Airworthiness Directive · Amendment 39-15085 · General Electric Company (GE) CF6-80C2B Series Turbofan Engines
General Electric Company (GE) CF6-80C2B Series Turbofan Engines
Superseded. A later AD replaced this one: AD 2012-04-05. Comply with the one in force.
This AD applies to General Electric Company (GE) CF6-80C2B1F, -80C2B2F, -80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -80C2B7F, and -80C2B8F turbofan engines with electronic control units (ECUs), installed on Boeing 747 and 767 series airplanes.
The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2B series turbofan engines with electronic control units (ECUs), installed on Boeing 747 and 767 series airplanes. This AD requires installing software version 8.2.Q1 to the engine ECU, which increases the engine's 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. Though the root cause investigation is not yet complete, we believe exposure to ice crystals during flight is associated with these flameout events. We are issuing this AD to provide increased margin to flameout, which will minimize the potential of an all-engine flameout event 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.
For Boeing 767 series airplanes:
(1) All affected engines must have ECU software version 8.2.Q1 installed at next engine shop visit or ECU shop visit, whichever occurs first, but no later than five years after the effective date of this AD.
(2) Within 24 months after the effective date of this AD, at least one of the airplane's affected engines must have ECU software version 8.2.Q1 installed.
(3) Do the software installations specified in paragraphs (g)(1) and (g)(2) of this AD using paragraphs 3.A. through 3.B.(3)(f)4. of the Accomplishment Instructions of GE Service Bulletin No. CF6-80C2 S/B 73-0339, Revision 1, dated April 24, 2007.
For Boeing 747 series airplanes:
(1) All affected engines must have ECU software version 8.2.Q1 installed at next engine shop visit or ECU shop visit, whichever occurs first, but no later than five years after the effective date of this AD.
(2) Do the software installations specified in paragraph (h)(1) of this AD using paragraphs 3.A. through 3.B.(3)(f)4. of the Accomplishment Instructions of GE Service Bulletin No. CF6-80C2 S/B 73-0339, Revision 1, dated April 24, 2007.
(i) After the effective date of this AD:
(1) Once software version 8.2.Q1 is installed in an ECU, reverting to previous versions of ECU software in that ECU is prohibited.
(2) For a period of 24 months after the effective date of this AD, once an ECU containing software version 8.2.Q1 is installed on an engine, that ECU can be replaced with an ECU containing a previous software version. The calendar time requirements in paragraphs (g) and (h) of this AD are not to be exceeded.
(3) After 24 months from the effective date of this AD, once an ECU containing software version 8.2.Q1 is installed on an engine, if the ECU needs to be replaced for any reason, it must only be replaced by another ECU containing version 8.2.Q1 software.
For the purposes of this AD:
(1) Next shop visit of the engine ECU is when the ECU is removed from the engine for overhaul or for maintenance.
(2) Next shop visit of the engine is when the engine is removed from the airplane for maintenance in which a major engine 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 engine shop visit:
(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.
