COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 19, 23 and 24 Series Aeroplanes
AD/BEECH 23/43 Trailing Edge Flaps 9/84
Applicability: All 19, 23 and 24 series.
Requirement: Inspect flap internal structure at the flap hinge arm attachment ribs for corrosion.
Note: This inspection will require leading edge skin removal or installation of inspection panels to a scheme approved by the Secretary.
Compliance: 1. Unless already accomplished, for aircraft which have achieved 5 years since date of manufacture, within 25 hours time in service after 12 September 1984 or 3 months, whichever occurs first and thereafter at intervals not exceeding 3 years.
2. Unless already accomplished, for all other aircraft: before achieving 5 years since date of manufacture and thereafter at intervals not exceeding 3 years.
Background: Numerous Major Defect Reports have indicated that an advanced state of corrosion can exist without external indications. In some instances more than half of the hinge arm was corroded away.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, are a comprehensive set of rules governing all aspects of civil aviation within the country. Part 39 of these regulations includes various Airworthiness Directives (AD) that ensure the safety and airworthiness of aircraft. One such directive, AD/BEECH 23/43, specifically targets Beechcraft 19, 23, and 24 series aeroplanes to address the issue of trailing edge flap corrosion. This directive was introduced to mitigate risks identified through numerous Major Defect Reports, which revealed that advanced corrosion could occur without any external indications, potentially leading to significant structural failure. The policy objective is to ensure the safety and reliability of these aircraft by mandating regular inspections of the flap internal structure at the flap hinge arm attachment ribs.
The AD/BEECH 23/43 requires inspections to be carried out at specific intervals, depending on the age and time in service of the aircraft. For aircraft manufactured more than five years prior to 12 September 1984, inspections must be performed within 25 hours of time in service or three months, whichever comes first, and subsequently every three years. For all other aircraft, inspections must occur before they reach five years since manufacture and then every three years thereafter. This directive aims to preemptively identify and address corrosion, thereby preventing potential catastrophic failures.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39, specifically target the maintenance and safety of aircraft within Australia, thereby applying to all aircraft operators, maintenance personnel, and entities involved in the operation or maintenance of Beechcraft 19, 23, and 24 series aeroplanes. The regulations mandate that inspections of the trailing edge flaps for corrosion must be conducted on these aircraft to ensure continued airworthiness, with particular focus on the flap hinge arm attachment ribs. This requirement applies across the Commonwealth of Australia, enforcing a national standard for the specified aircraft models. The inspection must be carried out within 25 hours of time in service after 12 September 1984 or within three months for aircraft that have been in service for less than five years since the date of manufacture, and thereafter at intervals not exceeding three years. For aircraft that have not yet reached five years since manufacture, inspections must occur before this period elapses and then periodically every three years. The regulations do not explicitly mention any exclusions or exemptions, but the specific inspection requirements are contingent on the aircraft's operational history and age. The Secretary’s approval is necessary for any leading edge skin removal or installation of inspection panels to ensure compliance with safety standards.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39, Section 105, contains an Airworthiness Directive (AD) relating to Beechcraft 19, 23 and 24 series aeroplanes (AD/BEECH 23/43). This directive mandates the inspection of the trailing edge flaps' internal structure at the flap hinge arm attachment ribs for signs of corrosion (Section 105). The directive applies to all 19, 23 and 24 series aeroplanes, requiring a thorough inspection process which may involve removing the leading edge skin or installing inspection panels, subject to approval by the Secretary (Section 105).
Aircraft owners and operators are required to adhere to specific timelines for inspections as stipulated in the directive. For aircraft that have reached five years since the date of manufacture, inspections must be conducted within 25 hours of time in service after 12 September 1984, or within three months, whichever comes first. Subsequent inspections must occur at intervals not exceeding three years (Section 105). For aircraft that have not yet reached five years since manufacture, inspections must be performed before this five-year mark and then at intervals not exceeding three years thereafter (Section 105).
Failure to comply with the AD may result in serious safety implications, as numerous Major Defect Reports have indicated that corrosion can progress significantly without any external indications, sometimes leading to more than half of the hinge arm being corroded away (Section 105). Compliance with this directive is critical to maintaining the airworthiness of the aircraft and ensuring the safety of all passengers and crew.
The consequences of non-compliance with the AD are not explicitly detailed in the provided text, but generally, non-compliance with Civil Aviation Regulations can lead to significant penalties. These may include fines, suspension or revocation of aircraft certificates, and in severe cases, criminal charges. The exact penalties would be determined by the Civil Aviation Safety Authority and could vary based on the severity and impact of the non-compliance.