{"id":"F2009L00283","name":"AD/S-PUMA/78 Amdt 2 - Main Rotor Blade De-Icing System Clamps","slug":"ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76820,"registerId":"commonwealth-F2009L00283-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/78 Amdt 2 | Main Rotor Blade De-Icing System Clamps | 4/2009 DM |\n| ------------------- | --------------------------------------- | --------- |\n\n| Applicability: | EUROCOPTER AS332 C, C1, L and L1 helicopters, fitted with main rotor bladede-icing system distributor retaining clamps, P/N 225000-18454 or P/N D18454. |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Perform the inspections detailed in paragraph 2.B. of Eurocopter AS332 Alert Service Bulletin (ASB) No. 30.00.66 revision 1 or later approved revision.2. If there is a risk of interference between the screw head and the clamp, rework the clamp.If there is a crack in the screw shank, replace the screw.If there is no lock-wiring hole in the screw head, produce a hole and lock the screw.3. Do not install a main rotor blade de-icing system distributor retaining clamp fitted with an attachment screw on a helicopter, unless it has been inspected and corrected in accordance with the Requirements 1 and 2 of this AD, as applicable.4. Lock-wire the clamp attachment in accordance with paragraphs 2.B.1 and 2.B.5 of Eurocopter AS332 ASB No. 30.00.66 revision 2 or later approved revision.5. Pending compliance with Requirement 6 - Accomplish the following:a) Inspect the attachment screw for integrity in accordance with paragraph 2.B.7 of Eurocopter AS332 ASB No. 30.00.66 revision 2 or SA330 ASBNo. 30.20 revision 2, as applicable to the helicopter version; andb) Lockwire the clamp attachment in accordance with paragraph 2.B.5 of Eurocopter AS332 ASB No. 30.00.66 revision 2 or SA330 ASB No. 30.20 revision 2, as applicable to the helicopter version.6. On helicopters equipped with a clamp which has no batch number marked after its part number, return the clamp to conformity in accordance with a) or b) below: |\n\n| | a) Replace the attachment screw (variant with non-welded screw to its barrel) or the complete clamp (variant with welded screw to its barrel) with a serviceable part in accordance with paragraphs 2.B.1, 2.B.2, 2.B.3.d and 2.B.4 of Eurocopter AS332 ASB No. 30.00.66 revision 2.b) Verify that the hardness of the attachment screw is correct in accordance with paragraphs 2.B.1, 2.B.2 and 2.B.3.c of Eurocopter AS332 ASB No. 30.00.66 revision 2. In the case of non-conformity, before next flight, comply with Requirement 4 of this AD and thereafter with Requirement 5 and, without exceeding the compliance time limit of Requirement 6, replace parts as stated in Requirement 6a) of this AD.7. Do not install a main rotor blade de-icing system distributor retaining clamp or an associated attachment screw on a helicopter, unless its conformity has been established in accordance with the requirements of this AD.After accomplishment on a helicopter of Requirement 6 the actions detailed in Requirements 4 and 5 are no longer required for that helicopter.Note: EASA AD 2009-0003R1 dated 13 January 2009 refers. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | For Requirement 1 - Remains unchanged as detailed in the original issue of this AD as:On helicopters equipped with a main rotor blade de-icing system distributor retaining clamp fitted with an attachment screw that is not welded to the barrel - Within 50 flight hours (FH) or 3 months after 25 June 2008, whichever occurs first, unless previously accomplished.On helicopters equipped with a main rotor blade de-icing system distributor retaining clamp fitted with an attachment screw that is welded to the barrel - Within 20 FH or 1 month after 25 June 2008, whichever occurs first, unless previously accomplished.For Requirement 2 - Before further flight.For Requirement 3 - From the effective date of this AD.For Requirement 4 - Within 10 FH after the effective date of this AD.For Requirement 5a - At intervals not exceeding 10 FH.For Requirement 5b - Each time a main rotor blade de-icing system distributor is installed.For Requirement 6 - Within 8 months after the effective date of this AD. |\n\n| | For Requirement 7 - From the effective date of this AD. |\n| ----------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| | This Amendment becomes effective on 6 February 2009. |\n| Background: | This AD was issued in response to two cases of failure of the screw that secures the main rotor blade de-icing system distributor retaining clamp. The examinations carried out on these screws have revealed that these failures were the result of assembly stress in the screw head.In addition, in some cases, it was found that the lock-wiring hole was missing from the screw head, making it impossible to ensure additional security using lock-wiring between the screw head and the nut.Failure of the clamp attachment screw can lead to damage to the main or tail rotor blades, and is a risk for persons on the ground.Amendment 1included a change to the applicability section to include those attachment screws that are welded to the barrel, and to cover the absence of a part number on some clamps.More recently, a new case of failure of the clamp attachment screw has been reported after having complied with the instructions in a previous amendment of this AD and the lock-wire which is intended to secure the attachment screw, retained the clamp until the screw failure was discovered. Later examinations showed this failure was caused by non-conformity of the hardness of the affected screw.This amendment requires the installation of a supplementary lock-wire to ensure the clamp is retained pending replacement of the screw or the screw hardness condition has been verified to be correct.Pending corrective action on the screw, this AD also requires repetitively inspecting the integrity of the affected screws and retaining clamps.The original issue of this AD became effective 25 June 2008.Amendment 1 of this AD became effective on 29 August 2008. |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n3 February 2009","sortOrder":0},{"sectionNumber":"AD/S-PUMA/78 Amdt 2","sectionType":"part","heading":"AD/S-PUMA/78 Amdt 2","content":"## AD/S-PUMA/78 Amdt 2","sortOrder":1},{"sectionNumber":"Main Rotor Blade De-Icing System Clamps","sectionType":"part","heading":"Main Rotor Blade De-Icing System Clamps","content":"## Main Rotor Blade De-Icing System Clamps","sortOrder":2},{"sectionNumber":"4/2009 DM","sectionType":"part","heading":"4/2009 DM","content":"## 4/2009 DM","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":7,"scope_assessment":{"changed":true,"description":"Scope has expanded from the original AD. Amendment 1 broadened applicability to include clamps with attachment screws welded to the barrel and clamps missing part numbers; this amendment adds a supplementary lock-wire requirement, repetitive inspections and mandatory hardness verification or replacement where batch marks are absent (Background; Requirements 5 and 6). The change increases both the population of affected parts and the interim safeguards operators must carry out."},"complexity_factors":["Multiple conditional workstreams: different actions depending on whether the screw is welded to the barrel, whether a batch number is present, and on inspection findings (see Requirements 2 and 6).","References to external technical documents and versions: compliance ties to Eurocopter AS332 Alert Service Bulletin No. 30.00.66 (rev.1/2 or later) and SA330 ASB No. 30.20 rev.2, creating dependency on approved ASB revisions (Requirements 1, 4, 5 and general text).","Varied and short compliance timeframes increase operational disruption: e.g. 50 FH/3 months vs 20 FH/1 month for Requirement 1, before‑next‑flight for Requirement 2, 10 FH for Requirement 4, 8 months for Requirement 6 (Compliance section).","Recurring inspection burden: Requirement 5a mandates inspection at intervals not exceeding 10 flight hours and Requirement 5b for each installation of a distributor, creating ongoing maintenance workload (Requirement 5).","Technical verification obligation: hardness testing of attachment screws is required where no batch number exists; non-conforming screws must be replaced before next flight (Requirement 6b).","Installation prohibition until conformity established: operators must not install clamps or screws unless inspected and corrected per the AD, creating supply and maintenance gating (Requirements 3 and 7).","Temporary supplementary measures: this amendment mandates an additional lock-wire pending corrective action, adding a temporary compliance layer and recordkeeping (Background and Requirement 5).","Removal of repetitive requirements after part replacement: after accomplishing Requirement 6 for a helicopter, Requirements 4 and 5 cease to apply to that helicopter, adding conditional termination logic (end of Requirements 7 paragraph).","Who pays and incentives: costs fall on operators to inspect, rework, hardness-test or replace screws/clamps and to perform repeated inspections and lock-wiring (Requirements 1–6; Compliance).","Regulatory discretion and potential variability: 'approved revision' references allow the regulator to accept later ASB revisions, which can change technical obligations without amending this AD text directly (Requirements 1 and 4)."],"plain_english_summary":"This airworthiness directive requires operators of Eurocopter AS332 C/C1/L/L1 helicopters fitted with certain main rotor de-icing distributor clamps (P/N 225000-18454 or P/N D18454) to inspect, rework or replace clamp attachment screws, add lock-wiring, and not fit non‑compliant parts. \n\nIt imposes recurring inspections and time-limited replacement or hardness verification after reported screw failures because a loose or failed screw can damage rotors or injure people on the ground."},"kimi_summary":{"content_quality":"ok","complexity_score":6,"scope_assessment":{"changed":true,"description":"The original AD addressed screw failures from assembly stress and missing lock-wiring holes. Amendment 1 expanded applicability to include welded screws and clamps without part numbers. This Amendment 2 further expands scope after a new failure mode was discovered (incorrect screw hardness) despite previous compliance. It adds repetitive inspection requirements, supplementary lock-wiring mandates, and hardness verification procedures that go beyond the original 'inspect and replace' intent. The AD has evolved from a one-time inspection mandate to an ongoing monitoring and multi-stage correction regime."},"complexity_factors":["Multiple interdependent requirements (7 numbered requirements with cross-references between them)","Extensive cross-referencing to external manufacturer documents (Eurocopter Alert Service Bulletins 30.00.66 revisions 1 and 2, and SA330 ASB No. 30.20 revision 2)","Conditional logic throughout (e.g., 'If there is a risk of interference...', 'If there is a crack...', 'If there is no lock-wiring hole...')","Variant-specific applicability (welded vs non-welded screws, different helicopter versions requiring different ASB references)","Staggered compliance deadlines varying by requirement and equipment type (ranging from 'before further flight' to 8 months)","Nested exceptions and dependencies (Requirement 5 is explicitly 'pending compliance with Requirement 6', and Requirement 7 creates installation prohibitions)","Technical aviation terminology requiring specialized knowledge (P/N numbers, flight hours, lock-wiring, barrel assemblies, hardness testing)"],"plain_english_summary":"This CASA Airworthiness Directive requires operators of certain Eurocopter AS332 Super Puma helicopters in Australia to inspect and remediate defects in the main rotor blade de‑icing clamps and screws. It responds to failing screws (assembly stress, missing lock‑wire holes, incorrect hardness) that could let clamps detach and damage blades or harm people. Compliance—inspections, repairs, lock‑wiring or part replacement within specified timeframes—is mandatory before further flight."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps","history":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps/history","analysis":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps/analysis","conflicts":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps/conflicts","importantCases":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps/important-cases","documents":"/api/acts/ad-s-puma-78-amdt-2-main-rotor-blade-de-icing-system-clamps/documents"}}