Airworthiness Directives; Airbus Helicopters, 51695-51699 [2023-16555]

Download as PDF 51695 Rules and Regulations Federal Register Vol. 88, No. 149 Friday, August 4, 2023 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No.: FAA–2023–1442] Accepted Means of Compliance; Airworthiness Standards: Transport Category Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notification of availability. AGENCY: This document announces SAE International (SAE) aerospace standard (AS) for use as a means of compliance to the applicable airworthiness standards for transport category airplanes. The FAA accepts SAE Designation AS6960 ‘‘Performance Standards for Seat Furnishings’’, section 3.2.3 as a means of compliance with regard to the design of seat furnishings. DATES: Effective August 4, 2023. FOR FURTHER INFORMATION CONTACT: Dan Jacquet, Cabin Safety Section, AIR–624, Technical Policy Branch, Policy & Standards Division, Federal Aviation Administration, 2200 South 216th Street, Des Moines, WA 98198, telephone 206–231–3208, email Daniel.Jacquet@faa.gov. SUPPLEMENTARY INFORMATION: SUMMARY: TKELLEY on DSK125TN23PROD with RULES1 Background Under the provisions of the National Technology Transfer and Advancement Act of 1995 1 and Office of Management and Budget (OMB) Circular A–119, ‘‘Federal Participation in the Development and Use of Voluntary Consensus Standards and in Conformity Assessment Activities,’’ effective January 27, 2016, the FAA participates in the development of consensus standards and uses consensus standards as a means of carrying out its policy objectives where appropriate. The FAA has been working with industry and VerDate Sep<11>2014 15:58 Aug 03, 2023 Jkt 259001 other stakeholders through the SAE Aircraft Seat Committee to develop consensus standards for seat furnishings to prevent hazards, such as object entrapment. This document is the result of a safety recommendation, precipitated by an event where a passenger cell phone was crushed in the mechanism of a first class cabin seat on a British Airways Boeing 747 airplane that caused smoke and fire. A pilot declared an emergency landing due to the fire. The crew used four Bromochlorodifluoromethane (BCF) and two water fire extinguishers to extinguish the cell phone fire. The FAA investigators found that the first and business class electrical power seats could jam a cell phone or tablet within its mechanism and crush its lithium battery to cause a fire. In the 2017 safety recommendation, the British Airways maintenance department said they saw at least one cell phone per day get jammed in electrically operated seats. Also noted in the safety recommendation, American Airlines maintenance department reported receiving five calls per day to retrieve lost cell phones in seats at John F. Kennedy International Airport alone. According to the FAA website lithium battery incidents continue to be reported and are ongoing. (https:// www.faa.gov/hazmat/resources/ lithium_batteries/incidents) The FAA determined that seat designs that allow small objects (e.g., cell phones, keys, wallets) to migrate to a location that prevents the return of critical seat features to their taxi, takeoff, and landing position, or be crushed to cause a potential fire hazard, is non-compliant with §§ 25.601 and 25.1301(a)(4). Section 25.601 states, in part, ‘‘The airplane may not have design features or details that experience has shown to be hazardous or unreliable.’’ In addition, § 25.1301(a)(4) states, ‘‘Each item of installed equipment must function properly when installed.’’ The FAA accepts SAE Designation AS6960 ‘‘Performance Standards for Seat Furnishings’’, section 3.2.3 as a means of compliance for Title 14, Code of Federal Regulations (14 CFR) 25.601 and 25.1301(a)(4) with regard to the design of seat furnishings. Means of Compliance Accepted The FAA accepts SAE AS6960, ‘‘Performance Standards for Seat Furnishings’’, section 3.2.3 as an PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 acceptable means of compliance with §§ 25.601 and 25.1301(a)(4) for preventing hazards, such as stated herein, from object entrapment in seat furnishings. The FAA is notifying the public by publishing the acceptance of this consensus standard in the Federal Register. The means of compliance accepted by this document is one means, but not the only means, of complying with §§ 25.601 and 25.1301(a)(4) with regard to design of seat furnishings. Applicants who desire to use means of compliance reflected by other revisions to SAE standards not previously accepted may seek guidance and possible acceptance from the FAA for the use of those means of compliance on a case-by-case basis. Applicants may also propose alternative means of compliance for FAA review and possible acceptance. Availability SAE AS6960, ‘‘Performance Standards for Seat Furnishings in Transport Category Aircraft’’ is available for purchase at https://www.sae.org/ standards or by contacting SAE at telephone number (877) 606–7323 or through email at https://store.sae.org. To inquire about consensus standard content, contact Nicole Mattern, Aircraft Seat Committee, (724) 772–4039 at Nicole.Mattern@sae.org. Issued in Kansas City, Missouri. Mary Schooley, Acting Manager, Technical Policy Branch, Policy and Standards Division, Aircraft Certification Service. [FR Doc. 2023–16094 Filed 8–3–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2023–0016; Project Identifier MCAI–2022–00416–R; Amendment 39–22506; AD 2023–14–06] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: E:\FR\FM\04AUR1.SGM 04AUR1 51696 Federal Register / Vol. 88, No. 149 / Friday, August 4, 2023 / Rules and Regulations The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters. This AD was prompted by a report of corrosion detected on certain partnumbered landing gear assemblies. This AD requires, 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 (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 AD will allow an affected part or affected part sub-assembly to be installed on a helicopter if certain actions in this AD are accomplished. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 8, 2023. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 8, 2023. ADDRESSES: 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 final rule, the European Union Aviation Safety Agency (EASA) AD, 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. Material Incorporated by Reference: • 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 airbus.com/en/ products-services/helicopters/hcareservices/airbusworld. • You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. It is also available at regulations.gov under Docket No. FAA–2023–0016. TKELLEY on DSK125TN23PROD with RULES1 SUMMARY: VerDate Sep<11>2014 15:58 Aug 03, 2023 Jkt 259001 FOR FURTHER INFORMATION CONTACT: Stephanie Sunderbruch, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (817) 222–4659; email: Stephanie.L.Sunderbruch@faa.gov. SUPPLEMENTARY INFORMATION: Background The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters. The NPRM published in the Federal Register on January 19, 2023. The NPRM was prompted by EASA AD 2022–0053, dated March 23, 2022 (EASA AD 2022–0053), issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA advises of an occurrence 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. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 In the NPRM, the FAA proposed to require, for helicopters with certain part-numbered landing gear assemblies installed, removing and cleaning certain parts; visually inspecting certain areas of the landing gear tubes for cracks and corrosion; and if any crack, leafing corrosion, or exfoliant corrosion is detected, removing certain parts from service and replacing with airworthy parts. If any corrosion other than leafing or exfoliant corrosion is detected, the NPRM proposed to require removing the corrosion. The NPRM also proposed to require borescope inspecting the internal side of the landing gear tubes for cracks and corrosion. If any crack, leafing corrosion, or exfoliant corrosion is detected, the NPRM proposed to 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, the NPRM proposed to require removing the corrosion. The NPRM also proposed, if any corrosion other than leafing or exfoliant corrosion is detected during any of the inspections, removing all corrosion and measuring the remaining thickness of the landing gear tubes and interpreting the results of the measurements. If the remaining thickness does not meet the permitted criteria as specified, the NPRM proposed to 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, the NPRM proposed to require applying a chemical conversion coating and a double layer of primer. Finally, the NPRM proposed to allow an affected part or affected part subassembly to be installed on a helicopter, if certain proposed requirements of the NPRM have been accomplished. Discussion of Final Airworthiness Directive Comments The FAA received comments from one commenter, Air Methods.1 The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Allow Credit for Previously Issued Service Information Air Methods requested that the FAA allow credit for the inspections and corrective actions proposed in the NPRM, if these actions were performed in accordance with Revision 1 of the service information before the effective 1 This comment does not appear in the docket because it was marked ‘‘proprietary information.’’ E:\FR\FM\04AUR1.SGM 04AUR1 Federal Register / Vol. 88, No. 149 / Friday, August 4, 2023 / Rules and Regulations date of the AD. Air Methods added that Figure 4 of the service information required by this AD does not properly label ‘‘Zone B’’ and ‘‘Zone C,’’ but commented that it considers the service information sufficiently adequate to identify the areas. The FAA partially agrees. Paragraph (f) of this AD requires compliance with this AD within the compliance times specified, unless the actions have already been done. Therefore, this AD already permits credit for complying with the AD’s required actions if those actions were performed before the effective date of this AD. However, the FAA disagrees with allowing credit for all of this AD’s required actions if done in accordance with Revision 1 of the service information, before the effective date of this AD, because the corrective actions in Revision 1 of the service information differ from this AD’s corrective actions. Operators may request approval of specific corrective actions as an alternative method of compliance (AMOC) under the provisions of paragraph (h) of this AD. TKELLEY on DSK125TN23PROD with RULES1 Comments Regarding Methods To Remove Corrosion Air Methods stated that Revision 1 of the service information refers to the Standard Practices Manual (MTC) for procedures to remove corrosion and that the MTC includes details on important considerations when removing corrosion from aluminum parts. Air Methods further stated that the MTC contains safe procedures for corrosion removal based on service history. Lastly, Air Methods stated that the specific use of just a non-metal abrasive pad, as proposed in the NPRM, may not be adequate to remove corrosion in severe cases and asserted that restricting the corrosion removal procedure does not provide any measurable improvement to the level of safety. The FAA infers that Air Methods is requesting the FAA not limit corrosion removal to only using a non-metal abrasive pad. The FAA agrees. The FAA has revised the required actions paragraph of this final rule by removing the requirement to use a non-metal abrasive pad, and only requires removing all corrosion from all zones. Conclusion 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 of the unsafe condition described in its AD. The FAA reviewed the relevant data, considered the comments received, and determined that air safety VerDate Sep<11>2014 15:58 Aug 03, 2023 Jkt 259001 requires adopting this AD as proposed. Accordingly, the FAA is issuing this AD to address the unsafe condition on these helicopters. Except for minor editorial changes, and any other changes described previously, this AD is adopted as proposed in the NPRM. None of the changes increase the economic burden on any operator. 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 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 ADDRESSES. Differences Between This 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 AD requires the initial inspections to be completed within 13 months after the effective date of this 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 AD requires 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, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 51697 whereas this AD does 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 AD does not require reporting. Interim Action The FAA considers that this AD is an interim action. Once final action has been identified, the FAA might consider further rulemaking. Costs of Compliance The FAA estimates that this AD affects 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 AD. Removing and cleaning parts, and visually inspecting the external surface of each landing gear tube for cracks and corrosion takes 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) takes 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 takes about 2 work-hours and parts 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 takes 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 takes up to 1 work-hour for an estimated cost of $85 per helicopter. If required, replacing a landing gear assembly takes about 2 work-hours and parts cost up to $106,612 for an estimated cost of up to $106,782 per replacement. If required, replacing a front crossbeam takes about 1 work-hour and parts cost up to $9,081 for an estimated cost of up to $9,166 per replacement. If required, replacing a rear crossbeam takes about 1 work-hour and parts 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 takes about 1 work-hour and parts cost up to $21,447 E:\FR\FM\04AUR1.SGM 04AUR1 51698 Federal Register / Vol. 88, No. 149 / Friday, August 4, 2023 / Rules and Regulations § 39.13 for an estimated cost of up to $21,532 per skid assembly replacement. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. TKELLEY on DSK125TN23PROD with RULES1 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. 15:58 Aug 03, 2023 Jkt 259001 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Authority for This Rulemaking VerDate Sep<11>2014 [Amended] 2023–14–06 Airbus Helicopters: Amendment 39–22506; Docket No. FAA–2023–0016; Project Identifier MCAI–2022–00416–R. (a) Effective Date This airworthiness directive (AD) is effective September 8, 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (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 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, 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 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, 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 ASB 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 E:\FR\FM\04AUR1.SGM 04AUR1 Federal Register / Vol. 88, No. 149 / Friday, August 4, 2023 / Rules and Regulations 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 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: 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. TKELLEY on DSK125TN23PROD with RULES1 (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, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; 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 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. EC120–32A014, Revision 1, dated October 17, 2022. VerDate Sep<11>2014 22:50 Aug 03, 2023 Jkt 259001 (ii) Airbus Helicopters ASB No. EC130– 32A013, Revision 1, dated October 17, 2022. (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 airbus.com/en/ products-services/helicopters/hcare-services/ airbusworld. (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. Issued on July 12, 2023. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023–16555 Filed 8–3–23; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [Docket Number USCG–2023–0256] RIN 1625–AA00 Safety Zone; Ohio River MM 469.5– 470.5 and Licking River MM 0.0 to 0.3, Cincinnati, OH Coast Guard, DHS. Temporary final rule. AGENCY: ACTION: The Coast Guard is establishing a temporary safety zone from Mile Marker 469.5—Mile Marker 470.5 of the Ohio River and from Mile Marker 0.0—Mile Marker 0.3 of the Licking River. This action is necessary to provide for the safety of life on these navigable waters near Cincinnati, OH during the Redbull Flugtag sporting event occurring on August 12, 2023. This safety zone prohibits persons and vessels from transiting through the safety zone unless authorized by the Captain of the Port Sector Ohio Valley or a designated representative. DATES: This rule is effective from noon through 5 p.m. on August 12, 2023. ADDRESSES: To view documents mentioned in this preamble as being available in the docket, go to https:// www.regulations.gov, type USCG–2023– 0256 in the search box and click SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 51699 ‘‘Search.’’ Next, in the Document Type column, select ‘‘Supporting & Related Material.’’ FOR FURTHER INFORMATION CONTACT: If you have questions on this rule, call or email MST1 Julie Thomas, Marine Safety Detachment Cincinnati, U.S. Coast Guard; telephone 513–921–9033, email Julie.A.Thomas@uscg.mil. SUPPLEMENTARY INFORMATION: I. Table of Abbreviations CFR Code of Federal Regulations DHS Department of Homeland Security FR Federal Register NPRM Notice of proposed rulemaking § Section U.S.C. United States Code II. Background Information and Regulatory History The Coast Guard is issuing this temporary rule without prior notice and opportunity to comment pursuant to authority under section 4(a) of the Administrative Procedure Act (APA) (5 U.S.C. 553(b)). This provision authorizes an agency to issue a rule without prior notice and opportunity to comment when the agency for good cause finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under 5 U.S.C. 553(b)(B), the Coast Guard finds that good cause exists for not publishing a notice of proposed rulemaking (NPRM) with respect to this rule because due to timeline requirements, it is impracticable to publish an NPRM and consider the comments because we must establish this safety zone by August 12, 2023. Under 5 U.S.C. 553(d)(3), the Coast Guard finds that good cause exists for making this rule effective less than 30 days after publication in the Federal Register. Delaying the effective date of this rule would be impracticable because immediate action is needed to respond to the potential safety hazards associated with growing public interest for the scheduled event starting August 12, 2023. III. Legal Authority and Need for Rule The Coast Guard is issuing this rule under authority in 46 U.S.C. 70034. The Captain of the Port Sector Ohio Valley (COTP) has determined that potential hazards associated with a sporting event starting August 1, 2023, will be a safety concern for anyone within Mile Marker 469.5—Mile Marker 470.5 of the Ohio River and Mile Marker 0.0—Mile Marker 0.3 of the Licking River. This rule is needed to protect waterway users, vessels, and the marine environment in the navigable waters within the safety zone while the E:\FR\FM\04AUR1.SGM 04AUR1

Agencies

[Federal Register Volume 88, Number 149 (Friday, August 4, 2023)]
[Rules and Regulations]
[Pages 51695-51699]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-16555]


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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; 
Amendment 39-22506; AD 2023-14-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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[[Page 51696]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters Model EC120B, EC130B4, and EC130T2 helicopters. This 
AD was prompted by a report of corrosion detected on certain part-
numbered landing gear assemblies. This AD requires, 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 (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 AD will 
allow an affected part or affected part sub-assembly to be installed on 
a helicopter if certain actions in this AD are accomplished. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective September 8, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 8, 
2023.

ADDRESSES: 
    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 final rule, the European Union Aviation Safety 
Agency (EASA) AD, 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.
    Material Incorporated by Reference:
     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 airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
     You may view this service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110. It is also available at 
regulations.gov under Docket No. FAA-2023-0016.

FOR FURTHER INFORMATION CONTACT: Stephanie Sunderbruch, Aviation Safety 
Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; 
telephone (817) 222-4659; 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 all Airbus Helicopters 
Model EC120B, EC130B4, and EC130T2 helicopters. The NPRM published in 
the Federal Register on January 19, 2023. The NPRM was prompted by EASA 
AD 2022-0053, dated March 23, 2022 (EASA AD 2022-0053), issued by EASA, 
which is the Technical Agent for the Member States of the European 
Union. EASA advises of an occurrence 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.
    In the NPRM, the FAA proposed to require, for helicopters with 
certain part-numbered landing gear assemblies installed, removing and 
cleaning certain parts; visually inspecting certain areas of the 
landing gear tubes for cracks and corrosion; and if any crack, leafing 
corrosion, or exfoliant corrosion is detected, removing certain parts 
from service and replacing with airworthy parts. If any corrosion other 
than leafing or exfoliant corrosion is detected, the NPRM proposed to 
require removing the corrosion.
    The NPRM also proposed to require borescope inspecting the internal 
side of the landing gear tubes for cracks and corrosion. If any crack, 
leafing corrosion, or exfoliant corrosion is detected, the NPRM 
proposed to 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, the NPRM proposed to 
require removing the corrosion.
    The NPRM also proposed, if any corrosion other than leafing or 
exfoliant corrosion is detected during any of the inspections, removing 
all corrosion and measuring the remaining thickness of the landing gear 
tubes and interpreting the results of the measurements. If the 
remaining thickness does not meet the permitted criteria as specified, 
the NPRM proposed to 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, the NPRM proposed 
to require applying a chemical conversion coating and a double layer of 
primer.
    Finally, the NPRM proposed to allow an affected part or affected 
part sub-assembly to be installed on a helicopter, if certain proposed 
requirements of the NPRM have been accomplished.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter, Air Methods.\1\ The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.
---------------------------------------------------------------------------

    \1\ This comment does not appear in the docket because it was 
marked ``proprietary information.''
---------------------------------------------------------------------------

Request To Allow Credit for Previously Issued Service Information

    Air Methods requested that the FAA allow credit for the inspections 
and corrective actions proposed in the NPRM, if these actions were 
performed in accordance with Revision 1 of the service information 
before the effective

[[Page 51697]]

date of the AD. Air Methods added that Figure 4 of the service 
information required by this AD does not properly label ``Zone B'' and 
``Zone C,'' but commented that it considers the service information 
sufficiently adequate to identify the areas.
    The FAA partially agrees. Paragraph (f) of this AD requires 
compliance with this AD within the compliance times specified, unless 
the actions have already been done. Therefore, this AD already permits 
credit for complying with the AD's required actions if those actions 
were performed before the effective date of this AD. However, the FAA 
disagrees with allowing credit for all of this AD's required actions if 
done in accordance with Revision 1 of the service information, before 
the effective date of this AD, because the corrective actions in 
Revision 1 of the service information differ from this AD's corrective 
actions. Operators may request approval of specific corrective actions 
as an alternative method of compliance (AMOC) under the provisions of 
paragraph (h) of this AD.

Comments Regarding Methods To Remove Corrosion

    Air Methods stated that Revision 1 of the service information 
refers to the Standard Practices Manual (MTC) for procedures to remove 
corrosion and that the MTC includes details on important considerations 
when removing corrosion from aluminum parts. Air Methods further stated 
that the MTC contains safe procedures for corrosion removal based on 
service history. Lastly, Air Methods stated that the specific use of 
just a non-metal abrasive pad, as proposed in the NPRM, may not be 
adequate to remove corrosion in severe cases and asserted that 
restricting the corrosion removal procedure does not provide any 
measurable improvement to the level of safety. The FAA infers that Air 
Methods is requesting the FAA not limit corrosion removal to only using 
a non-metal abrasive pad.
    The FAA agrees. The FAA has revised the required actions paragraph 
of this final rule by removing the requirement to use a non-metal 
abrasive pad, and only requires removing all corrosion from all zones.

Conclusion

    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 of the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data, considered the comments received, and determined that air safety 
requires adopting this AD as proposed. Accordingly, the FAA is issuing 
this AD to address the unsafe condition on these helicopters. Except 
for minor editorial changes, and any other changes described 
previously, this AD is adopted as proposed in the NPRM. None of the 
changes increase the economic burden on any operator.

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 
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 ADDRESSES.

Differences Between This 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 AD requires the initial 
inspections to be completed within 13 months after the effective date 
of this 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 AD requires 
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 AD does 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 AD does not 
require reporting.

Interim Action

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

Costs of Compliance

    The FAA estimates that this AD affects 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 AD.
    Removing and cleaning parts, and visually inspecting the external 
surface of each landing gear tube for cracks and corrosion takes 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) takes 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 takes about 2 work-hours and parts 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 
takes 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 takes up to 1 work-hour 
for an estimated cost of $85 per helicopter.
    If required, replacing a landing gear assembly takes about 2 work-
hours and parts cost up to $106,612 for an estimated cost of up to 
$106,782 per replacement.
    If required, replacing a front crossbeam takes about 1 work-hour 
and parts cost up to $9,081 for an estimated cost of up to $9,166 per 
replacement.
    If required, replacing a rear crossbeam takes about 1 work-hour and 
parts 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 
takes about 1 work-hour and parts cost up to $21,447

[[Page 51698]]

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. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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:

2023-14-06 Airbus Helicopters: Amendment 39-22506; Docket No. FAA-
2023-0016; Project Identifier MCAI-2022-00416-R.

(a) Effective Date

    This airworthiness directive (AD) is effective September 8, 
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 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, 
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 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, 
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 ASB 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

[[Page 51699]]

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 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, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 
410, Westbury, NY 11590; telephone (817) 222-4659; email: 
[email protected].

(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. 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, 2701 North Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or 
at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
    (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 July 12, 2023.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2023-16555 Filed 8-3-23; 8:45 am]
BILLING CODE 4910-13-P
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