| AD Number | 64-13-01 | Status | Active |
| Effective Date | June 26, 1964 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | Federal Register: May 27, 1964 | ||
| Manufacturer(s) | de Havilland Aircraft Co., Ltd., The |
| Model(s) | D.H. 104 Dove Series 1A D.H. 104 Dove Series 2A D.H. 104 Dove Series 5A D.H. 104 Dove Series 5BA D.H. 104 Dove Series 6A D.H. 104 Dove Series 6BA D.H. 104 Dove Series 7A D.H. 104 Dove Series 7AXC D.H. 104 Dove Series 8A D.H. 104 Dove Series 8AXC |
64-13-01 de HAVILLAND: Amdt. 739, Part 507, Federal Register May 27, 1964. Applies to All Model 104 "Dove" Aircraft.
Compliance required as indicated.
To prevent overheating of the electric cables in the cockpit and fuselage nose areas caused by a high resistance ground at the main ground post, accomplish either (a) or (b) as follows:
(a) If the main ground (earth) has not been removed and inspected within 12 months prior to January 8, 1964, accomplish the provisions of paragraph (c) within the next 200 hours' time in service after the effective date of this AD unless already accomplished.
(b) If the main ground (earth) has been removed and inspected within the 12 months prior to January 8, 1964, accomplish the provisions of paragraph (c) within the next 300 hours' time in service after the effective date of this AD unless already accomplished.
(c) Dismantle, clean, inspect, and reassemble the main ground (earth) assembly in the forward fuselage in accordance with the method described in Hawker Siddeley Aviation, de Havilland Division, T.N.S. CT (104) No. 186, or an equivalent method approved by the Chief, Aircraft Certification Division, Europe, Africa, and Middle East.
This directive effective June 26, 1964.