Mon, Mar 01, 2004
AD Number
2004-04-07
Manufacturer: General Electric
Subject: Detect and prevent cracks in the bottoms
of the dovetail slots
Product: Engine
Effective Date: 03/12/2004 Recurring: Yes
Supersedes: 2001-10-07, 2003-01-05
Model Applicability: This AD applies to the
General Electric Company (GE) turbofan engine models CF6 -80A,
CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3,
CF6-80C2A5, CF6-80C2A8, CF6-80C2A5F, CF6-80C2B1, CF6-80C2B2,
CF6-80C2B4, CF6-80C2B6, CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F,
CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B6FA, CF6-80C2B7F, CF6-80C2D1F,
CF6-80E1A2 and CF6-80E1A4
Summary: The
FAA is superseding two existing airworthiness directives (ADs) for
GE CF6-80 series turbofan engines with certain stage 1
high-pressure turbine (HPT) rotor disks. Those ADs currently
require initial and repetitive inspections of certain stage 1 HPT
rotor disks for cracks in the bottom of the dovetail slot. This
action retains the initial inspection requirement, as a
qualification for the mandatory rework procedures for certain
disks, and continues repetitive inspections only for the disks for
which the rework procedures are not yet defined. This action
requires reworking certain disks before further flight. In
addition, this AD expands the population of affected engines and
removes certain CF6-80E1 series disks from service. This AD results
from the manufacturer’s investigation and development of a
rework procedure that chamfers the aft breakage of the dovetail
slot bottom. We are issuing this AD to detect and prevent cracks in
the bottoms of the dovetail slots that could propagate to failure
of the disk and cause an uncontained engine failure.
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