final rule, because some of those airplanes listed as active have not
accrued utilization statistics for years. The agency has identified 9
out of the 21 affected airplanes that have not accrued utilization for
the past two years or longer. If the airplanes are not accumulating
flight cycles or hours for years, then given the age of these
airplanes, the FAA assumes that these airplanes are parked or retired.
    This final rule will impose either the retirement of an airplane at
LOV or a set of maintenance changes to extend the LOV for the airplane.
In this final regulatory analysis, the assumption is that operators
will retire the airplanes at LOV. The airplane retirement cost is the
operator's most expensive economic choice based on compliance with the
final rule.
    The FAA's analysis determined that no small entities currently
operate airplanes over 100% of LOV.
    One small entity currently operates one airplane between 90-100% of
LOV. Four small entities currently operate four airplanes between 80-
90% of LOV. Lastly, the database lists four small entities operating
seven airplanes between 75-80% of LOV. Table 1 shows these results:
[GRAPHIC] [TIFF OMITTED] TR15NO10.000

    To estimate when an airplane will exceed LOV, the FAA followed
these steps: From the March 2009 OAG Associates Fleet database the FAA
calculated the average age of U.S.-operated part 25 transport category
retired airplanes over time. OAG defines a retired airplane as one that
has been retired, scrapped or otherwise destroyed by its owner/operator
at the end of the airplane's useful life. The FAA calculated the
average age based upon the retired airplanes in the OAG fleet database
beginning in the 1940s. On average, part 25 passenger airplanes were
operated for 25 years and cargo airplanes were operated for 34 years,
and then retired from U.S. service.
    For the base case in the regulatory evaluation, the FAA assumed
that in year 25 of operation, every affected passenger airplane will
convert to cargo service and then retire from cargo service at 34
years. The FAA chose this scenario for the cost model because it
captures nearly all of the affected airplanes.
    The FAA applied these average ages to the affected airplanes in
Table 1 and retired airplanes over the average retirement age of 34
years over the 20-year analysis interval used in the regulatory
evaluation. Under this model, the agency assumes retirement of only one
Boeing 747 airplane operated by a small business entity, because that
airplane will reach its LOV before reaching its average retirement age.
    The model estimates one small business entity will retire one
airplane soon after the rule is promulgated. This small business entity
will need to implement an appropriate WFD program, and either apply for
an extended LOV or retire the airplane. For the FRFA, the FAA assumed
the affected small entity will retire the airplane.
    The FAA estimated the final rule's present value costs to the air
carrier based on the 2009 Avitas Bluebook of Jet Aircraft residual
value of the airplane forced to retire. The present-value residual
value of the affected airplane is $3.6 million. The ratio of this
present value cost to annual revenues is 1.28%. The FAA does not
consider this impact to be economically significant, and since only one
entity is potentially affected, this is not a substantial number of
small entities.
    The FAA Administrator certifies that this rule will not have a
significant economic impact on a substantial number of small entities.

International Trade Impact Analysis

    The Trade Agreements Act of 1979 (Pub. L. 96-39), as amended by the
Uruguay Round Agreements Act (Pub. L. 103-465), prohibits Federal
agencies from establishing standards or engaging

in related activities that create unnecessary obstacles to the foreign
commerce of the United States. Pursuant to these Acts, the
establishment of standards is not considered an unnecessary obstacle to
the foreign commerce of the United States, so long as the standard has
a legitimate domestic objective, such as the protection of safety, and
does not operate in a manner that excludes imports that meet this
objective. The statute also requires consideration of international
standards and, where appropriate, that they be the basis for United
States standards. The FAA has assessed the potential effect of this
final rule and determined that it will impose the same costs on
domestic and international entities and thus has a neutral trade
impact.

Unfunded Mandates Assessment

    Title II of the Unfunded Mandates Reform Act of 1995 (Pub. L. 104-
4) requires each Federal agency to prepare a written statement
assessing the effects of any Federal mandate in a proposed or final
agency rule that may result in an expenditure of $100 million or more
(in 1995 dollars) in any one year by State, local, and Tribal
governments, in the aggregate, or by the private sector; such a mandate
is deemed to be a ``significant regulatory action.'' The FAA currently
uses an inflation-adjusted value of $136.1 million in lieu of $100
million. This final rule does not contain such a mandate. The
requirements of Title II do not apply.

Executive Order 13132, Federalism

    The FAA has analyzed this final rule under the principles and
criteria of Executive Order 13132, Federalism. We determined that this
action will not have a substantial direct effect on the States, the
relationship between the national government and the States, or on the
distribution of power and responsibilities among the various levels of
government. Therefore, today's rule does not have federalism
implications.

Regulations Affecting Intrastate Aviation in Alaska

    Section 1205 of the FAA Reauthorization Act of 1996 (110 Stat.
3213) requires the FAA, when modifying its regulations in a manner
affecting intrastate aviation in Alaska, to consider the extent to
which Alaska is not served by transportation modes other than aviation,
and to establish appropriate regulatory distinctions. In the NPRM, the
FAA requested comments on whether the proposed rule should apply
differently to intrastate operations in Alaska. As discussed earlier,
the FAA received comments on this subject from the late Senator
Stevens, Senator Murkowski, and Everts Air Cargo and has determined
that there would not be an adverse effect on intrastate air
transportation in Alaska and that regulatory distinctions are not
appropriate.

Environmental Analysis

    FAA Order 1050.1E identifies FAA actions that are categorically
excluded from preparation of an environmental assessment or
environmental impact statement under the National Environmental Policy
Act in the absence of extraordinary circumstances. The FAA has
determined this rulemaking action qualifies for the categorical
exclusion identified in paragraph 312f of the order and involves no
extraordinary circumstances.

Regulations That Significantly Affect Energy Supply, Distribution, or
Use

    The FAA has analyzed this rule under Executive Order 13211, Actions
Concerning Regulations that Significantly Affect Energy Supply,
Distribution, or Use (May 18, 2001). We have determined that it is not
a ``significant regulatory action'' under the executive order because,
while it is a ``significant regulatory action'' under Executive Order
12866 and DOT's Regulatory Policies and Procedures, it is not likely to
have a significant adverse effect on the supply, distribution, or use
of energy.

List of Subjects

14 CFR Part 25

    Aircraft, Aviation safety, Reporting and recordkeeping
requirements, Continued airworthiness.

14 CFR Part 26

    Aircraft, Aviation safety, Continued airworthiness.

14 CFR Parts 121 and 129

    Air carriers, Aircraft, Aviation safety, Continued airworthiness,
Reporting and recordkeeping requirements.

The Amendments

0
In consideration of the foregoing, the Federal Aviation Administration
amends Chapter I of Title 14, Code of Federal Regulations, parts 25,
26, 121, and 129, as follows:

PART 25--AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES

0
1. The authority citation for part 25 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701, 44702 and 44704.

0
2. Amend Sec.  25.571 by revising paragraphs (a)(3) introductory text
and (b) introductory text to read as follows:

Sec.  25.571  Damage-tolerance and fatigue evaluation of structure.

    (a) * * *
    (3) Based on the evaluations required by this section, inspections
or other procedures must be established, as necessary, to prevent
catastrophic failure, and must be included in the Airworthiness
Limitations section of the Instructions for Continued Airworthiness
required by Sec.  25.1529. The limit of validity of the engineering
data that supports the structural maintenance program (hereafter
referred to as LOV), stated as a number of total accumulated flight
cycles or flight hours or both, established by this section must also
be included in the Airworthiness Limitations section of the
Instructions for Continued Airworthiness required by Sec.  25.1529.
Inspection thresholds for the following types of structure must be
established based on crack growth analyses and/or tests, assuming the
structure contains an initial flaw of the maximum probable size that
could exist as a result of manufacturing or service-induced damage:
* * * * *
    (b) Damage-tolerance evaluation. The evaluation must include a
determination of the probable locations and modes of damage due to
fatigue, corrosion, or accidental damage. Repeated load and static
analyses supported by test evidence and (if available) service
experience must also be incorporated in the evaluation. Special
consideration for widespread fatigue damage must be included where the
design is such that this type of damage could occur. An LOV must be
established that corresponds to the period of time, stated as a number
of total accumulated flight cycles or flight hours or both, during
which it is demonstrated that widespread fatigue damage will not occur
in the airplane structure. This demonstration must be by full-scale
fatigue test evidence. The type certificate may be issued prior to
completion of full-scale fatigue testing, provided the Administrator
has approved a plan for completing the required tests. In that case,
the Airworthiness Limitations section of the Instructions for Continued
Airworthiness required by Sec.  25.1529 must specify that no airplane
may be operated beyond a number of cycles equal to \1/2\ the number of
cycles accumulated on the fatigue test article,

until such testing is completed. The extent of damage for residual
strength evaluation at any time within the operational life of the
airplane must be consistent with the initial detectability and
subsequent growth under repeated loads. The residual strength
evaluation must show that the remaining structure is able to withstand
loads (considered as static ultimate loads) corresponding to the
following conditions:
* * * * *

0
3. Amend section H25.4 of Appendix H to part 25 by revising paragraph
(a)(1) and adding paragraph (a)(4) to read as follows:

Appendix H to Part 25--Instructions for Continued Airworthiness

* * * * *
H25.4 Airworthiness Limitations section.

    (a) * * *
    (1) Each mandatory modification time, replacement time,
structural inspection interval, and related structural inspection
procedure approved under Sec.  25.571.
* * * * *
    (4) A limit of validity of the engineering data that supports
the structural maintenance program (LOV), stated as a total number
of accumulated flight cycles or flight hours or both, approved under
Sec.  25.571. Until the full-scale fatigue testing is completed and
the FAA has approved the LOV, the number of cycles accumulated by
the airplane cannot be greater than \1/2\ the number of cycles
accumulated on the fatigue test article.
* * * * *

PART 26--CONTINUED AIRWORTHINESS AND SAFETY IMPROVEMENTS FOR
TRANSPORT CATEGORY AIRPLANES

0
4. The authority citation for part 26 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701, 44702 and 44704.

0
5. Revise Sec.  26.5 to read as follows:

Sec.  26.5  Applicability table.

    Table 1 of this section provides an overview of the applicability
of this part. It provides guidance in identifying what sections apply
to various types of entities. The specific applicability of each
subpart and section is specified in the regulatory text.

                                     Table 1--Applicability of Part 26 Rules
----------------------------------------------------------------------------------------------------------------
                                                              Applicable sections
                             -----------------------------------------------------------------------------------
                                                    Subpart C      Subpart D fuel
                              Subpart B EAPAS/     widespread           tank         Subpart E damage  tolerance
                                     FTS         fatigue damage     flammability                data
----------------------------------------------------------------------------------------------------------------
Effective date of rule......  December 10,      January 14, 2011  December 26,      January 11, 2008
                               2007.                               2008.
Existing \1\ TC Holders.....  26.11...........  26.21...........  26.33...........  26.43, 26.45, 26.49
Pending \1\ TC Applicants...  26.11...........  26.21...........  26.37...........  26.43, 26.45
Future \2\ TC applicants....  N/A.............  N/A.............  N/A.............  26.43
Existing \1\ STC Holders....  N/A.............  26.21...........  26.35...........  26.47, 26.49
Pending \1\ STC/ATC           26.11...........  26.21...........  26.35...........  26.45, 26.47, 26.49
 applicants.
Future \2\ STC/ATC            26.11...........  26.21...........  26.35...........  26.45, 26.47, 26.49
 applicants.
Manufacturers...............  N/A.............  N/A.............  26.39...........  N/A
----------------------------------------------------------------------------------------------------------------
\1\ As of the effective date of the identified rule.
\2\ Application made after the effective date of the identified rule.

0
6. Add subpart C to read as follows:
Subpart C--Aging Airplane Safety--Widespread Fatigue Damage
Sec.
26.21 Limit of validity.
26.23 Extended limit of validity.

Subpart C--Aging Airplane Safety--Widespread Fatigue Damage

Sec.  26.21  Limit of validity.

    (a) Applicability. Except as provided in paragraph (g) of this
section, this section applies to transport category, turbine-powered
airplanes with a maximum takeoff gross weight greater than 75,000
pounds and a type certificate issued after January 1, 1958, regardless
of whether the maximum takeoff gross weight is a result of an original
type certificate or a later design change. This section also applies to
transport category, turbine-powered airplanes with a type certificate
issued after January 1, 1958, if a design change approval for which
application is made after January 14, 2011 has the effect of reducing
the maximum takeoff gross weight from greater than 75,000 pounds to
75,000 pounds or less.
    (b) Limit of validity. Each person identified in paragraph (c) of
this section must comply with the following requirements:
    (1) Establish a limit of validity of the engineering data that
supports the structural maintenance program (hereafter referred to as
LOV) that corresponds to the period of time, stated as a number of
total accumulated flight cycles or flight hours or both, during which
it is demonstrated that widespread fatigue damage will not occur in the
airplane. This demonstration must include an evaluation of airplane
structural configurations and be supported by test evidence and
analysis at a minimum and, if available, service experience, or service
experience and teardown inspection results, of high-time airplanes of
similar structural design, accounting for differences in operating
conditions and procedures. The airplane structural configurations to be
evaluated include--
    (i) All model variations and derivatives approved under the type
certificate; and
    (ii) All structural modifications to and replacements for the
airplane structural configurations specified in paragraph (b)(1)(i) of
this section, mandated by airworthiness directives as of January 14,
2011.
    (2) If the LOV depends on performance of maintenance actions for
which service information has not been mandated by airworthiness
directive as of January 14, 2011, submit the following to the FAA
Oversight Office:
    (i) For those maintenance actions for which service information has
been issued as of the applicable compliance date specified in paragraph
(c) of this section, a list identifying each of those actions.
    (ii) For those maintenance actions for which service information
has not been issued as of the applicable compliance date specified in
paragraph (c) of this section, a list identifying each of those actions
and a binding schedule for providing in a timely manner the necessary
service information for those actions. Once the FAA Oversight Office
approves this schedule, each person identified in paragraph (c) of this
section must comply with that schedule.

    (3) Unless previously accomplished, establish an Airworthiness
Limitations section (ALS) for each airplane structural configuration
evaluated under paragraph (b)(1) of this section.
    (4) Incorporate the applicable LOV established under paragraph
(b)(1) of this section into the ALS for each airplane structural
configuration evaluated under paragraph (b)(1) and submit it to the FAA
Oversight Office for approval.
    (c) Persons who must comply and compliance dates. The following
persons must comply with the requirements of paragraph (b) of this
section by the specified date.
    (1) Holders of type certificates (TC) of airplane models identified
in Table 1 of this section: No later than the applicable date
identified in Table 1 of this section.
    (2) Applicants for TCs, if the date of application was before
January 14, 2011: No later than the latest of the following dates:
    (i) January 14, 2016;
    (ii) The date the certificate is issued; or
    (iii) The date specified in the plan approved under Sec.  25.571(b)
for completion of the full-scale fatigue testing and demonstrating that
widespread fatigue damage will not occur in the airplane structure.
    (3) Applicants for amendments to TCs, with the exception of
amendments to TCs specified in paragraphs (c)(6) or (c)(7) of this
section, if the original TC was issued before January 14, 2011: No
later than the latest of the following dates:
    (i) January 14, 2016;
    (ii) The date the amended certificate is issued; or
    (iii) The date specified in the plan approved under Sec.  25.571(b)
for completion of the full-scale fatigue testing and demonstrating that
widespread fatigue damage will not occur in the airplane structure.
    (4) Applicants for amendments to TCs, with the exception of
amendments to TCs specified in paragraphs (c)(6) or (c)(7) of this
section, if the application for the original TC was made before January
14, 2011 but the TC was not issued before January 14, 2011: No later
than the latest of the following dates:
    (i) January 14, 2016;
    (ii) The date the amended certificate is issued; or
    (iii) The date specified in the plan approved under Sec.  25.571(b)
for completion of the full-scale fatigue testing and demonstrating that
widespread fatigue damage will not occur in the airplane structure.
    (5) Holders of either supplemental type certificates (STCs) or
amendments to TCs that increase maximum takeoff gross weights from
75,000 pounds or less to greater than 75,000 pounds: No later than July
14, 2012.
    (6) Applicants for either STCs or amendments to TCs that increase
maximum takeoff gross weights from 75,000 pounds or less to greater
than 75,000 pounds: No later than the latest of the following dates:
    (i) July 14, 2012;
    (ii) The date the certificate is issued; or
    (iii) The date specified in the plan approved under Sec.  25.571(b)
for completion of the full-scale fatigue testing and demonstrating that
widespread fatigue damage will not occur in the airplane structure.
    (7) Applicants for either STCs or amendments to TCs that decrease
maximum takeoff gross weights from greater than 75,000 pounds to 75,000
pounds or less, if the date of application was after January 14, 2011:
No later than the latest of the following dates:
    (i) July 14, 2012;
    (ii) The date the certificate is issued; or
    (iii) The date specified in the plan approved under Sec.  25.571(b)
for completion of the full-scale fatigue testing and demonstrating that
widespread fatigue damage will not occur in the airplane structure.
    (d) Compliance plan. Each person identified in paragraph (e) of
this section must submit a compliance plan consisting of the following:
    (1) A proposed project schedule, identifying all major milestones,
for meeting the compliance dates specified in paragraph (c) of this
section.
    (2) A proposed means of compliance with paragraphs (b)(1) through
(b)(4) of this section.
    (3) A proposal for submitting a draft of all compliance items
required by paragraph (b) of this section for review by the FAA
Oversight Office not less than 60 days before the compliance date
specified in paragraph (c) of this section, as applicable.
    (4) A proposal for how the LOV will be distributed.
    (e) Compliance dates for compliance plans. The following persons
must submit the compliance plan described in paragraph (d) of this
section to the FAA Oversight Office by the specified date.
    (1) Holders of type certificates: No later than April 14, 2011.
    (2) Applicants for TCs and amendments to TCs, with the exception of
amendments to TCs specified in paragraphs (e)(4), (e)(5), or (e)(6) of
this section, if the date of application was before January 14, 2011
but the TC or TC amendment was not issued before January 14, 2011: No
later than April 14, 2011.
    (3) Holders of either supplemental type certificates or amendments
to TCs that increase maximum takeoff gross weights from 75,000 pounds
or less to greater than 75,000 pounds: No later than April 14, 2011.
    (4) Applicants for either STCs or amendments to TCs that increase
maximum takeoff gross weights from 75,000 pounds or less to greater
than 75,000 pounds, if the date of application was before January 14,
2011: No later than April 14, 2011.
    (5) Applicants for either STCs or amendments to TCs that increase
maximum takeoff gross weights from 75,000 pounds or less to greater
than 75,000 pounds, if the date of application is on or after January
14, 2011: Within 90 days after the date of application.
    (6) Applicants for either STCs or amendments to TCs that decrease
maximum takeoff gross weights from greater than 75,000 pounds to 75,000
pounds or less, if the date of application is on or after January 14,
2011: Within 90 days after the date of application.
    (f) Compliance plan implementation. Each affected person must
implement the compliance plan as approved in compliance with paragraph
(d) of this section.
    (g) Exceptions. This section does not apply to the following
airplane models:
    (1) Bombardier BD-700.
    (2) Bombardier CL-44.
    (3) Gulfstream GV.
    (4) Gulfstream GV-SP.
    (5) British Aerospace, Aircraft Group, and Societe Nationale
Industrielle Aerospatiale Concorde Type 1.
    (6) British Aerospace (Commercial Aircraft) Ltd., Armstrong
Whitworth Argosy A.W. 650 Series 101.
    (7) British Aerospace Airbus, Ltd., BAC 1-11.
    (8) BAE Systems (Operations) Ltd., BAe 146.
    (9) BAE Systems (Operations) Ltd., Avro 146.
    (10) Lockheed 300-50A01 (USAF C141A).
    (11) Boeing 707.
    (12) Boeing 720.
    (13) deHavilland D.H. 106 Comet 4C.
    (14) Ilyushin Aviation IL-96T.
    (15) Bristol Aircraft Britannia 305.
    (16) Avions Marcel Dassault-Breguet Aviation Mercure 100C.
    (17) Airbus Caravelle.
    (18) D & R Nevada, LLC, Convair Model 22.
    (19) D & R Nevada, LLC, Convair Model 23M.

            Table 1--Compliance Dates for Affected Airplanes
------------------------------------------------------------------------
                                                      Compliance date--
     Airplane model  (all existing \1\ models)          (months after
                                                      January 14, 2011)
------------------------------------------------------------------------
Airbus:
    A300 Series, A310 Series, A300-600 Series.....                    18
    A318 Series...................................                    48
    A319 Series...................................                    48
    A320 Series...................................                    48
    A321 Series...................................                    48
    A330-200, -200 Freighter, -300 Series.........                    48
    A340-200, -300, -500, -600 Series.............                    48
    A380-800 Series...............................                    60
Boeing:
    717...........................................                    48
    727 (all series)..............................                    18
    737 (Classics): 737-100, -200, -200C, -300, -                     18
     400, -500....................................
    737 (NG): 737-600, -700, -700C, -800, -900, -                     48
     900ER........................................
    747 (Classics): 747-100, -100B, -100B SUD, -                      18
     200B, [dash]200C, -200F, -300, 747SP, 747SR..
    747-400: 747-400, -400D, -400F................                    48
    757...........................................                    48
    767...........................................                    48
    777-200, -300.................................                    48
    777-200LR, 777-300ER, 777F....................                    60
Bombardier:
    CL-600: 2D15 (Regional Jet Series 705), 2D24                      60
     (Regional Jet Series 900)....................
Embraer:
    ERJ 170.......................................                    60
    ERJ 190.......................................                    60
Fokker:
    F.28 Mark 0070, Mark 0100.....................                    18
Lockheed:
    L-1011........................................                    18
    188...........................................                    18
    382 (all series)..............................                    18
McDonnell Douglas:
    DC-8, -8F.....................................                    18
    DC-9..........................................                    18
    MD-80 (DC-9-81, -82, -83, -87, MD-88).........                    18
    MD-90.........................................                    48
    DC-10.........................................                    18
    MD-10.........................................                    48
    MD-11, -11F...................................                    48
All Other Airplane Models Listed on a Type                            60
 Certificate as of January 14, 2011...............
------------------------------------------------------------------------
\1\ Type certificated as of January 14, 2011.

Sec.  26.23  Extended limit of validity.

    (a) Applicability. Any person may apply to extend a limit of
validity of the engineering data that supports the structural
maintenance program (hereafter referred to as LOV) approved under Sec.
25.571 of this subchapter, Sec.  26.21, or this section. Extending an
LOV is a major design change. The applicant must comply with the
relevant provisions of subparts D or E of part 21 of this subchapter
and paragraph (b) of this section.
    (b) Extended limit of validity. Each person applying for an
extended LOV must comply with the following requirements:
    (1) Establish an extended LOV that corresponds to the period of
time, stated as a number of total accumulated flight cycles or flight
hours or both, during which it is demonstrated that widespread fatigue
damage will not occur in the airplane. This demonstration must include
an evaluation of airplane structural configurations and be supported by
test evidence and analysis at a minimum and, if available, service
experience, or service experience and teardown inspection results, of
high-time airplanes of similar structural design, accounting for
differences in operating conditions and procedures. The airplane
structural configurations to be evaluated include--
    (i) All model variations and derivatives approved under the type
certificate for which approval for an extension is sought; and
    (ii) All structural modifications to and replacements for the
airplane structural configurations specified in paragraph (b)(1)(i) of
this section, mandated by airworthiness directive, up to the date of
approval of the extended LOV.
    (2) Establish a revision or supplement, as applicable, to the
Airworthiness Limitations section (ALS) of the Instructions for
Continued Airworthiness required by Sec.  25.1529 of this subchapter,
and submit it to the FAA Oversight Office for approval. The revised ALS
or supplement to the ALS must include the applicable extended LOV
established under paragraph (b)(1) of this section.
    (3) Develop the maintenance actions determined by the WFD
evaluation performed in paragraph (b)(1) of this section to be
necessary to preclude WFD from occurring before the airplane reaches
the proposed extended LOV. These maintenance actions must be documented
as airworthiness limitation items in the ALS and submitted to the FAA
Oversight Office for approval.

PART 121--OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL
OPERATIONS

0
7. The authority citation for part 121 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 40119, 41706, 44101, 44701-
44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44901, 44903-
44904, 44912, 45101-45105, 46105, 46301.

0
8. Add new Sec.  121.1115 to read as follows:

Sec.  121.1115  Limit of validity.

    (a) Applicability. This section applies to certificate holders
operating any transport category, turbine-powered airplane with a
maximum takeoff gross weight greater than 75,000 pounds and a type
certificate issued after January 1, 1958, regardless of whether the
maximum takeoff gross weight is a result of an original type
certificate or a later design change. This section also applies to
certificate holders operating any transport category, turbine-powered
airplane with a type certificate issued after January 1, 1958,
regardless of the maximum takeoff gross weight, for which a limit of
validity of the engineering data that supports the structural
maintenance program (hereafter referred to as LOV) is required in
accordance with Sec.  25.571 or Sec.  26.21 of this chapter after
January 14, 2011.
    (b) Limit of validity. No certificate holder may operate an
airplane identified in paragraph (a) of this section after the
applicable date identified in Table 1 of this section unless an
Airworthiness Limitations section approved under Appendix H to part 25
or Sec.  26.21 of this chapter is incorporated into its maintenance
program. The ALS must--
    (1) Include an LOV approved under Sec.  25.571 or Sec.  26.21 of
this chapter, as applicable, except as provided in paragraph (f) of
this section; and
    (2) Be clearly distinguishable within its maintenance program.
    (c) Operation of airplanes excluded from Sec.  26.21. No
certificate holder may operate an airplane identified in Sec.  26.21(g)
of this chapter after July 14, 2013, unless an Airworthiness
Limitations section approved under Appendix H to part 25 or Sec.  26.21
of this chapter is incorporated into its maintenance program. The ALS
must--
    (1) Include an LOV approved under Sec.  25.571 or Sec.  26.21 of
this chapter, as applicable, except as provided in paragraph (f) of
this section; and
    (2) Be clearly distinguishable within its maintenance program.
    (d) Extended limit of validity. No certificate holder may operate
an airplane beyond the LOV, or extended LOV, specified in paragraph
(b)(1), (c), (d), or (f) of this section, as applicable, unless the
following conditions are met:
    (1) An ALS must be incorporated into its maintenance program that--
    (i) Includes an extended LOV and any widespread fatigue damage
airworthiness limitation items approved under Sec.  26.23 of this
chapter; and
    (ii) Is approved under Sec.  26.23 of this chapter.
    (2) The extended LOV and the airworthiness limitation items
pertaining to widespread fatigue damage must be clearly distinguishable
within its maintenance program.
    (e) Principal Maintenance Inspector approval. Certificate holders
must submit the maintenance program revisions required by paragraphs
(b), (c), and (d) of this section to the Principal Maintenance
Inspector for review and approval.
    (f) Exception. For any airplane for which an LOV has not been
approved as of the applicable compliance date specified in paragraph
(c) or Table 1 of this section, instead of including an approved LOV in
the ALS, an operator must include the applicable default LOV specified
in Table 1 or Table 2 of this section, as applicable, in the ALS.

                                   Table 1--Airplanes Subject to Sec.   26.21
----------------------------------------------------------------------------------------------------------------
                                                    Compliance date--
                 Airplane model                   months after January     Default LOV [flight cycles (FC)  or
                                                        14, 2011                    flight hours (FH)]
----------------------------------------------------------------------------------------------------------------
Airbus--Existing\1\ Models Only:
    A300 B2-1A, B2-1C, B2K-3C, B2-203..........  30....................  48,000 FC
    A300 B4-2C, B4-103.........................  30....................  40,000 FC
    A300 B4-203................................  30....................  34,00 FC
    A300-600 Series............................  30....................  30,000 FC/67,500 FH
    A310-200 Series............................  30....................  40,000 FC/60,000 FH
    A310-300 Series............................  30....................  35,000 FC/60,000 FH
    A318 Series................................  60....................  48,000 FC/60,000 FH
    A319 Series................................  60....................  48,000 FC/60,000 FH
    A320-100 Series............................  60....................  48,000 FC/48,000 FH
    A320-200 Series............................  60....................  48,000 FC/60,000 FH
    A321 Series................................  60....................  48,000 FC/60,000 FH
    A330-200, -300 Series (except WV050 family)  60....................  40,000 FC/60,000 FH
     (non enhanced).
    A330-200, -300 Series WV050 family           60....................  33,000 FC/100,000 FH
     (enhanced).
    A330-200 Freighter Series..................  60....................  See NOTE.
    A340-200, -300 Series (except WV 027 and     60....................  20,000 FC/80,000 FH
     WV050 family) (non enhanced).
    A340-200, -300 Series WV 027 (non enhanced)  60....................  30,000 FC/60,000 FH
    A340-300 Series WV050 family (enhanced)....  60....................  20,000 FC/100,000 FH
    A340-500, -600 Series......................  60....................  16,600 FC/100,000 FH
    A380-800 Series............................  72....................  See NOTE.
Boeing--Existing\1\ Models Only:
    717........................................  60....................  60,000 FC/60,000 FH
    727 (all series)...........................  30....................  60,000 FC
    737 (Classics): 737-100, -200, -200C, -300,  30....................  75,000 FC
     -400, -500.
    737 (NG): 737-600, -700, -700C, -800, -900,  60....................  75,000 FC
     -900ER.
    747 (Classics): 747-100, -100B, -100B SUD, - 30....................  20,000 FC
     200B, -200C, -200F, -300, 747SP, 747SR.
    747-400: 747-400, -400D, -400F.............  60....................  20,000 FC
    757........................................  60....................  50,000 FC
    767........................................  60....................  50,000 FC
    777-200, -300..............................  60....................  40,000 FC

    777-200LR, 777-300ER.......................  72....................  40,000 FC
    777F.......................................  72....................  11,000 FC
Bombardier--Existing\1\ Models Only:
    CL-600: 2D15 (Regional Jet Series 705),      72....................  60,000 FC
     2D24 (Regional Jet Series 900).
Embraer--Existing\1\ Models Only:
    ERJ 170....................................  72....................  See NOTE.
    ERJ 190....................................  72....................  See NOTE.
Fokker--Existing\1\ Models Only:
    F.28 Mark 0070, Mark 0100..................  30....................  90,000 FC
Lockheed--Existing\1\ Models Only:
    L-1011.....................................  30....................  36,000 FC
    188........................................  30....................  26,600 FC
    382 (all series)...........................  30....................  20,000 FC/50,000 FH
McDonnell Douglas--Existing\1\ Models Only:
    DC-8, -8F..................................  30....................  50,000 FC/50,000 FH
    DC-9 (except for MD-80 models).............  30....................  100,000 FC/100,000 FH
    MD-80 (DC-9-81, -82, -83, -87, MD-88)......  30....................  50,000 FC/50,000 FH
    MD-90......................................  60....................  60,000 FC/90,000 FH
    DC-10-10, -15..............................  30....................  42,000 FC/60,000 FH
    DC-10-30, -40, -10F, -30F, -40F............  30....................  30,000 FC/60,000 FH
    MD-10-10F..................................  60....................  42,000 FC/60,000 FH
    MD-10-30F..................................  60....................  30,000 FC/60,000 FH
    MD-11, MD-11F..............................  60....................  20,000 FC/60,000 FH
Maximum Takeoff Gross Weight Changes:
    All airplanes whose maximum takeoff gross    30, or within 12        Not applicable.
     weight has been decreased to 75,000 pounds   months after the LOV
     or below after January 14, 2011 or           is approved, or
     increased to greater than 75,000 pounds at   before operating the
     any time by an amended type certificate or   airplane, whichever
     supplemental type certificate.               occurs latest.
All Other Airplane Models (TCs and amended TCs)  72, or within 12        Not applicable.
 not Listed in Table 2.                           months after the LOV
                                                  is approved, or
                                                  before operating the
                                                  airplane, whichever
                                                  occurs latest.
----------------------------------------------------------------------------------------------------------------
\1\ Type certificated as of January 14, 2011.

    Note: Airplane operation limitation is stated in the
Airworthiness Limitation section.

                                  Table 2--Airplanes Excluded from Sec.   26.21
----------------------------------------------------------------------------------------------------------------
                                                                     Default LOV  [flight cycles (FC)  or flight
                          Airplane model                                             hours (FH)]
----------------------------------------------------------------------------------------------------------------
Airbus:
    Caravelle.....................................................  15,000 FC/24,000 FH
Avions Marcel Dassault:
    Breguet Aviation Mercure 100C.................................  20,000 FC/16,000 FH
Boeing:
    Boeing 707 (-100 Series and -200 Series)......................  20,000 FC
    Boeing 707 (-300 Series and -400 Series)......................  20,000 FC
    Boeing 720....................................................  30,000 FC
Bombardier:
    CL-44D4 and CL-44J............................................  20,000 FC
    BD-700........................................................  15,000 FH
Bristol Aeroplane Company:
    Britannia 305.................................................  10,000 FC
British Aerospace Airbus, Ltd.:
    BAC 1-11 (all models).........................................  85,000 FC
British Aerospace (Commercial Aircraft) Ltd.:
    Armstrong Whitworth Argosy A.W. 650 Series 101................  20,000 FC
BAE Systems (Operations) Ltd.:
    BAe 146-100A (all models).....................................  50,000 FC
    BAe 146-200-07................................................  50,000 FC
    BAe 146-200-07 Dev............................................  50,000 FC
    BAe 146-200-11................................................  50,000 FC
    BAe 146-200-07A...............................................  47,000 FC
    BAe 146-200-11 Dev............................................  43,000 FC

    BAe 146-300 (all models)......................................  40,000 FC
    Avro 146-RJ70A (all models)...................................  40,000 FC
    Avro 146-RJ85A and 146-RJ100A (all models)....................  50,000 FC
D & R Nevada, LLC:
    Convair Model 22..............................................  1,000 FC/1,000 FH
    Convair Model 23M.............................................  1,000 FC/1,000 FH
deHavilland Aircraft Company, Ltd.:
    D.H. 106 Comet 4C.............................................  8,000 FH
Gulfstream:
    GV............................................................  40,000 FH
    GV-SP.........................................................  40,000 FH
Ilyushin Aviation Complex:
    IL-96T........................................................  10,000 FC/30,000 FH
Lockheed:
    300-50A01 (USAF C 141A).......................................  20,000 FC
----------------------------------------------------------------------------------------------------------------

PART 129--OPERATIONS: FOREIGN AIR CARRIERS AND FOREIGN OPERATORS OF
U.S.-REGISTERED AIRCRAFT ENGAGED IN COMMON CARRIAGE

0
9. The authority citation for part 129 continues to read:

    Authority: 49 U.S.C. 1372, 40113, 40119, 44101, 44701-44702,
44705, 44709-44711, 44713, 44716-44717, 44722, 44901-44904, 44906,
44912, 46105, Pub. L. 107-71 sec. 104.

0
10. Add new Sec.  129.115 to read as follows:

Sec.  129.115  Limit of validity.

    (a) Applicability. This section applies to foreign air carriers or
foreign persons operating any U.S.-registered transport category,
turbine-powered airplane with a maximum takeoff gross weight greater
than 75,000 pounds and a type certificate issued after January 1, 1958,
regardless of whether the maximum takeoff gross weight is a result of
an original type certificate or a later design change. This section
also applies to foreign air carriers or foreign persons operating any
other U.S.-registered transport category, turbine-powered airplane with
a type certificate issued after January 1, 1958, regardless of the
maximum takeoff gross weight, for which a limit of validity of the
engineering data that supports the structural maintenance program
(hereafter referred to as LOV) is required in accordance with Sec.
25.571 or Sec.  26.21 of this chapter after January 14, 2011.
    (b) Limit of validity. No foreign air carrier or foreign person may
operate a U.S.-registered airplane identified in paragraph (a) of this
section after the applicable date identified in Table 1 of this
section, unless an Airworthiness Limitations section (ALS) approved
under Appendix H to part 25 or Sec.  26.21 of this chapter is
incorporated into its maintenance program. The ALS must--
    (1) Include an LOV approved under Sec.  25.571 or Sec.  26.21 of
this chapter, as applicable, except as provided in paragraph (f) of
this section; and
    (2) Be clearly distinguishable within its maintenance program.
    (c) Operation of airplanes excluded from Sec.  26.21. No
certificate holder may operate an airplane identified in Sec.  26.21(g)
of this chapter after July 14, 2013, unless an ALS approved under
Appendix H to part 25 or Sec.  26.21 of this chapter is incorporated
into its maintenance program. The ALS must--
    (1) Include an LOV approved under Sec.  25.571 or Sec.  26.21 of
this chapter, as applicable, except as provided in paragraph (f) of
this section; and
    (2) Be clearly distinguishable within its maintenance program
    (d) Extended limit of validity. No foreign air carrier or foreign
person may operate an airplane beyond the LOV or extended LOV specified
in paragraph (b)(1), (c), (d), or (f) of this section, as applicable,
unless the following conditions are met:
    (1) An ALS must be incorporated into its maintenance program that--
    (i) Includes an extended LOV and any widespread fatigue damage
airworthiness limitation items (ALIs) approved under Sec.  26.23 of
this chapter; and
    (ii) Is approved under Sec.  26.23 of this chapter;
    (2) The extended LOV and the airworthiness limitation items
pertaining to widespread fatigue damage must be clearly distinguishable
within its maintenance program.
    (e) Principal Maintenance Inspector approval. Foreign air carriers
or foreign persons must submit the maintenance program revisions
required by paragraphs (b), (c), and (d) of this section to the
Principal Maintenance Inspector or Flight Standards International Field
Office for review and approval.
    (f) Exception. For any airplane for which an LOV has not been
approved as of the applicable compliance date specified in paragraph
(c) or Table 1 of this section, instead of including an approved LOV in
the ALS, an operator must include the applicable default LOV specified
in Table 1 or Table 2 of this section, as applicable, in the ALS.

                                   Table 1--Airplanes Subject to Sec.   26.21
----------------------------------------------------------------------------------------------------------------
                                                    Compliance date--
                 Airplane model                   months after January     Default LOV [flight  cycles (FC) or
                                                        14, 2011                    flight hours (FH)]
----------------------------------------------------------------------------------------------------------------
Airbus--Existing \1\ Models Only:
    A300 B2-1A, B2-1C, B2K-3C, B2-203..........  30....................  48,000 FC
    A300 B4-2C, B4-103.........................  30....................  40,000 FC
    A300 B4-203................................  30....................  34,000 FC
    A300-600 Series............................  30....................  30,000 FC/67,500 FH

    A310-200 Series............................  30....................  40,000 FC/60,000 FH
    A310-300 Series............................  30....................  35,000 FC/60,000 FH
    A318 Series................................  60....................  48,000 FC/60,000 FH
    A319 Series................................  60....................  48,000 FC/60,000 FH
    A320-100 Series............................  60....................  48,000 FC/48,000 FH
    A320-200 Series............................  60....................  48,000 FC/60,000 FH
    A321 Series................................  60....................  48,000 FC/60,000 FH
    A330-200, -300 Series (except WV050 family)  60....................  40,000 FC/60,000 FH
     (non enhanced).
    A330-200, -300 Series WV050 family           60....................  33,000 FC/100,000 FH
     (enhanced).
    A330-200 Freighter Series..................  60....................  See NOTE.
    A340-200, -300 Series (except WV 027 and     60....................  20,000 FC/80,000 FH
     WV050 family) (non enhanced).
    A340-200, -300 Series WV 027 (non enhanced)  60....................  30,000 FC/60,000 FH
    A340-300 Series WV050 family (enhanced)....  60....................  20,000 FC/100,000 FH
    A340-500, -600 Series......................  60....................  16,600 FC/100,000 FH
    A380-800 Series............................  72....................  See NOTE.
Boeing--Existing \1\ Models Only:
    717........................................  60....................  60,000 FC/60,000 FH
    727 (all series)...........................  30....................  60,000 FC
    737 (Classics): 737-100, -200, -200C, -300,  30....................  75,000 FC
     -400, -500.
    737 (NG): 737-600, -700, -700C, -800, -900,  60....................  75,000 FC
     -900ER.
    747 (Classics): 747-100, -100B, -100B SUD, - 30....................  20,000 FC
     200B, -200C, -200F, -300, 747SP, 747SR.
    747-400: 747-400, -400D, -400F.............  60....................  20,000 FC
    757........................................  60....................  50,000 FC
    767........................................  60....................  50,000 FC
    777-200, -300..............................  60....................  40,000 FC
    777-200LR, 777-300ER.......................  72....................  40,000 FC
    777F.......................................  72....................  11,000 FC
Bombardier--Existing \1\ Models Only:
    CL-600: 2D15 (Regional Jet Series 705),      72....................  60,000 FC
     2D24 (Regional Jet Series 900).
Embraer--Existing \1\ Models Only:
    ERJ 170....................................  72....................  See NOTE.
    ERJ 190....................................  72....................  See NOTE.
Fokker--Existing \1\ Models Only:
    F.28 Mark 0070, Mark 0100..................  30....................  90,000 FC
Lockheed--Existing \1\ Models Only:
    L-1011.....................................  30....................  36,000 FC
    188........................................  30....................  26,600 FC
    382 (all series)...........................  30....................  20,000 FC/50,000 FH
McDonnell Douglas--Existing \1\ Models Only:
    DC-8, -8F..................................  30....................  50,000 FC/50,000 FH
    DC-9 (except for MD-80 series).............  30....................  100,000 FC/100,000 FH
    MD-80 (DC-9-81, -82, -83, -87, MD-88)......  30....................  50,000 FC/50,000 FH
    MD-90......................................  60....................  60,000 FC/90,000 FH
    DC-10-10, -15..............................  30....................  42,000 FC/60,000 FH
    DC-10-30, -40, -10F, -30F, -40F............  30....................  30,000 FC/60,000 FH
    MD-10-10F..................................  60....................  42,000 FC/60,000 FH
    MD-10-30F..................................  60....................  30,000 FC/60,000 FH
    MD-11, MD-11F..............................  60....................  20,000 FC/60,000 FH
Maximum Takeoff Gross Weight Changes...........  30, or within 12        Not applicable.
                                                  months after the LOV
                                                  is approved, or
                                                  before operating the
                                                  airplane, whichever
                                                  occurs latest.
All airplanes whose maximum takeoff gross
 weight has been decreased to 75,000 pounds or
 below after January 14, 2011 or increased to
 greater than 75,000 pounds at any time by an
 amended type certificate or supplemental type
 certificate.
All Other Airplane Models (TCs and amended TCs)  72, or within 12        Not applicable.
 not Listed in Table 2.                           months after the LOV
                                                  is approved, or
                                                  before operating the
                                                  airplane, whichever
                                                  occurs latest.
----------------------------------------------------------------------------------------------------------------
\1\ Type certificated as of January 14, 2011.

    Note: Airplane operation limitation is stated in the
Airworthiness Limitation section.

                                  Table 2--Airplanes Excluded from Sec.   26.21
----------------------------------------------------------------------------------------------------------------
                                                                     Default LOV [flight  cycles (FC) or flight
                          Airplane model                                             hours (FH)]
----------------------------------------------------------------------------------------------------------------
Airbus:
    Caravelle.....................................................  15,000 FC/24,000 FH
Avions Marcel Dassault:
    Breguet Aviation Mercure 100C.................................  20,000 FC/16,000 FH
Boeing:
    Boeing 707 (-100 Series and -200 Series)......................  20,000 FC
    Boeing 707 (-300 Series and -400 Series)......................  20,000 FC
    Boeing 720....................................................  30,000 FC
Bombardier:
    CL-44D4 and CL-44J............................................  20,000 FC
    BD-700........................................................  15,000 FH
Bristol Aeroplane Company:
    Britannia 305.................................................  10,000 FC
British Aerospace Airbus, Ltd.:
    BAC 1-11 (all models).........................................  85,000 FC
British Aerospace (Commercial Aircraft) Ltd.:
    Armstrong Whitworth Argosy A.W. 650 Series 101................  20,000 FC
BAE Systems (Operations) Ltd.:
    BAe 146-100A (all models).....................................  50,000 FC
    BAe 146-200-07................................................  50,000 FC
    BAe 146-200-07 Dev............................................  50,000 FC
    BAe 146-200-11................................................  50,000 FC
    BAe 146-200-07A...............................................  47,000 FC
    BAe 146-200-11 Dev............................................  43,000 FC
    BAe 146-300 (all models)......................................  40,000 FC
    Avro 146-RJ70A (all models)...................................  40,000 FC
    Avro 146-RJ85A and 146-RJ100A (all models)....................  50,000 FC
D & R Nevada, LLC:
    Convair Model 22..............................................  1,000 FC/1,000 FH
    Convair Model 23M.............................................  1,000 FC/1,000 FH
deHavilland Aircraft Company, Ltd.:
    D.H. 106 Comet 4C.............................................  8,000 FH
Gulfstream:
    GV............................................................  40,000 FH
    GV-SP.........................................................  40,000 FH
Ilyushin Aviation Complex:
    IL-96T........................................................  10,000 FC/30,000 FH
Lockheed:
    300-50A01 (USAF C 141A).......................................  20,000 FC
----------------------------------------------------------------------------------------------------------------

    Issued in Washington, DC, on October 28, 2010.
J. Randolph Babbitt,
Administrator.
[FR Doc. 2010-28363 Filed 11-12-10; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 76, Number 82 (Thursday, April 28, 2011)]
[Notices]
[Pages 23805-23806]
[FR Doc No: 2011-10271]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings 1

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

    Docket Numbers: EC11-73-000.
    Applicants: Standard Binghamton LLC, Alliance Energy, New York LLC,
Standard Power LLC.
    Description: Application of Standard Binghamton LLC, et al.
    Filed Date: 04/22/2011.
    Accession Number: 20110422-5044.
    Comment Date: 5 p.m. Eastern Time on Friday, May 13, 2011.

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

    Docket Numbers: ER11-3048-000.
    Applicants: ISO New England Inc.
    Description: ISO New England Inc.'s additional information
regarding the Installed Capacity Requirement Values for the 2014/2015
Capability Year Forward Capacity Auction, pursuant to the FERC
Deficiency Letter dated April 14.
    Filed Date: 04/20/2011.
    Accession Number: 20110420-5186.
    Comment Date: 5 p.m. Eastern Time on Friday, April 29, 2011.

    Docket Numbers: ER11-3048-000.
    Applicants: ISO New England Inc.
    Description: ISO New England Inc.'s Motion for Leave to File One
Day Out-of-Time Supporting Materials, Including CEII, in Response to
Deficiency Letter.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5167.
    Comment Date: 5 p.m. Eastern Time on Friday, April 29, 2011.

    Docket Numbers: ER11-3414-000.
    Applicants: Blue Canyon Windpower VI LLC.
    Description: Blue Canyon Windpower VI LLC submits tariff filing per
35.12: Blue Canyon Windpower VI LLC MBR Tariff to be effective 6/20/
2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5142.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

    Docket Numbers: ER11-3415-000.
    Applicants: Midwest Independent Transmission System Operator, Inc.
    Description: Midwest Independent Transmission System Operator, Inc.
submits tariff filing per 35.13(a)(2)(iii): 04-21-11 Exit Fee Agmt to
be effective 5/31/2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5143.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

    Docket Numbers: ER11-3416-000.
    Applicants: Alta Wind VI, LLC.
    Description: Alta Wind VI, LLC submits tariff filing per 35.12:
Alta Wind VI, LLC MBR Tariff to be effective 5/16/2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5147.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

    Docket Numbers: ER11-3417-000.
    Applicants: Alta Wind VIII, LLC.
    Description: Alta Wind VIII, LLC submits tariff filing per 35.12:
Alta Wind VIII, LLC MBR Tariff to be effective 5/16/2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5148.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

    Docket Numbers: ER11-3418-000.
    Applicants: Xoom Energy, LLC.
    Description: Xoom Energy, LLC submits tariff filing per 35.12: Xoom
Energy, LLC Application for Market-Based Rates to be effective 5/23/
2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5155.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

    Docket Numbers: ER11-3419-000.
    Applicants: South Carolina Electric & Gas Company.
    Description: South Carolina Electric & Gas Company submits tariff
filing per 35.13(a)(2)(iii): FERC Electric Rate Schedule No. 60 to be
effective 4/21/2011.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5189.
    Comment Date: 5 p.m. Eastern Time on Thursday, May 12, 2011.

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

    Docket Numbers: ES11-22-000.
    Applicants: Midwest Independent Transmission System Operator, Inc.
    Description: Second Amendment to Application of the Midwest
Independent Transmission System Operator, Inc. under Section 204 of the
Federal Power Act to Issue Securities.
    Filed Date: 04/21/2011.
    Accession Number: 20110421-5191.
    Comment Date: 5 p.m. Eastern Time on Monday, May 2, 2011.

    Any person desiring to intervene or to protest in any of the above
proceedings 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 p.m. Eastern time on the specified comment
date. It is not necessary to separately intervene again in a subdocket
related to a compliance filing if you have previously intervened in the
same docket. 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. Anyone filing a motion to
intervene or protest must serve a copy of that document on the
Applicant. In reference to filings initiating a new proceeding,
interventions or protests submitted on or before the comment deadline
need not be served on persons other than the Applicant.
    As it relates to any qualifying facility filings, the notices of
self-certification [or self-recertification] listed above, do not
institute a proceeding regarding qualifying facility status. A notice
of self-certification [or self-recertification] simply provides
notification that the entity making the filing has determined the
facility named in the notice meets the applicable criteria to be a
qualifying facility. Intervention and/or protest do not lie in dockets
that are qualifying facility self-certifications or self-
recertifications. Any person seeking to challenge such qualifying
facility status may do so by filing a motion pursuant to 18 CFR
292.207(d)(iii). Intervention and protests may be filed in response to
notices of qualifying facility dockets other than self-certifications
and self-recertifications.
    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 St. NE., Washington, DC 20426.
    The filings in the above proceedings 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 e-mail notification
when a document is added to a subscribed dockets(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: April 22, 2011.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2011-10271 Filed 4-27-11; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 87, Number 228 (Tuesday, November 29, 2022)]
[Rules and Regulations]
[Page 73247]
[FR Doc No: 2022-25930]

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

DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 100

[Docket No. USCG-2022-0785]

Special Local Regulation; Marine Events Within the Eleventh Coast
Guard District--Mission Bay Parade of Lights.

AGENCY: Coast Guard, DHS.

ACTION: Notification of enforcement of regulation.

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

SUMMARY: The Coast Guard will enforce the special local regulation on
the waters of Mission Bay, CA, during the Mission Bay Parade of Lights
on December 10, 2022. This special local regulation is necessary to
provide for the safety of the participants, crew, sponsor vessels of
the event, and general users of the waterway. During the enforcement
period, persons and vessels are prohibited from entering into,
transiting through, or anchoring within this regulated area unless
authorized by the Captain of the Port Sector San Diego or their
designated representative.

DATES: The regulations in 33 CFR 100.1101 for the location described in
Item 6 in Table 1 to Sec.  100.1101, will be enforced from 5:30 p.m.
through 8 p.m. on December 10, 2022.

FOR FURTHER INFORMATION CONTACT: If you have questions about this
notification of enforcement, call or email Lieutenant Junior Grade
Shera Kim, Waterways Management, U.S. Coast Guard Sector San Diego, CA;
telephone<PHONE_NUMBER>, email [email protected].

SUPPLEMENTARY INFORMATION: The Coast Guard will enforce the special
local regulations in 33 CFR 100.1101 for the location identified in
Item No. 6 in Table 1 to Sec.  100.1101, from 5:30 p.m. until 8 p.m. on
December 10, 2022, for the Mission Bay Parade of Lights in Mission Bay,
CA. This action is being taken to provide for the safety of life on the
navigable waterways during the event. Our regulation for recurring
marine events in the San Diego Captain of the Port Zone, Sec.
100.1101, Item No. 6 in table 1 to Sec.  100.1101, specifies the
location of the regulated area for the Mission Bay Parade of Lights,
which encompasses portions of Mission Bay. Under the provisions of
Sec.  100.1101, persons and vessels are prohibited from entering into,
transiting through, or anchoring within this regulated area unless
authorized by the Captain of the Port, or his designated
representative. The Coast Guard may be assisted by other Federal,
State, or local law enforcement agencies in enforcing this regulation.
    In addition to this document in the Federal Register, the Coast
Guard will provide the maritime community with advance notification of
this enforcement period via the Local Notice to Mariners and marine
information broadcasts.

    Dated: November 22, 2022.
J.W. Spitler,
Captain, U.S. Coast Guard, Captain of the Port Sector San Diego.
[FR Doc. 2022-25930 Filed 11-28-22; 8:45 am]
BILLING CODE 9110-04-P


http://o-ring.info/en/datasheets/fkm-genuine-viton/		downloaded 8/15/06

FKM / Genuine Viton® - Datasheets

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FKM 514002

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 Genuine Viton® 514301 (73kB)  	FKM	80°	Standard compound

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 FKM 80 compound 514301 (182kB)  	FKM	80°	Standard compound

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 Genuine Viton® 514204

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[Federal Register Volume 83, Number 213 (Friday, November 2, 2018)]
[Notices]
[Page 55210]
[FR Doc No: 2018-24148]

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

SECURITIES AND EXCHANGE COMMISSION

Sunshine Act Meeting; Cancellation

FEDERAL REGISTER CITATION OF PREVIOUS ANNOUNCEMENT: 83 FR 54411,
October 29, 2018

PREVIOUSLY ANNOUNCED TIME AND DATE OF THE MEETING: Wednesday, October
31, 2018 at 10:00 a.m.

CHANGES IN THE MEETING: The Open Meeting scheduled for Wednesday,
October 31, 2018 at 10:00 a.m., has been cancelled.

CONTACT PERSON FOR MORE INFORMATION: For further information and to
ascertain what, if any, matters have been added, deleted or postponed,
please contact Brent J. Fields of the Office of the Secretary at (202)
551-5400.

    Dated: October 31, 2018.
Brent J. Fields,
Secretary.
[FR Doc. 2018-24148 Filed 10-31-18; 4:15 pm]
 BILLING CODE 8011-01-P