Commonwealth legislation

AD/PT6A/8 - Compressor Rear Hub Hardness

RepealedCTH

This Act has been repealed and is no longer in force. It is retained for historical reference.

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

This AD requires operators and maintenance organisations of specified Pratt & Whitney Canada PT6A/PT6B turboprop engines to verify the compressor rear hub meets required hardness before the engine can be installed after reconditioning, unless already modified per Service Bulletins 1079 or 1094.

Compliance must follow one of the approved technical documents (UACL Service Bulletin No. 62 Rev 3, No. 1035, or AD/UAC-T/2B). This prevents hub failure and preserves flight safety.

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AD/PT6A/8 - Compressor Rear Hub Hardness

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source Pratt and Whitney Canada Turbine Engines - PT6A Series

AD/PT6A/8 Compressor Rear Hub Hardness 10/85

Applicability: PT6A-6, -6A, -6B, -20 and PT6B-9 which do not include the intent of SB No. 1079 (old No. 119, Rev. 2) or SB No. 1094 (old No. 140, Rev. 3).

Document: 1. UACL SB No. 62, Rev. 3;

2. UACL SB No. 1035, or

3. AD/UAC-T/2B.

Compliance: Before installation in an aircraft following next reconditioning completed after 21 November 1969.

Source text

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