EASA AD No.: 2015

- 0159

- E

TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No

. : 2015

- 0159

- E

Date: 31 July 2015

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 E U 748/2012 , Part 2 1

. A.3B. In accordance with EU 1321/2014 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 wi th the requirements of that AD

, unless otherwise specified by the Agency [ EU 1321/2014 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:

ASI A VIATION Type/Model designation(s):

F 406 aeroplanes

TCDS Number: EASA.A.109

F oreign AD: Not applicable

Supersedure: None



### ATA 27 Flight Controls

– Rudde r Control Pedal Torque Tubes

– Inspection / Replacement

Manufacturer(s): ASI Aviation (formerly Reims Aviation Industries (RAI); Reims Aviation, S.A.)

Applicability: F 406 aeroplanes, serial number s from 0001 to 0098 inclusive

Reason: An occurrence was reported where one pilot rudder control pedal of an F 406 aeroplane detached in flight. No change in aeroplane attitude occurred. The

r udder was control led using the co

- pilot rudder pedal s, and the flight continued uneventfully until a safe landing was performed

. This condition, if not detected and corrected, could result in loss of directional control of the aeroplane. To address this unsafe condition, ASI Aviation issued Service Bulletin (SB) F406

- 104 to provide inspection instructions. For the reason described above, this AD requires inspection of the r udder

c ontrol p edal torque tube s, both left

- hand ( LH ) and right

- hand ( RH )

, and, depending on findings, replacement with a serviceable part.

T his AD also requires inspection before new installation of r udder c ontrol p edal torque tubes.

Effective Date: 03 August 2015EASA AD No.: 2015

- 0159

- E

TE. CAP.0011 1

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 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) Before next flight after the effective date of this AD, accomplish a visual i nspection and a dye or fluorescent penetrant inspect ion of the r udder

c ontrol p edal torque tube s, LH ( Part Number ( P/N ) 5115260

- 1 ) and RH ( P/N 5115260

- 2 ), in accordance with the instructions of ASI Aviation SB F406

- 104 part A. (2) If, during the inspection s as required by paragraph (1) of this AD, no crack is detected

, within 100 flight hours after the effective date of this A D, accomplish a magnetic particle inspection of the r udder c ontrol p edal torque tube s , LH ( P/N 5115260

- 1 ) and RH ( P/N 5115260

- 2 )

, in accordance with the instructions of ASI Aviation SB F406

- 104 part B

. (3) If, during any inspection as required by paragraph (1) or ( 2 ) of this AD, any crack is detected on a rudder control pedal torque tube , before next flight, replace the affected part with a serviceable part (see Note) in accordance with the instructions of ASI Aviation SB F406

- 104

. (4) From the effective date of this AD, it is allowed to install a r udder c ontrol p edal torque tube P/N 5115260

- 1 (LH ) or P/N 5115260

- 2 (RH ) on an aeroplane

, provided it is a serviceable part (see Note)

. Note : F or the purpose of this AD, a serviceable part is a r udder c ontrol pedal torque tube on which no cracks are found during accomplishment of a magnetic particle inspection in accordance with the instructions of ASI Aviation SB F406

- 10 4 part B.

Ref. Public ations: ASI Aviation SB F406

- 104 original issue dated 28 July 2015. 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 ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 3. Enquiries regarding this A D should be referred to the Safety Information 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: ASI Aviation Aérodrome de Reims Prunay 51360 Prunay, FRANCE Telephone +33 3 26 48 46 65 Customer Support Website: http://asi

- aviation.fr/asi

- aviation

- support/1.html