2018-13-08: Wings

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 removing Airworthiness Directive (AD) 2016-01-11, Amendment 39-18370 (81 FR 3316, January 21, 2016), and adding the following new AD: 2018-13-08 Airbus: Amendment 39-19320; Docket No. FAA-2017-1102; Product Identifier 2017-NM-078-AD. (a) Effective Date This AD is effective August 22, 2018. (b) Affected ADs This AD replaces AD 2016-01-11, Amendment 39-18370 (81 FR 3316, January 21, 2016) (``AD 2016-01-11''). (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 A319 and A320 series airplanes on which Airbus Modification 160000 (structural reinforcement for sharklet installation) has been embodied in production. (2) Model A321 series airplanes on which Airbus Modification 160021 (structural reinforcement for sharklet installation) has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at frame (FR) 36. This AD was also prompted by a determination that, during further investigations of the frame as part of the widespread fatiguedamage (WFD) campaign, certain inspection compliance times have to be revised and new inspections and a new potential terminating action modification have to be introduced. We are issuing this AD to address fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Airplane Configurations For the purposes of this AD, airplane configurations are defined in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and figure 2 to paragraphs (g) and (i)(1) of this AD. [GRAPHIC] [TIFF OMITTED] TR18JY18.001 [[Page 33814]] [GRAPHIC] [TIFF OMITTED] TR18JY18.002 (h) Actions Required for Previously Inspected Airplanes For Configuration 001, 002, or 003 airplanes, as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD, on which the inspections specified in Airbus Service Bulletin A320-57- 1178, dated October 29, 2013, have been accomplished before the effective date of this AD; but the additional work specified in Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014, has not been accomplished before the effective date of this AD: Before accomplishing the initial inspection required by paragraph (i)(1) of this AD, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA) for further instructions and accomplish those instructions accordingly. (i) Repetitive Inspections (1) Within the compliance time defined in figure 3 to paragraph (i)(1) of this AD, as applicable to airplane configuration as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and figure 2 to paragraphs (g) and (i)(1) of this AD, accomplish aspecial detailed inspection (SDI) for cracking of the radius of the front spar vertical stringers and the horizontal floor beam and the fastener holes on FR 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1178, Revision 03, including only Appendix 03, both dated November 29, 2016. [[Page 33815]] [GRAPHIC] [TIFF OMITTED] TR18JY18.003 (2) If no cracking is found during any inspection required by paragraph (i)(1) of this AD, repeat the inspection required by paragraph (i)(1) of this AD thereafter at intervals not to exceed the inspection interval values defined in figure 4 to paragraphs (i)(2) and (l) of this AD, except as provided by paragraph (l) of this AD. [[Page 33816]] [GRAPHIC] [TIFF OMITTED] TR18JY18.004 (j) Modification For A320 series airplanes, Configuration 001, 002, or 003 as identified in figure 1 to paragraphs (g), (h), (i)(1), and (j) of this AD: Within the compliance time defined in figure 5 to paragraph (j) of this AD, as applicable, modify the center wing box area, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1200, dated November 20, 2015, except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight. [GRAPHIC] [TIFF OMITTED] TR18JY18.005 (k) Corrective Action If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Where Airbus Service Bulletin A320-57-1178, Revision 03, including only Appendix 03, both dated November 29, 2016; and Airbus Service Bulletin A320-57-1200, dated November 20, 2015; specify to contact Airbus for appropriate action, and specify that action as ``RC'' (Required for Compliance), accomplish corrective actions in accordance with this paragraph. (l) Previous Repairs For airplanes that have been repaired in the inspection area specified in paragraph (i)(1) of this AD before the effective date of this AD using a method approved by the [[Page 33817]] Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA: Accomplish repetitive SDIs within the compliance time defined in those repair instructions for repetitive SDIs. If no compliance time is identified in the repair instructions for repetitive SDIs, accomplish the repetitive SDIs required by paragraph (i)(2) of this AD at the compliance times defined in figure 4 to paragraphs (i)(2) and (l) of this AD. (m) No Terminating Action Modification or repair of an airplane, as specified in paragraph (j) or (k) of this AD, does not constitute terminating action for the repetitive inspections required by this AD, unless it is specified otherwise in a repair method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Reporting Requirement Submit a report of the positive findings of the inspections required by paragraphs (i) and (j) of this AD to ``Airbus Service Bulletin Reporting Online Application'' on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Report within 30 days after that inspection. (2) If the inspection was done before the effective date of this AD: Report within 30 days after the effective date of this AD. (o) Other FAA AD Provisions (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 manager of the International Section, send it to the attention of the person identified in paragraph (p)(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 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 specified in paragraph (k) 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. (4) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 work-hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0099, dated June 8, 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-2017-1102. (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. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) 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 A320-57-1178, Revision 03, including only Appendix 03, both dated November 29, 2016. (ii) Airbus Service Bulletin A320-57-1200, dated November 20, 2015. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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.