Commonwealth legislation

AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

4/10 complexity

This airworthiness directive mandates inspections and any required repairs for certain Pratt & Whitney JT8D eighth-stage compressor hubs that have machining balance cuts. It affects operators, owners and maintenance organisations that have those hubs installed.

Issued after an overseas uncontained hub rupture, the AD aims to detect cracks at the balance-flange machining area to prevent failures; compliance costs, parts replacement and downtime fall to operators and their maintenance providers.

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Current sections

Direct links to the current provisions in AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub.

AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub

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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/JT8D/17 - Eighth Stage Rear Compressor Front Hub