AD 2023-22-02

80572 Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations (4) This AD does not adopt the provisions specified in paragraphs (4) and (5) of EASA AD 2023–0060. (5) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2023–0060. (l) New Provisions for Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as required by paragraph (j) 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 2023–0060. (m) 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 International Validation Branch, send it to the attention of the person identified in paragraph (n) 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 Dassault Aviation’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (n) Additional Information For more information about this AD, contact Tom Rodriguez, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone: 206–231– 3226; email: tom.rodriguez@faa.gov. (o) 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 this AD specifies otherwise. (3) The following service information was approved for IBR on December 26, 2023. (i) European Union Aviation Safety Agency (EASA) AD 2023–0060, dated March 16, 2023. (ii) [Reserved] (4) The following service information was approved for IBR on December 23, 2020 (85 FR 73404, November 18, 2020). (i) European Union Aviation Safety Agency (EASA) AD 2019–0141, dated June 17, 2019. (ii) [Reserved] (5) For EASA ADs 2023–0060 and 2019– 0141, 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 these EASA ADs on the EASA website at ad.easa.europa.eu. (6) 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. (7) 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 October 27, 2023. Caitlin Locke, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–25496 Filed 11–17–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1638; Project Identifier AD–2022–00466–E; Amendment 39–22586; AD 2023–22–02] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Division Engines AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is superseding Airworthiness Directive (AD) 2018–02– 10, which applied to certain Pratt & Whitney Division (PW) Model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 engines. AD 2018–02–10 required performing repetitive fluorescent penetrant inspections (FPIs) to detect cracks in the outer diffuser case (ODC), removal of any ODC that fails inspection, and updating the mandatory inspections in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA). Since the FAA issued AD 2018–02–10, PW developed a modification to reduce the susceptibility of ODC cracking. This AD retains the ALS update requirement from AD 2018– 02–10, requires replacing certain ODC part numbers with parts eligible for installation, expands the applicability to all ODC part numbers, and adjusts the compliance threshold of the FPIs of the ODC. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 26, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 26, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1638; 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 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 Pratt & Whitney Division, 400 Main Street, East Hartford, CT 06118; phone: (800) 565– 0140; email: help24@prattwhitney.com; website: connect.prattwhitney.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–1638. FOR FURTHER INFORMATION CONTACT : Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238– 7655; email: carol.nguyen@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2018–02–10, Amendment 39–19163 (FR 83 2896, January 22, 2018), (‘‘AD 2018–02–10’’). AD 2018–02–10 applied to PW Model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 engines with ODC part number (P/N) 50J775 or P/N 50J930, installed. The NPRM published in the Federal Register on August 8, 2023 (88 FR 53406). The NPRM was prompted by an updated analysis by the engine manufacturer, which determined that cracks on the ODC originated due to high stress in the area between Tt3 boss and thermocouple bracket boss. PW developed a modification to improve the surface area between Tt3 boss and VerDate Sep<11>2014 16:15 Nov 17, 2023 Jkt 262001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\20NOR1.SGM 20NOR1 ddrumheller on DSK120RN23PROD with RULES1

80573 Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations thermocouple bracket boss to reduce the ODC’s susceptibility to cracking. Consequently, the FAA determined that it is necessary to expand the applicability to all ODC P/Ns, adjust the initial FPI threshold for the ODC to improve the inspection program, and to require certain ODCs to be replaced with an ODC that has been modified to lower the stresses in the area between Tt3 boss and thermocouple bracket boss. In the NPRM, the FAA proposed to continue to require retain certain requirements of AD 2018–02–10. In the NPRM, the FAA also proposed to require revising the ALS of the existing airplane maintenance manual or ICA and your existing approved maintenance program, as applicable, to include piece-part inspections of the ODC; expanding the applicability to include all engines; initial and repetitive FPIs, and depending on the results of the FPI, require removal or re- inspection of the ODC. Lastly the NPRM proposed to require replacement of certain ODCs with a part eligible for installation at next piece-part exposure. Discussion of Final Airworthiness Directive Comments The FAA received comments from three commenters. Commenters included United Airlines, The Boeing Company, and Air Lines Pilots Association, International. All commenters supported the NPRM without change. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes which include updating the manufacturer contact information, this AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed PW Alert Service Bulletin (ASB) PW4G–112–A72–347, Revision 4, dated September 1, 2022. This ASB provides guidance on performing FPIs on certain bosses of the ODC. 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 . Other Related Service Information The FAA reviewed PW Service Bulletin (SB) PW4G–112–72–357, dated February 25, 2019. This SB provides procedures to modify and re-identify ODC assemblies to lower the stresses in the area between the Tt3 boss and the thermocouple bracket boss. Costs of Compliance The FAA estimates that this AD, affects 108 engines installed on airplanes of U.S. registry. The FAA has no way to determine the number of operators that will replace the ODC with a modified ODC or a zero-time ODC. As a result, the total cost on U.S. operators for these actions is not estimated. 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 Perform high sensitivity FPI of the ODC T3 thermocouple probe boss. 10 work-hours × $85 per hour = $850 ........... $0 $850 $91,800 Revise the ALS ............................................... 1 work-hour × $85 per hour = $85 ................. 0 85 9,180 Replace the ODC with modified ODC ............ 3 work-hours × $85 per hour = $255 ............. 12,000 12,255 ........................ Replace the ODC with zero-time ODC ........... 3 work-hours × $85 per hour = $255 ............. 2,300,000 2,300,255 ........................ 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 The FAA has determined that 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, (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: ■ a. Removing Airworthiness Directive 2018–02–10, Amendment 39–19163 (83 FR 2896, January 22, 2018); and ■ b. Adding the following new airworthiness directive: 2023–22–02 Pratt & Whitney Division: Amendment 39–22586; Docket No. FAA–2023–1638; Project Identifier AD– 2022–00466–E. VerDate Sep<11>2014 16:15 Nov 17, 2023 Jkt 262001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\20NOR1.SGM 20NOR1 ddrumheller on DSK120RN23PROD with RULES1

80574 Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations (a) Effective Date This airworthiness directive (AD) is effective December 26, 2023. (b) Affected ADs This AD replaces AD 2018–02–10, Amendment 39–19163 (83 FR 2896, January 22, 2018). (c) Applicability This AD applies to Pratt & Whitney Division (PW) Model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 engines. (d) Subject Joint Aircraft System Component (JASC) Code 7240, Turbine Engine Combustion Section. (e) Unsafe Condition This AD was prompted by the discovery of multiple cracked outer diffuser cases (ODCs). We are issuing this AD to prevent failure of the ODC. This condition, if not addressed, could result in failure of the ODC, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within the compliance times specified in paragraphs (g)(1)(i) though (iii) of this AD, perform an initial high sensitivity fluorescent penetrant inspection (FPI) of the ODC T3 thermocouple probe boss (Tt3 boss) for crack indications in accordance with the Accomplishment Instructions, paragraph 1.F. of Part A or paragraph 1.B. of Part B, as applicable, of PW Alert Service Bulletin PW4G–112–A72–347, Revision 4, dated September 1, 2022 (ASB PW4G–112–A72– 347, Rev 4). (i) For an ODC that has accumulated less than 12,000 cycles since new (CSN) with no prior high sensitivity FPI of the ODC Tt3 boss, perform the high sensitivity FPI before accumulating 9,200 CSN or within 1,000 flight cycles (FCs), after the effective date of this AD, whichever occurs later. (ii) For an ODC with unknown CSN or an ODC that has accumulated 12,000 CSN or more with no prior high sensitivity FPI of the ODC Tt3 boss, perform the high sensitivity FPI before accumulating 13,000 CSN or within 1,000 FCs, after February 26, 2018 (the effective date of AD 2018–02–10), whichever occurs later. (iii) For an ODC that has undergone a high sensitivity FPI of the ODC Tt3 boss prior to the effective date of this AD that resulted in no crack indication, perform the high sensitivity FPI before accumulating 2,000 FCs since performance of the last FPI or during the next engine shop visit, whichever occurs first. (iv) For an ODC that has undergone a high sensitivity FPI of the ODC Tt3 boss prior to the effective date of this AD that resulted in an indication of a crack, perform the actions required by paragraphs (g)(3)(i) through (iii) of this AD, as applicable. (2) Thereafter, repeat the high sensitivity FPI of the ODC Tt3 boss at each engine shop visit or before exceeding 2,000 FCs from the last high sensitivity FPI of the ODC Tt3 boss, whichever occurs first, in accordance with the Accomplishment Instructions, paragraphs 1.F. of Part A or paragraph 1.B. of Part B, as applicable, of ASB PW4G–112–A72–347, Rev 4. (3) If, during any inspection required by paragraphs (g)(1) or (2) of this AD, there is any crack indication, perform the actions specified in paragraphs (g)(3)(i) through (iii) of this AD. (i) For engines installed on an aircraft, repeat the high sensitivity FPI or remove the ODC from service in accordance with the actions and compliance times specified in the Accomplishment Instructions, Part A, paragraphs 1.G. and 1.H., of ASB PW4G– 112–A72–347, Rev 4. (ii) For engines not installed on an aircraft, repeat the high sensitivity FPI or remove the ODC from service in accordance with the actions and compliance times specified in the Accomplishment Instructions, Part B, paragraphs 1.C. and 1.D., of PW ASB PW4G– 112–A72–347, Rev 4. (iii) For engines at an engine shop visit, before further flight, remove the ODC from service. (4) Within 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (ALS) of the existing engine maintenance manual or Instructions for Continued Airworthiness and the existing approved maintenance program, as applicable, to include the piece-part inspections of the ODC as defined in Table 1 to paragraph (g)(4) of this AD. T ABLE 1 TO P ARAGRAPH (g)(4)—A DDITION TO ALS Description Part No. Cleaning, inspection and repair (CIR) manual section CIR manual inspection CIR manual Case, Diffuser, Outer ................................... All ................... 72–41–13 Inspection/Check (I/C–02) .......................... P/N 51A750 (5) For engines with ODC part number (P/ N) 50J775 or 50J930 installed, at the next piece-part exposure after the effective date of this AD, replace the ODC with a part eligible for installation. (h) Definitions (1) For the purpose of this AD, an ‘‘engine shop visit’’ is any time the ‘‘M’’ flange is separated. (2) For the purpose of this AD, a ‘‘piece- part exposure’’ is when the ODC is removed from the engine and fully disassembled. (3) For the purpose of this AD, a ‘‘part eligible for installation’’ is an ODC with P/ N 50J775–001, 50J775–002, 50J930–001, or 50J930–002. (i) 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 local Flight Standards District Office, as appropriate. If sending information directly to the manager of the AIR–520 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to: ANE- AD-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information For more information about this AD, contact Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7655; email: carol.nguyen@faa.gov. (k) 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) Pratt & Whitney Alert Service Bulletin PW4G–112–A72–347, Revision 4, dated September 1, 2022. (ii) [Reserved] (3) For service information identified in this AD, contact Pratt & Whitney Division, 400 Main Street, East Hartford, CT 06118; phone: (800) 565–0140; email: help24@ prattwhitney.com; website: connect.prattwhitney.com. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238–7759. (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. VerDate Sep<11>2014 16:15 Nov 17, 2023 Jkt 262001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\20NOR1.SGM 20NOR1 ddrumheller on DSK120RN23PROD with RULES1

80575 Federal Register / Vol. 88, No. 222 / Monday, November 20, 2023 / Rules and Regulations Issued on October 25, 2023. Caitlin Locke, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–25524 Filed 11–17–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1637; Project Identifier MCAI–2023–00184–E; Amendment 39–22588; AD 2023–22–04] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Engines AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000–A2, Trent 1000–AE2, Trent 1000–C2, Trent 1000– CE2, Trent 1000–D2, Trent 1000–E2, Trent 1000–G2, Trent 1000–H2, Trent 1000–J2, Trent 1000–K2, and Trent 1000–L2 engines. This AD was prompted by reports of cracking and separation of certain low-pressure turbine (LPT) stage 1 blade assemblies. This AD requires initial and repetitive inspections of affected LPT stage 1 blade assemblies for cracking or separation and, depending on the results of the inspections, reduction of the inspection interval or replacement of the LPT stage 1 blade set and disk, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 26, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 26, 2023. ADDRESSES : AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1637; 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 EASA, Konrad- Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–1637. FOR FURTHER INFORMATION CONTACT : Sungmo Cho, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238– 7241; email: sungmo.d.cho@faa.gov. SUPPLEMENTARY INFORMATION : Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all RRD Model Trent 1000–A2, Trent 1000–AE2, Trent 1000–C2, Trent 1000–CE2, Trent 1000–D2, Trent 1000– E2, Trent 1000–G2, Trent 1000–H2, Trent 1000–J2, Trent 1000–K2, and Trent 1000–L2 engines. The NPRM published in the Federal Register on July 31, 2023 (88 FR 49361). The NPRM was prompted by EASA AD 2023–0027, dated January 31, 2023 (EASA AD 2023–0027) (also referred to as the MCAI) issued by EASA, which is the Technical Agent for the Member States of the European Union. The MCAI states that manufacturer inspections detected cracking and separation of blade pairs in the weld region of certain LPT stage 1 blade assemblies. A blade assembly consists of a pair of blades welded together at the outer shroud. There are 85 LPT stage 1 blade assemblies in one set. Such cracking and separation could cause failure of affected parts and damage to the LPT module. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1637. In the NPRM, the FAA proposed to require initial and repetitive inspections of affected LPT stage 1 blade assemblies for cracking or separation and, depending on the results of the inspections, reduction of the inspection interval or replacement of the LPT stage 1 blade set and disk. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received one comment from The Boeing Company (Boeing). Boeing supported the NPRM without change. Conclusion These products have been approved by the aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting the AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. Related Service Information Under 1 CFR Part 51 The FAA reviewed EASA AD 2023– 0027, which specifies procedures for inspection of affected LPT stage 1 blade assemblies and replacement of the LPT stage 1 blade set and disk. EASA AD 2023–0027 also specifies a reduction of the repetitive inspection intervals if cracking or separation is detected and meets certain criteria. 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 ADDRESSES . Costs of Compliance The FAA estimates that this AD affects 26 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: VerDate Sep<11>2014 16:15 Nov 17, 2023 Jkt 262001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\20NOR1.SGM 20NOR1 ddrumheller on DSK120RN23PROD with RULES1