Airworthiness Directive · Amendment 39-15243 · General Electric Company (GE) CF6-80C2D1F Turbofan Engines
General Electric Company (GE) CF6-80C2D1F Turbofan Engines
This AD applies to General Electric Company (GE) CF6-80C2D1F turbofan engines, installed on, but not limited to, McDonnell Douglas Corporation MD-11 series airplanes.
The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2D1F turbofan engines, installed on, but not limited to, McDonnell Douglas Corporation MD-11 series airplanes. This AD requires removing previous software versions from the engine electronic control unit (ECU). Engines with new version software will have increased margin to flameout. This AD results from reports of engine flameout events during flight, including reports of events where all engines simultaneously experienced a flameout or other adverse operation. Although the root cause investigation is not yet complete, we believe that exposure to ice crystals during flight is associated with these flameout events. We are issuing this AD to minimize engine flameout caused by ice accretion and shedding during flight.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
These actions are interim actions due to the on-going investigation, and we may take further rulemaking actions in the future based on the results of the investigation and field experience.
At the next shop visit of the engine or of the ECU, whichever occurs first, and not to exceed 60 months from the effective date of this AD, remove the following software versions from the ECUs:
| Software version | Installed in ECU Part No. |
|---|---|
| (1) 8.5.A | 1851M51P01, 1851M51P02, 1851M52P01, 1851M52P02, 1851M53P01, 1851M53P02 |
| (2) 8.3C | 1471M69P01, 1471M69P02, 1519M91P01 |
| (3) 8.3.D | 1519M91P02 |
| (4) 8.3.E | 1519M91P03, 1519M91P04 |
| (5) 8.3.F | 1519M91P05 |
| (6) 8.3.G | 1519M91P06, 1820M34P01 |
| (7) 8.3.H | 1519M91P07, 1820M34P02 |
| (8) 8.3.J | 1519M91P09, 1519M91P10, 1820M34P04, 1820M34P05 |
For a period of 24 months after the effective date of this AD, once an ECU containing a software version not listed in Table 1 of this AD is installed on an engine, that ECU can be replaced with an ECU containing a previous version of software listed in Table 1.
(i) Once the software version listed in Table 1 of this AD has been removed and new FAA-approved software version is installed in an ECU, reverting to those older software versions in that ECU is prohibited.
(j) After 60 months from the effective date of this AD, use of an ECU with a software version listed in Table 1 of this AD is prohibited.
For the purposes of this AD:
(1) Next shop visit of the ECU is when the ECU is removed from the engine for overhaul or maintenance after the effective date of this AD.
(2) Next shop visit of the engine is when the engine is removed from the airplane for maintenance in which a major flange is disassembled after the effective date of this AD. The following engine maintenance actions, either separately or in combination with each other, are not considered a next shop visit of the engine:
(i) Removal of the upper high pressure compressor (HPC) stator case solely for airfoil maintenance.
(ii) Module-level inspection of the HPC rotor stages 3-9 spool.
(iii) Replacement of stage 5 HPC variable stator vane bushings or lever arms.
(iv) Removal of the accessory gearbox.
(v) Replacement of the inlet gearbox polytetrafluoroethylene seal.
