[Federal Register Volume 83, Number 115 (Thursday, June 14, 2018)]
[Proposed Rules]
[Pages 27724-27728]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12733]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A318, A319, A320 and A321 series airplanes. This 
AD requires revising the maintenance or inspection

[[Page 27725]]

program to incorporate new or more restrictive airworthiness 
limitations. This AD was prompted by an evaluation by the design 
approval holder (DAH) indicating that the principal structural elements 
and certain life-limited parts are subject to widespread fatigue damage 
(WFD). We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by July 30, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email <a href="/cdn-cgi/l/email-protection#305153535f455e441e515942475f4244581d555143705159425245431e535f5d"><span class="__cf_email__" data-cfemail="640507070b110a104a050d16130b16100c4901051724050d160611174a070b09">[email protected]</span></a>; internet http://www.airbus.com. 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.

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-
0512; 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 NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

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-2018-0512; 
Product Identifier 2017-NM-170-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage. It is 
associated with general degradation of large areas of structure with 
similar structural details and stress levels. As an airplane ages, WFD 
will likely occur, and will certainly occur if the airplane is operated 
long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    This AD was prompted by an evaluation by the DAH indicating that 
the principal structural elements and certain life-limited parts are 
subject to WFD.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0231, dated November 21, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320 and A321 series airplanes. The MCAI states:

    The airworthiness limitations for the A320 family aeroplanes are 
currently defined and published in the Airbus A318/A319/A320/A321 
Airworthiness Limitations Section (ALS) document(s). The Damage 
Tolerant Airworthiness Limitation Items are published in ALS Part 2, 
approved by EASA. The instructions contained in the ALS Part 2 have 
been identified as mandatory actions for continued airworthiness.
    Failure to comply with these instructions could result in an 
unsafe condition.
    Previously, EASA issued AD 2016-0239 [which corresponds to FAA 
AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) 
(``AD 2017-22-03'')] to require accomplishment of all maintenance 
tasks as described in ALS Part 2 at Revision 05, and [EASA] AD 2015-
0038 (later revised) [which corresponds to FAA AD 2016-09-06, 
Amendment 39-18504 (81 FR 26113, May 2, 2016) (``AD 2016-09-06'')] 
to require the implementation of reduced thresholds and intervals 
for the detailed inspection of the forward engine mount on both 
right hand and left hand sides of aeroplanes equipped with CFM56-5A/
5B engines, as specified in the ALS task 712111-01.
    Since those [EASA] ADs were issued, Airbus published Revision 06 
of the ALS Part

[[Page 27726]]

2, and variations up to 6.3, including new and/or more restrictive 
items, and new A320 family models were certified and added to the 
Applicability of the ALS. The ALS Part 2 Revision 06 also includes 
the reduced threshold and intervals required by EASA AD 2015-0038R1.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0239 and EASA AD 2015-0038R1, which are 
superseded, requires accomplishment of all maintenance tasks as 
described in the ALS Part 2 Revision 06, and ALS Part 2 variations 
6.1, 6.2 and 6.3 (hereafter collectively referred to as ``the ALS'' 
in this [EASA] AD), and maintains specific compliance times for ALS 
task 572021-01-1 (Wide Spread Fatigue Damage related).

    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-
0512.

Relationship Between Proposed AD, AD 2016-09-06 and AD 2017-22-03

    This NPRM would not supersede AD 2016-09-06 and AD 2017-22-03. 
Rather, we have determined that a stand-alone AD would be more 
appropriate to address the changes in the MCAI. This NPRM would require 
revising the maintenance or inspection program to incorporate new or 
more restrictive airworthiness limitations. Accomplishment of the 
proposed actions would then terminate the requirements of paragraphs 
(g) and (j) of AD 2016-09-06. Accomplishment of the proposed actions 
would also terminate paragraphs (g)(2) and (i) of 2017-22-03.

Related Service Information Under 1 CFR Part 51

    Airbus has issued A318/A319/A320/A321 Airworthiness Limitation 
Section Part 2--Damage Tolerant Airworthiness Limitation Items (DT-
ALI), Revision 06, dated April 10, 2017. The service information 
describes new or more restrictive airworthiness limitations.
    Airbus has also issued the following variations to A318/A319/A320/
A321 Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT--ALI), Revision 06, dated April 10, 
2017.
    <bullet> A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.1, dated May 18, 2017. The service information describes ALI tasks 
applicable to certain Model A320-200 and A321-200 airplane 
configurations.
    <bullet> A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.2, dated May 24, 2017. The service information describes ALI tasks 
applicable to Model A321-271N and -272N airplanes.
    <bullet> A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 
6.3, October 24, 2017. The service information describes ALI tasks 
associated with door stops for certain Model A318, A319, A320, and A321 
series airplanes.
    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.

FAA's Determination and Requirements of This Proposed AD

    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 these 
same type designs.
    This proposed AD would require revisions to certain operator 
maintenance documents to include new actions (e.g., inspections). 
Compliance with these actions is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired in 
the areas addressed by this proposed AD, the operator may not be able 
to accomplish the actions described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must request 
approval for an alternative method of compliance according to paragraph 
(j)(1) of this proposed AD. The request should include a description of 
changes to the required actions that will ensure the continued damage 
tolerance of the affected structure.

Differences Between This Proposed AD and the MCAI

    The MCAI specifies that if there are findings from the 
airworthiness limitations section (ALS) inspection tasks, corrective 
actions must be accomplished in accordance with Airbus maintenance 
documentation. However, this proposed AD does not include that 
requirement. Operators of U.S.-registered airplanes are required by 
general airworthiness and operational regulations to perform 
maintenance using methods that are acceptable to the FAA. We consider 
those methods to be adequate to address any corrective actions 
necessitated by the findings of ALS inspections required by this 
proposed AD.

Airworthiness Limitations Based on Type Design

    The FAA recently became aware of an issue related to the 
applicability of ADs that require incorporation of an ALS revision into 
an operator's maintenance or inspection program.
    Typically, when these types of ADs are issued by civil aviation 
authorities of other countries, they apply to all airplanes covered 
under an identified type certificate (TC). The corresponding FAA AD 
typically retains applicability to all of those airplanes.In addition, 
U.S. operators must operate their airplanes in an airworthy condition, 
in accordance with 14 CFR 91.7(a). Included in this obligation is the 
requirement to perform any maintenance or inspections specified in the 
ALS, and in accordance with the ALS as specified in 14 CFR 43.16 and 
91.403(c), unless an alternative has been approved by the FAA.
    When a type certificate is issued for a type design, the specific 
ALS, including revisions, is a part of that type design, as specified 
in 14 CFR 21.31(c).
    The sum effect of these operational and maintenance requirements is 
an obligation to comply with the ALS defined in the type design 
referenced in the manufacturer's conformity statement. This obligation 
may introduce a conflict with an AD that requires a specific ALS 
revision if new airplanes are delivered with a later revision as part 
of their type design.
    To address this conflict, the FAA has approved alternative methods 
of compliance (AMOCs) that allow operators to incorporate the most 
recent ALS revision into their maintenance/inspection programs, in lieu 
of the ALS revision required by the AD. This eliminates the conflict 
and enables the operator to comply with both the AD and the type 
design.
    However, compliance with AMOCs is normally optional, and we 
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection 
programs, including those for new airplanes delivered with later ALS 
revisions, to help standardize the maintenance of the fleet. To ensure 
that operators comply with the applicable ALS revision for newly 
delivered airplanes containing a later revision than that specified in 
an AD, we plan to limit the applicability of

[[Page 27727]]

ADs that mandate ALS revisions to those airplanes that are subject to 
an earlier revision of the ALS, either as part of the type design or as 
mandated by an earlier AD.
    This proposed AD therefore applies to certain Model Airbus Model 
A318, A319, A320 and A321 series airplanes with an original certificate 
of airworthiness or original export certificate of airworthiness that 
was issued on or before the date of approval of the ALS revision 
identified in this proposed AD. Operators of airplanes with an original 
certificate of airworthiness or original export certificate of 
airworthiness issued after that date must comply with the airworthiness 
limitations specified as part of the approved type design and 
referenced on the type certificate data sheet.

Costs of Compliance

    We estimate that this proposed AD affects 1,180 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:
    We have determined that revising the maintenance or inspection 
program takes an average of 90 work-hours per operator, although we 
recognize that this number may vary from operator to operator. In the 
past, we have estimated that this action takes 1 work-hour per 
airplane. Since operators incorporate maintenance or inspection program 
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate. 
Therefore, we estimate the total cost per operator to be $7,650 (90 
work-hours x $85 per work-hour).

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 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD.

(a) Comments Due Date

    We must receive comments by July 30, 2018.

(b) Affected ADs

    This AD affects AD 2016-09-06, Amendment 39-18504 (81 FR 26113, 
May 2, 2016) (``AD 2016-09-06'') and AD 2017-22-03, Amendment 39-
19083 (82 FR 49091, October 24, 2017) (``AD 2017-22-03'').

(c) Applicability

    This AD applies to all Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any 
category; with an original certificate of airworthiness or original 
export certificate of airworthiness issued on or before October 24, 
2017.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, 
and -271N airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -
251N, -253N, 271N, and -272N airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder, which indicates that principal structural elements and 
certain life-limited parts are subject to widespread fatigue damage 
(WFD). We are issuing this AD to prevent fatigue cracking, 
accidental damage, or corrosion in principal structural elements, 
and WFD, which could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) New Maintenance or Inspection Program Revision

    (1) Within 90 days after the effective date of this AD, revise 
the maintenance or inspection program, as applicable, to incorporate 
the airworthiness limitations (ALIs) specified in Airbus A318/A319/
A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 
10, 2017; and A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.3, October 24, 2017. Except for ALIs identified in 
paragraphs (g)(2) and (g)(3) of this AD, the initial compliance time 
for accomplishing the actions is at the applicable time identified 
in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness 
Limitation Section Part 2--Damage Tolerant Airworthiness Limitation 
Items (DT-ALI), Revision 06, dated April 10, 2017; A318/A319/A320/
A321 Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.3, October 24, 
2017; or within 90 days after the effective date of this AD, 
whichever occurs later; without exceeding the inspection intervals 
in

[[Page 27728]]

the ALIs required by paragraph (i) of AD 2017-22-03.
    (2) For airplanes identified in Airbus A318/A319/A320/A321 
Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 
18, 2017: Concurrently with the revision required by paragraph 
(g)(1) of this AD, revise the maintenance or inspection program, as 
applicable, to incorporate the ALIs specified in Airbus A318/A319/
A320/A321 Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 
18, 2017. The initial compliance time for accomplishing the actions 
is at the applicable time identified in the ALIs specified in Airbus 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, 
dated May 18, 2017, or within 90 days after the effective date of 
this AD, whichever occurs later; without exceeding the inspection 
intervals in the ALIs required by paragraph (i) of AD 2017-22-03.
    (3) For airplanes identified in Airbus A318/A319/A320/A321 
Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 
24, 2017: Concurrently with the revision required by paragraph 
(g)(1) of this AD, revise the maintenance or inspection program, as 
applicable, to incorporate the ALIs specified in A318/A319/A320/A321 
Airworthiness Limitation Section Part 2--Damage Tolerant 
Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 
24, 2017. The initial compliance time for accomplishing the actions 
is at the applicable time identified in the ALIs specified in Airbus 
A318/A319/A320/A321 Airworthiness Limitation Section Part 2--Damage 
Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, 
dated May 24, 2017, or within 90 days after the effective date of 
this AD, whichever occurs later; without exceeding the inspection 
intervals in the ALIs required by paragraph (i) of AD 2017-22-03.

(h) No Alternative Actions, Intervals, and Critical Design 
Configuration Control Limitations (CDCCLs)

    After the maintenance or inspection program has been revised as 
required by paragraph (g) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (j)(1) of 
this AD.

(i) Terminating Action for Other FAA ADs

    (1) Accomplishing the action required by paragraph (g) of this 
AD terminates the requirements of paragraphs (g) and (j) of AD 2016-
09-06.
    (2) Accomplishing the action required by paragraph (g) of this 
AD terminates the requirements of paragraphs (g)(2) and (i) of AD 
2017-22-03.

(j) 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 (k)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#5a63771b1417776b6b6c771b17151977081f0b0f1f090e091a3c3b3b743d352c"><span class="__cf_email__" data-cfemail="94adb9d5dad9b9a5a5a2b9d5d9dbd7b9c6d1c5c1d1c7c0c7d4f2f5f5baf3fbe2">[email protected]</span></a>.
    (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) AMOCs previously approved for AD 2015-05-02, Amendment 39-
18112 (80 FR 15152, March 23, 2015) that required incorporation of 
the service information in paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), 
(j)(1)(ii)(C), or (j)(1)(ii)(D), are approved as AMOCs for the 
corresponding provisions of this AD.
    (A) Airbus A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Revision 06, dated April 10, 2017.
    (B) Airbus A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.1, dated May 18, 2017.
    (C) Airbus A318/A319/A320/A321 Airworthiness Limitation Section 
Part 2 -Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.2, dated May 24, 2017.
    (D) A318/A319/A320/A321 Airworthiness Limitation Section Part 
2--Damage Tolerant Airworthiness Limitation Items (DT-ALI), 
Variation 6.3, October 24, 2017.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0231, dated November 21, 2017, 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-2018-0512.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email <a href="/cdn-cgi/l/email-protection#9bfaf8f8f4eef5efb5faf2e9ecf4e9eff3b6fefae8dbfaf2e9f9eee8b5f8f4f6"><span class="__cf_email__" data-cfemail="741517171b011a005a151d06031b06001c5911150734151d061601075a171b19">[email protected]</span></a>; internet http://www.airbus.com. 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.

    Issued in Des Moines, Washington, on June 6, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-12733 Filed 6-13-18; 8:45 am]
BILLING CODE 4910-13-P


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