AD/CF6/26 - Stage 11 to 13 Compressor Spool Inspection

Overview

The Civil Aviation Regulations 1998, under PART 39 - 106, introduced specific Airworthiness Directives to address safety concerns in aircraft operations. The legislation was enacted to ensure that the aviation industry adheres to strict safety standards, particularly concerning engine components that could compromise flight safety. One such directive, AD/CF6/26, was issued to mandate inspections and necessary actions for the CF6-45/-50 series turbine engines to mitigate the risk of fatigue cracking in the 12th stage compressor disc. This directive aligns with the technical requirements outlined in FAA AD 93-13-10 and references GE Service Bulletin No 72-1006 Revision 1 dated 14 November 1991. The policy objective behind these regulations is to enhance aviation safety by proactively addressing potential engine failures through timely inspections and maintenance, thereby safeguarding both passengers and crew.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 106, mandates airworthiness directives for aircraft maintenance and safety, with a particular focus on the General Electric Turbine Engines - CF6 Series under AD/CF6/26. This directive applies to CF6-45/-50 series engines, demanding compliance with the technical requirements set forth in the Federal Aviation Administration (FAA) AD 93-13-10. The directive references GE Service Bulletin No 72-1006 Revision 1 dated 14 November 1991, which guides the specific actions required for this inspection. The regulation’s jurisdiction extends across the Commonwealth of Australia, ensuring that all entities and persons operating within this sphere adhere to the stipulated airworthiness directives. The requirement for a one-time inspection for fatigue cracking in the 12th stage compressor disc, and subsequent actions based on the inspection results, is enforced to maintain the safety and reliability of aircraft operations. The directive ensures that any identified issues are rectified through replacement, reidentification, and relife of the affected components.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 106, includes Airworthiness Directives (ADs) for ensuring the safety of aviation operations. One such directive, AD/CF6/26, addresses the inspection of stage 11 to 13 compressor spools for General Electric Turbine Engines of the CF6 series (s. 12/93). This directive applies to CF6-45/-50 series engines and requires action in accordance with the technical requirements outlined in FAA AD 93-13-10 (s. 1). For compliance, reference is made to the General Electric Service Bulletin No 72-1006 Revision 1 dated 14 November 1991, and the directive became effective from 11 November 1993 (s. 2). The AD/CF6/26 mandates a one-time inspection of the stage 12 compressor disc web-to-rim transition area within the stage 11-13 compressor spool to detect any fatigue cracking, which has been reported previously (s. 3). The inspection must be conducted as specified by the FAA AD 93-13-10. Depending on the findings of the inspection, the compressor spools may require replacement, reidentification, and relifeing (s. 4). Entities governed by these regulations are obligated to ensure that all inspections, replacements, and relifeing of the affected compressor spools are carried out meticulously and in compliance with the FAA AD 93-13-10. This includes keeping detailed records of the inspections and any actions taken as a result (s. 5). Failure to comply with the AD/CF6/26 could result in severe safety implications, as the directive is designed to prevent fatigue cracking, which can lead to catastrophic engine failure (s. 6). In terms of consequences, non-compliance with the AD/CF6/26 can lead to significant civil and criminal penalties. Civil penalties can include fines and potential grounding of aircraft that do not meet the required airworthiness standards (s. 7). Criminal penalties may apply if the non-compliance results in a serious breach of aviation safety regulations, potentially leading to imprisonment and substantial fines (s. 8). The exact penalties are determined based on the severity of the breach and are governed by the broader civil aviation legislation.