AD 2023-11-04

39341 Federal Register / Vol. 88, No. 116 / Friday, June 16, 2023 / Rules and Regulations upgrading in order to meet minimum standards of safety and decency or current building code requirements); (3) $500,000 for eligible refinancing purposes; (4) 20 percent of the verified loss (not including refinancing or malfeasance), before deduction of compensation from other sources, up to a maximum of $500,000 for post-disaster mitigation (see § 123.107); and (5) $500,000 for eligible malfeasance, pursuant to § 123.18. * * * * * (c) SBA determines the loan maturity and repayment terms based on your needs and your ability to pay. Generally, you will pay monthly installments of principal and interest, beginning twelve months from the date of the initial disbursement. SBA will consider other payment terms if you have seasonal or fluctuating income. The maximum maturity for a home disaster loan is 30 years. There is no penalty for prepayment of disaster loans. (d) The SBA Administrator may increase the home loan lending limits within paragraph (a) of this section under an individual disaster declaration based on appropriate economic indicators for the region(s) in which the disaster occurred. SBA will publish any increased lending limit for an individual disaster declaration in the Federal Register . ■ 6. Amend § 123.106 by revising paragraph (b) to read as follows: § 123.106 What is eligible refinancing? * * * * * (b) Your home disaster loan for refinancing existing liens or encumbrances cannot exceed an amount equal to the lesser of $500,000, or the physical damage to your primary residence. Any refinancing amount will be reduced to the extent such lien or encumbrance is satisfied by insurance or otherwise. § 123.107 [Amended] ■ 7. Amend § 123.107 by removing the number ‘‘$200,000’’ and adding in its place the number ‘‘$500,000’’. ■ 8. Amend § 123.202 by: ■ a. Revising paragraph (c) introductory text; ■ b. Removing paragraph (d); and ■ c. Redesignating paragraph (e) as paragraph (d). The revision reads as follows: § 123.202 How much can my business borrow with a physical disaster business loan? * * * * * (c) Physical disaster business borrowers may request refinancing of liens on both damaged real property and machinery and equipment. Such amount shall be reduced to the extent such lien or encumbrance is satisfied by insurance or otherwise. Your business property must be totally destroyed or substantially damaged, which means: * * * * * ■ 9. Amend § 123.203 by revising paragraph (b) as follows: § 123.203 What interest rate will my business pay on a physical disaster business loan and what are the repayment terms? * * * * * (b) Generally, you will pay monthly installments of principal and interest, beginning twelve months from the date of the initial disbursement. SBA will consider other payment terms if you have seasonal or fluctuating income. There is no penalty for prepayment for disaster loans. * * * * * § 123.301 [Amended] ■ 10. Amend § 123.301 by removing and reserving paragraph (c). § 123.502 [Amended] ■ 11. Amend § 123.502 by removing and reserving paragraph (j). Isabella Casillas Guzman, Administrator. [FR Doc. 2023–12779 Filed 6–15–23; 8:45 am] BILLING CODE 8026–09–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–0439; Project Identifier MCAI–2022–01263–T; Amendment 39–22449; AD 2023–11–04] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD–100–1A10 airplanes. This AD was prompted by a report that a design deficiency was discovered which could allow a no-back pawl to be incorrectly installed in a horizontal stabilizer trim actuator (HSTA). This AD requires a check for part number and serial numbers of the HSTA, and if necessary, inspection of the no-back pawl installation, and corrective action. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 21, 2023. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 21, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–0439; 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 service information identified in this final rule, contact Bombardier Business Aircraft Customer Response Center, 400 Co ˆ te-Vertu Road West, Dorval, Que ´bec H4S 1Y9, Canada; telephone 514–855–2999; email ac.yul@ aero.bombardier.com; website bombardier.com . • You may view this service information 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– 2023–0439. FOR FURTHER INFORMATION CONTACT : Chirayu Gupta, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; email 9-avs- nyaco-cos@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc., Model BD–100–1A10 airplanes. The NPRM published in the Federal Register on March 24, 2023 (88 FR 17748). The NPRM was prompted by AD CF–2022– 55, dated September 21, 2022, issued by Transport Canada, which is the aviation authority for Canada (referred to after this as the MCAI). The MCAI states that during an unscheduled inspection, a design deficiency was discovered which could allow a no-back pawl to be VerDate Sep<11>2014 15:19 Jun 15, 2023 Jkt 259001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1 ddrumheller on DSK120RN23PROD with RULES1

39342 Federal Register / Vol. 88, No. 116 / Friday, June 16, 2023 / Rules and Regulations incorrectly installed in an HSTA. The no-back mechanism is a primary means to prevent back driving of the HSTA, and the motor brake assemblies (MBAs) are the secondary means. If this condition is not corrected, a non- functioning no-back mechanism in combination with loss of, or degraded HSTA MBA braking capability, could lead to a loss of control of the airplane. The MCAI also states that as a mitigating action, Transport Canada AD CF–2019–23, dated June 18, 2019, was issued to mandate a software upgrade for the horizontal stabilizer trim electronic control unit to verify the MBA for braking capability during the power up test on certain Bombardier, Inc., Model BD–100–1A10 airplanes. Transport Canada AD CF–2019–23 corresponds to FAA AD 2019–15–04, Amendment 39–19697 (84 FR 38862, August 8, 2019) (AD 2019–15–04). In the NPRM, the FAA proposed to require a check for part number and serial numbers of the HSTA, and if necessary, inspection of the no-back pawl installation, and corrective action. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–0439. Discussion of Final Airworthiness Directive Comments The FAA received comments from an individual who supported the SNPRM/ NPRM without change. Additional Changes to This AD The FAA has revised paragraph (h) of this AD to clarify the parts installation prohibition applies only to any HSTA with P/N C47100–003 or P/N C47100– 004 that does not have either the suffix- K following the serial number or a modification plate showing ‘‘SB C47100–27–02’’ or ‘‘SB C47100–27–03.’’ In the NPRM, the FAA had inadvertently stated that installation of an HSTA with a modification plate showing ‘‘SB C47100–27–02’’ or ‘‘SB C47100–27–03’’ was prohibited. Conclusion This product has been approved by the aviation authority of another country and is approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on this product. Except for minor editorial change, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed Bombardier Service Bulletins 100–27–20 and 350– 27–009, both Revision 01, both dated December 1, 2020. This service information specifies procedures for a check for part number and serial numbers of the HSTA, and if necessary, inspection of the no-back pawl installation and corrective action. Corrective actions include replacement of the HSTA, and a re-identification and test of the HSTA. These documents are distinct since they apply to different airplane configurations. 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 the ADDRESSES section. Costs of Compliance The FAA estimates that this AD will affect 703 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E STIMATED C OSTS FOR R EQUIRED A CTIONS Labor cost Parts cost Cost per product Cost on U.S. operators Up to 2 work-hours × $85 per hour = Up to $170 ............................................................. None ................. Up to $170 ....... Up to $119,510. The FAA estimates the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. The FAA has no way of determining the number of airplanes that might need these on-condition actions: E STIMATED C OSTS OF O N -C ONDITION A CTIONS Labor cost Parts cost Cost per product Up to 25 work-hours × $85 per hour = Up to $2,125 .......................................................................................... $2,905 Up to $5,030. According to the manufacturer, some or all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators. The FAA does not control warranty coverage for affected operators. As a result, the FAA has included all known costs in the cost estimate. 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 VerDate Sep<11>2014 15:19 Jun 15, 2023 Jkt 259001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1 ddrumheller on DSK120RN23PROD with RULES1

39343 Federal Register / Vol. 88, No. 116 / Friday, June 16, 2023 / Rules and Regulations responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES ■ 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] ■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2023–11–04 Bombardier, Inc.: Amendment 39–22449; Docket No. FAA– 2023–0439; Project Identifier MCAI– 2022–01263–T. (a) Effective Date This airworthiness directive (AD) is effective July 21, 2023. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model BD–100–1A10 airplanes, certificated in any category, having serial number 20003 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by a report that a design deficiency was discovered which could allow a no-back pawl to be incorrectly installed in a horizontal stabilizer trim actuator (HSTA). The FAA is issuing this AD to address incorrectly installed no-back pawls. The unsafe condition, if not addressed, could result in a non-functioning no-back mechanism, which, in combination with loss of or degraded HSTA motor brake assembly (MBA) braking capability, could lead to a loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Records Check and Corrective Actions Within 60 months after the effective date of this AD, check the airplane maintenance records or do a visual check to determine the part and serial numbers of the HSTA. (1) If the part number is C47100–005: No further action is required by this paragraph. (2) If the part number is C47100–004 and the serial number ends with the suffix-K: No further action is required by this paragraph. (3) If the serial number is listed in the table referred to in paragraph 2.B.(4) of the Accomplishment Instructions of the applicable Bombardier service bulletin identified in figure 1 to paragraph (g)(3) of this AD: Within 60 months from the effective date of this AD, inspect the HSTA no-back mechanism pawls in accordance with paragraph 2.C. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (i) If one or more pawls are not correctly installed: Before further flight, replace the HSTA in accordance with paragraph 2.E. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (ii) If all the pawls are correctly installed, re-identify and test the HSTA, and do all applicable corrective actions, in accordance with paragraphs 2.C.(4) and 2.F. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. F IGURE 1 TO P ARAGRAPH (g)(3)— A PPLICABLE S ERVICE I NFORMATION Airplane model Applicable bombardier service bulletin BD–100–1A10 (CH300 marketing). 100–27–20, Revision 01, dated December 1, 2020. BD–100–1A10 (CH 350 marketing). 350–27–009, Revision 01, dated December 1, 2020. (4) If the serial number is listed in the table referred to in paragraph 2.B.(5) of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD: Within 60 months from the effective date of this AD, add a modification plate to the HSTA in accordance with paragraph 2.D. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (5) If the records check is inconclusive, or if a visual check instead of a records check of the HSTA was accomplished: Within 60 months from the effective date of this AD, verify the part numbers and serial numbers of the HSTA, and verify the modification plate, in accordance with paragraph 2.B. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (i) If the HSTA has part number (P/N) C47100–005: No further action is required by this paragraph. (ii) If the HSTA has P/N C47100–004 and a serial number that ends with the suffix-K, or if the modification plate contains ‘‘SB C47100–27–02’’ or ‘‘SB C47100–27–03’’: No further action is required by this paragraph. (iii) If the serial number is listed in the table referred to in paragraph 2.B.(4) of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD: Within 60 months from the effective date of this AD, inspect the HSTA no-back mechanism pawls in accordance with paragraph 2.C. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (A) If one or more pawls are not correctly installed, before further flight, replace the HSTA in accordance with Paragraph 2.E. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (B) If all the pawls are correctly installed, re-identify and test the HSTA, and do all applicable corrective actions, in accordance with paragraphs 2.C.(4) and 2.F. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (iv) If the serial number is listed in the table referred to in paragraph 2.B.(5) of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD: Within 60 months from the effective date of this AD, add a modification plate to the HSTA in accordance with paragraph 2.D. of the Accomplishment Instructions of the applicable service bulletin identified in figure 1 to paragraph (g)(3) of this AD. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install an HSTA with P/N C47100–003 or P/N C47100–004 that does not have either the suffix-K following the serial number or a modification plate showing ‘‘SB C47100–27–02’’ or ‘‘SB C47100–27–03’’ on any airplane. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (i)(1) and (2) of this AD. (1) Bombardier Service Bulletin 100–27– 20, dated November 9, 2020. (2) Bombardier Service Bulletin 350–27– 009, dated November 9, 2020. (j) 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 VerDate Sep<11>2014 15:19 Jun 15, 2023 Jkt 259001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1 ddrumheller on DSK120RN23PROD with RULES1

39344 Federal Register / Vol. 88, No. 116 / Friday, June 16, 2023 / Rules and Regulations to the manager of the International Validation Branch, mail it to ATTN: Program Manager, Continuing Operational Safety, at the address identified in paragraph (k)(2) of this AD or email to: 9-avs-nyaco-cos@faa.gov. If mailing information, also submit information by email. 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 Transport Canada or Bombardier, Inc.’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (k) Additional Information (1) Refer to Transport Canada AD CF– 2022–55, dated September 21, 2022, for related information. This Transport Canada AD may be found in the AD docket at regulations.gov under Docket No. FAA– 2023–0439. (2) For more information about this AD, contact Chirayu Gupta, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email 9-avs-nyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (4) of this AD. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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 this AD specifies otherwise. (i) Bombardier Service Bulletin 100–27–20, Revision 01, dated December 1, 2020. (ii) Bombardier Service Bulletin 350–27– 009, Revision 01, dated December 1, 2020. (3) For service information identified in this AD, contact Bombardier Business Aircraft Customer Response Center, 400 Co ˆ te- Vertu Road West, Dorval, Que ´bec H4S 1Y9, Canada; telephone 514–855–2999; email ac.yul@aero.bombardier.com; website bombardier.com . (4) You may view this service information 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 service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibr- locations.html. Issued on June 7, 2023. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–12934 Filed 6–15–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–0425; Project Identifier MCAI–2022–00980–A; Amendment 39–22458; AD 2023–11–12] RIN 2120–AA64 Airworthiness Directives; DAHER AEROSPACE (Type Certificate Previously Held by SOCATA) Airplanes AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain DAHER AEROSPACE (type certificate previously held by SOCATA) Model TBM 700 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as interference between the emergency exit trim panel and the upholstery panel, which could result in additional effort required to open the emergency exit door. This AD requires modification of the gripping strap, which maintains the upholstery panel on the emergency exit trim panel. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective July 21, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 21, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–0425; 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 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 service information identified in this final rule, contact DAHER AEROSPACE, Customer Support, Airplane Business Unit, Tarbes Cedex 9, France 65921; phone: (833) 826–2273; email: tbmcare@daher.com; website: daher.com . • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. 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–2023–0425. FOR FURTHER INFORMATION CONTACT : Fred Guerin, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 206–231– 2346; email: fred.guerin@faa.gov . SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain DAHER AEROSPACE Model TBM 700 airplanes. The NPRM published in the Federal Register on March 8, 2023 (88 FR 14301). The NPRM was prompted by AD 2022–0149, dated July 21, 2022 (referred to after this as ‘‘the MCAI’’), issued by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. The MCAI was prompted by a report that, due to interference between the emergency exit trim panel and the upholstery panel, additional effort may be required to open the emergency exit door. An investigation revealed that the gripping strap, which maintains the upholstery panel on the emergency exit trim panel, is not properly sized. The MCAI requires inserting a temporary revision (TR) into the emergency procedures section of the applicable pilot’s operating handbook (POH), informing all flight crews, operating the airplane accordingly, and modifying the gripping strap, at which time the TR can be removed from the POH. The unsafe condition, if not addressed, could lead to failure of the emergency exit door to perform its intended function during an emergency opening, possibly resulting in reduced evacuation capacity from the airplane and injury to occupants. In the NPRM, the FAA proposed to require modification of the gripping strap, which maintains the upholstery panel on the emergency exit trim panel. The FAA is issuing this AD to address the unsafe condition on these products. VerDate Sep<11>2014 15:19 Jun 15, 2023 Jkt 259001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1 ddrumheller on DSK120RN23PROD with RULES1