AD/F100/8 - RH Wing Skin at Fuel Adaptor Position

Overview

The Civil Aviation Regulations 1998 (Cth) were enacted by the Australian Government to ensure the safety and efficiency of civil aviation within Australia. This piece of legislation, administered by the Civil Aviation Safety Authority (CASA), was introduced to address the need for consistent and stringent safety standards in the aviation industry. One specific legislative instrument under this regulation is the Airworthiness Directive AD/F100/8, which applies to Fokker F100 (F28 Mk 100) Series Aeroplanes, particularly those with serial numbers within a specified range. The policy objective of AD/F100/8 is to mitigate the risk of structural failure by requiring the installation of doubler plates at the fuel adaptor position on the right-hand wing skin of the affected aircraft. This measure is intended to prevent the development of cracks that could compromise the integrity and safety of the aircraft, ensuring compliance with airworthiness standards and ultimately protecting passengers and crew.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, which pertains to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, applies to Fokker F100 (F28 Mk 100) series aeroplanes, targeting a specific subset of these aircraft by serial numbers. The directive mandates the installation of internal and external doubler plates around the fuel adapter position on specified Fokker F100 aircraft to address a known issue of potential cracking in the lower skin of the right-hand wing at the attachment bolt holes of the fuel adapter. This requirement is to be fulfilled in accordance with the Accomplishment Instructions outlined in Fokker Service Bulletin F100-57-008 Revision 2. Aircraft that have already undergone the modification detailed in Fokker Service Bulletin F100-57-008, Revision 1, and any subsequent changes advised by the manufacturer, are exempt from this directive. Compliance with this Airworthiness Directive is mandatory unless the required modifications have been completed before the aircraft accumulates 12,000 flight cycles since new. The directive takes effect from 22 April 1999, aiming to mitigate the risk of structural failure due to fatigue, thereby ensuring the continued airworthiness of the affected aircraft.

Key Provisions

The Civil Aviation Regulations 1998, under Part 39, Section 105, detail an Airworthiness Directive (AD) specific to Fokker F100 (F28 Mk 100) series aeroplanes. The directive, identified as AD/F100/8, pertains to the RH (Right-Hand) wing skin at the fuel adaptor position, as outlined in section 4 of 1999. This directive applies to Fokker F100 aircraft with serial numbers ranging from 11244 through 11286, 11289 through 11293, 11295, 11297, 11300, 11303, 11306, 11308, 11310, and 11312. The requirement is to install internal and external doubler plates around the fuel adapter position in accordance with Fokker Service Bulletin (SB) F100-57-008 Revision 2, dated 22 September 1995. For aircraft that have already been modified in line with Fokker SB F100-57-008, Revision 1 (including any changes advised by the manufacturer), no further action is necessary. The AD imposes several obligations on the parties involved. Primarily, the operators of the specified Fokker F100 aircraft must ensure that the required modifications are completed unless the aircraft have already been modified as per the specified service bulletin. The modifications must be completed before the aircraft accumulates 12,000 flight cycles since new. This directive was made effective from 22 April 1999 and highlights the importance of addressing potential structural weaknesses to maintain the airworthiness of the aircraft. Compliance with this AD is crucial to prevent the development of cracks in the lower skin of the RH wing at the attachment bolt holes of the fuel adapter, which, if left unaddressed, can significantly reduce the fatigue life of the structure beyond acceptable safety limits. Breaching the provisions of this Airworthiness Directive can have serious consequences. While the specific penalties are not detailed in the text, non-compliance with airworthiness directives is generally considered a breach of civil aviation regulations. Such breaches can result in significant civil penalties, including fines, and may also lead to criminal charges in cases of gross negligence or willful disregard for aviation safety standards. The severity of the penalties can depend on the extent of the non-compliance and its impact on aviation safety. Ensuring adherence to the AD is, therefore, not only a regulatory requirement but also a critical aspect of maintaining the safety and reliability of the aircraft in operation.