EASA AD No.: 2012

- 0164

CAP.0011 0

- 001 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No: 201 2

- 0164

Date: 28 A ugust 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 accordan ce 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 :

Reims Aviation Industries Type/Model designation (s):

F406 aeroplanes

TCDS Number : EASA.A.109

Foreign AD: Not applicable

Supersedure : None



### ATA 27 Flight Controls

– Elevator Pushrod s

– Inspection / Replacement

Manufacturer s : Reims Aviation industries (RAI) , formerly Reims Aviation, S.A

.

Applicability: F406 aeroplane s , serial numbers (s/n) F406

- 0001 thru F406

- 0096

.

Reason: During maintenance, fretting has been found between the elevator pushrod assembly and horizontal tail structure on Reims F406 aeroplane s . In addition, bending w as found on a push rod assembly Part Number ( P/N ) 6015034

- 1

. The investigation has not yet established the exact cause(s) of these

occurrences

. This condition, i f not detected and corrected

, could lead to failure of a pushrod and consequent jamming of the elevator control s , possibly resulting in loss of control of the aeroplane

. For the reasons described above, t his AD requires inspection of the pushrods and horizontal tail structure to detect fretting, bending or eccentricity and

, depending on findings

, r eplacement with a serviceable p ushrod

, or repair

. This AD also requires the return on replaced pushrods to RAI for investigation.

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

Effective Date: 11 September 2012EASA AD No.: 2012

- 0164

CAP.0011 0

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

- Internet/Intranet. Required Action(s) and C ompliance Time(s) Required as indicated, unless accomplished previously:
(1) A t the next scheduled maintenance inspection or within 4 months, whichever occurs first after the effective date of this AD

, inspect push rod assemblies P/N 6015034

- 1 and horizontal tail structure in accord ance with the instructions of RAI S ervice B ulletin (SB) N ° F406

- 70

. (2) If

, during the inspection as required by paragraph (1) of this AD

, fretting (wear, chafing) is found on the structure, or the clearance between pushrod and structure is found to be insufficient, or looseness at riveted end fittings is found on the push rods , before next flight

, contact RAI Customer Support for approved repair instructions and accomplish th ose instructions accordingly

. (3) If

, during the inspection as required by paragraph (1) of this AD , bending or eccentricity of a pushrod is found, exceeding the limit as indicated in RAI SB N° F406

- 70, before next flight

, replace e ach affected push rod with

a serviceable part

. (4) Within 30 days after removal of a pushrod as required by paragraph (3) of this AD, return the removed rod to RAI for investigation

.

Ref. Publications: Reims Aviation Industries SB N° F406

- 70 dated 16 July 2012

. The use of later approved revisions of th i s document is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated

, EASA c an accept Alternati ve Methods of Compliance for this AD.

2. Based on t he 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 requirem ents in this AD, please contact: Reims Aviation Industries Aérodrome de Reims Prunay 51360 Prunay, FRANCE Telephone +33 3 26 48 46 65, Fax +33 3 26 49 18 57 E

- mail : Jn.sirot@reims

- aviation.fr

.