Document ID: chunk:federal_register_of_legislation:F2006B10970:body:0
Version: federal_register_of_legislation:F2006B10970
Segment Type: other
Provision Reference: 
Character Range: 0–1405

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

 Pratt and Whitney Canada Turbine Engines - JT15D Series

 AD/JT15D/7
 Amdt 2

 Fan Blade Rub 3/93

            Applicability: JT15D-4, -4B, -4D engines not incorporating Pratt and Whitney Canada Service Bulletin No. 7268 or 7300.

            Requirement: Inspect the low pressure compressor case inner diameter for evidence of fan blade rub.

            If fan blade rub is evident:

              1. Carry out a fan blade tip clearance check in accordance with PWC M/M P/N 3017542, chapter 72-30-53 and adjust as required.

2.    Carry out a fluorescent penetrant inspection of the rub area.

3.    If cracking of the low compressor case is evident, replace the low compressor case.

            Note 1: A fluorescent penetrant inspection shall be carried out by the holder of a valid NDT Authority.

            Note 2: Transport Canada Directive CF-88-03R1 refers.

            Compliance: Effective 4 March 1993; unless previously accomplished, within 25 hours time in service and thereafter at intervals not to exceed 300 hours time in service.

            Background: This Directive has been amended to reflect the issue of PWC SB No. 7300. Engines incorporating a vibration damper ring as detailed in SB 7268 or 7300 are no longer applicable.