Document ID: chunk:federal_register_of_legislation:F2006L03189:body:0:p1
Version: federal_register_of_legislation:F2006L03189
Segment Type: other
Provision Reference: 
Character Range: 0–3408

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 39.001(1) of CASR 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.

Short SD3-30 Series Aeroplanes
AD/SD3-30/48  Fuel Tank Safety - Fuel    11/2006
              Airworthiness Limitations

Applicability:  Model SD3-30 aeroplanes, all serial numbers.
Requirement:       1. Maintenance/Inspection Tasks -
                     a. Accomplish the inspections including any necessary rectification action together with the installation of additional electrical bonding as specified in Bombardier Aerospace Shorts Service Bulletin SD330-28-37 dated June 2004 or later EASA approved revision.
                     b. Incorporate the fuel system airworthiness limitations specified in Sections
                     5-20-01 and 5-20-02 of the Aircraft Maintenance Manual Publications as introduced by the Temporary Revisions TR330-AMM-35 and
                     TR330-AMM-35detailed into the operator approved maintenance programme/Schedule.
                Note 1:  Accomplishment of the tasks specified in Requirement 1 is required to ensure that baseline inspections/checks are accomplished.  Subsequent repeat inspections/checks shall then be accomplished in accordance with Section 5-20-01 of the AMM at the established repeat intervals.
                   2. Critical Design Control Configuration Limitations (CDCCL) - The operator shall ensure that their internal maintenance control documentation is amended to reflect the data contained within Section 5.20.02 of the AMM and to provide appropriate text to highlight the existence of each CDCCL.
                Note 2:  EASA AD 2006-0198 refers.
Compliance:     For Requirement 1 -
                     a. Within six months after the effective date of this Directive.
                     b. Within three months after the effective date of this Directive.
                For Requirement 2 - Before 1 July 2007.
                This Airworthiness Directive becomes effective on 26 October 2006.

Background:  Subsequent to accidents involving Fuel Tank System explosions in flight (Boeing 747-131 flight TWA800) and on the ground, the United States Federal Aviation Administration (FAA) published Special Federal Aviation Regulation 88 (SFAR88) in June 2001.  SFAR 88 required a safety review of the aircraft Fuel Tank System to determine that the design meets the requirements of FAR § 25.901 and § 25.981(a) and (b).

             A similar regulation has been recommended by the European Joint Aviation Authorities (JAA) to the European National Aviation Authorities in JAA letter 04/00/02/07/03-L024 of 3 February 2003.  The review was requested to be mandated by European National Airworthiness Authorities using JAR § 25.901(c), § 25.1309.

             In August 2005 the European Aviation Safety Agency (EASA) published a policy statement on