COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-34 (Seneca) Series Aeroplanes
AD/PA-34/36
Amdt 3
Rudder Torque Tube Attachment Fitting 9/92
Applicability: Models PA 34-200 S/No 34-7250001 to 34-7450220, PA 34-200T S/No 34-7570001
to 34-8170092, and PA 34-220T S/No 34-8133001 to 34-8533012.
Requirement: 1. Establish if the rudder torque tube fitting is steel or aluminium.
2. (a) If steel, inspect for proper attachment, and check the bolt torque in accordance with the criteria and instructions in Piper SB 899. If fitting is improperly attached or bolt torque is incorrect, rectify in accordance with Piper SB 899.
(b). If aluminium, replace with a steel fitting in accordance with the instructions in Piper SB 899.
3. If the steel fitting required by Requirement 2 (b) of this Directive has been ordered but is not available, as an interim until the fitting is available, accomplish the following:
(a). Visually inspect the aluminium fitting for corrosion. If any evidence of corrosion is found, remove and treat the corroded area in accordance with an acceptable process.
(b). Dye penetrant inspect the aluminium fitting for cracks. If found cracked, replace with an aluminium fitting found to be free from cracks and corrosion.
4. If the aluminium fitting is still fitted, visually inspect for proper attachment, cracks, and corrosion.
(a). If fitting is improperly attached or hardware is found loose, rectify in accordance with Piper SB 899.
(b). If any evidence of corrosion is found, remove and treat the corroded area in accordance with an acceptable process.
(c). If found cracked, replace with an aluminium fitting found to be free from cracks and corrosion; in accordance with the instructions in Piper SB 899.
Note: FAA AD 92-08-04 Amdt 39-8215 refers.
Compliance: 1. Prior to 23 August 1992.
2. (a). Prior to 23 September 1992.
2. (b) & 3. Unless already accomplished, prior to further flight after 23 August 1992.
4. Within 50 hours time in service after 23 August 1992, and thereafter at intervals not to exceed 50 hours time in service; until Requirement 2(b) is accomplished.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: There has been a history of insufficient torque retention on the retaining bolts. This has led to hole elongation and crack propagation in the aluminium fitting.
Amendment 2 required repetitive inspections until, in accordance with the Country of Origin AD, the now mandatory installation of a steel fitting was carried out. Amdt 3 is issued in response to an amendment to the FAA AD that relates to this Directive.
The FAA has determined that parts are currently not available to accomplish the modification required by AD 90-17-04 (the basis for the issue of AD/PA34/36 Amdt 2), and require specified actions be accomplished in order to maintain continuing airworthiness.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address the ongoing issue of insufficient torque retention on the retaining bolts of Piper PA-34 (Seneca) Series aeroplanes, which has resulted in hole elongation and crack propagation in the rudder torque tube attachment fittings. This problem necessitated the creation of Airworthiness Directives to ensure the safe operation of these aircraft. The Civil Aviation Safety Authority, as the enacting body, aims to maintain the airworthiness of aircraft through these directives. The policy objective is to enhance flight safety by ensuring that the rudder torque tube attachment fittings are properly inspected and maintained, thus preventing potential failures that could compromise aircraft control.
The Civil Aviation Regulations 1998, through Amendment 3, require specific actions to be taken for the Piper PA-34 series aeroplanes, including the identification of the material of the rudder torque tube attachment fitting, corrective measures for improper attachments or incorrect bolt torque, and interim actions if steel fittings are unavailable. Compliance with these directives is mandated to ensure the continuing airworthiness of the affected aircraft, with specific timelines provided for inspections and necessary rectifications.
Scope and Application
The Civil Aviation Regulations 1998, specifically PART 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, pertains to the Piper PA-34 (Seneca) series aeroplanes, including models PA 34-200, PA 34-200T, and PA 34-220T, with specific serial number ranges. This legislation mandates the inspection and rectification of the rudder torque tube attachment fitting, aiming to ensure the safety and airworthiness of these aircraft. The regulations apply to aircraft owners, operators, and maintenance personnel within the Australian jurisdiction, as per the Civil Aviation Regulations 1998. The Act does not specify exclusions or exemptions but provides detailed instructions and timelines for compliance, including the need to rectify issues before further flight and at regular intervals thereafter. Compliance with the requirements is overseen by the Civil Aviation Safety Authority, and the regulations can be extended or further specified through subordinate instruments.
Key Provisions
The Civil Aviation Regulations 1998 (part 39 - 105) include a schedule of airworthiness directives specifically addressing the Piper PA-34 (Seneca) series aeroplanes, notably AD/PA-34/36 Amendment 3. This directive focuses on the rudder torque tube attachment fitting, applicable to various model series (sections 1 and 2). It outlines a series of requirements starting with the identification of the material of the rudder torque tube fitting. If the fitting is steel, it mandates inspection for proper attachment and correct bolt torque, with specific instructions provided in Piper Service Bulletin 899. If any discrepancies are found, corrective actions must be taken as per the service bulletin. Conversely, if the fitting is aluminium, it must be replaced with a steel fitting, again using instructions from Piper SB 899.
The directive also includes interim measures for situations where the steel fitting is not yet available. In such cases, visual inspections for corrosion are required, with any evidence of corrosion needing to be treated using an acceptable process. Additionally, dye penetrant inspection for cracks is mandated, with cracked fittings to be replaced. If the aluminium fitting remains in place, it must undergo a visual inspection for proper attachment, cracks, and corrosion, with corrective actions taken if any issues are identified.
Compliance with these directives is critical and is governed by specific timelines. The initial compliance was required prior to 23 August 1992. Subsequent compliance deadlines are set for 23 September 1992, with ongoing inspections and actions required unless already completed. Specifically, inspections must be conducted prior to further flight after 23 August 1992 and then at intervals not exceeding 50 hours of time in service until the steel fitting is installed. These timelines are crucial for maintaining the airworthiness of the aircraft and ensuring the safety of operations.
Failure to comply with these airworthiness directives can result in serious consequences. The regulations stipulate that non-compliance could lead to the aircraft being deemed unairworthy, which can result in grounding of the aircraft until the required modifications and inspections are completed. Furthermore, operators found in breach of these directives may face enforcement actions, including fines and other penalties as prescribed by the Civil Aviation Safety Authority. The specific maximum penalties for non-compliance are not detailed in the text but are subject to the broader civil aviation regulatory framework in Australia.