FALCON 7X

No 182-R4

JULY 18, 2013

MANDATORY

ATA 32

LANDING GEAR

MAIN LANDING GEAR LEGS

COMPLIANCE OF CADMIUM PLATING THICKNESS ON

PINS

FALCON SERVICE BULLETIN

Copyright © 2013 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
LANDING GEAR

MAIN LANDING GEAR LEGS

COMPLIANCE OF CADMIUM PLATING THICKNESS ON PINS

Initial issuance December 17, 2010

List of effective pages :

1 to 4

Revision 1 December 07, 2011

List of effective pages :

1 to 5

List of modified pages :

1

REASON:Modification of the effectivity.

The revision is not applicable to aircraft already modified per the initial issuance of

this Service Bulletin.

Revision 2 June 01, 2012

List of effective pages :

1 to 5

List of modified pages :

1

REASON:- Modification of the effectivity.

- Incorporation of SAFRAN MESSIER-DOWTY change notice No 1.

The revision is not applicable to aircraft already modified per a previous revision of

this Service Bulletin.

Revision 3 February 26, 2013

List of effective pages :

1 to 5

List of modified pages :

1, 2, 3 and 4

FALCON 7X 7X -182

ATA 32
REASON:The purpose of this revision is to complete the initial kit of spacers to cover a wider

range of pintle pin adjustment.

This revision is not applicable to aircraft already modified per a previous revision of

this Service Bulletin.

Revision 4 July 18, 2013

List of effective pages :

1 to 5

List of modified pages :

1

REASON:The purpose of this revision is to mandate the Service Bulletin to the following list of

aircraft (Service Bulletin not yet applied):

S/N 4 to 6, 9, 12, 19, 21 to 25, 29, 32, 33, 37, 39 to 42, 45, 49 to 53, 55, 56, 62, 63,

65, 67 to 69, 81, 82, 84 and 120.

FALCON 7X 7X -182

ATA 32
PAGE INTENTIONALLY LEFT BLANK

FALCON 7X 7X -182

ATA 32
LANDING GEAR

MAIN LANDING GEAR LEGS

COMPLIANCE OF CADMIUM PLATING THICKNESS ON PINS

1. PLANNING INFORMATION

A. EFFECTIVITY

This Service Bulletin is applicable to FALCON 7X aircraft with serial numbers 1 through 89, 92 through

94, 96 through 100, 105, 106, 120, 121 and 124.

B. REASON

The main landing gear legs fitted on the aircraft listed hereabove, have an insufficient cadmium plating

thickness on the following internal pins pintle pins P/N 55-2355007-01. This insufficient thickness

increases the risk of corrosion on these pins.

The MLG pintle pins are designed to shear in case of excessive load on the main landing gear, ensuring

that the landing gear collapses and prevents consequently unacceptable structural damage to the wing.

If left untreated, corrosion may reduce the maximal load these pins can bear.

The purpose of this Service Bulletin is to replace the affected pins with new ones meeting the cadmium

plating thickness requirements.

C. DESCRIPTION

The operation consists in replacing the main landing gear pintle pin and cross pin with new ones.

D. COMPLIANCE

Mandatory:

• This Service Bulletin is rendered mandatory by EASA Airworthiness Directive No. 2013-0162.

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

E. APPROVAL

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

F. LABOR

Estimated labor-hours: Refer to Service Bulletin Commercial Summary.

NOTE: These labor-hours only concern the work described in this Service Bulletin and do not include

other maintenance work 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 -182

July 18, 2013 ATA 32

Revision 4 Page 1 / 5

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 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.

Refer to paragraph “H. Tools - Cost and availability” of SAFRAN MESSIER-DOWTY Service Bulletin.

NOTE: Some tools may be rented (refer to paragraph “3. MATERIAL INFORMATION” of this Service

Bulletin).

I. WEIGHT AND BALANCE

Change in weight: None.

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

J. REFERENCES

SAFRAN MESSIER-DOWTY Service Bulletin 870-32-021 revision 1.

Aircraft Maintenance Manual:

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

K. OTHER PUBLICATIONS AFFECTED

None.

FALCON 7X 7X -182

July 18, 2013 ATA 32

Revision 4 Page 2 / 5

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).

B. PROCEDURE

(1) Perform SAFRAN MESSIER-DOWTY Service Bulletin 870-32-021 revision 1 on each main landing

gear leg.

C. 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.

FALCON 7X 7X -182

July 18, 2013 ATA 32

Revision 4 Page 3 / 5

DASSAULT AVIATION Proprietary Data
3. MATERIAL INFORMATION

A. MODIFICATION KIT

Kit P/N SBF7X0182A for one MLG leg

NEW P/N QTY KEY WORD

81-2351008-00 1 Kit

NOTE: If none of the spacers included in kit SBF7X0182A nor the original spacer can be selected as

per paragraph 2.B (1) (a6) in Messier Service Bulletin, select one spacer from the kits below:

• Kit SBF7X0182B (thin spacers kit),

• kit SBF7X0182C (thick spacers kit).

Kit P/N SBF7X0182B

NEW P/N QTY KEY WORD

81-2351024-00 1 Kit of spacers

Kit P/N SBF7X0182C

NEW P/N QTY KEY WORD

81-2351025-00 1 Kit of spacers

81-2351026-00 1 Kit of spacers

81-2351027-00 1 Kit of spacers

B. RENTAL TOOLS

NECESSARY TOOLS For LH leg For RH leg

Removal/Installation hanging tool GS47110 GS47157

• Wing door protection • GS47141 • GS47141

• Jaws assy • GS47142 • GS47158

• Hanging lever assy • GS47143 • GS47159

Protection set GS47161 GS47160

• MLG ball bearing guide • GS47144 • GS47144

• MLG front protection • GS47156 • GS47154

MLG pintle pin removal/installation tool CAT5906-1

Hoisting cable for removal/installation MEM00018-2 (Spares P/N 2RU83)

Hoisting plate assy

• Hoisting plate

GS47617

• S49875

Tool sleeve for gap adjustment S49879

FALCON 7X 7X -182

July 18, 2013 ATA 32

Revision 4 Page 4 / 5

DASSAULT AVIATION Proprietary Data
Dummy pintle pin S49880

END OF DOCUMENT

FALCON 7X 7X -182

July 18, 2013 ATA 32

Revision 4 Page 5 / 5

DASSAULT AVIATION Proprietary Data
 870-32-021

Messier-Bugatti-Dowty 

Inovel Parc S ud 

78140 Vélizy-Villacoublay 

Tél. +33 (0)1 46 29 18 00 

Fax +33 (0)1 46 29 18 01 

 

SERVICE BULLETIN 

TRANSMITTAL SHEET 

 December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 1 of 1 

Please find enclosed revision No.1 of Service Bulletin 870-32-021 

MAIN LANDING GEAR LEGS 

Compliance of Cadmium plating thickness in bores 

REASONS: 

 

Incorporation of the Change Notice N°.1 

Addition of new kits, with text modification in the § 2. 

This Service Bulletin is totally re-issued 

This revision supersedes the original issue dated of December 16, 2010 

ISSUE DATES: Composition: 

Original issue: December 16, 2010 None 

 Revision No. 1: December 21, 2012 Pages: 1 to 23, and reporting form 

 
 870-32-021

Messier-Bugatti-Dowty 

Inovel Parc S ud 

78140 Vélizy-Villacoublay 

Tél. +33 (0)1 46 29 18 00 

Fax +33 (0)1 46 29 18 01 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 1 of 23 

MAIN LANDING GEAR LEGS 

Compliance of Cadmium plating thickness in bores 

1. PLANNING INFORMATION 

A. Effectivity 

(1) Affected in-service aircraft 

Falcon 7X 

 

(2) Affected in-service and spare components. 

 MLG Aircraft structure rear hinge point 

Pintle pin 55-2355007-01 

Cross pin 55-2355039-00 

B. Reason 

(1) Cases of low Cadmium plating thickness in pintle pin and cross pin bores have been 

reported 

(2) Aim of this Inspection Service Bulletin is to replace systematically the parts 

concerned (listed in § A. (2)) 

(3) This Service Bulletin is related to a Service Bulletin DASSAULT-AVIATION 

N° FALCON 7X - 182 

C. Classification 

Recommended 

D. Description 

The accomplishment of this Inspection Service Bulletin consists in the replacement of the 

subject parts by new ones. 

E. Approval 

The technical content of this document is approved under the authority of D.O.A. 

N° EASA.21J.051. 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 

F. Manpower 

Time required for compliance with this service bulletin 

Estimated time for compliance with this Service Bulletin inspection: 

 20 hours per leg 

 Mechanics : 2 + 1 partially 

NOTE: These times are given as a guide and do not include any reconditioning or 

administrative tasks that might be necessary 

G. Material - Cost and availability 

(1) Necessary parts 

The modification kit number is to be followed by one of the code numbers below, 

according to the required composition: 

-4 New parts + modified parts + expendable parts 

(2) Kit N° 81-2351008-00 (see figures 2 and 3 for P /N’s location) 

COMPOSITION OF MODIFICATION KIT CODE

PART NUMBER NOMENCLATURE Qty

55 2355007 01 Pintle pin X

55 2355037 00 R1 Spacer (3.86 mm(0.152 in )) X

55 2355037 00 R2 Spacer (3.88 mm (0.1528 in X

55 2355037 00 R3 Spacer (3.90 mm (0.1535 in )) X

55 2355037 00 R4 Spacer (3.92 mm (0.154 in )) X

55 2355037 00 R Spacer (3.94 mm (0.155 in )) X

55 2355037 00 R Spacer (3.96 mm (0.1559 in )) X

55 2355039 00 Cross locking pin X

30 2355040 00 Greaser retention assy X

M83461 020 Seal X

M83461 132 Seal X

M83461 008 Seal X

M83461 014 Seal X

MS14145L4 Nut self locking X

MS14144L5 Nut self locking X

MS14145L6 Nut self locking X

MS24665 134 Cotter pin X

MS24665 302 Cotter pin X

MS24665 353 Cotter pin X
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 3 

NOTE: In case none spacers contained in the kit N° 81-2351008-00 neither original 

spacer, could be selected as per § 2.B (1) (a6), one spacer of the following kits 

will have to be chosen

(3) Kit N° 81-2351024-00 (see figures 2 and 3 for P /N’s location) 

COMPOSITION OF MODIFICATION KIT CODE

PART NUMBER NOMENCLATURE Qty

55 2355072 01 Spacer (3.72 mm (0.146 in )) X

55 2355072 Spacer (3.75 mm (0.1476 in X

55 2355072 Spacer (3.78 mm (0.1488 in )) X

55 2355072 Spacer (3.81 mm (0.1500 in )) X

55 2355072 Spacer (3.84 mm (0.151 in )) X

(4) Kit N° 81-2351025-00 (see figures 2 and 3 for P /N’s location) 

COMPOSITION OF MODIFICATION KIT CODE

PART NUMBER NOMENCLATURE Qty

55 2355072 10 Spacer (3.99 mm (0.157 in )) X

55 2355072 11 Spacer (4.02 mm (0.158 in X

55 2355072 12 Spacer (4.05 mm (0.159 in )) X

55 2355072 13 Spacer (4.08 mm (0.1 06 in )) X

(5) Kit N° 81-2351026-00 (see figures 2 and 3 for P /N’s location) 

COMPOSITION OF MODIFICATION KIT CODE

PART NUMBER NOMENCLATURE Qty

55 2355072 14 Spacer (4.11 mm (0.1 18 in )) X

55 2355072 15 Spacer (4.14 mm (0.163 in X

55 2355072 16 Spacer (4.17 mm (0.164 in )) X

55 2355072 17 Spacer (4.20 mm (0.165 in )) X

(6) Kit N° 81-2351027-00 (see figures 2 and 3 for P /N’s location) 

COMPOSITION OF MODIFICATION KIT CODE

PART NUMBER NOMENCLATURE Qty

55 2355072 18 Spacer (4.23 mm (0.1665 in )) X

55 2355072 19 Spacer (4.26 mm (0.1677 in X

55 2355072 20 Spacer (4.29 mm (0.1689 in )) X

55 2355072 21 Spacer (4.32 mm (0.170 in )) X

 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 4 

 (3) Price and availability 

The parts that have to be replaced are provided free of charge (FOC). 

Kits are available from DAFS and DFJ 

American Continent 

DASSAULT FALCON JET 

SPARES DISTRIBUTION CENTER 

200 RISER ROAD 

LITTLE FERRY, NJ07643 

U.S.A 

Other Continents 

DASSAULT AVIATION FALCON SPARES 

DISTRIBUTION CENTER 

BOITE POSTALE 101 

AEROPORT DU BOURGET 

93352 LE BOURGET CEDEX 

 FRANCE 

H. Tools - Cost and availability 

NECESSARY TOOLS For LH leg For RH le

Removal/Installation hanging tool GS47110 GS47157 

.Wing door protection .GS47141 .GS47141 

.Jaws assy .GS47142 .GS47158 

.Hanging lever assy .GS47143 .GS47159 

 

Protection set GS47161 GS 47160 

.MLG ball bearing guide .GS47144 .GS47144 

.MLG front protection .GS47156 .GS47154 

 

MLG pintle pin removal/installation tool CAT5906-1 

Hoisting gear for removal/installation MEM00018-1 

Hoisting cable for removal/installation MEM00018-2 

Hoisting plate assy 

.Hoisting plate 

GS47617 

S49875 

Tool sleeve for gap adjustment S49879 

Dummy pintle pin S49880 

Hydraulic jack type COLUMBUS P/N 1504-50 or 

equivalent 

Feeler gauge 

(The dimension to be measured is around 

0.028 in.) 

Local furniture 

 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 5 

I. Weight and balance 

N/A. 

J. References 

- Service Bulletin DASSAULT AVIATION N° FALCON 7X - 182 

- Aircraft Maintenance Manuals (AMM) 

AMM Task 32-44-09-900-801 - Removal/Installation of wheels 

AMM Task 27-50-00-860-801 - Extension of the flaps 

AMM Task 32-10-00-640-801 - Lubrication of the MLG and MLG doors 

AMM Task 32-40-00-870-801 - Functional test of the normal extension and retraction 

K. Other publications affected 

N/A 

 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 6 

FIGURE 1

GENERAL VIEW 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 7 

 

FIGURE 2 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 8 

 

FIGURE 3 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 9 

 

FIGURE 4 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 10 

FIGURE 5 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 11 

2. ACCOMPLISHMENT INSTRUCTIONS 

A. General 

This Service Bulletin is to be accomplished aircraft on jacks. 

B. Procedure 

This procedure is for the LH MLG leg 

Procedure for the RH MLG leg is the same, with relevant tools. 

 

CAUTION: Before accomplishment of this procedure, replace the ring of the hanging 

lever assy by the hoisting plate tool P/N GS47617 (refer to Appendix page 

18) 

(1) Tasks to be carried out on MLG leg aircraft on jacks 

(a) Disassembly 

 Jack up the aircraft in accordance with instructions given in AMM Task 

07-10-00-910-801

 Check that the aircraft systems are not energized.

 Remove wheels in accordance with AMM Task 32-44-09-900-801 

 Extend the flaps in accordance with AMM Task 27-50-00-860-801 

(a1) Disconnection of the retract actuator from the MLG leg (see figure 3) 

 

 Remove and discard cotter pin MS24665-134 

 Remove and discard self locking nut MS14145L5 

 Remove the two washers and the bolt 

 Remove the retract actuator pin from the MLG retract actuator 

(a2) Disconnection of the Door Rod from the MLG outboard door (see figure 3) 

 Remove and discard cotter MS24665-353 

Remove the nut 

Remove the washer and the threaded pin 

 Remove the bush 

 Safety the MLG shield door away from the MLG 

(a3) Disconnection of the Side Brace from the MLG leg (see figure 3) 

 

 Remove and discard cotter pin MS24665-302 

 Remove and discard self locking nut MS14145L6 

 Remove the two washers and the bolt 

 Remove the fitting pin 

 Disengage the Side brace 

Secure it in the wheel well (Refer to Appendix page 23) 

 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 12 

(a4) Installation of the tools (see Appendix at the end of this Service Bulletin) 

Remove the MLG removal access panel (550BT for LH leg/650BT for the 

RH leg) and install the wing door protector P/N GS47141 (Refer to 

Appendix page 19) 

Install the LH jaws assy P/N GS47142 (Refer to Appendix page 20) Install 

the LH hanging lever P/N GS47143 (Refer to Appendix page 19) 

Connect the LH hanging lever assy (GS47143) to the hoisting gear and the 

hoisting cable through the MLG removal access panel

Install the LH front protection P/N GS47156 (Refer to Appendix page 20) 

Install an hydraulic jack (type COLUMBUS P/N 1504-50 or equivalent) 

under the MLG trailing arm jacking dome. 

Put in contact the hydraulic jack with the MLG trailing arm jacking dome. 

(a5) Removal of the pintle pin 

Remove the MLG trunnion pin access panel (561AT for LH leg/661AT for 

RH leg) 

Install only the extractor rod of the MLG pintle pin tool CAT5906-1 (Refer to 

Appendix page 21) before removal of the cross pin in order to prevent 

movement during installation. 

CAUTION: slightly apply a load to the hoisting gear until the MLG begins to 

rotate inward to the aircraft center line no more than 2°. 

Remove and discard cotter pin MS24685-134, nut MS14145L4, 

Remove the spacer, the bonding braid and the end cap (see figure 2) 

Remove the cross pin 55-2355039-00. 

WARNING: at that time the MLG leg will shift forward. This movement can 

be prevented by an operator maintaining the leg 

Remove and discard greaser retention P/N 30-2355040-00, 

The spacer 55-2355037-00 could be stuck due to presence of grease. Use 

a thin tool to unstuck it. 

Raise the hydraulic jack under the MLG trailing arm jacking dome until free 

rotation and slight translation of the pintle pin. 

Remove the pintle pin from the MLG end fitting. 

Remove the spacer 55-2355037-00 and clean it 

Install the dummy pintle pin tool P/N S49880 to ensure the stabilization of 

the leg 

 

(a6) Gap adjustment of the new pintle pin (see figure 4 and Appendix page 20) 

The aim of this measurement is to choose the appropriate spacer using a 

comparison of adjustment gap with removed parts X and new parts Y. 

Dimension X is considered as the gap measured with the removed parts. 

Dimension Y is considered as the gap measured with new parts 

The dimension Y must be between (dimension X – 0.03mm) and 

dimension X. 

 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 13 

Put the tool sleeve on the removed pintle pin 55-2355007-01 as shown on 

figure 4. 

Install the removed spacer 55-2355037-00 against the tool sleeve as 

shown on figure 4. 

Install the removed cross pin 55-2355039-00 into the pintle pin 55-

2355007-01 as shown on figure 4 

Use feeler gauge on each side to measure the gap adjustment between 

the cross pin 55-2355039 and the spacer 

Make an average of measurements taken to obtain the dimension X 

Record dimension X (see figure 4) 

Determination of the spacer thickness according to the gap adjustment 

measured before. 

- Put the tool sleeve on the new pintle pin 55-2355007-01 from the retrofit 

kit, as shown on figure 4 

- Install the thinnest spacer from the retrofit kit 81-2351008-00 as shown on 

figure 4 

- Install the new cross pin 55-2355039-00 from the retrofit kit into the pintle 

pin 55-2355007-01 as shown on figure 4 

- Record dimension Y 

- Repeat the same dimension Y measurement with each of the spacers 

beginning from the thinner to the thicker of the retrofit kits until reaching 

dimension Y as requested above 

The removed spacer can also be used. 

- Refer to flow chart in page 14 

Example 1: X=0.86 mm and Y=0.84 mm  The spacer selected is 

appropriate 

 

Example 2: X=0.86 mm and Y=0.87 mm  The selected spacer is not 

appropriate, you have to choose a thinner spacer. 

Example 3: X=0.86 mm and Y=0.82 mm  The selected spacer is not 

appropriate, you have to choose a thicker spacer. 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 14 

The dimension Y is between 

dimension X and (dimension 

– 0.03 mm) 

Select one spacer from one 

of the retrofit kits 

The selected spacer is 

appropriate 

The dimension Y is over 

the dimension X

The dimension Y is lower than 

(dimension X – 0.03 mm)

The selected spacer is not 

appropriate; you have to choose 

a thinner spacer 

The selected spacer is not 

appropriate; you have to choose a 

thicker spacer 

NO 

NO 

YES

YES YES 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 15 

(b) Preparation before assembly 

 For cross pin 

Install and lubricate the new seal M83461-1-008 and the new packing 

preformed M83461-1-014 with synthetic grease 

Install the new seals on the new insert greaser P/N 30-2355-040-00 (see 

figure 2) 

 

 For Pintle pin 

 Remove and discard the two seals M83461-020 and the two seals 

M83461-1-132 (see figure 2) 

Lubricate two new seals M83461-1-020 and two seals M83461-1-132 with 

synthetic grease 

Install the new seals on the insert greaser P/N 55-2355036-00 (see figure 2) 

(c) Assembly 

(c1) Remove the dummy pintle pin tool P/N S49880 installed on the gear 

(c2) Installation of the spacer 55-2355037-00 

NOTE: The spacer must be installed on the landing gear side and not on 

the wing side (refer to figure 5) 

(c3) Installation of the pintle pin 

NOTE: Use the same pintle pin and cross pin as the ones used for spacer 

selection ((refer to section (a) before)) 

Apply a thin layer of synthetic grease on the outer of the insert greaser 

Insert the insert greaser in the pintle pin. 

Align the holes of the insert greaser and the holes of the pintle pin (see 

figure 2) 

Apply a thin layer of synthetic grease on the outer of the new pintle pin 

(see figure 2) 

Install the threaded end of the MLG pintle pin tool into the pintle pin (see 

Appendix page 21) 

Use the extractor rod of the MLG pintle pin tool CAT5906-1 to install the 

pintle pin through the A/C structure and into the MLG main fitting 

Push the MLG backward on its axis in order to align the borings for cross 

pin installation in the pintle pin and in the MLG main fitting (see figure 2) 

Apply a thin layer of synthetic grease on the outer of the new insert greaser 

Install the new pin greaser 

Apply a thin layer of synthetic grease on the outer of the new cross pin 

(see figure 2) 

Install the new cross pin P/N 55-2355039-00 in the main fitting through the 

aligned holes 

Install the end cap, the new bonding braid and the spacer (see figure 2) 

Install the new nut MS14145L4. Torque the nut between 2.26 and 3.40 Nm 

(20 and 30 lbf in). 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 16 

Safety the nut with a new cotter pin MS24665-134 

(d) Removal of the tools 

Lower the hydraulic jack and remove it from under the aircraft 

Remove the pintle pin installation/removal tool CAT5906-1 

Remove the cable from the hanging lever assy 

Remove the hanging lever assy (GS47143) 

Remove the jaws assy (GS47142) 

Remove the wing door protection 

CAUTION: After accomplishment of this Service Bulletin, re-install the original ring on 

the hanging lever assy instead of the hoisting plate assy P/N GS47617 (refer 

to Appendix page 18) 

(e) Check the free oscillation of the MLG on its axis under manual slight input 

(f) Re- connection of the MLG components 

(f1) Connection of the retract actuator from the MLG leg (see figure 3) 

 

 Install the retract actuator pin from the MLG retract actuator 

 Install the two washers and the bolt 

 Install a new self locking nut MS14144L5 

 Safety the nut with a new cotter pin MS24665-134 

(f2) Connection of the Side Brace from the MLG leg (see figure 3) 

 

 Engage the Side brace 

 Install the fitting pin 

 Install the two washers and the bolt 

 Install the new self locking nut MS14145L6 

 Safety the nut with a new cotter pin MS24665-302 

(f3) Connection of the Door Rod to the MLG Outboard door (see figure 3) 

 Install the bush 

Install the washer and the threaded pin 

 Install the nut 

Safety the nut with a new cotter pin MS24665-353 

(f4) Install the MLG trunnion pin access panel (561AT for LH leg/661AT for RH 

leg) 

 Install the MLG removal access panel (550BT for LH leg/650BT for the RH 

leg) 

(g) Installation of wheels 

Install the wheels in accordance with instructions given in AMM 

Task 32-44-09-900-801 

Lubrication of the MLG as per AMM Task 32-10-00-640-801 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 17 

(h) Test 

Do a slow retraction of the MLG leg as per AMM 32-31-00-860-801 

Do a normal extension of the MLG as per AMM 32-31-00-860-801 

Repeat the test with: 

Normal retraction of the MLG leg as per AMM 32-31-00-860-801 

Normal extension of the MLG as per AMM 32-31-00-860-801 

(i) Final actions 

Retract the flaps in accordance with AMM Task 27-50-00-860-801 

Jack the aircraft down to the ground in accordance with instructions given in 

AMM Task 07-10-00-910-801

Complete the REPORTING FORM (at the end of this Service Bulletin) 

Return the removed pintle pins and cross pins in Messier-Bugatti-Dowty (see 

Reporting Form at the end of this Service Bulletin)
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 18 

 HANGING LEVER ASSY BEFORE 

INSTALLATION OF THE HOISTING PLATE 

HANGING LEVER ASSY AFTER 

INSTALLATION OF THE HOISTING PLATE 
 870-32-021

 

SERVICE BULLETIN 

APPENDIX 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 19 

 

GS47141

LH and RH wing door protector 

GS47143

LH MLG hanging lever assy 
 870-32-021

 

SERVICE BULLETIN 

APPENDIX 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 20 

GS47142

LH MLG jaws assy 

GS47156

LH MLG front protection 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 21 
 870-32-021 

 

SERVICE BULLETIN 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 22 

X – 0.03mm
 870-32-021

 

SERVICE BULLETIN 

APPENDIX 

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 23 

MLG FOLDING BRACE IN SAFETY POSITION 
 870-32-021

SERVICE BULLETIN

December 16, 2010 Service Bulletin N° 870-32-021

December 21, 2012 (Rev. 1) Page 1 of 1 

REPORTING FORM 

REPLACEMENT OF THE PINS 

DATA: 

Date of the inspection: ....................... 

 A/C MSN: ................ Flight Cyles....... Flight hours........ 

 MLG Legs : LH: RH: 

 P/N ..................... .. ....................... 

S/N ..................... .. ....................... 

DESIGNATION P/N REMOVED P/N INSTALLED 

PINTLE PIN

P/N 55-2355007-01 LH RH LH RH 

S/N 

CROSS LOCKING PIN

P/N 55-2355039-00 LH RH LH RH 

S/N 

Record hereunder the Part Number of the spacer installed 

MLH L/H MLH R/H 

Spacer installed 

 

ACTION

Please return this sheet ASAP to Messier-Bugatti-Dowty Product Support Engineering. 

Sacha DEDIC: sacha.dedic@safranmbd.com

FAX : +33 1 46 29 79 48 

Laurence ASHBY: laurence.ashby@safranmbd.com 

DASSAULT AVIATION DGAC/DSC/F7X 

Corinne Exposito : 7xldginspectionreport@dassault-aviation.com 

FAX : + 33 1 47 11 89 49

Please return removed Pintle Pins P/N55-2355007-01and Cross Pins P/N 55-2355039-00 

to: Mr Alain Descums 

Messier-Bugatti-Dowty 

Usine de Bidos 

64401 OLORON Ste. MARIE 

FRANCE