Airworthiness Directive · Amendment 39-16961 · General Electric Company (GE) Turbofan Engines
General Electric Company (GE) Turbofan Engines
This AD applies to GE CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, and CF6-80C2B8F turbofan engines, including engines marked on the engine data plate as CF6-80C2B7F1.
We are superseding an existing airworthiness directive (AD) for all GE CF6-80C2B series turbofan engines. That AD currently requires installing software version 8.2.Q1 to the engine electronic control unit (ECU), which increases the engine's margin to flameout. This new AD requires the removal of the affected ECUs from service. This AD was prompted by two reports of engine flameout events during flight in inclement weather conditions, eight reports of engine in- flight shutdown (IFSD) events caused by dual-channel central processing unit (CPU) faults in the ECU, and four reports of engine flameout ground events. We are issuing this AD to prevent engine flameout or un- commanded engine IFSD of one or more engines, leading to an emergency or forced landing of the airplane.
(1) Remove from service ECUs with part numbers (P/Ns) listed in Table 1 of this AD within 6 months or 450 engine flight cycles after the effective date of this AD, whichever occurs first.
| 1471M63P01 | 1471M63P02 | 1471M63P03 | 1471M63P04 | 1471M63P05 |
| 1471M63P06 | 1471M63P07 | 1471M63P08 | 1471M63P09 | 1471M63P10 |
| 1471M63P11 | 1471M63P12 | 1471M63P13 | 1471M63P14 | 1471M63P15 |
| 1471M63P16 | 1471M63P17 | 1471M63P18 | 1471M63P23 | 1471M63P24 |
| 1471M63P25 | 1471M63P26 | 1471M63P27 | 1471M63P28 | 1471M63P29 |
| 1471M63P30 | 1471M63P31 | 1471M63P32 | 1471M63P33 | 1471M63P34 |
| 1471M63P35 | 1471M63P36 | 1519M89P01 | 1519M89P02 | 1519M89P03 |
| 1519M89P04 | 1519M89P05 | 1519M89P06 | 1519M89P07 | 1519M89P08 |
| 1519M89P09 | 1519M89P10 | 1519M89P13 | 1519M89P14 | 1519M89P15 |
| 1519M89P16 | 1519M89P17 | 1519M89P18 | 1519M89P19 | 1519M89P20 |
| 1519M89P21 | 1519M89P22 | 1519M89P23 | 1519M89P24 | 1519M89P25 |
| 1519M89P26 | 1820M33P01 | 1820M33P02 | 1820M33P03 | 1820M33P04 |
| 1820M33P05 | 1820M33P06 | 1820M33P07 | 1820M33P08 | 1820M33P09 |
(2) Remove from service ECUs with P/Ns 2121M37P01, 2121M37P02, 2121M38P01, 2121M38P02, 2121M41P01 and 2121M41P02 within 14 months or 1,050 engine flight cycles after the effective date of this AD, whichever occurs first.
(3) Remove from service ECUs with P/Ns listed in Table 2 of this AD within 60 months or 4,500 engine flight cycles after the effective date of this AD, whichever occurs first.
| 1471M63P37 | 1471M63P38 | 1471M63P39 | 1471M63P40 | 1471M63P42 |
| 1519M89P27 | 1519M89P28 | 1519M89P29 | 1519M89P30 | 1519M89P32 |
| 1820M33P10 | 1820M33P11 | 1820M33P12 | 1820M33P13 | 1820M33P15 |
| 2121M25P01 | 2121M25P02 | 2121M26P01 | 2121M26P02 | 2121M29P01 |
| 2121M29P02 | 2121M37P03 | 2121M38P03 | 2121M41P03 |
(1) After the effective date of this AD, do not install any ECU P/N listed in Table 1 of this AD onto any airplane.
(2) After the effective date of this AD, do not operate any airplane with more than one ECU P/N 2121M37P02, 2121M38P02, or 2121M41P02 installed.
