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.
Overview
The Airworthiness Directive (AD) AD/CT 58/15 was enacted in 2002 by the Civil Aviation Safety Authority (CASA) as a legislative instrument under subregulation 39.1 (1) of the Civil Aviation Regulations 1998. This directive addresses the identified problem of fatigue cracking in specific rotating parts of General Electric CT58 Series Turbine Engines, which could potentially lead to uncontained engine failure and damage to aircraft. The policy objective behind this AD is to ensure the safety of aircraft by mandating inspections and replacements of these critical engine components. The directive applies to various models of the CT58 Series turboshaft engines and requires actions to be taken according to the specific instructions and compliance periods outlined in the directive, ensuring that the unsafe conditions are rectified in a timely and effective manner.
Scope and Application
The Airworthiness Directive (AD) issued under the Civil Aviation Regulations 1998 targets specific models of General Electric CT58 series turboshaft engines, including CT58-100-2, -110-1, 110-2, -140-1, -140-2, and T58-GE-3/-5/-8F/-10/-100 series engines. The directive applies to these engines irrespective of the aircraft they are installed on, and it mandates that the prescribed inspections and replacements of rotating components must be carried out in accordance with FAA AD 97-19-17, with some exceptions for specific cooling plates. The directive's geographic reach is national, applying across Australia, as it is issued by the Civil Aviation Safety Authority (CASA) delegate. The AD does not exclude any particular entities or industries, but it specifically details the conditions under which the required actions must be taken, including time limits for compliance based on the operational history of the engines. Notably, the directive extends its application through references to subordinate instruments such as FAA AD 97-19-17 and GE Aircraft Engines Service Bulletins, thereby incorporating external regulatory standards into the national framework.
Key Provisions
The Airworthiness Directive (AD) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 requires certain actions to be taken in relation to specified models of General Electric CT58 Series turbine engines (sections 1-4). These actions involve the inspection and replacement of specific rotating components, excluding certain engine cooling plates, in accordance with FAA AD 97-19-17. For cooling plates listed in the directive, replacement is mandatory if they are identified by serial number in GE Aircraft Engines CT58 Service Bulletin 72-188 (CEB-293), Revision 1, dated 15 July 1997. Compliance with the AD must be achieved by adhering to specific timelines: for Requirement 1, the compliance periods stipulated by FAA AD 97-19-17 must be met from the effective date of this AD, and for Requirement 2, actions must be taken at the next exposure or next light overhaul, whichever comes first, but not to exceed 1,000 hours Time in Service (TIS) for engines involved in Repetitive Heavy Lift (RHL) operations, or 2,000 hours TIS for other engines, from the effective date of this AD.
The AD imposes specific obligations on the parties or entities it governs. Firstly, it mandates that the inspection and replacement of rotating components of the specified turbine engines must be carried out in accordance with the FAA AD 97-19-17, excluding certain cooling plates. Secondly, for the cooling plates identified by serial number in GE Aircraft Engines CT58 Service Bulletin 72-188 (CEB-293), Revision 1, dated 15 July 1997, a replacement with serviceable parts is mandatory. Additionally, compliance with the stipulated timelines is required, ensuring that these actions are performed either at the next exposure or next light overhaul, within the specified time limits based on the engine’s operational history.
Failure to comply with the requirements of this AD may result in civil or criminal consequences. The AD does not explicitly state maximum penalties, but non-compliance with Civil Aviation Regulations 1998 can lead to severe repercussions. Civil penalties can include fines, and in more serious cases, criminal penalties may apply, potentially involving imprisonment. The specific consequences will depend on the extent of non-compliance and any resultant harm or risk to aviation safety. Ensuring adherence to the AD is crucial to avoid these potential legal ramifications.