on all Fokker Services
B.V. Model F.28 Mark 0100 airplanes. The MCAI states:

    In 1997, a report was received concerning a Fokker 100 (F28 Mark
0100) aeroplane, where during landing following nose wheel touch-
down, the nose landing gear (NLG) broke off just below the pintle
pins. Subsequent inspection by the affected operator of other
aeroplanes in the fleet identified three more suspect NLG main
fittings. Eddy current (EC) and/or dye penetrant inspections of
these units later confirmed that cracks were present on the inner
side of the downlock plunger support web. The total number of flight
cycles (FC) accumulated by the cracked NLG main fittings at the time
of detection were between 9,300 FC and 17,600 FC.
    This condition, if not detected and corrected, could result in
further incidents of NLG collapse, possibly resulting in damage to
the aeroplane and/or injury to the occupants. To address this
potential unsafe condition [Civil Aviation Authority --Netherlands]
CAA-NL issued [an] AD * * * to require repetitive inspections of the
NLG main fitting and, depending on findings, rework or replacement
of the NLG main fitting.
    Since [that Netherlands] AD * * * was issued, it was determined
that replacement of a Messier-Dowty (M-D, formerly Dowty Rotol) Part
Number (P/N) 201071001 or P/N 201071002 NLG with, respectively, a P/
N 201071003 or P/N 201071004 (which have a so-called `heavy weight'
main fitting installed) or, respectively, with a P/N 201456001 or P/
N 201461001 (which are so-called `heavy weight' NLG units) cancels
the need for repetitive inspection and/or rework. The `heavy weight'
main fitting was originally developed for an increased weight
version (101,000 lbs. maximum take-off weight) of the Fokker 100, as
well as for the Fokker 70 (F28 Mark 0070), and introduced on the
production line.
    M-D issued Service Bulletin (SB) F100-32-94 and Fokker Services
issued SBF100-32-119, which provide instructions to install the P/N
201071003 or P/N 201071004 NLG on aeroplanes in service. In
addition, Fokker Services issued optional SBF100-32-149 to introduce
the P/N 201456001 or P/N 201461001 NLG units on aeroplanes in
service.
    In January 2010, a second NLG main fitting failure occurred. The
results of the investigation showed that the fracture started from
small fatigue cracks in the affected area. Prompted by this new
occurrence, combined with the NLG certification methodology (safe
life principle), EASA has decided that the existing terminating
action, installation of a P/N 201071003 or P/N 201071004 NLG should
be made mandatory. Alternatively, a P/N 201456001 or P/N 201461001
NLG can be installed, which meets the same requirement.
    For the reasons described above, EASA issued AD 2012-0002,
retaining the requirements of [the Netherlands] AD * * *, which was
superseded, and to require the replacement of all P/N 201071001 and
P/N 201071002 NLG units with, respectively, P/N 201071003 and P/N
201071004 NLG units, or alternatively with, respectively, P/N
201456001 or P/N 201461001 NLG units.
    Replacement of a NLG main fitting or of a NLG unit on an
aeroplane constitutes terminating action for the repetitive
inspections for that aeroplane.
    EASA AD 2012-0002 also prohibits, after modification of an
aeroplane, installation of a P/N 201071001 or P/N 201071002 NLG unit
on that aeroplane.
* * * * *
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0062-0002.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 11351, February 28,
2014) or on the determination of the cost to the public.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
    The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
    In the NPRM (79 FR 11351, February 28, 2014), we proposed to
prevent the use of repairs that were not specifically

developed to correct the unsafe condition, by requiring that the repair
approval provided by the State of Design Authority or its delegated
agent specifically refer to this FAA AD. This change was intended to
clarify the method of compliance and to provide operators with better
visibility of repairs that are specifically developed and approved to
correct the unsafe condition. In addition, we proposed to change the
phrase ``its delegated agent'' to include a design approval holder
(DAH) with State of Design Authority design organization approval
(DOA), as applicable, to refer to a DAH authorized to approve required
repairs for the proposed AD.
    No comments were provided to the NPRM (79 FR 11351, February 28,
2014) about these proposed changes. However, a comment was provided for
an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 78285,
December 26, 2013). The commenter stated the following: ``The proposed
wording, being specific to repairs, eliminates the interpretation that
Airbus messages are acceptable for approving minor deviations
(corrective actions) needed during accomplishment of an AD mandated
Airbus service bulletin.''
    This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, the European Aviation Safety Agency (EASA), or Fokker
Services B.V.'s EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
    This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that in many cases
the foreign manufacturer's service bulletin and the foreign authority's
MCAI might have been issued some time before the FAA AD. Therefore, the
DOA might have provided U.S. operators with an approved repair,
developed with full awareness of the unsafe condition, before the FAA
AD is issued. Under these circumstances, to comply with the FAA AD, the
operator would be required to go back to the manufacturer's DOA and
obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this AD. Before adopting such a
requirement, the FAA will coordinate with affected DAHs and verify they
are prepared to implement means to ensure that their repair approvals
consider the unsafe condition addressed in this AD. Any such
requirements will be adopted through the normal AD rulemaking process,
including notice-and-comment procedures, when appropriate.
    We also have decided not to include a generic reference to either
the ``delegated agent'' or ``DAH with State of Design Authority design
organization approval,'' but instead we have provided the specific
delegation approval granted by the State of Design Authority for the
DAH.

Clarification of Language in Paragraph (m)(2) of This AD

    In paragraph (m)(2) of the NPRM (79 FR 11351, February 28, 2014),
we specified to contact certain aviation authorities ``for instructions
and follow those instructions.'' As part of the change described
previously regarding ``Contacting the Manufacturer'' language, this
text has been revised in paragraph (m)(2) of this AD to specify doing a
repair using a method approved by the FAA, EASA, or Fokker Services
B.V.'s EASA DOA.

Conclusion

    We reviewed the available data 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 (79 FR 11351, February 28, 2014) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 11351, February 28, 2014).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    The actions required by AD 2000-17-03, Amendment 39-11876 (65 FR
52298, August 29, 2000), and retained in this AD take about 2 work-
hours per product, at an average labor rate of $85 per work-hour.
Required parts cost $0 per product. Based on these figures, the
estimated cost of the actions that were required by AD 2000-17-03 is
$170 per product.
    We also estimate that it will take about 8 work-hours per product
to comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $525,000 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $2,102,720, or $526,680 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 AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.

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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0062; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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 removing Airworthiness Directive (AD)
2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), and
adding the following new AD:

2014-23-09 Fokker Services B.V.: Amendment 39-18025. Docket No. FAA-
2014-0062; Directorate Identifier 2012-NM-031-AD.

(a) Effective Date

    This AD becomes effective December 31, 2014.

(b) Affected ADs

    This AD replaces AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000).

(c) Applicability

    This AD applies to Fokker Services B.V. Model F.28 Mark 0100
airplanes; certificated in any category; all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
Gear.

(e) Reason

    This AD was prompted by a report of a nose landing gear (NLG)
main fitting failure. We are issuing this AD to prevent cracking of
the NLG main fitting, which could lead to collapse of the NLG during
takeoff and landing, and possible injury to the flight crew and
passengers.

(f) Compliance

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

(g) Retained One-Time Detailed Visual Inspection

    This paragraph restates the actions required by paragraph (a) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000).
For airplanes equipped with a Messier-Dowty NLG having part number
(P/N) 201071001 or 201071002, on which a main fitting subassembly
(MFSA) having P/N 201071200, 201071228, 201071248, or 201071249 is
installed: Prior to the accumulation of 7,500 total flight cycles or
within 50 flight cycles after October 3, 2000 (the effective date of
AD 2000-17-03), whichever occurs later, perform a one-time detailed
visual inspection of the NLG main fitting subassembly to detect
cracking, in accordance with Part 1 of the Accomplishment
Instructions of Fokker Service Bulletin SBF100-32-118, dated October
8, 1999.
    (1) If no cracking is detected, no further action is required by
this paragraph.
    (2) If any cracking is detected, prior to further flight,
accomplish the actions required by paragraph (i) of this AD.

(h) Definition of a Detailed Visual Inspection

    For the purposes of this AD, a detailed visual inspection is
defined as: An intensive visual examination of a specific structural
area, system, installation, or assembly to detect damage, failure,
or irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirrors, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.

(i) Retained Repetitive Eddy Current and/or Dye Penetrant Inspections

    This paragraph restates the actions required by paragraph (b) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with a new exception. For airplanes equipped with a Messier-Dowty
NLG having P/N 201071001 or 201071002, on which a MFSA having P/N
201071200, 201071228, 201071248, or 201071249 is installed: Except
as required by paragraph (g)(2) of this AD, prior to the
accumulation of 7,875 total flight cycles, or within 375 flight
cycles after October 3, 2000 (the effective date of AD 2000-17-03),
whichever occurs later, perform an eddy current or dye penetrant
inspection of the NLG main fitting

subassembly to detect cracking, in accordance with Part 2 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
118, dated October 8, 1999. Such inspection within the compliance
time required by the introductory text of paragraph (g) of this AD
terminates the requirements of paragraph (g) of this AD. Repeat the
inspection thereafter, using an eddy current or dye penetrant
technique, at intervals not to exceed 750 flight cycles, except as
required by paragraph (m)(1) of this AD. Repeat the inspection until
the replacement specified in paragraph (l) of this AD is done, or
the installation specified in paragraph (n) of this AD is done.

(j) Retained Rework of Main Fitting

    This paragraph restates the actions required by paragraph (c) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with revised repair methods. If any cracking is detected during any
inspection required by paragraph (g) or (i) of this AD: Prior to
further flight, rework the main fitting of the NLG, in accordance
with Part 3 of the Accomplishment Instructions of Fokker Service
Bulletin SBF100-32-118, dated October 8, 1999. If, after rework, any
cracking remains that exceeds the limits specified in Fokker Service
Bulletin SBF100-32-118, dated October 8, 1999, prior to further
flight, accomplish the actions specified by either paragraph (j)(1)
or (j)(2) of this AD.
    (1) Replace the NLG in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF100-32-118, dated October
8, 1999; and within 7,875 flight cycles after such replacement,
perform the inspection as specified in paragraph (i) of this AD, and
repeat the inspection thereafter at intervals not to exceed 750
flight cycles.
    (2) Repair in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the Rijksluchtvaartdienst (RLD) (or its delegated agent); or the
European Aviation Safety Agency (EASA); or Fokker B.V. Service's
EASA Design Organization Approval (DOA).

    Note 1 to paragraph (j) of this AD: Fokker Service Bulletin
SBF100-32-118, dated October 8, 1999, references Messier-Dowty
Service Bulletin F100-32-92, Revision 1, dated October 8, 1999, as
an additional source of service information for accomplishing the
inspections and rework of the NLG main fitting subassembly.

(k) Retained Reporting Requirements

    This paragraph restates the actions required by paragraph (d) of
AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000),
with revised contact information and minor editorial changes. Submit
a report of the detailed visual inspection findings (positive and
negative) required by paragraph (g) of this AD, and a report of the
initial eddy current or dye penetrant inspection findings (positive
and negative) required by paragraph (i) of this AD, to Fokker
Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands;
or to Fokker Services B.V., Technical Services Dept., P.O. Box 1357,
2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350;
fax +31 (0)88-6280-111; email<EMAIL_ADDRESS>Internet
http://www.myfokkerfleet.com; at the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD. As of the effective date of
this AD, submit reports to Fokker Services B.V., Technical Services
Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone
+31 (0)88-6280-350; fax +31 (0)88-6280-111; email
<EMAIL_ADDRESS>Internet http://www.myfokkerfleet.com.
    (1) For airplanes on which the detailed visual inspection
specified by paragraph (g) of this AD, and the initial repetitive
eddy current or dye penetrant inspection specified by paragraph (i)
of this AD, are accomplished after October 3, 2000 (the effective
date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29,
2000)): Submit each report within 7 days after performing the
applicable inspection.
    (2) For airplanes on which the detailed visual inspection
specified by paragraph (g) of this AD, and the initial repetitive
eddy current or dye penetrant inspection specified in paragraph (i)
of this AD, have been accomplished prior to October 3, 2000 (the
effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298,
August 29, 2000)): Submit the reports within 7 days after October 3,
2000 (the effective date of AD 2000-17-03).

(l) New Requirement of This AD: Replacement

    Except as provided by paragraph (m) of this AD, before the next
scheduled main fitting overhaul of the NLG after the effective date
of this AD, or within 36 months after the effective date of this AD,
whichever occurs first: Replace all NLG units having P/N 201071001
with a new P/N 201071003 NLG unit, and replace all NLG units having
P/N 201071002 with a new P/N 201071004 NLG unit, in accordance with
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
32-119, Revision 1, dated November 15, 2011, including Fokker Manual
Change Notification MCNM-F100-043, dated January 31, 2000.

(m) New Compliance Time Extension and On-Condition Actions

    For airplanes on which the next scheduled main fitting overhaul
of the NLG is to occur later than 36 months after the effective date
of this AD: Operators may accomplish the replacement required by
paragraph (l) of this AD before the next scheduled main fitting
overhaul of the NLG after the effective date of this AD, or within
72 months after the effective date of this AD, whichever occurs
first, provided the actions specified in paragraphs (m)(1) and
(m)(2) of this AD are done.
    (1) Within 36 months after the effective date of this AD,
accomplish the inspection specified in paragraph (i) of this AD
within 750 flight cycles since the most recent inspection, and
repeat thereafter at intervals not to exceed 375 flight cycles until
the replacement specified in paragraph (l) of this AD is done or the
installation specified in paragraph (n) of this AD is done.
    (2) In addition to the inspection specified in paragraph (m)(1)
of this AD, do all other on-condition actions specified in paragraph
1.E(1)(b) of Fokker Service Bulletin SBF100-32-119, Revision 1,
dated November 15, 2011, including Fokker Manual Change Notification
MCNM-F100-043, dated January 31, 2000; except where Fokker Service
Bulletin SBF100-32-119, Revision 1, dated November 15, 2011,
including Fokker Manual Change Notification MCNM-F100-043, dated
January 31, 2000, specifies to contact Fokker Services B.V., before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Fokker Services B.V.'s EASA Design Organization Approval
(DOA).

    Note 2 to paragraph (m) of this AD:  Fokker Service Bulletin
SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker
Manual Change Notification MCNM-F100-043, dated January 31, 2000,
references Messier-Dowty Service Bulletin F100-32-94, dated January
5, 2000, as an additional source of service information for
replacing the NLG unit.

(n) New Optional Action

    Installing a new P/N 201456001 or P/N 201461001 NLG unit, in
accordance with Fokker Proforma Service Bulletin SBF100-32-149,
Revision 1, dated October 25, 2007, including Appendix 1, dated
December 12, 2006, is acceptable for compliance with the replacement
required by paragraph (l) of this AD, provided the installation is
accomplished within the compliance time specified in paragraph (l)
of this AD; and, except for airplanes that comply with paragraph (m)
of this AD, provided the installation is accomplished within the
compliance time specified in paragraph (m) of this AD.

(o) New Requirement: Concurrent Modification

    Prior to, or concurrently with, the installation of the NLG unit
required by paragraph (l) of this AD or the optional installation
specified in paragraph (n) of this AD, modify the NLG bracket, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-53-074, dated November 1, 1999.

(p) New Terminating Actions

    Accomplishing the replacement specified in paragraph (l) of this
AD or the installation specified in paragraph (n) of this AD
terminates the repetitive eddy current or dye penetrant inspections
required by paragraphs (i) and (m)(1) of this AD.

(q) New Parts Installation Prohibition

    (1) For airplanes equipped with a Messier-Dowty NLG having P/N)
201071001 or 201071002, on which a main fitting subassembly (MFSA)
having P/N 201071200, 201071228, 201071248, or 201071249 is
installed: As of October 3, 2000 (the effective date of AD 2000-17-
03, Amendment 39-11876 (65 FR 52298, August 29, 2000), and until the
effective date of this AD, no person may install an NLG having P/N
201071001 or 201071002 unless the installed MFSA has been inspected
by means of an eddy current or dye penetrant inspection, and
corrected in accordance with paragraph (i) of this AD.

    (2) For all airplanes: As of the effective date of this AD, no
person may install an NLG having P/N 201071001 or 201071002 on any
airplane.

(r) Credit for Previous Actions

    This paragraph provides credit for the replacement required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Fokker Service Bulletin SBF 100-32-
119, dated January 31, 2000, provided P/N 201071003 or 201071004
nose gear has been installed.

(s) 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: Tom
Rodriguez, 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: 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 Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Fokker Services B.V.'s EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0002R1, dated March 30,
2012, for related information. You may examine the MCAI in the AD
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0062-0002.
    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (u)(5) and (u)(6) of this AD.

(u) 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.
    (3) The following service information was approved for IBR on
December 31, 2014.
    (i) Fokker Service Bulletin SBF 100-32-119, Revision 1, dated
November 15, 2011, including Fokker Manual Change Notification MCNM-
F100-043, dated January 31, 2000.
    (ii) Fokker Proforma Service Bulletin SBF 100-32-149, Revision
1, dated October 25, 2007, including Appendix 1, dated December 12,
2006.
    (iii) Fokker Service Bulletin SBF 100-53-074, dated November 1,
1999.
    (4) The following service information was approved for IBR on
October 3, 2000 (65 FR 52298, August 17, 2000).
    (i) Fokker Service Bulletin SBF100-32-118, dated October 8,
1999.
    (ii) Reserved.
    (5) For service information identified in this AD, contact
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130
EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; email<EMAIL_ADDRESS>Internet http://www.myfokkerfleet.com.
    (6) 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.
    (7) 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 Renton, Washington, on November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-27361 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P