[Federal Register Volume 84, Number 90 (Thursday, May 9, 2019)]
[Rules and Regulations]
[Pages 20252-20256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-09523]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1005; Product Identifier 2018-NM-109-AD; Amendment 
39-19627; AD 2019-08-06]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-16-01, 
which applied to certain Airbus SAS Model A330-200 Freighter, -200, and 
-300 series airplanes. AD 2016-16-01 required an inspection of affected 
structural parts in the cargo and cabin compartments to determine if 
proper heat treatment has been done, and replacement or repair if 
necessary. This AD retains the requirements of AD 2016-16-01 and 
requires inspection of additional locations of the cabin compartment 
structure. This AD was prompted by a report of a manufacturing defect 
(i.e., improperly heat-treated materials) that affects the durability 
of affected parts in the cargo and cabin compartments. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective June 13, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 13, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile 
Dewoitine No: 2, 31700 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, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-1005.

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-
1005; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2016-16-01, Amendment 39-18599 (81 FR 51325, 
August 4, 2016; corrected September 1, 2016 (81 FR 60246)) (``AD 2016-
16-01''). AD 2016-16-01 applied to certain Airbus SAS Model A300-200 
Freighter, -200, and -300 series airplanes. The NPRM published in the 
Federal Register on December 10, 2018 (83 FR 63444). The NPRM was 
prompted by a report of a manufacturing defect (i.e., improperly heat-
treated materials) that affects the durability of affected parts in the 
cargo and cabin compartments. The NPRM proposed to continue to require 
an inspection of affected structural parts in the cargo and cabin 
compartments to determine if proper heat treatment has been done, and 
replacement or repair if necessary. The NPRM also proposed to require 
inspection of additional locations of the cabin compartment structure. 
We are issuing this AD to address crack initiation and propagation in 
affected parts in the cargo and cabin compartments, which could result 
in 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, issued EASA AD 2018-
0147, dated July 13, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus SAS Model A330-200 Freighter, -200, 
and -300 series airplanes. The MCAI states:

    It was determined that several structural parts, intended for 
cargo or cabin compartment installation, were manufactured from 
improperly heat-treated materials. A subsequent review identified 
that some of those parts were installed on aeroplanes manufactured 
between November 2011 and February 2013. Consequently, Airbus 
implemented measures into manufacturing processes to ensure 
detection and to prevent further installation of such non-conforming 
parts. A detailed safety assessment was accomplished to identify the 
possible impact of these parts on the aeroplane structure. The 
result of this structural analysis demonstrated the capability of 
the affected structure to sustain static limit loads, but failed to 
confirm that the affected structures meet the certified fatigue 
life.
    This condition, if not detected and corrected, could lead to 
crack initiation and propagation, possibly resulting in reduced 
structural integrity of the fuselage.
    To address this unsafe condition, Airbus published the 
applicable SBs [service bulletins] to provide inspection 
instructions for affected structural cargo and cabin parts, 
respectively. Consequently, EASA issued AD 2015-0212 [which 
corresponds to FAA AD 2016-16-01] to require a one-time special 
detailed inspection (SDI) [eddy current inspection] to measure the 
electrical conductivity of affected parts, to identify the presence 
or absence of heat treatment, and, depending on findings, applicable 
corrective action(s) [replacement or repair].
    Since that [EASA] AD was issued, Airbus identified that some 
additional affected parts, located in the cabin compartment 
structure, have been missed and need to be inspected. Consequently, 
Airbus issued SB A330-53-3228 Revision 01 to introduce the locations 
of those missed structural parts to be inspected.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0212, which is superseded, and expands 
the number and locations of structural parts to be inspected.

    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-
1005.

Comments

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

Request To Delay Issuance of AD

    American Airlines (American) stated its support for the NPRM, but 
noted that Airbus Service Bulletin A330-53-3228, Revision 01, dated 
April 11, 2018,

[[Page 20253]]

included several errors, including mislabeled parts, parts depicted in 
the wrong locations, and incorrect figure references. American reported 
that Airbus has verified the errors, which Airbus indicated would be 
addressed in a revised service bulletin. To avoid the need for requests 
for alternative methods of compliance (AMOCs), American requested that 
we delay issuance of the AD until revised service information has been 
released.
    We acknowledge the commenter's concerns. The amount of 
clarification needed would be too complex to include in this AD. We 
expect to work with Airbus and EASA to issue a global AMOC that 
addresses any known errors. In addition, we have added paragraph (n) in 
this AD, ``Exception to Service Information Specifications,'' to 
provide operators with information on how to address any other issues, 
if needed. We have redesignated subsequent paragraphs accordingly. We 
have also revised paragraphs (j), (k), (l)(2), and (m) of this AD to 
refer to this exception.
    In light of the critical nature of the identified unsafe condition, 
we do not consider it warranted to delay the issuance of this final 
rule. If Airbus provides a revision to Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018, we will review it in 
consideration of an AMOC for this AD, or we may consider future 
rulemaking action.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule 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 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 Service Bulletin A330-53-3227, Revision 02, dated 
July 25, 2018, which describes procedures for inspecting affected 
structural parts in the cargo compartment to determine if proper heat 
treatment has been done, and replacing discrepant parts.
    Airbus has also issued Service Bulletin A330-53-3228, Revision 01, 
dated April 11, 2018, which describes procedures for inspecting 
affected structural parts in the cabin compartment to determine if 
proper heat treatment has been done, doing additional work (inspecting 
additional locations of the cabin compartment structure), and doing 
related investigative and corrective actions. Related investigative 
actions include an eddy current inspection to verify the measurement 
from the inspection to determine if proper heat treatment has been 
done. Corrective actions include replacing discrepant parts.
    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 20 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.
                Actions                        Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2016-16-01...  11 work-hours x $85 per               $0            $935         $18,700
                                         hour = $935.
New additional work...................  5 work-hours x $85 per                 0             425           8,500
                                         hour = $425.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
action 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 this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
45 work-hours x $85 per hour = $3,825.          $0 \*\           $3,825
------------------------------------------------------------------------
* We have received no definitive data on the parts cost for the on-
  condition action.

    According to the manufacturer, some or all of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all known costs in our cost 
estimate.

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

[[Page 20254]]

applicable to transport category airplanes and associated appliances 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) 
2016-16-01, Amendment 39-18599 (81 FR 51325, August 4, 2016; corrected 
September 1, 2016 (81 FR 60246)), and adding the following new AD:

2019-08-06 Airbus SAS: Amendment 39-19627; Docket No. FAA-2018-1005; 
Product Identifier 2018-NM-109-AD.

(a) Effective Date

    This AD is effective June 13, 2019.

(b) Affected ADs

    This AD replaces AD 2016-16-01, Amendment 39-18599 (81 FR 51325, 
August 4, 2016; corrected September 1, 2016 (81 FR 60246)) (``AD 
2016-16-01'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, manufacturer serial numbers 1175, 1180, 1287 through 1475 
inclusive, 1478, 1480, 1483, and 1506.
    (1) Model A330-223F and -243F airplanes.
    (2) Model A330-201, -202, -203, -223, and -243 airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a manufacturing defect 
(i.e., improperly heat-treated materials) that affects the 
durability of affected parts in the cargo and cabin compartments. We 
are issuing this AD to address crack initiation and propagation in 
affected parts in the cargo and cabin compartments, which could 
result in reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Retained Inspection of Affected Structure in the Cargo Compartment, 
With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2016-16-01, with revised service information. Within 72 months since 
first flight of the airplane, do an eddy current inspection (i.e., 
conductivity measurement) of affected structural parts in the cargo 
compartment to determine if proper heat treatment has been done as 
identified in, and in accordance with, the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3227, dated August 
18, 2015; or Airbus Service Bulletin A330-53-3227, Revision 02, 
dated July 25, 2018. As of the effective date of this AD, only 
Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 
2018, may be used.

(h) Retained Replacement of Non-Conforming Parts in the Cargo 
Compartment, With Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2016-16-01, with revised service information. If, during the 
inspection required by paragraph (g) of this AD, an affected 
structural part in the cargo compartment is identified to have a 
measured value greater than 26 megasiemens per meter (MS/m), or 
greater than 44.8% International Annealed Copper Standard (IACS), 
before further flight, replace the affected structural part with a 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-53-3227, dated August 18, 2015; or 
Airbus Service Bulletin A330-53-3227, Revision 02, dated July 25, 
2018. As of the effective date of this AD, only Airbus Service 
Bulletin A330-53-3227, Revision 02, dated July 25, 2018, may be 
used.

(i) Retained Repair of Non-Conforming Parts in the Cargo Compartment, 
With Revised Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2016-16-01, with revised service information. If, during the 
inspection required by paragraph (g) of this AD, an affected 
structural part in the cargo compartment is identified to have a 
measured value other than those specified in Figure A-GFAAA, Sheet 
01, ``Inspection Flowchart,'' of Airbus Service Bulletin A330-53-
3227, dated August 18, 2015; or Airbus Service Bulletin A330-53-
3227, Revision 02, dated July 25, 2018; before further flight, 
repair 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. As of the effective date of this AD, 
only Airbus Service Bulletin A330-53-3227, Revision 02, dated July 
25, 2018, may be used to identify the measured value.

(j) Retained Inspection of Affected Structure in the Cabin Compartment, 
With Revised Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2016-16-01, with revised service information. Within 72 months since 
first flight of the airplane, do an eddy current inspection of 
affected structural parts in the cabin compartment to determine if 
proper heat treatment has been done as identified in, and in 
accordance with, the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3228, dated August 18, 2015; or Airbus Service 
Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as 
required by paragraph (n) of this AD. As of the effective date of 
this AD, only Airbus Service Bulletin A330-53-3228, Revision 01, 
dated April 11, 2018, except as required by paragraph (n) of this 
AD, may be used.

(k) Retained Replacement of Non-Conforming Parts in the Cabin 
Compartment, With Revised Service Information

    This paragraph restates the requirements of paragraph (k) of AD 
2016-16-01, with revised service information. If, during the 
inspection required by paragraph (j) of this AD, an affected 
structural part in the cabin compartment is identified to have a 
measured value greater than 26 MS/m or greater than 44.8% IACS, 
before further flight, replace the affected structural part with a 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-53-3228, dated August 18, 2015; or 
Airbus Service Bulletin A330-53-3228, Revision 01, dated April 11, 
2018, except as required by paragraph (n) of this AD. As of the 
effective date of this AD, only Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018, except as required by 
paragraph (n) of this AD, may be used.

[[Page 20255]]

(l) Retained Repair of Non-Conforming Parts in the Cabin Compartment, 
With Revised Service Information and New Alternative Actions

    This paragraph restates the requirements of paragraph (l) of AD 
2016-16-01, with revised service information and new alternative 
actions. If, during the inspection required by paragraph (j) of this 
AD, an affected structural part in the cabin compartment is 
identified to have a measured value other than those specified in 
Figure A-GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus 
Service Bulletin A330-53-3228, dated August 18, 2015; or to have a 
measured value between 22 MS/m and 26 MS/m or between 37.9 and 44.8% 
IACS, as specified in Airbus Service Bulletin A330-53-3228, Revision 
01, dated April 11, 2018; before further flight, do the actions 
specified in paragraph (l)(1) or (l)(2) of this AD. As of the 
effective date of this AD, only Airbus Service Bulletin A330-53-
3228, Revision 01, dated April 11, 2018, may be used to identify the 
measured value.
    (1) Repair using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the EASA; or Airbus 
SAS's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (2) Do an eddy current inspection to verify the measurement, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3228, Revision 01, dated April 11, 2018, except as 
required by paragraph (n) of this AD.
    (i) If an affected structural part in the cabin compartment is 
identified to have a measured value between 22 MS/m and 26 MS/m or 
between 37.9 and 44.8% IACS, before further flight, repair using a 
method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or the EASA; or Airbus SAS's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (ii) If an affected structural part in the cabin compartment is 
identified to have a measured value greater than 26 MS/m or greater 
than 44.8% IACS, before further flight, do the replacement specified 
in paragraph (k) of this AD.

(m) New Requirement of This AD: Inspection of Additional Cabin 
Locations

    For an airplane on which the cabin compartment structure was 
inspected and corrective actions were done before the effective date 
of this AD as specified in the Accomplishment Instructions of Airbus 
Service Bulletin A330-53-3228, dated August 18, 2015: Before 
exceeding 108 months since the airplane's first flight, do an eddy 
current conductivity test of the forward cabin overhead compartment, 
and do all applicable related investigative and corrective actions, 
in accordance with the applicable ``additional work'' task in the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3228, 
Revision 01, dated April 11, 2018, except as required by paragraph 
(n) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Where Airbus Service 
Bulletin A330-53-3228, Revision 01, dated April 11, 2018, specifies 
to contact Airbus for appropriate action: Before further flight, 
accomplish corrective actions in accordance with the procedures 
specified in paragraph (q)(2) of this AD.

(n) Exception to Service Information Specifications

    Any required action specified in Airbus Service Bulletin A330-
53-3228, Revision 01, dated April 11, 2018, that cannot be 
accomplished as specified therein must be accomplished using a 
method approved in accordance with the procedures specified in 
paragraph (q)(1) of this AD.

(o) No Reporting

    Although Airbus Service Bulletin A330-53-3227, Revision 02, 
dated July 25, 2018; and Airbus Service Bulletin A330-53-3228, 
Revision 01, dated April 11, 2018; specify to submit certain 
information to the manufacturer, and specify that action as ``RC'' 
(required for compliance), this AD does not include that 
requirement.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using the following 
service information.
    (i) Airbus Service Bulletin A330-53-3227, dated August 18, 2015, 
which was incorporated by reference in AD 2016-16-01.
    (ii) Airbus Service Bulletin A330-53-3227, Revision 01, dated 
July 5, 2016.
    (2) This paragraph provides credit for the actions specified in 
paragraphs (j), (k), and (l) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-53-3228, dated August 18, 2015, which was incorporated 
by reference in AD 2016-16-01.

(q) 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 (r)(2) of this AD. Information 
may be emailed to [email protected].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOC letters ANM-116-17-118, dated February 2, 2017; and 
AIR-676-18-369, dated September 17, 2018; approved previously for AD 
2016-16-01, are approved as AMOCs for the corresponding provisions 
of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus SAS'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 (i), (l), (m), and (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.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0147, dated July 13, 2018, 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-2018-1005.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3229.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(4) and (s)(5) of this AD.

(s) 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 
June 13, 2019.
    (i) Airbus Service Bulletin A330-53-3227, Revision 02, dated 
July 25, 2018.
    (ii) Airbus Service Bulletin A330-53-3228, Revision 01, dated 
April 11, 2018.
    (4) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 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.
    (5) 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.
    (6) 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.


[[Page 20256]]


    Issued in Des Moines, Washington, on April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-09523 Filed 5-8-19; 8:45 am]
 BILLING CODE 4910-13-P