AD 2023-23-11

This paragraph restates the requirements of paragraph (g) of AD 2019-12-07, with no changes. Within 41 months after June 29, 2007 (the effective date of AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25, 2007) (AD 2007-11-11)), replace all MLG shock absorbers equipped with MLG sliding tubes having serial numbers listed in Airbus All Operators Telex (AOT) A320-32A1273, Revision 01, dated May 6, 2004; or the Accomplishment Instructions of Airbus Service Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May 26, 2005; with new or serviceable MLG shock absorbers equipped with MLG sliding tubes having serial numbers not listed in Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004; or the Accomplishment Instructions of Airbus Service Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May-26, 2005; 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. As of June 29, 2007, only Airbus Service Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May 26, 2005, may be used to determine the affected MLG sliding tubes.

Note 1 to paragraph (g): Guidance on the replacement specified in paragraph (g) of this AD can be found in Airbus A318/A319/A320/A321 Aircraft Maintenance Manual Chapter 32-11-13, page block 401.

This paragraph restates the requirements of paragraph (h) of AD 2019-12-07, with no changes. Within three months after February 22, 2017 (the effective date of AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18, 2017) (AD 2017-01-11)): Do an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the MLG sliding tubes can be conclusively determined from that review.

This paragraph restates the requirements of paragraph (i) of AD 2019-12-07, with an updated reference. An airplane with an MSN not listed in figure 1 to paragraph (i) of this AD is not affected by the requirements of paragraph (j) of this AD, provided it can be determined that no MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD has been installed on that airplane since first flight of the airplane.

This paragraph restates the inspections required by paragraph (j) of AD 2019-12-07, with an updated reference. For each MLG sliding tube identified as required by paragraph (h) of this AD, having a part number and serial number listed in figure 2 to paragraph (i) of this AD: Within 3 months after February 22, 2017 (the effective date of AD 2017-01-11) inspect affected MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, and a Barkhausen noise inspection of the MLG sliding tube axles for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.

This paragraph restates the requirements of paragraph (k) of 2019-12-07, with no changes. If, during any inspection required by paragraph (j) of this AD, any damage is detected: Before further flight, replace the MLG sliding tube with a serviceable MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.

This paragraph restates the definition for serviceable MLG sliding tube specified in paragraph (l) of AD 2019-12-07, with updated references. For the purpose of paragraph (k) of this AD, a serviceable MLG sliding tube is defined as an MLG sliding tube that meets the criterion in either paragraph (l)(1) or (2) of this AD.

(1) An MLG sliding tube having a part number and serial number not listed in figure 2 to paragraph (i) of this AD.

(2) An MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD that has passed the inspections required by paragraph (j) of this AD.

This paragraph restates the parts installation prohibition specified in paragraph (m) of AD 2019-12-07, with updated references.

(1) For airplanes that have an MLG sliding tube installed that has a part number and serial number listed in figure 2 to paragraph (i) of this AD: After an airplane is returned to service following accomplishment of the actions required by paragraphs (h), (i), and (j) of this AD, no person may install on any airplane an MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD, unless that MLG sliding tube has passed the inspection required by paragraph (j) of this AD.

(2) For airplanes that, as of February 22, 2017 (the effective date of AD 2017-01-11), do not have an MLG sliding tube installed that has a part number and serial number listed in figure 2 to paragraph (i) of this AD: No person may install, on any airplane, an MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD unless that MLG sliding tube has passed the inspection required by paragraph (j) of this AD.

This paragraph restates the definitions specified in paragraph (n) of AD 2019-12-07, with new exception in paragraph (n)(2) of this AD. For the purpose of paragraphs (o), (p), (q), (r), and (s) of this AD, the following definitions apply.

(1) Affected MLG shock absorber: An MLG shock absorber having a part number and serial number as identified in Messier-Dowty Service Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model A318, A319, and A320 series airplanes; and Messier-Dowty Service Bulletin 201-32-43, Revision 3, dated October 3, 2008, for Model A321 series airplanes.

(2) Affected MLG sliding tube: An MLG sliding tube having a part number and serial number as identified in Appendix B of Safran Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for Model A318, A319, and A320 series airplanes, or Safran Service Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model A321 series airplanes; except parts identified in paragraphs (n)(2)(i) and (ii) of this AD and those parts that, after the inspection specified (n)(2)(i) or (ii) of this AD, have been repaired, using instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

Note 2 to the introductory text of paragraph (n)(2) of this AD: The affected MLG sliding tubes identified in paragraph (n)(2) of this AD are referred to as affected “Batch 1” MLG sliding tubes in EASA AD 2022-0204R1, dated February 15, 2023; corrected February 17, 2023.

(i) Parts that passed an inspection as specified in Safran Service Bulletin 200-32-321 or Safran Service Bulletin 201-32-68, as applicable.

(ii) Parts that have passed an inspection as specified in Safran component maintenance manual (CMM) task 32-11-33 (K0654), Revision 71, dated September 2020, or later; CMM task 32-12-25 (K0654), Revision 61, dated March 2020, or later; CMM task 32-12-12 (K0654), Revision 57, dated September 2020, or later; or CMM task 32-12-22 (K0654), Revision 56, dated March 2020, or later; as applicable.

(3) Serviceable MLG sliding tube: An MLG sliding tube that is not affected, or an affected MLG sliding tube, that has not exceeded 10,000 flight cycles since first installation on an airplane, or an affected MLG sliding tube that, within the last 5,000 flight cycles before installation on an airplane, passed an inspection specified in Airbus Service Bulletin A320-32-1441.

This paragraph restates the repetitive inspections required by paragraph (o) of AD 2019-12-07, with new service information and extended inspection interval. At the compliance time specified in figure 3 to paragraph (o) of this AD, and thereafter at intervals not to exceed 10,000 flight cycles: Do a detailed inspection of each affected MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017; or Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022. As of the effective date of this AD, only use Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022, for the actions required by this paragraph.

Note 3 to paragraph (o): If no reliable data regarding the number of flight cycles accumulated by the MLG sliding tube are available, operators may refer to the guidance specified in Chapter 5.2, “Traceability,” of Section 1, of Part 1 of the Airbus A318/A319/A320/A321 Airworthiness Limitations Section.

This paragraph restates the corrective actions required by paragraph (p) of AD 2019-12-07 for certain inspections required by paragraph (o) of this AD, with new service information. For airplanes on which any inspection required by paragraph (o) of this AD has been done before the effective date of this AD, comply with paragraph (p)(1) or (2) of this AD, as applicable. For airplanes on which any inspection required by paragraph (o) of this AD has been done on or after the effective date of this AD, comply with paragraph (y)(1) or (3) of this AD, as applicable.

(1) If any crack is detected on an MLG sliding tube, before further flight, replace that MLG sliding tube with a serviceable MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017; or Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022.

(2) Replacement of an MLG on an airplane with an MLG having a serviceable MLG sliding tube installed is an acceptable method to comply with the requirements of paragraph (p)(1) of this AD for that airplane.

This paragraph restates the parts replacement required by paragraph (q) of AD 2019-12-07, with new reference to new parts installation limitation.

(1) Within 10 years after August 1, 2019 (the effective date of AD 2019-12-07), replace each affected MLG sliding tube with an MLG sliding tube that is not affected. Installation of an MLG sliding tube that is not affected on an airplane constitutes terminating action for the repetitive inspections required by paragraph (o) of this AD for that airplane. As of the effective date of this AD, operators also must comply with the parts installation limitation specified in paragraph (aa) of this AD.

(2) Replacement of an MLG on an airplane with an MLG that does not have an affected MLG sliding tube installed is an acceptable method to comply with the requirements of paragraph (q)(1) of this AD for that airplane. As of the effective date of this AD, operators also must comply with the parts installation limitation specified in paragraph (aa) of this AD.

This paragraph restates the parts installation limitation specified in paragraph (r) of AD 2019-12-07, with a new exception to paragraph (r)(1) of this AD.

(1) As of August 1, 2019 (the effective date of AD 2019-12-07) and before the effective date of this AD, no person may install on any airplane an affected MLG shock absorber assembly containing a discrepant MLG sliding tube part number. As of the effective date of this AD, comply with the parts installation limitation specified in paragraph (aa)(1) of this AD.

(2) Do not install an affected MLG sliding tube on any airplane as specified in paragraph (r)(2)(i) or (ii) of this AD, as applicable.

(i) For an airplane with an affected MLG sliding tube installed as of August 1, 2019 (the effective date of AD 2019-12-07): After replacement of each affected MLG sliding tube as required by paragraph (q) of this AD.

(ii) For an airplane that does not have an affected MLG sliding tube installed as of August 1, 2019 (the effective date of AD 2019-12-07): As of August 1, 2019.

This paragraph restates the airplanes not affected provision specified in paragraph (s) of AD 2019-12-07, with no changes. An airplane on which Airbus Modification 161202 or Modification 161346 has been installed in production is not affected by the requirements of paragraphs (g), (h), (j), (o), and (q) of this AD, provided it has been verified that no affected MLG sliding tube is installed on that airplane.

This paragraph restates the credit for previous actions specified in paragraph (t) of AD 2019-12-07, with no changes.

(1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 29, 2007 (the effective date of AD 2007-11-11), using Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004. This document was incorporated by reference in AD 2004-11-13, Amendment 39-13659 (69 FR 31867, June 8, 2004).

(2) This paragraph provides credit for the initial inspection and applicable corrective actions required by paragraphs (o) and (p) of this AD if those actions were performed before August 1, 2019 (the effective date of AD 2019-12-07), using the Accomplishment Instructions in Airbus Service Bulletin A320-32-1441, dated December 28, 2016.

This paragraph restates the service information exception specified in paragraph (u) of AD 2019-12-07, with no changes. The service information specified in paragraph (g) of this AD has instructions to send any cracked part to Messier-Dowty. This AD does not include such a requirement.

This paragraph restates the no reporting requirement provision specified in paragraph (v) of AD 2019-12-07, with new service information. Although Airbus Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017; and Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022; specify to submit certain information to the manufacturer, and specify that action as “RC” (required for compliance), this AD does not include that requirement.

For the purpose of paragraphs (x), (y), (z), (aa), and (bb) of this AD, the following definitions apply.

(1) Affected MLG sliding tube: An MLG sliding tube having a part number identified in Safran Service Bulletin 200-32-321, Revision 4, dated November 3, 2021, for Model A318, A319, and A320 series airplanes, or Safran Service Bulletin 201-32-68, Revision 4, dated November 3, 2021, for Model A321 series airplanes; except those having a serial number identified in Appendix B of Safran Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for Model A318, A319, and A320 series airplanes, or Safran Service Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model A321 series airplanes; and except parts identified in paragraphs (w)(1)(i) and (ii) of this AD and those parts that, after the inspection specified (w)(1)(i) or (ii) of this AD, have been repaired, using instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

Note 4 to the introductory text of paragraph (w)(1) of this AD: The affected MLG sliding tubes identified in paragraph (w)(1) of this AD are referred to as affected “Batch 2” MLG sliding tubes in EASA AD 2022-0204R1, dated February 15, 2023; corrected February 17, 2023.

(i) Parts that passed an inspection as specified in Safran Service Bulletin 200-32-321 or Safran Service Bulletin 201-32-68, as applicable

(ii) Parts that have passed an inspection as specified in Safran CMM task 32-11-33 (K0654), Revision 71, dated September 2020, or later; CMM task 32-12-25 (K0654), Revision 61, dated March 2020, or later; CMM task 32-12-12 (K0654), Revision 57, dated September 2020, or later; or CMM task 32-12-22 (K0654), Revision 56, dated March 2020, or later; as applicable.

(2) Serviceable MLG sliding tube: Any MLG sliding tube other than those identified in paragraphs (w)(2)(i) thru (iii) of this AD.

(i) Any MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD.

(ii) Any affected MLG sliding tube identified in paragraph (n)(2) of this AD.

(iii) Any affected MLG sliding tube identified in paragraph (w)(1) of this AD.

At the compliance time specified in figure 4 to paragraph (x) of this AD, and thereafter at intervals not to exceed 10,000 flight cycles: Do a detailed inspection of each affected MLG sliding tube, as defined in paragraph (w)(1) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022.

Note 5 to paragraph (x): If no reliable data regarding the number of flight cycles accumulated by the MLG sliding tube are available, operators may refer to the guidance specified in Chapter 5.2, “Traceability,” of Section 1, of Part 1 of the Airbus A318/A319/A320/A321 Airworthiness Limitations Section.

(1) For airplanes on which any inspection required by paragraph (o) of this AD has been done on or after the effective date of this AD: If any crack is detected on an MLG sliding tube, before further flight, replace that MLG sliding tube with a serviceable MLG sliding tube, as defined in paragraph (w)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022.

(2) If, during any inspection required by paragraph (x) of this AD, any crack is detected on an MLG sliding tube: Before further flight, replace that MLG sliding tube with a serviceable MLG sliding tube, as defined in paragraph (w)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022.

(3) Replacement of an MLG on an airplane with an MLG having a serviceable MLG sliding tube, as defined in paragraph (w)(2) of this AD, installed is an acceptable method to comply with the requirements of paragraph (y)(1) or (2) of this AD for that airplane.

(1) Within 10 years after the effective date of this AD, replace each affected MLG sliding tube, as defined in paragraph (w)(1) of this AD, with a serviceable MLG sliding tube, as defined in paragraph (w)(2) of this AD. Replacement on an airplane of all affected MLG sliding tubes with serviceable MLG sliding tubes constitutes terminating action for the repetitive inspections required by paragraph (x) of this AD for that airplane.

(2) Replacement of an MLG on an airplane with an MLG that has a serviceable MLG sliding tube, as defined in paragraph (w)(2) of this AD, installed is an acceptable method to comply with the requirement of paragraph (z)(1) of this AD for that airplane.

(1) As of the effective date of this AD, no person may install on any airplane an MLG shock absorber assembly that contains any MLG sliding tube identified in paragraphs (aa)(i) through (iii) of this AD.

(i) Any MLG sliding tube having a part number and serial number listed in figure 2 to paragraph (i) of this AD.

(ii) Any affected MLG sliding tube identified in paragraph (n)(2) of this AD.

(iii) Any affected MLG sliding tube identified in paragraph (w)(1) of this AD.

(2) Do not install an affected MLG sliding tube identified in paragraph (w)(1) of this AD on any airplane as specified in paragraph (aa)(2)(i) or (ii) of this AD, as applicable.

(i) For an airplane with an affected MLG sliding tube installed as of the effective date of this AD: After replacement of each affected MLG sliding tube as required by paragraph (z) of this AD.

(ii) For an airplane that does not have an affected MLG sliding tube installed as of the effective date of this AD: As of the effective date of this AD.

An airplane on which Airbus Modification 161202 or Modification 161346 has been installed in production is not affected by the requirements for affected MLG sliding tubes in paragraph (x) of this AD and the requirement of paragraph (z) of this AD, provided it has been verified that no affected MLG sliding tube, as defined in paragraph (w)(2) of this AD, is installed on that airplane.

Although Airbus Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017; and Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022; specify to submit certain information to the manufacturer, and specify that action as “RC” (required for compliance), this AD does not include that requirement.

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the International Validation Branch, mail it to the address identified in paragraph (ee)(2) of this AD or email to: 9-AVS-AIR-730-AMOC@faa.gov. If mailing information, also submit information by email.

(i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.

(ii) AMOCs approved for AD 2019-12-07 are approved as AMOCs for the corresponding provisions of this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or the European Union Aviation Safety Agency (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 required by paragraphs (u), (v), and (dd)(2) 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.

(1) Refer to EASA AD 2022-0204R1, dated February 15, 2023; corrected February 17, 2023; for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA-2023-1645.

(2) For more information about this AD, contact Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 206-231-3667; email: Timothy.P.Dowling@faa.gov.

(3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (ff)(8) and (10) of this AD.

(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 January 23, 2024.

(i) Airbus Service Bulletin A320-32-1441, Revision 02, dated August 23, 2022.

(ii) Safran Service Bulletin 200-32-321, Revision 4, dated November 3, 2021.

(iii) Safran Service Bulletin 201-32-68, Revision 4, dated November 3, 2021.

(4) The following service information was approved for IBR on August 1, 2019 (84 FR 30579, June 27, 2019).

(i) Airbus Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.

(ii) Messier-Dowty Service Bulletin 200-32-286, Revision 3, dated October 3, 2008.

(iii) Messier-Dowty Service Bulletin 201-32-43, Revision 3, dated October 3, 2008.

(iv) Safran Service Bulletin 200-32-321, Revision 2, dated October 3, 2017.

(v) Safran Service Bulletin 201-32-68, Revision 2, dated October 3, 2017.

(5) The following service information was approved for IBR on February 22, 2017 (82 FR 5362, January 18, 2017).

(i) Airbus Service Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.

(ii) [Reserved]

(6) The following service information was approved for IBR on June 29, 2007 (72 FR 29241, May 25, 2007).

(i) Airbus Service Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May 26, 2005.

(ii) [Reserved]

(7) The following service information was approved for IBR on June 23, 2004 (69 FR 31867, June 8, 2004).

(i) Airbus All Operators Telex A320-32A1273, Revision 01, dated May 6, 2004.

(ii) [Reserved]

(8) For Airbus 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 account.airworth-eas@airbus.com; website airbus.com.

(9) For Safran and Messier-Dowty service information identified in this AD, contact Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone (859) 525-8583; fax (859) 485-8827; internet www.safran-landing-systems.com.

(10) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.

(11) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov.