AD/JT15D/7 Amdt 2 - Fan Blade Rub
1AD/JT15D/7 Amdt 2 - Fan Blade Rub
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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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:
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 Engines incorporating a vibration damper ring as detailed in SB 7268 or 7300 are no longer applicable.