{"id":"F2006L02253","name":"AD/AMD 50/35 - Flight Controls - Trailing Edge Flaps Rotating Rods","slug":"ad-amd-50-35-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":117579,"registerId":"commonwealth-F2006L02253-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AMD Falcon 50 and 900 Series Aeroplanes","sectionType":"division","heading":"AMD Falcon 50 and 900 Series Aeroplanes","content":"### AMD Falcon 50 and 900 Series Aeroplanes\n\n| AD/AMD 50/35 | Flight Controls - Trailing EdgeFlaps Rotating Rods | 8/2006 |\n| ------------ | -------------------------------------------------- | ------ |\n\n```html\n

Applicability:

Mystere Falcon 50, Mystere Falcon 900 and Falcon 900EX 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

Mystere Falcon 50

Dassault Aviation SB F50-468 or later DGAC approved revision.

Mystere Falcon 900

Dassault Aviation SB F900-367 or later DGAC approved revision.

Falcon 900EX

Dassault Aviation SB F900EX-269 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/AMD 50/35","sectionType":"part","heading":"AD/AMD 50/35","content":"## AD/AMD 50/35","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":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard single-issue Airworthiness Directive addressing a specific mechanical defect. It has not expanded beyond its original purpose of mandating inspection and correction of trailing edge flap rotating rods on the specified aircraft types."},"complexity_factors":["Short, single-purpose directive with only 3 numbered requirements","No defined terms section — uses plain technical language","Simple conditional logic: only one 'if' condition (if damaged, replace)","Cross-references limited to 3 specific Dassault Service Bulletins (SBs) listed in a single table","Compliance deadlines are straightforward time/flight hour alternatives","No nested exceptions or layered conditional provisions","Background section provides clear safety rationale without legal complexity"],"plain_english_summary":"This AD mandates owners/operators of certain Dassault Falcon 50/900/900EX jets in Australia to inspect, correct, and label the wing flap rotating rods and brackets after discovery that incorrect assembly can cause rod failure and dangerous flap asymmetry. \n\nIt’s compulsory because a failed rod (combined with an unnoticed warning-system fault) could lead to loss of control; affected aircraft must be checked and any damaged parts replaced before further flight."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The AD targets a specific hardware installation/failure mode for defined Falcon models and mandates inspection, replacement and labelling per Dassault SBs. It does not expand applicability beyond the listed aircraft or introduce new regulatory powers; it operationalises corrective work and timelines tied to the SBs (Applicability; Requirement 1–3; Compliance 1–3)."},"complexity_factors":["Relies on external manufacturer Service Bulletins (Dassault SB F50-468, F900-367, F900EX-269) and DGAC-approved revisions (Table 1) rather than fully self-contained instructions","Multiple required actions: verify assembly, replace damaged parts, and label components (Requirement 1–3)","Time-limited compliance with two parallel triggers: 330 flight hours or 7 months, and some actions required prior to further flight (Compliance 1–3)","Applies across three aircraft models with potentially different compartment locations (wing root and main landing gear compartments)","Potential logistical and parts-cost burdens on operators/maintenance organisations (implied by Requirement and Compliance)","Cross-reference to EASA AD and DGAC approvals introduces multi-jurisdictional dependency (Note/Background)"],"plain_english_summary":"Treats a known failure mode on Mystere Falcon 50, Falcon 900 and Falcon 900EX: operators must inspect flap rotating rods, replace any damaged rods, and label parts in accordance with Dassault Service Bulletins (Requirement 1–3; Table 1). Compliance deadlines are within 330 flight hours or 7 months, with some actions required before further flight (Compliance 1–3). The measure aims to prevent rod breakage that can cause flap asymmetry (Background). The aircraft operator/maintenance organisation bears the inspection, repair and labelling costs and must follow DGAC‑approved SB revisions."},"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-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods","history":"/api/acts/ad-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods/history","analysis":"/api/acts/ad-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods/analysis","conflicts":"/api/acts/ad-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods/conflicts","importantCases":"/api/acts/ad-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods/important-cases","documents":"/api/acts/ad-amd-50-35-flight-controls-trailing-edge-flaps-rotating-rods/documents"}}