Airworthiness Directive · Amendment 39-23024 · Main rotor head
Bell Textron Canada Limited Helicopters
Superseded. A later AD replaced this one: AD 2026-13-12. Comply with the one in force.
This AD applies to Bell Textron Canada Limited Model 430 helicopters, serial numbers 49001 through 49129 inclusive, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2021-24- 09, which applied to certain Bell Textron Canada Limited Model 430 helicopters. AD 2021-24-09 required a visual inspection of the main rotor (M/R) pitch link clevis (clevis), rod end, and a certain part- numbered universal bearing, performing a purge grease, and performing a magnetic particle inspection of each M/R clevis, and depending on the inspection results, removing or replacing certain parts and performing additional actions. AD 2021-24-09 also required recurring inspections of each M/R clevis and each universal bearing. Since the FAA issued AD 2021-24-09, the manufacturer has reduced the life limits of the affected parts and introduced new M/R pitch link assemblies by re- identifying the M/R pitch link assemblies that were required to be inspected by AD 2021-24-09. This AD requires similar actions as AD 2021-24-09 but reduces the life limits and requires replacing the M/R pitch link assemblies with re-identified part numbered assemblies. These actions are specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, Transport Canada AD CF-2024-40, dated December 3, 2024 (Transport Canada AD CF-2024-40).
(1) Where Transport Canada AD CF-2024-40 uses the term “new” in the definition of “serviceable part,” this AD requires replacing that text with “new (zero hours time-in-service).”
(2) Where Transport Canada AD CF-2024-40 requires compliance in terms of hours air time, this AD requires using hours time-in-service.
(3) Where Transport Canada AD CF-2024-40 refers to its effective date, this AD requires using the effective date of this AD.
(4) Where any paragraph in Transport Canada AD CF-2024-40 specifies performing a magnetic particle inspection (MPI) “if any suspected defects are found” after performing a detailed visual inspection, this AD requires performing an MPI after performing each detailed visual inspection.
(5) Where Part I paragraph A.8. and Part III paragraph B. of Transport Canada AD CF-2024-40 specify to purge grease the bearings, for this AD those actions are not required if already accomplished when doing Part I paragraph A.7 and Part III paragraph A. of Transport Canada AD CF-2024-40.
(6) Where Part I paragraph A.9. of Transport Canada AD CF-2024-40 specifies to re-identify the main rotor pitch link assemblies and sub-components, for this AD those actions are not required if already accomplished when doing Part I paragraphs A.2. through A.4. of Transport Canada AD CF-2024-40.
(7) Where Part I paragraph B. of Transport Canada CF-2024-40 specifies “replace each component listed in Table 1 of the Bell ASB before exceeding the applicable airworthiness life limit indicated in Table 4-1 of the applicable ALS,” for this AD that requirement does not apply to M/R pitch link assemblies part numbers 430-010-411-109, -109FM, -111, and -111FM.
Although the material referenced in Transport Canada AD CF-2024-40 specifies to submit certain information to the manufacturer, this AD does not require that action.
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.
