{"id":"F2007L02573","name":"AD/X-TS/8 - Flap Hinge and Flap Hinge Support Bracket","slug":"ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":68277,"registerId":"commonwealth-F2007L02573-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eagle X-TS Series Aeroplanes","sectionType":"division","heading":"Eagle X-TS Series Aeroplanes","content":"### Eagle X-TS Series Aeroplanes\n\n| AD/X-TS/8 | Flap Hinge and Flap HingeSupport Bracket | 10/2007 DM |\n| --------- | ---------------------------------------- | ---------- |\n\n| Applicability: | Model X-TS, X-TS 150 and 150B aircraft.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | Action in accordance with CTRM Aviation Service Bulletin 1126 original issue, or later Malaysia DCA approved revision.Note: Malaysia DCA CAM AD 001-07-2007 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n| Compliance:    | Within 25 flight hours after 15 August 2007, unless already accomplished.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n|                | This Airworthiness Directive becomes effective on 15 August 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| Background:    | A report was received of severe exfoliation corrosion on wing/canard flap hinges, part number 5731D01-16 (middle and outboard hinges) on a Model 150B aircraft; that was detected during a 100-hour inspection. The aircraft had accumulated more than 1,000 flight hours. The corrosion was so severe that the thickness of one of the flap hinges was reduced by 50%, and was not easily detected because the flap hinge is sandwiched between the flap hinge support bracket part number 5731D01-01. Failure of the hinge bracket could result in disintegration of flap canard/wing with consequent loss of control. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n13 August 2007","sortOrder":0},{"sectionNumber":"AD/X-TS/8","sectionType":"part","heading":"AD/X-TS/8","content":"## AD/X-TS/8","sortOrder":1},{"sectionNumber":"Flap Hinge and Flap HingeSupport Bracket","sectionType":"part","heading":"Flap Hinge and Flap HingeSupport Bracket","content":"## Flap Hinge and Flap Hinge  \nSupport Bracket","sortOrder":2},{"sectionNumber":"10/2007 DM","sectionType":"part","heading":"10/2007 DM","content":"## 10/2007 DM","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"},"flash_summary":{"complexity_score":2,"scope_assessment":{"changed":false,"description":"This Airworthiness Directive stays within the original, targeted purpose: address and remediate reported severe corrosion on specific flap hinges/hinge support brackets on the Eagle X‑TS family. It does not widen the affected models, add unrelated measures, or create ongoing surveillance obligations beyond the single required action tied to the CTRM service bulletin. The AD therefore does not materially change scope beyond that original safety focus."},"complexity_factors":["Narrow applicability: only three aircraft models specified (Model X‑TS, X‑TS 150, X‑TS 150B).","Single required action: compliance with CTRM Aviation Service Bulletin 1126 (original issue) or later Malaysia DCA‑approved revision.","One compliance deadline: within 25 flight hours after 15 August 2007.","Few technical details in the AD itself; substantive inspection/repair work is delegated to an external service bulletin (dependency on external document).","Two specific part numbers identified (5731D01‑16 hinge; 5731D01‑01 support bracket).","Short text with minimal conditional logic and no defined‑term section.","Cross‑reference to Malaysia DCA CAM AD 001‑07‑2007 adds one external regulatory cross‑reference."],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- Requires owners/operators of specified Eagle X-TS series aeroplanes to carry out the inspection and any subsequent work described in CTRM Aviation Service Bulletin 1126 (original issue), or in a later revision approved by the Malaysia Directorate General of Civil Aviation (Malaysia DCA).\n- Sets the deadline for compliance at within 25 flight hours after 15 August 2007.\n- Becomes effective on 15 August 2007.\n\n**Who is affected**\n\n- Owners, operators and maintainers of Model X-TS, X-TS 150 and X-TS 150B aircraft.\n\n**Why it matters (stated safety concern and mechanical effect)**\n\n- The directive responds to a report of severe exfoliation corrosion found on flap hinges (part number 5731D01-16) on a Model 150B during a 100‑hour inspection. The corrosion reduced hinge thickness by about 50%.\n- The hinge is located between the flap hinge support bracket (part number 5731D01-01) and the flap, so corrosion can be hidden from visual inspection unless the bracket/hinge assembly is checked as required by the service bulletin.\n- The safety risk identified: a failed hinge or bracket could lead to loss or disintegration of the flap/canard or wing control surfaces, with consequent loss of control of the aircraft.\n\n**Who pays and who decides**\n\n- Aircraft owners/operators pay for the inspection, any removal/disassembly required to expose the hinge, and for any repairs or replacement parts and labour recommended by the CTRM service bulletin.\n- The Civil Aviation Safety Authority (CASA) issued the directive; the detailed work is prescribed by an external CTRM service bulletin and by any later Malaysia DCA–approved revisions of that bulletin.\n\n**What behaviour changes**\n\n- Operators must obtain and follow CTRM Aviation Service Bulletin 1126 (or an approved later revision) and schedule the required inspection/work within the 25 flight‑hour window after the effective date.\n- Maintenance organisations will likely need to disassemble the hinge/bracket area to inspect for hidden corrosion and perform repairs or replacements where corrosion is found.\n\n**Practical implementation notes and trade‑offs**\n\n- The directive is narrowly targeted to three specific models and to specific part numbers (5731D01‑16 hinge, 5731D01‑01 support bracket), so the direct compliance cost is concentrated on operators of those aircraft.\n- Because the corrosion can be hidden between the hinge and the support bracket, inspections may require disassembly rather than a simple visual check; that increases labour time, possible parts replacement costs, and aircraft downtime.\n- The directive ties the mandatory action to an external service bulletin and to approval by a foreign regulator (Malaysia DCA). That creates a dependency: the exact inspection/repair tasks and authorised revisions are determined outside this instrument and can affect cost and scope of work required.\n- The safety benefit (preventing catastrophic control surface failure) is concentrated for aircraft that have corroded hinges; the compliance cost (inspection/repair) is borne by the small fleet of affected aircraft.\n\n**Source claim and short test against costs/incentives**\n\n- The directive’s stated purpose is to eliminate the risk posed by severe hinge corrosion on the specified models (source: background paragraph describing the reported corrosion and consequences).\n- Testing that claim against implementation costs: preventing an uncontained hinge failure requires inspection that may be intrusive; that creates measurable costs (labour, parts, downtime) for the small group of operators affected. The directive reduces the probability of catastrophic failure for those aircraft at the expense of those compliance costs.\n\n(Referenced items: applicability to Model X‑TS, X‑TS 150 and 150B; requirement to follow CTRM Service Bulletin 1126 or later Malaysia DCA‑approved revision; compliance within 25 flight hours after 15 August 2007; part numbers 5731D01‑16 and 5731D01‑01; background on corrosion and safety consequence.)"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard single-issue Airworthiness Directive addressing a specific safety defect in a specific aircraft type. It has not expanded beyond its original purpose of mandating inspection/repair of corroded flap hinges."},"complexity_factors":["Very short document (approximately 250 words)","Only 3 defined aircraft models in applicability","Single compliance action with clear deadline","No nested exceptions or conditional logic","One cross-reference to a service bulletin and a Malaysian aviation directive","Straightforward factual background without legal interpretation sections"],"plain_english_summary":"This CASA Airworthiness Directive orders owners/operators of Eagle X-TS, X-TS 150 and 150B aircraft to inspect and remedy severe exfoliation corrosion found in hidden wing flap hinges (PN 5731D01-16).  \n\nWork must follow CTRM Aviation Service Bulletin 1126 and be completed within 25 flight hours after 15 August 2007 to prevent hinge failure and potential loss of control."}},"importantCases":[],"_links":{"self":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket","history":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket/history","analysis":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket/analysis","conflicts":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket/conflicts","importantCases":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket/important-cases","documents":"/api/acts/ad-x-ts-8-flap-hinge-and-flap-hinge-support-bracket/documents"}}