Airworthiness Directives; Various Helicopters, 6008-6011 [2024-01932]

Download as PDF 6008 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations NRC licensing approval or the acceptability of licensee commitments to these RGs. Although these RGs are withdrawn, current licensees may continue to use them, and withdrawal does not affect any existing licenses or agreements. However, these RGs should not be used in future requests or applications for NRC licensing actions. II. Additional Information As noted in the Federal Register on December 9, 2022 (87 FR 75671), this document is being published in the ‘‘Rules’’ section of the Federal Register to comply with publication requirements under 1 CFR chapter I. III. Submitting Suggestions for Improvement of Regulatory Guides A member of the public may, at any time, submit suggestions to the NRC for improvement of existing RGs or for the development of new RGs. Suggestions can be submitted on the NRC’s public website at https://www.nrc.gov/readingrm/doc-collections/reg-guides/ contactus.html. Suggestions will be considered in future updates and enhancements to the ‘‘Regulatory Guide’’ series. Dated: January 25, 2024. For the Nuclear Regulatory Commission. Meraj Rahimi, Chief, Regulatory Guide and Programs Management Branch, Division of Engineering, Office of Nuclear Regulatory Research. [FR Doc. 2024–01872 Filed 1–30–24; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–0034; Project Identifier AD–2023–01154–Q; Amendment 39–22662; AD 2024–01–11] RIN 2120–AA64 Airworthiness Directives; Various Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all helicopters with certain Pacific Scientific Company rotary buckle assemblies (buckles) installed. This AD was prompted by a report of a manufacturing defect in the screws used inside the buckle. This AD requires inspecting the buckle screws and, lotter on DSK11XQN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 15:52 Jan 30, 2024 Jkt 262001 depending on the results, reidentifying the buckle, replacing the screws and reidentifying the buckle, or replacing the buckle. This AD also prohibits installing certain buckles. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2024. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 15, 2024. The FAA must receive comments on this AD by March 18, 2024. 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–2024–0034; 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, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For service information identified in this final rule, contact Parker Meggitt Services, 1785 Voyager Avenue, Simi Valley, CA 93063; phone: 877–666– 0712; email: TechnicalSupport@ meggitt.com; website: meggitt.com/ services_and_support/customer_ experience/update-on-buckle-assemblyservice-bulletins. • You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N– 321, 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– 2024–0034. FOR FURTHER INFORMATION CONTACT: David Kim, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627– 5274; email: david.kim@faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2024–0034; Project Identifier AD–2023–01154–Q’’ 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 Kim, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627–5274; email: david.kim@faa.gov. 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 has received a report of a manufacturing defect in the screws used inside Pacific Scientific Company buckle part number (P/N) 1111475 (all dash numbers) and P/N 1111548–01. The screws used to fasten the load plate to the body of the buckle were found to be susceptible to hydrogen embrittlement due to improper baking E:\FR\FM\31JAR1.SGM 31JAR1 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations during the electroplating process. This condition leads the screwhead to separate from the body of the screw when under load, which could result in the buckle failing to restrain the occupant to the seat. This issue was originally identified from a suspected lot of screws, Lot 348994–A. Since then, a buckle failed in an accident, calling into question Lot 348601–A. Lots 348601–A and 348994–A were the first two lots of screws received by Pacific Scientific Company from a new supplier and are the only suspected lots. The suspected buckles were manufactured between January 2012 and September 2012. The FAA is issuing this AD to address the unsafe condition on these products. The rotary buckle may be included as a component of a different partnumbered restraint system assembly. Table 1 of Parker Meggitt Service Bulletin (SB) 1111475–25–001–2023, Revision 001, dated December 1, 2023, and Parker Meggitt SB 1111548–25– 001–2023, Revision 001, dated December 1, 2023 (SB 1111475–25–001– 2023 Rev 001 and SB 1111548–25–001– 2023 Rev 001), includes a list of these restraint system assembly P/Ns. This AD applies to all helicopters with a Pacific Scientific Company buckle P/N 1111475 (all dash numbers) or P/N 1111548–01 installed, if the buckle was manufactured between January 2012 and September 2012, or if the date of manufacture of the buckle is unknown. These same part-numbered buckles may also be installed in airplanes; however, the FAA determined that a longer compliance time to accomplish the required actions is allowable for buckles installed in airplanes. Accordingly, the FAA plans to publish a separate notice of proposed rulemaking to address all airplanes with a Pacific Scientific Company buckle P/ N 1111475 (all dash numbers) or P/N 1111548–01 installed. lotter on DSK11XQN23PROD with RULES1 FAA’s Determination The FAA is issuing this AD because the agency has determined the unsafe condition described previously is likely to exist or develop on other helicopters with a restraint system with a buckle as part of their type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed SB 1111475–25– 001–2023 Rev 001 for buckle P/N 1111475 and SB 1111548–25–001–2023 Rev 001 for buckle P/N 1111548–01. This service information specifies procedures for inspecting the buckle for any missing or loose screw heads and, depending on the results, replacing the VerDate Sep<11>2014 15:52 Jan 30, 2024 Jkt 262001 buckle and sending the removed buckle to Parker Meggitt for repair or replacement. If after that first inspection, all of the screw heads are intact, this service information specifies procedures for inspecting the buckle for any Torx head screws (alloy steel) and, depending on the results, allowing the buckle assembly to remain in-service temporarily, replacing any Torx head screws (alloy steel) with new hex head screws (stainless steel), and checking the functionality of the buckle. This service information also specifies procedures for removing a buckle from a restraint system, installing a buckle on a restraint system, and returning buckles to Parker Meggitt. If the buckle passes the specified inspections or is modified by replacing Torx head screws (alloy steel) with new hex head screws (stainless steel) screws, this service information specifies procedures for reidentifying the back of the buckle. This service information also identifies known affected restraint systems. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. AD Requirements This AD requires accomplishing the actions specified in the service information already described, except as discussed under ‘‘Differences Between this AD and the Service Information.’’ Differences Between This AD and the Service Information The service information does not specify any compliance times, whereas this AD requires accomplishing the required actions within three months. This AD also prohibits installing an affected buckle on any helicopter as of the effective date of this AD. The service information specifies sending any damaged buckles to Parker Meggitt for repair or replacement, and this AD does not. Instead, this AD requires replacing the buckle with an airworthy buckle. The service information allows buckles with a Torx head (alloy steel) screw to remain in service temporarily and be replaced at a time convenient to the operator, and this AD does not. If a buckle has any number of Torx head (alloy steel) screws installed, this AD requires replacing all four screws with hex head screws before further flight. If a screw head breaks off during disassembly of a buckle or if reassembly of a buckle is not possible, the service information specifies returning the buckle to Parker Meggitt, whereas this AD does not. If a screw head breaks off PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 6009 during disassembly, this AD requires replacing the buckle with an airworthy buckle. If reassembly of a buckle is not possible, then the buckle is not airworthy. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(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 in an otherwise survivable accident, hard landing, or severe turbulence, the buckle may fail to restrain the occupant. Based on the rotorcraft accident rate, coupled with not knowing the propagation rate of this unsafe condition into failure, the FAA determined that the compliance time to inspect affected buckles installed in helicopters must be within three months. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(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 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 approximately 11,714 buckles installed on restraint systems in aircraft worldwide. The FAA has no way of knowing the number of helicopters of E:\FR\FM\31JAR1.SGM 31JAR1 6010 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations U.S. Registry that may have a restraint system with an affected buckle installed. The estimated costs on U.S. operators reflects the maximum possible costs based on affected buckles installed on restraint systems in aircraft worldwide. Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates that operators may incur the following costs in order to comply with this AD. Inspecting a buckle will take approximately 0.1 work-hour for an estimated cost of $9 per buckle and up to $105,426 for the U.S. fleet. If required, replacing a set of screws (four) will take approximately 0.5 work-hour and parts will cost a nominal amount for an estimated cost of $43 per buckle. Replacing a buckle will take approximately 0.5 work-hour and parts will cost approximately $740 for an estimated cost of $783 per buckle. The FAA estimates a nominal cost for reidentifying a buckle. 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, thereby reducing the cost impact on affected operators. lotter on DSK11XQN23PROD with RULES1 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: VerDate Sep<11>2014 15:52 Jan 30, 2024 Jkt 262001 (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: ■ 2024–01–11 Various Helicopters: Amendment 39–22662; Docket No. FAA–2024–0034; Project Identifier AD– 2023–01154–Q. (a) Effective Date This airworthiness directive (AD) is effective February 15, 2024. (b) Affected ADs None. (c) Applicability This AD applies to all helicopters, certified in any category, with a restraint system with a Pacific Scientific Company rotary buckle assembly (buckle) part number (P/N) 1111475 (all dash numbers) or P/N 1111548– 01 installed having a date of manufacture between January 2012 and September 2012 inclusive or an unknown date of manufacture. These buckles may be installed on, but not limited to, Airbus Helicopters model helicopters, 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 of a manufacturing defect in the screws used inside the buckle. The FAA is issuing this AD to prevent cracking and missing screw heads when under load. The unsafe condition, if not addressed, could result in a failure of the buckle to restrain the occupant. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (g) Required Actions (1) For helicopters with buckle P/N 1111475 (all dash numbers), within 3 months after the effective date of this AD, inspect each buckle screw for cracked, loose, and missing screw heads by following the Accomplishment Instructions, paragraphs B.(1) and (2), of Parker Meggitt Service Bulletin (SB) 1111475–25–001–2023, Revision 001, dated December 1, 2023 (SB 1111475–25–001–2023 Rev 001). (i) If any screw has a cracked, loose, or missing screw head, before further flight, replace the buckle with an airworthy buckle. (ii) If none of the four screw heads are cracked, loose, or missing, before further flight, inspect each screw to determine if any screw has a Torx head by using one of the following methods in the Accomplishment Instructions of SB 1111475–25–001–2023 Rev 001: paragraph B.(4)(a) (Magnet Test); paragraph B.(4)(b) (Inspection); or paragraphs C.(2) through (4) (removing the buckle from the restraint system) and paragraphs D.(1)(a) through (d) (disassembling the buckle). Note 1 to paragraph (g)(1): SB 1111475– 25–001–2023 Rev 001 refers to a magnifying glass as an ‘‘eye loupe.’’ (A) If none of the four screws have a Torx head, before further flight, reassemble the buckle (if necessary) by following the Accomplishment Instructions, paragraphs D.(1)(f) through (l), of SB 1111475–25–001– 2023 Rev 001, and reidentify the buckle with ‘‘INS. A’’ by following the Accomplishment Instructions, paragraph B.(6), of SB 1111475– 25–001–2023 Rev 001. (B) If at least one of the four screws has a Torx head, before further flight, with the buckle removed, replace each Torx head screw with a hex head screw, reassemble the buckle, and reidentify the buckle with ‘‘MOD. A’’ by following the Accomplishment Instructions, paragraphs D.(1)(e) through (m), of SB 1111475–25–001–2023 Rev 001, except you are not required to return any parts to Parker Meggitt. If a screw head breaks off during disassembly, before further flight, replace the buckle with an airworthy buckle. (2) For helicopters with buckle P/N 1111548–01, within 3 months after the effective date of this AD, inspect each buckle screw for cracked, loose, and missing screw heads by following the Accomplishment Instructions, paragraph B.(1), of Parker Meggitt SB 1111548–25–001–2023, Revision 001, dated December 1, 2023 (SB 1111548– 25–001–2023 Rev 001). (i) If any screw has a cracked, loose, or missing screw head, before further flight, replace the buckle with an airworthy buckle. (ii) If none of the four screw heads are cracked, loose, or missing, before further flight, inspect each screw to determine which screws have a Torx head by using one of the following methods in the Accomplishment Instructions of SB 1111548–25–001–2023 Rev 001: paragraph B.(3)(a) (except use Figure 6 for placement of the shim tool and use Figure 5 to distinguish the screw head types) (Inspection); or paragraph C. (removing the buckle from the restraint system) and paragraphs D.(1)(a) through (c) (disassembling the buckle). Before further flight, with the buckle removed, replace each Torx head screw with a hex head screw, E:\FR\FM\31JAR1.SGM 31JAR1 Federal Register / Vol. 89, No. 21 / Wednesday, January 31, 2024 / Rules and Regulations reassemble the buckle, and reidentify the buckle with ‘‘MOD. A’’ by following the Accomplishment Instructions, paragraphs D.(1)(d) through (m), of SB 1111548–25–001– 2023 Rev 001, except you are not required to return any parts to Parker Meggitt. If a screw head breaks off during disassembly, before further flight, replace the buckle with an airworthy buckle. Note 2 to paragraph (g)(2): SB 1111548– 25–001–2023 Rev 001 refers to a magnifying glass as an ‘‘eye loupe.’’ (3) As of the effective date of this AD, do not install a buckle identified in paragraph (c) of this AD on any helicopter unless the buckle is marked with ‘‘MOD. A’’ or ‘‘INS. A’’. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, West Certification 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 West Certification Branch, send it to the attention of the person identified in paragraph (i) of this AD. (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. lotter on DSK11XQN23PROD with RULES1 (i) Additional Information For more information about this AD, contact David Kim, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627–5274; email: david.kim@faa.gov. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Parker Meggitt Service Bulletin 1111475–25–001–2023, Revision 001, dated December 1, 2023. (ii) Parker Meggitt Service Bulletin 1111548–25–001–2023, Revision 001, dated December 1, 2023. (3) For service information identified in this AD, contact Parker Meggitt Services, 1785 Voyager Avenue, Simi Valley, CA 93063; phone: 877–666–0712; email: TechnicalSupport@meggitt.com; website: meggitt.com/services_and_support/ customer_experience/update-on-buckleassembly-service-bulletins. (4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N–321, 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, VerDate Sep<11>2014 15:52 Jan 30, 2024 Jkt 262001 visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on January 18, 2024. Victor Wicklund, Deputy Director, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–01932 Filed 1–26–24; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE International Trade Administration 19 CFR Part 356 [Docket No. 231127–0278] RIN 0625–AB20 Procedures and Rules for Article 10.12 of the United States-Mexico-Canada Agreement Enforcement and Compliance, International Trade Administration, Department of Commerce. ACTION: Final rule. AGENCY: The Department of Commerce (Commerce) publishes this action to update and make final an interim final rule that amended its regulations pertaining to the procedures and rules related to Article 1904 of the North American Free Trade Agreement (NAFTA) with appropriate references to the United States-Mexico-Canada Agreement (USMCA), which went into effect on July 1, 2020. Article 10.12 of the USMCA, like NAFTA Article 1904, provides a dispute settlement mechanism for purposes of reviewing antidumping and countervailing duty determinations issued by the United States, Canada, and Mexico. Commerce is amending its regulations to replace references to Article 1904 of NAFTA with references to Article 10.12 of the USMCA; to update outdated crossreferences to Commerce’s antidumping and countervailing duty regulations; update outdated notice, filing, service, and protective order procedures; and adopt other minor corrections and updates. DATES: This final rule is effective 30 days after January 31, 2024. This final rule does not apply to any binational panel review under NAFTA, or any extraordinary challenge arising out of any such review, that was commenced before July 1, 2020. FOR FURTHER INFORMATION CONTACT: Nikki Kalbing, Assistant Chief Counsel, at (202) 482–4343, Spencer Neff, Attorney, at (202) 482–8184, or Scott McBride, Associate Deputy Chief Counsel, at (202) 482–6292. SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 6011 SUPPLEMENTARY INFORMATION: USCMA Background As background, on November 30, 2018, the ‘‘Protocol Replacing the North American Free Trade Agreement with the Agreement Between the United States of America, the United Mexican States, and Canada’’ (the Protocol) was signed to replace the North American Free Trade Agreement (NAFTA). The Agreement Between the United States of America, the United Mexican States (Mexico), and Canada (the USMCA) 1 is attached as an annex to the Protocol and was subsequently amended to reflect certain modifications and technical corrections in the ‘‘Protocol of Amendment to the Agreement Between the United States of America, the United Mexican States, and Canada’’ (the Amended Protocol), which the Office of the United States Trade Representative (USTR) signed on December 10, 2019. The USMCA entered into force on July 1, 2020.2 Article 10.12 of the USMCA, like NAFTA Article 1904, provides a dispute settlement mechanism for purposes of reviewing antidumping and countervailing duty determinations issued by the United States, Canada, and Mexico. The procedures and rules for binational panel review of antidumping and countervailing duty administrative determinations under Article 10.12 of the USMCA are virtually unchanged from Article 1904 of NAFTA. Sections 421–433 and 504 of the USMCA Implementation Act provide 1 The Agreement Between the United States of America, the United Mexican States, and Canada is the official name of the USMCA treaty. Please be aware that, in other contexts, the same document is also referred to as the United States-MexicoCanada Agreement. 2 Mexico, Canada, and the United States certified their preparedness to implement the USMCA on December 12, 2019, March 13, 2020, and April 24, 2020, respectively. Pursuant to section 106 of the Bipartisan Congressional Trade Priorities and Accountability Act of 2015 (19 U.S.C. 4205) and section 151 of the Trade Act of 1974 (19 U.S.C. 2191), the United States adopted the USMCA through the enactment of the United States— Mexico—Canada Agreement Implementation Act (USMCA Implementation Act), Public Law 116– 113, 134 Stat. 11 (19 U.S.C. Chapter 29), on January 29, 2020. Pursuant to paragraph 2 of the Protocol, which provides that the USMCA will take effect on the first day of the third month after the last signatory party provides written notification of the completion of the domestic implementation of the USMCA through the enactment of implementing legislation, the USMCA entered into force on July 1, 2020. On December 27, 2020, subsequent to the USMCA’s entry into force date of July 1, 2020, the Consolidated Appropriations Act, 2021 (Appropriations Act), Public Law 116–260, was enacted with Title VI of the Act containing technical corrections to the USMCA Act. All of the changes contained within Title VI of the Appropriations Act are retroactively effective on July 1, 2020. E:\FR\FM\31JAR1.SGM 31JAR1

Agencies

[Federal Register Volume 89, Number 21 (Wednesday, January 31, 2024)]
[Rules and Regulations]
[Pages 6008-6011]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-01932]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0034; Project Identifier AD-2023-01154-Q; 
Amendment 39-22662; AD 2024-01-11]
RIN 2120-AA64


Airworthiness Directives; Various Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
helicopters with certain Pacific Scientific Company rotary buckle 
assemblies (buckles) installed. This AD was prompted by a report of a 
manufacturing defect in the screws used inside the buckle. This AD 
requires inspecting the buckle screws and, depending on the results, 
reidentifying the buckle, replacing the screws and reidentifying the 
buckle, or replacing the buckle. This AD also prohibits installing 
certain buckles. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective February 15, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 15, 
2024.
    The FAA must receive comments on this AD by March 18, 2024.

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-2024-0034; 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, any comments received, and other 
information. The street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information identified in this final rule, 
contact Parker Meggitt Services, 1785 Voyager Avenue, Simi Valley, CA 
93063; phone: 877-666-0712; email: [email protected]; 
website: meggitt.com/services_and_support/customer_experience/update-on-buckle-assembly-service-bulletins.
     You may view this service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 
6N-321, 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-2024-0034.

FOR FURTHER INFORMATION CONTACT: David Kim, Aviation Safety Engineer, 
FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: (562) 627-
5274; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2024-0034; Project Identifier AD-
2023-01154-Q'' 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 
Kim, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, 
CA 90712; phone: (562) 627-5274; email: [email protected]. 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 has received a report of a manufacturing defect in the 
screws used inside Pacific Scientific Company buckle part number (P/N) 
1111475 (all dash numbers) and P/N 1111548-01. The screws used to 
fasten the load plate to the body of the buckle were found to be 
susceptible to hydrogen embrittlement due to improper baking

[[Page 6009]]

during the electroplating process. This condition leads the screwhead 
to separate from the body of the screw when under load, which could 
result in the buckle failing to restrain the occupant to the seat. This 
issue was originally identified from a suspected lot of screws, Lot 
348994-A. Since then, a buckle failed in an accident, calling into 
question Lot 348601-A. Lots 348601-A and 348994-A were the first two 
lots of screws received by Pacific Scientific Company from a new 
supplier and are the only suspected lots. The suspected buckles were 
manufactured between January 2012 and September 2012. The FAA is 
issuing this AD to address the unsafe condition on these products.
    The rotary buckle may be included as a component of a different 
part-numbered restraint system assembly. Table 1 of Parker Meggitt 
Service Bulletin (SB) 1111475-25-001-2023, Revision 001, dated December 
1, 2023, and Parker Meggitt SB 1111548-25-001-2023, Revision 001, dated 
December 1, 2023 (SB 1111475-25-001-2023 Rev 001 and SB 1111548-25-001-
2023 Rev 001), includes a list of these restraint system assembly P/Ns.
    This AD applies to all helicopters with a Pacific Scientific 
Company buckle P/N 1111475 (all dash numbers) or P/N 1111548-01 
installed, if the buckle was manufactured between January 2012 and 
September 2012, or if the date of manufacture of the buckle is unknown. 
These same part-numbered buckles may also be installed in airplanes; 
however, the FAA determined that a longer compliance time to accomplish 
the required actions is allowable for buckles installed in airplanes. 
Accordingly, the FAA plans to publish a separate notice of proposed 
rulemaking to address all airplanes with a Pacific Scientific Company 
buckle P/N 1111475 (all dash numbers) or P/N 1111548-01 installed.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop on 
other helicopters with a restraint system with a buckle as part of 
their type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed SB 1111475-25-001-2023 Rev 001 for buckle P/N 
1111475 and SB 1111548-25-001-2023 Rev 001 for buckle P/N 1111548-01. 
This service information specifies procedures for inspecting the buckle 
for any missing or loose screw heads and, depending on the results, 
replacing the buckle and sending the removed buckle to Parker Meggitt 
for repair or replacement. If after that first inspection, all of the 
screw heads are intact, this service information specifies procedures 
for inspecting the buckle for any Torx head screws (alloy steel) and, 
depending on the results, allowing the buckle assembly to remain in-
service temporarily, replacing any Torx head screws (alloy steel) with 
new hex head screws (stainless steel), and checking the functionality 
of the buckle. This service information also specifies procedures for 
removing a buckle from a restraint system, installing a buckle on a 
restraint system, and returning buckles to Parker Meggitt. If the 
buckle passes the specified inspections or is modified by replacing 
Torx head screws (alloy steel) with new hex head screws (stainless 
steel) screws, this service information specifies procedures for 
reidentifying the back of the buckle. This service information also 
identifies known affected restraint systems.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in ADDRESSES.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information already described, except as discussed under ``Differences 
Between this AD and the Service Information.''

Differences Between This AD and the Service Information

    The service information does not specify any compliance times, 
whereas this AD requires accomplishing the required actions within 
three months. This AD also prohibits installing an affected buckle on 
any helicopter as of the effective date of this AD.
    The service information specifies sending any damaged buckles to 
Parker Meggitt for repair or replacement, and this AD does not. 
Instead, this AD requires replacing the buckle with an airworthy 
buckle.
    The service information allows buckles with a Torx head (alloy 
steel) screw to remain in service temporarily and be replaced at a time 
convenient to the operator, and this AD does not. If a buckle has any 
number of Torx head (alloy steel) screws installed, this AD requires 
replacing all four screws with hex head screws before further flight.
    If a screw head breaks off during disassembly of a buckle or if 
reassembly of a buckle is not possible, the service information 
specifies returning the buckle to Parker Meggitt, whereas this AD does 
not. If a screw head breaks off during disassembly, this AD requires 
replacing the buckle with an airworthy buckle. If reassembly of a 
buckle is not possible, then the buckle is not airworthy.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(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 in an otherwise survivable accident, hard landing, or severe 
turbulence, the buckle may fail to restrain the occupant. Based on the 
rotorcraft accident rate, coupled with not knowing the propagation rate 
of this unsafe condition into failure, the FAA determined that the 
compliance time to inspect affected buckles installed in helicopters 
must be within three months. Accordingly, notice and opportunity for 
prior public comment are impracticable and contrary to the public 
interest pursuant to 5 U.S.C. 553(b)(3)(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 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 approximately 11,714 buckles 
installed on restraint systems in aircraft worldwide. The FAA has no 
way of knowing the number of helicopters of

[[Page 6010]]

U.S. Registry that may have a restraint system with an affected buckle 
installed. The estimated costs on U.S. operators reflects the maximum 
possible costs based on affected buckles installed on restraint systems 
in aircraft worldwide. Labor rates are estimated at $85 per work-hour. 
Based on these numbers, the FAA estimates that operators may incur the 
following costs in order to comply with this AD.
    Inspecting a buckle will take approximately 0.1 work-hour for an 
estimated cost of $9 per buckle and up to $105,426 for the U.S. fleet. 
If required, replacing a set of screws (four) will take approximately 
0.5 work-hour and parts will cost a nominal amount for an estimated 
cost of $43 per buckle. Replacing a buckle will take approximately 0.5 
work-hour and parts will cost approximately $740 for an estimated cost 
of $783 per buckle. The FAA estimates a nominal cost for reidentifying 
a buckle.
    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, 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, 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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2024-01-11 Various Helicopters: Amendment 39-22662; Docket No. FAA-
2024-0034; Project Identifier AD-2023-01154-Q.

(a) Effective Date

    This airworthiness directive (AD) is effective February 15, 
2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all helicopters, certified in any category, 
with a restraint system with a Pacific Scientific Company rotary 
buckle assembly (buckle) part number (P/N) 1111475 (all dash 
numbers) or P/N 1111548-01 installed having a date of manufacture 
between January 2012 and September 2012 inclusive or an unknown date 
of manufacture. These buckles may be installed on, but not limited 
to, Airbus Helicopters model helicopters, 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 of a manufacturing defect in 
the screws used inside the buckle. The FAA is issuing this AD to 
prevent cracking and missing screw heads when under load. The unsafe 
condition, if not addressed, could result in a failure of the buckle 
to restrain the occupant.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For helicopters with buckle P/N 1111475 (all dash numbers), 
within 3 months after the effective date of this AD, inspect each 
buckle screw for cracked, loose, and missing screw heads by 
following the Accomplishment Instructions, paragraphs B.(1) and (2), 
of Parker Meggitt Service Bulletin (SB) 1111475-25-001-2023, 
Revision 001, dated December 1, 2023 (SB 1111475-25-001-2023 Rev 
001).
    (i) If any screw has a cracked, loose, or missing screw head, 
before further flight, replace the buckle with an airworthy buckle.
    (ii) If none of the four screw heads are cracked, loose, or 
missing, before further flight, inspect each screw to determine if 
any screw has a Torx head by using one of the following methods in 
the Accomplishment Instructions of SB 1111475-25-001-2023 Rev 001: 
paragraph B.(4)(a) (Magnet Test); paragraph B.(4)(b) (Inspection); 
or paragraphs C.(2) through (4) (removing the buckle from the 
restraint system) and paragraphs D.(1)(a) through (d) (disassembling 
the buckle).
    Note 1 to paragraph (g)(1): SB 1111475-25-001-2023 Rev 001 
refers to a magnifying glass as an ``eye loupe.''
    (A) If none of the four screws have a Torx head, before further 
flight, reassemble the buckle (if necessary) by following the 
Accomplishment Instructions, paragraphs D.(1)(f) through (l), of SB 
1111475-25-001-2023 Rev 001, and reidentify the buckle with ``INS. 
A'' by following the Accomplishment Instructions, paragraph B.(6), 
of SB 1111475-25-001-2023 Rev 001.
    (B) If at least one of the four screws has a Torx head, before 
further flight, with the buckle removed, replace each Torx head 
screw with a hex head screw, reassemble the buckle, and reidentify 
the buckle with ``MOD. A'' by following the Accomplishment 
Instructions, paragraphs D.(1)(e) through (m), of SB 1111475-25-001-
2023 Rev 001, except you are not required to return any parts to 
Parker Meggitt. If a screw head breaks off during disassembly, 
before further flight, replace the buckle with an airworthy buckle.
    (2) For helicopters with buckle P/N 1111548-01, within 3 months 
after the effective date of this AD, inspect each buckle screw for 
cracked, loose, and missing screw heads by following the 
Accomplishment Instructions, paragraph B.(1), of Parker Meggitt SB 
1111548-25-001-2023, Revision 001, dated December 1, 2023 (SB 
1111548-25-001-2023 Rev 001).
    (i) If any screw has a cracked, loose, or missing screw head, 
before further flight, replace the buckle with an airworthy buckle.
    (ii) If none of the four screw heads are cracked, loose, or 
missing, before further flight, inspect each screw to determine 
which screws have a Torx head by using one of the following methods 
in the Accomplishment Instructions of SB 1111548-25-001-2023 Rev 
001: paragraph B.(3)(a) (except use Figure 6 for placement of the 
shim tool and use Figure 5 to distinguish the screw head types) 
(Inspection); or paragraph C. (removing the buckle from the 
restraint system) and paragraphs D.(1)(a) through (c) (disassembling 
the buckle). Before further flight, with the buckle removed, replace 
each Torx head screw with a hex head screw,

[[Page 6011]]

reassemble the buckle, and reidentify the buckle with ``MOD. A'' by 
following the Accomplishment Instructions, paragraphs D.(1)(d) 
through (m), of SB 1111548-25-001-2023 Rev 001, except you are not 
required to return any parts to Parker Meggitt. If a screw head 
breaks off during disassembly, before further flight, replace the 
buckle with an airworthy buckle.
    Note 2 to paragraph (g)(2): SB 1111548-25-001-2023 Rev 001 
refers to a magnifying glass as an ``eye loupe.''
    (3) As of the effective date of this AD, do not install a buckle 
identified in paragraph (c) of this AD on any helicopter unless the 
buckle is marked with ``MOD. A'' or ``INS. A''.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, West Certification 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 West Certification Branch, send it to 
the attention of the person identified in paragraph (i) of this AD.
    (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.

(i) Additional Information

    For more information about this AD, contact David Kim, Aviation 
Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; 
phone: (562) 627-5274; email: [email protected].

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Parker Meggitt Service Bulletin 1111475-25-001-2023, 
Revision 001, dated December 1, 2023.
    (ii) Parker Meggitt Service Bulletin 1111548-25-001-2023, 
Revision 001, dated December 1, 2023.
    (3) For service information identified in this AD, contact 
Parker Meggitt Services, 1785 Voyager Avenue, Simi Valley, CA 93063; 
phone: 877-666-0712; email: [email protected]; website: 
meggitt.com/services_and_support/customer_experience/update-on-buckle-assembly-service-bulletins.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 
6N-321, 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 [email protected].

    Issued on January 18, 2024.
Victor Wicklund,
Deputy Director, Deputy Director, Compliance & Airworthiness Division, 
Aircraft Certification Service.
[FR Doc. 2024-01932 Filed 1-26-24; 4:15 pm]
BILLING CODE 4910-13-P
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