{"id":"F2006L01572","name":"AD/PHS/23 - Blade Spar Corrosion","slug":"ad-phs-23-blade-spar-corrosion","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":59255,"registerId":"commonwealth-F2006L01572-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Propellers - Variable Pitch - Hamilton S","sectionType":"division","heading":"Propellers - Variable Pitch - Hamilton Standard","content":"### Propellers - Variable Pitch - Hamilton Standard\n\n| AD/PHS/23 | Blade Spar Corrosion | 7/2006 TX |\n| --------- | -------------------- | --------- |\n\n| Applicability: | Hamilton Sundstrand (formerly Hamilton Standard Division) model 14RF-9 propellers with propeller blades of the \"+E'' repair configuration (excludes \"+E2'' repair configuration) having serial numbers (SNs) below 885751.Note 1: These propellers are installed on, but not limited to, Embraer 120 aeroplanes.Note 2: The \"+E'' blade marking can be found on the blade airfoil or stamped on the blade shank, adjacent to the blade and pin assembly part number.Note 3: If the blade is stamped with \"+E2'' no further action is required.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Initial Inspection of Installed Blades Not Previously InspectedFor installed blades not previously inspected using Hamilton Sundstrand Alert Service Bulletin (ASB) No. 14RF-9-61-A143, dated 21 November 2005; or Revision 1, dated 5 December 2005; or ASB No. 14RF-9-61-A144, dated27 February 2006; or ASB No. 14RF-9-61-A145, dated 13 April 2006; or ASB No. 14RF-9-61-146, dated 3 April 2006, perform initial visual, feeler gage, and tap test inspections for delamination in accordance with paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No.14RF-9-61-A145.2. 2nd Inspection of Installed BladesFor installed blades that have not been reinspected using Hamilton Sundstrand ASB No. 14RF-9-61-A143 original issue or Revision 1; or ASB No.14RF-9-61-A144; or ASB No. 14RF-9-61-A145; or ASB No. 14RF-9-61-A146, perform a 2nd inspection of installed blades for delamination in accordance with paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF-9-61-A145. |\n\n|             | 3. Blades Placed in Service After the Effective Date of This ADFor blades being installed after the effective date of this AD that were not previously inspected using Hamilton Sundstrand ASB No. 14RF-9-61-A143 original issue or Revision 1; or ASB No. 14RF-9-61-A144; or ASB No.14RF-9-61-A145, do the following:(a) Perform initial visual, feeler gage, and tap test inspections for delamination in accordance with paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No. 14RF- 9-61-A146.(b) Perform a 2nd inspection for delamination in accordance with paragraph 3 of the Accomplishment Instructions of Hamilton Sundstrand ASB No.14RF-9-61-A146.4. Blades That Fail InspectionRemove propeller blades from service that fail inspection.5. Blade Removal From ServiceRemove from service all blades of the \"+E'' repair configuration having SNs below 885751.6. \"+E'' repair configuration having SNs below 885751.Do not install any blades of the \"+E'' repair configuration having SNs below 885751, onto any propeller.Note 4: Hamilton Sundstrand ASB No. 14RF-9-61-A147, dated 19 April 2006, contains information on upgrading the removed blades to the \"+E2'' repair configuration.7. Inspection Reporting RequirementRecord the inspection data on a copy of the data sheet. The data sheet is on page 10 of ASB No. 14RF-9-61-A145 and ASB No. 14RF-9-61-A146. Report the inspection data to Hamilton Sundstrand, fax 0011-1-800-654-5107, and CASA via the SDR reporting system.Note 5: FAA AD 2006-10-07 Amdt 39-14591 refers. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | 1. Within 10 flight cycles or 5 days after the effective date of this AD, whichever occurs first.2. After accumulating an additional 500 flight cycles or by 1 July 2006, whichever occurs first, after the effective date of this AD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              |\n\n|             | 3. (a) Before installing the blade.3. (b) At least 7 days after installing the blade, but no later than 60 days after the initial inspection.4. Before further flight, after the effective date of this AD.5. By 1 March 2007.6. After 1 March 2007.7. Within 10 days after each blade inspection, unless previously accomplished. |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Airworthiness Directive becomes effective on 25 May 2006.                                                                                                                                                                                                                                                                     |\n| Background: | This AD results from reports of delaminated blade fibreglass repair patches that allowed corrosion to form on the aluminium blade spar under the patch. The requirements of this AD are to prevent blade failure that could result in separation of a propeller blade and loss of control of the aeroplane.                        |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n22 May 2006","sortOrder":0},{"sectionNumber":"AD/PHS/23","sectionType":"part","heading":"AD/PHS/23","content":"## AD/PHS/23","sortOrder":1},{"sectionNumber":"Blade Spar Corrosion","sectionType":"part","heading":"Blade Spar Corrosion","content":"## Blade Spar Corrosion","sortOrder":2},{"sectionNumber":"7/2006 TX","sectionType":"part","heading":"7/2006 TX","content":"## 7/2006 TX","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"This AD converts what had been manufacturer-repair guidance and incident reports into mandatory regulatory requirements for \"+E\" blades with SNs below 885751: operators must inspect, report, remove failing blades, and cease installing those blades. The instrument narrows applicability to a defined subset of blades (excludes \"+E2\") and imposes staged compliance deadlines and a prohibition on future installation, thereby expanding enforceable obligations on operators/owners compared with prior non-mandatory service bulletin guidance."},"complexity_factors":["Multiple referenced Alert Service Bulletins (ASB Nos. 14RF-9-61-A143, -A144, -A145, -A146, -A147) with different dates and revisions, creating conditional applicability depending on which ASB was used for prior inspections.","Serial-number and repair-configuration specificity: applies only to \"+E\" repair configuration blades with SNs below 885751; \"+E2\" blades are excluded.","Staged inspection regime: initial inspection, a 2nd inspection, and separate rules for blades installed after the AD’s effective date, each with different timing triggers.","Short compliance windows for some actions (e.g. initial inspection within 10 flight cycles or 5 days), increasing operational pressure on operators.","Mandatory removal from service and a prohibition on reinstalling affected blades after specified dates, which imposes parts/asset retirement costs.","Mandatory reporting of inspection data to Hamilton Sundstrand (fax) and CASA via the SDR system, increasing administrative burden.","Reference to upgrade path via ASB A147 and cross-reference to FAA AD 2006-10-07, creating inter-jurisdictional compliance considerations.","Specified inspection techniques (visual, feeler gauge, tap test) require technical competence and may produce subjective outcomes."],"plain_english_summary":"This Airworthiness Directive requires operators of Hamilton Sundstrand 14RF-9 propellers with \"+E\" repaired blades (serial numbers below 885751) to inspect for delamination/corrosion, remove blades that fail, and stop installing affected blades. The stated purpose is to prevent blade failure from corrosion under delaminated repair patches.\n\nCASA mandates inspections per Hamilton Sundstrand Alert Service Bulletins, sets short staged deadlines, and requires reporting to Hamilton Sundstrand and CASA. Operators/owners pay for inspections, removals or upgrades and must change maintenance and installation practices accordingly."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific corrosion risk in a defined population of propeller blades. The various inspection tiers and deadlines represent standard phased compliance approaches for aviation safety directives rather than scope creep."},"complexity_factors":["Multiple overlapping compliance deadlines (flight cycles OR calendar dates, whichever comes first)","Cross-references to 6 different manufacturer service bulletins (ASB 14RF-9-61-A143 through A146)","Conditional applicability based on repair configuration marking (\"+E\" vs \"+E2\") and serial number threshold","Different inspection requirements depending on whether blades are already installed or newly installed","Nested reporting requirements to two separate entities (manufacturer and CASA)","Specific technical inspection methods referenced but not defined in the document (visual, feeler gage, tap test)"],"plain_english_summary":"This CASA AD orders urgent inspections and eventual mandatory removal of Hamilton Sundstrand 14RF‑9 propeller blades repaired with “+E” (not +E2) and with serial numbers below 885751, commonly fitted to Embraer 120s. It responds to delaminating fibreglass repairs that expose the aluminium spar to corrosion and risk blade failure.\n\nOperators must do an immediate inspection (within 10 flights or 5 days), a follow‑up by 500 flights or 1 July 2006, report results to Hamilton Sundstrand and CASA, and remove all affected blades by 1 March 2007."},"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-phs-23-blade-spar-corrosion","history":"/api/acts/ad-phs-23-blade-spar-corrosion/history","analysis":"/api/acts/ad-phs-23-blade-spar-corrosion/analysis","conflicts":"/api/acts/ad-phs-23-blade-spar-corrosion/conflicts","importantCases":"/api/acts/ad-phs-23-blade-spar-corrosion/important-cases","documents":"/api/acts/ad-phs-23-blade-spar-corrosion/documents"}}