AD 76-10-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 1A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 2A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5BA | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6BA | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7AXC | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8AXC | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 Airplanes |
Unsafe Condition
Corrosion and cracking of the drag brace fittings at the center section spar lower cap could lead to structural failure of the wing.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 50 hours time in service after June 1, 1976, inspect drag brace fittings P/N 4FS.1797(L.H.) and 4FS.1798(R.H.) for corrosion and cracks per Hawker Siddeley Technical News Sheet CT104-230. If cracks or severe corrosion are found, replace with improved P/N 14FS.6069-70 before further flight. For surface corrosion, remove corrosion, protect per FAR 43.13, and reinspect every 100 hours. Reinspections stop after installing improved fittings.
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Compliance Time
within the next 50 hours time in service after the effective date of this AD
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Affected Aircraft
Hawker Siddeley Aviation Limited Model DH-104 airplanes, certificated in all categories not altered in accordance with Hawker Siddeley Aviation Ltd. Modification 1067
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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