[Federal Register: September 17, 2007 (Volume 72, Number 179)]
[Notices]
[Page 52875]
[DOCID:fr17se07-54]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CP07-445-000]

Southern Natural Gas Company; Transcontinental Gas Pipe Line
Corporation; Notice of Joint Application for Abandonment

September 11, 2007.
    Take notice that on September 5, 2007, Southern Natural Gas Company
(Southern) and Transcontinental Gas Pipe Line Corporation (Transco)
filed a joint application in abbreviated format pursuant to section
7(b) of the Natural Gas Act, as amended, and the Rules and Regulations
of the Commission, for an order permitting and approving abandonment of
the transportation services provided pursuant to Transco's Rate
Schedule X-169 and Southern's Rate Schedule X-146.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211 and 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the date as indicated
below. Anyone filing an intervention or protest must serve a copy of
that document on the Applicant. Anyone filing an intervention or
protest on or before the intervention or protest date need not serve
motions to intervene or protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://www.ferc.gov.
 Persons unable to file electronically should submit an

original and 14 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street, NE., Washington, DC
20426.
    This filing is accessible on-line at http://www.ferc.gov, using the

``eLibrary'' link and is available for review in the Commission's
Public Reference Room in Washington, DC. There is an ``eSubscription''
link on the Web site that enables subscribers to receive e-mail
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please e-mail
<EMAIL_ADDRESS>or call<PHONE_NUMBER> (toll free). For

TTY, call<PHONE_NUMBER>.
    Comment Date: 5 p.m. Eastern Time September 19, 2007.

Kimberly D. Bose,
Secretary.
[FR Doc. E7-18253 Filed 9-14-07; 8:45 am]

BILLING CODE 6717-01-P


[Federal Register Volume 83, Number 190 (Monday, October 1, 2018)]
[Rules and Regulations]
[Pages 49265-49269]
[FR Doc No: 2018-21100]

========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.

========================================================================

Federal Register / Vol. 83, No. 190 / Monday, October 1, 2018 / Rules
and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0417; Product Identifier 2017-NM-132-AD; Amendment
39-19440; AD 2018-20-06]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-25-03,
which applied to certain Airbus Model A300 F4-600R series airplanes. AD
2016-25-03 required repetitive high frequency eddy current (HFEC)
inspections of the aft lower deck cargo door (LDCD) frame forks; a one-
time check of the LDCD clearances; and a one-time detailed visual
inspection of hooks, eccentric bushes, and x-stops; and corrective
actions if necessary. This AD requires repetitive HFEC inspections of
the aft LDCD frame forks; a one-time check of the LDCD clearances; and
a one-time detailed visual inspection of hooks, eccentric bushes, and
x-stops; and corrective actions if necessary. This AD was prompted by a
report of two adjacent frame forks that were found cracked on the aft
LDCD of two airplanes during scheduled maintenance, and the
introduction of frame fork reinforcement or repair procedures that,
when done, allow an extension of repetitive inspection intervals. We
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 5, 2018.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 5,
2018.
    The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
January 26, 2017 (81 FR 93801, December 22, 2016).

ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet http://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, 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-2018-0417.

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-2018-
0417; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-25-03, Amendment 39-18729 (81 FR 93801,
December 22, 2016) (``AD 2016-25-03''). AD 2016-25-03 applied to
certain Airbus Model A300 F4-600R series airplanes. The NPRM published
in the Federal Register on May 25, 2018 (83 FR 24244). The NPRM was
prompted by a report of two adjacent frame forks that were found
cracked on the aft LDCD of two airplanes during scheduled maintenance,
and the introduction of frame fork reinforcement or repair procedures
that, when done, allow an extension of repetitive inspection intervals.
The NPRM proposed to continue to require repetitive HFEC inspections of
the aft LDCD frame forks; a one-time check of the LDCD clearances; and
a one-time detailed visual inspection of hooks, eccentric bushes, and
x-stops; and corrective actions if necessary. The NPRM also proposed to
require revised corrective actions and compliance times. We are issuing
this AD to address cracked or ruptured aft LDCD frames, which could
allow loads to be transferred to the remaining structural elements.
This condition could lead to the rupture of one or more vertical aft
LDCD frames, which could result in reduced structural integrity of the
aft LDCD.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0152R1, dated May 23, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus SAS
Model A300 F4-600R series airplanes. The MCAI states:

    During scheduled maintenance at frames (FR) 61 and FR61A on the
aft lower deck cargo door (LDCD) of two A300-600F4 aeroplanes, two
adjacent frame forks were found cracked. Subsequent analysis
determined that, in case of cracked or ruptured aft cargo door
frame(s), loads will be transferred to the remaining structural
elements. However, these secondary load paths will be able to
sustain the loads for a limited number of flight cycles only.
    This condition, if not detected and corrected, could lead to the
rupture of one or more vertical aft cargo door frame(s), resulting
in reduced structural integrity of the aft cargo door.
    To address this unsafe condition, Airbus issued Alert Operators
Transmission (AOT) A52W011-15 to provide inspection instructions,
and, consequently, EASA issued AD 2015-0152 [which corresponds to
FAA AD 2016-25-03] to require repetitive inspections of the aft LDCD
frame forks and, depending on findings, the accomplishment of
applicable corrective action(s).
    Since that [EASA] AD was issued, Airbus published Service
Bulletin (SB) SB A300-52-6085 which provides frame fork

reinforcement instruction and SB A300-52-6086 which provides
instruction to inspect the cargo door for cracks as well as frame
fork replacement instructions having the inspection interval
extended from 600 flight cycles (FC) to 1,200 FC.
    For the reason described above, this [EASA] AD is revised to
introduce frame forks replacement or repair [or reinforcement] as an
allowance to extend the inspection interval.

    Required actions include repetitive HFEC inspections of the aft
LDCD frame forks and repair, reinforcement, or replacement if
necessary; a one-time check of the LDCD clearances and adjustment if
necessary; and a one-time detailed visual inspection of hooks,
eccentric bushes, and x-stops for wear, and corrective actions if
necessary. Corrective actions include blend-out, adjustment, and
replacement of hooks, bushes and x-stops. 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-2018-0417.

Comments

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

Request To Incorporate Revised Service Bulletins

    FedEx Express requested that we revise the proposed AD to
incorporate Airbus Service Bulletin A300-52-6085, Revision 01, dated
May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 01,
dated May 29, 2018. FedEx Express also requested that we update table 1
to paragraph (g) of the proposed AD with the revised compliance times
specified in Airbus Service Bulletin A300-52-6086, Revision 01, dated
May 29, 2018.
    We partially agree with the commenter's requested changes. We agree
to incorporate Airbus Service Bulletin A300-52-6085, Revision 01, dated
May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision 01,
dated May 29, 2018; because the changes to the procedures in those
documents are not significant. The changes include updating reference
documents and figures and do not result in any additional work for
airplanes modified using the previous issue. Therefore, we have revised
this AD to refer to Airbus Service Bulletin A300-52-6085, Revision 01,
dated May 2, 2018; and Airbus Service Bulletin A300-52-6086, Revision
01, dated May 29, 2018, as the appropriate sources of service
information for certain actions. We have also revised this AD to give
credit for certain actions accomplished using Airbus Service Bulletin
A300-52-6085, Revision 00, dated December 22, 2016; and Airbus Service
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
    The updated compliance times in Airbus Service Bulletin A300-52-
6086, Revision 01, dated May 29, 2018, are substantively different from
the compliance times specified in the proposed AD and would increase
the scope of this AD without allowing for public notice and comment.
Therefore, we have not changed this AD with regard to the compliance
times specified in Airbus Service Bulletin A300-52-6086. However, under
the provisions of paragraph (n)(1) of this AD, we will consider
requests for approval of alternative compliance times if sufficient
data are submitted to substantiate that the extension would provide an
acceptable level of safety.

Conclusion

    We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this final rule as proposed, except for minor editorial changes. We
have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for addressing 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 final
rule.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Alert Operators Transmission A52W011-15, Revision 00,
including Appendices 1, 2, 3, and 4, dated July 23, 2015, which
describes procedures for a check of the aft LDCD clearances ``U'' and
``V'' between the latching hooks and the eccentric bush at frame FR60
through FR64A and an adjustment of the latching hook; a detailed
inspection to detect signs of wear of the hooks, eccentric bushes, and
x-stops and corrective actions; and an HFEC inspection to detect
cracking at all frame fork stations of the aft LDCD and a replacement
of the frame fork.
     Service Bulletin A300-52-6085, Revision 01, dated May 2,
2018, which describes procedures for reinforcing frame fork fastener
holes, which include related investigative and corrective actions. The
related investigative actions include a rotating probe inspection for
cracking of the fastener holes and a check to determine the hole
diameter. Corrective actions include repair and cold working the
fastener holes.
     Service Bulletin A300-52-6086, Revision 01, dated May 29,
2018, which describes procedures for a check of the aft LDCD clearances
``U'' and ``V'' between the latching hooks and the eccentric bush at
FR60 through FR64A and an adjustment of the latching hook; and HFEC
inspection to detect cracking at all frame fork stations of the aft
LDCD and a repair of the frame fork.
    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 58 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
17 work-hours x $85 per hour = $1,445........................              $0           $1,445          $83,810
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need these on-condition actions:

                 Estimated Costs of On-condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
Up to 65 work-hours x $85 per hour =           $10,000          $15,525
 $5,525...............................
------------------------------------------------------------------------

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 removing Airworthiness Directive (AD)
2016-25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016), and
adding the following new AD:

2018-20-06 Airbus SAS: Amendment 39-19440; Docket No. FAA-2018-0417;
Product Identifier 2017-NM-132-AD.

(a) Effective Date

    This AD is effective November 5, 2018.

(b) Affected ADs

    This AD replaces AD 2016-25-03, Amendment 39-18729 (81 FR 93801,
December 22, 2016) (``AD 2016-25-03'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 F4-605R and A300 F4-
622R airplanes, certificated in any category, on which Airbus SAS
modification 12046 has been embodied in production. Modification
12046 has been embodied in production on manufacturer serial numbers
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of two adjacent frame forks
that were found cracked on the aft lower deck cargo door (LDCD) of
two airplanes during scheduled maintenance, and the introduction of
frame fork reinforcement or repair procedures that, when done, allow
an extension of repetitive inspection intervals. We are issuing this
AD to address cracked or ruptured aft LDCD frames, which could allow
loads to be transferred to the remaining structural elements. This
condition could lead to the rupture of one or more vertical aft LDCD
frames, which could result in reduced structural integrity of the
aft LDCD.

(f) Compliance

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

(g) Retained Inspection Requirements and On-Condition Actions, With
Revised Compliance Times and New Service Information

    This paragraph restates the requirements of paragraph (g) of AD
2016-25-03, with revised compliance times and new service
information. At the applicable time specified in paragraph (h) of
this AD, or before exceeding the threshold defined in table 1 to
paragraph (g) of this AD, whichever occurs later: Do the actions
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Repeat the high frequency eddy current (HFEC) inspection specified
in paragraph (g)(3) of this AD thereafter at intervals not to exceed
the applicable times specified in table 1 to paragraph (g) of this
AD.
    (1) A one-time check of the aft LDCD clearances ``U'' and ``V''
between the latching hooks and the eccentric bush at FR60 through
FR64A, in accordance with the instructions of Airbus Alert Operators
Transmission A52W011-15, Revision 00, dated July 23, 2015; or the
Accomplishment Instructions of Airbus Service Bulletin A300-52-6086,
Revision 01, dated May 29, 2018. If any value outside tolerance is
found, adjust the latching hook before further flight, in accordance
with the instructions of Airbus Alert Operators Transmission
A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment
Instructions of Airbus Service Bulletin A300-52-6086, Revision 01,
dated May 29, 2018.
    (2) A one-time detailed inspection to detect signs of wear of
the hooks, eccentric bushes, and x-stops, in accordance with the
instructions of Airbus Alert Operators Transmission A52W011-15,
Revision 00, dated July 23, 2015. If any wear is found, do all
applicable corrective actions before further flight, in accordance
with the instructions of Airbus Alert Operators Transmission
A52W011-15, Revision 00, dated July 23, 2015.
    (3) An HFEC inspection to detect cracking at all frame fork
stations of the aft LDCD, in accordance with the instructions of
Airbus Alert Operators Transmission A52W011-15, Revision 00, dated
July 23, 2015; or the Accomplishment Instructions of Airbus Service
Bulletin A300-52-6086, Revision 01, dated May 29, 2018, 2016. If any
crack is found, before further flight, replace the cracked frame
fork, in accordance with the instructions of Airbus Alert Operators
Transmission A52W011-15, Revision 00,

dated July 23, 2015; repair the cracked frame fork, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-52-6086, Revision 01, dated May 29, 2018; or reinforce the
cracked frame fork, including doing all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-52-6085,
Revision 01, dated May 2, 2018, except as required by paragraph (i)
of this AD.
[GRAPHIC] [TIFF OMITTED] TR01OC18.004

(h) Retained Compliance Times, With No Changes

    At the later of the times specified in paragraphs (h)(1) and
(h)(2) of this AD, do the actions required by paragraph (g) of this
AD.
    (1) Before the accumulation of 4,500 total flight cycles.
    (2) At the applicable time specified by paragraph (h)(2)(i) or
(h)(2)(ii) of this AD.
    (i) For airplanes that have accumulated 8,000 or more total
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 100 flight cycles after January 26, 2017.
    (ii) For airplanes that have accumulated fewer than 8,000 total
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 400 flight cycles after January 26, 2017.

(i) Service Information Exception

    Where Airbus Service Bulletin A300-52-6085, Revision 01, dated
May 2, 2018, specifies to contact Airbus for appropriate action:
Before further flight, accomplish corrective actions in accordance
with the procedures specified in paragraph (n)(2) of this AD.

(j) No Terminating Action

    Accomplishment of corrective actions on an airplane as required
by paragraph (g)(1) or (g)(2) of this AD, or repair, reinforcement,
or replacement of a frame fork as required by paragraph (g)(3) of
this AD, on the aft LDCD of an airplane does not constitute
terminating action for the repetitive HFEC inspections required by
paragraph (g)(3) of this AD for that airplane.

(k) Compliance Time Clarification

    After replacement, repair, or reinforcement of any frame fork on
the aft LDCD of an airplane, as specified in paragraph (g)(3) of
this AD, the next HFEC inspection as required by paragraph (g)(3) of
this AD can be deferred for any frame fork that is replaced,
repaired, or reinforced, but must be accomplished before exceeding
6,800 flight cycles after the replacement, repair, or reinforcement
of that frame fork.

(l) No Reporting

    Although the Accomplishment Instructions of Airbus Alert
Operators Transmission A52W011-15, Revision 00, dated July 23, 2015;
and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29,
2018; specify to submit certain information to the manufacturer,
this AD does not include that requirement.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by
paragraphs (g)(1) and (g)(3) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
    (2) This paragraph provides credit for actions required by
paragraph (g)(3) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A300-52-
6085, Revision 00, dated December 22, 2016.

(n) Other FAA AD Provisions

    (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 International Section, send it to the attention of
the person identified in paragraph (o)(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 European Aviation Safety Agency (EASA); or
Airbus SAS's EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraph (i) and paragraph (l) 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2015-0152R1, dated May 23, 2017, for related
information. This MCAI may be found in the AD docket on the
iInternet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0417.
    (2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des

Moines, WA 98198; telephone and fax<PHONE_NUMBER>.
    (3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.

(p) 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
November 5, 2018.
    (i) Airbus Service Bulletin A300-52-6085, Revision 01, dated May
2, 2018.
    (ii) Airbus Service Bulletin A300-52-6086, Revision 01, dated
May 29, 2018.
    (4) The following service information was approved for IBR on
January 26, 2017 (81 FR 93801, December 22, 2016).
    (i) Airbus Alert Operators Transmission A52W011-15, Revision 00,
dated July 23, 2015, including the following appendices:
    (A) Appendix 1--Flowchart, undated.
    (B) Appendix 2--Reporting Sheet, undated. (The pages of Appendix
2 are not numbered.)
    (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/
L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is
identified with an appendix number only on page 1 of Airbus Alert
Operators Transmission A52W011-15, Revision 00, dated July 23,
2015.)
    (D) Appendix 4--Part number identification for frame forks and
bushings, undated.
    (ii) Reserved.
    (5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; Internet
http://www.airbus.com.
    (6) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (7) 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 Des Moines, Washington, on September 21, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-21100 Filed 9-28-18; 8:45 am]
 BILLING CODE 4910-13-P