COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Cessna 210 Series Aeroplanes
AD/CESSNA 210/10
Amdt 3
Main Landing Gear Actuators - Modification 12/75
Applicability: All 210 Series with S/Nos. 21058510 and below.
Requirement: Unless previously accomplished, replace all integral flange and gear spindle assemblies, Cessna P/No. ED11935L and R, with modified splined shaft and sector listed in:
- Cessna SL SE69-17 - for aircraft S/No. 21058460 and below;
2. Cessna SL SE75-21 - for aircraft S/Nos. 21058461 to 21058510.
Compliance: For Sub-Para. 1 - Within 300 hours time in service after 29 June 1973 or at first major inspection after 1 September 1973, whichever occurs first.
For Sub-Para. 2 - Before 1 September 1976.
Note: Aircraft complying with DCA/CESSNA 210/10A or 10B satisfy compliance with this issue of the Directive.
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, establish a comprehensive framework for ensuring civil aviation safety across the nation. Part 39 of these regulations specifically targets airworthiness directives, aiming to address potential safety issues in various aircraft models through targeted modifications and compliance requirements. The AD/CESSNA 210/10 Amendment 3, introduced under this part, seeks to resolve identified safety concerns related to the main landing gear actuators of Cessna 210 series aeroplanes. This directive mandates the replacement of specific components in certain serial number ranges to enhance the safety and reliability of the aircraft, thereby protecting passengers, crew, and the general public. The policy objective is to mitigate risks associated with potential failures in the landing gear system, ensuring that all affected aircraft meet stringent safety standards set by the Civil Aviation Safety Authority.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the airworthiness of Cessna 210 Series aeroplanes, with this legislative instrument focusing on the modification of main landing gear actuators. The applicability of this regulation extends to all Cessna 210 Series aircraft with serial numbers up to and including 21058510. The directive mandates the replacement of specific components, namely the integral flange and gear spindle assemblies, with modified assemblies that adhere to the specifications outlined in Cessna Service Letters SL SE69-17 and SL SE75-21, depending on the aircraft's serial number. Compliance with this airworthiness directive is contingent on the aircraft's operational history, requiring modifications within a specified timeframe following the date of the directive or at the first major inspection post-issuance. Notably, aircraft that have previously complied with related directives, DCA/CESSNA 210/10A or 10B, are deemed to satisfy the requirements of this directive. The scope of this regulation is geographically expansive, applying across the Commonwealth of Australia, and is enforced by the Civil Aviation Safety Authority (CASA).
Key Provisions
The Civil Aviation Regulations 1998, under PART 39 - 105, specify detailed requirements for maintaining the airworthiness of specific aircraft types, particularly the Cessna 210 Series aeroplanes. Section AD/CESSNA 210/10 Amendment 3 focuses on modifications to the main landing gear actuators. It is applicable to all Cessna 210 Series aeroplanes with serial numbers (S/Nos.) 21058510 and below (Section 12/75). The primary requirement is to replace all integral flange and gear spindle assemblies, identified as Cessna Part Number ED11935L and R, with modified splined shaft and sector assemblies as listed in specific service letters. For aircraft with S/Nos. 21058460 and below, the replacement must align with Cessna Service Letter SE69-17, while for those with S/Nos. 21058461 to 21058510, the replacement must align with Cessna Service Letter SE75-21.
Operators of these aircraft must adhere to strict compliance timelines. For the aircraft covered under Sub-Paragraph 1 (S/Nos. 21058460 and below), the modification must be completed within 300 hours of time in service after 29 June 1973 or at the first major inspection after 1 September 1973, whichever comes first (Section 1). For aircraft covered under Sub-Paragraph 2 (S/Nos. 21058461 to 21058510), the modification must be completed before 1 September 1976 (Section 2). Additionally, aircraft that have already complied with either AD/CESSNA 210/10A or AD/CESSNA 210/10B are deemed to satisfy the requirements of this directive.
Failure to comply with the provisions of this directive could result in significant legal and safety consequences. The Civil Aviation Regulations enforce strict compliance to ensure that aircraft maintain their airworthiness standards. Operators who do not adhere to the specified timelines and modification requirements risk non-compliance with regulatory standards, potentially leading to penalties under the Civil Aviation Act 1988. Such penalties can include fines, suspension or revocation of aircraft operating certificates, and other enforcement actions deemed necessary by the Civil Aviation Safety Authority (CASA). The exact penalties are determined by CASA but can be substantial, reflecting the critical importance of adhering to airworthiness directives to ensure the safety of aviation operations.