AD/F100/25 - Small Cargo Door Hinge Assembly - 2

Overview

The Civil Aviation Regulations 1998, as amended by the Legislative Instrument F2006B09626, introduced Airworthiness Directive AD/F100/25 to address the issue of premature fatigue cracks found in the small cargo door hinge assemblies of Fokker F100 (F28 Mk 100) Series aeroplanes. This directive was enacted to ensure the safety of aircraft operations by mandating detailed inspections and repairs of specific hinge assemblies. The problem it aimed to resolve was the discovery of unexpected fatigue cracks in the small cargo door hinges during routine inspections, which posed a potential risk to aircraft safety. The objective of this legislative measure was to mitigate these risks by ensuring that the affected hinge assemblies were inspected and repaired as necessary, thus maintaining the airworthiness of the aircraft. This directive was issued by the Civil Aviation Safety Authority (CASA) to enforce compliance with the specified inspection and repair procedures. The Airworthiness Directive AD/F100/25 applies to all Fokker F100 (F28 Mk 100) series aeroplanes equipped with small cargo doors, specifically those with hinge assemblies bearing part numbers A28410-405, A28410-407, or D28410-409. It mandates a comprehensive inspection of these hinge assemblies and requires repairs if cracks are detected. The directive stipulates that inspections must be conducted before the hinge assemblies accumulate 8,000 flight cycles since new or before 22 May 1999, whichever is later, and then at intervals not exceeding 8,000 flight cycles. All repairs must be completed before further flight. This directive became effective on 22 April 1999, underscoring the urgency and importance of addressing the identified safety concern.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, governs the safety requirements for Fokker F100 (F28 Mk 100) series aeroplanes. This particular regulation, AD/F100/25, pertains to small cargo door hinge assemblies with specific part numbers installed on F.28 Mk.0100 aircraft equipped with small cargo doors. The directive mandates that aircraft operators and maintenance personnel ensure compliance with detailed inspection and repair protocols to address fatigue cracks found in these hinge assemblies. The requirement to inspect the hinges before a certain number of flight cycles or by a specified date ensures that any potential issues are identified and rectified in a timely manner, thereby maintaining the airworthiness of the aircraft. Failure to comply with these directives could result in significant safety risks and non-compliance with aviation regulations. The regulation applies nationally across Australia, overseen by CASA, and is applicable to all operators of Fokker F100 series aeroplanes with the specified hinge assemblies. The directive not only includes the initial inspection deadline but also establishes ongoing inspection intervals to ensure continued safety. Any repairs identified during these inspections must be completed before further flights. This AD was issued due to the discovery of premature fatigue cracks in the cargo door hinges, highlighting the importance of adhering to these safety mandates to prevent similar occurrences in the future.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, includes a directive for Fokker F100 (F28 Mk 100) series aeroplanes, identified as AD/F100/25. This directive (paragraph 1) focuses on the small cargo door hinge assemblies with particular part numbers (A28410-405, A28410-407, and D28410-409) installed in Fokker F100 aircraft. The primary requirement (paragraph 2) is to check the aircraft maintenance records to determine the total number of flights for each affected hinge assembly. Following this, a detailed inspection of the hinge assemblies must be conducted in accordance with the Fokker 70/100 Non-Destructive Testing (NDT) Manual, Part 6, Procedure 52-30-01. If any cracks are detected during the inspection, they must be repaired according to a Fokker-developed repair scheme, with reference to RLD BLA 1996-125/2. Compliance with this directive (paragraph 3) necessitates that inspections and repairs be completed before 22 May 1999, or before the hinge assemblies accumulate 8,000 flight cycles since new, whichever is later. If the number of flight cycles cannot be established, inspections must be conducted before 22 May 1999. Subsequent inspections are required at intervals not exceeding 8,000 flight cycles. It is mandated that all repairs to the cargo door hinges be completed before further flight. This Airworthiness Directive became effective on 22 April 1999. The obligations imposed by this directive (paragraph 4) require aircraft operators to meticulously maintain and inspect the specified cargo door hinge assemblies. Operators must ensure that inspections are conducted at the prescribed intervals and that any identified issues are promptly addressed according to the outlined repair procedures. Furthermore, operators must update their maintenance records to reflect the number of flights and inspections performed on each hinge assembly. Failure to comply with these obligations may result in serious safety concerns and potential regulatory penalties. Violations of this directive (paragraph 5) can lead to significant consequences. The Civil Aviation Regulations 1998 do not specify penalties for non-compliance within the directive itself. However, under broader aviation safety regulations, non-compliance can result in civil penalties, including fines, and criminal charges in cases of gross negligence. The severity of penalties can vary based on the extent of non-compliance and the impact on aviation safety. Operators found in breach of these requirements may also face operational restrictions or grounding of affected aircraft until compliance is achieved.