2022-07-08: Time Limits/Maintenance Checks, Flight Controls

1. The authority citation for part 39 continues to read as follows: Authority : 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive (AD) 2016-17-12, Amendment 39-18625 (81 FR 58823, August 26, 2016); and b. Adding the following new AD: 2022-07-08 Airbus SAS: Amendment 39-21996; Docket No. FAA-2021-0663; Project Identifier MCAI-2020-01618-T. (a) Effective Date This airworthiness directive (AD) is effective May 19, 2022. (b) Affected ADs (1) This AD replaces AD 2016-17-12, Amendment 39-18625 (81 FR 58823, August 26, 2016) (AD 2016-17-12). (2) This AD affects AD 2020-21-10, Amendment 39-21283 (85 FR 65190, October 15, 2020) (AD 2020-21-10). (c) Applicability 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. (d) Subject Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks; 27, Flight Controls. (e) Reason This AD was prompted by a determination that a more restrictive airworthiness limitation is necessary for the carbon friction disks on the no-back brake (NBB) of the trimmable horizontal stabilizer actuator (THSA). The FAA is issuing this AD to address premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection To Determine THSA Part Number and Accumulated Total Flight Cycles, With No Changes 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. (h) Retained Replacements, With No Changes 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. (i) Retained Definition of Serviceable THSA, With No Changes 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. (j) Retained Parts Installation Limitation, With No Changes 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. (k) Retained Credit for Previous Actions, With No Changes 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. (l) New Maintenance or Inspection Program Revision (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. (m) Exceptions to EASA AD 2020-0270 (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." (n) New Provisions for Alternative Actions and Intervals 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. (o) Terminating Action for Certain Requirements of AD 2020-21-10 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. (p) Additional AD Provisions 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: [email protected]. (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. (q) Related Information (1) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223; email [email protected]. (2) For UTC Aerospace Systems service information identified in this AD that is not incorporated by reference, contact Collins Aerospace, Product Support Department 13, Avenue de L'Eguillette-Saint-Ouen L'Aumone, Boite Postale 7186 95056 Cergy Pontoise Cedex, France; telephone 1-877-808-7575; email [email protected]; internet https://www.collinsaerospace.com/support. (r) 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. (3) The following service information was approved for IBR on May 19, 2022. (i) European Union Aviation Safety Agency (EASA) AD 2020-0270, dated December 7, 2020. (ii) [Reserved] (4) The following service information was approved for IBR on September 30, 2016 (81 FR 58823, August 26, 2016). (i) Airbus Service Bulletin A320-27-1242, Revision 01, dated February 4, 2016. (ii) [Reserved] (5) For EASA AD 2020-0270, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email [email protected]; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. (6) For Airbus service information, 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 https://www.airbus.com. (7) You may view this material 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. (8) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on March 18, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-07859 Filed 4-13-22; 8:45 am]BILLING CODE 4910-13-P