COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
AD/DHC-8/69 Wing/Fuselage Closing Angles 5/2000
Applicability: DHC-8 aircraft, Models 102, 103, 106, 201, 202, 301, 311, 314, and 315.
Requirement: Revise the Transport Canada approved maintenance program by incorporating the inspection and the inspection intervals of Airworthiness Limitations List (AWL), Structural Inspection Task 5310/31A as detailed in the Temporary Revisions (TRs) of the DHC-8 Maintenance Program Manuals specified below:
DHC-8 Models | Maintenance Program Manual | Temporary Revision No. |
102, 103, 106 | PSM 1-8-7 | TR AWL-71 |
201, 202 | PSM 1-82-7 | TR AWL2-15 |
301,311, 314, 315 | PSM 1-83-7 | TR AWL3-78 |
For those angles designated as PSEs, phase in the structural inspection tasks detailed above in accordance with the compliance part of this Directive.
Compliance: a. For aircraft that have accumulated less than 8,000 flight cycles as of 18 May 2000, perform the inspection at 10,000 flight cycles.
b. For aircraft that have accumulated more than 8,000 flight cycles as of 18 May 2000, perform the inspection within 2,000 flight cycles after 18 May 2000.
c. For aircraft that have accomplished the 40,000 flight cycle inspection, and where no cracks were found and/or where the closing angles were replaced, the repeat interval of 10,000 flight cycles starts from the date of the 40,000-flight cycle inspection and/or the date of replacement of the closing angles.
This Airworthiness Directive becomes effective on 18 May 2000.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: Fatigue cracks have been found in the outer closing angles at both the front and rear spar locations. The closing angles , which consist of three segments at the front spar and three similar locations at the rear spar, are part of the structure connecting the fuselage to the wing front and rear webs in the wing/fuselage interface area. Cracking of these closing angles which are principal structural elements (PSEs), could adversely affect the structural integrity of the aircraft.
Bernard Malcolm Hole
Delegate of the Civil Aviation Safety Authority 4 April 2000
The above AD is notified in the Commonwealth of Australia Gazette on 19 April 2000.
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, are designed to ensure the safety and efficiency of civil aviation in Australia. Among these regulations, Part 39 specifically addresses Airworthiness Directives, which are legally enforceable rules that aim to correct identified safety issues with aircraft. The Civil Aviation Safety Authority (CASA) is responsible for issuing these directives under subregulation 39.1 (1) of the Civil Aviation Regulations 1998. The Airworthiness Directive for Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes, issued on 18 May 2000, was introduced to address safety concerns regarding fatigue cracks found in the outer closing angles at both the front and rear spar locations of these aircraft models. These cracks, if left unaddressed, could potentially compromise the structural integrity of the aircraft. The directive mandates specific inspection and maintenance protocols to mitigate this risk, with the overarching policy objective being to ensure the ongoing airworthiness of the affected aircraft.
Scope and Application
The Civil Aviation Regulations 1998, specifically PART 39 - 105, mandates Airworthiness Directives issued by the Civil Aviation Safety Authority (CASA) to ensure the safety of civil aviation. This particular directive, AD/DHC-8/69, applies to the Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes, encompassing models 102, 103, 106, 201, 202, 301, 311, 314, and 315. The directive requires a revision of the Transport Canada approved maintenance program to incorporate specific inspection and interval details from the Airworthiness Limitations List (AWL), as outlined in the Temporary Revisions of the DHC-8 Maintenance Program Manuals. This requirement is necessary to address fatigue cracks found in the outer closing angles at the front and rear spar locations, which are critical structural elements that connect the fuselage to the wing. The directive sets compliance timelines based on the number of flight cycles accumulated by the aircraft, with inspections required at specific intervals to maintain airworthiness and ensure safety. This directive extends its reach across the Commonwealth of Australia, impacting all operators of the specified aircraft models within the country.
Key Provisions
The Airworthiness Directive (AD) for Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes (sections 5/2000) outlines specific requirements and compliance instructions for various models of the aircraft, namely DHC-8 Models 102, 103, 106, 201, 202, 301, 311, 314, and 315. The directive mandates the revision of the Transport Canada approved maintenance program to include inspections and inspection intervals of Airworthiness Limitations List (AWL), Structural Inspection Task 5310/31A as detailed in the Temporary Revisions (TRs) of the DHC-8 Maintenance Program Manuals (section 5(a)). For models 102, 103, and 106, PSM 1-8-7 TR AWL-71 is specified; for models 201 and 202, PSM 1-82-7 TR AWL2-15 is specified; and for models 301, 311, 314, and 315, PSM 1-83-7 TR AWL3-78 is specified. The directive also instructs that for angles designated as principal structural elements (PSEs), the structural inspection tasks should be phased in as per the compliance section of this directive (section 5(b)).
The obligations imposed by this AD include ensuring that inspections are performed in accordance with the specified requirements and intervals. For aircraft with less than 8,000 flight cycles as of 18 May 2000, the inspection must be conducted at 10,000 flight cycles. Aircraft that have accumulated more than 8,000 flight cycles as of 18 May 2000 must undergo the inspection within 2,000 flight cycles after this date (section 5(c)(a) and (b)). If the aircraft has already undergone a 40,000 flight cycle inspection and no cracks were found, or if the closing angles were replaced, the repeat inspection interval of 10,000 flight cycles begins from the date of the 40,000-flight cycle inspection or the date of the replacement of the closing angles (section 5(c)(c)).
Failure to comply with the requirements and compliance instructions set out in this AD could result in significant safety risks, potentially leading to structural failure. While the AD does not explicitly state penalties for non-compliance, it is governed under the Civil Aviation Regulations 1998, which may impose civil or criminal penalties for breaches of safety directives. The maximum penalties could include substantial fines and, in severe cases, imprisonment, as per the relevant sections of the Civil Aviation Act 1988 and other associated regulations. Ensuring adherence to this AD is critical for maintaining the airworthiness and safety of the DHC-8 Series Aeroplanes.