EASA AD No.: 2015-0159-E

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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 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

Supersedure: None

ATA 27 Flight Controls – Rudder Control Pedal Torque Tubes – Inspection / 

Replacement

Manufacturer(s): ASI Aviation (formerly Reims Aviation Industries (RAI); 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, this AD requires 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.

This AD also requires inspection before new installation of rudder control pedal 

torque tubes.

Effective Date: 03 August 2015
EASA AD No.: 2015-0159-E

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Required Action(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

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 the effective date 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 the effective date of this AD, it is allowed to install a 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 rudder control 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 F406-104 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. 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, 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