AD 2026-17-51

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

55447 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations SUPPLEMENTARY INFORMATION : Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments using a method listed under ADDRESSES . Include ‘‘Docket No. FAA–2026–8788; Project Identifier MCAI–2026–00842–R’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to David Wilson, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued Emergency AD 2026– 17–51, dated August 11, 2026 (Emergency AD 2026–17–51) (also referred to as the emergency AD), to address an unsafe condition on certain Bell Textron Canada Limited Model 222 helicopters. The FAA sent the emergency AD to all known U.S. owners and operators of these helicopters. The emergency AD requires removing tail rotor pitch horn part number (P/N) 222– 012–774–109 and associated tail rotor pitch links from service and installing tail rotor pitch horn P/N 222–012–705– 105 or P/N 222–012–705–107 and associated tail rotor pitch links as its replacement. The emergency AD also prohibits installing tail rotor pitch horn P/N 222–012–774–109 on any helicopter. Emergency AD 2026–17–51 was prompted by Transport Canada Emergency AD CF–2026–39, dated August 10, 2026 (Transport Canada Emergency AD CF–2026–39) (also referred to as the MCAI), issued by Transport Canada, which is the aviation authority for Canada, to correct an unsafe condition on certain Bell Textron Canada Limited Model 222 helicopters. The MCAI states a report was received of in-flight fatigue failure of a tail rotor pitch horn due to higher stresses induced at certain critical locations on the pitch horn tangs leading to premature fatigue cracking. The FAA is issuing this AD to address undetected cracks, remove affected tail rotor pitch horns and associated tail rotor pitch links from service, and prohibit installation of the affected tail rotor pitch horns on any helicopter. The unsafe condition, if not addressed, could lead to failure of the tail rotor pitch horn and secondary tail rotor hub components, which could result in loss of control of the helicopter. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2026–8788. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed Transport Canada Emergency AD CF–2026–39, which specifies procedures for removing tail rotor pitch horn P/N 222–012–774–109 and associated tail rotor pitch links from service and installing tail rotor pitch horn P/N 222–012–705–105 or P/N 222– 012–705–107 and associated tail rotor pitch links as its replacement. Transport Canada Emergency AD CF–2026–39 also prohibits installing tail rotor pitch horn P/N 222–012–774–109 on any helicopter. 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. FAA’s Determination These products have been approved by the civil aviation authority (CAA) 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 is issuing this AD after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. AD Requirements This AD requires accomplishing the actions specified in Transport Canada Emergency AD CF–2026–39, described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some CAA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, Transport Canada Emergency AD CF– 2026–39 is incorporated by reference in this AD. This AD requires compliance with Transport Canada Emergency AD CF–2026–39 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this AD. Material required by Transport Canada Emergency AD CF–2026–39 for compliance will be available at regulations.gov under Docket No. FAA– 2026–8788 after this AD is published. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq. ) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules effective in less than thirty days, upon a finding of good cause. An unsafe condition exists that required the immediate adoption of Emergency AD 2026–17–51, issued on August 11, 2026, to all known U.S. owners and operators of these helicopters. The FAA found that the risk to the flying public justified forgoing notice and comment prior to adoption of this rule because the tail rotor pitch horn is a critical flight control VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1

55448 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations component. The FAA has received a report of in-flight fatigue failure of a tail rotor pitch horn due to premature fatigue cracking which resulted in an accident. The FAA has no information pertaining to the extent of cracking on tail rotor pitch horns, which if not addressed, could lead to failure of the tail rotor pitch horn and secondary tail rotor hub components, which could result in loss of control of the helicopter. In addition, the affected parts must be removed from the helicopter before further flight. This compliance time is shorter than the time necessary for the public to comment and for the publication of the final rule. These conditions still exist, therefore, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C. 553(b). In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forego notice and comment. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Interim Action The FAA considers that this AD is an interim action. If final action is later identified, the FAA might consider additional rulemaking. Costs of Compliance The FAA estimates that this AD affects 15 helicopters 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 Verify tail rotor pitch horn part number ........... 1 work-hours × $85 per hour = $85 ............... $0 $85 $1,275 The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the part number verification. The agency has no way of determining the number of helicopters that might need this replacement: O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per product Remove affected tail rotor pitch horn and associated tail rotor pitch links and install serviceable tail rotor pitch horn and associated tail rotor pitch links. 2 work-hours × $85 per hour = $170 ................................. $13,730 $13,900 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, and (2) Will not affect intrastate aviation in Alaska. 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: 2026–17–51 Bell Textron Canada Limited: Amendment 39–23453; Docket No. FAA–2026–8788; Project Identifier MCAI–2026–00842–R. (a) Effective Date The FAA issued Emergency Airworthiness Directive (AD) 2026–17–51 on August 11, 2026 (also referred to as the emergency AD), directly to affected owners and operators. As a result of such actual notice, that emergency AD was effective for those owners and operators on the date it was received. This AD contains the same requirements as the emergency AD and, for those who did not receive actual notice, is effective on September 14, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Bell Textron Canada Limited Model 222 helicopters, certificated in any category, as identified in Transport Canada Emergency AD CF–2026–39, dated VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1

55449 Federal Register / Vol. 91, No. 166 / Friday, August 28, 2026 / Rules and Regulations August 10, 2026 (Transport Canada Emergency AD CF–2026–39). (d) Subject Joint Aircraft System Component (JASC) Code 6400, Tail rotor system. (e) Unsafe Condition This AD was prompted by a report of in- flight fatigue failure of a tail rotor pitch horn. The FAA is issuing this AD to address undetected cracks, remove affected tail rotor pitch horns and associated tail rotor pitch links from service, and prohibit installation of the affected tail rotor pitch horns. The unsafe condition, if not addressed, could lead to failure of the tail rotor pitch horns and secondary tail rotor hub components, which could result in loss of control of the helicopter. (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, Transport Canada Emergency AD CF–2026–39. (h) Exceptions to Transport Canada Emergency AD CF–2026–39 (1) Where Transport Canada Emergency AD CF–2026–39 specifies ‘‘before next flight after the effective date of this AD’’, this AD requires replacing that text with ‘‘before further flight after the effective date of this AD’’. (2) Where the material referenced in Transport Canada Emergency AD CF–2026– 39 specifies discarding parts, this AD requires removing those parts from service. (3) Where the material referenced in Transport Canada Emergency AD CF–2026– 39 specifies to make an entry in the helicopter logbook and historical service records indicating compliance with the referenced service material, this AD does not require those actions because those actions are already required in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, or 135.439. (i) No Reporting Requirement Although the material referenced in Transport Canada Emergency AD CF–2026– 39 specifies to submit certain information to the manufacturer, this AD does not require that action. (j) Special Flight Permits Special flight permits, as described in 14 CFR 21.197 and 21.199, are not allowed. (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 responsible Flight Standards 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 David Wilson, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222– 5786; email: david.wilson@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) Transport Canada Emergency AD CF– 2026–39, dated August 10, 2026. (ii) [Reserved] (3) 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. (4) You may view this material at 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 20, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026–17615 Filed 8–26–26; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–4647; Project Identifier MCAI–2025–01212–R; Amendment 39–23450; AD 2026–17–07] RIN 2120–AA64 Airworthiness Directives; Leonardo S.p.A. Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.A. Model A109A, A109A II, A109C, A109K2, A109E, A119, and AW119 MKII helicopters; and certain Model A109S and AW109SP helicopters. This AD was prompted by a report of an incorrectly installed swashplate duplex bearing (bearing). This AD requires a one-time inspection of the bearing and depending on the result, corrective action. This AD also prohibits the installation of an affected bearing unless certain requirements are met. 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–2026–4647; 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, 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–2026–4647. FOR FURTHER INFORMATION CONTACT : Evan Weaver, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 518– 9297; email: evan.weaver@faa.gov . SUPPLEMENTARY INFORMATION : VerDate Sep<11>2014 15:59 Aug 27, 2026 Jkt 268001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1 lotter on DSK8BHNXB4PROD with RULES1