AD 2026-20-15

65954 Federal Register / Vol. 91, No. 200 / Monday, October 19, 2026 / Rules and Regulations under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES ■ 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] ■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2026–21–03 Airbus SAS: Amendment 39– 23492; Docket No. FAA–2026–8780; Project Identifier MCAI–2026–00262–T. (a) Effective Date This airworthiness directive (AD) is effective November 23, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS airplanes specified in paragraphs (c)(1) and (2) of this AD, certificated in any category. (1) Model A330–243, A330–243F, A330– 341, A330–342, A330–343, A330–841, and A330–941 airplanes. (2) Model A340–211, A340–212, A340– 213, A340–311, A340–312, A340–313, A340– 541, and A340–642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Unsafe Condition This AD was prompted by reports of leaks on closed fuel low pressure shut-off valves (LPSOVs) due to the LPSOV failing to seal. The FAA is issuing this AD to address such leaks, which, depending on the amount of the leak, could sustain a fire. The unsafe condition, if not addressed, could lead to the inability to extinguish a fire and result in significant damage to airplane structure or systems. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2026– 0060R1, dated June 9, 2026 (EASA AD 2026– 0060R1). (h) Exceptions to EASA AD 2026–0060R1 (1) Where Table 1 of EASA AD 2026– 0060R1 specifies a compliance time of between November 12, 2025, and March 3, 2029, this AD requires accomplishing the initial leak check within 35 months after the effective date of this AD. (2) Where EASA AD 2026–0060R1 refers to April 3, 2026 (the effective date of the original issue of EASA AD 2026–0060), this AD requires using the effective date of this AD. (3) Where EASA AD 2026–0060R1 defines a serviceable part as ‘‘Any fuel LPSOV eligible for installation in accordance with Airbus instructions’’, for this AD, replace that text with ‘‘Any fuel LPSOV eligible for installation’’. (4) Where paragraph (4) of EASA AD 2026– 0060R1 specifies ‘‘any discrepancy of an affected part, as specified in the SB, is detected’’, for this AD, replace that text with ‘‘any discrepancy of an affected part is detected’’. (5) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2026–0060R1. (i) No Reporting and No Return of Parts Although the material referenced in EASA AD 2026–0060R1 specifies to submit certain information to the manufacturer and to send removed parts to the manufacturer, this AD does not include those requirements. (j) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, AIR–520, Continued Operational Safety 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 manager of the Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (k) of this AD and email to: AMOC@faa.gov. 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, AIR–520, Continued Operational Safety 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 material 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) Additional Information For more information about this AD, contact Anthony D. Decaro, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 562–627–5374; email: Anthony.D.Decaro@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2026–0060R1, dated June 9, 2026. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu. You may find this material on the EASA website at 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 98198. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on October 7, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–21325 Filed 10–16–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–4649; Project Identifier MCAI–2025–00835–T; Amendment 39–23488; AD 2026–20–15] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2025–04– VerDate Sep<11>2014 16:15 Oct 16, 2026 Jkt 271001 PO 00000 Frm 00068 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 lotter on DSK8BHNXB4PROD with RULES1

65955 Federal Register / Vol. 91, No. 200 / Monday, October 19, 2026 / Rules and Regulations 05, which applied to all Airbus SAS Model A330–841 and –941 airplanes. AD 2025–04–05 required a revision of the existing airplane flight manual (AFM) and removal of the previously required limitations; a revision of the existing minimum equipment list (MEL); one-time or repetitive seal integrity tests of each engine bleed air system (EBAS) high pressure valve (HPV); additional maintenance instructions and corrective actions; and repetitive replacement of affected HPV clips; as applicable. AD 2025–04–05 also limited the installation of affected HPV clips. Since the FAA issued AD 2025–04–05, an improved EBAS HPV with unaffected HPV clips was certified, and it was determined that the bleed monitoring computer (BMC) software (SW) must be updated. This AD continues to require the actions in AD 2025–04–05, except for repetitive replacement of affected HPV clips. This AD also requires updating the BMC SW, additional work, and an additional revision of the existing MEL for the engine bleed overpressure valve; as applicable. This AD also prohibits the installation of certain BMC software. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective November 23, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 23, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–4649; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For European Union Aviation Safety Agency (EASA) material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • 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. It is also available at regulations.gov under Docket No. FAA–2026–4649. FOR FURTHER INFORMATION CONTACT : Rochelle Montgomery, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 405– 551–0414; email: Rochelle.Montgomery@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2025–04–05, Amendment 39–22963 (90 FR 10853, February 28, 2025) (AD 2025–04–05). AD 2025–04–05 applied to all Airbus SAS Model A330–841 and –941 airplanes. AD 2025–04–05 required a revision of the existing AFM and removal of the previously required limitations; a revision of the existing MEL; one-time or repetitive seal integrity tests of each EBAS HPV; additional maintenance instructions and corrective actions; and repetitive replacement of affected HPV clips; as applicable. AD 2025–04–05 also limited the installation of affected HPV clips. The FAA issued AD 2025–04–05 to address a leaking HPV that may expose the pressure regulating valve (PRV), which is installed downstream from the HPV to high pressure, possibly damaging the PRV itself and preventing its closure. The unsafe condition, if not addressed, could result in high pressure and temperatures in the duct downstream from the PRV, with possible duct burst, damage to several systems, and consequent loss of control of the airplane. The NPRM was published in the Federal Register on June 4, 2026 (91 FR 33674). The NPRM was prompted by EASA AD 2025–0104R1, dated March 19, 2026 (EASA AD 2025–0104R1) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states an improved HPV has been certified (Airbus Modification 210503), which introduces several design improvements and is equipped with HPV clips that do not have to be replaced at predefined intervals. The MCAI also states that it has been determined that the optional modification to install BMC SW 5.0 must be mandated on airplanes on which BMC SW 4.0 or 4.1 is installed, additional work defined in a later revision of the other service information must be accomplished, and new master minimum equipment list (MMEL) content must be implemented for airplanes on which BMC SW 4.0 or 4.1 is installed. The MCAI further specifies that modification of both affected HPVs terminates the HPV clip replacement for the airplane, provided no affected HPV is re-installed on that airplane. In the NPRM, the FAA proposed to continue to require the actions in AD 2025–04–05 except for repetitive replacement of affected HPV clips, as specified in EASA AD 2025–0104R1. The NPRM also proposed to require updating the BMC SW, additional work, and an additional revision of the existing MEL for the engine bleed overpressure valve, as applicable; and to prohibit the installation of certain BMC software; as specified in EASA AD 2025–0104R1. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2026–4649. Discussion of Final Airworthiness Directive Comments The FAA received a comment from the Air Line Pilots Association, International (ALPA) who supported the NPRM without change. The FAA received an additional comment from Delta Air Lines (Delta). The following presents the comments received on the NPRM and the FAA’s response. Request To Provide Credit for Replacement of Affected HPVs Delta requested that the FAA revise the proposed AD to provide credit for replacement of affected EBAS HPVs (part number (P/N) 71070A010001 or P/ N 71070A020001) with non-affected EBAS HPVs (P/N 71070A030001), using FAA-approved maintenance data, including the Airbus aircraft maintenance manual (AMM). Delta noted Option 2 of Airbus Service Bulletin A330–36–3057, dated October 28, 2024 (Airbus Service Bulletin A330– 36–3057), provides procedures for replacing affected HPVs with non- affected HPVs using Airbus AMM Tasks 36–11–51–000–806 and 36–11–51–400– 806, in lieu of modification of the HPVs in Option 1 of that service bulletin as referenced in paragraph (30) of EASA AD 2025–0104R1. Delta stated operators are already conducting unscheduled removal and replacement of HPVs during normal operations, and that allowing credit for replacement of affected HPVs with non-affected HPVs using approved AMM procedures would provide operational flexibility during unscheduled maintenance while achieving the same configuration and VerDate Sep<11>2014 16:15 Oct 16, 2026 Jkt 271001 PO 00000 Frm 00069 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 lotter on DSK8BHNXB4PROD with RULES1

65956 Federal Register / Vol. 91, No. 200 / Monday, October 19, 2026 / Rules and Regulations maintaining an acceptable level of safety. The FAA agrees it acceptable to replace the affected HPVs with non- affected HPVs using Option 2 of Airbus Service Bulletin A330–36–3057 in lieu of modifying the affected HPVs using Option 1 of that service bulletin. Accordingly, the FAA has revised the exception in paragraph (h)(10) to specify that the modification or replacement of both affected HPVs in accordance with Airbus Service Bulletin A330–36–3057 constitutes terminating action for the HPV clip replacement. In addition, the FAA has added new paragraph (i) to this AD to provide credit for accomplishing the replacement using AMM Tasks 36– 11–51–000–806 and 36–11–51–400–806 before the effective date of this AD. Under the provisions of paragraph (k)(1) of this AD, the FAA will consider requests for alternative methods of compliance, should operators wish to use other maintenance data or the applicable AMM tasks after the effective date of this AD. Conclusion These products have been approved by the civil aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, that authority has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered any comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Material Incorporated by Reference Under 1 CFR Part 51 EASA AD 2025–0104R1 specifies procedures for the following retained actions: • For Group 1 airplanes (equipped with BMC SW 4.0) and Group 2 airplanes (equipped with BMC SW 4.1 standard), a revision of the Limitations section of the existing AFM; and for Groups 1 and 2 and Group 3 (equipped with BMC SW 5.0 or later approved SW standard and an affected HPV) airplanes, removal of the previously required limitations. • For Groups 1 and 2 airplanes, implementation of the MMEL update that includes new provisions and procedures for Air Conditioning Pack, Engine Bleed Air Supply System, Engine Bleed IP (Intermediate Pressure) Check Valve, and Engine Bleed HP (High Pressure) Valve; and cancellation of the dispatch restrictions. • For Group 2 airplanes, a seal integrity test of each HPV; for Group 1 airplanes, repetitive seal integrity tests of each HPV; and corrective actions, which include replacement of the HPV, a detailed inspection of the wing bellow on engine 1(2), and replacement of any damaged or deformed wing bellow. EASA AD 2025–0104R1 describes the following retained maintenance instructions, among other actions, to be accomplished following certain faults or failures, on Groups 1 and 2 airplanes: • HPV troubleshooting procedure and additional maintenance actions after any Class 1 maintenance message associated with an HPV fault and corrective actions, which includes replacement of the HPV or wing bellow. • HPV seal integrity test and the additional maintenance actions after any Class 1 or Class 2 maintenance message associated with a PRV fault and corrective actions, which includes replacement of the HPV and PRV, a detailed inspection of the wing bellow on engine 1(2), and replacement of any damaged or deformed wing bellow. • A visual (borescope) inspection of the EBAS to detect signs of foreign object debris (FOD), including metallic debris in the butterfly valve and dents or damage of the flaps of the intermediate pressure check valve (IPCV), and dents and missing segments in the PRV, the header of the HP/IP duct, y-duct, and pylon ducts after any failure of an HPV clip and/or any of the HPV butterfly sealing rings, and corrective actions, which includes FOD removal and replacement of the IPCV or PRV. • A seal integrity test of each HPV after any takeoff or go-around accomplished with ‘‘packs OFF’’ or ‘‘APU bleed ON’’ or ‘‘engine bleed OFF’’ and corrective actions, which include replacement of the HPV, a detailed inspection of the wing bellow on engine 1(2), and replacement of any damaged or deformed wing bellow. • Additional actions to be performed for any Class 1 maintenance message associated with an HPV fault. EASA AD 2025–0104R1 also specifies the following retained limitations for the installation of affected parts: • For Groups 1, 2, and 3 airplanes, installation of an affected HPV clip on an affected HPV on an airplane, provided it is a new affected clip ( i.e., not previously installed on any HPV) and that following installation, it is replaced according to the referenced service information. • For Groups 1, 2, and 3 airplanes, installation of an affected HPV on an airplane, provided it is a serviceable HPV and that following installation, the affected HPV clips of that HPV are replaced with new clips according to the referenced service information. EASA AD 2025–0104R1 also specifies that, for Group 1 airplanes, modification (update to BMC SW 4.1) of the airplane terminates the repetitive seal integrity tests of each HPV. EASA AD 2025–0104R1 specifies the following new actions: • For Groups 1 and 2 airplanes, modification (update to BMC SW 5.0) of the airplane, which includes deletion of the operations engineering bulletin (OEB) reminder data from the flight warning computer (FWC) database. • For Group 3 airplanes, accomplishment of additional work (deletion of the OEB reminder data from the FWC database). • For Groups 1 and 2 airplanes, implementation of the MMEL update that includes new provisions for Engine Bleed Overpressure Valve. EASA AD 2025–0104R1 also prohibits the installation of the following affected parts: • BMC SW 4.0 or BMC SW 4.1 on any Group 3 or Group 4 (embodied with Airbus modifications 210503 and 210504 in production) airplane, and on any Group 1 or 2 airplane after modification (update to BMC SW 5.0) of the airplane. • An affected HPV on any Group 4 airplane. EASA AD 2025–0104R1 also specifies that, for Groups 1, 2, and 3 airplanes, modification of both affected HPVs terminates the HPV clip replacement for the airplane, provided no affected HPV is re-installed on that airplane; and if modification of the two affected HPVs are accomplished at different times, the HPV clip replacement is only applicable to the affected HPV. This 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. Costs of Compliance The FAA estimates that this AD would affect 22 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 16:15 Oct 16, 2026 Jkt 271001 PO 00000 Frm 00070 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 lotter on DSK8BHNXB4PROD with RULES1

65957 Federal Register / Vol. 91, No. 200 / Monday, October 19, 2026 / Rules and Regulations E STIMATED C OSTS FOR R EQUIRED A CTIONS Action Labor cost Parts cost Cost per product Cost on U.S. operators Retained actions from AD 2025– 04–05. Up to 15 work-hours × $85 per hour = $1,275. Up to $28 .................... Up to $1,303 ............... Up to $28,666. New actions for Groups 1 and 2 airplanes (software update, ad- ditional work, and MEL revi- sion). 5 work-hours × $85 per hour = $425. $524 ............................ $949 ............................ Up to $20,878 *. New actions for Group 3 air- planes (additional work). 2 work-hours × $85 per hour = $170. $0 ................................ $170 ............................ Up to $3,740 *. * The FAA has no definitive data to determine how many affected airplanes are in each airplane group. The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need these on-condition actions: E STIMATED C OSTS OF O N -C ONDITION A CTIONS Labor cost Parts cost Cost per product Up to 19 work-hours × $85 per hour = $1,615 ....................... Up to $114,742 ...................................... Up to $116,357. The FAA has received no definitive data on which to base the cost estimates for the maintenance actions specified in this AD. E STIMATED C OSTS FOR O PTIONAL M ODIFICATION OF B OTH A FFECTED HPV S Labor cost Parts cost Cost per product 11 work-hours × $85 per hour = $935 ............................................................................................ $96,885 $97,790 Authority for This Rulemaking Title 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. The 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. Regulatory Findings This 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. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES ■ 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] ■ 2. The FAA amends § 39.13 by: ■ a. Removing Airworthiness Directive (AD) 2025–04–05, Amendment 39– 22963 (90 FR 10853, February 28, 2025); and ■ b. Adding the following new AD: 2026–20–15 Airbus SAS: Amendment 39– 23488; Docket No. FAA–2026–4649; Project Identifier MCAI–2025–00835–T. (a) Effective Date This airworthiness directive (AD) is effective November 23, 2026. (b) Affected ADs This AD replaces AD 2025–04–05, Amendment 39–22963 (90 FR 10853, February 28, 2025) (AD 2025–04–05). (c) Applicability This AD applies to all Airbus SAS Model A330–841 and –941 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 36, Pneumatic. (e) Unsafe Condition This AD was prompted by reports of leaking bleed system high pressure valves (HPV), likely due to HPV clip failure and sealing ring damage. This AD was also prompted by certification of an improved VerDate Sep<11>2014 16:15 Oct 16, 2026 Jkt 271001 PO 00000 Frm 00071 Fmt 4700 Sfmt 4700 E:\FR\FM\19OCR1.SGM 19OCR1 lotter on DSK8BHNXB4PROD with RULES1

65958 Federal Register / Vol. 91, No. 200 / Monday, October 19, 2026 / Rules and Regulations HPV with unaffected HPV clips and the determination that the bleed monitoring computer (BMC) software must be updated. The FAA is issuing this AD to address a leaking HPV that may expose the pressure regulating valve (PRV), which is installed downstream from the HPV to high pressure, possibly damaging the PRV itself and preventing its closure. The unsafe condition, if not addressed, could result in high pressure and temperatures in the duct downstream from the PRV, with possible duct burst, damage to several systems, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraphs (h), (i), and (j) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2025– 0104R1, dated March 19, 2026 (EASA AD 2025–0104R1). (h) Exceptions to EASA AD 2025–0104R1 (1) Where EASA AD 2025–0104R1 refers to May 21, 2025 (the effective date of the original issue of EASA AD 2025–0104, dated May 7, 2025), this AD requires using the effective date of this AD. (2) Where EASA AD 2025–0104R1 refers to May 28, 2024 (the effective date of EASA AD 2023–0111R1, dated May 28, 2024), this AD requires using April 4, 2025 (the effective date of AD 2025–04–05). (3) Where EASA AD 2025–0104R1 refers to June 2, 2023 (the effective date of the original issue of EASA AD 2023–0111, dated May 26, 2023), this AD requires using April 4, 2025 (the effective date of AD 2025–04–05). (4) Where paragraph (19) of EASA AD 2025–0104R1 refers to December 8, 2022 (the effective date of EASA AD 2022–0227, dated November 24, 2022), this AD requires using April 4, 2025 (the effective date of AD 2025– 04–05). (5) Where paragraph (21) of EASA AD 2025–0104R1 refers to December 8, 2022 (the effective date of EASA AD 2022–0227, dated November 24, 2022), this AD requires using July 18, 2023 (the effective date of AD 2023– 11–08, Amendment 39–22454 (88 FR 38384, June 13, 2023)). (6) Where EASA AD 2025–0104R1 refers to September 5, 2022 (the effective date of EASA AD 2022–0181, dated August 29, 2022), this AD requires using September 15, 2022 (the effective date of AD 2022–19–05, Amendment 39–22174 (87 FR 54870, September 8, 2022)). (7) Where EASA AD 2025–0104R1 defines a Serviceable HPV, in part, as ‘‘EBAS HPV, eligible for installation in accordance with Airbus instructions’’, this AD requires replacing that text with ‘‘EBAS HPV eligible for installation’’. (8) Where paragraphs (1), (2), (3), (7), and (29) of EASA AD 2025–0104R1 specify to inform all flightcrews of airplane flight manual (AFM) revisions and dispatch limitations, and thereafter operate the airplane accordingly, this AD does not require those actions, as those actions are already required by existing FAA operating regulations (see 14 CFR 91.9, 91.505, and 121.137 for AFM requirements and 14 CFR 121.628(a)(2) and (5) for minimum equipment list requirements). (9) Where paragraph (20) of EASA AD 2025–0104R1 specifies ‘‘as required by paragraph (17) of the original issue of this AD’’, this AD requires replacing that text with ‘‘as required by AD 2025–04–05 as specified in paragraph (17) of EASA AD 2023–0111R1’’. (10) Where paragraph (30) of EASA AD 2025–0104R1 specifies ‘‘Modification of both EBAS HPV’’, this AD requires replacing that text with ‘‘Modification or replacement of both affected HPVs’’. (11) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0104R1. (i) Credit for Previous Actions Replacing both affected HPVs with non- affected HPVs having part number 71070A030001 before the effective date of this AD using Airbus Aircraft Maintenance Manual (AMM) Tasks 36–11–51–000–806 and 36–11–51–400–806 may be accomplished in lieu of modifying both affected HPVs, as specified in paragraph (30) of EASA AD 2025–0104R1. (j) No Reporting Requirement Although the material referenced in EASA AD 2025–0104R1 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (k) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, AIR–520, Continued Operational Safety 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 manager of the Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (l)(1) of this AD and email to: 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 2025–04–05 are approved as AMOCs for the corresponding provisions of EASA AD 2025– 0104R1 that are required by paragraph (g) 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, AIR–520, Continued Operational Safety 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 paragraphs (j) and (k)(2) of this AD, if any material referenced in EASA AD 2025–0104R1 contains paragraphs that are labeled as RC, the instructions in RC paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended. The instructions in paragraphs, including subparagraphs under those paragraphs, 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC. (l) Additional Information (1) For more information about this AD, contact Rochelle Montgomery, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 405–551– 0414; email: Rochelle.Montgomery@faa.gov. (2) For Airbus SAS material identified in this AD that is not incorporated by reference, 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; website airbus.com . (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0104R1, dated March 19, 2026. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu. You may find this material on the EASA website at 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 at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on October 9, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–21331 Filed 10–16–26; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:15 Oct 16, 2026 Jkt 271001 PO 00000 Frm 00072 Fmt 4700 Sfmt 9990 E:\FR\FM\19OCR1.SGM 19OCR1 lotter on DSK8BHNXB4PROD with RULES1