Is AD 95-23-03 a recurring Airworthiness Directive?

Yes — AD 95-23-03 requires a repetitive inspection. Next-due depends on the aircraft's time in service.

Which aircraft does AD 95-23-03 apply to?

AD 95-23-03 applies to General Electric — models CF6-45, CF6-50, CF6-80A, CF6-80C2, CF6. Serial/part conditions may narrow it to specific aircraft.

Airworthiness Directive 95-23-03

recurring

Official AD 95-23-03 · FR doc 95-28527 · 1995-11-21 · turbine engine

Airworthiness Directives; General Electric Company CF6 Series Turbofan Engines

What this AD requires

This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6 series turbofan engines, that currently requires initial and repetitive ultrasonic and eddy current inspections of a certain population of high pressure compressor rotor (HPCR) stage 3-9 spools for cracks. This amendment retains the inspection requirements of the current AD, but would accelerate the inspection schedule for parts affected by the current AD, require initial and repetitive inspections of an expanded population of HPCR stage 3-9 spools installed on GE CF6-45/-50/-80A engines, include HPCR stage 3-9 spools installed on GE CF6-80C2 series engines, and require reporting to the FAA the results of inspections that equal or exceed the reject criteria. This amendment is prompted by recent field experience and the associated engineering investigation, which indicate that cracks are likely to develop in a larger population of parts than previously thought. The actions specified by this AD are intended to prevent HPCR stage 3-9 spool cracking and separation, which can result in an uncontained engine failure and aircraft damage.

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 95-23-03 applies to

MakesGeneral Electric

ModelsCF6-45, CF6-50, CF6-80A, CF6-80C2, CF6

Part-conditional — 1333M66G01, 1333M66G03, 1333M66G07, 1333M66G09, 1781M52P01, 1781M53G01, 1854M95P01, 1854M95P02.

Applies only to engines installed with the listed High Pressure Compressor Stage 3-9 Spools, regardless of prior modification/alteration/repair in the affected area; installed on but not limited to Airbus A300/A310, Boeing 747/767, and McDonnell Douglas DC-10/MD-11 aircraft.

Whether AD 95-23-03 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 95-23-03 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.