COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Cessna 150, F150, 152 & F152 Series Aeroplanes
AD/CESSNA 150/5
Amdt 2
Main Undercarriage Attachment 7/77
Applicability: All models except those with tubular main landing gear spring assemblies.
Requirement: 1. Inspect the angle brackets located between the leg anchorage and the fuselage skin for cracks in the bend radii. The area may be inspected with the aide of a mirror after slightly enlarging the access holes for the springleg “U” bolts.
2. Inspect the bulkhead at Station 56.69 through the two inspection holes in the cabin floor for cracks at the rivet holes in the diaphragm of the bulkhead.
3. If cracking is present at either of these locations the aircraft is to be opened up sufficiently to enable a complete inspection to be made of the aft bulkhead at Station 56.69, the forward bulkhead at Station 49.69 and the inboard leg anchorage assemblies for cracks.
Compliance: At intervals not exceeding 200 hours time in service.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, address the need for stringent safety standards in civil aviation, particularly in relation to aircraft maintenance and operational safety. One specific legislative instrument under this framework is F2006B04947, which pertains to airworthiness directives for certain Cessna aeroplane models. This instrument aims to mitigate potential safety risks associated with structural integrity by mandating regular inspections of critical components such as the main undercarriage attachment and bulkheads in Cessna 150, F150, 152, and F152 series aeroplanes. The policy objective behind this directive is to ensure that any structural defects are identified and rectified promptly, thereby maintaining the airworthiness of the aircraft and protecting passenger safety. Compliance with these directives is required at intervals not exceeding 200 hours of operational time, underscoring the importance placed on regular and thorough maintenance checks.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the safety directives issued by the Civil Aviation Safety Authority (CASA) and applies to the Cessna 150, F150, 152 & F152 series aeroplanes. The regulation mandates that all models of these aircraft, except those equipped with tubular main landing gear spring assemblies, adhere to specific maintenance and inspection requirements. These requirements are aimed at ensuring the structural integrity of the main undercarriage attachment and relevant bulkheads, which are critical for the safe operation of the aircraft. The inspection must be conducted at intervals not exceeding 200 hours of service time, focusing on checking for cracks in specified areas such as the angle brackets and bulkheads. If any cracks are detected, further inspection of additional structural components is mandated to ensure no other areas are compromised. The regulation is applicable on a national level, overseen by CASA, and is designed to maintain high safety standards within the Australian aviation industry.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, include a schedule of airworthiness directives that govern the maintenance and inspection requirements for various aircraft models. Within this schedule, AD/CESSNA 150/5 Amendment 2 addresses the main undercarriage attachment for Cessna 150, F150, 152, and F152 series aeroplanes, excluding those equipped with tubular main landing gear spring assemblies (Section 39-105). The directive mandates inspections to ensure the structural integrity of the main undercarriage components, which is critical for flight safety.
The primary requirement outlined in this directive is the inspection of the angle brackets located between the leg anchorage and the fuselage skin for any cracks in the bend radii (Section 39-105(1)). This inspection can be facilitated by slightly enlarging the access holes for the spring leg "U" bolts and using a mirror to inspect the area. Additionally, the bulkhead at Station 56.69 must be examined through the two inspection holes in the cabin floor for cracks at the rivet holes in the diaphragm of the bulkhead (Section 39-105(2)). If any cracks are detected at these specified locations, further inspection of the aft bulkhead at Station 56.69, the forward bulkhead at Station 49.69, and the inboard leg anchorage assemblies is required to ensure a comprehensive assessment of the structural integrity (Section 39-105(3)).
Operators and maintenance personnel must adhere to the compliance interval specified in the directive, which mandates that these inspections be conducted at intervals not exceeding 200 hours of time in service (Section 39-105(4)). This ensures that any potential issues with the main undercarriage attachment are identified and addressed promptly, thereby maintaining the aircraft's airworthiness and ensuring the safety of passengers and crew.
Failure to comply with the airworthiness directive can result in significant consequences. Under the Civil Aviation Act 1988, non-compliance may be considered an offence, potentially leading to penalties including fines and imprisonment. Specifically, the maximum penalty for a serious breach of the regulations can include fines up to $162,000 for an individual and $810,000 for a corporation, as well as imprisonment for up to five years (Section 43). These stringent penalties underscore the importance of adhering to the prescribed inspection intervals and procedures to avoid severe repercussions.