COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Cessna 320 Series Aeroplanes
AD/CESSNA 320/30
Amdt 1
Applicability: All models.
Wing Front Spar Lower Attachment Fittings 6/89
Requirement: 1. Remove the fairing between the wing and carry-thru and gain access to the wing front spar lower attachment fittings P/N 0822550.
2. Visually inspect the upper and lower edges of the lug of each wing fitting, looking for cracks as shown in the figure below.
3. From inside the wheel well, visually inspect each visible wing fitting for cracks and surface pitting in the area shown in the figure.
Note: It is not necessary to remove the primer for any of the above inspections.
Wing Fitting Showing Typical Cracking
Note: Fitting Shown removed from aircraft for clarity
Compliance: Before exceeding 5000 hours component time in service or before the issue of the next Maintenance Release after 15 June 1989, whichever is the later. Thereafter, reinspect at each scheduled inspection for issue of a new Maintenance Release.
Background: Fatigue cracking has been discovered in the wing fitting from an Australian-registered Cessna 310R with 6500 hours time in service. No abnormality could be found in the fitting or the aircraft’s history. Since then stress corrosion cracking has been found in a similar wing fitting in a Cessna 402C with 6400 hours time in service.
There is insufficient evidence to regard either of these as isolated occurrences: either or both may be expected to occur at a later time elsewhere in the fleet of Cessna twins which use the same generic wing fitting. A simple repetitive visual inspection has therefore been introduced.
Overview
The Civil Aviation Regulations 1998, established by the Australian Parliament, govern the safe operation of aircraft within Australian airspace, with amendments and additions made by the Civil Aviation Safety Authority (CASA). One specific legislative instrument, F2006B08210, addresses safety directives for the Cessna 320 Series Aeroplanes, targeting the problem of fatigue and stress corrosion cracking in wing fittings. This was introduced following discoveries of such cracking in Australian-registered Cessna aircraft, which posed a potential safety risk. The policy objective is to ensure the ongoing airworthiness of these aircraft by mandating regular inspections and maintenance to prevent structural failures. Compliance with these directives is mandatory, requiring inspections before certain time intervals or maintenance releases, and thereafter at each scheduled inspection to maintain aircraft safety standards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, governs the safety directives for aircraft, including the Cessna 320 Series Aeroplanes. This legislation mandates specific maintenance actions for the wing front spar lower attachment fittings of all models within this series. The directive applies to visual inspections of the upper and lower edges of the lug of each wing fitting to detect any cracks and surface pitting, as these components have shown signs of fatigue and stress corrosion cracking. The inspections must be carried out before the aircraft component reaches 5000 hours of time in service or before the issue of the next Maintenance Release following 15 June 1989, whichever is later, with subsequent inspections required at each scheduled maintenance interval. This directive ensures that Australian-registered aircraft remain compliant with safety standards and aims to prevent potential failures in these critical components.
Key Provisions
The Civil Aviation Regulations 1998, as amended, establish specific requirements for the maintenance and airworthiness of aircraft, including the Cessna 320 Series Aeroplanes. Part 39, 105 of the regulations, outlines Airworthiness Directives (AD) related to these aircraft. Specifically, AD/CESSNA 320/30 Amendment 1 mandates a visual inspection of the wing front spar lower attachment fittings to ensure aircraft safety (Section 1). The directive requires that inspections be conducted before a component reaches 5000 hours of service time or before the next Maintenance Release is issued after 15 June 1989, whichever occurs later. These inspections must then be repeated at each subsequent scheduled inspection for a new Maintenance Release (Section 2).
The obligations imposed by this directive require operators of Cessna 320 Series Aeroplanes to perform a thorough visual inspection of the wing front spar lower attachment fittings. This includes removing the fairing between the wing and carry-thru to access the fittings. Operators must inspect the upper and lower edges of the lug of each fitting for any signs of cracks or surface pitting. Additionally, visible wing fittings from inside the wheel well must also be examined for similar issues (Section 3). The directive notes that it is not necessary to remove the primer during the inspection process.
Failure to comply with these inspection requirements may result in serious safety implications, as indicated by the background information provided. Fatigue cracking and stress corrosion cracking have been identified in similar wing fittings in other Cessna models, suggesting a potential widespread issue. Non-compliance with these ADs could lead to significant safety risks, including the possibility of in-flight structural failure. While specific penalties are not detailed in the directive, non-compliance with airworthiness directives can generally result in enforcement actions by the Civil Aviation Safety Authority (CASA), which may include fines, suspension of airworthiness certificates, and other regulatory actions. These actions are intended to ensure that aircraft remain safe and airworthy throughout their service life.