COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-32 (Cherokee Six) Series Aeroplanes
AD/PA-32/25
Amdt 2
Stabilator Hinge Attaching Bolts 10/92
Applicability: Models PA-32-260 and -300 with serial numbers listed in Piper SL 614.
Requirement: 1. Remove tail cone fairing and closeout panel from the aft fuselage bulkhead to gain access to the twelve fitting attachment nuts. There are six bolts and nuts per fitting.
2. Inspect around bolt holes in bulkhead and fitting for cracks, deformation, or other damage.
3. Torque nuts to a value of 35-40 inch pounds and reinstall closeout panel and tail cone fairing.
Note: FAA AD 72-14-07 refers.
Compliance: Unless already accomplished; within 100 hours time in service after 17 September 1992. The compliance of the previous issue of this Directive was: Within 100 hours time in service after 31 August 1972. This Amendment is effective from 17 September 1992.
Background: This Directive was issued to ensure that the bolts on the attachment fittings were of a specified uniform torque value. Amendment 2 is issued to align the applicability with the relevant Country of Origin Directive.
Overview
The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority, were enacted to ensure the safety and efficiency of civil aviation within Australia. One specific instrument under these regulations is the Airworthiness Directive for Piper PA-32 (Cherokee Six) Series Aeroplanes, known as AD/PA-32/25 Amendment 2. This directive, which was introduced to address issues with stabilator hinge attaching bolts, aims to maintain the airworthiness of affected aircraft by ensuring that the bolts are properly torqued and free from damage. The amendment was necessitated to align with the requirements of the relevant country of origin directive and was made effective from 17 September 1992. Compliance with this directive is mandatory for specific models and serial numbers of the Piper PA-32 series, requiring inspections and adjustments to be conducted within a specified timeframe to ensure continued safe operation of the aircraft.
Scope and Application
The Civil Aviation Safety Authority Schedule of Airworthiness Directives under the Civil Aviation Regulations 1998, specifically Part 39 - 105, mandates the application of AD/PA-32/25 Amendment 2 to Piper PA-32 (Cherokee Six) Series Aeroplanes, namely the models PA-32-260 and -300, with serial numbers as listed in Piper SL 614. This directive is applicable to aircraft operators and maintenance personnel within the Commonwealth of Australia, ensuring compliance with national aviation safety standards. The directive mandates a specific inspection and maintenance procedure for stabilator hinge attaching bolts, requiring the removal of certain panels to inspect for cracks, deformation, or damage, followed by torquing the nuts to a specified range and reinstallation of the panels. This amendment is effective from 17 September 1992, and compliance must be achieved within 100 hours of time in service following this date, aligning with the requirements of the relevant Country of Origin Directive. The directive ensures the safety and airworthiness of the specified aircraft by standardising the maintenance of critical components.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to airworthiness directives concerning various aircraft types, including Piper PA-32 (Cherokee Six) Series Aeroplanes. One such directive, AD/PA-32/25 Amendment 2, concerns the stabilator hinge attaching bolts. According to section 10/92 of the directive, it applies to models PA-32-260 and -300 with specific serial numbers outlined in Piper SL 614. The main requirement of this directive involves the inspection and re-torquing of the stabilator hinge attaching bolts.
The directive mandates that the tail cone fairing and closeout panel be removed from the aft fuselage bulkhead to access the twelve fitting attachment nuts, which consist of six bolts and nuts per fitting. Operators must inspect these components for any signs of cracks, deformation, or other damage. Following the inspection, the nuts must be torqued to a specified value of 35-40 inch pounds, and the closeout panel and tail cone fairing must be reinstalled. This process is intended to ensure that the bolts are uniformly tightened, thereby maintaining the aircraft’s airworthiness.
Operators and owners of affected Piper PA-32 aeroplanes are obligated to comply with this directive. Specifically, the inspection and re-torquing of the stabilator hinge attaching bolts must be completed within 100 hours of time in service following 17 September 1992. This requirement ensures that the maintenance of these critical components is timely and does not compromise the safety of the aircraft. Failure to comply with these provisions can result in serious safety risks and potential regulatory penalties.
In the event of non-compliance with the airworthiness directive, operators may face civil or criminal consequences. While the specific penalties are not detailed in the directive, general provisions under the Civil Aviation Act 1988 may apply. These could include fines, suspension or revocation of air operator certificates, and other regulatory actions. The potential severity of these consequences underscores the importance of adhering to the requirements outlined in the directive to ensure continued airworthiness and safety.