EASA AD No.: 2010-0268-E 

EASA Form 111 Page 1/2 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0268-E 

Date: 21 December 2010 

Note: This Emergency Airworthiness Directive (AD) 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 participate 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 accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[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) exemption]. 

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 corrected, 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 interim 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 2010 
EASA 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 effective date of this AD, amend the applicable 

RFM by inserting the flight manual pages, 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 immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical 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.