Overview

The Civil Aviation Regulations 1998, specifically within Part 39, addresses the safety of civil aviation through various airworthiness directives. One such directive is the AD/SF340/86, issued in 2002 to address an issue identified with the Saab SF340 Series Aeroplanes, specifically those with serial numbers 004 to 028 inclusive. This directive was introduced to mitigate the risk of a momentary power bus voltage drop caused by a high initial current flow to the hydraulic pump. Such a voltage drop could lead to the left hand electronic flight information system screens going blank when the hydraulic pump initially supplies power to the landing gear and/or flaps, thereby increasing pilot workload. The Civil Aviation Safety Authority, through its delegate, mandated that the hydraulic pump electrical wiring circuits be modified in accordance with the specified service bulletin to reduce the initial current flow, ensuring safer operation of the affected aircraft. The Airworthiness Directive was enacted to ensure compliance with the safety standards set forth by the Civil Aviation Regulations 1998, with a clear policy objective to enhance the safety of aircraft operations by rectifying specific design and operational issues. The directive is effective as of 26 December 2002, with a compliance deadline set for 2 October 2003. This legislative instrument is instrumental in maintaining the safety and reliability of civil aviation within Australia, overseen by the Civil Aviation Safety Authority as the designated enforcing body.

Scope and Application

The Airworthiness Directive (AD) issued under the Civil Aviation Regulations 1998 applies specifically to SAAB SF340 series aeroplanes with serial numbers ranging from 004 to 028. The directive is issued by the Civil Aviation Safety Authority (CASA) delegate, James Coyne, to address a safety concern related to the hydraulic pump electrical wiring circuit. The directive mandates that the hydraulic pump electrical wiring be modified in accordance with Saab Aircraft Mandatory Service Bulletin (SB) SAAB 340-29-021 Revision 02 dated 2 October 2002, with modifications made in accordance with either SB SAAB 340-29-021 dated 15 May 2001 or Revision 01 dated 3 April 2002 considered acceptable. This modification is intended to prevent a high initial current flow to the hydraulic pump that may cause a momentary power bus voltage drop, leading to temporary loss of information on the left-hand electronic flight information system (LH EFIS) screens, thereby increasing pilot workload. The directive requires compliance by 2 October 2003, with the AD becoming effective from 26 December 2002. The regulation is applicable within the Commonwealth of Australia and is enforced through the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically in Part 39, Section 105, outline a procedure for issuing Airworthiness Directives (AD) aimed at ensuring the safety of civil aviation. This legislation empowers the Civil Aviation Safety Authority (CASA) to issue directives that mandate corrective actions on certain aircraft or aeronautical products. These directives are necessary when an unsafe condition is identified, and they are issued under the authority of subregulation 39.1 (1) of the Civil Aviation Regulations 1998. The AD specifies the action that must be taken, the aircraft or aeronautical products that are affected, and the conditions under which these actions must be performed, including the timeline for compliance. For the specific AD/SF340/86, the requirement is for the hydraulic pump electrical wiring circuit in Saab SF340A series aeroplanes with serial numbers ranging from 004 to 028 to be modified. This modification must be carried out in accordance with Saab Aircraft Mandatory Service Bulletin (SB) SAAB 340-29-021 Revision 02 dated 2 October 2002. Importantly, any prior modification following either SB SAAB 340-29-021 dated 15 May 2001 or Revision 01 dated 3 April 2002 is considered sufficient for compliance with this directive. The directive mandates that these modifications be completed before 2 October 2003 and became effective on 26 December 2002. The obligations imposed by this AD are clear and specific. Aircraft operators and owners within the specified serial number range must ensure that the hydraulic pump electrical wiring modifications are performed in line with the provided service bulletin. This includes conducting the necessary modifications by the specified compliance date to maintain the airworthiness of the aircraft. Failure to comply with the AD may result in the aircraft being deemed unairworthy, leading to potential grounding and enforcement actions by CASA. In terms of consequences, the Civil Aviation Act 1988 provides that failure to comply with an AD can lead to significant penalties. The maximum penalty for contravening an AD is generally substantial, reflecting the serious nature of ensuring aviation safety. Such penalties can include fines and, in severe cases, criminal charges against responsible individuals, such as the aircraft owner or operator. Ensuring compliance with ADs is critical, not only for maintaining the safety of the aircraft but also to avoid legal repercussions and potential harm to passengers and crew.