AD/CT7/8 - Replacement of Aft Stage 2 Turbine Cooling Plates (Cth)

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES

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 39.1 (1) of CAR 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.

General Electric Turbine Engines - CT7 Series

AD/CT7/8 Replacement of Aft Stage 2 Turbine Cooling Plates 4/2002

Applicability: General Electric CT7-5A2, -5A3, -7A and -7A1 engines incorporating part number 6064T07P02 stage 2 aft cooling plates with serial numbers beginning with the letters GFF.

Requirement: (a) Replace stage 2 aft cooling plates P/N 6064T07P02 having serial numbers that begin with the letters GFF with stage 2 aft cooling plates P/N 6064T07P05.

(b) After the effective date of this AD, do not install any stage 2 aft cooling plates P/N 6064T07P02 with serial numbers that begin with the letters GFF.

Note: FAA AD 2002-01-03 refers.

Compliance: Unless previously accomplished, at the next overhaul of the engine or hot section module or within 8000 cycles after the effective date of this AD, whichever occurs first.

This Airworthiness Directive becomes effective on 18 April 2002.

Background: Cracking of a stage 2 turbine aft cooling plate resulted in an uncontained engine failure. This AD has been issued to require removal of certain stage 2 aft cooling plates.