83 FR 27724 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 115 (June 14, 2018)

Page Range		27724-27728
FR Document		2018-12733
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 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.
Federal Register, Volume 83 Issue 115 (Thursday, June 14, 2018)
[Federal Register Volume 83, Number 115 (Thursday, June 14, 2018)]
[Proposed Rules]
[Pages 27724-27728]
From the Federal Register Online  [www.thefederalregister.org]
[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:
     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: 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 [email protected]; 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.
     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.
     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.
     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: [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) 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 [email protected]; 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
27724 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules

§ 39.13 [Amended] (2) For airplanes with more than 6,300 (2) Contacting the Manufacturer: For any
■ 2. The FAA amends § 39.13 by adding flight cycles since SSI 53–10–029 (MPD requirement in this AD to obtain corrective
the following new airworthiness 531029–DVl–10010–1) was last actions from a manufacturer, the action must
accomplished: Within 300 flight cycles or 4.5 be accomplished using a method approved
directive (AD):
months, whichever is earlier, since the last by the Manager, International Section,
BAE Systems (Operations) Limited: Docket accomplishment of SSI 53–10–029 (MPD Transport Standards Branch, FAA; or the
No. FAA–2018–0511; Product Identifier 531029–DVl–10010–1), or within 6 months European Aviation Safety Agency (EASA); or
2017–NM–145–AD. after the effective date of this AD, whichever BAE Systems (Operations) Limited’s EASA
is later. Design Organization Approval (DOA). If
(a) Comments Due Date
approved by the DOA, the approval must
We must receive comments by July 30, (h) Maintenance or Inspection Program include the DOA-authorized signature.
2018. Revisions
(m) Related Information
(b) Affected ADs Within 90 days after the effective date of
this AD: Revise the maintenance or (1) Refer to Mandatory Continuing
This AD affects AD 2005–15–11, inspection program, as applicable, by Airworthiness Information (MCAI) EASA AD
Amendment 39–14200 (70 FR 43025, July 26, incorporating the maintenance tasks and 2017–0187, dated September 22, 2017, for
2005) (‘‘AD 2005–15–11’’). related information. This MCAI may be
associated thresholds and intervals described
(c) Applicability in, and in accordance with, the found in the AD docket on the internet at
Accomplishment Instructions of BAE http://www.regulations.gov by searching for
This AD applies to all BAE Systems and locating Docket No. FAA–2018–0511.
(Operations) Limited Model 4101 airplanes, Systems (Operations) Limited Service
Bulletin J41–51–001, Revision 4, dated July (2) For more information about this AD,
certificated in any category, all manufacturer
11, 2017, as applicable. The initial contact Todd Thompson, Aerospace
serial numbers.
compliance times for new or revised tasks are Engineer, International Section, Transport
(d) Subject at the applicable times specified in BAE Standards Branch, FAA, 2200 South 216th
Air Transport Association (ATA) of Systems (Operations) Limited Service St., Des Moines, WA 98198; telephone and
America Code 05, Time Limits/Maintenance Bulletin J41–51–001, Revision 4, dated July fax 206–231–3228.
Checks. 11, 2017, or within 6 months after the (3) For service information identified in
effective date of this AD, whichever is later. this AD, contact BAE Systems (Operations)
(e) Reason Limited, Customer Information Department,
This AD was prompted by a determination (i) No Alternative Actions and Intervals Prestwick International Airport, Ayrshire,
that it is possible for cracks in fuselage frame After the maintenance or inspection KA9 2RW, Scotland, United Kingdom;
90 to exceed the critical length for failure in program has been revised as required by telephone +44 1292 675207; fax +44 1292
less time than the current inspection interval; paragraph (h) of this AD, no alternative 675704; email RApublications@
and a determination that inspection actions (e.g., inspections) or intervals may be baesystems.com; internet http://
requirements for a number of maintenance used unless the actions or intervals are www.baesystems.com/Businesses/
tasks involving certain airworthiness approved as an alternative method of RegionalAircraft/index.htm. You may view
limitations are incorrect. We are issuing this compliance (AMOC) in accordance with the this service information at the FAA,
AD to address cracking in fuselage frame 90, procedures specified in paragraph (l)(1) of Transport Standards Branch, 2200 South
which could cause it to fail and thereby this AD. 216th St., Des Moines, WA. For information
compromise the structural integrity of the on the availability of this material at the
aircraft pressure hull. We are also issuing this (j) Terminating Action for Requirements of FAA, call 206–231–3195.
AD to address fatigue damage of various AD 2005–15–11
Issued in Des Moines, Washington, on June
airplane structures, which could result in Accomplishment of the actions required by 6, 2018.
reduced structural integrity of the airplane. paragraph (h) of this AD terminates all
requirements of AD 2005–15–11. Michael Kaszycki,
(f) Compliance Acting Director, System Oversight Division,
Comply with this AD within the (k) No Reporting Requirement Aircraft Certification Service.
compliance times specified, unless already Although the Accomplishment Instructions [FR Doc. 2018–12732 Filed 6–13–18; 8:45 am]
done. of BAE Systems (Operations) Limited Alert BILLING CODE 4910–13–P
Service Bulletin J41–A53–058, dated
(g) Inspection December 6, 2016, specify to submit certain
At the compliance times specified in information to the manufacturer, this AD
paragraphs (g)(1) and (g)(2) of this AD, as does not include that requirement.
DEPARTMENT OF TRANSPORTATION
applicable: Do a detailed inspection of
fuselage frame 90 for cracking or fatigue (l) Other FAA AD Provisions Federal Aviation Administration
damage, in accordance with the The following provisions also apply to this
Accomplishment Instructions of BAE AD: 14 CFR Part 39
Systems (Operations) Limited Alert Service (1) Alternative Methods of Compliance
[Docket No. FAA–2018–0512; Product
Bulletin J41–A53–058, dated December 6, (AMOCs): The Manager, International
Identifier 2017–NM–170–AD]
2016. If any cracking or fatigue damage is Section, Transport Standards Branch, FAA,
found: Before further flight, repair using a has the authority to approve AMOCs for this RIN 2120–AA64
method approved by the Manager, AD, if requested using the procedures found
International Section, Transport Standards in 14 CFR 39.19. In accordance with 14 CFR Airworthiness Directives; Airbus
Branch, FAA; or the European Aviation 39.19, send your request to your principal Airplanes
Safety Agency (EASA); or BAE Systems inspector or local Flight Standards District
(Operations) Limited’s EASA Design Office, as appropriate. If sending information AGENCY: Federal Aviation
Organization Approval (DOA). directly to the International Section, send it Administration (FAA), DOT.
daltland on DSKBBV9HB2PROD with PROPOSALS

(1) For airplanes with 6,300 flight cycles or to the attention of the person identified in
ACTION: Notice of proposed rulemaking
fewer since Structural Significant Items (SSI) paragraph (m)(2) of this AD. Information may
53–10–029 (Maintenance Planning Document be emailed to: 9-ANM-116-AMOC- (NPRM).
(MPD) 531029–DVl–10010–1) was last REQUESTS@faa.gov. Before using any
accomplished: Within 6,600 flight cycles approved AMOC, notify your appropriate SUMMARY: We propose to adopt a new
after the last accomplishment of SSI 53–10– principal inspector, or lacking a principal airworthiness directive (AD) for certain
029 (MPD 531029–DVl–10010–1), or within 6 inspector, the manager of the local flight Airbus Model A318, A319, A320 and
months after the effective date of this AD, standards district office/certificate holding A321 series airplanes. This AD requires
whichever is later. district office. revising the maintenance or inspection

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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27725

program to incorporate new or more Comments Invited The WFD rule (75 FR 69746,
restrictive airworthiness limitations. November 15, 2010) does not require
This AD was prompted by an evaluation We invite you to send any written identifying and developing maintenance
by the design approval holder (DAH) relevant data, views, or arguments about actions if the DAHs can show that such
indicating that the principal structural this proposal. Send your comments to actions are not necessary to prevent
elements and certain life-limited parts an address listed under the ADDRESSES WFD before the airplane reaches the
are subject to widespread fatigue section. Include ‘‘Docket No. FAA– LOV. Many LOVs, however, do depend
damage (WFD). We are proposing this 2018–0512; Product Identifier 2017– on accomplishment of future
AD to address the unsafe condition on NM–170–AD’’ at the beginning of your maintenance actions. As stated in the
these products. comments. We specifically invite WFD rule, any maintenance actions
comments on the overall regulatory, necessary to reach the LOV will be
DATES: We must receive comments on economic, environmental, and energy mandated by airworthiness directives
this proposed AD by July 30, 2018. aspects of this NPRM. We will consider through separate rulemaking actions.
ADDRESSES: You may send comments, all comments received by the closing In the context of WFD, this action is
using the procedures found in 14 CFR date and may amend this NPRM based necessary to enable DAHs to propose
11.43 and 11.45, by any of the following on those comments. LOVs that allow operators the longest
methods: We will post all comments we operational lives for their airplanes, and
• Federal eRulemaking Portal: Go to receive, without change, to http:// still ensure that WFD will not occur.
http://www.regulations.gov. Follow the www.regulations.gov, including any This approach allows for an
instructions for submitting comments. personal information you provide. We implementation strategy that provides
• Fax: 202–493–2251. will also post a report summarizing each flexibility to DAHs in determining the
• Mail: U.S. Department of substantive verbal contact we receive timing of service information
Transportation, Docket Operations, about this NPRM. development (with FAA approval),
while providing operators with certainty
M–30, West Building Ground Floor, Discussion regarding the LOV applicable to their
Room W12–140, 1200 New Jersey
Fatigue damage can occur locally, in airplanes.
Avenue SE, Washington, DC 20590. This AD was prompted by an
• Hand Delivery: Deliver to Mail small areas or structural design details,
or globally, in widespread areas. evaluation by the DAH indicating that
address above between 9 a.m. and 5 the principal structural elements and
p.m., Monday through Friday, except Multiple-site damage is widespread
damage that occurs in a large structural certain life-limited parts are subject to
Federal holidays. WFD.
element such as a single rivet line of a
For service information identified in The European Aviation Safety Agency
lap splice joining two large skin panels.
this NPRM, contact Airbus, (EASA), which is the Technical Agent
Widespread damage can also occur in
Airworthiness Office—EIAS, 1 Rond for the Member States of the European
multiple elements such as adjacent
Point Maurice Bellonte, 31707 Blagnac Union, has issued EASA Airworthiness
frames or stringers. Multiple-site
Cedex, France; telephone +33 5 61 93 36 Directive 2017–0231, dated November
damage and multiple-element damage 21, 2017 (referred to after this as the
96; fax +33 5 61 93 44 51; email
cracks are typically too small initially to Mandatory Continuing Airworthiness
account.airworth-eas@airbus.com;
be reliably detected with normal Information, or ‘‘the MCAI’’), to correct
internet http://www.airbus.com. You
inspection methods. Without an unsafe condition for all Airbus
may view this service information at the
intervention, these cracks will grow, Model A318, A319, A320 and A321
FAA, Transport Standards Branch, 2200
and eventually compromise the series airplanes. The MCAI states:
South 216th St., Des Moines, WA. For
structural integrity of the airplane. This
information on the availability of this The airworthiness limitations for the A320
condition is known as widespread
material at the FAA, call 206–231–3195. family aeroplanes are currently defined and
fatigue damage. It is associated with
published in the Airbus A318/A319/A320/
Examining the AD Docket general degradation of large areas of A321 Airworthiness Limitations Section
structure with similar structural details (ALS) document(s). The Damage Tolerant
You may examine the AD docket on
and stress levels. As an airplane ages, Airworthiness Limitation Items are published
the internet at http://
WFD will likely occur, and will in ALS Part 2, approved by EASA. The
www.regulations.gov by searching for instructions contained in the ALS Part 2 have
certainly occur if the airplane is
and locating Docket No. FAA–2018– been identified as mandatory actions for
operated long enough without any
0512; or in person at the Docket continued airworthiness.
intervention.
Management Facility between 9 a.m. Failure to comply with these instructions
and 5 p.m., Monday through Friday, The FAA’s WFD final rule (75 FR could result in an unsafe condition.
except Federal holidays. The AD docket 69746, November 15, 2010) became Previously, EASA issued AD 2016–0239
contains this NPRM, the regulatory effective on January 14, 2011. The WFD [which corresponds to FAA AD 2017–22–03,
rule requires certain actions to prevent Amendment 39–19083 (82 FR 49091, October
evaluation, any comments received, and 24, 2017) (‘‘AD 2017–22–03’’)] to require
other information. The street address for structural failure due to WFD
accomplishment of all maintenance tasks as
the Docket Operations office (telephone throughout the operational life of described in ALS Part 2 at Revision 05, and
800–647–5527) is in the ADDRESSES certain existing transport category [EASA] AD 2015–0038 (later revised) [which
section. Comments will be available in airplanes and all of these airplanes that corresponds to FAA AD 2016–09–06,
the AD docket shortly after receipt. will be certificated in the future. For Amendment 39–18504 (81 FR 26113, May 2,
daltland on DSKBBV9HB2PROD with PROPOSALS

existing and future airplanes subject to 2016) (‘‘AD 2016–09–06’’)] to require the
FOR FURTHER INFORMATION CONTACT: the WFD rule, the rule requires that implementation of reduced thresholds and
Sanjay Ralhan, Aerospace Engineer, DAHs establish a limit of validity (LOV) intervals for the detailed inspection of the
International Section, Transport of the engineering data that support the forward engine mount on both right hand
Standards Branch, FAA, 2200 South and left hand sides of aeroplanes equipped
structural maintenance program. with CFM56–5A/5B engines, as specified in
216th St., Des Moines, WA 98198; Operators affected by the WFD rule may the ALS task 712111–01.
telephone and fax 206–231–3223. not fly an airplane beyond its LOV, Since those [EASA] ADs were issued,
SUPPLEMENTARY INFORMATION: unless an extended LOV is approved. Airbus published Revision 06 of the ALS Part

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27726 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules

2, and variations up to 6.3, including new 6.2, dated May 24, 2017. The service using methods that are acceptable to the
and/or more restrictive items, and new A320 information describes ALI tasks FAA. We consider those methods to be
family models were certified and added to applicable to Model A321–271N and adequate to address any corrective
the Applicability of the ALS. The ALS Part –272N airplanes. actions necessitated by the findings of
2 Revision 06 also includes the reduced • A318/A319/A320/A321
threshold and intervals required by EASA
ALS inspections required by this
AD 2015–0038R1.
Airworthiness Limitation Section Part proposed AD.
For the reason described above, this 2—Damage Tolerant Airworthiness
Limitation Items (DT–ALI), Variation Airworthiness Limitations Based on
[EASA] AD retains the requirements of EASA Type Design
AD 2016–0239 and EASA AD 2015–0038R1, 6.3, October 24, 2017. The service
which are superseded, requires information describes ALI tasks The FAA recently became aware of an
accomplishment of all maintenance tasks as associated with door stops for certain issue related to the applicability of ADs
described in the ALS Part 2 Revision 06, and Model A318, A319, A320, and A321 that require incorporation of an ALS
ALS Part 2 variations 6.1, 6.2 and 6.3 series airplanes. revision into an operator’s maintenance
(hereafter collectively referred to as ‘‘the This service information is reasonably or inspection program.
ALS’’ in this [EASA] AD), and maintains available because the interested parties Typically, when these types of ADs
specific compliance times for ALS task are issued by civil aviation authorities
have access to it through their normal
572021–01–1 (Wide Spread Fatigue Damage of other countries, they apply to all
related).
course of business or by the means
identified in the ADDRESSES section. airplanes covered under an identified
You may examine the MCAI in the type certificate (TC). The corresponding
AD docket on the internet at http:// FAA’s Determination and Requirements FAA AD typically retains applicability
www.regulations.gov by searching for of This Proposed AD to all of those airplanes.In addition, U.S.
and locating Docket No. FAA–2018– This product has been approved by operators must operate their airplanes in
0512. the aviation authority of another an airworthy condition, in accordance
country, and is approved for operation with 14 CFR 91.7(a). Included in this
Relationship Between Proposed AD, AD
in the United States. Pursuant to our obligation is the requirement to perform
2016–09–06 and AD 2017–22–03
bilateral agreement with the State of any maintenance or inspections
This NPRM would not supersede AD Design Authority, we have been notified specified in the ALS, and in accordance
2016–09–06 and AD 2017–22–03. of the unsafe condition described in the with the ALS as specified in 14 CFR
Rather, we have determined that a MCAI and service information 43.16 and 91.403(c), unless an
stand-alone AD would be more referenced above. We are proposing this alternative has been approved by the
appropriate to address the changes in AD because we evaluated all pertinent FAA.
the MCAI. This NPRM would require information and determined an unsafe When a type certificate is issued for
revising the maintenance or inspection condition exists and is likely to exist or a type design, the specific ALS,
program to incorporate new or more develop on other products of these same including revisions, is a part of that type
restrictive airworthiness limitations. type designs. design, as specified in 14 CFR 21.31(c).
Accomplishment of the proposed This proposed AD would require The sum effect of these operational
actions would then terminate the revisions to certain operator and maintenance requirements is an
requirements of paragraphs (g) and (j) of maintenance documents to include new obligation to comply with the ALS
AD 2016–09–06. Accomplishment of the actions (e.g., inspections). Compliance defined in the type design referenced in
proposed actions would also terminate with these actions is required by 14 CFR the manufacturer’s conformity
paragraphs (g)(2) and (i) of 2017–22–03. 91.403(c). For airplanes that have been statement. This obligation may
previously modified, altered, or repaired introduce a conflict with an AD that
Related Service Information Under 1
in the areas addressed by this proposed requires a specific ALS revision if new
CFR Part 51
AD, the operator may not be able to airplanes are delivered with a later
Airbus has issued A318/A319/A320/ accomplish the actions described in the revision as part of their type design.
A321 Airworthiness Limitation Section revisions. In this situation, to comply To address this conflict, the FAA has
Part 2—Damage Tolerant Airworthiness with 14 CFR 91.403(c), the operator approved alternative methods of
Limitation Items (DT–ALI), Revision 06, must request approval for an alternative compliance (AMOCs) that allow
dated April 10, 2017. The service method of compliance according to operators to incorporate the most recent
information describes new or more paragraph (j)(1) of this proposed AD. ALS revision into their maintenance/
restrictive airworthiness limitations. The request should include a inspection programs, in lieu of the ALS
Airbus has also issued the following description of changes to the required revision required by the AD. This
variations to A318/A319/A320/A321 actions that will ensure the continued eliminates the conflict and enables the
Airworthiness Limitation Section Part damage tolerance of the affected operator to comply with both the AD
2—Damage Tolerant Airworthiness structure. and the type design.
Limitation Items (DT—ALI), Revision However, compliance with AMOCs is
06, dated April 10, 2017. Differences Between This Proposed AD normally optional, and we recently
• A318/A319/A320/A321 and the MCAI became aware that some operators
Airworthiness Limitation Section Part The MCAI specifies that if there are choose to retain the AD-mandated ALS
2—Damage Tolerant Airworthiness findings from the airworthiness revision in their fleet-wide
Limitation Items (DT–ALI), Variation limitations section (ALS) inspection maintenance/inspection programs,
daltland on DSKBBV9HB2PROD with PROPOSALS

6.1, dated May 18, 2017. The service tasks, corrective actions must be including those for new airplanes
information describes ALI tasks accomplished in accordance with delivered with later ALS revisions, to
applicable to certain Model A320–200 Airbus maintenance documentation. help standardize the maintenance of the
and A321–200 airplane configurations. However, this proposed AD does not fleet. To ensure that operators comply
• A318/A319/A320/A321 include that requirement. Operators of with the applicable ALS revision for
Airworthiness Limitation Section Part U.S.-registered airplanes are required by newly delivered airplanes containing a
2—Damage Tolerant Airworthiness general airworthiness and operational later revision than that specified in an
Limitation Items (DT–ALI), Variation regulations to perform maintenance AD, we plan to limit the applicability of

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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27727

ADs that mandate ALS revisions to This proposed AD is issued in (b) Affected ADs
those airplanes that are subject to an accordance with authority delegated by This AD affects AD 2016–09–06,
earlier revision of the ALS, either as part the Executive Director, Aircraft Amendment 39–18504 (81 FR 26113, May 2,
of the type design or as mandated by an Certification Service, as authorized by 2016) (‘‘AD 2016–09–06’’) and AD 2017–22–
earlier AD. FAA Order 8000.51C. In accordance 03, Amendment 39–19083 (82 FR 49091,
This proposed AD therefore applies to with that order, issuance of ADs is October 24, 2017) (‘‘AD 2017–22–03’’).
certain Model Airbus Model A318, normally a function of the Compliance (c) Applicability
A319, A320 and A321 series airplanes and Airworthiness Division, but during This AD applies to all Airbus airplanes
with an original certificate of this transition period, the Executive identified in paragraphs (c)(1), (c)(2), (c)(3),
airworthiness or original export Director has delegated the authority to and (c)(4) of this AD; certificated in any
certificate of airworthiness that was issue ADs applicable to transport category; with an original certificate of
issued on or before the date of approval category airplanes to the Director of the airworthiness or original export certificate of
of the ALS revision identified in this System Oversight Division. airworthiness issued on or before October 24,
proposed AD. Operators of airplanes 2017.
with an original certificate of Regulatory Findings (1) Model A318–111, –112, –121, and –122
airworthiness or original export airplanes.
We determined that this proposed AD (2) Model A319–111, –112, –113, –114,
certificate of airworthiness issued after would not have federalism implications –115, –131, –132, and –133 airplanes.
that date must comply with the under Executive Order 13132. This (3) Model A320–211, –212, –214, –216,
airworthiness limitations specified as proposed AD would not have a –231, –232, –233, –251N, and –271N
part of the approved type design and substantial direct effect on the States, on airplanes.
referenced on the type certificate data the relationship between the national (4) Model A321–111, –112, –131, –211,
sheet. Government and the States, or on the –212, –213, –231, –232, –251N, –253N, 271N,
distribution of power and and –272N airplanes.
Costs of Compliance
responsibilities among the various (d) Subject
We estimate that this proposed AD levels of government.
affects 1,180 airplanes of U.S. registry. Air Transport Association (ATA) of
We estimate the following costs to For the reasons discussed above, I America Code 05, Time Limits/Maintenance
comply with this proposed AD: certify this proposed regulation: Checks.
We have determined that revising the 1. Is not a ‘‘significant regulatory (e) Reason
maintenance or inspection program action’’ under Executive Order 12866;
This AD was prompted by an evaluation by
takes an average of 90 work-hours per 2. Is not a ‘‘significant rule’’ under the the design approval holder, which indicates
operator, although we recognize that DOT Regulatory Policies and Procedures that principal structural elements and certain
this number may vary from operator to (44 FR 11034, February 26, 1979); life-limited parts are subject to widespread
operator. In the past, we have estimated 3. Will not affect intrastate aviation in fatigue damage (WFD). We are issuing this
that this action takes 1 work-hour per Alaska; and AD to prevent fatigue cracking, accidental
airplane. Since operators incorporate damage, or corrosion in principal structural
4. Will not have a significant elements, and WFD, which could result in
maintenance or inspection program economic impact, positive or negative, reduced structural integrity of the airplane.
changes for their affected fleet(s), we on a substantial number of small entities
have determined that a per-operator under the criteria of the Regulatory (f) Compliance
estimate is more accurate than a per- Flexibility Act. Comply with this AD within the
airplane estimate. Therefore, we compliance times specified, unless already
estimate the total cost per operator to be List of Subjects in 14 CFR Part 39 done.
$7,650 (90 work-hours × $85 per work- Air transportation, Aircraft, Aviation (g) New Maintenance or Inspection Program
hour). safety, Incorporation by reference, Revision
Authority for This Rulemaking Safety. (1) Within 90 days after the effective date
The Proposed Amendment of this AD, revise the maintenance or
Title 49 of the United States Code inspection program, as applicable, to
specifies the FAA’s authority to issue Accordingly, under the authority incorporate the airworthiness limitations
rules on aviation safety. Subtitle I, delegated to me by the Administrator, (ALIs) specified in Airbus A318/A319/A320/
section 106, describes the authority of the FAA proposes to amend 14 CFR part A321 Airworthiness Limitation Section Part
the FAA Administrator. ‘‘Subtitle VII: 39 as follows: 2—Damage Tolerant Airworthiness
Aviation Programs,’’ describes in more Limitation Items (DT–ALI), Revision 06,
detail the scope of the Agency’s PART 39—AIRWORTHINESS dated April 10, 2017; and A318/A319/A320/
authority. A321 Airworthiness Limitation Section Part
DIRECTIVES 2—Damage Tolerant Airworthiness
We are issuing this rulemaking under
Limitation Items (DT–ALI), Variation 6.3,
the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39 October 24, 2017. Except for ALIs identified
Part A, Subpart III, Section 44701: continues to read as follows: in paragraphs (g)(2) and (g)(3) of this AD, the
General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701. initial compliance time for accomplishing the
section, Congress charges the FAA with actions is at the applicable time identified in
promoting safe flight of civil aircraft in § 39.13 [Amended] the ALIs specified in Airbus A318/A319/
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding A320/A321 Airworthiness Limitation Section
daltland on DSKBBV9HB2PROD with PROPOSALS

for practices, methods, and procedures Part 2—Damage Tolerant Airworthiness
the following new airworthiness Limitation Items (DT–ALI), Revision 06,
the Administrator finds necessary for directive (AD):
safety in air commerce. This regulation dated April 10, 2017; A318/A319/A320/A321
Airbus: Docket No. FAA–2018–0512; Product Airworthiness Limitation Section Part 2—
is within the scope of that authority Damage Tolerant Airworthiness Limitation
Identifier 2017–NM–170–AD.
because it addresses an unsafe condition Items (DT–ALI), Variation 6.3, October 24,
that is likely to exist or develop on (a) Comments Due Date 2017; or within 90 days after the effective
products identified in this rulemaking We must receive comments by July 30, date of this AD, whichever occurs later;
action. 2018. without exceeding the inspection intervals in

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Document Created: 2018-06-14 01:39:20
Document Modified: 2018-06-14 01:39:20
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by July 30, 2018.
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.
FR Citation		83 FR 27724
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
83 FR 27724 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 115 (June 14, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
