Airworthiness Directives; Airbus Helicopters, 3330-3334 [2023-00886]

Download as PDF khammond on DSKJM1Z7X2PROD with PROPOSALS 3330 Federal Register / Vol. 88, No. 12 / Thursday, January 19, 2023 / Proposed Rules ensure that the animals are accompanied by an interstate certificate of veterinary inspection (ICVI) or other document required by this part for the interstate movement of animals. (b) Forwarding of documents. (1) The APHIS representative, State or Tribal representative, or accredited veterinarian issuing an ICVI or other document required for the interstate movement of animals under this part must forward a copy of the ICVI or other document to the State or Tribal animal health official of the State or Tribe of origin within 7 calendar days from the date on which the ICVI or other document is issued. The State or Tribal animal health official in the State or Tribe of origin must forward a copy of the ICVI or other document to the State or Tribal animal health official the State or Tribe of destination within 7 calendar days from date on which the ICVI or other document is received. (2) The animal health official or accredited veterinarian issuing or receiving an ICVI or other interstate movement document in accordance with paragraph (b)(1) of this section must keep a copy of the ICVI or alternate documentation. For poultry and swine, such documents must be kept for at least 2 years, and for cattle and bison, sheep and goats, cervids, and equine species, 5 years. (c) Cattle and bison. Cattle and bison moved interstate must be accompanied by an ICVI unless: (1) They are moved directly to a recognized slaughtering establishment, or directly to an approved livestock facility and then directly to a recognized slaughtering establishment, and they are accompanied by an owner-shipper statement. (2) They are moved directly to an approved livestock facility with an owner-shipper statement and do not move interstate from the facility unless accompanied by an ICVI. (3) They are moved from the farm of origin for veterinary medical examination or treatment and returned to the farm of origin without change in ownership. (4) They are moved directly from one State through another State and back to the original State. (5) They are moved as a commuter herd with a copy of the commuter herd agreement or other document as agreed to by the States or Tribes involved in the movement. (6) Additionally, cattle and bison may be moved between shipping and receiving States or Tribes with documentation other than an ICVI, e.g., a brand inspection certificate, as agreed VerDate Sep<11>2014 17:06 Jan 18, 2023 Jkt 259001 upon by animal health officials in the shipping and receiving States or Tribes. (7) The official identification number of cattle or bison must be recorded on the ICVI or alternate documentation unless: (i) The cattle or bison are moved from an approved livestock facility directly to a recognized slaughtering establishment; or (ii) The cattle and bison are sexually intact cattle or bison under 18 months of age or steers or spayed heifers; Except that: This exception does not apply to dairy cattle of any age or to cattle or bison used for rodeo, exhibition, or recreational purposes. (d) Horses and other equine species. Horses and other equine species moved interstate must be accompanied by an ICVI unless: (1) They are used as the mode of transportation (horseback, horse and buggy) for travel to another location and then return direct to the original location; or (2) They are moved from the farm or stable for veterinary medical examination or treatment and returned to the same location without change in ownership; or (3) They are moved directly from a location in one State through another State to a second location in the original State. (4) Additionally, equids may be moved between shipping and receiving States or Tribes with documentation other than an ICVI, e.g., an equine infectious anemia test chart, as agreed to by the shipping and receiving States or Tribes involved in the movement. (5) Equids moving commercially to slaughter must be accompanied by documentation in accordance with part 88 of this subchapter. Equine infectious anemia reactors moving interstate must be accompanied by documentation as required by part 75 of this subchapter. (e) Poultry. Poultry moved interstate must be accompanied by an ICVI unless: (1) They are from a flock participating in the National Poultry Improvement Plan (NPIP) and are accompanied by the documentation required under the NPIP regulations (parts 145 through 147 of this chapter) for participation in that program; or (2) They are moved directly to a recognized slaughtering or rendering establishment; or (3) They are moved from the farm of origin for veterinary medical examination, treatment, or diagnostic purposes and either returned to the farm of origin without change in ownership or euthanized and disposed of at the veterinary facility; or PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (4) They are moved directly from one State through another State and back to the original State; or (5) They are moved between shipping and receiving States or Tribes with a VS Form 9–3 or documentation other than an ICVI, as agreed upon by animal health officials in the shipping and receiving States or Tribes; or (6) They are moved under permit in accordance with part 82 of this subchapter. (f) Sheep and goats. Sheep and goats moved interstate must be accompanied by documentation as required by part 79 of this subchapter. (g) Swine. Swine moved interstate must be accompanied by documentation in accordance with § 71.19 of this subchapter or, if applicable, with part 85 of this subchapter. (h) Captive cervids. Captive cervids moved interstate must be accompanied by documentation as required by part 77 of this subchapter. Done in Washington, DC, this 5th day of January 2023. Jennifer Moffitt, Under Secretary for Marketing and Regulatory Programs. [FR Doc. 2023–00505 Filed 1–18–23; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–0016; Project Identifier MCAI–2022–00416–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters. This proposed AD was prompted by a report of corrosion detected on certain part-numbered landing gear assemblies. This proposed AD would require, for helicopters with certain part-numbered landing gear assemblies installed, visually inspecting for cracks and corrosion; borescope inspecting; and if required, removing corrosion, measuring thickness, interpreting results of the measurements, applying chemical conversion coating and primer, and removing affected parts SUMMARY: E:\FR\FM\19JAP1.SGM 19JAP1 khammond on DSKJM1Z7X2PROD with PROPOSALS Federal Register / Vol. 88, No. 12 / Thursday, January 19, 2023 / Proposed Rules (landing gear assembly) and affected part sub-assemblies (front or rear crossbeam or left-hand or right-hand skid assembly) from service and replacing with airworthy parts. This proposed AD would allow an affected part or affected part sub-assembly to be installed on a helicopter if certain actions in this proposed AD are accomplished. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by March 6, 2023. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA–2023–0016; 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 NPRM, the mandatory continuing airworthiness information (MCAI), any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: • For service information identified in this NPRM, 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 www.airbus.com/ helicopters/services/technicalsupport.html. • You may view this 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 this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–0016. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. VerDate Sep<11>2014 17:06 Jan 18, 2023 Jkt 259001 FAA–2023–0016; Project Identifier MCAI–2022–00416–R’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Stephanie Sunderbruch, Aerospace Engineer, Safety Risk Management Section, Systems Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–4659; email Stephanie.L.Sunderbruch@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2022–0053, dated March 23, 2022 (EASA AD 2022–0053), to correct an unsafe condition for Airbus Helicopters Model EC 120 B, EC 130 B4, and EC 130 T2 helicopters, all serial numbers. EASA advises an occurrence was reported of corrosion found on a landing gear assembly of a Model EC 130 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 3331 helicopter. EASA further advises that other helicopter models are affected by the same unsafe condition due to design similarity. This condition, if not addressed, could result in the landing gear collapsing, damage to the helicopter, and injury to occupants. Accordingly, EASA AD 2022–0053 requires, for helicopters with certain part-numbered landing gear assemblies installed, a one-time visual inspection of the external areas of the landing gear tubes for corrosion and cracks, and a borescope inspection of the internal sides of the landing gear tubes for corrosion (including, but not limited to, leafing and exfoliant corrosion) and cracks. EASA AD 2022–0053 also requires contacting Airbus Helicopters for approved corrective action if any crack, or leafing or exfoliant corrosion, is found or if the remaining thickness of affected part sub-assemblies do not meet specified acceptability criteria during any of the inspections. EASA AD 2022– 0053 allows replacing the affected part sub-assembly in lieu of contacting Airbus Helicopters for approved corrective action. EASA AD 2022–0053 also requires reporting inspection results to Airbus Helicopters within 30 days after the inspection or within 30 days after the effective date of EASA AD 2022–0053, whichever occurs later. Additionally, EASA AD 2022–0053 allows credit for certain inspections and corrective actions if those actions were done before the effective date of EASA AD 2022–0053, and allows an affected part or affected part sub-assembly to be installed on a helicopter if certain requirements of EASA AD 2022–0053 are met. EASA considers its AD an interim action and states that further AD action may follow. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA about the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determining that the unsafe condition described previously is likely to exist or develop on other helicopters of these same type designs. Related Service Information Under 1 CFR Part 51 The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) No. EC120– 32A014 (EC120–32A014 Rev 1), for Model EC120B helicopters and Airbus Helicopters ASB No. EC130–32A013 (EC130–32A013 Rev 1), for Model E:\FR\FM\19JAP1.SGM 19JAP1 3332 Federal Register / Vol. 88, No. 12 / Thursday, January 19, 2023 / Proposed Rules khammond on DSKJM1Z7X2PROD with PROPOSALS EC130B4 and EC130T2 helicopters, both Revision 1, and both dated October 17, 2022. This service information includes Detail A Figure 3 (EC120–32A014 Rev 1) and Detail A Figure 4 (EC130–32A013 Rev 1), which identify the areas and zones to be inspected for cracks and corrosion (including, but not limited to leafing and exfoliant corrosion). This service information also includes Table 3, which identifies the minimum material thickness permitted after corrosion is removed. Additionally, this service information specifies procedures for visually inspecting the external areas and borescope inspecting the internal areas of the landing gear tubes, removing corrosion, measuring thickness, interpreting results of the measurements, and applying a chemical conversion coating and primer. 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. Proposed AD Requirements in This NPRM This proposed AD would require, for helicopters with certain part-numbered landing gear assemblies installed, removing and cleaning certain parts and visually inspecting the external areas of the landing gear tubes for cracks and corrosion (including, but not limited to, leafing and exfoliant corrosion). If any crack, leafing corrosion, or exfoliant corrosion is detected, this proposed AD would require removing certain parts from service and replacing with airworthy parts. If any corrosion other than leafing or exfoliant corrosion is detected, this proposed AD would require removing the corrosion. This proposed AD would also require borescope inspecting the internal side of the landing gear tubes for cracks and corrosion (including, but not limited to, leafing and exfoliant corrosion). If any crack, leafing corrosion, or exfoliant corrosion is detected, this proposed AD would require removing any affected part from service and replacing it with an airworthy part. If any corrosion other than leafing or exfoliant corrosion is detected, this proposed AD would require removing the corrosion. If any corrosion other than leafing or exfoliant corrosion is detected during any of the inspections required by this proposed AD, this proposed AD would require removing all corrosion and measuring the remaining thickness of the landing gear tubes. This proposed AD would require interpreting the results of the measurements and if the remaining thickness does not meet the permitted criteria as specified, this VerDate Sep<11>2014 17:06 Jan 18, 2023 Jkt 259001 proposed AD would require removing each affected sub-assembly from service and replacing it with an airworthy part. If the remaining thickness meets the permitted criteria as specified, this proposed AD would require applying a chemical conversion coating and a double layer of primer. Additionally, this proposed AD would allow an affected part or affected part sub-assembly to be installed on a helicopter, if certain requirements of this proposed AD have been accomplished. Differences Between This Proposed AD and EASA AD 2022–0053 EASA AD 2022–0053 requires, for certain helicopters, the initial inspections to be completed within certain compliance times specified in Table 1 of EASA AD 2022–0053, whereas this proposed AD would require the initial inspections to be completed within 13 months after the effective date of this proposed AD. EASA AD 2022–0053 requires contacting Airbus Helicopters for repair instructions if any cracks, leafing corrosion, or exfoliant corrosion are found, or if the residual thickness of an affected part sub-assembly does not meet certain criteria, whereas this proposed AD would require removing the affected part or part sub-assembly from service instead. EASA AD 2022– 0053 allows credit for certain inspections and corrective actions if these requirements were accomplished in accordance with previously issued service information, whereas this proposed AD would not allow credit for the inspections and corrective actions if previously issued service information was used. EASA AD 2022–0053 requires reporting the inspection results to Airbus Helicopters, whereas this proposed AD would not require reporting. Interim Action The FAA considers this proposed AD would be an interim action. Once final action has been identified, the FAA might consider further rulemaking. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 353 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 proposed AD. Removing and cleaning parts, and visually inspecting the external surface of each landing gear tube for cracks and corrosion would take about 2 workhours for an estimated cost of $170 per PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 inspection, up to $680 per helicopter (4 landing gear tubes per helicopter), and up to $240,040 for the U.S. fleet. Borescope inspecting the internal side of each landing gear tube for cracks and corrosion (including, but not limited to, leafing and exfoliant corrosion) would take about 1 work-hour for an estimated cost of $85 per inspection, up to $340 per helicopter (4 landing gear tubes per helicopter), and up to $120,020 for the U.S. fleet. If required, applying a chemical conversion coating and a double layer of primer would take about 2 work-hours and parts would cost a minimal amount for an estimated cost of $170 per helicopter and up to $60,010 for the U.S. fleet. If required, disassembling certain zones and removing corrosion would take about 1 work hour for an estimated cost of $85 per helicopter. If required, measuring the thickness of the internal side of each landing gear tube and interpreting the results would take up to 1 work-hour for an estimated cost of $85 per helicopter. If required, replacing a landing gear assembly would take about 2 workhours and parts would cost up to $106,612 for an estimated cost of up to $106,782 per replacement. If required, replacing a front crossbeam would take about 1 workhour and parts would cost up to $9,081 for an estimated cost of up to $9,166 per replacement. If required, replacing a rear crossbeam would take about 1 work-hour and parts would cost up to $11,639 for an estimated cost of up to $11,724 per replacement. If required, replacing a right-hand or left-hand skid assembly would take about 1 work-hour and parts would cost up to $21,447 for an estimated cost of up to $21,532 per skid assembly replacement. 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. E:\FR\FM\19JAP1.SGM 19JAP1 Federal Register / Vol. 88, No. 12 / Thursday, January 19, 2023 / Proposed Rules 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would 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 Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: ■ Airbus Helicopters: Docket No. FAA–2023– 0016; Project Identifier MCAI–2022– 00416–R. khammond on DSKJM1Z7X2PROD with PROPOSALS (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by March 6, 2023. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters certificated in any category. (d) Subject Joint Aircraft Service Component (JASC) Code: 3213, Main Landing Gear Strut, Axle, Truck. VerDate Sep<11>2014 17:06 Jan 18, 2023 Jkt 259001 (e) Unsafe Condition This AD was prompted by a report of corrosion detected on certain part-numbered landing gear assemblies. The FAA is issuing this AD to detect corrosion and cracks on the landing gear tubes. The unsafe condition, if not addressed, could result in the landing gear collapsing, damage to the helicopter, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 13 months after the effective date of this AD, for Model EC120B helicopters with landing gear assembly part number (P/N) C321A2106102, P/N C321A2501101, P/N C321A2501102, P/N C321A2601051AA, P/N C321A2601051CA, or P/N C321A2601052 installed, and for Model EC130B4 and EC130T2 helicopters with landing gear assembly P/N 350A41– 0077–0201, P/N 350A41–0080–1102, P/N 350A41–0080–1103, P/N 350A41–0081– 0201, P/N 350A41–0082–0101, or P/N 350A41–0082–0102 installed, except those having a date of first installation on a helicopter of February 16, 2022 or later; and for helicopters with a landing gear assembly having a P/N specified in this paragraph, with an unknown installation date, do the following: (i) Remove the landing gear fairing from the rear crossbeam and clean the external areas of each of the landing gear tubes item a, item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F, and M as depicted in Detail A, Figure 3, and Details B and C, Figure 4 of Airbus Helicopters Alert Service Bulletin (ASB) No. EC120–32A014 (ASB EC120–32A014 Rev 1), or as depicted in Detail A, Figure 4, and Details B and C, Figure 5 of Airbus Helicopters ASB No. EC130–32A013 (ASB EC130–32A013 Rev 1), both Revision 1, and both dated October 17, 2022, as applicable to your model helicopter. (ii) Visually inspect the external areas of each of the landing gear tubes item a, item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F, and M for corrosion (including, but not limited to leafing and exfoliant corrosion) and cracks. (A) If any crack or leafing or exfoliant corrosion is detected, before further flight, remove the affected part from service and replace it with an airworthy part. (B) If any corrosion is detected in Zone C1, C2, or E, other than leafing or exfoliant corrosion, before further flight, disassemble the landing gear and using a non-metal abrasive pad, remove all corrosion from all zones. (C) If any corrosion is detected in only Zone B1, B2, D, F, or M, other than leafing or exfoliant corrosion, before further flight, using a non-metal abrasive pad, remove all corrosion from all zones. (iii) Borescope inspect the internal side of each of the landing gear tubes item a, item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F, and M for corrosion (including, but not limited to leafing and exfoliant corrosion) and cracks. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 3333 (A) If any crack, leafing corrosion, or exfoliant corrosion is detected, before further flight, remove the affected part from service and replace it with an airworthy part. (B) If any corrosion is detected in Zone C1, C2, or E, other than leafing or exfoliant corrosion before further flight, disassemble the landing gear and using a non-metal abrasive pad, remove all corrosion from all zones. (C) If any corrosion is detected in only Zone B1, B2, D, F, or M, other than leafing or exfoliant corrosion, before further flight, using a non-metal abrasive pad, remove all corrosion from all zones. (iv) Before further flight after performing the inspections required by paragraphs (g)(1)(ii) and (iii) of this AD, if any corrosion was detected during any inspection required by paragraphs (g)(1)(ii) and (iii) of this AD other than leafing or exfoliant corrosion, using an ultrasonic thickness gauge, measure the remaining thickness of the landing gear tubes in the zones where any corrosion was removed. Interpret the results of the measurement using the criteria specified in Table 3 of ASB EC120–32A014 Rev 1 or Table 3 of EC130–32A013 Rev 1, as applicable to your model helicopter. If the remaining thickness does not meet the permitted criteria as specified, before further flight, remove each affected sub-assembly from service and replace it with an airworthy part. If the remaining thickness meets the permitted criteria as specified, before further flight, accomplish the actions required by paragraph (g)(1)(v) of this AD. (v) Apply a chemical conversion coating (Alodine 1200) or equivalent, and a double layer of chromate Primer P05 and Primer P20, or equivalent, below the collar in Zones F and M and to any reworked zone. (2) For Model EC120B helicopters, as of the effective date of this AD, do not install landing gear assembly P/N C321A2106102, P/N C321A2501101, P/N C321A2501102, P/ N C321A2601051AA, P/N C321A2601051CA, or P/N C321A2601052, previously installed with an unknown installation date or a date of first installation on a helicopter before February 16, 2022; and do not install a front crossbeam, rear crossbeam, left-hand (LH) skid assembly, or right-hand (RH) skid assembly having a P/N identified in Table 2 of ASB EC120–32A014 Rev 1, previously installed with an unknown installation date, or a date of first installation on a helicopter before February 16, 2022, on any helicopter; unless the actions required by paragraphs (g)(1)(i) through (v) of this AD, as applicable, have been accomplished on the part. (3) For Model EC130B4 and EC130T2 helicopters, as of the effective date of this AD, do not install landing gear assembly P/ N 350A41–0077–0201, P/N 350A41–0080– 1102, P/N 350A41–0080–1103, P/N 350A41– 0081–0201, P/N 350A41–0082–0101, or P/N 350A41–0082–0102, previously installed with an unknown installation date or a date of first installation on a helicopter before February 16, 2022, and do not install a front crossbeam, rear crossbeam, LH skid assembly, or RH skid assembly, having a P/ N identified in Table 2 of ASB EC130– 32A013 Rev 1 previously installed with an unknown installation date, or a date of first installation on a helicopter before February E:\FR\FM\19JAP1.SGM 19JAP1 3334 Federal Register / Vol. 88, No. 12 / Thursday, January 19, 2023 / Proposed Rules 16, 2022, on any helicopter, unless the actions required by paragraphs (g)(1)(i) through (v) of this AD, as applicable, have been accomplished on the part. Issued on January 12, 2023. Gaetano A. Sciortino, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. (h) Alternative Methods of Compliance (AMOCs) [FR Doc. 2023–00886 Filed 1–18–23; 8:45 am] BILLING CODE 4910–13–P (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)(2) 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. khammond on DSKJM1Z7X2PROD with PROPOSALS (i) Additional Information (1) Refer to European Union Aviation Safety Agency (EASA) AD 2022–0053, dated March 23, 2022, for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA– 2023–0016. (2) For more information about this AD, contact Stephanie Sunderbruch, Aerospace Engineer, Safety Risk Management Section, Systems Policy Branch, Policy & Innovation Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–4659; email Stephanie.L.Sunderbruch@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 this AD specifies otherwise. (i) Airbus Helicopters Alert Service Bulletin (ASB) No. EC120–32A014, Revision 1, dated October 17, 2022. (ii) Airbus Helicopters ASB No. EC130– 32A013, Revision 1, dated October 17, 2022. (3) For service information identified in this AD, contact Airbus Helicopters, Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at 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: www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 17:06 Jan 18, 2023 Jkt 259001 DEPARTMENT OF COMMERCE National Oceanic and Atmospheric Administration 15 CFR Part 922 [Docket No. 221216–0275] RIN 0648–BJ62 Proposed Lake Ontario National Marine Sanctuary; Notice of Proposed Rulemaking Office of National Marine Sanctuaries (ONMS), National Ocean Service (NOS), National Oceanic and Atmospheric Administration (NOAA), Department of Commerce (DOC). ACTION: Proposed rule. AGENCY: NOAA proposes to designate the Lake Ontario National Marine Sanctuary (LONMS) in eastern Lake Ontario to recognize the national significance of the area’s historical, archaeological, and cultural resources and to manage this special place as part of the National Marine Sanctuary System. The proposed sanctuary boundary would encompass 1,302 nmi2 (1,724 mi2) of eastern Lake Ontario waters and would border Wayne, Cayuga, Oswego, and Jefferson counties. NOAA would co-manage LONMS with New York State. NOAA also proposes regulations to implement the national marine sanctuary designation and establish its terms of designation. This proposed rule follows NOAA’s publication of a draft environmental impact statement (DEIS) and draft management plan (DMP) in July 2021. NOAA is soliciting public comment on the proposed rule, as well as possible names for the sanctuary. DATES: Comments: Send comments by March 20, 2023. Public Meetings: NOAA will host four public meetings: three in-person meetings and one virtual meeting. The in-person scoping meetings will occur at the following dates and times: • Oswego, NY, Date: February 28, 2023, Location: Lake Ontario Event and Conference Center, Address: 26 E 1st St., Oswego, NY 13126, Time: 6:30 p.m.–8 p.m. Eastern Time • Wolcott, NY, Date: March 1, 2023, Location: Wolcott Elks Lodge No. SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 1763, Address: 6161 W Port Bay Rd., Wolcott, NY 14590, Time: 6:30 p.m.– 8 p.m. Eastern Time • Watertown, NY, Date: March 2, 2023, Location: Jefferson Community College, Address: 1220 Coffeen St., Sturtz Theater, Room 4–111, Watertown, NY 13601, Time: 6:30 p.m.–8 p.m. Eastern Time The virtual public scoping meeting will occur at the following dates and time: • Wednesday, March 8, 2023, 6:30 p.m. to 8 p.m. Eastern Time Please check https:// sanctuaries.noaa.gov/lake-ontario for meeting links and the most up-to-date information, should plans for these public meetings change. NOAA may end a virtual or in-person meeting before the time noted above if all participants have concluded their oral comments. You may submit comments on this document, identified by NOAA– NOS–2021–0050, by any of the following methods: • Federal e-Rulemaking Portal: https://www.regulations.gov and search for ‘‘NOAA–NOS–2021–0050’’. Follow the instructions for sending comments. • Mail: Send any hard copy public comments by mail to Ellen Brody, Great Lakes Regional Coordinator, 4840 South State Road, Ann Arbor, MI 48108–9719. • Public Meetings: Provide oral comments during public meetings, as described under DATES. Webinar registration details and additional information about how to participate in these public scoping meetings is available at: https:// sanctuaries.noaa.gov/lake-ontario. Instructions: Comments sent by any other method, to any other address or individual, or received after the end of the comment period, may not be considered by NOAA. All comments received are a part of the public record and will generally be posted for public viewing on www.regulations.gov without change. All personal identifying information (e.g., name, address), confidential business information, or otherwise sensitive information submitted voluntarily by the sender will be publicly accessible. NOAA will accept anonymous comments (enter ‘‘N/ A’’ in the required fields if you wish to remain anonymous). Comments that are not responsive or contain profanity, vulgarity, threats, or other inappropriate language will not be considered. FOR FURTHER INFORMATION CONTACT: Ellen Brody, 734–741–2270, ellen.brody@noaa.gov. SUPPLEMENTARY INFORMATION: ADDRESSES: E:\FR\FM\19JAP1.SGM 19JAP1

Agencies

[Federal Register Volume 88, Number 12 (Thursday, January 19, 2023)]
[Proposed Rules]
[Pages 3330-3334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-00886]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-0016; Project Identifier MCAI-2022-00416-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Helicopters Model EC120B, EC130B4, and EC130T2 
helicopters. This proposed AD was prompted by a report of corrosion 
detected on certain part-numbered landing gear assemblies. This 
proposed AD would require, for helicopters with certain part-numbered 
landing gear assemblies installed, visually inspecting for cracks and 
corrosion; borescope inspecting; and if required, removing corrosion, 
measuring thickness, interpreting results of the measurements, applying 
chemical conversion coating and primer, and removing affected parts

[[Page 3331]]

(landing gear assembly) and affected part sub-assemblies (front or rear 
crossbeam or left-hand or right-hand skid assembly) from service and 
replacing with airworthy parts. This proposed AD would allow an 
affected part or affected part sub-assembly to be installed on a 
helicopter if certain actions in this proposed AD are accomplished. The 
FAA is proposing this AD to address the unsafe condition on these 
products.

DATES: The FAA must receive comments on this proposed AD by March 6, 
2023.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to regulations.gov. Follow 
the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2023-0016; 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 NPRM, the mandatory continuing airworthiness 
information (MCAI), any comments received, and other information. The 
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information identified in this NPRM, 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 
www.airbus.com/helicopters/services/technical-support.html.
     You may view this 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 this 
material at the FAA, call (817) 222-5110. It is also available at 
regulations.gov under Docket No. FAA-2023-0016.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2023-0016; Project Identifier 
MCAI-2022-00416-R'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Stephanie Sunderbruch, Aerospace Engineer, Safety Risk Management 
Section, Systems Policy Branch, Policy & Innovation Division, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-4659; 
email [email protected]. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union, has issued 
EASA AD 2022-0053, dated March 23, 2022 (EASA AD 2022-0053), to correct 
an unsafe condition for Airbus Helicopters Model EC 120 B, EC 130 B4, 
and EC 130 T2 helicopters, all serial numbers. EASA advises an 
occurrence was reported of corrosion found on a landing gear assembly 
of a Model EC 130 helicopter. EASA further advises that other 
helicopter models are affected by the same unsafe condition due to 
design similarity. This condition, if not addressed, could result in 
the landing gear collapsing, damage to the helicopter, and injury to 
occupants.
    Accordingly, EASA AD 2022-0053 requires, for helicopters with 
certain part-numbered landing gear assemblies installed, a one-time 
visual inspection of the external areas of the landing gear tubes for 
corrosion and cracks, and a borescope inspection of the internal sides 
of the landing gear tubes for corrosion (including, but not limited to, 
leafing and exfoliant corrosion) and cracks. EASA AD 2022-0053 also 
requires contacting Airbus Helicopters for approved corrective action 
if any crack, or leafing or exfoliant corrosion, is found or if the 
remaining thickness of affected part sub-assemblies do not meet 
specified acceptability criteria during any of the inspections. EASA AD 
2022-0053 allows replacing the affected part sub-assembly in lieu of 
contacting Airbus Helicopters for approved corrective action. EASA AD 
2022-0053 also requires reporting inspection results to Airbus 
Helicopters within 30 days after the inspection or within 30 days after 
the effective date of EASA AD 2022-0053, whichever occurs later.
    Additionally, EASA AD 2022-0053 allows credit for certain 
inspections and corrective actions if those actions were done before 
the effective date of EASA AD 2022-0053, and allows an affected part or 
affected part sub-assembly to be installed on a helicopter if certain 
requirements of EASA AD 2022-0053 are met. EASA considers its AD an 
interim action and states that further AD action may follow.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA about the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determining that 
the unsafe condition described previously is likely to exist or develop 
on other helicopters of these same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. EC120-32A014 (EC120-32A014 Rev 1), for Model EC120B helicopters and 
Airbus Helicopters ASB No. EC130-32A013 (EC130-32A013 Rev 1), for Model

[[Page 3332]]

EC130B4 and EC130T2 helicopters, both Revision 1, and both dated 
October 17, 2022. This service information includes Detail A Figure 3 
(EC120-32A014 Rev 1) and Detail A Figure 4 (EC130-32A013 Rev 1), which 
identify the areas and zones to be inspected for cracks and corrosion 
(including, but not limited to leafing and exfoliant corrosion). This 
service information also includes Table 3, which identifies the minimum 
material thickness permitted after corrosion is removed. Additionally, 
this service information specifies procedures for visually inspecting 
the external areas and borescope inspecting the internal areas of the 
landing gear tubes, removing corrosion, measuring thickness, 
interpreting results of the measurements, and applying a chemical 
conversion coating and primer.
    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.

Proposed AD Requirements in This NPRM

    This proposed AD would require, for helicopters with certain part-
numbered landing gear assemblies installed, removing and cleaning 
certain parts and visually inspecting the external areas of the landing 
gear tubes for cracks and corrosion (including, but not limited to, 
leafing and exfoliant corrosion). If any crack, leafing corrosion, or 
exfoliant corrosion is detected, this proposed AD would require 
removing certain parts from service and replacing with airworthy parts. 
If any corrosion other than leafing or exfoliant corrosion is detected, 
this proposed AD would require removing the corrosion.
    This proposed AD would also require borescope inspecting the 
internal side of the landing gear tubes for cracks and corrosion 
(including, but not limited to, leafing and exfoliant corrosion). If 
any crack, leafing corrosion, or exfoliant corrosion is detected, this 
proposed AD would require removing any affected part from service and 
replacing it with an airworthy part. If any corrosion other than 
leafing or exfoliant corrosion is detected, this proposed AD would 
require removing the corrosion.
    If any corrosion other than leafing or exfoliant corrosion is 
detected during any of the inspections required by this proposed AD, 
this proposed AD would require removing all corrosion and measuring the 
remaining thickness of the landing gear tubes. This proposed AD would 
require interpreting the results of the measurements and if the 
remaining thickness does not meet the permitted criteria as specified, 
this proposed AD would require removing each affected sub-assembly from 
service and replacing it with an airworthy part. If the remaining 
thickness meets the permitted criteria as specified, this proposed AD 
would require applying a chemical conversion coating and a double layer 
of primer.
    Additionally, this proposed AD would allow an affected part or 
affected part sub-assembly to be installed on a helicopter, if certain 
requirements of this proposed AD have been accomplished.

Differences Between This Proposed AD and EASA AD 2022-0053

    EASA AD 2022-0053 requires, for certain helicopters, the initial 
inspections to be completed within certain compliance times specified 
in Table 1 of EASA AD 2022-0053, whereas this proposed AD would require 
the initial inspections to be completed within 13 months after the 
effective date of this proposed AD. EASA AD 2022-0053 requires 
contacting Airbus Helicopters for repair instructions if any cracks, 
leafing corrosion, or exfoliant corrosion are found, or if the residual 
thickness of an affected part sub-assembly does not meet certain 
criteria, whereas this proposed AD would require removing the affected 
part or part sub-assembly from service instead. EASA AD 2022-0053 
allows credit for certain inspections and corrective actions if these 
requirements were accomplished in accordance with previously issued 
service information, whereas this proposed AD would not allow credit 
for the inspections and corrective actions if previously issued service 
information was used. EASA AD 2022-0053 requires reporting the 
inspection results to Airbus Helicopters, whereas this proposed AD 
would not require reporting.

Interim Action

    The FAA considers this proposed AD would be an interim action. Once 
final action has been identified, the FAA might consider further 
rulemaking.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 353 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 proposed AD.
    Removing and cleaning parts, and visually inspecting the external 
surface of each landing gear tube for cracks and corrosion would take 
about 2 work-hours for an estimated cost of $170 per inspection, up to 
$680 per helicopter (4 landing gear tubes per helicopter), and up to 
$240,040 for the U.S. fleet.
    Borescope inspecting the internal side of each landing gear tube 
for cracks and corrosion (including, but not limited to, leafing and 
exfoliant corrosion) would take about 1 work-hour for an estimated cost 
of $85 per inspection, up to $340 per helicopter (4 landing gear tubes 
per helicopter), and up to $120,020 for the U.S. fleet.
    If required, applying a chemical conversion coating and a double 
layer of primer would take about 2 work-hours and parts would cost a 
minimal amount for an estimated cost of $170 per helicopter and up to 
$60,010 for the U.S. fleet.
    If required, disassembling certain zones and removing corrosion 
would take about 1 work hour for an estimated cost of $85 per 
helicopter.
    If required, measuring the thickness of the internal side of each 
landing gear tube and interpreting the results would take up to 1 work-
hour for an estimated cost of $85 per helicopter.
    If required, replacing a landing gear assembly would take about 2 
work-hours and parts would cost up to $106,612 for an estimated cost of 
up to $106,782 per replacement.
    If required, replacing a front crossbeam would take about 1 work-
hour and parts would cost up to $9,081 for an estimated cost of up to 
$9,166 per replacement.
    If required, replacing a rear crossbeam would take about 1 work-
hour and parts would cost up to $11,639 for an estimated cost of up to 
$11,724 per replacement.
    If required, replacing a right-hand or left-hand skid assembly 
would take about 1 work-hour and parts would cost up to $21,447 for an 
estimated cost of up to $21,532 per skid assembly replacement.

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.

[[Page 3333]]

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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus Helicopters: Docket No. FAA-2023-0016; Project Identifier 
MCAI-2022-00416-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by March 6, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Helicopters Model EC120B, EC130B4, 
and EC130T2 helicopters certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 3213, Main Landing 
Gear Strut, Axle, Truck.

(e) Unsafe Condition

    This AD was prompted by a report of corrosion detected on 
certain part-numbered landing gear assemblies. The FAA is issuing 
this AD to detect corrosion and cracks on the landing gear tubes. 
The unsafe condition, if not addressed, could result in the landing 
gear collapsing, damage to the helicopter, and injury to occupants.

(f) Compliance

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

(g) Required Actions

    (1) Within 13 months after the effective date of this AD, for 
Model EC120B helicopters with landing gear assembly part number (P/
N) C321A2106102, P/N C321A2501101, P/N C321A2501102, P/N 
C321A2601051AA, P/N C321A2601051CA, or P/N C321A2601052 installed, 
and for Model EC130B4 and EC130T2 helicopters with landing gear 
assembly P/N 350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-
0080-1103, P/N 350A41-0081-0201, P/N 350A41-0082-0101, or P/N 
350A41-0082-0102 installed, except those having a date of first 
installation on a helicopter of February 16, 2022 or later; and for 
helicopters with a landing gear assembly having a P/N specified in 
this paragraph, with an unknown installation date, do the following:
    (i) Remove the landing gear fairing from the rear crossbeam and 
clean the external areas of each of the landing gear tubes item a, 
item c, item d, and item e, including Zones B1, B2, C1, C2, D, E, F, 
and M as depicted in Detail A, Figure 3, and Details B and C, Figure 
4 of Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014 (ASB EC120-32A014 Rev 1), or as depicted in Detail A, Figure 
4, and Details B and C, Figure 5 of Airbus Helicopters ASB No. 
EC130-32A013 (ASB EC130-32A013 Rev 1), both Revision 1, and both 
dated October 17, 2022, as applicable to your model helicopter.
    (ii) Visually inspect the external areas of each of the landing 
gear tubes item a, item c, item d, and item e, including Zones B1, 
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited 
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack or leafing or exfoliant corrosion is detected, 
before further flight, remove the affected part from service and 
replace it with an airworthy part.
    (B) If any corrosion is detected in Zone C1, C2, or E, other 
than leafing or exfoliant corrosion, before further flight, 
disassemble the landing gear and using a non-metal abrasive pad, 
remove all corrosion from all zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or 
M, other than leafing or exfoliant corrosion, before further flight, 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (iii) Borescope inspect the internal side of each of the landing 
gear tubes item a, item c, item d, and item e, including Zones B1, 
B2, C1, C2, D, E, F, and M for corrosion (including, but not limited 
to leafing and exfoliant corrosion) and cracks.
    (A) If any crack, leafing corrosion, or exfoliant corrosion is 
detected, before further flight, remove the affected part from 
service and replace it with an airworthy part. (B) If any corrosion 
is detected in Zone C1, C2, or E, other than leafing or exfoliant 
corrosion before further flight, disassemble the landing gear and 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (C) If any corrosion is detected in only Zone B1, B2, D, F, or 
M, other than leafing or exfoliant corrosion, before further flight, 
using a non-metal abrasive pad, remove all corrosion from all zones.
    (iv) Before further flight after performing the inspections 
required by paragraphs (g)(1)(ii) and (iii) of this AD, if any 
corrosion was detected during any inspection required by paragraphs 
(g)(1)(ii) and (iii) of this AD other than leafing or exfoliant 
corrosion, using an ultrasonic thickness gauge, measure the 
remaining thickness of the landing gear tubes in the zones where any 
corrosion was removed. Interpret the results of the measurement 
using the criteria specified in Table 3 of ASB EC120-32A014 Rev 1 or 
Table 3 of EC130-32A013 Rev 1, as applicable to your model 
helicopter. If the remaining thickness does not meet the permitted 
criteria as specified, before further flight, remove each affected 
sub-assembly from service and replace it with an airworthy part. If 
the remaining thickness meets the permitted criteria as specified, 
before further flight, accomplish the actions required by paragraph 
(g)(1)(v) of this AD.
    (v) Apply a chemical conversion coating (Alodine 1200) or 
equivalent, and a double layer of chromate Primer P05 and Primer 
P20, or equivalent, below the collar in Zones F and M and to any 
reworked zone.
    (2) For Model EC120B helicopters, as of the effective date of 
this AD, do not install landing gear assembly P/N C321A2106102, P/N 
C321A2501101, P/N C321A2501102, P/N C321A2601051AA, P/N 
C321A2601051CA, or P/N C321A2601052, previously installed with an 
unknown installation date or a date of first installation on a 
helicopter before February 16, 2022; and do not install a front 
crossbeam, rear crossbeam, left-hand (LH) skid assembly, or right-
hand (RH) skid assembly having a P/N identified in Table 2 of ASB 
EC120-32A014 Rev 1, previously installed with an unknown 
installation date, or a date of first installation on a helicopter 
before February 16, 2022, on any helicopter; unless the actions 
required by paragraphs (g)(1)(i) through (v) of this AD, as 
applicable, have been accomplished on the part.
    (3) For Model EC130B4 and EC130T2 helicopters, as of the 
effective date of this AD, do not install landing gear assembly P/N 
350A41-0077-0201, P/N 350A41-0080-1102, P/N 350A41-0080-1103, P/N 
350A41-0081-0201, P/N 350A41-0082-0101, or P/N 350A41-0082-0102, 
previously installed with an unknown installation date or a date of 
first installation on a helicopter before February 16, 2022, and do 
not install a front crossbeam, rear crossbeam, LH skid assembly, or 
RH skid assembly, having a P/N identified in Table 2 of ASB EC130-
32A013 Rev 1 previously installed with an unknown installation date, 
or a date of first installation on a helicopter before February

[[Page 3334]]

16, 2022, on any helicopter, unless the actions required by 
paragraphs (g)(1)(i) through (v) of this AD, as applicable, have 
been accomplished on the part.

(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)(2) 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) Additional Information

    (1) Refer to European Union Aviation Safety Agency (EASA) AD 
2022-0053, dated March 23, 2022, for related information. This EASA 
AD may be found in the AD docket at regulations.gov under Docket No. 
FAA-2023-0016.
    (2) For more information about this AD, contact Stephanie 
Sunderbruch, Aerospace Engineer, Safety Risk Management Section, 
Systems Policy Branch, Policy & Innovation Division, FAA, 10101 
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-4659; 
email [email protected].

(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 this AD specifies otherwise.
    (i) Airbus Helicopters Alert Service Bulletin (ASB) No. EC120-
32A014, Revision 1, dated October 17, 2022.
    (ii) Airbus Helicopters ASB No. EC130-32A013, Revision 1, dated 
October 17, 2022.
    (3) For service information identified in this AD, contact 
Airbus Helicopters, Airbus Helicopters, 2701 North Forum Drive, 
Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; 
fax (972) 641-3775; or at 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: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on January 12, 2023.
Gaetano A. Sciortino,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-00886 Filed 1-18-23; 8:45 am]
BILLING CODE 4910-13-P
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