[Federal Register: October 29, 2008 (Volume 73, Number 210)]
[Notices]
[Page 64324-64325]
[DOCID:fr29oc08-59]

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ENVIRONMENTAL PROTECTION AGENCY

[EPA-HQ-OPP-2008-0751; FRL-8386-2]

Pesticide Products; Registration Applications

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice.

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SUMMARY: This notice announces receipt of applications to register
pesticide products containing new active ingredients not included in
any currently registered products pursuant to the provisions of section
3(c)(4) of the Federal Insecticide, Fungicide, and Rodenticide Act
(FIFRA), as amended.

DATES: Comments must be received on or before November 28, 2008.

ADDRESSES: Submit your comments, identified by docket identification
(ID) number EPA-HQ-OPP-2008-0751, by one of the following methods:
     Federal eRulemaking Portal: http://www.regulations.gov.
Follow the on-line instructions for submitting comments.
     Mail: Office of Pesticide Programs (OPP) Regulatory Public
Docket (7502P), Environmental Protection Agency, 1200 Pennsylvania
Ave., NW., Washington, DC 20460-0001.
     Delivery: OPP Regulatory Public Docket (7502P),
Environmental Protection Agency, Rm. S-4400, One Potomac Yard (South
Bldg.), 2777 S. Crystal Dr., Arlington, VA. Deliveries are only
accepted during the Docket Facility's normal hours of operation (8:30
a.m. to 4 p.m., Monday through Friday, excluding legal holidays).
Special arrangements should be made for deliveries of boxed
information. The Docket Facility telephone number is<PHONE_NUMBER>.
    Instructions: Direct your comments to docket ID number EPA-HQ-OPP-
2008-0751. EPA's policy is that all comments received will be included
in the docket without change and may be made available on-line at
http://www.regulations.gov, including any personal information
provided, unless the comment includes information claimed to be
Confidential Business Information (CBI) or other information whose
disclosure is restricted by statute. Do not submit information that you
consider to be CBI or otherwise protected through regulations.gov or e-
mail. The regulations.gov website is an ``anonymous access'' system,
which means EPA will not know your identity or contact information
unless you provide it in the body of your comment. If you send an e-
mail comment directly to EPA without going through regulations.gov,
your e-mail address will be automatically captured and included as part
of the comment that is placed in the docket and made available on the
Internet. If you submit an electronic comment, EPA recommends that you
include your name and other contact information in the body of your
comment and with any disk or CD-ROM you submit. If EPA cannot read your
comment due to technical difficulties and cannot contact you for
clarification, EPA may not be able to consider your comment. Electronic
files should avoid the use of special characters, any form of
encryption, and be free of any defects or viruses.
    Docket: All documents in the docket are listed in the docket index
available at http://www.regulations.gov. Although listed in the index,
some information is not publicly available, e.g., CBI or other
information whose disclosure is restricted by statute. Certain other
material, such as copyrighted material, is not placed on the Internet
and will be publicly available only in hard copy form. Publicly
available docket materials are available either in the electronic
docket at http://www.regulations.gov, or, if only available in hard
copy, at the OPP Regulatory Public Docket in Rm. S-4400, One Potomac
Yard (South Bldg.), 2777 S. Crystal Dr., Arlington, VA. The hours of
operation of this Docket Facility are from 8:30 a.m. to 4 p.m., Monday
through Friday, excluding legal holidays. The Docket Facility telephone
number is<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Chris Pfeifer, Biopesticides and
Pollution Prevention Division (7511P), Office of Pesticide Programs,
Environmental Protection Agency, 1200 Pennsylvania Ave., NW.,
Washington, DC 20460-0001; telephone number:<PHONE_NUMBER>; e-mail
address<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

I. General Information

A. Does this Action Apply to Me?

    You may be potentially affected by this action if you are an
agricultural producer, food manufacturer, or pesticide manufacturer.
Potentially affected entities may include, but are not limited to:
     Crop production (NAICS code 111).
     Animal production (NAICS code 112).
     Food manufacturing (NAICS code 311).
     Pesticide manufacturing (NAICS code 32532).
    This listing is not intended to be exhaustive, but rather provides
a guide for readers regarding entities likely to be affected by this
action. Other types of entities not listed in this unit could also be
affected. The North American Industrial Classification System (NAICS)
codes have been provided to assist you and others in determining
whether this action might apply to certain entities. If you have any
questions regarding the applicability of this action to a particular
entity, consult the person listed under FOR FURTHER INFORMATION
CONTACT.

B. What Should I Consider as I Prepare My Comments for EPA?

     1. Submitting CBI. Do not submit this information to EPA through
regulations.gov or e-mail. Clearly mark the part or all of the
information that you claim to be CBI. For CBI information in a disk or
CD-ROM that you mail to EPA, mark the outside of the disk or CD-ROM as
CBI and then identify electronically within the disk or CD-ROM the
specific information that is

claimed as CBI. In addition to one complete version of the comment that
includes information claimed as CBI, a copy of the comment that does
not contain the information claimed as CBI must be submitted for
inclusion in the public docket. Information so marked will not be
disclosed except in accordance with procedures set forth in 40 CFR part
2.
    2. Tips for preparing your comments. When submitting comments,
remember to:
    i. Identify the document by docket ID number and other identifying
information (subject heading, Federal Register date and page number).
     ii. Follow directions. The Agency may ask you to respond to
specific questions or organize comments by referencing a Code of
Federal Regulations (CFR) part or section number.
    iii. Explain why you agree or disagree; suggest alternatives and
substitute language for your requested changes.
    iv. Describe any assumptions and provide any technical information
and/or data that you used.
    v. If you estimate potential costs or burdens, explain how you
arrived at your estimate in sufficient detail to allow for it to be
reproduced.
    vi. Provide specific examples to illustrate your concerns and
suggest alternatives.
    vii. Explain your views as clearly as possible, avoiding the use of
profanity or personal threats.
    viii. Make sure to submit your comments by the comment period
deadline identified.

II. Registration Applications

    EPA received applications as follows to register pesticide products
containing active ingredients not included in any previously registered
products pursuant to the provision of section 3(c)(4) of FIFRA. Notice
of receipt of these applications does not imply a decision by the
Agency on the applications.
    File Symbol: 53575-GG. Applicant: Pacific Biocontrol Corporation,
14615 NE 13th Court, Suite A, Vancouver, WA 98685. Product name:
Isomate[reg] - LBAM Plus. Active ingredient: (E,E)-9,11-Tetradecadien-
1-y1 Acetate at 2.64%. Proposal classification/Use: Straight-chain
lepidopteron pheromone for the mating disruption of the Light Brown
Apple Moth (LBAM). (J. Pfeifer).

List of Subjects

    Environmental protection, Pesticides and pest.

    Dated: October 9, 2008.
W. Michael McDavit,
Acting Director, Biopesticides and Pollution Prevention Division,
Office of Pesticide Programs.
[FR Doc. E8-25406 Filed 10-28-08; 8:45 am]

BILLING CODE 6560-50-S


[Federal Register Volume 76, Number 196 (Tuesday, October 11, 2011)]
[Proposed Rules]
[Pages 62673-62678]
[FR Doc No: 2011-26113]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-050-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD), for
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, and F4-605R airplanes, that would supersede an existing AD.
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:

    Following the occurrence of cracks on the MLG [main landing
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) was issued to require repetitive
inspections and, as terminating action * * * [.]
    Subsequently, new cases of cracks were discovered during
scheduled maintenance checks by operators of A300B4 and A300-600
type aeroplanes on which the terminating action * * * [was]
embodied. This condition, if not corrected, could affect the
structural integrity of those aeroplanes.
* * * * *
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 November 25,
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, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail<EMAIL_ADDRESS>Internet http://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. 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 Operations office
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 Operations office (telephone<PHONE_NUMBER>) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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-2011-1066;
Directorate Identifier 2011-NM-050-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 based on 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

    On November 3, 2010, we issued AD 2010-23-26, Amendment 39-16516
(75 FR 74610, December 1, 2010). That AD required actions intended to
address an unsafe condition on the products listed above.
    Since we issued AD 2010-23-26, Amendment 39-16516 (75 FR 74610,
December 1, 2010), we have determined that it is necessary to mandate
the optional spot-facing modification specified in paragraph (q) of the
existing AD: The European Aviation Safety Agency (EASA), which is the
aviation authority for the Member States of the European Community, has
issued EASA Airworthiness Directive 2011-0029, dated February 24, 2011
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:

    Following the occurrence of cracks on the MLG [main landing
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) was issued to require repetitive
inspections and, as terminating action, the embodiment of Airbus
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
    Subsequently, new cases of cracks were discovered during
scheduled maintenance checks by operators of A300B4 and A300-600
type aeroplanes on which the terminating action SB's were embodied.
This condition, if not corrected, could affect the structural
integrity of those aeroplanes.
    To address and correct this condition, Airbus developed an
inspection programme for aeroplanes modified in accordance with SB
A300-57-0235 or A300-57-6088. This inspection programme was required
to be implemented by DGAC France AD F-2005-113, original issue and
later revision 1 [parallel to part of FAA AD 2006-12-13, Amendment
39-14639 (71 FR 33994, June 13, 2006)].
    A new EASA [European Aviation Safety Agency] AD 2008-0111,
superseding DGAC France AD F-2005-113R1, was issued to reduce the
applicability. For aeroplanes already compliant with DGAC France AD
F-2005-113R1, no further action was required.
    Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection
programmes of SB A300-57A0246 and SB A300-57A6101 to introduce
repetitive inspections including a new inspection technique for
holes 47 and 54 and to reduce inspections threshold and intervals
from 700 Flight Cycles (FC) to 400 FC until a revised terminating
action is made available.
    For the reasons stated above, EASA AD 2009-0081 superseded EASA
AD 2008-0111 and required operators to comply with the new
inspection programme introduced in Revisions 3 of Airbus SB A300-
57A0246 and Airbus SB A300-57A6101.
    EASA AD 2009-0081 R1 [which corresponds to FAA AD 2010-23-26,
Amendment 39-16516 (75 FR 74610, December 1, 2010)] has been
published to introduce an optional terminating action which
consisted of spot-facing the sensitive holes of the MLG Rib 5 (LH
and RH) bottom flanges.
    Later discussions with Airbus have demonstrated the necessity to
require the spot-facing modification as a final solution (no longer
optional). This new [EASA] AD retains the inspection requirements of
EASA AD 2009-0081 R1, which is superseded, and requires the spot-
facing of sensitive holes of the MLG Rib 5 (LH and RH) bottom
flanges as terminating action.

Required actions include repairing discrepancies (e.g., cracking or a
2nd oversize or greater fastener hole). You may obtain further
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A300-57-0254,
Revision 01, including Appendix 1, dated June 14, 2011; and A300-57-
6110, Revision 01, including Appendix 1, dated June 6, 2011. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.

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

Differences Between This 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

    Based on the service information, we estimate that this proposed AD
would affect about 155 products of U.S. registry.
    The actions that are required by AD 2010-23-26, Amendment 39-16516
(75 FR 74610, December 1, 2010), and retained in this AD take about 79
work-hours per product, at an average labor rate of $85 per work hour.
Required parts cost about $10,270 per product. Based on these figures,
the estimated cost of the currently required actions is $16,985 per
product.
    We estimate that it would take about 100 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $1,317,500, or
$8,500 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 removing Amendment 39-16516 (75 FR
74610, December 1, 2010) and adding the following new AD:

Airbus: Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-
050-AD.

Comments Due Date

    (a) We must receive comments by November 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010).

Applicability

    (c) This AD applies to the airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD;
except airplanes on which Airbus Modification 11912 or 11932 has
been installed.
    (1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, and F4-605R airplanes.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    Following the occurrence of cracks on the MLG [main landing
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) was issued to require repetitive
inspections and, as terminating action, the embodiment of Airbus
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
    Subsequently, new cases of cracks were discovered during
scheduled maintenance checks by operators of A300B4 and A300-600
type aeroplanes on which the terminating action SB's were embodied.
This condition, if not corrected, could affect the structural
integrity of those aeroplanes.
* * * * *

Compliance

    (f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Restatement of Requirements of AD 2000-05-07, Amendment 39-11616 (65 FR
12077, March 8, 2000):

Repetitive Inspections

    (g) Perform a detailed inspection and a high-frequency eddy
current (HFEC) inspection to detect cracks in Gear Rib 5 of the main
landing gear (MLG) attachment fittings at the lower flange, in
accordance with the Accomplishment Instructions of any applicable
service bulletin listed in Table 1 and Table 2 of this AD, at the
time specified in paragraph (g)(1) or (g)(2) of this AD. After April
12, 2000 (the effective date of AD 2000-05-07, Amendment 39-11616
(65 FR 12077, March 8, 2000)), only the service bulletins listed in
Table 2 of this AD may be used. Repeat the inspections thereafter at
intervals not to exceed 1,500 flight cycles, until the actions
specified in paragraph (i), (j), or (l) of this AD are accomplished.

                                    Table 1--Revision 01 of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6087  01....................  March 11, 1998.
 B4-605R, B4-622R and F4-605R
 airplanes.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0234  01....................  March 11, 1998.
 B4-103, and B4-203 airplanes.
----------------------------------------------------------------------------------------------------------------

                                  Table 2--Other Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57A6087  02, including Appendix  June 24, 1999.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       03, including Appendix  May 19, 2000.
                                                        01.
                                                       04, including Appendix  February 19, 2002.
                                                        01.
                                                       05, including Appendix  March 10, 2008.
                                                        01.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57A0234  02....................  June 24, 1999.
 B4-103, and B4-203 airplanes.
                                                       03, including Appendix  September 2, 1999.
                                                        01.
                                                       04, including Appendix  May 19, 2000.
                                                        01.
                                                       05, including Appendix  February 19, 2002.
                                                        01.
----------------------------------------------------------------------------------------------------------------

     (1) For airplanes that have accumulated 20,000 or more total
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect
within 500 flight cycles after March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total
flight cycles as of March 9, 1998: Inspect prior to the accumulation
of 18,000 total flight cycles, or within 1,500 flight cycles after
March 9, 1998, whichever occurs later.

    Note 1:  For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good

lighting at intensity deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying lenses, etc., may be
used. Surface cleaning and elaborate access procedures may be
required.''

    Note 2:  Accomplishment of the initial detailed and HFEC
inspections prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57A0234 or A300-57A6087, both dated August 5,
1997, as applicable, is considered acceptable for compliance with
the initial inspections required by paragraph (g) of this AD.

Repair for Any Crack Found During Inspections Required by Paragraph (g)
of This AD

    (h) If any crack is detected during any inspection required by
paragraph (g) of this AD, prior to further flight, accomplish the
requirements of paragraph (h)(1) or (h)(2) of this AD, as
applicable.
    (1) If a crack is detected at one hole only, and the crack does
not extend out of the spotface of the hole, repair in accordance
with the Accomplishment Instructions of the applicable service
bulletin in Table 2 of this AD.
    (2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or its delegated agent).

Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD

    (i) Except as required by paragraph (l) of this AD, prior to the
accumulation of 21,000 total flight cycles, or within 2 years after
October 20, 1999 (the effective date of AD 99-19-26, Amendment 39-
11313 (64 FR 49966, September 15, 1999)), whichever occurs later:
Modify Gear Rib 5 of the MLG attachment fittings at the lower flange
in accordance with the Accomplishment Instructions of the applicable
service bulletin in Table 3 of this AD. After July 18, 2006 (the
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994,
June 13, 2006)), only Revision 04 of Airbus Service Bulletin A300-
57-6088, and Revisions 04 and 05 of Airbus Service Bulletin A300-57-
0235 may be used. Accomplishment of this modification constitutes
terminating action for the repetitive inspection requirements of
paragraphs (g) and (j) of this AD.

                             Table 3--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6088  01, including Appendix  February 1, 1999.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       02....................  September 5, 2002.
                                                       04....................  December 3, 2003.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0235  01, including Appendix  February 1, 1999.
 B4-103, and B4-203 airplanes.                          01.
                                                       03....................  September 5, 2002.
                                                       04....................  March 13, 2003.
                                                       05....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------

    Note 3: Accomplishment of the modification required by paragraph
(i) of this AD prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5,
1998; as applicable; is acceptable for compliance with the
requirements of that paragraph.

Restatement of Requirements of AD 2006-12-13, Amendment 39-14639 (71 FR
33994, June 13, 2006):

Additional Repetitive Inspections

    (j) For airplanes on which the modification specified in
paragraph (i) or (l) of this AD has not been done before July 18,
2006 (the effective date of AD 2006-12-13, Amendment 39-14639 (69 FR
54063, September 7, 2004)), perform a detailed and an HFEC
inspection to detect cracks of the lower flange of Gear Rib 5 of the
MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the
applicable service bulletin listed in Table 4 of this AD. Perform
the inspections at the applicable time specified in paragraph
(j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Repeat the inspections
thereafter at intervals not to exceed 700 flight cycles until the
terminating modification required by paragraph (l) of this AD is
accomplished. Accomplishment of the inspections per paragraph (j) of
this AD terminates the inspection requirements of paragraph (g) of
this AD.

                              Table 4--Service Bulletins for Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57A6087  04, including Appendix  February 19, 2002.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       05, including Appendix  March 10, 2008.
                                                        01.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57A0234  05, including Appendix  February 19, 2002.
 B4-103, and B4-203 airplanes.                          01.
----------------------------------------------------------------------------------------------------------------

    (1) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes that have accumulated 18,000 or
more total flight cycles as of July 18, 2006: Within 700 flight
cycles after July 18, 2006.
    (2) For Model A300 B2-1C, B2K-3C, and B2-203 airplanes that have
accumulated less than 18,000 total flight cycles as of July 18,
2006: Prior to the accumulation of 18,000 total flight cycles, or
within 700 flight cycles after July 18, 2006, whichever occurs
later.
    (3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have
accumulated less than 18,000 total flight cycles as of July 18,
2006: Prior to the accumulation of 14,500 total flight cycles, or
within 700 flight cycles after July 18, 2006, whichever occurs
later.
    (4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes that have accumulated less than 18,000
total flight cycles as of July 18, 2006: Prior to the accumulation
of 11,600 total flight cycles, or within 700 flight cycles after
July 18, 2006, whichever occurs later.

Crack Repair

    (k) If any crack is detected during any inspection required by
paragraph (j) of this AD, prior to further flight, accomplish the
requirements of paragraphs (k)(1) and (k)(2) of this AD, as
applicable.
    (1) If a crack is detected at only one hole, and the crack does
not extend out of the spotface of the hole, repair in accordance
with Airbus Service Bulletin A300-57A0234, Revision 05, including
Appendix 01, dated February 19, 2002 (for Model A300 B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087,
Revision 04, including Appendix 01, dated February 19, 2002; or
A300-57A6087, Revision 05, dated March 10, 2008 (for Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R
airplanes); as applicable.
    (2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the EASA (or its delegated agent).

Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD for Certain Airplanes

    (l) For airplanes on which the terminating modification in
paragraph (i) of this AD has not been accomplished before July 18,
2006: At the earlier of the times specified in paragraphs (l)(1) and
(l)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings
at the lower flange. Except as provided by paragraph (m) of this AD,
do the modification in accordance with the applicable service
bulletin in Table 5 of this AD. This action terminates the
repetitive inspections requirements of paragraphs (g) and (j) of
this AD.
    (1) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999, whichever is later.
    (2) Within 16 months after July 18, 2006.

                             Table 5--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6088  04....................  December 3, 2003.
 B4-605R, B4-622R and F4-605R
 airplanes.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0235  04....................  March 13, 2003.
 B4-103, and B4-203 airplanes.
                                                       05....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------

    (m) Where the applicable service bulletin specified in paragraph
(l) of this AD specifies to contact Airbus for modification
instructions; or if there is a previously installed repair at any of
the affected fastener holes; or if a crack is found when
accomplishing the modification: Prior to further flight, modify in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the EASA (or its delegated agent).

Actions Accomplished per Previous Issues of Service Bulletins

    (n) Actions accomplished before July 18, 2006, in accordance
with the service bulletins listed in Table 6 of this AD, are
considered acceptable for compliance with the corresponding action
specified in paragraphs (g) through (m) of this AD.

                                  Table 6--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                   Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0235.............................  02, including Appendix 01...  September 27, 1999.
                                           03..........................  September 5, 2002.
A300-57-6088.............................  02..........................  September 5, 2000.
                                           03..........................  March 13, 2003.
----------------------------------------------------------------------------------------------------------------

No Reporting

    (o) Although the service bulletins identified in Tables 1, 2, 3,
4, 5, and 6 of this AD specify to submit certain information to the
manufacturer, this AD does not include such a requirement.
    Restatement of Requirements of AD 2010-23-26, Amendment 39-16516
(75 FR 74610, December 1, 2010), with Certain Service Information
Required after the Effective Date of This AD:

Actions and Compliance

    (p) Unless already done, do the following actions.
    (1) At the applicable time specified in paragraph (p)(2) of this
AD, perform a detailed inspection for cracking at the locations
specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of
this AD, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated
March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009, or Revision 04, dated September 9, 2009; as applicable. As
of the effective date of this AD only Revision 04 of these service
bulletins may be used.
    (i) The bottom flange and vertical web in the area between the
wing rear spar/gear Rib 5 attachment and the forward reaction-rod
pick-up lug.
    (ii) On the inboard side, around the fastener holes at locations
43, 47 to 50, 52, and 54.
    (iii) On the outboard side, the lower flange, the vertical web
and around the fastener holes at locations 43, 47 to 50, 52 and 54.
    (2) Do the inspection required by paragraph (p)(1) of this AD at
the later of the times in paragraphs (p)(2)(i) and (p)(2)(ii) of
this AD.
    (i) Within 400 flight cycles after the accomplishment of the
actions required by paragraph (i) or (l) of this AD, as applicable.
    (ii) Within 400 flight cycles or 4 months after January 5, 2011
(the effective date of AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010)), whichever occurs first.
    (3) If no cracking is detected during the inspection required by
paragraph (p)(1) of this AD, before further flight, perform a
fluorescent penetrant inspection (FPI) at holes location 47 and 54,
in the right-hand and left-hand MLG Rib 5 attachment fitting lower
flange, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57A0246, Revision 03, dated March
11, 2009, or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009, or Revision 04, dated September 9, 2009; as applicable. As
of the effective date of this AD, only Revision 04 of these service
bulletins may be used.
    (4) Thereafter, at intervals not to exceed 400 flight cycles,
repeat the detailed and FPI inspections, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57A0246, Revision 03, dated March 11, 2009, or Revision 04,
dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated
September 9, 2009; as applicable; until the terminating action
required by paragraph (q) of this AD has been

accomplished. As of the effective date of this AD, only Revision 04
of these service bulletins may be used.
    (5) If any crack is detected during any of the inspections
required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, and
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated
March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March
11, 2009, or Revision 04, dated September 9, 2009; recommends
contacting Airbus for appropriate action: Before further flight,
contact Airbus for a repair solution, and do the repair; or repair
the cracking using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or EASA or its
delegated agent. As of the effective date of this AD, only Revision
04 of these service bulletins may be used.
    New Requirements of This AD:

Terminating Action

    (q) Within 30 months after the effective date of this AD: Modify
the spot-faces around all the fastener holes at locations 43, 47 to
50, 52, and 54 (except for spot-faces of holes which have been
previously repaired) on the bottom flange MLG ribs, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A300-57-0254, Revision 01, including Appendix 1, dated June
14, 2011; or Airbus Mandatory Service Bulletin A300-57-6110,
Revision 01, including Appendix 1, dated June 6, 2011; as
applicable. Accomplishing this modification terminates the
repetitive inspection requirements of paragraph (p)(4) of this AD.

Credit for Actions Accomplished in Accordance With Previous Service
Information

    (r) Modifying the spot-faces before the effective date of this
AD, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-0254, dated June 4, 2010; or
Airbus Mandatory Service Bulletin A300-57-6110, dated June 7, 2010;
as applicable; is considered acceptable for compliance with the
requirements of paragraph (q) of this AD.

FAA AD Differences

    Note 4: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

    (s) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): Manager,
International Branch, ANM-116, 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, Washington 98057-3356; telephone
(425) 227-2125; fax<PHONE_NUMBER>. Information may be e-mailed to:
<EMAIL_ADDRESS>Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD. AMOCs approved previously in
accordance with AD 2000-05-07, Amendment 39-11616 (65 FR 12077,
March 8, 2000); AD 2006-12-13, Amendment 39-14639 (69 FR 54063,
September 7, 2004); and AD 2010-23-26, Amendment 39-16516 (75 FR
74610, December 1, 2010), are approved as AMOCs for the
corresponding provisions of this AD.
    (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.

Related Information

    (t) Refer to MCAI EASA Airworthiness Directive 2011-0029, dated
February 24, 2011; and the service information specified in Table 7
of this AD, for related information.

                                      Table 7--Related Service Information
----------------------------------------------------------------------------------------------------------------
                Airbus--                             Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A300-57A0246.  04, including Appendices 1 and   September 9, 2009.
                                           2.
Mandatory Service Bulletin A300-57-0254.  01.............................  June 14, 2011.
Mandatory Service Bulletin A300-57A6101.  04, including Appendices 1 and   September 9, 2009.
                                           2.
Mandatory Service Bulletin A300-57-6110.  01.............................  June 6, 2011.
Service Bulletin A300-57A0234...........  02.............................  June 24, 1999.
                                          03, including Appendix 01......  September 2, 1999.
                                          04, including Appendix 01......  May 19, 2000.
                                          05, including Appendix 01......  February 19, 2002.
Service Bulletin A300-57A6087...........  02, including Appendix 01......  June 24, 1999.
                                          03, including Appendix 01......  May 19, 2000.
                                          04, including Appendix 01......  February 19, 2002.
                                          05, including Appendix 01......  March 10, 2008.
Service Bulletin A300-57-0235...........  04.............................  March 13, 2003.
                                          05.............................  December 3, 2003.
Service Bulletin A300-57-6088...........  04.............................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------

    Issued in Renton, Washington, on September 30, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-26113 Filed 10-7-11; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 88, Number 211 (Thursday, November 2, 2023)]
[Notices]
[Page 75352]
[FR Doc No: 2023-24175]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-98810; File No. SR-CboeEDGA-2023-015]

Self-Regulatory Organizations; Cboe EDGA Exchange, Inc.; Notice
of Withdrawal of Proposed Rule Change To Amend Its Fee Schedule Related
to Physical Port Fees

October 27, 2023
    On September 1, 2023, Cboe EDGA Exchange, Inc. (``Exchange'') filed
with the Securities and Exchange Commission (``Commission''), pursuant
to Section 19(b)(1) of the Securities Exchange Act of 1934
(``Act''),\1\ and Rule 19b-4 thereunder,\2\ a proposed rule change to
amend certain connectivity and port fees.
---------------------------------------------------------------------------

    \1\ 15 U.S.C. 78s(b)(1).
    \2\ 17 CFR 240.19b-4.
---------------------------------------------------------------------------

    The proposed rule change was immediately effective upon filing with
the Commission pursuant to Section 19(b)(3)(A) of the Act.\3\ The
proposed rule change was published for comment in the Federal Register
on September 20, 2023.\4\ On September 29, 2023, pursuant to Section
19(b)(3)(C) of the Act,\5\ the Commission: (1) temporarily suspended
the proposed rule change; and (2) instituted proceedings under Section
19(b)(2)(B) of the Act \6\ to determine whether to approve or
disapprove the proposed rule change.\7\ On October 25, 2023, the
Exchange withdrew the proposed rule change (SR-CboeEDGA-2023-015).
---------------------------------------------------------------------------

    \3\ 15 U.S.C. 78s(b)(3)(A). A proposed rule change may take
effect upon filing with the Commission if it is designated by the
exchange as ``establishing or changing a due, fee, or other charge
imposed by the self-regulatory organization on any person, whether
or not the person is a member of the self-regulatory organization.''
15 U.S.C. 78s(b)(3)(A)(ii).
    \4\ See Securities Exchange Act Release No. 98394 (September 14,
2023), 88 FR 64947.
    \5\ 15 U.S.C. 78s(b)(3)(C).
    \6\ 15 U.S.C. 78s(b)(2)(B).
    \7\ See Securities Exchange Act Release No. 98652, 88 FR 68677
(October 4, 2023).

    For the Commission, by the Division of Trading and Markets,
pursuant to delegated authority.\8\
---------------------------------------------------------------------------

    \8\ 17 CFR 200.30-3(a)(12).
---------------------------------------------------------------------------

J. Matthew DeLesDernier,
Deputy Secretary.
[FR Doc. 2023-24175 Filed 11-1-23; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 83, Number 50 (Wednesday, March 14, 2018)]
[Notices]
[Pages 11192-11193]
[FR Doc No: 2018-05106]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

Notice of Attendance at the Colorado Public Utilities
Commission's Fifth Commissioner Information Meeting

    The Federal Energy Regulatory Commission (Commission) hereby gives
notice that members of its staff may attend the Colorado Public
Utilities Commission's Commissioner Information Meeting (CIM) as noted
below. Their attendance is part of the Commission's ongoing outreach
efforts.
    The CIM will be held on March 20, 2018 from 9:00 a.m. until 3:00
p.m. Mountain Time at the Colorado Public Utilities Commission, Hearing
Room A, 1560 Broadway, Suite 250, Denver, CO 80202. The phone number is
(303) 894-2533.
    The discussions may address matters at issue in the following
proceedings:

Docket No. ER12-1179, Southwest Power Pool, Inc.
Docket No. ER15-1809, ATX Southwest, LLC
Docket No. ER15-2028, Southwest Power Pool, Inc.
Docket No. ER15-2115, Southwest Power Pool, Inc.
Docket No. ER15-2236, Midwest Power Transmission Arkansas, LLC
Docket No. ER15-2237, Kanstar Transmission, LLC
Docket No. ER15-2324, Southwest Power Pool, Inc.
Docket No. ER15-2594, South Central MCN LLC
Docket No. EL16-91, Southwest Power Pool, Inc.
Docket No. EL18-19, Southwest Power Pool, Inc.
Docket No. EL16-108, Tilton Energy v. Midcontinent Independent
System Operator, Inc.
Docket No. EL16-110, Southwest Power Pool, Inc.
Docket No. ER16-204, Southwest Power Pool, Inc.
Docket No. ER16-2522, Southwest Power Pool, Inc.
Docket No. ER16-2523, Southwest Power Pool, Inc.
Docket No. EL17-11, Alabama Power Co. v. Southwest Power Pool, Inc.
Docket No. EL17-21, Kansas Electric Co. v. Southwest Power Pool,
Inc.
Docket No. EL17-69, Buffalo Dunes et al. v. Southwest Power Pool,
Inc.
Docket No. EL17-86, Nebraska Public Power District v. Southwest
Power Pool, Inc.
Docket No. ER17-426, Southwest Power Pool, Inc.
Docket No. ER17-428, Southwest Power Pool, Inc.
Docket No. ER17-469, Southwest Power Pool, Inc.
Docket No. ER17-772, Southwest Power Pool, Inc.
Docket No. ER17-889, Southwest Power Pool, Inc.
Docket No. ER17-953, South Central MCN LLC
Docket No. ER17-1092, Southwest Power Pool, Inc.
Docket No. ER17-1575, Southwest Power Pool, Inc.
Docket No. ER17-2229, Southwest Power Pool, Inc.
Docket No. ER18-171, Southwest Power Pool, Inc.
Docket No. ER18-194, Southwest Power Pool, Inc.
Docket No. ER18-195, Southwest Power Pool, Inc.
Docket No. ER18-374, Southwest Power Pool, Inc.
Docket No. ER18-381, Southwest Power Pool, Inc.
Docket No. ER18-499, Southwestern Electric Power Company

Docket No. ER18-500, Southwestern Electric Power Company
Docket No. ER18-590, Southwest Power Pool, Inc.
Docket No. ER18-594, Southwest Power Pool, Inc.
Docket No. ER18-592, Southwest Power Pool, Inc.
Docket No. ER18-599, Southwest Power Pool, Inc.
Docket No. ER18-736, Southwest Power Pool, Inc.
Docket No. ER18-748, Southwest Power Pool, Inc.
Docket No. ER18-769, Southwest Power Pool, Inc.
Docket No. ER18-840, Xcel Energy Services, Inc.
Docket No. ER18-854, Southwest Power Pool, Inc.
Docket No. EL18-9-000, Xcel Energy Services, Inc. v. Southwest Power
Pool, Inc.
Docket No. EL18-20-000, Indicated SPP Transmission Owners v.
Southwest Power Pool, Inc.
Docket No. EL18-26, EDF Renewable Energy, Inc. v. Midcontinent
Independent System Operator, Inc., Southwest Power Pool, Inc., and
PJM Interconnection, L.L.C.
Docket No. EL18-35, Southwest Power Pool, Inc.

    This meeting is open to the public.
    For more information, contact Patrick Clarey, Office of Energy
Market Regulation, Federal Energy Regulatory Commission at (317) 249-
5937 or p[email protected].

    Dated: March 6, 2018.
Kimberly D. Bose,
Secretary.
[FR Doc. 2018-05106 Filed 3-13-18; 8:45 am]
 BILLING CODE 6717-01-P