AIRWORTHINESS DIRECTIVE ADDHC-8137 Wing Front Spar to Fuselage by lindash


More Info
									COMMONWEALTH OF AUSTRALIA                                                       (Civil Aviation Safety Regulations 1998), PART 39 - 105

                                                   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.

Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes

AD/DHC-8/137                                 Wing Front Spar to Fuselage Attachment                                                                  4/2008

Applicability:               DHC-8 aircraft, Models 400, 401, and 402, serial numbers 4001, and 4003 through

Requirement:                 Action in accordance with the requirements of Transport Canada Emergency AD

                             Note: Bombardier Inc. Alert Service Bulletin A84-57-19 original issue, or later
                             Transport Canada approved revision, refers.

Compliance:                  As specified in the Requirement document, with a revised effective date of 8 February

                             This Airworthiness Directive becomes effective on 8 February 2008.

Background:                  During scheduled maintenance, an operator found cracks in the DSC228-16 barrel nut
                             at one of the four primary front spar wing to fuselage attachment joints. The
                             investigation determined that the cracks were due to hydrogen embrittlement and the
                             problem is believed to be restricted to a batch of 166 barrel nuts from one supplier.
                             Further inspection by a different operator revealed that cracked barrel nuts were found
                             at three of the four wing front spar to fuselage joints on the same aircraft. All three
                             barrel nuts were from the suspect batch. Failure of the barrel nuts could compromise
                             the integrity of the wing to fuselage attachments.

David Villiers
Delegate of the Civil Aviation Safety Authority

6 February 2008

                                                                                                                                                     Page 1 of 1
                                                     Federal Register of Legislative Instruments F2008L00311

To top