Document ID: FAA-2017-1245-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2018-01-12T05:00Z

[Federal Register Volume 83, Number 9 (Friday, January 12, 2018)]
[Proposed Rules]
[Pages 1579-1582]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00342]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / 
Proposed Rules  

[[Page 1579]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A318 series airplanes and Model A319 series 
airplanes; all Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and all Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes. This proposed AD was prompted by an evaluation by 
the design approval holder (DAH) indicating that the holes of the upper 
cleat to upper stringer attachments at certain areas of the left- and 
right-hand wings are subject to widespread fatigue damage (WFD). This 
proposed AD would require modifying the holes of the upper cleat to 
upper stringer attachments at certain areas of the left- and right-hand 
wings. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by February 26, 
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, 1601 Lind Avenue SW, Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1245; 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, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-
227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-1245; 
Product Identifier 2017-NM-099-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

[[Page 1580]]

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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0117, dated July 7, 2017 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus Model A318 series airplanes; Model 
A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes. The MCAI states:

    Within the scope of work of service life extension for A320 
aeroplanes and of widespread fatigue damage evaluations, it has been 
determined that a structural modification is required to allow the 
aeroplanes to continue operation up to the limit of validity (LoV).
    This condition, if not corrected, may affect the structural 
integrity of the wing.
    To address this potential unsafe condition, Airbus issued SB 
A320-57-1208, providing instructions to oversize the holes of the 
upper cleat to upper stringer attachments at Rib 2 to Rib 7 
(inclusive).
    For the reason described above, this [EASA] AD requires 
modification of the affected holes.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1245.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-57-1208, dated 
November 21, 2016. The service information describes procedures for 
modifying the stringer attachments at rib 2 through rib 7 of the left- 
and right-hand wings. The modification includes oversizing the holes, 
doing an eddy current inspection of the affected holes for damage, and 
repair. 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.

Costs of Compliance

    We estimate that this proposed AD affects 1,136 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification (by oversizing and      125 work-hours x $85 per            $26,260         $36,885     $41,901,360
 doing eddy current inspection).      hour = $10,625.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This 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.

[[Page 1581]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD.

(a) Comments Due Date

    We must receive comments by February 26, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-111, -112 -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all 
manufacturer serial numbers, except airplanes specified in 
paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A318 series airplanes on which Airbus Modification 
(Mod) 39195 has been embodied in production or Airbus Service 
Bulletin A320-00-1219 has been embodied in service.
    (2) Model A319 series airplanes on which Airbus Mod 28238, Mod 
28162, and Mod 28342 have been embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that the holes of the upper cleat to upper 
stringer attachments at rib 2 through rib 7 of the left- and right-
hand wings are subject to widespread fatigue damage. We are issuing 
this AD to prevent fatigue cracking in the stringer attachment holes 
of the wings, which could result in reduced structural integrity of 
the wings.

(f) Compliance

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

(g) Modification

    Before reaching the upper limit, but not before reaching the 
lower limit, as defined in table 1 to paragraph (g) of this AD, as 
applicable: Modify the holes of the upper cleat to upper stringer 
attachments at rib 2 through rib 7 inclusive, on the left- and 
right-hand wings by oversizing the holes, doing eddy current 
inspections of the holes for damage, and repairing any damage found, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1208, dated November 21, 2016, except as required 
by paragraph (h) of this AD. Repair all damage before further 
flight.
[GRAPHIC] [TIFF OMITTED] TP12JA18.000

(h) Service Information Exception

    Where Airbus Service Bulletin A320-57-1208, dated November 21, 
2016, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance): Before 
further flight, accomplish corrective actions in accordance with the 
procedures specified in paragraph (i)(2) of this AD.

(i) 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 (j)(2) of this AD. Information 
may be emailed to [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the 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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD: If

[[Page 1582]]

any service information contains procedures or tests that are 
identified as RC, those procedures and tests must be done to comply 
with this AD; any procedures or tests that are not identified as RC 
are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0117, dated July 7, 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-2017-1245.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 
425-227-1405; fax: 425-227-1149.
    (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, 1601 Lind Avenue SW, Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on December 26, 2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-00342 Filed 1-11-18; 8:45 am]
BILLING CODE 4910-13-P