2024-26-08: Main Landing Gear

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2024-26-08 Leonardo S.p.a. Helicopters: Amendment 39-22923; Docket No. FAA-2024-2719; Project Identifier MCAI-2024-00664-R. (a) Effective Date This airworthiness directive (AD) is effective January 17, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Leonardo S.p.a. Model AB139 and AW139 helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 3210, Main Landing Gear. (e) Unsafe Condition This AD was prompted by reports of broken main landing gear (MLG) shock absorber piston rod eye ends. The FAA is issuing this AD to address fatigue cracking of the MLG shock absorber piston rod eye ends. The unsafe condition, if not addressed, could result in structural failure of the MLG and consequent damage to the helicopter and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition For the purpose of this AD, a landing is counted anytime the helicopter lifts off into the air and then lands again regardless of the duration of the landing and regardless of whether the engine is shutdown. (h) Requirements Except as specified in paragraph (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with European Union Aviation Safety Agency Emergency AD 2024-0211-E, dated November 7, 2024 (EASA Emergency AD 2024-0211-E). (i) Exceptions to EASA Emergency AD 2024-0211-E (1) Where EASA Emergency AD 2024-0211-E requires compliance in terms of flight hours, this AD requires using hours time-in-service. (2) Where EASA Emergency AD 2024-0211-E refers to its effective date, this AD requires using the effective date of this AD. (3) Where Note 2 of EASA Emergency AD 2024-0211-E specifies procedures for calculating the number of landings if the number of landings since new is not known: if the "FH" (total hours time-in-service) accumulated on the affected part, as defined in EASA Emergency AD 2024-0211-E, cannot be determined, this AD requires using the total hours-time-in-service on the helicopter for that calculation. (4) Where paragraph (1) of EASA Emergency AD 2024-0211-E specifies accomplishing special detailed inspections (SDIs), this AD requires the landing gear in the fully extended position for the SDIs. (5) Where paragraph (1) of EASA Emergency AD 2024-0211-E specifies accomplishing SDIs and the material referenced in EASA Emergency AD 2024-0211-E specifies that the ultrasonic testing inspections must be performed by personnel qualified in accordance with the non-destructive testing requirements of EN4179/NAS410 for Level II or higher, or of an equivalent standard recognized by the competent authority, this AD requires the ultrasonic testing inspections be accomplished by a Level II or Level III inspector certified in the FAA-acceptable standards for nondestructive inspection personnel. Note 1 to paragraph (i)(5): Advisory Circular 65-31B contains examples of FAA-acceptable Level II and Level III qualification standards criteria for inspection personnel doing nondestructive test inspections. (6) Where paragraph (2) of EASA Emergency AD 2024-0211-E states "discrepancies, as identified in the EASB, are," this AD requires replacing that text with "a cracked or broken piston rod eye end, or an ultrasonic testing inspection indication equal to or greater than 80% full screen height (FSH) within the recording gate, as defined in the material referenced in EASA Emergency AD 2024-0211-E, of an upper or lower piston rod eye end, is." (7) Where the material referenced in EASA Emergency AD 2024-0211-E specifies sending parts to Leonardo Helicopters [LH], this AD does not require that action. (8) Where paragraph (3) of EASA Emergency AD 2024-0211-E allows credit for the initial instance of the (ultrasonic testing) inspection required by paragraph (1) of EASA Emergency AD 2024-0211-E, this AD allows that credit if the ultrasonic testing inspection that was previously done was accomplished by a Level II or Level III inspector certified in the FAA-acceptable standards for nondestructive inspection personnel. Note 2 to paragraph (i)(8): Advisory Circular 65-31B contains examples of FAA-acceptable Level II and Level III qualification standards criteria for inspection personnel doing nondestructive test inspections. (9) Where paragraph (5) of EASA Emergency AD 2024-0211-E specifies reporting inspection results to Leonardo within 10 days after accomplishment of any inspection required by paragraph (1) of EASA Emergency AD 2024-0211-E, this AD requires reporting inspection results of each instance of the inspection required by paragraph (1) of EASA Emergency AD 2024-0211-E at the applicable compliance times specified in paragraph (i)(9)(i) or (ii) of this AD. This AD does not require submitting information to Liebherr. (i) For an inspection done on or after the effective date of this AD: Submit the report within 10 days after the inspection. (ii) For an inspection done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD. (10) This AD does not adopt the "Remarks" section of EASA Emergency AD 2024-0211-E. (j) 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 (k)(1) 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. (k) Additional Information (1) For more information about this AD, contact Adam Hein, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946-4116; email: [email protected]. (2) For advisory circular material identified in this AD that is not incorporated by reference, go to faa.gov/regulations_policies/advisory_circulars/index.cfm/go/document.information/documentID/1023552. (l) 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) Emergency AD 2024-0211-E, dated November 7, 2024. (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 the EASA material on the EASA website at ad.easa.europa.eu. (4) 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. (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 December 23, 2024. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-31511 Filed 12-30-24; 11:15 am]BILLING CODE 4910-13-P