AD 2021-24-15

70966 Federal Register / Vol. 86, No. 237 / Tuesday, December 14, 2021 / Rules and Regulations blade that has accumulated or exceeded 6,800 total hours TIS. For each TR blade that has accumulated less than 6,800 total hours TIS do the following: (i) Create a component history card or equivalent record to establish a life limit of 6,800 total hours TIS. (ii) Re-identify each TR blade P/N L642A2002101 as P/N L642A2002104 and re- identify each T/R blade P/N L642A2002111 as P/N L642A2002112 by following paragraph 3.B.5 of the Accomplishment Instructions of ASB EC135H–04A–002, or paragraph 3.B.7 of the Accomplishment Instructions of ASB EC135–04A–014 as applicable to your model helicopter. (iii) Thereafter, remove from service any TR blade P/N L642A2002104 or P/N L642A2002112 before it accumulates 6,800 total hours TIS. (2) For Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with TR blade P/N L642A2002103 that has previously been installed on Model EC135P3 or EC135T3 helicopters, within 350 hours TIS after the effective date of this AD, determine the total hours TIS of the TR blade in accordance with a method approved by the Manager, General Aviation and Rotorcraft Section, International Validation Branch, FAA; or European Union Aviation Safety Agency (EASA); or Airbus Helicopters’ EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) For Model EC135P3 and EC135T3 helicopters within 350 hours TIS after the effective date of this AD, remove from service any TR blade P/N L642A2002103 before exceeding 6,800 total hours TIS. (4) For Model EC135P3 and EC135T3 helicopters, as of the effective date of this AD, do not install any TR blade P/N L642A2002101, P/N L642A2002103, or P/N L642A2002111 on any helicopter. (5) For Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters, as of the effective date of this AD, do not install any TR blade P/N L642A2002101 or L642A2002111 that has accumulated or exceeded 500 total hours TIS while installed on a Model EC135P3 or EC135T3 helicopter. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: 9-AVS-AIR- 730-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. (i) Related Information (1) For more information about this AD, contact Andrea Jimenez, Aerospace Engineer, COS Program Management Section, Operational Safety Branch, Compliance & Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. (2) Service information identified in this AD, is available at the contact information specified in paragraphs (j)(3) and (4) of this AD. (3) The subject of this AD is addressed in European Union Aviation Safety Agency (EASA) AD 2021–0050, dated February 23, 2021. You may view the EASA AD at https:// www.regulations.gov in Docket No. FAA– 2021–0797. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Alert Service Bulletin ASB EC135H–04A–002, Revision 1, dated December 21, 2020. (ii) Airbus Helicopters Alert Service Bulletin ASB EC135–04A–014, Revision 1, dated December 21, 2020. (3) For service information identified in this AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbus.com/helicopters/services/ technical-support.html. (4) 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. (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 November 17, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–26975 Filed 12–13–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0830; Project Identifier AD–2020–00257–R; Amendment 39–21836; AD 2021–24–15] RIN 2120–AA64 Airworthiness Directives; Bell Textron Canada Limited Helicopters AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited Model 206L–1, 206L–3, and 206L–4 helicopters with certain Air Comm Corporation air conditioning systems installed. This AD was prompted by reports of damage to the drive ring spline teeth and the mating spline teeth. This AD requires visually inspecting the drive ring spline teeth and the mating area spline teeth on the oil cooler blower shaft for signs of deformation and fretting and depending on the results of the inspection, removing certain parts from service. This AD also requires reinstalling certain parts, applying torque, and aligning certain bolt holes. The FAA is issuing this AD to address the unsafe condition on these products. DATES : This AD is effective January 18, 2022. The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of January 18, 2022. ADDRESSES : For service information identified in this final rule, contact Air Comm Corporation, 1575 Westminster, CO 80234; telephone (303) 440–4075; or at https://www.aircommcorp.com. You may view the referenced 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–2021–0830. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0830; 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 referenced service VerDate Sep<11>2014 16:20 Dec 13, 2021 Jkt 256001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1 jspears on DSK121TN23PROD with RULES1

70967 Federal Register / Vol. 86, No. 237 / Tuesday, December 14, 2021 / Rules and Regulations information, any comments received, and other information. The street 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 : Matthew Bryant, Aerospace Engineer, Denver ACO Branch, FAA, 26805 East 68th Avenue, Denver, CO 80249; telephone (303) 342–1080; email 9- Denver-Aircraft-Cert@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 Bell Textron Canada Limited Model 206L–1, Model 206L–3, and Model 206L–4 helicopters with certain Air Comm Corporation air conditioning systems installed. The NPRM published in the Federal Register on September 24, 2021 (86 FR 53015). In the NPRM, the FAA proposed to require within 300 hours time-in-service (TIS), and thereafter at intervals not to exceed 300 hours TIS, gaining access to the drive ring spline teeth and the mating area spline teeth on the oil cooler blower shaft, repetitively inspecting the drive ring spline teeth and the mating spline teeth on the tail rotor drive’s oil cooler blower shaft for deformation and fretting, and depending on the results of each inspection, removing certain parts from service before further flight. The NPRM also proposed to require reinstalling certain parts, and if required, reinstalling the drive pulley by torqueing and aligning the drive pulley bolt holes. The FAA issued Special Airworthiness Information Bulletin SW–19–05 on April 4, 2019 (SAIB SW– 19–05), to alert owners and operators of Bell Textron Canada Limited Model 206L–1, 206L–3, and 206L–4 helicopters with Air Comm Corporation’s Supplemental Type Certificate (STC) SH2750NM installed. SAIB SW–19–05 was prompted by reports of the air conditioner pulley’s locking system, which is installed on the oil cooler drive shaft’s splined quill, causing excessive spline tooth wear to the drive ring spline teeth and the mating spline teeth on the oil cooler blower shaft. SAIB SW–19–05 recommends following the inspection instructions of certain Air Comm Corporation service information and routinely inspecting the air conditioner pulley lock ring. At the time SAIB SW–19–05 was issued, the airworthiness concern was not determined to be an unsafe condition that would warrant AD action under 14 CFR part 39. However, subsequent investigations were not able to determine whether the limited damaged observed on several oil cooler blower shafts would remain localized or progress to a point where the shaft is no longer safe for continued use. The FAA also later determined that operators may have difficulty aligning the air conditioning system’s drive ring holes with the air conditioning condenser drive pulley without leaving the condenser drive pulley under-torqued. This condition, if not addressed, could result in a failure of the oil cooler blower shaft, which could lead to loss of tail rotor authority and subsequent loss of helicopter control. Accordingly, the FAA is issuing this AD for Bell Textron Canada Limited Model 206L–1 and 206L–3 helicopters with Bell Model 206L1/L3 Service Instruction for Increased Gross Weight Upgrade Kit BHT–206–SI–2052, Revision 1, dated October 14, 2010, installed and Bell Model 206L–4 helicopters equipped with one of the following Air Comm Corporation STC SH2750NM air conditioning systems part number; 206EC–204–1, 206EC– 204–2, 206EC–208–1, 206EC–208–2, 206EC–210–1, 206EC–210–2, 206EC– 210–3, 206EC–212–3 or 206EC–212–4. Helicopters with a 206L–1+ designation are Model 206L–1 helicopters and helicopters with a 206L–3+ designation are Model 206L–3 helicopters. Discussion of Final Airworthiness Directive Comments The FAA received no comments on the NPRM or on the determination of the costs. Conclusion The FAA reviewed the relevant data and determined that air safety requires adopting this AD as proposed except for minor editorial changes. Accordingly, the FAA is issuing this AD to address the unsafe condition on these helicopters. Related Service Information Under 1 CFR Part 51 The FAA reviewed ACC Air Comm Corporation Service Bulletin SB 206EC– 091119, Rev B, dated May 26, 2021 (SB 206EC–091119 Rev B), which specifies procedures for visually inspecting the drive ring spline teeth and the mating spline teeth on the tail rotor drive’s oil cooler blower shaft for deformation or fretting. 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. Differences Between This AD and the Service Bulletin SB 206EC–091119 Rev B requires inspecting the air conditioning compressor drive belt tension and the general condition of the drive belt, drive pulley, and surrounding components, whereas this AD does not. SB 206EC– 091119 Rev B requires reporting any deformation or fretting to Air Comm Corporation Service Department, whereas this AD does not. SB 206EC– 091119 Rev B provides an option to deactivate the air conditioning system if deformation or fretting is found on the drive ring or the oil cooler blower shaft assembly, whereas this AD requires removing these parts from service instead. Costs of Compliance The FAA estimates that this AD affects up to 100 helicopters of U.S. Registry. Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates the following costs to comply with this AD. Removing the tail rotor drive system’s forward short shaft, spline adaptor, and drive ring and visually inspecting the drive ring spline teeth and the mating area spline teeth take about 1 work-hour for an estimated cost of $85 per helicopter and $8,500 for the U.S. fleet per inspection cycle. Replacing the drive ring takes about 3 work-hours and parts cost about $300 for an estimated cost of $555 per replacement. Replacing the oil cooler blower assembly takes about 3 work-hours and parts cost about $2,720 for an estimated cost of $2,975 per replacement. Aligning each bolt hole and re- torqueing the drive pulley take about 0.5 work-hours for an estimated cost of $43 per helicopter. 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 VerDate Sep<11>2014 16:20 Dec 13, 2021 Jkt 256001 PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1 jspears on DSK121TN23PROD with RULES1

70968 Federal Register / Vol. 86, No. 237 / Tuesday, December 14, 2021 / Rules and Regulations 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: 2021–24–15 Bell Textron Canada Limited: Amendment 39–21836; Docket No. FAA–2021–0830; Project Identifier AD– 2020–00257–R. (a) Effective Date This airworthiness directive (AD) is effective January 18, 2022. (b) Affected ADs None. (c) Applicability This AD applies to the Bell Textron Canada Limited helicopters identified in paragraphs (c)(1) and (2) of this AD: (1) Model 206L–1 and Model 206L–3 helicopters, certificated in any category, with Bell Model 206L1/L3 Service Instruction for Increased Gross Weight Upgrade Kit BHT– 206–SI–2052, Revision 1, dated October 14, 2010, installed and that are equipped with one of the following Air Comm Corporation Supplemental Type Certificate (STC) SH2750NM air conditioning systems part number (P/N) 206EC–204–1, 206EC–204–2, 206EC–208–1, 206EC–208–2, 206EC–210–1, 206EC–210–2, 206EC–210–3, 206EC–212–3, or 206EC–212–4; and Note 1 to paragraph (c)(1) of this AD: Helicopters with a 206L–1+ designation are Model 206L–1 helicopters and helicopters with a 206L–3+ designation are Model 206L– 3 helicopters. (2) Model 206 L–4 helicopters, certificated in any category, and that are equipped with one of the following Air Comm Corporation STC SH2750NM air conditioning systems P/ N 206EC–204–1, 206EC–204–2, 206EC–208– 1, 206EC–208–2, 206EC–210–1, 206EC–210– 2, 206EC–210–3, 206EC–212–3, or 206EC– 212–4. (d) Subject Joint Aircraft Service Component (JASC) Code: 6510, Tail Rotor Drive Shaft. (e) Unsafe Condition This AD was prompted by reports of deformation or fretting of the spline teeth on the air conditioning system drive ring and on the oil cooler blower shaft. The FAA is issuing this AD to detect deformation and fretting. The unsafe condition, if not addressed, could result in a failure of the oil cooler blower shaft, which could lead to loss of tail rotor authority and subsequent loss of helicopter control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Within 300 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 300 hours TIS: (1) Gain access to the drive ring spline teeth and the mating area spline teeth on the oil cooler blower shaft by removing the tail rotor drive system’s forward short shaft and spline adaptor, and the air conditioner system’s drive ring. Refer to Figure 1 of ACC Air Comm Corporation Service Bulletin SB 206EC–091119, Rev B, dated May 26, 2021 for a depiction of each component’s location. (2) Visually inspect the drive ring spline teeth and the mating area spline teeth on the oil cooler blower shaft for deformation and fretting. (i) If there is deformation or fretting on the drive ring spline teeth, before further flight, remove the drive ring from service and replace it with an airworthy part. (ii) If there is deformation or fretting on the mating area spline teeth of the oil cooler blower shaft, before further flight, remove the oil cooler blower assembly from service and replace with an airworthy part. (3) Reinstall the drive ring, spline adapter, and the forward short shaft. If the compressor drive pulley was removed, torque the drive pulley to 200–300 in-lbs, increasing torque in this range to align the four threaded holes with the through holes in the drive ring. Do not back-off torque to align the bolt holes. (h) Special Flight Permits Special flight permits are prohibited. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Denver ACO, 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 Denver ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-Denver-Aircraft-Cert@ 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 (1) For more information about this AD, contact Matthew Bryant, Aerospace Engineer, Denver ACO Branch, FAA, 26805 East 68th Avenue, Denver, CO 80249; telephone (303) 342–1092; email 9-Denver-Aircraft-Cert@ faa.gov. (2) Service information identified in this AD, is available at the contact information specified in paragraphs (k)(3) and (4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) ACC Air Comm Corporation Service Bulletin SB 206EC–091119, Rev B, dated May 26, 2021. (ii) [Reserved] (3) For service information identified in this AD, contact Air Comm Corporation, 1575 W 124th Ave. #210, Westminster, CO 80234; telephone: (303) 440–4075; email service@ aircommcorp.com. (4) 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. (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. VerDate Sep<11>2014 16:20 Dec 13, 2021 Jkt 256001 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1 jspears on DSK121TN23PROD with RULES1

70969 Federal Register / Vol. 86, No. 237 / Tuesday, December 14, 2021 / Rules and Regulations Issued on November 19, 2021. Ross Landes, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–27012 Filed 12–13–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–1061; Project Identifier AD–2021–01192–E; Amendment 39–21853; AD 2021–23–51] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY : Federal Aviation Administration (FAA), DOT. ACTION : Final rule; request for comments. SUMMARY : The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34– 8C and CF34–8E model turbofan engines. This AD was prompted by an in-flight shutdown of an engine and subsequent investigation by the manufacturer that revealed a broken variable geometry (VG) actuator rod end caused by corrosion and seizure of the rod end bearing. This AD requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. This AD also requires reporting the results of the inspection to GE. The FAA previously sent an emergency AD to all known U.S. owners and operators of these GE CF34– 8C and CF34–8E model turbofan engines and is now issuing this AD to address the unsafe condition on these products. DATES : This AD is effective December 29, 2021. Emergency AD 2021–23–51, issued on November 4, 2021, which contained the requirements of this amendment, was effective with actual notice. The Director of the Federal Register approved the incorporation by reference of certain publications identified in this AD as of December 29, 2021. The FAA must receive comments on this AD by January 28, 2022. 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 service information identified in this final rule, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513) 552–3272; email: aviation.fleetsupport@ge.com; website: https://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 (817) 222– 5110. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 1061. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–1061; 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 street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT : Scott M. Stevenson, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7132; fax: (781) 238– 7199; email: scott.m.stevenson@faa.gov . SUPPLEMENTARY INFORMATION : Background On November 4, 2021, the FAA issued Emergency AD 2021–23–51 (the emergency AD), which requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. The emergency AD also requires reporting the results of the inspection to GE. The FAA sent the emergency AD to all known U.S. owners and operators of these engines. This action was prompted by an event on August 11, 2021, in which a Bombardier CRJ1000 airplane, powered by GE CF34–8C5 model engines, experienced an in-flight engine shutdown that resulted in a diversion. The manufacturer’s investigation found that these engines were parked outdoors for extended lengths of time within 10 miles (16 km) from a saltwater coastline. These conditions caused corrosion to develop on the compressor VG actuator rod end bearing, which restricted the motion in the bearing leading to an elevated stress in the rod end. Subsequently, the higher stress cracked the rod end which eventually fractured. This condition, if not addressed, could result in failure of one or more engines, loss of engine thrust control, and reduced control of the airplane. FAA’s Determination The FAA is issuing this AD because the agency evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed GE CF34–8C Service Bulletin (SB) 75–0028 R00 and GE CF34–8E SB 75–0023 R00, both dated November 2, 2021. These SBs specify procedures for performing a one- time inspection of the master compressor VG actuator and slave compressor VG actuator, differentiated by engine model, to identify possible rod end corrosion or seizure. These SBs also instruct operators to report the inspection results to GE. 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 . AD Requirements This AD requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. This AD also requires reporting the results of the inspection to GE. Interim Action The FAA considers this AD to be an interim action. The FAA anticipates that further AD action will follow. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq. ) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, VerDate Sep<11>2014 16:20 Dec 13, 2021 Jkt 256001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\14DER1.SGM 14DER1 jspears on DSK121TN23PROD with RULES1