EASA AD No : 2010- 0045 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0045 

[2nd Correction: 30 March 2010] 

Date: 18 March 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 – Upper Control Bellcrank Assembly –

Modification / Inspection / Replacement

Manufacturer(s): Eurocopter Deutschland GmbH and American Eurocopter LLC 

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

Reason: 

During accomplishment of inspections on MBB BK117 C-2 helicopters, bellcrank 

bearings have been discovered which were incorrectly staked. 

This condition, if not detected and corrected, may cause the affected bellcrank 

to shift in the axial direction and cause chafing. Under unfavourable 

circumstances, this could lead to interference between the bolts connecting the 

control rods to Bellcrank-Q and Bellcrank-K, possibly resulting in reduced control 

of the helicopter. 

For the reasons described above, this AD requires a check of the affected 

bearings for correct attachment, a modification to change the direction of the bolt 

connected to Bellcrank-Q, repetitive inspections of the affected components and 

replacement of damaged and corroded parts. 

This AD has been republished to correct the allowed deviation (up to 10%) of 

compliance time for the repetitive inspection as required by paragraph (2) of this 

AD. The flexibility provision was added to §§ (1) and (3) in error. 

Effective Date: 01 April 2010 
EASA AD No : 2010- 0045 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 100 flight hours (FH) or 1 month, whichever occurs first after 

the effective date of this AD, check the affected bearings for correct 

attachment and modify the affected bellcrank assemblies in accordance 

with the instructions of ECD ASB MBB BK117 C-2-67A-011 Revision 1. 

(2) After modification of a helicopter as required by paragraph (1) of this AD or 

after helicopter first flight, as applicable, at intervals not exceeding 300 FH 

(+10%), inspect the bellcrank levers in accordance with the instructions of 

ECD ASB MBB BK117 C-2-67A-011 Revision 1. 

(3) Installation on a helicopter of a spare bellcrank or bellcrank assembly 

that has been delivered prior to 17 February 2010: Within 100 FH after 

installation, but not before accumulating 50 FH after installation, accomplish 

a one-time inspection of the replacement part in accordance with the 

instructions of ECD ASB MBB BK117 C-2-67A-011 Revision 1. 

(4) If, during the check as required by paragraph (1) or during any inspection 

as required by paragraphs (2) or (3) of this AD, damaged or corroded parts 

are detected, before further flight, replace the affected part(s). 

(5) Installation of replacement parts as specified in paragraph (3) or as required 

by paragraph (4) of this AD does not constitute terminating action for the 

repetitive inspections required by paragraph (2) of this AD. 

Ref. Publications: 

Eurocopter Deutschland GmbH ASB MBB BK117 C-2-67A-011 Revision 1, 

dated 23 February 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 required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 

process after publication. 

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.