Airworthiness Directive · Amendment 39-9346 · General Electric Company CF6 Series Turbofan Engines
General Electric Company CF6 Series Turbofan Engines
Superseded. A later AD replaced this one: AD 2006-12-24. Comply with the one in force.
General Electric Company (GE) CF6-45/-50 series turbofan engines installed on, but not limited to, Airbus A300 series, Boeing 747 series, and McDonnell Douglas DC-10 series aircraft. Note: 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 use the authority provided in paragraph (d) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD.
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-45/-50 series turbofan engines, that requires an initial and repetitive on-wing visual inspection of the side links of the five-link forward mount assembly for cracks, and replacement of the side links and pylon attachment bolts, and inspection of the fail-safe bolt and platform lug, if the side links are found cracked. This AD also requires a shop-level refurbishment of the side links as a terminating action to the on-wing inspection program. This amendment is prompted by four reports of cracked side links detected during routine engine shop visits. The actions specified by this AD are intended to prevent a side link fracture, which could result in the failure of the second side link, or the forward engine mount pylon attachment bolts, and possible separation of the engine from the aircraft.
