Commonwealth legislation

AD/MSR/26 - Wing Structural Fatigue Life Limitation

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

This instrument mandates permanent retirement of the wing main spar and centre‑section splice plates on all Aerospatiale Rallye series 235E aircraft when either component reaches 2,800 hours component time-in-service. It affects owners/operators (who bear removal, disposal and replacement costs) and is based on manufacturer data establishing a safe fatigue life, with the limit subject to future review if further substantiation is provided.

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/MSR/26 - Wing Structural Fatigue Life Limitation.

AD/MSR/26 - Wing Structural Fatigue Life Limitation

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 Aerospatiale Rallye Series Aeroplanes

AD/MSR/26 Wing Structural Fatigue Life Limitation 3/80

Applicability: All series 235E aircraft.

Requirement: Retire the wing main spar and the centre section splice plates from service.

Note: This fatigue life limitation will be reviewed upon receipt of future substantiation data from the manufacturer.

Compliance: Upon or prior to achieving 2800 hours component time in service.

Background: Based on information provided by the manufacturer, a safe fatigue life has been determined for the wing structure.

Source text

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