LANDING GEAR - REPLACEMENT OF MAIN LANDING GEAR RETRACTION ACTUATOR

1. PLANNING INFORMATION

A. SB EFFECTIVITY

Aircraft affected:

MODEL SN

EMBRAER 190 ECJ 19000109, 19000140, 19000159, 19000177, 19000203,

19000225, 19000236, and 19000243, equipped with

affected component.

Affected component:

Main landing gear (MLG) Retraction Actuator PN 190-70980-403 installed on the aircraft

or in stock.

NOTE: This effectivity list includes the aircraft originally equipped with the affected

component. Since this component is a Line Replaceable Unit (LRU), it may

be necessary to refer to the fleet maintenance control record and verify

whether the unit has been replaced with another one during routine

maintenance.

In-production effectivity:

Embraer 190 ECJ model aircraft SN 19000261, 19000278, 19000296, 19000307,

19000317 and on, have an equivalent modification factory-incorporated.

B. CONCURRENT REQUIREMENTS

None.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 1 of 85

Copyright © 2011 by Embraer S.A. All rights reserved.
C. REASON

(1) HISTORY

The retraction actuator PN 190-70980-403 failed during qualification tests as follows:

– Cap Bearing: during hydraulic fatigue test at 10,000 Flight Cycles, resulting in

hydraulic leakage;

– Rod Threaded Area: during mechanical fatigue test at 19,000 Flight Cycles,

resulting in rupture of the rod. In case of rupture, this may lead to undamped

extension, resulting in rupture also in the side stay, and loss of mechanical

confirmation of gear extension;

– Spherical Bearing: during endurance retraction/lowering test at 34,000 Flight

Cycles, resulting in similar condition to the damages found in the fleet, which

generated extra costs.

(2) OBJECTIVE

This Service Bulletin gives the instructions to replace the existing main landing gear

retraction actuators and attaching parts installed, with new ones.

(3) EXPECTED BENEFITS

To improve the reliability of the main landing gear (MLG) retraction actuator.

(4) REVISION HISTORY

None.

D. DESCRIPTION

The modification presented in this bulletin consists of replacing the left-hand (LH) and

right-hand (RH) main landing gear (MLG) retraction actuator PN 190-70980-403 with a

new and improved one PN 190-70980-405.

Liebherr-Aerospace will modify the retraction actuator PN 190-70980-403 to PN

190-70980-405 through the accomplishment of Liebherr-Aerospace SB190-70980-32-02

presented in section 4. APPENDIX 3 of this Bulletin.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 2

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
The replacement of the retraction actuator requires that the attaching point of the main

fitting also be changed.

To perform the modification described above, the operator has two alternatives as follows:

(1) A temporary modification through the accomplishment of Liebherr-Aerospace SB

32-11-190-MLG-05, presented in section 4. APPENDIX 1 of this Service Bulletin.

NOTE: The temporary modification makes on-wing accomplishment of this service

bulletin easy until the final modification is incorporated.

(2) A final modification through the accomplishment of Liebherr-Aerospace SB

32-11-190-MLG-03, attached to the section 4. APPENDIX 2 of this Service Bulletin.

For this, this Bulletin is divided into 03 PARTS, as follows:

PART I

LH MAIN LANDING GEAR RETRACTION ACTUATOR REPLACEMENT

AND MODIFICATION OF ATTACHMENT POINT - TEMPORARY

MODIFICATION

Applicable to: All SB effectivity. Refer to 1.A. SB EFFECTIVITY.

Replacement of the left-hand (LH) main landing gear (MLG) retraction actuator together

with the temporary modification through the accomplishment of Liebherr-Aerospace SB

32-11-190-MLG-05, is presented in section 4. APPENDIX 1 of this Service Bulletin.

NOTE: Part I of this Bulletin is a temporary modification to be done while Part III is

not accomplished.

To do this, it is necessary to gain access to the work area at the LH main landing gear.

PART II

RH MAIN LANDING GEAR RETRACTION ACTUATOR REPLACEMENT

AND MODIFICATION OF ATTACHMENT POINT - TEMPORARY

MODIFICATION

Applicable to: All SB effectivity. Refer to 1.A. SB EFFECTIVITY.

Replacement of the right-hand (RH) main landing gear (MLG) retraction actuator together

with the temporary modification through the accomplishment of Liebherr-Aerospace SB

32-11-190-MLG-05, is presented in section 4. APPENDIX 1 of this Service Bulletin.

NOTE: Part II of this Bulletin is temporary modification to be done while Part III is not

accomplished.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 3

Copyright © 2011 by Embraer S.A. All rights reserved.
To do this, it is necessary to gain access to the work area at the RH main landing gear.

PART III

LH AND RH MAIN LANDING GEAR RETRACTION ACTUATOR

REPLACEMENT AND MODIFICATION OF ATTACHMENT POINT - FINAL

MODIFICATION

Applicable to: All SB effectivity. Refer to 1.A. SB EFFECTIVITY.

NOTE: Replacement of the left-hand (LH) and right-hand (RH) main landing gear

(MLG) retraction actuator is necessary only if Part I and Part II have not

been accomplished.

The final modification consists of the bushing replacement described at

Liebherr-Aerospace SB 32-11-190-MLG-03, attached to section 4. APPENDIX 2 of this

Service Bulletin, is a planned maintenance action for landing gear overhaul.

To do this, it is necessary to gain access to the work area at the LH and RH main landing

gear.

NOTE: The modification presented in this bulletin does not affect the Fatigue

Critical Structure (FCS).

E. COMPLIANCE

Embraer recommends that the replacement of the actuator shall be performed by the time

the aircraft logs 12000 Flight Cycle(s).

F. APPROVAL

The technical aspects of this Service Bulletin are approved by: Agência Nacional de

Aviação Civil (ANAC).

G. ESTIMATED MANPOWER

This estimate is for direct labor only, performed by experienced personnel, and does not

include the time to plan, prepare, or inspect the work.

It is assumed that all the tools, parts, and other means are readily available when

necessary.

This estimate does not include the sealant, paint, or adhesive curing time.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 4

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
(1) APPLICABLE TO PART I

– Access opening: None.

– Inspection: None.

– Modification: 2.0 man-hours.

– Access closure: None.

– Test: None.

NOTE: Refer to paragraph 1.G. ESTIMATED MANPOWER of Liebherr-Aerospace

SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1 of this bulletin.

(2) APPLICABLE TO PART II

– Access opening: None.

– Inspection: None.

– Modification: 2.0 man-hours.

– Access closure: None.

– Test: None.

NOTE: Refer to paragraph 1.G. ESTIMATED MANPOWER of Liebherr-Aerospace

SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1 of this bulletin.

(3) APPLICABLE TO PART III

– Access opening: None.

– Inspection: None.

– Modification: 4.0 man-hours.

– Access closure: None.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 5

Copyright © 2011 by Embraer S.A. All rights reserved.
– Test: None.

NOTE: Refer to paragraph 1.G. ESTIMATED MANPOWER of Liebherr-Aerospace

SB 32-11-190-MLG-03 attached to section 4. APPENDIX 2 of this bulletin.

H. WEIGHT AND BALANCE

(1) APPLICABLE TO PART I

– Change in basic weight: + 0.805 lb (+ 0.365 kg).

– Change in basic moment: + 591.390 lb.in (+ 6.811 kg.m).

(2) APPLICABLE TO PART II

– Change in basic weight: + 0.805 lb (+ 0.365 kg).

– Change in basic moment: + 591.390 lb.in (+ 6.811 kg.m).

(3) APPLICABLE TO PART III

– Change in basic weight: + 1.610 lb (+ 0.730 kg).

– Change in basic moment: + 1182.78 lb.in (+ 13.622 kg.m).

I. SOFTWARE ACCOMPLISHMENT SUMMARY

None.

J. REFERENCES

AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD

PRACTICES-AIRFRAME.

AMM 190LIN/( ) Aircraft Maintenance Manual PART II - 32-00-00 and 32-31-01 -

LANDING GEAR.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 6

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
K. OTHER PUBLICATIONS AFFECTED

AIPC 190LIN/( ) Aircraft Illustrated Parts Catalog - 32-11-01 - LANDING GEAR.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 7

Copyright © 2011 by Embraer S.A. All rights reserved.
2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) MATERIAL AVAILABLE FROM EMBRAER

None.

(2) MATERIAL AVAILABLE FROM OTHER VENDORS

Refer to the following section and paragraphs of this bulletin:

(a) Section 2.C. MATERIAL NECESSARY FOR EACH AIRCRAFT ;

(b) Paragraph 2.A. MATERIAL – PRICE AND AVAILABILITY of Liebherr-Aerospace

SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1 ;

(c) Paragraph 2.A. MATERIAL – PRICE AND AVAILABILITY of Liebherr-Aerospace

SB 32-11-190-MLG-03 attached to section 4. APPENDIX 2 ;

(d) Paragraph 2.A. MATERIAL – PRICE AND AVAILABILITY of Liebherr-Aerospace

SB190-70980-32-02 attached to section 4. APPENDIX 3 .

B. INDUSTRY SUPPORT INFORMATION

The current main landing gear (MLG) retraction actuator PN 190-70980-403 may be

reworked into a new one PN 190-70980-405. For this, it should be sent to one of the

Liebherr-Aerospace approved repair facilities, at the address presented in paragraph 2.A.

MATERIAL - PRICE AND AVAILABILITY of Liebherr-Aerospace SB190-70980-32-02

attached to section 4. APPENDIX 3 of this bulletin.

C. MATERIAL NECESSARY FOR EACH AIRCRAFT

When applicable, the use of alternative or similar parts in place of the one specified in the

kits is allowable, provided that these alternative or similar parts are approved by Embraer

as indicated in the related Embraer Technical Publications or through a formal Embraer

communication channel.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 8

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
The necessary expendable or consumable parts presented in the AMM Tasks referred to

in this bulletin should be procured from the operator’s inventories or ordered as spares.

The complementary information, when necessary, is presented as Notes in the respective

Table.

(1) TOP KITS AND KITS

None.

(2) MATERIAL TO BE PROCURED

(a) Parts

If necessary, the parts below should be procured from the supplier, as indicated

in the associated Note.

Applicable to PART I, PART II and PART III

NEW PN DESCRIPTION OLD PN QTY DISP/

Notes

190-70980-405 Retraction Actuator 190-70980-403 02 3/ [1], [2]

1. LIEBHERR-AEROSPACE.

2. Replacement of the left-hand (LH) and right-hand (RH) main landing gear (MLG) retraction

actuator at Part III is not necessary if Part I and Part II have been accomplished.

DISPOSITION: 3 = Replace part bearing OLD PN with part bearing NEW

PN

The materials required for the accomplishment of this bulletin should be

obtained as described in the following paragraphs:

1 APPLICABLE TO PART I

Paragraph 2.D. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 32-11-190-MLG-05 attached to section 4.

APPENDIX 1 for material necessary to modify each main landing gear

(MLG) shock strut;

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 9

Copyright © 2011 by Embraer S.A. All rights reserved.
2 APPLICABLE TO PART II

Paragraph 2.D. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 32-11-190-MLG-03 attached to section 4.

APPENDIX 2 for material necessary to modify each main landing gear

(MLG) shock strut;

3 APPLICABLE TO PART III

Paragraph 2.C. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 190-70980-32-02 attached to section 4. APPENDIX

3 for material required to modify each returned main landing gear (MLG)

retraction actuator PN 190-70980-403 into new one PN 190-70980-405 by

one of the Liebherr-Aerospace approved repair facilities.

(b) Consumable Materials

Refer to the following paragraphs of this bulletin:

1 Paragraph 2.D. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 32-11-190-MLG-05 attached to section 4.

APPENDIX 1 ;

2 Paragraph 2.D. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 32-11-190-MLG-03 attached to section 4.

APPENDIX 2 ;

3 Paragraph 2.C. MATERIAL NECESSARY FOR EACH COMPONENT of

Liebherr-Aerospace SB 190-70980-32-02 attached to section 4. APPENDIX

3 .

D. MATERIAL NECESSARY FOR EACH SPARE

None.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 10

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
E. REIDENTIFIED PARTS

Refer to paragraph 2.E. REIDENTIFIED PARTS of Liebherr-Aerospace SB

32-11-190-MLG-05 attached to section 4. APPENDIX 1 and to paragraph 2.E.

REIDENTIFIED PARTS of Liebherr-Aerospace SB 32-11-190-MLG-03 attached to

section 4. APPENDIX 2 of this bulletin.

F. TOOLING - PRICE AND AVAILABILITY

Refer to paragraph 2.F. TOOLING - PRICE AND AVAILABILITY of Liebherr-Aerospace

SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1 and to paragraph 2.F.

TOOLING - PRICE AND AVAILABILITY of Liebherr-Aerospace SB 32-11-190-MLG-03

attached to section 4. APPENDIX 2 of this bulletin.

Whenever required, the necessary tooling presented in the AMM Tasks referred to in this

bulletin, should be procured from the operator’s inventories or ordered as spares.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 11

Copyright © 2011 by Embraer S.A. All rights reserved.
3. ACCOMPLISHMENT INSTRUCTIONS

NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the referenced

manuals and procedures.

2) The Manuals and other documents are referred to by acronyms or using

a simplified form. Refer to section 1.J. REFERENCES for a more

complete definition.

3) This Service Bulletin is divided into 03 PARTS. The SB PARTS are

featured to allow their independent accomplishment.

The steps below outline the general accomplishment instructions.

The detailed sequence is included in the respective figure, when necessary.

A. Temporary modification:

(1) PART I - LH MAIN LANDING GEAR RETRACTION ACTUATOR REPLACEMENT

AND MODIFICATION OF ATTACHMENT POINT - TEMPORARY MODIFICATION

(a) Make sure that the aircraft is safe for maintenance. Refer to AMM TASK

20-00-00-910-801-A/200 - Aircraft Maintenance Safety Procedures - Standard

Procedures.

(b) Make sure that the aircraft is safe for landing gear maintenance. Refer to AMM

TASK AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for

Maintenance.

(c) Remove retraction actuator PN 190-70980-403 of the left-hand (LH) main

landing gear (MLG). Refer to AMM TASK 32-31-01-000-801-A/400 -

Main-Landing-Gear Retraction Actuator - Removal.

NOTE: Send the removed main landing gear (MLG) retraction actuator to be

modified to PN 190-70980-405, according to Liebherr-Aerospace SB

190-70980-32-02 attached to section 4. APPENDIX 3 of this Bulletin.

Refer to paragraph 2.B. INDUSTRY SUPPORT INFORMATION for

contact information.

(d) Replace the sleeve and washer installed in the left-hand (LH) main landing gear

(MLG) and reidentify the MLG Shock Strut, according to the instructions

presented in paragraph 3. ACCOMPLISHMENT INSTRUCTIONS of

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 12

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
Liebherr-Aerospace SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1

of this Service Bulletin.

(e) Install new retraction actuator PN 190-70980-405 of the left-hand (LH) main

landing gear (MLG). Refer to AMM TASK 32-31-01-400-801-A/400 -

Main-Landing-Gear Retraction Actuator - Installation.

NOTE: Part I of this Bulletin is temporary modification to be done while Part III

is not accomplished.

(f) Restore the aircraft after the landing gear maintenance. Refer to AMM TASK

32-00-00-860-802-A/200 - Landing Gear - Restore after Maintenance.

(g) Restore the aircraft to normal.

(h) Enter the accomplishment of PART I of this bulletin in the applicable documents.

(2) PART II - RH MAIN LANDING GEAR RETRACTION ACTUATOR REPLACEMENT

AND MODIFICATION OF ATTACHMENT POINT - TEMPORARY MODIFICATION

(a) Make sure that the aircraft is safe for maintenance. Refer to AMM TASK

20-00-00-910-801-A/200 - Aircraft Maintenance Safety Procedures - Standard

Procedures.

(b) Make sure that the aircraft is safe for landing gear maintenance. Refer to AMM

TASK AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for

Maintenance.

(c) Remove retraction actuator PN 190-70980-403 of the right-hand (RH) main

landing gear (MLG). Refer to AMM TASK 32-31-01-000-801-A/400 -

Main-Landing-Gear Retraction Actuator - Removal.

NOTE: Send the removed main landing gear (MLG) retraction actuator to be

modified to PN 190-70980-405, according to Liebherr-Aerospace SB

190-70980-32-02 attached to section 4. APPENDIX 3 of this Bulletin.

Refer to paragraph 2.B. INDUSTRY SUPPORT INFORMATION for

contact information.

(d) Replace the sleeve and washer installed in the right-hand (RH) main landing

gear (MLG) and reidentify the MLG Shock Strut, according to the instructions

presented in paragraph 3. ACCOMPLISHMENT INSTRUCTIONS of

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 13

Copyright © 2011 by Embraer S.A. All rights reserved.
Liebherr-Aerospace SB 32-11-190-MLG-05 attached to section 4. APPENDIX 1

of this Service Bulletin.

(e) Install new retraction actuator PN 190-70980-405 of the right-hand (RH) main

landing gear (MLG). Refer to AMM TASK 32-31-01-400-801-A/400 -

Main-Landing-Gear Retraction Actuator - Installation.

NOTE: Part II of this Bulletin is temporary modification until Part III is

accomplished.

(f) Restore the aircraft after the landing gear maintenance. Refer to AMM TASK

32-00-00-860-802-A/200 - Landing Gear - Restore after Maintenance.

(g) Restore the aircraft to normal.

(h) Enter the accomplishment of PART II of this bulletin in the applicable

documents.

B. Final modification:

(1) PART III - LH AND RH MAIN LANDING GEAR RETRACTION ACTUATOR

REPLACEMENT AND MODIFICATION OF ATTACHMENT POINT - FINAL

MODIFICATION

(a) Make sure that the aircraft is safe for maintenance. Refer to AMM TASK

20-00-00-910-801-A/200 - Aircraft Maintenance Safety Procedures - Standard

Procedures.

(b) Make sure that the aircraft is safe for landing gear maintenance. Refer to AMM

TASK AMM TASK 32-00-00-860-801-A/200 - Landing Gear - Prepare for

Maintenance.

(c) Remove retraction actuator PN 190-70980-403 of the left-hand (LH) and

right-hand (RH) main landing gear (MLG). Refer to AMM TASK

32-31-01-000-801-A/400 - Main-Landing-Gear Retraction Actuator - Removal.

NOTE: Replacement of the left-hand (LH) and right-hand (RH) main landing

gear (MLG) retraction actuator is necessary only if Part I and Part II

have not been accomplished.

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 14

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
NOTE: Send the removed main landing gear (MLG) retraction actuator to be

modified to PN 190-70980-405, according to Liebherr-Aerospace SB

190-70980-32-02 attached to section 4. APPENDIX 3 of this Bulletin.

Refer to paragraph 2.B. INDUSTRY SUPPORT INFORMATION for

contact information.

(d) Replace the bushing installed in the left-hand (LH) and right-hand (RH) main

landing gear (MLG) and reidentify, according to the instructions presented in

paragraph 3. ACCOMPLISHMENT INSTRUCTIONS of Liebherr-Aerospace SB

32-11-190-MLG-03, attached to section 4. APPENDIX 2 of this bulletin. Refer to

2.B. INDUSTRY SUPPORT INFORMATION for Liebherr contact.

(e) Install new retraction actuator PN 190-70980-405 of the left-hand (LH) and

right-hand (RH) main landing gear (MLG). Refer to AMM TASK

32-31-01-400-801-A/400 - Main-Landing-Gear Retraction Actuator - Installation.

(f) Restore the aircraft after the landing gear maintenance. Refer to AMM TASK

32-00-00-860-802-A/200 - Landing Gear - Restore after Maintenance.

(g) Restore the aircraft to normal.

(h) Enter the accomplishment of PART III of this bulletin in the applicable

documents.

NOTE:

1) Please inform us by e-mail reliability.executive@embraer.com.br of

the aircraft manufacturer serial number and the SB incorporation

date, specifying the SB Part(s) incorporated or whether the whole

SB has been incorporated. This will enable Embraer to consider

your aircraft configuration when providing future modifications.

2) To formally inform that the SB has been incorporated fleet-wide or

that the SB will not be incorporated, so that Embraer can update

the affected technical publications, use the “Service Bulletin

Full-Fleet Incorporation Report” form, which is available on the

Flyembraer portal (http://www.flyembraer.com).

3) Use the attached “Service Bulletin Evaluation” form to send us your

comments regarding this SB. Your feedback will be much

appreciated as an aid for us to improve the quality of the SBs.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 15

Copyright © 2011 by Embraer S.A. All rights reserved.
4. APPENDIX 1

SB 32-11-190-MLG-05 - RETRACTION ACTUATOR ATTACHMENT POINT - TEMPORARY

MODIFICATION

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 16

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

MAIN LANDING GEAR – RETRACTION ACTUATOR ATTACHMENT

POINT - TEMPORARY MODIFICATION

1. PLANNING INFORMATION

A. EFFECTIVITY

Affected components:

Main Landing Gear (MLG) Shock Struts:

– PN 2821A0000-02 (LH) all SNs

– PN 2822A0000-02 (RH) all SNs

– PN 2821A0000-03 (LH) all SNs

– PN 2822A0000-03 (RH) all SNs

– PN 4259A0000-01 (LH) all SNs

– PN 4260A0000-01 (RH) all SNs

– PN 4573A0000-01 (LH) all SNs

– PN 4574A0000-01 (RH) all SNs

B. CONCURRENT REQUIREMENTS

None

C. REASON

The spherical bearing of the retraction actuator (RA) PN 190-70980-403 does not comply with

the required endurance life. Consequently the retraction actuator PN 190-70980-403 must be

replaced by a new one PN 190-70980-405 which has a free movable spherical ball bearing instead

of a restrained one.

The replacement of the retraction actuator requires that the RA attachment on the main fitting is

also replaced.

D. DESCRIPTION

This Service Bulletin describes the procedure to modify the RA attachment point:

– Washer and sleeve on the main fitting.

– Bolt (where applicable).

This Service Bulletin is only a temporary solution which allows operators to modify the MLG Shock

Strut on aircraft until the next occasion when the shock strut is removed from aircraft and sent to

the repair shop. If this temporary solution is used, the final solution (SB 32-11-190-MLG-03) must

be applied during the next shop visit.

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 1 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 17

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

After incorporation of the Service Bulletin the MLG Shock Struts can only be used together with

MLG Retraction Actuator PN 190-70980-405.

E. COMPLIANCE

This Service Bulletin can be performed at any time.

F. APPROVAL

Government or other regulatory agency approval of this Service Bulletin is Embraer’s responsibility.

G. MANPOWER

– Modification of the RA Attachment point: 1 manhours 1 mechanic

H. WEIGHT AND BALANCE

None

I. SOFTWARE ACCOMPLISHMENT SUMMARY

None

J. REFERENCES

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

K. PUBLICATIONS AFFECTED

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 2 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 18

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) A modification kit PN 4259A8800-01 and a bolt PN 2821-0028 will be supplied

Free-Of-Charge (FOC). The FOC conditions are limited to 12,000 Flight Cycles.

(2) The temporary modification kits and bolts ordered after the period stated above will be

available at a price of:

– US$ 533.41 (economic conditions 2010) for the kit PN 4259A8800-01

– US$ 1109.52 (economic conditions 2010) for the bolt PN 2821-0028.

(3) Replacement of the Bolt PN 2821-0028.

The bolts PN 2821-0028 installed in MLG Shock Strut before SN 208 (LH) and SN 5207 (LH)

do not have Xylan treatment. This bolts must be replaced by a new one with Xylan treatment

applied. The old bolt must be sent back to Liebherr-Aerospace.

The table below shows the serial numbers of the MLG Shock Struts for which bolts must be

replaced.

Bolt PN 2821-0028 Replacement Effectivity

Table 1

MLG SHOCK STRUT SERIAL NUMBER REPLACEMENT NECESSARY

101 to 207 (LH) x

5101 to 5206 (RH) x

(4) Make sure that orders specify:

– This Service Bulletin.

– The MSN of each aircraft affected by this Service Bulletin.

– The serial number of each MLG Shock Strut affected by this Service Bulletin.

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 3 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 19

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(5) Send purchase orders to one of the Liebherr-Aerospace facilities that follow:

(a) Europe the Middle East and Africa

Customer Service

Liebherr-Aerospace Lindenberg GmbH

Pfaenderstrasse 50-52

D-88161 Lindenberg - Germany

Phone: +49 (0)8381 46-4868

Fax: +49 (0)8381 46 4103

Mail: spares.lli@liebherr.com

(b) North America and South America

Customer Service

Liebherr- Aerospace Saline

1465 Woodland Drive Saline

Michigan 48176 – 1259 USA

Phone: +1 734 944 6378

Fax: +1 734 429 5357

(c) Oceania and Asia

Customer Service

Liebherr- Aerospace Singapore

8 Pandan Avenue

Singapore 609384 Singapore

Phone: +65 6424 7211

Fax: +65 6265 2657

(d) China

Customer Service

Liebherr-Aerospace Shanghai

88 Keyuan Road Pudong

Zhang Jiang Hi-Tech Park

201203 Shanghai P.R. China

Phone: +86 21 5027 6092

Fax: +86 21 5027 6116

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 4 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 20

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

B. INDUSTRY SUPPORT INFORMATION

Not applicable

C. MATERIAL NECESSARY FOR EACH AIRCRAFT

Refer to the associated Embraer airframe Service Bulletin.

D. MATERIAL NECESSARY FOR EACH COMPONENT

(1) MODIFICATION KIT

(a) Modification Kit PN 4259A8800-01:

Each modification kit PN 4259A8800-01 contains the parts that follow:

Kit Contents

Table 2

NEW PN DESCRITION OLD PN QTY

USED DISP

2225-0003 Sleeve 2225-0002 1 3

2225-0073 Washer NAS1149C1690R 1 3

4259-0001 Identification Plate - 1 2

DISPOSITION: 3= Replace part bearing OLD PN with part bearing NEW PN

2= Incorporate part bearing NEW PN.

(2) MATERIAL TO BE PROCURED

(a) Parts

The part below required for the accomplishment of this bulletin should be procured

from the operator’s inventories or from a local supplier.

Part to be Procured

Table 3

PN DESCRITION QTY USED

MS24665-374 Cotter-pin 1

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 5 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 21

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(b) Consumables

The materials below or equivalents required for the accomplishment of this bulletin

should be procured from the operator’s inventories or from a local supplier.

Consumables

Table 4

DESCRIPTION PRODUCT NAME SPECIFICATION QTY DISP

Cleaning Agent Lint-free Cloth DEF 1410-1

A A59323 AR 6

Cleaning Agent Turco Solv LO - AR 6

PR1826B2ALO - AR 6*

Sealant PR1826B2ALO-1/2 - AR 6*

PR1826B2ALO-1/4 - AR 6*

Tape - - AR 6

This table does not reference the consumables needed neither for the primer paint application procedure nor

for the standard procedures. For the primer paint refer to the applicable CMM. For the standard procedures

refer to these procedures.

QTY: AR= As Required.

DISPOSITION: 6= Apply as required.

*= Approved alternative.

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 6 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 22

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

E. RE-IDENTIFIED PARTS

Reidentified Parts

Table 5

DESCRITION OLD PN NEW PN Notes

Main Landing Gear

Shock Strut 2821A0000-02 - [1]

Main Landing Gear

Shock Strut 2822A0000-02 - [1]

Main Landing Gear

Shock Strut 2821A0000-03 - [1]

Main Landing Gear

Shock Strut 2822A0000-03 - [1]

Main Landing Gear

Shock Strut 4259A0000-01 - [1]

Main Landing Gear

Shock Strut 4260A0000-01 - [1]

Main Landing Gear

Shock Strut 4573A0000-01 - [1]

Main Landing Gear

Shock Strut 4574A0000-01 - [1]

Notes: [1]= A new identification plate is introduced.

F. TOOLING - PRICE AND AVALABILITY

Special tools listed below can be borrowed or purchased from one of the Liebherr-Aerospace

facilities listed in:- 2.A MATERIAL – PRICE and AVAILABILITY.

Tooling

Table 6

REFERENCE PART NUMBER DESIGNATION QTY USED

Commercially available - Polyethylene Spatula 1

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 7 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 23

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. PROCEDURE

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU USE CLEANING

AGENTS: WEAR SAFETY GOGGLES. WEAR PROTECTIVE CLOTHING. DO

NOT LET CLEANING AGENTS TOUCH YOUR SKIN EYES AND MOUTH. WORK

IN AN AREA THAT HAS A GOOD AIRFLOW. OBEY THE MANUFACTURERS

INSTRUCTIONS. GET MEDICAL AID IF IRRITATION OCCURS. CLEANING

AGENTS CAN CAUSE INJURIES.

(1) Remove the old RA attachment point, refer to Figure 1:

(a) Remove and discard the cotter-pin (1).

(b) Remove the nut (2).

(c) Remove and discard the washer (3).

(d) Remove the bolt (5). Where applicable, replace the bolt, refer to Chap 2.A. MATERIAL

- PRICE AND AVAILABILITY, Table 2.

NOTE: If you replace the bolt (5), send the old bolt (5) to one of the Liebherr-Aerospace

facilities refer to Chap 2.A. MATERIAL - PRICE AND AVAILABILITY

(e) Remove and discard the sleeve (4).

(f) Use a Polyethylene Spatula and approved Cleaning Agent to remove all sealant from

the retraction actuator attachment point.

(2) Install the new RA attachment point, refer to Figure 2:

(a) Make sure that the bolt (5) has the Xylan surface finish applied, refer to figure 2.

(b) Hold the new sleeve (4) in position and install a new or the same bolt (5), where

applicable.

(c) Install the new washer (3).

(d) Install the nut (2).

(e) Tighten the nut (2).

(f) Install a new cotter-pin (1).

(3) Change the identification information on the MLG, refer to Figure 3.

(a) Use approved Cleaning Agent to clean the applicable surface.

(b) Bend the new plate (6) to the same shape of the main fitting.

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 8 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 24

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(c) Apply a layer of approximately 0.25 mm (0.01 in.) of PR1826B2ALO to the back of

the new plate (6).

(d) Put the new plate (6) in position.

(e) Press the new plate (6) with your hands during 5 min.

NOTE: Make sure that no air bubbles are between the new plate and the main fitting.

(f) Use an Cleaning Agent and remove the unwanted sealant.

(g) Use tape to attach the new plate (6) to the main fitting until the sealant dry.

NOTE: The time of drying depends the type of sealant you use.

(h) Apply a bead of PR1826B2ALO to the joint of the new plate (6) and the main fitting.

(4) Record in the applicable document that this service bulletin has been satisfactorily completed.

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 9 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 25

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320062.CGM

A

A

1. COTTER PIN

 P/N MS24665-374

 (INSTALL NEW

 SAME P/N)

2. NUT

3. WASHER

 P/N NAS1149C169OR

 (REMOVE AND 

 DISCARD)

4. SLEEVE

 P/N 2225-0002

 (REMOVE AND

 DISCARD)

RETRACTION

ACTUATOR

ATTACHMENT

5. BOLT

 P/N 2821-0028

 (SEND TO LIEBHERR 

 WHERE APPLICABLE)

Removal of the old RA Attachment Point

FIGURE 1

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 10 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 26

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320063.CGM

A

RETRACTION

ACTUATOR

ATTACHMENT

A

1. COTTER PIN

 PN MS24665-374

 (INSTALL NEW

 SAME P/N)

2. NUT

3. WASHER

 P/N 2225-0073

 (INSTALL NEW PN)

5. BOLT

 PN 2821-0028

 (INSTALL SAME P/N)

B

XYLAN PAINT

(BLACK COLOR)

B

4. SLEEVE

 P/N 2225-0003

 (INSTALL NEW PN)

Installation of the new RA Attachment Point

FIGURE 2

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 11 of 12

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 27

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320066.CGM

XXXXXXXXX-XX

MLG SHOCK STRUT, ASSY

MIL-H-5606

D9893

P/N

S/N

DATE

AMDT.

FLUID:

INSP.

MANUFACTURED BY

LIEBHERR-AEROSPACE

Lindenberg GmbH

COOPERATION

6. Plate

 4259-00001

 (INSTALL NEW PN)

2713MOD0191

A

A

Re-Identification

FIGURE 3

Initial Issue : Sep 20/10 32-11-190-MLG-05

Revision 0 : Sep 20/10 Page 12 of 12

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 28

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
4. APPENDIX 2

SB 32-11-190-MLG-03 - RETRACTION ACTUATOR ATTACHMENT POINT - FINAL

MODIFICATION

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 29

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

MAIN LANDING GEAR – RETRACTION ACTUATOR ATTACHMENT

POINT - FINAL MODIFICATION

1. PLANNING INFORMATION

A. EFFECTIVITY

Affected components:

Main Landing Gear (MLG) Shock Struts:

– PN 2821A0000-02 (LH) all SNs

– PN 2822A0000-02 (RH) all SNs

– PN 2821A0000-03 (LH) all SNs

– PN 2822A0000-03 (RH) all SNs

– PN 4259A0000-01 (LH) all SNs

– PN 4260A0000-01 (RH) all SNs

– PN 4573A0000-01 (LH) all SNs

– PN 4574A0000-01 (RH) all SNs

B. CONCURRENT REQUIREMENTS

None

C. REASON

The spherical bearing of the retraction actuator PN 190-70980-403 does not comply with the

required fatigue life. Consequently the retraction actuator PN 190-70980-403 must be replaced

by a new one PN 190-70980-405 which has a free movable spherical ball bearing instead of a

restrained one.

The replacement of the retraction actuator requires that the bushings on the main fitting attachment

are also replaced.

D. DESCRIPTION

This Service Bulletin describes the procedure to replace the retraction actuator attachment:

– Bushings on the main fitting.

– Bolt (where applicable).

This Service Bulletin describes also the repair procedures to follow in the event that corrosion on

the retraction actuator attachment is found during accomplishment of the bulletin.

A temporary solution which allows operators to modify the retraction actuator attachment on aircraft

can be performed through the SB 32-11-190-MLG-05. This service bulletin must be applied on the

occasion of the next shop visit and at the latest during the overhaul (20.000 Flight Cycles).

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 1 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 30

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

After incorporation of the Service Bulletin the MLG Shock Struts can only be used together with

MLG Retraction Actuator PN 190-70980-405.

E. COMPLIANCE

This Service Bulletin can be performed at any time, and should be performed at the latest during

first overhaul (20,000 Flight Cycles).

F. APPROVAL

Government or other regulatory agency approval of this Service Bulletin is Embraer’s responsibility.

G. MANPOWER

– Removal of the old bushings: 0.5 manhours 1 mechanic

– Installation of the new bushings: 2 manhours 1 mechanic

H. WEIGHT AND BALANCE

None

I. SOFTWARE ACCOMPLISHMENT SUMMARY

None

J. REFERENCES

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

K. PUBLICATIONS AFFECTED

Aircraft Illustrated Part Catalogue

– AIPC 32-11-01 – Main Landing Gear Shock Strut

Aircraft Maintenance Manual

– MPP 32-31-01-04 – Main Landing Gear Retraction Actuator - Removal/Installation

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 2 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 31

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

(1) The table below shows the bushings modification kit which is applicable to the serial number

of the MLG Shock Strut.

Bushings Modification Kit Effectivity

Table 1

MLG SHOCK STRUT SERIAL

NUMBER KIT PN 4259A8100-01 KIT PN 4259A8200-01

101 to 109 (LH) x

110 (LH) x

111 to 135 (LH) x

136 (LH) x

137 to 159 (LH) x

160 (LH) x

161 to 173 (LH) x

174 (LH) x

175 to 177 (LH) x

178 (LH) x

179 to 195 (LH) x

196 (LH) x

197 to 313 (LH) x

314 (LH) x

315 to 323 (LH) x

324 (LH) x

325 to 368 (LH) x

369 (LH) x

370 to 454 (LH) x

455 (LH) x

456 and on (LH) x

5101 to 5167 (RH) x

5168 (RH) x

5169 to 5238 (RH) x

5239 (RH) x

5240 to 5248 (RH) x

5249 (RH) x

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 3 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 32

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

Bushings Modification Kit Effectivity

Table 1 (continued)

5250 to 5260 (RH) x

5261 (RH) x

5262 to 5275 (RH) x

5276 (RH) x

5277 to 5317 (RH) x

5318 (RH) x

5319 to 5473 (RH) x

5474 (RH) x

5475 and on (RH) x

(2) Replacement of the Bolt PN 2821-0028.

The bolts PN 2821-0028 installed in MLG Shock Strut before SN 208 (LH) and SN 5207 (LH)

do not have Xylan treatment. This bolts must be replaced by a new one with Xylan treatment

applied. The old bolt must be sent back to Liebherr-Aerospace.

The table below shows the serial numbers of the MLG Shock Struts for which bolts must be

replaced.

NOTE: For the MLG Shock Struts where the temporary solution SB 32-11-190-MLG-05 has

been applied, the bolts have been already replaced through this service bulletin

and do not have to be replaced again.

Bolt PN 2821-0028 Replacement Effectivity

Table 2

MLG SHOCK STRUT SERIAL NUMBER REPLACEMENT NECESSARY

101 to 207 (LH) x

5101 to 5206 (RH) x

(3) These modification kits and bolts will be supplied Free-Of-Charge (FOC). The FOC conditions

are limited to 20,000 Flight Cycles or the first overhaul (whichever comes first).

(4) The bushings modification kits and bolts ordered after the period stated above will be

available at a price of:

– US$ 876.32 (economic conditions 2010) for the kit PN 4259A8100-01

– US$ 2764.27 (economic conditions 2010) for the kit PN 4259A8200-01

– US$ 1109.52 (economic conditions 2010) for the bolt PN 2821-0028.

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 4 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 33

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(5) Make sure that orders specify:

– This Service Bulletin.

– The MSN of each aircraft affected by this Service Bulletin.

– The serial number of each MLG Shock Strut affected by this Service Bulletin.

(6) Send purchase orders to one of the Liebherr-Aerospace facilities that follow:

(a) Europe the Middle East and Africa

Customer Service

Liebherr-Aerospace Lindenberg GmbH

Pfaenderstrasse 50-52

D-88161 Lindenberg - Germany

Phone: +49 (0)8381 46-4868

Fax: +49 (0)8381 46 4103

Mail: spares.lli@liebherr.com

(b) North America and South America

Customer Service

Liebherr- Aerospace Saline

1465 Woodland Drive Saline

Michigan 48176 – 1259 USA

Phone: +1 734 944 6378

Fax: +1 734 429 5357

(c) Oceania and Asia

Customer Service

Liebherr- Aerospace Singapore

8 Pandan Avenue

Singapore 609384 Singapore

Phone: +65 6424 7211

Fax: +65 6265 2657

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 5 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 34

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(d) China

Customer Service

Liebherr-Aerospace Shanghai

88 Keyuan Road Pudong

Zhang Jiang Hi-Tech Park

201203 Shanghai P.R. China

Phone: +86 21 5027 6092

Fax: +86 21 5027 6116

B. INDUSTRY SUPPORT INFORMATION

Not applicable

C. MATERIAL NECESSARY FOR EACH AIRCRAFT

Refer to the associated Embraer airframe Service Bulletin.

D. MATERIAL NECESSARY FOR EACH COMPONENT

(1) MODIFICATION KIT

(a) Modification Kit PN 4259A8100-01:

Each modification kit PN 4259A8100-01 contains the parts that follow:

Kit Contents

Table 3

NEW PN DESCRITION OLD PN QTY

USED DISP

4259-0106 Bushing 2225-0106 1 3

4259-0107 Bushing 2225-0107 1 3

- Sleeve 2225-0002 1 5

DISPOSITION: 3= Replace part bearing OLD PN with part bearing NEW PN

5= Discard part bearing OLD PN.

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 6 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 35

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(b) Modification Kit PN 4259A8200-01:

Each modification kit PN 4259A8200-01 contains the parts that follow:

Kit Contents

Table 4

NEW PN DESCRITION OLD PN QTY

USED DISP

4259-0106FS01 Bushing 2225-0106FS01 1 3*

4259-0107FS01 Bushing 2225-0107FS01 1 3*

4259-0106FS02 Bushing 2225-0106FS02 1 3*

4259-0107FS02 Bushing 2225-0107FS02 1 3*

- Sleeve 2225-0002 1 5

DISPOSITION: 3= Replace part bearing OLD PN with part bearing NEW PN

5= Discard part bearing OLD PN.

*= Two sizes of bushings are included in this kit. The correct bushings to install

depend the ones which are already installed. Refer to 3.ACCOMPLISHMENT

INSTRUCTIONS.

(2) MATERIAL TO BE PROCURED

(a) Parts

The part below required for the accomplishment of this bulletin should be procured

from the operator’s inventories or from a local supplier.

Part to be Procured

Table 5

PN DESCRITION QTY USED

MS24665-374 Cotter-pin 1

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 7 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 36

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(b) Consumables

The materials below or equivalents required for the accomplishment of this bulletin

should be procured from the operator’s inventories or from a local supplier.

Consumables

Table 6

DESCRIPTION PRODUCT NAME SPECIFICATION QTY DISP

Cleaning Agent Lint-free Cloth DEF 1410-1

A A59323 AR 6

Abrasive Cloth Emery Cloth

Abrasive Cloth to Fed.

Spec. A-A-1048 or

P-C-451

grid No. 220

AR 6

Nitrogen Liquid - - AR 6

Cleaning Agent Turco Solv LO - AR 6

Grease - MIL-PRF-23827C Type II AR 6

PR1826B2ALO - AR 6*

Sealant PR1826B2ALO-1/2 - AR 6*

PR1826B2ALO-1/4 - AR 6*

This table does not reference the consumables needed neither for the primer paint application procedure nor

for the standard procedures. For the primer paint refer to the applicable CMM. For the standard procedures

refer to these procedures.

QTY: AR= As Required.

DISPOSITION: 6= Apply as required.

* = Approved alternative.

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 8 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 37

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

E. RE-IDENTIFIED PARTS

Reidentified Parts

Table 7

DESCRITION OLD PN NEW PN Notes

Main Landing Gear Leg 2821A0000-02 - AMDT "04"

Main Landing Gear Leg 2822A0000-02 - AMDT "04"

Main Landing Gear Leg 2821A0000-03 2821A0000-04 -

Main Landing Gear Leg 2822A0000-03 2822A0000-04 -

Main Landing Gear Leg 4259A0000-01 4259A0000-02 -

Main Landing Gear Leg 4260A0000-01 4260A0000-02 -

Main Landing Gear Leg 4573A0000-01 4573A0000-02 -

Main Landing Gear Leg 4574A0000-01 4574A0000-02 -

F. TOOLING - PRICE AND AVALABILITY

Special tools listed below can be borrowed or purchased from one of the Liebherr-Aerospace

facilities listed in:- 2.A MATERIAL – PRICE and AVAILABILITY.

Tooling

Table 8

REFERENCE PART NUMBER DESIGNATION QTY USED

Commercially available - Wrench - 30 mm (1.18 in) 2

Commercially available - Polyethylene Spatula 1

Commercially available - Wrench Type-Click arm length

>= 40cm 1

Commercially available - 3/4 in. multi-sided Socket 1

Commercially available - 7/8 in. multi-sided Socket 1

Commercially available - Ears protection 1

Commercially available - Inside Calliper for diameter 40

mm (1.5748 in) 1

- 3229A0000-01 Bushing Removal/Installation

Tool 1

- 2821A0100-03W08 Bore Reamer 1

- 2821A0100-03W01 Flange Reamer 1*

This table does not reference the specifics tools needed to perform the standard procedures. For the standard

procedures refer to these procedures.

* Optional (If a machine of the bushing flange can not be performed).

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 9 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 38

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

A. PROCEDURE

WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU USE CLEANING

AGENTS: WEAR SAFETY GOGGLES. WEAR PROTECTIVE CLOTHING. DO

NOT LET CLEANING AGENTS TOUCH YOUR SKIN EYES AND MOUTH. WORK

IN AN AREA THAT HAS A GOOD AIRFLOW. OBEY THE MANUFACTURERS

INSTRUCTIONS. GET MEDICAL AID IF IRRITATION OCCURS. CLEANING

AGENTS CAN CAUSE INJURIES.

(1) Remove the old bushings. Refer to Figure 1:

(a) Remove and discard the cotter-pin (1).

(b) Remove the nut (2).

(c) Remove the washer (3).

(d) Remove the bolt (5). Where applicable, replace the bolt, refer to Chap 2.A. MATERIAL

- PRICE AND AVAILABILITY, Table 2.

NOTE: If you replace the bolt (5) send the old bolt (5) to one of the Liebherr-Aerospace

facilities refer to Chap 2.A. MATERIAL - PRICE AND AVAILABILITY

(e) Remove and discard the sleeve (4).

(f) Use a Polyethylene Spatula and approved Cleaning Agent to remove all sealant from

the retraction actuator attachment point.

(g) Use the Bushing Removal/Installation Tool - PN 3229A0000-01 to remove the bushing

(6):

1 Install the shim (t7) between the two flanges.

2 Prepare the bolt (t1):

a Assemble the bolt (t1) with the bell (t2).

b Apply Grease (MIL-PRF-23827C Type II) on the threads of the bolt (t1).

3 Hold the extractor (t3) between the two flanges and install the bolt assembly (t1).

4 Install the spacer (t4), the washer (t11), and the nut (t6) on the bolt.

5 Tighten the nut (t6).

6 Torque the nut (t6) to remove the bushing (6).

NOTE: Use the second wrench to not let the bolt (t1) rotate.

7 Remove the nut (t6) and the washer (t11) from the bolt (t1).

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 10 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 39

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

8 Remove the spacer (t4)

9 Keep the extractor (t3) in position and remove the bolt assembly (t1) with the

bushing (6).

10 Remove the extractor (t3).

(h) Use the Bushing Removal/Installation Tool - PN 3229A0000-01 to remove the bushing

(7):

1 Make sure that the shim (t7) is installed between the two flanges.

2 Prepare the bolt (t1):

a Assemble the bolt (t1) with the washer (t5), the plastic bushing (t9) and

the spacer (t4).

b Apply Grease (MIL-PRF-23827C Type II) on the threads of the bolt (t1).

3 Install the bolt assembly (t1).

4 Install the extractor (t3), the washer (t11) and the nut (t6) on the bolt.

5 Tighten the nut (t6).

6 Torque the nut (t6) to remove the bushing (7).

NOTE: Use the second wrench to not let the bolt (t1) rotate.

7 Remove the nut (t6) and the washer (t11) from the bolt (t1).

8 Remove the extractor (t3.)

9 Keep the bushing (7) in position and remove the bolt assembly (t1).

10 Remove the bushing (7).

(i) Record the PN printed on the removed bushing (7). Refer to Table 4 and select the

correct replacement bushings from the kit.

NOTE: This step is only necessary if you use the modification kit PN 4259A8200-01.

(j) Discard the old bushings (6) and (7).

(2) Examine the condition of the retraction actuator attachment point of the main fitting:

(a) Use an Abrasive Cloth to make the surface of the bores and of the flanges smooth.

(b) Use approved Cleaning Agent to remove the sealant and to clean the surface of the

bores and of the flanges.

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SB No.: 190LIN-32-0015

PAGE: 40

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(c) Do a visual inspection for cracks:

– If you find any cracks replace the MLG Shock Strut.

(d) Do an inspection of the bores and the flanges, refer to INSPECTION OF THE BORES

AND THE FLANGES, Page 29.

WARNING: USE THE CORRECT PROTECTIVE CLOTHING WHEN YOU WORK WITH

LIQUID NITROGEN BECAUSE THE PARTS WILL BECOME VERY COLD

AND CAN BURN YOU. LIQUID NITROGEN CAN CAUSE SERIOUS INJURY

TO YOUR EYES OR SKIN.

(3) Install the new bushings. Refer to Figure 2:

(a) Refer to the Repair Page Block of the applicable CMM and apply and let dry a layer of

primer paint on each side of the flanges around the bores of the main fitting.

(b) Installation of the Bushing (8):

NOTE: The installation of the bushing must be a wet-installation. Do not let the primer

paint on the bushing dry before to install it.

1 Refer to the Repair Page Block of the applicable CMM and apply a layer of primer

paint on the external surface of the bushing (8).

2 Put the bushing (8) in a liquid nitrogen bath to decrease the temperature of the

bushing to 195 °C ( 320 °F).

CAUTION: DO NOT EXCEED A TEMPERATURE OF 190°C (374°F) WHEN

YOU INCREASE THE TEMPERATURE OF AN AREA OF THE

MAIN FITTING. A TOO HIGH TEMPERATURE CAN CAUSE A

LOSS OF TENSILE STRENGTH.

3 Use a heat gun to increase the temperature of the bore to approximately 60°C

(140°F).

4 Install the new bushing (8) and apply pressure to the bushing for 1 min.

NOTE: Use the Bushing Removal/Installation Tool - PN 3229A0000-01 if

necessary, refer to INSTALLATION OF THE BUSHINGS USING

SPECIAL TOOL, Page 25.

(c) Install the bushing (9):

1 If you can machine the bush (9) do step (d).

2 If you can not machine the bush (9) do step (e).

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Revision 0 : Sep 27/10 Page 12 of 39

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DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 41

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(d) Machine and Installation of the Bushing (9):

NOTE: The installation of the bushing must be a wet-installation. Do not let the primer

paint on the bushing dry before to install it.

CAUTION: THE SURFACE OF THE FLANGES OF THE MAIN FITTING AND

OF THE BUSHINGS ARE NOT PLANNED. MAKE SURE TO

MEASURE THE DISTANCE FROM THE CORRECT POINTS. BAD

POINTS WILL GIVE YOU BAD VALUE.

1 Measure the distance d1 between the upper point of the flange of the bushing (8)

and the opposite lower point of the flange of the retraction actuator attachment.

2 Machine the flange of the bush (9) to have a distance d2 between the two

upper points of the bushes after installation equal to between 38.15 - 38.35 mm

(1.50197- 1.50984 in).

3 Refer to the Repair Page Block of the applicable CMM and apply a layer of primer

paint on the external surface of the bushing (9).

4 Put the bushing (9) in a liquid nitrogen bath to decrease the temperature of the

bushing to 195 °C ( 320 °F).

CAUTION: DO NOT EXCEED A TEMPERATURE OF 190°C (374°F) WHEN

YOU INCREASE THE TEMPERATURE OF AN AREA OF THE

MAIN FITTING. A TOO HIGH TEMPERATURE CAN CAUSE A

LOSS OF TENSILE STRENGTH.

5 Use a heat gun to increase the temperature of the bore to approximately 60°C

(140°F).

6 Install the new bushing (9) and apply pressure to the bushing for 1 min.

NOTE: Use the Bushing Removal/Installation Tool - PN 3229A0000-01 if

necessary, refer to INSTALLATION OF THE BUSHINGS USING

SPECIAL TOOL, Page 25.

7 Measure and make sure that the value of the distance d2 between the two upper

points of the bushings is between 38.15 - 38.35 mm (1.50197- 1.50984 in).

NOTE: If the distance d2 between the two bushes is not between 38.15 - 38.35

mm (1.50197- 1.50984 in), do step 2_ again.

(e) Installation of the Bushing (9) and Reaming of its Flange:

NOTE: You must use the Flange Reamer - PN 2821A0100-03W01 to do this

procedure.

NOTE: The installation of the bushings must be a wet-installation. Do not let the

primer paint on the bushings dry before to install the bushings.

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Revision 0 : Sep 27/10 Page 13 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 42

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

1 Refer to the Repair Page Block of the applicable CMM and apply a layer of primer

paint on the external surface of the bushing (9).

2 Put the bushing (9) in a liquid nitrogen bath to decrease the temperature of the

bushing to 195 °C ( 320 °F).

CAUTION: DO NOT EXCEED A TEMPERATURE OF 190°C (374°F) WHEN

YOU INCREASE THE TEMPERATURE OF AN AREA OF THE

MAIN FITTING. A TOO HIGH TEMPERATURE CAN CAUSE A

LOSS OF TENSILE STRENGTH.

3 Use a heat gun to increase the temperature of the bore to approximately 60°C

(140°F).

4 Install the new bushing (9) and apply pressure to the bushing for 1 min.

NOTE: Use the Bushing Removal/Installation Tool - PN 3229A0000-01 if

necessary, refer to INSTALLATION OF THE BUSHINGS USING

SPECIAL TOOL, Page 25.

5 Use the Flange Reamer - PN 2821A0100-03W01 to ream the bush (9) until you

have a distance d2 between the two bushes equal to between 38.15 - 38.35 mm

(1.50197- 1.50984 in):

a Assemble the bolt (fr1) with the hand wheel (fr3) and the guide (fr5).

b Hold the reamer (fr4) between the two flanges and install the bolt (fr1)

assembly.

c Install the guide (fr2).

d Set the reamer (fr4).

e Turn the hand wheel (fr3) clockwise to apply pressure to the reamer (fr3).

NOTE: More you apply pressure to the reamer (fr4), more the thickness

removed by the reamer (fr4) is important.

f Turn the bolt (fr1) counter clockwise to ream the flange of the bush (9) until

you have a distance d2 between the two bushes equal to between 38.15 -

38.35 mm (1.50197- 1.50984 in).

NOTE: Do step (e) when the pressure to the reamer is not sufficient.

g Release the reamer (fr4).

h Remove the guide (fr2).

i Hold the reamer (fr4) between the two flanges and remove the bolt (fr1)

with the hand wheel (fr3) and the guide (fr2).

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SB No.: 190LIN-32-0015

PAGE: 43

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

j Remove the reamer (fr4).

k Use an Abrasive Cloth to make the edges of the bush (9) smooth.

WARNING: USE EAR PROTECTION DURING ALL THE PROCEDURE. LOUD

NOISES CAN CAUSE INJURY TO YOUR EARS.

CAUTION: DO NOT TURN THE REAMER IN A COUNTERCLOCKWISE

DIRECTION EVEN TO REMOVE THE REAMER. YOU CAN DAMAGE

THE BLADES OF THE REAMER.

CAUTION: DO NOT USE A POWER DRILL. THE SPEED OF THIS TYPE OF

MACHINE IS TOO HIGH.

(f) Use the Bore Reamer PN 2821A0100-03W08 to adjust the inner diameter of the

bushings:

1 Engage the Bore Reamer (br1) in the holes of the bushings.

2 Attach the type-click or the pneumatic wrench to the Bore Reamer (br1).

CAUTION: THE REAMER MUST BE INSERTED TO THE END OF ITS

BLADES.

3 Turn the Bore Reamer (br1) clockwise applying a transversal pressure to ream

the holes of the bushings.

NOTE: Regularly pull backwards the Bore Reamer (br1) to remove the chips of

metal to make easier the reaming procedure.

4 Turn clockwise and pull the Bore Reamer (br1) to remove it.

5 Use approved Cleaning Agent to clean the bores and the flanges surfaces from

chips of metal.

(g) Apply a bead of sealant PR1826B2ALO around the joint of the bushings and the main

fitting.

(h) Make sure that the bolt (5) has the Xylan surface finish applied, refer to figure 2.

(i) Install a new or the same bolt (5) where applicable.

(j) Install the washer (3).

(k) Install the nut (2).

(l) Tighten the nut (2).

(m) Install a new cotter-pin (1).

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Revision 0 : Sep 27/10 Page 15 of 39

SERVICE BULLETIN

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PAGE: 44

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(4) Change the identification information on the MLG identification plate. See Figure 3.

(5) Record in the applicable document that this service bulletin has been satisfactorily completed.

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 16 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 45

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320041.CGM

A

A

1. COTTER PIN

P/N MS24665-374

REMOVE AND DISCARD

2. NUT

P/N MS14145-16

REMOVE

3. WASHER

 P/N NAS1149C169OR

 REMOVE

4. SLEEVE

 P/N 2225-0002

 REMOVE AND

 DISCARD

6. BUSH

 P/N 2225-0107

 REMOVE AND

 DISCARD

RETRACTION

ACTUATOR

ATTACHMENT

7. BUSH

 P/N 2225-0106

 REMOVE AND

 DISCARD

5. BOLT

P/N 2821-0028

REMOVE AND

IF APPLICABLE

SEND TO LIEBHERR

PRE-MOD

Removal of the old Bushings

(Sheet 1 of 3)

FIGURE 1

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Revision 0 : Sep 27/10 Page 17 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 46

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320058.CGM

BUSH (6.) TO REMOVE

ANTI-ROTATION PIN

t11

BUSH (6.) TO BE REMOVED

t2

t7

ANTI-ROTATION PIN

t4

t3

t6

t1

t2

t3

t4

t6

t7

t11

t1

A

B1-B1

B1

B1

REMOVAL OF BUSHES

Removal of the old Bushings

Removal of the Bushing - Anti-rotation Pin Opposite Side (Sheet 2 of 3)

FIGURE 1

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 18 of 39

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DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 47

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320059.CGM

BUSH (7.) TO BE REMOVED

t4 t3

t5

t9

t7

ANTI-ROTATION PIN

BUSH (6.) TO REMOVE

ANTI-ROTATION PIN

t3

t4

t5

t6

t7

t9

t11

t1 t6

t11

A2

B2-B2

B2

B2

t1

REMOVAL OF BUSHES

Removal of the old Bushings

Removal of the Bushing - Anti-rotation Pin Side (Sheet 3 of 3)

FIGURE 1

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Revision 0 : Sep 27/10 Page 19 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 48

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320042.CGM

A

A

1. COTTER PIN

 PN MS24665-374

 INSTALL NEW

 SAME P/N

2. NUT

 PN MS14145-16

 RE-INSTALL

3. WASHER

 PN NAS1149C169OR

 RE-INSTALL

5. BOLT

 PN 2821-0028

 INSTALL SAME P/N

9. BUSH

 INSTALL NEW

 PN 4259-0107

8. BUSH

 INSTALL NEW

 PN 4259-0106

B

XYLAN PAINT

(BLACK COLOR)

B

RETRACTION

ACTUATOR

ATTACHMENT

D

C

C

Installation of the new Bushings (Sheet 1 of 3)

FIGURE 2

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Revision 0 : Sep 27/10 Page 20 of 39

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DATE: 10/Feb/2011

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SB No.: 190LIN-32-0015

PAGE: 49

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

C-C

BUSH (8.)

d1

BUSH (9.) TO REAM

OR TO MACHINE

CLEARANCE BETWEEN THE TWO BUSHES

FOR INSTALLATION

MEASURE

FROM THIS

POINT

ANTI-ROTATION

PIN

38.15 mm (1.50197 in.) < d2 < 38.35 mm (1.50984 in.)

LB190SB320044.CGM

BUSH (9.)

REAMING OF THE FLANGE 

(IF THE FLANGE CAN NOT BE REWORKED)

fr1

fr2

fr3 fr5 fr4

fr1

fr2

fr5

fr3

fr4

BUSH (9.) TO REAM

E

E

E-E

D

Clearance and Reaming of the Bushing Flange (Sheet 2 of 3)

FIGURE 2

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Revision 0 : Sep 27/10 Page 21 of 39

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SB No.: 190LIN-32-0015

PAGE: 50

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320057.CGM

END OF BLADES

REAMER (br1)

2821A0100-03W08

SOCKET 7/8"

REAMING OF THE BORES

BUSH (9.) BUSH (8.)

ANTIROTATION

PIN

Reaming of the Bores (Sheet 3 of 3)

FIGURE 2

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Revision 0 : Sep 27/10 Page 22 of 39

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DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 51

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320043.CGM

A

XXXXXXXXX-XX

MLG SHOCK STRUT, ASSY

MIL-H-5606

D9893

P/N

S/N

DATE

AMDT.

FLUID:

INSP.

MANUFACTURED BY

LIEBHERR-AEROSPACE

Lindenberg GmbH

COOPERATION

STAMP 04 HERE A

XXXXXXXXX-XX

MLG SHOCK STRUT, ASSY

MIL-H-5606

D9893

P/N

S/N

DATE

AMDT.

FLUID:

INSP.

MANUFACTURED BY

LIEBHERR-AEROSPACE

Lindenberg GmbH

COOPERATION

XXXXXXXXX-XX

MLG SHOCK STRUT, ASSY

MIL-H-5606

D9893

P/N

S/N

DATE

AMDT.

FLUID:

INSP.

MANUFACTURED BY

LIEBHERR-AEROSPACE

Lindenberg GmbH

COOPERATION

FOR PN 4259A0000-01

 4260A0000-01

 4573A0000-01

 4574A0000-01

A CROSS OUT "01"

AND WRITE "02"

FOR PN 2821A0000-02

 2822A0000-02

A

FOR PN 2821A0000-03

 2822A0000-03

CROSS OUT "01"

AND WRITE "04"

Identification

FIGURE 3

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SERVICE BULLETIN

This page intentionally left blank.

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SB No.: 190LIN-32-0015

PAGE: 53

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

INSTALLATION OF THE BUSHINGS USING SPECIAL TOOL

1. GENERAL

This part describes the procedure to install the new bushings using the Bushing Removal/Installation

Tool - PN 3229A0000-01, if an installation by hand is not possible.

A. PROCEDURE

(1) Installation of the Bushing (8), refer to Figure 4, Sheet 1:

NOTE: The installation of the bushing must be a wet-installation. Do not let the primer paint

on the bushing dry before to install it.

(a) Make sure that the shim (t7) is installed between the two flanges.

(b) Prepare the bolt (t1):

1 Assemble the bolt (t1) with a washer (t5) and the plastic washer (t8).

2 Apply Grease (MIL-PRF-23827C Type II) on the threads of the bolt (t1).

(c) Refer to the Repair Page Block of the applicable CMM and apply a layer of primer paint

on the external surface of the applicable bushing.

(d) Put the applicable bushing in a liquid nitrogen bath to decrease the temperature of the

applicable bushing to 195 °C ( 320 °F).

(e) Install the plastic bushing (t9).

(f) Hold the applicable bushing with the plastic bushing (t10) and a washer (t5) in position,

and install the bolt assembly (t1).

(g) Install the spacer (t4), the washer (t11), and the nut (t6) on the bolt (t1).

(h) Tighten the nut (6).

(i) Torque the nut (t6) to install the applicable bushing and keep the pressure to the

bushing for 1 min.

NOTE: Use the second wrench to not let the bolt (t1) rotate.

(j) Remove the nut (t6) and the washer (t11) from the bolt (t1).

(k) Remove the spacer (t4)

(l) Keep the washer (t5) in position and remove the bolt assembly (t1).

(m) Remove the washer (t5).

(n) Remove the plastic bushing (t10).

INSTALLATION OF THE BUSHINGS USING SPECIAL TOOL

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Revision 0 : Sep 27/10 Page 25 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 54

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(2) Installation of the Bushing (9), refer to Figure 4, Sheet 2:

NOTE: The installation of the bushing must be a wet-installation. Do not let the primer paint

on the bushing dry before to install it.

(a) Make sure that the shim (t7) is installed between the two flanges.

(b) Prepare the bolt (t1):

1 Assemble the bolt (t1) with a washer (t5) and the plastic washer (t8).

2 Apply Grease (MIL-PRF-23827C Type II) on the threads of the bolt (t1).

(c) Refer to the Repair Page Block of the applicable CMM and apply a layer of primer paint

on the external surface of the applicable bushing.

(d) Put the applicable bushing in a liquid nitrogen bath to decrease the temperature of the

applicable bushing to 195 °C ( 320 °F).

(e) Hold the applicable bushing with the plastic bushing (t10) and a washer (t5) in position

and install the bolt assembly (t1).

(f) Install the spacer (t4) the washer (t11) and the nut (t6) on the bolt (t1).

(g) Tighten the nut (t6).

(h) Torque the nut (t6) to install the applicable bushing and keep the pressure to the

bushing for 1 min.

NOTE: Use the second wrench to not let the bolt (t1) rotate.

(i) Remove the nut (t6) and the washer (t11) from the bolt (t1).

(j) Remove the spacer (t4)

(k) Keep the washer (t5) in position and remove the bolt assembly (t1).

(l) Remove the washer (t5).

(m) Remove the plastic bushing (t10).

INSTALLATION OF THE BUSHINGS USING SPECIAL TOOL

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DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 55

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320060.CGM

BUSH(8.) TO INSTALL

t7

t8

BUSH (8.) TO BE INSTALLED

t4

t9 t5

t1

t5

t10

ANTI-ROTATION PIN

BUSH TO INSTALL

ANTI-ROTATION PIN

t1

t4

t5

t6

t7

t8

t9

t10

t5

t11

t11 t6

30mm (1.18in.)WRENCH

30mm (1.18in.)

WRENCH

Installation of the Bushings

Installation of the Bushing - Anti-rotation Pin Side (Sheet 01 of 2)

FIGURE 4

INSTALLATION OF THE BUSHINGS USING SPECIAL TOOL

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Revision 0 : Sep 27/10 Page 27 of 39

SERVICE BULLETIN

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REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LB190SB320061.CGM

t4

BUSH (9.) TO BE INSTALLED

t10

t5

t8

t5

ANTI-ROTATION

PIN

t1

t5

t10

t5

BUSH (9.) TO INSTALL

t8

t7

t4

t11

t6

BUSH TO INSTALL

ANTI-ROTATION PIN

t1 t11

t6

30mm (1.18in.)WRENCH

30mm (1.18in.)

WRENCH

t7

Installation of the Bushings

Installation of the Bushing - Anti-rotation Pin Opposite Side (Sheet 02 of 2)

FIGURE 4

INSTALLATION OF THE BUSHINGS USING SPECIAL TOOL

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 28 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 57

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

INSPECTION OF THE BORES AND THE FLANGES

1. GENERAL

This part describes the inspection procedure of the bores and the flanges before to install the new

bushings.

A. MANPOWER

– Inspection: 1 manhours 1 mechanic

B. REFERENCES

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

Standard Procedures:

– MIL-STD-865D - Selective Brush Plating Electro-Deposition

– MIL-R-81841 - Rotary Flap Peening of Metal Parts

– MIL-STD-1949 - Inspection Magnetic Particle

– ASTM-E-1417 - Inspection Liquid Penetrant

– MIL-STD-867 - Temper Etch Inspection

– ASTM-E-426-98 - Standard Practice for Electromagnetic (Eddy-Current) Examination of

Seamless and Welded Tubular Products Austenitic Stainless Steel and Similar Alloys

C. PROCEDURE

(1) Do an inspection for tolerances, corrosion and cadmium plating:

(a) Examine, measure and record the tolerances of the bores and the flanges.

NOTE: It is possible that the bores are not cylindrical. Therefore measure the

diameter of the bores at several points.

INSPECTION OF THE BORES AND THE FLANGES

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 29 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 58

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

Acceptable Bore Tolerances

Table 9

Bushings Removed Tolerances WITHOUT

Cadmium Plating

Tolerances WITH Cadmium

Plating

Thickness of

Cadmium Plating

2225-0106

2225-0107

40 - 40.035 mm

(1.5748 - 1.5761 in)

39.96 - 40.015 mm

(1.5732 - 1.5754 in)

0.01 - 0.02 mm

(0.0003937 -

0.0007874 in)

2225-0106FS01

2225-0107FS01

40.2 - 40.235 mm

(1.5826 - 1.5840 in)

40.16 - 40.215 mm

(1.5811 - 1.5832 in)

0.01 - 0.02 mm

(0.0003937 -

0.0007874 in)

2225-0106FS02

2225-0107FS02

40.4 - 40.435 mm

(1.5905 - 1.5919 in)

40.36 - 40.415 mm

(1.589 - 1.5911 in)

0.01 - 0.02 mm

(0.0003937 -

0.0007874 in)

(b) If only the conditions of the cadmium plating surface shows:

– dark areas

– damage

– a thickness not in accordance with the tolerances of the Table 9 above.

1 You must do a repair of the cadmium plating surface, refer to the standard

procedure MIL-STD-865D

(c) If the difference between the entrance value and the exit value of the diameter of the

bores exceed 0.035 mm, refer to Figure 5:

1 You must do a repair, refer to the MASTER REPAIR PROCEDURE - BORE

REPAIR, Page 37.

(d) If the tolerances of the bores are not in accordance with the tolerances of the Table 9

above you must do a repair, refer to the LOCAL REPAIR PROCEDURE, Page 31.

(e) If you find only corrosion:

1 You must do a repair, refer to the LOCAL REPAIR PROCEDURE, Page 31.

INSPECTION OF THE BORES AND THE FLANGES

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 30 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 59

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

LOCAL REPAIR PROCEDURE

1. GENERAL

This part describes the procedure to do if corrosion has been found and/or if tolerances are not in

accordance with the design specifications.

If the condition is more than the tolerance given, a master repair procedure will be necessary (Refer

to: MASTER REPAIR PROCEDURES page 37).

A. MANPOWER

– Repair: 5 manhours 1 mechanic

B. REFERENCES

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

Standard Procedures:

– MIL-STD-865D - Selective Brush Plating Electro-Deposition

– MIL-R-81841 - Rotary Flap Peening of Metal Parts

– MIL-STD-1949 - Inspection Magnetic Particle

– ASTM-E-1417 - Inspection Liquid Penetrant

– MIL-STD-867 - Temper Etch Inspection

– ASTM-E-426-98 - Standard Practice for Electromagnetic (Eddy-Current) Examination of

Seamless and Welded Tubular Products Austenitic Stainless Steel and Similar Alloys

C. CHECK THAT A LOCAL REPAIR PROCEDURE CAN BE DONE, refer to Figure 5.

(1) Corrosion Check:

NOTE: If the corrosion is more than the limits given, do the MASTER REPAIR

PROCEDURE, page 37.

– The corrosion must be points of corrosion only.

– No more than one point of corrosion on each quarter of each surface is permitted.

– The thickness of the points of corrosion must not exceed 0.2 mm.

– The shape and the dimension of the points of corrosion must be in accordance with

the Figure 5.

– For corrosion on the flanges sides besides the condition above the width of the flange

must be greater than 21.35 mm.

LOCAL REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 31 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 60

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(2) Bore Tolerance Check:

NOTE: If the value is more than the limits given, do the MASTER REPAIR PROCEDURE,

page 37.

– The difference between the entrance value and the exit value of the diameter of the

bore must not exceed 0.035 mm.

D. CORROSION REPAIR, refer to Figure 5.

(1) If the removal of the corrosion is permitted:

(a) Use an applicable tool to remove the corrosion points.

(b) Do a Temper Etch Inspection Test on the applicable areas refer to the standard

procedure MIL-STD-867.

(c) Make sure that the roughness of the applicable surface after removal of corrosion

is Ra <= 1.6.

(d) For Corrosion on a Flange Side:

1 Flap-peen the applicable surface refer to the standard procedure MIL-R-81841.

NOTE: Intensity: A 0.15 - 0.35 mm (A 0.006 - 0.0138 in).

Coverage: >100%

2 Do a repair of the cadmium plating surface refer to the standard procedure

MIL-STD-865D

(e) For Corrosion on a Bore:

1 Do a repair of the cadmium plating surface refer to the standard procedure

MIL-STD-865D

LOCAL REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 32 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 61

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

E. BORE TOLERANCES REPAIR, refer to Figure 5.

NOTE: This repair procedure explains how to adjust the dimension of the bushing related to the

dimension of the bore when the dimension of the bore is out of tolerance.

(1) Material to be procured

Send a purchase order for the parts below to one of Liebherr-Aerospace facilities refer to

Chap 2.A. MATERIAL - PRICE AND AVAILABILITY.

Repair Bushings

Table 10

PN DESCRITION QTY USED

4259-0106RS01 Bush 1

4259-0107RS01 Bush 1

(2) Procedure:

(a) Calculate the final dimension of the bushing, refer to Figure 5 Sheet 2.

(b) Machine the outer surface of the repair bushing to the correct dimension.

(c) Do an a Inspection Liquid Penetrant Test on the bushing refer to the standard

procedure ASTM-E-1417.

(d) Apply cadmium plating on the machined surface of the bushing refer to the standard

procedure MIL-STD-865D.

NOTE: The thickness of the cadmium plating must be between 0.005 - 0.010 mm

(0.00019685 - 0.000393701 in).

(e) Refer to the Accomplishment Instructions of this Service Bulletin to install the bushings.

LOCAL REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 33 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 62

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

 4mm

3mm FOR THE BORE

6mm FOR THE FLANGE

0.2mm 3mm 3mm

LB190SB320056.CGM

BORE

QUARTER

FLANGE

QUARTER

SHAPE OF A POINT

OF CORROSION

>21.35mm

D1

I D1 - D2 I < 0.035 mm

D2

I D1 - D2 I < 0.035 mm

CIRCULAR CORROSION

(MASTER REPAIR ONLY)

CORROSION ON

AN EDGE

(MASTER

REPAIR ONLY)

CORROSION POINTS

ON THE BORE

(ONLY ONE PER QUARTER

PERMITTED TO REMOVE.

IF MORE:

MASTER REPAIR ONLY)

CORROSION ON

THE FLANGE

(ONLY ONE PER QUARTER

PERMITTED TO REMOVE

IF MORE:

MASTER REPAIR ONLY)

LENGTHWISE CORROSION

(MASTER REPAIR ONLY)

Repair Procedure Possible Locally

Repair Procedure for Corrosion (Sheet 1 of 2)

FIGURE 5

LOCAL REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 34 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

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PAGE: 63

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SERVICE BULLETIN

Cd

CADMIUM PLATING

THICKNESS

CALCULATION OF THE THICKNESS

OF THE BUSH TO REMOVE

ADJUSTMENT = H7s6

d_INITIAL = 40.6 mm

D + (Cd x 2 ) + 0.043 > d_FINAL > D + (Cd x 2 ) + 0.059

Th = <(d_INITIAL - d_FINAL) /2>

EG:

D = 40.015 mm

Cd = 0.015 mm

40.015 + 0.03 + 0.043 > d_FINAL > 40.015 + 0.03 + 0.059

40.088 > d_FINAL > 40.104

(40.6 - 40.088) /2 > Th > (40.6 - 40.104) /2

0.256 > Th > 0.248

Th = (0.256 + 0.248)/2

Th = 0.252 mm

d

= SURFACE TO MACHINE

= SURFACE TO CADMIUM PLATE

REPAIR BUSH

TYPE XXX RS01

CADMIUM

PLATING

d

LB190SB320055.CGM

STEP 1

MACHINE THE BUSH

D

AFTER

CADMIUM

PLATING

FLANGE

STEP 2

APPLY CADMIUM PLATING

Repair Procedure Possible Locally

Repair for Bad Tolerances of the Bore (Sheet 2 of 2)

FIGURE 5

LOCAL REPAIR PROCEDURE

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Revision 0 : Sep 27/10 Page 35 of 39

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This page intentionally left blank.

LOCAL REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 36 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 65

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

MASTER REPAIR PROCEDURE

1. GENERAL

This part describes the repair procedures which must be done in case that a local one is not permitted.

A. MANPOWER

– Repair: 8 manhours 1 mechanic

B. REFERENCES

Component Maintenance Manual:

– CMM 32-11-14 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-15 - Main Landing Gear Shock Strut LH/RH

– CMM 32-11-19 - Main Landing Gear Shock Strut LH/RH

Standard Procedures:

– MIL-STD-865D - Selective Brush Plating Electro-Deposition

– MIL-R-81841 - Rotary Flap Peening of Metal Parts

– MIL-STD-1949 - Inspection Magnetic Particle

– MIL-STD-867 - Temper Etch Inspection

– ASTM-E-426-98 - Standard Practice for Electromagnetic (Eddy-Current) Examination of

Seamless and Welded Tubular Products Austenitic Stainless Steel and Similar Alloys

C. BORE REPAIR

(1) Parts to be procured

Send a purchase for the applicable parts below to one of Liebherr-Aerospace facilities refer

to Chap 2.A. MATERIAL - PRICE AND AVAILABILITY.

Repair Bushings

Table 11

NEW PN DESCRITION OLD PN QTY

USED DISP

4259-0106FS01 Bush 2225-0106 1 3

4259-0107FS01 Bush 2225-0107 1 3

4259-0106FS02 Bush 2225-0106FS01 1 3

4259-0107FS02 Bush 2225-0107FS01 1 3

4259-0106RS01 Bush 2225-0106FS02 1 3

4259-0107RS01 Bush 2225-0107FS02 1 3

DISPOSITION: 3= Replace part bearing OLD PN with part bearing NEW PN.

MASTER REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 37 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 66

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

(2) Procedure:

CAUTION: DO NOT EXCEED A BORE OF 41.525 MM WHEN YOU MACHINE

THE BORES OF THE RETRACTION ACTUATOR ATTACHMENT. A

DIMENSION OVER 41.525 MM WILL CAUSE A LOSS OF TENSILE

STRENGTH.

(a) Machine the bore to the limits of the next repair step:

– If the standard bushings were installed machine the bore to between 40.2 - 40.225

mm (1.5826 - 1.5836 in).

– If the bushings FS01 were installed machine the bore to between 40.4 - 40.425

mm (1.5905 - 1.5915 in).

– If the bushings FS02 were installed machine the bore to between 40.6 - 40.625

mm (1.5984 - 1.5994 in).

NOTE: If the bushings FS02 were installed a machining of the bushings

4259-0106RS01 and 4259-0106RS01 is necessary refer to the LOCAL

REPAIR PROCEDURE - BORE TOLERANCES REPAIR, page 31.

(b) Make sure that the roughness of the applicable surface after machining is Ra <= 1.6.

(c) Do Non Destructive Tests (NDT) on the bore:

1 If an applicable Standard Practice for Electromagnetic (Eddy-Current)

Examination of Seamless and Welded Tubular Products Austenitic Stainless

Steel and Similar Alloys installation is available do an Eddy Current Test on the

bore refer to the standard procedure ASTM-E-426-98.

2 If an applicable Standard Practice for Electromagnetic (Eddy-Current)

Examination of Seamless and Welded Tubular Products Austenitic Stainless

Steel and Similar Alloys installation is NOT available do:

– An Inspection Magnetic Particle Test on the bore refer to the standard

procedure MIL-STD-1949.

– A Temper Etch Inspection Test on the bore refer to the standard procedure

MIL-STD-867.

(d) Apply cadmium plating on the surface of the bore refer to the standard procedure

MIL-STD-865D.

NOTE: The thickness of the cadmium plating must be between 0.01 - 0.020 mm

(0.0003937 - 0.0007874 in).

(e) Refer to the Accomplishment Instructions of this Service Bulletin to install the bushings.

MASTER REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 38 of 39

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 67

Copyright © 2011 by Embraer S.A. All rights reserved.
SERVICE BULLETIN

D. FLANGE REPAIR

CAUTION: THE THICKNESS OF THE A FLANGE MUST NEVER BE LESS THAN 21.35

MM. A THICKNESS LESS WILL CAUSE A LOSS OF TENSILE STRENGTH.

MAKE SURE THAT THE THICKNESS OF THE A FLANGE WILL BE MORE

THAN THIS VALUE AFTER MACHINING.

CAUTION: DO NOT EXCEED A DEPTH OF 0.5 MM WHEN YOU MACHINE A FLANGE

OF THE RETRACTION ACTUATOR. A DEPTH MORE THAN 0.5 MM WILL

CAUSE A LOSS OF TENSILE STRENGTH.

(1) Machine the flange over to the thickness of the corrosion into the limit of 0.5 mm.

(2) Do Non Destructive Tests (NDT) on the bore:

(a) If an applicable Standard Practice for Electromagnetic (Eddy-Current) Examination of

Seamless and Welded Tubular Products Austenitic Stainless Steel and Similar Alloys

installation is available do an Eddy Current Test on the flange refer to the standard

procedure ASTM-E-426-98.

(b) If an applicable Standard Practice for Electromagnetic (Eddy-Current) Examination of

Seamless and Welded Tubular Products Austenitic Stainless Steel and Similar Alloys

installation is NOT available do:

– An Inspection Magnetic Particle Test on the flange refer to the standard procedure

MIL-STD-1949.

– A Temper Etch Inspection Test on the flange refer to the standard procedure

MIL-STD-867.

(3) Flap-peen the flange, refer to the standard procedure MIL-R-81841.

NOTE: Intensity: A 0.15 - 0.35 mm (A 0.006 - 0.0138 in).

Coverage: >100%

(4) Make sure that the roughness of the applicable surface after machining is Ra <= 1.6.

(5) Apply cadmium plating on the applicable surface refer to the standard procedure

MIL-STD-865D.

NOTE: The thickness of the cadmium plating must be between 0.01 - 0.020 mm (0.0003937

- 0.0007874 in).

MASTER REPAIR PROCEDURE

Initial Issue : Sep 27/10 32-11-190-MLG-03

Revision 0 : Sep 27/10 Page 39 of 39

SERVICE BULLETIN

SB No.: 190LIN-32-0015

PAGE: 68

DATE: 10/Feb/2011

REVISION No.:

Copyright © 2011 by Embraer S.A. All rights reserved.
4. APPENDIX 3

SB190-70980-32-02 - MODIFICATION OF MLG RETRACTION ACTUATOR FROM P/N

190-70980-403 TO PN 190-70980-405

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 69

Copyright © 2011 by Embraer S.A. All rights reserved.
 

 

 

 

 SERVICE BULLETIN

DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 1 of 16 

LANDING GEAR - MODIFICATION OF MLG RETRACTION ACTUATOR 

FROM P/N 190-70980-403 TO PN 190-70980-405 

 

1. PLANNING INFORMATION 

A. SB EFFECTIVITY 

Affected Component: 

MLG Retraction Actuator P/N 190-70980-403 all serial numbers. 

B. CONCURRENT REQUIREMENTS 

Not applicable. 

C. REASON 

During the Qualification Tests Campaign, damages on the cylinder, rod eye end 

housing and on the anti-rotation of cylinder were found. After analyses, it was 

verified that these damages occurred due to fretting phenomenon and low fatigue 

capabilities of the actuator parts. 

In order to avoid these damages, a new treatment with improved protective 

material was qualified and parts were reinforced. The existing MLG Retraction 

Actuators must be reworked to replace the spherical bearings and apply the new 

treatment. 

D. DESCRIPTION 

This Service Bulletin provides instructions for the modification of the MLG 

Retraction Actuator from P/N 190-70980-403 to P/N 190-70980-405. 

SERVICE BULLETIN

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 2 of 16 

E. COMPLIANCE (LIMITATION) 

(1) TIME FOR ACCOMPLISHMENT 

Refer to the compliance of the EMBRAER airframe SB. 

F. APPROVAL 

Government or other regulatory agency approval of this service bulletin is under 

Embraer’s responsibility. 

G. ESTIMATED MANPOWER 

- Disassembly: 1,0 man-hour. 

- Modification: 6,0 man-hour. 

- Assembly: 2,5 man-hour. 

- Test: 3,0 man-hour. 

NOTE: This estimate is for direct labor only, performed by experienced 

personnel, and does not include the time to plan, prepare or inspect the 

work. 

It is assumed that all the tools, parts, and other means are promptly 

available when necessary. 

H. WEIGHT AND BALANCE 

Not affected. 

I. SOFTWARE ACCOMPLISHMENT SUMMARY 

Not applicable. 

SERVICE BULLETIN

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 3 of 16 

J. REFERENCES 

C.M.M T.P.190/E007 – “MLG Retraction Actuator” - Component Maintenance 

Manual, ATA Chapter No. 32-31-02. 

AMS 2410 – Plating, Silver Nickel Strike, High Bake 

AMS 2430 – Shot Peening, Automatic 

AMS 2460 – Plating, Chromium 

AMS 2700 – Passivation of Corrosion Resistant Steels 

AMS 2759/9 – Hydrogen Embrittlement Relief (Baking) of Steel Parts 

ASTM E1444 – Standard Practice for Magnetic Particle Testing 

MIL-STD-1501 – Chromium Plating, Low Embrittlement, Electro-Deposition 

MIL-STD-1907 – Inspection, Liquid Penetrant and Magnetic Particle, Soundness 

Requirements for Materials, Parts and Weldments 

NEDE E40-066 – Electrolytic Silver Plating 

 

K. OTHER PUBLICATIONS AFFECTED 

C.M.M T.P.190/E007 – “MLG Retraction Actuator” - Component Maintenance 

Manual, ATA Chapter No. 32-31-02. 

L. INTERCHANGEABILITY/INTERMIXABILITY 

Not applicable. 

SERVICE BULLETIN

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 4 of 16 

2. MATERIAL INFORMATION 

A. MATERIAL – PRICE AND AVAILABILITY

(1) Liebherr Aerospace will provide rotable units to replace the component 

removed from the aircraft, subject to confirmation upon receipt of orders. For 

further information about the exchange schedule, contact Liebherr Aerospace 

at the addresses in paragraph (5). 

(2) The component removed from the aircraft must be sent to one of the LiebherrAerospace facilities. 

(3) The modification kit P/N 190-70980-601 required for the accomplishment of 

this Service Bulletin and rotable units will be supplied FOC. The FOC 

conditions are limited to 12 000 FC. 

(4) The modification kit P/N 190-70980-601 ordered after the period stated above 

will be available at a price of US$ 20,331.36 (economical conditions 2010). 

(5) Send purchase orders to one of the Liebherr-Aerospace facilities that follow: 

(a) Europe, the Middle East and Africa 

 Customer Service 

 Liebherr-Aerospace Lindenberg GmbH 

 Pfaenderstrasse 50-52 

 D-88161 Lindenberg - Germany 

 Phone: +49 (0)8381 46-4868 

 Fax: +49 (0)8381 46-4103 

 Mail: spares.lli@liebherr.com 

(b) North America and South America 

Customer Service 

Liebherr-Aerospace Saline 

1465 Woodland Drive Saline 

Michigan 48176 - 1259 USA 

Phone: +1 734 944 6378 

Fax: +1 734 429 5357 

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REVISION No.: Initial Issue Page 5 of 16 

(c) Oceania and Asia 

Customer Service 

Liebherr-Aerospace Singapore 

8 Pandan Avenue 

Singapore 609384 Singapore 

Phone: +65 6424 7211 

Fax: +65 6265 2657 

(d) China 

Customer Service 

Liebherr-Aerospace Shanghai 

88 Keyuan Road Pudong 

Zhang Jiang Hi-Tech Park 

201203 Shanghai P.R. China 

Phone: +86 21 5027 6092 

Fax: +86 21 5027 6116 

B. INDUSTRY SUPPORT INFORMATION

Not applicable. 

C. MATERIAL NECESSARY FOR EACH COMPONENT

(1) To modify each MLG Retraction Actuator P/N 190-70980-403 in accordance 

with this Service Bulletin, the modification Kit P/N 190-70980-601 is required. 

(2) Each modification kit P/N 190-70980-601 contains the following items: 

MODIFICATION PARTS 

Table 1 

NEW PN DESCRIPTION OLD PN QTY DISP

190-70959-003 Piston Nut 190-70959-001 1 3 

190-70958-003 Piston 190-70958-001 1 3 

190-70952-901 Bearing 190-70973-901 1 3 

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 6 of 16 

NEW PN DESCRIPTION OLD PN QTY DISP

190-70966-003 Gland Cap 190-70966-001 1 3 

190-70968-405 Bearing Cap Assy 190-70968-401 1 3 

190-70956-405 

190-70956-411 Rod Assy 

190-70956-407 

1 3 

MS24665-366 Cotter pin MS24665-366 1 7 

MS9581-09 Locking Washer MS9581-09 3 7 

5484-01300-954-043 Wedgpak Face Seal 5484-01300-954-043 1 7 

5484-01500-954-043 Wedgpak Face Seal 5484-01500-954-043 1 7 

S38000-0012H-19 Wedgpak Face Seal S38000-0012H-19 2 7 

5460S22200J043 Scraper Ring 5460S22200J043 1 7 

293-22200-954-0420 ACT Ring 292-22200-954-0420 1 7 

296-34400-954-0420 ACT Ring 296-34400-954-0420 1 7 

M8791/1-128 Packing Retainer M8791/1-128 2 7 

MS27595-242 Packing Retainer MS27595-242 1 7 

NAS1611-128A Preformed Packing NAS1611-128A 1 7 

NAS1611-242A Preformed Packing NAS1611-242A 1 7 

PNE104003-017 Nameplate PNE104003-017 1 7 

DISPOSITION: 3 = Replace part bearing OLD P/N with part bearing NEW P/N. 

7 = Replace with part bearing SAME P/N. 

 

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 7 of 16 

(3) To accomplish this Service Bulletin it is necessary to have the following 

consumable and expendable materials: 

CONSUMABLE AND EXPENDABLE MATERIALS 

Table 2 

DESIGNATION SPECIFICATION QTY SUPPLIER

Adhesive Loctite 328A and 

328B or Loctite 327A or 

327B 

- A.R. Commercially available 

Clear Polyurethane Varnish 

683-3-2/X-310A - A.R. Commercially available 

Corrosion Inhibitive 

Compound Mastinox 6856K - A.R. Commercially available 

Light Consistency Grease 

DC 33 A-A-59173 A.R. Commercially available 

Lint-Free Cloth - A.R. Commercially available 

Lock Wire MS20995C32 A.R. Commercially available 

Methyl Ethyl Ketone (MEK) ASTM D740 A.R. Commercially available 

Nylon Varnish Nycote 7-11 - 

Dark Blue MEP 10-057 A.R. Commercially available 

Sealant PR 1826 B2 A LO AMS 3277, Class 

B2, Type I A.R. Commercially available 

A.R. = As Required 

NOTE: Equivalent substitutes can be used. 

(4) The consumable and expendable materials presented in the tasks referred to 

this Service Bulletin, necessary for its accomplishment, should be procured 

from the operator's inventories, from a local supplier or ordered as spare. 

(5) The consumable and expendable materials necessary for the accomplishment 

of this Service Bulletin should be procured from the operator’s inventories, 

from a local supplier or ordered as spare. 

SERVICE BULLETIN

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DATE: 10/Feb/2011

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 8 of 16 

D. MATERIAL NECESSARY FOR EACH SPARE

Refer to paragraph 2.C. 

E. RE-IDENTIFIED PARTS

The MLG Retraction Actuator and its components must be re-identified as 

follows: 

RE-IDENTIFICATION OF THE PARTS 

Table 3 

NEW P/N DESCRIPTION OLD P/N

190-70980-405 MLG Retraction Actuator 190-70980-403 

190-70953-401 

190-70953-405 Cylinder Assy 190-70953-403 

190-70954-001 

190-70954-005 Cylinder 190-70954-003 

NOTE: The methods of re-identification of the parts are described on item 3 

.ACCOMPLISHMENT INSTRUCTIONS. 

F. TOOLING – PRICE AND AVAILABILITY

Not applicable. 

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REVISION No.: Initial Issue Page 9 of 16 

3. ACCOMPLISHMENT INSTRUCTIONS 

A. Disassemble the MLG Retraction Actuator P/N 190-70980-403 (Ref. C.M.M. – 

“Component Maintenance Manual” - Chapter 32-31-02, Page block 3000 

DISASSEMBLY). Refer to the Figure 01, Sheet 1. 

B. Remove the old bearing P/N 190-70973-901 from the Cylinder Assy P/N 190-

70953-401 or P/N 190-70953-403 (Ref. C.M.M. – “Component Maintenance 

Manual” - Chapter 32-31-02, Page block 6000 REPAIR). Refer to the Figure 01, 

Sheet 2. 

C. Remove fully the painting from the Cylinder P/N 190-70954-001 or P/N 190-70954-

003 (Ref. C.M.M. – “Component Maintenance Manual” - Chapter 32-31-02, Page 

block 6000 REPAIR). 

D. Machine the bearing housing bore of the Cylinder P/N 190-70954-001 to agree 

with the dimension “Before Silver Plating”, shown in the Figure 01, Sheet 2. 

E. Remove the silver plating from the bearing housing bore of the Cylinder P/N 190-

70954-003 with a Nitric Acid Stripping Solution. 

NOTE: 1. Solution: 50 liters of nitric acid stripping per 100 liter of solution (*). 

2. Temperature: Room temperature. 

3. (*) Distilled or Demineralized water. 

F. Do the hydrogen embrittlement relief (AMS 2759/9) of the Cylinder P/N 190-70954-

003. 

NOTE: You must start this treatment in less than 4 hours after the silver plating 

removal is completed. 

G. Make sure that the dimension of the bearing housing bore of the Cylinder P/N 190-

70954-001 or P/N 190-70954-003 agrees with the dimension “Before Silver 

Plating”, shown in the Figure 01, Sheet 2. 

H. Measure the internal rugosity of the Cylinder P/N 190-70954-001 or P/N 190-

70954-003 and make sure it agrees with the value shown in the Figure 01, Sheet 

2. If necessary, rework the rugosity. 

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REVISION No.: Initial Issue Page 10 of 16 

I. Do the stress relief of the Cylinder P/N 190-70954-001 at 190 ± 5 °C (374 ± 9 °F) 

for 4 hours minimum, within 8 hours after machining process is completed. 

NOTE: Do the stress relief (paragraph I) for Cylinder P/N 190-70954-003 only if its 

internal rugosity was reworked (paragraph H). 

J. Do the magnetic particle method inspection ASTM E1444 and MIL-STD-1907 on 

the Cylinder P/N 190-70954-001 or P/N 190-70954-003 for presence of cracks and 

make sure that the parts have no signs of discrepancies. 

K. Do the shot peening (AMS 2430) on the Cylinder P/N 190-70954-001 or P/N 190-

70954-003, on the areas shown in the Figure 01, Sheet 2. 

NOTE: 1. Intensity: 0.006 to 0.010A. 

2. Shot Size: S230. 

3. Coverage: 200%. 

L. Apply hard chromium plating (AMS 2460 Class 2 and MIL-STD-1501) to the 

Cylinder P/N 190-70954-001 or P/N 190-70954-003, on the areas shown in the 

Figure 01, Sheet 2. 

M. Do the hydrogen embrittlement relief (AMS 2759/9) of the Cylinder P/N 190-70954-

001 or P/N 190-70954-003. 

NOTE: You must start this treatment in less than 3 hours after the chromium 

plating process is completed. 

N. Re-identify the Cylinder P/N 190-70954-001 or P/N 190-70954-003, as follows 

(Refer to the Figure 02, Sheet 1): 

1. Do one or two dashes with a pneumatic pencil or a pantograph on the P/N 190-

70954-001 or P/N 190-70954-003 stamped on the Cylinder. 

CAUTION: DO NOT ERASE THE SERIAL NUMBER FROM THE CYLINDER. 

THE ORIGINAL SERIAL NUMBER MUST BE KEPT. 

2. Stamp the new related part number of TABLE 3 - RE-IDENTIFICATION OF THE 

PARTS, on the area shown in the Figure 02, Sheet 1. 

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REVISION No.: Initial Issue Page 11 of 16 

NOTE: The impression shall be rounded with radius greater than 0.2 mm and 

the depth must be the maximum of 0.20 to 0.25 mm. 

O. Passivate fully the re-identified Cylinder P/N 190-70954-005 (AMS 2700, Method 1, 

Type 2). Refer to the Figure 01, Sheet 2. 

P. Apply silver plating (NEDE E40-066 and AMS 2410) on the bearing housing bore 

of the re-identified Cylinder P/N 190-70954-005. Refer to the Figure 01, Sheet 2. 

Q. Do the hydrogen embrittlement relief (AMS 2759/9) of the re-identified Cylinder P/N 

190-70954-005. 

NOTE: You must start this treatment in less than 4 hours after the silver plating 

process is completed. 

R. Install the new bearing P/N 190-70952-901 on the reworked Cylinder (Ref. C.M.M. 

– “Component Maintenance Manual” - Chapter 32-31-02, Page block 6000 

REPAIR). Refer to the Figure 01, Sheet 2. 

S. Restore the painting protection of the reworked Cylinder (Ref. C.M.M. – 

“Component Maintenance Manual” - Chapter 32-31-02, Page block 6000 REPAIR). 

T. Re-identify the reworked Cylinder Assy P/N 190-70953-401 or P/N 190-70953-403 

by ink jet method. Refer to Table 3 - RE-IDENTIFICATION OF THE PARTS for the 

new P/N which must be marked and Figure 02, Sheet 1 for the area where the new 

P/N must be positioned. 

U. Assemble the MLG Retraction Actuator with the new and reworked parts (Ref. 

C.M.M. – “Component Maintenance Manual” - Chapter 32-31-02, Page block 7000 

ASSEMBLY). Refer to the Figure 01, Sheet 1. 

V. Re-identify the new MLG Retraction Actuator P/N 190-70980-405, as follows 

(Refer to the Figure 02, Sheet 2): 

1. Engrave the new MLG Retraction Actuator P/N 190-70980-405 on the new 

nameplate P/N PNE104003-017. 

2. Transfer the serial number and the description from the old nameplate of the 

MLG Retraction Actuator to the new nameplate. 

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 12 of 16 

3. Install the new nameplate P/N PNE104003-017 on the reconfigured MLG 

Retraction Actuator (Ref. C.M.M. – “Component Maintenance Manual” - Chapter 

32-31-02, Page block 6000 REPAIR). 

W. Do the tests on the MLG Retraction Actuator P/N 190-70980-405 (Ref. C.M.M. – 

“Component Maintenance Manual” - Chapter 32-31-02, Page block 1000 TESTS 

AND FAULT ISOLATION). 

X. Record in the applicable document that this Service Bulletin has been satisfactorily 

completed. 

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DATE: 10/Feb/2011

REVISION No.:

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 13 of 16 

FIGURE 01 – MODIFICATION OF MLG RETRACTION ACTUATOR 

(SHEET 01 OF 02) 

SERVICE BULLETIN

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 14 of 16 

FIGURE 01 – MODIFICATION OF MLG RETRACTION ACTUATOR 

(SHEET 02 OF 02) 

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DATE: 10/Feb/2011

REVISION No.:

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 15 of 16 

FIGURE 02 – RE-IDENTIFICATION OF MLG RETRACTION ACTUATOR 

(SHEET 01 OF 02) 

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DATE: 06/SEP/2010 190-70980-32-02 

REVISION No.: Initial Issue Page 16 of 16 

FIGURE 02 – RE-IDENTIFICATION OF MLG RETRACTION ACTUATOR 

(SHEET 02 OF 02) 

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:

SB No.: 190LIN-32-0015

PAGE: 85

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