Airworthiness Directives; Airbus Helicopters, 26225-26228 [2025-11339]

Download as PDF Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Proposed Rules ddrumheller on DSK120RN23PROD with PROPOSALS1 presented for importation undergo multiple inspections to ensure that communicable animal disease does not enter the United States. Section 93.314(a) requires that horses be accompanied by an original certificate showing that the horse has been inspected on the premises of origin and found free of evidence of communicable disease and exposure to disease during the 60 days preceding exportation. Section 93.304 allows APHIS to request additional inspections or attestations of disease freedom as a condition for issuing a permit for the importation of the horses; if a permitting condition requires inspection within a specific time period, it must still be adhered to. Section 93.306 requires that horses be inspected at the United States port of entry for evidence of communicable disease or exposure thereto. Horses that do not meet these criteria are refused entry. Finally, as noted previously in this document, § 93.301(a) allows the Administrator, upon request, to develop case-specific import protocols, which could include pre-export inspections. For the above reasons, we believe that sufficient safeguards exist to prevent the introduction of communicable animal disease into the United States related to the importation of horses, and that removing the requirement for the additional pre-export inspection established in the final rule will not increase disease risk. We also note that the final rule addressed the issue of sick or injured horses arriving at the port of entry in numerous ways, not only by requiring an additional inspection. For example, we clarified the health certificate requirements in § 93.314 to help us confirm the legitimacy of health certificates and thereby increase compliance, and added additional requirements to help decrease disease risk, such as requiring that a horse was not gelded shortly before importation. We also added shipping container requirements in § 93.302, including measures to ensure that horses are transported safely. These provisions, as well as all other requirements related to the importation of horses into the United States, would remain in place and unchanged by this rule. Executive Order 12866, Executive Order 14192, and Regulatory Flexibility Act This rule does not meet the criteria of a ‘‘significant regulatory action’’ under Executive Order 12866, as amended by Executive Orders 14215 and 13563. Therefore, the Office of Management and Budget (OMB) has not reviewed this rule under those orders. VerDate Sep<11>2014 17:39 Jun 18, 2025 Jkt 265001 This regulation is also not a ‘‘regulatory action,’’ as the meaning of that term is set forth in Executive Order 14192 and implementing guidance. Initial Regulatory Flexibility Act Under the Regulatory Flexibility Act (RFA) (5 U.S.C. 601–612) (as amended by the Small Business Regulatory Enforcement Fairness Act (SBREFA) of 1996; 5 U.S.C. 601 et seq.), agencies must prepare and make available for public comment a regulatory flexibility analysis that describes the effect of the rule on small entities (i.e., small businesses, small organizations, and small government jurisdictions). No regulatory flexibility analysis is required, however, if the head of an agency or an appropriate designee certifies that the rule will not have a significant economic impact on a substantial number of small entities. APHIS has concluded and hereby certifies that this rule will not have a significant economic impact on a substantial number of small entities; therefore, an analysis is not included. This proposed recission rule will only have minor and beneficial impacts on small entities engaged in the importation of equines by removing a requirement that has proven logistically difficult to implement consistently. This proposed recission rule will have a beneficial effect on these small entities, lowering costs related to paperwork and otherwise improving regulatory compliance with the remaining provisions of the regulations. Executive Order 12988 This proposed rule has been reviewed under Executive Order 12988, Civil Justice Reform. If this proposed rule is adopted: (1) All State and local laws and regulations that are inconsistent with this rule will be preempted; (2) no retroactive effect will be given to this rule; and (3) administrative proceedings will not be required before parties may file suit in court challenging this rule. Paperwork Reduction Act This proposed rule contains no new reporting or recordkeeping requirements under the Paperwork Reduction Act of 1995 (44 U.S.C. 3501 et seq.). Further, this proposed rule would reduce the reporting and recordkeeping requirements in 9 CFR 93.314. List of Subjects in 9 CFR Part 93 Animal diseases, Imports, Livestock, Poultry and poultry products, Reporting and recordkeeping requirements. Accordingly, we propose to amend 9 CFR part 93, subpart C, as follows: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 26225 PART 93—IMPORTATION OF CERTAIN ANIMALS, BIRDS, FISH, AND POULTRY, AND CERTAIN ANIMAL, BIRD, AND POULTRY PRODUCTS; REQUIREMENTS FOR MEANS OF CONVEYANCE AND SHIPPING CONTAINERS 1. The authority citation for part 93 continues to read as follows: ■ Authority: 7 U.S.C. 1622 and 8301–8317; 21 U.S.C. 136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22, 2.80, and 371.4. § 93.314 [Amended] 2. Amend § 93.314 by removing paragraph (a)(5), and renumbering paragraphs (a)(6) and (a)(7) as paragraphs (a)(5) and (a)(6), respectively. ■ Done in Washington, DC, this 17th day of June 2025. Michael Watson, Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2025–11395 Filed 6–18–25; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–1108; Project Identifier MCAI–2025–00428–R] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2020–24–07, which applies to certain Airbus Helicopters Model AS350B3, EC130B4, and EC130T2 helicopters. AD 2020–24–07 requires modifying and inspecting the pilot’s and co-pilot’s throttle twist grip (twist grip) for proper operation. Since the FAA issued AD 2020–24–07, Airbus Helicopters developed another modification of the twist grip and additional corrective actions for helicopters already modified. This proposed AD was prompted by reports of the engine remaining in idle when the twist grip was turned from the ‘‘IDLE’’ mode to the ‘‘FLIGHT’’ mode. This proposed AD would retain the actions required by AD 2020–24–07 and mandate an additional modification, which would constitute terminating action for the repetitive inspections. SUMMARY: E:\FR\FM\20JNP1.SGM 20JNP1 ddrumheller on DSK120RN23PROD with PROPOSALS1 26226 Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Proposed Rules This proposed AD would also expand the helicopter applicability, propose additional requirements for certain helicopters, and would prohibit installing affected microswitches or an affected twist grip with the affected microswitch. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this NPRM by August 4, 2025. 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 above 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–2025–1108; 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 European Union Aviation Safety Agency (EASA) material identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. • You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, 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–2025–1108. FOR FURTHER INFORMATION CONTACT: Zain Jamal, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (847) 294– 7264; email: zain.jamal@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or VerDate Sep<11>2014 17:39 Jun 18, 2025 Jkt 265001 arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2025–1108; Project Identifier MCAI–2025–00428–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 the 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 Zain Jamal, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. 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 FAA issued AD 2020–24–07, Amendment 39–21337 (85 FR 78954, December 8, 2020) (AD 2020–24–07), for Airbus Helicopters Model AS350B3 helicopters with an ARRIEL 2B1 engine with the two-channel Full Authority Digital Engine Control (FADEC) and with new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine installed; Model EC130B4 helicopters with an ARRIEL 2B1 engine with the two-channel FADEC and with new twist grip MOD 073773 installed; and Model EC130T2 helicopters with an ARRIEL PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 2D engine installed. AD 2020–24–07 was prompted by MCAI originated by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued EASA AD 2017– 0059, dated April 6, 2017 (EASA AD 2017–0059), to correct an unsafe condition identified, as the microswitches in the engine ‘‘IDLE’’/ ‘‘FLIGHT’’ control system could be affected by the corrosive effects of a saltladen atmosphere. AD 2020–24–07 requires repetitively inspecting the wiring, performing an insulation test, inspecting the pilot and copilot twist grip controls, and testing the pilot and copilot twist grip controls for proper functioning. The FAA issued AD 2020–24–07 to prevent the failure of one of the microswitches, 53Ka, 53Kb, or 65K, which can prevent switching from ‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during autorotation training making it impossible to recover from a practice autorotation and compelling the pilot to continue the autorotation to the ground. This condition could result in unintended touchdown to the ground at a flight-idle power setting during a practice autorotation, damage to the helicopter, and injury to occupants. Actions Since AD 2020–24–07 Was Issued Since the FAA issued AD 2020–24– 07, EASA superseded AD 2017–0059 and issued EASA AD 2023–0133, dated July 5, 2023 (EASA AD 2023–0133). EASA AD 2023–0133 states that Airbus Helicopters developed MOD 074782, introducing a new engine power control assembly with microswitches 53Ka, 53Kb and 65K, and mandating installation of a serviceable assembly, while prohibiting installation of an affected microswitch on any helicopter. EASA AD 2023–0133 also expands the applicability to all serial numbers of Airbus Helicopters Model AS 350 B3, EC 130 B4, and EC 130 T2 helicopters. EASA then superseded AD 2023–0133 and issued EASA AD 2023–0187, dated October 27, 2023 (EASA AD 2023– 0187). EASA AD 2023–0187 states that errors were found in the modification installation procedure and requires amending the modification instructions and additional work for certain helicopters already modified. EASA then superseded AD 2023–0187 and issued EASA AD 2023–0187R1, dated March 20, 2025 (EASA AD 2023– 0187R1) (also referred to as the MCAI), to correct an unsafe condition for all Airbus Helicopters Model AS 350 B3, EC 130 B4, and EC 130 T2 helicopters. The MCAI states that the salt-laden atmospheric condition definition should be re-formulated, adjusting to the less E:\FR\FM\20JNP1.SGM 20JNP1 Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Proposed Rules restrictive description provided in the applicable aircraft maintenance manual. The FAA did not issue an AD corresponding to EASA AD 2023–0133 and EASA AD 2023–0187. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA–2025–1108. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2023– 0187R1, which specifies procedures for modifying the twist grip operational logic on helicopters with MOD 074263 installed. EASA AD 2023–0187R1 also specifies procedures for repetitively inspecting for no marks, residue, or corrosion and testing the ‘‘IDLE’’ and ‘‘FLIGHT’’ controls on the pilot’s and copilot’s twist grips on helicopters with MOD 074699 installed. Additionally, EASA AD 2023–0187R1, specifies procedures for installing MOD 074782 on helicopters if an affected microswitch is installed, which would constitute terminating action for the repetitive inspections. For those helicopters with MOD 074782 installed, EASA AD 2023–0187R1 specifies accomplishing a one-time inspection of the installation of the microswitch assembly of the engine power control. EASA AD 2023–0187R1 also prohibits installing a microswitch having a part number (P/N) T3933–3 or a twist grip containing a microswitch P/N T3933–3 on any helicopter. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. ddrumheller on DSK120RN23PROD with PROPOSALS1 FAA’s Determination These products have been approved by the aviation authority of another country and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with this State of Design Authority, it has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed AD Requirements in This NPRM This proposed AD would retain all the requirements of AD 2020–24–07. This proposed AD would require installing new microswitches. This proposed AD would also require accomplishing the actions specified in the material already described, except for any differences identified as VerDate Sep<11>2014 17:39 Jun 18, 2025 Jkt 265001 exceptions in the regulatory text of this proposed AD. See ‘‘Differences Between this Proposed AD and the MCAI’’ for a discussion of the general differences included in this AD. Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, the FAA proposes to incorporate EASA AD 2023–0187R1 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2023– 0187R1 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Material referenced in EASA AD 2023– 0187R1 for compliance will be available at regulations.gov under Docket No. FAA–2025–1108 after the FAA final rule is published. Differences Between This Proposed AD and the MCAI EASA AD 2023–0187R1 specifies the initial inspections within 10 flight hours or 7 days; this AD requires compliance before the next autorotation training flight, 100 hours time-in-service, or 6 months, whichever occurs first, as the unsafe condition only occurs when transitioning the throttle in-flight from flight to idle and back to flight, such as during a practice autorotation. Additionally, EASA AD 2023–0187R1 specifies installing Airbus Helicopters MOD 074263; this proposed AD would not require the modification as it would not correct the unsafe condition. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 856 helicopters of U.S. registry. Labor costs are estimated at $85 per hour. Based on these numbers, the FAA estimates the following costs to comply with this proposed AD. Inspecting the wiring, performing an insulation test, inspecting the pilot and copilot twist grip controls, and testing the pilot and copilot twist grip controls required by MOD 074699 would take about 4 work-hours, for an estimated cost of $340 per helicopter and $291,040 for the U.S. fleet. Installing MOD 074782 would take about 4 work-hours, for an estimated cost of $340 per helicopter. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 26227 The FAA has included all known costs in its cost estimate. According to the manufacturer, however, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected operators. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA 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 above, I certify that the 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: E:\FR\FM\20JNP1.SGM 20JNP1 26228 Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2020–24–07, Amendment 39–21337 (20 FR 19121, December 8, 2020); and ■ b. Adding the following new airworthiness directive: ■ ■ Airbus Helicopters: Docket No. FAA–2025– 1108; Project Identifier MCAI–2025– 00428–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by August 4, 2025. (b) Affected ADs This AD replaces AD 2020–24–07, Amendment 39–21337 (20 FR 19121, December 8, 2020). (c) Applicability This AD applies to Airbus Helicopters Model AS350B3, EC130B4, and EC130T2 helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 7600, Engine Controls. (e) Unsafe Condition This AD was prompted by reports of the of the engine remaining in idle when the throttle twist grip was turned from the ‘‘IDLE’’ mode to the ‘‘FLIGHT’’ mode. The FAA is issuing this AD to correct the failure of one of the microswitches, 53Ka, 53Kb, or 65K which can prevent the pilot from switching from ‘‘IDLE’’ mode to ‘‘FLIGHT’’ mode during autorotation training making it impossible to recover from a practice autorotation and compelling the pilot to continue the autorotation to the ground. This condition could result in unintended touchdown to the ground at a flight-idle power setting during a practice autorotation, damage to the helicopter, and injury to occupants. ddrumheller on DSK120RN23PROD with PROPOSALS1 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in and in accordance with European Union Aviation Safety Agency AD 2023–0187R1, dated March 20, 2025 (EASA AD 2023–0187R1). (h) Exceptions to EASA AD 2023–0187R1 (1) Where EASA AD 2023–0187R1 refers to its effective date, November 10, 2023 (the effective date of EASA AD 2023–0187, dated October 27, 2023), or July 19, 2023 (the effective date of EASA AD 2023–0133, dated VerDate Sep<11>2014 17:39 Jun 18, 2025 Jkt 265001 July 5, 2023), this AD requires using the effective date of this AD. (2) Where EASA AD 2023–0187R1 refers to April 13, 2017 (the effective date of EASA AD 2017–0059, dated April 6, 2017), this AD requires using January 30, 2019 (the effective date of AD 2018–26–02, Amendment 39– 19532 (83 FR 66093, December 26, 2018)). (3) Where EASA AD 2023–0187R1 refer to flight hours (FH), this AD requires using hours time-in-service. (4) This AD does not adopt paragraphs (1) and (2) of EASA AD 2023–0187R1. (5) Instead of complying with the compliance times in Table 1 in paragraph (3) of EASA AD 2023–0187R1, this AD requires the helicopters identified under the Helicopters in Pre-MOD 074699 Configuration column to accomplish the actions required by paragraph (3) of EASA AD 2023–0187R1 before the next practice autorotation, within 100 hours time-inservice, or 6 months after January 12, 2021 (the effective date of AD 2020–24–07), whichever occurs first. (6) Where Table 2 in paragraph (4), Table 3 in paragraph (7), and Table 4 in paragraph (9) of EASA AD 2023–0187R1 states ‘‘For helicopters which operate or have operated in salt-laden atmospheric conditions,’’ this AD requires replacing that text with ‘‘For helicopters which operate or have operated in salt-laden atmospheric conditions, or if it cannot be determined if a helicopter has been operated in salt-laden atmospheric conditions.’’ (7) Where paragraph (6) of EASA AD 2023– 0187R1 states ‘‘discrepancies are detected,’’ this AD requires replacing that text with ‘‘marks, residue, corrosion, flaky varnish are detected; the values of the insulation test are less than 10 megaOhms; the microswitch closes in the ‘‘IDLE’’ position and does not open as soon as the twist grip is turned to the ‘‘FLIGHT’’ position; or the microswitch is open in the ‘‘FLIGHT’’ position and does not close as soon as the twist grip is turned to the ‘‘IDLE’’ position’’. (8) Where paragraph (9) of EASA AD 2023– 0187R1 states ‘‘any discrepancy,’’ for purposes of this AD, discrepancy is defined as a nut torque that is outside allowable torque limits, or clearance between the support plate assembly and the washers that is not within 01.mm to 0.3 mm. (9) This AD does not adopt the ‘‘Remarks’’ section of EASA AD 2023–0187R1. (i) 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 (j) of this AD and email to: 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (j) Related Information For more information about this AD, contact Zain Jamal, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (847) 294–7264; email: zain.jamal@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023–0187R1, dated March 20, 2025. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: ADs@easa.europa.eu; website: easa.europa.eu. You may find this EASA material on the EASA website at ad.easa.europa.eu. (4) You may view this material at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, 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 material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ ibr-locations or email fr.inspection@nara.gov. Issued on June 16, 2025. Paul R. Bernado, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025–11339 Filed 6–18–25; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2025–1107; Project Identifier MCAI–2024–00784–A] RIN 2120–AA64 Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier Inc. and de Havilland, Inc.) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2022–23–08, which applies to all Viking Air Limited (Viking) Model DHC–3 airplanes. AD 2022–23–08 requires a visual inspection of the stabilizer actuator to confirm that the stabilizer SUMMARY: E:\FR\FM\20JNP1.SGM 20JNP1

Agencies

[Federal Register Volume 90, Number 117 (Friday, June 20, 2025)]
[Proposed Rules]
[Pages 26225-26228]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-11339]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2025-1108; Project Identifier MCAI-2025-00428-R]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2020-24-07, which applies to certain Airbus Helicopters Model AS350B3, 
EC130B4, and EC130T2 helicopters. AD 2020-24-07 requires modifying and 
inspecting the pilot's and co-pilot's throttle twist grip (twist grip) 
for proper operation. Since the FAA issued AD 2020-24-07, Airbus 
Helicopters developed another modification of the twist grip and 
additional corrective actions for helicopters already modified. This 
proposed AD was prompted by reports of the engine remaining in idle 
when the twist grip was turned from the ``IDLE'' mode to the ``FLIGHT'' 
mode. This proposed AD would retain the actions required by AD 2020-24-
07 and mandate an additional modification, which would constitute 
terminating action for the repetitive inspections.

[[Page 26226]]

This proposed AD would also expand the helicopter applicability, 
propose additional requirements for certain helicopters, and would 
prohibit installing affected microswitches or an affected twist grip 
with the affected microswitch. The FAA is proposing this AD to address 
the unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by August 4, 2025.

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 above 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-2025-1108; 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 European Union Aviation Safety Agency (EASA) material 
identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3, 
50668 Cologne, Germany; phone: +49 221 8999 000; email: 
[email protected]; website: easa.europa.eu. You may find this material 
on the EASA website at ad.easa.europa.eu.
     You may view this material at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Parkway, 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-2025-1108.

FOR FURTHER INFORMATION CONTACT: Zain Jamal, Aviation Safety Engineer, 
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (847) 
294-7264; email: [email protected].

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 the ADDRESSES section. Include ``Docket No. FAA-2025-1108; 
Project Identifier MCAI-2025-00428-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 the 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 Zain 
Jamal, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590. 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 FAA issued AD 2020-24-07, Amendment 39-21337 (85 FR 78954, 
December 8, 2020) (AD 2020-24-07), for Airbus Helicopters Model AS350B3 
helicopters with an ARRIEL 2B1 engine with the two-channel Full 
Authority Digital Engine Control (FADEC) and with new twist grip 
modification (MOD) 073254 or with an ARRIEL 2D engine installed; Model 
EC130B4 helicopters with an ARRIEL 2B1 engine with the two-channel 
FADEC and with new twist grip MOD 073773 installed; and Model EC130T2 
helicopters with an ARRIEL 2D engine installed. AD 2020-24-07 was 
prompted by MCAI originated by EASA, which is the Technical Agent for 
the Member States of the European Union. EASA issued EASA AD 2017-0059, 
dated April 6, 2017 (EASA AD 2017-0059), to correct an unsafe condition 
identified, as the microswitches in the engine ``IDLE''/``FLIGHT'' 
control system could be affected by the corrosive effects of a salt-
laden atmosphere.
    AD 2020-24-07 requires repetitively inspecting the wiring, 
performing an insulation test, inspecting the pilot and copilot twist 
grip controls, and testing the pilot and copilot twist grip controls 
for proper functioning. The FAA issued AD 2020-24-07 to prevent the 
failure of one of the microswitches, 53Ka, 53Kb, or 65K, which can 
prevent switching from ``IDLE'' mode to ``FLIGHT'' mode during 
autorotation training making it impossible to recover from a practice 
autorotation and compelling the pilot to continue the autorotation to 
the ground. This condition could result in unintended touchdown to the 
ground at a flight-idle power setting during a practice autorotation, 
damage to the helicopter, and injury to occupants.

Actions Since AD 2020-24-07 Was Issued

    Since the FAA issued AD 2020-24-07, EASA superseded AD 2017-0059 
and issued EASA AD 2023-0133, dated July 5, 2023 (EASA AD 2023-0133). 
EASA AD 2023-0133 states that Airbus Helicopters developed MOD 074782, 
introducing a new engine power control assembly with microswitches 
53Ka, 53Kb and 65K, and mandating installation of a serviceable 
assembly, while prohibiting installation of an affected microswitch on 
any helicopter. EASA AD 2023-0133 also expands the applicability to all 
serial numbers of Airbus Helicopters Model AS 350 B3, EC 130 B4, and EC 
130 T2 helicopters. EASA then superseded AD 2023-0133 and issued EASA 
AD 2023-0187, dated October 27, 2023 (EASA AD 2023-0187). EASA AD 2023-
0187 states that errors were found in the modification installation 
procedure and requires amending the modification instructions and 
additional work for certain helicopters already modified. EASA then 
superseded AD 2023-0187 and issued EASA AD 2023-0187R1, dated March 20, 
2025 (EASA AD 2023-0187R1) (also referred to as the MCAI), to correct 
an unsafe condition for all Airbus Helicopters Model AS 350 B3, EC 130 
B4, and EC 130 T2 helicopters. The MCAI states that the salt-laden 
atmospheric condition definition should be re-formulated, adjusting to 
the less

[[Page 26227]]

restrictive description provided in the applicable aircraft maintenance 
manual. The FAA did not issue an AD corresponding to EASA AD 2023-0133 
and EASA AD 2023-0187.
    You may examine the MCAI in the AD docket at regulations.gov under 
Docket No. FAA-2025-1108.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed EASA AD 2023-0187R1, which specifies procedures 
for modifying the twist grip operational logic on helicopters with MOD 
074263 installed. EASA AD 2023-0187R1 also specifies procedures for 
repetitively inspecting for no marks, residue, or corrosion and testing 
the ``IDLE'' and ``FLIGHT'' controls on the pilot's and copilot's twist 
grips on helicopters with MOD 074699 installed. Additionally, EASA AD 
2023-0187R1, specifies procedures for installing MOD 074782 on 
helicopters if an affected microswitch is installed, which would 
constitute terminating action for the repetitive inspections. For those 
helicopters with MOD 074782 installed, EASA AD 2023-0187R1 specifies 
accomplishing a one-time inspection of the installation of the 
microswitch assembly of the engine power control. EASA AD 2023-0187R1 
also prohibits installing a microswitch having a part number (P/N) 
T3933-3 or a twist grip containing a microswitch P/N T3933-3 on any 
helicopter.
    This material is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

FAA's Determination

    These products have been approved by the aviation authority of 
another country and are approved for operation in the United States. 
Pursuant to the FAA's bilateral agreement with this State of Design 
Authority, it has notified the FAA of the unsafe condition described in 
the MCAI referenced above. The FAA is issuing this NPRM after 
determining that the unsafe condition described previously is likely to 
exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all the requirements of AD 2020-24-
07. This proposed AD would require installing new microswitches. This 
proposed AD would also require accomplishing the actions specified in 
the material already described, except for any differences identified 
as exceptions in the regulatory text of this proposed AD. See 
``Differences Between this Proposed AD and the MCAI'' for a discussion 
of the general differences included in this AD.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA developed a process to use some civil aviation 
authority (CAA) ADs as the primary source of information for compliance 
with requirements for corresponding FAA ADs. The FAA has been 
coordinating this process with manufacturers and CAAs. As a result, the 
FAA proposes to incorporate EASA AD 2023-0187R1 by reference in the FAA 
final rule. This proposed AD would, therefore, require compliance with 
EASA AD 2023-0187R1 in its entirety through that incorporation, except 
for any differences identified as exceptions in the regulatory text of 
this proposed AD. Material referenced in EASA AD 2023-0187R1 for 
compliance will be available at regulations.gov under Docket No. FAA-
2025-1108 after the FAA final rule is published.

Differences Between This Proposed AD and the MCAI

    EASA AD 2023-0187R1 specifies the initial inspections within 10 
flight hours or 7 days; this AD requires compliance before the next 
autorotation training flight, 100 hours time-in-service, or 6 months, 
whichever occurs first, as the unsafe condition only occurs when 
transitioning the throttle in-flight from flight to idle and back to 
flight, such as during a practice autorotation. Additionally, EASA AD 
2023-0187R1 specifies installing Airbus Helicopters MOD 074263; this 
proposed AD would not require the modification as it would not correct 
the unsafe condition.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 856 helicopters of U.S. registry. Labor costs are estimated at 
$85 per hour. Based on these numbers, the FAA estimates the following 
costs to comply with this proposed AD.
    Inspecting the wiring, performing an insulation test, inspecting 
the pilot and copilot twist grip controls, and testing the pilot and 
copilot twist grip controls required by MOD 074699 would take about 4 
work-hours, for an estimated cost of $340 per helicopter and $291,040 
for the U.S. fleet. Installing MOD 074782 would take about 4 work-
hours, for an estimated cost of $340 per helicopter.
    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this 
proposed AD may be covered under warranty, thereby reducing the cost 
impact on affected operators.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA 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 above, I certify that the 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:

[[Page 26228]]

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:
0
a. Removing Airworthiness Directive 2020-24-07, Amendment 39-21337 (20 
FR 19121, December 8, 2020); and
0
b. Adding the following new airworthiness directive:

Airbus Helicopters: Docket No. FAA-2025-1108; Project Identifier 
MCAI-2025-00428-R.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by August 4, 2025.

(b) Affected ADs

    This AD replaces AD 2020-24-07, Amendment 39-21337 (20 FR 19121, 
December 8, 2020).

(c) Applicability

    This AD applies to Airbus Helicopters Model AS350B3, EC130B4, 
and EC130T2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7600, Engine 
Controls.

(e) Unsafe Condition

    This AD was prompted by reports of the of the engine remaining 
in idle when the throttle twist grip was turned from the ``IDLE'' 
mode to the ``FLIGHT'' mode. The FAA is issuing this AD to correct 
the failure of one of the microswitches, 53Ka, 53Kb, or 65K which 
can prevent the pilot from switching from ``IDLE'' mode to 
``FLIGHT'' mode during autorotation training making it impossible to 
recover from a practice autorotation and compelling the pilot to 
continue the autorotation to the ground. This condition could result 
in unintended touchdown to the ground at a flight-idle power setting 
during a practice autorotation, damage to the helicopter, and injury 
to occupants.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in and in accordance 
with European Union Aviation Safety Agency AD 2023-0187R1, dated 
March 20, 2025 (EASA AD 2023-0187R1).

(h) Exceptions to EASA AD 2023-0187R1

    (1) Where EASA AD 2023-0187R1 refers to its effective date, 
November 10, 2023 (the effective date of EASA AD 2023-0187, dated 
October 27, 2023), or July 19, 2023 (the effective date of EASA AD 
2023-0133, dated July 5, 2023), this AD requires using the effective 
date of this AD.
    (2) Where EASA AD 2023-0187R1 refers to April 13, 2017 (the 
effective date of EASA AD 2017-0059, dated April 6, 2017), this AD 
requires using January 30, 2019 (the effective date of AD 2018-26-
02, Amendment 39-19532 (83 FR 66093, December 26, 2018)).
    (3) Where EASA AD 2023-0187R1 refer to flight hours (FH), this 
AD requires using hours time-in-service.
    (4) This AD does not adopt paragraphs (1) and (2) of EASA AD 
2023-0187R1.
    (5) Instead of complying with the compliance times in Table 1 in 
paragraph (3) of EASA AD 2023-0187R1, this AD requires the 
helicopters identified under the Helicopters in Pre-MOD 074699 
Configuration column to accomplish the actions required by paragraph 
(3) of EASA AD 2023-0187R1 before the next practice autorotation, 
within 100 hours time-in-service, or 6 months after January 12, 2021 
(the effective date of AD 2020-24-07), whichever occurs first.
    (6) Where Table 2 in paragraph (4), Table 3 in paragraph (7), 
and Table 4 in paragraph (9) of EASA AD 2023-0187R1 states ``For 
helicopters which operate or have operated in salt-laden atmospheric 
conditions,'' this AD requires replacing that text with ``For 
helicopters which operate or have operated in salt-laden atmospheric 
conditions, or if it cannot be determined if a helicopter has been 
operated in salt-laden atmospheric conditions.''
    (7) Where paragraph (6) of EASA AD 2023-0187R1 states 
``discrepancies are detected,'' this AD requires replacing that text 
with ``marks, residue, corrosion, flaky varnish are detected; the 
values of the insulation test are less than 10 megaOhms; the 
microswitch closes in the ``IDLE'' position and does not open as 
soon as the twist grip is turned to the ``FLIGHT'' position; or the 
microswitch is open in the ``FLIGHT'' position and does not close as 
soon as the twist grip is turned to the ``IDLE'' position''.
    (8) Where paragraph (9) of EASA AD 2023-0187R1 states ``any 
discrepancy,'' for purposes of this AD, discrepancy is defined as a 
nut torque that is outside allowable torque limits, or clearance 
between the support plate assembly and the washers that is not 
within 01.mm to 0.3 mm.
    (9) This AD does not adopt the ``Remarks'' section of EASA AD 
2023-0187R1.

(i) 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 (j) of 
this AD and email 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.

(j) Related Information

    For more information about this AD, contact Zain Jamal, Aviation 
Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; phone: (847) 294-7264; email: [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) European Union Aviation Safety Agency (EASA) AD 2023-0187R1, 
dated March 20, 2025.
    (ii) [Reserved]
    (3) For EASA material identified in this AD, contact EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 
000; email: [email protected]; website: easa.europa.eu. You may 
find this EASA material on the EASA website at ad.easa.europa.eu.
    (4) You may view this material at FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Parkway, 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 material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on June 16, 2025.
Paul R. Bernado,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2025-11339 Filed 6-18-25; 8:45 am]
BILLING CODE 4910-13-P
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