EASA AD No : 2009-0119 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0119 

Date: 04 June 2009 

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 65 Tail Rotor Drive – Tail Rotor (T/R) Drive Shaft – Inspection 

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

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

Reason: 

During a recent review of the Aircraft Maintenance Manual (AMM) for the 

Eurocopter Deutschland (ECD) MBB-BK 117 C-2 helicopter, it was discovered 

that this document erroneously allowed the replacement of the solid rivets on 

the long T/R drive shaft with blind rivets. 

All delivered helicopters had T/R drive shafts installed during production fitted 

with solid rivets. Based on this fact, only long T/R drive shafts that have been 

repaired in-service in accordance with the AMM may have blind rivets installed. 

This condition, if not corrected, could lead to a significant reduction of the 

lifetime of the long T/R drive shaft, potentially resulting in failure of the T/R drive 

shaft and consequent loss of control of the helicopter. 

For the reasons described above, this EASA AD requires a one-time inspection 

of all long T/R drive shafts to verify that correct (solid) rivets are installed and, if 

blind rivets are found, the replacement of the T/R drive shaft assembly. In 

addition, this AD prohibits any further application of the erroneous AMM (which 

will be revised by ECD) repair instructions for long T/R drive shafts. 

Effective Date: 18 June 2009 
EASA AD No : 2009-0119 

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) after the effective date of this AD, 

inspect the long T/R drive shaft in accordance with the instructions of 

ECD Alert Service Bulletin (ASB) MBB BK117 C-2-65A-003. 

(2) If, during the inspection as required by paragraph (1) of this AD, it is 

confirmed that no blind rivets are installed, no further action is required by 

this AD. 

(3) If, during the inspection as required by paragraph (1) of this AD, blind 

rivets are found to be installed on the long T/R drive shaft, within the next 

100 FH after the inspection, replace the affected T/R drive shaft assembly 

with a serviceable unit in accordance with the instructions of ECD ASB 

MBB BK 117 C-2-65A-003. 

(4) From the effective date of this AD: 

(4.1) Do not repair any long T/R drive shaft in accordance with the instructions 

of ECD MBB-BK 117 C-2 AMM Chapter 65-11-00, 8-3. 

(4.2) Do not install on a helicopter any long T/R drive shaft that has been 

repaired in accordance with the instructions of ECD MBB-BK 117 C-2 

AMM Chapter 65-11-00, 8-3. 

Ref. Publications: Eurocopter Deutschland ASB MBB BK117 C-2-65A-003 dated 04 May 2009. 

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.