COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
DHC-2 (Beaver) Series Aeroplanes
AD/DHC-2/24
Amdt 3
Wing Strut Assembly Lower Attachment Fittings 2/94
Applicability: All Models DHC-2 aircraft fitted with wing lift strut part numbers C2W1103, C2W1103A, C2W1104, or C2W1104A.
Requirement: Action in accordance with the Accomplishment Instructions of de Havilland of Canada Service Bulletin 2/41 Revision B. In lieu of the dye penetrant inspection specified in the above referenced service bulletin, a fluorescent penetrant inspection of the lower clevis fitting shall be carried out by a person holding a valid appropriate Non-Destructive Testing Authority.
Note: Transport Canada AD CF-85-08R3 refers.
Compliance: a. For aircraft operating in a salt water environment:
(i) For aircraft which have complied with Amendment 2 of this Directive, within one calendar year since the previous inspection, and thereafter at intervals not to exceed one calendar year; and
(ii) For aircraft which have not complied with Amendment 2 of this Directive, within 100 hours time in service or one calendar year after 3 February 1994, whichever occurs first, and thereafter at intervals not to exceed one calendar year.
b. For all other aircraft:
(i) For aircraft which have complied with Amendment 2 of this Directive, within two calendar years since the previous inspection, and thereafter at intervals not to exceed two calendar years; and
(ii) For aircraft which have not complied with Amendment 2 of this Directive, within 100 hours time in service or one calendar year after 3 February 1994, whichever occurs first, and thereafter at intervals not to exceed two calendar years.
Background: A report was received of stress corrosion cracking occurring in the wing lift strut lower clevis fitting. This Directive requires certain actions in order to preclude failure of the wing lift strut.
Amendment 1 expanded the part number applicability and removed the serial number range and date of manufacture provisions.
Amendment 2 replaced the dye penetrant inspection with the fluorescent penetrant inspection.
Amendment 3 is issued in response to a new Transport Canada AD revision which allows a longer inspection interval for aircraft which are not operated in a salt water environment.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Overview
The Civil Aviation Regulations 1998, as part of the broader legislative framework overseen by the Civil Aviation Safety Authority (CASA), was enacted to regulate and ensure the safety of civil aviation within Australia. This legislation was introduced to address the need for stringent safety standards and regulatory oversight in the civil aviation sector, ensuring that all aircraft meet safety requirements to protect passengers, crew, and the general public. One specific area of focus is the issuance of Airworthiness Directives (ADs) to address identified safety issues. The AD/DHC-2/24 Amendment 3, for example, pertains to DHC-2 (Beaver) Series Aeroplanes and was introduced in response to reported stress corrosion cracking in the wing lift strut lower clevis fitting. This AD mandates particular actions to prevent failure of the wing lift strut, including specified inspection intervals and methods, as detailed in the Accomplishment Instructions of de Havilland of Canada Service Bulletin 2/41 Revision B. The policy objective of these amendments is to maintain the highest safety standards in civil aviation by mitigating identified risks associated with specific aircraft components.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning Airworthiness Directives, applies to all DHC-2 (Beaver) series aeroplanes equipped with wing lift strut parts numbered C2W1103, C2W1103A, C2W1104, or C2W1104A. This regulation is mandated by the Civil Aviation Safety Authority and is applicable across the Commonwealth of Australia, ensuring uniform standards for aircraft airworthiness nationwide. The directive requires actions to be taken in accordance with the Accomplishment Instructions outlined in de Havilland of Canada Service Bulletin 2/41 Revision B, with an alternative provision allowing for a fluorescent penetrant inspection conducted by a qualified individual holding a valid Non-Destructive Testing Authority. Compliance with these directives varies based on operational environment, with stricter intervals required for aircraft operating in salt water environments. This regulation extends its application through subordinate instruments, ensuring consistent oversight and maintenance standards are met across the aviation industry within Australia.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes the Civil Aviation Safety Authority's Schedule of Airworthiness Directives (ADs), which govern the maintenance and operation of aircraft within Australia. One such directive, AD/DHC-2/24 Amendment 3, pertains to the DHC-2 (Beaver) series aeroplanes, specifically addressing the wing strut assembly lower attachment fittings. This directive applies to all DHC-2 models equipped with certain wing lift strut part numbers (C2W1103, C2W1103A, C2W1104, or C2W1104A) (section 1). The directive mandates compliance with the Accomplishment Instructions of de Havilland of Canada Service Bulletin 2/41 Revision B, and requires that a fluorescent penetrant inspection be carried out by a qualified individual holding a valid Non-Destructive Testing Authority instead of the previously specified dye penetrant inspection (section 2).
The AD imposes specific obligations on the operators of DHC-2 aircraft. For aircraft operating in salt water environments, inspections must be conducted within one calendar year from the previous inspection, or within 100 hours of time in service or one calendar year from 3 February 1994, whichever is earlier. These inspections must then occur at intervals not exceeding one calendar year (section 3(a)(i) and (ii)). For all other aircraft, the inspections must occur within two calendar years from the previous inspection, or within 100 hours of time in service or one calendar year from 3 February 1994, whichever is earlier, followed by inspections at intervals not exceeding two calendar years (section 3(b)(i) and (ii)). This requirement aims to ensure that stress corrosion cracking, previously reported in the wing lift strut lower clevis fitting, is identified and rectified to prevent potential failure.
Failure to comply with the AD/DHC-2/24 Amendment 3 may result in serious safety implications, as the directive was issued in response to reports of stress corrosion cracking in the wing lift strut lower clevis fitting. Non-compliance could potentially lead to structural failure of the wing strut, posing significant risks to flight safety. While specific civil or criminal penalties are not outlined in the text, non-compliance with Civil Aviation Regulations can result in enforcement actions by the Civil Aviation Safety Authority, which may include fines, suspension or revocation of an aircraft’s certificate of airworthiness, or other regulatory actions. The maximum penalties for such breaches would be in line with the broader regulatory framework established under the Civil Aviation Act 1988.