EASA AD No.: 2009-0272 

EASA Form 110 Page 1/3

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0272 

Date: 18 December 2009 

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 Anex 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]. 

Type 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 LBA Germany AD D-2005-233 dated 24 June 2005, EASA 

approval 2005-6109. 

ATA 62 Main Rotor – Sliding Sleeve – Pre-Flight Check Amendment 

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

Applicability: 

EC 135 P1(CDS), EC 135 P1(CPDS), EC 135 P2(CPDS), EC 135 T1(CDS), 

EC 135 T1(CPDS), EC 135 T2(CPDS) and EC 635 T1(CPDS) helicopters, all 

serial numbers. 

Note: This AD does not apply to EC 135 P2+, EC 135 T2+, EC 635 P2+ and 

EC 635 T2+ helicopters, as these have been certificated and delivered with 

the appropriate Rotorcraft Flight Manual (FLM) pre-flight check instructions. 

Reason: 

During two separate pre-flight checks on EC 135 helicopters in 2005, it was 

detected that one of the plain journal bearings of the sliding sleeve had moved 

to the outside of the sliding sleeve. 

This condition, if not detected and corrected, could lead to a complete shift of 

the plain journal bearing to the inside or outside, creating the possibility of a 

limited movement of the collective, which could result in reduced control of the 

helicopter. 

To address and correct this unsafe condition, the Luftfahrt-Bundesamt (LBA) 

of Germany issued AD D-2005-233 (EASA approval 2005-6109) to require an 

extension of the pre-flight check with the purpose of detecting any dislocated 

plain journal bearing in time, and corrective action, depending on findings. 

Since that AD was issued, Eurocopter Deutschland (ECD) has developed 

FLM revisions to incorporate the requirements of this AD. Consequently, this 

EASA AD retains the requirements of LBA AD D-2005-233, which is 
EASA AD No.: 2009-0272 

EASA Form 110 Page 2/3

superseded, and introduces an alternative method to comply, by amending 

the FLM with the appropriate revision that contains the AD requirements with 

regard to the pre-flight check procedures. 

Effective Date: 01 January 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before next flight after 24 June 2005 (the effective date of LBA AD 

D-2005-233), insert a copy of the FLM page which is attached to ECD 

Alert Service Bulletin (ASB) EC135-62A-021 into the applicable FLM. 

(2) Before next flight after the FLM amendment as required by paragraph (1) 

of this AD, and thereafter during each subsequent pre-flight check, 

visually check the position of the upper and lower plain journal bearings in 

the sliding sleeve to detect any dislocated plain journal bearings, in 

accordance with the instructions of the FLM page of ECD ASB EC135-

62A-021. 

Note: The actions required by paragraphs (1) and (2) of this AD can be 

accomplished by the pilot. 

(3) If, during any pre-flight check as required by paragraph (2) of this AD, the 

bushing is found not to be in its correct position, before further flight, 

contact ECD for approved corrective action instructions and accomplish 

those instructions accordingly. 

(4) Accomplishment of corrective actions does not constitute terminating 

action for the pre-flight checks as required by paragraph (2) of this AD. 

(5) Amending the applicable FLM to the appropriate revision level as 

indicated in Appendix I of this AD for each affected model, or a later 

approved revision, constitutes an alternative method to comply with the 

requirements of this AD. 

Ref. Publications: 

ECD ASB EC135-62A-021, Initial Issue dated 23 June 2005. 

Rotorcraft Flight Manual (FLM) revisions as listed in Appendix I of this AD. 

The use of later approved revisions of these documents 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 required actions and the risk allowance have granted the issuance of 

a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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 Deutschland GmbH, Industriestrasse 4, 86607 Donauwörth, 

Federal Republic of Germany 

Telephone: + 49 (0)151-1422 8976; Facsimile: + 49 (0)906-71 4111. 
EASA AD No.: 2009-0272 

EASA Form 110 Page 3/3

Appendix I 

The following Rotorcraft Flight Manual (FLM) Revisions, applicable to the individual rotorcraft 

model/variant (or a later approved revision) contain the pre-flight checks required by this AD, as part of 

the Section 4.3.2 “Exterior Check”: 

Model FLM Revision 

EC135 P1(CDS) Rev. 15 

EC135 P1(CPDS) Rev. 15 

EC135 P2(CPDS) Rev. 13 

EC135 T1(CDS) Rev. 18 

EC135 T1(CPDS) Rev. 19 

EC135 T2(CPDS) Rev. 9 

EC635 T1(CPDS) Rev. 19