AD/CESSNA 208/12 - Flap Outboard Support

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, was enacted to ensure the airworthiness of aircraft and to provide a regulatory framework that safeguards the interests of the public and the aviation industry. This legislation was introduced to address safety concerns and ensure compliance with international standards, aiming to mitigate risks associated with aviation operations. The Civil Aviation Safety Authority, as the enacting body, established this directive to mandate specific safety measures for the Cessna 208 series aeroplanes, thereby enhancing the safety profile of these aircraft. The policy objective behind this regulation is to prevent structural failures that could compromise the aircraft's safety, as evidenced by the potential for fatigue cracks in the outboard flap support rib structure. The Cessna 208 Series Aeroplanes Airworthiness Directive (AD/CESSNA 208/12) focuses on the critical issue of potential structural failure in the outboard flap support rib flanges, which was identified through rigorous fatigue testing. The directive mandates visual inspections and specific modifications to the affected areas to prevent catastrophic failure that could lead to a loss of control over the aircraft. By implementing these measures, the regulation aims to ensure that the identified safety risks are mitigated, thereby maintaining the overall safety standards required by the Civil Aviation Safety Authority.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, applies to the Cessna 208 (Caravan 1) series aeroplanes, including Models 208 and 208A with serial numbers ranging from 20800001 to 20800227, and Model 208B with serial numbers from 208B0001 to 208B0336. The regulation mandates visual inspection of the outboard flap support rib flanges at wing station 214.30 in line with Cessna Service Bulletin (SB) CAB93-11 and the accomplishment instructions. Additionally, it requires the installation of modifications SK208-109-1 and SK208-109-2 for the left and right flaps, respectively, following the same service bulletin and instructions. Compliance with these requirements involves inspecting the aircraft before 2000 hours of time in service or before 50 hours after 25 May 1995, whichever is later, and then re-inspecting at intervals not exceeding 100 hours of time in service. Should cracks be detected, the numbered compliance paragraphs in Cessna SB CAB93-11 must be adhered to. Installation of the specified modifications cancels the inspection requirements of this Airworthiness Directive. The modifications themselves must be installed before 500 hours of time in service post-inspection or within 100 hours after 25 May 1995, whichever is later.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, include Airworthiness Directives (AD) that govern the maintenance and operation of aircraft. One such AD, AD/CESSNA 208/12, pertains to the Cessna 208 series aeroplanes, models 208 and 208A with serial numbers 20800001 to 20800227 inclusive, and model 208B with serial numbers 208B0001 to 208B0336 inclusive. This directive focuses on the flap outboard support rib flanges, emphasising the necessity for regular inspections and modifications to ensure airworthiness and safety (AD/CESSNA 208/12). Under this directive, operators must visually inspect the outboard flap support rib flanges at Wing Station (WS) 214.30 as per Cessna Service Bulletin (SB) CAB93-11. This inspection should be conducted before the aircraft accumulates 2000 hours of time in service or before 50 hours of time in service after 25 May 1995, whichever is later. The inspection is crucial for detecting any cracks that may develop due to fatigue in the outboard flap support rib structure. If cracks are found, the operator must follow the compliance instructions detailed in Cessna SB CAB93-11. Additionally, operators are required to install modifications SK208-109-1 (left flap) and SK208-109-2 (right flap) as per the same service bulletin. The installation of these modifications should occur before 500 hours of time in service after the initial inspection, or before 100 hours of time in service after 25 May 1995, whichever is later (AD/CESSNA 208/12). It is important to note that the installation of these modifications cancels the inspection requirements stipulated in this AD. Failure to comply with the requirements of AD/CESSNA 208/12 could result in significant safety risks. The potential for fatigue cracks in the outboard flap support rib structure could lead to a loss of the flap, which in turn could result in the loss of the aircraft. The regulations impose clear obligations on aircraft operators to ensure that these inspections and modifications are carried out in a timely manner to mitigate these risks. By adhering to the specified inspection intervals and modification timelines, operators can ensure the continued airworthiness of the Cessna 208 series aeroplanes, thereby enhancing safety and compliance with aviation standards. The consequences of non-compliance with these directives are serious. Civil Aviation Regulations 1998 provide for both civil and criminal penalties for violations. In the event of a breach, operators may face fines and imprisonment. The maximum penalties for civil offences under the regulations can include substantial financial penalties, while criminal offences can result in fines up to $210,000 for individuals and $1,050,000 for corporations, as well as imprisonment for up to five years. These stringent penalties underscore the importance of adhering to the ADs to prevent potential hazards and ensure the safety of all persons on board and on the ground.