Airworthiness Directive · Amendment 39-21853 · Turbine engine compression section
General Electric Company Turbofan Engines
This AD applies to General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 model turbofan engines installed on an airplane that has accumulated more than 250 parked days outdoors in the last 24 months within 10 miles (16 km) from a saltwater coastline.
Note 1 to paragraph (c): A “parked day” is 24 consecutive hours with no engine operation.
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines. This AD was prompted by an in-flight shutdown of an engine and subsequent investigation by the manufacturer that revealed a broken variable geometry (VG) actuator rod end caused by corrosion and seizure of the rod end bearing. This AD requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. This AD also requires reporting the results of the inspection to GE. The FAA previously sent an emergency AD to all known U.S. owners and operators of these GE CF34-8C and CF34-8E model turbofan engines and is now issuing this AD to address the unsafe condition on these products.
(1) On one engine installed on an airplane, before accumulating 30 flight hours (FHs) or within 5 calendar days, whichever occurs first after the effective date of this AD, perform an inspection of the master compressor VG actuator, significant item number (SIN) 30401, and slave compressor VG actuator, SIN 30402, in accordance with the Accomplishment Instructions, paragraphs 3.A.(1) and (2), of GE CF34-8C Service Bulletin (SB) 75-0028 R00 (GE CF34-8C SB 75-0028) or GE CF34-8E SB 75-0023 R00 (GE CF34-8E SB 75-0023), both dated November 2, 2021, as applicable to the engine model.
(2) On the other engine installed on the airplane, not inspected as required by paragraph (g)(1) of this AD, before accumulating 350 FHs or within 60 calendar days, whichever occurs first after the effective date of this AD, perform an inspection of the master compressor VG actuator, SIN 30401, and slave compressor VG actuator, SIN 30402, in accordance with the Accomplishment Instructions, paragraphs 3.A.(1) and (2), of GE CF34-8C SB 75-0028 or GE CF34-8E SB 75-0023, as applicable to the engine model.
(3) For engines not in service, before further flight, perform an inspection of the master compressor VG actuator, SIN 30401, and slave compressor VG actuator, SIN 30402, in accordance with the Accomplishment Instructions, paragraphs 3.A.(1) and (2), of GE CF34-8C SB 75-0028 or GE CF34-8E SB 75-0023, as applicable to the engine model.
(4) If the master compressor VG actuator, SIN 30401, or the slave compressor VG actuator, SIN 30402, does not pass any inspection required by paragraphs (g)(1) through (3) of this AD, before further flight, remove the part and replace with a part eligible for installation.
Within 10 days after performing the inspections required by paragraphs (g)(1) through (3) of this AD, in accordance with paragraphs 3.A.(1) and (2), of GE CF34-8C SB 75-0028 or GE CF34-8E SB 75-0023, send your inspection report form, pictures, or report findings to GE at aviation.fleetsupport@ge.com.
