AD 73-19-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bell Helicopter Textron Canada Limited | 206A | Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206A-1 (OH-58A) | Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B | Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters |
| aircraft | Bell Helicopter Textron Canada Limited | 206B-1 | Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters |
Unsafe Condition
Corrosion and cracks in the main rotor blade pitch link tubes, P/N 206-010-330, could result in failure of the pitch link assemblies.
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Required Actions
Inspect the ends and outside diameter surface of each tube for corrosion and cracking using a 3 power or higher magnifying glass. Replace corroded or cracked tubes prior to next flight, except under FAR 21.197. Track main rotor blades after replacement or adjustment. Apply corrosion preventive compound as specified. Adjust inspection intervals upon FAA approval.
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Compliance Time
within 25 hours time in service after the effective date of this A.D., unless previously accomplished and thereafter at intervals not to exceed 50 hours time in service from the last inspection
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Affected Aircraft
Bell Model 206A, 206B, 206A-1 and 206B-1 helicopters equipped with main rotor blade pitch link assemblies P/N 206-010-330 and 206-010-342
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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