EASA AD No.: 2012-0216

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0216

Date: 18 October 2012

Note: This 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 AD is issued in accordance with EC 748/2012, Part 21.A.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].

Design Approval Holder’s Name:

EUROCOPTER DEUTSCHLAND GmbH

Type/Model designation(s):

MBB-BK 117 C-2 helicopters

TCDS Number: EASA.R.010

Foreign AD: not applicable

Supersedure: None

ATA 22 Auto Flight – Autopilot – Dispatch Restriction

Manufacturer(s): Eurocopter Deutschland GmbH (ECD), (formerly Messerschmitt-Bölkow-Blohm 

GmbH, Eurocopter Hubschrauber GmbH), American Eurocopter

Applicability: MBB-BK 117 C-2 helicopters, all serial numbers.

Reason: In a recent incident, the autopilot (AP) of a MBB-BK 117 C-2 helicopter failed 

in flight with messages "ACTUATOR" and "BACKUP SAS" appearing on the 

Caution and Advisory Display (CAD), Red AP on warning unit (WU) and Y 

(Yaw actuator) and P (pitch actuator) on the Primary Flight Display (PFD). With 

the AP switched off, cautions "YAW SAS" and "BACKUP SAS" appeared on 

the CAD. When the AP was selected ON again, "YAW SAS" caution 

extinguished while "BACKUP SAS" was still indicated.

The initial results of the investigation appear to indicate that an internal short 

cut on the yaw SEMA (Smart Electro-Mechanical Actuator) “ACTIV” input to 

ground led to the seizure of all five SEMA units.

This condition, if not corrected, combined with an inoperative Autotrim in Pitch 

or Roll, or combined with an inoperative Autotrim in Cyclic and Yaw axis, could 

significantly reduce the pilot’s reaction time to stabilize the helicopter, possibly 

resulting in loss of control of the helicopter. This scenario is valid when 

operating under Instrument Flight Rules (IFR) or Night Visual Flight Rules 

(VFR).

For the reasons described above, this AD prohibits dispatch of a helicopter with 

an inoperative Autotrim in Pitch or Roll, or dispatch with a combined inoperative 

Autotrim in Cyclic and Yaw axis, when operating under IFR or Night VFR. For 

operators using a Minimum Equipment List (MEL) based on the existing ECD 

Master MEL, this AD requires revision of the MMEL and changes to the 

operator’s MEL accordingly.
EASA AD No.: 2012-0216

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 22 October 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Within 25 flight cycles or 30 days, whichever occurs first after the effective date 

of this AD, amend the Rotorcraft Flight Manual (RFM) and operator’s MEL, as 

applicable, by implementing the following dispatch restriction for all IFR and 

Night VFR operations in accordance with the instructions of ECD Alert Service 

Bulletin (ASB) MBB-BK117 C-2-22A-013, inform all flight crews and thereafter 

operate the helicopter accordingly:

Dispatch under IFR or Night VFR with the Autotrim 

inoperative in Pitch or Roll or a combined inoperative 

Autotrim in Cyclic and Yaw axis is PROHIBITED

Note 1: This limitation is related to ECD MMEL BK117 C-2 (EC145) Series, 

items 22 1.5, 22 1.6 and 22 1.8.

Note 2: Incorporation of an appropriate revision of the MMEL into the 

operator’s MEL, or inserting a copy of this AD into the RFM is acceptable to 

comply with the requirements of this AD.

Ref. Publications: ECD ASB MBB-BK117 C-2-22A-013, dated 12 October 2012.

ECD MMEL BK117 C-2 (EC145) Series, original issue, dated 12 March 2012, 

or Revision 1 (to be published).

The use of later approved revisions of these documents 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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive 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)151-1422 8976, Fax: + 49 (0)906-71 4111.