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Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 FALCON 7X No 211-R2 JUNE 22, 2011 MANDATORY ATA 27 FLIGHT CONTROLS PITCH TRIM ADDITION OF A REVERSION LOGIC AND MANUAL OVERRIDE FALCON SERVICE BULLETIN Copyright © 2011 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. 785 ### Page 2 FLIGHT CONTROLS PITCH TRIM ADDITION OF A REVERSION LOGIC AND MANUAL OVERRIDE Initial issuance June 02, 2011 List of effective pages : 1 to 47 REASON:This original issue has been validated by DASSAULT AVIATION and may be used as manufacturer's instructions to retrofit the aircraft. Final approval will be provided through a revision of this Service Bulletin when the associated modification is approved by the Airworthiness Authorities. INITIAL ISSUANCE HAS NEVER BEEN IMPLEMENTED. Revision 1 June 14, 2011 List of effective pages : 1 to 60 REASON:This revision 1 defines the operations necessary to perform cockpit and baggage compartment modifications and LRU update, according to M1235 and M1236. Revision 2 June 22, 2011 List of effective pages : 1 to 90 REASON:This revision installs relays as an alternate solution to contactors. This revision is applicable to the aircraft already modified per revision 1of this Service Bulletin: for these aircraft, the revision consists in authorizing to replace the switch frame of the emergency switch panel for better lighting. FALCON 7X 7X-211 ATA 27 ### Page 3 FLIGHT CONTROLS PITCH TRIM ADDITION OF A REVERSION LOGIC AND MANUAL OVERRIDE 1. PLANNING INFORMATION A. EFFECTIVITY This Service Bulletin is applicable to FALCON 7X aircraft with serial numbers 1 and subsequent which have not previously implemented DASSAULT AVIATION modifications 7X M1235 and M1236. NOTE: The implementation of Service Bulletin 7X-114 (M1025) “FCS STANDARD 2.1.7.1” is a prerequisite. B. REASON Following a pitch trim incident reported on a FALCON 7X, it has been determined that it was necessary to add another automatic reversion logic and to add a means for the pilot to override the pitch trim control normal modes. The purpose of this Service Bulletin is to install this new reversion system and to allow flight crew to manually switch to the back-up motor of the horizontal stabilizer trim function. C. DESCRIPTION This Service Bulletin is divided into 3 sections. Depending on the kit delivered, only one of these sections is applicable: • SECTION 7X-211-1: Installation of contactors is applicable for kit SBF7X0211A, • SECTION 7X-211-2: Installation of relays is applicable for kit SBF7X0211A1 with relay DR50E41D included, • SECTION 7X-211-3: Installation of relays is applicable for kit SBF7X0211A1 with relay DS50E42D included. For each section, the operation consists in: • using a spare switch from emergency switch box to override pitch trim normal mode and activate back-up motor, • installing wiring between the overhead control panel and the new “TRIM EMERG” switch, • installing two contactors or relays and control relays in the baggage compartment, • connecting these contactors or relays and control relays to the primary power distribution boxes and flight control system, • replacing the HSTC modules with new ones, and • uploading the MAIC modules. CAUTION: THE UPLOADING OF THE MAIC MODULES MUST BE PERFORMED BY AN OPERATOR AUTHORIZED BY THE COMPONENT MANUFACTURER DASSAULT EQUIPEMENTS AFTER A SPECIFIC TRAINING. D. COMPLIANCE Mandatory: FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 1 / 90 DASSAULT AVIATION Proprietary Data ### Page 4 • This Service Bulletin is rendered mandatory by EASA Emergency Airworthiness Directive No 2011-0114-E. • As prescribed by the Airworthiness Authorities of the country of registration of the aircraft. E. APPROVAL This Service Bulletin covers DASSAULT AVIATION FALCON 7X modifications M1235 and M1236 which are approved by the EASA. The technical content of this document is approved by DASSAULT AVIATION. F. LABOR Estimated labor-hours: 140 hours (some tests must be performed during run-up) 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. G. MATERIAL - PRICE AND AVAILABILITY The modification kit may be obtained from either address listed below: Western hemisphere: DASSAULT FALCON JET CORP. SPARES DISTRIBUTION CENTER 200 RISER ROAD LITTLE FERRY, NJ 07643 U.S.A. Telephone: • CANADA and U.S.A.: 1-800-800-4036 • MEXICO: 001-800-800-4036 • Other countries: 1-201-541-4809 Fax: • CANADA and U.S.A.: 1-800-800-4817 • MEXICO: 001-800-800-4817 • Other countries: 1-201-440-7021 Other continents: DASSAULT AVIATION Falcon Spares BOITE POSTALE N°101 AEROPORT DU BOURGET 93350 - LE BOURGET Cedex (FRANCE) Please contact your Dassault Aviation Account Representative Telephone: 33 (0)1.48.35.56.78 Fax: 33 (0)1.48.35.56.00 Price and availability on request. H. TOOLING - PRICE AND AVAILABILITY • Normal maintenance tooling. • Chronometer. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 2 / 90 DASSAULT AVIATION Proprietary Data ### Page 5 • multimeter (TO-20-360). • SECTION 7X-211-1: 1 tool P/N F7X0211E (refer to paragraph 4. “MATERIAL INFORMATION”) or equivalent. • SECTIONS 7X-211-2 and 3 : 2 tools P/N F7X0211E (refer to paragraph 4. “MATERIAL INFORMATION”) or equivalent. NOTE: break-out box (F7XC202059530) can be used as an equivalent to tool P/N F7X0211E. I. WEIGHT AND BALANCE Change in weight: +1,3 kg (2.9 lb). Change in balance with respect to 25% MAC: 7 m.kg (673 in.lbf) nose-up. J. REFERENCES Structure Repair Manual: • DRILLING (Refer to SRM 51-40-03) Aircraft Maintenance Manual: • INTERNAL ACCESSES (Refer to SDS 06-30-00) • GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801) • PRINCIPLES AND CHECK OF THE ELECTRICAL BONDING (Refer to TASK 20-20-00-910-801) • INSERTION AND EXTRACTION OF A WIRE FITTED WITH A LOCK-IN CONTACT IN AND FROM AN ITEM OF EQUIPMENT (Refer to TASK 20-95-00-910-801) • REMOVAL / INSTALLATION OF THE AUDIO PANEL (Refer to TASK 23-50-01-900-801) • ENERGIZATION / DE-ENERGIZATION OF THE AIRCRAFT WITH THE ELECTRICAL GROUND POWER UNIT (GPU) (Refer to TASK 24-00-00-860-803) • ELECTRICAL SYSTEM MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 24-00-00-910-801) • OPERATIONAL TEST OF THE PRIMARY DC GENERATION SYSTEM (Refer to TASK 24-31-00-710-801) • DISCONNECTION / CONNECTION OF THE BATTERIES (Refer to TASK 24-32-01-920-801) • OPERATIONAL TEST OF THE PRIMARY POWER DISTRIBUTION SYSTEM (Refer to TASK 24-61-00-710-801) • REMOVAL / INSTALLATION OF THE PRIMARY-POWER DISTRIBUTION-BOXES (PPDB) (Refer to TASK 24-61-01-900-801) • REMOVAL / INSTALLATION OF THE REAR SECONDARY-POWER DISTRIBUTION-BOXES (SPDB) (Refer to TASK 24-62-09-900-801) • REMOVAL / INSTALLATION OF THE COCKPIT BULKHEADS (Refer to TASK 25-10-01-900-801) • REMOVAL / INSTALLATION OF THE PILOT SEATS (Refer to TASK 25-11-01-900-801) • REMOVAL / INSTALLATION OF THE THIRD CREW MEMBER SEAT (Refer to TASK 25-12-00-900-801) • REMOVAL / INSTALLATION OF THE COCKPIT LININGS (Refer to TASK 25-13-13-900-801) • REMOVAL / INSTALLATION OF THE BAGGAGE COMPARTMENT LININGS (Refer to TASK 25-52-01-900-801) • ¨ • GROUND TEST OF THE FCS (Refer to TASK 27-00-00-700-802) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 3 / 90 DASSAULT AVIATION Proprietary Data ### Page 6 • FUNCTIONAL TEST OF THE FLIGHT CONTROL SYSTEM WITHOUT HYDRAULIC POWER (Refer to TASK 27-00-00-720-802) • FLIGHT CONTROL SYSTEM MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 27-00-00-910-801) • TEST OF RESERVOIR FILLING AND LOCAL HYDRAULIC GENERATOR OPERATION (Refer to TASK 27-11-09-710-801) • REMOVAL / INSTALLATION OF THE LH REAR FCS MODULES (Refer to TASK 27-90-01-900-802) • REMOVAL / INSTALLATION OF THE RH REAR FCS MODULES (Refer to TASK 27-90-01-900-804) • REMOVAL / INSTALLATION OF THE LH REAR FCS RACK (Refer to TASK 27-90-05-900-802) • REMOVAL / INSTALLATION OF THE RH REAR FCS RACK (Refer to TASK 27-90-05-900-804) • PRESSURIZATION / DE-PRESSURIZATION OF THE HYDRAULIC SYSTEMS WITH THE HYDRAULIC GROUND POWER UNIT (GPU) (Refer to TASK 29-00-00-860-803) • REMOVAL / INSTALLATION OF THE WINDSHIELD DE-ICING POWER SUPPLIES (Refer to TASK 30-41-01-900-801) • REMOVAL / INSTALLATION OF THE EMERGENCY SWITCH BOX (Refer to TASK 31-13-01-900-801) • OPERATIONAL TEST OF THE CENTRAL DISPLAY SYSTEM (CDS) (Refer to TASK 31-60-00-710-801) • REMOVAL / INSTALLATION OF THE DISPLAY UNITS (Refer to TASK 31-60-13-900-801) • OPERATIONAL TEST OF THE EXTERIOR LIGHTING (Refer to TASK 33-40-00-710-801) • REMOVAL / INSTALLATION OF THE CREW OXYGEN MASKS AND STOWAGE BOXES (Refer to TASK 35-10-01-900-801) • USE OF THE CENTRAL MAINTENANCE COMPUTER (CMC) - QUICK REFERENCE HANDBOOK (Refer to TASK 45-10-00-910-801) • REMOVAL / INSTALLATION OF THE FLIGHT DECK PRINTER (Refer to TASK 45-10-09-900-801) • REMOVAL / INSTALLATION OF THE DATA MANAGEMENT UNIT (DMU) (Refer to TASK 45-90-01-900-801) • APU STARTING AND SHUTDOWN (Refer to TASK 49-10-01-860-801) • REMOVAL / INSTALLATION OF THE COCKPIT, CABIN AND BAGGAGE COMPARTMENT FLOOR PANELS (Refer to TASK 53-01-00-900-801) • REMOVAL / INSTALLATION OF THE SEALING DAM (Refer to TASK 53-80-05-900-801) Fault Isolation Manual • TROUBLESHOOTING PROCEDURE FOR THE FCS (Refer to TASK 27-00-00-910-801) Supplemental Maintenance Manual: • (Refer to SDS 33-20-00) DASSAULT AVIATION Service Bulletin 7X-114 K. OTHER PUBLICATIONS AFFECTED The following publications are revised to account for the changes introduced by this Service Bulletin: • Airplane Flight Manual: CP55 and CP56 • Chapter 5-40 CP009 DGT107838 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 4 / 90 DASSAULT AVIATION Proprietary Data ### Page 7 The following publications will be revised at a later date to account for the changes introduced by this Service Bulletin: • Illustrated Parts Catalog. • Maintenance Manual. • Wiring Diagram Manual: • 27-04-00 • 27-45-00 • 31-53-00 • MPD/Chapter 5. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 5 / 90 DASSAULT AVIATION Proprietary Data ### Page 8 2. ACCOMPLISHMENT INSTRUCTIONS FOR AIRCRAFT WHICH HAVE NOT ALREADY IMPLEMENTED THE REVISION 1 OF THE SERVICE BULLETIN A. PRELIMINARY STEPS (1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801). (2) If the aircraft configuration allows it, set the horizontal stabilizer (9500CH) to the up position: (a) Connect the electrical Ground Power Unit (GPU) (Refer to TASK 24-00-00-860-803). (b) Energize the aircraft systems (Refer to TASK 24-00-00-860-803). (c) Push the upper part of the “PITCH” trim control dual rocker on the trim unit (106CZ) to give a nose-down command, (d) On the PDUs, make sure that the pitch trim position indicator moves to the “ND” indication . NOTE: You must move the horizontal stabilizer (9500CH) sufficiently until you gain access to the screw of the horizontal stabilizer actuator access panel (325AR). (e) De-energize the aircraft systems (Refer to TASK 24-00-00-860-803). (3) Obey the Electrical System Maintenance and Safety Precautions (Refer to TASK 24-00-00-910-801). (4) Obey the Flight Control System Maintenance and Safety Precautions (Refer to TASK 27-00-00-910-801). (5) If the HSTC 3 module (403CZ) and HSTC 4 module (1304CZ) are not yet removed: (a) We recommend to perform the ground test of the FCS (Refer to TASK 27-00-00-700-802). NOTE: At the end of the test, do not disconnect the electrical ground power unit and do not install the four multi-function probe covers (KPC3-780-45). • If the ground test is completed with the amber "FCS: TEST FAIL " or "CHECK STATUS" CAS messages displayed on the primary display unit, perform the troubleshooting procedure for the FCS (Refer to TASK 27-00-00-910-801 , paragraph 4.B to 4.D). • If no FCS-related CAS and no Fault messages are displayed, then perform the “CLOSE- UP” paragraph of the ground test of the FCS (Refer to TASK 27-00-00-700-802 , paragraph 5). (b) In the baggage compartment: NOTE: In addition to the elements listed below, it may be necessary to remove other items (optional equipment, completion add-ons), depending on the aircraft customization. 1 Remove the LH and RH shelves (L9512MK)/(R9512MK) (Refer to TASK 25-52-01-900-801). 2 Remove the following linings (Refer to SDS 06-30-00 ) and (Refer to TASK 25-52-01-900-801): • frame 40 middle lining (272PZ), • frame 40 upper lining (272OZ), • frame 40 lower lining (272QZ), • frame 39 lower lining (272NZ), FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 6 / 90 DASSAULT AVIATION Proprietary Data ### Page 9 • frame 40 middle lining (271OZ), • frame 40 upper lining (271NZ), • frame 40 lower lining (271PZ), • frame 39 lower lining (271MZ), • frame 40 center lining (271RZ). 3 If necessary, remove the towbar and its support to remove the carpet. 4 Remove the baggage compartment doorsill. 5 Remove the baggage compartment carpet. 6 Remove floor panels ( 271DZ) and (272EZ) (Refer to TASK 53-01-00-900-801). 7 Remove the sealing dam (Refer to TASK 53-80-05-900-801). 8 Remove the HSTC 3 module ( 403CZ) (Refer to TASK 27-90-01-900-802). NOTE: The removed HSTC 3 module (403CZ) must be sent to one of the adresses listed in paragraph 1.G. 9 Remove the HSTC 4 module ( 1304CZ) (Refer to TASK 27-90-01-900-804). NOTE: The removed HSTC 4 module (1304CZ) must be sent to one of the adresses listed in paragraph 1.G. (6) Upload of the modules: NOTE: Depending on the means available, the MAIC modules may also have to be removed and replaced. (a) Upload the following modules (refer to DASSAULT AVIATION FCS data loading procedure DT EQUIP 43913 issue D): CAUTION: UPLOADING MUST BE PERFORMED BY AN OPERATOR AUTHORIZED BY THE COMPONENT MANUFACTURER DASSAULT EQUIPEMENTS AFTER A SPECIFIC TRAINING. CAUTION: IN PROCEDURE DT EQUIP 43913 ISSUE D, DO NOT REMOVE F1 FUSE (L9500CZ) AND F1 FUSE (R9500CZ). NOTE: If the tools or the authorized operator are not available, uploading will be performed later. • MAIC 1A module (1402CZ), • MAIC 2A module (601CZ), • MAIC 3A module (1202CZ), • MAIC 4A module (401CZ). (b) Record the results of this upload in the “NEW STANDARD INSTALLATION CHECKLIST” sheet attached. (c) Have the “NEW STANDARD INSTALLATION CHECKLIST” sheet signed by an aircraft inspector. (d) Send back the “NEW STANDARD INSTALLATION CHECKLIST” sheet and the “FIELD UPLOAD RECORD” to DASSAULT AVIATION at technicalcenter@dassault-aviation.com. (7) Place warning placards: “WARNING: DO NOT APPLY ELECTRICAL POWER”: (a) adjacent to the ground power receptacle, FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 7 / 90 DASSAULT AVIATION Proprietary Data ### Page 10 (b) in the cockpit, (c) at the aircraft batteries. (8) Make sure that the aircraft electrical systems are de-energized. (9) Make sure that the electrical ground power unit is disconnected from the aircraft. (10) Disconnect the batteries (Refer to TASK 24-32-01-920-801). (11) In the cockpit: NOTE: In addition to the elements listed below, it may be necessary to remove other items (optional equipment, completion add-ons), depending on the aircraft customization. (a) Remove the third crew member seat (M1001MP) (if installed) (Refer to TASK 25-12-00-900-801). (b) Remove the LH/RH pilot seats (L1001MP)/(R2001MP) (Refer to TASK 25-11-01-900-801). (c) Remove the following pedestal linings (Refer to SDS 06-30-00 ) and (Refer to TASK 25-13-13-900-801): • pedestal rear lining (221NZ), • pedestal middle lining (221MZ), • pedestal middle lining (222MZ). (d) Remove pedestal rear access panel (221QZ) (Refer to SDS 06-30-00) and (Refer to TASK 53-01-00-900-801) . (e) Remove cockpit lateral lining No.4 (222VZ) (Refer to SDS 06-30-00 ) and (Refer to TASK 25-13-13-900-801). (f) Pull slowly the rear upper corner of cockpit lateral lining No.2 (222TZ) (Refer to SDS 06-30-00) and remove the RH pilot wrist rest (R4001MP). (g) Remove the following linings (Refer to SDS 06-30-00 ) and (Refer to TASK 25-13-13-900-801): • cockpit lateral lining No.3 (222UZ), • cockpit lateral lining No.2 (222TZ), • cockpit lateral lining No.5 (222XZ), • cockpit lateral lining No.7 (222ZZ), • cockpit lateral lining No.5 (221XZ), • cockpit upper lining No.4 (221GZ), • cockpit upper lining No.8 (222HZ), • cockpit upper lining No.6 (221IZ), • cockpit upper lining No.5 (221HZ), • cockpit upper lining No.3 (221FZ), and, • remove the following RH side items and any other necessary items before removing cockpit upper lining No.7 (222EZ): • RH pilot sun visor (R102MP), • the three screws from the mounting rail of the RH pilot sun visor, • the mounting rail of the RH pilot sun visor, • the reading light, • cockpit upper lining No.1 (221DZ) and central arch window finisher (221CZ), • the RH PDU (R101FD) (Refer to TASK 31-60-13-900-801), FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 8 / 90 DASSAULT AVIATION Proprietary Data ### Page 11 • the electronic flight bag display and its support if installed, without disconnecting it, • the gasper. (h) Remove the entryway switch panel (7251XC) (refer to SMM, SDS 33-20-00). CAUTION: THE UPPER AND LOWER EXIT SIGN CONNECTORS CAN’T BE DISCONNECTED BEFORE BULKHEAD REMOVAL. THEY MUST BE DISCONNECTED DURING THE OPERATION, AS SOON AS THEY ARE ACCESSIBLE. (i) Remove the FR9 LH cockpit bulkhead ( L9630MP) (Refer to TASK 25-10-01-900-801). (j) Remove the following floor panels (Refer to TASK 53-01-00-900-801): • cockpit floor (114CZ), • cockpit floor (114FZ), • cockpit floor (114GZ), • cockpit floor (113GZ), • cockpit floor (121AZ), • cockpit floor (113HZ), • crew documentation stowage door (113IZ), • cockpit floor (121BZ). (k) Remove the crew documentation stowage box (9500MP): • Remove the eight screws (1-fig. 1) from the crew documentation stowage box. • Remove the crew documentation stowage box. (l) Remove the third crew member audio panel ( 1301FP) (Refer to TASK 23-50-01-900-801). (m) Remove the third crew member oxygen mask and stowage box (M1002WH) (Refer to TASK 35-10-01-900-801). (n) Remove the DMU (901FP) (Refer to TASK 45-90-01-900-801). (o) Remove the flight deck printer (104MP) (Refer to TASK 45-10-09-900-801) if installed, or the printer blanking plate. (p) Remove the LH windshield de-icing power supply (L1001DG) and the RH windshield de-icing power supply (R1001DG) (Refer to TASK 30-41-01-900-801). (q) Remove the emergency switch box (1001FW) (Refer to TASK 31-13-01-900-801). (r) Disconnect the electrical connectors 5000PM2A and 5000PM3A from the overhead panel (5000PM). (12) In the baggage compartment, remove the following items, if not previously removed: (a) Remove the LH and RH shelves (L9512MK)/(R9512MK) (Refer to TASK 25-52-01-900-801). (b) Remove the following linings (Refer to SDS 06-30-00 ) and (Refer to TASK 25-52-01-900-801): • frame 40 middle lining (272PZ), • frame 40 upper lining (272OZ), • frame 40 lower lining (272QZ), • frame 39 lower lining (272NZ), • FR. 36 - FR. 39 oblique lining (272HZ), • frame 39 upper lining (272MZ), FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 9 / 90 DASSAULT AVIATION Proprietary Data ### Page 12 • frame 40 middle lining (271OZ), • frame 40 upper lining (271NZ), • frame 40 lower lining (271PZ), • frame 39 lower lining (271MZ), • frame 40 center lining (271RZ), • FR. 36 - FR. 39 oblique lining (271FZ), • frame 39 upper lining (271LZ), • front rest seal lining (271JZ), • rear rest seal lining (271KZ). (c) If necessary, remove the towbar and its support to remove the carpet. (d) Remove the baggage compartment doorsill. (e) Remove the baggage compartment carpet. (f) Remove floor panels ( 271DZ) and (272EZ) (Refer to TASK 53-01-00-900-801). (g) Remove the sealing dam (Refer to TASK 53-80-05-900-801). (h) Remove the LH rear FCS rack (2003CZ) (Refer to TASK 27-90-05-900-802). (i) Remove the RH rear FCS rack ( 2004CZ) (Refer to TASK 27-90-05-900-804). WARNING: BEFORE REMOVING THE PPDB AND THE SPDB, MAKE SURE THAT THE ELECTRICAL GROUND POWER UNIT IS DISCONNECTED FROM THE AIRCRAFT AND THAT THE BATTERIES ARE DISCONNECTED. CAUTION: THE PPDB FEEDER STUDS SHOULD NOT BE OVERSTRESSED DURING REMOVAL/INSTALLATION. DO NOT EXERT ANY BENDING LOAD WHEN SCREWING/UNSCREWING FEEDER NUTS. (j) Remove the LH PPDB (5000PC) and the RH PPDB (6000PC) (Refer to TASK 24-61-01-900-801). (k) Remove the LH rear SPDB (L2000PM) and the RH rear SPDB (R2000PM) (Refer to TASK 24-62-09-900-801). B. GENERAL ELECTRICAL INSTRUCTIONS (1) 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 into the wire bundles, since they 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. (2) Due to the risk of damaging the wire insulation, it is prohibited to blindly drill holes through a box structure containing wiring. (3) To allow passage through the pressure seal boxes, use one of the spare wires mounted in these boxes. (4) New wires which are installed alongside existing wires should be secured by the existing clamp. (5) Check that all connections are properly protected to ensure proper insulation and that markings are visible and appropriate. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 10 / 90 DASSAULT AVIATION Proprietary Data ### Page 13 (6) Connector wires should be inserted and extracted as per the recommendations in Standard practices, (Refer to TASK 20-95-00-910-801). (7) Electric and electronic equipment should be removed and installed as per the recommendations in Standard Practices, (Refer to TASK 20-00-00-910-801). (8) Visually inspect the work area for particles or debris, then vacuum-clean. The blowing of compressed air is prohibited since it could move metal chips to inaccessible areas. (9) Wiring diodes must be installed in the unbent sections of bundles, attached with moderately tightened lacing tape. Do not use self-tightening clamps or wires ties. C. SECTION 7X-211-1: INSTALLATION OF CONTACTORS WARNING: AS THE ELECTRICAL AND MECHANICAL MODIFICATIONS TO BE PERFORMED IN THE BAGGAGE COMPARTMENT ARE TIGHTLY CONNECTED AND MUST BE CARRIED OUT SIMULTANEOUSLY, WE STRONGLY RECOMMEND TO CAREFULLY READ THE FOLLOWING SECTION PRIOR TO STARTING ANY OPERATION. WARNING: MAKE SURE TO USE APPROPRIATE TOOLS AND TO APPLY INDICATED TORQUE VALUES WHEN INSTALLING THE CONTACTORS AND RELAYS. (1) Mechanical modification (a) Install the new contactor (3311CH) (1-fig. 13) in the baggage compartment LH side, as follows: CAUTION: WHEN REROUTING FEEDERS ON LH SIDE, UNTIGHTEN ALL NECESSARY CLAMPS FROM FEEDTHROUGH TO THE WORK AREA TO ENSURE A 0.16 IN. (4 MM) MINIMUM CLEARANCE BETWEEN NEW FEEDER LOCATION AND SURROUNDING ELEMENTS (SEE FIG. 5). 1 On workbench, using fig. 14, drill two holes (A-fig. 14) in the omega support (19-fig. 14) to 0.19 in (4.9 mm). 2 Install the two stud supports (6-fig. 14). 3 In accordance with fig. 13, drill the four holes (A-fig. 13) to 0.2 in (5.2 mm). 4 Position the contactor on the omega support in accordance with fig. 14 then drill the omega support to install the three anchor nuts (13-fig. 14). NOTE: One hole is not used. 5 Install the three anchor nuts (13-fig. 14) on the omega support. 6 Install the four anchor nuts (4-fig. 13) on the omega support. 7 In accordance with fig. 13, position the assembly in the baggage compartment. NOTE: The omega support must be installed 0.078 in (2 mm) from the existing support (B-fig. 13). 8 Counterdrill the assembly to 0.098 in (2.5 mm) and maintain it in position using pins. 9 Drill the omega support for the four rivets (16-fig. 14) and the six rivets (15-fig. 14) (Refer to SRM 51-40-03). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 11 / 90 DASSAULT AVIATION Proprietary Data ### Page 14 10 Install the omega support using rivets (15-fig. 14) and (16-fig. 14). CAUTION: THE INSTALLATION OF THE LUGS MUST BE DONE IN ACCORDANCE WITH FIG. 5. 11 Once the electrical modification is done, install the six lugs on the omega support using the four screws (2-fig. 13) and washers (3-fig. 13). 12 Do a check of the electrical bonding (Refer to TASK 20-20-00-910-801). NOTE: The value measured must not exceed 2.5 mΩ. 13 Protect the assembly with vinyl varnish. 14 Install the contactor (1-fig. 13) on the omega support using the three screws (11-fig. 14) and the three washers (12-fig. 14). NOTE: One hole is not used. 15 Drill the existing bracket (C-fig. 13) for rivet (10-fig. 13) (Refer to SRM 51-40-03). 16 On the existing bracket (C-fig. 13), install the new cable holder (8-fig. 13) with a new rivet (10-fig. 13). 17 Install the new clamp (18-fig. 13). NOTE: The existing clamp on the fitting must be moved to its new position. 18 Replace the old support (D-fig. 13) with the new stud support (6-fig. 13). 19 Turn the clamp (E-fig. 13) to face forward. 20 In accordance with fig. 14, position the new support (30-fig. 14). NOTE: On support (30-fig. 14), enlarge the attachment holes for relay to dia 0.175 in. (4.4 mm) prior to installing the support plate. 21 Counterdrill the new support to 0.098 in (2.5 mm) and maintain it in position using pins. 22 Drill the new support for the two rivets (16-fig. 14) and the two rivets (32-fig. 14) (Refer to SRM 51-40-03). 23 Install the new support using rivets (32-fig. 14) and (16-fig. 14). 24 Once the electrical modification is done, install the new spacers (7-fig. 13) and (9-fig. 13). NOTE: The new spacers are used to route and maintain separation with the new cables. (b) Install the new contactor (R3311CH) (1-fig. 15) in the baggage compartment RH side, as follows: 1 On workbench, using fig. 15, drill a hole in the omega support (20-fig. 15) for rivet (14-fig. 15) (Refer to SRM 51-40-03). 2 Install the new stud support (17-fig. 15) using rivet (14-fig. 15). 3 Drill a hole in the omega support for rivet (15-fig. 16) (Refer to SRM 51-40-03). 4 Install the new craddle base (35-fig. 16) using rivet (15-fig. 16). 5 In accordance with fig. 16, drill the three holes (A-fig. 16) to 0.2 in (5.2 mm). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 12 / 90 DASSAULT AVIATION Proprietary Data ### Page 15 6 Position the contactor on the omega support in accordance with fig. 15 then drill the omega support to install the three anchor nuts (13-fig. 15). NOTE: One hole is not used. 7 Install the three anchor nuts (13-fig. 15) on the omega support. 8 Install the three anchor nuts (4-fig. 16) on the omega support. 9 Cut out the original bracket (A-fig. 15) for the installation of the new omega support. 10 In accordance with fig. 15, position the assembly in the baggage compartment. 11 Counterdrill the assembly to 0.098 in (2.5 mm) and maintain it in position using pins. 12 Drill the omega support for the four rivets (16-fig. 15) and the six rivets (15-fig. 15) (Refer to SRM 51-40-03). 13 Install the omega support using rivets (15-fig. 15) and (16-fig. 15). CAUTION: THE INSTALLATION OF THE LUGS MUST BE DONE IN ACCORDANCE WITH FIG. 6. 14 Once the electrical modification is done, install the five lugs on the omega support using the three screws (2-fig. 16) and washers (3-fig. 16). 15 Do a check of the electrical bonding (Refer to TASK 20-20-00-910-801). NOTE: The value measured must not exceed 2.5 mΩ. 16 Protect the assembly with vinyl varnish. 17 Install the contactor (1-fig. 15) on the omega support using the three screws (11-fig. 15) and the three washers (12-fig. 15). NOTE: One hole is not used. 18 In accordance with fig. 15, position the new support (31-fig. 15). NOTE: On support (31-fig. 15), enlarge the attachment holes for relay to dia 0.175 in. (4.4 mm) prior to installing the support plate. 19 Counterdrill the new support to 0.098 in (2.5 mm) and maintain it in position using pins. 20 Drill the new support for the two rivets (32-fig. 15) and the two rivets (33-fig. 15) (Refer to SRM 51-40-03). 21 Install the new support using rivets (32-fig. 15) and (33-fig. 15). 22 Once the electrical modification is done, install: • the two new spacers (7-fig. 16), • the two new spacers (34-fig. 16), • the new spacer (36-fig. 16), • the new spacer (37-fig. 16). NOTE: The new spacers are used to route and maintain separation with the new cables. (2) Electrical modification WARNING: MAKE SURE WIRING DOES NOT INTERFERE WITH SURROUNDING STRUCTURE OR OTHER ELECTRICAL WIRING. (a) In the cockpit: FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 13 / 90 DASSAULT AVIATION Proprietary Data ### Page 16 1 In order to save the emergency power supplies, on the overhead panel: • disconnect 5000PM3C connector, • make a shunt between 5000PM3C pin 15 and 5000PM3A pin 1. 2 In the cockpit, route new wires in accordance with fig. 2 , fig. 3 and fig. 4. CAUTION: NEW SHIELDED WIRE AND BOTH SHIELDING TERMINATIONS HAVE TO BE PROTECTED WITH CORSIL SHEATH. NOTE: The added wire is overlaid on the strand wire, no need to cut the existing bindings. Meanwhile, the added wire has to be held in place with the strand wire each time the strand wire is attached to the structure with tyraps or mechanical clamps. 3 Perform the electrical modification according to fig. 7 to fig. 12. 4 Do the wire-by-wire check of the new wiring installation. 5 Install the red bindings as necessary. 6 Install the blue bindings as necessary and as far as access permits. NOTE 1: To facilitate the inspection of potential ignition source wirings (15 Amps or more), wire bundles involved are identified with blue wire bindings instead of black ones. NOTE 2: The blue bindings must be installed at intervals of 300 mm (11.8 in) maximum. 7 Remove the shunt between 5000PM3C pin 15 and 5000PM3A pin 1. 8 Connect 5000PM2A, 3A and 3C to the overhead panel. (b) In the baggage compartment: 1 Route new wires in accordance with fig. 5 and fig. 6. CAUTION: WHEN ASSEMBLING SOCKET 5000PC7, POSITION THE TERMINAL BOOT PROPERLY USING LOCATOR KEY FIG. 17. NOTE: Wires jacketed with CORSIL sheath must be identified with FBW identification sleeve in accordance with FBW channels. 2 Perform the electrical modification according to: • fig. 7 to fig. 12. • the following instructions: • Wires jacketed with CORSIL sheath must be identified with FBW identification sleeve in accordance with FBW channels. • On contactors (R3311CH/3311CH), torque the nuts of terminals 3 and 4 to 10.62 lbf.in (1.2 N.m) and apply torque seal on the fittings. • On contactors (R3311CH/3311CH), torque the nuts of terminals A and B to 21.68 lbf.in (2.45 N.m) and apply torque seal on the fittings. • on relay support plates (40-fig. 14) and (41-fig. 15), enlarge the attachment holes for relay to dia 0.175 in (4.4 mm) prior to installing the support plates. • LH side: 3314CH relay support (40-fig. 14) must be installed at the same time as relays 3312CH and 3313CH with interlaying sealant. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 14 / 90 DASSAULT AVIATION Proprietary Data ### Page 17 • RH side: R3314CH relay support (41-fig. 15) must be installed at the same time as relays R3312CH and R3313CH and connector 2746J with interlaying sealant. • Do not bend the lugs. 3 Do the wire-by-wire check of the new wiring installation. 4 Protect the terminals lugs (A, B, 3 and 4) on contactors (R3311CH/3311CH) with high temperature sealant. 5 Protect new power supply cables coming from LH PPDB (5000PC) and RH PPDB (6000PC) with appropriate heat-shrinkable sheath (PR025). 6 Install the red bindings as necessary. 7 Install the blue bindings as necessary and as far as access permits. NOTE 1: To facilitate the inspection of potential ignition source wirings (15 Amps or more), wire bundles involved are identified with blue wire bindings instead of black ones. NOTE 2: The blue bindings must be installed at intervals of 300 mm (11.8 in) maximum. 8 Stick one of the two labels marked “3311CH”, “3312CH”, “3313CH”, “3314CH”, “R3311CH”, “R3312CH”, “R3313CH”, ”R3314CH”, “2746J” and “2747J” on the corresponding equipment body. Stick the second label on the adjacent aircraft structure. (3) Add “TRIM EMERG” label on the emergency switch box (1001FW) according to procedure in appendix A. D. SECTIONS 7X-211-2 AND 7X-211-3: INSTALLATION OF RELAYS WARNING: AS THE ELECTRICAL AND MECHANICAL MODIFICATIONS TO BE PERFORMED IN THE BAGGAGE COMPARTMENT ARE TIGHTLY CONNECTED AND MUST BE CARRIED OUT SIMULTANEOUSLY, WE STRONGLY RECOMMEND TO CAREFULLY READ THE FOLLOWING SECTION PRIOR TO STARTING ANY OPERATION. WARNING: MAKE SURE TO USE APPROPRIATE TOOLS AND TO APPLY INDICATED TORQUE VALUES WHEN INSTALLING THE RELAYS. (1) Mechanical modification (a) Install the new relay (3311CH) (50-fig. 21) in the baggage compartment LH side, as follows: CAUTION: WHEN REROUTING FEEDERS ON LH SIDE, UNTIGHTEN ALL NECESSARY CLAMPS FROM FEEDTHROUGH TO THE WORK AREA TO ENSURE A 0.16 IN. (4 MM) MINIMUM CLEARANCE BETWEEN NEW FEEDER LOCATION AND SURROUNDING ELEMENTS FIG. 19. 1 On workbench, using fig. 22, drill two holes (A-fig. 22) in the omega support (19-fig. 22) to 0.19 in (4.9 mm). 2 Install the two stud supports (6-fig. 22). 3 In accordance with fig. 21, drill the four holes (A-fig. 21) to 0.2 in (5.2 mm). 4 In accordance with fig. 22, drill the two holes (B-fig. 22) to install the two anchor nuts (52- fig. 22). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 15 / 90 DASSAULT AVIATION Proprietary Data ### Page 18 5 Install the two anchor nuts (52-fig. 22) on the omega support. 6 Install the four anchor nuts (4-fig. 21) on the omega support . 7 In accordance with fig. 21, position the assembly in the baggage compartment. NOTE: The omega support must be installed 0.078 in (2 mm) from the existing support (B-fig. 21). 8 Counterdrill the assembly to 0.098 in (2.5 mm) and maintain it in position using pins. 9 Drill the omega support for the four rivets (16-fig. 22) and the six rivets (15-fig. 22) (Refer to SRM 51-40-03). 10 Install the omega support using rivets (16-fig. 22) and (15-fig. 22). CAUTION: THE INSTALLATION OF THE LUGS MUST BE DONE IN ACCORDANCE WITH FIG. 19. 11 Once the electrical modification is done, depending on the part number of the relay to be installed, install the five or six lugs on the omega support using the three or four screws (2-fig. 21) and washers (3-fig. 21). 12 Do a check of the electrical bonding (Refer to TASK 20-20-00-910-801). NOTE: The value measured must not exceed 2.5 mΩ. 13 Protect the assembly with vinyl varnish. 14 Install the relay (50-fig. 21) on the omega support using the two screws (53-fig. 22) and the two washers (54-fig. 22). 15 Drill the existing bracket (C-fig. 21) for rivet (10-fig. 21) (Refer to SRM 51-40-03). 16 On the existing bracket (C-fig. 21), install the new cable holder (8-fig. 21) with a new rivet (10-fig. 21). 17 Install the new clamp (18-fig. 21). NOTE: The existing clamp on the fitting must be moved to its new position. 18 Replace the old support (D-fig. 21) with the new stud support (6-fig. 21). 19 Turn the clamp (E-fig. 21) to face forward. 20 In accordance with fig. 22, position the new support (30-fig. 22). 21 On relay support plate (30-fig. 22), enlarge the attachment holes for relay to dia 0.175 in (4,4 mm) prior to installing the support plate. 22 Counterdrill the new support to 0.098 in (2.5 mm) and maintain it in position using pins. 23 Drill the new support for the two rivets (16-fig. 22) and the two rivets (32-fig. 22) (Refer to SRM 51-40-03). 24 Install the new support using rivets (16-fig. 22) and (32-fig. 22). 25 Once the electrical modification is done, install the new spacers (7-fig. 21) and (9-fig. 21). NOTE: The new spacers are used to route and maintain separation with the new cables. (b) Install the new relay (R3311CH) (51-fig. 23) in the baggage compartment RH side, as follows: FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 16 / 90 DASSAULT AVIATION Proprietary Data ### Page 19 1 On workbench, using fig. 23, drill a hole in the omega support (20-fig. 23) for rivet (14-fig. 23) (Refer to SRM 51-40-03). 2 Install the new cable holder (17-fig. 23) using rivet (14-fig. 23). 3 Drill a hole in the omega support for rivet (15-fig. 24) (Refer to SRM 51-40-03). 4 Install the new craddle base (35-fig. 24) using rivet (15-fig. 24). 5 In accordance with fig. 24, drill the hole (A-fig. 24) to 0.2 in (5.2 mm). 6 In the omega support, drill the three holes (B-fig. 24) to a dia. of 0.39 in (10 mm) to install the three anchor nuts (56-fig. 24). NOTE: The plate (55-fig. 24) can be used to draw the axis holes. 7 Install the three anchor nuts (56-fig. 24) on the omega support. 8 Install the anchor nut (4-fig. 24) on the omega support. 9 Cut out the original bracket (A-fig. 23) for the installation of the new omega support. 10 In accordance with fig. 23, position the assembly in the baggage compartment. 11 Counterdrill the assembly to 0.098 in (2.5 mm) and maintain it in position using pins. 12 Drill the omega support for the four rivets (16-fig. 23) and the six rivets (15-fig. 23) (Refer to SRM 51-40-03). 13 Install the omega support using rivets (16-fig. 23) and (15-fig. 23). CAUTION: THE INSTALLATION OF THE LUGS MUST BE DONE IN ACCORDANCE WITH FIG. 20. 14 Once the electrical modification is done, install the three lugs on the omega support using the screw (2-fig. 24) and washer (3-fig. 24). 15 Do a check of the electrical bonding (Refer to TASK 20-20-00-910-801). NOTE: The value measured must not exceed 2.5 mΩ. 16 Protect the assembly with vinyl varnish. 17 Install the relay (51-fig. 24) on the plate (55-fig. 24) using the three nuts (59-fig. 24). 18 Install plate/relay assembly on the omega support using the three screws (57-fig. 24) and the three washers (58-fig. 24). 19 In accordance with fig. 23, position the new support (31-fig. 23). 20 On relay support plate (31-fig. 23), enlarge the attachment holes for relay to dia 0.175 in (4,4 mm) prior to installing the support plate. 21 Counterdrill the new support to 0.098 in (2.5 mm) and maintain it in position using pins. 22 Drill the new support for the two rivets (32-fig. 23) and the two rivets (33-fig. 23) (Refer to SRM 51-40-03). 23 Install the new support using rivets (32-fig. 23) and (33-fig. 23). 24 Once the electrical modification is done, install: • the two new spacers (7-fig. 24), • the two new spacers (34-fig. 24), FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 17 / 90 DASSAULT AVIATION Proprietary Data ### Page 20 NOTE: The new spacers are used to route and maintain separation with the new cables. (2) Electrical modification WARNING: MAKE SURE WIRING DOES NOT INTERFERE WITH SURROUNDING STRUCTURE OR OTHER ELECTRICAL WIRING. (a) In the cockpit: 1 In order to save the emergency power supplies, on the overhead panel: • disconnect 5000PM3C connector, • make a shunt between 5000PM3C pin 15 and 5000PM3A pin 1. 2 In the cockpit, route new wires in accordance with fig. 2 , fig. 3 and fig. 4. CAUTION: NEW SHIELDED WIRE AND BOTH SHIELDING TERMINATIONS HAVE TO BE PROTECTED WITH CORSIL SHEATHING. NOTE: The added wire is overlaid on the strand wire, no need to cut the existing bindings. Meanwhile, the added wire has to be held in place with the strand wire each time the strand wire is attached to the structure with tyraps or mechanical clamps. 3 SECTION 7X-211-2: Perform the electrical modification according to fig. 7, fig. 25, fig. 9, fig. 26, fig. 27 and fig. 28. 4 SECTION 7X-211-3: Perform the electrical modification according to fig. 7, fig. 29, fig. 9, fig. 30, fig. 31 and fig. 32. 5 Do the wire-by-wire check of the new wiring installation. 6 Install the red bindings as necessary. 7 Install the blue bindings as necessary and as far as access permits. NOTE 1: To facilitate the inspection of potential ignition source wirings (15 Amps or more), wire bundles involved are identified with blue wire bindings instead of black ones. NOTE 2: The blue bindings must be installed at intervals of 300 mm (11.8 in) maximum. 8 Remove the shunt between 5000PM3C pin 15 and 5000PM3A pin 1. 9 Connect 5000PM2A, 3A and 3C to the overhead panel. (b) In the baggage compartment: 1 Route new wires in accordance with fig. 19 and fig. 20. CAUTION: WHEN ASSEMBLING SOCKET 5000PC7, POSITION THE TERMINAL BOOT PROPERLY USING LOCATOR KEY FIG. 17. NOTE: Wires jacketed with CORSIL sheath must be identified with FBW identification sleeve in accordance with FBW channels. 2 Perform the electrical modification according to: • SECTION 7X-211-2: fig. 7, fig. 25, fig. 9, fig. 26, fig. 27 and fig. 28, • SECTION 7X-211-3: fig. 7, fig. 29, fig. 9, fig. 30, fig. 31 and fig. 32. • the following instructions: • identify the studs of both relays (3311CH/R3311CH) fig. 33, FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 18 / 90 DASSAULT AVIATION Proprietary Data ### Page 21 • On relay 3311CH, torque the nuts of terminals A2 and A3 to 14.6 lbf.in (1.65 N.m) and apply torque seal on all the fittings of the relay, • On relay R3311CH, torque the nuts of terminals A1 and A2 to 14.6 lbf.in (1.65 N.m) and apply torque seal on all the fittings of the relay, • Do not bend the lugs. 3 Do the wire-by-wire check of the new wiring installation. 4 Protect the terminals lugs of relays (R3311CH/3311CH) with high temperature sealant. 5 Protect new power supply cables coming from LH PPDB (5000PC) and RH PPDB (6000PC) with appropriate heat-shrinkable sheath (PR025). 6 Install the red bindings as necessary. 7 Install the blue bindings as necessary and as far as access permits. NOTE 1: To facilitate the inspection of potential ignition source wirings (15 Amps or more), wire bundles involved are identified with blue wire bindings instead of black ones. NOTE 2: The blue bindings must be installed at intervals of 300 mm (11.8 in) maximum. 8 Stick one of the two labels marked ”3311CH”, “3312CH”, “3313CH”, ”R3311CH”, “R3312CH”, “R3313CH”, “2746J” and “2747J” on the corresponding equipment body. Stick the second label on the adjacent aircraft structure. (3) Add “TRIM EMERG” label on the emergency switch box (1001FW) according to Appendix A. E. INSTALLATION CAUTION: FOR THE REFERRED TASKS, YOU MUST ONLY REFER TO THE “INSTALLATION” PARAGRAPHS. DO NOT PERFORM THE “TEST” PARAGRAPHS. (1) In the cockpit (a) Install the emergency switch box (1001FW) (Refer to TASK 31-13-01-900-801). (b) Install the LH windshield de-icing power supply (L1001DG) and the RH windshield de-icing power supply (R1001DG) (Refer to TASK 30-41-01-900-801). (c) Install the DMU (901FP) (Refer to TASK 45-90-01-900-801). (d) Install the third crew member audio panel (1301FP) (Refer to TASK 23-50-01-900-801). (e) Install the third crew member oxygen mask and stowage box (M1002WH) (Refer to TASK 35-10-01-900-801). (f) Install the RH PDU ( R101FD) (Refer to TASK 31-60-13-900-801). (g) Install the flight deck printer (104MP) (Refer to TASK 45-10-09-900-801) if removed, or the printer blanking plate. (h) Stick the 2 placards P/N F7XC531811115A1 on the instrument panel, over the old placards using araldite AV138M + hardener HV998. (2) In the baggage compartment: (a) Install the LH rear FCS rack (2003CZ) (Refer to TASK 27-90-05-900-802). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 19 / 90 DASSAULT AVIATION Proprietary Data ### Page 22 (b) Install the RH rear FCS rack (2004CZ) (Refer to TASK 27-90-05-900-804). (c) Install the LH rear FCS modules in the LH rear FCS rack (2003CZ) (Refer to TASK 27-90-01-900-802). NOTE: If HSTC 3 module (403CZ) P/N 0877X403-12 is not yet available, it will be installed just before performing the test of the FCS connectors. (d) Install the RH rear FCS modules in the RH rear FCS rack (2004CZ) (Refer to TASK 27-90-01-900-804). NOTE: If HSTC 4 module (1304CZ) P/N 0877X404-13 is not yet available, it will be installed just before performing the test of the FCS connectors. ¨ (e) For aircraft equipped with contactors, remove contactor (3311CH) from its support without disconnecting it and secure it during the installation of the LH PPDB (5000PC) (in order not to have the contactor hanging from the cables). CAUTION: THE PPDB FEEDER STUDS SHOULD NOT BE OVERSTRESSED DURING REMOVAL/INSTALLATION. DO NOT EXERT ANY BENDING LOAD WHEN SCREWING/UNSCREWING FEEDER NUTS. (f) Install the LH PPDB (5000PC) and the RH PPDB (6000PC) (Refer to TASK 24-61-01-900-801). NOTE: Apply torque seal F-900 (CPS 0232150) RED on the fitting, once nuts are torque- tightened. (g) For aircraft equipped with contactors, install contactor (3311CH) on its support. (h) Install the air-conditioning pipes located below the LH/RH rear FCS rack frames and the PPDBs. (i) Check the correct installation of the modification: 1 Make sure that the feeders do not interfere with surronding elements (clearance 0.16 in (4mm)). NOTE: If the clearance cannot be respected, protect them with teflon sheet (see figure below). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 20 / 90 DASSAULT AVIATION Proprietary Data ### Page 23 2 Make sure that the bindings are correctly installed. 3 Make sure that the lugs are not bent. (j) Install the LH rear SPDB (L2000PM) and the RH rear SPDB (R2000PM) (Refer to TASK 24-62-09-900-801). (k) Do an electrical bonding check (Refer to TASK 20-20-00-910-801 ) between the aircraft structure and: • LH rear SPDB (L2000PM) and RH rear SPDB (R2000PM), • LH PPDB (5000PC) and RH PPDB (6000PC). F. TESTS NOTE: Connector references are given for troubleshooting purposes if validation tests fail. (1) Connect the electrical ground power unit (GPU) (Refer to TASK 24-00-00-860-803). (2) Connect the batteries (Refer to TASK 24-32-01-920-801). (3) Energize the aircraft (Refer to TASK 24-00-00-860-803). (4) Perform the operational test of RH PDU (R101FD) (Refer to TASK 31-60-00-710-801). (5) Test of connector 5000PC3: (a) On the fire panel (200WZ), make sure that the engine 1 "DISCH 2" switch/light (952WZ) and engine 3 "DISCH 2" switch/light (962WZ) are extinguished. (6) Test of connector 6000PC3: (a) On the fire panel (200WZ), make sure that the engine 2 "DISCH 2" switch/light (957WZ) is extinguished. (7) Test of connectors 5000PC1: (a) On the maintenance panel (1010TP), set the "BATT 1/BATT 2" switch (310TP) to the “BATT1” position. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 21 / 90 DASSAULT AVIATION Proprietary Data ### Page 24 (b) Make sure that the amber LED set and the 3 green LED sets (U1, U2, U3) illuminate on the battery voltage indicator (210TP). (8) Test of connectors 6000PC1: (a) On the maintenance panel (1010TP), set the "BATT 1/BATT 2" switch (310TP) to the “BATT2” position. (b) Make sure that the amber LED set and the 3 green LED sets (U1, U2, U3) illuminate on the battery voltage indicator (210TP). (9) Test of connector L2000PM13: (a) On the maintenance panel (1010TP), set the "TEST E2" switch (L511CZ) to the up position. (b) On the “FCS” synoptic page, make sure that the “MFCC1” indicator (item 1) is displayed green. (c) On the maintenance panel (1010TP), set the "TEST E2" switch (L511CZ) to the down position (guard down). (10) Test of connector R2000PM19: (a) On the maintenance panel (1010TP), set the "TEST E1" switch (R511CZ) to the up position. (b) On the “FCS” synoptic page, make sure that the “SFCC1” indicator (item 2 on figure above) is displayed green. (c) On the maintenance panel (1010TP), set the "TEST E1" switch (R511CZ) to the down position (guard down). (11) Test of connectors 5000PM2A and 5000PM3A: (a) On the CMC, go to the 27-00 "OVERHEAD PANEL COMMANDS" maintenance screen. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 22 / 90 DASSAULT AVIATION Proprietary Data ### Page 25 (b) On the overhead panel (5000PM), push and hold the NORM "FCS ENGAGE" pushbutton (L9980PM). (c) Check that the status of the parameters shown are as follows: • "FBW3 / PFCS ENGAGE BUTTONS / NORMAL CMD 1": green, • "FBW4 / PFCS ENGAGE BUTTONS / NORMAL CMD 1": green. (12) Test of connector 5000PC7 (test of the modification implemented through this Service Bulletin): This test will be performed during the tests of FCS connectors. (13) Test of connector 5000PM2C: (a) Set the TCU engine 2 fuel switch (M9500EC) to “ON”. (b) On the overhead panel (5000PM), push and hold for 1s. the "ENG2" pushbutton (L9590PM) to the START position. (c) On the ENG-CAS display on the PDU, make sure the “START” indicator is displayed for the engine 2 N1 gauge. (d) Set the TCU engine 2 fuel switch (M9500EC) to “OFF”. (14) Test of connectors 5000PM2D and R2000PM22: (a) On the overhead panel (5000PM), set the "MASTER" APU pushbutton (R9500PM) to “ON”. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 23 / 90 DASSAULT AVIATION Proprietary Data ### Page 26 (b) Make sure that the APU master “ON” indicator light (item 1) flashes. NOTE: The APU master “ON” indicator light first flashes for 5 seconds. Then, it remains steady on. (c) Set the "MASTER" APU pushbutton (R9500PM) to the off position. (15) Test of connector 5000PM3D: (a) On the overhead panel (5000PM), check that the PAX "FWD TEMP" potentiometer (R9590PM) is set to “AUTO”. (b) On the “ECS” synoptic page, check that “PAX AUTO” (item 1) is displayed. (c) Set the PAX "FWD TEMP" potentiometer (R9590PM) to “MAN”. (d) On the “ECS” synoptic page, check that “PAX MAN” (item 2) is displayed. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 24 / 90 DASSAULT AVIATION Proprietary Data ### Page 27 (OCR) DASSAULT SERVICE BULLETIN AVIATION FALCON 7X 7X-211 (e) Set the PAX "FWD TEMP" potentiometer (R9590PM) to "AUTO". OXYGEN PRESSURIZATION MANUAL R9590PM NORMAL 20 °C CREW MA 20 20 °C LDG ELEV LOWE G11000 ft PAX AUTO PAX ON 20 °c REMOTEL VOL: 600 20 °C 9.7 2000 QTY: 30 ft/min NORMAL PACK HUMID:AUTO PAX XBLEEDS ECS CREW Д РСАВ CABIN ALT RATE OXYGEN CREW MA 20 °C PRESSURIZATION MANUAL DASSAULT AVIATION Proprietary Data LDG ELEV _OWE NORMAL 20 °C G11000 ft PAX MAN PAX ON 20 °C REMOTED VOL 600 20 °C 9.7 2000 QTY 30 ft/min NORMAL PACK HUMID:AUTO PAX XBLEEDS ECS CREW Д РСАВ CABIN ALT RATE (16) Test of connector 5000PC4: (a) On the overhead panel (5000PM), set the "GEN 1" pushbutton (L9710PM) to "OFF". (b) Make sure that the GEN1 "OFF" indicator light (item 1) illuminates. (c) Set the "GEN 1" pushbutton (L9710PM) to the auto position. (d) Make sure that the GEN1 "OFF" indicator light (item 1) extinguishes. DC SUPPLY L9710PM L9760PM 2 3 L9770PM June 22, 2011 ATA 27/ Revision 2 Page 25 / 90 ### Page 28 (17) Test of connector 5000PC6: (a) On the overhead panel (5000PM), set the "GEN 3" pushbutton (L9770PM) to “OFF”. (b) Make sure that the GEN3 “OFF” indicator light (item 3 on figure above) illuminates. (c) Set the "GEN 3" pushbutton (L9770PM) to the auto position. (d) Make sure that the GEN3 “OFF” indicator light (item 3 on figure above) extinguishes. (18) Test of connector 6000PC4: (a) On the overhead panel (5000PM), set the "GEN 2" pushbutton (L9760PM) to “OFF”. (b) Make sure that the GEN2 “OFF” indicator light (item 2 on figure above) illuminates. (c) Set the "GEN 2" pushbutton (L9760PM) to the auto position. (d) Make sure that the GEN2 “OFF” indicator light (item 2 on figure above) extinguishes. (19) Test of connector 5000PM3C: (a) On the overhead panel (5000PM), set the "EMERG LIGHTS" selector switch (R9920PM) to “ON”: • Check that “EMERG LIGHTS” (item 1) illuminates. • Check that the emergency lights illuminate in the cabin. (b) On the overhead panel (5000PM), set the "EMERG LIGHTS" selector switch (R9920PM) to “OFF”: • ¨ • Check that the emergency lights extinguish in the cabin. (20) Do the test after installation of the LH windshield de-icing power supply (L1001DG) and the RH windshield de-icing power supply (R1001DG) (Refer to TASK 30-41-01-900-801). (21) Test of connector 6000PC5: (a) On the “TEST” page, push the “RAT” soft key until the white "ELEC: RAT TEST IN PROGRESS" CAS message is displayed. (b) Make sure that the amber "ELEC: RAT GCU TEST FAIL" CAS message does not show. (22) Do the test after installation of the emergency switch box (1001FW): FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 26 / 90 DASSAULT AVIATION Proprietary Data ### Page 29 (a) On the emergency switch box (1001FW), make sure the "RAT AUTO" switch/light (1010PN) is set to “INHIBIT” position. NOTE: The "RAT AUTO" switch/light (1010PN) illuminates. (b) Make sure that the white "ELEC: RAT AUTO INHIBIT" CAS message is displayed. (c) On the “TEST” page, push the “LIGHTS” soft key. (d) On the emergency switch box (1001FW), make sure that the switch/lights illuminate. (e) Release the “LIGHTS” soft key. (f) Make sure that the switch/lights extinguish. NOTE: The "RAT AUTO" switch/light (1010PN) stays on. (23) Do the test after installation of the flight deck printer (104MP) (Refer to TASK 45-10-09-900-801) if installed. (24) Do the test after installation of the third crew member audio panel (1301FP) (Refer to TASK 23-50-01-900-801). (25) Perform the test of the third crew member oxygen mask and stowage box (M1002WH) (Refer to TASK 35-10-01-900-801). (26) Do the test after installation of the DMU (901FP) (Refer to TASK 45-90-01-900-801). (27) Test of connector L2000PM18: (a) Depending on the SATCOM installed: • in the “SAT” page of the radio management window, make sure that the “SAT status” is “AVAILABLE”, • or, make a SATCOM communication when the aircraft is out before the first flight. (28) Test of connectors 5000PC2 and 6000PC2: (a) On the RH PPDB (6000PC), disengage "BAG COMP FAN" circuit breaker (119HD) (CB270) and, 5 s later, disengage "BAG COMP FAN CTRL" circuit breaker (R219HD) (CB269). (b) Wait 20 s minimum and engage "BAG COMP FAN" circuit breaker (119HD) (CB270) and, 5 s later, engage "BAG COMP FAN CTRL" circuit breaker (R219HD) (CB269). (c) Check that the baggage compartment ventilation fan (109HD) runs. (d) Check that the following CAS messages are not displayed on the PDUs (L101FD)/(R101FD): • "15 COND: AFT FCS BOX OVHT" • "COND: BAG COMP HI TEMP" • "COND: BAG FAN FAULT" • "26 ELEC: AFT DIST BOX OVHT" • "ELEC: AFT DIST BOX HI TEMP" NOTE: For tests 29 to 32, switch on all applicable exterior lights from the cockpit and check that the corresponding lights come on outside the A/C. (29) Test of connectors 5000PM2B and L2000PM17: (a) Perform the operational test of the navigation lights (103LX)/(203LX)/(303LX) (Refer to TASK 33-40-00-710-801). (30) Test of connector 5000PM3B: FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 27 / 90 DASSAULT AVIATION Proprietary Data ### Page 30 (a) Perform the operational test of the RH landing light (R101LX) (Refer to TASK 33-40-00-710-801). (31) Test of connector L2000PM15 and L2000PM16: (a) Perform the operational test of the upper red anti-collision light (104LX) (Refer to TASK 33-40-00-710-801). (32) Test of connector R2000PM21 and R2000PM23: (a) Perform the operational test of the lower red anti-collision light (204LX) (Refer to TASK 33-40-00-710-801). (33) De-energize the aircraft sytems (Refer to TASK 24-00-00-860-803). G. TEST OF THE FCS CONNECTORS (1) PRELIMINARY STEPS (a) Obey the flight control system maintenance and safety precautions (Refer to TASK 27-00-00-910-801) (b) If not already done, upload the MAIC modules: NOTE: Depending on the means available, the MAIC modules may also have to be removed and replaced. 1 Upload the following modules (refer to DASSAULT AVIATION FCS data loading procedure DT EQUIP 43913 issue D): CAUTION: UPLOADING MUST BE PERFORMED BY AN OPERATOR AUTHORIZED BY THE COMPONENT MANUFACTURER DASSAULT EQUIPEMENTS AFTER A SPECIFIC TRAINING. CAUTION: IN PROCEDURE DT EQUIP 43913 ISSUE D, DO NOT REMOVE F1 FUSE (L9500CZ) AND F1 FUSE (R9500CZ). • MAIC 1A module (1402CZ), • MAIC 2A module (601CZ), • MAIC 3A module (1202CZ), • MAIC 4A module (401CZ). 2 Record the results of this upload in the “NEW STANDARD INSTALLATION CHECKLIST” sheet attached. 3 Have the “NEW STANDARD INSTALLATION CHECKLIST” sheet signed by an aircraft inspector. 4 Send back the “NEW STANDARD INSTALLATION CHECKLIST” sheet and the “FIELD UPLOAD RECORD” to DASSAULT AVIATION at technicalcenter@dassault- aviation.com. (c) If not already done, install the new HSTC 3 module (403CZ) P/N 0877X403-12 (Refer to TASK 27-90-01-900-802). (d) If not already done, install the new HSTC 4 module (1304CZ) 0877X404-13 (Refer to TASK 27-90-01-900-804). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 28 / 90 DASSAULT AVIATION Proprietary Data ### Page 31 (e) Connect the hydraulic ground power unit (GPU) to the hydraulic systems A, B and C (Refer to TASK 29-00-00-860-803). (f) Remove the four multi-function probe covers. (g) On the maintenance panel (1010TP), set the "TEST E1" switch (R511CZ) and "TEST E2" switch (L511CZ) to the ON position. REMINDER: THE AIRCRAFT IS DE-ENERGIZED. CAUTION: DURING THE FOLLOWING TESTS, MAKE SURE THAT THE PROTECTIVE CAP OF CONNECTORS 2746J AND 2747J DOES NOT MAKE CONTACT WITH THE CONTACTORS. (h) SECTIONS 7X-211-2 and 7X-211-3, using multimeter (TO-20-360) in ohmeter position and two tools P/N F7X0211E, check that the value between pins 1 and 2 of connector 2746J is less than 1 ohm. (i) Energize the aircraft sytems (Refer to TASK 24-00-00-860-803). (j) Pressurize hydraulic systems A and B and C (Refer to TASK 29-00-00-860-803) (2) Perform the ground test of the FCS except the “CLOSE-UP” paragraph (Refer to TASK 27-00-00-700-802). (3) Check the identification of the modules (Refer to TASK 27-00-00-720-802 ), only paragraph 5 “MODULES IDENTIFICATION”. MODULES NEW P/N HSTC 3 module (403CZ) 0877X403-12 HSTC 4 module (1304CZ) 0877X404-13 MAIC 1A module (1402CZ) ENS7X501-22 MAIC 2A module (601CZ) ENS7X501-22 MAIC 3A module (1202CZ) ENS7X501-22 MAIC 4A module (401CZ) ENS7X501-22 (4) Go to the 27-90 "FCS ELECTRONIC FAILURES (4/4)" maintenance screen. (5) On the overhead panel, push the NORM "FCS ENGAGE" pushbutton (L9980PM) during 5 s and verify in the maintenance screen that no discrete interface failure exists for SLM1, SLM2, SLM3 and SLM4. (6) Repeat the same operation for the ST-BY "FCS ENGAGE" pushbutton (L9990PM). (7) Test of the connectors: (a) Module test • Go to the 27-90 "FCS ELECTRONIC FAILURES (1/4)" maintenance screen. • Select the “MODULE TEST” soft key to start the test and make sure that the white "FCS: TEST IN PROGRESS" CAS message shows on the PDUs. NOTE: The test stops automatically after 20 seconds. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 29 / 90 DASSAULT AVIATION Proprietary Data ### Page 32 • Make sure that the four indicators of the “SYSTEM COMPATIBILITY CHECK” line do not show on the four “FCS ELECTRONIC FAILURES (X/4)” maintenance screens. If they show, replace the module indicated as failed on the “FCS ELECTRONIC FAILURES (X/4)” maintenance screen. Make sure that the amber "FCS: TEST FAIL" CAS message does not show on the PDUs. • On 27-90 "FCS ELECTRONIC FAILURES (1/4)" maintenance screen, select the “STOP TEST” soft key. (b) Engage function of the overhead panel • Go to the 27-00 "OVERHEAD PANEL COMMANDS" maintenance screen. • On the overhead panel (5000PM), push and hold the NORM "FCS ENGAGE" pushbutton (L9980PM): • Check the status of the parameters “FBWx / PFCS ENGAGE BUTTONS / NORMAL CMD x”: • All the sixteen parameters show green on the maintenance screen when the button is pressed. • Make sure that no indicator of the line “INTERNAL FAILURES CMOP” shows in red on the maintenance screen. • On the overhead panel (5000PM), push and hold the ST-BY "FCS ENGAGE" pushbutton (L9990PM): • Check the status of the parameters “FBWx / PFCS ENGAGE BUTTONS / STANDBY CMD x”: • All the sixteen parameters show green on the maintenance screen when the button is pressed. • Make sure that no indicator of the line “INTERNAL FAILURES CMOP” shows red on the maintenance screen. • On the overhead panel (5000PM), push to release the "A/B AUTO EXT." pushbutton (L9500PM). • Check the status of the parameters “FBWx / DISARM CMD x”: • All the eight parameters show green on the maintenance screen when the button is pressed. • Make sure that no indicator of the line “INTERNAL FAILURES CMOP” shows in red on the maintenance screen. • Check that the "FCS: AB AUTO EXTEND OFF" CAS message is displayed. • Check on the PDU that “DISARM” is displayed. • On the overhead panel (5000PM), push the "A/B AUTO EXT." pushbutton (L9500PM). (c) Electric segregation 1 FBW 1 test • On the maintenance panel, switch off the "TEST E2" switch (L511CZ). On the RH rear SPDB (R2000PM), disengage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). Go to the “C/B AND SSPC STATUS” page, with “FLIGHT CONTROL” selected in the SELECTED SYSTEM window, open and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 30 / 90 DASSAULT AVIATION Proprietary Data ### Page 33 The control surfaces position indications are dashed. Visually check , outside the aircraft, the correct deflection of the control surfaces when sidestick and rudder pedals are actuated. Ailerons, elevators and rudder are shown green with amber frame at the FCS synoptic. • On the maintenance panel, switch on the "TEST E2" switch (L511CZ). On the RH rear SPDB (R2000PM), engage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). Go to the C/B AND SSPC STATUS page, with FLIGHT CONTROL selected in the SELECTED SYSTEM window, close and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). • Perform a “FCS ENGAGE” by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel and check the correct deflection of the control surfaces when sidestick and rudder pedals are actuated and check their green representation at the FCS synoptic. 2 FBW 2 test • On the maintenance panel, switch off the "TEST E1" switch (R511CZ). On the RH rear SPDB (R2000PM), disengage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). Go to the C/B AND SSPC STATUS page, with FLIGHT CONTROL selected in the SELECTED SYSTEM window, open and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). The control surfaces position indications are dashed. Visually check , outside the aircraft, the correct deflection of the control surfaces when sidestick and rudder pedals are actuated. Ailerons, elevators and rudder are shown green with amber frame at the FCS synoptic. • On the maintenance panel, switch on the "TEST E1" switch (R511CZ). On the RH rear SPDB (R2000PM), engage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). Go to the C/B AND SSPC STATUS page, with FLIGHT CONTROL selected in the SELECTED SYSTEM window, close and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). • Perform a FCS ENGAGE by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel and check the correct deflection of the control surfaces when sidestick and rudder pedals are actuated and check their green representation at the FCS synoptic. 3 FBW 3 test • On the maintenance panel, switch off the "TEST E1" switch (R511CZ) and "TEST E2" switch (L511CZ). On the RH rear SPDB (R2000PM), disengage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). The control surfaces position indications are dashed. Visually check , outside the aircraft, the correct deflection of the control surfaces when sidestick and rudder pedals are actuated. Ailerons, elevators and rudder are shown green with amber frame at the FCS synoptic. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 31 / 90 DASSAULT AVIATION Proprietary Data ### Page 34 • On the maintenance panel, switch on the "TEST E1" switch (R511CZ) and "TEST E2" switch (L511CZ). On the RH rear SPDB (R2000PM), engage "FBW RR E4 SOL" circuit breaker (414CZ) and "FBW RR E4" circuit breaker (614CZ). • Perform a FCS ENGAGE by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel and check the correct deflection of the control surfaces when sidestick and rudder pedals are actuated and check their green representation at the FCS synoptic. 4 FBW 4 test • On the maintenance panel, switch off the "TEST E1" switch (R511CZ) and "TEST E2" switch (L511CZ). Go to the C/B AND SSPC STATUS page, with FLIGHT CONTROL selected in the SELECTED SYSTEM window, open and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). The control surfaces position indications are dashed. Visually check , outside the aircraft, the correct deflection of the control surfaces when sidestick and rudder pedals are actuated. Ailerons, elevators and rudder are shown green with amber frame at the FCS synoptic. • On the maintenance panel, switch on the "TEST E1" switch (R511CZ) and "TEST E2" switch (L511CZ). Go to the C/B AND SSPC STATUS page, with FLIGHT CONTROL selected in the SELECTED SYSTEM window, close and lock the Solid State Power Controllers (SSPC) "FBW LR E3 SOL" SSPC (313CZ) and "FBW LR E3" SSPC (413CZ). • Perform a FCS ENGAGE by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel and check the correct deflection of the control surfaces when sidestick and rudder pedals are actuated and check their green representation at the FCS synoptic. (d) THS motor tests Refer to fig. 18 CAUTION: DURING THIS TEST, MAKE SURE THAT NO INDICATOR SHOWS RED ON THE MAINTENANCE SCREEN. CAUTION: ON THE “FCS” SYNOPTIC PAGE, CHECK THAT THE “FCS MODE” IS IN NORMAL MODE. 1 THS motor 3 • Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen and check the THS motor 3 engagement. • Put the THS control surface on ND stop position. • Check the travel duration from ND to NU position : From the ND stop position, push the lower part of the PITCH trim control dual rocker to give a nose-up command and start chronometer when actual horizontal stabilizer movement is evidenced on a FBWx / HORIZONTAL STABILIZER POSITION (°) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 32 / 90 DASSAULT AVIATION Proprietary Data ### Page 35 maintenance parameter of the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen. Perform complete deflection from ND to NU. When parameter reaches full NU, stop chronometer: this travel duration must be equal to 20.5 seconds +/-2s. • Check the travel duration from NU to ND position : From the NU stop position, push the upper part of the “PITCH” trim control dual rocker to give a nose-down command and start chronometer when actual horizontal stabilizer movement is evidenced on a “FBWx / HORIZONTAL STABILIZER POSITION (°)” maintenance parameter of the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen. Perform complete deflection from NU to ND. When parameter reaches full ND, stop chronometer: this travel duration must be equal to 20.5 seconds +/-2s. 2 THS motor 4 • Select the “MOTOR 4 TEST” soft key. • Check the THS motor 4 engagement. • Check that the THS control surface is on ND stop position. • Check the travel duration from ND to NU position: perform the same test as for THS motor 3. • Check the travel duration from NU to ND position: perform the same test as for THS motor 3. 3 THS motor BU • Select the “MOTOR BU TEST” soft key. • Check the THS motor BU engagement. • Check that the THS control surface is on ND stop position. • Check the travel duration from ND to NU position: perform the same test as for THS motor 3 with deflection duration equal to 34 seconds +/-3s. • Check the travel duration from NU to ND position: perform the same test as for THS motor 3 with deflection duration equal to 34 seconds +/-3s. • Select the “STOP TEST” soft key and check the motor 3 engagement. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 33 / 90 DASSAULT AVIATION Proprietary Data ### Page 36 (8) Test of connector 5000PC7 and relays (3314CH/R3314CH) (test of the modification implemented through this Service Bulletin) (a) On the “FCS” synoptic page, make sure that the “THS” is displayed green. (b) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen and check the THS motor 3 engagement. (c) Push the “TRIM EMERG” switch (111CH) on emergency switch box (1001FW). (d) Check that the “ON” indication illuminates. (e) Push the lower part of the “PITCH” trim control dual rocker to give a nose-up command until NU stop is reached. (f) On 27-40 "HORIZONTAL STABILIZER ACTUATOR " maintenance screen, check the BU motor engagement and check that the amber "FCS: ALTN LAWS ACTIVE" and "FCS: THS DEGRAD" CAS messages are displayed on the PDUs. (g) Check on the FCS synoptic page that the THS is displayed green with an amber frame. NOTE: On 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, several parameters will be displayed in red : “HSTC3 - HSECU” and/or “HSTC4 - HSECU” and “THS ACTUATOR FAIL”. (h) On the PDUs, make sure that the pitch trim position indicator moves to the “NU” indication. (i) Push the upper part of the “PITCH” trim control dual rocker to give a nose-down command until ND stop is reached. (j) On the PDUs, make sure that the pitch trim position indicator moves to the “ND” indication. (k) Push the “TRIM EMERG” switch (111CH) of the emergency switch box (1001FW) and make sure that the “ON” indication extinguishes. (l) Perform a “FCS ENGAGE” by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel and check: • the motor 3 engagement on 27-40 "HORIZONTAL STABILIZER ACTUATOR " maintenance screen, FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 34 / 90 DASSAULT AVIATION Proprietary Data ### Page 37 • that THS is displayed green on the “FCS” synoptic page. (m) On 27-40 "HORIZONTAL STABILIZER ACTUATOR " maintenance screen, select the “MOTOR 4 TEST” soft key and check the THS motor 4 engagement. (n) Perform the same tests as motor 3 above (steps (c) to (k). (o) On 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “STOP TEST” soft key and check the motor 3 engagement. (p) Perform a “FCS ENGAGE” by pushing on the NORM "FCS ENGAGE" pushbutton (L9980PM) or the ST-BY "FCS ENGAGE" pushbutton (L9990PM) on the overhead panel. (9) SECTION 7X-211-1: Test of relays (3312CH / 3313CH / R3312CH / R3313CH) NOTE: During the following tests, use multimeter (TO-20-360) in ohmeter position and tool P/N F7X0211E. (a) Release the park brake handle (804GC) and wait for 30 s. (b) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “motor 4 test” soft key and: 1 Check that "FCS: ACMU3 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU3 fault (THS3)” 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 4 Check that value between connector 2746 pin 2 and the A/C grounding reference (9500MT) is less than 1 ohm. 5 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is less than 1 ohm. (c) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “motor BU test” soft key and: 1 Check that: • "FCS: ACMU4 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU4 fault (THS4)”, • "FCS: ACMU3 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU3 fault (THS3)”, • "FCS: ALTERNATE MODE CAUSE" is displayed with root cause “THS POS OR ACTUATION fault”, • "FCS: THS DEGRAD " and "FCS: ALTN LAWS ACTIVE " CAS messages are displayed • THS is displayed green with an amber frame on the FCS synoptic page. 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 35 / 90 DASSAULT AVIATION Proprietary Data ### Page 38 4 Check that value between connector 2746 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 5 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. (d) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “STOP TEST” soft key and check the THS motor 3 engagement: 1 Check that the previous CAS messages and fault messages are no more displayed and that THS is displayed green on the “FCS” synoptic page. 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is less than 1 ohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is less than 1 ohm. 4 Check that value between connector 2746 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 5 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. (e) Pull the park brake handle (804GC) to the first notch. (10) SECTIONS 7X-211-2 and 7X-211-3: Test of relays (3312CH / 3313CH / R3312CH / R3313CH) NOTE: During the following tests, use multimeter (TO-20-360) in ohmeter position, and tool P/N F7X0211E. (a) Release the park brake handle (804GC) and wait for 30 s. (b) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “motor 4 test” soft key and: 1 Check that "FCS: ACMU3 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU3 fault (THS3)”. 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 4 Check that value between connector 2746 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 5 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. (c) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “motor BU test” soft key and: 1 Check that: • "FCS: ACMU3 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU3 fault (THS3)”, • "FCS: ACMU4 ACTUATION FAULT" is displayed on FAULT page with root cause “ACMU4 fault (THS4)”, FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 36 / 90 DASSAULT AVIATION Proprietary Data ### Page 39 • "FCS: ALTERNATE MODE CAUSE" is displayed with root cause “THS POS OR ACTUATION fault”, • "FCS: THS DEGRAD " and "FCS: ALTN LAWS ACTIVE " CAS messages are displayed, • THS is displayed green with an amber frame on the FCS synoptic page. 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is greater than 1 Mohm. 4 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is less than 25 ohm. (d) Go to the 27-40 "HORIZONTAL STABILIZER ACTUATOR" maintenance screen, select the “STOP TEST” soft key and check the THS motor 3 engagement: 1 Check that the previous CAS messages and fault messages are no more displayed and that THS is displayed green on the “FCS” synoptic page. 2 Check that value between connector 2747 pin 2 and the A/C grounding reference (9500MT) is less than 1 ohm. 3 Check that value between connector 2747 pin 3 and the A/C grounding reference (9500MT) is less than 1 ohm. 4 Check that value between connector 2746 pin 3 and the A/C grounding reference (9500MT) is less than 25 ohm. (e) Pull the park brake handle (804GC) to the first notch. (11) Perform the test of the EBHA (Refer to TASK 27-11-09-710-801 , paragraph “EBHA TEST”). (12) On 27-10 "SPOILERS ACTUATORS" maintenance screen, select the “STOP TEST” soft key. (13) FCS Ground test : • Perform a FCS Ground test, except the “CLOSE-UP” paragraph (Refer to TASK 27-00-00-700-802). • Go to the CMC “ACTIVE MAINTENANCE MESSAGES” page (Refer to TASK 45-10-00-910-801) and check that no ATA 27 maintenance message is active. (14) On the overhead panel (5000PM), set the "PROBE 1+2" pushbutton (R9810PM), the "PROBE 3" pushbutton (R9820PM) and the "PROBE 4" pushbutton (R9830PM) to the “OFF” position. (15) On the maintenance panel (1010TP), set the "TEST E2" switch (L511CZ) and the "TEST E1" switch (R511CZ) to the OFF position. (16) Perform the operational test of the primary-power distribution-system (Refer to TASK 24-61-00-710-801). (17) Remove the electrical and hydraulic GPUs. (18) Perform the operational test of the primary DC generation system (Refer to TASK 24-31-00-710-801). (19) Perform the operational test of the APU starter-generator system (Refer to TASK 49-10-01-860-801). FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 37 / 90 DASSAULT AVIATION Proprietary Data ### Page 40 H. FINAL STEPS ¨ (1) Install and tighten LH and RH FCS rack covers according to the CLOSE-UP paragraph of “Removal/ Installation of the LH rear FCS modules” procedure (Refer to TASK 27-90-01-900-802). (2) In the cockpit and the baggage compartment, install all the items, access panels and linings removed. (3) Perform a test of the EFB (Refer to CMC Electronics Pilotview™). I. DOCUMENTATION (1) Update the Airplane Flight Manual with CP55 and CP56 pages. (2) Incorporate Chapter 5-40 CP009. (3) Incorporate the wiring diagram schematics into the wiring diagram manual. J. RECORDING For continuing airworthiness, retain a copy of this Service Bulletin in your maintenance documentation until the AMM and IPC are revised. In the appropriate aircraft documents, record compliance with: • Service Bulletin 7X-211-R2-1 for aircraft which have performed SECTION 7X-211-1 (installation of contactors P/N 02N10556-MODA), • Service Bulletin 7X-211-R2-2 for aircraft which have performed SECTION 7X-211-2 (installation of relays including relay P/N DR50E41D), • Service Bulletin 7X-211-R2-3 for aircraft which have performed SECTION 7X-211-3 (installation of relays including relay P/N DS50E42D), Fill out the electronic Service Bulletin reply form located in the ”Service Bulletin" page on the Falcon portal. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 38 / 90 DASSAULT AVIATION Proprietary Data ### Page 41 3. ACCOMPLISHMENT INSTRUCTIONS FOR AIRCRAFT WHICH HAVE ALREADY IMPLEMENTED REVISION 1 OF THIS SERVICE BULLETIN A. PRELIMINARY STEPS (1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801). B. MODIFICATION (1) Replace the frame (item 4) of the emergency switch box (1001FW) in accordance with the appendix A. (2) Perform the test of the emergency switch box (1001FW) emergency switch box (1001FW) (Refer to TASK 31-13-01-900-801). C. RECORDING Record compliance with Service Bulletin 7X-211-R2-1 in the appropriate aircraft documents. Fill out the electronic Service Bulletin reply form located in the ”Service Bulletin" page on the Falcon portal. FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 39 / 90 DASSAULT AVIATION Proprietary Data ### Page 42 4. MATERIAL INFORMATION A. MODIFICATION OF MODULE PART NUMBERS (1) Module Part Numbers to be removed and replaced NEW P/N QTY DESIGNATION OLD P/N 0877X403-12 1 HSTC 3 module (403CZ) 0877X403-11 0877X404-13 1 HSTC 4 module (1304CZ) 0877X404-12 (2) Module Part Numbers to be uploaded NOTE: Depending on the logistics, the MAIC modules can also be removed and replaced. NEW P/N QTY DESIGNATION OLD P/N ENS7X501-22 1 MAIC 1A module (1402CZ) ENS7X501-20 ENS7X501-22 1 MAIC 2A module (601CZ) ENS7X501-20 ENS7X501-22 1 MAIC 3A module (1202CZ) ENS7X501-20 ENS7X501-22 1 MAIC 4A module (401CZ) ENS7X501-20 B. MODIFICATION KIT NOTE 1: • SECTION 7X-211-1: Use kits SBF7X0211A, SBF7X0211B, SBF7X0211C, SBF7X0211D and SBF7X0211F. • SECTION 7X-211-2: Use kits SBF7X0211A1 (including relay DR50E41D), SBF7X0211B , SBF7X0211C and SBF7X0211F. • SECTION 7X-211-3: Use kits SBF7X0211A1 (including relay DS50E42D), SBF7X0211B, SBF7X0211C and SBF7X0211F. NOTE 2: Wire identification sleeves (01PR0TMSxxx) can be locally manufactured. Kit P/N SBF7X0211AR1 NEW P/N Q T Y KEY WORD SBF7X0211A 1 For contactor installation or SBF7X0211A1 1 For relay Installation Kit P/N SBF7X0211A (contactor installation) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 40 / 90 DASSAULT AVIATION Proprietary Data ### Page 43 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION I T E M F I G 02N10556-MODA 2 Contactor R3311CH / 3311CH 1 13, 15 22208BC050012LE 2 Screw 2 4 23111BC050LE 2 Washer 3 4 5SR1009M 1 Anchor nut ¨ ¨ 78754 3 Stud support 6 13, 14 78777-01 3 Spacer 7 13, 16 78772-003 1 Cable holder 8 13 78776-01 3 Spacer 9 13, 4 35053-3210ID 1 Rivet 10 13 NAS1142V3 6 Screw 11 14, 15 NAS1149CN816R 6 Washer 12 14, 15 MS21059L08 6 Anchor nut 13 14, 15 35053-3210ID 1 Rivet 14 15 35053-3208ID 12 Rivet 15 15 35053-4010ID 8 Rivet 16 15 78774-001 1 Cable holder 17 15 78651RH14CS 1 Clamp 18 13 F7XC535141111E01 1 Omega support 19 14 F7XC535141112E01 1 Omega support 20 15 35053-2405ID 12 Rivet 22431BC050LE 2 Nut For shielding termination 22 4 Table 1: MECHANICAL KIT NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION 82525904 1 TRIM EMERG label Contains: ”TRIM EMERG” legend FE1574-05 label (See appendix A for details) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 41 / 90 DASSAULT AVIATION Proprietary Data ### Page 44 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION 01EQTPRL08R01 4 Splice SP5000PM2A-4 SP2004CZ104 SP2003CZ306 SP5000PM3A 01EQTPRL08B01 1 Splice SP1001FW2A-6 01C0K308-22DS01 4 Contact 1001FW-20, 1001FW-17 01C0K308-08P01 1 Contact 5000PC7-A 01C0A54148FC22 12 Dummy contact 5000PM3A, 2003CZ306 01EQTEC1-1 28 Plug 01EQTRB23-1R 2 Self-soldering sleeve 1001FWT1-1001FWT2 01EQTPRL16B01 2 Splice 5000PM2A - 5000PM3A 01EQTRB32-6A 2 Self-soldering sleeve (B053-70-02) 01PR0PRL05 2 Kit (B500-02-107) 6000PC-218/R3311CH-A 2 Wire identification sleeve (01PR0TMS1-8GR) 5000PC7-A/3311CH-B 2 Wire identification sleeve (01PR0TMS1-4GR) 1001FW2A-17/SP5000PM2A 2 Wire identification sleeve (01PR0TMS1-8GR) 1001FW2A-20/SP5000PM3A 2 3311CH-T1/AA 2 1001FW2A-16/SP1001FW2A-6 2 1001FW2A-18/SP1001FW2A-6 2 1001FW2A-20/1001FW-T2 2 1001FW2A-17/1001FW-T1 2 SP5000PM2A 1 Splice identification sleeve (01PR0TMS3-32GR) SP2004CZ104 1 SP2003CZ306 1 SP5000PM3A 1 SP1001FW2A-6 1 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 42 / 90 DASSAULT AVIATION Proprietary Data ### Page 45 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION 01EQTC0S20-04-071-22 6 Lug 3311CH-3/-4, R3311CH-3/-4 01EQTC0S30-05-119-08 2 3311CH-A, 3311CH-B 01EQTC0S20-05-071-22 2 3311CH-B*, R3311CH-B* 01EQTC0S20-05-079-20 3 3311CH-T1-1001FWT2 01EQTC0S20-05-095-12 3 6000PC-218, R3311CH-A 01C0A54148-17-21-7 1 Cable union 5000PC7 01PR0PM0-3K18-5 1 Heat-shrinkable molded part 5000PC7 01CAB211-1-22 40 ft (12 m) Cable 01CAN211-1-22 4 ft (1 m) Cable 01CAN211-1-12 4 ft (1 m) Cable 03CAN600-1-D08 4 ft (1 m) Cable 01CAN203-1-20B 4 ft (1,2 m) Cable 01PR0FVE02W 36 ft (12 m) CORSIL sheath 02PR0TSL050BK 16 ft (5 m) Black braiding 01PR0RNF1-4BK 2 ft (0.6 m) Heat shrinkable sheath 01PR025-1-4BK 2 ft (0.6 m) 01PR025-1-2BK 1 ft (0.3 m) 01PR0KYN1-8TR 3 in (75 mm) Wire 27040142 Wire 27040155 01PR0ATU6-2BK 3 in (75 mm) 5000PC7 78750-02 50 Tyrap 3311CH 2 ”STERLING” E19 label R3311CH 2 “STERLING” E19 label Table 2: ELECTRICAL KIT FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 43 / 90 DASSAULT AVIATION Proprietary Data ### Page 46 kit SBF7X0211A1 NEW P/N Q T Y KEY WORD INSTRUCTIONS DISPOSITION ITEM FIG DS50E42D or DR50E41D 1 Relay 3111CH 50 21 ES1501444W1361 1 Relay R3111CH 51 23 22208BC050012LE 1 Screw 2 4 23111BC050LE 2 Washer 3 4 78754 3 Stud support 6 21, 22 78777-01 4 Spacer 7 21, 24 78772-003 1 Cable holder 8 21 78776-01 3 Spacer 9 4, 21 35053-3210ID 1 Rivet 10 21 35053-3210ID 1 Rivet 14 23 35053-3208ID 12 Rivet Omega support 15 22, 23 35053-4010ID 8 Rivet 16 22, 23 78774-001 1 Cable holder 17 23 78651RH14CS 1 Clamp 18 21 F7XC535141111E01 1 Omega support 19 22 F7XC535141112E01 1 Omega support 20 23 35053-2405ID 10 Rivet For anchor nut 22431BC050LE 1 Nut For ground lug 22 4 MS21059L08 2 Anchor nut For relay DR/DSxxx 52 22 MS27039AV10XF 2 Screw For relay DR/DSxxx 53 22 NAS1149DN816K 2 Washer For relay DR/DSxxx 54 22 F7XC535141130 1 Plate For relay ES1501444W1361 55 24 MS21071L3 3 Anchor nut 56 24 NAS9203-7 3 Screw 57 24 NAS1149D0316K 3 Washer 58 24 MS21042L04 3 Nut 59 24 Table 3: MECHANICAL KIT FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 44 / 90 DASSAULT AVIATION Proprietary Data ### Page 47 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION 82525904 1 TRIM EMERG label Contains: ”TRIM EMERG” legend FE1574-05 label (See appendix A for details) 01EQTPRL08B01 1 Splice SP1001FW2A-6 01C0K308-22DS01 4 Contact 1001FW-20, 1001FW-17 01C0K308-08P01 1 Contact 5000PC7-A 01C0A54148FC22 12 Dummy contact 5000PM3A, 2003CZ-306 01EQTEC1-1 28 Plug 01EQTRB23-1R 2 Self-soldering sleeve 1001FWT1-1001FWT2 01EQTPRL16B01 2 Splice 5000 PM2A-5000PM3A01EQTRB32-6A 2 Self-soldering sleeve(B053-70-02) 01PR0PRL05 2 Kit (B500-02-107) 5000PC7-A/3311CH-A2 2 Wire identification sleeve (01PR0TMS1-4GR) 2316JE/SP3311CH-X1 2 Wire identification sleeve(01PR0TMS1-8GR) 3311CH-X2/SP3313CH-A3 3311CH-T1/AA 3311CH-X2/SP3313CH-A3 3313CH-A2/SP3312CH-A2 3313CH-A1/2747J-3 SP3313CH-A3/2747J-1 SP3312CH-A3/SP3313CH-A3 3312CH-A1/2747J-2 SP3312CH-A3/3312CH-T3 2316JE/SP3312CH-X1 SP3312CH-X1/3313CH-X1 1001FW2A-17/SP5000PM3A 1001FW2A-17/1001FW-T2 SP2003CZ306/SP3312CH-A3 3312CH-X2/2319JE-A 3313CH-X2/2318JE-A 2318JE-K/3313CH-T2 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 45 / 90 DASSAULT AVIATION Proprietary Data ### Page 48 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION SP2003CZ303-45/2318JE-K 2 Wire identification sleeve(01PR0TMS1-8GR) SP2003CZ303-35/2319JE-K 2319JE-K/3312CH-T2 3311CHT-GRD/3311CH-T2 6000PC-218/R3311CH-A1 2416JE/SPR3311CH-X1 R3311CH-A2/R3311CH-T1 R3311CH-XY2/SPR3312CH-A2 SPR3312CH-A2/2746J-1 R3312CH-A3/2746J-2 R3313CH-A3/2746J-3 R3313CH-A1/R3312CH-A1 2416JE/SPR3312CH-X1 SPR3312CH-X1/R3313CH-X1 1001FW2A-19/SP5000PM2A 1001FW2A-19/1001FW-T1 SP2004CZ104/R3313CH-A2 R3313CH-A2/R3313CH-T1 R3313CH-X2/2418JE-A R3312CH-X2/2419JE-A SP2004CZ409-35/2419JE-K SP2004CZ409-45/2418JE-K 2419JE-K/R3312CH-T2 2418JE-K/R3313CH-T2 SP3311CH-3 1 Splice identification sleeve(01PR0TMS3-32GR) SP3313CH-A3 SP3312CH-A3 SP3313CH-X1 SP3312CH-A2 SP2003CZ303-45 SP2003CZ303-35 SP5000PM3A FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 46 / 90 DASSAULT AVIATION Proprietary Data ### Page 49 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION SP2003CZ306 1 Splice identification sleeve(01PR0TMS3-32GR) SPR3311CH-X1 SPR3312CH-A2 SPR3312CH-X1 SP2004CZ409-35 SP2004CZ409-45 SP5000PM2A SP2004CZ104 01EQTC0S30-04-103-08 2 Lug 3311CH-A2, 3311CH-A3 01EQTC0S20-04-071-22 2 3311CH-A2* R3311CH-A1* 01EQTC0S20A03-071-22 2 3311CH-X1 , 3311CH-X2 01EQTC0S20-04-079-20 1 3311CH-GRD 01EQTC0S20-05-079-20 4 3311CH- T1-3311CHT2-1001FWT1-1 001FWT2 01EQTC0S20-05-095-12 1 6000PC-218 01EQTC0S20-04-095-12 2 R3311CH-A1 R3311CH-A2 01C0A54148-17-21-7 1 Cable union 5000PC7 01PR0PM0-3K18-5 1 Heat-shrinkable molded part 5000PC7 01EQTSR03-20S01 2 Contact R3311CH 01C0A54148FC20 4 Dummy contact 01CAB211-1-22 39 ft (12m) Cable 01CAN211-1-12 3 ft (1 m) 03CAN600-1-D08 3 ft (1 m) 01CAN203-1-20B 4 ft (1.20 m) 01PR0FVE02W 39 ft (12 m) Corsil sheath 02PR0TSL050BK 16 ft (5 m) Black braiding 01PR0RNF1-4BK 2 ft (0.6 m) Heat shrinkable sheath 01PR025-1-4BK 2 ft (0.6 m) 01PR025-1-2BK 1 ft (0.3 m) 01PR0KYN1-8TR 3 in (75 mm) 01PR0ATU6-2BK 3 in (75 mm) 78750-02 50 Tyrap FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 47 / 90 DASSAULT AVIATION Proprietary Data ### Page 50 NEW P/N Q T Y KEY WORD INSTRUCTIONSDISPOSITION 3311CH 2 ”STERLING” E19 label R3311CH 3311CH-T1 3311CH-T2 3313CH-T2 3312CH-T2 3312CH-T1 3312CH-T3 R3313CH-T1 R3313CH-T2 R3312CH-T2 R3311CH-T1 1001FW-T2 1001FW-T1 Table 4: ELECTRICAL KIT Kit P/N SBF7X0211B NEW P/N Q T Y KEY WORD I T E M F I G F7XC535141123 1 Relays and Test Connector Support 30 14, 22 F7XC535141124 1 Relay and Test Connector Support 31 15, 23 35053-4010ID 2 Rivet 16 14, 22 35053-3207ID 4 Rivet 32 14, 15, 22, 23 35053-4008ID 2 Rivet 33 15, 23 78777-02 2 Spacer 34 16, 24 78757-02 1 Craddle base 35 16, 24 78776-01 1 Spacer 36 16 78776-02 1 Spacer 37 16 22208BC050012LE 5 Screw 2 13, 16, 21, 24 23111BC050LE 5 Washer 3 13, 16, 21, 24 5SR2009M 7 Anchor nut 4 13, 16, 21, 22 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 48 / 90 DASSAULT AVIATION Proprietary Data ### Page 51 NEW P/N Q T Y KEY WORD I T E M F I G 78754 2 Stud support 6 13, 14, 21, 22 35053-3208ID 4 Rivet 15 16, 24 35067-2405ID 26 Rivet for anchor nut ¨ Table 5: MECHANICAL KIT NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 01APP3203-2RT05M03D3-05B or 315203DPMQ28 or M210D4N006 or M210D4NC-ER 4 Relay 3312CH 3313CH R3312CH R3313CH 01APP3205-028-2-1L03 or S210A1A1 or S315E01A25001 or 01APP3205-028-2-1-03 4 Support 01APPMDR20-2A0-0600 4 Diode 2318JE 2319JE 2418JE 2419JE 01APPMF20-0A5 2 Fuse 2316JE 2416JE 01EQT53105A20P01 12 Contact 2318JE 2319JE 2418JE 2419JE 2316JE 2416JE FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 49 / 90 DASSAULT AVIATION Proprietary Data ### Page 52 NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 01C0R54148-0CW09-35SNL 2 Connector 2746J 2747J01C0A54148-12-09-7-001 or GTR1054-9NFACS1 2 Straight union 01C01A54148B00-09-7D 2 Plug SN1862-2-10VAI 2 Backplate AN515-4R10 4 Screw 01CAB211-1-22 60 ft (18 m) Cable 01CAN203-1-20B 10 ft (3 m) Cable 01CAN211-1-22 26 ft (8 m) Cable 01CAN211-1-20 3 ft (1 m) Cable 01PR0FVE02W 53 ft (16 m) CORSIL sheath 01EQTC0S20-05-079-20 9 Lug 3312CHT2 3313CHT2 3312CHT1 3311CHT2 R3311CHT1 R3312CHT2 R3313CHT2 R3313CHT1 01EQTPRL16B01 10 Splice SP2003CZ306 / SP2004CZ104 / SP2003CZ409-45 / SP2004CZ409-35 / SP2003CZ303-45 / SP2003CZ303-35 01EQTRB32-6A 10 Self-soldering sleeve (B053-70-02) 01PR0PRL05 10 Kit (B500-02-107 01EQTRB23-1R 6 Self-soldering sleeve 3312CH-T1 / 3312CH- T2 / 3313CH-T3 / R3312CH-T1 / R3312CH-T2 / R3313CH-T3 01EQTRB23-2R 1 Self-soldering sleeve R3311CHT1 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 50 / 90 DASSAULT AVIATION Proprietary Data ### Page 53 NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 01EQTSR03-20S01 20 Contact 3312CH 3313CH R3312CH R3313CH 01C0A54148FC20 12 Blanking pin 01C0K308-22DS01 6 Contact 2746J 2747J01C0A54148FC22 6 Blanking pin 01EQTPRL08B02 8 Splice SP3311CH-3 / SP3312CH-A2 / SP3312CH-A3 / SPR3311CH-3 / SPR3312CH-A2 / SPR3312CH-A3 01EQTPRL08B01 2 Splice SP3313CH-A3 / SPR3313CH-A3 /// 18 FBW identification sleeve (01PR0TMS1-4W) //// 18 FBW identification sleeve (01PR0TMS1-4W) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 51 / 90 DASSAULT AVIATION Proprietary Data ### Page 54 NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 2316JE / SP3311CH-3 2 Wire identification sleeve (01PR0TMS1-8GR) ONLY FOR SECTION 7X-211-1 SP2003CZ306 / SP3312CH-A3 3311CH-4 / SP3313CH-A3 SP3312CH-A3 / SP3313CH-A3 SP3212CH-A3 / 3312CH-T3 3311CH-T1 / AA 2316JE / SP3312CH-X1 3312CH-A1 / 2747J-2 SP3313CH-A 3/ 2747J-1 SP3312CH-A2 / 3313CH-A2 SP3312CH-X1 / 3313CH-X1 3313CH-A1 / 2747J-3 3313CH-X2 / 2318JE-A 3312CH-X2 / 2319JE-A SP2003CZ303-45 / 2318JE-K SP2003CZ303-35 / 2319JE-K 2319JE-K / 3312CH-T2 2318JE-K / 3313CH-T2 3312CH-T1 / SP3312CH-A2 2416JE /SPR3311CH-3 SPR3312CH-A3 / SPR3313CH-A3 SPR3313CH-A3 / R3313CHT1 SP2004CZ104 / SPR3313CH-A3 R3311CH-4 / SPR3312CH-A3 2416JE / SPR3312CH-X1 R3312CH-A1 / 2746J-2 SPR3312CH-A 3/ 2746J-1 SPR3312CH-A2 / R3313CH-A2 SPR3312CH-X1 / R3313CH-X1 R3313CH-A1 / 2746J-3 R3313CH-X2 / 2418JE-A R3312CH-X2 / 2419JE-A SP2004CZ409-45 / 2418JE-K SP2004CZ409-35 / 2419JE-K FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 52 / 90 DASSAULT AVIATION Proprietary Data ### Page 55 NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 2419JE-K / R3312CH-T2 2 Wire identification sleeve (01PR0TMS1-8GR) ONLY FOR SECTION 7X-211-1 2418JE-K / R3313CH-T2 R3312CH-T1 / SPR3312CH-A2 R3311CH-T1 / R3311CH-B SP3311CH-3 1 Splice identification sleeve (01PR0TMS3-32GR) ONLY FOR SECTION 7X-211-1 SP2003CZ306 SP3313CH-A3 SP3311CH-4 SP3312CH-X1 SP3312CH-A3 SP3312CH-A2 SP2003CZ303-45 SP2003CZ303-35 SPR3311CH-3 SP2004CZ104 SPR3313CH-A3 SPR3312CH-X1 SPR3312CH-A3 SPR3312CH-A2 SP2004CZ409-45 SP2004CZ409-35 2318JE 1 Identification diode(01PR0RNF1-2GR) 2319JE 2316JE 2418JE 2419JE 2416JE FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 53 / 90 DASSAULT AVIATION Proprietary Data ### Page 56 NEW P/N QTY KEY WORD INSTRUCTIONS DISPOSITIONS 3312CH 2 ”STERLING” E19 Green label 3313CH 2 R3312CH 2 R3313CH 2 2746J 2 2747J 2 2318JE 1 2319JE 1 2316JE 1 ”STERLING” E19 Green label 2418JE 1 2419JE 1 2416JE 1 Table 6: ELECTRICAL KIT Kit P/N SBF7X0211C NEW P/N QTY KEY WORD F7XC531811115A1 2 Instrument panel placard Kit SBF7X0211D NEW P/N Q T Y KEY WORD ITEM FIG F7XC535141129 1 LH relay support 40 14 F7XC535141128 1 RH relay support 41 15 22208BC050012LE 2 Srew 2 13, 16 23111BC050LE 2 Washer 3 13, 16 5SR2009M 2 Anchor nut 4 13, 16 35067-2405ID 4 Rivet for anchor nut Table 7: MECHANICAL KIT FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 54 / 90 DASSAULT AVIATION Proprietary Data ### Page 57 NEW P/N Q T Y KEY WORD INSTRUCTIONS DISPOSITION 01APP3203-2RT05M03D3-05B or 315203DPMQ28 or M210D4N006 or M210D4NC-ER 2 Relay 3314CH R3314CH 01APP3205-028-2-1L03 or S210A1A1 or S315E01A25001 or 01APP3205-028-2-1-03 2 Support 3314CH R3314CH 01C0A54148FC20 8 Dummy contact 3314CH R3314CH 01EQTSR03-20S01 8 Contact 3314CH R3314CH 01EQTC0S20-05-079-20 2 Lug 3314CH-T2 R3314CH-T2 1001FW2A-20 / SP5000PM3A 2 Wire identification sleeve(01PR0TMS1-8GR)1001FW2A-20 / 1001FW-T2SP2003CZ306 / 3314CH-X2 3314CH-A2 / 3314CH-T2 SP3312CH-X1 / 3314CH-X1 2 Wire identification sleeve(01PR0TMS1-8GR) 3314CH-A1 / SP3312CH-A3 1001FW2A-17 / SP5000PM2A 1001FW2A-17 / 1001FW-T1 R3314CH-X1 / SPR3312CH-X1 SP2004CZ104 / R3314CH-T1 R3314CH-A2 / R3314CH-T2 R3314CH-A1 / SPR3313CH-A3 01EQTPRL08B02 4 Splice SP3312CH-X1 / SP3312CH-A3 / SPR3312CH-X1 / SPR3312CH-A3 FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 55 / 90 DASSAULT AVIATION Proprietary Data ### Page 58 NEW P/N Q T Y KEY WORD INSTRUCTIONS DISPOSITION R3314CH 1 “STERLING “ E19 Green label 3314CH 1 Table 8: ELECTRICAL KIT KIT SBF7X0211E NOTE 1: • SECTION 7X-211-1: one tool is needed • SECTIONS 7X-211-2 AND 7X-211-3: two tools are needed NOTE 2: break-out box (F7XC202059530) can be used as an equivalent to tool P/N F7X0211E. NEW P/N Q T Y KEY WORD F7X0211E 1 Tool for FCS connector tests KIT SBF7X0211F NEW P/N Q T Y KEY WORD 28524044 1 Frame for emergency panel switch C. RENTAL TOOLS FOR UPLOAD OF MAIC MODULES NEW P/N QTY DESIGNATION MEM405-01 including: • MGB660-01 • MEM40501-01 • MEM40505-01 • MEM40506-01 • MEM40504-01 • MEM40508-01 1 • 1 • 1 • 1 • 1 • 1 • 1 FCS UPLOADER including: • Extraction tool • Electronic unit • LHF interface module • RHF interface module • Hand-held scanner • Installation plug DDM001-03 including: • DDM00101-03 • DDM00102-03 1 • 1 • 1 Standard 2.1.7.2 UPLOAD SUPPORT including: • Standard 2.1.7.2 software media • FCS label paperbook MEM40507-01 1 CD installation media D. LOCAL PROCUREMENT As indicated in Consumable Products Manual (CPM): • vinyl varnish FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 56 / 90 DASSAULT AVIATION Proprietary Data ### Page 59 • leak detector • Raychem Glue (S1125KIT1) • Red binding (01FFFTF02R) • Blue binding (01FFFTF04B) • interlaying sealant • torque seal F-900 (CPS 0232150) RED • high temperature sealant (RTV106) • hardener HV998 • araldite AV138M Spare parts if necessary for FCS rack conditioning pipes: • O'ring P/N 120513 (qty max: 2) • Seal P/N W932-12F (qty max: 4) • Seal P/N W932-20F (qty max: 2) Spare part if necessary for FCS rack: • Gasket P/N T84011010501 (qty max: 4 per FCS rack) FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 57 / 90 DASSAULT AVIATION Proprietary Data ### Page 60 Figure 1: Removal / Installation of the Crew Documentation Stowage Box FALCON 7X 7X-211 June 22, 2011 ATA 27 Revision 2 Page 58 / 90 DASSAULT AVIATION Proprietary Data The text continues at https://openairdocs.org/service-documents/dassault/7x-211/file/17cb004932fb.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.