AD 2026-12-04

34750 Federal Register / Vol. 91, No. 110 / Tuesday, June 9, 2026 / Rules and Regulations (4) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find the EASA material on the EASA website at ad.easa.europa.eu. (5) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 10101 Hillwood Parkway, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (6) 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 June 3, 2026. Paul R. Bernado, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–11560 Filed 6–8–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–3475; Project Identifier MCAI–2025–01561–T; Amendment 39–23374; AD 2026–12–04] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 airplanes. This AD was prompted by a manufacturing investigation that found improper application of the fastener retorque process at the center wing box (CWB) and belly fairing (BF) junctions could lead to insufficient clamping. This AD requires replacing each affected part and applying additional head nut cap protection. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 14, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 14, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–3475; 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–2026–3475. FOR FURTHER INFORMATION CONTACT : Anthony DeCaro, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 562– 627–5374; email: anthony.d.decaro@ faa.gov. SUPPLEMENTARY INFORMATION : Background The 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 airplanes. The NPRM was published in the Federal Register on April 3, 2026 (91 FR 16867). The NPRM was prompted by EASA AD 2025–0209, dated September 24, 2025 (EASA AD 2025–0209) (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 that during manufacturing investigation of an early production A350–941 airplane, it was found that improper application of the fastener retorque process at the CWB and BF junctions could lead to insufficient clamping. Fasteners with part number EN6115 code B were particularly susceptible to rotation, and if not torqued correctly, could potentially compromise structural integrity and compliance with the electromagnetic hazard requirements of the airplane. This condition, if not corrected, could, in the case of a fuel leak, create a source of ignition, possibly resulting in an uncontrolled fire. In the NPRM, the FAA proposed to require replacing affected fasteners installed on the left-hand (LH) and right-hand (RH) sides of the CWB and BF junctions and applying additional head nut cap protection, as specified in EASA AD 2025–0209. 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–2026–3475. Discussion of Final Airworthiness Directive Comments The FAA received a comment from the Air Line Pilots Association, International (ALPA) that they supported the NPRM. 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, 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 2025–0209 specifies procedures for replacing affected fasteners installed on the LH and RH sides of the CWB and BF junctions and applying additional head nut cap protection. 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 affects 2 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 15:59 Jun 08, 2026 Jkt 268001 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1 lotter on DSK8BHNXB4PROD with RULES1

34751 Federal Register / Vol. 91, No. 110 / Tuesday, June 9, 2026 / Rules and Regulations E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 68 work hours × $85 per hour = $5,780 Up to $940 .............................. Up to $6,720 ........................... Up to $13,440. 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 adding the following new airworthiness directive: 2026–12–04 Airbus SAS: Amendment 39– 23374; Docket No. FAA–2026–3475; Project Identifier MCAI–2025–01561–T. (a) Effective Date This airworthiness directive (AD) is effective July 14, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A350–941 airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2025– 0209, dated September 24, 2025 (EASA AD 2025–0209). (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a manufacturing investigation that found improper application of the fastener retorque process at the center wing box (CWB) and belly fairing (BF) junctions could lead to insufficient clamping. The FAA is issuing this AD to address improperly torqued fasteners that could lead to insufficient clamping and potentially compromise the airplane’s structural integrity and compliance with electromagnetic hazard requirements. The unsafe condition, if not addressed, could, in case of a fuel leak, create a source of ignition and possibly result in an uncontrolled fire. (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, EASA AD 2025–0209. (h) Exceptions to EASA AD 2025–0209 (1) Where EASA AD 2025–0209 refers to its effective date, this AD requires using the effective date of this AD. (2) Where the definition of ‘‘Affected parts’’ in EASA AD 2025–0209 specifies ‘‘as specified in the SB’’, this AD requires replacing that text with ‘‘as specified in Airbus Service Bulletin A350–57–P093, dated June 17, 2025’’. (3) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0209. (i) 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 (j) 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 (i)(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. (j) Additional Information For more information about this AD, contact Anthony DeCaro, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 562–627–5374; email: anthony.d.decaro@faa.gov. (k) 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. VerDate Sep<11>2014 15:59 Jun 08, 2026 Jkt 268001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1 lotter on DSK8BHNXB4PROD with RULES1

34752 Federal Register / Vol. 91, No. 110 / Tuesday, June 9, 2026 / Rules and Regulations (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 2025–0209, dated September 24, 2025. (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 June 4, 2026. Brian Knaup, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–11511 Filed 6–8–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–2715; Project Identifier MCAI–2025–01779–A; Amendment 39–23371; AD 2026–12–01] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC– 12/47E airplanes. This AD was prompted by a report of the stall warning protection system (SWPS) engaging when not appropriate. This AD requires updating operational software and incorporating a pilot’s operating handbook (POH) temporary revision (TR). This AD also prohibits the installation of affected software. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 14, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 14, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–2715; 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; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: 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, 1100 Main, Kansas City, MO 64105. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2026–2715. FOR FURTHER INFORMATION CONTACT : Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329–4059; email: doug.rudolph@ faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Pilatus Model PC–12/ 47E airplanes. The NPRM was published in the Federal Register on March 19, 2026 (91 FR 13240). The NPRM was prompted by AD 2025–0271, dated December 2, 2025 (EASA AD 2025–0271) (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 that during a test flight on a Pilatus Model PC–12/47E airplane in which the airplane flew specific maneuvers where gravitational loads (g-loads) were close to 0 g, during landing with flaps at 40 degrees, the SWPS triggered at a higher- than-expected airspeed, including the aural warning, stick shaker, and stick pusher. This same software is on the delivered airplanes that are affected by this AD. This condition, if not addressed, could result in reduced safety margins of the airplane, increased pilot workload, and reduced control of the airplane. In the NPRM, the FAA proposed to require updating operational software and incorporating a POH TR. The NPRM also proposed to prohibit the installation of affected software, as specified in EASA AD 2025–0271. 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–2026–2715. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. 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. This AD is adopted as proposed in the NPRM. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2025– 0271, which specifies procedures for updating the Honeywell Primus APEX operational software, and for incorporating Pilatus PC–12/47E POH TR No. 32 into the POH. EASA AD 2025–0271 also allows for the incorporation of a later POH revision that includes the same POH amendment content and prohibits the installation of affected software. 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 affects 265 airplanes of U. S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 15:59 Jun 08, 2026 Jkt 268001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\09JNR1.SGM 09JNR1 lotter on DSK8BHNXB4PROD with RULES1