COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F100 (F28 Mk 100) Series Aeroplanes
AD/F100/23 Cargo Door Frame 4/99
Applicability: F.28 Mk.0100 aircraft, serial numbers as listed in Fokker Service Bulletin (SB) F100- 52-050, Revision 1 dated 14 September 1994.
Requirement: Install two reinforcement plates under each hook latch fitting of each large cargo door in accordance with the Accomplishment Instructions of Fokker SB F100-52-050 Revision 1 dated 14 September 1994.
Note: RLD BLA 94-157(A) refers.
Compliance: Unless previously accomplished, before accumulating 11,000 flight cycles since new or 22 May 1999, whichever occurs later.
This Airworthiness Directive becomes effective on 22 April 1999.
Background: Stress analyses and destructive tests on the frames of F.28 Mk.0100 large cargo doors have shown that fatigue cracks may develop in the area of the hook latch fittings.
This AD requires a modification to repair possible existing cracks and to prevent the development of new cracks in the affected large cargo door frames.
Overview
The Civil Aviation Regulations 1998, which were enacted by the Commonwealth Parliament, aim to ensure the safety and airworthiness of aircraft operating in Australia. One of the specific legislative instruments under this Act is the Airworthiness Directive (AD) pertaining to Fokker F100 (F28 Mk 100) Series Aeroplanes, particularly addressing cargo door frame issues. This directive was introduced to address identified safety concerns with the cargo door frames of Fokker F100 aircraft, specifically the F.28 Mk.0100 series, as revealed through stress analyses and destructive tests indicating potential fatigue cracks in the area of the hook latch fittings. The directive mandates the installation of two reinforcement plates under each hook latch fitting of each large cargo door in accordance with specified instructions, ensuring compliance before the aircraft accumulates 11,000 flight cycles since new or by 22 May 1999, whichever occurs later. The policy objective is to mitigate risks associated with cargo door structural integrity, thereby enhancing overall aviation safety.
Scope and Application
The Civil Aviation Regulations 1998, specifically under Part 39 - 105, encompasses the scope and application of the Civil Aviation Safety Authority's Airworthiness Directives. This legislative instrument focuses on ensuring the safety and airworthiness of Fokker F100 (F28 Mk 100) series aeroplanes, particularly addressing structural concerns related to the cargo door frames. The directive applies to F.28 Mk.0100 aircraft with serial numbers as listed in Fokker Service Bulletin (SB) F100-52-050, Revision 1 dated 14 September 1994. The requirement mandates the installation of two reinforcement plates under each hook latch fitting of each large cargo door in accordance with the instructions detailed in the same service bulletin. This modification is critical to repair any existing fatigue cracks and prevent the development of new cracks in the cargo door frames. Compliance is mandatory, with the directive requiring adherence before accumulating 11,000 flight cycles since new or by 22 May 1999, whichever occurs later. The Airworthiness Directive becomes effective from 22 April 1999, ensuring that the specified modifications are implemented to maintain the safety standards required by the Civil Aviation Regulations.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, provide detailed requirements for the airworthiness of aircraft, including Fokker F100 (F28 Mk 100) series aeroplanes. Section AD/F100/23 pertains to the cargo door frame, establishing a mandate to install two reinforcement plates under each hook latch fitting of each large cargo door on these aircraft (Section AD/F100/23). This directive is applicable to F.28 Mk.0100 aircraft with specific serial numbers outlined in Fokker Service Bulletin (SB) F100-52-050, Revision 1 dated 14 September 1994 (Applicability). Compliance with these requirements is essential to ensure the structural integrity and safety of the cargo door frames, as stress analyses and destructive tests have revealed potential fatigue cracks in the area of the hook latch fittings (Background). The reinforcement must be completed in accordance with the Accomplishment Instructions provided in the referenced service bulletin (Requirement).
The obligations imposed by this Airworthiness Directive are stringent and must be adhered to by the aircraft operators and maintenance providers. Operators must ensure that the specified modifications are made before the aircraft accumulates 11,000 flight cycles since new or by 22 May 1999, whichever comes later (Compliance). This timeline ensures that the safety enhancements are implemented in a timely manner to prevent the risk of fatigue cracks compromising the cargo door integrity. Operators must keep detailed records of the modifications carried out and ensure that all work is performed by qualified personnel in accordance with the instructions in the Fokker Service Bulletin (RLD BLA 94-157(A)).
Failure to comply with the requirements set out in this Airworthiness Directive can have significant consequences. The Civil Aviation Regulations 1998 outline that non-compliance may result in civil or criminal penalties. The specific penalties depend on the severity of the breach and could include substantial fines or, in more serious cases, imprisonment. For instance, operating an aircraft that does not comply with the mandated modifications could be considered a breach of safety regulations, potentially leading to enforcement actions by the Civil Aviation Safety Authority (CASA). The maximum penalties for such offences are determined by the specific provisions of the Civil Aviation Act 1988, which may include fines up to several thousand Australian dollars and imprisonment for directors or responsible persons involved in the non-compliance (Penalties).