AD/PITTS S-2/7 - Control Tube Assembly - Inspection and Modification

Overview

The Civil Aviation Regulations 1998, which are overseen by the Civil Aviation Safety Authority (CASA), were enacted to ensure the safety of civil aviation in Australia. Specifically, Part 39 - 105 within these regulations includes Airworthiness Directives (ADs) that address specific safety concerns for particular aircraft models. One such AD, AD/PITTS S-2/7, pertains to Pitts S-1 and S-2 series aeroplanes and mandates a detailed inspection and modification of the control tube assembly. This directive was introduced to mitigate the risk of structural failure in the control tube assembly, particularly at the junction where the control stick housing is welded to the control tube, which could lead to serious safety issues if left unaddressed. The policy objective behind this AD is to ensure that all model S-2A aeroplanes undergo the specified inspections and modifications to maintain their airworthiness and ensure the safety of flight operations.

Scope and Application

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, includes the Civil Aviation Safety Authority Schedule of Airworthiness Directives, which governs the inspection and modification requirements for Pitts S-1 and S-2 Series Aeroplanes. This legislation applies to all model S-2A aircraft, focusing on the control tube assembly to ensure safety. The regulation mandates a visual inspection of the Control Tube Assembly P/No. 2-5100 for cracks at the junction of the control stick housing at the aft end of the tube where it is welded to the control tube. This inspection must be performed before each flight until the tube is modified. Additionally, the control tube must be modified in accordance with Pitts Aviation Enterprises Service Letter No. 5. This modification should be completed within 100 hours of time in service following the date of the directive, 21 May 1975. The repetitive inspection must be documented on the maintenance release as maintenance required, with the option for the pilot in command to perform the inspection without certification, or alternatively, it can be performed and certified by a Licensed Aircraft Maintenance Engineer. This legislation is applicable across the Commonwealth of Australia, and while it is specific to the Pitts S-2A model, it underscores the importance of stringent safety measures in civil aviation.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, includes AD/PITTS S-2/7 which mandates specific procedures for Pitts S-1 and S-2 Series Aeroplanes, particularly focusing on the Control Tube Assembly. The directive applies to all model S-2A aircraft (section 1). The main requirement is a visual inspection of the Control Tube Assembly P/No. 2-5100 for any cracks at the junction of the control stick housing at the aft end of the tube, where it is welded to the control tube (section 1.1). The inspection area must be cleared of any paint to ensure visibility and must remain unpainted until the modification is performed (section 1.1 note). Additionally, the Control Tube Assembly P/No. 2-5100 must be modified according to the specifications outlined in Pitts Aviation Enterprises Service Letter No. 5 (section 1.2). The repetitive inspection mandated by this directive must be documented on the maintenance release as maintenance required (section 1.3). Notably, the pilot in command may perform this inspection without requiring certification, although in other cases, certification is required and may be done by a Licensed Aircraft Maintenance Engineer (section 1.3). The obligations imposed by this legislation include ensuring that the inspection of the Control Tube Assembly P/No. 2-5100 for cracks is conducted before each flight after 21 May 1975 until the modification is completed (section 1.1). The modification must be carried out within 100 hours of time in service after 21 May 1975 (section 1.2). The repetitive nature of this inspection means it must be performed continuously, and the results must be documented on the maintenance release (section 1.3). The documentation must clearly state the requirement for maintenance, and where appropriate, it must be certified by a qualified professional (section 1.3). Failure to comply with the requirements outlined in AD/PITTS S-2/7 could result in significant consequences. The legislation does not explicitly state penalties for non-compliance. However, any failure to adhere to the inspection and modification requirements could potentially lead to safety risks, which could in turn result in regulatory action under other provisions of the Civil Aviation Regulations 1998. This could include enforcement actions by the Civil Aviation Safety Authority, which may encompass fines or other regulatory measures. The exact penalties would depend on the specific circumstances of the non-compliance and any resultant safety issues.