Airworthiness Directives; Airbus Helicopters, 67303-67307 [2021-25703]

Download as PDF Federal Register / Vol. 86, No. 225 / Friday, November 26, 2021 / Rules and Regulations (b) Affected ADs (i) No Reporting Requirement None. (c) Applicability This AD applies to Leonardo S.p.a. Model A119 and AW119 MKII helicopters, certificated in any category, all serial numbers. (d) Subject (j) Alternative Methods of Compliance (AMOCs) Comply with this AD within the compliance times specified, unless already done. (1) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR730-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. (g) Requirements (k) Related Information 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 2021–0096, dated March 31, 2021 (EASA AD 2021–0096). 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., Mail Stop: Room 410, Westbury, NY 11590; telephone (516) 228–7330; email andrea.jimenez@faa.gov. Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft Flight Control. (e) Unsafe Condition This AD was prompted by reports of abnormal play on the collective torque tube on two Model AW119 MKII helicopters. The FAA is issuing this AD to address abnormal play on the collective torque tube, which could result in reduced control of the helicopter, resulting in a forced landing and consequent damage to the helicopter and injury to occupants. (f) Compliance (h) Exceptions to EASA AD 2021–0096 jspears on DSK121TN23PROD with RULES1 Although the service information referenced in EASA AD 2021–0096 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (1) Where EASA AD 2021–0096 refers to flight hours (FH), this AD requires using hours time-in-service (TIS). (2) Where EASA AD 2021–0096 refers to its effective date, this AD requires using the effective date of this AD. (3) Where paragraphs (1) and (2) of EASA AD 2021–0096 specify the compliance times for Group 1 helicopters to inspect the affected part, this AD requires an initial inspection within 50 hours TIS after the effective date of this AD, and thereafter at intervals not to exceed 100 hours TIS. (4) Where paragraph (5) of EASA AD 2021– 0096 specifies, for Group 1 helicopters, replacement of an affected part with a serviceable part ‘‘within 36 months after April 3, 2019 [the effective date of EASA AD 2019–0057],’’ for this AD, that replacement must be done within 24 months after the effective date of this AD. (5) Where the service information referenced in EASA AD 2021–0096 specifies to return a torque tube assembly to the manufacturer, this AD does not include that requirement. (6) Where the service information referenced in EASA AD 2021–0096 specifies to contact the manufacturer ‘‘in case of doubt’’ regarding the batch number on a torque tube assembly, determining the batch number is required by this AD but contacting the manufacturer is not required. (7) This AD does not mandate compliance with the ‘‘Remarks’’ section of EASA AD 2021–0096. VerDate Sep<11>2014 16:31 Nov 24, 2021 Jkt 256001 (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2021–0096, dated March 31, 2021. (ii) [Reserved] (3) For EASA AD 2021–0096, 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. (4) You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N 321, Fort Worth, TX 76177. For information on the availability of the EASA material at the FAA, call (817) 222–5110. (5) 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/ibrlocations.html. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 67303 Issued on October 13, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–25690 Filed 11–24–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0197; Project Identifier 2018–SW–107–AD; Amendment 39–21789; AD 2021–22–16] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was prompted by the failure of a main gearbox (MGB) second stage planet gear. This AD requires replacing the MGB, or as an alternative, replacing the epicyclic reduction gear module for certain serial numbered planet gear assemblies installed on the MGB. This AD also requires inspecting the MGB magnetic plugs and MGB filter for particles, and for certain serial-numbered planet gear assemblies, inspecting the oil sump for particles. Depending on the outcome of these inspections, this AD requires further inspections and replacing certain parts. This AD also prohibits installing certain parts. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 3, 2022. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of January 3, 2022. ADDRESSES: For service information identified in this final rule, 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. 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. Service information SUMMARY: E:\FR\FM\26NOR1.SGM 26NOR1 67304 Federal Register / Vol. 86, No. 225 / Friday, November 26, 2021 / Rules and Regulations that is incorporated by reference is also available at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0197. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0197; 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 European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, 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: Rao Edupuganti, Aerospace Engineer, Dynamic Systems Section, Technical Innovation Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email rao.edupuganti@faa.gov. SUPPLEMENTARY INFORMATION: jspears on DSK121TN23PROD with RULES1 Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Airbus Helicopters Model EC 155B and EC155B1 helicopters. The NPRM published in the Federal Register on July 22, 2021 (86 FR 38608). In the NPRM, the FAA proposed to require for helicopters with at least one Type Y planet gear assembly with a certain serial number (S/N) installed, or at least one Type Z planet gear assembly with a certain S/N installed, within 10 hours time-in-service (TIS) after the effective date of the AD and thereafter at intervals not to exceed 10 hours TIS, inspecting the MGB magnetic plugs for particles. If there are particles, the NPRM proposed to require further inspections and analyses and replacing the MGB, depending on the type and the size of the particles. The NPRM also proposed to require for helicopters with a Type Y planet gear assembly with a certain S/N installed, within 25 hours TIS after the effective date of the AD, inspecting the MGB filter for particles. If there are particles, the NPRM proposed to require further inspections and analyses and replacing the MGB, depending on the type and the size of the particles. The NPRM proposed to require for helicopters with at least one Type Y VerDate Sep<11>2014 16:31 Nov 24, 2021 Jkt 256001 planet gear assembly with a certain S/ N installed, within 50 hours TIS after the effective date of the AD, replacing the MGB. As an alternative to replacing the MGB, the NPRM would allow replacing the epicyclic reduction gear in the affected MGB. Additionally, the NPRM proposed to require, for helicopters without any Type Y planet gear assembly but at least one Type Z planet gear assembly with a certain S/N installed, replacing the MGB within 50 hours TIS after the effective date of the AD or before any planet gear assembly accumulates 1,800 total hours TIS, whichever occurs later. As an alternative to replacing the MGB, the NPRM would allow replacing the epicyclic reduction gear in the affected MGB. The NPRM also proposed to require, for helicopters with at least one Type Z planet gear with a certain S/N installed, within certain compliance times specified in the figures in this AD, inspecting the MGB filter and inspecting the oil sump for particles. If there are particles, the NPRM proposed to require further inspections and analyses, and replacing the MGB, depending on the type and the size of the particles. The NPRM also proposed to prohibit installing an MGB with a certain serial numbered Type Y planet gear assembly and proposed to prohibit installing a Type Y planet gear assembly with a certain S/N on any helicopter. Additionally, the NPRM proposed to prohibit installing certain serial numbered Type Z planet gear assemblies that have accumulated 1,800 or more total hours TIS and prohibit installing an MGB with certain serial numbered Type Z planet gear assemblies that have accumulated 1,800 or more total hours TIS. Finally, the NPRM proposed to prohibit installing an MGB if the type of the planet gear assembly cannot be determined and also prohibit installing any planet gear assembly if the type cannot be determined. The NPRM was prompted by EASA AD 2018–0263, dated December 7, 2018 (EASA AD 2018–0263), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Airbus Helicopters Model EC 155 B and EC 155 B1 helicopters. EASA advises that after an accident on a Model EC225 helicopter, an investigation revealed the failure of an MGB second stage planet gear. EASA states that one of the two types of planet gear used in the MGB epicyclic module is subject to higher outer race contact pressures and therefore is more susceptible to spalling and cracking. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 This condition, if not addressed, could result in failure of a MGB planet gear assembly, failure of the MGB, and subsequent loss of helicopter control. Accordingly, EASA AD 2018–0263 requires repetitive inspections of the MGB magnetic plugs, the MGB filer, and the oil sump for particles, and depending on the results of those inspections, removing or replacing certain parts. EASA AD 2018–0263 also requires reducing the life limit of Type Z planet gear assemblies. EASA AD 2018–0263 also requires, if certain gear assemblies are installed, either replacing the MGB or replacing the epicyclic reduction gear. Finally, EASA AD 2018– 0263 prohibits installing a Type Y planet gear assembly or an MGB with a Type Y planet gear assembly on any helicopter. Discussion of Final Airworthiness Directive Comments The FAA received comments from one commenter. The following presents the comments received on the NPRM and the FAA’s response. Request to Revise the Required Actions Section of the NPRM Airbus Helicopters Inc., requested that the FAA revise the Required Actions section of this AD dealing with the 25 hours TIS inspection for the oil sump (also referred to as inspecting the bottom housing of the MGB) by removing that repetitive inspection and explained that some of the proposed actions are unclear and not in line with the original equipment manufacturer’s (OEM) service information. The commenter also provided an example of a similar AD, AD 2021–12–06, Amendment 39–21593 (86 FR 31612, June 15, 2021) (AD 2021–12–06), stating that AD 2021–12–06 is clear in explaining both the required repetitive actions and the limits provided by the OEM for the MGB oil filter inspection after finding particle(s) on the chip detector. The commenter stated that, as written, the proposed actions would create extra work, which could lead to an unwanted condition exposing the dynamic component to possible contamination and possibly foreign object debris. The FAA agrees that the repetitive 25 hours TIS oil sump inspection for Type Y planet gears is not necessary and has revised paragraph (g)(1) of the Required Actions section in this final rule by deleting this inspection. Conclusion The FAA reviewed the relevant data, considered the comments received, and E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 86, No. 225 / Friday, November 26, 2021 / Rules and Regulations determined that air safety and the public interest require adopting this AD as proposed, except for the change described previously, updating the service information for the optional replacement of the epicyclic reduction gear module in paragraphs (g)(3) and (4) of this AD, and for clarity, deleting the corrective actions when there are no 16NCD13 particles. The FAA has determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. assembly that has accumulated 1,800 or more total hours TIS installed, EASA AD 2018–0263 requires replacing the MGB or epicyclic reduction gear within 600 flight hours after March 16, 2018, whereas this AD requires either of those replacements within 50 hours TIS after the effective date of this AD instead. If 16NCD13 particles are present, EASA AD 2018–0263 requires taking a 1 liter sample of oil and returning it to Airbus Helicopters and removing the MGB for depot-level inspection, whereas this AD requires replacing the MGB instead. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB No. EC155– 05A034, Revision 5, dated December 4, 2018 (ASB EC155–05A34 Rev 5) for Model EC 155 helicopters, which specifies periodic inspections of the MGB magnetic plugs, the MGB filter, and the oil sump for particles. ASB EC155–05A34 Rev 5 also specifies identifying the type of gear assembly installed in the MGB and replacing any Type Y planet gear assembly within 50 hours TIS. For Type Z gear assemblies that have logged less than 1,800 hours TIS since new, this service information specifies replacing the gear assembly before exceeding 1,800 total hours TIS, and for Type Z gear assemblies that have logged 1,800 or more total hours TIS, replacing the gear assembly within 600 hours TIS. The FAA also reviewed Airbus Helicopters Service Bulletin SB No. EC155–63–016, Revision 5, dated March 6, 2019, for Model EC 155 helicopters. This service information specifies procedures for replacing the MGB epicyclic reduction gear without removing the MGB. 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. Costs of Compliance The FAA estimates that this AD affects 14 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. Inspecting the magnetic plugs for particle deposits takes about 1 workhour for an estimated cost of $85 per helicopter per inspection cycle. Inspecting the MGB filter or oil sump for particle deposits takes about 1 workhour for an estimated cost of $85 per helicopter per inspection cycle. Replacing an MGB takes about 42 work-hours, and parts cost about $295,000 (overhauled) for an estimated total cost of $298,570 per helicopter. Replacing the epicyclic reduction gear takes about 56 work-hours and parts cost about $11,404 for an estimated total cost of $16,164 per helicopter. jspears on DSK121TN23PROD with RULES1 Interim Action The FAA considers this AD to be an interim action. If final action is later identified, the FAA might consider further rulemaking then. Differences Between This AD and EASA AD 2018–0263 EASA AD 2018–0263 specifies compliance times based on flight hours and calendar dates. This AD sets compliance times based on hours TIS or before further flight. EASA AD 2018– 0263 allows a pilot to inspect the MGB magnetic plugs for particles, while this AD does not. For helicopters with at least one affected Type Z planet gear VerDate Sep<11>2014 16:31 Nov 24, 2021 Jkt 256001 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 helicopters 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 67305 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: ■ 2021–22–16 Airbus Helicopters: Amendment 39–21789; Docket No. FAA–2021–0197; Project Identifier 2018–SW–107–AD. (a) Effective Date This airworthiness directive (AD) is effective January 3, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Helicopters Model EC 155B and EC155B1 helicopters, certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor Drive System. (e) Unsafe Condition This AD was prompted by the failure of a main gearbox (MGB) second stage planet gear. The FAA is issuing this AD to prevent failure of an MGB planet gear assembly. The unsafe condition, if not addressed, could result in failure of the MGB and subsequent loss of helicopter control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\26NOR1.SGM 26NOR1 67306 Federal Register / Vol. 86, No. 225 / Friday, November 26, 2021 / Rules and Regulations (g) Required Actions (1) For helicopters with at least one Type Y planet gear assembly with a serial number (S/N) listed in Appendix 4.A. of Airbus Helicopters Alert Service Bulletin ASB No. EC155–05A034, Revision 5, dated December 4, 2018 (ASB EC155–05A034 Rev 5) or with at least one Type Z planet gear assembly with an S/N listed in Appendix 4.B. of ASB EC155–05A034 Rev 5 installed, within 10 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 10 hours TIS, inspect the MGB magnetic plugs for particles. If there are any particles that consist of any scale, flake, splinter, or other particle other than cotter pin fragments, pieces of lock wire, swarf, abrasion, or miscellaneous non-metallic waste, and any of the planet gears have accumulated less than 50 total hours TIS, before further flight, inspect the MGB filter for particles. Thereafter, for 25 hours TIS, continue to inspect the MGB plugs for particles before each flight, inspect the MGB filter for particles at intervals not to exceed 25 hours TIS, and inspect the cumulative surface area of the particles collected from the magnetic plugs, the MGB filter, since last MGB overhaul, or since new if no overhaul has been performed. Note 1 to the introductory text of paragraph (g)(1): Airbus Helicopters service information refers to an MGB filter as an oil filter. (i) If the total surface area of the particles is less than 3 mm2, examine the particles with the largest surface area (S), greatest length (L), and greatest thickness (e). (A) If any (S) of all of the particles is less than or equal to 1 mm2, the (L) is less than or equal to 1.5 mm, and the (e) is less than or equal to 0.2 mm, inspect the MGB plugs for particles before further flight, and inspect the MGB filter for particles within 25 hours TIS. Thereafter: (1) For 25 hours TIS, continue to inspect the MGB plugs for particles before each flight and perform the actions required by paragraphs (g)(1)(i) and (ii) of this AD. (2) Inspect the MGB filter for particles at intervals not to exceed 25 hours TIS and perform the actions required by paragraphs (g)(1)(i) and (ii) of this AD. (B) If any (S) is greater than 1 mm2, (L) is greater than 1.5 mm, or (e) is greater than 0.2 mm, perform a metallurgical analysis for any 16NCD13 particles, using a method in accordance with FAA-approved procedures. (C) If there are any 16NCD13 particles, before further flight, replace the MGB with an airworthy MGB. (ii) If the total surface area of collected particles is greater than or equal to 3 mm2, before further flight, perform a metallurgical analysis for any 16NCD13 particles using a method in accordance with FAA-approved procedures. If there are any 16NCD13 particles, before further flight, replace the MGB with an airworthy MGB. (2) For helicopters with at least one Type Y planet gear assembly with an S/N listed in Appendix 4.A. of ASB EC155–05A034 Rev 5 installed, within 25 hours TIS after the effective date of this AD, inspect the MGB filter for particles. If there are any particles that consist of any scale, flake, splinter, or particle other than cotter pin fragments, pieces of lock wire, swarf, abrasion, or miscellaneous non-metallic waste, and any of the planet gears have accumulated more than 50 total hours TIS, before further flight, perform the actions required by paragraphs (g)(1)(i) and (ii) of this AD. (3) For helicopters with at least one Type Y planet gear assembly with an S/N listed in Appendix 4.A. of ASB EC155–05A034 Rev 5 installed, within 50 hours TIS after the effective date of this AD, replace the MGB or as an alternative to replacing an affected MGB, replace the epicyclic reduction gear module in the affected MGB in accordance with paragraph 3.B.2. of the Accomplishment Instructions of Airbus Helicopters Service Bulletin SB No. EC155–63–016, Revision 5, dated March 6, 2019 (SB EC155–63–016 Rev 5), except you are not required to contact Airbus Helicopters. (4) For helicopters without any Type Y planet gear assembly installed but with at least one Type Z planet gear assembly with an S/N listed in Appendix 4.B. of ASB EC155–05A034 Rev 5 installed, within 50 hours TIS after the effective date of this AD, or before any gear accumulates 1,800 total hours TIS, whichever occurs later, replace the MGB or as an alternative to replacing an affected MGB, replace the epicyclic reduction gear module in the affected MGB in accordance with paragraph 3.B.2. of the Accomplishment Instructions of SB EC155– 63–016 Rev 5, except you are not required to contact Airbus Helicopters. (5) For helicopters with at least one Type Z planet gear assembly with an S/N listed in Appendix 4.B. of ASB EC155– 05A034 Rev 5 installed, inspect the MGB filter for particles within the compliance times specified in Figure 1 to paragraph (g)(5) of this AD and inspect the oil sump for particles within the compliance times specified in Figure 2 to paragraph (g)(5) of this AD, based on the total hours TIS accumulated by the Type Z planet gear with the most total hours TIS accumulated since first installation in an MGB. If there are particles, before further flight, perform the actions required by paragraphs (g)(1)(i) and (ii) of this AD. FIGURE 1 TO PARAGRAPH (g)(5) Total hours TIS accumulated Compliance time for initial inspection Less than 400 total hours TIS ........................... Within 55 hours TIS after the effective date of this AD. Within 25 hours TIS after the effective date of this AD. 400 or more total hours TIS .............................. Compliance time for repetitive inspections Within 55 hours TIS. Within 25 hours TIS. FIGURE 2 TO PARAGRAPH (g)(5) Total hours TIS accumulated Compliance time for initial inspection Less than 400 total hours TIS ........................... Before exceeding 400 hours TIS after the effective date of this AD. Within 55 hours TIS after the effective date of this AD. Within 55 hours TIS. (7) As of the effective date of this AD, do not install a Type Z planet gear assembly with an S/N listed in Appendix 4.B. of ASB EC155–05A034 Rev 5 that has accumulated 1,800 or more total hours TIS on any helicopter, and do not install an MGB with at least one Type Z planet gear assembly with an S/N listed in Appendix 4.B. of ASB EC155–05A034 Rev 5 that has accumulated 1,800 or more total hours TIS on any helicopter. (8) As of the effective date of this AD, do not install any planet gear on any helicopter if the planet gear assembly type cannot be determined, and do not install any MGB on any helicopter if any of the planet gear assembly types cannot be determined. jspears on DSK121TN23PROD with RULES1 400 or more total hours TIS .............................. (6) As of the effective date of this AD, do not install a type Y planet gear assembly with an S/N listed in Appendix 4.A. of ASB EC155–05A034 Rev 5 on any helicopter, and do not install an MGB with a Type Y planet gear assembly with an S/N listed in Appendix 4.A. of ASB EC155–05A034 Rev 5 on any helicopter. VerDate Sep<11>2014 16:31 Nov 24, 2021 Jkt 256001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Compliance time for repetitive inspections Within 55 hours TIS. E:\FR\FM\26NOR1.SGM 26NOR1 Federal Register / Vol. 86, No. 225 / Friday, November 26, 2021 / Rules and Regulations (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-AIR730-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 Rao Edupuganti, Aerospace Engineer, Dynamic Systems Section, Technical Innovation Policy Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email rao.edupuganti@faa.gov. (2) The subject of this AD is addressed in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2018–0263, dated December 7, 2018. You may view the EASA AD at https:// www.regulations.gov in Docket No. FAA– 2021–0197. jspears on DSK121TN23PROD with RULES1 (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 No. EC155–05A034, Revision 5, dated December 4, 2018. (ii) Airbus Helicopters Service Bulletin SB No. EC155–63–016, Revision 5, dated March 6, 2019. (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. VerDate Sep<11>2014 16:31 Nov 24, 2021 Jkt 256001 Issued on October 19, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–25703 Filed 11–24–21; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0714; Project Identifier 2019–CE–016–AD; Amendment 39–21794; AD 2021–22–21] RIN 2120–AA64 Airworthiness Directives; ASI Aviation (Type Certificate Previously Held by Reims Aviation S.A.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all ASI Aviation (type certificate previously held by Reims Aviation S.A.) Model F406 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as failure of a circuit breaker (CB) switch. This AD requires replacing certain CB switches and establishing a life limit for the CB switches. The FAA is issuing this AD to address the unsafe condition on these products. This AD is effective January 3, 2022. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 3, 2022. ADDRESSES: For service information identified in this final rule, contact ASI Aviation, Ae´rodrome de Reims Prunay, 51360 Prunay, France; telephone: +33 3 26 48 46 84; fax: +33 3 26 49 18 57; email: contact@asi-aviation.fr; website: https://asi-aviation.fr/pageAccueil.html. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0714. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0714; 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 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: Gregory Johnson, Aviation Safety Engineer, International Validation Section, FAA, 901 Locust, Room 301, Kansas City, MO 64106–2641; phone: (720) 626–5462; email: gregory.johnson@faa.gov. SUPPLEMENTARY INFORMATION: Background SUMMARY: DATES: 67307 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all ASI Aviation (type certificate previously held by Reims Aviation S.A.) Model F406 airplanes. The NPRM published in the Federal Register on August 27, 2021 (86 FR 48067). The NPRM was prompted by MCAI originated by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued AD 2019–0015, dated January 29, 2019 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition on ASI Aviation (type certificate previously held by Reims Aviation S.A.) Model F406 airplanes. The MCAI states: After the Federal Aviation Administration issued AD 2005–20–25 [70 FR 59237, October 12, 2005], applicable to Cessna 400 series aeroplanes equipped with certain avionics bus CB switches, it was determined that, due to design commonality, one of the affected avionics bus CB switches, P/N [part number] CM3589–50, was also installed on Reims F 406 aeroplanes. This condition, if not corrected, could lead to smoke and/or burning smell in the cockpit, possibly resulting in reduced control of the aeroplane. To address that potential unsafe condition, RAI issued SB [service bulletin] F406–62 to provide instructions to remove certain switches from service. Consequently, EASA issued AD 2006–0134 to require identification of the date code of P/N CM3589–50 CB switches and, depending on findings, replacement with improved design CB switches, P/N 4061–2400–1. That [EASA] AD also imposed a life limit on the affected CB switches P/N CM3589–50. E:\FR\FM\26NOR1.SGM 26NOR1

Agencies

[Federal Register Volume 86, Number 225 (Friday, November 26, 2021)]
[Rules and Regulations]
[Pages 67303-67307]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-25703]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0197; Project Identifier 2018-SW-107-AD; Amendment 
39-21789; AD 2021-22-16]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was 
prompted by the failure of a main gearbox (MGB) second stage planet 
gear. This AD requires replacing the MGB, or as an alternative, 
replacing the epicyclic reduction gear module for certain serial 
numbered planet gear assemblies installed on the MGB. This AD also 
requires inspecting the MGB magnetic plugs and MGB filter for 
particles, and for certain serial-numbered planet gear assemblies, 
inspecting the oil sump for particles. Depending on the outcome of 
these inspections, this AD requires further inspections and replacing 
certain parts. This AD also prohibits installing certain parts. The FAA 
is issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective January 3, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of January 3, 2022.

ADDRESSES: For service information identified in this final rule, 
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. 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. Service 
information

[[Page 67304]]

that is incorporated by reference is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0197.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0197; 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 
European Aviation Safety Agency (now European Union Aviation Safety 
Agency) (EASA) AD, 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: Rao Edupuganti, Aerospace Engineer, 
Dynamic Systems Section, Technical Innovation Policy Branch, Policy & 
Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone (817) 222-5110; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model EC 155B and EC155B1 helicopters. The NPRM published in the 
Federal Register on July 22, 2021 (86 FR 38608). In the NPRM, the FAA 
proposed to require for helicopters with at least one Type Y planet 
gear assembly with a certain serial number (S/N) installed, or at least 
one Type Z planet gear assembly with a certain S/N installed, within 10 
hours time-in-service (TIS) after the effective date of the AD and 
thereafter at intervals not to exceed 10 hours TIS, inspecting the MGB 
magnetic plugs for particles. If there are particles, the NPRM proposed 
to require further inspections and analyses and replacing the MGB, 
depending on the type and the size of the particles.
    The NPRM also proposed to require for helicopters with a Type Y 
planet gear assembly with a certain S/N installed, within 25 hours TIS 
after the effective date of the AD, inspecting the MGB filter for 
particles. If there are particles, the NPRM proposed to require further 
inspections and analyses and replacing the MGB, depending on the type 
and the size of the particles. The NPRM proposed to require for 
helicopters with at least one Type Y planet gear assembly with a 
certain S/N installed, within 50 hours TIS after the effective date of 
the AD, replacing the MGB. As an alternative to replacing the MGB, the 
NPRM would allow replacing the epicyclic reduction gear in the affected 
MGB.
    Additionally, the NPRM proposed to require, for helicopters without 
any Type Y planet gear assembly but at least one Type Z planet gear 
assembly with a certain S/N installed, replacing the MGB within 50 
hours TIS after the effective date of the AD or before any planet gear 
assembly accumulates 1,800 total hours TIS, whichever occurs later. As 
an alternative to replacing the MGB, the NPRM would allow replacing the 
epicyclic reduction gear in the affected MGB.
    The NPRM also proposed to require, for helicopters with at least 
one Type Z planet gear with a certain S/N installed, within certain 
compliance times specified in the figures in this AD, inspecting the 
MGB filter and inspecting the oil sump for particles. If there are 
particles, the NPRM proposed to require further inspections and 
analyses, and replacing the MGB, depending on the type and the size of 
the particles.
    The NPRM also proposed to prohibit installing an MGB with a certain 
serial numbered Type Y planet gear assembly and proposed to prohibit 
installing a Type Y planet gear assembly with a certain S/N on any 
helicopter.
    Additionally, the NPRM proposed to prohibit installing certain 
serial numbered Type Z planet gear assemblies that have accumulated 
1,800 or more total hours TIS and prohibit installing an MGB with 
certain serial numbered Type Z planet gear assemblies that have 
accumulated 1,800 or more total hours TIS.
    Finally, the NPRM proposed to prohibit installing an MGB if the 
type of the planet gear assembly cannot be determined and also prohibit 
installing any planet gear assembly if the type cannot be determined.
    The NPRM was prompted by EASA AD 2018-0263, dated December 7, 2018 
(EASA AD 2018-0263), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, to correct an unsafe condition 
for Airbus Helicopters Model EC 155 B and EC 155 B1 helicopters. EASA 
advises that after an accident on a Model EC225 helicopter, an 
investigation revealed the failure of an MGB second stage planet gear. 
EASA states that one of the two types of planet gear used in the MGB 
epicyclic module is subject to higher outer race contact pressures and 
therefore is more susceptible to spalling and cracking. This condition, 
if not addressed, could result in failure of a MGB planet gear 
assembly, failure of the MGB, and subsequent loss of helicopter 
control.
    Accordingly, EASA AD 2018-0263 requires repetitive inspections of 
the MGB magnetic plugs, the MGB filer, and the oil sump for particles, 
and depending on the results of those inspections, removing or 
replacing certain parts. EASA AD 2018-0263 also requires reducing the 
life limit of Type Z planet gear assemblies. EASA AD 2018-0263 also 
requires, if certain gear assemblies are installed, either replacing 
the MGB or replacing the epicyclic reduction gear. Finally, EASA AD 
2018-0263 prohibits installing a Type Y planet gear assembly or an MGB 
with a Type Y planet gear assembly on any helicopter.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter. The following 
presents the comments received on the NPRM and the FAA's response.

Request to Revise the Required Actions Section of the NPRM

    Airbus Helicopters Inc., requested that the FAA revise the Required 
Actions section of this AD dealing with the 25 hours TIS inspection for 
the oil sump (also referred to as inspecting the bottom housing of the 
MGB) by removing that repetitive inspection and explained that some of 
the proposed actions are unclear and not in line with the original 
equipment manufacturer's (OEM) service information. The commenter also 
provided an example of a similar AD, AD 2021-12-06, Amendment 39-21593 
(86 FR 31612, June 15, 2021) (AD 2021-12-06), stating that AD 2021-12-
06 is clear in explaining both the required repetitive actions and the 
limits provided by the OEM for the MGB oil filter inspection after 
finding particle(s) on the chip detector. The commenter stated that, as 
written, the proposed actions would create extra work, which could lead 
to an unwanted condition exposing the dynamic component to possible 
contamination and possibly foreign object debris.
    The FAA agrees that the repetitive 25 hours TIS oil sump inspection 
for Type Y planet gears is not necessary and has revised paragraph 
(g)(1) of the Required Actions section in this final rule by deleting 
this inspection.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and

[[Page 67305]]

determined that air safety and the public interest require adopting 
this AD as proposed, except for the change described previously, 
updating the service information for the optional replacement of the 
epicyclic reduction gear module in paragraphs (g)(3) and (4) of this 
AD, and for clarity, deleting the corrective actions when there are no 
16NCD13 particles. The FAA has determined that these changes will not 
increase the economic burden on any operator or increase the scope of 
this final rule.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB No. 
EC155-05A034, Revision 5, dated December 4, 2018 (ASB EC155-05A34 Rev 
5) for Model EC 155 helicopters, which specifies periodic inspections 
of the MGB magnetic plugs, the MGB filter, and the oil sump for 
particles. ASB EC155-05A34 Rev 5 also specifies identifying the type of 
gear assembly installed in the MGB and replacing any Type Y planet gear 
assembly within 50 hours TIS. For Type Z gear assemblies that have 
logged less than 1,800 hours TIS since new, this service information 
specifies replacing the gear assembly before exceeding 1,800 total 
hours TIS, and for Type Z gear assemblies that have logged 1,800 or 
more total hours TIS, replacing the gear assembly within 600 hours TIS.
    The FAA also reviewed Airbus Helicopters Service Bulletin SB No. 
EC155-63-016, Revision 5, dated March 6, 2019, for Model EC 155 
helicopters. This service information specifies procedures for 
replacing the MGB epicyclic reduction gear without removing the MGB.
    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.

Interim Action

    The FAA considers this AD to be an interim action. If final action 
is later identified, the FAA might consider further rulemaking then.

Differences Between This AD and EASA AD 2018-0263

    EASA AD 2018-0263 specifies compliance times based on flight hours 
and calendar dates. This AD sets compliance times based on hours TIS or 
before further flight. EASA AD 2018-0263 allows a pilot to inspect the 
MGB magnetic plugs for particles, while this AD does not. For 
helicopters with at least one affected Type Z planet gear assembly that 
has accumulated 1,800 or more total hours TIS installed, EASA AD 2018-
0263 requires replacing the MGB or epicyclic reduction gear within 600 
flight hours after March 16, 2018, whereas this AD requires either of 
those replacements within 50 hours TIS after the effective date of this 
AD instead. If 16NCD13 particles are present, EASA AD 2018-0263 
requires taking a 1 liter sample of oil and returning it to Airbus 
Helicopters and removing the MGB for depot-level inspection, whereas 
this AD requires replacing the MGB instead.

Costs of Compliance

    The FAA estimates that this AD affects 14 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.
    Inspecting the magnetic plugs for particle deposits takes about 1 
work-hour for an estimated cost of $85 per helicopter per inspection 
cycle.
    Inspecting the MGB filter or oil sump for particle deposits takes 
about 1 work-hour for an estimated cost of $85 per helicopter per 
inspection cycle.
    Replacing an MGB takes about 42 work-hours, and parts cost about 
$295,000 (overhauled) for an estimated total cost of $298,570 per 
helicopter.
    Replacing the epicyclic reduction gear takes about 56 work-hours 
and parts cost about $11,404 for an estimated total cost of $16,164 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 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 helicopters identified in this rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2021-22-16 Airbus Helicopters: Amendment 39-21789; Docket No. FAA-
2021-0197; Project Identifier 2018-SW-107-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 3, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model EC 155B and EC155B1 
helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6300, Main Rotor 
Drive System.

(e) Unsafe Condition

    This AD was prompted by the failure of a main gearbox (MGB) 
second stage planet gear. The FAA is issuing this AD to prevent 
failure of an MGB planet gear assembly. The unsafe condition, if not 
addressed, could result in failure of the MGB and subsequent loss of 
helicopter control.

(f) Compliance

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

[[Page 67306]]

(g) Required Actions

    (1) For helicopters with at least one Type Y planet gear 
assembly with a serial number (S/N) listed in Appendix 4.A. of 
Airbus Helicopters Alert Service Bulletin ASB No. EC155-05A034, 
Revision 5, dated December 4, 2018 (ASB EC155-05A034 Rev 5) or with 
at least one Type Z planet gear assembly with an S/N listed in 
Appendix 4.B. of ASB EC155-05A034 Rev 5 installed, within 10 hours 
time-in-service (TIS) after the effective date of this AD, and 
thereafter at intervals not to exceed 10 hours TIS, inspect the MGB 
magnetic plugs for particles. If there are any particles that 
consist of any scale, flake, splinter, or other particle other than 
cotter pin fragments, pieces of lock wire, swarf, abrasion, or 
miscellaneous non-metallic waste, and any of the planet gears have 
accumulated less than 50 total hours TIS, before further flight, 
inspect the MGB filter for particles. Thereafter, for 25 hours TIS, 
continue to inspect the MGB plugs for particles before each flight, 
inspect the MGB filter for particles at intervals not to exceed 25 
hours TIS, and inspect the cumulative surface area of the particles 
collected from the magnetic plugs, the MGB filter, since last MGB 
overhaul, or since new if no overhaul has been performed.
    Note 1 to the introductory text of paragraph (g)(1): Airbus 
Helicopters service information refers to an MGB filter as an oil 
filter.
    (i) If the total surface area of the particles is less than 3 
mm\2\, examine the particles with the largest surface area (S), 
greatest length (L), and greatest thickness (e).
    (A) If any (S) of all of the particles is less than or equal to 
1 mm\2\, the (L) is less than or equal to 1.5 mm, and the (e) is 
less than or equal to 0.2 mm, inspect the MGB plugs for particles 
before further flight, and inspect the MGB filter for particles 
within 25 hours TIS. Thereafter:
    (1) For 25 hours TIS, continue to inspect the MGB plugs for 
particles before each flight and perform the actions required by 
paragraphs (g)(1)(i) and (ii) of this AD.
    (2) Inspect the MGB filter for particles at intervals not to 
exceed 25 hours TIS and perform the actions required by paragraphs 
(g)(1)(i) and (ii) of this AD.
    (B) If any (S) is greater than 1 mm\2\, (L) is greater than 1.5 
mm, or (e) is greater than 0.2 mm, perform a metallurgical analysis 
for any 16NCD13 particles, using a method in accordance with FAA-
approved procedures.
    (C) If there are any 16NCD13 particles, before further flight, 
replace the MGB with an airworthy MGB.
    (ii) If the total surface area of collected particles is greater 
than or equal to 3 mm\2\, before further flight, perform a 
metallurgical analysis for any 16NCD13 particles using a method in 
accordance with FAA-approved procedures. If there are any 16NCD13 
particles, before further flight, replace the MGB with an airworthy 
MGB.
    (2) For helicopters with at least one Type Y planet gear 
assembly with an S/N listed in Appendix 4.A. of ASB EC155-05A034 Rev 
5 installed, within 25 hours TIS after the effective date of this 
AD, inspect the MGB filter for particles. If there are any particles 
that consist of any scale, flake, splinter, or particle other than 
cotter pin fragments, pieces of lock wire, swarf, abrasion, or 
miscellaneous non-metallic waste, and any of the planet gears have 
accumulated more than 50 total hours TIS, before further flight, 
perform the actions required by paragraphs (g)(1)(i) and (ii) of 
this AD.
    (3) For helicopters with at least one Type Y planet gear 
assembly with an S/N listed in Appendix 4.A. of ASB EC155-05A034 Rev 
5 installed, within 50 hours TIS after the effective date of this 
AD, replace the MGB or as an alternative to replacing an affected 
MGB, replace the epicyclic reduction gear module in the affected MGB 
in accordance with paragraph 3.B.2. of the Accomplishment 
Instructions of Airbus Helicopters Service Bulletin SB No. EC155-63-
016, Revision 5, dated March 6, 2019 (SB EC155-63-016 Rev 5), except 
you are not required to contact Airbus Helicopters.
    (4) For helicopters without any Type Y planet gear assembly 
installed but with at least one Type Z planet gear assembly with an 
S/N listed in Appendix 4.B. of ASB EC155-05A034 Rev 5 installed, 
within 50 hours TIS after the effective date of this AD, or before 
any gear accumulates 1,800 total hours TIS, whichever occurs later, 
replace the MGB or as an alternative to replacing an affected MGB, 
replace the epicyclic reduction gear module in the affected MGB in 
accordance with paragraph 3.B.2. of the Accomplishment Instructions 
of SB EC155-63-016 Rev 5, except you are not required to contact 
Airbus Helicopters.
    (5) For helicopters with at least one Type Z planet gear 
assembly with an S/N listed in Appendix 4.B. of ASB EC155-05A034 Rev 
5 installed, inspect the MGB filter for particles within the 
compliance times specified in Figure 1 to paragraph (g)(5) of this 
AD and inspect the oil sump for particles within the compliance 
times specified in Figure 2 to paragraph (g)(5) of this AD, based on 
the total hours TIS accumulated by the Type Z planet gear with the 
most total hours TIS accumulated since first installation in an MGB. 
If there are particles, before further flight, perform the actions 
required by paragraphs (g)(1)(i) and (ii) of this AD.

                      Figure 1 to Paragraph (g)(5)
------------------------------------------------------------------------
                                    Compliance time     Compliance time
   Total hours TIS accumulated       for  initial       for repetitive
                                      inspection          inspections
------------------------------------------------------------------------
Less than 400 total hours TIS...  Within 55 hours     Within 55 hours
                                   TIS after the       TIS.
                                   effective date of
                                   this AD.
400 or more total hours TIS.....  Within 25 hours     Within 25 hours
                                   TIS after the       TIS.
                                   effective date of
                                   this AD.
------------------------------------------------------------------------


                      Figure 2 to Paragraph (g)(5)
------------------------------------------------------------------------
                                    Compliance time     Compliance time
   Total hours TIS accumulated       for  initial       for repetitive
                                      inspection          inspections
------------------------------------------------------------------------
Less than 400 total hours TIS...  Before exceeding    Within 55 hours
                                   400 hours TIS       TIS.
                                   after the
                                   effective date of
                                   this AD.
400 or more total hours TIS.....  Within 55 hours     Within 55 hours
                                   TIS after the       TIS.
                                   effective date of
                                   this AD.
------------------------------------------------------------------------

    (6) As of the effective date of this AD, do not install a type Y 
planet gear assembly with an S/N listed in Appendix 4.A. of ASB 
EC155-05A034 Rev 5 on any helicopter, and do not install an MGB with 
a Type Y planet gear assembly with an S/N listed in Appendix 4.A. of 
ASB EC155-05A034 Rev 5 on any helicopter.
    (7) As of the effective date of this AD, do not install a Type Z 
planet gear assembly with an S/N listed in Appendix 4.B. of ASB 
EC155-05A034 Rev 5 that has accumulated 1,800 or more total hours 
TIS on any helicopter, and do not install an MGB with at least one 
Type Z planet gear assembly with an S/N listed in Appendix 4.B. of 
ASB EC155-05A034 Rev 5 that has accumulated 1,800 or more total 
hours TIS on any helicopter.
    (8) As of the effective date of this AD, do not install any 
planet gear on any helicopter if the planet gear assembly type 
cannot be determined, and do not install any MGB on any helicopter 
if any of the planet gear assembly types cannot be determined.

[[Page 67307]]

(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: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    (1) For more information about this AD, contact Rao Edupuganti, 
Aerospace Engineer, Dynamic Systems Section, Technical Innovation 
Policy Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone (817) 222-5110; email [email protected].
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2018-0263, dated December 7, 2018. You may view the EASA AD at 
https://www.regulations.gov in Docket No. FAA-2021-0197.

(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 No. EC155-
05A034, Revision 5, dated December 4, 2018.
    (ii) Airbus Helicopters Service Bulletin SB No. EC155-63-016, 
Revision 5, dated March 6, 2019.
    (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-25703 Filed 11-24-21; 8:45 am]
BILLING CODE 4910-13-P