CTHIn ForceLegislation
AD/S-PUMA/62 Amdt 1 - Landing Gear - Electro-Valve Power Supply
Eurocopter AS 332 (Super Puma) Series HeEurocopter AS 332 (Super Puma) Series Helicopters
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Eurocopter AS 332 (Super Puma) Series Helicopters
| AD/S-PUMA/62 Amdt 1 | Landing Gear - Electro-Valve Power Supply | 12/2006 |
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| Applicability: | AS 332 C, C1, L and L1 helicopters, pre MOD 0723817: |
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| 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 | |
| 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. | |
| 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. |
| 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. | |
| 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. | |
| 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. | |
| Note: EASA AD 2006-0152 refers. | |
| Compliance: | Requirement 1: Prior to 31 December 2005.Requirement 2: Prior to 23 February 2007.Requirement 3: Prior to 23 February 2007. |
| Requirement 4: Before installation on a helicopter.Compliance time for Requirement 1 remains unchanged from the original issue of this AD. |
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