EASA AD No.: 2013-0103

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0103

Date: 02 May 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Design Approval Holder’s Name:
EUROCOPTER Type/Model designation(s): EC 225 LP helicopters

TCDS Number: EASA R.002

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2007-0180-E dated 29 June 2007.



### ATA 62 Main Rotor – Blade Leading Edge Protective S trip – Check

Manufacturer(s): Eurocopter

Applicability: EC 225 LP helicopters, all serial nu mbers, if equipped with Main Rotor Blades (MRB) Part Number (P/N) 332A11.0050.00 or P/N 332A1 1.0055.00 or P/N 332A11.0050.02 or P/N 332A11.0055.02, all serial nu mbers.

Reason: Significant de-bonding of the stainless ste el protective strip was found on a MRB installed on a helicopter. The initial investigation revealed rapidly progress ing de-bonding, which is suspected to be caused by water seepage through a c rack detected in the leading edge stainless steel protective strip. This condition, if not detected and corrected, coul d lead to loss of the MRB stainless steel protective strip resulting in exces sive vibrations induced by rotor blade weight unbalance and forced landing of the he licopter. To address this unsafe condition, Eurocopter issued Alert Service Bulletin (ASB) EC225 05A010 to provide instructions to check the MRB protective strip to detect any de-bonding. Consequently, EASA issued AD 2007-0180-E to require repetitive inspections of the MRB leading edge stainless steel protective strip, and depending on findings, accomplishment of applicable corrective a ction(s). Since that AD was issued, Eurocopter developed modi fication MOD 0740714, improving the MRB tip cap design by replacement of its leading edge stainless steel protective strip with new leading edge Nickel -Cobalt protective strip and resulting in re-identification of the modified MRB with a new P/N. MRB P/NEASA AD No.: 2013-0103

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 332A11.0050.00 or P/N 332A11.0055.00 modified in ac cordance with MOD 0740714 is re-identified as P/N 332A11.0050.02 or P /N 332A11.0055.02 respectively. Nevertheless, these MRB P/N 332A11.00 50.02 and P/N 332A11.0055.02 are still susceptible to de-bonding of the main leading edge stainless steel protective strip and therefore requ ire the same inspections to be applied. For the reasons described above, this AD retains th e requirements of EASA AD 2007-0180-E, which is superseded, but applies to an extended population of MRB P/N.

Effective Date: 07 May 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Initially, within the threshold specified in Ta ble 1 of this AD, as applicable to MRB P/N, and, thereafter, at intervals not to excee d 85 flight hours (FH), visually inspect and tap test the leading edge stai nless steel protective strip on each MRB in accordance with the instructions of paragraph 2.B of Eurocopter ASB EC225 05A010.

Table 1 Inspection Threshold

MRB P/N Compliance time

332A11.0050.00 and 332A11.0055.00 Within 15 FH after 03 July 2007 [the effective date of EASA AD 2007-0180-E]

332A11.0050.02 and 332A11.0055.02 Within 15 FH after the effective date of this AD

(2) If, during any visual inspection and tap test a s required by paragraph (1) of this AD, any of the conditions is found, as specifi ed in table 2 of this AD, within 15 FH after detection and, thereafter, at in tervals not to exceed 15 FH, tap test the affected area of the MRB leading e dge protective strip in accordance with the instructions of paragraph 2.B.2 .b or 2.B.2.c or 2.B.2.d, as applicable, of Eurocopter ASB EC225 05A010.

Table 2 – Possible discrepancies
Open de-bonding of blade leading edge, located outs ide the area D at the end of the blade main section on the blade tip cap side (see Figure 1 of Eurocopter ASB EC225 05A010), within the permi ssible criteria defined in Aircraft Maintenance Manual (MMA) Task 6 2-10-00-211. Cut in the blade root polyurethane protective strip and no de-bonding of the area (Figure 2 of Eurocopter ASB EC225 05A01 0). Crack of blade leading edge, within the permissible criteria defined in MMA Task 62-10-00-211.
(3) If, during any visual inspection or tap test as required by paragraph (1) or paragraph (2) of this AD, blind or open de-bonding or crack beyond the permissible criteria defined in MMA Task 62-10-00-2 11 is found on the leading edge stainless steel protective strip of a MRB, before next flight, replace the affected MRB with a serviceable part. (4) Replacement of a MRB, as required by paragraph (3) of this AD, with a serviceable part P/N 332A11.0050.00 or P/N 332A11.0 055.00 or P/N 332A11.0050.02 or P/N 332A11.0055.02 does not const itute terminating action for the repetitive inspections required by p aragraph (1) or (2) of this AD. (5) Inspections and corrective actions, accomplishe d before the effective date of this AD in accordance with the instructions of E urocopter ASB EC 225EASA AD No.: 2013-0103

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 05A010 at Revision 0 or Revision 1, are acceptable to comply with the requirements of paragraphs (1), (2) and (3) of this AD. After the effective date of this AD, inspections and corrective actions must be accomplished in accordance with the instructions of Eurocopter A SB EC225 05A010 at Revision 2 or later approved revisions. (6) From the effective date of this AD, installatio n of a MRB P/N 332A11.0050.00 or P/N 332A11.0055.00 or P/N 332A11. 0050.02 or P/N 332A11.0055.02 is allowed, provided the MRB is new or overhauled, or, before release to service of the helicopter, the MR B has passed the visual inspection and tap test of its leading edge stainle ss steel protective strip in accordance with the instructions of paragraph 2.B o f Eurocopter ASB EC225 05A010.

Ref. Publications: Eurocopter ASB EC225 05A010 at R evision 2 dated 22 April 2013. The use of later approved revisions of this documen t is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. Based on the required actions and the compliance time, EASA have decided to issue a Final AD with Request for Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive 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 (STDI) – Aéroport de Marseille Provence 13725 Marignane Cedex, France; telephone +33 (4) 42 85 97 97; facsi mile +33 (4) 42 85 99 66; E-mail: Directive.technical-support@eurocopter.com

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