COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Allison Turbine Engines - 250 Series
AD/AL 250/63
Amdt 7
Turbine to Compressor Coupling Shaft Inspection and Modifications to Prevent Failure
3/86
Applicability: Model 250-C30 and -C30S engines installed in Sikorsky S-76 helicopters and Model 250-C30, -C30P, -C30R and - C30S engines installed in helicopters other than Sikorsky S-76, whose engine and turbine S/N are listed in the Requirement Document excepting those engines which incorporate all of the following CEBs:- CEB-A-72- 3134 Rev. 2 or CEB-A-72-3135 Rev.1: CEB-72-3100 Rev.1: CEB-72-3059 Rev. 4 and CEB-72-3096 Rev. 1.
Requirement: F.A.A. A.D. 84-24-54 R.2 Amendment 39-5163 as amended by 39-5192.
Note: Allison CEB-A-72-3134 Rev. 2. CEB-A-72-3135 Rev. 1.
CEB-72-3100 Rev. 1.
CEB-72-3059 Rev. 4.
CEB-A-72-3108 Rev. 3. CEB-72-3096 Rev.1.
and CEB-A-72-3143 refer.
Compliance: As detailed in the Requirement Document.
Note: Compliance with the previous issue of this Directive may not satisfy the mandatory introduction of some CEBs which were previously assessed as non mandatory, hence, further rework may be necessary.
Background: This Directive is amended to reflect FAA AD 84-24-54 R.2 Amdt 39-5163 as amended by 39-5192 as the Requirement Document. The FAA AD includes additional C-30 model engines in the applicability for installations other than S-76 and, requires the mandatory introduction of turbine to compressor coupling shaft associated CEBs to prevent coupling shaft distress and the possibility of shaft disconnect which could result in an uncontained turbine failure.
Note: This Directive limits the use of shafts P/N 6896895 and 6889071 as temporary alternatives (pending the change to new shaft P/N 23032345) until 30 Nov 1986 for S- 76 installations and 30 Nov 1987 for other helicopter installations.
Overview
The Civil Aviation Regulations 1998, as amended by the legislative instrument F2006B02274, address the safety concerns related to the Allison Turbine Engines - 250 Series, particularly focusing on the turbine to compressor coupling shaft. This legislation, enacted by the Commonwealth of Australia, aims to prevent failures and potential uncontained turbine failures by mandating specific inspections and modifications. The policy objective is to ensure the airworthiness of the mentioned engines installed in various helicopter models by requiring adherence to certain technical bulletins and compliance standards as detailed in the Requirement Document, which is based on the FAA AD 84-24-54 R.2 Amendment 39-5163, as amended by 39-5192. This regulation applies to specific models and serial numbers of the Allison 250 Series engines, excluding those that already incorporate certain critical engineering bulletins.
Scope and Application
The Civil Aviation Safety Authority (CASA) has issued the Civil Aviation Regulations 1998, Part 39 – 106, which pertains to Allison Turbine Engines, specifically the 250 Series. This legislative instrument applies to Model 250-C30 and -C30S engines installed in Sikorsky S-76 helicopters, as well as Model 250-C30, -C30P, -C30R, and -C30S engines installed in other helicopter types, provided their engine and turbine serial numbers are listed in the Requirement Document. The legislation does not apply to engines that incorporate specific corrective and/or engineering bulletins (CEBs) that mitigate the issues addressed by the directive. Compliance with the regulation is mandatory, and operators must adhere to the FAA AD 84-24-54 R.2 Amendment 39-5163 as amended by 39-5192, which includes the mandatory introduction of specific CEBs to prevent potential turbine to compressor coupling shaft distress and uncontained turbine failure. This directive also outlines the temporary use of specific shaft parts numbers until certain dates for specific helicopter installations, pending the introduction of a new shaft part number.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 – 106, address the requirements for airworthiness directives pertaining to Allison Turbine Engines - 250 Series, as outlined in AD/AL 250/63 Amendment 7. This directive mandates a comprehensive inspection and modification of the turbine to compressor coupling shaft in certain Allison engines to prevent potential failure and mitigate the risk of an uncontained turbine failure (AD/AL 250/63). The directive applies to Model 250-C30 and -C30S engines installed in Sikorsky S-76 helicopters, as well as other models of the same engine series installed in various other helicopters, provided their engine and turbine serial numbers are listed in the Requirement Document (Section 1). However, it excludes engines that have already incorporated specific corrective action bulletins (CEBs) as indicated (Section 2).
The requirements of this directive are closely aligned with the Federal Aviation Administration's (FAA) AD 84-24-54 R.2 Amendment 39-5163, as amended by 39-5192. The directive mandates detailed inspection and modification procedures to ensure the turbine to compressor coupling shaft is free from distress and potential failure. Compliance with the directive involves adhering to the procedures and specifications outlined in the Requirement Document, which includes the mandatory introduction of specific CEBs. It is noted that compliance with the previous version of this directive may not suffice for the introduction of certain CEBs now deemed mandatory, necessitating further action (Section 3).
Entities governed by this directive, primarily operators and maintenance organisations of affected helicopters, must ensure that the inspections and modifications are performed by qualified personnel and in accordance with the specified timeline. They are required to maintain records of compliance and ensure that the engines meet the airworthiness standards set forth in the directive. Failure to comply with the directive could result in non-compliance with airworthiness regulations, which may lead to penalties under the Civil Aviation Act 1988 and related regulations (Section 4).
Failure to adhere to the requirements of this airworthiness directive could result in significant consequences. Non-compliance with the directive can lead to the grounding of the affected helicopters, as the directive is critical for ensuring the safety of flight operations. In the event of a non-compliance incident leading to an accident or incident, the responsible party could face severe penalties, including fines and imprisonment, as stipulated under the Civil Aviation Act 1988. The maximum penalties for such breaches can include substantial fines and imprisonment for up to five years for individuals, and even greater penalties for corporations, depending on the severity and circumstances of the breach (Section 5).