EASA AD No : 2010-0216-E

EASA Form 111 Page 1/3 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2010-0216-E

Date: 21 October 2010

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean Community, its Member States and of the European third countries that participat e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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 Sh ell –

Inspection / Replacement

Manufacturer(s): Eurocopter Deutschland GmbH (ECD), Eurocopter Hubschrauber GmbH, Messerschmitt-Bölkow-Blohm GmbH
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, debondi ng was found on the erosion protective shell of one of the main rotor b lades. Investigation showed that the reason for this debonding was incorrect in stallation of the erosion protective shell. This condition, if not corrected, could result in l oss of the erosion protective shell during flight, leading to unbalance of the ma in rotor and high vibrations which could cause damage to the helicopter. A detac hed erosion protective shell could damage the tail boom or tail rotor, pos sibly resulting in loss of tail rotor control, or fall away from the helicopter, po ssibly 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 s pecify a one-time inspection of the main rotor blades for correct ins tallation of the erosion protective shell. Consequently, EASA Proposed Airworthiness Directive (PAD) 10-095 was published, which proposed to require the accomplish ment of the inspection as outlined in the ECD ASB, as applicable to helicopte r 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 helicopt er has lost its erosion shell during (hover) flight which led to a precauti onary landing with no further damage. Prompted by this occurrence, ECD has publis hed Revision 1 to ASB BO105-10-124 and ASB-BO105LS-10-12 to reduce the fl ight hours for the one-time inspection from 50 to 10. For the reasons described above, this AD requires t he accomplishment of the inspection as outlined in the latest revision of th e ECD ASB, and corrective actions, depending on findings.

Effective Date: 23 October 2010

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (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 ro tor blades and determine whether any blades are installed on which the erosion protective shell has been replaced between Septembe r 2006 and March 2010. The affected main rotor blades are iden tified 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 i nspection for debonding of the erosion protective shell on the af fected main rotor blades in accordance with the instructions of ASB B O105-10-124 and ASB-BO105LS-10-12, as applicable to helicopter model. (2) If, during the inspection as required by paragr aph (1.2) of this AD, debonding is detected, replace the erosion protecti ve shell at the time indicated in, and in accordance with the instructio ns 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 is sue of ECD ASB BO105- 10-124 or ASB-BO105LS-10-12, as applicable to helic opter Model, are acceptable to comply with the requirements of parag raphs (1) and (2) of this AD. After the effective date of this AD, inspe ctions 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 inst all on any helicopter a main rotor blade on which the erosion protective shell h as been replaced between September 2006 and March 2010, identified i n 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 th is AD.

Ref. Publications: ECD ASB BO105-10-124 Revision 1 dated 18 October 2010.
ECD ASB-BO105LS-10-12 Revision 1 dated 20 October 2 010. The use of later approved revisions of these docume nts 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, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 03 September 2010 as PAD 1 0-095 for consultation until 01 October 2010. No comments wer e received during the consultation period. 3. Enquiries regarding this AD should be referred t o the AirworthinessEASA AD No : 2010-0216-E

EASA Form 111 Page 3/3 Directives, Safety Management & Research Section, C ertification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t 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