Airworthiness Directive AD/BEECH 90/99 Main Landing Gear Torque Knee
Beechcraft King Air 90 · Other Documents
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) of Australia, specifically addressing the Beechcraft King Air 90 and related models. The directive mandates inspections and potential replacements of the main landing gear torque knees due to reported fatigue cracks that could lead to separation of the landing gear from the aircraft. The AD outlines specific compliance timelines and procedures to ensure the safety and airworthiness of the affected aircraft. It is crucial for operators and maintenance personnel to adhere to these directives to mitigate risks associated with landing gear failures.
- Inspect main landing gear torque knees for fatigue cracks within 100 hours after April 18, 2002.
- If cracks are found, replace the torque knees as per Service Bulletin SB 32-3116.
- Repetitive inspections are not required if both torque knees are replaced with new parts.
- Compliance intervals for inspections are not to exceed 1,000 hours of service after the initial inspection.
- The directive applies to specific serial numbers of the Beechcraft King Air 90 series.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Other Documents
- Year
- 2002
- Pages
- 2
- File size
- 15 KB
- Publisher
- services.casa.gov.au
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In this document
Applicability
The directive applies to several models within the Beechcraft King Air series, specifically the 65-90, 65-A90, B90, C90, C90A, E90, and H-90, with specified serial number ranges for each model.
Requirements
Operators are required to inspect the main landing gear upper and lower torque knees for fatigue cracks. If any cracks are found, the affected torque knees must be replaced according to the referenced service bulletins. Notably, if both upper and lower torque knees are replaced with new parts, the repetitive inspection requirements are waived.
Compliance
The inspections must be completed within 100 hours of service after the directive's effective date of April 18, 2002, and subsequently at intervals not exceeding 1,000 hours. Immediate action is required if cracks are discovered.
Background
The directive was issued following multiple reports of fatigue cracks leading to serious incidents, including the separation of landing gear from the aircraft. This emphasizes the critical nature of the inspections mandated by the AD.
Safety notes
- Fatigue cracks in the main landing gear can lead to separation from the aircraft, posing serious safety risks.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 1 of 2 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. COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 2 of 2 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.