2018-25-08: 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) 2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017), and adding the following new AD: 2018-25-08 Airbus SAS: Amendment 39-19519; Docket No. FAA-2018-0641; Product Identifier 2018-NM-032-AD. (a) Effective Date This AD is effective February 1, 2019. (b) Affected ADs This AD replaces AD 2017-22-07, Amendment 39-19087 (82 FR 56158, November 28, 2017) (``AD 2017-22-07''). (c) Applicability This AD applies to Airbus SAS 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; manufacturer serial numbers through 0758 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame forks and outer skin on the forward and aft cargo compartment doors are subject to widespread fatigue damage (WFD), and a determination that a modification of the frame forks must be accomplished. We are issuing this AD to address cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Definition of Affected Door, With No Changes This paragraph restates the definition in paragraph (g) of AD 2017-22-07, with no changes. For the purpose of this AD, an ``affected door'' is a forward or aft cargo compartment door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied. [[Page 67052]] [GRAPHIC] [TIFF OMITTED] TR28DE18.008 (h) Retained Repetitive Special Detailed Inspection of Frame Forks, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2017-22-07, with no changes. At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02,dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review. (1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane. (2) Within 900 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), without exceeding 41,950 flight cycles since first installation of the door on an airplane. (3) Within 50 flight cycles after January 2, 2018 (the effective date of AD 2017-22-07), for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane. (4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320-52-1032. (i)Retained Corrective Actions, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2017-22-07, with no changes. If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (l) and (m) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections. (j) Terminating Modification for Repetitive Inspections Before the accumulation of 56,300 flight cycles, but not before the accumulation of 21,700 flight cycles since first installation of the affected door on an airplane: Modify all affected doors of an airplane, including accomplishment of all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018. Accomplishing this modification constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (k) Retained Optional Terminating Action, With Changes Related to Compliance This paragraph restates the requirements of paragraph (j) of AD 2017-22-07, with changes related to compliance. (1) Modification of all affected doors of an airplane before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997 (which is incorporated by reference in AD 2017-22-07 and is not incorporated in this AD), constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph(j) of this AD, for that airplane, provided that, after modification, no affected door is re- installed on that airplane. For airplanes not previously modified before the effective date of this AD, the modification required by paragraph (j) of this AD must be done. (2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions, if done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018, except as specified in paragraph (l) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re-installed on that airplane. For airplanes not previously modified before the effective date of this AD,the modification required by paragraph (j) of this AD must be done. (3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), if done before the effective date of this AD and done in accordance with 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 [[Page 67053]] (DOA); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD and a method of compliance for the modification required by paragraph (j) of this AD, for that airplane, provided that, after modification, no affected door is re- installed on that airplane. For airplanes not previously modified before the effective date of this AD, the modification required by paragraph (j) of this AD must be done. (l) Retained Exception to Service Information, With Updated Service Information This paragraph restates the requirements of paragraph (k) of AD 2017-22-07, with updated service information. Where Airbus Service Bulletin A320-52-1170, dated September 5, 2016; Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018; or Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017; 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 (q)(2) of this AD. (m) Retained Provision: No Reporting Requirement This paragraph restates the provision provided in paragraph (l) of AD 2017-22-07, with no changes. Although Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, specifies to submit certain information to the manufacturer, and specifies that action as ``RC,'' this AD does not include that requirement.(n) Retained Credit for Previous Actions This paragraph restates the provisions specified in paragraph (m) of AD 2017-22-07, with no changes. (1) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD. (2) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before January 2, 2018 (the effective date of AD 2017-22-07), using Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016. (o) New Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (j) and (k)(2) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1170, dated September 5, 2016. (2) This paragraph provides credit for the optional terminating modification specified in paragraph (k)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997. (p) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless less than 56,300 flight cycles have accumulated since first installation of the door on an airplane, and unless the door has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) of this AD. (q) 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 International Section, send it to the attention of the person identified in paragraph (r)(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 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): Except as specified in paragraphs (l) and (m) 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2018-0024, dated January 29, 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-2018-0641. (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 (s)(5) and (s)(6) of this AD. (s) 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 1, 2019. (i) Airbus Service Bulletin A320-52-1170, Revision 01, dated June 14, 2018. (ii) [Reserved] (4) The following service information was approved for IBR on January 2, 2018 (82 FR 56158, November 28, 2017). (i) Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017. (ii) [Reserved] (5) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 2 Rond Point Emile Dewoitine, 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.