{"id":"F2007L01353","name":"AD/TB10/18 Amdt 2 - Cabin Door Catch","slug":"ad-tb10-18-amdt-2-cabin-door-catch","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":65609,"registerId":"commonwealth-F2007L01353-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Aerospatiale (Socata) TB9 and TB10 (Toba","sectionType":"division","heading":"Aerospatiale (Socata) TB9 and TB10 (Tobago) Series Aeroplanes","content":"### Aerospatiale (Socata) TB9 and TB10 (Tobago) Series Aeroplanes\n\n| AD/TB10/18 Amdt 2 | Cabin Door Catch | 6/2007 |\n| ----------------- | ---------------- | ------ |\n\n| Applicability: | Model TB 9 and TB 10 aircraft, all serial numbers, equipped with cabin access door hooks made of aluminium alloy.                                                                                                                                                                                                                                                                                                  |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | 1. Check aluminium alloy cabin access door hooks for cracks in accordance with the Accomplishment Instructions of EASA SOCATA Service Bulletin No.10-058 Amdt 2.2. Remove and discard AU4G aluminium alloy cabin access door hooks and replace them with part number TB 10 250 72 101 steel hooks.Note: EASA AD 2007-0101 refers.                                                                                  |\n| Compliance:    | 1. At the next scheduled 100 hour inspection or annual inspection after 7 June 2007, whichever occurs first. Inspect thereafter at intervals not to exceed 110 flight hours; until alloy hooks are replaced with part number TB 10 250 72 101 steel hooks.2. Upon the accumulation of 1,500 hours time in service of the alloy hooks, or by 31 December 2011, whichever occurs first; unless already accomplished. |\n|                | This Amendment becomes effective on 7 June 2007.                                                                                                                                                                                                                                                                                                                                                                   |\n| Background:    | Instances of cracked catches on cabin access doors have been attributed to incorrect adjustment. This condition may result in failure of the door catch and a cabin door opening in flight.Amendment 1 provided for additional part number replacement catches.                                                                                                                                                    |\n\n|     | Amendment 2 is issued in response to a new EASA AD, which limits applicability to aircraft equipped with alloy cabin access door hooks, and requires eventual replacement of the alloy hooks with part number TB 10 250 72 101 steel hooks. |\n| --- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n24 April 2007","sortOrder":0},{"sectionNumber":"AD/TB10/18 Amdt 2","sectionType":"part","heading":"AD/TB10/18 Amdt 2","content":"## AD/TB10/18 Amdt 2","sortOrder":1},{"sectionNumber":"Cabin Door Catch","sectionType":"part","heading":"Cabin Door Catch","content":"## Cabin Door Catch","sortOrder":2},{"sectionNumber":"6/2007","sectionType":"part","heading":"6/2007","content":"## 6/2007","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 2 narrows the AD’s applicability to only those TB9 and TB10 aircraft equipped with aluminium alloy cabin access door hooks, where previous versions evidently covered a broader set of part numbers or hook types. It also adds a mandatory eventual replacement requirement (replace alloy hooks with a specified steel part), increasing regulatory effect from periodic inspection alone to an inspection‑plus‑compulsory replacement regime. In short: the amendment focuses the population affected (only alloy‑hook aircraft) while expanding obligations for that population by mandating eventual part replacement."},"complexity_factors":["Single aircraft type family (TB9/TB10) and single equipment feature (cabin door hooks)","Narrow applicability: only aircraft equipped with aluminium alloy (AU4G) hooks","Two main compliance paths: recurring inspections every 110 flight hours until replacement, and mandatory replacement at 1,500 hours TIS or by a calendar date","Clear part number specified for replacement (TB 10 250 72 101)","Cross‑references to EASA Service Bulletin and EASA AD for inspection details","Short document with few conditional layers or nested exceptions"],"plain_english_summary":"**What this AD does (in plain English)**\n\n- This airworthiness direction (AD) applies to Aerospatiale (Socata) TB9 and TB10 (Tobago) aeroplanes that have cabin access door hooks made of aluminium alloy.\n\n- It requires operators to inspect those aluminium alloy cabin door hooks for cracks at the next scheduled 100‑hour inspection or annual inspection (whichever comes first), and then at intervals not to exceed 110 flight hours until the alloy hooks are replaced with steel hooks (part number TB 10 250 72 101).\n\n- It also requires the alloy hooks to be removed and discarded and replaced with the specified steel hooks either when the alloy hooks reach 1,500 hours time‑in‑service or by 31 December 2011, whichever occurs first, unless the replacement has already been done.\n\n- The AD becomes effective 7 June 2007 and cross‑refers to EASA SOCATA Service Bulletin No.10‑058 Amdt 2.2 and EASA AD 2007‑0101 for the inspection and replacement instructions.\n\n**Who is affected**\n\n- Aircraft owners and operators of TB9 and TB10 aeroplanes fitted with aluminium alloy cabin access door hooks.\n- Maintenance organisations and engineers who perform the inspections and part replacements.\n\n**Why it matters (stated purpose and practical effect)**\n\n- The AD is issued because cracked door catches—attributed to incorrect adjustment—may lead to door catch failure and a cabin door opening in flight. The stated purpose is to detect cracked alloy hooks early and to replace them with steel hooks that aren’t subject to the same cracking issue.\n\n**How it works mechanically (who pays, who decides, what behaviour changes)**\n\n- Who pays: aircraft owners/operators must pay for the additional inspections and for purchasing and fitting the steel replacement hooks.\n- Who decides: maintenance providers perform the inspections and decide whether a hook is cracked; operators schedule inspections to meet the AD timelines. CASA enforces compliance with the AD.\n- Behaviour changes required: operators must bring forward the next 100‑hour or annual inspection if necessary, conduct recurring inspections every 110 flight hours until replacement, and plan for replacement of alloy hooks by the time limit (1,500 hours TIS or 31/12/2011).\n\n**Implementation details and compliance mechanics**\n\n- Inspect alloy hooks for cracks in accordance with the Accomplishment Instructions of EASA SOCATA Service Bulletin No.10‑058 Amdt 2.2.\n- If alloy hooks are present, remove and discard AU4G alloy hooks and fit steel hooks part number TB 10 250 72 101.\n- Inspection interval: at the next scheduled 100‑hour or annual inspection after 7 June 2007 (whichever is sooner), then every 110 flight hours until the alloy hooks have been replaced.\n- Mandatory replacement deadline: when alloy hooks accumulate 1,500 hours time‑in‑service or by 31 December 2011, whichever is earlier.\n\n**Trade‑offs, risks and implementation considerations**\n\n- Direct costs: parts and labour to replace hooks; possible short‑term scheduling/downtime when replacements are fitted at or before the next inspection.\n- Timing risk: operators must track hook time‑in‑service precisely to determine the 1,500‑hour replacement point; mis‑tracking could lead to non‑compliance or safety risk.\n- Supply/availability risk: if many aircraft require the same steel hook part within a short window, parts lead times could delay compliance.\n- Inspection sensitivity: detection of small or developing cracks depends on inspection quality; inconsistent inspection standards increase residual risk until replacement is completed.\n- Enforcement and records: operators will need to record inspections and replacement to demonstrate compliance to CASA.\n\n**Source attribution and limits**\n\n- The AD cites EASA SOCATA Service Bulletin No.10‑058 Amdt 2.2 and EASA AD 2007‑0101 for the detailed inspection method and replacement instructions. The AD text states the safety rationale (risk of door opening in flight) and implements inspection and replacement controls to mitigate that risk."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":true,"description":"The original directive likely required only periodic inspections of the door hooks. Amendment 2 significantly expands the scope by mandating complete replacement of all aluminium alloy hooks with steel ones by a hard deadline (31 December 2011 or 1,500 hours), effectively phasing out the problematic part entirely rather than managing risk through ongoing inspection."},"complexity_factors":["Single, clearly defined applicability (two specific aircraft models with specific part material)","Two straightforward compliance requirements with clear deadlines","Only one technical reference to an external service bulletin (EASA SOCATA SB No.10-058 Amdt 2)","Minimal conditional logic (simple 'whichever occurs first' timing clauses)","No defined terms section or extensive cross-referencing","Short document (approximately 300 words of substantive content)"],"plain_english_summary":"This AD mandates owners/operators of Socata TB9/TB10 aircraft with aluminium cabin-door hooks to inspect for cracks at the next routine check after 7 June 2007 and every 110 flight hours until the hooks are replaced.  \n\nIt requires removal of aluminium hooks and installation of steel hooks (TB 10 250 72 101) by 1,500 flight hours or by 31 December 2011. Amendment 2 moves from ongoing inspections to mandatory replacement due to crack-related in‑flight door‑opening risk."}},"importantCases":[],"_links":{"self":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch","history":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch/history","analysis":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch/analysis","conflicts":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch/conflicts","importantCases":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch/important-cases","documents":"/api/acts/ad-tb10-18-amdt-2-cabin-door-catch/documents"}}