EASA AD No.: 2012-0131

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0131

Date: 31 July 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 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].

Design Approval Holder’s Name:

EUROCOPTER

Type/Model designation(s):

EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: None

ATA 62 Main Rotor – Main Rotor Hub Swashplates – Inspection / Replacement

Manufacturer(s) Eurocopter (formerly Eurocopter France).

Applicability: Eurocopter EC 225 LP helicopters, all serial numbers, with Main 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: The 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 requires repetitive inspections of the 

affected swashplates that could be corroded after a two years period of time and 

replacement of the MRH assembly in case a crack is found.

Effective Date: 03 August 2012
EASA AD No.: 2012-0131

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Required Action(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 

Table 1 of this AD, depending on the number of flight hours (FH) 

accumulated by the MRH assembly since new or since last Eurocopter 

Repair, as applicable, and thereafter at intervals 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 Alert Service Bulletin 

(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: If, during any inspection as required 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 operating in very cold weather conditions (outside air 

temperature (OAT) is below -30° Celsius): If, during any inspection as 

required by paragraph (1) of this AD, corrosion is found, accomplish the 

following actions:

(3.1) Before next flight, install a placard

“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) 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.

Concurrently, the placard and insertion in the flight manual as 

previously required by paragraph (3.1) of this AD can be removed 

from the helicopter and RFM.

(4) For helicopters not operating in very cold weather conditions: If, during 

any inspection as required 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 required by paragraph (3.2) or 

paragraph (4) of this AD, as applicable, does not constitute terminating 

action for the repetitive inspections required by paragraph (1) of this AD.

(6) From the effective date of this AD, do not install any MRH assembly on a 

helicopter, unless in compliance with the requirements of this AD.

Ref. Publications: Eurocopter ASB No. EC225-05A030 Revision 0 dated 12 July 2012.

The use of later approved revisions of this document is acceptable for 
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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 actions and the compliance time, EASA have decided 

to issue of a Final AD with Request for Comments, postponing the public 

consultation process 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 this 

AD, please contact: EUROCOPTER (STDI) – Aéroport de Marseille 

Provence 13725 Marignane Cedex, France,

Telephone +33 (4) 42 85 97 97; Facsimile +33 (4) 42 85 99 66;

E-mail: Directive.technical-support@eurocopter.com.