Airworthiness Directive · Amendment 39-21885 · Engine controls
Safran Helicopter Engines, S.A. (Type Certificate Previously Held by Turbomeca S.A.) Turboshaft Engines
This AD applies to Safran Helicopter Engines, S.A. (Type Certificate previously held by Turbomeca S.A.) Arrius 2B1, Arrius 2B1A, (including those that embody modification (mod) TU45C, identified as Arrius 2B1A_1) and Arrius 2B2 model turboshaft engines with an installed engine electronic control unit (EECU) having part number (P/N) 70EMF01080 or 70EMF01090—for Arrius 2B1 model turboshaft engines without overspeed protection option (TU 19C); P/N 70EMF01100 or P/N 70EMF01120—for Arrius 2B1 model turboshaft engines with overspeed protection option (TU 67C or TU 23C); P/N 70EMH01000 or 70EMH01010—for Arrius 2B1A model turboshaft engines; or P/N 70EMM01000—for Arrius 2B2 model turboshaft engines.
Note 1 to paragraph (c): Turbomeca Mandatory Service Bulletin (MSB) No. 319 73 2082, Version D, dated June 6, 2011, references Arrius 2B1A_1 model turboshaft engines. Arrius 2B1A model turboshaft engines with mod TU 45C applied are identified as Arrius 2B1A_1 on the engine identification plate.
The FAA is superseding Airworthiness Directive (AD) 2005-12-08 for certain Safran Helicopter Engines, S.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B1A-1, and 2B2 model turboshaft engines. AD 2005-12- 08 required replacing the software in the engine electronic control unit (EECU). This AD was prompted by a report of simultaneous loss of automatic control on both engines installed on an Airbus Helicopters Deutschland (formerly Eurocopter Deutschland) EC135 helicopter during flight. This AD requires replacement of the EECU or upgrade of the EECU software for engines with a certain EECU part number (P/N) installed. This AD also prohibits installation of an affected EECU onto any engine. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For engines with an EECU having P/N 70EMF01090, 70EMF01100, 70EMF01120, 70EMH01010, or 70EMM01000, within 90 days after June 29, 2005 (the effective date of AD 2005-12-08), or before further flight, whichever occurs later, upload the EECU software on both engines of the helicopter simultaneously using paragraph 2, Instructions to be incorporated, of the applicable Turbomeca MSB listed in Table 1 to paragraph (g) of this AD, or replace the affected EECU with a part eligible for installation.
(2) For engines with an EECU having P/N 70EMF01080 or 70EMH01000, within 90 days after June 29, 2005 (the effective date of AD 2005-12-08), or before further flight, whichever occurs later, replace the affected EECU with a part eligible for installation.
After the effective date of this AD, do not install onto any engine any EECU having a P/N identified in paragraph (c) of this AD.
For the purpose of this AD, a “part eligible for installation” is an EECU having a P/N that is not identified in paragraph (c) of this AD.
The reporting requirements specified in Turbomeca MSB No. 319 73 2080, Revision 1, dated February 13, 2004; Turbomeca MSB No. 319 73 2081, Revision 1, dated February 13, 2004; Turbomeca MSB No. 319 73 2082, Revision 1, dated February 13, 2004, Version C, dated July 31, 2008, and Version D, dated June 6, 2011; and Turbomeca MSB No. 319 73 2090, Original Issue, dated February 13, 2004, are not required by this AD.
