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Airworthiness Directive 95-9133

recurring
AD 95-9133 · 1995-04-13 · turbine engine

Airworthiness Directives; General Electric Company (GE) CF6-45 and CF6-50 Series Turbofan Engines

What this AD requires

This amendment revises an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6-45 and CF6-50 series turbofan engines, that currently requires repetitive inspections of high pressure compressor (HPC) rear shafts, and also requires installation of a certain rear shaft flange bolt configuration . This amendment clarifies that engines with a Parts Manufacturer Approval (PMA) bolt part number (P/N) installed must accomplish the inspection requirements of the AD, and allow the installation of the PMA bolt in lieu of the GE bolt. This amendment is prompted by the omission of the PMA bolt P/N from the current AD requirements. The actions specified by this AD are intended to prevent an HPC rear shaft fracture, which could result in an inflight engine shutdown and an uncontained engine failure.

Repetitive inspection. Re-inspect. The next-due date/hours depend on this aircraft’s time in service — a records report computes it from the logbooks.

Which aircraft AD 95-9133 applies to

MakesGeneral Electric
Part-conditional — 9127M58P03, 9079M63P12, 9079M63P15, 9079M63P16, 9079M63P17, 9079M63P18, 9079M63P19.

Applies to GE turbofan engines (specific model not present in the available applicability excerpt, which references only 'each engine identified in the preceding applicability provision'). Requires fluorescent penetrant inspection of listed HPC rear shaft P/Ns per GE Service Bulletin 72-958 Rev 1, on a schedule keyed to cycles since new and whether hook bolts (P/N 9012M99G10, 9114M95G07, 9114M95G10) or turn-around/tapered turn-around bolts (P/N 9249M54P01, 1375M69P01, VCD0016) are installed, to prevent HPC rear shaft fracture and uncontained engine failure.

Whether AD 95-9133 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:

Method of compliance — The specific action taken (inspected, replaced, modified) and to what revision.
Date — When the work was done.
Aircraft time — Total time in service / tach at compliance — how recurring next-due is computed.
Signature & certificate — The A&P/IA who returned it to service, with certificate number.
Is AD 95-9133 complied with on your aircraft?

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.