EASA AD No.: 2010-0208-E 

EASA Form 111 Page 1/3

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0208-E 

Date: 12 October 2010 

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 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 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]. 

Type Approval Holder’s Name : 

DASSAULT AVIATION 

Type/Model designation(s) :

Mystère-Falcon 50 aeroplanes 

TCDS Number : EASA.A.062 

Foreign AD : Not applicable 

Supersedure : None 

ATA 32 Landing Gear – Emergency Brake Installation – Inspection / 

Modification 

Manufacturer(s): Dassault Aviation 

Applicability: Mystère Falcon 50 and 50EX aeroplanes, all serial numbers 

Reason: On two occurrences on Mystère-Falcon 50 aeroplanes in service, it was 

detected that two pipes of the emergency brake system #2 located near the 

nose landing gear bearing were swapped. 

The swapping of these two pipes implies that when the Left Hand (LH) brake 

pedal is depressed, the Right Hand (RH) brake unit is activated, and 

conversely, when the RH brake pedal is depressed, the LH brake unit is 

actuated. This constitutes an unsafe condition, which may go unnoticed as 

the condition is latent until the emergency brake system #2 is used. This 

condition, if not corrected, could ultimately lead to a runway excursion of the 

aeroplane. 

For the reasons described above, this AD requires an inspection of the main 

landing gear braking system and, in case of findings, proper re-installation of 

the emergency brake system #2 pipes. This AD also requires painting the 

affected pipes for clear identification in order to avoid mistakes while reinstalling them after maintenance. 

Effective Date: 14 October 2010 
EASA AD No.: 2010-0208-E 

EASA Form 111 Page 2/3

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before next flight after the effective date of this AD, inspect the 

emergency brake system #2 in accordance with the procedure indicated 

in Appendix 1 of this AD. This inspection may be accomplished by the 

flight crew. Two crew members are necessary. 

(2) Alternately to the inspection required by paragraph (1) of this AD, before 

next flight after the effective date of this AD, inspect the emergency 

brake system #2 in accordance with the instructions of paragraph 2B 

(Section F50-515-1) of Dassault Aviation Service Bulletin (SB) F50-515. 

(3) Following the inspection as required by paragraph (1) or (2) of this AD, 

in case of incorrect installation of the emergency brake system #2, 

before next flight, install emergency brake system #2 pipes properly in 

accordance with the instructions of paragraph 2 B (4) (b) of Dassault 

Aviation SB F50-515. 

(4) Within 7 months after the effective date of this AD, paint the pipes end of 

the emergency brake system #2 and related unions in accordance with 

the instructions of paragraph 2 C of Dassault Aviation SB F50-515. 

Ref. Publications: Dassault Aviation SB F50-515 dated 11 October 2010. 

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 safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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

4. For any question concerning the technical contents 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. 
EASA AD No.: 2010-0208-E 

EASA Form 111 Page 3/3

APPENDIX 1 

Procedure for the inspection required by paragraph (1) of this AD 

Make sure the wheel chocks are in place and engines off 

First crewmember in cockpit (in the L/H seat): 

- Make sure that the park brake handle is released. 

- Energize the aircraft system ( BAT1 and BAT2 switches 

to ON; Battery power or Ground Power may be used) 

- Set Hydraulic Standby Pump switch to ON 

- On the hydraulic control panel, set "BRAKE" selector 

switch to the position “# 2 OFF”. 

- Fully apply brake pressure on L/H brake pedal only 

Second crewmember outside : 

- Check that the brake disks engage on the Left Main 

Landing Gear (MLG) (movement of the brake disks 

must be checked visually, with help of a flashlight) 

First crew member: 

- Set brake selector to “#1 ON” 

- Set hydraulic standby pump to OFF 

- De-energize the aircraft (BAT 1 and BAT2 to OFF) 

- PARK BRAKE intermediate detent 

(end of procedure)