AD/A320/85 - Probe Heat Computer

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105 Civil Aviation Safety Authority Schedule of Airworthiness Directives, introduced the AD/A320/85 to address an identified safety issue with the Airbus Industrie A319, A320, and A321 series aeroplanes. This legislative instrument was enacted to prevent a simultaneous loss of heating in the probes, which could lead to erroneous anemometric calculations during operations in freezing conditions, potentially compromising flight safety. The directive applies to all Airbus Industrie A320 models that have not yet incorporated Airbus Industrie modification No. 26403 or Airbus Industrie Service Bulletin A320-30-1036 Revision 1 dated 7 July 1997. The requirement outlined in the directive mandates the modification of the wiring between engine interface units one and two with probe heat computer one and three, in line with the specified Airbus Industrie Service Bulletin, to ensure compliance before 22 May 1998. This airworthiness directive became effective on 6 November 1997, establishing a clear policy objective to enhance aviation safety by mitigating the risks associated with the identified issue.

Scope and Application

The Civil Aviation Safety Authority Schedule of Airworthiness Directives, specifically AD/A320/85 concerning Airbus Industrie A319, A320 and A321 Series Aeroplanes, applies to all Airbus Industrie A320 models that have not yet incorporated Airbus Industrie modification No.26403 or Airbus Industrie Service Bulletin A320-30-1036 Revision 1 dated 7 July 1997. The directive mandates the modification of the wiring between engine interface units one and two with probe heat computer one and three in accordance with the specified Airbus Industrie Service Bulletin. This requirement is intended to prevent a simultaneous loss of heating of probes (CAPT and STBY side) due to a single failure, which could lead to erroneous anemometric calculations by the concerned systems while operating in freezing conditions. Compliance with this directive is mandatory prior to 22 May 1998, with the directive becoming effective on 6 November 1997. The directive references DGAC AD 97-203-102(B) for additional context. This regulation extends the application through the incorporation of specific service bulletins and modifications, ensuring that the safety and airworthiness standards of the aircraft are met.

Key Provisions

The main operative sections of this legislative instrument, specifically AD/A320/85, pertain to the modification of wiring for certain Airbus Industrie A320 models. Section (1) outlines the applicability, indicating that the directive applies to all Airbus Industrie A320 models that do not have Airbus Industrie modification No.26403 or Airbus Industrie Service Bulletin A320-30-1036 Revision 1 dated 7 July 1997 incorporated. Section (2) states the requirement, which is to modify the wiring between engine interface units one and two with probe heat computer one and three in accordance with Airbus Industrie Service Bulletin A320-30-1036. The directive notes that this requirement should be implemented unless the modification has already been done. The directive references DGAC AD 97-20-3-102(B) for additional context. The obligations imposed by the Civil Aviation Regulations 1998 on the parties governed by this Act include ensuring that the specified wiring modifications are implemented for applicable Airbus Industrie A320 models. Operators of these aircraft must ensure compliance with the directive prior to 22 May 1998, as stated in section (3). The directive became effective on 6 November 1997, meaning that operators had to be aware and implement the changes within the specified timeframe. Failure to comply with this airworthiness directive could lead to safety risks, particularly in freezing conditions, where erroneous anemometric calculations could occur due to a simultaneous loss of heating of probes. The background provided indicates that the purpose of this airworthiness directive is to prevent a simultaneous loss of heating of probes (CAPT and STBY side) due to a single failure, which would result in erroneous anemometric calculations by the systems concerned. This is particularly important for operations in freezing conditions, where accurate readings are critical for safe flight operations. By ensuring the wiring modifications are implemented, the risk of such failures is mitigated, thereby enhancing the safety and reliability of the aircraft. The legislative instrument does not explicitly state any specific offences, penalties, or civil/criminal consequences for breach within the provided text. However, failure to comply with airworthiness directives in general could potentially lead to enforcement actions under the Civil Aviation Act 1988, which may include fines or other regulatory actions. The severity of these penalties can vary depending on the specific breach and the discretion of the regulatory authorities. The aim is to ensure strict compliance to maintain the highest safety standards in civil aviation.