Document ID: chunk:federal_register_of_legislation:F2006B09244:body:0
Version: federal_register_of_legislation:F2006B09244
Segment Type: other
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Character Range: 0–2858

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 39.1 (1) of CAR 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-8/85 Fuselage to Wing Rear Spar Fittings 3/2002

 Applicability: Models 102, 103, 106, 201, and 202, serial numbers 003 through 539 (except 097).

            Model 301, serial numbers 100 through 200.

            Models 311, 314, and 315, serial numbers 202 through 539 (except 395).

              Requirement: 1. Accomplish the following in accordance with Bombardier Service Bulletin 8-27- 83, dated 19 October 2001:

                  1. Perform visual inspections on the rear spar fittings part numbers 85320053, 85322060, and 85334180 for cracks and wear damage in accordance with Tables 1 and 2 of the Requirement document.

                 b.         Replace the damaged fittings before further flight if any of the following conditions are present:

(i)            The wear damage before blending is greater than the limits specified in Table 2 of the Requirement document.

(ii)         The area removed after blending is greater than that specified in Table 3 of the Requirement document.

(iii)       If the fitting is cracked.

              2. Re-inspect /repair fittings in accordance with the requirements of the compliance table specified in the Requirement document.

            Note 1: Incorporation of modification 8/3149 will terminate the inspection requirements of this Directive.

            Note 2: Transport Canada AD CF-2001-42 refers.

 Compliance: 1. Within 12 months after the effective date of this Directive.

            2. As specified in the Requirement document.

            This Airworthiness Directive becomes effective on 21 March 2002.

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

 AD/DHC-8/85 (continued)

            Background: Chafing/wear has been found on the fuselage to wing rear spar fittings as a result of inadequate clearance between these fittings and the flex shaft of the flap secondary drive mechanism.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 8 February 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 27 February 2002.