AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/84 Amdt 1 and issues the following 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/A320/84
Amdt 2
Wing Rear Spar 10/2001
Applicability: All Model A320 aircraft without Airbus Industrie modification 24591 or Airbus Industrie Service Bulletin A320-57-1089 incorporated.
Requirement: Action in accordance with the technical requirements of DGAC AD 2001-249(B).
Note: Airbus Industrie Service Bulletins A320-57-1004, -1060, -1088, and -1089 refer.
Compliance: As specified in the Requirement document with a revised effective date of 4 October 2001.
This Amendment becomes effective on 4 October 2001.
Background: This Directive requires inspections of the rear spar to detect fatigue cracks, which could affect the structural integrity of the aircraft.
Amendment 1 was prompted by the manufacturer’s determination that the previously defined inspection thresholds need to be reduced.
Amendment 2 is issued in response to a new DGAC AD which was prompted by a A320 aircraft family fleet survey which highlighted some differences between the mission parameters of in-service aircraft and those initially considered. The differences are mainly weight of fuel on landing and zero fuel weight, which are higher than those defined for the analysis of the fatigue related tasks, and has led to an adjustment of the reference fatigue mission.
Amendment 1 of this Airworthiness Directive became effective on 7 October 1999.
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/84 Amdt 2 (Continued)
The original issue of this Airworthiness Directive became effective on 30 June 1997.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 20 August 2001
The above AD is notified in the Commonwealth of Australia Gazette on 12 September 2001.
Overview
The Civil Aviation Safety Authority has issued Airworthiness Directive AD/A320/84 Amendment 2 to address a safety issue identified in Airbus Industrie A319, A320 and A321 Series Aeroplanes. This amendment revokes the previous AD/A320/84 Amendment 1, which was enacted to address initial inspection threshold requirements, and introduces new requirements to ensure the structural integrity of the aircraft is maintained. The directive responds to findings from a fleet survey that revealed discrepancies between the operational parameters of in-service aircraft and those initially considered, particularly in terms of fuel weight on landing and zero fuel weight, which are critical factors in fatigue analysis. By mandating inspections in accordance with the technical requirements of DGAC AD 2001-249(B), this legislative instrument aims to ensure that any fatigue cracks in the rear spar are detected and addressed, thereby preventing potential safety hazards. This Airworthiness Directive was issued under the authority of the Civil Aviation Regulations 1998 and was gazetted on 12 September 2001.
Scope and Application
This Airworthiness Directive issued by the Civil Aviation Safety Authority (CASA) applies specifically to all Airbus Industrie A320 aircraft that have not yet incorporated Airbus Industrie modification 24591 or Airbus Industrie Service Bulletin A320-57-1089. The directive mandates inspections of the wing rear spar to detect any fatigue cracks, which could compromise the structural integrity of the aircraft. The directive requires compliance with the technical requirements outlined in DGAC AD 2001-249(B). This action is necessary due to identified differences in the mission parameters of in-service aircraft compared to those initially considered, primarily concerning higher weight of fuel on landing and zero fuel weight. This amendment, which became effective on 4 October 2001, adjusts the reference fatigue mission to address these discrepancies. The directive is part of the Commonwealth's regulatory framework and is applicable across Australia, ensuring the safety and airworthiness of the specified aircraft in accordance with the Civil Aviation Regulations 1998.
Key Provisions
The Airworthiness Directive (AD) AD/A320/84 Amdt 2 primarily pertains to all Airbus Industrie A320 aircraft without Airbus Industrie modification 24591 or Airbus Industrie Service Bulletin A320-57-1089 incorporated. It mandates that specific actions be taken to address identified safety issues. The directive requires adherence to the technical requirements outlined in DGAC AD 2001-249(B), which includes modifications detailed in Airbus Industrie Service Bulletins A320-57-1004, -1060, -1088, and -1089. The compliance period is set to commence as specified in the requirement document, with an effective date of 4 October 2001. This AD replaces Amendment 1, which was effective from 7 October 1999, and it is a continuation of the original directive issued on 30 June 1997.
The obligations imposed by AD/A320/84 Amdt 2 require aircraft operators to perform inspections on the rear spar to detect any fatigue cracks. This inspection is critical as it ensures the structural integrity of the aircraft is maintained. The directive is applicable only to the specified models of Airbus aircraft that have not yet incorporated the necessary modifications or service bulletins. The primary focus of the AD is to mitigate the risk associated with potential fatigue cracks in the rear spar, which could compromise the safety of the aircraft during operation.
Failure to comply with the provisions of AD/A320/84 Amdt 2 may result in serious safety consequences, including the potential for in-flight structural failure. Civil Aviation Safety Authority (CASA) delegates have the authority to enforce this directive, and non-compliance may lead to penalties. The exact nature and severity of these penalties are not detailed in the text, but they could include fines, suspension of airworthiness certificates, or other regulatory actions deemed necessary to ensure compliance. The directive underscores the importance of adhering to these safety requirements to maintain the airworthiness of the aircraft and ensure the safety of all passengers and crew.