AD/F100/15 - Centre Section Frame Strips

Overview

The Civil Aviation Regulations 1998, under Part 39 - 105, introduced a series of airworthiness directives to ensure the safety and reliability of aircraft in Australian airspace. One such directive, AD/F100/15, specifically addresses Fokker F100 (F28 Mk 100) Series Aeroplanes and mandates the installation of reinforcement plates at specified fuselage locations to mitigate the risk of cracks that were identified during fatigue testing. This directive was enacted to enhance the structural integrity of affected aircraft, ensuring they remain airworthy and compliant with safety standards. The directive applies to Fokker F100 aircraft within the specified serial number range and requires compliance before the aircraft accumulates 24,000 flight cycles since new, or if such installation has not already been performed. This legislative measure aims to preemptively address potential structural failures, thereby maintaining high safety standards in civil aviation.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 105, specifically addresses the airworthiness of Fokker F100 (F28 Mk 100) series aeroplanes through Airworthiness Directives (AD). This particular directive, AD/F100/15, applies to F.28 Mk.0100 aircraft with serial numbers ranging from 11244 to 11371. It mandates the installation of two reinforcement plates at specific fuselage stations, STA.14911 and STA.17011, as detailed in Fokker Service Bulletin (SB) F100-53-072 dated 12 March 1993. This requirement must be fulfilled unless the aircraft has already undergone this modification, and it must be completed before the aircraft accumulates 24,000 flight cycles since its manufacture. The directive became effective on 22 April 1999, following the discovery of cracks in the frame strips during fatigue tests, which prompted this modification to enhance the crack initiation threshold beyond 90,000 flight cycles.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes a schedule of airworthiness directives, with AD/F100/15 being one such directive applicable to Fokker F100 (F28 Mk 100) series aeroplanes. This directive pertains to the installation of reinforcement plates in the centre section frame strips of F.28 Mk.0100 aircraft, specifically those with serial numbers 11244 through 11371 (section 39-105). The requirement is to install two reinforcement plates at fuselage structural assembly (STA) locations 14911 and 17011, following the specifications provided in Fokker Service Bulletin (SB) F100-53-072 dated 12 March 1993 (section 39-105). It is noteworthy that the relevant reference document is RLD BLA 93-037(A) (section 39-105). The directive mandates compliance for aircraft that have not previously implemented the reinforcement measures, and must be completed before the aircraft accumulates 24,000 flight cycles since new (section 39-105). This Airworthiness Directive became effective on 22 April 1999 (section 39-105). The directive was prompted by fatigue tests conducted on the F.28 Mk.0100, during which cracks were detected in the frame strips at fuselage STA.14911 and STA.17011. The installation of the reinforcement plates aims to raise the crack initiation threshold beyond 90,000 flight cycles (section 39-105). Compliance with AD/F100/15 imposes certain obligations on the operators and owners of the affected Fokker F100 series aeroplanes. They must ensure that the specified reinforcement plates are installed at the designated fuselage STA locations as per the provided Fokker Service Bulletin (SB) F100-53-072. This involves following the instructions and specifications outlined in the service bulletin to correctly implement the modifications. Operators and owners must also ensure that the modifications are carried out before the aircraft reaches 24,000 flight cycles since new, or if already accomplished, verify that the modifications have been previously completed (section 39-105). Failure to comply with the requirements set out in AD/F100/15 may result in civil or criminal consequences. The specific penalties for breach of the Civil Aviation Regulations 1998 are not detailed in the provided text, but breaches of airworthiness directives generally attract significant penalties under Australian law. These can include fines, imprisonment, or both, depending on the severity of the breach and the discretion of the court. The exact penalties would be determined based on the specific circumstances of the case, but the potential consequences underscore the importance of adhering to the directive to maintain the safety and airworthiness of the aircraft (section 39-105).