2019-08-07: Fuselage

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: [[Page 23466]] 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) 2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014), and adding the following new AD: 2019-08-07 Airbus SAS: Amendment 39-19628; Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD. (a) Effective Date This AD is effective June 26, 2019. (b) Affected ADs This AD replaces AD 2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014) (``AD 2014-20-04''). (c) Applicability This AD applies to the Airbus SAS airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in anycategory, all manufacturer serial numbers. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We are issuing this AD to address cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014-20-04, with no changes. For Model A320-211 and -231 series airplanes, manufacturer serial numbers 003 through 092 inclusive: Prior to the accumulation of 12,000 total landings on the airplane, or within 300 days after January 10, 1994 (the effective date of AD 93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), whichever occurs later, modify the belly fairing structure, in accordance with the Accomplishment Instructions of an Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. As of November 7, 2014 (the effective date of AD 2014-20-04), use only the Airbus service bulletin specified in paragraph (g)(3) of this AD. (1) Airbus Industrie Service Bulletin A320-53-1014, dated June 25, 1992. (2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, dated May 26, 1993. (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated September 1, 1994. (h) Retained Repetitive Inspection, With Updated Service Information This paragraph restates the requirements of paragraph (h) of AD 2014-20-04, with updated service information. At the latest of the compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD: Do a detailed inspection for cracking of the four titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA-- Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (1) Before the accumulation of 30,000 total flight cycles or 60,000 total flight hours, whichever occurs first after first flight of the airplane. (2) Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after modification of the airplane as required by paragraph (g) of this AD, or after installation of new titanium angles, provided that, prior to installation, a rototest for cracking on the open holes has been accomplished with no crack findings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA-- Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (3) Within 3,000 flight cycles or 6,000 flight hours, whichever occurs first after November 7, 2014 (the effective date of AD 2014- 20-04). (i) Retained Post-Inspection Actions for No Crack Findings, With Updated Service Information This paragraph restates the requirements of paragraph (i) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is no crack finding: Accomplish the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Repeat the inspection required by paragraph (h) of this AD at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first. (2) Before further flight after the inspection required by paragraph (h) of this AD, remove all inspected titanium angles, accomplish a rototest for cracking on the open holes and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (j) Retained Post-Inspection Actions for Any Crack Findings, With Updated Service Information This paragraph restates the requirements of paragraph (j) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is any crack finding: Before further flight, remove the affected titanium angle(s), accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (k) Retained Post-Installation Repetitive Inspections,With Updated Service Information and Revised Compliance Language This paragraph restates the requirements of paragraph (k) of AD 2014-20-04, with updated service information and revised compliance language. For airplanes on which new titanium angles were installed as specified in paragraph (i)(2) or (j) of this AD: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after the installation, accomplish a detailed inspection for cracking of the replaced titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus [[Page 23467]] Service Bulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (l) Retained Post-Inspection Actions for Any Crack Findings During Post-Installation Inspections, With Updated Service Information This paragraph restates the requirements of paragraph (l) of AD 2014-20-04, with updated service information. If, during any inspection as required by paragraph (k) of this AD, there is any crack finding: Before further flight, remove the affected titanium angles, accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus ServiceBulletin A320-53-1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. (m) Retained Corrective Action for Rototest Crack Finding, With Updated Contact Information This paragraph restates the requirements of paragraph (m) of AD 2014-20-04, with updated contact information. If, during any rototest as required by paragraph (i), (j), or (l) of this AD, any crack is found: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or theEuropean Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (n) Retained No Termination Action for Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2014-20-04, with no changes. Repair or replacement of parts as specified in this AD does not terminate the repetitive inspections required by this AD. (o) New Requirement of This AD: Detailed Inspection for Certain Rivets For airplanes previously modified (replacement of affected titanium angles) using the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259: At the earlier of the times specified in paragraphs (o)(1) and (o)(2) of this AD, do a detailed inspection of the rivet installation in the belly fairing shear walls and the titanium angles for part number EN6081D4 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. A review of the airplane maintenance records is acceptable to comply with the requirements of this paragraph for that airplane, provided it can be determined that no titanium angles have been installed on that airplane in accordance with the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259, or if only rivets having part number EN6081D5 have been used to install the titanium angles on that airplane in accordance with the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/ 005/2018, Issue 1, dated February 08, 2018. (1) Within 2,000 flight cycles or 4,000 flight hours, whichever occurs first after the effective date of this AD. (2) Before exceeding5,000 flight cycles or 10,000 flight hours, whichever occurs first after accomplishment of the last inspection specified in paragraph (h) of this AD. (p) New Requirements of This AD: Replacement of Certain Rivets If any part number EN6081D4 series rivet is found during any inspection required by paragraph (o) of this AD, before further flight, do the actions specified in paragraphs (p)(1) and (p)(2) of this AD. (1) Remove the part number EN6081D4 series rivets and do a rotating probe test of the open holes for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017. If any crack is found during any inspection required by this paragraph, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. (2) Replace part number EN6081D4 series rivets with part number EN6081D5 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/ 005/2018, Issue 1, dated February 08, 2018. (q) Service Information Exception Where the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, specify to install titanium angle part numbers D5337060121200 and D5337060121400, this AD allows the installation of titanium angle part numbers D5337060121295 and D5337060121495, respectively. (r) 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 International Section, send it to the attention of the person identified in paragraph (s)(2) of this AD. Information may be emailed to: [email protected]. (i) 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. (ii) AMOCs approved previously for AD 2014-20-04, are approved as AMOCs for the corresponding provisions of this AD. (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 SAS's EASA 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. (s) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD2018-0091, dated April 20, 2018, 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-2018-0795. (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; phone and fax: 206-231-3223. (t) 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. [[Page 23468]] (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 26, 2019. (i) Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. (ii) Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 08, 2018. The date appears only on the last page of the document. (4) The following service information was approved for IBR on November 7, 2014 (79 FR 59636, October 3, 2014). (i) Airbus Service Bulletin A320-53-1014, Revision 2, dated September 1, 1994, including supplementary page 7A. Pages 1 through 3, 15, 19, 20, and 25 of this document are identified as Revision 2, dated September 1, 1994; pages 4 through 8, 10, 12, 16 through 18, and 21 through 24 are identified as Revision 1, dated May 26, 1993; and pages 9, 11, 13, 14, and 26 are identified as the original, dated June 25, 1992. (ii) [Reserved] (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. (6) You may view this service information atthe 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. (7) 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.