{"id":"F2006B07197","name":"AD/SWSA226/56 Amdt 3 - Cockpit and Cabin Windows","slug":"ad-swsa226-56-amdt-3-cockpit-and-cabin-windows","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":48907,"registerId":"commonwealth-F2006B07197-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/SWSA226/56 Amdt 3 - Cockpit and Cabin Windows","content":"---\nmeta-content-style-type: text/css\nmeta-content-type: application/xhtml+xml; charset=utf-8\nmeta-generator: Aspose.Words for .NET 22.10.0\n---\n\n?xml version=\"1.0\" encoding=\"utf-8\" standalone=\"no\"?>\n\n \n\n![](image.001.png)  Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes\n\n \n\nAD/SWSA226/56\n\nAmdt 3\n\n\nCockpit and Cabin Windows 1/97\n\n \n\nApplicability: Models SA26-T, SA26-AT, SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227- AT, SA227-AC, SA227-BC, and SA227-TT.\n\n \n\nRequirement: 1. Replace each single pane cockpit side window and then carry out a post installation inspection in accordance with the documents appropriate to the aircraft model and the inspection to be carried out, as listed at Paragraph 4. If cracking is discovered, carry out the action/s specified in the Table at Appendix 1.\n\n \n\n2.    Inspect all acrylic single pane cockpit side windows for cracks in accordance with the documents appropriate to the aircraft model and the inspection to be carried out, as listed at Paragraph 4. If cracking is discovered, carry out the action/s specified in the Table at Appendix 1.\n\n \n\n3.    Visually inspect dual pane cockpit side windows, and all acrylic cabin windows for cracks in accordance with the documents appropriate to the aircraft model and the inspection to be carried out, as listed at Paragraph 4. If cracking is discovered, carry out the action/s specified in the Table at Appendix 2.\n\n \n\n4.    Inspect in accordance with the following document/s as appropriate.\n\n \n\n1. For acrylic cabin windows:\n\n\n \n\n# Models Service Bulletins\n\n \n\nSA26-T and SA26-AT 26-56-20-042, Issued: November 28, 1988, Revised:\n\nFebruary 7, 1991\n\n \n\nSA226-T and SA226-T(B) 226-56-001, Issued: February 2, 1983, Revised:\n\nNovember 26, 1991\n\n \n\nSA226-AT and SA226-TC 226-56-002, Issued: March 3, 1983, Revised:\n\nMay 29, 1992,\n\n \n\nSA227-AT, SA227-AC, and SA227-BC\n\n\n227-56-002, Issued: January 5, 1984, Revised:\n\nMay 29, 1992, and April 1, 1993\n\n \n\nSA227-TT 227-56-001, Issued: February 2, 1983, Revised:\n\nNovember 26, 1991\n\n \n\nb.    For acrylic cockpit side windows:\n\n \n\n# Models Service Bulletins\n\nSA26-T and SA26-AT 26-56-10-038, Issued: October 8, 1984, Revised:\n\nFebruary 7, 1991\n\nSA226-T, SA226-T(B), SA226-AT, and SA226-TC\n\n\n226-56-003, Issued: September 13, 1984, Revised:\n\nNovember 2, 1989\n\nSA227-AT, SA227-AC, SA227-BC, and SA227-TT\n\n\n227-56-003, Issued: September 13, 1984, Revised:\n\nNovember 2, 1989\n\nNote 1: FAA AD 96-20-08 refers.\n\n \n\nNote 2: The repetitive inspections required by this AD are also referenced in the approved Fairchild Airframe Airworthiness Limitations Manual, ST-UN-M001.\n\n \n\nCompliance: 1. Before 5000 hours component time in service, or within 1000 hours time in service whichever occurs last, after the effective date of this Amendment; thereafter at each 5000 hours component time in service.\n\n \n\nThe post installation inspection must be carried out between 10 and 20 hours time in service after each installation.\n\n \n\n2.    As specified in Appendix 1, after the effective date of this Directive.\n\n \n\n3.    As specified in Appendix 2, after the effective date of this Directive. This Directive has effect from 02 January 1997.\n\nBackground:  In-flight failures have been reported overseas, involving injuries. Inspection and replacement of windows will preclude failure with resultant injury to crew members and passengers. Amendment 1 revised the Directive to clarify Applicability and update the FAA AD reference.\n\n \n\nAmendment 2 was issued in response to a new FAA AD which shortened the repetitive inspection interval as a consequence of several acrylic window failures that occurred prior to the previously required inspection interval.\n\n \n\nAmendment 3 introduces a life limit for single pane cockpit side windows and a post installation inspection.\n\n \n\nAmendment 2 of this Airworthiness Directive became effective on 1 December 1993. Amendment 1 of this Airworthiness Directive became effective on 15 June 1989.\n\nThe original issue of this Airworthiness Directive became effective on 26 January 1989.\n\n \n\n| Condition | Initial Action | Repetitive Action |\n| --- | --- | --- |\n| At the effective date. | Inspect at 150 hours TIS after the effective date of this AD | Reinspect at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable condition column entry to determine compliance times if cracks are found. |\n\n \n\n- If cracks are found where the sum total of all cracks is less than4.3 inches in combined length, but where a crack meets or exceeds0.30 inches as specified in the Crack Limitations section of the service information referenced in paragraph 4. of this AD. Accomplish one of the following:1. Prior to further fight, replace the window with a new approved window in accordance with the applicable maintenance manual. Accomplish the corresponding repetitive action:\n\n1. Reinspect initially between 10 and 20 hours TIS after replacing the window to ensure that no damage has occurred after installation, and thereafter at intervals not to exceed 1000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found.or- - - - - - - - - - - - - - - - - -2. Repeat the inspection specified in paragraph 2. of the AD at intervals not to exceed 25 hours TIS or 30 calendar days, whichever occurs first, provided the sum total of all cracks does not exceed 4.3 inches in combined length. Use the “If cracks are found where the sum total of all cracks meets or exceeds 4.3 inches in combined length” conditions column for replacement and inspection times if the cracks found are at that level.\n- or\n- - - - - - - - - - - - - - - - - -\n- 2. Prior to further flight, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot’s clear view close to the pressurisation controls:\n- “AIRPLANE MUST BE OPERATED UNPRESSURISED”,and prior to further flight, insert a copy of this AD into the Limitations Section of the approved Aircraft Flight Manual.\n- If cracks are found where the sum total of all cracks meets or exceeds 4.3 inches in combined length. Prior to further flight, replace the window with an approved new window in accordance with the applicable maintenance manual Reinspect initially between 10 and 20 hours TIS after replacing the window to ensure that no damage has occurred after installation, and thereafter at intervals not to exceed 1000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found.\n\n \n\n- With cracks found that are less than0.30 inches ( as specified in the applicable service information referenced in paragraph 4. of this AD) provided the sum total of all cracks does not exceed 4.3 inches in combined length. Reinspect within 25 hours TIS or 30 calendar days, whichever occurs first. Continue this reinspection at intervals not to exceed 25 hours TIS or 30 calendar days, whichever occurs first, provided no crack is found that is 0.30 inches or greater or the combined length of all cracks exceeds 4.3 inches. Use applicable “Condition” column entry to determine compliance times if any of these crack limits are met.\n- With no cracks found after one of the inspections required by this AD. Reinspection within 1,000 hours TIS or 12 calendar months after the last inspection, whichever occurs first. Reinspect at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found.\n- Condition Initial Action Repetitive Action\n- At the effective date. Inspect at 150 hours TIS after the effective date of the AD, unless already accomplished within the last 1,000 hours TIS or 12 calendar months, which would put aircraft in compliance with the previous issue of this AD. Use the results of the previous inspection under the previous issue to determine repetitive action. Reinspect at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found.For aircraft owners/operators taking “unless already accomplished” credit for results from the previous inspection under the previous issue to determine the repetitive action.\n\n \n\n- If cracks are found where the sum total of all cracks is less than4.3 inches in combined length, but where a crack meets or exceeds.30 inches as specified in the Crack Limitations section of the service information referenced in paragraph 4 of this AD. Accomplish one of the following:\n\n1. Prior to further fight, replace the window with an approved new window in accordance with the applicable maintenance manual. or- - - - - - - - - - - - - - - - - - - - - -2. Prior to further flight, fabricate a placard with the following words in letters at least 0.10 inch in height and install this placard within the pilot’s clear view close to the pressurisation controls: ”AIRCRAFTMUST BE OPERATEDUNPRESSURISED” and prior to further flight, insert a copy of this AD into the Limitations Section of the approved Aircraft Flight Manual (AFM). Accomplish the corresponding repetitive action:\n\n1. Reinspect initially between 10 and 20 hours TIS after replacing the window to ensure that no damage has occurred after installation, and thereafter at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found. or- - - - - - - - - - - - - - - - - - - - - - -2. Repeat the inspection specified in paragraph 3. of this AD at intervals not to exceed 25 hours TIS or 30 calendar days, whichever occurs first, provided the sum total of all cracks does not exceed 4.3 inches in combined length. Use the “ If cracks are found where the sum total of all cracks meets or exceeds4.3 inches in combined length” “Condition” column for replacement and inspection times if the cracks found are at that level.\n- If cracks are found where the sum total of all cracks meets or exceeds 4.3 inches in combined length. Prior to further flight, replace the window with an approved new window in accordance with the applicable maintenance manual. Reinspection initially between 10 and 20 hours TIS after replacing the window to ensure that no damage has occurred after installation, and thereafter at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found.\n\n| With cracks found that are less than<br>.30 inches (as specified in the applicable service information referenced in paragraph 4 of the AD) provided the sum total of all cracks does not exceed 4.3 inches in combined length | Reinspect within 25 hours TIS or 30 calendar days, whichever occurs first. | Continue the reinspection at intervals not to exceed 25 hours TIS or 30 calendar days, whichever occurs first, provided no crack is found that is 0.30 inches or greater, or the combined length of the cracks exceeds 4.3 inches in combined length. Use applicable “Condition” column entry to determine compliance times if any of these crack limits are met. |\n| --- | --- | --- |\n| With no cracks found after one of the inspections required by this AD. | Reinspect within 1,000 hours TIS or12 calendar months after the last inspection, whichever occurs first. | Reinspect at intervals not to exceed 1,000 hours TIS or 12 calendar months, whichever occurs first, provided no cracks are found. Use applicable “Condition” column entry to determine compliance times if cracks are found. |\n\n\n \n","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":8,"scope_assessment":{"changed":true,"description":"Amendment 3 broadened the AD beyond earlier text by imposing an explicit component life limit for single‑pane cockpit side windows (5,000 hours) and by requiring a post‑installation inspection 10–20 hours after any window replacement. Earlier iterations focused on inspection intervals and crack limits; Amendment 3 adds mandatory replacement timing and a specified short‑term post‑install check. Those additions increase the regulation’s effect on maintenance planning, parts procurement and operational availability (introducing a recurring replacement cost and an extra mandatory inspection obligation)."},"complexity_factors":["Multiple aircraft models listed (SA26, SA226, SA227 variants) requiring different service bulletins","Cross‑references to many model‑specific service bulletins in paragraph 4","Multiple inspection categories (single‑pane cockpit, dual‑pane cockpit, acrylic cabin windows) with different actions","Several numerical thresholds and branching rules (single‑crack threshold 0.30 in; combined length 4.3 in)","Several overlapping inspection intervals (10–20 hours post‑install; 25 hours/30 days; 1,000 hours/12 months; 5,000 hours life limit)","Permitted alternative remedies (immediate replacement OR repeat inspections OR placard + AFM limitation) creating conditional compliance paths","References to external documents (FAA AD, Airframe Airworthiness Limitations Manual) that affect compliance timing","Duplicative and partially inconsistent wording in the AD increases interpretive risk (repeated paragraphs and slightly varying phrasing)","Requirement to modify operational limits (install placard and AFM entry) in some cases increases non‑maintenance compliance obligations"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- Applies to Fairchild (Swearingen) SA26 and SA226/SA227 series aeroplanes (specific models listed in the AD).\n- Requires removal/replacement and/or regular inspection of cockpit side windows (single- and dual-pane) and all acrylic cabin windows, using the model-specific service bulletins referenced in paragraph 4 of the AD.\n- Introduces a **life limit** for single‑pane cockpit side windows: they must be replaced before they accumulate 5,000 hours component time in service (or within 1,000 hours TIS after the amendment, whichever is later), and then every 5,000 hours thereafter (see Compliance). A post‑installation inspection is also required between 10 and 20 hours TIS after any replacement.\n- Sets inspection schedules and defect thresholds. Inspections must look for cracks; the AD sets two critical numerical limits used to decide remedial action:\n  - A single crack size threshold of 0.30 inches (≥ 0.30 in triggers more urgent action);\n  - A combined total‑length threshold of 4.3 inches (≥ 4.3 in total combined crack length triggers mandatory replacement before next flight).\n- Provides a choice of remedial measures depending on crack size/total: immediate replacement with reinspection (10–20 hours post‑install) and then routine intervals, OR more frequent repeat inspections (every 25 hours TIS or 30 calendar days) while continuing to operate, OR (in limited cases) grounding pressurisation by installing a cockpit placard and placing the AD in the Aircraft Flight Manual (AFM) limitations section. The placard text required by the AD is: “AIRPLANE MUST BE OPERATED UNPRESSURISED”.\n- Cross‑references model‑specific Fairchild service bulletins for inspection procedures and to the FAA AD and the Airframe Airworthiness Limitations Manual for repetitive inspection entry.\n\n**Who this affects (who pays and who decides)**\n\n- Aircraft owners/operators of the listed Fairchild models must comply. They pay for inspections, potential window replacements, installation of placards and AFM changes, and any operational impacts (downtime, lost revenue if an aeroplane must be grounded or flown unpressurised).\n- Licensed maintenance organisations perform the inspections and replacements under the maintenance manuals/service bulletins referenced by the AD.\n- The operator (or maintenance organisation acting under the operator’s authority) decides which remedial option to use where the AD allows a choice (e.g., replace immediately or operate under more frequent inspections, or install the unpressurised placard where permitted).\n\n**Why the regulator says it matters (and how that claim maps to costs/incentives)**\n\n- The AD states the purpose is to prevent in‑flight window failures that have occurred overseas and have led to injuries. Preventing sudden window failure is the stated safety rationale.\n- Costs and incentives created by the AD:\n  - Direct costs to operators: recurring inspection labour and recordkeeping, purchase and fitment of replacement windows (approved parts), and potential operational losses during replacements or if restricted to unpressurised operation.\n  - Concentrated benefit to maintenance/parts suppliers: predictable demand for approved replacement windows and inspection work.\n  - Operational trade‑off: where interim measures (frequent re‑inspections or an unpressurised placard) are allowed, operators can choose a lower immediate cash cost at the price of higher ongoing inspection cost and potential flight restrictions (operating unpressurised reduces payload/route options and may require different crew procedures).\n  - Potential supply risk: if approved replacement windows are limited in supply, multiple aircraft may face downtime awaiting parts.\n\n**Implementation and compliance friction**\n\n- The AD is prescriptive but cross‑references several model‑specific service bulletins for inspection technique and crack‑measurement standards — operators must obtain and follow the correct bulletin for their model.\n- The AD contains multiple conditional branches (different actions depending on crack size and combined length) and different inspection intervals (25 hours/30 days; 1000 hours/12 months; 5000 hours component life limit), which increases administrative and recordkeeping burden.\n\n**Key mechanics to remember**\n\n- Life limit for single‑pane cockpit side windows: replace by 5,000 hours component time (Compliance section).\n- Post‑installation inspection: 10–20 hours TIS after any window installation.\n- Crack thresholds: 0.30 inches (single crack) and 4.3 inches (combined length) determine whether to replace immediately, to inspect more frequently, or to allow temporary unpressurised operation with placard and AFM amendment.\n- Inspection intervals vary by condition: 25 hours/30 days for close monitoring of minor cracks, or 1,000 hours/12 months when no cracks are found.\n\n(Requirements and compliance timing are specified in the AD under \"Requirement\" paragraphs 1–4 and the \"Compliance\" section; model‑specific procedures are in the service bulletins listed in paragraph 4.)"},"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":7,"scope_assessment":{"changed":true,"description":"The original directive (1989) required inspections only. Amendment 2 (1993) shortened inspection intervals after new failures. Amendment 3 (1997) introduced a hard life limit (replacement required at 5,000 hours) and post-installation inspections, effectively shifting from a 'inspect and monitor' regime to a 'replace and verify' regime with stricter material controls. The scope expanded from reactive inspection to proactive component life limits."},"complexity_factors":["Multiple overlapping compliance timelines based on 'whichever occurs first/last' logic (e.g., 5,000 hours vs 1,000 hours vs calendar months)","Nested conditional logic: crack severity thresholds (0.30 inches vs 4.3 inches total length) trigger different action pathways","Four different aircraft model groups with distinct service bulletin references (8 separate documents referenced)","Dual appendix structure (Appendix 1 for cockpit windows, Appendix 2 for cabin windows) with cross-referenced tables","Amendment history layered throughout (Amendments 1, 2, and 3) creating multiple effective dates and transitional provisions","Alternative compliance paths (replace window OR operate unpressurised with placard) with different subsequent inspection intervals","Defined terms used but not explicitly defined in the text (TIS = Time In Service, assumed knowledge)","Post-installation inspection window (10-20 hours TIS) creates a third temporal dimension beyond initial and repetitive inspections"],"plain_english_summary":"This AD requires owners/operators of specified Fairchild (Swearingen) SA26/SA226/SA227 aircraft to inspect and replace acrylic cockpit and cabin windows to prevent in‑flight window failures. It establishes inspection schedules, mandates replacement of single‑pane cockpit side windows, and prescribes actions when cracks are found.\n\nIt affects the listed SA26/SA226/SA227 models and responds to overseas incidents of acrylic window cracking and failure that caused injuries and risked decompression."}},"importantCases":[],"_links":{"self":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows","history":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows/history","analysis":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows/analysis","conflicts":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows/conflicts","importantCases":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows/important-cases","documents":"/api/acts/ad-swsa226-56-amdt-3-cockpit-and-cabin-windows/documents"}}