COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Propellers - Variable Pitch - McCauley
AD/PMC/43 Blade Shank Corrosion 8/89
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.
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.
Unless already accomplished; by 31 August 1989. Thereafter reinspect at intervals not exceeding 100 hours time in service.
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.