EASA AD No.: 2015-0102-E 

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 1/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2015-0102-E 

Date: 08 June 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: 

DASSAULT AVIATION 

Type/Model designation(s): 

Falcon 2000EX aeroplanes 

TCDS Numbers : EASA.A.008 

Foreign AD : Not applicable 

Supersedure : None 

ATA 30 Ice and Rain Protection – Engine Air Inlet Anti-Ice System – Aircraft 

Flight Manual – Amendment 

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

Applicability: Falcon 2000EX aeroplanes, all manufacturer serial numbers. 

Reason: A quality review of recently delivered aeroplanes identified a manufacturing 

deficiency of some engine air inlet anti ice piccolo tubes. 

This condition, if not detected and corrected, could lead to reduced 

performance of the engine anti-ice protection system, with consequent ice 

accretion and ingestion, possibly resulting in dual engine power loss and 

reduced control of an aeroplane. 

The Falcon 2000EX Aircraft Flight Manual (AFM) contains a procedure 4-200-

05,”Operations in Icing Conditions”, addressing minimum fan speed rotation 

(N1) during combined operation of wing anti-ice and engine anti-ice systems. 

However, the AFM does not specify minimum N1 values for stand-alone engine 

anti-ice system operation. The subsequent investigation demonstrated that the 

operation of an engine at or above the minimum N1 value applicable for 

combined wing and engine anti-ice operations, provides efficient engine anti ice 

performance during stand-alone engine anti-ice operation for engines equipped 

with an air inlet affected by the manufacturing deficiency. 

For the reasons described above, this AD requires amendment of the 

applicable AFM which can be removed (or is not applicable) for aeroplanes 

having both engine air inlet marked “NRK” on the associated data plate. 

This AD is considered to be an interim measure and further AD action may 
EASA AD No.: 2015-0102-E 

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

follow. 

Effective Date: 10 June 2015 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 10 flight cycles after the effective date of this AD, amend the 

applicable AFM as specified in Appendix 1 of this AD, inform the flight crew 

and, thereafter, operate the aeroplane accordingly.

 Amending the AFM can be accomplished by inserting a copy of Appendix 1 

of this AD into the applicable AFM. 

(2) Aeroplanes which incorporate an engine air inlet, with a mark “NRK” on the 

associated data plate, on both engines, are not affected by the requirement 

of paragraph (1) of this AD. 

Note: Engine air inlets which were already refurbished and comply with the 

design standard are marked as “NRK” on the air inlet data plate. 

Ref. Publications: N/A 

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 your Dassault Falcon Technical 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 
EASA AD No.: 2015-0102-E 

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 3/3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Appendix 1 

Amendment to AFM sections 4-200-05, 4-200-05A OPERATION IN ICING CONDITIONS 

This amendment comes in additions to existing AFM procedures 

Engine Anti Ice System Operation 

During in flight operation of an engine anti-ice system (ENG ANTI-ICE) maintain the N1 of both engines

equal to or more then the values defined in Table 1 of this Appendix, as applicable to atmospheric 

condition. 

Table 1 

Minimum N1 values required during in flight operation of an engine anti-ice system 

TAT – Total Air Temperature 

Z - Altitude 

Note 1: Maintaining the N1 above the minimum anti-ice N1 on both engines may lead to exceedance of 

approach speed. Early approach or landing configuration of an aeroplane and/or application of airbrakes 

may be used to control the excessive airspeed. If, the airspeed remains higher than required, it is 

authorized to reduce the thrust by reducing the N1 below to values indicated in the Table 1 of this 

Appendix for the last 3 minutes before touchdown. In this case disengage Autothrottle, if previously 

engaged. This 3 minutes operation below the minimum N1 does not apply to any other in-flight icing 

situation. 

Note 2: During ground operations before take-off, the engine anti ice system remains efficient when 

engine power levers are at idle.