Airworthiness directives › 2012-23-05
AD 2012-23-05 Airworthiness Directives; Eurocopter Deutschland Helicopters
Applicability*9
This AD becomes effective December 26, 2012.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5114; email george.schwab@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
Required actions
(1) Eurocopter Deutschland GmbH Alert Service Bulletin MBB-BK117 C-2-24A-010 Revision 2, dated September 14, 2011, which is not incorporated by reference, contains additional information about the subject of this AD. (2) For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052, telephone (972) 641-0000 or (800) 232-0323, fax (972) 641-3775, or at http://www.eurocopter.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (3) The subject of this AD is addressed in European Aviation Safety Agency AD No. 2011-0149R1, dated September 30, 2011.
Unsafe condition
(1) Within the next 300 hours time-in-service or 6 months, whichever occurs first, replace all GCUs with no MOD, MOD A, or MOD B with an airworthy GCU. (2) Do not install a GCU P/N 51530-021-EI with no MOD, MOD A, or MOD B on any helicopter.
Affected ADs
This AD defines the unsafe condition as an internal short circuit in certain GCUs. This condition could result in loss of electrical generating power, resulting in the loss of systems required for continued safe flight and landing, and subsequent loss of control of the helicopter.
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