OpenAirDocs.org

Dassault SB 7X-601: No revision named

Open the Markdown

Copy · SB_7X-601_Initial_04-24-2023 · 29 pages

Open PDF· 29 pages, 7.0 MB

© 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.

TextPartly OCR

Some pages are OCR from a scan. OCR can misread letters and numbers.

Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = 'f0941e2d51a3df1ea5d238c76a17a57f722e474d6e6c7195c4e5392d9f8c86a9'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

Page 1Open in PDF

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.

Page 2Open in PDF

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 3Open in PDF

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.

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 1 / 27 DASSAULT AVIATION Proprietary Data

Page 4Open in PDF

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.

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 2 / 27 DASSAULT AVIATION Proprietary Data

Page 5Open in PDF

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) FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 3 / 27 DASSAULT AVIATION Proprietary Data

Page 6Open in PDF

• 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 FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 4 / 27 DASSAULT AVIATION Proprietary Data

Page 7Open in PDF

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).

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 5 / 27 DASSAULT AVIATION Proprietary Data

Page 8Open in PDF

(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).

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 6 / 27 DASSAULT AVIATION Proprietary Data

Page 9Open in PDF

(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, FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 7 / 27 DASSAULT AVIATION Proprietary Data

Page 10Open in PDF

• 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 (dfig. 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.

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 8 / 27 DASSAULT AVIATION Proprietary Data

Page 11Open in PDF

(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, FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 9 / 27 DASSAULT AVIATION Proprietary Data

Page 12Open in PDF

• 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).

FALCON 7X 7X -601 April 24, 2023 ATA 00 Initial issuance Page 10 / 27 DASSAULT AVIATION Proprietary Data

Pages 13–24 of 29