TailplateTailplate
Run a report

Airworthiness Directive 02-31754

recurring
AD 02-31754 · 2002-12-19 · turbine engine

Airworthiness Directives; General Electric Company (GE) CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines

What this AD requires

This amendment supersedes three existing airworthiness directives (AD's), that are applicable to GE CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines. Those AD's currently require specific handling of the GE CF6 series high pressure compressor rotor (HPCR) stage 3-9 spools during a fluorescent penetrant inspection process, and initial and repetitive ultrasonic and eddy current inspections of certain HPCR stage 3-9 spools for cracks. This amendment removes the AD that requires special handling of the spools during fluorescent- penetrant inspection, and adjusts and combines the initial and repetitive inspection requirements, currently listed in two AD's, into one AD for the HPCR stage 3-9 spool. This amendment aligns repetitive inspection requirements with the more stringent initial inspection requirements mandated by AD 2000-16-12, Amendment 39-11868 (65 FR 50623, August 21, 2000) and terminates AD 95-18-14, Amendment 39-9361 (60 FR 46216, September 6, 1995) that is no longer necessary. The actions specified by this AD are intended to prevent cracks, which can cause separation of the HPCR stage 3-9 spool and possible 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 02-31754 applies to

MakesGeneral Electric
ModelsCF6-45, CF6-50, CF6
Part-conditional — 9136M89G02, 9136M89G06, 9136M89G08, 9253M85G02, 9273M14G01, 9331M29G01.

Applies to CF6-45/-50 16-inch billet HPCR stage 3-9 spools: P/N's 9136M89G02 and 9136M89G06 apply to all serial numbers; P/N's 9136M89G08, 9253M85G02, 9273M14G01, and 9331M29G01 apply only to the specific serial numbers listed in Table 2 of the AD (a long SN list beginning MPOE3486... and MPOG series, truncated in source text) -- to detect cracks that could cause spool separation and uncontained engine failure.

Whether AD 02-31754 actually applies to your aircraft (by serial and installed parts) and whether it’s already complied with comes from that aircraft’s records.

Supersession

Supersedes AD 95-18-14.

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 02-31754 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.