{"id":"F2008L00551","name":"AD/PW300/2 - Engine Fan Blade Fracture","slug":"ad-pw300-2-engine-fan-blade-fracture","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":119467,"registerId":"commonwealth-F2008L00551-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Pratt and Whitney Canada Turbine Engines","sectionType":"division","heading":"Pratt and Whitney Canada Turbine Engines - PW300 Series","content":"### Pratt and Whitney Canada Turbine Engines - PW300 Series\n\n| AD/PW300/2 | Engine Fan Blade Fracture | 4/2008 TX |\n| ---------- | ------------------------- | --------- |\n\n| Applicability: | Pratt & Whitney Canada (P&WC) - PW305A and PW305B engines serial numbers:CA0192, CA0195, CA0197, CA0199, CA0200, CA0202, CA0203, CA0204, CA0206, CA0207, CA0208, CA0209, CA0210, CA0211, CA0212, CA0213, CA0214, CA0215, CA0216, CA0217, CA0218, CA0220, CA0221, CA0223, CA0228, CA0231, CA0232, CA0234, CA0235, CA0240, CA0241, CA0243, CA0244, CA0246, CA0247, CA0257, CA0259, CA0260, CA0280, CA0300 fitted with fan blade part number (P/N) 30B2855-01.                                                                                                                                                                                                                                                                                                             |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Inspect the low-pressure compressor fan blades in accordance with Alert Service Bulletin (ASB) No. A24588R2 or later revisions approved by the Chief, Continuing Airworthiness, National Aircraft Certification, Transport Canada.2. Replace any blade that is found to be under-minimum material condition in accordance with Alert Service Bulletin (ASB) No. A24588R2 or later revisions approved by the Chief, Continuing Airworthiness, National Aircraft Certification, Transport Canada.Compliance with earlier versions of ASB No. A28280R2 requirements or incorporation of SB No. 24595, prior to the effective date of this AD satisfies the corrective action requirements of this AD.Note: Transport Canada AD CF-2008-08 dated 30 January 2008 refers. |\n| Compliance:    | 1. For engines with more than 5000 hours of operating time - Before further flight after the effective date of this AD. One repositioning maintenance flight to facilitate the subject inspection may be allowed.For engines with 5000 or less, but more than 4000 hours of operating time - Within 30 hours of operating item but not later than 30 September 2008.For engines with 4000 or less, but more than 2500 hours of operating time - in accordance with one of the following schedules, whichever occurs first.- at the next First Stage High Pressure Compressor Rotor inspection (Ref05-20-00 Scheduled Maintenance Checks), or                                                                                                                            |\n\n|             | - at the next scheduled opportunity where the low-pressure compressor fan is removed, (Ref. Hot Section Inspection or Overhaul Shop Visit), or- within 300 hours of operating time from 24 August 2007.For engines with 2500 or less hours of operating time - Before it accumulates 4000 hours of operating time, but not later than 30 September 2008.2. Before further flight after the effective date of this AD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Airworthiness Directive becomes effective on 22 February 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n| Background: | There have been two incidents of fan blade dislodgements due to blade fracture on relatively hi-time PW305 engines (over 5000 Hrs). The blade dislodgement in both cases was contained. However, engine installations sustained considerable collateral damage. The root cause of fan blade fracture was determined to be the under-minimum material condition at the fracture location.P&WC has established that the subject under-minimum material condition is limited only to fan blades P/N 30B2855-01, manufactured under heat code: MCBWF. Accordingly, P&WC on 24 August 2007 issued Alert Service Bulletin (ASB) No. A24588, requiring, on priority bases, identification and removal of all such discrepant fan blades from service, in accordance with Special Instructions (SI) No.37-2007. ASB No. A24588 was subsequently revised (Rev. 2) on 27 November 2007 to include clarification on the incorporation of another Service Bulletin (SB) No. 24595, on the same subject.Considering the potentially hazardous consequence of possible uncontained dislodgement of discrepant blade and its impact on aircraft safety, this AD is issued to mandate the inspection of the affected engine low-pressure (LP) compressor fan blades in accordance with ASB A24588 requirements. |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n19 February 2008","sortOrder":0},{"sectionNumber":"AD/PW300/2","sectionType":"part","heading":"AD/PW300/2","content":"## AD/PW300/2","sortOrder":1},{"sectionNumber":"Engine Fan Blade Fracture","sectionType":"part","heading":"Engine Fan Blade Fracture","content":"## Engine Fan Blade Fracture","sortOrder":2},{"sectionNumber":"4/2008 TX","sectionType":"part","heading":"4/2008 TX","content":"## 4/2008 TX","sortOrder":3}],"analysis":{"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"},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":false,"description":"The AD confines action to the manufacturer‑identified population: PW305A/B engines with fan blade P/N 30B2855-01 (heat code MCBWF) and the listed serial numbers. It implements the corrective steps in ASB A24588R2 (and accepts prior compliant SB/ASB incorporation) and does not expand applicability beyond the manufacturer/Transport Canada identification."},"complexity_factors":["Narrow technical applicability: specific engine models (PW305A/PW305B), many discrete serial numbers and single blade part number P/N 30B2855-01 (Applicability).","Defect limited by manufacture detail: manufacturer identified under‑minimum material condition tied to heat code MCBWF (Background).","Tiered compliance schedule based on accumulated engine hours with different deadlines (Compliance: >5000 hrs immediate; 4000–5000 hrs within 30 hours; 2500–4000 hrs various triggers; ≤2500 hrs before 4000 hrs or 30 Sep 2008).","Cross‑referenced service documents: mandates inspection/replacement per ASB A24588R2, allows compliance via earlier ASB versions or SB No. 24595 where applicable (Requirement).","Regulatory approval and discretion: later ASB revisions must be approved by the Chief, Continuing Airworthiness, National Aircraft Certification, Transport Canada (Requirement).","Operational exception: limited allowance for one repositioning maintenance flight to enable inspection for engines >5000 hours (Compliance).","Safety consequence framing: issued in response to two incidents of fan blade fracture and contained dislodgement with collateral damage, which justifies urgent action (Background).","Record and implementation burden on operators and maintenance organisations to identify affected serial numbers, schedule inspections within tight windows, and replace non‑conforming blades."],"plain_english_summary":"This Airworthiness Directive orders operators of specific Pratt & Whitney Canada PW305A/B engines (listed serial numbers) fitted with fan blade P/N 30B2855-01 to inspect low‑pressure compressor fan blades per Alert Service Bulletin A24588R2 and to replace any blade that is under minimum material. Deadlines vary by engine hours — engines over 5,000 hours must be inspected before further flight — and compliance follows Transport Canada‑approved service bulletin revisions. Operators pay for inspections and replacements; Transport Canada’s Chief, Continuing Airworthiness approves any later ASB revisions. It responds to blade fractures that caused dislodgements and collateral damage."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a targeted safety directive addressing a specific manufacturing defect in a defined population of engines. The scope remains precisely limited to the identified risk (fan blade P/N 30B2855-01, heat code MCBWF) and does not expand beyond the original safety purpose."},"complexity_factors":["Multiple cascading compliance deadlines based on four distinct operating hour thresholds (5000+, 4000-5000, 2500-4000, under 2500)","Cross-reference to external technical documents (Alert Service Bulletin A24588R2 and Transport Canada AD CF-2008-08) that are not reproduced in the directive itself","Conditional exception allowing one 'repositioning maintenance flight' before compliance for high-time engines","Specific serial number applicability list (40 individual engine serial numbers) rather than a range or pattern","Nested alternative compliance paths for the 2500-4000 hour category (three different triggering events)","Reference to prior compliance with earlier versions of different service bulletins (A28280R2, SB 24595) as satisfying current requirements"],"plain_english_summary":"This AD mandates urgent inspection and, if needed, replacement of certain Pratt & Whitney Canada PW305A/B low‑pressure compressor fan blades (specific serial numbers) after reports of fractures due to under‑minimum material. It affects operators and maintenance organisations and sets near‑term compliance deadlines based on engine hours. Issued to prevent potentially catastrophic engine damage or uncontained failure, the directive adopted a Canadian service bulletin and became mandatory in Australia on 22 February 2008."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pw300-2-engine-fan-blade-fracture","history":"/api/acts/ad-pw300-2-engine-fan-blade-fracture/history","analysis":"/api/acts/ad-pw300-2-engine-fan-blade-fracture/analysis","conflicts":"/api/acts/ad-pw300-2-engine-fan-blade-fracture/conflicts","importantCases":"/api/acts/ad-pw300-2-engine-fan-blade-fracture/important-cases","documents":"/api/acts/ad-pw300-2-engine-fan-blade-fracture/documents"}}