Airworthiness Directives; General Electric Company Turbofan Engines, 33494-33498 [2021-13424]

Download as PDF 33494 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations AMS is committed to complying with the E-Government Act, to promote the use of the internet and other information technologies to provide increased opportunities for citizen access to Government information and services, and for other purposes. Analysis of Comments An interim final rule was published in the Federal Register on February 24, 2021, providing a 60-day comment period that ended April 26, 2021. This rule will adopt most of the changes in the interim final rule. One comment was received requesting a change to section 1206.34 Procedures, concerning what constitutes a quorum at a Board meeting. Section 1206.34 was changed due to the reduction of the Board from 21 to 18, a decrease in quorum requirements was necessary, and therefore, changed from 11 to at least 10 of the 18 Board members are present. The commenter stated that this is problematic when the Board is not at full capacity and recommends a quorum at Board meetings be when at least one more than half of the voting members are present. USDA believes that this comment has merit and is revising section 1206.34 Procedures to specify that a quorum at a Board meeting exists when at least one more than half of the voting members are present. In addition, USDA made a correction to section 1206.43 Exemptions to clarify a change that was made inadvertently exempting domestic first handlers when the intent was to simply remove frozen mangos as a covered commodity. Therefore, the section has been corrected to exempt first handlers or importers of less than 500,000 pounds of mangos per calendar year, and domestically exported mangos. After consideration of all relevant matters presented, including comments, the referendum vote and other available information, it is hereby found that finalizing the interim final rule, with the changes below, as published in the Federal Register [86 FR 11094] on February 24, 2021, will tend to effectuate the purposes of the 1996 Act. lotter on DSK11XQN23PROD with RULES1 List of Subjects in 7 CFR Part 1206 Administrative practice and procedure, Advertising, Consumer information, Marketing agreements, Mango promotion, Reporting and recording requirements. Accordingly, the interim final rule amending 7 CFR part 1206, which was published in the February 24, 2021, Federal Register [86 FR 11094], is adopted as final with the following changes: VerDate Sep<11>2014 16:27 Jun 24, 2021 Jkt 253001 PART 1206—MANGO RESEARCH, PROMOTION, AND INFORMATION ORDER 1. The authority citation for 7 CFR part 1206 continues to read as follows: ■ Authority: 7 U.S.C. 7411–7425 and 7 U.S.C. 7401. 2. In § 1206.34, revise paragraph (a) to read as follows: ■ § 1206.34 Procedure. (a) At a Board meeting, it will be considered a quorum when at least one more than half of the voting members are present. * * * * * ■ 3. In § 1206.43, revise paragraph (a) to read as follows: § 1206.43 Exemptions. (a) Any first handler or importer of less than 500,000 pounds of mangos per calendar year may claim an exemption from the assessments required under § 1206.42. Mangos produced domestically and exported from the United States may annually claim an exemption from the assessments required under § 1206.42. * * * * * Erin Morris, Associate Administrator, Agricultural Marketing Service. [FR Doc. 2021–13317 Filed 6–24–21; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2020–0850; Project Identifier AD–2020–00288–E; Amendment 39–21569; AD 2021–11–07] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan 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) GEnx– 1B64, 1B64/P1, –1B64/P2, –1B67, –1B67/P1, –1B67/P2, –1B70, –1B70/75/ P1, –1B70/75/P2, –1B70/P1, –1B70/P2, –1B70C/P1, –1B70C/P2, –1B74/75/P1, –1B74/75/P2, –1B76/P2, –1B76A/P2, –2B67, –2B67/P, and –2B67B model turbofan engines. This AD was prompted by a finding during an inspection by the manufacturer that two SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 stages 6–10 compressor rotor spools in the high-pressure compressor (HPC) assembly were damaged at similar locations. Additionally, the manufacturer reported that certain stages 6–10 compressor rotor spool webs did not undergo a required fluorescent penetrant inspection (FPI) during production. This AD requires inspection of the stages 6–10 compressor rotor spool and, depending on the results of the inspection, replacement of the stages 6–10 compressor rotor spool. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 30, 2021. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 30, 2021. ADDRESSES: 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@ae.ge.com; website: www.ge.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238– 7759. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2020– 0850. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2020–0850; 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. FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7743; fax: (781) 238– 7199; email: Mehdi.Lamnyi@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 GEnx–1B and GEnx–2B model turbofan engines. The E:\FR\FM\25JNR1.SGM 25JNR1 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations NPRM published in the Federal Register on September 24, 2020 (85 FR 60103). The NPRM was prompted by a report from the manufacturer that an inspection had found two stages 6–10 compressor rotor spools in the HPC assembly damaged at similar locations on the webs. The subsequent investigation determined that tool marks were created during the manufacturing process. In addition, the manufacturer also reported that certain stages 6–10 compressor rotor spool webs did not undergo a required FPI during production. In the NPRM, the FAA proposed to require inspection of the stages 6–10 compressor rotor spool. Operators of certain affected GEnx–1B or GEnx–2B model turbofan engines have already completed acceptable inspections of the aft web of stage 6, stage 7, and stage 8 of the stages 6–10 compressor rotor spool. The FAA proposed to require operators of those affected engines to complete the inspection of the stages 6– 10 compressor rotor spool no later than the next engine shop visit. The FAA proposed to require all other remaining affected GEnx–1B and GEnx–2B model turbofan engines to complete this inspection by the next engine shop visit, before the stages 6–10 compressor rotor spools accumulate 6,500 cycles since new, or before further flight if 6,500 cycles since new has already been accumulated as of the effective date of this AD. Depending on the results of the inspection, the FAA proposed to require replacement of the stages 6–10 compressor rotor spool with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products. lotter on DSK11XQN23PROD with RULES1 Discussion of Final Airworthiness Directive Comments The FAA received comments from seven commenters. The commenters were American Airlines (American), GE Aviation, Japan Airlines, Nippon Cargo Airlines (NCA), the Air Line Pilots Association, International, United Airlines Engineering, and Boeing Commercial Airplanes. Three commenters supported the proposed rule without change. One commenter requested that the FAA add a term to the Definitions paragraph of the proposed rule, and use the latest version of the service information. Three commenters requested certain clarifications or changes to the Required Actions and Previous Credit sections. The following presents the comments received on the NPRM and the FAA’s response to each comment. VerDate Sep<11>2014 16:27 Jun 24, 2021 Jkt 253001 Request To Clarify Rejectable Indication GE Aviation requested that the FAA define the term ‘‘rejectable indication’’ to avoid confusion in the event an indication is found during inspection. GE Aviation requested that the FAA define rejectable indication as an indication that does not meet the serviceable or repairable limits defined in the special procedure referenced in GE GEnx–1B Service Bulletin (SB) 72– 0472 R02, dated November 5, 2020 (GEnx–1B SB 72–0472) and GE GEnx– 2B SB 72–0415 R02, dated November 5, 2020 (GEnx–2B SB 72–0415). The FAA agrees to define a ‘‘rejectable indication’’ as used in paragraph (g)(2) of the Required Actions section of this AD and added the definition in paragraph (h), Definitions, of this AD. Request To Clarify Acceptance of Reworked Parts American requested that the FAA clarify paragraph (g)(2) and paragraph (i), Credit for Previous Actions, regarding installation of parts that initially failed inspection with a rejectable indication but were later reworked and found acceptable. American stated that GE has been accepting parts that were reworked using GE Subtask 72–00–00–210–012 in the GEnx–1B EM 72–00–00, Special Procedure 023, in accordance with approved GE Departure Recommendations. The FAA disagrees. Paragraph (g)(2) of this AD requires that if during an inspection, a stages 6–10 compressor rotor spool is found to have a rejectable indication, as defined in paragraph (h) of this AD, then the stages 6–10 compressor rotor spool must be removed from service. If the stages 6–10 compressor rotor spool is subsequently repaired or reworked, operators would need to submit an alternative methods of compliance (AMOC) request to the FAA to allow use of the repaired or reworked stages 6–10 compressor rotor spool. Request To Revise References to Service Bulletin GE Aviation requested that the FAA update the specified service information by referencing Revision 2 of GE GEnx– 1B SB 72–0472 and GE GEnx–2B SB 72– 0415. GE noted that Revision 2 of these SBs had not been issued at the time of publication of the NPRM. The FAA agrees and has updated this AD to reference GEnx–1B SB 72–0472 R02 and GEnx–2B SB 72–0415 R02, both dated November 5, 2020. This change to this AD imposes no additional burden on operators. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 33495 Request To Revise Previous Credit Japan Airlines requested that the FAA grant credit for the borescope inspection (BSI) or eddy current inspection (ECI) required by paragraph (g)(1) of this AD if inspections were previously performed in accordance with GE GEnx–1B SB 72–0472 R01, dated July 24, 2020. The FAA agrees and has updated paragraph (i), Credit for Previous Actions, to allow credit for inspections performed using GE GEnx–1B SB 72– 0472 R01, dated July 24, 2020 or GE GEnx–2B SB 72–0415 R01, dated July 24, 2020, as applicable. Request for Reference Date Clarification NCA requested that the FAA clarify the meaning of ‘‘previously undergone’’ in paragraph (g)(1)(ii) of this AD. NCA commented that one of its engines underwent an inspection during an engine shop visit using GEnx–2B SB 72– 0385 R02, dated July 29, 2019 and GE GEnx–2B SB 72–0398 R00, dated October 30, 2019, before the effective date of this AD but after publication of GEnx–2B SB 72–0415 R01. NCA noted that the reference to ‘‘previously undergone’’ means that it has been implemented in accordance with SB in the past without any specific timeframe, so it is not clear if the NCA’s engine can apply the no cycles since new (CSN) limit. The FAA clarified paragraph (g)(1)(i) and (ii) of this AD by removing the phrase ‘‘previously undergone’’ and referring instead to engines that have undergone inspections ‘‘before the effective date of this AD.’’ Change to Compliance Time The FAA updated Table 1 to paragraph (g)(1) of this AD by allowing operators 100 flight cycles to perform the inspections required by paragraph (g)(1) of this AD when an engine has a stages 6–10 compressor rotor spool with 6,400 CSN or greater as of the effective date of this AD. This change allows operators a grace period to complete the required inspections without unnecessary grounding of airplanes and still meets the safety intent of this AD. Conclusion The FAA reviewed the relevant data, considered any comments received, 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 and any other changes described previously, this AD is adopted as proposed in the NPRM. E:\FR\FM\25JNR1.SGM 25JNR1 33496 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed GE GEnx–1B Service Bulletin (SB) 72–0472 R02, dated November 5, 2020 (GEnx–1B SB 72–0472) and GE GEnx–2B SB 72–0415 R02, dated November 5, 2020 (GEnx–2B SB 72–0415). GEnx–1B SB 72–0472 describes procedures for performing a BSI or an ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore faces of the stages 6–10 compressor rotor spool for GEnx-1B model turbofan engines. GEnx–1B SB 72–0472 also provides the affected part and serial numbers of the stages 6–10 compressor rotor spools installed on GEnx–1B model turbofan engines. GEnx–2B SB 72–0415 describes procedures for performing a BSI or an ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore faces of the stages 6–10 compressor rotor spool for GEnx-2B model turbofan engines. GEnx–2B SB 72–0415 also provides the affected part and serial numbers of the stages 6–10 compressor rotor spools installed on GEnx-2B model turbofan engines. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES. Other Related Service Information The FAA also reviewed Subtask 72– 31–45–160–002 of TASK 72–31–45– 200–807 in GE GEnx–1B Engine Manual 05–21–00, Life Limits 001 Mandatory Inspections, Rev. 31 dated, January 31, 2020; and Subtask 72–31–45–160–002 of TASK 72–31–45–200–801 in GE GEnx–2B Engine Manual 05–21–00, Life Limits 001 Mandatory Inspections, Rev. 24 dated, January 31, 2020. The Subtasks provide guidance on performing the ECI on the stages 6–10 compressor rotor spool on GE GEnx–1B and GEnx–2B model turbofan engines. The FAA also reviewed the following GE SBs: GEnx–1B SB 72–0448 R00, dated July 29, 2019 (GEnx–1B SB 72– 0448); GEnx–1B SB 72–0460 R00, dated October 30, 2019 (GEnx–1B SB 72– 0460); GEnx–2B SB 72–0385 R02, dated July 29, 2019 (GEnx–2B SB 72–0385); and GEnx–2B SB 72–0398 R00, dated October 30, 2019 (GEnx–2B SB 72– 0398). GEnx–1B SB 72–0448 describes procedures for performing a BSI or an ECI of the stage 8 aft web of the HPC stages 6–10 rotor spool for GEnx–1B model turbofan engines. GEnx–1B SB 72–0460 describes procedures for performing a BSI or an ECI of the stage 6 and stage 7 aft web of the HPC stages 6–10 rotor spool for GEnx–1B model turbofan engines. GEnx–2B SB 72–0385 describes procedures for performing a BSI or an ECI of the stage 8 aft web of the HPC stages 6–10 spool for GEnx–2B model turbofan engines. GEnx–2B SB 72–0398 describes procedures for performing a BSI or an ECI of the stage 6 and stage 7 aft web of the HPC stages 6–10 rotor spool for GEnx–2B model turbofan engines. Costs of Compliance The FAA estimates that this AD affects 268 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Cost per product Labor cost BSI of GEnx–1B stage 6, stage 7, and stage 8 webs, web transitions and bore faces of the stages 6–10 compressor rotor spool. BSI of GEnx–2B stage 6, stage 7, and stage 8 webs, web transitions and bore faces of the stages 6–10 compressor rotor spool. 6 work-hours × $85 per hour = $510 ............. $0 $510 $89,760 6 work-hours × $85 per hour = $510 ............. 0 510 46,920 The FAA estimates the following costs to do any necessary replacements that would be required based on the Parts cost Cost on U.S. operators Action results of the inspection. The agency has no way of determining the number of aircraft that might need these replacements: lotter on DSK11XQN23PROD with RULES1 ON-CONDITION COSTS Action Labor cost Replace the stages 6–10 compressor rotor spool ....... 64 work-hours × $85 per hour = $5,440 ...................... 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 VerDate Sep<11>2014 16:27 Jun 24, 2021 Jkt 253001 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. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Parts cost $1,018,600 Cost per product $1,024,040 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: E:\FR\FM\25JNR1.SGM 25JNR1 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2021–11–07 General Electric Company: Amendment 39–21569; Docket No. FAA–2020–0850; Project Identifier AD– 2020–00288–E. (a) Effective Date This airworthiness directive (AD) is effective July 30, 2021. (b) Affected ADs 33497 (d) Subject None. (c) Applicability This AD applies to: (1) General Electric Company (GE) GEnx– 1B64, GEnx–1B64/P1, GEnx–1B64/P2, GEnx– 1B67, GEnx–1B67/P1, GEnx–1B67/P2, GEnx– 1B70, GEnx–1B70/75/P1, GEnx–1B70/75/P2, GEnx–1B70/P1, GEnx–1B70/P2, GEnx– 1B70C/P1, GEnx–1B70C/P2, GEnx–1B74/75/ P1, GEnx–1B74/75/P2, GEnx–1B76/P2, GEnx–1B76A/P2 model turbofan engines with stages 6–10 compressor rotor spools in the high-pressure compressor (HPC) assembly with the following part numbers (P/N) installed: (i) P/N 2357M30G01, P/N 2357M30G02, P/N 2439M35G01, P/N 2439M35G02, or P/N 2445M40G02, all serial numbers (S/Ns); (ii) P/N 2610M90G01 with the S/Ns listed in paragraph 4., APPENDIX—A, Table 1 of the GE GEnx–1B Service Bulletin (SB) 72– 0472 R02, dated November 5, 2020 (GEnx–1B SB 72–0472); and (iii) P/N 2628M56G01 with the S/Ns listed in paragraph 4., APPENDIX—A, Table 2 or Table 3 of GEnx–1B SB 72–0472. (2) GEnx–2B67, GEnx–2B67/P, GEnx– 2B67B model turbofan engines with the following stages 6–10 compressor rotor spools P/Ns installed: (i) P/N 2357M30G02, P/N 2439M35G02, or P/N 2445M40G02, all S/Ns; (ii) P/N 2340M36G01 with S/Ns listed in paragraph 4., APPENDIX—A, Table 1 of GE GEnx–2B SB 72–0415 R02, dated November 5, 2020 (GEnx–2B SB 72–0415); and (iii) P/N 2628M56G01 with S/Ns listed in paragraph 4., APPENDIX—A, Table 2 or Table 3 of GEnx–2B SB 72–0415. Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by a finding during an inspection that two stages 6–10 compressor rotor spools were damaged at similar locations. In addition, the manufacturer reported that certain stages 6– 10 compressor rotor spool webs did not undergo a required fluorescent penetrant inspection (FPI) during production. The FAA is issuing this AD to prevent failure of the compressor rotor spool. The unsafe condition, if not addressed, could result in uncontained release of 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 (1) For all affected GEnx–1B and GEnx–2B model turbofan engines, before exceeding the compliance time in Table 1 to paragraph (g)(1) of this AD, perform a borescope inspection (BSI) or eddy current inspection (ECI) of the stage 6, stage 7, and stage 8 webs, web transitions, and bore faces of the stages 6–10 compressor rotor spool in accordance with the Accomplishment Instructions, paragraph 3, of GEnx–1B SB 72–0472 (for GEnx–1B models) or the Accomplishment Instructions, paragraph 3, of GEnx–2B SB 72– 0415 (for GEnx–2B models). TABLE 1 TO PARAGRAPH (g)(1) Cycles Since New (CSN) accumulated on the stages 6–10 compressor rotor spool Compliance time Less than 6,400 CSN .......................................... Next engine shop visit or before the stages 6–10 compressor rotor spool accumulates 6,500 CSN, whichever occurs first after the effective date of this AD. Within 100 flight cycles after the effective date of this AD. lotter on DSK11XQN23PROD with RULES1 6,400 CSN or greater .......................................... (i) For GEnx–1B model turbofan engines, except those identified in paragraph 4, APPENDIX—A, Table 3 of SB 72–0472, if, before the effective date of this AD, the engines have undergone inspections of the aft web of stage 6, stage 7, and stage 8 of the stages 6–10 compressor rotor spool using both GE GEnx–1B SB 72–0448 R00, dated July 29, 2019, and GE GEnx–1B SB 72–0460 R00, dated October 30, 2019, regardless of the CSN accumulated on the stages 6–10 compressor rotor spool, perform the inspection required by paragraph (g)(1) of this AD no later than the next engine shop visit after the effective date of this AD. (ii) For GEnx–2B model turbofan engines, except those identified in paragraph 4., APPENDIX—A, Table 3 of SB 72–0415, if, before the effective date of this AD, the engines have undergone inspections of the aft web of stage 6, stage 7, and stage 8 of the stages 6–10 compressor rotor spool using VerDate Sep<11>2014 16:27 Jun 24, 2021 Jkt 253001 both GE GEnx–2B SB 72–385 R02, dated July 29, 2019, and GE GEnx–2B SB 72–0398 R00, dated October 30, 2019, regardless of the CSN accumulated on the stages 6–10 compressor rotor spool, perform the inspection required by paragraph (g)(1) of this AD no later than the next engine shop visit after the effective date of this AD. (2) For all affected GEnx–1B and GEnx–2B model turbofan engines, during the inspections required by paragraph (g)(1) of this AD, if a rejectable indication is found, before further flight, remove the stages 6–10 compressor rotor spool from service and replace it with a part eligible for installation. (h) Definitions (1) For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 flanges solely for the purposes of transportation of the engine without subsequent engine maintenance does not constitute an engine shop visit. (2) For the purpose of this AD, a rejectable indication is: (i) A BSI indication that does not meet the BSI serviceable or repairable limits referenced in the Accomplishment Instructions, paragraph 3.A.(1)(a)2, of GEnx– 1B SB 72–0472, or paragraph 3.A.(1)(a)2 of GEnx–2B SB 72–0415, and the affected part has not undergone a subsequent ECI; or (ii) A BSI indication that does not meet the BSI serviceable or repairable limits referenced in the Accomplishment Instructions, paragraph 3.A.(1)(a)2, of GEnx– 1B SB 72–0472, or paragraph 3.A.(1)(a)2 of GEnx–2B SB 72–0415, and the affected part has undergone a subsequent ECI in which the indication did not meet the ECI serviceable or repairable limits referenced in the E:\FR\FM\25JNR1.SGM 25JNR1 33498 Federal Register / Vol. 86, No. 120 / Friday, June 25, 2021 / Rules and Regulations Accomplishment Instructions, paragraph 3.A.(1)(b) of GEnx–1B SB 72–0472, or paragraph 3.A.(1)(b) of GEnx–2B SB 72–0415; or (iii) An ECI indication that does not meet the serviceable or repairable limits referenced in the Accomplishment Instructions, paragraph 3.A.(1)(b) of GEnx–1B SB 72–0472, or paragraph 3.A.(1)(b) of GEnx–2B SB 72– 0415. (i) Credit for Previous Actions (1) For affected GEnx–1B model turbofan engines, you may take credit for the BSI or ECI required by paragraph (g)(1) of this AD, if you performed an ECI of the stages 6–10 compressor rotor spool webs, web transitions, and bore faces before the effective date of this AD using Subtask 72–31–45– 160–002 of TASK 72–31–45–200–807 in GE GEnx–1B Engine Manual 05–21–00, Life Limits 001 Mandatory Inspections, Rev. 31, dated January 31, 2020, or earlier, and no rejectable indications were found. (2) For affected GEnx–2B model turbofan engines, you may take credit for the BSI or ECI required by paragraph (g)(1) of this AD, if you performed and ECI of the stages 6–10 compressor rotor spool webs, web transitions, and bore faces before the effective date of this AD using Subtask 72–31–45– 160–002 of TASK 72–31–45–200–801 in GE GEnx–2B Engine Manual 05–21–00, Life Limits 001 Mandatory Inspections, Rev. 24, dated January 31, 2020, or earlier, and no rejectable indications were found. (3) For affected GEnx–1B model turbofan engines, you may take credit for the BSI or ECI required by paragraph (g)(1) of this AD, if you performed that inspection before the effective date of this AD using GE GEnx–1B Service Bulletin (SB) 72–0472 R00, dated April 24, 2020, or GE GEnx–1B SB 72–0472 R01, dated July 24, 2020, and no rejectable indications were found. (4) For affected GEnx–2B model turbofan engines, you may take credit for the BSI or ECI required by paragraph (g)(1) of this AD, if you performed that inspection before the effective date of this AD using GE GEnx–2B SB 72–0415 R00, dated April 24, 2020, or GE GEnx–2B SB 72–0415 R01, dated July 24, 2020, and no rejectable indications were found. lotter on DSK11XQN23PROD with RULES1 (1) The Manager, ECO 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 certification office, send it to the attention of the person identified in Related Information. You may email your request 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. 16:27 Jun 24, 2021 Jkt 253001 (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) GE GEnx–1B Service Bulletin (SB) 72– 0472 R02, dated November 5, 2020. (ii) GE GEnx–2B SB 72–0415 R02, dated November 5, 2020. (3) For General Electric Company service information identified in this AD, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552– 3272; email: aviation.fleetsupport@ ae.ge.com; website: www.ge.com. (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 (781) 238–7759. (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: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued on May 19, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–13424 Filed 6–24–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 (j) Alternative Methods of Compliance (AMOCs) VerDate Sep<11>2014 (k) Related Information For more information about this AD, contact Mehdi Lamnyi, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7743; fax: (781) 238–7199; email: Mehdi.Lamnyi@faa.gov. [Docket No. FAA–2021–0512; Project Identifier MCAI–2020–01621–R; Amendment 39–21627; AD 2021–13–21] RIN 2120–AA64 Airworthiness Directives; Leonardo S.p.a. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: Examining the AD Docket The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139, AW139, and AW189 helicopters. This AD was SUMMARY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 prompted by a report of the in-flight failure of one of the three stainless steel external rings bonded to the main rotor swashplate boot. This AD requires repetitive inspections of these stainless steel external rings for corrosion, cracks, and the condition of the adhesive that bonds the rings to the main rotor swashplate boot, and corrective action if necessary, 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 July 12, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 12, 2021. The FAA must receive comments on this AD by August 9, 2021. 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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For EASA 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; internet www.easa.europa.eu EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view the EASA material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of the EASA material at the FAA, call (817) 222–5110. The EASA material is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0512. You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0512; or in person at Docket E:\FR\FM\25JNR1.SGM 25JNR1

Agencies

[Federal Register Volume 86, Number 120 (Friday, June 25, 2021)]
[Rules and Regulations]
[Pages 33494-33498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-13424]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0850; Project Identifier AD-2020-00288-E; 
Amendment 39-21569; AD 2021-11-07]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain General Electric Company (GE) GEnx-1B64, 1B64/P1, -1B64/P2, -
1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -
1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, -
1B76A/P2, -2B67, -2B67/P, and -2B67B model turbofan engines. This AD 
was prompted by a finding during an inspection by the manufacturer that 
two stages 6-10 compressor rotor spools in the high-pressure compressor 
(HPC) assembly were damaged at similar locations. Additionally, the 
manufacturer reported that certain stages 6-10 compressor rotor spool 
webs did not undergo a required fluorescent penetrant inspection (FPI) 
during production. This AD requires inspection of the stages 6-10 
compressor rotor spool and, depending on the results of the inspection, 
replacement of the stages 6-10 compressor rotor spool. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective July 30, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of July 30, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
phone: (513) 552-3272; email: [email protected]; website: 
www.ge.com. You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call (781) 238-7759. It is 
also available at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2020-0850.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-0850; 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.

FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aviation Safety 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: (781) 238-7743; fax: (781) 238-7199; 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 GE GEnx-1B and 
GEnx-2B model turbofan engines. The

[[Page 33495]]

NPRM published in the Federal Register on September 24, 2020 (85 FR 
60103). The NPRM was prompted by a report from the manufacturer that an 
inspection had found two stages 6-10 compressor rotor spools in the HPC 
assembly damaged at similar locations on the webs. The subsequent 
investigation determined that tool marks were created during the 
manufacturing process. In addition, the manufacturer also reported that 
certain stages 6-10 compressor rotor spool webs did not undergo a 
required FPI during production.
    In the NPRM, the FAA proposed to require inspection of the stages 
6-10 compressor rotor spool. Operators of certain affected GEnx-1B or 
GEnx-2B model turbofan engines have already completed acceptable 
inspections of the aft web of stage 6, stage 7, and stage 8 of the 
stages 6-10 compressor rotor spool. The FAA proposed to require 
operators of those affected engines to complete the inspection of the 
stages 6-10 compressor rotor spool no later than the next engine shop 
visit. The FAA proposed to require all other remaining affected GEnx-1B 
and GEnx-2B model turbofan engines to complete this inspection by the 
next engine shop visit, before the stages 6-10 compressor rotor spools 
accumulate 6,500 cycles since new, or before further flight if 6,500 
cycles since new has already been accumulated as of the effective date 
of this AD. Depending on the results of the inspection, the FAA 
proposed to require replacement of the stages 6-10 compressor rotor 
spool with a part 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 seven commenters. The commenters 
were American Airlines (American), GE Aviation, Japan Airlines, Nippon 
Cargo Airlines (NCA), the Air Line Pilots Association, International, 
United Airlines Engineering, and Boeing Commercial Airplanes. Three 
commenters supported the proposed rule without change. One commenter 
requested that the FAA add a term to the Definitions paragraph of the 
proposed rule, and use the latest version of the service information. 
Three commenters requested certain clarifications or changes to the 
Required Actions and Previous Credit sections. The following presents 
the comments received on the NPRM and the FAA's response to each 
comment.

Request To Clarify Rejectable Indication

    GE Aviation requested that the FAA define the term ``rejectable 
indication'' to avoid confusion in the event an indication is found 
during inspection. GE Aviation requested that the FAA define rejectable 
indication as an indication that does not meet the serviceable or 
repairable limits defined in the special procedure referenced in GE 
GEnx-1B Service Bulletin (SB) 72-0472 R02, dated November 5, 2020 
(GEnx-1B SB 72-0472) and GE GEnx-2B SB 72-0415 R02, dated November 5, 
2020 (GEnx-2B SB 72-0415).
    The FAA agrees to define a ``rejectable indication'' as used in 
paragraph (g)(2) of the Required Actions section of this AD and added 
the definition in paragraph (h), Definitions, of this AD.

Request To Clarify Acceptance of Reworked Parts

    American requested that the FAA clarify paragraph (g)(2) and 
paragraph (i), Credit for Previous Actions, regarding installation of 
parts that initially failed inspection with a rejectable indication but 
were later reworked and found acceptable. American stated that GE has 
been accepting parts that were reworked using GE Subtask 72-00-00-210-
012 in the GEnx-1B EM 72-00-00, Special Procedure 023, in accordance 
with approved GE Departure Recommendations.
    The FAA disagrees. Paragraph (g)(2) of this AD requires that if 
during an inspection, a stages 6-10 compressor rotor spool is found to 
have a rejectable indication, as defined in paragraph (h) of this AD, 
then the stages 6-10 compressor rotor spool must be removed from 
service. If the stages 6-10 compressor rotor spool is subsequently 
repaired or reworked, operators would need to submit an alternative 
methods of compliance (AMOC) request to the FAA to allow use of the 
repaired or reworked stages 6-10 compressor rotor spool.

Request To Revise References to Service Bulletin

    GE Aviation requested that the FAA update the specified service 
information by referencing Revision 2 of GE GEnx-1B SB 72-0472 and GE 
GEnx-2B SB 72-0415. GE noted that Revision 2 of these SBs had not been 
issued at the time of publication of the NPRM.
    The FAA agrees and has updated this AD to reference GEnx-1B SB 72-
0472 R02 and GEnx-2B SB 72-0415 R02, both dated November 5, 2020. This 
change to this AD imposes no additional burden on operators.

Request To Revise Previous Credit

    Japan Airlines requested that the FAA grant credit for the 
borescope inspection (BSI) or eddy current inspection (ECI) required by 
paragraph (g)(1) of this AD if inspections were previously performed in 
accordance with GE GEnx-1B SB 72-0472 R01, dated July 24, 2020.
    The FAA agrees and has updated paragraph (i), Credit for Previous 
Actions, to allow credit for inspections performed using GE GEnx-1B SB 
72-0472 R01, dated July 24, 2020 or GE GEnx-2B SB 72-0415 R01, dated 
July 24, 2020, as applicable.

Request for Reference Date Clarification

    NCA requested that the FAA clarify the meaning of ``previously 
undergone'' in paragraph (g)(1)(ii) of this AD. NCA commented that one 
of its engines underwent an inspection during an engine shop visit 
using GEnx-2B SB 72-0385 R02, dated July 29, 2019 and GE GEnx-2B SB 72-
0398 R00, dated October 30, 2019, before the effective date of this AD 
but after publication of GEnx-2B SB 72-0415 R01. NCA noted that the 
reference to ``previously undergone'' means that it has been 
implemented in accordance with SB in the past without any specific 
timeframe, so it is not clear if the NCA's engine can apply the no 
cycles since new (CSN) limit.
    The FAA clarified paragraph (g)(1)(i) and (ii) of this AD by 
removing the phrase ``previously undergone'' and referring instead to 
engines that have undergone inspections ``before the effective date of 
this AD.''

Change to Compliance Time

    The FAA updated Table 1 to paragraph (g)(1) of this AD by allowing 
operators 100 flight cycles to perform the inspections required by 
paragraph (g)(1) of this AD when an engine has a stages 6-10 compressor 
rotor spool with 6,400 CSN or greater as of the effective date of this 
AD. This change allows operators a grace period to complete the 
required inspections without unnecessary grounding of airplanes and 
still meets the safety intent of this AD.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, 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 and any 
other changes described previously, this AD is adopted as proposed in 
the NPRM.

[[Page 33496]]

None of the changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GE GEnx-1B Service Bulletin (SB) 72-0472 R02, 
dated November 5, 2020 (GEnx-1B SB 72-0472) and GE GEnx-2B SB 72-0415 
R02, dated November 5, 2020 (GEnx-2B SB 72-0415).
    GEnx-1B SB 72-0472 describes procedures for performing a BSI or an 
ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore 
faces of the stages 6-10 compressor rotor spool for GEnx-1B model 
turbofan engines. GEnx-1B SB 72-0472 also provides the affected part 
and serial numbers of the stages 6-10 compressor rotor spools installed 
on GEnx-1B model turbofan engines.
    GEnx-2B SB 72-0415 describes procedures for performing a BSI or an 
ECI of stage 6, stage 7, and stage 8 webs, web transitions, and bore 
faces of the stages 6-10 compressor rotor spool for GEnx-2B model 
turbofan engines. GEnx-2B SB 72-0415 also provides the affected part 
and serial numbers of the stages 6-10 compressor rotor spools installed 
on GEnx-2B model turbofan engines.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in ADDRESSES.

Other Related Service Information

    The FAA also reviewed Subtask 72-31-45-160-002 of TASK 72-31-45-
200-807 in GE GEnx-1B Engine Manual 05-21-00, Life Limits 001 Mandatory 
Inspections, Rev. 31 dated, January 31, 2020; and Subtask 72-31-45-160-
002 of TASK 72-31-45-200-801 in GE GEnx-2B Engine Manual 05-21-00, Life 
Limits 001 Mandatory Inspections, Rev. 24 dated, January 31, 2020. The 
Subtasks provide guidance on performing the ECI on the stages 6-10 
compressor rotor spool on GE GEnx-1B and GEnx-2B model turbofan 
engines.
    The FAA also reviewed the following GE SBs: GEnx-1B SB 72-0448 R00, 
dated July 29, 2019 (GEnx-1B SB 72-0448); GEnx-1B SB 72-0460 R00, dated 
October 30, 2019 (GEnx-1B SB 72-0460); GEnx-2B SB 72-0385 R02, dated 
July 29, 2019 (GEnx-2B SB 72-0385); and GEnx-2B SB 72-0398 R00, dated 
October 30, 2019 (GEnx-2B SB 72-0398).
    GEnx-1B SB 72-0448 describes procedures for performing a BSI or an 
ECI of the stage 8 aft web of the HPC stages 6-10 rotor spool for GEnx-
1B model turbofan engines. GEnx-1B SB 72-0460 describes procedures for 
performing a BSI or an ECI of the stage 6 and stage 7 aft web of the 
HPC stages 6-10 rotor spool for GEnx-1B model turbofan engines.
    GEnx-2B SB 72-0385 describes procedures for performing a BSI or an 
ECI of the stage 8 aft web of the HPC stages 6-10 spool for GEnx-2B 
model turbofan engines. GEnx-2B SB 72-0398 describes procedures for 
performing a BSI or an ECI of the stage 6 and stage 7 aft web of the 
HPC stages 6-10 rotor spool for GEnx-2B model turbofan engines.

Costs of Compliance

    The FAA estimates that this AD affects 268 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 GEnx-1B stage 6, stage 7, and    6 work-hours x $85 per                $0            $510         $89,760
 stage 8 webs, web transitions and       hour = $510.
 bore faces of the stages 6-10
 compressor rotor spool.
BSI of GEnx-2B stage 6, stage 7, and    6 work-hours x $85 per                 0             510          46,920
 stage 8 webs, web transitions and       hour = $510.
 bore faces of the stages 6-10
 compressor rotor spool.
----------------------------------------------------------------------------------------------------------------

    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:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the stages 6-10 compressor rotor spool  64 work-hours x $85 per hour =        $1,018,600      $1,024,040
                                                 $5,440.
----------------------------------------------------------------------------------------------------------------

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:

[[Page 33497]]

    (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:

2021-11-07 General Electric Company: Amendment 39-21569; Docket No. 
FAA-2020-0850; Project Identifier AD-2020-00288-E.

(a) Effective Date

    This airworthiness directive (AD) is effective July 30, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to:
    (1) General Electric Company (GE) GEnx-1B64, GEnx-1B64/P1, GEnx-
1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-
1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/
P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, 
GEnx-1B76A/P2 model turbofan engines with stages 6-10 compressor 
rotor spools in the high-pressure compressor (HPC) assembly with the 
following part numbers (P/N) installed:
    (i) P/N 2357M30G01, P/N 2357M30G02, P/N 2439M35G01, P/N 
2439M35G02, or P/N 2445M40G02, all serial numbers (S/Ns);
    (ii) P/N 2610M90G01 with the S/Ns listed in paragraph 4., 
APPENDIX--A, Table 1 of the GE GEnx-1B Service Bulletin (SB) 72-0472 
R02, dated November 5, 2020 (GEnx-1B SB 72-0472); and
    (iii) P/N 2628M56G01 with the S/Ns listed in paragraph 4., 
APPENDIX--A, Table 2 or Table 3 of GEnx-1B SB 72-0472.
    (2) GEnx-2B67, GEnx-2B67/P, GEnx-2B67B model turbofan engines 
with the following stages 6-10 compressor rotor spools P/Ns 
installed:
    (i) P/N 2357M30G02, P/N 2439M35G02, or P/N 2445M40G02, all S/Ns;
    (ii) P/N 2340M36G01 with S/Ns listed in paragraph 4., APPENDIX--
A, Table 1 of GE GEnx-2B SB 72-0415 R02, dated November 5, 2020 
(GEnx-2B SB 72-0415); and
    (iii) P/N 2628M56G01 with S/Ns listed in paragraph 4., 
APPENDIX--A, Table 2 or Table 3 of GEnx-2B SB 72-0415.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a finding during an inspection that two 
stages 6-10 compressor rotor spools were damaged at similar 
locations. In addition, the manufacturer reported that certain 
stages 6-10 compressor rotor spool webs did not undergo a required 
fluorescent penetrant inspection (FPI) during production. The FAA is 
issuing this AD to prevent failure of the compressor rotor spool. 
The unsafe condition, if not addressed, could result in uncontained 
release of 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

    (1) For all affected GEnx-1B and GEnx-2B model turbofan engines, 
before exceeding the compliance time in Table 1 to paragraph (g)(1) 
of this AD, perform a borescope inspection (BSI) or eddy current 
inspection (ECI) of the stage 6, stage 7, and stage 8 webs, web 
transitions, and bore faces of the stages 6-10 compressor rotor 
spool in accordance with the Accomplishment Instructions, paragraph 
3, of GEnx-1B SB 72-0472 (for GEnx-1B models) or the Accomplishment 
Instructions, paragraph 3, of GEnx-2B SB 72-0415 (for GEnx-2B 
models).

                       Table 1 to Paragraph (g)(1)
------------------------------------------------------------------------
Cycles Since New (CSN) accumulated
   on the stages 6-10 compressor               Compliance time
            rotor spool
------------------------------------------------------------------------
Less than 6,400 CSN...............  Next engine shop visit or before the
                                     stages 6-10 compressor rotor spool
                                     accumulates 6,500 CSN, whichever
                                     occurs first after the effective
                                     date of this AD.
6,400 CSN or greater..............  Within 100 flight cycles after the
                                     effective date of this AD.
------------------------------------------------------------------------

    (i) For GEnx-1B model turbofan engines, except those identified 
in paragraph 4, APPENDIX--A, Table 3 of SB 72-0472, if, before the 
effective date of this AD, the engines have undergone inspections of 
the aft web of stage 6, stage 7, and stage 8 of the stages 6-10 
compressor rotor spool using both GE GEnx-1B SB 72-0448 R00, dated 
July 29, 2019, and GE GEnx-1B SB 72-0460 R00, dated October 30, 
2019, regardless of the CSN accumulated on the stages 6-10 
compressor rotor spool, perform the inspection required by paragraph 
(g)(1) of this AD no later than the next engine shop visit after the 
effective date of this AD.
    (ii) For GEnx-2B model turbofan engines, except those identified 
in paragraph 4., APPENDIX--A, Table 3 of SB 72-0415, if, before the 
effective date of this AD, the engines have undergone inspections of 
the aft web of stage 6, stage 7, and stage 8 of the stages 6-10 
compressor rotor spool using both GE GEnx-2B SB 72-385 R02, dated 
July 29, 2019, and GE GEnx-2B SB 72-0398 R00, dated October 30, 
2019, regardless of the CSN accumulated on the stages 6-10 
compressor rotor spool, perform the inspection required by paragraph 
(g)(1) of this AD no later than the next engine shop visit after the 
effective date of this AD.
    (2) For all affected GEnx-1B and GEnx-2B model turbofan engines, 
during the inspections required by paragraph (g)(1) of this AD, if a 
rejectable indication is found, before further flight, remove the 
stages 6-10 compressor rotor spool from service and replace it with 
a part eligible for installation.

(h) Definitions

    (1) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation of the engine without subsequent engine maintenance 
does not constitute an engine shop visit.
    (2) For the purpose of this AD, a rejectable indication is:
    (i) A BSI indication that does not meet the BSI serviceable or 
repairable limits referenced in the Accomplishment Instructions, 
paragraph 3.A.(1)(a)2, of GEnx-1B SB 72-0472, or paragraph 
3.A.(1)(a)2 of GEnx-2B SB 72-0415, and the affected part has not 
undergone a subsequent ECI; or
    (ii) A BSI indication that does not meet the BSI serviceable or 
repairable limits referenced in the Accomplishment Instructions, 
paragraph 3.A.(1)(a)2, of GEnx-1B SB 72-0472, or paragraph 
3.A.(1)(a)2 of GEnx-2B SB 72-0415, and the affected part has 
undergone a subsequent ECI in which the indication did not meet the 
ECI serviceable or repairable limits referenced in the

[[Page 33498]]

Accomplishment Instructions, paragraph 3.A.(1)(b) of GEnx-1B SB 72-
0472, or paragraph 3.A.(1)(b) of GEnx-2B SB 72-0415; or
    (iii) An ECI indication that does not meet the serviceable or 
repairable limits referenced in the Accomplishment Instructions, 
paragraph 3.A.(1)(b) of GEnx-1B SB 72-0472, or paragraph 3.A.(1)(b) 
of GEnx-2B SB 72-0415.

(i) Credit for Previous Actions

    (1) For affected GEnx-1B model turbofan engines, you may take 
credit for the BSI or ECI required by paragraph (g)(1) of this AD, 
if you performed an ECI of the stages 6-10 compressor rotor spool 
webs, web transitions, and bore faces before the effective date of 
this AD using Subtask 72-31-45-160-002 of TASK 72-31-45-200-807 in 
GE GEnx-1B Engine Manual 05-21-00, Life Limits 001 Mandatory 
Inspections, Rev. 31, dated January 31, 2020, or earlier, and no 
rejectable indications were found.
    (2) For affected GEnx-2B model turbofan engines, you may take 
credit for the BSI or ECI required by paragraph (g)(1) of this AD, 
if you performed and ECI of the stages 6-10 compressor rotor spool 
webs, web transitions, and bore faces before the effective date of 
this AD using Subtask 72-31-45-160-002 of TASK 72-31-45-200-801 in 
GE GEnx-2B Engine Manual 05-21-00, Life Limits 001 Mandatory 
Inspections, Rev. 24, dated January 31, 2020, or earlier, and no 
rejectable indications were found.
    (3) For affected GEnx-1B model turbofan engines, you may take 
credit for the BSI or ECI required by paragraph (g)(1) of this AD, 
if you performed that inspection before the effective date of this 
AD using GE GEnx-1B Service Bulletin (SB) 72-0472 R00, dated April 
24, 2020, or GE GEnx-1B SB 72-0472 R01, dated July 24, 2020, and no 
rejectable indications were found.
    (4) For affected GEnx-2B model turbofan engines, you may take 
credit for the BSI or ECI required by paragraph (g)(1) of this AD, 
if you performed that inspection before the effective date of this 
AD using GE GEnx-2B SB 72-0415 R00, dated April 24, 2020, or GE 
GEnx-2B SB 72-0415 R01, dated July 24, 2020, and no rejectable 
indications were found.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 
certification office, send it to the attention of the person 
identified in Related Information. You may email your request 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) Related Information

    For more information about this AD, contact Mehdi Lamnyi, 
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: (781) 238-7743; fax: (781) 238-7199; 
email: [email protected].

(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) GE GEnx-1B Service Bulletin (SB) 72-0472 R02, dated November 
5, 2020.
    (ii) GE GEnx-2B SB 72-0415 R02, dated November 5, 2020.
    (3) For General Electric Company service information identified 
in this AD, contact General Electric Company, 1 Neumann Way, 
Cincinnati, OH 45215; phone: (513) 552-3272; email: 
[email protected]; website: www.ge.com.
    (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 (781) 238-7759.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on May 19, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-13424 Filed 6-24-21; 8:45 am]
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