83 FR 63598 - Airworthiness Directives; Airbus SAS Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 237 (December 11, 2018)

We propose to adopt a new airworthiness directive (AD) for certain Airbus SAS Model A318 and 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. This proposed AD was prompted by a report that taperloks used in a certain wing-to-fuselage junction were found to be non-compliant with the applicable specification, resulting in a loss of pre-tension in the fasteners. This proposed AD would require repetitive special detailed inspections of the center and outer wing box lower stiffeners and panels at a certain junction on the left- and right-hand sides for any cracking, and repair if necessary. We are proposing this AD to address the unsafe condition on these products.

[Federal Register Volume 83, Number 237 (Tuesday, December 11, 2018)]
[Proposed Rules]
[Pages 63598-63601]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2018-26624]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1007; Product Identifier 2018-NM-141-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS 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 SAS Model A318 and 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. This 
proposed AD was prompted by a report that taperloks used in a certain 
wing-to-fuselage junction were found to be non-compliant with the 
applicable specification, resulting in a loss of pre-tension in the 
fasteners. This proposed AD would require repetitive special detailed 
inspections of the center and outer wing box lower stiffeners and 
panels at a certain junction on the left- and right-hand sides for any 
cracking, and repair if necessary. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 25, 
2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For the incorporation by reference (IBR) material described in the 
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY 
INFORMATION, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; telephone +49 221 89990 1000; email [email protected]; 
internet www.easa.europa.eu. You may find this IBR material on the EASA 
website at https://ad.easa.europa.eu. You may view this IBR material at 
the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195. It is also available in the AD docket on the 
internet at http://www.regulations.gov.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1007; 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,

[[Page 63599]]

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-2018-1007; 
Product Identifier 2018-NM-141-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0218, dated October 11, 2018; corrected October 26, 2018 (``EASA 
AD 2018-0218'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus SAS Model A318 and 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:

    Taperloks used in the wing-to-fuselage junction at Rib 1 were 
found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane. To address this potential 
unsafe condition, Airbus issued SB A320-57-1129 and SB A320-57-1130, 
later revised twice, providing instructions for repetitive internal 
inspections of the lower stiffeners and for repetitive external 
inspections of the lower panels of the center and outer wing box at 
the level of Rib 1 junction. Consequently, EASA issued AD 2007-0067, 
later revised [which corresponds to FAA AD 2008-02-15, Amendment 39-
15345 (73 FR 4063, January 24, 2008) (``AD 2008-02-15'')], to 
require accomplishment of these inspections.
    Since EASA AD 2007-0067R1 was issued, new events and the results 
of studies identified an aging effect on these parts. Prompted by 
these findings, Airbus revised SB A320-57-1129 (now at Revision 05) 
and A320-57-1130 (now at Revision 04), expanding the applicability, 
modifying the area to be inspected and updating the inspection 
intervals.
    For the reasons stated above, this [EASA] AD retains the 
requirements of EASA AD 2007-0067R1, which is superseded, expands 
the Applicability, modifies the areas to be inspected and revises 
the inspection thresholds and intervals.
    This [EASA] AD is republished to correct typographical errors in 
paragraph (2) and in Tables 1 and 3.

Relationship Between Proposed AD and AD 2008-02-15

    This NPRM would not supersede AD 2008-02-15. Rather, we have 
determined that a stand-alone AD would be more appropriate to address 
the changes in the MCAI. This NPRM would require repetitive special 
detailed inspections of the center and outer wing box lower stiffeners 
and panels at the level of rib 1 junction on the left- and right-hand 
sides for any cracking, and repair if necessary. Accomplishment of the 
proposed actions would then terminate all of the requirements of AD 
2008-02-15.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2018-0218 describes procedures for repetitive special 
detailed inspections of the center and outer wing box lower stiffeners 
and panels at the level of rib 1 junction on the left- and right-hand 
sides for any cracking, and repair if necessary. EASA AD 2018-0218 also 
provides procedures for an optional modification, which would terminate 
the repetitive inspections. This material is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in the ADDRESSES section 
and it is publicly available through the EASA website.

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 referenced 
above. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of the same type design.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and the EASA to develop a process 
to use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2018-0218 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2018-0218, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2018-0218 that is required for 
compliance with EASA AD 2018-0218 will be available at http://www.regulations.gov under Docket No. FAA-2018-1007 after the FAA final 
rule is published.

Explanation of ``RC'' (Required for Compliance)

    EASA AD 2018-0218, dated October 11, 2018; corrected October 26, 
2018; might refer to service information that contains procedures or 
tests that are identified as RC. 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 alternative method of compliance 
(AMOC), provided the procedures and tests identified as RC can be done 
and the airplane can be put back in an airworthy condition.

Costs of Compliance

    We estimate that this proposed AD affects 516 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
51 work-hours x $85 per hour = $4,335........................              $0           $4,335       $2,236,860
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[[Page 63600]]

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

                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                                  Labor cost                                       Parts cost        product
----------------------------------------------------------------------------------------------------------------
244 work-hours x $85 per hour = $20,740.......................................          $5,120          $25,860
----------------------------------------------------------------------------------------------------------------

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 SAS: Docket No. FAA-2018-1007; Product Identifier 2018-NM-
141-AD.

(a) Comments Due Date

    We must receive comments by January 25, 2019.

(b) Affected ADs

    This AD affects AD 2008-02-15, Amendment 39-15345 (73 FR 4063, 
January 24, 2008) (``AD 2008-02-15'').

(c) Applicability

    This AD applies to Airbus SAS 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, as 
identified in the European Aviation Safety Agency (EASA) AD 2018-
0218, dated October 11, 2018; corrected October 26, 2018 (``EASA AD 
2018-0218'').

(d) Subject

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

(e) Reason

    This AD was prompted by a report that taperloks used in the 
wing-to-fuselage junction at rib 1 were found to be non-compliant 
with the applicable specification, resulting in a loss of pre-
tension in the fasteners. We are issuing this AD to address the loss 
of pre-tension in the fasteners, which could affect the structural 
integrity of the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2018-0218.

(h) Exceptions to EASA AD 2018-0218

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2018-0218 refers to its effective date, 
this AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2018-0218 does not apply.
    (3) Where EASA AD 2018-0218 refers to instructions provided by 
Airbus, for this AD, the instructions must be approved using a 
method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(i) Terminating Action for AD 2008-02-15

    Accomplishing the actions required by this AD terminates all 
requirements of AD 2008-02-15.

(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]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions

[[Page 63601]]

from a manufacturer, the instructions must be accomplished using a 
method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (j)(2) of this AD: Any RC procedures and tests identified 
in the service information referenced in EASA AD 2018-0218 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.

(k) Related Information

    (1) For information about EASA AD 2018-0218, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email [email protected]; Internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195. EASA AD 2018-0218 may be found in the AD docket on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-1007.
    (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.

    Issued in Des Moines, Washington, on November 29, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26624 Filed 12-10-18; 8:45 am]
 BILLING CODE 4910-13-P