Document ID: chunk:federal_register_of_legislation:F2007L02122:body:0
Version: federal_register_of_legislation:F2007L02122
Segment Type: other
Provision Reference: 
Character Range: 0–2349

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-8/131  Spring Tab Mechanism Bolts  8/2007

Applicability:  Bombardier Inc. Models DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201,
                DHC-8-202, DHC-8-301, DHC-8-311, DHC-8-314 and DHC-8-315, Serial Numbers 003 through 611.
Requirement:       1. Carry out a one-time inspection of the LH and RH elevator spring tab mechanism clamp bolts for correct installation, according to the Accomplishment Instructions of initial issue of Bombardier Service Bulletin (SB) 8-27-106, dated 7 Feb 2006, or later NAA approved revisions.

                   2. If the inspection discovered any bolt that is incorrectly installed, re-install bolt according to the Accomplishment Instructions of the above-noted SB.

                Note:  Transport Canada AD CF-2007-08 dated 4 June 2007 refers.
Compliance:        1. Within 12 months after the effective date of this AD unless already accomplished.

                   2. Prior to further flight after the effective date of this AD.
                This Airworthiness Directive becomes effective on 2 August 2007.
Background:     It has been discovered in several cases that clamp bolts of the elevator spring tab mechanism were not installed in the correct orientation.  Bolts have been found installed with bolt heads on the lower position and in two cases, some bolts, nuts and washers were found to be loose or missing.  Detachment of an elevator spring tab mechanism clamp bolt could lead to jamming of the elevator control system and reduced controllability of the aircraft.

David Punshon
Delegate of the Civil Aviation Safety Authority

21 June 2007