AD 78-09-04
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 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 2A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 5BA | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 6BA | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 7AXC | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8A | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
| aircraft | de Havilland Aircraft Co., Ltd., The | D.H. 104 Dove Series 8AXC | Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes |
Unsafe Condition
Cracking and possible failure of the lugs of the lower center section main spar wing to fuselage attachment.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within one month after the effective date, inspect the center section main spar bottom boom lugs for cracks using an ultrasonic method per TNS 238 or FAA-approved equivalent. Repeat inspections every two months until a steel lower boom is installed. After six inspections, install a steel lower boom per Modification 779 or FAA-approved equivalent. If cracks are found, replace the boom with a steel one before further flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within one month after the effective date of this AD, unless already accomplished within the last month, and thereafter at intervals not to exceed two months from the last inspection
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Hawker Siddeley Aviation Limited Model DH-104 'Dove' airplanes, all series, except those with Modification 779.
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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