Is AD 2009-18-01 a recurring Airworthiness Directive?

Yes — AD 2009-18-01 requires a repetitive inspection. Next-due depends on the aircraft's time in service.

Airworthiness Directive 2009-18-01

Q: Which aircraft does AD 2009-18-01 apply to?

AD 2009-18-01 applies to Cfm International, S.A. — models CFM56-5B1/P, CFM56-5B2/P, CFM56-5B3/P, CFM56-5B3/P1, CFM56-5B4/P, CFM56-5B4/P1, CFM56-5B5/P, CFM56-5B6/P. Serial/part conditions may narrow it to specific aircraft.

recurring

Official AD 2009-18-01 · FR doc E9-20284 · 2009-08-27 · turbine engine

Airworthiness Directives; CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P; -5B1/3; -5B2/3; -5B3/3; -5B4/3; -5B5/3; -5B6/3; -5B7/3; -5B8/3; -5B9/3; -5B3/3B1; and -5B4/3B1 Turbofan Engines

What this AD requires

The FAA is adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/ P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P; -5B1/3; -5B2/3; -5B3/3; - 5B4/3; -5B5/3; -5B6/3; -5B7/3; -5B8/3; -5B9/3; -5B3/3B1; and -5B4/3B1 turbofan engines. This AD requires initial and repetitive eddy current inspections (ECIs) of certain part number (P/N) low-pressure (LP) turbine rear frames. This AD results from a refined lifing analysis by the engine manufacturer that shows the need to identify initial and repetitive inspection thresholds for inspecting certain LP turbine rear frames. We are issuing this AD to detect low-cycle-fatigue cracks in the LP turbine rear frame, which could result in an engine separating from the airplane, causing damage to, and possibly leading to loss of control of the airplane.

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 2009-18-01 applies to

MakesCfm International, S.A.

ModelsCFM56-5B1/P, CFM56-5B2/P, CFM56-5B3/P, CFM56-5B3/P1, CFM56-5B4/P, CFM56-5B4/P1, CFM56-5B5/P, CFM56-5B6/P, CFM56-5B7/P, CFM56-5B8/P, CFM56-5B9/P, CFM56-5B1/3, CFM56-5B2/3, CFM56-5B3/3, CFM56-5B4/3, CFM56-5B5/3, CFM56-5B6/3, CFM56-5B7/3, CFM56-5B8/3, CFM56-5B9/3, CFM56-5B3/3B1, CFM56-5B4/3B1, CFM56

Part-conditional — 338-171-703-0, 338-171-704-0, 338-171-705-0, 338-171-706-0, 338-171-751-0, 338-171-752-0.

Applies only to engines with a low-pressure (LP) turbine rear frame installed: P/N 338-171-703-0, -704-0, -705-0, or -706-0 on commercial CFM56-5B1/P through -5B9/P and corporate -5B6/P and -5B7/P engines; or P/N 338-171-751-0 or -752-0 on corporate and commercial CFM56-5B1/P through -5B9/P and -5B1/3 through -5B9/3, -5B3/3B1, and -5B4/3B1 engines.

Whether AD 2009-18-01 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 2009-18-01 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.