| AD Number | 68-03-04 | Status | Active |
| Effective Date | March 07, 1968 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-551 |
| 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 |
68-03-04 VICKERS: Amendment 39-551. Applies to Viscount Models 744, 745D, and 810 Series airplanes.
Compliance required as indicated, unless already accomplished
To detect cracking of the upper and lower torsion link hinge pins of the nose landing gear, accomplish the following:
(a) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with less than 4,000 landings on the effective date of this AD, before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d).
(b) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 4,000 or more landings but less than 9,000 landings on the effective date of this AD, within the next 1,000 landings after the effective date of this AD and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings, comply with paragraph (d).
(c) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 9,000 or more landings on the effective date of this AD, within the next 500 landings or before the accumulation of 10,000 landings, whichever occurs later, and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d).
(d) Remove pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins and inspect for cracks using Magnaflux examination or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 233, Issue 3 (700 Series) and No. 99, Issue 3 (800 Series), or later ARB-approved issued, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region.
(e) If cracked hinge pins are found during the inspections required by paragraphs (a), (b) and (c), before further flight, replace the pins with serviceable pins of the same part number and comply with the inspection requirements of paragraph (a), or replace the pins with Modification D.3045 (700 Series) and FG.1861 (800 Series) pins.
(f) The repetitive inspections required by paragraphs (a), (b) and (c) may be discontinued on those hinge pins replaced by Modification D.3045 (700 Series) and FG.1861 (800 Series) pins.
(g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and 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 amendment becomes effective March 7, 1968.