Airworthiness Directive · Amendment 39-21996 · Time limits/maintenance checks
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2023-05-02. Comply with the one in force.
This AD applies to all Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1) through (7) of this AD.
(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.
(5) Model A319-151N, -153N, and -171N airplanes.
(6) Model A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes.
(7) Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes.
The FAA is superseding Airworthiness Directive (AD) 2016-17- 12, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016- 17-12 required inspecting certain trimmable horizontal stabilizer actuators (THSAs) to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. Since the FAA issued AD 2016-17-12, the FAA has determined that a more restrictive airworthiness limitations is necessary for carbon friction disks on the no-back brake (NBB) of the THSA. This AD continues to require the inspections of the THSAs and replacement if necessary. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2016-17-12, with no changes. For airplanes identified in paragraphs (c)(1) through (4) of this AD: No later than each date specified in paragraphs (g)(1) through (5) of this AD, inspect the THSA to determine if it has a part number (P/N) 47145-(XXX), and, if any THSA P/N 47145-(XXX) is found, determine the total number of flight cycles accumulated since the THSA's first installation on an airplane, or since the most recent NBB replacement, whichever is later. A review of airplane delivery or maintenance records is acceptable in lieu of this inspection if the part number of the THSA can be conclusively determined from that review. In case maintenance records concerning the most recent NBB disk replacement are unavailable or incomplete, the total flight cycles accumulated since first installation of the THSA on an airplane apply. Accomplishing the maintenance or inspection program revision required by paragraph (l) of this AD terminates the requirements of this paragraph.
(1) As of September 30, 2016 (the effective date of AD 2016-17-12): The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 40,000 total flight cycles.
(2) As of December 31, 2016: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 36,000 total flight cycles.
(3) As of December 31, 2017: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 33,600 total flight cycles.
(4) As of December 31, 2018: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 31,600 total flight cycles.
(5) As of December 31, 2019: The THSA flight-cycle limit (since first installation on an airplane, or since the most recent NBB replacement, whichever is later) is 30,000 total flight cycles.
This paragraph restates the requirements of paragraph (h) of AD 2016-17-12, with no changes. For airplanes identified in paragraphs (c)(1) through (4) of this AD: For airplanes with any THSA P/N 47145-(XXX), do the replacements required by paragraphs (h)(1) and (2) of this AD. Accomplishing the maintenance or inspection program revision required by paragraph (l) of this AD terminates the requirements of this paragraph.
(1) No later than each date specified in paragraphs (g)(1) through (5) of this AD, replace all THSA that have reached or exceeded on each date the corresponding number of flight cycles specified in paragraphs (g)(1) through (5) of this AD. Do the replacement in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. Affected THSAs must be replaced with serviceable THSAs.
(2) As of each date specified in paragraphs (g)(1) through (5) of this AD, and before exceeding the flight cycle limit corresponding to each date, as applicable: Replace each THSA with a serviceable THSA, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016.
This paragraph restates the definition of paragraph (i) of AD 2016-17-12, with no changes. For airplanes identified in paragraphs (c)(1) through (4) of this AD: For the purposes of this AD, a serviceable THSA is a THSA that has not exceeded the applicable flight-cycle limits, as specified paragraphs (g)(1) through (5) of this AD, since first installation of the THSA on an airplane or since last NBB replacement, whichever is later.
Note 1 to paragraph (i): Guidance for NBB disk replacement can be found in UTC Aerospace Systems Service Bulletin 47145-27-17, Revision 1, dated July 21, 2015.
This paragraph restates the provisions of paragraph (j) of AD 2016-17-12, with no changes. For airplanes identified in paragraphs (c)(1) through (4) of this AD: As of each date specified in paragraphs (g)(1) through (5) of this AD, as applicable, only installation of a serviceable THSA P/N 47145-(XXX) is allowed on an airplane. Accomplishing the maintenance or inspection program revision required by paragraph (l) of this AD terminates the requirements of this paragraph.
This paragraph restates the requirements of paragraph (k) of AD 2016-17-12, with no changes. For airplanes identified in paragraphs (c)(1) through (4) of this AD: This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before September 30, 2016 (the effective date of AD 2016-17-12), using Airbus Service Bulletin A320-27-1242, dated February 9, 2015.
(1) For the airplanes identified in paragraph (c) of this AD with an original airworthiness certificate or original export certificate of airworthiness issued on or before October 5, 2020, except as specified in paragraph (m) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2020-0270, dated December 7, 2020 (EASA AD 2020-0270). Accomplishing the maintenance or inspection program revision required by this paragraph terminates the requirements of paragraphs (g), (h), and (j) of this AD.
(2) For the airplanes identified in paragraph (c) of this AD with an original airworthiness certificate or original export certificate of airworthiness issued after October 5, 2020, revise the existing maintenance or inspection program, as applicable, to incorporate the provision specified in paragraph (m)(7) of this AD.
(1) Where EASA AD 2020-0270 refers to its effective date, this AD requires using the effective date of this AD.
(2) The requirements specified in paragraphs (1) and (2) of EASA AD 2020-0270 do not apply to this AD.
(3) Paragraph (3) of EASA AD 2020-0270 specifies revising “the approved AMP” within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, within 90 days after the effective date of this AD.
(4) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2020-0270 is at the applicable “limitations” as incorporated by the requirements of paragraph (3) of EASA AD 2020-0270, or within 90 days after the effective date of this AD, whichever occurs later.
(5) The provisions specified in paragraph (4) of EASA AD 2020-0270 do not apply to this AD.
(6) The “Remarks” section of EASA AD 2020-0270 does not apply to this AD.
(7) For all airplanes identified in paragraph (c) of this AD: Where the Note for Item 274000-00004-1-E of Section 4-1 in the service information referenced in EASA AD 2020-0270 specifies “NBB carbon disc replacement” instructions, for this AD, replace the text “NBB carbon disc replacement can be accomplished in accordance with SB A320-27-1242 or VSB 47145-27-17,” with “NBB carbon disk replacement must be accomplished in accordance with SB A320-27-1242.”
After the existing maintenance or inspection program has been revised as required by paragraph (l) of this AD, no alternative actions (e.g., inspections) or intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2020-0270.
Accomplishing the actions required by this AD terminates the airworthiness limitations section (ALS) limitation task 274000-00004-1-E for the THSA, as required by paragraph (i) of AD 2020-21-10.
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 (q)(1) 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 2016-17-12 are approved as AMOCs for the corresponding provisions of paragraphs (g) through (j) 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, 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): Except as required by paragraph (p)(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.
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.
