EASA AD No : 2010-0128 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0128 

Corrected: 25 June 2010 

Date: 23 June 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) : 

BO 105 helicopters 

TCDS Number : EASA.R.011 

Foreign AD : Not applicable 

Supersedure : None 

ATA 72 Engine – Power Turbine Speed – Operational Limitation 

Manufacturer(s): Eurocopter Deutschland GmbH, Eurocopter Hubschrauber GmbH, 

Messerschmitt-Bölkow-Blohm GmbH. 

Applicability: 

BO 105 C, BO 105 D, and BO 105 S helicopters, all variants as specified in 

Appendix 1 of this AD, all serial numbers, if equipped with Rolls Royce 

Corporation (formerly Allison, Detroit Diesel Allison) 250-C20 series engines, 

except helicopters that have been modified in accordance with ECD VTOL 

retrofit kit 105-80037. 

Reason: 

Several third stage turbine wheel failures have been reported on Rolls-Royce 

Corporation (RRC) 250 series engines. Investigation by RRC has determined 

that detrimental vibrations can occur within a particular range of turbine speeds, 

which are a potential contributing factor to these failures. 

This condition, if not corrected, could result in loss of engines power, possibly 

resulting in an emergency landing and consequent injuries to helicopter 

occupants. 

To address this unsafe condition, RRC issued Commercial Engine Bulletin 

(CEB) A-1400, now at Revision 3, to introduce an operational limitation to avoid 

engine N2 steady-state operation in a certain speed range (86.5% - 95.5%) for 

more than 60 seconds in single or cumulative events for engines with the third 

stage turbine wheel Part Number (P/N) 23065833 installed. 

In response, Eurocopter Deutschland (ECD) issued Alert Service Bulletin (ASB) 

BO105-60-110, now at Revision 1, to introduce the same operating limitation 

for BO 105 helicopters with the affected engines installed. 

For the reasons described above, this AD requires the introduction of a placard 

and the amendment of the Rotorcraft Flight Manual (RFM). 
EASA AD No : 2010-0128 

EASA Form 110 Page 2/3 

This AD is republished to correct paragraph (2), where the compliance time 

was missing. 

Effective Date: 07 July 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 30 days after the effective date of this AD, check both 

engines to verify whether a third stage turbine wheel P/N 23065833 is 

installed on the helicopter. This check can be accomplished through a 

maintenance records check, provided those records are sufficiently 

accurate to be relied upon for that purpose. 

(2) If the check as required by paragraph (1) of this AD indicates that a third 

stage turbine wheel P/N 23065833 is installed on the helicopter, within 30 

days after the effective date of this AD, accomplish the following actions 

concurrently: 

(2.1) Install a placard next to the triple RPM indicator, in full view of the 

pilot, as specified in, and in accordance with the instructions of, ECD 

ASB BO105-60-110: 

Min. Continuous 98% 

Min. Transient 95%

ASB BO105-60-110 

(2.2) Amend the RFM to incorporate the revision as referenced in 

Appendix 1 of this AD, as applicable to helicopter Model. 

(3) RRC no longer manufactures P/N 23065833 third stage turbine wheels. 

After modification of both engines on a helicopter by replacing the third 

stage turbine wheel P/N 23065833 with another P/N third stage turbine 

wheel in accordance with the instructions of paragraph 2.C.(1)(d) of RRC 

250-C20 Series CEB A-1400, the placard as required by this AD may be 

removed from that helicopter. 

Ref. Publications: 

Eurocopter Deutschland GmbH ASB BO105-60-110 Revision 1 dated 

03 March 2010. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Rolls-Royce Corporation 250-C20 Series CEB A-1400 Revision 3 dated 

19 January 2009. 

Remarks :

1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 25 May 2010 as PAD 10-051 for consultation until 

22 June 2010. No comments were received during the consultation period. 

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 

D-86607 Donauwörth, Germany 

Telephone: +49 (0)151-1422 8976; Facsimile: +49 (0) 906-71-4111. 
EASA AD No : 2010-0128 

EASA Form 110 Page 3/3 

Appendix 1 – BO 105 RFM Revisions 

Model Variants RFM Revision 

BO 105 C C23 (Europe), C-2 (USA) and CDN (Canada) 

BO 105 S CS (Europe) and CS-2 (USA) 

No.5 

BO 105 C CB (Europe), CB-2 (USA) and CDN-B (Canada) 

BO 105 S CBS (Europe), CBS-2 (USA) and CDN-BS (Canada) 

No.8 

BO 105 D DB and DBS (Europe) No.4