[Federal Register: January 12, 2009 (Volume 74, Number 7)]
[Notices]
[Page 1204-1205]
[DOCID:fr12ja09-56]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 2009-128]

Virginia Electric and Power Company; Notice of Application for
Amendment of License and Soliciting Comments, Motions To Intervene, and
Protests

January 6, 2009.
    Take notice that the following hydroelectric application has been
filed with the Commission and is available for public inspection:
    a. Application Type: Application for Non-Project Use of Project
Lands and Waters.
    b. Project No: 2009-128.
    c. Date Filed: November 28, 2008.
    d. Applicant: Virginia Electric and Power Company.
    e. Name of Project: Roanoke Rapids and Gaston Project.
    f. Location: The project is located on the Roanoke River, in
Brunswick and Mecklenburg Counties, Virginia and Halifax, Warren, and
Northampton Counties, North Carolina.
    g. Filed Pursuant to: Federal Power Act, 16 U.S.C. 791a-825r.
    h. Applicant Contact: Mr. Jim Thornton, Technical Consultant,
Dominion Virginia Power, 5000 Dominion Blvd., 1NE, Glen Allen, VA
23060, Telephone:<PHONE_NUMBER>, and e-mail<EMAIL_ADDRESS>    i. FERC Contact: Shana High,<PHONE_NUMBER>.
    j. Deadline for filing comments, motions to intervene, and protest:
February 6, 2009. All documents (original and eight copies) should be
filed with: Secretary, Federal Energy Regulatory Commission, 888 First
Street, NE., Washington, DC 20426.
    The Commission's Rules of Practice and Procedure require all
interveners

filing documents with the Commission to serve a copy of that document
on each person whose name appears on the official service list for the
project. Further, if an intervener files comments or documents with the
Commission relating to the merits of an issue that may affect the
responsibilities of a particular resource agency, they must also serve
a copy of the document on that resource agency. A copy of any motion to
intervene must also be served upon each representative of the Applicant
specified in the particular application.
    k. Description of Proposed Amendment: Virginia Electric and Power
Company requests approval to permit East Oaks, LLC to expand an
existing public marina on Lake Gaston. East Oaks, LLC does not have
direct water access for its existing off-water storage facility and is
proposing the addition of a forklift boat loading facility. The number
of boat storage slots within the area of the marina would not increase.
    l. Locations of the Application: A copy of the application is
available for inspection and reproduction at the Commission's Public
Reference Room, located at 888 First Street, NE., Room 2A, Washington,
DC 20426, or by calling<PHONE_NUMBER>. This filing may also be viewed
on the Commission's Web site at http://www.ferc.gov using the
``eLibrary'' link. Enter the docket number excluding the last three
digits in the docket number field to access the document. You may also
register online at http://www.ferc.gov/docs-filing/esubscription.asp to
be notified via e-mail of new filings and issuances related to this or
other pending projects. For assistance, call 1-866-208-3372 or e-mail
<EMAIL_ADDRESS>for TTY, call<PHONE_NUMBER>. A copy is
also available for inspection and reproduction at the address in item
(h) above.
    m. Individuals desiring to be included on the Commission's mailing
list should so indicate by writing to the Secretary of the Commission.
    n. Comments, Protests, or Motions to Intervene: Anyone may submit
comments, a protest, or a motion to intervene in accordance with the
requirements of Rules of Practice and Procedure, 18 CFR 385.210, .211,
.214. In determining the appropriate action to take, the Commission
will consider all protests or other comments filed, but only those who
file a motion to intervene in accordance with the Commission's Rules
may become a party to the proceeding. Any comments, protests, or
motions to intervene must be received on or before the specified
comment date for the particular application.
    o. Any filings must bear in all capital letters the title
``COMMENTS'', ``PROTEST'', or ``MOTION TO INTERVENE'', as applicable,
and the Project Number of the particular application to which the
filing refers.
    p. Agency Comments: Federal, state, and local agencies are invited
to file comments on the described application. A copy of the
application may be obtained by agencies directly from the Applicant. If
an agency does not file comments within the time specified for filing
comments, it will be presumed to have no comments. One copy of an
agency's comments must also be sent to the Applicant's representatives.
    q. Comments, protests and interventions may be filed electronically
via the Internet in lieu of paper. See, 18 CFR 385.2001(a)(1)(iii) and
the instructions on the Commission's Web site at http://www.ferc.gov
under the ``e-Filing'' link.

Kimberly D. Bose,
Secretary.
 [FR Doc. E9-337 Filed 1-9-09; 8:45 am]

BILLING CODE 6717-01-P


[Federal Register Volume 83, Number 28 (Friday, February 9, 2018)]
[Rules and Regulations]
[Pages 5689-5700]
[FR Doc No: 2018-01803]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0713; Product Identifier 2016-NM-199-AD; Amendment
39-19170; AD 2018-02-17]
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) 2012-12-12 and
AD 2013-16-26, which applied to all Airbus Model A330-200, A330-200
Freighter, A330-300, A340-200, and A340-300 series airplanes. AD 2012-
12-12 required repetitive inspections of the outer skin rivets of the
cargo doors, repair if necessary, and other repetitive inspections. AD
2013-16-26 required repetitive inspections of certain cargo doors, and
repair if necessary. This new AD continues to require repetitive
inspections, and repair if necessary. This new AD revises the
applicability; adds a one-time inspection and adjustment of certain
hook gaps; reinforcement of the door frame structure; related
investigative and corrective actions if necessary; and a modification,
which allows deferring reinforcement of the cargo door structure. This
AD was prompted by a determination that a new inspection procedure is
necessary to address the unsafe condition. We are issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective March 16, 2018. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in this AD as of March 16, 2018.

ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: [email protected];
internet: http://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 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-2017-0713.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0713; 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 address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057-3356; telephone<PHONE_NUMBER>; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-12-12, Amendment 39-17092 (77 FR 37797,
June 25, 2012) (``AD 2012-12-12''); and AD 2013-16-26, Amendment 39-
17564 (78 FR 53640, August 30, 2013) (``AD 2013-16-26''). AD 2012-12-12
and AD 2013-16-26 applied to all Airbus Model A330-200 series
airplanes, Model A330-200 Freighter series airplanes, Model A330-300
series airplanes, Model A340-200 series airplanes, and Model A340-300
series airplanes. The NPRM published in the Federal Register on August
10, 2017 (82 FR 37360). The NPRM was prompted by a determination that a
new inspection procedure is necessary to address the unsafe condition.
The NPRM proposed to continue to require repetitive inspections, and
repair if necessary. The NPRM also proposed to add a one-time
inspection and adjustment of certain hook gaps; reinforcement of the
door frame structure; related investigative and corrective actions if
necessary; and a modification, which would allow deferring
reinforcement of the cargo door structure. We are issuing this AD to
detect and correct cracked or ruptured cargo door frames, which could
result in reduced structural integrity of the forward or aft cargo
door.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0188, dated September 21, 2016; corrected September 22, 2016
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''); to correct an unsafe condition for
certain Airbus Model A330-200 and -300 series airplanes; Model A330-200
Freighter series airplanes; and Model A340-200, -300, -500, and -600
series airplanes. The MCAI states:

    Several cases of cracked forward (FWD) and aft (AFT) cargo door
frames, as well as loose, lost, or sheared rivets, have been
reported by operators. Investigation showed that these findings are
due to the low margins with respect to fatigue requirements for the
AFT/FWD cargo door internal structure. Further analysis determined
that the cargo door hook adjustment is a contributing factor to this
issue. In case of a cracked or ruptured (FWD or AFT) cargo door
frame, the loads will be transferred to the remaining structural
elements. However, the secondary load path is able to sustain those
loads only for a limited number of flight cycles (FC).
    This condition, if not detected and corrected, could lead to
rupture of adjacent vertical frames and consequent reduced
structural integrity of the FWD or AFT cargo door, possibly
resulting in a cargo door failure, decompression of the aeroplane
and injury to occupants.
    To initially address this potential unsafe condition, Airbus
issued Service Bulletin (SB) A330-52-3043 and SB A340-52-4053 and,
consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France issued AD 2001-124(B) and AD 2001-126(B), requiring a
special detailed inspection of A330 and A340 AFT cargo doors. Since
those [DGAC] ADs were issued, prompted by new occurrences, Airbus
issued Alert Operators Transmission (AOT) A330-52A3085, AOT A340-
52A4092, AOT A330-52A3084, AOT A340-52A4091, AOT A330-A52L003-12,
AOT 340-A52L004-12, AOT A330-A52L001-12 and AOT A340-A52L002-12,
providing instructions to inspect the affected areas of both FWD and
AFT cargo doors.
    Consequently, EASA issued AD 2011-0007 (later revised) [which
corresponds to FAA AD 2012-12-12], and AD 2012-0274 [which
corresponds to FAA AD 2013-16-26], to require repetitive detailed
visual inspections of AFT and FWD cargo doors at specific frames and
outer skin at all frame fork ends. Since these EASA ADs were issued,
Airbus published SB A330-52-3087, SB A330-52-3095, SB A340-52-4095,
SB A340-52-4101, SB A340-52-5020 and SB A340-52-5023, which took
over the instructions of the above mentioned AOTs, and introduced
revised thresholds and intervals. In addition, the inspection
program was expanded to A340-500/-600 aeroplanes. Taking into
account experience from inspections accomplished in accordance with
the applicable Airbus SBs at original issue (listed above), Airbus
issued Revision 01 of these SBs.
    Consequently, EASA issued AD 2015-0192, which superseded EASA AD
2011-0007R1 and EASA AD 2012-0274, to require for each FWD and AFT
cargo door, a one-time inspection/adjustment of the hook gaps ``U''
and ``V'', repetitive detailed inspections (DET) of all frame fork
areas, frame head areas and outer skin areas to detect cracks or
loose/sheared/missing fasteners, and, depending on findings,
accomplishment of applicable corrective action(s). In addition, EASA
AD 2015-0192 expanded the Applicability to Airbus A340-500/-600
aeroplanes.
    Since EASA AD 2015-0192 was issued, Airbus published Revision 02
of the inspection SBs, introducing high-frequency eddy-current
inspection method for the frame forks structure. Airbus also
determined that the interval for these repetitive inspections could
be increased. In addition, Airbus released some modifications (mod)
introducing reinforcements to the cargo door structure improving the
fatigue characteristics. These modifications and associated SBs
constitute terminating action for the required repetitive
inspections. Furthermore, Airbus also published other SBs,
introducing cold working after oversizing of the fastener holes as a
means for structural reinforcement. Accomplishment of these SBs
allows postponement of the required Point of Embodiment (Structural
Modification Point) for the structural reinforcement modification
SBs which terminate the repetitive inspection requirement.
    For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2015-0192, which is superseded,
and requires for each FWD and AFT cargo door initial and repetitive
special detailed inspections (SDI) of all frame fork areas and
detailed inspections (DET) of frame head areas and outer skin areas,
and a one-time inspection/adjustment of the hook gaps ``U'' and
``V'' and, depending on findings, the accomplishment of applicable
corrective action(s). Additionally, this [EASA] AD requires
reinforcement of the cargo door frame structure, while
accomplishment of a cold working modification allows to defer the
reinforcement of the cargo door structure.
    It should be noted that additional inspections exist for the
cargo doors, as specified in Airbus A330 ALS [Airworthiness
Limitation Section] Part 2 task 523211-02-01 and task 523211-02-02,
and in Airbus A340 ALS Part 2 Task 523211-02-01.
    This [EASA] AD is re-published to correct typographical errors
when referencing Airbus SB A340-52-4118.

    Related investigative actions include detailed inspections and high
frequency non-destructive test inspections. Corrective actions include
reaming holes, bushing holes, replacing affected parts, and repairing
cracks. Additional work includes a one-time inspection of the ``U'' and
``V'' hook gaps, and, if necessary, an adjustment of the hook gaps.
    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0713.

Comments

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

Request To Allow Alternative Fastener

    American Airlines (AAL) asked that we allow use of an alternative
fastener when doing repairs of the cargo doors. AAL stated that
paragraph (l) of the proposed AD allows credit for aft cargo doors
inspected in accordance with Airbus Service Bulletin A330-52-3095,
Revision 01, dated July 28, 2014. AAL noted that this service
information could not be accomplished due to the non-availability of
fasteners having part number ``ANSA2657'' that are necessary to repair
findings in the door beam 1 and 4 areas of the aft cargo door. AAL
added that, as a result of this parts issue, Airbus provided Technical
Advisory (TA) Reference 80016786/003/2014, Issue 03, for all affected
A330 operators, which allows using an alternative HST11 series
fastener; Airbus also issued Operators Information Transmission SBIT-
15-0085, dated

October 9, 2015, to identify this substitution and AALs compliance
paperwork was written with this deviation added. AAL asked that this
deviation to Airbus Service Bulletin A330-52-3095, Revision 01, dated
July 28, 2014, be acceptable for compliance with the proposed AD.
    We agree with the commenter's request for the reasons provided.
However, AAL transposed the part number in their comment, the correct
part number is ASNA2657. We have added paragraph (s)(5) to this AD to
include this exception.

Request To Revise Terminating Action Requirements

    Delta Airlines (DAL) asked that the terminating actions specified
in paragraphs (j), (n), and (o) of the proposed AD be revised. DAL
stated that the actions in those paragraphs specify that doing the
modification constitutes terminating action for the repetitive
inspections. DAL noted that this implies that an operator must do the
initial inspection prior to or concurrently with the initial
requirements; and if the modification is done prior to the repetitive
requirements that action would not comply with the requirements. DAL
added that the terminating action should be for both the initial and
repetitive inspections.
    We agree with the commenter's request because the intent of the
terminating modification is to terminate all inspections. Although the
EASA AD also specifies that the terminating action is for repetitive
inspections, EASA confirmed that it applies to all inspections.
Therefore, we have revised paragraphs (j), (n), and (o) of this AD to
include the initial inspection as terminated actions.

Request To Include a No-Reporting Provision

    DAL asked that a paragraph that specifically addresses that there
are no reporting requirements for the inspections be included in the
proposed AD. DAL stated that there are reporting instructions within
the ``RC'' (Required for Compliance) Accomplishment Instructions in
Airbus Service Bulletin A330-52-3087, Revision 02, including Appendix
01, dated February 18, 2016; and Airbus Service Bulletin A330-52-3095,
Revision 02, including Appendices 01 and 02, dated February 19, 2016.
DAL noted that operators must request an alternative method of
compliance if they deviate from an RC task, so a no-reporting paragraph
in the proposed AD would clarify that reporting would not be required
by the proposed AD.
    We agree with the commenter's request because the terminating
action will eliminate the unsafe condition, so reporting areas of
difficulty during accomplishment of the required inspections is not
necessary. We have added paragraph (r) to this AD to include a no-
reporting requirement, and re-redesignated subsequent paragraphs
accordingly.

Request To Revise Heading

    Delta requested that we revise the heading for paragraph (m) of the
proposed AD by removing ``For Pre-modified airplanes.'' Delta stated
that paragraph (m) specifies it pertains to the modification of pre-
modified airplanes. Paragraph (n) of the proposed AD specifies that
accomplishing (m)(1) or (m)(3) serves as terminating action for pre-
modified airplanes. However, for post-modified airplanes, paragraph (o)
of the proposed AD states that paragraphs (m)(1)(i) thru (m)(1)(vi) of
the proposed AD serve as terminating action--therefore, paragraph (m)
serves as terminating for both pre- and modified airplanes. Delta
therefore requested that we revise the heading to remove ``for pre-
modified airplanes''
    We agree to clarify the heading to paragraph (m) of this AD. We
acknowledge that the actions for the modification accomplished by the
service information in paragraph (m)(l)(i) through (m)(1)(iv) of this
AD are terminating actions to the inspections required by paragraph
(l)(1) and (l)(2) of this AD when accomplished on a pre- or post-
modified airplane. However, the actions for the modification
accomplished by the service information in paragraph (m)(1)(i) through
(m)(1)(iv) of this AD are optional for post-modified airplanes,
whereas, these actions are required for pre-modified airplanes.
Furthermore, the requirements of paragraph (m)(2) and (m)(3) of this AD
are not applicable to post-modified airplanes. For these reasons, the
heading of paragraph (m) of this AD is stated as ``Modification for
Pre-Modification Airplanes.'' We have not changed this AD in this
regard.

Request To Specify Modification Locations

    DAL asked that the word ``aft'' be included in the header for
paragraph (k) of the proposed AD. DAL stated that this would clarify
that the actions in that paragraph apply only to the aft cargo door
modification. DAL added that it would also align with the headers for
paragraphs (k) and (l) of the proposed AD.
    DAL also asked that the word ``aft'' be added to the first sentence
in paragraph (n) of the proposed AD. DAL stated that this would clarify
that the actions in that paragraph apply only to pre-modified aft cargo
doors.
    In addition, DAL asked that the header for paragraph (n) of the
proposed AD be revised from ``Aft Cargo Door Terminating Action'' to
include ``pre-modified airplanes'' in the header. DAL stated that this
would clarify that the requirements in that paragraph apply only to
pre-modified aft cargo doors.
    We agree with the commenter's requests to include the word ``aft''
in the header for paragraph (k) and the first sentence of paragraph (n)
of this AD for the reasons provided. We have included the word ``aft''
in the subject language for clarification.
    We agree to change the header for paragraph (n) of this AD. That
header for that paragraph merely gives information about the content of
the paragraph. We have changed the header for paragraph (n) of this AD
accordingly.

Request To Provide Credit for Certain Actions

    AAL asked that paragraphs (h)(2) and (l)(2) of the proposed AD be
revised to provide credit for previously accomplishing the check of the
forward and aft cargo door hook gaps, in accordance with Airbus Service
Bulletin A330-52-3087, Revision 01, dated July 9, 2014; or Airbus
Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014. AAL
stated that it accomplished the check in accordance with the referenced
service information.
    We agree with the commenter's request. However, paragraphs (s)(2)
and (s)(4) of this AD already provide the requested credit. Therefore,
we have not changed this AD in this regard.

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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.
    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

    Airbus has issued the following service information.
    The following service information describes procedures for
inspecting and repairing the frame fork area at beam 4 and frame head
area at beam 1 from frame 20B to frame 25 of the forward cargo door,
and adjusting the hook gaps ``U'' and ``V.'' This service information
is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3087, Revision 02, including
Appendix 01, dated February 18, 2016.
     Service Bulletin A340-52-4095, Revision 02, including
Appendix 01, dated November 29, 2015.
     Service Bulletin A340-52-5020, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for
modifying the frame fork area at beam 4 and frame head area at beam 1
from frame 20B to frame 25 of the forward cargo door frame. This
service information is distinct since it applies to different airplane
models and configurations.
     Service Bulletin A330-52-3105, dated February 24, 2016.
     Service Bulletin A330-52-3110, dated February 15, 2016.
     Service Bulletin A330-52-3111, dated February 15, 2016.
     Service Bulletin A340-52-4108, dated February 15, 2016.
     Service Bulletin A340-52-4113, dated February 15, 2016.
     Service Bulletin A340-52-4114, dated February 15, 2016.
    The following service information describes procedures for
modifying the fastener holes in the forward cargo door frame structure
by cold working and changing the fastener type and size. This service
information is distinct since it applies to different airplane models
and configurations.
     Service Bulletin A330-52-3116, dated April 20, 2016.
     Service Bulletin A330-52-3117, dated April 20, 2016.
     Service Bulletin A330-52-3118, dated April 20, 2016.
     Service Bulletin A340-52-4119, dated April 20, 2016.
     Service Bulletin A340-52-4120, dated April 20, 2016.
     Service Bulletin A340-52-4121, dated April 20, 2016.
    The following service information describes procedures for
inspecting the frame fork area at beam 4 and frame head area at beam 1
of the aft cargo door from frame 60 to frame 64A, adjusting the hook
gaps ``U'' and ``V,'' and doing corrective actions. This service
information is distinct since it applies to different airplane models
and configurations.
     Service Bulletin A330-52-3095, Revision 02, including
Appendices 01 and 02, dated February 19, 2016.
     Service Bulletin A340-52-4101, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
     Service Bulletin A340-52-5023, Revision 02, including
Appendices 01 and 02, dated November 27, 2015.
    The following service information describes procedures for
modifying the frame fork and head of the aft cargo door frame from
frame 59A to frame 65. This service information is distinct since it
applies to different airplane models and configurations.
     Service Bulletin A330-52-3106, dated February 24, 2016.
     Service Bulletin A330-52-3112, dated February 24, 2016.
     Service Bulletin A330-52-3113, dated February 15, 2016.
     Service Bulletin A330-52-3114, dated February 15, 2016.
     Service Bulletin A340-52-4109, dated February 25, 2016.
     Service Bulletin A340-52-4115, dated February 19, 2016.
    The following service information describes procedures for
modifying the fastener holes in the aft cargo door frame structure by
cold working and changing the fastener type and size. This service
information is distinct since it applies to different airplane models.
     Service Bulletin A330-52-3115, dated April 20, 2016.
     Service Bulletin A340-52-4118, dated April 20, 2016.
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 73 airplanes of U.S. registry.
    We estimate that it takes up to 888 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost up to $126,420 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be up to $14,738,700, or up to $201,900 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.

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.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator,

the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2012-12-12, Amendment 39-17092
(77 FR 37797, June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78
FR 53640, August 30, 2013); and
0
b. Adding the following new AD:

2018-02-17 Airbus: Amendment 39-19170; Docket No. FAA-2017-0713;
Product Identifier 2016-NM-199-AD.

(a) Effective Date

    This AD is effective March 16, 2018.

(b) Affected ADs

    This AD replaces AD 2012-12-12, Amendment 39-17092 (77 FR 37797,
June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78 FR 53640,
August 30, 2013).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certified in any category, all
manufacturer serial numbers, except those on which Airbus
Modification 202702 and Modification 202790 have been embodied in
production; and the Airbus airplanes identified in paragraphs (c)(3)
through (c)(5) of this AD, certified in any category, all
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, -223F, -243, and -243F
airplanes.
    (2) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
    (3) Model A340-211, -212, and -213 airplanes.
    (4) Model A340-311, -312, and -313 airplanes.
    (5) Model A340-541 and -642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of cracked forward and aft cargo
door frames, and loose, missing, or sheared rivets. We are issuing
this AD to detect and correct cracked or ruptured cargo door frames,
which could result in reduced structural integrity of the forward or
aft cargo door.

(f) Compliance

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

(g) Affected Cargo Doors

    For the purpose of this AD, the affected cargo doors are pre-
modification 202702 (forward cargo door) and pre-modification 202790
(aft cargo door), and are listed by part number (P/N) in the
applicable service information identified in paragraph (h)(1) or
(l)(1) of this AD. For post-modification doors, which are not
affected by this AD, the P/Ns are identified as F52370900XXX
(forward cargo door) and F52372315XXX (aft cargo door), where
``XXX'' can be a combination of any three numerical digits.

(h) Forward Cargo Door Repetitive Inspections

    (1) Before exceeding 5,300 total flight cycles since first
installation of the forward cargo door on an airplane, or within the
applicable compliance time specified in table 1 to paragraph (h)(1)
of this AD, whichever occurs later, except as specified in paragraph
(q) of this AD: Do all applicable detailed and high frequency eddy
current (HFEC) inspections of all frame fork areas, frame head
areas, and outer skin areas of each affected forward cargo door, as
applicable; in accordance with the Accomplishment Instructions of
the applicable service information specified in paragraph (h)(1)(i),
(h)(1)(ii), or (h)(1)(iii) of this AD. Do all applicable related
investigative actions and corrective actions before further flight
in accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (h)(1)(i), (h)(1)(ii), or
(h)(1)(iii) of this AD, except as required by paragraph (p) of this
AD. Repeat the applicable inspections of the frame fork areas, frame
head areas, and outer skin areas of each affected forward cargo door
thereafter at intervals not to exceed 1,400 flight cycles.
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    (i) Airbus Service Bulletin A330-52-3087, Revision 02, including
Appendix 01, dated February 18, 2016 (``SB A330-52-3087, R02'').
    (ii) Airbus Service Bulletin A340-52-4095, Revision 02,
including Appendix 01, dated November 29, 2015 (``SB A340-52-4095,
R02'').
    (iii) Airbus Service Bulletin A340-52-5020, Revision 02,
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-5020, R02'').
    (2) Concurrently with the first inspection required by paragraph
(h)(1) of this AD: Do a one-time detailed inspection of the hook
gaps ``U'' and ``V'' of each affected forward cargo door for proper
adjustment, and, depending on findings, adjust the hook(s), in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (h)(2)(i), (h)(2)(ii), or
(h)(2)(iii) of this AD. Do all the required hook gap adjustments
before further flight.
    (i) SB A330-52-3087, R02.
    (ii) SB A340-52-4095, R02.
    (iii) SB A340-52-5020, R02.

(i) Forward Cargo Door Modification

    (1) Except as specified in paragraph (i)(2) of this AD, before
exceeding 18,500 total flight cycles since first installation of the
forward cargo door on an airplane, or within 12 months after the
effective date of this AD, whichever occurs later: Do reinforcement
modifications on the frame structure of each affected forward cargo
door, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (i)(1)(i)
through (i)(1)(vi) of this AD, except as required by paragraph (p)
of this AD.
    (i) Airbus Service Bulletin A330-52-3105, dated February 24,
2016 (for certain Model A330-202, -223, and -243 airplanes; and
Model A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3110, dated February 15,
2016 (for certain Model A330-202, -203, -223, and -243 airplanes;
and Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3111, dated February 15,
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (iv) Airbus Service Bulletin A340-52-4108, dated February 15,
2016 (for certain Model A340-211, -212, and -213 airplanes; and
Model A340-311, -312, and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4113, dated February 15,
2016 (for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4114, dated February 15,
2016 (for certain Model A340-313 airplanes).
    (2) Accomplishment of the reinforcement modifications required
by paragraph (i)(1) of this AD may be deferred, provided that,
before exceeding 18,500 total flight cycles since first installation
of the forward cargo door on an airplane, or within 12 months after
the effective date of this AD, whichever occurs later, but not
earlier than 14,500 total flight cycles for Model A330 airplanes, or
12,500 total flight cycles for Model A340 airplanes, cold working is
accomplished on the frame structure of each affected forward cargo
door, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (i)(2)(i)
through (i)(2)(vi) of this AD, except as required by paragraph (p)
of this AD. Modification of an airplane by accomplishment of the
cold working specified in this paragraph does not constitute
terminating action for the repetitive inspections required by
paragraph (h)(1) of this AD.
    (i) Airbus Service Bulletin A330-52-3116, dated April 20, 2016
(for certain Model A330-202, -223, and -243 airplanes; and Model
A330-301, -321, -322, -341, and -342 airplanes).
    (ii) Airbus Service Bulletin A330-52-3117, dated April 20, 2016
(for certain Model A330-202, -203, -223, and -243 airplanes; and
Model A330-303, -323, and -343 airplanes).
    (iii) Airbus Service Bulletin A330-52-3118, dated April 20, 2016
(for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (iv) Airbus Service Bulletin A340-52-4119, dated April 20, 2016
(for certain Model A340-211, -212, and -213 airplanes; and Model
A340-311, -312, and -313 airplanes).
    (v) Airbus Service Bulletin A340-52-4120, dated April 20, 2016
(for certain Model A340-312 and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4121, dated April 20, 2016
(for certain Model A340-313 airplanes).
    (3) Within 18,500 flight cycles after cold working is
accomplished on the frame structure of each affected forward cargo
door as specified in paragraph (i)(2) of this AD: Do the
reinforcement modifications on the frame structure of each affected
forward cargo door, using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.

(j) Forward Cargo Door Terminating Action

    Modification of an airplane by reinforcement of the forward
cargo door frame structure required by paragraph (i)(1) or (i)(3) of
this AD constitutes terminating action for the inspections required
by paragraph (h)(1) and (h)(2) of this AD for that airplane.

(k) Definitions of Pre-Modified and Post-Modified Airplanes of Aft
Cargo Door

    (1) For the purpose of this AD, pre-modified Model A330-200
series airplanes, Model A330-200 Freighter series airplanes, Model
A330-300 series airplanes, Model A340-200 series airplanes, and
Model A340-300 series airplanes are defined as those not having
Airbus Modification 44852, or Modification 44854 applied in
production, or being in pre-Airbus Service Bulletin A330-52-3044 or
pre-Airbus Service Bulletin A340-52-4054 configuration, as
applicable.
    (2) For the purpose of this AD, post-modification Model A330-200
series airplanes, Model A330-200 Freighter series airplanes, Model
A330-300 series airplanes, Model A340-200 series airplanes, and
Model A340-300 series airplanes are defined as those having Airbus
Modification 44852 or Modification 44854 applied in production, or
modified in service as specified in Airbus Service Bulletin A330-52-
3044 or Airbus

Service Bulletin A340-52-4054, as applicable.

(l) Aft Cargo Door Repetitive Inspections

    (1) Before exceeding 4,000 total flight cycles for pre-modified
airplanes, or 12,000 total flight cycles for post-modified
airplanes, since first installation of the aft cargo door on an
airplane, as applicable, or within the compliance time specified in
table 2 to paragraph (l)(1) of this AD or table 3 to paragraph
(l)(1) of this AD, as applicable, whichever occurs later, except as
specified in paragraph (q) of this AD: Do all applicable inspections
of all frame fork areas, frame head areas, and outer skin area of
each affected aft cargo door, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD. Do all
applicable related investigative actions and corrective actions
before further flight in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD, except
as required by paragraph (p) of this AD. Repeat the applicable
inspections thereafter at intervals not to exceed 1,400 flight
cycles.
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    (i) Airbus Service Bulletin A330-52-3095, Revision 02, including
Appendices 01 and 02, dated February 19, 2016 (``SB A330-52-3095,
R02'').
    (ii) Airbus Service Bulletin A340-52-4101, Revision 02,
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-4101, R02'').
    (iii) Airbus Service Bulletin A340-52-5023, Revision 02,
including Appendices 01 and 02, dated November 27, 2015 (``SB A340-
52-5023, R02'').

    (2) Concurrently with the first inspection required by paragraph
(l)(1) of this AD: Do a one-time detailed inspection of the hook
gaps ``U'' and ``V'' of each affected aft cargo door for proper
adjustment and, depending on findings, adjust the hook(s) in
accordance with the Accomplishment Instructions of the applicable
service information specified in paragraph (l)(2)(i), (l)(2)(ii), or
(l)(2)(iii) of this AD. Do all the required hook gap adjustments
before further flight.
    (i) SB A330-52-3095, R02.
    (ii) SB A340-52-4101, R02.
    (iii) SB A340-52-5023, R02.

(m) Modification for Pre-Modified Airplanes

    (1) For pre-modified airplanes, except as specified in paragraph
(m)(2) of this AD: Before exceeding 18,500 total flight cycles since
first installation of the aft cargo door on an airplane, or within
12 months after the effective date of this AD, whichever occurs
later, do reinforcement modifications, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD,
except as required by paragraph (p) of this AD.
    (i) Airbus Service Bulletin A330-52-3106, dated February 24,
2016 (for certain Model A330-301, -321, -322, -341, and -342
airplanes).
    (ii) Airbus Service Bulletin A330-52-3112, dated February 24,
2016 (for certain Model A330-202 and -223 airplanes; and Model A330-
301, -322, -341, and -342 airplanes).
    (iii) Airbus Service Bulletin A330-52-3113, dated February 15,
2016 (for certain Model A330-223 and -243 airplanes; and Model A330-
322 and -342 airplanes).
    (iv) Airbus Service Bulletin A330-52-3114, dated February 15,
2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F
airplanes; and Model A330-302, -303, -323, -342, and -343
airplanes).
    (v) Airbus Service Bulletin A340-52-4109, dated February 25,
2016 (for certain Model A340-211, -212, and -213 airplanes; and
Model A340-311, -312, and -313 airplanes).
    (vi) Airbus Service Bulletin A340-52-4115, dated February 19,
2016 (for certain Model A340-212, -213, and -313 airplanes).
    (2) Accomplishment of the reinforcement modifications required
by paragraph (m)(1) of this AD may be deferred provided that before
exceeding 18,500 total flight cycles since first installation of the
aft cargo door on an airplane, or within 12 months after the
effective date of this AD, whichever occurs later, but not earlier
than 14,500 total flight cycles, cold working is accomplished on the
frame structure of each affected aft cargo door, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-52-
3115, dated April 20, 2016; or Airbus Service Bulletin A340-52-4118,
dated April 20, 2016; as applicable. Modification of an airplane by
accomplishment of the cold working specified in this paragraph does
not constitute terminating action for the repetitive inspections
required by paragraph (l)(1) of this AD.
    (3) For an airplane on which the cold working on the cargo door
frame structure is accomplished, as specified in paragraph (m)(2) of
this AD: Within 18,500 flight cycles after the application of cold
working, do reinforcement modifications, in accordance with the
Accomplishment Instructions of the service information specified in
paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, as applicable,
or using a method approved by the Manager, International Section,
Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.

(n) Terminating Action Aft Cargo Doors for Pre-Modified Airplanes

    Modification of an airplane by reinforcement of the aft cargo
door frame structure required by paragraph (m)(1) or (m)(3) of this
AD constitutes terminating action for the inspections required by
paragraph (l)(1) and (l)(2) of this AD for that airplane.

(o) Optional Terminating Action Modification for Post-Modified
Airplanes

    For post-modified airplanes, modification of an airplane by
reinforcement of the aft cargo door frame structure, in accordance
with the Accomplishment Instructions of the applicable service
information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of
this AD, or using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA, constitutes terminating action for the inspections required by
paragraph (l)(1) and (l)(2) of this AD for that airplane. If
approved by the DOA, the approval must include the DOA-authorized
signature.

(p) Exceptions to Service Information

    Where the service information specified in paragraphs (h)(1),
(i)(1), (i)(2), (l)(1), and (m) of this AD specifies to contact
Airbus for instructions or repair, before further flight, accomplish
corrective actions in accordance with the procedures specified in
paragraph (t)(2) of this AD.

(q) Exception to Initial Inspection Compliance Time

    For the purposes of table 1 to paragraph (h)(1) of this AD,
table 2 to paragraph (l)(1) of this AD, and table 3 to paragraph
(l)(1) of this AD: As soon as a cargo door is inspected using any
applicable service information specified in this AD, the previous
inspections accomplished in accordance with any alert operator
transmission can be disregarded for the determination of the
compliance time for the initial inspection required by this AD.

(r) Exception to Reporting in the Service Information

    Although the Airbus service bulletins specified in paragraphs
(r)(1) through (r)(6) of this AD specify to submit certain
information to the manufacturer, and specify that action as ``RC''
(Required for Compliance), this AD does not include that
requirement.
    (1) SB A330-52-3087, R02.
    (2) SB A330-52-3095, R02.
    (3) SB A340-52-4095, R02.
    (4) SB A340-52-4101, R02.
    (5) SB A340-52-5020, R02.
    (6) SB A340-52-5023, R02.

(s) Credit for Previous Actions

    (1) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3087, dated August 29, 2013; Airbus Service
Bulletin A340-52-4095, dated August 29, 2013; or Airbus Service
Bulletin A340-52-5020, dated August 29, 2013; as applicable;
provided that the actions identified as ``additional work'' in the
Accomplishment Instructions of Airbus Service Bulletin A330-52-3087,
Revision 01, dated July 9, 2014; Airbus Service Bulletin A340-52-
4095, Revision 01, dated July 28, 2014; or Airbus Service Bulletin
A340-52-5020, Revision 01, dated July 9, 2014; as applicable; are
accomplished within 1,100 flight cycles after that inspection; and
provided the next inspection of all frame fork areas, frame head
areas, and outer skin area of each affected forward cargo door is
accomplished within 1,100 flight cycles after that inspection, in
accordance with the Accomplishment Instructions of SB A330-52-3087,
R02; SB A340-52-4095, R02; or SB A340-52-5020, R02, as applicable.
    (2) This paragraph provides credit for the initial inspection
required by paragraph (h) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3087, Revision 01, dated July 9, 2014; Airbus
Service Bulletin A340-52-4095, Revision 01, dated July 28, 2014; or
Airbus Service Bulletin A340-52-5020, Revision 01, dated July 9,
2014; as applicable; provided that the next inspection of all frame
fork areas, frame head areas, and outer skin area of each affected
forward cargo door, is accomplished within 1,100 flight cycles after
that inspection in accordance with the Accomplishment Instructions
of SB A330-52-3087, R02; SB A340-52-4095, R02; or SB A340-52-5020,
R02, as applicable.
    (3) This paragraph provides credit for the initial inspection
required by paragraph (l) of this AD, if that inspection was
performed before the effective date of this AD using Airbus Service
Bulletin A330-52-3095, dated August 29, 2013; Airbus Service
Bulletin A340-52-4101, dated August 29, 2013; or Airbus Service
Bulletin A340-52-5023, dated August 29, 2013; provided that the
actions identified as ``additional work'' in the Accomplishment
Instructions of Airbus Service Bulletin A330-52-3095, Revision 01,
dated July 28, 2014; Airbus Service Bulletin A340-52-4101, Revision
01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5023,
Revision 01, dated July 28, 2014; as applicable; are accomplished
within 550 flight cycles after that inspection, and provided the
next inspection of all frame fork areas, frame head areas, and outer
skin area of each affected aft cargo door is accomplished within 550
flight cycles after that inspection in accordance with the
Accomplishment Instructions of SB A330-52-3095, R02; SB A340-52-
4101, R02; or SB A340-52-5023, R02, as applicable.
    (4) This paragraph provides credit for the initial inspection
required by paragraph (l) of this AD, if that inspection was
performed before the effective date of this AD using

Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28,
2014; Airbus Service Bulletin A340-52-4101, Revision 01, dated July
28, 2014; or Airbus Service Bulletin A340-52-5023, Revision 01,
dated July 28, 2014; as applicable; provided that the next
inspection of all frame fork areas, frame head areas, and outer skin
area of each affected aft cargo door is accomplished within 550
flight cycles after that inspection in accordance with the
Accomplishment Instructions of SB A330-52-3095, R02; SB A340-52-
4101, R02; or SB A340-52-5023, R02, as applicable.
    (5) Where Airbus Service Bulletins A330-52-3095, Revision 01,
dated July 28, 2014; A340-52-4101, Revision 01, dated July 28, 2014;
A340-52-5020, Revision 01, dated July 9, 2014; and A340-52-5023,
Revision 01, dated July 28, 2014; refers to using fasteners having
P/N ASNA2657, this AD also allows the use of alternative HST11
series fasteners.

(t) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the certification office, send it to the
attention of the person identified in paragraph (u)(2) of this AD.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
    (2) Contacting the Manufacturer: 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 Section, Transport Standards
Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (p) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.

(u) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0188, dated September 21, 2016; corrected
September 22, 2016, for related information. This MCAI may be found
in the AD docket on the internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0713.
    (2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
    (3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (v)(4) and (v)(5) of this AD.

(v) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-52-3087, Revision 02, including
Appendix 01, dated February 18, 2016.
    (ii) Airbus Service Bulletin A330-52-3095, Revision 02,
including Appendices 01 and 02, dated February 19, 2016.
    (iii) Airbus Service Bulletin A330-52-3105, dated February 15,
2016.
    (iv) Airbus Service Bulletin A330-52-3106, dated February 24,
2016.
    (v) Airbus Service Bulletin A330-52-3110, dated February 15,
2016.
    (vi) Airbus Service Bulletin A330-52-3111, dated February 15,
2016.
    (vii) Airbus Service Bulletin A330-52-3112, dated February 24,
2016.
    (viii) Airbus Service Bulletin A330-52-3113, dated February 15,
2016.
    (ix) Airbus Service Bulletin A330-52-3114, dated February 15,
2016.
    (x) Airbus Service Bulletin A330-52-3115, dated April 20, 2016.
    (xi) Airbus Service Bulletin A330-52-3116, dated April 20, 2016.
    (xii) Airbus Service Bulletin A330-52-3117, dated April 20,
2016.
    (xiii) Airbus Service Bulletin A330-52-3118, dated April 20,
2016.
    (xiv) Airbus Service Bulletin A340-52-4095, Revision 02,
including Appendix 01, dated November 27, 2015.
    (xv) Airbus Service Bulletin A340-52-4101, Revision 02,
including Appendices 01 and 02, dated November 27, 2015.
    (xvi) Airbus Service Bulletin A340-52-4108, dated February 15,
2016.
    (xvii) Airbus Service Bulletin A340-52-4109, dated February 25,
2016.
    (xviii) Airbus Service Bulletin A340-52-4113, dated February 15,
2016.
    (xix) Airbus Service Bulletin A340-52-4114, dated February 15,
2016.
    (xx) Airbus Service Bulletin A340-52-4115, dated February 19,
2016.
    (xxi) Airbus Service Bulletin A340-52-4118, dated April 20,
2016.
    (xxii) Airbus Service Bulletin A340-52-4119, dated April 20,
2016.
    (xxiii) Airbus Service Bulletin A340-52-4120, dated April 20,
2016.
    (xxiv) Airbus Service Bulletin A340-52-4121, dated April 20,
2016.
    (xxv) Airbus Service Bulletin A340-52-5020, Revision 02,
including Appendices 01 and 02, dated November 27, 2015.
    (xxvi) Airbus Service Bulletin A340-52-5023, Revision 02,
including Appendices 01 and 02, dated November 27, 2015.
    (3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: [email protected];
internet: http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 11, 2018.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-01803 Filed 2-8-18; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 78, Number 230 (Friday, November 29, 2013)]
[Notices]
[Pages 71694-71695]
[FR Doc No: 2013-28574]

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SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-70928; File No. SR-CME-2013-31]

Self-Regulatory Organizations; Chicago Mercantile Exchange Inc.;
Notice of Filing and Immediate Effectiveness of Proposed Rule Change
Regarding the Addition of a New Rate Option for Interest Rate Swaps
Denominated in Mexican Peso

November 22, 2013.
    Pursuant to Section 19(b)(1) of the Securities Exchange Act of 1934
(``Act'' or ``Exchange Act''),\1\ and Rule 19b-4 thereunder,\2\ notice
is hereby given that on November 12, 2013, Chicago Mercantile Exchange
Inc. (``CME'') filed with the Securities and Exchange Commission
(``Commission'') the proposed rule change described in Items I, II and
III below, which Items have been prepared primarily by CME. CME filed
the proposal pursuant to Section 19(b)(3)(A)(iii) of the Act,\3\ and
Rule 19b-4(f)(4)(ii) \4\ thereunder so that the proposal was effective
upon filing with the Commission. 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.
    \3\ 15 U.S.C. 78s(b)(3)(A)(iii).
    \4\ 17 CFR 240.19b-4(f)(4)(ii).
---------------------------------------------------------------------------

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

    CME is filing a proposed rule change that is limited to its
business as a derivatives clearing organization. More specifically, the
proposed rule change would update the CME Rulebook to reflect the
addition of MXN-TIIE-BANXICO Rate Option for interest rate swaps
denominated in Mexican Peso (``MXN'').

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

    In its filing with the Commission, CME included statements
concerning the purpose 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. CME 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

    CME is registered as a derivatives clearing organization with the
Commodity Futures Trading Commission and currently offers clearing
services for many different futures and swaps products. With this
filing, CME proposes to make amendments to its rules to reflect the
addition of the MXN-TIIE-BANXICO Rate Option for interest rate swaps
denominated in MXN. Although these changes will be effective on filing,
CME plans to operationalize the proposed changes on November 18, 2013.
    Section 90102.E of the Rulebook is being updated to reflect the
addition of MXN-TIIE-BANXICO Rate Option for interest rate swaps
denominated in MXN. CME will also be making certain conforming changes
to its IRS Manual of Operations for CME Cleared Interest Rate Swaps to
address the addition of MXN as an eligible currency and MXN-TIIE-
BANXICO as an eligible floating rate for fixed-floating interest rate
swaps.
    The changes that are described in this filing are limited to CME's
business as a derivatives clearing organization clearing products under
the exclusive jurisdiction of the Commodity Futures Trading Commission
(``CFTC'') and do not materially impact CME's security-based swap
clearing business in any way. CME notes that it has already submitted
the proposed rule change that is the subject of this filing to its
primary regulator, the CFTC, in CME Submissions 13-520 and 13-522 (and
will also be making an additional filing with CFTC in the near future,
CME Submission No. 13-523, to provide additional information required
for the new product to the CFTC separately under CFTC Regulation 39.5).
    CME believes the proposed rule change is consistent with the
requirements of the Exchange Act including Section 17A of the Exchange
Act.\5\ The proposed rule change reflects the addition of new
derivatives products, namely, the MXN-TIIE-BANXICO Rate Option for
interest rate swaps denominated in MXN, and as such is designed to
promote the prompt and accurate clearance and settlement of securities
transactions and, to the extent applicable, derivatives agreements,
contracts, and transactions, to assure the safeguarding of securities
and funds which are in the custody or control of the clearing agency or
for which it is responsible, and, in general, to protect investors and
the public interest consistent with Section 17A(b)(3)(F) of the
Exchange Act.\6\
---------------------------------------------------------------------------

    \5\ 15 U.S.C. 78q-1.
    \6\ 15 U.S.C. 78q-1(b)(3)(F).
---------------------------------------------------------------------------

    Furthermore, the proposed changes are limited in their effect to
swaps products offered under CME's authority to act as a derivatives
clearing organization. These products are under the exclusive
jurisdiction of the CFTC. As such, the proposed CME changes are limited
to CME's activities as a derivatives clearing organization clearing
swaps that are not security-based swaps; CME notes that the policies of
the CFTC with respect to administering the Commodity Exchange Act are
comparable to a number of the policies underlying the Exchange Act,
such as promoting market transparency for over-the-counter derivatives
markets, promoting the prompt and accurate clearance of transactions
and protecting investors and the public interest.
    Because the proposed changes are limited in their effect to swaps
products offered under CME's authority to act as a derivatives clearing
organization, the proposed changes are properly classified as effecting
a change in an existing service of CME that:
    (a) Primarily affects the clearing operations of CME with respect
to products that are not securities, including futures that are not
security futures, and swaps that are not security-based swaps or mixed
swaps; and
    (b) does not significantly affect any securities clearing
operations of CME or any rights or obligations of CME with respect to
securities clearing or persons using such securities-clearing service.
    As such, the changes are therefore consistent with the requirements
of Section 17A of the Exchange Act \7\ and are properly filed under
Section 19(b)(3)(A) \8\ and Rule 19b-4(f)(4)(ii) \9\ thereunder.
---------------------------------------------------------------------------

    \7\ 15 U.S.C. 78q-1.
    \8\ 15 U.S.C. 78s(b)(3)(A).
    \9\ 17 CFR 240.19b-4(f)(4)(ii).
---------------------------------------------------------------------------

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

    CME does not believe that the proposed rule change will have any
impact, or impose any burden, on competition. The rule change merely
adds new products for clearing.

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

    CME has not solicited, and does not intend to solicit, comments
regarding this proposed rule change. CME has not

received any unsolicited written comments from interested parties.

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

    The foregoing rule change has become effective pursuant to Section
19(b)(3)(A) \10\ of the Act and Rule 19b-4(f)(4)(ii) \11\ thereunder.
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.\12\
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    \10\ 15 U.S.C. 78s(b)(3)(A).
    \11\ 17 CFR 240.19b-4(f)(4)(ii).
    \12\ 15 U.S.C. 78s(b)(3)(C).
---------------------------------------------------------------------------

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 No. SR-CME-2013-31 on the subject line.

Paper Comments

     Send paper comments in triplicate to Elizabeth M. Murphy,
Secretary, Securities and Exchange Commission, 100 F Street NE.,
Washington, DC 20549-1090.

All submissions should refer to File Number SR-CME-2013-31. 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 or
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 CME and on CME's
Web site at http://www.cmegroup.com/market-regulation/rule-filings.html.
    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-CME-2013-31
and should be submitted on or before December 20, 2013.

    For the Commission, by the Division of Trading and Markets,
pursuant to delegated authority.\13\
---------------------------------------------------------------------------

    \13\ 17 CFR 200.30-3(a)(12).
---------------------------------------------------------------------------

Kevin M. O'Neill,
Deputy Secretary.
[FR Doc. 2013-28574 Filed 11-27-13; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 78, Number 131 (Tuesday, July 9, 2013)]
[Rules and Regulations]
[Pages 40956-40958]
[FR Doc No: 2013-16388]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0520; Directorate Identifier 2013-SW-027-AD;
Amendment 39-17484; AD 2013-12-06]
RIN 2120-AA64

Airworthiness Directives; Eurocopter Deutschland (Eurocopter)
Helicopters

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, and MBB-
BK117 C-2 helicopters with a Metro Aviation (Metro) vapor-cycle air
conditioning kit installed in accordance with Supplemental Type
Certificate (STC) No. SH3880SW. This AD requires repetitively
inspecting the air conditioning drive pulley (pulley) for looseness and
properly installed lockwire, and also requires reinstalling the pulley.
This AD is prompted by two reports of the pulley detaching from the
rotor brake disc on the tail rotor (T/R) driveshaft. These actions are
intended to prevent separation of the pulley, damage to the T/R
driveshaft, and subsequent loss of control of the helicopter.

DATES: This AD becomes effective July 24, 2013.
    We must receive comments on this AD by September 9, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
     Fax:<PHONE_NUMBER>.
     Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 AD, the STC, the economic
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 service information identified in this AD, contact Metro
Aviation, Inc., 1214 Hawn Ave, Shreveport, LA 71107; phone: (318) 222-
5529; Web site: metroproductsupport.com. You may review the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.

FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone<PHONE_NUMBER>;
email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments,

commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit them only
one time. We will file in the docket all comments that we receive, as
well as a report summarizing each substantive public contact with FAA
personnel concerning this rulemaking during the comment period. We will
consider all the comments we receive and may conduct additional
rulemaking based on those comments.

Discussion

    STC No. SH3880SW approves the installation of the Metro vapor-cycle
air conditioning kit on Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4,
MBB-BK117 B-1, and MBB-BK117 C-2 helicopters. The air conditioning
compressor is driven by a pulley attached to the rotor brake disc. We
received a report of a recent incident where the fasteners attaching
the air conditioning compressor pulley to the rotor brake disc lost
torque and allowed the pulley to separate. After the helicopter landed
without incident, the pulley was discovered loose, rotating freely on,
and causing damage to the T/R driveshaft. A prior incident in 2008
occurred where the pulley mount bolts sheared, resulting in the pulley
detaching from the rotor brake disc. Separation of the pulley from the
rotor brake disc could damage the T/R driveshaft, resulting in
subsequent loss of control of the helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all information
provided by Metro and determined the unsafe condition exists and is
likely to exist or develop on other helicopters of these same type
designs.

Related Service Information

    We reviewed Metro Alert Service Bulletin No. MA145-21A-003,
Revision A, dated April 26, 2013 (ASB MA145-21A-003), which describes
procedures to inspect the pulley for properly installed lockwire, and
for removing, inspecting, and re-installing the pulley.

AD Requirements

    This AD requires, before further flight, and thereafter at
intervals not exceeding 10 hours time-in-service (TIS), inspecting the
pulley for looseness and proper installation of the lockwire on the
pulley mount bolts.
    Additionally, within 25 hours TIS, this AD requires removing the
pulley, inspecting the bolts and mounting holes with a 10X or higher
magnifying glass for damage or distortion, and re-installing the
pulley. If there is any damage or distortion, this AD requires
replacing the damaged pulley.

Differences Between This AD and the Manufacturer's Service Information

    This AD requires repetitively inspecting the pulley bolts every 10
hours TIS; the ASB does not require the repetitive inspections after
re-installing the pulley.
    This AD also applies to Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-
BK117 B-1, and MBB-BK117 C-2 helicopters; the ASB only applies to Model
MBB-BK C-2 helicopters.

Interim Action

    We consider this AD to be an interim action. The design approval
holder is currently developing a modification that will address the
unsafe condition identified in this AD. Once this modification is
developed, approved, and available, we might consider additional
rulemaking.

Costs of Compliance

    We estimate that this AD will affect 75 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. At an average labor rate of $85 per hour,
inspecting the pulley will require about .5 work-hour, for a cost per
helicopter of $43, and a total cost of $3,225 for the fleet per
inspection cycle. Inspecting and re-installing the pulley will require
about 2 work-hours, for a cost per helicopter of $170, and a total cost
of $12,750 for the fleet.
    If necessary, replacing a damaged pulley would require about 2
work-hours, and required parts would cost $525, for a total cost per
helicopter of $695.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting
these AD requirements would delay implementing the safety actions
needed to correct this known unsafe condition. Therefore, we find that
the risk to the flying public justifies waiving notice and comment
prior to the adoption of this rule because the required corrective
actions must be accomplished within 25 hours TIS or 30 calendar days, a
very short time period based on the average flight hour utilization
rate of these helicopters in the air ambulance and offshore operations
industries.
    Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.

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, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply
with this 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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

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

2013-12-06 Eurocopter Deutschland (Eurocopter): Amendment 39-17484;
Docket No. FAA-2013-0520; Directorate Identifier 2013-SW-027-AD.

(a) Applicability

    This AD applies to Eurocopter Model MBB-BK 117 A-3, MBB-BK 117
A-4, MBB-BK 117 B-1, and MBB-BK 117 C-2 helicopters with a Metro
Aviation, Inc. (Metro) vapor-cycle air conditioning kit installed in
accordance with Supplemental Type Certificate (STC) No. SH3880SW,
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as loosening of an air
conditioning drive pulley (pulley) mount bolt, which could result in
separation of the pulley from the rotor brake disc on the tail rotor
(T/R) driveshaft, damage to the T/R driveshaft, and subsequent loss
of control of the helicopter.

(c) Effective Date

    This AD becomes effective July 24, 2013.

(d) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time.

(e) Required Actions

    (1) Before further flight, and thereafter at intervals not
exceeding 10 hours time-in-service (TIS), inspect the lockwire
securing the pulley mount bolts for proper installation and the
pulley for looseness. If the lockwire is damaged or broken, or is
not installed in a tightening direction, or if the pulley is loose,
remove and inspect the pulley as described in paragraphs (e)(2)(i)
and (e)(2)(ii) of this AD.
    (2) Within 25 hours TIS:
    (i) Remove the pulley from the rotor brake disc and, using a 10X
or higher power magnifying glass, inspect the bolts and mounting
holes glass for damage or distortion. If there is any damage or
distortion, replace the pulley.
    (ii) Install the pulley and torque each mount bolt to 90 inch-
pounds. After torqueing, determine whether a gap exists among each
bolt head, washer, and the mating surface of the rotor brake disc.
If there is a gap, replace the pulley.
    (iii) Lock wire each pulley mount bolt to its adjacent rotor
brake mounting bolt with 0.6 millimeter lockwire.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Martin Crane,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas
76137; telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.

(h) Additional Information

    (1) Metro Alert Service Bulletin No. MA145-21A-003, Revision A,
dated April 26, 2013, which is not incorporated by reference,
contains additional information about the subject of this AD. For
service information identified in this AD, contact Metro Aviation,
Inc., 1214 Hawn Ave, Shreveport, LA 71107; phone:<PHONE_NUMBER>;
Web site: metroproductsupport.com. You may review a copy of the
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
    (2) STC No. SH3880SW, amended April 16, 2004, may be found on
the Internet at http://www.regulations.gov in Docket No. FAA-2013-
0520.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6500: Tail Rotor
Drive.

    Issued in Fort Worth, Texas, on June 13, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-16388 Filed 7-8-13; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 78, Number 155 (Monday, August 12, 2013)]
[Notices]
[Page 48926]
[FR Doc No: 2013-19454]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

Notice of Request To Release Airport Property

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of Intent to Rule on Request to Release Airport Property
at the Ottumwa Regional Airport (OTM), Ottumwa, Iowa.

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SUMMARY: The FAA proposes to rule and invites public comment on the
release of land, Lot 3, at the Ottumwa Regional Airport,
Ottumwa, Iowa, under the provisions of 49 U.S.C. 47107(h)(2).

DATES: Comments must be received on or before September 11, 2013.

ADDRESSES: Comments on this application may be mailed or delivered to
the FAA at the following address: Lynn D. Martin, Airports Compliance
Specialist, Federal Aviation Administration, Airports Division, ACE-
610C, 901 Locust Room 364, Kansas City, MO 64106.
    In addition, one copy of any comments submitted to the FAA must be
mailed or delivered to: Tom Francis, Airport Manager, C/O Ottumwa
Regional Airport 14802 Terminal St. Ottumwa, IA 50501,<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Lynn D. Martin, Airports Compliance
Specialist, Federal Aviation Administration, Airports Division, ACE-
610C, 901 Locust Room 364, Kansas City, MO 64106,<PHONE_NUMBER>,
<EMAIL_ADDRESS>    The request to release property may be reviewed, by appointment, in
person at this same location.

SUPPLEMENTARY INFORMATION: The FAA invites public comment on the
request to release approximately 4.80 acres of airport property, Lot
3, at the Ottumwa Regional Airport (OTM) under the provisions
of 49 U.S.C. 47107(h)(2). On January 2, 2013, the Airport Manager at
the Ottumwa Regional Airport requested from the FAA that approximately
4.80 acres of property, Lot 3, be released for sale to CT
Development, LLC. for use as a warehouse operation. On July 16, 2013,
the FAA determined that the request to release property at the Ottumwa
Regional Airport (OTM) submitted by the Sponsor meets the procedural
requirements of the Federal Aviation Administration and the release of
the property does not and will not impact future aviation needs at the
airport. The FAA may approve the request, in whole or in part, no
sooner than thirty days after the publication of this Notice.
    The following is a brief overview of the request:
    Ottumwa Regional Airport (OTM) is proposing the release of one
parcel, Lot 3, containing 4.80 acres, more or less. The
release of land is necessary to comply with Federal Aviation
Administration Grant Assurances that do not allow federally acquired
airport property to be used for non-aviation purposes. The sale of the
subject property will result in the land at the Ottumwa Regional
Airport (OTM) being changed from aeronautical to non-aeronautical use
and release the lands from the conditions of the Airport Improvement
Program Grant Agreement Grant Assurances. In accordance with 49 U.S.C.
47107(c)(2)(B)(i) and (iii), the airport will receive fair market value
for the property, which will be subsequently reinvested in another
eligible airport improvement project for general aviation facilities at
the Ottumwa Regional Airport.
    Any person may inspect, by appointment, the request in person at
the FAA office listed above under FOR FURTHER INFORMATION CONTACT. In
addition, any person may, upon appointment and request, inspect the
application, notice and other documents determined by the FAA to be
related to the application in person at the Ottumwa Regional Airport.

    Issued in Kansas City, MO on August 2, 2013.
Rodney N. Joel,
Acting Manager, Airports Division.
[FR Doc. 2013-19454 Filed 8-9-13; 8:45 am]
BILLING CODE 4910-13-P