Overview

The Airworthiness Directive AD/BEECH 90/102, issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998, was enacted in 2004 to address a safety issue concerning the loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly in certain Raytheon (formerly Beech) aircraft models. This legislation was introduced by the Civil Aviation Safety Authority (CASA) to ensure the safe operation of Beechcraft 90 and 65-90 (King Air) Series aeroplanes. The directive aims to correct the unsafe condition by mandating inspections, corrective actions, and modifications to the engine controls and cross shaft hardware, as outlined in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634. The policy objective is to prevent potential failures that could compromise the effectiveness of control levers, potentially leading to aborted takeoffs.

Scope and Application

The Airworthiness Directive issued under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 applies specifically to the Raytheon (formerly Beech) 65-A90, B90, C90, C90A, E90, and F90 aeroplanes that meet the serial number criteria outlined in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634, dated September 2003. This AD mandates certain actions to address an unsafe condition identified with the engine controls cross shaft, specifically the improper installation and torque of the attach bolts. The requirement includes a thorough inspection and torque check of the cross shaft, correction of any identified issues, and modification of the pedestal along with the replacement of the cross shaft hardware. The directive outlines specific timelines for these actions, with the initial inspection to be conducted within the next 50 hours’ time-in-service after the effective date unless already completed within the last 50 hours, followed by inspections at intervals not exceeding 100 hours’ time-in-service until the final modification is executed. The AD also stipulates that modifications and replacements must be completed at the next scheduled maintenance interval or within 12 calendar months from the directive's effective date, whichever is later, with the possibility of performing the modifications earlier as a terminating action for the repetitive inspections and retorque requirements.

Key Provisions

The Airworthiness Directive (AD/BEECH 90/102) issued by the Civil Aviation Safety Authority (CASA) delegate pertains to the inspection and modification of specific components in Beechcraft 90 and 65-90 (King Air) Series aeroplanes. These aircraft must undergo specific inspections and modifications of their engine controls, cross shaft, and pedestal (section 1). The AD specifies that the inspection must be carried out within the next 50 hours of time-in-service (TIS) after the effective date, unless already done within the last 50 hours TIS (section 1(a)). If improper installation or incorrect torque is detected, corrective action must be taken before further flight (section 1(b)). Additionally, modification of the pedestal and replacement of the engine controls cross shaft hardware must be completed at the next scheduled maintenance interval or within 12 calendar months after the effective date of the AD, whichever occurs later (section 1(c)). This modification serves as the terminating action for the repetitive inspection and retorque requirements specified in Requirement 1. The AD imposes specific obligations on the owners and operators of the affected aircraft. They must ensure that the inspections and modifications are performed by qualified personnel and in accordance with the instructions set out in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634. The compliance schedule requires an initial inspection within the specified timeframe, followed by further inspections at intervals not exceeding 100 hours TIS until the modification is completed. Failure to adhere to these requirements may result in non-compliance with the AD and potential safety hazards. Non-compliance with the AD can result in serious safety risks, as the AD is issued to address numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. This condition could lead to limited effectiveness of the control levers, potentially causing an aborted takeoff. The AD does not explicitly state penalties for non-compliance, but the potential consequences of not adhering to the AD could include severe safety risks, aircraft grounding, and possible enforcement actions by CASA.