AD/A320/140 - Relay 11QG Testing After Relocation

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Legislation au F2006B01887 Not in force Legislative Instrument

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


AIRWORTHINESS DIRECTIVE


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 CAR 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.

 

Airbus Industrie A319, A320 and A321 Series Aeroplanes

 

AD/A320/140 Relay 11QG Testing After Relocation 10/2002

 

Applicability:  A319, A320 and A321 aeroplanes, all models and serial numbers without Airbus Industrie modification 26065 incorporated during production or Airbus Industrie Service Bulletin (SB) A320-24-1092, Revision 4, dated 20 June 2002 embodied.

Requirement: Perform the additional tests required by SB A320-24-1092 Revision 4.

 

Although addressing the relocation of relay 11QG, prior compliance with AD/A320/102 is not considered compliance with this Directive.

 

Note: DGAC AD 2002-365(B) refers.

 

Compliance: Within 600 hours’ time in service after the effective date of this Directive.

 

This Airworthiness Directive becomes effective on 3 October 2002.

 

Background: AD/A320/92 required the Engine/Master 1 relay to be relocated to improve phys ical separation of the electrical components and wiring. This AD was superseded by AD/A320/102, which required an additional inspection to ensure the correct electrical contacts were installed during the relocation.

This Directive requires additional testing following the relay relocation and will lower the risk of simultaneous cut-off of the fuel low pressure supply to both engines being caused by water ingress in relay box 103VU.


 

James Coyne

Delegate of the Civil Aviation Safety Authority 20 August 2002

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 11 September 2002.

 

 

 


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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.