Document ID: FAA-2018-0113-0005
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2019-05-23T04:00Z

[Federal Register Volume 84, Number 100 (Thursday, May 23, 2019)]
[Proposed Rules]
[Pages 23742-23748]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-10654]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: We are revising an earlier proposal to supersede Airworthiness 
Directive (AD) 2016-12-09, which applies to certain Airbus Model A330-
200, -200 Freighter, and -300 series airplanes; and Model A340-200 and 
-300 series airplanes. This action revises the notice of proposed 
rulemaking (NPRM) by revising the compliance time for the modification 
of the inside center wing box (CWB). We are proposing this AD to 
address the unsafe condition on these products. Since these actions 
would impose an additional burden over those in the NPRM, we are 
reopening the comment

[[Page 23743]]

period to allow the public the chance to comment on these changes.

DATES: The comment period for the NPRM published in the Federal 
Register on February 26, 2018 (83 FR 8201), is reopened.
    We must receive comments on this SNPRM by July 8, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For the material identified in this SNPRM that will be incorporated 
by reference (IBR), contact the European Aviation Safety Agency (EASA), 
at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You 
may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material 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 in the AD docket on the internet at http://www.regulations.gov.

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-
0113; 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 SNPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0113; 
Product Identifier 2017-NM-060-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this SNPRM. We will consider all 
comments received by the closing date and may amend this SNPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this SNPRM.

Discussion

    We issued AD 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 
2016) (``AD 2016-12-09''). AD 2016-12-09 requires actions to address an 
unsafe condition on certain Airbus Model A330-200, -200 Freighter, and 
-300 series airplanes, and Model A340-200 and -300 series airplanes. AD 
2016-12-09 requires removing fasteners, doing a rototest inspection of 
fastener holes, installing new fasteners, oversizing the holes and 
doing rototest inspections for cracks if necessary, and repairing any 
cracking that was found.
    We issued an NPRM to amend 14 CFR part 39 by adding an AD to 
supersede AD 2016-12-09 that would apply to certain Airbus Model A330-
200, -200 Freighter, and -300 series airplanes; and Model A340-200 and 
-300 series airplanes. The NPRM published in the Federal Register on 
February 26, 2018 (83 FR 8201) (``the NPRM''). The NPRM was prompted by 
reports that cracks were found on an adjacent hole of certain frames of 
the CWB. The NPRM proposed to require repetitive inspections of the 
fastener holes at frame (FR) 40, and, for certain airplanes, proposed 
to require a modification. The NPRM also proposed to provide an 
optional terminating action, for certain airplanes, which terminates 
the inspections.

Actions Since the NPRM was Issued

    Since we issued the NPRM, we have determined that the compliance 
time for the modification of the inside CWB must be revised.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2018-0249, dated November 16, 2018 
(``EASA AD 2018-0249'') (also referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus Model A330-200, -200 Freighter, and 
-300 series airplanes; and Model A340-200 and -300 series airplanes. 
The MCAI states:

    During accomplishment of A330 Airworthiness Limitation Item 
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between 
stringers (STR) 38 and STR39 on both left-hand (LH) and right-hand 
(RH) sides of the fuselage, cracks were found on an adjacent hole. 
After reaming at second oversize of the subject hole, the crack was 
still present. As a result of a sampling inspection program, 
additional crack findings were reported on this adjacent hole on 
other A330 and A340 aeroplanes.
    This condition, if not detected and corrected, could affect the 
structural integrity of the centre fuselage of the aeroplane.
    Prompted by these findings, Airbus issued the applicable 
Inspection [service bulletin] SB (at the time, all at original 
issue) to provide inspection instructions and, consequently, EASA 
issued AD 2014-0149 [which corresponds to FAA AD 2016-12-09] to 
require removal of the fasteners and repetitive special detailed 
inspections (SDI), including rototests, of fastener holes at FR40 
vertical web above or below CWB lower panel reference on both LH and 
RH sides of the fuselage, and, depending on findings, accomplishment 
of the applicable corrective actions. That [EASA] AD did not apply 
to aeroplanes on which Airbus modification (mod) 55792 or mod 55306 
had been embodied in production.
    After that [EASA] AD was issued, Airbus published SB A330-57-
3115 Revision 01 and SB A340-57-4124 Revision 02, which introduced 
revised thresholds and intervals for the repetitive inspections of 
the inside CWB (above bottom skin). In addition, for certain 
aeroplanes, Airbus developed mod 206051, introducing reinforcement 
of the structural integrity of the inside CWB (above bottom skin) 
area, and published the applicable Modification SB (both original 
issue), which avoided the need for repetitive inspections for the 
inside of the CWB for those aeroplane. Airbus also published SB 
A330-57-3116 Revision 01 and SB A340-57-4125 Revision 01, to include 
aeroplanes in post-mod 44360 and post-mod 49202 configuration for 
inspections of the outside CWB (below bottom skin), and introduced 
revised thresholds and intervals for the repetitive inspections of 
the outside CWB, and to provide an alleviation of the number of 
holes to be inspected. The repetitive inspection program for 
aeroplanes in pre-mod 44360 configuration remained unchanged.
    Consequently, EASA issued AD 2017-0069 [which corresponds to the 
FAA NPRM], partially retaining the requirements of EASA AD 2014-
0149, which was superseded, to require new repetitive SDI (which 
include rototests) of the fastener holes at FR40 of the inside and 
the outside CWB (above and

[[Page 23744]]

below bottom skin), and the implementation of the modification of 
the inside CWB.
    Since that [EASA] AD was issued, Airbus finalised an inspection 
program for A330-200F aeroplanes and published SB A330-57-3116 
Revision 02, SB A330-57-3132 Revision 01 and SB A330-57-3129 
Revision 01 accordingly. Airbus also published the applicable 
Modification SB, introducing a lower threshold for the modification, 
which allows operation to the Extended Service Goal (ESG) objective 
without any additional inspections. For the same reason, Airbus 
issued SB A330-57-3115 Revision 02, SB A330-57-4124 Revision 03, SB 
A330-57-3130 Revision 01 and SB A340-57-4137 Revision 01, for 
aeroplanes in post-mod 206050 configuration. Finally, it was 
determined that the lower threshold for embodiment of the applicable 
Modification SB must be counted from aeroplane first flight, not 
since Airbus mod 206049 implementation, as previously indicated.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2017-0069, which is superseded, extends the 
compliance time for A330-200F aeroplanes as no accomplishment 
instructions existed before, adds references to the latest Airbus SB 
revisions, introduces a window of embodiment for modification of the 
inside CWB, as well as a correction of the window of embodiment for 
the applicable Optional Modification SB.

    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-
0113.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2016-12-09, this proposed AD would retain certain of 
the requirements of AD 2016-12-09. Those requirements are referenced in 
EASA 2018-0249, which, in turn, is referenced in paragraph (g) of this 
proposed AD.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2018-0249 describes procedures for repetitive inspections 
of the fastener holes at FR40 vertical web of the affected CWB lower 
panel area for any cracking, and on-condition actions; modification of 
the inside CWB and an optional terminating action (modification of 
fastener holes by cold-working), which terminates the repetitive 
inspections. On-condition actions include installing new fasteners, 
additional inspections, repair, and modification. This material 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.

Comments

    We gave the public the opportunity to participate in developing 
this proposed AD. We considered the comments received.

Request To Use the Latest Service Information

    American Airlines (AAL) and Delta Airlines (DAL) requested that we 
use the latest service information in the NPRM. AAL also requested that 
we provide credit for earlier revisions of certain service information.
    We agree with the commenters request. We have revised this proposed 
AD to refer to EASA AD 2018-0249, dated November 16, 2018, which 
specifies the latest service information required to complete the 
actions specified in this proposed AD. EASA AD 2018-0249 also provides 
credit for earlier revisions of the applicable service information.

Request To Remove Certain Language From the NPRM

    DAL requested that we remove the ``pre-mod'' and ``post-mod'' 
language from the NPRM. DAL stated that paragraph (g) of the proposed 
AD (in the NPRM) defines accomplishment of repetitive inspections using 
Airbus Service Bulletin A330-57-3114, Airbus Service Bulletin A330-57-
3115, Airbus Service Bulletin A330-57-3116, Airbus Service Bulletin 
A340-57-4123, Airbus Service Bulletin A330-57-4124, and Airbus Service 
Bulletin A340-57-4125. DAL stated that each subparagraph in paragraph 
(g) of the proposed AD (in the NPRM) tries to address the affected 
airplanes using language such as ``pre-mod 56306 and pre-mod 55792.''
    DAL commented that it finds the pre-mod and post-mod language 
confusing and finds the effectivity in the service information more 
clear. DAL stated that in order to clarify the NPRM, it recommended 
that the NPRM state something such as, ``for A330-200 and -300 series 
airplanes as listed in the effectivity of the SB.'' DAL stated that it 
believes this clarification would also apply to paragraphs (m), (o), 
and (p) of the proposed AD (in the NPRM).
    We agree to clarify. The intent of paragraph (g) of the proposed AD 
(in the NPRM) was to provide additional details about which service 
information was applicable for the specified actions in the proposed 
AD, including which service information applied to specific airplane 
configurations. Paragraphs (m), (o) and (p) of the proposed AD (in the 
NPRM) also specified the airplane configuration for which the specified 
actions are applicable, which was intended to help operators determine 
which actions were applicable to a given airplane.
    As we stated previously, we have revised this proposed AD to refer 
to EASA AD 2018-0249, dated November 16, 2018, which specifies which 
actions are applicable for which airplane configurations. EASA AD 2018-
0249 has redefined configurations and clarified the ``pre-mod'' and 
``post-mod'' language.

Request To Remove the Word ``and'' From a Certain Paragraph in the 
Proposed AD

    DAL requested that we remove the word ``and'' from paragraph 
(g)(1)(iii) of the proposed AD (in the NPRM) where it discusses 
accomplishment of Airbus Service Bulletin A330-57-3115 for airplanes 
``in pre-mod 56306 and pre-mod 55792 configuration.'' DAL stated that 
normally the interpretation of the word ``and'' would mean those 
airplanes which are both pre-mod 56306 and pre-mod 55792. DAL commented 
that it has many airplanes in one group or the other, but no airplanes 
which are both pre-mod 56306 and pre-mod 55792.
    DAL stated that its airplanes are specified in the effectivity 
paragraph of the service information, and it was able to determine that 
the ``and'' was intended to mean those airplanes which are either pre-
mod 56306 or pre-mod 55792. DAL commented that EASA AD 2017-0069 refers 
to the modification numbers in the reason section of the service 
information, but thereafter refers to the service information 
effectivity, which avoids the confusion of the interpretation of 
``and'' in the text.
    We agree with the commenter's request. As we stated previously, we 
have revised this proposed AD to refer to EASA AD 2018-0249, dated 
November 16, 2018, which clarifies airplane configurations. EASA AD 
2018-0249 does not include the language DAL commented on.

Request To Revise the Grace Period From 18 Months to 24 Months

    DAL requested that we revise the grace period for the modification 
specified in paragraph (m) of the proposed AD (in the NPRM) from 18 
months to 24 months. DAL stated that paragraph (m) of the proposed AD 
(in the NPRM) specifies to do the modification using Airbus Service 
Bulletin A330-57-3129, which calls for modification within the limits 
of the service information, or within a grace period of 18 months after 
the effective date of the AD. DAL commented that its hangar check visit 
interval is 24 months.

[[Page 23745]]

DAL stated that it believes that the hangar aviation maintenance 
technicians have more structural repair experience and that the quality 
of the work would be greater if the experienced hangar crew could do 
the work. DAL also stated that the grace period in table 1 to paragraph 
(h) of the proposed AD (in the NPRM) would also need to be revised.
    We disagree with the commenter's request. The grace period, as part 
of the compliance time, is established by EASA to mitigate the unsafe 
condition. In developing the compliance time for this proposed AD 
action, we considered not only the safety implications of the 
identified unsafe condition, but the average utilization rate of the 
affected fleet, the practical aspects of an orderly modification of the 
fleet during regular maintenance periods, the availability of required 
parts, and the time necessary for the rulemaking process. The proposed 
compliance time following the effective date of the final rule was 
determined to be appropriate. We have not changed this proposed AD in 
this regard.

Request To Remove Paragraph (o)(1) of the Proposed AD (in the NPRM)

    DAL requested paragraph (o)(1) of the proposed AD (in the NPRM) be 
removed. DAL stated that paragraph (o)(1) of the proposed AD (in the 
NPRM) addressed the modification of post-mod 44360 airplanes, which are 
those affected by the inspection in Airbus Service Bulletin A330-57-
3116 and terminated by Airbus Service Bulletin A330-57-3132.
    DAL also stated that paragraph (o)(1) of the proposed AD (in the 
NPRM) includes a provision that requires that the modification be 
accomplished within the applicable compliance times specified in 
paragraph (g)(1) of the proposed AD (in the NPRM), which is the 
repetitive inspection specified in Airbus Service Bulletin A330-57-
3116. DAL commented that this means that the option to terminate exists 
only up to the limit specified in Airbus Service Bulletin A330-57-3116. 
DAL also commented that after the initial accomplishment of inspections 
specified in Airbus Service Bulletin A330-57-3116 and while doing the 
repetitive inspections specified in Airbus Service Bulletin A330-57-
3116, the optional terminating action specified in Airbus Service 
Bulletin A330-57-3132 no longer exists. DAL stated that it does not 
find a similar requirement in EASA AD 2017-0069, and it is not clear 
about why such a requirement would be technically required.
    We agree to clarify. Paragraph (o)(1) of the proposed AD (in the 
NPRM) describes an optional terminating action for a certain airplane 
configuration subject to repetitive inspections in accordance with 
paragraph (h) of the proposed AD (in the NPRM). This is the same action 
specified in paragraph (8) of EASA AD 2017-0069 (and paragraph (13) of 
EASA AD 2018-0249), which is part of the proposed requirements in 
paragraph (g) of this SNPRM. To address the unsafe condition, the 
modification specified in Airbus Service Bulletin A330-57-3132 must be 
accomplished at the time specified in Airbus Service Bulletin A330-57-
3116, which describes a lower bound (limit) of flight cycles or flight 
hours since first flight of the airplane. Airbus Service Bulletin A330-
57-3116 does not remove the option for the modification once an 
operator has begun doing the repetitive inspections on an airplane, but 
instead allows the option of doing the modification before further 
flight after an inspection is accomplished. We have not changed this 
proposed AD in this regard.

Request To Add Manufacturer Serial Numbers to the NPRM

    DAL requested that we add manufacturer serial numbers to paragraph 
(q)(3) of the proposed AD (in the NPRM). DAL stated that the paragraph 
lists several Airbus Technical Dispositions, but it was unable to find 
those Airbus Technical Dispositions on the Airbus website. DAL also 
commented that its local Airbus representatives were unable to find 
those Airbus Technical Dispositions.
    DAL stated that it submitted a request to Airbus and was told that 
these are individual repairs to individual airplanes per a telex. DAL 
stated that since the Airbus Technical Dispositions are not readily 
available, the inclusion of that Airbus Technical Dispositions 
specified in the NPRM would require each operator to submit a telex 
requesting clarification. DAL commented that if the NPRM is updated 
with a list of affected manufacturer serial numbers, each operator 
could review the list of manufacturer serial numbers, and if the 
operator does not have any manufacturer serial numbers on the list, the 
rest of the paragraph would not apply to the operator.
    We agree with the commenter's request. We have revised paragraph 
(i) of this proposed AD to specify the affected manufacturer serial 
numbers for each Airbus Technical Disposition.

FAA's Determination

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    Certain changes described above expand the scope of the NPRM. As a 
result, we have determined that it is necessary to reopen the comment 
period to provide additional opportunity for the public to comment on 
this SNPRM.

Proposed Requirements of This SNPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2018-0249 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2018-0249 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2018-0249, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2018-0249 that is required for 
compliance with EASA AD 2018-0249 will be available on the internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0113 after the FAA final rule is published.

Costs of Compliance

    We estimate that this proposed AD affects 103 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 23746]]

                                                          Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                        Labor cost                 Parts cost                Cost per product            Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2016-12-09.  Up to 155 work-hours x   $0.........................  Up to $13,175..............  Up to $1,357,025.
                                       $85 per hour = $13,175.
New proposed actions................  Up to 145 work-hours x   Up to $650.................  Up to $12,975..............  Up to $1,336,425.
                                       $85 per hour = $12,325.
--------------------------------------------------------------------------------------------------------------------------------------------------------

                  Estimated Costs for Optional Actions
------------------------------------------------------------------------
         Labor cost                Parts cost         Cost per product
------------------------------------------------------------------------
Up to 145 work-hours x $85    Up to $621..........  Up to $12,946.
 per hour = $12,325.
------------------------------------------------------------------------

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

                 Estimated costs of On-Condition Actions
------------------------------------------------------------------------
         Labor cost                Parts cost         Cost per product
------------------------------------------------------------------------
Up to 105 work-hours x $85    Up to $22,488.......  Up to $31,413.
 per hour = $8,925.
------------------------------------------------------------------------

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 proposed 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 and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016), and adding 
the following new AD:

Airbus SAS: Docket No. FAA-2018-0113; Product Identifier 2017-NM-
060-AD.

(a) Comments Due Date

    We must receive comments by July 8, 2019.

(b) Affected ADs

    This AD replaces AD 2016-12-09, Amendment 39-18558 (81 FR 38573, 
June 14, 2016) (``AD 2016-12-09'').

(c) Applicability

    This AD applies to Airbus SAS Model airplanes identified in 
paragraphs (c)(1) through (c)(5) of this AD, certificated in any 
category, as identified in European Aviation Safety Agency (EASA) AD 
2018-0249, dated November 16, 2018 (``EASA AD 2018-0249'').
    (1) Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Model A330-223F and -243F airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.
    (4) Model A340-211, -212, and -213 airplanes.
    (5) Model A340-311, -312, and -313 airplanes.

[[Page 23747]]

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports that cracks were found on an 
adjacent hole of certain frames of the center wing box (CWB) and a 
determination that the compliance time specified in AD 2016-12-09 
for the modification of the inside CWB must be revised. We are 
issuing this AD to address cracking of certain holes of certain 
frames of the CWB, which could affect the structural integrity of 
the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2018-0249.

(h) Exceptions to EASA AD 2018-0249

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2018-0249 refers to its effective date or 
the effective date of EASA AD 2017-0069, this AD requires using the 
effective date of this AD.
    (2) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2018-0249 refers to the effective date of 
EASA AD 2014-0149, this AD requires using June 29, 2016 (the 
effective date of AD 2016-12-09).
    (3) The ``Remarks'' section of EASA AD 2018-0249 does not apply 
to this AD.

(i) Reference to Manufacturer Serial Numbers for Airbus Technical 
Dispositions

    Figure 1 to paragraph (i) of this AD identifies the Airbus 
Technical Dispositions specified in paragraph (9) of EASA AD 2018-
0249 and their associated manufacturer serial numbers.
[GRAPHIC] [TIFF OMITTED] TP23MY19.000

(j) Terminating Action for AD 2016-12-09

    Accomplishing the actions required by this AD terminates all 
requirements of AD 2016-12-09.

(k) No Reporting Requirement

    Although the service information referenced in EASA AD 2018-0249 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

(l) 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 International Section, send it to the attention of 
the person identified in paragraph (m)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2018-0249 that contains RC procedures and 
tests: Except as required by paragraph (l)(2) of this AD, RC 
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.

(m) Related Information

    (1) For information about EASA AD 2018-0249, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email ADs@easa.europa.eu; Internet

[[Page 23748]]

www.easa.europa.eu. You may find this EASA AD on the EASA website at 
https://ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2018-0249 may be found in the AD docket 
on the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0113.
    (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.

    Issued in Des Moines, Washington, on May 6, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-10654 Filed 5-22-19; 8:45 am]
 BILLING CODE 4910-13-P