
[Federal Register Volume 84, Number 48 (Tuesday, March 12, 2019)]
[Rules and Regulations]
[Pages 8805-8807]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03405]


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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; Amendment 
39-19577; AD 2019-03-25]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting 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 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 AD requires 
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, as 
specified in an European Aviation Safety Agency (EASA) AD, which is 
incorporated by reference. This AD also provides an optional 
modification, which would terminate the repetitive inspections. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective April 16, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 16, 
2019.

ADDRESSES: For the incorporation by reference (IBR) material described 
in the ``Related IBR Material Under 1 CFR part 51'' section in 
SUPPLEMENTARY INFORMATION identified in this final rule, contact 
European Aviation Safety Agency (EASA), Konrad-Adenauer-Ufer 3, 50668 
Cologne, Germany; telephone +49 221 89990 1000; email 
ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR 
material on the EASA website at https://ad.easa.europa.eu. You may view 
this IBR material at the FAA, Transport Standards Branch, 2200 South 
216th St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2018-1007.

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 Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to 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 NPRM published in the Federal 
Register on December 11, 2018 (83 FR 63598). The NPRM 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. The NPRM proposed to 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, as 
specified in, and in compliance with, EASA AD 2018-0218, dated October 
11, 2018; corrected October 26, 2018 (``EASA AD 2018-0218''). The NPRM 
also proposed, as specified in EASA AD 2018-0218, an optional 
modification, which would terminate the repetitive inspections.
    We are issuing this AD to address the loss of pre-tension in the 
fasteners, which could affect the structural integrity of the airplane.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued 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.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for

[[Page 8806]]

and locating Docket No. FAA-2018-1007.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed, 
except for minor editorial changes. We have determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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.

Costs of Compliance

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

                                      Estimated Costs for Required Actions
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                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
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51 work-hours x $85 per hour = $4,335........................              $0           $4,335       $2,236,860
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    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this 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 AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2019-03-25 Airbus SAS: Amendment 39-19577; Docket No. FAA-2018-1007; 
Product Identifier 2018-NM-141-AD.

(a) Effective Date

    This AD is effective April 16, 2019.

(b) Affected ADs

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

[[Page 8807]]

(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) of this AD. Information may 
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2018-0218 that contains RC procedures and 
tests: Except as required by paragraph (j)(2) of this AD: RC 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(k) Related Information

    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.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Aviation Safety Agency (EASA) AD 2018-0218, dated 
October 11, 2018; corrected October 26, 2018.
    (ii) [Reserved]
    (3) For EASA AD 2018-0218, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; telephone +49 221 89990 6017; email 
ADs@easa.europa.eu; Internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) 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.
    (5) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on February 21, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-03405 Filed 3-11-19; 8:45 am]
 BILLING CODE 4910-13-P


