{"id":"F2006B03143","name":"AD/B747/246 Amdt 2 - Wing Front Spar Web","slug":"ad-b747-246-amdt-2-wing-front-spar-web","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42515,"registerId":"commonwealth-F2006B03143-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B747/246 Amdt 2 - Wing Front Spar Web","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \n\nAIRWORTHINESS DIRECTIVE\n\n![](image.001.png)  \n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B747/246 Amdt 1 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.\n\n![](image.001.png)  \n\nBoeing 747 Series Aeroplanes\n\nAD/B747/246\n\nAmdt 2\n\n  \nWing Front Spar Web 11/2003\n\nApplicability: Model 747 series aircraft, as listed in Boeing Service Bulletin 747-57A2311 Revision 2, dated 21 February 2002.\n\nRequirement: Inspect in accordance with the technical requirements of FAA AD 2003-16-12 Amdt 39-13265.\n\nNote: Boeing Alert Service Bulletins 747-57A2311, 747-57A2311Revision 1, including Appendices A and B, and 747-57A2311 Revision 2 refer.\n\nCompliance: As specified in the Requirement document, with a revised effective date of 30 October 2003.\n\nThis Amendment becomes effective on 30 October 2003.\n\nBackground: The FAA required inspections to detect and correct fatigue cracking of the wing front spar web, which could result in fuel leaking onto an engine and a consequent fire.\n\nAmendment 1 corrected compliance repeat inspection frequency.\n\nAmendment 2 is issued in response to a new FAA AD, which changes applicability, changes certain compliance times, adds certain new requirements, and introduces an optional modification.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.002.png)  \nAmendment 1 of this Airworthiness Directive became effective on 6 September 2001\\. The original issue of this Airworthiness Directive became effective on 12 July 2001.\n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 10 September 2003\n\n![](image.001.png)\n\nThe above AD is notified in the Commonwealth of Australia Gazette on 8 October 2003.\n\n  \n\nPage 1 of 1","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment stays within the original scope of addressing wing front spar web fatigue cracking. While Amendment 2 expands applicability, adds new requirements, and introduces an optional modification, these changes respond to the same underlying safety issue (fatigue cracking) rather than expanding into unrelated areas. The document remains a targeted airworthiness directive."},"complexity_factors":["Short, single-page document with clear structure (Applicability, Requirement, Compliance, Background)","Only 1 defined term implicitly referenced (the Boeing Service Bulletin)","Heavy reliance on external documents — the actual technical requirements are contained in FAA AD 2003-16-12 and Boeing Service Bulletins, which are not reproduced here","Simple conditional logic: if you operate this aircraft model, you must comply with the external standard","No nested exceptions or complex cross-referencing within the document itself"],"plain_english_summary":"This safety order requires owners/operators of certain Boeing 747s (per Boeing Service Bulletin 747‑57A2311 Rev 2) to inspect the wing front spar web for metal fatigue cracks, following FAA AD 2003‑16‑12, with compliance times set by that FAA document and the Australian order effective 30 October 2003. Amendment 2 updates applicability, inspection timing and options, and replaces the earlier amendment to prevent fuel leaks that could cause engine fires."},"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"},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":true,"description":"Amendment 2 changes the scope from the original AD by altering applicability, adjusting certain compliance times, adding new requirements and introducing an optional modification, as stated in the AD text (Amendment 2 paragraph)."},"complexity_factors":["Cross-reference to FAA AD 2003-16-12 and Boeing Service Bulletin 747-57A2311 Revision 2 (Requirement; Applicability) — operators must follow external technical documents.","Amendment history: revocation of prior AD and multiple amendments changing frequencies and requirements (Amendment 1; Amendment 2).","Technical subject matter: fatigue cracking of the wing front spar web requires specialist inspection methods and potential structural repairs (Background).","Variable compliance timing and repeat inspection intervals specified in the referenced FAA AD (Compliance; Requirement).","Introduction of an optional modification in Amendment 2 creates choices for operators and affects cost/maintenance planning (Amendment 2).","Enforcement and effective date set by CASA delegate, limiting administrative discretion but shifting compliance responsibility to operators (Compliance; signature/date)."],"plain_english_summary":"This Airworthiness Directive cancels the earlier AD and requires operators of specified Boeing 747 series aircraft to carry out inspections and corrective action on the wing front spar web in accordance with FAA AD 2003-16-12 and Boeing Service Bulletin 747-57A2311 Revision 2 (Requirement; Applicability). CASA’s delegate fixes the effective date and enforces compliance (Compliance). The inspections are intended to detect fatigue cracking that could allow fuel to leak onto an engine and cause a fire (Background)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web","history":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web/history","analysis":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web/analysis","conflicts":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web/conflicts","importantCases":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web/important-cases","documents":"/api/acts/ad-b747-246-amdt-2-wing-front-spar-web/documents"}}