EASA AD No : 2010-0216-E 

EASA Form 111 Page 1/3 

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0216-E 

[Corrected: 29 October 2010] 

Date: 21 October 2010 

Note: This Emergency 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) : 

BO105 helicopters 

TCDS Number : EASA.R.011 

Foreign AD : Not applicable 

Supersedure : None 

ATA 62 Main Rotor – Main Rotor Blade Erosion Protective Shell – 

Inspection / Replacement 

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

Messerschmitt-Bölkow-Blohm GmbH, Messerschmitt-Bölkow-Blohm 

Helicopter Canada Limited 

Applicability: BO105 A, BO105 C, BO105 D, BO105 LS A-1, BO105 LS A-3 and 

BO105 S helicopters, all variants (except variants CB-5 and DBS-5), all serial 

numbers. 

Reason: During an inspection on a BO105 helicopter, debonding was found on the 

erosion protective shell of one of the main rotor blades. Investigation showed 

that the reason for this debonding was incorrect installation of the erosion 

protective shell. 

This condition, if not corrected, could result in loss of the erosion protective 

shell during flight, leading to unbalance of the main rotor and high vibrations 

which could cause damage to the helicopter. A detached erosion protective 

shell could damage the tail boom or tail rotor, possibly resulting in loss of tail 

rotor control, or fall away from the helicopter, possibly causing serious injuries 

to the persons on the ground. 

To address this unsafe condition, ECD has published Alert Service Bulletin 

(ASB) ASB BO105-10-124 and ASB-BO105LS-10-12 that specify a one-time 

inspection of the main rotor blades for correct installation of the erosion 

protective shell. 

Consequently, EASA Proposed Airworthiness Directive (PAD) 10-095 was 

published, which proposed to require the accomplishment of the inspection as 

outlined in the ECD ASB, as applicable to helicopter Model, and corrective 

action, depending on findings. 
EASA AD No : 2010-0216-E 

EASA Form 111 Page 2/3 

Since the issuance of EASA PAD 10-095, one helicopter has lost its erosion 

shell during (hover) flight which led to a precautionary landing with no further 

damage. Prompted by this occurrence, ECD has published Revision 1 to ASB 

BO105-10-124 and ASB-BO105LS-10-12 to reduce the flight hours for the 

one-time inspection from 50 to 10. 

For the reasons described above, this AD requires the accomplishment of the 

inspection as outlined in the latest revision of the ECD ASB, and corrective 

actions, depending on findings. 

This AD has been republished to add the manufacturer of (most of) the Model 

BO 105 LS A-3 helicopters, Messerschmitt-Bölkow-Blohm Helicopter Canada 

Limited. 

Effective Date: 23 October 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 10 flight hours, or 4 flight cycles, or 4 weeks, whichever occurs 

first after the effective date of this AD, accomplish the following actions: 

(1.1) Identify the Part Number (P/N) of the main rotor blades and 

determine whether any blades are installed on which the erosion 

protective shell has been replaced between September 2006 and 

March 2010. The affected main rotor blades are identified in ECD 

ASB BO105-10-124 and ASB-BO105LS-10-12. 

(1.2) If the installed main rotor blades match the conditions as specified 

in paragraph (1.1) of this AD, accomplish a one-time inspection for 

debonding of the erosion protective shell on the affected main rotor 

blades in accordance with the instructions of ASB BO105-10-124 

and ASB-BO105LS-10-12, as applicable to helicopter model. 

(2) If, during the inspection as required by paragraph (1.2) of this AD, 

debonding is detected, replace the erosion protective shell at the time 

indicated in, and in accordance with the instructions of, Chapter 14-2 of 

the applicable BO105 Maintenance Manual (MM). 

(3) Inspections and corrective actions accomplished prior to the effective 

date of this AD, in accordance with the original issue of ECD ASB 

BO105-10-124 or ASB-BO105LS-10-12, as applicable to helicopter 

Model, are acceptable to comply with the requirements of paragraphs (1) 

and (2) of this AD. After the effective date of this AD, inspections and 

corrective actions must be accomplished in accordance with ECD ASB 

BO105-10-124 at R1 or ASB-BO105LS-10-12 at R1, as applicable to 

helicopter Model. 

(4) From the effective date of this AD, do not install on any helicopter a main 

rotor blade on which the erosion protective shell has been replaced 

between September 2006 and March 2010, identified in ECD ASB 

BO105-10-124 or ASB-BO105LS-10-12, as applicable to helicopter 

Model, unless it has been inspected and, depending on findings, 

corrected in accordance with the requirements of this AD. 

Ref. Publications: ECD ASB BO105-10-124 Revision 1 dated 18 October 2010. 

ECD ASB-BO105LS-10-12 Revision 1 dated 20 October 2010. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

ECD MM BO105, MM BO105 LS A-1 and MM BO105 LS A-3 

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

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 03 September 2010 as PAD 10-095 for 
EASA AD No : 2010-0216-E 

EASA Form 111 Page 3/3 

consultation until 01 October 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