Airworthiness Directive · Amendment 39-14517 · General Electric Company Model CF6-80C2D1F Turbofan Engines
General Electric Company Model CF6-80C2D1F Turbofan Engines
This AD applies to the following General Electric Company (GE) Model CF6-80C2D1F turbofan engines:
(1) Engines that have not incorporated either Middle River Aircraft Systems (MRAS) Service Bulletin (SB) No. CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, any earlier revision, or original issue, or SB No. CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, or original issue; and
(2) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005, or original issue; and
(3) Engines that have not incorporated MRAS SB No. CF6-80C2 S/B 78-1088, Revision 5, dated May 24, 2005, any earlier revision, or original issue. These engines are installed on, but not limited to, McDonnell Douglas Corporation MD-11 airplanes.
The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) Model CF6-80C2D1F turbofan engines. This AD requires modifying the latching system of the fan reverser. This AD results from 13 reports of released thrust reverser hardware. We are issuing this AD to prevent release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft.
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
If MRAS SB No. CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, any earlier revision, or original issue, or SB No. CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, or original issue, has not been incorporated, do the following:
(1) At the next normally scheduled maintenance period or within 1,200 flight hours time-in-service (TIS) after the effective date of this AD, whichever occurs first, modify the latching system of the fan reverser.
(2) Use the Accomplishment Instructions of either MRAS SB No. CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, or SB No. CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, (but not both SBs) to modify the latch assembly.
If MRAS SB No. CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005, or original issue, has not been incorporated, do the following:
(1) At the next normally scheduled maintenance period or within 6,000 flight hours TIS after the effective date of this AD, whichever occurs first, replace the existing L-shaped support brackets of the upper and lower ends of the upper latch operating cable with improved T-shaped support brackets.
(2) Use the Accomplishment Instructions of MRAS SB CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005, to replace the support brackets.
If MRAS SB No. CF6-80C2 S/B 78-1088, Revision 5, dated May 24, 2005, any earlier revision, or original issue, has not been incorporated, do the following:
(1) At the next normally scheduled maintenance period or within 6,000 flight hours TIS after the effective date of this AD, whichever occurs first, install the improved upper latch of the fan reverser.
(2) Use the Accomplishment Instructions of MRAS SB CF6-80C2 S/B 78-1088, Revision 5, dated May 24, 2005, to install the upper latch.
