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EASA AIRWORTHINESS DIRECTIVE 

AD No : 2007-0237 

Date: 31 August 2007

No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the 

requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.

Type Approval Holder’s Name : 

EUROCOPTER Deutschland GmbH 

Type/Model designation(s) : 

MBB-BK117 C-2 helicopters 

TCDS Number: EASA R.010 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA Emergency AD 2007-0189-E dated 12 July 2007. 

ATA 64 Tail Rotor System – Control Lever – Inspection/Replacement 

Manufacturer(s): Eurocopter Deutschland GmbH 

Applicability: Model MBB-BK 117C-2 helicopters, all serial numbers, if equipped with a Tail Rotor 

Control Lever Part Number (P/N) B642M1009103. 

Reason: EASA was informed by the manufacturer of an in-flight incident in which a dynamic 

weight broke off the control lever subsequently leading to considerable vibrations. A 

visual inspection revealed that the threaded bolt of the control lever had broken off. 

For this reason, the manufacturer issued the Alert Service Bulletin MBB BK117 C-2-

64A-002 to introduce a corresponding visual inspection. EASA issued Emergency 

AD (EAD) 2006-0379-E to require operators to accomplish the inspection. The aim 

of that EAD was to prevent separation of dynamic weights in flight, which can lead 

to severe vibration and reduced controllability of the helicopter. Subsequently, 

EASA issued EAD 2007-0189-E, retaining the requirements of EAD 2006-0379-E, 

reducing the inspection interval and limiting the s/n applicability, pending the 

approval of the terminating action. 

The present AD retains the inspection requirements of EAD 2007-0189-E and 

requires the replacement of the control lever with an improved part, which 

constitutes terminating action for the inspection requirements. 

Effective Date: 14 September 2007 

Compliance: Required as indicated, unless accomplished previously: 

(1) For helicopters that have not been inspected as required by EAD 2006-0379-E, 
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before next flight after 16 July 2007 (the effective date of EAD 2007-0189-E), 

visually inspect the control lever in accordance with section 3.A of the 

accomplishment instructions of EUROCOPTER Deutschland Alert Service 

Bulletin (ASB) MBB BK117 C-2-64A-002 Revision 01 dated 9 July 2007 or 

Revision 02 dated 06 August 2007; 

(2) For helicopters that have been inspected as required by EAD 2006-0379-E, 

within the next 8 flight hours (FH) or before accumulating 25 FH after the last 

inspection as required by EAD 2006-0379-E, whichever occurs first after 16 July 

2007 (the effective date of EAD 2007-0189-E), repeat the inspection as 

specified in paragraph (1) of this directive; 

(3) Thereafter, at intervals not to exceed 8 FH, repeat the inspection as specified in 

paragraph (1) of this directive; 

(4) If, during any of the inspections required by this directive, score marks, 

notching, scratching, cracks or similar damage is detected, before next flight, 

replace the affected control lever with an airworthy part; 

(5) Not later than 31 October 2007, replace all P/N B642M1009103 Tail Rotor 

Control Levers and Weights P/N B642M1011202 with the improved P/N 

B642M1009104 Tail Rotor Control Levers including weights in accordance with 

section 3.B of the accomplishment instructions of EUROCOPTER Deutschland 

ASB MBB BK117 C-2-64A-002 Revision 02 dated 06 August 2007. 

Note: After installation of a P/N B642M1009104 Tail Rotor Control Lever Assembly 

on a helicopter as required by paragraph (5) of this directive, the repetitive 

inspections as required by paragraph (3) of this directive may be discontinued. 

(6) After 31 October 2007, no person shall install a spare P/N B642M1009103 Tail 

Rotor Control Lever on a helicopter as a replacement part.

Ref. Publications: Eurocopter Deutschland ASB No. MBB BK117 C-2-64A-002 Revision 01 dated 09 

July 2007 and Revision 02 dated 06 August 2007. 

Remarks : 1. If requested and appropriately substantiated, EASA can accept Alternative 

Methods of Compliance for this AD. 

2. This AD was posted on 16 August 2007 as PAD 07-144 for consultation until 30 

August 2007. No comments were received during the consultation period. 

3. Enquiries regarding this AD should be referred to the AD Focal Point - 

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, 

Technical Support, 86607 Donauwörth, Germany; 

Tel +49-(0) 90671-4444, Fax +49-(0) 90671-4597