AD 68-15-03

68-15-03 BRITISH AIRCRAFT CORPORATION: Amendment 39-621. Applies to Viscount 744 and 745D airplanes.

Compliance required as indicated, unless already accomplished.

To prevent fatigue damage to the horizontal stabilizer top spar root joint fittings, P/N 70118-231/232 (Pre Mod. D. 3190) and P/N 70118-671/672 (Post Mod. D. 3190), accomplish the following:

(a) Inspect the horizontal stabilizer top spar root joint fittings for cracks in accordance with British Aircraft Corporation PTL No. 264, Issue 2, dated February 12, 1968 (700 Series) or later ARB-approved issue, or an FAA-approved equivalent, as follows:

(1) For fittings which have been involved in 11,500 or more landings on the effective date of this AD, within the next 500 landings, unless already accomplished within the last 2,500 landings, and thereafter at intervals not to exceed 3,000 landings for the last inspection.

(2) For fittings which have been involved in less than 11,500 landings on the effective date of this AD, prior to the accumulation of 12,000 landings and thereafter at intervals not to exceed 3,000 landings from the last inspection.

(b) After each inspection under paragraph (a), replace all cracked fittings with new fittings of the same part number before further flight.

(c) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type.

This superseded Amendment 39-371 (32 F.R. 4306), AD 67-9-5.

This amendment becomes effective August 15, 1968.