[Federal Register Volume 77, Number 192 (Wednesday, October 3, 2012)]
[Notices]
[Page 60429]
[FR Doc No: 2012-24360]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 13487-001]

FFP Project 77 LLC; Notice of Preliminary Permit Application
Accepted for Filing and Soliciting Comments, Motions To Intervene, and
Competing Applications

    On September 4, 2012, FFP Project 77, LLC filed an application for
a preliminary permit, pursuant to section 4(f) of the Federal Power Act
(FPA), proposing to study the feasibility of a hydropower project
located on the Mississippi River, near Anthonyville, in Crittenden
County, Arkansas, Desoto County, Mississippi and Shelby County,
Tennessee. The sole purpose of a preliminary permit, if issued, is to
grant the permit holder priority to file a license application during
the permit term. A preliminary permit does not authorize the permit
holder to perform any land-disturbing activities or otherwise enter
upon lands or waters owned by others without the owners' express
permission.
    The proposed Cow Island hydrokinetic project would consist of the
following: (1) Up to 1,070 SmarTurbine generating units installed in
arrays on the bottom of the river; (2) the total capacity of the
installation would be up to 42,800 kilowatts; (3) flexible cables would
convey each arrays power to a metering station; and (4) a transmission
line would interconnect with the power grid. The proposed project would
have an average annual generation of 97,337,000 kilowatt-hours, which
would be sold to a local utility.
    Applicant Contact: Ramya Swaminathan, Free Flow Power Corporation,
239 Causeway Street, Boston, MA 02114; phone<PHONE_NUMBER>.
    FERC Contact: Michael Spencer,<PHONE_NUMBER>.
    Deadline for filing comments, motions to intervene, competing
applications (without notices of intent), or notices of intent to file
competing applications: 60 days from the issuance of this notice.
Competing applications and notices of intent must meet the requirements
of 18 CFR 4.36. Comments, motions to intervene, notices of intent, and
competing applications may be filed electronically via the Internet.
See 18 CFR 385.2001(a)(1)(iii) and the instructions on the Commission's
Web site http://www.ferc.gov/docs-filing/efiling.asp. Commenters can
submit brief comments up to 6,000 characters, without prior
registration, using the eComment system at http://www.ferc.gov/docs-filing/ecomment.asp. You must include your name and contact information
at the end of your comments. For assistance, please contact FERC Online
Support at<EMAIL_ADDRESS>or toll free at 1-866-208-3676,
or for TTY,<PHONE_NUMBER>. Although the Commission strongly encourages
electronic filing, documents may also be paper-filed. To paper-file,
mail an original and seven copies to: Kimberly D. Bose, Secretary,
Federal Energy Regulatory Commission, 888 First Street NE., Washington,
DC 20426.
    More information about this project, including a copy of the
application, can be viewed or printed on the ``eLibrary'' link of
Commission's Web site at http://www.ferc.gov/docs-filing/elibrary.asp.
Enter the docket number (P-13487) in the docket number field to access
the document. For assistance, contact FERC Online Support.

    Dated: September 27, 2012.
 Kimberly D. Bose,
 Secretary.
[FR Doc. 2012-24360 Filed 10-2-12; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 86, Number 104 (Wednesday, June 2, 2021)]
[Rules and Regulations]
[Pages 29483-29486]
[FR Doc No: 2021-11444]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0135; Project Identifier MCAI-2020-01044-R;
Amendment 39-21554; AD 2021-10-21]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters Deutschland GmbH

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-07-07
for various Airbus Helicopters Deutschland GmbH (Airbus Helicopters)
Model MBB-BK117 and Model BO-105 helicopters. AD 2019-07-07 required
removing certain part numbered swashplate bellows (bellows) from
service, cleaning and inspecting certain parts, and depending on the
inspection results removing certain parts from service, applying
torque, and repetitively inspecting the swashplate assembly
(swashplate). This AD retains certain requirements of AD 2019-07-07,
expands the installation prohibition, adds additional inspections, and
updates the applicable service information. The FAA is issuing this AD
to address an unsafe condition on these products.

DATES: This AD is effective July 7, 2021.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 7, 2021.

ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX
75052; telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>;
or at https://www.airbus.com/helicopters/services/technical-support.html. You may view this service information at the FAA, Office
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For more information on the availability
of this material at the FAA, call<PHONE_NUMBER>. It is also available
on the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-0135.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2021-0135; 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 AD, the European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD,
any service information that is incorporated by reference, any comments
received, and other information. The street 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: Matt Fuller, AD Program Manager,
Operational Safety Branch, Airworthiness Products Section, General
Aviation & Rotorcraft Unit,

FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5110; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2019-07-07, Amendment 39-19618 (84 FR
16394, April 19, 2019) (AD 2019-07-07). AD 2019-07-07 applied to Airbus
Helicopters Model BO-105A, BO-105C, BO-105S, BO105LS A-3, MBB-BK 117A-
1, MBB-BK 117A-3, MBB-BK 117A-4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK
117C-1, MBB-BK 117C-2, and MBB-BK 117D-2 helicopters. The NPRM
published in the Federal Register on March 10, 2021 (86 FR 13665). The
NPRM proposed to require, within 50 hours time-in-service, removing the
affected bellows from the swashplate, cleaning and inspecting the
support tube for scratches, and depending on the inspection results
reworking the cylindrical area. The NPRM proposed to require inspecting
the clamp for corrosion, damage, and incorrect installation, and
depending on the inspection results, removing the clamp from service or
reinstalling the clamp correctly and applying a torque. The NPRM also
proposed to require inspecting each ball bearing for corrosion, and
depending on the inspection results, removing each ball bearing from
service. The NPRM proposed to require inspecting the deflection ring
for foreign objects by removing the lockwire, screws, and the outer
deflection ring and removing any foreign objects.
    Additionally, the NPRM proposed to require, within 400 hours TIS,
inspecting the swashplate for foreign objects and excessive bearing
rolling friction. Finally, the NPRM proposed to prohibit installing a
bellows P/N 105-10113.05, P/N<PHONE_NUMBER>, P/N<PHONE_NUMBER>, or P/N
B623M20X2240, or a gearbox with a bellows P/N 105-10113.05, P/N
4619305044, or P/N<PHONE_NUMBER> on any helicopter.
    EASA AD 2016-0142, dated July 19, 2016, which was revised to EASA
AD 2016-0142R1, dated April 12, 2018, issued by EASA, which is the
Technical Agent for the Member States of the European Union, to correct
an unsafe condition for Model MBB-BK117 A-1, MBB-BK117 A-3, MBB-BK117
A-4, MBB-BK117 B-1, MBB-BK117 B-2, MBB-BK117 C-1, MBB-BK117 C-2, and
MBB-BK117 C-2e helicopters, all serial numbers (S/Ns), and Model BO105
A, BO105 C, BO105 D, BO105 S, and BO105 LS A-3 helicopters, all
variants, all S/Ns. EASA advises of several reports of a lower clamp
found missing from the bellows and damaging the swashplate bearing ring
before becoming detached. EASA states that an investigation showed that
over-torqueing can damage the clamp, which may have caused the clamp to
become loose and detach. EASA further advises that this condition, if
not addressed, could result a detached clamp, which could damage the
swashplate and pitch link or strike the tail rotor, resulting in loss
of control of the helicopter.
    Accordingly, EASA AD 2016-0142R1 requires removing the bellows, and
performing modifications, inspections, and corrective actions in
accordance with the applicable service information for your helicopter.
EASA AD 2016-0142R1 also prohibits the installation of certain part-
numbered bellows or any gearbox with certain part-numbered bellows on
any helicopter.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or the determination of
the costs.

Conclusion

    These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA reviewed the relevant
data and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these helicopters.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB
(ASB) BO105-40A-107 for Model BO105C-series, D-series and S-series
helicopters; ASB BO105 LS-40A-12 for Model BO-105LS A-3 helicopters;
ASB MBB-BK117-40A-115 for Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK
117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1
helicopters; and ASB MBB-BK117 C-2-62A-007 for Model MBB-BK 117 C-2
helicopters, each Revision 5 and dated July 25, 2017. The FAA also
reviewed Airbus Helicopters ASB MBB-BK117 D-2-62A-003, Revision 3,
dated July 25, 2017, for Model MBB-BK 117 D-2 helicopters. This service
information specifies removing the bellows and repetitively inspecting
the swashplate.
    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.

Differences Between This AD and the EASA AD

    The EASA AD requires compliance within different time intervals for
some actions than what this AD requires. The EASA AD allows a non-
cumulative tolerance of 10 percent that may be applied to the
compliance times, and this AD does not. This AD applies to Model MBB-BK
117D-2 helicopters while the EASA AD does not. The EASA AD applies to
Model BO-105D helicopters, while this AD does not. The EASA AD requires
reporting corrosion to Airbus Helicopters while this AD does not.

Costs of Compliance

    The FAA estimates that this AD affects 211 helicopters of U.S.
Registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this AD.
    Inspecting the swashplate assembly takes about 3 work-hours for an
estimated cost of $255 per helicopter and $53,805 for the U.S. fleet
per inspection cycle.
    Repairing a scratched support tube takes about 3 work-hours for an
estimated cost of $255 per helicopter.
    Replacing a corroded or damaged clamp takes about 2 work-hours and
parts cost about $8 for a cost of $178 per helicopter.
    Replacing corroded ball bearings takes about 4 work-hours and parts
cost about $3,000 for a cost of $3,340 per helicopter.
    Removing foreign objects from the outer deflection ring takes about
2 work-hours for an estimated cost of $170 per helicopter.

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.

Regulatory Findings

    The FAA has 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) 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:
0
a. Removing Airworthiness Directive (AD) 2019-07-07, Amendment 39-19618
(84 FR 16394, April 19, 2019); and
0
b. Adding the following new AD:

2021-10-21 Airbus Helicopters Deutschland GmbH: Amendment 39-21554;
Docket No. FAA-2021-0135; Project Identifier MCAI-2020-01044-R.

(a) Effective Date

    This airworthiness directive (AD) is effective July 7, 2021.

(b) Affected ADs

    This AD replaces AD 2019-07-07, Amendment 39-19618 (84 FR 16394,
April 19, 2019) (2019-07-07).

(c) Applicability

    This AD applies to Airbus Helicopters Deutschland GmbH Model BO-
105A, BO-105C, BO-105S, BO105LS A-3, MBB-BK 117A-1, MBB-BK 117A-3,
MBB-BK 117A-4, MBB-BK 117B-1, MBB-BK 117B-2, MBB-BK 117C-1, MBB-BK
117C-2, and MBB-BK 117D-2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.

(e) Unsafe Condition

    This AD was prompted by a lower clamp found missing from the
swashplate bellows (bellows) and damaging the swashplate bearing
ring before becoming detached. The FAA is issuing this AD to prevent
a loose bellows clamp. The unsafe condition, if not addressed, could
result in loss of the bellows, contact of the bellows with the main
rotor blades, main rotor mast, and tail rotor, and subsequent loss
of helicopter control.

(f) Compliance

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

(g) Required Actions

    (1) Within 50 hours time-in-service (TIS) after the effective
date of this AD:
    (i) Remove from service bellows part number (P/N) 105-10113.05,
P/N<PHONE_NUMBER>, P/N<PHONE_NUMBER>, or P/N B623M20X2240 from the
swashplate assembly (swashplate).
    (ii) Clean and inspect the support tube for scratches as
depicted in Detail 11, Figure 6 of Airbus Helicopters Alert Service
Bulletin ASB (ASB) BO105-40A-107 (ASB BO105-40A-107); or Detail 11,
Figure 5 of ASB BO105 LS-40A-12 (ASB BO105 LS 40A-12); or Detail 11,
Figure 5 of ASB MBB-BK117-40A-115, (ASB MBB-BK117-40A-115); or
Detail 11, Figure 5 of ASB MBB-BK117 C-2-62A-007 (ASB MBB-BK117 C-2-
62A-007), each Revision 5 and dated July 25, 2017; or Detail 11,
Figure 5 of ASB MBB-BK117 D-2-62A-003, Revision 3, dated July 25,
2017 (ASB MBB-BK117 D-2-62A-003); as applicable to your model
helicopter. If there are scratches on the support tube, before
further flight, rework the cylindrical area to a max depth of 0.1 mm
with a polishing cloth #400 or equivalent polishing cloth. The
reworked area must not exceed 10 mm in width or 3 cm\2\ in area, the
minimum separation between any adjacent reworked areas must be 30
mm, and total reworked areas must not exceed 10 percent of the
cylindrical area.
    (iii) Inspect the clamp for corrosion and correct installation.

    Note 1 to paragraph (g)(1)(iii): A figure of the clamp is
depicted in Detail 9, Figure 6 of ASB BO105-40A-107; or Detail 9,
Figure 5 of ASB BO105 LS-40A-12, ASB MBB-BK117-40A-115, or ASB MBB-
BK117 C-2-62A-007; or Detail 9, Figure 5 of ASB MBB-BK117 D-2-62A-
003; as applicable to your model helicopter.

    (A) If there is corrosion on the clamp, before further flight
remove the clamp from service.
    (B) If the clamp is incorrectly installed, before further flight
install the clamp correctly on the shield as depicted in Detail 10,
Figure 6 of ASB BO105-40A-107; or Detail 10, Figure 5 of ASB BO105
LS-40A-12, ASB MBB-BK117-40A-115, or ASB MBB-BK117 C-2-62A-007; or
Detail 10, Figure 5 of ASB MBB-BK117 D-2-62A-003; as applicable to
your model helicopter.
    (C) Apply a torque between 0.5 Nm and 0.7 Nm to the screw and
install lockwire as depicted in Detail 8, Figure 6 of ASB BO105-40A-
107; or Detail 8, Figure 5 of ASB BO105 LS-40A-12, ASB MBB-BK117-
40A-115, or ASB MBB-BK117 C-2-62A-007; or Detail 8, Figure 5 of ASB
MBB-BK117 D-2-62A-003; as applicable to your model helicopter.
    (iv) Inspect each ball bearing for corrosion. If there is
corrosion on any ball bearing, before further flight, remove the
ball bearing from service.
    (v) Inspect the area under the deflection ring for foreign
objects by removing the lock wire, removing the screws, and removing
the outer deflection ring. If there are any foreign objects, remove
the foreign objects with a lint-free cloth.
    (2) Within 400 hours TIS after the effective date of this AD,
after complying with the actions in paragraph (g)(1) of this AD, and
thereafter at intervals not to exceed 400 hours TIS, inspect the
swashplate by following the Accomplishment Instructions, paragraph
3.B.4 of ASB BO105-40A-107; or paragraph 3.B.3 of ASB BO105 LS-40A-
12, ASB MBB-BK117-40A-115, ASB MBB-BK117 C-2-62A-007, or ASB MBB-
BK117 D-2-62A-003; as applicable to your model helicopter.
    (3) After May 24, 2019 (the effective date of AD 2019-07-07), do
not install a bellows P/N 105-10113.05, P/N<PHONE_NUMBER>, or P/N
4638305043, or a gearbox with a bellows P/N 105-10113.05, P/N
4619305044, or P/N<PHONE_NUMBER> on any helicopter.
    (4) As of the effective date of this AD, do not install a
bellows P/N B623M20X2240 on any helicopter.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, 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 local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the International Validation Branch, send
it to the attention of the person identified in paragraph (i)(1) 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.

(i) Related Information

    (1) For more information about this AD, contact Matt Fuller, AD
Program Manager, Operational Safety Branch, Airworthiness Products
Section, General Aviation & Rotorcraft Unit, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>

    (2) The subject of this AD is addressed in European Aviation
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD
2016-0142R1, dated April 12, 2018. You may view the EASA AD on the
internet at https://www.regulations.gov in Docket No. FAA-2021-0135.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference 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) Airbus Helicopters Alert Service Bulletin ASB (ASB) BO105-
40A-107, Revision 5, dated July 25, 2017.
    (ii) Airbus Helicopters ASB BO105 LS-40A-12, Revision 5, dated
July 25, 2017.
    (iii) Airbus Helicopters ASB MBB-BK117-40A-115, Revision 5,
dated July 25, 2017.
    (iv) Airbus Helicopters ASB MBB-BK117 C-2-62A-007, Revision 5,
dated July 25, 2017.
    (v) Airbus Helicopters ASB MBB-BK117 D-2-62A-003, Revision 3,
dated July 25, 2017.
    (3) For service information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or
at https://www.airbus.com/helicopters/services/technical-support.html.
    (4) You may view this service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call<PHONE_NUMBER>.
    (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 on Issued on May 5, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-11444 Filed 6-1-21; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 75, Number 244 (Tuesday, December 21, 2010)]
[Proposed Rules]
[Pages 79990-79992]
[FR Doc No: 2010-31983]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1255; Directorate Identifier 2010-CE-059-AD]
RIN 2120-AA64

Airworthiness Directives; B-N Group Ltd. Model BN-2, BN-2A, BN-
2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26,
BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-4R
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

    An event has been reported where Glass Fibre Reinforced Plastic
(GFRP) elevator tips have been found deformed on in-service
aircraft. The outboard three inches of the elevator tip assembly
profiles (top and bottom surfaces) had changed from being convex
profiles to concave profiles. There is concern that this could
potentially result in, or be caused by, internal structural
delamination and/or failure. Such a failure could have a serious
effect on the aircraft handling and could potentially result in loss
of control of the aircraft.

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

DATES: We must receive comments on this proposed AD by February 4,
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Airworthiness, Britten-Norman Aircraft Ltd., Bembridge Airport, Isle of
Wight, PO35 5PR, United Kingdom; telephone: +44(0) 20 3371 4000; fax:
+44(0) 20 3371 4001; e-mail<EMAIL_ADDRESS>You may review
copies of the 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>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES. section. Include ``Docket No. FAA-2010-
1255; Directorate Identifier 2010-CE-059-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No.: 2009-0105R2, dated March 9, 2010 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:

    An event has been reported where Glass Fibre Reinforced Plastic
(GFRP) elevator tips have been found deformed on in-service
aircraft. The outboard three inches of the elevator tip assembly
profiles (top and bottom surfaces) had changed from being convex
profiles to concave profiles. There is concern that this could
potentially result in, or be caused by, internal structural
delamination and/or failure. Such a failure could have a serious
effect on the aircraft handling and could potentially result in loss
of control of the aircraft.
    For the reasons stated above, the initial issue of this AD (AD
2009-0105) mandated inspection of the GFRP elevator tips and
replacement of any deformed parts.
    Its Revision 1 (AD 2009-0105R1) extends the compliance time by
three months.
    Its Revision 2 (AD 2009-0105R2) extends the compliance time by
an additional three months.

Relevant Service Information

    Britten-Norman Aircraft Limited has issued Service Bulletin Number
BN-2/SB 313, Issue 3, dated February 24, 2009; Drawing NB-31-235, Issue
13; Drawing NB-31-873, Issue 2; and Drawing NB-31-0906, Issue 3. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.

Differences Between This Proposed AD and the MCAI or Service
Information

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

Costs of Compliance

    We estimate that this proposed AD will affect 135 products of U.S.
registry. We also estimate that it would take about 2 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $10,000 per product.
    Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $1,372,950, or $10,170 per product.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

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

B-N Group Ltd.: Docket No. FAA-2010-1255; Directorate Identifier
2010-CE-059-AD.

Comments Due Date

    (a) We must receive comments by February 4, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to B-N Group Ltd. Models BN-2, BN-2A, BN-2A-
2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26,
BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-
4R airplanes, all serial numbers, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 27: Flight
Controls.

Reason

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

    An event has been reported where Glass Fibre Reinforced Plastic
(GFRP) elevator tips have been found deformed on in-service
aircraft. The outboard three inches of the elevator tip assembly
profiles (top and bottom surfaces) had changed from being convex
profiles to concave profiles. There is concern that this could
potentially result in, or be caused by, internal structural
delamination and/or failure. Such a failure could have a serious
effect on the aircraft handling and could potentially result in loss
of control of the aircraft.
    For the reasons stated above, the initial issue of this AD (AD
2009-0105) mandated inspection of the GFRP elevator tips and
replacement of any deformed parts.
    Its Revision 1 (AD 2009-0105R1) extends the compliance time by
three months.
    Its Revision 2 (AD 2009-0105R2) extends the compliance time by
an additional three months.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Before further flight after the effective date of this AD,
visually inspect for deformation of shape and signs of concavity the
elevator tip assemblies (top and bottom surfaces) as instructed in
paragraphs 6 and 9 of Britten-Norman Aircraft Limited Service
Bulletin Number BN-2/SB 313, Issue 3, dated February 24, 2009. If no
sign of deformity or concavity is found as a result of the
inspection required by paragraph (f)(1) of this AD, no further
action is required by this AD except for the requirements of
paragraph (f)(3) of this AD.
    (2) If signs of deformation or concavity are found, before
further flight, inspect for delamination the elevator tip as
instructed in paragraph 9 of Britten-Norman Aircraft Limited Service
Bulletin Number BN-2/SB 313, Issue 3, dated February 24, 2009.
    (i) If delamination is found as a result of any inspection
required by this AD, before further flight, replace the elevator tip
with a serviceable elevator tip following Britten-Norman Ltd.
Drawing NB-31-235, Issue 13; Britten-Norman Ltd. Drawing NB-31-873,
Issue 2; or Britten-Norman Ltd. Drawing NB-0906, Issue 3, as
applicable to airplane models.
    (ii) If no delamination is found as a result of any inspection
required by this AD, at intervals not to exceed 50 hours time-in-
service (TIS) and until accomplishment of paragraph (f)(2)(iii) of
this AD, inspect for delamination the elevator tip as instructed in
paragraph 9 of Britten-Norman Aircraft Limited Service Bulletin
Number BN-2/SB 313, Issue 3, dated February 24, 2009.
    (iii) Within 12 months after the effective date of this AD,
unless already done as required by paragraph (f)(2)(i) of this AD,
replace the elevator tip with a serviceable elevator tip following
Britten-Norman Ltd. Drawing NB-31-235, Issue 13; Britten-Norman Ltd.
Drawing NB-31-873, Issue 2; or Britten-Norman Ltd. Drawing NB-31-
0906, Issue 3, as applicable to airplane models.
    (3) After the effective date of this AD, do not install elevator
tips on any airplane, unless they have already been inspected in
accordance with Britten-Norman Aircraft Limited Service Bulletin
Number BN-2/SB 313, Issue 3, dated February 24, 2009, and determined
to be free from concavity and delamination.

FAA AD Differences

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

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Taylor Martin, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>. 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.

Related Information

    (h) Refer to MCAI EASA AD No.: 2009-0105R2, dated March 9, 2010;
Britten-Norman Aircraft Limited Service Bulletin Number BN-2/SB 313,
Issue 3, dated February 24, 2009, Britten-Norman Ltd. Drawing NB-31-
235, Issue 13; Britten-Norman Ltd. Drawing NB-31-873, Issue 2; and
Britten-Norman Ltd. Drawing NB-31-0906, Issue 3. For service
information related to this AD, contact Airworthiness, Britten-
Norman Aircraft Ltd., Bembridge Airport, Isle of Wight, PO35 5PR,
United Kingdom; telephone: +44(0) 20 3371 4000; fax: +44(0) 20 3371
4001; e-mail<EMAIL_ADDRESS>You may review copies of
the 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
816-329-4148.

    Issued in Kansas City, Missouri, on December 14, 2010.
William J. Timberlake,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-31983 Filed 12-20-10; 8:45 am]
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[Federal Register Volume 76, Number 65 (Tuesday, April 5, 2011)]
[Notices]
[Pages 18754-18755]
[FR Doc No: 2011-8029]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CP11-30-000; Docket No. CP11-41-000]

Tennessee Gas Pipeline Company; Dominion Transmission, Inc.;
Notice of Onsite Environmental Review

    On April 12 and 13, 2011, the Office of Energy Projects (OEP) staff
will be in Wyoming County, New York, and Tioga and Bradford Counties,
Pennsylvania to gather data for the environmental analysis of two
related projects

proposed by Tennessee Gas Pipeline Company (TGP) and Dominion
Transmission, Inc. (DTI). On April 12, 2011, OEP staff will visit the
location for the proposed Silver Springs Compressor Station associated
with DTI's Ellisburg to Craigs Project under consideration in Docket
No. CP11-41-000. On April 13, 2011, OEP staff will visit the proposed
Loop 315 pipeline route associated with TGP's Northeast Supply
Diversification Project under consideration in Docket No. CP11-30-000.
These onsite reviews will assist staff in completing its evaluation of
the environmental impacts of the proposed projects. Viewing of the
areas is anticipated to be from public access points and adjacent
existing right-of-way.
    All interested parties planning to attend must provide their own
transportation. Those attending should meet at the following locations:

Silver Springs Compressor Station Site Review, April 12, 2011, 9 a.m.
(EST), Meet at DTI Randall Gate Site, 4478 Oak Hill Road (near
intersection of, Oak Hill Road and West Lake Road), Silver Springs, NY
14550.
Loop 315 Site Review, April 13, 2011, 1 p.m. (EST), Meet at TGP
Compressor Station 317, 1249 Tennessee Gas Road, (near intersection of
Routes 14 and 514), Troy, PA 16947.
    Please use the Federal Energy Regulatory Commission's free
eSubscription service to keep track of all formal issuances and
submittals in these dockets. This can reduce the amount of time you
spend researching proceedings by automatically providing you with
notification of these filings, document summaries, and direct links to
the documents. To register for this service, go to http://www.ferc.gov/esubscribenow.htm.
    Information about specific onsite environmental reviews is posted
on the Commission's calendar at http://www.ferc.gov/EventCalendar/EventsList.aspx. For additional information, contact Office of External
Affairs at (866) 208-FERC.

    Dated: March 29, 2011.
Kimberly D. Bose,
Secretary.
[FR Doc. 2011-8029 Filed 4-4-11; 8:45 am]
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