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:
- 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.
Overview
The Airworthiness Directive F2006B09244, issued in 2002 by the Civil Aviation Safety Authority (CASA), addresses safety concerns identified in Bombardier (Boeing Canada/De Havilland) DHC-8 Series aeroplanes, specifically models 102, 103, 106, 201, 202, 301, 311, 314, and 315 within specified serial number ranges. This directive was enacted to address the problem of chafing and wear damage to the fuselage to wing rear spar fittings caused by inadequate clearance between these fittings and the flex shaft of the flap secondary drive mechanism. The policy objective of this Airworthiness Directive is to ensure the continued airworthiness and safety of these aircraft by mandating specific inspections and repairs as outlined in the directive to mitigate the identified unsafe condition.
Scope and Application
The Airworthiness Directive issued under subregulation 39.1(1) of the Civil Aviation Regulations 1998 applies specifically to Bombardier (Boeing Canada/De Havilland) DHC-8 Series aeroplanes, including Models 102, 103, 106, 201, and 202 with serial numbers ranging from 003 to 539 (excluding 097), Model 301 with serial numbers from 100 to 200, and Models 311, 314, and 315 with serial numbers from 202 to 539 (excluding 395). This directive mandates that visual inspections on specified rear spar fittings be conducted to identify any cracks or wear damage, with subsequent replacement if the damage exceeds specified limits or if a crack is present. The directive requires these actions to be completed within 12 months from the effective date of 21 March 2002, in accordance with Bombardier Service Bulletin 8-27-83 dated 19 October 2001. The directive also references Transport Canada AD CF-2001-42 and notes that incorporation of modification 8/3149 will terminate the inspection requirements of this directive.
Key Provisions
This Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1(1) of the Civil Aviation Regulations 1998, pertains specifically to certain models of Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes. The directive applies to models 102, 103, 106, 201, and 202 with serial numbers ranging from 003 to 539 (excluding 097), model 301 with serial numbers from 100 to 200, and models 311, 314, and 315 with serial numbers from 202 to 539 (excluding 395). The AD mandates that specified actions be taken to address an unsafe condition related to the fuselage to wing rear spar fittings.
The AD requires aircraft operators and owners to perform detailed visual inspections on specific rear spar fittings, as outlined in Bombardier Service Bulletin 8-27-83 dated 19 October 2001. This inspection is to check for cracks and wear damage on fittings with part numbers 85320053, 85322060, and 85334180, according to Tables 1 and 2 in the directive. If any of these fittings exhibit wear damage exceeding specified limits in Table 2, if the area removed after blending exceeds the specified limit in Table 3, or if the fitting is cracked, it must be replaced before any further flight. Additionally, operators are required to re-inspect and repair the fittings in accordance with the compliance table provided in the directive. The incorporation of modification 8/3149 will terminate the inspection requirements of this AD. Operators must comply with these requirements within 12 months from the effective date of this directive, which is 21 March 2002.
The AD imposes specific obligations on aircraft operators and owners to ensure that the required inspections and repairs are conducted promptly and in accordance with the specified instructions. Failure to comply with the requirements of this AD can result in serious safety implications, as the identified unsafe condition could potentially lead to structural failure. The AD also references Transport Canada AD CF-2001-42 for further information. Non-compliance with this AD can result in penalties, as outlined in the Civil Aviation Regulations 1998, which may include fines and other civil or criminal consequences. The exact penalties would depend on the nature and severity of the breach, but operators are expected to adhere strictly to the AD to ensure the continued airworthiness of the aircraft.