Airworthiness Directive · Amendment 39-21830 · Main rotor head
Bell Textron Canada Limited Helicopters
Superseded. A later AD replaced this one: AD 2025-09-03. Comply with the one in force.
This AD applies to Bell Textron Canada Limited Model 430 helicopters, having serial number 49001 through 49129, inclusive, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 430 helicopters. This AD was prompted by an in-flight failure of the main rotor (M/R) pitch link clevis (clevis) due to fatigue damage and excessive wear. This AD requires a visual inspection of the M/R 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. Depending on the visual inspection and magnetic particle inspection results, this AD requires removing certain parts from service, replacing certain parts, and performing additional actions. This AD also requires recurring inspections of each M/R clevis and each universal bearing. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, after the effective date of this AD:
(i) Remove and disassemble each M/R pitch link assembly part number (P/N) 430-010-411-105, or P/N 430-010-411-107, but do not remove the inserts from the tube. Visually inspect the M/R clevis P/N 430-010-432-101 and rod end for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. If there is any wear, corrosion or damage, before further flight, remove the affected M/R clevis or the affected rod end from service.
(ii) Visually inspect each universal bearing P/N 212-010-412-001 for binding, stiffness, wear, looseness, excess axial and radial play, and damage, which for the purposes of this inspection may be indicated by distortion, bending, or a crack.
(A) If there is any wear, looseness, excess axial and radial play, or damage and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated 5,000 or less total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 from service and replace with an airworthy part.
(B) If there is any binding or stiffness and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 and M/R clevis from service and replace with airworthy parts.
(C) If there is any wear, looseness, excess axial and radial play, or damage and the M/R pitch link assembly is P/N 430-010-411-105 or P/N 430-010-411-107 and has accumulated more than 5,000 total hours TIS, before further flight, remove the universal bearing P/N 212-010-412-001 from service and replace with an airworthy part.
(iii) Purge grease the bearings of each universal bearing.
(iv) Perform a magnetic particle inspection for any crack on each M/R clevis by following the Accomplishment Instructions, Part I, paragraphs 8. through 8.d., of Bell Alert Service Bulletin 430-21-60, dated July 13, 2021 (ASB 430-21-60). If there is any crack, before further flight, remove each affected M/R clevis from service. If there is no crack, before further flight, perform a selective brush cadmium plating to replace any missing cadmium plating and apply a chromate conversion coating.
(2) Within 50 hours TIS after completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 50 hours TIS:
(i) Using a 10X magnifying glass, visually inspect the neck and threaded area of each M/R clevis for wear, corrosion, and damage, which for the purposes of this inspection may be indicated by distortion, bending, a crack, or damaged M/R clevis threads. Refer to Figure 3 of ASB 430-21-60 for a depiction of the area to inspect on each M/R clevis. If there is any wear, corrosion, or damage, before further flight, remove the affected M/R clevis from service and replace with an airworthy part.
(ii) Perform the actions required in paragraph (g)(1)(iv) of this AD for each M/R clevis.
(3) Within 150 hours TIS after the completion of paragraph (g)(1) of this AD, and thereafter at intervals not to exceed 150 hours TIS, visually inspect and purge grease each universal bearing, by performing the actions as required in paragraphs (g)(1)(ii) and (iii) of this AD.
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.
