Airworthiness Directives; Pratt & Whitney Canada Corp. Engines, 12679-12682 [2025-04441]

Download as PDF 12679 Rules and Regulations Federal Register Vol. 90, No. 52 Wednesday, March 19, 2025 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. NUCLEAR REGULATORY COMMISSION 10 CFR Part 72 [NRC–2024–0182] RIN 3150–AL22 List of Approved Spent Fuel Storage Casks: Holtec International HI–STORM UMAX Canister Storage System, Certificate of Compliance No. 1040, Revision 1 to Amendment Nos. 0 Through 2 Nuclear Regulatory Commission. ACTION: Direct final rule; confirmation of effective date. AGENCY: The U.S. Nuclear Regulatory Commission (NRC) is confirming the effective date of April 21, 2025, for the direct final rule that was published in the Federal Register on February 4, 2025. This direct final rule amended the NRC’s spent fuel storage regulations by revising the Holtec International HI– STORM UMAX Canister Storage System listing within the ‘‘List of approved spent fuel storage casks’’ to include Revision 1 to Amendment Nos. 0 through 2 to Certificate of Compliance (CoC) No. 1040. Revision 1 to Amendment Nos. 0 through 2 updates the CoC appendix A technical specifications for radiation protection and the associated bases information to clearly articulate the basis for the dose rate limits for the closure lids, modify the dose rate limit values and the description of the location of the dose rate measurements, and make other editorial changes. DATES: Effective date: The effective date of April 21, 2025, for the direct final rule published February 4, 2025 (90 FR 8861), is confirmed. ADDRESSES: Please refer to Docket ID NRC–2024–0182 when contacting the NRC about the availability of information for this action. You may obtain publicly available information lotter on DSK11XQN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 15:54 Mar 18, 2025 Jkt 265001 related to this action by any of the following methods: • Federal Rulemaking Website: Go to https://www.regulations.gov and search for Docket ID NRC–2024–0182. Address questions about NRC dockets to Helen Chang; telephone: 301–415–3228; email: Helen.Chang@nrc.gov. For technical questions, contact the individual listed in the FOR FURTHER INFORMATION CONTACT section of this document. • NRC’s Agencywide Documents Access and Management System (ADAMS): You may obtain publicly available documents online in the ADAMS Public Documents collection at https://www.nrc.gov/reading-rm/ adams.html. To begin the search, select ‘‘Begin Web-based ADAMS Search.’’ For problems with ADAMS, please contact the NRC’s Public Document Room (PDR) reference staff at 1–800–397–4209, at 301–415–4737, or by email to PDR.Resource@nrc.gov. The revision of Certificate of Compliance No. 1040, the associated change(s) to the technical specification(s), and the final safety evaluation report(s) are available in ADAMS under Accession No. ML25065A166. • NRC’s PDR: The PDR, where you may examine and order copies of publicly available documents, is open by appointment. To make an appointment to visit the PDR, please send an email to PDR.Resource@nrc.gov or call 1–800–397–4209 or 301–415– 4737, between 8 a.m. and 4 p.m. eastern time, Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: George Tartal, Office of Nuclear Materials Safety and Safeguards, U.S. Nuclear Regulatory Commission, Washington, DC 20555–0001; telephone: 301–415–0016, email: George.Tartal@ nrc.gov. SUPPLEMENTARY INFORMATION: On February 4, 2025 (90 FR 8861), the NRC published a direct final rule amending its regulations in part 72 of title 10 of the Code of Federal Regulations to revise Amendment Nos. 0 through 2 to CoC No. 1040 for the Holtec International, HI–STORM UMAX Cannister Storage System. Revision 1 to Amendment Nos. 0 through 2 update the CoC appendix A technical specifications for radiation protection and the associated bases information to clearly articulate the basis for the dose rate limits for the closure lids, modify PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 the dose rate limit values and the description of the location of the dose rate measurements, and make other editorial changes. In the direct final rule, the NRC stated that if no significant adverse comments were received, the direct final rule would become effective on April 21, 2025. The NRC received one comment on the direct final rule that was out of scope and not significantly adverse. Therefore, this direct final rule will become effective as scheduled. Dated: March 14, 2025. For the Nuclear Regulatory Commission. Araceli Billoch Colon, Chief, Regulatory Analysis and Rulemaking Support Branch, Division of Rulemaking, Environmental, and Financial Support Office of Nuclear Material Safety and Safeguards. [FR Doc. 2025–04624 Filed 3–18–25; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2539; Project Identifier MCAI–2023–00971–E; Amendment 39–22985; AD 2025–05–13] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) Model PW535E and PW535E1 engines. This AD was prompted by a manufacturer design review that indicated certain flange bolts securing the gas generator case and turbine support case are susceptible to cracking at their current low-cycle fatigue (LCF) life. This AD requires repetitive borescope inspections (BSI) of the gas generator case to turbine support case retaining bolts for evidence of bolt cracks, bolt fracture, missing bolts, or loose bolts and replacement, if necessary, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\19MRR1.SGM 19MRR1 12680 Federal Register / Vol. 90, No. 52 / Wednesday, March 19, 2025 / Rules and Regulations This AD is effective April 23, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 23, 2025. DATES: ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No.FAA–2024–2539; 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 Transport Canada material identified in this AD, contact Transport Canada, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, Canada; phone: (888) 663–3639; email: TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca; website: tc.canada.ca/en/aviation. • You may view this material 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– 2024–2539. FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7146; email: barbara.caufield@ faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain P&WC Model PW535E and PW535E1 engines. The NPRM published in the Federal Register on November 26, 2024 (89 FR 93225). The NPRM was prompted by Transport Canada AD CF–2023–60, dated August 14, 2023 (Transport Canada AD CF– 2023–60) (also referred to as the MCAI), issued by Transport Canada, which is the aviation authority for Canada. The MCAI states that data from a design review by the manufacturer identified insufficient LCF life for flange bolts, having part number (P/N) MS9696–08 and P/N MS9489–06, that secure the engine gas generator and turbine support cases. At certain high-stress circumferential locations, LCF cracks could develop on the flange bolt and lead to fracture of the bolt. Multiple fractured bolts could lead to flange separation or case rupture, which may damage the engine and the airplane. To address this unsafe condition, the manufacturer published material that provides instructions for repetitive BSIs and replacement of the affected parts. In the NPRM, the FAA proposed to require repetitive BSI of the gas generator case to turbine support case retaining bolts for evidence of bolt cracks, bolt fracture, missing bolts, or loose bolts, and replacement, if necessary. The FAA is issuing this AD to address the unsafe condition on these products. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2024–2539. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. 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 and determined that air safety requires adopting this 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. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed Transport Canada AD CF–2023–60, which identifies the affected gas generator case to turbine support case retaining bolts and specifies procedures for repetitive BSIs and replacement. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Differences Between This AD and the MCAI Where the service information referenced in Transport Canada AD CF– 2023–60 requires reporting certain information to the manufacturer, this AD does not require such a submission. Costs of Compliance The FAA estimates that this AD affects 521 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost BSI of gas generator case to turbine support case retaining bolts. 2 work-hours × $85 per hour = $170 ............. lotter on DSK11XQN23PROD with RULES1 The FAA estimates the following costs to do any necessary replacements VerDate Sep<11>2014 15:54 Mar 18, 2025 Jkt 265001 that are required based on the results of the inspection. The agency has no way PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $170 Cost on U.S. operators $88,570 of determining the number of engines that might need these replacements: E:\FR\FM\19MRR1.SGM 19MRR1 Federal Register / Vol. 90, No. 52 / Wednesday, March 19, 2025 / Rules and Regulations 12681 ON-CONDITION COSTS Action Labor cost 4 work-hours × $85 per hour = $340 ........................... Replacement of the gas generator case to turbine support case retaining bolts. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (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. lotter on DSK11XQN23PROD with RULES1 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: VerDate Sep<11>2014 15:54 Mar 18, 2025 Jkt 265001 Parts cost PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(f), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2025–05–13 Pratt & Whitney Canada Corp.: Amendment 39–22985; Docket No. FAA–2024–2539; Project Identifier MCAI–2023–00971–E. (a) Effective Date This airworthiness directive (AD) is effective April 23, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Pratt & Whitney Canada Corp. (P&WC) Model PW535E and PW535E1 engines, as identified in Transport Canada Civil Aviation AD CF–2023–60, dated August 14, 2023 (Transport Canada AD CF–2023– 60). (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by a manufacturer design review that indicated certain flange bolts securing the gas generator case and turbine support case have an inadequate lowcycle fatigue life. The FAA is issuing this AD to prevent crack, fracture, missing, or loosening of the gas generator case to turbine support case retaining bolts. The unsafe condition, if not addressed, could result in uncontained engine debris, 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 Except as specified in paragraphs (h) and (i) of this AD: Perform all required actions within the compliance times specified in, and in accordance with, Transport Canada AD CF–2023–60. (h) Exceptions to Transport Canada AD CF– 2023–60 (1) Where Transport Canada AD CF–2023– 60 requires compliance from its effective date, this AD requires using the effective date of this AD. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 $337,701 Cost per product $338,041 (2) Where paragraph A.1. of Transport Canada AD CF–2023–60 refers to ‘‘discrepancy,’’ this AD defines that as ‘‘evidence of bolt cracks, bolt fracture, missing bolts, or loose bolts.’’ (3) Where paragraph A.2. in Transport Canada AD CF–2023–60 specifies to ‘‘Repeat the above paragraph A.1. inspection and rectification requirements of this AD at intervals not to exceed 400 engine cycles,’’ this AD requires replacing that text with ‘‘Repeat the above paragraph A.1. inspection and rectification requirements of this AD thereafter at intervals not to exceed 400 engine cycles.’’ (4) Where paragraph A.1. in Transport Canada AD CF–2023–60 specifies to ‘‘Inspect the bolts P/N MS9696–08 and P/N MS9489– 06 within 400 cycles from the effective date of this AD,’’ this AD requires replacing that text with ‘‘Inspect affected bolts having P/N MS9696–08 and P/N MS9489–06 within 400 engine cycles from the effective date of this AD.’’ (5) Where paragraph A.1. in Transport Canada AD CF–2023–60 specifies to ‘‘rectify any discrepancy in accordance with the Accomplishment Instructions of the applicable SB,’’ this AD requires replacing that text with ‘‘Following inspection, if any bolts are determined to be in an unserviceable condition, before further flight, replace the affected bolts in accordance with the applicable SB.’’ (i) No Reporting Requirement Although the service information referenced in Transport Canada AD CF– 2023–60 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) 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 (k) of this AD and email to: 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. (k) Additional Information For more information about this AD, contact Barbara Caufield, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des E:\FR\FM\19MRR1.SGM 19MRR1 12682 Federal Register / Vol. 90, No. 52 / Wednesday, March 19, 2025 / Rules and Regulations Moines, WA 98198; phone: (781) 238–7146; email: barbara.caufield@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Transport Canada AD CF–2023–60, dated August 14, 2023. (ii) [Reserved] (3) For Transport Canada material identified in this AD, contact Transport Canada, Transport Canada National Aircraft Certification, 159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; phone: (888) 663– 3639; email: TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca; website: tc.canada.ca/en/aviation. (4) You may view this material 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 March 6, 2025. Peter A. White, Deputy Director, Integrated Certificate Management Division, Aircraft Certification Service. [FR Doc. 2025–04441 Filed 3–18–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2024–2420; Project Identifier MCAI–2024–00143–T; Amendment 39–22978; AD 2025–05–06] RIN 2120–AA64 Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes lotter on DSK11XQN23PROD with RULES1 Correction In rule document, 2025–03880, appearing on pages 11800 through 11802, in the issue of Wednesday, March 12, 2025, make the following correction: D On page 11800, in the second column, under the heading DATES, in the first and second lines, ‘‘April 18, 3036’’ should read‘‘April 16, 2025’’. ■ On page 11801, in the third column, on the twentieth line from the bottom of VerDate Sep<11>2014 15:54 Mar 18, 2025 Jkt 265001 the page, Section 39.13 is corrected as set forth below. * * * * * § 39.13 * [Corrected] * * * * (a) Effective Date This airworthiness directive (AD) is effective April 16, 2025. * * * * * [FR Doc. C1–2025–03880 Filed 3–13–25; 5:15 pm] BILLING CODE 0099–10–D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–2151; Project Identifier AD–2023–00984–T; Amendment 39–22990; AD 2025–06–02] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes. This AD was prompted by a report of a 5-inch crack on the upper wing skin at a certain wing station of the right wing. This AD requires repetitive inspections for cracking of the upper wing skin common to certain fasteners and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 23, 2025. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 23, 2025. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–2151; 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 Boeing material identified in this AD, contact Boeing Commercial SUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; website myboeingfleet.com. • You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at regulations.gov under Docket No. FAA–2023–2151. Luis Cortez-Muniz, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206–231–3958; email: Luis.A.Cortez-Muniz@faa.gov. FOR FURTHER INFORMATION CONTACT: 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 The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes. The NPRM published in the Federal Register on November 17, 2023 (88 FR 80216). The NPRM was prompted by a report of a 5inch crack on the upper wing skin at wing station (WSTA) 460 of the right wing. In the NPRM, the FAA proposed to require repetitive inspections for cracking of the upper wing skin common to certain fasteners and applicable on-condition actions, including repair. The FAA issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes. The SNPRM published in the Federal Register on September 20, 2024 (89 FR 77049). The SNPRM was prompted by reports from Boeing of two events of cracking at the fastener 6 and 7 locations where the cracks initiated in the spanwise (inboard/outboard) direction. These cracks were detected only because of a repair accomplished on an adjacent fastener. The areas around the repaired fasteners were subsequently inspected with an open hole high frequency eddy current (HFEC) inspection, rather than with the ultrasonic (UT) inspection that was proposed in the NPRM. The SNPRM therefore proposed to require open hole HFEC inspections instead of UT inspections. The FAA is issuing this AD to address the possibility of an undetected upper wing skin crack. E:\FR\FM\19MRR1.SGM 19MRR1

Agencies

[Federal Register Volume 90, Number 52 (Wednesday, March 19, 2025)]
[Rules and Regulations]
[Pages 12679-12682]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-04441]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-2539; Project Identifier MCAI-2023-00971-E; 
Amendment 39-22985; AD 2025-05-13]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada Corp. Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Pratt & Whitney Canada Corp. (P&WC) Model PW535E and PW535E1 
engines. This AD was prompted by a manufacturer design review that 
indicated certain flange bolts securing the gas generator case and 
turbine support case are susceptible to cracking at their current low-
cycle fatigue (LCF) life. This AD requires repetitive borescope 
inspections (BSI) of the gas generator case to turbine support case 
retaining bolts for evidence of bolt cracks, bolt fracture, missing 
bolts, or loose bolts and replacement, if necessary, as specified in a 
Transport Canada AD, which is incorporated by reference. The FAA is 
issuing this AD to address the unsafe condition on these products.

[[Page 12680]]


DATES: This AD is effective April 23, 2025.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 23, 
2025.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No.FAA-2024-2539; 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 Transport Canada material identified in this AD, 
contact Transport Canada, Transport Canada National Aircraft 
Certification, 159 Cleopatra Drive, Nepean, Ontario, K1A 0N5, Canada; 
phone: (888) 663-3639; email: [email protected]; website: tc.canada.ca/en/aviation.
     You may view this material 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-2024-2539.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety 
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 
(781) 238-7146; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain P&WC Model 
PW535E and PW535E1 engines. The NPRM published in the Federal Register 
on November 26, 2024 (89 FR 93225). The NPRM was prompted by Transport 
Canada AD CF-2023-60, dated August 14, 2023 (Transport Canada AD CF-
2023-60) (also referred to as the MCAI), issued by Transport Canada, 
which is the aviation authority for Canada. The MCAI states that data 
from a design review by the manufacturer identified insufficient LCF 
life for flange bolts, having part number (P/N) MS9696-08 and P/N 
MS9489-06, that secure the engine gas generator and turbine support 
cases. At certain high-stress circumferential locations, LCF cracks 
could develop on the flange bolt and lead to fracture of the bolt. 
Multiple fractured bolts could lead to flange separation or case 
rupture, which may damage the engine and the airplane. To address this 
unsafe condition, the manufacturer published material that provides 
instructions for repetitive BSIs and replacement of the affected parts.
    In the NPRM, the FAA proposed to require repetitive BSI of the gas 
generator case to turbine support case retaining bolts for evidence of 
bolt cracks, bolt fracture, missing bolts, or loose bolts, and 
replacement, if necessary. The FAA is issuing this AD to address the 
unsafe condition on these products.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2024-2539.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

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 and 
determined that air safety requires adopting this 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.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed Transport Canada AD CF-2023-60, which identifies 
the affected gas generator case to turbine support case retaining bolts 
and specifies procedures for repetitive BSIs and replacement.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Differences Between This AD and the MCAI

    Where the service information referenced in Transport Canada AD CF-
2023-60 requires reporting certain information to the manufacturer, 
this AD does not require such a submission.

Costs of Compliance

    The FAA estimates that this AD affects 521 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
BSI of gas generator case to turbine    2 work-hours x $85 per                $0            $170         $88,570
 support case retaining bolts.           hour = $170.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that are required based on the results of the inspection. 
The agency has no way of determining the number of engines that might 
need these replacements:

[[Page 12681]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of the gas generator case to        4 work-hours x $85 per hour =           $337,701        $338,041
 turbine support case retaining bolts.           $340.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (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

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

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


Sec.  39.13  [Amended]

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

2025-05-13 Pratt & Whitney Canada Corp.: Amendment 39-22985; Docket 
No. FAA-2024-2539; Project Identifier MCAI-2023-00971-E.

(a) Effective Date

    This airworthiness directive (AD) is effective April 23, 2025.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pratt & Whitney Canada Corp. (P&WC) Model 
PW535E and PW535E1 engines, as identified in Transport Canada Civil 
Aviation AD CF-2023-60, dated August 14, 2023 (Transport Canada AD 
CF-2023-60).

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a manufacturer design review that 
indicated certain flange bolts securing the gas generator case and 
turbine support case have an inadequate low-cycle fatigue life. The 
FAA is issuing this AD to prevent crack, fracture, missing, or 
loosening of the gas generator case to turbine support case 
retaining bolts. The unsafe condition, if not addressed, could 
result in uncontained engine debris, 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

    Except as specified in paragraphs (h) and (i) of this AD: 
Perform all required actions within the compliance times specified 
in, and in accordance with, Transport Canada AD CF-2023-60.

(h) Exceptions to Transport Canada AD CF-2023-60

    (1) Where Transport Canada AD CF-2023-60 requires compliance 
from its effective date, this AD requires using the effective date 
of this AD.
    (2) Where paragraph A.1. of Transport Canada AD CF-2023-60 
refers to ``discrepancy,'' this AD defines that as ``evidence of 
bolt cracks, bolt fracture, missing bolts, or loose bolts.''
    (3) Where paragraph A.2. in Transport Canada AD CF-2023-60 
specifies to ``Repeat the above paragraph A.1. inspection and 
rectification requirements of this AD at intervals not to exceed 400 
engine cycles,'' this AD requires replacing that text with ``Repeat 
the above paragraph A.1. inspection and rectification requirements 
of this AD thereafter at intervals not to exceed 400 engine 
cycles.''
    (4) Where paragraph A.1. in Transport Canada AD CF-2023-60 
specifies to ``Inspect the bolts P/N MS9696-08 and P/N MS9489-06 
within 400 cycles from the effective date of this AD,'' this AD 
requires replacing that text with ``Inspect affected bolts having P/
N MS9696-08 and P/N MS9489-06 within 400 engine cycles from the 
effective date of this AD.''
    (5) Where paragraph A.1. in Transport Canada AD CF-2023-60 
specifies to ``rectify any discrepancy in accordance with the 
Accomplishment Instructions of the applicable SB,'' this AD requires 
replacing that text with ``Following inspection, if any bolts are 
determined to be in an unserviceable condition, before further 
flight, replace the affected bolts in accordance with the applicable 
SB.''

(i) No Reporting Requirement

    Although the service information referenced in Transport Canada 
AD CF-2023-60 specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

(j) Alternative Methods of Compliance (AMOCs)

    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 (k) of this AD and email to: [email protected].
    (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.

(k) Additional Information

    For more information about this AD, contact Barbara Caufield, 
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des

[[Page 12682]]

Moines, WA 98198; phone: (781) 238-7146; email: 
[email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) Transport Canada AD CF-2023-60, dated August 14, 2023.
    (ii) [Reserved]
    (3) For Transport Canada material identified in this AD, contact 
Transport Canada, Transport Canada National Aircraft Certification, 
159 Cleopatra Drive, Nepean, Ontario K1A 0N5, Canada; phone: (888) 
663-3639; email: [email protected]; website: tc.canada.ca/en/
aviation.
    (4) You may view this material 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 March 6, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft 
Certification Service.
[FR Doc. 2025-04441 Filed 3-18-25; 8:45 am]
BILLING CODE 4910-13-P
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