COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F50 (F27 Mk 50) Series Aeroplanes
AD/F50/30 Fuselage Upper Girder Connection at Frame Sta. 3415
1/90
Applicability: F27 Mark 50, serial numbers 20103 through to 20108, and 20110 through to 20147.
Requirement: Incorporate reinforcement modification in accordance with Fokker Service Bulletin F50-53-020 dated 15 September 1989.
Note: RLD BLA 89-110 refers.
Compliance: Prior to accumulating 10,000 flight cycles.
Background: Full scale fatigue tests have determined that the connection angle between the upper girder of the flight compartment window and the upper torsion box of the passenger door has insufficient fatigue resistance. This AD introduces a reinforcement bracket to the area.
Overview
The Civil Aviation Regulations 1998, as part of Part 39, include specific Airworthiness Directives (ADs) to ensure the safety and airworthiness of aircraft operating in Australia. One such directive, AD/F50/30, was introduced to address the problem of insufficient fatigue resistance in the fuselage upper girder connection at frame station 34151/90 on Fokker F50 (F27 Mk 50) series aeroplanes. Enacted by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Act 1988, this directive applies to Fokker F50 aircraft with specific serial numbers. The primary objective of AD/F50/30 is to enhance the structural integrity of the affected aircraft by mandating the incorporation of a reinforcement modification as specified in Fokker Service Bulletin F50-53-020 dated 15 September 1989. Compliance with this directive is required before the aircraft accumulates 10,000 flight cycles, reflecting CASA's commitment to maintaining high safety standards in civil aviation.
Scope and Application
The Civil Aviation Safety Authority's (CASA) Airworthiness Directives, specifically AD/F50/30, apply to Fokker F50 (F27 Mk 50) series aeroplanes, including those with serial numbers ranging from 20103 through to 20108, and from 20110 through to 20147. This regulation mandates that operators of these aircraft must incorporate a reinforcement modification to the fuselage upper girder connection at Frame Sta. 34151/90, as specified in Fokker Service Bulletin F50-53-020 dated 15 September 1989, before the aircraft accumulates 10,000 flight cycles. The requirement stems from full-scale fatigue tests revealing insufficient fatigue resistance at the connection angle between the upper girder of the flight compartment window and the upper torsion box of the passenger door. The directive is part of the Civil Aviation Regulations 1998, reflecting the Commonwealth's jurisdiction over civil aviation safety and is intended to ensure the ongoing airworthiness of the specified Fokker F50 series aircraft.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39, includes a section detailing Airworthiness Directives (ADs) which are legally binding instructions issued by the Civil Aviation Safety Authority (CASA) to address safety issues. Section 39.105 pertains to the Fokker F50 (F27 Mk 50) series aeroplanes, outlining the requirements for a reinforcement modification at the fuselage upper girder connection at frame station 34151/90. This AD applies to Fokker F50 aircraft with specific serial numbers ranging from 20103 to 20108, and from 20110 to 20147. The directive mandates that a reinforcement modification be incorporated in accordance with Fokker Service Bulletin F50-53-020 dated 15 September 1989. Additionally, it references RLD BLA 89-110 for further details. Compliance with this AD is required before the aircraft accumulates 10,000 flight cycles.
The AD imposes several obligations on the aircraft operators and maintenance personnel. Firstly, they must ensure that the specified Fokker F50 aircraft receive the reinforcement modification as outlined in the referenced Fokker Service Bulletin. This involves installing a reinforcement bracket at the designated fuselage upper girder connection to enhance the structural integrity of the area identified as having insufficient fatigue resistance. Secondly, operators and maintenance personnel must meticulously follow the instructions provided in the service bulletin to guarantee the modification is correctly and effectively implemented. Additionally, operators must ensure that the aircraft do not exceed 10,000 flight cycles without complying with the AD, thereby maintaining the aircraft's airworthiness and safety standards.
Failure to comply with the AD may result in serious consequences. The Civil Aviation Regulations 1998 outline various penalties for non-compliance with ADs. Generally, non-compliance can lead to enforcement actions by CASA, which may include fines and sanctions against the operators. Furthermore, operating an aircraft that does not comply with the AD may result in the aircraft being grounded, potentially leading to significant operational disruptions and financial losses. In severe cases, non-compliance can also result in criminal charges against individuals responsible for the oversight of the aircraft maintenance, leading to imprisonment and additional fines. The precise penalties depend on the severity and frequency of the non-compliance, as well as any resultant safety risks or incidents.