Commonwealth legislation

AD/SF340/86 - Hydraulic Pump Electrical Wiring

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Commonwealth

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legislative instrument

Plain English Summary

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This Airworthiness Directive requires operators of SAAB SF340A aeroplanes (serial numbers 004–028) to modify the hydraulic pump electrical wiring per Saab Service Bulletin SAAB 340-29-021 (Rev 02) to reduce the pump's initial current draw.

CASA's delegate set a compliance date (2 October 2003); aircraft operators pay for and carry out the wiring change to prevent a momentary voltage drop that can blank the left-hand EFIS screens when the pump starts, increasing pilot workload.

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AIRWORTHINESS DIRECTIVE

View image in the official source

View image in the official source
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.

SAAB SF340 Series Aeroplanes

AD/SF340/86 Hydraulic Pump Electrical Wi

AD/SF340/86 Hydraulic Pump Electrical Wiring 13/2002

Applicability: SF340A series aeroplanes with serial numbers 004 to 028 inclusive.

Requirement: Modify the hydraulic pump electrical wiring circuit in accordance with Saab Aircraft Mandatory Service Bulletin (SB) SAAB 340-29-021 Revision 02 dated 2 October 2002.

Prior modification in accordance with either SB SAAB 340-29-021 dated 15 May 2001 or Revision 01 dated 3 April 2002 is considered acceptable terminating action for this Directive.

Note: LFV AD 1-179 R1 refers.

Compliance: Before 2 October 2003.

This Airwo rthiness Directive becomes effective on 26 December 2002.

Background: A high initial current flow to the hydraulic pump may cause a momentary power bus voltage drop. The voltage drop could cause the left hand electronic flight information system (LH EFIS) screens to blank when the hydraulic pump initially starts to supply hydraulic power to the landing gear and/or flaps. This temporary loss of information on the LH EFIS screens increases pilot workload.

This Directive requires the modification of the hydraulic pump electrical wiring circuits to reduce the initial flow of current to the pump.

Signature of James Coyne Delegate of the Civil Aviation Safety Authority

James Coyne

Delegate of the Civil Aviation Safety Authority 18 November 2002

View image in the official source

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

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.

SAAB SF340 Series Aeroplanes

AD/SF340/86 Hydraulic Pump Electrical Wi AD/SF340/86 Hydraulic Pump Electrical Wiring 13/2002

AD/SF340/86 Hydraulic Pump Electrical Wiring 13/2002

Applicability: SF340A series aeroplanes with serial numbers 004 to 028 inclusive.

Requirement: Modify the hydraulic pump electrical wiring circuit in accordance with Saab Aircraft Mandatory Service Bulletin (SB) SAAB 340-29-021 Revision 02 dated 2 October 2002.

Prior modification in accordance with either SB SAAB 340-29-021 dated 15 May 2001 or Revision 01 dated 3 April 2002 is considered acceptable terminating action for this Directive.

Note: LFV AD 1-179 R1 refers.

Compliance: Before 2 October 2003.

This Airwo rthiness Directive becomes effective on 26 December 2002.

This Directive requires the modification of the hydraulic pump electrical wiring circuits to reduce the initial flow of current to the pump.

James Coyne

Delegate of the Civil Aviation Safety Authority 18 November 2002