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- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 1 2

- 0 156

Date: 23 August 201 2

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 Eu ropean 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 a n 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 Age ncy [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 2000 aeroplanes

TCDS Number: EASA.A. 008

Foreign AD: Not app licable

Supersedure: None



### ATA 05 Time Limits and Maintenance Checks

– Airworthiness Limitations

– Amendment / Implementation

Manufacturer(s): DASSAULT AVIATION

Applicability: Falcon 2000 aeroplanes

, all serial numbers

.

Reason: The airworthiness li mitations and maintenance requirements for the Falcon 2000 type design are included in Dassault Aviation Falcon 2000 (F2000) Aircraft Maintenance Manual (AMM) chapter 5

- 40 and are approved by the European Aviation Safety Agency (EASA). EASA issued AD 2008

- 0221 to require accomplishment of the maintenance tasks, and implementation of the airworthiness limitations, as specified in Dassault Aviation F2000 AMM chapter 5

- 40 at revision 1 2

. Since that AD was issued, Dassault Aviation have issued F2000 AMM chapter 5

- 40 at revision 17 , which introduces new or more restrictive maintenance requirements and/or airworthiness limitations.
Dassault Aviation AMM chapter 5

- 40 revision 17 contains among other changes the following requirements:

- Inspection and test of hori zontal stabilizer jackscrew ;

- O perational test of voltage monitoring circuits ;EASA AD No

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- Internet/Intranet. - Upgrade of screwjack of flap actuators from the older to the latest

- 3 version;

- Revised Time Between Overhaul for screwjack of flap actuators

- 3 version;

- Revised inte rval for checking the screw / nut play on screwjack of flap actuators

- 3 version;

- Removal of service life limit for screwjack of flap actuators;

- Test of flap asymmetry protection system. Compliance with the flap asymmetry test is required by DGAC Fra nce AD F

- 1999

- 038

- 008(B)R1. F2000 AMM chapter 5

- 40 at revision 17 introduces extended inspection interval;

- Inspection procedures of fuselage and wings;

- Check of overpressure tightness on pressurization control regulating v alves. Compliance with this check is required by EASA AD 2008

- 0072. F2000 AMM chapter 5

- 40 at revision 17 introduc es extended inspection interval. The maintenance tasks and airworthiness limitations, as specified in the F2000 AMM chapter 5

- 40, have been identified as mandatory action s for continued airworthiness of the F2000 type design. Failure to comply with AMM chapter 5

- 40 at revision 17 might constitute an unsafe condition. For the reasons described above, this AD requires the implementation of the maintenance tasks and airworthi ness limitations, as specified in Dassault Aviation F2000 AMM chapter 5

- 40 at revision 17

.

Effective Date: 06 September 2012

Required A ction(s) and Compliance Time(s): Required as indicated, unless previously accomplished: (1) After the effective date of this AD, accomplish the following actions, as specified in Dassault Aviation F2000 AMM chapter 5

- 40 at r evision 17 : (1.1) Replace each component before or upon reaching the applicable life limit, and (1.2) Within the thresholds and intervals, accomplish a ll applicable maintenance tasks. (2) In case of finding discrepancies (as defined in Dassault Aviation F2000 AMM Chapter 5

- 40) during any inspection as required by paragraph (1) of this AD, within the applicable compliance time specified in Dassault Aviati on F 200 0 AMM Chapter 5

- 40, accomplish the applicable maintenance procedures for corrective actions in accordance with approved maintenance documentation. If no compliance time is identified in the F2000 AMM Chapter 5

- 40, accomplish the applicable correctiv e actions before next flight. If a detected discrepancy is not identified in Dassault Aviation AMM chapter 5

- 40 at Revision 17 , before next flight, contact Dassault Aviation for approved instructions and accomplish those instructions accordingly. (3) Compl iance with the requirements of paragraphs (1) and (2) of this AD

can be demonstrated by: (3.1) Revising as follows, unless accomplished previously, the approved Aircraft Maintenance Programme (AMP) on the basis of which the operator or the owner ensures th e continuing airworthiness of each operated aeroplane:
Incorporate all airworthiness limitations

, maintenance tasks

, applicable thresholds and intervals specified in Dassault Aviation AMM chapter 5

- 40 at Revision 17

,

a nd (3.2) Complying with the approved AMP described in paragraph (3.1) ofEASA AD No

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- Internet/Intranet. this AD. (4) Compliance with the requirements of paragraphs (1) and (2) of this AD, or as specified in paragraph (3) of this AD, is acceptable to comply with the requirements of the following ADs:

DGAC France AD 1999

- 0 38

- 008(B)R1

, EASA AD 2008

- 0072 and EASA AD 2008

- 0221

.

Ref. Publications: Dassault Aviation Falcon 2000 A M M C hapter 5

- 40 at Revision 17 (DGT 113876)

. 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. This AD was posted on 10 July 2012 as PAD 1 2

- 0 75 f or consultation until 07 August 2012

. No comments we re received during the consultation period

. 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 conte nt 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 operator s: Help Desk: + 1 800

- 2FALCON (2325266) / Fax: + 1 201 541 4740

All other areas : Help Desk: +1 201 541 4747 / Fax: + 1 201 541 474 0

.