AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Beechcraft 300 Series Aeroplanes
AD/BEECH 300/18 Engine Controls Cross Shaft 11/2004
Applicability: Raytheon (Formely Beech) model 300, 300LW, B300 and B300C aeroplanes having serial numbers as detailed in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634, dated September 2003.
Requirement: 1. Inspect the engine controls/cross shaft/pedestal for proper installation and carry out a torque check of the attach bolts, in accordance with Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634.
2. If any improper installation or wrong torque is found during any inspection required by Requirement 1 of this Directive, correct the installation or torque in accordance with Part I, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634.
3. Unless previously accomplished modify the pedestal and replace the engine controls cross shaft hardware in accordance with Part II, Accomplishment Instructions of Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634.
Modification of the pedestal and replacement of the engine controls cross shaft hardware is the terminating action for the repetitive inspection and re-torque requirements specified in Requirement 1 of this Directive.
Note 1: FAA AD 2004-17-02 Amdt 39-13774 refers.
Note 2: The aeroplane maintenance manual also addresses the issues detailed in Requirements 1,2 and 3 of this Directive.
Compliance: For Requirement 1: Initially inspect within the next 50 hours time-in-service (TIS) after the effective date of this Directive, unless already done within the last 50 hours TIS, and thereafter at intervals not to exceed 100 hours TIS until the modification in Requirement 3 of this Directive is done.
For Requirement 2: Before further flight.
For Requirement 3: At the next scheduled Maintenance/inspection interval or 12 calendar months after the effective date of this Directive, whichever occurs later.
Beechcraft 300 Series Aeroplanes
AD/BEECH 300/18 (continued)
You may do this modification before this time as terminating action for the repetitive inspection and retorque requirements.
This Airworthiness Directive becomes effective on 28 October 2004.
Background: This Directive is the result of numerous reports of loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly. The requirements detailed in this Directive are to detect and correct loose bolts not securing the pedestal cross shaft, which could result in limited effectiveness of the control levers. This failure could lead to an aborted takeoff.
James Coyne
Delegate of the Civil Aviation Safety Authority 17 September 2004
The above AD is notified in the Commonwealth of Australia Gazette on 6 October 2004.
Overview
The Airworthiness Directive (AD) AD/BEECH 300/18, issued under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998, was enacted on 28 October 2004 by the Civil Aviation Safety Authority (CASA) to address safety concerns related to loose bolts on the pedestal attachment of the throttle/prop cross shaft assembly in Beechcraft 300 series aeroplanes. This directive aims to ensure the proper installation and torque of the attach bolts to prevent any failure that could result in limited effectiveness of the control levers and potentially lead to an aborted takeoff. The directive applies to Raytheon (formerly Beech) model 300, 300LW, B300 and B300C aeroplanes with specific serial numbers as outlined in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73-3634, dated September 2003. The compliance schedule requires inspections within the next 50 hours time-in-service after the effective date of the directive, and further inspections at intervals not exceeding 100 hours time-in-service until the modification is completed.
Scope and Application
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 applies specifically to Beechcraft 300 Series aeroplanes, including models 300, 300LW, B300, and B300C, with serial numbers as outlined in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634 dated September 2003. This AD mandates actions necessary to rectify an unsafe condition identified in the engine controls cross shaft pedestal. The directive requires inspections and corrective actions to ensure the proper installation and torque of the attach bolts of the engine controls cross shaft, with specific reference to the instructions detailed in the Raytheon Aircraft Company Mandatory Service Bulletin. Non-compliance with these requirements could lead to safety issues, including the potential for limited effectiveness of control levers, which could, in turn, result in severe operational hazards such as aborted takeoffs. The AD sets forth a compliance schedule for these inspections and modifications, specifying intervals and deadlines to ensure timely and effective maintenance.
Key Provisions
The Airworthiness Directive AD/BEECH 300/18 pertains specifically to Raytheon (formerly Beech) model 300, 300LW, B300, and B300C aeroplanes with certain serial numbers, as outlined in Raytheon Aircraft Company Mandatory Service Bulletin No. SB 73–3634, dated September 2003. According to the applicability section of this directive, it is necessary to inspect the engine controls/cross shaft/pedestal for proper installation and to conduct a torque check of the attach bolts. These inspections must be performed in accordance with Part I of the Accomplishment Instructions of the aforementioned service bulletin. If any improper installation or incorrect torque is found during these inspections, corrective action must be taken as outlined in Part I of the Accomplishment Instructions. Additionally, unless previously completed, the pedestal must be modified, and the engine controls cross shaft hardware must be replaced according to Part II of the Accomplishment Instructions. It is crucial to note that the modification of the pedestal and replacement of the cross shaft hardware serve as the terminating action for the repetitive inspection and re-torque requirements specified in Requirement 1 of this Directive.
The obligations imposed by this Airworthiness Directive are multifaceted. Firstly, the directive mandates that inspections must be conducted within 50 hours time-in-service (TIS) after the effective date of the directive, unless already performed within the last 50 hours TIS. These inspections must continue at intervals not exceeding 100 hours TIS until the modification in Requirement 3 of the directive is completed. Secondly, any identified issues must be corrected before further flight. Lastly, the modification and replacement actions must be carried out at the next scheduled maintenance/inspection interval or within 12 calendar months from the directive’s effective date, whichever comes later. This directive aims to ensure the continued airworthiness and safety of the specified aircraft by addressing potential issues with the engine controls/cross shaft/pedestal.
Failure to comply with this Airworthiness Directive can result in serious consequences. Non-compliance with the inspection and corrective actions could lead to the continued operation of aircraft with potentially unsafe conditions, thereby increasing the risk of accidents or incidents. The directive does not explicitly state penalties for non-compliance; however, non-compliance with airworthiness directives in Australia is generally considered a breach of civil aviation regulations. Such breaches can result in enforcement actions by the Civil Aviation Safety Authority (CASA), which may include fines, enforcement notices, or even the grounding of the aircraft in question until the required actions are completed. The severity of the penalties depends on the nature and extent of the non-compliance and any resultant harm or risk to aviation safety.