COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
AlliedSignal (Lycoming) Turbine Engines - LTS 101 Series
AD/LTS/4
Amdt 1
Gas Producer Turbine 9/86
Applicability: All LT101 engines with G.P. Turbine Rotor assemblies which do not have metal blade dampeners incorporated.
Requirement: Install improved Gas Producer Turbine Rotor assemblies P/N 4-111-050 -37/-38/ - 39/-40/-41/-42/-43/-44/-45/-46/-47/-49/-50 and -51 in accordance with Lycoming Service Bulletin No. LT 101-72-50-0079 Rev. 1.
Note: FAA AD 86-10-04 Amdt 39-5299 refers.
Compliance: 1. For LT101-700 Series engines: Prior to G.P. Turbine achieving 300 total operating hours in service or within 200 turbine operating hours after 27 January 1986 whichever is the greater but not later than 31 October 1986.
2. For LT101-600 Series engines: In accordance with the Requirement Document. Background: This Directive is amended to reflect the manufacturer's Revision 1 to SB LT 101-72-
50-0079 and to reference FAA AD 86-10-04 Amdt 39-5299. The FAA AD has tightened the manufacturer's compliance statement by imposing a calendar time limit for embodiment. This Directive is amended to incorporate a latest date for embodiment and add additional gas producer turbines by Pt/No.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia's Parliament, were established to regulate civil aviation safety and address gaps in ensuring safe and reliable air travel. One such legislative instrument under these regulations is the AlliedSignal (Lycoming) Turbine Engines - LTS 101 Series AD/LTS/4 Amendment 1, which specifically targets the safety of gas producer turbine rotor assemblies in certain LT101 engines. This amendment aims to address the problem of engine failures by requiring the installation of improved gas producer turbine rotor assemblies to mitigate risks associated with the operation of these engines.
This amendment to the Civil Aviation Regulations 1998 reflects the policy objective of enhancing aviation safety by ensuring that all relevant aircraft engines comply with updated safety standards. The amendment incorporates tighter compliance deadlines and expands the applicability to include additional part numbers of gas producer turbines. By aligning with the Federal Aviation Administration's Airworthiness Directive AD 86-10-04 Amendment 39-5299, the regulation underscores a commitment to international safety standards and collaborative efforts to maintain high levels of safety in civil aviation.
Scope and Application
The AlliedSignal (Lycoming) Turbine Engines - LTS 101 Series Airworthiness Directive AD/LTS/4 Amendment 1 applies to all LT101 engines with G.P. Turbine Rotor assemblies that do not have metal blade dampeners incorporated. This legislation falls under the Civil Aviation Regulations 1998, specifically Part 39 - 106, which is administered by the Civil Aviation Safety Authority (CASA). The directive is applicable nationwide across Australia, as it is a Commonwealth regulation. The requirement outlined in the directive is to install improved Gas Producer Turbine Rotor assemblies P/N 4-111-050 -37/-38/ - 39/-40/-41/-42/-43/-44/-45/-46/-47/-49/-50 and -51 in accordance with Lycoming Service Bulletin No. LT 101-72-50-0079 Rev. 1. Compliance must be achieved under specific timelines: for LT101-700 Series engines, it must occur before the G.P. Turbine reaches 300 total operating hours in service or within 200 turbine operating hours after 27 January 1986, whichever is greater, but not later than 31 October 1986. For LT101-600 Series engines, compliance is to be carried out in accordance with the requirement document. The directive references FAA AD 86-10-04 Amdt 39-5299, which imposes a calendar time limit for compliance, thereby amending the manufacturer's compliance statement.
Key Provisions
The main operative sections of the AlliedSignal (Lycoming) Turbine Engines - LTS 101 Series Airworthiness Directive (AD/LTS/4) specify the applicability and requirements for installing improved Gas Producer Turbine Rotor assemblies. Specifically, section 1 mandates the installation of improved Gas Producer Turbine Rotor assemblies (P/N 4-111-050 -37/-38/ - 39/-40/-41/-42/-43/-44/-45/-46/-47/-49/-50 and -51) for all LT101 engines without metal blade dampeners incorporated (section 2). This installation must comply with Lycoming Service Bulletin No. LT 101-72-50-0079 Rev. 1. The directive references FAA AD 86-10-04 Amdt 39-5299, which imposes stricter compliance timelines.
The obligations under this Act require engine owners and operators to ensure that the specified LT101 engines are fitted with the required Gas Producer Turbine Rotor assemblies within the stipulated timeframes. For LT101-700 Series engines, this must occur either before the G.P. Turbine reaches 300 total operating hours in service or within 200 turbine operating hours after 27 January 1986, but no later than 31 October 1986 (section 1). For LT101-600 Series engines, the compliance must follow the instructions in the Requirement Document. The installation should be performed in accordance with the specified Lycoming Service Bulletin.
Failure to comply with the provisions of this Airworthiness Directive can lead to significant legal and safety repercussions. Although the specific penalties are not detailed within the text provided, non-compliance with Civil Aviation Regulations can generally result in enforcement actions by the Civil Aviation Safety Authority (CASA). These actions may include fines, grounding of the aircraft until compliance is achieved, or other regulatory sanctions. Additionally, there may be civil or criminal liabilities for any resulting accidents or incidents due to non-compliance.