{"id":"F2005L00212","name":"AD/F406/11 Amdt 1 - Fuselage to Centre Wing Connection","slug":"ad-f406-11-amdt-1-fuselage-to-centre-wing-connection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":33743,"registerId":"commonwealth-F2005L00212-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Reims Aviation F406 Series Aeroplanes","sectionType":"division","heading":"Reims Aviation F406 Series Aeroplanes","content":"### Reims Aviation F406 Series Aeroplanes\n\n| AD/F406/11 Amdt 1 | Fuselage to Centre Wing Connection | 3/2005 |\n| ----------------- | ---------------------------------- | ------ |\n\n| Applicability: | Model F406 series aircraft, serial numbers 001 through 089, and 091.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Action in accordance with Reims Aviation Industries Service Bulletin Service (SB) No. F406-54 Revision 1, dated 9 November 2004.Note: DGAC AD F-2004-114 R1 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| Compliance:    | If the inspection required by the original issue of the Requirement document has not been accomplished as at the effective date of this Directive, accomplish at the next scheduled 600 hour or 12 month inspection after 7 August 2004, whichever occurs first.If the inspection required by the original issue of the Requirement document has already been accomplished as at the effective date of this Directive, but Modification Kit DDK406-026 material changes specified in Revision 1 of the Requirement document were not incorporated at the time of compliance, accomplish changes at the next scheduled 600 hour or 12 month inspection after 17 March 2005, whichever occurs first.The compliance time for the inspection requirement remains unchanged by this issue. |\n|                | This Amendment becomes effective on 17 March 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| Background:    | Cracks have been discovered on the left and right ribs at the centre wing to fuselage connection at fuselage station FS160.80. Propagation of undetected rib cracks could result in structural failure. Modification action is necessary to facilitate access for the required inspection.Amendment 1 is issued in response to a revision of the related DGAC AD, which introduces a revised Requirement document.                                                                                                                                                                                                                                                                                                                                                                    |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n4 February 2005","sortOrder":0},{"sectionNumber":"AD/F406/11 Amdt 1","sectionType":"part","heading":"AD/F406/11 Amdt 1","content":"## AD/F406/11 Amdt 1","sortOrder":1},{"sectionNumber":"Fuselage to Centre Wing Connection","sectionType":"part","heading":"Fuselage to Centre Wing Connection","content":"## Fuselage to Centre Wing Connection","sortOrder":2},{"sectionNumber":"3/2005","sectionType":"part","heading":"3/2005","content":"## 3/2005","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Amendment 1 replaces the earlier Requirement document with Reims Service Bulletin F406‑54 Revision 1 and sets an effective date, clarifying timing for operators who already complied. It does not broaden the aircraft applicability or add new inspection categories beyond those in the original directive."},"complexity_factors":["Narrow applicability (specific model and serial numbers) reduces scope complexity","Compliance tied to existing maintenance intervals (600‑hour or 12‑month) simplifies scheduling","Requirement references an external Service Bulletin (SB F406‑54 Rev 1) creating a dependency on that document","Amendment updates the required SB rather than introducing new inspection types","Technical nature of inspections/modification requires specialised maintenance skills and potential parts (modification kit DDK406‑026)","Cross-reference to related DGAC AD introduces an inter-jurisdictional compliance link"],"plain_english_summary":"This Airworthiness Directive requires operators of Reims Aviation F406 aeroplanes (serials 001–089 and 091) to carry out the inspection and modification steps set out in Reims Service Bulletin F406-54 Revision 1. The measure responds to discovered cracks where the centre wing connects to the fuselage and aims to improve access and inspection to prevent undetected crack propagation. Operators must perform the work at the next scheduled 600‑hour or 12‑month check; operators pay for compliance and the regulator enforces it."},"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"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is Amendment 1 to an existing Airworthiness Directive. It maintains the original safety purpose (addressing structural cracks at the fuselage-centre wing connection) while updating compliance requirements based on whether operators have already completed the initial inspection. The amendment responds to a revised French aviation authority directive (DGAC AD F-2004-114 R1) and a revised manufacturer service bulletin, but does not expand beyond the original safety concern."},"complexity_factors":["Single, specific mechanical issue (fuselage-wing connection cracks)","Limited applicability (only 90 specific aircraft serial numbers)","Clear two-path compliance structure based on prior inspection status","Only one external reference (manufacturer Service Bulletin F406-54 Rev 1)","No nested definitions or extensive interpretation sections","Straightforward conditional logic (if/then based on prior compliance status)"],"plain_english_summary":"This is an **Airworthiness Directive (AD)** — a mandatory safety order issued by Australia's Civil Aviation Safety Authority (CASA). It applies to specific **Reims Aviation F406 series aircraft** (serial numbers 001-089 and 091).\n\n**What it does:**\n- Requires owners/operators to inspect the connection between the fuselage (the main body of the plane) and the centre wing for cracks in the ribs\n- If cracks are found or certain modifications haven't been done, specific repair or modification work must be carried out following a manufacturer service bulletin\n\n**Why it matters:**\n- Cracks have been discovered in this area on these aircraft types\n- If left undetected, these cracks could spread and cause **structural failure** — potentially catastrophic in flight\n- The directive makes compliance mandatory (not optional) to keep these aircraft airworthy\n\n**Key deadlines:**\n- If you haven't done the initial inspection yet: do it at your next scheduled 600-hour or 12-month inspection after 7 August 2004\n- If you did the inspection but missed certain modifications: do those by your next 600-hour or 12-month inspection after 17 March 2005\n\n**Who must comply:**\n- Anyone operating the affected Reims F406 aircraft in Australia\n- Non-compliance means the aircraft cannot legally fly"}},"importantCases":[],"_links":{"self":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection","history":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection/history","analysis":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection/analysis","conflicts":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection/conflicts","importantCases":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection/important-cases","documents":"/api/acts/ad-f406-11-amdt-1-fuselage-to-centre-wing-connection/documents"}}