2019-16-11: Doors

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) 2018-20-06, Amendment 39-19440 (83 FR 49265, October 1, 2018), and adding the following new AD: 2019-16-11 Airbus SAS: Amendment 39-19714; Docket No. FAA-2019-0257; Product Identifier 2018-NM-175-AD. (a) Effective Date This AD is effective October 2, 2019. (b) Affected ADs This AD replaces 2018-20-06, Amendment 39-19440 (83 FR 49265, October 1, 2018) (``AD 2018-20-06''). (c) Applicability This AD applies to Airbus SAS Model A300 F4-605R and F4-622R airplanes, certificated in any category, on which Airbus modification 12046 has been embodiedin production. Modification 12046 has been embodied in production on manufacturer serial numbers (MSNs) 0805 and above, except MSNs 0836, 0837, and 0838. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of two adjacent frame forks that were found cracked on the aft lower deck cargo door (LDCD) of two airplanes during scheduled maintenance, and a determination that certain compliance times need to be revised. The FAA is issuing this AD to address cracked or ruptured aft LDCD frames, which could allow loads to be transferred to the remaining structural elements. This condition could lead to the rupture of one or more vertical aft LDCD frames, which could result in reduced structural integrity of the aft LDCD. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) New Affected Part Definition For the purposes of this AD, an affected part is a frame fork having a part number identified in figure 1 to paragraph (g) of this AD. [GRAPHIC] [TIFF OMITTED] TR28AU19.000 (h) Retained Inspection Requirements and On-Condition Actions, With Revised Compliance Language This paragraph restates the requirements of paragraph (g) of AD 2018-20-06, with revised compliance language. At the applicable time specified in paragraph (i) of this AD, or before exceeding the threshold defined in figure 2 to paragraph (h) of this AD, whichever occurs later: Do the actions specified in paragraphs (h)(1) through (3) of this AD. Repeat the high frequency eddy current (HFEC) inspection specified in paragraph (h)(3) of this AD at all LDCD frame fork stations having affected parts thereafter at intervals not to exceed the applicable times specified in figure 2 to paragraph (h) of this AD. (1) A one-time check of the aft LDCD clearances ``U'' and ``V'' between the latching hooks and the eccentric bush at frame (FR) 60 through FR64A, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300- 52-6086, Revision 01, dated May 29, 2018. If any value outside tolerance is found, adjust the latching hook before further flight, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018. (2) A one-time detailed inspection to detect signs of wear of the hooks, eccentric bushes, and x-stops, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015. If any wear is found, do all applicable corrective actions before further flight, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015. (3) An HFEC inspection to detect cracking at all frame fork stations of the aft LDCD, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018. If any crack is found, before further flight, replace the cracked frame fork, in accordance with the instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; repair the cracked frame fork, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018; or modify (reinforce) the cracked frame fork, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 2018; except as required by paragraph (j) of this AD. [[Page 45064]] [GRAPHIC] [TIFF OMITTED] TR28AU19.001 (i) Retained Compliance Times, With No Changes At the later of the times specified in paragraphs (i)(1) and (2) of this AD, do the actions required by paragraph (h) of this AD. (1) Before the accumulation of 4,500 total flight cycles. (2) At the applicable time specified by paragraph (i)(2)(i) or (ii) of this AD. (i) For airplanes that have accumulated 8,000 or more total flight cycles as of January 26, 2017 (the effective date of AD 2016- 25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016) (``AD 2016-25-03'')): Within 100 flight cycles after January 26, 2017. (ii) For airplanes that have accumulated fewer than 8,000 total flight cycles as of January 26, 2017 (the effective date of AD 2016- 25-03): Within 400 flight cycles after January 26, 2017. (j) Service Information Exception Where Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 2018, specifies to contact Airbus for appropriate action: Before further flight, accomplishcorrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD. (k) No Terminating Action Accomplishment of corrective actions on an airplane as required by paragraph (h)(1) or (2) of this AD; or repair, modification, or replacement of a frame fork as required by paragraph (h)(3) of this AD, on the aft LDCD of an airplane; does not constitute terminating action for the repetitive HFEC [[Page 45065]] inspections required by paragraph (h)(3) of this AD for that airplane. (l) No Reporting Although the Accomplishment Instructions of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015; and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018; specify to submit certain information to the manufacturer, this AD does not include that requirement. (m) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (h)(1) and (3) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-52-6086, Revision 00, dated December 25, 2016. (2) This paragraph provides credit for actions required by paragraph (h)(3) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-52- 6085, Revision 00, dated December 22, 2016. (n) 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 (o)(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 2018-20-06 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 the European 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018-0266, dated December 11, 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-2019-0257. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (6) of this AD. (p) 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 November 5, 2018 (83 FR 49265, October 1, 2018). (i) Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2, 2018. (ii) Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29, 2018. (4) The following service information was approved for IBR on January 26, 2017 (81 FR 93801, December 22, 2016). (i) Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015, including the following appendices: (A) Appendix 1--Flowchart, undated. (B) Appendix 2--Reporting Sheet, undated. (None of the pages of Appendix 2 are numbered.) (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/ L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is identified with an appendix number only on page 1 of Airbus Alert Operators Transmission A52W011-15, Revision 00, dated July 23, 2015.) (D) Appendix 4--P/N identification for frame forks and bushings, undated. (ii) [Reserved] (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 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. (6) 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. (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.