{"id":"F2009L00894","name":"AD/CAP 10/13 Amdt 1 - Flight Controls Tie Rod Bolts","slug":"ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":78214,"registerId":"commonwealth-F2009L00894-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Avions Mudry Cap Series Aeroplanes","sectionType":"division","heading":"Avions Mudry Cap Series Aeroplanes","content":"### Avions Mudry Cap Series Aeroplanes\n\n| AD/CAP 10/13 Amdt 1 | Flight Controls Tie Rod Bolts | 4/2009 |\n| ------------------- | ----------------------------- | ------ |\n\n| Applicability: | Model CAP 10B aircraft, serial numbers 300 through 317, and CAP 10B aircraft that have embodied APEX change 000302 - carbon fibre wing spars (trademarked asCAP 10C). |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Unless the rods and spacers have already been replaced in accordance with the initial issue of this Directive, inspect tie rod spacers part number 11.56.27.038 for condition in accordance with APEX CAP 10C Maintenance Manual Chapter27-10-00 page 6-3.2. If any damaged spacer is found during any inspection, remove tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038 and replace them by tie rod bolts part number 95.56.11.418 and spacers part number 11.56.27.138, in accordance with the accomplishment instructions of APEX AIRCRAFT Service Bulletin 040206, original issue, or later EASA approved revision.Removal of tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038 and replacement by tie rod bolts part number 95.56.11.418 and spacers part number 11.56.27.138, in accordance with the accomplishment instructions of APEX AIRCRAFT Service Bulletin 040206, original issue, or later EASA approved revision, constitutes terminating action to the requirements of this Directive.After the effective date of this Directive, no person shall install, on any aircraft, tie rod bolts part number 95.56.11.066 and spacers part number 11.56.27.038.Note: EASA AD 2008-0060R1 refers. |\n| Compliance: | 1. Within 50 flight hours after 9 April 2009, and thereafter at intervals not to exceed 50 flight hours; unless the rods and spacers have already been replaced.2. Before further flight. |\n| | This Amendment becomes effective on 9 April 2009. |\n\n| Background: | The manufacturer has determined that the flight controls tie rod bolts currently installed on CAP 10B aircraft are not in accordance with design data. The bolt shank length was found to be too short, and additionally, the material properties of the spacers have been found to be inadequate for the prescribed torque value. Excessive wear on the threads of the bolts could result in play in the flight controls, with consequent control surface vibration which could result in loss of control of the aircraft.Amendment 1 is issued in response to a revision of the related EASA AD, which introduces a repetitive inspection of the spacers, and optional terminating action for replacement of tie rod bolts and spacers by new part number parts. The EASA AD was prompted after investigation of removed spacers revealed no evidence of significant damage. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n24 February 2009","sortOrder":0},{"sectionNumber":"AD/CAP 10/13 Amdt 1","sectionType":"part","heading":"AD/CAP 10/13 Amdt 1","content":"## AD/CAP 10/13 Amdt 1","sortOrder":1},{"sectionNumber":"Flight Controls Tie Rod Bolts","sectionType":"part","heading":"Flight Controls Tie Rod Bolts","content":"## Flight Controls Tie Rod Bolts","sortOrder":2},{"sectionNumber":"4/2009","sectionType":"part","heading":"4/2009","content":"## 4/2009","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":6,"scope_assessment":{"changed":true,"description":"Amendment 1 expands the original directive by introducing a repetitive inspection requirement of tie-rod spacers (every 50 flight hours) and by providing an optional terminating action: removal of the old bolts and spacers and replacement with new part numbers in accordance with APEX Service Bulletin 040206 (original or later EASA‑approved revision). It also imposes a prohibition on reinstalling the old parts and cross‑references EASA AD 2008-0060R1 for related requirements."},"complexity_factors":["Narrow applicability: limited to CAP 10B serial numbers 300–317 and CAP 10B aircraft with APEX change 000302 (CAP 10C) — requires parcelled record checks and fleet identification.","Technical specificity: multiple exact part numbers for old and replacement bolts and spacers (95.56.11.066 → 95.56.11.418; 11.56.27.038 → 11.56.27.138) increase parts-control and procurement complexity.","Repetitive inspection regime: inspections required within 50 flight hours and then every 50 flight hours (Compliance), imposing recurring operational burden and recordkeeping.","Termination pathway: replacement as stated in APEX AIRCRAFT Service Bulletin 040206 (original or later EASA‑approved revision) constitutes terminating action — cross‑reference to external service document and EASA approval required.","Inspection procedure cross‑references: directs inspectors to APEX CAP 10C Maintenance Manual Chapter 27-10-00 page 6-3.2 for condition assessment, requiring access to and use of that maintenance data.","Installation prohibition: after effective date no person may install the old parts, creating a legal restriction on maintenance sourcing and inventory use.","Compliance timing: a specific effective date (9 April 2009) and staged compliance obligations (within 50 flight hours or before further flight) raise scheduling and operational planning issues.","Regulatory cross-links: references EASA AD 2008-0060R1 and requires EASA‑approved revisions of the SB for conforming work, adding certification and approval steps."],"plain_english_summary":"Mandates repeated inspection of specific tie-rod spacers and, if damaged, replacement of bolts and spacers with new part numbers on CAP 10B (S/N 300–317) and CAP 10B aircraft modified with APEX change 000302 (CAP 10C); prohibits reinstalling the old parts. The measure responds to short bolt shanks and spacers with inadequate material properties that can create control play and vibration, and allows replacement as an optional terminating action."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This Amendment 1 remains tightly scoped to the original safety issue (faulty tie rod bolts and spacers on CAP 10B/C aircraft). The amendment introduces repetitive inspections as an alternative to immediate replacement, but this is a refinement of the original safety response rather than scope creep. The instrument maintains its original purpose: preventing control system failures in specific aerobatic aircraft."},"complexity_factors":["Single discrete safety issue with clear mechanical remedy","Only 2 specific aircraft models affected with defined serial number ranges","Straightforward compliance path: either repetitive inspection OR single terminating action","References external technical documents (APEX Maintenance Manual, Service Bulletin, EASA AD) but provides sufficient standalone instruction","Minimal conditional logic — essentially 'inspect unless already replaced' and 'replace if damaged'","No nested definitions, interpretation sections, or complex cross-referencing within the instrument itself"],"plain_english_summary":"Owners and operators of specific Avions Mudry CAP 10B/C aerobatic aircraft must inspect or replace short tie‑rod bolts and inadequate spacers that cause wear, control play, vibration and risk loss of control. \n\nBy 9 April 2009 inspections every 50 flight hours were required unless bolts and spacers were replaced with improved parts (which ends inspections); reinstallation of the old parts is prohibited."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts","history":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts/history","analysis":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts/analysis","conflicts":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts/conflicts","importantCases":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts/important-cases","documents":"/api/acts/ad-cap-10-13-amdt-1-flight-controls-tie-rod-bolts/documents"}}