EASA AD No.: 2012

- 0 131

CAP.00110

- 001 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2012

- 0131

Date: 31 Ju ly 2012

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 ope rate 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].



### Design Approval Holder’s Name:

EUROCOPTER Type/Model designation(s):

EC 225 helicopters

TCDS Number: EASA.R.002

F oreign AD: Not applicable

Supersedure: N one



### ATA 6 2 Main Rotor

– Main Rotor Hub Swashplates

– 

### Inspect ion / Replacement

Manufacturer(s) Eurocopter (formerly Eurocopter France).

Applicability: Eurocopter EC 225 LP helicopters, all serial numbers, with M ain Rotor Hub (MRH) assembly equipped with rotating swashplate Part Number (P/N) 332A31

- 3074

- 00 or P/N 332A31

- 3076

- 00 and stationary swashplate P/N 332A31

- 3079

- 00 or P/N 332A31

- 3079

- 01, and one of which parts is installed on the MRH assembly since 2 years or more

.

Reason: T he presence of corrosion has been reported on the rotating and stationary swashplates of the MRH of several helicopters

.

This condition, if not detected and corrected, may
, over time

, cause the initiation of cracks on the swashplates with the potential of ultimate failure of those parts which would result in the loss of control of the helicopter

.

For the reasons described above, this AD require s repetitive i ns pection s of the affected swashplates that could be corro ded after a two years period of time and replacement of the MRH assembly in case a crack is found.

Effective Date: 0 3 August 2012EASA AD No.: 2012

- 0 131

CAP.00110

- 001 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously:
(1) After the effective date of this AD, within the compliance times specified in T able 1 of this AD, depending on the number of f light h ours (FH) accumulated by the MRH assembly since new or since last Eurocopter Repair, as applicable, and thereafter at interval s not to exceed 1 320 FH

, inspect the rotating and stationary swashplates in accordance with the instructions of paragraphs 3.B.1 to 3.B.4 of Eurocopter A lert S ervice B ulletin (ASB) No. EC225

- 05A030.

Table 1

– Initial inspection

Number of FH accumulated by the MRH assembly since new, or since last Eurocopter Repair Compliance Time

1 210 FH or more Within 110 FH after the effective of this AD

Less than 1 210 FH Upon accumulation of 1 320 FH

(2 ) For all helicopters : I f

, during any inspection as re quired by paragraph (1) of this AD

, a swashplate crack is found, before next flight, replace the MRH assembly with a serviceable assembly in accordance with the instructions of paragraph 3.B.5 of Eurocopter ASB No. EC225

- 05A030.
(3 ) For helicopters operat ing in very cold weather conditions ( ou tside air temperature (OAT) is below

- 30 ° C elsius ): I f

, during any inspection as

re quired by paragraph (1) of this AD

, corrosion is found

, accomplish the following actions:
(3 .1) B efore next flight, install a pl acard

“ NO FLIGHT IN OAT BELOW

- 30°C ”

in the full view of the pilots and insert such a Limitation in the Rotorcraft Flight Manual (RFM) of the helicopter

, and
(3 .2) W ithin 150 FH or 6 months after the inspection where the corrosion was first detected , whichever occurs first

, replace the MRH assembly with a serviceable assembly in accordance with the instructions of paragraph 3.B.5 of Eurocopter ASB No. EC225

- 05A030. Concurrently, the placard and insertion in the f light manual as
pre vio usly required by paragraph (3 .1) of this AD can be removed from the helicopter and RFM.
(4 ) For helicopters not operat ing in very cold weather conditions : I f

, during any inspection as req uired by paragraph (1) of this AD

, corrosion is found

, within 150 FH or 6 months after the inspection where the corrosion was first detected , whichever occurs first

, replace the MRH assembly with a serviceable assembly in accordance with the instructions of paragraph 3.B.5 of Eurocopter ASB No. EC225

- 05A030.
(5 ) Replacement of a MRH assembly as require d by paragraph ( 3 .2 ) or paragraph (4 ) of this AD, as applicable, does not constitute terminating action for the repetitive inspection s required by paragraph (1 ) of this AD

. (6) From the effective date of this AD, do not install any MRH assembly on a helicop ter, unless in complianc e with the requirements of this AD.

Ref. Public ations: Eurocopter ASB No. EC225

- 05A030 Revision 0 dated 12 Ju ly 2012

. The u se of later approved revisions of th i s document is acceptable forEASA AD No.: 2012

- 0 131

CAP.00110

- 001 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.

2. Based on the required act ions and the compliance time, EASA have decided to issue of a Final AD with Request for Comments, postponing the public consultation p rocess until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in t his AD, please contact: EUROCOPTER (STDI)

– Aéroport de Marseille Provence 13725 Marignane Cedex, France, T elephone +33 (4) 42 85 97 97; F acsimile +33 (4) 42 85 99 66; E

- mail: Directive.technical

- support@eurocopter.com

.