# FALCON SERVICE BULLETIN

573 704 635 

# FALCON 900EX

FALCON 900EX EASy

FALCON 900DX

No 329

- R 3

MARCH 10 , 2010



# MANDATORY

Copyright © 200 9 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 pe rmission

of Dassault Aviation. 

# ATA 57

- 7

WING

WING TANK MODIFICATION

# F

ALCON 900EX SER VICE BULLETIN

F900EX–329

F900EX–57–7 

# WING

WING T ANK MODIFICA

TION

________________________________________________________________________________

INITIAL ISSUANCE date: September 25, 2009

List of ef fective pages: 1 to 6.



# ________________________________________________________________________________

COMPLETE ISSUANCE: REVISION 1 date: October 30, 2009

List of ef fective pages: 1 to 6.

List of modified pages: 1 to 6.

REASON: The Service Bulletin is updated to give precise details about compliance and

training.

This revision is not applicable to aircraft already modified per the original issue.



# ________________________________________________________________________________

COMPLETE ISSUANCE: REVISION 2 date: February 15, 2010

List of ef fective pages: 1 to 6.

List of modified pages: 5 and 6.

REASON: Addition/correction of information in appendix 1, 2, 5 following installations

performed during training.

This revision is not applicable to aircraft already changed per the original issue or revision 1.



# ________________________________________________________________________________

COMPLETE ISSUANCE: REVISION 3 date: March 10, 2010

List of ef fective pages: 1 to 5.

List of modified page: 2.

REASON: Modification of paragraph “TRAINING”.

This revision is not applicable to aircraft already changed per the original issue or revision 1 or

revision 2.DASSAULTAVIATION Proprietary Data 

# SERVICE BULLETIN

F ALCON 900EX F900EX–329

March 10, 2010 F900EX–57–7

Revision 3 Page 1 

# WING

WING T ANK MODIFICA

TION

________________________________________________________________________________

1 . PLANNING INFORMA TION

A . EFFECTIVITY

This Service Bulletin is applicable to:

– F ALCON 900EX aircraft with serial numbers 1 through 600 (F900EX and F900EX EASy),

– F ALCON 900EX aircraft with serial numbers 601 and subsequent (F900DX),

which have not previously implemented DASSAUL T A VIA TION modification F900EX M5413.

B . REASON

An analysis of rare high-speed runway excursions has revealed that, in case of a main landing

gear leg failure due to overloads, the subsequent wing damage may cause a potential fuel

spill.

The purpose of this Service Bulletin is to prevent such a fuel spill in the event of such an

exceptional occurence by installing a sealed boundary between ribs No. 4 and 5 in front of

the rear wing spar

.

C . DESCRIPTION

The operation consists in:

– removing the structural removable lower wing panel,

– installing a drainage capability

, – installing a boundary between ribs No 4 and 5,

– applying a sealant around the boundary

, – performing a test for leakage.

The Accomplishment Instructions and the tests are included in the five Appendices to this

Service Bulletin.

D . COMPLIANCE

Mandatory:

Compliance with this Service Bulletin should be done no later than 12 years and 6 months

of its release date.

It is anticipated that this Service Bulletin will be rendered mandatory by an EASA

Airworthiness Directive. The Airworthiness authorities of other countries may also elect to

mandate compliance with this Service Bulletin and compliance timelines will be established

by those authorities.

Each person applying this Service Bulletin must have successfully completed a training

program. For more details refer to the training section of paragraph F

.DASSAULTAVIATION Proprietary Data 

# FALCON

900EX SER VICE BULLETIN

F900EX–329

March 10, 2010 F900EX–57–7

Revision 3 Page 2 E . APPROVAL

This Service Bulletin covers DASSAUL T A VIA TION modifications F900EX M5413 which has

been approved by EASA and M5517 which have been approved under the authority of DOA

nr . EASA.21J.051.

The technical content of this document is approved under the authority of DOA

nr . EASA.21J.051.

F . LABOR

Estimated labor–hours:

– Access time: 300 hours

– Modification: 300 hours

– 40 hours for paint touch (including lower wing panels and upper wings reworked areas)

NOTE: These labor–hours only concern the work described in this Service Bulletin and do

not include other maintenance work which may be performed on this occasion.

NOTE: The Service Bulletin instructions contained in the five APPENDICES constitute

complex structural rework activity that should only be accomplished at Service

Centers that have relevant experience working on Falcon aircraft and have a

high level of competency in the following areas:

– W ork on primary structure.

– Metal work.

– Precision adjustment.

– Non-destructive-T

esting (NDT) for cracks.

– Use of S-class screws and repair dimensions.

Failure to utilize an experienced Service Center with a high level of proficiency

in the above disciplines and specialized training in the operations covered

hereby, could result in inadvertent damage during the Service Bulletin

procedure, possibly requiring extensive aircraft repairs.

TRAINING: Each person applying this Service Bulletin must have successfully completed a

training program. This training program consists of applying this Service Bulletin in the

person’s facility under the supervision of a trainerfrom Dassault A viation, and/or Dassault

Aircraft Services (DAS) personnel that have received training from Dassault A viation.

Each facility applying this Service Bulletin must maintain capable individuals on staf f that have

successfully completed the Dassault training program prior to attempting this modification.

However , it is acceptable that a person from a facility that has successfully completed the

training program to be designated to serve as a trainer for that facility . As a consequence, it

is the responsibility of each maintenance facility applying this Service Bulletin to define an

internal training program of its technicians and maintain familiarization of the application of

the SB to maintain the required knowledge over the years.DASSAULTAVIATION Proprietary Data 

# SERVICE BULLETIN

F ALCON 900EX F900EX–329

March 10, 2010 F900EX–57–7

Revision 3 Page 3 G . MA TERIAL – PRICE AND A VAILABILITY

The modification kit will be delivered to the Service Centers approved from either address

listed below:

W estern hemisphere: DASSAUL T F ALCON JET CORP

. SP ARES DISTRIBUTION CENTER

200 RISER ROAD

LITTLE FERR Y

, 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: DASSAUL T A VIATION

Falcon Spares

BOITE POST

ALE N o 

# 101

AEROPORT DU BOURGET

93352 – LE BOURGET Cedex (FRANCE)

Please contact your Dassault A viation

Account Representative

T elephone: 33 (0)1.48.35.56.78

Fax: 33 (0)1.48.35.56.00

Price and availability on request.

H . T OOLING – PRICE AND A VAILABILITY

The specific tooling are listed in the APPENDIX 5.

I . WEIGHT AND BALANCE

Change in weight: + 6.4 lb (+ 2.9 kg).

Change in balance with respect to 25% MAC : + 32 ft.lb (+ 4,3 m.daN) nose up moment.DASSAULTAVIATION Proprietary Data 

# FALCON

900EX SER VICE BULLETIN

F900EX–329

March 10, 2010 F900EX–57–7

Revision 3 Page 4 J . REFERENCE

Aircraft Maintenance Manual:

– procedure 27-510,

– procedure 27-81 1,

– procedure 57-01 1.

Standard Practices:

– procedure 20-320,

– procedure 20-602,

– procedure 20-650.

AMM chap. 12, Ingredients and consumable products.

Airplane Flight Manual:

– F900EX Airplane Flight Manual (DTM561) Rev . 9 or subsequent.

– F900EX Easy Airplane Flight Manual (DGT84972) Rev . 6 or subsequent and in

Supplement 9 Revision 4 or subsequent for F900DX.

K . OTHER PUBLICA

TIONS AFFECTED

The following publications will be revised at a later date to account for the changes introduced

by this Service Bulletin:

– AMM.DASSAULTAVIATION Proprietary Data 

# SERVICE BULLETIN

F ALCON 900EX F900EX–329

March 10, 2010 F900EX–57–7

Revision 3 Page 5 

# END OF DOCUMENT 2 . ACCOMPLISHMENT INSTRUCTIONS

A

. ACCOMPLISHMENT INSTRUCTIONS ARE DESCRIBED IN THE FOLLOWING

APPENDICES:

(1) APPENDIX 1 DRY BA Y – ASSEMBL

Y OF BOUNDAR Y AND DRAINING CAP ABILITY

REVISION 2

(2) APPENDIX 2 DR Y BA Y – SEALANT APPLICA TION ON BOUNDAR Y

REVISION 3

(3) APPENDIX 3 DRY BA Y – LEAKAGE PRESSURE TEST FOR THE SEAL BOUNDAR Y

REVISION 2

(4) APPENDIX 4 DR Y BA Y – REPOR T OF DRILLING THE PR INJECTION HOLES

REVISION 1

B . DOCUMENT

ATION

Update, if not already done, the Airplane Flight Manual with:

– Airplane Flight Manual (DTM561) Rev . 9 or subsequent for a F900EX.

– Airplane Flight Manual (DGT84972) rev . 6 or subsequent for a F900EX Easy and in

Supplement 9 Revision 4 or subsequent for F900DX.

C . 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 A viation

or Dassault Falcon Jet, or fill out the Compliance Form on line on the Dassault Falcon website.



# 3 . MA TERIAL INFORMA

TION

Refer to DRY BAY APPENDIX 5 REVISION 3.

# DASSAULT F ALCON JET CORP

. PO BOX 1946

SO HACKENSACK NJ 07606–9946

ATTENTION:

FIELD SER VICE DEP

ARTMENT

FIRST CLASS MAIL PERMIT NO. 3306 HACKENSACK, NJ 07602



# DASSAULT A

VIATION

78, Quai Marcel Dassault

Cedex 300

92552 SAINT–CLOUD Cedex

FRANCE

A l’attention de DSC

# SERVICE BULLETINS COMPLIANCE

SER VICE BULLETINS COMPLIANCE



# SERVICE BULLETINS COMPLIANCE F ALCON 900EX

APPLICATION DES BULLETINS DE SER VICE DASSAULT A

VIA TION Number AT A Number



# Remarks: Coding: 

# A/C S/N

C

T complete compliance

partial compliance

Date : Signature : Performed by:

DASSAULT A

VIA TION Number AT A Number



# Remarks: Coding: 

# C

T complete compliance

partial compliance

Date : Signature : Performed by: 

# FALCON 900EX Avion N o

Numéro DASSAUL

T A VIATION Numéro A TA



# Fait par : application partielle application totale W ould you be kind enough to inform us that this Service Bulletin is complied with:

– For ”W estern 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 A viation: 33 (0)1.47.1 1.65.21.

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 SER VICE

Lorsque vous aurez appliqué ce Bulletin de Service sur votre avion, veuillez avoir l’amabilité

de nous en informer :

– Utiliser la carte réponse supérieure pour continent américain ( Dispensée de timbrage pour postage

depuis les U.S.A. ) 

# ou le fax pour Dassault Falcon Jet : 1–201–541–4700.

– Ou la carte réponse inférieure pour autres continents ou le fax pour Dassault A viation : 33 (0)1.47.1 1.65.21.

Eventuellement, si d’autres Bulletins de Service ont été appliqués simultanément,

vous pouvez les mentionner dans les cases vierges prévues à cet ef fet.

Remarques :



# 329

329 F900EX 57

57 7 7

Revision 3 Revision 3

Révision 3 

# F900EX F900EX F900EXPAGE1/49ASSEMBLING DRY BAY AND DRAINING CAPABILITYRevision 2February 15, 2010DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 2/49Revision 2February 15, 2010PROTECTION EQUIPMENTOPERATIONSHAZARDSCHEMICAL HAZARDS ON WORKSTATIONPicklingVacuumcleaner+Latex glovesAnti-dust maskCleaning with solventLatex glovesSealant applicationLatex glovesLong sleeves clothesDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 3/49Revision 2February 15, 2010Handling with travelling craneRisks of clashes, fall ofobjects+Authorized personnelClassic riveting, MGPL, FOBO,boring, reaming, broaching,countersinking, routing,trimming, pinning tightenedDeburring, spot-facingHandling of bridges, spars,panels, drilling gridsRisks of fall ofobjectsNON-CHEMICAL HAZARDS ON WORKSTATIONPROTECTION EQUIPMENTOPERATIONSHAZARDSDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 4/49F50F900 F900EX F2000 F2000EX27-811 27-811 27-811 27-811 27-81157-400 57-011 57-011 57-011 57-011Revision 2February 15, 2010Extend the flaps seeprocedure27-510 27-510 27-510Remove the wing’s structural fueltank removable panel seeprocedureRemove flap actuator(L25CF/R25CF) see procedure27-568 27-521PRELIMINARY STEPSDRY BAY APPENDIX-1CAUTION: Once panel is removed, ventilate with an air extractor to remove fuel vapors from the wing box.This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 5/49Strip the area prior to drilling the PR injection holesSee Standard practices 20-602 (Stripping and pickling)Revision 2February 15, 2010LOWER SURFACE BOTTOM VIEWUPPER SURFACE TOP VIEWRIB 4DRY AREAFRAMEFWDFWDRIB 5Strip paintChemical picklingStrip paintChemical picklingDRY BAY APPENDIX-1RIB 5REAR SPARUpper panel boundaryREAR SPARThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 6/49ASSEMBLING HALF-FRAMESFitting nut gang channels to half-frames:- On the workbench, cut out the nut gang channel 39600C332-13S (Item 26)- Mark the 2 gang channels: FGFB112500027Secure with rivets 21218DB2408J (Item 54)February 15, 2010- Fit all nut gang channels to half-frames Item 1-2 and Item 3-4, and interlay sealant (see Standard Pratices 20-650)Revision 2Cut-outHalf-frame Item 1-2FGFB112500011W1P01/FGFB122500011W1P01Half-frame Item 3-4FGFB112500012W1/FGFB122500012W1FGFB112500027Nut gang channel Item 2839600C102-04SNut gang channel Item 2739600C123-05SDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 7/49INSTALLATION OF DRY BAY STRUCTUREInstallation of angle Item 11-12 on half-frameAttach the angle (Item 11-12) to half-frame (Item 1-2) using an assembly screwDrill the angle (Item 11-12) dia. 0.1 in. ( 2.5 mm) hole in half-frameDisassemble angle, deburrAssemble angle with interlaying sealant (See Standard Practices 20-650) and rivets 21218DE2408JRevision 2February 15, 2010Half-frame Item 1-2FGFB112500011W1P01/FGFB122500011W1P01Angle Item 11-12FGFB112500005W1EQU/FGFB122500005W1EQURivet 21218DE2408J Item 54DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 8/49INSTALLATION OF DRY BAY STRUCTURE- Assemble cups Item 7-8 and item 9-10Cleco cups Item 7-8 and Item 9-10 through two dia. 0.1 in. ( 2.5 mm) predrilled holesDrill both 2 x dia. 0.1 in. ( 2.5 mm) of a cup in the other one and drill both holes to dia. 5.2 H9Remove, deburr and install both nut plates Item 48 on cup Item 7-8Assemble the 2 cups with interlaying sealant between the two parts+ 2 x screws Item 47PinningRevision 2February 15, 2010Recess Item 7-8FGFB112500003/FGFB122500003Cup Item 9-10FGFB112500004 /FGFB122500004Fill with bead sealantSee Standard Practices 20-650Dia.5.2 H9 ( +0Dia. 0,205 in. (+0 μin. +1.8 μin.)DRY BAY APPENDIX-12 x screw Item 4722201TX050003XFNut plates Item 485SF5009MCup Item 7-8FGFB112500003/FGFB122500003Cup Item 7-8FGFB112500003/FGFB122500003Repeat both 2 x Ø 0.1 in ( 2.5mm)This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 9/49INSTALLATION OF DRY BAY STRUCTUREFitting nut gang channels to cup assembly:Drill the cups to dia. 0.244 in. (6,2 mm)Secure with rivets 21218DB2408J (Item 54)- Fit 14ea nut gang channels to cups Item 7-8 and Item 9-10, and interlay sealant (see Standard Pratices 20-650)Revision 2February 15, 2010DRY BAY APPENDIX-1nut gang channel 39600C332-13SItem 26This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 10/49OMEGA STIFFENER REMOVAL + SEALING ON RIB 51) Remove the omega stiffener 113005004 / 113005004 on rib 5 do not enlarge the rivet holes2) Scrape and clean the sealant around the fastener doublers on rib 53) Check for presence of sealant between doubler and rib 5. If sealant is already applied, is not necessaryto remove the rivets to ease the PR injectionRevision 2February 15, 2010RIB 5Scrape and clean sealantOmega stiffener holesFGFB113005004DRY BAY APPENDIX-1RIB 5 REAR SPARRemove these rivets Item 57to ease the PR injectionDo not remove them if thereis sealant between doublerand rib 5Remove this rivet and replace with a100°-countersunk head screw,INSPECT FOR SEALANTSealant beetween doublerand rib 5Remove this rivet ifnecessary onlyRemove the OmegastiffenerFGFB113005004Remove this screwRIB 5NOTE: External wingskin top sideThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 11/49REMOVING AND CLEANING SEALANTRevision 2February 15, 2010DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 12/49ATTACHMENT REMOVAL FOR REAR SPAR ANGLESRemove the six fasteners and check the diameter of each screw (some may be oversize-dimension screws)Scrape and clean the sealant in the bent section aeraRevision 2February 15, 2010RIB 5REAR SPAR2 Screws 38472TX060Dia. 0.236 in. (6 mm)DRY BAY APPENDIX-1Scrape and clean the sealant inthis area1 Screw 38472TX060Dia. 0.236 in. (6 mm)2 Screws 22201TX050Dia. 0.197 in. (5 mm)or MPGL’s1 Screws 38472TX050Dia. 0.197 in. (5 mm)This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 13/49INSTALLATION OF BLANKING PLATE ON REAR SPARAfter removal of the removable panel and of the locating plug, perform the following:Protect the dia. .63 in. (Dia. 16mm) hole with alodine and install the 2 nut plates (Item 30) on both sides of the holePerform paint touch-up on the dia. .63 in. (Dia. 16mm) hole and nut platesInstall the plate (item 21) on the spar,NOTE: DO NOT INSTALL UNTIL AFTER THE PRESSURE TEST (Appendix 3 page 5)Using tool MA48401Z01-FGFB112005A2 drill 2 bores to a diameter of .19 in. (Dia. 4.8E9)Drill the locating plug to a diameter of.39 in. to .63 in. (Dia.10mm to 16mm),Revision 2February 15, 2010Rib 5Rib 4Rear sparLocatingplugBox structure - insideviewNut MS21059L3Locating plug tobe removedBox structure - insideviewRib 4Rib 5Plate Item 21 FGFB112005003(Installed outside the box structure)2 nuts Item 30MS21059L3installed with rivets(Item 56) 21218DE2410J2 screws Item 29NAS1133V4ADia,.63 in.(Dia.16mm)DRY BAY APPENDIX-1Drilled dia..63 in.(dia. 16mm). holeThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 14/49INSTALLATION OF DRAIN PROVISION ON LOWER SURFACE PANELRevision 2February 15, 2010Install the drilling tool ME48401Z01-SBF2000-358 and check for the dimension of .24 in. min (6 mm min).NOTE: Install a shim (thickness .2 in. (5 mm)) under the tool to escape the radius of the risers.If the dimension is smaller than .24 in. (6 mm), use drilling tool ME48402Z01-SBF2000-358,Pre-drill the lower panel to a diameter of 0.1 in. (Dia. 2.5 mm)Enlarge the 3 holes (see figure)Set clocos to attach the angle (Item 61-62) (FGFB112500060W3/FGFB122500060W3) with the appropriate shim FGFB112500063W3 and counterdrillthe shim and rib 4 for rivet 21215DE32Install anchor nut Item (NAS1473A3) on the angle with interlaying sealantProtect holes with alodine and touch-up with paint.DRY ZONERib 4.24 in. min6 mm miniTool ME484001Z00-SBF2000-358DRY BAY APPENDIX-1Rib 4Item 61-62Insert shim ifnecessaryRear sparRear sparRear sparØ .20 in.Ø 5 mmØ .20 in.Ø 5 mmØ .31 in.Ø 8 mmSECTION D-DRear sparThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 15/49REINFORCING RIB 5Revision 2February 15, 2010Back drill rib 5 holes into the shim (Item 22) to a diameter of 0.1 in.(Dia. 2.5 mm) with drill bush MA48401-01Back drill of rib 5 holes into the shim (Item 24) + angle bracket (item 25) to a diameter of Dia. .1 in.(Dia. 2.5 mm) with drill bush MA48401-01Cleco the shim (item 24) and the angle bracket (item 25) to rib 5Enlarge bores to dia.4,4 U9 ( Dia. 4,4U9 = 0.173 in. (-0,0009;-0,0020))Countersink the 4 or 5 holes(CAUTION: contersunking is on Rib5 side)DRY BAY APPENDIX-1Angle bracket Item 25FGFB113005041Rib 5Shim Item 22FGFB112500009Rib 5 reinforcementATTACHMENTDIRECTIONRemove this rivet, onlyif necessaryIf this configuration is encountered,rework the shims (item 22 & 24) to fitwith the stiffener’s shape.Shim -Item 24FGFB113005042This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 16/49DRILLING THE BENT SECTIONSHave the bent sections Item 13-14 and Item 15-16 resting on rib 5 and rear sparDrill existing holes drilled in panels to bent sections using Dia. 0.1 in. (Dia. 2.5 mm) drill bushesDrill the angle only to dia. 0.204 in. (5.2 D10)for vertical attachments, dia.0.244 in.(Dia. 6.2 D10) for lower surface attachment fittingsand Dia. 0.244 in.(dia. 6.2D10) and 0.204 in. (5.2 D10) for upper surface attachment fittingsRevision 2February 15, 2010RIB 5REAR SPARUPPER SURFACE BENT SECTIONItem 15-16FGFB11250006/FGFB122500006LOWER SURFACE BENT SECTIONItem 13-14FGFB11250007/FGFB122500007Dia. 0.204 in (Dia. 5.2 mm)D10 boreDia. 0.244 in (Dia. 6.2mm) D10 boreDRY BAY APPENDIX-1Dia. 0.244 in (Dia. 6.2mm) D10 boreDO NOT DRILL SKIN OR RIB 5 TOTHESE MEASUREMENTS(JUST BENT SECTIONS)This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 17/49DRILLING THE LOWER SURFACE PANEL STIFFENERUsing tool MA48402Z01-FGFB117/127000103, pre-drill the stiffener to a diameter of Dia. 0.1 in. (Dia. 2.5 mm)Revision 2February 15, 2010Rib 4Rib 5Rear sparRib 5Rib 4Pre-drilled stiffener (4 x Dia. .1 in.(Dia. 2.5mm))DRY BAY APPENDIX-1Tool MA48402Z01-FGFB117/127000103Rib 5This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 18/49DRILLING THE LOWER SURFACE PANEL STIFFENERRevision 2February 15, 2010Rear sparRib 5Rib 4Pre-drilled stiffener (12 x Dia. .1 in.(Dia. 2.5mm))DRY BAY APPENDIX-1NOTE: For easier access, use tool MA48401Z01-FGFB122500003 on LH side and tool MA48401Z01-FGFB112500003 on RH side.Attach tool MA48401Z01-FGFB112/122500003 to the stiffener and pre-drill to a diameter of 0.1 in. (Dia. 2.5 mm)Tool MA48401Z01-FGFB112/122500003Rib 5Rib 4This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 19/49INSTALLATION OF DRY BAY STRUCTURERevision 2February 15, 2010DRY BAY APPENDIX-1Inside the wing box, install the cup assembly (Item 7-9/8-10) against the lower panel stiffiner and Rib5Position the cup assembly 0.06 in. (1,5 mm) from the top of the stiffenerUsing screw clamps, secure the cup assembly to the lower panel stiffener and check the position (0.06 in. - 1.5 mm)Spot drill the three dia. 0.1 in. ( Dia.2.5 mm) pre-drilled holes of the lower skin panel stiffener in the cup asssembly,Attach the cup assembly to the stiffener,NOTE: Verify the position of cup assembly with respect to the stiffener (.06 in.(1.5mm))Rib 5Rib 4Cups FGFB112/122500003FGFB112/122500004Item 7-9/8-10CupsStiffener.06 in.1,5 mmThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 20/49INSTALLATION OF DRY BAY STRUCTUREIn case of interference between the half-frame and rib 5 during installation: See page 47Revision 2February 15, 2010Half-frame Item 1-2FGFB112500011W1P01 /FGFB122500011W1P01DRY BAY APPENDIX-1Draw a line on the half frame (Item 1-2) at 0.39 in. (10mm ) of the edge (see detail A)Resting on the cup assembly, position the half frame (item 1-2) embedded in rib 5 and bearing on toolMA40301Z01-FGFB112/122500010Check that the half-frame rests properly on the upper wing panel,Use bolt to assemble the half-frame to cup assembly.On half-frame, mark holes from rib 5 and the hole of the upper skin panel.Check for gaps between the upper panel attaching parts and and the half-frameDisassemble and check the gap as per page 47Tool MA40301Z01-FGFB112/122500010Rib 5Cup assemblyDETAIL AHole of the upperskin panelGapThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 21/49INSTALLATION OF DRY BAY STRUCTUREIn case of interference between the half-frame and rib 5 during installation: See page 47Revision 2February 15, 2010DRY BAY APPENDIX-1Inside the wing box assemble the half frame (Item1-2 and item 3-4) with the positioning template ME62001Z01-SBF2000-358 and attach the assemblywith screwsResting on the cup assembly, position the assembly in contact to rib 5 and bearing on toolMA40301Z01-FGFB112/122500010Check that the half-frames rest properly on the upper wing panel,Attach the assembly to cup assembly with screws,Insert shim (item 23) between half-frame (item 3-4) and rib 4, adjust shim thickness if necessaryTool MA40301Z01-FGFB112/122500010Rib 4Half-frame Item 1-2FGFB112500011W1P01 /FGFB122500011W1P01Half-frame Item 3-4112500012W1 /122500012W1Rib 5Cup assemblyPositioning templateME62001Z01-SBF2000-358Shim Item 23 (between Rib 4and half-frame)This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 22/49INSTALLATION OF DRY BAY STRUCTUREDrill both dia. 0.1 in. ( Dia. 2.5 mm) pre-drilled holes of the half-frames in the upper surface skinDrill both dia. 0.1 in. ( Dia. 2.5 mm) pre-drilled holes of the half-frames in the Rib 4Attach the half-frames to the upper surface skin and the rib 4 with shim item 23Drill rib 5 holes, dia. 0.1 in. (Dia. 2.5 mm) then dia. .161 in. (dia. 4,1 mm) into half-frame (Item 1-2)with drill bush MA48401-01Revision 2February 15, 2010Rib 5Drillhalf-frame/rib 5 linkHalf-frame Item 1-2FGFB112500011W1P01 /FGFB122500011W1P01DRY BAY APPENDIX-1Drill bushMA48401-01Rib 5This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 23/49INSTALLATION OF DRY BAY STRUCTUREDrill rib 4/half-frame link to dia. 0.158 in.(dia. 4mm) using tool MA48401Z01-FGFB112/122500010Revision 2February 15, 2010Rib 4Drill half-frame/rib 4linkHalf-frame Item 3-4FGFB112500012W1/FGFB122500012W1DRY BAY APPENDIX-1Tool MA48401Z01-FGFB112/122500010Rib 4This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 24/49ASSEMBLING THE DRY BAYCleco the drilling template MA48401Z01-FGFB116/126 and bore to a diameter of 0.158 in. (Ø4mm)the linking half-frames / upper wing surfaceDisassemble and deburr the assemblyPreparation of shim Item 19-20On shim Item 19-20 mark and drill a dia 0.204 in.(dia. 5.2) holeRevision 2February 15, 2010Shim Item 19-20FGFB112500016/FGFB12250001616 x dia. 0.158 in.(dia. 4 mm)1 x dia. 0.1 in.(Ø2,5 mm)DRY BAY APPENDIX-1Tool MA48401Z01-FGFB116/126This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 25/49ASSEMBLING THE DRY BAYDrill cup assembly on workbenchRevision 2February 15, 2010DRY BAY APPENDIX-1NOTE: Use the same tool as that used to drill the lower panel stiffenerPin tool MA48401Z01-FGFB112/122500003 to the cup assembly (item 7-9/8-10) and pre-drill to a diameter of 0.1 in. (Dia. 2.5 mm)Pin and position the plug (item 17-18) on the cup assembly (see DETAIL A)Drill dia 0.1 in. (Dia. 2.5 mm) pre-drill hole of cup assembly in the plug,Pin tool MA48401Z01-FGFB112/122500003 to the cup assembly and drill to a diameter of 0.158 in. (Dia. 4 mm)Pin the plug to tool MA48401Z01-FGFB112/122500003 and drill to a diameter of 0.158 in. (Dia. 4 mm)DETAIL AShim 0.06 in.(1.5 mm)Plug FGFB112/122500008Item 17-18Tool MA48401Z01-FGFB112/122500003Cup assemblyPlugCup assembly.03 in.0.8 mmThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 26/49ASSEMBLING THE DRY BAYRemove, deburr and reinstall the assemblyMEASUREMENT OF FRAME CLEARANCES BETWEEN RIB 4 / RIB 5AND BETWEEN THE CUP AND THE UPPER WING SURFACEAreas to check:Half frame Item 1-2 and rib 5Half frame Item 3-4 and rib 4Half frame Item 1-2 and Item 3-4 and the upper wing surfaceCup assembly Item 7-8 and Item 9-10 with the stiffener of the lower wing surfacePlug Item 17-18 with the stiffener of the lower wing surfaceRemove, clean and deburr the assemblyPut protections on the areas to be liquid shimmed: red adhesive tape reference CFR AVF HP or teflon tapeSand the areas to be liquid shimmedClean with authorized solventSpread filling compound (See Standard Practices 20-320)Revision 2February 15, 2010RIB 4HALF FRAME Item 3-4FGFB112500012W1 /FGFB122500012W1RIB 5UPPER WING SURFACESTIFFENERLOWER WING SURFACEMeasure and inject filler if =>0.002 in.( 0.05 mm ) <GAPCUP ASSEMBLY 7-9/ 8-10FGFB112500003 /FGFB112500004FGFB122500003 /FGFB122500004PLUG ITEM 17-18FGFB112500008 /FGFB122500008HALF FRAME ITEM 1-2FGFB112500011W1P01 /FGFB122500011W1P01Measure and inject liquid shim if => 0.05 mm < ClearanceDRY BAY APPENDIX-1NOTE 1: Do not work on wing while liquid shim is drying.NOTE 2: Apply Filleralu at the end of the day so that it can dry during the nightThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 27/49ASSEMBLING THE DRY BAYDrill links half frame/cup assembly to final hole sizeDisassemble, clean and deburr the assemblySee page 48 for boring tolerancesRevision 2February 15, 201013 x hole drilled to dia.5H97 x hole drilled to dia.5U916 x holes drilled todia.5U9 + countersink1 x hole drilled to dia.4U9+ countersink8 x hole drilled to dia.4.4 U9Rib 5Rib 4Rib 5Lower surface panelDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 28/49Revision 2February 15, 2010DETAIL OF RIB 5 SPLICERIB 5DRY BAY FRAMERIB 5 REINFORCEMENTCORDON DE PR A REALISERPAR L’INTERMEDIAIRE DE2 + 2 TROUS Ø2,3mm D'INJECTIONDRILLING THE PR INJECTION HOLES IN LOWER AND UPPER SURFACES AT RIB 5DETAIL OF RIB 5 SPLICESEALANT BEAD TO REALIZE WITH2 + 2 INJECTION HOLES DIA. 0.09 in. (2,3mm)DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 29/49Record the dimensions between the attachments of rib 5 reinforcement and the edge of rib 5 reinforcement baseplate (.35 in. 9mmPM)Draw the edge of rib 5 reinforcement baseplate on the skinDraw the middle line at .79 in. (20 mm) from the edge of rib 5 reinforcement baseplate(This line represents the interface between rib 5 and rib 5 reinforcement)Locate the drilling positions with the attachment marksDO NOT DRILL IF A CENTER-TO-CENTER DISTANCE OF .55 in, MIN (14 MM MIN.) CANNOT BE OBTAINEDFebruary 15, 2010Mark the center point of each drilling position at the interface between rib 5 reinforcement and rib 5; check that this point is located at 0.55 in. MIN (14mm mini) from each attachmentRevision 212431234LOWER SURFACE BOTTOM VIEW L/HPOSITIONING OF LOWER SURFACE HOLES DRILLED FOR PR INJECTIONEDGE OF RIB 5 REINFORCEMENT BASEPLATE2DIA. 0.09 in. (Ø 2.3 mm) holes drilled for interlayingsealantFWDMIDDLELINEREAR SPARRIB 5A/C CENTERLINEUPPER SURFACEPANELthick,ness 0.16in. (4 mm)LOWER SURFACEPANEL thickness 0,20in. (5 mm)SECTION AABe very careful when drilling hereDRY BAY APPENDIX-1

Ø 0,09 in. ( Ø 2.3)

1784 1785 1786 1787 1788 1789 1799

1792 1793 1794 1795 1796 1797 1798 .79 in. 20 mm

.35 in. 9 mmNOTE.55 in. MIN14 mm MINIThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 30/49Record the dimensions between the attachments of rib 5 reinforcement and the edge of rib 5 reinforcement baseplate (.35 in. 9 mm for ref.)Draw the edge of rib 5 reinforcement baseplate on the skinDraw the middle line at .79 in. (20 mm) from the edge of rib 5 reinforcement baseplate(This line represents the interface between rib 5 and rib 5 reinforcement)Locate the drilling positions with the attachment marksDO NOT DRILL IF A CENTER-TO-CENTER DISTANCE OF 14 MM MIN. CANNOT BE OBTAINEDFebruary 15, 2010Mark the center point of each drilling position at the interface between rib 5 reinforcement and rib 5; check that this point is located at 0.55 in. MIN (14mm mini) from each attachmentRevision 212431234UPPER SURFACE TOP VIEW L/HPOSITIONING OF UPPER SURFACE HOLES DRILLED FOR PR INJECTIONEDGE OF RIB 5 REINFORCEMENT BASEPLATE2 xØ .09 in.(Ø 2.3 mm) holes drilled for interlayingsealantFWDMIDDLE LINEREAR SPARRIB 5A/C CENTERLINEDRY BAYFRAMESECTION A-ABe very careful whendrilling hereDRY BAY APPENDIX-1 Ø 0,09 in. ( Ø 2.3)

1686 1687 1688 1689 1690 1692 1694 1696 1698

1691 1695 1697 1699

1693 .79 in. 20 mm .35 in. 9 m mLOWER SURFACEPANEL thickness 0,20in. (5 mm)UPPER SURFACEPANELthick,ness 0.16in. (4 mm)NOTE.55 in. MIN14 mm MINIThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 31/491) Punch the 2 holes in the skin: depth =.02 in. MAX ( 0.5 mm MAX).Ask a checker to check for a margin of.55 in. MIN (14 mm MIN.)between the 2 punch marks and the surrounding attachment fittings2) Pre-drill the PR injection holes atØ.079 in. ( 2 mm)Before drilling, check that the flat-tip drill bit diameter is.09 in. (2.3 mm)and the adjustment of the drill bit stop height (equal to the skin thickness)Fill the table 2 in ANNEXE 43) Drill to final diameter with drill bitØ.09 in. (Ø2.3 mm).Revision 2February 15, 2010Fill the table 1 in ANNEXE 4Before pre-drilling, ask an inspector to check that the drill bit has a diameter of.079 in. (2 mm)and check the adjustment of the drill bit stop(equal to the skin thickness)DRILLING THE PR INJECTION HOLESDRY BAY APPENDIX-1NOTE: Lower skin .20 in. (5 mm) stop depthUpper skin .16 in. (4 mm) stop depthThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 32/49INJECTING SEALANT INTO LOWER AND UPPER PANEL AND INTO RIB 5PRIOR TO PR INJECTION1) Clean the dia. 0.09 in.bore (Ø2.3 mm) on lower and upper panel2) Inject authorized solvent (with a spout type container) in each doubler hole to clean the interface (doubler / rib 5) )Revision 2February 15, 2010DRY BAY APPENDIX-1FIRST CLEAN AND DEGREASE CAREFULLY THE ASSEMBLY AREACAUTION : PRIOR TO STARTING SEALANT APPLICATION, ALL DRILLINGS MUST HAVE BEENPERFORMED, TO AVOID POLLUTING FRESH SEALANT WITH METAL SHAVINGSThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 33/49RIB 5/DOUBLER INJECTION AND SEALANTRIB 5 DOUBLER INJECTION SEALANT1) Sealant injection ((with a 1015 PSI (70 bars) extrusion gun fitted with a stiff end-piece)) in the doubler holes from rib 5Revision 2February 15, 2010DRY BAY APPENDIX-1- insert 2 x 2 item A screws- inject PR into item A holes until it flows out of item B holes- remove screws from item A holes and fit them into item B holes- inject PR into item B holes until it flows out of item C holes- remove screws from item B holes and fit them into item C holes- inject PR into item C holes- do the same for item D holesABBCCDDETAILINJECTION SCREWDrainage holeInjection holePR injection gun MA29501Z00-1or equivalent (see Appendix 5 page 6)Fit a stiff end-pieceINJECTION SCREWHoles to be injectedwith interlaying sealantThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 34/49INJECTING SEALANT INTO LOWER AND UPPER PANEL AND ON RIB 52) Set each doubler hole on rib 5 with clecos3) Remove the excess sealant, then smooth itRevision 2February 15, 2010DRY BAY APPENDIX-1Set each doubler holewith clecosRib 5 doublerRIB 5To rib 6RIB 5To RIB 4REAR SPARRemove the excess sealant, then smooth itThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE35/49INJECTING SEALANT INTO LOWER AND UPPER PANEL AND ON RIB 51) Sealant injection => 1st time inject the sealant in the hole located next to the rear spar, then to the front sparRevision 2February 15, 2010CTVisual control of sealant applicationDRY BAY APPENDIX-1TOWARD WING ROOTLOWER WINGSURFACEThickness=5Rear spar oflower upperwing surfaceSealant injectionholesRIB 5Rib 5doubler1st injectionhole2nd injectionholeRIB 51st injectionhole2nd injectionholeRIB 5UPPER WINGSURFACERear spar ofupper wingsurfaceTOWARD WING ROOTLOWER WINGSURFACEThickness=4UPPER WINGSURFACEMaterial: 2024 T351Protection: OACInstalled with PR.008 in. (0.2 mm)CHAMFER AT 45°Theoretical thickness.-.004 in. , - .0078 in.(- 0.1 , -0.2)PIN DETAILGRIP LENGTH:.4 μ in. to .78μ in.(10 μ to 20 μ)2) Check for sealant flow at FWD/AFT end ofupper/lower channels3) Blank each injection hole with studs and fresh PRat a grip length of .4 μ in. to .78μ in. (10 μ to 20 μ)This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 36/49INSTALLATION OF DRY BAY STRUCTUREBefore tightening, apply interlaying sealant to the underside of the screw heads.February 15, 2010- Final assembly of the lower and upper surface bent sections Item 13-14 and 15-16 of rib 5 foot with sealant (See Standard Practices 20-650)Revision 2DRY BAY APPENDIX-11 x screw Item 3938472TX060012XF1 x nut Item 38 6RH8035MUpper surface angleItem 13-14FGFB11250006/FGFB122500006Lower surface angleItem 15- 16FGFB11250007/FGFB122500007Rib 52 x screw Item 3122201TX050011XF2 x nut Item 32 5RH8035MRear spar1 x screw Item 40 38472TX060009XF1 x nut Item 38 6RH8035M1 x screw Item 44Item38472TX050012XF1 x nut Item 32 5RH8035M1 x screw Item 4038472TX060009XF1 x nut Item 38 6RH8035MAttachmentdirectionAttachmentdirectionAttachmentdirectionAttachmentdirectionThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 37/49INSTALLATION OF DRY BAY STRUCTUREASSEMBLING ANGLE BACKET WITH RIB 5Intall rivets 21215DE4009 (item 57)Installation of angle bracket (Item 25) + shim (Item 24) with interlaying sealant (See APPENDIX 2)Cleco shim (item 24)+ angle bracket (item 25) and reinforcement with interlay of sealantInstallation of 3 screws 38471BE044006ME (Item 50) for attachment of angle bracket / reinforcement / rib 5Installation of 2 screws 38471BE044005ME (item 51) for attachment of reinforcement / rib 5Installation of 5 rivets 21215DE4011 (item 53)Installation of 2 screws 38460BE044006ME (Item 49) for attachment of bracket / reinforcement / rib 5Installation of 2 screws 38460BE044005ME (item 52) for attachment of reinforcement / rib 5Screws are installed with 4RH8035M nuts (item 35)Revision 2February 15, 2010Angle bracket Item 25FGFB113005041Rib 5Shim -Item 24FGFB113005042Rib 5 reinforcementATTACHMENTDIRECTIONDRY BAY APPENDIX-1

REAR SPARInstall rivets Item 57This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 38/49INSTALLATION OF DRY BAY STRUCTUREINSTALLATION OF DRAIN PROVISIONInstall angle (item 61-62) and the shim (if you have used tool ME48401Z01-SBF2000-358 ) with rivet 21215DE32 and interlaying sealant,Revision 2February 15, 2010Rib 421215DE3208Item 55Item 61-62Insert shim ifnecessaryDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 39/41INSTALLATION OF DRY BAY STRUCTUREAssemble all parts with interlaying sealant see Appendix 2- Final installation of the cup assembly and plug on the lower surface panel stiffenerRevision 2February 15, 2010Lower surface panelRib 4Rib 5Cup assembly11 x screw Item 3622201TX050008XF11 x nut Item 32 5RH8035M2 x screw Item 3322201TX050010XF2 x nut Item 32 5RH8035MAttachment directionPlug Item 17-78FGFB112500008FGFB122500008DRY BAY APPENDIX-1NOTE: For easier access, screws item 33 and 36 can be installed in the reverse direction.This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 40/49INSTALLATION OF DRY BAY STRUCTUREFilling the recess with bead sealantRevision 2February 15, 2010DRY ZONERib 4Fill the recess with beadsealantDO NOT BLANK OFF THEDRAINING HOLEFill the 2 holes with bead sealantDo not fill the anchor nutsBasic sealing methodsSee Standard Practices20-650DRY BAY APPENDIX-1INTERLAYING SEALANTCOVERING SEALANTBEAD SEALANTREAR SPARThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 41/49INSTALLATION OF DRY BAY STRUCTURERevision 2February 15, 2010DRY BAY APPENDIX-1Apply sealant strips (See Appendix 2 page5: Sealant application for strips definition)Apply a coat of covering sealant in dry baySealant stripsThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 42/49INSTALLATION OF DRY BAY STRUCTUREAssembling all parts with interlaying sealant: see Appendix 2- Final assembly of the half-framesRevision 2February 15, 20101 x screw Item 42 38471BE040008ME1 x nut Item 35 4RH8035MDetail 1Detail 1Shim Item 19-20FGFB112500016/FGFB122500016Attachmentdirection15 x screw Item 4122258TX050008XF15 x nut Item 32 5RH8035M1 x Screw Item 4322258TX050010XF1 x nut Item 32 5RH8035MDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 43/49INSTALLATION OF DRY BAY STRUCTURE- Final installation of the half-framesFinal assembly checkRevision 2February 15, 2010Rib 4Rib 5Half-frame Item 3-4FGFB112500012W1/FGFB122500012W1Shim Item 23FGFB1125000157 x screw 22201TX050007XF7 x nut 5RH8035M8 x screw Item 4938460BE044006ME+8 x nut Item 35 4RH8035MAttachmentdirectionAttachmentdirectionAttachmentdirectionCTHalf-frame Item 1-2FGFB112500011W1P01 /FGFB122500011W1P01DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 44/49INSTALLATION OF DRY BAY STRUCTURERevision 2February 15, 2010DRY BAY APPENDIX-1Make all sealant beads as per Appendix 2: Sealant application,Once all sealant beads are dry, apply a coat of covering sealant in the dry bay, on Rib 5 and on sealant stripsRib 5Covering sealant on Rib 5Covering sealant on sealant stripsThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 45/49INSTALLATION OF DRY BAY STRUCTUREAfter sealing of dry bay box structure with sealant as per APPENDIX 2Check for cleanliness of dry bay box structure before closingInstall door with interlaying sealantSealing finish with sealant on door as per APPENDIX 2Revision 2February 15, 2010CTRib 5Rib 4Lower surface panelDoor Item 5-6FGFB112500002/FGFB122500002Rear spar25 x screw Item 45 22201TX050007XF25 x washer Item 46 23111DG050A14 x screw Item 33 22201TX050010XF14 x washer Item 46 23111DG050AFUEL ZONEDRY ZONERib 5Rib 4DRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 46/49IDENTIFICATION OF SERVICE BULLETIN1) In the landing gear compartment, clean and degrease the area above the wing identification plate(2) Write the number of this Service Bulletin on the “SERVICE BULLETIN COMPLIANCE”labels and bond them with PR to each wing, above the identification plate.Revision 2February 15, 2010DRY BAY APPENDIX-1Identification plate,Intall this plate once theleak check has beensuccesfully completedNOTE:For FALCON 2000, 2000EX and 2000DX aircraft (refer to SB F2000-358 Page 5 or SB F2000EX-171 Page 5) ), replace the fuel door placard. The placards on the wing uppersurface must be replaced with the "New Fuel Quantity" placards.For FALCON 50 aircraft (refer to SB F50-496 Page 5), replace the fuel door placard. The placards on the wing upper surface mustbe replaced with the new ones (No FuelQuantity).For some FALCON 900 aircraft (refer to SB F900-388 Page 5), the placards on the wing upper surface must be replaced with the new ones (No Fuel Quantity).This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 47/49Revision 2February 15, 20100.39 in.10 mmFrame machining allowed in order to increasethe gap between the fasteners rib 5 / wingupper panel and the frame+ alodine protection, PPR + PAC + finishingpaintSpot facing Ø12-R2allowed if required+ alodine protection, PPR + PACDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 48/49Check the tightening torque and re-tightening torque of fastenersCheck that all screws and MGPL (nuts, bushes) are properly installed, heads flush8 141.60.20.350.751.21.617.73166.4SCREW0.2360.276106.20.315SCREWSCREWSCREWSCREW0.1580.2054567Ø inch Ø mmTorque lfb.in. Torque mdaNRevision 2February 15, 2010TIGHTENING TORQUEMETRIC FASTENER(as per STD 30908)CTDia. 4U9 (-23μ , -53μ)Dia. 0.158 in. (-0.9 μin.; -2.1 μin.)Dia. 4,4U9 (-23μ , -53μ)Dia. 0.173 in. (-0.9 μin.; -2.1 μin.)Dia. 5U9 (-23μ , -53μ)Dia. 0.197 in. (-0.9 μin. - 2.1 μin)Dia. 6.2 D10 ( +40Dia. 0,244 in. (+1.5 μin. +3.9 μin.)'LD'Dia. 0.205 in. (+1.2 μin. +3.1 μin.)Dia. 5.2 H9 ( +0Dia. 0,205 in. (+0 μin. +1.8 μin.)'LD+Dia. 0,197 in. (+0 μin. +1.8 μin.)BORING TOLERANCESDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE 49/49FINAL STEPSF50F900 F900EX F2000 F2000EX57-400 57-011 57-011 57-011 57-01127-811 27-811 27-811 27-811 27-811Paint the pickling area in accordance with the paint scheme used for the exterior of the aircraft.Revision 2February 15, 2010Install the flap actuator,(L25CF/R25CF)see procedure27-568 27-521 27-510 27-510 27-510Retract the flaps,see procedureInstall the wing’s structural fuel tankremovable panel,see procedureSee DRY BAY APPENDIX-3 HYDROGEN PRESSURE TEST FOR DRY BAYDRY BAY APPENDIX-1This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE1/10SEALANT APPLICATION DRY BAY WING BOXRevision 3February 15, 2009DRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE2/10Revision 3February 15, 2009MEANS OF PROTECTIONOPERATIONSRISKSCHEMICAL RISKS LINKED TO WORK STATIONPicklingVacuumcleaner+Latex glovesAnti-dust maskCleaning with solventLatex glovesSealant applicationLatex glovesLong sleeves clothesDRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE3/10Revision 3February 15, 2009MEANS OF PROTECTIONOPERATIONSRISKSCarrier handlingRisk of injury, fall ofobjects.NON CHEMICAL RISKS LINKED TO WORK STATIONDRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE4/10DRY BAY ZONERevision 3February 15, 2009View detail following pagesDry fence framemade in 2 parts (FM)Linking sheet metal angle mountedwith sealant interpositionInterstice filled with sealantafter mountingCups mounted with sealant interpositionCovering lay after fastening3 lines of existing rivets covered by a sealantstrip cemented with sealant on the fuel sideDRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE5/10INSTALLATION AND CEMENTING OF SEALANT BANDS WITH SEALANT ON THE REAR SPARManufacture sealant strips with bead sealantOn flap vane, cement sealant strip with sealantSealant strip FGFB112005PR134Qty : 1Sealant strip FGFB112005PR118Qty : 2Sealant strip FGFB112005PR042Qty : 2Revision 3February 15, 2009Sealant strip 1120005PR042 / 112005PR042Sealant strip FGFB1120005PR134Sealant strip FGFB1120005PR118Rib 6Rib 5Slat cap of inboardairbrake5.3 in. (134 mm).6 in.16 mm4.65 in. (118 mm)F-F sectionCovering sealant laySealant strips cementedwith sealantBasic sealing methodsSee Standard Practices20-650DRY BAY APPENDIX-2

.12 in. 3 mm.6 in.16 mm

.12 in. 3 mm

.12 in. 3 mm1.65 in. (42mm).6 in.16 mmThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE6/10Revision 3February 15, 2009DETAIL 1DETAIL 2RIB 4FUEL ZONEDRY ZONERIB 5DOOR MOUNTED WITH INTERLAYING SEALANTDRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE7/10DETAIL 1DETAIL 2Revision 3February 15, 2009INTERLAYING SEALANTCOVERING SEALANT2 coatingBEAD SEALANTShim Item 22Shim Item 24Stiffening angle Item 25RIB 5RIB 4Door Item 5-6Half-frame Item 1-2Half-frame Item 3-4Shim Item 23Basic sealing methodsSee Standard Practices20-650DRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE8/10SECTION B-BDETAIL 4Revision 3February 15, 2009INTERLAYING SEALANTCOVERING SEALANT2 coatingBEAD SEALANTUPPER WING SURFACELOWER WING SURFACEFUELZONEDRY ZONERecessesHalf frameDoorDoorHalf frameBasic sealing methodsSee Standard Practices20-650DO NOT BLANK OFF THEDRAINING HOLEDRY BAY APPENDIX-2INSIDE PROTECTION DRY BAYWITH A COVERING SEALANT LAYERFRAME / UPPERWING SURFACEDOOR / FRAME / RECESSESThis document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE9/10Revision 3February 15, 2009SEALANT BEADS BY INJECTION INPANEL DRILLINGS ACCORDING TOPAGE 9+ BEAD SEALANT ON TIPSCTDETAIL RIB 5 SPLICEUPPER WING SURFACELOWER WING SURFACEVisual control of sealant applicationDRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE10/10SECTION C-C SECTION C-CRevision 3February 15, 2009CTVIEW G : RIB 5 SPLICEVisual control of sealant applicationCLEANING OF THE INTERFACE : RIB 5 / RIB 5 DOUBLER+ SEALANT INJECTION THROUGH THE 12 DRILLINGS AFTERREMOVAL OF THE HAT SECTIONSee page 33 APPENDIX 1Bead sealant on joint of splice / rib 5+ covering sealant lay on all the fasteners in limit of sealantapplication zone, located on the back of the dry wall between rib 4and rib 5.Beware not to blank off the stiffener access .BLANK THE CHAMBEROFF WITH SEALANTINTERLAYING SEALANTCOVERING SEALANT2 coatingBEAD SEALANTBasic sealing methodsSee Standard Practices20-650DRY BAY APPENDIX-2This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE1/7Revision 2October 21, 2009DRY BAY HYDROGEN PRESSURE TESTDRY BAY APPENDIX-3This document is the intellectual property of DASSAULT AVIATION. It may not be used, reproduced, modified or disclosed withoutits authorization. DASSAULT AVIATION Proprietary Data.PAGE2/71) DRY BAY HYDROGEN PRESSURE TESTComposition of the gas to be used: 95%of Nitrogen and 5% of HydrogenHydrogen leak detector H2000-C including:Main unit P/N AS90544Probe P/N AS90232Cable P/N AS90175Leak Detector P/N AS90422 calibration toolRevision 2October 21, 2009Main unit P/N AS90544Cable P/N AS90175Probe P/N AS90232DRY BAY APPENDIX-3Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE3/71) DRY BAY HYDROGEN PRESSURE TESTLEAK DETECTOR START UPConnect the probe to the main unitCAUTION : Always connect the probe to the unit prior to switching onSwitch the unit ONGreen indicator comes on and red indicator slowly flashes during warm-up phaseThe unit is used in Detection mode and the sensitivity must be set to 10.TEST BEFORE USEBefore each use, test the probe using tool P/N AS90422Connect tool to Nitrogen cylinder (95% of Nitrogen and 5% of Hydrogen)Switch the unit ONOpen cylinder valve and bring the probe near the tool. If leak is not detected, replace the probe with a new one.Revision 2October 21, 2009DRY BAY APPENDIX-3The below procedure, allowing to determine if a leak is present or not, is applicable to the hydrogen leak detector H2000-C validated byDassault . Equivalent tooling (should be capable of detecting an helium or 95% of Nitrogen and 5% of Hydrogen leak rate of least 1.10-5mbar.l/sec) can be used under the responsability of the Service Station, with instructions to be defined by the Service Station.Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE4/71) DRY BAY HYDROGEN PRESSURE TESTSettingRevision 2October 21, 2009Detector - gas cylinderMain unit P/N AS90544DRY BAY- PRESSURE TEST AREAHosePRESSURE REDUCING VALVESET TO 5.1 psi (350mbars)DRY BAY APPENDIX-3CAUTION : ADJUST THE VALUE OF PRESSURE REDUCING VALVE TO 5.1 psi (350 mbars).Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE5/71) Insert the seal plug into the drainage hole on the lower wing surface2) Connect the pressure gauge flexible line on the rear spar :- Close the valves of the pressure gauge and the gas bottle- Connect the flexible line of the detector gas on the pressure gauge- Open the pressure gauge valve to 5.1 psi (350 m.bars) pressure, then close the valve- Wait 30 minutes, time for the gas is spread inside the dry bay- Safety : disconnect the DETECTOR GAS bottle’s flexible line portion- Search for a leak see page 6Revision 2October 21, 2009LOWER WING SURFACESEAL PLUGMA85202Z---F50B117REAR SPARdia. 8 drainage holeDRY BAY APPENDIX-3Pressure gaugePressure gauge : closedpositionGas cylinder hoseREAR SPARLOWER WING SURFACEPressure gauge hose connected to thedia.16 hole of the rear spar(between rib 4 and rib 5)PRESSURIZATION TOOLMA85201Z---FGFB112WARNING:Before re-injecting gas ventilate the dry bayCe document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE6/73) Detection withHydrogen leak detector H2000-COctober 21, 2009Revision 2ProbeRib 5Rib 4Green LEDRed LEDProbeSwitch the leak detector ONUsing the probe, search for a leak around the door and near rib 5(between rib 5 and rib 6).If a leak is detected, the unit rings up and the red indicator comes on.The unit indicates "LEAK" where detected.Locate the leak and resume leak detection.Leak repair- Remove the PR arround the leak- Clean and degrease this area- Apply a new bead of PR or covering sealant- Make a new test.DRY BAY APPENDIX-3DoorCe document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE7/7Install the plate (item 21) on the rear spar (see Appendix 1 page 13/49)October 21, 2009Revision 2ZONE AIf there is a leak in zones A, contact DASSAULT AVIATION for specific repair solution.DRY BAY APPENDIX-3Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE1/3Revision 1October 20, 2009REPORT OF DRILLING THE PR INJECTION HOLESDRY BAY APPENDIX-4Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE2/3The technician and inspector must each fill-in the appropriate boxes of the table belowLowersurfaceUppersurfaceLowersurfaceUppersurfaceRevision 1October 20, 2009SignatureCheck of marginsNameDatePre-drilling bit dia.Location of injection holes Technician InspectorSkinThe adjustment of the drill bit stop height (equalto the skin thickness)Check of drilling locationDRILLING THE PR INJECTION HOLESTABLE 1DRY BAY APPENDIX-4Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.PAGE3/3LowersurfaceUppersurfaceLowersurfaceUppersurfaceThe adjustment of the drill bit stop height (equalto the skin thickness)Drilling bit dia.The technician and inspector must each fill-in the appropriate boxes of the table belowLocation of injection holes Technician InspectorSkinSignatureNameDateRevision 1October 20, 2009DRILLING THE PR INJECTION HOLESTABLE 2DRY BAY APPENDIX-4Ce document est la propriété intellectuelle de DASSAULT AVIATION. Il ne peut être utilisé, reproduit, modifié, ou communiqué sans son autorisation . DASSAULT AVIATION Proprietary Data.

# SER VICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 1 A . MODIFICA

TION KIT

(1) KIT P/N SBF2000-0358A

Structural parts

NEW P/N QTY KEY WORD INSTRUCTIONS

DISPOSITION ITEM F

I

G

FGFB112500011W1P01 1 Half–frame LH 1

FGFB112500012W1 1 Half–frame LH 3

FGFB112500002 1 Door LH 5

FGFB112500003 1 Recess LH 7

FGFB112500004 1 Recess LH 9

FGFB112500005W1EQU 1 Angle assy LH 11

FGFB112500007 1 Bent section LH 13

FGFB112500006 1 Bent section LH 15

FGFB112500008 1 Plug LH 17

FGFB112500016 1 Shim LH 19

FGFB112500060W3 1 Angle LH 61

FGFB122500011W1P01 1 Half–frame RH 2

FGFB122500012W1 1 Half–frame RH 4

FGFB122500002 1 Door RH 6

FGFB122500003 1 Recess RH 8

FGFB122500004 1 Recess RH 10

FGFB122500005W1EQU 1 Angle assy RH 12

FGFB122500007 1 Bent section RH 14

FGFB122500006 1 Bent section RH 16

FGFB122500008 1 Plug RH 18

FGFB122500016 1 Shim RH 20

FGFB122500060W3 1 Angle RH 62

FGFB112005003 2 Plate LH/RH 21

FGFB112500009 2 Shim LH/RH 22

FGFB112500015 2 Shim LH/RH 23

FGFB113005042 2 Shim LH/RH 24

FGFB113005041 2 Angle bracket LH/RH 25

39600C332-13S 4 Gang-channel LH/RH 26

39600C123-05S 2 Gang-channel LH/RH 27

39600C102-04S 2 Gang-channel LH/RH 28

# SERVICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 2 T ool kit

NEW P/N QTY KEY WORD

ME48401Z01-SBF2000-358 1 Drill tool

ME48402Z01-SBF2000-358 1 Drill tool

Hardware part

NEW P/N QTY KEY WORD INSTRUCTIONS

DISPOSITION ITEM FIG



# NAS1133V4A 4 

# Screw 29



# MS21059L3 4 

# Nut 30



# 22201TX050011XF 6 

# Screw 31



# 5RH8035M 78 

# Nut 32



# 22201TX050010XF 32 

# Screw 33



# 38145BE040006ME 16 

# Screw 34



# 4RH8035M 36 

# Nut 35



# 22201TX050008XF 22 

# Screw 36



# 22201TX050006XF 14 

# Screw 37



# 6RH8035M 6 

# Nut 38



# 38472TX060012XF 2 

# Screw 39



# 38472TX060009XF 4 

# Screw 40



# 22258TX050008XF 30 

# Screw 41



# 38471BE040008ME 2 

# Screw 42



# 22258TX050010XF 2 

# Screw 43



# 38472TX050012XF 2 

# Screw 44



# 2201TX050007XF 64 

# Screw 45



# 23111DG050A 78 

# Washer 46



# 22201TX050003XF 4 

# Screw 47



# 5SF5009M 4 

# Nut 48



# 38145BE044006ME

or

38460BE044006ME 20 

# Screw

Screw used instead of rivet 49



# 38471BE044006ME 6 

# Screw 50



# 38471BE044005ME 4 

# Screw 51



# 38460BE044005ME 4 

# Screw 52



# 21215DE4011 10 

# Rivet 53



# 21218DB2408J 20 

# Rivet 54

21218DE3208 8 Rivet 55

21215DE2410J 8 Rivet 56

21215DE4009 30 Rivet 57

79160 2 “SER VICE BULLETIN

COMPLIANCE” label 58

# SERVICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 3 (2) KIT P/N SBF2000-0358B

T ool kit to be made available in Service Center

.

P/N Q

T

Y KEY WORD T OOL BOX

ITEM

MA95101Z00-FGFB112500001 1 T ool box

Comprising:

MA48402Z00-FGFB117000103 1 Lower panel stif fener drilling tool (LH) 1

MA48401Z00-FGFB112500003 1 Recess/Stif fener drilling tool (LH) 2

MA40301Z00-FGFB112500010 1 Frame maintaining tool (LH) 3

MA48401Z00-FGFB112500010 1 Rib 4/half-frame drilling tool (LH) 4

MA48401Z00-FGFB116 1 Lower-panel Rib 4/Rib 5 drilling grid (LH) 5

MA48402Z00-FGFB112500010 1 Rib 5/half-frame drilling tool (LH) 6

MA48402Z00-FGFB127000103 1 Lower panel stif fener drilling tool (RH) 7

MA48401Z00-FGFB122500003 

# 1 Recess/Stif fener drilling tool (RH) 8

MA40301Z00-FGFB122500010 1 Frame maintaining tool (RH) 9

MA48401Z00-FGFB122500010 1 Rib 4/half-frame drilling tool (RH) 10

MA48401Z00-FGFB126 1 Lower-panel Rib 4/Rib 5 drilling grid (RH) 11

MA48402Z00-FGFB122500010 1 Rib 5/half-frame drilling tool (RH) 12

MA48401Z00-FGFB112005A2 1 Blanking plate rear spar boring tool (L/H

and R/H) 13

MA61101Z00-F50B101001 8 Washer , pinning 14

MA61101Z00-F50B101002 8 Washer , pinning 15

MA48401Z00-FGFB116001 3 Drill–bush, template 16

MA48401Z00-FGFB116002 3 Drill–bush, template 17

MA48401Z00-FGFB112500003051 10 Drill–bush, shouldered, dia. 2.5 18

MA48401Z00-FGFB112500003052 10 Drill–bush, shouldered, dia. 4 19

MA48401Z00-FGFB112500003053 10 Drill–bush, shouldered, dia. 5 20

MA48401Z00-FGFB112500003054 10 Drill–bush, shouldered, dia. 4.2 21

MA48401Z00-FGFB112500003055 10 Drill–bush, shouldered, dia. 4.4 22

MA48401Z00-FGFB112500003031 10 Pin, knurled dia 2.5 23

MA48401Z00-FGFB112500003041 10 Nut, dia 2.5 23

MA48401Z00-FGFB112500003032 10 Pin, knurled dia 4 24

MA48401Z00-FGFB112500003042 10 Nut, dia 4 24

MA48401Z00-FGFB112500003033 10 Pin, knurled dia 5 25

MA48401Z00-FGFB112500003043 10 Nut, dia 5 25

MA60401-01-DIA4U9 8 Pin, centering, dia. 4 U9 26

MA60401-01-DIA42U9 4 Pin, centering, dia. 4.2 U9 27

MA60401-01-DIA44U9 4 Pin, centering, dia. 4.4 U9 28

MA48401-01 3 Drill–bush, with handle, int. dia. 2.5, ext.

dia 4 29

# SERVICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 4

P/N Q

T

Y KEY WORD INSTRUCTIONS

DISPOSITION

MA95101Z00-FGFB112 1 T ool box

Comprising:

MA85202Z00-F50B117 2 Seal plug L/H and R/H

MA85201Z00-FGFB112 1 Presssurization tool applicable

ME62001Z00-SBF2000-358 2 Positioning template

ME29501Z00-38460BE040SB1 16 Screw

NOTE: In the tool reference 00 stand for the serial number

.

(3) KIT P/N SBF2000-0358F

This kit is to be orded for each SB application

NEW P/N Q

T

Y KEY WORD

MA29501Z00-F50B101001 1 Nozzle

ME29502Z00-SBF2000-358 2 Injection hose



# (4) KIT FOR APPLICA

TION OF SB F2000-358 ONL Y

KIT P/N SBF2000-0358C for aircraft without BS F2000-202 or without M1903

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

F2MA090200003A6 2 Instruction placard F2MA090200003XX Discard

F2MA090100024A6 1 Instruction placard F2MA090100024XX Discard



# KIT P/N SBF2000-0358D for aircraft with BS F2000-202 or with M1903

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

F2MA090200003A7 2 Instruction placard F2MA090200003XX Discard

F2MA090100024A7 1 Instruction placard F2MA090100024XX Discard

# SERVICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 5 (5) KIT FOR APPLICA

TION OF SB F2000EX 171 ONL Y

KIT P/N SBF2000X0171A for F2000EX aircraft

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

F2MB090200003A3 2 Instruction placard F2MB090200003XX Discard

F2MB090100024A3 1 Instruction placard F2MB090100024XX Discard



# KIT P/N SBF2000X0171B for F2000DX aircraft

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

F2ME090200003A1 2 Instruction placard F2ME090200003 Discard

F2ME090100024A1 1 Instruction placard F2ME090100024 Discard



# (6) KIT FOR APPLICA

TION OF SB F50-496 ONL Y

KIT P/N SBF50–0496AR1

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

F50B090100024A1 1 Instruction placard F50B800499012XX Discard

FGFB090200003A4 2 Instruction placard F50B800501002XX Discard



# (7) KIT FOR APPLICA

TION OF SB F900-388 ONL Y DFOR AIRCRAFT S/N 1 THROUGH 20

KIT P/N SBF900-0388A

NEW P/N Q

T

Y KEY WORD OLD P/N INSTRUCTIONS

DISPOSITION

FGFB090200003A4 2 Instruction placard FGFB090200003A1 Discard

# SERVICE BULLETIN

DR Y BA Y – APPENDIX 5

February 15, 2010

Revision 3 Page 6 

# END OF DOCUMENT B . LOCAL PROCUREMENT

As per chapter12, ingredients and consumable product

– Interlaying sealant PS 892C2.

– Covering sealant PR 1776A AS or AC350.

– Bead sealant PR 1776B2 or PR 1422B2.

– Filleralu.

– Alodine 1200.

– PU 66 CELOMER paint scheme.

– Stripper MIL-R-81294.

Specific tool:

(1) Hydrogen leak detector

– Dassault validated hydrogen leak detector comprising:

Main unit P/N AS90544

Probe P/N AS90232

Cable P/N AS90175

Leak detector calibration tool P/N AS90422

T o be used with a 95% of Nitrogen and 5% of Hydrogen gas

– Or an equivalent tool under the responsability of the Service Station

(2) PR injection gun

– Injection gun capable of an injection pressure of at least 1015 psi (70 bars)

– If your gun does not feature these characteristics, order kit SBF2000-0358E or hire gun

RB1140-04 and adapter ME29501Z00-SBF2000-358, otherwise using your gun implies to

manufacture the adapter locally for connecting the injection hose provided in the kit

SBF2000-0358F.

KIT P/N SBF2000-0358E

NEW P/N QTY KEY WORD

MA29501Z00-1VALISE 1 T ool case

comprising: 1

MA29501Z00-1 1 PR injection gun

MA29502Z00-F50B101001 1 Union

MA29502Z00-F50B101002 1 Union nut