| AD Number | 66-05-02 | Status | Active |
| Effective Date | February 27, 1966 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-185 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | Federal Register: January 28, 1968 | ||
| 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 |
66-05-02 HAWKER SIDDELEY: Amdt. 39-185, Part 39, Federal Register January 28, 1968. Applies to de Havilland Model 104 Dove Series Airplanes.
Compliance required within 150 hours' time in service after the effective date of this AD.
As a result of cracking of eye ends used in the rudder and elevator trim tab connecting rod assemblies, accomplish the following unless already accomplished.
(a) Remove eye ends, P/N's CM.2A and CM.2B, and inspect for cracks visually or by use of other FAA-approved methods.
(b) Replace cracked parts with uncracked parts of the same part number before further flight.
(Hawker Siddeley Aviation, de Havilland Division T.N.S. Dove (104) Series CT (104) No. 187 or later ARB-approved issues cover this same subject).
This directive effective February 27, 1966.