Overview

The Civil Aviation Regulations 1998 (CAR 1998) represent a critical component of Australian civil aviation legislation, enacted by the Commonwealth of Australia to ensure the safety and airworthiness of aircraft within its jurisdiction. This particular legislative instrument, F2006B02858, issued under the authority of the Civil Aviation Safety Authority (CASA), addresses a specific safety concern identified in the Boeing 737 Series Aeroplanes. The problem it targets is the reported fatigue cracking of the elevator hinge plates, which could potentially lead to a critical loss of attachment between the elevator and the horizontal stabiliser, thereby compromising the aircraft's controllability. This Airworthiness Directive (AD/B737/155) mandates actions to be taken to mitigate this risk, ensuring compliance with technical requirements as specified in FAA AD 2001-06-08 Amdt39-12155, and references Boeing Service Bulletin 737-55-1067. The directive aims to safeguard public safety by enforcing regular inspections and necessary repairs on affected aircraft within stipulated flight cycle intervals, underscoring the policy objective of maintaining the highest standards of aviation safety.

Scope and Application

The Civil Aviation Regulations 1998, as amended, mandate the maintenance and safety standards for aircraft operating within Australian airspace, and this particular Airworthiness Directive (AD) applies specifically to Boeing 737 Series Aeroplanes, namely the 737-600, -700, and -800 series aircraft, with line numbers 1 through 84. The AD, issued under the authority of the Civil Aviation Safety Authority (CASA), requires corrective action to be taken on the elevator hinge plates to address the identified risk of fatigue cracking which could compromise the attachment of the elevator to the horizontal stabiliser, thereby affecting the aircraft’s controllability. Compliance with the AD is mandatory for the specified aircraft, demanding adherence to the technical requirements outlined in the Federal Aviation Administration (FAA) AD 2001-06-08 Amdt 39-12155, with reference to Boeing Service Bulletin 737-55-1067. The directive stipulates that the necessary action must be completed before the aircraft accumulates 7,000 total flight cycles or within 90 days following 9 August 2001, whichever is later, and subsequently at intervals not exceeding 4,000 flight cycles until the optional terminating action specified in Boeing Service Bulletin 737-55-1067 Part II is accomplished.

Key Provisions

This Airworthiness Directive (AD) applies specifically to Boeing 737 series aeroplanes, namely the 737-600, -700, and -800 models, with line numbers ranging from 1 to 84. The directive mandates that actions be taken to address fatigue cracking of the elevator hinge plates, a condition that could potentially lead to a loss of attachment between the elevator and the horizontal stabiliser, thereby compromising the aircraft's controllability (Section 8/2001). The required actions must adhere to the technical requirements outlined in FAA AD 2001-06-08 Amdt39-12155 and Boeing Service Bulletin 737-55-1067. The AD stipulates that the corrective action must be implemented before the aircraft accumulates 7,000 total flight cycles or within 90 days following 9 August 2001, whichever comes later. Once initiated, these actions must be repeated at intervals not exceeding 4,000 flight cycles until the optional terminating action specified in Part II of Boeing Service Bulletin 737-55-1067 is accomplished. This AD became effective on 9 August 2001. The obligations imposed by this AD include ensuring that the specified maintenance actions are carried out in a timely and compliant manner. Operators of the affected Boeing 737 series aircraft must monitor the flight cycles of their aircraft and schedule the required inspections and repairs accordingly. Furthermore, they must maintain accurate records of the actions taken and the intervals at which they are performed. The AD also requires that all maintenance personnel involved in these activities are appropriately trained and certified to perform the specified tasks. Failure to comply with this AD could result in severe safety risks, as the unaddressed fatigue cracking could lead to a significant loss of control over the aircraft. In terms of penalties, while the specific civil or criminal consequences for non-compliance are not detailed in the text, it is implied that non-compliance could lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Such actions might include fines, grounding of the non-compliant aircraft, or other regulatory measures designed to ensure compliance and maintain aviation safety standards.