Airworthiness directives › 2009-18-01
AD 2009-18-01 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
Applicability*9
This AD applies to: (1) CFM International, S.A. turbofan engines with a low-pressure (LP) turbine rear frame, part number (P/N) 338-171-703-0; 338-171-704-0; 338-171-705-0; or 338-171-706-0 installed, as follows: (i) Commercial application CFM56-5B1/P; -5B2/P; -5B3/P; -5B3/P1; -5B4/P; -5B4/P1; -5B5/P; -5B6/P; -5B7/P; -5B8/P; -5B9/P turbofan engines. (ii) Corporate application CFM56-5B6/P and -5B7/P turbofan engines. (2) CFM International, S.A. turbofan engines with an LP turbine rear frame, P/N 338-171-751-0; or 338-171-752-0 installed, on corporate and commercial applications of 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. (3) These engines are installed on, but not limited to, Airbus A318, A319, A320, and A321 series airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Inspection (f) Perform an initial eddy current inspection (ECI) of the LP turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. Service Bulletin (SB) No. CFM56-5B S/B 72-0620, Revision 2, dated December 1, 2008, at the following compliance times: (1) For commercial engine applications, within 25,000 cycles-since-new (CSN) on the LP turbine rear frame. (2) For corporate engine applications, within 19,000 CSN on the LP turbine rear frame. (3) For engines with unknown LP turbine rear frame CSN, within 300 cycles-in-service from the effective date of this AD. Repetitive Inspections (g) Perform repetitive ECIs of the LP turbine rear frame using paragraphs 3.A. through 3.A.(7)(d) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56-5B S/B 72-0620, Revision 2, dated December 1, 2008. Use the inspection intervals in paragraph 3.A.(8) of the Accomplishment Instructions of CFM International, S.A. SB No. CFM56-5B S/B 72-0620, Revision 2, dated December 1, 2008. LP Turbine Rear Frame Removal Criteria (h) Remove LP turbine rear frames from service that have a single crack length of 2.56 inches (65 mm) or longer, or multiple cracks with an accumulated crack length of 2.56 inches (65 mm) or longer. Previous Credit (i) Initial and repetitive inspections done before the effective date of this AD using CFM International, S.A. SB No. CFM56-5B S/B 72-0620, dated May 3, 2007, or SB No. CFM56-5B S/B 72-0620, Revision 1, dated December 20, 2007, comply with the initial and repetitive inspection requirements specified in this AD. Operators must continue performing the repetitive inspections required in paragraph (g) of this AD. Alternative Methods of
Unsafe condition
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.
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