Airworthiness Directives; Pratt & Whitney Turbofan Engines, 1038-1042 [2024-00309]

Download as PDF 1038 Proposed Rules Federal Register Vol. 89, No. 6 Tuesday, January 9, 2024 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–2523; Project Identifier AD–2023–01086–E] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G–3, PW1524G, PW1524G–3, PW1525G, PW1525G–3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G–A engines. This proposed AD was prompted by an updated analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA–JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR–7) separation that resulted in an engine shutdown and aborted takeoff. This proposed AD would require performing an angled ultrasonic inspection (AUSI) of certain highpressure turbine (HPT) 1st-stage hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This proposed AD would also require accelerated replacement of certain HPC 7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd-stage air seals, HPT 1st-stage blade retaining plates, and HPT 2ndstage blade retaining plates. The FAA is proposing this AD to address the unsafe condition on these products. khammond on DSKJM1Z7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:01 Jan 08, 2024 Jkt 262001 The FAA must receive comments on this proposed AD by February 8, 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–2023–2523; 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 NPRM, any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For Pratt & Whitney service information identified in this AD, contact International Aero Engines, LLC, 400 Main Street, East Hartford, CT 06118; phone: (860) 565–0140; email: help24@pw.utc.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. 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: DATES: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2023–2523; Project Identifier AD– 2023–01086–E’’ at the beginning of your comments. The most helpful comments reference a specific portion of the PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 proposal, 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 proposal because of those comments. The FAA has been informed that PW has done some outreach with affected operators regarding the proposed corrective actions for this unsafe condition. As a result, affected operators are already aware of the proposed corrective actions and, in some cases, have already begun planning for replacement of the affected parts. Therefore, the FAA has determined that a 30-day comment period is appropriate given the particular circumstances related to the proposed correction of this unsafe condition. 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 NPRM. 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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to Carol Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. E:\FR\FM\09JAP1.SGM 09JAP1 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules Background On December 24, 2022, an Airbus Model A320neo airplane powered by IAE LLC Model PW1127GA–JM engines, experienced a failure of the HPC IBR– 7 that resulted in an engine shutdown and aborted take-off. Following this event, the manufacturer conducted a records review of production and fieldreturned parts and re-evaluated their engineering analysis methodology. The new analysis found that the failure of the HPC IBR–7 was caused by a nickel powdered metal anomaly, similar in nature to an anomaly previously observed. The analysis also concluded that there is an increased risk of failure for additional nickel powdered metal parts in certain nickel powdered metal production campaigns, and these parts are susceptible to failure much earlier than previously determined. As a result, the FAA is proposing additional AUSIs for certain affected nickel powdered metal parts and removal from service of certain affected nickel powdered metal parts. Certain PW Model PW1519G, PW1521G, PW1521GA, PW1521G–3, PW1524G, PW1524G–3, PW1525G, PW1525G–3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G–A engines are among the products affected by this condition. This condition, if not addressed, could result in uncontained disk failure, release of high-energy debris, damage to the engine, damage to the airplane, and possible loss of the airplane. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed the following service information: • PW Alert Service Bulletin (ASB) PW1000G–A–72–00–0196–00A–930A– D, Issue No: 002, dated November 30, 2023, and PW ASB PW1000G–A–72– 00–0141–00B–930A–D, Issue No: 002, dated November 30, 2023. This service information specifies a list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs that are identified by serial number (S/N) and installed on certain PW engines; and instructions for performing an AUSI on affected HPT 1st-stage hubs and HPT 2nd-stage hubs. • PW ASB PW1000G–A–72–00– 0197–00A–930A–D, Issue No: 004, dated November 30, 2023, and PW ASB PW1000G–A–72–00–0142–00B–930A– D, Issue No: 004, dated November 30, 2023. This service information specifies a list of affected HPC 8th-stage disks that are identified by S/N and installed on certain PW engines; and instructions for performing an AUSI on affected HPC 8th-stage disks. • PW ASB PW1000G–A–72–00– 0204–00A–930A–D Issue No: 001, dated November 30, 2023, and PW ASB PW1000G–A–72–00–0150–00B–930A–D Issue No: 001, dated November 30, 2023, which specifies procedures for performing repetitive AUSIs on affected HPC 8th-stage disks. • PW ASB PW1000G–A–72–00– 0205–00A–930A–D, Issue No: 001, dated November 30, 2023, and PW ASB PW1000G–A–72–00–0151–00B–930A– D, Issue No: 001, dated November 30, 2023, which specify procedures for performing repetitive AUSIs on affected HPT 1st-stage hubs and HPT 2nd-stage hubs. • PW Special Instruction No. 240F– 23, dated November 30, 2023, which specifies a list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs that are identified by S/N and installed on certain PW engines. 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. Proposed AD Requirements in This NPRM This proposed AD would require performing an AUSI of certain HPT 1st- 1039 stage hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage hubs, or HPC 8thstage disks. This proposed AD would also require accelerated replacement of certain HPC 7th-stage rotors, HPC 8thstage disks, HPC rear hubs, HPT 1ststage air seals, HPT 2nd-stage air seals, HPT 1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage blade retaining plates, and HPT 2nd-stage blade retaining plates. Interim Action The FAA considers this AD to be an interim action. This unsafe condition is still under investigation by the manufacturer and, depending on the results of that investigation, the FAA may consider further rulemaking action. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 430 engines installed on airplanes of U.S. registry. The FAA estimates that 160 engines would need the AUSI of the HPT 1st-stage hub, HPT 2nd-stage hub, and HPC 8th-stage disk; 218 engines would need replacement of the HPT 1ststage hub; 226 engines would need replacement of the HPT 2nd-stage hub; 231 engines would need replacement of the HPC 7th-stage rotor; 231 engines would need replacement of the HPC 8th-stage disk; 231 engines would need replacement of the HPC rear hub; 231 engines would need replacement of the HPT 1st-stage air seal; 233 engines would need replacement of the HPT 2nd-stage air seal; 232 engines would need replacement of the HPT 1st-stage blade retaining plate; and 231 engines would need replacement of the HPT 2nd-stage blade retaining plate. The FAA estimates the following costs to comply with this proposed AD: khammond on DSKJM1Z7X2PROD with PROPOSALS ESTIMATED COSTS Parts cost (average pro-rated cost) Action Labor cost Perform AUSI of HPT 1st-stage hub, HPT 2ndstage hub, and HPC 8th-stage disk. Replace HPT 1st-stage hub ..................................... Replace HPT 2nd-stage hub .................................... Replace HPC 7th-stage rotor ................................... Replace HPC 8th-stage disk .................................... Replace HPC rear hub ............................................. Replace HPT 1st-stage air seal ............................... Replace HPT 2nd-stage air seal .............................. Replace HPT 1st-stage blade retaining plate .......... 60 work-hours × $85 per hour = $5,100 .... VerDate Sep<11>2014 16:01 Jan 08, 2024 Jkt 262001 PO 00000 10 10 10 10 10 10 10 10 work-hours work-hours work-hours work-hours work-hours work-hours work-hours work-hours Frm 00002 × × × × × × × × $85 $85 $85 $85 $85 $85 $85 $85 Fmt 4702 per per per per per per per per hour hour hour hour hour hour hour hour Sfmt 4702 = = = = = = = = $850 $850 $850 $850 $850 $850 $850 $850 ....... ....... ....... ....... ....... ....... ....... ....... E:\FR\FM\09JAP1.SGM Cost per product Cost on U.S. operators $0 $5,100 $816,000 49,500 25,500 48,000 35,500 83,000 21,000 36,000 34,000 50,350 26,350 48,850 36,350 83,850 21,850 36,850 34,850 10,976,300 5,955,100 11,284,350 8,396,850 19,369,350 5,047,350 8,586,050 8,085,200 09JAP1 1040 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules ESTIMATED COSTS—Continued Labor cost Replace HPT 2nd-stage blade retaining plate ......... 10 work-hours × $85 per hour = $850 ....... 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 under warranty, 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 The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, khammond on DSKJM1Z7X2PROD with PROPOSALS Parts cost (average pro-rated cost) Action 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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 13,000 13,850 Cost on U.S. operators 3,199,350 International Aero Engines, LLC Model PW1127GA–JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor separation that resulted in an engine shutdown and aborted takeoff. The FAA is issuing this AD to prevent failure of the high-pressure turbine (HPT) 1st-stage hub, HPT 2nd-stage hub, and HPC 8th-stage disk. The unsafe condition, if not addressed, could result in uncontained hub failure, release of high-energy debris, damage to the engine, damage to the airplane, and possible loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. 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 Cost per product [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Pratt & Whitney: Docket No. FAA–2023– 2523; Project Identifier AD–2023–01086– E. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by February 8, 2024. (b) Affected ADs None. (c) Applicability Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G–3, PW1524G, PW1524G–3, PW1525G, PW1525G–3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G–A engines. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section; 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by an updated analysis of an event involving an (g) Required Actions (1) For PW1500G engines with an installed HPC 8th-stage disk having part number (P/N) 30G7208, at the next HPC engine shop visit, except as required by paragraph (g)(3) of this AD, perform an angled ultrasonic inspection (AUSI) of the affected HPC 8th-stage disk for cracks in accordance with the Accomplishment Instructions, paragraph 8., of PW Alert Service Bulletin (ASB) PW1000G–A–72–00–0197–00A–930A–D, Issue No: 004, dated November 30, 2023. (2) For PW1500G engines with an installed HPT 1st-stage hub having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202, at the next engine shop visit, except as required by paragraph (g)(3) of this AD, perform an AUSI of the affected HPT 1ststage hub or HPT 2nd-stage hub, as applicable, for cracks in accordance with the Accomplishment Instructions, paragraph 8.A. or 8.B., of PW ASB PW1000G–A–72–00– 0196–00A–930A–D, Issue No: 002, dated November 30, 2023. (3) For PW1500G engines with an installed part, P/N and serial number (S/N) listed in Table 1 to paragraph (g)(3) of this AD with no AUSI performed prior to the effective date of this AD, within the applicable compliance time listed in Table 1 to paragraph (g)(3) of this AD or within 100 flight cycles (FCs) after the effective date of this AD, whichever occurs later, perform an AUSI of the affected part for cracks in accordance with the applicable service bulletin listed in Table 1 to paragraph (g)(3) of this AD. TABLE 1 TO PARAGRAPH (g)(3)—AUSI COMPLIANCE TIMES Part Applicable S/N listing Compliance time Applicable service bulletin (see paragraph (m)(2) of this AD) HPC 8th-stage disk .... P/N 30G7208 Table 1 of PW ASB PW1000G–A–72–00– 0197–00A–930A–D. Accomplishment Instructions, paragraph 8., of PW ASB PW1000G–A–72–00–0197–00A–930A–D. HPT 1st-stage hub ..... P/N 30G8501 Table 2 of PW ASB PW1000G–A–72–00– 0196–00A–930A–D. Next HPC engine shop visit not to exceed 10,000 part cycles since new (CSN). Next engine shop visit not to exceed 5,000 part CSN. VerDate Sep<11>2014 17:29 Jan 08, 2024 Jkt 262001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Accomplishment Instructions, paragraph 8.A. of PW ASB PW1000G–A–72–00–0196–00A–930A–D E:\FR\FM\09JAP1.SGM 09JAP1 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules 1041 TABLE 1 TO PARAGRAPH (g)(3)—AUSI COMPLIANCE TIMES—Continued Part Applicable S/N listing Compliance time Applicable service bulletin (see paragraph (m)(2) of this AD) HPT 2nd-stage hub .... P/N 30G7202 HPT 1st-stage hub ..... P/N 30G8501 HPT 2nd-stage hub .... P/N 30G7202 Table 3 of PW ASB PW1000G–A–72–00– 0196–00A–930A–D. Table 4 of PW ASB PW1000G–A–72–00– 0196–00A–930A–D. Table 5 of PW ASB PW1000G–A–72–00– 0196–00A–930A–D. Next engine shop visit not to exceed 5,000 part CSN. Next engine shop visit not to exceed 4,000 part CSN. Next engine shop visit not to exceed 4,000 part CSN. Accomplishment Instructions, paragraph 8.B, of PW ASB PW1000G–A–72–00–0196–00A–930A–D. Accomplishment Instructions, paragraph 8.A, of PW ASB PW1000G–A–72–00–0196–00A–930A–D. Accomplishment Instructions, paragraph 8.B., of PW ASB PW1000G–A–72–00–0196–00A–930A–D. (4) Thereafter at each piece-part exposure of the affected part for PW1500G engines with an installed HPC 8th-stage disk having P/N 30G7208, an installed HPT 1st-stage hub having P/N 30G8501, or an installed HPT 2nd-stage hub having P/N 30G7202, do the following: (i) Perform an AUSI of the affected HPC 8th-stage disk for cracks in accordance with the Accomplishment Instructions, paragraph 5.B., PW ASB PW1000G–A–72–00–0204– 00A–930A–D, Issue No: 001, dated November 30, 2023. (ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT 2nd-stage hub, as applicable, for cracks in accordance with the Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB PW1000G–A–72–00– 0205–00A–930A–D, Issue No: 001, dated November 30, 2023. (5) For PW1900G engines with an installed HPC 8th-stage disk having P/N 30G7208, at the next HPC engine shop visit, except as required by paragraph (g)(7) of this AD, perform an AUSI of the affected HPC 8thstage disk for cracks in accordance with the Accomplishment Instructions, paragraph 8., of Pratt & Whitney PW ASB PW1000G–A– 72–00–0142–00B–930A–D, Issue No: 004, dated November 30, 2023. (6) For PW1900G engines with an installed HPT 1st-stage hub having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202, at the next engine shop visit, except as required by paragraph (g)(7) of this AD, perform an AUSI of the affected HPT 1st- stage hub and HPT 2nd-stage hub, as applicable, for cracks in accordance with the Accomplishment Instructions, paragraph 8.A. or 8.B., of PW ASB PW1000G–A–72–00– 0141–00B–930A–D, Issue No: 002, dated November 30, 2023. (7) For PW1900G engines with an installed part, P/N and S/N listed in Table 2 to paragraph (g)(7) of this AD, with no AUSI performed prior to the effective date of this AD, within the compliance time listed in Table 2 to paragraph (g)(7) of this AD or within 100 FCs after the effective date of this AD, whichever occurs later, perform an AUSI of the affected parts for cracks in accordance with the applicable service bulletin listed in Table 2 to paragraph (g)(7) of this AD. khammond on DSKJM1Z7X2PROD with PROPOSALS TABLE 2 TO PARAGRAPH (g)(7)—AUSI COMPLIANCE TIMES Applicable service bulletin (see paragraph (m)(2) of this AD) Part Table S/N is listed in Compliance time HPC 8th-stage disk having P/N 30G7208. HPT 1st-stage hub having P/N 30G8501. HPT 2nd-stage hub having P/N 30G7202. HPT 1st-stage hub having P/N 30G8501. HPT 2nd-stage hub having P/N 30G7202. Table 1 of PW ASB PW1000G–A–72–00– 0142–00B–930A–D. Table 2 of PW ASB PW1000G–A–72–00– 0141–00B–930A–D. Table 3 of PW ASB PW1000G–A–72–00– 0141–00B–930A–D. Table 4 of PW ASB PW1000G–A–72–00– 0141–00B–930A–D. Table 5 of PW ASB PW1000G–A–72–00– 0141–00B–930A–D. Next HPC engine shop visit not to exceed 10,000 part CSN. Next engine shop visit not to exceed 5,000 part CSN. Next engine shop visit not to exceed 5,000 part CSN. Next engine shop visit not to exceed 4,000 part CSN. Next engine shop visit not to exceed 4,000 part CSN. (8) Thereafter at each piece-part exposure of the affected part for PW1900G engines with an installed HPC 8th-stage disk having P/N 30G7208, or an installed HPT 1st-stage hub having P/N 30G8501, or an installed HPT 2nd-stage hub having P/N 30G7202, do the following: (i) Perform an AUSI of the affected HPC 8th-stage disk for cracks in accordance with the Accomplishment Instructions, paragraph 5.B., of PW ASB PW1000G–A–72–00–0150– 00B–930A–D, Issue No: 001, dated November 30, 2023. (ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT 2nd-stage hub, as applicable, for cracks in accordance with the Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB PW1000G–A–72–00– 0151–00B–930A–D, Issue No: 001, dated November 30, 2023. (9) If any crack is found during the inspections required by paragraph (g) of this AD, before further flight, remove the affected part from service and replace with a part eligible for installation. (10) For engines with an installed part and P/N listed in Table 3 to paragraph (g)(10) of this AD having 3,300 CSN or less on the effective date of this AD, before the part VerDate Sep<11>2014 17:29 Jan 08, 2024 Jkt 262001 accumulates 4,000 CSN or at the next engine shop visit after the effective date of this AD, whichever occurs first, remove the part from service and replace with a part eligible for installation. TABLE 3 TO PARAGRAPH (g)(10)— PART NUMBERS Part name P/N HPC 7th-stage rotor ................................ HPC 8th-stage disk ................................. HPC rear hub .......................................... HPT 1st-stage hub .................................. HPT 2nd-stage hub ................................. HPT 1st-stage air seal ............................ HPT 2nd-stage air seal ........................... HPT 1st-stage blade retaining plate ....... HPT 2nd-stage blade retaining plate ...... 30G3307 30G3248 30G2902 30G5701 30G5002 30G3132 30G3451 30G1692 30G1698 (11) For engines with an installed part and P/N listed in Table 3 to paragraph (g)(10) of this AD having more than 3,300 CSN on the effective date of this AD, at the next engine shop visit or within 700 FCs after the effective date of this AD, whichever occurs first, remove the part from service and replace it with a part eligible for installation. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Accomplishment Instructions, paragraph 8., of ASB PW1000G–A–72–00–0142–00B–930A–D. Accomplishment Instructions, paragraph 8.A., of ASB PW1000G–A–72–00–0141–00B–930A–D. Accomplishment Instructions, paragraph 8.B, of ASB PW1000G–A–72–00–0141–00B–930A–D. Accomplishment Instructions, paragraph 8.A., of ASB PW1000G–A–72–00–0141–00B–930A–D. Accomplishment Instructions, paragraph 8.B., of ASB PW1000G–A–72–00–0141–00B–930A–D. PW PW PW PW PW (12) For engines with an installed HPT 1ststage hub having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202 and an S/N listed in Table 1 of PW Special Instruction (SI) No. 240F–23, dated November 30, 2023, within 100 FCs from the effective date of this AD, remove the hub from service and replace it with a part eligible for installation. (13) If an affected part has accumulated 100 FCs or less since the last AUSI, reinspection is not required provided that the part was not damaged during removal from the engine. (h) Installation Prohibition After the effective date of this AD, do not install an HPT 1st-stage hub having P/N 30G8501 or an HPT 2nd-stage hub having P/ N 30G7202 and an S/N listed in Table 1 of PW SI No. 240F–23, dated November 30, 2023, in any engine. (i) Definitions (1) For the purposes of this AD, ‘‘PW1500G’’ engines are PW Model PW1519G, PW1521G, PW1521GA, PW1521G–3, PW1524G, PW1524G–3, PW1525G, and PW1525G–3 engines. E:\FR\FM\09JAP1.SGM 09JAP1 1042 Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / Proposed Rules khammond on DSKJM1Z7X2PROD with PROPOSALS (2) For the purposes of this AD, ‘‘PW1900G’’ engines are PW Model PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G–A engines. (3) For the purposes of this AD, a ‘‘part eligible for installation’’ is: (i) Any HPC 7th-stage rotor, P/N 30G5307 or later approved P/N. (ii) Any HPC 8th-stage disk, P/N 30G7208, that has passed the AUSI required by paragraph (g) of this AD or later approved P/N. (iii) Any HPC rear hub, P/N 30G7308 or later approved P/N. (iv) Any HPT 1st-stage hub, P/N 30G8501, that has passed the AUSI required by paragraph (g) of this AD or later approved P/N. (v) Any HPT 2nd-stage hub, P/N 30G7202, that has passed the AUSI required by paragraph (g) of this AD or later approved P/N. (vi) Any HPT 1st-stage air seal, P/N 30G5195 or later approved P/N. (vii) Any HPT 2nd-stage air seal, P/N 30G5196 or later approved P/N. (viii) Any HPT 1st-stage blade retaining plate, P/N 30G5193 or later approved P/N. (ix) Any HPT 2nd-stage blade retaining plate, P/N 30G5194 or later approved P/N. (4) For the purposes of this AD, a ‘‘piecepart exposure’’ is when the part is disassembled from the rotor assembly. (5) For the purposes of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except for the following situations, which do not constitute an engine shop visit. (i) The separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance. (ii) Fan case maintenance or replacement. (6) For the purposes of this AD, an ‘‘HPC engine shop visit’’ is when the HPC rotor assembly is removed from the engine. (j) Credit for Previous Actions This paragraph provides credit for the initial AUSI of the HPC 8th-stage disk, HPT 1st-stage hub and HPT 2nd-stage hub specified in paragraph (g)(1), (2), (4) and (5) of this AD, if the initial AUSI was performed before the effective date of this AD using the following service information; (1) PW ASB PW1000G–A–72–00–0196– 00A–930A–D, Issue No: 001, dated March 16, 2023; or (2) PW ASB PW1000G–A–72–00–0197– 00A–930A–D, Issue No: 001, dated March 22, 2023; or (3) PW ASB PW1000G–A–72–00–0197– 00A–930A–D, Issue No: 002, dated June 19, 2023; or (4) PW ASB PW1000G–A–72–00–0197– 00A–930A–D, Issue No: 003, dated August 14, 2023; or (5) PW ASB PW1000G–A–72–00–0141– 00B–930A–D, Issue No: 001, dated March 16, 2023; or (6) PW ASB PW1000G–A–72–00–0142– 00B–930A–D, Issue No: 001, dated March 22, 2023; or (7) PW ASB PW1000G–A–72–00–0142– 00B–930A–D, Issue No: 002, dated June 19, 2023.; or VerDate Sep<11>2014 16:01 Jan 08, 2024 Jkt 262001 (8) PW ASB PW1000G–A–72–00–0142– 00B–930A–D, Issue No: 003, dated August 14, 2023. (k) 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 AIR–520 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (l)(1) 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. (l) Additional Information (1) 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. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (4) of this AD. (m) 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 (PW) Alert Service Bulletin (ASB) PW1000G–A–72–00–0141– 00B–930A–D, Issue No: 002, dated November 30, 2023. (ii) PW ASB PW1000G–A–72–00–0142– 00B–930A–D, Issue No: 004, dated November 30, 2023. (iii) PW ASB PW1000G–A–72–00–0150– 00B–930A–D Issue No:001, dated November 30, 2023. (iv) PW ASB PW1000G–A–72–00–0151– 00B–930A–D, Issue No: 001, dated November 30, 2023. (v) PW ASB PW1000G–A–72–00–0196– 00A–930A–D, Issue No: 002, dated November 30, 2023. (vi) PW ASB PW1000G–A–72–00–0197– 00A–930A–D, Issue No: 004, dated November 30, 2023. (vii) PW ASB PW1000G–A–72–00–0204– 00A–930A–D Issue No:001, dated November 30, 2023. (viii) PW ASB PW1000G–A–72–00–0205– 00A–930A–D, Issue No: 001, dated November 30, 2023. (ix) PW Special Instruction No. 240F–23, dated November 30, 2023. (3) For PW service information identified in this AD, contact International Aero Engines, LLC, 400 Main Street, East Hartford, CT 06118; phone: (860) 565–0140; email: help24@pw.utc.com; website: connect.prattwhitney.com. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (4) 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. (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 December 27, 2023. Caitlin Locke, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–00309 Filed 1–5–24; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 53 [REG–142338–07] RIN 1545–BI33 Taxes on Taxable Distributions From Donor Advised Funds Under Section 4966 Internal Revenue Service (IRS), Treasury ACTION: Notice of proposed rulemaking; extension of comment period. AGENCY: This document extends the period to submit comments or to request a public hearing for a notice of proposed rulemaking (REG–142338–07) that was published in the Federal Register on Tuesday, November 14, 2023. The proposed regulations relate to excise taxes on taxable distributions made by a sponsoring organization from a donor advised fund, and on the agreement of certain fund managers to the making of such distributions. DATES: The period to submit written or electronic comments for the notice of proposed rulemaking published on November 14, 2023 (88 FR 77922) or to request a public hearing is extended from January 16, 2024, to February 15, 2024. ADDRESSES: Commenters are strongly encouraged to submit public comments electronically. Submit electronic submissions via the Federal eRulemaking Portal at www.regulations.gov (indicate IRS and REG–142338–07) by following the online instructions for submitting comments. Once submitted to the Federal eRulemaking Portal, comments cannot be edited or withdrawn. The Department of the Treasury (Treasury SUMMARY: E:\FR\FM\09JAP1.SGM 09JAP1

Agencies

[Federal Register Volume 89, Number 6 (Tuesday, January 9, 2024)]
[Proposed Rules]
[Pages 1038-1042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-00309]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 89, No. 6 / Tuesday, January 9, 2024 / 
Proposed Rules

[[Page 1038]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2523; Project Identifier AD-2023-01086-E]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, 
PW1521G-3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, 
PW1922G, PW1923G, and PW1923G-A engines. This proposed AD was prompted 
by an updated analysis of an event involving an International Aero 
Engines, LLC (IAE LLC) Model PW1127GA-JM engine, which experienced a 
high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-
7) separation that resulted in an engine shutdown and aborted takeoff. 
This proposed AD would require performing an angled ultrasonic 
inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage 
hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and, 
depending on the results of the inspections, replacing the HPT 1st-
stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This proposed 
AD would also require accelerated replacement of certain HPC 7th-stage 
rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage hubs, HPT 
2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd-stage air seals, HPT 
1st-stage blade retaining plates, and HPT 2nd-stage blade retaining 
plates. The FAA is proposing this AD to address the unsafe condition on 
these products.

DATES: The FAA must receive comments on this proposed AD by February 8, 
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-2023-2523; 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 NPRM, any comments received, and other 
information. The street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For Pratt & Whitney service information identified in this 
AD, contact International Aero Engines, LLC, 400 Main Street, East 
Hartford, CT 06118; phone: (860) 565-0140; email: [email protected]; 
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.

FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety 
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 
(781) 238-7655; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2023-2523; Project Identifier 
AD-2023-01086-E'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, 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 proposal because of those comments.
    The FAA has been informed that PW has done some outreach with 
affected operators regarding the proposed corrective actions for this 
unsafe condition. As a result, affected operators are already aware of 
the proposed corrective actions and, in some cases, have already begun 
planning for replacement of the affected parts. Therefore, the FAA has 
determined that a 30-day comment period is appropriate given the 
particular circumstances related to the proposed correction of this 
unsafe condition.
    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 NPRM.

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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to Carol 
Nguyen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des 
Moines, WA 98198. Any commentary that the FAA receives which is not 
specifically designated as CBI will be placed in the public docket for 
this rulemaking.

[[Page 1039]]

Background

    On December 24, 2022, an Airbus Model A320neo airplane powered by 
IAE LLC Model PW1127GA-JM engines, experienced a failure of the HPC 
IBR-7 that resulted in an engine shutdown and aborted take-off. 
Following this event, the manufacturer conducted a records review of 
production and field-returned parts and re-evaluated their engineering 
analysis methodology. The new analysis found that the failure of the 
HPC IBR-7 was caused by a nickel powdered metal anomaly, similar in 
nature to an anomaly previously observed. The analysis also concluded 
that there is an increased risk of failure for additional nickel 
powdered metal parts in certain nickel powdered metal production 
campaigns, and these parts are susceptible to failure much earlier than 
previously determined. As a result, the FAA is proposing additional 
AUSIs for certain affected nickel powdered metal parts and removal from 
service of certain affected nickel powdered metal parts. Certain PW 
Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, 
PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A 
engines are among the products affected by this condition. This 
condition, if not addressed, could result in uncontained disk failure, 
release of high-energy debris, damage to the engine, damage to the 
airplane, and possible loss of the airplane.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed the following service information:
     PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0196-00A-
930A-D, Issue No: 002, dated November 30, 2023, and PW ASB PW1000G-A-
72-00-0141-00B-930A-D, Issue No: 002, dated November 30, 2023. This 
service information specifies a list of affected HPT 1st-stage hubs and 
HPT 2nd-stage hubs that are identified by serial number (S/N) and 
installed on certain PW engines; and instructions for performing an 
AUSI on affected HPT 1st-stage hubs and HPT 2nd-stage hubs.
     PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004, 
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0142-00B-930A-D, 
Issue No: 004, dated November 30, 2023. This service information 
specifies a list of affected HPC 8th-stage disks that are identified by 
S/N and installed on certain PW engines; and instructions for 
performing an AUSI on affected HPC 8th-stage disks.
     PW ASB PW1000G-A-72-00-0204-00A-930A-D Issue No: 001, 
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0150-00B-930A-D 
Issue No: 001, dated November 30, 2023, which specifies procedures for 
performing repetitive AUSIs on affected HPC 8th-stage disks.
     PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001, 
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0151-00B-930A-D, 
Issue No: 001, dated November 30, 2023, which specify procedures for 
performing repetitive AUSIs on affected HPT 1st-stage hubs and HPT 2nd-
stage hubs.
     PW Special Instruction No. 240F-23, dated November 30, 
2023, which specifies a list of affected HPT 1st-stage hubs and HPT 
2nd-stage hubs that are identified by S/N and installed on certain PW 
engines.
    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.

Proposed AD Requirements in This NPRM

    This proposed AD would require performing an AUSI of certain HPT 
1st-stage hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks 
and, depending on the results of the inspections, replacing the HPT 
1st-stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This 
proposed AD would also require accelerated replacement of certain HPC 
7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage air 
seals, HPT 2nd-stage air seals, HPT 1st-stage hubs, HPT 2nd-stage hubs, 
HPT 1st-stage blade retaining plates, and HPT 2nd-stage blade retaining 
plates.

Interim Action

    The FAA considers this AD to be an interim action. This unsafe 
condition is still under investigation by the manufacturer and, 
depending on the results of that investigation, the FAA may consider 
further rulemaking action.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 430 engines installed on airplanes of U.S. registry. The FAA 
estimates that 160 engines would need the AUSI of the HPT 1st-stage 
hub, HPT 2nd-stage hub, and HPC 8th-stage disk; 218 engines would need 
replacement of the HPT 1st-stage hub; 226 engines would need 
replacement of the HPT 2nd-stage hub; 231 engines would need 
replacement of the HPC 7th-stage rotor; 231 engines would need 
replacement of the HPC 8th-stage disk; 231 engines would need 
replacement of the HPC rear hub; 231 engines would need replacement of 
the HPT 1st-stage air seal; 233 engines would need replacement of the 
HPT 2nd-stage air seal; 232 engines would need replacement of the HPT 
1st-stage blade retaining plate; and 231 engines would need replacement 
of the HPT 2nd-stage blade retaining plate.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                         Parts cost
                 Action                           Labor cost            (average pro-   Cost per   Cost on U.S.
                                                                         rated cost)     product     operators
----------------------------------------------------------------------------------------------------------------
Perform AUSI of HPT 1st-stage hub, HPT    60 work-hours x $85 per                   $0    $5,100        $816,000
 2nd-stage hub, and HPC 8th-stage disk.    hour = $5,100.
Replace HPT 1st-stage hub...............  10 work-hours x $85 per               49,500    50,350      10,976,300
                                           hour = $850.
Replace HPT 2nd-stage hub...............  10 work-hours x $85 per               25,500    26,350       5,955,100
                                           hour = $850.
Replace HPC 7th-stage rotor.............  10 work-hours x $85 per               48,000    48,850      11,284,350
                                           hour = $850.
Replace HPC 8th-stage disk..............  10 work-hours x $85 per               35,500    36,350       8,396,850
                                           hour = $850.
Replace HPC rear hub....................  10 work-hours x $85 per               83,000    83,850      19,369,350
                                           hour = $850.
Replace HPT 1st-stage air seal..........  10 work-hours x $85 per               21,000    21,850       5,047,350
                                           hour = $850.
Replace HPT 2nd-stage air seal..........  10 work-hours x $85 per               36,000    36,850       8,586,050
                                           hour = $850.
Replace HPT 1st-stage blade retaining     10 work-hours x $85 per               34,000    34,850       8,085,200
 plate.                                    hour = $850.

[[Page 1040]]

 
Replace HPT 2nd-stage blade retaining     10 work-hours x $85 per               13,000    13,850       3,199,350
 plate.                                    hour = $850.
----------------------------------------------------------------------------------------------------------------

    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 under warranty, 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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Pratt & Whitney: Docket No. FAA-2023-2523; Project Identifier AD-
2023-01086-E.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by February 8, 2024.

(b) Affected ADs

    None.

(c) Applicability

    Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-
3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, 
PW1922G, PW1923G, and PW1923G-A engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section; 7250, Turbine Section.

(e) Unsafe Condition

    This AD was prompted by an updated analysis of an event 
involving an International Aero Engines, LLC Model PW1127GA-JM 
engine, which experienced a high-pressure compressor (HPC) 7th-stage 
integrally bladed rotor separation that resulted in an engine 
shutdown and aborted takeoff. The FAA is issuing this AD to prevent 
failure of the high-pressure turbine (HPT) 1st-stage hub, HPT 2nd-
stage hub, and HPC 8th-stage disk. The unsafe condition, if not 
addressed, could result in uncontained hub failure, release of high-
energy debris, damage to the engine, damage to the airplane, and 
possible loss of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For PW1500G engines with an installed HPC 8th-stage disk 
having part number (P/N) 30G7208, at the next HPC engine shop visit, 
except as required by paragraph (g)(3) of this AD, perform an angled 
ultrasonic inspection (AUSI) of the affected HPC 8th-stage disk for 
cracks in accordance with the Accomplishment Instructions, paragraph 
8., of PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0197-00A-
930A-D, Issue No: 004, dated November 30, 2023.
    (2) For PW1500G engines with an installed HPT 1st-stage hub 
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N 
30G7202, at the next engine shop visit, except as required by 
paragraph (g)(3) of this AD, perform an AUSI of the affected HPT 
1st-stage hub or HPT 2nd-stage hub, as applicable, for cracks in 
accordance with the Accomplishment Instructions, paragraph 8.A. or 
8.B., of PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002, 
dated November 30, 2023.
    (3) For PW1500G engines with an installed part, P/N and serial 
number (S/N) listed in Table 1 to paragraph (g)(3) of this AD with 
no AUSI performed prior to the effective date of this AD, within the 
applicable compliance time listed in Table 1 to paragraph (g)(3) of 
this AD or within 100 flight cycles (FCs) after the effective date 
of this AD, whichever occurs later, perform an AUSI of the affected 
part for cracks in accordance with the applicable service bulletin 
listed in Table 1 to paragraph (g)(3) of this AD.

                               Table 1 to Paragraph (g)(3)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
                                                                                            Applicable service
                 Part                   Applicable S/N listing      Compliance time      bulletin (see paragraph
                                                                                            (m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk...................  Table 1 of PW ASB        Next HPC engine shop     Accomplishment
P/N 30G7208..........................   PW1000G-A-72-00-0197-0   visit not to exceed      Instructions,
                                        0A-930A-D.               10,000 part cycles       paragraph 8., of PW
                                                                 since new (CSN).         ASB PW1000G-A-72-00-
                                                                                          0197-00A-930A-D.
HPT 1st-stage hub....................  Table 2 of PW ASB        Next engine shop visit   Accomplishment
P/N 30G8501..........................   PW1000G-A-72-00-0196-0   not to exceed 5,000      Instructions,
                                        0A-930A-D.               part CSN.                paragraph 8.A. of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0196-00A-930A-D

[[Page 1041]]

 
HPT 2nd-stage hub....................  Table 3 of PW ASB        Next engine shop visit   Accomplishment
P/N 30G7202..........................   PW1000G-A-72-00-0196-0   not to exceed 5,000      Instructions,
                                        0A-930A-D.               part CSN.                paragraph 8.B, of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0196-00A-930A-D.
HPT 1st-stage hub....................  Table 4 of PW ASB        Next engine shop visit   Accomplishment
P/N 30G8501..........................   PW1000G-A-72-00-0196-0   not to exceed 4,000      Instructions,
                                        0A-930A-D.               part CSN.                paragraph 8.A, of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0196-00A-930A-D.
HPT 2nd-stage hub....................  Table 5 of PW ASB        Next engine shop visit   Accomplishment
P/N 30G7202..........................   PW1000G-A-72-00-0196-0   not to exceed 4,000      Instructions,
                                        0A-930A-D.               part CSN.                paragraph 8.B., of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0196-00A-930A-D.
----------------------------------------------------------------------------------------------------------------

    (4) Thereafter at each piece-part exposure of the affected part 
for PW1500G engines with an installed HPC 8th-stage disk having P/N 
30G7208, an installed HPT 1st-stage hub having P/N 30G8501, or an 
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
    (i) Perform an AUSI of the affected HPC 8th-stage disk for 
cracks in accordance with the Accomplishment Instructions, paragraph 
5.B., PW ASB PW1000G-A-72-00-0204-00A-930A-D, Issue No: 001, dated 
November 30, 2023.
    (ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT 
2nd-stage hub, as applicable, for cracks in accordance with the 
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB 
PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001, dated November 30, 
2023.
    (5) For PW1900G engines with an installed HPC 8th-stage disk 
having P/N 30G7208, at the next HPC engine shop visit, except as 
required by paragraph (g)(7) of this AD, perform an AUSI of the 
affected HPC 8th-stage disk for cracks in accordance with the 
Accomplishment Instructions, paragraph 8., of Pratt & Whitney PW ASB 
PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004, dated November 30, 
2023.
    (6) For PW1900G engines with an installed HPT 1st-stage hub 
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N 
30G7202, at the next engine shop visit, except as required by 
paragraph (g)(7) of this AD, perform an AUSI of the affected HPT 
1st-stage hub and HPT 2nd-stage hub, as applicable, for cracks in 
accordance with the Accomplishment Instructions, paragraph 8.A. or 
8.B., of PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 002, 
dated November 30, 2023.
    (7) For PW1900G engines with an installed part, P/N and S/N 
listed in Table 2 to paragraph (g)(7) of this AD, with no AUSI 
performed prior to the effective date of this AD, within the 
compliance time listed in Table 2 to paragraph (g)(7) of this AD or 
within 100 FCs after the effective date of this AD, whichever occurs 
later, perform an AUSI of the affected parts for cracks in 
accordance with the applicable service bulletin listed in Table 2 to 
paragraph (g)(7) of this AD.

                               Table 2 to Paragraph (g)(7)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
                                                                                            Applicable service
                 Part                   Table S/N is listed in      Compliance time      bulletin (see paragraph
                                                                                            (m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk having P/N 30G7208  Table 1 of PW ASB        Next HPC engine shop     Accomplishment
                                        PW1000G-A-72-00-0142-0   visit not to exceed      Instructions,
                                        0B-930A-D.               10,000 part CSN.         paragraph 8., of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0142-00B-930A-D.
HPT 1st-stage hub having P/N 30G8501.  Table 2 of PW ASB        Next engine shop visit   Accomplishment
                                        PW1000G-A-72-00-0141-0   not to exceed 5,000      Instructions,
                                        0B-930A-D.               part CSN.                paragraph 8.A., of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0141-00B-930A-D.
HPT 2nd-stage hub having P/N 30G7202.  Table 3 of PW ASB        Next engine shop visit   Accomplishment
                                        PW1000G-A-72-00-0141-0   not to exceed 5,000      Instructions,
                                        0B-930A-D.               part CSN.                paragraph 8.B, of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0141-00B-930A-D.
HPT 1st-stage hub having P/N 30G8501.  Table 4 of PW ASB        Next engine shop visit   Accomplishment
                                        PW1000G-A-72-00-0141-0   not to exceed 4,000      Instructions,
                                        0B-930A-D.               part CSN.                paragraph 8.A., of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0141-00B-930A-D.
HPT 2nd-stage hub having P/N 30G7202.  Table 5 of PW ASB        Next engine shop visit   Accomplishment
                                        PW1000G-A-72-00-0141-0   not to exceed 4,000      Instructions,
                                        0B-930A-D.               part CSN.                paragraph 8.B., of PW
                                                                                          ASB PW1000G-A-72-00-
                                                                                          0141-00B-930A-D.
----------------------------------------------------------------------------------------------------------------

    (8) Thereafter at each piece-part exposure of the affected part 
for PW1900G engines with an installed HPC 8th-stage disk having P/N 
30G7208, or an installed HPT 1st-stage hub having P/N 30G8501, or an 
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
    (i) Perform an AUSI of the affected HPC 8th-stage disk for 
cracks in accordance with the Accomplishment Instructions, paragraph 
5.B., of PW ASB PW1000G-A-72-00-0150-00B-930A-D, Issue No: 001, 
dated November 30, 2023.
    (ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT 
2nd-stage hub, as applicable, for cracks in accordance with the 
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB 
PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001, dated November 30, 
2023.
    (9) If any crack is found during the inspections required by 
paragraph (g) of this AD, before further flight, remove the affected 
part from service and replace with a part eligible for installation.
    (10) For engines with an installed part and P/N listed in Table 
3 to paragraph (g)(10) of this AD having 3,300 CSN or less on the 
effective date of this AD, before the part accumulates 4,000 CSN or 
at the next engine shop visit after the effective date of this AD, 
whichever occurs first, remove the part from service and replace 
with a part eligible for installation.

               Table 3 to Paragraph (g)(10)--Part Numbers
------------------------------------------------------------------------
                          Part name                               P/N
------------------------------------------------------------------------
HPC 7th-stage rotor..........................................    30G3307
HPC 8th-stage disk...........................................    30G3248
HPC rear hub.................................................    30G2902
HPT 1st-stage hub............................................    30G5701
HPT 2nd-stage hub............................................    30G5002
HPT 1st-stage air seal.......................................    30G3132
HPT 2nd-stage air seal.......................................    30G3451
HPT 1st-stage blade retaining plate..........................    30G1692
HPT 2nd-stage blade retaining plate..........................    30G1698
------------------------------------------------------------------------

    (11) For engines with an installed part and P/N listed in Table 
3 to paragraph (g)(10) of this AD having more than 3,300 CSN on the 
effective date of this AD, at the next engine shop visit or within 
700 FCs after the effective date of this AD, whichever occurs first, 
remove the part from service and replace it with a part eligible for 
installation.
    (12) For engines with an installed HPT 1st-stage hub having P/N 
30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202 and an 
S/N listed in Table 1 of PW Special Instruction (SI) No. 240F-23, 
dated November 30, 2023, within 100 FCs from the effective date of 
this AD, remove the hub from service and replace it with a part 
eligible for installation.
    (13) If an affected part has accumulated 100 FCs or less since 
the last AUSI, reinspection is not required provided that the part 
was not damaged during removal from the engine.

(h) Installation Prohibition

    After the effective date of this AD, do not install an HPT 1st-
stage hub having P/N 30G8501 or an HPT 2nd-stage hub having P/N 
30G7202 and an S/N listed in Table 1 of PW SI No. 240F-23, dated 
November 30, 2023, in any engine.

(i) Definitions

    (1) For the purposes of this AD, ``PW1500G'' engines are PW 
Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, 
PW1525G, and PW1525G-3 engines.

[[Page 1042]]

    (2) For the purposes of this AD, ``PW1900G'' engines are PW 
Model PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines.
    (3) For the purposes of this AD, a ``part eligible for 
installation'' is:
    (i) Any HPC 7th-stage rotor, P/N 30G5307 or later approved P/N.
    (ii) Any HPC 8th-stage disk, P/N 30G7208, that has passed the 
AUSI required by paragraph (g) of this AD or later approved P/N.
    (iii) Any HPC rear hub, P/N 30G7308 or later approved P/N.
    (iv) Any HPT 1st-stage hub, P/N 30G8501, that has passed the 
AUSI required by paragraph (g) of this AD or later approved P/N.
    (v) Any HPT 2nd-stage hub, P/N 30G7202, that has passed the AUSI 
required by paragraph (g) of this AD or later approved P/N.
    (vi) Any HPT 1st-stage air seal, P/N 30G5195 or later approved 
P/N.
    (vii) Any HPT 2nd-stage air seal, P/N 30G5196 or later approved 
P/N.
    (viii) Any HPT 1st-stage blade retaining plate, P/N 30G5193 or 
later approved P/N.
    (ix) Any HPT 2nd-stage blade retaining plate, P/N 30G5194 or 
later approved P/N.
    (4) For the purposes of this AD, a ``piece-part exposure'' is 
when the part is disassembled from the rotor assembly.
    (5) For the purposes of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except for the 
following situations, which do not constitute an engine shop visit.
    (i) The separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance.
    (ii) Fan case maintenance or replacement.
    (6) For the purposes of this AD, an ``HPC engine shop visit'' is 
when the HPC rotor assembly is removed from the engine.

(j) Credit for Previous Actions

    This paragraph provides credit for the initial AUSI of the HPC 
8th-stage disk, HPT 1st-stage hub and HPT 2nd-stage hub specified in 
paragraph (g)(1), (2), (4) and (5) of this AD, if the initial AUSI 
was performed before the effective date of this AD using the 
following service information;
    (1) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 001, dated 
March 16, 2023; or
    (2) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 001, dated 
March 22, 2023; or
    (3) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 002, dated 
June 19, 2023; or
    (4) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 003, dated 
August 14, 2023; or
    (5) PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 001, dated 
March 16, 2023; or
    (6) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 001, dated 
March 22, 2023; or
    (7) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 002, dated 
June 19, 2023.; or
    (8) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 003, dated 
August 14, 2023.

(k) 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 AIR-520 Continued Operational 
Safety Branch, send it to the attention of the person identified in 
paragraph (l)(1) 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.

(l) Additional Information

    (1) 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: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (4) of this AD.

(m) 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 (PW) Alert Service Bulletin (ASB) PW1000G-A-
72-00-0141-00B-930A-D, Issue No: 002, dated November 30, 2023.
    (ii) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004, 
dated November 30, 2023.
    (iii) PW ASB PW1000G-A-72-00-0150-00B-930A-D Issue No:001, dated 
November 30, 2023.
    (iv) PW ASB PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001, 
dated November 30, 2023.
    (v) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002, dated 
November 30, 2023.
    (vi) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004, 
dated November 30, 2023.
    (vii) PW ASB PW1000G-A-72-00-0204-00A-930A-D Issue No:001, dated 
November 30, 2023.
    (viii) PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001, 
dated November 30, 2023.
    (ix) PW Special Instruction No. 240F-23, dated November 30, 
2023.
    (3) For PW service information identified in this AD, contact 
International Aero Engines, LLC, 400 Main Street, East Hartford, CT 
06118; phone: (860) 565-0140; email: [email protected]; website: 
connect.prattwhitney.com.
    (4) 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.
    (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 December 27, 2023.
Caitlin Locke,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2024-00309 Filed 1-5-24; 4:15 pm]
BILLING CODE 4910-13-P
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