AD/CESSNA 210/42 - Fuel Flow Indication System - Hose Inspection and Replacement

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, address safety directives concerning aircraft airworthiness. This legislative instrument was enacted by the Commonwealth of Australia to ensure the safety of civil aviation, focusing on the inspection and replacement of fuel flow indication systems in specific Cessna 210 Series aeroplanes. The objective is to mitigate risks associated with potential fuel leaks, which could compromise the safety of the aircraft and its occupants. The regulations mandate a thorough inspection of the fuel flow transducer installation and require the replacement of unsuitable hose assemblies to prevent such leaks. Compliance with these directives is mandatory within a specified timeframe to maintain the airworthiness of the affected aircraft. The regulations were enacted by the Commonwealth of Australia and are overseen by the Civil Aviation Safety Authority (CASA), which is responsible for enforcing compliance with the directives. The policy objective is to enhance aviation safety by addressing specific technical issues identified in the fuel flow indication systems of certain Cessna 210 Series aeroplanes. The directives ensure that the aircraft meet necessary safety standards, thereby protecting passengers, crew, and ground personnel from potential hazards associated with fuel leaks.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39, specifically mandate airworthiness directives for the Cessna 210 series aeroplanes, including models 210L, T210L, 210M, T210M, and P210N, that have been modified to incorporate the Symbolic Displays Inc. fuel flow indicating system, as per STC SA3835WE. This regulation applies to aircraft with serial numbers 21061040 and subsequent. The primary requirement of this directive is to inspect the fuel flow transducer installation on the upper left side of the engine adjacent to the fuel distributor manifold. If an NAS 424-4 coupling is present between the transducer and the distributor manifold, it must be removed and replaced with either the Aeroquip P/No. AE7010001E0040 or Stratoflex P/No. 111D417-45-0040 hose assembly to prevent potential fuel leaks over the engine. Compliance with this directive is mandatory within 25 hours of time in service after 3 October 1979. This directive applies nationally within the Commonwealth of Australia and is enforced by the Civil Aviation Safety Authority (CASA).

Key Provisions

The main operative sections of the Civil Aviation Regulations 1998, Part 39 - 105, pertaining to Cessna 210 Series Aeroplanes, particularly the AD/CESSNA 210/42, mandate specific actions regarding the fuel flow indication system. Section 11/79 specifically targets Models 210L and T210L with serial numbers 21061040 onwards, as well as Models 210M, T210M, and P210N that have been modified to include the Symbolic Displays Inc. fuel flow indicating system as per STC SA3835WE. The requirement is to inspect the fuel flow transducer installation on the upper left side of the engine near the fuel distributor manifold. If an NAS 424-4 coupling is present between the transducer and the manifold, it must be removed and replaced with either a hose assembly Aeroquip P/No. AE7010001E0040 or Stratoflex P/No. 111D417-45-0040. This directive references FAA AD 79-19-06 Amendment 39-3558, which also addresses this issue. The obligations imposed by this Act require the aircraft operators to ensure that the specified inspections and replacements are carried out within 25 hours of the aircraft being in service after 3 October 1979. This timeline is critical to maintaining the airworthiness of the aircraft and preventing potential fuel leaks over the engine, which could pose safety hazards. Operators must document the inspections and any replacement work performed in accordance with the requirements set out in the directive. Failure to comply with these provisions could result in serious safety risks, as the hose assembly connecting the fuel flow transducer to the fuel distributor manifold has been identified as unsuitable and prone to leaking fuel. Such leaks could ignite and cause severe damage or even catastrophic failure during flight. The regulations do not explicitly detail specific offences, penalties, or consequences for non-compliance in this directive. However, non-compliance with Civil Aviation Regulations can generally result in enforcement actions by the Civil Aviation Safety Authority, including fines, suspension or revocation of the aircraft’s certificate of airworthiness, and potential criminal charges if the breach results in an accident or endangers flight safety. These penalties underscore the importance of adhering to the specified directives to ensure the safety and compliance of the aircraft operations.