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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 B oosted Section – Inspection / Rigging

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

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

Reason: During rigging of the main rotor controls o f 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, coul d lead to incorrect rigging results, which might impair the freedom of movement of the upper controls, possibly resulting in reduced control of the helico pter.

To address this potentially unsafe condition, ECD h as 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 p ower boosted section is properly rigged and, depending on findings, the nec essary corrective actions. After the inspection and, if necessary, corrective action, the RFM changes can be removed. This AD also requires the implementatio n of the improved rigging procedure as specified in Temporary Revision (TR) 1 2b of the MBB-BK117 C-2 AMM.

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

EASA Form 110 Page 2/4 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

(1) Within 30 days after the effective date of this AD, introduce temporary amendments into the RFM by incorporating the inform ation 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 appli cable to the helicopter. These actions can be accomplished by inserting a co py of Appendix 1 and Appendix 2 of this AD into the RFM (Supplement).

(2) Within 300 flight hours (+10 %) or 12 months, w hichever occurs first after the effective date of this AD, inspect the rigging of the power boosted section of the main rotor controls in accordance wi th the instructions of ECD Alert Service Bulletin (ASB) MBB BK117 C-2-67A- 012.

(3) If, during the inspection as required by paragr aph (2) of this AD, improper rigging is detected, before next flight, correct th e rigging in accordance with the instructions contained in TR 12b of the MB B-BK117 C-2 AMM.

(4) After accomplishment of the inspection as requi red by paragraph (2) of this AD and, if applicable, corrective action as require d 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 schedul ed or unscheduled rigging of the power boosted section of the main rotor cont rols must be carried out in accordance with the instructions of TR 12b of th e 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 mai ntenance programme for which the Operator or the Owner ensures the con tinuing 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 maintena nce programme described in paragraph (6.1) of this AD.

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

ECD MBB-BK117 C-2 AMM, TR 12b (pages attached to EC D ASB MBB BK117 C-2-67A-012) dated 16 September 2010.

The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.

2. This AD was posted on 23 September 2010 as PAD 1 0-100 and republished on 09 November 2010 as PAD 10-100R1, fo r 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 t o the Airworthiness Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: Eurocopter Deutschland GmbH, Industriestrasse 4, 86 607 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, excep t 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 bee n demonstrated.EASA AD No : 2010-0248

EASA Form 110 Page 4/4 

### APPENDIX 2

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