Airworthiness directives › 2007-11-18
AD 2007-11-18 Airworthiness Directives; General Electric Company CF6-50C Series Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF6-50C, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2F, and CF6-50C2R turbofan engines, with a forward fan stator case, part number (P/N) 9064M53G04, GO5, G06, G07, G08, G09, G10, G12, or G13, or P/N 9173M37G01, G02, G03, G04, G05, or G06 installed. These engines are installed on, but not limited to, Airbus A300, McDonnell Douglas DC-10 series, and DC-10-30F (KC-10A, KDC-10) airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) At the next engine shop visit after the effective date of this AD, but no later than June 30, 2010, rework the forward fan stator case and install the fan module secondary containment shield. (1) For engines on Airbus 300 series airplanes, use paragraph 3, Accomplishment Instructions, of GE Service Bulletin (SB) No. CF6-50 S/B 72-0985, Revision 2, dated March 21, 2007, to do the rework and installation. (2) For engines on McDonnell Douglas airplanes, use paragraph 3, Accomplishment Instructions, of GE SB No. CF6-50 S/B 72-0986, Revision 2, dated March 21, 2007, to do the rework and installation. (g) The rework and installation specified in paragraphs (f)(1) through (f)(2) of this AD can also be done on-wing. Previous Credit (h) Previous credit is allowed for fan stator cases reworked and containment shields installed using GE SB No. CF6-50 S/B 72- 0985, dated December 2, 1991 or Revision 1, dated September 15, 1998, or GE SB No. CF6-50 S/B 72-0986, dated December 2, 1991 or Revision 1, dated September 15, 1998, before the effective date of this AD. Alternative Methods of
Unsafe condition
This AD results from reports of uncontained fan blade failures causing damage and separation of airplane hydraulic lines. We are issuing this AD to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control.
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