AD 2024-16-14

67532 Federal Register / Vol. 89, No. 162 / Wednesday, August 21, 2024 / Rules and Regulations (4) This AD does not adopt the provisions specified in paragraph (4) of EASA AD 2024– 0003. (5) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2024–0003. (i) Provisions for Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions ( e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2024–0003. (j) Terminating Action for Certain Tasks Required by AD 2018–18–21 For Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, 300 F4–605R, F4–622R, and A300 C4–605R Variant F airplanes only: Accomplishing the actions required by this AD terminates the corresponding requirements of AD 2018–18– 21 for the tasks identified in the service information referenced in EASA AD 2017– 0202 only. (k) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): 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, mail it to the address identified in paragraph (l) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Additional Information For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 206–231– 3225; email: dan.rodina@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 this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024–0003, dated January 5, 2024. (ii) [Reserved] (3) For EASA AD 2024–0003, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +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, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations, or email fr.inspection@ nara.gov. Issued on July 12, 2024. Suzanne Masterson, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–18633 Filed 8–20–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2017; Project Identifier AD–2024–00204–T; Amendment 39–22820; AD 2024–16–14] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787–8, 787–9, and 787–10 airplanes. This AD was prompted by a report of uncommanded movement of the Captain’s seat in the forward direction that caused a rapid descent. This AD requires inspections of affected Captain’s and First Officer’s seats for missing or cracked rocker switch caps and for cracked or nonfunctional switch cover assemblies, a rocker switch cap pull test, marking of the seats, and applicable on-condition actions. This AD also limits the installation of affected seats. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective August 21, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publications listed in this AD as of August 21, 2024. The FAA must receive comments on this AD by October 7, 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 by searching for and locating Docket No. FAA–2024– 2017; 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 Ipeco material identified in this AD, contact Ipeco Holdings Limited, Aviation Way, Southend on Sea, SS2 6UN, United Kingdom; phone: +44 1702 545118; email: technicalsupport@ ipeco.com. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA–2024–2017. FOR FURTHER INFORMATION CONTACT : Brandon Lucero, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206– 231–3569; email: Brandon.Lucero@ 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 to an address listed under ADDRESSES . Include Docket No. FAA–2024–2017 and Project Identifier AD–2024–00204– T 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 VerDate Sep<11>2014 15:51 Aug 20, 2024 Jkt 262001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1 lotter on DSK11XQN23PROD with RULES1

67533 Federal Register / Vol. 89, No. 162 / Wednesday, August 21, 2024 / Rules and Regulations 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 Brandon Lucero, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3569; email: Brandon.Lucero@faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA has received reports of uncommanded horizontal movement of the Captain’s and First Officer’s seats installed in Boeing Model 787 airplanes. The FAA received the first report in March 2024 indicating that uncommanded movement of the Captain’s seat caused the control column input to disconnect the auto- pilot, resulting in a rapid descent until the First Officer took control of the flight. This incident further resulted in multiple passenger injuries, some of which were serious. Following that incident, the FAA received four additional reports from Boeing of uncommanded horizontal movement of the Captain’s and First Officer’s seats; the most recent occurred in June 2024. Three of the incidents were due to loose forward/aft rocker switch caps located under the spring-loaded rocker switch cover guard on the back of the Captain’s and First Officer’s seats; the loose forward/aft rocker switch caps were the result of cracking or un-bonded or de- bonded caps. The other two incidents are under investigation. A rocker switch with a dislodged rocker switch cap, if depressed by the rocker switch cover guard, can cause unintended and sustained movement of the seat. Uncommanded horizontal movement of an occupied seat can cause in-flight upset from unintended and abrupt flight control inputs, which could result in a rapid descent of the airplane and serious injury to passengers and crew. The FAA is issuing this AD to address the unsafe condition on these products. 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 in other products of the same type design. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. This material specifies the following procedures: • A general visual inspection for cracked or missing rocker switch caps of the Captain’s and First Officer’s seats, and replacement and bonding of any switch that has a cracked or missing switch cap. • A general visual inspection for cracks of the switch cover assemblies and local areas, a functional test of the switch cover, and replacement of cracked or nonfunctional parts. • A rocker switch cap pull test for the switch caps (except those that have been replaced). • Bonding of any unbonded or debonded switch caps (that fail the pull test) or any replaced rocker switches, including making sure cracked rocker switches are replaced with switches having bonded caps. • Marking of the seats. 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. AD Requirements This AD requires accomplishing the actions specified in the material already described, except for any differences identified as exceptions in the regulatory text of this AD. This AD also limits the installation of affected seats. Clarification of Required Actions Where Ipeco Service Bulletin 380–25– 06, Issue 03, dated July 17, 2024, specifies bonding the rocker switch cap for an un-bonded cap, this AD also allows replacing the switch and bonding the switch cap. Where paragraph 3. of Part A of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024, specifies a rocker switch cap pull test of all switch caps, this AD does not require the pull test for any switch that was replaced with a switch having a bonded cap. 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 the FAA has received, with increasing frequency since March 2024, reports of uncommanded horizontal movement of the Captain’s or First Officer’s seat, when occupied. Uncommanded horizontal seat movement can cause in-flight upset from unintended and abrupt flight control inputs, which could result in a rapid descent of the airplane and serious injury to passengers and crew. Furthermore, 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 notice VerDate Sep<11>2014 15:51 Aug 20, 2024 Jkt 262001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1 lotter on DSK11XQN23PROD with RULES1

67534 Federal Register / Vol. 89, No. 162 / Wednesday, August 21, 2024 / Rules and Regulations and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 158 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspections, cap pull test, part marking .......... 1 work-hour × $85 per hour = $85 ................. $0 $85 $13,430 The FAA estimates the following costs to do any on-condition actions that would be required based on the results of an inspection or cap pull test. The FAA has no way of determining the number of aircraft that might need these on-condition actions: O N -C ONDITION C OSTS Action Labor cost Parts cost Cost per seat Replacement ........................................... Up to 3 work-hours × $85 per hour = $255 ............................ Up to $4,600 ....... Up to $4,855. Cap bonding ........................................... Up to 3 work-hours × $85 per hour = $255 ............................ $37 ...................... Up to $292. 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: 2024–16–14 The Boeing Company: Amendment 39–22820; Docket No. FAA–2024–2017; Project Identifier AD– 2024–00204–T. (a) Effective Date This airworthiness directive (AD) is effective August 21, 2024. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8, 787–9, and 787–10 airplanes, certificated in any category, identified in paragraphs (c)(1) and (2) of this AD. (1) Airplanes with a Captain’s seat having Ipeco part number P/N 3A380–0007–XX–X or First Officer’s seat having Ipeco P/N 3A380–0008–XX–X. (2) Airplanes that do not have a seat identified in paragraph (c)(1) of this AD. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Unsafe Condition This AD was prompted by reports of uncommanded horizontal movement of the Captain’s and First Officer’s seats. The FAA is issuing this AD to address a dislodged rocker switch cap under the spring-loaded rocker switch cover guard, which can cause unintended and sustained movement of the seat. Uncommanded horizontal movement of a Captain’s or First Officer’s seat, when occupied, can cause in-flight upset from unintended and abrupt flight control inputs, which could result in a rapid descent of the airplane and serious injury to passengers and crew. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Switch Cap Inspection For airplanes identified in paragraph (c)(1) of this AD: Within 30 days after the effective date of this AD, do a general visual inspection for cracked or missing rocker switch caps of the Captain’s and First Officer’s seats, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. For any switch that has a cracked or missing switch cap, replace the switch and bond the switch cap within 30 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380– 25–06, Issue 03, dated July 17, 2024. Replacement may be delayed provided the airplane is operated under the provisions of Master Minimum Equipment List item 25– 11–01–0, but no later than 120 days after the effective date of this AD. (h) Switch Cover Assembly Inspection For airplanes identified in paragraph (c)(1) of this AD: Within 30 days after the effective VerDate Sep<11>2014 15:51 Aug 20, 2024 Jkt 262001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1 lotter on DSK11XQN23PROD with RULES1

67535 Federal Register / Vol. 89, No. 162 / Wednesday, August 21, 2024 / Rules and Regulations date of this AD, perform a general visual inspection for cracks of the switch cover assemblies and local areas and a functional test of the switch cover, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. Replace any cracked or nonfunctional parts within 30 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. Replacement may be delayed provided the airplane is operated under the provisions of Master Minimum Equipment List item 25–11–01–0, but no later than 120 days after the effective date of this AD. (i) Rocker Switch Cap Pull Test For airplanes identified in paragraph (c)(1) of this AD: Within 30 days after the effective date of this AD, except as specified in paragraph (k) of this AD, perform a rocker switch cap pull test of all switch caps, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380– 25–06, Issue 03, dated July 17, 2024. For any rocker switch cap that is un-bonded or de- bonded ( i.e., fails the test), bond the rocker switch cap, or replace the switch and bond the switch cap, within 30 days after the effective date of this AD, in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. The bonding may be delayed provided the airplane is operated under the provisions of Master Minimum Equipment List item 25–11–01–0, but no later than 120 days after the effective date of this AD. (j) Seat Marking For airplanes identified in paragraph (c)(1) of this AD: Before further flight after accomplishment of the applicable actions required by paragraphs (g) through (i) of this AD, mark the seat in accordance with the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. (k) Exceptions to Service Bulletin (1) Where a note in paragraph 3.a. of Part A of the Accomplishment Instructions of Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024, specifies to visually inspect the switch guard (3–270 or 3–270A) for cracks or modifications and ‘‘replace in accordance with the CMM,’’ this AD requires replacing that text with ‘‘replace the switch guard before further flight in accordance with the CMM if any crack or modification is found.’’ (2) For any switch that has been replaced with a switch having a bonded cap as required by paragraph (g) of this AD, the actions required by paragraph (i) of this AD are not required. (l) Parts Installation Limitation At the applicable time specified in paragraph (l)(1) or (2) of this AD, no person may install, on any airplane, a seat identified in paragraph (c)(1) of this AD, unless the seat is marked as specified in paragraph (j) of this AD. (1) For airplanes in paragraph (c)(1) of this AD: After accomplishment of all applicable actions required by this AD. (2) For airplanes identified in paragraph (c)(2) of this AD: As of the effective date of this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, AIR–520, Continued Operational Safety Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (n) of this AD. Information may be emailed 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, AIR–520, Continued Operational Safety Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (n) Related Information For more information about this AD, contact Brandon Lucero, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3569; email: Brandon.Lucero@faa.gov. (o) 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) Ipeco Service Bulletin 380–25–06, Issue 03, dated July 17, 2024. (ii) [Reserved] (3) For Ipeco material identified in this AD, contact Ipeco Holdings Limited, Aviation Way, Southend on Sea, SS2 6UN, United Kingdom; phone: +44 1702 545118; fax: +44 1702 540782; email: technicalsupport@ ipeco.com. (4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on August 2, 2024. John P. Piccola, Jr., Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2024–18843 Filed 8–19–24; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–1001; Project Identifier MCAI–2023–01129–T; Amendment 39–22787; AD 2024–14–06] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350–941 and –1041 airplanes. This AD was prompted by reports that certain engine bleed air system (EBAS) T-Ducts may not conform to the type design due to a quality escape not detected during the manufacturing process on Rolls-Royce Trent XWB–75, Trent XWB–84, and Trent XWB–97 engines. This AD requires replacement of affected EBAS T-Ducts and limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective September 25, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 25, 2024. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2024–1001; 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: VerDate Sep<11>2014 15:51 Aug 20, 2024 Jkt 262001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1 lotter on DSK11XQN23PROD with RULES1