EASA AD No.: 2015-0159R1

TE.CAP.00110-004 © 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.: 2015-0159R1

Date: 24 August 2015

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 EU 748/2012, Part 21.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 operate 

an aircraft to which an AD applies, except in accordance with 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 AVIATION

Type/Model designation(s):

F 406 aeroplanes

TCDS Number: EASA.A.109

Foreign AD: Not applicable

Revision: This AD revises EASA Emergency AD 2015-0159-E dated 31 July 2015.

ATA 27 Flight Controls – Rudder Control Pedal Torque Tubes –

Inspection / Replacement

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

Applicability: F 406 aeroplanes, serial numbers 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 rudder was controlled using the co-pilot rudder pedals, 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, EASA issued Emergency AD 2015-0159-E 

to require inspection of the rudder control pedal torque tubes, both left-hand 

(LH) and right-hand (RH), and, depending on findings, replacement with a 

serviceable part. That AD also required inspection before installation of 

replacement rudder control pedal torque tubes.

Since that AD was issued, it was found that the Note which defines a 

‘serviceable part’ was not clear regarding new parts. Consequently, this 

revised AD amends the Note to provide clarity.

Effective Date: Revision 1: 24 August 2015

Original issue: 03 August 2015
EASA AD No.: 2015-0159R1

TE.CAP.00110-004 © 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 Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before next flight after 03 August 2015 [the effective date of the original 

issue of this AD], accomplish a visual inspection and a dye or 

fluorescent penetrant inspection of the rudder control pedal torque 

tubes, 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 inspections as required by paragraph (1) of this AD, no

crack is detected, within 100 flight hours after 03 August 2015 [the 

effective date of the original issue of this AD], accomplish a magnetic 

particle inspection of the rudder control pedal torque tubes, 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 03 August 2015 [the effective date of the original issue of this AD], 

it is allowed to install a replacement rudder control pedal 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: For the purpose of this AD, a serviceable part is a new rudder control 

pedal torque tube (never been installed on an aeroplane); or a rudder 

control pedal torque tube that has been previously installed on an aeroplane 

and that has passed a magnetic particle inspection in accordance with the 

instructions of ASI Aviation SB F406-104 part B.

Ref. Publications: 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. Based on the required actions and the compliance time, EASA have 

decided to issue 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, 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

E-mail: contact@asi-aviation.fr.