AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window Frame

Overview

The Civil Aviation Regulations 1998, enacted by the Australian Parliament, were introduced to address the need for comprehensive regulation of civil aviation safety within Australia, ensuring that aircraft meet necessary safety standards. Within this legislative framework, Part 39 specifically targets airworthiness directives to maintain the safety and reliability of aircraft operations. One such directive, AD/A320/50, pertains to the Airbus Industrie A319, A320 and A321 series aeroplanes, focusing on the inspection of the lower forward corner of the cockpit sliding window frame at fuselage frame 4 to prevent and mitigate the risk of cracks. The policy objective of this directive is to enhance the structural integrity and safety of the specified aircraft models through regular and systematic inspections, ensuring compliance with both Australian and international aviation safety standards. The AD/A320/50 directive applies to specific serial numbers of the Airbus Industrie A320 series, requiring an initial inspection before 15,000 flights and subsequent re-inspections at intervals or based on the presence of cracks as outlined in Airbus Industrie Service Bulletin A320-53-1082. This directive became effective from 27 April 1995, following the discovery of cracks during a full-scale fatigue test, and aims to address and rectify potential safety hazards by mandating detailed inspection procedures.

Scope and Application

The Civil Aviation Regulations 1998, under the jurisdiction of the Civil Aviation Safety Authority, specifically address the airworthiness of Airbus Industrie A319, A320, and A321 series aeroplanes. This particular Airworthiness Directive (AD/A320/50) targets specific aircraft serial numbers, namely 002 to 008, 010 to 014, 016 to 078, and 080 to 098, with additional specific requirements for aircraft serial numbers 003, 004, and 023. The directive mandates a thorough inspection of the lower forward corner of the sliding window frame at fuselage frame 4 using high-frequency eddy current methods, as detailed in Airbus Industrie Service Bulletin A320-53-1082. Compliance with this directive is essential for maintaining the airworthiness of these aircraft and includes initial inspections before 15,000 flights, periodic re-inspections at 15,000 flight intervals for frames without cracks, and more stringent schedules for frames with detected cracks as outlined in Airbus Industrie Service Bulletin A320-53-1082. This directive has been in effect since 27 April 1995, following the discovery of cracks during a full-scale fatigue test.

Key Provisions

The Civil Aviation Regulations 1998, specifically PART 39 - 105, includes an Airworthiness Directive (AD/A320/50) concerning Airbus Industrie A319, A320, and A321 series aeroplanes. This directive mandates inspections of the lower forward corner of the cockpit sliding window frame at fuselage frame 4 for certain aircraft serial numbers. The directive is applicable to aircraft with serial numbers ranging from 002 to 008, 010 to 014, 016 to 078, and 080 to 098. However, specific serial numbers 003 and 004 require inspection of the left-hand window frame only, and serial number 023 requires inspection of the right-hand window frame only. The AD requires an inspection using high-frequency eddy current around the five specified fasteners at the lower forward corner of the sliding window frame at fuselage frame 4. This inspection must be conducted in accordance with Airbus Industrie Service Bulletin A320-53-1082. The initial inspection must occur before the aircraft accumulates 15,000 flights. For frames without cracks, re-inspection is required at intervals of 15,000 flights. Frames with cracks must be re-inspected according to the schedule specified in paragraph B(2)(b) of Airbus Industrie Service Bulletin A320-53-1082. It is noted that modifications made in accordance with Airbus Industrie Service Bulletin A320-53-1044 will negate the need for inspections under this AD. Compliance with the AD is essential to ensure airworthiness and safety. The directive imposes specific obligations on the aircraft operators to conduct and document the required inspections. Failure to comply with these requirements may result in the aircraft being deemed unairworthy, leading to potential grounding and enforcement actions by the Civil Aviation Safety Authority (CASA). The AD came into effect on 27 April 1995, following the discovery of cracks at the lower forward corner of the sliding window frame at frame 4 during a full-scale fatigue test. This highlights the importance of regular inspections to prevent structural failure and ensure the safety of the aircraft and its occupants. Failure to adhere to the requirements of this Airworthiness Directive may result in serious safety consequences, including potential aircraft structural failure. While the Civil Aviation Regulations 1998 do not specify penalties for non-compliance in this context, CASA may take enforcement actions against operators who fail to comply with ADs. These actions can include fines, directives to rectify non-compliance, and in severe cases, suspension or revocation of the aircraft's airworthiness certificate. It is therefore crucial for operators to strictly adhere to the inspection schedules and procedures outlined in the AD to maintain compliance and ensure the continued airworthiness of their aircraft.