Airworthiness Directive · Amendment 39-23071 · Main rotor mast/swashplate
Airbus Helicopters
This AD applies to Airbus Helicopters Model H160-B helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model H160-B helicopters. This AD was prompted by occurrences of premature in-service degradation of the main rotor swashplate assembly (swashplate) bearing. This AD requires repetitively inspecting the swashplate bearing for the presence of grease, and depending on the inspection results, performing corrective actions. This AD requires performing certain operational checks, downloading and analyzing certain data, and, depending on the results of the operational checks, further corrective actions. This AD also requires repetitively performing one flight under specific conditions. Additionally, this AD requires inspecting grease on the swashplate bearing and, depending on the inspection results, applying a certain grease or replacing the grease. This AD allows installing certain part- numbered swashplate bearings provided certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
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 2024-0229, dated December 2, 2024 (EASA AD 2024-0229).
(1) Where EASA AD 2024-0229 requires compliance in terms of flight hours, this AD requires using hours time-in-service (TIS).
(2) Where EASA AD 2024-0229 refers to its effective date or where EASA AD 2024-0229 refers to December 25, 2023 [the effective date of EASA AD 2023-0222-E], this AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0229 specifies “Within 15 flight hours (FH) or before the next cleaning of the swashplate bearing, whichever occurs first after December 25, 2023 [the effective date of EASA AD 2023-0222-E], and, thereafter, before any cleaning of the swashplate bearings or at intervals not exceeding 15 flight hours [FH], whichever occurs first”, this AD requires replacing that text with “Within 15 hours TIS or at the next 50 hour Swashplate Bearing—Functional Test or 300 hour Swashplate Bearing—Lubrication, whichever occurs first after July 17, 2025, the effective date of FAA AD 2025-13-05, and thereafter at intervals not to exceed 15 hours TIS”.
(4) Where the material referenced in paragraph (3) of EASA AD 2024-0229 specifies a check of the Health Usage Monitoring System (HUMS) flight report for reporting of MR SWASHPLATE: EXCEEDANCE in accordance with paragraph 4.3 of the accomplishment procedure of the ASB [Alert Service Bulletin], for this AD, the owner/operator (pilot) holding at least a private pilot certificate may perform only the initial check of the HUMS flight report for the presence of a reported event and must enter compliance into the helicopter maintenance records in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
Note 1 to paragraph (h)(4): The initial check of the HUMS flight report is part of the normal flight report procedures, and the flowcharts are not required to perform the initial check.
(5) Where paragraph (4) of EASA AD 2024-0229 specifies a check of the HUMS vibration overlimit monitoring for reporting of MR SWASHPLATE: UNDEFINED or MR SWASHPLATE: EXCEEDANCE in accordance with the instructions of paragraph 4.4 of the accomplishment procedure of the ASB, this AD requires those actions be accomplished by persons authorized under 14 CFR 43.3 and may not be performed by the owner/operator (pilot) holding at least a private pilot certificate.
(6) Where paragraph (6) of EASA AD 2024-0229 specifies “perform one flight to verify the status of the HUMS vibration overlimit monitoring in accordance with the instructions of paragraph 4.6 of the accomplishment procedure of the ASB”, this AD requires replacing that text with “perform one flight to verify the status of the HUMS vibration overlimit monitoring. The owner/operator (pilot) may perform this flight and verification and must enter compliance with this paragraph into the helicopter maintenance records in accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439”.
(7) Where paragraph (7) of EASA AD 2024-0229 specifies “Where the ASB provides instruction to contact AH [Airbus Helicopters] HUMS support, this AD requires to contact AH for applicable instructions and to accomplish those instructions accordingly”, this AD requires replacing that text with “Accomplish the instructions or corrective actions in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature”.
(8) Where paragraph (8) of EASA AD 2024-0229 specifies “check”, this AD requires replacing that text with “test”.
(9) Where paragraph (8) of EASA AD 2024-0229 refers to any discrepancy, for the purposes of this AD, a discrepancy (pertaining to any functional test [check]) is identified as any abnormal relief or hard point (ratcheting or blocking) felt during rotation at a low constant speed, or any axial play on the installed rotating swashplate. An abnormal relief occurs when the passage of the balls on a spalling of the race can be felt by vibrations in the hands and arms during the rotation. A hard point occurs when there is a ratcheting or blocking of the ball bearing and is felt by a sensation of braking or stopping exerting an additional force during the rotation. Axial play is detected by manually shaking the equipped rotating swashplate vertically from top to bottom (up and down).
Note 2 to paragraph (h)(9): Additional information to identify discrepancies is included in the video specified in Work Card Swashplate Bearing—Functional test 62-32-3001, 340, dated November 4, 2022.
(10) Where paragraph (8) of EASA AD 2024-0229 specifies “replace the main rotor mast assembly in accordance with the instructions of the ASB”, this AD requires replacing that text with “remove the main rotor mast assembly from service in accordance with the instructions of the ASB and replace it with an airworthy main rotor mast assembly”.
(11) Instead of complying with paragraph (10) of EASA AD 2024-0229, for this AD, as of the effective date of this AD, do not lubricate the swashplate bearing with unknown grease or any grease other than Nyco Grease GN10.
(12) Where paragraph (11) of EASA AD 2024-0229 specifies “Before next swashplate bearings lubrication or within 15 FH whichever occurs first after 25 December 2023 [the effective date of EASA AD 2023-0222-E],”, this AD requires replacing that text with “Within 15 hours TIS or at the next 300 hour Swashplate Bearing—Lubrication, whichever occurs first, after the effective date of AD 2025-13-05”.
(13) Where paragraph (12) of EASA AD 2024-0229 specifies “it is determined that the grease used during the last swashplate bearings lubrication is not listed in CM115 type 1, or it is unknown”, this AD requires replacing that text with “unknown grease or any grease other than Nyco Grease GN10 was used”.
(14) Where paragraph (14) of EASA AD 2024-0229 specifies “Inspection, corrective actions, and greasing accomplished on a helicopter before the effective date of this AD in accordance with the instructions of ASB H160-B 62-32-0001 Issue 001 are acceptable for compliance with the requirements of paragraphs (1) to (5), and (7) to (12) of this AD, as applicable, for that helicopter”, this AD requires replacing that text with “Initial inspection, corrective actions, and greasing accomplished on a helicopter before the effective date of AD 2025-13-05 in accordance with the instructions of ASB H160-B 62-32-0001 Issue 001, dated December 19, 2023, are acceptable for compliance with the requirements of paragraphs (1) through (5), and (7) through (12) of EASA AD 2024-0229, as applicable, for that helicopter”.
(15) This AD does not adopt the Remarks section of EASA AD 2024-0229.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
