| AD Number | 76-10-03 | Status | Active |
| Effective Date | June 01, 1976 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2614 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| 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 |
76-10-03 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-2614. Applies to Model DH-104 airplanes, certificated in all categories not altered in accordance with Hawker Siddeley Aviation Ltd. Modification 1067.
Compliance is required as indicated, unless already accomplished.
To detect corrosion and cracking of the drag brace fittings at the center section spar lower cap, and prevent possible structural failure of the wing, accomplish the following:
(a) Within the next 50 hours time in service after the effective date of this AD, inspect the drag brace fittings, P/N 4FS.1797(L.H.) and 4FS.1798(R.H.) for corrosion and cracks in accordance with paragraph No. 4, entitled "Inspection of Fittings," of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA- approved equivalent.
(b) If a crack or evidence of severe corrosion is found in either drag brace fitting, during an inspection specified in paragraph (a) of this AD, before further flight, replace the drag brace fitting with an improved fitting, P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent.
(c) "Severe corrosion" as used in this AD is internal corrosion that has progressed to a point where there is evidence of corrosion breaking through the exterior surface of the fitting. "Surface corrosion" as used in this AD means corrosion limited to surface pitting. NOTE: The Hawker Siddeley Aviation Ltd. Model DH-104 Maintenance and Repair Manual further defines the terms "severe corrosion" and "surface corrosion."
(d) If, during an inspection specified in paragraph (a) of this AD, no crack is found and evidence of corrosion is found but it is limited to surface corrosion and does not constitute the severe corrosion specified in paragraph (b) of this AD, remove the corrosion, protectthe surface from further corrosion in accordance with FAR 43.13, and re-inspect the drag brace fittings in accordance with the inspection requirements of paragraph (a) of this AD, at intervals not to exceed 100 hours time in service from the last inspection. NOTE: Advisory Circular AC 43.13-1A "Acceptable Methods, Techniques and Practices-Aircraft Inspection and Repair" contains information relating to corrosion protection and removal.
(e) If, during an inspection specified in paragraph (a) of this AD, no crack is found in the fittings, and the fittings are free of evidence of any corrosion, re-inspect the fittings in accordance with the inspection requirements of paragraph (a) of this AD at intervals not to exceed 100 hours time in service from the last inspection.
(f) The repetitive inspections required by paragraphs (d) and (e) of this AD may be terminated upon the installation of the improved fitting P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent.
This amendment becomes effective June 1, 1976.