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 of this directive became effective on 26 September 2001.
Jim Coyne
Delegate of the Civil Aviation Safety Authority 26 June 2003
The above AD is notified in the Commonwealth of Australia Gazette on 16 July 2003.
Overview
The Civil Aviation Safety Authority Amendment Instrument 2003 (F2006B06091) was enacted in 2003 to address safety concerns associated with fuel leaks from the engine driven fuel pump relief valve cover joint of Pilatus PC-12 Series Aeroplanes. This legislative instrument amends the existing Airworthiness Directive AD/PC-12/29, which was originally issued on 26 September 2001, in response to a reported fuel leak that posed a potential fire hazard. The primary objective of this amendment is to enhance the safety of these aircraft by requiring the inspection and replacement of specific engine driven fuel pump components. The Civil Aviation Safety Authority, as the enacting body, aims to mitigate the risk of fire by mandating regular inspections and the replacement of the engine driven fuel pump with a modified version, which addresses the issue of fuel leakage from the housing mating surface. This directive ensures compliance with safety standards and protects the operational integrity of Pilatus PC-12 aircraft.
Scope and Application
The Airworthiness Directive issued under the Civil Aviation Safety Regulations 1998 applies specifically to Pilatus PC-12 and PC-12/45 series aircraft equipped with a Lear Romec Engine Driven Pump (EDP) bearing the part number RG9570R1 or Pilatus P/N 968.84.51.106. This legislative instrument mandates that aircraft operators must comply with certain requirements to ensure the airworthiness of these aircraft, particularly focusing on the EDP component. The directive applies nationwide across the Commonwealth of Australia and is overseen by the Civil Aviation Safety Authority (CASA). The requirements outlined in the directive include inspecting the EDP relief valve for fuel leaks or gasket extrusion, replacing any EDP exhibiting such issues, substituting the original EDP with a modified version, and prohibiting the installation of the unmodified EDP moving forward. Compliance with these directives is mandatory, with specific timeframes set for each requirement, ranging from immediate action upon the directive’s effective date to inspections within 20 flight hours and at intervals not exceeding 100 flight hours thereafter. The directive also references previous safety bulletins and airworthiness directives, indicating its role in a broader safety management framework.
Key Provisions
The Airworthiness Directive AD/PC-12/29 Amendment 1 issued under subregulation 39.1(1) of the Civil Aviation Regulations 1998, pertains specifically to Pilatus PC-12 and PC-12/45 series aircraft equipped with a Lear Romec Engine Driven Pump (EDP) with part number RG9570R1 or Pilatus P/N 968.84.51.106. The directive mandates that specific actions must be taken to rectify an identified unsafe condition, namely a fuel leak from the EDP relief valve cover joint, which poses a fire hazard (s. 1). The actions include inspecting the EDP relief valve for fuel leaks or gasket extrusion, replacing any EDP showing signs of leakage or gasket extrusion, replacing the specified EDP with a modified version, and prohibiting the fitting of the unmodified EDP (s. 2).
The directive imposes specific obligations on the operators and owners of affected aircraft. They must ensure that the EDP relief valve is inspected within 20 flight hours from the effective date of the directive and subsequently at intervals not exceeding 100 flight hours (s. 3). Any EDP showing signs of leakage or gasket extrusion must be replaced before further flight (s. 4). The replacement of the specified EDP with the modified version must be completed within six months of the directive's effective date (s. 5). Additionally, the unmodified EDP must not be fitted from the effective date of the directive onwards (s. 6).
Failure to comply with the requirements of this Airworthiness Directive can result in serious safety implications. The directive does not specify particular penalties, but non-compliance can potentially lead to civil or criminal actions under the Civil Aviation Act 1988, which may include fines and imprisonment for breaches that result in serious harm or endanger the safety of aircraft operations. Additionally, non-compliance can result in the grounding of the aircraft until the required actions are taken, which could significantly impact the operational capabilities of the aircraft owner or operator.