Airworthiness Directives; GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Engines, 4181-4184 [2024-01218]

Download as PDF Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations (ii) The sensing element has been tested and found to be serviceable as specified in paragraph (i) of this AD; and the sensing element has been marked on one face of one connector hex nut with one green mark, as specified in Figure 11 of Bombardier Service Bulletin 100–36–10, dated December 23, 2022, or Bombardier Service Bulletin 350– 36–003, dated December 23, 2022, as applicable (the figure is representative for all sensing elements). (2) For purposes of this AD, a serviceable part is a sensing element that is not an affected part. khammond on DSKJM1Z7X2PROD with RULES (h) Revision of the Existing Airplane Flight Manual (AFM) For airplane serial numbers 20001 through 20457 inclusive and 20501 through 20906 inclusive: Within 30 days after the effective date of this AD, revise the existing AFM to include the information specified in paragraphs (h)(1) and (2) of this AD, as applicable. (1) For airplane serial numbers 20001 through 20457 inclusive: Section 05–42, Air Conditioning & Pressurization, Non-Normal Procedures Section, Bombardier Challenger 300 AFM (Imperial Version), Publication No. CSP 100–1, Revision 71, dated November 9, 2022. Note 1 to Paragraph (h)(1): For obtaining the procedures for Bombardier Challenger 300 AFM (Imperial Version), Publication No. CSP 100–1, use Document Identification No. CH 300 AFM–I. (2) For airplane serial numbers 20501 through 20906 inclusive: Section 05–42, Airconditioning & Pressurization, NonNormal Procedures Section, Bombardier Challenger 350 AFM, Publication No. CH 350 AFM, Revision 37, dated November 9, 2022. Note 2 to Paragraph (h)(2): For obtaining the procedures for Bombardier Challenger 350 AFM, Publication No. CH 350 AFM, use Document Identification No. CH 350 AFM. (i) Testing of Overheat Detection Sensing Elements For airplane serial numbers 20001 through 20457 inclusive and 20501 through 20906 inclusive: Within 7,500 flight cycles or 96 months, whichever occurs first, from the effective date of this AD, test the overheat detection sensing elements to determine if they are serviceable, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–36–10, dated December 23, 2022; or Bombardier Service Bulletin 350–36–003, dated December 23, 2022, as applicable. (1) For each sensing element that is serviceable, before further flight, mark the sensing element with a witness mark in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–36–10, dated December 23, 2022; or Bombardier Service Bulletin 350–36–003, dated December 23, 2022; as applicable. (2) For each sensing element that is not serviceable, before further flight, replace the sensing element with a serviceable part in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–36–10, dated December 23, 2022; or Bombardier Service Bulletin 350–36–003, dated December 23, 2022; as applicable. VerDate Sep<11>2014 16:06 Jan 22, 2024 Jkt 262001 (j) Parts Installation Prohibition As of the effective date of this AD, no person may install an affected part on any airplane. (k) No Reporting Requirement Although Bombardier Service Bulletin 100–36–10, dated December 23, 2022; and Bombardier Service Bulletin 350–36–003, dated December 23, 2022; specify to submit certain information to the manufacturer, this AD does not include that requirement. (l) Additional AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the International Validation Branch, mail it to the address identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-AVS-NYACO-COS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or Transport Canada; or Bombardier, Inc.’s Transport Canada Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (m) Additional Information (1) Refer to Transport Canada AD CF– 2023–09, dated February 14, 2023, for related information. This Transport Canada AD may be found in the AD docket at regulations.gov under Docket No. FAA–2023–1890. (2) For more information about this AD, contact Steven Dzierzynski, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7300; email 9-avs-nyaco-cos@faa.gov. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 100–36–10, dated December 23, 2022. (ii) Bombardier Service Bulletin 350–36– 003, dated December 23, 2022. (iii) Section 05–42, Air Conditioning & Pressurization, Non-Normal Procedures Section, Bombardier Challenger 300 AFM (Imperial Version), Publication No. CSP 100– 1, Revision 71, dated November 9, 2022. Note 3 to Paragraph (n)(2)(iii): For obtaining the procedures for Bombardier PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 4181 Challenger 300 AFM (Imperial Version), Publication No. CSP 100–1, use Document Identification No. CH 300 AFM–I. (iv) Section 05–42, Air Conditioning & Pressurization, Non-Normal Procedures Section, Bombardier Challenger 350 AFM, Publication No. CH 350 AFM, Revision 37, dated November 9, 2022. Note 4 to Paragraph (n)(2)(iv): For obtaining the procedures for Bombardier Challenger 350 AFM, Publication No. CH 350 AFM, use Document Identification No. CH 350 AFM. (v) Liebherr Service Bulletin CFD–F1958– 26–01, dated May 6, 2022. (3) For Bombardier service information identified in this AD, contact Bombardier Business Aircraft Customer Response Center, 400 Coˆte-Vertu Road West, Dorval, Que´bec H4S 1Y9, Canada; telephone 514–855–2999; email ac.yul@aero.bombardier.com; website bombardier.com. (4) For Liebherr-Aerospace Toulouse SAS service information identified in this AD, contact Liebherr-Aerospace Toulouse SAS, 408, Avenue des Etats-Unis—B.P.52010, 31016 Toulouse Cedex, France; telephone +33 (0)5.61.35.28.28; fax +33 (0)5.61.35.29.29; email techpub.toulouse@ liebherr.com; website liebherr.aero. (5) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (6) 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 21, 2023. Caitlin Locke, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–01170 Filed 1–22–24; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–1811; Project Identifier MCAI–2023–00146–E; Amendment 39–22654; AD 2024–01–03] RIN 2120–AA64 Airworthiness Directives; GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2023–01– SUMMARY: E:\FR\FM\23JAR1.SGM 23JAR1 khammond on DSKJM1Z7X2PROD with RULES 4182 Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations 07 for all GE Aviation Czech s.r.o. (GEAC) (type certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model H75–100, H75–200, H80, H80–100, H80–200, H85–100, and H85–200 engines. AD 2023–01–07 required revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) and the operator’s existing approved maintenance or inspection program, as applicable, to incorporate updated coefficients and recalculate the cycles accumulated on critical parts. Since the FAA issued AD 2023–01–07, the manufacturer revised the ALS of the EMM to introduce new and more restrictive airworthiness limitations and associated thresholds and intervals for life-limited parts, which prompted this AD action. This AD requires revising the ALS of the existing EMM and the operator’s existing approved engine maintenance or inspection program, as applicable, to incorporate new and more restrictive instructions and associated thresholds and intervals for life-limited parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 27, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 27, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1811; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For service information identified in this final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find this VerDate Sep<11>2014 16:06 Jan 22, 2024 Jkt 262001 material on the EASA website at ad.easa.europa.eu. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–1811. FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 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 to supersede AD 2023–01–07, Amendment 39–22301 (88 FR 2501, January 17, 2023; corrected February 3, 2023 (88 FR 7355); corrected February 16, 2023 (88 FR 10013)) (AD 2023–01– 07). AD 2023–01–07 applied to GEAC Model H75–100, H75–200, H80, H80– 100, H80–200, H85–100, and H85–200 engines. AD 2023–01–07 required revising the ALS of the existing EMM and the operator’s existing approved maintenance or inspection program, as applicable, to incorporate the updated coefficients and recalculate the cycles accumulated on critical parts. The FAA issued AD 2023–01–07 to prevent failure of the engine. The NPRM published in the Federal Register on September 6, 2023 (88 FR 60896). The NPRM was prompted by EASA AD 2023–0021, dated January 23, 2023 (EASA AD 2023–0021) (also referred to as the MCAI), issued by EASA, which is Technical Agent for the Member States of the European Union. EASA AD 2023–0021 supersedes EASA AD 2022–0008. The MCAI states that the manufacturer revised the ALS to introduce new and more restrictive instructions and associated thresholds and intervals for life-limited parts. The MCAI also states that GEAC published an Alert Service Bulletin, ASB–H75–72– 10–00–0062, ASB–H80–72–10–00–0107, ASB–H85–72–10–00–0051, ASB– M601F–72–10–00–0070, ASB–M601E– 72–10–00–0120, ASB–M601D–72–10– 00–0087 and ASB–M601Z–72–10–00– 0069; Revision 1, dated January 20, 2023, published as a single document, PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 which provides instructions to determine the accumulated life of certain propeller shafts. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2023–1811. In the NPRM, the FAA proposed to require accomplishing the actions specified in the MCAI described previously, except for any differences identified as exceptions in the regulatory text of the proposed AD. 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. Related Service Information Under 1 CFR Part 51 The FAA reviewed EASA AD 2023– 0021, which specifies procedures for operators to revise the ALS of the existing EMM and the operator’s existing approved engine maintenance or inspection program, as applicable, to incorporate new and more restrictive instructions and associated thresholds and intervals for life-limited parts, as applicable to each engine model. 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. Costs of Compliance The FAA estimates that this AD affects 33 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: E:\FR\FM\23JAR1.SGM 23JAR1 4183 Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Revise the ALS ................................................. 1 work-hours × $85 per hour = $85 ................. $0 $85 $2,805 Authority for This Rulemaking PART 39—AIRWORTHINESS DIRECTIVES Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA has determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2023–01–07, Amendment 39–22301 (88 FR 2501, January 17, 2023; corrected February 3, 2023 (88 FR 7355); corrected February 16, 2023 (88 FR 10013)); and ■ b. Adding the following new airworthiness directive: ■ ■ 2024–01–03 GE Aviation Czech s.r.o. (Type Certificate Previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): Amendment 39– 22654; Docket No. FAA–2023–1811; Project Identifier MCAI–2023–00146–E. (a) Effective Date This airworthiness directive (AD) is effective February 27, 2024. (b) Affected ADs This AD replaces AD 2023–01–07, Amendment 39–22301 (88 FR 2501, January 17, 2023; corrected February 3, 2023 (88 FR 7355); corrected February 16, 2023 (88 FR 10013)). (c) Applicability This AD applies to GE Aviation Czech s.r.o. (type certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model H75–100, H75–200, H80, H80–100, H80–200, H85–100, and H85– 200 engines. (d) Subject Joint Aircraft System Component (JASC) Code 7200, Engine (Turbine/Turboprop). The Amendment (e) Unsafe Condition This AD was prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) to introduce new and more restrictive airworthiness limitations and associated thresholds and intervals for life-limited parts. The FAA is issuing this AD to prevent failure of the engine. The unsafe condition, if not addressed, could result in uncontained release of a critical part, damage to the engine, and damage to the airplane. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (f) Compliance Comply with this AD within the compliance times specified, unless already done. List of Subjects in 14 CFR Part 39 khammond on DSKJM1Z7X2PROD with RULES (g) Required Actions Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 16:06 Jan 22, 2024 Jkt 262001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 (1) Except as specified in paragraph (h) of this AD: Perform all required actions within the compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2023–0021, dated January 23, 2023 (EASA AD 2023–0021). (2) The action required by paragraph (g)(1) of this AD may be performed by the owner/ operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (h) Exceptions to EASA AD 2023–0021 (1) Where EASA AD 2023–0021 defines the AMP as ‘‘the approved Aircraft Maintenance Programme containing the tasks on the basis of which the scheduled maintenance is conducted to ensure the continuing airworthiness of each operated engine,’’ for this AD, replace that text with, ‘‘the aircraft maintenance program containing the tasks on the basis of which the scheduled maintenance is conducted to ensure the continuing airworthiness of each operated airplane.’’ (2) Where EASA AD 2023–0021 defines the ALS as ‘‘the Airworthiness Limitations Section of GEAC EMM No. 0983402 Revision 25, dated November 21, 2022,’’ for this AD, replace that text with, ‘‘the airworthiness limitations section of GEAC EMM No. 0983402 Revision 26, dated February 1, 2023.’’ The ALS in Revision 26 of the EMM is unchanged from Revision 25 of the EMM. (3) Where EASA AD 2023–0021 refers to its effective date, this AD requires using the effective date of this AD. (4) Where paragraph (3) of EASA AD 2023– 0021 specifies revising ‘‘the approved AMP within 12 months after the effective date of EASA AD 2023–0021,’’ replace that text with, ‘‘the ALS of the existing approved engine maintenance or inspection program, as applicable, within 90 days after the effective date of this AD.’’ (5) This AD does not require compliance with paragraphs (1), (2), (4), and (5) of EASA AD 2023–0021. (6) This AD does not adopt the Remarks paragraph of EASA AD 2023–0021. (i) Provisions for Alternative Actions and Intervals After performing the actions required by paragraph (g) of this AD, no alternative actions and associated thresholds and intervals, including life limits, are allowed unless they are approved as specified in the provisions of the ‘‘Ref. Publications’’ section of EASA AD 2023–0021. E:\FR\FM\23JAR1.SGM 23JAR1 4184 Federal Register / Vol. 89, No. 15 / Tuesday, January 23, 2024 / Rules and Regulations (j) Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD and email to ANE-AD-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Federal Aviation Administration (k) Additional Information For more information about this AD, contact Barbara Caufield, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (781) 238– 7146; email: barbara.caufield@faa.gov. (l) Material Incorporated by Reference khammond on DSKJM1Z7X2PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023–0021, dated January 23, 2023. (ii) [Reserved] (3) For EASA AD 2023–0021, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find this EASA AD on the EASA website at ad.easa.europa.eu. (4) You may view this service information at 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-locationsoremailfr.inspection@nara.gov. Issued on January 17, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024–01218 Filed 1–22–24; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:06 Jan 22, 2024 Jkt 262001 14 CFR Part 39 [Docket No. FAA–2023–1647; Project Identifier AD–2023–00487–E; Amendment 39–22650; AD 2023–26–07] RIN 2120–AA64 Airworthiness Directives; General Electric Company Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model GE90–90B, GE90–94B, GE90–110B1, and GE90–115B engines. This AD was prompted by a manufacturer investigation that revealed certain highpressure turbine (HPT) stage 1 disks, HPT stage 2 disks, forward HPT rotor seals, interstage HPT seals, and stages 7–9 compressor rotor spools were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of affected HPT stage 1 disks, HPT stage 2 disks, forward HPT rotor seals, interstage HPT seals, and stages 7–9 compressor rotor spools. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 27, 2024. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 27, 2024. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–1647; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Material Incorporated by Reference: • For service information identified in this final rule, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552–3272; email: aviation.fleetsupport@ ge.com; website: ge.com. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety SUMMARY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–1647. FOR FURTHER INFORMATION CONTACT: Alexei Marqueen, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238–7178; email: Alexei.T.Marqueen@ 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 GE Model GE90–90B, GE90–94B, GE90–110B1, and GE90– 115B engines. The NPRM published in the Federal Register on September 5, 2023 (88 FR 60603). The NPRM was prompted by the manufacturer’s detection of iron inclusion in a turbine disk manufactured from the same powder metal material used to manufacture certain HPT stage 1 disks, HPT stage 2 disks, forward HPT rotor seals, interstage HPT seals, and stages 7–9 compressor rotor spools for GE90– 90B, GE90–94B, GE90–110B1, and GE90–115B engines. Further investigation by the manufacturer determined that the iron inclusion is attributed to deficiencies in the manufacturing process and may cause reduced material properties and a lower fatigue life capability, which may result in premature fracture and subsequent uncontained failure. The FAA was also informed that GE communicated with affected operators having affected HPT stage 1 and stage 2 disks identified in Table 1 to Paragraph (c) of this AD regarding the corrective action for this unsafe condition. As a result, affected operators are already aware of the corrective action and have already performed the actions required by this AD. Therefore, the FAA has determined that the compliance time to replace these affected HPT stage 1 and stage 2 disks before further flight is appropriate. In the NPRM, the FAA proposed to require replacement of certain HPT stage 1 disks, HPT stage 2 disks, forward HPT rotor seals, interstage HPT seals, and stages 7–9 compressor rotor spools with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. Discussion of Final Airworthiness Directive Comments The FAA received comments from five commenters. Commenters included E:\FR\FM\23JAR1.SGM 23JAR1

Agencies

[Federal Register Volume 89, Number 15 (Tuesday, January 23, 2024)]
[Rules and Regulations]
[Pages 4181-4184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-01218]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1811; Project Identifier MCAI-2023-00146-E; 
Amendment 39-22654; AD 2024-01-03]
RIN 2120-AA64


Airworthiness Directives; GE Aviation Czech s.r.o. (Type 
Certificate Previously Held by WALTER Engines a.s., Walter a.s., and 
MOTORLET a.s.) Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2023-01-

[[Page 4182]]

07 for all GE Aviation Czech s.r.o. (GEAC) (type certificate previously 
held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Model H75-
100, H75-200, H80, H80-100, H80-200, H85-100, and H85-200 engines. AD 
2023-01-07 required revising the airworthiness limitations section 
(ALS) of the existing engine maintenance manual (EMM) and the 
operator's existing approved maintenance or inspection program, as 
applicable, to incorporate updated coefficients and recalculate the 
cycles accumulated on critical parts. Since the FAA issued AD 2023-01-
07, the manufacturer revised the ALS of the EMM to introduce new and 
more restrictive airworthiness limitations and associated thresholds 
and intervals for life-limited parts, which prompted this AD action. 
This AD requires revising the ALS of the existing EMM and the 
operator's existing approved engine maintenance or inspection program, 
as applicable, to incorporate new and more restrictive instructions and 
associated thresholds and intervals for life-limited parts, as 
specified in a European Union Aviation Safety Agency (EASA) AD, which 
is incorporated by reference (IBR). The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective February 27, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 27, 
2024.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-1811; or in person at Docket Operations between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this final rule, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information identified in this final rule, 
contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: 
+49 221 8999 000; email: [email protected]; website: easa.europa.eu. 
You may find this material on the EASA website at ad.easa.europa.eu.
     You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (817) 222-5110. It is 
also available at regulations.gov under Docket No. FAA-2023-1811.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety 
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
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 to supersede AD 2023-01-07, Amendment 39-22301 (88 FR 2501, 
January 17, 2023; corrected February 3, 2023 (88 FR 7355); corrected 
February 16, 2023 (88 FR 10013)) (AD 2023-01-07). AD 2023-01-07 applied 
to GEAC Model H75-100, H75-200, H80, H80-100, H80-200, H85-100, and 
H85-200 engines. AD 2023-01-07 required revising the ALS of the 
existing EMM and the operator's existing approved maintenance or 
inspection program, as applicable, to incorporate the updated 
coefficients and recalculate the cycles accumulated on critical parts. 
The FAA issued AD 2023-01-07 to prevent failure of the engine.
    The NPRM published in the Federal Register on September 6, 2023 (88 
FR 60896). The NPRM was prompted by EASA AD 2023-0021, dated January 
23, 2023 (EASA AD 2023-0021) (also referred to as the MCAI), issued by 
EASA, which is Technical Agent for the Member States of the European 
Union. EASA AD 2023-0021 supersedes EASA AD 2022-0008. The MCAI states 
that the manufacturer revised the ALS to introduce new and more 
restrictive instructions and associated thresholds and intervals for 
life-limited parts. The MCAI also states that GEAC published an Alert 
Service Bulletin, ASB-H75-72-10-00-0062, ASB-H80-72-10-00-0107, ASB-
H85-72-10-00-0051, ASB-M601F-72-10-00-0070, ASB-M601E-72-10-00-0120, 
ASB-M601D-72-10-00-0087 and ASB-M601Z-72-10-00-0069; Revision 1, dated 
January 20, 2023, published as a single document, which provides 
instructions to determine the accumulated life of certain propeller 
shafts.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2023-1811.
    In the NPRM, the FAA proposed to require accomplishing the actions 
specified in the MCAI described previously, except for any differences 
identified as exceptions in the regulatory text of the proposed AD.

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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed EASA AD 2023-0021, which specifies procedures for 
operators to revise the ALS of the existing EMM and the operator's 
existing approved engine maintenance or inspection program, as 
applicable, to incorporate new and more restrictive instructions and 
associated thresholds and intervals for life-limited parts, as 
applicable to each engine model.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 33 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

[[Page 4183]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                Action                         Labor cost          Parts cost       product         operators
----------------------------------------------------------------------------------------------------------------
Revise the ALS........................  1 work-hours x $85 per             $0              $85           $2,805
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

    The FAA has determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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:
0
a. Removing Airworthiness Directive 2023-01-07, Amendment 39-22301 (88 
FR 2501, January 17, 2023; corrected February 3, 2023 (88 FR 7355); 
corrected February 16, 2023 (88 FR 10013)); and
0
b. Adding the following new airworthiness directive:

2024-01-03 GE Aviation Czech s.r.o. (Type Certificate Previously 
held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): 
Amendment 39-22654; Docket No. FAA-2023-1811; Project Identifier 
MCAI-2023-00146-E.

(a) Effective Date

    This airworthiness directive (AD) is effective February 27, 
2024.

(b) Affected ADs

    This AD replaces AD 2023-01-07, Amendment 39-22301 (88 FR 2501, 
January 17, 2023; corrected February 3, 2023 (88 FR 7355); corrected 
February 16, 2023 (88 FR 10013)).

(c) Applicability

    This AD applies to GE Aviation Czech s.r.o. (type certificate 
previously held by WALTER Engines a.s., Walter a.s., and MOTORLET 
a.s.) Model H75-100, H75-200, H80, H80-100, H80-200, H85-100, and 
H85-200 engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7200, Engine 
(Turbine/Turboprop).

(e) Unsafe Condition

    This AD was prompted by the manufacturer revising the 
airworthiness limitations section (ALS) of the existing engine 
maintenance manual (EMM) to introduce new and more restrictive 
airworthiness limitations and associated thresholds and intervals 
for life-limited parts. The FAA is issuing this AD to prevent 
failure of the engine. The unsafe condition, if not addressed, could 
result in uncontained release of a critical part, damage to the 
engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Except as specified in paragraph (h) of this AD: Perform all 
required actions within the compliance times specified in, and in 
accordance with, European Union Aviation Safety Agency (EASA) AD 
2023-0021, dated January 23, 2023 (EASA AD 2023-0021).
    (2) The action required by paragraph (g)(1) of this AD may be 
performed by the owner/operator (pilot) holding at least a private 
pilot certificate and must be entered into the aircraft records 
showing compliance with this AD in accordance with 14 CFR 43.9(a) 
and 91.417(a)(2)(v). The record must be maintained as required by 14 
CFR 91.417, 121.380, or 135.439.

(h) Exceptions to EASA AD 2023-0021

    (1) Where EASA AD 2023-0021 defines the AMP as ``the approved 
Aircraft Maintenance Programme containing the tasks on the basis of 
which the scheduled maintenance is conducted to ensure the 
continuing airworthiness of each operated engine,'' for this AD, 
replace that text with, ``the aircraft maintenance program 
containing the tasks on the basis of which the scheduled maintenance 
is conducted to ensure the continuing airworthiness of each operated 
airplane.''
    (2) Where EASA AD 2023-0021 defines the ALS as ``the 
Airworthiness Limitations Section of GEAC EMM No. 0983402 Revision 
25, dated November 21, 2022,'' for this AD, replace that text with, 
``the airworthiness limitations section of GEAC EMM No. 0983402 
Revision 26, dated February 1, 2023.'' The ALS in Revision 26 of the 
EMM is unchanged from Revision 25 of the EMM.
    (3) Where EASA AD 2023-0021 refers to its effective date, this 
AD requires using the effective date of this AD.
    (4) Where paragraph (3) of EASA AD 2023-0021 specifies revising 
``the approved AMP within 12 months after the effective date of EASA 
AD 2023-0021,'' replace that text with, ``the ALS of the existing 
approved engine maintenance or inspection program, as applicable, 
within 90 days after the effective date of this AD.''
    (5) This AD does not require compliance with paragraphs (1), 
(2), (4), and (5) of EASA AD 2023-0021.
    (6) This AD does not adopt the Remarks paragraph of EASA AD 
2023-0021.

(i) Provisions for Alternative Actions and Intervals

    After performing the actions required by paragraph (g) of this 
AD, no alternative actions and associated thresholds and intervals, 
including life limits, are allowed unless they are approved as 
specified in the provisions of the ``Ref. Publications'' section of 
EASA AD 2023-0021.

[[Page 4184]]

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation 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, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; 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 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) European Union Aviation Safety Agency (EASA) AD 2023-0021, 
dated January 23, 2023.
    (ii) [Reserved]
    (3) For EASA AD 2023-0021, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; phone: +49 221 8999 000; email: 
[email protected]; website: easa.europa.eu. You may find this EASA 
AD on the EASA website at ad.easa.europa.eu.
    (4) You may view this service information at 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/[email protected]">www.archives.gov/federal-register/cfr/[email protected].

    Issued on January 17, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-01218 Filed 1-22-24; 8:45 am]
BILLING CODE 4910-13-P
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