Commonwealth legislation

AD/MU-2/49 Amdt 1 - Underwing Pressure Bulkhead Flange

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires owners/operators of all Mitsubishi MU-2 aeroplanes to remove internal cabin lining and do a close visual inspection of the underwing pressure bulkhead flange (left and right) in the bend radius between fuselage stations 3905–4660 for cracks. Initial inspection is required before exceeding 5,000 pressurised flights or by 11 October 1991, then every 1,000 pressurised flights and whenever there is an unexplained difficulty maintaining cabin pressure. The amendment cites a reported 300 mm crack and narrows the inspected area to resolve field misunderstanding.

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/MU-2/49 Amdt 1 - Underwing Pressure Bulkhead Flange.

AD/MU-2/49 Amdt 1 - Underwing Pressure Bulkhead Flange

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 Mitsubishi MU-2 Series Aeroplanes

AD/MU-2/49

Amdt 1

Applicability: All Models.

Underwing Pressure Bulkhead Flange 10/94

Requirement: Remove the necessary internal cabin lining and perform a close visual inspection of the underwing pressure bulkhead. Look for cracks in the bend radius of the flange on both left and right hand sides of the bulkhead from F.Sta.3905 to F.Sta.4660.

Compliance: Prior to exceeding 5000 pressurised flights or prior to 11 October 1991, whichever occurs later. Thereafter at intervals not to exceed 1000 pressurised flights, and at any time there is an unexplained difficulty maintaining cabin pressure. The compliance of the initial issue of this Directive remains unchanged. This amendment is effective from 15 September 1994.

Background: There had been a report of a 300mm long crack in the bend radius of the pressure bulkhead flange on an Australian registered aircraft. Undetected cracking could cause a sudden loss of cabin pressure in flight. Amendment 1 is issued to specify the exact location of the area to be inspected in response to a reported misunderstanding in the field.

Source text

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