AD/A320/73 - Frame 60 and 62 Cargo Door Frame

Overview

The Civil Aviation Regulations 1998, specifically within Part 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, addresses the issue of structural integrity in Airbus Industrie A319, A320, and A321 series aeroplanes. Enacted by the Australian Government, this legislation aims to ensure the safety and airworthiness of these aircraft by mandating regular inspections and repairs to critical structural components. The problem it addresses is the detection and mitigation of potential structural failures, particularly in the cargo door frames, as identified through fatigue testing. The policy objective is to maintain high safety standards in civil aviation by preventing structural failures that could lead to catastrophic outcomes. The directive AD/A320/73, effective from 30 January 1997, applies to all Airbus A320 aircraft equipped with a bulk cargo door, excluding those that have already incorporated certain modifications or service bulletins. It requires an Eddy Current Inspection of the upper frame flanges at frames 60 and 62, with mandatory repairs if cracks are detected, in line with specified Airbus Industrie service bulletins. Compliance with these inspections must occur within 20,000 flights and then every 1,200 flights thereafter, ensuring ongoing safety and structural integrity of the aircraft in question.

Scope and Application

The Civil Aviation Safety Authority's Airworthiness Directive AD/A320/73 applies specifically to Airbus A320 aircraft equipped with a bulk cargo door and lacking Airbus Industrie Modification 21277 or Airbus Industrie Service Bulletin A320-53-1021. This directive mandates that an Eddy Current Inspection of the upper frame flanges at frames 60 and 62 between stringers 40 and 42 must be performed in accordance with Airbus Industrie Service Bulletin A320-53-1022 Revision 1. If any cracks are detected during this inspection, the directive requires the cracks to be repaired following the guidelines provided in Airbus Industrie Service Bulletin A320-53-1021 Revision 1. This requirement is intended to address issues identified during fatigue testing, where cracks were found in the flanges of the affected frames. Compliance with this directive necessitates inspections within 20,000 flights and every 1,200 flights thereafter. Notably, the incorporation of Airbus Industrie Service Bulletin A320-53-1021 Revision 1 serves as the terminating action for this directive. The directive came into effect on 30 January 1997.

Key Provisions

The Civil Aviation Regulations 1998, specifically in Part 39 - 105, include a schedule of Airworthiness Directives (AD) for various aircraft, such as the Airbus Industrie A319, A320 and A321 series aeroplanes. One such directive, AD/A320/73, concerns the frame 60 and 62 cargo door frame for the A320 series aircraft equipped with a bulk cargo door installed (Airbus Industrie Modification 20029) and lacking Airbus Industrie Modification 21277 or Airbus Industrie Service Bulletin A320-53-1021. The directive requires an Eddy Current Inspection of the upper frame flanges at frames 60 and 62, specifically between stringers 40 and 42, in accordance with Airbus Industrie Service Bulletin A320-53-1022 Revision 1 (section 2). If a crack is detected during this inspection, the directive mandates that repairs be made as per Airbus Industrie Service Bulletin A320-53-1021 revision 1. Entities governed by these regulations are required to ensure that the specified inspections and repairs are carried out as mandated. Compliance with these requirements is essential to maintain the airworthiness of the aircraft and to ensure the safety of passengers and crew. The directive specifies a timeline for compliance, which involves conducting the inspection within 20,000 flights and then every 1,200 flights thereafter (section 2). It is noted that incorporating Airbus Industrie Service Bulletin A320-53-1021 Revision 1 acts as a terminating action for this directive, effectively addressing the issue it was designed to mitigate. The failure to comply with the requirements set out in AD/A320/73 could result in significant legal and safety implications. The Civil Aviation Safety Authority (CASA) may take enforcement action against any non-compliance, which could include fines, penalties, or other regulatory measures. The exact nature and extent of these consequences depend on the specific circumstances of the non-compliance and the discretion of the regulatory authority. The directive has been in effect since 30 January 1997, underscoring the importance of adhering to these safety protocols.