Airworthiness Directive · Amendment 39-23045 · Turbine section
General Electric Company Engines
This AD applies to General Electric Company (GE) Model CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines with an installed high-pressure turbine (HPT) stage 1 disk or HPT stage 2 disk having 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 | 1863M36G06 | GWN0GP27. |
| HPT stage 1 disk | 1863M36G06 | GWN0GPM8. |
| HPT stage 1 disk | 1863M36G06 | GWN0GP26. |
| HPT stage 1 disk | 1863M36G06 | TMT5SW61. |
| HPT stage 1 disk | 1863M36G06 | TMT5SW59. |
| HPT stage 1 disk | 1863M36G06 | TMT5SW64. |
| HPT stage 1 disk | 1863M36G06 | TMT5SW82. |
| HPT stage 1 disk | 1863M36G06 | GWN0GPMG. |
| HPT stage 2 disk | 1778M72P05 | BTB77100. |
| HPT stage 2 disk | 1778M72P05 | MUNLD123. |
| HPT stage 2 disk | 1778M72P05 | MUNLD122. |
| HPT stage 2 disk | 1778M72P05 | MUN5B794. |
| HPT stage 2 disk | 1778M72P05 | BTB77102. |
The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines. This AD was prompted by a manufacturer investigation that revealed certain high-pressure turbine (HPT) stage 1 and HPT stage 2 disks were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of affected HPT stage 1 and HPT stage 2 disks with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Before further flight after the effective date of this AD, remove any affected HPT stage 1 disk having P/N 1863M36G06 and S/N GWN0GP27 from service and replace with a part eligible for installation.
(2) Before further flight after the effective date of this AD, remove any affected HPT stage 2 disk having P/N 1778M72P05 and S/N BTB77100 from service and replace with a part eligible for installation.
(3) For affected HPT stage 1 disks identified in table 1 to paragraph (c) of this AD that are not included in paragraph (g)(1) of this AD, at the next piece part exposure or before the affected HPT stage 1 disk exceeds 8,600 cycles since new (CSN), whichever occurs first after the effective date of this AD, remove the affected HPT stage 1 disk from service and replace with a part eligible for installation.
(4) For affected HPT stage 2 disks identified in table 1 to paragraph (c) of this AD that are not included in paragraph (g)(2) of this AD, at the next piece part exposure or before the affected HPT stage 2 disk exceeds 12,000 CSN, whichever occurs first after the effective date of this AD, remove the affected HPT stage 2 disk from service and replace with a part eligible for installation.
For the purpose of this AD:
(1) A “part eligible for installation” is any HPT stage 1 disk or HPT stage 2 disk that does not have a P/N and S/N identified in table 1 to paragraph (c) of this AD.
(2) A “piece part exposure” is when the affected part is removed from the engine and completely disassembled.
For affected HPT stage 1 disks having greater than 8,550 CSN on the effective date of this AD, the replacement required by paragraph (g)(3) of this AD may be deferred up to 50 flight cycles after the effective date of this AD.
