# Dassault Service Bulletin F2000EX-393: No revision named

- Rights: © Dassault Aviation. Filed by the FAA in regulations.gov docket FAA-2017-0494; AD 2017-19-17 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Dassault Service Bulletin F2000EX-393](https://openairdocs.org/service-documents/dassault/f2000ex-393.md)
- Title as filed: SB F2000EX-393
- Pages: 22
- PDF: https://openairdocs.org/files/sha256/5c/a7/5ca74d8740a54e39a4b895355763f6f96078008d4cb11faa2816e140c6199ae6
- Page: https://openairdocs.org/service-documents/dassault/f2000ex-393/file/5ca74d8740a5

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

FALCON 2000LXS
FALCON 2000S
No 393
JUNE 20, 2016
MANDATORY
ATA 30-14
ICE AND RAIN PROTECTION
INSPECTION OF WING ANTI-ICE PIPES
FALCON SERVICE BULLETIN
Copyright © 2016 by Dassault Aviation
All rights reserved. No part of this work may be reproduced or copied
in any form or by any means without written permission
of Dassault Aviation.
671

### Page 2

ICE AND RAIN PROTECTION
INSPECTION OF WING ANTI-ICE PIPES
Initial issuance June 20, 2016
List of effective pages :
1 to 18
FALCON 2000EX F2000EX -393
F2000EX -30-14

### Page 3

ICE AND RAIN PROTECTION
INSPECTION OF WING ANTI-ICE PIPES
 
1. PLANNING INFORMATION
A. EFFECTIVITY
This Service Bulletin is applicable to:
• F2000EX aircraft with serial numbers 263 through 305, 307 through 313, 315, 320 (F2000LXS),
• F2000EX aircraft with serial numbers 701 through 734 (F2000S).
B. REASON
Production line investigation revealed that a Falcon 900EX wing anti-ice pipe had been wrongly
installed on a Falcon 2000EX aircraft, due to an improper part identification.
In worst case scenario, such a situation could impact the performance of the wing anti-icing system.
The purpose of this Service Bulletin is to verify proper labeling and correct configuration of those anti-
ice pipes.
C. DESCRIPTION
This Service Bulletin is divided into two sections:
SECTION F2000EX-393-1: The operation consists in:
• Inspecting the internal geometry of left and right, inboard and outboard wing anti-ice pipes,
• Replacing the anti-ice pipe labels if incorrect.
SECTION F2000EX-393-2 : The operation consists in replacing the wing anti-ice pipe(s) in case of
incorrect geometry configuration.
D. COMPLIANCE
Mandatory:
• It is anticipated that this Service Bulletin will be rendered mandatory by an EASA Airworthiness
Directive.
• As prescribed by the Airworthiness Authorities of the country of registration of the aircraft.
E. APPROVAL
The technical content of this document is approved under the authority of DOA nr. EASA.21J.051.
F. LABOR
Estimated labor-hours: Refer to Service Bulletin Commercial Summary.
NOTE 1: The leak check of the wing anti-icing system is to be performed during engine run-up.
NOTE 2: These labor-hours only concern the work described in this Service Bulletin and do not
include other maintenance work that may be performed on this occasion.
FALCON 2000EX F2000EX -393
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DASSAULT AVIATION Proprietary Data

### Page 4

G. MATERIAL - PRICE AND AVAILABILITY
The modification kit may be obtained from either address listed below:
Western hemisphere: DASSAULT FALCON JET CORP.
SPARES DISTRIBUTION CENTER
200 RISER ROAD
LITTLE FERRY, NJ 07643 U.S.A.
Telephone:
• CANADA and U.S.A.: 1-800-800-4036
• MEXICO: 001-800-800-4036
• Other countries: 1-201-541-4809
Fax:
• CANADA and U.S.A.: 1-800-800-4817
• MEXICO: 001-800-800-4817
• Other countries: 1-201-440-7021
Other continents: DASSAULT AVIATION
Falcon Spares
BOITE POSTALE N°101
AEROPORT DU BOURGET
93350 - LE BOURGET Cedex (FRANCE)
Please contact your Dassault Aviation
Account Representative
Telephone: 33 (0)1.48.35.56.78
Fax: 33 (0)1.48.35.56.00
E/H dafsorder@dassault-aviation.com
Price and availability on request.
H. TOOLING - PRICE AND AVAILABILITY
Normal maintenance tooling.
Endoscope with a rotating head that must be 1-meter long (39.37 in).
Teflon wedge 7 (0.27 in) to 8 mm (0.31 in) thick.
I. WEIGHT AND BALANCE
Change in weight: None.
Change in balance with respect to 25% MAC: None.
J. ELECTRICAL LOAD ANALYSIS
Before: None
After: None
K. REFERENCES
Illustrated Parts Catalog:
FALCON 2000EX F2000EX -393
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### Page 5

• (Refer to IPC fig. 30-11-10-20)
Aircraft Maintenance Manual:
• GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801)
• BASIC SEALING METHODS (Refer to TASK 20-32-00-390-801)
• FUNCTIONAL TEST OF THE SLATS (Refer to TASK 27-80-00-720-801)
• LEAK CHECK OF THE WING ANTI-ICING SYSTEM (Refer to TASK 30-10-00-790-801)
• REMOVAL / INSTALLATION OF THE INBOARD SLATS (Refer to TASK 57-45-01-900-801)
• EXTERNAL ACCESSES (Refer to SDS 06-35-00)
L. OTHER PUBLICATIONS AFFECTED
None.
FALCON 2000EX F2000EX -393
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### Page 6

2. SECTION F2000EX-393-1 - INSPECTION OF THE LEFT AND RIGHT ANTI-ICE PIPES
The work to be done is described in the figures for the left side only. Operations are symmetrical for the RH
side.
A. PRELIMINARY STEPS
Refer to fig. 1.
(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801).
(2) On the left side, remove (Refer to SDS 06-35-00):
• wing root lower access door ( 143BL),
• wing root upper access door ( 251CL),
• wing lower surface inboard leading edge access panel ( 512BB),
• wing lower surface outboard leading edge access panel No. 1 ( 522AB),
• anti-ice pipe (c-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 320),
• thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
(3) On the right side, remove (Refer to SDS 06-35-00):
• wing root lower access door ( 144BR),
• wing root upper access door ( 252CR),
• wing lower surface inboard leading edge access panel ( 612BB),
• wing lower surface outboard leading edge access panel No. 1 ( 622AB)
• anti-ice pipe (c-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 320),
• thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
(4) On both sides, disassemble the WOF connector (e-fig. 1)  (Refer to IPC fig. 30-11-10-20  , item
993):
(a) Remove the lock-wire,
(b) Loosen the connector and open it,
(c) Put aside washers and seals (f-fig. 1) to allow accessibility to anti-ice pipes interface.
B. INSPECTION OF LEFT AND RIGHT ANTI-ICE PIPES
Refer to fig. 2, fig. 3 and fig. 4
CAUTION: PRECAUTIONS TO BE TAKEN FOR THE INSPECTION:
• USE A ROTATING HEAD ENDOSCOPE THAT MUST BE 1-METER LONG (39.37
IN) (A-FIG. 2).
• USE A TEFLON WEDGE (B-FIG. 2) 7 (0.27 IN) TO 8 MM (0.31 IN) THICK TO
SEPARATE ANTI-ICE PIPES.
• USE A FLEXIBLE PLASTIC PROTECTION AROUND ENDOSCOPE FIBRE ( FIG.
2) TO PROTECT ANTI-ICE PIPE EDGES AND ENDOSCOPE.
(1) Introduce the endoscope head inside the left inboard anti-ice pipe and check the presence of a
diaphragm in the inboard and outboard anti-ice pipes (fig. 3):
LEFT INBOARD ANTI-ICE PIPE LEFT OUTBOARD ANTI-ICE PIPE
F2MG725103300A1 F2MG725103100A1
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DASSAULT AVIATION Proprietary Data

### Page 7

(a) If there is no diaphragm, proceed with SECTION F2000EX-393-2 for applicable anti-ice pipe
replacement.
(b) If there is a diaphragm, check the anti-ice pipe part number ( fig. 4):
1 if the anti-ice pipe is correctly identified, using a marker, write a "C" like "Check"
between the serial number and the part number on each anti-ice pipe, put a control
stamp and apply a coat of varnish on them.
2 if the anti-ice pipe is not correctly identified, replace the identification label.
(2) Repeat the same operations on the right side to check right inboard and outboard anti-ice pipes:
RIGHT INBOARD ANTI-ICE PIPE RIGHT OUTBOARD ANTI-ICE PIPE
F2MG726103300A1 F2MG726103100A1
C. FINAL STEPS
(1) Safety the WOF connector coupling (e-fig. 1) with lockwire MS20995C32.
(2) On the left side, install (Refer to SDS 06-35-00):
• thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
• anti-ice pipe (c-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 320),
• wing lower surface outboard leading edge access panel No. 1 ( 522AB),
• wing lower surface inboard leading edge access panel ( 512BB),
• wing root upper access door ( 251CL),
• wing root lower access door ( 143BL),
(3) On the right side, install (Refer to SDS 06-35-00):
• thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
• anti-ice pipe (c-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 320),
• wing lower surface outboard leading edge access panel No. 1 ( 622AB)
• wing lower surface inboard leading edge access panel ( 612BB),
• wing root upper access door ( 252CR),
• wing root lower access door ( 144BR),
(4) Perform a leak check of the wing anti-icing system (Refer to TASK 30-10-00-790-801).
D. RECORDING
Record compliance with this Service Bulletin in the appropriate aircraft documents.
Fill out the card located at the end of the Service Bulletin and mail or fax it to Dassault Aviation or
Dassault Falcon Jet, or fill out the electronic Service Bulletin reply form located in the ”Service Bulletin"
page on the Falcon portal.
FALCON 2000EX F2000EX -393
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DASSAULT AVIATION Proprietary Data

### Page 8

3. SECTION F2000EX-393-2 - REPLACEMENT OF THE ANTI-ICE PIPE
The work to be done is described in the figures for the left side only. Operations are symmetrical for the RH
side.
Refer to fig. 5, fig. 6, fig. 7, fig. 8 and fig. 9
A. PRELIMINARY STEPS
(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801).
(2) To remove left inboard or outboard anti-ice pipe, remove (Refer to SDS 06-35-00):
• remove the LH inboard slat (Refer to TASK 57-45-01-900-801),
• wing inboard leading edge access panel ( 512BT),
• wing middle leading edge access panel (522AT),
• wing root upper access door ( 251CL).
(3) To remove right inboard or outboard anti-ice pipe, remove (Refer to SDS 06-35-00):
• remove the RH inboard slat (Refer to TASK 57-45-01-900-801),
• wing inboard leading edge access panel ( 612BT),
• wing middle leading edge access panel (622AT),
• wing root upper access door ( 252CR).
B. GENERAL STRUCTURAL WORK INSTRUCTIONS
(1) Obey the Structural Repair Manual and Standard Practices procedures for the following operation:
• basic sealing methods (Refer to TASK 20-32-00-390-801).
C. PROCEDURE
(1) Removal of the anti-ice pipe
(a) Remove thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
(b) To replace the inboard anti-ice pipe, separate the pipe from the anti-ice pressure switch (d-
fig. 8).
(c) Depending on the pipe to be replaced, remove the Detampel support protectors ( fig. 6 and 
fig. 7).
(d) Remove the inboard or outboard pipe to be replaced ( fig. 5).
(2) Installation of the pipe
(a) Depending on the pipe to be replaced, put pipe on Detampel supports and align it with the
others anti-ice pipes.
NOTE: Check that the clearance between pipe and pumps is 0.20 in ± 0.06 in (5 mm ± 1.5
mm).
(b) Secure pipe with sleeve clamps (16-fig. 7) (except detail A fig. 6 ) with protect strip
(47212A50D7127) at the location of ceramic sections (fig. 7).
(c) Lock all sleeve clamps on Detampel supports with lock-wire (EN2573U56-080) and coat the
end of lock-wire and the end of sleeve clamp flex strips with sealant (fig. 6 and fig. 7).
(d) Check clearances at the anti-ice pipe in accordance with fig. 9.
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DASSAULT AVIATION Proprietary Data

### Page 9

(e) Attach inboard anti-ice pipe, if replaced, to anti-ice pressure switch (d-fig. 8).
(f) Install the Detampel support protectors ( fig. 6 and fig. 7).
(g) Install thermal protector (d-fig. 1) (Refer to IPC fig. 30-11-10-20 , item 985).
D. FINAL STEPS
(1) Install the LH inboard slat or RH inboard slat (Refer to TASK 57-45-01-900-801)
(2) Perform a leak check of the wing anti-icing system (Refer to TASK 30-10-00-790-801).
(3) Perform a functional test of the slats (Refer to TASK 27-80-00-720-801) paragraph "Test of slats
in normal mode").
(4) If removed, install (Refer to SDS 06-35-00):
• wing root upper access door ( 251CL).
• wing middle leading edge access panel (522AT),
• wing inboard leading edge access panel ( 512BT)
(5) If removed, install (Refer to SDS 06-35-00):
• wing root upper access door ( 252CR).
• wing middle leading edge access panel (622AT),
• wing inboard leading edge access panel ( 612BT),
E. RECORDING
Record compliance with this Service Bulletin in the appropriate aircraft documents.
Fill out the card located at the end of the Service Bulletin and mail or fax it to Dassault Aviation or
Dassault Falcon Jet, or fill out the electronic Service Bulletin reply form located in the ”Service Bulletin"
page on the Falcon portal.
FALCON 2000EX F2000EX -393
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DASSAULT AVIATION Proprietary Data

### Page 10

4. MATERIAL INFORMATION
NOTE: Compliance with this Service Bulletin by substituting the part numbers below with interchangeable
subsequent part numbers is acceptable, provided the subsequent part numbers have the same
effectivity as the original part number.
A. MODIFICATION KIT
Kit P/N SBF900EX0464A - Identification of anti-ice pipes
Kit P/N SBF900EX0464A
NEW P/N QTY KEY WORD COMMENTS
KIT-ETIQ-
SBF900EX0464A 1
1 kit including:
- Left inboard anti-ice pipe identification label «FGFB725103100B1» Not used
- Left inboard anti-ice pipe identification label «FGFB726103100B1» Not used
- Left inboard anti-ice pipe identification label «FGFB725103300» Not used
- Left inboard anti-ice pipe identification label «FGFB726103300» Not used
- Left outboard anti-ice pipe identification label «F2MG725103100A1»
- Right outboard anti-ice pipe identification label «F2MG726103100A1»
- Left inboard anti-ice pipe identification label «F2MG725103300A1»
- Right inboard anti-ice pipe identification label «F2MG726103300A1»
Kit P/N SBF900EX0464B - Anti-ice pipe replacement
NOTE: Kit for one side (left or right)
Kit P/N SBF900EX0464B
NEW P/N QTY KEY WORD
ITEM
FIG
W991-24CE 3 Clip - (1-fig. 5) -
W932-24B 6 Seal - (2-fig. 5) -
78644C032052H 6 Sleeve clamp - (16-fig. 7) -
47212A50D7127 7 Protect strip - (4-fig. 6) -
78644C047067H 1 Sleeve clamp - (3-fig. 6) -
NAS673V3XF 7 Screw - (17-fig. 6) -
NAS1149D0316K 8 Washer - (8-fig. 6), (8-fig. 7) -
33491DG048A 7 Washer - (18-fig. 6) -
HW17-3DF 8 Nut - (10-fig. 6), (10-fig. 7) -
NAS673V1XF 5 Screw - (5-fig. 6) -
FALCON 2000EX F2000EX -393
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DASSAULT AVIATION Proprietary Data

### Page 11

Kit P/N SBF900EX0464B
NEW P/N QTY KEY WORD
ITEM
FIG
NAS1149D0363K 5 Washer - (6-fig. 6) -
NAS9203-1 0 1 Screw - (7-fig. 7) -
78654-04 1 Sleeve Clamp - (9-fig. 7) -
NAS1149D0363K 1 Washer - (11-fig. 7) -
NAS673V5XF 1 Screw - (12-fig. 7) -
NAS517V3-2XF 2 Screw - (13-fig. 7) -
AN815-4JFAB 1 Tube Fitting - (14-fig. 8) -
F50B721400003 1 Washer - (15-fig. 8) -
EN2573U56-080 500 mm
(19.69 in.)
Lock-wire
Kit P/N SBF2000X0393A - Replacement of left outboard anti-ice pipe
NEW P/N QTY KEY WORD
F2MG725103100A1 1 Left outboard anti-ice pipe
Kit P/N SBF2000X0393B - Replacement of right outboard anti-ice pipe
NEW P/N QTY KEY WORD
F2MG726103100A1 1 Right outboard anti-ice pipe
Kit P/N SBF2000X0393C - Replacement of left inboard anti-ice pipe
NEW P/N QTY KEY WORD
F2MG725103300A1 1 Left inboard anti-ice pipe
Kit P/N SBF2000X0393D - Replacement of right inboard anti-ice pipe
NEW P/N QTY KEY WORD
F2MG726103300A1 1 Right inboard anti-ice pipe
B. LOCAL PROCUREMENT
As indicated in Consumable Products Manual (CPM):
• O-ring (BA4709-6) - Quantity = 2 (19-fig. 1), (19-fig. 5).
• vinyl varnish.
• lockwire
FALCON 2000EX F2000EX -393
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DASSAULT AVIATION Proprietary Data

### Page 12 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
143BL / 251CL
522AB
512BB
WOF connector
Thermal protector  Anti-ice pipe
O-Ring
Figure 1: SECTION 2000EX-393-1 - ACCESS FOR INSPECTION
June 20, 2016  F2000EX -30-14
Initial issuance  Page 10 / 18

### Page 13 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
Rotating head endoscope
Teflon wedge,
7 to 8 mm thick
Introduce endoscope head inside inboard anti-ice pipe
to check presence of diaphragm
Figure 2: SECTION 2000EX-393-1 - INSPECTION OF DIAPHRAGM
June 20, 2016  F2000EX -30-14
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### Page 14 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
→Ø 1.5 in
(38.4 mm)
Diaphragm at 5.90 in (150 mm) from
the pipe entrance
5.90 in  5.90 in
(150 mm)  (150 mm)
Diaphragm at the external
pipe entrance
→Ø1 in
(26 mm)
If there is no diaphragm, replace the anti-ice pipe
Figure 3: SECTION 2000EX-393-1 - INSPECTION OF DIAPHRAGM
June 20, 2016  F2000EX -30-14
Initial issuance  Page 12 / 18

### Page 15 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
2005Ố(
00 A  FiNG A/ICE  - Serial number
FAR  MULT:
25856(1) PVH46551
522AB  /ING AICE
F2MG  - Part number
725101
512BB
Direct access by the lower doors
Left side
Inboard anti-ice pipe  Outboard anti-ice pipe
Figure 4: SECTION 2000EX-393-1 - INSPECTION OF ANTI-ICE PIPE IDENTIFICATION
June 20, 2016  F2000EX -30-14
Initial issuance  Page 13 / 18

### Page 16

Figure 5: SECTION 2000EX-393-2 - REPLACEMENT OF ANTI ICE PIPES
FALCON 2000EX F2000EX -393
June 20, 2016 F2000EX -30-14
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### Page 17 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
G
All Detampel supports are attached with:
screw
8) washer under screw head
18) washer under nut
10  ) nut with sealant
F2MG131/141000153A1
Cut 5 notches  Attach with:  ) ХЗ
and eliminate sharp edge  F50B131/141000181
X2
X2
B
Figure 6: SECTION 2000EX-393-2 - REPLACEMENT OF ANTI ICE PIPES
June 20, 2016  F2000EX -30-14
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### Page 18 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
6) X6
C) FGFB132142020A1
Attach with: (12
Locking for this sleeve clamp only
) X2 (with sealant)
Figure 7: SECTION 2000EX-393-2 - REPLACEMENT OF ANTI ICE PIPES
June 20, 2016  F2000EX -30-14
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### Page 19 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
Pressure switch 8G1199-5
Figure 8: SECTION 2000EX-393-2 - REPLACEMENT OF ANTI ICE PIPES
June 20, 2016  F2000EX -30-14
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### Page 20 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 2000EX  F2000EX -393
LOCATION
Location  Minimal Gap  Picture
Front Spar
Gap between anti-ice pipes
F2MG725/726103100A1 or  0.27 in
FGFB725/726103100B1 and  7 mm
rod TAC R21057
Front Spar - between ribs 6 and 7
Gap between rod attachment pin TAC
R21057/FGFB171104 and anti-ice pipes  0.23 in
F2MG725/726103100A1 or  6 mm
FGFB725/726103100B1
Front Spar
Gap between deflector F50B132/142020A1
and rod FGFB171105  0.11 in
3 mm
Figure 9: SECTION 2000EX-393-2 - GAP CHECK
June 20, 2016  F2000EX -30-14
END OF DOCUMENT
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### Page 21 (OCR)

NO POSTAGE
NECESSARY
FROM  IF MAILED
IN THE
UNITED STATES
ZIP CODE
BUSINESS REPLY MAIL
FIRST CLASS MAIL PERMIT NO. 3306 HACKENSACK, NJ 07602
POSTAGE WILL BE PAID BY ADDRESSEE:
DASSAULT FALCON JET CORP.
PO BOX 1946
SO HACKENSACK NJ 07606-9946
ATTENTION:
FIELD SERVICE DEPARTMENT
DASSAULT AVIATION
78, Quai Marcel Dassault
Cedex 300
92552 SAINT-CLOUD Cedex
FRANCE
A l'attention de DSC

### Page 22

SERVICE BULLETINS COMPLIANCE FALCON 2000EX A/C S/N    
DASSAULT AVIATION Number  ATA Number   
F2000EX 393  F2000EX 30 14   
        
        
        
        
Coding: C complete compliance
 
T partial compliance
   
Performed by:   
Remarks: Initial issuance Date: Signature:
SERVICE BULLETINS COMPLIANCE
Would you be kind enough to inform us that this Service Bulletin is complied with:
- For "Western Hemisphere", mail upper card (No postage necessary if mailed in the U.S.A.) or fax to Dassault Falcon Jet: 1-201-541-4700.
- For "Other Continents", mail card herebelow or fax to Dassault Aviation: 33 (0)1.47.11.65.21.
On the occasion, if other Service Bulletins have been simultaneously complied with could you complete the blank spaces provided for this
purpose.
APPLICATION DE BULLETINS DE SERVICE
Lorsque vous aurez applique ce Bulletin de Service sur votre avion, veuillez avoir l'amabilite de nous en informer:
- Utiliser la carte reponse superieure pour continent americain (Dispensee de timbrage pour postage depuis les U.S.A.) ou le fax pour
Dassault Falcon Jet : 1-201-541-4700.
- Ou la carte reponse inferieure pour autres continents ou le fax pour Dassault Aviation : 33 (0)1.47.11.65.21.
Eventuellement, si d'autres Bulletins de Service ont ete appliques simultanement, vous pouvez les mentionner dans les cases vierges
prevues a cet effet.
APPLICATION DES BULLETINS DE SERVICE   
SERVICE BULLETINS COMPLIANCE FALCON 2000EX A/C S/N    
DASSAULT AVIATION Number
Numero DASSAULT AVIATION  
ATA Number
Numero ATA   
F2000EX 393  F2000EX 30 14   
        
        
        
        
Coding: C complete complianceapplication totale
 
T partial complianceapplication partielle
   
Performed by:
Fait par:
  
Remarks: Initial issuance Date: Signature:
Remarques: Edition originale

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