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 CAR 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 90 and 65-90 (King Air) Series Aeroplanes
AD/BEECH 90/99 Main Landing Gear Torque Knee 4/2002
Applicability: | Model | Serial Number |
| 65-90, 65-A90, B90, C90, and C90A. | LJ-1 through LJ-1559 |
| 65-A90-1 | LM-1 through LM-141 |
| 65-A90-4 | LU-1 through LU-16 |
| E90 | LW-1 through LW-347 |
| H-90 | LL-1 through LL-61 |
Requirement: 1. Inspect the main landing gear upper torque knee and lower torque knee for fatigue cracks in accordance with Accomplishment Instructions paragraph of Raytheon Aircraft Mandatory Service Bulletin SB 32-3134, Revision 1, revised July 1999; and the applicable aircraft maintenance manual.
2. If fatigue cracks are found in the main landing gear torque knees during any inspection required by this Directive, replace the cracked torque knees in accordance with Service Bulletin SB 32-3116, issued October 1999.
Note 1: When both left and right main landing gear upper and lower torque knees are replaced with new upper torque knees, part number 50-810032-12, and new lower torque knees, part number 50-810295-25, in accordance with Service Bulletin SB 32-3116, the repetitive inspection requirements of this Directive are no longer required.
Note 2: FAA AD 2002-01-10 Amdt 39-12602 refers.
Compliance: 1. Within 100 hours’ time in service after 18 April 2002; thereafter at intervals not to exceed 1,000 hours’ time in service.
2. Before further flight.
This Airworthiness Directive becomes effective on 18 April 2002.
Beechcraft 90 and 65-90 (King Air) Series Aeroplanes
AD/BEECH 90/99 (continued)
Background: The FAA received numerous reports of fatigue cracks on main landing gear torque knees. In at least four cases, the main landing gear separated from the aircraft.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 8 March 2002
The above AD is notified in the Commonwealth of Australia Gazette on 27 March 2002.
Overview
The Airworthiness Directive AD/BEECH 90/99 was issued by the Civil Aviation Safety Authority (CASA) on 18 April 2002, addressing safety concerns regarding the main landing gear torque knees of Beechcraft 90 and 65-90 (King Air) series aeroplanes. This directive was introduced in response to reports from the Federal Aviation Administration (FAA) of fatigue cracks in the main landing gear torque knees, which in several instances led to the separation of the main landing gear from the aircraft. The policy objective of this directive is to ensure the safety of aircraft by mandating inspections and repairs of the specified components to prevent potential in-flight failures. Compliance with the directive requires inspections and, if necessary, replacement of the torque knees within specific timeframes, thereby mitigating the risk of structural failure due to fatigue.
Scope and Application
The Airworthiness Directive AD/BEECH 90/99 applies specifically to the Beechcraft 90 and 65-90 (King Air) Series Aeroplanes with serial numbers LJ-1 through LJ-1559, 65-A90-1LM-1 through LM-141, 65-A90-4LU-1 through LU-16, E90LW-1 through LW-347, and H-90LL-1 through LL-61. This directive is issued by the Civil Aviation Safety Authority (CASA) delegate, David Alan Villiers, under subregulation 39.1(1) of the Civil Aviation Regulations 1998, and it mandates corrective actions to address identified safety concerns with the main landing gear torque knees of these aircraft. The directive requires inspections for fatigue cracks and the replacement of any cracked torque knees, as outlined in the specific requirement and compliance sections. The AD becomes effective from 18 April 2002 and applies within the Commonwealth of Australia, with inspections and replacements mandated within 100 hours’ time in service after this date and thereafter at intervals not exceeding 1,000 hours’ time in service, or before further flight. Once all specified torque knees are replaced, further repetitive inspections under this directive are no longer required.
Key Provisions
The Airworthiness Directive AD/BEECH 90/99 pertains to the Beechcraft 90 and 65-90 (King Air) Series Aeroplanes and mandates specific actions to address identified safety concerns. According to section (a) of the requirement, all affected aircraft models, including 65-90, 65-A90, B90, C90, and C90A, must undergo inspections of their main landing gear upper and lower torque knees for fatigue cracks (section 1). These inspections must be conducted in accordance with the Accomplishment Instructions in Raytheon Aircraft Mandatory Service Bulletin SB 32-3134, Revision 1, and the applicable aircraft maintenance manual. If any fatigue cracks are detected during these inspections, section 2 of the requirement mandates the replacement of the cracked torque knees as per Service Bulletin SB 32-3116. The AD specifies that inspections should occur within 100 hours of time in service after 18 April 2002, and thereafter, at intervals not exceeding 1,000 hours of time in service or before further flight.
The AD imposes obligations on aircraft operators to ensure that the specified inspections and repairs are carried out in a timely and thorough manner. Operators are required to follow the instructions provided in the referenced service bulletins and maintenance manuals to identify and rectify any potential safety issues. The directive also includes a note clarifying that if both the left and right main landing gear upper and lower torque knees are replaced with new parts, the repetitive inspection requirements of this AD no longer apply. This ensures that once the corrective action is completed, the aircraft can operate without further need for these specific inspections.
The AD specifies that failure to comply with the mandated inspections and repairs could result in serious safety risks. The directive references FAA AD 2002-01-10 Amdt 39-12602, indicating alignment with other regulatory bodies' requirements. Non-compliance with this AD could potentially lead to severe consequences, including the possibility of the main landing gear separating from the aircraft, as reported in several instances. While the AD does not explicitly state civil or criminal penalties, the implications of failing to adhere to these safety requirements could result in significant legal and financial consequences for operators, including grounding of the aircraft until the issues are resolved.