Airworthiness Directive · Amendment 39-17203 · General Electric Company Turbofan Engines
General Electric Company Turbofan Engines
This AD applies to:
(1) General Electric Company (GE) GEnx-1B54, GEnx-1B58, GEnx-1B64, GEnx-1B67, GEnx-1B70, GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/P1, GEnx-1B67/P1, GEnx-1B70/P1, GEnx-1B70/72/P1, GEnx-1B70/75/P1, GEnx-1B74/75/P1, and GEnx-1B75/P1 turbofan engines with fan mid shaft (FMS) part number (P/N) 2331M20G02 or P/N 2332M81G01, installed; and
(2) GE GEnx-2B67 and GEnx-2B67B turbofan engines with FMS P/N 2332M33G01, installed.
We are adopting a new airworthiness directive (AD) for General Electric Company GEnx-1B54, GEnx-1B58, GEnx-1B64, GEnx-1B67, GEnx-1B70, GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/P1, GEnx-1B67/P1, GEnx-1B70/P1, GEnx-1B70/72/P1, GEnx-1B70/75/P1, GEnx-1B74/75/P1, GEnx-1B75/P1, GEnx- 2B67, and GEnx-2B67B turbofan engines. This AD requires initial and repetitive ultrasonic inspections (UI) of certain part number (P/N) fan mid shafts (FMS) for cracks. This AD was prompted by a report of an FMS failure and a report of a crack found in another FMS. We are issuing this AD to prevent failure of the FMS resulting in one or more engine failure(s) and possible loss of the airplane.
(1) Perform an initial UI for cracks in the FMS before further flight.
(2) Thereafter, perform repetitive UIs for cracks in the FMS within every 90 days since-last-inspection.
(3) Remove any cracked FMS from service before further flight.
(4) For engines listed in paragraph (c)(1) of this AD, use paragraphs 3.A and 3.B.(1) through 3.B.(9) of the Accomplishment Instructions of GE Service Bulletin (SB) No. GEnx-1B S/B 72-0107, Revision 2, dated September 14, 2012, to do the inspections.
(5) For engines listed in paragraph (c)(2) of this AD, use paragraphs 3.A and 3.B.(1) through 3.B.(9) of the Accomplishment Instructions of GEnx-2B S/B 72-0091, Revision 1, dated September 14, 2012, to do the inspections.
