AD 75-06-03
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
Fatigue cracks in the main rotor pitch link assembly upper and lower clevis threaded shank could result in loss of main rotor control.
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Required Actions
Inspect each main rotor blade pitch link assembly upper and lower clevis threaded shank for fatigue cracks using fluorescent penetrant or equivalent method. Replace any clevis with a cracked shank before further flight. Ensure swashplate outer ring horn bearings (P/N 206-010-469-1) have a breakaway force not exceeding 10 pounds; replace those exceeding the limit prior to further flight.
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Compliance Time
within 10 hours' time in service after March 12, 1975, unless already accomplished
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Affected Aircraft
Bell Model 206A, 206B, 206A-1, and 206B-1 helicopters equipped with pitch link assemblies P/N 206-010-330 or 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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