{"id":"F2006L03609","name":"AD/S-PUMA/62 Amdt 1 - Landing Gear - Electro-Valve Power Supply","slug":"ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":137286,"registerId":"commonwealth-F2006L03609-current","compilationNumber":null,"startDate":"2026-04-03","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/62 Amdt 1 | Landing Gear - Electro-Valve Power Supply | 12/2006 |\n| ------------------- | ----------------------------------------- | ------- |\n\n| Applicability: | AS 332 C, C1, L and L1 helicopters, pre MOD 0723817:                                                                                                                                                                                                                                                                                                           |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|                | a. Without the helicopter wiring modified in accordance with either MOD 0725670 or Eurocopter AS 332 Service Bulletin (SB) 32.00.12 dated 28 April 1999 or later revision approved by the EASA, and/or                                                                                                                                                         |\n|                | b. Equipped with a 33G landing gear control unit Part Number (PN)332A67-1623-00, 332A67-1623-06, 332A67-1623-0610 or 332A67-1623-0651, not modified per MOD 0725670 or 332P083218 or 332A088381 or per AS 332 SB 32.00.12 or later revision approved by the EASA.                                                                                              |\n| Requirement:   | 1. Modify the helicopter wiring and installed 33G landing gear control units in accordance with paragraph 2.B. of Eurocopter AS 332 Alert Service Bulletin (ASB) 32.00.18 or later revision approved by the EASA.                                                                                                                                              |\n|                | 2. Modify the helicopter wiring and installed 33G landing gear control units, PN 332A67-1623-0610, in accordance with paragraph 2.B. of AS 332 ASB 32.00.18 or later revision approved by the EASA and then check these modifications by carrying out functional tests, in compliance with the instructions specified in paragraph 2.B. of the referenced ASB. |\n|                | 3. Repeat the functional tests to check the modifications, in compliance with the instructions specified in paragraph 2.B.3. of AS 332 ASB 32.00.18 or later revision approved by the EASA for helicopters that have already been modified in compliance with AD/S-PUMA/62 and AS 332 ASB 32.00.18 Revision 0.                                                 |\n|                | 4. Modify the 33G landing gear control units, held as spares, in accordance with paragraph 2.B.5. ASB 32.00.18 or later revision approved by the EASA.                                                                                                                                                                                                         |\n|                | Note: EASA AD 2006-0152 refers.                                                                                                                                                                                                                                                                                                                                |\n| Compliance:    | Requirement 1: Prior to 31 December 2005.Requirement 2: Prior to 23 February 2007.Requirement 3: Prior to 23 February 2007.                                                                                                                                                                                                                                    |\n\n|             | Requirement 4: Before installation on a helicopter.Compliance time for Requirement 1 remains unchanged from the original issue of this AD.                                                                                                                                                                                |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | This Amendment becomes effective on 23 November 2006.                                                                                                                                                                                                                                                                     |\n| Background: | The Direction Générale de l’Aviation Civile of France has received reports of electro-valve power supply disruptions which have caused the landing gear to retract and the helicopter to drop resulting in damage to the forward section of the bottom structure.                                                         |\n|             | This Directive requires the modification of the helicopter and landing gear control unit wiring to prevent landing gear retraction whilst the helicopter is on the ground.This amendment extends the applicability of the AD to a new control unit and corrects the definition of the functional tests to be carried out. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n29 September 2006","sortOrder":0},{"sectionNumber":"AD/S-PUMA/62 Amdt 1","sectionType":"part","heading":"AD/S-PUMA/62 Amdt 1","content":"## AD/S-PUMA/62 Amdt 1","sortOrder":1},{"sectionNumber":"Landing Gear - Electro-Valve Power Suppl","sectionType":"part","heading":"Landing Gear - Electro-Valve Power Supply","content":"## Landing Gear - Electro-Valve Power Supply","sortOrder":2},{"sectionNumber":"12/2006","sectionType":"part","heading":"12/2006","content":"## 12/2006","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":4,"scope_assessment":{"changed":true,"description":"This amendment expanded the original directive's scope. The background explicitly states it 'extends the applicability of the AD to a new control unit' (covering additional part numbers previously excluded) and 'corrects the definition of the functional tests.' The original AD only covered some configurations; this version catches more helicopters that could have the same dangerous fault."},"complexity_factors":["Multiple nested applicability conditions combining 'and/or' logic (modified vs unmodified helicopters, specific part numbers, alternative modification paths)","Four separate numbered requirements with different compliance deadlines","Heavy reliance on external technical documents (Eurocopter Service Bulletins) that are not reproduced in the directive itself","Specific part numbers and modification numbers (MOD 0723817, MOD 0725670, etc.) that require cross-referencing","Amendment structure requires readers to understand what changed from the original AD versus what remains the same","Note referencing EASA AD 2006-0152 creates additional external cross-reference"],"plain_english_summary":"This Airworthiness Directive requires operators of specific Eurocopter AS 332 Super Puma variants in Australia to install a wiring and landing-gear-control-unit modification and run functional tests (and correct spare parts) to stop an unsafe fault that can cause the landing gear to retract on the ground. It makes the repair legally mandatory, expands coverage from an earlier AD, and prevents injury, damage, and grounded helicopters."},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"The amendment expands the AD's applicability to include an additional 33G control‑unit part number and corrects the functional‑test definition. Concretely, more helicopters and spare units are captured and operators must follow clarified test procedures per the revised ASB/EASA references (Background; Applicability; Requirements)."},"complexity_factors":["Technical specificity: requires work on aircraft wiring and specific 33G landing‑gear control unit part numbers (Applicability section; Requirement summary).","Multiple applicability conditions: depends on pre‑MOD 0723817 status and whether prior wiring mods (MOD 0725670 / SB 32.00.12) were applied (Applicability).","Cross‑references to external documents: mandates compliance with Eurocopter ASB 32.00.18 (paragraph 2.B.) and notes EASA AD 2006‑0152 (Requirement/Note).","Staged and finite compliance deadlines for different actions (Compliance section: dates for Requirements 1–3 and timing for spares).","Operational testing requirements: initial functional tests and repeat tests to verify modifications (Requirements 2–3), increasing maintenance labour and aircraft downtime.","Spare parts handling: requires modification of 33G units held as spares before installation (Requirement 4), creating logistics and inventory consequences.","Amendment action: extends applicability to an additional control unit and corrects test definitions, which broadens scope and creates potential retroactive compliance for some operators (Background).","Dependence on approved revisions: work must follow the ASB or later revisions approved by EASA, giving regulators and the OEM a role in defining acceptable compliance methods (Requirements)."],"plain_english_summary":"This amendment requires operators of specified Eurocopter AS 332 C/C1/L/L1 helicopters (pre‑MOD 0723817 or fitted with listed 33G control‑unit part numbers) to modify landing‑gear wiring and 33G control units and perform functional tests. The stated purpose is to prevent electro‑valve power‑supply disruptions that can cause inadvertent landing‑gear retraction on the ground. Operators and owners pay for the modifications, testing and spare‑unit updates within set deadlines; the change widens affected units and raises the compliance burden."}},"importantCases":[],"_links":{"self":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply","history":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply/history","analysis":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply/analysis","conflicts":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply/conflicts","importantCases":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply/important-cases","documents":"/api/acts/ad-s-puma-62-amdt-1-landing-gear-electro-valve-power-supply/documents"}}