AD/BEECH 95/28 - Elevator Control Fittings

Overview

The Civil Aviation Regulations 1998, enacted by the Australian Parliament, were established to regulate civil aviation activities in Australia and ensure safety standards. One specific legislative instrument, F2006B04300, pertains to the airworthiness directives for certain Beechcraft 95 series aeroplanes, focusing on elevator control fittings. This regulation was introduced to address the identified problem of cracking and potential failure of magnesium elevator control fittings, which could lead to catastrophic in-flight incidents. The policy objective is to mandate the determination of the composition of elevator control fittings and subsequent action if they are found to be made of magnesium, ensuring that all affected aircraft are fitted with safe, aluminium replacements. Compliance with these directives is crucial to maintain the airworthiness of the aircraft and ensure the safety of all passengers and crew.

Scope and Application

The Civil Aviation Regulations 1998, as amended, apply to specific models of Beechcraft 95 (Travelair) series aeroplanes, namely those with serial numbers ranging from TD-2 through TD-721. This legislation mandates the determination of the composition of elevator control fittings, specifically requiring a check to ascertain whether they are made of aluminium or magnesium, in accordance with Beechcraft Mandatory Service Bulletin 2242 Revision 1. If the fittings are identified as aluminium, no further action is required. However, if they are magnesium, a visual inspection is necessary to identify any cracks; cracked magnesium fittings must be replaced with aluminium fittings before further flight. The installation of aluminium fittings is considered the terminating action for compliance with this directive. This Act applies to the Commonwealth of Australia and its regulatory reach extends to all aircraft operating within its jurisdiction. There are no stated exclusions or exemptions within the scope of this directive, and compliance must be achieved before the aeroplanes exceed 100 hours of time in service after 30 November 1989, or at the next scheduled inspection for the issue of a Maintenance Release, whichever comes later, and subsequently at intervals not exceeding 100 hours of time in service. The application and requirements of this directive may be further refined through subordinate instruments as necessary.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes an Airworthiness Directive (AD) pertaining to Beechcraft 95 (Travelair) Series Aeroplanes, AD/BEECH 95/28, which addresses elevator control fittings (section 1). This directive applies to models 95, B95, B95A, D95A, E95 with serial numbers ranging from TD-2 through TD-721. The key requirement outlined in this directive is to determine the composition of the elevator control fittings, which must be done in accordance with Beechcraft Mandatory Service Bulletin 2242 Revision 1. If the fittings are found to be made of aluminium, no further action is necessary. However, if the fittings are determined to be magnesium, they must be visually inspected for cracks as per the same service bulletin. Any cracked magnesium fittings must be replaced with aluminium fittings before the aircraft can be flown again. This AD imposes clear obligations on the operators and maintenance personnel of the affected Beechcraft models. They are required to ascertain the material composition of the elevator control fittings and inspect them for cracks if they are magnesium. If any cracks are found in magnesium fittings, they must be replaced with aluminium fittings before further flight. Compliance with this directive must occur before the aircraft exceeds 100 hours of time in service after 30 November 1989 or at the next scheduled inspection for the issuance of a Maintenance Release after this date, whichever is later (section 1). Furthermore, these checks and replacements must continue at intervals not exceeding 100 hours of time in service until aluminium fittings are installed (section 2). Failure to comply with this AD can have serious consequences. The Federal Aviation Administration (FAA) has reported instances of cracking and failure of magnesium elevator control fittings, which could result in a loss of aircraft control in flight. While the Civil Aviation Regulations do not explicitly state penalties for non-compliance with this specific AD, non-compliance with regulations governing airworthiness can lead to severe consequences, including fines and imprisonment under the Civil Aviation Act 1988. The maximum penalties for breaches of airworthiness requirements can include substantial fines and imprisonment terms, reflecting the critical importance of adhering to these directives to ensure flight safety.