EASA AD No.: 2010-0268-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2010-0268-E

Date: 21 December 2010

Note: This Emergency Airworthiness Directive (A D) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that partici pate in the activities of EASA under Article 66 of that Regulation
This EAD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with t he requirements of that AD, unless otherwise specified by the Ag ency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemptio n].


### Type Approval Holder’s Name :
Eurocopter Deutschland GmbH Type/Model designation(s) :
MBB-BK117 C-2 helicopters

TCDS Number : EASA.R.010

Foreign AD : Not applicable

Supersedure : None



### ATA 24 Electrical Power – Starter/Generator Switch Off – Revised Flight Manual Procedure

Manufacturer(s): Eurocopter Deutschland GmbH (ECD), American Eurocopter LLC

Applicability: MBB-BK117 C-2 helicopters, all serial numbers

Reason: EASA have received reports that on some MBB-BK117 C-2 helicopters, a too high current flow was detected when one generator was deactivated (e.g. during the ENGINE POWER CHECK). This situation, if not detected and corr ected, could lead to failure of the generator, likely resulting in loss of electrical power and inducing loss of systems that are necessary for safe flight. For the reasons described above, this AD requires the introduction of additional Rotorcraft Flight Manual (RFM) procedures, to include visual monitoring of the electrical power display GEN AMPS on the Vehicle and Engine Multifunction Display (VEMD) during switching of a generator. This AD is considered to be an inte rim measure, pending the development of a final solution that will prevent this particular mode of generator failure; further AD action cannot be excluded.

Effective Date: 23 December 2010EASA AD No.: 2010-0268-E

EASA Form 111 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: Before next flight after the effectiv e date of this AD, amend the applicable RFM by inserting the flight manual p ages, included in ECD Alert Service Bulletin (ASB) MBB BK117 C-2-24A-008, into the RFM, and inform the flight crews accordingly.

Ref. Publications: ECD ASB MBB BK117 C- 2-24A-008 dated 20 December 2010. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to implement the full consultation process and an immedi ate publication and notification. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the tec hnical content of the requirements in this AD, please contact: Eurocopter Deutschland GmbH, Industriestrasse 4, 86607 Donauwörth, Federal Republic of Germany. Telephone: + 49 (0) 151 14 22 89 76, Facsimile: + 49 (0) 906 71-4111.