# Dassault Service Bulletin 7X-601: No revision named

- Rights: © Dassault Aviation. Filed by the FAA in regulations.gov docket FAA-2025-1729, the docket of AD 2025-22-05. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Dassault Service Bulletin 7X-601](https://openairdocs.org/service-documents/dassault/7x-601.md)
- Title as filed: SB_7X-601_Initial_04-24-2023
- Pages: 29
- PDF: https://openairdocs.org/files/sha256/f0/94/f0941e2d51a3df1ea5d238c76a17a57f722e474d6e6c7195c4e5392d9f8c86a9
- Page: https://openairdocs.org/service-documents/dassault/7x-601/file/f0941e2d51a3

## Text

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### Page 1

FALCON 7X
No 601
APRIL 24, 2023
 
ATA 00
GENERAL
ENHANCED AVIONICS SYSTEM
EASY IV - NGIO AIRCRAFT
FALCON SERVICE BULLETIN
Copyright © 2023 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.
769

### Page 2

GENERAL
ENHANCED AVIONICS SYSTEM
EASY IV - NGIO AIRCRAFT
Initial issuance April 24, 2023
List of effective pages:
1 to 27
FALCON 7X 7X -601
ATA 00

### Page 3

GENERAL
ENHANCED AVIONICS SYSTEM
EASY IV - NGIO AIRCRAFT
 
1. PLANNING INFORMATION
A. EFFECTIVITY
This Service Bulletin is applicable to FALCON 7X aircraft with serial numbers 262 thru 400 that have
not previously implemented DASSAULT AVIATION FALCON modification M2059.
B. REASON
The purpose of this Service Bulletin is to upgrade the aircraft avionics to the EASy IV load 18.0
standard that includes the following features:
• an advanced version of the INAV moving map with interactive Vertical Situation Display,
combined with new Vivid Displays,
• a combination of the most advanced versions of Honeywell’s NextGen FMS and Communication
Management Function,
• a dual charts function on aircraft already equipped with single charts, which introduces
redundancy for the use of the electronic Jeppesen charts,
• improved Jeppesen charts function with a new Night mode, a Panoramic mode, as well as the
display of the aircraft symbol on all georeferenced terminal charts (dual charts required),
• Runway Overrun Awarness and Alerting System (ROAAS) which analyzes the aircraft trajectory
and the TOLD landing performance to determine if the aircraft can safely come to a full stop
within the remaining runway length,
• enhanced ADS-B IN Cockpit Display of Traffic Information (CDTI) with 2 applications:
• Visual Separation on Approach (VSA): displays specific traffic information relative to select
traffic, to facilitate visual separation,
• AIRB: displays ADS-B airborne traffic on the INAV moving map,
• enhanced TOLD function,
• weak point fix in the Falcon 7X EASy avionics architecture (equivalent to DASSAULT AVIATION
Service Bulletin 7X-592 "EASY II 5TH CERT - NG I/O"). This weak point can lead to the display
of misleading data on the display units.
C. DESCRIPTION
The operation consists in:
• modifying the aircraft wiring,
• modifying the hardware configuration:
• replacement of modules in MAU 1 and 2,
• replacement of NIM modules,
• replacement of ASCB bus coupler modules,
• replacement of TCAS transceiver and antennas.
• performing a full software load.
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D. COMPLIANCE
If you choose to comply with this Service Bulletin, accomplishment can be performed at your
convenience.
E. APPROVAL
This Service Bulletin covers DASSAULT AVIATION modifications:
• M-OPT640, M-OPT1142, M-OPT1144, M1254, M1314 and M2059 that have been approved by
EASA.
• M-OPT22, M2034, M2060 and M2112 that have been approved under the authority of the DOA
ref. EASA.21J.051.
The technical content of this document is approved under the authority of DOA nr. EASA.21J.051.
NOTE: For aircraft not under EASA and FAA regulations, please refer to the Falcon Service Advisory
that lists the countries for which EASy IV is approved.
F. LABOR
Estimated labor-hours: Refer to Service Bulletin Commercial Summary.
NOTE: 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.
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:
• U.S.A. and CANADA: 1-800-800-4036
• MEXICO: 001-800-800-4036
• Other countries: 1-201-541-4809
Email to: Customer.Care@DassaultFalconJet.com
Other continents: DASSAULT AVIATION
Falcon Spares
54, AVENUE MARCEL DASSAULT
B.P. 24
33701 MERIGNAC Cedex (FRANCE)
Telephone: 33 (0)5.56.18.44.44
Email to: dafsorders@dassault-aviation.com
Price and availability on request.
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DASSAULT AVIATION Proprietary Data

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H. TOOLING - PRICE AND AVAILABILITY
TOOL BOX (TO-20-008)
I. WEIGHT AND BALANCE
Change in weight: None.
Change in balance with respect to 25% MAC: None.
J. REFERENCES
Structural Repair Manual:
• DRILLING (Refer to RPI 51-40-03)
• RIVETING (Refer to RPI 51-40-04)
• COUNTERSINKING (Refer to RPI 51-40-06)
Aircraft Maintenance Manual:
• GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801)
• USE OF THE AIRCRAFT MAINTENANCE PROCEDURES (Refer to TASK 20-00-00-910-803)
• BASIC SEALING METHODS (Refer to TASK 20-32-00-390-801)
• REPLACEMENT OF LOCKWIRES AND SNAPWIRES (Refer to TASK 20-42-01-960-801)
• PROTECTION SCHEME (Refer to SDS 20-60-00)
• APPLICATION OF ALODINE (Refer to TASK 20-60-00-370-801)
• APPLICATION OF TYPE 5014 AND 5015 POLYURETHANE PRIMERS (Refer to TASK
20-60-00-370-809)
• UNPLUGGING / PLUGGING OF THE MAU BACKSHELLS (Refer to TASK 20-92-00-910-801)
• INSERTION AND EXTRACTION OF A WIRE FITTED WITH A LOCK-IN CONTACT (Refer to
TASK 20-95-00-910-801)
• ENERGIZATION / DE-ENERGIZATION OF THE AIRCRAFT SYSTEMS (Refer to TASK
24-00-00-860-801)
• REMOVAL / INSTALLATION OF THE MAU CHASSIS (Refer to TASK 31-41-01-900-801)
• REMOVAL / INSTALLATION OF THE POWER SUPPLY MODULES (Refer to TASK
31-41-05-900-801)
• REMOVAL / INSTALLATION OF THE PROCESSOR MODULES (Refer to TASK
31-41-09-900-802)
• OPERATIONAL TEST OF THE DATA ACQUISITION SYSTEM - MAU (Refer to TASK
31-42-00-710-801)
• REMOVAL / INSTALLATION OF THE NIC / PROCESSOR MODULES (Refer to TASK
31-42-01-900-801)
• REMOVAL / INSTALLATION OF THE ASCB BUS COUPLERS (Refer to TASK
31-42-17-900-801)
• REMOVAL / INSTALLATION OF THE NETWORK INTERFACE MODULES (NIM) (Refer to
TASK 31-43-05-900-801)
• REMOVAL / INSTALLATION OF THE ADVANCED GRAPHICS MODULES (AGM) (Refer to
TASK 31-60-17-900-801)
• REMOVAL / INSTALLATION OF THE AIR DATA, ATTITUDE AND HEADING REFERENCE
SYSTEM (ADAHRS) UNIT (Refer to TASK 34-22-01-900-801)
• OPERATIONAL TEST OF THE TRAFFIC / COLLISION AVOIDANCE SYSTEM (TCAS) (Refer to
TASK 34-44-00-710-801)
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• REMOVAL / INSTALLATION OF THE TCAS TRANSCEIVER (Refer to TASK 34-44-01-900-801)
• REMOVAL / INSTALLATION OF THE TCAS ANTENNAS (Refer to TASK 34-44-05-900-801)
• OPERATIONAL TEST OF THE ENHANCED GROUND PROXIMITY WARNING SYSTEM
(EGPWS) (Refer to TASK 34-45-00-710-801)
• INSTALLATION OF AVIONICS SOFTWARE TOOLS (Refer to TASK 45-10-00-860-801)
• PERIODIC DATABASE LOADING (Refer to TASK 45-90-00-860-801)
• DATABASE LOADING (Refer to TASK 45-90-00-860-803)
• SOFTWARE LOADING (Refer to TASK 45-90-00-860-804)
• USE OF THE APM SETTINGS TOOL (Refer to TASK 45-91-00-910-801)
• REMOVAL / INSTALLATION OF THE CABIN FLOOR PANELS (Refer to TASK
53-04-01-900-801)
• REMOVAL / INSTALLATION OF THE OPTIONAL EQUIPMENT FLOOR PANEL (Refer to TASK
53-04-07-900-801)
• OPENING / CLOSING OF THE NOSE CONE (Refer to TASK 53-10-09-860-801)
• REMOVAL / INSTALLATION OF THE T34 BODY FAIRINGS (Refer to TASK 53-60-00-900-801)
Wiring Diagram Manual:
• Refer to WD 34-23-50
• Refer to WD 34-40-00
• Refer to WD 34-45-00
DASSAULT AVIATION Service Bulletins:
• 7X-603 "LOADING THE LATEST AMI DATABASE AND SWITCHING AMI DATABASE
PROVIDER"
K. OTHER PUBLICATIONS AFFECTED
The following publication is revised to account for the changes introduced by this Service Bulletin:
• Airplane Flight Manual revision 25 or subsequent revision
The following publications will be revised at a later date to account for the changes introduced by this
Service Bulletin:
• CODDE 1 revision 14
• CODDE 2 revision 25
• QRH 1 revision 25
• QRH 2 revision 25
• Illustrated Parts Catalog
• Aircraft Maintenance Manual
• Fault Isolation Manual
• Wiring Diagram Manual
Operational Suitability Data:
• Operational Suitability Data - Flight Crew:
• OSM-FC revision 8 or subsequent revision
• Operational Suitability Manual - Master Minimum Equipment List:
• OSM-MMEL revision 16 or subsequent revision
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### Page 7

2. ACCOMPLISHMENT INSTRUCTIONS
Refer to fig. 1 for general view of the work area.
A. GENERAL INSTRUCTIONS AND SAFETY PRECAUTIONS
(1) Obey the general maintenance and safety precautions (Refer to TASK 20-00-00-910-801).
(2) Obey the general electrical instructions:
(a) When mechanical retrofit and/or modification operations are performed on the aircraft, take
special care to protect the wiring in order to prevent metal chips (or burrs) from penetrating
the wire bundles, since these could eventually damage the insulation sheathing of the wires.
Whenever possible, it is recommended that the wiring be removed from the work area. If
that is not possible, it is absolutely necessary to protect the wiring.
(b) Due to the risk of damaging the wire insulation, it is prohibited to blindly drill holes through a
box structure containing wiring.
(c) New wires that are installed alongside existing wires should be secured with the existing
clamp.
(d) Check that all connections are properly protected to ensure proper insulation, and that
markings are visible and appropriate.
(e) Connector wires should be inserted and extracted as per the recommendations in Standard
Practices (Refer to TASK 20-95-00-910-801).
(f) Electrical and electronic equipment should be removed and installed as per the
recommendations in Standard Practices (Refer to TASK 20-00-00-910-801).
(g) Visually inspect the work area for particles or debris, then vacuum-clean the area. Blowing
compressed air is prohibited since it could move metal chips into inaccessible areas.
(3) Obey the Structural Repair Manual and Standard Practices procedures for the following
operations:
• drilling (Refer to RPI 51-40-03),
• riveting (Refer to RPI 51-40-04),
• countersinking (Refer to RPI 51-40-06),
• basic sealing methods (Refer to TASK 20-32-00-390-801).
B. PRELIMINARY STEPS
(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-803).
(2) Open the nose cone ( 210) (Refer to TASK 53-10-09-860-801).
(3) Remove the necessary equipment and interior accommodation items to get access to cabin floors
(121EZ), (121FZ), (121GZ), (131BZ) and (131CZ).
(4) Remove the cabin floors listed above (Refer to TASK 53-04-01-900-801).
(5) Remove the optional equipment floor panel (Refer to TASK 53-04-07-900-801).
(6) Remove the AIR DATA, ATTITUDE AND HEADING REFERENCE SYSTEM (ADAHRS) UNIT
(Refer to TASK 34-22-01-900-801).
(7) Remove the TCAS transceiver ( 103NP) (Refer to TASK 34-44-01-900-801).
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(8) Remove the MAU 1 chassis (Refer to TASK 31-41-01-900-801).
(9) Remove the backshells from the AGM modules (2301FD) and (2401FD) (Refer to TASK
20-92-00-910-801).
(10) Check the Mod version of Power Supply modules (1101FY), (1201FY), (1301FY) and (1401FY)
as follows:
(a) Remove the backshells from the power supply modules.
(b) For each power supply module, check that mod version of PN 7038248-1901 is B or higher.
NOTE: If not, the power supply module must be replaced by a PN 7038248-1901 Mod B or
higher.
C. ELECTRICAL MODIFICATIONS
(1) Perform the following modification on each AGM backshell 1:
(a) Fill the new connector ( 2-fig. 2) with blanking pins.
NOTE: This new connector has no wire connected to it.
(b) Open backshell 1.
(c) Remove the blank backplate ( a-fig. 2).
(d) Install the connector backplate ( 1-fig. 2) and the connector (2-fig. 2).
(e) Close backshell 1.
(2) Perform the following modification on each AGM backshell 2:
(a) Open backshell 2.
(b) Disconnect the two wires from the backshell ( item 1-fig. 3).
(c) Cap and stow the two wires inside the backshell.
(d) Close backshell 2.
(3) Perform the following modification on the backshell of the EGPWS 1 module ( 101FW):
(a) Open the backshell.
(b) Disconnect the two wires from the backshell ( item 2-fig. 3).
(c) Cap and stow the two wires with the wiring bundle under the cabin floor.
(d) Discard the backshell.
(4) Perform the electrical modification as per wiring diagrams fig. 4 and fig. 5.
(5) Perform an electrical continuity check of the aircraft wiring.
D. HARDWARE / EQUIPMENT MODIFICATIONS
(1) Install the new TCAS transceiver ( 103NP) (Refer to TASK 34-44-01-900-801).
(2) Re-install the MAU 1 chassis (Refer to TASK 31-41-01-900-801), and do the following steps:
(a) Install the processor P/N 7034056-1901 in slot 14 (initially in slot 16) (1-fig. 6 ) (Refer to
TASK 31-41-09-900-802).
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(b) Install the new processor P/N 7034056-1902 in slot 16 (2-fig. 6 ) (Refer to TASK
31-41-09-900-802).
(c) Install the new NIC/processor modules (2101FY) and (2201FY) (3-fig. 6 ) (Refer to TASK
31-42-01-900-801).
(d) Install the new AGM modules (2101FD) and (2201FD) (4-fig. 6 ) (Refer to TASK
31-60-17-900-801).
(e) Install the new processor 10 module (2051FY) P/N 7034056-1903 in slot 13 (in place of the
EGPWS 1 module) (5-fig. 6) (Refer to TASK 31-41-09-900-802).
(f) If needed (see step 2.B.(10)), install the new power supply modules (1101FY) and (1201FY) 
(6-fig. 6) (Refer to TASK 31-41-05-900-801).
(g) Re-install the other MAU 1 modules (Refer to TASK 31-41-01-900-801).
(h) Remove and replace the MAU 1 ASCB bus coupler module (5101FY) (Refer to TASK
31-42-17-900-801).
(3) Do the following steps on MAU 2:
(a) Remove and replace the NIC/processor modules (2301FY) and (2401FY) (3-fig. 6) (Refer to
TASK 31-42-01-900-801).
(b) Remove and replace the AGM modules (2301FD) and (2401FD) (4-fig. 6) (Refer to TASK
31-60-17-900-801).
(c) If needed (see step 2.B.(10)), remove and replace the power supply modules (1301FY) and
(1401FY) (6-fig. 6) (Refer to TASK 31-41-05-900-801).
(d) Remove and replace the MAU 2 ASCB bus coupler module (5201FY) (Refer to TASK
31-42-17-900-801).
(4) Remove and replace the NIM modules (1101NZ) and (1201NZ) (Refer to TASK
31-43-05-900-801).
(5) Replace the lower TCAS antenna as follows:
(a) Remove the fuel equipment bay door ( 151AL) (Refer to TASK 53-60-00-900-801).
(b) Remove the lower TCAS antenna ( 303NP) from the fuel equipment bay door (Refer to TASK
34-44-05-900-801).
(c) Apply aircraft paint finish on the new fuel equipment bay door  (151AL) (item 1) in
accordance with the Protection Scheme (Refer to SDS 20-60-00).
(d) Using new screws (item 2) and washers (item 3), install the new lower TCAS antenna
(503NP) (item 4) on the new fuel equipment bay door (Refer to TASK 34-44-05-900-801).
(e) Install the new fuel equipment bay door ( 151AL) (Refer to TASK 53-60-00-900-801).
(6) External access only: replace the upper TCAS antenna following fig. 7:
(a) Remove the upper TCAS antenna (203NP) from the fuselage (Refer to TASK
34-44-05-900-801) and retrieve the eight screws and washers.
(b) Remove the microballon taper shim specific to the old antenna.
(c) Prepare the work area:
• use a Plexiglas spatula to remove sealant to obtain a clean surface,
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• clean the work area with lint-free cloth moistened with cleaner.
(d) Protect both exposed lateral flange outer shims (a-fig. 7 ) with alodine (Refer to TASK
20-60-00-370-801) and anti-corrosion primer (Refer to SDS 20-60-00).
(e) With the help of a template (local procurement), create a microballon taper shim using
compound EC 3524 (b-fig. 7).
(f) Apply 5 mm interlaying sealant on the existing outer shim (c-fig. 7) all along the internal (d-
fig. 7) and external (e-fig. 7) borders (Refer to TASK 20-32-00-390-801).
(g) Apply an interlay of interlaying sealant between the new shim and the fuselage (f-fig. 7)
(Refer to TASK 20-32-00-390-801).
(h) Install the new interface shim ( 1-fig. 7) above the existing outer shim.
NOTE: This shim will be fastened with the eight antenna screws.
(i) Make sure that the O-ring provided with the new antenna is not installed.
(j) Make sure that the wiring insulating sleeves and the connectors, on aircraft side and TCAS
antenna side, are in good condition:
• no unwanted material in the connectors,
• no cracks on the wiring insulating sleeves,
• no pins bent,
• no corrosion on the electrical connectors.
(k) Apply demolding agent  around the antenna periphery exterior side (Refer to TASK
20-32-00-390-801).
(l) Remove the protective film marked "ANTENNA SIDE" from the polyurethane gasket (2-fig.
7).
NOTE: The protective film marked "AIRCRAFT SIDE" must stay in place on the
polyurethane gasket.
(m) Position the polyurethane gasket on the antenna.
(n) Remove the protective film marked "AIRCRAFT SIDE" from the polyurethane gasket.
(o) Position the upper TCAS antenna (603NP) (3-fig. 7), with the arrow on the antenna pointing
in the aircraft forward direction.
(p) Connect the four coaxial cables to the relevant connectors on the upper TCAS antenna.
NOTE: Each coaxial cable and its corresponding connector are identified by a specific
color.
(q) Safety the coaxial cables with the lockwire (Refer to TASK 20-42-01-960-801).
(r) Install the upper TCAS antenna.
(s) Install the screws and washers retrieved.
CAUTION: DO NOT OVERTORQUE THE SCREWS AS THIS CAN CAUSE CRACKS IN THE
ANTENNA.
(t) Tighten the screws to a torque of 2.2 to 2.8 N.m (19 to 25 lbf.in).
(u) Apply bead sealant (g-fig. 7) around the antenna base (Refer to TASK 20-32-00-390-801).
(v) Insert AIREX foam (h-fig. 7), cut to the shape of the screw holes, in the screw holes.
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(w) Apply covering sealant  (i-fig. 7 ) on the heads of the screws (Refer to TASK
20-32-00-390-801).
(x) Apply white primer 5014  (j-fig. 7) on the compound EC 3524  (b-fig. 7) (Refer to TASK
20-60-00-370-809).
(y) Apply aircraft paint finish up to the paint limit in accordance with the Protection Scheme
(Refer to SDS 20-60-00).
(7) Internal and external access: replace the upper TCAS antenna following fig. 8:
(a) Remove the upper TCAS antenna (203NP) from the fuselage (Refer to TASK
34-44-05-900-801) and discard the screws.
(b) Remove the microballon taper shim specific to the old antenna.
(c) Counterdrill the rivets ( a-fig. 8) (b-fig. 8), (c-fig. 8) and (d-fig. 8) to remove the existing outer
shim and the nut plates.
(d) Prepare the work area:
• use a Plexiglas spatula to remove sealant to obtain a clean surface,
• clean the work area with lint-free cloth moistened with cleaner
(e) Plug the six old rivet positions ( b-fig. 8) with new rivets (2-fig. 8).
(f) Install the 14 rivets ( 1-fig. 8) to hold the skin on the stringer.
(g) Pin and hold in position the new interface shim ( 6-fig. 8) on the fuselage.
(h) From inside, transfer the holes (3-fig. 8) and (4-fig. 8) from the fuselage to the shim to install
new rivets.
NOTE: Depending on aircraft configuration, two of the holes (4-fig. 8) may be missing. In
this case, use the dimensions shown on the fig. 8 to locate the holes to be drilled.
(i) From outside, transfer the three holes ( 5-fig. 8) from the new shim (6-fig. 8) to the fuselage.
(j) Counterdrill the three holes for the rivets ( 5-fig. 8).
(k) Remove the shim.
(l) Countersink all holes on the shim.
(m) Apply a 5 mm thick layer of interlaying sealant on the shim all along internal (e-fig. 8) and
external (f-fig. 8) borders (Refer to TASK 20-32-00-390-801).
(n) Install the shim using rivets ( 4-fig. 8) and (5-fig. 8).
(o) Apply an interlay of interlaying sealant between the nut plates and the fuselage (g-fig. 8)
(Refer to TASK 20-32-00-390-801).
(p) Re-install the nut plates using rivets ( 3-fig. 8).
(q) With the help of a template (local procurement), create a microballon taper shim using
compound EC 3524 (h-fig. 8).
(r) Make sure that the O-ring provided with the new antenna is not installed.
(s) Make sure that the wiring insulating sleeves and the connectors, on aircraft side and TCAS
antenna side, are in good condition:
• no unwanted material in the connectors,
• no cracks on the wiring insulating sleeves,
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• no pins bent,
• no corrosion on the electrical connectors.
(t) Apply demolding agent  around the antenna periphery exterior side (Refer to TASK
20-32-00-390-801).
(u) Remove the protective film marked "ANTENNA SIDE" from the polyurethane gasket (7-fig.
8).
NOTE: The protective film marked "AIRCRAFT SIDE" must stay in place on the
polyurethane gasket.
(v) Position the polyurethane gasket ( 7-fig. 8) on the antenna.
(w) Remove the protective film marked "AIRCRAFT SIDE" from the polyurethane gasket.
(x) Position the upper TCAS antenna (603NP) (8-fig. 8), with the arrow on the antenna pointing
in the aircraft forward direction.
(y) Connect the four coaxial cables to the relevant connectors on the upper TCAS antenna.
NOTE: Each coaxial cable and its corresponding connector are identified by a specific
color.
(z) Safety the coaxial cables with the lockwire (Refer to TASK 20-42-01-960-801).
(aa) Install the new screws (9-fig. 8) and washers (10-fig. 8).
CAUTION: DO NOT OVERTORQUE THE SCREWS AS THIS CAN CAUSE CRACKS IN THE
ANTENNA.
(ab) Tighten the screws to a torque of 2.2 to 2.8 N.m (19 to 25 lbf.in).
(ac) Apply bead sealant (i-fig. 8) around the antenna base (Refer to TASK 20-32-00-390-801).
(ad) Insert AIREX foam (j-fig. 8), cut to the shape of the screw holes, in the screw holes.
(ae) Apply covering sealant  (k-fig. 8 ) on the heads of the screws (Refer to TASK
20-32-00-390-801).
(af) Apply white primer 5014 (l-fig. 8) on the compound EC 3524 (h-fig. 8).
(ag) Apply aircraft paint finish up to the paint limit in accordance with the Protection Scheme
(Refer to SDS 20-60-00).
(8) Re-install all the other equipment removed when performing this Service Bulletin.
E. SOFTWARE LOADING
CAUTION: PRIOR TO STARTING THE SOFTWARE LOADING, MAKE SURE THAT YOU HAVE ALL
THE REQUIRED CD-ROMS MENTIONED IN PARAGRAPH 3.
(1) Energize the aircraft systems (Refer to TASK 24-00-00-860-801  - "Connection of the electrical
ground power unit" and “Energization with the electrical ground power unit”).
(2) Record the current APM Settings configuration of the aircraft (Refer to TASK 45-91-00-910-801).
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DASSAULT AVIATION Proprietary Data

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(3) Uninstall the old version of the Remote Terminal software from the client laptop.
CAUTION: USING AN INAPPROPRIATE VERSION OF CMC-RT / DLS TO LOAD THE
SOFTWARE OR DATABASE CAN LEAD TO AGM FAILURES WHICH MAY
REQUIRE AGM REPLACEMENT.
(4) Install the new version of the Remote Terminal software included in the HONEYWELL EPIC Tools
CD-ROM (Refer to TASK 45-10-00-860-801).
(5) Load the new software and databases in accordance with the data loading procedures (Refer to
TASK 45-90-00-860-801 ), (Refer to TASK 45-90-00-860-803 ), (Refer to TASK
45-90-00-860-804) and following the sequence hereafter:
CAUTION: PRIOR TO STARTING THE OPERATIONAL SOFTWARE LOADING, MAKE SURE
THAT THE “CRC32” VALUE CONTAINED ON THE LOAD CD-ROM MATCHES THE
CRC VALUE SHOWN ON FALCON PORTAL (REFER TO TASK 45-90-00-860-804).
NOTE: The "System Config ID" pages to check APM Data and Database Config ID can only be
accessed after all the FMS databases (FMS AEDB / Magvar / TOLD Database / INDS
EPIC AIRSPACE & COMM NAVIGATION DATA) have been loaded.
SOFTWARE KEY WORD EFFECTIVITY
Operational Software Top Level
System Part Number
EB60007394-0116
Load 18.0
All aircraft
Creation of the APM Settings files:
• Create and save the APM Settings file on the hard drive using the APM
Settings Tool included in the HONEYWELL EPIC Tools CD-ROM and
the configuration noted previously. Use the settings.def definition file
from the load 18.0 Operational Software located in the apm_defn folder.
NOTE: The create and load feature should not be used.
• Load the settings file created from the hard drive using DLS.
• Make a copy of this file generated by the APM Settings Tool on a media
(e.g. CD-ROM) and keep a copy on-board the aircraft.
NOTE: It is recommended to print the "settings.text" file generated by
the APM Settings Tool to keep a record of the latest settings
configuration.
TT60005561-XXXXX*
APM Options parameter configuration
NOTE: If an authorization code is
required, it will be specified on
the CD ROM label (Refer to
TASK 45-90-00-860-803).
18.0* LDI
Refer to 7X-603 Airline Modifiable Information (AMI)database Aircraft with Datalink installed
V0015* FLT (Fault Code database)
All aircraft
V0016* OPS (Consequences database)
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 11 / 27
DASSAULT AVIATION Proprietary Data

### Page 14

SOFTWARE KEY WORD EFFECTIVITY
V0038* ECL
Latest applicable version ECB
PS60002392-0006* FMS AEDB
PS60001004-0004* FMS MAGVAR
PS60004646-003* FMS TOLD
DS7-YYCC-RRR*
INDS EPIC AIRSPACE
& COMM NAVIGATION DATA
A/C without RNP-AR
DS8-YYCC-RRR* A/C with RNP-AR (RNP-AR=0.3 or
RNP AR DOWN TO RNP 0.1
APPROACH)
Full charts INDS Electronic Terminal Charts
All aircraft
DO69002412-0XXX*
(EGPWF database)
INDS EGPWF Data
996-0114-5XX*
(envelope modulation)
996-0146-6XX* INDS Terrain server
PS60001005-0015* ATC Database Aircraft with SB 7X-308
P1148 Issue 2* ACMF Optional but recommended to allaircraft for troubleshooting
69003872-040* EGPWF ROAAS Database All aircraft
* or latest applicable version (the most current software and database versions which can be loaded on the aircraft are
now tracked in the "MAINTENANCE DOCUMENTATION - Documentation Status" section of the Falcon Portal, where
you will be given the most up-to-date versions depending on the aircraft configuration).
(6) Discard all of the previous versions of the software, Options, Settings, Operator Tools and
Database CD-ROMs.
(7) Due to the Operational Software to EB60007394-0116, contact INDS to request the Navigation
database changes from (refer to Service Bulletin Commercial Summary):
• DS3 to DS7 for A/C without RNP-AR, or
• DS4 to DS8 for A/C with RNP-AR.
F. TESTS
(1) Perform the operational test of the TCAS system (Refer to TASK 34-44-00-710-801).
(2) Perform the test after installation relative to the following MAU modules:
• AGM modules (Refer to TASK 31-60-17-900-801),
• Processor, NIC/processor, power supply and ASCB bus coupler modules (Refer to TASK
31-42-00-710-801).
(3) Perform the test after installation of the NIM modules (Refer to TASK 31-43-05-900-801).
(4) Perform the operational test of the EGPWS (Refer to TASK 34-45-00-710-801).
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 12 / 27
DASSAULT AVIATION Proprietary Data

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(5) Perform the test of all the other equipment removed when performing this Service Bulletin, in
accordance with the Maintenance Manual Procedures.
G. FINAL STEPS
(1) De-energize the aircraft systems (Refer to TASK 24-00-00-860-801  -“De-energization with the
electrical ground power unit” and "Disconnection of the electrical ground power unit").
(2) Install the floors listed in step (Refer to TASK 53-04-01-900-801).
(3) Install all the interior accommodation removed for access.
(4) Close the nose cone ( 210) (Refer to TASK 53-10-09-860-801).
H. DOCUMENTATION
Incorporate Airplane Flight Manual revision 25 or subsequent revision pages.
Incorporate fig. 3 in Wiring Diagram Manual chapter 34-23-50.
Incorporate fig. 4 and fig. 5 in Wiring Diagram Manual chapters 34-40-00 and 34-45-00.
I. RECORDING
Record compliance with this Service Bulletin in the appropriate aircraft documents.
Fill out the electronic Service Bulletin reply form accessible from the ”Service Bulletin" page on the
Falcon portal or register SB implementation at Sbconfiguration@dassault-aviation.com, providing all
useful information for aircraft identification:
• aircraft type and serial number,
• SB compliance: complete or section(s) applied,
• remarks,
• compliance date,
• service center.
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 13 / 27
DASSAULT AVIATION Proprietary Data

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3. MATERIAL INFORMATION
NOTE: Compliance with this Service Bulletin by substituting the part numbers below with interchangeable
subsequent part numbers (as per the Master List or Dassault-approved supply list) is acceptable,
provided that subsequent part numbers have the same effectivity as the original ones.
A. MODIFICATION OF EQUIPMENT PART NUMBER
NEW P/N QTY KEY WORD OLD P/N INSTRUCTION/
DISPOSITION
7034056-1902 1 PROC module  (2-fig. 6)
7038231-2901 4 NIC/processor 7034057-1901  (3-fig. 6)
60000770-1907 4 AGM module 7036410-1903  (4-fig. 6)
7034056-1903 1 PROC module 7028419-1904  (5-fig. 6)
7038248-1901 mod
B or more
1 to 4 Power Supply Module 7038248-1901 If needed (see step 2.B.
(10))
 (6-fig. 6)
940-0452-001 with
software version
01/04 or
subsequent
1 TCAS Computer 9003000-55005
60000091-983 2 NIM module 60000091-913
7027566-903 2 Bus coupler 7027566-901
071-50001-8103 2 TCAS antenna 7514081-913 (303NP)
7514081-914 (203NP)
lower TCAS antenna
(503NP) / item 4
upper TCAS antenna
(603NP) / (8-fig. 8)
NOTE: Refer to Service Bulletin Commercial Summary to send back the modules removed.
B. MODIFICATION KIT
Kit P/N SBF7X0601A
Electrical kit
P/N QTY KEY WORD DISPOSITION/ITEM-FIG
01C0K600-22P01 9 Contact 103NPE, 103NPF
01C0K501-20S01 2 Contact SP2102NH1
01C0K309-22DS01 5 Contact 751J, 4101FY1
01C0AFHE2-7 1 Hexashield backshell 4101FY1
01C0A3682FC22 2 Dummy contact 103NPE-11C/12G
01EQTPRL16B01 2 Splice L200SP
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 14 / 27
DASSAULT AVIATION Proprietary Data

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P/N QTY KEY WORD DISPOSITION/ITEM-FIG
01EQTPRL08R01 5 Splice SP2102NH1, SP103NPF-7K,
SP103NPE-6J, 7J
01EQTRB23-1R 5 Soldering sleeve SP2102NH1, 103NPE
01EQTRB32-6A 1 Soldering sleeve L200SP
01PR0PRL05 1 Kit L200SP
01EQTEC1-1 10 Insulation cap
01CAN203-1-24W 1 m Wire
01CAB211-2-24 7.5 m Wire
01CAN211-1-24 12 m Wire
103NPE-10A/751J-34 2 Wire identification sleeve
(01PR0TMS1G1-8)103NPE-10E/751J-35 2
SP103NPE-6J/751J-36 2
103NPE-5E/SP103NPF-7K 2
103NPE-7A-7B/L200SP-43-44 2
4101FY1-20-21/L200SP-43-44 2
103NPE-15C-15D/2102NH-32-33 2
503NP1 1 Identification plate
01PR0TMSET1-0-10W4503NP2 1
503NP3 1
503NP4 1
603NP1 1
603NP2 1
603NP3 1
603NP4 1
503NP1 1 Self-adhesive label (STERLING
E19) Black marking on green
background503NP2 1
503NP3 1
503NP4 1
603NP1 1
603NP2 1
603NP3 1
603NP4 1
SP103NPF-7K 1 Splice identification sleeve
(01PR0TMS1G3-32)SP103NPE-6J 1
L200SP-43-44 1
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 15 / 27
DASSAULT AVIATION Proprietary Data

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P/N QTY KEY WORD DISPOSITION/ITEM-FIG
01C0A507CPC11A8-01 4 Connector backplate  (1-fig. 2)
01C0F501U62BS001L 4 Connector  (2-fig. 2)
01C0A54148FC22 256 Blanking pin 2101FD, 2201FD, 2301FD,
2401FD
78750-00 16 Cable grip Identification plate
Kit P/N SBF7X0601B
Effectivity: All aircraft for TCAS antennas installation kit with external access only
P/N QTY KEY WORD DISPOSITION/ITEM-FIG
F7XL533403312W1 1 Interface shim  (1-fig. 7)
AG822000-02 2 Polyurethane gasket  (2-fig. 7)
F7XL536031024 1 Fuel equipment bay door item 1
NAS1133V8A 8 Screw lower TCAS antenna (503NP) /
item 2
NAS1149D0332K 8 Washer lower TCAS antenna (503NP) /
item 3
Kit P/N SBF7X0601C
Effectivity: All aircraft for TCAS antennas installation with internal and external access
P/N QTY KEY WORD DISPOSITION/ITEM-FIG
35067-4008ID 14 Rivet  (1-fig. 8)
35067-3206ID 6 Rivet  (2-fig. 8)
35067-3209ID 6 Rivet  (3-fig. 8)
35067-3208ID 20 Rivet  (4-fig. 8)
35067-3207ID 3 Rivet  (5-fig. 8)
F7XL533403312W2 1 Interface shim  (6-fig. 8)
AG822000-02 2 Polyurethane gasket  (7-fig. 8)
F7XL536031024 1 Fuel equipment bay door item 1
NAS1133V8A 8 Screw lower TCAS antenna (503NP) /
item 2
NAS1133V12A 8 Screw upper TCAS antenna (603NP) / 
(9-fig. 8)
NAS1149D0332K 16 Washer lower TCAS antenna (503NP) /
item 3
upper TCAS antenna (603NP) / 
(10-fig. 8)
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 16 / 27
DASSAULT AVIATION Proprietary Data

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C. SOFTWARE
NEW P/N SOFTWARE KEY WORD EFFECTIVITY SUPPLIER
TM7035297-107
EPIC Tools including:
• Remote Terminal - RT 33, DLS 8.7.0
• APM Settings Tool - V 3.0
• APM Restoration Tool - V 2.2
All aircraft
HONEYWELL
MM7034838-020
Operational Software
Top Level System
Part Number
EB60007394-0116
Load 18.0
TT60005561-XXXXX APM Options parameter configuration
HONEYWELL
through
DASSAULT
AVIATION
PUB: 1001 18.0* LDI
DASSAULT
AVIATION
available on
Falcon eData
Refer to Service Bulletin 7X-603 AMI database Aircraft withDatalink installed
GDC or ARINC
Direct or
SATCOM
DIRECT
PUB: 1001 V0015* FLT (Fault Codedatabase)
All aircraft
DASSAULT
AVIATION
available on
Falcon eData
PUB: 1001 V0016*
OPS
(Consequences
database)
PUB: 1001 V0038* ECL Database
Full charts INDS ElectronicTerminal Charts
Integrated
Navigation
Data Service
(INDS)
EGPWF Data
DO69002412-0XXX*
(EGPWF Database) INDS EGPWF
Data996-0114-5XX*
(envelope modulation)
EGPWF Terrain Server
996-0146-XXX*
(terrain server)
INDS Terrain
server
DS7 DS7-YYCC-RRR* INDS EPIC
AIRSPACE &
COMM
NAVIGATION
DATA
A/C without RNP-
AR
DS8 DS8-YYCC-RRR*
A/C with RNP-AR
(RNP-AR=0.3 or
RNP AR DOWN
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 17 / 27
DASSAULT AVIATION Proprietary Data

### Page 20

NEW P/N SOFTWARE KEY WORD EFFECTIVITY SUPPLIER
TO RNP 0.1
APPROACH)
DM60004646-003* PS60004646-003* TOLD Database Aircraft with SB7X-411 
HONEYWELL
DM60002392-0006* PS60002392-0006* FMS AEDB
All aircraftDM60001004-0004* PS60001004-0004* Magvar
DBO69003872-040* 69003872-040* EGPWF ROAASDatabase
* or latest applicable version (the most current software and database versions which can be loaded on the aircraft are
now tracked in the "MAINTENANCE DOCUMENTATION - Documentation Status" section of the Falcon Portal, where
you will be given the most up-to-date versions depending on the aircraft configuration).
CD ROMS P/N REQUIRED ONLY IF NOT PREVIOUSLY PROCURED
P/N SOFTWARE KEY WORD EFFECTIVITY SUPPLIER
DM60001005-0015* PS60001005-0015* ATC database Aircraft with SB7X-308 HONEYWELL
PUB: 804 Latest applicable version ECB All aircraft DASSAULTAVIATION
PUB: 1001 P1148 Issue 2* ACMF
Optional but
recommended for
AP
troubleshooting
DASSAULT
AVIATION
available on
Falcon eData
*or latest applicable version (the most current software and database versions which can be loaded on the aircraft are
now tracked in the "SOFTWARE & DATABASES - Software & Databases Status" section of the Falcon Portal, where
you will be given the most up-to-date versions depending on the aircraft configuration).
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 18 / 27
DASSAULT AVIATION Proprietary Data

### Page 21

D. LOCAL PROCUREMENT
NOTE: If specific products, identified in parentheses "()" are no longer procurable, equivalent
products can be used.
Paint substitutes are given in the Protection Scheme (Refer to SDS 20-60-00).
As indicated in Consumable Products Manual (CPM):
• cleaner
• alodine
• anti-corrosion primer
• demolding agent
• AIREX foam
• compound EC 3524
• interlaying sealant
• covering sealant
• bead sealant
• white primer 5014
• lockwire
Contact: 01C0K309-22DS01 (4101FY3) - Quantity = 2
FALCON 7X 7X -601
April 24, 2023 ATA 00
Initial issuance Page 19 / 27
DASSAULT AVIATION Proprietary Data

### Page 22 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
FR9  FR12  FR14
ADAHRS  MAUZ  L200SP  TCAS
Figure 1: WORK AREA
April 24, 2023  ATA 00
Initial issuance  Page 20 / 27

### Page 23 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
001200/91
n--4-0
GAU-7-9  210148
2
Figure 2: AGM BACKSHELL
April 24, 2023  ATA 00
Initial issuance  Page 21 / 27

### Page 24 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
2301FD  2401FD
AGM2  AGM4
BEFORE MODIFICATION
FOR COMPLEMENT, SEE WDM CHAP. 34-23-50
108FT  * AGM3  - 2201FD
TERRAIN SERVER C 0 511712457_  R5511FD  - 524512457 B
AGM1  2101FD
EGPWM1  101FW
TERRAIN SERVER  L5511FD
UNLESS OTHERWISE SPECIFIED : ALL WIRE IS AWG 24
2301FD  2401FD  AFTER MODIFICATION
AGM2  AGM4
INCORPORATE IN WDM, CHAP.34-23-50
ADDED ELEMENTS
AGM3  2201FD
TERRAN SERVED I  5117/24S7  5245/24S7
R5511FD
AGM1  • 2101FD
EGPWM1  101FW
TERRAN SERVED 25 52122.  E8 00-51332457
125 OHM  • WIRES CAPPED AND STOWED INSIDE
F WIRES CAPPED AND STOWED TO WIRING BUNDLE
UNLESS OTHERWISE SPECIFIED : ALL WIRE IS AWG 24
Figure 3: WDM 34-23-50 - TERRAIN SERVER BUS WIRING MODIFICATION
April 24, 2023  ATA 00
Initial issuance  Page 22 / 27

### Page 25 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
BEFORE MODIFICATION
FOR COMPLEMENT, SEE WDM CHAP. 34-40-00 & 34-45-00  4101FY
103NP
TCAS/XPDR2 H
PROGRAM PIN COM
A/C ALT 4000
A/C ALT 16000  6H
ALT ALT 32000
OPTION PARITY  12G
RA N1 STATUS  14C
TA/RA DISPLAY 1  7E
TA/RA DISPLAY 2
39/20
203J5
PROG AUDIO LVL 6DB
PROG COMMON PIN OUT
RA VALID DISABLE
TOP ANT
TOP ANTENNA
203NP
153FT
BOT ANTENNA
303NP
SD 31-51-00, 45-32-00
UNLESS OTHERWISE SPECIFIED : ALL WIRE IS AWG 24  "2102ÑH  102NH
1 THE FOUR COAXIAL MUST HAVE THE SAME LENGTH.
2 THE FOUR COAXIAL MUST HAVE THE SAME LENGTH.
SHIELDED WIRES CONNECTED BY A TERMINAL JUNCTION OR SPLICE HAVE THE SHIELDING
JOINTED TOGETHER (THIS JUNCTION IS NOT ILLUSTRATED IN THIS WD
- 77J/P  LH FR1 BASIC ELEC CUT-OFF CONNECTOR  F1, LH
- 103NP  TCAS TRANSCEIVER  F12-16, UNDER CABIN FLOOR, LH
- 203NP  UPPER TCAS ANTENNA  F12-30, OVER CABIN FLOOR, LH
- 303NP  LOWER TCAS ANTENNA  F26-27, FUEL EQUIPMENT BAY
- 102NH  IRU 1  F19-20, IRS BAY
- 2102NH  ADAHRS UNIT  F8-12, UNDER CABIN FLOOR, LH
- 4101FY  GENERIC I/O 1 MODULE  F8-12, UNDER CABIN FLOOR
- 203J  TERMINAL STRIP  F8-9, OVER FLOOR, LH CABINET
Figure 4: WDM 34-40-00 & 34-45-00 - BEFORE WIRING MODIFICATION
April 24, 2023  ATA 00
Initial issuance  Page 23 / 27

### Page 26 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
AFTER MODIFICATION  INCORPORATE IN WDM, CHAP.34-40-00 & 34-45-00
FOR COMPLEMENT, SEE WDM CHAP. 34-40-00 & 34-45-00
103NP  4101FY
751
A429 IRU1 HI
A429 IRU1 LO
H-32-33
TCAS/XPDR2 H
PROGRAM PIN COM
A/C ALT 4000  6F  751  4101FY1-20-21  L200SP-43-44
A/C ALT 16000  ALT ALT 32000  6H  6J  SP103NPE-6J/751J-36  Гзе
MALE VOIE  SP103NPE-6J
OPTION PARITY  12G
L200SP
RA N1 STATUS  14C
RA N2 STATU
TA/RA DISPLAY 1
TA/RA DISPLAY 2  7J 39/20  A129 NIZ  203J5
PROG AUDIO LVL 6DB
PROG COMMON PIN OUT  7K  SP103NPF-7K
RA VALID DISABLE  4G
TOP ANTENNA
603NP
153FT
BOT ANTENNA
503NP
SD 31-51-00, 45-32-00  1 THE FOUR COAXIAL MUST HAVE THE SAME LENGTH.  UNLESS OTHERWISE SPECIFIED : ALL WIRE IS AWG 24  2102NH  102NH
2 THE FOUR COAXIAL MUST HAVE THE SAME LENGTH.
SHIELDED WIRES CONNECTED BY A TERMINAL JUNCTION OR SPLICE HAVE THE SHIELDING
JOINED TOGETHER (THIS JUNCTION IS NOT ILLUSTRATED IN THIS WD)
- 77J/P  LH FR1 BASIC ELEC CUT-OFF CONNECTOR  F1, LH
- 751J  BASIC/OPTION CUT-OFF CONNECTOR  CABIN AREA, F14 UNDER FLOOR, RH
- 103NP  TCAS TRANSCEIVER  F12-16, UNDER CABIN FLOOR, LH
- 603NP  UPPER TCAS ANTENNA  F12-30, OVER CABIN FLOOR, LH
- 503NP  LOWER TCAS ANTENNA  F26-27, FUEL EQUIPMENT BAY
- L200SP  SPLICE ZONE  F9-12, UNDER CABIN FLOOR, LH  DELETED ELEMENTS
- 102NH  IRU 1  F19-20, IRS BAY  ADDED ELEMENTS
- 2102NH  ADAHRS UNIT  F8-12, UNDER CABIN FLOOR, LH  MODIFIED ELEMENTS
- 4101FY  GENERIC I/O 1 MODULE  F8-12, UNDER CABIN FLOOR
- 203J  TERMINAL STRIP  F8-9, OVER FLOOR, LH CABINET
Figure 5: WDM 34-40-00 & 34-45-00 - AFTER WIRING MODIFICATION
April 24, 2023  ATA 00
Initial issuance  Page 24 / 27

### Page 27 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
• 3101FY  2201FY  910-
12|34567  8 | NIC1 | NIC2  10|11|12|13|14|15|16| PS2] SLOT NO.
CH B
POWER SUPPLY 1  CONTROL/VIDEO I/O 1  GENERIC I/O 2  EGPWM •  POWER SUPPLY 2
NIC/
0000
• CHA
BEFORE MODIFICATION  MAU T
430-  4401FY  930-
1|2 3 4 5 6|7 8| NIC1| NIC2 9 101112|13|14 15 16] PS2 SLOT NO.
CH B
POWER SUPPLY 1  AGM 4  GENERIC I/O 3  NIC/PROCESSOR 3  NIC/PROCESSOR 4  GENERIC V/O 4  AGM 2  SPARE  SPARE  POWER SUPPLY 2
PROC
00000
CH A
MAU 2
2101FD  4201FY  2201FD  IFY  IFY  IFY  IFY
110°  310*  • 250-  450-  295'  285
10|11|12|13  16 PS2 SLOT NO.
CH B
AFTER MODIFICATION  POWER SUPPLY 1  CONTROL/VIDEO I/O 1  GENERIC I/O 5  AGM 1  GENERIC  PROCESSOR 1  NIC/PROCESSOR 2  GENERIC I/O 2  POWER SUPPLY 2
• IN MAU1, PROCESSOR IN SLOT 16 MOVED TO SLOT 14  AND BECOME PROCESSOR 9.
E NEW P/N 7034056-1902 IS INSTALLED IN MAU1 SLOT 16.  0009
*MAU LOT 18 PROCESSOR BECOMES PROCESSOR WITH EW CT.  CH A
MAO
1 NIC PROCESSORS REPLACED BY NEW P/N.  1FD  2301FY  1FY  2401  440'  1FDI  2301  IFY  940
1 AGM MODULES REPLACED BY NEW P/N.  F EGPWM MODULE REPLACED BY PROCESSOR 10.  1213115/017 8 NoT No2 0 10 112131 15 81 82 SLOTNO.
• IF NEEDED, POWER SUPPLY MODULES REPLACED BY  SAME P/N, WITH MOD B OR MORE  POWER SUPPLY 1  AGM 4  1/0 3  NIC/PROCESSOR 3  NIC/PROCESSOR 4  GENERIC I/O 4  AGM 2  SPARE  OR  SUPPLY 2
8 0000  CH A
MAU 2
Figure 6: MAU LAYOUT
April 24, 2023  ATA 00
Initial issuance  Page 25 / 27

### Page 28 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
12.7 mm (0.5 in)
400 mm (15.7 in) DIA.
MICROBALLON TAPER SHIM LIMIT
FWD
FR15  - 2 FR16
FINISH PANT LIMIT
8 mm
(0.31 in)
d, e, f  INTERLAYING SEALENT
BEAD SEALENT  B-B
COVERING SEALENT
- WHITE PRIMER 5014
Figure 7: UPPER TCAS ANTENNA - INSTALLATION WITH EXTERNAL ACCES ONLY
April 24, 2023  ATA 00
Initial issuance  Page 26 / 27

### Page 29 (OCR)

DASSAULT  SERVICE BULLETIN
AVIATION
FALCON 7X  7X -601
12.7 mm (0.5 in)  cOR3 dOR4
9, 10
400 mm (15.7 in) DIA
MICROBALLON TAPER SHIM LIMI
FWD  81 mm
(3.19 in)
FR15  FR16
WIDTH=5 mm
0 mm (0.79 in)
FINISH PAINT LIMI
48 my  > 9 in
a OR 1 bOR2
15 mm
(0.59 in)
8 mm
WIDTH=5 mm  WIDTH=5 mm  (0.31 in)
a OR 1  35067-4008ID
bOR2  35067-3206ID  e, f, g  INTERLAYING SEALENT  B-B
C OR 3  35067-3209ID  BEAD SEALENT
dOR 4  35067-3208ID  COVERING SEALENT
WIDTH=5 mm
5  35067-3207ID  - WHITE PRIMER 5014
Figure 8: UPPER TCAS ANTENNA - INSTALLATION WITH INTERNAL AND EXTERNAL ACCES
April 24, 2023  ATA 00
END OF DOCUMENT
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