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-2/22
Amdt 1
Aileron Centre Hinge Bracket 1/88 DM
Applicability: All models DHC-2 Mk1 and MkII and DHC-2 MkIII. Turbo- Beaver Aircraft not incorporating Modification 2/1536.
Requirement: Modify in accordance with De-Havilland Canada S.B 2/37 Rev C.
Note: Canadian AD CF-84-02-R1 refers.
Compliance: Unless already accomplished within 200 hours time in service after 19 November 1987 or prior to 19 January 1988 whichever is earlier.
Background: The initial issue of this Directive allowed an open ended continued inspection. However, due to failure of a cast bracket in flight this option is now terminated.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, were enacted by the Australian Parliament to establish and enforce regulations related to civil aviation safety, including the issuing of Airworthiness Directives to ensure the safe operation of aircraft. One such directive, AD/DHC-2/22 Amendment 1, pertains to the DHC-2 (Beaver) series aeroplanes, focusing on the modification of the aileron centre hinge bracket to address a safety issue identified in certain models. This directive was necessitated by the failure of a cast bracket in flight, which prompted a requirement for modification in accordance with De-Havilland Canada Service Bulletin 2/37 Revision C. The policy objective is to enhance the safety of DHC-2 aircraft by mandating timely compliance with specified modifications to prevent in-flight failures.
The directive applies to all DHC-2 Mk1, MkII, and DHC-2 MkIII models, excluding Turbo-Beaver Aircraft that have already incorporated Modification 2/1536. Compliance with this directive is required unless the specified modification has already been completed within 200 hours of time in service after 19 November 1987 or before 19 January 1988, whichever is earlier. The directive references Canadian AD CF-84-02-R1 for additional context and aims to mitigate the risk of in-flight failures by enforcing stringent safety measures.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the Airworthiness Directives for the DHC-2 (Beaver) Series Aeroplanes, focusing on the aileron centre hinge bracket modification. This legislation applies to all models of DHC-2 Mk1 and MkII and DHC-2 MkIII aeroplanes, excluding Turbo-Beaver Aircraft that have already incorporated Modification 2/1536. The requirement mandates that these aircraft must be modified in accordance with De-Havilland Canada Service Bulletin 2/37 Revision C, with reference to Canadian AD CF-84-02-R1. Compliance with these directives is essential unless the modification has already been carried out within 200 hours of time in service after 19 November 1987 or prior to 19 January 1988, whichever is earlier. This directive effectively terminates the previously allowed option of continued inspection due to an in-flight failure of a cast bracket.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39 - 105, govern the requirements for maintaining the airworthiness of DHC-2 (Beaver) Series Aeroplanes. Specifically, Airworthiness Directive (AD) DHC-2/22 Amendment 1 pertains to the aileron centre hinge bracket of these aircraft. According to Section 1 of this directive, the modification must be carried out in accordance with De-Havilland Canada Service Bulletin 2/37, Revision C (SB 2/37 Rev C), and references Canadian AD CF-84-02-R1 for further information. The directive applies to all models of DHC-2 Mk1, MkII, and DHC-2 MkIII, excluding Turbo-Beaver Aircraft that have already incorporated Modification 2/1536.
The AD mandates that the aileron centre hinge bracket must be modified as specified in the referenced service bulletin. The modification must be completed unless the aircraft has already accumulated 200 hours of time in service after 19 November 1987, or before 19 January 1988, whichever comes first. This requirement is a direct response to an in-flight failure of a cast bracket, which has necessitated a firm compliance deadline to ensure safety.
Operators and owners of DHC-2 Series Aeroplanes must ensure compliance with the directive by implementing the specified modifications. This includes conducting thorough inspections and, if necessary, making the required alterations to the aileron centre hinge bracket. These obligations are critical to maintaining the airworthiness of the aircraft and ensuring the safety of all passengers and crew.
Failure to comply with the requirements outlined in AD DHC-2/22 Amendment 1 can result in significant consequences. Under the Civil Aviation Regulations 1998, non-compliance may lead to civil penalties, including fines and potential grounding of the aircraft. The exact penalties can vary, but they are designed to enforce adherence to the airworthiness directives to prevent unsafe conditions. Ensuring that the modifications are made in a timely manner is crucial to avoid these repercussions.