Airworthiness Directive · Amendment 39-10609 · Rolls-Royce Limited, Aero Division- Bristol, S.N.E.C.M.A., Olympus 593 Series Turbojet Engines
Rolls-Royce Limited, Aero Division- Bristol, S.N.E.C.M.A., Olympus 593 Series Turbojet Engines
Rolls-Royce Limited (R-R), Aero Division-Bristol, S.N.E.C.M.A., Olympus 593 Mk. 610-14-28 turbojet engines, installed on but not limited to British Aerospace/Aerospatiale Concorde series aircraft.
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A, Olympus 593 series turbojet engines. This action requires a radiological inspection of the combustion chamber No. 2 outer cooling ring scoop circumferential and axial weld for weld quality, and reweld and reinspection, if necessary; and an inspection of the combustion chamber No. 2 inner and outer cooling ring web length, marking acceptable components with the letter ``T'' adjacent to the part number, and replacement of unacceptable components with serviceable parts. This amendment is prompted by reports of circumferential cracks at the No. 2 outer and inner rings of the combustor chamber, resulting in a section of the combustion chamber detaching and causing significant ignitor and low pressure turbine damage. The actions specified in this AD are intended to prevent combustion chamber detachment, which could result in an inflight engine shutdown or an engine fire.
