Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 83, Number 28 (Friday, February 9, 2018)]
[Rules and Regulations]
[Pages 5689-5700]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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 425-227-1221. 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 425-227-1138; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

[[Page 5690]]

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

[[Page 5691]]

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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.

[[Page 5692]]

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.
    <bullet> Service Bulletin A330-52-3087, Revision 02, including 
Appendix 01, dated February 18, 2016.
    <bullet> Service Bulletin A340-52-4095, Revision 02, including 
Appendix 01, dated November 29, 2015.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3105, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3110, dated February 15, 2016.
    <bullet> Service Bulletin A330-52-3111, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4108, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4113, dated February 15, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3116, dated April 20, 2016.
    <bullet> Service Bulletin A330-52-3117, dated April 20, 2016.
    <bullet> Service Bulletin A330-52-3118, dated April 20, 2016.
    <bullet> Service Bulletin A340-52-4119, dated April 20, 2016.
    <bullet> Service Bulletin A340-52-4120, dated April 20, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3095, Revision 02, including 
Appendices 01 and 02, dated February 19, 2016.
    <bullet> Service Bulletin A340-52-4101, Revision 02, including 
Appendices 01 and 02, dated November 27, 2015.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3106, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3112, dated February 24, 2016.
    <bullet> Service Bulletin A330-52-3113, dated February 15, 2016.
    <bullet> Service Bulletin A330-52-3114, dated February 15, 2016.
    <bullet> Service Bulletin A340-52-4109, dated February 25, 2016.
    <bullet> 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.
    <bullet> Service Bulletin A330-52-3115, dated April 20, 2016.
    <bullet> 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,

[[Page 5693]]

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.
BILLING CODE 4910-13-P

[[Page 5694]]

[GRAPHIC] [TIFF OMITTED] TR09FE18.000


[[Page 5695]]


[GRAPHIC] [TIFF OMITTED] TR09FE18.001

BILLING CODE 4910-13-C
    (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

[[Page 5696]]

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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BILLING CODE 4910-13-C
    (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'').

[[Page 5699]]

    (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

[[Page 5700]]

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 425-227-1138; fax 425-227-1149.
    (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 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 202-741-6030, 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

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