{"id":"F2008L04131","name":"AD/S-PUMA/80 - Coupling Shaft Hardware","slug":"ad-s-puma-80-coupling-shaft-hardware","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76058,"registerId":"commonwealth-F2008L04131-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Eurocopter AS 332 (Super Puma) Series He","sectionType":"division","heading":"Eurocopter AS 332 (Super Puma) Series Helicopters","content":"### Eurocopter AS 332 (Super Puma) Series Helicopters\n\n| AD/S-PUMA/80 | Coupling Shaft Hardware | 12/2008 |\n| ------------ | ----------------------- | ------- |\n\n| Applicability: | Eurocopter (formerly Eurocopter France; Aerospatiale) Model AS 332 C, AS 332 C1, AS332 L, AS 332 L1 and AS 332 L2 helicopters, fitted with engine/main gearbox (MGB) coupling shaft flange threaded attachment bolt assemblies Part Number (P/N) 332A54.2009.01.Note 1: Engine/MGB coupling shaft P/N 332A54.0216.06, serial number 2803 is a spare assembly that has been supplied along with the threaded attachment bolt assemblies P/N 332A54.2009.01. |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. For helicopters on which the affected threaded bolt assemblies have been installed on the engine side on both engine/MGB coupling shafts - Replace the 6 threaded attachment bolt assemblies P/N 332A54-2009-01 with 6 airworthy threaded attachment bolt assemblies with another P/N in accordance with paragraph 2.B.2 Eurocopter AS332 ASB No.01.00.71 revision 1 or later approved revision.2. For helicopters on which the affected threaded bolt assemblies have been installed on the engine side on only one engine/MGB coupling shaft - Replace the 6 threaded attachment bolt assemblies P/N 332A54-2009-01 with 6 airworthy threaded attachment bolt assemblies with another P/N in accordance with paragraph 2.B.2 of Eurocopter AS332 ASB No.01.00.71 revision 1 or later approved revision.3. For spare assemblies and parts as listed in paragraph 1.A.2 of the referenced Eurocopter ASB, as applicable to type: spare P/N 332A54-2009-01 threaded attachment bolt assemblies may no longer be installed on any helicopter; and no person may install a spare engine/MGB coupling shaft on any helicopter, unless it has been verified that any installed threaded attachment bolt assemblies with P/N 332A54-2009-01 have been replaced in accordance with paragraph 2.B.2 of Eurocopter AS332 ASB No.01.00.71 revision 1 or later approved revision.4. Return the threaded attachment bolt assemblies P/N 332A54-2009-01 to Eurocopter Marignane.Note 2: EASA AD 2007-0134 dated 14 May 2007 refers. |\n\n| Compliance: | For Requirement 1 - Within the next 50 flight hours (FH), after the effective date of this AD, unless previously accomplished.For Requirement 2 - Within the next 100 FH after the effective date of this AD, unless previously accomplished.For Requirement 3 - From the effective date of this AD.For Requirement 4 - Within 7 days after removal from service. |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| | This Airworthiness Directive becomes effective on 20 November 2008. |\n| Background: | From 5 July 2006, Eurocopter delivered engine/MGB coupling shaft flange threaded attachment bolt assemblies P/N 332A54.2009.01, with new bolt definition. The intent was to provide a longer threaded section to the bolt as an improvement of the previous threaded bolt assemblies P/N 332A54.2009.00 on which a few anomalies without safety risk were reported (see EUROCOPTER Service Letter No. 1542-63-01 for further details).However, the feedback of information concerning first installations of the new threaded bolt assemblies has revealed a manufacturing non-conformity (additional length of the plain bolt shaft section). All the threaded bolt assemblies with P/N 332A54.2009.01 have this non-conformity.It is impossible to tighten the flange on the MGB side of the engine/MGB coupling shaft with those wrong assemblies while their installation on the flange on the engine side remains possible, but with an uncertainty about the torque tightness efficiency. Therefore, on the engine side only, where their assembly could have been made, this may lead to early tightening torque loss and subsequent failure of the threaded bolt assemblies attaching the engine, the flange, and the engine/MGB coupling shaft, which, in time, could result in the loss of the corresponding MGB input drive. The loss of torque tightness and resulting play in the coupling may be indicated by abnormal noise which can be detected by the flight crew.This AD requires replacement of all P/N 332A54.2009.01 engine/MGB coupling shaft flange threaded attachment bolt assemblies. |\n\n![](image.001.png) \nCharles Lenarcic \nDelegate of the Civil Aviation Safety Authority\n\n9 October 2008","sortOrder":0},{"sectionNumber":"AD/S-PUMA/80","sectionType":"part","heading":"AD/S-PUMA/80","content":"## AD/S-PUMA/80","sortOrder":1},{"sectionNumber":"Coupling Shaft Hardware","sectionType":"part","heading":"Coupling Shaft Hardware","content":"## Coupling Shaft Hardware","sortOrder":2},{"sectionNumber":"12/2008","sectionType":"part","heading":"12/2008","content":"## 12/2008","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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive with a focused, single-purpose scope: addressing a specific manufacturing defect in a particular bolt part number. The scope remains tightly constrained to the identified safety issue without expansion into broader operational or maintenance requirements."},"complexity_factors":["Multiple conditional requirements based on installation configuration (both shafts vs one shaft vs spare parts)","Cross-reference to external technical document (Eurocopter ASB No.01.00.71) for detailed replacement procedures","Specific part numbers and serial numbers that must be precisely identified","Four separate compliance deadlines with different timeframes (50 flight hours, 100 flight hours, immediate, 7 days)","Nested applicability note regarding spare assemblies with specific serial numbers"],"plain_english_summary":"This AD mandates removal and replacement of incorrectly manufactured engine-to-main-gearbox bolts found on certain Eurocopter AS 332 Super Puma models, prohibits their use as spares, and requires returned parts to Eurocopter. Compliance windows are short (measured in flight hours) depending on affected couplings. \n\nIt affects owners/operators of AS 332 C/C1/L/L1/L2 helicopters and addresses a bolt failure risk that could cause loss of engine power transmission and serious flight safety consequences."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The instrument implements a targeted remedial scope: it addresses the specific non‑conforming bolt P/N 332A54.2009.01 on listed AS332 models by mandating replacement, prohibiting installation of affected spares, and returning removed parts to the manufacturer. It does not expand applicability beyond the listed models/part numbers and relies on the Eurocopter ASB for replacement specifications (Applicability; Requirement 1–4)."},"complexity_factors":["Technical specificity: identifies a single non‑conforming part number (P/N 332A54.2009.01) and affected helicopter models (Applicability).","Multiple compliance deadlines: replacement within 50 flight hours, 100 flight hours, immediate prohibition on installing spares, and 7‑day return requirement (Compliance; Requirement 1–4).","Dependency on external documents: replacement must follow Eurocopter AS332 ASB No.01.00.71 paragraph 2.B.2 (Requirement 1–2 reference to ASB and approved revisions).","Operational verification burden: maintenance records and physical inspection required to determine whether bolts were installed engine‑side on one or both coupling shafts (Requirement distinctions).","Logistics and supply impact: removed bolts must be returned to Eurocopter and spares with the P/N may no longer be installed (Requirement 3–4), creating parts‑management and lead‑time considerations.","Safety consequence linkage: the AD ties a manufacturing dimensional non‑conformity to potential torque loss and MGB input drive loss, increasing priority and enforcement scrutiny (Background).","Cross‑regulatory reference: cites EASA AD 2007‑0134, requiring alignment with international directives (Background, Note 2)."],"plain_english_summary":"This Airworthiness Directive requires operators of Eurocopter AS332 C/C1/L/L1/L2 helicopters fitted with coupling shaft threaded attachment bolts P/N 332A54.2009.01 to replace those bolts with airworthy assemblies (per Eurocopter ASB paragraph 2.B.2), stop fitting affected spare bolts, and return removed bolts to Eurocopter. The measure responds to a manufacturing non‑conformity that can permit loss of tightening torque on the engine side, risking bolt failure and loss of the corresponding main gearbox (MGB) input drive; crew may detect abnormal noise. Compliance times vary (50 FH / 100 FH / immediate)."}},"importantCases":[],"_links":{"self":"/api/acts/ad-s-puma-80-coupling-shaft-hardware","history":"/api/acts/ad-s-puma-80-coupling-shaft-hardware/history","analysis":"/api/acts/ad-s-puma-80-coupling-shaft-hardware/analysis","conflicts":"/api/acts/ad-s-puma-80-coupling-shaft-hardware/conflicts","importantCases":"/api/acts/ad-s-puma-80-coupling-shaft-hardware/important-cases","documents":"/api/acts/ad-s-puma-80-coupling-shaft-hardware/documents"}}