Commonwealth legislation

AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement

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Commonwealth

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legislative instrument

Plain English Summary

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Requires owners/operators of specified Piper PA-38‑112 serial numbers to inspect the rudder upper hinge brackets for cracks, re-torque the upper hinge nut to 50–70 in·lb on re‑installation, and to replace aluminium brackets with steel P/N 77610‑03 within set flight‑hour limits; the steel fittings must be retired at 5,000 component hours. The directive aims to prevent hinge failures and has been revised to align with the applicable FAA airworthiness directive.

These obligations impose inspection, torque and parts‑replacement costs on aircraft owners/operators and remove recurring inspections once steel brackets are fitted.

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AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Piper PA-38 (Tomahawk) Series Aeroplanes

AD/PA-38/17

Amdt 2

Rudder Upper Hinge - Inspection and Replacement 2/81

Applicability: All models PA-38-112 with S/Nos. 38-78A0001 to 38-80A0099, 38-80A0113, 38- 80A0120 and 38-80A0123 to 38-80A0165.

Requirement: To avoid possible flight hazards associated with a crack in the rudder upper hinge fitting accomplish the following:

Remove the rudder upper hinge pin and carefully displace the rudder from the fin aft to expose the surfaces of both rudder upper hinge brackets P/N 77610-02.

2. Visually inspect all the hinge surfaces in the area of the hinge pin hole to the forward edge of the hinge for cracks using at least a 10X lens, or an approved dye penetrant technique.

3. On re-installation of the upper hinge bolt, torque nut to 50-70 inch pounds (do not exceed maximum figure).

4. Replace the hinge brackets with steel brackets P/N 77610-03 in accordance with Piper SB No. 686.

5. Retire the steel hinge brackets P/N 77610-03 from service.

Note: Installation of steel hinge brackets P/N 77610-03 obviates the need for inspection in accordance with paras. S1 and 2.

Compliance: For Paras. 1, 2 & 3 - Initially inspect within 10 hours time in service after 6 June 1980 and thereafter at intervals not exceeding 50 hours time in service until modified in accordance with Piper SB No. 686.

For Para. 4 - Within 300 hours time in service after 4 July 1980.

For Para. 5 - Prior to the accumulation of 5000 hours component time in service.

Background: Reports have been received of cracks developing in the upper rudder hinge brackets. This Directive has been revised to reflect the content of the applicable FAA AD 80- 22-13 Amdt. 39-3960.

Source text

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

1 AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement