EASA AD No.: 2012-0085-E 

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 1/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0085-E

Date: 17 May 2012

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]. 

Design Approval Holder’s Name:

Eurocopter Deutschland GmbH

Type/Model designation(s):

EC 135 and EC 635 helicopters

TCDS Number: EASA.R.009 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2012-0041R1 dated 15 March 2012. 

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

Manufacturer(s): Eurocopter Deutschland GmbH (ECD), Eurocopter España S.A., 

Eurocopter S.A. 

Applicability: EC 135 P1(CDS), EC 135 P1(CPDS), EC 135 P2(CPDS), EC 135 P2+, 

EC 135 T1(CDS), EC 135 T1(CPDS), EC 135 T2(CPDS), EC 135 T2+, 

EC 635 T1(CPDS), EC 635 P2+ and EC 635 T2+ helicopters, all serial 

numbers. 

Reason: During a periodical inspection of an EC 135 helicopter, a crack was detected on 

the lower hub-shaft flange of a main rotor hub (MRH) shaft. 

The investigation is on-going and the cause of the cracking has not been 

determined yet. 

This condition, if not detected, could lead to further crack propagation, possibly 

resulting in main rotor hub failure and consequent loss of the helicopter. 

To address this condition, EASA issued AD 2012-0041-E. 

Since issuance of that AD, further cracks have been detected on the lower hub 

shaft flange of two other helicopters during accomplishment of the pre-flight 

checks. In addition, it has been determined that the identification of deformed 

safety pins may not be sufficient to detect the cracks on the MRH shaft. 

To address this condition, ECD developed new inspection procedures. 

For the reasons described above, this AD requires: 

Repetitive pre-flight visual inspections of the main rotor blades attachment area 

in the upper and lower hub-shaft flanges, and repetitive visual inspection on the 
EASA AD No.: 2012-0085-E 

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 2/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

upper and lower hub-shaft flanges and the blade bolt area. 

This AD also requires reporting of any findings to ECD. 

This AD is considered to be an interim action and further AD action may follow. 

Effective Date: 18 May 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished:

(1) Within 3 days after the effective date of this AD and thereafter, before 

each flight, accomplish a pre-flight visual inspection in accordance with 

the instructions of section 3.B.Part 1 of ECD Alert Service Bulletin (ASB) 

No. EC135-62A-029 Revision 1. 

The flight duration between 2 pre-flight inspections must not exceed 6 

Flight Hours (FH). 

Note: The repetitive pre-flight inspections of this AD may be 

accomplished by the flight crew or the pilot-owner in accordance with the 

provisions of Part M and Part 145. Compliance of each pre-flight 

inspection as required by paragraph (1) of this AD should be recorded in 

the log book of the helicopter. 

(2) Upon accumulation of 400 FH by the MRH since first MRH installation on 

a helicopter, or within 10 FH, whichever occurs later after the effective 

date of this AD, and, thereafter, at intervals not to exceed 10 FH, 

perform: 

a visual inspection of the upper and lower hub-shaft flanges in 

accordance with the instructions of section 3.B.Part 2 of ECD ASB No. 

EC135-62A-029 Revision 1, and 

a visual inspection of blade bolt area in accordance with section 3.B.Part 

3 of ECD ASB No. EC135-62A-029 Revision 1. 

(3) If, during any of the inspections required by paragraph (1) and (2) of this 

AD, cracks are detected, before next flight, replace the MRH with a 

serviceable unit. 

(4) Replacement of a MRH as required by paragraph (3) of this AD does not 

constitute terminating action for the repetitive inspections as required by 

paragraph (1) and (2) of this AD. 

(5) Within 1 week after replacement of the MRH as required by paragraph 

(3) of this AD, report the findings and send the removed MRH for further 

investigation to ECD. 

(6) From the effective date of this AD, do not install a MRH that has 

accumulated more than 400 FH since first installation on an helicopter 

unless it has successfully passed the inspections as required by 

paragraph (2) of this AD. 

Ref. Publications: Eurocopter Deutschland ASB No. EC135-62A-029 Revision 1, dated 16 May 

2012. 

The use of later approved revisions of this document is acceptable for 

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. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail:ADs@easa.europa.eu.
EASA AD No.: 2012-0085-E 

CAP.00111-001 © European Aviation Safety Agency. All rights reserved. 3/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

4. For any question concerning the technical content of the requirements in 

this AD, please contact Eurocopter Deutschland GmbH, 

Industriestrasse 4, 86607 Donauwörth, Federal Republic of Germany 

Telephone: + 49 (0)151-1422 8976; Facsimile: + 49 (0)906-71 4111.