COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F28 Series Aeroplanes
AD/F28/82 Fuel Boost Pump Wiring 1/2000 DM
Applicability: Model F.28 Mk.1000 through Mk.4000 series aeroplanes.
Requirement: 1. Perform a one time review of the aeroplane Maintenance Logs in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin (SB) F28/28-046 dated 1 September 1999.
2. If, either during the Requirement 1 review or during subsequent service of the aeroplane, reports are found of resettable or non-resettable tripping of the Fuel Boost Pump circuit breakers, perform corrective actions in accordance with Part 2 of the Accomplishment Instructions of SB F28/28-046 dated 1 September 1999.
3. Check for signs of fuel leakage from the Boost Pump wiring conduits in accordance with Part 1 of the Accomplishment Instructions of SB F28/28-046 dated 1 September 1999.
4. If, during the Requirement 3 inspection or any other inspection, fuel leakage is found from the Boost Pump wiring conduit on the rear spar of the wing, perform corrective action in accordance with Part 2 of the Accomplishment Instructions of SB F28/28-046 dated 1 September 1999.
5. Replace the existing three single wires inside the Boost Pump metal conduit with three twisted wires, protected by a Polyamide braided wire sleeve in accordance with Part 3 of the Accomplishment Instructions of SB F28/28-046 dated 1 September 1999.
Accomplishment of Requirement 5 is considered terminating action for Requirements 1, 2 and 3.
Note 1: Netherlands AD 1999-114 (A) refers.
Compliance: 1. Within 30 days after the effective date of this Directive.
2. Within the ten days following the occurrence.
Note 2: During the ten days subsequent to the report of resettable or non-resettable circuit breaker tripping, operation with an unserviceable boost pump is only allowed provided that the boost pump circuit breaker is pulled and secured. Both the circuit breaker and the boost pump switch are to be placarded as ‘INOPERATIVE’.
MMEL item 28-22-1 and the relevant Operating Procedure also pertain to this subject.
3. Within 30 days after the effective date of this Directive and thereafter at intervals not to exceed 90 days.
4. Before further flight.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
5. In accordance with the following table:
Aircraft hours total time in service on the effective date of this Directive | Compliance period after the effective date of this Directive |
equal to or exceeding 40,000 | one year |
less than 40,000 | two years |
This Airworthiness Directive becomes effective on 8 December 1999.
Background: The Fokker B.V. Fuel System Safety Programme investigation of the boost pump wiring on Fokker F28 aeroplanes revealed that the boost pump wiring insulation layers can be damaged during installation/removal and/or chafing of the wiring. Additionally, signs of arcing between the wiring and the conduit was detected in two boost pump wiring metal conduits located in the collector tank.
This Directive requires a one time review of aircraft maintenance documentation, repetitive checks for signs of fuel leakage from the boost pump wiring conduits inside the Main Landing Gear strut bays and corrective action as necessary. The Directive also requires eventual replacement of the existing three single wires in the boost pump metal conduit.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, were introduced to ensure the safety and efficiency of civil aviation within Australia. Specifically, Part 39 - 105 of these regulations pertains to airworthiness directives, which serve to address and mitigate safety concerns in aircraft operations. One such directive, AD/F28/82, was issued to address issues identified with the fuel boost pump wiring on Fokker F28 series aeroplanes, particularly the potential for insulation damage and arcing that could compromise flight safety. This directive was developed in response to findings from the Fokker B.V. Fuel System Safety Programme, which highlighted risks associated with the boost pump wiring. The policy objective is to ensure the continuous airworthiness of affected aircraft through timely inspections, corrective actions, and wiring replacements.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, applies to Fokker F28 Series Aeroplanes, particularly the F.28 Mk.1000 through Mk.4000 series. The legislation mandates a series of actions aimed at enhancing the safety of these aircraft by addressing specific issues identified in the fuel boost pump wiring. The requirements include a comprehensive review of the aeroplane maintenance logs, corrective actions for reported issues of circuit breaker tripping, inspections for fuel leakage from the boost pump wiring conduits, and the replacement of existing wiring with a more secure configuration. The geographic and jurisdictional reach of this Act is national, as it is a Commonwealth regulation. Compliance with these directives is mandatory within specified timeframes, with particular urgency for addressing issues that may arise during ongoing service. Notably, the Act extends its application through reference to subordinate instruments, specifically Fokker Service Bulletin F28/28-046 dated 1 September 1999, which provides detailed instructions on how to meet the requirements set out in the Airworthiness Directives.
Key Provisions
The Civil Aviation Regulations 1998, Part 39 - 105, sets out specific airworthiness directives for the Fokker F28 series aeroplanes, with a particular focus on the fuel boost pump wiring (AD/F28/82 1/2000). This directive applies to Fokker F28 Mk.1000 through Mk.4000 series aeroplanes. It mandates several specific actions to be taken by operators to ensure the safety and airworthiness of these aircraft. Firstly, operators must conduct a one-time review of the aeroplane maintenance logs (Requirement 1) and perform corrective actions if reports of circuit breaker tripping are found (Requirement 2). Additionally, operators must check for signs of fuel leakage from the boost pump wiring conduits (Requirement 3) and take corrective action if any leakage is detected (Requirement 4). Finally, operators must replace the existing three single wires inside the boost pump metal conduit with three twisted wires, protected by a polyamide braided wire sleeve (Requirement 5). Completing Requirement 5 serves as the terminating action for Requirements 1, 2, and 3.
Operators of Fokker F28 series aeroplanes are required to adhere to stringent timelines and procedures to ensure compliance with the airworthiness directive. Specifically, the review of maintenance logs must be completed within 30 days from the effective date of the directive (Compliance 1). If circuit breaker tripping is reported, corrective actions must be taken within ten days, with specific placarding requirements in place during this period (Compliance 2). Inspections for fuel leakage must occur within 30 days from the directive's effective date and at intervals not exceeding 90 days thereafter (Compliance 3). Any detected fuel leakage must be addressed before further flight (Compliance 4). The replacement of the wiring must be carried out according to a specified schedule based on the aircraft's total time in service (Compliance 5).
Failure to comply with the provisions of this airworthiness directive may result in significant civil or criminal consequences. While the regulations do not explicitly state the penalties for non-compliance, non-adherence to airworthiness directives can lead to severe repercussions, including fines, suspension of airworthiness certificates, and potential criminal charges under Australian aviation law. The exact penalties can vary based on the severity of the breach and the discretion of the regulatory authorities.
The directive is grounded in findings from the Fokker B.V. Fuel System Safety Programme, which identified potential risks associated with the insulation of the boost pump wiring. Specifically, the investigation revealed that the wiring insulation layers could be damaged during installation or removal and that there were signs of arcing between the wiring and the conduits. This evidence necessitated the implementation of the directive to mitigate these risks and ensure the continued safety and airworthiness of Fokker F28 series aeroplanes.