Airworthiness Directive · Amendment 39-22276 · Turbine engine compressor section
General Electric Company Turbofan Engines
This AD applies to General Electric Company GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P model turbofan engines with an installed high-pressure turbine (HPT) stage 2 disk, forward seal, or stages 6-10 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 2 disk | 2300M84P02 | TMT4AF08 TMT4AF10 TMT4AF11 TMT4AF12 |
| Forward seal | 2417M60P02 or 2759M04P01 | VOLF1931 VOLF1933 VOLF1942 |
| VOLF1977 | ||
| VOLF1993 | ||
| VOLF2014 | ||
| Stages 6-10 compressor rotor spool | 2357M30G02 or 2340M36G01 | GWN0R86N |
| Stages 6-10 compressor rotor spool | 2439M35G01 or 2610M90G01 | GWN0RCKT GWN0R62G GWN0R86J |
| GWN0R5EK | ||
| GWN0R6EH | ||
| GWN0R7K1 | ||
| GWN0R89A | ||
| Stages 6-10 compressor rotor spool | 2439M35G02 | GWN0RA89 GWN0R6K9 |
| GWN0R7G9 | ||
| GWN0R7K4 | ||
| GWN0R752 | ||
| GWN0R98P |
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B and GEnx-2B model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) stage 2 disks, forward seals, and stages 6-10 compressor rotor spools were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of the affected HPT stage 2 disks, forward seals, and stages 6-10 compressor rotor spools. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Before exceeding 600 flight cycles after the effective date of this AD, remove the affected HPT stage 2 disk, forward seal, and stages 6-10 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 2 disk, forward seal, and stages 6-10 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 2 disk, forward seal, or stages 6-10 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, “engines not in service” are 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 2 disk, forward seal, or stages 6-10 compressor rotor spool with a P/N and S/N identified in Table 1 to paragraph (c) of this AD onto any engine.
