AD/S-PUMA/66 Amdt 1 Main Rotor Head Spindles (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/S-PUMA/66 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Eurocopter AS 332 (Super Puma) Series Helicopters
| AD/S-PUMA/66 Amdt 1 | Main Rotor Head Spindles | 1/2007 DM |
Applicability: | Model AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters, equipped with following main rotor head spindles, Part Numbers (P/N): 332A31-1390-all dash numbers, or 332A31-1398-all dash numbers, or 332A31-1410-all dash numbers, or 332A31-1485-all dash numbers. |
Requirement: | 1. Main rotor heads fitted with spindles P/N 332A31-1390-all dash numbers, or a. On spindles not fitted with the folding option: Check that there is no crack in the material section of the spindle yokes (front face and edge) on the leading edge, in accordance with paragraph 2.B.2 of Eurocopter Alert Service Bulletin (ASB) No. 05.00.67 Revision 1. b. On spindles fitted with the folding option before embodiment of modification 332A080950: Inspect the visible area of the edge of the material section of the yokes, on the leading edge of the spindles for cracks, in accordance with paragraphs 2.B.3.a.1 and 2.B. 3.a.2 of ASB No. 05.00.67 Revision 1. c. Modify the lock supports of the folding option in accordance with paragraph 2.B.6 of ASB No. 05.00.67 Revision 1. d. On spindles fitted with the folding option after embodiment of modification 332A080950: Inspect the visible area of the edge of the material section of the yokes, on the leading edge of the spindles for cracks, in accordance with paragraphs 2.B.3.a.1 and 2.B. 3.a.2 of ASB No. 05.00.67 Revision 1. |
| 2. Main rotor heads fitted with spindles P/N 332A31-1410-all dash numbers, or a. On spindles not fitted with the folding option: Check that there is no crack in the material section of the spindle yokes (front face and edge) on the leading edge, in accordance with paragraph 2.B. of Eurocopter Alert Service Bulletin (ASB) No. 05.00.67. b. On spindles fitted with the folding option: Inspect the visible area of the edge of the material section of the yokes, on the leading edge of the spindles for cracks, in accordance with paragraphs 2.B.4 of ASB No. 05.00.67 Revision 1. If cracking is detected in the material section during any check of the spindle yokes, before further flight, remove and replace the sleeve/spindle assembly. On non-installed equipment held as spares: Before installation on a helicopter of a spindle referenced in Requirement 1, and has logged operating hours since new or last overhaul, accomplish the check for cracks in accordance with paragraph 2.B.2 of ASB No. 05.00.67 Revision 1. Before installation on a helicopter of a main rotor head fitted with spindles with lock supports for the folding option without modification 332A080950 embodied, and corresponding to the items referenced in Requirement 2, modify the main rotor head in accordance with paragraph 2.B.6 of ASB No. 05.00.67 Revision 1. Before installation on a helicopter of a folding option lock support corresponding to those referenced in Requirement 2, and without modification 332A080950 embodied, modify the lock support in accordance with paragraph 2.B.6 of ASB No. 05.00.67 Revision 1. Note: EASA Emergency AD 2006-0349-E refers. | |
Compliance: | 1.a. Within 5 flight hours after 25 October 2006, and thereafter at intervals not to exceed 5 flight hours. 1.b. Unless accomplished previously, before further flight after 27 November 2006. Thereafter at intervals not to exceed 5 flight hours. 1.c. Within 110 flight hours after 27 November 2006. |
| 1.d. Within 5 flight hours after embodiment of modification. Thereafter at intervals not to exceed 5 flight hours. 2.a. Within 10 flight hours after 25 October 2006, and thereafter at intervals not to exceed 10 flight hours. 2.b. Unless accomplished previously, before further flight after 27 November 2006. Thereafter at intervals not to exceed 10 flight hours. The compliance times for Requirements 1.a. and 2.a. remain unchanged by this issue of the Directive. | |
| This Amendment becomes effective on 27 November 2006. | |
Background: | The EASA received a report of the failure of the lower material section on the leading edge of a main rotor head spindle yoke on an AS 332 L helicopter. The crack which led to the failure was externally visible. Amendment 1 is issued in response to a new EASA AD, which introduces both a check on main rotor heads equipped with the optional main rotor blade folding system, and the modification to certain lock supports of this optional equipment, in order to ease the subsequent checks. |
David Villiers
Delegate of the Civil Aviation Safety Authority
23 November 2006
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