Document ID: chunk:federal_register_of_legislation:F2006L00365:body:0
Version: federal_register_of_legislation:F2006L00365
Segment Type: other
Provision Reference: 
Character Range: 0–2325

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

CFE Company Turbine Engines - CFE 738 Series
AD/CFE 738/1  High Pressure Rotor Components  3/2006

Applicability:  CFE Company Model CFE738-1-1B turbofan engines.

                Note 1:  These engines installed on but not limited to the Dassault Aviation Falcon 2000 series aeroplanes.
Requirement:       1. Remove from service certain stage 4 and 5 blisks and impeller aft shafts prior to exceeding the new cyclic life limits as follows, and replace with serviceable parts:
                Nomenclature         Part Number (P/N)  Cyclic Life Limit
                Stage 4 and 5 Blisk  6079T74P08         6,700 cycles since new (CSN)
                Impeller Aft Shaft   6079T80P04         5,100 CSN
                                     6079T80P05         2,160 CSN
                                     6079T80P06         7,100 CSN
                                     6079T80P07         7,100 CSN

                Note 2:  FAA AD 2000-23-12 Amdt 39-11982 refers.
Compliance:     At the limits detailed in Requirement 1 of this AD.
                This Airworthiness Directive becomes effective on 16 March 2006.

Background:  This AD sets new life limits for certain HPC rotor components in all engines.  This amendment is prompted by a reduction in the calculated service life of certain compressor rotor rotating parts to values below currently approved service lives.  The actions specified by this AD are intended to prevent failure of certain HPC rotor components, which could result in an uncontained engine failure and damage to the aeroplane.

James Coyne
Delegate of the Civil Aviation Safety Authority

1 February 2006