Airworthiness Directive · Amendment 39-21908 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS airplanes specified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2018-0289R1, dated February 10, 2021 (EASA AD 2018-0289R1).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is superseding Airworthiness Directive (AD) 2019-20- 10, which applied to certain Airbus SAS Model A318 series airplanes; 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. AD 2019-20-10 required repetitive rototest inspections of the holes at the door stop fittings for any cracking, and corrective actions if necessary. Since the FAA issued AD 2019-20-10, a clarification of a certain compliance time for the rototest inspection was added. This AD clarifies a certain compliance time and continues to require repetitive rototest inspections of the holes at the door stop fittings for any cracking, and repair if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2018-0289R1.
(1) Where EASA AD 2018-0289R1 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2018-0289R1 does not apply to this AD.
(3) Where Table 1 of EASA AD 2018-0289R1 refers to a compliance time “after 31 May 2017,” this AD requires using a compliance time after May 31, 2018 (the effective date of task 531103-01-1 in “ALS Part 2 rev. 6”).
(4) Where paragraphs (3) and (6) of EASA AD 2018-0289R1 refers to actions that have been done “in accordance with Airbus Repair Design Approval Sheet (RDAS),” this AD includes repair done “in accordance with a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.”
(5) Where paragraph (3) of EASA AD 2018-0289R1 refers to accomplishing the next due inspection of each repaired affected area “within the compliance time as specified in, Airbus RDAS, as applicable,” for this AD use the applicable compliance time specified in the repair “approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.”
(6) Where condition “A” in Table 1 of EASA AD 2018-0289R1 specifies a compliance time of “Before exceeding 30[,]000 FC since aeroplane first flight,” this AD requires, for the inspection at frame 16 only, a compliance time of “Before exceeding 30,000 flight cycles since airplane's first flight, or within 30 days after the effective date of this AD, whichever occurs later.”
(7) If the actions in paragraph 3.C.(8) of the inspection service bulletin referenced in EASA AD 2018-0289R1 specifies to report all findings, this AD requires reporting if only the cracked intercostal(s) that have been replaced using repair instruction R53113118. Report results at the applicable time specified in paragraph (h)(7)(i) or (ii) of this AD. If operators have reported findings as part of obtaining any corrective actions approved by Airbus SAS's European Aviation Safety Agency (EASA) Design Organization Approval (DOA), operators are not required to report those findings as specified in this paragraph.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
(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 previously for AD 2019-20-10 are approved as AMOCs for the corresponding provisions of EASA AD 2018-0289R1 that are required by paragraph (g) of this AD, except for those airplanes having a compliance time specified in “Table 1: Inspection Thresholds,” Row B, of EASA AD 2018-0289R1.
(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, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): For any service information referenced in EASA AD 2018-0289R1 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC 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.
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.
