[Federal Register Volume 79, Number 217 (Monday, November 10, 2014)]
[Rules and Regulations]
[Pages 66621-66622]
[FR Doc No: 2014-26531]

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DEPARTMENT OF HOMELAND SECURITY

Coast Guard

33 CFR Part 117

[Docket No. USCG-2014-0960]

Drawbridge Operation Regulation; Gulf Intracoastal Waterway,
Belle Chasse, LA

AGENCY: Coast Guard, DHS.

ACTION: Notice of deviation from drawbridge regulation.

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

SUMMARY: The Coast Guard has issued a temporary deviation from the
operating schedule that governs the Louisiana State Route 23 (SR 23)
vertical lift span bridge, also known as the Judge Perez Bridge, across
the Gulf Intracoastal Waterway (Algiers Alternate Route), mile 3.8, at
Belle Chasse, Plaquemines Parish, Louisiana. This deviation is
necessary to provide for the safe movement of vehicular traffic during
major plant reconstruction on one side of the waterway and the
resulting change in work schedule and increase in workforce transiting
the bridge. This

deviation allows the bridge to remain temporarily closed to navigation
for an additional one hour in the evening during weekdays for two
months.

DATES: This deviation is effective from 5:30 p.m. on Friday, December
26, 2014 through 6:30 p.m. on Friday, February 20, 2015.

ADDRESSES: The docket for this deviation, [USCG-2014-0960] is available
at http://www.regulations.gov. Type the docket number in the ``SEARCH''
box and click ``SEARCH.'' Click on Open Docket Folder on the line
associated with this deviation. You may also visit the Docket
Management Facility in Room W12-140 on the ground floor of the
Department of Transportation West Building, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: If you have questions on this
temporary deviation, call or email David Frank, Bridge Administration
Branch, Coast Guard; telephone<PHONE_NUMBER>, email
<EMAIL_ADDRESS>If you have questions on viewing the docket,
call Cheryl F. Collins, Program Manager, Docket Operations, telephone
202-366-9826.

SUPPLEMENTARY INFORMATION: A member of the Louisiana State Legislature
requested a temporary deviation from the operating schedule on the
Louisiana State Route 23 (SR 23) vertical lift span bridge, also known
as the Judge Perez Bridge, across the Gulf Intracoastal Waterway
(Algiers Alternate Route), mile 3.8, at Belle Chasse, Plaquemines
Parish, Louisiana. The deviation requested allows the bridge to remain
closed to navigation for an additional one hour in the evening, Monday
through Friday, for two months. This same deviation was effective from
early March 2014 through April 2014, and no issues resulted.
    The Louisiana Legislature requested this deviation due to a change
in the work schedule and increased work force related to a major plant
reconstruction at the Conoco/Phillips Refinery in Alliance. During this
change, a temporary deviation will assist in the safe movement of
vehicular traffic across the bridge and will also help to minimize the
effects of the additional traffic on local residents.
    Presently, in accordance with 33 CFR 117.451(b), the draw shall
open on signal; except that, from 6 a.m. to 8:30 a.m. and from 3:30
p.m. to 5:30 p.m. Monday through Friday, except Federal holidays, the
draw need not open for the passage of vessels.
    This temporary deviation allows the vertical lift bridge to remain
closed to navigation for one additional hour in the afternoon. This
additional hour extends the afternoon curfew hours to 6:30 p.m. Monday
through Friday beginning December 26, 2014 through February 20, 2015.
In case of an emergency, the bridge will be able to open for the
passage of vessels.
    The State Route 23 vertical lift span drawbridge across the Gulf
Intracoastal Waterway (Algiers Alternate Route), mile 3.8, at Belle
Chasse, Louisiana has a vertical clearance of 40 feet above mean high
water in the closed-to-navigation position and 100 feet above mean high
water in the open-to-navigation position. Navigation on the waterway
consists primarily of tugs with tows, commercial fishing vessels, and
occasional recreational craft. Mariners may use the Gulf Intracoastal
Waterway (Harvey Canal) to avoid unnecessary delays. The Coast Guard
has coordinated this closure with the Gulf Intracoastal Canal
Association (GICA). The GICA representative indicated that the vessel
operators will be able to schedule transits through the bridge to avoid
delays and significant impacts on operations. Due to prior experience,
as well as coordination with waterway users, it has been determined
that this closure will not have a significant effect on these vessels.
    In accordance with 33 CFR 117.35, the draw bridge must return to
its regular operating schedule immediately at the end of the effective
period of this temporary deviation. This deviation from the operating
regulations is authorized under 33 CFR 117.35.

    Dated: October 27, 2014.
David M. Frank,
Bridge Administrator, Eighth Coast Guard District.
[FR Doc. 2014-26531 Filed 11-7-14; 8:45 am]
BILLING CODE 9110-04-P


[Federal Register Volume 82, Number 75 (Thursday, April 20, 2017)]
[Rules and Regulations]
[Pages 18547-18550]
[FR Doc No: 2017-06712]

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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. 82, No. 75 / Thursday, April 20, 2017 / Rules
and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD;
Amendment 39-18845; AD 2017-07-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200, A330-300, A340-200, and A340-300 series
airplanes. This AD was prompted by a report of cracking at fastener
holes located at a certain frame on the lower shell panel junction.
This AD requires repetitive inspections of certain fastener holes, and
related investigative and corrective actions if necessary. We are
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective May 25, 2017.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 25, 2017.

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_ADDRESS>Internet
http://www.airbus.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9192.

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-2016-
9192; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket 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 Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A330-
200, A330-300, A340-200, and A340-300 series airplanes. The NPRM
published in the Federal Register on October 25, 2016 (81 FR 73357)
(``the NPRM''). The NPRM was prompted by a report of cracking at
fastener holes located at a certain frame on the lower shell panel
junction. The NPRM proposed to require repetitive inspections of
certain fastener holes, and related investigative and corrective
actions if necessary. We are issuing this AD to detect and correct
cracking at frame 40 on the lower shell panel junction; such cracking
could lead to reduced structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A330, A340-200, and A340-300 series airplanes. The MCAI states:

    During A330/A340 aeroplanes full scale fatigue test specimen in
the FR40-to-fuselage skin panel junction, fatigue damage has been
found. Corrective actions consisted of the following actions:

--In-service installation of an internal reinforcing strap on
related junction required by DGAC [Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and [DGAC
France] AD 2001-070(B),
--retrofit improvement of internal reinforcing strap fatigue life
through recommended Airbus Service Bulletin (SB) A330-53-3145, and
--new design in production through Airbus modification 44360.

    The aeroplanes listed in the Applicability section of this
[EASA] AD are all aeroplanes post-mod 44360 and pre-mod 55792
(fuselage reinforcement at FR40 in production).
    Recently, during embodiment of a FR40 web repair on an A330
aeroplane and during FR40 keel beam fitting replacement on an A340
aeroplane, the internal strap was removed and rototest inspection
was performed on several holes.
    Cracks were found on both left-hand (LH) and right-hand (RH)
sides on internal strap, or butt strap, or keel beam fitting, or
forward fitting FR40 flange.
    This condition, if not detected and corrected, could lead to
crack propagation, possibly resulting in reduced structural
integrity of the fuselage.
    For the reasons described above, this [EASA] AD requires
repetitive rototest inspections of 10 fastener holes located at FR40
lower shell panel junction on both LH and RH sides, and, depending
on findings, accomplishment of the applicable corrective actions
[which include oversizing, installing fasteners and repair; and
accomplishment of applicable related investigative actions, which
include a rototest inspection for cracking after oversizing].

    The compliance time ranges between 20,000 flight cycles or 65,400
flight hours and 20,800 flight cycles or 68,300 flight hours, depending
on airplane utilization and configuration. The repetitive inspection
interval ranges between 14,000 flight cycles or 95,200 flight hours and
24,600 flight cycles or 98,700 flight hours, depending on airplane
configuration. 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-2016-9192.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM from a
single commenter, and the FAA's response to that comment.

Request To Refer to Revised Service Information

    Delta Airlines (DAL) requested that we revise paragraphs (g),
(g)(1), and (g)(2) of the proposed AD to refer to Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. DAL also
asked that credit be given in paragraph (h)(1) of the proposed AD for
previously accomplished actions using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014. DAL stated that if the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215,
Revision 01, dated April 17, 2014, are used, operators may incorrectly
reference kit part numbers in their instructions and would then need to
submit a request for approval of an alternative method of compliance
for the replaced part.
    We agree with the commenter's request to refer to Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. Airbus
Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016,
has also been issued. No additional work is required by Airbus Service
Bulletins A330-53-3215, Revision 02; and A340-53-4215, Revision 02,
both dated November 23, 2016; the revised service information merely
corrects typographical errors and contains minor editorial changes.
    We have revised the Related Service Information under 1 CFR part 51
section of this final rule and paragraphs (g), (g)(1), and (g)(2) of
this AD to refer to Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016. We have also revised paragraph
(h)(1) of this AD to provide credit for actions accomplished prior to
the effective date of this AD using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014; and Airbus Service Bulletin
A340-53-4215, Revision 01, dated April 17, 2014.

Conclusion

    We reviewed the relevant data, considered the comment 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 minor 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

    We reviewed Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016. The service information describes
procedures for repetitive rototest inspections of certain fastener
holes, and related investigative and corrective actions if necessary.
These documents are distinct since they apply to different airplane
models. 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 41 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                Action                           Labor cost              Parts cost        product                   Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...........................  41 work-hours x $85 per hour               $0           $3,485   $142,885 per inspection cycle.
                                        = $3,485 per inspection
                                        cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that
are required based on the results of the required inspection. We have
no way of determining the number of aircraft that might need these
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair....................................  46 work-hours x $85 per hour =              $4,186           $8,096
                                             $3,910.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:

    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

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):

2017-07-07 Airbus: Amendment 39-18845; Docket No. FAA-2016-9192;
Directorate Identifier 2016-NM-038-AD.

(a) Effective Date

    This AD is effective May 25, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD, having serial
numbers 0176 through 0915 inclusive.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of cracking at fastener holes
located at frame (FR) 40 on the lower shell panel junction. We are
issuing this AD to detect and correct cracking at FR40 on the lower
shell panel junction; such cracking could lead to reduced structural
integrity of the fuselage.

(f) Compliance

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

(g) Repetitive Inspections and Related Investigative and Corrective
Actions

    Within the compliance times defined in table 1 to the
introductory text of paragraph (g) of this AD, and, thereafter, at
intervals not to exceed the compliance times defined in Airbus
Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016;
or Airbus Service Bulletin A340-53-4215, Revision 02, dated November
23, 2016; as applicable, depending on airplane utilization and
configuration: Accomplish a special detailed inspection of fastener
holes located at FR40 lower shell panel junction on both left-hand
(LH) and right-side (RH) sides, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215,
Revision 02, dated November 23, 2016; or Airbus Service Bulletin
A340-53-4215, Revision 02, dated November 23, 2016; as applicable.

Table 1 to the Introductory Text of Paragraph (g) of this AD--Compliance
                       Time for Initial Inspection
------------------------------------------------------------------------
                                            Compliance time (whichever
                                              occurs later, A or B)
------------------------------------------------------------------------
A......................................  Before exceeding the compliance
                                          time ``threshold'' defined in
                                          table 1 of Airbus Service
                                          Bulletin A330-53-3215,
                                          Revision 02, dated November
                                          23, 2016; or Airbus Service
                                          Bulletin A340-53-4215,
                                          Revision 02, dated November
                                          23, 2016; as applicable,
                                          depending on airplane
                                          utilization and configuration
                                          and to be counted from
                                          airplane first flight
B......................................  For Model A330 airplanes:
                                          Within 2,400 flight cycles or
                                          24 months, whichever occurs
                                          first after the effective date
                                          of this AD
                                         For Model A340 airplanes:
                                          Within 1,300 flight cycles or
                                          24 months, whichever occurs
                                          first after the effective date
                                          of this AD
------------------------------------------------------------------------

    (1) If, during any inspection required by the introductory text
of paragraph (g) of this AD, any crack is detected, before further
flight, accomplish all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-53-3215, Revision 02,
dated November 23, 2016; or Airbus Service Bulletin A340-53-4215,
Revision 02, dated November 23, 2016; as applicable, except where
Airbus Service Bulletin A330-53-3215, Revision 02, dated November
23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02,
dated November 23, 2016, specifies to contact Airbus for repair
instructions, and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair before further flight using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
    (2) If, during any inspection required by the introductory text
of paragraph (g) of this AD, the hole diameter is not within
tolerance of the transition fit as nominal, or first oversize, or
second oversize, or next nominal, as applicable, and Airbus Service
Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or
Airbus Service Bulletin A340-53-4215, Revision 02, dated November
23, 2016, specifies to contact Airbus for repair instructions, and
specifies that action as ``RC'' (Required for Compliance), before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
    (3) Accomplishment of corrective actions, as required by
paragraph (g)(1) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (g) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by
paragraph (g)(2) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (g) of this AD for that airplane, unless the method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates
otherwise.

(h) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by
the introductory text of paragraph (g) of this AD and the related
investigative and corrective actions required by paragraph (g)(1) of
this AD, if those actions were performed before the effective date
of this AD using Airbus Service Bulletin A330-53-3215, dated June
21, 2013; or Revision 01, dated April 17, 2014; or Airbus Service
Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated
April 17, 2014; as applicable.
    (2) This paragraph provides credit for the inspections and
corrective actions required by paragraph (g) of this AD, if those
actions were performed before the effective date of this AD using
Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B,
dated July 12, 2011.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information
may be emailed to<EMAIL_ADDRESS>Before using any
approved AMOC, notify your appropriate

principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by
paragraphs (g)(1) and (g)(2) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 2014,
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-2016-9192.
    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.

(k) 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 A330-53-3215, Revision 02, dated
November 23, 2016.
    (ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated
November 23, 2016.
    (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_ADDRESS>
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
    (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 March 28, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06712 Filed 4-19-17; 8:45 am]
 BILLING CODE 4910-13-P