AD/B737/117 - Main Cargo Door

Overview

The Civil Aviation Regulations 1998, under Part 39, Section 105, includes Airworthiness Directives that are essential for maintaining the safety and integrity of civil aircraft in Australia. The specific AD/B737/117 issued for Boeing 737 Series Aeroplanes addresses concerns identified by the Federal Aviation Administration (FAA) regarding cracks in the main cargo door of the 737-200 and -300 series aircraft. This directive was enacted to ensure the structural integrity of the main deck cargo door and adjacent fuselage components, thereby preventing potential in-flight failures. The directive mandates a detailed visual inspection and replacement of any cracked parts to mitigate the risk of catastrophic structural failure. Compliance with this directive is crucial for operators of the specified aircraft models to ensure continued airworthiness and passenger safety.

Scope and Application

The Civil Aviation Safety Authority's (CASA) airworthiness directive applies to Boeing 737-200 and -300 series aircraft that are equipped with a main deck cargo door installed in accordance with Supplemental Type Certificate SA2969SO. This directive mandates a detailed visual inspection to detect cracks in specific areas of the main deck cargo door and upper jamb of the fuselage, with a focus on the hinge and lift actuator box area. Such inspections are critical to maintaining the structural integrity of the cargo door and fuselage, thereby preventing potential in-flight failure which could be catastrophic. Compliance with this directive requires that inspections be conducted before 31 May 1998, and subsequently at intervals not exceeding 600 flight cycles. The directive references FAA AD 98-04-41 Amdt 39-10352 and became effective on 21 May 1998. It is applicable nationally, governed under the Commonwealth of Australia's Civil Aviation Regulations 1998.

Key Provisions

The Civil Aviation Regulations 1998, specifically in Part 39 - 105 under the Civil Aviation Safety Authority's schedule of airworthiness directives, include a directive concerning Boeing 737 series aeroplanes, identified as AD/B737/117 (Part 39 - 105(1)). This directive mandates a detailed visual inspection of the main cargo door of Model 737-200 and -300 series aircraft to detect any cracks in the hinge and lift actuator box area of the main deck cargo door, as well as the upper jamb of the fuselage (Part 39 - 105(2)). The directive requires particular attention to be paid to the upper frame of the fuselage, the upper jamb frames of the main deck cargo door, the primary longeron, and the clips of the fuselage, especially in the hinge and lift actuator box area (Part 39 - 105(3)). Operators of the specified Boeing 737 models must ensure compliance with the directive by conducting the required inspections before 31 May 1998, and subsequently at intervals not exceeding 600 flight cycles (Part 39 - 105(4)). The directive became effective on 21 May 1998, marking the date from which compliance was mandatory (Part 39 - 105(5)). This directive is grounded on reports received by the Federal Aviation Administration (FAA) regarding cracks in the specified areas of the aircraft, which if left unchecked, could lead to a reduction in the structural integrity of the main cargo door and/or fuselage, potentially resulting in the loss or opening of the main deck cargo door during flight (Part 39 - 105(6)). Failure to comply with the airworthiness directive could result in significant safety risks, given the potential for structural failure of the cargo door or fuselage. Such non-compliance could be viewed as a breach of the Civil Aviation Regulations 1998, which could lead to enforcement actions by the Civil Aviation Safety Authority. The consequences for non-compliance could include administrative penalties, enforcement actions, and potentially criminal charges if the non-compliance is deemed to have endangered the safety of an aircraft in flight. The maximum penalties for such offences are not specified within this particular airworthiness directive but could vary based on the severity of the breach and the specific provisions of the Civil Aviation Act 1988 and associated regulations.