{"id":"F2007L02358","name":"AD/B747/358 - Integrated Display System and Fuel Tank Safety","slug":"ad-b747-358-integrated-display-system-and-fuel-tank-safety","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":67689,"registerId":"commonwealth-F2007L02358-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Boeing 747 Series Aeroplanes","sectionType":"division","heading":"Boeing 747 Series Aeroplanes","content":"### Boeing 747 Series Aeroplanes\n\n| AD/B747/358 | Integrated Display System and Fuel Tank Safety | 9/2007 |\n| ----------- | ---------------------------------------------- | ------ |\n\n```html\n

Applicability:

Boeing 747 series aeroplanes identified in the Boeing Alert Service Bulletins (ASB) listed in Table 1.

Table 1

747 Series Aeroplanes

747-400, 747-400D and 747-400F
747-400 and 747-400F
747-400 and 747-400F

Boeing ASB

747-31A2351, Revision 1, dated 17 March 2005
747-31A2350, Revision 1, dated 17 March 2005
747-31A2352, Revision 1, dated 17 March 2005

Requirement:

1. Install new IDS-504 software in the integrated display units and electronic flight instrument system/engine indication and crew alerting system interface units of the flight deck, in accordance with the Accomplishment Instructions of the applicable ASB identified in Table 2.

Table 2

747 Series Aeroplanes

747-400, 747-400D and 747-400F
747-400 and 747-400F
747-400 and 747-400F

Boeing ASB

747-31A2351, Revision 1, dated 17 March 2005
747-31A2350, Revision 1, dated 17 March 2005
747-31A2352, Revision 1, dated 17 March 2005

Note 1: Each ASB identified in Table 2 refers to Rockwell Collins Service Bulletin (SB) IDS-7000-31-49, IDS-7000-31-50 or IDS-7000-31-51; all dated 28 June 2004; as applicable; as an additional source of service information for installing the new IDS software.

Installing new IDS-504 software before the effective date of this Directive, in accordance with the applicable ASB identified in Table 3 or during production of the aeroplane, is acceptable for compliance with Requirement 1.

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Table 3

747 Series Aeroplanes

747-400, 747-400D and 747-400F
747-400 and 747-400F
747-400 and 747-400F

Boeing ASB

747-31A2351, dated 3 September 2004
747-31A2350, dated 3 September 2004
747-31A2352, dated 3 September 2004

For aeroplanes not equipped with a horizontal stabiliser tank (HST) - Installing
IDS-503 software before the effective date of this Directive, in accordance with the applicable ASB identified in Table 4, is acceptable for compliance with Requirement1.

Table 4

747 Series Aeroplanes

747-400, 747-400D and 747-400F

747-400 and 747-400F

747-400 and 747-400F

Boeing ASB

747-31A2340, Revision 1, dated 20 November 2003
747-31A2341, Revision 1, dated 20 November 2003
747-31A2342, Revision 1, dated 20 November 2003

Note 2: Each ASB identified in Table 4 refers to Rockwell Collins SB
IDS-7000-31-46, IDS-7000-31-47 or IDS-7000-31-48; all dated 22 April 2003; as applicable; as an additional source of service information for installing the IDS-503 software.

Installing IDS-505 or IDS-506 software during production of the aeroplane is acceptable for compliance with Requirement 1. Additionally, installing IDS-506 software as a retrofit in accordance with the applicable SB identified in Table 5, is acceptable for compliance with Requirement 1.

Table 5

747 Series Aeroplanes

747-400, 747-400D and 747-400F
747-400 and 747-400F
747-400 and 747-400F

Boeing SB

747-31-2376, dated 5 September 2006
747-31-2377, dated 5 September 2006
747-31-2378, dated 5 September 2006

Note 3: Each SB identified in Table 5 refers to Rockwell Collins SB IDS-7000-31-52, IDS-7000-31-53 or IDS-7000-31-54; all dated 30 August 2006; as applicable; as an additional source of service information for installing the IDS-506 software.

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2. For aeroplanes on which FR-HiTEMP fuel pumps have been installed in accordance with Boeing SB 747-28-2258, dated 19 December 2003, or Revision 1, dated 11 August 2005 or during production - Remove the ground wire of the wire integration unit that corresponds to the connector and pin locations in Table 6, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Chapter 20-41-03 of the Boeing 747-400 Aircraft Maintenance Manual is one approved method.

Table 6

Connector

L-EIU DM7353CA
C-EIU DM7352CA
R-EIU DM7351CA

Pin

G13
G13
G13

3. Except as specified in Requirement 4, revise the Limitations section of the Aircraft Flight Manual (AFM) to include the information at Annex A to this Directive.

4. For aeroplanes on which FR-HiTEMP fuel pumps have been installed in accordance with SB 747-28-2258, original issue or Revision 1, or during production - Revise the Limitations section of the AFM to include the information at Annex A to this Directive.

Amendment of the AFM may be accomplished by inserting a copy of Annex A to this Directive into the AFM.

5. Remove the AFM amendments specified in the Airworthiness Directives identified in Table 7.

Table 7

Directive

AD/B747/270
AD/B747/188 Amdt 3
AD/B747/280
AD/B747/283

Requirement

1
4
2
Not Applicable

Equivalent FAA AD

2001-12-21 Amdt 39-12277
2001-21-07 Amdt 39-12478
2002-19-52 Amdt 39-12900
2002-24-52 Amdt 39-12993

Later revisions of the above SBs, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2007-13-14, are considered acceptable for compliance with the equivalent Requirements of this Directive.

Note 4: FAA AD 2007-13-04 Amdt 39-15108 refers.

\n```\n\n| Compliance: | For Requirement 1 - Within six months after the effective date of this Directive. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| | For Requirement 2 - After installing the new IDS-504 software required by Requirement 1 and within six months after the effective date of this Directive. |\n| | For Requirement 3 - Concurrently with Requirement 1. |\n| | For Requirement 4 - Concurrently with the Requirement 2. |\n| | For Requirement 5 - Following compliance with Requirements 1 and 3. |\n| | This Airworthiness Directive becomes effective on 30 August 2007. |\n| Background: | This Directive is issued following a fuel system reviews conducted by the manufacturer. The Directive is issued to reduce the potential for ignition sources inside fuel tanks, which, in combination with flammable fuel vapours, could result in fuel tank explosions and consequent loss of the aeroplane. |\n\n![](image.001.png) \nDavid Punshon \nDelegate of the Civil Aviation Safety Authority\n\n26 June 2007\n\n \nAnnex A\n\nCertification Limitations\n\nCenter Wing Tank (CWT):\n\nThe CWT fuel quantity indication system must be operative to dispatch with CWT mission fuel.\n\nIf the FUEL LO CTR L or R message is displayed both CWT override/jettison pumps must be selected OFF.\n\nIf the FUEL PRESS CTR L or R message is displayed, the corresponding CWT override/jettison pump must be selected OFF.\n\nNote: In a low fuel situation, both CWT override/jettison pumps may be selected ON and all CWT fuel may be used.\n\nHorizontal Stabilizer Tank (HST):\n\nThe following additional limitations must be followed if the HST is fueled and used:\n\nThe HST fuel quantity indication system must be operative to dispatch with HST mission fuel.\n\nIf the FUEL PMP STB L or R message is displayed while on the ground both HST pumps must be selected OFF.\n\nIf the FUEL LO STAB L or R message is displayed in flight the corresponding HST pump must be selected OFF.\n\nIf the FUEL PRESS STAB L or R message is displayed the corresponding HST pump must be selected OFF.\n\nThe remaining fuel in the HST must be considered unusable, and the effects of that unusable fuel on balance (CG) must be considered.\n\nNote: In a low fuel situation, both HST transfer pumps may be selected ON and all HST fuel may be used.\n\nWarning\n\nDo not cycle CWT and HST pump switches from ON to OFF to ON with any continuous low pressure indication present.\n\nDo not reset a tripped fuel pump circuit breaker.\n\n \nDefueling:\n\nPrior to defueling any fuel tanks, perform a lamp test of the respective Fuel Pump Low Pressure indication lights. When defueling, the Fuel Pump Low Pressure indication lights must be monitored and the fuel pumps positioned to OFF at the first indication of fuel pump low pressure. When defueling with passengers on board, fuel pump switches must be selected OFF at or above approximately 7,000 pounds (3,200 kilograms) for the CWT, 3,000 pounds (1,400 kilograms) for main tanks, and 2,100 pounds (1,000 kilograms) for the HST.\n\nThe above requirements apply for defueling or transferring between tanks.","sortOrder":0},{"sectionNumber":"AD/B747/358","sectionType":"part","heading":"AD/B747/358","content":"## AD/B747/358","sortOrder":1},{"sectionNumber":"Integrated Display System and Fuel Tank ","sectionType":"part","heading":"Integrated Display System and Fuel Tank Safety","content":"## Integrated Display System and Fuel Tank Safety","sortOrder":2},{"sectionNumber":"9/2007","sectionType":"part","heading":"9/2007","content":"## 9/2007","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":7,"scope_assessment":{"changed":false,"description":"No evidence in the text that the Directive's applicability was broadened beyond the manufacturer’s fuel‑system review outcome. The instrument targets specified Boeing 747‑400 series aeroplanes and prescribes software retrofits, a wiring modification for a defined pump installation, and AFM limitations (Annex A). It also consolidates and replaces certain prior AFM amendments (Table 7) and references FAA ADs and AMOCs, but does not indicate an expansion of the original technical scope."},"complexity_factors":["Multiple acceptable software versions and retrofit paths (IDS‑504 required; IDS‑503/505/506 or production installs accepted in some cases) — see Requirement 1, Tables 2–5.","Several linked manufacturer service bulletins (Boeing ASBs and Rockwell Collins SBs) across different dates and revisions, creating alternative compliance paths and version control complexity — see Tables 2–5 and Notes 1–3.","Cross‑jurisdictional approval dependencies: wiring change (Requirement 2) must follow a method approved by the FAA Seattle ACO (Manager, Seattle ACO), so compliance may require FAA coordination and documentation.","Physical wiring modification (removal of ground wire at specific connectors/pin G13) requires maintenance access and verification — see Requirement 2 and Table 6.","AFM amendments (Requirement 3 and 4, Annex A) impose operational limitations and defueling procedures that change crew procedures and dispatchability rules, increasing training and operational compliance burden.","Sequenced and conditional compliance deadlines: different Requirements tie to each other (e.g. Requirement 2 only after installing IDS‑504) and have a six‑month overall compliance window — see Compliance section.","Interaction with prior Airworthiness Directives: operators must remove earlier AFM amendments listed in Table 7, requiring record reviews and document management.","Acceptance of later SB revisions as FAA AMOC to FAA AD introduces administrative review to confirm equivalence — see final paragraph and Note 4.","Operational monitoring obligations (lamp tests, fuel pump switch actions, unusable fuel/CG considerations) add recurrent operational checks and potential dispatch constraints (Annex A)."],"plain_english_summary":"This Directive requires operators of specified Boeing 747‑400 series aeroplanes to install updated IDS display software (or approved equivalents), remove a specific ground wire on aeroplanes fitted with certain FR‑HiTEMP fuel pumps, and insert new operational limitations into the Aircraft Flight Manual (Annex A). It affects airlines and maintenance organisations who must perform software and wiring work and update operating documentation within set deadlines; the stated aim is to reduce potential ignition sources inside fuel tanks."},"kimi_summary":{"content_quality":"ok","complexity_score":6,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with a focused, single-purpose scope: addressing fuel tank ignition risks in Boeing 747-400 series aircraft. The document does not show scope creep — it remains tightly focused on the original safety issue (fuel tank explosions) identified in the background section. The multiple tables and references are necessary to specify technical implementation details for different aircraft configurations, not an expansion of regulatory purpose."},"complexity_factors":["Multiple cross-referenced tables (7 tables) mapping aircraft models to specific Boeing Alert Service Bulletins and Service Bulletins","Nested compliance pathways — different software versions (IDS-503, IDS-504, IDS-505, IDS-506) acceptable depending on aircraft configuration and timing of installation","Conditional requirements based on aircraft equipment (horizontal stabilizer tank presence, FR-HiTEMP fuel pump installation status)","Reference to external documents (FAA AD 2007-13-14, Boeing maintenance manuals, Rockwell Collins service bulletins) without full text inclusion","Interdependent compliance deadlines — Requirement 2 cannot be completed before Requirement 1, Requirement 4 depends on Requirement 2, etc.","Technical aviation terminology throughout (EIU, ASB, AMOC, ACO, CWT, HST) requiring specialised knowledge","Exception clauses for pre-existing compliance (installations done before the effective date or during production)"],"plain_english_summary":"This CASA Airworthiness Directive mandates modifications to Boeing 747-400 series aircraft to reduce fuel-tank ignition risk: install IDS‑504 cockpit display software, remove a specific fuel-system ground wire on affected aircraft, and update the Aircraft Flight Manual with new fuel‑pump operating limits. \n\nIt affects Australian operators, maintenance organisations and pilots; compliance is legally required within the directive’s specified timeframes or the aircraft may be grounded."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety","history":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety/history","analysis":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety/analysis","conflicts":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety/conflicts","importantCases":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety/important-cases","documents":"/api/acts/ad-b747-358-integrated-display-system-and-fuel-tank-safety/documents"}}