Commonwealth legislation

AD/HILLER 12/26 - Rotor Tachometer Generator - Replacement

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires owners/operators of Hiller UH‑12D and UH‑12E helicopters converted by Soloy using 22A580 rotor tachometer generators to replace those generators. The replacement must be completed within 200 hours’ time in service after 31 May 1979, following Soloy Service Bulletin 03‑560 or FAA AD 79‑03‑07. The stated aim is to reduce false low‑rotor warnings and avoid unnecessary emergency procedures; operators pay for parts, labour and downtime caused by the mandated replacement.

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/HILLER 12/26 - Rotor Tachometer Generator - Replacement.

AD/HILLER 12/26 - Rotor Tachometer Generator - Replacement

meta-content-style-type: text/css meta-content-type: application/xhtml+xml; charset=utf-8 meta-generator: Aspose.Words for .NET 22.10.0

?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 Hiller UH-12 Series Helicopters

AD/HILLER 12/26 Rotor Tachometer Generator - Replacement 5/79

Applicability: Model UH-12D and UH-12E helicopters with Soloy Turbine Conversion using 22A580 tachometer generators in the rotors position.

Document: 1. Soloy Conversions SB 03-560; or

FAA AD 79-03-07.

Compliance: Within 200 hours’ time in service after 31 May 1979.

Background: The new rotor tachometer generator type is expected to reduce the number of failures being experienced with the present generators. The repeated execution of emergency procedures involving unnecessary external load deployment and full autorotation following false low rotor speed warning system activation should be avoided, thereby reducing the hazard to the aircraft.

Source text

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