EASA AD No : 2010-0248 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0248 

Date: 26 November 2010 

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 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-BK 117 C-2 helicopters 

TCDS Number : EASA.R.010 

Foreign AD : Not applicable 

Supersedure : None 

ATA 67 Rotor Flight Controls – Main Rotor Controls Power Boosted 

Section – Inspection / Rigging 

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

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

Reason: During rigging of the main rotor controls of a MBB-BK117 C-2 helicopter, it was 

discovered that the piston of the longitudinal main rotor actuator had moved 

after shut-down of the external pump drive. 

This condition, if not detected and corrected, could lead to incorrect rigging 

results, which might impair the freedom of movement of the upper controls, 

possibly resulting in reduced control of the helicopter. 

To address this potentially unsafe condition, ECD has developed an improved 

rigging procedure which will be incorporated into a next revision of the MBBBK117 C-2 Aircraft Maintenance Manual (AMM). 

For the reasons stated above, this AD requires the implementation of 

temporary changes to the Rotorcraft Flight Manual (RFM), a one-time 

inspection to verify that the main rotor controls power boosted section is 

properly rigged and, depending on findings, the necessary corrective actions. 

After the inspection and, if necessary, corrective action, the RFM changes can 

be removed. This AD also requires the implementation of the improved rigging 

procedure as specified in Temporary Revision (TR) 12b of the MBB-BK117 C-2 

AMM. 

Effective Date: 10 December 2010 
EASA AD No : 2010-0248 

EASA Form 110 Page 2/4 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 30 days after the effective date of this AD, introduce temporary 

amendments into the RFM by incorporating the information of Appendix 1 

of this AD into section 5.1.9 “Performance” of the RFM, and by 

incorporating the information of Appendix 2 of this AD into RFM 

Supplement 9.2-11 “External Hoist System”, as applicable to the 

helicopter. 

These actions can be accomplished by inserting a copy of Appendix 1 and 

Appendix 2 of this AD into the RFM (Supplement). 

(2) Within 300 flight hours (+10 %) or 12 months, whichever occurs first after 

the effective date of this AD, inspect the rigging of the power boosted 

section of the main rotor controls in accordance with the instructions of 

ECD Alert Service Bulletin (ASB) MBB BK117 C-2-67A-012. 

(3) If, during the inspection as required by paragraph (2) of this AD, improper 

rigging is detected, before next flight, correct the rigging in accordance 

with the instructions contained in TR 12b of the MBB-BK117 C-2 AMM. 

(4) After accomplishment of the inspection as required by paragraph (2) of this 

AD and, if applicable, corrective action as required by paragraph (3) of this 

AD, the RFM changes as required by paragraph (1) of this AD can be 

removed from the helicopter. 

(5) From the effective date of this AD, any scheduled or unscheduled rigging 

of the power boosted section of the main rotor controls must be carried out 

in accordance with the instructions of TR 12b of the MBB-BK117 C-2 

AMM. 

(6) Compliance with the requirements of paragraph (5) of this AD can be 

demonstrated by: 

(6.1) Revising as follows the approved aircraft maintenance programme 

for which the Operator or the Owner ensures the continuing 

airworthiness of each operated helicopter: 

 Incorporate the rigging instructions contained in ECD TR 12b of the 

MBB BK117 C-2 AMM. 

 and 

(6.2) Complying with the approved aircraft maintenance programme 

described in paragraph (6.1) of this AD. 

Ref. Publications: ECD ASB MBB BK117 C-2-67A-012 dated 16 September 2010. 

ECD MBB-BK117 C-2 AMM, TR 12b (pages attached to ECD ASB MBB BK117 

C-2-67A-012) dated 16 September 2010. 

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. This AD was posted on 23 September 2010 as PAD 10-100 and 

republished on 09 November 2010 as PAD 10-100R1, for consultation until 

23 November 2010. No comments were received during the consultation 

period. 
EASA AD No : 2010-0248 

EASA Form 110 Page 3/4 

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)151-1422 8976; Facsimile: + 49 (0)906-71 4111. 

APPENDIX 1 

The following information must be added to the RFM, Section 5.1.9: 

For hover out of ground effect in density altitudes up to 7000 ft, controllability 

has been demonstrated for winds up to 30 kts, except for winds from the rightrear side, where 20 kts has been demonstrated, and except for winds from the 

left-rear side, where 12 kts has been demonstrated.

For hover out of ground effect in density altitudes above 7000ft, controllability 

has also been demonstrated for winds up to 30 kts, except for winds from the 

right to the right-rear side, where 17 kts has been demonstrated, and except for 

winds from the left-rear side, where 12 kts has been demonstrated. 
EASA AD No : 2010-0248 

EASA Form 110 Page 4/4 

APPENDIX 2 

The following information must be added to RFM Supplement 9.2-11: