2018-23-11: Landing gear

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): 2018-23-11 Airbus SAS: Amendment 39-19497; Docket No. FAA-2018-0297; Product Identifier 2017-NM-181-AD. (a) Effective Date This AD is effective December 19, 2018. (b) Affected ADs This AD affects AD 2001-15-10, Amendment 39-12344 (66 FR 39413, July 31, 2001) (``AD 2001-15-10''), and AD 2016-06-13, Amendment 39- 18444 (81 FR 17365, March 29, 2016) (``AD 2016-06-13''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 26925 has been embodied in production, which introduces a modified alternate braking system that removes the brake dual distribution valve (BDDV). (1) Airbus SAS Model A319-111, -112, -113, -114, -115, -131, - 132, and -133 airplanes. (2) Airbus SAS Model A320-211, -212, -214, -231, -232, and -233 airplanes. (3) Airbus SAS Model A321-111, -112, -131,-211,-212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. We are issuing this AD to prevent water ingestion in the BDDV, freezing of the BDDV in flight, and consequent loss of braking system function after landing. These conditions could possibly result in damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Identification and Modification or Replacement Within 3 months after the effective date of this AD, identify the BDDV part number installed on the airplane. For each affected BDDV part number specified in figure 1 to paragraphs (g) and (h) of this AD, within 3 months after the effective date of this AD, do the actions in paragraph (g)(1), (g)(2), or (g)(3) of this AD. A review of airplane maintenance records is acceptable to identify the BDDV part number if the part number of the BDDV can be conclusively determined from that review. [[Page 56708]] [GRAPHIC] [TIFF OMITTED] TR14NO18.001 (1) Modify and re-identify the affected BDDV, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32- 1203, Revision 02, dated February 9, 2001. (2) Modify and re-identify the affected BDDV, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1415, Revision 02, dated December 10, 2015. Do all applicable related investigative and corrective actions before further flight. (3) Replace the affected BDDV with a BDDV having a part number not specified in figure 1 to paragraphs (g) and (h) of this AD, or replace the old part number with a new part number as specified in figure 2 to paragraphs (g)(3) and (h)(2) of this AD. Do the replacement 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. [GRAPHIC] [TIFF OMITTED] TR14NO18.002 (h) Parts Installation Prohibition As of the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, no person may install a BDDV having a part number specified in figure 1 to paragraphs (g) and (h) of this AD, on any airplane. (1) For any airplane that, on the effective date of this AD, has a BDDV installed with a part number specified in figure 1 to paragraphs (g) and (h) of this AD: After modification or replacement of the BDDV, as required by paragraph (g) of this AD. (2) For any airplane that, on the effective date of this AD, has a BDDV installed or replaced with a part number specified as `new P/ N' in figure 2 to paragraphs (g)(3) and (h)(2) of this AD, or has a BDDV installed or replaced with a part number not specified in figure 1 to paragraphs (g) and (h) of this AD: As of the effective date of this AD. (i) Terminating Action for Other ADs (1) Doing the actions in paragraph (g) of this AD terminates the requirements in paragraphs (e) and (f) of AD 2001-15-10 for Model A319, A320 and A321 series airplanes. (2) Doing the actions in paragraph (g) of this AD terminates all of the requirements of AD 2016-06-13. (j)Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraphs (j)(1)(i) or (j)(1)(ii) of this AD. (i) Airbus Service Bulletin A320-32-1203, dated June 4, 1999, which was incorporated by reference in AD 2001-15-10. (ii) Airbus Service Bulletin A320-32-1203, Revision 01, dated October 12, 2000. (2) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the service information in paragraphs (j)(2)(i) or (j)(2)(ii) of this AD. (i) Airbus Service Bulletin A320-32-1415, dated September 2, 2014, which was incorporated by reference in AD 2016-06-13. (ii) Airbus Service Bulletin A320-32-1415, Revision 01, dated April 23, 2015. (k) 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 (l)(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): 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 [[Page 56709]] 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0119, dated July 11, 2017, forrelated 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-2018-0297. (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 (m)(3) and (m)(4) of this AD. (m) 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 A320-32-1203, Revision 02, dated February 9, 2001.(ii) Airbus Service Bulletin A320-32-1415, Revision 02, dated December 10, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EIAS, 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. (4) 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. (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.