EASA AD No : 2013-0262

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0262

Date: 30 October 2013

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 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 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].

Design Approval Holder’s Name :

DASSAULT AVIATION

Type/Model designation(s) :

Falcon 10 aeroplanes

TCDS Numbers: EASA.A.173

Foreign AD: Not applicable

Supersedure: None

ATA 27 Flight Control – Flap Structural Box – Inspection / Replacement

Manufacturer(s): Dassault Aviation (formerly Avions Marcel Dassault-Bréguet Aviation)

Applicability: Falcon 10 aeroplanes, all serial numbers

Reason: Cracks were found on two Falcon 10 aeroplanes on the inboard end plate (rib)

of the Right Hand (RH) inboard flap. On both aeroplanes the crack had initiated 

in the same area of the rib.

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

the rib and loss of integrity of the flap structure.

To address this potential unsafe condition, Dassault Aviation published Service 

Bulletin (SB) F10-318, which provides instructions for inspection of the affected 

area.

For the reasons described above, this AD requires a one-time inspection of the 

RH and Left Hand (LH) inboard flaps and, depending on findings, replacement

of the cracked part.

Effective Date: 13 November 2013
EASA AD No : 2013-0262

TE.CAP.00110-003 © 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) Within 65 days after the effective date of this AD, inspect the ribs n°1 and 

n°3 of the LH and the RH inboard flaps for cracks in accordance with the 

accomplishment instructions of Dassault Aviation SB Falcon 10 No 318.

(2) If, during the inspection as required by paragraph (1) of this AD, a crack is 

found, before next flight, replace the inboard flap with a serviceable flap

(free from cracks) in accordance with the instructions of Dassault Aviation 

SB Falcon 10 No 318.

Ref. Publications: Dassault Aviation SB Falcon 10 No 318.

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, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in this 

AD, please contact your Dassault Falcon Technical Assistance:

 For Europe, Middle East and Africa based operators:

Hot Line: (33) 1 47 11 37 37 / Fax: (33) 1 47 11 89 49.

 For USA, Canada and Mexico based operators:

Help Desk: (1) 800-2FALCON (2325266) / Fax: (1) 201 541 4740.

 All other areas:

Help Desk: (1) 201 541 4747 / Fax: (1) 201 541 4740.