Commonwealth legislation

AD/PMC/43 - Blade Shank Corrosion

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Commonwealth

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legislative instrument

Plain English Summary

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This directive requires owners, operators and maintainers of aircraft fitted with specified McCauley propeller hubs and blades to disassemble the hub and perform an approved magnetic-particle inspection (CAO 108-8 referenced) of blade shanks to detect fatigue cracks. Initial inspections were due by 31 Aug 1989 (if not already done) and must be repeated at intervals no greater than 100 hours TIS. It imposes inspection costs, downtime and the need for qualified providers.

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Current sections

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AD/PMC/43 - Blade Shank Corrosion

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Propellers - Variable Pitch - McCauley

AD/PMC/43 Blade Shank Corrosion 8/89

Applicability: All McCauley Hubs P/No 41D5926 with blade P/No SS-135-6 or Hub P/No D-1093 with blade P/No SS-135-6M or SS-138-6.

Requirement: Disassemble and inspect the hub and blade shank for fatigue cracks using an approved magnetic particle inspection technique.

Note 1. The technique detailed in CAO 108-8 is an approved technique. Note 2. FAA AD 54-12-02 refers.

Compliance: Unless already accomplished; by 31 August 1989. Thereafter reinspect at intervals not exceeding 100 hours time in service.

Background: To ensure fatigue cracking is detected before loss of a blade occurs, a recurring magnetic particle inspection is required. Affected propellers are fitted to Boeing Stearman aircraft and may be fitted to other older style aircraft.

Source text

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

1 AD/PMC/43 - Blade Shank Corrosion