62-12-06 VICKERS: Amdt. 445 Part 507 Federal Register May 29, 1962. Applies to All Viscount Models 745D and 810 Series Aircraft.
Compliance required as indicated.
Failure of a main landing gear uplock mechanism resulted in inability to extend the gear. Inspection revealed that a cotter pin, which secures the connecting links to the center spindle, was missing. This permitted the clevis pin to drop into an inspection hole, and prevented the mechanism from moving to the unlock position. To prevent further cases of this malfunction, the following are required:
(a) Within the next 150 hours' time in service after the effective date of this AD, unless already accomplished within the past 100 hours' time in service and at periods thereafter not exceeding 250 hours' time in service from the last inspection, visually inspect the main landing gear uplock mechanisms to ensure that the clevis pin is in the correct position and secured with a cotter pin that is not worn or damaged. Prior to further flight, properly reinstall clevis pins that have worked loose or shifted and replace worn or damaged cotter pins.
(b) The inspections required by this airworthiness directive may be discontinued after replacement of the perspex covers with metal plates installed in accordance with Vickers Preliminary Technical Leaflet No. 236 Issue 3, Modification D.3049 (for 700 Series aircraft), or PTL No. 102 Issue 3 Mod. FG.1873 (for the 800 Series aircraft), or an FAA approved equivalent modification.
(c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, International Division, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
This directive effective June 29, 1962.