AD/PC-12/37 - Fuel Boost Pump Wiring

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B06100 In force Legislative Instrument

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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.


 

Pilatus PC-12 Series Aeroplanes

 

AD/PC-12/37 Fuel Boost Pump Wiring 9/2003 TX

 

Applicability: All PC-12 and PC-12/45, Manufacturers Serial Numbers 101 through 520 inclusive, with fuel boost pumps Part Number (P/N) 968.84.11.401, 968.84.11.403 or 968.84.11.404 installed.

 

Requirement: 1. Insert Temporary Revision No. 7 or No. 37, as applicable, into the Australian Aircraft Flight Manual (AFM) (Pilatus PC-12 Pilots Operating Handbook, Report No 02211 for PC-12/45 aeroplanes and Report No. 01973-001 for PC-12 aeroplanes).

 

2.         Insert Pilatus PC-12 Aircraft Maintenance Manual Temporary Revision (AMM TR) No. 12-03 (AMM 12-10-01) and AMM TR No. 28-02 (AMM 28-20-04) in the applicable AMM section.

 

3.         Perform an inspection to determine the P/N of the installed fuel boost pump.

 

4.         If, as result of the Requirement 3 inspection, a fuel boost pump with P/N 968.84.11.401 is found installed, replace the pump with a pump modified to the latest standard.

 

5.         If, as result of the Requirement 3 inspection, a fuel boost pump with P/N 968.84.11.403 or 968.84.11.404 is found installed, inspect the fuel pump leads for defects in accordance with Pilatus PC-12 Service Bulletin 28-011, Revision 1, dated 11 July 2003.

 

6.         If, as a result of the Requirement 5 Inspection, any defects are found replace the fuel boost pump with a fuel pump modified to the latest standard.

 

7.         If, as a result of the Requirement 5 Inspection, no defects are found, modify the fuel boost pumps P/N 968.84.11.403 or 968.84.11.404 by installing lead protection using spiral wrap and then re-identify the fuel pump by adding the suffix letter “B” adjacent to the serial number on the fuel pump identification plate. Both actions are to be carried out in accordance with the Accomplishment Instructions of SB 28-011 Revision 1.

 

8.         Remove Temporary Revision No. 7 or No. 37, as applicable, from the AFM.

 

9.         Fuel boost pumps with P/N 968.84.11.401 may not be installed on any PC-12 series aeroplane as a replacement part.

Pilatus PC-12 Series Aeroplanes

 

AD/PC-12/37 (continued)

 

10.    Fuel boost pumps P/N 968.84.11.403 or 968.84.11.404 may not be installed on any PC-12 series aeroplane as a replacement part unless inspected, modified and re-identified in accordance with Requirements 5 and 7, as applicable.

 

Note: Switzerland (FOCA) AD HB 2003-301 refers.

 

Compliance: For Requirement 1 - Before further flight after the effective date of this Directive.

 

For Requirement 2 - Before accomplishing any maintenance procedure after the effective date of this Directive.

 

For Requirements 3, 4 and 5 - Within 100 hours time in service (TIS) or six months, whichever occurs first, after the effective date of this Directive.

 

For Requirement 6 - Before further flight after the Requirement 5 inspection.

 

For Requirement 7 - Within 100 hours TIS or six months, whichever occurs first, after the effective date of this Directive.

 

For Requirement 8 - Immediately following completion of the Requirement 7 modification.

 

For Requirements 9 and 10 - As of the effective date of this Directive. This Airworthiness Directive becomes effective on 18 July 2003.

Background: The Swiss Federal Office for Civil Aviation has advised that it is possible to damage the electrical insulation of the fuel boost pumps during installation. This damage could cause electrical arcing within the fuel tank, which in turn could result in fire or explosion of a fuel tank.


Jim Coyne

Delegate of the Civil Aviation Safety Authority 16 July 2003

 

 

 

 

 

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 18 July 2003.

Overview

The Civil Aviation Safety Authority (CASA) issued Airworthiness Directive (AD) AD/PC-12/37 on 16 July 2003 to address a potential unsafe condition with fuel boost pumps installed in specific Pilatus PC-12 Series Aeroplanes. The AD was enacted under subregulation 39.1 (1) of the Civil Aviation Safety Regulations 1998 (CASR 1998) and became effective on 18 July 2003. The policy objective of this AD is to mitigate the risk of electrical arcing within the fuel tank that could result in fire or explosion, following advice from the Swiss Federal Office for Civil Aviation. The AD requires specific actions, including the insertion of temporary revisions into the Australian Aircraft Flight Manual and Aircraft Maintenance Manual, inspection of installed fuel boost pumps, and modification or replacement of certain parts to ensure compliance with safety standards.

Scope and Application

This Airworthiness Directive (AD) applies specifically to Pilatus PC-12 and PC-12/45 series aeroplanes with specific Manufacturer's Serial Numbers (MSNs) and installed fuel boost pumps of particular Part Numbers (P/Ns). The directive mandates actions to address potential unsafe conditions related to the fuel boost pump wiring, which could lead to electrical arcing and subsequent fire or explosion risks. The requirements include updating manuals, performing inspections, replacing or modifying fuel boost pumps, and implementing certain modifications and re-identifications. This AD is applicable within the jurisdiction of the Commonwealth of Australia and is enforced by the Civil Aviation Safety Authority (CASA). The directive does not explicitly state any exclusions or exemptions, implying that all specified aircraft within the given MSN and P/N range are subject to compliance. The timeframes for compliance are set within specific periods after the directive's effective date, and certain actions must be completed before further flights or maintenance procedures are undertaken.

Key Provisions

The Airworthiness Directive AD/PC-12/37 issued under the Civil Aviation Safety Regulations 1998 targets specific Pilatus PC-12 Series Aeroplanes to address an identified unsafe condition related to fuel boost pump wiring. It applies to all PC-12 and PC-12/45 aeroplanes with specified manufacturers' serial numbers and specific fuel boost pump part numbers installed. The main requirements of the AD include updating the Australian Aircraft Flight Manual (AFM) and the Aircraft Maintenance Manual (AMM) with Temporary Revisions No. 7 or No. 37, inspecting the installed fuel boost pump, replacing or modifying pumps as necessary, and updating the fuel pump identification in specific cases (sections 1 to 10). These steps are intended to mitigate the risk of electrical arcing in the fuel tank, which could lead to a fire or explosion. Operators and maintainers of the affected aircraft must ensure that the Temporary Revisions are incorporated into the AFM and AMM before further flight and maintenance activities, respectively (section 1, 2). Additionally, the inspection and modification of the fuel boost pump must be conducted within specified timeframes to address the identified unsafe condition (sections 3 to 7). The AD also mandates the removal of Temporary Revisions from the AFM after the specified modifications have been completed (section 8) and prohibits the installation of certain fuel boost pump part numbers unless specific inspection, modification, and re-identification procedures have been followed (sections 9 and 10). Failure to comply with the Airworthiness Directive may result in serious safety hazards, including potential fire or explosion of the fuel tank. Although the AD itself does not specify civil or criminal penalties for non-compliance, non-compliance with the Civil Aviation Safety Regulations 1998, under which this AD is issued, could result in enforcement actions by the Civil Aviation Safety Authority (CASA), including fines and other penalties as stipulated by the relevant legislation. The specific penalties for non-compliance with this AD are not detailed in the AD but would be subject to the broader regulatory framework governing civil aviation safety in Australia.

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