{"id":"F2006B03142","name":"AD/B747/245 - Longeron Splice Fittings, Stringer 11 at Body Station 2598","slug":"ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42514,"registerId":"commonwealth-F2006B03142-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B747/245 - Longeron Splice Fittings, Stringer 11 at Body Station 2598","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \n![](image.002.png)  \nBoeing 747 Series Aeroplanes\n\nAIRWORTHINESS DIRECTIVE\n\n![](image.002.png)\n\n![](image.002.png)  \nFor 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 CAR 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\nAD/B747/245 Longeron Splice Fittings, Stringer\n\n11 at Body Station 2598\n\n  \n7/2001\n\nApplicability: Model 747-400 series aircraft, as listed in Boeing Alert Service Bulletin 747- 53A2419, Revision 1 dated 21 September 2000.\n\nRequirement: Inspect in accordance with the technical requirements of FAA AD 2000-25-11 Amdt 39-12046.\n\nNote: Boeing Alert Service Bulletin 747-53A2419 Revision 1, including Appendix A, refer.\n\nCompliance: For the initial detailed visual inspection, at the later of the following times:\n\n    Before the accumulation of 17,000 total flight cycles or 63,000 total flight hours, whichever occurs first.\n\n    b. Before 30 January 2003.\n\nThereafter at the repeat inspection times specified in the Requirement document. This Airworthiness Directive becomes effective on 12 July 2001.\n\nBackground: The FAA requires inspections to detect and correct fatigue cracking of the longeron splice fittings and subsequent damage to adjacent structure. Such Damage could result in the inability of the structure to carry horizontal stabiliser flight loads, with consequent reduced controllability of the horizontal stabiliser.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.003.png)  \n\nDavid Alan Villiers\n\nDelegate of the Civil Aviation Safety Authority 18 May 2001\n\n![](image.002.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 13 June 2001.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive maintains its original narrow scope. It addresses a specific unsafe condition identified by the FAA regarding fatigue cracking in a particular structural component on a specific aircraft model (Boeing 747-400). The directive has not expanded beyond its original purpose of mandating inspections for this single safety issue."},"complexity_factors":["Short, single-purpose directive (approximately 300 words)","Only 4 defined structural references (longeron splice fittings, Stringer 11, Body Station 2598, horizontal stabiliser)","Single cross-reference to FAA AD 2000-25-11 and Boeing Service Bulletin 747-53A2419 Revision 1","Simple conditional logic: two alternative compliance deadlines (flight cycles/hours vs calendar date), with 'later of' determining which applies","No nested exceptions or sub-delegations","Technical aviation terminology requires some domain knowledge but is standard for the industry"],"plain_english_summary":"This CASA safety order requires operators of certain Boeing 747-400s (those listed in Boeing Alert Service Bulletin 747-53A2419, Rev 1) to inspect the longeron splice fitting at Stringer 11, Body Station 2598. The FAA found fatigue cracking there that could spread and impair horizontal stabiliser control.\n\nFirst inspection must occur before 17,000 flight cycles or 63,000 flight hours (and no later than 30 Jan 2003); repeat inspections follow FAA AD 2000-25-11. Non‑compliance grounds an aircraft from Australian airspace."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The AD adopts the FAA AD inspection requirements and the Boeing service bulletin applicability as stated. The text does not expand or narrow applicability beyond the documents it references."},"complexity_factors":["Cross-reference to external documents (FAA AD 2000-25-11 and Boeing Alert Service Bulletin 747-53A2419 Rev 1) — operator must consult and follow multiple technical sources (Requirement / Note).","Technical nature of required work: 'detailed visual inspection' implies need for trained maintenance personnel and possible non-routine access/fixtures (Requirement / Compliance).","Conditional compliance timing: initial inspection triggered by whichever occurs first of flight cycles, flight hours or a calendar date (Compliance).","Ongoing obligation: repeat inspections are mandated by the referenced FAA AD, creating a continuing maintenance schedule (Compliance / Requirement).","Potential operational cost and downtime: inspections may reveal cracking requiring corrective action or repairs that affect aircraft availability and repair costs (Background / Requirement).","Regulatory mechanism: issued under subregulation 39.1(1) of CAR 1998 by CASA delegate, creating a legally enforceable obligation on operators (preamble)."],"plain_english_summary":"This directive requires operators of the specified Boeing 747‑400 aircraft to carry out detailed visual inspections of the longeron splice fittings at stringer 11, body station 2598, following FAA AD 2000‑25‑11 and Boeing Alert Service Bulletin 747‑53A2419 Rev 1. The first inspection must occur before 17,000 flight cycles or 63,000 flight hours, or by 30 January 2003, with repeat inspections as in the FAA AD. Operators pay for inspections and any repairs; the inspection aims to find fatigue cracking that could impair horizontal stabiliser load capability."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598","history":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598/history","analysis":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598/analysis","conflicts":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598/conflicts","importantCases":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598/important-cases","documents":"/api/acts/ad-b747-245-longeron-splice-fittings-stringer-11-at-body-station-2598/documents"}}