Document ID: chunk:federal_register_of_legislation:F2006B02559:body:0
Version: federal_register_of_legislation:F2006B02559
Segment Type: other
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Character Range: 0–1484

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 AlliedSignal (Garrett/AiResearch) Turbine Engines - ATF3 Series

AD/ATF3/2 Exhaust Splitter Seal Bolted Flange System 8/86

            Applicability: ATF3-6-4C, -6A-3C and -6A-4C models with Part and Serial numbers as listed in the Requirement.

            Requirement: Install exhaust splitter seal bolted flange system in accordance with G.T.E.C. S.B. ATF3-72-6092 Rev. 2.

            Note: FAA AD T84-20-51 refers.

            Compliance: Unless already accomplished, at the next removal of H.P. turbine module but not later than 200 engine operating hours or 6 calendar months after 31 August 1986 whichever occurs first.

            Background: An ATF3 engine has experienced an uncontained failure of the 6th stage L.P. turbine rotor blades as the result of detachment of the exhaust splitter seal from the exhaust liner.

            FAA AD T84-11-51 issued 25 May 1984 (superseded by FAA AD T84-20-51 October 84) instituted repetitive inspections of the stationary seal/6th stage L.P. turbine rotor for evidence of seal/rotor contact and/or looseness I.A.W. SBs A72-6090 and 6089; and the relevant engine L.M.M.s. These inspections are not necessary on engines which incorporate the splitter seal bolted flange system. This Directive is issued to prevent the possibility of an uncontained engine failure from this cause.