AD/PHS/10 Amdt 1 - Hydromatic Aluminium Propeller Blades

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B06187 Not in force Legislative Instrument

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


Propellers - Variable Pitch - Hamilton Standard

 

AD/PHS/10

Amdt 1


Hydromatic Aluminium Propeller Blades 5/87

 

Applicability: Hamilton Standard Hydromatic (non-counterweighted) propellers with aluminium blades that use engine oil for pitch control (does not apply to propellers with integral oil control or to propellers with steel blades) of the following types:              22D30, 22D40, 23D40, 23E50, 23E60, 24D50, 24E60, 33D50, 33E60, 34D50, 34D51, 34E60,

43D50, 43D51, 43E60, and 43H60, as installed on various reciprocating engine powered aircraft.

 

Requirement: Remove blades and visually inspect for evidence of corrosion in the blade fillet and shank area, particularly under the teflon friction reduction strip and the resin corrosion barrier, in accordance with Hamilton Standard Aluminium Blade Overhaul Manual No. 130B dated 1 March 1980.

 

Compliance: 1. Propellers with less than 2 years calendar time in service since reconditioning or the last inspection in accordance with this requirement; before exceeding 3 years calendar time in service after 30 April 1983 and thereafter at periods not exceeding 6 years calendar time in service.

 

2. Propellers with greater than 2 years calendar time in service since reconditioning or the last inspection in accordance with this requirement; within 12 months calendar time in service after 30 April 1983 and thereafter at periods not exceeding 6 years calendar time in service.

 

Note: Calendar periods are deemed to commence from the time the propeller is first installed on an aircraft following reconditioning or inspection in accordance with this requirement and shall be uninterrupted including all subsequent service and storage periods.

 

Background: The FAA advise the possibility of fatigue cracking, leading to blade separation, initiated by severe corrosion around the shank and blade fillet area, particularly under the teflon friction strip. This Directive has been amended to extend the inspection period after initial inspection.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.