AD/CFE 738/3 High Pressure Turbine Stage 1 Aft Cooling Plate and Stage 2 Disc (Cth)

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 738/3 High Pressure Turbine Stage 1 Aft
Cooling Plate and Stage 2 Disc 3/2006

Applicability:

CFE Company model CFE738-1-1B turbofan engines with high pressure turbine (HPT) stage 1 aft cooling plates, part number (P/N) 6083T38P07, and HPT stage 2 disks, P/N's 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, and 6083T92P11, installed.

Note 1:  These engines are installed on, but not limited to Dassault-Breguet Falcon 2000 series aeroplanes.

Requirement:

1.    Replace the HPT stage 1 aft cooling plate P/N 6083T38P07.

2.    Replace HPT stage 2 disks, P/N's 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, and 6083T92P11.

3.    Do not install any HPT stage 1 aft cooling plate, P/N 6083T38P07, that exceeds 3,500 CSN.

4.    Do not install any HPT stage 2 disk, P/N 6083T92P06, 6083T92P07, 6083T92P08, 6083T92P10, or 6083T92P11, that exceeds 2,700 CSN.

Note 2:  FAA AD 2002-09-10 Amdt 39-12743 refers.

Compliance:

1.    At or before the cooling plate accumulates 3,500 cycles-since-new (CSN).

2.    At or before the disk accumulates 2,700 CSN.

3.    After the effective date of this AD.

4.    After the effective date of this AD.

This Airworthiness Directive becomes effective on 16 March 2006.

Background: This AD requires replacing the HPT stage 1 aft cooling plate and HPT stage 2 disks at or before they reach new reduced life cycle limits.  This is prompted by analysis of the existing life cycle limits by the engine manufacturer.  The actions specified by this AD are intended to prevent failure of the HPT stage 1 aft cooling plate and HPT stage 2 disks, 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