Document ID: chunk:federal_register_of_legislation:F2006B08302:body:0
Version: federal_register_of_legislation:F2006B08302
Segment Type: other
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Character Range: 0–2242

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Cessna 400 Series Aeroplanes

 AD/CESSNA 400/15
 Amdt 2

 Turbocharger Heat Shield 3/97

            Applicability: All Cessna Model 401, 401A, 401B, 402, 402A and 402B aircraft fitted with Teledyne Continental Motors (TCM) TSIO-520-E engines and not incorporating steel turbocharger heat shields as detailed in Cessna Service Letter ME72-4.

            Requirement: To detect impending failure of the turbocharger turbine housings; remove both engine top cowls and turbocharger turbine housing insulation blankets and visually inspect the complete surface of the turbine housing of the TCM turbocharger assemblies P/N 632729 (AID P/N 406610) for evidence of cracks, bulges and burnt areas.

            Replace parts found to have evidence of cracks, bulges and burnt areas before further flight.

            Note 1: FAA Airworthiness Directive 70-03-04R1 refers.

            Note 2: This directive is only applicable to aircraft not incorporating the steel heat shields. Whilst Cessna has advised the parts required to fit steel heat shields are no longer available, the FAA has suggested the use of serviceable salvaged parts. CASA concurs with the FAA advice.

            Compliance: Effective 27 February 1997; prior to exceeding 400 hours turbocharger time in service from new or from overhaul, and thereafter at intervals not to exceed 120 hours time in service.

            This Amendment becomes effective on 27 February 1997.

            Background:  This directive was originally issued to require the inspection of certain turbocharger turbine housings. Amendment 1 of this directive reflected the availability of a steel heat shield in lieu of the insulation blanket and clarified the inspection requirements. This amendment introduces a terminating action. The requirements of this directive are not applicable to an aircraft incorporating steel heat shields on both engines.
            Amendment 1 of this Airworthiness Directive became effective on 31 August 1987. The original issue of this Airworthiness Directive became effective on
            15 September 1971.