FALCON 7X

No 092-R1

JANUARY 04, 2010

MANDATORY

ATA 29

HYDRAULIC POWER

PRIMARY HYDRAULIC POWER

ADDITION OF A PROTECTIVE PLATE ON THE CENTER

REAR TANK WALL

FALCON SERVICE BULLETIN

Copyright © 2009 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
HYDRAULIC POWER

PRIMARY HYDRAULIC POWER

ADDITION OF A PROTECTIVE PLATE ON THE CENTER REAR TANK WALL

Revision 1 January 04, 2010

List of effective pages:

1 to 8

REASON: This Service Bulletin becomes mandatory in accordance with an EASA Airworthiness

Directive to be released.

FALCON 7X 7X-092

ATA 29
PRIMARY HYDRAULIC POWER

ADDITION OF A PROTECTIVE PLATE ON THE CENTER REAR TANK WALL

1. PLANNING INFORMATION

A. EFFECTIVITY

This Service Bulletin is applicable to FALCON 7X aircraft which have not previously implemented

DASSAULT AVIATION modification 7X M964.

B. REASON

In the L/H main Landing Gear (L/G) well, the theoretical clearance between the hydraulic pipe coupling of

the hydraulic system A return line and the center rear tank wall may not be sufficient. In case of contact,

this could lead to damage to the rear tank wall.

The purpose of this Service Bulletin is to protect the center rear tank wall from the hydraulic coupling, by

installing a protective plate on the center rear tank wall.

C. DESCRIPTION

The operation consists in:

• checking the rear tank wall contact area for good condition (visual inspection) and, if necessary, for

cracks (Penetrant crack detection or Eddy-current inspection),

• bonding a stainless steel protective plate on the rear tank wall, behind the hydraulic pipe T-junction.

D. COMPLIANCE

Mandatory:

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

Directive.

• As prescribed by the Airworthiness Authorities of the country of registration of the aircraft.

E. APPROVAL

This Service Bulletin covers DASSAULT AVIATION modification FALCON 7X M964 which has been

approved under the authority of DOA nr. EASA.21J.051.

The technical content of this document is approved under the authority of DOA nr. EASA. 21J.051.

F. LABOR

Estimated labor-hours:

• Visual inspection and installation of protective plate: 1 hour.

• Removal/installation of hydraulic pipe and non-destructive test: 4 hours.

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:

FALCON 7X 7X-092

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DASSAULT AVIATION Proprietary Data
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 N101

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.

I. WEIGHT AND BALANCE

Change in weight: None.

Change in balance with respect to 25% MAC: None.

J. REFERENCES

Maintenance Manual:

• GENERAL MAINTENANCE AND SAFETY PRECAUTIONS (Refer to TASK 20-00-00-910-801)

• REMOVAL / INSTALLATION OF THE HYDRAULIC PIPES (Refer to TASK 20-33-00-900-801)

• PENETRANT CRACK DETECTION (Refer to TASK 20-70-00-230-801)

• EDDY-CURRENT DETECTION OF CRACKS (Refer to TASK 20-70-00-250-801)

• BLEEDING OF THE HYDRAULIC SYSTEMS (Refer to TASK 29-00-00-870-801)

• MANUAL OPENING / CLOSING OF THE MLG MAIN DOORS (Refer to TASK 32-10-00-860-801)

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DASSAULT AVIATION Proprietary Data
K. OTHER PUBLICATIONS AFFECTED

None.

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DASSAULT AVIATION Proprietary Data
2. ACCOMPLISHMENT INSTRUCTIONS

A. PRELIMINARY STEPS

(1) The aircraft must be in the maintenance configuration (Refer to TASK 20-00-00-910-801).

(2) Manually open MLG main door (733) to access the L/H main L/G well (Refer to TASK

32-10-00-860-801).

B. PROCEDURE

(1) Unscrew and remove cover (A-fig. 1).

(2) Check the rear tank wall for good condition:

(a) Perform a visual inspection of the rear tank wall, to check for absence of marks at the contact

area (behind nut (B-fig. 1)):

• If no marks are detected, go to step (3).

• If contact marks are detected:

• Remove the hydraulic pipe (C-fig. 1) (Refer to TASK 20-33-00-900-801).

• At the contact area (fig. 1, detail B), perform either an Eddy current detection of cracks

(Refer to TASK 20-70-00-250-801) or a penetrant crack detection (Refer to TASK

20-70-00-230-801).

• If crack is detected, send a report to:

• structure-repair@dassault-aviation.com (E/H),

or

• structures@falconjet.com (W/H),

to get appropriate disposition before aircraft release.

• If no cracks are detected, go to step (3).

(3) Install the protective plate on the rear tank wall (fig. 2):

(a) Clean the mounting area of:

• the rear tank wall to be protected,

• the protective plate to be bonded (1-fig. 2),

with a lint-free cloth moistened with cleaner.

(b) Bond the protective plate (1-fig. 2) to the rear tank wall, with interlaying sealant (fig. 2).

(c) Remove the excess sealant, expelled from the protective plate edges and drilled holes, with a

Plexiglas spatula.

(d) Wait for curing.

(e) Apply lubricant spray on the protective plate, for a corrosion protection.

(4) If hydraulic pipe (C-fig. 1) is removed:

(a) Install hydraulic pipe (C-fig. 1) (Refer to TASK 20-33-00-900-801).

(b) Bleed the reservoir of hydraulic system A (Refer to TASK 29-00-00-870-801).

(5) Install cover (A-fig. 1).

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DASSAULT AVIATION Proprietary Data
C. FINAL STEPS

(1) Manually close MLG main door (733) (Refer to TASK 32-10-00-860-801).

D. RECORDING

Record compliance with this Service Bulletin in the appropriate aircraft documents.

Fill out the electronic Service Bulletin reply form located in the “Service Bulletin" page on the Falcon portal.

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DASSAULT AVIATION Proprietary Data
3. MATERIAL INFORMATION

A. MODIFICATION KIT

KIT P/N SBF7X0092A

NEW P/N

Q

T

Y

KEY WORD INSTRUCTIONS

DISPOSITION

I

T

E

M

F

I

G

F7XC534545617 1 Protective plate 1 2

B. LOCAL PROCUREMENT

As indicated in Consumable Products Manual (CPM):

• cleaner.

• interlaying sealant (PS892C).

• lubricant spray.

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DASSAULT AVIATION Proprietary Data
Figure 1: Preparation Before Installation

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DASSAULT AVIATION Proprietary Data
Figure 2: Installation of Protective Plate

END OF DOCUMENT

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