AD/PITTS S-2/5 - Induction Air Box Door - Inspection and Modification

Overview

The Civil Aviation Regulations 1998, enacted by the Australian Government, form a critical part of the nation's regulatory framework for aviation safety. This particular legislative instrument pertains to the Pitts S-1 and S-2 series aeroplanes, with the specific directive AD/PITTS S-2/5 addressing the inspection and modification of the induction air box door assembly. This directive applies to Model S-2A aeroplanes with serial numbers 2001 to 2059 and was introduced to address safety concerns identified in these aircraft models. The policy objective is to ensure that any structural weaknesses, particularly in the welded areas of the induction air box flapper door assembly, are identified and rectified to prevent potential in-flight issues. Compliance with these regulations is mandatory, with inspections required before each daily flight until the modification is made, and modifications mandated within 100 hours of time in service following a specified date. The enactment of this regulation by the Civil Aviation Safety Authority under the authority of the Civil Aviation Act 1988, reflects a commitment to maintaining high safety standards within Australia's aviation sector. By specifying detailed requirements for inspection and modification, the regulation aims to proactively address potential safety hazards, thereby enhancing the overall safety and reliability of the affected aircraft models. This legislative measure underscores the importance of regular maintenance and adherence to safety directives to protect both the aircraft and its occupants.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 – 105, mandates that the Airworthiness Directives apply to Pitts S-1 and S-2 series aeroplanes, with a particular focus on model S-2A aircraft bearing serial numbers between 2001 and 2059. This regulation is concerned with ensuring the structural integrity of the induction air box flapper door assembly, which is identified by Pitts part number 2-7112-7. The directive applies directly to these aircraft and their operators, requiring both an inspection and potentially a modification to maintain compliance with safety standards. The inspection, which can be performed by the pilot, must be conducted visually to check for any cracks in the welded areas of the flapper door assembly, and it must be done prior to the first flight of each day until the modification is incorporated. The modification, involving the installation of a stiffener identified as Pitts part number 2-7112-16, is to be completed within 100 hours of time in service following 28 September 1973, with a specific requirement for aircraft that have more than 50 hours of service since new. This directive underscores the importance of regular maintenance and adherence to safety directives for ensuring the continued airworthiness of the specified aircraft models.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandates that Pitts S-2A series aeroplanes with serial numbers (S/Nos.) between 2001 and 2059 undergo certain inspections and modifications to their induction air box flapper door assembly. Under section (AD/PITTS S-2/5), the regulation requires an inspection of the flapper door assembly, Pitts P/N 2-7112-7, to visually check for cracks in the welded areas. This inspection can be performed by the pilot as specified in the note accompanying the directive. Additionally, a modification must be made by installing a stiffener, Pitts P/N 2-7112-16, to the flapper door assembly, in accordance with Pitts Service Letter No. 2. The compliance timeline for these actions is set out in the regulation, with the inspection required prior to the first flight of each day until the modification is incorporated, and the modification itself needing to be completed within 100 hours of time in service after 28 September 1973. These provisions place clear obligations on the operators of the affected Pitts S-2A aircraft. They must ensure that the visual inspection for cracks in the flapper door assembly is conducted before each flight. Furthermore, operators are required to install the specified stiffener within 100 hours of time in service post the date mentioned, to mitigate any identified risks associated with the flapper door assembly. These obligations are designed to ensure the airworthiness and safety of the aircraft, and compliance is critical to avoid any safety hazards that could arise from the failure to adhere to these directives. Failure to comply with the inspection and modification requirements stipulated in these regulations could result in serious consequences. The Civil Aviation Safety Authority (CASA) has the authority to enforce the provisions of the Civil Aviation Regulations. Non-compliance could lead to enforcement actions, which may include fines or other penalties as determined by CASA. The specific penalties are not detailed in the extract, but they may vary depending on the severity and frequency of the breach, as well as any resulting harm or risk posed to aviation safety.