AD 2026-15-12

55444 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations (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 AD 2025–0051R1, dated May 7, 2025 (EASA AD 2025–0051R1). (h) Exceptions to EASA AD 2025–0051R1 (1) Where EASA AD 2025–0051R1 refers to March 14, 2025 (the effective date of EASA AD 2025–0051, dated February 28, 2025), this AD requires using the effective date of this AD. (2) Where the definition of affected part in EASA AD 2025–0051R1 refers to ‘‘the ASB’’, for this AD, replace that text with ‘‘the applicable original issue of the alert service bulletins listed in Ref. Publications’’. (3) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0051R1. (i) No Reporting or Returning of Parts Although the material referenced in EASA AD 2025–0051R1 specifies submitting certain information and returning parts to the manufacturer for rework, this AD does not require those actions. (j) Special Flight Permits Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished provided that the rescue hoist is not used. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, 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 manager of the International Validation Branch, send it to the attention of the person identified in paragraph (l) of this AD and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (l) Additional Information For more information about this AD, contact Adam Hein, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946– 4116; email: adam.hein@faa.gov. (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 the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0051R1, dated May 7, 2025. (ii) [Reserved] (3) 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. (4) 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. (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 August 14, 2026. Paul R. Bernado, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–17583 Filed 8–27–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–0018; Project Identifier MCAI–2025–01384–A; Amendment 39–23424; AD 2026–15–12] 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 that the emergency exit door could not be opened from inside an airplane. This AD requires modification of the passenger service unit (PSU) trim panel if dual lock fastener tapes are not installed. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective October 2, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 2, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–0018; 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–2026–0018. 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 airplanes. The NPRM was published in the Federal Register on January 21, 2026 (91 FR 2512). The NPRM was prompted by EASA AD 2025–0182, dated August 25, 2025 (EASA AD 2025– 0182) (also referred to as the MCAI), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition on certain Pilatus Model PC– 12/47E airplanes. The MCAI states there was a report that the emergency exit door could not be opened from inside an airplane. Further investigation revealed that incorrect installation of the PSU trim panel, which is installed above the emergency exit door, could block the opening of the emergency exit if the PSU trim panel is positioned too far inboard. In the NPRM, the FAA proposed to require a visual inspection of the PSU trim panel for dual lock fastener tapes and modification if dual lock fastener VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1

55445 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations tapes are not installed. The NPRM also proposed to prohibit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products. The FAA issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Pilatus Model PC–12/47E airplanes. The SNPRM was published in the Federal Register on May 15, 2026 (91 FR 27878). The SNPRM was prompted by the FAA’s determination that the applicability of the NPRM referenced the incorrect airplane model. In the SNPRM, the FAA proposed to revise the NPRM to correct the affected airplane from Model PC–12 to Model PC–12/47E. 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–2026–0018. Discussion of Final Airworthiness Directive Comments The FAA received a comment from the Air Line Pilots Association, International. The commenter supported the SNPRM without change. Changes to Final Rule Since Issuance of the SNPRM Since issuance of the SNPRM, the FAA has determined that the inspection proposed in the SNPRM is not necessary and the reference to the instructions in the definition of ‘‘Affected part’’ in EASA AD 2025–0182 is adequate. This change also affects the Costs of Compliance section. 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 SNPRM. None of the changes will increase the economic burden on any operator. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2025– 0182, which specifies procedures for modifying the PSU trim panel if dual lock fastener tapes are not installed. EASA AD 2025–0182 also prohibits the installation of an affected part. EASA AD 2025–0182 also refers to instructions to determine whether dual lock fastener tapes are installed on a PSU trim panel. 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 276 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Modify PSU trim panel ........................................... 2 work-hours × $85 per hour = $170 .................... $100 $270 $74,520 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. 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: 2026–15–12 Pilatus Aircraft Ltd.: Amendment 39–23424; Docket No. FAA–2026–0018; Project Identifier MCAI–2025–01384–A. (a) Effective Date This airworthiness directive (AD) is effective October 2, 2026. (b) Affected ADs None. VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1

55446 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations (c) Applicability This AD applies to Pilatus Aircraft Ltd. Model PC–12/47E airplanes, manufacturer serial numbers 2001 through 2999, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 2500, Cabin Equipment/Furnishings. (e) Unsafe Condition This AD was prompted by a report that the emergency exit door could not be opened from inside an airplane. The FAA is issuing this AD to prevent the passenger service unit (PSU) trim panel from blocking the opening of the emergency exit. The unsafe condition, if not addressed, could prevent the opening of the emergency door, which could result in injury to occupants during an emergency evacuation. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions 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 AD 2025–0182, dated August 25, 2025 (EASA AD 2025–0182). (h) Exceptions to EASA AD 2025–0182 (1) Where EASA AD 2025–0182 refers to its effective date, this AD requires using the effective date of this AD. (2) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2025–0182. (i) No Reporting Requirement Although the material referenced in EASA AD 2025–0182 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, 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 International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD and email to: AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office/ certificate holding district office. (k) Additional Information For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (816) 329– 4059; email: doug.rudolph@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 the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2025–0182, dated August 25, 2025. (ii) [Reserved] (3) 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 this EASA AD on the EASA website at ad.easa.europa.eu. (4) 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. (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 August 26, 2026. Christopher R. Parker, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–17639 Filed 8–27–26; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–8788; Project Identifier MCAI–2026–00842–R; Amendment 39–23453; AD 2026–17–51] RIN 2120–AA64 Airworthiness Directives; Bell Textron Canada Limited Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 222 helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of in-flight fatigue failure of a tail rotor pitch horn. This AD requires removing the affected tail rotor pitch horn and associated tail rotor pitch links from service and installing a serviceable tail rotor pitch horn and associated tail rotor pitch links. This AD also prohibits installing an affected tail rotor pitch horn on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective September 14, 2026. Emergency AD 2026–17–51, issued on August 11, 2026, which contains the requirements of this amendment, was effective with actual notice. The Director of the Federal Register approved the incorporation by reference of a certain publication identified in this AD as of September 14, 2026. The FAA must receive comments on this AD by October 13, 2026. ADDRESSES : You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2026–8788; 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 street address for Docket Operations is listed above. Material Incorporated by Reference: • For Transport Canada material identified in this AD, contact Transport Canada, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, Canada; phone: (888) 663–3639; email: tc.airworthinessdirectives- consignesdenavigabilite.tc@tc.gc.ca; website: tc.canada.ca/en/aviation. • 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. It is also available at regulations.gov under Docket No. FAA–2026–8788. FOR FURTHER INFORMATION CONTACT : David Wilson, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222– 5786; email: david.wilson@faa.gov. VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1