Airworthiness Directive 2000-16-12
one-timeAirworthiness Directives; General Electric Company CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines
What this AD requires
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-45, -50, -80A, - 80C2, and -80E1 turbofan engines with certain high pressure compressor rotor (HPCR) stage 3-9 spools installed. This action requires initial ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This amendment is prompted by an uncontained failure of an HPCR 3-9 spool. The actions specified in this AD are intended to detect cracks which can cause separation of the HPCR stage 3-9 spool and result in an uncontained engine failure.
Which aircraft AD 2000-16-12 applies to
Applies only to engines with a high pressure compressor rotor (HPCR) stage 3-9 spool of one of the listed part numbers installed; specific P/N subsets apply per engine model (CF6-45/-50, CF6-80A, CF6-80C2, CF6-80E1 each has its own P/N list in the source AD). Installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series airplanes.
Whether AD 2000-16-12 actually applies to your aircraft (by serial and installed parts) and whether it’s already complied with comes from that aircraft’s records.
How AD compliance is recorded
A valid compliance record (14 CFR 43.9) states:
Tailplate reads a tail number’s logbooks and matches every applicable AD — including this one — to its compliance evidence, with recurring next-due dates computed.
Look up a tail number →Read the full directive (Federal Register)Applicability is derived from the FAA directive corpus and is advisory, not a legal airworthiness determination. Compliance is established only from an aircraft’s actual records.