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

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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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.