AD 69-25-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 1A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 2A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5BA | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6BA | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7AXC | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8A | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8AXC | Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes |
Unsafe Condition
Fatigue failure of the aileron lever P/N 4 WA.315 due to cracks at the lugs for connecting rod attachment and in the counterbored portion receiving the mass balance arm.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Visually inspect the aileron lever P/N 4 WA.315 for cracks at specified locations within 50 hours after AD effective date, and every 50 hours thereafter. If cracks found, use dye penetrant or approved method to verify and install new forged lever P/N 4 WA.491. If no cracks, install new lever within 1,000 hours after AD effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within 50 hours' time in service after the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series airplanes with aileron lever P/N 4 WA.315 installed
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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