AD/RB211/23 - HP Compressor Rotor Shaft to HP Turbine Rotor Disc Retaining Bolts (Cth)

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

Rolls Royce Turbine Engines - RB211 Series

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

AD/RB211/23 HP Compressor Rotor Shaft to HP Turbine Rotor Disc Retaining Bolts

Applicability: RB211-524G2, -524G3 and 524H2 series engines.

8/2000

Requirement: To introduce revised HP compressor shaft to HP turbine rotor disc retaining bolts made from INCO 718 material in accordance with Rolls Royce Service Bulletin RB211-72-C491 Revision 1.

Note: UK CAA AD 004-10-99 refers.

Compliance: Unless previously accomplished, by 20 August 2000.

This Airworthiness Directive becomes effective on 10 August 2000.

Background: This directive is raised to mandated replacement of the bolts connecting the HP compressor shaft to HP turbine rotor disc following failure in operating engines due to stress corrosion.

Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 27 June 2000

The above AD is notified in the Commonwealth of Australia Gazette on 12 July 2000.