AD 2026-13-09

This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Rules and Regulations Federal Register 38991 Vol. 91, No. 123 Monday, June 29, 2026 DEPARTMENT OF THE TREASURY Office of the Comptroller of the Currency 12 CFR Parts 34 and 160 [Docket ID OCC–2025–0736] RIN 1557–AF46 Real Estate Lending Escrow Accounts In rule document 2026–10036 beginning on page 29340 in the issue of Tuesday, May 19, 2026, make the following correction: On page 29340, in the first column, the heading should read as set forth above. [FR Doc. C1–2026–10036 Filed 6–26–26; 8:45 am] BILLING CODE 0099–10–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2026–4665; Project Identifier MCAI–2026–00553–E; Amendment 39–23391; AD 2026–13–09] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. Engines AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) Model PW210A, PW210A1, and PW210S engines. This AD was prompted by reports of circumferential cracks found at the turbine exhaust frame external surface caused by thermal stress from engine starts. This AD requires repetitive visual inspections of the turbine exhaust frame for cracks and, depending on the results of the inspections, replacement of the turbine exhaust frame. 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. The FAA must receive comments on this AD by August 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–2026–4665; 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. You may find the Transport Canada material on the Transport Canada website at tc.canada.ca/en/aviation. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. 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– 2026–4665. FOR FURTHER INFORMATION CONTACT : Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7146; email: barbara.caufield@ faa.gov. 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 the ADDRESSES section. Include ‘‘Docket No. FAA–2026–4665; Project Identifier MCAI–2026–00553–E’’ 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 Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. VerDate Sep<11>2014 16:37 Jun 26, 2026 Jkt 268001 PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 E:\FR\FM\29JNR1.SGM 29JNR1 lotter on DSK8BHNXB4PROD with RULES1

38992 Federal Register / Vol. 91, No. 123 / Monday, June 29, 2026 / Rules and Regulations Background Transport Canada, which is the aviation authority for Canada, has issued Transport Canada AD CF–2026– 23, dated May 29, 2026 (Transport Canada AD CF–2026–23) (also referred to as the MCAI), to correct an unsafe condition on P&WC Model PW210A, PW210A1, and PW210S engines. The MCAI states that operators reported circumferential cracks at the turbine exhaust frame external surface. A manufacturer investigation revealed that the cracks originated from a turbine exhaust frame wall found below the minimum required thickness, with subsequent crack initiation and growth caused by thermal stress from engine starts. To address this unsafe condition, the manufacturer published service material that specifies procedures for repetitive visual inspections of the turbine exhaust frame. This condition, if not addressed, could result in turbine exhaust frame failure, which could lead to loss of axial containment, release of parts, and damage to the helicopter. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2026–4665. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed Transport Canada AD CF–2026–23, which specifies procedures for repetitive visual inspections of the turbine exhaust frame for cracks and replacement of the turbine exhaust frame. 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 AD CF–2026–23, described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD. Interim Action The FAA considers this AD to be an interim action. If final action is later identified, the FAA might consider further rulemaking. 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 AD CF–2026–23 is incorporated by reference in this AD. This AD requires compliance with Transport Canada AD CF–2026–23 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 AD CF–2026–23 for compliance will be available at regulations.gov under Docket No. FAA–2026–4665 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 requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies forgoing notice and comment prior to adoption of this rule because multiple circumferential cracks at the turbine exhaust frame external surface have been reported, and investigation revealed that the cracking was associated with thermal stress linked to engine starts. Crack propagation of the turbine exhaust frame could result in turbine exhaust frame failure, which could lead to loss of axial containment, release of parts, and damage to the helicopter. At this time, the growth rate of the turbine exhaust frame cracking has not been determined. For these reasons, on certain helicopters, the initial actions required by this AD must be accomplished within 5 hours time-in- service or 20 engine starts after the effective date of this AD, whichever occurs first. The compliance time in this AD is shorter than the time necessary for the public to comment and for publication of the final rule. Accordingly, 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 forgo 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 the FAA has determined that it has good cause to adopt this rule without prior notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 48 engines 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 Visual inspection of turbine exhaust frame ...... .50 work-hours × $85 per hour = $85 .............. $0 $42.50 $2,040 VerDate Sep<11>2014 16:37 Jun 26, 2026 Jkt 268001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\29JNR1.SGM 29JNR1 lotter on DSK8BHNXB4PROD with RULES1

38993 Federal Register / Vol. 91, No. 123 / Monday, June 29, 2026 / Rules and Regulations The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The agency has no way of determining the number of engines that might need these replacements: O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per product Replacement of turbine exhaust frame .......................... 9 work-hours × $85 per hour = $765 ............................. $125,000 $125,765 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: 2026–13–09 Pratt & Whitney Canada Corp.: Amendment 39–23391; Docket No. FAA–2026–4665; Project Identifier MCAI–2026–00553–E. (a) Effective Date This airworthiness directive (AD) is effective July 14, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Pratt & Whitney Canada Corp. (P&WC) Model PW210A, PW210A1, and PW210S engines. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by reports of circumferential cracks found at the turbine exhaust frame external surface caused by thermal stress from engine starts. The FAA is issuing this AD to prevent failure of the turbine exhaust frame. The unsafe condition, if not addressed, could result in turbine exhaust frame failure, which could lead to loss of axial containment, release of parts, and damage to the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition For the purpose of this AD, an ‘‘engine start’’ includes the start of an engine for any reason, even if it is not followed by a flight. (h) Required Actions Except as specified in paragraphs (i) and (j) of this AD: Perform all required actions within the compliance times specified in, and in accordance with, Transport Canada AD CF–2026–23, dated May 29, 2026 (Transport Canada AD CF–2026–23). (i) Exceptions to Transport Canada AD CF– 2026–23 (1) Where Transport Canada AD CF–2026– 23 refers to its effective date, this AD requires using the effective date of this AD. (2) Where Transport Canada AD CF–2026– 23 requires compliance in terms of hours air time, this AD requires using hours time-in- service. (j) No Reporting Requirement Although the service material referenced in Transport Canada AD CF–2026–23 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (k) 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the AIR–520 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (l) 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 local flight standards district office/ certificate holding district office. (l) Additional Information For more information about this AD, contact Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7146; email: barbara.caufield@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) 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 AD CF–2026–23, dated May 29, 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. You may find the Transport Canada material on the VerDate Sep<11>2014 16:37 Jun 26, 2026 Jkt 268001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\29JNR1.SGM 29JNR1 lotter on DSK8BHNXB4PROD with RULES1

38994 Federal Register / Vol. 91, No. 123 / Monday, June 29, 2026 / Rules and Regulations Transport Canada website at tc.canada.ca/ en/aviation. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. 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 June 24, 2026. Lona C. Saccomando, Acting Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2026–13058 Filed 6–25–26; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–5026; Project Identifier MCAI–2024–00168–R; Amendment 39–23382; AD 2026–12–12] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160–B helicopters. This AD was prompted by a discovery during a maintenance operation that several self-locking nuts of the window jettisoning system could be loosened by hand due to a non- conformity in certain cable kits. This AD requires modifying each affected window into a serviceable window. This AD also prohibits installing an affected window or an affected door on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective August 3, 2026. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 3, 2026. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2025–5026; 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 the EASA 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–2025–5026. FOR FURTHER INFORMATION CONTACT : Eric Rivera, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (773) 412– 9048; email: eric.rivera01@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 all Airbus Helicopters Model H160–B helicopters. The NPRM was published in the Federal Register on November 20, 2025 (90 FR 52264). The NPRM was prompted by EASA AD 2024–0063, dated March 7, 2024 (EASA AD 2024–0063) (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 maintenance operation, several self-locking nuts of the window jettisoning system could be loosened by hand. The MCAI further states that the function of these nuts is to hold the threaded axis and the associated cable tightly together, as part of the passenger window jettisoning system. The MCAI also states that certain cable kits which are part of the window jettisoning system may not be in conformance with applicable specifications. In the NPRM, the FAA proposed to require modifying each affected window into a serviceable window. The NPRM also proposed to prohibit installing an affected window or an affected door on any helicopter. The FAA is issuing this AD to prevent failure of the jettisoning function of the window which, if not addressed, could result in the inability to evacuate helicopter occupants during an emergency situation. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2025–5026. Discussion of Final Airworthiness Directive Comments The FAA received comments from the Citizens Rulemaking Alliance. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Justify Forgoing Notice and Comment or Issue an NPRM The Citizens Rulemaking Alliance requested that the FAA either provide its justification for finding good cause to bypass notice and comment procedures, convert this action to an NPRM, or at a minimum reopen the comment period to allow comments. The commenter asserted the FAA has not adequately justified use of the good cause exemption to bypass notice and comment and the 30-day delayed effective date. The FAA notes the comment was submitted in response to an NPRM for which the FAA provided a 45-day comment period. This final rule is effective 35 days after its publication in the Federal Register . Therefore, no change to this AD is necessary. Request To Consider Impact on Small Entities The Citizens Rulemaking Alliance requested the FAA to either supplement the docket with a factual basis that complies with the Regulatory Flexibility Act (RFA) or withdraw the certification and conduct an initial regulatory flexibility analysis. The commenter stated that the analysis should consider the costs related to parts, labor, aircraft downtime, and the impact on small entities, and should involve reopening the comment period. Furthermore, the commenter asked the FAA to explore less burdensome options for small operators, such as implementing phased inspection intervals, extending compliance periods, granting credit for previous actions, and providing alternative methods of compliance (AMOC) templates. The FAA has considered the AD’s impact on small entities and provides the following factual basis for its RFA certification. The Regulatory Flexibility Act of 1980, Public Law 96–354, 94 Stat. 1164 (5 U.S.C. 601–612), as amended by the Small Business Regulatory Enforcement VerDate Sep<11>2014 16:37 Jun 26, 2026 Jkt 268001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\29JNR1.SGM 29JNR1 lotter on DSK8BHNXB4PROD with RULES1