Airworthiness Directive · Amendment 39-19580 · Doors
Airbus SAS Airplanes
This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Model A318-111, A318-112, A318-121, and A318-122 airplanes.
(2) Model A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, and A319-133 airplanes.
(3) Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes.
(4) Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes.
We are superseding Airworthiness Directive (AD) 2016-07-23, which applied to all Airbus SAS Model A318 and A319 series airplanes; Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes. AD 2016-07-23 required, for certain airplanes, repetitive replacements of the fixed fairing upper and lower attachment studs of both the left-hand (LH) and right-hand (RH) main landing gear (MLG); and repetitive inspections for corrosion, wear, fatigue cracking, and loose studs of each forward stud assembly of the fixed fairing door upper and lower forward attachments of both the LH and RH MLG; and replacement if necessary. AD 2016-07-23 also provided an optional terminating modification for the repetitive replacements of the fixed fairing upper and lower attachment studs. This AD retains the requirements of AD 2016-07-23 and, for certain airplanes, requires re-identification of the LH and RH MLG fixed fairing assemblies' part numbers. This AD was prompted by a determination that for some airplane configurations, associated fixed fairing assembly part numbers susceptible to fatigue cracking were not listed in certain service information required by AD 2016-07-23. In addition, we have determined that additional work is necessary to re- identify the fixed fairing assembly part number on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2016-07-23, with no changes. For airplanes in pre-Airbus Modification 27716 and pre-Airbus Service Bulletin A320-52-1100 configuration, with any of the components installed that are identified in paragraphs (g)(1) through (g)(5) of this AD: At the applicable compliance time specified in paragraph (h) of this AD, replace fixed fairing upper and lower attachment studs of both left-hand (LH) and right-hand (RH) MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. Repeat the replacements thereafter at intervals not to exceed 6,500 flight cycles.
(1) Plate—support having part number (P/N) D5284024820000.
(2) Plate—support having P/N D5284024820200.
(3) Stud—adjustment having P/N D5284024420000.
(4) Rod end assembly (lower) having P/N D5284000500000.
(5) Rod end assembly (upper) having P/N D5284000600000.
This paragraph restates the requirements of paragraph (h) of AD 2016-07-23, with no changes. For airplanes identified in paragraph (g) of this AD, except as provided by paragraph (o) of this AD: Do the initial replacement required by paragraph (g) of this AD at the latest of the times specified in paragraphs (h)(1) through (h)(4) of this AD.
(1) Before the accumulation of 6,500 total flight cycles since the airplane's first flight.
(2) Within 6,500 flight cycles since the last installation of a pre-Airbus Modification 27716 stud on the airplane.
(3) Within 1,500 flight cycles after June 6, 2016 (the effective date of AD 2016-07-23).
(4) Within 8 months after June 6, 2016 (the effective date of AD 2016-07-23).
This paragraph restates the requirements of paragraph (i) of AD 2016-07-23, with no changes. For airplanes in post-Airbus Modification 27716 or post-Airbus Service Bulletin A320-52-1100 configuration, with any of the components installed that are identified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD: At the applicable compliance time specified in paragraph (j) of this AD, do a detailed inspection of the LH and RH MLG forward stud assemblies of the fixed fairing door upper and lower forward attachments of both LH and RH MLG for indications of corrosion, wear, fatigue cracking, and loose studs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015. Repeat the detailed inspection thereafter at intervals not to exceed 12 months. Replacement of both LH and RH MLG forward stud assemblies on an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015, extends the interval for the next detailed inspection to 72 months; and the inspection must be repeated thereafter at intervals not to exceed 12 months.
(1) Stud—adjustment having P/N D5285600720000.
(2) Rod end assembly (lower) having P/N D5285600400000.
(3) Rod end assembly (upper) having P/N D5285600500000.
This paragraph restates the requirements of paragraph (j) of AD 2016-07-23, with no changes. For airplanes identified in paragraph (i) of this AD, except as provided by paragraph (o) of this AD: Do the initial inspection required by paragraph (i) of this AD at the latest of the times specified in paragraphs (j)(1) through (j)(4) of this AD.
(1) Before the accumulation of 72 months since the airplane's first flight.
(2) Within 72 months since the last installation of a post-Airbus Modification 27716 assembly or since accomplishment of the actions specified in Airbus Service Bulletin A320-52-1100.
(3) Within 1,500 flight cycles after June 6, 2016 (the effective date of AD 2016-07-23).
(4) Within 8 months after June 6, 2016 (the effective date of AD 2016-07-23).
This paragraph restates the requirements of paragraph (k) of AD 2016-07-23, with revised service information. If any discrepancy (including any indication of corrosion, wear, fatigue cracking, or loose studs) of any MLG forward stud assembly is found during any inspection required by paragraph (i) of this AD, except as specified in paragraph (l) of this AD: Before further flight, replace the discrepant upper and lower fixed fairing forward stud assemblies of the LH and RH MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used.
This paragraph restates the requirements of paragraph (l) of AD 2016-07-23, with revised service information. If any corrosion is found during any inspection required by paragraph (i) of this AD on any MLG fixed fairing forward stud assembly (upper, lower, LH or RH), but the corroded stud is not loose: Do the action specified in paragraph (l)(1) or (l)(2) of this AD.
(1) Before further flight, replace the affected assembly, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used.
(2) Within 4 months after finding corrosion, and thereafter at intervals not to exceed 4 months, do a detailed inspection for indications of corrosion, wear, fatigue cracking, and loose studs of the forward stud assembly of the affected (LH or RH) MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015.
This paragraph restates the requirements of paragraph (m) of AD 2016-07-23, with revised service information. If any indication of wear, fatigue cracking, or loose studs of any forward stud assembly is found during any inspection required by paragraph (l)(2) of this AD: Before further flight, replace the affected (LH or RH) MLG fixed fairing forward stud assembly, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017. As of the effective date of this AD only Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used.
This paragraph restates the requirements of paragraph (n) of AD 2016-07-23, with revised service information.
(1) Replacement of parts on an airplane, as required by paragraph (g), (k), (l)(1), or (m) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (i) of this AD, except as specified in paragraph (n)(3) of this AD.
(2) The repetitive replacements required by paragraph (g) of this AD may be terminated by modification of the airplane to post-Airbus Modification 27716 configuration, including a resonance frequency inspection for debonding of the composite insert and delamination of the honeycomb area around the insert, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12, 1999, provided all applicable corrective actions are done before further flight. Thereafter, refer to paragraph (i) of this AD to determine the compliance time for the next detailed inspection required by this AD.
(3) Modification of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, and including Appendix 02, dated October 23, 2015; or Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, constitutes terminating action for actions required by paragraphs (g) through (m) of this AD for the airplane on which the modification is done. As of the effective date of this AD only Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, may be used.
This paragraph restates the requirements of paragraph (o) of AD 2016-07-23, with no changes. An airplane on which Airbus Modification 155648 has been embodied in production is not affected by the requirements of paragraphs (g) and (i) of this AD, provided that no affected component, identified by part number as specified in paragraphs (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD, has been installed on that airplane since first flight of the airplane.
This paragraph restates the requirements of paragraph (p) of AD 2016-07-23, with a change to compliance requirements. Comply with this parts installation prohibition paragraph until the effective date of this AD. As of the effective date of this AD, comply with paragraph (t) of this AD.
(1) For airplanes in pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-1100 configuration: No person may install a component identified in paragraphs (g)(1) through (g)(5) of this AD on any airplane after doing the actions provided in paragraph (n)(2) of this AD.
(2) For airplanes in post-Airbus Modification 27716 or post Airbus Service Bulletin A320-52-1100 configuration: As of June 6, 2016 (the effective date of AD 2016-07-23), no person may install a component identified in paragraphs (g)(1) through (g)(5) of this AD on any airplane.
(3) For airplanes in pre-Airbus Modification 155648 or pre-Airbus Service Bulletin A320-52-1165 configuration: No person may install a component identified in paragraphs (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD on any airplane after doing the actions provided in paragraph (n)(3) of this AD.
(4) For airplanes in post-Airbus Modification 155648 or post-Airbus Service Bulletin A320-52-1165 configuration: As of June 6, 2016 (the effective date of AD 2016-07-23), no person may install a component identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of this AD on any airplane.
This paragraph restates the requirements of paragraph (q) of AD 2016-07-23, with no changes. Although Airbus Service Bulletin A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015, specifies to submit certain information to the manufacturer, and specifies that action as “RC” (Required for Compliance), this AD does not include that requirement.
For any airplane on which, before the effective date of this AD, any part was installed or replaced, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, dated November 3, 2014; Revision 01, dated October 13, 2015; or Revision 02, dated February 12, 2016: Within 12 months after the effective date of this AD, accomplish the instructions identified as “additional work” in the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, as applicable to the airplane configuration.
Modification of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, or as specified in paragraph (r) of this AD constitutes terminating action for the requirements of paragraphs (g) through (m) of this AD for that airplane.
(1) Do not install on any airplane a component specified in paragraphs (g)(1) through (g)(5) of this AD, as required by paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as applicable.
(i) For airplanes in pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-1100 configuration: After completing the optional modification specified in paragraph (n)(2) of this AD.
(ii) For airplanes in post-Airbus Modification 27716 or post Airbus Service Bulletin A320-52-1100 configuration: As of the effective date of this AD.
(2) Do not install on any airplane a component specified in paragraphs (g)(1) through (g)(5) of this AD or paragraphs (i)(1) through (i)(3) of this AD, as required by paragraph (t)(2)(i) or (t)(2)(ii) of this AD, as applicable.
(i) For airplanes in pre-Airbus Modification 155648 or pre-Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, configuration: After completion of the additional work required by paragraph (r) of this AD.
(ii) For airplanes in post-Airbus Modification 155648 or post-Airbus Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix 02, dated November 9, 2017, configuration: As of the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
