Is AD 2004-04-07 a recurring Airworthiness Directive?

Yes — AD 2004-04-07 requires a repetitive inspection. Next-due depends on the aircraft's time in service.

Airworthiness Directive 2004-04-07

Q: Which aircraft does AD 2004-04-07 apply to?

AD 2004-04-07 applies to General Electric — models CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5. Serial/part conditions may narrow it to specific aircraft.

recurring

Official AD 2004-04-07 · FR doc 04-3798 · 2004-02-26 · turbine engine

Airworthiness Directives; General Electric Company (GE) CF6-80 Series Turbofan Engines

What this AD requires

The FAA is superseding two existing airworthiness directives (ADs) for GE CF6-80 series turbofan engines with certain stage 1 high- pressure turbine (HPT) rotor disks. Those ADs currently require initial and repetitive inspections of certain stage 1 HPT rotor disks for cracks in the bottom of the dovetail slot. This action retains the initial inspection requirement, as a qualification for the mandatory rework procedures for certain disks, and continues repetitive inspections only for the disks for which the rework procedures are not yet defined. This action requires reworking certain disks before further flight. In addition, this AD expands the population of affected engines and removes certain CF6-80E1 series disks from service. This AD results from the manufacturer's investigation and development of a rework procedure that chamfers the aft breakedge of the dovetail slot bottom. We are issuing this AD to detect and prevent cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause 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 2004-04-07 applies to

MakesGeneral Electric

ModelsCF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A8, CF6-80C2A5F, CF6-80C2B1, CF6-80C2B2, CF6-80C2B4, CF6-80C2B6, CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F, CF6-80E1A2, CF6-80E1A4, CF6-80

Part-conditional — 9234M67G22, 9234M67G24, 9234M67G25, 9234M67G26, 9362M58G02, 9362M58G06, 9362M58G07, 9362M58G09.

Applies to the CF6-80 turbofan engine models listed with the specific high pressure turbine (HPT) stage 1 rotor disk part numbers shown in Table 1 of the AD, mapped by model group: CF6-80A/A1/A2/A3 use P/Ns 9234M67G22/G24/G25/G26, 9362M58G02/G06/G07/G09, 9367M45G02/G04/G09; CF6-80C2A1/A2/A3/A5/A8/A5F/B1/B2/B4/B6/B1F/B2F/B4F/B5F/B6F/B6FA/B7F/D1F use P/Ns 1862M23G01, 9392M23G10/G12/G21, 1531M84G02/G06/G08/G10; CF6-80E1A2/A4 use P/N 1639M41P04.

Whether AD 2004-04-07 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 2004-04-07 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.