AD/B747/201 Amdt 3 - Centre Fuel Tank Wiring and Components

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AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B747/201 Amdt 2 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.

 

Boeing 747 Series Aeroplanes

 

AD/B747/201

Amdt 3


Centre Fuel Tank Wiring and Components 13/2004

 

 

Applicability: Model 747 aeroplanes having line numbers 1 through 1124 inclusive.

 

Requirement: 1. For aeroplanes listed in Boeing Service Bulletin (SB) 747-28-2205 Revision 1 dated 16 April 1998 accomplish the following in accordance with either SB 747- 28-2205 Revision 1 dated 16 April 1998 or Revision 2 dated 17 May 1999:

 

  1. perform a one-time visual inspection of the centre fuel tank wiring and components to detect discrepancies (damage, disbonding or incorrect installation), and

 

b.        perform a one-time electrical bonding test of the centre fuel tank components.

 

Note 1: For the purposes of this Directive, a visual inspection is considered to be a general visual inspection defined as follows:

 

A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light and may require removal or opening of access panels or doors. Stands, ladders, or platforms, may be required to gain proximity to the area being checked.

 

2.         If, during the Requirement 1.a. visual inspection, any discrepancy is detected, either repair the discrepant component or replace it with a new or serviceable component.

 

3.         If, during the Requirement 1.b. electrical bonding test, any measured resistance exceeds the limits specified in the service bulletin, rework the discrepant component.

 

Note 2: Actions performed in accordance with SB 747-28-2205, dated 27 June 1997, accomplished prior to the effective date of this Directive or its original issue, are considered acceptable for compliance only with the corresponding applicable actions specified in this Directive. This excludes certain actions that are not described in that bulletin, such as inspection and testing of the body fuel tank components that are described in Revision 1 of SB 747-28-2205. Regardless of which version of the service bulletin is used to detect any discrepancies, the repair and replacement requirements of this Directive apply.

 

4.         For aeroplanes listed in Boeing Alert Service Bulletin (ASB) 747-28A2208 dated 14 May 1998, accomplish the following in accordance with either ASB 747- 28A2208 dated 14 May 1988 or Revision 1 dated 26 August 1999:

 

  1. perform a one-time insulation resistance test of the fuel quantity indicating system (FQIS),

 

b.         perform a one-time visual inspection of the FQIS wiring and components to detect discrepancies (chafing, damage to the wiring and incorrect configuration of the terminal blocks),

 

c.         replace FQIS probes (tank units and compensators) with new or serviceable components as detailed in Figure 5 of either ASB 747-28A2208 dated 14 May 1988 or Revision 1 dated 26 August 1999, and

 

d.         carry out a system adjustment and system operational test.

 

Note 3: Aeroplanes required to accomplish Requirement 4 of this Directive are exempt from accomplishing steps 1 through 9 in Figure 11 of SB 747-28-2205,

Revision 1, dated 16 April 1998.

 

Note 4: For aeroplanes on which steps 1 through 9 in Figure 11 of SB 747-28-2205,

dated 27 June 1997, or Revision 1, dated 16 April 1998, were accomplished prior to the effective date of this Directive, steps 1 through 6 in Figure 16 of ASB

747-28A2208, dated 14 May 1998 or Revision 1 dated 26 August 1999, are not required.

 

5.         If, during the Requirement 4 inspections and/or tests, any discrepancy is detected perform corrective actions in accordance with either ASB 747-28A2208 dated 14 May 1998 or Revision 1 dated 26 August 1999.

 

6.         For aeroplanes having line positions 1 through 971 inclusive, install a flame arrestor in the inlet line of the electrical motor-operated scavenge pump of the centre fuel tank, in accordance with ASB 747-22A2210 dated 14 May 1998.

 

Note 5: FAA AD 99-08-02 R1 Amdt 39-11215, AMOC 99-140S-177 dated 17 May

1999 and AMOC 99-140S-282 dated 11 August 1999 refer.

 

Compliance: 1. Within 24 months after the effective date of the original issue of this Directive.

 

2.         Before further flight.

 

3.         Before further flight.

 

4.         Within 24 months after the effective date of the original issue of this Directive.

 

5.         Before further flight.

 

6.        Within 24 months after the effective date of the original issue of this Directive. This Amendment becomes effective on 23 December 2004.

Background: This Directive is based on Federal Aviation Administration AD 99-08-02, the issue of which was prompted by a design review and testing results obtained in support of an accident investigation. The Directive is intended to remove ignition sources from the centre fuel tank and prevent consequent fire and/or explosion in the fuel tank.

 

Amendment 1 clarified Requirement 4.c., removing the terms ‘series 3’ and ‘series 4’ and replacing them with a reference to a figure in the Boeing ASB. A definition of ‘visual inspection’ as applicable to this Directive was also included as a note.

 

This amendment introduces an alternate method of compliance (AMOC) for Requirements 1, 2 and 3 reflecting a Federal Aviation Administration AMOC.

 

Amendment 2 introduced an AMOC for Requirements 4 and 5 reflecting a Federal Aviation Administration AMOC.

 


Amendment 2 of this Airworthiness Directive became effective on 6 September 2000. Amendment 1 of this Airworthiness Directive became effective on 2 December 1999. The original issue of this Airworthiness Directive became effective on 17 June 1999.

James Coyne

Delegate of the Civil Aviation Safety Authority 11 November 2004

 

 

 


The above AD is notified in the Commonwealth of Australia Gazette on 1 December 2004.

Overview

The Airworthiness Directive (AD) AD/B747/201 Amdt 3, issued by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Safety Regulations 1998, was enacted in 2004 to address safety concerns identified in Boeing 747 series aeroplanes. This directive revokes the previous Amendment 2 and introduces specific requirements to rectify unsafe conditions in the centre fuel tank wiring and components of Boeing 747 aeroplanes with line numbers ranging from 1 through 1124 inclusive. The primary objective of this directive is to prevent potential ignition sources within the centre fuel tank that could lead to fire or explosion, ensuring the airworthiness of the affected aircraft. Compliance with the directive is mandated within specific timeframes, with certain actions required before further flight and others within 24 months from the effective date of the original directive issue.

Scope and Application

The Airworthiness Directive (AD) AD/B747/201 Amdt 3 applies specifically to Boeing 747 Series aeroplanes with line numbers ranging from 1 through 1124 inclusive. This directive mandates certain actions to ensure the safety and airworthiness of the aircraft by addressing potential issues related to the centre fuel tank wiring and components. The requirements outlined in the AD necessitate actions such as performing a one-time visual inspection of the centre fuel tank wiring and components to detect discrepancies, an electrical bonding test of the centre fuel tank components, and a one-time insulation resistance test of the fuel quantity indicating system (FQIS), among others. These requirements must be carried out in accordance with specific Boeing Service Bulletins and Alert Service Bulletins, with actions to be completed within specified timelines to ensure compliance with safety regulations. The AD extends its applicability across the Commonwealth of Australia, thereby encompassing all relevant aircraft operating within the nation’s airspace. It is important to note that the AD incorporates alternate methods of compliance to provide flexibility in meeting its requirements.

Key Provisions

The Airworthiness Directive (AD) AD/B747/201 Amdt 3 applies to Boeing 747 series aeroplanes with line numbers 1 through 1124 inclusive (section 1). The directive outlines specific requirements to ensure the airworthiness of the aircraft, particularly concerning the centre fuel tank wiring and components. This includes a one-time visual inspection and electrical bonding test of the centre fuel tank wiring and components, with corrective actions if discrepancies are detected (sections 1.1 and 1.2). For aeroplanes listed in certain Boeing Service Bulletins (SB), additional steps are mandated, such as an insulation resistance test of the fuel quantity indicating system (FQIS) and visual inspection of its wiring and components, with replacement of FQIS probes as necessary (section 1.4). Furthermore, aeroplanes with specific line positions must install a flame arrestor in the inlet line of the centre fuel tank's electrical motor-operated scavenge pump (section 1.6). The AD imposes several obligations on the parties and entities it governs. Owners and operators of the specified Boeing 747 aeroplanes must ensure that the required inspections, tests, and corrective actions are performed as per the Boeing Service Bulletins and Alert Service Bulletins referenced in the directive (section 1). This includes conducting a one-time visual inspection and electrical bonding test of the centre fuel tank wiring and components, and replacing or repairing any discrepant components identified during these inspections (sections 1.1 and 1.2). For aeroplanes listed in certain Boeing Alert Service Bulletins, additional obligations such as performing an insulation resistance test of the FQIS and replacing FQIS probes are required (section 1.4). Compliance with these obligations must be achieved within specified timeframes, either within 24 months from the effective date of the original issue or before further flight, depending on the requirement (section 3). Failure to comply with the AD's requirements can result in civil or criminal consequences. Non-compliance with airworthiness directives is an offence under section 52 of the Civil Aviation Act 1988, which can lead to fines. The maximum penalties for such offences include fines of up to $126,000 for individuals and $630,000 for corporations, depending on the severity and circumstances of the breach (section 52(2) and (3)). Additionally, continued operation of an aircraft that does not comply with airworthiness standards can result in further enforcement actions, including grounding of the aircraft and potential prosecution. The AD also stipulates specific compliance deadlines. The required actions must be completed within 24 months from the effective date of the original issue of the directive or before further flight, depending on the specific requirement (section 3). For example, the visual inspection and electrical bonding test of the centre fuel tank wiring and components must be completed within 24 months from the effective date of the original issue (section 3.1). However, if any discrepancies are detected during these inspections, corrective actions must be taken before further flight (section 3.2). Similarly, the insulation resistance test of the FQIS and the visual inspection of its wiring and components must be completed within 24 months from the effective date of the original issue, with corrective actions required before further flight if any discrepancies are detected (section 3.4). Finally, the installation of a flame arrestor in the inlet line of the centre fuel tank's electrical motor-operated scavenge pump must be completed within 24 months from the effective date of the original issue (section 3.6).

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.