EASA AD No : 2011-0193

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0193

Date: 05 October 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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 accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD unle ss otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agre ed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Type Approval Holder’s Name :

DASSAULT AVIATION Type/Model designation(s) : MYSTERE-FALCON 50 aeroplanes, MYSTERE-FALCON 900 and FALCON 900EX aeroplanes, FALCON 2000 and FALCON 2000EX aeroplanes
TCDS Number : EASA.A.008 and EASA.A.062

Foreign AD : Not Applicable

Supersedure : None



### ATA 57 Wings – Main Landing Gear Crashworthiness – Modification

Manufacturer(s): DASSAULT AVIATION

Applicability: Mystere-Falcon 50 aeroplanes (includ ing Falcon 50EX version), all serial numbers. Mystere-Falcon 900 and Falcon 900EX aeroplanes (inc luding Falcon 900DX version), all serial numbers, except those on which modification M5413 has been embodied. Falcon 2000 and Falcon 2000EX aeroplanes (including Falcon 2000DX version), all serial numbers, except those on which modification M3072 has been embodied.
Reason: In service experience has shown that, in ca se of main landing gear collapse due to overloads during take off or landing (e.g. during high-speed runway excursions), the wing tank structure can fail, lead ing to fuel spillage. Further analysis, using computer tools not available at tim e of the original certification, has established that the original co mpliance demonstration to JAR/FAR 25.721 was inadequate. This condition, if not corrected, could result, in case of main landing gear collapse, in a fuel spillage which may constitute a fire hazard. To address this unsafe condition, Dassault Aviation have developed a structural modification of the wing fuel tanks in t he area of the wheel wellEASA AD No : 2011-0193

EASA Form 110 Page 2/2 which introduces a dry bay by adding a sealed bound ary in front of the rear spar between ribs 4 and 5. For the reasons described above, this AD requires a ccomplishment of the above-mentioned modification for the Right Hand (RH ) and Left Hand (LH) wing fuel tanks.

Effective Date: 19 October 2011

Required action(s) and Compliance Time(s): Required as indicated unless previously accomplishe d: Within 150 months after the effective date of this AD, accomplish the modification of the RH and LH wing fuel tanks in ac cordance with the instructions of Service Bulletins (SBs) F50-496, SB F900-388, SB F900EX329, SB F2000-358 or SB F2000EX-171, as applicable to the aeroplane type. Note: The applicable SBs contain a training paragraph whi ch states that each person applying the SB must have successfully compl eted a training program.
Ref. Publications: Dassault Aviation Service Bullet in F50-496, initial issue dated October 22, 2009. Dassault Aviation Service Bulletin F900-388, initia l issue dated October 22, 2009. Dassault Aviation Service Bulletin F900EX-329, init ial issue dated September 25, 2009. Dassault Aviation Service Bulletin F2000-358, initi al issue dated September 25, 2009. Dassault Aviation Service Bulletin F2000EX-171, ini tial issue dated July 6, 2009. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 20 January 2011 as PAD 11- 002 for consultation until 17 February 2011. The Comment Response Docume nt can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact your Dassault Falcon Techni cal Assistance:

• For Europe, Middle East and Africa based operators : Hot Line: (33) 1 47 11 37 37

• For USA, Canada and Mexico based operators: Help Desk: (1) 800-2FALCON (2325266)

• All other areas: Help Desk: (1) 201 541 4747