OpenAirDocs.org

Dassault MSB 7X-211: Revision 2

Open the Markdown

Copy · Dassault Aviation - Falcon - Service Bulletin, SB 7X-211 R2 · 161 pages

Open PDF· 161 pages, 22.4 MB

© Dassault Aviation. Filed by the FAA in regulations.gov docket FAA-2011-0631; AD 2011-16-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

TextPartly OCR

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

Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = '17cb004932fb1e5c93527d41c815d0713f772e3d142a0c75e64e193f7c29c2c5'
  ORDER BY p.page"

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

Page 1Open in PDF

FALCON 7X No 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.

Page 2Open in PDF

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 3Open in PDF

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 4Open in PDF

• 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 5Open in PDF

• 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 6Open in PDF

• 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 7Open in PDF

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 8Open in PDF

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 9Open in PDF

• 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 10Open in PDF

(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 11Open in PDF

• 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 12Open in PDF

• 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

Pages 13–24 of 161