| AD Number | 67-03-08 | Status | Active |
| Effective Date | January 28, 1967 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-330 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Vickers-Armstrongs (Aircraft Limited) |
| Model(s) | Viscount 744 Viscount 745D Viscount 810 |
67-03-08 VICKERS: Amdt. 39-330 Part 39 Federal Register December 29, 1966. Applies to Viscount Models 744, 745D, and 810 Series Airplanes.
Compliance required as indicated.
To prevent further failures of the nose landing gear bracing structure, accomplish the following:
(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, visually inspect the nose landing gear bracing structure for damage in accordance with British Aircraft Corporation (BAC) Ltd. Preliminary Technical Leaflet (PTL) No. 104, Issue 3 (800/810 Series), or No. 240, Issue 3 (700 Series), or later ARB-approved issue, and thereafter at intervals not to exceed 350 hours' time in service from the last inspection until modified in accordance with (e).
(b) Within the next 350 hours' time in service after the effective date of this AD, unless already accomplished within the last 1,050 hours' time in service, conduct a radiographic inspection or disassemble and inspect by dye penetrant the upper and lower actuator beam members and center diaphragms of the actuator beam for cracks in accordance with applicable PTL specified in (a) of this AD or later ARB-approved issue and thereafter at intervals not to exceed 1,400 hours' time in service from the last inspection until modified in accordance with (e).
(c) Conduct the visual inspection specified in (a) before further flight and the radiographic or dye penetrant inspection specified in (b) within the next 350 hours' time in service following any flight in which the nose landing gear is subjected to any of the high loadings discussed in the paragraph headed "The Cause" of the applicable PTL specified in (a) of this AD or later ARB-approved issue.
(d) Repair or replace any parts found damaged or cracked during the inspections required by this AD before further flight in accordance with the applicable PTL specified in (a) of this AD or later ARB-approved issue or an equivalent approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region.
(e) The repetitive inspections required by this AD may be discontinued after installation of BAC Modification D3147 (700 Series) or (800/810 Series) or an equivalent approved by the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region.
(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, Middle East Region, 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 that operator.
This directive effective January 28, 1967.