AD 2021-11-23

The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD 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 requires, for certain airplanes, an update of the hydraulic monitoring system to include additional redundancy. The FAA is issuing this AD to address the unsafe condition on these products.

Final rule.

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive: \n\n2021-11-23 Airbus SAS: Amendment 39-21585; Docket No. FAA-2021-0193; Project Identifier MCAI-2020-01612-T. \n\n(a) Effective Date \n\n\n\tThis airworthiness directive (AD) is effective September 3, 2021. \n\n(b) Affected ADs \n\n\n\tNone. \n\n\n\t(c) Applicability \n\n\n\tThis AD applies to Airbus SAS Model A350-941 and -1041 airplanes, certificated in any category; with an original airworthiness certificate or original export certificate of airworthiness issued after September 15, 2020. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 05, Time Limits/ Maintenance checks; 29, Hydraulic power. \n\n(e) Reason \n\n\n\tThis AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the overheat failure mode of the hydraulic engine-driven pump, which may cause a fast temperature rise of the hydraulic fluid, and, if combined with an inoperative fuel tank inerting system, could lead to an uncontrolled overheat of the hydraulic fluid, possibly resulting in ignition of the fuel-air mixture of the affected fuel tank. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Requirements \n\n\n\tExcept 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) AD 2020-0268, dated December 4, 2020 (EASA AD 2020-0268). \n\n(h) Exceptions to EASA AD 2020-0268 \n\n\n\t(1) Where Section6 of the service information referenced in EASA AD 2020-0268 specifies to update the hydraulic monitoring system ''to include additional redundancy to be installed (MOD 114073 and MOD 114075 OR 114531 and MOD 114075 OR MOD 114533 and MOD 114075 OR MOD 114535 and MOD 114075),'' this AD requires \n\n((Page 40934)) \n\nthat the update of the hydraulic monitoring system be accomplished using the method of compliance specified in paragraphs (h)(1)(i) through (iv) of this AD, as applicable. \n\t(i) For Model A350-941 airplanes identified in Airbus Service Bulletin A350-29-P025 (MOD 114531 and MOD 114075): The modification must be done in accordance with paragraphs 3.C., 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A350-29- P025, dated August 10, 2020. \n\t(ii) For Model A350-941 airplanes identified in Airbus Service Bulletin A350-29-P027 (MOD 114533 and MOD 114075): The modification must be done in accordance with paragraphs 3.C., 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A350-29- P027, dated November 24, 2020. \n\t(iii) For Model A350-941 airplanes identified in Airbus Service Bulletin A350-29-P029 (MOD 114535 and MOD 114075): The modification must be done in accordance with paragraphs 3.C., 3.D., and 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A350-29- P029, dated December 16, 2020. \n\t(iv) For Model A350-941 airplanes not identified in paragraphs (h)(1)(i) through (iii) of this AD, and without MOD 114073 and 114075 installed in production: The modification must be done 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. \n\t(2) Where EASA AD 2020-0268 refers to its effective date, this AD requires using the effective date of this AD. \n\t(3) The requirements specified in paragraphs (1) and (2) of EASA AD 2020-0268 do not apply to this AD. \n\t(4) Paragraph (3) of EASA AD 2020-0268 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. \n\t(5) The initial compliance time for doing the tasks specified in paragraph (3) of EASA AD 2020-0268 is at the applicable ''thresholds'' as incorporated by the requirements of paragraph (3) of EASA AD 2020-0268, or within 90 days after the effective date of this AD, whichever occurs later. \n\t(6) The provisions specified in paragraphs (4) and (5) of EASA AD 2020-0268 do not apply to this AD. \n\t(7) The ''Remarks'' section of EASA AD 2020-0268 does not apply to this AD. \n\n(i) Provisions for Alternative Actions, Intervals, and Critical Design Configuration Control Limitations (CDCCLs) \n\n\n\tAfter the existing maintenance or inspection program has been revised as requiredby paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and CDCCLs are allowed unless they are approved as specified in the provisions of the ''Ref. Publications'' section of EASA AD 2020-0268. \n\n(j) Other FAA AD Provisions \n\n\n\tThe following provisions also apply to this AD: \n\t(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 local Flight Standards District 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) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lackinga principal inspector, the manager of the local flight standards district office/ certificate holding district office. \n\t(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 DOA. If approved by the DOA, the approval must include the DOA-authorized signature. \n\t(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. \n\n\n\t(k) Related Information \n\n\n\tFor more information about this AD, contact Kathleen Arrigotti, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3218; Kathleen.Arrigotti@faa.gov. \n\n(l) Material Incorporated by Reference \n\n\n\t(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. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. \n\t(i) European Union Aviation Safety Agency (EASA) AD 2020-0268, dated December 4, 2020. \n\t(ii) Airbus Service Bulletin A350-29-P025, dated August 10, 2020. \n\t(iii) Airbus Service Bulletin A350-29-P027, dated November 24, 2020. \n\t(iv) Airbus Service Bulletin A350-29-P029, dated December 16, 2020. \n\t(3) For EASA AD 2020-0268, contact the EASA, Konrad-Adenauer- Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. For Airbus SAS service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email continued-airworthiness.a350@airbus.com; internet http://www.airbus.com. \n\t(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. This material may be found in the AD docketon the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-0193. \n\t(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 fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on May 21, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2021-16241 Filed 7-29-21; 8:45 am) BILLING CODE 4910-13-P

Discussion \n\n\n\tThe EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2020-0268, dated December 4, 2020 (EASA AD 2020-0268) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Airbus SAS Model A350-941 and -1041 airplanes. EASA AD 2020- 0268 refers to Airbus A350 Airworthiness Limitations Section (ALS), Part 5, ''Fuel Airworthiness Limitations (FAL),'' Revision 04, dated May 29, 2020; and Airbus A350 ALS Part 5, ''Fuel Airworthiness Limitations (FAL),'' Variation 4.1, dated September 15, 2020. Airplanes with an original airworthiness certificate or original export certificate of airworthiness issued after September 15, 2020, must comply with the airworthiness limitations specified as part of the approved type design and referenced on the type certificate data sheet; this AD therefore does not include those airplanes in the applicability. \n\tThe FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A350-941 and -1041 airplanes. The NPRM published in the Federal Register on March 26, 2021 (86 FR 16117). The NPRM was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The NPRM proposed to require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in EASA AD 2020-0268. The NPRM also proposed to require, for certain airplanes, an update of the hydraulic monitoring system to include additional redundancy. \n\tThe FAA is issuing this AD to address the overheat failure mode of the hydraulic engine-driven pump (EDP), which may cause a fast temperature rise of the hydraulic fluid, and, if combined with an inoperative fuel tank inerting system, could lead to an uncontrolled overheat of the hydraulic fluid, possibly resulting in ignition of the fuel-air mixture of the affected fuel tank. See the MCAI for additional background information. \n\nComments \n\n\n\tThe FAA gave the public the opportunity to participate in developing this final rule. The FAA has considered the comment received. The Air Line Pilots Association, International (ALPA) stated that it supports the NPRM. \n\nConclusion \n\n\n\tThe FAA reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. The FAA has determined that these minor changes: \n\tAre consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and \n\tDo not add any additional burden upon the public than was already proposed in the NPRM. \n\nRelated Service Information Under 1 CFR Part 51 \n\n\n\tEASA AD 2020-0268 describes new or more restrictive airworthiness limitations related to fuel tank ignition \n\n((Page 40933)) \n\nprevention and fuel tank flammability reduction. \n\tThis AD would also require accomplishing a certain airworthiness limitation using the following service information. This service information describes procedures for an update of the hydraulic monitoring system to include additional redundancy (i.e., modifying the case-drain filter manifolds by installing new dual temperature sensors on the hydraulic EDP). These documents are distinct since they apply to different airplane models. \n\tAirbus Service Bulletin A350-29-P025, dated August 10, 2020. \n\tAirbus Service Bulletin A350-29-P027, dated November 24, 2020. \n\tAirbus Service Bulletin A350-29-P029, dated December 16, 2020. \n\tThis material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. \n\nCosts of Compliance \n\n\n\tThe FAA estimates that this AD affects 15 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: \n\tThe FAA has determined that revising the existing maintenance or inspection program takes an average of 90 work-hours per operator, although the agency recognizes that this number may vary from operator to operator. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), the FAA has determined that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, the agency estimates the average total cost per operator to be $7,650 (90 work-hours x $85 per work-hour). \n\n\n\tEstimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- \n\tLabor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Up to 510 work-hoursx $85 per Up to $29,320.......... Up to $72,670............. Up to $1,090,050. \n\thour = Up to $43,350. ---------------------------------------------------------------------------------------------------------------- \n\n\n\tAccording to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in the cost estimate. \n\nAuthority for This Rulemaking \n\n\n\tTitle 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. \n\tThe FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. \n\nRegulatory Findings \n\n\n\tThis AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. \n\tFor the reasons discussed above, I certify that this AD: \n\t(1) Is not a ''significant regulatory action'' under Executive Order 12866, \n\t(2) Will not affect intrastate aviation in Alaska, and \n\t(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. \n\nList of Subjects in 14 CFR Part 39 \n\n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.