AD 98-13-20
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Rolls-Royce Limited | Olympus 593 Mk. 610-14-28 | Airworthiness Directives; Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A., Olympus 593 Series Turbojet Engines |
Unsafe Condition
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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a radiological inspection of the combustion chamber No. 2 outer cooling ring scoop circumferential and axial weld for weld quality, reweld and reinspect if necessary; inspect the combustion chamber No. 2 inner and outer cooling ring web length, mark acceptable components with the letter 'T' adjacent to the part number, and replace unacceptable components with serviceable parts.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
at the next combustor exposure after the effective date of this AD
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Affected Aircraft
Rolls-Royce Limited, 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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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