[Federal Register Volume 82, Number 91 (Friday, May 12, 2017)]
[Notices]
[Page 22133]
[FR Doc No: 2017-09674]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Notice of Effectiveness of Exempt Wholesale Generator Status

------------------------------------------------------------------------
                                                    Docket Nos.
------------------------------------------------------------------------
Flat Top Wind I, LLC....................  EG17-56-000
Solar Star Oregon II, LLC...............  EG17-57-000
Whitney Point Solar, LLC................  EG17-58-000
Westside Solar, LLC.....................  EG17-59-000
RE Tranquillity 8 Amarillo LLC..........  EG17-60-000
RE Tranquillity 8 Azul LLC..............  EG17-61-000
RE Tranquillity 8 Rojo LLC..............  EG17-62-000
RE Tranquillity 8 Verde LLC.............  EG17-63-000
Chambersburg Energy, LLC................  EG17-64-000
Gans Energy, LLC........................  EG17-65-000
Hunlock Energy, LLC.....................  EG17-66-000
Springdale Energy, LLC..................  EG17-67-000
Bath County Energy, LLC.................  EG17-68-000
Paulding Wind Farm IV LLC...............  EG17-69-000
Blue Summit Storage, LLC................  EG17-70-000
------------------------------------------------------------------------

    Take notice that during the month of April 2017, the status of the
above-captioned entities as Exempt Wholesale Generators became
effective by operation of the Commission's regulations. 18 CFR 366.7(a)
(2016).

    Dated: May 8, 2017.
Kimberly D. Bose,
Secretary.
[FR Doc. 2017-09674 Filed 5-11-17; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 84, Number 236 (Monday, December 9, 2019)]
[Rules and Regulations]
[Pages 67174-67176]
[FR Doc No: 2019-26401]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0671; Product Identifier 2019-NM-080-AD; Amendment
39-19788; AD 2019-22-09]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 787-8 airplanes. This AD was prompted
by a report of fatigue cracking in the lug root radius of a main
landing gear (MLG) aft hanger link lug fitting. This AD requires
repetitive surface high frequency eddy current (HFEC) inspections of
the left and right side MLG aft hanger link lug fitting for cracking,
and applicable on-condition actions. The FAA is issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective January 13, 2020.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 13,
2020.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0671.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0671; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Greg Rutar, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 787-8 airplanes. The NPRM published in the Federal
Register on September 6, 2019 (84 FR 46898). The NPRM was prompted by a
report of fatigue cracking in the lug root radius of an MLG aft hanger
link lug fitting. The NPRM proposed to require repetitive surface HFEC
inspections of the left and right side MLG aft hanger link lug fitting
for cracking, and applicable on-condition actions.
    The FAA is issuing this AD to address fatigue cracking in the left
and right side MLG aft hanger link lug fittings. This condition, if not
addressed, could result in undetected fatigue cracks that can grow and
weaken the primary structure such that it cannot sustain limit load,
which could adversely affect the structural integrity of the airplane.

Comments

    The FAA gave the public the opportunity to participate in
developing this final rule. The FAA has considered the comments
received.

Support for the NPRM

    The Air Line Pilots Association, International (ALPA), Boeing, and
Austin Russo expressed support for the NPRM.

Conclusion

    The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:

     Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin B787-81205-
SB530070-00 RB, Issue 001, dated August 31, 2018. This service
information describes procedures for repetitive surface HFEC
inspections of the left and right side MLG aft hanger link lug fitting
at the lug root radius for cracking, and applicable on-condition
actions. On-condition actions include repair. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 7 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Repetitive HFEC inspections.....  3 work-hours x $85               $0   $255 per inspection  $1,785 per
                                   per hour = $255                       cycle.               inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this AD.
    According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in the cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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) Will not affect intrastate aviation in Alaska, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13   [Amended]

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

2019-22-09 The Boeing Company: Amendment 39-19788; Docket No. FAA-
2019-0671; Product Identifier 2019-NM-080-AD.

(a) Effective Date

    This AD is effective January 13, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, as identified in Boeing Alert
Requirements Bulletin B787-81205-SB530070-00 RB, Issue 001, dated
August 31, 2018.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of fatigue cracking in the lug
root radius of a main landing gear (MLG) aft hanger link lug
fitting. The FAA is issuing this AD to address fatigue cracking in
the left and right side MLG aft hanger link lug fittings. This
condition, if not addressed, could result in undetected fatigue
cracks that can grow and weaken the primary structure such that it
cannot sustain limit load, which could adversely affect the
structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin B787-81205-SB530070-00 RB, Issue 001,
dated August 31, 2018, do all applicable actions identified in, and
in accordance with, the Accomplishment Instructions of Boeing Alert
Requirements Bulletin B787-81205-SB530070-00 RB, Issue 001, dated
August 31, 2018.

    Note 1 to paragraph (g):  Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service

Bulletin B787-81205-SB530070-00, Issue 001, dated August 31, 2018,
which is referred to in Boeing Alert Requirements Bulletin B787-
81205-SB530070-00 RB, Issue 001, dated August 31, 2018.

(h) Exceptions to Service Information Specifications

    Where Boeing Alert Requirements Bulletin B787-81205-SB530070-00
RB, Issue 001, dated August 31, 2018, specifies contacting Boeing
for repair instructions: This AD requires doing the repair using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (j) of this AD. Information may be
emailed to<EMAIL_ADDRESS>    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.

(j) Related Information

    For more information about this AD, contact Greg Rutar,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>
(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Requirements Bulletin B787-81205-SB530070-00
RB, Issue 001, dated August 31, 2018
    (ii) [Reserved]
    (3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email<EMAIL_ADDRESS>or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on November 12, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-26401 Filed 12-6-19; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 84, Number 239 (Thursday, December 12, 2019)]
[Rules and Regulations]
[Pages 67851-67854]
[FR Doc No: 2019-26734]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0494; Product Identifier 2019-NM-051-AD; Amendment
39-19801; AD 2019-23-07]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes.
This AD was prompted by reports that the nose landing gear (NLG)
retracted on the ground, with weight on the airplane's wheels, due to
the incorrect installation of an NLG downlock pin in the apex pin inner
bore of the NLG lock link assembly. This AD requires installing an
insert to prevent installation of the pin in the incorrect location.
The FAA is issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective January 16, 2020.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 16,
2020.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0494.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0494; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 787-8, 787-9, and 787-10 airplanes. The NPRM published in
the Federal Register on July 23, 2019 (84 FR 35352). The NPRM was
prompted by reports that the NLG retracted on the ground, with weight
on the airplane's wheels, due to the incorrect installation of an NLG
downlock pin in the apex pin inner bore of the NLG lock link assembly.
The NPRM proposed to require installing an insert to prevent
installation of the pin in the incorrect location.
    The FAA is issuing this AD to address the NLG downlock pin being
incorrectly installed in the apex pin inner bore of the NLG lock link
assembly, which could result in the NLG retracting on the ground,
possibly causing serious injuries to personnel and passengers and
substantial damage to the airplane.

Comments

    The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.

Request To Revise Applicability of the Proposed AD

    American Airlines (AAL) requested that the FAA revise the
applicability of the AD to specify the affected part numbers of the NLG
lock link assembly rather than the affected airplanes because the
affected parts may be swapped between airplanes. AAL noted that
paragraph A.2. of Boeing Requirements Bulletin B787-81205-SB320040-00
RB, Issue 001, dated March 12, 2019, specifies to identify, modify, and
part mark the spares. AAL suggested that once the apex bin inner bore
insert is installed in the NLG lock link assembly in production, the
NLG lock link assembly part number should also change. AAL requested
that, should the FAA not revise the applicability of the proposed AD to
affected part numbers, the applicability of the proposed AD be revised
to include all Model 787 airplanes rather than only the airplanes
specified in Boeing Requirements Bulletin B787-81205-SB320040-00 RB,
Issue 001, dated March 12, 2019. AAL asserted that the unsafe condition
applies to all airplanes.
    The FAA disagrees with the request to revise the applicability of
this AD. This AD does not require operators to identify, modify, or
part mark their spares. Paragraph (g) of this AD specifies to
accomplish the actions in accordance with the Accomplishment
Instructions of Boeing Requirements Bulletin B787-81205-SB320040-00 RB,
Issue 001, dated March 12, 2019, and does not specify to accomplish
actions in accordance with paragraph A.2. of Boeing Requirements
Bulletin B787-81205-SB320040-00 RB, Issue 001, dated March 12, 2019.
Therefore, the FAA has determined that it is appropriate for this AD to
apply to Boeing Model 787-8, 787-9, 787-10 airplanes, line numbers 6
through 848 inclusive, as specified in Boeing Requirements Bulletin
B787-81205-SB320040-00 RB, Issue 001, dated March 12, 2019. Only these
airplanes need to have the apex bin inner bore insert installed in
order to address the identified unsafe condition.
    Regarding AAL's request to revise the applicability to all Model
787 airplanes, Boeing will incorporate the apex pin inner bore insert
as part of the airplane type design at line number 849 and subsequent.
At that time, the NLG lock link assembly will change part numbers, and
the airplane type design will be changed as a result. If an operator
installs an NLG lock link assembly of a different part number than what
is defined as airplane type design, then the airplane would be out of
compliance. Consequently, all airplanes will be required to have the
apex pin inner bore insert installed in the NLG lock link assembly. No
changes have been made to the applicability of this AD.

Requests To Change NLG Lock Link Assembly Part Number Post-Installation

    AAL requested that the FAA revise the proposed AD to add a
requirement that the NLG lock link assembly part number be changed upon
installing the apex pin inner bore insert. AAL reasoned that the NLG
lock link would be modified as an assembly and that, even though the
airplane may be in the proper configuration, there would be no
documentation to support the modification having been accomplished. AAL
also noted that there is no consistent procedure for marking the change
identification of the NLG lock link assembly amongst operators, which
could lead to configuration issues when parts are exchanged between
airlines. AAL suggested that operators should be informed on how Boeing
is marking the change identification of the NLG lock link assemblies
that are in production.
    The FAA does not agree with the request. Boeing Requirements
Bulletin B787-81205-SB320040-00 RB, Issue 001, dated March 12, 2019,
identifies the Boeing assigned NLG lock link assembly part number prior
to installation of the apex pin inner bore insert and indicates that
there is no new Boeing part number for the changed NLG lock link
assembly. Boeing Service Bulletin B787-81205-SB320040-00, Issue 001,
dated March 12, 2019 (which is referred to in Boeing Requirements
Bulletin B787-81205-SB320040-00 RB, Issue 001, dated March 12, 2019),
specifies to mark the change identification of the NLG lock link
assembly to indicate the apex pin bore insert has been installed.
Operators are not required to change the identification as specified in
Boeing Service Bulletin B787-81205-SB320040-00, Issue 001, dated March
12, 2019. Each operator has the latitude to identify the installed part
that is consistent with their internal operating procedures. Operators
may contact Boeing for information on how production airplanes are
being marked for change identification of the NLG lock link assembly.
The AD has not been changed in this regard.

Request To Allow Alternative Method of Compliance (AMOC)

    United Airlines (UAL) requested that the FAA issue an AMOC that
would allow the apex pin inner bore to be completely filled with
sealant. UAL stated that it recognized the possible unsafe condition of
the NLG downlock pin being incorrectly installed in the apex pin inner
bore of the NLG lock link assembly, and plugged the apex pin inner bore
with sealant as a preventive modification. UAL explained that it
applied this modification to its entire fleet prior to the issue of
Boeing Requirements Bulletin B787-81205-SB320040-00 RB, Issue 001,
dated March 12, 2019, and it proposed to add the apex pin inner bore
insert at the time of the next component overhaul to maintain
configuration control.
    The FAA disagrees with the request. The FAA and Boeing are
concerned that filling the apex pin inner bore with sealant is not a
long term solution because the sealant may deteriorate and degrade over
the life of the landing gear. The FAA has determined that the proposed
apex pin inner bore insert is a more robust solution that will address
the unsafe condition and withstand the harsh environment of the NLG.
The AD has not been changed in this regard. However, if any person has
data that would justify an alternative solution, that person may
request approval of an AMOC under the provisions of paragraph (i) of
this AD.

Requests To Identify a Certain Step as Non-RC (Required for Compliance)

    UAL requested that the FAA identifies the step that specifies to
mark the change identification of the NLG lock link assembly as Non-RC.
UAL predicted that each operator will implement their own unique change
identification method and reasoned that its own internal controls
clearly identify its compliance with the requirements and
accomplishment of the modification, which would negate the need to
require change identification of the NLG lock link assembly.
    The FAA agrees to clarify. The change identification of the NLG
lock link assembly is not required for compliance. The change
identification in the Requirements Bulletin is a ``refer to''
procedure. As stated in a note under the Accomplishment Instructions of
Boeing Requirements Bulletin B787-81205-SB320040-00, Issue 001, dated
March 12, 2019, procedures marked as ``refer to'' may be deviated from
using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. The AD has
not been changed in this regard.

Request To Clarify NLG Retraction Incident

    Boeing requested that the FAA clarify the Discussion of the NPRM to
state that the NLG retraction incident that took place in March of 2016
was caused by the lack of an NLG downlock pin being installed on the
NLG, not by the installation of an NLG downlock pin in an incorrect
location. Boeing conceded that the event was an inadvertent NLG
retraction, but maintained that the event was not due to the NLG
downlock pin being installed incorrectly.
    We partially agree with the request to change the Discussion
section of the NPRM. As specified above, the design approval holder
noted in their investigation that the inadvertent NLG retraction in
March of 2019 was caused by a missing NLG downlock pin. However, we
also received a safety recommendation submitted by Aviation Technical
Services that indicated the probable cause was that the NLG downlock
pin was installed in the wrong location for both incidents referenced
in the Discussion section of the NPRM.
    We note that we have received conflicting information about the
March 2016 incident and what was the probable cause of the incident.
However, we have not changed this final rule in this regard because the
Discussion section of the NPRM is not restated in the final rule.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Requirements Bulletin B787-81205-SB320040-
00 RB, Issue 001, dated March 12, 2019. The service information
describes procedures for installing an insert into the apex pin inner
bore of the NLG lock link assembly to prevent the NLG downlock pin from
being inserted in the incorrect location. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD would affect 73 airplanes of U.S.
registry. The agency estimates the following costs to comply with this
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Install insert......................  2 work-hours x $85 per           $1,820           $1,990         $145,270
                                       hour = $170.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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) Will not affect intrastate aviation in Alaska, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

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

2019-23-07 The Boeing Company: Amendment 39-19801; Docket No. FAA-
2019-0494; Product Identifier 2019-NM-051-AD.

(a) Effective Date

    This AD is effective January 16, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8, 787-9, and
787-10 airplanes, certificated in any category, as identified in
Boeing Requirements Bulletin B787-81205-SB320040-00 RB, Issue 001,
dated March 12, 2019.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports that the nose landing gear (NLG)
retracted on the ground, with weight on the airplane's wheels, due
to the incorrect installation of an NLG downlock pin in the apex pin
inner bore of the NLG lock link assembly. The FAA is issuing this AD
to address the NLG downlock pin being incorrectly installed in the
apex pin inner bore of the NLG lock link assembly, which could
result in the NLG retracting on the ground, possibly causing serious
injuries to personnel and passengers and substantial damage to the
airplane.

(f) Compliance

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

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Requirements Bulletin B787-81205-SB320040-00 RB, Issue 001, dated
March 12, 2019, do all applicable actions identified in, and in
accordance with, the Accomplishment Instructions of Boeing
Requirements Bulletin B787-81205-SB320040-00 RB, Issue 001, dated
March 12, 2019.
    Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Service Bulletin B787-
81205-SB320040-00, Issue 001, dated March 12, 2019, which is
referred to in Boeing Requirements Bulletin B787-81205-SB320040-00
RB, Issue 001, dated March 12, 2019.

(h) Exceptions to Service Information Specifications

    For purposes of determining compliance with the requirements of
this AD: Where Boeing Requirements Bulletin B787-81205-SB320040-00
RB, Issue 001, dated March 12, 2019, uses the phrase ``the Issue 001
date of Requirements Bulletin B787-81205-SB320040-00 RB,'' this AD
requires using ``the effective date of this AD.''

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (j) of this AD. Information may be
emailed to<EMAIL_ADDRESS>    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.

(j) Related Information

    For more information about this AD, contact Allen
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des

Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Requirements Bulletin B787-81205-SB320040-00 RB,
Issue 001, dated March 12, 2019.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email<EMAIL_ADDRESS>or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on December 2, 2019.
John Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-26734 Filed 12-11-19; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 86, Number 170 (Tuesday, September 7, 2021)]
[Rules and Regulations]
[Pages 49903-49904]
[FR Doc No: 2021-19245]

========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.

========================================================================

Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 /
Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0334; Project Identifier MCAI-2020-01662-T;
Amendment 39-21686; AD 2021-17-03]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

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

SUMMARY: The FAA is correcting an airworthiness directive (AD) that was
published in the Federal Register. That AD applies to certain Airbus
SAS Model A318-111, -112, and -122 airplanes; Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -
212, -214, -231, -232, and -233 airplanes. As published, the AD number
specified in the preamble and regulatory text is incorrect. This
document corrects this error. In all other respects, the original
document remains the same.

DATES: This correction is effective October 5, 2021.
    The effective date of AD 2021-17-03 remains October 5, 2021.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 5,
2021 (86 FR 48485, August 31, 2021).

ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone
+49 221 8999 000; email<EMAIL_ADDRESS>internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at https://ad.easa.europa.eu. You may view this IBR material at the
FAA, Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>. It is also available in
the AD docket at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0334.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov under
Docket No. FAA-2021-0334; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>;
email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: AD 2021-17-03, Amendment 39-21686 (86 FR
48485, August 31, 2021) (AD 2021-17-03), requires repetitive
inspections for cracking at the left- (LH) and right-hand (RH) sides of
the fuselage skin at certain frames, and repair if necessary, as
specified in European Union Aviation Safety Agency (EASA) AD 2020-0280,
dated December 14, 2020 (EASA AD 2020-0280). That AD applies to certain
Airbus SAS Model A318-111, -112, and -122 airplanes; Model A319-111, -
112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-
211, -212, -214, -231, -232, and -233 airplanes.

Need for the Correction

    As the AD was published, the AD number specified in the preamble
and regulatory text is incorrect. AD 2021-17-03 incorrectly identified
the AD number as 2017-17-03. The correct AD number for this AD is 2021-
17-03.

Related Service Information Under 1 CFR Part 51

    EASA AD 2020-0280 describes procedures for doing repetitive
external general visual inspections or special detailed inspections
(i.e., phased array ultrasonic technology inspections of the external
skin, or detailed inspections for primer/paint cracks and high
frequency eddy current inspections of the internal skin) and repair for
cracking at the LH and RH sides of the fuselage skin, above stringer 6
from FR35 to FR47. This material is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Correction of Publication

    This document corrects an error in two locations and correctly adds
the AD as an amendment to 14 CFR 39.13. Although no other part of the
preamble or regulatory information has been corrected, the FAA is
publishing the entire rule in the Federal Register.
    The effective date of this AD remains October 5, 2021.
    Since this action only corrects the AD number, it has no adverse
economic impact and imposes no additional burden on any person.
Therefore, the FAA has determined that notice and public procedures are
unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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   [Corrected]

0
2. The FAA corrects Sec.  39.13 by correcting the airworthiness
directive published at 86 FR 48485 (August 31, 2021) to read:

2021-17-03 Airbus SAS: Amendment 39-21686; Docket No. FAA-2021-0334;
Project Identifier MCAI-2020-01662-T.

(a) Effective Date

    This airworthiness directive (AD) is effective October 5, 2021.

(b) Affected ADs

    This AD replaces AD 2017-12-13, Amendment 39-18928 (82 FR 27983,
June 20, 2017).

(c) Applicability

    This AD applies to Airbus SAS airplanes specified in paragraphs
(c)(1) through (3) of this AD, certificated in any category, as
identified in European Union Aviation Safety Agency (EASA) AD 2020-
0280, dated December 14, 2020 (EASA AD 2020-0280).
    (1) Model A318-111, -112, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a crack found during an
inspection of the pocket radius of the fuselage frame, and a
determination that similar cracks may develop in nearby areas of the
fuselage frame and that additional airplanes are subject to the
unsafe condition. The FAA is issuing this AD to address cracking of
the pocket radius, which could lead to in-flight decompression of
the airplane and possible injury to the passengers.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2020-0280.

(h) Exceptions to EASA AD 2020-0280

    (1) Where EASA AD 2020-0280 refers to its effective date, this
AD requires using the effective date of this AD.
    (2) Where paragraph (9) of EASA AD 2020-0280 specifies if any
crack is found during any inspection to ``contact Airbus for
approved repair instructions and accomplish those instructions
accordingly,'' this AD requires if any cracking is found, the
cracking must be repaired before further flight using a method
approved by the Manager, Large Aircraft Section, International
Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
    (3) Where paragraph (10) of EASA AD 2020-0280 specifies credit
for actions ``in accordance with the instructions of an Airbus
Repair Design Approval Sheet (RDAS), [and to] accomplish the next
inspection of each repaired area in accordance with the instructions
of, and within the compliance time as specified in, the applicable
RDAS,'' this AD requires using ``in accordance with repair
instructions approved, and within the compliance time specified in
the repair approval, using a method approved by the Manager, Large
Aircraft Section, International Validation Branch, FAA; or EASA; or
Airbus SAS's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.''
    (4) Where paragraph (11) of EASA AD 2020-0280 specifies
terminating actions apply only if specified ``in the Airbus RDAS
instructions for a repaired aeroplane,'' this AD requires using ``in
repair instructions approved using a method approved by the Manager,
Large Aircraft Section, International Validation Branch, FAA; or
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.''
    (5) The ``Remarks'' section of EASA AD 2020-0280 does not apply
to this AD.

(i) No Reporting Requirement

    Although the service information referenced in EASA AD 2020-0280
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.

(j) Other FAA AD Provisions

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

(k) Related Information

    For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, Large Aircraft Section, International Validation
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax<PHONE_NUMBER>; email<EMAIL_ADDRESS>
(l) 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
October 5, 2021 (86 FR 48485, August 31, 2021).
    (i) European Union Aviation Safety Agency (EASA) AD 2020-0280,
dated December 14, 2020.
    (ii) [Reserved]
    (4) For EASA AD 2020-0280, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
<EMAIL_ADDRESS>internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (5) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call<PHONE_NUMBER>.
    (6) 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, email<EMAIL_ADDRESS>or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 1, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-19245 Filed 9-1-21; 4:15 pm]
BILLING CODE 4910-13-P


[Federal Register Volume 78, Number 154 (Friday, August 9, 2013)]
[Notices]
[Page 48672]
[FR Doc No: 2013-19361]

=======================================================================
-----------------------------------------------------------------------

ENVIRONMENTAL PROTECTION AGENCY

[ER-FRL-9010-5]

Environmental Impacts Statements;

Notice of Availability

    Responsible Agency: Office of Federal Activities, General
Information<PHONE_NUMBER> or http://www.epa.gov/compliance/nepa/.
Weekly receipt of Environmental Impact Statements Filed 07/29/2013
Through 08/02/2013 Pursuant to 40 CFR 1506.9.

Notice

    Section 309(a) of the Clean Air Act requires that EPA make public
its comments on EISs issued by other Federal agencies. EPA's comment
letters on EISs are available at: http://www.epa.gov/compliance/nepa/eisdata.html.
EIS No. 20130231, Final EIS, USFS, OR, West Bend Vegetation Management
Project, Review Period Ends: 09/19/2013, Contact: Beth Peer 541-383-
4769
EIS No. 20130232, Final EIS, USN, MD, Outdoor Research, Development,
Test and Evaluation Activities at NSWC, Review Period Ends: 09/09/2013,
Contact: Stacia Courtney<PHONE_NUMBER>
EIS No. 20130233, Draft Supplement, USFS, ID, Salmon-Challis National
Forest Travel Planning and OHV Designation Project, Comment Period
Ends: 10/08/2013, Contact: Karen Gallogly<PHONE_NUMBER>
EIS No. 20130234, Draft EIS, BLM, NM, Ochoa Mine Project, Comment
Period Ends: 09/23/2013, Contact: Shiva Achet<PHONE_NUMBER>
EIS No. 20130235, Draft EIS, VCT, NM, Valles Caldera National
Preserve--Landscape Restoration and Stewardship Plan, Comment Period
Ends: 09/26/2013, Contact: Marie E. Rodriguez<PHONE_NUMBER>

Amended Notices

EIS No. 20130148, Draft Supplement, USACE, FL, Jacksonville Harbor
Navigation, Comment Period Ends: 09/30/2013, Contact: Paul Stodola 904-
232-3271
    Revision to FR Notice Published 07/12/2013; Extending Comment
Period from 07/31/2013 to 09/30/2013.

    Dated: August 6, 2013.
Cliff Rader,
Director, NEPA Compliance Division, Office of Federal Activities.
[FR Doc. 2013-19361 Filed 8-8-13; 8:45 am]
BILLING CODE 6560-50-P


[Federal Register Volume 76, Number 137 (Monday, July 18, 2011)]
[Notices]
[Page 42124]
[FR Doc No: 2011-17987]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 4009-001]

Henwood Associates, Inc.; White Mountain Ranch, LLC; Notice of
Transfer of Exemption

    By letter filed June 8, 2011, Henwood Associates, Inc. informed the
Commission that its exemption from licensing for the Millner Creek
Hydro Project No. 4009, originally issued July 16, 1981,\1\ has been
transferred to White Mountain Ranch, LLC. The project is located on the
Millner Creek Water System in Mono County, California. The transfer of
an exemption does not require Commission approval.
---------------------------------------------------------------------------

    \1\ Henwood Associates, Inc., 16 FERC ] 62,075 (1981).
---------------------------------------------------------------------------

    White Mountain Ranch, LLC, located at 30130 Cabrillo Avenue,
Temecula, California, is now the exemptee of the Millner Creek Hydro
Project No. 4009.

    Dated: July 11, 2011.
Kimberly D. Bose,
Secretary.
[FR Doc. 2011-17987 Filed 7-15-11; 8:45 am]
BILLING CODE 6717-01-P