{"id":"F2006B03133","name":"AD/B747/235 Amdt 1 - Fuselage Skin at BS 980 Drag Splice Fitting","slug":"ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42505,"registerId":"commonwealth-F2006B03133-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B747/235 Amdt 1 - Fuselage Skin at BS 980 Drag Splice Fitting","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\nAIRWORTHINESS DIRECTIVE\n\n![](image.001.png)\n\n![](image.001.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B747/235 and issues the following 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\nBoeing 747 Series Aeroplanes\n\nAD/B747/235\n\nAmdt 1\n\n  \nFuselage Skin at BS 980 Drag Splice Fitting 13/2001\n\nApplicability: All Model 747 series aircraft.\n\nRequirement: Inspect in accordance with the technical requirements of FAA AD 2001-22-04 Amdt 39-12483.\n\nNote: Boeing Service Bulletins 747-53A2444 Revision 1 and Revision 2 refer.\n\nCompliance: As specified in the Requirement document with a revised effective date of 27 December 2001.\n\nThis amendment becomes effective on 27 December 2001.\n\nBackground: The FAA requires certain inspections to detect and correct fatigue cracking of the fuselage skin adjacent to the BS 980 drag splice fitting. Such cracking could result in reduced structural integrity of the fuselage.\n\nAmendment 1 is issued in response to a new FAA AD which introduces repetitive ultrasonic, high frequency eddy current, and detailed visual inspections in response to reports of fatigue cracking in the fuselage skin and adjacent structure.\n\nThe original issue of this Airworthiness Directive became effective on 2 November 2000.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.002.png)  \n\nDavid Alan Villiers\n\nDelegate of the Civil Aviation Safety Authority 16 November 2001\n\n![](image.001.png)\n\nThe above AD is notified in the Commonwealth of Australia Gazette on 5 December 2001.\n\n  \n\nPage 1 of 1","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 1 replaces the original AD (effective 2 November 2000) by adopting FAA AD 2001-22-04, which introduces repetitive inspections and specific non‑destructive test methods (ultrasonic and high‑frequency eddy‑current) together with detailed visual inspections. The amendment broadens the inspection regimen and adds repetition and new inspection techniques while keeping applicability to all Model 747 series; effective date revised to 27 December 2001."},"complexity_factors":["Cross-reference to FAA AD 2001-22-04 for technical requirements (Requirement) — creates dependency on an external regulatory document.","Wide applicability: 'All Model 747 series aircraft' (Applicability) — large affected population.","Technical inspection methods specified: repetitive ultrasonic, high frequency eddy current, and detailed visual inspections (Background/Requirement) — requires trained staff and equipment.","Compliance timing and revised effective date of 27 December 2001 (Compliance) — creates scheduling and record-keeping obligations.","Revocation and replacement of the original AD (opening paragraph/Background) — administrative update operators must track.","Reference to Boeing Service Bulletins 747-53A2444 Revision 1 and 2 (Note) — operators must consult manufacturer service information."],"plain_english_summary":"This amendment requires operators of all Boeing 747 series aircraft to carry out inspections of the fuselage skin at the BS 980 drag splice fitting by following the technical steps in FAA AD 2001-22-04. CASA revoked the previous AD and set a revised effective date of 27 December 2001. The measure aims to detect fatigue cracking that could reduce fuselage structural integrity by mandating repetitive ultrasonic, high‑frequency eddy‑current and detailed visual inspections."},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This amendment maintains the original scope (inspection of fuselage skin at BS 980 drag splice fitting on Boeing 747 aircraft). The amendment updates the inspection methodology and frequency based on new safety data, but does not expand the directive to cover additional aircraft types, additional structural components, or unrelated safety issues. The scope remains tightly focused on the specific fatigue cracking issue identified in the original 2000 directive."},"complexity_factors":["Very short document (1 page)","Only 4 defined structural elements (BS 980 drag splice fitting, FAA AD 2001-22-04 Amdt 39-12483, Boeing Service Bulletins 747-53A2444 Revisions 1 and 2)","No nested conditional logic or exceptions","Single clear compliance pathway: inspect per FAA directive","Minimal cross-referencing (only to external FAA document and Boeing bulletins)","Straightforward temporal structure: applicability → requirement → compliance → background"],"plain_english_summary":"This safety order revokes the earlier AD and requires all Boeing 747s operating in Australia to undergo specified inspections (ultrasonic, high‑frequency eddy‑current and detailed visual) of the fuselage around the BS 980 drag splice fitting. It replaces one‑time checks with repeated, ongoing inspections after reports of fatigue cracking. Airlines, owners and maintenance crews must comply by the deadlines or the aircraft cannot fly. The measures align Australia’s rules with the FAA and aim to prevent structural failure."},"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-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting","history":"/api/acts/ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting/history","analysis":"/api/acts/ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting/analysis","conflicts":"/api/acts/ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting/conflicts","importantCases":"/api/acts/ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting/important-cases","documents":"/api/acts/ad-b747-235-amdt-1-fuselage-skin-at-bs-980-drag-splice-fitting/documents"}}