AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub
1AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub
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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 Turbine Engines - JT8D Series
AD/JT8D/17 Eighth Stage Rear Compressor Front Hub 9/80
Applicability: All JT8D engines fitted with eighth stage rear compressor front hubs P/N 690908, 701308, 717608, 717708 and 738308 which contain balance cuts.
Document: 1. FAA Emergency Telegraphic AD TAD No. T80 15 51; or
- Pratt & Whitney Aircraft Alert SB ASB 5154 Rev. 1; or 3. AD/PW-T/53.
Compliance: As detailed in Requirement Document No. 1.
Background: Overseas, a JT8D engine experienced an uncontained rupture of a rear compressor front hub, P/N 738308. Subsequent investigation concluded that a fracture originated in the transition radius of a machining cut on the balance flange. This Directive is issued in order to provide inspection procedures and compliance requirements needed to detect cracks in the affected areas of P/N 738308 and similar JT8D hubs.