Commonwealth legislation

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

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This AD requires owners/operators of Grumman G21 (all models) fitted with rudder control push‑rod P/N 12727‑1 to have the assembly removed, both rod‑end fittings cleaned and dye‑penetrant inspected (minimum 10X magnifier) before issue of a Certificate of Airworthiness and thereafter every 100 flying hours. Maintenance organisations or authorised personnel must perform and fund the work; the AD specifies inspection only (no corrective actions) and cross‑references FAA AD 63‑27‑2.

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Current sections

Direct links to the current provisions in AD/G21/4 - Rudder Control Push-Rod Assembly P/N 12727-1 - Inspection.

AD/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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

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