AD 2017-25-01

[Federal Register Volume 82, Number 232 (Tuesday, December 5, 2017)]
[Rules and Regulations]
[Pages 57340-57343]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-26037]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0709; Product Identifier 2016-NM-200-AD; Amendment 
39-19115; AD 2017-25-01]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 Model A318 series airplanes; Model A319 series airplanes; and 
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. This 
AD was prompted by a report indicating that the lower rib foot angle of 
the center wing box did not match with the bottom skin panel inner 
surface. This AD requires repetitive inspections for cracking of the 
external bottom skin in certain areas on the left and right wings, and 
corrective actions if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective January 9, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 9, 
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 <a href="/cdn-cgi/l/email-protection#345557575b415a401a555d46435b46405c1951554774555d465641471a575b59"><span class="__cf_email__" data-cfemail="1f7e7c7c706a716b317e766d68706d6b77327a7e6c5f7e766d7d6a6c317c7072">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. You may view this referenced 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. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0709.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0709; 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, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

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 
and A319 series airplanes; and Model A320-211, -212, -214, -216, -231, 
-232, and -233 airplanes. The NPRM published in the Federal Register on 
July 25, 2017 (82 FR 34453) (``the NPRM''). The NPRM was prompted by a 
report indicating that the lower rib foot angle of the center wing box 
did not match with the bottom skin panel inner surface. The NPRM 
proposed to require repetitive inspections for cracking of the external 
bottom skin in certain areas on the left and right wings, and 
corrective actions if necessary, and provided an optional terminating 
modification for the repetitive inspections. We are issuing this AD to 
detect and correct cracking of the external bottom skin in the area of 
the rib 2 attachment 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 
2016-0222, dated November 7, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A318 and A319 
series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and 
-233 airplanes. The MCAI states:

    During installation in production of new wing box ribs on post-
mod 39729 aeroplanes, it was discovered that the centre wing lower 
rib foot angle was not matching with the bottom skin panel inner 
surface.
    This condition, if not detected and corrected, could induce 
fatigue cracking of the skin panel at the rib foot attachment, with 
possible detrimental effect on wing structural integrity.
    This condition was initially addressed by Airbus on the 
production line through adaptation mod 152155, then through mod 
152200. For affected aeroplanes in service, Airbus issued Service 
Bulletin (SB) A320-57-1205, providing instructions for repetitive 
detailed inspections (DET) or special detailed inspections (SDI), 
and SB A320-57-1207, providing modification instructions.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections (DET or SDI) of the wing bottom skin lower 
surface for crack detection and, depending on findings, the 
accomplishment of applicable corrective action(s). This [EASA] AD 
also includes reference to an optional modification (Airbus SB A320-
57-1207), providing terminating action for the repetitive 
inspections required by this [EASA] AD.

    The corrective action for cracking is to repair using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; EASA; or Airbus's EASA Design Organization Approval. You 
may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0709.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response.

Request To Include Technical Adaptations

    Delta Airlines asked for another ``Contacting the Manufacturer'' 
subparagraph acknowledging Technical Adaptations from Airbus to be 
added under paragraph (j) of the proposed AD, ``Other FAA AD 
Provisions.'' Delta observed that the FAA provision for contacting the 
manufacturer in paragraph (j) of the proposed AD would provide 
allowances for corrective actions without alternative methods of 
compliance (AMOCs). Delta noted that operators often receive Technical 
Adaptations that include an EASA Design Organization Approval (DOA)

[[Page 57341]]

authorized signature for typographical, omitted instruction, and 
technical errors, and that they should be included in the proposed AD.
    We disagree with the commenter. The ``Contacting the Manufacturer'' 
paragraph in ADs only addresses the requirement to contact the 
manufacturer for corrective actions for the identified unsafe condition 
and does not cover deviations from other AD requirements. This 
paragraph states, in part, that for any requirement in an AD to obtain 
corrective actions from a manufacturer, the actions must be 
accomplished using a method approved by the FAA; or the EASA; or 
Airbus's EASA DOA. We do not agree to extend this allowance to other AD 
requirements. All deviations from the service information sections that 
are marked ``RC'' (Required for Compliance) require AMOC approval 
unless otherwise stated in the AD. We have not changed this AD in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comment 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:

    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 Service Bulletin A320-57-1205, dated May 26, 
2016. This service information describes procedures for inspecting the 
external bottom skin for cracking in the area of the rib 2 attachment 
between stringer 8 and stringer 11 on both wings, and repairing any 
cracks.
    Airbus has also issued Service Bulletin A320-57-1207, including 
Appendix 01 and Appendix 02, dated May 26, 2016. This service 
information describes procedures for inspecting the lower rib feet (rib 
2) and the bottom skin upper surface on both wings for cracking, 
modifying the wings by installing shims between the lower rib foot (rib 
2) and the bottom skin upper surface, and repairing any cracks.
    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 10 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per  product         operators
----------------------------------------------------------------------------------------------------------------
Inspection....................  5 work-hours x $85                $0  $425 per inspection   $4,250 per
                                 per hour = $425 per                   cycle.                inspection cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification...............................  32 work-hours x $85 per hour =               $5,750          $8,470
                                              $2,720.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.
    According to the manufacturer, some of the costs of the optional 
modification of this AD may be covered under warranty, thereby reducing 
the cost impact on affected individuals. We do not control warranty 
coverage for affected individuals. As a result, we have included all 
available costs in our cost estimate.

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 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.

[[Page 57342]]

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):

2017-25-01 Airbus: Amendment 39-19115; Docket No. FAA-2017-0709; 
Product Identifier 2016-NM-200-AD.

(a) Effective Date

    This AD is effective January 9, 2018.

(b) Affected ADs

    None.

 (c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers on which Airbus Modification 39729 
was embodied in production, except those airplanes on which Airbus 
Modification 152155 or Modification 152200 was embodied in 
production.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.

 (d) Subject

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

 (e) Reason

    This AD was prompted by a report indicating that the lower rib 
foot angle of the center wing box did not match with the bottom skin 
panel inner surface. Misalignment of the lower rib foot angle of the 
center wing box with the bottom skin panel inner surface could 
induce fatigue cracking of the skin panel at the rib foot 
attachment. We are issuing this AD to detect and correct cracking of 
the external bottom skin in the area of the rib 2 attachment 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) Repetitive Inspections

    Before exceeding the applicable compliance time specified in 
table 1 to paragraph (g) of this AD, or within 3 months after the 
effective date of this AD, whichever occurs later: Do a detailed 
inspection or a special detailed inspection for cracking of the 
external bottom skin in the area of the rib 2 attachment between 
stringer 8 and stringer 11 of the left and right wings, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1205, dated May 26, 
2016. Do all applicable corrective actions before further flight. 
Repeat the inspection thereafter at the applicable intervals, based 
on the method used for the most recent inspection, as specified in 
table 2 to paragraph (g) of this AD.

      Table 1 to Paragraph (g) of This AD--Initial Inspection Times
------------------------------------------------------------------------
                                                   Compliance time--
                                                 whichever occurs first
       Airplane model and configuration        since first flight of the
                                                        airplane
------------------------------------------------------------------------
Model A318 series airplanes; Model A319        Before the accumulation
 series airplanes; and Model A320-211, -212, -  of 14,500 total flight
 214, -216, -231, -232, and -233 airplanes;     cycles or 29,000 total
 pre-Airbus Modification 155374; not used as    flight hours.
 VIP or Elite.
Model A318 series airplanes; Model A319        Before the accumulation
 series airplanes; and Model A320-211, -212, -  of 13,600 total flight
 214, -216, -231, -232, and -233 airplanes;     cycles or 27,300 total
 post-Airbus Modification 155374; not used as   flight hours.
 VIP or Elite.
Model A319 series airplanes; post-Airbus       Before the accumulation
 Modifications 28162, 28238, and 28342; used    of 7,400 total flight
 as VIP or CJ.                                  cycles or 32,000 total
                                                flight hours.
Model A318 series airplanes; post-Airbus       Before the accumulation
 Modification 39195; used as VIP or Elite.      of 14,500 total flight
                                                cycles or 43,500 total
                                                flight hours.
------------------------------------------------------------------------


  Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                       Detailed        Special detailed
                                     inspection--        inspection--
Airplane model and configuration   whichever occurs    whichever occurs
                                         first               first
------------------------------------------------------------------------
Model A318 series airplanes;      4,000 flight        5,000 flight
 Model A319 series airplanes;      cycles or 8,000     cycles or 10,000
 and Model A320-211, -212, -214,   flight hours.       flight hours.
 -216, -231, -232, and -233
 airplanes; not used as VIP or
 Elite.
Model A319 series airplanes;      2,000 flight        2,500 flight
 post-Airbus Modifications         cycles or 8,600     cycles or 11,000
 28162, 28238 and 28342; used as   flight hours.       flight hours.
 VIP or CJ.
Model A318 series airplanes;      4,000 flight        5,000 flight
 post-Airbus Modification 39195;   cycles or 12,000    cycles or 15,000
 used as VIP or Elite.             flight hours.       flight hours.
------------------------------------------------------------------------

    Note 1 to paragraph (g) of this AD: Airbus Modification 155374 
defines the minimum airplane configuration for operation on 
Commonwealth of Independent States runway profiles.

 (h) Terminating Action Limitation

    Repair of an airplane, as required by paragraph (g) of this AD, 
does not constitute terminating action for the repetitive 
inspections required by paragraph (g) of this AD unless otherwise 
specified in the instructions obtained using the procedures 
specified in paragraph (j)(2) of this AD.

 (i) Optional Terminating Action

    Modification of the wings including a detailed inspection of the 
lower rib feet (rib 2) and bottom skin upper surface of the wings 
for cracking and all applicable corrective actions, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-57-1207, including Appendix 01 and Appendix 02, dated May 26, 
2016, constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD for that airplane. If, during 
modification of an airplane as specified in this paragraph, 
accomplishment of any modification instruction is not possible due 
to configuration difficulties, accomplish the modification using the 
procedures specified in paragraph (j)(1) of this AD.

 (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

[[Page 57343]]

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 manager of the International 
Branch, send it to the attention of the person identified in 
paragraph (k)(2) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#c6ffeb87888bebf7f7f0eb878b8985eb948397938395929586a0a7a7e8a1a9b0"><span class="__cf_email__" data-cfemail="7e47533f3033534f4f48533f33313d532c3b2f2b3b2d2a2d3e181f1f50191108">[email&#160;protected]</span></a>. 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 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): 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.

 (k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0222, dated November 7, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket 
No. FAA-2017-0709.
    (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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(4) of this AD.

 (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) Airbus Service Bulletin A320-57-1205, dated May 26, 2016.
    (ii) Airbus Service Bulletin A320-57-1207, including Appendix 01 
and Appendix 02, dated May 26, 2016.
    (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 <a href="/cdn-cgi/l/email-protection#e28381818d978c96cc838b90958d90968acf878391a2838b90809791cc818d8f"><span class="__cf_email__" data-cfemail="b6d7d5d5d9c3d8c298d7dfc4c1d9c4c2de9bd3d7c5f6d7dfc4d4c3c598d5d9db">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) 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.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26037 Filed 12-4-17; 8:45 am]
 BILLING CODE 4910-13-P