{"id":"F2006L01056","name":"AD/X-TS/5 Amdt 2 - Flap Hinge Support Bracket","slug":"ad-x-ts-5-amdt-2-flap-hinge-support-bracket","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":58356,"registerId":"commonwealth-F2006L01056-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/5 Amdt 2 | Flap Hinge Support Bracket | 5/2006 |\n| ---------------- | -------------------------- | ------ |\n\n| Applicability: | All Model X-TS, X-TS 150 and 150B Aircraft.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Perform a visual inspection of the canard starboard inboard flap hinge support brackets p/n: 5731D01-05 and the canard port inboard flap hinge support brackets p/n: 5731D01-02 for cracking, according to the following procedure:1. Visually inspect the gusset weld area for cracks. See figure 1 for the typical crack location. If there is any cracked, lifted or missing paint in the area of the weld, or a crack is suspected, then perform a further detailed inspection in accordance with requirement 2.2. (a) Remove paint in the weld area shown in figure 1.(b) Visually inspect the weld area for cracks using a bright light and magnifying glass.(c) If doubt still exists as to whether a crack is present, confirm using Fluorescent Penetrant Inspection (FPI).(d) If the bracket is cracked, repair or replace the cracked bracket. Any repairs must be in accordance with manufacturer’s instructions or a repair scheme approved by a CAR 35 Authorised Person.Embodiment of Eagle Aircraft (M) Sdn. Bhd. Service Bulletin 1120 Original or later approved issue is terminating action for the requirements of this AD.Note: Malaysian DCA Airworthiness Directive CAM AD 001-01-2004 R1, issued23 December 2005, and Eagle Aircraft S/B 1109 issued 29 August 2003 refer. Service Bulletin 1109 contains an inspection report form, which must be completed and returned to Eagle Aircraft, if any cracks are found. |\n\n|             | Figure 1: Inspection Location                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Compliance: | 1. At each daily inspection of the aircraft.2. Before further flight.This directive shall be entered on the maintenance release as maintenance required. The required visual inspection per Requirement 1 may be performed and certified by a Pilot in Command who has been trained to do the inspection by an appropriately qualified person.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n|             | This Amendment becomes effective on 11 May 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     |\n| Background: | A defect was reported where an inner flap attachment bracket was found cracked along the gusset weld line. Failure of this bracket may result in asymmetric flap deployment and/or inability to lower or raise the flaps. A failure of this type would most probably result in loss of control, with catastrophic consequences.Amendment 1 was issued to reference the Malaysian AD that was raised to reflect the requirements of the original issue of this AD. There was no change to the requirements or compliance, other than clarification of part numbers.Amendment 2 is issued in response to a revision of the related DCA AD, which introduces an optional modification as terminating action for the repetitive inspections required by this Directive.The original issue of this AD became effective on 2 October 2003. |\n\n![](image.010.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n29 March 2006","sortOrder":0},{"sectionNumber":"AD/X-TS/5 Amdt 2","sectionType":"part","heading":"AD/X-TS/5 Amdt 2","content":"## AD/X-TS/5 Amdt 2","sortOrder":1},{"sectionNumber":"Flap Hinge Support Bracket","sectionType":"part","heading":"Flap Hinge Support Bracket","content":"## Flap Hinge Support Bracket","sortOrder":2},{"sectionNumber":"5/2006","sectionType":"part","heading":"5/2006","content":"## 5/2006","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is Amendment 2 of an existing Airworthiness Directive. The amendments have remained tightly focused on the original safety issue (flap hinge bracket cracking). Amendment 1 merely added references and clarified part numbers. Amendment 2 adds an optional modification as terminating action. The scope has not expanded beyond the specific mechanical defect and affected aircraft models originally identified."},"complexity_factors":["Single specific mechanical defect addressed with clear sequential steps","Only 2 part numbers specified (5731D01-05 and 5731D01-02)","Straightforward conditional logic: visual check → detailed inspection → FPI → repair/replace","One terminating action clearly identified (Service Bulletin 1120)","Cross-references to 2 external documents (Malaysian DCA AD and Service Bulletin 1109) but these are informational rather than operational dependencies","No nested definitions or interpretation sections","Practical compliance timeline: 'at each daily inspection' and 'before further flight' are simple trigger conditions"],"plain_english_summary":"This AD mandates inspections of the canard flap-hinge support brackets on Eagle X-TS, X-TS 150 and X-TS 150B aeroplanes after an in-service crack was found; owners and operators must check for cracking and repair or replace suspected parts to prevent flap failure and loss of control.  \n\nDaily visual checks may be performed by a trained Pilot‑in‑Command; detailed inspection, repair, or installation of Service Bulletin 1120 (which terminates the checks) requires appropriate maintenance approval."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Amendment 2 did not broaden the directive's applicability or create new mandatory inspection targets. It introduced an optional terminating modification (Service Bulletin 1120) consistent with the directive's original safety goal (addressing cracked flap hinge brackets) and otherwise clarified cross-references and part numbers. The core scope—inspecting and fixing the specified brackets on the listed aircraft models—remains unchanged."},"complexity_factors":["Single-safety-issue focus (one component: canard inboard flap hinge support brackets)","Two part numbers specified (p/n 5731D01-05 and p/n 5731D01-02)","One main requirement with four escalating inspection steps (visual, paint removal, magnifier/light, FPI)","Option for terminating action via Service Bulletin 1120 (cross-reference to manufacturer's SB)","Cross-references to Malaysian DCA AD and another manufacturer Service Bulletin (1109) containing report form","Permission for a trained Pilot in Command to perform and certify the visual inspection (non-standard certificant)","Repair requirement constrained by CAR 35 authorised person approval","Compliance timing specified (each daily inspection and before further flight) and a maintenance-release logging requirement"],"plain_english_summary":"**What this directive does (mechanical change)\n\n- Requires owners/operators of all Eagle X-TS, X-TS 150 and 150B aeroplanes to inspect specific canard inboard flap hinge support brackets (starboard p/n 5731D01-05 and port p/n 5731D01-02) for cracking. The inspection follows a stepped procedure: a basic visual check of the gusset weld area; if paint is cracked, lifted or a crack is suspected, removal of paint and closer visual inspection with bright light and magnifier; use of Fluorescent Penetrant Inspection (FPI) if doubt remains; and repair or replacement of any cracked bracket in accordance with the manufacturer or a CAR 35 authorised repair scheme. (Requirement)\n\n- Allows the embodiment (installation) of Eagle Aircraft Service Bulletin 1120 (original or later approved issue) as a terminating action — i.e. doing that modification removes the need for further repetitive inspections under this directive. The directive also refers to Service Bulletin 1109, which contains an inspection-report form to be returned to the manufacturer if cracks are found. (Terminating action / Notes)\n\n- Sets the inspection frequency: perform the visual check at each daily inspection of the aircraft and before further flight. The inspection must be recorded on the maintenance release. A Pilot in Command may perform and certify the required visual inspection if they have been trained by an appropriately qualified person. (Compliance)\n\n- Repairs must follow manufacturer instructions or a repair scheme approved by a CAR 35 Authorised Person. (Requirement)\n\nWhy it matters\n\n- The directive responds to a reported cracked inner flap attachment bracket. Failure of this bracket could cause asymmetric or failed flap deployment, which may lead to loss of control. The directive therefore establishes a routine inspection and a repair/replace pathway to reduce that safety risk. (Background)\n\nWho it affects and who pays\n\n- Directly affects owners/operators of all Eagle X-TS, X-TS 150 and 150B aircraft, and maintenance organisations that service them. Owners/operators pay for recurring inspections, paint removal, FPI where needed, and any repairs or replacement parts. If operators choose the terminating modification (Service Bulletin 1120), they pay the one-off modification cost but avoid the ongoing inspection burden. Maintenance organisations and CAR 35 authorised persons decide on repair schemes and perform certified repairs.\n\nPractical effects, incentives and trade-offs\n\n- Behavioural change: operators must add the inspection to pre-flight/daily routines, remove paint and escalate to FPI when suspicion exists, and lodge defects and repairs on the maintenance release. Some operators may prefer the one-off terminating modification to avoid repetitive inspections and reduce ongoing labour costs and aircraft downtime.\n\n- Cost and downtime: frequent inspections impose recurring labour costs and potential aircraft downtime (especially when paint removal and FPI are needed). Repair or replacement of brackets and the terminating modification are additional cost options. Availability of parts and qualified repair approval (CAR 35) may affect repair timing.\n\n- Compliance burden mitigation: the directive permits a trained Pilot in Command to perform and certify the visual inspection, which can lower maintenance labour costs and reduce dependency on maintenance workshops for the basic check, but shifts the responsibility for accurate inspection to the operator/pilot and requires training.\n\n- Detection and implementation risks: the effectiveness depends on correct inspection technique, quality of FPI where used, and timely repairs. False positives or marginal findings may increase costs; missed cracks increase safety risk.\n\nCross-references and administrative notes\n\n- The directive cross-references Malaysian DCA AD CAM AD 001-01-2004 R1 and Eagle service bulletins (1109 and 1120). SB1109 includes a reporting form that must be returned to Eagle if cracks are found. The directive must be recorded on the maintenance release and became effective on 11 May 2006. (Background / Notes)\n\nSummary statement\n\n- Mechanically, this airworthiness directive mandates routine inspections of two canard inboard flap hinge brackets on specified Eagle X-TS series aircraft, prescribes escalation steps for suspected cracking (paint removal, magnified inspection, FPI), requires repair/replacement under approved procedures, allows a particular service bulletin as terminating action, and permits trained pilots to perform the basic visual check. It shifts recurring monitoring costs to operators while offering a one‑time modification as an alternative to ongoing inspections."},"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-x-ts-5-amdt-2-flap-hinge-support-bracket","history":"/api/acts/ad-x-ts-5-amdt-2-flap-hinge-support-bracket/history","analysis":"/api/acts/ad-x-ts-5-amdt-2-flap-hinge-support-bracket/analysis","conflicts":"/api/acts/ad-x-ts-5-amdt-2-flap-hinge-support-bracket/conflicts","importantCases":"/api/acts/ad-x-ts-5-amdt-2-flap-hinge-support-bracket/important-cases","documents":"/api/acts/ad-x-ts-5-amdt-2-flap-hinge-support-bracket/documents"}}