Document ID: chunk:federal_register_of_legislation:F2006B09202:body:0
Version: federal_register_of_legislation:F2006B09202
Segment Type: other
Provision Reference: 
Character Range: 0–2315

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

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

 AD/DHC-8/47
 Amdt 1

 Engine Compartment Hydraulic System 13/98

 Applicability: All DHC-8 model 100 and 300 series aircraft, serial number 003 through 405. Requirement:               1. Aircraft within S/N range 003 through 154.
             Incorporate modification 8/1152 to relocate the parking brake accumulator in accordance with de Havilland SB 8-32-128 Revision B dated 30 August 1996.

2.    Aircraft within S/N range 003 through 392.

             Incorporate modification 8/1982 to relocate the parking brake charging valve in accordance with de Havilland SB 8-32-128 Revision B dated 30 August 1996.

3.    Aircraft within S/N range 003 through 405.

             Incorporate modification 8/1983 to relocate the No.2 standby power unit in accordance with de Havilland SB 8-29-23 dated 06 December 1996, Or

             Incorporate modification 8/2781 in accordance with de Havilland SB 8-29-29, dated 27 February 1998 for aircraft where this modification has not been incorporated during manufacture.

             Upon incorporation of either modification above, the corresponding Aircraft Flight Manual (AFM) revision identified in section D, compliance, of the applicable Service Bulletin must be inserted in the affected aircraft's AFM.

            Note: Transport Canada AD CF-96-25R2 refers.

            Compliance: Unless previously accomplished comply with Requirements 1, 2 and 3, as applicable, prior to 15 June 2000.

            This Airworthiness Directive becomes effective on 3 December 1998.

            Background: The manufacturer has advised that two fuel-fed fires in the engine compartment resulted in fire damage to hydraulic components located in the number 2 engine nacelle. This resulted in total loss of system 1 and 2 hydraulic pressure. Component relocation will ensure hydraulic pressure for rudder operation continues to be maintained.

            The revision of this AD was introduced to allow alternate compliance with requirement 3 of this AD.

            The original issue of this Airworthiness Directive became effective on 27 February 1997.