Document ID: chunk:federal_register_of_legislation:F2006B10118:body:0
Version: federal_register_of_legislation:F2006B10118
Segment Type: other
Provision Reference: 
Character Range: 0–991

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Grumman G21 (Goose) Series Aeroplanes

                        AD/G21/4 Rudder Control Push-Rod Assembly P/N 12727-1 - Inspection

10/77

 Applicability: All models.

 Requirement: 1. Remove rudder control push rod assembly P/N 12727-1.

             2.    Thoroughly clean both rod end fittings.

3.    Inspect both fittings for cracks using a dye penetrant technique in conjunction with at least a 10X magnifying glass.

            Note 1. Push rod assembly P/N 12727-1 is connected to the LH rudder pedals and is located below the pilot's compartment floor approximately 240 mm to the right of the aircraft centre line.

            Note 2. FAA AD 63-27-2 Amendment 655 refers.

            Compliance: Inspect initially before issue of Certificate of Airworthiness and thereafter at intervals not exceeding 100 hours time in service.