COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Partenavia P68 Series Aeroplanes
AD/P68/13
Amdt 2
Longitudinal Trim Indicator - Check and Modification 7/79
Applicability: All models P68 and P68B aircraft with trim system and indicator not modified in accordance with schemes approved by the Secretary.
Requirement: 1. To check accuracy of longitudinal trim indicator until incorporation of Partenavia S/B No. 41.
(a) Set trim indicator to zero by rotating trim wheel.
(b) Position stabilator leading edge to zero reference point (rivet reference on fuselage left hand side) and check that trim tab is streamlined with stabilator. If this is the case, trim indicator is correct.
(c) If trim tab not streamlined with stabilator, maintaining leading edge to zero, rotate trim wheel until streamlined and consider this position of trim indicator as zero.
(d) Set take off trim with reference to new zero position.
(e) If reference rivet referred to in para. (b) above is not fitted consider zero reference point for stabilator to be 4.17 inches below upper longitudinal row of rivets.
2. Modify in accordance with Partenavia SB No. 41 and install trim indicator Type B P/N S.6041B or later equivalent.
3. Modify trim indicator by fitting an approved transparent cover or guard to prevent displacement of the pointer from the associated driving scroll.
Note: Registro Aeronautico Italiano AD No. 78-216/P68-19 refers to paras. 1 and 2 of this requirement.
Compliance: 1. Before each flight after 13 June 1979 until modified in accordance with paras. 2 and 3. For aircraft maintained in accordance with ANO 100.5.1, this Directive shall be entered on the maintenance release as maintenance required. The inspection may be performed by the pilot in command in which case certification is not required. In all other cases certification may be made on the maintenance release. This inspection may also be performed and certified by any Licensed Aircraft Maintenance Engineer.
2. Within 10 hours time in service after 13 June 1979.
3. Within 100 hours time in service after 13 June 1979.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, serve to regulate and ensure the safety of civil aviation within Australia. This legislation, overseen by the Civil Aviation Safety Authority, was introduced to address the need for consistent safety standards and regulations within the aviation industry. Among these regulations is Part 39 - 105, which includes specific directives related to airworthiness, such as the Partenavia P68 Series Aeroplanes AD/P68/13 Amendment 2 concerning the longitudinal trim indicator. This particular directive, issued on 7/79, aims to ensure the accuracy and reliability of the longitudinal trim indicator in Partenavia P68 and P68B aircraft models. It requires regular checks and modifications to the trim system and indicator, mandating that these actions are performed before each flight and within specific timeframes post-June 13, 1979, to maintain compliance with safety standards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, establish the requirements for the airworthiness of Partenavia P68 Series Aeroplanes under the authority of the Civil Aviation Safety Authority (CASA). This legislation applies to all models P68 and P68B aircraft equipped with a trim system and indicator that have not yet been modified in accordance with schemes approved by the Secretary. The regulations mandate a series of checks and modifications to ensure the longitudinal trim indicator's accuracy, which is crucial for the aircraft's safe operation. Compliance with these airworthiness directives is mandatory and must be performed at specific intervals post the directive's issuance date of 13 June 1979, with the inspections to be conducted before each flight until modifications are made. Additionally, the regulations allow for the modification of the trim indicator in accordance with Partenavia Service Bulletin No. 41 and the installation of a specified type of trim indicator or an approved transparent cover to prevent pointer displacement. Compliance with these directives is a critical aspect of maintaining the airworthiness of the affected aircraft, with the potential for certification by a Licensed Aircraft Maintenance Engineer or the pilot in command, depending on the context of the inspection.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39, Section 105, mandate a set of airworthiness directives concerning the Partenavia P68 series aeroplanes, particularly focusing on the longitudinal trim indicator. The requirement outlined in AD/P68/13 Amendment 2, involves a thorough inspection and modification process to ensure the accuracy and functionality of the trim system and indicator (s.1). This includes setting the trim indicator to zero by rotating the trim wheel, verifying the stabilator leading edge position, and ensuring the trim tab aligns with the stabilator. If it does not, the trim wheel must be adjusted until the trim tab is streamlined with the stabilator, with the new position considered as zero (s.1(a)-(c)). Additionally, the take-off trim must be set with reference to this new zero position. If a specific rivet reference is absent, a different zero reference point is designated (s.1(d)-(e)). The directive also mandates that modifications align with Partenavia Service Bulletin No. 41 and specifies the installation of a particular trim indicator type or an equivalent version (s.2). Furthermore, an approved transparent cover or guard must be fitted to the trim indicator to prevent displacement of the pointer (s.3).
The obligations imposed by this legislation on the relevant parties, including aircraft operators and maintenance engineers, are quite specific. Operators must ensure that the trim indicator accuracy check is performed before each flight, and if the inspection is conducted by the pilot in command, certification is not mandatory (s. Compliance 1). For aircraft maintained under ANO 100.5.1, the directive must be logged as maintenance required on the maintenance release. For other cases, certification by a licensed aircraft maintenance engineer is necessary. Moreover, the modifications specified in the directive must be completed within 10 hours of service post-inspection and the fitting of the transparent cover or guard must occur within 100 hours of service (s. Compliance 2-3).
Failure to comply with these airworthiness directives can lead to serious consequences. Civil Aviation Regulations do not explicitly detail penalties for non-compliance in this particular directive; however, general regulations under the Civil Aviation Act 1988 could apply. Non-compliance may result in the aircraft being deemed unairworthy, leading to potential grounding and operational prohibitions. Additionally, individuals or entities found in breach may face legal action, including fines and other civil or criminal penalties as prescribed under broader aviation safety legislation. The exact penalties would depend on the severity of the non-compliance and the specific regulatory provisions applicable at the time of the offence.