2017-21-02: Fuselage

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): 2017-21-02 Airbus: Amendment 39-19073; Docket No. FAA-2017-0480; Product Identifier 2016-NM-204-AD. (a) Effective Date This AD is effective November 27, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated in any category; except those on which Airbus Modification 5438 was embodied in production. (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Model A300 B4-605R and B4-622R airplanes. (3) Model A300 F4-605R and F4-622R airplanes. (4) Model A300 C4-605R Variant F airplanes. (5) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking in the door sill area of the aft cargo door. We are issuing this AD to detect and correct cracking of the door sill area of the aft cargo; such cracking could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Within the applicable compliance time specified in table 1 to paragraph (g) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the door sill area (including the sill beam flag, lock fitting, door sill web, and torsion door panel) of the aft cargo door lower torsion box area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 2016; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 15,100 flight cycles. [[Page 48912]] Table 1 to Paragraph (g) of This AD--Initial Inspection ------------------------------------------------------------------------ Airplane configuration Compliance time ------------------------------------------------------------------------ Repaired (date known), post-Airbus Before exceeding 25,800 Modification 10319 lock fittings installed flight cycles since the using Airbus Structural Repair Manual lock fitting replacement. (SRM) Task 51-72-00. Repaired (no record, date unknown), post- Before exceeding 25,800 Airbus Modification 10319 lock fittings flight cycles from installed using Airbus SRM Task 51-72-00. November 1, 1996. Non-repaired airplane, or airplane repaired No inspection required. with pre-Airbus Modification 10319 lock fittings using Airbus SRM Task 51-72-00. ------------------------------------------------------------------------ (h) Corrective Action If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 2016; as applicable; except, where Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin A310-53-2143, dated February 11, 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 (j)(2) of this AD. (i) Terminating Action Repair of a lock fitting as required by paragraph (h) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for the repaired fitting location only. All other post-Airbus Modification 10319 installed fittings are to be inspected as required by paragraph (g) 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 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 (k)(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: 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): 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 deviatedfrom 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 2016-0241, dated December 6, 2016, 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-2017-0480. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. (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 A300-53-6185, dated February 11, 2016. (ii) Airbus Service Bulletin A310-53-2143, dated February 11, 2016. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 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, 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.