COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 200 (Super King Air) Series Aeroplanes
AD/BEECH 200/35
Amdt 6
Applicability: All models.
Wing Fatigue Life Limitation 3/98
Requirement: 1. For aircraft serial numbers BB-2 through BB-161:-
Retire from service the outer wing lower spar cap assembly in accordance with Beech Service Bulletin No 2240.
Note: FAA AD 89-02-03 refers.
2. (a). For aircraft serial numbers BB-1158, BB-1167, BB-1193 through BB-1203, BB-1207 through BB-1312, BB1314 through BB-1334, BL-124 through BL- 132, and BT-33:
Modify the lower forward wing spar attachment fittings by installing Beech Kit No 101-4050, and,
2. (b). For aircraft serial numbers BB-1158, BB-1167, BB-1193 and on, BL-73 and on, BN-5 and on, and BT-31 and on:
Remove the wings and inspect the wing spar shear attach fittings for cracks using a fluorescent dye penetrant method in accordance with CAO 108.10.
Note: FAA AD 91-12-10 refers.
3. For all aircraft, retire from service the wing centre and outer section main spar lower cap assemblies.
Note 1: The lower cap assemblies includes the lower wing attachment fittings.
Note 2: Section 4-00-00 of the Beech 200 Maintenance Manual contains related information.
Compliance: 1. Retire in accordance with Beech Service Bulletin No 2240.
2. (a). Modify prior to exceeding 9 500 hours component time in service.
2. (b). Initially inspect prior to 15000 hours time in service. Re-inspect at intervals not to exceed 6000 hours component time in service until 30000 flight cycles. Thereafter inspect at intervals of 1500 hours time in service, or 1200 flight cycles, whichever occurs sooner.
3. Retire prior to exceeding 30 000 hours component time in service. This amendment becomes effective on 26 February 1998.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: Amendment 3 introduced a reduced spar-cap life for aircraft listed in Requirement 1. Early spar cap assemblies were manufactured with a smaller critical radius in the spar cap fitting which reduced the spar cap fatigue life. Beech SB No. 2240 refers.
Amendment 4 introduced the attachment fitting requirements of FAA AD 91-12-10 and the interim lives applicable to Requirement 2 aircraft. The lower life limits for the unmodified attachment fittings result from a fatigue test in which the shear fitting failed well short of the interim 15 000 hour life. The Beech modification kit introduces cold worked bushes to the attachment fitting lug holes, reducing their susceptibility to fatigue failure.
Amendment 5 makes a correction to the applicability of Requirement 2.
Amendment 6 incorporates revised wing spar shear attachment fitting fatigue lives of 30000 hours time in service with an associated inspection schedule. These extensions to the aircraft fatigue lives have been accepted by CASA for Australian operators, based on a critical review of the manufacturer’s fatigue test results.
Amendment 5 of this airworthiness directive became effective on 14 September 1995. Amendment 4 of this airworthiness directive became effective on 5 September 1991. The original issue of this airworthiness directive became effective on
30 September 1981.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, provide a comprehensive framework for ensuring the safety of civil aviation within Australia. One specific focus of these regulations is the issuance of Airworthiness Directives (ADs) to address safety issues in aircraft operations. The Civil Aviation Safety Authority (CASA) is the body responsible for enforcing these regulations and issuing ADs to mitigate identified safety risks. In the context of the Beechcraft 200 (Super King Air) Series Aeroplanes, the AD/BEECH 200/35 aims to address the problem of wing fatigue by specifying maintenance and operational requirements to ensure the aircraft remain airworthy. The overarching policy objective is to enhance aviation safety by mandating specific maintenance actions and inspections that are based on empirical data and rigorous testing. These directives are designed to extend the operational life of critical components while maintaining the highest safety standards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39, includes detailed airworthiness directives concerning Beechcraft 200 (Super King Air) Series Aeroplanes. This legislation applies to all models of these aircraft and outlines specific maintenance and inspection requirements to ensure their airworthiness. The directives mandate actions such as retiring certain wing components, modifying wing spar attachments, and inspecting wing spar shear attachments for cracks. The application of these directives is enforced by the Civil Aviation Safety Authority (CASA) and is applicable nationally across Australia. Notably, certain aircraft serial numbers are specifically targeted by these directives, with precise timelines and intervals set for compliance, such as modifying components before certain flight hours and inspecting them at specified intervals. These requirements are derived from both CASA and FAA directives, ensuring alignment with international safety standards. The regulations do not explicitly state exclusions, but the specific applicability to certain serial numbers implies that not all Beechcraft 200 series aeroplanes are uniformly affected. Further details and specific procedural requirements are provided through subordinate instruments and service bulletins issued by Beechcraft and CASA.
Key Provisions
The Civil Aviation Regulations 1998, as amended, specifically in Part 39 - 105, contain detailed airworthiness directives for the Beechcraft 200 (Super King Air) Series Aeroplanes, under AD/BEECH 200/35 Amendment 6. These directives pertain to the structural integrity and safety of certain components of the aircraft, particularly focusing on the wing fatigue life limitations. The main operative sections (3/98) provide specific requirements for different aircraft serial numbers. Firstly, for aircraft with serial numbers BB-2 through BB-161, the outer wing lower spar cap assembly must be retired from service in accordance with Beech Service Bulletin No 2240. Secondly, for a subset of these aircraft, specific lower forward wing spar attachment fittings need modification by installing Beech Kit No 101-4050. Additionally, a series of aircraft must have their wings inspected for cracks using a fluorescent dye penetrant method in accordance with CAO 108.10. Lastly, all aircraft must retire the wing centre and outer section main spar lower cap assemblies.
These directives impose specific obligations on aircraft operators and maintenance personnel. Operators must ensure compliance with the specified modifications and retirements. For instance, operators must retire the outer wing lower spar cap assembly as per the detailed Beech Service Bulletin No 2240. Similarly, modifications to the lower forward wing spar attachment fittings must be carried out before exceeding 9500 hours of component time in service. Operators must also conduct inspections at prescribed intervals: initially before 15000 hours of time in service, and subsequently at intervals not exceeding 6000 hours of component time in service until 30000 flight cycles, and then at intervals of 1500 hours of time in service or 1200 flight cycles, whichever comes sooner. Additionally, the wing centre and outer section main spar lower cap assemblies must be retired before exceeding 30000 hours of component time in service.
Failure to comply with these airworthiness directives can lead to significant consequences. While the Civil Aviation Regulations 1998 do not explicitly state penalties within this specific context, non-compliance with airworthiness directives generally results in severe civil and potentially criminal consequences. Civil Aviation Safety Authority (CASA) can enforce compliance through various measures, including fines and the potential grounding of non-compliant aircraft. Such actions underscore the importance of adhering to the specified timelines and procedures to ensure the continued airworthiness and safety of the aircraft in question.