[Federal Register Volume 80, Number 27 (Tuesday, February 10, 2015)]
[Rules and Regulations]
[Pages 7290-7298]
[FR Doc No: 2015-01710]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0142; Directorate Identifier 2012-NM-161-AD;
Amendment 39-18093; AD 2015-02-24]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2007-03-18, AD
2008-17-02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model
A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R,
and F4-600R series airplanes, and Model A300 C4-605R Variant F
airplanes (collectively called Model A300-600 series airplanes); and
Model A310 series airplanes. AD 2007-03-18, AD 2008-17-02, AD 2012-08-
03, and AD 2012-15-14 required repetitive inspections of the forward
lugs of the aft bearing at rib 5 of the main landing gear (MLG) on the
left-hand (LH) and right-hand (RH) wings, and repair if necessary; and
installation of new bushes with increased interference fit in the
forward lug of the aft bearing at rib 5 of the MLG on the LH and RH
wings. This new AD adds airplanes to the applicability; and adds, for
certain airplanes, repetitive inspections of the MLG rib 5 aft bearing
forward lugs, and repair if necessary. This AD was prompted by reports
of cracking in the forward lug of the MLG rib 5 aft bearing attachment.
We are issuing this AD to detect and correct cracking of the forward
lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings,
which could affect the structural integrity of the MLG attachment,
resulting in possible MLG collapse during landing or rollout.

DATES: This AD becomes effective March 17, 2015.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 17,
2015.
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 11, 2012 (77 FR 46937, August 7, 2012).
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 29,
2012 (77 FR 24367, April 24, 2012).
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 17, 2008 (73 FR 47032, August 13, 2008).
    The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
February 6, 2007 (72 FR 2612, January 22, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0142; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS,
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51;
email<EMAIL_ADDRESS>Internet http://www.airbus.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>. It
is also available on the Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2014-0142.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116,

Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA
98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008-17-02, Amendment 39-15640 (73 FR 47032,
August 13, 2008); AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April
24, 2012); and AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August
7, 2012). AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14, applied to
certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series
airplanes); and Model A310 series airplanes. The NPRM published in the
Federal Register on March 12, 2014 (79 FR 13938).
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2012-0176, dated September 7, 2012, corrected
September 20, 2012 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:

Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 aft
fitting forward lug have been reported on A310 family aeroplanes. In
some instances, corrosion pits caused the cracking of the forward
lug.

This condition, if not detected and corrected, may lead to the
complete failure of the fitting and thus could affect the structural
integrity of the MLG installation.

EASA ADs 2006-0372R1 (http://ad.easa.europa.eu/blob/easa_ad_2006_0372_R1_superseeded.pdf/AD_2006-0372R1_1), 2007-0195
(http://ad.easa.europa.eu/blob/easa_ad_2007_0195_superseded.pdf/AD_2007-0195_1) [which corresponds with FAA AD 2008-17-02, Amendment
39-15640 (73 FR 47032, August 13, 2008)], 2010-0250 (http://ad.easa.europa.eu/blob/easa_ad_2010_0250_superseded.pdf/AD_2010-0250_1) [which corresponds with FAA AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012)] and 2010-0251 (http://ad.easa.europa.eu/blob/easa_ad_2010_0251_superseded.pdf/AD_2010-0251_1) [which corresponds with FAA AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012)] were issued to address this
condition and required a repetitive inspection programme of the MLG
Rib 5 fitting forward lugs and, as terminating action, the
embodiment of mandatory design change (bushes with increased
interference fit).

MLG Rib 5 forward lug on A320 family aeroplanes is a similar design
to the A300/A300-600/A310 family. Since those [EASA] ADs were
issued, on two A321 aeroplanes, post modification (bushes with
increased interference fit) MLG Rib 5 forward lugs were reportedly
found ruptured. One other case was due to a sealant discrepancy that
led to water ingress and consequently corrosion initiation, leading
to cracking. Subsequent investigation results have shown that a
remaining defect, not removed during the repair, had propagated,
resulting in rupture of the lug.

For the reasons stated above, this new [EASA] AD retains the
requirements of EASA ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-
0251, which are superseded, expands the applicability to all models
and series of A300, A310, A300-600 and A300-600ST aeroplanes, and
requires:
--For aeroplanes not yet modified or repaired, implementation of
Modification Service Bulletin (SB) A300-57-0249, A310-57-2090, A300-
57-6106, or A300-57-9019, all at Revision 3, and
--for aeroplanes which already embody that modifications, at
original issue or revision 01 or 02 of the applicable SB, or have
MLG Ribs already repaired in accordance with Airbus repair
instruction R57240221 or R57249121, implementation of an additional
inspection programme [repetitive detailed inspection for cracking or
ultrasonic inspections for any crack indication] and associated
corrective action(s) [detailed inspection for cracking if any crack
indication found, and repair].

The unsafe condition is cracking of the forward lugs of the aft bearing
at rib 5 of the MLG on the LH and RH wings, which could affect the
structural integrity of the MLG attachment, resulting in possible MLG
collapse during landing or rollout.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0142-0002.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 13938, March 12, 2014) and the FAA's response to each comment.

Request To Withdraw the NPRM (79 FR 13938, March 12, 2014)

    United Parcel Service (UPS) requested that we withdraw the NPRM (79
FR 13938, March 12, 2014) and focus on airplanes that have been
serviced at the facilities where the two airplanes specified in the
Discussion section of the NPRM had been reworked. UPS stated that both
events are the result of an operator not following procedures.
    We disagree with the commenter's request to withdraw the NPRM (79
FR 13938, March 12, 2014). This issue concerns more than one operator
and airplane model. We have no data indicating that these events are
definitively limited to just one repair station or operator. Therefore,
the unsafe condition may exist on other airplanes of a similar type
design. Consequently, the actions required by this final rule must be
done for airplanes identified in paragraph (c) of this AD. We have not
changed this AD in this regard.

Request To Revise Post-Modification Repetitive Inspection

    UPS requested that we revise the post-modification repetitive
inspections to a one-time inspection. UPS stated that it does not
believe that the root cause of the reported events is addressed in the
NPRM (79 FR 13938, March 12, 2014). UPS explained that the primary
focus of Airbus Mandatory Service Bulletin A300-57-6106, Revision 03,
dated January 26, 2012, and the incident investigation is on sealing
and protection in the bushing head area. UPS stated that the only
difference between the sealing process of Airbus Mandatory Service
Bulletin A300-57-6106, Revision 03, dated January 26, 2012, and prior
service bulletin revision levels, is the application of a single coat
of polyurethane paint applied over the fillet seal around the bushing
flange. UPS explained that, based on a process review of Airbus Service
Bulletin A300-57-6106 and the failure analysis results from the two
post-modification reported events, it concurs that a post-modification
check of the modification integrity is valid; however, the post-
modification repetitive inspection should be a one-time inspection to
verify proper accomplishment of the rework process.
    We disagree with the commenter's request to revise the post-
modification repetitive inspections to a one-time inspection. The
corresponding MCAI specifies that the inspection be repeated; FAA ADs
match the MCAI requirements if the MCAI provides an adequate level of
safety and does not conflict with FAA policies. The sealing process
could be compromised over time. Thus a repetitive inspection is
considered necessary to ensure that corrosion will not occur and to
ensure the structural integrity of the MLG rib 5. However, under the
provisions of paragraph (aa) of this AD, we might approve requests for
adjustments to the compliance time if data are submitted to
substantiate that such an adjustment would provide an acceptable level
of safety. We have not changed this AD in this regard.

Request To Supersede AD 2007-03-18, Amendment 39-14929 (72 FR 5919,
February 8, 2007)

    UPS requested that we revise the wording in paragraph (o) of the
NPRM (79 FR 13938, March 12, 2014) to terminate the inspections
required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8,
2007); and to add AD 2007-03-18 to the list of superseded ADs in
paragraph (b)(1) of the NPRM. UPS stated that it believes the intent of
paragraph (g) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August
7, 2012), was to terminate the AD 2007-03-18 inspection requirements
upon initiation of inspections as described in Airbus Mandatory Service
Bulletin A300-57-6107, including Appendix 01, dated August 8, 2007.
    We agree with the commenter's request to add AD 2007-03-18,
Amendment 39-14929 (72 FR 5919, February 8, 2007), to the list of
superseded ADs in this final rule. We have revised paragraph (b) of
this AD by removing paragraph (b)(2) of the NPRM (79 FR 13938, March
12, 2014); re-designating paragraph (b)(1) of the NPRM as paragraph (b)
of this AD; adding new paragraph (b)(1) to this AD, which adds AD 2007-
03-18 to the list of superseded ADs in this AD; and re-designating
paragraphs (b)(1)(i) through (b)(1)(iii) of the NPRM as paragraphs
(b)(2) through (b)(4) of this AD, respectively.

Request To Remove Repair Approval Requirement

    UPS requested that we remove the statement ``For a repair method to
be approved, the repair approval must specifically refer to this AD''
in paragraph (x) of the NPRM (79 FR 13938, March 12, 2014). UPS
acknowledged that the rules governing the AD repair and deviation
approval process for foreign-manufactured aircraft differ from
domestic-built airplanes. UPS recommended that the FAA meet with U.S.
operators of foreign-built airplanes to discuss concerns about repair
instructions being used that might not fully address the unsafe
condition and to review options to alleviate those concerns.
    We concur with the commenter's request to remove from this final
rule the requirement that repair approvals must specifically refer to
this AD. Our responses to specific aspects of this request are
presented as follows.
    Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD. The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact
the manufacturer for corrective actions, such as a repair. Briefly, the
Airworthy Product paragraph allowed owners/operators to use corrective
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved
by the State of Design Authority (or its delegated agent) are
considered to be FAA-approved.
    In the NPRM (79 FR 13938, March 12, 2014), we proposed to prevent
the use of repairs that were not specifically developed to correct the
unsafe condition, by requiring that the repair approval provided by the
State of Design Authority or its delegated agent specifically refer to
this FAA AD. This change was intended to clarify the method of
compliance and to provide operators with better visibility of repairs
that are specifically developed and approved to correct the unsafe
condition. In addition, we proposed to change the phrase ``its
delegated agent'' to include ``the Design Approval Holder (DAH) with
State of Design Authority's design organization approval'' to refer to
a DAH authorized to approve required repairs for the proposed AD.
    UPS also commented on an NPRM having Directorate Identifier 2012-
NM-101-AD (78 FR 78285, December 26, 2013). UPS stated the following:
``The proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed that paragraph and
retitled it ``Contacting the Manufacturer.'' This paragraph now
clarifies that for any requirement in this AD to obtain corrective
actions from a manufacturer, the actions must be accomplished using a
method approved by the FAA, EASA, or Airbus's EASA Design Organization
Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
    This clarification does not remove flexibility afforded previously
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that, in many
cases, the foreign manufacturer's service bulletin and the foreign
authority's MCAI may have been issued some time before the FAA AD.
Therefore, the DOA may have provided U.S. operators with an approved
repair, developed with full awareness of the unsafe condition, before
the FAA AD is issued. Under these circumstances, to comply with the FAA
AD, the operator would be required to go back to the manufacturer's DOA
and obtain a new approval document, adding time and expense to the
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this

AD. Before adopting such a requirement, the FAA will coordinate with
affected DAHs and verify they are prepared to implement means to ensure
that their repair approvals consider the unsafe condition addressed in
the AD. Any such requirements will be adopted through the normal AD
rulemaking process, including notice-and-comment procedures, when
appropriate.
    We have also decided not to include a generic reference to either
the ``delegated agent'' or the ``DAH with State of Design Authority
design organization approval,'' but instead we will provide the
specific delegation approval granted by the State of Design Authority
for the DAH.

Change to Paragraph (h)(3) of This AD

    We removed a requirement to use the latest revision of certain
service information, which appeared as the last sentence at the end of
paragraph (h)(3) of the NPRM (79 FR 13938, March 12, 2014). That
requirement already appears in paragraph (h)(2) of this AD.

Conclusion

    We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the
NPRM (79 FR 13938, March 12, 2014) for correcting the unsafe condition;
and
     Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 13938, March 12, 2014).
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service bulletins.
    Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A310-57-2090, Revision 02, dated June 18,
2010. The service information describes procedures for installation of
new bushes with increased interference fit in the forward lug of the
aft bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012. The service information
describes procedures for inspections of the forward lugs of the aft
bearing at rib 5 of the MLG on the LH and RH wings.
    This service information is reasonably available; see ADDRESSES for
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 194 airplanes of U.S. registry.
    The actions that are required by AD 2008-17-02, Amendment 39-15640
(73 FR 47032, August 13, 2008), and retained in this AD take about 5
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the actions that were
required by AD 2008-17-02 is $425 per product.
    The actions that are required by AD 2012-08-03, Amendment 39-17019
(77 FR 24367, April 24, 2012), and retained in this AD take about 38
work-hours per product, at an average labor rate of $85 per work-hour.
Required parts cost about $4,590 per product. Based on these figures,
the estimated cost of the actions that were required by AD 2012-08-03
is $7,820 per product.
    The actions that are required by AD 2012-15-14, Amendment 39-17143
(77 FR 46937, August 7, 2012), and retained in this AD take about 3
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the actions that were
required by AD 2012-15-14 is $255 per product.
    We also estimate that it would take about 3 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $49,470, or $255 per product.
    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD. We
have no way of determining the number of products that may need these
actions.
    According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is 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.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);

    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0142; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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 removing Airworthiness Directive (AD)
2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007); AD 2008-
17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008); AD 2012-08-
03, Amendment 39-17019 (77 FR 24367, April 24, 2012); and AD 2012-15-
14, Amendment 39-17143 (77 FR 46937, August 7, 2012); and adding the
following new AD:

2015-02-24 Airbus: Amendment 39-18093. Docket No. FAA-2014-0142;
Directorate Identifier 2012-NM-161-AD.

(a) Effective Date

    This AD becomes effective March 17, 2015.

(b) Affected ADs

    This AD replaces the ADs specified in paragraphs (b)(1) through
(b)(4) of this AD.
    (1) AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8,
2007).
    (2) AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13,
2008).
    (3) AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24,
2012).
    (4) AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7,
2012).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category, all
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203
airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking in the forward lug
of the main landing gear (MLG) rib 5 aft bearing attachment. We are
issuing this AD to detect and correct cracking of the forward lugs
of the aft bearing at rib 5 of the MLG on the left-hand (LH) and
right-hand (RH) wings, which could affect the structural integrity
of the MLG attachment, resulting in possible MLG collapse during
landing or rollout.

(f) Compliance

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

(g) Retained Repetitive Detailed Inspection and Corrective Actions

    This paragraph restates the requirements of paragraph (f) of AD
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008). For
Model A310 airplanes, except for those where LH and RH wing MLG rib
5 forward lugs have been repaired by installation of oversized
interference fit bushes as per Airbus A310 Repair Instruction R572-
49121, or which have had Airbus Service Bulletin A310-57-2090
(Airbus Modification 13329) embodied in service: Do the actions
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57A2088, dated November 6, 2006.
    (1) Before the accumulation of 12,000 total flight cycles, or
within 14 days after February 6, 2007 (the effective date of AD
2007-02-09, Amendment 39-14896 (72 FR 2612, January 22, 2007)),
whichever occurs later: Perform a detailed visual inspection of the
LH and RH wing MLG rib 5 aft bearing forward lugs.
    (2) If any crack is detected at LH and/or RH aft bearing forward
lug, contact Airbus and proceed with the replacement before next
flight.
    (3) Repeat the inspection at intervals not exceeding 100 flight
cycles.

(h) Retained Actions and Compliance

    This paragraph restates the requirements of paragraph (g) of AD
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008), with
new service information for paragraphs (h)(2), (h)(3), and
(h)(4)(ii) of this AD, and specific delegation approval language in
paragraphs (h)(3) and (h)(4)(ii) of this AD. For Model A310
airplanes, except for those where LH and RH wing MLG rib 5 forward
lugs have been repaired by installation of oversized interference
fit bushes as per Airbus A310 Repair Instruction R572-49121, or
which have had Airbus Service Bulletin A310-57-2090 (Airbus
Modification 13329) embodied in service: Before the accumulation of
12,000 total flight cycles or before the accumulation of 12,000
flight cycles on MLG rib 5, or within 14 days after September 17,
2008 (the effective date of AD 2008-17-02), whichever occurs latest,
perform either a detailed visual inspection (DVI) or an ultrasonic
inspection of the LH and RH MLG rib 5 aft bearing forward lug for
cracks, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22,
2007. If a MLG rib 5 has been replaced on one side only, then the LH
and RH must be considered separately. Doing this inspection ends the
requirements of paragraph (g) of this AD for that MLG rib 5 only.
    (1) If no crack is detected during any inspection required by
paragraph (h) of this AD: Repeat the applicable inspection at the
time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Repeat the DVI thereafter at intervals not to exceed 100
flight cycles.
    (ii) Repeat the ultrasonic inspection thereafter at intervals
not to exceed 825 flight cycles.
    (2) Replacement of the MLG rib 5 bushes with new bushes with
high interference fit in the aft bearing forward lugs of MLG rib 5,
in accordance with the Accomplishment Instructions of a service
bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or
(h)(2)(iii) of this AD, ends the repetitive inspections required by
paragraph (h)(1) of this AD for that MLG rib 5 only. As of the
effective date of this AD, use only Airbus Mandatory Service
Bulletin A310-57-2090, Revision 03, dated January 23, 2012, for the
actions specified in this paragraph.
    (i) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007.
    (ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision
02, dated June 18, 2010.
    (iii) Airbus Mandatory Service Bulletin A310-57-2090, Revision
03, dated January 23, 2012.
    (3) If any crack is detected during the DVI required by
paragraph (h) of this AD: Before further flight, contact Airbus for
replacement instructions and replace the MLG rib 5 bushes before
further flight. As of the effective date of this AD: Before further
flight, replace using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA); or Airbus's EASA
Design Organization Approval (DOA). Repeat the applicable inspection
in paragraph (h) of this AD at the time specified in paragraph
(h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of
the MLG rib 5 bushes with new bushes with high interference fit in
the aft bearing forward lugs of MLG rib 5, in accordance with the
Accomplishment

Instructions of a service bulletin specified in paragraph (h)(2)(i),
(h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive
inspections required by paragraph (h)(1) of this AD for that MLG rib
5 only.
    (4) If any crack is detected during the ultrasonic inspection
required by paragraph (h) of this AD, before further flight,
accomplish the actions specified in paragraph (h)(4)(i) or
(h)(4)(ii) of this AD, as applicable.
    (i) If any crack is not visible on MLG rib 5: Before further
flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572-
49121, Issue C, dated May 2007. After embodiment of the repair
instruction, no further actions are necessary as required by
paragraphs (g) and (h) of this AD and specified in Airbus Service
Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007,
for that MLG rib 5 only.
    (ii) If any crack is visible on MLG rib 5: Before further
flight, contact Airbus for rib replacement instructions, and replace
before further flight. As of the effective date of this AD: Before
further flight, replace using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA; or Airbus's EASA DOA. Repeat the applicable inspection
in paragraph (h) of this AD at the time specified in paragraph
(h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of
the MLG rib 5 bushes with new bushes with high interference fit in
the aft bearing forward lugs of MLG rib 5, in accordance with the
Accomplishment Instructions of a service bulletin specified in
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the
repetitive inspections required by paragraph (h) of this AD for that
MLG rib 5 only.
    Note 1 to paragraph (h) of this AD: The ultrasonic inspection
will detect any crack at an early stage and will limit the risk of
extensive repairs. This earlier crack detection is not possible with
the DVI.

(i) Retained Installation

    This paragraph restates the requirements of paragraph (g) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraph (j) of this AD.
Within 30 months after May 29, 2012 (the effective date of AD 2012-
08-03), install new bushes with increased interference fit in the
gear rib 5 aft bearing forward lug on the LH and RH wings, in
accordance with the Accomplishment Instructions of the applicable
service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of
this AD; except as specified in paragraph (k) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03,
dated January 18, 2012 (for Model A300 B4-2C, B4-103, and B4-203
airplanes).
    (2) Airbus Mandatory Service Bulletin A300-57-6106, Revision 03,
dated January 26, 2012 (for Model A300-600 series airplanes).
    (3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03,
dated January 23, 2012 (for Model A310 series airplanes).

(j) Affected Airplanes for the Actions Required by Paragraph (i) of
This AD

    For airplanes identified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD: Do the actions required by paragraph (i) of this
AD.
    (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all
serial numbers; except airplanes on which the MLG rib 5 forward lugs
of the LH and RH wings have been repaired by installation of
oversized interference fit bushes specified in Airbus Repair
Instruction R57240221, or those on which the LH and RH wings have
had Airbus Service Bulletin A300-57-0249 embodied in service.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus
Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-
605R Variant F airplanes; all serial numbers; except airplanes on
which the MLG rib 5 forward lugs of the LH and RH wings have been
repaired by installation of oversized interference fit bushes
specified in Airbus Repair Instruction R57240221, or those on which
the LH and RH wings have had Airbus Service Bulletin A300-57-6106
embodied in service.
    (3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; all serial numbers; except airplanes on which
the MLG rib 5 forward lugs of the LH and RH wings have been repaired
by installation of oversized interference fit bushes specified in
Airbus Repair Instruction R57249121, or those on which the LH and RH
wings have had Airbus Service Bulletin A310-57-2090 embodied in
service.

(k) Retained Exception for Airplanes Identified in Paragraphs (j)(1),
(j)(2), and (j)(3) of This AD

    This paragraph restates the requirements of paragraph (h) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraphs (j)(1), (j)(2),
and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG
repaired by installing oversized interference fit bushes, as
specified in Airbus Repair Instruction R57240221 or Airbus Repair
Instruction R572-49121, as applicable to the airplane model, then
installing new bushes with increased interference fit in the aft
bearing forward lug of the gear rib, as specified in paragraph (i)
of this AD, is required for the opposite wing only.

(l) Retained Terminating Action for Certain Inspections

    This paragraph restates the requirements of paragraph (i) of AD
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and
applies to the airplanes identified in paragraphs (j)(1), (j)(2),
and (j)(3) of this AD. Installation of new bushes, as specified in
paragraph (i) of this AD, is terminating action for the repetitive
inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR
5919, February 8, 2007); and by paragraphs (g) and (h) of this AD.

(m) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (g) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD.
Except as provided by paragraph (o) of this AD: Before the
accumulation of 12,000 total flight cycles since new, or within
12,000 flight cycles since the most recent MLG rib 5 replacement, if
applicable, or within 10 days after September 11, 2012 (the
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012)), whichever occurs latest, do a detailed inspection
or an ultrasonic inspection for cracking of the LH and RH MLG rib 5
aft bearing forward lugs, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-57-0251,
including Appendix 01, dated August 8, 2007 (for Model A300 B4-103,
B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin
A300-57-6107, including Appendix 01, dated August 8, 2007 (for Model
A300-600 series airplanes). Repeat the applicable inspections
thereafter at the applicable interval specified in paragraph (m)(1)
or (m)(2) of this AD, until the modification specified in paragraph
(q) of this AD is accomplished.
    (1) Repeat the detailed inspections at intervals not to exceed
100 flight cycles.
    (2) Repeat the ultrasonic inspections at intervals not to exceed
675 flight cycles.

(n) Affected Airplanes for the Actions Required by Paragraph (m) of
This AD

    For Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; all
serial numbers; except for airplanes identified in paragraphs
(n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by
paragraph (m) of this AD, except as provided by paragraph (o) of
this AD.
    (1) Airplanes on which LH and RH wing MLG rib 5 forward lugs
have oversized interference fit bushings installed per Airbus Repair
Instruction R57240221.
    (2) Model A300 B4-103, B4-203, and B4-2C airplanes on which
Airbus Service Bulletin A300-57-0249 has been done in service on the
LH and RH wings.
    (3) Model A300-600 series airplanes on which Airbus Service
Bulletin A300-57-6106 has been done in service on the LH and RH
wings.

(o) Retained Exception for Certain Airplanes Identified in Paragraph
(n) of This AD

    This paragraph restates the requirements of paragraph (h) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD on
which an inspection required by AD 2007-03-18, Amendment 39-14929
(72 FR 5919, February 8, 2007), has been done as of September 11,
2012 (the effective date of AD 2012-15-14): Within 100 flight cycles
after doing the most recent inspection required by AD 2007-03-18, or
within 10 days after September 11, 2012, whichever occurs later, do
a detailed or ultrasonic inspection as specified in paragraph (m) of
this AD. Repeat the applicable inspection thereafter at the times
specified in paragraph (m) of this AD.

(p) Retained Repair

    This paragraph restates the requirements of paragraph (i) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), with
specific delegation approval language. If any cracking is detected
during any detailed or ultrasonic inspection of the LH and RH MLG
rib 5 aft bearing forward lugs required by paragraph (m) of this AD,
before further flight, repair using a method approved by Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA; or Airbus's EASA DOA.

(q) Retained Optional Terminating Modification

    This paragraph restates the optional terminating modification of
paragraph (j) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012), and applies to the airplanes identified in
paragraph (n) of this AD. Performing the applicable actions
specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(4) of this
AD, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18,
2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus
Mandatory Service Bulletin A300-57-6106, Revision 03, dated January
26, 2012 (for Model A300-600 series airplanes); terminates the
repetitive inspections required by paragraph (m) of this AD.
    (1) Perform a general visual inspection and dye penetrant flaw
detection inspection for corrosion and damage of the bore and
spotfaces of the lug.
    (2) Determine that the diameter of the bore of the lug
(dimension Y) is within the tolerance specified in the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service
Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for
Model A300-600 series airplanes).
    (3) If damage or corrosion is detected during any inspection
specified in paragraph (q)(1) of this AD, or if dimension Y is
outside the tolerance specified in the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C
airplanes); or Airbus Mandatory Service Bulletin A300-57-6106,
Revision 03, dated January 26, 2012 (for Model A300-600 series
airplanes); repair using a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
    (4) Install bushings with an increased interference fit in the
aft bearing forward lugs, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A300-57-0249,
Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and
B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106,
Revision 03, dated January 26, 2012 (for Model A300-600 series
airplanes).

(r) Retained Terminating Action for AD 2007-03-18, Amendment 39-14929
(72 FR 5919, February 8, 2007)

    This paragraph restates the terminating action statement of
paragraph (k) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012), and applies to the airplanes identified in
paragraph (n) of this AD. Doing the actions required by paragraph
(q) of this AD terminates the inspections required by AD 2007-03-18,
Amendment 39-14929 (72 FR 5919, February 8, 2007), for that
airplane.

(s) Retained Reporting

    This paragraph restates the requirements of paragraph (l) of AD
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and
applies to the airplanes identified in paragraph (n) of this AD.
Submit a report (including both positive and negative findings),
using the applicable report sheet attached to Airbus Mandatory
Service Bulletin A300-57-0251, including Appendix 01, dated August
8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or
Airbus Mandatory Service Bulletin A300-57-6107, including Appendix
01, dated August 8, 2007 (for Model A300-600 series airplanes); of
the first inspection required by paragraph (m) of this AD. Submit
the report to Airbus, Customer Services Directorate, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical
Data and Documentation Services; fax: (+33) 5 61 93 28 06; email:
<EMAIL_ADDRESS>at the applicable time specified in
paragraph (s)(1) or (s)(2) of this AD.
    (1) If the inspection was done on or after September 11, 2012
(the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR
46937, August 7, 2012)): Submit the report within 30 days after the
inspection.
    (2) If the inspection was done before September 11, 2012 (the
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937,
August 7, 2012)): Submit the report within 30 days after September
11, 2012.

(t) New Repetitive Inspections

    For airplanes identified in paragraph (u) of this AD: At the
applicable time specified in paragraph (v)(1) or (v)(2) of this AD,
do a detailed inspection for cracking, or an ultrasonic inspection
for any crack indications of the LH and RH MLG rib 5 aft bearing
forward lugs, in accordance with the Accomplishment Instructions of
the applicable service bulletin specified in paragraph (t)(1),
(t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at
intervals not to exceed the applicable time specified in paragraph
(v)(3) or (v)(4) of this AD.
    (1) Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C,
B2K-3C, and B2-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R
airplanes).
    (3) Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes).

(u) Affected Airplanes for the Actions Required by Paragraph (t) of
This AD

    For airplanes on which any modification or repair described in
the service bulletins identified in paragraph (u)(1), (u)(2), or
(u)(3) of this AD, as applicable, has been accomplished in service;
and for airplanes with MLG rib 5 already repaired as specified in
Airbus Repair Instruction R57240221 or R572-49121, including any
airplane with the MLG rib 5 forward lugs repaired on one wing; by
installation of oversized interference fit bushes, as specified in
Airbus Repair Instruction R57240221 or R572-49121, as applicable: Do
the actions required by paragraph (t) of this AD.
    (1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007;
Revision 01, dated December 19, 2007; or Airbus Mandatory Service
Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model
A300 B4-2C, B4-103, and B4-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6106, dated May 22, 2007;
Revision 01, dated January 28, 2008; or Revision 02, dated June 18,
2010 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes).
    (3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007;
Revision 01, dated December 19, 2007; or Revision 02, dated June 18,
2010 (for Model A310 series airplanes).

(v) Compliance Times for Paragraph (t) of This AD

    This paragraph specifies the compliance times for the actions
specified in paragraph (t) of this AD.
    (1) For airplanes identified in paragraph (c)(1) of this AD: Do
the initial inspection required by paragraph (t) of this AD within
2,500 flight cycles after any modification or repair specified in
paragraph (u) of this AD was done, or within 550 flight cycles after
the effective date of this AD, whichever occurs later.
    (2) For airplanes identified in paragraph (c)(2) of this AD: Do
the initial inspection required by paragraph (t) of this AD within
2,500 flight cycles after any modification or repair specified in
paragraph (u) of this AD was done, or within 775 flight cycles after
the effective date of this AD, whichever occurs later.
    (3) For airplanes identified in paragraph (c)(1) of this AD: For
the repetitive inspection required by paragraph (t) of this AD,
repeat the inspection within 550 flight cycles after any detailed
inspection, and within 1,000 flight cycles after any ultrasonic
inspection, as applicable.
    (4) For airplanes identified in paragraph (c)(2) of this AD: For
the repetitive inspection required by paragraph (t) of this AD,
repeat the inspection within 775 flight cycles after any detailed
inspection, and within 1,300 flight cycles after any ultrasonic
inspection, as applicable.

(w) New Requirement of This AD: Report and Detailed Inspection

    If, during any ultrasonic inspection required by paragraph (t)
of this AD, any crack indication is detected: Before further

flight, report to Airbus using the applicable report sheet attached
to the applicable Airbus service bulletin specified in paragraph
(t)(1), (t)(2), or (t)(3) of this AD, and concurrently accomplish a
detailed inspection for cracking of the affected MLG rib 5 aft
bearing forward lug, in accordance with the Accomplishment
Instructions of the applicable Airbus service bulletin specified in
paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed
inspection thereafter at intervals not to exceed 100 flight cycles.

(x) New Requirement of This AD: Cracking Repair

    If any cracking is detected during any detailed inspection
required by paragraph (t) or (w) of this AD: Before further flight,
repair the cracking using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the EASA; or Airbus's EASA DOA.

(y) New Requirement of This AD: Reporting

    Submit a report (including both positive and negative findings),
using the reporting sheet attached to the applicable Airbus service
bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this
AD, of the first inspection required by paragraph (t) of this AD.
Submit the report to Airbus, Customer Services Directorate, 1 Rond
Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1
Technical Data and Documentation Services; fax: (+33) 5 61 93 28 06;
email<EMAIL_ADDRESS>Submit the report within 30 days
after the inspection or within 30 days after the effective date of
this AD, whichever occurs later.
    (1) Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C,
B2K-3C, and B2-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R
airplanes).
    (3) Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes).

(z) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by
paragraph (i) of this AD, if those actions were performed before May
29, 2012 (the effective date of AD 2012-08-03, Amendment 39-17019
(77 FR 24367, April 24, 2012)), using an applicable service bulletin
specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this
AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203 airplanes: The
service bulletins are specified in paragraphs (z)(1)(i)(A),
(z)(1)(i)(B), and (z)(1)(i)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-0249, dated May 22, 2007,
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-0249, Revision 01, dated
December 19, 2007, which is not incorporated by reference in this
AD.
    (C) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010, incorporated by reference in AD 2012-15-14,
Amendment 39-17143 (77 FR 46937, August 7, 2012).
    (ii) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, and F4-622R airplanes; and Model A300 C4-605R Variant
F airplanes: The service bulletins are specified in paragraphs
(z)(1)(ii)(A), (z)(1)(ii)(B), and (z)(1)(ii)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-6106, dated May 22, 2007,
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-6106, Revision 01, dated
January 28, 2008, which is not incorporated by reference in this AD.
    (C) Airbus Service Bulletin A300-57-6106, Revision 02, dated
June 18, 2010, which is not incorporated by reference in this AD.
    (iii) For Model A310 series airplanes: The service bulletins are
specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and
(z)(1)(iii)(C) of this AD.
    (A) Airbus Service Bulletin A310-57-2090, dated May 22, 2007,
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007, incorporated by reference in AD 2008-17-02,
Amendment 39-15640 (73 FR 47032, August 13, 2008).
    (C) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010, which is incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by
paragraph (q) of this AD, if those actions were performed before
September 11, 2012 (the effective date of AD 2012-15-14, Amendment
39-17143 (77 FR 46937, August 7, 2012)), using an applicable service
bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii),
(z)(2)(iv), and (z)(2)(v) of this AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service
Bulletin A300-57-0249, dated May 22, 2007, which is not incorporated
by reference in this AD.
    (ii) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service
Bulletin A300-57-0249, Revision 01, dated December 19, 2007, which
is not incorporated by reference in this AD.
    (iii) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622,
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, dated May 22, 2007, which is not
incorporated by reference in this AD.
    (iv) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, Revision 01, dated January 28, 2008,
which is not incorporated by reference in this AD.
    (v) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus
Service Bulletin A300-57-6106, Revision 02, dated June 18, 2010,
which is not incorporated by reference in this AD.
    (aa) Other FAA AD Provisions
    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>    (i) 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.
    (ii) AMOCs approved previously for AD 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the
corresponding provisions of paragraphs (g) and (h) of this AD.
    (iii) AMOCs approved previously for AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the
corresponding provisions of paragraphs (i), (j), (k), and (l) of
this AD.
    (iv) AMOCs approved previously for AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the
corresponding provisions of paragraphs (m) through (s) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
    (3) Reporting Requirements: 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.

(bb) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0176, dated September 7,
2012, corrected September 20, 2012, for related information. You may

examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0142-0002.
    (2) Service information identified in this AD that is not
incorporated by reference in this AD is available at the addresses
specified in paragraphs (cc)(9) and (cc)(10) of this AD.

(cc) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on
March 17, 2015.
    (i) Airbus Service Bulletin A300-57-0255, including Inspection
Reporting Form, dated January 13, 2012.
    (ii) Airbus Service Bulletin A300-57-6112, including Inspection
Reporting Form, dated January 13, 2012.
    (iii) Airbus Service Bulletin A310-57-2090, Revision 02, dated
June 18, 2010.
    (iv) Airbus Service Bulletin A310-57-2101, including Inspection
Reporting Form, dated January 13, 2012.
    (4) The following service information was approved for IBR on
September 11, 2012 (77 FR 46937, August 7, 2012).
    (i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02,
dated June 18, 2010.
    (ii) Airbus Mandatory Service Bulletin A300-57-0251, including
Appendix 01, dated August 8, 2007.
    (iii) Airbus Mandatory Service Bulletin A300-57-6106, Revision
03, dated January 26, 2012.
    (iv) Airbus Mandatory Service Bulletin A300-57-6107, including
Appendix 01, August 8, 2007.
    (5) The following service information was approved for IBR on
May 29, 2012 (77 FR 24367, April 24, 2012).
    (i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03,
dated January 18, 2012.
    (ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision
03, dated January 23, 2012.
    (6) The following service information was approved for IBR on
September 17, 2008 (73 FR 47032, August 13, 2008).
    (i) Airbus Service Bulletin A310-57-2090, Revision 01, dated
December 19, 2007.
    (ii) Airbus Service Bulletin A310-57-2091, excluding Appendix
01, dated May 22, 2007.
    (iii) Airbus A310 Repair Instruction R572-49121, Issue C, dated
May 2007.
    (7) The following service information was approved for IBR on
February 6, 2007 (72 FR 2612, January 22, 2007).
    (i) Airbus Service Bulletin A310-57A2088, excluding Appendix 01,
dated November 6, 2006.
    (ii) Reserved.
    (8) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email<EMAIL_ADDRESS>
Internet http://www.airbus.com.
    (9) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (10) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-01710 Filed 2-9-15; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 12 (Friday, January 17, 2014)]
[Notices]
[Pages 3261-3262]
[FR Doc No: 2014-01033]

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SECURITIES AND EXCHANGE COMMISSION

[File No. 500-1]

Power Air Corporation, Wescorp Energy, Inc., and World Ventures,
Inc.; Order of Suspension of Trading

January 15, 2014.
    It appears to the Securities and Exchange Commission that there is
a

lack of current and accurate information concerning the securities of
Power Air Corporation because it has not filed any periodic reports
since the period ended June 30, 2010.
    It appears to the Securities and Exchange Commission that there is
a lack of current and accurate information concerning the securities of
Wescorp Energy, Inc. because it has not filed any periodic reports
since the period ended September 30, 2011.
    It appears to the Securities and Exchange Commission that there is
a lack of current and accurate information concerning the securities of
World Ventures, Inc. because it has not filed any periodic reports
since the period ended October 31, 2009.
    The Commission is of the opinion that the public interest and the
protection of investors require a suspension of trading in the
securities of the above-listed companies. Therefore, it is ordered,
pursuant to Section 12(k) of the Securities Exchange Act of 1934, that
trading in the securities of the above-listed companies is suspended
for the period from 9:30 a.m. EST on January 15, 2014, through 11:59
p.m. EST on January 29, 2014.

    By the Commission.

Elizabeth M. Murphy,
Secretary.
[FR Doc. 2014-01033 Filed 1-15-14; 4:15 pm]
BILLING CODE 8011-01-P


[Federal Register Volume 79, Number 90 (Friday, May 9, 2014)]
[Proposed Rules]
[Pages 26678-26679]
[FR Doc No: 2014-10809]

=======================================================================
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ENVIRONMENTAL PROTECTION AGENCY

40 CFR Part 770

[EPA-HQ-OPPT-2012-0018; FRL-9910-75]
RIN 2070-AJ92

Formaldehyde Emission Standards for Composite Wood Products

AGENCY: Environmental Protection Agency (EPA).

ACTION: Proposed rule; extension of comment period.

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SUMMARY: On June 10, 2013, EPA published a notice of proposed
rulemaking in the Federal Register entitled ``Formaldehyde Emissions
Standards for Composite Wood Products.'' On April 8, 2014, EPA
published a notice in the Federal Register announcing a public meeting
and reopening the comment period for

30 days for comments related to the treatment of laminated products
under the proposed rule. Based on requests from the public, EPA
extended the public comment period. On May 6, 2014, EPA posted a
memorandum in the docket for this proposed rule. That memorandum
ensured that the docket would remain open until the announcement of the
extension of the public comment period, which was set to end on May 8,
2014, could be published in the Federal Register. On May 6, 2014, an
Agency-compiled list of stakeholders was notified of the extension of
the comment period via email. This document announces the extension of
the comment period until May 26, 2014.

DATES: Comments, identified by docket identification (ID) number EPA-
HQ-OPPT-2012-0018, must be received on or before May 26, 2014.

ADDRESSES: Follow the detailed instructions as provided under ADDRESSES
in the Federal Register document of June 10, 2013 (78 FR 34820) (FRL-
9342-3).

FOR FURTHER INFORMATION CONTACT: Sara Kemme, National Program Chemicals
Division (7404T), Office of Pollution Prevention and Toxics,
Environmental Protection Agency, 1200 Pennsylvania Ave. NW.,
Washington, DC 20460-0001; telephone number:<PHONE_NUMBER>; email
address<EMAIL_ADDRESS>    For general information contact: The TSCA-Hotline, ABVI-Goodwill,
422 South Clinton Ave., Rochester, NY 14620; telephone number: (202)
554-1404; email address<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: This document formally announces the
extension of the public comment period established in the Federal
Register of April 8, 2014 (79 FR 19306) (FRL-9909-05). In that
document, EPA announced a public meeting on April 28, 2014, and
reopened the comment period for the June 10, 2013 Federal Register
document for 30 days to allow additional comments to be submitted by
the public and interested stakeholders specifically on the issue of
laminated products. On May 6, 2014, EPA posted a memorandum in the
docket for this proposed rule. That memorandum ensured that the docket
would remain open until the announcement of the extension of the public
comment period, which was set to end on May 8, 2014, could be published
in the Federal Register. On May 6, 2014, an Agency-compiled list of
stakeholders was notified of the extension of the comment period via
email. On May 12, 2014, the Agency placed a transcript of the public
meeting in the docket for this proposed rule. This document announces
the extension of the comment period until May 26, 2014.
    To submit comments, or access the docket, please follow the
detailed instructions as provided under ADDRESSES in the June 10, 2013
Federal Register document. If you have questions, consult the technical
person listed under FOR FURTHER INFORMATION CONTACT.

List of Subjects in 40 CFR Part 770

    Environmental protection, Formaldehyde, Reporting and recordkeeping
requirements, Toxic substances, Wood.

    Dated: May 6, 2014.
Louise P. Wise,
Acting Assistant Administrator, Office of Chemical Safety and Pollution
Prevention.
[FR Doc. 2014-10809 Filed 5-7-14; 4:15 pm]
BILLING CODE 6560-50-P


[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Notices]
[Pages 26277-26279]
[FR Doc No: 2016-10155]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-77716; File No. SR-ISEMercury-2016-09]

Self-Regulatory Organizations; ISE Mercury, LLC; Notice of Filing
of Proposed Rule Change Relating to Preferenced Volume

April 26, 2016.
    Pursuant to Section 19(b)(1) of the Securities Exchange Act of 1934
(the ``Act''),\1\ and Rule 19b-4 thereunder,\2\ notice is hereby given
that on April 13, 2016, ISE Mercury, LLC (the ``Exchange'' or ``ISE
Mercury'') filed with the Securities and Exchange Commission
(``Commission'') the proposed rule change as described in Items I and
II below, which Items have been prepared by the self-regulatory
organization. The Commission is publishing this notice to solicit
comments on the proposed rule change from interested persons.
---------------------------------------------------------------------------

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

I. Self-Regulatory Organization's Statement of the Terms of the
Substance of the Proposed Rule Change

    The purpose of this proposed rule change is to amend the Exchange's
Schedule of Fees to explain that while 100% of eligible traded volume
preferenced to a Market Maker counts towards that member's volume
tiers, Market Makers not preferenced on an order will receive credit
for the volume those non-preferenced members execute. The text of the
proposed rule change is available on the Exchange's Web site (http://www.ise.com), at the principal office of the Exchange, and at the
Commission's Public Reference Room.

II. Self-Regulatory Organization's Statement of the Purpose of, and
Statutory Basis for, the Proposed Rule Change

    In its filing with the Commission, the self-regulatory organization
included statements concerning the purpose of, and basis for, the
proposed rule change and discussed any comments it received on the
proposed rule change. The text of these statements may be examined at
the places specified in Item IV below. The self-regulatory organization
has prepared summaries, set forth in sections A, B and C below, of the
most significant aspects of such statements.

A. Self-Regulatory Organization's Statement of the Purpose of, and
Statutory Basis for, the Proposed Rule Change

1. Purpose
    On March 10, 2016, ISE Mercury introduced fee and rebate tiers for
Market Maker \3\ and Priority Customer \4\ orders based on the average
daily volume (``ADV'') that a member executes in Priority Customer
orders.\5\ The Exchange assesses fees and rebates for Market Maker and
Priority Customer orders based on five tiers of Total Affiliated
Priority Customer ADV, as described in Table 4 of the Fee Schedule: \6\
0--19,999 contracts (``Tier 1''), 20,000--39,999 contracts (``Tier
2''), 40,000--59,999 contracts (``Tier 3''), 60,000--79,999 contracts
(``Tier 4''), and 80,000 or more contracts (``Tier 5'').\7\ As

is the case on ISE Mercury's affiliated exchanges--the International
Securities Exchange, LLC (``ISE'') and ISE Gemini, LLC (``ISE
Gemini'')--the Exchange's ADV calculation includes volume executed by
affiliated members. In particular, the Exchange aggregates all eligible
volume from affiliated members in determining applicable tiers,
provided that there is at least 75% common ownership between the
members as reflected on the member's Form BD, Schedule A. While this
method of aggregating volume is beneficial to large firms with multiple
affiliated members, the Exchange believed that it was also important to
give smaller firms the ability to compete for more favorable fees and
rebates.
---------------------------------------------------------------------------

    \3\ The term Market Makers refers to ``Competitive Market
Makers'' and ``Primary Market Makers'' collectively.
    \4\ A ``Priority Customer'' is a person or entity that is not a
broker/dealer in securities, and does not place more than 390 orders
in listed options per day on average during a calendar month for its
own beneficial account(s), as defined in ISE Mercury Rule
100(a)(37A).
    \5\ See Securities Exchange Act Release No. 77409 (March 21,
2016), 81 FR 16240 (March 25, 2016) (SR-ISE Mercury-2016-05).
    \6\ The Total Affiliated Priority Customer ADV category includes
all Priority Customer volume executed on the Exchange in all symbols
and order types, including volume executed in the PIM, Facilitation,
and QCC mechanisms.
    \7\ The highest tier threshold attained applies retroactively in
a given month to all eligible traded contracts and applies to all
eligible market participants. Any day that the market is not open
for the entire trading day or the Exchange instructs members in
writing to route their orders to other markets may be excluded from
the ADV calculation; provided that the Exchange will only remove the
day for members that would have a lower ADV with the day included.
---------------------------------------------------------------------------

    On March 10, 2016, the Exchange adopted ADV tiers that are based on
preferenced volume \8\--i.e., volume directed to a specific Market
Maker as provided in Supplementary Material .03 to Rule 713.\9\ In
particular, the Exchange gives Market Makers volume credit for 100% of
eligible traded volume preferenced to that member,\10\ regardless of
the actual allocation that the Market Maker receives. For example,
assume Market Maker ABC is quoting at the national best bid or offer
(``NBBO'') and receives a Preferenced Order for 10 contracts from an
unaffiliated firm for the account of a Priority Customer. If there are
other Market Makers quoting at the NBBO, Market Maker ABC may receive
an allocation of 4 contracts--i.e., 40% of the order. Rather than
counting only the 4 contracts executed towards the Market Maker's
volume total, the Exchange gives that Market Maker credit for the full
10 contracts preferenced to it. This is the same credit the member
would receive if the 10 contracts were sent to the exchange by an
affiliated member. The purpose of the current rule filing is to clarify
that even though Market Maker ABC receives full credit for all 10
contracts when executing 4 contracts, the non-preferenced Market Makers
that execute the remaining 6 contracts will still receive credit for
those 6 contracts as they normally would.
---------------------------------------------------------------------------

    \8\ See Securities Exchange Act Release No. 77412 (March 21,
2016), 81 FR 16238 (March 25, 2016) (SR-ISE Mercury-2016-06).
    \9\ An Electronic Access Member (``EAM'') may designate a
``Preferred Market Maker'' on orders it enters into the System
(``Preferenced Orders''). Supplementary Material .03 to Rule 713
describes the Exchange's rules concerning Preferenced Orders.
    \10\ ``Eligible volume'' refers to volume that would otherwise
count towards to applicable volume tier. In the case of ADV
thresholds based on Total Affiliated Priority Customer ADV, as
currently implemented on ISE Mercury, all Priority Customer volume
would be ``eligible.'' See note 6 supra.
---------------------------------------------------------------------------

2. Statutory Basis
    The Exchange believes that the proposed rule change is consistent
with the requirements of the Act, and the rules and regulations
thereunder that are applicable to a national securities exchange, and,
in particular, with the requirements of Section 6(b) of the Act.\11\ In
particular, the proposal is consistent with Section 6(b)(5) of the
Act,\12\ because it is designed to promote just and equitable
principles of trade, remove impediments to and perfect the mechanisms
of a free and open market and a national market system and, in general,
to protect investors and the public interest. The Exchange believes
that the proposed clarification is reasonable and equitable because it
will eliminate member confusion regarding how volume is counted among
Market Makers when contracts are preferenced to a Market Maker and
executed by preferenced and non-preferenced Market Makers.
---------------------------------------------------------------------------

    \11\ 15 U.S.C. 78f(b).
    \12\ 15 U.S.C. 78f(b)(5).
---------------------------------------------------------------------------

B. Self-Regulatory Organization's Statement on Burden on Competition

    In accordance with Section 6(b)(8) of the Act,\13\ the Exchange
does not believe that the proposed rule change will impose any burden
on intermarket or intramarket competition that is not necessary or
appropriate in furtherance of the purposes of the Act. To the contrary,
the Exchange believes that the proposed rule change merely clarifies an
existing rule already in effect.
---------------------------------------------------------------------------

    \13\ 15 U.S.C. 78f(b)(8).
---------------------------------------------------------------------------

C. Self-Regulatory Organization's Statement on Comments on the Proposed
Rule Change Received From Members, Participants, or Others

    The Exchange has not solicited, and does not intend to solicit,
comments on this proposed rule change. The Exchange has not received
any written comments from members or other interested parties.

III. Date of Effectiveness of the Proposed Rule Change and Timing for
Commission Action

    Because the proposed rule change does not (i) significantly affect
the protection of investors or the public interest; (ii) impose any
significant burden on competition; and (iii) become operative for 30
days from the date on which it was filed, or such shorter time as the
Commission may designate if consistent with the protection of investors
and the public interest, the proposed rule change has become effective
pursuant to Section 19(b)(3)(A) of the Act \14\ and Rule 19b-4(f)(6)
thereunder.\15\
---------------------------------------------------------------------------

    \14\ 15 U.S.C. 78s(b)(3)(A).
    \15\ 17 CFR 240.19b-4(f)(6). As required under Rule 19b-
4(f)(6)(iii), the Exchange provided the Commission with written
notice of its intent to file the proposed rule change, along with a
brief description and the text of the proposed rule change, at least
five business days prior to the date of filing of the proposed rule
change, or such shorter time as designated by the Commission.
---------------------------------------------------------------------------

    At any time within 60 days of the filing of the proposed rule
change, the Commission summarily may temporarily suspend such rule
change if it appears to the Commission that such action is necessary or
appropriate in the public interest, for the protection of investors, or
otherwise in furtherance of the purposes of the Act. If the Commission
takes such action, the Commission shall institute proceedings to
determine whether the proposed rule should be approved or disapproved.

IV. Solicitation of Comments

    Interested persons are invited to submit written data, views, and
arguments concerning the foregoing, including whether the proposed rule
change is consistent with the Act. Comments may be submitted by any of
the following methods:

Electronic Comments:

     Use the Commission's Internet comment form (http://www.sec.gov/rules/sro.shtml); or
     Send an email to<EMAIL_ADDRESS>Please include
File Number SR-ISEMercury-2016-09 on the subject line.

Paper Comments

     Send paper comments in triplicate to Brent J. Fields,
Secretary, Securities and Exchange Commission, 100 F Street NE.,
Washington, DC 20549-1090.

All submissions should refer to File Number SR-ISEMercury-2016-09. This
file number should be included on the subject line if email is used. To
help the Commission process and review your comments more efficiently,
please use only one method. The Commission will post all comments on
the Commission's Internet Web site (http://www.sec.gov/rules/sro.shtml). Copies of the submission, all subsequent amendments, all
written statements with respect to the proposed rule change that are
filed with the Commission, and all written communications relating to
the proposed rule change between the Commission and any person, other
than

those that may be withheld from the public in accordance with the
provisions of 5 U.S.C. 552, will be available for Web site viewing and
printing in the Commission's Public Reference Room, 100 F Street NE.,
Washington, DC 20549 on official business days between the hours of
10:00 a.m. and 3:00 p.m. Copies of such filing also will be available
for inspection and copying at the principal office of the Exchange. All
comments received will be posted without change; the Commission does
not edit personal identifying information from submissions. You should
submit only information that you wish to make available publicly. All
submissions should refer to File Number SR-ISEMercury-2016-09, and
should be submitted on or before May 23, 2016.\16\
---------------------------------------------------------------------------

    \16\ 17 CFR 200.30-3(a)(12).

    For the Commission, by the Division of Trading and Markets,
pursuant to delegated authority.
Robert W. Errett,
Deputy Secretary.
[FR Doc. 2016-10155 Filed 4-29-16; 8:45 am]
 BILLING CODE 8011-01-P


[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Notices]
[Page 14023]
[FR Doc No: 2014-05307]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 2351-000]

Public Service Company of Colorado; Notice of Authorization for
Continued Project Operation

    On February 27, 2012, the Public Service Company of Colorado,
licensee for the Cabin Creek Pumped Storage Project, filed an
Application for a New License pursuant to the Federal Power Act (FPA)
and the Commission's regulations thereunder. The Cabin Creek Pumped
Storage Project is located on the South Clear Creek and its tributary
Cabin Creek in Clear Creek County, Colorado.
    The license for Project No. 2351 was issued for a period ending
February 28, 2014. Section 15(a)(1) of the FPA, 16 U.S.C. 808(a)(1),
requires the Commission, at the expiration of a license term, to issue
from year-to-year an annual license to the then licensee under the
terms and conditions of the prior license until a new license is
issued, or the project is otherwise disposed of as provided in section
15 or any other applicable section of the FPA. If the project's prior
license waived the applicability of section 15 of the FPA, then, based
on section 9(b) of the Administrative Procedure Act, 5 U.S.C. 558(c),
and as set forth at 18 CFR 16.21(a), if the licensee of such project
has filed an application for a subsequent license, the licensee may
continue to operate the project in accordance with the terms and
conditions of the license after the minor or minor part license
expires, until the Commission acts on its application. If the licensee
of such a project has not filed an application for a subsequent
license, then it may be required, pursuant to 18 CFR 16.21(b), to
continue project operations until the Commission issues someone else a
license for the project or otherwise orders disposition of the project.
    If the project is subject to section 15 of the FPA, notice is
hereby given that an annual license for Project No. 2351 is issued to
the licensee for a period effective March 1, 2014 through February 28,
2015 or until the issuance of a new license for the project or other
disposition under the FPA, whichever comes first.
    If issuance of a new license (or other disposition) does not take
place on or before February 28, 2015, notice is hereby given that,
pursuant to 18 CFR 16.18(c), an annual license under section 15(a)(1)
of the FPA is renewed automatically without further order or notice by
the Commission, unless the Commission orders otherwise. If the project
is not subject to section 15 of the FPA, notice is hereby given that
the licensee, Public Service Company of Colorado, is authorized to
continue operation of the Cabin Creek Pumped Storage Project, until
such time as the Commission acts on its application for a subsequent
license.

    Dated: March 5, 2014.
Kimberly D. Bose,
Secretary.
[FR Doc. 2014-05307 Filed 3-11-14; 8:45 am]
BILLING CODE 6717-01-P