Commonwealth legislation

AD/JT8D/30 Amdt 1 - Low Pressure Turbine Inspection and Modification

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Commonwealth

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legislative instrument

Plain English Summary

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This airworthiness directive requires operators of Pratt & Whitney JT8D-1 through -17R engines to inspect third- and fourth-stage low-pressure turbine blades and to fit improved low-pressure turbine containment hardware and No.6 bearing scavenge pump bracket bushings, following the technical steps in FAA AD 97-19-14 (Requirement 1–2).

Engine owners/operators and maintenance organisations pay for and carry out the work; compliance was required by 29 January 1998, and fitting the specified modifications ends the recurring inspection obligation (Requirement 2; Compliance).

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AD/JT8D/30 Amdt 1 - Low Pressure Turbine Inspection and Modification

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/30

Amdt 1

Low Pressure Turbine Inspection and Modification 2/98

Applicability: JT8D-1 through -17R series engines.

Requirement: 1. Inspect the third and fourth stage turbine blades of affected engines in accordance with the technical requirements of FAA AD 97-19-14 Amdt 39-10135.

Note 1: The extent of the inspection requirements is dependent on modification/build status of individual engines.

Modify affected engines to incorporate improved low pressure turbine containment hardware and improved No.6 bearing scavenge pump attach bracket bushings in accordance with the technical requirements of FAA AD 97-19-14 Amdt 39-10135.

Incorporation of these modifications is terminating action for the inspections specified in Requirement 1 of this directive.

Compliance: Effective 29 January 1998, as detailed in the requirement document.

Note 2: This directive supersedes AD/JT8D/28.

This amendment becomes effective on 29 January 1998.

Background: Uncontained engine failures have occurred as a result of low pressure turbine blade and shaft fractures.

This amendment revises the original Requirement Document to reflect FAA AD 97- 19-14 in lieu of FAA AD 94-20-08. FAA AD 97-19-14 reduces the compliance period for the modifications specified in Requirement 2 for engines in which certain 4th stage low pressure turbine hubs are installed. AD/JT8D/34 also refers.

The original issue of this airworthiness directive became effective on 2 February 1995.

Source text

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

1 AD/JT8D/30 Amdt 1 - Low Pressure Turbine Inspection and Modification