AD/BEECH 55/73 - Elevator Control Fittings

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, introduced the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives to ensure the continued safety of aircraft in Australian airspace. The Act was enacted to address the problem of in-flight failures due to the cracking of magnesium elevator control fittings in certain Beechcraft aeroplanes. The policy objective is to mandate the inspection and replacement of such fittings to prevent potential in-flight failures that could lead to catastrophic outcomes. The directive applies to Beechcraft 55, 58, and 95-55 (Baron) Series Aeroplanes with specific serial numbers. Compliance requires that affected aircraft be inspected and, if necessary, have their magnesium elevator control fittings replaced with aluminium ones before exceeding 100 hours of time in service after 30 November 1989, and subsequently at intervals not exceeding 100 hours. The Airworthiness Directive AD/BEECH 55/73, introduced by CASA, mandates the determination and replacement of magnesium elevator control fittings in certain Beechcraft aeroplanes to prevent in-flight failures. The directive was developed in response to reports of cracking and failure of such fittings, which could lead to the loss of control over the aircraft. The requirement is for operators to determine the composition of the elevator control fittings and replace any magnesium fittings with aluminium ones, as per the Beechcraft Mandatory Service Bulletin 2242 Revision 1. The directive ensures that these safety measures are implemented before exceeding 100 hours of time in service after 30 November 1989 and at regular intervals thereafter.

Scope and Application

The Civil Aviation Regulations 1998, under the scope of the Civil Aviation Safety Authority, specifically address the airworthiness of Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes through AD/BEECH 55/73, focusing on elevator control fittings. This legislation applies to specific models of the Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes, namely those with particular serial numbers as outlined within the directive. The regulation mandates a determination of the composition of elevator control fittings, requiring a visual inspection if the fittings are magnesium and subsequent replacement with aluminium fittings if any cracks are detected. Compliance with this directive is essential and must occur either before exceeding 100 hours of time in service after 30 November 1989, or at the next scheduled inspection for issuing a Maintenance Release after that date, and thereafter at intervals not exceeding 100 hours’ time in service until the aluminium fittings are installed. The directive references the FAA AD 89-05-02, highlighting the critical nature of the requirement due to the potential for in-flight failure and loss of the aircraft. This regulation underscores the importance of adhering to specific safety standards to ensure the continued airworthiness of these aircraft models.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105 and the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, mandate actions concerning the elevator control fittings of certain Beechcraft 55, 58, and 95-55 (Baron) series aeroplanes. The relevant directive, AD/BEECH 55/73, pertains to models 95-55, 95-A55, 95-B55, 95-B55A with serial numbers TC-1 through TC-1287, and models 95-C55, 95-C55A, D55, D55A with serial numbers TE-1 through TE-767. Section 1 of the directive requires operators to determine whether the elevator control fittings are made of aluminium or magnesium, following the specifications in Beechcraft Mandatory Service Bulletin 2242 Revision 1. If the fittings are aluminium, no further action is required. However, if they are magnesium, a visual inspection must be conducted, as per the same bulletin, and any cracked fittings must be replaced with aluminium fittings before further flight. Operators of the specified aircraft must comply with this directive by performing the required actions before exceeding 100 hours’ time in service after 30 November 1989, or at the next scheduled inspection for the issue of a Maintenance Release after 30 November 1989, whichever occurs later. Furthermore, operators must repeat these checks at intervals not exceeding 100 hours’ time in service until aluminium fittings are installed. These compliance requirements are designed to ensure that the aircraft remain airworthy and safe for operation. Failure to adhere to these directives may result in significant safety risks, including potential in-flight failures of the elevator control fittings, which could lead to loss of control of the aircraft. The directive is based on reports received by the Federal Aviation Administration (FAA) regarding the cracking and failure of magnesium elevator control fittings. The FAA's AD 89-05-02 references similar concerns, highlighting the international consensus on the need for these safety measures. Any breach of these regulations could lead to severe consequences, including the grounding of the aircraft until compliance is achieved, and potential civil or criminal penalties for non-compliance. The specific penalties are not detailed in the directive but could include fines and other regulatory actions under the Civil Aviation Act 1988.