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 - CT58 Series

AD/CT 58/15 Inspection/Replacement of Rotating Parts 5/2002

DM

Applicability: Models CT58-100-2, -110-1, 110-2, -140-1, -140-2, and T58-GE-3/-5/-8F/-10/-100

series turboshaft engines

Requirement: 1. Inspect/replace the various rotating components in accordance with FAA AD 97-19-17 with the exception of engine cooling plates:

• Stage 1 front cooling plates, P/N: 37C300055P101;
• Stage 2 front cooling plates, P/N: 3000T88P02; and
• Stage 2 aft cooling plates, P/N: 30002T27P01.

2. For cooling plates listed in Requirement 1 above, and identified by serial number in GE Aircraft Engines CT58 Service Bulletin (SB) 72-188 (CEB-293), Revision 1, dated 15 July, 1997, replace with serviceable parts.

Note 1: FAA AD 97-21-08 refers to Requirement 2 of this Airworthiness Directive.

Note 2: GE Aircraft Engines Service Bulletins (SB) (CT58): A72-162 (CEB- 258), Revision 8, dated 16 June, 1997; 72-181 (CEB-284) Revision 2, dated 15

July1997, and 72-188 (CEB-293) Revision 1, dated 15 July, 1997 refer.

Compliance: For Requirement 1: Unless already accomplished, at the compliance periods required by FAA AD 97-19-17 from the effective date of this Airworthiness Directive.

For Requirement 2: Unless already accomplished, at the next exposure, or next light overhaul, whichever occurs first, but not to exceed 1,000 hours Time in Service (TIS) for engines installed on aircraft that have engaged in Repetitive Heavy Lift (RHL) operations, or 2,000 hours TIS for engines installed on aircraft that have never engaged in RHL operations, in accordance with CT58 Service Bulletin (SB) 72-188 (CEB-293) Revision 1, dated 15 July, 1997 from the effective date of this Airworthiness Directive.

General Electric Turbine Engines - CT58 Series

AD/CT 58/15 (continued)

Note: For the purpose of this Airworthiness Directive, the following definitions apply:

a)        RHL operation is defined as performing more than 10 lift-carry-drop cycles per hour TIS without landing, or more than 10 takeoffs and landings per hour TIS;

b)        Light overhaul is defined as scheduled engine maintenance that allows the engine to continue in service until scheduled major overhaul time is reached.

This Airworthiness Directive becomes effective on 27 March 2002

Background: This Airworthiness Directive (AD) combines two FAA AD’s that were raised after concerns with fatigue cracking of specific engine rotating parts which in the event of failure could cause an uncontained engine failure and damage to the aircraft. In the event of cooling plate fracture, this could cause an un-contained engine failure and an in-flight engine shutdown.

Eugene Paul Holzapfel

Delegate of the Civil Aviation Safety Authority 19 March 2002

The above AD is notified in the Commonwealth of Australia Gazette on 27 March 2002.