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. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0102-E

Date: 08 June 2015

Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the E uropean Community, its Member States and of the European third countries that participat e in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 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 accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 manufa cturer serial numbers.

Reason: A quality review of recently delivered aero planes identified a manufacturing deficiency of some engine air inlet anti ice piccol o tubes. This condition, if not detected and corrected, coul d lead to reduced performance of the engine anti-ice protection syste m, 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) cont ains a procedure 4-200- 05,”Operations in Icing Conditions”, addressing min imum 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 investiga tion demonstrated that the operation of an engine at or above the minimum N1 v alue applicable for combined wing and engine anti-ice operations, provi des efficient engine anti ice performance during stand-alone engine anti-ice oper ation for engines equipped with an air inlet affected by the manufacturing def iciency. For the reasons described above, this AD requires a mendment of the applicable AFM which can be removed (or is not appl icable) for aeroplanes having both engine air inlet marked “NRK” on the as sociated data plate.
This AD is considered to be an interim measure and further AD action mayEASA AD No.: 2015-0102-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. follow.

Effective Date: 10 June 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 10 flight cycles after the effective dat e of this AD, amend the applicable AFM as specified in Appendix 1 of this A D, 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 inle t, with a mark “NRK” on the associated data plate, on both engines, are not aff ected by the requirement of paragraph (1) of this AD. Note: Engine air inlets which were already refurbis hed and comply with the design standard are marked as “NRK” on the air inle t data plate.

Ref. Publications: N/A

Remarks : 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The results of the safety assessment have indica ted the need for immediate publication and notification, without the full public consultation process. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification 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 4747EASA AD No.: 2015-0102-E

TE.CAP.00111-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

### Appendix 1 Amendment to AFM sections 4-200-05, 4-200-05A OPERA TION IN ICING CONDITIONS

This amendment comes in additions to existing AFM p rocedures

Engine Anti Ice System Operation During in flight operation of an engine anti-ice sy stem (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 N 1 values required during in flight operation of an en gine anti-ice system



### TAT – Total Air Temperature Z - Altitude

Note 1: Maintaining the N1 above the minimum anti-i ce N1 on both engines may lead to exceedance of approach speed. Early approach or landing configura tion of an aeroplane and/or application of airbrake s 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 previousl y 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, t he engine anti ice system remains efficient when engine power levers are at idle.