{"id":"F2006L02222","name":"AD/F2000/16 - Flight Controls - Trailing Edge Flaps Rotating Rods","slug":"ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":117549,"registerId":"commonwealth-F2006L02222-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Dassault Aviation Falcon 2000 Series Aer","sectionType":"division","heading":"Dassault Aviation Falcon 2000 Series Aeroplanes","content":"### Dassault Aviation Falcon 2000 Series Aeroplanes\n\n| AD/F2000/16 | Flight Controls - Trailing EdgeFlaps Rotating Rods | 8/2006 |\n| ----------- | -------------------------------------------------- | ------ |\n\n```html\n

Applicability:

Falcon 2000 and 2000EX aeroplanes.

Requirement:

1. Verify the correct assembly of the flap rotating rods and associated retaining brackets installed in the LH/RH wing root compartment and in the LH and / or RH main landing gear compartment, as instructed in the respective Dassault Aviation Service Bulletins (SB) listed in table 1 below.

2. If a rod is found damaged, replace this rod in accordance with the respective Dassault Aviation SB given in the table 1 below.

3. Label the rods and associated retaining brackets as instructed in the respective Dassault Aviation SB given in table 1 below.

Table 1

Falcon 2000

Dassault Aviation SB F2000-326 or later DGAC approved revision.

Falcon 2000EX

Dassault Aviation SB F2000EX-83 or later DGAC approved revision.

Note: EASA AD 2006-0115 dated 10 May 2006 refers.

Compliance:

1. Within 330 flight hours or within 7 months from the effective date of this AD, whichever occurs first.

2. Prior to further flight after the effective date of this AD.

3. Within 330 flight hours or within 7 months from the effective date of this AD, whichever occurs first.

This Airworthiness Directive becomes effective on 3 August 2006.

\n```\n\n| Background: | A rotating rod in the trailing edge flap control linkage broke in flight. Investigations revealed that the rotating rod had been installed in the wrong side during maintenance. The incorrect installation of the rod caused contact between the rotating rod and its retaining bracket leading, after some time in operation, to rod breakage and a flap asymmetry situation.Flap asymmetry combined with a latent failure of the asymmetry detection system is classified as a catastrophic failure condition. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n21 June 2006","sortOrder":0},{"sectionNumber":"AD/F2000/16","sectionType":"part","heading":"AD/F2000/16","content":"## AD/F2000/16","sortOrder":1},{"sectionNumber":"Flight Controls - Trailing EdgeFlaps Rot","sectionType":"part","heading":"Flight Controls - Trailing EdgeFlaps Rotating Rods","content":"## Flight Controls - Trailing Edge \nFlaps Rotating Rods","sortOrder":2},{"sectionNumber":"8/2006","sectionType":"part","heading":"8/2006","content":"## 8/2006","sortOrder":3}],"analysis":{"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":3,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific mechanical defect in a specific aircraft type. It has not expanded beyond the original safety issue of incorrect rotating rod installation."},"complexity_factors":["Short, single-purpose directive with only 3 requirements","No defined terms section — uses plain technical language","Simple conditional logic: 'If damaged, replace'","Single cross-reference to European aviation safety regulation (EASA AD 2006-0115) in a non-binding note","Clear compliance deadlines with straightforward alternatives (flight hours OR calendar time)","References external technical documents (Dassault Service Bulletins) but provides specific document numbers in a simple table format"],"plain_english_summary":"This mandatory CASA Airworthiness Directive requires owners/operators of Dassault Falcon 2000 and 2000EX jets to inspect and verify correct assembly of the trailing‑edge flap rotating rods and retaining brackets, replace any damaged rods before the next flight, and label parts to prevent incorrect reinstallation. It addresses a maintenance‑related rod failure that can cause catastrophic flap asymmetry; inspections and labeling are due within 330 flight hours or 7 months from 3 Aug 2006."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD’s scope is consistent with its stated purpose: it targets Falcon 2000 and 2000EX aeroplanes and mandates inspection, replacement and labeling per Dassault Service Bulletins to prevent rod breakage and flap asymmetry. It does not broaden applicability beyond those models or add unrelated requirements; it implements a corrective maintenance regime within specified time limits to address the identified failure mode."},"complexity_factors":["Technical specificity: requires hands-on inspection, possible part replacement and physical labeling of components (operational maintenance complexity).","Cross-references external documents: compliance depends on following specific Dassault Aviation Service Bulletins (DGAC-approved revisions).","Multiple compliance triggers: fixed calendar/flying-hour deadline (330 flight hours or 7 months) and an immediate \"prior to further flight\" obligation if damage is detected.","Safety consequence linkage: corrective action is tied to elimination of a low-probability but high-consequence failure (flap asymmetry), affecting inspection rigour.","Regulatory layering: notes and references to EASA AD and DGAC-approved SBs increase oversight and potential for differing revision controls.","Operational impact: potential grounding or immediate maintenance where damage is found, imposing direct cost on aircraft operators."],"plain_english_summary":"This Airworthiness Directive requires operators of Dassault Falcon 2000 and 2000EX aeroplanes to inspect the assembly of trailing-edge flap rotating rods, replace any damaged rods, and label the rods and retaining brackets in accordance with the listed Dassault Service Bulletins. The Civil Aviation Safety Authority (issued by its delegate) sets mandatory compliance deadlines — inspection and corrective work must be done within 330 flight hours or 7 months, or before further flight if damage is found. The measure addresses a rod-installation error that led to in-flight rod breakage and potential flap asymmetry."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods","history":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods/history","analysis":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods/analysis","conflicts":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods/conflicts","importantCases":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods/important-cases","documents":"/api/acts/ad-f2000-16-flight-controls-trailing-edge-flaps-rotating-rods/documents"}}