[Federal Register Volume 75, Number 246 (Thursday, December 23, 2010)]
[Notices]
[Page 80805]
[FR Doc No: 2010-32202]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Combined Notice of Filings No. 1

December 16, 2010.
    Take notice that the Commission has received the following Natural
Gas Pipeline Rate and Refund Report filings:

    Docket Numbers: RP11-1613-000.
    Applicants: NGO Transmission, Inc.
    Description: NGO Transmission, Inc. submits tariff filing per
154.204: NGO Transmission--Negotiated Rate Filing, to be effective 1/1/
2011.
    Filed Date: 12/15/2010.
    Accession Number: 20101215-5015.
    Comment Date: 5 p.m. Eastern Time on Monday, December 27, 2010.

    Docket Numbers: RP11-1614-000.
    Applicants: CenterPoint Energy Gas Transmission Company.
    Description: CenterPoint Energy Gas Transmission Company submits
tariff filing per 154.204: Negotiated Rate--December 2010 to be
effective 12/15/2010.
    Filed Date: 12/15/2010.
    Accession Number: 20101215-5021.
    Comment Date: 5 p.m. Eastern Time on Monday, December 27, 2010.

    Docket Numbers: RP11-1615-000.
    Applicants: Northern Natural Gas Company.
    Description: Northern Natural Gas Company submits tariff filing per
154.204: 20101215 GRE Non-conforming to be effective 1/15/2011.
    Filed Date: 12/15/2010.
    Accession Number: 20101215-5089.
    Comment Date: 5 p.m. Eastern Time on Monday, December 27, 2010.

    Docket Numbers: RP11-1616-000.
    Applicants: Carolina Gas Transmission Corporation.
    Description: Carolina Gas Transmission Corporation's 2010 IT
Revenue Sharing Report.
    Filed Date: 12/15/2010.
    Accession Number: 20101215-5199.
    Comment Date: 5 p.m. Eastern Time on Monday, December 27, 2010.

    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.
    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>.

Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2010-32202 Filed 12-22-10; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 79, Number 77 (Tuesday, April 22, 2014)]
[Rules and Regulations]
[Pages 22369-22371]
[FR Doc No: 2014-08074]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0018; Directorate Identifier 2013-CE-049-AD;
Amendment 39-17822; AD 2014-07-08]
RIN 2120-AA64

Airworthiness Directives; Centrair Gliders

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for
Centrair Model 101, 101A, 101AP, and 101P gliders. This AD results from
mandatory continuing airworthiness information (MCAI) issued by an
aviation authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as structural damage to the fuselage. We are issuing this AD
to require actions to address the unsafe condition on these products.

DATES: This AD is effective May 27, 2014.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 27, 2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0018; or in person at Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this AD, contact
Soci[eacute]t[eacute] Nouvelle CENTRAIR, Aerodrome B.P. 44, F- 36300
LeBlanc, France; telephone: +33(0)254370796, fax: +33(0)254374864,
email<EMAIL_ADDRESS>Internet: none. You may view this
referenced service information at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to Centrair Model 101, 101A,
101AP, and 101P airplanes. The NPRM was published in the Federal
Register on January 15, 2014 (79 FR 2593). The NPRM proposed to correct
an unsafe condition for the specified products and was based on
mandatory continuing airworthiness information (MCAI) originated by an
aviation authority of another country. The MCAI states:

    Occurrences of structural damage were reported on several
Centrair 101 sailplane fuselage. The results of the subsequent
investigations identified that these findings were accidental damage
related and not identified in time during routine maintenance, due
to inadequate maintenance instructions.
    This condition, if not detected and corrected, could reduce the
structural integrity of the sailplane.
    To address this potential unsafe condition,
Soci[eacute]t[eacute] Nouvelle (SN) Centrair issued Service Bulletin
(SB) 101-06 to provide instructions for structural inspections and
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) of
France issued AD 85-21-(A) to mandate the fuselage inspections
described in that SB.
    Since that AD was issued, SN Centrair issued SB 101-06 at
revision (rev.) 1 to provide improved instructions to identify
accidental structural damages.
    For the reasons described above, this AD retains the
requirements of DGAC France AD 85-21-(A), which is superseded, but
requires accomplishment of those fuselage structural inspections in
accordance with improved instructions.

The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2014-0018-0002.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 2593, January 15,
2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed except for
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM (79 FR 2593, January 15, 2014) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD will affect 43 products of U.S. registry.
We also estimate that it would take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour.
    Based on these figures, we estimate the cost of this AD on U.S.
operators to be $10,965, or $255 per product.
    Since there are currently no repair instructions available if
discrepancies are found during the required inspections, we have no way
of determining the number of products that may need follow-on actions
or what the cost per product would be.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
    We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0018; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains the NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Office
(telephone<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

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 AD:

2014-07-08 Centrair: Amendment 39-17822; Docket No. FAA-2014-0018;
Directorate Identifier 2013-CE-049-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 27,
2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CENTRAIR Models 101, 101A, 101P, and 101AP
gliders, all serial numbers, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as structural
damage to the fuselage. We are issuing this AD to detect and correct
structural damage not identified during routine maintenance
inspections, which could lead to reduced structural integrity of the
glider.

(f) Actions and Compliance

    Unless already done, do the following actions in paragraphs
(f)(1) through (f)(3) of this AD:
    (1) Within 25 days after May 27, 2014 (the effective date of
this AD) and repetitively thereafter at intervals not to exceed
every 12 months, inspect all fuselage frames and ribs following the
instructions in Soci[eacute]t[eacute] Nouvelle CENTRAIR Mandatory
Service Bulletin 101-06, Revision 1, dated August 5, 2013.
    (2) If structural damage is detected during any inspection
required by paragraph (f)(1) of this AD, before further flight,
contact Soci[eacute]t[eacute] Nouvelle CENTRAIR at the address
specified in paragraph (i) of this AD to obtain FAA-approved repair
instructions approved specifically for this AD, and before further
flight, repair the glider using these repair instructions.
    (3) Accomplishment of a repair, as required by paragraph (f)(2)
of this AD, does not constitute terminating action for the
inspection required by paragraph (f)(1) of this AD.

    Note 1 to paragraph (f) of this AD:  We recommend that you also
inspect the fuselage frames and ribs after the occurrence of any of
the following events following the instructions in
Soci[eacute]t[eacute] Nouvelle CENTRAIR Mandatory Service Bulletin
101-06, Revision 1, dated August 5, 2013: Landing with retracted
gear, landing gear retraction during landing run, ground looping
during take-off or landing, hard landing, or damage of internal
structure of the fuselage. If structural damage is detected during
any of these inspections, we recommend you contact
Soci[eacute]t[eacute] Nouvelle CENTRAIR at the address specified in
paragraph (i) of this AD for FAA-approved repair instructions.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2013-0258, dated October 25, 2013, for related information. The MCAI
can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2014-0018-0002.

(i) 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) Soci[eacute]t[eacute] Nouvelle CENTRAIR Mandatory Service
Bulletin 101-06, Revision 1, dated August 5, 2013.
    (ii) Reserved.
    (3) For Centrair Gliders service information identified in this
AD, contact Soci[eacute]t[eacute] Nouvelle CENTRAIR, Aerodrome B.P.
44, F- 36300 LeBlanc, France; telephone: +33(0)254370796, fax:
+33(0)254374864, email<EMAIL_ADDRESS>Internet: none.
    (4) You may view this service information at the FAA, Small
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on April 4, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014-08074 Filed 4-21-14; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)]
[Rules and Regulations]
[Pages 12401-12405]
[FR Doc No: 2017-03951]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9298; Directorate Identifier 2015-NM-161-AD;
Amendment 39-18811; AD 2017-05-01]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A300 series airplanes. This AD was prompted by an
evaluation by the design approval holder (DAH) that indicates that a
section of the wing and aft fuselage is subject to widespread fatigue
damage (WFD). This AD requires an inspection to determine if certain
modifications have been done. We are issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective April 7, 2017.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 7,
2017.

ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office-EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view
this referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>. It is also
available on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-9298.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9298; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A300
series airplanes. The NPRM published in the Federal Register on October
26, 2016 (81 FR 74354) (``the NPRM''). The NPRM was prompted by an
evaluation by the DAH that indicates that a section of the wing and aft
fuselage is subject to WFD. The NPRM proposed to require an inspection
to determine if certain modifications have been done. For airplanes on
which the specified modifications have not been done, this AD requires
accomplishing those modifications, including doing related
investigative and corrective actions if necessary. We are issuing this
AD to prevent reduced structural integrity of these airplanes due to
the failure of certain structural components.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2015-0173R1, dated August 31, 2016, (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus Model A300 series airplanes.
The MCAI states:

    A widespread fatigue damage (WFD) analysis conducted on A300
aeroplanes identified areas which are susceptible to crack
development.
    This condition, if not corrected, could affect the structural
integrity of the aeroplane.
    To address this issue, Airbus developed a modification (mod) to
reinforce the structure of the aeroplane. Airbus issued Service
Bulletin (SB) A300-53-0271 to provide instructions for a cold
expansion of the foot attachment holes of certain fuselage frames,
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France issued AD F-2004-001 to require this mod [which corresponds
with certain requirements in FAA AD 2004-23-20, Amendment 39-13875
(69 FR 68779, November 26, 2004)].
    Since that [DGAC] AD was issued, Airbus released twelve other
mods with corresponding SBs, to complete the set of inspections and
repairs in the frame of the A300 WFD campaign. EASA issued AD 2015-
0115 to require ten of these mods through section 3 of ALS
[Airworthiness Limitations Section] Part 2, and decision is made to
delete section 3 from ALS Part 2.
    For the reasons described above, EASA issued AD 2015-0173,
retaining the requirements of DGAC France AD F-2004-001, which was
superseded, to require implementation of the additional inspection,
modification and/or repair actions, as applicable to aeroplane
model.
    This [EASA] AD is revised to give credit for previous use of any
earlier revision of an affected Airbus SB, based on the fact that no
additional work is included in the later SB revisions.

    Required actions include an inspection to determine if certain
modifications have been done. For airplanes on which the specified
modifications have not been done, this AD requires accomplishing those
modifications, including doing related investigative and corrective
actions if necessary. Depending on airplane configuration, the
compliance times for modifying the airplane structure range between
13,300 flight cycles and 48,000 flight cycles since first flight of the
airplane. You may examine the MCAI in the AD docket on the Internet at
http://www.regulations.gov by searching for and locating Docket No.
FAA-2016-9298.

Comments

    We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information:
     Airbus Service Bulletin A300-53-0239, Revision 02, dated
March 6, 2000. This service information describes procedures to modify
the longitudinal junction. The modification includes the addition of
external doublers and installation of interference fit attachments and
related investigative and corrective actions. The related investigative
actions are rotary probe inspections for cracking of the fastener
holes. The corrective action is repair.
     Airbus Service Bulletin A300-53-247, Revision 2, dated
July 20, 1990. This service information describes procedures to modify
the fuselage upper door frame structure, which consists of eddy current
inspections of certain structure for cracks, and structural
modification or repair.
     Airbus Service Bulletin A300-53-0271, Revision 05, dated
June 21, 2013. This service information describes procedures to modify
the fuselage frame (FR), which includes cold expansion of the fastener
holes between FR 41 and FR 54, and related investigative and corrective
actions. The related investigative actions including rotary probe
inspections for cracking of the fastener holes. The corrective action
is repair.
     Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
This service information describes procedures to modify the fuselage
frame, which includes installing an additional external doubler on the
fuselage lap joint at fuselage stringers (STGR) 22, left and right,
between FR 26 and FR 40.
     Airbus Service Bulletin A300-53-0368, dated April 7, 2005.
This service information describes procedures to modify the rear
fuselage, which includes installing an additional external doubler on
the fuselage lap joint at STGR 51, left and right, between FR 72 and FR
80.
     Airbus Service Bulletin A300-53-0369, Revision 03, dated
September 1, 2010. This service information describes procedures to
modify the rear fuselage, which includes reinforcing the butt joint at
FR 72 by installation of an additional external doubler at the butt
joint of FR 72 at STGR 14, left and right.
     Airbus Service Bulletin A300-53-0373, Revision 03, dated
September 1, 2010. This service information describes procedures to
modify the rear fuselage, which includes reinforcing the butt joint at
FR65 by installation of an additional external doubler at the butt
joint of FR65 between STGR 13 left and right.
     Airbus Service Bulletin A300-53-0374, Revision 04, dated
July 5, 2013. This service information describes procedures to modify
the rear fuselage, which includes reinforcing the butt joints at FR55
and FR58 by installation of additional external doublers without cutout
at certain butt joints.
     Airbus Service Bulletin A300-53-0375, Revision 01, dated
June 24, 2013. This service information describes procedures to modify
the forward fuselage, which includes reinforcing the fuselage
circumferential butt joint at FR 26 by installation of an additional
external doubler at the butt joint of FR 26 between STGR 13 left and
STGR 13 right.
     Airbus Service Bulletin A300-53-0393, dated September 27,
2013. This service information describes procedures to modify the
fuselage frame which includes reinforcing the longitudinal butt joints
with additional butt straps at certain fuselage frames and stringers.
     Airbus Service Bulletin A300-57-0203, Revision 04, dated
February 18, 2015. This service information describes procedures to
modify the outer wing, which includes removal of the wing stringer and
run-out plate at STGR 19 on the bottom wing skin; replacement of the
taper-lok bolts with interference fit parallel bolts; and related
investigative and corrective actions. Related investigative actions
include detailed visual and high frequency eddy current (HFEC)
inspections of the stringer runouts for cracks; eddy current
inspections for cracks of the fastener holes; and detailed visual and
HFEC inspections of the stringer run-outs for cracks and damage.
Corrective actions include repair.
     Airbus Service Bulletin A300-57-0258, dated September 30,
2014 (for Model A300 B4-103 and A300 B4-2C airplanes). This service
information describes procedures to modify the wing structure, which
includes a first oversize of the critical holes on certain wing
stringers, and related investigative and corrective actions. Related
investigated actions include detailed visual inspections for damage of
the top wing skin external surface and the stringer joint; and roto-
probe inspections for damage of the fastener holes. Corrective actions
include repair.
     Airbus Service Bulletin A300-57-0259, dated September 30,
2014 (for Model A300 B2-1C, A300 B2-203, and A300 B2K-3C airplanes).
This service information describes procedures to modify the wing
structure, which includes a first oversize of the critical holes on
certain wing stringers, and related investigative and corrective
actions. Related investigated actions include detailed visual
inspections for damage of the top wing skin external surface and the
stringer joint; and roto-probe inspections for damage of the fastener
holes. Corrective 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

    We estimate that this AD affects 8 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification.......................  3,291 work-hours x $85 per         $142,845        $422,580      $3,380,640
                                      hour = $279,735.
----------------------------------------------------------------------------------------------------------------

    In addition, we estimate that any necessary follow-on actions will
take about 15 work-hours and require parts costing $10,000, for a cost
of $11,275 per product. We have no way of determining the number of
aircraft that might need this action.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
    We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in

air commerce by prescribing regulations for practices, methods, and
procedures the Administrator finds necessary for safety in air
commerce. This regulation is within the scope of that authority because
it addresses an unsafe condition that is likely to exist or develop on
products identified in this rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

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):

2017-05-01 Airbus: Amendment 39-18811; Docket No. FAA-2016-9298;
Directorate Identifier 2015-NM-161-AD.

(a) Effective Date

    This AD is effective April 7, 2017.

(b) Affected ADs

    This AD affects AD 2004-23-20, Amendment 39-13875 (69 FR 68779,
November 26, 2004) (``AD 2004-23-20'').

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes, certificated in any
category, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval
holder that indicates that a section of the wing and aft fuselage is
subject to widespread fatigue damage. We are issuing this AD to
prevent reduced structural integrity of these airplanes due to the
failure of certain structural components.

(f) Compliance

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

(g) Verification of Embodied Modifications

    Within 4 months after the effective date of this AD, verify
whether the Airbus modifications specified in table 1 to paragraphs
(g), (h), and (i) of this AD, as applicable to airplane model, have
been embodied on the airplane, in accordance with the Accomplishment
Instructions of the applicable Airbus service bulletin specified in
table 1 to paragraphs (g), (h), and (i) of this AD. A review of the
airplane maintenance records is acceptable to accomplish the
verification required by this paragraph, provided those records can
be used to conclusively determine whether the modifications have
been embodied.

 Table 1 to Paragraphs (g), (h), and (i) of This AD--Airbus Modification
                     and Applicable Service Bulletin
------------------------------------------------------------------------
                                      Airbus         Applicable Airbus
              Set                  modification       service bulletin
------------------------------------------------------------------------
Set 1A........................  751..............  A300-53-247, Revision
                                                    2, dated July 20,
                                                    1990.
                                7301.............  A300-53-0239,
                                                    Revision 02, dated
                                                    March 6, 2000.
                                10326............  A300-57-0203,
                                                    Revision 04, dated
                                                    February 18, 2015.
                                12735............  A300-53-0366, dated
                                                    April 7, 2005.
                                12736............  A300-53-0368, dated
                                                    April 7, 2005.
                                12737............  A300-53-0369,
                                                    Revision 03, dated
                                                    September 1, 2010.
                                12798............  A300-53-0375,
                                                    Revision 01, dated
                                                    June 24, 2013.
                                07757 and 12977..  A300-53-0271,
                                                    Revision 05, dated
                                                    June 21, 2013.
                                13611............  A300-57-0258, dated
                                                    September 30, 2014.
                                13692............  A300-53-0393, dated
                                                    September 27, 2013.
                                13716............  A300-57-0259, dated
                                                    September 30, 2014.
Set 1B........................  12794............  A300-53-0374,
                                                    Revision 04, dated
                                                    July 5, 2013.
                                12796............  A300-53-0373,
                                                    Revision 03, dated
                                                    September 1, 2010.
------------------------------------------------------------------------

(h) Corrective Actions for Modifications Which Have Not Been Embodied

    If, during the verification required by paragraph (g) of this
AD, it is determined that any modification has not been embodied, do
the applicable actions specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD.
    (1) If it is determined that any Airbus modification, specified
in the applicable Airbus Service Bulletin, identified in ``Set 1A''
of table 1 to paragraphs (g), (h), and (i) of this AD is not
embodied: Within the applicable compliance time specified in the
applicable Airbus Service Bulletin identified in ``Set 1A'' of table
1 to paragraphs (g), (h), and (i) of this AD, or within 4 months
after the effective date of this AD, whichever occurs later, do the
applicable actions specified in paragraphs (h)(1)(i) through
(h)(1)(xi) of this AD, except as required by paragraph (i) of this
AD. Do all applicable related investigative and corrective actions
before further flight.
    (i) For airplanes on which Airbus Service Bulletin A300-53-0239,
Revision 02, dated March 6, 2000, has not been embodied: Modify the
longitudinal junction and do all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0239, Revision 02,
dated March 6, 2000.
    (ii) For airplanes on which Airbus Service Bulletin A300-53-247,
Revision 2, dated July 20, 1990, has not been embodied: Modify the
fuselage upper door frame structure by doing eddy current
inspections for cracks of the structure specified in Airbus Service
Bulletin A300-53-247, Revision 2, dated July 20, 1990, and a
structural modification or repair, as applicable, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
247, Revision 2, dated July 20, 1990.
    (iii) For airplanes on which Airbus Service Bulletin A300-53-
0271, Revision 05, dated

June 21, 2013, has not been embodied: Modify the fuselage frame, and
do all applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-0271, Revision 05, dated June 21, 2013.
    (iv) For airplanes on which Airbus Service Bulletin A300-53-
0366, dated April 7, 2005, has not been embodied: Modify the
fuselage frame, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (v) For airplanes on which Airbus Service Bulletin A300-53-0368,
dated April 7, 2005, has not been embodied: Modify the rear
fuselage, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (vi) For airplanes on which Airbus Service Bulletin A300-53-
0369, Revision 03, dated September 1, 2010, has not been embodied:
Modify the rear fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0369, Revision 03,
dated September 1, 2010.
    (vii) For airplanes on which Airbus Service Bulletin A300-53-
0375, Revision 01, dated June 24, 2013, has not been embodied:
Modify the forward fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0375, Revision 01,
dated June 24, 2013.
    (viii) For airplanes on which Airbus Service Bulletin A300-53-
0393, dated September 27, 2013, has not been embodied: Modify the
fuselage frame, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-53-0393, dated September 27, 2013.
    (ix) For airplanes on which Airbus Service Bulletin A300-57-
0203, Revision 04, dated February 18, 2015, has not been embodied:
Modify the outer wing, and do all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0203, Revision 04,
dated February 18, 2015.
    (x) For airplanes on which Airbus Service Bulletin A300-57-0258,
dated September 30, 2014, has not been embodied: Modify the wing
structure and do all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-0258, dated September 30, 2014.
    (xi) For airplanes on which Airbus Service Bulletin A300-57-
0259, dated September 30, 2014, has not been embodied: Modify the
wing structure, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0259, dated
September 30, 2014.
    (2) If it is determined that Airbus Service Bulletin A300-53-
0374, Revision 04 dated July 5, 2013 (mod 12794) has not been
embodied: Within the compliance time specified in paragraphs
(h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as
applicable, modify the rear fuselage, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-0374,
Revision 04, dated July 5, 2013, except as required by paragraph (i)
of this AD.
    (i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame
(FR) 55: Within 31,300 flight cycles since first flight of the
airplane, or within 4 months after the effective date of this AD,
whichever occurs later.
    (ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within
49,700 flight cycles since first flight of the airplane, or within 4
months after the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600
flight cycles since first flight of the airplane, or within 4 months
after the effective date of this AD, whichever occurs later.
    (iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800
flight cycles since first flight of the airplane, or within 4 months
after the effective date of this AD, whichever occurs later.
    (3) If it is determined that Airbus Service Bulletin A300-53-
0373, Revision 03, dated September 1, 2010 (mod 12796) has not been
embodied: Within the compliance time specified in paragraphs
(h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable,
modify the rear fuselage, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-0373, Revision 03,
dated September 1, 2010, except as required by paragraph (i) of this
AD.
    (i) For Model A300 B2 airplanes: Within 42,700 flight cycles
since first flight of the airplane, or within 4 months after the
effective date of this AD, whichever occurs later.
    (ii) For Model A300 B4-100 airplanes: Within 41,700 flight
cycles since first flight of the airplane, or within 4 months after
the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes: Within 47,900 flight
cycles since first flight of the airplane, or within 4 months after
the effective date of this AD, whichever occurs later.

(i) Exception to the Service Information

    Where any service information identified in table 1 to
paragraphs (g), (h), and (i) of this AD specifies to contact the
manufacturer for instructions or solutions, before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus's EASA Design Organization
Approval (DOA).

(j) Terminating Action for Certain Requirements in AD 2004-23-20

    Accomplishing the modification required by paragraph (h)(1)(iii)
of this AD terminates the modification required by paragraph (i) of
AD 2004-23-20 for that airplane only.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
    (3) Required for Compliance (RC): 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.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA AD 2015-0173R1, dated August 31, 2016, for related information.
This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-9298.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-53-0239, Revision 02, dated
March 6, 2000.
    (ii) Airbus Service Bulletin A300-53-247, Revision 2, dated July
20, 1990.
    (iii) Airbus Service Bulletin A300-53-0271, Revision 05, dated
June 21, 2013.
    (iv) Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (v) Airbus Service Bulletin A300-53-0368, dated April 7, 2005.
    (vi) Airbus Service Bulletin A300-53-0369, Revision 03, dated
September 1, 2010.
    (vii) Airbus Service Bulletin A300-53-0373, Revision 03, dated
September 1, 2010.

    (viii) Airbus Service Bulletin A300-53-0374, Revision 04, dated
July 5, 2013.
    (ix) Airbus Service Bulletin A300-53-0375, Revision 01, dated
June 24, 2013.
    (x) Airbus Service Bulletin A300-53-0393, dated September 27,
2013.
    (xi) Airbus Service Bulletin A300-57-0203, Revision 04, dated
February 18, 2015.
    (xii) Airbus Service Bulletin A300-57-0258, dated September 30,
2014.
    (xiii) Airbus Service Bulletin A300-57-0259, dated September 30,
2014.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office-EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33
5 61 93 44 51; email<EMAIL_ADDRESS>Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03951 Filed 3-2-17; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 85, Number 161 (Wednesday, August 19, 2020)]
[Notices]
[Page 51044]
[FR Doc No: 2020-18062]

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

DEPARTMENT OF HOMELAND SECURITY

Federal Emergency Management Agency

[Internal Agency Docket No. FEMA-3531-EM; Docket ID FEMA-2020-0001]

Virgin Islands; Amendment No. 1 to Notice of an Emergency
Declaration

AGENCY: Federal Emergency Management Agency, DHS.

ACTION: Notice.

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

SUMMARY: This notice amends the notice of an emergency declaration for
the territory of the U.S. Virgin Islands (FEMA-3531-EM), dated July 29,
2020, and related determinations.

DATES: This amendment was issued August 6, 2020.

FOR FURTHER INFORMATION CONTACT: Dean Webster, Office of Response and
Recovery, Federal Emergency Management Agency, 500 C Street SW,
Washington, DC 20472,<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: Notice is hereby given that the incident
period for this emergency is closed effective July 31, 2020.

    The following Catalog of Federal Domestic Assistance Numbers
(CFDA) are to be used for reporting and drawing funds: 97.030,
Community Disaster Loans; 97.031, Cora Brown Fund; 97.032, Crisis
Counseling; 97.033, Disaster Legal Services; 97.034, Disaster
Unemployment Assistance (DUA); 97.046, Fire Management Assistance
Grant; 97.048, Disaster Housing Assistance to Individuals and
Households In Presidentially Declared Disaster Areas; 97.049,
Presidentially Declared Disaster Assistance--Disaster Housing
Operations for Individuals and Households; 97.050, Presidentially
Declared Disaster Assistance to Individuals and Households--Other
Needs; 97.036, Disaster Grants--Public Assistance (Presidentially
Declared Disasters); 97.039, Hazard Mitigation Grant.

Pete Gaynor,
Administrator, Federal Emergency Management Agency.
[FR Doc. 2020-18062 Filed 8-18-20; 8:45 am]
BILLING CODE 9111-23-P


[Federal Register Volume 76, Number 242 (Friday, December 16, 2011)]
[Rules and Regulations]
[Pages 78153-78154]
[FR Doc No: 2011-32260]

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

DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 117

[Docket No. USCG-2011-1116]

Drawbridge Operation Regulation; Oakland Inner Harbor, Oakland,
CA

AGENCY: Coast Guard, DHS.

ACTION: Notice of temporary deviation from regulations.

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

SUMMARY: The Commander, Eleventh Coast Guard District, has issued a
temporary deviation from the regulation governing the operation of the
Fruitvale Avenue Drawbridge across Oakland Inner Harbor, mile 5.6,
between the cities of Alameda and Oakland, Alameda County, CA. The
deviation is necessary to allow the County of Alameda Public Works
Agency to perform seismic retrofitting on the drawbridge. This
deviation allows the bridge owner to secure the drawspan in the closed-
to-navigation position during the project.

DATES: This deviation is effective from 12:01 a.m., December 12, 2011
to 11:59 p.m. on February 3, 2012.

ADDRESSES: Documents mentioned in this preamble as being available in
the docket are part of the docket USCG-2011-1116 and are available
online by going to http://www.regulations.gov, inserting USCG-2011-1116
in the ``Keyword'' box and then clicking ``Search''. They are also
available for inspection or copying at the Docket Management Facility
(M-30), U.S. Department of Transportation, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between
9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: If you have questions on this rule,
call or email David H. Sulouff, Chief, Bridge Section, Eleventh Coast
Guard District; telephone<PHONE_NUMBER>, email
<EMAIL_ADDRESS>If you have

questions on viewing the docket, call Renee V. Wright, Program Manager,
Docket Operations, telephone<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION: The County of Alameda Public Works Agency
has requested a temporary change to the operation of the Fruitvale
Avenue Drawbridge, mile 5.61, over Oakland Inner Harbor, between the
cities of Alameda and Oakland, Alameda County, CA. The drawbridge
navigation span provides a vertical clearance of 15 feet above Mean
High Water in the closed-to-navigation position. The draw opens on
signal; except that, from 8 a.m. to 9 a.m. and 4:30 p.m. to 6:30 p.m.
Monday through Friday except Federal holidays, the draw need not be
opened for the passage of vessels. However, the draw shall open during
the above closed periods for vessels which must, for reasons of safety,
move on a tide or slack water, if at least two hours notice is given,
as required by 33 CFR 117.181. Navigation on the waterway is commercial
and recreational.
    The drawspan will be secured in the closed-to-navigation position
for seismic retrofitting during three time periods: (a) From 12:01
a.m., December 12, 2011 to 11:59 p.m. on December 23, 2011; (b) from
12:01 a.m., January 3, 2012 to 11:59 p.m. on January 12, 2012; and (c)
from 12:01 a.m., January 23, 2012 to 11:59 p.m. on February 3, 2012. At
all other times, the drawspan will promptly return to normal operation.
This temporary deviation has been coordinated with waterway users. No
objections to the proposed temporary deviation were raised.
    Vessels that can transit the bridge, while in the closed-to-
navigation position, may continue to do so at any time.
    In accordance with 33 CFR 117.35(e), the drawbridge must return to
its regular operating schedule immediately at the end of the designated
time period. This deviation from the operating regulations is
authorized under 33 CFR 117.35.

    Dated: December 2, 2011.
D.H. Sulouff,
District Bridge Chief, Eleventh Coast Guard District.
[FR Doc. 2011-32260 Filed 12-15-11; 8:45 am]
BILLING CODE 9110-04-P