2021-22-18: Doors

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 adding the following new airworthiness directive: 2021-22-18 Airbus SAS: Amendment 39-21791; Docket No. FAA-2021-0545; Project Identifier MCAI-2021-00071-T. (a) Effective Date This airworthiness directive (AD) is effective December 29, 2021. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A350-941 and -1041 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of a broken forward guide arm found during a passenger door emergency opening test. Investigation results indicated that the opening speed of the door was higher than expected, likely caused by a reduced damping due to oil leakage of the passenger door damper emergency opening actuator (DEOA). The FAA is issuing this AD to address failure of a passenger door to perform its intended function during an emergency opening, which could result in reduced evacuation capacity from the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) EASA AD 2021-0085, dated March 19, 2021 (EASA AD 2021-0085). (h) Exceptions and Clarifications to EASA AD 2021-0085 (1) Where EASA AD 2021-0085 refers to January 29, 2021 (the effective date of EASA AD 2021-0018), this AD requires using the effective date of this AD. (2) Where EASA AD 2021-0085 refers to its effective date, this AD requires using the effective date of this AD. (3) This AD does not mandate compliance with the "Remarks" section of EASA AD 2021-0085. (4) Where paragraphs (4) and (5) of EASA AD 2021-0085 refer to "the limits as defined in the inspection SB [service bulletin]," for this AD use "the limits as defined in ASR [aircraft structural repair] A350-A-51-73-11-01ZZZ-667Z-A." (5) Where paragraphs (1) and (2) of EASA AD 2021-0085 specify to "replace the forward and aft guide arms on that door in accordance with the instructions of the inspection SB," this AD requires "removing the forward and aft guide arms on that door, in accordance with the instructions of the inspection SB; doing a detailed inspection of the forward and aft guide arm support bracket on that door and all applicable corrective actions as specified in paragraphs (3) through (5) of EASA AD 2021-0085; and installing new forward and aft guide arms on that door, in accordance with the instructions of the inspection SB." (6) Where paragraph (6) of EASA AD 2021-0085 specifies to modify the airplane "in accordance with the instructions of the modification SB," this AD allows the replacement of DEOA P/N FE396001001with DEOA P/N FE396001004, FE396001005, or FE396001006, in addition to DEOA P/N FE396001003. (7) Where paragraph (6) of EASA AD 2021-0085 specifies to modify the airplane "in accordance with the instructions of the modification SB", this AD allows DEOAs that are "serviceable" to be used as replacement parts, provided the part fits the definition of a "serviceable part" as identified in EASA AD 2021-0085. (8) Where paragraph (4) of EASA AD 2021-0085 specifies to accomplish the applicable corrective actions "in accordance with the instructions of the inspection SB," this AD requires the use of cotter pins having P/N MS24665-300 instead of cotter pins having P/N MS24665-155. (9) Where paragraphs (6) and (7) of EASA AD 2021-0085 specify to modify the airplane to ensure that there is a maximum of one affected part per door pair and that replacement of each affected part is terminating action, which involves the use of CML 04SBA3 varnish polyurethane to protect the identification plate, this AD also allows the use of CA8800/B900 varnish polyurethane in lieu of the CML 04SBA3 varnish polyurethane. (11) Where the service information referenced in EASA AD 2021-0085 specifies discarding discrepant parts, this AD does not require that action. (i) No Reporting Requirement Although the service information referenced in EASA AD 2021-0085 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) 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 (k)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (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 (j)(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. (k) Related Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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. (i) European Union Aviation Safety Agency (EASA) AD 2021-0085, dated March 19, 2021. (ii) [Reserved] (3) For EASA AD 2021-0085, 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. (4) 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. (5) 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 October 21, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021-25534 Filed 11-23-21; 8:45 am]BILLING CODE 4910-13-P