Document ID: chunk:federal_register_of_legislation:F2006B06091:body:0:p1
Version: federal_register_of_legislation:F2006B06091
Segment Type: other
Provision Reference: 
Character Range: 20–3131

AIRWORTHINESS DIRECTIVE
 For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PC-12/29 and issues the following 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.

 Pilatus PC-12 Series Aeroplanes

 AD/PC-12/29
 Amdt 1

 Engine Driven Fuel Pump 8/2003

            Applicability: All PC-12 and PC12/45 series aircraft incorporating a Lear Romec Engine Driven Pump (EDP) part number (P/N) RG9570R1, Pilatus P/N 968.84.51.106.

              Requirement: 1. Inspect the EDP relief valve for evidence of fuel leaks or gasket extrusion in accordance with the AMM 05-20-10.

2.        Replace any EDP having signs of fuel leakage or extrusion of the gasket.

3.        Replace the Lear Romec EDP P/N RG9570R1, Pilatus P/N 968.84.51.106, with EDP P/N RG9570R1/M, Pilatus P/N 968.84.51.108, in accordance with the accomplishment instructions of Pilatus PC-12 Service Bulletin No. 28-010 dated 16 September 2002.

4.        Do not fit any Lear Romec EDP P/N RG9570R1, Pilatus P/N 968.84.51.106.

            Note 1: FOCA AD HB 2003-251 refers.

            Note 2: Inspections carried out in accordance with Pilatus PC-12 SB 28-009 satisfy the initial inspection requirements of Requirement 1 of this Directive. Future inspections carried out should be in accordance with the AMM.

Compliance:  For Requirement 1.   Unless previously accomplished, within 20 flight hours from the effective date of this Directive, thereafter at intervals not to exceed 100 flight hours from the last inspection.
             For Requirement 2.   Prior to further flight.
             For Requirement 3.   Within 6 months from the effective date of this Directive.
             For Requirement 4.   From the effective date of this Directive.

            This Amendment becomes effective on 7 August 2003.

            Background: Amendment 1 of this directive requires repetitive inspection of the engine driven fuel pump, the replacement of the engine driven fuel pump with one modified by replacement of the relief valve body housing and seals, and removes reference to Pilatus SB 28-009 and FOCA AD HB 2001-500.

 Pilatus PC-12 Series Aeroplanes

 AD/PC-12/29 Amdt 1 (continued)

            The fitment of the modified housing is to prevent fuel from leaking from the housing mating surface. This replacement supersedes previous torque checking requirements.

            The original Directive was issued to address a reported fuel leak from an engine driven fuel pump relief valve cover joint. A fuel leak from the relief valve could result in a fire hazard.

            The original issue