COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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 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-8/94 Pitot Static System 13/2003

Applicability: DHC-8 aeroplanes Models 102, 103, 106, 201, 202, 301, 311, 314 and 315, serial

numbers (S/N) 003 through 598 inclusive.

Requirement: If not previously accomplished, carry out the following:

For aeroplanes S/N 003 through 590 inclusive - Provide increased independence between the pilot's primary and standby instrument static pressure source by incorporating ModSum 8Q101238 and 8Q101340 in accordance with Part A and Part C of the Accomplishment Instructions of Bombardier Service Bulletin (SB) 8-34-221, dated 27 May 2003.

For aeroplanes S/N 591 through 598 inclusive - Correct the static system hose length by incorporating ModSum 8Q101340 in accordance with Part B and

Part C of the Accomplishment Instructions of SB 8-34-221.

Note: Transport Canada AD CF-2003-25 refers.

Compliance: Within 24 months after the effective date of this directive

This Airworthiness Directive becomes effective on 25 December 2003.

Background: Transport Canada has advised that investigation of an incident involving erroneous readings of the pilot’s flight instruments has revealed that a leak in the pilot’s static pressure system, downstream of the alternate selector valve, could result in a loss of both the pilot’s normal and alternate static systems. This condition could result in the display of misleading altitude or airspeed information to the flight crew.

Jim Coyne

Delegate of the Civil Aviation Safety Authority 14 November 2003

The above AD is notified in the Commonwealth of Australia Gazette on 3 December 2003.

Page 1 of 1