Airworthiness Directive · Amendment 39-22366 · Turbine engine compressor section
General Electric Company Turbofan Engines
This AD applies to General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines with an installed high-pressure compressor (HPC) rotor stage 7-9 spool with part number (P/N) 2032M23G01, P/N 2032M23G02, P/N 2676M00G01, or P/N 2676M00G02, and a serial number listed in paragraph 4., Appendix—A, Table 1 of GE GE90-100 Service Bulletin (SB) 72-0905 R00, dated July 25, 2022 (GE SB 72-0905).
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines. This AD was prompted by a manufacturer investigation which discovered that florescent penetrant inspections (FPI) were not performed on the dovetail pressure face of certain high-pressure compressor (HPC) rotor spools at overhaul. This AD requires FPI of the affected HPC rotor stage 7-9 spool and, depending on the results of the inspection, replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
(1) At the next engine shop visit after the effective date of this AD, perform an FPI of the dovetail pressure face of the affected HPC rotor stage 7-9 spool in accordance with the Accomplishment Instructions, paragraph 3.A.(1)(a) of GE SB 72-0905.
(2) If, during the FPI required by paragraph (g)(1) of this AD, the HPC rotor stage 7-9 spool does not meet the part serviceability criteria in the Accomplishment Instructions, paragraph 3.A.(1)(a) of GE SB 72-0905, before further flight, replace the compressor rotor stage 7-9 spool with a part eligible for installation.
For the purpose of this AD, an “engine shop visit” is the induction of an engine into the shop for maintenance involving separation of pairs of major mating engine flanges, except for the following situations, which do not constitute an engine shop visit:
(i) Separation of engine flanges solely for the purposes of transportation of the engine without subsequent maintenance; or
(ii) Separation of engine flanges solely for the purpose of replacing the fan or propulsor without subsequent maintenance.
