Document ID: chunk:federal_register_of_legislation:F2006B06277:body:0:p1
Version: federal_register_of_legislation:F2006B06277
Segment Type: other
Provision Reference: 
Character Range: 4–2905

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

    Propellers - Variable Pitch - McCauley

    AD/PMC/14
    Amdt 10

    Threaded Propeller Hubs 4/95

    Applicability: All McCauley threaded propeller hubs.

               Note: To identify a threaded hub, inspect hub P/N. If numerals after the "C" are less than 200 the hub is of the threaded type. e.g. 2AF34C17. If numerals after the "C" are 200 or higher hub is non threaded hub and the requirements of this Directive do not apply. e.g. B2A34C205.

                 Requirement: 1. Remove spinner and check whether hub is a dye oil filled or non dye oil filled type.

2.    If hub is a dye oil filled type visually check hub for signs of dye oil leaks. If the spinner backing plate prevents a thorough hub inspection, removal of the propeller and backing plate will be required. If the inspection confirms there is no leakage from the hub and the correct quantity of dye oil is contained in the hub no further action is required and this Directive may be certified as complied with. If any dye oil leakage is apparent, the propeller is to be removed from service for dismantling and internal hub inspection procedures.

               Note: To check for correct oil level, place two bladed propeller vertical. In a three bladed propeller the number one blade should be vertical. Remove oil filler plug, which should be approximately at the ten o'clock position and confirm dye oil level is to bottom of oil filler hole.

3.    If hub is a non oil filled type or is not currently dye oil filled, remove propeller from engine and remove backing plate, if fitted. Using Group 1 dye penetrant to CAO 108.10 inspect hub in the following areas:

               Note: Ensure solvent does not enter blade socket area as loss of lubricant from this area can affect blade pitch change action.

                   (a)     the outer 38 mm (one and one half inches) of the complete circumference of each blade socket paying particular attention to the rear segment of each socket;

                   (b)     the rear circumference of the hub barrel adjacent to the attachment face, including the complete mounting flange face; and

                   (c)     inspect blades for excessive looseness and ensure both expansion lock plugs are installed in each blade retention nut.

4.    After completion of dye penetrant inspection lubricate the area where the steel shim/circlip are mounted in the blade retaining ferrule using Aeroshell W65. If Aeroshell W65 is unavailable any SAE 10W or SAE 10W multi-grade piston engine oil is acceptable.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

           Compliance:  For propellers installed on aircraft