| AD Number | 72-10-01 | Status | Active |
| Effective Date | May 31, 1972 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-1441 |
| 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 |
72-10-01 HAWKER SIDDELEY AVIATION: Amendment 39-1441. Applies to Hawker Siddeley de Havilland Model DH-104 "Dove" airplanes.
Compliance is required as indicated.
To detect cracks in the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, accomplish the following:
(a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished within the last 2,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service from the last inspection, inspect the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, for cracks, using a dye penetrant method, in accordance with Hawker Siddeley Technical News Sheet Series: CT(104) No. 219, Issue 1, dated October 19, 1970, or later ARB-approved issue or FAA-approved equivalent. If no cracks are found, visually inspect the upper radiused surface of the upper arm of the rudder control reversal lever for marks or other evidence of mechanical damage.
(b) If a crack is found during an inspection required by paragraph (a), before further flight replace the rudder control pedal reversal lever, P/N 4CF.767A, with a new part of the same part number and continue to inspect in accordance with paragraph (a).
(c) If marks or other evidence of mechanical damage are found during an inspection required by paragraph (a), before further flight smoothly blend out the marks and renew the protective treatment, using selenious acid treatment, or an FAA-approved equivalent, and repaint the part. After refitting the part, continue to inspect in accordance with paragraph (a).
This amendment is effective May 31, 1972.