Commonwealth legislation

AD/A320/151 - Keel Beam Side Panels

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This Act has been repealed and is no longer in force. It is retained for historical reference.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

3/10 complexity

This directive requires operators of Airbus A319/A320 (except frames fitted in production with Modification No. 30355) to inspect the keel beam side panels for fatigue cracks, following the procedures of DGAC AD 2003-146(B). Cracks were found during structural fatigue testing in rivet and cut‑out areas below the centre wing box; if unchecked they could threaten structural integrity. The directive also corrects the inspection trigger from “3,500 flight hours” to “3,500 flights,” a significant operational difference.

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Current sections

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AIRWORTHINESS DIRECTIVE

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For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

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Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/151 Keel Beam Side Panels 12/200

AD/A320/151 Keel Beam Side Panels 12/2003

Applicability: All Model A320 and A319 aircraft, except aircraft with Modification No. 30355 incorporated in production.

Requirement: Inspect in accordance with the requirements of DGAC AD 2003-146(B).

Note: A correction to Compliance paragraph 3.1 of DGAC AD 2003-146(B) was issued on 14 May 2003, and corrected the 3,500 flight hours threshold to read 3,500 flights.

Compliance: As specified in the Requirement document, with a revised effective date of 27 November 2003.

This Airworthiness Directive becomes effective on 27 November 2003.

Background: During certification structural fatigue tests, cracks were found on both sides of the keel beam around the rivets below the centre wing box between FR40 and FR42, and in part of the area of the upper elliptical cut-out forward of FR41.

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David Villiers

Delegate of the Civil Aviation Safety Authority 17 October 2003

View image in the official source

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/151 Keel Beam Side Panels 12/200 AD/A320/151 Keel Beam Side Panels 12/2003

AD/A320/151 Keel Beam Side Panels 12/2003

Applicability: All Model A320 and A319 aircraft, except aircraft with Modification No. 30355 incorporated in production.

Requirement: Inspect in accordance with the requirements of DGAC AD 2003-146(B).

Note: A correction to Compliance paragraph 3.1 of DGAC AD 2003-146(B) was issued on 14 May 2003, and corrected the 3,500 flight hours threshold to read 3,500 flights.

Compliance: As specified in the Requirement document, with a revised effective date of 27 November 2003.

This Airworthiness Directive becomes effective on 27 November 2003.

David Villiers

Delegate of the Civil Aviation Safety Authority 17 October 2003