Commonwealth legislation

AD/BEECH 55/28 - Landing Gear Upper and Lower Torque Link Clevis Pins

RepealedCTH

This Act has been repealed and is no longer in force. It is retained for historical reference.

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

This rule requires operators of Beechcraft Baron 55, 58, and 95-55 series aeroplanes with over 1,000 hours to remove and visually inspect the small AN/MS lock pins that join the upper and lower landing-gear torque links, and to replace any pins showing wear or corrosion.

Inspections must be done within 100 flight hours after 29 March 1972 and at least every 3 years thereafter to prevent landing-gear failure on takeoff or landing.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/BEECH 55/28 - Landing Gear Upper and Lower Torque Link Clevis Pins.

AD/BEECH 55/28 - Landing Gear Upper and Lower Torque Link Clevis Pins

meta-content-style-type: text/css meta-content-type: application/xhtml+xml; charset=utf-8 meta-description: CASA Airworthiness Directive meta-generator: Aspose.Words for .NET 22.10.0 meta-keywords: Issue 3/1972,Aircraft below 5700 kg,Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes,Landing Gear Upper and Lower Torque Link Clevis Pins,28 title: Airworthiness Directive - AD/BEECH 55/28 - Landing Gear Upper and Lower Torque Link Clevis Pins

?xml version="1.0" encoding="utf-8" standalone="no"?>

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes

AD/BEECH 55/28 Landing Gear Upper and Lower

Torque Link Clevis Pins

Applicability: All models which have exceeded 1000 hours’ time in service.

3/72

Requirement: Remove and inspect the AN or MS lock pins in the upper and lower torque link clevis pins on the main and nose landing gear assemblies. Any pins which exhibit wear or corrosion shall be replaced.

Compliance: Within 100 hours’ time in service after 29 March 1972 and thereafter at intervals not exceeding 3 years.

Source text

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