Airworthiness Directives; GE Aviation Czech s.r.o. (Type Certificate Previously Held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.) Turboprop Engines, 78532-78535 [2022-27670]

Download as PDF 78532 Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2022–25–15 The Boeing Company: Amendment 39–22271; Docket No. FAA–2022–1061; Project Identifier AD– 2022–00441–T. (a) Effective Date This airworthiness directive (AD) is effective January 26, 2023. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. lotter on DSK11XQN23PROD with RULES1 (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report indicating that a crack was found in one of the holes of the wing rear spar lower chord at the main landing gear (MLG) aft fitting at wing buttock line (WBL) 157. The FAA is issuing this AD to address cracking in the rear spar lower chord at a fastener common to the MLG aft support fitting. This condition, if not addressed, could result in the inability of the rear spar lower chord to sustain limit loads, resulting in reduced structural integrity of the airplane and possible loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 16:02 Dec 21, 2022 Jkt 259001 (g) Required Actions for Group 1 Airplanes For airplanes identified as Group 1 in Boeing Alert Requirements Bulletin 737– 57A1353 RB, dated February 10, 2022: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (h) Required Actions for Group 2 and Group 3 Airplanes For airplanes identified as Group 2 and Group 3 in Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022: Except as specified by paragraph (i) of this AD, at the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022. Note 1 to paragraph (h): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 737–57A1353, dated February 10, 2022, which is referred to in Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022. (i) Exceptions to Service Information Specifications (1) Where the Compliance Time columns of the tables in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 737– 57A1353 RB, dated February 10, 2022, use the phrase ‘‘the original issue date of Requirements Bulletin 737–57A1353 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO 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 certification office, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Manager, Los Angeles ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact Wayne Ha, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5238; email: wayne.ha@faa.gov. (l) 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) Boeing Alert Requirements Bulletin 737–57A1353 RB, dated February 10, 2022. (ii) [Reserved] (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet myboeingfleet.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on November 30, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–27751 Filed 12–21–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–1239; Project Identifier MCAI–2022–00301–E; Amendment 39–22279; AD 2022–26–01] 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.) Turboprop Engines Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\22DER1.SGM 22DER1 Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations ACTION: Final rule. The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601D–11, M601E–11, M601E–11A, M601E–11AS, M601E–11S, M601F, H75–100, H75–200, H80, H80–100, H80–200, H85–100, and H85–200 model turboprop engines. This AD was prompted by reports of cracks in dilution tube weld areas of the combustion chamber outer liner. This AD requires initial and repetitive borescope inspections (BSIs) of the dilution tube weld areas of the combustion chamber outer liner and, depending on the results of the inspections, replacement of the combustion chamber outer liner with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 26, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 26, 2023. ADDRESSES: AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–1239; 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 GEAC service information identified in this final rule, contact GE Aviation Czech s.r.o., Beranovy´ch 65, 199 02 Praha 9, Letnˇany, Czech Republic; phone: +420 222 538 111. • You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information SUMMARY: on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2022–1239. FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 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 GEAC M601D–11, M601E–11, M601E–11A, M601E–11AS, M601E–11S, M601F, H75–100, H75– 200, H80, H80–100, H80–200, H85–100, and H85 200 model turboprop engines. The NPRM published in the Federal Register on September 27, 2022 (87 FR 58466). The NPRM was prompted by AD 2022–0034, dated March 4, 2022, issued by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union (referred to after this as ‘‘the MCAI’’). The MCAI states that occurrences of cracks in dilution tube weld areas of the combustion chamber outer liner have been reported. These cracks can lead to crack propagation, possibly resulting in part separation, loss of engine power, and reduced control of the aircraft. In the NPRM, the FAA proposed to require initial and repetitive BSIs of the dilution tube weld areas of the combustion chamber outer liner and, depending on the results of the inspections, corrective action in accordance with the service information. 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–2022–1239. 78533 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 GEAC Alert Service Bulletin (ASB) ASB–H75–72– 40–00–0056 [01], ASB–M601E–72–40– 00–0113 [01], ASB–H80–72–40–00– 0099 [01], ASB–M601D–72–40–00–0081 [01], ASB–M601F–72–40–00–0064 [01], ASB–M601Z–72–40–00–0063 [01], and ASB–H85–72–40–00–0045 [01], (single document; formatted as service bulletin identifier [revision number]), dated February 16, 2022. This service information specifies procedures for BSIs of the dilution tube weld areas of the combustion chamber outer liner and replacement of the combustion chamber outer liner. 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: lotter on DSK11XQN23PROD with RULES1 ESTIMATED COSTS Action Labor cost BSI of combustion chamber outer liner .......... 2.5 work-hours × $85 per hour = $212.50 ..... The FAA estimates the following costs to do any necessary replacements that would be required based on the VerDate Sep<11>2014 16:02 Dec 21, 2022 Jkt 259001 results of the inspection. The agency has no way of determining the number of PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 Cost on U.S. operators $212.50 aircraft that might need these replacements: E:\FR\FM\22DER1.SGM 22DER1 $7,012.50 78534 Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations ON-CONDITION COSTS Labor cost On-wing replacement of combustion chamber outer liner. In-shop replacement of combustion chamber outer liner. 64 work-hours × $85 per hour = $5,440 ...................... $74,909 $80,349 56 work-hours × $85 per hour = $4,760 ...................... 74,909 79,669 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. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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. lotter on DSK11XQN23PROD with RULES1 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. VerDate Sep<11>2014 16:02 Dec 21, 2022 Jkt 259001 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2022–26–01 GE Aviation Czech s.r.o (Type Certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): Amendment 39– 22279; Docket No. FAA–2022–1239; Project Identifier MCAI–2022–00301–E. (a) Effective Date This airworthiness directive (AD) is effective January 26, 2023. (b) Affected ADs None. (c) Applicability This AD applies to GE Aviation Czech s.r.o. (GEAC) M601D–11, M601E–11, M601E– 11A, M601E–11AS, M601E–11S, M601F, H75–100, H75–200, H80, H80–100, H80–200, H85–100, and H85–200 model turboprop engines installed on single-engine airplanes, with an installed combustion chamber outer liner having part numbers (P/Ns) M601– 229.3, M601–229.3A, M601–229.3B, M601– 229.31A, or M601–229.31B. (d) Subject Joint Aircraft System Component (JASC) Code 7240, Turbine Engine Combustion Section. (e) Unsafe Condition This AD was prompted by reports of cracks in dilution tube weld areas of the combustion chamber outer liner. The FAA is issuing this AD to prevent failure of the combustion chamber outer liner. The unsafe condition, if not addressed, could result in uncontained release of the combustion chamber outer liner, loss of engine power, and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Parts cost Cost per product Action (g) Required Actions (1) At the next 300-hour (Type 3) engine inspection, or within 25 flight hours (FHs) after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 300 FHs, perform a borescope inspection (BSI) of the dilution tube weld areas of the combustion chamber outer liner in accordance with the Accomplishment Instructions, paragraph 2.1 of GEAC Alert Service Bulletin (ASB) ASB–H75–72–40–00– 0056 [01], ASB–M601E–72–40–00–0113 [01], ASB–H80–72–40–00–0099 [01], ASB– M601D–72–40–00–0081 [01], ASB–M601F– 72–40–00–0064 [01], ASB–M601Z–72–40– 00–0063 [01], and ASB–H85–72–40–00–0045 [01] (single document; formatted as service bulletin identifier [revision number]), dated February 16, 2022 (the ASB). (2) If a crack is detected during any BSI required by paragraph (g)(1) of this AD, before further flight, perform the applicable corrective actions in accordance with the Accomplishment Instructions, paragraph 2.1, Table 1 of the ASB. (h) Terminating Action Replacing the affected combustion chamber outer liner with a combustion chamber outer liner that does not have P/N M601–229.3, M601–229.3A, M601–229.3B, M601–229.31A, or M601–229.31B, constitutes a terminating action for the repetitive inspections required by paragraph (g)(1) of this AD. (i) Conditional Part Installation (1) After the effective date of this AD, it is permissible to install an engine, having an affected combustion chamber outer liner installed, on a single-engine airplane, provided that prior to operation, the BSI required by paragraph (g)(1) of this AD is performed and, depending on the findings, the applicable corrective actions are performed as required by paragraph (g)(2) of this AD. (2) After the effective date of this AD, it is permissible to install an affected combustion chamber outer liner on the engine of a singleengine airplane, provided that it is a part eligible for installation, as defined in paragraph (j) of this AD, and provided that prior to operation, the BSI required by paragraph (g)(1) of this AD is performed and, depending on the findings, the applicable corrective actions are performed as required by paragraph (g)(2) of this AD. (j) Definitions For the purpose of this AD, a ‘‘part eligible for installation’’ is an affected combustion chamber outer liner, which was not previously installed on an engine, or an affected combustion chamber outer liner that, E:\FR\FM\22DER1.SGM 22DER1 Federal Register / Vol. 87, No. 245 / Thursday, December 22, 2022 / Rules and Regulations before installation, has passed an inspection (no defects found) in accordance with the Accomplishment Instructions, paragraphs 2.2 and 2.3 of the ASB, or a combustion chamber outer liner that does not have P/Ns M601– 229.3, M601–229.3A, M601–229.3B, M601– 229.31A, or M601–229.31B. www.archives.gov/federal-register/cfr/ibrlocations.html. (k) Alternative Methods of Compliance (AMOCs) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in § 39.19. In accordance with § 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 certification office, send it to the attention of the person identified in paragraph (l)(2) of this AD or email to: ANE-AD-AMOC@faa.gov. 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. [FR Doc. 2022–27670 Filed 12–21–22; 8:45 am] lotter on DSK11XQN23PROD with RULES1 (l) Additional Information (1) Refer to European Union Aviation Safety Agency (EASA) AD 2022–0034, dated March 4, 2022, for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA– 2022–1239. (2) For more information about this AD, contact Barbara Caufield, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7146; email: barbara.caufield@faa.gov. (m) 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) GE Aviation Czech s.r.o. (GEAC) Alert Service Bulletin (ASB) ASB–H75–72–40–00– 0056 [01], ASB–M601E–72–40–00–0113 [01], ASB–H80–72–40–00–0099 [01], ASB– M601D–72–40–00–0081 [01], ASB–M601F– 72–40–00–0064 [01], ASB–M601Z–72–40– 00–0063 [01], and ASB–H85–72–40–00–0045 [01] (single document; formatted as service bulletin identifier [revision number]), dated February 16, 2022. (ii) [Reserved] (3) For GEAC service information identified in this AD, contact GE Aviation Czech s.r.o., Beranovy´ch 65, 199 02 Praha 9, Letnˇany, Czech Republic; phone: +420 222 538 111. (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 service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: VerDate Sep<11>2014 16:02 Dec 21, 2022 Jkt 259001 Issued on December 7, 2022. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–1567; Project Identifier MCAI–2022–00099–T; Amendment 39–22265; AD 2022–25–09] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350–941 and A350–1041 airplanes. This AD was prompted by a report that Heavy Expanded Copper Foil (HECF) patches may not have been installed at all required locations of the upper and lower wing covers. This AD requires a one-time detailed inspection of the affected areas and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective January 6, 2023. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 6, 2023. The FAA must receive comments on this AD by February 6, 2023. 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 SUMMARY: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 78535 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2022–1567; 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 street address for Docket Operations is listed above. Material Incorporated by Reference: • For material incorporated by reference (IBR) in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; website easa.europa.eu. You may find 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, 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–2022–1567. Dat Le, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone (516) 228–7317; email Dat.V.Le@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2022–1567; Project Identifier MCAI–2022–00099–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, 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 final rule because of those comments. 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 final rule. E:\FR\FM\22DER1.SGM 22DER1

Agencies

[Federal Register Volume 87, Number 245 (Thursday, December 22, 2022)]
[Rules and Regulations]
[Pages 78532-78535]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-27670]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1239; Project Identifier MCAI-2022-00301-E; 
Amendment 39-22279; AD 2022-26-01]
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.) Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 78533]]


ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain GE Aviation Czech s.r.o. (GEAC) M601D-11, M601E-11, M601E-11A, 
M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-200, 
H85-100, and H85-200 model turboprop engines. This AD was prompted by 
reports of cracks in dilution tube weld areas of the combustion chamber 
outer liner. This AD requires initial and repetitive borescope 
inspections (BSIs) of the dilution tube weld areas of the combustion 
chamber outer liner and, depending on the results of the inspections, 
replacement of the combustion chamber outer liner with a part eligible 
for installation. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 26, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 26, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2022-1239; 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 GEAC service information identified in this final 
rule, contact GE Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 
Praha 9, Let[ncaron]any, Czech Republic; phone: +420 222 538 111.
     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-2022-1239.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
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 GEAC M601D-11, 
M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, 
H80, H80-100, H80-200, H85-100, and H85 200 model turboprop engines. 
The NPRM published in the Federal Register on September 27, 2022 (87 FR 
58466). The NPRM was prompted by AD 2022-0034, dated March 4, 2022, 
issued by the European Union Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Union 
(referred to after this as ``the MCAI''). The MCAI states that 
occurrences of cracks in dilution tube weld areas of the combustion 
chamber outer liner have been reported. These cracks can lead to crack 
propagation, possibly resulting in part separation, loss of engine 
power, and reduced control of the aircraft.
    In the NPRM, the FAA proposed to require initial and repetitive 
BSIs of the dilution tube weld areas of the combustion chamber outer 
liner and, depending on the results of the inspections, corrective 
action in accordance with the service information. 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-2022-1239.

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 GEAC Alert Service Bulletin (ASB) ASB-H75-72-40-
00-0056 [01], ASB-M601E-72-40-00-0113 [01], ASB-H80-72-40-00-0099 [01], 
ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-00-0064 [01], ASB-M601Z-
72-40-00-0063 [01], and ASB-H85-72-40-00-0045 [01], (single document; 
formatted as service bulletin identifier [revision number]), dated 
February 16, 2022. This service information specifies procedures for 
BSIs of the dilution tube weld areas of the combustion chamber outer 
liner and replacement of the combustion chamber outer liner.
    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:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
BSI of combustion chamber outer liner.  2.5 work-hours x $85 per              $0         $212.50       $7,012.50
                                         hour = $212.50.
----------------------------------------------------------------------------------------------------------------

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

[[Page 78534]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
On-wing replacement of combustion chamber    64 work-hours x $85 per hour =              $74,909         $80,349
 outer liner.                                 $5,440.
In-shop replacement of combustion chamber    56 work-hours x $85 per hour =               74,909          79,669
 outer liner.                                 $4,760.
----------------------------------------------------------------------------------------------------------------

    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

    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 adding the following new airworthiness 
directive:

2022-26-01 GE Aviation Czech s.r.o (Type Certificate previously held 
by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): Amendment 
39-22279; Docket No. FAA-2022-1239; Project Identifier MCAI-2022-
00301-E.

(a) Effective Date

    This airworthiness directive (AD) is effective January 26, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to GE Aviation Czech s.r.o. (GEAC) M601D-11, 
M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, 
H80, H80-100, H80-200, H85-100, and H85-200 model turboprop engines 
installed on single-engine airplanes, with an installed combustion 
chamber outer liner having part numbers (P/Ns) M601-229.3, M601-
229.3A, M601-229.3B, M601-229.31A, or M601-229.31B.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7240, Turbine Engine 
Combustion Section.

(e) Unsafe Condition

    This AD was prompted by reports of cracks in dilution tube weld 
areas of the combustion chamber outer liner. The FAA is issuing this 
AD to prevent failure of the combustion chamber outer liner. The 
unsafe condition, if not addressed, could result in uncontained 
release of the combustion chamber outer liner, loss of engine power, 
and reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) At the next 300-hour (Type 3) engine inspection, or within 
25 flight hours (FHs) after the effective date of this AD, whichever 
occurs later, and thereafter at intervals not to exceed 300 FHs, 
perform a borescope inspection (BSI) of the dilution tube weld areas 
of the combustion chamber outer liner in accordance with the 
Accomplishment Instructions, paragraph 2.1 of GEAC Alert Service 
Bulletin (ASB) ASB-H75-72-40-00-0056 [01], ASB-M601E-72-40-00-0113 
[01], ASB-H80-72-40-00-0099 [01], ASB-M601D-72-40-00-0081 [01], ASB-
M601F-72-40-00-0064 [01], ASB-M601Z-72-40-00-0063 [01], and ASB-H85-
72-40-00-0045 [01] (single document; formatted as service bulletin 
identifier [revision number]), dated February 16, 2022 (the ASB).
    (2) If a crack is detected during any BSI required by paragraph 
(g)(1) of this AD, before further flight, perform the applicable 
corrective actions in accordance with the Accomplishment 
Instructions, paragraph 2.1, Table 1 of the ASB.

(h) Terminating Action

    Replacing the affected combustion chamber outer liner with a 
combustion chamber outer liner that does not have P/N M601-229.3, 
M601-229.3A, M601-229.3B, M601-229.31A, or M601-229.31B, constitutes 
a terminating action for the repetitive inspections required by 
paragraph (g)(1) of this AD.

(i) Conditional Part Installation

    (1) After the effective date of this AD, it is permissible to 
install an engine, having an affected combustion chamber outer liner 
installed, on a single-engine airplane, provided that prior to 
operation, the BSI required by paragraph (g)(1) of this AD is 
performed and, depending on the findings, the applicable corrective 
actions are performed as required by paragraph (g)(2) of this AD.
    (2) After the effective date of this AD, it is permissible to 
install an affected combustion chamber outer liner on the engine of 
a single-engine airplane, provided that it is a part eligible for 
installation, as defined in paragraph (j) of this AD, and provided 
that prior to operation, the BSI required by paragraph (g)(1) of 
this AD is performed and, depending on the findings, the applicable 
corrective actions are performed as required by paragraph (g)(2) of 
this AD.

(j) Definitions

    For the purpose of this AD, a ``part eligible for installation'' 
is an affected combustion chamber outer liner, which was not 
previously installed on an engine, or an affected combustion chamber 
outer liner that,

[[Page 78535]]

before installation, has passed an inspection (no defects found) in 
accordance with the Accomplishment Instructions, paragraphs 2.2 and 
2.3 of the ASB, or a combustion chamber outer liner that does not 
have P/Ns M601-229.3, M601-229.3A, M601-229.3B, M601-229.31A, or 
M601-229.31B.

(k) Alternative Methods of Compliance (AMOCs)

    The Manager, ECO Branch, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in Sec.  39.19. 
In accordance with Sec.  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 certification 
office, send it to the attention of the person identified in 
paragraph (l)(2) of this AD or email to: [email protected]. 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) Refer to European Union Aviation Safety Agency (EASA) AD 
2022-0034, dated March 4, 2022, for related information. This EASA 
AD may be found in the AD docket at regulations.gov under Docket No. 
FAA-2022-1239.
    (2) For more information about this AD, contact Barbara 
Caufield, Aviation Safety Engineer, ECO Branch, FAA, 1200 District 
Avenue, Burlington, MA 01803; phone: (781) 238-7146; email: 
[email protected].

(m) 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) GE Aviation Czech s.r.o. (GEAC) Alert Service Bulletin (ASB) 
ASB-H75-72-40-00-0056 [01], ASB-M601E-72-40-00-0113 [01], ASB-H80-
72-40-00-0099 [01], ASB-M601D-72-40-00-0081 [01], ASB-M601F-72-40-
00-0064 [01], ASB-M601Z-72-40-00-0063 [01], and ASB-H85-72-40-00-
0045 [01] (single document; formatted as service bulletin identifier 
[revision number]), dated February 16, 2022.
    (ii) [Reserved]
    (3) For GEAC service information identified in this AD, contact 
GE Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9, 
Let[ncaron]any, Czech Republic; phone: +420 222 538 111.
    (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 service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 7, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-27670 Filed 12-21-22; 8:45 am]
BILLING CODE 4910-13-P
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