Airworthiness Directive · Amendment 39-11786 · General Electric Company Models CF6-80C2A1/A2/A3/A5/A5F/A8/D1F Turbofan Engines
General Electric Company Models CF6-80C2A1/A2/A3/A5/A5F/A8/D1F Turbofan Engines
General Electric Company (GE) Models CF6-80C2A1/A2/A3/A5/A5F/ A8/D1F turbofan engines, with left hand aft engine mount link assemblies, part numbers (P/Ns) 9348M79G01 or 9348M79G02 installed, or right hand aft engine mount link assemblies, P/Ns 9348M84G01 or 9348M84G02 installed. These engines are installed on but not limited to Airbus Industrie A300 and A310 series, and McDonnell Douglas MD-11 series aircraft.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) Models CF6-80C2A1/A2/A3/ A5/A5F/A8/D1F turbofan engines. This AD requires initial and repetitive visual inspections of left hand and right hand aft engine mount link assemblies for separations, cracks and spherical bearing race migration. Cracked or separated parts must be replaced prior to further flight. If spherical bearing race migration is discovered, an additional borescope inspection for cracks is also required. If no cracks are discovered by the additional borescope inspection, assemblies have a 75-cycle grace period for remaining in service before replacement. Finally, installation of improved aft engine mount link assemblies constitutes terminating action to the inspections of this AD. This amendment is prompted by a report of a fractured left hand aft engine mount link discovered during a scheduled removal of an engine of similar design. The actions specified by the AD are intended to prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure.
To prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure, accomplish the following:
(a) Visually inspect aft engine mount link assemblies for separations, cracks, and spherical bearing race migration. as follows:
(1) Within 400 cycles-in-service (CIS) after the effective date of this AD, if not previously inspected using GE CF6-80C2 Alert Service Bulletin (ASB) 72-A0964, Revision 2, dated January 24, 2000, Revision 1, dated November 12, 1999, or Original, dated April 16, 1999, OR
(2) Within 400 cycles-since-last-inspection (CSLI), if previously inspected using GE CF6-80C2 Alert Service Bulletin (ASB) 72-A0964, Revision 2, dated January 24, 2000, Revision 1, dated November 12, 1999, or Original, dated April 16, 1999,
(3) Inspect in accordance with the Accomplishment Instructions of GE CF6-80C2 ASB 72-A0964, Revision 2, dated January 24, 2000.
(4) If a crack or separation is discovered, prior to further flight:
(i) Remove the cracked or separated aft engine mount link assembly and the attaching hardware from service; AND
(ii) Replace with serviceable parts.
(5) If an aft engine mount link assembly is found with spherical bearing race migration, but no cracks or separations, prior to further flight, EITHER:
(i) Remove the aft engine mount link assembly and the attaching hardware from service and replace with serviceable parts; OR
(ii) Perform an additional borescope inspection for cracks in accordance with paragraph (3)(I) of the Accomplishment Instructions of GE CF6-80C2 ASB 72-A0964, Revision 2, dated January 24, 2000.
(6) If a crack indication is discovered, prior to further flight, remove the cracked aft engine mount link assembly and the attaching hardware from service, and replace with serviceable parts.
(7) If crack indications are not discovered, within 75 CIS after the inspection performed in accordance with paragraph (a)(5)(ii) of this AD, remove the aft engine mount link assembly from service, and replace with serviceable parts.
(8) Attaching hardware may be returned to service after inspection in accordance with paragraph 3(I)(1)(d) or 3(I)(2)(d) of GE CF6-80C2 ASB 72-A0964, Revision 2, dated January 24, 2000, as applicable, only if visual inspection of the removed link shows no cracks or separations.
Note 2: Link attaching hardware includes the nuts, bolts and washers that secure the link.
(b) Thereafter, perform the actions required by paragraph (a) and associated subparagraphs at intervals not to exceed 400 CSLI.
(c) Replace aft engine mount link assemblies with improved aft engine mount link assemblies at the next engine shop visit (ESV), or before accumulating 29,000 engine cycles since new (CSN), whichever occurs first.
(1) Replace in accordance with the Accomplishment Instructions of CF6-80C2 ASB 72-A0989, dated January 19, 2000.
(2) Replace left-hand aft engine mount link assemblies, P/Ns 9348M79G01 or 9348M79G02, with improved left-hand aft engine mount link assemblies, P/N 1846M23G01.
(3) Replace right hand aft engine mount link assemblies, P/Ns 9348M84G01 or 9348M84G02, with improved right hand aft engine mount link assemblies, P/N 9348M84G03.
(d) Installation of improved aft engine mount link assemblies in accordance with paragraph (c) and its subparagraphs constitutes terminating action to the inspections required by paragraphs (a) and (b) of this AD.
