Airworthiness Directive · Amendment 39-22236 · Turbine engine compressor section
General Electric Company Turbofan Engines
This AD applies to General Electric Company GE90-90B, GE90-94B, GE90-110B1, and GE90-115B model turbofan engines with an installed high-pressure turbine (HPT) stage 1 disk, HPT stage 2 disk, or stages 7-9 compressor rotor spool with a part number (P/N) and serial number (S/N) identified in Table 1 to paragraph (c) of this AD.
| Part name | P/N | S/N |
|---|---|---|
| HPT stage 1 disk | 1847M95G04 | GWN0R5K4 |
| HPT stage 2 disk | 1711M47G13 | TMT5N068 |
| HPT stage 2 disk | 1865M14P04 | TMT5P744 |
| TMT5P745 | ||
| TMT5P749 | ||
| TMT5P755 | ||
| TMT5P762 | ||
| Stages 7-9 compressor rotor spool | 2032M23G02 | GWN0R5M5 |
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-90B, GE90-94B, GE90-110B1, and GE90-115B model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) stage 1 disks, HPT stage 2 disks, and stages 7-9 compressor rotor spools were manufactured from powder metal material suspected to contain iron inclusion. This AD requires the replacement of the affected HPT stage 1 disks, HPT stage 2 disks, and stages 7-9 compressor rotor spools. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Before exceeding 400 flight cycles after the effective date of this AD, remove the affected HPT stage 1 disk, HPT stage 2 disk, and stages 7-9 compressor rotor spool from service and replace with a part eligible for installation.
(2) For affected engines not in service, before further flight, remove the affected HPT stage 1 disk, HPT stage 2 disk, and stages 7-9 compressor rotor spool and replace with a part eligible for installation.
(1) For the purpose of this AD, a “part eligible for installation” is any HPT stage 1 disk, HPT stage 2 disk, or stages 7-9 compressor rotor spool with a P/N and S/N not identified in Table 1 to paragraph (c) of this AD.
(2) For the purpose of this AD, “affected engines not in service” are affected engines that are in long-term or short-term storage as of the effective date of this AD.
After the effective date of this AD, do not install an HPT stage 1 disk, HPT stage 2 disk, or stages 7-9 compressor rotor spool with a P/N and S/N identified in Table 1 to paragraph (c) of this AD onto any engine.
