[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)]
[Rules and Regulations]
[Pages 22354-22357]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: R1-2018-09280]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD; Amendment 
39-19266; AD 2018-09-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes Republication

Republication

    Editorial Note: Rule document 2018-09280 was originally 
published on pages 19925 through 19928 in the issue of Monday, May 
7, 2018. In that publication, on page 19927, in Table 1 to paragraph 
(g) of this AD, the last line was omitted from the table. The 
corrected document is published here in its entirety.

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 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 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 AD requires 
modifying the holes of the upper cleat to upper stringer attachments at 
certain areas of the left- and right-hand wings. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective June 11, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 11, 
2018.

ADDRESSES: For service information identified in this final rule, 
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 referenced 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. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-1245.

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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, 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 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

[[Page 22355]]

-232 airplanes. The NPRM published in the Federal Register on January 
12, 2018 (83 FR 1579) (``the NPRM''). The NPRM was prompted by an 
evaluation by the 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 WFD. The NPRM proposed to require modifying the 
holes of the upper cleat to upper stringer attachments at certain areas 
of the left- and right-hand wings. 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.
    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 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. 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 
[service bulletin] 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment. United Airlines agreed with the 
intent of the NPRM.

Request To Clarify Applicability

    Allegiant Air asked that we clarify the manufacturer serial numbers 
(MSNs) identified in the applicability section of the proposed AD. 
Allegiant Air stated that the effectivity specified in Airbus Service 
Bulletin A320-57-1208, dated November 21, 2016, identifies airplanes up 
to and including MSN 7493, and asked about airplanes having MSNs higher 
than 7493. Allegiant Air noted that it has 11 Model A320 airplanes with 
MSNs outside those listed in Airbus Service Bulletin A320-57-1208, 
dated November 21, 2016. Allegiant Air added that it understands the AD 
takes precedence over the service information, but there are several 
configurations listed therein. Allegiant Air also added that since the 
MSNs in question are not listed in the effectivity of the service 
information, an operator with an MSN outside the effectivity will not 
know which modification kit to order.
    We agree to clarify. The effectivity in Airbus Service Bulletin 
A320-57-1208, dated November 21, 2016, does not include all MSNs for 
Model A320 airplanes, and the applicability specified in paragraph (c) 
of this AD includes all MSNs for Model A320 airplanes, except for 
airplanes having certain modifications. We acknowledge that the 
referenced service information may not be adequate for certain airplane 
configurations. Therefore, we have revised paragraph (g) of this AD to 
provide an option for doing the modification, including identification 
of the appropriate modification kit, using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA Design Organization Approval (DOA).
    In addition, Airbus has informed us that Revision 1 of the 
referenced service information will expand the effectivity to include 
MSNs up to 8555. Airbus has also informed us that, upon request, it 
will issue a technical adaptation as an interim method of compliance 
until a revised service bulletin is issued.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD 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 correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-57-1208, dated 
November 21, 2016. This 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.

Costs of Compliance

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification (by oversizing and doing   125 work-hours x $85 per         $26,260         $36,885     $41,901,360
 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 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:

[[Page 22356]]

``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 to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that 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):

2018-09-09 Airbus: Amendment 39-19266; Docket No. FAA-2017-1245; 
Product Identifier 2017-NM-099-AD.

(a) Effective Date

    This AD is effective June 11, 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 
before further flight, 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; or 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.

[[Page 22357]]

[GRAPHIC] [TIFF OMITTED] TR15MY18.000

(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 EASA; or Airbus's EASA 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 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, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.

(k) 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) Airbus Service Bulletin A320-57-1208, dated November 21, 
2016.
    (ii) Reserved.
    (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.
    (4) 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.
    (5) You may view this service information 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 April 20, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. R1-2018-09280 Filed 5-14-18; 8:45 am]
 BILLING CODE 1301-00-P


