2016-01-11: 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) 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998), and adding the following new AD: 2016-01-11 Airbus: Amendment 39-18370. Docket No. FAA-2015-1422; Directorate Identifier 2014-NM-125-AD. [[Page 3318]] (a) Effective Date This AD becomes effective February 25, 2016. (b) Affected ADs This AD replaces AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998). (c) Applicability This AD applies to Airbus Model A320-211, -212, and -231 airplanes, certificated in any category, manufacturer serial numbers (MSN) 0001 through 0155 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by cracks found on the front vertical stringer at frame 36. This AD was also prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections Within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and do a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD. (1) For Configuration 1 airplanes identified in paragraph (h)(1) of this AD: At intervals not to exceed 8,800 flight cycles or 17,700 flight hours, whichever occurs first. (2) For Configuration 2, 3, and 4 airplanes identified in paragraphs (h)(2) through (h)(4) of this AD: At intervals not to exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs first. (h) Compliance Times for Initial Inspections Required by Paragraph (g) of This AD Do the initial inspections required by paragraph (g) of this AD within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD. (1) For Configuration 1 airplanes, having MSNs 0001 through MSN 0079 inclusive, on which the modification specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, has not been accomplished: Inspect at the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD. (i) Inspect at the later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD. (A) Prior to the accumulation of 24,000 flight cycles or 48,000 flight hours, whichever occurs first since airplane first flight. (B) Within 60 days after the effective date of this AD. (ii) Inspect within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished. (iii) Inspect within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD, without exceeding 14,000 flight cycles after the last inspection specified in Airbus Service Bulletin A320-57-1016 was accomplished. (2) For Configuration 2 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have not been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated December 6, 1995, was accomplished. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (3) For Configuration 3 airplanes, having MSNs 0001 through 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320-57-1016, have been done prior to accomplishing the actions specified by Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997: Inspect at the later of the times specified by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Within 24,900 flight cycles or 49,800 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320-57-1017, dated September 3, 1991; or Airbus Service Bulletin A320-57-1017, Revision 01, dated March 17, 1997, was accomplished. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (4) For Configuration 4 airplanes, having MSNs 0080 through 0155 inclusive: Inspect at the later of the times specified inparagraphs (h)(4)(i) or (h)(4)(ii) of this AD. (i) Prior to the accumulation of 54,300 flight cycles or 108,600 flight hours, whichever occurs first since airplane first flight. (ii) Within 60 days after the effective date of this AD. (i) Repair If any crack is detected during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. 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. The AMOC approval letter must specifically reference 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0069, dated March 19, 2014, 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-2015-1422. (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. (3) The following service information was approved for IBR on February 25, 2016. (i) Airbus Service Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including Appendix 01, dated May 28, 2014. (ii) Reserved. (4) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice [[Page 3319]] 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. (5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (6) 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.