Notices. Final rule

9,651 words·~44 min read·/register/2022/05/23/2022-10952·

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BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2021-1183; Project Identifier AD-2021-01193-E; Amendment 39-22029; AD 2022-09-09] RIN 2120-AA64 Airworthiness Directives; CFM International, S.A. Turbofan Engines Editorial Note: Rule document 2022-10447 was originally published on pages 29651 through 29654 in the issue of Monday, May 16, 2022. In that publication on page 29653, in the third column, in paragraph 2(a), “June 20, 2022” should read “June 21, 2022”.

The corrected document is published here in its entirety. AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive

(AD)for all CFM International, S.A.

(CFM)LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine

(HPT)rotor interstage seals, HPT rotor stage 2 disks, low pressure turbine

(LPT)stage 1 disks, LPT stage 2 disks, LPT stage 3 disks, and LPT stage 4 disks. This AD requires revising the airworthiness limitations section

(ALS)of the applicable CFM LEAP-1A Engine Shop Manual

(ESM)and the operator's existing approved continuous airworthiness maintenance program

(CAMP)to incorporate reduced life limits for these parts. This AD also requires the removal of certain LPT stage 4 disks identified by serial number (S/N) prior to their new life limits. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 21, 2022. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 21, 2022. ADDRESSES: For service information identified in this final rule, contact CFM International, S.A., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone:

(877)432-3272; email: *fleetsupport@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

(817)222-5110. It is also available at *https://www.regulations.gov* by searching for and locating Docket No. FAA-2021-1183. Examining the AD Docket You may examine the AD docket at *https://www.regulations.gov* by searching for and locating Docket No. FAA-2021-1183; 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 all CFM LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines. The NPRM published in the **Federal Register** on January 18, 2022 (87 FR 2563). The NPRM was prompted by the manufacturer's detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, HPT rotor interstage seals, HPT rotor stage 2 disks, LPT stage 1 disks, LPT stage 2 disks, LPT stage 3 disks, and LPT stage 4 disks (life-limited parts (LLPs)). Through the manufacturer's investigation, it was determined that these LLPs may have subsurface anomalies that developed during the manufacturing process, resulting in a lower life capability. In the NPRM, the FAA proposed to require revising the ALS of the CFM LEAP-1A ESM, as applicable to each affected engine model, and the operator's existing approved CAMP to incorporate reduced life limits for certain LLPs. In the NPRM, the FAA also proposed to require operators to remove certain LPT stage 4 disks, identified by S/N, before reaching their new life limits. The LPT stage 4 disks, identified by S/N in Figure 1 to paragraph (g)(2) of the NPRM, were discovered by the manufacturer after publication of the ALS revision. After the NPRM was issued, CFM revised its service information by including additional part numbers for newly manufactured parts that did not exist prior to NPRM publication. Accordingly, the FAA has revised paragraph (g)(1)(iii) of this AD to require operators to update the ALS of the applicable CFM LEAP-1A ESM and the operator's existing approved CAMP to include CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 010-00, dated February 15, 2022, instead of CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021. The FAA has also added a credit for previous actions paragraph to this AD, providing credit to operators that incorporated CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021, into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD. 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 two commenters. The commenters were American Airlines

(AA)and Air Line Pilot Association, International (ALPA). The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Include Future Revisions to ESM AA requested that the FAA add “. . . or later” to the following ALS references in paragraph

(g)of this AD to allow for the use of future revisions;

(i)CFM High Pressure Compressor Rotor Life Limits LEAP 1A-05-11-02-01A-0B1B-C, Issue 010-00, dated September 15, 2021, or later;

(ii)CFM High Pressure Turbine Rotor Life Limits LEAP 1A-05-11-03-01A-0B1B-C, Issue 007-00, dated September 15, 2021, or later; and

(iii)CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021, or later. AA stated that they are currently using Issues 7, 9, and 10 of the referenced service information and their ALS and CAMP are already in compliance with this AD. AA also stated that CFM continues to update the referenced service information and Issues 7, 9, and 10 will be further revised. As a result, the requirements of this AD will cause AA to use outdated service information. The FAA disagrees with adding “or later” when referencing the service information in paragraph

(g)of this AD. Future revisions of the service information have not yet been published by the manufacturer or reviewed by the FAA. A request for an alternative method of compliance can be submitted to the FAA if future revisions of the service information referenced in paragraph

(g)of this AD are published. Additionally, if future revisions of the service information are published by the manufacturer and approved by the FAA, the FAA may consider further rulemaking. Request To Add Credit for Previous Actions AA requested that the FAA add a new paragraph (h)(3) to this AD to allow credit for previous actions associated with the required actions proposed in paragraph (g)(1)(iii) of the NPRM, similar to the credit paragraphs proposed in (h)(1) and (h)(2) of the NPRM. AA requested that the new paragraph (h)(3) provide credit to operators if CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 008-00 was incorporated into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD. The FAA notes that CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021, was the first issue of this service information to include the reduced life limits for that module as a result of the investigation into melt-related freckles in the billet. Issue 008-00 and earlier issues do not include the reduced life limits so the FAA will not provide credit for issues released prior to Issue 009-00. Since the FAA issued the NPRM, the manufacturer published CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 010-00, dated February 15, 2022. As a result, the FAA has added paragraph (h)(3) to this AD, providing credit for actions required by paragraph (g)(1)(iii) of this AD if CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021, was incorporated into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD. Support for the AD ALPA expressed support for the AD as written. 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. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 The FAA reviewed CFM High Pressure Compressor Rotor Life Limits LEAP 1A-05-11-02-01A-0B1B-C, Issue 010-00, dated September 15, 2021 (CFM LEAP 1A-05-11-02-01A-0B1B-C); CFM High Pressure Turbine Rotor Life Limits LEAP 1A-05-11-03-01A-0B1B-C, Issue 007-00, dated September 15, 2021 (CFM LEAP 1A-05-11-03-01A-0B1B-C); and CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 010-00, dated February 15, 2022 (CFM LEAP 1A-05-11-04-01A-0B1B-C). CFM LEAP 1A-05-11-02-01A-0B1B-C provides the new life limits for the high-pressure compressor, CFM LEAP 1A-05-11-03-01A-0B1B-C provides the new life limits for the HPT rotor, and CFM LEAP 1A-05-11-04-01A-0B1B-C provides the new life limits for the LPT rotor. 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 reviewed CFM LEAP 1A-05-11-02-01A-0B1B-C, Issue 009-00, dated July 26, 2021; CFM LEAP 1A-05-11-03-01A-0B1B-C, Issue 006-00, dated July 26, 2021, and CFM LEAP 1A-05-11-04-01A-0B1B-C, Issue 009, dated June 1, 2021. This service information provides the new life limits for the LLPs. The FAA also reviewed CFM Service Bulletin

(SB)LEAP-1A-72-00-0413-01A-930A-D, Issue 004-00, dated December 11, 2021 (CFM SB LEAP-1A-72-00-0413-01A-930A-D). CFM SB LEAP-1A-72-00-0413-01A-930A-D specifies procedures for removing and replacing the LLPs, and provides new life limits for certain S/Ns of the LLPs. Costs of Compliance The FAA estimates that this AD affects 256 engines installed on airplanes of U.S. registry. The FAA estimates that 256 engines installed on airplanes of U.S. registry require revising the ALS of the CFM LEAP-1A ESM and the operator's existing approved CAMP. The FAA estimates that zero airplanes of U.S. registry require replacement of the LPT stage 4 disk. The FAA estimates the following costs to comply with this AD: Estimated Costs Action Labor cost Parts cost Cost per product Cost on U.S. operators Revise ALS of Engine Manual and the operator's existing approved CAMP 1 work-hour × $85 per hour = $85 $0 $85 $21,760 The FAA estimates the following costs to replace the LPT stage 4 disk: Estimated Costs Action Labor cost Parts cost Cost per product Cost on U.S. operators Replace LPT Stage 4 disk 225 work-hours × $85 per hour = $19,125 $129,000 $148,125 $0 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 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: **2022-09-09 CFM International, S.A.:** Amendment 39-22029; Docket No. FAA-2021-1183; Project Identifier AD-2021-01193-E.

(a)Effective Date This airworthiness directive

(AD)is effective June 21, 2022.

(b)Affected ADs None.

(c)Applicability This AD applies to CFM International, S.A.

(CFM)LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A model turbofan engines.

(d)Subject Joint Aircraft System Component

(JASC)Code 7230, Turbine Engine Compressor Section, and JASC Code 7250, Turbine Section.

(e)Unsafe Condition This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life of certain compressor rotor stages 6-10 spools, high pressure turbine

(HPT)rotor interstage seals, HPT rotor stage 2 disks, low pressure turbine

(LPT)stage 1 disks, LPT stage 2 disks, LPT stage 3 disks, and LPT stage 4 disks. The FAA is issuing this AD to prevent the failure of the high-pressure compressor, HPT rotor, and LPT rotor. The unsafe condition, if not addressed, could result in release of uncontained 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)Within 60 days after the effective date of this AD, revise the airworthiness limitations section

(ALS)of the applicable CFM LEAP-1A Engine Shop Manual (the ESM) and the operator's existing approved continuous airworthiness maintenance program

(CAMP)by incorporating the following service information:

(i)CFM High Pressure Compressor Rotor Life Limits LEAP 1A-05-11-02-01A-0B1B-C, Issue 010-00, dated September 15, 2021; and

(ii)CFM High Pressure Turbine Rotor Life Limits LEAP 1A-05-11-03-01A-0B1B-C, Issue 007-00, dated September 15, 2021; and

(iii)CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 010-00, dated February 15, 2022.

(2)Before the LPT stage 4 disk, part number (P/N) 362-039-520-0, with serial numbers identified in Figure 1 to paragraph (g)(2) of this AD (Figure 1) accumulates the cycles in Figure 1, or within 100 cycles after the effective date of this AD, whichever occurs later, remove the affected LPT stage 4 disk from service and replace with a part eligible for installation. Figure 1 to Paragraph

(g)(2)—Life Limits for LPT Stage 4 Disks, P/N 362-039-520-0 LPT stage 4 disk serial No. Life limit for LEAP-1A23, -1A24, -1A24E1, -1A26, -1A26E1, -1A29, -1A30, -1A32, -1A33, -1A33B2, and -1A35A Life limit for LEAP-1A26CJ and -1A29CJ PC975638 PC975635. 2,500 cycles 1,400 cycles.

(h)Credit for Previous Actions

(1)You may take credit for the action required by paragraph (g)(1)(i) of this AD if the following service information was incorporated into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD: CFM High Pressure Compressor Rotor Life Limits LEAP 1A-05-11-02-01A-0B1B-C, Issue 009-00, dated July 26, 2021.

(2)You may take credit for the action required by paragraph (g)(1)(ii) of this AD if the following service information was incorporated into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD: CFM High Pressure Turbine Rotor Life Limits LEAP 1A-05-11-03-01A-0B1B-C, Issue 006-00, dated July 26, 2021.

(3)You may take credit for the action required by paragraph (g)(1)(iii) of this AD if the following service information was incorporated into the ALS of the applicable ESM and the operator's existing approved CAMP prior to the effective date of this AD: CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 009-00, dated June 1, 2021.

(i)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 paragraph

(j)of this AD. 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.

(j)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.*

(k)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)CFM High Pressure Compressor Rotor Life Limits LEAP 1A-05-11-02-01A-0B1B-C, Issue 010-00, dated September 15, 2021.

(ii)CFM High Pressure Turbine Rotor Life Limits LEAP 1A-05-11-03-01A-0B1B-C, Issue 007-00, dated September 15, 2021.

(iii)CFM Low Pressure Turbine Rotor Life Limits LEAP 1A-05-11-04-01A-0B1B-C, Issue 010-00, dated February 15, 2022.

(3)For service information identified in this AD, contact CFM International, S.A., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone:

(877)432-3272; email: *fleetsupport@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

(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: *https://www.archives.gov/federal-register/cfr/ibr-locations.html.* Issued on April 15, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. R1-2022-10447 Filed 5-20-22; 8:45 am] BILLING CODE 0099-10-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2022-0086; Project Identifier MCAI-2021-01035-T; Amendment 39-22026; AD 2022-09-06] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes Editorial Note: Rule document 2022-10460 was originally published on pages 29654 through 29657 in the issue of Monday, May 16, 2022. In that publication on page 29655, in the first column, in the DATES , “June 20, 2022” should read “June 21, 2022”. Also, in that publication, on page 29656, in the first column, paragraph 2(a), “June 20, 2022” should read “June 21, 2022”. The corrected document is published here in its entirety. AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding Airworthiness Directive

(AD)2021-13-06, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-13-06 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2021-13-06, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-13-06 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, 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 is effective June 21, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 21, 2022. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 3, 2021 (86 FR 40934, July 30, 2021). ADDRESSES: 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* ; internet *www.easa.europa.eu.* You may find this IBR material on the EASA website at *https://ad.easa.europa.eu.* You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available in the AD docket at *https://www.regulations.gov* by searching for and locating Docket No. FAA-2022-0086. Examining the AD Docket You may examine the AD docket at *https://www.regulations.gov* by searching for and locating Docket No. FAA-2022-0086; 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. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email *dan.rodina@faa.gov.* SUPPLEMENTARY INFORMATION: Background EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2021-0208, dated September 15, 2021 (EASA AD 2021-0208) (also referred to as the MCAI), to correct an unsafe condition for all Airbus SAS Model A350-941 and -1041 airplanes. The FAA issued a notice of proposed rulemaking

(NPRM)to amend 14 CFR part 39 to supersede AD 2021-13-06, Amendment 39-21611 (86 FR 40934, July 30, 2021) (AD 2021-13-06). AD 2021-13-06 applied to certain Airbus SAS Model A350-941 and -1041 airplanes. The NPRM published in the **Federal Register** on February 9, 2022 (87 FR 7397). The NPRM was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The NPRM proposed to continue to require the actions in AD 2021-13-06 and require revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, as specified in EASA AD 2021-0208. The FAA is issuing this AD to address hazardous or catastrophic airplane system failures. See the MCAI for additional background information. Discussion of Final Airworthiness Directive Comments The FAA received a comment from the Air Line Pilots Association, International

(ALPA)who supported the NPRM without change. Conclusion The FAA reviewed the relevant data, considered the comment received, and determined that air safety requires adopting this AD as proposed. Except for minor editorial changes, this AD is adopted as proposed in the NPRM. None of the changes will increase the economic burden on any operator. Accordingly, the FAA is issuing this AD to address the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 EASA AD 2021-0208 describes new or more restrictive airworthiness limitations for airplane structures and safe life limits. This AD also requires EASA AD 2020-0211, dated October 5, 2020, and EASA AD 2021-0026, dated January 20, 2021, which the Director of the Federal Register approved for incorporation by reference as of September 3, 2021 (86 FR 40934, July 30, 2021). This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 27 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: The FAA estimates the total cost per operator for the retained actions from AD 2021-13-06 to be $7,650 (90 work-hours × $85 per work-hour). The FAA has determined that revising the existing maintenance or inspection program takes an average of 90 work-hours per operator, although the agency recognizes that this number may vary from operator to operator. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), the FAA has determined that a per-operator estimate is more accurate than a per-airplane estimate. The FAA estimates the total cost per operator for the new proposed actions to be $7,650 (90 work-hours × $85 per work-hour). 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

(AD)2021-13-06, Amendment 39-21611 (86 FR 40934, July 30, 2021); and b. Adding the following new AD: **2022-09-06 Airbus SAS:** Amendment 39-22026; Docket No. FAA-2022-0086; Project Identifier MCAI-2021-01035-T.

(a)Effective Date This airworthiness directive

(AD)is effective June 21, 2022.

(b)Affected ADs

(1)This AD replaces AD 2021-13-06, Amendment 39-21611 (86 FR 40934, July 30, 2021) (AD 2021-13-06).

(2)This AD affects AD 2019-20-01, Amendment 39-19754 (84 FR 55495, October 17, 2019) (AD 2019-20-01).

(c)Applicability This AD applies to Airbus SAS Model A350-941 and -1041 airplanes, certificated in any category, with an original airworthiness certificate or original export certificate of airworthiness issued on or before July 20, 2021.

(d)Subject Air Transport Association

(ATA)of America Code 05, Time Limits/Maintenance Checks.

(e)Reason This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address hazardous or catastrophic airplane system failures.

(f)Compliance Comply with this AD within the compliance times specified, unless already done.

(g)Retained Maintenance or Inspection Program Revision, With No Changes This paragraph restates the requirements of paragraph

(g)of AD 2021-13-06, with no changes. For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before July 22, 2020: Except as specified in paragraph

(h)of this AD, comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency

(EASA)AD 2020-0211, dated October 5, 2020 (EASA AD 2020-0211); and EASA AD 2021-0026, dated January 20, 2021 (EASA AD 2021-0026). Where EASA AD 2021-0026 affects the same airworthiness limitations (tasks and life limits) as those in EASA AD 2020-0211, the airworthiness limitations referenced in EASA AD 2021-0026 prevail. Accomplishing the revision of the existing maintenance or inspection program required by paragraph

(j)of this AD terminates the requirements of this paragraph.

(h)Retained Exceptions to EASA AD 2020-0211 and EASA AD 2021-0026, With No Changes This paragraph restates the requirements of paragraph

(h)of AD 2021-13-06, with no changes. For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before July 22, 2020:

(1)Where EASA AD 2020-0211 and EASA AD 2021-0026 refers to its effective date, this AD requires using September 3, 2021 (the effective date of AD 2021-13-06).

(2)The requirements specified in paragraphs

(1)and

(2)of EASA AD 2020-0211 and EASA AD 2021-0026 do not apply to this AD.

(3)Paragraph

(3)of EASA AD 2020-0211 and EASA AD 2021-0026 specifies revising “the approved AMP [aircraft maintenance program]” within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, to incorporate the “limitations, tasks and associated thresholds and intervals” specified in paragraph

(3)of EASA AD 2020-0211 and EASA AD 2021-0026 within 90 days after September 3, 2021 (the effective date of AD 2021-13-06).

(4)The initial compliance time for doing the tasks specified in paragraph

(3)of EASA AD 2020-0211 and EASA AD 2021-0026 is at the applicable “thresholds” as incorporated by the requirements of paragraph

(3)of EASA AD 2020-0211 and EASA AD 2021-0026, or within 90 days after September 3, 2021 (the effective date of AD 2021-13-06), whichever occurs later.

(5)The provisions specified in paragraphs

(4)and

(5)of EASA AD 2020-0211 do not apply to this AD.

(6)The provisions specified in paragraph

(4)of EASA AD 2021-0026 do not apply to this AD.

(7)The “Remarks” section of EASA AD 2020-0211 and EASA AD 2021-0026 does not apply to this AD.

(i)Retained Provisions for Alternative Actions and Intervals, With a New Exception This paragraph restates the requirements of paragraph

(i)of AD 2021-13-06, with a new exception. For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before July 22, 2020: Except as required by paragraph

(j)of this AD, after the existing maintenance or inspection program has been revised as required by paragraph

(g)of this AD, no alternative actions ( *e.g.,* inspections) and intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2020-0211 or EASA AD 2021-0026.

(j)New Maintenance or Inspection Program Revision Except as specified in paragraph

(k)of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2021-0208, dated September 15, 2021. Accomplishing the revision of the existing maintenance or inspection program required by this paragraph terminates the requirements of paragraph

(g)of this AD.

(k)Exceptions to EASA AD 2021-0208

(1)Where EASA AD 2021-0208 refers to its effective date, this AD requires using the effective date of this AD.

(2)The requirements specified in paragraphs

(1)and

(2)of EASA AD 2021-0208 do not apply to this AD.

(3)Paragraph

(3)of EASA AD 2021-0208 specifies to revise “the AMP” within 12 months after its effective date, but this AD requires revising the existing maintenance or inspection program, as applicable, within 90 days after the effective date of this AD.

(4)The initial compliance time for doing the tasks specified in paragraph

(3)of EASA AD 2021-0208 is at the applicable “limitations” as incorporated by the requirements of paragraph

(3)of EASA AD 2021-0208, or within 90 days after the effective date of this AD, whichever occurs later.

(5)The provisions specified in paragraphs

(4)and

(5)of EASA AD 2021-0208 do not apply to this AD.

(6)The “Remarks” section of EASA AD 2021-0208 does not apply to this AD.

(7)Where EASA AD 2021-0208 refers to Airbus A350 Airworthiness Limitations Section

(ALS)Part 4, Revision 6 and Variation 6.1, replace the text “Airbus A350 Airworthiness Limitations Section

(ALS)Part 4, Revision 6 and Variation 6.1,” with “Airbus A350 Airworthiness Limitations Section

(ALS)Part 4, Revision 6 and Variation 6.1; for any airworthiness limitations (tasks and life limits) that are in both documents, the airworthiness limitations (tasks and life limits) specified in Variation 6.1 prevail.”

(l)New Provisions for Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as required by paragraph

(j)of this AD, no alternative actions ( *e.g.,* inspections) and intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2021-0208.

(m)Terminating Action for Certain Requirements of AD 2019-20-01 Accomplishing the actions required by paragraph

(g)or

(j)of this AD terminates the repetitive greasing task for batch 02 group of affected thrust reverser actuators required by paragraph

(g)of AD 2019-20-01.

(n)Additional AD Provisions The following provisions also apply to this AD:

(1)*Alternative Methods of Compliance (AMOCs):* The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph

(o)of this AD. Information may be emailed to: *9-AVS-AIR-730-AMOC@faa.gov.* Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.

(2)*Contacting the Manufacturer:* For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(o)Related Information For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email *dan.rodina@faa.gov.*

(p)Material Incorporated by Reference

(1)The Director of the Federal Register approved the incorporation by reference

(IBR)of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2)You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(3)The following service information was approved for IBR on June 21, 2022.

(i)European Union Aviation Safety Agency

(EASA)AD 2021-0208, dated September 15, 2021.

(ii)[Reserved]

(4)The following service information was approved for IBR on September 3, 2021 (86 FR 40934, July 30, 2021).

(i)European Union Aviation Safety Agency

(EASA)AD 2020-0211, dated October 5, 2020.

(ii)European Union Aviation Safety Agency

(EASA)AD 2021-0026, dated January 20, 2021.

(5)For the EASA ADs identified 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.* You may find this EASA AD on the EASA website at *https://ad.easa.europa.eu.*

(6)You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195.

(7)You may view this material 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: *https://www.archives.gov/federal-register/cfr/ibr-locations.html.* Issued on April 15, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. R1-2022-10460 Filed 5-20-22; 8:45 am] BILLING CODE 0099-10-D DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2022-0146; Project Identifier AD-2021-00449-R; Amendment 39-22054; AD 2022-11-04] RIN 2120-AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is superseding Airworthiness Directive

(AD)2020-26-13, which applied to certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. AD 2020-26-13 required establishing the life limit for certain part-numbered horizontal stabilizer root fittings FWD (forward root fittings) and certain part-numbered stabilizer strut fittings. AD 2020-26-13 also required repetitively inspecting certain parts, and depending on the inspection results, removing parts from service. Finally AD 2020-26-13 prohibited installing certain stabilizer assemblies on any helicopter. Since the FAA issued AD 2020-26-13, the manufacturer notified the FAA that due to an error in the service information, certain part numbers in AD 2020-26-13 are incorrect. Also, the FAA determined that additional inspections are required to address the unsafe condition. This AD retains certain requirements and the prohibition for installing certain stabilizer assemblies on any helicopter from AD 2020-26-13, corrects certain part numbers, and requires additional repetitive inspections. The actions of this AD are intended to address an unsafe condition on these products. DATES: This AD is effective June 27, 2022. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 1, 2021 (85 FR 84201, December 28, 2020). ADDRESSES: For service information identified in this final rule, contact Sikorsky's Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbell, CT 06611, United States; phone:

(800)946-4337; email: *wcs_cust_service_eng.gr-sik@lmco.com;* website: *www.sikorsky360.com.* You may view this service information 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 this material at the FAA, call

(817)222-5110. It is also available at *https://www.regulations.gov* by searching for and locating Docket No. FAA-2022-0146. Examining the AD Docket You may examine the AD docket on the internet at *https://www.regulations.gov in* Docket No. FAA-2022-0146; 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 AD, any service information that is incorporated by reference, 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: Dorie Resnik, Aerospace Engineer, Aviation Safety Section, Boston ACO Branch, Compliance & Airworthiness Division, 1200 District Avenue, Burlington, MA 01803; telephone

(781)238-7693; email *9-AVS-AIR-BACO-COS@faa.gov.* SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking

(NPRM)to amend 14 CFR part 39 to supersede AD 2020-26-13, Amendment 39-21368 (85 FR 84201, December 28, 2020) (AD 2020-26-13). AD 2020-26-13 applied to Sikorsky Model S-92A helicopters with forward root fitting part number (P/N) 92209-07111-101 or 92070-20125-101; or stabilizer strut fitting P/N 92209-07404-041, 92209-07403-041, or 92070-20117-041 installed on horizontal stabilizer assembly (stabilizer assembly) P/N 92070-20117-045, 92070-20117-046, 92070-20125-041, 92070-20125-042, 92070-20125-043, 92070-20125-044, 92205-07400-043, or 92205-07400-045. The NPRM published in the **Federal Register** on February 23, 2022 (87 FR 10115). The NPRM was prompted by the discovery that incorrect P/Ns were identified in the Applicability and the Required Actions paragraphs of AD 2020-26-13. Additionally, after the FAA issued AD 2020-26-13, Sikorsky notified the FAA that an additional repetitive inspection of certain parts of the stabilizer strut assembly is required to prevent the unsafe condition. Finally, after the FAA issued AD 2020-26-13, Sikorsky requested and the FAA approved a global Alternative Method of Compliance

(AMOC)to allow only removing parts from service that are cracked, corroded, or have fretting, deformation, or wear rather than require removing the upper and lower support strut rod ends, including lug and conical fitting and both upper and lower attachment fittings on the stabilizer from service. In the NPRM, the FAA proposed to expand the applicability of AD 2020-26-13 by adding an additional part-numbered stabilizer assembly. The NPRM also proposed to correct paragraph (g)(4) of the Required Actions so that the installation of the titanium stabilizer strut fitting is terminating action for the 50-hour time-in-service

(TIS)inspections of the aluminum stabilizer strut fitting. The NPRM also proposed to require an additional repetitive inspection of certain parts of the stabilizer strut assembly. Finally, the NPRM proposed to incorporate the FAA approved global AMOC. Discussion of Final Airworthiness Directive Comments The FAA received a comments from Sikorsky stating that in the section titled “Actions Since AD 2020-26-13 Was Issued” of the NPRM, the part number specified (92070-20117-04) is incorrect and should be 92070-20117-041. The FAA acknowledges this comment; however, the part number is not used in the “Background” section of this final rule. In light of this, the commenter's request no longer applies. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety requires adopting the 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. None of the changes will increase the economic burden on any operator. Related Service Information Under 1 CFR Part 51 This AD continues to require S-92 Maintenance Manual, SA S92A-AMM-000, Temporary Revision

(TR)55-33, dated March 24, 2020 (TR 55-33), which the Director of the Federal Register approved for incorporation by reference as of February 1, 2021 (85 FR 84201, December 28, 2020). 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 the ADDRESSES section. Other Related Service Information The FAA reviewed S-92 Maintenance Manual SA S92A-AWL-000, TR No. 4-58, dated October 2, 2017 (TR 4-58), and S-92 Maintenance Manual SA S92A-AWL-000, TR No. 4-66 dated November 20, 2019 (TR 4-66). This service information revises Task 4-00-00-200-000, Table 1 Replacement Schedule, dated November 30, 2015. Both TR 4-58 and 4-66 revise the Airworthiness Limitations Schedule by removing certain part-numbered components, introducing new part-numbered components, and establishing replacement intervals and recurring inspections for the forward root fitting and the horizontal stabilizer strut fitting. TR 4-58 also specifies inspecting the horizontal stabilizer and attaching hardware at a recurring interval of 250 hours TIS. Differences Between This AD and the Service Information The service information requires returning affected parts to a Sikorsky specialist; this AD does not. Costs of Compliance The FAA estimates that this AD affects 82 helicopters of U.S. registry. Labor costs are estimated at $85 per work-hour. Based on these numbers, the FAA estimates the following costs to comply with this AD. Visually inspecting the stabilizer assembly and attached hardware takes about 3 work-hours for an estimated cost of $255 per helicopter and $20,910 for the U.S. fleet per inspection cycle. If required, replacing a hat bushing and both upper fittings and lower fittings takes about 1 work-hour and parts cost about $10,000 for an estimated cost of $10,085 per replacement. If required, replacing the upper and lower support strut rod ends, including lug and conical fitting, takes about 1 work-hour and parts cost about $10,000 for an estimated cost of $10,085 per replacement. If required, replacing Mylar washers takes about 0.5 work-hour and parts cost about $76 for an estimated cost of $119 per replacement. If required, performing a fluorescent penetrant inspection takes about 3 work-hours for an estimated cost of $255 per inspection. If required, replacing a stabilizer assembly takes about 6 work-hours and parts cost about $312,000 for an estimated cost of $312,510 per replacement. If required, replacing a forward root fitting takes about 10 work-hours and parts cost about $25,000 for an estimated cost of $25,850 per replacement. If required, replacing a stabilizer strut fitting takes about 10 work-hours and parts cost about $10,000 for an estimated cost of $10,850 per replacement. If required, replacing a forward root fitting and an aft attachment fitting takes about 20 work-hours and parts cost about $50,000 for an estimated cost of $51,700 per replacement. If required, removing wear or corrosion and applying corrosion preventative compound takes about 0.5 work-hour and parts cost a nominal amount for an estimated cost of $43 per action. If required, replacing a stabilizer attachment bolt and barrel nut set takes about 1 work-hour and parts cost about $500 for an estimated cost of $585 per replacement. If required, replacing a fastener takes about 0.1 work-hour and parts cost a nominal amount for an estimated cost of $9 per fastener. If required, removing the abrasion-resistant Teflon coating to inspect each forward and aft attachment fitting mating surface takes about 5 work-hours for an estimated cost of $425 per inspection. If required, applying alodine or equivalent and applying abrasion-resistant Teflon coating takes about 5 work hours with minimal parts cost for an estimated cost of $425 per application. According to Sikorsky, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all costs in this cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA has determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD:

(1)Is not a “significant regulatory action” under Executive Order 12866,

(2)Will not affect intrastate aviation in Alaska, and

(3)Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive AD 2020-26-13, Amendment 39-21368 (85 FR 84201, December 28, 2020); and b. Adding the following new airworthiness directive: **2022-11-04 Sikorsky Aircraft Corporation:** Amendment 39-22054; Docket No. FAA-2022-0146; Project Identifier AD-2021-00449-R.

(a)Effective Date This airworthiness directive

(AD)is effective June 27, 2022.

(b)Affected ADs This AD replaces AD 2020-26-13, Amendment 39-21368 (85 FR 84201, December 28, 2020) (AD 2020-26-13).

(c)Applicability This AD applies to Sikorsky Aircraft Corporation Model S-92A helicopters, certificated in any category, with the following installed: Horizontal stabilizer root fitting FWD (forward root fitting) part number (P/N) 92209-07111-101 or 92070-20125-101; or stabilizer strut fitting P/N 92209-07403-041 or 92070-20117-041 installed on horizontal stabilizer assembly (stabilizer assembly) P/N 92070-20117-045, 92070-20117-046, 92070-20125-041, 92070-20125-042, 92070-20125-043, 92070-20125-044, 92205-07400-043, 92205-07400-045, or 92205-07400-047.

(d)Subject Joint Aircraft System Component

(JASC)Code: 5510, Horizontal Stabilizer Structure.

(e)Unsafe Condition This AD was prompted by incidents of fatigue cracks in a forward root fitting and life limit recalculations for forward root fitting P/N 92209-07111-101 and 92070-20125-101. The FAA is issuing this AD to prevent a forward root fitting from remaining in service beyond its life limit, detect fatigue cracking in a forward root fitting, and prevent increased load and stress cracking in the stabilizer root fitting aft. The unsafe condition, if not addressed, could result in failure of a stabilizer root fitting, separation of the stabilizer assembly from the helicopter, and subsequent loss of control of the helicopter.

(f)Compliance Comply with this AD within the compliance times specified, unless already done.

(g)Required Actions

(1)Within 50 hours time-in-service

(TIS)after the effective date of this AD:

(i)Determine the total hours TIS of the forward root fitting P/N 92209-07111-101 or 92070-20125-101. If the total hours TIS of the forward root fitting is unknown, use the total hours TIS of the stabilizer assembly instead.

(A)If the forward root fitting has accumulated 7,900 or more total hours TIS, before further flight, remove the forward root fitting from service.

(B)If the forward root fitting has accumulated less than 7,900 total hours TIS, before exceeding 7,900 total hours TIS, remove the forward root fitting from service.

(ii)Thereafter following paragraph (g)(1)(i) of this AD, remove the forward root fitting from service before accumulating 7,900 total hours TIS.

(iii)For stabilizer assemblies with stabilizer strut fitting P/N 92070-20117-041 installed, perform the following actions:

(A)Determine the total hours TIS of stabilizer strut fitting P/N 92070-20117-041.

(B)If the stabilizer strut fitting has accumulated 19,100 or more total hours TIS, before further flight, remove the stabilizer strut fitting from service.

(C)If the stabilizer strut fitting has accumulated less than 19,100 total hours TIS, before exceeding 19,100 total hours TIS, remove the stabilizer strut fitting from service.

(iv)Thereafter following paragraph (g)(1)(iii) of this AD, remove the stabilizer strut fitting from service before accumulating 19,100 total hours TIS.

(2)For helicopters with stabilizer strut fitting P/N 92070-20117-041 or 92209-07403-041 installed, within 50 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 50 hours TIS:

(i)Remove the support strut and using a cheese cloth (or similar cloth) and isopropyl alcohol, clean the upper and lower support strut rod ends, horizontal stabilizer attachment fitting, and the tail rotor pylon attachment fitting.

(ii)If installed, visually inspect the surface of each Mylar washer P/N 92070-20117-104 (Mylar washer). The surface should be smooth and continuous. If there is any visible damage such as any tear or scrape, remove the Mylar washer from the peelable-ply washer P/N 92070-20117-105 (peelable-ply washer) and remove the Mylar washer from service as follows:

(A)Dampen a low-lint cloth with 3M 6041 adhesive remover and place on the top of the Mylar washer.

(B)Allow the adhesive remover to soften the Mylar washer and peel the Mylar washer back.

(C)Repeat with more solvent until the Mylar washer and adhesive are removed.

(D)Clean the peelable-ply washer with cheese cloth moistened with isopropyl alcohol and adhere a new Mylar washer to the peelable-ply washer. **Note 1 to paragraph (g)(2)(ii):** Stabilizer assembly P/Ns 92070-20125-041, 92070-20125-042, 92070-20125-043, and 92070-20125-044 do not utilize the Mylar washer. The inspection of the Mylar washer is not required on helicopters with stabilizer assembly P/N 92070-20125-041, 92070-20125-042, 92070-20125-043, or 92070-20125-044 installed.

(iii)Using a 10X or higher power magnifying glass, a flashlight, and a mirror, visually inspect the hat bushing and both upper fittings and lower fittings for a crack, corrosion, fretting, deformation, and wear. If there is a crack, corrosion, fretting, deformation, or wear on any part, before further flight, remove the part from service.

(iv)Using a 10X or higher power magnifying glass, a flashlight, and a mirror, visually inspect both upper and lower support strut rod ends, including each lug and conical fitting, and both upper and lower attachment fittings on the stabilizer and pylon including the bushings for a crack, corrosion, fretting, deformation, and wear. If there is a crack, corrosion, fretting, deformation, or wear on any part, before further flight, remove the part from service.

(3)Within 250 hours TIS or one year, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 250 hours TIS or one year, whichever occurs first:

(i)Remove the stabilizer assembly and visually inspect each stabilizer attachment bolt and barrel nut set for corrosion, a crack, and damage to the threads. For the purposes of this inspection, damage may be indicated by uneven threads, missing threads, or cross-threading.

(A)If there is corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA-approved procedures.

(B)If there is corrosion that exceeds allowable limits, or a crack, or damage to the threads, before further flight, remove the bolt and barrel nut set from service.

(ii)Inspect the forward root fitting and the aft attachment fitting by:

(A)Gaining access to the inside of the horizontal stabilizer.

(B)Using Brulin Cleaner SD 1291 (or equivalent) and a low-lint cloth, remove all traces of sealing compound, oil, and dirt from the stabilizer mounting surfaces.

(C)Using a 10X or higher magnifying glass, inspect for any crack, wear, and corrosion. ( *1* ) If there is a crack, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( *2* ) If there is wear or corrosion that exceeds allowable limits, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( *3* ) If there is wear or corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA-approved procedures.

(D)Visually inspect each attachment fitting bolt hole and fastener hole for a crack, wear, and corrosion. ( *1* ) If there is a crack, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( *2* ) If there is wear or corrosion that exceeds allowable limits, before further flight, remove the affected forward root fitting and the affected aft attachment fitting from service. ( *3* ) If there is wear or corrosion within allowable limits, before further flight, treat for corrosion in accordance with FAA approved procedures.

(E)Inspect for loose or working fasteners. If there is a loose or working fastener, before further flight, remove the fastener from service.

(iii)As an alternative means to inspect for cracks in paragraphs (g)(3)(i) and

(ii)of this AD, perform a florescent penetrant inspection (FPI).

(iv)Visually inspect each forward and aft attachment fitting mating surface for wear of the abrasion-resistant Teflon coating and degradation. For the purposes of this inspection, degradation may be indicated by fretting. Refer to Figure 204, of S-92 Maintenance Manual, SA S92A-AMM-000, Temporary Revision 55-33, Task 55-11-01-210-004, dated March 24, 2020 (TR 55-33), for a depiction of the area to be inspected. For the purposes of this inspection, wear may be indicated by less than 100% coverage of the abrasion-resistant Teflon coating. If there is wear to the abrasion-resistant Teflon coating or degradation, before further flight:

(A)Chemically strip the abrasion-resistant Teflon coating from the entire mounting pad in accordance with paragraph 7.A.(7)(a) of TR 55-33.

(B)FPI or eddy current inspect for a crack. If there is a crack, before further flight, remove the stabilizer assembly from service.

(C)If there is no crack, treat the affected area by applying alodine or equivalent. Apply abrasion-resistant Teflon coating in accordance with paragraphs 7.A.(7)(d) through

(e)of TR 55-33.

(4)Installing stabilizer strut fitting P/N 92209-07404-041 is a terminating action for the requirements in paragraph (g)(2) of this AD.

(5)As of the effective date of this AD, do not install stabilizer assembly P/N 92205-07400-043, 92205-07400-045, or 92205-07400-047 on any helicopter.

(h)Alternative Methods of Compliance (AMOCs)

(1)The Manager, Boston 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 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

(i)of this AD.

(i)Related Information For more information about this AD, contact Dorie Resnik, Aerospace Engineer, Boston ACO Branch, 1200 District Avenue, Burlington, Massachusetts 01803; telephone 781-238-7693; email *9-AVS-AIR-BACO-COS@faa.gov.*

(j)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.

(3)The following service information was approved for IBR on February 1, 2021 (85 FR 84201, December 28, 2020).

(i)S-92 Maintenance Manual, SA S92A-AMM-000, Temporary Revision

(TR)55-33, dated March 24, 2020.

(ii)[Reserved]

(4)For Sikorsky Aircraft Corporation service information identified in this AD, contact Sikorsky's Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbell, CT 06611, United States; phone:

(800)946-4337; email: *wcs_cust_service_eng.gr-sik@lmco.com;* website: *www.sikorsky360.com.*

(5)You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call

(817)222-5110.

(6)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: *https://www.archives.gov/federal-register/cfr/ibr-locations.html.* Issued on May 16, 2022. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-10952 Filed 5-20-22; 8:45 am]

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